Airworthiness Directive · Amendment 39-11666 · Boeing Model 727 Series Airplanes
Boeing Model 727 Series Airplanes
Model 727-100, -100C, and -200 series airplanes, line numbers 1 through 1214 inclusive; certificated in any category; except those on which the modification specified by either Boeing Service Bulletin 727-57-0127, Revision 2, dated February 13, 1976, or Boeing Service Bulletin 727-57-0127, Revision 3, dated August 24, 1989, has been installed.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (h) 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.
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 series airplanes, that requires repetitive structural inspections of certain aging airplanes, and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their economic design service goal. The actions specified by this AD are intended to prevent degradation of the structural capabilities of the affected airplanes. This AD relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 727 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished.
To prevent degradation of the structural capabilities of the affected airplanes, accomplish the following:
(a) For those airplanes on which the initial inspection has not been accomplished in accordance with AD 94-07-08, amendment 39-8866: Prior to the accumulation of 16,000 total flight cycles or within 2,000 flight cycles after the effective date of this AD, whichever occurs later, accomplish the inspections required by either paragraph (c) or (d) of this AD.
(b) For those airplanes on which the initial inspection has been accomplished in accordance with AD 94-07-08, amendment 39-8866: Within 2,000 flight cycles after the effective date of this AD, unless accomplished within the last 12,000 flight cycles in accordance with AD 94-07-08, accomplish the inspections required by either paragraph (c) or (d) of this AD.
(c) Perform a fluorescent dye penetrant inspection (Type I) to detect cracking of certain wing ribs at the rib-to-stringer attachment in the areas specified in Boeing Service Bulletin 727-57-0127, Revision 3, dated August 24, 1989; in accordance with Boeing Standard Overhaul Practices Manual D6-51702, Chapter 20-20-02, Revision 79, dated March 1, 1999.
(d) Perform a high frequency eddy current inspection to detect cracking of certain wing ribs at the rib-to-stringer attachment in the areas specified in Boeing Service Bulletin 727-57-0127, Revision 3, dated August 24, 1989; in accordance with Boeing Commercial Jet Nondestructive Test Manual, Chapter 51-00-00, Part 6, dated August 5, 1997.
(e) If no crack is detected during any inspection required by either paragraph (c) or (d) of this AD, repeat the applicable inspection thereafter at intervals not to exceed 14,000 flight cycles.
(f) If any crack is detected during any inspection required by either paragraph (c) or (d) of this AD, prior to further flight, repair in accordance with Boeing Service Bulletin 727-57-0127, Revision 3, dated August 24, 1989; or in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA Transport Airplane Directorate; 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. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD. Repeat the applicable inspection thereafter at intervals not to exceed 14,000 flight cycles, following accomplishment of the repair.
(g)(1) Accomplishment of the actions required by this AD constitutes terminating action for the inspections required by paragraph (a) of AD 94-07-08, as specified in Boeing Service Bulletin 727-57-0127, Revision 3, dated August 24, 1989.
(2) Accomplishment of the structural modifications specified in either Boeing Service Bulletin 727-57-0127, Revision 2, dated February 13, 1976; or Revision 3, dated August 24, 1989; constitutes terminating action for the requirements of this AD.
