Airworthiness Directives; The Boeing Company Airplanes, 81890-81894 [2011-33355]

Download as PDF 81890 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules PART 39—AIRWORTHINESS DIRECTIVES Authority for This Rulemaking Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. wreier-aviles on DSK3TPTVN1PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 15:07 Dec 28, 2011 Jkt 226001 Other FAA AD Provisions (j) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM–116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Authority: 49 U.S.C. 106(g), 40113, 44701. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. VerDate Mar<15>2010 modifications required by paragraph (g) of this AD. 1. The authority citation for part 39 continues to read as follows: than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $88,120, or $11,015 per product. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Saab AB, Saab Aerosystems: Docket No. FAA–2011–1410; Directorate Identifier 2011– NM–033–AD. Comments Due Date (a) We must receive comments by February 13, 2012. Affected ADs (b) None. Applicability (c) This AD applies to Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, all serial numbers; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 29: Hydraulic Power. Reason (e) This AD was prompted by reports of hydraulic accumulator failure. We are issuing this AD to prevent failure of hydraulic accumulators, which may result in damage to the airplane and injury to occupants. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Within 12 months after the effective date of this AD, replace all hydraulic accumulators having part number (P/N) 08 8423 030 1, with stainless steel hydraulic accumulators having P/N 40800–2050, and do the structural modifications in the nose landing gear bay, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–29–024, Revision 01, dated November 5, 2010. Parts Installation (h) After replacement of hydraulic accumulators having P/N 08 8423 030 1 with hydraulic accumulators having P/N 40800– 2050, and doing the structural modifications in the nose landing gear bay, as required by paragraph (g) of this AD, no person may install any hydraulic accumulator having P/ N 08 8423 030 1 on any airplane. Credit for Actions Accomplished in Accordance With Previous Service Information (i) Replacing the hydraulic accumulators and doing the structural modifications in the nose landing gear bay, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–29–024, dated November 18, 2009, before the effective date of this AD, is acceptable for compliance with the corresponding replacement and structural PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Related Information (k) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011– 0004, dated January 17, 2011; and Saab Service Bulletin 2000–29–024, Revision 01, dated November 5, 2010; for related information. Issued in Renton, Washington, on December 19, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–33275 Filed 12–28–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1326; Directorate Identifier 2010–NM–177–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\29DEP1.SGM 29DEP1 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules We propose to supersede an existing airworthiness directive (AD) that applies to The Boeing Company Model 757–200, –200CB, and –300 series airplanes. The existing 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. Since we issued that AD, we have received reports of additional cracking in the fuselage skin. This proposed AD would add inspections for airplanes having repairs or preventative modifications installed and supplemental inspections for certain airplanes. This proposed AD also would add airplanes to the applicability. We are proposing 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. DATES: We must receive comments on this proposed AD by February 13, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227– 1221. wreier-aviles on DSK3TPTVN1PROD with PROPOSALS SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through VerDate Mar<15>2010 15:07 Dec 28, 2011 Jkt 226001 Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6440; fax: (425) 917–6590; email: nancy.marsh@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–1326; Directorate Identifier 2010–NM–177–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On April 28, 2004, we issued AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004), for certain Model 757–200 series airplanes. That AD 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 AD also provides an optional terminating action for the repetitive inspections. That AD resulted from reports of cracking in the fuselage skin and bear strap at the forward, upper corner of the L1 entry door cutout. We issued that 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. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 81891 Actions Since Existing AD Was Issued Since we issued AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004), we have received reports of additional cracking in the fuselage skin. We also have determined that all Model 757–200, –200CB, and –300 series airplanes may be subject to the unsafe condition, and that the existing actions may not adequately address the unsafe condition. Relevant Service Information We reviewed Boeing Special Attention Service Bulletin 757–53– 0094, Revision 1, dated August 12, 2009. The service information describes procedures for the following repetitive inspections, depending on configuration: • High frequency eddy current (HFEC) and low frequency eddy current (LFEC) inspections for cracking of the skin and bear strap at the forward upper corner of the L1 entry door cutout. • Supplemental HFEC and LFEC inspections for cracking of the bear strap and inner chord strap on airplanes having a repair doubler, tripler, and quadrupler installed. • Supplemental HFEC, LFEC, and detailed inspections for cracking of the skin, bear strap, doubler, tripler, and quadrupler on airplanes having a repair doubler, tripler, and quadrupler installed. • Supplemental HFEC, LFEC, and detailed inspections for cracking of the skin, bear strap, inner chord strap, doubler, and tripler on airplanes having a repair doubler and tripler installed. • Supplemental HFEC, LFEC, and detailed inspections for cracking of the skin, bear strap, and doubler on airplanes having a preventive modification doubler installed. • Supplemental HFEC and LFEC inspections for cracking of the bear strap and inner chord strap on airplanes having a doubler installed. That service bulletin also provides procedures for corrective actions, which include repairing certain cracks, and contacting Boeing for certain other repair instructions. The compliance times for the initial inspections are either before 22,000 total flight cycles or within 500 flight cycles after the issue date on Boeing Special Attention Service Bulletin 757–53– 0094, dated January 16, 2008, whichever occurs later; or within 12,000 flight cycles after the modification, or within 500 flight cycles after the issue date on Boeing Special Attention Service Bulletin 757–53–0094, Revision 1, dated August 12, 2009, whichever occurs later; depending on configuration. The E:\FR\FM\29DEP1.SGM 29DEP1 81892 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules repetitive inspection interval for these inspections is 1,400 flight cycles. The compliance times for the initial supplemental inspections are 37,500 total flight cycles (for inspection of the skin, bear strap, doubler, and tripler), or 50,000 total flight cycles (for inspection of the bear strap and inner chord strap). The repetitive inspection interval for these inspections is either 4,000 flight cycles or 12,000 flight cycles, depending on configuration. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements necessary. This proposed AD also would add airplanes to the applicability of the existing AD. Exceptions to Certain Compliance Times The service bulletin specifies to do certain HFEC, LFEC, and detailed inspections before the accumulation of 37,500 total flight cycles. However, in order to address airplanes that might have already exceeded that threshold, this proposed AD would require the inspections to be accomplished at the latest of the times below: • Before the accumulation of 37,500 total flight cycles. • Within 4,000 flight cycles since installation of the modification. • Within 24 months after the effective date of this AD. Changes to Existing AD This proposed AD would retain all requirements of AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004). This proposed AD would add inspections for airplanes having repairs or preventative modifications installed, and supplemental inspections for certain airplanes; and repair, if This proposed AD would retain all requirements of AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004). Since AD 2004–09–32 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Corresponding requirement in this proposed AD Requirement in AD 2004–09–32 paragraph paragraph paragraph paragraph (a) (b) (c) (d) paragraph (g) paragraph (h) paragraph (i) paragraph (j) Boeing Commercial Airplanes has received an Organization Designation Authorization (ODA). We have revised paragraph (i) of this proposed AD to delegate the authority to approve an alternative method of compliance for any repair required by this proposed AD to the Boeing Commercial Airplanes ODA rather than a Designated Engineering Representative (DER). Costs of Compliance We estimate that this proposed AD affects 591 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Average labor rate per hour Work-hours Inspections (retained actions from existing AD). Inspection (new proposed action). Supplemental inspection ....... Cost per airplane Number of U.S.-registered airplanes 2 $85 $170 per inspection cycle ..... 57 3 85 $255 per inspection cycle ..... 591 15 85 $1,275 per inspection cycle .. 591 We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspections. We have no way Fleet cost $9,690 per inspection cycle. $150,705 per inspection cycle. $753,525 per inspection cycle. of determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Repair ............................................ Up to 26 work-hours × $85 = Up to $2,210 18 work-hours × $85 = $1,530 Up to $2,661 ................................. Up to $4,871 depending on configuration. $2,868. Preventive modification .................. wreier-aviles on DSK3TPTVN1PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, VerDate Mar<15>2010 15:07 Dec 28, 2011 Jkt 226001 $1,338 ........................................... ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. E:\FR\FM\29DEP1.SGM 29DEP1 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004), and adding the following new AD: The Boeing Company: Docket No. FAA– 2011–1326; Directorate Identifier 2010– NM–177–AD. (a) Comments Due Date The FAA must receive comments on this AD action by February 13, 2012. (b) Affected ADs This AD supersedes AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004). wreier-aviles on DSK3TPTVN1PROD with PROPOSALS (c) Applicability This AD applies to all The Boeing Company Model 757–200, –200CB, and –300 series airplanes; certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53: Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracks in the fuselage skin and bear strap at the forward upper corner of the L1 entry door cutout. 