Airworthiness Directives; Airbus Airplanes, 72398-72401 [2015-29442]

Download as PDF 72398 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules the inspection at the later of the times specified in paragraphs (h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD. (A) Within 20,600 flight cycles or 30,900 flight hours after first flight of the airplane, whichever occurs first. (B) Within 1,600 flight cycles or 2,400 flight hours after the effective date of this AD, whichever occurs first. (3) For ‘‘normal range operations’’ airplanes having an average flight time of 1.5 flight hours or more: Repeat the inspection at the applicable time required in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) For Model A300 F4–605R and F4–622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles or 19,400 flight hours, whichever occurs first. (ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,100 flight cycles or 15,300 flight hours, whichever occurs first. (4) For ‘‘short range operations’’ airplanes having an average flight time of less than 1.5 flight hours: Repeat the inspection at the applicable time required in paragraphs (h)(4)(i) and (h)(4)(ii) of this AD. (i) For Model A300 F4–605R and F4–622R airplanes: Repeat the inspection thereafter at intervals not to exceed 9,700 flight cycles or 14,500 flight hours, whichever occurs first. (ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Repeat the inspection thereafter at intervals not to exceed 7,600 flight cycles or 11,500 flight hours, whichever occurs first. rmajette on DSK2TPTVN1PROD with PROPOSALS (i) Definition of Average Flight Time for Paragraph (h) of This AD For the purpose of paragraph (h) of this AD, the Average Flight Time must be established as follows: (1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold. (3) For all inspection intervals onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. (j) New Requirement of This AD: Corrective Action for Any Cracking Found If any crack is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. Accomplishing a repair does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (k) Credit for Previous Actions This paragraph provides credit for inspections required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 (k)(1), (k)(2), and (k)(3) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A300–57–6028, Revision 04, dated October 25, 1999. (2) Airbus Service Bulletin A300–57–6028, Revision 05, dated January 11, 2002. (3) Airbus Service Bulletin A300–57–6028, Revision 06, dated May 17, 2006. Issued in Renton, Washington, on November 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–29443 Filed 11–18–15; 8:45 am] BILLING CODE 4910–13–P (l) 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: 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-116AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2014–0119, dated May 13, 2014, 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 Docket No. FAA–2015–4817. (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. PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4815; Directorate Identifier 2015–NM–112–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2015–03– 06, for all Airbus Model A330–200, A330–200 Freighter, A330–300, A340– 200, A340–300, A340–500, and A340– 600 series airplanes. AD 2015–03–06 currently requires repetitive inspections of the left-hand and right-hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. Since we issued AD 2015–03–06, we have received reports of additional cracking of the MLG rib 6 aft bearing lugs. This proposed AD would reduce certain compliance times. We are proposing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing. DATES: We must receive comments on this proposed AD by January 4, 2016. 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, SUMMARY: E:\FR\FM\19NOP1.SGM 19NOP1 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 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 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. rmajette on DSK2TPTVN1PROD with PROPOSALS 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–2015– 4815; 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: 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: 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–2015–4815; Directorate Identifier 2015–NM–112–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 On February 2, 2015, we issued AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015). AD 2015– 03–06 requires actions intended to address an unsafe condition on all Airbus Model A330–200, A330–200 VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 Freighter, A330–300, A340–200, A340– 300, A340–500, and A340–600 series airplanes. Since we issued AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015), we have determined that it is necessary to introduce a more restrictive initial inspection threshold and a grace period for airplanes that have already exceeded the new threshold. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0120, dated June 26, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, A330–300, A340–200, A340–300, A340– 500, and A340–600 series airplanes. The MCAI states: During Main Landing Gear (MLG) lubrication, a crack was visually found in the MLG rib 6 aft bearing forward lug on one A330 in-service aeroplane. The crack had extended through the entire thickness of the forward lug at approximately the 4 o’clock position (when looking forward). It has been determined that a similar type of crack can develop on other aeroplane types that are listed in the Applicability paragraph. This condition, if not detected and corrected, could affect the structural integrity of the MLG attachment. To address this situation, Airbus issued inspection Service Bulletin (SB) A330–57– 3096, SB A340–57–4104 and SB A340–57– 5009 to provide instructions for repetitive inspections of the gear rib lugs. Prompted by these findings, EASA issued Emergency AD 2006–0364–E to require repetitive detailed visual inspections of the Left Hand (LH) and Right Hand (RH) wing MLG rib 6 aft bearing lugs. Later, EASA issued AD 2007–0247–E, which superseded [EASA] AD 2006–0364–E, to: —expand the Applicability to all A330 and A340 aeroplanes, because the interference fit bushes cannot be considered as a terminating action, owing to unknown root cause; and —add a second parameter quoted in flight hours (FH) to the inspection interval in order to reflect the aeroplane utilisation in service. EASA AD 2007–0247–E was revised to correct a typographical error. Since the first crack finding and issuance of the inspection SBs and related ADs, six further cracks were reported. Consequently, EASA issued AD 2013–0271 [which corresponds to FAA AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015)], which retained the requirements of [EASA] AD 2007–0247R1–E, which was superseded, and expanded the Applicability of the [EASA] AD to the newly certified models A330–223F and A330–243F. That AD also reduced the inspection threshold(s) to reflect the updated risk assessment and inservice experience. PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 72399 Since this [EASA] AD was issued, a new occurrence of crack finding was reported. Further analysis resulted in the need to reduce the threshold of the initial inspection. Prompted by this finding, Airbus issued SB A330–57–3096 Revision 06 to introduce a more restrictive initial inspection threshold and a grace period for aeroplanes which have already passed the new threshold. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2013–0271, which is superseded, and introduces reduced initial inspection thresholds. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4815. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–57–3096, Revision 06, dated May 29, 2015. The service information describes procedures for detailed inspections to detect any cracking on the forward and aft lugs of the Left Hand (LH) and Right Hand (RH) wing MLG Rib 6. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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. Explanation of ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD E:\FR\FM\19NOP1.SGM 19NOP1 72400 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a Note under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. rmajette on DSK2TPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 101 airplanes of U.S. registry. The actions required by AD 2015–03– 06, Amendment 39–18102 (80 FR 8511, February 18, 2015), and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2015–03–06 is $170 per product. This proposed AD reduces the initial compliance time but adds no new actions. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. –342, and –343 airplanes; and Model A340– 211, –212, –213 –311, –312, –313, –541, and –642 airplanes; certificated in any category; all manufacturer serial numbers. 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. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. 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. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015), and adding the following new AD: ■ Airbus: Docket No. FAA–2015–4815; Directorate Identifier 2015–NM–112–AD. (a) Comments Due Date We must receive comments by January 4, 2016. (b) Affected ADs This AD replaces AD 2015–03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015). (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F –301, –302, –303, –321, –322, –323, –341, PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 (e) Reason This AD was prompted by reports of cracking of the main landing gear (MLG) rib 6 aft bearing forward lug. We are issuing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a detailed inspection for cracking of the lefthand and right-hand wing MLG rib 6 aft bearing lugs (forward and aft), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–57–3096, Revision 06, dated May 29, 2015 (for Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes); A340–57– 4104, Revision 04, dated October 17, 2013 (for Model A340–211, –212, –213, –311, –312, –313 airplanes); or A340–57–5009, Revision 03, dated October 17, 2013 (for Model A340–541 and –642 airplanes); as applicable. (1) Within 24 months or 2,000 flight cycles, whichever occurs first since airplane first flight or since the last MLG support rib replacement, as applicable. (2) Within 30 days after the effective date of this AD. (h) Repetitive Inspections Repeat the inspection required by paragraph (g) of this AD thereafter at the time specified in paragraphs (h)(1) through (h)(7) of this AD, as applicable. (1) For Model A330–201, –202, –203, –223, and –243 airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 1,500 flight hours, whichever occurs first. (2) For Model A330–223F and –243F airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 900 flight hours, whichever occurs first. (3) For Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes: Repeat the inspections at intervals not to exceed 300 flight cycles or 900 flight hours, whichever occurs first. (4) For Model A340–211, –212, and –213 airplanes: Repeat the inspections at intervals not to exceed 200 flight cycles or 800 flight hours, whichever occurs first. (5) For Model A340–311 and –312 airplanes; and Model A340–313 airplanes (except weight variant (WV) 27): Repeat the inspections at intervals not to exceed 200 flight cycles or 800 flight hours, whichever occurs first. (6) For Model A340–313 (only WV27) airplanes: Repeat the inspections at intervals E:\FR\FM\19NOP1.SGM 19NOP1 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules not to exceed 200 flight cycles or 400 flight hours, whichever occurs first. (7) For Model A340–541 and –642 airplanes: Repeat the inspections at intervals not to exceed 100 flight cycles or 500 flight hours, whichever occurs first. rmajette on DSK2TPTVN1PROD with PROPOSALS (i) Corrective Action If any crack is found during any inspection required by paragraphs (g) or (h) of this AD: Before further flight, replace the cracked MLG support rib using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Replacement of an MLG support rib does not terminate the repetitive inspections required by paragraph (h) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraphs (j)(1) through (j)(15) of this AD. (1) Airbus Service Bulletin A330–57A3096, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (74 FR 4416, January 31, 2007). (2) Airbus Service Bulletin A330–57A3096, Revision 01, dated April 18, 2007, which is not incorporated by reference by this AD. (3) Airbus Service Bulletin A330–57–3096, Revision 02, dated August 13, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (4) Airbus Service Bulletin A330–57–3096, Revision 03, dated October 24, 2012, which is not incorporated by reference by this AD. (5) Airbus Service Bulletin A330–57–3096, Revision 04, dated February 6, 2013, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A330–57–3096, Revision 05, dated October 17, 2013, which was incorporated by reference in AD 2015– 03–06, Amendment 39–18102 (80 FR 8511, February 18, 2015). (7) Airbus Service Bulletin A340–57A4104, dated December 5, 2006, which was incorporated by reference in AD 2007–03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007). (8) Airbus Service Bulletin A340–57–4104, Revision 01, dated August 13, 2007, which is not incorporated by reference in this AD. (9) Airbus Service Bulletin A340–57–4104, Revision 02, dated September 5, 2007, which was incorporated by reference in AD 2007– 22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (10) Airbus Service Bulletin A340–57– 4104, Revision 03, dated October 24, 2012, which is not incorporated by reference in this AD. (11) Airbus Service Bulletin A340– 57A5009, dated December 5, 2006, which was incorporated by reference in AD 2007– 03–04, Amendment 39–14915 (72 FR 4416, January 31, 2007). VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 72401 (12) Airbus Service Bulletin A340–57– 5009, Revision 01, dated August 13, 2007, which was incorporated by reference in AD 2007–22–10, Amendment 39–15246 (72 FR 61796, November 1, 2007; corrected November 16, 2007 (72 FR 64532)). (13) Airbus Service Bulletin A340–57– 5009, Revision 02, dated October 24, 2012, which is not incorporated by reference in this AD. (14) Airbus Alert Operators Transmission A57L005–14, dated July 15, 2014, which is not incorporated by reference in this AD. (15) Airbus Alert Operators Transmission A57L005–14, Revision 01, dated August 15, 2014, which is not incorporated by reference in this AD. June 26, 2015, 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 Docket No. FAA– 2015–4815. (2) 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 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. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. Issued in Renton, Washington, on November 11, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0120, dated PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 [FR Doc. 2015–29442 Filed 11–18–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4816; Directorate Identifier 2014–NM–238–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 certain Airbus Model A319, A320, and A321 series airplanes. This proposed AD was prompted by investigations that revealed that the cover seal of the brake dual distribution valve (BDDV) was damaged and did not ensure efficient sealing. This proposed AD would require modifying the BDDV having certain part numbers; modifying the drain hose of the BDDV; checking for the presence of water, ice, and hydraulic fluid; and re-identifying the BDDV; and related investigative and corrective actions if necessary. We are proposing this AD to prevent damage to the BDDV, which could lead to water ingestion in the BDDV and freezing of the BDDV in flight, possibly resulting in loss of braking system function after landing. DATES: We must receive comments on this proposed AD by January 4, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\19NOP1.SGM 19NOP1

