G58 Baron POH/AFM

G58 Baron POH/AFM
sec03atoc.fm Page 1 Thursday, May 1, 2008 2:18 PM
Model G58
SECTION 3A
ABNORMAL PROCEDURES
TABLE OF CONTENTS
SUBJECT
PAGE
Air Start. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-3
Landing Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-4
One-Engine-Inoperative Landing . . . . . . . . . . . . . . . . . . 3A-4
One-Engine-Inoperative Go-Around. . . . . . . . . . . . . . . . 3A-5
Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-6
Starter Engage [L START ENGD] or
[R START ENGD] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-6
Alternator High Voltage [LBUS VOLT HI] or
[RBUS VOLT HI] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-6
Alternator Low Voltage [LBUS VOLT LO] or
[RBUS VOLT LO] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-7
Circuit Breaker Tripped . . . . . . . . . . . . . . . . . . . . . . . . . 3A-8
Landing Gear Manual Extension . . . . . . . . . . . . . . . . . . 3A-8
Landing Gear Retraction After Practice
Manual Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-9
Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-10
Surface Deice System . . . . . . . . . . . . . . . . . . . . . . . 3A-10
Electrothermal Propeller Deice System . . . . . . . . . . 3A-11
Emergency Static Air Source System. . . . . . . . . . . . 3A-12
Electrothermal Heated Windshield Segment . . . . . . 3A-12
Heated Pitot Tube. . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-13
Forward Cabin Door Open in Flight . . . . . . . . . . . . . . 3A-13
Avionics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14
Autopilot Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-14
Failure of Autopilot Pre-Flight Test . . . . . . . . . . . . . . 3A-14
Autopilot Out-Of-Trim . . . . . . . . . . . . . . . . . . . . . . . . 3A-14
Loss of a Flight Director/Autopilot Mode. . . . . . . . . . 3A-15
Loss of Navigation Information . . . . . . . . . . . . . . . . . 3A-15
Avionics Master Switch Failure . . . . . . . . . . . . . . . . . . 3A-16
April, 2008
3A-1
sec03atoc.fm Page 2 Thursday, May 1, 2008 2:18 PM
Model G58
SECTION 3A
ABNORMAL PROCEDURES
TABLE OF CONTENTS (CONT’D)
SUBJECT
PAGE
Transponder Failure . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-16
Engine and/or Fuel Display Failure . . . . . . . . . . . . . . . 3A-16
Erroneous Failure Displays . . . . . . . . . . . . . . . . . . . . . 3A-17
Failed Heading During Ground Operations. . . . . . . . . 3A-18
System Failure without an
associated Failure Display . . . . . . . . . . . . . . . . . . . . . 3A-18
Failure of Cooling Fans [PFD FAN FAIL],
[MFD FAN FAIL] or [AVIONICS FAN]
Advisory Message. . . . . . . . . . . . . . . . . . . . . . . . . . . . 3A-18
Global Positioning System (GPS) . . . . . . . . . . . . . . . . 3A-19
Loss of, or Invalid GPS Signal . . . . . . . . . . . . . . . . . 3A-19
Position Error [POSN ERROR] . . . . . . . . . . . . . . . . 3A-19
Failure of Remote Autonomous Integrity
Monitoring (RAIM). . . . . . . . . . . . . . . . . . . . . . . . . 3A-19
Garmin Terrain Awareness and
Warning System (TAWS) . . . . . . . . . . . . . . . . . . . . . 3A-20
TAWS Forward Looking Caution [TERRAIN] . . . . . 3A-20
Excessive Descent Rate Caution [TERRAIN] . . . . . 3A-21
Negative Climb Rate After Takeoff [TERRAIN] . . . . 3A-22
Premature Descent During
An Approach [TERRAIN] . . . . . . . . . . . . . . . . . . . . 3A-23
Ditching, Off-Airport Landing,
or Flying VFR Around Unique Terrain . . . . . . . . . . 3A-23
Altimeter Disagreement . . . . . . . . . . . . . . . . . . . . . . 3A-23
Additional Caution Annunciations . . . . . . . . . . . . . . . . 3A-24
Oil Pressure Low [OIL PRESS LO] . . . . . . . . . . . . . 3A-25
Fuel Quantity Low [FUEL QTY LO] . . . . . . . . . . . . . 3A-25
Alternator Load High [ALT LOAD] . . . . . . . . . . . . . . 3A-25
Surface Deice Air Pump
[L AIR PUMP] or [R AIR PUMP] . . . . . . . . . . . . . . 3A-26
3A-2
April, 2008
sec03a.fm Page 3 Thursday, May 1, 2008 2:18 PM
Model G58
Section 3A
Abnormal Procedures
Closed [BRACKETS] in this section denotes Warning, Caution
and Advisory alerts which appear on the PFD and MFD.
AIR START
The pilot should determine the reason for
engine failure before attempting an airstart.
