ELEVATOR TRIM SERVO CAPSTAN CABLE RETENTION IMPROVEMENT ICA Supplement

TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

MODEL NO: 525B

SUPPLEMENT NO: ICA-525B-27-00009 SUPPLEMENT DATE: 7/13/2020

REVISIONS ICA-525B-27-00009 Rev: - Date: Jul/13/2020 ICA Summary Pages 1-6 Manuals Affected Description Title Maintenance Manual 27-30-02 pages ELEVATOR AND TAB SYSTEM COMPONENTS - 401-427 REMOVAL/INSTALLATION • This section contains the revised procedures for installation of the GSM 86 Elevator Trim Servo Gearbox and Cable. Appendix A: Illustrated Parts See Attached Catalog Parts Table Appendix B: Wiring Diagram NOT USED Manual

1. Export Compliance A. 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. Diversion contrary to U.S. law is prohibited. ECCN: 9E991

2. Revision Bars A. 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 Numbering A. 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, left of 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 and subject/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 element number (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 of subsystem units in which maintenance information is necessary. E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into specified types 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 Practices section. 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 Operation Page 101 through 199 - Troubleshooting Page 201 through 299 - Maintenance Practices Page 301 through 399 - Servicing Page 401 through 499 - Removal/Installation Page 501 through 599 - Adjustment/Test Page 601 through 699 - Inspection/Check Page 701 through 799 - Cleaning/Painting Page 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, Figure 202 would be the second figure in a Maintenance Practices section.

4. Supplement Revisions A. 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 manuals listed above and should be used in conjunction with those manuals until the next available revision is released. A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS table will indicate the incorporation status as of the release date of the published revision.

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B. The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation Status" column in the ICA Supplement List, when those ICAs associated with that manual have been incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used for 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 incorporation status. C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when it has been incorporated in all of the manuals.

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INTRODUCTION

1. Purpose A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the ELEVATOR TRIM SERVO CAPSTAN CABLE RETENTION IMPROVEMENT on the Cessna Model 525B until this information gets incorporated into the next revision 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 for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 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 "ICA Supplement List" in the "Introduction" section of the respective manual for the status of all applicable ICA Supplements. D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement prior to incorporation into all of the affected manuals.

NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROM or Model 525B Maintenance Manual and incorporated into the operator's scheduled maintenance program.

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

Model Beginning Effectivity Ending Effectivity 525B -0632 and On

3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the ELEVATOR TRIM SERVO CAPSTAN CABLE RETENTION IMPROVEMENT on the Cessna Model 525B. All items must be available to the operator at initial delivery. (1) Model 525B Maintenance Manual

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

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LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 525B Maintenance Manual A. Chapter 27 Flight Controls (1) ATA 27-30-02 Elevator and Tab System Components- Removal/Installation

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INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

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

2. Airworthiness Limitations A. 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 maintenance required under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved.

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

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CESSNA® MODEL 525B MAINTENANCE MANUAL

ELEVATOR AND TAB SYSTEM COMPONENTS - REMOVAL/INSTALLATION

1. General A. This section gives information about the removal and installation of components related to the elevator and elevator trim tab systems. For control cable removal/installation and rigging information, 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 Equipment A. For a list of tools and equipment, refer to Flight Controls - General.

3. Forward Elevator Sector Assembly Removal/Installation A. Remove the Forward Elevator Sector Assembly (Airplanes -0001 thru -0056 and -0058 thru -0450) (Refer to Figure 401). (1) Remove the copilot's seat. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. (2) Get access to the forward elevator sector. (a) Remove the cockpit floorboard panels 251BTC and 251CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Get access to the elevator control cable turnbuckles. (a) Remove the tailcone baggage panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (4) Install a rig pin in the aft sector. (a) Remove the clip and loosen the elevator autopilot cable turnbuckle. (b) Remove the safety clips and loosen the elevator control cable turnbuckles. (5) Identify and label the forward elevator control cables. (6) Remove the nuts, washers, and screws that keep the forward elevator cables in the forward elevator sector. Keep the hardware. (7) Remove the cotter pin, nut, washers, and bolt that attach the connecting link to the forward elevator sector. (8) Remove the screws that attach the stop block to the upper and lower sector brackets. (9) Remove the safety wire, pivot bolt, and washer that attach the forward elevator sector to upper and lower sector brackets. (10) Remove the screws that attach the upper sector bracket to lower sector bracket. (a) Remove the aileron and rudder trim controls. (b) Remove upper sector bracket, spacer, and stop block. (11) Remove the forward elevator sector from airplane. B. Install the Forward Elevator Sector (Airplanes -0001 thru -0056 and -0058 thru -0450) (Refer to Figure 401). (1) Put the forward elevator sector in position on the lower sector bracket. (2) Put the stop block in position on the lower sector bracket. (3) Put the upper sector bracket and spacer in position on the lower sector bracket. (4) Put the washer on the pivot bolt and attach the sector assembly to the upper and lower sector brackets. (5) Attach the stop block to the sector brackets with two screws. (6) Put a safety wire on the pivot bolt head. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices. (7) Install the screws that attach each end of the upper sector bracket to the lower sector bracket. (8) Install the forward elevator cables in the forward elevator sector with the screws, washers, and nuts kept from the removal. (9) Attach the connecting link to forward elevator sector with a bolt, washers, nut, and cotter pin. (a) Install the aileron and rudder trim controls removed before. (10) Rig the elevator control system cables and adjust the stop bolts. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (11) Install the tailcone baggage compartment panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

