S-TEC Fifty Five X Autopilot Pilot’s Operating Handbook

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System Fifty Five X

Autopilot

Pilot’s Operating

Handbook

SYS FIFTY FIVE X POH

List of Effective Pages

Record of Revisions

* Asterisk indicates pages changed, added, or deleted by

revision.

Edition Number

1 st

Edition

2 nd

Edition

2nd Ed: May 31, 2002

Retain this record in front of handbook. Upon receipt of a revision, insert changes and complete table below.

Publication Date Insertion Date/Initials

November 8, 2000

May 31, 2002 i

SYS FIFTY FIVE X POH

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Section Page

Editons.....................................................................................................................i

Table of Contents..................................................................................................iii

List of Figures.......................................................................................................v

1.0

Introduction.........................................................................................................1-3

2.0

System Fifty Five X Block Diagram................................................................2-3

3.0

Autopilot Overview............................................................................................3-3

4.0

Procedures.........................................................................................................4-3

4.1

Pre-flight Procedures..........................................................................4-3

4.1.1

Autopilot Self Test...................................................................4-3

4.1.2

Pre-flight Test...........................................................................4-4

4.1.3

Manual Electric Trim Test......................................................4-6

4.2

Normal Operating Procedures..........................................................4-7

4.2.1

Heading Mode.........................................................................4-7

4.2.2

NAV Intercept and Tracking...................................................4-7

4.2.2.1 Pilot Selectable Intercept Angles (DG or HSI)...................4-9

4.2.3

Approach (APR) Mode Switch..............................................4-10

4.2.4

GPS Steering (GPSS) Mode................................................4-10

4.2.5

GPSS Operating Procedures..............................................4-11

4.2.5.1 Pilot Selectable Intercept Angles (GPSS) Mode..............4-11

4.2.6

Standard GPS Approach......................................................4-12

4.2.7

GPS Steering (GPSS) Approach........................................4-13

4.2.8

Reverse (REV) Mode.............................................................4-13

4.2.9

Vertical Speed (VS)...............................................................4-13

4.2.10 Altitude (ALT)............................................................................4-14

4.2.11

Control Wheel Steering (CWS)..........................................4-15

4.2.12 Pitch Trim Indicator...............................................................4-16

4.2.13 Autotrim..................................................................................4-16

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(Cont'd)

Section Page

4.3

Approach Procedures.........................................................................4-19

4.3.1

Procedure Turn Localizer Approach (Standard DG)......4-19

4.3.2

Straight-In Localizer Intercept & Tracking

(Standard DG)........................................................................4-21

4.3.3

Pilot Selectable Intercept Angles (Standard DG)...........4-22

4.3.4

Procedure Turn Localizer Approach (Optional HSI)......4-22

4.3.5

Localizer Intercept & Tracking (Optional HSI).................4-25

4.3.6

Pilot Selectable Intercept Angles (Optional HSI).............4-27

4.3.7

Glide-slope Intercept & Tracking.......................................4-27

4.3.8

Manual Arm / Automatic Capture........................................4-30

4.3.9

Procedure Turn Localizer Back-Course Approach

(Optional HSI)........................................................................4-31

4.3.10 Localizer Back Course Intercept and Tracking

(Optional HSI).......................................................................4-34

4.4

System Failure and Caution Annunciations..................................4-37

4.5

Autopilot Disconnect...........................................................................4-38

4.6

Yaw Damper (If Installed)...................................................................4-38

4.6.1

Yaw Damper Controls.........................................................4-38

4.6.2

Yaw Damper Preflight Procedures...................................4-39

4.6.3

Yaw Damper Inflight Procedures.......................................4-39

4.7

Single-Cue Flight Director Operation (Optional)..........................4-40

5.0

System Fifty Five X Specifications................................................................5-3

6.0

Glossary..............................................................................................................6-3

iv 2nd Ed: May 31, 2002

FIGURE

4.3.3.1

4.3.4.1

4.3.5.1

4.3.7.1

4.3.7.2

4.3.9.1

4.3.9.2

SYS FIFTY FIVE X POH

LIST OF FIGURES

Page

Procedure Turn Localizer Approach & Track

(Standard DG)......................................................................................4-20

Procedure Turn Localizer Approach & Tracking (Opt HSI)............4-24

Straight-In Localizer Approach & Tracking (Opt HSI)....................4-26

Glide-slope Intercept & Track.............................................................4-28

Procedure Turn for Glide-slope Approach......................................4-29

Back-Course Procedure Turn (HSI).................................................4-33

Back-Course Straight-In Approach (Opt HSI).................................4-36

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SECTION 1 INTRODUCTION

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1.0

Introduction

The primary purpose of the System Fifty Five X Pilot Operating Handbook

(POH) is to provide pilots with step-by-step functional Preflight and In-

Flight Operating Procedures for the installed system.

This System Fifty Five X Pilot's Operating Handbook, part number 87109, dated 31 May 2002 or later, must be carried in the aircraft and be made available to the pilot while in flight.

NOTICE

The information in this manual must be used in conjuction with the FAA approved Airplane Flight Manual Supplement

(AFMS), Pilot Operating Handbook Supplement (POHS), or

Supplemental Flight Manual (SFM). Refer to the specific AFMS,

POHS, or SFM for your aircraft's specific information and emergency operating procedures.

If the autopilot is to be used during Instrument Flight Rules

(IFR) operations, we recommend that you develop a thorough understanding of the autopilot system, its functions and characteristics in Visual Meteorological Conditions (VMC).

Accomplish this before undertaking an IFR flight.

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SECTION 2 BLOCK DIAGRAM

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2.0

Block Diagram

SYSTE M FIFTY FIV E X B LO C K D IA G R A M

R E M O TE A NN U NC IATO R

(O P TIO N A L)

F LIG H T D IR E CTO R

(O P TIO N A L)

A UTO P ILO T D IS CO NN E C T/

T RIM IN TE R RU P T S W IT C H

A/P DIS C

T RIM INT R PT

CW S

A LT ITU D E S E LE C TO R/A LE R TE R

(O P TIO N A L)

H S I

(O P TIO N A L)

C O NT R O L W H E E L

S T E E RIN G S W IT CH

S A -200 A LTIT UD E P R E -S E LE C T

(O P TIO N A L)

H D G

N AV

A P R

IFT Y

IV E

R E V T R IM A LT G S V S

VS x 100

A BS O LU TE P R E S S U RE

T RA NS D U C E R

S Y S T E M FIFT Y FIV E X

P R O G R A M M E R / C O M P UT E R

A /P M A S T E R

S W IT CH

T UR N CO O RD IN ATO R

TRIM

ON FAIL

* T RIM

M O N ITO R

S W IT CH

R O LL S E RV O

P ITC H S E RV O

T RIM S E R V O

(O P TIO N A L)

T RIM CO M M A N D

S W IT CH

* N O T AVA ILA BL E O N A L L A IR CR A FT

YAW D A M P E R

(O P TIO N A L)

Fig. 2-1. System Fifty Five X Block Diagram

YAW S E RV O

(O P TIO N A L)

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SECTION 3 AUTOPILOT OVERVIEW

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3.0 Autopilot Overview

3.1 System Fifty Five X Autopilot Overview

The System Fifty Five X is a rate autopilot that controls the roll and pitch axes of the aircraft. The autopilot's main function is to convert pilot commands to logic signals for the roll and pitch computers. As the pilot enters the desired mode by pressing the appropriate mode selector switch, the computer acknowledges the mode, causing the appropriate annunciator to illuminate.

