# Proposed AD 2002-SW-25-AD: Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, and TH-55A Helicopters

- Type: Proposed airworthiness directive (not in force)
- Status: Became AD 2003-13-15
- Products: Schweizer
- Product type: Aircraft
- Action: Notice of proposed rulemaking (NPRM).
- Published: February 19, 2004, 69 FR 7710
- Comments due: April 19, 2004
- Became: [AD 2003-13-15](https://openairdocs.org/ad/2003-13-15)
- Docket: 2002-SW-25-AD
- FR document: 04-3495
- Official PDF: https://openairdocs.org/files/sha256/9a/11/9a11319826d5a9af589caf814afd6d7630ef499755b19fccc0b63fa7452a4e56 (from https://www.govinfo.gov/content/pkg/FR-2004-02-19/pdf/04-3495.pdf)
- Federal Register: https://www.federalregister.gov/documents/2004/02/19/04-3495/airworthiness-directives-schweizer-aircraft-corporation-model-269a-269a-1-269b-269c-and-th-55a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/82EDB7DC1BBF571C86256E3F004D99AA.0001
- Page: https://openairdocs.org/proposed/2002-SW-25-AD

## Summary

This document proposes to revise an existing airworthiness directive (AD) for Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters. That AD currently requires inspecting the lugs on certain aft cluster fittings and each aluminum end fitting on certain tailboom struts. Modifying or replacing each strut assembly within a specified time period and serializing certain strut assemblies is also required. Additionally, a one-time inspection and repair, if necessary, of certain additional cluster fittings, and replacement and modification of certain cluster fittings within 150 hours time-in-service (TIS) or 6 months, whichever occurs first, is required. This action would require the same actions as the existing AD, but would revise the Applicability section of the AD. This proposal is prompted by the discovery of an error in the Applicability section of the existing AD. The actions specified by the proposed AD are intended to prevent failure of a tailboom support strut or a cluster fitting, which could cause rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.

## Notices in this docket

- Feb 26, 2003: Notice of proposed rulemaking (NPRM). (first notice), FR document 03-4479, comments due Apr 28, 2003 (https://www.federalregister.gov/documents/2003/02/26/03-4479/airworthiness-directives-schweizer-aircraft-corporation-model-269a-269a-1-269b-269c-and-th-55a)
- Feb 19, 2004: Notice of proposed rulemaking (NPRM)., FR document 04-3495, comments due Apr 19, 2004 (https://www.federalregister.gov/documents/2004/02/19/04-3495/airworthiness-directives-schweizer-aircraft-corporation-model-269a-269a-1-269b-269c-and-th-55a)

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