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A29101

PIVOT BOLT SCREW

UPPER SECTOR BRACKET WASHER

A SPACER STOP STOP BLOCK BOLT BOLT NUT STOP BOLT

FORWARD ELEVATOR CABLE, RIGHT WASHER

CONNECTING LINK FORWARD ELEVATOR CABLE, LEFT ROD END WASHER

COTTER PIN NUT

LOWER SECTOR BRACKET

SCREW

DETAIL A AIRPLANES −0001 THRU −0056 AND AIRPLANES −0058 THRU −0450 6310T1072 A6363T1017 Forward Elevator Sector Installation Figure 401 (Sheet 1)

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A94137 SCREW

TRIM BEARING PLATE

SCREW

PIVOT BOLT

UPPER BRACKET WASHER

STOP BLOCK

NUT SPACER STOP BOLT

BOLT ELEVATOR CABLE (RIGHT)

WASHER

CONNECTING ELEVATOR CABLE LINK (LEFT) ROD END FORWARD ELEVATOR WASHER SECTOR NUT

COTTER PIN LOWER BRACKET

DETAIL A AIRPLANES −0057 AND −0451 AND ON A6315T1168 Forward Elevator Sector Installation Figure 401 (Sheet 2)

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(12) Install cockpit floorboard panels 251BTC and 251CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (13) Install the copilot's seat. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. C. Remove the Forward Elevator Sector Assembly (Airplanes -0057 and -0451 and On) (Refer to Figure 401). (1) Remove copilots seat. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. (2) Gain access to the forward elevator sector by removing panels 251BTC and 251CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Gain access to the elevator control cable turnbuckles in the tailcone by removing panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (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. (5) Disconnect the rudder forward trim control cables from the chain at the control pedestal in the cockpit. Refer to Rudder and Tab System - Maintenance Practices. (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. (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 you disconnect the connecting link from the forward elevator sector. The control column can fall forward and damage the displays if protective pads or foam covers are not installed on the avionics displays.

(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. (13) Remove the screws, washers, and nuts that attach the aileron trim gearbox to the pedestal structure. (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 sufficiently 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. (19) Remove screws securing upper sector bracket to lower sector bracket. Remove upper sector bracket and stop block. (20) Remove elevator sector from airplane. D. Install the Forward Elevator Sector Assembly (Airplanes -0057 and -0451 and On) (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.

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(7) Tighten the pivot bolt. (a) Safety the pivot bolt with safety wire. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices, 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. Refer to Aileron and Tab System Control Cables - Maintenance Practices. (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. (14) Connect the elevator forward trim cables to the chain at the control pedestal in the cockpit. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (15) Attach the control column connecting link to elevator sector assembly using bolt, washers, nut and cotter pin. Refer to the Citation Standard Practices Manual, 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 Elevator and Tab System Control Cables - Adjustment/Test. (17) Install the aft pedestal switch panel. Refer to Chapter 31, Instrument and Switch Panels - Maintenance Practices. (18) Install panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (19) Install panels 251BTC and 251CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (20) Install the copilot seat. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. (21) Remove the protective pad or foam cover from the avionics displays.

4. Aft Elevator Sector Removal/Installation

NOTE: The left elevator sector channel can be removed to help with removal of the aft elevator sector. The right sector channel is riveted to the structure. A. Remove Aft Elevator Sector (Refer to Figure 402). (1) Get access to the elevator control cable turnbuckles. Remove tailcone baggage panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (2) Carefully clamp the horns to the horizontal stabilizer to attach both elevator surfaces. (a) Remove the safety clips and loosen the elevator control cable turnbuckles. (3) Get access to the aft elevator sector and aft elevator control cables. Remove vertical stabilizer access panels 340ATC, 340AL, 340AR, 340BL, 340BR, 340DL, 340EL, 340CR and 340ER. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (4) Remove the screws and nuts that attach the retainers over the pushrod attach bolt in the aft elevator sector. Remove the retainers.

CAUTION: If the elevator surfaces are moved with the pushrods not attached, you can cause damage the rib which they pass through.

(5) Remove cotter pin, nut, washers, and bolt that keep elevator pushrods in aft elevator sector. (6) Remove nuts, washers, and screws that attach aft elevator cables to aft elevator sector. (7) Identify, tag, and disconnect aft elevator cables from the aft elevator sector assembly. (8) Remove nuts, washers, and bolts that attach stop blocks to right rigid channel, left removable channel, and stop block lower attach bracket. Remove stop blocks. (9) Remove bolts, washers, and nuts from lower end of left removable channel. (10) Remove bolts and washers from upper end of left removable channel.

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(11) Remove bolts, washers, and nuts from outer surface of left removable channel. (12) Remove cotter pin, nut, washers, and pivot bolt. (13) Remove aft elevator sector and left removable channel from airplane. B. Install Aft Elevator Sector Assembly (Refer to Figure 402). (1) Put the aft elevator sector and left removable channel in the vertical stabilizer. Make sure the elevator pushrod bolt hole is below the elevator sector centerline. (2) Install the pivot bolt, washers, nut, and cotter pin to attach the aft elevator sector and left removable channel to the right rigid channel. (3) Install bolts, washers, and nuts to the lower end of the left removable channel.

NOTE: Make sure there are washers under the bolt heads and, between the channel and the nuts.

(4) Put the stop blocks between upper part of the elevator sector channels and the lower attach brackets. Attach in position with bolts, washers, and nuts.

NOTE: The down stop block is longer than the up stop block.

(5) Install bolts, washers, and nuts to attach the outer surface of the aft elevator sector left removable channel to the structure. Make sure washers are installed between the bolt heads and channel, and between the nuts and the structure.

NOTE: The upper bolt is the longest bolt that attaches the elevator left removable channel to the structure.

