Airworthiness Directive · Amendment 39-16032 · Boeing Model 767-200, -300, and -300F Series Airplanes
Boeing Model 767-200, -300, and -300F Series Airplanes
Superseded. A later AD replaced this one: AD 2010-22-01. Comply with the one in force.
This AD applies to Boeing Model 767-200, -300, and -300F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008.
We are adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires repetitive inspections for fatigue cracking and corrosion of the upper link fuse pin of the nacelle struts, and related investigative and corrective actions if necessary. This AD also provides terminating action for the repetitive inspections. This AD results from two reports of cracked upper link fuse pins. We are issuing this AD to prevent fatigue cracking or corrosion of the upper link fuse pin, which could result in failure of the fuse pin and consequent reduced structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane during flight.
Comply with this AD within the compliance times specified, unless already done.
Inspect the upper link fuse pin of the nacelle struts for fatigue cracking and corrosion at the applicable time specified in Table 1 of this AD. Do the applicable inspection by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008; and do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection at intervals not to exceed 3,000 flight cycles or 24 months, whichever is first, until the requirements of paragraph (g) of this AD have been done.
| Engine type | At the later of: initial inspection threshold | Grace period |
|---|---|---|
| JT9D | 14,000 total flight cycles | Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever is first. |
| CF6-80A | 24,000 total flight cycles | Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever is first. |
| PW4000 | 8,000 total flight cycles | Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever is first. |
| CF6-80C2 | 10,000 total flight cycles | Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever is first. |
| RB211 | 24,000 total flight cycles | Within 3,000 flight cycles or 18 months after the effective date of this AD, whichever is first. |
Note 1: The upper link inspections can be done with the pylon and/or engine in any position.
Note 2: In paragraph 3.B, Steps 4.b.(1)(a) and 4.b.(2)(b)2){a} of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008, the procedures specify to apply two layers of Boeing Material Specification (BMS) 10-11 primer to the inside surface of the fuse pin if no crack indication is found. However, two layers of primer are only necessary to touch up bare areas on the fuse pin if no crack indication is found.
Accomplishment of the modification specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, terminates the inspections required by paragraph (f) of this AD.
(1) For Model 767 series airplanes powered by Rolls-Royce RB211 series engines, as identified in AD 2000-19-09: Modification of the nacelle strut and wing structure, as required by paragraphs (a) and (b) of AD 2000-19-09.
(2) For Model 767-200, -300, and -300F series airplanes powered by Pratt & Whitney and General Electric engines, as identified in AD 2004-16-12: Modification of the nacelle strut and wing structure, as required by paragraphs (a), (b), (d), and (e) of AD 2004-16-12.
Inspection of the fuse pins before the effective date of this AD in accordance with Boeing Service Bulletin 767-54-0074, dated March 27, 1997, is acceptable for compliance with the inspections required by paragraph (f) of this AD if the inspections are accomplished without using an operator's equivalent procedure. Replacement of the fuse pins with new fuse pins before the effective date of this AD in accordance with Boeing Service Bulletin 767-54-0074, dated March 27, 1997, is acceptable for compliance with the modification required by paragraph (g) of this AD.
