Airworthiness Directives; Airbus Airplanes, 1623-1626 [2016-31960]

Download as PDF Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules Revision 21, dated June 2011. The initial compliance times for the tasks are at the applicable times specified in Section 05–40/ 00, Airworthiness Limitations, of Chapter 5– 40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 21, dated June 2011, or within 30 days after March 19, 2013, whichever occurs later. (h) Retained Provision Regarding Alternative Actions, Intervals, and Critical Design Configuration Control Limitations (CDCCLs), With New Exception This paragraph restates the requirements of paragraph (h) of AD 2013–03–12, with a new exception. Except as required by paragraph (i) of this AD: After accomplishing the revisions required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used other than those specified in Section 05–40/00, Airworthiness Limitations, of Chapter 5–40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 21, dated June 2011, unless the actions, intervals, and/or CDCCLs are approved as an alternative methods of compliance (AMOC) in accordance with the procedures specified in paragraph (l)(1) of this AD. (i) New Maintenance or Inspection Program Revision Within 30 days after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate airworthiness limitations, maintenance tasks, and associated thresholds and intervals specified in Section 05–40/00, Airworthiness Limitations, of Chapter 5–40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 23, dated July 2015. The initial compliance times for the tasks are at the applicable times specified in Section 05–40/ 00, Airworthiness Limitations, of Chapter 5– 40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 23, dated July 2015, or within 30 days after the effective date of this AD, whichever occurs later. Accomplishing the revision of the maintenance or inspection program required by this paragraph terminates the requirements of paragraph (g) of this AD. sradovich on DSK3GMQ082PROD with PROPOSALS (j) New Provision Regarding Alternative Actions and Intervals After the maintenance or inspection program has been revised as required by paragraph (i) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions and intervals are approved as an AMOC in accordance with the procedures specified in paragraph (l)(1) of this AD. (k) Terminating Action for Certain ADs Accomplishing the actions required by paragraph (g) or (i) of this AD terminates all requirements of AD 2010–26–05 and AD 2012–02–18 for the Dassault Aviation Model MYSTERE–FALCON 50 airplanes specified in those ADs. VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 (l) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 Dassault Aviation’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 Airworthiness Directive 2016–0067, dated April 7, 2016, 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– 2016–9569. (2) For service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// www.dassaultfalcon.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 December 27, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–31963 Filed 1–5–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 1623 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9567; Directorate Identifier 2016–NM–147–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) 2007–13– 08, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007–13–08 currently requires repetitive inspections of the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake, and applicable corrective actions. Since we issued AD 2007–13–08, a determination was made that the unsafe condition could occur on additional airplanes. This proposed AD would expand the applicability in AD 2007–13–08, and include an optional terminating installation for the repetitive actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 21, 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, Airworthiness Office–EIAS, 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 SUMMARY: E:\FR\FM\06JAP1.SGM 06JAP1 1624 Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules 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–2016– 9567; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: sradovich on DSK3GMQ082PROD with PROPOSALS 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–2016–9567; Directorate Identifier 2016–NM–147–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 June 12, 2007, we issued AD 2007–13–08, Amendment 39–15112 (72 FR 33877, June 20, 2007) (‘‘AD 2007– 13–08’’), for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2007–13–08 was prompted by mandatory continuing airworthiness information issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. AD 2007–13–08 currently requires repetitive inspections of the APU starter motor, APU inlet plenum, and APU air intake for discrepancies; repetitive cleaning of the APU air intake, and applicable VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 corrective actions. We issued AD 2007– 13–08 to detect and correct reverse flow during APU startup, leading to flame propagation in the APU air inlet and intake duct. Such conditions could result in an in-flight fire in the APU area. Since we issued AD 2007–13–08, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0176, dated August 31, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 airplanes. The MCAI states: An operator reported black smoke at the rear of the fuselage during taxi after landing. The smoke was caused by a fire in the auxiliary power unit (APU) air intake. The subsequent analysis demonstrated that, following numerous unsuccessful APU start attempts in flight, there is a risk of reverse flow leading to flame propagation to the APU air inlet and air intake duct. This condition, if not detected and corrected, could result in an in-flight fire in the APU area. Prompted by these findings, Airbus issued Service Bulletin (SB) A320–49–1068 to provide inspection and cleaning instructions. The applicable Flight Crew Operating Manual (FCOM) already contained a limitation for the number of APU start attempts, as follows: APU STARTER After 3 Starter Motor Duty Cycles, Wait 60 Minutes