HYDRAULIC POWER - STAINLESS STEEL TUBE ASSEMBLY INSTALLATION

CESSNA CITATION JET · Service Bulletins

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Overview

This service bulletin, SB525A-29-07, addresses the installation of stainless steel hydraulic tube assemblies in the flap wells of the Cessna 525A (CJ2) and 525A (CJ2+) aircraft. It is aimed at aircraft owners and maintenance personnel, providing detailed instructions and parts necessary for the modification. The bulletin highlights the importance of addressing premature corrosion of aluminum hydraulic tubes due to environmental conditions. Compliance with this bulletin is optional and can be performed at the discretion of the aircraft owner, but it must be completed by Cessna-owned or authorized service centers to ensure proper maintenance and compliance with FAA regulations.

This service bulletin applies to Cessna 525A (CJ2) and 525A (CJ2+) models.
Installation of stainless steel hydraulic tubes is recommended to prevent corrosion.
Compliance with the bulletin is optional but must be performed by authorized service centers.
The weight change from the installation is +4.32 pounds for kit SB525A-29-07-0.
Safety warnings emphasize the importance of securing the landing gear during maintenance.

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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: Service Bulletins
Year: 2011
Pages: 12
File size: 65 KB
Publisher: www.weststaraviation.com

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In this document

Effectivity

The service bulletin applies to Cessna 525A (CJ2) aircraft with serial numbers -0001 through -0244 and Cessna 525A (CJ2+) aircraft with serial numbers -0300 and on. If an aircraft's marketing designation is not listed, this bulletin does not apply.

Compliance

Compliance with this service bulletin is optional. However, it must be recorded in the aircraft logbook only after all instructions are completed by a qualified mechanic, using the correct parts supplied with the service bulletin kit.

Installation Instructions

The bulletin provides step-by-step instructions for replacing aluminum hydraulic tube assemblies with stainless steel ones. Key steps include lifting the aircraft, connecting hydraulic power, measuring flap and landing gear operation times, and ensuring proper installation of the new tube assemblies.

Weight and Balance Changes

The installation of the new tube assemblies results in a weight change of +4.32 pounds for kit SB525A-29-07-0, while kit SB525A-29-07-1 has a negligible weight change.

Safety Warnings

Several warnings are included regarding the risk of accidental landing gear extension during the installation process. It is crucial to ensure the landing gear is down and locked before removing or installing hydraulic lines.

Safety notes

Accidental landing gear extension can occur if the emergency release cable is moved during hydraulic line work.
Ensure the landing gear is down and locked before removing or installing hydraulic lines.

