FORM: 2391 DRAWING NO: ICA-525-27-00005 Cessna Aircraft ...

FORM: 2391DRAWING NO: ICA-525-27-00005 Cessna Aircraft Company P.O Box 7704 WICHITA, KS 67277

ENGINEERING DRAWING AND PART LIST SIGNATURE AUTHORIZATION Originals Electronically Signed in the VPM System

================================================================================REVISION: ICA-525-27-00005 ICA ---

PKG: 0000113572 ================================================================================ ORIGINATOR (DRM) Brice Logan (APPROVE 11/22/2017 15:08:15) MAINTENANCE_ENG (ALL) Stephen Taylor (APPROVE 11/22/2017 13:53:46) ICA_COORDINATOR (ALL) Jason Peterson (APPROVE 11/22/2017 15:10:04) PROJECT (525 SERIES) Neil Hague (APPROVE 11/22/2017 14:03:23) AIRWORTHINESS (ALL) Chad Groene (APPROVE 11/22/2017 14:54:36) ODA ICA admin (ALL) Doug Carpenter (APPROVE 11/22/2017 14:30:41) ICA_COORDINATOR (ALL) Jason Peterson (APPROVE 11/22/2017 15:11:10) RELEASE (ALL) Stephanie Haymond (APPROVE 11/22/2017 15:15:59)

TEXTRON AVIATION INC.AIRCRAFT DIVISION

WICHITA, KANSAS 67277

AUTOPILOT CLAMP BLOCK IMPROVEMENTICA Supplement

MODEL NO: 525

SUPPLEMENT NO: ICA-525-27-00005SUPPLEMENT DATE: 11/22/2017

© TEXTRON AVIATION INC.Form 2261 Rev 1



REVISIONS

ICA-525-27-00005 Rev: - Date: Nov 22/2017

ICA Summary Pages 1-6

Manuals Affected Description TitleMaintenance Manual 22-10-25 pages

401- 408GARMIN RUDDER AUTOPILOT SERVO ASSEMBLY -REMOVAL/INSTALLATION

• This section contains the revised procedures for installation of the autopilot clamp blocks.

Maintenance Manual 22-10-35 pages 401- 405

GARMIN ELEVATOR AUTOPILOT SERVO ASSEMBLY- REMOVAL/INSTALLATION


Maintenance Manual 27-30-05 pages201- 214

ELEVATOR AND TAB SYSTEM CONTROL CABLES -MAINTENANCE PRACTICES


Maintenance Manual 27-30-10 pages401- 420

ELEVATOR AND TAB SYSTEM COMPONENTS -REMOVAL/INSTALLATION


Appendix A: Illustrated PartsCatalog

NOT USED

Appendix B: Wiring DiagramManual

See AttachedParts Table

NOTE 1: This change to clamp block installation and torque speciication has also revised procedures for torquespeciications of clamp blocks introduced in Airplanes -0871 thru -0971. Clamp blocks installed onAirplanes -0871 thru -0971 was 25 inch pounds to 40 inch pounds and is NOW 30 inch pounds to 40inch pounds to match new design.

1. Export ComplianceA. This publication contains technical data and is subject to U.S. export regulations. This information has

been exported from the United States in accordance with export administration regulations. Diversioncontrary to U.S. law is prohibited.

ECCN: 9E991

2. Revision BarsA. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the

released maintenance manual.• New ICAs that are not in the current maintenance manual will have a revision bar from top to

bottom along the left margin.• ICAs that are in the current maintenance manual and have information added, deleted or revised

will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information.• New or changed illustrations will have a change bar for the entire length of the page.

3. Page NumberingA. The page number system for ICA included in this supplement have three-element numbers that are

separated by dashes. The three-element number is found at the bottom right corner of the page, leftof the page number. The date is found below the page number.

Page 1 of 6Nov 22/2017

© TEXTRON AVIATION INC.ICA-525-27-00005 Form 2261 Rev 1



B. When the chapter/system element number is followed with zeros in the section/subsystem andsubject/unit element number (28-00-00), the information is applicable to the entire system.

C. When the section/subsystem element number is followed with zeros in the subject/unit elementnumber (28-21-00), the information is applicable to the subsystems in the system.

D. The subject/unit element number is used to identify information applicable to units in the subsystems.The subject/unit element number continues in sequence from the number -01- with the number ofsubsystem units in which maintenance information is necessary.

E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into speciiedtypes of information: Description and Operation, Troubleshooting, Maintenance Practices, etc.Blocks of page numbers that are in sequence are used to identify the type of information:(1) Description and Operation or Troubleshooting information may not be included if the procedure

is easy. When subtopics are short, they may be put together into the Maintenance Practicessection. Maintenance Practices can have a mix of subtopics that includes information to service,remove, install, adjust, test, clean, paint or do approved repairs.

(2) Longer procedures that are not as easy to do may be included in a speciied section.Page 1 through 99 - Description and OperationPage 101 through 199 - TroubleshootingPage 201 through 299 - Maintenance PracticesPage 301 through 399 - Servicing01 through 499 - Removal/InstallationPage 501 through 599 - Adjustment/TestPage 601 through 699 - Inspection/CheckPage 701 through 799 - Cleaning/PaintingPage 801 through 899 - Approved Repairs

F. A typical page number:

G. Illustrations use the same igure numbers as the page block in which they appear. For example, Figure202 would be the second igure in a Maintenance Practices section.





4. Supplement RevisionsA. Revisions to this supplement may be accomplished if changes to this supplement are required after

release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table.

B. All revisions to this supplement will have changes identiied in detail in the revision block(s) above.

C. All pages in this ICA supplement will have the same date and are valid as of the date shown.

5. ICA Incorporation into Applicable Manuals

NOTE: Most ICA supplements will be incorporated in the next available revision to the manualslisted above and should be used in conjunction with those manuals until the next availablerevision is released.

A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONStable will indicate the incorporation status as of the release date of the published revision.

B. The manual revision level of the supplement incorporation will be listed in the "Manual IncorporationStatus" column in the ICA Supplement List, when those ICAs associated with that manual have beenincorporated. After ICAs are incorporated, the manual that they are incorporated in must now be usedfor those ICAs instead of the supplement.• Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this

supplement may be incorporated in the manuals at different times.• There will not be a revision to this supplement to indicate incorporation in the manuals. Users are

required to check the ICA Supplement List for each manual affected to determine incorporationstatus.

C. This supplement will be completely superseded by the manuals listed in the REVISIONS table whenit has been incorporated in all of the manuals.





INTRODUCTION

1. PurposeA. The purpose of this Supplement is to provide the maintenance technician with the information

necessary to ensure the correct functionality and performance of the AUTOPILOT CLAMP BLOCKIMPROVEMENT on the Cessna Model 525 (M2) until this information gets incorporated into the nextrevision to the manuals listed in the "REVISIONS" section of this supplement.

B. This ICA supplement is designed to satisfy the requirements of 14 CFR 23.1529 "Instructions forContinued Airworthiness" associated with this installation. This document is a supplement to theModel 525 (0685 and -0800 and On) Maintenance Manual and will be incorporated in the next revisionto the manual.

C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS"section, those manuals shall take precedence over this supplemental document. Refer to the "ICASupplement List" in the "Introduction" section of the respective manual for the status of all applicableICA Supplements.

D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplementprior to incorporation into all of the affected manuals.

NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROMor Model 525 (0685 and -0800 and On) Maintenance Manual and incorporated into theoperator's scheduled maintenance program.

2. EffectivityA. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and

serialization.

Model Beginning Effectivity Ending Effectivity

525 (M2) -0972 and On

3. Complete ICA DocumentsA. The following document(s), in conjunction with this supplement, constitute the Instructions for

Continued Airworthiness for the AUTOPILOT CLAMP BLOCK IMPROVEMENT on the CessnaModel 525 (M2). All items must be available to the operator at initial delivery.(1) Model 525 (0685 and 0800 and On) Maintenance Manual

4. System ComponentsA. Refer to Appendix A: Illustrated Parts Catalog





LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 525 (0685 and 0800 and On) Maintenance ManualA. Chapter 22 Auto Flight

(1) ATA 22-10-25 Garmin Rudder Autopilot Servo Assembly - Removal/Installation(2) ATA 22-10-35 Garmin Elevator Autopilot Servo Assembly - Removal/Installation

B. Chapter 27 Flight Contols(1) ATA 27-30-05 Elevator and Tab System Control Cables - Maintenance Practices(2) ATA 27-30-10 Elevator and Tab System Components- Removal/Installation





INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection ProgramA. This ICA Supplement does not affect the current inspection program.

2. Airworthiness LimitationsA. Cessna Aircraft Company Model 525 (0685 and 0800 and On) Maintenance Manual, Chapter 4,

Airworthiness Limitations, contains the system and airframe limitations for the Model 525 (M2).

NOTE: The Airworthiness Limitations section is FAA-approved and speciies maintenancerequired under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unlessan alternative program has been FAA approved.

(1) There are no new (or additional) airworthiness limitations associated with this equipment and/orinstallation.



CESSNA®MODEL 525 (SERIALS -0685 AND -0800 AND ON)

MAINTENANCE MANUAL

GARMIN RUDDER AUTOPILOT SERVO ASSEMBLY - REMOVAL/INSTALLATION

1. GeneralA. This section gives the removal and installation procedures for the Garmin Rudder Autopilot Servo

Assembly. The Garmin Rudder Autopilot Servo Assembly includes the Garmin GSA 80 RudderAutopilot Servo Actuator and the Garmin GSM 86 Rudder Autopilot Servo Gear Box. For a generaldescription of the rudder autopilot function, refer to Auto Flight - General. For more detailedGarmin GSM 86 maintenance data refer to the GSM 86 Servo Gear Box Installation Manual P/N190-00303-83 found in the Supplier publication List.

2. Tools and EquipmentA. Refer to Chapter 22, Auto Flight - General Tools and Equipment.

3. Garmin GSA 80 Rudder Autopilot Servo Actuator (Motor) Removal/InstallationA. Remove the Rudder Autopilot Servo Actuator (Motor) (Refer to Figure 401).

(1) Remove the electrical power from the airplane.(2) Disengage the Automatic Flight Control System (AFCS) circuit breaker on the right circuit breaker

panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Remove aft baggage compartment panel 321AL to get access to the rudder autopilot servo

actuator. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(5) Disconnect the electrical connector (JT310) from the rudder autopilot servo actuator electricalconnector.

(6) Remove the bolts and the washers that attach the rudder autopilot servo actuator to the rudderautopilot servo gear box.

(7) Remove the rudder autopilot servo actuator from the rudder autopilot servo gear box and theairplane.

(8) If necessary, use a clean, lint-free cloth and remove unwanted grease buildup from the rudderautopilot servo actuator output gear.

(9) If the rudder autopilot servo actuator is not going to be installed immediately, put covers over theopenings to keep the rudder autopilot servo gear box and rudder autopilot servo actuator clean.

