Airworthiness Directives; the Boeing Company Airplanes, 64164-64167 [2013-24042]

Download as PDF 64164 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 15, 2011; or Airbus Service Bulletin A320– 35–1058, dated June 15, 2011; as applicable; are excluded from the requirements of paragraph (g) of this AD, unless an oxygen container with a part number listed in paragraph (g)(1)(i) of this AD and a serial number listed in paragraph (g)(1)(ii) of this AD is installed. Note 1 to paragraph (g) of this AD: The oxygen container assemblies listed in paragraph (g)(1)(i) of this AD and paragraph (g)(1)(ii) of this AD are B/E Aerospace products with the mark ‘‘B/E AEROSPACE’’ on the identification plate. wreier-aviles on DSK5TPTVN1PROD with RULES (h) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an oxygen container with a part number listed in paragraph (g)(1)(i) of this AD, and serial number listed in paragraph (g)(1)(ii) of this AD, unless the oxygen container has been modified according to Airbus Service Bulletin A320–35–1049, dated June 15, 2011; Airbus Service Bulletin A320–35–1053, dated June 15, 2011; Airbus Service Bulletin A320–35–1054, dated June 15, 2011; Airbus Service Bulletin A320–35–1055, dated June 15, 2011; Airbus Service Bulletin A320–35– 1056, dated June 15, 2011; Airbus Service Bulletin A320–35–1057, dated June 15, 2011; or Airbus Service Bulletin A320–35–1058, dated June 15, 2011; as applicable. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; fax (425) 227– 1149. Information may be emailed to: 9ANM-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 FAAapproved 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. (j) Related Information Refer to Mandatory Continuing Airworthiness Information European Aviation Safety Agency Airworthiness Directive 2012–0055, dated April 3, 2012, for VerDate Mar<15>2010 12:59 Oct 25, 2013 Jkt 232001 related information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-0465-0002. (k) 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) Airbus Service Bulletin A320–35–1049, dated June 15, 2011. (ii) Airbus Service Bulletin A320–35–1053, dated June 15, 2011. (iii) Airbus Service Bulletin A320–35– 1054, dated June 15, 2011. (iv) Airbus Service Bulletin A320–35– 1055, dated June 15, 2011. (v) Airbus Service Bulletin A320–35–1056, dated June 15, 2011. (vi) Airbus Service Bulletin A320–35– 1057, dated June 15, 2011. (vii) Airbus Service Bulletin A320–35– 1058, dated June 15, 2011. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may review copies of the 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 17, 2013. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–23909 Filed 10–25–13; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0303; Directorate Identifier 2012–NM–220–AD; Amendment 39–17620; AD 2013–20–14] RIN 2120–AA64 Airworthiness Directives; the Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: Frm 00012 Fmt 4700 Final rule. We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 747–400 and –400F series airplanes. This AD was prompted by a report of cracks on airplanes prior to line number 1308 in the forward and aft inner chords of the station (STA) 2598 bulkhead, and the bulkhead upper and lower webs. This AD requires, as applicable, repetitive high frequency eddy current (HFEC) and low frequency eddy current (LFEC) inspections for cracks in the splice fitting, support frame, forward and aft inner chords, floor support, bulkhead upper web on the upper left and right side of the bulkhead, and the bulkhead lower web on the lower left side of the bulkhead and repair if necessary; and repetitive post-repair inspections and repair if necessary. We are issuing this AD to detect and correct cracks in the splice fitting, support frame, floor support, forward and aft inner chords, and the bulkhead upper and lower webs of the STA 2598 bulkhead, which could adversely affect the structural integrity of the airplane. DATES:DATES: This AD is effective December 2, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 2, 2013. 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 review copies of the 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. SUMMARY: Examining the AD Docket DEPARTMENT OF TRANSPORTATION PO 00000 ACTION: Sfmt 4700 You may examine the AD docket on the Internet at http:// 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document 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. E:\FR\FM\28OCR1.SGM 28OCR1 64165 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. The NPRM published in the Federal Register on April 12, 2013 (78 FR 21854). The NPRM proposed to require, as applicable, repetitive HFEC and LFEC inspections for cracks in the splice fitting, support frame, forward and aft inner chords, floor support, bulkhead upper web on the upper left and right side of the bulkhead, and the bulkhead lower web on the lower left side of the bulkhead and repair if necessary; and repetitive post-repair inspections and repair if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (78 FR 21854, April 12, 2013) and the FAA’s response to each comment. Request To Include the Lower Web in the Inspection of the Unrepaired Structure Boeing requested that we revise paragraph (g) of the NPRM (78 FR 21854, April 12, 2013) to clarify that the inspection of the unrepaired structure includes the lower webs. Boeing stated that the inspections for the unrepaired structure include both the upper and lower bulkhead webs, but that paragraph (g)(2)(ii) of the NPRM (78 FR 21854, April 12, 2013) specifies only the upper web. We agree with Boeing’s comment. For appropriate service information, the NPRM (78 FR 21854, April 12, 2013) referred to Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012, which also describes procedures for inspecting the bulkhead lower web. We have clarified the inspection in paragraph (g)(2)(ii) of this AD by referring to Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012, for specific inspection procedures and locations. Request To Revise the Unsafe Condition Boeing requested that, for clarity, the unsafe condition be revised to more specifically identify the location of potential cracking (i.e., the body station 2598 bulkhead). We agree with Boeing’s request. We have revised the unsafe condition in the SUMMARY and paragraph (e) of this final rule to clarify the location of the bulkhead. Request To Clarify the Discussion Section Boeing requested clarification of the Discussion section in the NPRM (78 FR 21854, April 12, 2013). Boeing stated that the Discussion does not mention cracks found in the splice fitting and incorrectly refers to the ‘‘cutout for the horizontal stabilizer rear spar.’’ We agree that the commenter’s proposed clarification provides a more accurate description of the report of cracks. However, the Discussion section is not carried over into the final rule; therefore, no change to this final rule is necessary 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 with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 21854, April 12, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 21854, April 12, 2013). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 11 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspections ............................. 28 work-hours × $85 per hour = $2,380 per inspection cycle. $0 $2,380 per inspection cycle ... $26,180 per inspection cycle. We estimate the following costs to do any necessary repairs and post-repair inspections that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need this repair: ON-CONDITION COSTS wreier-aviles on DSK5TPTVN1PROD with RULES Action Labor cost Parts cost Repair ........................................................................... Post-repair Inspection ................................................... 13 work-hours × $85 per hour = $1,105 ...................... 