Airworthiness Directives; The Boeing Company Airplanes, 43940-43944 [2015-17978]

Download as PDF 43940 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations the FAA amends 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 adding the following new airworthiness directive (AD): ■ AD 2015–15–08 Bombardier, Inc.: Amendment 39–18217. Docket No. FAA–2015–0088; Directorate Identifier 2014–NM–179–AD. (a) Effective Date This AD becomes effective August 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes, equipped with a spoiler electronic control unit (SECU) having part number (P/N) C47330–006, C47330–007, or C47330–008; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by testing of the spoiler electronic control unit (SECU) software for an upgrade, which revealed a timing error between the command and monitor channels. We are issuing this AD to prevent a timing error in the SECU software, which, in combination with failure of the roll disconnect switch, could result in complete loss of spoiler functionality and consequent reduced controllability of the airplane. rmajette on DSK2VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revision of the Maintenance or Inspection Program Within 600 flight hours since the most recent operational test of the aileron disconnect system for spoiler functionality as of the effective date of this AD, or within 400 flight hours after the effective date of this AD, whichever occurs first: Revise the maintenance or inspection program, as applicable, to incorporate repetitive operational tests of the aileron disconnect system for spoiler functionality, and all applicable corrective actions, using a method approved by the Manager, New York ACO, ANE–170, FAA. Note 1 to paragraph (g) of this AD: Guidance on operational tests of the aileron disconnect system can be found in the Bombardier Inc., BD–100–1A10 Time Limits/ Maintenance Checks (TLMC) Manual. VerDate Sep<11>2014 14:07 Jul 23, 2015 Jkt 235001 (h) Modification of the SECU Within 1,600 flight hours or 48 months after the effective date of this AD, whichever occurs first: Modify and re-identify the SECU, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–27–16, dated October 31, 2013. Doing the actions required by this paragraph terminates the actions required by paragraph (g) of this AD. (i) Parts Installation Prohibition As of the effective date of this AD, no person may install an SECU, P/N C47330– 006, C47330–007, or C47330–008, on any airplane. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–24, dated August 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2015–0088–0002. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 100–27–16, dated October 31, 2013. (ii) Reserved. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 855–7401; email thd.crj@ aero.bombardier.com; Internet https:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on July 15, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–17937 Filed 7–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–1052; Directorate Identifier 2014–NM–140–AD; Amendment 39–18210; AD 2015–15–01] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2004–13– 02, which applied to certain The Boeing Company Model 747–100, –200B, and –200F series airplanes. AD 2004–13–02 required repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This new AD adds post-repair inspections for cracking and corrosion, and repair if necessary; structural modification at the lap joints; and post-modification inspections for cracking and corrosion, and repair if necessary. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the longitudinal lap joints are subject to widespread fatigue damage (WFD). The actions mandated by this AD are necessary to reach the limit of validity (LOV). We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. SUMMARY: E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations This AD is effective August 28, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 28, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 1052. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 1052; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: Bill.Ashforth@faa.gov. SUPPLEMENTARY INFORMATION: rmajette on DSK2VPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004). AD 2004–13–02 applied to certain The Boeing Company Model 747–100, –200B, and –200F series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3506). The NPRM was prompted by an evaluation by the DAH that indicates the longitudinal lap joints are subject to WFD. A structural modification at the lap joint, and post- VerDate Sep<11>2014 14:07 Jul 23, 2015 Jkt 235001 modification repetitive inspections of the skin, existing internal doubler, or splice strap for cracks, and corrective actions if necessary, are necessary to reach the limit of validity (LOV). The NPRM proposed to continue to require repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary; and to add postrepair inspections for cracking and corrosion, and repair if necessary; structural modification at the lap joints; and post-modification inspections for cracking and corrosion, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 3506, January 23, 2015) and the FAA’s response to each comment. Support for the NPRM (80 FR 3506, January 23, 2015) Boeing stated that it concurs with the content of the proposed rule (80 FR 3506, January 23, 2015). Request