AH-64A Apache Combat Mission Simulator Technical Manual
The AH-64A Apache Combat Mission Simulator is a fixed-base simulation system designed for training in the use of AH-64A Apache helicopters. It provides normal and emergency procedural mission training and weapons delivery, as well as navigation instrument flight operation, day, dusk, and night visual flight operations, and ordnance delivery systems of the attack helicopter.
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TECHNICAL MANUAL
TM 55-6930-214-10
OPERATOR'S MANUAL
FOR
AH-64A (APACHE) COMBAT MISSION SIMULATOR
“Approved for public release; distribution is unlimited.”
HEADQUARTERS, DEPARTMENT OF THE ARMY
15 MARCH 1988
CHANGE
NO. 2
TM 55-6930-214-10
C 2
HEADQUARTERS
DEPARTMENT OF THE ARMY
WASHINGTON, D.C., 30 April 1992
Operator’s Manual f o r
AH-64A (Apache) Combat Mission Simulator
T M 5 5 - 6 9 3 0 - 2 1 4 - 1 0 , 1 5 M a r c h 1 9 8 8 , i s c h a n g e d a s f o l l o w s :
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R e m o v e a n d i n s e r t p a g e s a s i n d i c a t e d b e l o w . N e w o r c h a n g e d t e x t m a t e r i a l i s i n d i c a t e d b y a v e r t i c a l b a r i n t h e m a r g i n . A n i l l u s t r a t i o n c h a n g e i s i n d i c a t e d b y a m i n i a t u r e p o i n t i n g h a n d .
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C 2
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R e t a i n t h i s s h e e t i n f r o n t o f m a n u a l f o r r e f e r e n c e p u r p o s e s .
By Order of the Secretary of the Army:
Official:
GORDON R. SULLIVAN
General, United States Army
Chief of Staff
MILTON H. HAMILTON
Administrative Assistant to the
Secretary of the Army
01735
DISTRIBUTION:
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CHANGE
No. 1
TM 55-6930-214-10
C 1
HEADQUARTERS
DEPARTMENT OF THE ARMY
W A S H I N G T O N
, D.C., 17 January 1989
Operator's Manual f o r
AH-64A (Apache) Combat Mission Simulator
TM 55-6930-214-10, 15 March 1988, is changed as follows:
1.
R e m o v e a n d i n s e r t p a g e s a s i n d i c a t e d b e l o w .
New or changed test material i s i n d i c a t e d b y a v e r t i c a l b a r i n t h e m a r g i n .
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R e t a i n t h e s e s h e e t s i n f r o n t o f m a n u a l f o r r e f e r e n c e p u r p o s e s .
TM 55-6930-214-10
C 1
By Order of the Secretary of the Army:
CARL E. VUONO,
General, United States Army
Chief of Staff
Official:
WILLIAM J. MEEHAN II
Brigadier General, United States Army
The Adjutant General
DISTRIBUTION:
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R e q u i r e m e n t s f o r A H - 6 4 A H e l i c o p t e r , A t t a c k , ( A p a c h e ) .
TM 55-6930-214-10
WARNING
HIGH VOLTAGE i s u s e d i n t h e o p e r a t i o n o f t h i s e q u i p m e n t .
DEATH ON CONTACT o r s e v e r e i n j u r y m a y r e s u l t i f p e r s o n n e l f a i l t o o b s e r v e s a f e t y p r e c a u t i o n s .
L e a r n t h e a r e a s c o n t a i n i n g h i g h v o l t a g e i n e a c h p i e c e o f e q u i p m e n t .
U n d e r n o c i r c u m s t a n c e s s h o u l d o p e r a t i o n o f t h i s d e v i c e b e u n d e r t a k e n when cabinets and/or protective covers are removed or open.
WARNING
M o t i o n s y s t e m o p e r a t i o n r e q u i r e s t h a t
SEAT BELTS BE USED AT ALL TIMES.
In the case of runaway motion, immediately activate EMERGENCY STOP switch.
DEATH o r s e v e r e i n j u r y m a y r e s u l t i f p e r s o n n e l f a i l t o o b s e r v e s a f e t y p r e c a u t i o n s .
WARNING
EMERGENCY STOP
C o n t r o l s a r e l o c a t e d a t e a c h t r a i n e e s t a t i o n c o n t r o l p a n e l a n d a t e a c h i n s t r u c t o r / o p e r a t o r c o n s o l e .
D e p r e s s i n g t h i s s w i t c h s h u t s d o w n t h e e n t i r e s i m u l a t o r c o m p l e x .
DEATH o r s e v e r e i n j u r y m a y r e s u l t i f p e r s o n n e l f a i l t o o b s e r v e s a f e t y p r e c a u t i o n s .
a
TM 55-6930-214-10
WARNING
S e n s o r s t h a t d e t e c t h e a t , l a c k o f a i r f l o w , a n d u n s a f e m e c h a n i c a l conditions are provided.
UNDER NO CIRCUMSTANCES SHOULD THE MISSION
SIMULATOR BE OPERATED WITH A SAFETY INTERLOCK BYPASSED.
DEATH or severe injury may result if personnel fail to observe safety prec a u t i o n s .
WARNING
FIRE
Should fire develop, activate EMERGENCY STOP a n d e x i t c o c k p i t . DO NOT USE FIRE EXTINGUISHER IN CONFINED COCKPIT.
DEATH or severe injury may result if personnel fail to observe safety p r e c a u t i o n s .
WARNING
BOARDING RAMP
M a y f a i l t o d e p l o y d u r i n g a p o w e r f a i l u r e .
C a u t i o n s h o u l d b e e x e r c i s e d w h e n e x i t i n g s i m u l a t o r .
DEATH o r s e v e r e i n j u r y m a y r e s u l t i f p e r s o n n e l f a i l t o o b s e r v e s a f e t y p r e c a u t i o n s .
WARNING
R e l e a s i n g t r a i n e r f r o m f r e e z e c o n d i t i o n with incorrect rotor rpm may cause motion surges.
D E A T H o r s e v e r e i n j u r y m a y r e s u l t i f p e r s o n n e l f a i l t o o b s e r v e s a f e t y p r e c a u t i o n s .
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FLIGHT CONTROLS m a y m o v e a b r u p t l y u p o n i n i t i a l t u r n o n o r d e m o n s t r a t i o n e x e r c i s e s .
K e e p c l e a r o f c o c k p i t c o n t r o l s u n t i l n e u t r a l p o s i t i o n i s r e a c h e d .
D E A T H or severe injury may result if personnel fail to observe safety precautions.
WARNING
FIRE EXTINGUISHER
E x p o s u r e t o h i g h c o n c e n t r a t i o n s o f m o n o b r o m o t r i f l u o r o m e t h a n e
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B r ) e x t i n g u i s h i n g a g e n t o r d e c o m p o s i t i o n p r o d u c t s s h o u l d b e a v o i d e d .
T h e l i q u i d s h o u l d n o t b e a l l o w e d t o c o m e i n t o c o n t a c t w i t h t h e s k i n b e c a u s e i t c a u s e s f r o s t b i t e o r l o w - t e m p e r a t u r e b u r n s .
WARNING
FIRE EXTINGUISHING SYSTEM
(HALON)
H a l o n g a s i s u s e d a s a f i r e e x t i n g u i s h i n g a g e n t t h r o u g h o u t t h e s i m u l a t o r c o m p l e x .
H a l o n g a s d i s p l a c e s o x y g e n i n c o n f i n e d s p a c e s . A s p h y x i a t i o n c a n r e s u l t i f c o c k p i t i s n o t e v a c u a t e d i m m e d i a t e l y u p o n H a l o n d i s c h a r g e .
DEATH or severe Injury may result if personnel fail to observe safety precautions.
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B Change 1
RECORD OF CHANGES
CHANGE
NO.
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DATE
17 JANUARY 1989
TITLE OR BRIEF DESCRIPTION
INCORPORATION OF CUSTOMER
COMMENTS TO EXISTING MANUAL
TM 55-6930-214-10
ENTERED
BY
SINGER - LINK
Change 1 C/(D blank)
TM 55-6930-214-10
PREFACE
The M-64 Combat Mission Simulator (CMS), designed and manufactured by CAR-Link
Corp. , L i n k P l i g h t S i m u l a t i o n D i v i s i o n , B i n g h a m t o n , N e w Y o r k , h a s b e e n s p e c i f i c a l l y d e v e l o p e d f o r f l i g h t s i m u l a t i o n r e l a t i v e t o h i g h - p e r f o r m a n c e a i r c r a f t . T h i s m a n u a l c o n t a i n s o p e r a t i n g I n s t r u c t i o n s f o r b o t h t h e p i l o t a n d c o p i l o t / g u n n e r s t a t i o n s o f the M-64 CMS.
N o t a t i o n s u s e d i n t h i s m a n u a l a r e a s f o l l o w s :
WARNING
O p e r a t i n g a n d m a i n t e n a n c e p r o c e d u r e s , p r a c t i c e s , e t c . , t h a t m u s t b e s t r i c t l y o b s e r v e d t o p r e v e n t i n j u r y t o p e r s o n n e l o r l o s s o f l i f e .
CAUTION
O p e r a t i n g a n d m a i n t e n a n c e p r o c e d u r e s , e t c . , t h a t m u s t b e o b s e r v e d t o p r e v e n t e q u i p m e n t d a m a g e .
NOTE
O p e r a t i n g a n d m a i n t e n a n c e p r o c e d u r e s , c o n d i t i o n , o r I n f o r m a t i o n , e t c . , r e q u i r i n g p a r t i c u l a r e m p h a s i s .
EFFECTIVITY CODING. T h i s m a n u a l r e f l e c t s a l l d i f f e r e n c e s t h a t e x i s t b e t w e e n s i m u l a t o r s ( f o r h a r d w a r e a n d / o r o p e r a t i o n ) w i t h e f f e c t i v i t y c o d e s ; o t h e r w i s e , t h e d a t a i s a p p l i c a b l e t o a l l s i m u l a t o r s . T h e f o l l o w i n g c o d e s d e n o t i n g d i f f e r e n c e s a r e u s e d w h e n t h e d a t a p e r t a i n s t o a s p e c i f i c s i m u l a t o r . T h e s i m u l a t o r c o d e s a r e d e f i n e d a s f o l l o w s :
( 1 ) = S i m u l a t o r N o . 2 1 3 7 0 2 0 ( p r o t o t y p e )
( 2 ) = S i m u l a t o r N o . 2 1 3 7 0 2 1
SECURITY REQUIREMENTS. T h e A H - 6 4 C M S s i m u l a t e s t h e A p a c h e h e l i c o p t e r a n d i t s r e l a t e d s y s t e m s t o t h e s a m e l e v e l o f p e r f o r m a n c e a s f o u n d i n t h e o p e r a t i o n a l s y s t e m s . T h e C M S , t h e r e f o r e , m u s t b e p r o t e c t e d t o t h e s a m e l e v e l a s t h e a i r c r a f t o p e r a t i o n a l s y s t e m s w h e r e t h e y a r e c l a s s i f i e d .
I n a d d i t i o n , t h e C M S c a n b e u s e d t o d e m o n s t r a t e o r t e a c h t a c t i c a l t h r e a t e n g a g e m e n t s c e n a r i o s . D e m o n s t r a t i o n o f t h e s e s c e n a r i o s i n t h e C M S i s c l a s s i f i e d t o t h e s a m e l e v e l a s t h e o p e r a t i o n a l m i s s i o n d e s c r i p t i o n . T h e S y s t e m S e c u r i t y C l a s s i f i c a t i o n
G u i d e s ( S C G ) l i s t e d b e l o w a p p l y , t o t h e l a t e s t r e v i s i o n , i n c l u d i n g d e c l a s s i f i c a t i o n p r o v i s i o n s :
Advanced Attack Helicopter (AAH) SCG dated 1 October 1984, with Revision No. 1, d a t e d 1 O c t o b e r 1 9 8 5
T a r g e t A c q u i s i t i o n D e s i g n a t i o n S i g h t ( T A D S ) a n d P i l o t N i g h t V i s i o n S e n s o r
(PNVS) SCG dated 1 October 1984 and Revision 2 dated 18 January 1985
H e l l f i r e L a s e r A i r D e f e n s e S u p p r e s s i o n a n d F i r e a n d T a r g e t G u i d e d M i s s i l e
System SCG, dated 12 August 1985
C h a n g e 2 i
TM 55-6930-214-10
Active Infrared Jammers AN/ALQ-147 and AN/ALQ-144 SCG. dated 1 December 1980
Radar Jammer AN/ALQ-136 SCG. dated 1 December 1980
D i s p e n s e r , G e n e r a l P u r p o s e , Aircraft Ml30 SCG, dated 1 December 1980
Radar Warning Receiver AN/APR-39 SCG, dated 1 December 1980
VRS UHF-AM COM Radio Set with Have Quick AN/ARC-164(v)
E a c h C M S i n s t a l l a t i o n m u s t b e d e s i g n e d t o p h y s i c a l l y p r o t e c t t h e d e v i c e b y l i m i t i n g a c c e s s t o u n a u t h o r i z e d p e r s o n n e l .
W h e n t h e C M S i s n o t i n o p e r a t i o n , w i t h t h e s o f t w a r e ( d i s k p a c k s , m a g n e t i c t a p e s ) r e m o v e d , i t i s u n c l a s s i f i e d . W h e n t h e s o f t w a r e i s l o a d e d I n t o t h e C M S a n d t h e d e v i c e i s o p e r a t i o n a l , I t i s c l a s s i f i e d
SECRET.
C M S d i s k p a c k s a n d m a g n e t i c t a p e s a r e c l a s s i f i e d S E C R E T i n a c c o r d a n c e w i t h t h e h i g h e s t l e v e l o f i n f o r m a t i o n d e r i v e d f r o m t h e a i r c r a f t s y s t e m s d a t a c o n t a i n e d o n t h e d i s k .
P u b l i c a t i o n s .
P u b l i c a t i o n s , r e p o r t s , d r a w i n g s . s c h e m a t i c s , p h o t o g r a p h s , m o c k u p s , t r a i n i n g a i d s , t e s t d a t a , e t c . . a r e a s s i g n e d a s e c u r i t y c l a s s i f i c a t i o n c o m m e n s u r a t e w i t h t h a t o f t h e p e r f o r m a n c e c h a r a c t e r i s t i c o f t h e c l a s s i f i e d e l e m e n t s o f t h e s y s t e m a n d a r e d e c l a s s i f i e d I n a c c o r d a n c e w i t h t h e s a m e d o c u m e n t .
There are two c l a s s i f i e d a n n e x e s ( T h r e a t a n d O w n s h i p W e a p o n S c o r i n g ) t o t h e T r a i n e r T e s t
P r o c e d u r e s a n d R e s u l t s R e p o r t , V o l u m e I , B o o k 5 .
A l l o t h e r t e s t d o c u m e n t a t i o n i s u n c l a s s i f i e d .
Hardware.
A l l C M S h a r d w a r e i s u n c l a s s i f i e d .
I n o r d e r t o r e d u c e e l e c t r o m a g n e t i c r a d i a t i o n w h i c h m a y c o n t a i n c l a s s i f i e d i n f o r m a t i o n , s e v e r a l h a r d w a r e f e a t u r e s h a v e b e e n i n c o r p o r a t e d i n t o t h e C M S .
T h e r e f e a t u r e s i n c l u d e c a b i n e t s , c o n n e c t o r s . a n d c a b l e s h i e l d i n g .
O p e r a t i o n , m a i n t e n a n c e a n d m o d i f i c a t i o n o f t h e d e v i c e m u s t p r e s e r v e t h e s e f e a t u r e s .
D u r i n g m a i n t e n a n c e p r o c e s s e s , c o n f i g u r a t i o n o f t h e e q u i p m e n t m u s t b e m a i n t a i n e d I n a c c o r d a n c e w i t h t h e a s s e m b l y d r a w i n g s , w i r i n g d i a g r a m s . a n d c a b l e d i a g r a m s t o a v o i d c o m p r o m i s i n g e l e c t r o m a g n e t i c r a d i a t i o n s e c u r i t y .
I n a d d i t i o n t o o p e r a t i o n w i t h c a b i n e t d o o r s c l o s e d ( c o c k p i t a n d s i g n a l c o n v e r s i o n e q u i p m e n t o n l y ) s o m e c a b l e s m a y p o s s i b l y r a d i a t e i n f o r m a t i o n ’ i f s h i e l d i n g i s c o m p r o m i s e d .
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All data on this page deleted.
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TABLE OF CONTENTS
C h a p t e r / p a r a
S e c t i o n I
S e c t i o n I I
S e c t i o n I I I
S e c t i o n I V
S e c t i o n V
PREFACE
E f f e c t i v i t y C o d i n g
S e c u r i t y R e q u i r e m e n t s
SAFETY SUMMARY
INTRODUCTION
SCOPE
GENERAL
TECHNICAL MANUAL CHANGES
FORMS AND RECORDS
REPORTING OF ERRORS
ABBREVIATIONS
SYSTEM DESCRIPTION AND OPERATION
GENERAL
OPERATIONAL SYSTEM
SIMULATOR COMPARTMENTS
INSTRUCTOR/OPERATOR STATIONS
MOTION SYSTEM
VISUAL SYSTEM
COMPUTER SYSTEM
INSTRUCTOR/OPERATOR STATION DESCRIPTION
GENERAL DESCRIPTION
IOS CONTROL PANELS
TRAINEE CONTROL PANELS
INSTRUCTOR SEATS
OBSERVER SEATS
IOS AREA LIGHTING
INSTRUCTOR INTERCOMMUNICATIONS SYSTEM
TIME REFERENCES
MODES OF OPERATION
TRAINING
AUTOFLY
DEMONSTRATION
TRAINING CAPABILITIES
GENERAL
TRAINING OBJECTIVES
SIMULATION SYSTEM CAPABILITIES
VISUAL SYSTEM CAPABILITIES
TRAINING TASKS
SYSTEM SIMULATED
GENERAL
ACCESSORY SYSTEMS
SOUND SIMULATION
MOTION SIMULATION
VIBRATION SIMULATION
COCKPIT INSTRUMENTATION SIMULATION
i v
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l - l l - l l - l l - l l - l l - l l - l
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C h a p t e r / p a r a
2-30 RADIO COMMUNICATION AND INTERCOMMUNICATIONS SYSTEM
(ICS) SIMULATION
AVIONICS
3-4 RADAR AND TRANSPONDER EQUIPMENT
OPERATING LIMITS AND RESTRICTIONS
5-8 IOS CRT-CONTROLLABLE PARAMETERS
S e c t i o n I
CONTROLS AND INDICATORS
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C h a p t e r / p a r a
S e c t i o n I I
LIGHTING CONTROL
HEADSET VOLUME CONTROL
STORE/RESET CURRENT CONDITIONS
MALFUNCTION CONTROLS
CRASH/HIT OVERRIDE
INSTRUCTOR VISUAL CONTROL
MANUAL FREEZE
ELAPSED-TIME CLOCK (TIMER)
REPLAY CONTROL
INSTRUCTORS MONITORS
TRAINER CONTROL PANEL
OBSERVER COMMUNICATIONS PANEL
IOS SCREEN DISPLAY
CRT PAGE DISPLAYS DESCRIPTIONS
MINI-INDEXES
INITIAL CONDITIONS
CURRENT CONDITIONS
PARAMETERS FREEZE
FLIGHT MONITOR
VISUAL MODE HELP PAGE
NAVIGATION/COMMUNICATIONS
UHF-AM HAVE QUICK RADIO
BATTLE POSITION MAPS
CROSS-COUNTRY
TACTICAL INSTRUMENTATION AREA DISPLAY
MAP SYMBOLOGY
GCA PLOTS
ALTITUDE/AIRSPEED PLOTS
CONTROL PANEL CRT DISPLAYS
TARGET ENGAGEMENT EXERCISE
TARGET STATUS
TARGET TYPES LIST
TARGET SITES LIST
TARGET SITES OVERVIEW
BATTLE POSITION TARGET SITES
MANUAL TARGET CONTROL
VISIONICS POINTING/ REMOTE DESIGNATOR
TARGET EVALUATOR
WEAPONS LOADING/ROCKET CONFIGURATION
FARP CONTROL
ENGAGEMENT PERFORMANCE
THREAT SCORING
AUTOMATIC MALFUNCTION INSERTION
MANUAL MALFUNCTION
DEMONSTRATIONS
AUTOFLY
RECORD/PLAYBACK
MISSING MAN
OWNSHIP WEAPONS SCORING
REMOTE DESIGNATION
THREAT SCORING GRAPHICS
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C h a p t e r / p a r a
SECTION III AUTOMATED PROGRAM PREPARATION
7-58 INSTRUCTIONAL FEATURE PREPARATION
7-60 DEMONSTRATION PREPARATION
7-62 TARGET ENGAGEMENT EXERCISE PREPARATION
S e c t i o n I V SIMULATED MALFUNCTIONS
8 EMERGENCY PROCEDURES AND SAFETY
S e c t i o n I EMERGENCY PROCEDURES
S e c t i o n I I SAFETY
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55-6930-214-10
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F i g u r e
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LIST OF ILLUSTRATIONS
T i t l e
Typical AH-64 CMS and Computer Rooms System Complex
( 3 s h e e t s )
I n s t r u c t o r / O p e r a t o r S t a t i o n
P i l o t / C P G I O S C o n s o l e C o n t r o l P a n e l s ( 4 s h e e t s )
P i l o t / C P G I O S F o r w a r d C o n t r o l P a n e l s
( D e l e t e d )
T r a i n e e S t a t i o n
T r a i n e e C o n t r o l P a n e l
P i l o t / C P G I O S C o n s o l e C o n t r o l P a n e l s ( 4 s h e e t s )
P i l o t / C P G T r a i n e e C o n t r o l P a n e l
D a t a E n t r y K e y b o a r d C o n t r o l P a n e l
P i l o t / C P G I O S F o r w a r d C o n t r o l P a n e l s
Observer Communications Panel
IOS CRT Screen Display
Typical CRT Page Status Areas
Mini-Indexes
I n i t i a l C o n d i t i o n s / C u r r e n t C o n d i t i o n s I n d e x P a g e D i s p l a y
( 3 s h e e t s )
I n i t i a l C o n d i t i o n s P a g e D i s p l a y ( 2 s h e e t s )
C o c k p i t D i s c r e p a n c i e s P a g e D i s p l a y
C u r r e n t C o n d i t i o n s P a g e D i s p l a y ( 2 s h e e t s )
Parameter Freeze Page Display
F l i g h t M o n i t o r P a g e D i s p l a y
Visual Mode Help Page Display
Navigation and Communication Index Page Display
N a v i g a t i o n a n d C o m m u n i c a t i o n s F a c i l i t i e s P a g e 6 0 1 D i s p l a y
N a v i g a t i o n a n d C o m m u n i c a t i o n s F a c i l i t i e s P a g e 6 0 2 D i s p l a y
UHF-AM Have Quick Radio Page
B a t t l e P o s i t i o n R a p P a g e D i s p l a y
Cross-Country Map Page Display
Cross-Country Rap (Zoom On) Page Display
T a c t i c a l I n s t r u m e n t G a m i n g A r e a P a g e D i s p l a y
T a c t i c a l I n s t r u m e n t G a m i n g A r e a ( Z o o m O n ) P a g e D i s p l a y
Map Symbology Page Display
T y p i c a l M a p S y m b o l s ( 2 s h e e t s )
GCA 10-Mile Scale Page Display
GCA 2-Mile Scale Page Display
6 - K M A l t i t u d e / A i r s p e e d P l o t s P a g e D i s p l a y l - K M A l t i t u d e / A i r s p e e d P l o t s P a g e D i s p l a y
C P G M i s s i l e C o n t r o l P a n e l P a g e D i s p l a y
C P G F i r e C o n t r o l P a n e l P a g e D i s p l a y
P i l o t M i s s i l e C o n t r o l P a n e l P a g e D i s p l a y
P i l o t F i r e C o n t r o l P a n e l P a g e D i s p l a y
CPG ORT Page Display
CPG Cyclic Page Display
P i l o t C y c l i c P a g e D i s p l a y
D o p p l e r C o m p u t e r D i s p l a y U n i t P a g e D i s p l a y
T a r g e t E n g a g e m e n t E x e r c i s e P a g e D i s p l a y
T a r g e t S t a t u s P a g e D i s p l a y
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T i t l e
T a r g e t T y p e s L i s t P a g e D i s p l a y
Visual Gaming Weapons Symbols (8 sheets)
T a r g e t S i t e s L i s t P a g e D i s p l a y ( 4 s h e e t s )
Target Sites Overview Page Display
Target Sites Overview (Zoom On) Page Display
T y p i c a l T a r g e t S y m b o l s ( 2 s h e e t s )
B a t t l e P o s i t i o n T a r g e t S i t e M a p P a g e D i s p l a y
M a n u a l T a r g e t C o n t r o l P a g e D i s p l a y
V i s i o n i c s P o i n t i n g / R e m o t e D e s i g n a t o r C o n t r o l P a g e D i s p l a y
T a r g e t E v a l u a t i o n P a g e D i s p l a y
Weapons Loading Page Display
R o c k e t C o n f i g u r a t i o n P a g e D i s p l a y
Forward Arming and Refueling Point (FARP) Control Page
D i s p l a y
O w n s h i p E n g a g e m e n t P e r f o r m a n c e P a g e D i s p l a y ( 2 s h e e t s )
T h r e a t S c o r i n g P a g e D i s p l a y
A u t o m a t i c M a l f u n c t i o n I n s e r t i o n P a g e D i s p l a y
M a l f u n c t i o n I n d e x P a g e D i s p l a y ( 2 s h e e t s )
T y p i c a l M a l f u n c t i o n s P a g e D i s p l a y
Demos/Autofly/Record Playback Index Page 400A Display
Demos/Autofly/Record Playback Index Page 400B Display
D e m o n s t r a t i o n S e t N o . P a g e D i s p l a y
Demos/Autofly/Record Playback Index Page 400C Display
Demos/Autofly/Record Playback Index Page 400D Display
Autofly Set Page Display
Record/Playback Command Page Display
Missing Man/Independent Mode Master Page Display
Missing Man/Independent Mode Slave Page Display
Ownship Weapons Scoring Page
Remote Designation Page
T h r e a t S c o r i n g G r a p h i c s P a g e
A u t o m a t i c M a l f u n c t i o n I n s e r t i o n P r e p P a g e D i s p l a y
A M I P r e p D a t a W o r k s h e e t ( 3 s h e e t s )
D e m o n s t r a t i o n P r e p a r a t i o n P a g e D i s p l a y
A u t o f l y P r e p a r a t i o n P a g e D i s p l a y
T a r g e t E n g a g e m e n t E x e r c i s e P r e p P a g e D i s p l a y
T E E P r e p D a t a W o r k s h e e t ( 5 s h e e t s )
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T a b l e
TM 55-6930-214-10
LIST OF TABLES
T i t l e
I n t e g r a t e d / I n d e p e n d e n t O p e r a t i o n F e a t u r e s
Avionics Systems
V i s u a l D i s p l a y A v a i l a b i l i t y
K e y b o a r d I n t e r p r e t e r M e s s a g e T y p e s
V i s u a l M o n i t o r D i s p l a y n o d e s
General CRT Page Grouping
IDS CRT Status Area Data
R a n g e o f V a l u e s f o r I n i t i a l C o n d i t i o n s L i n e E n t r i e s
R a n g e o f V a l u e s f o r C u r r e n t C o n d i t i o n s L i n e E n t r i e s
T a c t i c s C u r r e n t C o n d i t i o n s
M i s c e l l a n e o u s C u r r e n t C o n d i t i o n s
T a r g e t S t a t u s I n f o r m a t i o n
I n s t r u c t i o n s f o r U s e o f M a n u a l T a r g e t C o n t r o l C R T P a g e
Engagement Performance Data
Threat Scoring Page Data Display
AMI Prep Data Entry Procedure
T E E P r e p D a t a E n t r y P r o c e d u r e
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SAFETY SUMMARY
T h e f o l l o w i n g a r e g e n e r a l s a f e t y p r e c a u t i o n s t h a t a r e n o t r e l a t e d t o a n y s p e c i f i c p r o c e d u r e s a n d t h e r e f o r e d o n o t a p p e a r e l s e w h e r e i n t h i s p u b l i c a t i o n . T h e s e a r e r e c o m m e n d e d p r e c a u t i o n s t h a t p e r s o n n e l m u s t u n d e r s t a n d a n d a p p l y d u r i n g m a n y p h a s e s o f o p e r a t i o n a n d m a i n t e n a n c e .
KEEP AWAY FROM LIVE CIRCUITS
O p e r a t i n g p e r s o n n e l m u s t a t a l l t i m e s o b s e r v e a l l s a f e t y r e g u l a t i o n s . D o n o t r e p l a c e c o m p o n e n t s o r m a k e a d j u s t m e n t s i n s i d e t h e e q u i p m e n t w i t h t h e h i g h - v o l t a g e s u p p l y t u r n e d o n .
U n d e r c e r t a i n c o n d i t i o n s , d a n g e r o u s p o t e n t i a l s m a y e x i s t w h e n t h e p o w e r c o n t r o l i s i n t h e o f f p o s i t i o n , d u e t o c h a r g e s r e t a i n e d b y c a p a c i t o r s .
T o a v o i d c a s u a l t i e s , a l w a y s r e m o v e p o w e r a n d d i s c h a r g e a n d g r o u n d a c i r c u i t b e f o r e t o u c h i n g i t .
DO NOT SERVICE OR ADJUST ALONE
U n d e r n o c i r c u m s t a n c e s s h o u l d a n y p e r s o n r e a c h i n t o o r e n t e r t h e e n c l o s u r e f o r t h e p u r p o s e o f s e r v i c i n g o r a d j u s t i n g t h e e q u i p m e n t e x c e p t i n t h e p r e s e n c e o f s o m e o n e w h o i s c a p a b l e o f r e n d e r i n g a i d .
RESUSCITATION
P e r s o n n e l w o r k i n g w i t h o r n e a r h i g h v o l t a g e s s h o u l d b e f a m i l i a r w i t h m o d e r n m e t h o d s o f r e s u s c i t a t i o n . S u c h i n f o r m a t i o n m a y b e o b t a i n e d f r o m t h e B u r e a u o f M e d i c i n e a n d
Surgery .
T h e f o l l o w i n g w a r n i n g s a p p e a r i n t h e t e x t i n t h i s m a n u a l a n d a r e r e p e a t e d h e r e f o r emphasis :
WARNING
F l i g h t c o n t r o l s m a y m o v e a b r u p t l y u p o n s y s t e m t u r n - o n , i n i t i a l c o n d i t i o n s i n s e r t i o n , d e m o n s t r a t i o n m a n e u v e r s o r c o n d i t i o n s s t o r e / r e s e t .
K e e p c l e a r o f c o n t r o l s u n t i l n e u t r a l p o s i t i o n i s reached.
WARNING
Care should be exercised when exiting the simulator during power f a i l u r e .
The boarding ramp may fail to deploy.
WARNING
P r i o r t o t h e a c t i v a t i o n o f m o t i o n , a l l o c c u p a n t s o f t h e s i m u l a t e d c o c k p i t a n d I O S ( l i m i t e d t o t h r e e p e r s o n s p e r f l i g h t c o m p a r t m e n t ) a r e r e q u i r e d t o f a s t e n s e a t b e l t s .
Change 2 xi
TM 55-6930-214-10
WARNING
Do not discharge a CG
3
BR fire extinguisher in the confined cockpit .
CAUTION
Due to abnormal shutdown possible hardware damage may occur.
x i i Change 2
T M 5 5 - 6 9 3 0 - 2 1 4 - 1 0
CHAPTER 1
INTRODUCTION
1 - 1 .
SCOPE.
T h i s o p e r a t o r ' s m a n u a l c o n t a i n s c o m p l e t e o p e r a t i n g i n s t r u c t i o n s a n d p r o c e d u r e s f o r t h e c o m b a t m i s s i o n s i m u l a t o r ( C M S ) s y s t e m f o r t h e A R - 6 4
( A p a c h e ) h e l i c o p t e r .
T h i s m a n u a l i s o n l y f o r u s e b y a n i n s t r u c t o r / o p e r a t o r f o r t h e t r a i n i n g o f p i l o t s ( P L T ) a n d / o r c o p i l o t / g u n n e r s ( C P G ) i n t h e t e c h n i q u e s
I n v o l v e d f o r a l l n o r m a l a n d e m e r g e n c y f l i g h t , t a c t i c a l m a n e u v e r s , a n d w e a p o n s d e l i v e r y o f t h e A p a c h e h e l i c o p t e r .
l - 2 .
GENERAL.
T h e C M S c o n s i s t s o f t w o o p e r a t i o n a l f l i g h t s i m u l a t o r c o m p a r t m e n t s ( P L T a n d C P G ) , e a c h h a v i n g a s i x - d e g r e e - o f - f r e e d o m m o t i o n s y s t e m .
E a c h i s e q u i p p e d w i t h a v i s u a l s y s t e m t h a t s i m u l a t e s n a t u r a l h e l i c o p t e r e n v i r o n m e n t s u r r o u n d i n g s .
A c e n t r a l c o m p u t e r s y s t e m c o n t r o l s t h e o p e r a t i o n o f t h e s i m u l a t o r c o m p l e x .
T h e h a r d w a r e a n d s o f t w a r e t h a t c o m p r i s e t h i s c o m p l e x w e r e d e s i g n e d a n d b u i l t b y C A E - L i n k C o r p . , B i n g h a m t o n , N e w Y o r k .
a . S i m u l a t i o n .
T h e C M S p r o v i d e s n o r m a l a n d e m e r g e n c y p r o c e d u r a l m i s s i o n t r a i n i n g a n d w e a p o n s d e l i v e r y .
A d d i t i o n a l c a p a b i l i t i e s i n c l u d e n a v i g a t i o n
I n s t r u m e n t f l i g h t o p e r a t i o n , d a y , d u s k , a n d n i g h t v i s u a l f l i g h t o p e r a t i o n s , a n d o r d n a n c e d e l i v e r y s y s t e m s o f t h e a t t a c k h e l i c o p t e r .
b . C o n f i g u r a t i o n .
T h e b a s i s f o r s i m u l a t i o n a n d c o n f i g u r a t i o n o f t h e A H - 6 4
( A p a c h e ) C M S i s t h e a i r c r a f t d a t a a v a i l a b l e a s o f 1 J u n e 1 9 8 3 u n d e r t h e b a s i c c o n t r a c t .
1-3.
TECHNICAL MANUAL CHANGES.
C h a n g e s a n d s u p p l e m e n t s t o t h i s m a n u a l w i l l b e p u b l i s h e d w h e n n e c e s s a r y t o a d d , d e l e t e , o r c h a n g e a n o p e r a t i n g r e q u i r e m e n t .
S u c h c h a n g e s w i l l b e b a s e d o n f a c t u a l d a t a a c c u m u l a t e d a s a r e s u l t o f o p e r a t i n g e x p e r i e n c e w i t h t h e t r a i n i n g d e v i c e a n d e q u i p m e n t .
c h a n g e s t o t h e t e x t a r e i n d i c a t e d b y a v e r t i c a l l i n e i n t h e o u t e r m a r g i n e x t e n d i n g c l o s e t o t h e e n t i r e a r e a o f t h e m a t e r i a l a f f e c t e d .
C h a n g e s t o i l l u s t r a t i o n s a n d w i r i n g d i a g r a m s a r e i n d i c a t e d b y c h a n g e l e g e n d s .
l - 4 .
FORMS AND RECORDS. M a i n t e n a n c e f o r m s a n d r e c o r d s u s e d b y a l l l e v e l s o f m a i n t e n a n c e p e r s o n n e l a r e i n D A P a m p h l e t 7 3 8 - 7 5 1 .
l - 5 .
REPORTING OF ERRORS.
R e p o r t o f e r r o r s o r o m i s s i o n s a n d r e c o m m e n d a t i o n s f o r i m p r o v i n g t h i s p u b l i c a t i o n b y t h e u s e r a r e e n c o u r a g e d .
R e p o r t s s h o u l d b e s u b m i t t e d o n D A F o r m 2 0 2 8 , R e c o m m e n d e d C h a n g e s t o P u b l i c a t i o n s , a n d f o r w a r d e d d i r e c t t o U . S . A r m y A v i a t i o n S y s t e m s C o m m a n d , A t t n :
AMSAV-MC, 4300 Goodfellow
B l v d . , S t . L o u i s , M O . 6 3 1 2 0 - 1 7 9 8
1 - 6 .
ABBREVIATIONS.
N o n s t a n d a r d a b b r e v i a t i o n s a n d a c r o n y m s u s e d i n t h i s m a n u a l a r e c o n t a i n e d i n t h e G l o s s a r y .
Change 2 1 - 1 / ( 1 - 2 b l a n k )
TM 55-6930-214-10
CHAPTER 2
SYSTEM DESCRIPTION AND OPERATION
Section I. GENERAL
2 - 1 .
OPERATIONAL SYSTEM.
T h e A H - 6 4 C M S i s a f i x e d - b a s e s i m u l a t i o n s y s t e m d e s i g n e d f o r t r a i n i n g i n t h e u s e o f A H - 6 4 A p a c h e h e l i c o p t e r s .
F i g u r e 2 - 1 s h o w s t h e r e c o m -
m e n d e d g e n e r a l a r r a n g e m e n t o f a p o r t i o n o f t h e s y s t e m c o m p l e x w i t h i n t h e G o v e r n m e n t - b u i l t f a c i l i t y .
T h e s i m u l a t o r r o o m , w h e r e t r a i n i n g i s c o n d u c t e d , c o n s i s t s o f t w o i n s t r u c t o r / t r a i n e e s t a t i o n s e q u i p p e d w i t h v i s u a l d i s p l a y s y s t e m s .
B a c h s t a t i o n i s m o u n t e d o n a s i x - d e g r e e - o f - f r e e d o m h y d r a u l i c m o t i o n s y s t e m a n d c o n t r o l l e d b y a c e n t r a l c o m p u t e r s y s t e m .
T h e b a s i c a r e a s o f t h e s i m u l a t o r c o m p l e x a r e f u r t h e r d e s c r i b e d i n t h e f o l l o w i n g p a r a g r a p h s .
2 - 2 .
SIMULATOR COMPARTMENTS.
T h e s i m u l a t o r r o o m c o n t a i n s s e p a r a t e m i s s i o n s i m u l a t o r c o m p a r t m e n t s f o r i n d i v i d u a l t r a i n i n g o f p i l o t a n d c o p i l o t / g u n n e r ( C P G ) t r a i n e e s .
E a c h s i m u l a t o r c o m p a r t m e n t h o u s e s a c o c k p i t s t a t i o n a n d a n i n s t r u c t o r / o p e r a t o r s t a t i o n ( I O S ) .
T h e c o c k p i t ( t r a i n e e ) s t a t i o n s a r e l o c a t e d i n t h e f o r w a r d p o r t i o n o f t h e i r r e s p e c t i v e c o m p a r t m e n t s .
E a c h C P G s i m u l a t o r c o m p a r t m e n t i n c l u d e s v i s u a l , m o t i o n , a n d s o u n d s i m u l a t i o n .
T h e p i l o t a n d C P G t r a i n e e s c a n t r a i n e i t h e r i n i n d e p e n d e n t m o d e s o f o p e r a t i o n w i t h s e p a r a t e a n d u n i q u e f l i g h t c o n d i t i o n s , o r i n a n i n t e g r a t e d m o d e w i t h c o m m o n t r a i n i n g c o n d i t i o n s .
a .
T h e p i l o t t r a i n e e s t a t i o n i s a r e p l i c a o f t h e a i r c r a f t p i l o t p o s i t i o n a n d i n c l u d e s f a c s i m i l e s o f t h e c o c k p i t w i n d o w a r r a n g e m e n t s , p i l o t s e a t , m a i n i n s t r u m e n t a n d c o n t r o l p a n e l , f l i g h t c o n t r o l s , i n t e g r a t e d h e l m e t a n d d i s p l a y s i g h t s y s t e m
( I H A D S S ) , p i l o t n i g h t v i s i o n s e n s o r ( P N V S ) , t a r g e t a c q u i s i t i o n / d e s i g n a t i o n s i g h t
(TADS), and video display unit (VDU).
L e f t a n d r i g h t e q u i p m e n t c o n s o l e s a r e a c t u a l a i r c r a f t - t y p e p a r t s .
b .
T h e C P G t r a i n e e s t a t i o n i s a r e p l i c a o f t h e a i r c r a f t C P G p o s i t i o n . A c t u a l a i r c r a f t c o c k p i t e q u i p m e n t i n c l u d e s t h e m a i n i n s t r u m e n t a n d c o n t r o l p a n e l , l e f t a n d r i g h t e q u i p m e n t c o n s o l e s , f l i g h t c o n t r o l s , i n t e g r a t e d h e l m e t a n d d i s p l a y s i g h t s y s t e m ( I H A D S S ) , o p t i c a l r e l a y t u b e ( O R T ) , p i l o t n i g h t v i s i o n s e n s o r ( P N V S ) , t a r g e t a c q u i s i t i o n / d e s i g n a t i o n s i g h t ( T A D S ) , a n d v i d e o r e c o r d e r s y s t e m ( V R S ) .
c .
A l l c o n t r o l s , i n d i c a t o r s . a n d p a n e l s o p e r a t e i n a s i m u l a t e d c o n d i t i o n a n d a r e i d e n t i c a l i n a p p e a r a n c e t o t h o s e i n T M 5 5 - 1 5 2 0 - 2 3 8 - 1 0 . O p e r a t o r ’ s M a n u a l f o r A H - 6 4
A p a c h e H e l i c o p t e r .
d .
T h r e e p a i r s o f l o u d s p e a k e r s a n d o n e s u b w o o f e r i n e a c h s i m u l a t o r c o m p a r t m e n t p r o v i d e r e a l i s t i c a u r a l c u e s o u n d s w i t h c h a r a c t e r i s t i c s c o r r e c t i n r e s p e c t t o l o c a t i o n , f r e q u e n c y , a n d l o u d n e s s ( w i t h i n l i m i t s o f s a f e t y ) . A u r a l c u e s o u n d s c a n b e v a r i e d i n l o u d n e s s b y t h e i n s t r u c t o r .
e .
T h e t r a i n e e c o c k p i t s e a t s c a n b e v i b r a t e d t o s i m u l a t e t h e c o n t i n u o u s a n d p e r i o d i c o s c i l l a t i o n s a n d v i b r a t i o n s e x p e r i e n c e d b y t h e c r e w d u r i n g f l i g h t c o n d i t i o n s a n d m a n e u v e r s .
V i b r a t i o n s r e p r e s e n t i n g p r o g r e s s i v e m a l f u n c t i o n s a r e a l s o s i m u l a t e d .
S e a t v i b r a t i o n i s i s o l a t e d f r o m t h e r e m a i n d e r o f t h e s i m u l a t o r c o m p a r t m e n t b y m e a n s o f d a m p i n g e l e m e n t s i n t h e s e a t m o u n t i n g c o n s t r u c t i o n .
Change 2 2-1
TM 55-6930-214-10
UNIT/ UNIT/
REF DES IDENTIFICATION REF DES IDENTIFICATION
1 PILOT COCKPIT (TRAINEE SECTION) 58 CRT DISPLAY
2 COPILOT/GUNNER COCKPIT (TRAINEE SECTION) 59 650 THERMAL PRINTER
3 VISUAL INTERFACE CABINET 60 (NOT USED)
4-l PILOT MOTION PLATFORM 61 (NOT USED)
4-2 COPILOT/GUNNER MOTION PLATFORM 62 CRT TERMINAL MPCS-E
5 PILOT COCKPIT CABINE T 63 DISK UNIT 1
6 COPILOT/GUNNER COCKPIT CABINET
64 DISK UNIT 2
7 PILOT INSTRUCTOR OPERATOR STATION 65
CPU CABINET 3
8 COPILOT/GUNNER INSTRUCTOR STATION 66 I/O CABINET 2
9 PILOT FLOOR CABINET (3-BAY) 67 CPU CABINET 2
10 COPILOT/GUNNER FLOOR CABINET (3-BAY) 68 I/O CABINET 1
11 POWER CABINET 69 CPU CABINET 1
I2 PILOT FCC/MASTER CONTROLLER CABINET 70 SHARED MEMORY CABINET 1
13 COPILOT/GUNNER FCC/MASTER CONTROLLER CABINET 71 CPU CABINET
14 400-HZ MOTOR-GENERATOR SET 72 I/O CABINET 4
15 400-HZ CONTROL BOX 73 CPU CABINET 5
16 PILOT VISUAL SYSTEM 74 I/O CABINET 6
17 COPILOT/GUNNER VISUAL SYSTEM 75 CPU CABINET 6
18 PILOT AIR CONDITIONER 76 DlSK UNIT 5
19 COPILOT/GUNNER AIR CONDITIONER 77 DISK UNIT 6
20-l PILOT MOTION CABINET 78 COMPUTER ROOM AUDIO BOX
20-2 COPILOT/GUNNER MOTION CABINET 79-l PILOT HYDRAULIC MOTION PUMP
21 1-CHANNEL PRIORITY SECTOR PROCESSOR CABINET 79-2 COPILOT/GUNNER HYDRAULIC MOTION PUMP
22 I-CHANNEL FRAME CALCULATOR CABINET 80 PILOT CONTROL LOADING - CONTROL BOX
23 1-CHANNEL FRAME SCANLINE COMPUTER CABINET 91 PILOT CONTROL LOADING - START/STOP BOX
24 l-CHANNEL VIDEO GENERATOR CABINET 82 PILOT CONTROL LOADING - HYDRAULIC POWER
25 I-CHANNEL POWER CABINET 83 PILOT CONTROL LOADING - OIL COOLER
26 3-CHANNEL PRIORITY SECTOR PROCESSING CABINET 84 PILOT CONTROL LOADING- CONSOLE
27 3-CHANNEL FRAME CALCULATOR CABINET 85 PILOT CONTROL LOADING - VACUUM PUMP
28 3-CHANNEL SCANLINE COMPUTER CABINET 86 COPILOT/GUNNER CONTROL LOADING -CONTROL BOX
29 3-CHANNEL VIDEO GENERATOR CABINET 87 COPILOT/GUNNER CONTROL LOADING - START/STOP BOX
30 3-CHANNEL POWER CABINET 88 COPILOT/GUNNER CONTROL LOADING -HYDRAULIC POWER
31 TADS CPU COMPUTER CABINET 89 COPILOT/GUNNER CONTROL LOADING-OIL COOLER
32 TADS SUPPORT COMPUTER CABINET 90 COPILOT/GUNNER CONTROL LOADING- CONSOLE
33 TADS 8260AT DELTA TERMINAL UNIT (CONSOLE) 91 COPILOT/GUNNER CONTROL LOADING - VACUUM PUMP
34 TADS 655 HARDCOPY UNIT 92 PNVS FLIR CABINET
35 TADS 8260AT DELTA CRT TERMINAL UNIT (DIG DIAGNOSTICS) 93 TADS FLIR CABINET
36 TADS DISK UNIT 94 PILOT RAMP
37 TADS DISK UNIT 95 COPILOT/GUNNER RAMP
38 PNVS CPU COMPUTER CABINET 96 APU CABINET 3
39 PNVS SUPPORT COMPUTER CABINET 97 (NOT USED)
40 MAGNETIC TAPE UNIT COMPUTER CABINET 98 (NOT USED)
41 PNVS 8260AT DELTA CRT TERMINAL UNIT (CONSOLE) 99 APU CABINET S
42 PNVS 655 HARDCOPY UNIT l00 CRT TERMINAL
43 PNVS 8260AT DELTA CRT TERMINAL UNIT (CONSOLE) 101 FIRE DETECTION CABINET
44 PNVS DISK UNIT 102 APU CABINET 1
45 PNVS DISK UNIT 103 DIG TEXTURE CABINET - TADS
46 LINE PRINTER 104 DIG TEXTURE CABINET - PNVS
47 MAINTENANCE CONSOLE - TADS VISUAL CONTROL CONSOLE 105 MTU - l-CHANNEL
48 MAINTENANCE CONSOLE - TAOS VISUAL CONTROL CONSOLE 106 LINE PRINTER -1-CHANNEL
49 MAGNETIC TAPE UNIT COMPUTER CABINET 107 (NOT USED)
50 SHARED I/O CABINET l08 (NOT USED)
51 DISK UNIT - 3 109 SWITCH BOX
52 DlSK UNIT - 4 110 SWITCH BOX
53 SHARED MEMORY CABINET 2 1ll PRINTER
54 CPU CABINET 7 112 PRINTER
55 CR1 DISPLAY 113 CRT 5
56 650 THERMAL PRINTER 114 CRT 6
57 LINE PRINTER
Figure 2-1. Typical AH-64 CMS and Computer Rooms System Complex (Sheet 3)
2 - 4 Change 2 All data on pages 2-5 and 2-6 deleted.
TM 55-6930-214-10
UNIT/
REF DES
IDENTIFICATION
PILOT COCKPIT (TRAINEE SECTION)
COPILOT/GUNNER COCKPIT (TRAINEE SECTION)
VISUAL INTERFACE CABINET
PILOT MOTION PLATFORM
COPILOT/GUNNER MOTION PLATFORM
PILOT COCKPILOT CABINET
PILOT/GUNNER COCKPIT CABINET
PILOT INSTRUCTOR OPERATOR STATION
COPILOT/GUNNNER INSTRUCTOR OPERATOR STATION
PILOT FLOOR CABINET (3-DAY)
COPILOT/ FLOOR (1 CABINET (3-DAY)
POWER CABINET
PILOT FCC/MASTER CONTROLLER CABINET
COPILOT/GUNNER FCC/MASTER CONTROLLER CABINET
4OO-HZ MOTOR-GENERATOR SET
4OO-HZ CONTROL BOX
PILOT VISUAL SYSTEM
COPILOT/GUNNER VISUAL SYSTEM
PILOT AIR CONDITIONER
COPILOT/GUNNER AIR CONDITIONER
PILOT MOTION CABINET
COPILOT/GUNNER MOTION CABINET
1-CHANNEL PRIORITY SECTOR PROCESSOR CABINET
1-CHANNEL FRAME CALCULATOR CABINET
1-CHANNEL SCANLINE COMPUTER CABINET
1-CHANNEL VIDEO GENERATOR CABINET
1-CHANNEL POWER CABINET
3-CHANNEL PRIORITY SECTOR PROCESSING CABINET
3-CHANNEL FRAME CALCULATOR CABINET
3-CHANNEL SCANLINE COMPUTER CABINET
3-CHANNEL VIDEO GENERATOR CABINET
3-CHANNEL POWER CABINET
TADS CPU COMPUTER CABINET
TADS SUPPORT COMPUTER CABINET
TADS 550 CRT TERMINAL UNIT (CONSOLE)
TADS 655 HARDCOPY UNIT
TADS 550 CRT TERMINAL UNIT (DIG DIAGNOSTICS)
TADS DISK UNIT
TADS DISK UNIT
PNVS CPU COMPUTER CABINET
PNVS SUPPORT COMPUTER CABINET
MAGNETIC TAPE UNIT COMPUTER CABINET
PNVS 550 CRT TERMINAL WIT (CONSOLE)
PNVS 655 HARDCOPY UNIT
PNVS 550 CRT TERMINAL UNIT (CONSOLE)
PNVS DISK UNIT
PNVS DISK UNIT
LINE PRINTER
MAINTENANCE CONSOLE - TADS VISUAL CONTROL
CONSOLE
MAINTENANCE CONSOLE - TADS VISUAL CONTROL
CONSOLE
MAGNETIC TAPE UNIT COMPUTER CABINET
SHARED
I/O
CABINET
DISK UNIT - 3
DISK UNIT - 4
SHARED MEMORY CABINET 2
CPU CABINET 7
UNIT/
REF DES
107
108
IDENTIFICATION
CRT DISPLAY
HARDCOPY UNIT
CRT TERMINAL
CRT DISPLAY
HARDCOPY UNIT
LINE PRINTER
CRT TERMINAL
CRT TERMINAL
DISK UNIT 1
DISK UNIT 2
CPU CABINET 3
I/O CABINET 3
CPU CABINET 2
I/O CABINET 1, 2
CPU CABINET 1
SHARED MEMORY CABINET 1
CPU CABINET 4
I/O CABINET 4, 5
CPU CABINET 5
I/O CABINET 6
CPU CABINET 6
DISK UNIT 5
DISK UNIT 6
COMPUTER ROOM AUDIO BOX
PILOT HYDRAULIC MOTION PUMP
COPILOT/GUNNER HYDRAULIC MOTION PUMP
PILOT CONTROL LOADING - CONTROL BOX
PILOT CONTROL LOADING - START/STOP BOX
PILOT CONTROL LOADING - HYDRAULIC POWER
PILOT CONTROL LOADING - OIL COOLER
PILOT CONTROL LOADING - CONSOLE
PILOT CONTROL LOADING -VACUUM PUMP
COPILOT/GUNNER CONTROL LOADING - CONTROL BOX
COPILOT/GUNNER CONTROL LOADING - START/STOP BOX
COPILOT/GUNNER CONTROL LOADING - HYDRAULIC POWER
COPILOT/GUNNER CONTROL LOADING - OIL COOLER
COPILOT/GUNNER CONTROL LOADING - CONSOLE
COPILOT/GUNNER CONTROL LOADING - VACUUM PUMP
PNVS FLIR CABINET
TADS FLIR & CABINET
PILOT RAMP
COPILOT/GUNNER RAMP
APU CABINET 3
APU CABINET 2
APU CABINET 4
APU CABINET 5
CRT TERMINAL
FIRE DETECTION CABINET
APU CABINET 1
DIG TEXTURE CABINET - TADS
NOT USED
DIG TEXTURE CABINET - PNVS
NOT USED
RESERVED FOR MTU - 1-CHANNEL
RESERVED FOR LINE PRINTER - 1-CHANNEL
RESERVED FOR LINE PRINTER - 1-CHANNEL
RESERVE0 FOR LINE PRINTER - 3-CHANNEL
EFFECTIVITY CODES:
2137020-001 ONLY
2137021-00l ONLY
Figure 2-1.
