AUTOPILOT CLAMP BLOCK IMPROVEMENT ICA Supplement

TEXTRON AVIATION INC.AIRCRAFT DIVISION

WICHITA, KANSAS 67277

AUTOPILOT CLAMP BLOCK IMPROVEMENTICA Supplement

MODEL NO: 525B

SUPPLEMENT NO: ICA-525B-27-00007SUPPLEMENT DATE: 12/07/2017

© TEXTRON AVIATION INC.Form 2261 Rev 1



REVISIONS

ICA-525B-27-00007 Rev: - Date: Dec 07/2017

ICA Summary Pages 1-6

Manuals Affected Description TitleMaintenance Manual 22-12-30 pages

401 - 404Garmin Elevator Autopilot Servo Assembly -Removal/Installation

• Adds new installation procedures for clamp block update.

Maintenance Manual 27-30-01 pages201 - 217

Elevator and Tab System Control Cables - MaintenancePractices

• Adds new installation procedures for clamp block update.

Appendix A: Illustrated PartsCatalog

See AttachedParts Table

Appendix B: Wiring DiagramManual

NOT USED

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.

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.

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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 specifiedtypes 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 specified section.Page 1 through 99 - Description and OperationPage 101 through 199 - TroubleshootingPage 201 through 299 - Maintenance PracticesPage 301 through 399 - ServicingPage 401 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 figure numbers as the page block in which they appear. For example, Figure202 would be the second figure 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 identified 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 525B 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 525B Maintenance Manual and will be incorporated in the next revision to 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 525B Maintenance Manual and incorporated into the operator's scheduledmaintenance program.

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

serialization.

Model Beginning Effectivity Ending Effectivity

525B -0536 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. All items must beavailable to the operator at initial delivery.(1) Model 525B Maintenance Manual

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





LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 525B Maintenance ManualA. Chapter 22 Auto Flight

(1) ATA 22-12-30, Garmin Elevator Autopilot Servo Assembly - Removal/Installation

B. Chapter 27 Flight Controls(1) ATA 27-30-01, Elevator and Tab System Control Cables - Maintenance Practices





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 525B Maintenance Manual, Chapter 4, Airworthiness Limitations,

contains the system and airframe limitations for the Model 525B.

NOTE: The Airworthiness Limitations section is FAA-approved and specifies 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.



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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 80 ElevatorAutopilot Torque Servo and the Garmin GSM 86 ServoMount. For a general description of the elevatorautopilot function, refer to Auto Flight - General. For more detailed maintenance data, refer to theGSM 86 Servo Gear Box Installation Manual P/N 190-00303-83 found in the Introduction, SupplierPublication List.

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

3. Garmin GSA 80 Elevator Autopilot Torque Servo Removal/InstallationA. Remove the Elevator Autopilot Torque Servo (PT304) (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) Get access to the elevator autopilot servo assembly in the tailcone. Remove aft baggage

compartment access panels 322CL, 321CC, and 321BL. Refer to Chapter 6, Access Platesand Panels Identification - Description and Operation.

(4) Disconnect the electrical connector (JT311) from the servo electrical connector.(5) Remove the bolts and the washers that attach the torque servo to the servo mount.(6) Remove the elevator autopilot torque servo from the servo mount and the airplane.(7) If necessary, use a clean, lint-free cloth and remove unwanted grease buildup from the torque

servo output gear.(8) If the torque servo is not going to be installed immediately, put a cover over the servo mount

opening to keep the mount clean.

B. Install the Elevator Autopilot Torque Servo (Refer to Figure 401).(1) Apply a thin layer of grease to the torque servo output gear.(2) If necessary, remove the servo mount protective cover from the servo mount opening.(3) Align the splines on the torque servo shaft with the splines in the servo mount.(4) Put the torque servo in its correct position on the servo mount.(5) Install the washers and bolts that attach the torque servo to the servo mount as follows:

(a) Insert all bolts and thread in approximately two turns by hand.(b) Starting with two opposite corner bolts, tighten all bolts until 1/64 inch to 1/32 inch (1/2 to

1 turn) from fully seated.(c) Make sure that the GSA 80 is still slightly loose relative to the GSM 86 and that there is

still relative movement between the two units.(d) Starting with two opposite corner bolts, torque all bolts to between 25.0 to 40.0 inch-pounds

(2.82 N-m to 4.52 N-m).(6) Connect the electrical connector (JT311) to the servo electrical connector.(7) Engage the AFCS circuit breaker on the right circuit breaker panel in the cockpit.(8) If a new torque servo has been installed, do the G3000 Baseline Software and Configuration

load. Refer to Chapter 34, Garmin Integrated Avionics System - Adjustment/Test.(9) For more data applicable to the Model 525B G3000 software and configuration 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.