Full document text

Citation SERVICE BULLETIN SB525A-29-07 TITLE HYDRAULIC POWER - STAINLESS STEEL TUBE ASSEMBLY INSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS 525A (CJ2) -0001 thru -0244 525A (CJ2+) -0300 and On NOTE: If the marketing designation for your airplane does not appear in the EFFECTIVITY section, this service document does not apply to your airplane. NOTE: SB525A-32-11 Landing Gear - Brake Hydraulic And Pneumatic Tube Improvement must be accomplished prior to or in conjunction with this service bulletin. NOTE: Cessna-owned or Cessna-authorized Citation Service Centers are the only facilities that can complete this service bulletin. REASON Operating the airplane in certain environmental conditions can cause premature corrosion on the hydraulic tube assemblies located in the flap wells. DESCRIPTION This service bulletin provides parts and instructions to replace the aluminum hydraulic tube assemblies located in the flap wells with stainless steel tube assemblies. COMPLIANCE OPTIONAL. This service bulletin can be accomplished at the discretion of the owner. A service bulletin published by Cessna Aircraft Company 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 bulletin, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service bulletin kit. Only with written authorization from Cessna Aircraft Company 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 bulletin only as approved and published. 4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraft serial numbers identified in the “Effectivity” section of the bulletin. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. Mar 9/2011 525A-29-07 Page 1 of 9 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT © 2011 Mar 9/2011 525A-29-07 Page 2 Citation SERVICE BULLETIN SB525A-29-07 No individual or corporate organization other than Cessna Aircraft Company is authorized to make or apply any changes to a Cessna-issued service bulletin, service letter, or flight manual supplement without prior written consent from Cessna Aircraft Company. Cessna Aircraft Company is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Cessna-owned Citation Service Center. FLIGHT CREW OPERATIONS No Changes APPROVAL Cessna received FAA approval for the technical data in this publication that changes the airplane type design. This information is an amendment to the applicable maintenance manual. MANPOWER WORK PHASE MAN-HOURS Modification * MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST SB525A29-07-0 * * SB525A29-07-1 * * * Refer to the Manpower, Material - Cost and Availability, and Warranty sections in the attached Service Bulletin Supplemental Data sheet. CONSUMABLE MATERIAL In addition to the above kit(s), you must use the consumable materials that follow, or their equivalent, to complete this service bulletin. NAME NUMBER MANUFACTURER USE Conical Seal 651-525-9004 Cessna Service Parts & Programs 7121 Southwest Boulevard Wichita, KS 67215 To repair leaking fittings. Conical Seal 651-525-9006 Cessna Service Parts & Programs 7121 Southwest Boulevard Wichita, KS 67215 To repair leaking fittings. CHANGE IN WEIGHT AND BALANCE KITS WEIGHT CHANGE RESULTANT MOMENT MOMENT/100 SB525A-29-07-0 +4.32 pounds +1330.87 inch-pounds +13.31 inch-pounds SB525A-29-07-1 Negligible Negligible Negligible Citation SERVICE BULLETIN SB525A-29-07 REFERENCES Cessna Model 525A Maintenance Manual NOTE: To install stainless steel hydraulic lines on your airplane, you must get the engineering documents that follow. You must use the most recent revision and all of the applicable drawing change notices (DCN) for each engineering document. DOCUMENT NUMBER TITLE 6398018 Aircraft Mod - Hydraulic System PUBLICATIONS AFFECTED Cessna Model 525A Illustrated Parts Catalog ACCOMPLISHMENT INSTRUCTIONS 1. Lift the airplane with jacks. (Refer to the Model 525A Maintenance Manual, Chapter 7, Lifting - Maintenance Practices.) 2. Apply external electrical power. 3. Connect a hydraulic ground power cart. A. Adjust the hydraulic ground power cart to deliver 1,500 PSI and 6 gallons per minute flow rate. 4. Measure the landing gear and flap extension and retraction times. NOTE: Do not perform Step 4 if the aluminum hydraulic line integrity is compromised. A. Make sure that the landing gear extends in less than 5 seconds and retracts in 5 seconds +1.0 or -1.0 second. B. Make sure that the flaps extend and retract within the times listed below: Direction Detent Position Time in seconds Tolerance in seconds Extend 0° to 35° 12.5 +2.0, -2.0 Extend 35° to 60° 1.5 +0.5, -0.5 Retract 60° to 35° 5.5 +1.0, -1.0 Retract 35° to 0° 9.0 +1.0, -1.0 5. Make sure that the 35° flap position switch was not moved. A. Move the flap handle to a position between the 35° detent and 60° detent. B. Make sure that the flap move to 38° +1.0° or -1.0°. C. Adjust the 35° flap position switch if necessary. (Refer to the Model 525A Maintenance Manual, Chapter 27, Flap System - Adjustment/Test.) 6. Extend the flaps to 60°. 7. Make sure that the landing gear is extended. 8. Disconnect the hydraulic ground power cart. 9. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. Mar 9/2011 525A-29-07 Page 3 Mar 9/2011 525A-29-07 Page 4