Before Attempting 3 More Cycles To address this potential unsafe condition, EASA issued AD 2006–0153 to require repetitive inspections of the APU starter motor, APU inlet plenum and APU air intake [for discrepancies], as well as repetitive cleaning of the APU air intake [and applicable corrective actions]. As the reverse flow inside the APU can only occur in flight with the APU inlet closed, various modifications (mod) were developed to introduce a new electronic control box (ECB) with associated software, the functionality of which keeps the APU inlet door open for 15 minutes, following an APU auto-shutdown in flight. Consequently, AD 2006–0153 was revised [which corresponds to FAA AD 2007–13–08], reducing the Applicability by excluding certain post-mod aeroplanes, and introducing these modifications as optional terminating actions. After EASA AD 2006–0153R2 was issued, it was determined that, as an APU ECB can be replaced (or moved from one aeroplane to another) in service, inadvertently installing a pre-mod ECB would reintroduce the unsafe condition. Prompted by this finding, EASA issued AD 2016–0159, retaining the requirements of EASA AD 2006–0153R2, which was superseded, expanding the Applicability and including references to additional optional terminating actions. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Since EASA AD 2016–0159 was issued, it was determined that paragraph (5) of the [EASA] AD contained some erroneous statements, inadvertently excluding certain aeroplanes, those that have Airbus mod 23698 or mod 24498 embodied in production, from the repetitive actions. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016–0159, which is superseded, and corrects paragraph (5). For post-mod aeroplanes where, inadvertently, an ‘affected’ ECB has been installed in service, this AD adds the requirement to restore those aeroplanes to post-mod configuration by installation of a ‘serviceable’ ECB. This [EASA] AD also introduces some editorial changes, not affecting the required actions. Discrepancies include a defective APU starter motor, misaligned brush wear indicator-pin, oil contamination of the brush wear indicator, and dirt, debris, dust, sand, oil, combustible residues, grease and other contaminations of the APU inlet plenum. Corrective actions include replacement of the APU starter motor and cleaning the APU air intake, if necessary. 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–2016– 9567. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–49–1068, Revision 01, dated February 2, 2006. The service information describes procedures for repetitive inspections for discrepancies of the APU starter motor, APU inlet plenum, and APU air intake, as well as repetitive cleaning of the APU air intake and applicable corrective actions. Airbus has also issued the following service information, which describes procedures for replacing the ECB. These documents are distinct since they apply to different airplane models in different configurations. • Airbus Service Bulletin A320–49– 1070, dated July 28, 2006. • Airbus Service Bulletin A320–49– 1075, Revision 01, dated December 1, 2006. • Airbus Service Bulletin A320–49– 1077, Revision 04, dated February 27, 2013. • Airbus Service Bulletin A320–49– 1098, dated June 21, 2011. • Airbus Service Bulletin A320–49– 1102, dated January 3, 2012. • Airbus Service Bulletin A320–49– 1107, Revision 02, dated May 10, 2016. 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. E:\FR\FM\06JAP1.SGM 06JAP1 Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules 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. sradovich on DSK3GMQ082PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 1,182 airplanes of U.S. registry. The actions required by AD 2007–13– 08, and retained in this proposed AD, take about 4 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 2007–13–08 is $340 per product. We also estimate that it would take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $401,880, or $340 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 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 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) 2007–13–08, Amendment 39–15112 (72 FR 33877, June 20, 2007), and adding the following new AD: ■ Airbus: Docket No. FAA–2016–9567; Directorate Identifier 2016–NM–147–AD. (a) Comments Due Date We must receive comments by February 21, 2017. 1625 (d) Subject Air Transport Association (ATA) of America Code 49, Airborne Auxiliary Power. (e) Reason This AD was prompted by a report of a fire in the auxiliary power unit (APU) air intake. An analysis demonstrated that, following numerous unsuccessful APU start attempts in flight, there is a risk of reverse airflow, leading to flame propagation to the APU air inlet and air intake duct. This AD was also prompted by the determination that AD 2007–13–08 only addresses the unsafe condition for certain airplanes. We are issuing this AD to detect and correct reverse flow during APU startup, leading to flame propagation in the APU air inlet and intake duct. Such conditions could result in an inflight fire in the APU area. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as provided by paragraph (i) of this AD, within 600 flight hours after July 25, 2007 (the effective date of AD 2007–13–08), or within 60 days after the effective date of this AD, whichever occurs later: Inspect the APU starter motor, APU air inlet plenum, and APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD for discrepancies; and do all applicable corrective actions before further flight; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–49–1068, Revision 01, dated February 2, 2006. Repeat the inspection thereafter at intervals not to exceed 600 flight hours. TABLE 1 TO PARAGRAPHS (g), (h), (i)(2), (j), AND (k) OF THIS AD—AFFECTED APU AND ELECTRONIC CONTROL BOX (ECB) APU APIC APS 3200. Honeywell 131–9A. ECB Part Numbers (P/N) 4500003D, 4500003E, 4500003F, 4500003G, 4500003H, or 4500003J. 3888394–120201, 3888394– 121202, 3888394–121203, 3888394–221202, or 3888394–221203. 