Agencies

[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72398-72401]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29442]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4815; Directorate Identifier 2015-NM-112-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 supersede Airworthiness Directive (AD) 2015-03-
06, for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-
200, A340-300, A340-500, and A340-600 series airplanes. AD 2015-03-06 
currently requires repetitive inspections of the left-hand and right-
hand wing main landing gear (MLG) rib 6 aft bearing lugs (forward and 
aft) to detect any cracks on the two lugs, and replacement if 
necessary. Since we issued AD 2015-03-06, we have received reports of 
additional cracking of the MLG rib 6 aft bearing lugs. This proposed AD 
would reduce certain compliance times. We are proposing this AD to 
detect and correct cracking of the MLG rib 6 aft bearing lugs, which 
could result in collapse of the MLG upon landing.

DATES: We must receive comments on this proposed AD by January 4, 2016.

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,

[[Page 72399]]

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 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-2015-
4815; 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: 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: 

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-2015-4815; 
Directorate Identifier 2015-NM-112-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

    On February 2, 2015, we issued AD 2015-03-06, Amendment 39-18102 
(80 FR 8511, February 18, 2015). AD 2015-03-06 requires actions 
intended to address an unsafe condition on all Airbus Model A330-200, 
A330-200 Freighter, A330-300, A340-200, A340-300, A340-500, and A340-
600 series airplanes.
    Since we issued AD 2015-03-06, Amendment 39-18102 (80 FR 8511, 
February 18, 2015), we have determined that it is necessary to 
introduce a more restrictive initial inspection threshold and a grace 
period for airplanes that have already exceeded the new threshold.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0120, dated June 26, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, A330-200 Freighter, A330-300, A340-200, A340-300, A340-500, 
and A340-600 series airplanes. The MCAI states:

    During Main Landing Gear (MLG) lubrication, a crack was visually 
found in the MLG rib 6 aft bearing forward lug on one A330 in-
service aeroplane. The crack had extended through the entire 
thickness of the forward lug at approximately the 4 o'clock position 
(when looking forward). It has been determined that a similar type 
of crack can develop on other aeroplane types that are listed in the 
Applicability paragraph.
    This condition, if not detected and corrected, could affect the 
structural integrity of the MLG attachment.
    To address this situation, Airbus issued inspection Service 
Bulletin (SB) A330-57-3096, SB A340-57-4104 and SB A340-57-5009 to 
provide instructions for repetitive inspections of the gear rib 
lugs.
    Prompted by these findings, EASA issued Emergency AD 2006-0364-E 
to require repetitive detailed visual inspections of the Left Hand 
(LH) and Right Hand (RH) wing MLG rib 6 aft bearing lugs.
    Later, EASA issued AD 2007-0247-E, which superseded [EASA] AD 
2006-0364-E, to:
    --expand the Applicability to all A330 and A340 aeroplanes, 
because the interference fit bushes cannot be considered as a 
terminating action, owing to unknown root cause; and
    --add a second parameter quoted in flight hours (FH) to the 
inspection interval in order to reflect the aeroplane utilisation in 
service.
    EASA AD 2007-0247-E was revised to correct a typographical 
error.
    Since the first crack finding and issuance of the inspection SBs 
and related ADs, six further cracks were reported.
    Consequently, EASA issued AD 2013-0271 [which corresponds to FAA 
AD 2015-03-06, Amendment 39-18102 (80 FR 8511, February 18, 2015)], 
which retained the requirements of [EASA] AD 2007-0247R1-E, which 
was superseded, and expanded the Applicability of the [EASA] AD to 
the newly certified models A330-223F and A330-243F. That AD also 
reduced the inspection threshold(s) to reflect the updated risk 
assessment and in-service experience.
    Since this [EASA] AD was issued, a new occurrence of crack 
finding was reported. Further analysis resulted in the need to 
reduce the threshold of the initial inspection.
    Prompted by this finding, Airbus issued SB A330-57-3096 Revision 
06 to introduce a more restrictive initial inspection threshold and 
a grace period for aeroplanes which have already passed the new 
threshold.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2013-0271, which is superseded, 
and introduces reduced initial inspection thresholds.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4815.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-57-3096, Revision 06, dated 
May 29, 2015. The service information describes procedures for detailed 
inspections to detect any cracking on the forward and aft lugs of the 
Left Hand (LH) and Right Hand (RH) wing MLG Rib 6. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this NPRM.