To Increase Inspection Frequency for Certain Airplanes An anonymous commenter expressed an opinion that there may be more reason to check airplanes that are frequently pressurized to a greater than 2.0 per-square-inch (psi) range than those that are not pressurized to that extent. The commenter also asked if there should be a weighted system that requires inspections sooner if an airplane has proportionally more flight cycles in the greater-than-, rather than the less-than, 2.0-psi differentials. We do not agree with the commenter’s request for different inspection intervals based on pressurization ranges. The proposed inspection intervals were based on airplanes flying in a normal condition, which included full pressurization. In the past, if an operator had documentation substantiating flight cycles of less than 2.0 psi, some of the inspection requirements could be reduced. This reduced inspection requirement was relieving in nature and occurred roughly 10 years ago. We have since determined that fleet findings did not support this relief and have disallowed reduced inspection requirements in future ADs. We have not provided this relief in this AD. We PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 43941 have not changed this final rule in this regard. Request To Increase WFD Rule Applicability An anonymous commenter requested a reason why the WFD regulation applies only to Boeing and not to any other airplane manufacturer. The commenter stated that it seems like this type of WFD would be present in more than just Boeing airplanes, and yet the regulation and requirement for inspection seems to single out Boeing. The commenter suggested that it would make sense to consolidate and apply these requirements equally over all the types of airplanes. We do not agree with the commenter’s request. On May 24, 2012, we made effective Amendment 26–6 of 14 CFR 26.21, ‘‘Limit of Validity,’’ of the Federal Aviation Regulations (14 CFR 26.21). This regulation required all design approval holders (DAHs) to develop an LOV for affected airplanes, which affected several manufacturers and models (not exclusively Boeing). The LOV is established by means of engineering data that support the structural maintenance program that corresponds to the period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that WFD will not occur in the airplane. We have not changed this final rule in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 3506, January 23, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 3506, January 23, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014. The service information describes procedures for inspections and repairs of cracks and corrosion in the skin at lap joints in the fuselage. This service information is reasonably available because the E:\FR\FM\24JYR1.SGM 24JYR1 43942 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate the following costs to comply with this AD: We estimate that this AD affects 2 airplanes of U.S. registry. ESTIMATED COSTS Parts cost Action Labor cost Inspections [actions retained from AD 2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004)]. Modification [new action] ............................. 5,628 work-hours × $85 per hour = $478,380 per inspection cycle. Up to 3,764 work-hours × $85 per hour = $319,940. Up to 3,764 work-hours × $85 per hour = $319,940 per inspection cycle. Post-modification/post-repair [new action]. inspections We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. rmajette on DSK2VPTVN1PROD with RULES 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under 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, VerDate Sep<11>2014 14:07 Jul 23, 2015 Jkt 235001 Cost per product Cost on U.S. operators $0 $478,380 per inspection cycle. $956,760 per inspection cycle. $0 Up to $319,940 ........ Up to $639,880. $0 Up to $319,940 per inspection cycle. Up to $639,880 per inspection cycle. Adoption of the Amendment (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) that indicates the longitudinal lap joints are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking in the upper and lower skins of the fuselage lap joints, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (f) Compliance Comply with this AD within the compliance times specified, unless already done. PART 39—AIRWORTHINESS DIRECTIVES (g) Inspections for Corrosion, and Corrective Actions For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014: Except as provided by paragraph (l)(3) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, do an external low frequency eddy current inspection for corrosion at the upper row of fasteners in the lap joint, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection at the upper row of fasteners in the lap joint thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(3) of this AD. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. 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. 