Airworthiness Directive · Amendment 39-17292 · Fuselage
The Boeing Company Airplanes
This AD applies to all The Boeing Company Model 757-200, -200CB, and -300 series airplanes, certificated in any category. Model 757-200PF series airplanes are not affected by this AD.
We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. That AD currently requires initial and repetitive inspections of the fuselage skin and bear strap at the forward, upper corner of the L1 entry door cutout for cracking, and repair if necessary. That action also provides an optional terminating action for the repetitive inspections. That AD also requires additional inspections for airplanes having repairs or preventative modifications installed and inspections for certain other airplanes. This AD requires the previous actions with additional airplane group configurations added to paragraph (n) of this AD. This AD was prompted by a determination that certain airplane group configurations in paragraph (n) of the existing AD were inadvertently removed in the final rule. We are issuing this AD to detect and correct cracking of the fuselage skin and bear strap at the forward upper corner of the L1 entry door cutout, which could result in reduced structural integrity of the L1 entry door, and consequent rapid decompression of the airplane.
This paragraph restates the requirements of paragraph (g) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with a terminating action. For airplanes having line numbers 1 through 90 inclusive: Within 500 flight cycles after May 24, 2004 (the effective date of AD 2004-09-32, Amendment 39-13622 (69 FR 25481, May 7, 2004)), or within 90 days after May 24, 2004 (the effective date of AD 2004-09-32), whichever occurs later, do the inspections of the forward upper corner of the L1 entry door cutout specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, per Part 1 of the Work Instructions of Boeing Special Attention Service Bulletin 757-53-0089, dated March 18, 2004, until the initial inspection required by paragraph (k) of this AD has been done. Doing the repair specified in paragraph (i) or (l) of this AD, or doing the preventive modification specified in paragraph (j) of this AD, terminates the inspections required by this paragraph.
(1) Do a high frequency eddy current (HFEC) inspection for cracking of the fuselage skin around the adjacent fasteners.
(2) Do an HFEC inspection for cracking along the edge of the skin and bear strap.
(3) Do a low frequency eddy current (LFEC) inspection for cracking of the bear strap around each fastener.
This paragraph restates the requirements of paragraph (h) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with a terminating modification. If no crack is detected during any inspection required by paragraph (g) of this AD: Repeat the inspections required by paragraph (g) of this AD at intervals not to exceed 1,400 flight cycles, until the requirements of paragraph (k) of this AD are done. Doing the repair specified in paragraph (i) or (l) of this AD, or doing the preventive modification specified in paragraph (j) of this AD, as applicable, terminates the repetitive inspections required by this paragraph.
This paragraph restates the requirements of paragraph (i) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with a repair option. If any crack is detected during any inspection required by paragraph (g) or (h) of this AD, and Boeing Special Attention Service Bulletin 757-53-0089, dated March 18, 2004, specifies to contact Boeing for appropriate action: Before further flight, repair, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the type certification basis of the airplane approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make such findings; or using a method approved in accordance with the procedures specified in paragraph (r) of this AD. For a repair method to be approved, the approval must specifically reference this AD. Doing the repair terminates the inspections required by paragraphs (g) and (h) of this AD.
This paragraph restates the optional preventive modification specified in paragraph (j) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). As an alternative to accomplishing the inspections required by paragraphs (g) and (h) of this AD, do the optional preventative modification of the forward upper corner of the L1 entry door cutout, and do all applicable related investigative/corrective actions, by accomplishing all the actions specified in Part 2 of the Work Instructions of Boeing Special Attention Service Bulletin 757-53-0089, dated March 18, 2004. Accomplishment of the modification constitutes terminating action for the inspections required by paragraphs (g) and (h) of this AD.
This paragraph restates the requirements of paragraph (k) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). For airplanes in Group 1, Configurations 1 and 2, and Group 2, Configuration 1, as defined in Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009: Except as provided by paragraph (p)(1) of this AD, at the applicable times specified in paragraph 1.E, “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, do HFEC and LFEC inspections for cracking of the skin and bear strap at the forward upper corner of the L1 entry door cutout, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, except as provided by paragraph (p) of this AD. Repeat the inspections thereafter at intervals not to exceed 1,400 flight cycles. Doing the initial inspection required by this paragraph terminates the inspections required by paragraphs (g) and (h) of this AD. Doing the repair specified in paragraph (l) of this AD, or doing the optional preventive modification specified in paragraph (m) of this AD, terminates the inspections required by this paragraph.