B. Install the Rudder Autopilot Servo Actuator (Motor) (Refer to Figure 401).(1) Remove the protective covers from the rudder autopilot servo gear box and rudder autopilot

servo actuator openings.(2) Apply a thin layer of Aeroshell 33MS grease or an equivalent to the rudder autopilot servo

actuator output gear. Refer to Chapter 22, Auto Flight - General.(3) Put the rudder autopilot servo actuator in it's correct position on the rudder autopilot servo gear

box.(4) Align the splines on the rudder autopilot servo actuator shaft with the splines in the rudder

autopilot servo gear box.(5) Starting with two opposite corner bolts, tighten all bolts until 0.01 to 0.03 Inches (0.25 to 0.76

mm) from fully seated.(6) Verify that the rudder autopilot servo actuator is still slightly loose relative to the rudder autopilot

servo gear box, ensuring there is still relative movement between the two units.(7) Starting with two opposite corner bolts, torque all bolts from 25.00 to 40.00 inch-pounds (2.82

N-m to 4.51 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(8) Connect the electrical connector (JT310) to the rudder autopilot servo actuator electrical

connector.(9) Engage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.

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(10) If a new rudder autopilot servo actuator has been installed, do the G3000 Baseline Software/Coniguration Installation. Refer to Chapter 34, Garmin Integrated Avionics System -Adjustment/Test.

NOTE: For more data applicable to the Model 525 G3000 software and conigurationuploading procedures, refer to Section 6 and Section 8 of the Garmin G3000Integrated Avionics System Line Maintenance Manual, P/N 190-01579-00, found inthe Introduction, Supplier Publication List.

(11) Do the Garmin GFC 700 AFCS Operational Test, Yaw Axis Check. Refer to Chapter 22, GarminGFC 700 AFCS - Adjustment/Test.

(12) Install the aft baggage compartment panel 321AL. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.

(13) Close the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -Description and Operation.

4. Garmin GSM 86 Rudder Autopilot Servo Gear Box (Mount) and Cables Removal/InstallationA. Remove the Rudder Autopilot Servo Gear Box (Mount) and Cables. (Refer to Figure 401).

(1) Remove the electrical power from the airplane.(2) Disengage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Remove aft baggage compartment panel 321AL to get access to the rudder autopilot servo

motor. Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.(5) Remove the rudder autopilot servo actuator. Refer to, Garmin GSA 80 Rudder Autopilot Servo

Actuator (Motor) Removal/Installation in this section.(6) For Airplanes -0685 and -0800 and On, do the steps that follow:

(a) Remove the clips from the turnbuckle that connects the rudder upper autopilot cable to theaft rudder autopilot cable. Refer to Chapter 20, Safetying - Maintenance Practices.

(b) Loosen the turnbuckle to release the cable tension.(c) Remove the rudder upper autopilot cable from the turnbuckle.(d) For Airplanes -0685 and -0800 thru -0870 that have NOT incorporating SB525-27-24, put

a mark on the rudder left aft cable that shows the clamp block position for the attachmentof the rudder lower autopilot cable to the rudder left aft cable.

NOTE: 11.4 +0.50 or -0.50 Inches (289.56 +12.70 or -12.70 mm) from the center ofthe rudder autopilot servo gear box.

(e) Loosen the clamp block screws and nuts.

NOTE: Airplanes -0685, and -0800 thru -0870 NOT incorporating SB525-27-24 use aclamp block that is attached with screws and nuts.

(f) For Airplanes -0685 and -0800 thru -0870 Incorporating SB525-27-24 and Airplanes -0871and On, remove eyebolt and cable.

(g) Remove the clips from the turnbuckle that connects the rudder upper autopilot cable to theaft rudder autopilot cable. Refer to Chapter 20, Safetying - Maintenance Practices.

(h) Loosen the turnbuckle to release the cable tension.(i) Remove the rudder upper autopilot cable from the turnbuckle.(j) Remove the bolt, washer, nut, and cotter pin from the fork end terminal that connect the

left aft rudder cable to the rudder lower autopilot cable and left middle rudder cable.(k) Remove the lower rudder autopilot cable from the left aft rudder cable.(l) Remove the lower autopilot rudder cable from the left aft rudder cable.

(7) Remove the bolts that attach the rudder autopilot servo gear box to the bracket.(8) Remove the rudder autopilot servo gear box and the cables from the airplane.(9) If the rudder autopilot servo gear box is to be replaced remove the cable as follows:

(a) Remove the screws and the washers that attach the capstan cover to the cable guard pins.1 Remove the capstan cover from the pins.


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(b) Remove the cable guard pins from the rudder autopilot servo gear box.(c) Record how the cable is installed on the capstan drum.(d) Remove the cable from the capstan drum.

1 If the servo gearbox capstan has retaining clips, the swaged ball end of the cable canbe removed by sliding the ball past the clip while pressing the retaining clip with a latscrewdriver or similar tool. Refer to, Figure 402.

B. Install the Rudder Autopilot Servo Gear Box (Mount) and Cables. (Refer to Figure 401).(1) If the rudder autopilot servo gear box has been replaced install the cables as follows:

(a) Install cables on the rudder autopilot servo gear box capstan drum as recorded.

CAUTION: Make sure the ball is fully seated in the capstan.

(b) Install the cable guard pins in the positions A, C, F, and J on the rudder autopilot servogear box.

(c) Put the capstan cover in its position on the cable guard pins.(d) Install but do not tighten the capstan cover screws and washers.(e) Start with two opposite screws, torque all the screws from 8.00 to 12.00 inch-pounds (0.90

N-m to 1.35 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(2) Put the rudder autopilot servo gear box and the cables in their position at the rudder autopilot

servo gear box bracket assembly.(a) Start with two opposite bolts, torque all the bolts from 25.00 to 40.00 inch-pounds (2.82

N-m to 4.51 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(3) For Airplanes -0685 and -0800 thru -0870 that have NOT incorporated SB525-27-24, do the

steps that follow:(a) Put the lower rudder autopilot cable in the clamp block.(b) Make sure the clamp block is aligned at the mark on the left aft rudder cable.

NOTE: 14.50 +0.50 or -0.50 Inches (368.30 +12.70 or -12.70 mm) from the center ofthe rudder autopilot servo gear box.

(c) Tighten the clamp block nuts from 12.00 to 15.00 inch-pounds (1.35 N-m to 1.69 N-m).Refer to Chapter 20, Torque Data - Maintenance Practices.

(d) Install the rudder upper autopilot cable to the turnbuckle that connects the upper rudderautopilot cable to the upper aft rudder autopilot cable.

(4) For Airplanes -0685 and -0800 thru -0870 Incorporating SB525-27-24 and airplanes -0871 andOn, do the steps that follow:(a) Install the bolt, washer, nut and cotter pin to the fork end terminal that connects the left aft

rudder cable to the rudder lower autopilot cable and left middle rudder cable.(b) Install the rudder upper autopilot cable to the turnbuckle that connects the upper rudder

autopilot cable to the upper aft rudder autopilot cable.(5) Install the rudder autopilot servo actuator. Refer to , Garmin GSA 80 Rudder Autopilot Servo

Actuator (Motor) Removal/Installation in this section.(6) Tighten the rudder servo cable turnbuckle to the correct cable tension. Refer to Chapter 27,

Rudder and Tab System - Adjustment/Test, Figure 502.(7) Install the clips on the turnbuckle. Refer to Chapter 20, Safetying - Maintenance Practices.(8) Engage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.(9) If the rudder autopilot servo gear box and the rudder autopilot servo actuator were replaced new

as an assembly, do the G3000 Baseline Software/Coniguration Installation. Refer to Chapter34, Garmin Integrated Avionics System - Adjustment/Test.


(10) Do the Garmin GFC 700 AFCS Operational Test, Yaw Axis Check. Refer to Chapter 22, GarminGFC 700 AFCS - Adjustment/Test.


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(11) Install the aft baggage compartment panel 321AL. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.



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Garmin Rudder Autopilot Servo AssemblyFigure 401 (Sheet 1)


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Swaged Ball from 3/32" Spiral Wrap CapstanFigure 402 (Sheet 1)


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GARMIN ELEVATOR AUTOPILOT SERVO ASSEMBLY - REMOVAL/INSTALLATION

1. GeneralA. This section gives the removal and installation procedures for the Garmin Elevator Autopilot Servo

Assembly. The Garmin Elevator Autopilot Servo Assembly includes the Garmin GSA 81 ElevatorAutopilot Servo Actuator and the Garmin GSM 86 Elevator Autopilot Servo Gear Box. For a generaldescription of the elevator autopilot function, refer to Auto Flight - General. For more detailedmaintenance data, refer to the GSM 86 Servo Gear Box Installation Manual P/N 190-00303-83 foundin the Supplier publication List.

2. Tools and EquipmentA. Refer to Chapter 22, Auto Flight - General Tools and Equipment.

3. Garmin GSA 81 Elevator Autopilot Servo Actuator (Motor) Removal/InstallationA. Remove the Elevator Autopilot Servo Actuator (Motor) (Refer to Figure 401).

(1) Remove the electrical power from the airplane.(2) Disengage the Automatic Flight Control System (AFCS) circuit breaker on the right circuit breaker

panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Remove aft baggage compartment panel 321AL to get access to the elevator autopilot servo

actuator. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(5) Disconnect the electrical connector (JT311) from the elevator autopilot servo actuator electricalconnector.

(6) Remove the bolts and the washers that attach the elevator autopilot servo actuator to the elevatorautopilot servo gear box.

(7) Remove the elevator autopilot servo actuator from the elevator autopilot servo gear box and theairplane.

(8) If necessary, use a clean, lint-free cloth and remove unwanted grease buildup from the elevatorautopilot servo actuator output gear.

(9) If the elevator autopilot servo actuator is not going to be installed immediately, put covers overthe openings to keep the elevator autopilot servo gear box and elevator autopilot servo actuatorclean.

B. Install the Elevator Autopilot Servo Actuator (Motor) (Refer to Figure 401).(1) Remove the protective covers from the elevator autopilot servo gear box and elevator autopilot

servo actuator openings.(2) Apply a thin layer of Aeroshell 33MS grease or an equivalent to the elevator autopilot servo

actuator output gear. Refer to Chapter 22, Auto Flight - General.(3) Put the elevator autopilot servo actuator in it's correct position on the elevator autopilot servo

gear box.(4) Align the splines on the elevator autopilot servo actuator shaft with the splines in the elevator

autopilot servo gear box.(5) Starting with two opposite corner bolts, tighten all bolts until 0.01 to 0.03 Inches (0.25 to 0.76

mm) from fully seated.(6) Verify that the rudder autopilot servo actuator is still slightly loose relative to the rudder autopilot

servo gear box, ensuring there is still relative movement between the two units.(7) Starting with two opposite corner bolts, torque all bolts from 25.00 to 40.00 inch-pounds (2.82

N-m to 4.51 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(8) Connect the electrical connector (JT311) to the elevator autopilot servo actuator electrical

connector.(9) Engage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.