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) 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004), and adding the following new AD: ■ 2015–15–01 The Boeing Company: Amendment 39–18210; Docket No. FAA–2014–1052; Directorate Identifier 2014–NM–140–AD. (a) Effective Date This AD is effective August 28, 2015. (b) Affected ADs This AD replaces AD 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004). (c) Applicability This AD applies to The Boeing Company Model 747–100, –200B, and –200F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 (h) Inspections for Cracking, and Corrective Actions For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin E:\FR\FM\24JYR1.SGM 24JYR1 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 747–53A2463, Revision 2, dated June 16, 2014: Except as provided by paragraph (l)(3) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, do an internal medium frequency eddy current inspection for skin cracks at the lower row of fasteners in the lap joint, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection at the lower row of fasteners in the lap joint thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(3) of this AD. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. rmajette on DSK2VPTVN1PROD with RULES (i) Structural Modification For airplanes identified as Groups 2 through 14 in Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do a structural modification at the lap joints, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Accomplishment of the structural modification required by this paragraph terminates the inspections required by paragraphs (g), (h), and (k) of this AD in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (j) Post-Modification Inspections and Corrective Actions For airplanes on which the actions required by paragraph (i) of this AD have been done: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do an internal high frequency eddy current (HFEC) inspection for cracks of the skin or existing internal doublers, and an open-hole HFEC inspection for splice strap cracks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in VerDate Sep<11>2014 14:07 Jul 23, 2015 Jkt 235001 paragraph (n) of this AD. Repeat the inspections of the skin, internal doublers, and splice straps thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014. (k) Post-Repair Inspections and Corrective Actions For airplanes with any new or existing external doubler repair accomplished at a lap joint and the repair doubler length is 40 inches or longer: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(2) of this AD, do an internal HFEC inspection for cracking or corrosion of the repairs, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of external doubler repairs accomplished at lap joints thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014. Accomplishment of a structural modification in accordance with Part 5 of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, except as provided by paragraph (l)(1) of this AD, terminates the inspection requirements of this paragraph in the area of the modification only. The actions required by paragraph (j) of this AD are still applicable in the area of the modification. (l) Exceptions (1) If, during any action required by this AD, Boeing Alert Service Bulletin 747– 53A2463, Revision 2, dated June 16, 2014, specifies to contact Boeing for an inspection or modification procedure, or repair instructions: Before further flight, do the inspection, or modification, or repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (2) Where Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2463, Revision 2, dated June 16, 2014, specifies a compliance time ‘‘after the Revision 2 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (3) For the compliance threshold and repetitive interval calculations for inspections required by paragraphs (g) and (h) of this AD, the provisions specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this AD apply regarding differential pressure. (i) For inspections done before the effective date of this AD: Flight cycles in which the cabin differential pressure was at 2.0 poundsper-square-inch (psi) or less need not be counted in the flight-cycle determination, provided that flight cycles with momentary spikes in cabin differential pressure above 2.0 psi were included as full pressure flight cycles. For this provision to apply, all cabin pressure records must have been maintained PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 43943 for each airplane. No fleet-averaging of cabin pressure is allowed. (ii) For inspections done on or after the effective date of this AD: All flight cycles must be counted, regardless of differential pressure. (m) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (m)(1) or (m)(2) of this AD. (1) Boeing Alert Service Bulletin 747– 53A2463, dated March 7, 2002, including Appendices A, B, and C, dated March 7, 2002, which was incorporated by reference in AD 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004). (2) Boeing Alert Service Bulletin 747– 53A2463, Revision 1, dated April 16, 2009, which is not incorporated by reference in this AD. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (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 manager of the ACO, send it to the attention of the person identified in paragraph (o)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (o) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: Bill.Ashforth@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference E:\FR\FM\24JYR1.SGM 24JYR1 43944 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 747– 53A2463, Revision 2, dated June 16, 2014. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on July 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. regulations to be abandoned under the blanket certificate regulations, subject to those regulations’ requirements. DATES: This rule will become effective October 7, 2015. FOR FURTHER INFORMATION CONTACT: Katherine Liberty, Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, (202) 502– 6491, katherine.liberty@ferc.gov. Gordon Wagner, Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, (202) 502– 8947, gordon.wagner@ferc.gov. Howard Wheeler, Office of Energy Projects, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, (202) 502– 8688, howard.wheeler@ferc.gov. Shannon Jones, Office of Energy Projects, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, (202) 502– 6410, shannon.jones@ferc.gov. SUPPLEMENTARY INFORMATION: ORDER NO. 790–B Table of Contents Paragraph Nos. [FR Doc. 2015–17978 Filed 7–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Parts 2 and 157 [Docket No. RM12–11–003; Order No. 790– B] Revisions to Auxiliary Installations, Replacement Facilities, and Siting and Maintenance Regulations Federal Energy Regulatory Commission. ACTION: Final rule, order on clarification. AGENCY: The Federal Energy Regulatory Commission (Commission) is amending its regulations to: Provide pre-granted authority under a new paragraph to abandon or replace auxiliary facilities, subject to certain conditions; permit auxiliary facilities that cannot meet the conditions for the pre-granted abandonment authority in the new paragraph to be abandoned under the blanket certificate regulations, subject to those regulations’ requirements; and permit replacement facilities constructed under the rmajette on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:07 Jul 23, 2015 Jkt 235001 I. Discussion ............................. A. Section 2.55(a) Auxiliary Facilities ................ B. Section 2.55(b) Replacements .................... II. Information Collection Statement .............................. III. Environmental Analysis .... IV. Regulatory Flexibility Act V. Document Availability ....... VI. Effective Date and Congressional Notification ......... 4 9 14 18 23 24 26 29 Order No. 790–B Final Rule Order on Rehearing and Clarification 1. On November 20, 2014, the Federal Energy Regulatory Commission (Commission) issued Order No. 790–A,1 which affirmed, inter alia, the Commission’s clarification in Order No. 790 2 that auxiliary facilities installed under section 2.55(a) of the Commission’s regulations 3 may only utilize rights-of-way, facility sites, and 1 Revisions to Auxiliary Installations, Replacement Facilities, and Siting and Maintenance Regulations, Order No. 790–A, 79 FR 70056 (Nov. 25, 2014), FERC Stats. & Regs. ¶ 31,361 (2014) (cross-referenced at 149 FERC ¶ 61,144 (2014)). 2 Order No. 790, 78 FR 72794–801 (Dec. 4, 2013), FERC Stats. & Regs. ¶ 31,351 (2013) (crossreferenced at 145 FERC ¶ 61,154 (2013)). 3 18 CFR 2.55 (2014). PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 work spaces authorized for the construction and operation of interstate transmission facilities. 2. On December 22, 2014, National Fuel Gas Supply Corporation and Empire Pipeline, Inc. (collectively, National Fuel) filed a request that the Commission revise its part 157, subpart F, blanket certificate regulations to provide a mechanism under those regulations for the abandonment of auxiliary facilities that were constructed under section 2.55(a) and replacement facilities that were constructed under section 2.55(b). National Fuel also requests clarification that in addition to authorizing new auxiliary installations, section 2.55(a) also authorizes the replacement of existing auxiliary facilities without the need for abandonment authority under section 7(b) of the Natural Gas Act (NGA). 3. As discussed below, this order responds to National Fuel’s requests by (1) adopting a new subsection 2.55(a)(3) to provide pre-granted authority to abandon or replace auxiliary facilities, subject to certain conditions; (2) amending part 157 to provide authority, subject to the blanket certificate regulations’ conditions, to abandon section 2.55(a) auxiliary facilities that cannot meet the conditions for the pregranted abandonment authority being added to section 2.55(a) and to abandon section 2.55(b) replacement facilities. I. Discussion 4. In Order No. 790–A, the Commission explained that section 2.55 facilities are installed under the certificate authority that authorized the interstate transmission pipeline facilities being augmented or replaced. The Commission further explained that because section 2.55 auxiliary and replacement facilities are certificated facilities, a company needs prior authorization under NGA section 7(b) to abandon such facilities. The Commission stated that in many instances companies should be able to rely on their part 157, subpart F, blanket certificate authority to abandon section 2.55 facilities. In view of this statement, National Fuel believes it is the Commission’s intent that companies be able to rely on their part 157 blanket certificate authority to abandon facilities installed under section 2.55. 5. National Fuel points out, however, that section 157.202(b)(3) of the blanket certificate regulations states that a ‘‘facility’’ for purposes of the blanket program does not include a facility ‘‘described under section 2.55,’’ and that section 157.216 states that blanket certificate abandonment authority is limited to facilities that ‘‘did or could E:\FR\FM\24JYR1.SGM 24JYR1

