2015-22-02: Tail Rotor Control System

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2015-22-02 Bell Helicopter Textron Canada Limited: Amendment 39- 18306; Docket No. FAA-2015-4345; Directorate Identifier 2015-SW-049- AD. (a) Applicability This AD applies to Model 429 helicopters with a pitch link assembly part number 429-012-112-101 or -103 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a worn pitch link. This condition, if not detected and corrected, could result in pitch link failure and subsequent loss of control of the helicopter. (c) Affected ADsThis AD supersedes Emergency AD 2015-16-51, Directorate Identifier 2015-SW-23-AD, dated August 6, 2015. (d) Effective Date This AD becomes effective November 12, 2015. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) For helicopters with 50 or more hours time-in-service (TIS), before further flight, and for helicopters with less than 50 hours TIS, before accumulating 50 hours TIS, inspect each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play. If there is axial or radial bearing play, remove the tail rotor pitch link and perform a dimensional inspection for wear. If there is wear that exceeds the allowable limits, replace the tail rotor pitch link assembly. (2) Thereafter, at intervals not to exceed 50 hours TIS, repeat the inspections required by paragraph (f)(1) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222- 5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information (1) Bell Helicopter Alert Service Bulletin 429-15-16, dated February 18, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identifiedin this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in Transport Canada Emergency AD No. CF-2015-16R1, dated August 6, 2015. You may view the Transport Canada Emergency AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-4345. (i) Subject Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor Control System.