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(10) If a new elevator autopilot servo actuator has been installed, do the G3000 Baseline Software/Coniguration Installation. Refer to Chapter 34, Garmin Integrated Avionics System -Adjustment/Test.


(11) Do the Garmin GFC 700 AFCS Operational Test, Pitch Axis Check. Refer to Chapter 22, GarminGFC 700 AFCS - Adjustment/Test.

(12) Install aft baggage compartment panel 321AL. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.


4. Garmin GSM 86 Elevator Autopilot Servo Gear Box (Mount) and Cables Removal/InstallationA. Remove the Elevator Autopilot Servo Gear Box (Mount) and Cables (Refer to Figure 401).

(1) Remove the electrical power from the airplane.(2) Disengage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Remove aft baggage compartment panel 321AL to get access to the elevator autopilot servo

mount and cable. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(5) Remove the elevator autopilot servo actuator. Refer to, Garmin GSA 81 Elevator Autopilot ServoActuator (Motor) Removal/Installation in this section.

(6) For Airplanes -0685 and -0800 and On, do the steps that follow:(a) Remove the clips from the turnbuckle that connects the elevator upper autopilot cable to the

upper elevator aft autopilot cable. Refer to Chapter 20, Safetying - Maintenance Practices.(b) Loosen the turnbuckle to release the cable tension.(c) Remove the elevator upper autopilot cable from the turnbuckle.(d) Put a mark on the elevator left aft cable that shows the clamp block position for the

attachment of the elevator lower autopilot cable to the elevator left aft cable.

NOTE: 11.4 +0.50 or -0.50 Inches (289.56 +12.70 or -12.70 mm) from the center ofthe elevator autopilot servo gear box.

(e) Loosen the clamp block screws/nuts.

NOTE: Airplanes -0685, and -0800 thru -0870 use a clamp block that is attachedwith screws and nuts.

NOTE: Airplanes -0871 and On use a clamp block that is attached with screws onthreaded clamp block half.

(f) Remove the elevator lower autopilot cable from the elevator left aft cable.(7) Remove the bolts that attach the elevator autopilot servo gear box to the bracket.(8) Remove the elevator autopilot servo gear box and the cables from the airplane.(9) If the elevator autopilot servo gear box is to be replaced remove the cable as follows:

(a) Remove the screws and the washers that attach the capstan cover to the cable guard pins.1 Remove the capstan cover from the pins.

(b) Remove the cable guard pins from the elevator autopilot servo gear box.(c) Record how the cable is installed on the capstan drum.(d) Remove the cable from the capstan drum.

1 If the servo gearbox capstan has retaining clips, the swaged ball end of the cable canbe removed by sliding the ball past the clip while pressing the retaining clip with a latscrewdriver or similar tool. Refer to, Figure 402.


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B. Install the Elevator Autopilot Servo Gear Box (Refer to Figure 401).(1) If the elevator autopilot servo gear box has been replaced install the cables as follows:

(a) Install cables on the elevator autopilot servo gear box capstan drum as recorded.

CAUTION: Make sure the ball is fully seated in the capstan.

(b) Install the cable guard pins in the positions A, C, F, and J on the elevator autopilot servogear box.

(c) Put the capstan cover in its position on the cable guard pins.(d) Install but do not tighten the capstan cover screws and washers.(e) Start with two opposite screws, torque all the screws from 8.00 to 12.00 inch-pounds (0.90

N-m to 1.35 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(2) Put the elevator autopilot servo gear box and the cables in their position at the elevator autopilot

servo gear box bracket assembly.(a) Start with two opposite bolts, torque all the bolts from 25.00 to 40.00 inch-pounds (2.82

N-m to 4.51 N-m). Refer to Chapter 20, Torque Data - Maintenance Practices.(3) Put the elevator lower autopilot cable in the clamp block.(4) Make sure the clamp block is aligned at the mark on the elevator left aft cable.

NOTE: 11.4 +0.50 or -0.50 Inches (289.56 +12.70 or -12.70 mm) from the center of theelevator autopilot servo gear box.

NOTE: Airplanes -0685, and -0800 thru -0870 use a clamp block that is attached withscrews and nuts.

NOTE: Airplanes -0871 and On use a clamp block that is attached with screws on threadedclamp block half.

(a) Airplanes -0685 and -0800 thru -0870, tighten the clamp block nuts from 12.00 and 15.00inch-pounds (1.35 N-m to 1.69 N-m).

(b) Airplanes -0871 and On, tighten the clamp block nuts from 30-40 inch pounds (3.39 N-mto 4.51 N-m)

(c) Install the elevator upper autopilot cable to the turnbuckle that connects the elevator upperautopilot cable to the upper elevator aft autopilot cable.

(5) Install the elevator autopilot servo actuator. Refer to , Garmin GSA 81 Elevator Autopilot ServoActuator (Motor) Removal/Installation in this section.

(6) Tighten the elevator autopilot servo cable turnbuckle to the correct cable tension. Refer toElevator and Tab System Control Cables - Adjustment/Test, Figure 502.

(7) Install the clips on the turnbuckle. Refer to Chapter 20, Safetying - Maintenance Practices.(8) Engage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.(9) If the elevator autopilot servo gear box and the elevator autopilot servo actuator were replaced

new as an assembly, do the G3000 Baseline Software/Coniguration Installation. Refer toChapter 34, Garmin Integrated Avionics System - Adjustment/Test.


(10) Do the Garmin GFC 700 AFCS Operational Test, Pitch Axis Check. Refer to Chapter 22, GarminGFC 700 AFCS - Adjustment/Test.

(11) Install aft baggage compartment panel 321AL. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.



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Garmin Elevator Autopilot Servo AssemblyFigure 401 (Sheet 1)


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Swaged Ball from 3/32" Spiral Wrap CapstanFigure 402 (Sheet 1)


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ELEVATOR AND TAB SYSTEM CONTROL CABLES - MAINTENANCE PRACTICES

1. GeneralA. Refer to Elevator and Tab System Components - Removal/Installation for elevator and tab components

not covered in this section.

B. Refer to Chapter 55, Elevator - Removal/Installation for removal, installation and maintenance of theelevator.

2. Tools and EquipmentA. For a list of necessary tools and equipment, refer to Flight Controls - General.

3. Elevator Forward Control Cables Removal/InstallationA. Remove the Forward Control Cables (Refer to Figure 201).

(1) Remove the pilot and copilot seats. Refer to Chapter 25, Crew Seats - Maintenance Practices.(2) Remove panels 241BTC , 252ATC, 252BTC, 252CTC, 252DTC, 252GC, and 251FL to get

access to the forward control cables. Refer to Chapter 6, Access Plates and Panels Identiication- Description and Operation.

(3) Remove the aft evaporator to get access to the pressure seals on the aft pressure bulkhead.Refer to Chapter 21, Cooling System - Maintenance Practices.

(4) Remove screws, washers and nuts attaching the upper left fairlead to the forward control cablesat FS 208.67 and FS 249.16, and remove the fairleads.

(5) Enter aft baggage compartment.(6) Remove panels 321A, 321AZ, 321BB, 321CB, 321DC and 321FC to get access to the forward

control cables. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(7) Remove the clips and loosen the turnbuckle for the elevator autopilot servo cable. Refer toChapter 22, Garmin Elevator Autopilot Servo Assembly - Removal/Installation.

(8) Remove the clips and disconnect the forward control cable turnbuckles at FS 339.55 and FS355.74 from the aft control cables.

(9) Remove the guard pins from the pulley brackets at FS 131.50 and FS 147.00 in the cabin andFS 313.44 in the tailcone.

(10) Remove the spring retainers and the pressure seals at the aft pressure bulkhead (FS 285.00).(11) Remove the fairlead halves from the cable tubes for the forward elevator control cables at the

control lock slide assembly. Refer to Control Lock System - Maintenance Practices.(12) Remove the nuts, washers and screws attaching the forward control cables to the forward

elevator sector at FS 126.00.(13) Pull the cables forward and remove the control cables from airplane.(14) If a removed cable will be replaced with a new cable, record the distance of the swaged ball from

the forward ball end on the cable.

NOTE: This distance measurement will be used to locate the ball on the new cable beforeit is installed.

B. Install the Elevator Forward Control Cables (Refer to Figure 201).

NOTE: The left forward control cable is approximately 17 inches (0.43 m) longer than the rightforward control cable. The ball ends of the left and right forward control cables are nottypical.

(1) If a new forward elevator control cable is installed, put the swage ball at the recorded distancefrom the forward ball end on the cable.

NOTE: The recorded distance was measured during the last step of the removal of theinitial cable.

(a) Use a 1/8 inch (3.18 mm) cable die to swage the ball in position.


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Elevator Control Cables InstallationFigure 201 (Sheet 1)


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(2) Attach the left forward control cable to forward sector at FS 126.00 with a screw, washer andnut.

(3) Route the left forward control cable aft through the forward pulley (FS 131.50), control lock,fairleads (FS 208.67 and FS 249.16) and the aft pressure bulkhead.

(4) Attach the right forward control cable to the forward sector at FS 126.00 with a screw, washerand nut.

(5) Route the right forward control cable aft through the forward pulley (FS 131.50), control lock,fairleads (FS 208.67 and FS 249.16) and aft pressure bulkhead.

(6) Mark the forward control cables where the cable contacts the aft pressure bulkhead.(7) Withdraw the forward control cables 12 inches (30 cm) into cabin.(8) Locate the mark made earlier on the forward control cables, and lubricate them with 5565450-28

grease 6 inches (0.15 m) on both sides of the mark.(9) Install the fairlead halves to the cable tubes for the forward elevator control cables at the control

lock slide assembly. Refer to Control Lock System - Maintenance Practices.(10) Install the pressure seals in the aft pressure bulkhead using spring retainers.(11) In the tailcone, route the forward control cables through pulleys at FS 313.44 and connect to the

mating control cable turnbuckles.(12) Install the guard pins in the pulley brackets at FS 131.50 and FS 147.00 in the cabin, and FS

313.44 in the tailcone.(13) Install fairleads, screws, washers and nuts at FS 208.67 and FS 249.16.(14) Adjust control cables for correct rigging. Refer to Control Cables Adjustment.(15) Install the aft evaporator. Refer to Chapter 21, Cooling System - Maintenance Practices.(16) Install panels 241BTC, 252ATC, 252BTC, 252CTC, 252DTC, 252GC, and 251FL, and 525GR.

Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.(17) Install tailcone baggage panels 321A, 321AZ, 321BB, 321CB, 321DC and 321FC. Refer to

Chapter 6, Access Plates and Panels Identiication - Description and Operation.(18) Install the pilot and copilot seats. Refer to Chapter 25, Crew Seats - Maintenance Practices.