Agencies

[Federal Register Volume 80, Number 142 (Friday, July 24, 2015)]
[Rules and Regulations]
[Pages 43940-43944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-17978]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1052; Directorate Identifier 2014-NM-140-AD; 
Amendment 39-18210; AD 2015-15-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2004-13-02, 
which applied to certain The Boeing Company Model 747-100, -200B, and -
200F series airplanes. AD 2004-13-02 required repetitive inspections to 
find discrepancies in the upper and lower skins of the fuselage lap 
joints, and repair if necessary. This new AD adds post-repair 
inspections for cracking and corrosion, and repair if necessary; 
structural modification at the lap joints; and post-modification 
inspections for cracking and corrosion, and repair if necessary. This 
AD was prompted by an evaluation by the design approval holder (DAH) 
that indicates the longitudinal lap joints are subject to widespread 
fatigue damage (WFD). The actions mandated by this AD are necessary to 
reach the limit of validity (LOV). We are issuing this AD to detect and 
correct fatigue cracking in the upper and lower skins of the fuselage 
lap joints, which could result in sudden fracture and failure of a lap 
joint and rapid in-flight decompression of the airplane fuselage.

[[Page 43941]]


DATES: This AD is effective August 28, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 28, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1052.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
1052; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: Bill.Ashforth@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2004-13-02, Amendment 39-13682 (69 FR 35237, 
June 24, 2004). AD 2004-13-02 applied to certain The Boeing Company 
Model 747-100, -200B, and -200F series airplanes. The NPRM published in 
the Federal Register on January 23, 2015 (80 FR 3506). The NPRM was 
prompted by an evaluation by the DAH that indicates the longitudinal 
lap joints are subject to WFD. A structural modification at the lap 
joint, and post-modification repetitive inspections of the skin, 
existing internal doubler, or splice strap for cracks, and corrective 
actions if necessary, are necessary to reach the limit of validity 
(LOV). The NPRM proposed to continue to require repetitive inspections 
to find discrepancies in the upper and lower skins of the fuselage lap 
joints, and repair if necessary; and to add post-repair inspections for 
cracking and corrosion, and repair if necessary; structural 
modification at the lap joints; and post-modification inspections for 
cracking and corrosion, and repair if necessary. We are issuing this AD 
to detect and correct fatigue cracking in the upper and lower skins of 
the fuselage lap joints, which could result in sudden fracture and 
failure of a lap joint and rapid in-flight decompression of the 
airplane fuselage.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 3506, January 23, 2015) and the FAA's response to each comment.

Support for the NPRM (80 FR 3506, January 23, 2015)

    Boeing stated that it concurs with the content of the proposed rule 
(80 FR 3506, January 23, 2015).

Request To Increase Inspection Frequency for Certain Airplanes

    An anonymous commenter expressed an opinion that there may be more 
reason to check airplanes that are frequently pressurized to a greater 
than 2.0 per-square-inch (psi) range than those that are not 
pressurized to that extent. The commenter also asked if there should be 
a weighted system that requires inspections sooner if an airplane has 
proportionally more flight cycles in the greater-than-, rather than the 
less-than, 2.0-psi differentials.
    We do not agree with the commenter's request for different 
inspection intervals based on pressurization ranges. The proposed 
inspection intervals were based on airplanes flying in a normal 
condition, which included full pressurization. In the past, if an 
operator had documentation substantiating flight cycles of less than 
2.0 psi, some of the inspection requirements could be reduced. This 
reduced inspection requirement was relieving in nature and occurred 
roughly 10 years ago. We have since determined that fleet findings did 
not support this relief and have disallowed reduced inspection 
requirements in future ADs. We have not provided this relief in this 
AD. We have not changed this final rule in this regard.

Request To Increase WFD Rule Applicability

    An anonymous commenter requested a reason why the WFD regulation 
applies only to Boeing and not to any other airplane manufacturer. The 
commenter stated that it seems like this type of WFD would be present 
in more than just Boeing airplanes, and yet the regulation and 
requirement for inspection seems to single out Boeing. The commenter 
suggested that it would make sense to consolidate and apply these 
requirements equally over all the types of airplanes.
    We do not agree with the commenter's request. On May 24, 2012, we 
made effective Amendment 26-6 of 14 CFR 26.21, ``Limit of Validity,'' 
of the Federal Aviation Regulations (14 CFR 26.21). This regulation 
required all design approval holders (DAHs) to develop an LOV for 
affected airplanes, which affected several manufacturers and models 
(not exclusively Boeing). The LOV is established by means of 
engineering data that support the structural maintenance program that 
corresponds to the period of time, stated as a number of total 
accumulated flight cycles or flight hours or both, during which it is 
demonstrated that WFD will not occur in the airplane. We have not 
changed this final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 3506, January 23, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 3506, January 23, 2015).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2463, Revision 2, 
dated June 16, 2014. The service information describes procedures for 
inspections and repairs of cracks and corrosion in the skin at lap 
joints in the fuselage. This service information is reasonably 
available because the

[[Page 43942]]

interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section of this 
AD.