(6) Install the bolts and washers into the upper end of the right rigid channel. (7) Attach the elevator pushrod to the aft elevator sector using a bolt, nut, washers, and cotter pin. Make sure washers are against the outer bearing surface of each pushrod. (8) Install retainers over the elevator pushrod attach bolt. Attach with screws and nuts. (9) Install the aft elevator cables to the aft elevator sector with screws, washers, and nuts. (10) Rig elevator control cables. Refer to Elevator and Tab System Control Cables - Maintenance Practices (11) Install vertical stabilizer access panels 340ATC, 340AL, 340AR, 340BL, 340BR, 340DL, 340EL, 340CR and 340ER. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (12) Install aft baggage compartment panel 321BL. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation.

5. Elevator Pushrods and Horn Removal/Installation A. Remove the Elevator Pushrods (Refer to Figure 402). (1) Get access to the pushrods. Remove vertical stabilizer access panels 340ATC, 340BL and 340BR. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (2) Remove cotter pin, nut, washers, and bolt that attach the elevator pushrods to elevator horns. Carefully lower the elevator. (3) Remove the screws, nuts, and retainers over the pushrod attachment bolt, on the aft elevator sector. Remove the retainers. (4) Remove cotter pin, nut, washers, and bolt that attach elevator pushrods to aft elevator sector assembly. (5) Remove the elevator pushrods from airplane. B. Install the Elevator Pushrods (Refer to Figure 402). (1) Install bolts, with washers, on both sides of each pushrod clevis, nuts, and cotter pins to attach the elevator pushrods to the elevator horns. (2) Install bolt, with washers on each side of the elevator pushrod bearings, nut, and cotter pin to attach elevator pushrods to the aft elevator sector. (3) Install retainers over pushrod attachment bolt location on aft elevator sector with screws and nuts.

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A29102

ELEVATOR ELEVATOR HORN, PUSHROD HORN, RIGHT CLEVIS LEFT END PIVOT BOLT

ELEVATOR TORQUE TUBE ELEVATOR PUSHROD, RIGHT

WASHER ELEVATOR ELEVATOR HORN PUSHROD, ATTACH FITTING BOLT LEFT AFT ELEVATOR SECTOR JAM NUT PUSHROD EYE END COTTER PIN B NUT

DETAIL A

6310T1072 A6363T1018 Elevator Aft Sector, Pushrod, and Horn Installation Figure 402 (Sheet 1)

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A485

WASHER RIGHT RIGID NUT CHANNEL

COTTER DOWN PIN AFT STOP ELEVATOR BLOCK SECTOR RETAINER

NUT WASHER

WASHER

BOLT

LEFT BLOCK REMOVABLE UP BOLT CHANNEL STOP JAM NUT BLOCK

PIVOT BOLT AFT ELEVATOR CABLE

STOP BLOCK LOWER ATTACH BRACKET DETAIL B

B6363T1027 Elevator Aft Sector, Pushrod, and Horn Installation Figure 402 (Sheet 2)

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(4) Make sure the elevator rigging is correct. Refer to Elevator and Tab System Control Cables - Maintenance Practices.

NOTE: If the cables and elevator aft sector stops were not disturbed, then only the travel of the affected must be checked.

(5) Install vertical stabilizer access panels 340ATC, 340BL and 340BR. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. C. Remove the Elevator Horn (Refer to Figure 402).

NOTE: Left and right elevator horn removal/installation is typical.

(1) Get access to the elevator horn. Remove vertical stabilizer panel 340ATC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (2) Remove the cotter pin, nuts, washers, and bolt which attach the pushrod to the horn. (a) Remove the cotter pin, nuts, washers, and bolts which attach the pushrod to the horn. (a) Remove the cotter pin, nut, washer, and bolts that attach the elevator horn to the elevator torque tube. (3) Remove the cotter pin, nut, washer, spacer, and bolt that attach the elevator horn to the elevator horn attach fitting. (4) Remove the elevator from the aircraft. Refer to Chapter 55, Elevator - Maintenance Practices. (5) Remove the cotter pin, nut, washers, and bolt that attach elevator pushrod to elevator horn. (6) Remove the elevator horn from airplane. D. Install the Elevator Horn (Refer to Figure 402). (1) Install the pivot bolt, washer, spacer, nut, and cotter pin to attach elevator horn to elevator horn attach fitting. (2) Install bolt, with washers on both sides of each pushrod clevis, nut, and cotter pin to attach the elevator pushrod to the elevator horn. (3) Install the elevator onto the aircraft. Refer to Chapter 55, Elevator - Maintenance Practices. (4) Install vertical stabilizer panel 340ATC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Install bolts, washers, nuts, and cotter pins to attach elevator horn to elevator torque tube.

6. Control Column Removal/Installation

NOTE: Pilot and copilot control column removal/installation are typical, except as noted. A. Remove the Control Column (Refer to Figure 403). (1) Disengage PITCH TRIM, AUDIO, XPDR, ANG OF ATTACK AND AP (DC and AC) circuit breakers. Put a label on the circuit breakers: DO NOT ENGAGE - MAINTENANCE IN PROGRESS. (2) Remove the pilot's and copilot's seats. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. (3) Remove the screws that attach control column boot to cockpit floorboard panels. (4) Get access to the control column by removing cockpit floorboard panels 251BT, 251CT, 251BTC, 251CTC, 252CT and 252CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Disconnect the aileron crossover cable. Disconnect the left and right aileron forward control cables. Refer to Aileron and Tab System Control Cables - Maintenance Practices. (a) Remove the Aileron Forward Pulley Bracket and both left and right Support Plate Assemblies from the aircraft. (6) Remove the cotter pin, nut, washers, and bolt that attach connecting link to the torque tube. (7) Disconnect the electrical connector (JC303, left or JF303, right) from control column wire bundles. (8) Remove the bolts and washers that attach the torque tube to the control column. (9) Move the torque tube aft until clear of the control columns. (10) Move the control column inboard to free it from the bearing support and remove the control column from airplane.

