Airworthiness Directive · Amendment 39-17575 · Wings
the Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 767-200, 767-300, 767-300F, and 767-400ER series airplanes; certificated in any category; as identified in Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013.
(2) Installation of Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/ $FILE/ST01920SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of cracked and corroded nuts on an outboard flap support rib. This AD requires, for certain airplanes, repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, and related investigative and corrective actions if necessary. For certain other airplanes, this AD also requires repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, related investigative and corrective actions if necessary, and if necessary, a detailed inspection to determine the nut type installed in the outboard flap support rib and corrective actions. This AD also provides terminating action for the repetitive inspections under certain conditions. We are issuing this AD to detect and correct cracked and corroded nuts and bolts and the installation of incorrect nuts on certain outboard flap support ribs, which could lead to additional nut and bolt damage in the joint, result in loss of an outboard flap, and adversely affect continued safe flight and landing of the airplane.
For Group 1 airplanes, as specified in Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Except as required by paragraph (j) of this AD, at the time specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of the cap seal for damaged sealant on the nuts common to outboard flap support rib numbers 1, 2, 7, and 8, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all applicable related investigative and corrective actions before further flight, except as specified in paragraphs (g)(1)(ii) and (g)(2)(ii) of this AD.
(1) If, during any detailed inspection of the cap seal required by paragraph (g) of this AD, no damaged sealant is found on any support rib, do the actions specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that support rib thereafter at the intervals specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, until all fasteners are replaced within that support rib as required by paragraph (g)(1)(ii) of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace all fasteners within the support rib, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013.
(2) If, during any related investigative action required by paragraph (g) of this AD, no cracking and no corrosion is found on the nut, bolt, and washers of any support rib, do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that support rib thereafter at the intervals specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, until all fasteners are replaced within that support rib as required by paragraph (g)(2)(ii) of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time specified in table 1 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Replace all fasteners within the support rib, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013.
For Group 2 and 3 airplanes, as specified in Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Except as required by paragraph (j) of this AD, at the time specified in table 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, do a detailed inspection of the cap seal for damaged sealant on the nuts common to outboard flap support rib numbers 1, 2, 7, and 8, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all applicable related investigative and corrective actions before further flight.
(1) If, during any detailed inspection of the cap seal required by paragraph (h) of this AD, no damaged sealant is found on any support rib, do the actions specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that support rib thereafter at the intervals specified in table 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, until the actions required by paragraph (h)(1)(ii) of this AD are done or until all fasteners are replaced within that support rib as specified in paragraph (i) of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time specified in table 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a detailed inspection to determine the nut type installed in the outboard flap support rib and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all applicable corrective actions before further flight.
(2) If, during any related investigative action required by paragraph (h) of this AD, no cracking and no corrosion is found on the nut, bolt, and washers of any support rib, do the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that support rib thereafter at the intervals specified in table 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, until the actions required by paragraph (h)(2)(ii) of this AD are done or until all fasteners are replaced within that support rib as specified in paragraph (i) of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time specified in table 2 of paragraph 1.E., “Compliance,” of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013: Do a detailed inspection to determine the nut type installed in the outboard flap support rib and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013. Do all applicable corrective actions before further flight.
(1) If cracking is found during any inspection required by paragraph (g) or (h) of this AD: Replacing all the fasteners within the outboard flap support rib number 1, 2, 7, or 8, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, terminates the inspections required by paragraph (g) or (h) of this AD for that support rib only.
(2) If a discrepancy other than cracking is found (e.g., corrosion) during any inspection required by paragraph (g) of this AD: Replacing all the fasteners within the outboard flap support rib number 1, 2, 7, or 8, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, terminates the inspections required by paragraph (g) of this AD for that support rib only.
(3) If a discrepancy other than cracking is found (e.g., corrosion) during any inspection required by paragraph (h) of this AD: Replacing the affected fastener terminates the repetitive inspections for only that fastener within that support rib.
Where Boeing Service Bulletin 767-57A0131, Revision 1, dated May 8, 2013, specifies a compliance time relative to the issue date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
