99-22-03: Chafing Within Engine Nacelle

99-22-03 BRITISH AEROSPACE REGIONAL AIRCRAFT [Formerly Jetstream Aircraft Limited; British Aerospace (Commercial Aircraft) Limited]: Amendment 39-11381. Docket 99-NM-19-AD. Issued October 14, 1999. Applicability: BAe Model ATP airplanes, except those airplanes on which British Aerospace Modification 10455A or 10455B (reference British Aerospace Service Bulletin ATP-71-15, dated December 11, 1998) has been accomplished, 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 (c) of this AD. The request should include an assessment of the effect of themodification, 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 chafing within the engine nacelle, which could result in flammable fluid leaking into a zone that contains ignition sources, accomplish the following: Repetitive Inspections and Corrective Actions (a) Prior to the accumulation of 3,000 total flight hours, or within 1 month after the effective date of this AD, whichever occurs later, perform the actions required in paragraphs (a)(1), (a)(2), and (a)(3) of this AD in accordance with British Aerospace Alert Service Bulletin ATP-A71-14, dated November 4, 1998. Thereafter, repeat the inspections required by paragraphs (a)(1) and (a)(2) of this AD at intervals not to exceed 1,500 flight hours, until accomplishment of the actions specified in paragraph (b) of this AD. (1) Perform an inspection of the access panel, part number (P/N) JD713J0037-000, to detect chafe damage. If any chafe damage is detected, repair the access panel in accordance with the service bulletin at the time specified in paragraph (a)(1)(i), (a)(1)(ii), or (a)(1)(iii), of this AD, as applicable. (i) If the damage has reduced the skin thickness by 10 percent or less: Repair within 600 flight hours. (ii) If the damage has reduced the thickness of the skin by more than 10 percent, but less than 20 percent: Repair within 100 flight hours. (iii) If the damage has reduced the thickness of the skin by more than 20 percent: Repair prior to further flight. (2) Perform an inspection of the fuel manifold drain hose, P/N JD007J0983-000 (C37351), to detect chafe damage. If any chafe damage is detected, either replace the fuel manifold drain hose with a new fuel manifold drain hose, P/N JD007J0983-000, in accordance with the service bulletin at the time specified in paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii) of this AD, as applicable; or accomplish the replacement specified in paragraph (b) of this AD. Replacement of the fuel manifold drain in accordance with paragraph (b) of this AD constitutes terminating action for the repetitive inspections required by this AD. (i) If there are signs of worn or polished strands in the outer braid, but no strand is broken: Replace within 1,500 flight hours. (ii) If five or less strands are broken: Replace within 300 flight hours. (iii) If more than five strands are broken or any sign of fuel leakage exists: Replace prior to further flight. (3) Install a protective spiral binding, P/N EFWRAP-125, on the fuel manifold drain hose. Optional Terminating Action (b) Replacement of the fuel manifold drain hose, P/N JD007J0983-000 (C37351), with a new, improved drain hose, P/N JD007J2377-000 (C44311), in accordance with British Aerospace Service Bulletin ATP-71-15, dated December 11, 1998, constitutes terminating action for the requirements of this AD. Alternative Methods of Compliance (c) 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, FAA, Transport Airplane Directorate. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtainedfrom the International Branch, ANM-116. Special Flight Permits (d) 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. Incorporation by Reference (e) The actions shall be done in accordance with British Aerospace Alert Service Bulletin ATP-A71-14, dated November 4, 1998; or British Aerospace Service Bulletin ATP-71-15, dated December 11, 1998, as applicable. 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 British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. 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. (f) This amendment becomes effective on November 26, 1999.