The Roll Computer receives select input signals from the Directional Gyro

(DG) or Horizontal Situation Indicator (HSI), Very High Frequency Omnidirectional Radio (VOR), Localizer (LOC) or Global Positioning System (GPS),

Deviation Indicators, and the Turn Coordinator. It then computes roll servo commands for stabilization, turns, navigation intercepts, and tracking.

Sensing for trim annunciation or automatic elevator trim is provided by the pitch servo. Drive for the elevator trim servo is provided by the pitch computer.

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SECTION 4 PROCEDURES

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4.0

Procedures

4.1

Pre-Flight Procedures

4.1.1 Autopilot Self-Test

NOTE:

The System Fifty Five X incorporates a SELF-TEST that requires a 100% pass rate before the autopilot can be engaged. To perform the test, aircraft DC electrical power must be supplied to the autopilot.

1. Autopilot Master switch..........................................................Set to FD / AP

—Observe that all segments of the Programmer / Computer display and annunciators illuminate for 5 seconds during test.

—Satisfactory completion of the SELF-TEST is indicated when the Ready

(RDY) annunciator remains on at the end of the 5-second self-test.

—Should a fault be detected, the FAIL annunciator will remain on at the

conclusion of the self-test and the autopilot will not operate.

NOTE:

If the autopilot detects the Turn Coordinator rotor speed as low or not turning, the display will remain blank and the autopilot will remain inoperable. In cold weather, the Turn

Coordinator may take longer to attain proper operating speed due to temperature sensitivity. If either condition occurs, consult your dealer before use of the autopilot is attempted.

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4.1.2 Pre-flight Test

Trim Master (ON / OFF) Switch....................................................................ON

HDG and VS switches......................................................PRESS / RELEASE

—Ensure that HDG and VS illuminates on the Fifty Five X annunciator.

Control Wheel Steering (CWS) switch...........................PRESS / RELEASE

—Verify that CWS and VS are highlighted on the annunciator.

4-4

CWS switch...............................................................................PRESS / HOLD

—Verify that the autopilot servos have dis-engaged and the controls are free.

CWS switch.................................................................................. RELEASE

—Servos should re-engage.

VS Knob........................................................................................ROTATE CW

—Pitch control should move slowly out (pilot may have to assist a heavy yoke).

VS Knob......................................................................................ROTATE CCW

—Pitch control should move slowly in.

A/P DISC Trim Interrupt Switch (on control yoke)..............................PRESS

—Verify the autopilot disconnects.

HDG Mode...........................................................................................ENGAGE

10. DG or HSI HDG bug.................................................................MOVE LT / RT

—Roll control should follow the HDG bug.

11. Altitude Hold (ALT) button......................................................................PUSH

—Slowly pull out (nose up) on the pitch control. Autotrim should run nose down with TRIM flashing on the remote annunciator and the autopilot computer / programmer after approximately 3 seconds.

—Slowly move pitch control foward (nose down). After 3 seconds, autotrim should move nose up with TRIM flashing on the remote annunciator and the autopilot computer / programmer after approximately 3 seconds.

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12. Trim Master (ON / OFF) Switch.................................................................OFF

NOTE:

If HSI equipped, center the course arrow under the lubber line and push the NAV button. Move the course arrow on the HSI left then right. Roll control should follow the course arrow. Channel a valid VOR signal and move course arrow just enough to deflect the left / right needle

1 or 2 dots. Roll control should follow the Course

Deviation Indicator (CDI) left / right needle during the test. ( This test is only valid if the left / right needle is centered with the course arrow under the lubber line).

NOTE:

If DG equipped, center the HDG bug under the lubber line. Channel a valid VOR signal. Move the OBS to cause left / right CDI needle deflection. The roll control should follow the left / right needle movement.

13. REV Mode button.....................................................................................PUSH

—Roll control should respond opposite to the course arrow and

CDI left / right needle inputs.

14. Autopilot Master Switch (If FD Equipped)...............................SELECT FD

—Note the roll, pitch and trim servos are disengaged. The steering

bar should be in view on the attitude indicator.

15. HDG Mode...........................................................................................ENGAGE

—MOVE HDG bug 45 degrees left. The roll steering bar should slowly

indicate a left steering command. Repeat the same test for the

right side.

16. VS Mode.............................................................................................ENGAGE

—SELECT 1500 FPM rate of climb. Note the pitch steering bar moves

slowly up. Repeat the same test for the down direction.

17. Autopilot Master Switch......................................................SELECT FD / AP

—The servos should re-engage.

18. Trim Master (ON / OFF) Switch....................................................................ON

19. Manual Electric Trim Command Switch.....................MOVE FWD or AFT

—The autopilot should disconnect.

NOTE:

The Manual Electric Trim Command Switch will disconnect the autopilot only if there is a Pitch Mode engaged.

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4.1.3 Manual Electric Trim Test

1. Trim Master (ON / OFF) switch..................................................................ON

—Move each segment of the Manual Electric Trim Command Switch

FWD and AFT. Trim should not run.

—Move both segments of the Trim Command switch FWD. Trim should run nose down.

—Move both segments of the Trim Command switch AFT. Trim should run nose up.

—Re-trim aircraft for takeoff and check controls for freedom of movement. Be sure the autopilot and trim servos are dis-engaged.

NOTE:

If the aircraft is equipped with Optional Yaw Damper, reference the Yaw Damper Section of this POH for the

Pre-flight check.

NOTE:

If either the Manual Electric Trim or Auto-trim fails any portion of the Pre-flight Test, move the Trim Master

Switch to OFF.

DO NOT USE THE ELECTRIC TRIM UNTIL THE FAULT

IS CORRECTED.

With the Trim Master switch OFF, the Autopilot Trim

Indicators and Audio Warning are activated. If the electric trim fails, or has an in-flight power failure, the system automatically reverts to an out-of-trim annunciation and audio warning.

SHOULD THIS OCCUR, MOVE THE TRIM MASTER

SWITCH TO OFF, AND REVERT TO MANUAL

AIRCRAFT TRIM UNTIL THE FAULT IS CORRECTED.

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4.2

Normal Operating Procedures

4.2.1 Heading Mode

Set the heading bug on the DG or HSI to the desired heading, and press the HDG button. The HDG annunciator will illuminate. New headings can be selected simply by repositioning the heading bug.

NOTE:

When operating in the HDG Mode, the system is not coupled to any navigation aid. It merely flies the heading bug. It will be necessary to monitor navigation instruments for course deviation due to wind drift and wind correction angles.

4.2.2 NAV Intercept and Tracking

If your aircraft is equipped with an HSI, your S-TEC autopilot will receive both left / right deviation and course information. With an HSI, the heading bug is not used during tracking. To intercept and track a VOR or GPS course, select the desired course with the HSI Course Pointer and engage the NAV Mode.

If your aircraft is equipped with a DG, the HDG bug must be set to the desired course before engaging NAV Mode. The HDG bug provides course information when using the NAV Modes.

If the course needle is at full-scale deviaton, the autopilot will establish a

! intercept angle. As the aircraft approaches the selected course, the autopilot senses the closure rate and gradually shallows the intercept angle. The point at which this turn begins is variable, depending on the aircraft position and closure rate to the course. However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

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During the intercept sequence, the system operates in maxium gain and sensitivity to needle position and motion and can command the aircraft at 90% of the standard rate turn. When the selected course is intercepted, and the needle is centered, indicating course capture, initiation of the tracking gain program is automatic.

