Airworthiness directives › 2002-23-04
AD 2002-23-04 Airworthiness Directives; Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 Helicopters
Models named: SA-365N, SA-365N1, AS-365N2, AS 365 N3. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters, with MOD 0753B31 installed, certificated in any category. Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance
Required as indicated, unless accomplished previously. To prevent failure of the 9-degree frame (frame) due to a crack at the latch support, loss of a passenger door, damage to the rotor system, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 50 hours time-in-service, inspect each frame by measuring the edge distance at the two 5.2 mm (0.205 inch) diameter attachment holes for the latch support for the passenger door in accordance with the Accomplishment Instructions, paragraph 2.B.1., of Eurocopter France AS 365 Alert Service Bulletin 53.00.42, dated January 31, 2001 (ASB). Inspect the area around the attachment holes for a crack. (1) If the edge distance of both attachment holes is equal to or more than 8 mm (0.315 inch) and no crack is present, no action is required by this AD. (2) If the edge distance is less than 8 mm and no crack is present, before further flight, install a reinforcing plate in accordance with the Accomplishment Instructions paragraph 2.B.2. of the ASB. Accomplishing the requirements of paragraph 2.B.2. of the ASB constitutes terminating action for the requirements of this AD. (3) If there is a crack, before further flight, stop-drill the crack with a 3-millimeter diameter hole and repair the frame in accordance with the Accomplishment Instructions, paragraph 2.B.3., of the ASB. Accomplishing the requirements of paragraph 2.B.3. of the ASB constitutes terminating action for the requirements of this AD. (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, Regulations Group, 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, Regulations Group. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group. (c) Special flight permits may be issued in accordance with 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 inspection and repair shall be done in accordance with the Accomplishment Instructions of Eurocopter France AS 365 Alert Service Bulletin 53.00.42, dated January 31, 2001. 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; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC. (e) This amendment becomes effective on January 3, 2003. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD No. 2001-060-052(A), dated February 21, 2001. Issued in Fort Worth, Texas, on November 6, 2002. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 02-29155 Filed 11-27-02; 8:45 am] BILLING CODE 4910-13-P
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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