Typical AH-64 CMS and Computer Rooms System Complex (Sheet
5)
2-6
TM 55-6930-214-10
f .
The ambient temperature of the simulator compartment and the cockpit is c o n t r o l l e d b y a d j u s t i n g t h e t h e r m o s t a t l o c a t e d o n t h e b a c k w a l l o f t h e c o m p a r t ment.
Conditioned air is ducted through the compartment area and the normal h e l i c o p t e r c o c k p i t h e a t i n g a n d d e f r o s t i n g d u c t s .
The cockpit environment control s y s t e m s w i t c h e s a n d c o n t r o l s a r e n o n f u n c t i o n a l .
g.
A platform step is provided alongside each cockpit to facilitate entrance and e x i t .
L o w - l e v e l s t e p l i g h t i n g i s p r o v i d e d f o r s a f e t y a n d i s a f u n c t i o n o f t h e facility power.
2 - 3 .
INSTRUCTOR/ OPERATOR STATIONS.
T h e i n s t r u c t o r / o p e r a t o r s t a t i o n s ( I O S ) a r e l o c a t e d a d j a c e n t a n d t o t h e r e a r o f t h e c o c k p i t I n e a c h s i m u l a t o r c o m p a r t m e n t .
( R e f e r t o S e c t i o n I I f o r f u r t h e r d e t a i l s . ) T h e I O S a l l o w s i n s t r u c t o r s / o p e r a t o r s t o c o n t r o l t h e t r a i n i n g p r o g r a m a n d e f f e c t i v e l y m o n i t o r a n d e v a l u a t e t r a i n e e p e r f o r m ance .
D u r i n g t r a i n i n g , the pilot and CPG IOS function in either independent or i n t e g r a t e d m o d e s o f o p e r a t i o n .
2 - 4 .
MOTION SYSTEM.
Each simulator compartment is mounted on a six-degree-offreedom (6-DOF) motion system consisting of a moving platform assembly driven and s u p p o r t e d f r o m b e l o w b y s i x i d e n t i c a l h y d r a u l i c a c t u a t o r s .
The motion system is c a p a b l e o f p r o v i d i n g c u e s f o r p i t c h , r o l l , y a w , l a t e r a l , l o n g i t u d i n a l , a n d v e r t i c a l movements.
System motion can be either Independent (without simultaneous motion in any other degree of freedom) or in any combination desired to produce real-time dynamic motion cues.
a .
F l i g h t s i m u l a t i o n i n c l u d e s c o m b i n e d m o t i o n r e p r e s e n t i n g c h a n g e s i n a i r c r a f t a t t i t u d e a s a d i r e c t r e s u l t o f f l i g h t c o n t r o l s , r o u g h a i r , a n d w i n d , a n d c h a n g e s i n a i r c r a f t w e i g h t a n d c e n t e r - o f - g r a v i t y r e s u l t i n g f r o m f u e l c o n s u m p t i o n o r w e a p o n a n d ammunition depletion.
Also, motion effects such as droop-stop pounding, blade s t a l l , b l a d e i m b a l a n c e , d a m p e r f a i l u r e , blades out-of-track, and touchdown impact can be produced.
b .
The computer-controlled simulation program causes the motion system to respond realistically to aerodynamic forces and moments within the mechanical limits o f t h e s y s t e m .
All motions except pitch are imperceptibly washed out to the n e u t r a l p o s i t i o n a f t e r t h e c o m p u t e d a c c e l e r a t i o n s h a v e r e a c h e d z e r o .
P i t c h a t t i t u d e i s m a i n t a i n e d a s n e c e s s a r y t o s i m u l a t e s u s t a i n e d l o n g i t u d i n a l a c c e l e r a t i o n c u e s .
A c c e l e r a t i o n o n s e t c u e s a r e s c a l e d a s l a r g e a s p o s s i b l e t o f u l l y u t i l i z e t h e r a n g e o f m o t i o n c a p a b i l i t i e s o f e a c h d e g r e e - o f - f r e e d o m .
c . D e p e n d i n g o n t h e p a r t i c u l a r f l i g h t p r o g r a m , the motion system responds to computer input signals as noted in the following examples:
( 1 ) G r o u n d c o n d i t i o n s .
T h e m o t i o n s y s t e m p r o v i d e s t h e v i b r a t i o n a l i n d i c a t i o n s a p p r o p r i a t e t o m o t i o n o f t h e a i r c r a f t d u r i n g s t a r t u p .
The system produces a random, l o w - f r e q u e n c y , l o w - a m p l i t u d e . m u l t i d i r e c t i o n a l o s c i l l a t i o n w i t h r e a s o n a b l y a b r u p t a p p l i c a t i o n .
The computer simulation program varies the amplitude of oscillation t o r e p r o d u c e t h e i r r e g u l a r i t i e s o f l e s s t h a n i d e a l f l i g h t t a k e o f f c o n d i t i o n s .
( 2 ) T a k e o f f a n d l a n d i n g .
T h e m o t i o n s y s t e m p r o v i d e s s i m u l a t e d r e a l i s t i c e f f e c t s f o r a l l f o r m s o f t a k e o f f , f l i g h t , a n d l a n d i n g c o n d i t i o n s .
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( a ) D u r i n g e n g i n e r u n u p a n d i n i t i a l h o v e r f o r t a k e o f f , t h e g r o u n d p e r f o r m a n c e o f t h e m o t i o n s y s t e m i s a s d e s c r i b e d i n p a r a g r a p h ( 1 ) . T h e m o t i o n s y s t e m m a i n t a i n s a n a t t i t u d e a p p r o p r i a t e f o r h o v e r a n d p r o v i d e s t h e c o r r e c t i n d i c a t i o n s o f t a k e o f f .
A p p r o p r i a t e m o t i o n e f f e c t s o c c u r a s a r e s u l t o f c h a n g e s i n a c c e l e r a t i o n a n d l i f t d u r i n g t r a n s i t i o n t o f o r w a r d f l i g h t .
( b ) S i m i l a r e f f e c t s a r e r e p r o d u c e d d u r i n g t h e l a n d i n g p h a s e .
The motion s y s t e m c a u s e s a p p r o p r i a t e l o n g i t u d i n a l , v e r t i c a l , a n d l o w - f r e q u e n c y v i b r a t i o n e f f e c t s t o o c c u r a s i n t h e h e l i c o p t e r .
The motion system correctly reproduces the l a n d i n g i m p a c t a c c o r d i n g t o t h e e x i s t i n g a i r c r a f t a t t i t u d e a n d v e r t i c a l a n d s i d e s l i p v e l o c i t i e s .
When the vertical momentum is greater than the absorption capab i l i t i e s o f t h e l a n d i n g g e a r , l a n d i n g b o u n c e i s s i m u l a t e d .
( 3 ) N o r m a l f l i g h t .
The motion system correctly simulates the complex and rep e a t e d c u e s o c c u r r i n g d u r i n g m a n e u v e r s a s s o c i a t e d w i t h n o r m a l f l i g h t c o n d i t i o n s .
T h e r a n d o m i n t r o d u c t i o n o f v a r y i n g d e g r e e s o f t u r b u l e n c e p r o d u c e s t h e a p p r o p r i a t e m o t i o n e f f e c t s o f s m a l l v a r i a t i o n s i n y a w a n d r o l l , c l i m b o r d e s c e n t , a n d a i r speed.
Superimposed upon the flight maneuver motions is the background motion.
T h e m o t i o n s y s t e m p r o v i d e s c h a r a c t e r i s t i c p e r i o d i c o s c i l l a t i o n s o f t h e a i r c r a f t , l a t e r a l i n s t a b i l i t y , and aircraft vibrations up to a maximum of 5 cycles per second.
C o n t i n u o u s h i g h e r f r e q u e n c y v i b r a t i o n s a r e s i m u l a t e d u s i n g t h e s e a t s h a k e r i n l i e u o f t h e m o t i o n s y s t e m .
( 4 ) A b n o r m a l f l i g h t .
T h e m o t i o n s y s t e m c o r r e c t l y r e p r o d u c e s t h e e f f e c t s o f r o t o r o u t - o f - t r a c k a n d r o t o r o u t - o f - b a l a n c e f a i l u r e s .
The motion simulated includes t h e e f f e c t o f m o m e n t a r y i n c o r r e c t c o n t r o l i n p u t s a s w e l l a s c o n d i t i o n s a p p r o p r i a t e t o m a l f u n c t i o n s .
A n a i r c r a f t h y d r a u l i c s y s t e m f a i l u r e r e s u l t i n g i n a b n o r m a l d i r e c t i o n a l c o n t r o l o f t h e a i r c r a f t i s p r o v i d e d b y a p p r o p r i a t e m o t i o n c u e s .
H i g h a i r s p e e d c h a r a c t e r i s t i c s a n d t r i m c h a n g e e f f e c t s a r e a l s o p r o d u c e d b y t h e m o t i o n system.
2 - 5 .
VISUAL SYSTEM.
T h e p i l o t a n d C P G t r a i n e e s t a t i o n s a r e p r o v i d e d w i t h f o r w a r d , l e f t , a n d r i g h t s i d e w i n d o w v i s u a l d i s p l a y s .
The visual generation system provides imagery to every sensor display in the CMS, including IHADSS, PNVS, OTW scene, VDU, and TADS/FLIR.
( R e f e r t o C h a p t e r 6 f o r v i s u a l s y s t e m s d e t a i l s . )
2 - 6 .
COMPUTER SYSTEM.
I n a n o n r i g o r o u s s e n s e , the CMS consists of the pilot main computational system (MCS), m a d e u p o f c e n t r a l p r o c e s s i n g u n i t s ( C P U ’ s ) 1 , 2 . a n d 3 and their associated auxiliary processing units (APU's); and the CPG MCS, made up of CPU’s 4, 5, and 6 and their associated APU’s.
Bach CPU has private memory that o n l y I t a n d i t s a s s o c i a t e d A P U ’ s c a n a c c e s s .
The CPG MCS has complex shared memory that only CPU’s 4, 5, and 6 can access.
The pilot MCS has complex shared memory that only CPU’s 1, 2, and 3 can access.
I n a d d i t i o n , a m e m o r y r e g i o n c a l l e d g l o b a l memory exists that all six CPU’s can access.
2-8
TM 55-6930-214-10
S e c t i o n I I .
INSTRUCTOR/OPERATOR STATION DESCRIPTION
2 - 7 .
GENERAL DESCRIPTION.
Each instructor/operator station (IOS) accommodates one i n s t r u c t o r a n d a n o b s e r v e r .
( F i g u r e 2 - 2 i n d i c a t e s t h e a r r a n g e m e n t o f t h e
i n s t r u c t o r / o p e r a t o r s t a t i o n s a n d t h e i r r e l a t i o n s h i p w i t h t h e t r a i n e e s t a t i o n s . )
T h e I O S a r r a n g e m e n t p e r m i t s c l o s e , direct contact between instructors/operators and t r a i n e e s .
The locations of the forward control panel and the console control panel p r o v i d e c o n v e n i e n t c o n t r o l o f e a c h o r b o t h c o c k p i t s , a n d d i r e c t c o n t a c t w i t h t h e
C R T d i s p l a y s o f i n f o r m a t i o n r e q u i r e d t o m o n i t o r , g u i d e , a n d e v a l u a t e t r a i n e e p e r formance .
B r i e f d e s c r i p t i o n s o f t h e v a r i o u s f e a t u r e s o f t h e i n s t r u c t o r a r e a s a r e g i v e n i n t h e f o l l o w i n g p a r a g r a p h s .
2 - 8 .
IOS CONTROL PANELS.
A T e a c h I O S , t w o c o n t r o l p a n e l s p r o v i d e c o n t r o l a n d m a n a g e m e n t o f s i m u l a t o r t r a i n i n g .
T h e p a n e l s a r e s i m i l a r , w i t h t h e e x c e p t i o n o f s p e c i a l c o n t r o l s a t t h e C P G I O S t h a t a r e u s e d i n c o n j u n c t i o n w i t h a u t o m a t i c f l i g h t p r o g r a m s w h e n t h e C P G c o c k p i t i s o p e r a t e d i n t h e i n d e p e n d e n t m o d e .
i l l u s t r a t e s t h e p i l o t a n d C P G I O S c o n s o l e s c o n t r o l p a n e l s . ) T o t h e l e f t o f t h e
f o r t h e i n s t r u c t o r s v i d e o m o n i t o r , d i s c r e t e c o n t r o l s f o r s o m e t r a i n i n g f e a t u r e s , and a discrete control for communications with the computer room. On the bulkhead, l e f t o f t h e c o c k p i t , i s a c o n t r o l p a n e l f o r o b s e r v e r c o m m u n i c a t i o n s , t h e I O S a m b i e n t l i g h t i n g , a n d s t e p l i g h t s .
(The trainee flight compartment layout is shown
c o n t r o l l i n g a n y t r a i n i n g s i t u a t i o n i s e n s u r e d .
Two CRT’s provide simultaneous viewing of the PLT and CPG PNVS/TADS information.
R e l a t e d C R T d i s p l a y c o n t r o l s , p r o b l e m f l i g h t c h a r a c t e r i s t i c s a n d c o n t r o l s , and simulator setup and communications c o n t r o l s a r e o n t h e c o n s o l e c o n t r o l p a n e l .
O n l y m i n o r d i f f e r e n c e s e x i s t i n t h e c o n t r o l l a b e l i n g a n d f u n c t i o n s b e t w e e n t h e p i l o t a n d C P G I O S p a n e l s .
2 - 9 .
TRAINER CONTROL PANELS.
The pilot and CPG trainee control panels are located a l o n g t h e o u t e r e d g e o f t h e l e f t s i d e c a n o p y r a i l s .
2 - 1 0 .
INSTRUCTION SEATS.
T h e i n s t r u c t o r s e a t i s m o u n t e d o n a t r a c k t o a l l o w f o r w a r d o r r e a r w a r d a d j u s t m e n t f o r o p t i m u m p o s i t i o n i n g .
T h e s e a t a l s o h a s a 3 6 0 d e g r e e s w i v e l c a p a b i l i t y , a s w e l l a s u p a n d d o w n a d j u s t m e n t , t o e n a b l e t h e i n s t r u c t o r t o a d j u s t f o r o p t i m u m C R T a n d / o r c o c k p i t s t a t i o n i n s t r u m e n t s v i e w i n g a n g l e .
P o s i t i v e l o c k s i n t h e t r a c k , s w i v e l , a n d h e i g h t s y s t e m s p r e v e n t t h e s e a t f r o m m o v i n g i n r e s p o n s e t o m o t i o n s o f t h e s i m u l a t o r c o m p a r t m e n t .
The normal position of t h e s e a t p l a c e s t h e i n s t r u c t o r ’ s e y e l e v e l s l i g h t l y a b o v e a n d t o t h e l e f t o f t h e t r a i n e e ’ s e y e l e v e l t o p e r m i t e a s i e r s u r v e i l l a n c e o f t h e c o c k p i t i n s t r u m e n t a n d c o n t r o l p a n e l s .
2 - 1 1 .
OBSERVER SEATS.
A n o b s e r v e r s e a t , e q u i p p e d w i t h f o l d - d o w n a r m s a n d a n a b d o m i n a l s e a t b e l t , i s l o c a t e d t o t h e l e f t o f t h e I O S c o n s o l e i n t h e s i m u l a t o r compartment.
I t i s m o u n t e d o n a t r a c k t o a l l o w s i d e t o s i d e a d j u s t m e n t f a c i l i t a t i n g o v e r a l l v i e w i n g o f i n s t r u c t o r / t r a i n e e p e r f o r m a n c e .
An intercommunications s y s t e m ( I C S ) c o n t r o l p a n e l o n t h e w a l l a n d s e p a r a t e h e a d s e t j a c k i n t h e c e i l i n g , w i t h a c o r d o f s u f f i c i e n t l e n g t h s o a s t o b e n o n i n t e r f e r r i n g , p r o v i d e o b s e r v e r c o m m u n i c a t i o n w i t h t h e i n s t r u c t o r .
Change 2 2-9
TM 55-6930-214-10
CPG ISTRUCTOR FORWARD CONTROL PANEL
Figure 2-4. Pilot/CPG IOS Forward Control Panels
15523
Change 2
2-15/(2-16 blank)
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Figure 2-6.
T r a i n e e S t a t i o n
15527
Change
2 2-17
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2-18
Change 2
F i g u r e 2 - 7 .
Trainee Control Panel
15528
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2 - 1 2 .
IOS AREA LIGHTING.
T h e I O S a r e a i s p r o v i d e d w i t h a v a r i a b l e - i n t e n s i t y o v e r h e a d l i g h t , m a p l i g h t , and clip-on light to provide ambient illumination during a n y p h a s e o f t h e t r a i n i n g .
A b l a c k c u r t a i n i s p r o v i d e d t o s h i e l d t h e c r e w m e m b e r s t a t i o n f r o m
I O S l i g h t i n g .
2 - 1 3 .
INSTRUCTOR INTERCOMMUNICATION SYSTEM.
Headset cords and microphone switches f o r e a c h i n s t r u c t o r a r t i n s t a l l e d t o p e r m i t m i n i m u m i n t e r f e r e n c e w i t h t h e t r a i n i n g f u n c t i o n .
C o m m u n i c a t i o n o n a p r i v a t e b a s i s i s p r o v i d e d f o r i n s t r u c t o r s , o b s e r v e r s , and the computer room.
( A v i s u a l w a r n i n g c u t i s p r o v i d e d f o r t h e i n s t r u c t o r s , a n d a n a u r a l w a r n i n g c u t i s p r o v i d e d i n t h e c o m p u t e r r o a r . )
2 - 1 4 .
TIME REFERENCES. A digital readout time-of-day clock is located above the observer control panel on the wall to the left of the IOS.
Change 2 2-19
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S e c t i o n I I I .
MODES OF OPERATION
2 - 1 5 .
GENERAL.
T h e C M S c a n o p e r a t e o n - l i n e i n t h r e e c a t e g o r i e s : t r a i n i n g , a u t o f l y , a n d d e m o n s t r a t i o n .
T h e C M c a n b e u s e d w i t h t h e v i s u a l d i s p l a y s a n d / o r m o t i o n s y s t e m i n o p e r a t i o n .
W i t h t w o v i s u a l s y s t e m s , b o t h c o c k p i t s c a n h a v e o u t - t h e - w i n d o w ( O T W ) v i s u a l d i s p l a y s .
T h e p i l o t o r C P G c o c k p i t c a n e i t h e r b e o p e r a t e d i n d e p e n d e n t l y , o r b o t h c a n b e o p e r a t e d a s o n a s i n g l e i n t e g r a t e d m i s s i o n a s c r e w m e m b e r s o f t h e s a m e a i r c r a f t .
T h e C M S m u s t b e i n t h e f r e e z e m o d e t o s e t u p o r e d i t a d e m o n s t r a t i o n .
F o r m u l a t i o n o f a d e m o n s t r a t i o n i n v o l v e s r e c o r d i n g a n d s t o r i n g t h e c h a r a c t e r i s t i c s o f p a r t i c u l a r f l i g h t o r m i s s i o n p r o f i l e s i n t h e c o m p u t e r m e m o r y .
A n a c c o m p a n y i n g a u d i o c o m m e n t a r y c a n a l s o b e r e c o r d e d a n d s y n c h r o n i z e d t o t h e m o t i o n .
D u r i n g p l a y b a c k o f a r e c o r d e d d e m o n s t r a t i o n f o r t r a i n i n g , t h e C M S f l i e s i t s e l f t h r o u g h a n e s t a b l i s h e d m i s s i o n e x e r c i s e i n a h a n d s - o f f - t h e - c o n t r o l s c o n d i t i o n .
A s t h e C M S r e f l i e s t h e m i s s i o n , a l l m o t i o n , a u r a l s o u n d s , i n s t r u m e n t i n d i c a t i o n s , a n d v i s u a l d i s p l a y s c e n e s a r e r e c r e a t e d .
T h i s c a n s h o w t h e t r a i n e e p i l o t a n d / o r C P G p a r t i c u l a r s t a n d a r d m a n e u v e r s s p e c i a l f l i g h t p r o b l e m s .
( F u r t h e r i n -
s y s t e m f e a t u r e s a v a i l a b l e t o e a c h c o c k p i t f o r t h e m o d e s o f b o t h i n d e p e n d e n t a n d i n t e g r a t e d o p e r a t i o n a r t o u t l i n e d i n t a b l e 2 - l .
2 - 1 6 .
TRAINING.
T h e a d m i n i s t r a t i o n o f t r a i n i n g t o t r a i n e e s o c c u p y i n g t h e p i l o t o r
C P G c o c k p i t s i s u n d e r t h e p o s i t i v e c o n t r o l o f t h e i n s t r u c t o r .
For independent m o d e s , t h e i n s t r u c t o r c a n e m p l o y a u t o f l y w i t h a u t o m a t i c p e r f o r m a n c e r e c o r d i n g , p r e c o r d e d d e m o n s t r a t i o n s . I n i t i a l c o n d i t i o n s , p r e p r o g r a m m e d m a l f u n c t i o n s , o r o t h e r a i d s t h r o u g h t h e u s e o f c o n t r o l s a n d C R T d i s p l a y s p r o v i d e d a t t h e I O S .
I n f o r m a t i o n t o b e d i s p l a y e d a t t h e I O S i s u p d a t e d c o n t i n u o u s l y d u r i n g t h e t r a i n i n g p r o g r a m t o r e f l e c t c u r r e n t s t a t u s .
a .
I n d e p e n d e n t T r a i n i n g .
I n t h e i n d e p e n d e n t m o d e , e a c h i n s t r u c t o r i s f r e e t o c o n t r o l a n y o f t h e m a n u a l f e a t u r e s o f t h e C M S .
T h i s i n c l u d e s i n s e r t i n g o w n c o c k p i t m a l f u n c t i o n s , c h a n g i n g i n i t i a l c o n d i t i o n s , c u r r e n t c o n d i t i o n s a n d w e a p o n l o a d i n g c o n f i g u r a t i o n s , a n d s e l e c t i o n o f n a v / c o m m e q u i p m e n t a n d f a c i l i t i e s .
I n a d d i t i o n , a t r a i n i n g s e s s i o n c a n b e f r o z e n , a n d a 1 5 - s e c o n d t o 5 - m i n u t e d y n a m i c p l a y b a c k o f t h e c u r r e n t t r a n s p i r e d f l i g h t c o n d i t i o n s i s a v a i l a b l e f o r r e v i e w .
b . I n t e g r a t e d T r a i n i n g .
I n t h e i n t e g r a t e d m o d e , t h e a d m i n i s t r a t i o n o f t r a i n i n g t o t h e t r a i n e e s i n b o t h c o c k p i t s i s u n d e r t h e p o s i t i v e c o n t r o l o f e i t h e r t h e P L T o r t h e C P G i n s t r u c t o r .
T h e c o n t r o l l i n g i n s t r u c t o r c o n t r o l s t h e m a n u a l f e a t u r e s o f t h e
CMS.
T h i s i n c l u d e s i n s e r t i n g m a l f u n c t i o n s , c h a n g i n g i n i t i a l c o n d i t i o n s , s e l e c t i o n o f n a v / c o m m e q u i p m e n t a n d f a c i l i t i e s , a n d a l l a s p e c t s o f t r a i n i n g . T h e o t h e r i n s t r u c t o r g e n e r a l l y a c t s a s a n o b s e r v e r a n d h a s u s e o f o n l y t h e e m e r g e n c y c o n t r o l s , h a r d c o p y r e q u e s t s , t i m e r , a n d C R T d i s p l a y s e l e c t ( w i t h o u t e d i t i n g c a p a b i l i t y ) . A l l a s p e c t s o f t r a i n i n g i n t h e i n t e g r a t e d m o d e c a n b e a c c o m p l i s h e d w i t h o u t t h e o t h e r instructor present.
2 - 1 7 .
AUTOFLY.
T h e n e e d f o r a p i l o t a t a l l t i m e s i s o v e r r i d d e n b y t h e u s e o f t h e a u t o m a t i c f l i g h t m o d e o f o p e r a t i o n .
W h e n t h e C P G c o c k p i t i s o p e r a t e d i n t h e i n d e p e n d e n t m o d e , t h e C M S f l i e s i t s e l f t o c o m p e n s a t e f o r t h e m i s s i n g p i l o t . T h e a u t o f l y f e a t u r e f l i e s t h e c o p i l o t / g u n n e r t h r o u g h a p r e r e c o r d e d a i r c r a f t m a n e u v e r , o r s e r i e s o f m a n e u v e r s .
W h e n a c t i v e i n t h e a u t o f l y m o d e , t h e C M S p e r f o r m s a s i f a p i l o t w e r e a c t u a l l y f l y i n g t h e a i r c r a f t .
D u r i n g t h e a u t o f l y , t h e i n s t r u c t o r c a n i n t e r r u p t t h e f l i g h t a n d a s s u m e m a n u a l c o n t r o l o f t h e s i m u l a t e d a i r c r a f t h e a d i n g a n d a l t i t u d e ( i . e . , a c t a s t h e p i l o t ) .
B y d o i n g s o , t h e C P G i s a l l o w e d a d d i t i o n a l t i m e , i f n e e d e d , t o o p e r a t e s e n s o r , s i g h t i n g , a n d w e a p o n s y s t e m s .
2-20 Change 2
T M 5 5 - 6 9 3 0 - 2 1 4 - 1 0
Integrated
T a b l e 2 - 1 . Integrated/Independent Operation Features
Pilot independent
a . N / A
CPG independent
a. N/A a .
Recording or editing a demonstration.
b .
Demonstration playback
-preprogrammed audio, slow-time, and pause.
b. Automated flight with preprogrammed audio, slow-time. and pause.
System dots not respond to trainee control inputs.
b. Automated flight with preprogrammed audio, slowtime. and pause.
c .
N/A c .
d .
e .
Dynamic recording/ performance playback with audio (no audio in slow-time).
A l l
N/A c. Automatic flight with preprogrammed audio, visual, and movement.
d. Dynamic recording/ performance playback - with audio
(no audio in slowt i m e ) .
e . A l l d .
Dynamic recording/ performance playback - with audio
(no audio in slowt i m e ) .
e .
Program variation and c o n t r o l s -
M a l f u n c t i o n s
Initial conditions
Z e r o i n g
Environmental c o n d i t i o n s
Nav fail
Parameter freeze
Problem freeze
R e f u e l / a r m
T h r e a t s
Hardcopy
Timer
Display select
(Limited to editing m a l f u n c t i o n s )
MASTER
IOS
ONLY
ROTH
IOS
SLAVE
IOS
Change 2 2-21
TM 55-6930-214-10
2-18.
DEMONSTRATION.
For demonstration playback, t h e i n s t r u c t o r c a n s e l e c t a n u m b e r o f p r e r e c o r d e d d e m o n s t r a t i o n s .
Each demonstration can be further subdivided i n t o n i n e s e p a r a t e m a n e u v e r s .
T h e s e i n d i v i d u a l m a n e u v e r s c a n b e s e l e c t i v e l y a c c e s s e d , o r t h e y c a n b e r e a r r a n g e d t o f o r m u l a t e o n e m i s s i o n f o r p l a y b a c k .
Synchronized audio accompanying the demonstration is not available to the pilot or CPG c o m p a r t m e n t i f t h e o t h e r i n s t r u c t o r h a s a l r e a d y c h o s e n t h e s a m e d e m o n s t r a t i o n w i t h audio . The instructor can delete a demonstration at any point.
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Section IV. TRAINING CAPABILITIES
2-19. GENERAL. The CMS is a fully operational combat mission simulator with separate pilot and CPG simulator compartments.
Each has its own six degree-of freedom motion system, visual system, and instructor/operator station.
Each cockpit station duplicates its portion of the actual helicopter cockpit configuration.
The CMS simulates, in real-time, applicable normal and emergency aircraft operation with respect to both transient and steady-state flight conditions.
Operation of the CMS involves such capabilities as engine performance, flying qualities, weapons systems performance and operation, aircraft systems performance and operation, radio communications and navigation systems performance and operation, environmental effects, nap-of-the-earth operation, and flightpath.
Simulation is reflected by appropriate trainee and IOS station instrument and aural indications, aircraft control reactions, visual cue presentations, and display traces responding to trainee, instructor, and computer-programmed control inputs.
Use of the CMS when the visual and/or motion system is inoperative severely limits training capab i l i t i e s .
2-20. TRAINING OBJECTIVES. The CMS can be used to provide transition training proficiency flying, and weapons delivery practice. The CMS can also be used to train pilots to perform all normal and emergency flight maneuvers, weapons delivery operations, nap-of-the-earth flight and navigation, and starting, runup, and shutdown procedures. It is capable of full mission simulation, and it can be used for training of both the pilot and CPG simultaneously on the same mission or independently on different missions. This is accomplished in either integrated or independent operating modes of visual, motion, and cockpit simulation available to both pilot and CPG in any situation. The CMS can also be used for the training of instructor pilots.
NOTE
Training maneuvers are not limited to those listed in this paragraph.
a.
Basic Maneuvers.
Training for the following basic aircraft maneuvers can be conducted:
Cockpit procedures
Startup and initial hover
Hovering flight (including turns)
Traffic pattern
Normal takeoff from a hover
Normal takeoff from the ground
Normal approach to a hover
Normal approach to the ground
Straight-and-level flight
Level turns
Straight climbs and descents
Turning climbs and descents b.
Advanced Maneuvers.
Training for the following advanced aircraft maneuvers can be conducted:
Maximum performance takeoff
Steep approach
Basic autorotation (power recovery and termination with power)
DASE OFF (digital automatic stabilization equipment) flight
Running landings
High-speed flight
Change 1
2-23
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High-speed dive (normal)
High-speed dive (steep)
Running takeoff
Night operations c. Emergency Maneuvers.
Training for the following emergency aircraft maneuvers can be conducted:
Forced landings (normal and high speed)
Autorotative glides and turns
Decelerations
Simulated tail rotor control failure
Simulated hydraulic failure
Transient torque control
Emergency procedures (including emergency shutdown procedures)
Autorotations with turns (power recovery, termination with power, touchdown)
Hovering autorotation
Basic autorotations (power recovery, termination with power, touchdown)
Low flat glide autorotation
Low-level, high-speed autorotation (with power recovery, termination with power, touchdown) d.
Nap-of-the-Earth Maneuvers.
Training for the following low-level nap-of-theearth (NOE) aircraft maneuvers can be conducted:
Low-level navigation techniques
Hovering in and out of ground effect
NOE takeoff
NOE flight
NOE approach
NOE downwind takeoff
NOE downwind flight
NOE downwind approach
NOE navigation
NOE radio procedure
NOE quick stop
Masking and unmasking techniques
Scan and detection techniques e.
Gunnery Maneuvers.
Training for the following tactical gunnery maneuvers can be conducted:
Weapons cockpit procedures
Internal Boresight setting
Diving fire
Running fire
Diving to running fire
Low-level/NOE firing (combat sight setting)
Low-level/NOE firing
2-21.
SIMULATION SYSTEM CAPABILITIES.
Capabilities of the various areas and systems of the CMS are outlined below.
a.
Visual Area Navigation.
A simulated area of terrain 32 km by 40 km contains
28 navigation aids (radio stations).
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Change 2
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b.
Nav/Comm Radio.
Navigation and communication radio capabilities are provided
c. Tactical Environment.
Any of 15 different weapon loading configurations are available for firing at 10 active targets, five of which can be moving, selected from the targets available.
Appropriate weapon effects are used to enhance own weapons targets and threats.
d.
Atmospheric Environment.
The simulated environment can be controlled by the instructor to provide variable winds, turbulence levels (light, moderate, severe), gusts, temperature, and barometric pressure.
Temperature in degrees centigrade and barometric pressure in inches of mercury are displayed on the instructor/operator station (IOS) and are referenced at mean sea level.
The indications presented on the cockpit instruments, and as seen by the computer, are pressure altitude and temperature based upon application of standard lapse (2
O
C/1000 feet).
e.
Motion Cues.
A six-degree-of-freedom motion base provides motion cues of pitch, roll, yaw, heave, longitudinal, and lateral. The simulation is further enhanced by a seat vibration system for both the pilot and CPG seats. The seat vibration system can provide continuous and periodic oscillations and vibrations experienced during normal and emergency flight conditions, including progressive malfunctions.
Both motion and vibration can be selected or deselected at the IOS console CRT.
f .
Environmental Sound Cues.
Environmental sound cues are available at five levels of loudness and can be selected and varied at the IOS console CRT.
g.
Seat Positions.
Each flight simulator compartment provides seat positions for one trainee, an instructor, and an observer.
h.
Special Capabilities.
The CMS has some limitations that preclude its utilization for training in certain maneuvers.
The most serious limitation is in the area of visual field-of-view required for contact flight. On the other hand, the CMS provides the following unique capabilities that the operational aircraft cannot provide:
(1) Freeze simulator action at any instant.
(2) Initiate a training program at any one of 45 predefined locations within the game environment from which the flight can proceed.
(3) Reset to an initialization point that has been modified.
Reset is identical to initialization, indicated by freeze indicator blinking.
(4) Override an impending aircraft crash.
(5) Dynamically record and play back up to previous 5 minutes of a current f l i g h t .
(6) Insertion of up to 15 of approximately 336 malfunctions simultaneously.
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TM 55-6930-214-10
(7) Demonstrate prerecorded maneuvers automatically.
(8) Independent CPG task accomplished with the use of AUTO FLY.
(9) Monitor program progress and trainee performance.
(10) Freeze flight parameters selectively.
(11) Administer audio briefings automatically.
(12) Stop and abort a program at any time in event of emergency.
(13) Retrieve stored performance data via hardcopy printer/plotter.
(14) Fully control training program from IOS, or limited control from trainee cockpit station.
(15) View on IOS CRT end/or obtain hardcopy time history plots of airspeed, altitude, and ground track.
(16) Alter environmental conditions that act on the aircraft.
(17) Compute and display ground-controlled approach (GCA) commands.
(18) Train pilot and CPG in safety.
(19) Train pilot and CPG both independently and/or simultanously.
(20) Display up to 10 interactive hostile threats.
2-22.
VISUAL SYSTEM CAPABILITIES.
The full-color visual simulation system, combined with computer-generated visual effects, provides a realistic view of ground and sky conditions to the pilot and CPG trainees.
(Additional information on the
visual system and its capabilities is contained in Chapter 6).
2-23.
TRAINING TASKS.
Training of pilot and CPG trainees is carried out in either integrated or independent operating modes of visual, motion, and cockpit simulation.
The task of the trainees is to become thoroughly knowledgeable with all aspects of the pilot and CPG positions of the actual helicopter.
The instructor task is to maintain complete control of simulated conditions for training and to fully monitor trainee performance in all normal and emergency operational aspects of the helicopter.
a.
Simulated Aircraft.
The M-64 Apache is a twin-turbine-engine, four-bladerotor, high-performance attack helicopter with a two-man crew seated in tandem, the
CPG in front of the pilot.
The primary mission of this aircraft is that of an armed tactical aircraft with capabilities including weapons delivery, low-altitude high-speed flight, nap-of-the-earth flight, search and target acquisition, reconnaissance, multiple-weapons fire support, and troop aircraft support.
b.
Fliqht Control.
The simulated flight can be controlled by the following:
(1) By the pilot in the integrated mode with the CPG acting as CPG only, unless CPG control is selected by the master instructor.
2-26
Change 2
TM 55-6930-214-10
(2) By both pilot and CRG in the independent mode, each flying completely separate and independent aircraft.
(3) By the instructor via prerecorded demonstrations independent modes.
in either integrated or c. Trainee Tasks.
The task of a trainee in the CMS is to learn, practice, and verify the skills and knowledge associated with the pilot and CPG positions on the actual helicopter.
The CMS provides transition training, proficiency flying, weapons delivery practice, and the training of instructor pilots.
(1) through (3) (Deleted) d.
Instructor Tasks.
The task of the instructor is to facilitate and verify learning by the trainee crew.
Instructional and operational functions include:
(1)
(2)
(3)
Selection of mission or lesson plan.
Preflight briefing of trainees.
Demonstration of proper techniques and procedures.
Observation, monitoring, and critique of trainee performance.
(4)
(5)
(6)
(7)
(8)
(9)
(10)
(11)
(12)
Evaluation of individual or crew training needs.
Identification of areas that need coaching or more special practice.
Scheduled structuring of subsequent practice.
Preproblem setup of helicopter configuration and position.
Setup and modification of environmental conditions.
Random insertion and removal of simulated malfunctions.
Hardcopy recording of important aspects of trainee performance.
Monitoring and controlling operational status of simulator.
(13)
(14)
(15)
Serving as an air traffic controller when appropriate.
Act as other factors, i.e., remote designator on the battlefield.
Act as controller for threat forces.
Change 2
2-27
TM 55-6930-214-10
e.
Automation of Instructional Functions.
Many facets of the functions noted above have been automated, thus unburdening the instructor. An additional value of this automation is the standardization it provides. Among the more important features of the CMS in terms of automating instructor function are the following:
(1) Demonstration maneuvers. Demonstration of maneuvers and problems for the
CPG in which previously recorded pilot data is played back is available.
(2) Autofly maneuvers. When operated in the independent mode, the CMS is flown for the CPG through a prerecorded maneuver or series of maneuvers. This enhances the role of the CMS by performing for the CPG trainee without the presence of the pilot.
(3) Ground-controlled approach (GCA). Proper GCA instructions based on the simulated position are displayed on the IOS CRT. This enables the instructor to simply read them, rather than having to interpret graphic displays.
(4) Trainee scoring and evaluation.
Evaluation data is available to the instructor from CRT displays and from direct observation of the trainees and their instruments and indicators.
f .
Briefing. Briefings prior to training missions are live.
In this manner, the trainees are provided with an up-to-date report of what is expected throughout the mission.
Also, any unclear areas of the operation can be resolved with a question-and-answer session prior to beginning.
g.
Critique.
While a critique of trainee performance after a training exercise is not automated, it can be based on a comprehensive and standardized set of criteria.
The critique is aided by the available hardcopy records of trainee performance.
Such pictures are often worth the proverbial thousand words of instructor comment. A learning feature that can be most useful in critiquing is the 15-second to 5-minute dynamic playback of trainee performance. This can be accomplished either in real-time or in slow-time. Another function is the hardcopy print of graphic displays available at instructor discretion.
h.
Cueinq.
Cueing is sometimes defined as the provision of stimuli, usually of a secondary or faint nature, that guide the trainee to the correct response. Such cueing, sometimes called prompting, is of considerable value in programmed instruction.
Application of prompts, or cues, are gradually withdrawn or faded as learning progresses. Cueing has a somewhat different meaning in the context of the
2-28
Change 2
TM 55-6930-214-10
CMS. Cues for action are the stimuli normally present in helicopter flight, such as instrument and indicator readings, positions of cockpits controls, aspects of the out-the-window visual scene, cockpit motion and vibration, feel of the controls, and sounds associated with helicopter operations. These cues are simulated with a high degree of realism.
i .
Feedback.
Feedback to the trainee concerning the adequacy of the performance is provided in two ways: from the pattern of cues resulting from control reactions in the course of operation of the simulated helicopter, and from the measures of performance that can be made available after a training exercise.
Feedback during the exercise is provided by the cueing methods as described above.
Feedback after the exercise is provided by the scoring and evaluation hardcopy records.
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TM 55-6930-214-10
Section V. SYSTEMS SIMULATED
2-24.
GENERAL.
The aircraft systems simulated by the CMS are outlined in the following paragraphs.
Since each aspect of pseudo real-time simulation employs unique hardware and computer software programs to implement them, simulation details are not provided.
2-25.
ACCESSORY SYSTEMS.
The following aircraft accessory systems that provide operational status to the trainee are simulated by software via computer control:
Auxiliary power unit (APU)
Engine - fuel
Engine - oil
Fuel supply
Transmission - oil
Power train
Rotor
Electrical power system
Hydraulic system
Instrument indications
Weight and balance
Navigation and communication
Armament
Flight controls
Outside environment
Day, dusk, or night conditions
Digital automatic stabilization equipment
(DASE)
2-26.
SOUND SIMULATION. Analog generation under computer control provides the following sound simulation cues: a.
Aircraft Sounds.
The following aircraft sounds are simulated:
Engine
Transmission
Main rotor
Aerodynamic airflow
APU
Electrical generators
Hydraulic pumps
Environmental control system (ECS)
Forward avionics bay (FAB)
Taxi
Threat weapons
Crash b.
Weapon Sounds.
The following weapon sounds are simulated:
Aerial rocket control system (ARCS)
Point target weapon system (Hellfire)
Area weapons (M-230E1, 30-mm cannon)
2-27.
MOTION SIMULATION.
An electrohydraulic-actuated 6-post synergistic 6-degreeof-freedom (6-DOF) motion system under computer control provides the following cues:
Longitudinal displacement/onset cues
Lateral displacement/onset cues
Heave displacement/onset cues
Roll attitude/onset cues
Pitch attitude/onset cues
Yaw attitude/onset cues
Turbulence effects
Rotor out-of-track/balance effects
2-28.
VIBRATION SIMULATION.
An electrohydraulic seat shaker is used to transmit vibrational effects to the trainees while isolating the effects from other compartment-mounted hardware and occupants.
2-30
TM 55-6930-214-10
2-29.
COCKPIT INSTRUMENTATION SIMULATION.
All cockpit instruments and controls simulated are actual modified aircraft instruments.
They accept outputs from dc analog circuitry under computer control and respond with the desired deflections or rotations.
Three basic types of circuitry are used to drive the following classes of instruments:
Meter movement instruments
Servo instruments
Synchro instruments
2-30. RADIO COMMUNICATION AND INTERCOMMUNICATION SYSTEM (ICS) SIMULATION. The radio communications, guidance, and ICS systems simulated are listed and described
2-31. MALFUNCTION SIMULATION. There are 336 insertable, simulated malfunctions available. These malfunctions are divided into five systems: flight, circuit
breakers, communications, tactics, and navigation. (Refer to tables 7-15 and 7-16
for listing and descriptions).
2-32. CONTROL LOADING. The control loading system provides a realistic and responsive feel to the simulated helicopter flight controls. Electrohydraulic units combined with a mechanical linkage system produce control initiating and reactive forces.
Feedback from the simulation computer results in appropriate motions of the aircraft in flight. During a demonstration playback, the cockpit flight controls are driven by the computer and appropriately positioned in response to the motion of the aircraft.
WARNING
Flight controls may move abruptly upon system turn-on, initial conditions insertion, demonstration maneuvers or conditions store/ reset.
Keep clear of controls until neutral position is reached.
2-33.
ARMAMENT SYSTEMS.
Simulation for the following armament systems is provided:
M-230E1 30-mm area weapon system
HELLFIRE missile system
M-261 19-tube FFAR rocket launcher
Integrated helmet and display sight system (IHADSS)
Pilot night vision system (PNVS)
Optical relay tube (ORT)
Target acquisition and designation system (TADS)
Laser rangefinder/designator
Laser tracker
Video display unit (VDU)
Video recorder system (VRS)
Change
2-31/(2-32 blank)
TM 55-6930-214-10
CHAPTER 3
AVIONICS
3-l. GENERAL. Simulation for all onboard avionics equipment utilizes actual aircraft panel hardware backed up by applicable analog and digital processing and driver circuitry, all under computer control.
Operation of nearly all panel controls and indicators is simulated to depict actual equipment functions.
3-1 lists the avionics systems that are simulated in the CMS).
3-2.
COMMUNICATIONS EQUIPMENT.
Simulated radio communications are such that the two-way communication primarily takes place between the trainee(s) and the instructor(s). At the same time, electronics interfacing with the computer, which defines and controls some of the variables, allows for complete system flexibility. System power controls and indications, aircraft flight parameters, and simulated equipment failure commands are brought into the computer for processing. From these inputs, the necessary commands are then generated for the avionics and system-related equipment.
3-3.
NAVIGATION EQUIPMENT.
Navigation systems and equipment provide location and course-related information to the pilot and CPG via radio receiving links and instrument panel indications.
3-4.
RADAR AND TRANSPONDER EQUIPMENT.
The radar and transponder equipment is limited in simulation to provide status indications to either the pilot trainee or the instructor.
3-l
TM 55-6930-214-10
Class
Intercommunication
FM/AM Communication
FM/AM Comnunication
UHF Communication
Voice Security System
Automatic Direction
Lightweight Doppler
Navigation Set (LDNS)
Identification
Friend or Foe
Absolute Altimeter
Heading and Attitude
Reference Set
Table 3-1. Avionics Systems
Nomenclature Use
Intercomnunication System
C-11746(V)/ARC
Remote Transmit Select
Switch Indicator
ID-2403/ARC RTSS
Radio Set AN/ARC-186(V)
VHF-FM/AM No. 1
Intercommunication between crewmembers and control of navigation and communication radios.
Remote transmit select switch.
Two-way FM voice communications: FM and continuouswave homing in the frequency range 30 - 87.975 MHz plus AM 118 - 152 MHz.
Radio Set AN/ARC-186(V)
VHF-FM/AM No. 2
Radio Set AN/ARC-164(V)
UHF-AM
Same as No. 1 VHF-FM set except no homing capability.
Two-way voice comnunication with Have Quick function of in the frequency range 225 through 399.95 MHz.
TSEC/KY28 C-8157/ARC
Direction Finder Set
Doppler Navigation Set
AN/ASN-128
Transponder Set
AN/APX100(V)
Radar Altimeter
AN/APN-209
Secure communication for pilot FM radio.
Radio range and broadcast reception; automatic direction finding and homing in the frequency range of 100 to 3000 kHz.
Provides present position or destination navigation information in latitude and longitude (degrees and minutes) or universal transverse mercator (UTM) coordinates.
Transmits a specially coded reply to a ground-based IFF radar interrogator system.
Measures height above terrain or above ground level
(AGL).
LR-80 HARS
Senses helicopter attitude and motion to define roll, pitch, heading, and flightpath.
3-2
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TM 55-6930-214-10
CHAPTER 4
TACTICS
4-l.
GENERAL.
The CMS, having full mission tactical weapons capability, enables the pilot and/or CPG trainee to practice and improve proficiency in missions involving missile and rocket delivery and gunnery exercises. The following armament systems and components are simulated and interfaced with the computer via signal-conditioning equipment:
M-230E1 30-mm area weapon system
Point target weapons system (Hellfire)
Integrated helmet and display sight system (IHADSS)
Optical relay tube (ORT)
Pilot night vision system (PNVS)
Aerial rocket control system (ARCS)
Target acquisition and designation system (TADS)
Laser rangefinder/designator
Video display unit (VDU)
APR-39 radar warning receiver
ALQ-136 radar jammer
ALQ 144 IR jammer
M-130 chaff dispenser
Video recorder system (VRS)
4-2. VISUAL SIMULATION. The simulated environment consists of out-the-window displays for the pilot and CPG trainees with tactical targets in the visual scene.
Scorable targets of opportunity are provided in the visual scene at selected locations in the form of military vehicles or missile launching sites.
The display also portrays such weapon effects as rocket and missile flightpaths, weapon burnout, target or ground impact. The sensor displays also present similar effects for the pilot and CPG trainees with appropriate field-of-view and sensor-sighting directions. Reticles and symbology are included as necessary.
4-3. TRAINING. To initiate a problem, the pilot or CPG instructor can choose selected targets as movable targets that will be displayed on the ORT or out the window.
Velocity is under instructor control, and direction of the moving targets is along predetermined pathways in the visual scene.
Weapon loading is carried out by the instructor by means of IOS console CRT/keyboard action. There are 15 different weapon loading configurations available.
The current status of remaining armament is presented on one of the IOS CRT status area and is based on the initial conditions of the weapon loading configuration and weapons previously fired.
4-4. EVALUATION. The instructor is provided with weapon scoring data on a CRT page. The displayed data provides the number of rounds fired, hit/miss status, and miss distances, displayed as distance, long or short, left or right, and high or low, where applicable.
The aural cue system provides for simulation of normal and abnormal sounds that make up the cockpit acoustic environment. Weapon sounds include: ARCS, Hellfire, and area weapon system 30-mm guns.
Change 2
4-1/(4-2 blank)
TM 55-6930-214-10
CHAPTER 5
OPERATING LIMITS AND RESTRICTIONS
5-1. GENERAL. The CMS has a high degree of similarity to the actual helicopter.
Since the purpose of the CMS is for individual and crew proficiency and tactical training, certain operations and functions of the aircraft are simulated only partially or not at all. Those operations and functions that follow were determined to have very low or no applicability for the enhancement of pilot and
CPG training and proficiency. General items include the following:
Transparent canopy plexiglass is not present
Canopy removal arm/fire mechanisms are installed but nonfunctional
Pilot lighting control panel is functional but limited
5-2. AVIONICS. Comnunications equipment provides for instructor and trainee communications, but not actual signal reception or transmission. Discrete frequency radio communications channels are not available.
(Additional limitations
that exist with the avionics equipment are described in Chapter 3.)
5-3. TEMPERATURE AND HUMIDITY. The simulator compartments and motion systems are required to operate in a comfort-controlled environment at a temperature of 75
(±10)
O
F (18.33 to 29.44
O
C) at a 50 (±5)% relative humidity. The computer complex is required to operate in a controlled environment of 70 (±5) at a 50 (±5)% relative humidity.
O
P (18.33 to 23.88
O
C ) a. In the course of operation, variations in room temperature must not result in the development of relative humidity above 70% or below 30% at any temperature within the range from 50 to 100 O F (10 to 38 O C).
Temperature sensors in the equipment cabinets are capable of sensing two overheat temperatures.
At 100
Illuminate a light on the failure indications panel indicating that a particular cabinet location is in an overheat condition.
In addition, an aural warning is activated. If the overheating condition is not corrected, the entire CMS complex is automatically shut down when the temperature exceeds 110
O
F (44
O
O F (38 O C). they
C).
b. The internal temperature of the pilot and CPG CMS compartments is controlled by separate, dedicated air conditioners ducted at supplementary outlets within the compartment and the normal cockpit heating and defrosting ducts.
Separate thermostat controls are provided on the inside rear wall of each compartment.
The cockpit air temperature controls, although present, are nonfunctional.
5-4. OCCUPANCY. During simulated maneuvers, safety reasons require that occupancy of each flight compartment is limited to three persons: the trainee, an instructor, and an observer.
Use of seat belts is mandatory while in motion.
5-5. MOTION SYSTEM. For multiaxis motion, the maximum platform excursion values are given below with respect to a forward reference point.
These values are measured with respect to an origin established when the motion platform is considered to be at a neutral position: that is, with the hydraulic cylinder legs at midposition:
Vertical
Lateral
Longitudinal
33 inches up, 38 inches down
±58 inches
±53 inches
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TM 55-6930-214-10
Pitch
Roll
Yaw
31
±32
±32
O down, 36
O
O
O up
5-6. VISUAL SYSTEM. Two DIG systems are used in the CMS, differing only in the number of channels offered and in the hardware required related to that difference. The same software is used for both DIG’s.
a.
There are timing constraints or desired system performance to provide highdensity scenes with DTV and FLIR images at a 60-Hz rate.
b.
The DIG’s consist of a three-channel DIG system and a one-channel DIG system.
The three-channel system provides either a three-channel out-the-window (OTW) display or pilot night vision sensor (PNVS) video.
The one-channel system provides simulation of the three target acquisition and designation system (TADS) sensors: forward-looking infrared (FLIR), day TV (DTV), and direct-view optics (DVO). Since there are only two DIG systems, there are limitations on the number of visual displays that can be viewed simultaneously.
(Table 5-1 lists the displays available
in each cockpit during integrated or independent CMS operations.)