4. Elevator Aft Control Cables Removal/InstallationA. Remove Elevator Aft Control Cables (Refer to Figure 201).

(1) Remove panels 340ATC, 340BL, 340BR, 340CR, 340CL, 340DL and 340ER to get access tothe aft control cables. Refer to Chapter 6, Access Plates and Panels Identiication - Descriptionand Operation.

(2) Remove aft evaporator. Refer to Chapter 21, Cooling System - Maintenance Practices.(3) Open the aft baggage compartment door.(4) Remove tailcone baggage panels 321CB, 321BC, 321DC, 321FC and 321GC to get access to

the aft control cables. Refer to Chapter 6, Access Plates and Panels Identiication - Descriptionand Operation.

(5) Remove the clips and loosen the autopilot elevator servo cable turnbuckle on the left aft controlcable.

(6) Remove the clips and disconnect the aft control cable turnbuckles (FS 339.55 and FS 355.74)to release the aft control cables from the forward control cables.

(7) On airplanes 0685, -0800 thru -0870 with clamp block connection:(a) Put a mark at the two clamp blocks to show the correct position on the elevator trim cables.(b) Remove the screws, washers, and nuts that attach the clamp blocks to the elevator trim

servo cables and the elevator trim cables.(c) Remove the clamp blocks from the cables.

(8) Airplanes -0871 and On with clamp block connection, do the steps that follow:(a) Put a mark at the two clamp blocks to show the correct position on the elevator trim cables.(b) Remove the screws that attach the clamp blocks to the elevator trim servo cables and the

elevator trim cables.(c) Remove the clamp blocks from the cables.

(9) On airplanes -0685, -0800 and On, with eyebolt connection:(a) Remove bolt, washer, nut, and cotter key from the elevator trim cables.

(10) Remove the bolts and the washers that attach the fairleads and the retainers to the verticalstabilizer ribs at VFS 79.50 and VFS 105.60.(a) Remove the fairleads and the retainers from the airplane.


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(11) Remove the guard pins attaching the aft control cables pulley brackets at FS 387.00 and FS424.07.

(12) Remove the nuts, washers and screws attaching the aft control cables to the elevator aft sector.(13) Withdraw the cables and remove from the airplane.

B. Install Elevator Aft Control Cables (Refer to Figure 201).

NOTE: The right aft control cable is 17 inches (0.43 m) longer than the left aft control cable. Theball ends of the left and right aft control cables are not typical.

(1) Attach the left aft control cable to the left forward cable turnbuckle. Do not tighten turnbuckle.(2) Route the cable aft through the pulleys (FS 387.00 and FS 424.07) to the aft elevator sector.(3) Attach the control cable to the aft sector assembly using a screw, washer and nut.(4) Attach the right aft control cable to the aft elevator sector with a screw, washer and nut.(5) Route the right aft control cable forward through the pulleys (FS 424.07 and FS 387.00) to the

right forward control cable turnbuckle.(6) Connect the right forward control cable and the right aft control cables at the turnbuckle (FS

339.55).(7) Airplanes -0685 and -0800 thru -0870 with clamp block connection do the steps that follow:

CAUTION: The clamp blocks and the nuts must be installed in the correctposition to make sure that they do not catch on the adjacentcables or structure. Damage to the cables or the structure canoccur if the cables or the nuts are not installed in the correctposition.

(a) Put the elevator auto pilot servo cables and the clamp blocks in their recorded position onthe elevator trim cables.

(b) Install clamp block screws and nuts.(c) Torque the clamp block nuts to 12-15 inch pounds (1.35 N-m to 1.69 N-m).

(8) Airplanes -0871 and On with clamp block connection, do the steps that follow:(a) Put the elevator autopilot servo cables and the clamp blocks in their recorded position on

the elevator trim cables.(b) Make sure lush side of clamp block is installed to provide the largest amount of clearance

between the control cables.(c) Install clamp block screws and torque to 30-40 inch pounds (3.39 N-m to 4.51 N-m).

(9) On airplanes -0685, and -0800 and On, with eyebolt connection:(a) Install bolt, washer, nut, and cotter key to the elevator trim cables.

(10) Install the guard pins in the pulley brackets at FS 387.00 and FS 424.07.(11) Put the fairleads and the retainers in their position on the vertical stabilizer ribs at VFS 79.50

and VFS 105.60.

NOTE: The fairlead and the retainer bolt holes are larger than the bolts to help move themto make sure that they do not touch the control cables.

(a) Install the bolts and the washers.

NOTE: The bolts will be removed and have sealant applied to the threads after theinal adjustment of the cables.

(12) Adjust the trim system for correct rigging. Refer to Elevator and Tab System Control Cables -Adjustment/Test, Elevator Trim Cables Rigging

(13) Remove one of the bolts and the washers that attach the fairleads and the retainers to the verticalstabilizer ribs at VFS 79.50 and VFS 105.60.


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CAUTION: Be careful to not move the fairlead or the retainer from theirposition on the vertical stabilizer rib. The fairlead and the retainerare installed in a position to make sure that they do not cause anunwanted movement of the cables.

(14) Shank seal the bolt with Type X, Class B sealant. Refer to Chapter 20, Fuel, Weather, Pressure,and High-Temperature Sealing - Maintenance Practices.(a) Install the bolt and the washer.(b) Do the steps again for the other bolts.

(15) Install the aft evaporator. Refer to Chapter 21, Cooling System - Maintenance Practices.(16) Install panels 321CB, 321BC, 321DC, 321FC and 321GC. Refer to Chapter 6, Access Plates

and Panels Identiication - Description and Operation.(17) Install panels 340ATC, 340BL, 340BR, 340CR, 340CL, 340DL and 340ER. Refer to Chapter 6,

Access Plates and Panels Identiication - Description and Operation.

5. Elevator Forward Trim Cables Removal/Installation

NOTE: The forward trim cables have a chain installed between two cables. The left and right forwardtrim cables extend from their connecting point with the trim chain below the control pedestal,through pulleys and fairleads, to interconnecting turnbuckles in the tailcone.

A. Remove the Forward Trim Cables (Refer to Figure 202).(1) Remove panels 241BTC,, and 252ATC, 252BTC, 252CTC, 252DTC, 252GC, 252GR, and

251FL to get access to the forward trim cables. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.

(2) Remove vertical stabilizer panels 340BL and 340BR to get access to the aft elevator sector.Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.

(3) Install a #10 rigging pin in the aft elevator sector or put an approved clamp on the elevator hornto the horizontal stabilizer to hold the elevator in a ixed position.

(4) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -Description and Operation.

(5) Remove panels 321A, 321CTC, 321DC and 321FC to get access to the forward trim cablesin the tailcone. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(6) Install an inclinometer on the left elevator and the left elevator trim tab.(7) Use the pitch trim wheel in the cockpit to manually move the elevator trim tabs 4 degrees (+1 or

-1 degree) down from the streamlined position.

NOTE: When the elevator trim tabs are at the 4 degree down from streamline position, thechains will be equal on each side of the trim tab actuator sprockets and the elevatortrim sprocket in the pedestal in the cockpit.

(8) Disengage PITCH TRIM circuit breaker.(9) Remove the pilot's crew seat. Refer to Chapter 25, Crew Seats - Maintenance Practices.(10) Remove the aft evaporator to get access to the pressure seals on the aft pressure bulkhead.

Refer to Chapter 21, Cooling System - Maintenance Practices.(11) Remove screws, washers and nuts attaching the upper left fairlead to the forward control cables

at FS 208.67 and FS 249.16, and remove the fairleads.(12) Remove the clips and loosen the turnbuckle for the elevator trim servo cable. Refer to Elevator

and Tab System Components - Removal/Installation, Garmin GSM 86 Elevator Trim ServoGearbox and Cable Removal/Installation.

(13) Remove the clips and disconnect the cables at the turnbuckles located in the tailcone.(14) Remove the guard pins from the pulley brackets throughout cable routing.(15) Remove the spring retainers from the pressure seals in the aft pressure bulkhead.(16) Loosen and remove the stop blocks from the forward trim cables.(17) Route the cables forward through the aft pressure bulkhead, through fuselage pulleys to control

pedestal.


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Elevator Forward/Aft Trim Cables InstallationFigure 202 (Sheet 1)


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(18) Remove the spring clips from the connecting links that attach the left and right trim cables to thetrim control chain.(a) Remove the connecting links from the trim control chain and cables.

B. Install the Forward Trim Cable.

NOTE: The right forward trim cable is approximately 23 inches (0.58 m) longer than the leftforward trim cable.

(1) Mark the center of the trim cable chain.(2) Put the center mark of the trim chain over the top chain pulley. The top chain pulley is located

directly behind the elevator trim wheel.

NOTE: With the elevator tab at the 4 degree down position, the ends of the chain mustbe within 1 link of equal.

(3) Put the connecting links in their position on the left and the right forward elevator trim cables andthe elevator trim control chain.

(4) Install the spring clips on the connecting link.(5) Route the right half of the trim cable under the upper elevator trim pulley.

(a) Install two guard pins to keep the cable on the pulley.(6) Route the left half of the trim cable over the lower elevator trim pulley.

(a) Install two guard pins to keep the cable on the pulley.(7) Route the cables aft through the fuselage pulley assemblies and fairleads at FS 208.67 and FS

249.16.(8) Put the forward trim cables through the aft pressure bulkhead seals.(9) Mark the cables at the point where they go through the aft pressure bulkhead.(10) Lubricate forward trim cables using 5565450-28 grease, 12 inches (0.30 m) on both sides of

cable mark made earlier.(11) Install aft pressure bulkhead seals with forward trim cables through aft pressure bulkhead.(12) Put spring retainers on the seal to keep seal in place.(13) Install the fairleads at FS 208.67 and FS 249.16 using screws, washers and nuts.(14) Route the forward trim cables upward, along the aft pressure bulkhead to the upper trim cable

pulley bracket assembly.(15) Attach the forward trim cable to the aft trim cables at the turnbuckles.(16) Install the guard pins in the tailcone trim cable pulleys.(17) Adjust the trim system for correct rigging. Refer to Elevator and Tab System Control Cables -

Adjustment/Test, Elevator Trim Cables Rigging(18) Install the aft evaporator. Refer to Chapter 21, Cooling System - Maintenance Practices.(19) Remove the rigging pin from the aft elevator sector or the clamp from the elevator horn.(20) Remove the inclinometers from the left elevator and trim tab.(21) Install vertical stabilizer panels 340BL and 340BR. Refer to Chapter 6, Access Plates and Panels

Identiication - Description and Operation.(22) Install 241BTC,, and 252ATC, 252BTC, 252CTC, 252DTC, 252GC, 252GR, and 251FL. Refer

to Chapter 6, Access Plates and Panels Identiication - Description and Operation.(23) Install panels 321A, 321CTC, 321DC and 321FC. Refer to Chapter 6, Access Plates and Panels

Identiication - Description and Operation.(24) Close the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(25) Install the pilot's crew seat. Refer to Chapter 25, Crew Seats - Maintenance Practices.