(10) Do a check of the elevator control system. Refer to Garmin GFC700 Automatic Flight ControlSystem (AFCS) - Adjustment/Test.

(11) Install the aft baggage compartment access panels 322CL, 321CC, and 321BL. Refer to Chapter6, Access Plates and Panels Identification - Description and Operation.

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Garmin GSA 80 Elevator Autopilot Torque Servo Assembly InstallationFigure 401 (Sheet 1)


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4. Garmin GSM 86 Elevator Autopilot Servo Mount and Cable Removal/InstallationA. Remove the Servo Mount and Cable (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) Get access to the elevator autopilot servo assembly in the tailcone. Remove aft baggage

compartment access panels 322CL, 321CC, and 321BL. Refer to Chapter 6, Access Platesand Panels Identification - Description and Operation.

(4) Remove the torque servo. Refer to Garmin GSA 81 Elevator Autopilot Torque Servo Removal/Installation in this section.

(5) Remove the clips from the turnbuckle. Refer to Chapter 20, Safetying - Maintenance Practices(6) Loosen the turnbuckle to release the cable tension.

(a) Remove the elevator upper autopilot cable from the turnbuckle.(7) Mark the position of the clamp block that attaches the lower elevator autopilot cable to the

elevator cable.(8) Loosen the nuts on the clamp block that attaches the lower elevator autopilot cable to the elevator

cable.(a) Remove the lower elevator autopilot cable from the clamp block.

(9) Remove the bolts that attach the mount to the bracket.(10) Remove the GSM 86 servo mount and the cable from the airplane.(11) If the servo mount is to be replaced remove the cable as follows:

(a) Put the servo mount and the cable on a table.(b) Remove the screws and the washers that attach the capstan cover to the cable guard pins.

1 Remove the capstan cover from the pins.(c) Record the locations where the cable guard pins are installed.(d) Remove the cable guard pins from the GSM 86 servo mount.(e) Record how the cable is installed on the capstan drum.(f) Remove the cable from the capstan drum.

B. Install the Elevator Servo Mount and Cable (Refer to Figure 401).(1) Put the cable in the recorded position on the capstan drum.(2) Install the cable guard pins in the recorded positions on the GSM 86 servo mount.(3) Put the capstan cover in its position on the cable guard pins.

(a) Install but do not tighten the capstan cover screws and washers.(b) Torque the screws to between 8.0 to 12.0 inch-pounds (0.90 N-m to 1.35 N-m).

(4) Put the GSM 86 servo mount and the cables in their position at the servo mount bracketassembly.(a) Starting with two opposing bolts, torque all bolts to between 25.0 to 40.0 inch-pounds (2.82

N-m to 4.51 N-m).(5) Install the torque servo. Refer to Garmin GSA 81 Elevator Autopilot Torque Servo Removal/

Installation in this section.(6) Install the elevator lower autopilot cable in the clamp block.

(a) Make sure the clamp block is in the position on the elevator cable your marked before.

CAUTION: Use the same style hardware that was removed.

(b) Airplanes -0001 thru -0535, tighten the clamp block nuts to between 12 and 15 inch-pounds(1.35 N-m to 1.69 N-m).

NOTE: Airplanes -0001 thru -0535 use a clamp block that is attached with screwsand nuts.

(c) Airplanes -0536 and On, tighten the clamp block screws to between 30 and 40 inch pounds(3.39 N-m to 4.51 N-m).

NOTE: Airplanes -0536 and On use a clamp block that is attached with screws ona threaded clamp block half.


