Airworthiness Directives; Airbus Airplanes, 72395-72398 [2015-29443]

Download as PDF Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2015–5808; Directorate Identifier 2015– NM–111–AD. (a) Comments Due Date We must receive comments by January 4, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 series airplanes, certificated in any category, as identified in the service information specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Boeing Alert Service Bulletin B787– 81205–SB380009–00, Issue 001, dated March 26, 2015. (2) Boeing Alert Service Bulletin B787– 81205–SB530029–00, Issue 001, dated March 26, 2015. (3) Boeing Alert Service Bulletin B787– 81205–SB530031–00, Issue 001, dated March 26, 2015. (d) Subject Air Transport Association (ATA) of America Code 38, Water/Waste; and Code 53, Fuselage. (e) Unsafe Condition This proposed AD was prompted by reports of water leakage from the potable water system due to improperly installed waterline couplings, and water leaking into the electronics equipment (EE) bays from above the floor in the main cabin, resulting in water on the equipment in the EE bays. We are issuing this AD to prevent a water leak from an improperly installed potable water system coupling, or main cabin water source, which could cause the equipment in the EE bays to become wet, resulting in an electrical short and potential loss of system functions essential for safe flight. (f) Compliance Comply with this AD within the compliance times specified, unless already done. rmajette on DSK2TPTVN1PROD with PROPOSALS (g) Replace Potable Waterline Couplings Within 24 months after the effective date of this AD: Replace the existing potable waterline couplings located above the forward and aft EE bays with new, improved couplings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB380009–00, Issue 001, dated March 26, 2015. Before further flight after doing the replacement, do a potable water system leak test and repair any leaks found before further flight, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB380009–00, Issue 001, dated March 26, 2015. VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 (h) Seal Floor Panels and Seat Tracks/Install Drip Shields and Reroute Wiring Within 60 months after the effective date of this AD: Do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Apply sealant to the main cabin floor areas located above the aft EE bay, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205–SB530029–00, Issue 001, dated March 26, 2015. (2) Install drip shields and foam blocks, and reroute the wire bundles above the equipment in the aft EE bay, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787–81205– SB530031–00, Issue 001, dated March 26, 2015. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, alteration, or modification required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact Susan L. Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 72395 Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6457; fax: 425–917–6590; email: susan.l.monroe@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–29441 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–2015–4817; Directorate Identifier 2014–NM–115–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) 95–18–08, for all Airbus Model A300–600 series airplanes. AD 95–18–08 currently requires repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, and repair if necessary. Since we issued AD 95–18– 08, we received a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. This proposed AD would, for certain airplanes, reduce the compliance times for the inspections. We are proposing this AD to detect and correct such fatigue-related cracking, which could result in reduced structural integrity of the wing. 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. SUMMARY: E:\FR\FM\19NOP1.SGM 19NOP1 72396 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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– 4817; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–4817; Directorate Identifier 2014–NM–115–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. VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 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 August 29, 1995, we issued AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995). AD 95–18– 08 requires actions intended to address an unsafe condition on all Airbus Model A300–600 series airplanes (which includes Airbus Model A300 C4–605R Variant F airplanes, Model A300 B4– 622 airplanes, and Model A300 F4– 622R airplanes that were added to the U.S. Type Certificate Data Sheet since issuance of AD 95–18–08). Since we issued AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), we received a report that updated fatigue and damage tolerance analyses and a fleet survey done to support a second extended service goal for Model A300–600 series airplanes found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0119, dated May 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes). The MCAI states: Full-scale fatigue tests carried out on the A300–600 test specimen by Airbus revealed crack initiation in the bottom skin adjacent to the aft pylon attachment fitting. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this unsafe condition, DGAC ´ ´ [Direction Generale de l’Aviation Civile] France issued AD 94–069–158(B) (http:// ad.easa.europa.eu/blob/1994069158tb_ superseded.pdf/AD_F-1994-069-158_2) [which corresponds to FAA AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995)] to require repetitive detailed visual inspections (DVI) of the wing bottom skin in the area of the cut-out for the pylon rear attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to detect cracks, and repair if necessary]. Since that [DGAC] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300–600 Extended Service Goal (ESG2) exercise. As a PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 result, it was revealed that the inspection threshold and interval must be reduced to allow timely detection of cracks and the accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued Revision 07 of Service Bulletin (SB) A300–57–6028. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 94–069–158(B), which is superseded, but reduces the inspection thresholds and intervals [e.g., compliance times]. 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– 4817. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A300–57–6028, Revision 07, dated June 6, 2011. The service information describes procedures for inspections to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, and repair. 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. Costs of Compliance We estimate that this proposed AD affects 124 airplanes of U.S. registry. The actions that are required by AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), and retained in this proposed AD take about 6 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 95– 18–08 is $510 per product. In addition, we estimate that any necessary follow-on actions would take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of E:\FR\FM\19NOP1.SGM 19NOP1 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules determining the number of aircraft that might need these actions. The new requirements of this proposed AD add no additional economic burden. 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. 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. rmajette on DSK2TPTVN1PROD with PROPOSALS 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: VerDate Sep<11>2014 14:08 Nov 18, 2015 Jkt 238001 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), and adding the following new AD: ■ Airbus: Docket No. FAA–2015–4817; Directorate Identifier 2014–NM–115–AD. (a) Comments Due Date We must receive comments by January 4, 2016. (b) Affected ADs This AD replaces AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (2) Airbus Model A300 B4–605R and B4– 622R airplanes. (3) Airbus Model A300 F4–605R and F4– 622R airplanes. (4) Airbus Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct such fatigue-related cracking, which could result in reduced structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Action With Additional Repair Information This paragraph restates the requirements of paragraph (a) of AD 95–18–08, Amendment 39–9355 (60 FR 47677, September 14, 1995), with additional repair contact information. Prior to the accumulation of 24,000 total flight cycles since date of manufacture of the airplane, or within 750 flight cycles after October 16, 1995 (the effective date of AD 95–18–08), whichever occurs later, perform a detailed visual inspection to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, in accordance with Airbus Service Bulletin A300–57–6028, Revision 3, dated September PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 72397 13, 1994. Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles. If any crack is detected, prior to further flight, repair the wing bottom skin in accordance with a method approved by the Manager, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate, or 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). Accomplishing any inspection required by paragraph (h) of this AD terminates the inspections required by this paragraph. (h) New Requirement of This AD: Revised Inspection Thresholds and Intervals Within the applicable compliance times required in paragraphs (h)(1) and (h)(2) of this AD, do a detailed visual inspection of the wing bottom skin in the area of the cutout for the pylon rear attachment fitting on left-hand and right-hand wings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–6028, Revision 07, dated June 6, 2011. Repeat the inspections thereafter at the applicable intervals required in paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) For ‘‘normal range operations’’ airplanes having an average flight time of 1.5 flight hours or more: Do the inspection at the applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) For Model A300 F4–605R and F4–622R airplanes: Do the inspection at the later of the times specified in paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD. (A) Within 24,000 flight cycles or 51,800 flight hours after first flight of the airplane, whichever occurs first. (B) Within 2,000 flight cycles or 4,300 flight hours after the effective date of this AD, whichever occurs first. (ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Do the inspection at the later of the times specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD. (A) Within 19,100 flight cycles or 41,200 flight hours after first flight of the airplane, whichever occurs first. (B) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For ‘‘short range operations’’ airplanes having an average flight time of less than 1.5 flight hours: Do the inspection at the applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) For Model A300 F4–605R and F4–622R airplanes: Do the inspection at the later of the times specified in paragraphs (h)(2)(i)(A) and (h)(2)(i)(B) of this AD. (A) Within 25,900 flight cycles or 38,800 flight hours after first flight of the airplane, whichever occurs first. (B) Within 2,100 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (ii) For Model A300 B4–600, B4–600R, and Model A300 C4–605R Variant F airplanes: Do E:\FR\FM\19NOP1.SGM 19NOP1 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