If the aircraft is equipped with an optional remote annunciator, the gain level will be indicated. NAV and CAP (Capture) Modes will be annunciated.

The high sensitivity level (CAP) is maintained for about 15 seconds while the wind correction angle is established. After 15 seconds, the maximum turn rate is then reduced to 45% of the standard rate turn (CAP, SOFT).

The optional remote annunciator will indicate NAV, CAP, and SOFT.

Approximately 60 seconds later, the turn rate maximum is reduced to

15%standard rate and the lowest level of sensitivity is acheived (SOFT).

At this point, the optional remote annunciator will indicate NAV and

SOFT. The CAP annunciator will extinguish.

4-8

If the course pointer, on an HSI or HDG bug on a DG, is within 5

of center and needle deflection is less than 10%, the computer will immediately establish this lowest sensitivity when NAV is selected.

This condition provides low activity levels during station passage when

VOR signals are erratic. In other words, it ignores short-term needle excursions.

The system includes a course deviation monitor. If the aircraft strays off course or LOC centerline by 50% needle deflection, the NAV annunciator flashes a warning. It flashes at station passage because of short-term needle excursion, and because the NAV signal is inadequate. It also flashes when the NAV flag is displayed. When this occurs, the FAIL annunciator will illuminate.

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When operating in the NAV / SOFT Mode and a needle deflection of 50% or more is experienced for 1.5 minutes, the gain program will switch to

NAV/CAP/SOFT, increasing sensitivity and authority to reestablish the aircraft on course.

When a course change of 10

! or more is required at an enroute VOR, select the new course using the course pointer (if HSI equipped or HDG bug if DG equipped). The autopilot will acknowledge the changes and automatically adjust for intercept.

4.2.2.1 Pilot Selectable Intercept Angles (DG or HSI)

The pilot may select an angle of intercept less than the standard 45

Simply place the heading bug to the desired heading to be used for the course intercept and push both HDG and NAV switches simultaneously.

Both HDG and NAV will be annunciated.

The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept. At the time the on course turn begins, the HDG annunciator will extinguish. If using a DG, it is imperative that the pilot set the HDG bug to the selected course at this time.

NOTE:

Intercept angles greater than 45

! usually result in some course overshoot depending on the distance of the aircraft from the station and aircraft speed. Therefore, angles greater than 45 ! are not recommended.

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4.2.3

Approach (APR) Mode Switch

The APR Mode provides increased sensitivity for VOR or GPS approaches.

The pilot may also select this mode if increased sensitivity is desired for enroute NAV tracking. To engage this mode press the APR switch on the

Programmer / Computer. NAV and APR will be displayed on the annunciator.

If the aircraft is equipped with a remote annunciator NAV, APR, CAP, and SOFT will be displayed.

4.2.4

GPS Steering (GPSS) Mode

NOTE:

The Autopilot is equipped with a GPS Steering (GPSS)

Mode that can be used for normal GPS course tracking or for GPS approach. In GPSS Mode, the heading bug and / or course arrow position has no effect on the autopilot and may be preset for the missed approach heading, etc..., as desired.

NOTE:

When operating in the GPSS Mode and properly coupled to the GPS receiver, the autopilot will automatically steer the aircraft around the GPS approach without further heading or course inputs required by the pilot.

NOTE:

The autopilot will track only those segments of the approach contained in the GPS Navigator database.

Procedure turns and holding patterns are not usually contained in the data base.

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4.2.5

GPSS Operating Procedures

1. To enter the GPSS Mode, push the NAV button twice.

2. The autopilot will accept steering commands from the GPS unit and will fly the lateral segments of the approach without any further input from the pilot.

3. When in the GPSS Mode, NAV and GPSS will be annunciated.

4. To delete the GPSS function, push the NAV button again or select HDG or CWS Mode.

NOTE:

Turns while in GPSS Mode can exceed the standard rate by 20 to 30%.

4.2.5.1 Pilot Selectable Intercept Angles (GPSS Mode)

The autopilot may also be programmed for Pilot Selectable Intercept Angles while using the GPSS Mode. Simply, push and hold the HDG button, then push the NAV button twice. HDG, NAV, and GPSS will be displayed on the annunciator.

As the aircraft nears the on-course turn point, the HDG annunciator will extinguish.

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NOTE:

Some Fifty Five X Autopilot installations inhibit the use of the GPSS mode when the NAV source selector switch on the GPS navigator is in the VOR / LOC position or the external NAV selector switch (as appropriate) is in

NAV position. To determine how your system operates conduct the following pre-flight test:

1. Provide power to the autopilot.

2. Observe a ready (RDY) indication on the annunciator.

3. Select VOR / LOC on the GPS navigator or select the NAV Mode on the external NAV selector switch (as appropriate). Channel an invalid VOR frequency.

4. Press the autopilot NAV button twice. If flashing NAV and steady FAIL is annunciated, the system is inhibited from entering the GPSS Mode with the NAV source selector switch in the VOR / LOC or NAV position.

If flashing NAV, GPSS, and steady FAIL is annunciated, the system is not inhibited from entering the GPSS Mode anytime the NAV button is pressed twice. The following CAUTION will apply to those systems.

CAUTION

With the autopilot in the GPSS Mode, NAV and GPSS will be annunciated. In this mode, guidance is received directly from the GPS Navigator regardless of what is displayed on the

NAV indicators (HSI, CDI...). If the GPS Navigator has a valid flight plan active and the autopilot is in the GPSS Mode, the autopilot will follow that flight plan. If no flight plan is active, the autopilot will annunciate a flashing GPSS and FAIL will be steady. The aircraft will continue straight, wings level .

NOTE:

For all autopilot navigation operations not utilizing GPSS, ensure that GPSS is NOT annunciated.

4.2.6 Standard GPS Approach

NOTE:

The autopilot is capable of conducting non-precision

GPS approaches when coupled to a valid GPS signal.

These are conducted in the same manner as a VOR

Approach.

1. When the autopilot is interfaced with an HSI or DG it is capable of intercepting and tracking a valid GPS course.

2. Place the Course Pointer on the HSI or HDG bug on the DG on the indicated bearing to the waypoint.

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3. Select the APR Mode. The autopilot will intercept and track the GPS signal.

4. If desired, the pilot can use the pilot selectable intercept angle procedure as described on preceeding pages. (Ref. 4.2.5.1 Pilot Selectable

Intercept Angles).

5. For procedure turns, the pilot must select the HDG Mode and fly the aircraft through the procedure turn with the heading bug.

6. Once established on the INBOUND course to the Final Approach Fix

(FAF), select the APR Mode.

4.2.7. GPS Steering (GPSS) Approach

NOTE:

When operating in the GPSS Mode, the autopilot requires no further inputs from the HSI or DG (i.e.

heading or course changes) as the approach progresses.

1. Program the desired approach into the GPS Navigator.

2. Press the autopilot NAV button twice to access the GPSS Mode. Verify that GPSS is displayed on the autopilot annunciator panel.

3. Verify the aircraft begins a turn toward the Initial Approach Fix (IAF) or that segment of the approach that transitions to the selected approach.

4. Monitor the autopilot as it moves around the approach using vertical speed and altitude hold to fly the vertical elements of the approach.

5. Select HDG to accomplish a procedure turn.

6. Engage the GPSS again to complete the approach.

4.2.8 Reverse (REV) Mode

The Reverse Mode provides roll commands for intercept and tracking the localizer back course inbound or localizer front course outbound.

