Citation SERVICE BULLETIN SB525C-56-01

CESSNA CITATION JET · Maintenance Manual

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Overview

This service bulletin provides instructions and parts for modifying the windshield and cockpit side window frames of the Cessna 525C (CJ4) aircraft. The modification aims to enhance moisture protection by adding new ground plates and sealing around the window frames. Compliance with this bulletin is recommended during scheduled maintenance periods or inspections. The document outlines the necessary steps for inspection, removal, and installation of components, as well as the materials and tools required for the task. It emphasizes the importance of using Textron Aviation-approved parts and practices to ensure safety and compliance with aviation standards.

The service bulletin applies to Cessna 525C (CJ4) aircraft with specific serial number ranges.
Modification is recommended during scheduled maintenance to prevent moisture incursion.
A total of 162 labor hours is estimated for the modification process.
Specific materials and part numbers are required for the installation, including various sealants and ground plates.
Compliance documentation must be recorded in the aircraft logbook.

Document

Source

Originally published by www.weststaraviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Maintenance Manual
Year: 2024
Pages: 22
File size: 2.2 MB
Publisher: www.weststaraviation.com

Documentation completeness

4/7

Most owners only have the POH. Here's the essential set for the CESSNA CITATION JET.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

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In this document

Effectivity

The service bulletin applies to Cessna 525C (CJ4) aircraft with serial numbers ranging from -0001 to -0414, excluding specific serial numbers. It specifies which aircraft are affected and which have already incorporated the changes in production.

Compliance

The bulletin recommends that the modifications be performed during scheduled maintenance. It outlines the requirements for documenting compliance, including the need for a qualified mechanic to complete all instructions and use only approved parts.

Materials Required

A list of consumable materials and parts is provided, including epoxy primer, sealants, and specific ground plates. The bulletin specifies the part numbers and quantities needed for the modification.

Accomplishment Instructions

Detailed step-by-step instructions are provided for removing existing windshields and side windows, inspecting for corrosion, and installing new ground plates. The instructions include cautions to prevent damage during the process and emphasize the need for proper sealing and bonding.

Labor Hours

The bulletin estimates that the modification will require approximately 162 labor hours to complete, providing a guideline for maintenance facilities to plan their work.

Safety notes

Ensure protective covering is applied to windshields before removal to prevent damage.
Inspect for corrosion and report any findings to Team Structures using the online Web SDR Form.

