## Service Bulletin Fokker 70/100

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Apr 07/11 SBF100-32-161 Page 1

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. LANDING GEAR

Main Landing Gear - Introduction of a Piston with Improved Corrosion Protection.

1. Planning Information A. Effectivity (1) F28 Mark 0070/0100 aircraft serial numbers:

11244 thru 11585

(2) Production version of this modification: Not applicable. B. Concurrent Requirements (1) Not applicable.

C. Reason (1) During a normal walk around check a large crack was discovered in the lower portion of the RH Main Landing Gear (MLG) piston. Visual examination of the piston showed a crack running on the aft side from the upper part of the wheel axle platform down through the area between the lower torque link attachment lugs to the bore on the lower side of the piston. Also a horizontal crack running on the aft side of the piston, in the transition area from piston tube to wheel axle platform, was visible. (2) In order to safeguard fleet airworthiness on the short term a detailed visual inspection has been performed shortly after the occurrence, ref. SBF100-32-158 without finding more cracks. If equipped with Goodrich MLG pn’s : 41050 -7/-8/-9/-10/-11/-12/-13/-14/-15/-16 or 41060 -1/-2/-3/-4/-5/-6 in a pre-mod Goodrich SB 41000-32-29 configuration LANDING GEAR Main Landing Gear - Introduction of a Piston with Improved Corrosion Protection.

## Service Bulletin Fokker 70/100

SBF100-32-161 Apr 07/11 Page 2

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. (3) The piston has been investigated in detail by Goodrich. The crack originated from the wheel speed wire port and progressed in multiple steps. The crack was initiated by corrosion pits. The extensive corrosion indicate s that the initial crack existed for an extended period before a high loading event c aused the crack to grow further by ductile overload. (4) Goodrich issued Service Bulletin (SB) 41000-32-29 to introduce an improved surface protection of the affected area which is considered as a terminating action for therepeat inspection as introduced in the Airworthiness Limitations Section (report SE623 issue 8) in Appendix 1 of the MRB document. (5) This Service Bulletin introduces the above terminating modification consisting of the installation of two pistons modified in accordance with Goodrich SB 41000-32-29 (i.e. pn 41141-5 in place of pn 41141-3). (6) To safeguard the integrity until the SBF100-32-161 has been accomplished a visual inspection similar to the inspection as per SBF100-32-158 with an interval of 1year is introduced in the Airworthiness Limitations Section (report SE-623 issue 8) in Appendix 1 of the MRB document. D. Description (1) This Service Bulletin tells you how to: - Remove the pre-mod Goodrich SB 41000-32-29 MLG’s. - Install the post-mod Goodrich SB 41000-32-29 MLG’s. E. Compliance (1) Recommended. Fokker Services recommends the accomplishment of this Service Bulletin within 10 years after the issue date of this Service Bulletin or during scheduled restoration of the MLG whichever is sooner. For the first 5 years after the issue date of this Service Bulletin it is allowed to install MLG pistons or MLG's equipped with pistons as spare replacements which are still in a pre-Goodrich SB 41000-32-29 configuration. NOTE : It is expected that EASA will issue an Airworthiness Directive (AD) with respect to this subject with the same compliance terms. Refer to the EASA website for the publication of a Proposed Airworthiness Directive for comments. F. Approval (1) The technical content of this document is approved under the authority of DOA nr. EASA.21J.059.

## Service Bulletin Fokker 70/100

Apr 07/11 SBF100-32-161 Page 3

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. G. Manpower (1) Approximately 24 man-hours are necessary to do this Service Bulletin on one aircraft. This table of manpower will help you to schedule and do this Service Bulletin:

Instructions Men Man-hours Elapsed time (hours) Removal 4 8 2 Modification Inspection * * * Installation 4 16 4 Testing Total 24 6 NOTE : This estimate does not include the time necessary for the paint to dry and/or the sealant to cure. *NOTE : Refer to Goodrich SB 41000-32-29.

(2) The estimated hours are for direct labor done by experienced personnel. They are calculated based on the conditions given in SBF100-00-001 (Service Bulletin Introduction, section 2.C., "Manpower"). H. Weight and Balance (1) Weight change: None Index change: None.

I. Electrical Load Data (1) Not changed. J. Software Accomplishment Summary (1) Not applicable.

K. References (1) Fokker 70/100 Aircraft Maintenance Manual (AMM) Fokker 70/100 Maintenance Review Board (MRB) document Fokker 70/100 Service Bulletin (SB): - SBF100-32-158 Fokker internal reference(s): - ECR 15737 Goodrich Service Bulletin (SB) - 41000-32-29

## Service Bulletin Fokker 70/100

SBF100-32-161 Apr 07/11 Page 4

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. L. Publications Affected (1) This SB affects the publications listed below: (a) Maintenance Documentation

Not affected.

