Airworthiness Directives; The Boeing Company Airplanes, 8516-8519 [2015-02689]

Download as PDF 8516 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations test to check for bonding between the re-fuel adaptor of the gravity fill and the top skin panels on the left-hand and right-hand wings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 57–1152, Revision 01, dated December 19, 2013. (1) If the resistance value is 10 milliohms or less at the left-hand and right-hand wing, no further action is required by this paragraph. (2) If the resistance value is greater than 10 milliohms at the left-hand or right-hand wing, before further flight, do a general visual inspection for corrosion of the component interface and adjacent area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1152, Revision 01, dated December 19, 2013. If any corrosion is found during the inspection, before further flight, repair the gravity fill fuel adaptor, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1152, Revision 01, dated December 19, 2013; except where Airbus Service Bulletin A320–57–1152, Revision 01, dated December 19, 2013, specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. mstockstill on DSK4VPTVN1PROD with RULES (h) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–57–1152, dated June 14, 2010, which was incorporated by reference in AD 2012–09–07, Amendment 39–17042 (77 FR 28238, May 14, 2012). (i) New Requirement of This AD: Maintenance Check/Electrical Bonding Test and Corrective Action if Necessary For airplanes other than those identified in paragraph (g) of this AD: Within 24 months after the effective date of this AD, determine whether a corrosion repair has been done on an overwing refueling aperture, whereby a primer coating has been applied on the mating surface of the aperture flange. A review of the airplane maintenance records is acceptable to make this determination, provided that whether a primer coat was applied can be conclusively determined from that review. (1) If it is determined that a primer coating was applied on the mating surface of the aperture flange; or if a determination cannot be made, or the outcome is inconclusive: Within 24 months after the effective date of this AD do the electrical bonding test specified in paragraph (g) of this AD, and before further flight, do all applicable actions specified in paragraph (g)(2) of this AD. (2) If it is determined that a corrosion repair has not been done, and a primer coating has not been applied on the mating surface of the aperture flange since first entry into service, no further action is required by this paragraph. VerDate Sep<11>2014 17:46 Feb 17, 2015 Jkt 235001 (j) Corrosion Repair Provision As of the effective date of this AD, any corrosion repair done on an overwing refueling aperture on any airplane must comply with the repair requirements of paragraph (g)(2) of this AD. (k) 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: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2012–09–07, Amendment 39–17042 (77 FR 28238, May 14, 2012), are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0277R1, dated December 4, 2013, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov/#!document Detail;D=FAA-2014-0484-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (m)(4) and (m)(5) of this AD. (m) 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 A320–57–1152, Revision 01, dated December 19, 2013. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (ii) Reserved. (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 https://www.airbus.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 February 4, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–02697 Filed 2–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0522; Directorate Identifier 2014–NM–087–AD; Amendment 39–18100; AD 2015–03–04] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. This AD requires repetitive inspections of the fuselage skin of the MED 1 cutout for cracking, and repair if necessary; and also provides an optional terminating modification, including post-repair or post-modification fuselage skin inspections for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. DATES: This AD is effective March 25, 2015. SUMMARY: E:\FR\FM\18FER1.SGM 18FER1 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 25, 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– 0522. 