Airworthiness Directives; Airbus Airplanes, 92749-92753 [2016-30018]

Download as PDF Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): mstockstill on DSK3G9T082PROD with PROPOSALS ■ Dassault Aviation: Docket No. FAA–2016– 9500; Directorate Identifier 2016–NM– 140–AD. (a) Comments Due Date We must receive comments by February 3, 2017. VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 (b) Affected ADs None. (c) Applicability This AD applies to all Dassault Aviation Model FAN JET FALCON, Model MYSTERE– FALCON 20–C5, 20–D5, 20–E5, and 20–F5 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 26, Fire protection. (e) Reason This AD was prompted by reports of defective fire extinguisher tubes. We are issuing this AD to prevent fire extinguisher failure. Such a failure could result in the inability to extinguish a fire in the rear compartment, and possible damage to the airplane and injury to the occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Fire Extinguisher Tubes Replacement Within 450 flight cycles after the effective date of this AD, replace each affected hose, part numbers (P/N) MY20791–121 and P/N MY20791–122, with a serviceable hose, P/N MY20791–121–1 or MY20791–122–1, as applicable, in accordance with the Accomplishment Instructions of Dassault Service Bulletin F20–790, dated September 14, 2016. (h) Parts Installation Prohibition No person may install a fire extinguisher tube, P/N MY20791–121 or P/N MY20791– 122, on any airplane, as of the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) For an airplane equipped with an affected fire extinguisher tube as of the effective date of this AD: After modification of that airplane as required by paragraph (g) of this AD. (2) For an airplane that is not equipped with an affected fire extinguisher tube as of the effective date of this AD: As of the effective date of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of PO 00000 Frm 00047 Fmt 4702 Sfmt 4702 92749 the local flight standards district office/ certificate holding district office. (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. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0154, dated July 28, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9500. (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: https:// 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 6, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–30027 Filed 12–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9508; Directorate Identifier 2016–NM–065–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2015–22– 06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015–22–06 currently requires revising the After Start Normal Procedures section of the airplane flight manual (AFM) to provide procedures that address latent failures in the Spoiler and Elevator Computer (SEC). Since we issued AD 2015–22–06, there have been reports that some maintenance messages pointed out the loss of elevator servo SUMMARY: E:\FR\FM\20DEP1.SGM 20DEP1 92750 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules control monitoring performed by SEC 1, SEC 2, or both, during the engine start. This proposed AD would add a requirement to install updated SEC software. We are proposing this AD to address the unsafe condition on these products. We must receive comments on this proposed AD by February 3, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this 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 https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425 227–1221. DATES: mstockstill on DSK3G9T082PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9508; 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: VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 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–2016–9508; Directorate Identifier 2016–NM–065–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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On October 22, 2015, we issued AD 2015–22–06, Amendment 39–18311 (80 FR 68429, November 5, 2015) (‘‘AD 2015–22–06’’). AD 2015–22–06 requires revision of the AFM intended to address an unsafe condition that can occur in the SEC for all Airbus Model A318, A319, A320, and A321 series airplanes. Since we issued AD 2015–22–06, there have been reports that some maintenance messages were recorded within the Post Flight Report (PFR) that pointed out the loss of elevator servo control monitoring performed by SEC 1, SEC 2, or both, during the engine start. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive, 2016–0056, dated March 18, 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 series airplanes. The MCAI states: Following the introduction of new Spoiler and Elevator Computer (SEC) hardware C Part Number (P/N) B372CAM0100 with software (SW) standards 122, 124 and 125 (identified by P/N B372CAM0101, P/N B372CAM0102 and P/N B372CAM0103, respectively, and hereafter referred to as an ‘‘affected SEC software standard’’ in this [EASA] AD), some airlines reported receiving maintenance messages, e.g. ‘‘SEC OR WIRING FROM L or R ELEV POS MON XDCR’’ and/or ‘‘SEC OR WIRING FROM G or Y ELEV POS XDCR’’, which are associated with servo control or elevator transducer monitoring. Such messages are triggered by a short data inconsistency due to power transients, when the engines are started. This condition, if not corrected, could lead to an undetected loss of redundancy during flight if an affected SEC cannot control the PO 00000 Frm 00048 Fmt 4702 Sfmt 4702 related elevator servo control(s), possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, EASA issued AD 2015–0191 [which corresponds to AD 2015–22–06] to require amendment of the applicable [Airbus] Airplane Flight Manual (AFM) to include the flight crew procedure necessary to recover full SEC redundancy. Since that [EASA] AD was issued, to fix the software deficiency, SEC software standard 126 (identified by P/N B372CAM0104) was developed, which is embodied in production through Airbus modification (mod) 161208 (installation of SEC software standard 126), and introduced in service through Airbus Service Bulletin (SB) A320–27–1252. For the reason described above, this [EASA] AD retains the AFM change requirements of EASA AD 2015–0191, which is superseded, and requires the removal and/ or upgrade of [an affected] SEC. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9508. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: • Airbus Service Bulletin A320–27– 1252, Revision 01, dated February 18, 2016. • Airbus Service Bulletin A320–27– 1257, dated December 18, 2015. This service information provides information for identifying affected SECs and updating the software on affected SECs. These documents are distinct since they apply to different airplane configurations. Airbus also issued A318/A319/A320/ A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 Airplane Flight Manual. This service information describes the reset of SEC 1 and SEC 2 that must be done after engines start. 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 E:\FR\FM\20DEP1.SGM 20DEP1 92751 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules develop on other products of these same type designs. Differences Between This Proposed AD and the Service Information Subtask 271257–832–006–001, Instructions ‘‘2’’ and ‘‘3,’’ in the Accomplishment Instructions of Airbus Service Bulletin A320–27–1257, dated December 18, 2015, have software part numbers that are incorrect. Paragraph (n) of this proposed AD provides the corrected part numbers. The correct part numbers were provided by Airbus in Operators Information Transmission (OIT) 16–0001, Revision 00, dated January 20, 2016. Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost AFM revision (retained action from AD 2015–22–06) Removal and replacement of SEC (new proposed action). 1 work-hour × $85 per hour = $85 ..... 4 work-hours × $85 per hour = $340 mstockstill on DSK3G9T082PROD with PROPOSALS 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, VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 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 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–22–06, Amendment 39–18311 (80 FR 68429, November 5, 2015), and adding the following new AD: Airbus: Docket No. FAA–2016–9508; Directorate Identifier 2016–NM–065–AD. (a) Comments Due Date We must receive comments by February 3, 2017. (b) Affected ADs This AD replaces AD 2015–22–06, Amendment 39–18311 (80 FR 68429, November 5, 2015) (‘‘AD 2015–22–06’’). (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(4) of this AD, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. Frm 00049 Fmt 4702 $0 0 Cost on U.S. operators $85 340 $81,515 326,060 (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by reports that some maintenance messages were recorded within the Post Flight Report (PFR) that pointed out the loss of elevator servo control monitoring performed by Spoiler and Elevator Computer (SEC) 1, SEC 2, or both, during the engine start. We are issuing this AD to prevent an undetected loss of redundancy during flight if an affected SEC cannot control the related elevator servo control(s), possibly resulting in reduced control of the airplane. (f) Compliance [Amended] ■ PO 00000 Cost per product Parts cost Sfmt 4702 Comply with this AD within the compliance times specified, unless already done. (g) Retained Airplane Flight Manual Revision, With Revised Compliance Language This paragraph restates the requirements of paragraph (g) of AD 2015–22–06, with revised compliance language. For airplanes equipped with SEC hardware C part number (P/N) B372CAM0100 with software standards 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or both: Within 30 days after November 20, 2015 (the effective date of AD 2015–22–06), revise the After Start Normal Procedures section of the airplane flight manual (AFM) to include the statement specified in figure 1 to paragraph (g) of this AD. This may be done by inserting a copy of this AD, or AD 2015–22–06, or Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321 AFM, into the applicable AFM. E:\FR\FM\20DEP1.SGM 20DEP1 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules Note 1 to paragraph (g) of this AD: When a statement identical to that in figure 1 to paragraph (g) of this AD has been included in the After Start Normal Procedures section of the general revisions of the AFM, the general revisions may be inserted into the AFM, and this AD, or AD 2015–22–06, or Airbus A318/A319/A320/A321 Temporary Revision TR572, Issue 1.0, dated August 13, 2015, may be removed from the AFM. Note 2 to paragraph (g) of this AD: Airbus Operations Engineering Bulletin OEB–50 provides additional information on the subject addressed by this AD. (h) Retained Parts Installation Limitation, With No Change This paragraph restates the requirements of paragraph (i) of AD 2015–22–06, with no change. For all airplanes: As of November 20, 2015 (the effective date of AD 2015–22–06), do not install SEC hardware C P/N B372CAM0100 with software standard 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on SEC position 1 or 2, or both, on any airplane, unless the AFM of the airplane is revised concurrently with that installation, as required by paragraph (g) of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (i) New Requirement of This AD: Replacement of Software Within 3 months after the effective date of this AD, comply with the actions in paragraphs (i)(1) or (i)(2) of this AD, as applicable. (1) For an airplane that has received Airbus modification 39429 (installation of SEC hardware C P/N B372CAM0100) in production: Install SEC software standard 126, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 27–1252, Revision 01, dated February 18, 2016. (2) For an airplane that has not received Airbus modification 39429 in production: Inspect to