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(7) Install the upper autopilot cable in the turnbuckle.(a) Tighten the elevator turnbuckle to the correct autopilot servo cable tension. Refer to

Chapter 27, Elevator and Tab System Control Cables - Adjustment/Test, Figure 501.(b) Install the clips on the turnbuckle that connects the elevator interconnect cable to the

elevator control connector cable. 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 servo mount and the torque servo were replaced new as an assembly, do the G3000

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

(10) For more data applicable to the Model 525B G3000 software and configuration 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.

(11) Do a check of the elevator control system. Refer to Garmin GFC700 Automatic Flight ControlSystem (AFCS) - Adjustment/Test.

(12) Install aft baggage compartment access panels 322CL, 321CC, and 321BL. Refer to Chapter 6,Access Plates and Panels Identification - Description and Operation.


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ELEVATOR AND TAB SYSTEM CONTROL CABLES - MAINTENANCE PRACTICES

1. GeneralA. For elevator and tab components this section does not cover, refer to Elevator and Tab System

Components - Removal/Installation.

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

C. General(1) For installation, adjustment or adjustment of the elevator servo cables, refer to Chapter 22,

Autopilot Servo - Maintenance Practices.

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) Make sure that the control lock is disengaged.(a) Remove the pilot's seats. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices.

(2) Get access to the forward control cables. Remove the cockpit floorboard panels 251BTC,251CTC, and cabin floorboard panels 261AT, 261BT, 261CT, 261DT, 261ET, 261FT, 261GTand 261HT. Refer to Chapter 6, Access Plates and Panels Identification - Description andOperation.

(3) Remove the screws, washers, and nuts that attach the upper left fairleads at FS 172.74, FS204.95, FS 235.20, FS 263.67 and FS 294.91. Remove the fairleads.

(4) Enter the aft baggage compartment to get access to the forward control cables and removepanels 321A, 321BB, 321CB, 321DB, and 321BL. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(5) Remove the clips and disconnect the forward control cable turnbuckles from the aft control cablesat FS 426.44 and FS 442.62.

(6) Remove the guard pins from the pulley brackets at FS 131.50 and FS 147.00 in the cabin andFS 397.22 in the tailcone.

(7) Remove the spring retainers and pressure seals from the aft pressure bulkhead at FS 344.15.(8) Remove the nuts, washers, and screws that keep the forward control cables in the forward

elevator sector at FS 126.00.(9) Pull the cables forward and remove the control cables from the airplane.

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

NOTE: The left forward control cable is approximately 23.00 inches (0.58 m) longer than the rightforward control cable. The left forward control cable attaches to the sector through asingle swage ball end, while the right forward control cable has a double swage ball end.

(1) Install the left forward control cable in the forward sector at FS 126.00 with a screw, washer, anda nut.

NOTE: The retaining screw cannot be installed if the right hand cable is installed in theleft groove.

(2) Put the left forward control cable aft through the forward pulley at FS 131.50, fairleads at FS172.74, FS 204.95, FS 235.20, FS 263.67 and FS 294.91 and the aft pressure bulkhead at FS344.15.

(3) Install the right forward control cable to the forward sector at FS 126.00. Install the restrainingscrew, washer, and nut.

(4) Put the right forward control cable aft through forward pulley at, FS 147.00 fairleads FS 172.74,FS 204.95, FS 235.20, FS 263.67 and FS 294.91 and aft pressure bulkhead at FS 344.15.


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Elevator Control Cables InstallationFigure 201 (Sheet 1)


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(5) Apply a mark to the left and right forward control cables where the cables contact the aft pressurebulkhead.

(6) Move the forward control cables 12.00 inches (0.30 m) into the cabin.(7) Lubricate the forward control cables with Type VIII corrosion inhibiting grease 6.00 inches (0.15

m) on the forward and aft sides of the aft pressure bulkhead. Refer to Chapter 51, CorrosionInhibiting Compound (CIC) - Description and Operation.