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A29105

A COPILOT'S CONTROL WHEEL

PILOT'S CONTROL WHEEL

COPILOT'S CONTROL COLUMN

STICK SHAKER

PILOT'S CONTROL COLUMN BOOT

CONNECTING LINK

WASHER TURNBUCKLE

TORQUE TUBE CLIP-ON NUT NUT

COTTER PIN BOLT BEARING WASHER SUPPORT

6310T1072 DETAIL A A6315T1094 Control Column Installation Figure 403 (Sheet 1)

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B. Install the Control Column (Refer to Figure 403). (1) Put the control column in position to the bearing support. (2) Move the torque tube forward and attach both control columns to the torque tube with washers and bolts. (3) Install the left and right Support Plate assemblies and the Forward Aileron Pulley Bracket Assembly. (4) Attach the connecting link to the torque tube using bolt, nut, and cotter pin. (a) Install a rig pin in the forward elevator sector. (b) Put an inclinometer on the pilot seat rail and zero it. (c) Put the inclinometer on the aft face of the pilot's control column. (d) Adjust the connecting link to get an angle of 92 degrees, +0.5 or -0.5 degrees between the aft face of the pilot's column and the floor boards (i.e. column angle is 2 degrees forward of vertical). (e) Remove the rig pin. (5) Rig the aileron cables. Refer to Aileron and Tab System Control Cables - Maintenance Practices. (6) Attach the aileron crossover cable and forward aileron control cable. Refer to Aileron and Tab System Control Cables - Maintenance Practices. (7) Connect electrical connector (JC303, left or JF303, right) to the control column wire bundle assembly. (8) Install cockpit floorboard panels 251BT, 251CT, 251BTC, 251CTC, 252CT and 252CTC. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (9) Attach the control column boot to the cockpit floorboard panels with screws. (10) Install the pilot and copilot seats. Refer to Chapter 25, Flight Crew Seats - Maintenance Practices. (11) Remove the maintenance label from the circuit breaker panel. (12) Engage the PITCH TRIM, AUDIO, XPDR, ANG OF ATTACK and AP circuit breakers.

7. Elevator Trim Tab Actuator Removal/Installation A. Remove the Trim Tab Actuator (Refer to Figure 404). (1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel. (a) If possible, turn the elevator trim control wheel until the trim tabs are streamlined with the elevators. (2) Get access to the elevator trim tab actuator and turnbuckles. (a) Remove the tailcone baggage panels 322BT, 322CT, 321BB and 322BB. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Remove the elevator. Refer to Chapter 55, Elevator - Maintenance Practices. (4) Loosen the electric trim cable turnbuckle and the trim tab cable turnbuckles. (5) Remove the cotter pins, nuts, washers, and bolts that attach the pushrods to the elevator trim tab actuator. (6) Remove the screw and spacer from the chain guard and bend the chain guard away from the sprocket. (7) Remove the chain from sprocket. Use tape to hold the chain to the horizontal stabilizer. (8) Remove bolts that attach the elevator trim tab actuator to the horizontal stabilizer. (9) Move the elevator trim tab actuator aft to remove it from the airplane. Measure and record the distance from the face of the actuator to the center of the rod end bearings. B. Install the Trim Tab Actuator (Refer to Figure 404).

NOTE: If trim tab actuator part number 6396022-3 (left) or 6396022-4 (right) is installed, the actuator must also have a stainless steel trim control chain (part number S3526-25-109) installed. The trim tab actuator part number is stamped on the actuator body.

(1) Lubricate the elevator trim tab actuator at the grease fittings with 5565450-28 grease. (a) Manually turn the drive sprocket of the actuator until the distance from the face of the actuator to the center line of the rod end bearings equals the value obtained before. (2) Put the elevator trim tab actuator in position near the horizontal stabilizer. (3) Install the bolts that attach the trim tab actuator to the horizontal stabilizer. (4) Install the elevator onto the aircraft. Refer to Chapter 55, Elevator - Maintenance Practices.

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A29106

ELEVATOR TRIM TAB HORN

PUSHROD

ELEVATOR TRIM TAB ACTUATOR A CABLE OUTBOARD B SPROCKET ADJUSTABLE A PUSHROD

CHAIN BOLT SPACER HORIZONTAL CHAIN STABILIZER B GUARD SCREW

DETAIL A (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE)

6310T1072 A6363T1021 Elevator Trim Tab Actuator Installation Figure 404 (Sheet 1)

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A68735

0.50 INCH MINIMUM SEALANT

CLEVIS OUTBOARD ADJUSTMENT PUSHROD (NOTE 2)

VIEW A-A

TRIM TAB TRIM TRIM TAB ACTUATOR, RIGHT INTERCONNECT PULLEY BRACKET CHAIN ACTUATOR, FS 546.67 LEFT 17.96 TO 18.20 CABLE (NOTE 1) INCHES (456 TO 462 mm)

17.96 TO 18.20 CHAIN INCHES (NOTE 1) (456 TO 462 mm) RBL 29.50 RIGHT TRIM CABLE LEFT TRIM CABLE LBL 29.50

VIEW B-B

NOTE 1: INSTALL THE CHAIN ON THE ACTUATOR SPROCKETS WITH THE EYE OF THE ACTUATOR PUSHROD ALIGNED WITH THE ELEVATOR BEARINGS. CHAINS ARE EQUALLY DISTRIBUTED, TOP AND BOTTOM, WHEN PROPERLY RIGGED AND TRIMMED TO NEUTRAL POSITION OF 7 DEGREES DOWN. NOTE 2: MAKE SURE THAT THE OUTBOARD ADJUSTABLE PUSHROD IS APPROXIMATELY 7.45 INCHES (189.23 mm) BEFORE INSTALLATION.