determine whether an affected SEC software standard is installed. Do the inspection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1257, dated December 18, 2015, except as required by paragraph (n) of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the SEC C can be conclusively determined from that review. If an affected SEC software standard is found installed, replace the affected software standard using an installation method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or VerDate Sep<11>2014 18:20 Dec 19, 2016 Jkt 241001 Airbus’s EASA Design Organization Approval (DOA). (j) New Requirement of This AD: Compliance for Airplanes Having Airbus Modification 161208 Embodied in Production An airplane on which Airbus modification 161208 has been embodied in production is compliant with the requirements of paragraph (i) of this AD, provided it is determined that no affected SEC software standard, as identified in paragraph (g) of this AD, is installed on that airplane. (k) New Requirement of This AD: Disposition of AFM After Airplane Modification After modification of an airplane as required by paragraph (i) of this AD, remove the information specified in Airbus A318/ A319/A320/A321 TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/ A320/A321 AFM from the AFM of that airplane. (l) New Requirement of This AD: Parts Installation Prohibition As of the effective date of this AD, no person may install on any airplane an affected SEC software standard, or a SEC hardware C hosting an affected SEC software standard. (m) New Provision of This AD: Installation of Equivalent Software and Hardware Installation on an airplane of a SEC software standard, or of a SEC hardware standard, approved after the effective date of this AD, is acceptable for compliance with the requirements of paragraph (i) of this AD for that airplane, provided the conditions specified in paragraphs (m)(1) and (m)(2) of this AD are met. (1) The software and hardware standard, as applicable, is approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA; and (2) Replacement of the affected software standard is done using an installation method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (n) Exception to Service Information Specifications Subtask 271257–832–006–001 of Airbus Service Bulletin A320–27–1257, dated December 18, 2015, includes incorrect instructions. This AD requires that those instructions be followed as specified in paragraphs (n)(1) and (n)(2) of this AD. (1) For Subtask 271257–832–006–001 instruction ‘‘2’’: If SEC C 126 software P/N PO 00000 Frm 00050 Fmt 4702 Sfmt 4702 B372CAM0104 is found, no further action is required by this AD. (2) For Subtask 271257–832–006–001 instruction ‘‘3’’: If SEC C 122 software P/N B372CAM0101, SEC C 124 software P/N B372CAM0102, or SEC C 125 software P/N B372CAM0103 is found, do corrective actions using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (o) 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-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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. E:\FR\FM\20DEP1.SGM 20DEP1 EP20DE16.003</GPH> 92752 Federal Register / Vol. 81, No. 244 / Tuesday, December 20, 2016 / Proposed Rules (p) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0056, dated March 18, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–9508. (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 https://www.airbus.com. Issued in Renton, Washington, on December 7, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–30018 Filed 12–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2016–9506; Directorate Identifier 2016–NM–090–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This proposed AD was prompted by a report of an aborted takeoff because the rudder pedals were not operating correctly. Investigation revealed a protruding screw in the rudder pedal heel rest adjacent to the pedals. This proposed AD would require a torque check of the screws in the cover assembly of the heel rest for both the Captain and the First Officer’s rudder pedals, and corrective action if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR mstockstill on DSK3G9T082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 18:20 Dec 19, 2016 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9506. Jkt 241001 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9506; 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: Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6490; fax: 425–917–6590; email: Kelly.McGuckin@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–9506; Directorate Identifier 2016– PO 00000 Frm 00051 Fmt 4702 Sfmt 4702 92753 NM–090–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 because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received a report of an aborted takeoff because the rudder pedals were not operating correctly. Investigation revealed a protruding screw in the rudder pedal heel rest adjacent to the pedals. It was determined that the screws in the cover assembly of the heel rest for both the Captain and the First Officer’s rudder pedals may not have been properly torqued. A protruding screw from the cover assembly of the heel rest of a rudder pedal could restrict rudder pedal motion and reduce differential braking control during takeoff or landing, which could cause a high speed runway excursion. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737–25A1732, Revision 1, dated August 15, 2016. The service information describes procedures for a torque check of the screws in the cover assembly of the heel rest for both the Captain and the First Officer’s rudder pedals, and corrective action. 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 We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. For information on the procedures and compliance times, see this service information at https:// www.regulations.gov by searching for E:\FR\FM\20DEP1.SGM 20DEP1

