Airworthiness directives › 98-26-13
AD 98-26-13 Airworthiness Directives; Boeing Model 747 Series Airplanes
Models named: 747-100, -100B, -200, -200B, -200C, -300, - 400, 747SR series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 747-100, -100B, -200, -200B, -200C, -300, - 400, and 747SR series airplanes; having line numbers 1 through 830 inclusive; 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.
Compliance
Required as indicated, unless accomplished previously. To detect and correct stress corrosion cracking of the stop support fittings of the main entry doors and the resultant failure of the stop support fittings, which could result in loss of a main entry door and consequent rapid decompression of the airplane, accomplish the following: (a) Within 18 months after the effective date of this AD, perform a high frequency eddy current inspection to determine the material type of the stop support fittings of [[Page 70319]] the main entry doors, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53-2358, dated August 26, 1993. Perform the inspection only at those locations where the material type of the stop support fittings is unknown, as specified in Figure 3, Table 1, of the service bulletin. (1) If the fitting is made from 7075-T73 material, no further action is required by this AD for that fitting. (2) If the fitting is NOT made from 7075-T73 material, prior to further flight, perform a visual inspection to detect cracks of the stop support fitting of the main entry doors, in accordance with the service bulletin. (i) If no crack is detected, repeat the visual inspection thereafter at intervals not to exceed 36 months or 2,000 flight cycles, whichever occurs first. (ii) If any crack is detected, prior to further flight, replace the fitting with a stop support fitting made from 7075-T73 material, in accordance with the service bulletin. (b) Replacement of the stop support fitting of the main entry doors with a stop support fitting made from 7075-T73 material, in accordance with Boeing Service Bulletin 747-53-2358, dated August 26, 1993, constitutes terminating action for the repetitive inspection requirements of this AD for the replaced fitting. (c) As of the effective date of this AD, no person shall install a stop support fitting made from either 7079-T651 or 7075-T651 material on any airplane. (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 Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (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. (f) The actions shall be done in accordance with Boeing Service Bulletin 747-53-2358, dated August 26, 1993. 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. (g) This amendment becomes effective on January 25, 1999. Issued in Renton, Washington, on December 14, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-33541 Filed 12-18-98; 8:45 am] BILLING CODE 4910-13-U
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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