5-7. AUDIO SYSTEM. Once programmed, accompanying audio cannot be turned off while a demonstration continues.
Audio is not available during slow-time playback.
A l l aural cues are limited in loudness to within established safe levels of hearing.
Sounds associated with rain and hail are not provided.
5-8. IOS CRT-CONTROLLABLE PARAMETERS. The CRT display pages provide instructor control for aircraft environment, flight, and miscellaneous related parameters.
Selectable values for edit are limited within the range normally found in a realistic world or within the limitations of the actual helicopter.
a. Environmental Conditions. Selections of environmental conditions are limited as follows:
Barometric pressure
Outside air temperature
Wind velocity
Wind direction
Vertical wind gust
Horizontal wind gust
Turbulence level
V i s i b i l i t y
Ceiling
Cloud tops
Scud clouds
Random visibility
Icing enable
Horizon glow
28 to 31 inches Hg
-40
-40
O
O
C to +62
O
C
F to +252
O
F
0 to 30 knots in l-knot increments
001 to 360 degrees in l-degree increments
0 to 25 knots In 5-knot Increments
0 to 25 knots in 5-knot increments
0 to 5, 0 = off, 5 - max
0 to 99,999 meters
0 to 50,000 feet
0 to 50,000 feet
On/off
On/off (available only with visibility of 2000 meters or less) on/off
0 to 5, 0 - off, 5 - max
5-2
Change 1
1
2
3
CMS visual mode
Integrated
OTW
TM 55-6930-214-10
Table 5-1. Visual Display Availability
P i l o t
IHADSS
Symbol
IHADSS
PNVS
SYM
CPG
IHADSS
IHADSS TADS
ORT
HOD
VDU OTW symbol symbol HDD
Independent
4
5 a Includes operational monitoring capability (when pilot selects CPG monitor while CPG has DVO selected, a monochrome version of the DVO scene is provided on pilot IHADSS).
b
Duplicate imagery of pilot OTW.
c CPG views IHADSS symbology with or without TADS video.
d Either OTW and symbology or PNVS and VDU.
e Either TADS or PNVS.
b. Freezable Flight Conditions. During a training exercise, the following aircraft flight conditions are a direct result of the trainee flight inputs and are freezable only.
Altitude MSL
Airspeed
Heading
Fuel
Position
Roll
Pitch
Vertical speed
Conditions of yaw, torque pressure, and rate-of-turn are all interdependent flight parameters that assume in-turn conditions under software control and are not freezable.
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c. Editable Flight Conditions. Aircraft flight condition editable parameters are :
Fuel loading
Position
2509 pounds maximum
21s VK 80005000
21s WK 20005000
21s WK 20008200
21s VK 80008200 d.
Miscellaneous Conditions.
Parameter limits for related conditions are:
Sound level
Runway lights
VASI
Airbase cultural
Approach lights
Strobe
Beacon
Weapon load number
0 - 5, 0 = o f f , 5 = max
0 - 5, 0 = o f f , 5 = max cm/off
0 - 5, 0 = o f f , 5 = max
0 - 5, 0 = o f f , 5 = max on/off on/off
1 - 15
5-9. COCKPIT CIRCUIT BREAKERS. Circuit breakers on the ac and dc circuit breaker panels are functional and poppable.
5-10. ARMAMENT SYSTEM. Armament simulation is implemented so that the instructor must inform the trainee which weapon load configuration is in effect and that trainee actions and indications must be compatible.
In the aircraft, the backup bus controller assumes the task of providing weapons data if the fire control computer (FCC) fails.
In the simulator, the FCC is allowed to function and a warning light canes on to indicate the function.
5-11.
Deleted.
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5-12. INDEPENDENT MODE. This mode is limited as follows: a. Demonstrations cannot be dynamically recorded.
b. Deleted.
c. Instructors/operators cannot initiate malfunctions affecting the other cockpit.
d. The CPG instructor ray select VISIONICS POINTING and REMOTE DESIGNATIONS for the CPG.
e. AUTOFLY capability is available to the CPG cockpit.
f. The CPG has radio communications with the CPG instructor over the ICS, VHF, and UHF radios regardless of their operational status.
g. The CPG cannot affect electronic warfare threat environment.
h. Deleted.
5-13. INTEGRATED MODE. This mode is limited as follows: a. CPG visual is the same as the pilot front visual.
b. Either pilot or CPG instructor may be selected as master instructor with control and editing functions. The slave instructor has limited IOS control and editing functions.
Selection of CRT page displays without edit, and motion off, emergency stop, freeze, timer reset, edit malfunctions, and hardcopy request are available to the other instructor.
Master control can be assumed by or transferred to the other instructor at any time.
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5-5/(5-6 blank)
TM 55-6930-214-10
CHAPTER 6
VISUAL SYSTEM
6-1. GENERAL. The AH-64 CMS utilizes two digital image generation (DIG) systems to provide the necessary visual displays. A computer-generated data base provides a tactical gaming area and an airfield area of approximately 1,200 square kilometers (32 x 40 km). The gaming area is a generic terrain representation that was specifically designed to meet the diverse training requirements related to attack helicopter operations.
NOTE
Since these are only two DIG systems provided with the CMS, there are limitations on the number of visual displays that can
be viewed simultaneously. (Chapter 5 lists the displays
available in each cockpit during integrated or independent CMS operations.) a. Out-the-Window Displays. Each cockpit has three out-the-window displays
(left, front, and right). In the independent mode, each cockpit requires the use of its DIG system to provide OTW scenes. In the integrated mode, one DIG provides
OTW scenes to both cockpits but from the pilot’s perspective.
b. Sensor System Displays. The visual generation system has the capability of providing imagery to every sensor display in the CMS. These include the pilot
IHADSS with PNVS and symbology, the OTW scene, and the VDU. The pilot can also monitor the CPG TV or TADS FLIR on the VDU during integrated flight training. The
CPG has displays for IHADSS and ORT heads-down display (HDD), plus heads-out displays (HOD) for TV and FLIR.
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6-1/(6-2 blank)
TM 55-6930-214-10
CHAPTER 7
NORMAL OPERATING PROCEDURES
Section I.
CONTROLS AND INDICATORS
CAUTION
Due to abnormal shutdown possible hardware damage nay occur.
7-l. EMERGENCY STOP. Emergency stop switches are located on the various electronic cabinets throughout the CMS complex and at the trainee stations. These switches should not be used unless an actual emergency exists. Emergency stop, when depressed, removes facility power to the entire CMS complex, including the motion and visual systems.
a. The motion platform is returned to the settle position at the fastest practical speed by a quick-settle control valve if emergency stop is activated.
b. Emergency stop switches are at the following locations:
Instructor/operator station (IOS) console control panel
Trainee control panel
Linkage cabinet
Motion cabinet
Motion pumps
Power cabinet
7-2. MAJOR MODE SELECT. Major mode select permits the instructor a choice of integrated or independent training mode configurations for the CMS.
In the integrated mode, both CMS cockpits are electronically coupled and provide a simulated aircraft and environment for pilot and CPG training as a crew.
The instructor can select and designate from which IOS station to conduct and manage training.
This decision is based upon what the specific training objectives are for that training period.
In the independent mode, each CMS cockpit is an independent simulated.
aircraft, and training can be conducted in each cockpit without interfering with the other cockpit.
a.
Four switchlights on the left side of the IOS console control panel permit the selection and designation of the major mode of operation and training config-
uration for the CMS. (See figure 7-1.) The switchlights are IND, INTEG, PILOT
INSTR MSTR, and CPG INSTR MSTR. The IND/INTEG switchlights are used to select either independent or integrated mode of operation.
If integrated mode is selected, one IOS must be designated to be the master station (PILOT INSTR MSTR or CPG
INSTR MSTR). The raster station has control of the CMS instructional features that are used to establish and control the training process. When switching from independent to integrated, the master station function defaults to the CPG IOS.
b.
The following characteristics are related to major mode selection:
(1) Rode changes must be requested while in problem freeze.
(2) When a mode change is initiated from independent to integrated or vice versa, an automatic master reset occurs; that is, all temporary modifications,
TEE's, AMI’s, and IC’s are removed from the simulation.
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7 - l
TM 55-6930-214-10
(3) During integrated mode. the following switches are active only at the master IO station:
Condition store
Condition reset
Replay resume
Replay flyout
Replay slow-time
Flight command pilot
Flight command CPG
Master reset
Pilot instructor master
CPG instructor master
Left CRT
Right CRT
Status interchange
CRT interchange master station only refer to NOTE
Either IO can select the master IO function by depressing the
PILOT INSTR MSTR or CPG INSTR MSTR switchlight.
(4) In integrated mode, demos are active only at the master station.
(5) For AMI and TEE preps, the CPG IOS station must be the master.
c. The MODE select switchlights are used to prepare the CMS for crew training, to select independent training for pilot and CPG, and to designate which IOS will be the master station.
7-3. MOTION CONTROL. Motion controls are located on the IOS console control panel
(figure 7-1) and the trainee control panel (figure 7-2). Incorporated with the
motion control switchlights are a series of microswitch safety interlocks.
a. When the MOTION ON switchlight is depressed, the following microswitches must be closed for motion to come up:
Cockpit/instructor station entrance door
Door bar
Ramp
Right visual display
Service gates to motion areas
Cabinet doors located on motion platform
Pressure pads on platform floor b. The motion system immediately settles to a nonerect position if any microswitch interlock is opened during flight. The IOS console control panel has interlock warning lights to indicate any open switch during flight or before motion is activated.
7-4. FLIGHT COMMAND. The flight controls (cyclic, collective, and antitorque) in each trainee cockpit are totally independent and separate systems. In the independent mode of training, each set of controls works as in two different aircraft, and the computer responds accordingly to their outputs. However, when the CMS is
7-6
Change 2
TM 55-6930-214-10
Figure 7-2. Pilot/CPG Trainee Control Panel used in the integrated mode, separate systems do not work.
The computer must know which controls to receive outputs from.
The flight command (FLT CMD PILOT and FLT
CMD CPG) switchlights provide this function.
Flight controls may move abruptly upon system turn-on, initial conditions insertion, demonstration maneuvers or conditions store/ reset.
Keep clear of controls until neutral position is reached.
a. The FLT CMD PILOT or FLT CMD CPG switchlights are on the left side of the
pilot and CPG IOS console control panels (figure 7-1). A discrete switchlight is
provided for each trainee station.
When either switchlight is depressed, the corresponding set of controls provides flight control commands to the computer; other cockpit controls are inoperative.
b.
Characteristics of the flight command control system are as follows:
Active only in integrated mode
Active only at the master instruction station
Either switchlight can be activated while in freeze or on-the-fly
Inactive during playback, demos, and autofly c. These switchlights permit the instructor at the master station to designate which trainee will physically fly the simulated aircraft.
7-5. DATA ENTRY KEYBOARD. The data entry keyboard contains a set of alphanumeric and function keys that serve as the primary means of interface between the instructor and the CMS computer system.
a. The eight function keys on the keyboard (beginning at top left in figure 7-3)
are:
(1) PAGE RCL - Replaces currently displayed CRT page to which the keyboard is slaved with the most recently displayed page and displays the index and control for all pages if target status (page 30) has been fixed, using line 61 of page 150.
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7 - 7
TM 55-6930-214-10
(2) PAGE BACK - Replaces currently displayed page to which the keyboard is slaved with preceding page of a given file (e.g., replaces page 102 with page 101 or page 101B with page 101A).
(3) PAGE FWD - Replaces currently displayed page to which the keyboard is slaved with the succeeding page of a given file (e.g.. replaces page 102 with page
103 or page 101A with page 101B).
(4) CLEAR - Removes (erases) the edit/messages line of the CRT.
(5) BACK SPACE - Backs up one space on edit line.
(6) TAB - Used as a spacer/separator between fields of data entries: permits multiple data entries to be called prior to entry.
TAB also activates cueing information for subsequent data entries.
This data is displayed in the edit area prior to entry.
Only required for on-page editing.
(7) ENTER - Enters information typed on the alphanumeric keys into the simulation program.
(8) DISPL - Displays text/graphics as requested on the selected CRT using the alphanumeric keys.
b.
The data entry keyboard has functional software that provides interpretation for numeric keypad entries.
The interpreter accepts specific keypad entries as messages representing page numbers, item/line numbers, and/or data.
(Table 7-l provides the keyboard interpreter message types.) c.
The following format appears in the edit area during page editing:
KEYBOARD
ENTRY
NN AAAAAAAAAAAAA
= page number
= item/line number
= up to 16 digits in item label/title
= up to 10 alphanumeric characters in current value or state
= up to 10 alphanumeric characters in new value to be entered d.
UTM entries are two letters followed by eight or ten digits (US12345678). To enter letters via the data entry keyboard, two keystrokes must be made for each letter.
The first stroke designates the location of the letter on the key and is the left, center. or right column of the numeric keys. The second stroke selects the key on which the desired letter resides. In this manner, letters can be entered. All switches inputs are read as momentary Booleans by a routine that stores characters at a sufficiently rapid rate to permit the keyboard interpreter to receive all inputs.
e.
An example of letter entry is as follows (see figure 7-3):
(1) For an A entry, depress:
Key 1 for left column
Key 1 for A
7-8
Change 2
TM 55-6930-214-10
Figure 7-3.
Data Entry Keyboard Control Panel
(2) For a B entry, depress:
Key 2 for center column
Key 1 for B
(3) For a C entry, depress:
Key 3 for right column
Key 1 for C f. The data entry keyboard is on the IOS console control panel in each cockpit.
The instructors can use the data entry keyboard to:
Enter, delete, or modify data
Call up CRT pages for display
Clear the edit line
Enter or delete malfunctions
Enter initial conditions
Select demonstrations, TEE’s, autoflys, and record/playback
Enter UTM coordinates
7-9
TM 55-6930-214-10
Table 7-1. Keyboard Interpreter Message Types
For
Index display
Keystroke
N DISPL
Range of value
N = 0 to 9, 30
NNN DISPL NNN = 100 to 999 Page display
Displayed page
Boolean toggle NN ENTER or
NN TAB ENTER
NN = 01 to 99
NN = 01 to 99
(also displays label)
Displayed page data item change NN TAB NN ... NN ENTER
Nondisplayed page data item change
NNNOO NN ... NN ENTER
NN = 0 to 99
NN . . . NN =
(1) Reference #
(2) Real value
(3) UTM grid
NNN = 100 to 999
00 = 01 to 99
NN . . . NN =
(1) Reference #
(2) Real value
(3) UTM grid
Boolean feature NNNOO ENTER or
NNN = 100 to 999
00 = 01 to 99
Instructional feature activate NNN ENTER NNN = 100 to 999
7-6.
COMMUNICATIONS CONTROLS. The instructor communications control feature permits instructors to have complete control of the various communication networks available in the CMS. The controls permit discrete communications between the instructor, the observer, the pilot trainee, the CPG trainee, the computer room, and the other instructor station.
Additionally, the instructor can select and comnunicate with the trainees via the simulated VHF, UHF, and ICS systems. The control system includes a series of switchlights with identifying titles. The switchlights illuminate when in use, flash when being paged, and are off when not in use. Ten
of the simulator communication switchlights (figure 7-1) are on the pilot and CPG
COMM panel of the IOS console control panel.
The switchlight used to communicate with the computer room is on the right side of the forward control panel.
Rules and guidelines in the following paragraphs apply to the use of the CMS communications systems.
7-10
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TM 55-6930-214-10
a.
Instructor Private Communications (PILOT/CPG INSTR PVT, OBV PVT). The following criteria apply:
(1) Instructors can call and communicate with the other instructor or with their own observer.
(2) Either observer can call and communicate with either instructor.
(3) When a call is initiated by a keypress, the caller switchlight and the called party switchlight identifying the caller both flash.
(4) The flashing light is terminated by:
(a) The caller pressing the same switchlight.
(b) The caller selecting another interlocked switchlight.
(c) The called party answering the call by pressing the flashing switchlight.
(5) When the called party answers the call by pressing the flashing switchlight, both the caller switchlight and the called party switchlight are lit steadily, and a communications path between them is established. Actuation of push-to-talk switches on the headset cord is required to enable the audio gates.
(6) The lights are extinguished and communications terminated by:
(a) The caller pressing the same switchlight.
(b) The caller selecting another interlocked switchlight.
(c) The called party deselecting the call by pressing the caller switchlight.
(d) The called party initiating another call on an interlocked switchlight.
(7) The instructor (PILOT INST PVT or CPG INST PVT) PRIVATE COMM is functional in integrated and independent mode.
b.
Trainee Private Communications (PILOT PVT, CPG PVT). The following criteria apply:
(1) Either instructor can selectively communicate with either trainee.
(2) Private communications to trainees is operational in integrated and independent mode.
(3) The trainee PRIVATE COMM (PILOT PVT or CPG PVT) is an override function.
The instructor can communicate with the trainee regardless of trainee communications configuration.
(4) The instructor selects the desired trainee private communications switchlight. The pertinent switchlight is then lit steadily, and a private communications path to the trainee is enabled. Hot-mic operation is used.
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TM 55-6930-214-10
(5) The instructor deselects trainee private communications by:
(a) Pressing the same switchlight.
(b) Selecting another interlocked switchlight.
c. Trainee Monitor (MON PILOT, MON CPG). The following criteria apply:
(1) In integrated mode, either instructor and either observer can monitor pilot or CPG communications.
(2) In independent mode:
(a) Both the pilot instructor and the pilot observer can monitor pilot communications.
(b) Both the CPG instructor and CPG observer can monitor CPG communications.
(3) An instructor or observer initiates the monitor function by pressing the associated switchlight on the IOS COMM control panel. The selected switchlight is lit steadily, and the pertinent trainee headset audio is gated to the monitor input in the instructor or observer audio system.
(4) The light is extinguished and the audio monitor terminated when the instructor or observer presses the monitor switchlight that is lit.
d. Radio Communications (PILOT VHF, CPG VHF, UHF). The following criteria apply:
(1) In integrated mode:
(a) Either instructor can communicate with either trainee over one of the two ARC-186 (VHF) or over the ARC-164 (UHF), provided the sets are operational. A radio set is operational if the set and either ICS COMM box are powered up.
(b) The instructor initiates a call to a trainee by depressing the XMIT
(VHF, UHF) switchlight associated with the desired communications set.
(c) If the set is operational, the switchlight is lit, and the instructor mic audio is gated to the proper simulated radio receiver. Actuation of the instructor push-to-talk transmit switch is required.
(d) A trainee initiates a call on the desired set by configuring the cockpit set and COMM box properly and keying the press-to-talk switch.
(e) If the set is operational, the associated switchlight on both IOS COMM panels flash.
Trainee-to-instructor call audio is always enabled.
(f) The flashing light is terminated by:
1 The trainee releasing the press-to-talk switch.
2 Either instructor pressing the flashing XMIT (PILOT VHF or CPG VHF,
PILOT UHF or CPG UHF) switchlight.
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TM 55-6930-214-10
(g) The instructor who pressed the flashing XMIT switchlight sees the light become steady, and mic audio is gated to the proper simulated radio receiver.
(h) Subsequent press-to-talk actuations by the trainee while transmitting on that particular radio set do not cause flashing of the XMIT switchlight of that set at either IOS COMM panel.
(i) After one instructor has elected to answer the call, the other IOS XMIT switchlight neither flashes nor lights. Audio over the particular radio set is not enabled for the inactive instructor.
(j) The second instructor can get in the loop by selecting the same radio set XMIT switchlight on the COMM panel.
(k) If both instructors are in the loop, one can disengage from the loop without deselecting the whole loop.
(1) At the disengaged IOS, the light is extinguished, and audio for that radio set is disabled.
(m) Radio communication is terminated by the last instructor in the loop by:
1 Pressing the radio set XMIT switchlight.
2 Selecting another interlocked switchlight.
(2) In independent mode:
(a) The pilot instructor can communicate with the pilot trainee over the pilot ARC-186 (VHF) or ARC-164 (UHF) if the sets are operational, and over the CPG
ARC-186 (VHF) regardless of its operational status.
(b) The CPG instructor can communicate with the CPG trainee over the CPG
ARC-186 (VHF) if the set is operational, and over the pilot ARC-186 (VHF) and
ARC-164 (UHF) regardless of their operational status.
(c) The instructor initiates a call to a trainee by depressing the XMIT switchlight associated with the desired communications set.
Actuating the transmit switch completes the transmission loop.
(d) The switchlight is lit, and the instructor mic audio is gated to the proper simulated radio receiver:
1 If the selected radio set is operational where it is required to be operational.
2 If the selected radio set is to be used regardless of operational status.
(e) A trainee initiates a call on the desired set by configuring the cockpit set and COMM box properly and keying the press-to-talk switch.
(f) When the operational requirements for the set are met, the associated switchlight on the respective IOS COMM panel flashes. Trainee-to-instructor call audio is always enabled.
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TM 55-6930-214-10
(g) The flashing light is terminated by:
1 The trainee releasing the press-to-talk switch.
2 The instructor pressing the flashing XMIT switchlight.
(h) When the instructor presses the flashing XMIT switchlight, it becomes steadily lit, and mic audio is gated to the proper simulated radio receiver.
(i) Subsequent press-to-talk actuations by the trainee on that particular radio set do not flash the switchlight while it is selected.
(j) Radio communication is terminated when the instructor:
1 Presses the radio set XMIT switchlight.
2 Selects another interlocked switchlight.
e.
Intercommunications System (ICS) Communications.
The following criteria apply:
(1) In integrated mode:
(a) Instructors, observers, and trainees can all communicate via the intercommunication system (ICS), provided the sets are operational. Trainee sets are powered separately.
lights.
(b) Instructors and observers enter the system by pressing the ICS switch-
(c) When either ICS set is operational, the selected switchlight is lit, and caller mic audio is gated to the simulated ICS whenever the transmit switch is actuated.
(d) When a trainee transmits on an operational ICS set, the ICS switchlight on both instructor and both observer COMM panels flash. Trainee-to-instructor call audio is always enabled.
(e) The flashing light is terminated by:
1 The trainee releasing the press-to-talk switch.
2 An instructor or an observer pressing the flashing ICS switchlight.
(f) The instructor or observer who pressed the flashing ICS switchlight sees the light become steady, and mic audio is gated to the simulated ICS.
(g) Subsequent press-to-talk actuations by the trainee while transmitting on the ICS do not cause flashing of the ICS switchlight on any IOS or observer COMM panel.
(h) After a call has been answered, the ICS switchlights at the other COMM panels neither flash nor light. ICS audio is enabled only for the instructor or observer who has selected ICS.
7-14
TM 55-6930-214-10
(i) Any instructor or observer can enter the loop by pressing the ICS switchlight.
(j) If more than one instructor or observer are in the loop, any one can disengage from the loop without deselecting the whole loop.
abled.
(k) When ICS is deselected, the light is extinguished and ICS audio is dis-
(1) ICS communication is terminated by the last instructor or observer in the loop by:
1 Pressing the ICS switchlight.
2 Selecting another interlocked switchlight.
(2) In independent mode:
(a) The pilot instructor, pilot observer, and pilot trainee can communicate on the ICS, provided the pilot ICS is operational.
(b) The CPG instructor, CPG observer, and CPG trainee can communicate on the
ICS, provided the CPG ICS is operational.
(c) The effects of instructor, observer, or trainee switchlight selections and transmissions are as in integrated mode, except that such effects are confined to each cockpit.
f. Computer Room Communications.
The following criteria apply:
(1) The instructors can each communicate with computer area personnel, and vice versa.
(2) The COMP ROOM CALL switchlight on the IOS forward control panel (figure
7-4) is not interlocked with the other switchlights on the IOS console control
panel. This allows instructor communications to the computer area even while in communication with a trainee or another instructor.
(3) When an instructor presses the COMP ROOM CALL switchlight, the switchlights on the IOS COMM panel and on the computer room audio control panel flash and a chime sounds in the computer area.
(4) Computer room personnel can call either instructor by pressing the correspondingly identified switchlight on the computer roan audio control panel.
(5) When this happens, the COMP ROOM CALL switchlight at the COMM panel of the desired instructor, as well as the switchlight on the computer room audio control panel, flashes.
(6) The flashing lights are extinguished if the caller presses the switchlight again.
(7) The flashing lights become steadily lit when the called party answers by depressing the flashing switchlight. A communications path between them is then established.
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7-16
Change 2
Figure 7-4. Pilot/CPG IOS Forward Control Panels
TM 55-6930-214-10
(8) Lights are extinguished at both panels at the termination of a call; that is, when either the caller or the called party presses the switchlight. Communications are then disabled.
7-7. HARDCOPY. A hardcopy unit at each IOS can be accessed through a HARDCOPY
switchlight on the pilot and CPG console control panels (figure 7-1). The unit
accepts up to five requests for copy in rapid succession. The hardcopy unit is used to provide a copy of perishable information displayed on the selected CRT; to aid the instructor in subsequent review of trainee performance; and to provide objective information for permanent records.
Use of the hardcopy feature does not affect any aspect of the simulation except for the generation of the copy. This feature can be used independently of other instructional activities in progress.
7-8. LEFT CRT/RIGHT CRT. These switchlights allow the keyboard to be assigned to the left or right CRT respectively for page control, data entry, and hard copy.
7-8.1 STATUS INTERCHANGE. Status interchange allows for the selectable switching of the status pages between the two CRTs.
7-8.2 CRT INTERCHANGE. CRT interchange allows for the selectable switching of the main page area and index and control page areas together between the two CRTs.
7-9. INDICATOR LAMP TEST. There is one indicator lamp test switchlight on the
console control panel (figure 7-1) at each IOS. When depressed at either IOS, this
switchlight causes the illumination of all lamps on the console control panel and forward control panel at the respective IOS.
7-10. MASTER RESET. A master reset switchlight is located in the miscellaneous
section of the console control panel (figure 7-1) at each IOS. The master reset,
when depressed, deletes all temporary modifications to the simulation (e.g., all
TEE’s. AMI’s, and IC’s).
7-11. CPG AUTOFLY CONTROL. These controls are used to manually control heading and altitude of the CPG trainer during target engagement activities and weapons firing in the autofly mode of operation.
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a. The MANUAL switchlight on the console control panel allows the instructor to have manual control at hover points, to allow the CPG trainee more time to complete firing activities. Control of heading and altitude is accomplished by the use of a
4-direction joystick. Heading is accomplished by left or right movement, and altitude is changed by moving the joystick forward for up and backward for down.
b. Manual control can be activated any time prior to arrival, or while at a preselected hover location. This feature can be used to extend the period that the aircraft is unmasked beyond that which was originally recorded.
c. These controls are on the right side of the console control panel (figure
7-l) at the CPG IOS only.
7-12. LIGHTING CONTROL. This control varies intensity of switchlights on both control panels.
7-13. HEADSET VOLUME CONTROL. The headset volme control is a multiposition
potentiometer located on each console control panel (figure 7-1). When this poten-
tiometer is turned fully counterclockwise it allows minimum volume to the respective headset, and when turned fully clockwise it allows maximum volume to the respective headset.
7-14. STORE/RESET CURRENT CONDITIOUS. The store/reset (S/R) current conditions feature permits the CMS to be returned rapidly to a previously encountered set of simulated conditions. When activated, the store function places the current flight conditions into memory (temporary memory) for subsequent recall or reset. Only one set of conditions can be stored at any one time with this feature. The reset function returns (resets) the CMS to the flight conditions that existed at the time the store function was activated.
a. Controls for the S/R feature are on the forward control panel (figure 7-4) at
each IOS and on the trainee control panel (figure 7-2) on the left side of each
trainee cockpit. The store function can be used any time in or out of freeze. The reset function, however, can be accessed only while the CMS is In freeze.
b. Instructors can use the store reset current conditions function to enable rapid and easy reestablishment of the exact condition needed for a particular instructional activity, and to provide access to a modified IC set without having to repeat the modification process.
c. If no current conditions have been stored during a training period, activation of the reset function returns the CMS to the most recently selected IC set.
Selection of a new IC set automatically replaces any stored conditions.
d. If desired or required, a set of stored conditions can be either displayed, hardcopied, or saved as a temporary IC set. The following procedures will permit the instructor to:
(1) Display:
(a) Place the simulator in problem freeze.
(b) Activate RESET.
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(c) When flashing FREEZE light ceases, call up and display CC page 150.
(2) Hardcopy:
(a) Display CC page 150 on IOS CRT.
(b) Depress HARDCOPY switchlight on console control panel.
(3) Save as an IC set:
(a) After RESET is activated and flashing FREEZE ceases, call up and display any IC set.
(b) Use command lines 53 and 54 to save the set of conditions as a temporary
IC set at that IC set number. This temporary IC set is retained until a master reset is activated.
7-15. MALFUNCTION CONTROLS. There are two switchlight keys on the forward control
panel (figure 7-4) associated with malfunction control, MALF OVERRIDE and REMOVE
ACTIVE MALFS.
a. MALF OVERRIDE can be used to delete an impending AMI during the 10-second alert period before it is actually activated. This AMI is disabled for the duration of the training period and does not affect the remaining malfunctions in that AMI set. However, the overridden AMI can be manually inserted via the manual malfunction pages and the data entry keyboard.
b. REMOVE ACTIVE MALFS can be used to delete all active malfunctions, either manual or automatic, from the simulation.
7-16. CRASH/HIT OVERRIDE. The CRASH/HIT OVERRIDE feature freezes or suspends ongoing simulated activity when predetermined conditions are met. The effects upon the simulation and upon the cockpit and IOS controls of an automatically initiated freeze are identical to those of a manually initiated freeze. The purpose of the automatic freeze (AF) feature is to place the simulator in freeze immediately upon the occurrence of specified events, and to do so without intervention by the instructor, observer, or trainee.
a. Three kinds of events can trigger an automatic freeze:
(1) Entering a set of flight conditions that would be the equivalent of a crash (e.g., exceeding aircraft structural limits or impacting the surface at an excessive rate).
(2) Being impacted by sufficient hits from threat weapons (and the malfunctions associated with such hits) that crash conditions result.
(3) Encountering conditions that mandate placing the simulator In freeze
(e.g., preparing the simulator for an initial instructional activity or reaching the end of a period of recorded flight, i.e., DEMOS, AUTOFLY, PLAYBACK).
b. Since the initiation of a freeze condition resulting from such events may not be expected, its onset is called to the attention of the instructor via a flashing
PROB FREEZE switchlight, symbology on MAP pages, and an alert message appearing in the CRT alert block.
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c. The simulator can be released from freeze by insertion of a new IC set or depressing HIT OVERRIDE. However, in the case of an automatically initiated freeze resulting from the entry of the simulated aircraft into crash conditions, action must be taken to remove or overcome those conditions before the period of freeze can be ended. This can be done while the simulator is in freeze by selecting and inserting a new set of initial conditions preparatory to beginning a new training activity, thus effectively removing the aircraft from the conditions that led to the freeze. Alternatively, the instructor can elect to override the crash conditions and permit the flight to continue from the point of crash. When this alternative is selected, the simulated aircraft flies out of the crash conditions following termination of freeze.
d. In addition to standard crash conditions, automatic initiation of freeze occurs when the simulator threat-scoring algorithm determines that the simulated aircraft has received a sufficient number of rounds from an enemy weapon that aircraft systems are degraded to the point where an emergency landing is required and that landing is unsuccessful. When this occurs, the simulator enters the freeze state automatically and remains in that state until it is ended by removing the malfunctions. The instructor can also elect in advance to override the malfunctions associated with the threat algorithm in order to avoid frequent forced landings for an unskilled pilot. This is accomplished by engaging HIT OVERRIDE. When
HIT OVERRIDE is engaged, the effects of being hit, except aircraft degradation, occur (e.g., sounds and weapons signatures). Scoring and status information is displayed at the IOS. However, the aircraft continues to be flyable. The instructor can elect to override or not override hit or crash conditions.
e. Other events that automatically initiate freeze relate to administrative aspects of the simulator instructional process and provide an interruption in the simulation at points at which a decision must be made concerning the next instructional activity. No automatic freeze override function is appropriate with respect to these events, because their occurrence indicates a choice point at which a different activity must be initiated if the simulation is to continue. Such an event occurs when the simulator is initially made ready for use at the beginning of a period of instruction and at the end of a segment of recorded flight (e.g., upon completion of a demonstration or a selected interval of record/playback).
f. Controls for CRASH OVERRIDE and HIT OVERRIDE are alternate-action switch-
lights on the IOS forward control panels (figure 7-4). These switchlights are used
to prevent crash conditions, override a crash condition, and prevent aircraft systems degradation due to hits.
7-17. INSTRUCTOR VISUAL CONTROL. All controls for monitoring of the visual systems
are on the right side of the forward control panel (figure 7-4). These switch-
lights allow the instructors to monitor different types of displays depending on the mode of operation.
a. VIS L, VIS FRONT, and VIS R Switchlights. These switchlights allow the instructor to select the desired OTW display to be viewed on the overhead DVO/OTW monitor.
b. Unique CPG IOS Switchliqhts. The following switchlights are at the CPG IOS only:
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(1) MON PILOT VIDEO (active in the integrated mode only) allows the CPG instructor to view the current sensor system field of view being used by the pilot on map displays.
(2) CPG DVO allows the CPG instructor to monitor the CPG DVO display when it is being employed.
c. Unique Pilot IOS Switchlights. The following switchlights are at the pilot
IOS only:
(1) MON CPG VIDEO (active in the integrated mode only) allows the pilot instructor to view the current sensor field of view system being used by the CPG on nap displays.
(2) INDEP IHADSS ENABLE allows the pilot instructor to activate, but not monitor, the IHADSS in the independent mode only. This switchlight does not operate in the integrated mode of operation.
7-18. MANUAL FREEZE. Manual freeze (MF) enables the instructor or the trainee to freeze or suspend ongoing simulated activity. During the period of suspension, the simulated conditions existing at the onset of MF are preserved, and the suspended activity can be resumed at the option of the instructor or the trainee. Except for the primary flight controls, controls and displays at the IOS and in the cockpit retain their normal function during use of this feature and can be used to change the preserved conditions. During a period of freeze, cockpit avionics displays reflect the fixed position of the simulated aircraft, but otherwise function normally in response to operation of the controls associated with such displays.
a. The primary purpose of the MF feature is to permit interruption of the simulation so that other instructional or supporting activities can take place or to provide a break in the instruction. The secondary purpose of this feature is to provide a stable condition during periods in which the CMS is on but the cockpit can be unoccupied; thus allowing necessary setup or simulation modification functions to be performed through controls at the IOS. Cockpit ingress/egress also is possible during periods of freeze without concern for inadvertent movement of cockpit controls.
b. Controls for manual freeze are on the forward control panel (figure 7-4) of
each IOS and on the trainee control panel (figure 7-2) of each cockpit. In the in-
tegrated mode of operation, activation of the freeze control in either cockpit suspends activities in both cockpits. In independent mode of operation, activation of the freeze control in one cockpit has no effect on the other cockpit.
c. The manual freeze function is used to:
Temporarily interrupt an ongoing training activity to critique performance
Reposition the CMS for another instructional activity
Preserve Perishable CRT data while hardcopy is being used
Effect changes in the simulation
Access other instructional features d. A modification to the simulation that involves a discontinuity in any parameter affecting flight can be made only while the simulator is in a freeze state
(e.g., repositioning of the simulated aircraft or substituting one external visual display scene for another). Discontinuities involving visual displays require that
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such displays be blanked to minimize distractions to the pilot. Instructional features that are incompatible with simulated flight under pilot control can be initiated only when the simulator is in a freeze state (e.g., record/playback and demonstration). Likewise, use of the hardcopy feature when simultaneous copies of multiple displays are desired, can occur only when the simulator is in freeze. Use of other features, such as malfunction simulation, automatic malfunction insertion, and parameter freeze, can be initiated without respect to the freeze status of the simulator, but the effect of these features upon the simulation is noted only when the simulation resumes.
7-19. ELAPSED-TIME CLOCK (TIMER). The elapsed-tire clock is a digital display that, when activated, displays real-time in minutes and seconds. A discrete timer and controls are provided for each instructor. The timer can be operated independently at each IOS except during periods of the blinking PROBLEM FREEZE switchlight
( i . e . , except during periods of reset or changing simulator conditions).
a. The timer digital display is located in the upper left-hand corner of the main page area on one of the IOS CRTs. It is permanently displayed during training and remains so even during page changes. Zero minutes and zero seconds (00:00) are displayed until the timer is activated. Controls to operate the timer are on the
forward control panel (figure 7-4). A discrete switchlight is used to start and
stop the timer action. When activated (TIMER START/STOP depressed), the display counts real-time in seconds and minutes. When depressed again (TIMER START/STOP), the display maintains the last digits in a freeze state. When depressed again, it activates the display, and displayed time is cumulative. Additionally, A TIMER
RESET switch, when depressed, resets the minutes and seconds to zero.
b. The instructors use the timers to determine elapsed problem time, to relate errors to problem time, and to relate training events/activities to problem time.
7-20. REPLAY CONTROL. Four switchlights associated with the playback mode of operation are located in the lower right corner of the forward control panel
(figure 7-4). The switchlights operate as follows:
a. REPLAY RESUME allows the instructor to freeze the playback at any point and select RESUME. When selected, the simulator resets to the starting point of playback activation and permits training to continue from that point. When initiated.
the REPLAY RESUME switchlight illuminates, and the PROBLEM FREEZE switchlight flashes until initialization is complete and reset discrepancies have been cleared.
b. REPLAY FLYOUT allows the instructor to freeze the playback at any Point and select FLYOUT. When selected, training can continue from that point in the playback operation.
c. REPLAY SLOW TIME allows the instructor to slow the playback down, to allow more time for the trainee to grasp important relationships between control inputs and resulting instrument indications, aircraft attitude, and system performance.
slow-time playback takes twice as long to occur as real-time playback. There is no audio communications replay during slow-time playback.
d. REPLAY AUDIO OFF allows the instructor to turn audio on or off any time during real-time playback.
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7-21. INSTRUCTORS MONITORS. The instructor video monitor is a color CRT that pernits instructors to monitor selectively any of the three out-the-window (OTW) visual displays or the CPG direct view optics (DVO) display. The only time a video signal is available to monitor with this CRT is when the CMS is being operated in integrated mode with visual mode 2 (OTW & DVO), in pilot independent lode with
visual mode 5, or CPG independent mode with visual mode 4. (Refer to table 7-2).
a. The instructor video monitor is above the data graphic display CRT at the
IDS. (See figure 2-2). There is a power ON/OFF switch on the monitor. Controls
to select the visual display to be monitored are on the forward control panel. The
pilot instructor has three switchlights, VIS L, VIS FRONT, and VIS R, (figure 7-4)
for selection of the left, front, or right visual display. The CPG instructor has
four witchlights, VIS L, VIS FRONT, VIS R, and CPG DVO (figure 7-4). for selection
of the left, front, right, or DVO visual display.
b. The instructor can use the video monitor to selectively monitor either the pilot or CPG OTW field-of-view and to monitor DVO when the CPG trainee is employing that system.
CMS visual mode
2
3
Integrated
1
Table 7-2. Visual Monitor Display Modes
P i l o t
IHADSS
IHADSS PNVS
OTW symbo1 symbol VDU
CPG
IHADSS ORT
IHADS
TADS HOD
OTW symbol symbol HDD
Independent
4
5 a
Includes operational monitoring capability (when pilot selects CPG monitor while
CPG has DVO selected, a monochrome version of the DVO scene is provided on pilot
IHADSS).
b
Dup1icate imagery of pilot OTW.
c CPG views IHADSS symbology with or without TADS video.
d
Either OTW and symbology or PNVS and VDU.
e
Either TADS or PNVS.
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c. The TADS/PNVS monitor features include two black-and-white CRTs. Use of two
CRTs permit the instructor to monitor the FLIR sensor imagery (IHADSS, TADS/PNVS) and symbology being viewed by both pilot or CPG. The visual system permits the pilot/CPG to view one sensor display at a time; the instructor monitors are repeaters of both pilot and CPG displays.
d. The TADS/PNVS monitors are above the IOS CRT (figure 2-2). The TADS/PNVS
pointing information is displayed on CRT page 160. This page provides information related to the direction the TADS, PNVS or IHADSS being monitored is pointing; that is, the line-of-sight of the trainee using the sensor. The display indicates line-of-sight in degrees left or right of center, indicating the up or down view angle, and which field-of-view is being used: Z = zoom, N = narrow, W = wide, and
M = medium.
e. Instructors can use their displays to monitor/observe the pilot trainee PNVS
FLIR scene, to monitor/observe the CPG trainee TADS FLIR scene, to obtain data from the symbology displayed on the pilot/CPG TADS/PNVS displays, and to provide mission assistance to trainee during independent mode training.
7-22. TRAINEE CONTROL PANEL. These panels provide the trainees with limited con-
trol of simulator functions. The panel is located on the left canopy rail (figure
7-2) in each cockpit and contains six switches. These switches are identical to,
and perform the same functions as, the respective switches on the IOS consoles.
7-23. OBSERVER COMMUNICATIONS PANEL. The observer communications panel is on the
rear wall adjacent to the observer station (figure 7-5). Included on the panel are
an OBS HDST VOL knob to control the observer headset volume, and five communication
switchlights that are explained in paragraph 7-6. A separate headset jack, with an
audio preamplifier, is mounted in the ceiling above and behind the observer’s chair. The observer COMM panel and headset allows the observer to communicate with the trainee and the instructor at all times.
7-24. IOS CRT SCREEN DISPLAY. The instructor data graphics CRT display is composed of five areas that provide various types of information necessary for monitoring and controlling the simulation.
a. Main Page Area (Figure 7-6). This constitutes the largest portion of the CRT
page and is used to display pages of alphanumeric and graphic information. Pages are displayed in logical groupings containing common subject matter and are addressed via the data entry keyboard. These logical groupings make up a general index.
each having its own detailed mini index that lists the contents of that group. All directly addressable CRT pages have a unique 3-digit identifier or page number.
(Table 7-3 lists the groups and their respective page numbers.)
(1) CRT pages fall into two categories: editable, or modifiable; and noneditable, or fixed. The editable/modifiable pages contain listings that may be used as sets in their entirety and/or listings for which specific selections or modifications may be made. A page categorized as editable/modifiable has a reference line number for each of the items on that page that can be changed by the instructor.
Examples of such pages are:
Initial condition (IC) sets (pages 101 - 145)
Current conditions (CC) (pages 150 - 151) parameter freeze (page 160)
Playback control (page 470)
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Figure 7-5. Observer Communications Panel
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TM 55-6930-214-10
7-26
Figure 7-6. IOS CRT Screen Display
6
7
4
5
8
9
2
3
0
1
Display group
Table 7-3. General CRT Page Grouping subject
General Index
Initial/current conditions
Malfunctions
Graphics
Demonstrations/autofly/record playback
Targets
Navigation/communication
700 series Index
800 series index
Preparation and test
Paqe
100
200
300
400
500
600
700
800
900
TM 55-6930-214-10
Target control (page 580)
Visionics pointing/remote designator (page 581)
Target evaluation (page 583)
FARP control (page 592)
Malfunctions (pages 221 - 233)
Missing/independent mode (page 175)
(2) The noneditable/fixed pages contain listings and graphics that are used as is and cannot be changed by the instructor. The instructor can make selections from sane of these listings, but cannot otherwise modify the content of the programs listed. Many of these listings and graphics pages are used primarily to provide feedback or other information to the instructor. Listings from which selections can be made include:
AMI sets (pages 201-215)
Demonstrations (pages 401-420)
Autofly sets (pages 421-460)
Target engagement exercises (pages 501-520)
Target type list (page 531)
Target site list (pages 532-535)
Weapons loading/rocket configuration (pages 590 and 591)
Indexes (pages 100,200,......900)
(3) Listings and/or graphics pages that provide feedback or other information include:
Cockpit discrepancies (page 170)
Target status (page 530)
Target sites overview (page 540)
Battle position (pages 301-334, 541-574)
Map symbology (page 342)
Cross-country (X-C) (pages 340, 343)
Engagement performance (pages 595-596)
Threat weapons scoring (page 594)
GCA (pages 350-351)
Flight monitor (page 180)
Ownship weapon scoring (page 597)
Remote designation (page 582)
Threat scoring graphics (page 593)
(4) The first page of each group is the index page for that group (e.g., 100,
200, up to and including 900). The first digit of each page number identifies the grouping, and the second and third digits identify the page address within the group (e.g., the current conditions page (CC) is CRT page 150, the target control page is CRT page 580). In these examples, for CRT page 150 the 1 identifies the
IC/CC (initial/current conditions) grouping, and 50 is the address of CURRENT
CONDITIONS within that group. For CRT page 580, the 5 identifies the TARGET grouping, and 80 is the address of TARGET
CONTROL within that group.
(5) On pages containing data where selections can be made or the value of a parameter changed, there is a 2-digit line reference number for each selection or parameter. Thus, each datum has a unique 5-digit address consisting of its page number (the first three digits) and its line number (the last two digits).
Examples of the 5-digit address are shown below. In the first example, the line number 03 illustrates the selection of an item within a set, whereas the second
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example illustrates the line number of a parameter (airspeed) that may be changed if the instructor so desires.
Example 1: Number 22303
2
23
03
MALFUNCTION group
ENGINE SYSTEMS MALFUNCTIONS (Malfunction type #23)
#1 HOT START (Line #03 within engine malfunctions)
Example 2: Number 10103
1
01
03
IC/CC group
IC SET NUMBER 1 (Initial conditions set #01)
AIRSPEED line reference number (Line #03 within IC set #1) b. Status Area. The upper left-hand corner of the CRT display contains a status area. The status area displays a variety of information including mission elapsed time, mode of CMS operation, aircraft flight data, rotor and engine data, active malfunctions, weapons status, and communications channels in use. The information is updated continuously and allows the instructor to monitor key elements of the
status area. The top area includes mission elapsed time (MET), CMS mode, visual mode, and features in use. The second area depicts aircraft flight, rotor, and engine data: the third area, active manual malfunctions; the fourth area, weapons status: and the fifth area includes communications frequencies, trainee (student) identification, and threat event numbers. A second status area display includes the Alpha Numeric Display and the number of chaff remaining.
c. Index and Control Area. The lower left-hand corner of the CRT display is an
index and control area. Each major grouping of CRT pages has a mini-index (figure
7-8) that is usually displayed in the index and control area whenever any page from
the parent group is displayed in the main page area. The mini-index provides a ready reference to other items within the group during normal training operations.
On some occasions, the mini-index is replaced with a special reference list unique to the display in the main page area of the CRT. For example, whenever a GCA page is displayed, the index and control area contains reference numbers for keyboard inputs that initiate and terminate the GCA program at the airfield. In addition.
certain graphic CRT pages have reference lists for erasing or recalling ground track traces and for advancing the field-of-fire on the battle position pages.
d. Edit Area. The last three rows of the CRT display are an edit area (figure
7-6). This area echos or repeats all of the instructor keystrokes, prior to
entry. The edit area also displays operator error messages (e.g., keystroking a number beyond the established range of values for a given entry). Erroneous keystrokes can be deleted one item at a time via the backspace key, or the entire edit line can be deleted via the clear key.
e. Alert Area. The lower right-hand corner of the CRT display is for alert mes-
sages (figure 7-6). This area displays systems messages to the instructor. Examples
of the type of messages that appear in the alert area are: IC IN PROGRESS - when an IC has been entered and is being set up, this message appears in the alert area:
22303 #1 HOT START - when an AMI set is in use and a malfunction is triggered, a message similar to this appears for 10 seconds prior to insertion/activation.
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Item
MET
SIM MODE
VIS MODE
AMI; TEE; IC
REPLAY
FROZEN
ALT
Figure 7-7.
Typical CRT Page Status Areas
Table 7-4.
IOS CRT Status Area Data
Information
Hours, minutes, and seconds of mission elapsed time. The clock starts with Initialization and restarts with new
IC’S.
The MET halts during freeze and resumes after freeze.
Integrated (INTEG) or Independent (INDEP)
1, 2, 3, 4, 5 (Refer to IC pages and table 7-2.)
Displays the number of each set selected and entered into the simulation.
Indicates the demo, playback, or autofly program selected and time to completion of the program.
Indicates which parameters have been frozen, (up to eight parameters may be frozen, e.g., ALT, AS, HD).
Indicates radar altitude up to 1500 feet AGL.
Indicates altitude in feet MSL.
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Item
AS
VS
HDG
NR
TQ1
TQ2
MALFUNCTIONS
ROCKET (GND/OFF/NORM)
GUN (FXD/OFF/NORM)
MISSILE (ON/OFF)
COMM P
COMM C
STUDENT
EVENT
ALPHA NUMERIC DISPLAY
CHAFF REMAINING
Table 7-4.
IOS CRT Status Area Data - Continued
Information
Indicates airspeed in knots TAS.
Indicates vertical speed in feet per minute.
Indicates heading in degrees magnetic.
Indicates rotor rpm as a percent of maximum.
Indicates engine torque as a percent of maximum.
Indicates engine torque as a percent of maximum.
Indicates active malfunction number and title (up to six can be displayed).
Indicates position of pilot(P)/CPG(C) fire control selector switch and total rounds remaining for each system.
Indicates pilot VHF FM, VHF AM, and UHF radio frequency tuned on control head.
Indicates CPG VHF FM and VHF AM radio frequency tuned on control head.
Student (trainee) identification number entered by instructor via the data entry keyboard.
Indicates threat acquisition event number up to 99.
Each time a threat acquires the ownship, a sequential number appears here (1-99). To save this event data, a hardcopy of CRT page 594 must be made before event 13.
(Only the last 12 events are displayed.) or
Applicable alpha numeric display data repeated.
Number of bundles of chaff remaining.
7-30 Change 2
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Section II.
CRT PAGE DISPLAYS DESCRIPTIONS
7-25.
MINI-INDEXES.
The mini-indexes are displayed In the index and control area of each CRT page.
The type of CRT page called up determines whether a mini-index
(figure 7-8) is displayed. Any of the map pages, when displayed, have control in-
formation that is displayed In the index and control area instead of the mini indexes .
Any mini-index can be displayed at any time regardless of the type of CRT page currently displayed.
To display the available mini-indexes, key In 0 DISPL on the data entry keyboard.
This calls up the general index. Select the desired miniindex from the general Index, and key in n (where n - 0 - 9).
NOTE
Display pages Illustrated in this manual reflect display format only.
Conditions Indicated are typical and may not reflect a current operational condition.
0 INDEX
DISP
SUBJECT
1 INIT/CURR COND
2 MALFUNCTIONS
3 GRAPHICS
4 DEMOS/AF/RP
5 TARGETS
6 NAV/COMM
7 700 SERIES INDEX
8 800 SERIES INDEX
9 PREP & TEST
PAGE
100
200
300
400
500
600
700
800
900
Figure 7-8.
Mini-Indexes
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7-26.
INITIAL CONDITIONS.
Initial condition (IC sets (figures 7-9 and 7-10) are
preprogramed sets of operation configurations and geographical locations for the simulated aircraft.
The computer memory is capable of storing up to 45 permanent
IC sets.
The setup points associated with automated training programs (demonstrations) can also be used as IC sets.
In addition, the store/reset and record/playback features offer additional sources of initial conditions. Each IC set places the simulated aircraft in a specific geographical location and configuration (e.g., aircraft dead on the ramp, aircraft with engines running at an airport, aircraft airborne at 200 feet, etc.).
(A sample set of initial conditions is shown in
figure 7-10.) The IC sets provide a fairly broad range of starting points for
various instructional activities and save instructor setup time.
a.
If none of the permanent IC sets meets requirements. individual parameters can be temporarily changed by the instructor.
Each set of initial conditions contains items/parameters and three command lines.
For any sat of conditions (e.g..
the permanent IC’s. IC’s from auto training programs), the instructor
CM retain specific parameters and can modify the value of the remaining items; change X-Y location, add/delete fuel (at zero pounds of fuel, the engine flames out: amount of fuel onboard affects the center of gravity). change OAT, change wind direction (WD) and wind velocity (WV), etc.
In addition, the instructor can build a set of temporary conditions to wet a specific training requirement.
In this way, the instructor can design a temporary set of conditions to establish and control all parameters of the training period.
b.
Initial conditions sets are accessed through the keyboard at the IOS index of permanent IC sets appears on CRT page 100.
The specific characteristics of a given set can be displayed for review (or modification) by keying in its line number and depressing DISPL on data entry keyboard.
range of values for each parameter/item.) If review or modification is not necessary, an IC set can be entered directly into the simulation by keying in its 3digit identifier code and depressing ENTER. IC sets can be displayed for review at any time, but the CMS rust be in FREEZE to enter an IC.
c.
The initial conditions set is used to place the CMS in the desired geographical location and configuration to start training, to move the CMS to a new location and/or configuration during training, end to establish or modify a given
IC set to suit particular training needs (e.g., change altitude, airspeed, heading.
fuel weight, turbulence, etc.).
NOTE
multiple-page IC’s (101A. 101B, etc.) can be brought up by depressing the PAGE FWD switchlight on the data entry keyboard.
