Airworthiness Directives; Airbus Airplanes, 47084-47091 [2017-21224]

Download as PDF 47084 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations parts have been inoperative since the OTS was abolished in 2011. Furthermore, with respect to the removal of the parts of chapter V that govern savings associations and savings and loan holding companies, the Department of the Treasury finds that notice and comment under the APA are neither necessary nor in the public interest. As discussed above, titles III and X of the Dodd-Frank Act transferred the powers, authorities, rights, and duties of the OTS to the Agencies on July 21, 2011 and abolished the OTS on October 19, 2011. Since that time, the Agencies have issued rules that supersede the OTS regulations relating to savings associations and savings and loan holding companies. This final rule does not make any substantive changes to the regulations currently applicable to savings associations and savings and loan associations and does not substantively affect these regulated entities or the public. It simply removes obsolete provisions that are likely to be a source of confusion. For these reasons, advance notice and comment under the APA are unnecessary and not in the public interest. ethrower on DSK3G9T082PROD with RULES Regulatory Flexibility Act Analysis The Regulatory Flexibility Act 4 (RFA) applies only to rules for which an agency publishes a general notice of proposed rulemaking pursuant to 5 U.S.C. 553(b). Pursuant to the APA at 5 U.S.C. 553(b)(B), general notice and an opportunity for public comment are not required prior to the issuance of a final rule when an agency, for good cause, finds that ‘‘notice and public procedure thereon are impracticable, unnecessary, or contrary to the public interest.’’ As discussed above, the Department of the Treasury has determined for good cause that the APA does not require notice and public comment on this final rule and, therefore, it is not publishing a notice of proposed rulemaking. Thus, the RFA, pursuant 5 U.S.C. 601(2), does not apply to this final rule. Unfunded Mandates Reform Act Section 202 of the Unfunded Mandates Reform Act of 1995 requires that an agency prepare a budgetary impact statement before promulgating any rule likely to result in a Federal mandate that may result in the expenditure by state, local, and tribal governments, in the aggregate, or by the private sector, of $100 million or more in any one year, adjusted for inflation.5 Because this final rule removes inoperative and superseded regulations, 4 (Pub. L. 96–354, Sept. 19, 1980). Law 104–4 (2 U.S.C. 1532). 5 Public VerDate Sep<11>2014 20:04 Oct 10, 2017 Jkt 244001 the Department of the Treasury has determined that there is no Federal mandate imposed by this rulemaking. Executive Order 12866 This rule is not a significant regulatory action under Executive Order 12866, Regulatory Planning and Review. 12 CFR Chapter V [Removed] For the reasons set forth in the preamble and pursuant to titles III and X of the Dodd-Frank Act, amend title 12 of the Code of Federal Regulations by removing chapter V. ■ Dated: October 4, 2017. Kody H. Kinsley, Assistant Secretary for Management. [FR Doc. 2017–21904 Filed 10–10–17; 8:45 am] BILLING CODE 4810–25–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0624; Product Identifier 2016–NM–135–AD; Amendment 39–19067; AD 2017–20–10] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. This AD was prompted by a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current flight management and guidance computer (FMGC) standard. This AD requires identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective November 15, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 15, 2017. ADDRESSES: For service information identified in this final rule, contact DATES: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 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 Standards Branch, 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–2017– 0624. 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–2017– 0624; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. The NPRM published in the Federal Register on June 29, 2017 (82 FR 29440) (‘‘the NPRM’’). The NPRM was prompted by a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current FMGC standard. The NPRM proposed to require identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are issuing this AD to prevent unstable approaches due to an unexpected thrust increase, which could result in reduced E:\FR\FM\11OCR1.SGM 11OCR1 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations controllability of the airplane and runway excursions. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0122, dated June 21, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A319 series airplanes, Model A320–211, –212, –214, –231, –232, and –233 airplanes, and Model A321–111, –112, –131, –211, –212, –213, –231, and 232 airplanes. The MCAI states: Following an instrument landing system (ILS) approach, during night, in rainy condition, an A321 aeroplane experienced a longitudinal runway excursion. Investigation revealed that the approach was not stabilized with an overspeed of 19 knots (kts) over the runway threshold, followed by a long flare (18 seconds) with touchdown far behind the touchdown zone. The aeroplane exited the runway at 75 kts and came to rest around 300 meters beyond the end of the runway. During the final approach, at 150 feet Radio Altimeter (RA) altitude, the corrected airspeed of the aeroplane was 165 kts (24 kts overspeed). Auto thrust (ATHR) commanded a transient N1 increase up to 70% due to the ATHR speed Mach control law. The ATHR system on A320 family aeroplane was designed to maintain accurately the aircraft speed/Mach to speed/ Mach target by commanding the thrust, featuring also a trade-off at low altitude between thrust corrections to maintain speed equal to speed target and too large thrust corrections destabilizing the aircraft trajectory near the ground. The conclusions of the investigations were that the main contributor to this runway excursion was a non-stabilized approach not followed by a go-around. ATHR misbehaviour in case of large overspeed led to an unexpected thrust increase, which is considered as a contributor to the long flare. This ATHR characteristic, reported as ‘‘Spurious thrust increase during approach,’’ was initially found in 1996 and a modification was developed and introduced in Flight Guidance (FG) 2G standard ‘‘C8 or I8’’ (C for CFM engines and I for IAE