12 work-hours × $85 per hour = $1,020 ...................... Cost per product $0 0 For any repairs that would be necessary based on the results of the post-repair inspection, we have not received definitive data that would enable us to VerDate Mar<15>2010 15:52 Oct 25, 2013 Jkt 232001 provide cost estimates for that oncondition action. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 $1,105 1,020 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, E:\FR\FM\28OCR1.SGM 28OCR1 64166 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 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 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 1. The authority citation for part 39 continues to read as follows: wreier-aviles on DSK5TPTVN1PROD with RULES ■ 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): ■ 2013–20–14 The Boeing Company: Amendment 39–17620; Docket No. VerDate Mar<15>2010 12:59 Oct 25, 2013 Jkt 232001 FAA–2013–0303; Directorate Identifier 2012–NM–220–AD. (a) Effective Date This AD is effective December 2, 2013. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–400 and –400F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracks on airplanes prior to line number 1308 in the forward and aft inner chords of the station (STA) 2598 bulkhead, and the bulkhead upper and lower webs. We are issuing this AD to detect and correct cracks in the splice fitting, support frame, floor support, forward and aft inner chords, and the bulkhead upper and lower webs of the STA 2598 bulkhead, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) Inspections At the compliance time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012; except as provided by paragraph (h)(2) of this AD: Do HFEC and LFEC inspections, as applicable, for cracks in the splice fitting, support frame, floor support, forward and aft inner chords, the bulkhead upper web on the upper left and right side of the bulkhead, and the bulkhead lower web on the lower left side of the bulkhead, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012. (1) If no cracking is found, repeat the applicable inspections specified in paragraph (g) of this AD, thereafter, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012. (2) If any cracking is found, do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Before further flight, do the applicable repair, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012; except as provided by paragraph (h)(1) of this AD. (ii) At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012, do HFEC and LFEC PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 inspections for cracks in the unrepaired structure, and do an HFEC inspection for cracks in the repaired structure; as specified in and in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012. (A) If no cracking is found, repeat the applicable HFEC and LFEC inspections specified in paragraph (g)(2)(ii) of this AD, thereafter, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012. (B) If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (h) Exceptions to the Service Information (1) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (2) Where Boeing Alert Service Bulletin 747–53A2815, dated November 8, 2012, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (i) 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 (j) 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. (j) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6428; fax: 425–917– 6590; email: Nathan.P.Weigand@faa.gov. E:\FR\FM\28OCR1.SGM 28OCR1 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations (k) 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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 747– 53A2815, dated November 8, 2012. (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 review copies of the 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. (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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on September 19, 2013. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–24042 Filed 10–25–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30923; Amdt. No. 3558] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: wreier-aviles on DSK5TPTVN1PROD with RULES VerDate Mar<15>2010 12:59 Oct 25, 2013 Jkt 232001 This rule is effective October 28, 2013. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 28, 2013. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: For Examination— 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; 2. The FAA Regional Office of the region in which the affected airport is located; 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. The National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/ federal_register/code_of_federal_ regulations/ibr_locations.html. Availability—All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit http:// www.nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from: 1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; or 2. The FAA Regional Office of the region in which the affected airport is located. DATES: FOR FURTHER INFORMATION CONTACT: This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic SUMMARY: requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. Richard A. Dunham III, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) Telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or revoking SIAPS, Takeoff Minimums PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 64167 and/or ODPS. The complete regulators description of each SIAP and its associated Takeoff Minimums or ODP for an identified airport is listed on FAA form documents which are incorporated by reference in this amendment under 5 U.S.C. 552(a), 1 CFR part 51, and 14 CFR 97.20. The applicable FAA Forms are FAA Forms 8260–3, 8260–4, 8260– 5, 8260–15A, and 8260–15B when required by an entry on 8260–15A. The large number of SIAPs, Takeoff Minimums and ODPs, in addition to their complex nature and the need for a special format make publication in the Federal Register expensive and impractical. Furthermore, airmen do not use the regulatory text of the SIAPs, Takeoff Minimums or ODPs, but instead refer to their depiction on charts printed by publishers of aeronautical materials. The advantages of incorporation by reference are realized and publication of the complete description of each SIAP, Takeoff Minimums and ODP listed on FAA forms is unnecessary. This amendment provides the affected CFR sections and specifies the types of SIAPs and the effective dates of the, associated Takeoff Minimums and ODPs. This amendment also identifies the airport and its location, the procedure, and the amendment number. The Rule This amendment to 14 CFR part 97 is effective upon publication of each separate SIAP, Takeoff Minimums and ODP as contained in the transmittal. Some SIAP and Takeoff Minimums and textual ODP amendments may have been issued previously by the FAA in a Flight Data Center (FDC) Notice to Airmen (NOTAM) as an emergency action of immediate flight safety relating directly to published aeronautical charts. The circumstances which created the need for some SIAP and Takeoff Minimums and ODP amendments may require making them effective in less than 30 days. For the remaining SIAPS and Takeoff Minimums and ODPS, an effective date at least 30 days after publication is provided. Further, the SIAPs and Takeoff Minimums and ODPS contained in this amendment are based on the criteria contained in the U.S. Standard for Terminal Instrument Procedures (TERPS). In developing these SIAPS and Takeoff Minimums and ODPs, the TERPS criteria were applied to the conditions existing or anticipated at the affected airports. Because of the close and immediate relationship between these SIAPs, Takeoff Minimums and ODPs, and safety in air commerce, I find that notice and public procedures before E:\FR\FM\28OCR1.SGM 28OCR1

