SI 22-01 Auto Pilot Installation - Rev 2 Oct 29-13_Auto_Pilot_Installation.… · YAW DAMPER OVER VOLT UNDER VOLT 12 Vdc OUTLET 12 A MAX. 10 A CONT. E-GYRO Install AP Circuit Breaker

Found Aircraft Canada Inc. SI-22-01 Rev 2 R.R.#2, 95 Airport Rd., Parry Sound, Ontario, Canada, P2A 2W8 October 29, 2013 T (705) 378-0530 F (705) 378-0594 www.foundair.com Page 1 of 42

S-Tec 55X Autopilot Installation

SUBJECT / REASON / DESCRIPTION:

This service instruction provides detailed installation instructions for installing an S-Tec 55X Autopilot into a FBA-2C3 equipped with a Garmin G500 Advanced Avionics Suite.

COMPLIANCE:

Compliance is optional. EFFECTIVITY:

Serial #301 when retrofit with the Garmin G500 Advanced Avionics Suite (reference Found Aircraft Canada drawing X2500). Serial #302 onward

APPROVAL:

This modification has been approved by FAC Engineering and TCCA where applicable.

SPECIAL TOOLS / EQUIPMENT:

None

SERVICE INSTRUCTION SI-22-01

Revision 2


PARTS LIST (BILL OF MATERIALS): A. Main Wire Harness Kit # FAC-SI-22-01A R01

Qty Part # Description 1 L2167 Autopilot Harness 1 L2174 Autopilot Flight Panel Harness1 55254-1 Computer Tray (Chassis) 1 601482-2 Connector Bracket 4 1103S440-2 Screws, (Connector Bracket) 4 1111C400-6A Screws, (Backshell Mounting) 2 5504 S-Tec Backshells 1 MS3320-5 Circuit Breaker 1 L933 Attenuated Post Light 1 X2164 AP Master Sw Placard

B. Turn Coordinator Kit # FAC-SI-22-01D R01

Qty Part # Description 1 6405-28L Turn Coordinator4 MS33737-16C Nut 4 MS35214-31 Screw 1 MS3320-1 Circuit Breaker

C. Pressure Transducer Kit # FAC-SI-22-01E R00

Qty Part # Description 1 0111 Pressure Transducer1 T60-1 Tee 1 4060-1 ¼-5/32 Reducer 2 AN525-832R9 Screw 4 AN960-8L Washer 2 MS21083N08 Nut 6” 5/32 Clear Flex Tube Tube 6” ¼ Clear Flex Tube Tube 7 Tie Wrap Tie Wrap


D. Pitch Servo Kit # FAC-SI-22-01B R00 Qty Part # Description 1 0108-1-P2 Pitch Servo 2 6121 Cable Clamp1 7001-16 Bridle Cable 1 F2403 Rub Strip 2 MS35206-246 Screw 2 AN960-8 Washer 2 MS21083N08 Nut 4 AN3-5A Bolt 8 AN960-10 Washer 4 MS21083N3 Nut

E. Roll Servo Kit # FAC-SI-22-01C R00

Qty Part # Description 1 0106-15-R9 Roll Servo 2 6121 Cable Clamp1 7001-16 Bridle Cable 4 AN3-4A Bolt 4 AN960-10L Washer

F. Cygnet Control Wheel Kit # FAC-SI-22-01F R01

Qty Part # Description 1 Q2471 Pilot's Control Wheel 1 Q2473 Copilot's Control Wheel 1 Q2475 Center Harness 2 C2591 Control Wheel Shaft Assembly 3 1-66105-3 Socket 1 206037-1 Connector 1 206036-3 Connector 2 206070-1 Cable Clamp 2 MS21919WJC4 Clamp 1 MS21919WCJ6 Clamp 6 AN3-7A Bolt 12 AN960-10L Washer 6 MS21042-3 Nut 2 240-068 Roll Pin 6 656-182 Shim Ring 20 Tie wrap Tie wrap 6" 605262-1 ( Newark p/n 95F113G ) 1" Black Rubber Fusion Tape 12" Roundit 2000 NX 1/2" Abrasion Protection 1 CB200 - 3.5 gm Click Bond Adhesive 4 CB9302V3 Click Bond Tye Wrap


G. Computer/Programmer & Manuals # FAC-SI-22-01G R00

Qty Part # Description 1 01192-34-5T Computer/Programmer 1 41297 Bushing/Cooling Spigot 1 87109 55X POH 1 S03 Flight Manual Supplement 1 600 S-Tec General Installation Bulletin

WEIGHT & BALANCE: Item Part Number Weight (lbs) Arm (in) Computer 01192-34-5T 2.7 -4 Pitch Servo 0108-1-P2 2.9 46 Roll Servo 0106-15-R9 2.9 35 Pressure Transducer 111 0.2 -10 Main Wire Harness L2167 2.1 20 A/P Switch & Indicator Harness L2174 0.2 -2 Turn Coordinator 1394T100-14RB 1.8 -2

DRAWINGS/MANUALS: FAC Maintenance Manual FAC2-M200 FAC Flight Manual Supplement S03 S-Tec General Installation Bulletin 600 L2073 Autopilot Install Schematic


IMPLEMENTATION INSTRUCTIONS: A. Main Wire Harness, Flight Panel Harness, and Computer Tray Installations The main wire harness is connected to the following components:

Roll Servo Pitch Servo Pitch Trim Servo (Future option) Autopilot Computer Pilot’s Control Wheel Garmin G500 PFD/MFD Turn Coordinator Pressure Transducer

General Notes:

All wiring shall be connected per L2073 Autopilot Schematic. Unless otherwise specified all wiring shall be in accordance AC43.13-1B Chapter 11. In

addition ensure that wires and cables are provided with enough slack to meet the following requirements:

o Permit ease of maintenance o Prevent mechanical strain on the wires, cables, junctions, and supports. o Permit free movement of shock and vibration mounted equipment. o Allow shifting of equipment, as necessary, to perform alignment, servicing,

tuning, removal of dust covers and changing of internal components while installed in aircraft.

Unless otherwise specified all field fabricated wiring shall be MIL-W-22759/16 or equivalent.

To gain access follow steps 1 to 6:

1. Remove the crew seats per MM Chapter 25-13. 2. Remove the passenger seats per MM Chapter 25-24. 3. Remove cabin liner panels as required per MM Chapter 25-80. 4. Remove cabin insulation as required per MM Chapter 25-90. 5. Remove the floors per Chapter 53-20 of Maintenance Manual FAC2-M200 6. Remove the instrument panels as required per MM Chapter 31. 7. Disconnect battery negative cable per MM Chapter 24. 8. Install the required circuit breakers for the Turn Coordinator and the Autopilot. See

Figure 1 for C.B. locations. (Note, labels may be required for the new circuit breakers). 9. Install L2167 Main AP Harness per Figure 2, Figure 3, and Figure 4. Note: Starting at aircraft S/N 304, the lower right panel, a.k.a. the circuit breaker panel, is installed with circular plastic connectors, (a.k.a. CPCs).