(8) Install the pressure seals in the aft pressure bulkhead with the spring retainers.(9) Work from within the aft baggage compartment and put the forward control cables through the

pulleys at FS 397.22 and connect to the control cable turnbuckles mates.(10) Install the guard pins in the pulley brackets at FS 131.50 and FS 147.00 in the cabin and FS

397.22 in the tailcone.(11) Install the fairleads, screws, washers and nuts at FS 172.74, FS 204.95, FS 235.20, FS 263.67

and FS 294.91.(12) Adjust the control cables. Refer to Elevator And Tab System Control Cables - Adjustment/Test,

Elevator Control Cables Adjustment.(13) Install the clips at the turnbuckles that connect the forward control cable turnbuckles to the aft

control cables at FS 426.44 and FS 442.62.(14) Install cockpit floorboard panels 251BTC, 251CTC, and cabin floorboard panels 261AT, 261BT,

261CT, 261DT, 261ET, 261FT, 261GT and 261HT. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(15) Install panels 321A, 321BB, 321CB, 321DB, and 321BL in the aft baggage compartment. Referto Chapter 6, Access Plates and Panels Identification - Description and Operation.

(16) Install the pilot's seat. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices.

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

(1) Get access to the aft control cables. Remove the vertical stabilizer access panels 340ATC,340BL, 340BR, 340CR, 340DL, 340EL and 340ER. Refer to Chapter 6, Access Plates andPanels Identification - Description and Operation.

(2) Open the aft baggage compartment door to access to the aft control cables. Remove panels321CB, 321DB, and 321BL. Refer to Chapter 6, Access Plates and Panels Identification -Description and Operation.

(3) Remove clips and loosen autopilot elevator servo cable turnbuckle on the left aft control cable.(4) Remove clips and disconnect the aft control cable turnbuckles at FS 426.44 and FS 442.62 to

free the aft control cables from the forward control cables.(5) Remove the nuts, washers and screws that attach the elevator servo cable clamp blocks to the

aft control cables.(6) Remove the clamp blocks.(7) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, remove the

bolts and the washers that attach the fairleads and the retainers to the vertical stabilizer ribs atVFS 99.09 and VFS 111.99.(a) Remove the fairleads and the retainers from the airplane.

(8) Remove the guard pins that keep the aft control cables in the pulley brackets at FS 496.16 andFS 504.16.

(9) Remove the nuts, washers and screws that keep the aft control cables in the elevator aft sector.(10) Remove the cables from the airplane.

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

NOTE: The right aft control cable is longer than the left aft control cable. The left aft control cableattaches to the sector's upper groove through a single swage ball end, while the right aftcontrol cable has a double swage ball end.

(1) Attach the left aft control cable to the left forward cable turnbuckle.(a) Do not tighten the turnbuckle at FS 442.62.

(2) For Airplanes -0057 and -0451 and On, remove and discard the cotter pin from the bolt thatattaches the elevator cable assemblies.(a) Remove the bolt , the washer and the nut that attaches the elevator cable assemblies.


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(3) Put the left aft control cable aft through pulleys FS 469.16 and FS 504.16 to the aft elevatorsector.

(4) Install the left aft control cable in the aft sector assembly with a screw, washer, and nut.(5) Install the right aft control cable in the aft elevator sector with a screw, washer, and nut.(6) Put the right aft control cable forward through pulleys FS 469.16 and FS 504.16 to the right

forward control cable turnbuckle.(7) Connect the right forward control cable and the right aft control cables at turnbuckle FS 426.44.(8) Install the elevator servo cables and the clamp blocks to the aft control cables.

(a) Make sure that the elevators are at the streamlined position.


(b) For Airplanes -0001 thru -0056 and -0058 thru -0450, put the clamp block on the right handcable and make sure that the FWD edge of the block is 12.5 in +0.5 or - 0.5 in (317.5 mm+12.7 or -12.7 mm) from the C/L of the servo capstan.1 Install the screws, washers, and nuts.

(c) For Airplanes -0001 thru -0056 and -0058 thru -0450, put the clamp block on the left cableso the AFT edge of the block is at least 4.2 inches (0.11 m) from the rudder pulley bracketimmediately aft.1 Install the screws, washers, and nuts.

NOTE: Make sure that the clamp blocks are installed so that the flush side ofthe clamp block gives the greatest amount of clearance between thecontrol and servo cables.

(d) For Airplanes -0057 and -0451 thru -0535, put the clamp block on the right hand cable andmake sure that the FWD edge of the block is 12.7 in +0.5 or - 0.5 in (322.6 mm +12.7 or-12.7 mm) from the C/L of the servo capstan.

NOTE: Airplanes -0001 thru -0535 use a clamp block that is attached with screwsand nuts.