6. Elevator Aft Trim Cables and Trim Interconnect Cable Removal/InstallationA. Remove the Elevator Aft Trim Cables and Trim Interconnect Cable (Refer to Figure 202).

(1) Disengage the PITCH TRIM circuit breaker.(2) Remove panels 340ATC, 340BL, 340BR, 340CR, 340CL, 340DL and 340ER. panels 331AB,

and 322AB to get access to the vertical stabilizer trim cables. Refer to Chapter 6, Access Platesand Panels Identiication - Description and Operation.


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(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -Description and Operation.

(4) Remove panels321CB, 321CTC, 322BC, 321DC, 321FC and 321GC to get access to the aft trimcables. Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.

(5) Remove vertical stabilizer panels 340BL and 340BR to get access to the aft elevator sector.Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.

(6) Install a #10 rigging pin in the aft elevator sector or put an approved clamp on the elevator hornto the horizontal stabilizer to hold the elevator in a ixed position.

(7) Install an inclinometer on the left elevator and the left elevator trim tab.(8) Use the pitch trim wheel in the cockpit to manually move the elevator trim tabs 4 degrees (+1 or

-1 degree) down from the streamlined position.

NOTE: When the elevator trim tabs are at the 4 degree down from streamline position, thechains will be equal on each side of the trim tab actuator sprockets and the elevatortrim sprocket in the pedestal in the cockpit.

(9) Remove the guard pins from the tailcone pulley bracket assemblies.(10) Tag the elevator electric trim cables and forward trim cables.(11) Remove the bolts and the washers that attach the fairleads and the retainers to the vertical

stabilizer ribs at VFS 79.50 and VFS 118.80.(a) Remove the fairleads and the retainers from the airplane.

(12) Mark the location of the clamp blocks.(13) Remove the clamp blocks attaching the elevator electric trim cables to the aft elevator trim

cables.

NOTE: Airplanes -0685 and -0800 thru -0971 use clamp blocks that attach with screwsand nuts.

NOTE: Airplanes -0972 and On use clamp blocks that attach with screws to a threadedclamp block half.

(14) Disconnect the electric trim cables.(15) Disconnect the aft trim cables from the forward trim cables at the interconnecting turnbuckles.(16) Remove the spring clips from the connecting links that attach the aft trim cables and the trim

interconnect cable to the elevator trim actuator chains.(a) Remove the connecting links.

(17) Remove the aft trim cables and the trim interconnect cable from the airplane.

B. Install the Elevator Aft Trim Cables and Trim Interconnect Cable (Refer to Figure 202).

NOTE: The left aft trim cable is approximately 20 inches (0.50 m) longer than the right aft trimcable.

(1) Put the aft trim cables and the trim interconnect cable in their position at the elevator trim actuatorchains.

(2) Put the connecting links in their position on the aft trim cables, trim interconnect cable, andelevator trim actuator chains.(a) Install the spring clips.(b) Make sure that the spring clips are fully installed in the groove cuts.

(3) Route the aft trim cables from the horizontal stabilizer, through the vertical in, pulleys and tointerconnecting turnbuckles.

(4) Connect the cables at the turnbuckles.


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CAUTION: Use the same style clamp block that was removed

(5) Attach the elevator electric trim cables to the aft trim cables, using clamp blocks.

NOTE: Airplanes -0685 and -0800 thru -0971 use clamp blocks that attach with screwsand nuts.

NOTE: Airplanes -0972 and On use clamp blocks that attach with screws to a threadedclamp block half.

(6) Airplanes -0685 and -0800 thru -0971, torque the clamp block nuts to 12-15 inch pounds (1.35N-m to 1.69 N-m).

(7) Airplanes -0972 and On, install clamp block screws and torque to 30-40 inch pounds (3.39 N-mto 4.51 N-m)

(8) Install the guard pins to keep the aft trim cables in the tailcone pulley bracket assemblies.(9) Put the fairleads and the retainers in their position on the vertical stabilizer ribs at VFS 79.50

and VFS 118.80.

NOTE: The fairlead and the retainer bolt holes are larger than the bolts to help move themto make sure that they do not touch the control cables.

(a) Install the bolts and the washers.(10) Adjust the trim system for correct rigging. Refer to Elevator and Tab System Control Cables -

Adjustment/Test, Elevator Trim Cables Rigging(11) Remove one of the bolts and the washers that attach the fairleads and the retainers to the vertical

stabilizer ribs at VFS 79.50 and VFS 118.80.

CAUTION: Be careful to not move the fairlead or the retainer from theirposition on the vertical stabilizer rib. The fairlead and the retainerare installed in a position to make sure that they do not cause anunwanted movement of the cables.

(12) Shank seal the bolt with Type X, Class B sealant. Refer to Chapter 20, Fuel, Weather, Pressure,and High-Temperature Sealing - Maintenance Practices.(a) Install the bolt and the washer.(b) Do the steps again for the other bolts.

(13) Remove the rigging pin from the aft elevator sector or the clamp from the elevator horn.(14) Remove the inclinometers from the left elevator and trim tab.(15) Install vertical stabilizer panels 340BL and 340BR. Refer to Chapter 6, Access Plates and Panels

Identiication - Description and Operation.(16) Install panels 340ATC, 340BL, 340BR, 340CR, 340CL, 340DL and 340ER, panels 331AB, and

322AB . Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.(17) Install panels 321CB, 321BC, 321DC, 321FC and 321GC. Refer to Chapter 6, Access Plates

and Panels Identiication - Description and Operation.


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ELEVATOR AND TAB SYSTEM COMPONENTS - REMOVAL/INSTALLATION

1. GeneralA. This section provides information relating to the removal and installation of components associated

with the elevator and elevator trim tab systems. For control cable removal/installation and rigginginformation, refer to Elevator and Tab System Control Cables - Maintenance Practices.

B. For removal and installation of the elevator, refer to Chapter 55, Elevator - Removal/Installation .

2. Tools and EquipmentA. For a list of tools and equipment, refer to Flight Controls - General.

3. Forward Elevator Sector Assembly Removal/InstallationA. Remove the Forward Elevator Sector Assembly (Refer to Figure 401).

(1) Remove copilots seat. Refer to Chapter 25, Crew Seats - Maintenance Practices.(2) Gain access to the forward elevator sector by removing panel 241BTC. Refer to Chapter 6,

Access Plates and Panels Identiication - Description and Operation.(3) Gain access to the elevator control cable turnbuckles in the tailcone by removing panels 321BC

and 321FC. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(4) Disconnect the elevator forward trim cables from the chain at the control pedestal in the cockpit.Refer to Elevator and Tab System Control Cables - Maintenance Practices, Elevator ForwardTrim Cables Removal/Installation .

(5) Disconnect the rudder forward trim control cables from the chain at the control pedestal in thecockpit. Refer to Rudder and Tab System - Maintenance Practices, Rudder Trim Tab ControlCables and Stop Blocks Removal/Installation.

(6) Disconnect the fuselage aileron trim cables from the chain at the control pedestal in the cockpit.Refer to Aileron and Tab System Control Cables - Maintenance Practices, Fuselage Aileron TrimCable Removal/Installation .

(7) Remove safety clips and loosen elevator control cable turnbuckles.(8) Remove nuts, washers and screws securing elevator control cables to forward sector.(9) Tag and disconnect elevator control cables.

CAUTION: Be careful to prevent damage to the avionics displays when youdisconnect the connecting link from the forward elevator sector.The control column can fall forward and damage the displays ifprotective pads or foam covers are not installed on the avionicsdisplays.

(10) Put a protective pad or foam cover on the avionics displays.(11) Remove and discard the cotter pin from the nut and the bolt that connect the forward elevator

connecting link to the forward elevator sector.(a) Remove the nut, washers, and bolt and carefully move the control columns forward as you

disconnect the connecting link from the sector.(12) Remove the aft pedestal switch panel to get access to the aileron trim gearbox. Refer to Chapter

31, Instrument and Switch Panels - Maintenance Practices, Aft Pedestal Switch Panel Removal/Installation.

(13) Remove the screws, washers, and nuts that attach the aileron trim gearbox to the pedestalstructure.

(14) Remove the screws that attach the rudder trim gearbox to the pedestal structure.(15) Remove the screws that attach the trim bearing plate to the upper sector bracket.(16) Lift the sprockets suficiently to pull the bearing plate away from the upper sector bracket.

(a) Remove the bearing plate from the airplane.(17) Remove screws securing stop block to upper and lower sector brackets.(18) Remove safety wire, pivot bolt and washers securing sector assembly to upper and lower sector

brackets.


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Forward Elevator Sector InstallationFigure 401 (Sheet 1)


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(19) Remove screws securing upper sector bracket to lower sector bracket. Remove upper sectorbracket and stop block.

(20) Remove elevator sector from airplane.

B. Install the Forward Elevator Sector Assembly (Refer to Figure 401.).(1) Position forward elevator sector assembly in its position on the lower sector bracket.(2) Put the NAS43DD6-29 spacer on top of the forward elevator sector assembly bearing.(3) Put the upper sector bracket in its position on the forward elevator sector.

(a) Loosely install the pivot bolt with the washer through the upper sector bracket, spacer,forward elevator sector, and lower sector bracket.

(4) Put the stop block in its position between the upper and lower sector bracket.(a) Loosely install the screws that attach the stop block to the upper and lower sector brackets.

(5) Install the screws that attach the upper sector bracket to the lower sector bracket.(6) Tighten the screws that attach the stop block to the upper and lower sector brackets.(7) Tighten the pivot bolt.

(a) Safety the pivot bolt with safety wire. Refer to Chapter 20, Safetying - MaintenancePractices, Safety Wire Installation.

(8) Install elevator cables to elevator sector assembly using screws, washers and nuts.(9) Loosely put the trim bearing plate assembly, aileron sprocket, and rudder trim sprocket in their

position on the upper sector bracket.(a) Make sure that the chains are in their correct routing positions on the sprockets.(b) Install the screws that attach the trim bearing plate assembly to the upper sector bracket.

(10) Put the rudder trim gearbox in its position on the pedestal structure.(a) Install the screws.

(11) Put the aileron trim gearbox in its position on the pedestal structure.(a) Install the screws, washers, and nuts.

(12) Connect the fuselage aileron trim cables to the chain at the control pedestal in the cockpit. Referto Aileron and Tab System Control Cables - Maintenance Practices, Fuselage Aileron Trim CableRemoval/Installation .

(13) Connect the rudder forward trim control cables to the chain at the control pedestal in the cockpit.Refer to Rudder and Tab System - Maintenance Practices, Rudder Trim Tab Control Cables andStop Blocks Removal/Installation.

(14) Connect the elevator forward trim cables to the chain at the control pedestal in the cockpit. Referto Elevator and Tab System Control Cables - Maintenance Practices, Elevator Forward TrimCables Removal/Installation .