NAVLTS

COMM1

NO SMOKINGFASTEN SEATBELTS

FIRE EXTINGUISHER LOCATEDON R/H SIDE OF CONSOLE

ALTFIELD

FUELPUMP

PULSECNTRL

CREWLTS

LANDLTS

STROBELTS

NAV 1GPS 1

COMM2 XPNDR

12 V.d.c.10 AMP

TRAFFIC AUDIOPANEL

VOLTREG

IGNSW

CLOCK HOBBSMETER

STALLWARN

PITOTHEAT

GEARMOTOR

GEARCNTRL

FLAPMOTOR

TURNCO-OR

FLAPIND

GEARADV

ENGMON

PFD AHRS ADC

CODET.

PULSELT

PANELLTS

NOISEH/P

PITCHINDIC

RUDDERTRIM

COWLFLAP

CABINLTS

NAV 2GPS 2

AVNFAN

ADF DMEXM WX AUTOPILOT

YAWDAMPER

OVERVOLT

UNDERVOLT

12 Vdc OUTLET12 A MAX.

10 A CONT.

E-GYRO

Install AP Circuit Breaker HereM3320-5, 2TL1-5, 5 Amp CB

Install TC Circuit Breaker HereM3320-1, 2TL1-1, 1 Amp CB

Figure 1 CB Install Locations


Roll, Pitch, Trim Cables

Flight Panel Connector9 Pin D-Sub

Pressure TransducerConnector 3 Pin Molex

P2 Connector (Part Of L2167)

P1 Connector (Part Of L2167)

16 Pin CPC(Designated CW1,

Control Wheel 1)

24 Pin CPC (AC 304 Onward)Power And Light Dimming

AC304 Onward = Ground BlockAC300 Thru 303 = Top Of Console Ground Studs #10

Turn CoordinatorStbd Side With

Amphibian Floats,Port Side WithoutAmphibian Floats.

Figure 2 L2167 Harness Installation Forward Of IPs (View From Above)

Roll And Trim CablesRoute To Wing RootAnd Onward As Required

Pitch CableRoute Below DoorAnd OnwardAs Required

24 Pin CPC(AC 304 Onward)

A+ And Light Dimming

Turn CoordinatorStbd Side With

Amphibian Floats,Port Side WithoutAmphibian Floats.

P1

P2

Flight Panel Connector9 Pin D-Sub

Flight Computer

Note: CW1 Located@ Stbd Side Of ConsoleAbove Fire Extinguisher

AC304 Onward= Ground Block:AC300 Thru 303

= Top Of Console Ground Studs #10

3 Pin Molex ConnectorPressure Transducer(Between AHRS & ADC)

Figure 3 L2167 Harness Installation (View Looking Aft)


Rol

l Se

rvo

Cen

ter

Aft

Mai

n S

par

Pitc

h S

ervo

Cen

ter

Pa

ssen

ger

Flo

or

Trim

Ca

ble

Rou

te A

lon

g U

pper

Po

rt A

ft F

use

lag

e L

ong

eron

App

ly A

bra

sio

n P

rote

ctio

n T

oC

able

In A

rea

Of J

oin

t Bet

we

enF

ore

An

d A

ft F

use

lage

.

Rou

te R

oll C

ab

le T

hro

ugh

Hol

e In

Spa

r W

ith O

ther

Wire

s

L21

67M

ain

AP

Ha

rnes

s

Trim

Se

rvo

(Fut

ure

Opt

ion)

Figure 4 Roll, Pitch & Trim Servo Harness Routing


Note: Power and lighting wires will terminate at the CPCs per schematic L2073. For aircraft S/N 303 and earlier the power and lighting wires may require extending. For connections to the dimmer circuit see Figure 5 and Figure 24-60-15 of the maintenance manual. For the power wires simply follow the existing wire routes to the appropriate circuit breaker.

VR3

VR1

2 X NTE245 DARLINGTONPOWER TRANSISTOR TO-3 PACK

2 X RV4NAYSD502A5K POTENTIOMETER

9 8

A

YY

X

XX

XX

X

* A

A

*A

A

* A

A

X

A *

A

*

A

A

*

A

YL933

68O

X

Y 68O

C9

C7C8

7

4

C6

Acceptable To JumperTo Any Terminal BlockAttached To Q3 Dimmer

Y 68O

Connect Post Light In ParallelWith Other Flight Panel Lamps

Figure 5 Light Dimmer Circuit

Note: For the routing of the pitch, roll and trim servo cables, it may be convenient to disconnect the associated 9 pin D-Sub connectors. Connectors should be removed with


proper tools, contacts protected during routing process and reinstalled in accordance with schematic L2073 and other diagrams as specified.

Note: Ground connection shall be at the preexisting "ground block" atop the control console at the front using the appropriate terminals, (AMP p/n 66105-4 or equivalent), or atop the control console using preexisting #10 ground studs with #10 ring tongue terminals. 10. Install the flight panel harness, L2174, per Figure 6, Figure 7, Figure 9, and Figure 9.

Install IndicatorPer Figure 22-01-09

Route And SecureL2174 HarnessAs Shown

Flight Panel

Logic ModuleSecure To Existing

Harnesses Via Tie Wraps

9 Pin D-Sub (Male)

Figure22-01-06Aft View

Figure 6 Flight Panel Harness Installation (View From Back Of Flight Panel)


L933 Installation Notes (Items Ref Only);(Note, this device has a resistor installed on the power wire to dim the lamp.This is done to match other lighting on the panel. Do not remove resistor).1-Install main body of post lamp (item 1) into the front of panel.2-Install plastic washer (item 2) onto the threaded shaft of the main body.3-Install split washer (item 3) onto the threaded shaft of the main body.4-Install jam nut (item 4) onto the threaded shaft of the main body.5-Tighten jam nut sufficently to flatten the split washer. DO NOT OVER TIGHTEN.6-Next install the ground wire ring tongue terminal (item 5).7-Before installing the MS21083-N08 nut (item 6) first install the nut onto an 8-32 screw to relieve the nylon locking mechanism. THIS IS IMPORTANT AS THE THREADED SHAFT OF THE MAIN BODY IS HOLLOW AND MADE FROM A SOFT ALLOY WHICH MAY OTHERWISE BE DAMAGED.8-DO NOT OVERTIGHTEN ITEM 69-Parallel power wires to existing post lights on the flight panel.10-Finally, install power connector (item 7) with finger pressure only.