This paragraph restates the terminating repair specified in paragraph (l) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). If any cracking is found during any inspection required by paragraph (k) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, except as required by paragraph (p) of this AD. Doing the repair terminates the repetitive inspections required by paragraph (k) of this AD.
This paragraph restates the optional preventive modification specified in paragraph (m) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). Accomplishing the optional preventive modification, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, except as provided by paragraph (p) of this AD, terminates the repetitive inspections required by paragraph (k) of this AD.
This paragraph restates the requirements of paragraph (n) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012), with new airplane group configurations. For airplanes in Group 1, Configurations 3, 4, and 5; and Group 2, Configurations 2, 3, and 4; as identified in Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009; with a repair doubler; a doubler and a tripler; or a doubler, tripler, and quadrupler installed; or with a preventive modification doubler installed: At the applicable times specified in paragraph 1.E, “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, except as required by paragraph (p)(2) of this AD, do LFEC, HFEC, and detailed inspections, as applicable, for cracking of the doubler, tripler, quadrupler, skin, bear strap, and inner chord strap, as applicable, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009.
This paragraph restates the requirements of paragraph (o) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). If any cracking is found during any inspection required by paragraph (n) of this AD, before further flight, repair the crack in accordance with the procedures specified in paragraph (r) of this AD.
This paragraph restates the exceptions specified in paragraph (p) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). The following exceptions apply to this AD.
(1) Where Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, specifies a compliance time after the “original issue date” or “Revision 1 date of the service bulletin,” this AD requires compliance within the specified compliance time after October 3, 2012 (the effective date of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012)).
(2) Where Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, specifies doing the HFEC, LFEC, and detailed inspections required by paragraph (n) of this AD before the accumulation of 37,500 total flight cycles, this AD requires the inspections to be accomplished at the latest of the times specified in paragraphs (p)(2)(i), (p)(2)(ii), and (p)(2)(iii) of this AD.
(i) Before the accumulation of 37,500 total flight cycles.
(ii) Within 24 months after October 3, 2012 (the effective date of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012)).
(iii) Within 4,000 flight cycles since installation of a repair doubler; a doubler and a tripler; or a doubler, tripler, and quadrupler; or on which a preventive modification doubler is installed; in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009; or in accordance with paragraph (h) of this AD.
(3) Where Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, specifies contacting Boeing for repair instructions, this AD requires repairing in accordance with the procedures specified in paragraph (r) of this AD.
(4) Where Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, specifies a specific fastener and material to be used for accomplishing a repair, this AD allows the substitution of fastener and material, as specified in Chapter 51 of the Boeing 757 Structural Repair Manual.
(5) Where Boeing Special Attention Service Bulletin 757-53-0094, Revision 1, dated August 12, 2009, specifies a specific fastener grip length, this AD allows substitution of a fastener grip length, as specified in Chapter 51 of the Boeing 757 Structural Repair Manual.
(6) If it is necessary to remove more parts for access, those parts may be removed. If access is possible without removing identified parts, it is not necessary to remove all of the identified parts.
This paragraph restates the credit provisions specified in paragraph (q) of AD 2012-15-15, Amendment 39-17144 (77 FR 52212, August 29, 2012). For airplanes in Group 1, Configurations 1 and 2; and Group 2, Configuration 1; as defined in Boeing Special Attention 757-53-0094, Revision 1, dated August 12, 2009: This paragraph provides credit for the actions required by paragraph (k) of this AD, if those actions were performed before October 3, 2012 (the effective date of AD 2012-15-15), using Boeing Special Attention Service Bulletin 757-53-0094, dated January 16, 2008; or Boeing Special Attention Service Bulletin 757-53-0089, dated March 18, 2004 (which are not incorporated by reference in 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
