Airworthiness Directives; Airbus Airplanes, 35911-35914 [2017-16052]

Download as PDF 35911 Proposed Rules Federal Register Vol. 82, No. 147 Wednesday, August 2, 2017 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0714; Directorate Identifier 2017–NM–042–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) 2012–21– 04, which applies to all Airbus Model A300 series airplanes; Model A310 series airplanes; and 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). AD 2012–21–04 currently requires repetitive inspections for, and replacement of, any cracked hood halves of fuel pump canisters. Since we issued AD 2012–21–04, we allowed inspections of the outer tank and trim tank fuel pump canister hood halves to be terminated. However, we have received reports of new in-service events of outer tank fuel pump canister hood cracking. This proposed AD would retain the requirements of AD 2012–21– 04, reinstate the terminated inspections, and add optional terminating actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 18, 2017. jstallworth on DSKBBY8HB2PROD with PROPOSALS SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. ADDRESSES: VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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–2017– 0714; 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–2017–0714; Directorate Identifier 2017–NM–042–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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 October 25, 2012, we issued AD 2012–21–04, Amendment 39–17220 (77 FR 64701, October 23, 2012) (‘‘AD 2012–21–04’’), for all Airbus Model A300 series airplanes; Model A310 series airplanes; and Model A300 B4– 600, B4–600R, and Model A300–600 series airplanes. AD 2012–21–04 was prompted by reports of cracked fuel pump canister hoods located in fuel tanks. AD 2012–21–04 requires repetitive inspections for, and replacement of, any cracked hood halves of fuel pump canisters. We issued AD 2012–21–04 to prevent any detached canister hood fragments/debris from being ingested into the fuel feed system, and becoming a potential source of ignition with consequent fire or explosion. Since we issued AD 2012–21–04 (which corresponds to European Aviation Safety Agency (EASA) AD 2011–0124, dated June 30, 2011), EASA has issued EASA AD 2011–0124R1, dated September 5, 2014. That EASA AD introduced optional terminating action for the wing inner and center fuel tanks, and cancelled the repetitive inspections of the fuel pump canister hood halves in outer wing and trim tanks, for which no cracks had been reported following the initial inspection. The FAA provided a global alternative method of compliance (AMOC) to AD 2012–21–04 providing relief to operators from conducting the inspection for the fuel pump canister hoods in the outer wing and trim tanks. Since the FAA provided the global AMOC, we have received reports of new in-service events of outer tank fuel pump canister hood cracking. EASA has issued AD 2017–0051, dated March 23, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes; Model A310 series airplanes; E:\FR\FM\02AUP1.SGM 02AUP1 35912 Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules and Model A300–600 series airplanes. The MCAI states: Reports were received of finding cracked fuel pump canister hoods located in fuel tanks on in-service aeroplanes. Initial analyses, laboratory testing and examinations suggested that vibration-induced fatigue could have caused these cracks. However, initial data could not exclude some other potential contributing factors. This condition, if not detected and corrected, could lead to detached canister hood fragments or debris being ingested into the fuel feed system. In addition, metallic debris inside the fuel tank could result in a potential source of fuel vapour ignition, possibly resulting in a fire or fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, EASA issued AD 2011–0124 (later revised) [FAA AD 2012–21–04 corresponds to EASA AD 2011–0124] to require repetitive inspections of the canister hood halves installed on all fuel pump canisters and, if any damage was found, replacement. EASA AD 2011–0124R1 introduced an optional terminating action for the wing inner and centre fuel tanks, and cancelled the repetitive inspections of the fuel pump canister hoods in outer wing and trim tanks, for which no cracks had been reported following the initial inspection. Since that [EASA] AD was issued, new in service events of outer tank fuel pump canister hood cracking have been reported. Consequently, the canister hoods of the outer tank fuel pumps and trim tank fuel pumps will need to be inspected. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2011–0124R1, which is superseded, retaining the repetitive inspections of fuel pump canister hoods in wing inner and centre tanks, and reintroduces repetitive detailed inspections (DET) for outer tank and trim tank fuel pump canister hoods. This [EASA] AD also retains the existing optional terminating action for the repetitive DET of wing inner and centre tank fuel pump canister hoods, and introduces a new optional terminating action for the repetitive DET of the outer and trim tank fuel pump canister hoods required by this [EASA] AD. jstallworth on DSKBBY8HB2PROD with PROPOSALS 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–2017– 0714. FAA’s Determination and Requirements of This Proposed AD Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Mandatory Service Bulletin A300–28–0089, Revision 03, dated December 16, 2016. This service information describes procedures for repetitive detailed inspections of all fuel pump locations (center, wing-inner, and wing-outer tank), and replacing any cracked hood halves of fuel pump canisters. VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 • Airbus Service Bulletin A300–28– 0092, Revision 01, dated August 29, 2014; Airbus Service Bulletin A300–28– 6110, Revision 01, dated August 29, 2014; and Airbus Service Bulletin A310–28–2175, Revision 01, dated August 29, 2014. This service information describes procedures for replacement of the hood halves of the fuel pump canisters with newer design hood halves for the wing-inner tank and the center tank fuel pumps. These documents are distinct since they apply to different airplane models. • Airbus Service Bulletin A300–28– 0094, Revision 00, dated January 9, 2017. This service information describes procedures for replacement of the hood halves of the fuel pump canisters with newer design hood halves for the wingouter tank. • Airbus Mandatory Service Bulletin A300–28–6106, Revision 03, dated December 16, 2016; and Airbus Mandatory Service Bulletin A310–28– 2173, Revision 03, dated December 16, 2016. This service information describes procedures for repetitive detailed inspections of all fuel pump locations (center, wing-inner, wing-outer, and trim tank), and replacing any cracked hood halves of fuel pump canisters. These documents are distinct since they apply to different airplane models. • Airbus Service Bulletin A300–28– 6114, Revision 00, dated January 9, 2017; and Airbus Service Bulletin A310–28–2178, Revision 00, January 9, 2017. This service information describes procedures for replacement of the hood halves of the fuel pump canisters with newer design hood halves for the wingouter tank and the trim tank fuel pumps. These documents are distinct since they apply to different airplane models. 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. 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 these same type designs. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Costs of Compliance We estimate that this proposed AD affects 168 airplanes of U.S. registry. The actions required by AD 2012–21– 04, and retained in this proposed AD take about 12 work-hours per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are required by AD 2012–21–04 is $1,020 per product. We also estimate that it would take about 9 work-hours per product to comply with the new basic requirements of this proposed AD, at an average labor rate of $85 per work-hour. Based on these figures, we estimate the cost of the new basic requirements of this proposed AD on U.S. operators to be $128,520, or $765 per product. In addition, we estimate that the optional terminating actions would take about 1 work-hour and require parts costing $255, for a cost of $340 per product. We have no way of determining the number of aircraft that might need these actions. 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; E:\FR\FM\02AUP1.SGM 02AUP1 Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules 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 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) 2012–21–04, Amendment 39–17220 (77 FR 64701, October 23, 2012), and adding the following new AD: ■ Airbus: Docket No. FAA–2017–0714; Directorate Identifier 2017–NM–042–AD. (a) Comments Due Date We must receive comments by September 18, 2017. (b) Affected ADs This AD replaces AD 2012–21–04, Amendment 39–17220 (77 FR 64701, October 23, 2012) (‘‘AD 2012–21–04’’). jstallworth on DSKBBY8HB2PROD with PROPOSALS (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all certificated models, all manufacturer