Airworthiness Directive · Amendment 39-13786 · Boeing Model 727, 727C, 727-100, -100C, and -200 Series Airplanes
Boeing Model 727, 727C, 727-100, -100C, and -200 Series Airplanes
Model 727, 727C, 727-100, -100C, and -200 series airplanes, line numbers 1 through 887 inclusive; certificated in any category.
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 727C, 727-100, -100C, and -200 series airplanes. This amendment requires an inspection of the forward trunnion attach fittings of the main landing gear (MLG), inspections of the attach fitting holes of the forward trunnion attach fittings if necessary, replacement of the forward trunnion attach fittings if necessary, and corrective actions if necessary. This action is necessary to detect and correct cracks and corrosion on the attach fitting holes of the forward trunnion attach fittings of the MLG, which could result in the collapse of the MLG. This action is intended to address the identified unsafe condition.
To detect and correct cracks and corrosion on the attach fitting holes of the forward trunnion attach fittings of the main landing gear (MLG), which could result in the collapse of the MLG, accomplish the following:
(a) The term “service bulletin,” as used in this AD, means Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003.
(b) Perform an inspection of the forward trunnion attach fittings of the MLG to determine the part number (P/N) of the attach fitting, in accordance with “Part 1” of the Accomplishment Instructions of the service bulletin, at the latest of the times specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD:
(1) Prior to airplanes reaching 240 months old since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness; or
(2) Within 18 months after the effective date of this AD; or
(3) Within 120 months after the last inspection/rework/repair of the attach fitting per Boeing Service Bulletin 727-57A0132, dated June 28, 1974, Revision 1, dated October 31, 1975, or Revision 2, dated April 24, 1981; or Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003.
(c) If, during the inspection required by paragraph (b) of this AD, both attach fittings are found to have P/N 65-19296-9, -10, -13, or -14; P/N 65-99909-1724 or -1727; P/N 65-19296U13 or P/N 65-19296U14 (attach fitting made of 7075-T73511 or 7050-T7451 aluminum); no further action is required by this paragraph.
(d) If, during the inspection required by paragraph (b) of this AD, any attach fitting is found to have P/N 65-19296-1 through -8 inclusive (attach fitting made of 7079-T6 aluminum): Before further flight, perform the actions in paragraphs (d)(1) and (d)(2) of this AD, as applicable.
(1) Do detailed and high frequency eddy current inspections of the attach fitting holes for cracks and corrosion, repair any crack or corrosion found, and rework the attach fitting holes, in accordance with Figures 4 and 5 of the service bulletin, except as provided by paragraph (d)(2) of this AD.
(2) If the attach fitting hole cannot be reworked or repaired in accordance with Figures 4 and 5 of the service bulletin: Before further flight, replace the attach fitting with a new attach fitting that has P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, P/N 65-19296U13, or P/N 65-19296U14, in accordance with paragraph 7 of “Part II” of the Accomplishment Instructions of the service bulletin. Accomplishment of this replacement is terminating action for that fitting.
(e) Within 120 months after the effective date of this AD, replace attach fittings that have P/N 65-19296-1 through -8 (attach fittings made of 7079-T6 aluminum) with new attach fittings that have P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, P/N 65-19296U13, or P/N 65-19296U14 (attach fittings made of 7075-T73511 or 7050-T7451 aluminum), in accordance with paragraph 7 of “Part II” of the Accomplishment Instructions of the service bulletin. Replacement of all attach fittings made of 7079-T6 aluminum with new attach fittings made of 7075-T73511 or 7050-T7451 aluminum terminates the requirements of paragraph (d) of this AD.
(f) As of the effective date of this AD, no person shall install, on any airplane, an attach fitting, P/N 65-19296-1, -2, -3, -4, -5, -6, -7, or -8 (attach fitting made of 7079-T6 aluminum), unless it has been inspected/reworked/repaired in accordance with paragraph (d) of this AD.
(g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD.
(2) An AMOC that provides an acceptable level of safety may be used for any rework/repair required by this AD, if it is approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a rework/repair method to be approved, the approval must specifically reference this AD.
