Airworthiness Directive · Amendment 39-13959 · Boeing Model 767-200, -300, and -300F Series Airplanes
Boeing Model 767-200, -300, and -300F Series Airplanes
This AD applies to all Boeing Model 767-200, -300, and -300F series airplanes, certificated in any category.
The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 767-200, -300, and -300F series airplanes. That AD currently requires examination of maintenance records to determine if Titanine JC5A (also known as Desoto 823E508) corrosion inhibiting compound ("C.I.C.") was ever used; inspection for cracks or corrosion and corrective action, if applicable; repetitive inspections and C.I.C. applications; and modification of the aft trunnion area of the outer cylinder, which terminates the need for the repetitive inspections and C.I.C. applications. This new AD also requires, for certain other airplanes, repetitive inspections for cracks or corrosion, corrective action if necessary, and repetitive C.I.C. applications. This AD is prompted by a report that JC5A was used on more airplanes during production than previously identified. We are issuing this AD to prevent severe corrosion in the main landing gear (MLG) outer cylinder at the aft trunnion, which could develop into stress corrosion cracking and consequent collapse of the MLG.
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 with L/Ns 1 through 833 inclusive, and 875 and subsequent: Do the actions specified in paragraphs (g) through (q) of this AD, as applicable.
Within 90 days after May 6, 2002 (the effective date of AD 2002-08-07, amendment 39-12715), examine airplane records to determine if Titanine JC5A or Desoto 823E508 (hereafter collectively referred to as “JC5A”) corrosion inhibiting compound (“C.I.C.”) was used in the aft trunnion area of the MLG outer cylinder during general maintenance, overhaul, or incorporation of Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995, Revision 1, dated October 10, 1996 (required by paragraph (e) of AD 96-21-06, amendment 39-9783), or Revision 2, dated November 30, 2000; in accordance with Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003. If records do not show conclusively which compound was used, assume JC5A was used. Refer to Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001, for the line numbers of airplanes that were assembled new using JC5A.
Note 1: Prior to January 31, 2001, if BMS 3-27 was ordered from Boeing, Boeing shipped JC5A as a substitute.
Except as provided by paragraph (p) (“Use of JC5A Prohibited”) of this AD, if, according to the criteria of paragraph (g) of this AD, JC5A was never used, no further action is required by this AD.
(i) For Category 1 MLG outer cylinders as identified in Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001: If, according to the criteria of paragraph (g) of this AD, JC5A may have been used, perform the actions specified in both paragraphs (j) and (k) of this AD, as applicable, in accordance with Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003.
(j) For MLGs and MLG outer cylinders identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD: Within 90 days after May 6, 2002, perform the C.I.C. application on the MLG in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003. Thereafter, repeat at intervals not to exceed 180 days until the terminating action required by paragraph (q) of this AD has been accomplished.
(1) MLG outer cylinders that are less than 3 years old since new.
(2) MLGs that have been overhauled less than 3 years before May 6, 2002.
(3) MLGs on which rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000, was accomplished less than 3 years before May 6, 2002.
(k) Before the MLG outer cylinder is 3 years old since new, since last overhaul, or since rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000; or within 90 days after May 6, 2002; whichever is later; perform a detailed inspection for cracks and corrosion of the cross bolt bushing holes and chamfers in accordance with “Part 1—Cross Bolt Hole Inspection—Bushings Removed” of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003.
Note 2: For the purposes of this AD, a detailed inspection is defined as: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.”
(1) If no crack or corrosion is found during the detailed inspection required by paragraph (k) of this AD, perform the actions in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD, at the applicable times indicated.
(i) Before further flight, perform the restoration steps shown in Figure 2 of the service bulletin; and thereafter at intervals not to exceed 180 days, perform the C.I.C. application on the landing gear in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of the service bulletin.
(ii) Within 18 months after performing the detailed inspection required by paragraph (k) of this AD, and thereafter at intervals not to exceed 18 months, perform the detailed inspection for cracks and corrosion of the cross bolt hole inner chamfer, in accordance with “Part 2—Cross Bolt Hole Inner Chamfer Inspection—Bushings Not Removed” of the Accomplishment Instructions of the service bulletin, until the terminating action required by paragraph (q) of this AD has been accomplished.
(iii) Before the MLG cylinder is 6 1/2 years old since new, since last overhaul, or since rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000; whichever is later; perform the terminating action described in paragraph (q) of this AD.
(2) If any corrosion is found on the cross bolt holes or outer chamfers during the detailed inspection required by paragraph (k) of this AD, before further flight, remove the corrosion per Figure 2 of the service bulletin.
(i) If all of the corrosion can be removed: Before further flight, perform the restoration steps shown in Figure 2 of the service bulletin; thereafter at intervals not to exceed 180 days, perform the C.I.C. application on the MLG in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of the service bulletin; and perform the terminating action described in paragraph (q) of this AD, at the applicable time specified in paragraph (k)(2)(i)(A) or (k)(2)(i)(B) of this AD.