AA5561T1106 BB6363T1010 Elevator Trim Tab Actuator Installation Figure 404 (Sheet 2)

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(5) Attach the elevator pushrods to the trim tab actuator with bolts, washers, nuts, and cotter pins. (6) Move the elevator to the neutral position. (a) Insert a rig pin to hold the elevator in the aft elevator sector or clamp the horn to the horizontal stabilizer. (7) Put an inclinometer on the elevator which did not have the trim actuator replaced. (a) Put the inclinometer above the trim actuator and align it normal to the hinge line. (b) Zero the inclinometer. (8) Move the inclinometer straight aft onto the trim tab and record the deflection relative to the elevator. (9) Put an inclinometer on the elevator that was replaced. (a) Put the inclinometer above the trim actuator and align it normal to the hinge line. (b) Zero the inclinometer. (10) Move the inclinometer straight aft onto the tab and temporarily attach in place with tape. (11) Manually turn the trim actuator drive sprocket to get the tab deflection recorded before. (12) Clean the free end of the chain with solvent to remove dirt and contaminants. (13) Lubricate the trim tab actuator loop chain with LPS-3 dry lubricant. (14) On Airplanes -0306 and On and Airplanes -0001 thru -0305 that have stainless steel trim tab actuator control chain(s) installed, do not lubricate the trim tab actuator control chain and primary sprocket. (15) On Airplanes -0001 thru -0305 that do not have stainless steel trim tab actuator control chain(s) installed, lubricate the trim tab actuator control chain and sprockets with LPS-3 dry lubricant. (16) Manually hold the opposite tab from to prevent movement. (a) Pull the slack out of the crossover cable and put the chain over the trim actuator drive sprocket. (b) Install the chain over the actuator sprocket.

NOTE: If the opposite tab is not held, the opposite trim actuator can move when you pull on the crossover cable and the trim actuators will not be synchronized.

(17) Connect the fwd and aft elevator trim cables at the turnbuckles. (18) Adjust the elevator trim tab actuator system. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (19) Install the tailcone baggage panels 322BT, 322CT, 321BB and 322BB. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (20) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel.

8. Elevator Trim Tab Pushrod Removal/Installation

NOTE: The outboard adjustable pushrod and pushrod removal/installation are typical. A. Remove the Elevator Trim Tab Pushrod (Refer to Figure 404). (1) Lift the elevator full trailing edge up. (2) Remove the cotter pin, nut, washer, and bolt that attaches the pushrod to the elevator trim tab actuator. (3) Remove the cotter pin, nut, washer, and bolt that attaches the pushrod to the elevator trim tab horn. (4) Remove the pushrod from airplane.

NOTE: If both pushrods were removed, attach the fixed length (inboard) first. Adjust the outboard pushrod as necessary to get a slip fit on the bolt common to the trim actuator. B. Install the Elevator Trim Tab Pushrod (Refer to Figure 404). (1) Make sure that the outboard adjustable pushrod length is nominally 7.45 inches (189.23 mm). (2) Attach the pushrod to the elevator trim tab horn with a bolt, washer, nut, and cotter pin. (3) Lift the elevator trailing edge up and attach the adjustable pushrod to the trim tab actuator with a bolt, washer, nut, and cotter pin. (4) Make sure the elevator trim tab is rigged properly. Refer to Elevator and Tab System Control Cables - Maintenance Practices.

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9. Elevator Trim Control Wheel Removal/Installation A. Remove the Elevator Trim Control Wheel (Refer to Figure 405). (1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel. (2) Turn the trim wheel until the trim indicator pointer is aligned with the forward line of the TO range and put a mark on the wheel. (3) Remove the screws that attach the control wheel to the control quadrant. (4) Remove the control wheel from the airplane.

NOTE: On airplanes -0001 through -0034, the spacer is removed with the control wheel. B. Install the Elevator Trim Control Wheel (Refer to Figure 405). (1) Hold the elevators by clamping the horns to the horizontal stabilizer. (a) Turn the elevator trim sprocket in the cockpit until the tab is streamlined with the elevator. (2) Put an inclinometer on one elevator above the trim actuator and aligned normal to the hinge line. (a) Put a second inclinometer directly aft on the trim tab. Zero both inclinometers. (3) Turn the elevator trim sprocket in the cockpit, until the trim tab is moved 4.0 degrees, +0.5 or -0.5 degrees trailing edge down. (4) Pull the trim indicating pointer aft until it is aligned with the forward line of the TO range. (5) Hold the trim indicating pointer in place while you move the trim wheel so that the mark from made previously is aligned with the pointer. (6) Put the trim control wheel against the spacer and attach with screws.

NOTE: On airplanes -0001 through -0034, the spacer is installed with the same screws as the control wheel.

(7) Remove any restraints from the elevator. (8) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel.

10. Elevator Trim Control Wheel Sprocket and Bearing Removal/Installation A. Remove Elevator Trim Control Wheel Sprocket and Bearing (Refer to Figure 405). (1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel. (a) Turn the trim control wheel until the trim indicator pointer is aligned with the forward line of the TO range. (b) Put a mark on the control wheel in line with the trim indicator pointer. (2) Get access to the trim tab cable turnbuckles. Remove tailcone baggage panels 322BT and 322CT. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (3) Loosen the trim tab control cable turnbuckles. (4) Remove the screws that attach the control wheel to the sprocket. (5) Remove the control wheel and spacer from the airplane. (a) Remove the screws that hold the spacer to the sprocket then remove the spacer.