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 VerDate Mar<15>2010 15:07 Dec 28, 2011 Jkt 226001 81893 door and consequent rapid decompression of the airplane. the repair terminates the inspections required by paragraphs (g) and (h) of this AD. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (j) Optional Preventive Modification 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. RESTATEMENT OF REQUIREMENTS OF AD 2004–09–32, AMENDMENT 39–13622 (69 FR 25481, MAY 7, 2004), WITH NEW TERMINATING ACTION (g) Initial Inspections 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, 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 inspection 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 of the bear strap. (h) No Crack Detected: Repetitive Inspections and New 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) are done. Doing the repair specified in paragraph (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. (i) Any Crack Detected: Repair, With New 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 a Boeing Company Organization Designation Authorization who 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 (q) of this AD. For a repair method to be approved, the approval must specifically reference this AD. Doing PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 New Requirements of This AD (k) Inspections For airplanes in Group 1, Configurations 1– 2, and Group 2, Configuration 1, as identified in Boeing Special Attention Service Bulletin 757–53–0094, Revision 1, dated August 12, 2009: 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. 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. (l) Repair 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)(3) of this AD. Doing the repair terminates the repetitive inspections required by paragraph (k) of this AD. (m) Optional Preventive Modification Accomplishment of 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, terminates the repetitive inspections required by paragraph (k) of this AD. (n) Supplemental Inspections and Repair For airplanes in Group 1, Configurations 3–5, and Group 2, Configurations 2–4 as identified in Boeing Special Attention Service Bulletin 757–53–0094, Revision 1, dated August 12, 2009; on which a repair doubler, tripler, or quadrupler is installed, or on which a preventive modification doubler E:\FR\FM\29DEP1.SGM 29DEP1 81894 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules is installed: At the applicable times 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. (o) Supplemental Repair 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 (q) of this AD. wreier-aviles on DSK3TPTVN1PROD with PROPOSALS (p) Exceptions to Service Bulletin Specifications 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 after the effective date of this AD. (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) and (p)(2)(ii) of this AD. (i) Before the accumulation of 37,500 total flight cycles. (ii) Within 24 months after the effective date 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 (q) of this AD. (q) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM– 120S, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917– 6440; fax: (425) 917–6432; email: nancy.marsh@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. VerDate Mar<15>2010 15:07 Dec 28, 2011 Jkt 226001 (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2004–09–32, Amendment 39–13622 (69 FR 25481, May 7, 2004), are approved as AMOCs for the corresponding actions in paragraphs (g), (h), and (i) of this AD. (r) Related Information (1) For more information about this AD, contact Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6440; fax: (425) 917–6432; email: nancy.marsh@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766– 5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227–1221. Issued in Renton, Washington, on December 16, 2011. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–33355 Filed 12–28–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1325; Directorate Identifier 2010–NM–250–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all EMBRAER Model ERJ 170 airplanes. The existing AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) to incorporate new SUMMARY: PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 structural inspection requirements. Since we issued that AD, during full scale fatigue testing, cracks were found in certain structural components of the airplane. Analysis of these cracks resulted in manufacturer modifications of the ALS of Embraer ERJ 170 Maintenance Review Board Report (MRBR), which include new inspections tasks, or modification of the current tasks and their respective thresholds and intervals. This proposed AD would revise the maintenance program to incorporate new or revised structural inspection requirements. We are proposing this AD to detect and correct fatigue cracking which could result in the loss of structural integrity of the airplane. We must receive comments on this proposed AD by February 13, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria ˜ Lima, 2170–Putim–12227–901 Sao Jose dos Campos–SP–BRASIL; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email: distrib@embraer.com.br; Internet: https:// www.flyembraer.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call (425) 227– 1221. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The E:\FR\FM\29DEP1.SGM 29DEP1