(15) Attach the control column connecting link to elevator sector assembly using bolt, washers, nutand cotter pin. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter Pin Installation.

(16) Do the rigging of the elevator control system cables and the adjust stop blocks. Refer to Elevatorand Tab System Control Cables - Adjustment/Test.

(17) Install the aft pedestal switch panel. Refer to Chapter 31, Instrument and Switch Panels -Maintenance Practices, Aft Pedestal Switch Panel Removal/Installation .

(18) Install panels 321BC and 321FC. Refer to Chapter 6, Access Plates and Panels Identiication -Description and Operation.

(19) Install panel 241BTC. Refer to Chapter 6, Access Plates and Panels Identiication - Descriptionand Operation.

(20) Install the copilot seat. Refer to Chapter 25, Crew Seats - Maintenance Practices.(21) Remove the protective pad or foam cover from the avionics displays.

4. Elevator Aft Sector Assembly Removal/Installation

NOTE: The left elevator sector channel is removable to facilitate removal of the aft elevator sector.The right sector channel is riveted to structure.

A. Remove Elevator Aft Sector Assembly (Refer to Figure 402.).(1) Gain access to the elevator control cable turnbuckles and the elevator autopilot servo cables in

the tailcone by removing panels 321BC, 321EC, and 321FC. Refer to Chapter 6, Access Platesand Panels Identiication - Description and Operation.

(2) Remove the safety clips and loosen the elevator control cable and the elevator autopilot servocable turnbuckles.


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(3) Gain access to the aft elevator sector and control cables by removing panels 340ATC, 340AL,340AR, 340BL, 340BR, 340CL, 340DL, 340CR and 340ER. Refer to Chapter 6, Access Platesand Panels Identiication - Description and Operation.

(4) Remove screws and nuts securing retainers over pushrod attach bolt at sector. Removeretainers.

(5) Remove cotter pin, nut, washers and bolt securing elevator pushrods to elevator aft sectorassembly.

(6) Remove nuts, washers and screws securing elevator control cables to elevator sector assembly.(a) Carefully let the elevators down.

(7) Tag and disconnect elevator control cables from the elevator aft sector assembly.(8) Remove nuts, washers and bolts securing elevator sector stop blocks to channels (upper) and

attach brackets (lower). Remove elevator sector stop blocks.(9) Remove bolts, washers and nuts from lower end of aft elevator sector channel assembly (left).(10) Remove bolts and washers from upper end of aft elevator sector channel assembly (left).(11) Remove bolts, washers and nuts from outer surface of aft elevator sector channel (left).(12) Remove cotter pin, nut, washers and sector pivot bolt.(13) Remove elevator sector assembly and elevator sector channel (left) from airplane.

B. Install Elevator Aft Sector Assembly (Refer to Figure 402.).(1) Position elevator sector assembly and elevator sector channel (left) assembly in vertical in.

Ensure opening for elevator pushrod retaining bolt is below elevator sector centerline.(2) Loosely install the sector pivot bolt, washers, and nut to secure the elevator sector and the

elevator sector channel (left) to the rigid sector channel (right).(3) Loosely install the bolts, washers, and nuts to the lower end of the elevator sector channel (left).

Make sure that the washers are installed between the bolt heads and the channel, and betweenthe nuts and the channel.

(4) Position the elevator stops between the elevator sector channels (upper) and between the attachbrackets (lower).(a) Loosely install the bolts, washers, and nuts.

(5) Loosely install the bolts, washers, and nuts to secure the outer surface of the elevator sectorchannel (left) to the structure. Make sure that the washers are installed between the bolt headsand the channel, and between the nuts and the structure.

NOTE: The upper bolt is the longest bolt securing the elevator left channel assembly tothe structure.

(6) Loosely install the bolts and the washers into the upper end of the elevator sector channel.(7) Fully tighten all of bolts that were loosely installed and install the cotter pins to the necessary

locations. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter Pin Installation.(8) Install a rigging pin in the aft elevator sector.(9) Put the elevator pushrods in their position at the aft elevator sector.

(a) Put the bolt with one washer through the pushrods and the aft sector.1 Make sure that the washer is between the bolt head and the outboard side of the left

pushrod bearing.2 Make sure that the trailing edges of the elevators are lush with the trailing edge of

the horizontal stabilizer.3 If the trailing edges are not lush, adjust the pushrods until they are lush. Refer to

Elevator and Tab System Control Cables Adjustment/Test.(b) Install the second washer and the nut on the bolt.

1 Make sure that the washer is between the nut and the outboard side of the rightpushrod bearing.

2 Install the cotter pin. Refer to Chapter 20, Safetying - Maintenance Practices, CotterPin Installation.

(10) Install retainers over pushrod attach bolt with screws and nuts.(11) Attach elevator control cables to sector using screws washers and nuts. Rig elevator control

cables. Refer to Elevator and Tab System Control Cables - Maintenance Practices.(12) Remove the rigging pin from the aft elevator sector.


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(13) Install vertical in access panels 340ATC, 340AL, 340AR, 340BL, 340BR, 340CL, 340DL,340CR and 340ER. Refer to Chapter 6, Access Plates and Panels Identiication - Descriptionand Operation.

(14) Install aft baggage compartment panels 321BC, 321EC, and 321FC. Refer to Chapter 6, AccessPlates and Panels Identiication - Description and Operation.

5. Elevator Pushrods and Horns Removal/InstallationA. Remove Elevator Pushrods (Refer to Figure 402).

(1) Gain access to pushrods by removing panels 340ATC, 340BL and 340BR. Refer to Chapter 6,Access Plates and Panels Identiication - Description and Operation.

(2) Remove screws and nuts securing retainers over pushrod attachment bolt location on sector.Remove retainers.

(3) Remove cotter pin, nut, washers and bolt securing elevator pushrods to elevator sectorassembly.

(4) Remove cotter pin, nut, washers and bolt securing elevator pushrods to elevator horn.(5) Remove elevator pushrods from airplane.

B. Install Elevator Pushrods. (Refer to Figure 402).(1) Install bolts, washers, and nuts to secure the elevator pushrods to the elevator horns.

(a) Make sure that the washers are installed on both sides of each pushrod clevis.(b) Install the cotter pins. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter Pin

Installation.(2) Install a rigging pin in the aft elevator sector.(3) Put the elevator pushrods in their position at the aft elevator sector.

(a) Put the bolt with one washer through the pushrods and the aft sector.1 Make sure that the washer is between the bolt head and the outboard side of the left

pushrod bearing.2 Make sure that the trailing edges of the elevators are lush with the trailing edge of

the horizontal stabilizer.3 If the trailing edges are not lush, adjust the pushrods until they are lush. Refer to

Elevator and Tab System Control Cables Adjustment/Test.(b) Install the second washer and the nut on the bolt.

1 Make sure that the washer is between the nut and the outboard side of the rightpushrod bearing.

2 Install the cotter pin. Refer to Chapter 20, Safetying - Maintenance Practices, CotterPin Installation.

(4) Install retainers over pushrod attachment bolt location on sector with screws and nuts.(5) Do the rigging of the elevator control system cables. Refer to Elevator and Tab System Control

Cables - Adjustment/Test.(6) Remove the rigging pin from the aft elevator sector.(7) Install panels 340ATC, 340BL and 340BR. Refer to Chapter 6, Access Plates and Panels

Identiication - Description and Operation.

C. Remove the Elevator Horn (Refer to Figure 402).

NOTE: The removal procedure for the left and the right elevator horn is typical.

(1) Gain access to the elevator horn and the aft elevator sector by removing panels 340BLand 340ATC. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(2) Remove the elevator to get access to the elevator horn. Refer to Chapter 55, Elevator - Removal/Installation.

(3) Remove the cotter pin, nut, washers and bolt securing the elevator horn to the horizontalstabilizer attach itting.

(4) Remove the cotter pin, nut, washers and bolt securing the elevator pushrod to the elevator horn.(5) Remove the elevator horn from the airplane.

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Elevator Aft Sector, Pushrod and Horn InstallationFigure 402 (Sheet 1)


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D. Install the Elevator Horn (Refer to Figure 402).

NOTE: The installation procedure for the left and the right elevator horn is typical.

(1) Shank seal bolts with Type X Class B sealant, Refer to Chapter 20, Fuel, Weather, Pressureand High Temperature Sealing.

(2) Install bolts, washers, nut and cotter pin to secure the elevator horn to the horizontal stabilizerattach itting.

(3) Install the elevator. Refer to Chapter 55, Elevator - Removal/Installation.(4) Install a rigging pin in the aft elevator sector.(5) Temporarily attach the pushrod to the elevator horn with the bolt.

(a) Make sure that the trailing edge of the elevator is lush with the trailing edge of the horizontalstabilizer.1 If necessary, disconnect the pushrod and adjust the clevis end until the trailing edge

is lush when the pushrod is connected.(6) Fully install the bolt, washers, nut to attach the elevator pushrod to the elevator horn.

(a) Make sure that there is one washer on each side of the pushrod clevis.(b) Install the cotter pin. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter Pin

Installation.(7) Remove the rigging pin from the aft elevator sector.(8) Install panels 340BL and 340ATC. Refer to Chapter 6, Access Plates and Panels Identiication

- Description and Operation.

6. Control Column Removal/InstallationA. Remove Control Column (Refer to Figure 403).

(1) Disengage PITCH TRIM, AUDIO/MKR 1, AUDIO/MKR 2, XPDR 1, XPDR 2, ANG OF ATTACK, AFCS AND AFCS CONTROL circuit breakers. Tag circuit breakers: DO NOT ENGAGE -MAINTENANCE IN PROGRESS.

(2) Remove pilot and copilot seats. Refer to Chapter 25, Crew Seats - Maintenance Practices.(3) Remove screws securing control column boots to loor panels.(4) Gain access to the control column by removing panels 241BT, 241CT, 241BTC, 242CT and

242AT. Refer to Chapter 6, Access Plates and Panels Identiication - Description and Operation.(5) Disconnect the aileron crossover cable, forward aileron synchronizing cable, and aileron control

cables. Refer to Aileron and Tab System Control Cables - Maintenance Practices.(6) Remove control column boot assembly from control column.

CAUTION: Be careful to prevent damage to the avionics displays when youdisconnect the connecting link from the forward elevator sector.The control column can fall forward and damage the displays ifprotective pads or foam covers are not installed on the avionicsdisplays.

(7) Put a protective pad or foam cover on the avionics displays.(8) Remove and discard the cotter pin from the nut and the bolt that connect the forward elevator

connecting link to the forward elevator sector.(a) Remove the nut, washers, and bolt and carefully move the control columns forward as you

disconnect the connecting link from the sector.(9) Disconnect electrical connectors (PC313 and PF313) to control column wire bundles.(10) Remove bolts and washers securing control column torque tube to control column.(11) If installed, record the number and position of shims installed between the control column torque

tube and the control column.(a) Remove the shims from the airplane.

