GOODRICH 

SERVICE BULL 

F-28 MARK 070/100 

MAIN LANDING GEAR INSTALLATION 

PISTON - PRODUCT IMPROVEMEN1 

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SECTION I - PLANNING INFORMATIOI 

EFFECTIVITY 

Piston PN 41141-3, (all serial numbers), installed in 

MLG Dressed Shock Strut Assembly PN 41050 -7/-8/-9/-10/-11 /-12/-13/-14/-15/-16 all serial 

numbers and MLG Dressed Shock Strut Assembly PN 41060 -1/-2/-3/-4/-5/-6 all serial 

numbers. 

CONCURRENT REQUIREMENTS 

SB 41000-32-28 R1- Detailed Visual Inspection of Piston Assembly 

REASON 

Nickel Plate is introduced, as a product improvement, for enhanced corrosion protection. 

DESCRIPTION 

The dressed Shock Strut is disassembled, as required. Nickel Plate is applied to in-service 

piston PN 41141-3. The piston is reidentified as PN 41141-5. The dressed Shock Strut is 

assembled. 

COMPLIANCE 

Goodrich Landing Gear in concurrence with the aircraft manufacturer recommends 

accomplishment of this Service Bulletin at operators earliest convenience. 

APPROVAL 

This bulletin contains no modification information that revises approved configurations, and 

therefore does not require governmental or other regulatory agency approval. 

The technical content of this Service Bulletin has been reviewed and accepted by Fokker 

Services B.V. (EASA. 21J.059). 

MANPOWER 

2.0 manhours are required to accomplish this Service Bulletin 

MATERIAL COST AND AVAILABILITY 

NA 

TOOLING 

NA 

41000-32-29 Nov 10/10 

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 
I 

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

10. WEIGHT AND BALANCE 

NA : rj 

11. ELECTRICAL LOAD &ATA 

NA J 

12. REFERENCES j 

Fokker 100 Aircra'ftlvljbintenance Manual 

Goodrich Landing Gear Component Maintenance Manual 32-12-03 

•-^©GdnchXajidXngjGe^r Component Maintenance Manual 32-12-04 

13. OTHER PUBLICATIONS AFFECTED 

Goodrich Landing Gear Component Maintenance Manual 32-12-03 

Goodrich Landing Gear Component Maintenance Manual 32-12-04 

SECTION II - ACCOMPLISHMENT INSTRUCTIONS 

Procedure (Refer to Figure 1) 

NOTE: Numbers in parenthesis refer to CMM 32-12-03/04, IPL Figure-Item Number. 

A. Disassemble dressed shock strut assembly to remove expanding plug (1-260) and piston 

(2-920) (Refer to CMM 32-12-03/04). 

B. Remove primer, plating and corrosion from rework area. 

NOTE: Make sure the rework area is clean and dry. 

C. Mask all areas not to be plated, as required (Ref. Figure 1). 

D. Locally apply nickel plating to area as shown in Figure 1. 

E. Remove masking and assemble dressed shock strut per CMM 32-12-03/04. 

Re-identification 

CAUTION: DO NOT LETTER STAMP NAMEPLATE ON ASSEMBLY. THIS CAN DAMAGE 

THE ASSEMBLY. 

A. Reidentify pistonas PN 41141-5^oi^he vibro-peen method (Ref. Figure 1). 

B. Vibro-peen SB 32-29 and date accomplished on nameplate (1-20). 

SECTION ill - MATERIAL INFORMATION 

NA 

41000-32-29 Nov 10/10 

Page 2 of 3 

Reference Goodrich CMM for proprietary information 
«3> 

Goodrich Landing Gear Division 

Goodrich Aerospace Canada Ltd. 

TORQUE LINKS AND DRESSINGS 

NOT SHOWN FOR CLARITY 

NAMEPLATE (1-20) 

LOWER 

TORQUE 

LINK LUG 

(REF) 

PISTON 

(REF) 

0.565 - 0.625 

(14,35-15,88) 

PARTIAL SECTION A-A 

EXPANDING BUSHING, WASHER AND WIRING HARNESS NOT SHOWN FOR CLARITY 

SB41000 32 29 

NICKEL PLATE COVERAGE 

ON PORT SURFACES 

VIEW ON ARROW B 

NOTES 

A\ PISTON PN, SN LOCATION. 

/ 2 \ APPLY NICKEL PLATE PER AMS 2404 

0.0015 - 0.0020 (0,038 - 0,051) THICK. 

RUNOUT TO BE 0.030 - 0.060 (0,76 -1,52). 

/ 3 \ 0.750 - 0.760 (19,05 -19,30) AFTER NICKEL 

PLATE. 

DIMENSIONS INCH (mm) 

Piston - Rework 

Figure 1 

41000-32-29 Nov 10/10 

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Reference Goodrich CMM for proprietary information