Agencies

[Federal Register Volume 76, Number 250 (Thursday, December 29, 2011)]
[Proposed Rules]
[Pages 81890-81894]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-33355]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1326; Directorate Identifier 2010-NM-177-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

[[Page 81891]]

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to The Boeing Company Model 757-200, -200CB, and -300 
series airplanes. The existing 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. Since we issued that AD, we have 
received reports of additional cracking in the fuselage skin. This 
proposed AD would add inspections for airplanes having repairs or 
preventative modifications installed and supplemental inspections for 
certain airplanes. This proposed AD also would add airplanes to the 
applicability. We are proposing 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.

DATES: We must receive comments on this proposed AD by February 13, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone (206) 544-
5000, extension 1; fax (206) 766-5680; email me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington. For information 
on the availability of this material at the FAA, call (425) 227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6440; fax: (425) 917-6590; email: nancy.marsh@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-1326; 
Directorate Identifier 2010-NM-177-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On April 28, 2004, we issued AD 2004-09-32, Amendment 39-13622 (69 
FR 25481, May 7, 2004), for certain Model 757-200 series airplanes. 
That AD 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 AD also provides an 
optional terminating action for the repetitive inspections. That AD 
resulted from reports of cracking in the fuselage skin and bear strap 
at the forward, upper corner of the L1 entry door cutout. We issued 
that 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-09-32, Amendment 39-13622 (69 FR 25481, May 
7, 2004), we have received reports of additional cracking in the 
fuselage skin. We also have determined that all Model 757-200, -200CB, 
and -300 series airplanes may be subject to the unsafe condition, and 
that the existing actions may not adequately address the unsafe 
condition.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 757-53-0094, 
Revision 1, dated August 12, 2009. The service information describes 
procedures for the following repetitive inspections, depending on 
configuration:
     High frequency eddy current (HFEC) and low frequency eddy 
current (LFEC) inspections for cracking of the skin and bear strap at 
the forward upper corner of the L1 entry door cutout.
     Supplemental HFEC and LFEC inspections for cracking of the 
bear strap and inner chord strap on airplanes having a repair doubler, 
tripler, and quadrupler installed.
     Supplemental HFEC, LFEC, and detailed inspections for 
cracking of the skin, bear strap, doubler, tripler, and quadrupler on 
airplanes having a repair doubler, tripler, and quadrupler installed.
     Supplemental HFEC, LFEC, and detailed inspections for 
cracking of the skin, bear strap, inner chord strap, doubler, and 
tripler on airplanes having a repair doubler and tripler installed.
     Supplemental HFEC, LFEC, and detailed inspections for 
cracking of the skin, bear strap, and doubler on airplanes having a 
preventive modification doubler installed.
     Supplemental HFEC and LFEC inspections for cracking of the 
bear strap and inner chord strap on airplanes having a doubler 
installed.
    That service bulletin also provides procedures for corrective 
actions, which include repairing certain cracks, and contacting Boeing 
for certain other repair instructions.
    The compliance times for the initial inspections are either before 
22,000 total flight cycles or within 500 flight cycles after the issue 
date on Boeing Special Attention Service Bulletin 757-53-0094, dated 
January 16, 2008, whichever occurs later; or within 12,000 flight 
cycles after the modification, or within 500 flight cycles after the 
issue date on Boeing Special Attention Service Bulletin 757-53-0094, 
Revision 1, dated August 12, 2009, whichever occurs later; depending on 
configuration. The

[[Page 81892]]

repetitive inspection interval for these inspections is 1,400 flight 
cycles.
    The compliance times for the initial supplemental inspections are 
37,500 total flight cycles (for inspection of the skin, bear strap, 
doubler, and tripler), or 50,000 total flight cycles (for inspection of 
the bear strap and inner chord strap). The repetitive inspection 
interval for these inspections is either 4,000 flight cycles or 12,000 
flight cycles, depending on configuration.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2004-09-32, 
Amendment 39-13622 (69 FR 25481, May 7, 2004). This proposed AD would 
add inspections for airplanes having repairs or preventative 
modifications installed, and supplemental inspections for certain 
airplanes; and repair, if necessary. This proposed AD also would add 
airplanes to the applicability of the existing AD.

Exceptions to Certain Compliance Times

    The service bulletin specifies to do certain HFEC, LFEC, and 
detailed inspections before the accumulation of 37,500 total flight 
cycles. However, in order to address airplanes that might have already 
exceeded that threshold, this proposed AD would require the inspections 
to be accomplished at the latest of the times below:
     Before the accumulation of 37,500 total flight cycles.
     Within 4,000 flight cycles since installation of the 
modification.
     Within 24 months after the effective date of this AD.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 2004-09-32, 
Amendment 39-13622 (69 FR 25481, May 7, 2004). Since AD 2004-09-32 was 
issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                      Corresponding requirement in this
    Requirement in AD 2004-09-32                 proposed AD
------------------------------------------------------------------------
             paragraph (a)                        paragraph (g)
             paragraph (b)                        paragraph (h)
             paragraph (c)                        paragraph (i)
             paragraph (d)                        paragraph (j)
------------------------------------------------------------------------

    Boeing Commercial Airplanes has received an Organization 
Designation Authorization (ODA). We have revised paragraph (i) of this 
proposed AD to delegate the authority to approve an alternative method 
of compliance for any repair required by this proposed AD to the Boeing 
Commercial Airplanes ODA rather than a Designated Engineering 
Representative (DER).