4.2.9 Vertical Speed (VS)

To engage vertical speed, the autopilot roll axis must be engaged.

Selecting HDG Mode or any roll mode will satisfy this requirement.

With any roll mode engaged, the pilot may select VS Mode by pressing the VS Mode select switch. The autopilot will synchronize with the aircraft's vertical speed at the time the mode is selected and the corresponding vertical speed will be indicated in the Programmer / Computer display.

Vertical speed may now be modified in 100 ft. increments by rotating the

VS knob clockwise or counter-clockwise.

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The + (positive) symbol annunciation indicates a veritcal speed climb selection. Clockwise rotation of the VS knob increases the rate of climb and counter-clockwise rotation decreases the rate of climb to 0. The

-

(negative) symbol annuncation indicates a vertical speed descent selection. Counter-clockwise rotation of the VS knob increases the rate of descent and clockwise rotation decreases the rate of descent to 0.

Maximum selectable VS limits are # 1600 feet-per-minute (FPM) in most aircraft (see the AFMS for your installation).

NOTE:

If the VS Mode annunciator flashes while in the VS

Mode, this is an indication of excessive error between actual vertical speed compared to selected vertical speed (usually in a climb) and the pilot should adjust aircraft power or reduce the vertical speed command as appropriate.

4.2.10 Altitude (ALT)

The Altitude Mode, ALT, may be engaged with any roll mode displayed by pressing the ALT Mode switch. The aircraft will maintain the pressure altitude present at the time of the ALT Mode selection.

Altitude Correction for enroute barometic pressure changes may be made while in ALT Mode by rotation of the VS knob. Each "click" will change the altitude by 20 ft. The maximum altitude correction is # 360 ft. Corrections in excess of # 360 ft. will require selecting the VS Mode and climbing or descending to the new altitude and re-engaging ALT Mode.

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4.2.11 Control Wheel Steering

The System Fifty Five X Autopilot is equipped with a Control Wheel steering

(CWS) Mode of operation that is entered by use of the CWS switch located on the control wheel. In order to use the mode, both a roll and pitch axis mode must be engaged.

Use of the CWS Mode allows the pilot to manually maneuver the aircraft without disconnecting the autopilot. Examples of its use include maneuvering to avoid traffic, placing the aircraft in a specific bank or climbing or descending without having to disconnect the autopilot.

Depress and hold the Control Wheel Steering Switch located on the aircraft's control wheel. The CWS and VS Modes will annunciate.

Maneuver the aircraft as desired.

NOTE:

Aircraft vertical speed (times 100) will be displayed in the Programmer / Computer Annunciator window directly above the VS selector knob.

Example:

+ 6 equals 600 Feet Per Minute (FPM) rate of climb.

If desiring a specfic attitude, press CWS switch. Allow the aircraft to stabilize in the desired attitude for 2 to 3 seconds, release the Control

Wheel Steering switch and the autopilot roll and pitch servos will engage and synchronize with the aircraft's turn rate and vertical speed.

NOTE:

If the aircraft roll angle is greater than a standard rate turn when the CWS switch is released, the bank angle will be reduced to produce 90% of a standard rate turn as a maximum.

From the CWS Mode, the pilot may select other modes such as HDG,

NAV, ALT, or may modify the present vertical speed using the VS knob.

The pilot may re-enter the CWS Mode at any time by simply depressing the CWS switch on the control wheel, positioning the aircraft in the desired roll and pitch attitude and releasing the CWS switch.

NOTE:

When in the CWS Mode, the autopilot is not referencing any specific heading or attitude but is simply maintaining the approximate aircraft attitude that existed upon release of the CWS switch.

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4.2.12 Pitch Trim Indicator

If automatic trim has failed or is turned off, a sensor in the System Fifty

Five X Autopilot pitch servo detects out-of-trim elevator loads. When such forces exceed a preset level and time delay, TRIM will annunciate on the

Programmer / Computer with either the up or down symbol annunciated to indicate the direction elevator trim is required. In addition, an audible warning tone will sound 5 for seconds (this is same audible beeping tone emitted when the autopilot is disconnected but at a slower rate).

The annunciation will be steady for about 5 seconds, then flash until proper trim conditions have been met. The pilot will be required to manually trim the aircraft until the trim indicator is extinguished.

NOTE:

If trim is annunciated and the pilot disengages the autopilot, there will be residual out of trim force at the control wheel. Be alert if the autopilot is disengaged while TRIM is annunciated.

4.2.13 Autotrim

With the autotrim functioning normally, the aircraft elevator trim will be maintained automatically when the Trim Master switch is on and a pitch mode is activated.

When the elevator trim is in motion, TRIM and the up or down symbol will annunciate indicating trim in motion and the direction of travel. Should the trim continue to run in excess of 7 seconds, these annunciations will flash.

4-16

If the trim master switch is OFF or a failure has occurred in the Autotrim, the system will automatically revert to "Pitch Trim Indicator" mode of operation.

NOTE:

Using the trim switch on the control wheel while the pitch axis of the autopilot is engaged, disconnects the autopilot.

The pilot is also provided with Manual Electric Trim when the autopilot is disengaged or if only a roll axis mode has been engaged.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

To use Manual Electric Trim, simply move the trim switch located on the aircraft's control wheel in the desired direction of trim. FWD for nose down or AFT for nose up. TRIM will be annunciated and will flash while the trim is in motion.

NOTE:

The S-TEC trim system is designed to accept any type of single failure (mechanical or electrical) without uncontrolled operation resulting. To ensure that no hidden failures have occurred, conduct a trim pre-flight check prior to every flight.

2nd Ed: May 31, 2002 4-17

SYS FIFTY FIVE X POH

Page Intentionally Blank

4-18 2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

4.3

Approach Procedures

4.3.1

Procedure Turn Localizer Approach (Standard DG)

Select the appropriate localizer frequency. Set the heading bug to the

OUTBOUND localizer course and engage the REV Mode to track the localizer front course outbound or back course inbound.

When a localizer is channeled and REV Mode is selected, the System

Fifty Five X will automatically execute high sensitivity gain for the approach and APR and REV will be annunciated.

If the course needle is at full-scale deviaton, the autopilot will establish a

intercept angle. As the aircraft approaches the localizer course, the autopilot senses the closure rate and gradually shallows the intercept angle. The point that this turn begins is variable depending on the aircraft position and closure rate to the course. However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

During the intercept sequence, the system operates in maximum gain and sensitivity to needle position and motion and can command the aircraft at 90% of the standard rate turn. When the localizer course is intercepted and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If the aircraft is equipped with the optional remote annunciator, the

APR, REV, and CAP Modes will be annunciated.

The high sensitivity level is maintained for about 15 seconds while wind correction angle is established. Turn rate maximum is then reduced to

45% of standard rate.

The optional remote annunciator will indicate APR, REV, CAP, and

SOFT.

2nd Ed: May 31, 2002 4-19

SYS FIFTY FIVE X POH

If the heading bug is within 5

of center and needle deflection is less than10%, the computer will immediately establish this sensitivity level when REV is selected.

Set the heading bug to the outbound procedure turn heading and select heading mode. At the appropriate time, in 90

increments, set the heading bug to the INBOUND procedure turn heading. Once established on the

INBOUND procedure turn heading, follow the localizer intercept and tracking procedures for standard DG noted below.