(A) If the MLG outer cylinder is less than 5 years old since new, if the MLG was last overhauled less than 5 years before May 6, 2002, or if rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000; was accomplished less than 5 years before May 6, 2002: Within 18 months after performing the detailed inspection required by paragraph (k) of this AD.
(B) If the MLG outer cylinder is 5 years old or more since new, if the MLG was last overhauled 5 years or more before May 6, 2002, or if rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000; was accomplished 5 years or more before May 6, 2002: Before the MLG outer cylinder is 6 1/2 years old since new, since last overhaul, or since rework per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated October 10, 1996; or Revision 2, dated November 30, 2000; whichever is later.
(ii) If any corrosion cannot be removed, before further flight, perform the terminating action described in paragraph (q) of this AD.
(3) If any crack is found anywhere during the detailed inspection required in paragraph (k) of this AD, or if corrosion in the inner cross bolt hole chamfers is found, before further flight, perform the terminating action described in paragraph (q) of this AD.
(l) For Category 2 MLG outer cylinders as identified in Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001: If, according to the criteria of paragraph (g) of this AD, JC5A may have been used, perform the actions specified in both paragraphs (m) and (n) of this AD, as applicable, in accordance with Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003.
(m) For MLGs and MLG outer cylinders identified in paragraphs (m)(1) and (m)(2) of this AD: Within 90 days after May 6, 2002, perform the C.I.C. application on the MLG in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003. Thereafter, repeat the application at intervals not to exceed 180 days until the terminating action required by paragraph (q) of this AD has been accomplished.
(1) MLG outer cylinders that are less than 3 years old since new.
(2) MLGs that have been overhauled less than 3 years before May 6, 2002.
(n) Before the MLG outer cylinder is 3 years old since new or since the last overhaul, or within 90 days after May 6, 2002, whichever is later, perform a detailed inspection for cracks and corrosion of the cross bolt hole inner chamfer, in accordance with “Part 2—Cross Bolt Hole Inner Chamfer Inspection—Bushings Not Removed” of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003.
(1) If no crack or corrosion is found during the inspection required by paragraph (n) of this AD, before further flight, and thereafter at intervals not to exceed 180 days, perform the C.I.C. application on the MLG in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of the service bulletin, until the next MLG overhaul. After the next MLG overhaul has been completed, no further action is required by this AD.
(2) If any corrosion is found during the detailed inspection required by paragraph (n) of this AD, before further flight, remove the cross bolt bushings and perform the detailed inspection specified in paragraph (k) of this AD, and remove the corrosion per Figure 2 of the service bulletin.
(i) If all of the corrosion can be removed, perform the actions specified in paragraph (n)(2)(i)(A) and (n)(2)(i)(B) of this AD, at the applicable times indicated.
(A) Prior to further flight, perform the restoration steps shown in Figure 2 of the service bulletin; and thereafter at intervals not to exceed 180 days, perform the C.I.C. application on the MLG in accordance with “Part 3—C.I.C. Application” of the Accomplishment Instructions of the service bulletin.
(B) Within 18 months after the corrosion removal required by paragraph (n)(2) of this AD, perform the terminating action described in paragraph (q) of this AD.
(ii) If all the corrosion cannot be removed, before further flight, perform the terminating action required by paragraph (q) of this AD.
(3) If any crack is found during the detailed inspection required by paragraph (n) of this AD, before further flight, perform the terminating action described in paragraph (q) of this AD.
As of May 6, 2002, no person shall install on any airplane an MLG outer cylinder unless maintenance records conclusively show that JC5A has never been used on that MLG outer cylinder, or unless it complies with paragraph (q) of this AD.
As of May 6, 2002, no person shall use the C.I.C. JC5A in the aft trunnion area of the MLG outer cylinder on any airplane.
Perform the terminating action (including removal of the existing bushings, repair of the aft trunnion area of the outer cylinder, and machining and installation of new bushings) in accordance with “Part 4—Terminating Action” of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March 13, 2003. Completion of the terminating action terminates the requirements for the repetitive inspections and C.I.C. applications of this AD.
For all airplanes, accomplishment of the actions specified in paragraph (q) of this AD is considered acceptable for compliance with the requirements of paragraph (e) of AD 2002-01-13, amendment 39-12607.
For airplanes with L/Ns 834 through 874 inclusive: Do the actions specified in paragraphs (s)(1), (s)(2), and (s)(3) of this AD.
(1) Within 90 days after the effective date of this AD, and thereafter at intervals not to exceed 180 days: Do the actions specified in paragraph (m) of this AD until the terminating action required by paragraph (q) of this AD has been accomplished.
(2) Before the MLG outer cylinder is 3 years old since new or since last overhaul, or within 90 days after the effective date of this AD, whichever is later: Do the actions as specified in paragraph (n) of this AD.
(3) As of the effective date of this AD, the actions specified in paragraphs (o) and (p) of this AD must be complied with.
Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include such a requirement.