1. Alternator (inoperative engine) . . . . . . . . . . . . . . . . .OFF
2. Fuel Selector Valve. . . . . . . . . . . . . . . . . . . . . . . . . . .ON
(feel for detent; confirm visually)
3. Throttle . . . . . . . . . . . . . . SET (approximately 1/4 travel)
4. Mixture Control:
• FULL RICH, below 5000 ft (1/2 travel above 5000 ft)
5. Fuel Boost Pump . . . . . . . . . . . . . . . . . . . . . . . . . . LOW
6. Magnetos . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON
7. Propellers:
With Unfeathering Accumulators:
a. Propeller Control . . . . . . . . . . . . . . . . FORWARD OF
FEATHERING DETENT
(until engine obtains 600 RPM)
b. Propeller Control . . . . . . . . . . . . BACK TO DETENT
(to avoid overspeeding)
c. Starter (if necessary) . . . . ENGAGE MOMENTARILY
(to accomplish unfeathering)
d. If propeller does not unfeather or engine does not
turn, proceed to Without Unfeathering Accumulators
procedure.
Without Unfeathering Accumulators:
a. Propeller Control. . . . . . . . . . . . . . . . . FORWARD OF
FEATHERING DETENT
April, 2008
3A-3
Document Date
3A-3
sec03a.fm Page 4 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
b. Starter . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
(to accomplish unfeathering)
c. If engine fails to run, clear engine by allowing it to
windmill with mixture in CUT OFF. When engine fires,
advance mixture to full rich.
8. After Engine Starts . . . . . . . . . . . ADJUST THROTTLE,
PROPELLER and MIXTURE
CONTROLS
9. Fuel Boost Pump. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
(when reliable power has been regained)
10. Alternator. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
11. Oil Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
12. Warm Up Engine (approximately 1500 RPM and 15 in.
Hg)
13. Power . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED
14. Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED
LANDING EMERGENCIES
ONE-ENGINE-INOPERATIVE LANDING
On final approach and when it is certain that the field can be
reached:
1. Landing Gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
2. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . APPROACH (15°)
3. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 KTS
4. Power . . . . . . . . . . . . . . . . . . . . . . . . . . .AS REQUIRED
(to maintain 800 ft/min rate of descent)
When it is certain there is no possibility of go-around:
5. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN (30°)
6. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KTS
7. Execute Normal Landing
3A-4
3A - 4
April, 2008
Document Date
sec03a.fm Page 5 Thursday, May 1, 2008 2:18 PM
Model G58
Section 3A
Abnormal Procedures
ONE-ENGINE-INOPERATIVE GO-AROUND
Level flight might not be possible for certain
combinations of weight, temperature and
altitude. In any event, DO NOT attempt a
one-engine-inoperative go-around after
flaps have been fully extended.
1. Power . . . . . . . . . . . . . . . . . . . MAXIMUM ALLOWABLE
2. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP
3. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP (0°)
4. Airspeed . . . . . . . . . . . . .MAINTAIN 101 KTS MINIMUM
April, 2008
3A-5
Document Date
3A-5
sec03a.fm Page 6 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
SYSTEMS
STARTER ENGAGE [L START ENGD] or
[R START ENGD]
After engine start, should the starter relay remain engaged, the
starter will remain energized and the starter energized Warning Alert will remain illuminated. Continuing to supply power to
the starter will result in eventual loss of electrical power.
Ground Operations:
1. Alternators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
2. Batteries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
3. DO NOT TAKE OFF.
Illuminated In Flight After Air Start:
1. Alternator (affected engine). . . . . . . . . . . . . . . . . . . OFF
2. Battery (affected engine) . . . . . . . . . . . . . . . . . . . . . OFF
NOTE
Depending on which Bus is affected, heading and attitude information will be lost. Use
standby instruments.
3. Land as soon as practical.
ALTERNATOR HIGH VOLTAGE [LBUS VOLT HI]
or [RBUS VOLT HI]
Display of either [LBUS VOLT HI] or [RBUS VOLT HI] caution
alert on the PFD:
1. MFD Softkeys . . . . . . SELECT ENGINE AND SYSTEM
2. Bus Volts (failed side) . . . . . . . . . . . . . . . . . . . . . CHECK
If voltage is less than 30 volts a false warning is indicated:
3. Continue to use the alternator.
3A-6
3A - 6
April, 2008
Document Date
sec03a.fm Page 7 Thursday, May 1, 2008 2:18 PM
Model G58
Section 3A
Abnormal Procedures
If voltage is greater than 30 volts a failure on the voltage regulator is indicated:
4. Alternator (failed side). . . . . . . . . . . . . . . . . . . . . . . .OFF
5. Nonessential Electrical Equipment . . . . . . . . . . . OFF AS
REQUIRED
(to reduce load on operative alternator)
6. Bus Volts (failed side) . . . . . . . . . . VERIFY < 28 VOLTS
7. Alternator (failed side). . . . . . . . . . . . . . . . . . . . BUS TIE
(ties the side with the functional alternator to the inoperative side)
8. Alt Load. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
9. Nonessential Electrical Equipment . . . . . . . . . . . .ON AS
REQUIRED
(maintain load limits of operative alternator)
ALTERNATOR LOW VOLTAGE [LBUS VOLT LO]
or [RBUS VOLT LO]
Display of either [LBUS VOLT LO] or [RBUS VOLT LO] caution
alert on the PFD:
1. MFD Softkeys . . . . . . .SELECT ENGINE AND SYSTEM
2. Bus Volts (failed side) . . . . . . . . . . . . . . . . . . . . . CHECK
If voltage is greater than 24 volts a false warning is indicated:
3. Continue to use the alternator.
If voltage is less than 24 volts a failure on the voltage regulator
is indicated:
4. Alternator (failed side). . . . . . . . . . . . . . . . . . . . . . . .OFF
5. Nonessential Electrical Equipment . . . . . . . . . . . OFF AS
REQUIRED
(to reduce load on operative alternator)
6. Bus Volts (failed side) . . . VERIFY APPROX. 24 VOLTS
April, 2008
3A-7
Document Date
3A-7
sec03a.fm Page 8 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
7. Alternator (failed side) . . . . . . . . . . . . . . . . . . . . BUS TIE
(ties the side with the functional alternator to the inoperative side)
8. Alt Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
9. Nonessential Electrical Equipment . . . . . . . . . . . ON AS
REQUIRED
(maintain load limits of operative alternator)
CIRCUIT BREAKER TRIPPED
1. Nonessential Circuit . . . . . DO NOT RESET IN FLIGHT
2. Essential Circuit (necessary for continued safe flight):
a. Circuit Breaker
(after allowing to cool
for a minimum of 10 sec) . . . . . . PUSH TO RESET
If Circuit Breaker Trips Again:
b. Circuit Breaker . . . . . . . . . . . . . . . . DO NOT RESET
LANDING GEAR MANUAL EXTENSION
1. Airspeed . . . . . . . . . . . . . . . . . . . . . . .152 KTS or LESS
NOTE
Manual extension of the gear can be facilitated by first reducing the airspeed as much
as practical.
2. LANDING GEAR MOTOR Circuit Breaker
(left circuit breaker panel). . . . . . . . . . . . . . . . . . . PULL
3. Landing Gear Handle . . . . . . . . . . . . . . . . . . . . . DOWN
4. Handcrank Handle Cover
(at rear of front seat) . . . . . . . . . . . . . . . . . . . . REMOVE
5. Handcrank . . . . . . . . . . . . . . . . . . ENGAGE AND TURN
CCW AS FAR AS POSSIBLE
(approximately 50 turns)
3A-8
3A - 8
April, 2008
Document Date
sec03a.fm Page 9 Monday, January 12, 2009 8:40 AM
Model G58
Section 3A
Abnormal Procedures
6. If the electrical system is operative, a positive gear down
indication can be made as follows:
a. LDG GR WARN and LDG GR POS LTS
Circuit Breaker . . . . . . . . . . . . . . . . . . . . . .CHECK IN
b. Landing GEAR DN &
LOCKED Lights. . . . . . . . . .ILLUMINATED (3 green)
c. CHECK that the gear warning horn does not sound
when either throttle is retarded to idle.
7. Handcrank . . . . . . . . . . . . . DISENGAGE, THEN STOW
8. Do not move the Landing Gear Handle or reset the
LANDING GEAR MOTOR Circuit Breaker.
9. The landing gear should be considered UNLOCKED
until the airplane is on jacks and the system has been
cycled and checked.
Do not operate the landing gear electrically
with the handcrank engaged. Damage to
the mechanism could occur.
The manual extension system is designed
to lower the landing gear only. DO NOT
ATTEMPT TO RETRACT THE GEAR
MANUALLY.
LANDING GEAR RETRACTION AFTER PRACTICE
MANUAL EXTENSION
After practice manual extension of the landing gear, the gear
can only be retracted electrically, as follows:
1. Handcrank . . . . . . . . . . . . . . . . . . CONFIRM STOWED
2. LANDING GEAR MOTOR Circuit Breaker . . . . . . . . . IN
3. Landing Gear Handle . . . . . . . . . . . . . . . . . . . . . . . . . UP
April, 2008
3A-9
3A-9
sec03a.fm Page 10 Wednesday, November 12, 2008 3:05 PM
Section 3A
Abnormal Procedures
Model G58
NOTE
The landing gear will not retract unless the
throttle is in a position corresponding to
approximately 15 in. Hg manifold pressure
or above.
ICE PROTECTION
SURFACE DEICE SYSTEM
Failure of the AUTO Mode:
• Surface Deice Switch. . . . . . . . . . . . . . . . . . . . MANUAL
(Do not hold more than 8 seconds.)
NOTE
The boots will inflate only as long as the
switch is held in the MAN (manual) position.
When the switch is released, the boots will
deflate.
