# APPH Service Bulletin 32-19: Revision 4 - Rights: © APPH. Filed by the FAA in regulations.gov docket FAA-2014-0020; AD 2014-07-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [APPH Service Bulletin 32-19](https://openairdocs.org/service-documents/apph/sb-32-19.md) - Title as filed: U.S. DOT/FAA - APPH 32-19 - Pages: 9 - PDF: https://openairdocs.org/files/sha256/3f/fb/3ffb7f787caf044b7ee5e00398328361c038e6c37988b59eca82289de3f1aad1 - Page: https://openairdocs.org/service-documents/apph/sb-32-19/file/3ffb7f787caf ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) apph SERVICE BULLETIN 32-19 LETTER OF TRANSMITTAL Tor Revision 4 Issued: - April 3rd 2013 By:- Technical Publications APPH Ltd Engineering Division Unit 1 Pembroke Court Manor Park, Runcorn Cheshire WA7 1TG England ACTION REASON (1) revised service bulletin 32-19 Rev 4. Destroy the existing service bulletin 32-19 Rev 3 and replace with the Figure 2 revised. Repair procedure revised, Date of initial issue: December 19th 1985 Date of revision 1: Not Known Date of revision 2: April 4th 1989 Date of revision 3: March 16th 1990 Signed. G CI Chief Design Engineer Date.. 1/04113 Letter of Transmittal No. 4 Page 1 of 1 ### Page 2 (OCR) apph BBA Aviation APPH Ltd. Engineering Division, Unit 1, Pembroke Court, Chancellor Road, Manor Park, Runcorn, Cheshire, WA7 1TG, England. FAX (+44) 01928 579626 TEL (+44) 01928 532600 SERVICE BULLETIN 32-19 MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING 1. PLANNING INFORMATION A. Effectivity (1) Aircraft: Jetstream (2) Unit: MLG (3) Part Numbers: Port Types 1863 (Pre strike off 3) 1863/4A, 1863/4B and 1863/4C (Pre Mod 86-04-003 Re-issue 6) B00A702850A (Pre strike off 7) B00A702925A (Pre strike off 5) Starboard Types 1864 (Pre strike off 3) 1864/4A, 1864/4B and 1864/4C (Pre Mod 86-04-003 Re-issue 6) B00A702851A (Pre strike off 7) B00A702926A (Pre strike off 5) B. Reason A crack has been found in a cylinder attachment spigot during routine inspection after a landing gear removal. Investigation has attributed the cause to stress corrosion. C. Description This Service Bulletin requires an inspection to be made for signs of cracks on the cylinder attachment spigot housing. Compliance with this Service Bulletin is not required when SB D. Compliance The technical content of this Service Bulletin is subject to EASA AIRWORTHINESS DIRECTIVE consultation and must be accomplished at the next and subsequent overhauls. The inspection must also be carried out on spare or overhauled landing gear before installing into the aircraft. On installed landing gear the inspection should be carried out within 300 landings or 3 calendar months whichever is the sooner and repeated thereafter at 1200 landings or 1 calendar year whichever is the sooner. It is recommended that intermediate visual inspection be carried out to aircraft manufacturers instructions. It is also recommended that the inspection be carried out at 300 landings or 3 months after a heavy landing has occurred. December 19 / 85 Revision 4 April 3rd 2013 32-19 Page 1 ### Page 3 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING E. Approval The technical content of this bulletin is approved under the authority of Design Organisation Approval No. DOA. EASA.21J.131. F. Manpower Assuming the main gear to be in service allow two manhours to complete the work detailed in Section 2 of this bulletin. G. Material, cost and availability Not applicable H. Special Tools Not applicable Weight Change None J. References BAE SYSTEMS Regional Aircraft Service Bulletin 32-A-JA851226. K. Other Publications Affected Recommended Maintenance Schedule Publication No. J/PSD/RMS/80. This Service Bulletin amplifies the Special Instructions contained within the Recommended Maintenance Schedules, Section 3, Page 4, Para, 4.1.2, but does not constitute substitution for these Special Instructions. 