Agencies

[Federal Register Volume 81, Number 244 (Tuesday, December 20, 2016)]
[Proposed Rules]
[Pages 92749-92753]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30018]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9508; Directorate Identifier 2016-NM-065-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) 2015-22-
06 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD
2015-22-06 currently requires revising the After Start Normal
Procedures section of the airplane flight manual (AFM) to provide
procedures that address latent failures in the Spoiler and Elevator
Computer (SEC). Since we issued AD 2015-22-06, there have been reports
that some maintenance messages pointed out the loss of elevator servo

[[Page 92750]]

control monitoring performed by SEC 1, SEC 2, or both, during the
engine start. This proposed AD would add a requirement to install
updated SEC software. We are proposing this AD to address the unsafe
condition on these products.

DATES: We must receive comments on this proposed AD by February 3,
2017.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this 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 https://www.airbus.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425 227-1221.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9508; 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-2016-9508;
Directorate Identifier 2016-NM-065-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 https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

On October 22, 2015, we issued AD 2015-22-06, Amendment 39-18311
(80 FR 68429, November 5, 2015) (``AD 2015-22-06''). AD 2015-22-06
requires revision of the AFM intended to address an unsafe condition
that can occur in the SEC for all Airbus Model A318, A319, A320, and
A321 series airplanes.
Since we issued AD 2015-22-06, there have been reports that some
maintenance messages were recorded within the Post Flight Report (PFR)
that pointed out the loss of elevator servo control monitoring
performed by SEC 1, SEC 2, or both, during the engine start.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive, 2016-0056, dated March 18, 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 series airplanes. The MCAI states:

Following the introduction of new Spoiler and Elevator Computer
(SEC) hardware C Part Number (P/N) B372CAM0100 with software (SW)
standards 122, 124 and 125 (identified by P/N B372CAM0101, P/N
B372CAM0102 and P/N B372CAM0103, respectively, and hereafter
referred to as an ``affected SEC software standard'' in this [EASA]
AD), some airlines reported receiving maintenance messages, e.g.
``SEC OR WIRING FROM L or R ELEV POS MON XDCR'' and/or ``SEC OR
WIRING FROM G or Y ELEV POS XDCR'', which are associated with servo
control or elevator transducer monitoring. Such messages are
triggered by a short data inconsistency due to power transients,
when the engines are started.
This condition, if not corrected, could lead to an undetected
loss of redundancy during flight if an affected SEC cannot control
the related elevator servo control(s), possibly resulting in reduced
control of the aeroplane.
To address this potential unsafe condition, EASA issued AD 2015-
0191 [which corresponds to AD 2015-22-06] to require amendment of
the applicable [Airbus] Airplane Flight Manual (AFM) to include the
flight crew procedure necessary to recover full SEC redundancy.
Since that [EASA] AD was issued, to fix the software deficiency,
SEC software standard 126 (identified by P/N B372CAM0104) was
developed, which is embodied in production through Airbus
modification (mod) 161208 (installation of SEC software standard
126), and introduced in service through Airbus Service Bulletin (SB)
A320-27-1252.
For the reason described above, this [EASA] AD retains the AFM
change requirements of EASA AD 2015-0191, which is superseded, and
requires the removal and/or upgrade of [an affected] SEC.

