AD 2002-24-03 Airworthiness Directives; Boeing Model 747 Series Airplanes Powered by General Electric (GE) CF6-80C2 Series Engines

Model 747-200B, −300, −400, −400D, and −400F series airplanes powered by General Electric CF6-80C2 series engines, as listed in Boeing Alert Service Bulletin 747-54A2207, dated November 16, 2000, certificated in any category. Note 1: This AD applies to each airplane 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 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 (d) 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 find and fix discrepant fasteners of the diagonal brace fittings, which could result in reduced structural integrity of the diagonal brace-to-strut attachment, and possible separation of the strut and engine from the airplane, accomplish the following: Repetitive Inspections and Torque Checks/Corrective Action (a) Do a detailed inspection and torque check to find discrepancies of the fasteners (e.g., loose, fractured, or missing fastener heads) that attach the diagonal brace fittings of the lower spar to the inboard engine struts, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD, per Boeing Alert Service Bulletin 747-54A2207, dated November 16, 2000, excluding Evaluation Form. Repeat the inspection and check after that every 8,000 flight hours or 24 months, whichever is first. Note 2: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” (1) For airplanes that have not been modified as required by AD 95-13-06, amendment 39-9286 (all Group 2 airplanes): Before the accumulation of 6,000 total flight cycles or within 24 months after the effective date of this AD, whichever is later. (2) For airplanes that have been modified as required by AD 95-13-06 (all Group 1 airplanes): Before the accumulation of 6,000 total flight cycles after doing the modification or within 24 months after the effective date of this AD, whichever is later. (b) If no discrepancy is found during any inspection/check required by paragraph (a) of this AD, repeat the inspection/check at the time specified in paragraph (a) of this AD until the terminating action specified in paragraph (c) of this AD is done. If any discrepancy is found, do the applicable actions specified in paragraph (b)(1) or (b)(2) of this AD. (1) If any discrepancy is found in the area that connects the diagonal brace fitting to the aft bulkhead, before further flight, repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, as required by this paragraph, the approval must specifically reference this AD. (2) If any discrepancy is found in any area other than that specified in paragraph (b)(1) of this AD, before further flight, do the terminating action specified in paragraph (c) of this AD. Terminating Action (c) Except as provided by paragraph (b)(2) of this AD, within 72 months after the effective date of this AD: Do the modification (including doing a high frequency eddy current (HFEC) inspection, oversizing the fastener holes, and installing new fasteners) as specified in and per Figure 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2207, dated November 16, 2000, excluding Evaluation Form. If any cracking is found during the HFEC inspection and the service bulletin specifies contacting Boeing for repair procedures, before further flight, repair per a method approved by the Manager, Seattle ACO; or per data meeting the type certification basis of the airplane approved by a Boeing Company DER who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, as required by this paragraph, the approval must specifically reference this AD. Accomplishment of the actions specified in this paragraph ends the repetitive inspections and checks. Alternative Methods of Compliance (d) 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, Seattle ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (e) 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 (f) Except as provided by paragraphs (b)(1) and (c) of this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 747-54A2207, dated November 16, 2000, excluding Evaluation Form. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. Effective Date (g) This amendment becomes effective on January 7, 2003. Issued in Renton, Washington, on November 20, 2002. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-30343 Filed 12-2-02; 8:45 am] BILLING CODE 4910-13-P