7-32 Change 2
TM 55-6930-214-10
Line number
09
27
28
29
30
21
22
23
24
25
26
01
03
04
05
06
07
08
31
32
Table 7-5.
Range of Values for Initial conditions Line Entries
Item description
Range of value
INITIAL CONDITIONS PAGE 101A
RADAR ALTITUDE 0 - 1500
AIRSPEED 0 - 299
Metric/
Increment
Feet AGL
Knots
HEADING
FURL
WEAPONS LOAD #
ENG STATUS
PRESENT POSITION
10 METER RESOLUTION
001 - 360
0 - 2509
1 - 15
ON/OFF
21S VK 8000 5000
Degrees
Pounds
UTM
21S VK 80000 50000
UTM
PRESENT POSITION
1 METER RESOLUTION
MAG VAR
VISUAL MODE
SCENE ILLUMINATION
VISIBILITY
CEILING
CLOUD - TOPS
HORIZON GLOW
00 - 99 E/W
1 - 5
1 - 11
0 - 99,999
0 - 50000
0 - 50000
0 - 5
Degrees
- -
SCUD
RANDOM VIS
FARP #
BAR0 PRESSURE
OUTSIDE AIR TEMP
WIND DIRECTION
ON/OFF
ON/OFF
1 - 10
28.00 - 31.00
-40 - +62
015 - 360
Meters
Feet MSL
Feet MSL
0 - off
5 - max
- -
- -
- -
Inches of mercury
Degrees of centigrade
15-degree increments
7-38 Change 2
TM 55-6930-214-10
Line
Table 7-5.
Range of Values for Initial Conditions Line Entries - Continued number
Item description
Range of value
Metric increment
INITIAL CONDITIONS PAGE 101 - Continued
33 WIND VELOCITY 0 - 30
34 VERTICAL GUST
0 - 25 l-knot increments
5-knot increments
35 HORIZONTAL GUEST 0 - 25
36
37
38
39
TURBULENCE LEVEL
SOUND LEVEL
ICING ENABLE
AIRBASE/CULTURAL
0 - 5
0 - 5
ON/OFF
0 - 5
S-knot increments
0 = off
5 = max
0 - off
5 = max
- -
0 - off
5 = max
40
41
RUNWAY LIGHTS
APPROACH LIGHTS
0 - 5
0 - 5
0 = off
5 = max
0 - off
5 = max
- -
42
43
44
45
VASI
STROBE
BEACON
FARP
ON/OFF
ON/OFF
ON/OFF
0 - 5
- -
- -
0
=
off
5 = max
46 TODENDORF AND
EXTRANEOUS BUILDINGS
0 - 5
0
5
=
off
= max
Change 2
7-39
TM 55-6930-214-10
Table 7-5.
Range of Values for Initial Conditions Line Entries - Continued
Line number
53
54
55
01 - 10
11
20,22,24,26
21,23,25,27
53,54,55
Item description
DOPP DEST
HOME
FCC WAYPT
ALT
Same as page 10lA
Range of value
INITIAL CONDITIONS PAGE 10lA - Continued
EXTRACT CURRENT
STATE AS IC
- -
SAVE DISPLAYED
DATA AS IC #
1 - 45
EXECUTE DISPLAYED IC
- -
INITIAL CONDITIONS WAYPOINTS PAGE 10lB
21S WK 2000 5000
21S VK 8000 8200
21S WK 2000 8200
0 - 9999
Metric/ increment
- -
- -
UTM
UTM
UTM
Feet d.
All FCC waypoints (lines 20, 22, 24, and 26) are programmable when operating the CMS In the independent mode.
(Refer to paragraph 7-57 for independent
mode/missing man operation.) e.
There are three command lines in the lower right-hand corner of each IC page
(lines 53, 54, and 55).
Lines 53 and 54 provide the capability to save the modified IC set for reuse during the training period or to save any position and state to which the simulator is flown during a period. Line 55 is the command line used to Insert a displayed IC into the simulated environment.
(1) Whatever current conditions exist or have been modified can be extracted as an IC by keying in 53 ENTER while in freeze.
(2) The conditions extracted In step 1 can now be stored in the numerical location designated and can be recalled during the remainder of the period by keying in 54 TAB _ _ (any number 1 through 45) and depressing ENTER. This temporary IC set replaces the set normally stored at that location.
(3) In changing from one IC set to another, it is possible to encounter a situation in which current switch and/or control positions art incompatible with those of the new IC.
When this occurs, an alert message appears in the CRT alert
area directing the instructor to call up cockpit discrepancy page 170 (figure
7-11): where specific discrepancies are Identified. These must be corrected before
the new IC can be accepted by the computer system.
If the instructor determines the discrepancy is not critical, depressing FREEZE causes it to override the discrepancy: however, a crash situation may result.
7-40
Change 1
TM 55-6930-214-10
7-27.
CURRENT CONDITIONS.
Current conditions pages 150 and 151 are lists of the current parameters and conditions of the simulated aircraft at any given time while it is being used for training.
Parameters being shown are identical to the initial conditions (IC) set while the stimulator is in freeze following initialization.
When out of freeze, the current conditions pages reflect the actual state of the simulator.
The status of each of the items/parameters is shown on the currant condi-
tions CRT pages (figure 7-12).
Items or parameters with line reference numbers can be modified during training. Host items/parameters can be changed while out of freeze. but to change others, the simulator must be in a freeze state to preclude discontinuities.
The current conditions pages contain the following categories:
Aircraft
Visual
Environmental
Lighting
Tactics
Miscellaneous
Doppler navigation
Waypoint/targeting b.
The first four categories cm page 150 are essentially the same on the current conditions page as in the IC sets.
The current conditions page located in group 1 (IC/CC) can be accessed via the data entry keyboard by keying in 150 DISPL.
(Ranges of values for each
parameter/item are listed In table 7-6.) To modify the following items/parameters,
the simulator must be In a freeze state:
Altitude
Heading
Weapons load
Present position
Present position
Line 01/02
Line 04
Line 06
Line 08
Line 09
10 meter resolution
1 meter resolution
NOTE
Random visibility (line 28) is available only if the visibility
(line 23) is 2000 feet or below.
NOTE
To change items/parameters when operating in the independent mode, refer to missing man operating paragraph 7-57 and missing man/independent mode display CRT page 175.
d.
Two categories of Information/control included on the current conditions page, but not on the initial conditions page, art tactics and miscellaneous.
(Refer to tables 7-7 and 7-8.)
e. Any set of current conditions can be saved temporarily by depressing STORE on the IOS forward control panel.
This data is then available for recall and relocation by depressing PROB FREEZE and RESET.
If the instructor desires to save more than one set of current conditions during a period. they can be saved by designating the sets as a temporary IC set.
Up to 45 IC sets can be temporarily saved.
To save a temporary IC set from current conditions, perform the following procedures:
7-42 Change 2
31
32
27
28
29
30
09
21
22
23
24
25
26
03
04
01
02
05
06
07
08
Line number
TM 55-6930-214-10
Table 7-6.
Range of Values for Current Conditions Line Entries
Item description
Range of value
Metric/ increment
CURRENT CONDITIONS PAGE 150
RADAR ALTITUDE
ALTITUDE
0 - 1500
0 - 9999
Feet AGL
Feet MSL
AIRSPEED 0 - 165 Knots
HEADING
FUEL
WEAPONS LOAD #
GROSS WT
001 - 360
0 - 2509
1 - 15
Degrees
Pounds
- -
21S VK 8000 5000
UTM
PRESENT POSITION
10 METER RESOLUTION
PRESENT POSITION
1 METER RES0LUTION
VISUAL MODE
SCENE ILLUMINATION
21S VK 80000 50000
1 - 5
1 - 11
UTM
- -
- -
VISIBILITY
CEILING
CLOUD TOPS
HORIZON GLOW
SCUD
RANDOM VISIBILITY
FARP #
BARO PRESSURE
0 - 99999
0 - 50000
0 - 50000
0 - 5
ON/OFF
ON/OFF
1 - 10
28.00 - 31.00
Meters
Feet MSL
Feet MSL
0 = off
5
= max
- -
- -
- -
OUTSIDE AIR TEMP
WIND DIRECTION
-40 - +62
015 - 360
Inches of mercury
Degrees centigrade
15-degree
Increments
Change 2 7-45
TM 55-6930-214-10
42
43
44
45
Line
Table 7-6.
Range of Values for Current Conditions Line Entries - Continued number
Item description
Range of value
Metric/ increment
CURRENT CONDITIONS PAGE 150 - continued
33 WIND VELOCITY 0 - 30
34
VERTICAL GUST
0 - 25 l-knot increments
5-knot increments
35 HORIZONTAL GUST 0 - 25
36
37
38
39
TURBULENCE LEVEL
SOUND LEVEL
ICING ENABLE
AIRBASE CULTURAL
0 - 5
0 - 5
ON/OFF
0 - 5
5-knot increments
0 = off
5 = max
0 = off
5 = max
- -
0 = off
5 = max
40
41
RUNWAY LIGHTS
APPROACH LIGHTS
0 - 5
0 - 5
0 = off
5 = max
0 = o f f
5 = max
VASI
STROBE
BEACON
FARP
ON/OFF
ON/OFF
ON/OFF
0 - 5
46 TODENDORF AND
EXTRANEOUS BUILDINGS
0 - 5
0 = off
5 = max
0 = off
5 = max
7-46 Change 2
TM 55-6930-214-10
Table 7-6.
Range of Values for Current Conditions Line Entries - Continued
Line number
Item description
Range of value
Metric/ increment
CURRENT CONDITIONS PAGE 150 - continued
53 WEAPONS DISPERSION
ON/OFF
--
54 CUM BORESIGHT ERROR
0 - 2
- -
55
56
CUM ERROR RESET
THREAT LETHALITY LEVEL
ON/OFF
0 - 10
- -
- -
57
58
HOSTILITY INTERRUPT
STUDENT ID #
ON/OFF
0000 - 9999
- -
- -
59
SEAT SHARER ON/OFF
- -
CURRENT CONDITION WAYPOINTS PAGE 151
01 - 10
11
12
13
DOPP DEST
HOME
FLY TO DEST
DROP ERROR RESET
21S WK 2000 5000
21S UK 2000 5000
Select # or H
UTM
UTM
UTM
-
20,22,24,26,28,
30,32,34,36,38
FCC WAYPOINT 215 VK 8000 8200
UTM
21,23,25,27,29,
31,33,35,37,39
ALTITUDE 0 - 9999 Feet
40
41
TGT WAYPT SEL
SLAVE TO TGT WAYPT
0 - 9
ON/OFF
-
NOTE
Lines 12, 40, and 41 are for use In the independent mode to allow PLT IOS access to doppler navigation and FCC waypoint/ targeting information.
When accessing lint 12, PLT IOS receives proper command steer Information on HMD, VDU, and HSI for the number selected.
When accessing line 40, FCC is alerted to respond to line 41 activation.
When line 41 is turned on, PLT
IOS receives proper TADS slaving information on HMD, VDU, and
HSI for the number selected on line 40.
Change 2 7-47
TM 55-6930-214-10
Title/line No.
Table 7-7.
Tactics Current Conditions
Function/use
WEAPONS DISPERSION ON/OFF This Instructor-controlled line item permits turning
Line 53 weapons on or off and affects the 30-mm and 2.75 FFAR.
In the OFF position, each round fired impacts In the same position, with all variables (flight, environment, range etc.) being equal.
In the ON position, rounds impact in a random pattern in and around the impact point consistent with a standard dispersion pattern and limits for the specific weapon. To use, key in 53
ENTER.
CUM BORESIGHT ERROR
OFF/SLOW/FAST
Line 54
CUM ERROR RESET ON/OFF
Line 55
This line permits the instructor to insert a cumulative boresight error at a SLOW or PAST accumulation rate.
When error is present, the trainee Initiates boresighting procedures by moving the boresight enable switch to the UP position.
The trainee boresight procedures can then be monitored by the instructor. In the OFF position error accumulation stops, but error may still exist.
To use, key in 54 TAB 1 for SLOW error accumulation or 54 TAB 2 for FAST error accumulation.
This line permits the instructor to clear any accumulated boresight error.
THREAT LETHALITY LEVEL
Line 56
This line permits the instructor to increase the possibility of a hit being scored on the ownship. Range of values is from 0.0 through 10.0 in increments of
1.0.
The normal iniltialization value of threat lethality when threat lethality is ON is 5.0. To reduce the possibility of a hit on the ownship, change the threat lethality to a lower value.
To increase the chance of a hit, change the threat lethality to a higher value.
To use, key in, as an example, 56 TAB
5.0 ENTER.
HOSTILITY INTERRUPT ON/OFF When ON and the threat weapon acquires the ownship, the
Line 57 threat algorithm analyzes the variables (LOS, exposure time, range, use of backdrop, and ASE equipment) to determine the possibility of a hit. When OFF, hostile activities are temporarily suspended for all active threats except that search radar is still active. To use, key in 57 ENTER.
7-48 Change 2
TM 55-6930-214-10
Title/line No.
STUDENT ID #
Line 58
SEAT SHAKER
Line 59
FIXED INDEX PG
Line 61
TRNG SEL GUNNERY/TARGET
CLEAN/THREAT
Line 62
Table 7-8.
Miscellaneous Current Conditions
Function/use
This line permits the instructor to enter the last four digits of the trainee’s social security number. The number, when entered, is displayed in the status area of the CRT display and appears on any hardcopies of CRT displays printed during the training period. To use, key in 58 TAB nnnn (where nnnn - 0001 - 9999)
This lint permits the instructor to turn the seat shaker on or off.
To use, key in 59 ENTER.
Calls up desired index page 30. To use, key in 61
TAB n ENTER, where n = desired index page.
Toggles between GUNNERY/TARGET and CLEAN/THREAT.
Instructor has the capability of electing a weapon load and engaging the target.
In CLEAN/THREAT, no weapon load is selectable: only dummy loads. Threat targets have interaction on the ownship. Line 62 is accessible only in the independent mode.
To use, key in 62 ENTER.
(1) Depress PROB FREEZE.
(2) Key in and display any IC set (pages 101 - 145) (example: 145 DISPL).
(3) Use command line 53 (i.e., key in 53 ENTER); this extracts the current conditions as an IC.
(4) Key in 54 TAB 45 ENTER; this temporarily inserts the set of current conditions in place of IC set 45 on page 145. The condition remains in storage until a raster reset is performed.
7-28.
PARAMETER FREEZE.
Parameter freeze (PF) enables the instructor to freeze one or more of the flight parameters to current value(s). When a parameter is in freeze state, all other parameters are unaffected. However, all simulator performance and the displays at the IOS reflect the fixed value of the frozen parameter.
A parameter can be frozen without respect to whether or not the simulator is in freeze.
Thus, a parameter frozen while the simulator is in freeze remains in the freeze state when the simulator freeze is ended.
a.
Parameters that can be frozen by the instructor art:
Altitude
Airspeed
Heading
Fuel
Position
Roll
Pitch
Vertical speed
Change 2 7-49
TM 55-6930-214-10
b.
The parameter freeze feature is accessed through CRT page 160 (figure 7-13)
on the IOS CRT.
Parameters that can be frozen art listed by lint number.
To freeze a given parameter, key in its line number at the keyboard and depress ENTER. To unfreeze a frozen parameter, repeat the process.
The parameter freeze page includes two command lines at the bottom, lines 88 and 99. To freeze all parameters simultaneously, key in 88 ENTER.
To clear all frozen parameters, key in 99 ENTER.
If all parameters are frozen, individual parameters cannot be selected to be unfrozen.
Parameters that have been frozen art displayed in the status area of the CRT.
C.
The parameter freeze feature is used to freeze one or more parameters. to reduce trainee task load, to assist the Instructional staff in preparing demonstrations and autofly programs, and to freeze all parameters.
d.
In the independent mode of operation, freezing a parameter in one cockpit has no effect on the other cockpit.
In integrated mode of operation, freezing a parameter In one cockpit also freezes it in the other.
e. The systems restore controls permit the Instructor to restore a system to its basic state.
The systems that can be restored are charge battery (line 21), charge hydraulic accumulator (line 22), align HARS (line 23). and cool FLIR (line 24).
Use restore all systems (line 77) to Instantaneously restore the above items (lines
21 through 24).
f .
The TADS/PNVS point Indicator display will display point indicator information.
It will display TADS, PNVS, or IHADSS, based on user selection.
Field of view will display N, M, W, or Z, for narrow, medium, wide, or zoom selections.
In addition, the pilot or copilot azimuth and elevation angles are displayed.
No pilot or copilot information is displayed when power is off or no selections were made.
7-29.
PLIGHT MONITOR.
The flight monitor page is a display-only page for monitoring 34 different flight parameters.
This page allows the instructor to evaluate trainees performance during the simulation process.
The flight monitor page
(figure 7-14) is accessed through the data entry keyboard by keying in 180 DISPL,
and is included on the IC index page.
7-30.
VISUAL MODE HELP PAGE.
This Page is a display-only page (figure 7-15) used
in conjunction with the IC and CC pages to aid the instructor in determining the correct visual mode for the type of training to be accomplished, either integrated or independent.
This page displays visual resources for both the pilot and CPG.
The visual mode help page is in group 1 (IC/CC) and can be accessed via the data entry keyboard by keying in 190 DISPL.
7-31.
NAVIGATION/ COMMUNICATIONS.
The nav/comm facilities pages 601 and 602 define each navigation and communication facility in the gaming area.
Each facility is defined by the following:
ID/name
Type
Frequency
Location
Status
a. The nav/comm facilities pages (figures 7-16 through 7-18) are in group 6
(NAV/COM) and can be accessed via the data entry keyboard by keying in 601 DISPL.
CRT page 602 can be accessed by depressing PAGE FWD or by keying in 602 DISPL.
7-50
Change 2
TM 55-6930-214-10
b .
e . g . ,
To activate/deactivate a facility, key in the facility number and ENTER keystroke 05 ENTER). This process toggles the status indication on the CRT page. This can also be performed on the tactical instrument gaming area page display (CRT page 341), in the index and control area.
Nav/comm facilities can also be viewed graphically on the tactical instrument gaming area page display (CRT page 341).
7-31.1.
UHF-AH Have Quick Radio.
The UHF-AH Have Quick radio is page number 610
This page can be accessed directly by keying in 610 DISPL, or by pressing PAGE FWD from page 602.
a.
The page contains seven lines which are editable by the instructor. These are :
Day of the month (Specifies WOD)
Frequency selection
Anti jam mode selection
Satellite active
Time of day manual entry
Time of day mismatch
UHF jamming signal b.
In addition, the following are displayed at the IOS, but are not editable:
Jammed frequency
Required word of day frequency for channels 15 to 20
Pilot entered word of day frequency for channels 15 to 20
UHF frequency selection
Pilot and CPG VHF frequency selection
Change 2
7-50.1/(7-50.2 blank)
TM 55-6930-214-10
7-32.
BATTLE POSITION MAPS.
The battle position map CRT pages are information displays that provide graphic data related to battle/firing positions and associated target sites and provide the instructor with a 12- by 12-km graphic overview of the ownship and the target engagement area of interest.
a.
There are 34 designated battle positions included in the visual gaming area-
(Figure 7-19 is a typical battle position MP CRT page 325.) These battle posi-
tions each include from one to eight firing positions.
The battle positions are designed in 1-kilometer squares and should be entered from only one side of the square kilometer.
The battle position is composed of relatively high terrain that overlooks target engagement areas (low terrain containing target sites). Within each battle position are nap-of-the-earth (NOE) routes leading to the firing positions.
b.
The battle position raps are always oriented on the CRT display so that magnetic north is up.
Each battle position map shows the battle position by number and all of the active target sites within its area of view.
Since each battle position has one or more firing positions, several fields-of-fire are available to the trainee.
Each battle position has been designed with eight selectable fieldsof-fire for the instructor to choose from when viewing the target sites in the target engagement areas.
c .
The battle position map CRT pages are in group 3 (GRAPHICS) and can be accessed via the data entry keyboard (CRT pages 301-334).
In the index and control area of the CRT page when battle position maps are displayed, control reference numbers are provided to permit selection of fields-of-fire.
When the page is first called up, the field-of-fire is defaulted to the entry point.
Each battle position has only one entrance side, shown on the map with an index.
Starting in the upper right corner of the battle position, the fields-of-fire are numbered 1 through 8 in a clockwise direction.
In the control area, reference number 01 is the command far selecting the FIELD OF FIRE number. Reference numbers 02 and 03 are aircraft TRACK
ERASE and TRACK RECALL. respectively.
Reference number 01 can be entered via the data entry keyboard while the map is displayed (e.g., 01 TAB 6 ENTER), and causes the viewing direction of the field-f-fire to change for the specified battle position.
As fields-of-fire are selected (advanced), the map automatically repositions in relation to the battle position to maintain the maximum field-of-view in the direction of the field-of-fire (i.e., when field-of-fire 6 is selected, the battle position is displayed on the left side of the CRT page and centered vertically: when field-of-fire 2 is selected, the battle position is displayed on the right side of the CRT page and centered vertically).
d.
The selected sensor system field-of-view is graphically shown by two radii from the ownship, at the battle position, out to 10 kilometers. The angle subtended between the radii is representative of the field-of-view selected for the sensor system (i.e., wide, narrow, medium, or zoom). The radii are dashed lines with a dot every kilometer.
e .
When targets have been selected and positioned on the target sites within a battle position map, target symbols appear on the map.
When intervisibility or LAB exists between the ownship and any target(s). the target symbol(s) illuminate in high intensity.
f .
Battle position map displays can be used to determine which target sites are in proximity of a battle/firing position, observe the relationship between ownship
7-56.2
Change 2
TM 55-6930-214-10
and active targets, observe graphically when intervisibility exists between the ownship and targets, and determine range from ownship to active targets.
g.
The remote designator will be displayed if activated and within the confines of the map.
Change 2 7-57
TM 55-6930-214-10
7-33.
CROSS-COUNTRY MAP.
The cross-country map display is a graphic display of the visual gaming area.
It is a horizontal area plot displaying background map data and traces of the aircraft route of flight.
It permits the instructor to monitor certain trainee activities and provides information in a graphic form that would be difficult, if not impossible, to provide via standard text.
a.
The cross-country map (figures 7-20 and 7-21) includes the following
characteristics:
(1) Prominent terrain features.
(2) Active targets (see target symbols).
(3) FARP locations (see symbols).
(4) Two-scale capability:
12 x 12 kilometers with zoom off
6 x 6 kilometers with zoom on
(5) Automatic recentering of ownship.
(6) Ownship ground track trace that provides:
(a) 2O-minute track history.
(b) 3-minute time marks (see symbols).
(c) Event marks along track for:
Malfunctions
Exceeding structural limits,
Object/tree strikes
(d) Track erase.
(e) Track recall.
(7) Ownship symbol.
(8) Remote designator When active and within the confines of the map.
NOTE
Zoom, track erase, and track recall controls are in the index and control area.
b.
The cross-country map display is in group 3 (GRAPHICS) and can be accessed via the data entry keyboard by keying in 340 DISPL.
Change 2
7-59
TM 55-6930-214-10
C.
The instructors can use the cross-country map displays to:
Monitor trainee enroute location and route
Maintain general orientation in visual gaming area
Monitor relationship between ownship location and threat
Record locations of object or tree strikes
Record periods of intervisibility and exposure to threat weapons
Show malfunction occurrences
Critique/debrief trainee performance via hardcopy feature d.
When intervisibility exists between the ownship and the target(s). the target symbol is shown in high intensity on the cross-country map.
7-34.
TACTICAL INSTRUMENT GAMING AREA DISPLAY.
The tactical instrument gaming area display is a graphic overview of the instrument navigational and approach facilities available in the gaming area.
It provides the instructor with the capability of monitoring the trainee tactical Instrument route of flight.
a.
The display (figures 7-22 and 7-23) includes the following characteristics:
(1) Symbology for nondirectional radio beacons.
(2) Symbology for GCA facilities.
(3) Two scales with a zoom capability (when zoom is on, CRT main page area is cleared, except for ownship symbol):
40 x 32 kilometers with zoom off
6 x 6 kilometers with zoom on
(4) Ownship ground track trace which provides:
(a) 20-minute track history.
(b) 3-minute time marks.
(c) Event marks along track for:
Malfunctions
Exceeding structural limits
Object/tree strikes
(d) Track erase.
(e) Track recall.
(5) GCA select NO.
(6) GCA cancel.
(7) Activate NDB number.
(8) Fail NDB number.
7-62
(9) Remote designator.
Change 2
TM 55-6930-214-10
b.
The display is in group 3 (GRAPHICS) and can be accessed via the data entry keyboard by keying in 341 DISPL.
C.
Instructors can use the displays to:
Monitor trainee instrument route of flight
Note locations of object or tree strikes
Show malfunction occurrences during instrument flight
Locate and vector ownship to GCA facility
Select or cancel GCA facility
Critique/debrief trainee performance via remote display or hardcopy feature
Activate/fail NDB sites
7-35.
MAP SYMBOLOGY.
The map symbols shown on the CRT map displays are graphic representations of specific items or objects.
They have been provided to enhance the informational value of the map displays and provide timely feedback to the instructor.
a.
Types of symbols include the following:
Targets
Target site
FARP location
Navigation aids
Ownship
3-minute time mark
Malfunction
Crash
Prominent points
K i l l
Remote designator with 1 km markers
Illumination round burst
Weapon impact points b.
The map symbology CRT display (figure 7-24) lists and shows all the available
symbols.
The symbols appear on the following graphic display pages:
Target site overview (page 540)
Target site pathway detailed display (page 540)
Battle position target site (pages 541 - 575)
Cross-country map (page 340)
Tactical instrument gaming area (page 341)
GCA (pages 350 - 351)
Gaming area map (page 343)
Battle positions (pages 301 - 334)
Ownship weapons scoring (page 597)
Remote designator (page 582)
The map symbology page is in group 3 (GRAPHICS) and can be accessed via the
data entry keyboard and keying in 342 DISPL. (Figure 7-25 illustrates the map
symbols employed in the CMS, shown larger than actual size to aid in identification.)
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Figure 7-25.
Typical Map Symbols (Sheet 1)
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7-68 Change 2
Figure 7-25.
Typical Map Symbols (Sheet 2)
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d.
The symbols art used to:
Identify target types and sites
Identify FARP landing areas
Identify PM transmitters, NDB’s, and GCA sites
Identify ownship location
Identify locations of malfunction occurrences
Identify location and cause of crashes
Obtain tine checks along route of flight
Identify the 1 km points on the range lines on the ownship weapon scoring and remote designation pages.
Identify the burst location (illumination round only)
Identify the weapon impact locations
7-36.
GCA PLOTS.
The ground-controlled approach (GCA) display is a stylized representation of the precision approach radar (PAR) glideslope and centerline.
The simulated progress along both paths is displayed using a symbol for the ownship and a track trace.
The GCA display provides computer-generated command information required to conduct the final controller portion of a simulated GCA approach. Instructions appearing in the command box on the CRT reflect simulated aircraft position with respect to the final approach path to the runway. The display provides the instructor with a graphic display of the aircraft location in relation to the glideslope and centerline for the approach runway and the alphanumerical commands to be used by the instructor to conduct the GCA.
a.
The GCA displays are on CRT pages 350 (figure 7-26) and 351 (figure 7-27).
These displays include the following information and characteristics:
Glideslope and centerline deviation track
GCA commands - correction to course, corrections to glideslope
Two scale displays:
10- and 2-nmi
GCA selection and cancellation in index and control area b.
The GCA display pages are in group 3 (GRAPHICS) and can be accessed by keying in 350 DISPL via the data entry keyboard.
Access CRT page 351 by depressing PAGE
FWD or by keying 351 DISPL.
Before calling up the GCA display, the instructor can use the tactical instrument gaming area map to vector the simulated aircraft into the approach course corridor.
The NDB can also be used to vector the aircraft into the approach corridor.
The GCA window or corridor is approximately a 4500-foot square at 10 nmi on the approach side of the runway extended centerline.
The instructor can use the GCA display to conduct GCA approaches to the airfield, to supplement information derived from cockpit instruments and the status area display, and to critique/debrief trainee GCA performance via the remote display or the hardcopy feature.
C.
There is only one GCA available, facility No. 52, runway 20, at the airbase.
When CRT page 350 is displayed, the index and control area contains command reference lines.
To activate the GCA program, key in 01 TAB 52 ENTER on the data entry keyboard.
Line 02 permits the instructor to cancel the GCA program. GCA can also be activated by using page 602 line 52 or page 341 line 4. Alternately, the GCA program automatically turns off when the ownship is 15 km outbound from the base.
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NOTE
The instructor must ensure that ownship penetrates the upper GCA box displayed on page 341 to receive command information in the command box on GCA pages.
7-37.
ALTITUDE/AIRSPEED PLOTS.
The altitude/airspeed plots graphically depict a history of aircraft performance related to altitude and airspeed versus distance.
The altitude is measured and recorded above obstacles from the surface to a maximum of 200 feet AGL.
Airspeed is IAS recorded up to normal cruise speed of the actual aircraft.
Distance is selectable by the instructor in two scales. Distance is measured in terms of cumulative movement without respect to direction of such move- ment .
a.
Major characteristics of the plots (sham in figures 7-28 and 7-29) include:
Altitude above ground versus distance
Indicated airspeed versus distance
Two selectable plot scales: 6- and l-km b.
The airspeed/altitude plots are in group 3 (GRAPHICS) and art accessed via the data entry keyboard by keying in CRT page 360 or CRT page 361. Typical uses of the altitude/airspeed plots include:
(1) Monitoring trainee altitude control during enroute navigation:
NOE navigation routes
Tactical instrument routes (under 200 feet only)
(2) Monitoring trainee altitude control in the firing position.
(3) Monitoring trainee airspeed control throughout training missions.
(4) Debriefing/critiquing trainee performance via the hardcopy feature.
7-38.
CONTROL PANEL CRT DISPLAYS.
The control panel CRT displays are facsimile representations of aircraft cockpit control panels.
These displays include the panel title, title and position of each switch, setting of each control, status of each indicator, and value of each readout on the panel represented. The eight control panel displays and their CRT page numbers are:
CPG missile control panel and data entry keyboard (page 370) (figure 7-u))
CPG fire control panel (page 371) (figure 7-31)
Pilot missile control panel (page 372) (figure 7-32)
Pilot fire control panel (page 373) (figure 7-33)
CPG ORT panel (page 374) (figure 7-34)
CPG cyclic control switches (page 375) (figure 7-35)
Pilot cyclic control switches (page 376) (figure 7-36)
Doppler computer display unit (page 377) (figure 7-37)
a.
The control panel CRT displays art in group 3 (GRAPHICS) and are accessed via the data entry keyboard by calling up CRT pages 370 through 377.
(Refer to the list and associated page numbers above.)
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b.
These panel displays are updated continuously to indicate the changes that have occurred in the represented cockpit panel.
c.
These panel displays permit the instructor to monitor switches, controls, and indicators in the trainee cockpits that might otherwise not be viewable; analyze trainee performance of procedures related to use of each panel; determine if panel switch, controls, and indicators are correct; and provide Doppler inputs to the pilot during independent mode operations.
7-39. TARGET ENGAGEMENT EXERCISE. The target engagement exercise (TEE) is a feature that automatically inserts events associated with the engagement of hostile targets in response to certain relationships between ownship and the target and trainees performance.
The events include initiation of targets movement, targets firing at ownship, activation of hostile radar, weapons hits on ownship. and system malfunctions resulting from hits. The factors that trigger these events include altitude, line-of-sight exposure, range to target, and release of ownship weapons.
Up to three of these triggering contingencies may be required to activate an event.
When the specified insertion contingencies have been met, the target event occurs in the manner programmed for it without instructor intervention.
a.
There are 20 preprogrammed TEE’s available for training.
They are available to both the pilot and CPG instructors in the independent and the integrated modes.
Each TEE can include up to ten targets. Five of the targets are capable of moving over predetermined routes.
The other five are on fixed sites and do not travel.
All targets capable of firing weapons can articulate and fire at the ownship. Weapons systems with radar are capable of electronic emissions that activate the radar warning receiver on the ownship.
Aircraft survivability equipment (ASE) aboard the ownship is capable of foiling the respective type of weapons system.
b.
All threat weapons systems are modeled after real-world weapons and perform accordingly.
Preprogramned hostile events in a TEE are controlled via a sophisticated threat algorithm once the triggering contingencies have been met.
For example, when intervisibility exists between the ownship and a hostile target and the ownship is within the effective range of the threat, the threat begins the acquisition process.
If the threat is employing radar, it triggers the ownship radar warning receiver.
If line-of-sight exposure is maintained, the threat engages the ownship.
Hits on the ownship and resultant damage (malfunctions) are preprogrammed for each target in the TEE.
Breaking line-of-sight (remasking) disrupts the threat acquisition process.
Engagement and destruction of the threat also terminate the acquisition process.
c.
Trainee (student) performance data is automatically stored during target engagements.
This data is on CRT pages 595-596 and can be displayed at the IOS and retrieved in hardcopy.
Additionally, data related to threat acquisition of the ownship is automatically recorded and can be displayed by calling up CRT page 594.
d.
Preprogrammed TEE sets are indexed on CRT pages 500A and 500B.
Individual
TEE's are described in CRT pages 501 through 520. (See figure 7-38.) This page is
addressed via the data entry keyboard on the console control panel. A TEE set can be reviewed on the CRT by keying in the 3-digit page number and depressing DISPL.
The displayed TEE set provides all the data related to the targets for that set.
This data includes target types, location, presence or absence of hostility, direction of travel, hits and associated malfunctions, and triggering contingencies applicable to each target. To enter a TEE set into the simulation, key in the
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3-digit page number via the keyboard and depress ENTER. The TEE set is now available. When the triggering contingencies are met, the set activates, only one
TEE set can be entered into simulation at a time. The simulator need not be in freeze to enter TEE sets. Entering an additional TEE set during training automatically deletes the previously entered set.
e.
After a TEE has been entered, various aspects of it can be reviewed by displaying other pages related to targets.
Target status CRT page 530 summarizes targets and their related activity.
Target site overview CRT page 540 graphically depicts all 99 target sites and indicates, with symbols, which sites have been selected with the current TEE. A target site detailed display, which provides a specific target site and the routes of travel from the site, can be called up by using the index and control area on CRT page 540. Detailed firing position sites that graphically depict threat targets visible from that specific firing position are on CRT pages 541 through 575.
f .
Student/trainee engagement performance data are summaries of engagement activity and are on CRT pages 595-596.
g.
Threat acquisition data are summaries of hostile weapons activity and are on
CRT page 594.
h.
TEE sets are used to:
Permit preprogramming threat activities to establish a hostile environment
Reduce instructor workload
Provide a greater degree of standardization in the presentation of threat situations
Permit an increased degree of control over the content of training
Permit rapid rearrangement of threat activity
Permit expansion of the battlefield environment and flexibility in structuring training scenarios
7-40.
TARGET STATUS. The target status page provides status information for targets that are currently entered in the simulation.
elements displayed on the page.)
a. Characteristics of the target status page (figure 7-39) include a summary of
the most recently activated TEE or manually inserted targets, and a depiction of up to 10 targets (ten is the maximum number of active targets).
b.
The target status page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by calling up CRT page 530.
c.
The target status page is used to determine:
Number and type of active targets
Site location of active targets
Which targets are hostile and which malfunctions are associated with a hit
Which targets will move and their path and speed
IR signature type for each target
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Table 7-9.
Target Status Information
Item
TARGET REFERENCE #
Data
Number of selected target.
TARGET TYPE #
TARGET SITE #
HOSTILE ACTIVITY
Number from target type list.
Number of site that target is located on.
ON/OFF; if ON, hostile activity includes electronic missions (radar) and threat weapons firing at ownship.
HIT CODE
INFRA RED
MOTION
When hits on ownship are enabled, the
5-digit malfunction number associated with the hit is displayed.
HOT/COLD.
ON/OFF; when ON, target travels over a predetermined path.
PATHWAY
SPEED
Number of pathway that target will travel from target site. (Refer to
TARGET SITE PATHWAY detailed display.)
Ground target speed from 10 to 40 kph in 10-kph increments is displayed; speed for helicopter targets is up to 200 kph.
7-41.
TARGET TYPES LIST. The target types list page (figure 7-40) is a list of
available targets and depicts the name, type number, and whether it has a radar or weapons system available. These targets can be placed on the target sites available in the visual gaming area. Targets are selected and placed via the TEE’s or manually via the target control page. The list includes 44 different vehicles.
a.
The target types list page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by calling up CRT page 531 and using page forward or page back to access 531B and 531C. The target TYPE # on CRT page 531A-C is the same reference number that is depicted on the target status page, and is the number to be used when designating target type for TEE’s and the target control page. Each
target type that appears in the computer-generated visual scene is shown in figure
7-41.
The graphic illustrations are shown in the same level of detail as would be seen close up or through sensor magnification.
NOTE
The SA-4 appears as an SA-6, and the FLATWHEEL radar appears as a KRAZ-255B truck. However, it is not difficult to discriminate between the simulated electronic emissions.
The I-HAWK can only be placed on fixed target sites.
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15535
Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 1)
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7-90
Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 2)
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1 5 5 3 6
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Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 3)
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7-90.2
Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 4)
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Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 5)
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7-90.3
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7-90.4
Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 6)
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Figure 7-41. Visual Gaming Weapons Symbols (Sheet 7)
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7-90.5
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7-90.6
Figure 7-41.
Visual Gaming Weapons Symbols (Sheet 8)
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b.
The target types list page is used to identify the types of available targets. to select and enter targets into the simulation, and to determine whether a target type has radar and/or weapons.
7-42.
TARGET SITES LIST. The target sites list page (figure 7-42) is an informa-
tion list for the 99 target sites In the visual gaming area.
The list provides the site name, site number, and site position in UTM coordinates.
The site number is the reference number used to designate a site when preparing TEE’s or when using the manually inserted targets via the target control page.
a. The first 20 target sites (01 through 20) have been designated as moving target sites (e.g., sites that have specific, preprogrammed ground or airborne pathways that targets will follow when notion is enabled and activated).
Fifteen of these roving target sites are ground sites (1 through 15) that can accommodate up to five targets each.
The targets move on separately numbered paths (1 through 5) and generally follow the same route for approximately 15 kilometers.
The remaining five moving target sites (16 through 20) have been designed for use with aircraft.
The airborne sites each have a single flightpath.
The aircraft maintains a fixed altitude (MSL) throughout the route of flight.
Hostile aircraft on any moving target site have a hostile capability.
If ownship enters designed firing cone
(approximately ±20
O from the threat aircraft CL out to maximum weapon range) hostile helicopters will engage ownship until cone limits are exceeded.
b.
The remaining 79 sites (21 through 99) are fixed target sites.
These sites have no pathways, and targets do not travel when positioned on them.
When targets are positioned at fixed sites, they can be designated as hostile; in that case, both radar and weapons are directed against the ownship when hostile activities are selected.
Ground systems rotate and point toward the ownship prior to firing.
Hostile aircraft on fixed sites (excluding MI-24D, F) will come to 25 foot hover, turn, and engage ownship until LOS is broken.
The TEE and the manual target control page are used to establish the initial criteria for hostile threat activity and ownship hits.
These criteria are evaluated in a threat algorithm (refer to
THREAT WEAPONS SCORING) to determine the outcome of the threat activity.
c.
The target sites list page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by calling up CRT pages 532 through 535. The CRT page is used to determine target sites names and positions/locations (UTM coordinates), moving target sites, and airborne target sites.
7-43.
TARGET SITES OVERVIEW. The target sites page (figures 7-43 and 7-44) is a
graphic picture of the simulated visual gaming area indicating each target site location by number within a 40- by 32-km area.
When a target has been selected and positioned on a target site. either manually or via activation of a TEE, a symbol appears on the target site overview identifying the specific type of target.
7-45 shows the symbols used to identify the different targets from the target list.
Figure 7-45 also shows symbols used for FARP’s, NDB’s, GCA’s, ownship, malfunctions,
and 3-minute index marks.
In addition to appearing on the target site overview display, these symbols also appear on other graphic CRT pages (e.g.. cross-country raps, battle position target site maps, etc.).
a.
The target site overview page (figure 7-43) is in group 5 (TARGETS) and can
be accessed via the data entry keyboard and keying in 540 DISPL.
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7-98
Change 2
Figure 7-45.
Typical Target Symbols (Sheet 1)
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Figure 7-45.
Typical Target Symbols (Sheet 2)
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b.
Target site pathway detailed displays can be called up for display via the data entry keyboard and the reference numbers in the index and control area when target site overview CRT page 540 is displayed (e.g., 01 TAB 05 ENTER, displays the pathway, If any. associated with target number 5).
These pathways are used with
TEE’s and with the manual target control page to designate the path to be traveled by a specific type target (e.g., T-80. T-62, etc.).
W h e n a t a r g e t s i t e i s i s entered, all target reference numbers disappear from the display. To return the target reference numbers. key in 03 ENTER.
This recalls all sites to the display and deletes the pathway previously displayed.
Command 03 is used to recall all sites and terrain markings.
c.
The target site overview page is used to:
Determine relative location of each target site within visual gaming area
Determine which targets art active
Determine type targets that have been placed on the 10 active target sites
Call up and display target site pathway detailed displays
7-44.
BATTLE POSITION TARGET SITES. The battle position target site (available
target sites reference) CRT pages (figure 7-46) provide graphic data related to
battle/firing positions and associated target sites and provide the instructor with a 12- by 12-km graphic overview of the target engagement area of interest.
a.
There are 34 designated battle positions included in the visual gaming area.
These battle positions include from one to tight firing positions each.
The battle positions are designed in l-kilometer squares and can be entered from only one side of the square kilometer.
The battle position is composed of relatively high terrain that overlooks target engagement areas (low terrain containing target sites).
Within each battle position are nap-of-the-earth (NOE) routes leading to the firing positions.
b.
Battle position target sites are always oriented on the CRT display so that north is up.
Bach battle position target site shows the battle position by number and all of the target sites within its 10-kilometer range.
Since each battle position has one or more firing positions. several fields-of-fire are available to the trainee.
Bach battle position has been designed with tight selectable fields-offire for the Instructor to choose from when viewing the target sites in the target engagement areas.
c .
cessed
The battle position target site pages are in group 5 (TARGETS) and can be acvia the data entry keyboard (CRT pages 541-574).
In the index and control area of the CRT page when battle position target site maps art displayed, control reference numbers are provided to permit selection of fields-of-fire.
Each battle position has only one entrance side. shown on the map with an index.
Starting in the upper right-hand corner of the battle position, the fields-of-fire are numbered
1 through 8 in a clockwise direction.
In the control area, reference number 01 is the command for selecting the FIELD OF FIRE number. Reference numbers 02 and 03 are aircraft TRACK ERASE and TRACK RECALL, respectively.
Reference number 01 can be entered via the data entry keyboard while the map is displayed (e.g., 01 TAR 6
ENTER) and causes the viewing direction of the field-of-fire to change for the specified battle position.
As fields-of-fire art selected (advanced), the map automatically repositions in relation to the battle position to maintain the maximum field-of-view in the direction of the field-of-fire (i.e., when field-of-fire 6 is selected, the battle position is displayed on the left side of the CRT page and
7-100 Change 2
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centered vertically: when field-of-fire 2 is selected, the battle position is displayed on the right side of the CRT page and centered vertically).
d.
When targets have been selected and positioned on the target sites within a battle position target site map, target symbols appear on the map.
When intervisibility or LOS exists between the ownship and any target(s), the target symbol(s) illuminate in high intensity.
e.
Battle position target site maps CRT pages can be used to determine which target sites are in proximity of a battle/firing position. and to observe graphically when intervisibility exists between the ownship and targets.
These CRT pages are primarily used by the instructors for planning new TEE sets. as they do not display the ownship symbol.
Battle position maps (CRT pages 301-334) should be used to monitor training activity during normal simulation training periods.
7-45, MANUAL TARGET CONTROL. The target control CRT page provides the instructor with the capability to manually select targets and designate the characteristics associated with them.
This page includes 22 command entry lines that are used to activate and control target/characteristics.
The target control page (figure 7-47) is in group 5 (TARGETS) and can be
accessed via the data entry keyboard by keying in 580 DISPL.
The page permits selection and insertion of one target at a time into the simulation.
Up to 10 targets can be selected and active in the simulation at any one time.
Up to five of these targets can be designated as moving targets.
commands, range of values, keystrokes required, and comments related to use of the target control CRT page.)
NOTE
580-01 must be set to OFF to manually activate/remove targets.
b.
The target control page is used to temporarily inhibit TEE events from occurring (activation of motion and onset of hostility) and to establish a temporary threat array for a training mission.
NOTE
While manual selection of targets provides considerable flexibility with selection of threat arrays, such selection can become overly time-consuming because of the number of entry commands required.
If an appropriate TEE is available, its selection and use will reduce setup time.
Triggering contingencies are not available with manual target control.
Consequently, threat activities are activated when freeze is deactivated.
To establish control of threat activity and maintain visual contact with targets, manual control is best employed while the simulator is in freeze at the desired battle position.
7-46.
VISIONICS POINTING/REMOTE DESIGNAT0R. The visionics pointing/remote desig-
nator control page (figure 7-48) is a dual-function control page. First, during
independent mode training, it permits the instructor to act as the missing crewmember to identify and designate targets.
Second, it permits the selection and designation of targets for engagement via remote designators (GLLD, etc.). The page includes five command reference lines; line 01 is used for visionics pointing, and lines 02 through 05 are used for remote designation.
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Command
Table 7-10.
Instructions for Use of Manual Target Control CRT Page
Range of value
Keystroke
Comments
TEE CONTROL
01 TEE
STATUS
OFF/ON 01 ENTER
02 SUSPEND
TEE EVENTS
YES/NO 02 ENTER
Must be set to OFF to activate/remove targets.
When set to ON, motion and hostility edit can be done.
Suspends active TEE.
Temporarily inhibits automatic target event insertion. Manual target control prohibited.
03 TARGET SITE
REFERENCE NUMBER
1 - 10
TARGET ACTIVATE/REMOVE
03 TAB N ENTER
04 TARGET TYPE
NUMBER
05 TARGET SITE
NUMBER
06 HOSTILE
ACTIVITY
07 MISS-HIT
1 - 22
27 - 48
1 - 99
YES/NO
0 or 5-digit number
04 TAB N ENTER
05 TAB N ENTER
06 ENTER
07 TAB N ENTER
N = 1 to 10. Site reference number corresponds to reference number on target status page.
Used to count targets being inserted. (Refer to commands 09, 10, and
11 below.)
N = 1 to 22 and 27 to 48.
Target type number corresponds to type number on target type list and identifies specific target type.
N = 1 to 99. Site number corresponds to target site list and identifies target site location.
YES enables radar/weapons firing at ownship.
08 INFARED HOT/COLD 08 ENTER
N
=
5-digit malfunction number from malfunction list for a HIT. Defines malfunction when this target hits ownship.
N - 0 for no malfunction with threat hit.
Defines hot/cold infrared signature.
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Table 7-10.
Instructions for Use of Manual Target Control CRT Page - Continued
Command
09 MOTION
Range of value Keystroke Comments
TARGET ACTIVATE/REMOVE - continued
ON/OFF 09 ENTER
Enables pathway travel for target site reference numbers 1-5.
10 PATHWAY 0-5, 7 10 TAB N ENTER
11 SPEED 0 - 40 (ground)
0 - 200 (air)
11 TAB N ENTER
N = 0 to 5,7. Defines pathway target will travel for site reference numbers l-5, and 7 for air pathway.
N = 0 to 40/200.
Kilometers per hour in 10-kph increments.
12 ACTIVATE
TARGET
13 REMOVE TARGET
12 ENTER
13 ENTER
Inserts target into simulation and activates motion/hostility.
Deletes target from simulation.
99 REMOVE ALL
TARGETS
99 ENTER
Deletes all targets from simulation.
14 TARGET
REFERENCE NUMBER
1 - 10
TARGET HOSTILITY EDIT
14 TAB N ENTER
15 HOSTILITY
16 HOSTILITY
EDIT FOR ALL
TARGETS
0 - 1
0 - 1
15 TAB N ENTER
16 TAB N ENTER
N = 1 to 10. Site reference number on target status page.
Used to count targets being inserted.
N - 0 to 1.
0 for hostility off and 1 for hostility on for selected target.
N= 0 to 1. 0 for hostility off and 1 for hostility on for all active targets.
17 TARGET
REFERENCE NUMBER
1 - 10
TARGET MOTION EDIT
17 TAB N ENTER N= 1 to 10. Site reference number on target status page.
Used to count targets being inserted.
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Table 7-10.
Instructions for Use of Manual Target Control CRT Page - Continued
Command
Range of value Keystroke Comments
18 MOTION 0 - l
TARGET MOTION EDIT - continued
18 TAB N ENTER
19 SPEED 0 40 (ground)
0 - 200 ( a i r )
19 TAB N ENTER
N = 0 to 1.
0 turns motion off and 1 turns motion on. Enables pathway travel for target site reference numbers l-5.
N = 0 to 40/200. Kilometers per hour in
10-kph increments.
20 MOTION FOR
ALL TARGETS
0 - 1 20 TAB N ENTER N = 0 to 1. 0 turns motion for all targets off and 1 turns motion for all targets on.
21 SPEED FOR
ALL TARGETS
0 - 40 21 TAB N ENTER N = 0 to 40. Kilometers per hour in 10-kph increments for all targets.
NOTE
Commands 02, 06, 08, and 09 are Booleans and, when entered a second time, provide the reciprocal command (e.g., YES or NO, ON or OFF, etc.).
Commands 14, 15, and 17 through 19 affect only those targets referenced in their respective sections.
Commands
16, 20, and 21 affect all targets referenced in their respective sections.
When commands 14, 15, and 17 through 19 are used, there are no display values for commands 16, 20, and 21.
a.
The visionics pointing/remote designator control page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 581 DISPL.
b.
The instructor uses line 01 to identify a target for the pilot or CPG trainee during independent mode training.
The target reference number (line 01) is selected from the target status page (value 1 to 10). When the reference number is entered, trainee visionics art cued to a line-of-sight between the ownship and the designated target after the trainee has executed the necessary procedures.
c.
The instructor completes data entries for lines 02 through 05 on the visionics pointing/remote designator control page to select and designate targets for attack by a remote designator (e.g., GLLD).
This allows the CPG trainee to practice all the procedures associated with the selection, preparation, and launching of a missile to be controlled by a remote designator.
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NOTE
Command lines 01 through 04 require that TAB be depressed between the command line entry and the value (e.g.. 01 TAB 09 ENTER).
Line 05 is Boolean for ON/OFF and requires only 05 and ENTER.
The simulation assumes that a line-of-sight exists for the UTM selected. A quick method for entering UTM is to pick a grid intersection within the acquisition fan and enter those coordinates (e.g., QGl2003400).
7-47.
TARGET EVALUATION. The target evaluation page provides the capability to selectively review TEE’s or manually inserted target arrays.
a.
The six command/reference lines on the CRT page (figure 7-49) are:
(1) Lines 02 and 04 through 06 establish a position for the ownship in the visual gaming area and identify the targets (TEE or manual) to be observed.
(2) Line 03 INVISIBLE AH-64, when YES, allows the instructor to observe targets without triggering hostility, motion, or hits.
(3) Line 03 INVISIBLE AH-64, when NO, permits events to occur as programmed when the TARGET EVALUATION MODE is activated.
(4) Line 01 TARGET EVALUATION MODE is used to activate/deactivate the evaluation feature.
b.
The target evaluation page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 583 DISPL.
The primary purpose of the target evaluation page is to permit instructors and/or course developers who prepare TEE’s to observe and visually review the tactical array of targets placed in TEE’s. A secondary, but equally important, purpose is to allow flight instructors undergoing simulator instructor training to observe and review targets within TEE’s and targets that have been manually selected for subsequent training periods. The instructor may find this feature useful with some trainees early in training.
Many target sites are visible from more than one battle position; the target evaluation page permits quick positioning to battle positions and firing positions to determine the most suitable locations from which to conduct training.
c.
After completing entries for lines 02 through 06, the simulator and the associated visual display are initialized at the selected UTM to permit observation by keying in 01 ENTER.
Heading and altitude can be changed as desired via lines 05 and 06 while at the evaluation position.
Activating the HIT OVERRIDE switchlight permits observing the targets and checking the operation of triggering parameters
(e.g., enable motion and hostility with line-of-sight) without being hit.
d.
The target evaluation page is used to:
Permit instructors and course developers to review newly prepared TEE’s
Permit familiarization of TEE’s for new instructors
Permit instructors to review manual target arrays
Familiarize trainees with firing positions and threat arrays
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7-48.