serial numbers. (1) Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 203 airplanes. (2) Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (3) Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes, Model A300 B4–605R and B4–622R airplanes, Model A300 F4–605R and F4–622R airplanes, and Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. (e) Reason This AD was prompted by reports of cracked fuel pump canister hoods located in fuel tanks and new in-service events of outer tank fuel pump canister hood cracking. We VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 are issuing this AD to prevent any detached canister hood fragments/debris from being ingested into the fuel feed system, and becoming a potential source of ignition with consequent fire or explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Initial Inspection and Replacement, With Revised Requirements and Service Information This paragraph restates the requirements of paragraph (g) of AD 2012–21–04, with revised service information. Within 30 months after November 27, 2012 (the effective date of AD 2012–21–04), do a detailed inspection for cracking of the fuel pump canister hood halves installed on all wing center and inner tank fuel pump canisters having part numbers (P/N) 2052C11, 2052C12, and C93R51–601, in accordance with the Accomplishment Instructions of the service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. If any crack is found on any fuel pump canister hood half during any inspection, before further flight, replace the fuel pump canister hood half, in accordance with the Accomplishment Instructions of the service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable. (1) For Model A300 series airplanes: Airbus Mandatory Service Bulletin A300–28– 0089, Revision 01, including Inspection Findings—Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin A300–28– 0089, Revision 03, dated December 16, 2016. As of the effective date of this AD, only use Airbus Service Bulletin A300–28–0089, Revision 03, dated December 16, 2016. (2) For Model A300–600 series airplanes: Airbus Mandatory Service Bulletin A300–28– 6106, Revision 01, including Inspection Findings—Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin A300–28– 6106, Revision 03, dated December 16, 2016. As of the effective date of this AD, only use Airbus Service Bulletin A300–28–6106, Revision 03, dated December 16, 2016. (3) For Model A310 series airplanes: Airbus Mandatory Service Bulletin A310–28– 2173, Revision 01, including Inspection Findings—Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin A310–28– 2173, Revision 03, dated December 16, 2016. As of the effective date of this AD, only use Airbus Service Bulletin A310–28–2173, Revision 03, dated December 16, 2016. (h) Retained Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2012–21–04, with no changes. Within 30 months after accomplishing the actions specified in paragraph (g) of this AD, and thereafter at intervals not to exceed 30 months, repeat the detailed inspection specified in paragraph (g) of this AD. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 35913 (i) New Repetitive Inspections and Replacement of the Outer Tank and Trim Tank Fuel Pump Canister Hood Halves Within 30 months after the effective date of this AD, do a detailed inspection for cracking of the outer tank and trim tank, as applicable, fuel pump canister hood halves installed on all fuel pump canisters having part numbers (P/N) 2052C11, 2052C12, and C93R51–601, in accordance with the Accomplishment Instructions of the service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable. Repeat the inspection thereafter at intervals not to exceed 30 months. If any crack is found on any fuel pump canister hood half during any inspection, before further flight, replace the fuel pump canister hood half, in accordance with the Accomplishment Instructions of the service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable. (1) For Model A300 series airplanes: Airbus Service Bulletin A300–28–0089, Revision 03, dated December 16, 2016. (2) For Model A300–600 series airplanes: Airbus Service Bulletin A300–28–6106, Revision 03, dated December 16, 2016. (3) For Model A310 series airplanes: Airbus Service Bulletin A310–28–2173, Revision 03, dated December 16, 2016. (j) New Optional Terminating Actions Replacement of the fuel pump canister hood halves installed on all fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51–601, constitutes terminating action for the inspections required by paragraphs (g) and (h) of this AD. The replacement of the fuel pump canister hood