4

Mounting Hole5

Typical Panel

12

3

76

Dimming Resistor

(Ø.17)Drill #19

(Ø.25)Drill 1/4

CLSYM

.11 1.11

.50

FD

AP

OFF

L933X2164

706203000

Red SwitchCover

Placard

AttenuatedPost LightSee NotesThis Sheet

Front ViewFlight Panel

Front ViewFlight Panel

Figure 7 Flight Panel Harness Installation (Mechanical Details)


.691±0.004

.691±0.004

R.07max.

Create Hole As IndicatedLocate Between Stall Light

And Check Engine LightAnd Center Level With Each Other

Flight Panel

(Stall Light)

(Check Engine Light)

Figure 8 Mode Annunciator (Mounting Hole Details)

LampModule

Note"TOP"

Bulbs

HousingNote

"TOP"

Seal

Flight Panel

Seal

Spacer(1 Required)

MountingSleeve

ReceptacleNote

"TOP"

(Stall Light)

(Check Engine Light)

A

View On Arrow "A"Mounting Cam Screws

Mounting CamsOne Per Side

Cam ScrewCam Screw

Note CamsOne Per Side

L2174 Complete

Master Switch(FD Option)

Logic Module(Shown Without Sheath)

Figure 9 Mode Annunciator (Assembly Details)


11. Locate the G500 interface wiring bundle, (located near the aft port side of the center instrument panel and associated avionics trays), and remove temporary wire sheaths.

12. Attach the appropriate terminations and prepare the shield drains for specific wires. For standard density sockets use M39029/63-368 or equivalent. Crimp with hand tool M22520/2-01 and positioning tool M22520/2-08 or equivalent.

13. Insert G500 interface wires into "P1" and "P2" connectors of harness L2167 per schematic L2174. For reference see Figure 10 and Figure 11.

14. Install the computer tray and connect the connectors P1 and P2, per Figure 12 and Figure 13. Note these connectors are mechanically identical. Ensure they are properly installed with P2 on the port side and P1 on the starboard side.

15. Connect the CPC designated as "CW1", (control wheel 1), to the control wheel harness. 16. Connect the 3 pin molex connector to the pressure transducer. 17. If the aircraft does not have the appropriate turn coordinator proceed to section B and

install a turn coordinator before reinstalling the instrument panels 18. Reinstall instrument panels per MM Chapter 31. 19. Reinstall the LRUs (Line Replaceable Units) as required.


HDG DATUM HIHDG DATUM LO

CRS DATUM HICRS DATUM LO

Shield DrainLAT DEV FLAG+LAT DEV FLAG-

LAT DEV +LTLAT DEV +RT

Shield DrainGS DEV FLAG+GS DEV FLAG-

GS DEV+UPGS DEV +DOWN

Shield DrainGPSS STEERING

GPS TRACK GAIN

LOC SWITCH

AB

Shield DrainAB

ALT SEL JUMPERGROUND

429 GPSS DATA IN {ALT SEL/BARO ALT

RS-485

0637-220638-22

0639-22

0631-22 BLU0631-22 WHT

0632-22 BLU0632-22 WHT

0633-22 BLU0633-22 WHT

0634-22 BLU0634-22 WHT

0635-22 BLU0635-22 WHT

0636-22 BLU0636-22 WHT

0640-22 BLU0640-22 WHT

0641-22 BLU0641-22 WHT

0537A-22 (Existing Wire)

0642A-22

Connect 0642a stub to 0642bfrom the existing harnesswith a solder sleeve.

12

18193938

3637402120

2342

FD LOGIC

ROLL FD STEERINGSIG REF (ROLL FD)

PITCH FD STEERINGSIGNAL REF (PITCH FD)

AUDIO OUT

4

122946133049

2745

0681-22 SH

0643-22 WHT

0644-22 WHT0644-22 BLU

0643-22 BLU

0642B-22

SYSTEM 55XAUTO PILOT

2829

1112441314

313045

49

32

P1P2

Shield Drain

Shield Drain

Shield Drain

n/cn/c

Figure 10 Autopilot L2167 Connectivity


P2

P1

CONNECTIONS AT P1, P2

WIRE NUMBER TERMINATIONSHIELD

TERMINATION0631-22 BLU P1-28 P1-440631-22 WHT P1-29 P1-44

0632-22 BLU P1-11 P1-44

0632-22 WHT P1-12 P1-44

0633-22 BLU P1-13 P1-45

0633-22 WHT P1-14 P1-45

0634-22 BLU P1-31 P1-45

0634-22 WHT P1-30 P1-45

0635-22 BLU P2-1 P2-39

0635-22 WHT P2-2 P2-39

0636-22 BLU P2-18 P2-39

0636-22 WHT P2-19 P2-39

0639-22 P1-32 N/A

0640-22 BLU P2-36 P2-40

0640-22 WHT P2-37 P2-40

0641-22 BLU P2-21 P2-40

0641-22 WHT P2-20 P2-40

0642-22 P2-4 N/A

0643-22 BLU P2-12 P2-46

0643-22 WHT P2-29 P2-46

0644-22 BLU P2-13 P2-49

0644-22 WHT P2-30 P2-49

0681-22 SH P2-27 P2-45

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

A B C

Figure 11 Autopilot L2167 Connectivity Summary


5525

4-1

Cha

ssis

Ass

embl

y

5504

(P1

Ba

ck S

hell)

550

4(P

2 B

ack

She

ll)

1103

S44

0-2

4 P

lcs

(4-4

0 S

crew

s)A

pp

ly S

ma

ll A

mou

nt

Loct

ite #

242

On

Thr

eads

Pri

or T

o F

inal

Ass

embl

y

1111

C40

0-6A

4 P

lcs

(Scr

ews)60

148

2-2

Con

nect

or B

rack

et

4129

7

150

5-12

Cot

ter

Pin

(M

S24

665-

134)

Bu

shin

g (

Co

olin

g S

pigo

t)

Fig

ure

22-

01-1

3

#8 C

S S

cre

w,w

ash

er a

nd n

ut6

Plc

s

CA

UT

ION

: T

he

50

Pin

Con

nec

tors

Are

Iden

tical

. Che

ck T

o B

e S

ure

Tha

t

T

he P

1 C

onne

ctor

Is

Inst

alle

d O

n T

he S

tbd

Sid

e A

nd P

2 P

ort S

ide.