WEAPONS LOADING/ROCKET CONFIGURATION. The weapons loading pages (figures
7-50 and 7-51) show the 15 weapons configurations available in the CMS. Mounting
hardware, weapons, and ammunition quantities associated with each configuration are also shown. The variety of available loads gives the instructor maximum flexibility for selection of mission loads.
a.
Loads 02 through 05 are for anti-armor missions and include only Hellfire missiles and 30-mm. Loads 06 through 15 are for covering force and airmobile escort missions. These loads all include 2.75-inch rockets. The following five rocket types art available in the simulated weapons system:
High-explosive, RC fuse
High-explosive, point-detonating
Illumination
Smoke (white phosphorus), time fuse
Multipurpose submunitions, time fuse
RC4
PD4
6IL
SK4
6MP b.
The weapons loading page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 590 DISPL.
The line number associated with each load is the number to be entered on tither line 06 of the IC set page, line 06 of the current conditions page, or line 01 of the weapons loading page.
When a weapons load has been selected and activated, that load is reflected in the weapons status area of the CRT display.
c.
Each load configuration that includes rockets indicates the number of rockets on each wing and a reference number to identify the rocket load configuration.
(See figure 7-50.) That is, the reference number identifies what type rocket is
loaded and available for use in each zone of the rocket system. By paging forward
(PAGE FWD) from weapons loading CRT page 590, rocket configuration CRT page 591
(figure 7-51) is displayed. This page lists the ten rocket load configurations and
identifies what type rockets have been loaded in the weapons load indicated on CRT page 590.
d.
The weapons loading page is used to determine what weapons loads are available for training, to select a load configuration to be entered in IC or CC page(s), and to determine what types of rockets are available.
7-49.
FARP CONTROL. The forward arming and refueling point (FARP) control page
(figure 7-52) lists the 10 sites on which the FARP can be established in the visual
gaming area.
The list includes the site number, name/description, and UTM location of the site.
The FARP area includes a landing area with lighted inverted-Y fuel points, ammunition boxes, and fuel bladders. However, refueling and rearming are actually performed by the instructor modifying the appropriate lines on the CC page during training periods.
a.
The FARP control page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 592 DISPL. Only one model of a FARP is available in the CMS visual database. This FARP can be placed on any one of the sites of the
FARP control page.
b.
The site number listed to the left of the name/description is the number to be entered on line 29 of the IC or CC page. The FARP can be repositioned in the gaming area
7-110
Change 1
TM 55-6930-214-10 at any time by the instructor (e.g., while the CC CRT page is displayed, keying in
29 TAB 01 ENTER causes the FARP to be located at FARP site 01).
c.
The FARP control page can also be used to position and or reposition the FARP during training periods.
7-50. ENGAGEMENT PERFORMANCE. The engagement performance pages 595A through F and
596A through F (figure 7-53) summarize the twelve most recent target engagements by
tither trainee with any of the aircraft weapons systems. An engagement consists of one missile launch, one burst of cannon fire, or all rockets released in one trigger pull.
a.
The engagement performance page provides the instructor with feedback on pilot and CPG trainee performance during target engagements.
explains the data elements that art recorded automatically and summarized on the
CRT page during all engagements.) b.
The engagement performance page is in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 595 DISPL or 596 DISPL.
The data presented permits the instructor to analyze trainee performance using objective data that is not normally available during conventional weapons systems training.
The engagement performance information on CRT pages 595 and 596 can be preserved for future reference by using the hardcopy feature.
c.
The engagement performance page is used by the instructor to analyze trainee performance when engaging threat targets; to provide the instructor with feedback related to trainee performance; and to debrief/critique trainees after the training period.
7-51.
THREAT SCORING. The threat scoring page (figure 7-54) summarizes the threat
during the four most recent target engagements by either trainee with any of the aircraft weapons systems.
An engagement consists of one missile launch, one burst of cannon fire, or all rockets released in one trigger pull. Threat scoring pages
594A, 594B, and 594C summarize four target engagements each for a total of 12 engagements or events. Since the three pages art identical in content, only one is illustrated.
a.
The threat scoring pages provide the instructor with feedback on the threat to the aircraft during target engagements.
(Table 7-12 lists and explains the data
elements that art recorded automatically and summarized on the CRT page during all engagements.) b.
The threat scoring pages are in group 5 (TARGETS) and can be accessed via the data entry keyboard by keying in 594 DISPL.
Use page-forward to review pages 594B,
594C, or 594D.
The data presented permits the instructor to analyze trainee performance using objective data that is not normally available during conventional weapons systems training.
The threat scoring information on CRT page 594 can be preserved for future reference by using the hardcopy feature.
c.
The threat scoring pages art used by the instructor to analyze trainee performance when engaging threat targets; to provide the instructor with feedback related to trainee performance and threat to the aircraft; and to debrief/critique trainees after the training period.
7-114 Change 2
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Item
Table 7-11.
Engagement Performance Page Data Display
Data
Guns and Rockets
ENGAGEMENT NUMBER
CREWMEMBER
WEAPONS TYPE
WEAPON MODE
TARGET SITE
TARGET TYPE
TARGET RANGE
LOS/DESIGNATION SOURCE
ROUNDS FIRED
DISPOSITION
MISS DISTANCE BEST:
LEFT/RIGHT, SHORT/LONG,
LOW/HIGH
Number given to the engagement (1-999), only the
12 most recent are displayed.
Crew member delivering the weapon, PLT or CPG.
Rockets or 30mm gun.
Mode in which weapon was released: GUN-NORM,
FIXED; ROCKET-NORM, GROUND STOW, FLIGHT STOW,
COOPERATIVE, IMPROPER COOP.
No. between 1 and 99 from target sites list CRT pages 532 through 535.
No. 1-48 from target type list CRT pages 531A-C.
Distance from ownship to target in meters at time of weapon release.
Aiming or designation method used.
Results
Include the following: TADS, CPG IHADSS, PLT
IHADSS, Remote, Autonomous, both, none.
Total rounds fired at target during a single engagement.
HIT or MISS or KILL
The resultant distance, in meters, at which the closest impact point occurs, broken down into it’s individual dimensions.
MISS DISTANCE WORST:
LEFT/RIGHT, SHORT/LONG
LOW/HIGH
MISS DISTANCE AVERAGE:
LEFT/RIGHT, SHORT/LONG,
LOW/HIGH
MISS DIST COMPONENT RNG:
LEFT/RIGHT, SHORT/LONG,
LOW/HIGH
STANDARD DEVIATION:
LEFT/RIGHT, SHORT/LONG,
LOW/HIGH
The resultant distance, in meters, at which the furthest impact point occurs, broken down into it’s individual dimensions.
The average of all the resultant impact distances broken down Into it’s individual dimensions.
The miss distance range spread, in meters, of all the impact points in the individual dimensions.
The standard deviation of miss distance range spreads in the individual dimensions.
Change 2
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Item
Table 7-11.
Engagement Performance Page Data Display - Continued
Data
SIGHTING ERRORS:
AZIMUTH, ELEVATION
ENGAGEMENT NUMBER
LOS START TIME
Guns and Rockets - continued
The deviation between the azimuth and elevation of the sighting path and the ownship to target
LOS vector.
Missiles
Number given to the engagement (l-999) only the
12 most recent are displayed.
Time, hr:min:sec, at which LOS was first obtained between the target and ownship.
WEAPONS FIRE TIME
TOTAL EVENT TIME
CREW MEMBER
WEAPON MODE
TARGET SITE
TARGET TYPE
TARGET STATUS
TARGET RANGE
LOS/DESIGNATION SOURCE
PITCH RATE
YAW RATE
TOF
Time, hr:min:sec, at which the weapon was fired.
Total time, In hr:min:sec, recorded from start of
LOS to weapon fire time.
PLT or CPG
Mode in which missile was released: LOBL,
LOAL-DIR, LOAL-LO, LOAL-HI, with either NORM,
RIPL or HAN.
No. between 1 and 99 from target sites list CRT pages 532 through 535.
No. 1-48 from target type list CRT pages 531A-C
Disposition of target at weapon fire time with respect to LOS, Hostility, Motion, Destroyed status (L,H,M, and K respectively).
Slant range from ownship to target, in meters, at weapon fire time.
Source of designation laser, either ownship or remote designator.
Rate of change, in deg/sec, of ownship pitch at weapon fire time.
Rate of change, in deg/sec, of ownship yaw at weapon fire time.
Weapon Time of Flight measured from weapons fire time to impact of missile.
7-116.2
Change 2
Item
TM 55-6930-214-10
Table 7-11.
Engagement Performance Page Data Display - Continued
Data
DISPOSITION
MISS DISTANCE BEST:
LEFT/RIGHT, SHORT/LONG
DES ON/OFF TARGET TIME
DES DELAY TIME
Missiles - continued
Hit or Miss
The resultant distance, in meters, at which the closest impact point occurs, broken down Into it’s individual dimensions.
The amount of time the ownship laser was on or off the target.
Time delay between missile launch and the ownship lasing the target.*
IMPROPER OFFSET TIME
SEEKER ON/OFF TARGET TIME
LAUNCH/REMOTE DES ANGLE
VISIBILITY
DES/SEEKER OBSCURED:
CLOUDS, SMOKE/DUST
MASK INTERCEPTION:
DES CONSISTENCY/MODE
MISSILE SEEKER CODE
HORZ/VERT
Amount or time (in critical window) that the ownship was not lasing on the target.*
The time the seeker sees the target, based on the seeker tracking the designation laser spot and the spot is on the target.*
Launch : Angle between seeker (on Rail) and target at weapon fire time.*
Remote : Splash angle of remote designator on the target.*
Entered visibility at missile fire time.*
The time, in seconds, that the designator and/or seeker were obscured from the target by one or more of the obscuration items listed during the entire flight of the missile.*
Record of seeker intersection with mask at any time during the missile flight.*
Standard deviation of the designation point variances during the Critical Illumination Period
(CIP) of the missile flight.*
Seeker code to assigned to missile fired in current engagement.*
LRF/D Code
Code assigned to ownship’s laser designator during the current engagement.*
REMOTE CODE Code assigned to remote designator during current engagement.*
*Indicates item is a “tolerance” item. When the value of these fields exceeds allowable limits an asterisk (*) is placed next to the field on the CRT page.
Change 2
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TM 55-6930-214-10
Item
EVENT NUMBER
TARGET TYPE
TARGET SITE NUMBER
Table 7-12.
Threat Scoring Page Data Display
Data
Defines which particular event that has occurred; as each event occurs, events scroll right with latest event displayed in leftlost column of CRT page 594A
Target that caused the end of an event
(there are 16 target types)
Target site that was being used during event recorded (site number range is 0 - 99)
EVENT START TIME
EVENT END TIME
EVENT EXPOSURE TIME
Specific time that event started; this is associated with MET
Specific time that event ended; this is associated with MET
Length of time that event lasted; this is the difference between event start and end times
7-118 Change 2
TM 55-6930-214-10
Table 7-12.
Threat Scoring Page Data Display - Continued
Item
TOTAL EXPOSURE TIME
Data
EXPOSURE ZONE (MAX)
Length of time that target was in line-ofsight of ownship; time is accumulated over each event until ownship breaks line-ofsight for greater than 5 seconds, in which case total exposure time is reset to 0
Maximum unmasked area that ownship was in during event (value range is 0 - 5)
EXPOSURE ZONE (MEAN)
EXPOSURE ZONE (FINAL)
Average unmasked area that ownship was in during event (value range is 0 - 5)
Last unmasked area that ownship was in at time event ended (value range is 0 - 5)
FINAL RANGE (M) Distance in meters between target and ownship at time event ended
VISIBILITY (M)
BACKDROP UTILIZATION
ASE UTILIZATION
Maximum distance in meters that ownship can visually obtain an object
Percentage of backdrop that was used over a particular time during event (value range is
0 - 100)
Defines aircraft servicability equipment that was used effectively against a threat during event (parameters used are RDR,IR,and CF)
PA (MAX)
PA (MEAN)
PA (FINAL)
PH (MAX)
PH (MEAN)
Maximum probability of being acquired that ownship obtained during event (value range is 0.00 - 1.00)
Average probability of being acquired that ownship obtained during event (value range is 0.00 - 1.00)
Final probability of being acquired that ownship obtained at time event ended (value range is 0.00 - 1.00)
Maximum probability of being hit that ownship obtained during event (value range is
0.00 - 1.00)
Average probability of being hit that ownship obtained during event (value range is
0.00 - 1.00)
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Item
PH (FINAL)
DISPOSITION
HIT OVRD
HOSTILITY
Table 7-12.
Threat Scoring Page Data Display - Continued
Data
Final probability of being hit that ownship obtained at time event ended (value range is
0.00 - 1.00)
Result that occurred at end of event (parameters used are HIT, MISS, and blank)
ROUNDS REMAINING
OWNSHIP ENGAGEMENTS
CUM OWNSHIP ENGAGEMENTS
TARGETS DESTROYED
CUM TGTS DESTROYED
Defines whether or not a malfunction will be executed when ownship takes ahit from a threat (parameter is ON or OFF)
Defines whether or not a target is a threat to the ownship during event (parameters are
ON or OFF)
Number of rounds that threat has left at time event ended
Number of times that ownship fired a weapon at any target during event: number is tallied against all targets fired upon regardless of which target caused end of event
Total number of times that ownship fired a weapon at any target, accumulated over all events
Number of targets destroyed during event
Total number of targets destroyed, accumulated over all events
7-52.
AUTOMATIC MALFUNCTION INSERTION.
Automatic malfunction insertion (AMI)
(figure 7-55) automatically inserts malfunctions or systems failures of simulated
aircraft components in response to preprogrammed conditions expected to occur during an instructional activity.
These contingent conditions/parameters include:
No. 1 engine rpm - %
No. 2 engine rpm -- %
Altitude - feet MSL
Altitude - feet AGL
Indicated airspeed - knots
Weapons release - seconds after
Mission elapsed time - minutes
Previous malfunction occurrence
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a.
There are 15 sets of AMI programs available, with up to 10 malfunctions programmed for each one.
Up to three different contingent conditions/parameters can be designated for each malfunction.
The contingent conditions/parameters can be programed so all must occur or any one of the designated set can trigger the malfunction.
For example, one malfunction in an AMI set could be: engine No. 1 fails when altitude is greater than 30 feet AGL, airspeed is less than 10 knots, and mission elapsed time is equal to 30 minutes.
When the specified insertion contingencies have been met. the malfunction occurs in the manner programmed for it without instructor intervention.
b.
Since the insertion of specific malfunctions are controlled automatically and are triggered by conditions that may be beyond Instructor control and their occurrence may disrupt training or overload a trainee at that point, the instructor receives an alert message.
Ten seconds prior to insertion of an AMI malfunction. an alert message with the name of the malfunction is displayed in the IOS CRT alert area.
The instructor has the option at this time to allow the malfunction insertion and to monitor trainee response, or to delete it.
If the instructor chooses to delete the malfunction during the 10-second alert period, the MALF OVERRIDE switchlight on the forward control panel must be depressed.
Depressing the switchlight deletes the impending malfunction for the remainder of the training period without affecting the remainder of the malfunctions in the AMI set.
Once an automatic malfunction has been overridden (deleted), the instructor can insert it manually via the data entry keyboard and the manual malfunctions pages.
c.
The instructor can remove any automatically inserted malfunction from the simulation by keying in the unique 5-digit identifier associated with that malfunction and ENTER on the data entry keyboard.
Alternatively, all active malfunctions can be removed from the simulation by depressing the REMOVE ACTIVE MALFS switchlight on the forward control panel.
d.
AMI sets are called up for CRT display and/or activated via the data entry keyboard on the console control panel.
AMI sets are in group 2 (MALFUNCTION INDEX) and are listed on CRT pages 201 through 215. An AMI set can be displayed on the main page of the CRT by depressing the 3-digit unique page number and DISPL on the keyboard (e.g., AMI set number 5 is on CRT page 205). The AMI set can be entered into the simulation when it is currently displayed on the CRT by keying in the
3-digit page number and ENTER on the keyboard. Alternatively, an AMI set can be directly entered without displaying it on the CRT by keying in the 3-digit page number and depressing ENTER.
The simulator does not have to be in freeze condition to enter any AMI.
Only one AMI set can be active at a time.
Selection of subsequent AMI sets during a period automatically deletes the previously selected set.
e.
The HALF OVERRIDE switchlight for deleting automatic insertion of malfunctions and the REMOVE ACTIVE MALFS switchlight for deleting all active malfunctions are at the top left on the IOS forward control panel.
These switchlights are used to relieve instructor workload, permit skilled pilots to practice emergency procedures independently, and provide a greater degree of standardization.
Change 2 7-121
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The AMI should not be used to introduce pilots to malfunctions or in conjunction with other training activities for relatively unskilled pilots.
Manual insertion of malfunctions should be used for introduction.
(Refer to MANUAL MALFUNCTIONS.) AMI’s may Increase the trainee task loading; as such, they should be used for advanced or continuation training activities and for training pilots in maintenance of skills.
7-53.
MANUAL MALFUNCTION.
Malfunction simulation (MS) enables the instructor to fail, partially or totally, a simulated aircraft component or to introduce an abnormal aircraft condition.
When such a failure is inserted into the simulation, the consequences duplicate the consequences of a corresponding failure in the aircraft.
Actions taken by the trainee in the simulator following insertion of a failure have the same consequences as would be experienced under corresponding circumstances in the aircraft.
The instructor can insert or remove a simulated malfunction, but cannot change its programmed characteristic.
a.
Malfunction simulation enables the instructor to simulate the occurrence of component malfunctions and failures so that the pilot and/or copilot/gunner can be trained to determine that an abnormal condition has occurred, identify the condition, and take the prescribed corrective or compensating action.
Since the simulator provides a safe environment in which such training can take place, it provides the only environment in which training associated with the most hazardous malfunctions can take place.
Approximately 336 malfunctions are available in the CMS.
(Refer to tables 7-15 and 7-16, in Section IV of this chapter.)
b.
Malfunctions are entered into the simulation through the data entry keyboard on the console control panel at each IOS.
Categories of available malfunctions are
indexed by system on CRT page 200 (figure 7-56).
Individual malfunctions are coded with a specific 5-digit identifier made up of the number of the CRT page on which it appears (3 digits) and the line number (2 digits) on that CRT page.
7-57.) Typing the 5-digit identifier and depressing ENTER on the keyboard inserts
the malfunction into the simulation (e.g., typing 22102 ENTER inserts the malfunction appearing on line 02 of CRT page 221). Once inserted, the malfunction can be removed by reentering its identifier.
Up to 15 malfunctions can be active at any one time, and up to six of these are displayed in the status area of the IOS CRT display.
Active malfunctions can also be removed from the simulation by depressing the REMOVE ACTIVE MALFS switchlight on the forward control panel.
c.
Instructors can use the malfunction simulation function to provide the trainee with exposure to, and practice in dealing with, possible aircraft in-flight emergencies and aircraft systems malfunctions.
7-54.
DEMONSTRATIONS.
Demonstrations (DEMOS) consist of a prerecorded aircraft maneuver or a series of aircraft maneuvers that provide a model for the desired performance of the maneuver being demonstrated. During demos, instruments, indicators, aircraft flight controls, motion system movements, visual display scenes, and associated aircraft sounds reflect an idealized performance of the maneuver as flown by an expert.
Demos include audio briefings, explanations. and instructional commentary to facilitate trainees subsequent performance of the maneuver.
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a.
Most trainees can read the performance requirements for a maneuver or procedure, and with sone verbal assistance from an instructor, execute the maneuver.
Occasionally, because of the complexity of a maneuver or because of the need for precise performance timing, the instructor provides a demonstration of the maneuver prior to trainee execution and practice. In dual-controlled aircraft, an instructor simply takes control of the aircraft and provides the required demonstration. In the CMS, this instructor function has been automated to save time and to standardize instruction.
The automated demonstrations in the CMS are generally short, and can be played in either real-time or in slow-time. In slow-time, there is no audio, and the instructor must provide any required commentary.
b.
The demos are in group 4 (DEMOS/AF/RP) and are accessed via the data entry keyboard by keying in 400 DISPL.
(See INDEX area, figure 7-58, and DEMO INDEX,
figure 7-59). The demos are on CRT pages 401 through 420. (See figure 7-60).
c.
The REPLAY AUDIO OFF and the REPLAY SLOW TIME switchlights on the forward control panel can be used to turn off the synchronized audio comnentary and start and stop slow-time, respectively.
d.
Demo programs can be displayed at the IOS for review prior to entry during the selection process, or they can be entered directly into the simulation without displaying them.
They can be initiated from the beginning of the program, or they can be initiated from an intermediate segment of a program.
(For direct entry without display, the demo/segment number should be determined during premission planning.) The following methods and procedures can be used to select, display, enter, and activate demos:
(1) To call up a demo page (figure 7-60) for review or entry, proceed as
follows:
(a) Key in 400 DISPL to display demo index in CRT main page area.
(b) Select 3-digit set number and DISPL (e.g.. to display demo set No. 6, which is on CRT page 406, key in 406 DISPL).
(c) DISPL permits reviewing demo content prior to entering. To enter a demo that is currently displayed, key in 01 TAR (1-10) ENTER.
(d) After ENTER. demo is ready for activation when PROB FREEZE switchlight stops flashing.
(2) Demos can contain up to ten segments. Generally, each segment is a complete maneuver or series of maneuvers.
Each segment is individually numbered and addressable.
The demo can be initiated from an intermediate segment by either of the following:
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(a) With demo page displayed, select segment reference number and enter it via data entry keyboard, using 01 TAB (segment 1-10) ENTER.
(b) If the page is not displayed, identify desired demo and its segment number during premission planning.
With simulator in freeze, activate demo segment by keying in demo CRT page number. segment number, and
ENTER.
e.
Maximum operating time for a demonstration is 5 minutes.
At the conclusion of the demo, the simulator enters an automatic freeze.
To continue training activ i t i e s , the instructor can do one of the following:
(1) Enter required 3-digit number to reselect completed demo or any other demo, then enter 01 TAR (segment 1-10) ENTER.
(2) Enter required 3-digit number to select a new set of IC’s and, when PROB
FREEZE switchlight stops flashing, continue training from that point.
f .
Resume or flyout functions can be employed at any time during a demonstration by activating PROB FREEZE, then selecting either the REPLAY RESUME or REPLAY
FLYOUT switchlight.
(1) Depress REPLAY RESUME switchlight on forward control panel to continue training from the point at which demo was initiated (problem freeze condition prior to start of demo).
When PROB FREEZE switchlight stops flashing, depress PROB FREEZE switchlight to permit training to continue from that point.
(2) Depress REPLAY FLYOUT switchlight on forward control panel to continue training from the point at which the demo terminates.
Then, depress PROB
FREEZE switchlight to permit training to continue from that point.
g.
Demonstrations are used to:
(1) Supplement, or substitute for, a demonstration flown by the instructor.
(2) Provide an idealized, standardized model of maneuver performance in realor slow-time.
(3) Present a standardized description of a maneuver or procedure, including relationships between relevant controls and indicators, the performance standard associated with the maneuver or procedure, and other instructional information.
7-55. AUTOFLY. When the CPG cockpit is operated in the independent mode, there is in effect no pilot to fly the aircraft.
To compensate for the missing pilot, automatic flight (AUTOFLY) flies the aircraft for the CPG.
The autofly feature flies through a prerecorded aircraft maneuver or series of contiguous maneuvers.
When an autofly set is active. all CPG cockpit instrument and indicator activations, motion system movements, visual display scenes, and mechanical and aerodynamic sounds occur.
The CPG trainee has full access to and control over all sighting, sensor, and weapons systems normally available in that cockpit. At predetermined points within the autofly set, usually firing positions, the instructor can interrupt the flight and assume manual control of the simulated aircraft heading and altitude.
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This allows the trainee additional time, if needed, to operate sighting, sensor, and weapon systems.
a.
The autofly sets are in group 4 (DEMOS/AF/RP) and are accessed via the data entry keyboard by keying in 400 DISPL and PAGE FWD to CRT page 400B or PAGE FWD again to 400C to view the autofly index.
The autofly sets are on CRT pages 421 through 460.
(See figures 7-59 and 7-61 through 7-63.)
b.
Autofly programs can be displayed at the IOS for review prior to entry during the selection process, or they can be entered directly into the simulation without displaying them.
They can be initiated from the beginning of the program, or they can be initiated from an intermediate segment of a program.
(For direct entry without display, the set/segment number should be determined during premission planning).
The following methods and procedures can be used to select, display, enter, and activate autofly programs:
(1) To call up an autofly set page (figure 7-63) for review or entry, proceed
as follows:
(a) Key in 400 DISPL and PAGE FWD to display autofly index in CRT main page area.
(b) Select 3-digit set number and DISPL. (e.g., to display autofly set
N O
.
5, which is on CRT page 425, key in 425 DISPL).
(Simulator must be in freeze to enter autofly programs.)
(c) DISPL permits reviewing autofly content prior to entering.
To enter an autofly set that is currently displayed, key in 01 TAB (segment 1-10)
ENTER.
(d) After ENTER, autofly is ready for activation when PROB FREEZE switchlight stops flashing.
(2) To activate an autofly set at an intermediate segment rather than the beginning of the set, use either of the procedures below.
In general, the intermediate segment is used to permit independent CPG gunnery training, permit independent CPG emergency systems training, and increase the line-of-sight exposure time at selected locations.
Proceed as follows:
(a) With autofly set displayed on main page area of CRT, select 2-digit line number adjacent to segment desired and enter it via the data entry keyboard by entering 01 TAB (segment 1-10) ENTER.
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(b) Depress PROBLEM FREEZE to initiate autofly program.
c.
AUTOFLY sets contain hover points at specific geographic locations that permit the instructor to assume control of altitude and heading during target engagement activities and weapons firing.
The instructor can elect to manually control heading and altitude at these hover points to allow the trainee more time to complete firing activities.
(Using this feature, the instructor can extend the period during which the aircraft is unmasked beyond that which was originally recorded).
The CPG IOS console control panel contains an AUTOFLY CONTROL panel that includes a
MAN switchlight for manual control activation and a 4-direction joystick.
Depression of the MAN switchlight any time prior to arrival, or while at a preselected hover location, engages the manual control.
During manual control, the autofly program is on a temporary hold.
Heading corrections can be made by moving the joystick left or right for respective left or right turns.
Altitude can be changed by moving the joystick forward for up and backward for down.
The simulated aircraft will not descend below the minimum altitude that was recorded for that hover point.
When firing activities are completed at that location, depressing the MAN switchlight releases the temporary hold and permits the autofly program to continue as originally recorded.
7-56.
RECORD/PLAYBACK.
Record/playback permits the replay of recent or immediately preceding segments of simulated flight.
Recording and playback are available in the independent and integrated training modes.
a.
The record aspect continuously records the most recent 5 minutes of flight.
Recording occurs automatically whenever the simulator is being flown from the trainee station.
Periods of freeze, demonstration, or control of the simulator from the IOS are not recorded except to the extent that is required to establish initial conditions.
Control movement is recorded in the integrated mode based upon selection of either the FLT CMD PILOT or FLT CMD CPG switchlight on the console control panel.
b.
The playback aspect replays the cockpit control movements, cockpit instrument values, cockpit displays, motion cues, visual scenes, mechanical and aerodynamic sounds, and voice communications that occurred during the period of recorded time selected for replay.
Recorded flight can be accessed for playback in approximately
15-second intervals up to the full 5 minutes available. The playback can be in real- or slow-time and can be frozen at any point by depressing the PROB FREEZE switch, thus allowing the instructor to discuss a problem in detail before resuming the playback.
c.
Audio communications are not replayed during slow-time replay.
Audio can be turned off/on at any time during real-time playback.
The playback can be repeated as many times as required or desired with synchronized audio.
d.
In slow-time, events take twice as long to occur as in real-time.
Slow-time playback can be particularly useful in cases where the flight situation is changing very rapidly, as in autorotation or other emergency situations.
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e.
The RELAY AUDIO OFF and the REPLAY SLOW TIME switchlights on the forward control panel can be used to turn off the synchronized audio commentary and start and stop slow-time, respectively.
f .
The record/playback command page (figure 7-64) is in group 4 (DEMOS/AF/RP)
and can be accessed via the data entry keyboard by keying in 470 DISPL.
Playback must be addressed from a freeze condition.
Line 01 on CRT page 470 permits entry via the keyboard of playback segments in approximate 15-second increments (e.g., depress 01 TAB 130 ENTER for 2 minutes, 10 seconds of playback or 01 TAB 045 ENTER for 45 seconds of playback).
g. The instructor can terminate playback by any one of the following methods:
(1) Allow playback to replay total time selected and terminate with automatic freeze at end of replay.
NOTE
REPLAY FLYOUT or REPLAY RESUME functions can be employed at any time during a demonstration by activating PROB FREEZE, then selecting either one.
(2) Depress REPLAY FLYOUT on forward control panel to permit training to continue from that point in the playback.
When PROB FREEZE switchlight stops flashing, depress PROB FREEZE switchlight to permit training to continue from that point.
(3) Depress REPLAY RESUME switchlight on forward control panel to continue training from the point at which playback was Initiated (problem freeze condition prior to start of playback).
When PROB FREEZE switchlight stops flashing, depress PROB FREEZE switchlight to permit training to continue from that point.
h.
Instructors can use the record/playback function to:
(1) Allow trainees to review their own performance.
(2) Verify that a disputed event did or did not occur.
(3) Relate trainee control Inputs to instrument Indications and systems performance.
(4) Slow down action to allow more time for trainee to grasp important relationships between control inputs and resulting instrument indications, aircraft attitude, and systems performance.
(5) Provide an aid in critiquing trainee performance.
(6) Provide an aid in reducing problems of overcontrol.
7-57. MISSING MAN. Missing man/independent mode is designed so that each flight simulator compartment (PLT and CPG) can be used independently to allow for two separate training sessions simultaneously.
In the PLT training complex, software is added to compensate for hardware found only in the CPG complex and vise versa.
Change 1 7-137
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7-57.1 Visual moding in the independent mode allows for PNVS, TADS, and OTW display generation.
(Refer to table 5-l.) Since visual displays in the independent mode depend on only one DIG providing that display, changing visual modes in one compartment affects the display on the other.
This change is automatic to the compartment not instituting the visual mode edit.
The compartment not instituting the change is placed in blinking freeze, and the visual mode changes on that compartment correspond to what is allowable for the edited mode.
7-57.2 The instructor has some control over missing man hardware in the independent mode by calling up missing man/Independent mode display CRT page 175.
a.
The CPG IOS station missing man display (figure 7-65) provides the control-
ling instructor with insertable control functions, each of which is provided with a default value.
The CPG IOS can use the missing man display to:
(1) Select which ARCS zone to load (line 01).
(2) Select quantity of rockets to be fired per trigger pull (line 02).
(3) Establish certain conditions by toggling lines 03 through 10 to turn the item on or off or, in case of line 04, lock or unlock the tailwheel.
(4) The last three lines (11 through 13) provide a means of establishing radar altitude high and low warnings and selecting one of 28 NDB ranges.
b.
The master display is divided into three columns: the first identifies the function, the second identifies the range of the function, and the third lists the default or selected value.
c.
The pilot IOS missing man display (figure 7-66) provides a means of turning
on or off the air data sensor system (ADSS), which controls various aircraft systems.
In the normal (default) mode, the ADSS switch is
O N
.
7-57.3 Ability to edit FCC waypoints in the independent mode is available to both instructors by CRT current conditions page 151. UTM and altitude entries are on separate lines for each waypoint.
In addition, the instructions have the capability to select one of two training configurations at each trainer. The GUNNER/TARGET configuration provides training in weapons delivery skills and the CLEAN/THREAT configuration develops threat recognition and avoidance skills.
The appropriate configuration is selected from CRT page 150, line 62.
7-57.4 OWNSHIP WEAPONS SCORING.
The ownship weapons scoring page (figure 7-66.1)
is a map page provided to show the following features:
Target or Illumination round of interest
Sighting designation path
Impact locations
Angular constraint markings for missiles
1, 2, and 3 km selectable scales
Target centered on map at time of engagement
Weapon type, disposition, and miss distance a.
The user can select any of the 12 defined engagements from the weapon scoring pages, as well as any of the three allowable map scales.
Change 2
7-140.1
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7-57.5 REMOTE DESIGNATION.
The Remote Designation page (figure 7-66.2) is a map
page provided to show the following features:
20 km x 20 km map
Map centered on target of interest when max is selected
Remote designation position, range vector, and its angular constraint markings when remote designator is active.
Ownship position and heading vector, and range vector
1 km markers on both range vectors
Target site, target type, remote designator code, and remote designator location a.
In addition, the user can select to erase or recall the ownship track lines.
7-57.6 THREAT SCORING GRAPHICS.
The threat scoring graphics page (figure 7-66.3)
is a plot page provided to graphically display the probability of hit and acquisition for each of the latest 12 events.
The minimum required probability will also be shown on this page.
The following data will be displayed for each defined event:
Event number
Target type number
Site
Hostility
Disposition
Change 2 7-140.3
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Section III.
AUTOMATED PROGRAM PREPARATION
7-58.
INSTRUCTIONAL FEATURE PREPARATION.
Provisions have been incorporated into the CMS that permit designated instructors to prepare the automated programs used by all instructors during training.
In the interest of maintaining quality control of program content and standardizing training, only designated instructors are responsible for developing and/or modifying automated exercises.
The skills required to make changes or to prepare new programs are those typically possessed by the AH-64 CMS flight instructors.
No special technical or programming skills are required.
There are four feature preparation programs in the CMS, located in group 9
(PREPARATION).
In order to call up the preparation programs from the IOS, the system must be enabled by a qualified operator in the computer room.
Once the preparation programs are enabled in the computer room, any of the four programs can be called up via the data entry keyboard by keying in its 3-digit page number.
The programs and their page numbers are:
Automatic malfunction insertion preparation (CRT page 920)
Demonstration preparation (CRT page 940)
Autofly preparation (CRT page 945)
Target engagement exercise preparation (CRT page 950) b.
Specific planning must take place prior to the development of an AM, demo, autofly, or TEE to:
(1) Develop a scenario that clearly indicates what the training objectives of the program are.
(2) Ensure that each exercise or demonstration supports one or more training objective(s).
c.
The following checklist has been prepared for use as a guide to enhance the development of automated exercises and demos:
(1) Objectives of the training period:
(a) Perform basic aircraft flight maneuvers.
(b) Perform tactical instrument flight.
(c) Perform NOE flight with/without PNVS/TADS.
(d) Perform NOE navigation with/without PNVS/TADS.
(e) Perform target-type engagements:
Hard
Soft
(f) Weapons to be employed:
Missiles
Rockets
30-mm
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(g) Type of weapons engagements:
Autonomous
Remote - Designation
Single-target engagements
Multitarget engagements
(h) Range to target engagement:
Long range
Medium range
Short range
(i) Perform emergency procedures/systems malfunction training:
1 Enroute to battle positions:
Instrument environment
Visual environment
PNVS/TADS environment
Mission go-no-go decision required
2 At the battle position:
With/without active threat
Aircraft systems failures
Hit induced malfunctions
3 Systems and crewmember:
Pilot
CPG
(2) Type of demo required to support training periods (remember, demos are of short duration and employment of them optimizes simulator training time):
Complex flight procedures (e.g., autorotations)
Complex engagement procedures and/or techniques
Emergency procedures
(3) Supporting materials/simulator features required for the training period:
Maps
OP-orders
IC sets
FARPS
Training period worksheets
TEE
AMI
DEMO
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TM 55-6930-214-10 d.
After assembling all the required material and preparing the flight profiles or flight scenarios and descriptions of the tactical situation, an AMI, demo, autofly, or TEE worksheet should be prepared.
After completing the appropriate worksheet(s), the data is ready to be entered for the selected exercise or demo.
Descriptions, instruction models, and worksheets for the preparation of each type of automated program are provided in the following sections.
7-59.
AMI PREPARATION.
The purpose of the AMI preparation feature is to permit
AMI exercises to be prepared by selecting a set of malfunctions to be simulated during a subsequent training period and the identifying contingencies, which, if met during that period, will trigger the insertion of each of the selected malfunctions.
Up to three contingencies (parameters) may be required to activate the appropriate malfunction.
There is computer space for preparation and storage of 15 sets of AMI exercises in the CMS, while up to 10 malfunctions can be selected for each AMI exercise.
a.
In conjunction with the development of the scenarios, the IC set to be used with each scenario should be identified.
This is important because using a specified IC set with a particular AMI exercise provides an additional degree of standardization for the planned malfunction instruction and places the simulated aircraft in an initial position most likely to trigger the AMI.
b.
When CRT page 920 is keyed in via the data entry keyboard, the main page area
contains a blank AMI set page (figure 7-67) that is filled in during the prepara-
tion process and then stored in group 2 (MALFUNCTIONS, CRT pages 201 through 215) for recall during subsequent training periods. The data from the AMI worksheet
(figure 7-68) should be entered on the appropriate lines on CRT page 920. The
index and control area (figure 7-67) includes the AMI PREP IDENTIFIERS with refer-
ence numbers (REF #) for the PARAMETERS, OPERATORS, and CORRECTORS that are required for entry on the CRT page.
c.
Line 01 AMI PREP (main page area, figure 7-67) is used to enter the identi-
fying set number for the AMI set.
When these sets are completed and stored, they appear in the malfunctions index (CRT page 200). and each has a discrete page number.
CRT pages 201 through 215 correspond to AMI sets 1-15, respectively.
d.
On CRT page 920, there are four lines of data for each malfunction.
The first line for each malfunction (lines 02, 06, 10, 14, 18, 22, 26, 30, 34, and 38) is used to key in the selected 5-digit malfunction numbers for the set being prepared.
The indented line numbers (03, 04. 05; 07, 08, 09; etc.) are for insertion of the contingencies that will trigger the malfunction.
Up to three contingencies can be entered for each malfunction.
Each contingency line accommodates one parameter, one operator, and one connector, as required to define the triggering activity.
(The contingencies are further explained in subparagraph f).
e.
Command line 77 is used to clear the display and, when keyed in, clears all data items entered.
When an AMI prep is complete, keying command line 88 places the data displayed on CRT page 920 in permanent storage in the malfunction grouping where it is available for recall by its CRT page number (201 through 215). Command line 99 is used to terminate (cancel) the preparation activity: nothing is retained in storage when line 99 is keyed in.
7-144
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7-146
Change 2
Figure 7-68. AMI Prep Data Worksheet (Sheet 1)
TM 55-6930-214-10
Figure 7-68.
AMI Prep Data Worksheet (Sheet 2)
Change 2 7-147
TM 55-6930-214-10
7-148 Change 2
Figure 7-68.
AM Prep Data Worksheet (Sheet 3)
TM 55-6930-214-10
f .
The index and control area of CRT page 920 (AMI PREP IDENTIFIERS, figure
7-67) provides command reference numbers (RRF #) so that titles and or multiple
items can be keyed in with a single keystroke.
(1) Reference numbers 1 through 8 are used to enter the appropriate triggering parameters.
When reference number 1 through 8 is keyed in on a specific line, the parameter title appears on that line of CRT page 920.
The appropriate metrics for parameters are shown in the parenthetical note behind the parameter (e.g., %, FT,
KIAS, MINS, etc.).
(2) Reference numbers 9 through 11 are used to enter arithmetic operators of less than, equal to, or greater than (<, =, >) the assigned value for the triggering parameter (00000 through 99999).
The assigned value must be keyed in as a 5-digit entry after the associated operator reference number (e.g., 9 TAB 02000
ENTER is the entry for less than 2000 feet). Each parameter must have an operator and a value assigned to trigger it.
(3) Reference numbers 12 and 13 are used to enter logical connectors. If more than one parameter is to be associated with a malfunction, than a logical connector
(AND, OR) must be designated for all but the last parameter. Reference numbers 12 and 13 are used for these connectors.
When AND is used as a connector, all parameters connected with AND must be met to trigger the malfunction.
If OR is used as a connector, any of the parameters connected by OR will trigger the malfunction when it is met.
(4) Reference number 101 is used to clear a line (e.g., 5 TAB 101 clears line
5).
When a line which has other lines dependent on it is cleared the dependent lines are also cleared (e.g., 2 TAB 101 clears lines 2, 3, 4 and 5).
g.
During AMI preparation functions, the edit area of the CRT page provides operator prompts for data input and error messages for any out-of-range or invalid entries.
Numerical inputs via the keyboard are echoed in the edit area with a cursor to Indicate the next entry.
When TAB is depressed between data fields, the appropriate data input appears on the first line of the edit area (e.g., when 03
TAB is keyed In, the prompt appearing in the edit area states:
ENTER PARAMETER REF
# ).
Each time ENTER is keyed in, the data in line 3 of the edit area blanks and the data appears on that numbered line of the prep page (main page area).
h.
Table 7-13 indicates the procedure required to enter the worksheet data into
CRT page 920 and the prompts and data displayed in the edit area.
In the entry column are the numbers to be entered plus the appropriate action key (e.g., DISPL,
TAB, ENTER).
The edit area dislays column depicts three line entries to include
(Blank) when nothing is shown and a line (
) for the cursor mark. This procedure completes the required entries for the first malfunction and its associated parameters.
The process is continued for each additional malfunction (up to 10) to be entered.
The additional malfunctions use lines 06, 10, 14, etc.
Change 2 7-149
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Entry
DISPL
Table 7-13.
AMI Prep Data Entry Procedure
Edit area displays
1.
To call up AMI prep page, enter:
920 (Blank)
920
(Blank)
(Blank)
(Blank)
2.
To assign set number, enter:
01 (Blank)
01
(Blank)
TAB
02
ENTER
ENTER SET NO.
01
(Blank)
(Blank)
02
(Blank)
ENTER (Blank)
(Blank)
3.
To enter first malfunction, enter:
02 (Blank)
02
(Blank)
22307 (Blank)
02 22307
02 MALF 22307 01 FIRE INTERNAL
(Blank)
(Blank)
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Table 7-13.
AMI Prep Data Entry Procedure - Continued
Entry
4.
To enter first parameter, enter:
Edit area displays
03
TAB
(Blank)
03
(Blank)
ENTER PARAMETER REF #
03
(Blank)
NOTE
1
Each time TAB is entered, a prompt appears in the edit area requesting specific data.
ENTER PARAMETER REF #
03 1
03 NG ENGINE #1 (%)
TAB
ENTER OPERATOR REF #
03 1
03 NG ENGINE #1 (%)
5.
To enter first operator, enter:
11 ENTER OPERATOR REF #
03 1 11
03 NG ENGINE #1 (%) >
TAB
6.
To enter parameter value, enter:
00080
ENTER PARAMETER VALUE
03 1 11 00080
03 NG ENGINE #1 (%) > 00080
ENTER
ENTER PARAMETER VALUE
03 1 11
03 NB ENGINE #1 (%)1 >
(Blank)
(Blank)
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Table 7-13.
AMI Prep Data Entry Procedure - Continued
Entry
Edit area displays
8.
To enter second parameter, enter:
04
TAB
(Blank)
04
(Blank)
ENTER PARAMETER REF #
04
(Blank)
3
ENTER PARAMETER REF #
04 3
04 ALTITUDE AGL (FT)
TAB ENTER OPERATOR REP #
04 3
04 ALTITUDE AGL (FT)
9.
To enter second operator, enter:
10 ENTER OPERATOR REF #
04 3 10
04 ALTITUDE AGL (FT) =
TAB ENTER PARAMETER VALUE
04 3 10
04 ALTITUDE AGL (FT) =
10.
To enter parameter value, enter:
00025
ENTER PARAMETER VALUE
04 3 10 00025
04 ALTITUDE AGL (FT) = 00025
TAB
ENTER CONNECTOR REF #
04 3 10 00025
04 A L T I T U D E ( F T ) - 00025
11.
To enter second connector, enter:
13 ENTER CONNECTOR REF #
04 3 10 00025 13
04 ALTITUDE AGL (FT) = 00025 OR
ENTER
(Blank)
(Blank)
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Table 7-13.
AMI Prep Data Entry Procedure - Continued
Entry
12.
To enter third parameter, enter:
Edit area displays
05
TAB
(Blank)
05
(Blank)
ENTER PARAMETER REF #
05
(Blank)
6
TAB
ENTER PARAMETER REP #
05 6
05 MISSION TIME (MIN)
ENTER OPERATOR REF #
05 6
05 MISSION TIME (MIN)
13.
To enter third operator, enter:
11
TAB
ENTER OPERATOR REF #
05 6 11
05 MISSION TIME (MIN) >
ENTER PARAMETER VALUE
05 6 11
05 MISSION TIME (MIN) >
14.
To enter parameter value, enter:
00015
ENTER PARAMETER VALUE
05 6 11 00015
05 MISSION TIME (MIN) > 00015
ENTER (Blank)
(Blank)
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7-60.
DEMONSTRATION PREPARATION.
The purpose of the demonstration (DEMO) preparation feature is to permit demos to be prepared by recording a period of flight performance in the CMS, modifying that recording as required to enhance its instructional value, and adding the appropriate instructional commentary.
The subject matter of demos should consist of complex individual maneuvers or a rapidly occurring series of maneuvers.
It is not expected that demos will be prepared to illustrate mission segments in which individual maneuvers are separated by extended periods of relatively simple aircraft control tasks. For these reasons, most demos, including those that contain pauses and slow-time segments, will be brief (i.e..
less than 5 minutes in duration).
Long demos are counterproductive in most instances and should not be prepared.
There is computer space for preparation and storage of 20 demos of up to 5 minutes duration each.
a.
Recording of a demo is normally preceded by the development of a scenario for the demo.
The scenario should identify or include the follwing:
(1) Simulated conditions under which the maneuver(s) of interest will be flown
(IC set), and the flight profile to be followed.
(2) Number of repetitions of all or designated portions of the maneuver that are to be included in the completed demo.
(3) Where pauses are to appear for insertion of instructional commentary.
(4) Which segments, if any, are to be presented in slow-time.
(5) Beginning of each demo segment that is to be directly accessible by the instructor.
(6) Script for the planned instructional commentary.
b.
Following development of the scenario with its accompanying audio commentary script, the demo described in it is ready to be prepared.
The follwing sequence of activities is required to prepare a demo: enable demo prep: set up, fly, and record flight profile; and edit (pauses, slow-time, segment identification, audio recording).
(1) Enable demo prep.
Setting up the CMS for the task of preparing a demo, except for enabling the preparation feature at the computer roan, is comparable to setting it up for an instructional training period.
Demo prep enable is defined as
a state in which the commands on the demo prep CRT page 940 (figure 7-69) are pro-
cessed and/or executed.
The following conditions must be satisfied to enable the demo prep instructional feature:
(a) Demo prep can be selected only when the prep mode is enabled at the computer room.
(b) Demo prep CRT page 940 is then called up from the keyboard at the master
IOS.
(Either IOS can be the master, but the master cannot be changed while demo prep is active.)
During demo recording. the demo records on the CPG disk only.
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(c) The instructor preparing the demo must specify the replay configuration of the CMS for playback of the demo before preparation of the demo.
Replay configuration selections (INTEGRATED, INDEPENDENT, and VISUAL REPLAY MODE) are on lines 15 through 17 of CRT page 940.
(d) The simulator must be in a freeze state when enabling demo prep.
(e) Commands are honored only from the master IOS, although the other station can call up and monitor the prep page.
(f) Demos must be prepared while the CMS is in the integrated mode.
(g) The DEMO NO. (line 01) must be entered to provide identification for subsequent recall of the demo (e.g., 01 TAB 02 ENTER identifies this as demo number
2).
(2) Set up, fly, and record.
After enabling the demo prep mode, one instructor flies the simulator from the pilot trainee station, another may be required in the CPG trainee station, and a third operates the selected master IOS.
The demo training objectives determine whether two or three instructors are required to prepare the demo.
The following rules and guidelines are provided to assist in preparation and to define the function of the commands on the demo prep CRT page
940:
(a) The instructor can call up, edit, and initialize IC sets while in demo prep. Initialization must be accomplished while in freeze.
(b) A stored reset point can be used to Initialize for a demo start point
(if one exists), or the current conditions existent when entering demo prep may be used.
Current conditions may also be edited to define the start state of the demo.
(c) The instructor selects the record by editing line 03.
(d) The instructor flies and records the maneuver record and terminates the recording by freezing (manual or auto).
The maneuver can then be reset to the beginning for re-record or playback (line 04) and monitor of the recorded maneuver. The demo elapsed-time indicator (in the CRT status area) provides the information to enable selecting any portion of the recording for playback.
(e) When the maneuver record is satisfactory, the RECORD command (line 03) can be used to sequence to the next maneuver record for recording the next portion of the demo.
(3) Demo edit functions.
Editing can include the insertion of pauses, periods of slow-time, segmentation of the demo, and the addition of the appropriate instructional commentary. Each of these editing functions are described below.
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(a) Periods of pause can be inserted (during freeze or playback) to permit extended audio commentary in the demo without a conflict between commentary and the maneuver being demonstrated.
The pause is inserted via the PAUSE SET command (line
07).
The inserted pause(s) can be as long as desired, up to 5 minutes.
However.
if a pause were inserted midway in a recording and the total record plus pause time exceed 5 minutes, no additional recording time would be available for the demo. By deleting pauses (line 09), the lost recording time can be regained. The period of pause can be terminated and the recording continued by Inserting the PAUSE END command (line 08).
Remember, if the recording and pauses total 5 minutes, additional demo activities cannot be added.
Five minutes is the maximum time available for a demo, Including all recording pauses.
(b) Slow-time periods are inserted during playback via the SLOWTIME SET command (line 10).
Periods of slow-time are ended via the SLOW-TIME END command (line
11).
Periods of slow-time can be removed by using the SLOW-TIME CLEAR command (line
12).
(c) The PLAYBACK command (line 04) is active during pause and slowtime edit activities and can be used to review the preparation.
(d) Up to ten segments are automatically numbered via the SET SEGMENT command (line 05).
Nine of the segments can be inserted anywhere, and need not be associated with pauses for freezes. Segment one is the beginning of the demo. The segment identifies an individually addressable point within a demo that may be desired for a future start point. These segments can be labeled with text to identify and describe the segment. Segments can be identified and marked during on-the-fly, playback, or during freezes. During playback and review, unwanted segment marks can be deleted via the CLEAR SEGMENT command (line 06).
(e) The PLAYBACK command (line 04) is active during segmentation and can be used to review the preparation up to this point.
(f) During playback of the demo, including periods of pause and slow-time.
audio commentary can be recorded and synchronized throughout the demo. The RECORD
AUDIO command (line 13) initiates recording.
(g) The audio commentary can then be monitored during subsequent playbacks
Via the MONITOR AUDIO command (line 14).
(h) When the demo is complete and ready for permanent storage and subsequent recall during training, the instructor Inserts the PREP COMPLETE, SAVE DEMO FOR
REPLAY command (line 88). Demos are numbered 1 through 20 and are filed on CRT pages 401 through 420, respectively.
(i) During preparation of a demo, the instructor should work on a temporary storage or work disk. Incomplete demos or demos being edited can then be stored for future access and preparation/editing activities until they are ready for the permanent file. The PREP INCOMPLETE, SAVE CURRENT STATE OF DEMO FOR CONTINUATION
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command (line 99) can be used at the completion of a demo prep period to save an incomplete effort. This command can be used at any point during the development of a demo. Demos that have been completed and are in the permanent file can be modifled within certain constraints. These same constraints apply to demos being prepared for the first time.
(j) With the exception of maneuver recording, any phase of the preparation process can be addressed and edited at any time. This includes editing pauses
(adding/deleting), slow-time, segmentation, and audio recording. Remember, modification of pauses or slow-time may impact the synchronization of the audio commentary so that it may require some modification.
(k) The major exception to the editing/modification process as it affects maneuver recording Involves re-recording. If, for any reason, a segment of the recorded flight maneuver(s) requires a modification, all of the demo beyond the point of modification will be lost. This means, for example, if the recorded portion of the last 2 minutes of flight is modified, all the pauses, slow-time segment, segmentation, and audio after that point are automatically erased.
This provision avoids discontinuities and disruptions to the demo.
However, after re-recording any part of a complete or partially complete demo, the editing process as described above can be accessed and the newly modified demo then completed.
(4) Text insertion.
Descriptions and/or titles can be added to the demo number and to each segment of the demo for display on CRT pages. This activity is a process that is performed offline by a separate task.
7-61. AUTOFLY PREPARATION. The purpose of the autofly preparation is to permit the recording of flight profiles that can be used with the CPG trainee cockpit when it is operating in the independent mode. Preparation of an autofly recording is normally preceded by the development of a scenario for the flight profile to be recorded.
a.
The scenario should identify or include the following:
(1) Specification of the simulated conditions under which the flightpath and maneuvers of Interest will be flown.
(2) Planned route of flight.
(3) Definition of targets arrays and type of threat activities required.
(4) Identification of malfunctions and/or system failures that will affect the training mission.
(5) Requirements for instructions or other communications to the CPG during the training mission.
b.