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Citation SERVICE BULLETIN SB525A-29-07 (2) Disconnect external electrical power. C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" written on them. 10. Disengage the BRAKE SYSTEM circuit breaker on the left circuit breaker panel. 11. Remove the access panels that follow: (Refer to the Model 525A Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.) • 192B • 512DB • 522AB • 612DB • 622AB 12. Depressurize the hydraulic system. WARNING: The landing gear may release from the up and locked position if the landing gear emergency release cable is moved. The emergency gear release may be inadvertently moved when removing and installing the hydraulic lines. Accidental landing gear extension can be avoided if the landing gear is down and locked before the hydraulic lines are removed and installed. 13. Remove and discard the aluminum tube assemblies from the left wheel well, right wheel well, left flap well, and right flap well. (Refer to Cessna Engineering Drawing 6398018-5.) NOTE: Record the position of each tube assembly where they pass through the clamp locations. NOTE: Take pictures or map the routing of the hydraulic tubes to make installation easier. WARNING: The landing gear may release from the up and locked position if the landing gear emergency release cable is moved. The emergency gear release may be inadvertently moved when removing and installing the hydraulic lines. Accidental landing gear extension can be avoided if the landing gear is down and locked before the hydraulic lines are removed and installed. 14. (Airplanes -0001 thru -0084.) Remove and discard the aluminum tube assemblies from the aft dry bay. (Refer to Cessna Engineering Drawing 6398018-5.) 15. Install the stainless steel tube assemblies in the left flap well. (Refer to Cessna Engineering Drawing 6398018-5.) (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose and Fittings - Maintenance Practices.) A. Record the position of the flap and speed brake hoses. NOTE: The position of the hoses is important after they have taken a certain shape or set. The hoses could fail prematurely if they are removed and installed in a different position that opposes their shape or set. The shape or set can be affected by rotating the end fittings to a different position. Make sure that the hoses are installed in the same position as when they were removed. B. Cessna offers the suggestions that follow to help make the installation easier. • Follow the tube routing on the Cessna Engineering Drawing 6398018-5. • Install the 6327012-43 (Gear Extend), 6327012-45 (Gear Retract), and 6327012-61 (LH Brake) Tube Assemblies first. • When installing the stainless steel lines it may be necessary to start inserting the stainless steel lines in the flap well through an additional rib(s) either inboard or outboard of the final location. • Install the stainless steel tube assemblies from inboard to outboard. • Use 651-525-9004 and 651-525-9006 Conical Seals to repair any leaks instead of exceeding the torque specification. C. Torque all tube assembly fittings. (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose, and Fluid Fittings - Maintenance Practices.) Citation SERVICE BULLETIN SB525A-29-07 WARNING: The landing gear may release from the up and locked position if the landing gear emergency release cable is moved. The emergency gear release may be inadvertently moved when removing and installing the hydraulic lines. Accidental landing gear extension can be avoided if the landing gear is down and locked before the hydraulic lines are removed and installed. 16. Install the stainless steel tube assemblies in the right flap well. (Refer to Cessna Engineering Drawing 6398018-5.) (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose and Fittings - Maintenance Practices.) A. Record the position of the flap and speed brake hoses. NOTE: The position of the hoses is important after they have taken a certain shape or set. The hoses could fail prematurely if they are removed and installed in a different position that opposes their shape or set. The shape or set can be affected by rotating the end fittings to a different position. Make sure that the hoses are installed in the same position as when they were removed. B. Cessna offers the suggestions that follow to help make the installation easier. • Follow the tube routing on the Cessna Engineering Drawing 6398018-5. • Install the 6327012-44 (Gear Extend), 6327012-46 (Gear Retract), and 6327012-62 (RH Brake) Tube Assemblies first. • When installing the stainless steel lines it may be necessary to start inserting the stainless steel lines in the flap well through an additional rib(s) either inboard or outboard of the final location. • Install the stainless steel tube assemblies from outboard to inboard. • Use 651-525-9004 and 651-525-9006 Conical Seals to repair any leaks instead of exceeding the torque specification. C. Torque all tube assembly fittings. (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose, and Fluid Fittings - Maintenance Practices.) WARNING: The landing gear may release from the up and locked position if the landing gear emergency release cable is moved. The emergency gear release may be inadvertently moved when removing and installing the hydraulic lines. Accidental landing gear extension can be avoided if the landing gear is down and locked before the hydraulic lines are removed and installed. 