98-24-03 R1: Combustion Core Fairings

98-24-03 R1 BMW ROLLS-ROYCE GmbH: Amendment 39-11425. Docket 98-ANE-74-AD. Revises AD 98-24-03, Amendment 39-11050. Issued November 5, 1999. Applicability: BMW Rolls-Royce GmbH (BRR) Model BR700-710A1-10 and BR700-710A2-20 turbofan engines installed on, but not limited to, Gulfstream Aerospace G-V and Bombardier BD-700-1A10 series airplanes. Note 1: This airworthiness directive (AD) applies to each engine 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 engines 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 (f) 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 engine compressor and combustion core fairing (also referred to as the engine core fairing) detachment which could result in damage to the engine bypass duct, engine failure and damage to the aircraft, accomplish the following: Inspections, Repair, Replacement, and Torquing (a) Prior to further flight, visually inspect the engine core fairings and fasteners to ensure correct installation and for cracks, loose fairings, or fasteners, and if loose, cracked, damaged, or improperly installed, repair or replace with serviceable parts. Torque all the fasteners to the increased torque value, in accordance with BRR Service Bulletin (SB) R700-72-900062, Revision 1, dated October 29, 1998, or Revision 2, dated November 3, 1998, or Revision 3, dated March 24, 1999. (b) Thereafter, except as provided in paragraphs (c) or (d) of this AD, at intervals not to exceed 50 hours time-in-service (TIS) since last inspection, visually inspect the engine core fairings and fasteners for cracks, loose fairings, or fasteners, and, if loose, cracked, or damaged, repair or replace with serviceable parts. Torque all the fasteners to the increased torque value, in accordance with BRR SB BR700-72-900062, Revision 2, dated November 3, 1998, or Revision 3, dated March 24, 1999. (c) Following an initial inspection in accordance with paragraph (a) of this AD, and one follow-on inspection in accordance with paragraph (b), if both inspections found no cracks, damage, loose fairings or fasteners the repetitive inspection interval may be increased to 150 hours TIS since last inspection in accordance with the procedures described in paragraph (b) of this AD. (d) Reinspection and retorquing prior to further flight is required in accordance with paragraph (a) of this AD, following any engine core fairing or fastener which has been removed, repaired or replaced. One successful follow-on inspection and retorque in accordance with paragraph (b) of this AD must be accomplished before the repetitive 150 hour TIS inspection interval described in paragraph (c) of this AD is permitted. Optional Terminating Action (e) Incorporation of the redesigned engine core fairings in accordance with BRR SB BR700-72-100900, Revision 1, dated September 10, 1999, constitutes terminating action for the requirements specified in paragraphs (a), (b), (c), and (d) of this AD. Alternative Methods of Compliance (f) 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, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. Incorporation by Reference (g) The actions required by this AD shall be done in accordance with the following BRR SBs: BR700-72-900062, Revision 1, dated October 29, 1998; Revision 2, dated November 3, 1998; Revision 3, dated March 24, 1999; and BR700-72-100900, Revision 1, dated September 10, 1999. 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 BMW Rolls-Royce GmbH, Eschenweg 11, D-15827 Dahlewitz, Germany; telephone 011-49-33-7086-1883; fax 011-49-33-7086-3276. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.(h) This amendment becomes effective on December 27, 1999.