1 Loosely install the screws, washers, and nuts.a Torque the nuts from 12 to 15 inch-pounds (1.35 to 1.69 N-m).

(e) For Airplanes -0536 and On, put the clamp block on the right hand cable and make surethat the FWD edge of the block is 12.7 in +0.5 or - 0.5 in (322.6 mm +12.7 or -12.7 mm)from the C/L of the servo capstan.

NOTE: Airplanes -0536 and On use a clamp block that is attached with screws ona threaded clamp block half.

1 Torque the screws from 30 to 40 inch-pounds (3.39 to 4.51 N-m). Make sure that theclamp blocks do not slip.

(f) For Airplanes -0057 and -0451 andOn, Install the bolt , the washer and the nut that attachesthe elevator cable assemblies.1 Install a new cotter pin to the bolt that attaches the elevator cable assemblies. Refer

to Chapter 20, Safetying - Maintenance Practices.(9) Install the guard pins in the pulley brackets at FS 496.16 and FS 504.16.


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(10) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, put thefairleads and the retainers in their position on the vertical stabilizer ribs at VFS 99.09 and VFS111.99.

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 thefinal adjustment of the cables.

(11) Adjust the elevator control cables. Refer to Elevator And Tab System Control Cables -Adjustment/Test, Elevator Control Cables Adjustment.

(12) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, do the stepsthat follow:(a) Remove one of the bolts and the washers that attach the fairleads and the retainers to the

vertical stabilizer ribs at VFS 99.09 and VFS 111.99.

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

(b) Shank seal the bolt with Type X, Class B sealant. Refer to Chapter 20, Fuel, Weather,Pressure, and High-Temperature Sealing - Maintenance Practices.

(c) Install the bolt and the washer.(d) Do the steps again for the other bolts.

(13) Install the clips on the autopilot elevator servo cable turnbuckle on the left aft control cable.(14) Install the clips on the turnbuckles that connect the aft control cable to the forward control cables

at FS 426.44 and FS 442.62.(15) Install the aft baggage compartment panels 321CB, 321DB, and 321BL. Refer to Chapter 6,

Access Plates and Panels Identification - Description and Operation.(16) Install vertical stabilizer access panels 340ATC, 340BL, 340BR, 340CR, 340DL, 340EL and

340ER. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

5. Forward Elevator Trim Cables Removal/Installation

NOTE: The forward elevator trim cables have a chain installed between two cables. The forwardelevator trim cables extend from the trim chain, below the control pedestal, through pulleysand fairleads, to interconnected turnbuckles in the tailcone.

A. Remove the Forward Elevator Trim Cables (Refer to Figure 202).(1) Put the trim tab and indicator in the neutral position.(2) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel.(3) Remove the pilot's seats. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices.(4) Remove cockpit floorboard panels 251BTC, 251CTC, and cabin floorboard panels 261AT,

261BT, 261CT, 261DT, 261ET, 261FT, 261GT and 261HL. Refer to Chapter 6, Access Platesand Panels Identification - Description and Operation.

(5) For Airplanes -0001 thru -0056 and -0058 thru -0450, remove access panels 254AL, 254BL, and254CL from the left side of the control pedestal. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(6) For Airplanes -0057 and -0451 and On, remove access panels 254AL and 254BC from thecontrol pedestal. Refer to Chapter 6, Access Plates and Panels Identification - Description andOperation.

(7) Remove the screws, washers and nuts that attach the upper left fairleads to the forward elevatortrim cables at FS 172.70, FS 204.95, FS 235.20 and FS 263.67 and FS 294.91. Remove thefairleads.


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


ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL



ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL



ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL



ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL



ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL

(8) For Airplanes -0057 and -0451 and On, do the steps that follow:(a) Remove the cotter pin, washer, and guard pin that attach the bracket cap to the pulley

bracket at FS 144.81.1 Remove the bracket cap from the pulley bracket.

(b) Remove the screws, washers, and nuts that attach the fairlead cap to the fairlead base onthe aft side of the pullet bracket at FS 144.81.1 Remove the fairlead cap from the fairlead base.

(9) Remove the aft baggage compartment panels 321A, 321BB, 321CB, 321DB and 321BL. Referto Chapter 6, Access Plates and Panels Identification - Description and Operation.