Pro

gram

me

r/C

ompu

ter

Ma

y B

e In

stal

led

Top

or

Bot

tom

Of

Cen

ter

Pan

el.

Figure 12 Programmer/Computer Tray Installation


The Mounting Tray Must Be Installed SoThat The Left And Right Edges Of TheTray Are Flush With The Aft Face Of TheInstrument Panel. This Will Ensure ProperEngagement Of Electrical Connectors WhenThe Programmer/Computer Is Installed.

After Wiring Has Been Completed And TheConnector Assembly Has Been Secured To TheMounting Tray, Slide programmer ComputerInto Mounting Tray And Secure In Place With 5/64 AllenWrench Through Hole In Center Of Face PlateBetween The "APR" And "REV" Mode Select Switches

Access Hole For RollCentering Adjustment

See Figure22-01-12

Figure 13 Additional Mechanical Tray Installation Details


B. Turn Coordinator Installation The turn coordinator is installed in the cabin directly on the flight panel, see Figure 14.

1. Turn off Master Switch. 2. Remove the GDU 620 graphical display unit per MM Chapter 34-70. This allows easy

access to the back of the instrument panel. 3. Remove the blanking plate. Blanking plate and the hardware will not be reused. 4. Place the instrument in the flight panel. 5. Secure the instrument with screws. 6. Install the "light tray" on the instrument. 7. Connect the circular connecter at the instrument back. 8. Reinstall the GDU 620 per Chapter 34-70. 9. Ensure that the “ball” is level when the aircraft is level in the roll axis. Note that the

mounting holes for this instrument are oval shaped to allow the “ball” leveling adjustment.

MS35214-31MS33737-16C

4 PLACES

6405-28L

Turn Coordinator

(GDU 620)

Figure 14


C. Pressure Transducer Installation The pressure transducer is installed beside the air data computer located directly above the pilot’s rudder pedals. It connects to the autopilot electrical harness as well as the static pressure line, see Figure 15

1. Turn off Master Switch. 2. Locate the pressure transducer, mark and drill mounting holes. 3. Deburr edges and touch up with primer meeting or exceeding MIL-P-23377. 4. Cut the STATIC line near the Air Data Computer, install the Tee (T60-1) and tie wraps. 5. Prepare the plumbing for the pressure transducer including the reducer (4060-1). 6. Connect the pressure transducer plumbing to Tee and tie wrap. 7. Connect the plumbing to the pressure transducer and tie wrap. 8. Plug electrical harness connector. 9. Secure the pressure transducer to frame with screws.


To Air DataComputerØ1/4 Static Line

4060-1Use single tiewrap on

each line

Ø1/4 Clear Flex Tube

Ø5/32 Clear Flex Tube

A/C

FWD.

T60-1Use single tiewrap on each line

Use TWO tiewraps to securethe line to pressure x-ducer.Stagger tiewrap heads.

AN525-832R9AN960-8L (x2)MS21083N08

2 PLACES

0111

Air Data Computer

Ø1/4 Static Line

Electrical HarnessConnector

Figure 15 Pressure Transducer Installation


D. Pitch Servo Installation The pitch servo is connected to the elevator cable and it is located under the passenger floor at fuselage station 55, see Figure 17.

1. Placard the aircraft as required to ensure that elevators are not moved during installation as personnel injury can occur if hands are caught in moving parts.

2. Turn the Master Switch to off position. 3. Secure the elevators in the trailing edge down position.

NOTE: Ensure proper rigging and cable tensioning of airframe systems before installing servo.

CAUTION: The servo clutch torque is set at the factory. Disassembly of the clutch and capstan assembly is not necessary and not recommended. Some clutch arrangements are keyed to the capstan with roll pins. Further disassembly than what is shown in Figure 16may misalign pins with holes in the clutch disc. 4. Remove 4 screws securing the capstan cover and the 4 cable guards to the servo. Retain

the hardware. See Figure 16. 5. Place the servo onto the mounting bracket in the fuselage and snug the fasteners enough

to temporarily secure the servo. See Figure 17. 6. Temporarily install the upper cable guard (finger tight). 7. Adjust the servo height so that the distance between the upper cable guard and the

elevator cable is 1/16"-1/8" and torque the 4 mounting bolts. 8. Rotate the capstan so that the hole for the centre ball is in the 2 o'clock position as viewed

from the right side of the aircraft. 9. Depress the center ball of the bridle cable to the bottom of the hole in the capstan and

tighten the center ball set screw. 10. Wrap the cable onto the capstan (clockwise) until the forward cable clamp is aligned with

the aft face of fuselage steel tube; see Figure 17. Snug the forward cable clamp onto the elevator cable.

11. Wrap the other end of the cable 7800 (counter clockwise) and snug the aft clamp onto the elevator cable.

12. Adjust the cable clamps in or out along the elevator cable to obtain cable tension of 15 ±2 lbs. The heads of the bolts shall be oriented to the left side of the airplane in order to maximize the clearance between the clamps and the adjacent rudder cable, see Figure 17.

13. Torque cable clamp bolts to 55±5 in-lbs. Note this should result in a "gap" of at least 0.005" between the clamp halves, See Figure 17. If the gap is less than 0.005” check the cables for condition if the cables are not damaged replace the cable clamp.

14. Carefully install the remaining cable guards (3) into the servo (Finger Tight). Then tighten with a screw driver.

15. Place the capstan cover on cable guards and align all four holes. 16. Insert one screw with a star washer through the cover and into one of the cable guards

and tighten finger tight. Repeat this step with the remaining screws and washers.


17. Tighten screws with a screw driver using a crisscross pattern assuring an even pressure on the cover.

18. After the Servo Capstan Cover is installed determine there is no interference between the capstan and the cover.

19. Install the rub strip, F2403, such that it just touches the control cables. 20. Connect the electrical wires. 21. Remove any temporary placards and release the elevators. Perform an operational check

of the elevator system by cycling the control column fore and aft to ensure there is no binding in the system and the elevators achieve their full travel. While cycling the control column observe the pitch servo bridle cables to ensure there are no interferences throughout the full range of travel.

Capstan Type Servo

Frangible Cable Guards

Capstan Cover

Star Washer

Screw

Figure 16


Pitch Servo

Pitch Servo

A/C FWD.

SIDE VIEWView looking left (port)

TOP VIEWView looking down

Torque Clamp Bolts55 In.lbs ± 5 In. lbs

Gap =.005after torquing

Cable Clamp(Fwd.)

Cable Clamp(Aft)

Ref. alignmentfor installation

Fuel Tub

38" BribleCable

GapBetween Cable Guard

and Elevator Cable1/16"-1/8"

Cable RubStrip

Depress center ballto bottom of holeand tighten setscrew.