(12) Remove the screws that attach the aileron pulley bracket to left and the right support plateassemblies at the seat rail support structure,(a) Remove the aileron pulley bracket from the airplane.


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Control Column InstallationFigure 403 (Sheet 1)


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(13) Remove the screws that attach the left and the right support plate assemblies to the supportstructure and the support angle assemblies for the pilot's and the copilot's seat rails,(a) Remove the support plate assemblies and the support angle assemblies from the airplane.

(14) Move the control column torque tube aft to release control column.(15) Remove control column from airplane.(16) If necessary, remove the control column torque tube from the airplane.

NOTE: It is necessary to turn the torque tube at an angle to remove it.

B. Install Control Column. (Refer to Figure 403).(1) If necessary, put the control column torque tube in its position in the airplane.

NOTE: It is necessary turn the torque tube at an angle to put it in its position.

(a) If removed, put the shims in their recorded position between the control column torque tubeand the control column.

(b) Install the bolts and the washers that attach the control column torque tube to the controlcolumn.

(2) Position control column into bearing mount.(3) Install the bolts and the washers that attach the control column torque tube to the control column.(4) Examine the control column for lateral free play.

(a) If necessary, install shims between the control column torque tube and the control column.

NOTE: Not more than two shims are permitted on either side of the torque tube. If morethan two shims are necessary on either side of the torque tube, it is necessary toreplace one or both of the bearing mounts.

(5) Position control column boot assembly on control column.(6) Put the left and the right support plate assemblies and the support angle assemblies in their

position on the support structure for the pilot's and the copilot's seat rails,(a) Install the screws.

(7) Put the aileron pulley bracket in its position between the left and the right support plateassemblies at the seat rail support structure,(a) Install the screws.

(8) Install a rigging pin in the forward elevator sector.(9) Put the connecting link in its position on the forward elevator sector.

(a) Move the pilot's control column until the angle between the aft face of the column and theloor boards is 92 degrees, +0.5 or -0.5 degrees when the bolt that attaches it to the sectorcan be installed freely.

(10) If the bolt will not install freely, do the steps that follow to adjust the connecting link.(a) Loosen the connecting link jam nut.(b) Adjust the rod end on the connecting link until you can install the bolt freely when the control

column is at the speciied angle.(c) Tighten the connecting link jam nut.(d) Put the connecting link in its position at the forward sector.

1 Install the bolt, washers, nut, and cotter pin. Refer to Chapter 20, Safetying -Maintenance Practices, Cotter Pin Installation.

(11) Remove the rigging pin from the forward elevator sector.(12) Attach the aileron crossover cable, forward aileron synchronizing cable, and aileron control

cables. Refer to Aileron and Tab System Control Cables - Maintenance Practices.(13) Rig aileron cables. Refer to Aileron and Tab System Control Cables - Maintenance Practices.(14) Identify and connect electrical connectors (PC313 and PF313) to control column wire bundles.(15) Install panels 241BT, 241CT, 241BTC, 242CT and 242AT. Refer to Chapter 6, Access Plates

and Panels Identiication - Description and Operation.(16) Install boot on control column and secure to loorboard panels with screws.(17) Install pilot and copilot seats. Refer to Chapter 25, Crew Seats - Maintenance Practices.(18) Remove maintenance tag, engage PITCH TRIM, AUDIO/MKR 1, AUDIO/MKR 2, XPDR 1,

XPDR 2, ANG OF ATTACK , AFCS and AFCS CONTROL circuit breakers.(19) Remove the protective pad or foam cover from the avionics displays.


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7. Elevator Trim Tab Actuator Removal/InstallationA. Remove the Trim Tab Actuator. (Refer to Figure 404).

(1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(2) Gain access to the trim tab actuator and the turnbuckle by removing panels 321CTC and 331AB

(right) or 332AB (left). Refer to Chapter 6, Access Plates and Panels Identiication - Descriptionand Operation.

(3) Find the trim actuator that will be removed.(a) Used an approved clamp to temporarily hold the opposite elevator in the streamlined

position.(b) Use the pitch trim wheel in the cockpit to manually move the elevator trim tab until it is lush

with the elevator.(c) Install an inclinometer on the opposite elevator and the elevator trim tab.

1 Zero the inclinometers.(d) Use the pitch trim wheel in the cockpit to manually move the elevator trim tabs 4 degrees

(+1 or -1 degree) down from the streamlined position.1 Use tape to hold the trim tab to the elevator.

(4) Remove the clamp from the elevator.(5) Measure and record the distance from the rod end bearings to the actuator face plate.

CAUTION: Make sure that the trim pushrods do not catch on the adjacentstructure when they are disconnected from the trim actuators.Damage to the structure can occur if the elevator tab is movedwhen the pushrods are disconnected.

(6) Carefully lift the elevators with your hands to get access to the elevator trim actuator pushrods.(7) Remove the cotter pins, nuts, washers and bolts that attach the elevator trim actuator push rods

to trim tab actuator.(a) Disconnect the pushrods from the actuator.(b) Put a #10 bolt through the trim actuator rod end bearings to keep them in the correct

alignment.(8) Remove the elevator to get access to the elevator trim actuator. Refer to Chapter 55, Elevator -

Removal/Installation.(9) Loosen the elevator trim and the elevator electric trim cable turnbuckles.(10) Remove the screw and the spacer from the trim tab actuator chain guard.(11) Remove/lift the trim tab actuator chain from the trim tab actuator sprocket.(12) Remove the bolts securing the actuator to the horizontal stabilizer.(13) Remove the actuator from the airplane.

B. Install the Trim Tab Actuator (Refer to Figure 404.).(1) If a new elevator trim tab actuator is installed, do the steps that follow:

(a) Install a #10 bolt between both rod end bearings to keep their alignment.(b) Turn the drive sprocket to put the rod end bearings at the recorded distance from the

actuator face plate.(2) If the initial elevator trim tab actuator is installed, do the steps that follow:

(a) Lubricate elevator trim tab actuator with 5565450-28 grease. Refer to Chapter 12, FlightControl Servicing.

(b) Use the drive sprocket to fully extend and retract the trim tab actuator between four andsix times.

(c) Turn the drive sprocket to put the rod end bearings back to the recorded distance from theactuator face plate.

(3) Put the trim tab actuator in its position at the horizontal stabilizer.(4) Install the trim tab actuator chain over the trim tab actuator sprocket.

NOTE: Install chain(s) on actuator sprocket(s) as shown in Figure 404, with eye of actuatorpushrod aligned with the elevator bearings. Cable assembly/chain interface shouldbe even (top and bottom) when the elevator trim system is properly rigged andplaced in its neutral position of 4 degrees down.


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Elevator Trim Tab Actuator InstallationFigure 404 (Sheet 1)


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(5) Install the spacer and the screw in the trim tab actuator chain guard.(6) Remove the #10 bolt from the trim actuator rod end bearings.(7) Install the bolts in the horizontal stabilizer and the trim tab actuator.(8) Install the elevator. Refer to Chapter 55, Elevator - Removal/Installation.(9) Secure the elevator pushrods to the actuator using the bolts, washers, nuts and cotter pins.(10) Do the rigging of the elevator control system cables. Refer to Elevator and Tab System Control

Cables - Adjustment/Test(11) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.

C. Install panels 321CTC and 331AB (right) or 332AB (left). Refer to Chapter 6, Access Plates andPanels Identiication - Description and Operation.

D. Remove the Trim Tab Pushrods (Refer to Figure 404).(1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(2) Set the control lock system to keep the elevator position.(3) Remove the cotter pins, nuts, washers and bolts securing the trim tab pushrods to the elevator

trim tab horn.(4) Remove the cotter pins, nuts, washers and bolts securing the trim tab pushrods to the elevator

trim tab actuator.(5) Put a #10 bolt through the trim actuator rod end bearings to keep them in the correct alignment.(6) Remove the pushrods from the airplane.(7) Remove the cotter pin and the pin that connects the clevis ends for the adjustable pushrod and

the pushrod.(8) If the adjustable pushrod will be replaced, measure and record its length.

E. Install the Trim Tab Pushrods (Refer to Figure 404).(1) If a new elevator trim tab pushrod is installed, set it to the recorded length of the initial adjustable

pushrod.(2) Remove the #10 bolt from the trim actuator rod end bearings.(3) Put the pushrod assembly in its outoard position in the airplane.

(a) Install the bolts, washers, nuts, and cotter pins that connect the pushrod assembly to theelevator trim tab horn and the elevator trim tab actuator rod end. Refer to Chapter 20,Safetying - Maintenance Practices, Cotter Pin Installation.

(4) Put the adjustable pushrod assembly in its inboard position in the airplane.(a) Install the bolt, washer, nut, and cotter pin that connects the pushrod assembly to the

elevator trim tab horn. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter PinInstallation.

(b) Examine the bolt for the adjustable pushrod for a slip it at the trim actuator inboard rodend bearing.1 If necessary, adjust the pushrod until it has a slip it.

(c) Install the bolt, washer, nut, and cotter pin that connects the pushrod assembly to theactuator rod end. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter PinInstallation.

(5) Install the cotter pin and the pin that connects the clevis ends for the adjustable pushrod and thepushrod. Refer to Chapter 20, Safetying - Maintenance Practices, Cotter Pin Installation.

(6) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(7) Make sure that the elevator trim tab rigging is correct. Refer to Elevator and Tab System Control

Cables - Maintenance Practices.

8. Elevator Trim Control Wheel Removal/InstallationA. Remove Elevator Trim Control Wheel (Refer to Figure 405).

(1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(2) Turn the control wheel to put the elevator trim pointer at the forward edge of the safe take-off

band.(3) Make a mark on the trim wheel circumference across from the trim pointer.(4) Make a mark on the outboard face of the trim wheel to show the up direction.(5) Use a piece of tape to mark the position of the trim pointer and trim control wheel positions on

the throttle LED panel.(6) Remove the screws that attach the trim control wheel to the pedestal.


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Elevator Trim Control InstallationFigure 405 (Sheet 1)


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(7) Hold the trim pointer and remove the trim control wheel from the pedestal.(a) Carefully release the pointer forward.

B. Install Elevator Trim Control Wheel (Refer to Figure 405).(1) Use the mark on the trim control wheel face to put it in its correct alignment for installation.

(a) Loosely install the screws that attach the trim control wheel to the hub.(b) Carefully pull the trim pointer back until it is in its correct alignment with the mark on the

trim wheel circumference.(c) Carefully push the trim wheel in to engage the trim pointer index pin into the groove.(d) Fully tighten the screws that attach the control wheel to the hub.

(2) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(3) Do an Elevator Trim Tab Travel Check. Refer to Elevator And Tab System Control Cables -

Adjustment/Test.

