Airworthiness directives › 2003-23-03
AD 2003-23-03 Airworthiness Directives; Boeing Model 737-100, -200, and -200C Series Airplanes
Models named: 737-100, -200, -200C series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 737-100, -200, and -200C series airplanes; line numbers 1 through 291 inclusive; certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To detect and correct discrepancies in the upper and lower skins of the fuselage lap joint and circumferential joint, which could result in sudden fracture and failure of a lap joint or circumferential joint and rapid decompression of the airplane fuselage, accomplish the following: Requirements of AD 2000-17-04, Amendment 39-11878 Initial and Repetitive Inspections (a) Perform the applicable (initial and repetitive) inspections as specified in Figures 1 through 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1224, dated August 17, 2000, to detect discrepancies ( i.e. , cracks, pillowing, corrosion, delamination, or loose or missing fasteners) in the upper and lower skins of the fuselage lap joint. Perform the inspections at the applicable times specified in Tables 1 and 2 of section 1.E. ‘Compliance’ of the alert service bulletin, in accordance with the alert service bulletin; except that where Table 1 specifies a compliance time of “airplane flight cycles at time of service bulletin release,” this AD requires a compliance time of “airplane flight cycles as of September 11, 2000 (the effective date of AD 2000-17-04, amendment 39-11878).” Repair (b) Prior to further flight: Repair any discrepancies detected during any inspection required by paragraph (a) of this AD in accordance with Boeing Alert Service Bulletin 737-53A1224, dated August 17, 2000; repair any discrepancies detected during any inspection required by paragraph (c) of this AD in accordance with Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002. If any discrepancy is detected and the alert service bulletin specifies that the manufacturer may be contacted for disposition of certain repairs, prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with 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. New Requirements of This AD Compliance Times (c) Where the compliance times in Section 1.E. ‘Compliance’ of Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002, specify a compliance time interval calculated “from release of service bulletin,” this AD requires compliance within the interval specified in the service bulletin “after the effective date of this AD.” In addition, where the compliance time for the initial and repetitive inspections in Tables 1 through 3 of section 1.E. ‘Compliance’ of the service bulletin specifies “airplane flight cycles at time of service bulletin release,” this AD requires a compliance time of “airplane flight cycles as of the effective date of this AD.” Initial and Repetitive Inspections (d) Except as provided by paragraph (e) of this AD: Perform the applicable (initial and repetitive) inspections as specified in Figures 1 through 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002, to detect discrepancies ( i.e. , cracks, pillowing, corrosion, delamination, or loose or missing fasteners) in the upper and lower skins of the fuselage lap joint and circumferential joint. Perform the inspections at the applicable times specified in Tables 1 and 2 of section 1.E. “Compliance” of the alert service bulletin, in accordance with the alert service bulletin, until accomplishment of paragraph (f) of this AD. Accomplishment of this paragraph terminates the inspections required by paragraph (a) of this AD. (e) For airplanes that have accumulated more than 70,000 total flight cycles as of the effective date of this AD: Do the first repeat inspection at the earlier of the times specified in paragraph (e)(1) or (e)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles. (1) Within 2,000 flight cycles after the last inspection done per AD 2000-17-04. (2) Within 1,000 flight cycles after the last inspection done per AD 2000-17-04, or within 500 flight cycles after the effective date of this AD, whichever is later. Terminating Modification (f) Perform the modification of the skin of all fuselage lap joints between body stations 259.5 and 1016 per part IV of the Work Instructions of Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002; at the applicable times specified in Table 3 of section 1.E. “Compliance” of the alert service bulletin; in accordance with the alert service bulletin. Accomplishment of this paragraph terminates the repetitive inspection requirements of this AD. Alternative Methods of Compliance (g)(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 (h) Unless otherwise specified by this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 737-53A1224, dated August 17, 2000; and Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002; as applicable. (1) The incorporation by reference of Boeing Alert Service Bulletin 737-53A1224, Revision 1, dated March 14, 2002, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Boeing Alert Service Bulletin 737-53A1224, dated August 17, 2000, was approved previously by the Director of the Federal Register as of September 11, 2000 (65 FR 51750, August 25, 2000). (3) 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 (i) This amendment becomes effective on December 23, 2003. Issues in Renton, Washington, on November 7, 2003. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-28492 Filed 11-17-03; 8:45 am] BILLING CODE 4910-13-P
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1