AD 2003-16-14 Airworthiness Directives; Boeing Model 747 Series Airplanes Equipped with Pratt & Whitney JT9D-3 or JT9D-7 Series Engines (except JT9D-70 Series Engines)

Models named: 747 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 747 series airplanes, equipped with Pratt & Whitney JT9D-3 or JT9D-7 series engines (excluding JT9D-70 series engines), as listed in Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001; 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 (g) 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 detect and correct cracking or other damage to the structure of the upper or lower surface of the forward lower spar and any loose or damaged fasteners, which could result in reduced structural capability of nacelle struts one through four, and possible separation of the strut and engine from the airplane during flight, accomplish the following: Inspection of Upper Surface of Forward Lower Spar (a) At the later of the times shown in paragraphs (a)(1) and (a)(2) of this AD: Perform a detailed inspection of the upper surface of the forward lower spar to detect cracks, fretting damage, and any loose or damaged fasteners, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001. (1) Within 500 flight cycles, but no sooner than 300 flight cycles, after modification of the strut in accordance with AD 95-10-16, amendment 39-2933; or (2) Within 6 months after the effective date of this AD. 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.” Inspection of Lower Surface of Forward Lower Spar (b) If the detailed inspection required by paragraph (a) of this AD reveals any crack or fretting damage, or any loose or damaged fastener: Prior to further flight, perform a detailed inspection of the lower surface of the forward lower spar to detect cracks, fretting damage, and any loose or damaged fasteners, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001. Follow-up Inspection (c) If the detailed inspection of the upper surface of the forward lower spar required by paragraph (a) of this AD reveals no crack or fretting damage and no loose or damaged fastener: At the later of the times specified in paragraphs (c)(1) and (c)(2) of this AD, repeat the detailed inspection of the upper surface of the forward lower spar and perform a detailed inspection of the lower surface of the forward lower spar, in accordance with Parts 1 and 2, respectively, of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001. (1) Within 1,500 flight cycles, but no sooner than 1,300 flight cycles, after modification of the strut, in accordance with AD 95-10-16; or (2) Within 18 months after the effective date of this AD. Optional Follow-up Inspection (d) If the detailed inspection of the upper surface of the forward lower spar required by paragraph (a) of this AD reveals no crack or fretting damage, and no loose or damaged fastener: Prior to further flight, the operator may elect to perform a detailed inspection of the lower surface of the forward lower spar to detect cracks, fretting damage, and any loose or damaged fasteners, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001, provided that the airplane has accumulated at least 1,300 flight cycles since modification of the strut per AD 95-10-16. Corrective Action (e) If any detailed inspection described in paragraph (a), (b), (c), or (d) of this AD reveals any crack or fretting damage to the upper or lower surface of the forward lower spar or any loose or damaged fastener: Prior to further flight, accomplish the actions specified in paragraph (e)(1) or (e)(2) of this AD, as applicable. (1) If the crack or fretting damage to the upper or lower surface of the forward lower spar falls within the parameters specified in Figure 4 or 5 (as applicable) of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001, and the airplane has accumulated 1,300 flight cycles or more since modification of the strut per AD 95-10-16: Remove any loose or damaged fasteners, repair any cracks or fretting damage to the upper or lower surface of the forward lower spar, and install new fasteners, in accordance with the Accomplishment Instructions of the service bulletin. No further action is required by this AD. (2) If the crack or fretting damage to the upper or lower surface of the forward lower spar does not fall within the parameters specified in Figure 4 or 5 (as applicable) of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2209, dated November 8, 2001, or if the airplane has accumulated fewer than 1,300 flight cycles since modification of the strut per AD 95-10-16: Accomplish additional 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 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. (f) If the detailed inspection specified in paragraph (c) or (d) of this AD reveals no cracks or other damage to the upper or lower surface of the forward lower spar and no loose or damaged fasteners, no further action is required by this AD. Alternative Methods of Compliance (g) 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, FAA. 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 (h) 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 (i) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 747-54A2209, dated November 8, 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 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 (j) This amendment becomes effective on September 22, 2003. Issued in Renton, Washington, on August 6, 2003. Neil D. Schalekamp, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-20712 Filed 8-15-03; 8:45 am] BILLING CODE 4910-13-P