Center ball located atthe 2 o'clock position(approximately)

Wrap 780°and aft

TRIM

TRIM

RUDDER

RUDDER

ELEVATOR

ELEVATOR

2 PlacesBolt,Nut

Bridle Cable

61216121 0108-1-P2

F2403

7001-16

Cable Clamp

MS35206-246AN960-8

MS21083N08

2 PLACES

AN3-5AAN960-10(BRACKET & FLANGE)AN960-10MS21083N3

4 PLACES

Figure 17 Pitch Servo Installation


E. Roll Servo Installation The roll servo is connected to the aileron balance cable and it is located in the cabin area mounted on the aft face of the wing main spar at fuselage station 36, see Figure 18.

1. Placard the aircraft as required to ensure that ailerons are not moved during installation as personnel injury can occur if hands are caught in moving parts.

2. Turn the Master Switch to off position. 3. Secure the ailerons in the neutral position.

NOTE: Ensure proper rigging and cable tensioning of airframe systems before installing servo.

CAUTION: The servo clutch torque is set at the factory. Disassembly of the clutch and capstan assembly is not necessary and not recommended. Some clutch arrangements are keyed to the capstan with roll pins. Further disassembly than what is shown in Figure 16 may misalign pins with holes in the clutch disc.

4. Remove 4 screws securing the capstan cap and the 4 cable guards to the servo, see Figure

16. 5. Place the servo onto the mounting bracket and torque the fasteners. 6. Rotate the capstan so that the hole for the centre ball is facing aft. 7. Depress the center ball of the bridle cable to the bottom of the hole in the capstan and

tighten the center ball set screw. 8. Wrap the left (port) cable onto the capstan clockwise 3600 and snug the cable clamp onto

the aileron balance cable. 9. Wrap the right (stbd) cable onto the capstan counter clockwise 3600 and snug the cable

clamp onto the aileron balance cable. 10. Adjust the cable clamps in or out along the aileron balance cable to obtain cable tension

of 15 ±2 lbs. 11. Torque cable clamp bolts to 55±5 in-lbs. Note this should result in a "gap" of at least

0.005" between the clamp halves, See Figure 18. If the gap is less than 0.005” check the cables for condition if the cables are not damaged replace the cable clamp.

12. Carefully install the cable guards (4) into the servo (Finger Tight). Then tighten with a screw driver.

13. Place the capstan cover on cable guards and align all four holes. 14. Insert one screw with a star washer through the cover and into one of the cable guards

and tighten finger tight. Repeat this step with the remaining screws and washers. 15. Tighten screws with a screw driver using a crisscross pattern assuring an even pressure

on the cover. 16. After the Servo Capstan Cover is installed determine there is no interference between the

capstan and the cover or between the balance cable and the aft most cable guard. 17. Connect electrical wires. 18. Remove any temporary placards and release the ailerons. Perform an operational check of

the aileron system by rotating the control wheel from side-to-side to ensure there is no


binding in the system and the ailerons achieve their full travel. While cycling the wheel observe the aileron servo bridle cables to ensure there are no interferences throughout its full range of travel.


Torque Clamp Bolts55 In.lbs ± 5 In. lbs

Gap =.005after torquing

2 PlacesBolt,Nut

Bridle Cable

Roll Servo

Balance Cable

Roll Servo

Main Spar

A/CFwd.

Cable Clamp

Minimum Gap BetweenCable Guard And Balance Cable

1/16

38" Bridle Cable

A

View on 'A'

A/C FWD.

Wrap 360°& stbd.

Wrap 360°& port

Depress center ballto bottom of holeand tighten setscrew.Aileron balance

cable

6121

6121

Cable Clamp

Cable Clamp

0106-15-R9Roll Servo

AN3-4AAN960-10L

4 PLACES

7001-16

Figure 18 Roll Servo Installation


F. Cygnet Control Wheel Installation The Cygnet control wheel is required with the autopilot system. It is designed such that it incorporates the autopilot controls. Therefore, if not already equipped, the control wheel(s) must be replaced with the Cygnet control wheel(s).

1. Placard the aircraft as required to ensure that ailerons are not moved during installation as personnel injury can occur if hands are caught in moving parts.

2. Turn the Master Switch to off position. 3. Cut curly cord wires at the wire splices located below engine controls panel, see Figure

19. 4. Pull the control column aft to gain access to wiring 5. Remove all tie wraps/clamps securing the Push-to-Talk (PPT) wire to the control column. 6. Remove the control wheel bolt and remove the control wheel, see Figure 20. Discard the

hardware. The control wheel will not be used. 7. Remove the End Cap from the control arm. Retain the cap. 8. Loosen the Clamping Collar screws. 9. Remove the Control Arm Nut. The control arm nut is threaded into the control arm. Turn

counter-clock wise to remove. Retain the nut. 10. Cut the lock-wire securing the sprocket roll pin and remove the roll pin. Discard the

hardware. 11. Remove the control wheel shaft by simultaneously replacing it with a temporary shaft.

This technique will keep all the internal parts in exactly the same order eliminating a need for any further disassembly. The control wheel shaft will not be used.

12. Install the new, C2591, shaft assembly by simultaneously replacing the temporary shaft, see Figure 21.

13. Install the roll pin through the sprocket and the control wheel shaft. 14. Check play in the stack. Max allowable gap is .005". If required, shim using the 656-182

Shim Rings to reduce play. 15. Install the Control Arm Nut and tension the chain. 16. Tighten the Clamping Collar Screws thus securing the Control Arm Nut. 17. Check operation of the newly installed control wheel shaft by rotating it from side to side. 18. Install the End Cap. 19. Repeat steps 4-18 for the other control wheel. 20. Secure the ailerons in neutral position. 21. Remove the face plate from the Cygnet control wheel (2 screws) and mount the control

wheel onto the control wheel shaft plate, see Figure 22. Only snug the bolts. 22. Ensure the ailerons are in neutral. 23. Position the control wheel so that it is straight and level and torque the mounting

fasteners. 24. Re-install the face plate on the control wheel (2 screws). 25. Repeat steps 21-24 for the other wheel. 26. Secure the wires to the control arms and connect the Center Harness, Q2475, as shown in

Figure 23 and Figure 24.


27. Install the connector sockets on the remaining cut wires and assemble connector, see Figure 25.

28. Connect the Center Harness, Q2475. 29. Secure the connector per AC43.13-1B Chapter 11 30. Remove any temporary placards and release the ailerons. Perform an operational check of

the aileron system by rotating the control wheel from side-to-side to ensure there is no binding in the system and the ailerons achieve their full travel.