(b) Maintenance Programs - Fokker 70/100 Maintenance Review Board (MRB) - Fokker 70/100 Maintenance Planning Document (MPD) (c) Special Instructions for Continued Airworthiness (ICA) The effect of this Service Bulletin on the special ICA is as follows:

YES NO - Electrical Wiring Interconnection System (EWIS) - X - Fuel Tank Safety (FTS) - X - Damage Tolerance of Fatigue Critical Structure - X NOTE : If “YES”, when not already incorporated, the changed ICA will be incorporated in the MRB document within one calendar year from the date of issue of this Service Bulletin. Until then, no actions are required. (d) Operational Documentation

Not affected.

(2) Report to Fokker Services that this SB has been carried out on the applicable aircraft. (3) For incorporation of this Service Bulletin in your documentation refer to SBF100-00-001 (Service Bulletin Introduction, section 4 "Incorporation of Service Bulletins in Documentation of Fokker Services"). M. Interchangeability or Intermixability of Parts (1) Operation with on one side a MLG post-mod Goodrich SB 41000-32-29 and on the opposite side a MLG pre-mod Goodrich SB 41000-32-29 is allowed. NOTE: However, the aircraft records shall in that case clearly identify the mixed configuration for maintenance planning purposes.

## Service Bulletin Fokker 70/100

Apr 07/11 SBF100-32-161 Page 5

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 2. Material Information A. Material – Price and Availability (1) Refer to Goodrich SB 41000-32-29. B. Material Required (1) These parts, which are necessary to complete this Service Bulletin on 1 aircraft, are not part of the mod kit. (a) Refer to Goodrich SB 41000-32-29. C. Tooling – Price and Availability (1) Not applicable. D. Drawings Required (1) Not applicable.

## Service Bulletin Fokker 70/100

SBF100-32-161 Apr 07/11 Page 6

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 3. Accomplishment Instructions

General:



### - Put up warning signs in the flight compartment and at the hydraulic ground-servicing panel to

tell persons: “DO NOT PRESSURIZE THE HYDRAULIC SYSTEMS”. - Make sure the ground safety pins are installed. - These instructions are applicable to the left and right installations. - Data for the right installation is between parentheses. WARNING : BE CAREFUL WHEN YOU OPERATE THE LANDING GEAR. MAKE SURE THE LANDING GEAR AREA IS CLEAR. INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT CAN OCCUR. CAUTION : THE INITIAL RETRACTION AND EXTENSION MUST BE SLOW AND CONTROLLED. BE PREPARED TO STOP THE OPERATION IF NECESSARY TO PREVENT DAMAGE. WARNING : BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY INSTRUCTIONS. A. Lift the aircraft with wing jacks; refer to the AMM chapter 07-11-00. B. Remove and keep the LH (RH) MLG wheels and brakes; refer to the AMM chapter 32-42-01-000-814. C. Remove the LH (RH) MLG from the aircraft, refer to AMM chapter 32-11-01-000-814. D. Install the LH (RH) MLG with SB 32-29 on the nameplate, in the aircraft, refer to AMM chapter 32-11-01-400-814. E. Install wheels and brakes, refer to AMM chapter 32-42-01-400-814.

F. Make sure all circuit breakers are closed. G. Remove all tools, materials and equipment from the work area. Make sure the work area is clean. H. Do an operational test of the LH (RH) ground/flight sensors, refer to AMM chapter 32-63-03-400-814. I. Do an operational test of the MLG (and position indication system), refer to AMM chapter 32-11-01-400-814. J. Do a functional check of the MLG system, refer to AMM chapter 32-00-00-720-815. K. Do an operational check to make sure that the hydraulic brake lines or anti-skid wiring are not cross-connected, refer to AMM chapter 32-11-01-400-814.

## Service Bulletin Fokker 70/100

Apr 07/11 SBF100-32-161 Page 7

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. L. Do a detailed inspection of the LH (RH) main gear and the LH (RH) wheelbay, refer to AMM chapter 32-11-00-220-816 and in addition: - Check for signs of hydraulic leakage and interference. - Check for security of electrical wi re harness assemblies and hydraulic lines. M. Lower the aircraft, refer to AMM chapter 07-11-00.