Full document text

Citation SERVICE BULLETIN SB525C-56-01 TITLE WINDOWS - WINDSHIELD AND COCKPIT SIDE WINDOW FRAME MODIFICATION EFFECTIVITY MODEL SERIAL NUMBERS 525C (CJ4) -0001 thru -0024, -0026 thru -0028, -0030 thru -0040, -0042, -0044 thru -0072, -0074 thru -0154, -0156 thru -0208, -0210 thru -0230, -0232 thru -0313, -0315 thru -0414 NOTE: Textron Aviation-owned or Textron Aviation-authorized Service Centers are the only facilities that can complete this service document. The equivalent of this service document has been incorporated on production airplanes -0025, -0029, -0041, -0043, -0073, -0155, -0209, -0231, -0314 and -0415 and On. REASON To add new windshield ground plates and sealing to the area around the frame of the windshields and cockpit side windows to decrease the potential for moisture incursion. DESCRIPTION This service document provides parts and instructions to inspect the windshield and cockpit side windows installation and install new ground plates. COMPLIANCE RECOMMENDED. This service document should be accomplished at a scheduled maintenance period or inspection. A service document published by Textron Aviation may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service document, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service document kit. Only with written authorization from Textron Aviation can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service document only as approved and published. 4) The mechanic or airplane owner must apply the information in the service document only to aircraft serial numbers identified in the Effectivity section of the document. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Textron Aviation is authorized to make or apply any changes to a Textron Aviation-issued service document or flight manual supplement without prior written consent from Textron Aviation. Textron Aviation is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Textron Aviation-owned Service Center. SB525C-56-01 April 29, 2024 Page 1 of 18 Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800 This document 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 COPYRIGHT © 2024 SB525C-56-01 Page 2 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 APPROVAL Textron Aviation received FAA approval for the technical data in this publication that changes the airplane type design. FLIGHT CREW OPERATIONS No Changes CONSUMABLE MATERIAL You must use the consumable materials that follow, or their equivalent, to complete this service document. NAME NUMBER MANUFACTURER USE Epoxy Primer 10P8-11 (Base) Akzo Nobel Aerospace Coatings 1 East Water Street Waukegan, IL 60085 Color Chemical Film Treatment U074093 (Bonderite M-CR 1132 Aero pen or Alodine 1132 Touch n Prep) Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS 67215 To prepare bare aluminum surface for intermediate primer. Sealant U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS 67215 To seal nuts, nut plates, ground plates and fay seal cockpit side window retainers. Sealant (Type XII, Grade 2) PR-1425 Class B or PR-1425CF Semkits PPG Aerospace PRC-DeSoto Int'l Inc. 11601 United Street Mojave, CA 91209 To be used as a windshield and window sealant. Parting Agent MoldMates 3460 or equivalent Textron Aviation Parts Distribution 7121 Southwest Boulevard Wichita, KS 67215 To prevent sealant sticking. Adhesive U000370 (3M DP820) Minnesota Mining and Manufacturing Company Adhesive Coatings and Sealers Division - 3M 3M Center St. Paul, MN 55144 To install rivetless adhesive nutplates. TOOLING No specialized tooling is required to complete this service document. WEIGHT AND BALANCE INFORMATION Negligible REFERENCES Cessna Model 525C Maintenance Manual (Revision 12 or later) Citation Standard Practices Manual (Revision 6 or later) Cessna Model 525C Structural Repair Manual (Revision 6 or later) PUBLICATIONS AFFECTED Cessna Model 525C Illustrated Parts Catalog Citation SERVICE BULLETIN SB525C-56-01 ACCOMPLISHMENT INSTRUCTIONS 1. Remove the windshields and cockpit side window installations. CAUTION: Make sure to add protective covering to the inside and outside of the windshields and cockpit side windows prior to removal. A. Remove the left and right windshield. (Refer to the Model 525C Maintenance Manual, Chapter 56, Windshield - Removal/Installation.) (1) Discard the attaching fasteners. B. (Airplanes -0001 thru -0388) Remove the left and right cockpit side window and retainers. (Refer to the Model 525C Maintenance Manual, Chapter 56, Cockpit Side Window - Removal/Installation.) (1) Discard the attaching fasteners. NOTE: It is permissible to leave the left and right cockpit side windows installed. To prevent them from falling out, after removal of window retainer, loosely reinstall two fasteners on opposite sides to prevent the window from moving. 2. Remove and discard the 7111013-3, 7111013-4, 7111013-9, 7111013-10, 7111013-11, 7111013-12 Ground Plates and fasteners from the airplane structure. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Fastener Installation and Removal.) 3. (Airplanes -0001 thru -0388) Inspect the following areas of the left and right windshield and cockpit

