Airworthiness Directives; Airbus Airplanes, 23909-23912 [2014-09412]

Download as PDF Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0255; Directorate Identifier 2014–NM–056–AD; Amendment 39–17840; AD 2014–09–05] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. This AD requires repetitive inspections of certain sidestay upper cardan pins of the main landing gear (MLG), and associated nuts and retainer assemblies, and pin replacement if necessary. This AD also provides for an optional measurement of the cardan pin clearance dimensions (gap check) and corrective actions if necessary, which would terminate the repetitive inspections. This AD was prompted by a report of a sidestay upper cardan pin of the MLG migrating out of position. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. DATES: This AD becomes effective May 14, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 14, 2014. We must receive comments on this AD by June 13, 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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room sroberts on DSK5SPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:55 Apr 28, 2014 Jkt 232001 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 AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0255; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: 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 2014–0066, (correction) dated March 20, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. The MCAI states: An A330 aeroplane equipped with Basic (main landing gear) MLG was rolling out after landing when it experienced a nose wheel steering fault (unrelated to the safety subject addressed by this [EASA] AD), which resulted in the crew stopping the aeroplane on the taxiway after vacating the runway. The subsequent investigation revealed that the right-hand MLG sidestay upper cardan pin had migrated out of position. The sidestay upper cardan nut and retainer were PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 23909 found in the landing gear bay detached from the upper cardan pin. The nut and the retainer were still bolted together. This condition, if not detected and corrected, could lead to a complete migration of the sidestay upper cardan pin and a disconnection of the sidestay upper arm from the aeroplane structure, possibly resulting in MLG collapse with consequent damage to the aeroplane and injury to occupants. To address this potential condition, Airbus published Alert Operators Transmission (AOT) A32L003–14, providing inspection instructions. For the reasons described above, this [EASA] AD requires accomplishment of repetitive [detailed inspections for visible chrome] of the MLG upper cardan pin, nut and retainer [and pin replacement if necessary. This [EASA] AD also requires accomplishment of a gap check between wing rear spar fitting lugs and the bush flanges [and corrective actions if necessary. Corrective actions include repair or replacement of the cardan pin assembly]. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2014–0255. Relevant Service Information Airbus has issued Airbus Alert Operators Transmission (AOT) A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Differences Between This AD and the MCAI Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2014–0066, (correction) dated March 20, 2014, specifies that accomplishment of the gap check and corrective actions constitute terminating action for the AD. We consider the replacement of the cardan pin assembly as specified in paragraph (g)(3) to be terminating action for the repetitive inspections required by this AD. FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or E:\FR\FM\29APR1.SGM 29APR1 23910 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations develop on other products of these same type designs. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because migration of the sidestay upper cardan pin and disconnection of the sidestay upper arm from the airplane structure, could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. sroberts on DSK5SPTVN1PROD with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0255; Directorate Identifier 2014–NM–056– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Interim Action This AD is considered to be interim action. We are currently considering requiring a measurement of the cardan pin clearance dimensions (gap check) to determine that no gap exists between wing rear spar fitting lugs and the associated bush flanges of the left-hand and right-hand main landing gear (MLG), and applicable corrective actions, which will constitute terminating action for the repetitive inspections required by this AD action. However, the planned compliance time for the measurement would allow enough time to provide notice and opportunity for prior public comment on the merits of the measurement and applicable corrective actions. VerDate Mar<15>2010 15:55 Apr 28, 2014 Jkt 232001 Costs of Compliance We estimate that this AD affects 83 airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $7,055, or $85 per product. In addition, we estimate that any necessary follow-on actions will take about 4 work-hours and require parts costing $7,530, for a cost of $7,870 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 AD is 2120–0056. The paperwork cost associated with this 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. 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. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ 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): ■ 2014–09–05 Airbus: Amendment 39–17840. Docket No. FAA–2014–0255; Directorate Identifier 2014–NM–056–AD. (a) Effective Date This AD becomes effective May 14, 2014. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330–201, A330–202, A330–203, A330–223, A330–243, A330–301, A330–302, A330–303, A330–321, A330–322, A330–323, A330–341, A330–342, and A330– 343 airplanes, all manufacturer serial numbers (MSNs), equipped with basic (201252 series) main landing gear (MLG), or growth (201490 series) MLG. (2) Airbus Model A340–211, A340–212, A340–213, A340–311, A340–312, and A340– E:\FR\FM\29APR1.SGM 29APR1 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 313 airplanes, all MSNs, equipped with basic (201252 series) MLG or growth (201490 series) MLG. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a report of a sidestay upper cardan pin of the MLG migrating out of position. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and which could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. sroberts on DSK5SPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Detailed Inspections (1) For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years since first overhaul, as of the effective date of this AD, except those MLG that have had a second overhaul: Within 30 days after the effective date of this AD, accomplish a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, and associated nut and retainer assembly, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (i) Airplanes equipped with any MLG sidestay upper cardan pin subassembly part number (P/N) 201267202 (on 201252 series MLG). (ii) Airplanes equipped with any MLG sidestay upper cardan pin subassembly P/N 201483202 (on 201490 series MLG). (2) If, during any inspection required by paragraph (g)(1) of this AD, no pin chrome is visible inboard of the wing rear spar fitting lug, repeat the detailed inspection for visible chrome specified in paragraph (g)(1) of this AD, thereafter at intervals not to exceed 10 days. (3) If, during any inspection required by paragraphs (g)(1) or (g)(2) of this AD, pin chrome is visible inboard of the wing rear spar fitting lug, before further flight, replace the affected cardan pin assembly, in accordance with the instructions of Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). Replacement of the affected cardan pin assembly terminates the need for repetitive inspections required by paragraph (g)(2) of this AD. Note 1 to paragraph (g) of this AD: MLG sidestay upper cardan pin subassembly P/N 201267202 (found in Airbus Illustrated Parts Catalogue (IPC) as item 32–11–18–01) includes the cardan pin P/N 201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 (found in Airbus IPC as item 32–11–18–01) includes the cardan pin P/N 201483600. VerDate Mar<15>2010 15:55 Apr 28, 2014 Jkt 232001 23911 (h) Optional Terminating Action—Gap Check Measuring the cardan pin clearance dimensions (gap check) and doing the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD terminates the repetitive inspections required by paragraphs (g)(1) and (g)(2) of this AD for that sidestay upper cardan pin, nut, and retainer only. The measurement must be done in accordance with the instructions of Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (1) If the total clearance dimension (gap check result) is equal to or greater than 1.5 mm, replace the cardan pin assembly, in accordance with Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (2) If the total clearance dimension (gap check) is less than 1.5 mm but greater than 0.6 mm, do the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) Send the information (Appendix 2 proforma, photographs, and the movement traceability sheet) specified in paragraph 4.2.3, ‘‘Findings’’ of Airbus AOT A32L003– 14, dated March 10, 2014, including Appendices 1, 2, and 3, to Airbus at the address specified in Appendix 2 of Airbus AOT A32L003–14, dated March 10, 2014. (ii) 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). of Design Authority’s design organization approval, as applicable). 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. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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 (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 Alert Operators Transmission (AOT) A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2014–0066, (correction) dated March 20, 2014, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2014–0255. (k) Material Incorporated by Reference E:\FR\FM\29APR1.SGM 29APR1 23912 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations Issued in Renton, Washington, on April 16, 2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–09412 Filed 4–28–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0164; Directorate Identifier 2013–NE–10–AD; Amendment 39–17834; AD 2014–08–10] RIN 2120–AA64 Airworthiness Directives; Austro Engine GmbH Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding airworthiness directive (AD) 2013–14– 08 for all Austro Engine GmbH model E4 engines. AD 2013–14–08 required removing from service certain part number (P/N) waste gate controllers. This AD requires removing certain additional P/N waste gate controllers from service. This AD was prompted by several reports of power loss events due to fracture of the waste gate controller lever. We are issuing this AD to prevent failure of the waste gate controller lever, which could lead to damage to one or more engines, loss of thrust control, and damage to the airplane. DATES: This AD is effective June 3, 2014. ADDRESSES: For service information identified in this AD, contact Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A–2700 Weiner Neustadt, Austria; phone: +43 2622 23000; fax: +43 2622 23000–2711; Internet: www.austroengine.at. 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. SUMMARY: sroberts on DSK5SPTVN1PROD with RULES 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–2013– 0164; 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 mandatory continuing airworthiness information VerDate Mar<15>2010 15:55 Apr 28, 2014 Jkt 232001 (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238– 7199; email: wego.wang@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2013–14–08, Amendment 39–17513 (78 FR 42677, July 17, 2013), (‘‘AD 2013–14–08’’). AD 2013–14–08 applied to the specified products. The NPRM published in the Federal Register on January 10, 2014 (79 FR 1774). The NPRM proposed to continue to require removal from service of certain P/N waste gate controllers. The NPRM also proposed that, based on additional in-service failures, additional P/N waste gate controllers no longer be eligible for installation. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 1774, January 10, 2014). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD affects 128 engines installed on airplanes of U.S. registry. We also estimate that it will take about 0.5 hours per engine to comply with this AD. The average labor rate is $85 per hour. Required parts cost about $231 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $35,008. 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. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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 to the extent that it justifies making a regulatory distinction, 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 part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2013–14–08, Amendment 39–17513 (78 FR 42677, July 17, 2013) and adding the following new AD: ■ 2014–08–10 Austro Engine GmbH Engines: Amendment 39–17834; Docket No. E:\FR\FM\29APR1.SGM 29APR1