Following development of the scenario, the flight profile is ready to be recorded. Autofly recordings can be up to 15 minutes long. There is sufficient storage space for up to 40 autofly recordings. once recorded and stored,
7-158 Change 2
TM 55-6930-214-10
the autofly sets are indexed on CRT page 400.
CRT pages 421 through 460 have been
dedicated for autofly sets and provide a description of each set. (See figure
c.
During the recording of the flight profile, the instructor can make use of other CMS instructional features, such as problem freeze, store/reset, current conditions, and IC sets, as often as necessary until a model performance of the desired flight profile is obtained. This process can be repeated until the instructor is satisfied that each segment of the profile has been flown to the required standards.
d.
After completing the recording of the flight profile, up to nine segment identifiers that permit direct access to the individual segments of the recording for future training use can be added.
The text description and segment identifier descriptions can then be added to the autofly set by running a separate offline task.
e.
The autofly preparation CRT page is 945.
(See figure 7-70.) The following
rules and guidelines are applicable to the use of this page during preparation:
(1) The AUTOFLY SET NO. (line 01) is used for identification and recall of autofly sets (e.g., 01 TAB 02 ENTER identifies autofly set No. 2).
(2) Autofly recording begins at the record number selected by the user. The maneuver record is defined by recordings between periods of freeze. For a new autofly, recording must start at segment one.
(3) The RECORD command (line 03) starts the recording (when PROB FREEZE is released). When that portion of the profile is complete. problem freeze is activated.
(4) The recorded portion can now be played back for review and critique via the PLAYBACK command (line 04). The autofly elapsed-time indicator (in the status area) provides a time indication of the playback period.
(5) (Deleted)
(6) (Deleted)
(7) The SET SEGMENT command (line 05) is used to mark segment beginnings. as desired. The CLRAR SEGMENT command (line 06) removes a segment marking that is not required or desired.
(8) When the segmentation of the recording is complete, autofly set is ready for permanent storage. The PREP COMPLETE, SAVE AUTOFLY FOR REPLAY command (line
88) is used. The text descriptions for autofly can be added by processing the offline task to do this.
Change 2 7-159
TM 55-6930-214-10
7-62.
TARGET ENGAGEMENT EXERCISE PREPARATION.
The purpose of the TEE preparation feature is to permit target engagement exercises to be prepared by selecting a set of target events to be simulated during a subsequent instructional activity and identifying specific contingencies that, if met, during such instruction, will trigger the insertion of each of the selected target events.
Preparation of a TEE is preceded by the development of a tactical situation description or scenario.
This scenario provides a context within which the intended target engagement instructional activities can take place.
It also permits the instructor to determine which target sites should be activated, what targets should be placed on each activated site, when target events should be activated to be of most instructional value, and the triggering contingencies that are both probable (as to occurrence) and realistic (as to circumstances of occurrence).
There is computer space for preparation and storage of 20 TEE’s in the CMS.
a.
The major characteristics of each TEE are as follows:
(1) Each TEE can accomnodate up to 10 individual targets.
(2) Targets are selected from the 44 types on target list CRT pages 951A, 951B and 951C.
(3) A maximum of five targets per TEE can be assigned to travel over predetermined paths, and five can be assigned to fixed sites.
(4) Up to 15 events can be programmed for each TEE (events equal motion and hostile actions).
(5) Up to three sets of triggering contingencies can be defined for each event.
(Contingencies include parameters and operators and. if more than one parameter is selected, connectors required.)
(6) Specific aircraft malfunctions/systems failures can be assigned to each hostile target; the failure occurs if the threat scores a hit on ownship.
(7) HOT or COLD IR coding can be assigned to each target (only stationary targets can be IR COLD).
(8) For ground targets assigned to sites permitting motion, travel pathways can be selected, and vehicle speed from 0 to 40 kph, in 10-kph increments, can be designated.
(9) Five sites are designated for airborne targets only. When any of these sites are assigned to a TEE, vehicle speed up to 200 kph can be designated.
b.
In conjunction with the development of the scenario for the TEE, the instructor should identify IC or autofly set(s) to be used with it.
This is important because using a specific IC or autofly set with a particular exercise will place the simulated aircraft in the vicinity of the target sites to be activated and provide an additional degree of standardization for the planned target engagement instruction.
c.
When CRT page 950 is called up via the data entry keyboard, the main page
area contains a blank target engagement exercise prep page (figure 7-71) that is
completed during the preparation process and then stored in group 5 (TARGETS, CRT pages 501 through 520) for recall during subsequent training periods.
The data from
Change 2 7-161
TM 55-6930-214-10
the TEE worksheet (figure 7-72) should be entered on the appropriate lines of
CRT page 950.
The index and control area (figure 7-71) includes the TEE PREP IDENTI-
FIERS with reference numbers (REF #) for the TARGET EVENTS, PARAMETERS, OPERATORS, and CONNECTORS that are required for entry on the CRT page.
d.
Line 01 (main page area, figure 7-71) is used to enter the identifying set
number for the TEE.
Command line 77 is used to clear the display and, when keyed
In, clears all data items entered.
When a TEE prep is complete, keying command line 88 places the data displayed on CRT page 950 in permanent storage in the target grouping where it is available for recall by its CRT page number (501 through 520).
Command line 99 is used to terminate (cancel) the preparation activity; nothing is retained in storage when line 99 is keyed in.
e.
On CRT page 950, there are four lines of data for each target In lines 02 through 11.
The first line for each target (lines 12, 16, 20, etc.) is for identifying the target site number from the target site list and the event reference number from the Index and control area.
The indented line numbers (13, 14, 15; 17,
18. 19; etc.) are for insertion of the contingencies that will trigger the event.
Up to three contingencies can be entered for each event.
Each contingency line accommodates one parameter, one operator, and one connector, as required to define the triggering activity.
(The contingencies are further explained in the following subparagraph f.) f .
The index and control area of CRT page 950 (TEE PREP IDENTIFIERS, figure
7-71) provides command reference numbers (REF #) so that titles and or multiple
items can be keyed In with a signal keystroke.
(1) Reference numbers 1 and 2 are used to key in the target event. When motion (reference number 1) is enabled and the triggering contingencies have been met, the target travels over a predetermined path at a designated speed for approximately 15 km and stops. When hostile activity (reference number 2) is enabled and the triggering contingencies have been met, the target fires at the ownship. If a hit (malfunction code number) has been designated and the threat algorithm concurs, a malfunction or system failure occurs with the hit.
(2) Reference numbers 3 through 6 are used to enter the appropriate triggering parameters.
When any reference number (3 through 6) is keyed in on a specific line, the parameter title appears on that line of CRT page 950. The appropriate metrics for parameters are shown In the parenthetical note behind the parameter
( e . g . , %, FT, KIAS, MINS, etc.). The following parameters can be assigned as triggering contingencies:
ALT AGL
LOS
TGT RANGE
- Ownship altitude
- Line-of-sight (intervisibility) between ownship and target, measured in seconds of exposure
- Distance from ownship to target, measured in meters
WPNS RELEASE Firing/release of ownship weapons, measured in seconds after release
(3) Reference numbers 7 through 9 are used to enter arithmetic operators of less than, equal to, or greater than (<, =, >) the assigned value for the triggering parameter.
The assigned value must be keyed in after the associated operator reference number (e.g., 9 TAR 20 ENTER is the entry for greater than 20 f e e t ) .
Each parameter must have an operator and a value assigned to trigger it.
Change 1 7-163
TM 55-6930-214-10
7-164
Change 2
Figure 7-72.
TEE Prep Data Worksheet (Sheet 1)
TM 55-6930-214-10
Figure 7-72.
TEE Prep Data Worksheet (Sheet 2)
Change 2 7-165
TM 55-6930-214-10
7-166 Change 2
Figure 7-72.
TEE Prep Data Worksheet (Sheet 3)
TM 55-6930-214-10
Figure 7-72.
TEE Prep Data worksheet (Sheet 4)
Change 2 7-167
TM 55-6930-214-10
7-168 Change 2
Figure 7-72.
TEE Prep Data Worksheet (Sheet 5)
TM 55-6930-214-10
(4) Reference numbers 10 and 11 are used to enter logical connectors.
If more than one parameter is to be associated with an event, then a logical connector
(AND, OR) must be designated for all but the last parameter. Reference numbers 10 and 11 are used for these connectors.
When AND is used as a connector, all parameters connected with AND must be met to trigger the event.
If OR is used as a connector, any of the parameters connected by OR will trigger the event when it is met.
(5) Reference number 101 is used to clear a line (e.g., 15 TAB 101 clears line
15).
When a line which has other lines dependent on it is cleared, the dependent lines are also cleared (e.g.. 16 TAB 101 clears lines, 16, 17. 18 and 19).
g.
During TEE preparation functions, the edit area of the CRT page provides operator prompts for data input and error messages for any out-of-range or invalid entries.
Numerical inputs via the keyboard are echoed in the edit area with a cursor to indicate the next entry.
When TAB is depressed between data fields, the appropriate data input appears on the first line of the edit area (e.g., when 02
TAB is keyed in, the prompt appearing in the edit area states:
ENTER TARGET TYPE
REFERENCE NUMBER).
(Target type reference numbers are listed on the target types list CRT page 951).
NOTE
If an error is made entering in data, an error message appears in the edit area (e.g., ERROR - VALUE OUT OF RANGE). To correct the error, depress the BACKSPACE or CLEAR keys to delete the entry, then insert the correct data.
h.
Table 7-14 indicates the procedure required to enter the worksheet data into
CRT page 950 and the prompts and data displayed in the edit area.
In the entry column are the numbers to be entered plus the appropriate action key (e.g., DISPL,
TAB, ENTER).
The edit area displays column depicts three line entries to include
(Blank) when nothing is shown and a line (
) for the cursor mark. Lines 02 through 06 accommodate entries for MOTION, PATHWAY, and SPEED. Lines 07 through 11 have no MOTION prompts, so ENTER is keyed in after entering the IR code.
After entering all the targets (lines 02 through 11) for a TEE, the triggering contingencies are then entered in lines 12 through 68.
completes the required entries for the first target type, site associated activity, events, and two triggering contingencies.
The process is repeated for each additional target until the TEE prep page is complete.
Each time ENTER is keyed in. the data in line 3 of the edit area blanks and the data appears on that numbered line in the main page area of the prep page.
Change 2 7-169
TM 55-6930-214-10
Entry
Table 7-14.
TEE Prep Data Entry Procedure
Edit area displays
1.
To call up the TEE prep page, enter:
950 (Blank)
950
(Blank)
DISPL (Blank)
(Blank)
2.
To assign a TEE set number, enter:
01 (Blank)
01
(Blank)
TAB ENTER SET NO.
01
(Blank)
NOTE
Each time TAB is keystroked, a prompt appears in the edit area requesting specific data.
01
ENTER
(Blank)
01 01
( B l a n k )
(Blank)
(Blank )
3.
To enter the first target line, enter:
02
(Blank)
02
(Blank)
TAB ENTER TARGET TYPE REFERENCE NUMBER
02
(Blank)
3 ENTER TARGET TYPE REFERENCE NUMBER
02 3
( B l a n k )
7-170
TM 55-6930-214-10
Entry
TAB
20
ENTER
Table 7-14.
TEE Prep Data Entry Procedure - Continued
Edit area displays
ENTER PATHWAY SPEED (0 - 40 IN INCREMENTS OF 10)
02 3 4 22205 1 1 3 20
T-62 SITE 4 HOS ACT ON 22205 HOT MOTION ON PATH 3
ENTER PATHWAY SPEED (0 - 40 IN INCREMENTS OF 10)
02 3 4 22205 1 1 3 20
T-62 SITE 4 HOS ACT ON 22205 HOT MOTION ON PATH 3
(Blank)
(Blank )
NOTE
Step 2. above completes the line entries required for the first target.
To enter additional targets in lines 03 through 11, repeat the procedure.
3.
To enter the first event for TEE set No. 1, enter:
12 (Blank)
12
(Blank)
TAB
4
ENTER SITE NUMBER
12
(Blank)
ENTER SITE NUMBER
12 4
( B l a n k )
TAB ENTER TARGET EVENT REFERENCE NUMBER
12 4
S I T E 4
2
ENTER
ENTER TARGET EVENT REFERENCE NUMBER
12 4 2
SITE 4
(Blank)
(Blank)
7-171
TM 55-6930-214-10
Entry
Table 7-14.
TEE Prep Data Entry Procedure - Continued
Edit area displays
4.
To enter triggering contingcies, enter:
13
TAB
3
TAB
9
TAB
20
(Blank)
13
(Blank)
ENTER PARAMETER REFERENCE NUMBER
13
(Blank)
ENTER PARAMETER
REFERENCE NUMBER
13 3
( B l a n k )
ENTER OPERATOR REFERENCE NUMBER
13 3
ALT (FT AGL)
ENTER OPERATOR REFERENCE NUMBER
13 3 9
ALT (FT AGL)
ENTER PARAMETER VALUE
13 3 9
ALT (FT AGL) >
ENTER PARAMETRE VALUE
13 3 9 20
ALT (FT AGL)>
ENTER
14
(Blank)
(Blank)
(Blank)
14
(BlanK)
TAB
ENTER PARAMETE REFERENCE NUMBER
14
(Blank)
7-172 Change 2
Entry
6
TAB
TAB
10
9
TAB
5
ENTER
TM 55-6930-214-10
Table 7-14.
TEE Prep Data Entry Procedure - Continued
Edit area displays
ENTER PARAMETER REFERENCE NUMBER
14 6
( B l a n k )
ENTER OPERATOR REFERENCE NUMBER
14 6
WPNS (RELEASE - SECS)
ENTER OPERATOR REFERENCE NUMBER
14 6 9
WPNS (RELEASE SECS)
ENTER PARAMETERVALUE
14 6 9
WPNS (RELEASE - SECS) >
ENTER PARAMETER VALUE
1 4 6 9 5
WPNS (RELEASE - SECS) >
ENTER CONNECTOR REFERENCE NUMBER
1 4 6 9 5
WPNS (RELEASE - SECS) >5
ENTER CONNECTOR REFERENCE NUMBER
14 6 9 5 10
WPNS (RELEASE- SECS) >5
(Blank)
(Blank)
Change 2
7-173/(7-174 blank)
TM 55-6930-214-10
Section IV.
SIMULATED MALFUNCTIONS
7-63.
GENERAL.
There are approximately 336 simulated malfunctions, systematically arranged on 29 CRT pages, available for the CMS.
These pages are used to reference the malfunction for selection and possible insertion into the training exercise.
Malfuctions are entered into the simulated environment through the data entry keyboard.
Categories of available malfunctions are indexed by system on CRT page 200.
a.
Active malfunctions are displayed in the status area, and up to six active malfunctions are displayed at one time.
Up to 15 malfunctions can be active at a time.
b.
Individual malfunctions are coded with a specific 5-digit identifier made up of the number of the CRT page that it appears on (three digits) and the line number
(two digits) on that CRT page.
Typing the 5-digit identifier and depressing ENTER on the keyboard inserts the malfunction into simulation.
7-64.
MALFUNCTION INSERTION.
There are two ways of inserting malfunctions into the simulated environment.
One is manually, and the other uses automatic malfunction insertion (AMI).
There are 15 sets of AMI programs available, with up to 10 malfunctions programmed for each one.
a.
During simulation, a selected preprogrammed set of malfunctions can be automatically entered by choosing an AMI before or during training.
Up to three different contingent conditions/parameters can be designated for each malfunction. An
AMI can be inserted at the IOS CRT via the data entry keyboard.
b.
Since the insertion of specific malfunctions is controlled and triggered by conditions that may be beyond instructor control. and the occurrence may disrupt training or overload a trainee at that point, the instructor receives an alert message.
Ten seconds prior to insertion of an AMI malfunction, an alert message with the name of the malfunction flashes in the alert area of the CRT display.
The instructor has the option at this time to allow the malfunction insertion and to monitor trainee response, or to delete it.
If the instructor decides to delete the malfunction, the MALF OVERRIDE switchlight on the forward control panel must be depressed.
Depressing the switchlight deletes the impending malfunction for the remainder of the training period without affecting the remainder of the malfunctions in the AMI set.
Once an automatic malfunction has been overridden (deleted), if the Instructor desires, it can be inserted manually via the data entry keyboard.
7-65.
MALFUNCTI0N DELETION.
Active malfunctions can be deleted at any time by either of the following methods: a.
Once Inserted, the malfunction can be removed by reentering the identifier.
b.
Active malfunctions can also be removed by depressing the REM0VE ACTIVE MALFS switchlight on the forward control panel.
7-66.
CLEARING MALFUNCTI0NS.
A11 malfunctions can be cleared by deletion except the ones that trip circuit breakers (CB).
Circuit breakers must be manually reset after the malfunction has been deleted.
When a CB malfunction is active, the circuit breaker cannot be manually reset.
7-175
TM 55-6930-214-10
7-67.
MALFUNCTION LIST.
Table 7-15 lists the CRT line select numbers and descrip-
tive titles of the available malfunctions.
Primarily, the malfunctions are grouped by system in numerical order.
Malfunction details In table 7-16 include the mal-
function name as It appears on the CRT, the CRT reference number, aircraft indications and related effects, the Indications presented to the instructor and trainee, and any corrective action that is required.
The CRT reference number consists of the CRT page number (first three digits) and the CRT page line number (last two digits).
7-176 Change 1
TM 55-6930-214-10
Table 7-15.
Malfunctions List
221 Auxiliary Power Unit/Fuel System
Auxiliary Power Unit
22l0l
22102
22103
22104
APU FAIL
AFU HANG START
APU CNTRL. NG>107
APU FIRE
Fuel Systems
22120
22121
22122
22123
22124
22125
22126
22127
22128
22129
22130
FUEL BOOST PUMP
FUEL XFER PUMP
PLT FUEL QTY IND
FUEL QTY UNBAL
FUEL CROSSFEED
FUEL CONTAMINATE
#l FUEL FTR CLOG
#2 FUEL FTR CLOG
#I1 FUEL PRESSURE
#2 FUEL PRESSURE
REFUEL VALVE OPN
222Ol
22202
22203
22204
22205
22206
22207
22208
22209
22210
222ll
22212
22213
22214
222 Enqine Instruments/Environmental Control
Engine Instruments
#l NG IND 0
#2 NC IND 0
#1 OIL PRESS 0
#2 OIL PRESS 0
PILOT NR IND 0
PLT/CPG NR IND 0
#l TGT IND 0
#2 TGT IND 0
PILOT #l TQ 0
PILOT #2 TQ 0
PLT/CPG #1 TQ 0
PLT NPl IND 0
PLT NP2 IND 0
P/G NPl IND 0
Environmental Control
22220
22221
SDC
ECS
change 1 7-177
22309
22310
22311
22312
22313
22314
22315
22316
22301
22302
22303
22304
22305
22306
22307
22308
22317
22318
22319
TM 55-6930-214-10
Table 7-15.
Malfunctions List - Continued
223 Engine Systems
#l NO START
#2 NO START
#l HOT START
#2 HOT START
#l RANG START
#2 HANG START
#l FIRE INTERNAL
X2 FIRE INTERNAL
#l FIRE EXTERNAL
#2 FIRE EXTERNAL
#l FLAMEOUT
#2 FLAMEOUT
BOTH FLAMEOUT
#l FUEL CONTROL
#2 FUEL CONTROL
#l ALTERNATOR
#2 ALTERNATOR
#l ECU HI
#2 ECU HI
22328
22329
22330
22331
22332
22333
22334
22335
22320
22321
22322
22323
22324
22325
22326
22327
22336
22337
22338
#1 ECU LO
#2 ECU LO
#l LD DMD SPNDL
#2 LD DMD SPNDL
#l PWR AVL SPNDL
#2 PWR AVL SPNDL
#1 CMPRESS STALL
#2 CMPRESS STALL
#l LOSS OF OIL
#2 LOSS OF OIL
#l OIL FILTER
#2 OIL FILTER
#2 CHIPS LIGHT
#1 CHIPS W/FAIL
#2 CHIPS W/FAIL
#1 ACC DRIVE SET
#2 ACC DRIVE SET
#l ANTl-ICE
#2 ANTI-ICE
Fliqht Controls
22401 CONTROL FRICTION
224 Fliqht Controls/ASE/Stabllator
Stabilator
22440
22441
AUTO STAB
MANUAL STAB
ASE
22420
22421
22422
22423
22424
22425
22426
22427
SAS LOSS PITCH
SAS LOSS ROLL
SAS LOSS YAW
SAS ALL CHNLS
SAS ERRATIC
CAS LOSS
BUCS
DASE
7-178 Change 1
TM 55-6930-214-10
Electrical
226O9
22610
22611
22612
22613
22614
22615
22616
22601
22602
22603
22604
22605
22606
22607
22608
Table 7-15. Malfunctions List - Continued
225 Transmission/Rotor
Transmission
22509
22510
22511
22512
22513
22514
22515
22516
22517
22518
22501
22502
22503
22504
22505
22506
22507
22508
#l XMSN OIL PRESS
#2 XMSN OIL PRESS
#l XMSN COOLER
#2 XMSN COOLER
#1 OIL QTY LOW
#2 OIL QTY LOW
MAIN XMSN CHIPS
#1 INPT DRIV SFT
#2 INPT DRIV SFT
ACC DRIVE GBX
#l NOSE GBX PUMP
#2 NOSE GBX PUMP
#l NOSE GBX HOT
#2 NOSE GBX HOT
#l NOSE GBX CHIP
#2 NOSE GBX CHIP
GBX VIBRATION
COOLING FAN
Rotor
22520
22521
22522
22523
22524
22525
22526
22527
22528
MRTR OUT OF TRK
MRTR OUT OF BAL
BLADEDAMPER
RTR BK ENG FLT
TLRTR BLADE LOSS
TLRTR GBX LOSS
TRTR THRUST LOSS
TLRTR FIXED
TLRTR OUT OF TRK
BATTERY RELAY
HOT BATTERY
BATTERY CHARGER
#1 AC GENERATOR
#2 AC GENERATOR
BOTH AC GENS
#l AC CONTACTOR
#2 AC CONTACTOR
DC CONTACTOR
PLT FLT INST LT
CPG FLT INST LT
#l TRU
#2 TRU
BOTH TRU'S
#l TRU HOT
#2 TRU HOT
226 Electrical/Hydraulic
Hydraulic
22620
22621
22622
22623
22624
22625
22626
22627
22628
22629
22630
PRI HYD
UTIL HYD
BOTH HYD
PRI HYD OIL LOU
UTIL HYD OIL LOW
PRI HYD FILTER
UTIL HYD FILTER
UTIL ACCUM PRESS
LEFT BRAKE
RIGHT BRAKE
TAILWHEEL LOCK
Change 1 7-179
22801
22802
22803
22804
22805
22806
22807
22808
22809
22810
22811
22812
22717
22718
22719
22720
22721
22722
22723
22724
22709
22710
22711
22712
22713
22714
22715
22716
22701
22702
22703
22704
22705
22706
22707
22708
TM 55-6930-214-10
Table 7-15. Malfunctions List - Continued
227 Pilot Center Circuit Breaker Panel
ASE AC
ASE DC
ASE BUCS
VIB MON
ENG INST
FIRE DETR ENG 1
FIRE DETR ENG 2
FIRE DETR APU
FIRE EXTGH PLT
FIRE EXTGH CPG
FIRE EXTGH APU
FUEL VLV ACTR
FUEL FILL
FUEL AFU
ENG WARN
JETT
LT ANTI COL
LT PRI
LT NAV
LT FORM
LT SRCH LDG
LT SRCH/LDG CNTR
LT CAUT
LT UTIL SEC
22725
22726
22727
22728
22729
22730
22731
22732
22733
22734
22735
22736
22737
22738
22739
22740
22741
22742
22743
22744
22745
22746
22747
22748
EMERG HYD
TRIM
RDR ALT
STBY ATTD
THROT
ENG CUT
ENG LVR
ENG START
FUEL XFEED
FUEL TRANS
FUEL BST
TWHL LOCK
COMM ADF
COMM IFF
COMM KY 58
COMM UHF AM
COMM KY 28
COMMVHF FM
COMM ICS
PITOT HTR
RDR WARN
RTR BRK
AFU HOLD
CHAFF
228 Pilot Forward Circuit Breaker Panel
MISSION JETT
MISSION EL DC
MISSION EL AC
MISSION PNVS DC
MISSION PNVS AC
MISSION SYM GEN
NAV HARS AC
NAV HARS DC
NAV DPLR
RKT ELEX
ARMCONTR
PEN AIDS CONTR
22813
22814
22817
22818
22819
22820
22821
22822
22823
RDR JAM DC
IHADSS
22815
HSI
22816 VDU
FC AC
FC DC
IR JAM PWR
IR JAM XMTR
RDR JAM AC
AIR DATA AC
AIR DATA DC
7-180 Change 1
TM 55-6930-214-10
Table 7-15.
Malfunctions List - Continued
229 Pilot Aft Circuit Breaker Panel
22901
22902
22903
22904
22905
22906
22907
22908
22909
22910
22911
ECS FAB FANS
ECS CAB
ECS AFT FAN
STAB AUTO AC
STAB AUTO DC
STAB MAN DC
STAB MAN AC
WSHLD WPR
ICE DET
BLADE DEICE CONT
BLADE DEICE
22912
22913
22914
22915
22916
22917
22918
22919
22920
22921
CNPY ANTIICE CNT
NOSE GRBX HT
ENG ANTI ICE
CANOPY ANTI ICE
PWR XFMR RECT 1
POWER ENG 1
POWER ENG 2
PWR XFMR RECT 2
PWR BATT CHGR AC
PWR BATT CHGR DC
230 CPG Circuit Breakers
CPG N
O
. 2 Panel
23032
23033
23034
23035
IHADSS
TADS DC
TADS AC
LASER
CPG No. 1 Panel
23017
23018
23019
23020
23021
23022
23023
23024
23025
23026
23027
23028
23029
23030
23031
23001
23002
23003
23004
23005
23006
23007
23008
23009
23010
23011
23012
23013
23014
23015
23016
PRI LT
CAUT
UTIL SEC LT
ENG INST
VHF AM FM
ICS
MSL ARM
MSL L OUTBD DC
MSL R OUTBD AC
MSL L INBD DC
MSL R INBD AC
MSL DC ELEC
MSL R OUTBD DC
MSL L INBD AC
MSL R INBD DC
MSL L OUTBD AC
FC FCC AC
FC FCC DC
FC RCDR
ATTD IND
AWS AMMO
AWS MTR
AWS AC
AWS DC
MUX L PYL OUTBD
MUX L PYL INBD
MUX R PYL OUTBD
MUX R PYL INBD
MUX FAB L
MUX FAB R
MUX CPG
Change 1 7-180.1
TM 55-6930-214-10
Flight Instruments
23101
23102
23103
23104
23105
23106
23107
PITOT TUBE MOIST
TURN INDICATOR
MAGNETIC COMPASS
RADAR ALTIMETER
PILOT ATT IND
STABILATOR IND
ADSS
Communications
23120
23121
23122
23123
23124
23125
VHF XCVR-PLT
VHF XCVR-CPG
UHF XCVR
PLT INTERCOM
CFG INTERCOM
IFF
Table 7-15.
Malfunctions List - Continued
231 Fliqht Instruments/Communications/Navigtion
Navigation
23140
23141
23142
23143
23144
23145
23146
23147
23148
23149
23150
23151
ADF RCVR
ADF BEARING
DOPPLER RTA
DOPPLER SDC PVR
HARS HEADING
HARS
HSI COMPASS CARD
HSI COURSE BAR
ADF TO HSI
LDNS TO HSI
RMI PTR FRZ
ADI-CPG
23201
23202
23203
23204
23205
23206
23207
23208
23209
23210
23211
232 Mission Avionics
Target Acquisition/Designation Siqht Pilot Niqht Vision Sensor
TADS
RANGEFINDER
DESIGNATOR
LASER HOT
DTV
TADS-FLIR
TADS-FLIR COOLER
LASER SPOT TRKR
IAT NO LOCK-ON
IMAGE AUTO TRKR
LMC
23220
23221
23222
23223
23224
23225
23226
23227
PNVS
PNVS LOCKED
PNVS VIDEO
PNVS AZ DRIVE MTR
PNVS COOLER
SEU
PLT DAP
CPG DAP
Symbol Generator
23240 SYMBOL GENERATOR
Fire Control Computer
23260 FCC
Video Display Unit
23280 VDU
7-180.2
Change 1
TM 55-6930-214-10
Table 7-15.
Malfunctions List - Continued
233 Weapons/Aircraft Survivabllity Equipment
Missiles
23301
23302
23303
23304
23305
23306
23307
23308
23309
HELLFIRE SYSTEM
MISSILE HANGFIRE
MISSILE MISFIRE
MSL UNLATCHED
MSL BIT
L OUTBD LNCHR
L INBD LNCHR
R OUTBD LNCHR
R INBD LNCHR
Gun/Rockets
23310
23311
23312
23313
23314
GUN TURRET JAM
GUN NO FIRE
ARCS
ROCKET HANGFIRE
ROCKETS MISFIRE
Aircraft Survivability Equipment
23320
23321
23322
23323
IR JAMMER
RADAR JAMMER
CHAFF DISPENSER
RDR WARN RCVR
Change 1 7-180.3/(7-180.4 blank)
Change 1
Required malfunction
APU FAIL
Table 7- 16.
Malfunction Details
Ref Aircraft indications number and related effects
22101 After starting, APU rpm is below minimum requirement.
Corrective act ion
Noncorrectable
APU
HANG START
APU CNTLR.
NG>107
APU FIRE
22102
22103
22104
APU fails to ramp to full rpm value (8216).
APU Ng exceeds design limits and fails to enter auto shutdown.
Fire condition is present in APU compartment.
Noncorrectable
Noncorrectable
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: APU FAIL appears on CRT.
Trainee : APU ON light is off. FAIL APU light illuminates. APU performs an auto shutdown. Fault signal
( FD/LS ) .
Instructor: APU HANG START appears on CRT.
Trainee: APU START light does not illuminate. FAIL
APU light illuminates. Fault signals (FD/LS) Apu start and
APU clutch signals (FD/LS)
Instructor: NO APU FAIL appears on CRT.
Trainee: APU FAIL light is off. No auto shutdown occurs. After 2 minutes (±5.0
seconds . APU fails.
Instructor: APU FIRE appears on CRT.
Trainee: APU FIRE PULL HAN
DLE. APU FIRE MASTER CAUTION.
and MASTER CAUTION lights illuminate.
TM 55-6930-214-10
7-182
Required malfunction
FUEL BOOST
PUMP
FUEL XFER
PLT FUEL
QTY IND
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22120
Boost pump fails to pressurize.
Noncorrectable Instructor: FUEL BOOST PUMP appears on CRT.
22121
22122
FUEL TRANSFER switch has no control over transfer pump.
Pilot fuel quantity indicator fails.
Noncorrectable
Noncorrectable
Trainee: If boost pump was operating prior to insertion of this malfunction, BOOST
PHP ON light extinguishes.
Engines 1 and 2 startups are not possible.
Instructor: FUEL XFER PUMP appears on CRT.
Trainee: Fuel quantity indicators show fuel tank depletion/gain based on position of TRANSFER switch prior to insertion of malfunction.
TASK SELECT switch must be used for fuel management.
Instructor: PLT FUEL QTY IND appears on CRT.
Trainee: Pilot fuel quantity indicator (aft) fails and remains in last position.
Change 1
Required malfunction
FUEL QTY
UNBAL
FUEL
CROSSFEED
FUEL
CONTAMINATE
#l FUEL FTR
CLOG
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22123 Unbalanced fuel burning in forward tank after 30 minutes operation (depending on when malfunction is inserted).
Noncorrectable Instructor: FUEL QTY UNBAL appears on CRT.
Trainee : FUEL LOU light illuminates on pilot and CPG caution panels.
Fuel quantity gages reflect fuel status.
22124 FUEL CROSSFEED switch has no control over position of crossfeed valve.
22125 Unsuccessful fuel use.
Noncorrectable
Noncorrectable
Instructor: FUEL CROSSFEED appears on CRT.
Trainee : Fuel quantity indicators show fuel depletion from appropriate tank based on position prior to insertion of malfunction.
Instructor : FUEL CONTAMINATE appears on CRT.
22126 Engine 1 fuel filter becomes clogged and is bypassed.
Noncorrectable
Trainee : FUEL BYP ENG 1 light illuminates. followed
30 seconds later by FUEL BYP
ENG 2.
Engine power may fluctuate.
Instructor: #l FUEL FTR CLOG appears on CRT.
Trainee: Fuel bypass ENG 1 light illuminates.
TM 55-6930-214-10
7-182
7-184
Change 1
Required malfunction
#2 FUEL FTR
CLOG
#l FUEL
PRESSURE
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22127 Engine 2 fuel filter becomes clogged and is bypassed.
22128 Engine 1 fuel pressure is lost and rate of flow decreases.
Noncorrectable Instructor: #2 FUEL FTR CLOG appears on CRT.
Trainee: Fuel bypass ENG 2 light illuminates.
Either crewmember Instructor:
#l fUEL PREScan engage boost SURE appears on CRT.
pump within 15 seconds.
Trainee: Engine 1 flames out if boost pump is not engaged within 15 seconds.
If boost pump is engaged, pilot MASTER CAUTION and
BOOST PHP ON lights illuminate. and engine 1 runs off boost pump.
If engine 1 flames out, pilot and CPG
MASTER CAUTION and ENG 1 OUT lights illuminate.
All engine 1 instruments settle to zero.
TM 55-6930-214-10
Change 1
Required malfunction
#2 FUEL
PRESSURE
REFUEL
VALVE OPN
#l NG IND 0
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
22129
Engine 2 fuel pressure is lost.
Corrective act ion
Indications presented to instructor/operator and trainee
Either crewmember Instructor: #2 FUEL PREScan engage boost SURE appears on CRT.
pump within 15 seconds. Trainee: Engine 2 flames out if boost pump is not engaged within 15 seconds.
If boost pump is engaged, pilot MAST-
ER CAUTION and BOOST PMP ON lights illuminate, and engine 2 runs off boost pump.
If engine 2 flames out, pilot and CPG MASTER CAUTION and
ENG 2 OUT lights illuminate.
All engine 2 instruments settle to zero.
22130 Refuel valve is open.
Noncorrectable Instructor: REFUEL VALVE appears on CRT.
22201 Engine 1 gas generator stays at or goes to zero.
Noncorrectable
Trainee: REFUEL VALVE OPEN and RASTER CAUTION lights illuminate.
Instructor: #l NC IND 0 appears on CRT.
Trainee : If starting engine.
indicator remains at zero while engine 1 spools up.
If engine is operating normally. indicator decreases to zero while engine continues to operate normally.
TM 55-6930-214-10
7-185
7-186
Change 1
Required malfunction
#2 NG IND 0
#l OIL
PRESS 0
#2 OIL
PRESS 0
Ref number and related effects
22202
Table 7-16.
Malfunction Details Continued
Aircraft indications
Engine 2 gas generator stays at or goes to zero.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #2 NG IND 0 appears on CRT.
22203
Engine 1 oil pressure indi- Noncorrectable cation decreases to zero.
Trainee: If starting engine.
indicator remains at zero while engine 2 spools up.
If engine is operating normally, indicator decreases to zero while engine continues to operate normally.
Instructor: #l
OIL
PRESS 0 appears on CRT.
22204 Engine 2 oil pressure indi- Noncorrectable cation decreases to zero.
Trainee: Engine 1 indicated oil pressure decreases to zero.
OIL PRESS ENG 1 caution light does not illuminate.
Instructor: X2 OIL PRESS 0 appears on CRT.
Trainee: Engine 2 indicated oil pressure decreases to zero.
OIL PRESS ENG 1 caution light does not illuminate.
TM 66-6930-214-10
Change 1
Required malfunction
PILOT NR
IND 0
PLT/CPG
NR IND 0
#l TGT
IND 0
#2 TGT
IND 0
PILOT #l
TQ 0
Ref
22205
Table 7-16.
Halfunction Details - Continued
Aircraft indications number and related effects
Pilot rotor tachometer decreases to zero.
Corrective act ion
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: PILOT NR IND 0 appears on CRT.
22206 Rotor tachometers fluctuate Noncorrectable and decrease to zero.
Trainee: Pilot indicated rotor tachometer decreases to zero.
Instructor: PLT/CPG NR IND appears on CRT.
Trainee: Rotor tachometer fluctuates for 30 seconds and then decreases to zero.
22207
Engine 1 turbine gas temperature indicator decreases to zero.
Noncorrectable
Instructor: #l TGT IND 0 appears on CRT.
Trainee: Engine 1 indicated engine turbine gas temperature decreases to zero.
22208
Engine 2 turbine gas temperature indicator decreases to zero.
Noncorrectable
22209 Engine 1 torque indicator decreases to zero.
Noncorrectable
Instructor: #2 TGT IND 0 appears on CRT.
Trainee:
Engine 2 indicated engine turbine gas temperature decreases to zero.
Instructor:
PILOT #l TQ 0 appears on CRT.
Trainee: Engine 1 torque indicator decreases to zero.
TM 55-6930-214-10
7-187
7-188
Change 1
Required malfunction
PILOT #2
TQ O
PLT/CPG #l
TQ 0
PLT NP1
IND 0
PLT NP2
IND 0
Ref number
Table 7-16.
Malfunction Details - Continued
A i r c r a f t i n d i c a t i o n s and related effects
Corrective action
Indications presented to instructor/operator and trainee
22210
Engine 2 torque indicator decreases to zero.
Noncorrectable Instructor : PILOT #2 TQ 0 appears on CRT.
Trainee :
Engine 2 torque indicator decreases to zero.
22211 Engine 1 torque indicator decreases to zero for both crewmembers.
Noncorrectable I n s t r u c t o r :
PLT/CFG #1 TQ 0 appears on CRT.
-
Engine 1 torque indicator decreases to zero.
22212 Pilot NP1 indicator drops t o z e r o .
Noncorrectable I n s t r u c t o r : PLT NP1 IND 0 appears on CRT.
Trainee : Engine 1 NP ind i c a t o r i n p i l o t c o c k p i t drops to zero.
22213 Pilot NP2 indicator drops t o z e r o .
Noncorrectable I n s t r u c t o r : PLT NP2 IND 0 appears on CRT.
Trainee : Engine 2 NP indicator in pilot cockpit drops to zero.
TM 55-6930-214-10
Change 1
Required malfunction
P/G NP1
IND 0
SDC
ECS
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
22211
Engine 1 pilot and CPG NP indicators drop to zero.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: P/G NP1 IND 0 appears on CRT.
22220
22221
Pressurized air from
SDC compressor not available.
Pressurized air from
ECS not available.
Noncorrectable
Noncorrectable
Trainee: Engine 1 NP indicator in pilot and CPG cockpits drop to zero. Both indicators drop simultaneously in integrated mode.
In independent mode, only active indicator drops.
Instructor: SDC appears on CRT.
Trainee: SHAFT DRIVEN COMP and MASTER CAUTION lights illuminate.
(Air still flows to simulator to avoid damage to equipment.)
Instructor : ECS FAIL appears on CRT.
Trainee: ECS and MASTER CAU-
TION lights illuminate.
(Air still flows to simulator to avoid damage to equipment.)
TM 55-6930-214-10
7-189
7-190
Change 1
#l NO 22301 Starter circuit breaker
START
Pops .
Table 7-16. Malfunction Details - Continued
Indications presented
Required Ref Aircraft indications Corrective to instructor/operator malfunction number and related effects act ion and trainee
Noncorrectable Instructor: #1 NO START appears on CRT.
Trainee: Starter circuit breaker pops. If NG is 40% or greater, there is no further effect. If NG is less than 40%. NG decreases to zero, and ENG 1 light above
ENG START switch extinguishes.
#2 No
START
22302 Starter circuit breaker pops.
Noncorrectable Instructor: #2 NO START appears on CRT.
Trainee: Starter circuit breaker pops. If NG is 40% or greater, there is no further effect. If NG is less than 40%. NG decreases to zero, and ENG 2 light above
ENG START switch extinguishes.
#l HOT
START
22303 Engine 1 lights and accelerates normally but stabilizes below idle conditions. TGT begins to rise at 1.5 times normal rate.
886°C not exceeded Instructor: #l HOT START if abort proce- appears on CRT.
dures initiated in time to correct Trainee: NG increases to
HOT START about 40%. then decreases to 37 (±5)%. TGT increases
1.5 times normal rate and exceeds 886°C on engine 1 if corrective action not taken.
TM 55-6930-214-10
Change 1
Required malfunction
#2 HOT
START
#1 HANG
START
#2 HANG
START
#l FIRE
INTERNAL
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
22304
Engine 2 lights and accelerates normally but stabilizes below idle condit ions.
TGT begins to rise at 1.5 times normal rate.
22305 Engine 1 lights normally and accelerates but stabilizes below normal idle speed and engine 1 TGT stabilizes below starting limit.
Corrective action
Indications presented to instructor/operator and trainee
886°C not exceeded
Instructor: #2 HOT START if abort proceappears on CRT.
dures initiated in time to correct Trainee: NG increases to
HOT START.
about 40%. then decreases to
37 (±5N.
TGT increases 1.5
times normal rate and exceeds
886°C on engine 2 if corrective action not taken.
Noncorrectable Instructor: #1 HANG START appears on CRT.
Trainee : Engine 1 NG hangs around 40 (+5)% and TGT hangs about 35O°C (+20%).
22306 Engine 2 lights normally and accelerates but stabilizes below normal idle speed and engine 2 TGT stabilizes below starting limit.
Noncorrectable
22307
TGT increases above 886º C.
Noncorrectable
Instructor: #2 HANG START appears on CRT.
Trainee: Engine 2 NG hangs around 40 (+5)% and TGT hangs about 35O°C (±20%).
Instructor: #l FIRE INTERNAL appears on CRT.
Trainee:
Engine 1 TGT increases above 886°C.
TM 55-6930-214-10
7-191
7-192
Change 1
Required malfunction
#2 FIRE
INTERNAL
#l FIRE
EXTERNAL
#2 FIRE
EXTERNAL
#l FLAMEOUT
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Corrective action
22308
TGT increases above 886° C.
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #2 FIRE INTERNAL appears on CRT.
Trainee: Engine 2 TGT increases above 886°C.
22309 Fire condition is present in engine 1 bay.
Noncorrectable
Instructor: #1 FIRE EXTERNAL appears on CRT.
Trainee: Engine 1 FIRE PULL
HANDLE light illuminates.
22310 Fire condition is present in engine 2 bay.
Noncorrectable
Instructor: #2 FIRE INTERNAL appears on CRT.
Trainee : Engine 2 FIRE PULL
HANDLE light illuminates.
22311 Engine 1 flames out due to Pilot must perform Instructor:
#l FLAMEOUT momentary fuel stoppage.
an in-the-air
Malfunction is deactivated engine restart after engine 1 PCL is moved to IDLE.
appears on CRT.
Trainee : Sudden reduction in engine noise, NG, TGT,
NP. oil pressure, and engine torque for engine 1.
When
NG reaches 55%. ENG OUT,
ENGINE 1, and ENG OIL PRESS warning lights and MASTER
CAUTION light illuminate.
TM 55-6930-214-10
Change 1
Required malfunction
#2 FLAMEOUT
BOTH
FLAMEOUT
#l FUEL
CONTROL
Ref number
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22312 Engine 2 flames out due to Pilot must perform Instructor: #2 FLAMEOUT momentary fuel stoppage.
an in-the-air
Malfunction is deactivated engine restart after engine 2 PCL is moved to IDLE.
appears on CRT.
Trainee : Sudden reduction in engine noise, NG, TGT,
NP. oil pressure. and engine torque for engine 2.
When
NG reaches 55%. ENG OUT,
ENGINE 2, and ENG OIL PRESS warning lights and MASTER
CAUTION light illuminate.
22313
Both engines flame out due
Pilot must perform Instructor: BOTH FLAMEOUT to momentary fuel stoppage.
an in- the-air appears on CRT.
Malfunction is deactivated engine restart after both engine PCL’s are moved to IDLE.
Trainee: Sudden reduction in engine noise. NG, TGT,
NP. oil pressure. and engine torque for both engines.
When NG reaches 55%. ENG OUT,
ENGINE 2, and ENG OIL PRESS warning lights, and MASTER
CAUTION light illuminate.
22314
Engine 1 HMU fails closed.
Noncorrectable Instructor: #l FUEL CONTROL appears on CRT.
Trainee: Sudden reduction in engine noise. NG. TGT,
NP, oil pressure, and engine torque for engine 1.
When
NG reaches 55%. ENG OUT, ENG
OIL PRESS, ENG 1, and MASTER
CAUTION lights illuminate.
7-193
TM 55-6930-214-10
7-194
Change 1
Required malfunction
#2 FUEL
CONTROL
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Corrective action
22315 Engine 2 HMU fails closed.
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #12 FUEL CONTROL appears on CRT.
#1 ALTERNATOR 22316 Loss of engine 1 alternator.
Noncorrectable
Trainee: Sudden reduction in engine noise, NG, TNT, NP.
oil pressure, and engine torque for engine 2.
When
NG reaches 55%. ENG OUT, ENG
OIL PRESS, ENG 2, and MASTER
CAUTION lights illuminate.
Instructor: #l ALTERNATOR appears on CRT.
Trainee : ENGINE 1 OUT and
MASTER CAUTION lights illuminate.
Engine 1 turbine speed, torque, and gas generator speed indicators decrease to zero.
All engine 1 ECU functions are lost except turbine overspeed protection and gas generator speed limiting.
TM 55-6930-214-10
Change 1
Required malfunction
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
#2 ALTERNATOR 22317 Loss of engine 2 alterna tor.
Noncorrectable Instructor:
#2 ALTERNATOR appears on CRT.
Trainee: Engine 2 OUT and
MASTER CAUTION lights illuminate.
Engine 2 turbine speed, torque. and gas generator speed indicators decrease to zero.
All engine 2
ECU functions are lost except turbine overspeed protection and gas generator speed limiting.
#l ECU HI 22318 Engine 1 ECU power turbine Noncorrectable reference speed goes to
104.5 (±2)%.
Instructor: #l ECU HI appears on CRT.
Trainee: If engine 1 is operating independently. engine 1 power turbine and main rotor speed increases to 104 (±2)%. HIGH RPM
ROTOR and RASTER CAUTION lights illuminates.
If both engines are operating, engine 1 power turbine speed increases to 104 (±2)%, and main rotor speed increases to 102 (+2)%.
TM 55-6930-214-10
7-195
7-196
Change 1
Required malfunction
#2 ECU HI
#l ECU LO
Ref number
22319
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Engine 2 ECU power turbine reference speed goes to
104.5 (±2)%.
Corrective act ion
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #2 ECU HI appears on CRT.
Trainee:
If engine 2 is operating independently. engine 2 power turbine and main rotor speed increases to 104
(±2)%.
HIGH RPM ROTOR and
MASTER CAUTION lights illuminate.
If both engines are operating, engine 2 power turbine speed increases to
104 (±2)%. and main rotor speed increases to 102 (+2)%.
22320 Engine 1 ECU power turbine Noncorrectable reference speed goes to
90 (+2)%.
Instructor: #1 ECU LOU appears on CRT.
Trainee: If engine 1 is operating independently, engine 1 power turbine and main rotor speed decreases to 90
(±2)%.
LOW RPM MOTOR and
MASTER CAUTION lights illuminate.
If both engines are operating. engine 1 power turbine speed decreases to
90 (+2)%, but main rotor speed remains at 100 (±2)%.
TM 55-6930-214-10
Change 1
Required malfunction
#2 ECU LO
#l LD DMD
SPNDL
#2 LD DMD
SPNDL
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22321
Engine 2 ECU power turbine Noncorrectable reference speed goes to
90 (±2)%.
Instructor: #2 ECU LOW appears on CRT.
Trainee: If engine 2 is operating independently. engine 2 power turbine and main rotor speed decreases to 90
(±2)%.
LOW RPM MOTOR and
MASTER CAUTION lights illuminate.
If both engines are operating, engine 2 power turbine speed decreases to
90 (±2)%, but main rotor speed remains at 100 (±2)%.
22322 Failure in load demand spindle linkage for engine 1.
Control of power supplied is lost.
Power lever can be used to prevent overspeed if power required is less than min ECU trim at LDS setting available.
Instructor: #l LD DMD SPNDL appears on CRT.
Trainee:
Engine 1 responds more slowly to changes in power requirements within limit of ECU trim. No change in collective force.
22323
Failure In load demand spindle linkage for engine 2.
Control of power supplied is lost.
Power lever can be used to prevent overspeed if power required is less than min ECU trim at LDS setting available.
Instructor: #2 LD DMD SPNDL appears on CRT.
Trainee: Engine 2 responds more slowly to changes in power requirements within limit of ECU trim. No change in collective force.
TM 55-9930-214-10
7-197
7-198
Change 1
Required malfunction
#l PWR AVL
SPNDL
#2 PWR AVL
SPNDL
#l CMPRESS
STALL
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective act ion
Indications presented to instructor/operator and trainee
22324 Failure in power available
Noncorrectable spindle linkaye for engine
1.
22325 Failure in power available spindle linkage for engine
2.
Noncorrectable
Instructor: #1 PWR AVL SPNDL appears on CRT.
Trainee: Power available from engine 1 remains constant with change in PLC setting.
No change in PLC force.
Instructor: #2 PWR AVL SPNDL appears on CRT.
Trainee: Power available from engine 2 remains constant with change in PLC setting.
No change in PLC force.
22326 NG actuator fails and engine compressor section stalls when engine torque is above 65%.
Noncorrectable Instructor: #l CMPRESS STALL appears on CRT.
Trainee: Noticeable bangs heard.
Engine response erratic.
TGT, NG, NP, and engine torque fluctuate for 15 seconds.
When NG reaches
55%, engine goes out and OIL
PRESS ENG 1 and MASTER CAU-
TION lights illuminate.
TM 55-6930-214-10
Change 1
Required malfunction
#2 CMPRESS
STALL
#l LOSS OF
OIL
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective act ion
Indications presented to instructor/operator and trainee
22327 NG actuator fails and engine compressor section stalls when engine torque is above 65%.
Noncorrectable
Instructor: #2 CHPRESS STALL appears on CRT.
Trainee : heard.
Noticeable bangs
Engine response erratic.
TGT, NG, NP, and engine torque fluctuate for 15 seconds.
When NG reaches
55%. engine goes out and OIL
PRESS ENG 1 and MASTER CAU-
TION lights illuminate.
Noncorrectable
22328
Engine 1 oil pressure decreases to zero and subsequent engine seizure occurs.
Instructor: #l LOSS OF OIL appears on CRT.
Trainee : Engine 1 oil pressure drops to zero in approximately 15 seconds. At 27.5
psi, yellow gage lamp segment lights. At 22.5 psi, red gage lamp segment lights.
At 0 psi, OIL PSI ENG 1 caution light illuminates.
After 15 seconds, engine 1 fails, with sudden drop in
NG, TGT, NP, and engine torque.
When engine 1 NG reaches 55%. ENGINE 1 out.
ENG 1 warning, and MASTER
CAUTI
ON lights illuminate.
TM 55-6930-214-10
7-199
Change 1
Required malfunction
#2 LOSS OF
OIL
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22329 Engine 2 oil pressure decreases to zero.
Noncorrectable Instructor: #2 LOSS OF OIL appears on CRT.
#l OIL FILTER 22330
#2 OIL FILTER 22331
Engine 1 oil pressure too high.
Engine 2 oil pressure too high.
Noncorrectable
Noncorrectable
Trainee : Engine 2 oil pressure drops to zero in approximately 15 seconds. At 27.5
psi, yellow gage lamp segment lights.
At 0 psi, OIL
PSI ENG 2 caution light illuminates.
After 15 seconds, engine 2 fails, with sudden drop in NG, TGT, NP, and engine torque.
When engine 2
NG reaches 55%.
ENGINE
2 out,
ENG 2 warning, and MASTER
CAUTION lights illuminate.
Instructor: #l OIL FILTER appears on CRT.
Trainee : Pilot and CPG MAST-
ER CAUTION, pilot OIL BYP
ENG 1, and CPG engine 1 CAU-
TION lights illuminate.
Instructor: #2 OIL FILTER appears on CRT.
Trainee : Pilot and CPG MAST-
ER CAUTION. pilot OIL BYP
ENG 2, and CPG engine 1 CAU-
TION lights illuminate.
TM 55-6930-214-10
Change 1
Required malfunction
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
#2 CHIPS LIGHT 22332 CHIPS ENG 2 caut ion light illuminates.
Noncorrectable Instructor:
#2 CHIPS LIGHT appears on CRT.
#l CHIPS
U/FAIL
22333 Metal chips are detected in oil for engine 1.
Noncorrectable
Trainee: CHIPS ENG #2 and
MASTER CAUTION lights illuminate.