Costs of Compliance

    We estimate that this AD affects 2 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                               Parts                             Cost on U.S.
              Action                       Labor cost           cost     Cost per product         operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained      5,628 work-hours x $85          $0  $478,380 per          $956,760 per
 from AD 2004[dash]13[dash]02,      per hour = $478,380 per             inspection cycle.     inspection cycle.
 Amendment 39[dash]13682 (69 FR     inspection cycle.
 35237, June 24, 2004)].
Modification [new action]........  Up to 3,764                     $0  Up to $319,940......  Up to $639,880.
                                    work[dash]hours x $85
                                    per hour = $319,940.
Post-modification/                 Up to 3,764                     $0  Up to $319,940 per    Up to $639,880 per
 post[dash]repair inspections       work[dash]hours x $85               inspection cycle.     inspection cycle.
 [new action].                      per hour = $319,940 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2004-13-02, Amendment 39-13682 (69 FR 35237, June 24, 2004), and adding 
the following new AD:

2015-15-01 The Boeing Company: Amendment 39-18210; Docket No. FAA-
2014-1052; Directorate Identifier 2014-NM-140-AD.

(a) Effective Date

    This AD is effective August 28, 2015.

(b) Affected ADs

    This AD replaces AD 2004-13-02, Amendment 39-13682 (69 FR 35237, 
June 24, 2004).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, -200B, and 
-200F series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 
16, 2014.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) that indicates the longitudinal lap joints are subject 
to widespread fatigue damage (WFD). We are issuing this AD to detect 
and correct fatigue cracking in the upper and lower skins of the 
fuselage lap joints, which could result in sudden fracture and 
failure of a lap joint and rapid in-flight decompression of the 
airplane fuselage.

(f) Compliance

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

(g) Inspections for Corrosion, and Corrective Actions

    For airplanes identified as Groups 2 through 14 in Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014: 
Except as provided by paragraph (l)(3) of this AD, at the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, do an 
external low frequency eddy current inspection for corrosion at the 
upper row of fasteners in the lap joint, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 
2, dated June 16, 2014, except as provided by paragraph (l)(1) of 
this AD. Do all applicable corrective actions before further flight. 
Repeat the inspection at the upper row of fasteners in the lap joint 
thereafter at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014, except as provided by paragraph 
(l)(3) of this AD. Accomplishment of a structural modification in 
accordance with Part 5 of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014, except as provided by paragraph 
(l)(1) of this AD, terminates the inspection requirements of this 
paragraph in the area of the modification only. The actions required 
by paragraph (j) of this AD are still applicable in the area of the 
modification.

(h) Inspections for Cracking, and Corrective Actions

    For airplanes identified as Groups 2 through 14 in Boeing Alert 
Service Bulletin

[[Page 43943]]

747-53A2463, Revision 2, dated June 16, 2014: Except as provided by 
paragraph (l)(3) of this AD, at the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2463, Revision 2, dated June 16, 2014, do an internal medium 
frequency eddy current inspection for skin cracks at the lower row 
of fasteners in the lap joint, and do all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 
16, 2014, except as provided by paragraph (l)(1) of this AD. Do all 
applicable corrective actions before further flight. Repeat the 
inspection at the lower row of fasteners in the lap joint thereafter 
at the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014, except as provided by paragraph 
(l)(3) of this AD. Accomplishment of a structural modification in 
accordance with Part 5 of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014, except as provided by paragraph 
(l)(1) of this AD, terminates the inspection requirements of this 
paragraph in the area of the modification only. The actions required 
by paragraph (j) of this AD are still applicable in the area of the 
modification.