Agencies

[Federal Register Volume 78, Number 208 (Monday, October 28, 2013)]
[Rules and Regulations]
[Pages 64164-64167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24042]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0303; Directorate Identifier 2012-NM-220-AD; 
Amendment 39-17620; AD 2013-20-14]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
the Boeing Company Model 747-400 and -400F series airplanes. This AD 
was prompted by a report of cracks on airplanes prior to line number 
1308 in the forward and aft inner chords of the station (STA) 2598 
bulkhead, and the bulkhead upper and lower webs. This AD requires, as 
applicable, repetitive high frequency eddy current (HFEC) and low 
frequency eddy current (LFEC) inspections for cracks in the splice 
fitting, support frame, forward and aft inner chords, floor support, 
bulkhead upper web on the upper left and right side of the bulkhead, 
and the bulkhead lower web on the lower left side of the bulkhead and 
repair if necessary; and repetitive post-repair inspections and repair 
if necessary. We are issuing this AD to detect and correct cracks in 
the splice fitting, support frame, floor support, forward and aft inner 
chords, and the bulkhead upper and lower webs of the STA 2598 bulkhead, 
which could adversely affect the structural integrity of the airplane.

DATES:DATES: This AD is effective December 2, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 2, 
2013.

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 review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document 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.

[[Page 64165]]


FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: Nathan.P.Weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
The NPRM published in the Federal Register on April 12, 2013 (78 FR 
21854). The NPRM proposed to require, as applicable, repetitive HFEC 
and LFEC inspections for cracks in the splice fitting, support frame, 
forward and aft inner chords, floor support, bulkhead upper web on the 
upper left and right side of the bulkhead, and the bulkhead lower web 
on the lower left side of the bulkhead and repair if necessary; and 
repetitive post-repair inspections and repair if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 21854, April 12, 2013) and the FAA's response to each comment.