Failure of boots to deflate:
1. Pull Surface Deice Circuit Breaker on pilot’s sidewall circuit breaker panel.
2. If boots reinflate after Surface Deice Circuit Breaker is
reset, use circuit breaker as a manual surface deice
switch, following the procedures outlined in Failure of the
AUTO Mode.
Failure of AUTO and MAN modes of operation:
• Exit icing conditions as soon as possible.
3A-10
3A - 10
December, 2008
sec03a.fm Page 11 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
ELECTROTHERMAL PROPELLER DEICE SYSTEM
An abnormal reading on the Propeller Deice Ammeter indicates need for the following action:
1. Zero Amps:
Check the propeller deice circuit breaker switch. If the circuit breaker portion of the switch has tripped the switch off,
wait approximately 30 seconds before resetting. If the
switch trips again, do not reset. If the ammeter reads zero
and the switch has not tripped, check Alt Load for deflection as the switch is cycled on and off to confirm a malfunction of the ammeter. If Alt load does not show a
deflection, consider the propeller deice system to be inoperative.
2. Zero to 14 Amps:
If the propeller deice system ammeter occasionally or regularly indicates less than 14 amps, operation of the propeller deice system can continue unless serious propeller
imbalance results from irregular ice shedding.
3. 18 to 23 Amps:
If the propeller deice system ammeter occasionally or regularly indicates 18 to 23 amps, operation of the propeller
deice system can continue unless serious propeller imbalance results from irregular ice shedding.
4. More than 23 Amps:
If the propeller deice system ammeter occasionally or regularly indicates more than 23 amps, the system should not
be operated unless the need for propeller deicing is
urgent.
NOTE
If the propeller deice system becomes inoperative, leave icing conditions as soon as
possible. Cycling of the propeller RPM will
assist the propellers in shedding ice.
April, 2008
Document Date
3A-11
3A-11
sec03a.fm Page 12 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
EMERGENCY STATIC AIR SOURCE SYSTEM
THE EMERGENCY STATIC AIR SOURCE SHOULD BE
USED FOR CONDITIONS ANYTIME THE NORMAL STATIC
SOURCE HAS BEEN OBSTRUCTED. When the airplane has
been exposed to moisture and/or icing conditions (especially
on the ground), the possibility of obstructed static ports should
be considered. Partial obstruction will result in the rate of climb
indication being sluggish during a climb or descent. Verification
of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of
climb. This may be accompanied by abnormal indicated airspeed and altitude changes beyond normal calibration differences.
Whenever any obstruction exists in the Normal Static Air System, or the Emergency Static Air System is desired for use:
1. Emergency Static Air Source . . . . . EMERGENCY (ON)
(lower sidewall adjacent to pilot)
2. For Airspeed Calibration and Altimeter Correction, refer
to Section 5, PERFORMANCE.
When the Emergency Static Air System is no longer needed:
3. Emergency Static Air Source . . . . . . . . (NORMAL) OFF
ELECTROTHERMAL HEATED WINDSHIELD SEGMENT
Failure of the heated windshield segment can be confirmed by
cycling the WSHLD HEAT switch to OFF, then ON. If a deflection of the Alt Load is not apparent, consider the system inoperative and exit icing conditions. Partial windshield deicing may
be accomplished using the defroster. Maximum defrost heat is
achieved as follows:
1. Heater Switch . . . . . . . . . . . . . . . . . . . . . . . . . . HEATER
2. Cabin Air Control . . . . . . . . . . . . . . . . . . . . . . .PULL AFT
(not more than 1/2 travel)
3A-12
3A - 12
April, 2008
Document Date
sec03a.fm Page 13 Thursday, January 29, 2009 4:03 PM
Model G58
Section 3A
Abnormal Procedures
3. Cabin Heat Control . . . . . . . . . . . . . . . . . . . . PULL OUT
4. Defrost Control . . . . . . . . . . . . . . . . . . . . . . . PULL OUT
5. Pilot Air Control . . . . . . . . . . . . . . . . . . . . . . . . . PUSH IN
6. Copilot Air Control. . . . . . . . . . . . . . . . . . . . . . . PUSH IN
HEATED PITOT TUBE
Failure of pitot heat in icing conditions may be noticed by a
rapid decrease in indicated airspeed, or some other inappropriate reading for the given flight condition. Leave icing conditions
as soon as possible.
CABIN HEATER
Failure of the cabin heater in icing conditions:
1. Heater . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TURN OFF
2. Icing Conditions . . . . . . EXIT AS SOON AS POSSIBLE
WING ICE LIGHT
Failure of the Wing Ice Light at night in icing conditions:
1. Cabin Lights Circuit Breaker . . . . . . . . . . . . . . . . CHECK
2. Icing Conditions . . . . . . EXIT AS SOON AS POSSIBLE
FORWARD CABIN DOOR OPEN IN FLIGHT
If the forward cabin door is not properly latched, it may open
during takeoff roll or during flight. The door may trail open
approximately 3 inches, but the flight characteristics of the airplane will not be affected. The rate-of-climb will be reduced.