Costs of Compliance

    We estimate that this proposed AD affects 591 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
            Action               Work-hours     Average labor      Cost per        registered       Fleet cost
                                                rate per hour      airplane         airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (retained actions               2             $85  $170 per                      57  $9,690 per
 from existing AD).                                             inspection                        inspection
                                                                cycle.                            cycle.
Inspection (new proposed                    3              85  $255 per                     591  $150,705 per
 action).                                                       inspection                        inspection
                                                                cycle.                            cycle.
Supplemental inspection......              15              85  $1,275 per                   591  $753,525 per
                                                                inspection                        inspection
                                                                cycle.                            cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspections. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair...............................  Up to 26 work-hours x    Up to $2,661...........  Up to $4,871 depending
                                        $85 = Up to $2,210                                on configuration.
Preventive modification..............  18 work-hours x $85 =    $1,338.................  $2,868.
                                        $1,530
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.

[[Page 81893]]

    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing airworthiness directive 
(AD) 2004-09-32, Amendment 39-13622 (69 FR 25481, May 7, 2004), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2011-1326; Directorate Identifier 
2010-NM-177-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 13, 
2012.

(b) Affected ADs

    This AD supersedes AD 2004-09-32, Amendment 39-13622 (69 FR 
25481, May 7, 2004).

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200CB, 
and -300 series airplanes; certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53: Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracks in the fuselage skin 
and bear strap at the forward upper corner of the L1 entry door 
cutout. 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.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

RESTATEMENT OF REQUIREMENTS OF AD 2004-09-32, AMENDMENT 39-13622 (69 FR 
25481, MAY 7, 2004), WITH NEW TERMINATING ACTION

(g) Initial Inspections

    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, 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 inspection 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 of the 
bear strap.

(h) No Crack Detected: Repetitive Inspections and New 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) are done. Doing the 
repair specified in paragraph (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.

(i) Any Crack Detected: Repair, With New 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 a 
Boeing Company Organization Designation Authorization who 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 (q) 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.

(j) Optional Preventive Modification

    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.

New Requirements of This AD

(k) Inspections

    For airplanes in Group 1, Configurations 1-2, and Group 2, 
Configuration 1, as identified in Boeing Special Attention Service 
Bulletin 757-53-0094, Revision 1, dated August 12, 2009: 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. 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.

(l) Repair

    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)(3) of this AD. Doing the 
repair terminates the repetitive inspections required by paragraph 
(k) of this AD.

(m) Optional Preventive Modification

    Accomplishment of 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, terminates the repetitive inspections required by paragraph 
(k) of this AD.

(n) Supplemental Inspections and Repair

    For airplanes in Group 1, Configurations 3-5, and Group 2, 
Configurations 2-4 as identified in Boeing Special Attention Service 
Bulletin 757-53-0094, Revision 1, dated August 12, 2009; on which a 
repair doubler, tripler, or quadrupler is installed, or on which a 
preventive modification doubler

[[Page 81894]]

is installed: At the applicable times 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.

(o) Supplemental Repair

    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 (q) of this 
AD.

(p) Exceptions to Service Bulletin Specifications

    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 after the effective date of 
this AD.
    (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) and (p)(2)(ii) of this AD.
    (i) Before the accumulation of 37,500 total flight cycles.
    (ii) Within 24 months after the effective date 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 (q) of this AD.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the ACO, send it to 
ATTN: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 
(425) 917-6440; fax: (425) 917-6432; email: nancy.marsh@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2004-09-32, Amendment 39-13622 (69 FR 
25481, May 7, 2004), are approved as AMOCs for the corresponding 
actions in paragraphs (g), (h), and (i) of this AD.

(r) Related Information

    (1) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 1601 Lind Avenue 
SW., Renton, Washington 98057-3356; phone: (425) 917-6440; fax: 
(425) 917-6432; email: nancy.marsh@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
(206) 544-5000, extension 1; fax (206) 766-5680; email 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call (425) 227-1221.

    Issued in Renton, Washington, on December 16, 2011.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-33355 Filed 12-28-11; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.