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.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD

[[Page 72400]]

compliance. The procedures and tests identified as Required for 
Compliance (RC) in any service information have a direct effect on 
detecting, preventing, resolving, or eliminating an identified unsafe 
condition.
    As specified in a Note under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in an airworthy condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 101 airplanes of U.S. 
registry.
    The actions required by AD 2015-03-06, Amendment 39-18102 (80 FR 
8511, February 18, 2015), and retained in this proposed AD take about 2 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2015-03-06 is $170 per product.
    This proposed AD reduces the initial compliance time but adds no 
new actions.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We 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.

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. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2015-03-06, Amendment 39-18102 (80 FR 8511, February 18, 2015), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-4815; Directorate Identifier 2015-NM-
112-AD.

(a) Comments Due Date

    We must receive comments by January 4, 2016.

(b) Affected ADs

    This AD replaces AD 2015-03-06, Amendment 39-18102 (80 FR 8511, 
February 18, 2015).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213 -311, -312, -313, 
-541, and -642 airplanes; certificated in any category; all 
manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracking of the main landing 
gear (MLG) rib 6 aft bearing forward lug. We are issuing this AD to 
detect and correct cracking of the MLG rib 6 aft bearing lugs, which 
could result in collapse of the MLG upon landing.

(f) Compliance

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

(g) Inspections

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Do a detailed inspection for cracking of the 
left-hand and right-hand wing MLG rib 6 aft bearing lugs (forward 
and aft), in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-57-3096, Revision 06, dated May 29, 
2015 (for Model A330-201, -202, -203, -223, -223F, -243, -243F, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes); 
A340-57-4104, Revision 04, dated October 17, 2013 (for Model A340-
211, -212, -213, -311, -312, -313 airplanes); or A340-57-5009, 
Revision 03, dated October 17, 2013 (for Model A340-541 and -642 
airplanes); as applicable.
    (1) Within 24 months or 2,000 flight cycles, whichever occurs 
first since airplane first flight or since the last MLG support rib 
replacement, as applicable.
    (2) Within 30 days after the effective date of this AD.

(h) Repetitive Inspections

    Repeat the inspection required by paragraph (g) of this AD 
thereafter at the time specified in paragraphs (h)(1) through (h)(7) 
of this AD, as applicable.
    (1) For Model A330-201, -202, -203, -223, and -243 airplanes: 
Repeat the inspections at intervals not to exceed 300 flight cycles 
or 1,500 flight hours, whichever occurs first.
    (2) For Model A330-223F and -243F airplanes: Repeat the 
inspections at intervals not to exceed 300 flight cycles or 900 
flight hours, whichever occurs first.
    (3) For Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes: Repeat the inspections at intervals not to 
exceed 300 flight cycles or 900 flight hours, whichever occurs 
first.
    (4) For Model A340-211, -212, and -213 airplanes: Repeat the 
inspections at intervals not to exceed 200 flight cycles or 800 
flight hours, whichever occurs first.
    (5) For Model A340-311 and -312 airplanes; and Model A340-313 
airplanes (except weight variant (WV) 27): Repeat the inspections at 
intervals not to exceed 200 flight cycles or 800 flight hours, 
whichever occurs first.
    (6) For Model A340-313 (only WV27) airplanes: Repeat the 
inspections at intervals

[[Page 72401]]

not to exceed 200 flight cycles or 400 flight hours, whichever 
occurs first.
    (7) For Model A340-541 and -642 airplanes: Repeat the 
inspections at intervals not to exceed 100 flight cycles or 500 
flight hours, whichever occurs first.

