Airworthiness Directive · Amendment 39-14833 · Boeing Model 767 Airplanes
Boeing Model 767 Airplanes
Superseded. A later AD replaced this one: AD 2011-14-02. Comply with the one in force.
This AD applies to all Boeing Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive detailed and high frequency eddy current (HFEC) inspections of the station (STA) 1809.5 bulkhead for cracking and corrective actions if necessary. This AD results from fatigue cracks found in the forward outer chord and horizontal inner chord at STA 1809.5. We are issuing this AD to detect and correct cracking in the bulkhead structure at STA 1809.5, which could result in failure of the bulkhead structure for carrying the flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Before the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever is later: Do the detailed and high frequency eddy current (HFEC) inspections for cracking as specified in Parts 1, 2, 3, and 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006; and do all corrective actions before further flight; by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006, except as provided by paragraph (g) of this AD. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles. Accomplishing the corrective action for the inspections specified in Part 1, 2, 3, or 4 of the service bulletin, as applicable, terminates the repetitive inspections for that area only.
If any cracking is found in the skin or in any structure other than the forward outer chord or horizontal inner chord, during any inspection required by this AD, and Boeing Alert Service Bulletin 767-53A0131, dated March 30, 2006, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
If no cracking is found during the most recent detailed and HFEC inspections for a specified area as required by paragraph (f) of this AD: Modification of a specified area according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, terminates the repetitive inspections required by paragraph (f) of this AD for that area only. For a forward outer chord, one approved method is accomplishment of the actions in Steps 4.A through 4.C and 4.G through 4.P of Repair 9, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 Structural Repair Manual (SRM), Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable. For a horizontal inner chord, one approved method is accomplishment of the actions in Steps 4.A, 4.B, and 4.F through 4.P of Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable.
(i) Repair of a forward outer chord done before the effective date of this AD in accordance with Repair 9, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable; is acceptable for compliance with the requirements of paragraph (f) of this AD for that area only. Repair of a horizontal inner chord before the effective date of this AD in accordance with Repair 10, dated April 15, 2006, of Chapter 53-80-08 of the Boeing 767-200 SRM, Document D634T201; Boeing 767-300 SRM, Document D634T210; Boeing 767-300F SRM, Document D634T215; or Boeing 767-400 SRM, Document D634T225; as applicable; is acceptable for compliance with the requirements of paragraph (f) of this AD for that area only.