9. Elevator Trim Pointer Removal/InstallationA. Remove the Elevator Trim Pointer (Refer to Figure 405).

(1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(2) Remove the trim control wheel from the pedestal. Refer to Elevator Trim Control Wheel Removal/

Installation in this section.(3) Remove the screws that attach the top pedestal bezel aft assembly to the pedestal.(4) Remove the top pedestal bezel aft assembly from the pedestal.(5) Disconnect the spring from the trim pointer.(6) Remove the bolt, washer, trim pointer, and spacer from the pedestal.

B. Install the Elevator Trim Pointer (Refer to Figure 405).(1) Put the spacer and trim pointer in their positions on the pedestal.

(a) Make sure that the trim pointer is in its correct position in the groove on the trim arm guide.(2) Install the washer and the bolt.(3) Connect the spring to the trim pointer.(4) Put the top pedestal bezel aft assembly in its position on the pedestal.(5) Install the screws.(6) Install the trim control wheel to the pedestal. Refer to Elevator Trim Control Wheel Removal/

Installation in this section.(7) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(8) Do an Elevator Trim Tab Travel Check. Refer to Elevator And Tab System Control Cables -

Adjustment/Test.

10. Garmin GSA 81 Elevator Trim Servo Motor Removal/Installation

NOTE: The GSA 81 elevator trim servo motor is attached to the GSM 86 elevator trim servo gearbox.This procedure includes the applicable access and maintenance information related to theModel 525 airplane. For the removal/installation of the servo motor, refer to the Garmin GSM86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List.

A. Remove the Garmin GSA 81 Elevator Trim Servo Motor (Refer to Figure 406).(1) Remove the electrical power from the airplane.(2) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Open hinged aft baggage compartment panel 321BTC to get access to the elevator trim

servo (UT313). Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(5) Remove aft baggage compartment panel 321CTC to get access to the elevator trim servo. Referto Chapter 6, Access Plates and Panels Identiication - Description and Operation.

(6) Disconnect the electrical connector (JT313) from the elevator trim servo electrical connector.(7) Remove the elevator trim servo motor from the servo gearbox and the airplane. Refer to the

Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier PublicationList.


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Elevator Trim Servo InstallationFigure 406 (Sheet 1)


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Elevator Trim Servo InstallationFigure 406 (Sheet 2)


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B. Install the Garmin GSA 81 Elevator Trim Servo Motor (Refer to Figure 406).(1) Install the elevator trim servo to the servo gearbox. Refer to the Garmin GSM 86 Servo Gear

Box Installation Manual in the Introduction, Supplier Publication List.(2) Connect the electrical connector (JT313) to the elevator trim servo electrical connector.(3) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(4) If a new trim servo has been installed, do the G3000 Baseline Software and Coniguration load.

Refer to Chapter 34, Garmin Integrated Avionics System - Adjustment/Test.(5) For more data applicable to the Model 525 G3000 software and coniguration uploading

procedures, refer to Section 6 and Section 8 of the most current revision of the GarminG3000 Integrated Avionics System Line Maintenance Manual, P/N 190-01579-00, found in theIntroduction, Supplier Publication List.

(6) Do the Elevator Trim Control System Functional Check. Refer to Elevator and Tab System -Inspection/Check.

(7) Install aft baggage compartment panel 321CTC. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.

(8) Close hinged aft baggage compartment panel 321BTC. Refer to Chapter 6, Access Plates andPanels Identiication - Description and Operation.


11. Garmin GSM 86 Elevator Trim Servo Gearbox and Cable Removal/Installation

NOTE: The GSM 86 elevator trim servo gearbox is attached to the GSA 81 elevator trim servo motor.This procedure includes the applicable access and maintenance information related to theModel 525 airplane. For the removal/installation of the servo gearbox, refer to the Garmin GSM86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List.

A. Remove the Garmin GSM 86 Elevator Trim Servo Gearbox and Cable (Refer to Figure 406).

NOTE: The electric trim servo stays attached to the electric trim servo gearbox during theremoval and the installation of the gearbox and cable.

(1) Remove the electrical power from the airplane.(2) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(3) Open the tailcone baggage compartment door. Refer to Chapter 6, Dimensions and Areas -

Description and Operation.(4) Open hinged aft baggage compartment panel 321BTC to get access to the elevator trim

servo gearbox. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(5) Remove aft baggage compartment panel 321CTC to get access to the elevator trim servogearbox. Refer to Chapter 6, Access Plates and Panels Identiication - Description andOperation.

(6) Disconnect the electrical connector (JT313) from the elevator trim servo (UT313) electricalconnector.

(7) Remove the clips from the turnbuckle that connects the forward and the aft elevator trim servocables. Refer to Chapter 20, Safetying - Maintenance Practices.(a) Loosen the turnbuckle to release the cable tension.

(8) On airplanes 0685, -0800 thru -0971 with clamp block connection:(a) Put a mark at the two clamp blocks to show the correct position on the elevator trim cables.(b) Remove the screws, washers, and nuts that attach the clamp blocks to the elevator trim

servo cables and the elevator trim cables.(c) Remove the clamp blocks from the cables.

(9) Airplanes -0972 and On with clamp block connection, do the steps that follow:(a) Put a mark at the two clamp blocks to show the correct position on the elevator trim cables.(b) Remove the screws that attach the clamp blocks to the elevator trim servo cables and the

elevator trim cables.(c) Remove the clamp blocks from the cables.

(10) Remove bolts and the washers that attach the elevator trim servo gearbox to the elevator trimbracket assembly.


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(11) Remove the elevator trim servo gearbox and the elevator trim servo cables from the airplaneand put them on a table.

(12) Remove the capstan cover, cable guard pins, and cable from the servo gearbox. Refer to theGarmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier PublicationList.(a) Slide the ball past the clip while pressing the retaining clip with a lat screwdriver or similar

tool.(13) If necessary, disconnect the forward and the aft elevator trim servo cables from the turnbuckle.(14) If necessary, remove the elevator trim servo motor from the elevator trim servo gearbox. Refer to

the Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier PublicationList.

B. Install the Elevator Trim Servo Gearbox and Cable (Refer to Figure 406).

NOTE: The electric trim servo stays attached to the electric trim servo gearbox during theremoval and the installation of the gearbox and cable.

(1) If necessary, install the elevator trim servo motor to the elevator trim servo gearbox. Refer tothe Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier PublicationList.

(2) If necessary, connect the forward and the aft elevator trim servo cables to the turnbuckle.(3) Install the cable, cable guard pins, and capstan cover to the servo gearbox. Refer to the Garmin

GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List.(4) Put the elevator trim servo gearbox and the elevator trim servo cables in their position at the

elevator trim bracket assembly.(a) Install the bolts and the washers.

(5) On airplanes 0685, -0800 thru -0971 with clamp block connection:

CAUTION: The clamp blocks and the nuts must be installed in the correctposition to make sure that they do not catch on the adjacentcables or structure. Damage to the cables or the structure canoccur if the cables or the nuts are not installed in the correctposition.

(a) Put the elevator trim servo cables and the clamp blocks in their recorded position on theelevator trim cables.

(b) Install clamp block screws and nuts.1 Torque the clamp block nuts to 12-15 inch pounds (1.35 N-m to 1.69 N-m).

(6) Airplanes -0972 and On with clamp block connection, do the steps that follow:(a) Put the elevator trim servo cables and the clamp blocks in their recorded position on the

elevator trim cables.(b) Make sure lush side of clamp block is installed to provide the largest amount of clearance

between the control cables.(c) Install clamp block screws and torque to 30-40 inch pounds (3.39 N-m to 4.51 N-m).

(7) Do the Elevator Trim Cables Rigging. Refer to Elevator and Tab System Control Cables -Adjustment/Test.

(8) Install the clips in the turnbuckle for the elevator trim servo cables. Refer to Chapter 20, Safetying- Maintenance Practices, Locking Clip Installation.

(9) Connect the electrical connector (JT313) to the elevator trim servo (UT313) electrical connector.(10) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.(11) If the servo gearbox and the trim servo were replaced new as an assembly, do the G3000

Baseline Software and Coniguration load. Refer to Chapter 34, Garmin Integrated AvionicsSystem - Adjustment/Test.

(12) For more data applicable to the Model 525 G3000 software and coniguration uploadingprocedures, refer to Section 6 and Section 8 of the most current revision of the GarminG3000 Integrated Avionics System Line Maintenance Manual, P/N 190-01579-00, found in theIntroduction, Supplier Publication List.


ICA-525-27-00005 Form 2261 Rev 1


MAINTENANCE MANUAL


(14) Install aft baggage compartment panel 321CTC. Refer to Chapter 6, Access Plates and PanelsIdentiication - Description and Operation.

(15) Close hinged aft baggage compartment panel 321BTC. Refer to Chapter 6, Access Plates andPanels Identiication - Description and Operation.


12. Pitch Trim Switch Removal/InstallationA. Remove the Pitch Trim Switch (Refer to Figure 407).

NOTE: The removal of the pilot's and the copilot's pitch trim switch is typical.

(1) Remove the electrical power from the airplane.(2) Remove the Allen screws that attach the control wheel cap to the control wheel.(3) Pull the control wheel cap away from the control wheel to get access to the electrical wiring and

the set screw.(4) Tag the electrical wires.(5) Remove the solder from the electrical wires to disconnect them from the pitch trim switch (SC313

pilot's, SF313 copilot's). Refer to the Model 525 Wiring Diagram Manual (-0685 and -0800 andOn).

(6) Remove the setscrew that holds the pitch trim switch in the control wheel cap.(a) Remove the pitch trim switch from the airplane.

B. Install the Pitch Trim Switch (Refer to Figure 407).

NOTE: The installation of the pilot's and the copilot's pitch trim switch is typical.

(1) Put the pitch trim switch (SC313 pilot's, SF313 copilot's) in its position in the control wheel cap.(a) Apply 222 anaerobic adhesive on the threads of the set screw. Refer to Chapter 20,

Anaerobic Adhesives - Maintenance Practices.(b) Install the set screw.

(2) Put the control wheel cap suficiently near the control wheel to connect the electrical wires.(a) Solder the electrical wires to connect them to the trim switch. Refer to the Model 525 Wiring

Diagram Manual (-0685 and -0800 and On).(b) Remove the tags from the electrical wires.

(3) Put the control wheel cap in its position on the control wheel.(a) Install the Allen screws.



ICA-525-27-00005 Form 2261 Rev 1


MAINTENANCE MANUAL

Pitch Trim Switch InstallationFigure 407 (Sheet 1)


ICA-525-27-00005 Form 2261 Rev 1



SUPPLEMENT NO: ICA-525-27-00005

APPENDIX A: ILLUSTRATED PARTS CATALOG

Nomenclature Part Number QuantityScrew MS24667-20 3 per clamp block

Clamp Block Half (Inner) 6361011-37 1

Clamp Block Half (Outer) 6361011-38 1

Clamp Block Half (Inner) 6361011-39 1

Clamp Block Half (Outer) 6361011-40 1




SUPPLEMENT NO: ICA-525-27-00005

APPENDIX B: WIRING DIAGRAM MANUAL

NOT APPLICABLE


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