Airworthiness Directive · Amendment 39-17555 · Wings
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category.
(2) This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections, methods, and compliance times). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) according to paragraph (k) of this AD. The request should include a description of changes to the required actions that will ensure the continued operational safety of the airplane.
We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727- 200F series airplanes. This AD was prompted by a structural re- evaluation by the manufacturer, which identified elements within the wing trailing edge flap area that qualify as structural significant items (SSIs). This AD requires revising the maintenance inspection program to include inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs, and repairing any cracked structure. We are issuing this AD to detect and correct fatigue cracking of the wing trailing edge structure, which could result in compromised structural integrity of the airplane.
(1) Before the accumulation of 55,000 total flight cycles, or within 12 months after the effective date of this AD, whichever occurs later: Revise the maintenance program to incorporate inspections that provide no less than the required damage tolerance rating (DTR) for each SSI listed in Boeing Document D6-48040-2, Supplemental Structural Inspection Document For Model 727 Airplanes, Appendix A, dated December 2010. The required DTR value for each SSI is identified in Boeing Document D6-48040-2, Supplemental Structural Inspection Document For Model 727 Airplanes, Appendix A, dated December 2010. The revision to the maintenance inspection program must include and must be implemented in accordance with the procedures in Section 3.0, “Flap and Support Structure (Flap Structure) SSI Information,” of Boeing Document D6-48040-2, Supplemental Structural Inspection Document For Model 727 Airplanes, Appendix A, dated December 2010; and in accordance with the procedures in Section 5.0, “Damage Tolerance Rating (DTR) System Application,” and Section 6.0, “SSI Discrepancy Reporting,” of Boeing Document D6-48040-1, Supplemental Structural Inspection Document (SSID), Volume 1, Revision H, dated June 1994.
(2) The initial compliance time for the inspections is before the accumulation of 55,000 total flight cycles, or within 3,000 flight cycles after 12 months from the effective date of this AD, whichever occurs later.
For any SSI that has been repaired or altered before the effective date of this AD such that the repair or design change affects the ability to accomplish the actions required by paragraph (g) of this AD: Before further flight, obtain FAA approval of an alternate inspection, in accordance with the procedures specified in paragraph (k) of this AD, or do the actions specified in paragraphs (h)(1) and (h)(2) of this AD as an approved method of compliance for the requirements of paragraph (g) of this AD.
(1) At the initial compliance time specified in paragraph (g) of this AD, identify each repair or design change to that SSI.
(2) Within 12 months after the identification of a repair or design change required by paragraph (h)(1) of this AD, assess the damage tolerance characteristics of each SSI affected by each repair or design change to determine the effectiveness of the applicable SSID inspection for that SSI and, if not effective, incorporate a revision into the maintenance inspection program to include a damage-tolerance-based alternative inspection program for each affected SSI. Thereafter, inspect the affected structure in accordance with the alternative inspection program. The inspection method and compliance times (i.e., threshold and repetitive intervals) of the alternative inspection program must be approved in accordance with the procedures specified in paragraph (k) of this AD.
If any cracked structure is found during any inspection specified in Boeing Document D6-48040-2, Supplemental Structural Inspection Document For Model 727 Airplanes, Appendix A, dated December 2010, before further flight, repair the cracked structure using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used other than those specified in Boeing Document D6-48040-2, Supplemental Structural Inspection Document For Model 727 Airplanes, Appendix A, dated December 2010, unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (k) of this AD.