307950–1, 307950–2, 307950–3, 307950–4, 304640–1, 304640–2, 304640–3, 304640–4, 304817–1, or 304817–2. (b) Affected ADs This AD replaces AD 2007–13–08, Amendment 39–15112 (72 FR 33877, June 20, 2007) (‘‘AD 2007–13–08’’). Honeywell GTCP36– 300. (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer serial numbers, certificated in any category. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (h) Repetitive Cleanings Except as provided by paragraph (i) of this AD, prior to the accumulation of 2,400 flight hours since first flight of the airplane, or within 600 flight hours after July 25, 2007 (the effective date of AD 2007–13–08), or within 60 days after the effective date of this AD, whichever occurs latest, unless accomplished previously in accordance with Airbus Service Bulletin A320–49–1098, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\06JAP1.SGM 06JAP1 1626 Federal Register / Vol. 82, No. 4 / Friday, January 6, 2017 / Proposed Rules dated June 21, 2011: Clean the APU air intake of each affected APU identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 49–1068, Revision 01, dated February 2, 2006. Repeat the cleaning task thereafter at intervals not to exceed 2,400 flight hours. (i) Exceptions to Requirements in Paragraphs (g) and (h) of This AD (1) For airplanes equipped with an APU and associated ECB part number identified in table 2 to paragraphs (i)(1), (i)(2), and (j) of this AD, the actions specified in paragraphs (g) and (h) of this AD are not required. effective date of this AD is installed, the actions specified in paragraphs (g) and (h) of this AD are not required, provided the conditions specified in paragraphs (i)(3)(i) and (i)(3)(ii) of this AD are met. (i) The part number must be approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (ii) The installation must be accomplished in accordance with airplane modification instructions approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (j) Optional Terminating Action TABLE 2 TO PARAGRAPHS (i)(1), (i)(2), AND (j) OF THIS AD—NON-AFFECTED ECB APU APIC APS 3200. Honeywell 131–9A. sradovich on DSK3GMQ082PROD with PROPOSALS Honeywell GTCP36– 300. ECB Part Numbers (P/N) 4500003K, 4500003L, or 4500003M. 3888394–121204, 3888394– 121205, 3888394–221204, 3888394–221205, or 3888394–321206. 304640–5, 304817–3, or 3888394–230301. (2) For airplanes on which Airbus Modification 35803, 35936, 152289, 152645, 155015, or 157848 has been embodied in production, the actions specified in paragraphs (g) and (h) of this AD are not required provided that, within 30 days after the effective date of this AD, the applicable actions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD are done. (i) The part number of the installed ECB is identified. (ii) Any affected ECB identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD that is found to be installed is replaced with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2), and (j) of this AD, as applicable to the APU installed on the airplane; and the replacement is done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD; or 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). (A) Airbus Service Bulletin A320–49–1070, dated July 28, 2006. (B) Airbus Service Bulletin A320–49–1075, Revision 01, dated December 1, 2006. (C) Airbus Service Bulletin A320–49–1077, Revision 04, dated February 27, 2013. (D) Airbus Service Bulletin A320–49–1098, dated June 21, 2011. (E) Airbus Service Bulletin A320–49–1102, dated January 3, 2012. (F) Airbus Service Bulletin A320–49–1107, Revision 02, dated May 10, 2016. (3) For airplanes on which an APU ECB having a part number approved after the VerDate Sep<11>2014 17:49 Jan 05, 2017 Jkt 241001 Replacing an affected ECB identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD with an ECB having a part number identified in table 2 to paragraphs (i)(1), (i)(2), and (j) of this AD, as applicable to the APU installed on the airplane, constitutes terminating action for the repetitive inspections required by paragraphs (g) and (h) of this AD. The replacement must be done in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(2)(ii) (A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD, or using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (k) Parts Installation Prohibition As of the effective date of this AD, no person may install on any airplane an APU with an associated ECB identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD. (l) Credit for Previous Actions This paragraph provides credit for actions specified in paragraphs (i)(2) and (j) of this AD, if those actions were performed before the effective date of this AD using any of the service information specified in paragraphs (l)(1) through (l)(7) of this AD. (1) Airbus Service Bulletin A320–49–1075, dated September 22, 2006, which was incorporated by reference in AD 2007–13–08. (2) Airbus Service Bulletin A320–49–1077, dated March 21, 2007, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A320–49–1077, Revision 01, dated August 9, 2007, which is not incorporated by reference in this AD. (4) Airbus Service Bulletin A320–49–1077, Revision 02, dated July 1, 2008, which is not incorporated by reference in this AD. (5) Airbus Service Bulletin A320–49–1077, Revision 03, dated December 8, 2008, which is not incorporated by reference in this AD. (6) Airbus Service Bulletin A320–49–1107, dated November 5, 2013, which is not incorporated by reference in this AD. (7) Airbus Service Bulletin A320–49–1107, Revision 01, dated July 28, 2015, which is not incorporated by reference in this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: PO 00000 Frm 00019 Fmt 4702 Sfmt 9990 (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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; 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 2007–13–08 are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0176, dated August 31, 2016, 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–2016–9567. (2) For service information identified in this AD, contact Airbus, Airworthiness Office–EIAS, 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 December 23, 2016. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–31960 Filed 1–5–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\06JAP1.SGM 06JAP1