If the forward cabin door opens in flight:
1. Maintain Control of the Airplane.
2. Do not attempt to close the door until after landing.
3. All Occupants remain seated with seat belts fastened.
4. Land as soon as practical using Normal Procedures.
December, 2008
3A-13
3A-13
sec03a.fm Page 14 Wednesday, November 12, 2008 3:06 PM
Section 3A
Abnormal Procedures
Model G58
If occupant in right seat can assist:
5. Hold door during and after landing to prevent it from
swinging open.
AVIONICS
AUTOPILOT FAILURES
FAILURE OF AUTOPILOT PRE-FLIGHT TEST
Red [PFT]
1. AP SERVOS Circuit Breaker. . . . . . . . . . . . . . . . . PULL
[PFT] - Extinguished
2. Do Not Reset Circuit Breaker Unless Airplane is on the
Ground.
AUTOPILOT OUT-OF-TRIM
Yellow [RUD→], [←RUD], [←AIL], [AIL→], [↑ELE], or [↓ELE]
Do not attempt to overpower the autopilot in
the event of a mistrim. The autopilot servos
will oppose pilot input and, in the case of
the pitch axis, will trim the elevator in the
opposite direction to the pilot input. This
could lead to a significant out-of-trim condition.
If [←AIL] or [AIL→], is illuminated:
1. Slip/Skid Indicator . . . . . . . . . . . . . . . .VERIFY CENTER
2. Fuel Imbalance . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
(max. allowable = 15 Gal. or ~1.6 divisions on indicator)
If [←RUD] or [RUD→] is illuminated during a climb:
3. Rudder Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST
(as required)
3A-14
3A - 14
December, 2008
Section 3A
Abnormal Procedures
Model G58 Baron
Temporary Change
to the
Pilot’s Operating Handbook
and
FAA Approved Airplane Flight Manual
P/N 58-590000-67TC1 Rev 1
Publication
Affected
Model G58 Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual (58590000-67, Issued November, 2005)
Airplane Serials TH-2125 thru TH-2158 not in compliance
Numbers
with S.B. 22-3795.
Affected
Description of
Change
Uncommanded pulsing of the control
column during overly aggressive autopilot
captures and during use of the PIT mode
(affects and ABNORMAL and NORMAL
PROCEDURES Sections).
Filing
Instructions
Insert the following pages of this temporary
change into the Model G58 Pilot’s Operating
Handbook and FAA Approved Airplane
Flight Manual and retain until rescinded by
Service Bulletin 22-3795.
- Page 2 of 4 and 1 of 4 following page 3A14 (Abnormal Procedures section).
- Page 3 of 4 and 4 of 4 following page 4-30
(Normal Procedures section).
1 of 4
P/N 58-590000-67TC1 Rev 1
June, 2006
Model G58 Baron
Section 3A
Abnormal Procedures
ABNORMAL PROCEDURES
AVIONICS
AUTOPILOT FAILURES
NUISANCE PITCH PULSE
If a nuisance pitch pulse is encountered, disconnect autopilot.
Retrim and stabilize airplane in the desired flight path and reengage the autopilot, if desired.
P/N 58-590000-67TC1 Rev 1
June, 2006
2 of 4
sec03a.fm Page 15 Wednesday, November 12, 2008 3:06 PM
Model G58
Section 3A
Abnormal Procedures
If an annunciation remains illuminated:
4. Control Wheel . . . . . . . . . . . . . . . . . . . . . HOLD FIRMLY
(be prepared to apply force in the direction of the arrow)
5. AP DISC Switch . . . . . . . . . . . . . . . . . . . . . . . . . PRESS
6. Pitch & Aileron Trim . . . . . . . . . . . . . .RETRIM IF REQD
7. Autopilot (after mistrim is corrected) . . . . . RE-ENGAGE
LOSS OF A FLIGHT DIRECTOR/AUTOPILOT MODE
Yellow flashing Mode Annunciator
Loss of a mode, or failure of it to engage, will be annunciated
by a flashing of the mode in yellow in the AFCS status bar.
After 10 seconds the flight director will revert to the default
mode (ROL or PIT).
Loss of Selected Vertical Mode (FLC, VS, ALT, GS), or,
Loss of Selected Lateral Mode (HDG, VOR, GPS, BC, LOC,
VAPP, LOC)
1. Autopilot Mode Control . . . . . . . . . . SELECT ANOTHER
VERTICAL OR LATERAL MODE
If on an Instrument Approach:
2. Autopilot (if coupled) & Flight Director . . DISCONNECT
(continue the approach manually or execute missed
approach)
LOSS OF NAVIGATION INFORMATION
Yellow flashing Mode annunciator [VOR], [VAPP], [GPS],
[LOC], [BC], or [GS]
Loss of a navigation signal will be annunciated by a flashing of
the mode in yellow in the AFCS status bar. After 10 seconds
the flight director will revert to the default ROL mode.