Agencies

[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72395-72398]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29443]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-115-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 95-18-08, 
for all Airbus Model A300-600 series airplanes. AD 95-18-08 currently 
requires repetitive inspections to detect cracks in the bottom skin of 
the wing in the area of the cut out for the pylon rear attachment 
fitting, and repair if necessary. Since we issued AD 95-18-08, we 
received a report that updated fatigue and damage tolerance analyses 
and a fleet survey found that certain inspection thresholds and 
intervals must be reduced to allow more timely findings of cracking. 
This proposed AD would, for certain airplanes, reduce the compliance 
times for the inspections. We are proposing this AD to detect and 
correct such fatigue-related cracking, which could result in reduced 
structural integrity of the wing.

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.

[[Page 72396]]

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4817; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-4817; 
Directorate Identifier 2014-NM-115-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 August 29, 1995, we issued AD 95-18-08, Amendment 39-9355 (60 FR 
47677, September 14, 1995). AD 95-18-08 requires actions intended to 
address an unsafe condition on all Airbus Model A300-600 series 
airplanes (which includes Airbus Model A300 C4-605R Variant F 
airplanes, Model A300 B4-622 airplanes, and Model A300 F4-622R 
airplanes that were added to the U.S. Type Certificate Data Sheet since 
issuance of AD 95-18-08).
    Since we issued AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995), we received a report that updated fatigue and 
damage tolerance analyses and a fleet survey done to support a second 
extended service goal for Model A300-600 series airplanes found that 
certain inspection thresholds and intervals must be reduced to allow 
more timely findings of cracking.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0119, dated May 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes). The MCAI states:

    Full-scale fatigue tests carried out on the A300-600 test 
specimen by Airbus revealed crack initiation in the bottom skin 
adjacent to the aft pylon attachment fitting.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 94-
069-158(B) (http://ad.easa.europa.eu/blob/1994069158tb_superseded.pdf/AD_F-1994-069-158_2) [which corresponds 
to FAA AD 95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 
1995)] to require repetitive detailed visual inspections (DVI) of 
the wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on Left Hand (LH) and Right Hand (RH) wings [to 
detect cracks, and repair if necessary].
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. As a result, it was revealed that the inspection threshold 
and interval must be reduced to allow timely detection of cracks and 
the accomplishment of an applicable corrective action. Prompted by 
these findings, Airbus issued Revision 07 of Service Bulletin (SB) 
A300-57-6028.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 94-069-158(B), which is superseded, 
but reduces the inspection thresholds and intervals [e.g., 
compliance times].