halves must be done in accordance with the Accomplishment Instructions of the service information specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. (1) For Model A300 series airplanes: Airbus Service Bulletin A300–28–0092, Revision 01, dated August 29, 2014 (for wing center and inner tank fuel pump canister hood halves); and Airbus Service Bulletin A300–28–0094, Revision 00, dated January 9, 2017 (for outer tank fuel pump canister hood halves). (2) For Model A300–600 series airplanes: Airbus Service Bulletin A300–28–6110, Revision 01, dated August 29, 2014 (for wing center and inner tank fuel pump canister hood halves); and Airbus Service Bulletin A300–28–6114, Revision 00, dated January 9, 2017 (for outer tank and trim tank fuel pump canister hood halves). (3) For Model A310 series airplanes: Airbus Service Bulletin A310–28–2175, Revision 01, dated August 29, 2014 (for wing center and inner tank fuel pump canister hood halves); and Airbus Service Bulletin A310–28–2178, Revision 00, January 9, 2017 (for outer tank and trim tank fuel pump canister hood halves). (k) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD. (i) Airbus Service Bulletin A300–28–0089, dated January 13, 2011; or Airbus Service E:\FR\FM\02AUP1.SGM 02AUP1 35914 Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / Proposed Rules jstallworth on DSKBBY8HB2PROD with PROPOSALS Bulletin A300–28–0089, Revision 02, dated April 25, 2014. (ii) Airbus Service Bulletin A300–28–6106, dated January 13, 2011; or Airbus Service Bulletin A300–28–6106, Revision 02, dated April 25, 2014. (iii) Airbus Service Bulletin A310–28– 2173, dated January 13, 2011; or Airbus Mandatory Service Bulletin A310–28–2173, Revision 02, dated April 25, 2014. (2) This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD. (i) Airbus Service Bulletin A300–28–0089, dated January 13, 2011; Airbus Service Bulletin A300–28–0089, Revision 01, dated April 15, 2011; or Airbus Service Bulletin A300–28–0089, Revision 02, dated April 25, 2014. (ii) Airbus Service Bulletin A300–28–6106, dated January 13, 2011; Airbus Service Bulletin A300–28–6106, Revision 01, dated April 15, 2011; or Airbus Service Bulletin A300–28–6106, Revision 02, dated April 25, 2014. (iii) Airbus Service Bulletin A310–28– 2173, dated January 13, 2011; Airbus Service Bulletin A310–28–2173, Revision 01, dated April 15, 2011; or Airbus Service Bulletin A310–28–2173, Revision 02, dated April 25, 2014. (3) This paragraph provides credit for the actions specified in paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–28–6110, Revision 00, dated November 28, 2013. (l) Other FAA AD Provisions (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 the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (ii) AMOCs approved previously for AD 2012–21–04, Amendment 39–17220 (77 FR 64701, October 23, 2012), are not approved as AMOCs with 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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by VerDate Sep<11>2014 15:16 Aug 01, 2017 Jkt 241001 the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0051, dated March 23, 2017, 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–2017–0714. (2) For more information about this AD, 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. (3) 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 July 19, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–16052 Filed 8–1–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0020; Directorate Identifier 2016–NE–33–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Honeywell International Inc. AS907 series turbofan engines. This proposed AD was prompted by two loss-of-thrustcontrol events, and two in-flight shutdowns (IFSDs) of new production, low-time engines attributed to water intrusion of the engine electronic control unit (ECU). This proposed AD would require applying sealant to identified areas of the ECU and requires inserting a copy of certain airplane operating procedures into the applicable flight manuals. We are proposing this SUMMARY: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 18, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: 800– 601–3099; Internet: https:// myaerospace.honeywell.com/wps/ portal/!ut/. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (781) 238– 7125. 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–2017– 0020; 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627–5246; fax: 562–627–5210; email: joseph.costa@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this NPRM. Send your comments to an address listed under the ADDRESSES E:\FR\FM\02AUP1.SGM 02AUP1