(10) Remove the clips and loosen the turnbuckle for the electric trim cable.(a) Remove the clips and disconnect the cables at the turnbuckles in the tailcone between FS

436.01 and FS 450.11.(11) Remove the guard pins from all pulley brackets throughout the cable route.

(a) Remove the guard pins around the chain sprockets directly below the control wheel.(b) Remove the four screws from the control wheel sprocket chain guard and move the guard

away from the sprocket.(12) Remove the spring retainers and pressure seals in the aft pressure bulkhead at FS 344.15.(13) Loosen and remove the stop blocks from the forward elevator trim cables.(14) Put the cables forward through the aft pressure bulkhead and through the fuselage pulleys to

the control pedestal.(15) Lift the chain free from the trim control sprocket and lower sprockets.(16) Remove the trim cable from the airplane.(17) If necessary, remove the left and right trim cables from the trim tab control chain.

(a) On Airplanes -0306 and On and Airplanes -0001 thru -0305 that have stainless steel trimtab control chains installed, remove the spring clips from the connecting links that attachthe left and right trim cables to the trim tab control chain.

(b) Remove the connecting link that attaches the fuselage trim cables to the trim tab controlchain.

NOTE: The part number for the stainless steel elevator trim tab control chain isS3526-25-239.

(c) On Airplanes -0001 thru -0305 that do not have a stainless steel elevator control chain,remove the rivets that connects the left and right trim cable to the trim tab chain. Refer toChapter 20, Chains, Control Cables, Seals and Pulleys - Maintenance Practices.

B. Install Forward Elevator Trim Cable (Refer to Figure 202).

NOTE: The right forward elevator trim cable is approximately 23.00 inches (0.58 m) longer thanthe left forward trim cable and has a left-threaded terminal.

(1) Put a mark the center of the forward elevator trim cable chain.(2) Put the center mark of the chain over the trim control wheel sprocket.

(a) Put the forward part of the chain down and around the bottom of the lower sprocketassembly.

(b) Put the aft part of the chain down and around the bottom of the upper sprocket assembly.(c) Install the guard pins to maintain the chain position on the sprockets.

(3) On airplanes that have a stainless steel control chain, if removed, put the connecting links thatattaches the left and right fuselage trim cable to the trim tab control chain in the correct positionon the trim tab chain and trim control cable.

(4) Install the spring clips on the connecting link.(5) On airplanes that have a stainless steel control chain, if removed, install the rivets that connect

the cables to the chain. Refer to Chapter 20, Chains, Control Cables, Seals and Pulleys -Maintenance Practices.

(6) Connect the left and right forward elevator trim cables to the chain with a rivet. Refer to Chapter20, Chains, Control Cables, Seals and Pulleys - Maintenance Practices.

(7) Put the forward elevator trim cables aft through fuselage pulley assemblies at FS 144.81 andFS 157.72 and fairleads at FS 172.74, FS 204.95, FS 235.20, FS 263.67 and FS 294.91.


ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL

(8) For Airplanes -0001 thru -0056 and -0058 thru -0450, install the guard pins and the cotter pinsto the pulley brackets at FS 144.81 and FS 157.72.

(9) For Airplanes -0057 and -0451 and On, do the steps that follow:(a) Put the fairlead cap in its position on the fairlead base at the aft side of the pullet bracket

at FS 144.81.1 Install the screws, washers, and nuts.

(b) Put the bracket cap in its position on the pulley bracket at FS 144.81.1 Install the guard pin, washer, and cotter pin.

(c) Install the guard pin and the cotter pin to the pulley bracket at FS 157.72.(10) Put the forward trim cables through the aft pressure bulkhead seals. Put a mark the forward

elevator trim cables at the point where the cables route through the aft pressure bulkhead.(11) Lubricate the forward trim cables with 5565450-28 grease, 12.00 inches (0.30 m) on forward

and aft sides of cable mark.(12) Install the aft pressure bulkhead seals with the forward trim cables through the aft pressure

bulkhead. Attach with spring retainers.(13) Install the fairleads at FS 172.74, FS 204.95, FS 235.20, FS 263.67 and FS 294.91 with screws,

washers and nuts.(14) Put 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) Install stop blocks but do not tighten.(18) Adjust the trim cables. Refer to Adjust the trim system. Refer to Elevator Trim Cables Adjustment

in this section.(19) Install the clips at the turnbuckle for the electric trim cable.

