Airworthiness Directive · Amendment 39-17871 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 727-100 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991, unless previously modified using the service information specified in paragraphs (c)(1), (c)(2), or (c)(3) of this AD.
(1) Boeing Service Bulletin 727-53-0041, Revision 4, dated July 27, 1973.
(2) Boeing Service Bulletin 727-53-0041, Revision 5, dated January 25, 1990.
(3) Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991.
Note 1 to paragraph (c) of this AD: Boeing Service Bulletin 727-53-0041, Revision 4, dated July 27, 1973, is specified in Boeing Document D6-54860 “Aging Airplane Service Bulletin Structural Modification Program—Model 727,” Revision C, dated December 11, 1989, as mandated by AD 90-06-09, Amendment 39-6488 (55 FR 8370, March 7, 1990).
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727-100 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. For certain airplanes, this AD requires repetitive inspections for cracking in stringers or frames until modification, and repair if necessary. We are issuing this AD to detect and correct cracking in stringers or frames originating at or near stringer-to-frame attachment fastener holes, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
Before the accumulation of 16,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do a high frequency eddy current inspection and a general visual inspection for cracking in stringers and frames originating at or near stringer-to-frame attachment fastener holes, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles until the modification specified by paragraph (h) of this AD is accomplished. If any crack is found during any inspection required by this paragraph: Before further flight, repair or modify the affected stringer-to-frame attachment locations, in accordance with Part V, “Repair Data,” of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991.
Modifying the affected stringer-to-frame attachment locations, in accordance with Part IV, “Preventive Modification Data,” of the Accomplishment Instructions of Boeing Service Bulletin 727-53-0041, Revision 6, dated September 5, 1991, terminates the repetitive inspections required by paragraph (g) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