Instructor:
#l CHIPS W/FAIL appears on CRT.
X2 CHIPS
U/FAIL
22334 Metal chips are detected in oil for engine 2.
Noncorrectable
Trainee : CHIPS ENG #1 and
MASTER CAUTION lights illuminate.
Engine 1 power fluctuates, 45 seconds after CHIPS light illuminates.
After 1
(±O.5) minutes, engine 1 failure occurs.
Instructor: #2 CHIPS W/FAIL appears on CRT.
Trainee: CHIPS ENG #2 and
MASTER CAUTION lights illuminate.
Engine 2 power fluctuates 45 seconds after
CHIPS light illuminates.
After 1 (±0.5) minutes.
engine 2 failure occurs.
TM 55-6930-214-10
7-201
7-202
Change 1
Required malfunction
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
#l ACC DRIVE
22335
#l accessory drive shaft
SET fails and drive functions
(such as oil pressure.
NG indication. and NG sensor signals) are lost.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #1 ACC DRIVE SET appears on CRT.
Trainee: Engine 1 main power
ECU is lost.
NG indicator goes to zero in 10 (±l) seconds for both pilot and CPG.
NG sensor signal is lost, and oil pressure decreases to zero for engine 1.
OIL PRESS
ENG 1 and MASTER CAUTION lights illuminate.
#2 ACC DRIVE 22336
#2 accessory drive fails
SET and drive functions (such as oil pressure, NG indication, and NG sensor signals) are lost.
Noncorrectable
Instructor: #2 ACC DRIVE SST appears on CRT.
Trainee: Engine 2 main power
ECU is lost.
NG indicator goes to zero in 10 (±l) seconds for both pilot and CPG.
NG sensor signal is lost. and oil pressure decreases to zero for engine 2.
OIL PRESS
ENG 2 and MASTER CAUTION lights illuminate.
TM 55-6930-214-10
Change 1
Required malfunction
#l ANTI-ICE
#2 ANTI-ICE
CONTROL
FRICTION
SAS LOSS
PITCH
Ref number and related effects
22337
22338
22401
Table 7-16.
Malfunction Details - Continued
Aircraft indications
Engine 1 nose gearbox heat er is overheated and in creasing.
Engine 2 nose gearbox heat er is overheated and increasing.
Control friction failures.
Corrective action
Noncorrectable
Noncorrectable
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #l ANTI-ICE appears on CRT.
Trainee :
MASTER CAUTION at both stations, pilot ENG 1
ANTI-ICE, and CPG ENG ANTI-
ICE lights illuminate.
Instructor:
#2 ANTI-ICE appears on CRT.
Trainee: MASTER CAUTION at both stations. pilot ENG 2
ANTI-ICE and CPG ENG ANTI-
ICE lights illuminate.
Instructor : CONTROL FRICTION appears on CRT.
22420 Loss of stability augmentation system in pitch axis.
Noncorrectable
Trainee: Collective stick creeps during flight.
Instructor: SAS LOSS PITCH appears on CRT.
Trainee:
ASE warning light illuminates. ASE PITCH switch drops to off.
TM 55--6930-214-10
7-203
7-204
Change 1
Required malfunction
SAS LOSS
ROLL
SAS LOSS
YAW
SAS ALL
CHNLS
SAS
ERRATIC
Ref numbcr
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective act ion
Indications presented to instructor/operator and trainee
22421
22422
Loss of stability augmentation system in roll axis.
Loss of stability augmentation system in yaw axis.
Noncorrectable
Noncorrectable
Instructor:
SAS LOSS ROLL appears on CRT.
Trainee: ASE warning light illuminates. ASE ROLL switch drops to off.
Instructor: SAS LOSS YAW appears on CRT.
22423 Loss of stability augmentation system in all channels.
Noncorrectable
Trainee : ASE warning light illuminates.
ASE YAW switch drops to off.
Instructor: SAS ALL CHNLS appears on CRT.
22424 Erratic flight augmentation.
Noncorrectable
Trainee : Switches on DASE panel drop to off. SAS and
MASTER CAUTION lights illuinate at pilot station.
Instructor: SAS ERRATIC appears on CRT.
Trainee : Erratic flight augmentation within envelope of augmentation performance.
TM 55-6930-214-10
Change 1
Required malfunction
CAS LOSS
BUCS
DASE
AUTO STAB
Ref
Table 7-16. Malfunction Details - Continued
Aircraft indications number and related effects
Corrective action lndications presented to instructor/operator and trainee
22425
Loss of command augmentation system.
Disengage SAS
Instructor:
CAS LOSS appears on CRT.
22426
BUCS failure
Noncorrectable
Trainee: Pitch. roll. and yaw inputs no longer augmented.
Aircraft control is sluggish.
Instructor:
BUCS appears on
CRT.
22427
22440
DASE ceases to function.
Stabilator automatic mode failure.
Noncorrectable
Noncorrectable
Trainee: BUC FAIL light illuminates.
Instructor:
DASE appears on CRT.
Trainee:
DASE panel switches drop to off.
ASE and MASTER
CAUTION lights illuminate in pilot station.
If a BUCS malfunction, BUCS capabilities are lost.
Instructor:
AUTO STAB appears on CRT.
Trainee:
MAN STAB and MAST-
ER CAUTION lights illuminate.
Stabilator angle of incidence only changes manually.
Stabilator fail audio is activated .
TM 55-6930-214-10
7-205
7-206
Change 1
Required malfunction
MANUAL STAB
#1 XMSN OIL
PRESS
#2 XMSN OIL
PRESS
#l XMSN
COOLER
Ref
22441
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Stabilator manual mode failure.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MANUAL STAB appears on CRT.
Trainee:
Stabilator position no longer responds to
STABILATOR MANUAL CONTROL switches.
22501 No. 1 transmission oil pump failure.
Noncorrectable Instructor: #l XMSN OIL
PRESS appears on CRT.
22502
22503
No. 2 transmission oil pump failure.
Transmission No. 1 cooler failure causes oil temperature to go out of limits.
Noncorrectable
Noncorrectable
Trainee: OIL PRES MNXHSN 1 light illuminates.
Oil pressure main transmission 1 decreases to zero.
Instructor:
#2 XMSN OIL
PRESS appears on CRT.
Trainee:
OIL PRES MNXMSN 2 light illuminates.
Oil pressure main transmission 2 decreases to zero.
Instructor: #l MHSN COOLER appears on CRT.
Trainee :
OIL PRES MNXMSN 1 light illuminates.
TM 55-6930-214-10
Change 1
Required malfunction
#2 XMSN
COOLER
#1 OIL
QTY LOW
#2 OIL
QTY LOW
MAIN XMSN
CHIPS
Ref number
Table 7-16.
Malfunction Details - continued
Aircraft indications and related effects corrective action
Indications presented to instructor/operator and trainee
22504 Transmission No. 2 cooler failure causes oil temperature to go out of limits.
Noncorrectable Instructor: #2 XMSN COOLER appears on CRT.
Trainee:
OIL PRES MNXMSN 2 light illuminates.
22505 No.1 transmission oil low Noncorrectable
22506
No.2 transmission oil low Noncorrectable
Instructor: #l OIL QTY LOW appears on CRT.
Trainee : MASTER CAUTION light illuminates.
XMSN 1
CPG illuminates concurrent with either OIL PSI MAIN 1 or OIL HOT MAIN XMSN 1.
Instructor: #2 OIL QTY LOW appears on CRT.
22507
Metal chips are detected in main transmission.
Noncorrectable
Trainee: MASTER CAUTION light illuminates.
XMSN 2
CPG illuminates concurrent with either OIL PSI MAIN 2 or OIL HOT MAIN XMSN 2.
Instructor : MAIN XMSN CHIPS appears on CRT.
Trainee: CHIPS MAIN XMSN light illuminates on pilot and CPG panels.
7-207
TM 55-6930-214-10
7-208
Change 1
Required malfunction
#1 INPT
DRIV SFT
#2 INPT
DRIV SFT
ACC
DRIVE GBX
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22508 Input driveshaft from engine 1 nose gear box to
#1 main transmission fails.
Noncorrectable Instructor: #1 INPT DRIV SFT appears on CRT.
Trainee: Power turbine torque from engine 1 is lost.
Power turbine speed increases rapidly to maximum and then shuts down automatically when NP overspeed control is triggered.
22509 Input driveshaft from engine 2 nose gearbox to
#2 main transmission fails.
Noncorrectable
22510 This oil pump failure results in accessory gears not being lubricated when
APU or main transmission is operating.
Noncorrectable
Instructor: #2 INPT DRIV SFT appears on CRT.
Trainee:
Power turbine torque from engine 2 is lost.
Power turbine speed increases rapidly to maximum and then shuts down automatically when
NP overspeed control is triggered.
Instructor:
ACC DRIVE GBX appears on CRT.
Trainee: MASTER CAUTION and
OIL PSI ACC lights illumi nate.
TM 55-6930-214-10
Change 1
Required malfunction
#1 NOSE
GBX PUMP
#2 NOSE
GBX PUMP
#1 NOSE
GBX HOT
#2 NOSE
GBX HOT
Ref number
Table 7- 16.
Malfunction Details Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22511
Failure of No. 1 nose gear box pump.
Noncorrectable Instructor: #1 NOSE GBX PUMP appears on CRT.
22512
Failure of No. 2 nose gear box pump.
Noncorrectable
Trainee: OIL PRESS NS GRBX1 light illuminates.
Oil pressure #1 nose gearbox decreases to zero.
Instructor: #2 NOSE GBX PUMP appears on CRT.
22513
No. 1 nose gearbox oil temperature exceeds 284 O .
Noncorrectable
Trainee : OIL PRESS NS GRBX2 light illuminates.
Oil pressure in #2 nose gearbox decreases to zero.
Instructor: #1 NOSE GBX HOT appears on CRT.
Trainee:
Pilot OIL HOT NOSE
GRBX1 and MASTER CAUTION lights illuminate.
CPG ENG
1 light illuminates.
22514 No. 2 nose gearbox oil temperature exceeds 284
O
.
Noncorrectable Instructor:
#2 NOSE GBX HOT appears on CRT.
Trainee: OIL HOT NOSE GRBX2 and MASTER CAUTION lights illuminate.
CPG ENG 2 light illuminates.
TM 55-6930-214-10
7-209
7-210 Change 1
Required malfunction
#1 NOSE
GBX CHIP
#2 NOSE
GBX CHIP
GBX
VIBRATION
COOLING
FAN
Ref number and related effects
22515
Table 7-16. Malfunction Details - Continued
Aircraft indications
Metal chips detected in
No. 1 nose gearbox pump.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #1 NOSE GBX CHIP appears on CRT.
Trainee: CHIP NOSE GRBX1 and
ENGINE 1 lights illuminate.
22516 Metal chips detected in
No. 2 nose gearbox pump.
Noncorrectable Instructor:
#2 NOSE GBX CHIP appears on CRT.
Trainee: CHIP NOSE GRBX2 and
ENGINE 2 lights illuminate.
22517 Gearbox vibrates.
Noncorrectable
22518 Intermediate and tail gearbox cooling fan failure.
Noncorrectable
Instructor: GBX VIBRATION appears on CRT.
Trainee: MASTER CAUTION and
VIB GRBX lights illuminate at both cockpits.
Directional controls vibrate.
Instructor: COOLING FAN appears on CRT.
Trainee: TEMP TR and TEMP
INT lights illuminate in both cockpits.
TM 55-6930-214-10
Change 1
Required malfunction
MRTR OUT
OF TRK
MRTR OUT
OF BAL
BLADE
DAMPER
RTR BK
ENG FLT
Ref number and related effects
22520
Table 7-16.
Malfunction Details Continued
Aircraft indications
One blade flaps at a different angle from the others due to structural warping or bending.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MRTR OUT OF TRK appears on CRT.
22521
Center-of-gravity of rotor does not coincide with center of hub due to broken blade or other mass imbalance.
Noncorrectable
Trainee: Motion indicating cycling pitch and roll oscillation at main rotor frequency.
Instructor: MRTR OUT OF BAL appears on CRT.
Trainee: Severe vibration at rotor frequency transmitted via motion.
22522
Blade damper for main rotor Noncorrectable becomes inoperative due to separation of bonded rubber from either inside or outside plates of damper.
Instructor:
BLADE DAMPER appears on CRT.
22523 Rotor brake engaged in flight.
Noncorrectable
Trainee Lateral oscillation ranging in frequency from 0 to 5 Hz proportional to main rotor rpm.
Amplitude of oscillation is ±0.2
inch.
Instructor.
RTR BK ENG FLT appears on CRT.
Trainee: ROTOR BRAKE caution light illuminates.
7-211
TM 55-6930-214-10
7-212
Change 1
Required malfunction
TLRTR
BLADE LOSS
TLRTR
GBX LOSS
TRTR
THRUST LOSS
Ref number
22524
Aircraft indications and related effects
All of tail rotor blades gone.
Table 7-16. Malfunction Details - Continued
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: TLRTR BLADE LOSS appears on CRT.
22525 Tail rotor gearbox, blades, and controls lost.
Noncorrectable
Trainee: No directional control authority.
Pitch down due to weight loss.
Severe vibration occurs for 2 seconds before gearbox separation.
TAIL GBX or INTMD
GRBX, VIB GRBX, and TRMPTR lights illuminate.
Instructor: TLRTR GBX LOSS appears on CRT.
22526 Tail rotor does not function; i.e.. no spinning.
Noncorrectable
Trainee: TRMP, INT, VIB
GRBX, and TEMP TR lights illuminate.
Severe vibration occurs for 2 seconds before gearbox separation.
No directional control authority.
Pitch down due to weight loss.
Instructor: TRTR THRUST LOSS appears on CRT.
Trainee: Complete loss of directional control.
TM 55-6930-214-10
Change 1
Required malfunction
TLRTR
FIXED
TLRTR OUT
OF TRK
BATTERY
RELAY
HOT
BATTERY
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Corrective action
22527 Pitch of tail rotor remains Noncorrectable fixed.
Indications presented to instructor/operator and trainee
22528 One blade rotates out of normal plane of rotation of tail rotor due to structural warping or bending .
22601 Battery power not available.
Noncorrectable
Noncorrectable
Instructor: TLRTR FIXED appears on CRT.
Trainee :
Pedals continue to move with no effect on tail rotor thrust.
Instructor:
MRTR OUT OF TRK appears on CRT.
Trainee: Oscillations at tail rotor.
Instructor: BATTERY RELAY appears on CRT.
22602 Temperature reaches 54 exists.
O to Noncorrectable
60°C or cell dissimilarity
Trainee: Emergency battery power is not available when required.
When battery is only source of power, these systems are lost.
Instructor: HOT BATTERY appears on CRT.
Trainee: HOT BATTERY caution light illuminates.
TM 55-6930-214-10
7-213
7-214
Change 1
Required malfunction
BATTERY
CHARGER
#1 AC
GENERATOR
#2 AC
GENERATOR
Ref number
22603
22604
22605
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Battery charger not functional.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: BATTERY CHARGER appears on CRT.
Loss of output from one generator.
Loss of output from one generator.
Noncorrectable
Noncorrectable
Trainee:
CHARGER and MASTER
CAUTION lights illuminate.
Instructor:
#1 AC GENERATOR appears on CRT.
Trainee:
GEN 1 caution light illuminates.
(Also see #2 AC GENERATOR).
Instructor: #2 AC GENERATOR appears on CRT.
Trainee: GEN 2 caution light illuminates.
If both
GEN 1 and GEN 2 are failed,
MASTER CAUTION lights at both stations illuminate.
Pilot GEN 1. GEN 2, RECT 1,
RECT 2, and battery charger caution lights illuminate.
CPG ELEC SYS FAIL lights illuminate.
Generator power is lost.
Battery emergency bus system remains active for 12 minutes.
TM 55-6930-214-10
Change 1
7-215
Required malfunction
BOTH AC
GENS
#1 AC
CONTACTOR
#2 AC
CONTACTOR
Ref number
22606
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Loss of output from both generators.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
BOTH AC GENS appears on CRT.
Trainee : GEN 1, GEN 2, FAIL
ELECT, RECT 1, RECT 2, and battery charger CAUTION lights illuminate. Generator power is lost.
Battery emergency bus system remains active for 12 minutes.
22607 Loss of ac bus 1.
Noncorrectable
22608
Loss of ac bus 2.
Noncorrectable
Instructor: #1 AC CONTACTOR appears on CRT.
Trainee: Loss of power available to subfunction tied to ac bus 1.
RECT 1 light illuminates.
Instructor: #2 AC CONTACTOR appears on CRT.
Trainee: Loss of power available to subfunction tied to ac bus 2.
RECT 2 caution light illuminates.
TM 55-6930-214-10
7-216 Change 1
Required malfunction
DC
CONTACTOR
PLT FLT
INST LT
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22609
Loss of power to dc busses Noncorrectable
1, 2, and 3.
Instructor: DC CONTACTOR appears on CRT.
22610 Loss of lighting Noncorrectable
Trainee: CHARGER CAUTION and FAIL ELECT lights illuminate.
Loss of power available to subfunctions tied to dc essential busses
1, 2, or 3.
Battery emergency bus powered systems remain active for 12 minutes.
Instructor:
PLT FLT INST LT appears on CRT.
Trainee: Loss of lighting to the following systems: video display, clock, stabilator placard, radio placard, turnand-slip indicator, barometric altimeter, vertical speed indicator, and accelerometer.
TM 55-6930-214-10
Change 1
7-217
Required malfunction
CPG FLT
INST LT
#1 TRU
Ref number
Table 7-16.
Malfunction Details continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22611 Loss of lighting.
Noncorrectable Instructor: CPG FLT INST LT appears on CRT.
22612 Loss of output from #1
TRANS/RECT with failure of either TRANS/RECT.
Noncorrectable
Trainee: Loss of lighting to the following systems: attitude indicator, CPG clock, vertical speed indicator, radio magnetic indicator, barometric altimeter, caution/warning panel.
Instructor:
#1 TRU appears on CRT.
Trainee:
RECT 1 and MASTER
CAUTION lights illuminate.
If both #1 and #2 TRU’s are failed, RECT 1, RECT 2,
CHARGER CAUTION, ELEC SYS
FAIL, and MASTER CAUTION lights illuminate.
All dc essential busses are lost.
Battery emergency bus system remains active for 12 minutes.
TM 55-6930-214-10
7-218 Change 1
Required malfunction
#2 TRU
BOTH TRU’S
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
22613
Loss of output from #2
TRANS/RECT with failure of either TRANS/RECT.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: #2 TRU appears on CRT.
Trainee: MASTER CAUTION and
RECT 2 caution lights illuminate. If both #1 and #2
TRU’s are failed, RECT 1,
RECT 2, CHARGER CAUTION,
ELEC SYS FAIL, and MASTER
CAUTION lights illuminate.
All dc essential busses are lost. Battery emergency bus system remains active for 12 minutes.
22614
Loss of all dc essential busses and associated power available.
Noncorrectable Instructor: BOTH TRW’s appears on CRT.
Trainee: RECT 1, RECT 2.
CHARGER CAUTION, and FAIL
ELECT lights illuminate.
All dc essential busses are lost.
Battery emergency bus system remains active for 12 minutes.
TM 55-6930-214-10
Change 1
7-219
Required malfunction
#1 TRU
HOT
#2 TRU
HOT
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22615 Rectifier fan for #1 TRU fails.
Pilot can pull
XFMR RECT #1 CB.
Instructor: #1 TRU HOT appears on CRT.
22616 Rectifier fan for #2 TRU fails.
Pilot can pull
XFER RECT #2 CB.
Trainee:
HOT RECT 1 and
MASTER CAUTION lights illuminate. If pilot pulls XFMR
RECT #1 CB, No. 1 TRU shuts down. Load transfers to #2
TRU. Pilot HOT RECT 1 light then extinguishes and RECT 1 light illuminates.
Instructor: #2 TRU HOT appears on CRT.
Trainee: HOT RECT 2 and
MASTER CAUTION lights illuminate.
If pilot pulls XFMR
RECT #2 CB, No. 2 TRU shuts down.
Load transfers to #1
TRU.
Pilot HOT RECT 2 light then extinguishes and RECT 2 light illuminates.
TM 55-6930-214-10
7-220 Change 1
Required malfunction
PRI HYD
UTIL HYD
Ref number
22620
Aircraft indications and related effects
Loss of primary hydraulic system.
Table 7-16.
Malfunction Details - Continued
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: PRI HYD appears on CRT.
22621 Loss of utility hydraulic systems.
Noncorrectable
Trainee: Servo actuators
For DASE and BUCS are lost.
OIL PRES PRI HYD light illuminates. HYD PRESS gage goes to zero in approximately 1 second.
OIL LOW PRI HYD and
MASTER CAUTION lights illuminate at both pilot and CPG stations.
Instructor: UTIL HYD appears on CRT.
Trainee: Hydraulic pressure lost to area weapon. external stores, tailwheel lock, and ammo carrier drive.
HYD PRES
UTL gage goes to zero in approximately 1 second. Pilot
OIL PRESS UTL HYD, OIL LOW
UTL HYD, and MASTER CAUTION lights illuminate.
CPG UTL
HYD and MASTER CAUTION lights illuminate.
Emergency hydraulic accumulator depletes if pilot or CPG EMER HYD switch is ON.
TM 55-6930-214-10
Change 1 7-221
Required malfunction
BOTH HYD
PRI HYD
OIL LOW
UTIL HYD
OIL LOW
PRIM HYD
FILTER
Ref
Table 7-16. Malfunction Details - Continued
Aircraft indications number and related effects
22622
22623
Loss of both primary and utility systems.
Primary system hydraulic fluid is at minimum operating level.
Corrective action
Set EMERGENCY
HYDRAULIC switch to on when collective or cyclic control is needed and off when not.
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: BOTH HYD appears on CRT.
Trainee: OIL PRES PRI HYD and OIL PRES UTL HYD lights illuminate. Both gages go to zero in 1 second.
Loss of pressure same as with individual system.
Instructor: PRI HYD OIL LOW appears on CRT.
Trainee: OIL LOW PRI HYD and
MASTER CAUTION lights illuminate.
22624
22625
Utility system hydraulic fluid is at minimum operating level.
Primary hydraulic filter is clogged.
Noncorrectable
Noncorrectable
Instructor: UTIL HYD OIL LOW appears on CRT.
Trainee: OIL LOW UTIL HYD and MASTER CAUTION lights illuminate.
Instructor: PRI HYD FILTER appears on CRT.
Trainee: OIL BYP PRI HYD and
MASTER CAUTION lights illuminate.
TM 55-6930-214-10
7-222
Change 1
Required malfunction
UTIL HYD
FILTER
UTIL ACCUM
PRESS
LEFT BRAKE
Ref number and related effects
22626
Table 7-16.
Malfunction Details - Continued
Aircraft indications
Utility hydraulic filter is clogged.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: UTIL HYD FILTER appears on CRT.
Trainee:
OIL BYP UTIL HYD and MASTER CAUTION lights illuminate.
22627 Utility accumulator pressure falls to zero.
Noncorrectable
Instructor: UTIL ACCUM PRESS appears on CRT.
Trainee : UTIL ACC pressure gage falls to zero. APU does not start.
Emergency hydraulic switch and associated functions do not operate.
Rotor brake does not function and, if previously locked, unlocks.
22628 Hydraulic connection to left brake diverted.
Noncorrectable
Instructor: LEFT BRAKE appears on CRT.
Trainee: Left toe brake does not increase friction on left wheel and is ineffective in bringing aircraft to a stop.
TM 55-6930-214-10
Change 1
Required malfunction
RIGHT BRAKE
TAILWHEEL
LOCK
ASE AC
Ref
22629
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Hydraulic connection to right brake diverted.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: RIGHT BRAKE appears on CRT.
22630 Tailwheel locked in direction of aircraft axis.
Noncorrectable
Trainee: Right toe brake does not increase friction on right wheel and is ineffective in bringing aircraft to a stop.
Instructor: TAILWHEEL LOCK appears on CRT.
22701 Pilot center CB panel.
Noncorrectable
Trainee: Tailwheel remains locked regardless of tailwheel lock switch position.
Tailwheel lock advisory light does not illuminate.
Instructor:
ASE AC appears on CRT.
Trainee:
Circuit breaker pops.
Loss of power to indicated system.
All stability and command augmentation capabilities are lost.
7-223
TM 55-6930-214-10
7-224
Change 1
Required malfunction
ASE DC
ASE BUCS
VIB MON
ENG INST
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
22702 Pilot center CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: on CRT.
ASE DC appears
22703 Pilot center CB panel.
Noncorrectable
Trainee:
Circuit breaker pops.
Loss of power to indicated system. All stability and command augmentation capabilities are lost.
Instructor: ASE BUCS appears on CRT.
22704
Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops.
Loss of power to indicated system.
All backup control capabilities are lost.
Instructor: VIB MON appears on CRT.
Trainee: Circuit breaker pops.
Loss of power to indicated system.
22705 Pilot center CB panel.
Noncorrectable
Instructor: ENG INST appears on CRT.
Trainee : Circuit breaker pops. Every other light segments for all engine instruments illuminate.
AUX PWR light above test switch also illuminates.
TM 55-6930-214-10
Change 1
Required malfunction
FIRE DETR
ENG 1
FIRE DETR
ENG 2
FIRE DETR
APU
FIRE EXTGH
PLT
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22706
Pilot center CB panel.
Noncorrectable Instructor: FIRE DETR ENG 1 appears on CRT.
Trainee: Circuit breaker pops. Loss of indication of fires for both crewmembers for engine 1.
22707 Pilot center CB panel.
Noncorrectable
22708 Pilot center CB panel.
Noncorrectable
Instructor: FIRE DETR ENG 2 appears on CRT.
Trainee: Circuit breaker pops. LOSS of indication of fires for both crewmembers for engine 2.
Instructor: FIRE DETR APU appears on CRT.
Trainee: Circuit breaker pops. Loss of indication of
APU fires in pilot station.
22709 Pilot center CB panel.
Noncorrectable
Instructor: FIRE EXTGH PLT appears on CRT.
Trainee: Circuit breaker pops. Loss of capability to extinguish fires for engine
1 or 2 through pilot station.
TM 55-6930-214-10
7-225
7-226
Change 1
Required malfunction
FIRE EXTGH
CPG
FIRE EXTGH
APU
FUEL VLV
ACTR
FUEL FILL
Table 7-16.
Ref Aircraft indications number and related effects
Malfunction Details
-
Continued
Corrective action
Indications presented to instructor/operator and trainee
22710 Pilot center CB panel.
Noncorrectable Instructor: FIRE EXTGH CPG appears on CRT.
22711
22712
22713
Pilot center CB panel.
Pilot center CB panel.
Pilot center CB panel.
Noncorrectable
Noncorrectable
Noncorrectable
Trainee : Circuit breaker pops. Loss of capability to extinguish fires for engine
1 or 2 through CPG station.
Instructor : FIRE EXTGH APU appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. LOSS of capability to extinguish fires for APU.
Instructor : FUEL VLV ACTR appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system.
Instructor: FUEL FILL appears on CRT.
Trainee: Circuit breaker pops.
TM 55-6930-214-10
Change 1
7-227
Required malfunction
FUEL APU
ENG WARN
JETT
LT ANTI
COL
Ref number
22714
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Pilot center CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: FUEL APU appears on CRT.
22715 Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to indicated system.
If running.
APU winds down and stops.
Instructor: ENG WARN appears on CRT.
Trainee: Loss of power to engine out warning system.
22716 Pilot center CB panel.
Noncorrectable
22717 Pilot center CB panel.
Noncorrectable
Instructor: JETT appears on
CRT.
Trainee: If both mission jettison and jettison CB’s are tripped, weapons cannot be jettisoned.
Instructor: LT ANTI COL appears on CRT.
Trainee : Circuit breaker pops.
TM 55-6930-214-10
7-228 Change 1
Required malfunction
LT PRI
LT NAV
LT FORM
LT SRCH
LDG
LT SRCH/LDG
CNTR
Ref number
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22718 Pilot center CB panel.
Noncorrectable Instructor: LT PRI appears on CRT.
22719
Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to indicated system.
Loss of lighting to various systems.
Instructor: LT NAV appears on CRT.
22720 Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops.
Instructor: LT FORM appears on CRT.
Trainee: Circuit breaker pops.
22721 Pilot center CB panel.
Noncorrectable
22722 Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of control and power to searchlight.
Instructor: LT SRCH/LDG CNTR appears on CRT.
Trainee: Circuit breaker pops. Loss of control and power to searchlight.
TM 55-6930-214-10
Change 2
Required malfunction
LT CAUT
LT UTIL
SEC
EMERG
HYD
TRIM
Ref
Table 7-16. Malfunction Details - Continued
A i r c a f t indications number and related effects
22723 Pilot center CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
LT CAUT appears on CRT.
Trainee: Circuit breaker pops. Loss of power to pilot and master caution and warning panels.
22724 Pilot center CB panel.
Noncorrectable Instructor: LT UTIL SEC appears on CRT.
22725
Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to PLT
UTILITY LT.
Instructor: EMERG HYD appears on CRT.
22726 Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to
EMERG HYD switch at both stations. Accumulator cannot be used to control movements.
Instructor: TRIM appears on
CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. HSI HDG flag is in view.
TM 55-6930-214-10
7-229
7-230 Change 2
Required malfunction
RDR ALT
STBY ATTD
THROT
Ref number
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to Instructor/operator and trainee
22727 Pilot center CB panel.
Noncorrectable
Instructor: on CRT.
RDR ALT appears
22728
Pilot center CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of power to RDR
ALT. Altitude pointer freezes behind mask, digital display blanks, and flag is in view.
Instructor: STBY ATTD appears on CRT.
22729
Pilot center CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of power to STBY
ADI. Pitch and roll slowly decrease (pitch down and roll to the right) as the gyro runs down. OFF flag is in view.
Instructor:
THROT appears on CRT.
Trainee : Circuit breaker pops. Loss of power to indicated system. CPG cannot activate pilot throttle release.
Loss of solenoid operation in throttle quadrant.
TM 55-6930-214-10
Change 1
Required malfunction
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
ENG CUT
22730 Pilot center CB panel.
Noncorrectable Instructor: ENG CUT appears on CRT.
ENG LVR
ENG START
22731
22732
Pilot center CB panel.
Pilot center CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to engine chop collar.
Engines do not go to idle when chop is activated.
Instructor: ENG LVR appears on CRT.
Trainee: Engine LVR circuit breaker pops.
Instructor: ENG START appears on CRT.
FUEL XFEED 22733
Pilot center CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to engine ignition system.
Instructor: pears on CRT.
FUEL XFEED ap-
Trainee:
Circuit breaker pops. Loss of power to indicated system.
Fuel crossfeed switch is nonfunctional for crossfeed if full.
TM 55-6930-214-10
7-231
7-232 Change 1
Required malfunction
FUEL TRANS
FUEL BST
TWHL LOCK
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22734
Pilot center CB panel.
Noncorrectable Instructor: FUEL TRANS appears on CRT.
Trainee : Circuit breaker pops. Loss of power to indicated system.
Fuel transfer switch is nonfunctional for transfer of fuel.
22735 Pilot center CB panel.
Noncorrectable Instructor:
FUEL BST appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. Fuel boost switch is nonfunctional.
22736
Pilot center CB panel.
Noncorrectable Instructor: pears on CRT.
TWHL LOCK ap-
Trainee: Circuit breaker pops. Loss of power to indicated system. No power to tailwheel lock panel and switch.
TM 55-6930-214-10
Change 2 7-233
Required malfunction
COMM ADF
COMM IFF
COMM KY 58
COMM UHF AH
Ref
22737
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Pilot center CB panel.
Corrective action
Noncorrectable
Indications presented to Instructor/operator and trainee
Instructor: COMM ADF appears on CRT.
Trainee : Circuit breaker pops. Loss of power to ADF.
ADF audio ceases. Bearing indication on RMI and HSI
PTR #2 freeze at current value.
22738 Pilot center CB panel.
Noncorrectable
22739
22740
Pilot center CB panel.
Pilot center CB panel.
Noncorrectable
Noncorrectable
Instructor:
COMM IFF appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. All IFF functions cease.
Instructor: COMM KY 58 appears on CRT.
Trainee : Circuit breaker pops.
Instructor: COMM UHF AM appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. UHF AM radio inoperative. UHF switch lights extinguish.
TM 55-6930-214-10
7-234 Change 2
Required malfunction
COMM KY 28
COMM VHF FM
COMM ICS
PITOT
HTR
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft Indications number and related effects
22741 Pilot center CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: pears on CRT.
COMM KY 28 ap-
Trainee : Circuit breaker pops. Loss of power to indicated system. KY-28 tones cease, and status lights extinguish.
22742
Pilot center CB panel.
Noncorrectable
Instructor: pears on CRT.
COMM VHF FM ap-
22743
Pilot center CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of power to indicated system. PLT VHF
AM/FM radio inoperative.
Loss of comunications.
PLT
VHF switch lights extinguish.
Instructor:
COMM ICS appears on CRT.
22744 Pilot center CB pane 1.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to PLT
ICS. Pilot loses all comunications (UHF, VHF,
ICS).
Instructor: PITOT HTR appears on CRT.
Trainee : Circuit breaker pops. Loss of power to pitot static system.
TM 55-6930-214-10
Change 1
Required malfunction
RDR WARN
RTR BRK
APU HOLD
CHAFF
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft indications number and related effects
Corrective action
Indications presented to instructor/operator and trainee
22745 Pilot center CB panel.
Noncorrectable Instructor: RDR WARN appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system.
After removal of malfunction, RWR system takes up to 30 seconds to become fully operational.
22746 Pilot center CB panel.
Noncorrectable
22747
22748
Pilot center CB panel.
Pilot center CB panel.
Noncorrectable
Noncorrectable
Instructor: RTR BRK appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to indicated system.
Rotor brake switch is nonfunctional.
Instructor:
APU HOLD ap pears on CRT.
Trainee:
Circuit breaker pops.
Instructor: CHAFF appears on CRT.
Trainee: Circuit breaker pops. Loss of power to chaff system. No CHAFF arm light illumination when chaff system is armed.
TM 55-6930-214-10
7-235
7-236 Change 1
Required malfunction
MISSION
JETT
MISSION
EL DC
MISSION
EL AC
MISSION
PNVS DC
Ref number
22801
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Pilot forward CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MISSION JETT appears on CRT.
Trainee: Circuit breaker pops. Pilot cannot perform selection jettison of weapons. Pilot and CPG can still jettison all weapons if JETT CB is not popped.
22802 Pilot forward CB panel.
Noncorrectable
22803 Pilot forward CB panel.
Noncorrectable
Instructor: MISSION EL DC appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system.
Instructor: MISSION EL AC appears on CRT.
22804 Pilot forward CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to indicated system.
Instructor: MISSION PNVS DC appears on CRT.
Trainee: Circuit breaker pops. Loss of power to PNVS.
No PNVS imagery available when PNVS is selected as video source for IHADSS, IVD displays, or VDU. Symbology remains.
TM 55-6930-214-10
Change 1 7-237
Required malfunction
MISSION
PNVS AC
MISSION
SYM GEN
Ref number
22805
Table 7-16.
Malfunction Details - Continued
Aircraft Indications and related effects
Pilot forward CB panel.
Corrective action
Noncorrectable
Indications presented to Instructor/operator and trainee
Instructor: MISSION PNVS AC appears on CRT.
Trainee: Circuit breaker pops. Loss of power to PNVS.
No PNVS imagery available when PNVS is selected as video source for IHADSS, IVD displays, or VDU. Symbology remains.
22806
Pilot forward CB panel.
Noncorrectable Instructor: MISSION SYM GEN appears on CRT.
Trainee: Circuit breaker pops. Loss of power to symbol generator.
All video and symbology coming from or going to symbol generator is lost. Crew must use auxiliary video inputs to ORT and
IHADSS without symbology.
TM 55-6930-214-10
7-238
Change 2
Required malfunction
NAV HARS
AC
NAV HARS
DC
Ref number
22807
Table 7-16.
Malfunction Details - Continued
Aircraft Indications and related effects
Pilot forward CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: NAV HARS AC appears on CRT.
Trainee : Circuit breaker pops. Loss of power to HARS.
CPG ADI, RMI, and HSI compass rings, HSI PTR #2, and
RMI PTR freeze at current conditions with ADI off flag, HSI HDG flag, and RMI off flag, in view. Doppler
HAL light illuminates.
22808 Pilot forward CB panel.
Cycle doppler OFF
Instructor: NAV HARS DC then back ON, HARS appears on CRT.
inflight alignment procedure continued.
Trainee : Circuit breaker pops. Loss of power to HARS.
HARS MUX BUS outputs lost.
CPG ADI pitches 45
0
O
O & rolls with off flag in view.
RMI and PLT HSI attitude and heading indications freeze.
With HSI HDG flag & RMI off flag in view, doppler HALF light illuminates.
TM 55-6930-214-10
Change 1
Required malfunction
NAV DPLR
RKT ELEX
ARM CONTR
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22809 Pilot forward CB panel.
Noncorrectable Instructor: NAV DPLR appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. All displays and lamps on DPLR panel extinguish. HSI course deviation bar centers.
NAV flag and range shutter are in view. HSI PRT #l parks at 90 O index mark.
22810
22811
Pilot forward CB panel.
Pilot forward CB panel
Noncorrectable
Noncorrectable
Instructor: RKT ELEX appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to into select, arm, or fire rockets.
Instructor: ARM CONTR appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. Crew unable to arm or fire weapon.
TM 55-6930-214-10
7-239
7-240 Change 1
Required malfunction
PEN AIDS
CONTR
RDR HAN
DC
IHADSS
Ref number
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22812 Pilot forward CB panel.
Noncorrectable Instructor: PEN AIDS CONTR appears on CRT.
22813
22814
Pilot forward CB panel.
Pilot forward CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to indicated system. IR jammer inoperable with no visible indication.
Radar jammer selftest lamps do not illuminate during self-test.
Instructor: RDR JAM DC appears on CRT.
Trainee : Circuit breaker pops. Loss of power to indicated system. Radar jammer inoperable. RDR JAM caution light illuminates if jammer is in STBY or OPR.
Instructor: IHADSS appears on CRT.
Trainee: Circuit breaker pops. Loss of power to
IHADSS. No IHADSS LOS information or imagery available at either cockpit.
TM 55-6930-214-10
Change 1
Required malfunction
HSI
VDU
FC AC
FC DC
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22815 Pilot forward CB panel.
Noncorrectable Instructor: HSI appears on
CRT.
Trainee: Circuit breaker pops. Loss of power to HSI.
All HSI flags and shutter in view. PTR’s and compass card freeze at current indications.
22816
Pilot forward CB panel.
Noncorrectable
22817
Pilot forward CB panel.
Noncorrectable
Instructor: VDU appears on
CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system.
Instructor : FC AC appears on CRT.
Trainee: Circuit breaker pops. Loss of ac power to fire control panels. Crew cannot select, arm, or fire weapons.
22818
Pilot forward CB panel.
Noncorrectable Instructor: FC DC appears on CRT.
Trainee : Circuit breaker pops. Loss of dc power to fire control panels. Crew cannot select, arm, or fire weapons.
TM 55-6930-214-10
7-241
7-242 Change 1
Required malfunction
IR JAM
PWR
IR JAM
XMTR
RDR JAM
AC
Ref
Table 7-16.
Malfunction Details Continued number and related effects
22819
Aircraft indications
Pilot forward CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
IR JAM PWR appears on CRT.
22820
22821
Pilot forward CB panel.
Pilot forward CB panel.
Noncorrectable
Noncorrectable
Trainee : Circuit breaker pops. Loss of power to indicated system. IR JAM caution light illuminates during jammer cooldown, if jammer was on (up to 60 sec.); then extinguishes.
Instructor: IR JAM CMTR appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to indicated system. IR JAM caution light illuminates if IR jammer is on.
Instructor:
RDR JAM AC appears on CRT.
Trainee:
Circuit breaker pops. Loss of ac power to indicated system. IR JAM caution light illuminates if
IR jammer is on.
TM 55-6930-214-10
Change 1
Required malfunction
AIR DATA
AC
AIR DATA
DC
ECS FAB
FANS
ECS CAB
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22822
Pilot forward CB panel.
Noncorrectable Instructor:
AIR DATA AC appears on CRT.
22823
Pilot forward CB panel.
Noncorrectable
Trainee:
Circuit breaker pops. Loss of ac power to indicated system.
Air data processor is inoperative.
Instructor: AIR DATA DC appears on CRT.
22901
22902
Pilot aft CB panel.
Pilot aft CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of ac power to indicated system. Air data processor is inoperative.
Instructor: ECS FAB FANS appears on CRT.
Trainee: Circuit breaker pops. Sound of ECS FAB fans stop.
Instructor:
ECS CAB appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. Loss of
ECS standby fans.
7-243
TM 55-6930-214-10
7-244
Change 1
Required malfunction
ECS AFT
FAN
STAB AUTO
AC
STAB AUTO
DC
STAB MAN
DC
Ref number
22903
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Pilot aft CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
ECS AFT FAN appears on CRT.
22904
22905
22906
Pilot aft CB panel.
Pilot aft CB panel
Pilot aft CB panel.
Noncorrectable
Noncorrectable
Noncorrectable
Trainee : Circuit breaker pops. Sound of aft avionics fan stops.
Instructor:
STAB AUTO AC appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to indicated system. Automatic stabilator positioning capabilities are lost.
Instructor: STAB AUTO DC appears on CRT.
Trainee : Circuit breaker pops. Loss of power to indicated system. Automatic stabilator positioning capabilities are lost.
Instructor :
STAB HAN DC appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system.
Stabilator positioning capabilities are lost.
TM 55-6930-214-10
Change 1
Required malfunction
STAB MAN
AC
WSHLD
WPR
ICE DET
BLADE DEICE
CONT
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22907 Pilot aft CB panel.
Noncorrectable Instructor: STAB MAN AC appears on CRT.
Trainee : Circuit breaker pops. Loss of power to indicated system. Stabilator positioning capabilities are lost.
22908 Pilot aft CB panel.
Noncorrectable
22909 Pilot aft CB panel.
Noncorrectable
Instructor: WSHLD WPR appears on CRT.
Trainee: Circuit breaker pops.
Instructor: ICE DET appears on CRT.
22910 Pilot aft CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to indicated system. Automatic rotor blade deice function inoperable.
Instructor: BLADE DEICE
CONT appears on CRT.
Trainee: Circuit breaker pops. Loss of power to indicated system. Blade deicing capability is lost.
TM 55-6930-214-10
7-245
7-246
Change 1
Required malfunction
BLADE DEICE
CNPY
ANTIICE CNT
NOSE GRBX
HT
ENG
ANTI ICE
CANOPY
ANTI ICE
Ref number
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
22911
Pilot aft CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
BLADE DEICE appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to indicated system.
22912 Pilot aft CB panel.
Noncorrectable
Instructor: CNPY ANTI ICE
CNT appears on CRT.
22913
22914
22915
Pilot aft CB panel.
Pilot aft CB panel
Pilot aft CB panel
Noncorrectable
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops.
Instructor: NOSE GRBX HT appears on CRT.
Trainee:
Circuit breaker pops. Loss of engine inlet device capability.
Instructor: ENG ANTIICE appears on CRT.
Trainee:
Circuit breaker pops. Engines go into deicing.
Instructor:
CANOPY ANTI ICE appears on CRT.
Trainee:
Circuit breaker pops.
TM 55-6930-214-10
Change 1
7-247
Required malfunction
PWR XFMR
RECT 1
POWER
ENG 1
POWER
ENG 2
PWR XFER
RECT 2
PWR BATT
CHGR AC
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
22916 Pilot aft CB panel.
Noncorrectable Instructor: PWR XFMR RECT 1 appears on CRT.
Trainee: Circuit breaker pops. Loss of transformer rectifier 1.
22917 Pilot aft CB panel.
Noncorrectable
22918
Pilot aft CB panel.
Noncorrectable
Instructor:
POWER ENG 1 appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to engine 1 ECU.
Instructor:
POWER ENG 2 appears on CRT.
22919 Pilot aft CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of power to engine 2 ECU.
Instructor: PWR XFER RECT 2 appears on CRT.
22920 Pilot aft CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of transformer rectifier 2.
Instructor: PWR BATT CHGR
AC appears on CRT.
Trainee: Circuit breaker pops. HOT BATT light illuminutes.
TM 55-6930-214-10
7-248
Change 1
Required malfunction
PWR BATT
CHGR DC
PRI LT
CAUT
UTIL
SEC LT
Ref number
22921
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Pilot aft CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: PWR BATT CHGR
DC appears on CRT.
23001 CPG main CB panel.
Noncorrectable
Trainee: Circuit breaker pops. Battery power available to dc emergency bus for 12 minutes before battery power is lost.
Instructor: PRI LT appears on CRT.
23002
23003
CPG main CB panel.
CPG main CB pane 1.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of panel lighting.
Instructor: CAUT appears on
CRT.
Trainee: Circuit breaker pops. Loss of power to CPG
CW/A and MASTER CAUTION panel.
Instructor: UTIL SEC LT appears on CRT.
Trainee:
Circuit breaker pops. Loss of power to CPG utility light.
TM 55-6930-214-10
Change 2 7-249
Required
ENG
INST
Ref
23004
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
CPG main CB pane 1.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
ENG INST appears on CRT.
VHF AM
FM
ICS
MSL ARM
23005
23006
23007
CFG main CB panel.
CPG main CB panel.
CPG main CB panel.
Noncorrectable
Noncorrectable
Noncorrectable
Trainee : Circuit breaker pops. Every other light segment for all engine instruments illuminates in both crew stations.
AUX PWR light above test switch on pilot instrument test panel illuminates.
Instructor: VHF AM FM appears on CRT.
Trainee : Circuit breaker pops. Loss of power to CPG
VHF radio.
Loss of VHF
AM/FM communications. CPG
VHF switch lights extinguish.
Instructor:
ICS appears on
CRT.
Trainee : Circuit breaker pops. Loss of power to CPG
ICS; all CPG COMM lost.
Instructor : MSL ARM appears on CRT.
Trainee :
Circuit breaker pops. Loss of power to indicated system. Crew unable to arm or fire missiles.
TM 55-6930-214-10
7-250 Change 1
Required malfunction
MSL L
OUTBD DC
MSL R
OUTBD AC
MSL L
INBD DC
Ref
Table 7-16. Malfunction Details - Continued
Aircraft indications number and related effects
23008 CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MSL L OUTB DC appears on CRT.
23009
CPG main CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of dc power to indicated system. Crew unable to arm or fire lefthand outboard missiles.
Instructor: MSL R OUTB AC appears on CRT.
23010
CPG main CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of ac power to indicated system. Crew unable to arm or fire righthand outboard missiles.
Instructor: MSL L INB DC appears on CRT.
Trainee :
Circuit breaker pops. Loss of dc power to indicated system. Crew unable to arm or fire lefthand inboard missiles.
TM 55-6930-214-10
Change 1
7-251
Required malfunction
MSL R
INBD AC
MSL DC
ELEC
MSL R
OUTBD DC
Ref number
23011
Table 7-16.
Malfunction Details Continued
Aircraft indications and related effects
CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MSL R INB AC appears on CRT.
23012 CPG main CB panel Noncorrectable
Trainee: Circuit breaker pops. Loss of ac power to indicated system. Crew unable to arm or fire righthand inboard missiles.
Instructor: MSL DC ELEC appears on CRT.
Trainee : Circuit breaker pops. Loss of dc power to missiles electronics.
Unable to select, arm. or launch missiles.
23013 CPG main CB panel.
Noncorrectable
Instructor: MSL R OUTBD DC appears on CRT.
Trainee: Circuit breaker pops. Loss of dc power to right outboard missile.
Crew unable to arm or fire righthand outboard missiles.
TM 55-6930-214-10
7-252 Change 1
Required malfunction
MSL L
INBD AC
MSL R
INBD DC
MSL L
OUTBD AC
FC FCC
AC
Ref
Table 7-16. Malfunction Details - Continued
Aircraft indications number and related effects
23014 CPG main CB panel.
23015
23016
CPG main CB panel.
CPG main CB panel.
Corrective action
Noncorrectable
Noncorrectable
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MSL L INBD AC appears on CRT.
Trainee: Circuit breaker pops. Loss of ac power to left inboard launcher. Unable to fire left-hand inboard missiles.
Instructor : MSL R INBD DC appears on CRT.
Trainee: Circuit breaker pops. Loss of dc power to right inboard launcher.
Unable to fire right-hand inboard missiles.
Instructor: MSL L OUTBD AC appears on CRT.
23017
CPG main CB panel.
Noncorrectable
Trainee : Circuit breaker pops. Loss of ac power to left outboard launcher.
Unable to fire left-hand outboard missiles.
Instructor: FC FCC AC appears on CRT.
Trainee: Circuit breaker pops. Loss of ac power to
FCC. No FCC functions available.
TM 55-6930-214-10
Change 1
Required malfunction
FC FCC
DC
FC RCDR
ATTD IND
Ref number
23018
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
FC FCC DC appears cm CRT.
Trainee:
Circuit breaker pops. Loss of dc power to
FCC. FCC switches to seconddary. If MIX switch is in primary position, PRI MUX caution light illuminates.
23019 CPG main CB panel.
Noncorrectable
23020 CPG main CB panel.
Noncorrectable
Instructor: FC RCDR appears on CRT.
Trainee: Circuit breaker pops. Loss of power to recorder panel.
Instructor: ATTD appears on
CRT.
Trainee: Circuit breaker pops. Loss of power to CPG.
ADI, and RMI systems.
All indications on both instruments freeze at current conditions, with flags in view.
TM 55-6930-214-10
7-253
7-254 Change 1
Required malfunction
AWS AMMO
AWS MTR
AWS AC
AWS DC
Ref number and related effects
23021
Table 7-16.
Malfunction Details - Continued
Aircraft indications
CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
AWS AMMO appears on CRT.
Trainee: circuit breaker pops. Loss of Power to gun ammo electronics.
Unable to fire gun.
23022 CPG main CB Panel.
Noncorrectable
Instructor: on CRT.
AWS MTR appears
23023
23024
CPG main CB panel.
CPG main CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of Power to AWS
MTR. Unable to fire or aim gun.
Instructor: AWS AC appears on CRT.
Trainee: Circuit breaker pops. Loss of ac power to gun. Unable to use gun.
Instructor: AWS DC appears on CRT.
Trainee: Circuit breaker pops. LOSS of dc power to gun.
Unable to use gun.
TM 55-6930-214-10
Change 1
7-255
Required malfunction
MUX L
PYL OUTBD
MUX L
PYL INBD
MUX R
PYL OUTBD
Ref number
23025
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MUX L PYL OUTBD appears on CRT.
Trainee: Circuit breaker pops. Loss of MUX communication with left outboard pylon. Cannot fire from left outboard pylon.
23026
CPG main CB panel.
Noncorrectable
23027
CPG main CB panel.
Noncorrectable
Instructor: MUX L PYL INBD appears on CRT.
Trainee: Circuit breaker pops. Loss of MUX communication with left inboard pylon.
Cannot fire from left inboard pylon.
Instructor:
MUX R PYL OUTBD appears on CRT.
Trainee: Circuit breaker pops. Loss of MUX communication with right outboard pylon.
Cannot fire from right outboard pylon.
TM 55-6930-214-10
7-256 Change 1
Required malfunction
MUX R
PYL INBD
MUX
FAB L
MUX
FAB R
MUX CPG
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
23028 CPG main CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MUX R PYL INBD appears on CRT.
Trainee:
Circuit breaker pops. Loss of MUX communication with right inboard pylon. Cannot fire from right inboard pylon.
23029 CPG main CB panel.
Noncorrectable
Instructor: MUX FAB L appears on CRT.
23030
23031
CPG main CB panel.
CPG main CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of MUX communications left.
Instructor: MUX FAB R appears on CRT.
Trainee: Circuit breaker pops. Loss of MUX communications right.
Instructor: MUX CPG appears on CRT.
Trainee: Circuit breaker pops. Loss of MUX communications in CPG station.
TM 55-6930-214-10
7-257
Required malfunction
IHADSS
TADS DC
TADS AC
Ref number and related effects
23032
Table 7-16.
Malfunction Details -- Continued
Aircraft indications
CPG auxiliary CB panel.
Corrective act ion
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
IHADSS appears on CRT.
23033
23034
CPG auxiliary CB panel.
CPG auxiliary CB panel.
Noncorrectable
Noncorrectable
Trainee: Circuit breaker pops. Loss of power to
IHADSS. No IHADSS LOS information for FCC or imagery for pilot or CPG.
Instructor: TADS DC appears on CRT.
Trainee : Circuit breaker pops. Loss of dc power to
TADS. DVO still available.
No TADS or LRF/D/T capabilities.
Instructor: TADS AC appears on CRT.
Trainee: Circuit breaker pops. Loss of ac power to
TADS. DVO still available.
No TADS or LRP/D/T capabilities.