Agencies

[Federal Register Volume 79, Number 82 (Tuesday, April 29, 2014)]
[Rules and Regulations]
[Pages 23909-23912]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-09412]



[[Page 23909]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0255; Directorate Identifier 2014-NM-056-AD; 
Amendment 39-17840; AD 2014-09-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and 
-300 series airplanes. This AD requires repetitive inspections of 
certain sidestay upper cardan pins of the main landing gear (MLG), and 
associated nuts and retainer assemblies, and pin replacement if 
necessary. This AD also provides for an optional measurement of the 
cardan pin clearance dimensions (gap check) and corrective actions if 
necessary, which would terminate the repetitive inspections. This AD 
was prompted by a report of a sidestay upper cardan pin of the MLG 
migrating out of position. We are issuing this AD to detect and correct 
migration of the sidestay upper cardan pin, which could result in 
disconnection of the sidestay upper arm from the airplane structure, 
and could result in a landing gear collapse and consequent damage to 
the airplane and injury to occupants.

DATES: This AD becomes effective May 14, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2014.
    We must receive comments on this AD by June 13, 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 https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus SAS--
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0255; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

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 2014-0066, (correction) dated March 20, 2014 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Airbus Model A330-200 and -300 series airplanes, and Model 
A340-200 and -300 series airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic (main landing gear) MLG 
was rolling out after landing when it experienced a nose wheel 
steering fault (unrelated to the safety subject addressed by this 
[EASA] AD), which resulted in the crew stopping the aeroplane on the 
taxiway after vacating the runway.
    The subsequent investigation revealed that the right-hand MLG 
sidestay upper cardan pin had migrated out of position. The sidestay 
upper cardan nut and retainer were found in the landing gear bay 
detached from the upper cardan pin. The nut and the retainer were 
still bolted together.
    This condition, if not detected and corrected, could lead to a 
complete migration of the sidestay upper cardan pin and a 
disconnection of the sidestay upper arm from the aeroplane 
structure, possibly resulting in MLG collapse with consequent damage 
to the aeroplane and injury to occupants.
    To address this potential condition, Airbus published Alert 
Operators Transmission (AOT) A32L003-14, providing inspection 
instructions.
    For the reasons described above, this [EASA] AD requires 
accomplishment of repetitive [detailed inspections for visible 
chrome] of the MLG upper cardan pin, nut and retainer [and pin 
replacement if necessary. This [EASA] AD also requires 
accomplishment of a gap check between wing rear spar fitting lugs 
and the bush flanges [and corrective actions if necessary. 
Corrective actions include repair or replacement of the cardan pin 
assembly].

    You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0255.

Relevant Service Information

    Airbus has issued Airbus Alert Operators Transmission (AOT) 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 (the 
issue date is not specified on the appendices). The actions described 
in this service information are intended to correct the unsafe 
condition identified in the MCAI.

Differences Between This AD and the MCAI

    Mandatory Continuing Airworthiness Information (MCAI) European 
Aviation Safety Agency Airworthiness Directive 2014-0066, (correction) 
dated March 20, 2014, specifies that accomplishment of the gap check 
and corrective actions constitute terminating action for the AD. We 
consider the replacement of the cardan pin assembly as specified in 
paragraph (g)(3) to be terminating action for the repetitive 
inspections required by this AD.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or

[[Page 23910]]

develop on other products of these same type designs.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
migration of the sidestay upper cardan pin and disconnection of the 
sidestay upper arm from the airplane structure, could result in a 
landing gear collapse and consequent damage to the airplane and injury 
to occupants. Therefore, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and that good 
cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2014-0255; Directorate 
Identifier 2014-NM-056-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Interim Action

    This AD is considered to be interim action. We are currently 
considering requiring a measurement of the cardan pin clearance 
dimensions (gap check) to determine that no gap exists between wing 
rear spar fitting lugs and the associated bush flanges of the left-hand 
and right-hand main landing gear (MLG), and applicable corrective 
actions, which will constitute terminating action for the repetitive 
inspections required by this AD action. However, the planned compliance 
time for the measurement would allow enough time to provide notice and 
opportunity for prior public comment on the merits of the measurement 
and applicable corrective actions.

