Airworthiness directives › 2003-13-09
AD 2003-13-09 Airworthiness Directives; Boeing Model 747 Series Airplanes
Models named: 747 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 747 series airplanes, line numbers 1 through 695 inclusive; certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To find and fix cracking of the upper skin of the outboard and center sections of the horizontal stabilizer and the rear spar structure, hinge fittings, terminal fittings, and splice plates, which could lead to reduced structural capability of the outboard and center sections of the horizontal stabilizer, and result in loss of controllability of the airplane; accomplish the following: Repetitive Inspections (a) At the time specified in paragraph (b) of this AD, do the Zone B inspections for Groups 1, 2, and 3 airplanes, as required by either paragraph (a)(1) or (a)(2) of this AD, per the Work Instructions of Boeing Alert Service Bulletin 747-55A2050, Revision 1, dated May 1, 2003. Repeat the applicable inspection at the applicable time specified in Sheet 2 of Figure 1 of the service bulletin. (1) Do nondestructive test (NDT) inspections for cracking of the upper skin of the outboard and center sections of the horizontal stabilizer and the rear spar structure, hinge fittings, terminal fittings, and splice plates, per Part 3 of the service bulletin. The inspections include an ultrasonic inspection of the outboard and center sections, rear spar upper chords under the hinge fitting halves, upper skins under the splice plates, and the rear spar webs behind the terminal fittings; a high frequency eddy current (HFEC) inspection of the terminal fitting around the fasteners; a low frequency eddy current inspection of the splice plates around the fasteners; a surface HFEC inspection of the rear spar upper chords in the radius area above the terminal fitting and the lower surface of the horizontal flange; and an HFEC inspection of the rear spar webs in the exposed area above the terminal fitting. (2) In lieu of the inspections required by paragraph (a)(1) of this AD: Do an alternate open hole HFEC inspection for cracking of the splice plates, terminal fittings, hinge fitting halves, rear spar upper chords, rear spar webs, and upper skins; and a magnetic particle inspection or fluorescent penetrant inspection for fracture or cracking of the bolts, if applicable; per Part 4 of the service bulletin. (b) Do the inspections required by paragraph (a) of this AD at the later of the times specified in paragraphs (b)(1) and (b)(2) of this AD. (1) Before the accumulation of 27,000 total flight cycles or 117,000 total flight hours, whichever is first. (2) Within 90 days after the effective date of this AD. Repair (c) If any discrepancy (cracking or damage) is found during any inspection per paragraph (a) of this AD: Before further flight, repair per the Work Instructions of Boeing Alert Service Bulletin 747-55A2050, Revision 1, dated May 1, 2003. Where the service bulletin specifies contacting the manufacturer for a repair method: 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 who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Alternative Methods of Compliance (d)(1) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, is authorized to approve alternative methods of compliance (AMOC) for this AD. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 747-55A2050, Revision 1, dated May 1, 2003. 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 (f) This amendment becomes effective on July 15, 2003. Issued in Renton, Washington, on June 18, 2003. Kalene Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-15855 Filed 6-27-03; 8:45 am] BILLING CODE 4910-13-P
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