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– 0522; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on August 5, 2014 (79 FR 45385). The NPRM was prompted by reports of fuselage skin cracks at the lower forward corner of the MED 1 cutout. The NPRM proposed to require repetitive inspections of the fuselage VerDate Sep<11>2014 17:46 Feb 17, 2015 Jkt 235001 skin of the MED 1 cutout for cracking, and repair if necessary. The NPRM also provided optional terminating modification, including post-repair or post-modification inspections for cracking of the fuselage skin, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 45385, August 5, 2014) and the FAA’s response to each comment. Support for the NPRM (79 FR 45385, August 5, 2014) UPS stated that it agrees with the intent of the NPRM (79 FR 45385, August 5, 2014). Request To Withdraw the NPRM (79 FR 45385, August 5, 2014) Mr. Jerry Adams requested that we withdraw the NPRM (79 FR 45385, August 5, 2014). Mr. Adams stated that the manufacturer’s analysis and subsequent action referred to in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, should be sufficient. Mr. Adams stated that the cost of compliance does not include the increased cost of airframes that the customer must pay for, and that will subsequently be passed along to the traveling consumer. Mr. Adams asserted that this AD action would be counterproductive to business and the cost of transportation to the general public. We agree with the comment that the actions described in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, are sufficient to correct the identified unsafe condition. However, we do not agree with the commenter’s request to withdraw the NPRM (79 FR 45385, August 5, 2014). We have identified an unsafe condition that is likely to exist or develop in other products. Therefore, we must issue an airworthiness directive to correct the identified unsafe condition, as required by section 39.5 of the Federal Aviation Regulations (14 CFR 39.5). We accomplish this by mandating specified actions described in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, by AD action. We have not changed this AD in this regard. We also note that although the commenter stated that the cost of airframes was not included in the NPRM (79 FR 45385, August 5, 2014), PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 8517 this AD does not require replacing airframes. The costs of accomplishing the actions required by this AD, as specified in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014 (inspection, repair if necessary, and optional modification), are included in the Costs of Compliance section of this AD. Request To Revise the Description of the Location Where Cracking Was Identified Boeing requested that we revise the SUMMARY and Discussion sections of the preamble, and paragraphs (e), (g), and (i) in the proposed AD (79 FR 45385, August 5, 2014) to clarify that the cracking occurs in the fuselage skin, which would match the title of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. We agree with the commenter’s request because this change will help clarify the cracking location. We have revised this AD accordingly. Request To Revise Service Information and Cost Estimate UPS requested that we revise the service information used in this AD. UPS stated that the power panels and other equipment outboard of the main equipment center (MEC) must be removed in order to access the repair or modification area specified in the NPRM (79 FR 45385, August 5, 2014). UPS stated that these removals are currently not included in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, and will require significantly greater manpower than specified in the NPRM. We disagree with the commenter’s request. We have determined it is not appropriate to delay this AD to incorporate revised service information that might be published sometime in the future. Note 10, in the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, states: If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. Therefore, operators are already permitted to alter the way they gain access to the required areas for inspections/repairs/modifications specified in this AD. We have received no definitive data that would enable us to provide cost estimates for the MEC removal. We have not changed this AD in this regard. E:\FR\FM\18FER1.SGM 18FER1 8518 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 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 (79 FR 45385, August 5, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 45385, August 5, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. 2014. The service information describes procedures for inspection, repair, and modification at the lower forward corner of the fuselage main entry door 1. This service information is reasonably available; see ADDRESSES for ways to access this service information. Related Service Information Under 1 CFR Part 51 We estimate that this AD affects 165 airplanes of U.S. registry. We estimate the following costs to comply with this AD: We reviewed Boeing Alert Service Bulletin 747–53A2863, dated March 11, Costs of Compliance ESTIMATED COSTS Action Labor cost Inspection (per door) ............... 11 work-hours × $85 per hour = $935 per inspection cycle. Up to 66 work-hours × $85 per hour = $5,610. 11 work-hours × $85 per hour = $935 per inspection cycle. Optional modification (per door). Post-repair or -modification inspection (per door). We estimate the following costs to do any necessary repair that would be Parts cost Cost per product Cost on U.S. operators $0 $935 per inspection cycle ....... $154,275 per inspection cycle. 0 Up to $5,610 ........................... Up to $925,650. 