4.3.3.1 Procedure Turn Localizer Approach and Tracking with Standard D.G.

4-20

1. a. Tune navigation radio to LOC frequency.

b. Set heading bug to published outbound LOC heading.

c. Push REV Mode switch.

2. a. Set heading bug to outbound procedure turn heading.

b. Press HDG Mode switch.

3. a. In 90

increments, set heading bug to inbound procedure turn heading.

4. a. Set heading bug to inbound LOC heading.

b. Press NAV Mode switch. Autopilot will intercept and capture localizer course and track inbound to the airport.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

4.3.2

Straight-In Localizer Intercept and Tracking (Standard DG)

With the appropriate localizer frequency selected, set the heading bug to the INBOUND localizer course and engage the NAV mode to track the localizer front course inbound or back course outbound.

When a localizer is channeled and NAV Mode is selected, the System

Fifty Five X will automatically execute high sensitivity gain for the approach and activate the APR Mode. NAV and APR will be annunciated.

If the course needle is at full-scale deviation, the autopilot will establish a 45

intercept angle. As the aircraft approaches the localizer course, the autopilot senses the closure rate, and gradually shallows the intercept angle. The point at which this turn begins is variable, depending on the aircraft position and closure rate to the course. However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

During the intercept sequence, the system operates in maximum gain and sensitivity to needle position and motion and can command the aircraft at 90% of the standard rate turn. When the localizer course is intercepted, and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If the aircraft is equipped with the optional remote annunciator, the

NAV, APR, and CAP modes will be annunciated.

The high sensitivity level is maintained for about 15 seconds while wind correction angle is established. Turn rate maximum is then reduced to

45%of standard rate.

If the heading bug is within 5

of center and needle deflection is less than 10%, the computer will immediately establish this sensitivity level when NAV is selected.

The system also includes a course deviation monitor. If the aircraft strays off LOC centerline by 50% needle deflection, the NAV annunciator flashes a warning. It also flashes when the OBS NAV flag is displayed. When that occurs, the FAIL annunciation will illuminate.

2nd Ed: May 31, 2002 4-21

SYS FIFTY FIVE X POH

4.3.3

Pilot Selectable Intercept Angles (Standard DG)

The pilot may select an angle of intercept less than the standard 45

Place the heading bug on the DG to the desired heading used for the course intercept and simultaneously push both HDG and NAV switches.

HDG, NAV, and APR will be displayed on the autopilot annunciator.

The selected heading will now be flown until the autopilot computes that an on course turn must be made to minimize overshoot at the point of intercept. At the time the on-course turn begins, the HDG Mode will extinguish and you must move the heading bug to match the localizer

course.

NOTE:

Intercept angles greater than 45

! usually result in some course overshoot, depending on the distance from the station and aircraft speed. Therefore, angles greater than 45

are not recommended.

4.3.4

Procedure Turn Localizer Approach (Optional HSI)

Select the appropriate localizer frequency. Set the course pointer to the

INBOUND localizer course and engage the Reverse (REV) Mode to track the localizer front course outbound or back course inbound.

When a localizer is channeled and REV Mode is selected, the system will automatically execute high sensitivity gain for the approach and APR and

REV will be displayed on the autopilot annunciator.

4-22

If the course needle is at full-scale deviation, the autopilot will establish a 45

intercept angle. As the localizer course is approached, the autopilot senses the closure rate and gradually shallows the intercept angle. The inbound turning point is variable, depending on aircraft position and closure rate to the course. However, the turn will always begin between

100% (full-scale) needle deflection and 20% of full-scale.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

During the intercept sequence, the system operates at maximum gain and sensitivity to needle position and motion and can command the aircraft at 90% of the standard rate turn. When the localizer course is intercepted and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If the aircraft is equipped with an optional remote annunciator, the

APR, REV, and CAP modes will be annunciated.

The high sensitivity level is maintained for about 15 seconds while wind correction angle is established. Turn rate maximum is then reduced to

45% of standard rate.

The optional remote annunciator will indicate APR, REV, CAP and

SOFT.

If the course selector is within 5

of center and needle deflection is less than 10%, the computer will immediately establish this sensitivity level when REV is selected.

Set the heading bug to the outbound procedure turn heading and select heading mode. At the appropriate time, in 90

increments, set the heading bug to the inbound procedure turn heading. Once established on the inbound procedure turn heading, follow the straight-in localizer approach and tracking procedures for the optional HSI.

2nd Ed: May 31, 2002 4-23

SYS FIFTY FIVE X POH

4.3.4.1 Procedure Turn Localizer Approach and Tracking with Optional HSI

1. a. Tune navigation radio to LOC frequency.

b. Set published inbound LOC course heading with course pointer.

c. Push REV Mode switch.

2. a. Set heading bug to published outbound procedure turn heading.

b. Press HDG Mode switch.

3. a. In 90

increments, set heading bug to inbound procedure turn heading.

b. When established on inbound procedure turn heading, press NAV

Mode switch.

4. a. Once established in NAV Mode, set heading bug to the published missed approach heading. (If a missed approach is declared, at the Middle Marker (MM), disconnect the autopilot and stabilize the aircraft for the missed approach before engaging HDG and VS

Modes).

4-24 2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

4.3.5

Straight-In Localizer Intercept and Tracking (Optional HSI)

With the appropriate localizer frequency selected, set the course selector to the INBOUND localizer course and engage the NAV Mode to track the localizer front course inbound or back course outbound.

When a localizer is channeled and NAV Mode is selected, the system will automatically execute high sensitivity gain for the approach and activate the APR Mode with NAV and APR being annunciated.

If the course needle is at full-scale deviaton, the autopilot will establish a

intercept angle. As the aircraft approaches the localizer course, the autopilot senses the closure rate, and gradually shallows the intercept angle. The point that this turn begins is variable depending on the aircraft position and closure rate to the course. However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

During the intercept sequence, the system operates in maximum gain and sensitivity to needle position and motion and can command the aircraft at 90% of the standard rate turn. When the localizer is intercepted and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If the aircraft is equipped with the optional remote annunciator the

NAV, APR, and CAP modes will be annunciated.

The high sensitivity level is maintained for about 15 seconds while wind correction angle is established. Turn rate maximum is then reduced to

45% of standard rate.

The optional remote annunciator will indicate NAV, APR, CAP, and

SOFT.

2nd Ed: May 31, 2002 4-25

SYS FIFTY FIVE X POH

If the course selector is within 5 ! of center and needle deflection is less than 10%, the computer will immediately establish this sensitivity level when NAV is selected.

Since the heading bug is not used for the final approach segment, the pilot may elect to move the heading bug to the published missed approach heading for reference and use in the heading mode should a missed approach be necessary.

When this occurs, the FAIL anunciation will illuminate.

4.3.5.1

Straight-In Localizer Intercept and Tracking (Optional HSI)

1. a. Tune navigation radio to LOC frequency.

b. Set course pointer to published inbound LOC course heading.

c. Press NAV Mode switch.

2. a. Once NAV Mode is established, heading bug can be set to published missed approach heading.

b. At the Middle Marker, if a missed approach is declared, disconnect the autopilot and stabilize the aircraft for the missed approach before engaging HDG and VS Modes.

4.3.6

Pilot Selectable Intercept Angles (Optional HSI)

The pilot may select an angle of intercept less than the standard 45

Place the heading bug on the desired heading to be used for thecourse intercept and simultaneously push the HDG and NAV switches. HDG,

NAV, and APR will be displayed on the autopilot annunciator.

