AD 91-03-19 R1

91-03-19 R1 BOEING: Amendment 39-8237. Docket No. 91-NM-231-AD. Revises AD 91-03-19, Amendment 39-6885.

Applicability: Model 727-200 and 727-200F series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent rapid depressurization of the cabin due to fuselage cracks under the center engine inlet pedestal housing, accomplish the following:

(a) Perform a detailed external visual inspection for fuselage skin cracks from body station (BS) 1090 to BS 1110, in accordance with Boeing Alert Service Bulletin 727-53A0204, Revision 3, dated August 15, 1991, or previous FAA-approved revisions, within the time specified in subparagraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.

(1) For airplanes identified as Group 1 in the service bulletin, inspect within 500 flight cycles or 2 months after March 11, 1991 (the effective date of AD 91-03-19, Amendment 39-6885), whichever occurs first.

(2) For airplanes identified as Group 2 in the service bulletin, inspect within 1,250 flight cycles or 6 months after March 11, 1991, whichever occurs first.

(3) For airplanes identified as Group 3 in the service bulletin, inspect within 2,500 flight cycles or 18 months after March 11, 1991, whichever occurs first.

(b) Repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 3,000 flight cycles or 18 months, whichever occurs first.

(c) If fuselage skin cracks are found, prior to further flight, accomplish either of the following:

(1) Repair in accordance with the Boeing Alert Service Bulletin 727-53A0204, Revision 2, dated August 9, 1990, or previous FAA-approved revisions. After repair, continue the repetitive inspections in accordance with paragraph (b) of this AD. Or

(2) Repair in accordance with Part III, paragraph B. or D., of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0204, Revision 3, dated August 15, 1991. This constitutes terminating action for the repetitive inspections required by paragraph (b) of this AD.

(d) In cases where cracking is not found, modification in accordance with one of the following service documents constitutes terminating action for the repetitive inspections required by paragraph (b) of this AD:

(1) Boeing Drawing 65C35757; or

(2) Paragraph C. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0204, Revision 2, dated August 9, 1990, or Revision 3, dated August 15, 1991.

(e) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.

(f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished.

(g) The inspection, repair, and modification shall be done in accordance with Boeing Alert Service Bulletin 727-53A0204, Revision 2, dated August 9, 1990; or Revision 3, dated August 15, 1991; as appropriate. 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. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.

(h) This amendment becomes effective on June 12, 1992.