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side window installations: CAUTION: Make sure not to damage the paint when removing sealant. A. Remove any remaining fillet seal from the fuselage skin using best shop practices to prevent damaging the paint or primer. B. Visually inspect the fuselage skins and structure under and around the windshields and side window retainers and paint up to 2.0 inches outward from the edge of the retainers for bubbling, blistering or chipping of paint, or any signs of corrosion. NOTE: Removal of paint to perform the inspection is not required. C. Visually inspect for any previous skin repairs under the windshields and side window retainers. Verify any identified repairs have been addressed by an approved field repair. (1) If skin repairs are found with no approved field repair, report damage to Team Structures using the online Web SDR Form located at https://ww2.txtav.com/service/tasdaq. D. Visually inspect the bores of all open holes from the removed screws and fasteners for any signs of corrosion. (Refer the Model 525C Structural Repair Manual, Chapter 51, Crack, Scratch, Gouge and Corrosion.) NOTE: Make sure to inspect the two fastener holes that are loosely holding the cockpit side windows in place from the NOTE in Step 1.B. NOTE: The holes may need to be cleaned using best shop practices to remove sealant for proper inspection. E. If any corrosion is found, report damage to Team Structures using the online Web SDR Form located at https://ww2.txtav.com/service/tasdaq. F. If no corrosion is found, go to Step 5. 4. (Airplanes -0389 thru -0414) Inspect the following areas of the left and right windshield installations: CAUTION: Make sure not to damage the paint when removing sealant. A. Remove any remaining fillet seal from the fuselage skin using best shop practice to prevent damaging the paint or primer. SB525C-56-01 April 29, 2024 Page 3 SB525C-56-01 Page 4 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 B. Visually inspect the fuselage skins and structure under and around the windshields and paint up to 2.0 inches outward from the edge of the retainers for bubbling, blistering or chipping of paint or any signs of corrosion. NOTE: Removal of paint to perform the inspection is not required. C. Visually inspect for any previous skin repairs under the windshields. Verify any identified repairs have been addressed by an approved field repair. (1) If skin repairs are found with no approved field repair, report damage to Team Structures using the online Web SDR Form located at https://ww2.txtav.com/service/tasdaq. D. Visually inspect the bores of all open holes from the removed screws and fasteners for any signs of corrosion. (Refer the Model 525C Structural Repair Manual, Chapter 51, Crack, Scratch, Gouge and Corrosion.) NOTE: Holes may need to be cleaned using best shop practices to remove sealant for proper inspection. E. If any corrosion is found, report damage to Team Structures using the online Web SDR Form located at https://ww2.txtav.com/service/tasdaq. F. If no corrosion is found, go to Step 5. 5. (Refer to Figure 1, Detail A. Detail B, View A-A, View B-B, View C-C, View D-D, View E-E, View F-F and Figure 2, Detail A and View A-A.) Install a new 7111013-13 Left Upper Mid Outboard Ground Plate, 7111013-14 Right Upper Mid Outboard Ground Plate, 7111013-15 Left Upper Outboard Ground Plate, 7111013-16 Right Upper Outboard Ground Plate, 7111013-17 Left Lower Mid Outboard Ground Plate, 7111013-18 Right Lower Mid Outboard Ground Plate, 7111013-19 Left Upper Inboard Ground Plate, 7111013-20 Right Upper Inboard Ground Plate, 7111013-23 Left Lower Inboard Ground Plate and 7111013-24 Right Lower Inboard Ground Plate. A. Temporarily locate each ground plate on the airplane structure. B. Locate and mark existing skin bond assembly fasteners that will need to be removed to secure each new ground plate. C. Remove the ground plates from the airplane structure. D. Carefully remove all identified existing fasteners at each new ground plate location. (1) When removing existing fasteners, create and save conical washers for use during installation of bonding plates. E. Clean the removed fastener holes with Methyl n-Propyl Ketone. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) F. Apply U074093 color chemical film treatment to the holes at the removed fastener locations. G. Temporarily locate each ground plate on the airplane structure. NOTE: The ground plate is non-structural. The edge distance can not be less than 0.16 inch. (1) (Refer to Figure 1, View A-A and Detail B.) Locate the new 7111013-13 Left Upper Mid Outboard Ground Plate, 7111013-14 Right Upper Mid Outboard Ground Plate, 7111013-15 Left Upper Outboard Ground Plate, 7111013-16 Right Upper Outboard Ground Plate, 7111013-17 Left Lower Mid Outboard Ground Plate, 7111013-18 Right Lower Mid Outboard Ground Plate, 7111013-19 Left Upper Inboard Ground Plate and 7111013-20 Right Upper Inboard Ground Plate. (a) Center the cutouts around the existing windshield bolt holes and locate them 0.5 inches from the center of the existing bolt hole to the outside edge of the ground plate. (2) (Refer to Figure 1, View A-A and Detail B.) Locate the new 7111013-23 Left Lower Inboard Ground Plate and 7111013-24 Right Lower Inboard Ground Plate with the curved edge of the Citation SERVICE BULLETIN SB525C-56-01 plate matching the curvature of the windshield skin opening. The plate should be rotated to center the ground plate cutouts between the existing windshield bolt holes. H. Mark hole locations on each ground plate to match existing hole locations on the airplane structure. I. Remove the ground plates from the airplane structure. J. Drill three 0.1625 to 0.1645 inch-diameter holes in the marked locations in the 7111013-13 Left Upper Mid Outboard Ground Plate and 7111013-14 Right Upper Mid Outboard Ground Plate. (1) Countersink the 0.1625 to 0.1645 inch-diameter holes 100° x 0.290 inch-diameter. K. Drill three Number 30 (0.128 inch-diameter) holes in the marked locations in the 7111013-15 Left Upper Outboard Ground Plate and 7111013-16 Right Upper Outboard Ground Plate. (1) Countersink the Number 30 (0.128 inch-diameter) holes 100° x 0.225 inch-diameter. L. Drill two 0.1625 to 0.1645 inch-diameter holes in the marked locations in the 7111013-17 Left Lower Mid Outboard Ground Plate and 7111013-18 Right Lower Mid Outboard Ground Plate. (1) Countersink the 0.1625 to 0.1645 inch-diameter holes 100° x 0.290 inch-diameter. M. Drill two Number 30 (0.128 inch-diameter) holes in the marked locations in the 7111013-19 Left Upper Inboard Ground Plate and 7111013-20 Right Upper Inboard Ground Plate. (1) Countersink the Number 30 (0.128 inch-diameter) holes 100° x 0.225 inch-diameter. N. Drill four Number 30 (0.128 inch-diameter) holes in the marked locations in the 7111013-23 Left Lower Inboard Ground Plate and 7111013-24 Right Lower Inboard Ground Plate. (1) Countersink the Number 30 (0.128 inch-diameter) holes 100° x 0.225 inch-diameter. O. Deburr the holes that were drilled. P. Clean the holes with Methyl n-Propyl Ketone and apply U074093 color chemical film treatment. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) Q. Lightly clean the ground plates with Methyl n-Propyl Ketone. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) NOTE: Lightly cleaning the ground plates will make sure the color chemical film treatment will not be removed. R. Polish the areas of the windshield retainer and skin to the base metal that will be in contact with the grounding plates. (Refer the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) (1) Do not remove any metal material. (2) Only remove the protective finish. (3) Polish the skins and retainers by hand with a very fine scotch brite pad. S. Apply U074093 color chemical film treatment to any bare aluminum under and around the ground plates. (Refer to the Citation Standard Practices Manual, Chapter 20, Exterior Finish - Cleaning/Painting.) T. Locate the conical washers created in Step 5.D or fabricate 10 conical washers from the heads of CM3827AD4 Rivets and 10 conical washers from the heads of CM3827AD5 Rivets. NOTE: The conical washers must be made from driven rivets for proper shape. U. Install the 7111013-13 Left Upper Mid Outboard Ground Plate and 7111013-14 Right Upper Mid Outboard Ground Plate. (1) Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to the 7111013-13 Left Upper Mid Outboard Ground Plate and 7111013-14 Right Upper Mid Outboard Ground Plate to make a fay seal between each grounding plate and skin. (Refer to the Citation SB525C-56-01 April 29, 2024 Page 5 SB525C-56-01 Page 6 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) (2) Attach the 7111013-13 Left Upper Mid Outboard Ground Plate and 7111013-14 Right Upper Mid Outboard Ground Plate to the airplane structure with three each conical washers (made in Step 5.D or from CM3827AD5 Rivet heads made in Step 5.T), HL19PB-5-5 Hi-Lok Pins and HL70-5 Hi-Lok Collars. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) V. Install the 7111013-15 Left Upper Outboard Ground Plate and 7111013-16 Right Upper Outboard Ground Plate. (1) Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to make a fay seal between each grounding plate and skin. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) (2) Attach the 7111013-15 Left Upper Outboard Ground Plate and 7111013-16 Right Upper Outboard Ground Plate to the airplane structure with three each conical washers (made in Step 5.D or from CM3827AD4 Rivet heads made in Step 5.T) and CM3827AD4 Rivets. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) W. Install the 7111013-17 Left Lower Mid Outboard Plate and 7111013-18 Right Lower Mid Outboard Plate. (1) Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to make a fay seal between each grounding plate and skin. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) (2) Attach the 7111013-17 Left Lower Mid Outboard Ground Plate and 7111013-18 Right Lower Mid Outboard Ground Plate with two each conical washers (made in Step 5.D or from CM3827AD5 Rivet heads made in Step 5.T), HL19PB5-5 Hi-Lok Pins and HL70-5 Hi-Lok collars. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) X. Install the 7111013-19 Left Upper Inboard Ground Plate and 7111013-20 Right Upper Inboard Ground Plate. (1) Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to make a fay seal between each grounding plate and skin. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) (2) Attach the 7111013-19 Left Upper Inboard Ground Plate and 7111013-20 Right Upper Inboard Ground Plate to the airplane structure with two each conical washers (made in Step 5.D or from CM3827AD4 Rivet heads made in Step 5.T) and CM3827AD4 Rivets. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) Y. Install the 7111013-23 Left Lower Inboard Ground Plate and 7111013-24 Right Lower Inboard Ground Plate. (1) Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to make a fay seal between each grounding plate and skin. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) (2) Attach the 7111013-23 Left Lower Inboard Ground Plate and 7111013-24 Right Lower Inboard Ground Plate to the airplane structure with four CM3827AD4 Rivets. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) Z. Plug any holes left open at the previous ground plate locations with CM3827AD4 Rivets installed wet with U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Pressure, Weather and High Temperature Sealing - Maintenance Practices.) Citation SERVICE BULLETIN SB525C-56-01 AA. Do a Type I electrical bond check between each grounding plate and the surrounding skin structure. (Refer to the Citation Standard Practices Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices.) AB. Apply U074093 color chemical film treatment to any bare aluminum around the new ground plates and where the removed ground plates were located. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) AC. Touch up any bare aluminum around the new ground plates and where the removed ground plates were located with 10P8-11 corrosion resistant primer. (Refer to the Model 525C Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) NOTE: The surfaces of the grounding plates that will mate directly with the windshield retainer should have color chemical film treatment only and no primer. AD. Fillet seal around the new ground plates with U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) AE. Apply U470637 (Type I, Class B1/2) or U470642 (Type I, Class B2) Sealant to the driven head of the installed fasteners to create a dome seal. (Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure, and High-Temperature Sealing - Maintenance Practices.) 6. (Refer to Figure 1, Detail A.) Inspect the rivetless nutplates. A. If the rivetless nutplates are all secure, go to Step 7. B. If any of the rivetless nutplates have come loose, replace the applicable rivetless nutplate(s). (Refer to the Model 525C Structural Repair Manual, Chapter 51, Fastener Installation and Removal.) (1) Inspect for the presence of the correct 10P8-11 corrosion resistant primer in the windshield bolt holes. If the primer is damaged or not present, corrosion resistant primer needs to be added. 