You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9508.

Related Service Information Under 1 CFR Part 51

Airbus has issued the following service information:
Airbus Service Bulletin A320-27-1252, Revision 01, dated
February 18, 2016.
Airbus Service Bulletin A320-27-1257, dated December 18,
2015.
This service information provides information for identifying
affected SECs and updating the software on affected SECs. These
documents are distinct since they apply to different airplane
configurations.
Airbus also issued A318/A319/A320/A321 Temporary Revision TR572,
Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/A320/A321
Airplane Flight Manual. This service information describes the reset of
SEC 1 and SEC 2 that must be done after engines start.
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

[[Page 92751]]

develop on other products of these same type designs.

Differences Between This Proposed AD and the Service Information

Subtask 271257-832-006-001, Instructions ``2'' and ``3,'' in the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1257,
dated December 18, 2015, have software part numbers that are incorrect.
Paragraph (n) of this proposed AD provides the corrected part numbers.
The correct part numbers were provided by Airbus in Operators
Information Transmission (OIT) 16-0001, Revision 00, dated January 20,
2016.

Costs of Compliance

We estimate that this proposed AD affects 959 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (retained action from AD 2015- 1 work-hour x $85 per hour = $85........................... $0 $85 $81,515
22-06).
Removal and replacement of SEC (new 4 work-hours x $85 per hour = $340......................... 0 340 326,060
proposed action).
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-22-06, Amendment 39-18311 (80 FR 68429, November 5, 2015), and
adding the following new AD:

Airbus: Docket No. FAA-2016-9508; Directorate Identifier 2016-NM-
065-AD.

(a) Comments Due Date

We must receive comments by February 3, 2017.

(b) Affected ADs

This AD replaces AD 2015-22-06, Amendment 39-18311 (80 FR 68429,
November 5, 2015) (``AD 2015-22-06'').

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

(d) Subject

Air Transport Association (ATA) of America Code 27, Flight
Controls.

(e) Reason

This AD was prompted by reports that some maintenance messages
were recorded within the Post Flight Report (PFR) that pointed out
the loss of elevator servo control monitoring performed by Spoiler
and Elevator Computer (SEC) 1, SEC 2, or both, during the engine
start. We are issuing this AD to prevent an undetected loss of
redundancy during flight if an affected SEC cannot control the
related elevator servo control(s), possibly resulting in reduced
control of the airplane.

(f) Compliance

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

(g) Retained Airplane Flight Manual Revision, With Revised Compliance
Language

This paragraph restates the requirements of paragraph (g) of AD
2015-22-06, with revised compliance language. For airplanes equipped
with SEC hardware C part number (P/N) B372CAM0100 with software
standards 122 (P/N B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N
B372CAM0103), on SEC position 1 or 2, or both: Within 30 days after
November 20, 2015 (the effective date of AD 2015-22-06), revise the
After Start Normal Procedures section of the airplane flight manual
(AFM) to include the statement specified in figure 1 to paragraph
(g) of this AD. This may be done by inserting a copy of this AD, or
AD 2015-22-06, or Airbus A318/A319/A320/A321 Temporary Revision
TR572, Issue 1.0, dated August 13, 2015, to the Airbus A318/A319/
A320/A321 AFM, into the applicable AFM.

[[Page 92752]]

[GRAPHIC] [TIFF OMITTED] TP20DE16.003

Note 1 to paragraph (g) of this AD: When a statement identical
to that in figure 1 to paragraph (g) of this AD has been included in
the After Start Normal Procedures section of the general revisions
of the AFM, the general revisions may be inserted into the AFM, and
this AD, or AD 2015-22-06, or Airbus A318/A319/A320/A321 Temporary
Revision TR572, Issue 1.0, dated August 13, 2015, may be removed
from the AFM.