NOTE: On airplanes -0001 through -0034 the spacer and control wheel have common fasteners.

(6) Remove the electrical and avionics equipment from the aft portion of pedestal, as required, to give access to the trim control components. Refer to applicable sections of the Maintenance Manual. (7) Remove the screws that hold the chain guard around the control sprocket. (8) Remove the chain guard. (9) Remove and keep screws that attach the upper trim edge to the control quadrant. (10) Remove the nut, sleeve, washer, and bolt that attach the sprocket to the control quadrant. (11) Lower the sprocket and bearing to free them from the chain. (12) Remove the sprocket and bearing. B. Install the Elevator Trim Control Wheel Sprocket and Bearing (Refer to Figure 405). (1) Install the sprocket and bearing under the chain. (2) Attach the sprocket to the control quadrant with a bolt, sleeve, washer, and nut.

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A29107 NOSE DOWN MARKER T TRIM NOSE H DOWN R POINTER O FULL DOWN A POSITION T T L T E POINTER 6 DEGREE O TAB TRAILING EDGE DOWN POINTER FULL NOSE UP POSITION IDLE NOSE UP

NOSE UP NUT MARKER SPEED GUARD BRAKE CHAIN A

VIEW A−A A UPPER TRIM EDGE

BOLT

BEARING

SPACER POINTER SCREW SPACER WASHER SPROCKET CONTROL WHEEL

SCREW

6310T1072 DETAIL A A6363T1052 AA5664T1003 Elevator Trim Control Wheel Installation Figure 405 (Sheet 1)

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(3) Attach the upper trim edge to the pedestal with screws kept from the removal. (4) Install the spacer and attach with screws. (5) Make sure the elevator trim system is properly rigged. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (6) Pull the trim indicator pointer aft and align with the forward line of the TO range. (7) Align the mark on the trim wheel with the trim indicator pointer and put it against the spacer. (8) Attach the trim wheel with screws. (9) Install the electrical and avionics equipment, removed for access, into aft portion of pedestal. Refer to applicable sections of the Maintenance Manual. (10) Install tailcone baggage panels 322BT and 322CT. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (11) Engage the PITCH TRIM circuit breaker.

11. Elevator Electric Trim Motor Removal/Installation (Airplanes -0001 thru -0056 and -0058 thru -0450) A. Remove Elevator Electric Trim Motor (Refer to Figure 406). (1) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel. (2) Disconnect electrical connector (PT304) from the elevator electric trim motor (MT001). (3) Disconnect the elevator electric trim cables from the elevator trim cables. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (4) Remove the elevator electric trim cables. (5) Remove the screws and washers that attach the elevator electric trim motor to the mount assembly. (6) Remove the elevator electric trim motor and electric trim cables from the airplane. B. Install the Elevator Trim Motor (Refer to Figure 406). (1) Do an electric trim clutch torque check. (a) Attach the outboard side of the servo capstan to prevent movement of the capstan during torque check. (b) Put a torque wrench on the capstan drive shaft. (c) Turn the shaft and make sure the running torque from the torque wrench is 32 inch-pounds, +3 or -3 inch-pounds (3.62 N-m, +0.34 N-m or -0.34 N-m). 1 Remove the safety wire from the adjustment bolt in the center of the capstan to adjust the torque. 2 Loosen or tighten the bolt as necessary to get 32 inch-pounds, +3 or -3 inch-pounds (3.62 N-m, +0.34 N-m or -0.34 N-m). 3 Put safety wire on the bolt. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices. (2) Install the elevator electric trim cables to the elevator electric trim motor. (3) Install the cables, wind each cable approximately three and one quarter (3 1/4) times around the elevator cable drum. (4) Put the elevator electric trim motor in position and attach it to the mount assembly with screws and washers. (5) Connect the electrical connector (PT304) to elevator electric trim motor. (6) Attach the elevator electric trim cables to the elevator trim cables. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (7) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel. (8) Make sure the elevator trim operates and is properly rigged. Refer to Elevator and Tab System Control Cables - Maintenance Practices.

12. Garmin GSA 81 Elevator Trim Servo Motor Removal/Installation (Airplanes -0057 and -0451 and On)

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 the Model 525B airplane. For the removal/installation of the servo motor, refer to the Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List. A. Remove the Garmin GSA 81 Elevator Trim Servo Motor (Refer to Figure 407). (1) Remove the electrical power from the airplane. (2) Disengage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit.

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A29109

ELEVATOR ELECTRIC TRIM CABLE

CABLE DRUM

MOUNT ELEVATOR ASSEMBLY ELECTRIC TRIM MOTOR

SHELF SUPPORT ELECTRICAL CONNECTOR (PT304)

DETAIL A 6310T1072 A6363T1009 Elevator Electric Trim Motor Installation Figure 406 (Sheet 1)

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A93908 A

SERVO GEARBOX

ELEVATOR TRIM BRACKET ASSEMBLY

ELEVATOR TRIM SERVO MOTOR (UT313)

WASHER

BOLT ELEVATOR TRIM CABLES B

ELECTRICAL CONNECTOR

ELECTRICAL CONNECTOR (JT313)

DETAIL A

6310T1072 A6363T1062

Elevator Trim Servo Installation Figure 407 (Sheet 1)

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A93909

ELEVATOR TRIM CABLE CLAMP BLOCK (NOTE 1)

A CLAMP BLOCK (NOTE 1) (NOTE 2)

