Airworthiness Directive · Amendment 39-18215 · Wings
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company airplanes, certificated in any category, identified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD.
(i) Model 767-200, -300, and -300F series airplanes, as specified in Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012.
(ii) Model 767-400ER series airplanes, as specified in Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012.
(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 superseding Airworthiness Directive (AD) 2003-13-01 for certain The Boeing Company Model 767 airplanes. AD 2003-13-01 required an inspection to detect cracks and fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, and follow-on and corrective actions if necessary. For certain airplanes, AD 2003-13-01 required an inspection to determine if a tool runout option has been performed in the area. This new AD reduces certain compliance times, adds airplanes to the applicability, and provides optional terminating action for certain inspections. This AD was prompted by reports of hinge assembly fractures found before certain required compliance times in AD 2003-13-01. We are issuing this AD to prevent the inboard aft flap from separating from the wing and potentially striking the airplane, which could result in damage to the surrounding structure and potential personal injury.
This paragraph restates the requirements of paragraph (a) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with revised service information. Perform either a detailed inspection, or a detailed inspection plus an eddy current inspection, of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap to detect cracks and fractures and evidence of a tool runout option, as applicable. For the purposes of this AD, a detailed inspection is defined as an intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.
(1) For Model 767-200, -300, and -300F series airplanes identified in Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001: Inspect before the airplane accumulates 2,700 total flight cycles, or within 90 days after July 29, 2003 (the effective date of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003)), whichever occurs later, in accordance with Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012. As of the effective date of this AD, only Boeing Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012, may be used for the inspection.
(2) For Model 767-400ER series airplanes identified in Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002: Inspect before the airplane accumulates 12,000 total flight cycles, except as required by paragraph (m) of this AD, in accordance with Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; or the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012. As of the effective date of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012, may be used for the inspection.
This paragraph restates the requirements of paragraph (b) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with revised service information. Following the initial inspections required by paragraph (g) of this AD, perform applicable follow-on and corrective actions at the times specified in Figure 1 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001 (for Model 767-200, -300, and -300F series airplanes); or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002 (for Model 767-400ER series airplanes); until the initial inspection required by paragraph (n) of this AD is accomplished, and repeat thereafter at the applicable times specified in paragraph (n) of this AD. Do the follow-on and corrective actions (including repetitive inspections and replacement of the fittings with new fittings) in accordance with Part 1 or Part 2 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; or in accordance with the Accomplishment Instructions of the service information identified in paragraph (h)(1) or (h)(2) of this AD; except as required by paragraph (i)(2) of this AD. For Model 767-200, -300, and -300F series airplanes: If the fitting has the tool runout, and no cracking or fracture is found during the inspection, this AD requires no further action for that hinge fitting. As of the effective date of this AD, for the actions required by this paragraph, only the service information identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, may be used.
(1) Boeing Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012 (for Model 767-200, -300, and -300F series airplanes).
(2) Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012 (for Model 767-400ER series airplanes).
This paragraph restates the requirements of paragraphs (c) and (d) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), without the reporting requirement and with revised service information. The following exceptions specified in paragraphs (i)(1) and (i)(2) of this AD apply.
(1) Where the terminating action in Part 3 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001, and Revision 3, dated April 4, 2012; and Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002, and Revision 2, dated March 23, 2012; as applicable; is specified as corrective action, this AD requires that the terminating action, if required, be accomplished before further flight.
(2) Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; and Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012; specify to contact Boeing before the terminating action is done as corrective action for any cracking or fracture found on a Model 767-200, -300, or -300F series airplane with the tool runout. However, this AD requires that any such crack or fracture on those airplanes be repaired in accordance with Part 3 of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012. This AD does not require a report.
This paragraph restates the provisions of paragraph (f) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). Unless required to do so by paragraph (h) of this AD, operators may choose to accomplish the terminating action (including replacement of the fittings with new fittings, and reinstallation of existing upper skin access panels and fairing midsections on the trailing edge of the main flap) in accordance with Part 3 of the Work Instructions of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 2002; as applicable; or do the terminating actions specified in paragraph (o) of this AD. As of the effective date of this AD, use only the terminating action specified in paragraph (o) of this AD. Accomplishment of the terminating action terminates the repetitive inspection requirements of paragraph (h) of this AD.
As of the effective date of this AD, no person may install on any airplane identified in paragraph (c) of this AD, a hinge fitting assembly that has part number (P/N) 113T2271-13, 113T2271-14, 113T2271-23, 113T2271-24, 113T2271-29, 113T2271-30, 113T2271-33, 113T2271-34, 113T2271-401, or 113T2271-402, unless the applicable requirements of this AD have been accomplished for that fitting.
This paragraph restates the provisions of paragraph (g) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with revised credit provisions. This paragraph provides credit for actions required by paragraphs (g)(1), (h), and (j) of this AD, if those actions were performed before July 29, 2003 (the effective date of AD 2003-13-01), using Boeing Alert Service Bulletin 767-57A0076, dated October 26, 2000, which is not incorporated by reference in this AD.
For Model 767-400ER airplanes identified in Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012, on which the inspection required in paragraph (g) of this AD has not been done as of the effective date of this AD: Before the accumulation of 6,000 total flight cycles, or within 750 flight cycles after the effective date of this AD, whichever occurs later, perform either a detailed inspection or a detailed inspection plus an eddy current inspection to detect cracks or fractures of the outboard hinge fitting assemblies on the trailing edge of the inboard main flap, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012. Accomplishment of this inspection terminates the inspection requirement of paragraph (g)(2) of this AD. If any cracking or fracture is found, before further flight, replace the fittings in accordance with Part 3 of the Work Instructions of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012.
Repeat the inspection specified in paragraph (h) or (m) of this AD, as applicable, at intervals not to exceed the time specified in paragraph (n)(1) or (n)(2) of this AD, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012 (for Model 767-200, -300, and -300F series airplanes); or Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012 (for Model 767-400ER series airplanes); until the actions specified in paragraph (o) of this AD are done.
(1) If the most recent inspection was a detailed inspection: Do the next inspection within 300 flight cycles after doing the detailed inspection, and continue to repeat the inspection(s) thereafter at the time specified in paragraph (n) of this AD.
(2) If the most recent inspections were a detailed inspection and an eddy current inspection: Do the next inspections at the applicable time specified in paragraph (n)(2)(i) or (n)(2)(ii) of this AD, and continue to repeat the inspection(s) thereafter at the time specified in paragraph (n) of this AD.
(i) For Model 767-200, -300, and -300F series airplanes: Do the next inspection at the applicable time specified in paragraph (n)(2)(i)(A) or (n)(2)(i)(B) of this AD.
(A) If the detailed inspection and eddy current inspection were done before the effective date of this AD: Do the next inspection within 1,500 flight cycles after doing the detailed and eddy current inspections.
(B) If the detailed inspection and eddy current inspection were done on or after the effective date of this AD: Do the next inspection within 750 flight cycles after doing the detailed and eddy current inspection.
(ii) For Model 767-400ER series airplanes: Do the next inspection within 750 flight cycles after doing the detailed inspection and eddy current inspection.
Replacement of the inboard main flap outboard hinge fittings in accordance with step 4 of Part 3 of the Work Instructions of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012 (for Model 767-400ER series airplanes); or step 4 of Part 3 of the Work Instructions of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-57A0076, Revision 3, dated April 4, 2012 (for Model 767-200, -300, and -300F series airplanes); terminates the repetitive inspections required by paragraphs (h) and (n) 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