Request To Include the Lower Web in the Inspection of the Unrepaired 
Structure

    Boeing requested that we revise paragraph (g) of the NPRM (78 FR 
21854, April 12, 2013) to clarify that the inspection of the unrepaired 
structure includes the lower webs. Boeing stated that the inspections 
for the unrepaired structure include both the upper and lower bulkhead 
webs, but that paragraph (g)(2)(ii) of the NPRM (78 FR 21854, April 12, 
2013) specifies only the upper web.
    We agree with Boeing's comment. For appropriate service 
information, the NPRM (78 FR 21854, April 12, 2013) referred to Boeing 
Alert Service Bulletin 747-53A2815, dated November 8, 2012, which also 
describes procedures for inspecting the bulkhead lower web. We have 
clarified the inspection in paragraph (g)(2)(ii) of this AD by 
referring to Boeing Alert Service Bulletin 747-53A2815, dated November 
8, 2012, for specific inspection procedures and locations.

Request To Revise the Unsafe Condition

    Boeing requested that, for clarity, the unsafe condition be revised 
to more specifically identify the location of potential cracking (i.e., 
the body station 2598 bulkhead).
    We agree with Boeing's request. We have revised the unsafe 
condition in the SUMMARY and paragraph (e) of this final rule to 
clarify the location of the bulkhead.

Request To Clarify the Discussion Section

    Boeing requested clarification of the Discussion section in the 
NPRM (78 FR 21854, April 12, 2013). Boeing stated that the Discussion 
does not mention cracks found in the splice fitting and incorrectly 
refers to the ``cutout for the horizontal stabilizer rear spar.''
    We agree that the commenter's proposed clarification provides a 
more accurate description of the report of cracks. However, the 
Discussion section is not carried over into the final rule; therefore, 
no change to this final rule is necessary 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 with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 21854, April 12, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 21854, April 12, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 11 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections.....................  28 work-hours x $85              $0   $2,380 per           $26,180 per
                                   per hour = $2,380                     inspection cycle.    inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs and 
post-repair inspections that would be required based on the results of 
the inspection. We have no way of determining the number of aircraft 
that might need this repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair.......................................  13 work-hours x $85 per hour =                $0           $1,105
                                                $1,105.
Post-repair Inspection.......................  12 work-hours x $85 per hour =                 0            1,020
                                                $1,020.
----------------------------------------------------------------------------------------------------------------

For any repairs that would be necessary based on the results of the 
post-repair inspection, we have not received definitive data that would 
enable us to provide cost estimates for that on-condition action.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I,

[[Page 64166]]

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

    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 adding the following new airworthiness 
directive (AD):

2013-20-14 The Boeing Company: Amendment 39-17620; Docket No. FAA-
2013-0303; Directorate Identifier 2012-NM-220-AD.

(a) Effective Date

    This AD is effective December 2, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and -400F 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 747-53A2815, dated November 8, 2012.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of cracks on airplanes prior to 
line number 1308 in the forward and aft inner chords of the station 
(STA) 2598 bulkhead, and the bulkhead upper and lower webs. We are 
issuing this AD to detect and correct cracks in the splice fitting, 
support frame, floor support, forward and aft inner chords, and the 
bulkhead upper and lower webs of the STA 2598 bulkhead, which could 
adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current 
(LFEC) Inspections

    At the compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2815, dated 
November 8, 2012; except as provided by paragraph (h)(2) of this AD: 
Do HFEC and LFEC inspections, as applicable, for cracks in the 
splice fitting, support frame, floor support, forward and aft inner 
chords, the bulkhead upper web on the upper left and right side of 
the bulkhead, and the bulkhead lower web on the lower left side of 
the bulkhead, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2815, dated November 8, 2012.
    (1) If no cracking is found, repeat the applicable inspections 
specified in paragraph (g) of this AD, thereafter, at the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2815, dated November 8, 2012.
    (2) If any cracking is found, do the actions specified in 
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
    (i) Before further flight, do the applicable repair, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2815, dated November 8, 2012; except as 
provided by paragraph (h)(1) of this AD.
    (ii) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2815, dated 
November 8, 2012, do HFEC and LFEC inspections for cracks in the 
unrepaired structure, and do an HFEC inspection for cracks in the 
repaired structure; as specified in and in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2815, dated November 8, 2012.
    (A) If no cracking is found, repeat the applicable HFEC and LFEC 
inspections specified in paragraph (g)(2)(ii) of this AD, 
thereafter, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2815, dated 
November 8, 2012.
    (B) If any cracking is found, before further flight, repair 
using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD.

(h) Exceptions to the Service Information

    (1) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2815, dated November 8, 
2012, specifies to contact Boeing for appropriate action: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (i) of this 
AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2815, dated 
November 8, 2012, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

(i) 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 (j) 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.

(j) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
Nathan.P.Weigand@faa.gov.

[[Page 64167]]

(k) 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 the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-53A2815, dated November 8, 
2012.
    (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 review copies of the 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.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 19, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24042 Filed 10-25-13; 8:45 am]
BILLING CODE 4910-13-P