Agencies

[Federal Register Volume 82, Number 147 (Wednesday, August 2, 2017)]
[Proposed Rules]
[Pages 35911-35914]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16052]


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Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 82, No. 147 / Wednesday, August 2, 2017 / 
Proposed Rules

[[Page 35911]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0714; Directorate Identifier 2017-NM-042-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) 2012-21-
04, which applies to all Airbus Model A300 series airplanes; Model A310 
series airplanes; and 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). AD 2012-21-04 currently 
requires repetitive inspections for, and replacement of, any cracked 
hood halves of fuel pump canisters. Since we issued AD 2012-21-04, we 
allowed inspections of the outer tank and trim tank fuel pump canister 
hood halves to be terminated. However, we have received reports of new 
in-service events of outer tank fuel pump canister hood cracking. This 
proposed AD would retain the requirements of AD 2012-21-04, reinstate 
the terminated inspections, and add optional terminating actions. We 
are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by September 18, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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-2017-
0714; 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-2017-0714; 
Directorate Identifier 2017-NM-042-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 October 25, 2012, we issued AD 2012-21-04, Amendment 39-17220 
(77 FR 64701, October 23, 2012) (``AD 2012-21-04''), for all Airbus 
Model A300 series airplanes; Model A310 series airplanes; and Model 
A300 B4-600, B4-600R, and Model A300-600 series airplanes. AD 2012-21-
04 was prompted by reports of cracked fuel pump canister hoods located 
in fuel tanks. AD 2012-21-04 requires repetitive inspections for, and 
replacement of, any cracked hood halves of fuel pump canisters. We 
issued AD 2012-21-04 to prevent any detached canister hood fragments/
debris from being ingested into the fuel feed system, and becoming a 
potential source of ignition with consequent fire or explosion.
    Since we issued AD 2012-21-04 (which corresponds to European 
Aviation Safety Agency (EASA) AD 2011-0124, dated June 30, 2011), EASA 
has issued EASA AD 2011-0124R1, dated September 5, 2014. That EASA AD 
introduced optional terminating action for the wing inner and center 
fuel tanks, and cancelled the repetitive inspections of the fuel pump 
canister hood halves in outer wing and trim tanks, for which no cracks 
had been reported following the initial inspection. The FAA provided a 
global alternative method of compliance (AMOC) to AD 2012-21-04 
providing relief to operators from conducting the inspection for the 
fuel pump canister hoods in the outer wing and trim tanks. Since the 
FAA provided the global AMOC, we have received reports of new in-
service events of outer tank fuel pump canister hood cracking.
    EASA has issued AD 2017-0051, dated March 23, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; Model A310 series airplanes;

[[Page 35912]]

and Model A300-600 series airplanes. The MCAI states:

    Reports were received of finding cracked fuel pump canister 
hoods located in fuel tanks on in-service aeroplanes. Initial 
analyses, laboratory testing and examinations suggested that 
vibration-induced fatigue could have caused these cracks. However, 
initial data could not exclude some other potential contributing 
factors.
    This condition, if not detected and corrected, could lead to 
detached canister hood fragments or debris being ingested into the 
fuel feed system. In addition, metallic debris inside the fuel tank 
could result in a potential source of fuel vapour ignition, possibly 
resulting in a fire or fuel tank explosion and consequent loss of 
the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2011-
0124 (later revised) [FAA AD 2012-21-04 corresponds to EASA AD 2011-
0124] to require repetitive inspections of the canister hood halves 
installed on all fuel pump canisters and, if any damage was found, 
replacement. EASA AD 2011-0124R1 introduced an optional terminating 
action for the wing inner and centre fuel tanks, and cancelled the 
repetitive inspections of the fuel pump canister hoods in outer wing 
and trim tanks, for which no cracks had been reported following the 
initial inspection.
    Since that [EASA] AD was issued, new in service events of outer 
tank fuel pump canister hood cracking have been reported. 
Consequently, the canister hoods of the outer tank fuel pumps and 
trim tank fuel pumps will need to be inspected.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0124R1, which is superseded, retaining 
the repetitive inspections of fuel pump canister hoods in wing inner 
and centre tanks, and reintroduces repetitive detailed inspections 
(DET) for outer tank and trim tank fuel pump canister hoods. This 
[EASA] AD also retains the existing optional terminating action for 
the repetitive DET of wing inner and centre tank fuel pump canister 
hoods, and introduces a new optional terminating action for the 
repetitive DET of the outer and trim tank fuel pump canister hoods 
required by this [EASA] AD.