Note 2 to paragraph (g) of this AD: Airbus Operations
Engineering Bulletin OEB-50 provides additional information on the
subject addressed by this AD.

(h) Retained Parts Installation Limitation, With No Change

This paragraph restates the requirements of paragraph (i) of AD
2015-22-06, with no change. For all airplanes: As of November 20,
2015 (the effective date of AD 2015-22-06), do not install SEC
hardware C P/N B372CAM0100 with software standard 122 (P/N
B372CAM0101), 124 (P/N B372CAM0102), or 125 (P/N B372CAM0103), on
SEC position 1 or 2, or both, on any airplane, unless the AFM of the
airplane is revised concurrently with that installation, as required
by paragraph (g) of this AD.

(i) New Requirement of This AD: Replacement of Software

Within 3 months after the effective date of this AD, comply with
the actions in paragraphs (i)(1) or (i)(2) of this AD, as
applicable.
(1) For an airplane that has received Airbus modification 39429
(installation of SEC hardware C P/N B372CAM0100) in production:
Install SEC software standard 126, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1252,
Revision 01, dated February 18, 2016.
(2) For an airplane that has not received Airbus modification
39429 in production: Inspect to determine whether an affected SEC
software standard is installed. Do the inspection in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-27-
1257, dated December 18, 2015, except as required by paragraph (n)
of this AD. A review of airplane maintenance records is acceptable
in lieu of this inspection if the part number of the SEC C can be
conclusively determined from that review. If an affected SEC
software standard is found installed, replace the affected software
standard using an installation 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).

(j) New Requirement of This AD: Compliance for Airplanes Having Airbus
Modification 161208 Embodied in Production

An airplane on which Airbus modification 161208 has been
embodied in production is compliant with the requirements of
paragraph (i) of this AD, provided it is determined that no affected
SEC software standard, as identified in paragraph (g) of this AD, is
installed on that airplane.

(k) New Requirement of This AD: Disposition of AFM After Airplane
Modification

After modification of an airplane as required by paragraph (i)
of this AD, remove the information specified in Airbus A318/A319/
A320/A321 TR572, Issue 1.0, dated August 13, 2015, to the Airbus
A318/A319/A320/A321 AFM from the AFM of that airplane.

(l) New Requirement of This AD: Parts Installation Prohibition

As of the effective date of this AD, no person may install on
any airplane an affected SEC software standard, or a SEC hardware C
hosting an affected SEC software standard.

(m) New Provision of This AD: Installation of Equivalent Software and
Hardware

Installation on an airplane of a SEC software standard, or of a
SEC hardware standard, approved after the effective date of this AD,
is acceptable for compliance with the requirements of paragraph (i)
of this AD for that airplane, provided the conditions specified in
paragraphs (m)(1) and (m)(2) of this AD are met.
(1) The software and hardware standard, as applicable, is
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; and
(2) Replacement of the affected software standard is done using
an installation method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or
Airbus's EASA DOA.

(n) Exception to Service Information Specifications

Subtask 271257-832-006-001 of Airbus Service Bulletin A320-27-
1257, dated December 18, 2015, includes incorrect instructions. This
AD requires that those instructions be followed as specified in
paragraphs (n)(1) and (n)(2) of this AD.
(1) For Subtask 271257-832-006-001 instruction ``2'': If SEC C
126 software P/N B372CAM0104 is found, no further action is required
by this AD.
(2) For Subtask 271257-832-006-001 instruction ``3'': If SEC C
122 software P/N B372CAM0101, SEC C 124 software P/N B372CAM0102, or
SEC C 125 software P/N B372CAM0103 is found, do corrective actions
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA
DOA.

(o) 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. 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 EASA; or
Airbus's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.

[[Page 92753]]

(p) Special Flight Permits

Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.

(q) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2016-0056, dated March 18, 2016,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-9508.
(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 https://www.airbus.com.

Issued in Renton, Washington, on December 7, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30018 Filed 12-19-16; 8:45 am]
BILLING CODE 4910-13-P

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