Airworthiness directives › 98-06-39
AD 98-06-39 Airworthiness Directives; Eurocopter France Model AS 332C, L, L1, and L2 Helicopters
Models named: AS 332C, L, L1, L2. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model AS 332C, L, L1, and L2 helicopters, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, [[Page 13512]] or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD.
Compliance
Required as indicated, unless accomplished previously. To detect cracks in the cockpit door hinge tenons (hinge tenons) due to unintended loading of the improperly shimmed tenons caused by closing the door, which may lead to separation of the door from the helicopter, impact with the main rotor or tail rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 50 hours time-in-service (TIS), inspect the thickness of the shim washers and perform the following in accordance with Eurocopter Service Bulletin No. 01.00.50, dated August 5, 1997: (1) If the washers are equal to or less than 3 mm thick, perform the requirements of paragraph 2.B.1.1. and 2.B.2. (2) If the washers are more than 3 mm thick and equal to or less than 3.5 mm thick, perform the requirement of paragraph 2.B.1.2. and 2.B.2. (3) If the washers are more than 3.5 mm thick, perform a dye penetrant inspection for cracks on the hinge tenon as specified in paragraph 2.B.1.3. (i) If a crack is found, before further flight, install an airworthy, zero hours TIS hinge tenon in accordance with the requirements of paragraph 2.B.1.3. and 2.B.2. (ii) If the hinge tenon is determined to be airworthy and is reinstalled, remove and replace the reinstalled hinge tenon with an airworthy, zero hours TIS hinge tenon within 500 hours TIS, in accordance with paragraph 2.B.1.3. and 2.B.2. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (d) The inspections and replacement shall be done in accordance with Eurocopter Service Bulletin No. 01.00.50, dated August 5, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 6, 1998. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 97-108-006(AB)R1 and AD 97-109-061(AB)R1, both dated August 27, 1997. Issued in Fort Worth, Texas, on March 12, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-7230 Filed 3-19-98; 8:45 am] BILLING CODE 4910-13-U
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1