Airworthiness Directives; Airbus Airplanes, 15266-15269 [2014-06009]

Download as PDF 15266 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules May 26, 2009, for multi-engine airplanes; and in OIL OI331–18R4, dated May 26, 2009, for single-engine airplanes. Information on fuel control drive spline inspection can be found in Section 72–00–00 of the applicable TPE331 maintenance manuals. These Honeywell International Inc., OILs and the TPE331 maintenance manuals, which are not incorporated by reference in this AD, can be obtained from Honeywell International Inc., using the contact information in paragraph (i)(4) of this AD. (4) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802; Internet: https:// myaerospace.honeywell.com/wps/portal/!ut; phone: 800–601–3099. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. DEPARTMENT OF TRANSPORTATION You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 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. 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. Federal Aviation Administration Examining the AD Docket Issued in Burlington, Massachusetts, on March 10, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–06029 Filed 3–18–14; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 B4–603, B4–620, B4–622, B4–605R, B4–622R; F4–605R, F4–622R and C4–605R variant F airplanes. This proposed AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. This proposed AD would require repetitive detailed inspections of the lower frame fittings, related investigative actions, and corrective actions if necessary. We are proposing this AD to detect and correct cracking on the lower frame fittings, which could reduce the structural integrity of the airplane. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: We must receive comments on this proposed AD by May 5, 2014. DATES: VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0143; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD’’ at the beginning of your comments. We specifically invite PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the technical agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0103, dated June 11, 2012 (corrected June 19, 2012) (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During maintenance checks, cracks were discovered by A300 and A300–600 operators in the frame [base] feet fittings, connecting the frame lower positions to the centre wing box. These occurrences were followed by a dedicated sampling inspection programme carried out by Airbus. During this sampling programme, 22 A300–600 aeroplanes were found with cracks on the lower fittings of frame 44 to frame 46 left hand (LH) and right hand (RH) side. This condition, if not detected and corrected, could affect the structural integrity of the fuselage of all aeroplanes operated up to the extended service goal (ESG). For the reasons described above, this [EASA] AD requires repetitive detailed visual inspections [for discrepancies (cracking)] of the lower frame fittings between frame 41 and frame 46 and, depending on findings, accomplishment of a repair. This [EASA] AD has been republished to correct Note 2 in Appendix 1. Related investigative actions include doing a rotating probe inspection for cracking of the crack stop hole. Corrective actions include repairing or replacing cracking and cracked base fittings. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2014–0143. Relevant Service Information Airbus has issued Mandatory Service Bulletin A300–53–6111, Revision 05, including Appendix 01, dated January 28, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\19MRP1.SGM 19MRP1 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules wreier-aviles on DSK5TPTVN1PROD with PROPOSALS FAA’s Determination and Requirements of This Proposed AD authorized to approve required repairs for this proposed AD. This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. In many FAA transport ADs, when the service information specifies to contact the manufacturer for further instructions if certain discrepancies are found, we typically include in the AD a requirement to accomplish the action using a method approved by either the FAA or the State of Design Authority (or its delegated agent). We have recently been notified that certain laws in other countries do not allow such delegation of authority, but some countries do recognize design approval organizations. In addition, we have become aware that some U.S. operators have used repair instructions that were previously approved by a State of Design Authority or a Design Approval Holder (DAH) as a method of compliance with this provision in FAA ADs. Frequently, in these cases, the previously approved repair instructions come from the airplane structural repair manual or the DAH repair approval statements that were not specifically developed to address the unsafe condition corrected by the AD. Using repair instructions that were not specifically approved for a particular AD creates the potential for doing repairs that were not developed to address the unsafe condition identified by the MCAI AD, the FAA AD, or the applicable service information, which could result in the unsafe condition not being fully corrected. To prevent the use of repairs that were not specifically developed to correct the unsafe condition, this proposed AD would require that the repair approval specifically refer to the FAA AD. This change is intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we use the phrase ‘‘its delegated agent, or the DAH with State of Design Authority design organization approval, as applicable’’ in this proposed AD to refer to a DAH Differences Between This Proposed AD and the MCAI or Service Information Unlike the procedures described in Airbus Mandatory Service Bulletin A300–53–6111, Revision 05, including Appendix 01, dated January 28, 2013; this proposed AD would not permit further flight if discrepancies (cracking or cracked frames) are detected in the base fitting of the left-hand and righthand frames 41 to 46 of the fuselage. We have determined that, because of the safety implications and consequences associated with that cracking, any cracked frame must be repaired or modified before further flight. This difference has been coordinated with EASA. Airbus Mandatory Service Bulletin A300–53–6111, Revision 05, including Appendix 01, dated January 28, 2013, does not provide corrective action for cracking that measures 20 mm. This AD would require repairing the cracking using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA), or its delegated agent, or the Design Approval Holder with EASA’s design organization approval, as applicable. VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 Costs of Compliance We estimate that this proposed AD affects 124 airplanes of U.S. registry. We also estimate that it would take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $340, or $42,160 per product. In addition, we estimate that any necessary follow-on actions would take about 348 work-hours and require parts costing $61,810, for a cost of $91,390 per product. We have no way of determining the number of aircraft that might need these actions. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this proposed AD is 2120– PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 15267 0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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. E:\FR\FM\19MRP1.SGM 19MRP1 15268 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD. (a) Comments Due Date We must receive comments by May 5, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4– 603, B4–620, B4–622, B4–605R, B4–622R; F4–605R, F4–622R and C4–605R variant F airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. We are issuing this AD to detect and correct cracking on the lower frame fittings, which could reduce the structural integrity of the airplane. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Actions At the applicable time specified in paragraphs (g)(1) through (g)(4) of this AD, do a detailed inspection for discrepancies (cracking) of the base fitting of the left-hand and right-hand frames 41 to 46 of the fuselage, and do all applicable related investigative actions and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–53–6111, Revision 05, dated January 28, 2013, except as required by paragraph (k) of this AD. Do all applicable related investigative actions and corrective actions before further flight. Repeat the inspections at the applicable time specified in paragraphs (h)(1) through (h)(4) of this AD. VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 (1) For any frame on which no affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane has operated with an average flight time (AFT) of more than 1.5 hours: At the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) Within 5,000 flight cycles (FC) or 10,800 flight hours, whichever occurs first, since airplane first flight. (ii) Within 1,000 flight cycles after the effective date of this AD. (2) For any frame on which no affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane has operated with an AFT of equal to or less than 1.5 hours: At the later of the times specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Within 5,400 flight cycles or 8,100 flight hours, whichever occurs first since airplane first flight. (ii) Within 1,000 flight cycles after the effective date of this AD. (3) For any frame on which any of the affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane has operated with an AFT of more than 1.5 hours: At the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Within 45,400 flight cycles or 98,000 flight hours, whichever occurs first since frame repair embodiment. (ii) Within 1,000 flight cycles after the effective date of this AD. (4) For any frame on which any of the affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane operated with an AFT of equal to or less than 1.5 hours: At the later of the times specified in paragraphs (h)(4)(i) and (h)(4)(ii) of this AD. (i) Within 49,000 flight cycles or 73,500 flight hours, whichever occurs first since frame repair embodiment. (ii) Within 1,000 flight cycles after the effective date of this AD. (h) Repetitive Inspection Compliance Times (1) For any frame on which no affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane has operated with an AFT of more than 1.5 hours: Inspect within 3,200 flight cycles or 7,000 flight hours, whichever occurs first. (2) For any frame on which no affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane operated with an AFT of equal to or less than 1.5 hours: Inspect within 3,500 flight cycles or 5,300 flight hours, whichever occurs first since airplane first flight. (3) For any frame on which any of the affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD and the airplane operated with an AFT of more than 1.5 hours: Inspect within 45,400 flight cycles or 98,000 flight hours, whichever occurs first since frame repair embodiment. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 (4) For any frame on which any of the affected repairs specified in paragraph (i) of this AD have been accomplished as of the effective date of this AD, and the airplane operated with an AFT of equal to or less than 1.5 hours: Inspect within 49,000 flight cycles or 73,500 flight hours, whichever occurs first, since frame repair embodiment. (i) Definition of Affected Repairs For the purposes of this AD, affected repairs are R53810322, R53810323, R53810329, R53810330, R53810331, R53810332, and any repair specified in Airbus Mandatory Service Bulletin A300–53– 6111, Revision 05, including Appendix 01, dated January 28, 2013, as well as repairs accomplished in accordance with Airbus Mandatory Service Bulletin A300–53–6111, any revision. (j) Definition of Average Flight Time (AFT) For the purposes of this AD, the AFT is defined as a computation of the number of flight hours divided by the number of flight cycles accumulated since last inspection, or since airplane first flight, as applicable. (k) Exceptions to Service Information Specifications Where Airbus Mandatory Service Bulletin A300–53–6111, Revision 05, including Appendix 01, dated January 28, 2013, does not specify action for a repair that measures 20 mm, if during any inspection required by paragraph (g) of this AD cracking is found that measures 20 mm, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or European Aviation Safety Agency (EASA) (or its delegated agent, or the Design Approval Holder with EASA’s design organization approval, as applicable). For a repair method to be approved, the repair approval must specifically refer to this AD. (l) Reporting of Inspection Results At the applicable time specified in paragraphs (l)(1) and (l)(2) of this AD: After accomplishment of any inspection specified in paragraph (g) of this AD, report discrepancies (cracking) to Airbus, in accordance with Appendix 01 of Airbus Mandatory Service Bulletin A300–53–6111, Revision 05, dated January 28, 2013. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (m) Clarification Accomplishment of corrective action(s) as required by paragraph (g) of this AD does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Mandatory Service Bulletin A300–53–6111, E:\FR\FM\19MRP1.SGM 19MRP1 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules wreier-aviles on DSK5TPTVN1PROD with PROPOSALS Revision 04, including Appendix 01, dated August 25, 2011, which is not incorporated by reference in this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM–116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; 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, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure the product is airworthy before it is returned to service. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0103, dated June 11, 2012, (corrected June 19, 2012) for related information. This MCAI may be found in the AD docket on the Internet at VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 http://www.regulations.gov by searching for and locating it in Docket No. FAA–2014– 0143. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 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. 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. Issued in Renton, Washington, on March 7, 2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–06009 Filed 3–18–14; 8:45 am] BILLING CODE 4910–13–P 15269 • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Dowty Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL2 9QN, UK; phone: 44 (0) 1452 716000; fax: 44 (0) 1452 716001. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0776; Directorate Identifier 2009–NE–32–AD] RIN 2120–AA64 Airworthiness Directives; Dowty Propellers Constant Speed Propellers Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to revise airworthiness directive (AD) 2010–17– 11R1, which applies to all Dowty Propellers R408/6–123–F/17 model propellers. AD 2010–17–11R1 requires initial and repetitive application of sealant between the bus bar assembly and the backplate assembly of certain line-replaceable units (LRUs). That AD also provides an optional terminating action to the repetitive re-application of sealant. This proposed AD would increase the interval allowed between the required re-application of sealant, and would specify an additional acceptable sealant. We are proposing this AD to prevent an in-flight double generator failure, which could result in reduced control of the airplane. DATES: We must receive comments on this proposed AD by May 19, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2009– 0776; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7761; fax 781–238–7170; email: michael.schwetz@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0776; Directorate Identifier 2009–NE–32–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// E:\FR\FM\19MRP1.SGM 19MRP1