Agencies

[Federal Register Volume 82, Number 4 (Friday, January 6, 2017)]
[Proposed Rules]
[Pages 1623-1626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31960]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2007-13-
08, for certain Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2007-13-08 currently requires repetitive inspections of 
the auxiliary power unit (APU) starter motor, APU inlet plenum, and APU 
air intake for discrepancies; repetitive cleaning of the APU air 
intake, and applicable corrective actions. Since we issued AD 2007-13-
08, a determination was made that the unsafe condition could occur on 
additional airplanes. This proposed AD would expand the applicability 
in AD 2007-13-08, and include an optional terminating installation for 
the repetitive actions. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by February 21, 
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, 
Airworthiness Office-EIAS, 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

[[Page 1624]]

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-2016-
9567; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2016-9567; 
Directorate Identifier 2016-NM-147-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 June 12, 2007, we issued AD 2007-13-08, Amendment 39-15112 (72 
FR 33877, June 20, 2007) (``AD 2007-13-08''), for certain Airbus Model 
A318, A319, A320, and A321 series airplanes. AD 2007-13-08 was prompted 
by mandatory continuing airworthiness information issued by an 
airworthiness authority of another country to identify and correct an 
unsafe condition on an aviation product. AD 2007-13-08 currently 
requires repetitive inspections of the APU starter motor, APU inlet 
plenum, and APU air intake for discrepancies; repetitive cleaning of 
the APU air intake, and applicable corrective actions. We issued AD 
2007-13-08 to detect and correct reverse flow during APU startup, 
leading to flame propagation in the APU air inlet and intake duct. Such 
conditions could result in an in-flight fire in the APU area.
    Since we issued AD 2007-13-08, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2016-0176, dated August 31, 2016 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for all 
Airbus Model A318, A319, A320, and A321 airplanes. The MCAI states:

    An operator reported black smoke at the rear of the fuselage 
during taxi after landing. The smoke was caused by a fire in the 
auxiliary power unit (APU) air intake. The subsequent analysis 
demonstrated that, following numerous unsuccessful APU start 
attempts in flight, there is a risk of reverse flow leading to flame 
propagation to the APU air inlet and air intake duct.
    This condition, if not detected and corrected, could result in 
an in-flight fire in the APU area.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A320-49-1068 to provide inspection and cleaning instructions. The 
applicable Flight Crew Operating Manual (FCOM) already contained a 
limitation for the number of APU start attempts, as follows:

APU STARTER

After 3 Starter Motor Duty Cycles, Wait 60 Minutes Before 
Attempting 3 More Cycles

    To address this potential unsafe condition, EASA issued AD 2006-
0153 to require repetitive inspections of the APU starter motor, APU 
inlet plenum and APU air intake [for discrepancies], as well as 
repetitive cleaning of the APU air intake [and applicable corrective 
actions].
    As the reverse flow inside the APU can only occur in flight with 
the APU inlet closed, various modifications (mod) were developed to 
introduce a new electronic control box (ECB) with associated 
software, the functionality of which keeps the APU inlet door open 
for 15 minutes, following an APU auto-shutdown in flight. 
Consequently, AD 2006-0153 was revised [which corresponds to FAA AD 
2007-13-08], reducing the Applicability by excluding certain post-
mod aeroplanes, and introducing these modifications as optional 
terminating actions.
    After EASA AD 2006-0153R2 was issued, it was determined that, as 
an APU ECB can be replaced (or moved from one aeroplane to another) 
in service, inadvertently installing a pre-mod ECB would reintroduce 
the unsafe condition. Prompted by this finding, EASA issued AD 2016-
0159, retaining the requirements of EASA AD 2006-0153R2, which was 
superseded, expanding the Applicability and including references to 
additional optional terminating actions.
    Since EASA AD 2016-0159 was issued, it was determined that 
paragraph (5) of the [EASA] AD contained some erroneous statements, 
inadvertently excluding certain aeroplanes, those that have Airbus 
mod 23698 or mod 24498 embodied in production, from the repetitive 
actions.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0159, which is superseded, and corrects 
paragraph (5). For post-mod aeroplanes where, inadvertently, an 
`affected' ECB has been installed in service, this AD adds the 
requirement to restore those aeroplanes to post-mod configuration by 
installation of a `serviceable' ECB. This [EASA] AD also introduces 
some editorial changes, not affecting the required actions.

    Discrepancies include a defective APU starter motor, misaligned 
brush wear indicator-pin, oil contamination of the brush wear 
indicator, and dirt, debris, dust, sand, oil, combustible residues, 
grease and other contaminations of the APU inlet plenum. Corrective 
actions include replacement of the APU starter motor and cleaning the 
APU air intake, if necessary. 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-2016-9567.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-49-1068, Revision 01, dated 
February 2, 2006. The service information describes procedures for 
repetitive inspections for discrepancies of the APU starter motor, APU 
inlet plenum, and APU air intake, as well as repetitive cleaning of the 
APU air intake and applicable corrective actions.
    Airbus has also issued the following service information, which 
describes procedures for replacing the ECB. These documents are 
distinct since they apply to different airplane models in different 
configurations.
     Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
     Airbus Service Bulletin A320-49-1075, Revision 01, dated 
December 1, 2006.
     Airbus Service Bulletin A320-49-1077, Revision 04, dated 
February 27, 2013.
     Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
     Airbus Service Bulletin A320-49-1102, dated January 3, 
2012.
     Airbus Service Bulletin A320-49-1107, Revision 02, dated 
May 10, 2016.
    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.