1. CDI Soft Key . . . . . .SELECT ANOTHER NAV SOURCE
2. HDG Bug (if reqd.) . . . . . SELECT INTERCEPT ANGLE
3. HDG Mode (if reqd.) . . . . . . . . . . . . . . . . . . . . . SELECT
December, 2008
3A-15
3A-15
sec03a.fm Page 16 Thursday, January 29, 2009 1:31 PM
Section 3A
Abnormal Procedures
Model G58
4. NAV Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM
If on an instrument approach at the time the navigation signal
is lost:
5. Execute Missed Approach
AVIONICS MASTER SWITCH FAILURE
If the Avionics Master Switch fails to Operate in the on Position:
• AVIONICS MASTER Circuit Breaker (Left panel) . . . . PULL
NOTE
Turning on the Avionics Master Switch
removes power that holds the avionics
relay open. If the switch fails to the OFF
position, pulling the AVIONICS MASTER
circuit breaker will restore power to the avionics buses.
TRANSPONDER FAILURE
[XPDR FAIL]
The display is not receiving information from the transponder.
1. Confirm status of transponder with ATC.
If Transponder is inoperative:
2. Traffic Advisory System (TAS) (if installed). . . . . . STBY
ENGINE AND/OR FUEL DISPLAY FAILURE
Indications which are not compatible with other instruments.
If the L or R ENG/AFR SENSOR Circuit Breaker is out, the following displays will be inoperative for the corresponding
engine: MAP, RPM, EGT, CHT, Oil Press, Oil Temp, Fuel
Flow, Fuel Qty, and Alt Load.
3A-16
3A - 16
December, 2008
sec03a.fm Page 17 Thursday, January 29, 2009 1:31 PM
Model G58
Section 3A
Abnormal Procedures
If all engine instruments are inoperative:
1. L and R ENG/AFR SENSOR
Circuit Breaker . . . . . . . . . . . . . . . . . . . . . . . .CHECK IN
If a partial failure has occurred:
2. L or R ENG/AFR SENSOR
Circuit Breaker (affected side) . . . . . PULL AND RESET
If one or more engine or fuel displays remain inoperative:
3. Power
(if RPM and/or MAP are inop) . . . . . . SET BASED ON:
a. Throttle Position
b. Engine Noise
c. Airspeed
d. Fuel Flow from cruise tables in Section 5, PERFORMANCE
e. EGT
4. Available Instruments . . . . . . . . . . . . . . . . . . . MONITOR
ERRONEOUS FAILURE DISPLAYS
Erroneous Warning, Caution or Advisory Alerts, Red X’s, or
Erroneous Exceedence displays.
There is a remote chance that an alert, red X or red
exceedence display may be erroneously displayed.
If it is suspected that an erroneous failure display has
occurred:
1. Use other system information to determine if the failure
display is valid.
If the validity of the failure display cannot be confirmed:
2. Assume the failure display is valid and follow the appropriate Emergency or Abnormal procedures.
December, 2008
3A-17
3A-17
sec03a.fm Page 18 Monday, January 12, 2009 9:05 AM
Section 3A
Abnormal Procedures
Model G58
FAILED HEADING DURING GROUND OPERATIONS
(RED “X” OVER [HDG] FLAG ON PFD)
Interference from GPS repeaters operating inside nearby hangars or magnetic anomalies caused by nearby structures can
cause an intermittent loss of heading display while the airplane
is on the ground. Moving the airplane more than 100 yards
away from the source of the interference should alleviate the
condition. Takeoff should not be attempted until fault clears.
SYSTEM FAILURE WITHOUT AN ASSOCIATED
FAILURE DISPLAY
There is a remote chance that a system failure could occur
WITHOUT an associated failure indication (Alert, Red X, or
Exceedence Display.)
1. Use other system information to determine if the system
failure is valid.
If it cannot be determined that the system failure is the result of
an erroneous display:
2. Assume the failure is valid and follow the appropriate
Emergency or Abnormal procedures.
FAILURE OF COOLING FANS [PFD FAN FAIL],
[MFD FAN] or [AVIONICS FAN] Advisory Message
Presentation of one or more of these advisory messages indicates that the PFD fan has failed, the MFD fan has failed, or
the Avionics Fan has failed. Cooling extends the life of this
equipment, but is not required for continued operation.
1. Continue to destination.
2. Repair as soon as practical.
3A-18
3A - 18
April, 2008
58-590000-67A8_sec03a.fm Page 19 Wednesday, May 11, 2011 4:54 PM
Model G58
Section 3A
Abnormal Procedures
GLOBAL POSITIONING SYSTEM (GPS)
LOSS OF, OR INVALID GPS SIGNAL
• Utilize NAV 1 or NAV 2 receivers.
POSITION ERROR [POSN ERROR]
1. GPS signal will flag.
2. Utilize NAV 1 or NAV 2 receivers.
LOSS OF RECEIVER AUTONOMOUS INTEGRITY
MONITORING (RAIM)
During enroute, oceanic, terminal, or initial approach phase of
flight:
1. Continue to navigate using GPS.
2. Verify position using NAV 1 or NAV 2 every 15 minutes.
Or:
3. Utilize NAV 1 or NAV 2 receivers.
During Final Approach:
1. GPS navigation will continue for up to 5 minutes.
2. Conduct missed approach.
3. If terminal GPS sensitivity is lost during the missed
approach, revert to NAV 1 or NAV 2 receivers.