0 $935 per inspection cycle ....... $154,275 per inspection cycle. required based on the results of the inspection. We have no way of determining the number of airplanes that might need this repair: ON-CONDITION COSTS Action Labor cost Parts cost Repair (per door) .............................. 66 work-hours × $85 per hour = $5,610. $7,380 or $9,360 .............................. Authority for This Rulemaking mstockstill on DSK4VPTVN1PROD with RULES 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. 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. Regulatory Findings Adoption of the Amendment 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 17:46 Feb 17, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Cost per product $12,990 or $14,970. 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): ■ 2015–03–04 The Boeing Company: Amendment 39–18100 ; Docket No. FAA–2014–0522; Directorate Identifier 2014–NM–087–AD. (a) Effective Date This AD is effective March 25, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. E:\FR\FM\18FER1.SGM 18FER1 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations (e) Unsafe Condition This AD was prompted by reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014: Do a detailed inspection and a surface high frequency eddy current inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Do all applicable corrective actions before further flight. Repeat the inspections of the applicable MED 1 cutout thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. Accomplishing the corrective actions required by this paragraph terminates the repetitive inspection requirements of this paragraph. (h) Optional Terminating Action For airplanes on which no crack is found during the initial inspections required by paragraph (g) of this AD: Installing the preventive modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, terminates the repetitive inspections required by paragraph (g) of this AD. mstockstill on DSK4VPTVN1PROD with RULES (i) Post-Repair or Post-Modification Repetitive Inspections and Corrective Actions For airplanes on which the corrective actions required by paragraph (g) of this AD have been done, or airplanes that have installed the preventive modification specified in paragraph (h) of this AD: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, do a detailed inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the fuselage skin at the applicable MED 1 cutout thereafter at the intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014. VerDate Sep<11>2014 17:46 Feb 17, 2015 Jkt 235001 8519 (j) Exceptions to Service Information (1) Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, 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. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2863, dated March 11, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. 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. (k) 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 (l)(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. DEPARTMENT OF COMMERCE (l) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425– 917–6590; email: Nathan.P.Weigand@faa.gov. (m) 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– 53A2863, dated March 11, 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 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on February 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–02689 Filed 2–17–15; 8:45 am] BILLING CODE 4910–13–P Bureau of Industry and Security 15 CFR Parts 730 and 744 [Docket No. 150123073–5073–01] RIN 0694–AG48 Updated Statements of Legal Authority for the Export Administration Regulations To Include Presidential Notice of January 21, 2015 Bureau of Industry and Security, Commerce. ACTION: Final rule. AGENCY: This rule updates the Code of Federal Regulations (CFR) legal authority paragraphs in the Export Administration Regulations (EAR) to cite a Presidential notice that extended an emergency declared pursuant to the International Emergency Economic Powers Act. This is a procedural rule that only updates authority paragraphs of the EAR. It does not alter any right, obligation or prohibition that applies to any person under the EAR. DATES: The rule is effective February 18, 2015. FOR FURTHER INFORMATION CONTACT: William Arvin, Regulatory Policy Division, Bureau of Industry and Security, Email william.arvin@ bis.doc.gov, Telephone: (202) 482–2440. SUPPLEMENTARY INFORMATION: SUMMARY: Background The authority for parts 730 and 744 of the EAR (15 CFR parts 730 and 744) rests, in part, on Executive Order 12947 of January 23, 1995—Prohibiting Transactions With Respect to Terrorists Who Threaten To Disrupt the Middle East Peace Process (60 FR 5079, 3 CFR, 1995 Comp., p. 356) and on annual notices by the President continuing the emergency declared in that order. This rule updates the authority paragraphs in 15 CFR parts 730 and 744 to cite the Notice of January 21, 2015, 80 FR 3461 (January 22, 2015), which is the most E:\FR\FM\18FER1.SGM 18FER1