    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-2017-
0714.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Mandatory Service Bulletin A300-28-0089, Revision 
03, dated December 16, 2016. This service information describes 
procedures for repetitive detailed inspections of all fuel pump 
locations (center, wing-inner, and wing-outer tank), and replacing any 
cracked hood halves of fuel pump canisters.
     Airbus Service Bulletin A300-28-0092, Revision 01, dated 
August 29, 2014; Airbus Service Bulletin A300-28-6110, Revision 01, 
dated August 29, 2014; and Airbus Service Bulletin A310-28-2175, 
Revision 01, dated August 29, 2014. This service information describes 
procedures for replacement of the hood halves of the fuel pump 
canisters with newer design hood halves for the wing-inner tank and the 
center tank fuel pumps. These documents are distinct since they apply 
to different airplane models.
     Airbus Service Bulletin A300-28-0094, Revision 00, dated 
January 9, 2017. This service information describes procedures for 
replacement of the hood halves of the fuel pump canisters with newer 
design hood halves for the wing-outer tank.
     Airbus Mandatory Service Bulletin A300-28-6106, Revision 
03, dated December 16, 2016; and Airbus Mandatory Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016. This service 
information describes procedures for repetitive detailed inspections of 
all fuel pump locations (center, wing-inner, wing-outer, and trim 
tank), and replacing any cracked hood halves of fuel pump canisters. 
These documents are distinct since they apply to different airplane 
models.
     Airbus Service Bulletin A300-28-6114, Revision 00, dated 
January 9, 2017; and Airbus Service Bulletin A310-28-2178, Revision 00, 
January 9, 2017. This service information describes procedures for 
replacement of the hood halves of the fuel pump canisters with newer 
design hood halves for the wing-outer tank and the trim tank fuel 
pumps. These documents are distinct since they apply to different 
airplane models.
    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.

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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 168 airplanes of U.S. 
registry.
    The actions required by AD 2012-21-04, and retained in this 
proposed AD take about 12 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 2012-21-04 is $1,020 per 
product.
    We also estimate that it would take about 9 work-hours per product 
to comply with the new basic requirements of this proposed AD, at an 
average labor rate of $85 per work-hour. Based on these figures, we 
estimate the cost of the new basic requirements of this proposed AD on 
U.S. operators to be $128,520, or $765 per product.
    In addition, we estimate that the optional terminating actions 
would take about 1 work-hour and require parts costing $255, for a cost 
of $340 per product. We have no way of determining the number of 
aircraft that might need these actions.

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;

[[Page 35913]]

    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) 
2012-21-04, Amendment 39-17220 (77 FR 64701, October 23, 2012), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0714; Directorate Identifier 2017-NM-
042-AD.

(a) Comments Due Date

    We must receive comments by September 18, 2017.

(b) Affected ADs

    This AD replaces AD 2012-21-04, Amendment 39-17220 (77 FR 64701, 
October 23, 2012) (``AD 2012-21-04'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all certificated models, all manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.
    (3) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by reports of cracked fuel pump canister 
hoods located in fuel tanks and new in-service events of outer tank 
fuel pump canister hood cracking. We are issuing this AD to prevent 
any detached canister hood fragments/debris from being ingested into 
the fuel feed system, and becoming a potential source of ignition 
with consequent fire or explosion.

