# Tecnam Service Bulletin 995-CS: No revision named - Rights: © Tecnam. Filed by the FAA in regulations.gov docket FAA-2026-11784; AD 2026-19-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Tecnam Service Bulletin 995-CS](https://openairdocs.org/service-documents/tecnam/995-cs.md) - Title as filed: Tecnam Service Bulletin SB 995-CS-Ed 1 Rev 2 - Pages: 3 - PDF: https://openairdocs.org/files/sha256/4a/7e/4a7e6b7a8d5d2679965beda27f25c2e1fd81ed7fd2ac5823e61bd73c16cac269 - Page: https://openairdocs.org/service-documents/tecnam/995-cs/file/4a7e6b7a8d5d ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 SERVICE BULLETIN N° SB 995 – CS – Ed. 1 Rev. 2 Date: 21/04/2026 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-995-260421 Rev1: 25/08/2026 Rev2: 18/09/2026 Page 1/3 MOD. PD-006-03 rev.3 data: 04/03/20 SERVICE BULLETIN Edition 1 Rev.1 MANDATORY by the AD No. 2026-0124 May become MANDATORY after EASA evaluation RECOMMENDED ……………………………. INFORMATION ………………………………………….. SUBJECT: P2006T and P2006T NG – ATA 27 – Flight Controls – Aileron Hinges and Cotter Pins – Inspection SCOPE: Following reports regarding the P2006T fleet, Tecnam has iden- tified instances of improperly installed cotter pins securing the aileron hinge pins. Incorrect installation of these safety devices may lead to hinge pin migration, potentially resulting in aileron detachment and subsequent loss of aircraft control. Although the inspection of aile ron hinges and related compo- nents is currently required as part of the 100-hour/annual peri- odic inspection as specified in AMM (Aircraft Maintenance Manual), ATA 05-20, this Service Bulletin requires a one-time detailed inspection of the aileron hinges and cotter pins locking aileron hinge pins (two cotter pi ns per each hinge/hinge pin) to verify for cracks, integrity and proper installation. Refer to Appendix A for the complete inspection procedure. APPLICABILITY:  Tecnam P2006T aeroplanes up to serial number 434 (inclu- sive), including serial number 442;  Tecnam P2006T NG aeroplanes up to serial number 1028 (inclusive), excluding seri al numbers: 1012, 1013, 1018, 1021, 1022, 1023, 1025, 1026 and 1027. TIME OF COMPLIANCE: Within the next 25 FH or 1 calendar month (whichever comes first) MANPOWER: 0.5 man-hour REQUIRED MATERIAL: Nil TOOLING: Standard toolbox WEIGHT AND BALANCE: Nil REFERENCES: P2006T AMM – Last Issue P2006T NG AMM – Last issue PUB. AFFECTED: None ### Page 2 SERVICE BULLETIN N° SB 995 – CS – Ed. 1 Rev. 2 Date: 21/04/2026 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-995-260421 Rev1: 25/08/2026 Rev2: 18/09/2026 Page 2/3 MOD. PD-006-03 rev.3 data: 04/03/20 SERVICE BULLETIN Edition 1 Rev.1 Appendix A N Accomplishment Instructions 1 Park the airplane in safety conditions in accordance with AMM, ATA 10-10. 2 Verify that the Parking Brake is ON and the Master Switch is OFF. 3 Starting from either LH or RH wing, ensure clear access to the outboard and inboard ai-leron hinges. 4 Perform a Detailed Visual Inspection (DV I) of both inboard and out board aileron hinges as follows: 1) Clean the inspection area with an approved solvent. Ensure the hinge assemblies are free from grease, dirt, or debris; 2) Examine each hinge for cracks or damage on both the aileron and the wing box sides; 3) Verify the integrity of the torque seal on the aileron hinge screws (aileron side). Ensure there are no signs of misalignment; 4) Verify that the heads of the cotter pins (i nstalled at both ends of each hinge pin) are firmly seated with no evidence of looseness; Note: Verify proper cotter pin installation geom etry (refer to the figures below). Both prongs must be bent tightly around the circumference of the hinge pin. A minimal clearance is acceptable, but the prongs must be trimmed to prevent any contact with the hinge bracket or surrounding structure during aileron movement. 5) Move the aileron manually through its full rang e of travel. Verify that the cotter pin prongs do not interfere with the hinge brackets, wing structure, or aileron skin during movement; 6) Ensure that both the inboard and outboard hi nges are inspected in accordance with the steps detailed above. Correct installation geometry (torque seal removed for clarity) Correct complete installation 5 Repeat the full inspection procedure for the aileron on the opposite wing. ### Page 3 SERVICE BULLETIN N° SB 995 – CS – Ed. 1 Rev. 2 Date: 21/04/2026 The technical content of this document is approved under the authority of DOA ref. EASA.21J.335 Approval No: DO-995-260421 Rev1: 25/08/2026 Rev2: 18/09/2026 Page 3/3 MOD. PD-006-03 rev.3 data: 04/03/20 SERVICE BULLETIN Edition 1 Rev.1 N Accomplishment Instructions 6 If any discrepancy affecting the cotter pins is found during the inspections specified in Step 4, replace and secure the cotter pi n(s) (PN: MS24665-153) in accordance with the instructions contained in AMM, ATA 20-40 and report the findings to Tecnam. If any discrepancy affecting the aileron hinges is found during the inspections specified in Step 4, contact Tecnam for further instructions. 7 If no discrepancy is found, return the aircraft to service. 8 Record compliance with this Service Bulletin in the aircraft maintenance log. For further information please contact TECNAM:  Technical Support: o Email: technical.support@tecnam.com or Tel: 0039 0823 997538  Spare Parts o Email: spareparts@tecnam.com or Tel: 0039 0823 62229 --- 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.