Billet Control Wheel

Billet Control Wheel

Cut wires

Figure 19

Control wheel bolt

End capTemporary shaft

Clamping collarscrews

Roll Pin

Control arm nut

Figure 20


Clamping collarscrews

C2591

Control arm nut

Clamping collar

C2591

240-068

Roll Pin

Lock-wire with Ø.025"stainless steel wire

Sprocket

Spacer

Bearing

BearingSpacer

Control arm nut

A

A

SECTION A-A

MAX. ALLOWABLEGAP IN STACK IS .005".

SHIM STACK WITH656-182 SHIM RINGS

TO TAKE UPPOSSIBLE SLACK

IN STACK-UP.

Figure 21


AN3-7A3 Places

Q2471

Q2473

Pilot's (shown)

Co-Pilot's

MS21042-3

3 Places

AN960-10L6 Places

MS21919WCJ4

Figure 22


Q2471

Q2473

TyewrapAnchor

CB9302V3

MS21919WCJ6Secure Main Curly Cord With Adel Clamp: Note, AddAbrsion Protection, (Black Heat Shrink or Equivalent)

(Note: This clamp when installed correctly will helpkeep the curly cord away from the trim wheel.)

Tiewrap cord to clampingscrews. Figure "8"

TyewrapAnchorCB9302V3

Tiewrap cord to clampingscrews. Figure "8"

Q2475

Secure splices toweldment with tiewrap

Splice wires using soldersleeves stagger splices toreduce splice size

Cover Wire Splices With AbrasionProtection Roundit 2000 NX or Heat Shrink

Use 605262-1 Rubber Tape To Seal Each EndOf Roundit 2000NX Use Tyewraps As Required

Locate Approximately As ShownClean Surfaces Throughly

Figure 23


0159-22

0162-22 (Co-Pilot)

0160-22 (Pilot)

Belden8490

BLKGRN

3

4

5

16

7

6

8

9

10

12

11

13

14

15

2

1

3

4

5

16

7

6

8

9

10

12

11

13

14

15

W w/Blk

Blu

Wht

Gry

Vlt

Grn

Yel

Org

Red

BrnBlk

W w/Brn

W w/Red

W w/Org

W w/Yel

W w/Grn

W w/Blu

W w/Vlt

W w/Gry

W w/Blk

Blu S-Tec3934

WHT

SW21, P.T.T., CO-PILOT

BLKGRN

WHT

Wht

Gry

Vlt

Grn

Yel

Org

Red

Brn

Blk

W w/Brn

W w/Red

W w/Org

W w/Yel

W w/Grn

W w/Blu

W w/Vlt

W w/Gry

S-Tec3934

2

1

Wht

Gry

Vlt

Grn

Yel

Org

Red

Brn

Blk

W w/Brn

W w/Red

W w/Org

W w/Yel

W w/Grn

W w/Blu

W w/Vlt

W w/Gry

W w/Blk

Blu

SW

13, P

.T.T

., PILO

T

N.C.

Note: Short Extensions May Be RequiredExtensions May Be Vendor Supplied

Connections May Be Solder SleevesOr Solder and Heat Shrink Tube.

Figure 24


206037-1

206070-1

1-66105-3Wire 0160-22 (White)Pin #10

3 Places

Wire 0159-22 (Black)Pin #2

To Q2475

Wire 0162-22 (Green)Pin #6

Figure 25


G. G500 Configuration, Static Leak Check, and Ground Tests 1. Re-install the floors per Chapter 53-20 of Maintenance Manual FAC2-M200 2. Re-install cabin insulation per MM Chapter 25-90 3. Re-install cabin liner panels per MM Chapter 25-80 4. Re-install the passenger seats per MM Chapter 25-24. 5. Re-install the crew seats per MM Chapter 25-13. 6. Reconnect the battery negative terminal per MM Chapter 24. Note: It is recommended to connect ground service power as configuration and ground testing can be demanding of the battery. 7. Test the turn coordinator:

7.1. Turn on Master Switch. A red flag should disappear, indicating the power is on.

7.2. Listen to the indicator to determine if the gyro is properly turning. 7.3. If the gyro is not heard, remove the indicator, and take it to a qualified technician for

replacement or repair. 8. Disengage all circuit breakers except for the “PFD". This will allow the G500 system to be

configured while minimizing demand on the battery. 9. Clear the propeller area and apply power with the aircraft Master Switch. 10. Perform a static leak check by slowly applying suction to the static system until the altimeter

reads 1,000 feet above the field elevation. Cut off the suction source to maintain a closed system for one minute. Leakage shall not exceed 100 feet of altitude loss as indicated on the altimeter.

11. Configure the G500 per section 5 of the installation manual, Garmin p/n STC G500

Installation Manual 190-01102-06. 11.1. To enter the configuration mode perform the following: (Ref Section 5.4.1 of Garmin

Manual 190-01102-06) 11.1.1. Pull the "PFD" circuit breaker.


11.1.2. Insert the correct "Installer Download Card" if applicable, (Altitude Preselect for example), into the top SD card slot and "Installer Unlock Card" into the bottom slot.

11.1.3. While holding the "ENT" button restore power by closing the "PFD" circuit breaker.

11.1.4. When the words "INITIALIZING SYSTEM" appear release the "ENT" button. 11.2. Proceed to Section 5.5.5 Optional Feature Activation and Section 5.5.6 Autopilot

Configuration and Section 5.5.10 Flight Director Configuration as required. Note: the autopilot configuration shall be set for "King KI 525". 11.3. After configurations are complete turn Off the Master Switch.

12. Autopilot Ground Test Procedures: 12.1. Reengage circuit breakers, clear propeller area and turn on the Master and Avionics

Switches. 12.2. Check that the autopilot circuit breaker is engaged. Place the autopilot master switch

in the "AP" position. All segments of the programmer/computer display should illuminate including: HDG, RDY, NAV, CWS, APR, FAIL, TRIM ơ, ALT, GS, VS, +16. The software revision number will briefly appear after 10 to 20 seconds after which only the RDY annunciation will remain illuminated indicating the system is ready to engage.

12.3. Depress button "HDG", the roll solenoid should be heard to engage. A green "AP" should appear on the "Mode Indicator" above the PFD.

12.4. Depress Button "ALT", the pitch servo solenoid should be heard to engage. 12.5. Depress and release control wheel steering switch, (blue switch on pilot's control

wheel). "CWS" and "VS" modes will annunciate and "HDG" and "ALT" will extinguish. Move aircraft controls to determine that the roll and pitch servos are engaged.

12.6. Depress and release the control wheel disconnect switch, (red button on pilot's control wheel). "RDY" will flash and then annunciate steady. An audible tone will indicate autopilot disconnect. Check to see that the roll and pitch servo solenoids are disconnected.