4-26 2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

NOTE:

Intercept angles greater than 45

usually result in some course overshoot, depending on the distance from the station and aircraft speed. Therefore, angles greater than 45

! are not recommend.

4.3.7

Glide-slope Intercept and Tracking (Software Version 4 and below)

To arm the automatic glide-slope (GS) capture function, the following conditions must be met: a. NAV receiver must be tuned to the appropriate frequency.

b. Glide-slope signal must be valid - no flag.

c. Autopilot must be in NAV / APR / ALT Modes.

d. Aircraft must be 60% or more below GS centerline during the approach to the intercept point, and within 50% needle deviation of the localizer centerline at the point of intercept - usually the Outer Maker.

Glide-slope arming will occur when the above conditions have existed for 10 seconds. Illumination of the GS annunciator will occur, indicating arming has been accomplished. The ALT annunciator remains on.

Glide-slope capture is indicated by extinguishing of the ALT annunciation.

2nd Ed: May 31, 2002 4-27

SYS FIFTY FIVE X POH

NOTE:

If vectored to intercept the localizer too close to the glideslope intercept point (resulting in less than 60% GS needle deviation when on course), the system will not automatically arm the glide-slope. Manual arming must be followed. (See page 4-30).

NOTE:

If the 55X computer is of software version 5 and above

(as evidenced by the number 5 in the right side of the display, when first powered up) the glideslope will arm when the CDI is from 20% to 100% up deflection for 1 second. The glideslope will capture immediately if the

CDI is within a window of 20% up needle to 10% down needle when the altitude hold button is pressed and all the other required conditions are met.

4.3.7.1

Glide-slope Intercept and Track

Flying the Glide-slope

When making an ILS approach, be sure to follow the published procedure for the approach you have been cleared to make. (Ref. 4.3.2 Localizer Intercept and

Tracking.)

Approach the glide-slope intercept point with the aircraft stabilized in the A l t i t u d e

Hold (ALT) Mode. If the aircraft requires approach flaps, lower the flaps to the proper position. (Refer to FAA / AFM supplement for flap use limitations.)

At glide-slope intercept, lower the landing gear (if applicable) and adjust power for the desired descent speed and published rate of descent. For best tracking results, make power adjustments in small, smooth increments to maintain the desired rate of descent and airspeed.

At the Missed Approach Point (MAP), Decision Height (DH), or the autopilot's minimum operating altitude (whichever is higher), disengage the autopilot to execute a manual landing or a Go-Around maneuver. If a Missed Approach is declared, the autopilot can be re-engaged after a stabilized climb has been established.

4-28 2nd Ed: May 31, 2002

4.3.7.2

Procedure Turn for Glide-slope Approach

SYS FIFTY FIVE X POH

1. a. Tune navigation radio to ILS frequency.

b. Follow the procedure(s) for LOC Approach Intercept and Tracking in this manual.

2. a. If a procedure turn is required, enter the procedure turn above the published altitude.

b. Upon entering the inbound procedure turn sequence, press the

VS Mode switch.

c. Rotate the VS SELECTOR knob to establish the desired rate of descent to reach approach altitude at completion of the procedure turn.

d. Upon reaching approach altitude, press the ALT Mode switch.

e. When the NAV Mode switch is pressed, and if the aircraft is below the glide-slope, the APR and GS annunciations will illuminate along with the ALT annunciation.

f. Upon capture of the glide-slope, the ALT annunciation will extinguish. (Ref. 4.3.7 Glide-slope Intercept and Track).

3. a. If a circling or straight-in approach to the ILS course is established, descend to approach altitude well in advance of reaching the

Outer Marker.

b. Upon reaching approach altitude, press the ALT Mode switch.

c. Upon capture of LOC course, NAV, APR, ALT, and GS will illuminate if all conditions for glide-slope operation are met (Ref. Glideslope Operation). This signifies automatic arming of the glideslope function.

d. Upon glide-slope capture, the ALT annunciation will extinguish, signifying GS capture.

NOTE:

If the final approach flown locates the aircraft above the glide-slope prior to reaching the Outer Marker, follow the procedure outlined in the text on Manual

Arming of the glide-slope.

2nd Ed: May 31, 2002 4-29

SYS FIFTY FIVE X POH

4.3.8

Manual Arm / Automatic Capture

If approach vectoring locates the aircraft above or too near the glideslope centerline at the intercept point (usually the outer marker), it becomes necessary to execute manual arming of the glideslope. This is done by pressing the

ALT switch once (if operating in the altitude hold mode) pressing the ALT switch twice (if operating in the VS Mode). Once capture is achieved, the

GS annunciation will illuminate and the ALT annunciation will extinguish.

The system includes a glide-slope deviation monitor. If the aircraft strays off glide-slope centerline by 50% needle deflection, the GS annunciator flashes a warning. It also flashes when the GS flag is displayed. When this occurs, the FAIL annunciation will illuminate.

NOTE:

If it becomes necessary to establish a holding pattern at the Outer Marker, automatic glide-slope arming can be disabled by pressing the APR switch a second time while in the NAV / APR Mode. The GS annunciator will flash and ALT will annunciate.

4-30

The GS annunciator will flash, and the ALT and DSBL annunciators will illuminate on the optional remote annunciator to indicate the GS Mode is disabled.

To re-establish GS arming, press the APR Mode switch again. The disable

(DSBL) annunciator will extinguish, the GS annunciator will cease to flash and remain steady. Re-arming will occur when all other required conditions stated have been met.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

CAUTION

If the aircraft is not equipped with the optional remote annunciator, the only indication that the glide-slope function

has been disabled is the flashing GS annunciator on the

autopilot programmer.

To fly the holding pattern, if inbound to the Outer Marker, press the APR switch twice to disable the glide-slope arming. When the Outer Marker or holding fix is reached, press the HDG switch and rotate the heading bug in the direction of the turn. It is best to select the reciprocal course in increments of 90

, rather than the full 180

When the outbound leg is completed, again rotate the HDG bug in the direction of the turn, in 90

increments, to re-establish the inbound course, and press the APR switch twice when localizer needle deflection is near 50% of full scale. If on this inbound leg you wish to rearm the glide-slope, press the APR switch once.

4.3.9

Procedure Turn Localizer Back-Course Approach (Optional HSI)

Select the appropriate localizer frequency. Set the course selector to the

INBOUND Localizer FRONT Course and engage the NAV Mode to track the localizer back course outbound or front course inbound. When a localizer is channeled and NAV Mode is selected, the System Fifty Five X will automatically execute high sensitivity gain for the approach and NAV and APR will be annnunciated.

If the course needle is at full-scale deviation, the autopilot will establish a 45

intercept angle. As the aircraft approaches the localizer course, the autopilot senses the closure rate and gradually shallows the intercept angle. The point at which this turn begins is variable depending on the aircraft position and closure rate to the course. However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

2nd Ed: May 31, 2002 4-31

SYS FIFTY FIVE X POH

During the intercept sequence, the system operates in maximum gain and sensitivity to needle positon and motion and can command the aircraft at 90% of the standard rate turn. When the localizer course i s intercepted and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If the aircraft is equipped with the optional remote annunciator, the

NAV, APR, and CAP modes will be displayed.

The high sensitivity level is maintained for about 15 seconds while the wind correction angle is established. Turn rate maximum is then reduced to 45% of standard rate.

The optional remote annunciator will indicate NAV, APR, CAP, and

SOFT.

If the course selector is within 5

! of center and needle deflection is less than 10%, the computer will immediately establish this sensitivity level when NAV is selected.