Agencies

[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Rules and Regulations]
[Pages 8516-8519]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02689]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0522; Directorate Identifier 2014-NM-087-AD; 
Amendment 39-18100; AD 2015-03-04]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes. This AD was prompted by reports of fuselage 
skin cracks at the lower forward corner of the main entry door (MED) 1 
cutout. This AD requires repetitive inspections of the fuselage skin of 
the MED 1 cutout for cracking, and repair if necessary; and also 
provides an optional terminating modification, including post-repair or 
post-modification fuselage skin inspections for cracking, and 
corrective actions if necessary. We are issuing this AD to detect and 
correct skin cracking, which can become large and could adversely 
affect the structural integrity of the airplane.

DATES: This AD is effective March 25, 2015.

[[Page 8517]]

    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 25, 
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-
0522.

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-
0522; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), 
FAA, 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 by adding an AD that would apply to certain The Boeing Company 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 
747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series 
airplanes. The NPRM published in the Federal Register on August 5, 2014 
(79 FR 45385). The NPRM was prompted by reports of fuselage skin cracks 
at the lower forward corner of the MED 1 cutout. The NPRM proposed to 
require repetitive inspections of the fuselage skin of the MED 1 cutout 
for cracking, and repair if necessary. The NPRM also provided optional 
terminating modification, including post-repair or post-modification 
inspections for cracking of the fuselage skin, and corrective actions 
if necessary. We are issuing this AD to detect and correct skin 
cracking, which can become large and could adversely affect the 
structural integrity of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 45385, August 5, 2014) and the FAA's response to each comment.

Support for the NPRM (79 FR 45385, August 5, 2014)

    UPS stated that it agrees with the intent of the NPRM (79 FR 45385, 
August 5, 2014).

Request To Withdraw the NPRM (79 FR 45385, August 5, 2014)

    Mr. Jerry Adams requested that we withdraw the NPRM (79 FR 45385, 
August 5, 2014). Mr. Adams stated that the manufacturer's analysis and 
subsequent action referred to in Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014, should be sufficient. Mr. Adams stated 
that the cost of compliance does not include the increased cost of 
airframes that the customer must pay for, and that will subsequently be 
passed along to the traveling consumer. Mr. Adams asserted that this AD 
action would be counterproductive to business and the cost of 
transportation to the general public.
    We agree with the comment that the actions described in Boeing 
Alert Service Bulletin 747-53A2863, dated March 11, 2014, are 
sufficient to correct the identified unsafe condition. However, we do 
not agree with the commenter's request to withdraw the NPRM (79 FR 
45385, August 5, 2014). We have identified an unsafe condition that is 
likely to exist or develop in other products. Therefore, we must issue 
an airworthiness directive to correct the identified unsafe condition, 
as required by section 39.5 of the Federal Aviation Regulations (14 CFR 
39.5). We accomplish this by mandating specified actions described in 
Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, by AD 
action. We have not changed this AD in this regard.
    We also note that although the commenter stated that the cost of 
airframes was not included in the NPRM (79 FR 45385, August 5, 2014), 
this AD does not require replacing airframes. The costs of 
accomplishing the actions required by this AD, as specified in Boeing 
Alert Service Bulletin 747-53A2863, dated March 11, 2014 (inspection, 
repair if necessary, and optional modification), are included in the 
Costs of Compliance section of this AD.

Request To Revise the Description of the Location Where Cracking Was 
Identified

    Boeing requested that we revise the SUMMARY and Discussion sections 
of the preamble, and paragraphs (e), (g), and (i) in the proposed AD 
(79 FR 45385, August 5, 2014) to clarify that the cracking occurs in 
the fuselage skin, which would match the title of Boeing Alert Service 
Bulletin 747-53A2863, dated March 11, 2014.
    We agree with the commenter's request because this change will help 
clarify the cracking location. We have revised this AD accordingly.

Request To Revise Service Information and Cost Estimate

    UPS requested that we revise the service information used in this 
AD. UPS stated that the power panels and other equipment outboard of 
the main equipment center (MEC) must be removed in order to access the 
repair or modification area specified in the NPRM (79 FR 45385, August 
5, 2014). UPS stated that these removals are currently not included in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014, and will require significantly greater 
manpower than specified in the NPRM.
    We disagree with the commenter's request. We have determined it is 
not appropriate to delay this AD to incorporate revised service 
information that might be published sometime in the future. Note 10, in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014, states:

    If it is necessary to remove more parts for access, you can 
remove those parts. If you can get access without removing 
identified parts, it is not necessary to remove all of the 
identified parts. Jacking and shoring limitations must be observed.