7. Apply corrosion resistant primer and seal the windshields prior to installation. (Refer to the Model 525C Maintenance Manual, Chapter 56, Windshield - Removal/Installation.) NOTE: The surfaces of the grounding plates that will mate directly with the windshield retainer should have color chemical film treatment only and no primer. 8. Install the left and right windshield with new NAS1580C3R11 Bolts. (Refer to the Model 525C Maintenance Manual, Chapter 56, Windshield - Removal/Installation.) A. Do a Type I electrical bond check of the windshield retainers. (Refer to the Citation Standard Practices Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices.) 9. (Airplanes -0001 thru -0388) Apply corrosion resistant primer and seal the left and right cockpit side window retainers prior to installation. (Refer to the Model 525C Maintenance Manual, Chapter 56, Cockpit Side Window - Removal/Installation.) 10. (Airplanes -0001 thru -0388) (Refer to Figure 2, Detail A, View A-A.) Install the left and right cockpit side windows and retainers with new NAS1580C3R4 Bolts, NAS1580C3R15 Bolts, NAS1149F0363P Washers and MS21044N3 Nuts. (Refer to the Model 525C Maintenance Manual, Chapter 56, Cockpit Side Window - Removal/Installation.) A. Use two NAS1149F0636P Washers on each NAS1580C3R15 Bolt during installation to achieve proper torque. 11. Do the Windshield Temperature Controller Operational Check. (Refer to the Model 525C Maintenance Manual, Chapter 30, Windshield Temperature Controller - Adjustment/Test.) 12. Do the Pressure Vessel Leak Check. (Refer to the Model 525C Maintenance Manual, Chapter 21, Pressurization - Inspection/Check.) A. After completing the pressure vessel leak check, do a one time re-torque of all windshield bolts to 38-40 inch-pounds. (Refer to the Citation Standard Practices Manual, Chapter 20, Torque Data - Maintenance Practices.) SB525C-56-01 April 29, 2024 Page 7 SB525C-56-01 Page 8 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 13. Make an entry in the airplane logbook that states compliance and method of compliance with this service document. NOTE: Textron Aviation recommends that compliance with all service documents is reported to a maintenance tracking system provider. • Complete a record of compliance. (Maintenance Transaction Report, Log Book Entry, or other record of compliance) • Put a copy of the completed record of compliance in the airplane logbook. • Send a copy of the completed record of compliance to the maintenance tracking system provider used. Citation SERVICE BULLETIN SB525C-56-01 Figure 1. Windshield Frame Ground Plate Installation (Sheet 1) SB525C-56-01 April 29, 2024 Page 9 SB525C-56-01 Page 10 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 Figure 1. Windshield Frame Ground Plate Installation (Sheet 2) Citation SERVICE BULLETIN SB525C-56-01 Figure 2. Ground Plate Locations (Sheet 1) SB525C-56-01 April 29, 2024 Page 11 SB525C-56-01 Page 12 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 Figure 2. Ground Plate Locations (Sheet 2) Citation SERVICE BULLETIN SB525C-56-01 Figure 2. Ground Plate Locations (Sheet 3) SB525C-56-01 April 29, 2024 Page 13 SB525C-56-01 Page 14 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 Figure 2. Ground Plate Locations (Sheet 4) Citation SERVICE BULLETIN SB525C-56-01 Figure 3. Cockpit Side Window Frame Sealing (Sheet 1) SB525C-56-01 April 29, 2024 Page 15 SB525C-56-01 Page 16 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 Figure 4. Windshield And Side Window Corrosion Inspection (Sheet 1) Citation SERVICE BULLETIN SB525C-56-01 MATERIAL INFORMATION Order the kit/parts below to install this modification. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION SB525C-56-01 1 Kit, consisting of the following parts: CM3827AD4-10 84 Rivet CM3827AD5-10 15 Rivet HL19PB-5-5 10 Hi-Lok Pin HL70-5 10 Hi-Lok Collar MS21044N3 154 Nut NAS1149F0363P 308 Washer NAS1580C3R4 8 Bolt NAS1580C3R11 122 Bolt NAS1580C3R15 146 Bolt 7111013-13 1 Left Upper Mid Outboard Ground Plate 7111013-14 1 Right Upper Mid Outboard Ground Plate 7111013-15 1 Left Upper Outboard Ground Plate 7111013-16 1 Right Upper Outboard Ground Plate 7111013-17 1 Left Lower Mid Outboard Ground Plate 7111013-18 1 Right Lower Mid Outboard Ground Plate 7111013-19 1 Left Upper Inboard Ground Plate 7111013-20 1 Right Upper Inboard Ground Plate 7111013-23 1 Left Lower Inboard Ground Plate 7111013-24 1 Right Lower Inboard Ground Plate SB525C-56-01 1 Instructions SB525C-56-01 April 29, 2024 Page 17 SB525C-56-01 Page 18 April 29, 2024 Citation SERVICE BULLETIN SB525C-56-01 It may be necessary to order the parts below to install this modification. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION CB6008CR3-4P As Required Rivetless Nutplate CB6008CR3-5P As Required Rivetless Nutplate CB6008CR3-6P As Required Rivetless Nutplate R441257 300 inches Seal R881500 300 inches Seal * Please contact your Regional Textron Aviation Parts Distribution Customer Support Team for current cost and availability of parts listed in this service document. Phone at 1-800-835-4000 (Domestic) or 1-316-517-5603 (International). For more information, please visit the TAPD Support & Aftermarket Account Management website at https://ww2.txtav.com/Parts/Promos/TAPD. Based on availability and lead times, parts may require advanced scheduling. Citation OWNER ADVISORY SB525C-56-01 TITLE WINDOWS - WINDSHIELD AND COCKPIT SIDE WINDOW FRAME MODIFICATION TO: Cessna CJ4 Model Aircraft Owner REASON To add new windshield ground plates and sealing to the area around the frame of the windshields and cockpit side windows to decrease the potential for moisture incursion. COMPLIANCE RECOMMENDED. This service document should be accomplished at a scheduled maintenance period or inspection. LABOR HOURS WORK PHASE LABOR-HOURS Modification 162.0 MATERIAL AVAILABILITY PART NUMBER AVAILABILITY COST SB525C-56-01 * * CB6008CR3-4P * * CB6008CR3-5P * * CB6008CR3-6P * * R441257 * * R881500 * * * Please contact your Regional Textron Aviation Parts Distribution Customer Support Team for current cost and availability of parts listed in this service document. Phone at 1-800-835-4000 (Domestic) or 1-316-517-5603 (International). For more information, please visit the TAPD Support & Aftermarket Account Management website at https://ww2.txtav.com/Parts/Promos/TAPD. Based on availability and lead times, parts may require advanced scheduling. WARRANTY This service document is recommended. Eligible airplanes may qualify for parts and labor coverage to the extent noted in the Labor Hours and Material Availability sections of this document. SB525C-56-01 April 29, 2024 Page 1 of 2 Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800 This document 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 COPYRIGHT © 2024 SB525C-56-01 Page 2 April 29, 2024 Citation OWNER ADVISORY SB525C-56-01 Eligibility: Airplanes identified within the serial number effectivity of this service document must have active Airframe warranty coverage on the original issue date of this document. Parts Coverage: Textron Aviation-owned and Textron Aviation-authorized Service Facilities, operators, or other maintenance facilities may submit a claim for the parts required to accomplish this service document as defined in the Material Availability section of this document. Labor Coverage: Textron Aviation-owned and Textron Aviation-authorized Service Facilities rated to perform maintenance on the specific model of Cessna Aircraft may submit a claim for the labor necessary to accomplish this service document as defined in the Labor Hours section of this document. Credit Application: After this service document has been accomplished, a claim must be submitted to Textron Aviation within 30 days of the service document completion. Claims for compliance of this service document are to be filed as a W4 type claim. Please submit your claim form online at ww2.txtav.com/Parts or email the completed Textron Aviation Claim Form to warranty@txtav.com. If submitted on-line a Return Authorization will be provided. If a paper claim is submitted your claim will be entered into the system and a Return Authorization will be sent to you. The Return Authorization must accompany any required return parts (see Material Availability), to the point of purchase. Parts to be returned to Textron Aviation should be forwarded to: TEXTRON AVIATION INC CORE RETURNS 201 N GREENWICH RD BLDG 94 Wichita, KS 67206-2558 Expiration: April 29, 2029 (After this date the owner/operator assumes the responsibility for compliance costs.) Textron Aviation reserves the right to void continued airplane warranty coverage for the parts affected by this service document until the service document is accomplished. NOTE: As a convenience, service documents are now available online to all our customers through a simple, free-of-charge registration process. If you would like to sign up, please visit the Customer Access link at support.txtav.com to register.

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