June, 2011
3A-19
58-590000-67A8_sec03a.fm Page 20 Wednesday, May 11, 2011 4:54 PM
Section 3A
Abnormal Procedures
Model G58
GARMIN TERRAIN AWARENESS AND WARNING
SYSTEM (TAWS)
(TH-2138, TH-2141 and after and prior airplanes in compliance with Service Bulletin. 34-3774.)
TAWS FORWARD LOOKING TERRAIN CAUTIONS
[TERRAIN]
Voice Caution Alert: See the following table.
Reduced Required Terrain (or Obstacle) Clearance (RTC or
ROC) Caution - Voice caution alerts and annunciators are provided if the airplane flight path is projected to violate a set of
terrain and obstacle minimum clearance requirements within
approximately 60 seconds.
Imminent Terrain (or Obstacle) Impact (ITI or IOI) Caution Voice caution alerts and annunciators are provided if the airplane flight path is projected to impact the terrain or an obstacle within approximately 60 seconds.
In all cases, a yellow [TERRAIN] will be displayed on the PFD
and the MFD TAWS page, if selected. One of the following
voice caution alerts will be heard.
REASON
VOICE CAUTION ALERT
Violation of Required Terrain
Clearance (RTC) Requirements
within 60 seconds
“Caution Terrain, Caution
Terrain”
Imminent Terrain Impact (ITI)
within 60 seconds
“Terrain Ahead, Terrain Ahead”
Violation of Required Obstacle
Clearance (ROC) Requirements
within 60 seconds
“Caution Obstacle, Caution
Obstacle”
Imminent Obstacle Impact (IOI)
within 60 seconds
“Obstacle Ahead, Obstacle
Ahead”
3A-20
April, 2008
sec03a.fm Page 21 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
NOTE
When the TAWS Page is not displayed and
a terrain or obstacle caution is issued, a
pop-up window is displayed in the lower
right corner of the MFD displaying an
appropriate annunciator. See Section 7,
SYSTEMS DESCRIPTION.
NOTE
Pilots are authorized to deviate from their
current air traffic control (ATC) clearance to
the extent necessary to comply with a
TAWS caution.
The following procedure should be followed if any of the preceding cautions occur.
1. Stop descending, or climb, and/or turn as necessary,
based on analysis of all available instruments and visual
observations, in order to cancel the alert. (The voice
caution alert will be repeated until the threat no longer
exists.)
2. Advise Air Traffic Control as necessary.
EXCESSIVE DESCENT RATE CAUTION [TERRAIN]
Voice Caution Alert: “Sink Rate”
Excessive Descent Rate (EDR) Caution - A Voice caution alert
and annunciator are provided if the airplane is below 5,000 feet
and approaching the terrain at an excessive rate of descent in
relation to the altitude above the terrain. The cautions will be
provided whether or not the TAWS system is enabled. A yellow
[TERRAIN] will be displayed on the PFD and the MFD TAWS
page, if selected, and the voice caution alert “SINK RATE” will
be heard. If corrective action is not taken, an EDR warning will
follow the caution. See Section 3, EMERGENCY PROCEDURES.
April, 2008
Document Date
3A-21
3A-21
sec03a.fm Page 22 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
NOTE
When the TAWS Page is not displayed,
and an EDR caution is issued, a pop-up
window is displayed in the lower right corner of the MFD displaying a yellow [SINK
RATE].
The following procedure should be followed if the above caution occurs.
• Level wings and reduce rate of descent until visual and aural
alerts cease.
NEGATIVE CLIMB RATE AFTER TAKEOFF [TERRAIN]
Voice Caution Alert: “Don't Sink”
A Voice caution alert and annunciator are provided to alert the
pilot that the airplane is losing altitude after takeoff. The cautions will be provided whether or not the TAWS system is
enabled. The alerts are only active if all of the following conditions are met:
• The takeoff phase of flight. (The system must have
detected an actual takeoff. Alerts are not provided for goarounds or missed approaches.)
• The height above the terrain is less than 700 feet.
• The airplane is less than 2 nm from the departure airport.
• The airplane heading is less than 110 from the departure
runway heading.
The following procedure should be followed if the above caution occurs.
• Level wings and immediately establish a positive rate of
climb.
3A-22
3A - 22
April, 2008
Document Date
sec03a.fm Page 23 Thursday, May 1, 2008 2:18 PM
Model G58
Section 3A
Abnormal Procedures
PREMATURE DESCENT DURING AN APPROACH
[TERRAIN]
Voice Caution Alert: “Too Low, Terrain”
A Voice caution alert and annunciator are provided to alert the
pilot that the airplane has descended too low for the particular
kind of approach; e.g. a visual approach (no approach loaded),
a non-precision approach, or an ILS approach.
