49600-32-63 R1

SERVICE BULLETIN 

HIGHLIGHTS 

May 17/11 

Page 1 of 1

CRJ MAIN LANDING GEAR 

RETRACTION ACTUATOR ASSEMBLY – ROD END/PISTON INTERFACE INSPECTION

REVISION NO. 1 – May 17, 2011 

Service Bulletin 49600-32-63 Revision 1 supersedes Service Bulletin 49600-32-63 dated Sep 27/10 

and is reissued in its entirety with the changes listed below. 

The compliance in the previous issue of this Service Bulletin is not affected by this revision. No 

additional rework is introduced by this revision. 

Please destroy all copies of SB 49600-32-63 dated Sep 27/10. 

Page/Para Change 

Section I, Page 1, Para 1 . Effectivity updated. 

Section II, Page 2 Note added at Para. 1, step (2). Return address 

moved from step (4). 

49600-32-63 R1

SERVICE BULLETIN 

May 17/11 

Page 1 of 3 

THESE COMMODITIES, SOFTWARE OR TECHNOLOGY WERE EXPORTED/RE-EXPORTED IN ACCORDANCE WITH U.S. EXPORT ADMINISTRATION REGULATION. 

DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED. 

Reference Goodrich CMM for proprietary information 

CRJ MAIN LANDING GEAR 

RETRACTION ACTUATOR ASSEMBLY - ROD END/PISTON INTERFACE INSPECTION

-------------------------------------------------------------------------------------------------------------------------------------- 

SECTION I - PLANNING INFORMATION 

1. EFFECTIVITY

Retract Actuator Assembly PN 49600-5/ -7/ -11, SN SPP0001 to SPP0388 and 

SPP020389 to SPP021300 and SPP011301 to SPP011318, SPP011355 and 

SPP011356. 

2. CONCURRENT REQUIREMENTS 

NA 

3. REASON 

Problem/Condition 

A potential for corrosion exists on retract actuator assembly piston/rod end interface. 

 Objective/Benefit

This service bulletin is issued to give instructions for inspection at the piston/rod end interface. 

4. DESCRIPTION

The retract actuator assembly piston/rod end interface is inspected for evidence of corrosion, 

and security of jam nut locking. 

Loose jam nuts are torqued per the CMM, a torque stripe is applied at the interface. 

5. COMPLIANCE 

 Goodrich Landing Gear recommends incorporation of this bulletin within 1200 Flight Hours for 

units with more than 8,000 Flight Hours TSN or more than 48 months in service. 

6. APPROVAL

The technical content of this Service Bulletin has been approved under the authority of the 

TCCA Design Approval Organization No DAO#93-Q-02. 

7. MANPOWER 

 Approximately 2.0 man-hours are required to do this Service Bulletin. 

8. MATERIAL COST AND AVAILABILITY

 NA 

9. TOOLING

NA 
49600-32-63 R1 

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

 May 17/11 

Page 2 of 3 

Reference Goodrich CMM for proprietary information 

10. WEIGHT AND BALANCE

 NA 

11. ELECTRICAL LOAD DATA

 NA 

12. REFERENCES 

 Goodrich Landing Gear Component Maintenance Manual 32-11-28 

13. OTHER PUBLICATIONS AFFECTED 

NA 

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SECTION II - ACCOMPLISHMENT INSTRUCTIONS 

NOTE: Item numbers in parenthesis () refer to CMM 32-11-28 IPL Figure-Item number. 

1. Inspection 

A. Inspect rod end assembly (1-80) and jam nut (1-70) interface as follows: 

(1) Check for the presence of torque stripes make sure they are not broken or 

misaligned. 

(2) Inspect for evidence of corrosion with no staining from interface joint. 

NOTE: If evidence of corrosion is found return Retract Actuator to Goodrich 

Landing Gear. 

Goodrich Corporation Tele: 1-704-282-2549 

Customer Services Fax: 1-704-290-5959 

4115 Corporate Center Dr 

Monroe, NC 28110-1313 ATT: Customer Services Administrator 

USA 

(3) Make sure lockwire and lock key (1-90) are in place and not damaged. 

(4) Check jam nut (1-70) for security, make sure the jam nut cannot be moved by hand. 

NOTE: Loose jam nut (1-70) can be retorqued a total of 2 times, refer to CMM 32-

11-28 ASSEMBLY. If a third jam nut retorquing is required, return Retract 

Actuator to Goodrich Landing Gear. 

(5) For assemblies with damaged torque stripes or retorqued jam nuts, reapply torque 

stripe across rod end/jam nut interface using F-925 Anti- Sabotage lacquer. 

2. Re-identification 

CAUTION: DO NOT LETTER STAMP THE NAMEPLATE ON ACTUATOR. THIS CAN 

CAUSE DAMAGE TO CYLINDER. 

A. Vibro-peen SB32-63 and date incorporated in MOD field of nameplate (1-60). 
49600-32-63 R1 

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

 May 17/11 

Page 3 of 3 

Reference Goodrich CMM for proprietary information 

B. If jam nut (1-70) was retorqued once, add the letter ‘A’ after SB32-63. After the second 

retorque, add the letter ‘B’ after SB32-63. 

NOTE: If a third jam nut retorquing is required, do not re-identify the unit, return Retract 

Actuator to Goodrich Landing Gear. 

NOTE: If required due to limited access, ink stamp data on the actuator cylinder instead of 

vibro-peen on name plate. Apply clear lacquer (Akzo 683-3-x or equivalent) over 

ink stamp.

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SECTION III - MATERIAL INFORMATION 

NA