2. ACCOMPLISHMENT INSTRUCTIONS The MLG must be removed from the aircraft. A. Inspect the cylinder attachment spigot housing. (1) Clean the areas to be inspected, refer to Figure 1. (2) Carry out the Non Destructive Test (NDT) examination in accordance with the procedure given in 2.B., or approved equivalent. If the protective finish shows signs of lifting or cracking, affected areas are to be cleaned back to bare metal and re-inspected. December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 2 ### Page 4 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING B. Carry out Non Destructive Test, refer to Figures 3 and 4. () Equipment and Materials (a) Hocking Locator UH' test set or equivalent. (D) Standard calibration block NFE. (C) Shielded spade probe NFE 2 MHz. (a) 0,08 - 0,1 mm PTFE tape. (2) Instrument Setting and Calibration Operating mode: Zero limit Alarm: Continuous Frequency: 2 MHz Metal selector Al. Mg. (a) Attach PTFE cover or tape to probe tip. With probe connected, carry out initial setting-up and balancing procedure on equipment with probe on standard NFE calibration block in accordance with manufacturers instruction. (b) Use Sensitivity/Gain control, calibrate equipment to give 80% full scale deflection on meter from 0,5 mm deep slot in standard calibration block. (c) Adjust lamp and buzzer alarm to operate at 20% of full scale deflection. The above procedure is based on the use of EC52 issue 2, eddy current test equipment. If other equipment is used, approved equivalent apparatus, materials, instrument settings and calibration must be employed. (3) Procedure (a) Position probe in scan areas A and B, refer to Figures 1 and 3. Position the equipment and check the probe lines up with the scan area, then zero the equipment. Carry out a series of tight zig-zag scans at probe width intervals to examine the complete scan area. (c) Position the probe in scan areas C and D, refer to Figures 1 and 4. Position the equipment and check the probe lines up with the scan area, then zero the equipment. (d) Carry out a series of tight zig-zag scans at probe width intervals to examine the complete scan area. December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 3 ### Page 5 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING (e) Any indication which cannot be attributed to edge, geometric, ferrous effect or probe handling is to be considered a defect. (T) Care must be taken to ensure the probe is kept normal to the scan surface and the scan is carried out as close to the machined flat edge and steel spigot as possible. (g) Small cracks may be repaired as shown in Figure 2, to a maximum permissible depth of 0.10 inch measured from the face of the spigot housing. NOTE Two or more cracks of any depth, or a single crack in excess of 0.10 inch depth, are cause for rejection and replacement of the affected landing gear leg. (h) Reprotect any areas where the protective treatment has been removed using Alocrom 1200. Paint all areas with primer followed by polyurethane paint, except area 'C'. DO NOT PAINT AREA 'C' WITH PRIMER AND POLYURETHANE PAINT EXCEPT ANY MINOR LOCAL REPAIRS. C. Method of identification (1) Record the incorporation of this Service Bulletin in the appropriate aircraft log book and in the log cards for the port and starboard main gear. (2) The results of this inspection, whether cracks are found or not are to be reported to Customer Technical Support at: Customer Technical Support (Building 37) BAE Systems (Operations) Ltd Prestwick International Airport Ayrshire, KA9 2RW Scotland Fax: +44 (0) 1292675432 email: raengliaison@baesystems.com 3. MATERIAL INFORMATION Not applicable 4. ISSUING AUTHORITY The technical content of this document is approved under the authority of DOA number EASA.21J.131. Signed. APPH LIMITED Date !іo4!!3 December 19 / 85 Revision 4 April 3rd 2013 32-19 Page 4 ### Page 6 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING POSITION WHERE CRACK INITIATES AREA A POSSIBLE PATH OF CRACK POSITION WHERE CRACK INITIATES AREA B INSPECT THE WHOLE OF THE AREA C END FACE AT BOTH ENDS AREA D NOTE: SHADED AREAS INDICATE WHERE INSPECTION IS TO TAKE PLACE Scan Areas Figure 1 December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 5 ### Page 7 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING SMOOTH BLEND I APPLY ALOCROM ONLY TO THE FACE OF AREA 'C'. THE FACE OF AREA 'D' CAN BE REPAIRED WITH ALOCROM, PRIMER AND PAINT. 0.50 INCH MIN RAD ANY LOCAL REPAIRED 0.50 INCH SURFACES CAN BE REPAIRED WITH ALOCROM, PRIMER AND PAINT. 0.10 INCH MAX V NOTE: REPAIR TO HAVE POLISHED FINISH, FREE FROM TOOL MARKS Local Repair Figure 2 December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 6 ### Page 8 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING MACHINED FLAT TYPICAL SCAN PATH EXPECTED DEFECT SCAN AREA 1.5 INCH MIN SPIGOT Scan Areas A and B Figure 3 December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 7 ### Page 9 (OCR) apph BBA Aviation MLG ASSEMBLY - INSPECT CYLINDER ATTACHMENT SPIGOT HOUSING MACHINED FLAT , EXPECTED DEFECT TYPICAL SCAN PATH SCAN AREA Scan Areas C and D Figure 4 December 19 / 85 32-19 Revision 4 April 3rd 2013 Page 8 --- 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.