# GippsAero Mandatory Service Bulletin SB-GA200-2012-08 Copy: Revision 1 ("U.S. DOT/FAA - Service Information"), 4 pages: PDF https://openairdocs.org/files/sha256/7a/c2/7ac2ef069ab8d92307ce3ea7594e5b9f90ca31d5a896b0963b9a44fabdf761b9; text https://openairdocs.org/service-documents/gippsaero/sb-ga200-2012-08/file/7ac2ef069ab8.md. Rights: © GippsAero. Filed by the FAA in regulations.gov docket FAA-2012-0946; AD 2012-18-10, 2012-18-10 R1 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [GippsAero](https://openairdocs.org/service-documents/gippsaero.md) - Type: Service bulletin (Mandatory Service Bulletin) - Number: SB-GA200-2012-08 - Latest revision known: SB-GA200-2012-08, Issue 2, dated September 4, 2012 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/gippsaero/sb-ga200-2012-08 ## ADs that cite it (2) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2012-18-10 R1](https://openairdocs.org/ad/2012-18-10-R1.md), effective Jan 31, 2013: Revisions 1 and 2 - [AD 2012-18-10](https://openairdocs.org/ad/2012-18-10.md), effective Sep 14, 2012: Revision 1 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/gippsaero/sb-ga200-2012-08/proposed.md). ## Text (4 pages) Rights: © GippsAero. Filed by the FAA in regulations.gov docket FAA-2012-0946; AD 2012-18-10, 2012-18-10 R1 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 SB-GA200-2012-08 Issue 1 MANDATORY PO Box 881, Morwell, Victoria 3840, Australia Ph + 61 (0) 3 5172 1200 Fax + 61 (0) 3 5172 1201 www.gippsaero.com Service Bulletin SB-GA200-2012-08 Issue: 1 Date of Issue: 22/8/2012 Page 1 of 4 Subject: Replacement of wing strut mounting bolts. Applicability: All GA200 & GA200C aircraft. Amendments: Nil (initial issue). Background: As a result of a reported case of failure of the strut bolt through the main spar on a GA200C aircraft, GippsAero has issued this Service Bulletin to a lert operators and maintenance organisations and to provide inspection and rectification actions. Compliance: This Service Bulletin is to be carried out within the next 10 flight hours then every periodic inspection thereafter. Applicable Documents: GA200 or GA200C Service Manual as applicable GA200 Illustrated Parts Catalogue AC43.13-1B Method: Carry out an in -situ inspection of the port and starboard strut fittings and take appropriate corrective action as follows, refer Service Manual Chapter 57: 1. Remove the main strut/wing fairing assembly and strut/fuselage fairing assembly (if fitted). 2. Support the wing as required. Remove and inspect all three strut attachment bolts in turn. 3. Diameters for each fitting should be as specified below: a. 570006-19 inboard (upper) strut fitting – 0.500 to 0.510 inches ### Page 2 SB-GA200-2012-08 Issue 1 MANDATORY PO Box 881, Morwell, Victoria 3840, Australia Ph + 61 (0) 3 5172 1200 Fax + 61 (0) 3 5172 1201 www.gippsaero.com Service Bulletin SB-GA200-2012-08 Issue: 1 Date of Issue: 22/8/2012 Page 2 of 4 b. 570006-17 strut fitting main spar – 0.375 to 0.385 inches c. 570006-15 strut fitting rear spar – 0.750 to 0.760 inches d. 570006-13 eccentric bush rear spar – 0.375 to 0.385 inches 4. If hole size is correct, skip to Step 9 otherwise proceed to Step 5 5. If the inboard (upper) strut fitting hole diameter is larger than specified in step 3 , notify GippsAero for corrective action. 6. If the main spar h ole diameter is larger than specified in step 3, ream the main spar strut fitting holes on the strut and the wing spar to a diameter of 0.43 8 to 0.440 inches. NOTE Care is to be taken when reaming to ensure reamer does not damage surrounding structure. 7. If the hole diameter for the 570006-13 eccentric bush is larger than specified in step 3, replace the bush with a new 570006-13 bush. 8. If the rear spar strut hole diameter is larger than specified in step 3, notify GippsAero for corrective action. 9. Re-attach strut to wing in accordance with the Service Manual, section 57-10-10. The following hardware is to be used in lieu of the original fit: a. Replace AN8-23A bolt with NAS6608-29 bolt b. Replace AN6-23A bolt with NAS6606-31 bolt, or c. Replace AN6-23A bolt with NAS6607-31 bolt if hole has been reamed oversize d. Replace AN6-15A bolt with NAS6606-21 bolt e. Use MS21042-6 nut and MS27151-19 Pal Nut f. Use AN365-720 nut and MS27151-21 Pal Nut g. Use AN365-820 nut and MS27151-24 Pal Nut h. Use AN960- washers as required. 10. Reassemble using Duralac (barium chromate) m ating compound to all attaching hardware. Torque in accordance with Chapter 20, Table 1. Should you require any further information please contact our Customer Support Department: Tel.: +61 (0) 3 5172 1200 Fax: +61 (0) 3 5172 1201 Email: support@gippsaero.com ### Page 3 SB-GA200-2012-08 Issue 1 MANDATORY PO Box 881, Morwell, Victoria 3840, Australia Ph + 61 (0) 3 5172 1200 Fax + 61 (0) 3 5172 1201 www.gippsaero.com Service Bulletin SB-GA200-2012-08 Issue: 1 Date of Issue: 22/8/2012 Page 3 of 4 Strut Fairings Inboard strut attachment bolt, rear spar bolt & main spar bolt Strut/Wing Fairing Strut/Fuselage Fairing Main spar bolt Rear spar bolt Inboard strut attach. bolt ### Page 4 SB-GA200-2012-08 Issue 1 MANDATORY PO Box 881, Morwell, Victoria 3840, Australia Ph + 61 (0) 3 5172 1200 Fax + 61 (0) 3 5172 1201 www.gippsaero.com Service Bulletin SB-GA200-2012-08 Issue: 1 Date of Issue: 22/8/2012 Page 4 of 4 570006-19 570006-17 570006-13 570006-15 Main Strut Attachment Rear Strut Attachment Inboard (upper) Strut Attachment --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.