Costs of Compliance

    We estimate that this AD affects 83 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $7,055, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $7,530, for a cost of 
$7,870 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 AD is 2120-
0056. The paperwork cost associated with this 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. 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 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

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):

2014-09-05 Airbus: Amendment 39-17840. Docket No. FAA-2014-0255; 
Directorate Identifier 2014-NM-056-AD.

(a) Effective Date

    This AD becomes effective May 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, A330-202, A330-203, A330-223, A330-
243, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, 
A330-341, A330-342, and A330-343 airplanes, all manufacturer serial 
numbers (MSNs), equipped with basic (201252 series) main landing 
gear (MLG), or growth (201490 series) MLG.
    (2) Airbus Model A340-211, A340-212, A340-213, A340-311, A340-
312, and A340-

[[Page 23911]]

313 airplanes, all MSNs, equipped with basic (201252 series) MLG or 
growth (201490 series) MLG.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a report of a sidestay upper cardan pin 
of the MLG migrating out of position. We are issuing this AD to 
detect and correct migration of the sidestay upper cardan pin, which 
could result in disconnection of the sidestay upper arm from the 
airplane structure, and which could result in a landing gear 
collapse and consequent damage to the airplane and injury to 
occupants.

(f) Compliance

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

(g) Repetitive Detailed Inspections

    (1) For airplanes identified in paragraphs (g)(1)(i) and 
(g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years 
since first overhaul, as of the effective date of this AD, except 
those MLG that have had a second overhaul: Within 30 days after the 
effective date of this AD, accomplish a detailed inspection for 
visible chrome of each affected MLG sidestay upper cardan pin, and 
associated nut and retainer assembly, in accordance with the 
instructions of Airbus Alert Operators Transmission (AOT) A32L003-
14, dated March 10, 2014, including Appendices 1, 2, and 3 (the 
issue date is not specified on the appendices).
    (i) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly part number (P/N) 201267202 (on 201252 series MLG).
    (ii) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly P/N 201483202 (on 201490 series MLG).
    (2) If, during any inspection required by paragraph (g)(1) of 
this AD, no pin chrome is visible inboard of the wing rear spar 
fitting lug, repeat the detailed inspection for visible chrome 
specified in paragraph (g)(1) of this AD, thereafter at intervals 
not to exceed 10 days.
    (3) If, during any inspection required by paragraphs (g)(1) or 
(g)(2) of this AD, pin chrome is visible inboard of the wing rear 
spar fitting lug, before further flight, replace the affected cardan 
pin assembly, in accordance with the instructions of Airbus AOT 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 
(the issue date is not specified on the appendices). Replacement of 
the affected cardan pin assembly terminates the need for repetitive 
inspections required by paragraph (g)(2) of this AD.

    Note 1 to paragraph (g) of this AD:  MLG sidestay upper cardan 
pin subassembly P/N 201267202 (found in Airbus Illustrated Parts 
Catalogue (IPC) as item 32-11-18-01) includes the cardan pin P/N 
201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 
(found in Airbus IPC as item 32-11-18-01) includes the cardan pin P/
N 201483600.

(h) Optional Terminating Action--Gap Check

    Measuring the cardan pin clearance dimensions (gap check) and 
doing the applicable corrective action specified in paragraph (h)(1) 
or (h)(2) of this AD terminates the repetitive inspections required 
by paragraphs (g)(1) and (g)(2) of this AD for that sidestay upper 
cardan pin, nut, and retainer only. The measurement must be done in 
accordance with the instructions of Airbus AOT A32L003-14, dated 
March 10, 2014, including Appendices 1, 2, and 3 (the issue date is 
not specified on the appendices).
    (1) If the total clearance dimension (gap check result) is equal 
to or greater than 1.5 mm, replace the cardan pin assembly, in 
accordance with Airbus AOT A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3 (the issue date is not specified on 
the appendices).
    (2) If the total clearance dimension (gap check) is less than 
1.5 mm but greater than 0.6 mm, do the actions specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Send the information (Appendix 2 proforma, photographs, and 
the movement traceability sheet) specified in paragraph 4.2.3, 
``Findings'' of Airbus AOT A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3, to Airbus at the address specified 
in Appendix 2 of Airbus AOT A32L003-14, dated March 10, 2014.
    (ii) 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).

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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, as applicable). 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.

(j) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2014-0066, 
(correction) dated March 20, 2014, for related information. You may 
examine the MCAI on the Internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0255.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission (AOT) A32L003-14, dated 
March 10, 2014, including Appendices 1, 2, and 3 (the issue date is 
not specified on the appendices).
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@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/ibr-locations.html.


[[Page 23912]]


    Issued in Renton, Washington, on April 16, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-09412 Filed 4-28-14; 8:45 am]
BILLING CODE 4910-13-P
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