12.7. Center the heading bug on the G500, (select the heading "HDG" bezel key on the PFD and depress the center PFD Knob, (lower left knob on G500Display)).

12.8. Depress the "HDG" mode selector switch on the programmer/computer. "HDG" will annunciate and "RDY" will extinguish. Rotate the heading bug to the right and then to the left of the center indicator and note that the control wheel movement follows the direction of the commanded input. Re-center the PFD heading bug.

12.9. Ensure that the control wheel remains motionless, otherwise adjust the roll centering, (3 turn potentiometer accessible through the face plate between the "REV" and "ALT" mode selector switches), for zero roll servo activity. (Note this adjustment will be further verified during Flight Testing).

12.10. Move elevator to a mid-travel position and select VS mode to engage the pitch servo. Turn the VS knob clockwise to select a positive vertical speed and observe the control


wheel's travel aft or pitching nose up. Select a negative vertical speed (VS knob counterclockwise) and observe control wheel moves slowly in or aircraft nose down. Note: Flashing "VS" annunciator during this test may or may not occur. Flashing "VS" indicates system is unable to resolve a vertical speed error, a condition that may occur during ground test.

12.11. OVERPOWER - Grasp control wheel and overpower autopilot in both roll and pitch. Be alert that no excessive play exists in the control system and/or between the control system and the roll and pitch servos.

12.12. Momentarily depress control wheel disconnect switch - move control wheel in roll and pitch and assure that the roll and pitch servos have disconnected and that the controls are free. The "RDY" light should illuminate flashing for 5 seconds and then be steady, along with an audible tone, indicating autopilot disconnect.

12.13. Trim Test - Move elevator control to a mid travel position and re-engage "HDG" and "VS" modes. Apply forward pressure, (nose down), to elevator control and hold for 3 seconds minimum. "TRIM ▲" should annunciate for 4 seconds. After 4 seconds the "TRIM ▲" will begin flashing. Apply aft pressure on the control wheel, (nose up), and hold for 3 seconds minimum - observe the same annunciations with the "TRIM ▼" annunciator. Hold control wheel and disengage autopilot.

12.14. Tune the Navigation receiver to the local OMNI station or simulate signal and center the needle on the G500 HSI display. Select "NAV" mode on the programmer/computer and rotate the OMNI bearing selector right and then left. Control wheel should move right with right needle deflection and left with left needle deflection. Note, when "NAV" or "REV" mode is selected and no valid navigation information is present, the "FAIL" annunciator should illuminate and the respective mode light will flash.

12.15. Channel an ILS radio frequency. Select "APR" and "ALT" modes. Select "APR" mode a second time - the "ALT" annunciations should remain illuminated with a flashing "GS". Select "APR" once again to return to "APR" (normal). Select "ALT" mode. Select "ALT" mode a second time to arm/engage "GS", ("ALT" extinguishes). Hold control wheel and disengage autopilot.

12.16. To check "GPSS", engage the autopilot "HDG" mode. Push the "NAV" mode button twice, (2 times), "GPSS" should annunciate, (this will require a valid GPS signal). The "GPSS annunciator will also flash if ground speed and bank angle labels are not received from GPS navigator. Select "NAV" once again to return to "NAV" (normal). The aircraft will need to be flight tested to check operation of GPSS. Hold control wheel and disengage autopilot.

13. Turn OFF all master switches.


H. Flight Adjustments and Flight Tests Before take-off the pilot in command shall perform all the preflight and ground checks applicable to the autopilot system as specified in the flight manual supplement P/N S03. In-flight Adjustment: The in-flight adjustments for this system consist of one 3 turn adjustable potentiometer (roll centering) located behind the face plate of the programmer/computer and accessible with a small slot screwdriver, through the hole in the face plate between the "REV" and "ALT" mode switches, See Figure 13. 1. Fly the aircraft into smooth air, and trim for level flight. 2. Ensure autopilot circuit breaker is engaged and toggle AP Master Switch to "AP". 3. Center the heading bug on the G500 HSI and engage "HDG" and "ALT" modes on the

programmer/computer. 4. Select a desired radial on the navigation receiver or use the "CRS' selector on the G500.

Engage "NAV" mode on the programmer/computer and allow the aircraft time to establish on course.

5. Check roll center adjustments in "NAV" mode after system has timed out to "NAV-SOFT" and fine adjust (if necessary) to fly a centered needle. (Assuming the aircraft is already close to the desired course selection the AP should achieve "NAV-SOFT" in less than 5 minutes. See section "3.1.2 Navigation (NAV) Mode" of the S-Tec POH for further explanation of the various navigation modes and associated gain changes). Select "HDG" mode and check heading bug centered ±3°.

Note: The roll centering potentiometer is a 3 turn potentiometer and should be adjusted in very small increments. Allow sufficient time between adjustments for the system to stabilize. Clockwise rotation of the potentiometer produces right turn and counterclockwise produces left turn. Note: If the rudder is incorrectly trimmed, the autopilot will cause the aircraft to fly with a wing low in an effort to maintain the selected heading. Note: The pitch system does not require flight adjustments.


Flight Tests: The following tests may be performed in any order. 1. VS Verification:

1.1. AP in "HDG or NAV" and "VS" 1.2. Select a "VS" for 90 to 100 KIAS Note: The commanded and indicated vertical speeds should be approximately the same once the aircraft stabilizes. Caution: For a given altitude the autopilot can command vertical speeds in excess of the aircraft capabilities. This could result in the aircraft stalling. An irresolvable vertical speed will be announced by a flashing "VS". 1.3. Perform a pitch deviation of -10° and release. (This should be a "Crisp" input resulting

in an altitude change of less than 200'). The pitch oscillations should be damped in approximately 2 cycles.

1.4. Set aircraft to a 0.9 Vne, (≃ 172 KIAS), @ MCP descent. 1.5. Perform a pitch deviation of +10° and release. (This should be a "Crisp" input). The

aircraft should return to it's former attitude and the pitch oscillations should be damped in approximately 2 cycles.

2. ALT Verification: 2.1. Establish the aircraft in a stable climb, (let the aircraft stabilize but be aware of the

degradation in performance with altitude. Set a climb rate appropriate for the altitude). The commanded VS and G500 indicated VS should match.

2.2. Establish the aircraft in a stable descent, (let the aircraft stabilize). The commanded VS and G500 indicated VS should match. Do not exceed 0.9Vne or 172 KIAS.