Agencies

[Federal Register Volume 79, Number 53 (Wednesday, March 19, 2014)]
[Proposed Rules]
[Pages 15266-15269]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06009]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R; F4-605R, 
F4-622R and C4-605R variant F airplanes. This proposed AD was prompted 
by reports of cracks in the frame base fittings connecting the frame 
lower positions to the center wing box. This proposed AD would require 
repetitive detailed inspections of the lower frame fittings, related 
investigative actions, and corrective actions if necessary. We are 
proposing this AD to detect and correct cracking on the lower frame 
fittings, which could reduce the structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by May 5, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0143; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0143; 
Directorate Identifier 2012-NM-113-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the technical 
agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0103, dated June 11, 2012 (corrected June 
19, 2012) (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    During maintenance checks, cracks were discovered by A300 and 
A300-600 operators in the frame [base] feet fittings, connecting the 
frame lower positions to the centre wing box.
    These occurrences were followed by a dedicated sampling 
inspection programme carried out by Airbus. During this sampling 
programme, 22 A300-600 aeroplanes were found with cracks on the 
lower fittings of frame 44 to frame 46 left hand (LH) and right hand 
(RH) side.
    This condition, if not detected and corrected, could affect the 
structural integrity of the fuselage of all aeroplanes operated up 
to the extended service goal (ESG).
    For the reasons described above, this [EASA] AD requires 
repetitive detailed visual inspections [for discrepancies 
(cracking)] of the lower frame fittings between frame 41 and frame 
46 and, depending on findings, accomplishment of a repair.
    This [EASA] AD has been republished to correct Note 2 in 
Appendix 1.