(f) Compliance

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

(g) Retained Initial Inspection and Replacement, With Revised 
Requirements and Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-21-04, with revised service information. Within 30 months after 
November 27, 2012 (the effective date of AD 2012-21-04), do a 
detailed inspection for cracking of the fuel pump canister hood 
halves installed on all wing center and inner tank fuel pump 
canisters having part numbers (P/N) 2052C11, 2052C12, and C93R51-
601, in accordance with the Accomplishment Instructions of the 
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD, as applicable. If any crack is found on any fuel pump 
canister hood half during any inspection, before further flight, 
replace the fuel pump canister hood half, in accordance with the 
Accomplishment Instructions of the service bulletin specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Mandatory Service 
Bulletin A300-28-0089, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A300-28-
0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Mandatory 
Service Bulletin A300-28-6106, Revision 01, including Inspection 
Findings--Reporting Sheet, dated April 15, 2011; or Airbus Service 
Bulletin A300-28-6106, Revision 03, dated December 16, 2016. As of 
the effective date of this AD, only use Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Mandatory Service 
Bulletin A310-28-2173, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A310-28-
2173, Revision 03, dated December 16, 2016.

(h) Retained Repetitive Inspections, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-21-04, with no changes. Within 30 months after accomplishing 
the actions specified in paragraph (g) of this AD, and thereafter at 
intervals not to exceed 30 months, repeat the detailed inspection 
specified in paragraph (g) of this AD.

(i) New Repetitive Inspections and Replacement of the Outer Tank and 
Trim Tank Fuel Pump Canister Hood Halves

    Within 30 months after the effective date of this AD, do a 
detailed inspection for cracking of the outer tank and trim tank, as 
applicable, fuel pump canister hood halves installed on all fuel 
pump canisters having part numbers (P/N) 2052C11, 2052C12, and 
C93R51-601, in accordance with the Accomplishment Instructions of 
the service bulletin specified in paragraph (i)(1), (i)(2), or 
(i)(3) of this AD, as applicable. Repeat the inspection thereafter 
at intervals not to exceed 30 months. If any crack is found on any 
fuel pump canister hood half during any inspection, before further 
flight, replace the fuel pump canister hood half, in accordance with 
the Accomplishment Instructions of the service bulletin specified in 
paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016.

(j) New Optional Terminating Actions

    Replacement of the fuel pump canister hood halves installed on 
all fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-
601, constitutes terminating action for the inspections required by 
paragraphs (g) and (h) of this AD. The replacement of the fuel pump 
canister hood halves must be done in accordance with the 
Accomplishment Instructions of the service information specified in 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0092, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-0094, Revision 00, dated January 9, 2017 (for outer 
tank fuel pump canister hood halves).
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6110, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-6114, Revision 00, dated January 9, 2017 (for outer 
tank and trim tank fuel pump canister hood halves).
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2175, Revision 01, dated August 29, 2014 (for wing center 
and inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A310-28-2178, Revision 00, January 9, 2017 (for outer tank 
and trim tank fuel pump canister hood halves).

(k) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; or Airbus Service

[[Page 35914]]

Bulletin A300-28-0089, Revision 02, dated April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; or Airbus Service Bulletin A300-28-6106, Revision 02, dated 
April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; or Airbus Mandatory Service Bulletin A310-28-2173, Revision 
02, dated April 25, 2014.
    (2) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the service information specified in 
paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; Airbus Service Bulletin A300-28-0089, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A300-28-0089, Revision 02, 
dated April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; Airbus Service Bulletin A300-28-6106, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A300-28-6106, Revision 02, 
dated April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; Airbus Service Bulletin A310-28-2173, Revision 01, dated April 
15, 2011; or Airbus Service Bulletin A310-28-2173, Revision 02, 
dated April 25, 2014.
    (3) This paragraph provides credit for the actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A300-28-
6110, Revision 00, dated November 28, 2013.

(l) Other FAA AD Provisions

    (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 the attention of 
the person identified in paragraph (m)(2) of this AD. 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.
    (ii) AMOCs approved previously for AD 2012-21-04, Amendment 39-
17220 (77 FR 64701, October 23, 2012), are not approved as AMOCs 
with 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 European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (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) EASA AD 2017-0051, dated March 23, 2017, 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-2017-0714.
    (2) For more information about this AD, 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.
    (3) 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 July 19, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-16052 Filed 8-1-17; 8:45 am]
 BILLING CODE 4910-13-P