Airworthiness Directive · Amendment 39-14592 · Boeing Model 767-200, -300, and -300F Series Airplanes
Boeing Model 767-200, -300, and -300F Series Airplanes
This AD applies to Boeing Model 767-200, -300, and -300F series airplanes; certificated in any category; identified in Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action if necessary. This new AD requires new inspections for cracking or severe wear of the bearings of the link assembly, inspections of any link assembly not previously inspected for damage, and corrective actions if necessary. This AD also ends the existing repetitive inspections for certain airplanes, and extends the repetitive interval for the existing repetitive inspections and the compliance time for the corrective action on certain other airplanes. This AD also provides an optional terminating action. This AD results from additional reports indicating fractured bearings of the link assembly joint in the inboard and outboard flaps of the trailing edge. We are issuing this AD to prevent failure of the bearings in the link assembly joint, which could result in separation of the inboard or outboard flap and consequent loss of control 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.
For airplanes having line numbers 1 through 819 inclusive, on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Within 90 days after February 14, 2002 (the effective date of AD 2002-01-15), or within 36 months after date of manufacture of the airplane, whichever is later, do detailed inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies (e.g., lubrication passage blocked, fractured bearing, loose or damaged joint); per Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004. After the effective date of this AD, only Revision 2 of the service bulletin may be used.
For airplanes having line numbers 1 through 819 inclusive, on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Do the actions required by paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable, at the time specified, per the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004. After the effective date of this AD, only Revision 2 of the service bulletin may be used.
(1) If the lubrication passage is not blocked and no fractured bearing or loose or damaged joint is found, do paragraph (h) of this AD.
(2) If the lubrication passage is blocked and no fractured bearing or loose or damaged joint is found, repeat the inspection required by paragraph (f) of this AD at intervals not to exceed 60 days, and within 24 months after the most recent inspection required by paragraph (a) or (b)(1) of AD 2002-01-15, or paragraph (f) of this AD, as applicable, do the actions required by paragraph (g)(3) of this AD.
(3) If any fractured bearing or loose or damaged joint is found, before further flight, do the corrective action (including removal of the link assembly, inspection for damage, and replacement with a new assembly if damaged), as specified in Part 2 of the Accomplishment Instructions of the service bulletin.
For airplanes having line numbers 1 through 819 inclusive, on which the lubrication passage has not been found blocked and no fractured bearing or loose or damaged joint has been found, and on which Part 2 of Boeing Alert Service Bulletin 767-27A0167 has not been done: Within 24 months after the most recent inspection in accordance with paragraph (a) or (b)(1) of AD 2002-01-15, or paragraph (f) of this AD, as applicable, remove the link assembly, perform a detailed inspection of the link assembly for damage, and reinstall the undamaged link or replace it with a new link assembly that has been inspected and found to be free of damage or other discrepancy, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004.
(i) For all airplanes: Remove the link assembly, and perform a detailed inspection for cracking of the bearing ball, and for severe wear of the outer race of the bearing, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004. Do this action at the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. Then, repeat this action at intervals not to exceed 72 months. If any cracking or severe wear is found during any inspection required by this paragraph: Before further flight, do the corrective action in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004, or do paragraph (j) of this AD.
(1) For airplanes identified in the service bulletin as being in Group 1: Within 72 months after doing Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, dated December 7, 2000; or Revision 2, dated October 7, 2004, or within 18 months after the effective date of this AD, whichever is later.
(2) For airplanes identified in the service bulletin as being in Group 2: Within 72 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness; or within 18 months after the effective date of this AD; whichever is later.
For all airplanes: Replacing the existing link assemblies of the trailing edge flaps with new, improved or modified assemblies that contain new bearings, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-27-0196, dated April 21, 2005, ends the repetitive removal/inspections required by paragraph (g), (h), and (i) of this AD, as applicable.
Inspections and corrective actions done before the effective date of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-27A0167, Revision 1, dated June 6, 2002, are acceptable for compliance with the corresponding actions required by this AD.
Although Boeing Alert Service Bulletin 767-27A0167, Revision 2, dated October 7, 2004, specifies to submit certain information to the manufacturer, this AD does not require that action.