BRACKET ELEVATOR WASHER TRIM BOLT SERVO AFT ELEVATOR TRIM A GEARBOX SERVO CABLE

CLIP

TURNBUCKLE FORWARD ELEVATOR TRIM SERVO CABLE IDLER PULLEY

CAPSTAN DRUM DETAIL B CABLE AIRPLANES -0057 AND -0451 THRU -0631 GUARD PIN CAPSTAN COVER NOTE 1: AIRPLANES -0057 AND -0451 THRU -0535 HAVE WASHER SCREWS, WASHERS, AND NUTS THAT ATTACH SCREW THE CLAMP BLOCK HALVES TOGETHER. NOTE 2: ON AIRPLANES -0536 AND ON, ONE OF THE TWO CLAMP BLOCKS HAS THREADS AND HAS SCREWS THAT ATTACH THE CLAMP BLOCK HALVES TOGETHER. THE FORWARD CLAMP BLOCK SCREWS ARE INSTALLED IN THE SAME DIRECTION AS THE AFT CLAMP BLOCK SCREWS. B6363T1070 Elevator Trim Servo Installation Figure 407 (Sheet 2)

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A109430

ELEVATOR TRIM CABLES CLAMP BLOCK

A CLAMP BLOCK

UPPER ELEVATOR TRIM SERVO CABLE BRACKET LOWER AFT ELEVATOR WASHER TRIM SERVO CABLE A BOLT

CLIP TURNBUCKLE LOWER FORWARD ELEVATOR TRIM SERVO CABLE ELEVATOR TRIM SERVO GEARBOX

CAPSTAN DRUM CABLE GUARD PIN CAPSTAN COVER WASHER SCREW

DETAIL B AIRPLANES -0632 AND ON

B6360200-2 Elevator Trim Servo Installation Figure 407 (Sheet 3)

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A109429

LEFT ELEVATOR 1.17 +0.25 or TRIM CABLE -0.25 INCHES 2.08 +0.25 or (29.72 +6.35 -0.25 INCHES or -6.35 mm) (52.83 +6.35 or -6.35 mm)

RIGHT ELEVATOR TRIM CABLE

VIEW A-A AIRPLANES -0057 AND -0451 THRU -0535

LEFT ELEVATOR 1.17 +0.25 or TRIM CABLE -0.25 INCHES 2.08 +0.25 or (29.72 +6.35 -0.25 INCHES or -6.35 mm) (52.83 +6.35 or -6.35 mm)

RIGHT ELEVATOR TRIM CABLE VIEW A-A

AIRPLANES -0536 AND ON AA6360200-2 Elevator Trim Servo Installation Figure 407 (Sheet 4)

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(3) Open the tailcone baggage compartment door. (4) Remove aft baggage compartment panels 322CT and 322ET to get access to the elevator trim servo motor (UT313). Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Disconnect the electrical connector (JT313) from the elevator trim servo motor electrical connector. (6) 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 Publication List. B. Install the Garmin GSA 81 Elevator Trim Servo Motor (Refer to Figure 407). (1) Install the elevator trim servo motor 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 motor (UT313) electrical connector. (3) Engage the PITCH TRIM circuit breaker on the left circuit breaker panel in the cockpit. (4) If a new trim servo motor has been installed, load the correct software and configuration. Refer to Chapter 34, Garmin G3000 Integrated Avionics System - Adjustment/Test (Airplanes with Software Versions 2.3 or 3.2) or (Airplanes with Software Version 4.8 and Later). (5) 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 applicable Garmin G3000 Integrated Avionics System Line Maintenance Manual, P/N 190-01785-00 or 190-02655-00, found in the Introduction, Supplier Publication List. (6) Do the Elevator Trim Control System Functional Check. Refer to Elevator and Tab System Control Cables - Inspection/Check. (7) Install aft baggage compartment panels 322CT and 322ET. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (8) Close the tailcone baggage compartment door.

13. Garmin GSM 86 Elevator Trim Servo Gearbox and Cable Removal/Installation (Airplanes -0057 and -0451 and On)

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 the Model 525B airplane. For the removal/installation of the servo gearbox, refer to the Garmin GSM 86 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 407).

NOTE: The electric trim servo stays attached to the electric trim servo gearbox during the removal 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. (4) Remove aft baggage compartment panels 322CT and 322ET to get access to the elevator trim servo gearbox. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (5) Disconnect the electrical connector (JT313) from the elevator trim servo motor (UT313) electrical connector. (6) On Airplanes -0057 and -0451 thru -0631 remove the clips from the turnbuckle that connects the forward and the aft elevator trim servo cables. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices. (a) Loosen the turnbuckle to release the cable tension. (7) On Airplanes -0632 and On, remove the clips from the turnbuckle that connects the lower forward and the lower aft elevator trim servo cables. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices. (a) Loosen the turnbuckle to release the cable tension.

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(8) Put a mark at the two clamp blocks to show the correct position on the elevator trim cables.

NOTE: The forward edge of the aft clamp block is 2.08 ± 0.25 inches (52.83 ± 6.35 mm) from the edge of the right aft elevator trim cable terminal. The aft edge of the forward clamp block is 1.17 ± 0.25 inches (29.72 ± 6.35 mm) from the edge of the left aft elevator trim cable terminal.

(9) For Airplanes -0057 and -0451 thru -0535, remove the screws, washers, and nuts that attach the clamp blocks to the elevator trim servo cables and the elevator trim cables. (a) Remove the clamp blocks from the cables. (10) For Airplanes -0536 and On, remove the screws that attaches the clamp blocks to the elevator trim servo cables and the elevator trim cables. (a) Remove the clamp blocks from the cables. (11) Remove bolts and the washers that attach the elevator trim servo gearbox to the elevator trim bracket assembly. (12) Remove the elevator trim servo gearbox and the elevator trim servo cables from the airplane and put them on a table. (13) Record how the cable(s) are installed on the capstan drum. (14) Record the position of cable guard pins on the elevator autopilot servo gear box.