    Related investigative actions include doing a rotating probe 
inspection for cracking of the crack stop hole. Corrective actions 
include repairing or replacing cracking and cracked base fittings. You 
may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-
2014-0143.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-53-6111, Revision 
05, including Appendix 01, dated January 28, 2013. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

[[Page 15267]]

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, this proposed AD would require that 
the repair approval specifically refer to the FAA AD. This change is 
intended to clarify the method of compliance and to provide operators 
with better visibility of repairs that are specifically developed and 
approved to correct the unsafe condition. In addition, we use the 
phrase ``its delegated agent, or the DAH with State of Design Authority 
design organization approval, as applicable'' in this proposed AD to 
refer to a DAH authorized to approve required repairs for this proposed 
AD.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Unlike the procedures described in Airbus Mandatory Service 
Bulletin A300-53-6111, Revision 05, including Appendix 01, dated 
January 28, 2013; this proposed AD would not permit further flight if 
discrepancies (cracking or cracked frames) are detected in the base 
fitting of the left-hand and right-hand frames 41 to 46 of the 
fuselage. We have determined that, because of the safety implications 
and consequences associated with that cracking, any cracked frame must 
be repaired or modified before further flight. This difference has been 
coordinated with EASA.
    Airbus Mandatory Service Bulletin A300-53-6111, Revision 05, 
including Appendix 01, dated January 28, 2013, does not provide 
corrective action for cracking that measures 20 mm. This AD would 
require repairing the cracking using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; or 
European Aviation Safety Agency (EASA), or its delegated agent, or the 
Design Approval Holder with EASA's design organization approval, as 
applicable.

Costs of Compliance

    We estimate that this proposed AD affects 124 airplanes of U.S. 
registry.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $340, or $42,160 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 348 work-hours and require parts costing $61,810, for a cost 
of $91,390 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    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.

[[Page 15268]]

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-
113-AD.

(a) Comments Due Date

    We must receive comments by May 5, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R; F4-605R, F4-622R and C4-605R variant F airplanes; 
certificated in any category; all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks in the frame base 
fittings connecting the frame lower positions to the center wing 
box. We are issuing this AD to detect and correct cracking on the 
lower frame fittings, which could reduce the structural integrity of 
the airplane.

(f) Compliance

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

(g) Inspection and Corrective Actions

    At the applicable time specified in paragraphs (g)(1) through 
(g)(4) of this AD, do a detailed inspection for discrepancies 
(cracking) of the base fitting of the left-hand and right-hand 
frames 41 to 46 of the fuselage, and do all applicable related 
investigative actions and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-53-6111, Revision 05, dated January 28, 2013, except as 
required by paragraph (k) of this AD. Do all applicable related 
investigative actions and corrective actions before further flight. 
Repeat the inspections at the applicable time specified in 
paragraphs (h)(1) through (h)(4) of this AD.
    (1) For any frame on which no affected repairs specified in 
paragraph (i) of this AD have been accomplished as of the effective 
date of this AD, and the airplane has operated with an average 
flight time (AFT) of more than 1.5 hours: At the later of the times 
specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Within 5,000 flight cycles (FC) or 10,800 flight hours, 
whichever occurs first, since airplane first flight.
    (ii) Within 1,000 flight cycles after the effective date of this 
AD.
    (2) For any frame on which no affected repairs specified in 
paragraph (i) of this AD have been accomplished as of the effective 
date of this AD, and the airplane has operated with an AFT of equal 
to or less than 1.5 hours: At the later of the times specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Within 5,400 flight cycles or 8,100 flight hours, whichever 
occurs first since airplane first flight.
    (ii) Within 1,000 flight cycles after the effective date of this 
AD.
    (3) For any frame on which any of the affected repairs specified 
in paragraph (i) of this AD have been accomplished as of the 
effective date of this AD, and the airplane has operated with an AFT 
of more than 1.5 hours: At the later of the times specified in 
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
    (i) Within 45,400 flight cycles or 98,000 flight hours, 
whichever occurs first since frame repair embodiment.
    (ii) Within 1,000 flight cycles after the effective date of this 
AD.
    (4) For any frame on which any of the affected repairs specified 
in paragraph (i) of this AD have been accomplished as of the 
effective date of this AD, and the airplane operated with an AFT of 
equal to or less than 1.5 hours: At the later of the times specified 
in paragraphs (h)(4)(i) and (h)(4)(ii) of this AD.
    (i) Within 49,000 flight cycles or 73,500 flight hours, 
whichever occurs first since frame repair embodiment.
    (ii) Within 1,000 flight cycles after the effective date of this 
AD.