[[Page 1625]]

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 1,182 airplanes of U.S. 
registry.
    The actions required by AD 2007-13-08, and retained in this 
proposed AD, take about 4 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 2007-13-08 is $340 per product.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $401,880, or $340 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-
147-AD.

(a) Comments Due Date

    We must receive comments by February 21, 2017.

(b) Affected ADs

    This AD replaces AD 2007-13-08, Amendment 39-15112 (72 FR 33877, 
June 20, 2007) (``AD 2007-13-08'').

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer 
serial numbers, certificated in any category.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 49, Airborne 
Auxiliary Power.

(e) Reason

    This AD was prompted by a report of a fire in the auxiliary 
power unit (APU) air intake. An analysis demonstrated that, 
following numerous unsuccessful APU start attempts in flight, there 
is a risk of reverse airflow, leading to flame propagation to the 
APU air inlet and air intake duct. This AD was also prompted by the 
determination that AD 2007-13-08 only addresses the unsafe condition 
for certain airplanes. We are issuing this AD to detect and correct 
reverse flow during APU startup, leading to flame propagation in the 
APU air inlet and intake duct. Such conditions could result in an 
in-flight fire in the APU area.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as provided by paragraph (i) of this AD, within 600 
flight hours after July 25, 2007 (the effective date of AD 2007-13-
08), or within 60 days after the effective date of this AD, 
whichever occurs later: Inspect the APU starter motor, APU air inlet 
plenum, and APU air intake of each affected APU identified in table 
1 to paragraphs (g), (h), (i)(2), (j), and (k) of this AD for 
discrepancies; and do all applicable corrective actions before 
further flight; in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 
2, 2006. Repeat the inspection thereafter at intervals not to exceed 
600 flight hours.

    Table 1 to Paragraphs (g), (h), (i)(2), (j), and (k) of This AD--
              Affected APU and Electronic Control Box (ECB)
------------------------------------------------------------------------
                  APU                         ECB Part Numbers (P/N)
------------------------------------------------------------------------
APIC APS 3200..........................  4500003D, 4500003E, 4500003F,
                                          4500003G, 4500003H, or
                                          4500003J.
Honeywell 131-9A.......................  3888394-120201, 3888394-121202,
                                          3888394-121203, 3888394-
                                          221202, or 3888394-221203.
Honeywell GTCP36-300...................  307950-1, 307950-2, 307950-3,
                                          307950-4, 304640-1, 304640-2,
                                          304640-3, 304640-4, 304817-1,
                                          or 304817-2.
------------------------------------------------------------------------

(h) Repetitive Cleanings

    Except as provided by paragraph (i) of this AD, prior to the 
accumulation of 2,400 flight hours since first flight of the 
airplane, or within 600 flight hours after July 25, 2007 (the 
effective date of AD 2007-13-08), or within 60 days after the 
effective date of this AD, whichever occurs latest, unless 
accomplished previously in accordance with Airbus Service Bulletin 
A320-49-1098,

[[Page 1626]]

dated June 21, 2011: Clean the APU air intake of each affected APU 
identified in table 1 to paragraphs (g), (h), (i)(2), (j), and (k) 
of this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-49-1068, Revision 01, dated February 2, 
2006. Repeat the cleaning task thereafter at intervals not to exceed 
2,400 flight hours.

(i) Exceptions to Requirements in Paragraphs (g) and (h) of This AD

    (1) For airplanes equipped with an APU and associated ECB part 
number identified in table 2 to paragraphs (i)(1), (i)(2), and (j) 
of this AD, the actions specified in paragraphs (g) and (h) of this 
AD are not required.

