Airworthiness Directive · Amendment 39-21412 · Wings
The Boeing Company Airplanes
This AD applies to all The Boeing Company 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 series airplanes. This AD was prompted by a determination that excessive sealant coating on internal wing Structural Significant Items (SSIs) may not reveal cracks during inspections required by AD 98-11-03 R1. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs of the wing. This AD also requires repetitive inspections for cracking of the affected SSIs and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Prior to reaching the applicable time specified in paragraph (g)(2)(i) or (ii) of this AD, incorporate a revision into the existing maintenance or inspection program, as applicable, that provides no less than the required damage tolerance rating (DTR) for each SSI of the wing listed in Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume I, Temporary Revision 08-1001, dated February 2020; and Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume II, Temporary Revision 11-1001, dated February 2020.
(2) At the applicable time specified in paragraph (g)(2)(i) or (ii) of this AD, perform initial inspections to detect cracks in the SSIs identified in Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume I, Temporary Revision 08-1001, dated February 2020; and Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume II, Temporary Revision 11-1001, dated February 2020.
(i) For Model 727-100C and 727-200F series airplanes: Inspect prior to the accumulation of 46,000 total flight cycles, or within 12 months after the effective date of this AD, whichever occurs later.
(ii) For all airplanes except for those airplanes identified in paragraph (g)(2)(i) of this AD: Inspect prior to the accumulation of 55,000 total flight cycles, or within 3,000 flight cycles measured from the date 12 months after the effective date of this AD, whichever occurs later.
(3) At the intervals specified in in Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume I, Temporary Revision 08-1001, dated February 2020; and Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume II, Temporary Revision 11-1001, dated February 2020, as applicable, repeat the inspections required by paragraph (g)(2) of this AD.
(4) If any cracked structure is found during any inspections required by paragraph (g) of this AD, repair before further flight using an FAA-approved method or using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Within 12 months after repair, incorporate a revision into the maintenance or inspection program, as applicable, to include a damage-tolerance-based alternative inspection program for the repaired structure. Thereafter, inspect the affected structure in accordance with the alternative program. The inspection method and compliance times (i.e., threshold and repetitive intervals) of the alternative program must be approved in accordance with the procedures specified in paragraph (j) of this AD.
After the existing maintenance or inspection program has been revised as required by paragraph (g)(1) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j) of this AD.
Accomplishing the revision required by paragraph (g)(1) of this AD and the initial inspections identified in Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume I, Temporary Revision 08-1001, dated February 2020; and Boeing 727 Supplemental Structural Inspection Document D6-48040-1, Volume II, Temporary Revision 11-1001, dated February 2020, as required by paragraph (g)(2) of this AD, terminate the corresponding SSI inspections specified in Boeing Document No. D6-48040-1, Volumes 1 and 2, “Supplemental Structural Inspection Document” (SSID), Revision H, dated June 1994, as required by AD 98-11-03 R1.