    Therefore, operators are already permitted to alter the way they 
gain access to the required areas for inspections/repairs/modifications 
specified in this AD. We have received no definitive data that would 
enable us to provide cost estimates for the MEC removal. We have not 
changed this AD in this regard.

[[Page 8518]]

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 (79 FR 45385, August 5, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 45385, August 5, 2014).
    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 747-53A2863, dated March 
11, 2014. The service information describes procedures for inspection, 
repair, and modification at the lower forward corner of the fuselage 
main entry door 1. This service information is reasonably available; 
see ADDRESSES for ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 165 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
----------------------------------------------------------------------------------------------------------------
Inspection (per door)............  11 work-hours x $85            $0  $935 per inspection   $154,275 per
                                    per hour = $935 per                cycle.                inspection cycle.
                                    inspection cycle.
Optional modification (per door).  Up to 66                        0  Up to $5,610........  Up to $925,650.
                                    work[dash]hours x
                                    $85 per hour =
                                    $5,610.
Post-repair or -modification       11 work-hours x $85             0  $935 per inspection   $154,275 per
 inspection (per door).             per hour = $935 per                cycle.                inspection cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
             Action                    Labor cost           Parts cost                Cost per product
----------------------------------------------------------------------------------------------------------------
Repair (per door)...............  66 work-hours x $85  $7,380 or $9,360...  $12,990 or $14,970.
                                   per hour = $5,610.
----------------------------------------------------------------------------------------------------------------

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

    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):

2015-03-04 The Boeing Company: Amendment 39-18100 ; Docket No. FAA-
2014-0522; Directorate Identifier 2014-NM-087-AD.

(a) Effective Date

    This AD is effective March 25, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SR, and 747SP series airplanes, certificated in 
any category, as identified in Boeing Alert Service Bulletin 747-
53A2863, dated March 11, 2014.

(d) Subject

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

[[Page 8519]]

(e) Unsafe Condition

    This AD was prompted by reports of fuselage skin cracks at the 
lower forward corner of the main entry door (MED) 1 cutout. We are 
issuing this AD to detect and correct skin cracking, which can 
become large and could adversely affect the structural integrity of 
the airplane.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as specified in paragraph (j)(1) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014: Do 
a detailed inspection and a surface high frequency eddy current 
inspection for cracking of the fuselage skin at the applicable MED 1 
cutout, and do all applicable corrective actions, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2863, dated March 11, 2014. Do all applicable corrective 
actions before further flight. Repeat the inspections of the 
applicable MED 1 cutout thereafter at the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2863, dated March 11, 2014. Accomplishing the 
corrective actions required by this paragraph terminates the 
repetitive inspection requirements of this paragraph.

(h) Optional Terminating Action

    For airplanes on which no crack is found during the initial 
inspections required by paragraph (g) of this AD: Installing the 
preventive modification in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014, terminates the repetitive inspections required by 
paragraph (g) of this AD.

(i) Post-Repair or Post-Modification Repetitive Inspections and 
Corrective Actions

    For airplanes on which the corrective actions required by 
paragraph (g) of this AD have been done, or airplanes that have 
installed the preventive modification specified in paragraph (h) of 
this AD: At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014, do a detailed inspection for cracking of the 
fuselage skin at the applicable MED 1 cutout, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014, except as specified in paragraph (j)(2) of this AD. 
Do all applicable corrective actions before further flight. Repeat 
the inspection of the fuselage skin at the applicable MED 1 cutout 
thereafter at the intervals specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated 
March 11, 2014.

(j) Exceptions to Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2863, dated March 11, 2014, 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.
    (2) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 747-53A2863, dated March 
11, 2014, specifies to contact Boeing for appropriate action: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(k) 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 (l)(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.

 (l) Related Information

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

(m) 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 747-53A2863, dated March 11, 
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 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on February 2, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02689 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.