NOTE: Airplanes -0057 and -0451 thru -0631 have the Garmin GSM 86 Servo Gear Box installed that includes an idler pulley. It has one cable that is routed around the drum and idler pulley, and it is not attached to the drum. Airplanes -0632 and On have the Garmin GSM 86 Servo Gear Box installed that does not include an idler pulley, and two cables that attach to the drum with retaining clips.

(15) Remove the capstan cover, cable guard pins, and cable(s) from the servo gearbox. Refer to the Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List. (a) For airplanes -0632 and On with the servo gearbox capstan that has retaining clips, the swaged ball ends of the cables can be removed from the drum by sliding the balls past the clips while pressing the retaining clips with a flat screwdriver or similar tool. (16) If necessary, on airplanes -0057 and -0451 thru -0631 disconnect the forward and the aft elevator trim servo cables from the turnbuckle. (17) If necessary, on airplanes -0632 and On, disconnect the lower forward and the lower aft elevator trim servo cables from the turnbuckle. (18) 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 Publication List. B. Install the Elevator Trim Servo Gearbox and Cable (Refer to Figure 407).

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

(1) If necessary, install the elevator trim servo motor (UT313) to the elevator trim servo gearbox. Refer to the Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List. (2) If necessary, on airplanes -0057 and -0451 thru -0631 connect the forward and the aft elevator trim servo cables to the turnbuckle. (3) If necessary, on airplanes -0632 and On, connect the lower forward and the lower aft elevator trim servo cables to the turnbuckle.

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(4) Install the cable(s), cable guard pins, and capstan cover in their recorded positions to the servo gearbox. Refer to the Garmin GSM 86 Servo Gear Box Installation Manual in the Introduction, Supplier Publication List. (5) 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. (6) Put the elevator trim servo cables and the clamp blocks in their recorded position on the elevator trim cables.

CAUTION: The clamp blocks and the nuts must be installed in the correct position to make sure that they do not catch on the adjacent cables or structure. Damage to the cables or the structure can occur if the cables or the nuts are not installed in the correct position.

(a) For Airplanes -0057 and -0451 thru -0535, loosely install the screws, washers, and nuts. (b) For Airplanes -0536 and On, loosely install the screws. (c) Make sure that the nuts are installed on the side away from the adjacent cables. (d) For Airplanes -0057 and -0451 thru -0535, torque the nuts from 12 to 15 inch-pounds (1.35 to 1.69 N-m). (e) For Airplanes -0536 and On, torque the screws from 30 to 40 inch-pounds (3.39 to 4.51 N-m). Make sure that the clamp blocks do not slip. (7) Do the Elevator Trim Cables Adjustment. Refer to Elevator and Tab System Control Cables - Maintenance Practices. (8) Install the clips in the turnbuckle for the elevator trim servo cables. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices, Locking Clip Installation. (9) Connect the electrical connector (JT313) to the elevator trim servo motor 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, load the correct software and configuration. Refer to Chapter 34, Garmin G3000 Integrated Avionics System - Adjustment/Test (Airplanes with Software Versions 2.3 or 3.2) or (Airplanes with Software Version 4.8 and Later). (12) 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 applicable Garmin G3000 Integrated Avionics System Line Maintenance Manual, P/N 190-01785-00 or 190-02655-00, found in the Introduction, Supplier Publication List. (13) Do the Elevator Trim Control System Functional Check. Refer to Elevator and Tab System Control Cables - Inspection/Check. (14) Install aft baggage compartment panels 322CT and 322ET. Refer to Chapter 6, Access Plates and Panels Identification - Description and Operation. (15) Close the tailcone baggage compartment door.

14. Pitch Trim Switch Removal/Installation (Airplanes -0057 and -0451 and On) A. Remove the Pitch Trim Switch (Refer to Figure 408).

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.

27-30-02 Page 425 © TEXTRON AVIATION INC. Jul 13/2020 ICA-525B-27-00009 Form 2261 Rev 1 CESSNA® MODEL 525B MAINTENANCE MANUAL

A95520

A PITCH TRIM SWITCH (SC313 PILOT’S SF313 COPILOT’S) ALLEN SCREW

CONTROL WHEEL CAP

NUT CONTROL WHEEL

SET SCREW WASHER

DETAIL A LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE

6310T1072 A6760T1106 Pitch Trim Switch Installation Figure 408 (Sheet 1)

27-30-02 Page 426 © TEXTRON AVIATION INC. Jul 13/2020 ICA-525B-27-00009 Form 2261 Rev 1 CESSNA® MODEL 525B MAINTENANCE MANUAL

(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 525B Wiring Diagram Manual. (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 408).

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 the Citation Standard Practices Manual, Chapter 20, Anaerobic Adhesives - Maintenance Practices. (b) Install the set screw. (2) Put the control wheel cap sufficiently 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 525B Wiring Diagram Manual. (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. (4) Do the Elevator Trim Control System Functional Check. Refer to Elevator and Tab System Control Cables - Inspection/Check.

TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-525B-27-00009 APPENDIX A: ILLUSTRATED PARTS CATALOG

Nomenclature Part Number Quantity GSM 86 Servo Mount 011-02490-21 1 Standoff Kit 011-01028-09 1 Cable, Elevator Trim Lower 6361013-18 1 Forward Cable, Elevator Trim Upper 6361013-19 1

TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-525B-27-00009 APPENDIX B: WIRING DIAGRAM MANUAL

NOT APPLICABLE