(a) Install the clips at the turnbuckles in the tailcone between FS 436.01 and FS 450.11.


(20) For Airplanes -0001 thru -0535, torque the nuts from 12 to 15 inch-pounds (1.35 to 1.69 N-m)that attaches the block to the cables.

NOTE: Airplanes -0001 thru -0535 use a clamp block that is attached with screws and nuts.

(21) For Airplanes -0536 and On, torque the screws from 30 to 40 inch-pounds (3.39 to 4.51 N-m)that attaches the block to the cables. Make sure that the clamp blocks do not slip.

NOTE: Airplanes -0536 and On use a clamp block that is attached with screws on athreaded clamp block half.

(22) Install cockpit floorboard panels 251BTC, 251CTC, and cabin floorboard panels 261AT, 261BT,261CT, 261DT, 261ET, 261FT, 261GT and 261HL. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(23) For Airplanes -0001 thru -0056 and -0058 thru -0450, install access panels 254AL, 254BL, and254CL to the left side of the control pedestal. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(24) For Airplanes -0057 and -0451 and On, install access panels 254AL and 254BC to the controlpedestal. Refer to Chapter 6, Access Plates and Panels Identification - Description andOperation.

(25) Install the aft baggage compartment panels 321A, 321BB, 321CB, 321DB and 321BL. Refer toChapter 6, Access Plates and Panels Identification - Description and Operation.

(26) Install pilot's seats. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices.

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

(1) Disengage the PITCH TRIM circuit breaker, on the left circuit breaker panel.


ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL

(2) Get access to the aft trim cables. Remove vertical stabilizer access panels 340ATC, 340BL,340BR, 340CR, 340DL, 340EL and 340ER. Refer to Chapter 6, Access Plates and PanelsIdentification - Description and Operation.

(3) Remove aft baggage compartment panels 321BB, 321CB, 321DB, 321BL, 321BC and 322BB.Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

(4) Remove the guard pins from the pulley bracket assemblies in the tailcone.(5) Tag the left and right aft elevator trim cables and forward elevator trim cables.(6) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, remove the

bolts and the washers that attach the fairleads and the retainers to the vertical stabilizer ribs atVFS 99.09 and VFS 138.39.(a) Remove the fairleads and the retainers from the airplane.

(7) Put a mark at the location of the clamp blocks. Remove the clips and loosen the turnbuckle inthe elevator electric trim cable.(a) Remove the clamp blocks that attach the aft elevator electric trim cables to the aft elevator

trim cables.(b) Disconnect the electric trim cables.

(8) Remove the safety clips and loosen the turnbuckles to disconnect the aft elevator trim cablesfrom the forward trim cables.

(9) Remove the aft trim cables from airplane.(10) If the trim crossover cable is to be removed, complete the steps that follow.

(a) Remove the screws and spacers that attach the chain guards to the trim actuators. Bendthe guards back and lift the chains from the actuators' drive sprockets.

(b) Remove the guard pin from the pulley and remove the cable from the pulley.

B. Install Aft Trim Cable (Refer to Figure 202).

NOTE: The left aft trim cable is approximately 17.00 inches (0.43 m) longer than the right afttrim cable.

(1) If the crossover cable was removed:(a) Put the chain over the right actuator drive sprocket so there is a total of 10 inches (0.25 m)

more chain on the lower (free) end. Bend the chain guard to be 0.04 to 0.06 inches (1.02to 1.52 mm) from the chain and install the spacer and screw.

(b) Install the cable in the pulley and install the guard pin.(c) Put the chain over the left actuator's drive sprocket. Bend the chain guard flanges to get

a 0.04 to 0.06 inch (1.02 to 1.52 mm) clearance to the chain. Install the spacer and screwin the chain guard.

(d) On airplanes that have stainless steel trim tab control chains installed, install the connectinglink that attaches the control cables to the trim tab control chain.

NOTE: The part number for the stainless steel elevator trim tab control chain isS3526-25-109.

