AD 98-09-22 Airworthiness Directives; Aerospatiale Model ATR42-200, -300, and -320 Series Airplanes

Models named: ATR42-200, -300, -320 series. Read the applicability below — it usually turns on serial or part numbers too.

Model ATR42-200, -300, and -320 series airplanes, on which [[Page 23382]] Aerospatiale Modification 01392 has not been installed, certificated in any category. Note 1: This AD applies to each airplane 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 airplanes 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.

Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the airplane resulting from fatigue cracking of the windshield frame structure, accomplish the following: (a) Prior to the accumulation of 24,000 total flight cycles, or within 60 days after the effective date of this AD, whichever occurs later: Inspect to detect cracking of the windshield frame structure in accordance with Operation Description (B--Inspection) of the Accomplishment Instructions of Aerospatiale Service Bulletin ATR42- 53-0093, Revision 1, or ATR42-53-0094, Revision 2, both dated February 19, 1996. (1) If the inspection reveals no crack, or reveals cracking that does not exceed the specifications listed in Figure 6, Sheet 1, of Service Bulletin ATR42-53-0093, Revision 1, dated February 19, 1996: Prior to further flight, modify the windshield frame structure in accordance with either service bulletin. (2) If the inspection reveals any crack that exceeds the specifications in Figure 6, Sheet 1, of Service Bulletin ATR42-53- 0093, Revision 1, dated February 19, 1996, but does not exceed the cut-out areas specified in Figure 7, Sheet 1, of Service Bulletin ATR42-53-0094, Revision 2, dated February 19, 1996: Prior to further flight, modify the windshield frame structure in accordance with Service Bulletin 42-53-0094, Revision 2, dated February 19, 1996. (3) If the inspection reveals any crack that exceeds the cut-out areas specified in Figure 7, Sheet 1, of Service Bulletin ATR42-53- 0094, Revision 2, dated February 19, 1996: Prior to further flight, modify the windshield frame structure in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Note 2: Accomplishment of the modifications specified in ATR Service Bulletin ATR42-53-0093, Revision 1, or ATR42-53-0094, Revision 2, both dated February 19, 1996, is not equivalent to accomplishment of Aerospatiale Modification 01392. Therefore the ATR42 Time Limits Document inspection items with ``PRE MOD 1392'' effectivity are still applicable for airplanes modified by either of the previously described service bulletins. (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, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (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 airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with the following Aerospatiale Service Bulletins, which contain the specified effective pages: ---------------------------------------------------------------------------------------------------------------- Service bulletin referenced and Revision level date Page number shown on page shown on page Date shown on page ---------------------------------------------------------------------------------------------------------------- ATR42-53-0093, Revision 1, 1-4, 13.................. 1................. February 19, 1996. February 19, 1996. 5-12, 14-41............. Original.......... April 26, 1995. ATR42-53-0094, Revision 2, 1, 2, 8, 9, 16, 18, 39, 2................. February 19, 1996. February 19, 1996. 40, 48, 53, 54. 3, 4, 7, 10-15, 17, 19- 1................. May 29, 1995. 24, 26, 27, 29-32, 34- 38, 47, 55, 56. 5, 6, 25, 28, 33, 41-46, Original.......... April 24, 1995 49-52. ---------------------------------------------------------------------------------------------------------------- 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 4: The subject of this AD is addressed in French airworthiness directive 95-126-061(B), dated June 21, 1995. (e) This amendment becomes effective on June 3, 1998. Issued in Renton, Washington, on April 21, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-11068 Filed 4-28-98; 8:45 am] BILLING CODE 4910-13-U