Set the heading bug to the outbound procedure turn heading and select

Heading Mode (HDG). At the appropriate time, in 90 ! increments, set the heading bug to the inbound procedure turn heading. Once established on the inbound procedure turn heading, follow the localizer back-course intercept and tracking procedures for optional HSI (as

noted in para. 4.3.9.1).

4-32 2nd Ed: May 31, 2002

4.3.9.1

Back-Course Procedure Turn (HSI)

SYS FIFTY FIVE X POH

REVerse Mode is used to track the front course outbound or the back course inbound to the airport.

The HSI Course Pointer MUST be set to the front course inbound heading.

1. a. Tune the navigation receiver to LOC frequency.

b. Set course pointer to published inbound LOC front course heading.

c. Press NAV Mode switch. The autopilot will capture and track back course outbound.

2. a. Set heading bug to the published outbound procedure turn heading.

b. Press the HDG Mode switch.

3. a. In 90

! increments, set heading bug to the inbound procedure turn heading.

b. Press REV Mode switch. Autopilot will intercept, capture, and track back course inbound to the airport.

2nd Ed: May 31, 2002 4-33

SYS FIFTY FIVE X POH

4.3.10

Localizer Back-Course Intercept and Tracking (Optional HSI)

With the appropriate localizer frequency selected, set the course pointer to the INBOUND Localizer FRONT Course and engage the REV Mode to track the localizer back course inbound or front course outbound.

When a localizer is channeled and REV Mode is selected, the System

Fifty Five X will automatically execute high sensitivity gain for the approach and automatically activate the APR Mode. APR and REV will be annunciated.

4-34

If the course needle is at full-scale deviation, the autopilot will establish a 45

! intercept angle. As the aircraft approaches the localizer course, the autopilot senses the closure rate and gradually shallows the intercept angle. The point at which this turn begins is variable depending on the aircraft position and closure rate to the course.

However, the turn will always begin between 100% (full-scale) needle deflection and 20% of full-scale.

During the intercept sequence, the system operates in maximum gain and sensitivity to needle position and motion and can command the aircraft to 90% of the standard rate turn. When the localizer course is intercepted and the needle is centered (indicating course capture), initiation of the tracking gain program is automatic.

If equipped with the optional remote annunciator, the APR, REV, and CAP modes will be annunciated.

The high sensitivity level is maintained for about 15 seconds while wind correction angle is established. Turn rate maximum is then reduced to 45% of standard rate.

The optional remote annunciator will indicate APR, REV, CAP, and

SOFT.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

If the course pointer is within 5

of center and needle deflection is less than 10%, the computer will immediately establish this sensitivity level when REV is selected.

Since the heading bug is not used for the final approach segment, the pilot may elect to move the heading bug to the published Missed

Approach Heading for reference and use in the Heading Mode, should a Missed Approach be necessary.

When this occurs, the FAIL annunciator will illuminate.

4.3.11

Pilot Selectable Intercept Angles (Optional HSI)

The pilot may select an angle of intercept less than the standard 45

This is done by placing the heading bug on the desired heading to be used for the course intercept while simultaneously pushing the HDG and REV switches. HDG, APR, and REV is annunciated.

The selected heading is flown until the autopilot computes that an on-course turn must be made to minimize overshoot at the point of intercept. When the on-course turn begins, HDG Mode will extinguish.

NOTE:

Intercept angles greater than 45

usually result in some course overshoot, depending on the distance from the station and aircraft speed. Therefore, angles greater than 45

are not recommended.

2nd Ed: May 31, 2002 4-35

SYS FIFTY FIVE X POH

4.3.9.2

Back Course Straight-In Approach (Optional HSI)

1. a. Tune navigation radio to LOC frequency.

b. Set Course Pointer to published inbound front course heading.

c. Press REV Mode switch.

d. Heading bug can be set to missed approach heading after course capture.

NOTE:

To establish a selected angle of intercept (dual mode intercept), on the back course, set the course pointer to the published inbound front course heading, and the heading bug to the desired heading to establish the selected angle intercept.

Press the HDG and REV Mode switches simultaneously. Upon capture of the back course, the autopilot automatically cancels HDG Mode and tracks the final approach course.

4-36 2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

4.4

System Failure and Caution Annunciations

The System Fifty Five X contains a number of automatic failure and caution annunciations to advise the pilot of operational problems. They are the following:

ANNUNCIATION

Flashing RDY for 5 seconds with audible tone

CONDITION

Indicates autopilot disconnect. All annunciations except

RDY are cleared.

ACTION

N/A

Flashing RDY with audible tone then extinguished

Flashing NAV,

REV, or APR

Turn Coordinator

Gyro Rotor Speed

Check Power to

Turn Coordinator.

low. Autopilot disconnects and

Conduct other system checks cannot be re-engaged as necessary.

Indicates off navigation course by 50% needle deviation or more.

Use HDG Mode until problem is identified.

Cross-check raw

NAV data, compass

HDG, radio operation.

FlashingNAV,

REV, or APR

Steady FAIL

Flashing VS

Indicates invalid

Radio Navigational

Signal.

Check NAV Radio for proper reception,

Use HDG Mode until problem is corrected.

Reduce VS command and / or adjust power as appropriate.

Flashing GS

Flashing GS, steady FAIL

Flashing VS and number (with 01282 only)

Flashing GS plus ALT

2nd Ed: May 31, 2002

Indicates excessive

Vertical Speed Error over selected VS

(usually climb).

Indicates Off glideslope centerline by 50% needle deviation or more.

Indicates invalid glide-slope radio navigation signal.

Indicates incorrect VS polarity for target altitude.

Indicates Manual glide-slope disable.

Check altitude, power. Add or reduce power as appropriate.

Disconnect autopilot and initiate go-around or missed approach as appropriate. Inform

Air Traffic Control.

Enter the appropriate

VS value

Re-enable by pushing

APR Mode Switch.

4-37

SYS FIFTY FIVE X POH

4.5

4.6

NOTE:

If any of the aforementioned failure annunciations occur at low altitude or during an actual instrument approach disengage the autopilot and execute a go-around or missed approach as appropriate. Inform ATC of the problem. Do not attempt to troubleshoot or otherwise identify the nature of the failure until a safe altitude and maneuvering area are reached or safe landing is executed.

Autopilot Disconnect

The autopilot can be disconnected by any of the following actions:

1. Turn the Autopilot Master switch OFF.

2. Press the Autopilot Disconnect / Trim Interrupt switch on the aircraft's control wheel.

3. Pull the aircraft's AUTOPILOT Circuit Breaker.

4. If the pitch axis of the autopilot is engaged, activate the Trim Command switch on the aircraft control wheel FWD or AFT.

Yaw Damper (Optional)

(Configuration may vary with installation)

4.6.1

Yaw Damper Controls

4-38

The Yaw Damper Master switch is a three-position (center OFF) switch. In theAUTO position, the Yaw Damper will engage any time an autopilot

Roll Mode (HDG, NAV, ect) is engaged. The Yaw Damper can also be used by itself when the autopilot is disengaged by by moving the switch to the YAW ON position. The Yaw Damper Trim Control is used to make small corrections after the Yaw Damper is engaged to keep the slip / skid ball centered.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

4.6.2 Yaw Damper Pre-flight Procedures

1. Place the Yaw Damper Master switch in the YAW AUTO position and engage the autopilot HDG Mode. Note that the Yaw Damper engages and causes increased pedal force.