(h) Repetitive Inspection Compliance Times

    (1) For any frame on which no affected repairs specified in 
paragraph (i) of this AD have been accomplished as of the effective 
date of this AD, and the airplane has operated with an AFT of more 
than 1.5 hours: Inspect within 3,200 flight cycles or 7,000 flight 
hours, whichever occurs first.
    (2) For any frame on which no affected repairs specified in 
paragraph (i) of this AD have been accomplished as of the effective 
date of this AD, and the airplane operated with an AFT of equal to 
or less than 1.5 hours: Inspect within 3,500 flight cycles or 5,300 
flight hours, whichever occurs first since airplane first flight.
    (3) For any frame on which any of the affected repairs specified 
in paragraph (i) of this AD have been accomplished as of the 
effective date of this AD and the airplane operated with an AFT of 
more than 1.5 hours: Inspect within 45,400 flight cycles or 98,000 
flight hours, whichever occurs first since frame repair embodiment.
    (4) For any frame on which any of the affected repairs specified 
in paragraph (i) of this AD have been accomplished as of the 
effective date of this AD, and the airplane operated with an AFT of 
equal to or less than 1.5 hours: Inspect within 49,000 flight cycles 
or 73,500 flight hours, whichever occurs first, since frame repair 
embodiment.

(i) Definition of Affected Repairs

    For the purposes of this AD, affected repairs are R53810322, 
R53810323, R53810329, R53810330, R53810331, R53810332, and any 
repair specified in Airbus Mandatory Service Bulletin A300-53-6111, 
Revision 05, including Appendix 01, dated January 28, 2013, as well 
as repairs accomplished in accordance with Airbus Mandatory Service 
Bulletin A300-53-6111, any revision.

(j) Definition of Average Flight Time (AFT)

    For the purposes of this AD, the AFT is defined as a computation 
of the number of flight hours divided by the number of flight cycles 
accumulated since last inspection, or since airplane first flight, 
as applicable.

(k) Exceptions to Service Information Specifications

    Where Airbus Mandatory Service Bulletin A300-53-6111, Revision 
05, including Appendix 01, dated January 28, 2013, does not specify 
action for a repair that measures 20 mm, if during any inspection 
required by paragraph (g) of this AD cracking is found that measures 
20 mm, before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or European Aviation Safety Agency (EASA) (or its 
delegated agent, or the Design Approval Holder with EASA's design 
organization approval, as applicable). For a repair method to be 
approved, the repair approval must specifically refer to this AD.

(l) Reporting of Inspection Results

    At the applicable time specified in paragraphs (l)(1) and (l)(2) 
of this AD: After accomplishment of any inspection specified in 
paragraph (g) of this AD, report discrepancies (cracking) to Airbus, 
in accordance with Appendix 01 of Airbus Mandatory Service Bulletin 
A300-53-6111, Revision 05, dated January 28, 2013.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(m) Clarification

    Accomplishment of corrective action(s) as required by paragraph 
(g) of this AD does not constitute terminating action for the 
repetitive inspections required by paragraph (h) of this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Mandatory Service Bulletin 
A300-53-6111,

[[Page 15269]]

Revision 04, including Appendix 01, dated August 25, 2011, which is 
not incorporated by reference in this AD.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-2125; fax (425) 227-1149. Information may 
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval). For a repair method to be approved, 
the repair approval must specifically refer to this AD. You are 
required to ensure the product is airworthy before it is returned to 
service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0103, dated June 11, 2012, 
(corrected June 19, 2012) for related information. This MCAI may be 
found in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2014-0143.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 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. 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.

    Issued in Renton, Washington, on March 7, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-06009 Filed 3-18-14; 8:45 am]
BILLING CODE 4910-13-P