(i) Corrective Action

    If any crack is found during any inspection required by 
paragraphs (g) or (h) of this AD: Before further flight, replace the 
cracked MLG support rib using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA). Replacement of an MLG support 
rib does not terminate the repetitive inspections required by 
paragraph (h) of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using the applicable service 
information identified in paragraphs (j)(1) through (j)(15) of this 
AD.
    (1) Airbus Service Bulletin A330-57A3096, dated December 5, 
2006, which was incorporated by reference in AD 2007-03-04, 
Amendment 39-14915 (74 FR 4416, January 31, 2007).
    (2) Airbus Service Bulletin A330-57A3096, Revision 01, dated 
April 18, 2007, which is not incorporated by reference by this AD.
    (3) Airbus Service Bulletin A330-57-3096, Revision 02, dated 
August 13, 2007, which was incorporated by reference in AD 2007-22-
10, Amendment 39-15246 (72 FR 61796, November 1, 2007; corrected 
November 16, 2007 (72 FR 64532)).
    (4) Airbus Service Bulletin A330-57-3096, Revision 03, dated 
October 24, 2012, which is not incorporated by reference by this AD.
    (5) Airbus Service Bulletin A330-57-3096, Revision 04, dated 
February 6, 2013, which is not incorporated by reference in this AD.
    (6) Airbus Service Bulletin A330-57-3096, Revision 05, dated 
October 17, 2013, which was incorporated by reference in AD 2015-03-
06, Amendment 39-18102 (80 FR 8511, February 18, 2015).
    (7) Airbus Service Bulletin A340-57A4104, dated December 5, 
2006, which was incorporated by reference in AD 2007-03-04, 
Amendment 39-14915 (72 FR 4416, January 31, 2007).
    (8) Airbus Service Bulletin A340-57-4104, Revision 01, dated 
August 13, 2007, which is not incorporated by reference in this AD.
    (9) Airbus Service Bulletin A340-57-4104, Revision 02, dated 
September 5, 2007, which was incorporated by reference in AD 2007-
22-10, Amendment 39-15246 (72 FR 61796, November 1, 2007; corrected 
November 16, 2007 (72 FR 64532)).
    (10) Airbus Service Bulletin A340-57-4104, Revision 03, dated 
October 24, 2012, which is not incorporated by reference in this AD.
    (11) Airbus Service Bulletin A340-57A5009, dated December 5, 
2006, which was incorporated by reference in AD 2007-03-04, 
Amendment 39-14915 (72 FR 4416, January 31, 2007).
    (12) Airbus Service Bulletin A340-57-5009, Revision 01, dated 
August 13, 2007, which was incorporated by reference in AD 2007-22-
10, Amendment 39-15246 (72 FR 61796, November 1, 2007; corrected 
November 16, 2007 (72 FR 64532)).
    (13) Airbus Service Bulletin A340-57-5009, Revision 02, dated 
October 24, 2012, which is not incorporated by reference in this AD.
    (14) Airbus Alert Operators Transmission A57L005-14, dated July 
15, 2014, which is not incorporated by reference in this AD.
    (15) Airbus Alert Operators Transmission A57L005-14, Revision 
01, dated August 15, 2014, which is not incorporated by reference in 
this AD.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0120, dated June 26, 2015, 
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 Docket No. FAA-2015-4815.
    (2) 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 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 November 11, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-29442 Filed 11-18-15; 8:45 am]
BILLING CODE 4910-13-P