    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-
4817.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-57-6028, Revision 07, 
dated June 6, 2011. The service information describes procedures for 
inspections to detect cracks in the bottom skin of the wing in the area 
of the cut out for the pylon rear attachment fitting, and repair. 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.

Costs of Compliance

    We estimate that this proposed AD affects 124 airplanes of U.S. 
registry.
    The actions that are required by AD 95-18-08, Amendment 39-9355 (60 
FR 47677, September 14, 1995), and retained in this proposed AD take 
about 6 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 95-18-08 is $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of

[[Page 72397]]

determining the number of aircraft that might need these actions.
    The new requirements of this proposed AD add no additional economic 
burden.

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) 
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-4817; Directorate Identifier 2014-NM-
115-AD.

(a) Comments Due Date

    We must receive comments by January 4, 2016.

(b) Affected ADs

    This AD replaces AD 95-18-08, Amendment 39-9355 (60 FR 47677, 
September 14, 1995).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that updated fatigue and damage 
tolerance analyses and a fleet survey found that certain inspection 
thresholds and intervals must be reduced to allow more timely 
findings of cracking. We are issuing this AD to detect and correct 
such fatigue-related cracking, which could result in reduced 
structural integrity of the wing.

(f) Compliance

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

(g) Retained Inspection and Corrective Action With Additional Repair 
Information

    This paragraph restates the requirements of paragraph (a) of AD 
95-18-08, Amendment 39-9355 (60 FR 47677, September 14, 1995), with 
additional repair contact information. Prior to the accumulation of 
24,000 total flight cycles since date of manufacture of the 
airplane, or within 750 flight cycles after October 16, 1995 (the 
effective date of AD 95-18-08), whichever occurs later, perform a 
detailed visual inspection to detect cracks in the bottom skin of 
the wing in the area of the cut out for the pylon rear attachment 
fitting, in accordance with Airbus Service Bulletin A300-57-6028, 
Revision 3, dated September 13, 1994. Repeat the inspection 
thereafter at intervals not to exceed 9,000 flight cycles. If any 
crack is detected, prior to further flight, repair the wing bottom 
skin in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate, or 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). 
Accomplishing any inspection required by paragraph (h) of this AD 
terminates the inspections required by this paragraph.

(h) New Requirement of This AD: Revised Inspection Thresholds and 
Intervals

    Within the applicable compliance times required in paragraphs 
(h)(1) and (h)(2) of this AD, do a detailed visual inspection of the 
wing bottom skin in the area of the cut-out for the pylon rear 
attachment fitting on left-hand and right-hand wings, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-57-6028, Revision 07, dated June 6, 2011. Repeat the 
inspections thereafter at the applicable intervals required in 
paragraphs (h)(3) and (h)(4) of this AD. Accomplishing any 
inspection required by this paragraph terminates the inspections 
required by paragraph (g) of this AD.
    (1) For ``normal range operations'' airplanes having an average 
flight time of 1.5 flight hours or more: Do the inspection at the 
applicable time required in paragraphs (h)(1)(i) and (h)(1)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(1)(i)(A) and (h)(1)(i)(B) of this AD.
    (A) Within 24,000 flight cycles or 51,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,000 flight cycles or 4,300 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do the inspection at the later of the times 
specified in paragraphs (h)(1)(ii)(A) and (h)(1)(ii)(B) of this AD.
    (A) Within 19,100 flight cycles or 41,200 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 1,500 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For ``short range operations'' airplanes having an average 
flight time of less than 1.5 flight hours: Do the inspection at the 
applicable time required in paragraphs (h)(2)(i) and (h)(2)(ii) of 
this AD.
    (i) For Model A300 F4-605R and F4-622R airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(h)(2)(i)(A) and (h)(2)(i)(B) of this AD.
    (A) Within 25,900 flight cycles or 38,800 flight hours after 
first flight of the airplane, whichever occurs first.
    (B) Within 2,100 flight cycles or 3,200 flight hours after the 
effective date of this AD, whichever occurs first.
    (ii) For Model A300 B4-600, B4-600R, and Model A300 C4-605R 
Variant F airplanes: Do

[[Page 72398]]

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.

(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 (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.

(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-116-AMOC-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.

    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