7-258
Required malfunction
LASER
PITOT TUBE
HOIST
TURN
INDICATOR
MAGNETIC
COMPASS
Ref number and related effects
23035
Table 7-16. Malfunction Details - Continued
Aircraft indications
CPG auxiliary CB panel.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: LASER appears on CRT.
23101
Moisture in pitot system.
Set PITOT HEAT switch on. After a 2-minute delay, system operates normally.
Trainee: Circuit breaker pops. Loss of power to laser.
No laser range finding, designation, or tracking capabilities.
Instructor: PITOT TUBE MOIST appears on CRT.
23102
23103
Turn indicator always centered.
Magnetic compass indicator fails.
Noncorrectable
Noncorrectable
Trainee : Both pilot and CPG altimeters, IVSI’s. and airspeed indicators show static erroneous readings of 10 (±
2) knots prior to engine start.
Instructor: TURN INDICATOR appears on CRT.
Trainee : Turn indicator always centered.
Instructor: MAGNETIC COMPASS appears on CRT.
Trainee: Indicator freezes at current heading.
TM 55-6930-214-10
7-259
7-259
Required malfunction
RADAR
ALTIMETER
PILOT ATT
IND
STABILATOR
IND
Ref number
Table 7-16. Malfunction Details - continued
Aircraft Indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
23104
Radar altimeter cannot lock Noncorrectable onto a valid signal.
Instructor: RADAR ALTIMETER appears on CRT.
Trainee : Radar altimeter needle is driven behind the mask, digital display is blanked, and off flag is in view.
23105 Pilot standby attitude
Indicator falls.
Noncorrectable
23106 Stabilator indicator frozen.
Noncorrectable
Instructor: PILOT ATT IND appears on CRT.
Trainee: AD1 fails to respond to changes In aircraft movement.
OFF flag in view.
Pitch and roll indications freeze at current indications.
Pulling cage knob forces indicator to read 0 degrees pitch & 0 degrees r o l l .
Instructor:
STABILATOR IND appears on CRT.
Trainee : Both stabilator indicators freeze at current setting at time of malfunction insertion.
Stabilator operates normally in automatic and manual modes.
7-260
Required malfunction
ADSS
VHF
XCVR-PLT
VHF
XCVR-CPG
UHF XCVR
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Corrective act ion
Indications presented to instructor/operator and trainee
23107
Air data sensor subsystem stops providing data to
FCC.
Noncorrectable
Instructor: ADSS FAIL appears on CRT.
Trainee: outputs to FCC stop.
MASTER CAUTION light illuminates.
ADS light illuminates at both stations.
23120
Pilot VHF FM/AM transceiver unable to transmit or receive signals.
Noncorrectable Instructor: VHF XCVR-PLT appears on CRT.
Trainee: No PLT VHF reception. transmission. or sidetone.
23121
CPG VHF transceiver unable to transmit or receive signals.
Noncorrectable Instructor: VHF XCVR-CPG appears on CRT.
Trainee : No CPG VHF reception. transmission, or sidetone.
23122
UHF transceiver unable to transmit or receive signals.
Noncorrectable Instructor: on CRT.
UHF XCVR appears
Trainee : No UHF reception.
transmission, or sidetone.
TM 55-6930-214-10
7-261
Required malfunction
PLT
INTERCOM
CPG
INTERCOM
IFF
ADF RCVR
Ref
23123
Table 7-16. Malfunction Details - Continued
Aircraft Indications number and related effects
Corrective action
C-11746 COMM panel In pilot Noncorrectable cockpit is inoperative.
Indications presented to Instructor/operator and trainee
Instructor:
PLT INTERCOM appears on CRT.
Trainee:
Pilot cannot transmit or receive on ICS or any radio.
23124
23125
C-11746 COMM panel In CPG cockpit is Inoperative.
IFF KIT computer fails.
Noncorrectable
Noncorrectable
Instructor:
CPG INTERCOM appears on CRT.
Trainee: CPG cannot transmit or receive on ICS or any other radio.
Instructor: IFF FAIL appears on CRT.
23140 No ADF signal reception available.
Noncorrectable
Trainee : KIT status light on IFF panel illuminates.
IFF caution lights illuminate In both cockpits.
IFF
NO-GO light illuminates when
MODE 4 TEST is selected.
Instructor: ADF RCVR appears on CRT.
Trainee : All ADF audio is lost.
HSI PTR #2 and RMI
PTR freeze at current condit Ions.
TM 55-6930-214-10
7-262
Required malfunction
ADF BEARING
ERROR
DOPPLER
RTA
Ref number
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects f a c i l i t i e s .
Corrective action
23141 ADF radio cannot lock onto Noncorrectable signals from radio
Indications presented to instructor/operator and trainee instructor: ADF BEARING
ERROR appears on CRT.
23142 Receiver-transmitter antenna falls.
Doppler beam Information is lost.
Noncorrectable: backup mode is available.
Trainee : HSI and RMI bearing pointers oscillate ±20° from station bearing at a rate of 6 deg/sec.
Instructor: DOPPLER RTA appears on CRT.
Trainee: HSI range and NAV flags drop Into view. Bearing pointer 1 parks at 90° and course deviation bar centers.
CDU MEM light illuminates. 1553 bus outputs disabled. After system test:
MAL light illuminates
DNS display reads:
147 130 000
315 then, display reads:
MN R-00000
TM 55-6930-214-10
Change 2
7-262.1/(7-262.2 blank)
Required malfunction
DOPPLER
SDC PWR
HARS
HEADING
Ref number
T a b l e 7 - 1 6 . M a l f u n c t i o n D e t a i l s - c o n t i n u e d
A i r c r a f t i n d i c a t i o n s a n d r e l a t e d e f f e c t s
23143 T h e p o w e r s u p p l y i n t h e s i g n a l d a t a c o n v e r t e r f a i l s .
A l l s i g n a l s r o u t e d to DNS through the SDC a r e l o s t .
C o r r e c t i v e act ion
Noncorrectable; turn DNS off.
I n d i c a t i o n s p r e s e n t e d t o I n s t r u c t o r / o p e r a t o r a n d t r a i n e e
Instructor: DOPPLER SDC PWR appears on CRT.
T r a i n e e : H S I r a n g e a n d N A V f l a g s d r o p i n t o v i e w . B e a r i n g p o i n t e r 1 p a r k s a t 9 0
O a n d H S I c o u r s e d e v i a t i o n b a r centers. CDU MEM and MAL l i g h t s i l l u m i n a t e . D N S o u t p u t s a n d d i s p l a y s a r e e r r o n e o u s . 1 5 5 3 b u s o u t p u t s a r e i n e r r o r . A f t e r r u n n i n g s y s t e m t e s t :
T h e d i s p l a y r e a d s :
000 000 000 000 t h e n d i s p l a y r e a d s :
NG S890000
23144 Valid HARS heading data i s l o s t .
N o n c o r r e c t a b l e
Instructor: HARS HEADING appears on CRT.
T r a i n e e : C o m p a s s r i n g s o n
H S I a n d R M I f r e e z e a t t h e i r c u r r e n t i n d i c a t i o n s , c o m p a s s r i n g f l a g s I n v i e w .
TM 55-6930-214-10
7263
Required malfunction
HARS
HSI COMPASS
CARD
HSI COURSE
Ref
Table 7-16.
Malfunction Details - Continued
Aircraft Indications number and related effects
23146
23147
HSI compass card freezes at Noncorrectable current condition.
HSI course deviation bar fails.
Corrective action
23145
HARS built-in-test detects When malfunction failure in gyro package.
is deleted. the
HARS is fully operational - no delay.
Noncorrectable
Indications presented to Instructor/operator and trainee
Instructor: on CRT.
HARS appears
Trainee :
PLT HSI and CPG
RMI HDG, and AD1 flags fall
Into view.
HSI and RMI compass rings freeze. CPG AD1 and PLT VDU pitch and roll freeze.
DASE switches drop out. ASE caution light illuminates.
HARS mux bus outputs reflect the above conditions.
Instructor: HSI COMPASS CARD appears on CRT.
Trainee : HSI compass card does not move with changes In
A/C heading.
Flag not In view.
Instructor: HSI COURSE BAR appears on CRT.
Trainee : HSI course deviation bar is centered.
NAV warning flag is not in view.
TM 55-6930-214-10
7-264
Required malfunction
ADF
TO HSI
LDNS
TO HSI
RMI PTR
FRZ
AD1 CPG
Ref
23149
Table 7-16.
Malfunction Details - Continued
Aircraft Indications number and related effects
23148 HSI bearing pointer 2 freezes.
Connector on HSI for
LDNS data breaks.
Corrective action
Indications presented to instructor/operator and trainee
Use bearing indiInstructor: ADF TO HSI cation on HSI pointer 1 or RMI appears on CRT.
Trainee : HSI PTR #2 does not reflect ACFT movements relative to a tuned ADF station.
Noncorrectable
Instructor: LDNS TO HSI appears on CRT.
23150
RMI bearing pointer freezes.
Noncorrectable
Trainee : HSI range and NAV flags drop into view. Course bar centers.
PTR #l parks at 90° index mark.
LDNS mux bus interface not affected.
Instructor: RMI PTR FRZ appears on CRT.
Trainee : RMI bearing pointer does not reflect A/C movements relative to a tuned
ADF.
23151
Attitude Indicator in CPG cockpit fails.
Noncorrectable
Instructor: AD1 CPG appears on CRT.
Trainee : Pitch and roll indications on CPG ADI freeze at current conditions. OFF flag in view.
TM 55-6930-214-10
7-265
Required malfunction
TADS
RANGERFINDER
DESIGNATOR
Ref
Table 7-16.
Malfunction Details - continued
Aircraft indications number and related effects
Corrective action
Indications presented to instructor/operator and trainee
23201 TEU failure-processor fault.
Noncorrectable Instructor: TADS appears on CRT.
Trainee : TEU does not respond to FCC.
Turret locks in position. No laser tracker or rangefinder/ designator available. T A D S light illuminates.
TADS
FAIL message appears on AND if TADS is selected sight.
23202
23203
Failure of laser rangefinder.
Failure of laser.
Noncorrectable
Noncorrectable
Instructor:
RANGERFINDER appears on CRT.
Trainee: No laser range available for FCC.
FD/LS flashes in sensor. ID field of TADS display. RFD-D goes blank in LRF/D and LST code status section of AND.
Instructor: DESIGNATOR appears on CRT.
Trainee:
Crew unable to autonomously designate targets for HELLFIRE missiles.
FD/LS flashes in sensor ID field of TADS display.
RFD-D goes blank in
LRF/D and LST code status section of AND.
TM 55-69320-214-10
7-266
Required malfunction
LASER
HOT
DTV
TADS-FLIR
Ref Aircraft indications number and related effects
23204
23205
Table 7-16.
Malfunction Details - Continued
Laser overtemp failure in LRF/D.
Loss of TADS TV imagery.
Corrective action
Noncorrectable
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
LASER HOT appears on CRT.
Trainee: TADS laser transceiver unit (LTU) fails.
LRF-D overtemp message appears in high-action display.
Instructor: DTV appears on
CRT.
23206 L
OSS of TADS-FLIR imagery.
Noncorrectable
Trainee: No imagery when
TADS TV is selected as video source for IDV, IHADSS. or
VDU.
TV FAIL displayed in sight status section of AND.
FD/LS flashes in sensor ID field of TADS displays.
Instructor: TADS-FLIR appears on CRT.
Trainee: No imagery when
TADS FLIR is selected as video source for IDV.
IHADSS. or VDU.
FD/LS flashes in sensor ID field of TADS displays.
FLIR FAIL is displayed in sight status of AND.
TM 55-6930-214-10
7-267
Required Ref
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
Corrective action
Indications presented to instructor/operator and trainee
TADS-FLIR 23207
COOLER
Failure of Cooling to
IR detectors.
Noncorrectable Instructor: TADS-FLIR COOLER appears on CRT.
LASER SPOT
TRKR
23208
Failure of laser tracker.
Noncorrectable
Trainee: TADS FLIR imagery gain decreases. Noise increases. FLIR NOT COOLED is displayed.
Instructor:
LASER SPOT TRKR appears on CRT.
Trainee: CPG unable to lock on and track remotely designated target.
FD/LS flashes in sensor ID field of TADS displays. LST-C goes blank in LRF-D and LST code status sections of AND. LST FAILED is displayed in TRACKER
STATUS section of AND.
IAT NO
LOCK-ON
23209
CRG unable to lock on targets in TADS imagery.
Noncorrectable Instructor: IAT NO LOCK-ON appears on CRT.
Trainee: IAT symbology available but CPG unable to obtain image lock (IAT) on targets in TADS.
TM 55-6930-214-10
7-268
Required malfunction
IMAGE AUTO
TRKR
Ref number
Table 7-16. Malfunction Details - Continued
Aircraft indications and related effects
Corrective action
Indications presented to instructor/operator and trainee
23210 Failure of TADS image auto tracker.
Noncorrectable Instructor: IMAGE AUTO TRKR appears on CRT.
Trainee: Loss of capability to lock on and track objects in TADS FLIR and TV imagery.
FD/LS flashes in sensor ID fields of TADS displays. IAT
FAILED is displayed in TRACK-
ER STATUS section of AND.
LMC 23211
LMC switch failure on
TADS ORT.
Noncorrectable
PNVS 23220 PEU total failure.
Noncorrectable
Instructor: LMC FAIL appears on CRT.
Trainee: LMC mode not selectable.
Manual updates of line-of-sight must be made.
Instructor: PNVS appears on
CRT.
Trainee: PNVS turret locks in posit ion. PNVS video fails.
PNVS caution light illuminates and PNVS NO-GO appears on FD/LS.
TM 55-6930-214-10
7-269
Required Ref
Table 7-16. Malfunction Details - continued
Aircraft indications malfunction number and related effects
Corrective action
Indications presented to instructor/operator and trainee
PNVS
LOCKED
23221 PNVS turret motion locks in current azimuth and elevation.
Noncorrectable
Instructor: PNVS LOCKED appears on CRT.
Trainee : Crew unable to slew PRVS line-of-sight in azimuth or elevation.
PNVS
VIDEO
23222
Loss of PNVS video.
Noncorrectable Instructor : PNVS VIDEO appears on CRT.
PNVS AZ
DRIVE MTR
PNVS
COOLER
23223
23224
PNVS azimuth drive motor failure.
Failure of Cooling to
IR detectors.
Noncorrectable
Noncorrectable
Trainee: No PNVS video when
PNVS is selected as video source for IHADSS. IVD. or
VDU. Flight symbology remains.
Instructor: PNVS AZ DRIVE
MTR appears on CRT.
Trainee: Crew unable to slew PNVS line-of-sight in azimuth. Turret AZ locks in current position.
Instructor: PNVS COOLER appears on CRT.
Trainee: PNVS imagery gain decreases and noise increases over a period of 70 seconds. PNVS NOT COOLED displayed on VDU.
TM 55-6930-214-10
7-270
R e q u i r e d Ref
Table 7-16.
Malfunction Details Continued
Aircraft indications malfunction number and related effects
Corrective action
Indications presented to instructor/operator and trainee
SEU
PLT DAP
23225 Loss of line-of-sight information to pilot and CPG.
23226
Loss of PNVS imagery
(video and symbology).
Malfunction deleted automatical- on CRT.
ly after breaklock occurs.
Noncorrectable
Instructor: SEU FAIL appears
Trainee: No IHADSS LOS information available for FCC.
FD/LS flashes in ID field of
TADS displays. If FD/LS is selected, IHADSS NO-GO is displayed.
IHADSS FAILED is displayed in sight status section of HAD symbology of
IDV displays and VDU. If
IHADSS is selected sight,
IHADFAIL is displayed in weapon status section of high-action displays.
Instructor: PLT DAP appears on CRT.
Trainee: No imagery or synbology when PNVS is selected as video source for pilot
IHADSS.
TM 55-6930-214-10
7-271
R e q u i r e d Ref
CPG DAP 23227
Table 7-16.
Malfunction Details - continued
Aircraft indications malfunction number and related effects
Loss of PNVS imagery.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
CPG DAP appears o n C R T .
Trainee: No imagery or symbology when PNVS is selected as video source for CPG
IHADSS.
SYMBOL
GENERATOR
23240 Total failure of symbol generator.
Noncorrectable
FCC
23260 Failure of fire control computer.
Noncorrectable
Instructor:
SYMBOL GENERATOR appears on CRT.
Trainee:
LOSS of all video and symbology that comes from or goes through symbol generator.
Crew must use auxiliary video inputs to
ORT and IHADSS without symbology.
Instructor: FCC appears on
C
R T
.
Trainee : If MUX switch on
CPG FCP is in PRI when malfunction is selected. FCC stops and PRI MUX light illuminates.
If MUX switch is in SEC, no indication occurs.
TM 55-6930-214-10
7-272
R e q u i r e d Ref
VDU
23280
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
Power fail in VDU.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: VDU appears on CRT.
Trainee : No video available on pilot VDU.
HELLFIRE 23301 RHE hardware failure
SYSTEM
( w a t c h d o g t i m e r ) .
Noncorrectable Instructor: HELLFIRE SYSTEM appears on CRT.
MISSILE
HANGFIRE
23302 Hangfire for next missile fires.
Malfunction deleted automatically after hangfire.
Trainee: RHE reports failure to FCC. MISSILE caution light illuminates.
Missile
NO-Go displayed by FD/LS. N
O
Hellfire capabilities exist.
Instructor: MISSILE HANGFIRE appears on CRT.
Trainee: Next missile fails to fire.
Missile failure light illuminates. FD/LS flashes in sensor ID section of TADS displays. HANGFIRE is displayed in weapons status sections of high-action displays and on AND display.
TM 55-6930-214-10
7-273
Required
Aircraft indications malfunction number and related effects
MISSILE
MISFIRE
Ref
Table 7-16.
Malfunction Details - Continued
Corrective action
Indications presented to instructor/operator and trainee
23303 Next missile fails to fire.
Malfunction de-
Instructor: MISSILE MISFIRE leted automatical appears on CRT.
ly after missile fails to fire.
Trainee: Next missile fails to fire.
Missile failure light illuminates in both cockpits.
FD/LS flashes in sensor ID section of TADS displays.
M S L
UNLATCHED
23304 Unlatched signal to RHE for affected MSL.
Noncorrectable Instructor: MSL UNLATCHED appears on CRT.
Trainee: FCC displays missile unlatched condition.
MU displayed in proper missile position of AND.
Malfunction clears to IS after a missile is unlatched.
MSL
BIT
23305 Next missile fails to uncage and spin up.
Noncorrectable
Instructor: MSL BIT appears on CRT.
Trainee:
RHE reports MSL failed to spin up for display.
Missile NO-GO is displayed by FD/LS.
MF displayed in proper missile position of AND.
TM 55-6930-214-10
7-274
R e q u i r e d Ref
Table 7-16.
Malfunction Details Continued
Aircraft indications malfunction number and related effects
Corrective action
Indications presented to instructor/operator and trainee
L OUTBD
LNCHR
23306 All analog replies from affected launcher are set to zero.
Noncorrectable Instructor: L OUTBD LNCHR appears on CRT.
Trainee: The word FAIL appears vertically in missile inventory and status section of the AND for left outboard launcher.
FD/LS also indicates failure until removed by IS.
L INBD
LNCHR
23307 All analog replies from affected launcher are set to zero.
Noncorrectable
R OUTBD
LNCHR
23308 All analog replies from affected launcher are set to zero.
Noncorrectable
Instructor: L INBD LNCHR appears on CRT.
Trainee: The word FAIL appears vertically in missile inventory and status section of the AND for left inboard launcher. FD/LS also indicates failure until removed by IS.
Instructor: R OUTBD LNCHR appears on CRT.
Trainee: The word FAIL appears vertically in missile inventory and status section of the AND for right outboard launcher.
TM 55-6930-214-10
7-275
Required Ref
Table 7-16. Malfunction Details Continued
Aircraft indications malfunction number and related effects
Corrective action
Indications presented to instructor/operator and trainee
R INBD
LNCHR
23309 All analog replies from affected launcher are set to zero.
Noncorrectable
Instructor: R INBD LNCHR appears on CRT.
Trainee: The word FAIL appears vertically in missile inventory and status section of the AND for right inboard launcher.
GUN TURRET
JAM
GUN NO
FIRE
23310 Gun turret jammed.
Noncorrectable
Noncorrectable
Instructor: GUN TURRET JAM appears on CRT.
Trainee: Crew unable to fire gun. Turret jams at position gun is in when malfunction is inserted.
INSTRUCTOR: GUN NO FIRE appears on CRT.
Trainee: Crew unable to fire gun. GUN FAILURE illuminates on pilot and CPG caution panels. FD/LS flashes in sensor ID field of TADS displays.
GUN FAIL displayed in weapons section of HAD and
AND, on IDV display, and
VDU.
TM 55-6930-214-10
7-276
R e q u i r e d R e f
Table 7-16.
M a l f u n c t i o n D e t a i l s - C o n t i n u e d malfunction number and related effects
ARCS
23312
Aircraft indications Corrective action
Failure in rocket subsystem Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: ARCS appears on
CRT.
Trainee : Crew unable to fire rockets.
Rocket control panel goes blank.
ROCKET light illuminates.
FD/LS flashes in sensor ID field of
TADS displays. RKT FAIL displayed in weapon status section of HAD, IDV displays,
VDU, and AND.
ROCKET
HANGFIRE
23313 Next rocket fired burns
IN tube.
Malfunction deleted automatically after hangfire.
Instructor: ROCKET HANGFIRE appears on CRT.
Trainee: Next rocket fails to launch.
HAMFIRE causes yaw movement to helicopter.
ROCKETS
MISFIRE
23314
Next rocket fails to fire.
Malfunction deleted automatically after rocket fails to fire.
Instructor: to fire.
ROCKET MISFIRE appears on CRT.
Trainee: Next rocket fails
IR
JAMMER
23320 Failure of IR jammer system.
Noncorrectable Instructor: IR JAMMER appears on CRT.
Trainee: IR missile cannot be jammed. IR JAM caution light illuminates.
TM 5-6930-214-10
7-277
R e q u i r e d Ref
RADAR
JAMMER
23321
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
Failure of radar jammer system.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
RADAR JAMMER appears on CRT.
Trainee : Crew unable to cause threats to break radar lock so track mode continues, followed by missile launch unless crew remasks.
If radar jammer is on, RDR
JAM caution light illuminates. If malfunction is removed while radar jammer is on, RDR JAM caution light remains illuminated for approximately 3 minutes while jammer warms up.
CHAFF
DISPENSER
23322 Failure of CHAFF dispenser system.
Noncorrectable
RDR WARN
RCVR
23323 Failure of left forward
RWR antenna.
Noncorrectable
Instructor: CHAFF DISPENSER appears on CRT.
Trainee: Pilot unable to eject chaff.
CHAFF counter indicator does not cycle.
ARM light on CHAFF dispenser does not illuminate.
Instructor: RDR WARN RCVR appears on CRT.
Trainee: Incorrect bearing and strobe length displayed for threats between 225° and
4 5 ° .
TM 55-6930-214-10
7-278
R e q u i r e d Ref
AUTO BUCS
COLL
*
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
Lift-axis flight control linkage is severed.
Lift-axis BUCS is engaqed.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor:
AUTO BUCS COLL appears on CRT.
Trainee: BUCS ON and MASTER
CAUTION lights illuminate.
In integrated mode, control of aircraft is assigned to designated flyer (pilot or
CPG). In independent mode, pilot controls PLT cockpit.
and CPG controls CPG cockpit.
AUTO BUC
CYC-LON
*
Longitudinal-axis flight control linkage is severed.
Longitudinal axis BUCS is engaged.
Noncorrectable Instructor: AUTO BUC CYC LON appears on CRT.
Trainee: BUCS ON and MASTER
CAUTION lights illuminate,
SAS damping not available
(ASK switches engaged), CAS not available, and force trim operational.
In integrated mode, control of aircraft is assigned to designated flyer (pilot or CPG).
In independent mode, pilot controls PLT cockpit, and
CPG controls CPG cockpit.
TM 55-6930-214-10
7-279
Required malfunction
AUTO BUCS
PDLS
AUTO BUCS
CYC- LAT
Ref
number and related effects
*
Table 7-16.
Malfunction Details - Continued
Aircraft indications
Yaw-axis flight control
linkage is severed.
Yaw-axis BUCS is engaged.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: AUTO BUCS PDLS appears on CRT.
Trainee: BUCS ON and MASTER
CAUTION lights illuminate.
SAS damping not available
(ASE switches engaged). CAS
not available, and force
trim operational.
In inte-
grated mode. control of aircraft is assigned to designated flyer (pilot or CPG).
In independent mode. pilot controls PLT cockpit, and
CPG controls CPG cockpit.
*
Lateral-axis flight control Noncorrectable linkage is severed.
is engaged.
BUCS
Instructor: AUTO BUCS CYC
LAT appears on CRT.
Trainee: BUCS ON and MASTER
CAUTION lights illuminate,
SAS damping not available
(ASE switches engaged). CAS
not available, and force
trim operational.
In inte-
grated mode, control of aircraft is assigned to designated flyer (pilot CPG). In
independent mode, pilot con-
trols PLT cockpit, and CPG controls CPG cockpit.
TM 55-6930-214-10
7-280
R e q u i r e d Ref malfunction number and related effects
MNL BUCS
COLL
* jams.
Table 7-16.
Malfunction Details - Continued
Aircraft indications
Lift-axis flight control corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MNL BUCS COLL appears on CRT.
MNL BUCS
CYC LON
*
Longitudinal-axis flight control jams.
Noncorrectable
Trainee: BUCS ON and MASTER
CAUTION lights illuminate.
In integrated mode, designated crewmember must break simulated shear pin.
Control of other crewmember remains jammed.
In independent mode, each crewmember must break simulated shear pin to remove jam and engage
BUCS.
Instructor: MNL BUCS CYC LON appears on CRT.
Trainee: BUCS ON and MASTER
CAUTION lights illuminate.
SAS damping and CAS not available.
In integrated mode, designated crewmember must break simulated shear pin.
Control of other crewmember remains jammed. In independent mode, each crewmember must break simulated shear pin to remove jam and engage BUCS.
If CPG engages
BUCS. force trim is lost.
TM 55-6930-214-10
7-281
R e q u i r e d Ref malfunction number
MNL BUCS
PDLS
*
Table 7-16.
Malfunction Details - Continued
Aircraft indications and related effects
Yaw-axis flight control jams.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MNL BUCS PDLS appears on CRT.
Trainee:
BUCS ON and MASTER
CAUTION lights illuminate,
SAS damping not available
(ASE switches engaged,. and
CAS not available.
In integrated mode, designated crewmember must break simulated shear pin. Control of other crewmember remains jammed. In independent mode, each crewmember must break simulated shear pin to remove jam and engage BUCS.
If CPG engages BUCS, force trim is lost.
TM 55-6930-214-10
7-282
R e q u i r e d Ref
MNL BUCS
CYC LAT l
Table 7-16.
Malfunction Details - Continued
Aircraft indications malfunction number and related effects
Lateral-axis flight control jams.
Corrective action
Noncorrectable
Indications presented to instructor/operator and trainee
Instructor: MNL BUCS CYC LAT appears on CRT.
Trainee : BUCS ON and MASTER
CAUTION lights illuminate,
SAS damping not available
(ASE switches engaged), and
CAS not available.
In integrated mode, designated crewmember must break simulated shear pin.
Control of other crewmember remains jammed.
In independent mode, each crewmember must break simulated shear pin to remove jam and engage BUCS, If CPG engages BUCS, force trim is lost.
TM 55-6930-214-10
TM 55-6930-214-10
CHAPTER 8
EMERGENCY PROCEDURES AND SAFETY
Section I.
EMERGENCY PROCEDURES
CAUTION
Due to abnormal shutdown possible hardware damage may occur.
NOTE
This section contains procedures to be used during an actual simulator malfunction or failure.
Procedures for use during
simulated malfunctions are contained in Chapter 7, table 7-16.
8-l.
EMERGENCY SHUTDOWN.
Emergency stop switches are provided throughout the camplex for emergency shutdown of the complete CMS system, motion system only, or visual system only.
Emergency shutdown can be accomplished at the following locations : a.
Complete Simulator Complex.
The following are major locations of switches that shut down the complete CMS complex:
Instructor/operator stations
Trainee control panels
Digital linkage cabinet
SCE cabinet
Motion cabinets
Power cabinet
Motion pumps b.
Motion System Only. MOTION OFF switches at the ‘following locations shut down only the associated (pilot or copilot/gunner) motion system:
IOS simulator control panels
Trainee control panels
Motion cabinets
C.
Control Loading System.
The control loading system may be deactivated manually by depressing the MANUAL ABORT switchlight on the remote power controller panel.
8-2.
SYSTEM FAILURES.
Should a failure be detected, use intercom to contact the computer room and reguest maintenance.
If the system failure cannot be cleared within 15 minutes, exit simulator.
System failures can occur for several reasons:
Electronic failure
Hydraulic failure
Mechanical failure
Operator-induced failure
Change 2 8-l
TM 55-6930-214-10
WARNING
Care should be exercised when exiting the simulator during power failure.
The boarding ramp may fail to deploy.
8-3.
FACILITY POWER FAILURE. Loss of facility power results in shutdown of the entire CMS complex.
the following:
The total simulator becomes deactivated with the exception of
Emergency lighting
Fire detection system
Ramp
Telephone intercom
8-2 Change 2
TM 55-6930-214-10
Section II. SAFETY
8-4. OPERATIONAL SAFETY. The CMS is designed for safe operation during all phases of training.
WARNING
Prior to the activation of motion, all occupants of the simulated cockpit and IOS (limited to three persons per flight compartment) are required to fasten seat belts.
a. Each motion system employs numerous devices to ensure safe operation for personnel. Among these are controlled deceleration devices, cushion stops, limitsensing, leveling and locking devices, thermal cutout for hydraulic fluid, emergency stop switches, and red warning lights in personnel areas.
b. The entrance/emergency exit doors are equipped with safety interlocks that prevent motion activation until the door is secure.
c. The motion equipment is located within a gated area with gate interlocks that prevent motion activation unless the gates are closed.
d. The boarding ramps are equipped with sensing switches to prevent boarding ramp motion with additional weight (person) on the ramp. The motion system is not activated until the boarding ramp is completely raised.
e. Normal activation and deactivation of each motion system is accomplished at the respective IOS. Motion for each flight compartment is controlled separately and is not mode-dependent.
f . Fail-safe circuitry prevents erratic movement of the motion system when equipment malfunctions.
g.
Temperature sensors are located in each equipment cabinet. If the temperature reaches 100°F or if adequate airflow is not maintained, visual and aural warnings activate in the computer room. At 110°F, the entire complex automatically shuts down.
h. Actuation of any emergency STOP switch results in the immediate shutdown of the entire complex, motion system. and/or visual system. Once an EMERGENCY STOP switch has been actuated and the power shuts down. the main and linkage circuit breakers must be manually reset before power can be reapplied.
i . In the emergency stop condition, a quick-settle control valve returns the motion platform to the settled position at the highest practicable speed.
The boarding ramp lowers under power of a reserve stored energy source. Personnel can safely egress to the access balcony in approximately 24 to 31 seconds, depending on the position of the motion platform at the time electrical power was cut off.
j .
Emergency escape ropes are provided in case power failure or hydraulic failure prevent a boarding ramp from deployment.
Change 2 8-3
TM 55-6930-214-10
WARNING
Do not discharge a CF
3 cockpit.
BR fire extinguisher In the confined k.
Five fire extinguishers are located In central areas of the CMS complex. one
In the computer room, two in the simulator room, and one In each pump room. Two other fire extinguishers are located in the flight simulator compartments, forming a part of the normal cockpit equipment.
The fire extinguishers are monobromotrifuloromethane (CF
3
BR).
These fire extinguishers are caustic In nature and can seriously damage sensitive electronic equipment not already damaged by fire.
l .
The visual system safety system Includes an emergency egress switch in the cockpit.
Actuation of the switch causes the right window viewing head to swing away from the cockpit to allow egress.
m.
In the event an anomaly called “Computer Runaway” occurs, PROBLEM FREEZE,
MOTION OFF, and all communications fall to operate.
The recommended procedure to halt the motion system Is to activate the RIGHT VISUAL DISPLAY CONTROL switch In the trainee station.
This triggers the motion system microswitch and shuts down motion.
n.
When the ownship takes a direct weapons hit, there Is a violent reaction from the motion system.
The pilot station receives a 10- to 15-degree pitch-up cue and
700- to 900-knot side wind effect.
The CPG station receives only the side wind effects to prevent Injury when the CPG’s face is lowered toward the cockpit display.
o.
An abort, or safety, circuit Is provided on card 4 of each axis to protect against excessive control motion due to an abnormal transient Input or a hard-over condition resulting from a malfunction.
The circuit senses control acceleration
(derivative of velocity) and switches a high resistance in series with the servo valve torque motor when excessive control acceleration is present.
Since this circuit interfaces with a solenoid-operated dump valve via the start-stop Interlock controls (SSIC), hydraulic pressure to the control loader actuators is also dumped when excessive acceleration Is sensed.
The control loading system can also be aborted manually by depressing the MANUAL ABORT pushbutton on the remote power controller panel.
8-4 Change 2
BATT
BAR0
BUCS
C
CB
CC
CDU
CF
3
CMD
BR
CMS
COMM
COMP
CPG
CPU
CRT
CUM
DA
DASE
DIG
DISPL
DNS
DTV
DVO
6-DOF
ADF
ADI
ADSS
AF
AGL
ALT
AMI
AND
APU
ARCS
AS
ASE
GLOSSARY
Six-degree-of-freedom
A
Autopilot direction finder
Attitude direction Indicator
Air data sensor system
Autofly
Above ground level
Altitude
Automatic malfunction insertion
Alphanumeric display
Auxilliary processing unit or auxilliary power unit
Aerial rocket control system
Airspeed
Aircraft survivability equipment
B
Battery
Barometric
Backup control system
C
Centigrade
Circuit breaker
Current conditions
Computer display unit
Monobromotrifluoromethane
Command
Combat mission simulator
Communication
Computer
Copilot/gunner
Central processing unit
Cathode-ray tube
Accumulative
D
Department of the Army
Digital automatic stabilization equipment
Digital image generation
Display
Doppler navigation system
Day television
Direct-view optics
TM 55-6930-214-10
Glossary 1
HAD
HARS
HDD
HDG
HDST
HE
HMD
HOD
HSI
HSS
HTR
HYD
Tm 55-6930-214-10
ECS
ECU
EMER
F
FAB
FARP
FCC
FD/LS
FLIR
FLT
FWD
GBX
GCA
IC
ICS
IHADSS
INBD
IND
INDEP
INST
INTEG
IOS
IR
Environmental control system
Electrical control unit
Emergency
E
F
Fahrenheit
Forward avionics bay
Forward arming and refueling point
Fire control computer
Fault detection and location system
Forward-looking infrared
Flight
Forward
G
Gearbox
Ground-controlled approach
H
High-action display
Heading and attitude reference system
Heads-down display
Heading
Headset
Hellfire electronics
Helmet-mounted display
Head-out display
Horizontal situation indicator
Helmet sight subsystem
Heater
Hydraulic
I
Initial condition
Intercommunication system
Integrated helmet and display sight system
Inboard
Independent
Independent
Instructor
Integrated
Instructor/operator station
Infrared
J
K
Glossary 2
LDNS
LOS
LRF/D/T
LKD
LT
MALF
MCS
MET
MF
MNL
MON
MS
MSL
MSTR
NAV
NOE
NR
OBS or OBV
ORT
OTW
OUTBD
OVRD
PA
PAR
PDS
PEN AIDS
PF
PH
PLT
PNVS
PTR
PVT
RA
RCL
RD
L
Lightweight Doppler navigation set
Line-of-sight
Laser range finder/designation/tracking
Locked
Light
M
Malfunction
Main computational system
Mission elapsed time
Manual freeze
Manual
Monitor
Malfunction simulation
Missile or mean sea level
Master
N
Navigation
Nap-of-the-earth
Main rotor speed
O
Observer
Optical relay tube
Out-the-window
Outboard
Override
P
Probability of being acquired
Precision approach radar
Program design specifications
Penetration aids
Parameter freeze
Probability of being hit
Pilot
Pilot night vision sensor
Pointer
Private
Q
R
Radar altitude
Recall
Remote display
TM 55-6930-214-10
Glossary 3
TADS
TEE
TGT
TQ
TRU
TSU
TV
TM 55-6930-214-10
RDR
RGN
RKT
RMI
RP
RTR
S/R
SCAS
SCE
SCG
SEL
SIM
SYS
UTM
VASI
VDU
VIB
VIS
VIS FRONT
VIS L
VIS R
VRS
VS
WAYPT
WD
WPNS
WT
WV
R - Continued
Radar
Range
Rocket
Radio magnetic indicator
Record/playback
Rotor
S
Store/reset stability and command augmentation system
Signal Conversion equipment
Security classification guide
Select
Simulator
System
T
Target acquisition/designation sight
Target engagement exercise
Target
Torque
Transformer rectifier unit
Telescopic sight unit
Television
U
Universal transverse mercator
V
Visual approach slope indicator video display unit
Vibration
Visual
Visual (display) front
Visual (display) left
Visual (display) right
Video Recorder System
Vertical speed
W
Waypoint wind direct ion
Weapons
Weight
Wind velocity
Glossary 4 Change 2
x-c
XMIT
XMSN
Cross-country
Transmit
Transmission x
Y
Z
TM 55-6930-214-10
Glossary 5/(Glossary 6 blank)
TM 55-6930-214-10
INDEX
Subject
1-KM Altitude/Airspeed Plots Page Display
6-KM Altitude/Airspeed Plots Page Display
A
ABBREVIATIONS
ACCESSORY SYSTEMS
ALTITUDE/AIRSPEED PLOTS
AMI Prep Data Entry Procedure
AMI Prep Data Worksheet
AMI PREPARATION
ARMAMENT SYSTEMS
AUDIO SYSTEM
AUTOFLY
Autofly Prep Page Display
AUTOFLY PREPARATION
Autofly Set Page Display
AUTOMATED PROGRAM PREPARATION
AUTOMATIC MALFUNCTION INSERTION
Automatic Malfunction Insertion Page Display
Automatic Malfunction Insertion Preparation Page Display
AVIONICS
Avionics Systems
B
Battle Position Map Page Display
BATTLE POSITION MAPS
Battle Position Target Site Map Page Display
BATTLE POSITION TARGET SITES
C
CLEARING MALFUNCTIONS
COCKPIT CIRCUIT BREAKERS
Cockpit Discrepancies Page Display
COCKPIT INSTRUMENTATION SIMULATION
COMMUNICATIONS CONTROL
COMMUNICATIONS EQUIPMENT
COMPUTER SYSTEM
CONTROL LOADING
CONTROL PANEL CRT DISPLAYS
CONTROLS AND INDICATORS
CPG AUTOFLY CONTROL
CPG Cyclic Page Display
Paragraph,
Figure.
Table
Number
F7-29
F7-28
Page
7-74
7-73
5-7
2-17,
7-55
F7-70
7-61
F7-63
III
7-52 l-6
2-25
7-37
T7-13
F7-68
7-59
5-10,
2-33
F7-55
F7-67
3,
5-2
T3-1
F7-19
7-32
F7-46
7-44
5-2
2-20,
7-131 l-160
7-158
7-135
7-142 l-120 l - l
2-30
7-72 l-150
7-146
7-144
5-4,
2-31
7-122
7-145
3-1,
5-l
3-2
7-58
7-56.2
7-101
7-100
7-66
5-9
F7-11
2-29
7-6
3-2
2-6
2-32
7-38
I
7-11
F7-35
7-175
5-4
7-41
2-31
7-10
3-l
2-8
2-31
7-72
7-1
7-17
7-80
Change 2 Index 1
TM 55-6930-214-10
Paragraph
Figure,
Table
Number
Subject
C - Continued
CPG Fire Control Panel Page Display
CPG Missile Control Panel Page Display
CPG ORT Page Display
CRASH/HIT OVERRIDE
CROSS-COUNTRY MAP
Cross-Country Map (Zoom On) Page Display
Cross-Country Map Display Page
CRT INTERCHANGE
CRT PAGE DISPLAYS DESCRIPTION
CURRENT CONDITIONS
Current Conditions Page Display
D
DATA ENTRY KEYBOARD
Data Entry Keyboard Control Panel
Demonstration Prep Page Display
DEMONSTRATION PREPARATION
Demonstration Set No. Page Display
DEMONSTRATIONS
Demos/Autofly/Record Playback Index Page 400A Display
Demos/Autofly/Record Playback Index Page 4008 Display
Demos/Autofly/Record Playback Index Page 400C Display
Demos/Autofly/Record Playback Index Page 400D Display
Doppler Computer Display Unit Page Display
E
Effectivity Coding
ELAPSED-TIME CLOCK (TIMER)
EMERGENCY PROCEDURES
EMERGENCY PROCEDURES AND SAFETY
EMERGENCY SHUTDOUW
EMERGENCY STOP
ENGAGEMENT PERFORMANCE
Engagement Performance Page Data Display
EVALUATION
F
FACILITY POWER FAILURE
FARP CONTROL
FLIGHT COMMAND
FLIGHT MONITOR
Flight Monitor Page Display
FORMS AND RECORDS
Index 2 Change 2
8-3
7-49
7-4
7-29
F7-14 l-4
F7-31
F7-30
F7-34
7-16
7-33
F7-21
F7-20
7-8.2
I I
7-27
F7-12
7-5
F7-3
F7-69
7-60
F7-60
2-18,
7-54
F7-58
F7-59
F7-61
F7-62
F7-37
7-19
I
8
8-l
7-l
7-50
T7-11
4-4
Page
8-2
7-110
7-6
7-50
7-52 l-l
7-76
7-75
7-79
7-19
7-59
7-61
7-60
7-17
7-31
7-42
7-43
7-7
7-9
7-155
7-154
7-130
2-22,
7-123
7-128
7-129
7-133
7-134
7-82 i
7-22
8-l
8-l
8-l
7-l
7-114
7-116.1
4-l
Paragraph,
Figure,
Table
Number
TM 55-6930-214-10
Page
Subject
F - Continued
Forward Arming and Refueling Point (FARP) Control
Page Display
F7-52
GCA 10-Hile Scale Page Display
GCA 2-Mile Scale Page Display
GCA PLOTS
General CRT Page Grouping
GENERAL DESCRIPTION
GLOSSARY
F7-26
F7-27
7-36
T7-3
2-7
H
HARDCOPY
HEADSET VOLUME CONTROL
7-7
7-13
I
INDEPENDENT MODE
INDEX
INDICATOR LAMP TEST
INITIAL CONDITIONS
Initial Conditions Page Display
Initial Conditions/Current Conditions Index Page Display
INSTRUCTIONAL FEATURE PREPARATION
Instructions for Use of Manual Target Control CRT Page
INSTRUCTOR INTERCOMMUNICATIONS SYSTEM
INSTRUCTOR SEATS
INSTRUCTOR VISUAL CONTROL
INSTRUCTOR/OPERATOR STATION DESCRIPTION
Instructor/Operator Stations
INSTRUCTORS MONITORS
INTEGRATED MODE
Integrated/Independent Operation Features
INTRODUCTION
IOS AREA LIGHTING
IOS CONTROL PANELS
IOS CRT SCREEN DISPLAY
IOS CRT Status Area Data
IOS CRT-CONTROLLABLE PARAMETERS
J
5-12
7-17
I I
F2-2,
2-3
7-21
5-13
T2-1
1
7-9
7-26
F7-10
F7-9
7-58
T7-10
2-13
2-10
2-12
2-8
7-24,
F7-6
T7-4
5-8
7-113
7-70
7-71
7-69
7-26
2-9
Glossary 1
7-17
7-18
5-5
Index 1
7-17
2-9
2-10,
2-7
7-22
5-5
2-21 l - l
2-19
7-32
7-36
7-33
7-142
7-105
2-19
2-9
7-20
2-9
7-24,
7-26
7-29
5-2
Change 2 Index 3
TM 55-6930-214-10
Subject
K
Keyboard Interpreter Message Types
L
LEFT CRT/RIGHT CRT
LIGHTING CONTROL
M
MAJOR MODE SELECT
MALFUNCTION CONTROLS
MALFUNCTION DELETION
Malfunction Details
Malfunction Index Page Display
HALFUNCTION INSERTION
HALFUNCTION LIST
MALFUNCTION SIMULATION
Malfunctions List
MANUAL FREEZE
MANUAL MALFUNCTION
MANUAL TARGET CONTROL
Manual Target Control Page Display
MAP SYMBOLOGY
Map Symbology Page Display
MASTER RESET
MINI-INDEXES
Miscellaneous Current Conditions
MISSING MAN
Missing Man/Independent Mode Master Page Display
Missing Han/Independent Mode Slave Page Display
MODES OF OPERATION
MOTION CONTROL
MOTION SIMULATION
MOTION SYSTEM
N
Navigation and Communication Index Page Display
Navigation and Communications Facilities Page 601
Display
Navigation and Communications Facilities Page 602
Display
NAVIGATION EQUIPMENT
NAVIGATION/COMMUNICATIONS
NORMAL OPERATING PROCEDURES
Index 4 Change 2
Paragraph,
Figure,
Table
Number
Page
T7-1
7-8
7-12
7-25,
F7-8
T7-8
7-57
F7-65
F7-66
I I I
7-3
2-27
2-4,
5-5
7-2
7-15
7-65
T7-16
F7-56
7-64
7-67
2-31
T7-15
7-18
7-53
7-45
F7-47
7-35
F7-24
7-10
F7-16
F7-17
F7- 18
3-3
7-31
7
7-10
7-17
7-18
7-31,
7-31
7-49
7-137
7-139
7-140
2-20
7-6
2-30
2-7,
5-l
7-177
7-21
7-123
7-102
7-103
7-65
7-66
7-17
7-l
7-19
7-175
7-181
7-124
7-175
7-176
2-31
7-54
7-55
7-56
3-l
7-50
7-1
Subject
O
OBSERVER COMMUNICATIONS PANEL
OBSERVER SEATS
OCCUPANCY
OPERATING LIMITS AND RESTRICTIONS
OPERATIONAL SAFETY
OPERATIONAL SYSTEM
Ownship Engagement Performance Page Display
P
PARAMETER FREEZE
Parameter Freeze Page Display
Pilot Cyclic Page Display
Pilot Fire Control Panel Page Display
Pilot Missile Control Panel Page Display
Pilot/CPG IOS Console Control Panels
Pilot/CPG Trainee Control Panel
PREFACE
Q
R
RADAR AND TRANSPONDER EQUIPMENT
RADIO COMMUNICATION AND INTERCOMMUNICATION SYSTEM
(ICS) SIMULATION
Range of Values for Current Conditions Line Entries
Range of Values for Initial Conditions Line Entries
RECORD/PLAYBACK
Record/Playback Command Page Display
REMOTE DISPLAY
REPLAY CONTROL
REPORTING OF ERRORS
Rocket Configuration Page Display
S
SAFETY
SAFETY SUMMARY
SCOPE
Security Requirements
SIMULATED MALFUNCTIONS
SIMULATION SYSTEM CAPABILITIES
Paragraph,
Figure.
Table
Number
TM 55-6930-214-10
Page
7-23,
F7-5
2-11
5-4
5
8-4
2-l
F7-53
7-28
F7-13
F7-36
F7-33
F7-32
F2-3,
F7-1,
F2-4,
F7-4
F7-2
7-24,
7-25
2-9
5-l
5-l
8-3
2-l
7-114.1
7-49
7-51
7-81
7-78
7-77
2-11,
7-2,
2-15,
7-16
7-7 i
3-4
2-30
T7-6
T7-5
7-56
F7-64
7-8
7-20 l-5
F7-51
3-1
2-31
7-45
7-38
7-136
7-138
7-17
7-22 l - l
7-112
I I l - l
I v
2-21
8-3 x l i l - l
7-175
2-24
Change 2 Index 5
TM 55-6930-214-10
Trainee Station
TRAINING
TRAINING CAPABILITIES
Paragraph,
Figure,
Table
Number
!
Subject
SIMULATOR COMPARTMENTS
SOUND SIMULATION
STATUS INTERCHANGE
STORE/RESET CURRENT CONDITIONS
SYSTEM DESCRIPTION AND OPERATION
SYSTEM FAILURES
SYSTEMS SIMULATED
S - Continued
T
Tactical Instrument Gaming Area (Zoom On) Page Display
TACTICAL INSTRUMENT GAMING AREA DISPLAY
Tactical Instrument Gaming Area Page Display
TACTICS
Tactics Current Conditions
TADS UNIT TARGETS
TARGET ENGAGEMENT EXERCISE
Target Engagement Exercise Page Display
Target Engagement Exercise Prep Page Display
TARGET ENGAGEMENT EXERCISE PREPARATION
TARGET EVALUATION
Target Evaluation Page Display
TARGET SITES LIST
Target Sites List Page Display
TARGET SITES OVERVIEW
Target Sites Overview (Zoom On) Page Display
Target Sites Overview Page Display
TARGET STATUS
Target Status Information
Target Status Page Display
TARGET TYPES LIST
Target Types List Page Display
TECHNICAL MANUAL CHANGES
TEE Prep Data Entry Procedure
TEE Prep Data Worksheet
TEMPERATURE AND HUMIDITY
THREAT SCORING
Threat Scoring Page Data Display
Threat Scoring Page Display
TIME REFERENCES
TRAINEE CONTROL PANELS
F7-43
7-40
T7-9
F7-39
7-41
F7-40 l-3
T7-14
F7-72
5-3
7-51
T7-12
F7-54
2-14
7-22,
F2-7,
2-9
F2-6
2-16,
4-3
I v
F7-71
7-62
7-47
F7-49
7-42
F7-42
7-43
F7-44
F7-23
7-34
F7-22
4
T7-7
5-11
7-39
F7-38
2-2
2-26
7-8A
7-14
2
8-2
V
Index 6 Change 2
Page
7-164
5-l
7-114
7-118
7-116
2-19
7-24,
2-18,
7-96
7-85
7-86
7-87
7-86
7-88 l - l
7-170
2-9
2-17
2-20,
4-l
2-23
7-162
7-161
7-108
7-109
7-91
7-92
7-91
7-97
7-64
7-62
7-63
4-l
7-48
5-4
7-83
7-84
2-l
2-30
7-17
7-18
2-l
8-1
2-30
Subject
T - Continued
TRAINING OBJECTIVES
TRAINING TASKS
Typical AH-64 CMS andComputer Rooms System Complex
Typical CRT Page Status Areas
Typical Malfunctions Page Display
Typical Map Symbols
Typical Target Symbols
U
V
VIBRATION SIMULATION
VISIONICS POINTING/REMOTE DESIGNATOR
Visionics Pointing/Remote Designator Control Page
Display
Visual Display Availability
Visual Gaming Weapons Symbols
VISUAL MODE HELP PAGE
Visual Mode Help Page Display
Visual Monitor Display Modes
VISUAL SIMULATION
VISUAL SYSTEM
VISUAL SYSTEM CAPABILITIES
W
Weapons Loading Page Display
WEAPONS LOADING/ROCKET CONFIGURATION
X
Y
Z
Paragraph,
Figure,
Table
Number
TM 55-6930-214-10
Page
2-20
2-23
F2-1
F7-7
F7-57
F7-25
F7-45
2-23
2-26
2-2
7-29
7-126
7-67
7-98
2-28
7-46
F7-48
T5-1
F7-41
7-30
F7-15
T7-2
4-2
2-5,
5-6,
6
2-22
F7-50
7-48
2-30
7-102
7-104
5-3
7-89
7-50
7-53
7-23
4-l
2-8,
5-2,
6-l
2-26
7-111
7-110
* U.S. GOVERNMENT PRINTING OFFICE: 1992 554-123/40048
Change 2 Index 7/(Index 8 blank)
P I N : 063796-002
TM 55-6930-214-10
By Order of the Secretary of the Army:
Official:
R. L. DILWORTH
Brigadier General, United States Army
The Adjutant General
CARL E. VUONO
General, United States Army
Chief of Staff
DISTRIBUTION:
To be distributed in accordance with DA Form 12-31, -10 & CL maintenance requirements for AH-64A Helicopter, Attack (APACHE)
PIN 063796-000
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Key Features
- Fixed-base simulation system
- Training in the use of AH-64A Apache helicopters
- Normal and emergency procedural mission training
- Weapons delivery
- Navigation Instrument flight operation
- Day, dusk, and night visual flight operations
- Ordnance delivery systems
- Six-degree-of-freedom motion system
- Visual system that simulates natural helicopter environment surroundings
Frequently Answers and Questions
What is the purpose of the AH-64A Apache Combat Mission Simulator?
What types of training can be conducted on the simulator?
How realistic is the simulation?
What are the key features of the simulator?
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