The following procedure should be followed if the preceding
caution occurs.
• Initiate positive action to fly the airplane up to the glide path
to cancel the alerts.
DITCHING, OFF-AIRPORT LANDING, OR FLYING
VFR AROUND UNIQUE TERRAIN
Inhibit the visual and voice alerts of the TAWS system using
the following procedure. The terrain page will remain operational on the MFD and the GPWS functions will still be operational.
On the MFD:
1. Large FMS Knob. . . . . . . . .SELECT THE MAP GROUP
2. Small FMS Knob . . . . . . . . . SELECT THE TAWS PAGE
3. Press the MENU Key
4. Small FMS Knob . . . . . . . . . . . . SELECT “INHIB TAWS”
5. Press ENT
ALTIMETER DISAGREEMENT
If a significant difference is noted between the altitude displayed on the PFD and the standby altimeter, the GPS ALT
displayed on the MFD may be used as a third altitude source
to help resolve the discrepancy.
April, 2008
Document Date
3A-23
3A-23
sec03a.fm Page 24 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
The GPS ALT displayed on the MFD is a
calculated value and must not be considered as a primary source of altitude. The
GPS ALT and the altitude displayed on the
PFD may differ by 100 feet or more. Its use
is not approved for navigation.
ADDITIONAL CAUTION ANNUNCIATIONS
Illumination of a CAUTION annunciation and its associated
single aural tone:
1. ALERTS softkey . . . . . . . . . . . . . . . . . . . . . . . . . PRESS
(displays message in alerts
window)
NOTE
On some software versions exceeding a
specific engine or electrical tolerance will
cause the engine display to automatically
revert to the default ENGINE page display.
Hence, the following caution annunciations
are not required. Other software versions
require the pilot to manually select the
ENGINE page display and necessitate
additional caution annunciations. It remains
the pilot’s responsibility to monitor and
operate the airplane within the specified
limits.
2. ENGINE softkey . . . . . . . . . . . . . . . . . . . . . . . . . PRESS
(As required to return to primary engine page.)
3. Appropriate action . . . . . . . . . . . . . . . . . .AS REQUIRED
3A-24
3A - 24
April, 2008
Document Date
sec03a.fm Page 25 Thursday, May 1, 2008 2:18 PM
Model G58
Section 3A
Abnormal Procedures
OIL PRESSURE LO [OIL PRESS LO]
1. Oil Pressure . . . . . . . . . . . . . . . . . . . CONFIRM < 30 psi
If confirmed:
2. Consider ENGINE FAILURE AFTER LIFT-OFF AND IN
FLIGHT procedures to secure affected engine.
or
3. Land at the nearest suitable airport using the minimum
power required.
FUEL QUANTITY LOW [FUEL QTY LO]
1. Fuel Indicators . . . . . . . . . . . . . . . . . . . .CONFIRM QTY
2. Power . . . . . . . . . . . . . . . . . . . REDUCE AS REQUIRED
3. Mixture . . . . . . . . . . . . . . . . . . . . .LEAN AS REQUIRED
4. Crossfeed (if fuel imbalance > 15 gals) . AS REQUIRED
5. Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Do not take off if the fuel quantity display
indicates in the yellow band or with less
than 13 gallons in each wing fuel system.
ALTERNATOR LOAD HIGH [ALT LOAD]
1. Alternator load (affected side). . CONFIRM > 100 AMPS
2. Non-essential electrical equipment . . . . . . . . . . . . . .OFF
If load does not decrease below 100 amps and annunciation
remains displayed:
3. Alternator (affected side) . . . . . . . . . . . . . . . . . . . . .OFF
4. Bus Voltage (affected side). . . . . . . . . . . . . . . MONITOR
(reads battery voltage)
April, 2008
Document Date
3A-25
3A-25
sec03a.fm Page 26 Thursday, May 1, 2008 2:18 PM
Section 3A
Abnormal Procedures
Model G58
Depending on the cause of the Bus Overload condition, battery operating time on
the affected side may be less than 30 minutes. When power to the Left Bus is only
being supplied by the battery, be prepared
to use standby instruments.
5. Land at the nearest suitable airport.
SURFACE DEICE AIR PUMP [L AIR PUMP] or [R AIR
PUMP]
1. Surface Deice Boots . . . . . . . . . . .CHECK OPERATION
2. Deice pressure gage:
a. While boots are inflating . . . . . . . . . . . . . . 9 to 20 PSI
b. When boots are fully inflated . . . . . 15 PSI MINIMUM
If boots operate normally:
3. Operations in icing conditions at pilot’s discretion; avoid,
if possible.
Otherwise:
4. Do not enter or continue operations in icing conditions.
3A-26
3A - 26
April, 2008
Document Date
Was this manual useful for you? yes no
Thank you for your participation!

* Your assessment is very important for improving the work of artificial intelligence, which forms the content of this project

Download PDF

advertising