2. Rotate the Yaw Damper Trim Control clockwise and note that the right rudder pedal moves slowly forward. Rotate the Yaw Damper Trim

Control counter-clockwise and note that the left rudder pedal moves forward. Re-center the trim control.

3. Press the Autopilot Disconnect Trim Interrupt switch on the control wheel and note that both the Autopilot and Yaw Damper disconnect.

Assure freedom of controls.

4. Yaw Damper must be OFF for takeoff and landing.

4.6.3 Yaw Damper In-flight Procedures

1. Trim the aircraft for the phase of flight being conducted (climb, cruise, descent) with the rudder trim.

2. Adjust the Yaw Damper Trim Control to center.

3. With the Yaw Damper Master switch in the AUTO position, engage the

Autopilot and note that Yaw Damper engages.

4. Make small Yaw Damper Trim adjustments as necessary to keep the slip / skid ball centered.

5. For Yaw Damper use with the Autopilot disengaged, move the Yaw

Damper Master switch to ON.

6. DISCONNECT the Yaw Damper for landing.

NOTE:

After making large power, configuration, or flight profile changes, it is advisable to disconnect the Yaw Damper to verify that the rudder is in trim then re-engage theYaw

Damper. The Yaw Damper will not trim the rudder automatically.

2nd Ed: May 31, 2002 4-39

SYS FIFTY FIVE X POH

4.7

Single-Cue Flight Director Operation (Optional)

This system, which integrates both the roll axis and pitch axis, offers synchronized display of the flight profile. It is automatically activated when the autopilot is engaged. A Flight Director provides a visual indication of how accurately the pilot or autopilot is tracking the commands of the active mode of operation.

4-40

Activation is indicated by the

FD annunciator on the remote annunciator.

A remote Parallax Adjustment is provided to change the height of the horizontal display to compensate for different seat heights and a remote switch allows flight director operation when the autopilot is not in use.

For proper flight technique, the system presentation requires the pilot to roll and pitch the aircraft toward the steering command bars until the delta-shaped reference is tucked into the steering command bars, indicating that commands have been satisfied. For example, if the display is up and left, the pilot would be required to establish a left turn, pitch-up attitude.

As bank angle and vertical speed approach the required amounts, bank angle and pitchup attitude are shallowed. When the delta reference and the steering bars are matched the commands have been met. Thereafter, it is necessary to maneuver the aircraft to keep the display elements matched in order to accurately fly the programmed modes.

Accurate flight director operation requires alertness by the pilot and monitoring of the movement of the display. Keeping it matched is quite simple. However, control inputs must be timely for accurate flight director following of the desired command.

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

For manually controlled flight by the flight director, place the FD/AP master switch in the "FD" position. This disables the autopilot servos, allowing the pilot to control the aircraft to the flight director commands.

To engage the autopilot without interruption, simply place the FD/AP master switch in the

"FD/AP" position.

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SECTION 5 SPECIFICATIONS

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Appendix A:

Specifications

System Requirements

Programmer/Computer

Power required

Weight

Dimensions

TSO

14/28 VDC

3.0 lbs.

6.25 X 1.50 X 10.60 in.

C9c

NOTE: Unit will operate with either 14 or 28 VDC input; however internal circuit board assemblies must be set up for a specific voltage.

Turn Coordinator

Power required:

Flag voltage detector operating limits:

Flag RPM detector operating limits:

Current Requirements

Weight:

Dimensions:

14/28 VDC

9.0 VDC (approx.)

Nominal RPM less 20%

0.8 Amp (max)

1.8 lbs.

3.28 X 3.28 X 5.62 in.

Roll Servo

Power required:

Current requirements:

Weight:

Dimensions:

Pitch Servo

Power required:

Current requirements:

Weight:

Dimensions:

14/28 VDC

Included in system current requirements

2.9 lbs.

3.75 X 3.75 X 7.25 in.

14/28 VDC

Included in system current requirements

2.9 lbs.

3.75 X 3.75 X 7.25 in.

2nd Ed: May 31, 2002 5-3

SYS FIFTY FIVE X POH

SPECIFICATIONS (Cont'd)

Altitude Pressure Transducer

Power required:

Pressure range:

Overpressure:

Weight:

10 VDC (supplied by autopilot)

0-15 PSI absolute

150% of operating maximum

0.2 lbs.

Remote Annunciator (OPTIONAL)

Power required:

Weight:

Dimensions:

0.2 Amp (max)

0.75 lbs.

1.60 X 3.42 X 3.80 in.

Trim Servo (OPTIONAL)

Power required:

Current requirements:

Weight:

Dimensions:

14/28 VDC

0.5 Amp (avg.), 2.0 Amp (max)

2.9 lbs

3.75 X 3.75 X 7.25 in.

Yaw Damper (OPTIONAL)

Power required:

Current requirements:

Weight:

Dimensions:

14/28 VDC

1.5 Amp (max continuous)

0.9 lbs

4.5 X 1.75 X 5.25 in.

System Current Requirements

(Approximate)

Average operating current:

Maximum current:

@14 VDC @28 VDC

1.0 Amp

5.0 Amp

0.5 Amp

3.0 Amp

5-4 2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

SECTION 6 GLOSSARY

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6-2 2nd Ed: May 31, 2002

Term

GPSS

HDG

HSI

IFR

LOC

N/A

NAV

POH

POHS

PSI

RDY

REV

RPM

SFM

TSO

VDC

VMC

VOR

CWS

DSBL

FAA

FPM

GPS

AFMS

ALT

APR

ATC

CAP

CDI

CON'T

2nd Ed: May 31, 2002

SYS FIFTY FIVE X POH

GLOSSARY

Meaning

Airplane Flight Manual Supplement

Altitude

Approach

Air Traffic Control

Capture

Course Deviation Indicator

Continued

Control Wheel Steering

Directional Gyro

Disable

Federal Aviaton Adminstration

Flight Director

Feet Per Minute

Global Positioning System

Global Positioning System Steering

Glideslope

Heading

Horizontal Situation Indicator

Instument Flight Rules

Localizer

Not Applicable

Navigation

Pilot Operating Handbook

Pilot Operating Handbook Supplement

Pounds Per Square Inch

Ready

Reverse

Revolutions Per Minute

Supplemental Flight Manual

Technical Standard Order

Volts Direct Current

Visual Meteorological Conditions

Very High Frequency Omnidirectional Radio

Range

Vertical Speed

6-3

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6-4 2nd Ed: May 31, 2002

S-TEC Corporation

A Meggitt Aerospace Systems Company

One S-TEC Way · Municipal Airport

Mineral Wells, Texas 76067-9236 USA

Telephone: 940/325-9406; FAX: 940/325-3904

1-800-USA-STEC www.s-tec.com

S-TEC and the S-TEC logo are registered trademarks of S-TEC Corporation.

P/N: 87109

Date: May 31, 2002

Printed in USA

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S-TEC Fifty Five X Autopilot Pilot’s Operating Handbook

System Fifty Five X

Autopilot

Pilot’s Operating

Handbook

TABLE OF CONTENTS

TABLE OF CONTENTS

LIST OF FIGURES

SECTION 1

INTRODUCTION

SECTION 2

BLOCK DIAGRAM

SECTION 3

AUTOPILOT OVERVIEW

SECTION 4

PROCEDURES

-

SECTION 5

SPECIFICATIONS

Appendix A:

Specifications

System Requirements

SECTION 6

GLOSSARY