 Table 2 to Paragraphs (i)(1), (i)(2), and (j) of This AD--Non-Affected
                                   ECB
------------------------------------------------------------------------
                  APU                         ECB Part Numbers (P/N)
------------------------------------------------------------------------
APIC APS 3200..........................  4500003K, 4500003L, or
                                          4500003M.
Honeywell 131-9A.......................  3888394-121204, 3888394-121205,
                                          3888394-221204, 3888394-
                                          221205, or 3888394-321206.
Honeywell GTCP36-300...................  304640-5, 304817-3, or 3888394-
                                          230301.
------------------------------------------------------------------------

    (2) For airplanes on which Airbus Modification 35803, 35936, 
152289, 152645, 155015, or 157848 has been embodied in production, 
the actions specified in paragraphs (g) and (h) of this AD are not 
required provided that, within 30 days after the effective date of 
this AD, the applicable actions specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD are done.
    (i) The part number of the installed ECB is identified.
    (ii) Any affected ECB identified in table 1 to paragraphs (g), 
(h), (i)(2), (j), and (k) of this AD that is found to be installed 
is replaced with an ECB having a part number identified in table 2 
to paragraphs (i)(1), (i)(2), and (j) of this AD, as applicable to 
the APU installed on the airplane; and the replacement is done in 
accordance with the Accomplishment Instructions of the applicable 
service information identified in paragraph (i)(2)(ii)(A), 
(i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or 
(i)(2)(ii)(F) of this AD; or 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).
    (A) Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
    (B) Airbus Service Bulletin A320-49-1075, Revision 01, dated 
December 1, 2006.
    (C) Airbus Service Bulletin A320-49-1077, Revision 04, dated 
February 27, 2013.
    (D) Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
    (E) Airbus Service Bulletin A320-49-1102, dated January 3, 2012.
    (F) Airbus Service Bulletin A320-49-1107, Revision 02, dated May 
10, 2016.
    (3) For airplanes on which an APU ECB having a part number 
approved after the effective date of this AD is installed, the 
actions specified in paragraphs (g) and (h) of this AD are not 
required, provided the conditions specified in paragraphs (i)(3)(i) 
and (i)(3)(ii) of this AD are met.
    (i) The part number must be approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.
    (ii) The installation must be accomplished in accordance with 
airplane modification instructions approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.

(j) Optional Terminating Action

    Replacing an affected ECB identified in table 1 to paragraphs 
(g), (h), (i)(2), (j), and (k) of this AD with an ECB having a part 
number identified in table 2 to paragraphs (i)(1), (i)(2), and (j) 
of this AD, as applicable to the APU installed on the airplane, 
constitutes terminating action for the repetitive inspections 
required by paragraphs (g) and (h) of this AD. The replacement must 
be done in accordance with the Accomplishment Instructions of the 
applicable service information identified in paragraph (i)(2)(ii) 
(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), (i)(2)(ii)(E), or 
(i)(2)(ii)(F) of this AD, or using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane an APU with an associated ECB identified in table 1 to 
paragraphs (g), (h), (i)(2), (j), and (k) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for actions specified in 
paragraphs (i)(2) and (j) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information specified in paragraphs (l)(1) through (l)(7) of 
this AD.
    (1) Airbus Service Bulletin A320-49-1075, dated September 22, 
2006, which was incorporated by reference in AD 2007-13-08.
    (2) Airbus Service Bulletin A320-49-1077, dated March 21, 2007, 
which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-49-1077, Revision 01, dated 
August 9, 2007, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A320-49-1077, Revision 02, dated 
July 1, 2008, which is not incorporated by reference in this AD.
    (5) Airbus Service Bulletin A320-49-1077, Revision 03, dated 
December 8, 2008, which is not incorporated by reference in this AD.
    (6) Airbus Service Bulletin A320-49-1107, dated November 5, 
2013, which is not incorporated by reference in this AD.
    (7) Airbus Service Bulletin A320-49-1107, Revision 01, dated 
July 28, 2015, which is not incorporated by reference in this AD.

(m) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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 2007-13-08 are approved as 
AMOCs for the corresponding provisions of paragraphs (g) and (h) of 
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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0176, dated August 31, 2016, 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-2016-9567.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office-EIAS, 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 December 23, 2016.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2016-31960 Filed 1-5-17; 8:45 am]
BILLING CODE 4910-13-P