2.3. Manually set aircraft in a trimmed normal cruise and engage autopilot in "HDG/NAV" and "ALT". Cruise for 5 minutes. In "ALT" mode the AP shall maintain an altitude tolerance of ±20 ft with a maximum excursion between plus or minus altitude over a time period of 5 minute in calm air, the results being imperceptible to the pilot.

2.4. Perform a pitch deviation of +10° deviating approximately 200 ft from altitude and release. The AP shall recover from upset within 1.5 cycles to 1/10 amplitude. Pitch corrections in altitude hold should cause imperceptible g changes.

3. Altitude Preselect, (if installed): 3.1. Set an altitude of 1000 ft above the current altitude on the G500 display. 3.2. Engage dual mode by depressing "ALT" and "VS" simultaneously.

3.3. Select a vertical speed appropriate for the aircraft's altitude, (ex. ≃500 fpm). 3.4. As the aircraft approaches the desired altitude the autopilot will automatically gradually

reduce the climb, (or descent), to 200 ft/min just before capture. Overshoot should be less than 20' with a smooth return to altitude at which time "VS" will extinguish and "ALT" shall remain.

4. Manual "ALT" Capture:


4.1. This function is performed simply by the pilot depressing the "ALT" mode switch while in the "VS" mode.

4.2. Set the aircraft into a 1500 fpm descent, ("HDG" and "VS" mode). 4.3. Once established select "ALT" at a convenient altitude. A maximum 10% overshoot is

permissible with a smooth return to the pressure altitude at time of capture. 5. HDG Verification:

5.1. Select "HDG" and "ALT" on the programmer/computer. 5.2. Rotate the heading knob, (PFD knob, (lower right on G500 display)), left 90°. 5.3. Aircraft should roll smoothly into a 90% standard rate one banked turn. 5.4. When turning to a commanded heading the aircraft should not overshoot/undershoot that

heading by more than 3 degrees. 5.5. Rotate heading bug right 90°, again, the aircraft should not overshoot/undershoot that

heading by more than 3 degrees. 5.6. Track heading bug for 5 minutes. While tracking the heading bug in smooth air the

aircraft heading should be maintained to within 2 degrees of the lubber line, (up to 5 degrees in moderate turbulence).

5.7. Perform rapid 20° roll upsets left or right and release controls. 5.8. Corrections from upsets should be smooth and without overshoot, (critically damped).

6. NAV Verification: 6.1. Place navigation receiver in GPS mode, (may be done at G500 display or at receiver). 6.2. Orient aircraft 90° to intended course. 6.3. Execute a "Direct-To" on the GPS. 6.4. Engage "NAV" twice on the autopilot. 6.5. "NAV" and "GPSS" will be displayed on the AP. 6.6. After interception, track GPS course for 10 Nm. In "NAV GPSS" mode, the AP should

have a cross track error of <0.7 Nm during enroute and approach phase. 6.7. Engage the navigation receiver in VLOC select an active signal. 6.8. Engage the autopilot in "NAV" mode. Track VOR course for 10 Nm. 6.9. The autopilot should track ± within a needle width, (or two). 6.10. Track over the VOR Station from 5Nm before to 5 Nm beyond. 6.11. The autopilot in VOR "NAV" mode should provide smooth passage with a minimum

or no roll oscillations, (wing rocking). 6.12. Turn off navigation receiver. 6.13. "NAV" will alternately flash with "FAIL", steering bars will flash, AP will track

course arrow. 6.14. Turn on navigation receiver. 6.15. Once receiver has completed self test, "NAV" will reengage, aircraft will maneuver to

intercept course. 7. Approaches:

7.1. GPS Approach: 7.1.1. Place autopilot in "GPSS" mode, (press "NAV" twice) 7.1.2. Engage navigation receiver in GPS mode. 7.1.3. While tracking a GPS signal, after CDI centers, the maximum cross-track error is

0.07Nm in smooth air, (0.12 Nm allowed in moderate turbulence).


7.1.4. A minimum two leg GPS approach shall be programmed, (ex. fly to IAF then to FAF then to the DA).

7.1.5. Turns should be anticipated with little or no overshoot. 7.2. ILS Approach:

7.2.1. Engage autopilot in "HDG" & "ALT" mode. 7.2.2. Place navigation receiver in VLOC and tuned to an active localizer. 7.2.3. Aircraft assumes a 45° intercept angle. 7.2.4. The CDI will be at full scale deflection, (this assumes that the aircraft was not

already on the course when the "NAV" function was engaged). 7.2.5. "APR" is displayed and the aircraft is on a 45° intercept to inbound course. 7.2.6. An overshoot of 50% of CDI is allowed. 7.2.7. Engage "APR". 7.2.8. CDI < 50%. 7.2.9. If aircraft is < 60% below glideslope center line for 10 seconds "GS" will be

armed and AP will display "APR" & "ALT". 7.2.10. Once established on LOC course, maximum allowable deviation in smooth air is

10% CDI deflection, (20% allowed in moderate turbulence). This evaluation should be made after the aircraft is stabilized on course for at least 3 minutes.

7.2.11. Capture of glideslope occurs when GS deviation is <50%. 7.2.12. Glideslope CDI deviations should not exceed 20% full-scale deflection except for

short excursions caused by turbulence that should be quickly resolved. Tracking quality should be maintained to the middle marker, (200' AGL)

7.3. Reverse Mode: 7.3.1. Engage autopilot in "HDG" & "ALT" mode. 7.3.2. Place navigation receiver in VLOC. 7.3.3. CDI should be at full scale deflection, (ie aircraft heading shall be other than the

BC approach. 7.3.4. Set course to inbound LOC, the aircraft should now be on an intercept course. 7.3.5. Depress the mode selector switch "REV". "REV" should be displayed. 7.3.6. In "REV" mode during a 45°intercept at cruise speeds up to 160 KIAS the

maximum allowable overshoot is 25% CDI deflection from center. Note, the intercept should be made at least 4Nm from the navigation source when evaluating intercept quality.


LOG BOOK CERTIFICATION:

1. If the Cygnet control wheels were already installed on the aircraft, upon completion of Parts

A, B, C, D, E, G, and H make an appropriate Log Book entry stating “SI 22-01, Rev 1, Parts A, B, C, D, E, G, and H accomplished”.

2. If the installer had to add the Cygnet control wheels, upon completion of Parts A to H make

an appropriate Log Book entry stating “SI 22-01, Rev 1, Parts A to H accomplished”.

SI 22-01 Auto Pilot Installation - Rev 2 Oct 29-13_Auto_Pilot_Installation.… · YAW DAMPER OVER VOLT UNDER VOLT 12 Vdc OUTLET 12 A MAX. 10 A CONT. E-GYRO Install AP Circuit Breaker

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