17. Install the stainless steel tube assemblies in the left wheel well. (Refer to Cessna Engineering Drawing 6398018-5.) (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose and Fittings - Maintenance Practices.) A. Torque all tube assembly fittings. (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose, and Fluid Fittings - Maintenance Practices.) 18. Install the stainless steel tube assemblies in the right wheel well. (Refer to Cessna Engineering Drawing 6398018-5.) (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose and Fittings - Maintenance Practices.) A. Torque all tube assembly fittings. (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose, and Fluid Fittings - Maintenance Practices.) 19. (Airplanes -0001 thru -0084.) Install the aluminum tube assemblies in the aft dry bay. (Refer to Cessna Engineering Drawing 6398018-5.) 20. Install the kept clamps and fittings. 21. Make sure that the tube assemblies are properly clamped. 22. Make sure that the tube assemblies and hoses are in the correct positions and orientations. (Refer to Cessna Engineering Drawing 6398018-5.) 23. Make sure that the tube assemblies and hoses will not kink, twist, or pinch when the components are extended or retracted. (Refer to the Model 525A Maintenance Manual, Chapter 20, Tubing, Hose and Fittings - Maintenance Practices.) Mar 9/2011 525A-29-07 Page 5 Mar 9/2011 525A-29-07 Page 6 Citation SERVICE BULLETIN SB525A-29-07 24. Engage the BRAKE SYSTEM circuit breaker on the left circuit breaker panel. 25. Apply external electrical power. 26. Connect a hydraulic ground power cart. 27. Do the landing gear pneumatic brake system functional check. (Refer to the Model 525A Maintenance Manual, Chapter 32, Emergency Brake System Components - Inspection/Check.) 28. Do the emergency landing gear extension test. (Refer to the Model 525A Maintenance Manual, Chapter 32, Landing Gear Extension and Retraction - Adjustment/Test.) CAUTION: Do not fully retract flaps until you can make sure that the flap extend lines are not leaking. If the flaps are fully retracted with the flap extend lines leaking you will not be able to extend the flaps. The flap actuator will lock the flaps in the retracted position and the flap actuator may not receive enough hydraulic pressure to unlock if the flap extend lines are leaking. There is no access to tighten fittings or manual unlock the flap actuator when the flaps are fully retracted. 29. Bleed the hydraulic system. (Refer to the Model 525A Maintenance Manual, Chapter 12, Hydraulic System Reservoir - Servicing.) NOTE: Complete the bleeding task before timing the extension and retraction times. A. Install inclinometers on the flaps. B. Make sure that the landing gear extends in less than 5 seconds and retracts in 5 seconds +1.0 or -1.0 second. C. Make sure that the flaps extend and retract within the times listed below: Direction Detent Position Time in seconds Tolerance in seconds Extend 0° to 35° 12.5 +2.0, -2.0 Extend 35° to 60° 1.5 +0.5, -0.5 Retract 60° to 35° 5.5 +1.0, -1.0 Retract 35° to 0° 9.0 +1.0, -1.0 D. Make sure that the 35° flap position switch was not moved. (1) Move the flap handle to a position between the 35° detent and 60° detent. (2) Make sure that the flap move to 38° +1.0° or -1.0°. (3) Adjust the 35° flap position switch if necessary. (Refer to the Model 525A Maintenance Manual, Chapter 27, Flap System - Adjustment/Test.) 30. Make sure that there are no leaks at the connections for the installed hydraulic tube assemblies. 31. Make sure that the tube assemblies and hoses are not damaged. 32. Make sure that the landing gear and brake pneumatic bottle is properly serviced. (Refer to the Model 525A Maintenance Manual, Chapter 12, Landing Gear and Brake Pneumatic System - Servicing.) 33. Remove the hydraulic ground power cart. 34. Remove external electrical power. 35. Lower the airplane and remove the jacks. (Refer to the Model 525A Maintenance Manual, Chapter 7, Lifting - Maintenance Practices.) 36. Install the access panels that were removed to complete this service bulletin. (Refer to the Model 525A Maintenance Manual, Chapter 6, Access Plates and Panels Identification - Description and Operation.) Citation SERVICE BULLETIN SB525A-29-07 37. Record that this service bulletin has been completed. A. Complete a Maintenance Transaction Report. B. Put a copy of the completed Maintenance Transaction Report in the airplane logbook. C. Send a copy of the completed Maintenance Transaction Report to CESCOM at the following address: CESCOM C/O, Camp Systems International, 8200 East 34th Street North, Building 1600 Suite 1607, Wichita, KS 67226. MATERIAL INFORMATION Order the kit below to install this modification. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION SB525A-29-07-0 1 Kit, consisting of the following parts: 6327011-19 1 Tube Assembly 6327500-31 Discard 6327011-20 1 Tube Assembly 6327500-32 Discard 6327011-37 1 Tube Assembly 63270500-47 or 6327017-31 Discard 6327011-38 1 Tube Assembly 63270500-48 or 6327017-32 Discard 6327011-45 1 Tube Assembly 6317014-15 Discard 6327011-46 1 Tube Assembly 6317014-16 Discard 6327011-49 1 Tube Assembly 6317013-41 or 6317213-25 Discard 6327011-50 1 Tube Assembly 6317013-42 or 6317213-26 Discard 6327011-57 1 Tube Assembly 6327500-19 Discard 6327011-58 1 Tube Assembly 6327500-20 Discard 6327012-1 1 Tube Assembly 6327017-9 Discard 6327012-2 1 Tube Assembly 6327017-10 Discard 6327012-5 1 Tube Assembly 6327017-17 Discard 6327012-6 1 Tube Assembly 6327017-18 Discard 6327012-13 1 Tube Assembly 6392016-9 or 6327016-33 Discard 6327012-14 1 Tube Assembly 6392016-10 or 6327016-34 Discard 6327012-15 1 Tube Assembly 6327016-21 Discard 6327012-16 1 Tube Assembly 6327016-22 Discard 6327012-37 1 Tube Assembly 6317015-31 Discard 6327012-38 1 Tube Assembly 6317015-32 Discard Mar 9/2011 525A-29-07 Page 7 Mar 9/2011 525A-29-07 Page 8 Citation SERVICE BULLETIN SB525A-29-07 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION 6327012-41 1 Tube Assembly 6317015-69 Discard 6327012-42 1 Tube Assembly 6317015-70 Discard 6327012-43 1 Tube Assembly 6327015-26 Discard 6327012-44 1 Tube Assembly 6317015-20 or 6317015-73 Discard 6327012-45 1 Tube Assembly 6317015-39 Discard 6327012-46 1 Tube Assembly 6317015-21 Discard 6327012-47 1 Tube Assembly 6317015-35 Discard 6327012-48 1 Tube Assembly 6317015-36 Discard 6327012-49 4 Tube Assembly 6317015-67 Discard 6327012-51 1 Tube Assembly 6327016-23 Discard 6327012-52 1 Tube Assembly 6727016-24 Discard 6327012-53 1 Tube Assembly 6392016-11 or 6327016-29 Discard 6327012-54 1 Tube Assembly 6392016-12 or 6327016-30 Discard 6327012-55 1 Tube Assembly 6327017-11 or 6327017-33 Discard 6327012-56 1 Tube Assembly 632701712 or 6327017-34 Discard 6327012-57 1 Tube Assembly 6327017-19 Discard 6327012-58 1 Tube Assembly 6327019-20 Discard 6327012-59 1 Tube Assembly 6392016-7 or 6327016-31 Discard 6327012-60 1 Tube Assembly 6392016-8 or 6327016-32 Discard 6327012-61 1 Tube Assembly 6317013-55 Discard 6327012-62 1 Tube Assembly 6317013-56 Discard 6327012-63 1 Tube Assembly 6317014-9 or 6317014-59 Discard 6327012-64 1 Tube Assembly 6317014-10 or 6317014-60 Discard 6327012-65 1 Tube Assembly 6317013-67 or 6317013-81 Discard 6327012-66 1 Tube Assembly 6317014-68 or 6317013-82 Discard 6327012-67 1 Tube Assembly 6317014-23 Discard 6327012-68 1 Tube Assembly 6317014-24 Discard SB525A-29-07 1 Instructions Citation SERVICE BULLETIN SB525A-29-07 (Airplanes -0001 thru -0084.) Order the kit that follows in addition to the SB525A-29-07-0 Kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION SB525A-29-07-1 1 Kit, consisting of the following parts: 6317015-72 1 Tube Assembly 6317015-18 Discard 6317015-74 1 Tube Assembly 6317015-22 Discard 6317015-75 1 Tube Assembly 6317015-38 Discard Mar 9/2011 525A-29-07 Page 9 Citation SERVICE BULLETIN SUPPLEMENTAL DATA SB525A-29-07 TITLE HYDRAULIC POWER - STAINLESS STEEL TUBE ASSEMBLY INSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS 525A (CJ2) -0001 thru -0244 525A (CJ2+) -0300 and On NOTE: If the marketing designation for your airplane does not appear in the EFFECTIVITY section, this service document does not apply to your airplane. NOTE: SB525A-32-11 Landing Gear - Brake Hydraulic And Pneumatic Tube Improvement must be accomplished prior to or in conjunction with this service bulletin. NOTE: Cessna-owned or Cessna-authorized Citation Service Centers are the only facilities that can complete this service bulletin. MANPOWER WORK PHASE MAN-HOURS Modification As Necessary MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST SB525A-29-07-0 * * SB525A-29-07-1 * * * Please contact Cessna Service Parts & Programs for current cost and availability of parts listed in this service bulletin. Phone at 1-800-835-4000 (Domestic) or 1-316-517-7542 (International). Send Email to: citationparts@cessna.textron.com or telefax at 1-316-517-7711. Based on availability and lead times, parts may require advanced scheduling. In cases where the required part(s) are available as exchange, order the exchange part and, upon completion, expedite the return of the removed core to avoid return penalties. Contact the Cessna Service Parts & Programs Sales Desk for availability of exchange parts. Mar 9/2011 525A-29-07 Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT © 2011

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