(i) Structural Modification

    For airplanes identified as Groups 2 through 14 in Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014: At 
the applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated June 
16, 2014, except as provided by paragraph (l)(2) of this AD, do a 
structural modification at the lap joints, and all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2463, Revision 
2, dated June 16, 2014, except as provided by paragraph (l)(1) of 
this AD. Do all applicable corrective actions before further flight. 
Accomplishment of the structural modification required by this 
paragraph terminates the inspections required by paragraphs (g), 
(h), and (k) of this AD in the area of the modification only. The 
actions required by paragraph (j) of this AD are still applicable in 
the area of the modification.

(j) Post-Modification Inspections and Corrective Actions

    For airplanes on which the actions required by paragraph (i) of 
this AD have been done: At the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2463, Revision 2, dated June 16, 2014, except as provided by 
paragraph (l)(2) of this AD, do an internal high frequency eddy 
current (HFEC) inspection for cracks of the skin or existing 
internal doublers, and an open-hole HFEC inspection for splice strap 
cracks, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014. 
If any cracking is found, before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (n) of this AD. Repeat the inspections of the skin, 
internal doublers, and splice straps thereafter at the applicable 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014.

(k) Post-Repair Inspections and Corrective Actions

    For airplanes with any new or existing external doubler repair 
accomplished at a lap joint and the repair doubler length is 40 
inches or longer: At the applicable time specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014, except as provided by paragraph 
(l)(2) of this AD, do an internal HFEC inspection for cracking or 
corrosion of the repairs, and do all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, 
except as provided by paragraph (l)(1) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
external doubler repairs accomplished at lap joints thereafter at 
the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2463, 
Revision 2, dated June 16, 2014. Accomplishment of a structural 
modification in accordance with Part 5 of Boeing Alert Service 
Bulletin 747-53A2463, Revision 2, dated June 16, 2014, except as 
provided by paragraph (l)(1) of this AD, terminates the inspection 
requirements of this paragraph in the area of the modification only. 
The actions required by paragraph (j) of this AD are still 
applicable in the area of the modification.

(l) Exceptions

    (1) If, during any action required by this AD, Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, 
specifies to contact Boeing for an inspection or modification 
procedure, or repair instructions: Before further flight, do the 
inspection, or modification, or repair using a method approved in 
accordance with the procedures specified in paragraph (n) of this 
AD.
    (2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2463, Revision 2, dated June 16, 2014, 
specifies a compliance time ``after the Revision 2 date of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (3) For the compliance threshold and repetitive interval 
calculations for inspections required by paragraphs (g) and (h) of 
this AD, the provisions specified in paragraphs (l)(3)(i) and 
(l)(3)(ii) of this AD apply regarding differential pressure.
    (i) For inspections done before the effective date of this AD: 
Flight cycles in which the cabin differential pressure was at 2.0 
pounds-per-square-inch (psi) or less need not be counted in the 
flight-cycle determination, provided that flight cycles with 
momentary spikes in cabin differential pressure above 2.0 psi were 
included as full pressure flight cycles. For this provision to 
apply, all cabin pressure records must have been maintained for each 
airplane. No fleet-averaging of cabin pressure is allowed.
    (ii) For inspections done on or after the effective date of this 
AD: All flight cycles must be counted, regardless of differential 
pressure.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using the service information 
identified in paragraph (m)(1) or (m)(2) of this AD.
    (1) Boeing Alert Service Bulletin 747-53A2463, dated March 7, 
2002, including Appendices A, B, and C, dated March 7, 2002, which 
was incorporated by reference in AD 2004-13-02, Amendment 39-13682 
(69 FR 35237, June 24, 2004).
    (2) Boeing Alert Service Bulletin 747-53A2463, Revision 1, dated 
April 16, 2009, which is not incorporated by reference in this AD.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (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 manager of the ACO, send it to the 
attention of the person identified in paragraph (o)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@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 2004-13-02, Amendment 39-13682 (69 FR 
35237, June 24, 2004), are approved as AMOCs for the corresponding 
provisions of paragraphs (g) and (h) of this AD.

(o) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email: 
Bill.Ashforth@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3) and (p)(4) of this AD.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference

[[Page 43944]]

(IBR) of the service information listed in this paragraph under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-53A2463, Revision 2, dated 
June 16, 2014.
    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 10, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-17978 Filed 7-23-15; 8:45 am]
BILLING CODE 4910-13-P
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