AD 92-19-11

92-19-11 BOEING: Amendment 39-8369. Docket No. 92-NM-37-AD. Supersedes AD 90-17-06, Amendment 39-6691.

Applicability: All Model 727 series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent loss of cabin pressurization, accomplish the following:

(a) For airplanes having line numbers 001 through 1432, perform a detailed visual, high frequency eddy current (HFEC), or dye penetrant inspection for cracks in the pressure floor, in accordance with Boeing Service Bulletin 727-53-149, Revision 2, dated March 20, 1981; or Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, or Revision 4, dated June 27, 1991. Accomplish the inspection prior to the compliance time specified in paragraph (a)(1) or (a)(2) of this AD, whichever occurs earlier:

(1) Prior to the accumulation of 30,000 landings, or within 2,500 landings after January 20, 1989 (the effective date of AD 88-26-02, amendment 39-6089), whichever occurs later; or

(2) Prior to the accumulation of 20,000 landings or within 2,500 landings after September 17, 1990 (the effective date of AD 90-17-06, amendment 39-6691), whichever occurs later.

(b) For airplanes defined as Group 2 in Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, and as Group I that have been modified in accordance with Boeing Service Bulletin 727-53-149, Revision 2, dated March 20, 1981: Prior to the accumulation of 20,000 landings since manufacture or within the next 2,500 landings after September 17, 1990 (the effective date of AD 90-17-06, Amendment 39-6691), whichever occurs later, perform a detailed visual, high frequency eddy current (HFEC), or dye penetrant inspection to detect cracks in the pressure floor, in accordance with Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989; or Revision 4, dated June 27, 1991.

(c) For all airplanes listed in Boeing Service Bulletin 727-53-0149, Revision 4, dated June 27, 1991: Prior to the accumulation of 20,000 landings since manufacture, or within the next 2,500 landings after the effective date of this AD, whichever occurs later, perform a detailed visual, high frequency eddy current (HFEC), or dye penetrant inspection to detect cracks in the pressure floor adjacent to BS 950, outboard of BL 50, in accordance with Boeing Service Bulletin 727-53-0149, Revision 4, dated June 27, 1991.

(d) Repeat the inspection required by paragraphs (a), (b), or (c) of this AD, as applicable, at intervals as follows:

(1) If the previous inspection was accomplished using a visual or dye penetrant inspection technique, the next inspection must be accomplished within 4,000 landings.

(2) If the previous inspection was accomplished using an HFEC inspection technique, the next inspection must be accomplished within 5,000 landings.

(e) If cracks are detected as a result of any of the inspections required by this AD that do not exceed the limits listed in Table I in the Accomplishment Instructions of Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, or Revision 4, dated June 27, 1991, prior to further flight, repair in accordance with the interim repair described in Part II of the Accomplishment Instructions, or the permanent repair described in Part III of the Accomplishment Instructions of the service bulletin, or repair in accordance with Boeing Drawing 65C36247, Revision A, dated January 15, 1992. The interim repair must be replaced within 600 landings after accomplishment with the permanent repair.

(f) If cracks are detected as a result of any of the inspections required by this AD that exceed the limits listed in Table I in the Accomplishment Instructions of Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, or Revision 4, dated June 27, 1991, prior to further flight, accomplish the permanent repair described in Part III of the Accomplishment Instructions of the service bulletin, or repair in accordance with Boeing Drawing 65C36247, Revision A.

(g) Blind fasteners installed in accordance with Part III of Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, or Revision 4, dated June 27, 1991, are to be used as an interim repair only. The blind fasteners have a life limit of 10,000 landings before they must be replaced with solid fasteners in accordance with Part III of the service bulletin. The blind fasteners must be inspected for loose or missing fasteners after accumulating 3,000 landings since installation or 1,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,500 landings. Blind fasteners installed prior to the effective date of this AD must be replaced prior to the accumulation of 10,000 landings or within 3,000 landings after the effective date of this AD, whichever occurs later.

(h) Terminating action for the repetitive inspection requirements of this AD is as follows:

(1) Incorporation of the permanent repairs in accordance with paragraphs (e) or (f) of this AD terminates the repetitive inspection requirements of paragraph (d) of this AD for that area. Incorporation of the preventative modification described in Part IV of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989, or Revision 4, dated June 27, 1991, terminates the repetitive inspection requirement of paragraph (d) of this AD for that area.

(2) Repair or modification in accordance with Boeing Drawing 65C36247, Revision A, dated January 15, 1992, constitutes terminating action for the repetitive inspection requirement of paragraph (d) of this AD.

(i) 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). 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Seattle ACO.

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

(k) The inspections, repairs, and modifications shall be done in accordance with Boeing Drawing 65C36247, Revision A, dated January 15, 1992; Boeing Service Bulletin 727-53-0149, Revision 4, dated June 27, 1991; Boeing Service Bulletin 727-53-0149, Revision 3, dated November 2, 1989; as applicable; and Boeing Service Bulletin 727-53-149, Revision 2, dated March 20, 1981, which contains the specified effective pages:

Page Number Revision Level Shown on Page Date Shown on Page 1-22, 25-26, 28-54 2 March 20, 1981 23-24, 27, 1 September 19, 1980

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.

This amendment 39-8369, AD 92-19-11, supersedes AD 90-17-06, amendment 39-6691, which superseded AD 88-26-02, amendment 39-6089.

(l) This amendment becomes effective on December 14, 1992.