(e) On airplanes that do not have stainless steel trim tab control chains installed, install therivets that attach the aft elevator cables to the trim actuator control chain. Use a rivet toconnect the aft elevator trim cable to the trim actuator drive chain. Refer to Chapter 20,Chains, Control Cables, Seals, and Pulleys - Maintenance Practices.

(2) Put the aft elevator trim cables from horizontal stabilizer through the vertical fin, through pulleysto the interconnected turnbuckles.(a) Connect the cables at the turnbuckles.


(3) Attach the elevator electric trim cables to the aft elevator trim cables with clamp blocks.(4) For Airplanes -0001 thru -0535, torque the nuts from 12 to 15 inch-pounds (1.35 to 1.69 N-m)

that attaches the clamp blocks to the cables.

NOTE: Airplanes -0001 thru -0535 use a clamp block that is attached with screws and nuts.


ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL

(5) For Airplanes -0536 and On, torque the screws from 30 to 40 inch-pounds (3.39 to 4.51 N-m)that attaches the clamp blocks to the cables. Make sure that the clamp blocks do not slip.

NOTE: Airplanes -0536 and On use a clamp block that is attached with screws on athreaded clamp block half.

(6) Install guard pins in the pulley bracket assemblies of the aft elevator trim cables in the tailcone.(7) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, put the

fairleads and the retainers in their position on the vertical stabilizer ribs at VFS 99.09 and VFS138.39.

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.(8) Adjust the trim system. Refer to Elevator Trim Cables Adjustment in this section.(9) For Airplanes -0282, -0287 and On, and airplanes that incorporate SB525B-27-03, do the steps

that follow:(a) Remove one of the bolts and the washers that attach the fairleads and the retainers to the

vertical stabilizer ribs at VFS 99.09 and VFS 138.39.

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

(b) Shank seal the bolt with Type X, Class B sealant. Refer to Chapter 20, Fuel, Weather,Pressure, and High-Temperature Sealing - Maintenance Practices.

(c) Install the bolt and the washer.(d) Do the steps again for the other bolts.

(10) Install the safety clips at the turnbuckles that connect the aft elevator trim cables to the forwardtrim cables.

(11) Install aft baggage compartment panels 321BB, 321CB, 321DB, 321BL, 321BL and 322BB.Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

(12) Install vertical stabilizer access panels340ATC, 340BL, 340BR, 340CR, 340DL, 340EL and340ER. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

7. Elevator Trim Cables AdjustmentA. Adjust the Elevator Trim Cables (Refer to Figure 201 and Figure 202).

(1) Refer to Elevator And Tab System Control Cables - Adjustment/Test, Elevator Trim CablesAdjustment

8. Elevator and Elevator Trim Tab CheckA. Do an Elevator and Elevator Travel Check.

(1) Move the control column to the full aft position.(2) Make sure that the elevator movement is 20.5 degrees, +0.5 or -0.5 degree, up from the neutral

position.(3) Move the control column to the full forward position.(4) Make sure that the elevator movement is 15 degrees, +1 or -1 degree, down from the neutral

position.

B. Do an Elevator Trim Tab Travel Check.(1) Turn the elevator trim control wheel to the FULL DOWN position.(2) Make sure that the elevator trim tab moves up nine degrees, +1 or -1 degree, from the neutral

position.(3) Turn the elevator trim control wheel to the FULL UP position.


ICA-525B-27-00007 Form 2261 Rev 1

CESSNA®MODEL 525B

MAINTENANCE MANUAL

(4) Make sure that the elevator trim tab is deflected down 17 degrees, +1 or -1 degree, from theneutral position.


ICA-525B-27-00007 Form 2261 Rev 1



SUPPLEMENT NO: ICA-525B-27-00007

APPENDIX A: ILLUSTRATED PARTS CATALOG

Part Number Quantity Nomenclature6361011-41 3 Clamp Block Half (Inner)

6361011-42 3 Clamp Block Half (Outer)

6361011-37 1 Clamp Block Half (Inner)

6361011-38 1 Clamp Block Half (Outer)

MS24667-20 12 (3 per clamp block) Clamp Block Attachment Screw




SUPPLEMENT NO: ICA-525B-27-00007

APPENDIX B: WIRING DIAGRAM MANUAL

NOT APPLICABLE