engines) in 2001. Prompted by these findings, Airbus introduced a programme to encourage operators to replace the FMGC Legacy with the FMGC equipped with Flight Management System type 2 (FMS2) and FG standard, which introduces additional operational capabilities, including Runway Overrun Protection System/Runway Overrun Warning (ROPS/ROW) and Autopilot/Traffic Collision Avoidance System (AP/TCAS). It was determined that the ROPS, in a scenario similar to the one described above, would have triggered a <<RUNWAY TOO SHORT>> aural alert before touchdown. Information was made available through Airbus Service Information Letter (SIL) 22–039 (later superseded by Word In Service Experience (WISE) In Service Information 22.83.00003), and EASA published Safety Information Bulletin (SIB) 2013–19, recommending the FMGC upgrade. Since EASA SIB was published, it was determined that many operators have chosen not to implement the optional upgrade that improves the ATHR behaviour. More recently, prompted by a recommendation from the BEA (Bureau ˆ ´ ´ d’Enquetes et d’Analyses pour la securite de l’aviation civile) of France, to reduce the risk of further runway excursions due to uninterrupted unstable approaches performed with the legacy FMGC standard, EASA decided to require installation of at least the first version of the FMS2 and associated FG for legacy aeroplanes. ´ ´ DGAC [Direction Generale de l’Aviation Civile] France issued AD 1999–411–140(B)R1 [which corresponds to FAA AD 2000–12–13, Amendment 39–11791 (65 FR 37845, June 19, 2000) (‘‘AD 2000–12–13’’)] and AD 1998– 226–119(B)R1 [which corresponds to FAA AD 98–19–08, Amendment 39–10750 (63 FR 50503, September 22, 1998)] to address different unsafe conditions, requiring to install a certain previous FMGC standard that may be susceptible to the ‘‘Spurious thrust increase during approach’’. For the reasons described above, this [EASA] AD * * * requires replacement of the affected FMGC units with upgraded units [and applicable concurrent actions]. Concurrent actions include the installation of certain FMGCs, wiring, display management computers, wiring associated with pin programming, and applicable operational program configuration disks. 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–2017–0624. Comments We gave the public the opportunity to participate in developing this AD. We 47085 considered the comment received. Air Line Pilots Association, International supported the NPRM. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information, which describes procedures for replacement of any affected FMGC with a serviceable FMGC. These documents are distinct since they apply to different airplane configurations. • Airbus Service Bulletin A320–22– 1090, Revision 11, dated July 20, 2004. • Airbus Service Bulletin A320–22– 1103, Revision 04, dated March 12, 2004. • Airbus Service Bulletin A320–22– 1116, Revision 04, dated March 29, 2004. • Airbus Service Bulletin A320–22– 1152, Revision 03, dated February 18, 2005. • Airbus Service Bulletin A320–22– 1243, Revision 05, dated May 31, 2010. • Airbus Service Bulletin A320–22– 1519, Revision 02, dated December 21, 2015. 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. Costs of Compliance We estimate that this AD affects 1,032 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS ethrower on DSK3G9T082PROD with RULES Action Labor cost Inspection ........................................................ 1 work-hour × $85 per hour = $85 ................. We estimate the following costs to do any necessary replacements required based on the results of the inspection. We have no way of determining the VerDate Sep<11>2014 20:04 Oct 10, 2017 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $85 Cost on U.S. operators $87,720 number of aircraft that might need these replacements. E:\FR\FM\11OCR1.SGM 11OCR1 47086 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Replacement ................................................................. 9 work-hours × $85 per hour = $765 ........................... ethrower on DSK3G9T082PROD with RULES 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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 20:04 Oct 10, 2017 Jkt 244001 Parts cost $30,000 Cost per product $30,765 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. reduced controllability of the airplane and runway excursions. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Comply with this AD within the compliance times specified, unless already done. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): ■ 2017–20–10 Airbus: Amendment 39–19067; Docket No. FAA–2017–0624; Product Identifier 2016–NM–135–AD. (a) Effective Date This AD is effective November 15, 2017. (b) Affected ADs This AD affects AD 2000–12–13, Amendment 39–11791 (65 FR 37845, June 19, 2000) (‘‘AD 2000–12–13’’). (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(3) of this AD, all manufacturer serial numbers. (1) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 22, Auto Flight. (e) Reason This AD was prompted by a report of a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current flight management and guidance computer (FMGC) standard. We are issuing this AD to prevent unstable approaches due to an unexpected thrust increase, which could result in PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (f) Compliance (g) Inspection and Replacement of Affected FMGC (1) Within 36 months after the effective date of this AD: Inspect the FMGC to determine if any FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD is installed. A review of airplane maintenance records is acceptable in lieu of inspecting the FMGC, provided those records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review. (2) If any affected FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD is found during any inspection or review required by paragraph (g)(1) of this AD: Within 36 months after the effective date of this AD, replace the FMGC with a serviceable FMGC having a part number that is not identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD, in accordance with the Accomplishment Instructions and paragraph 1.B. (concurrent actions) of the applicable service information specified in paragraphs (g)(2)(i) through (g)(2)(vi) of this AD, or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Refer to Figure 2 to paragraph (g)(2) of this AD and Figure 3 to paragraph (g)(2) of this AD for the lists of approved eligible FMGCs certified as of the effective date of this AD. (i) Airbus Service Bulletin A320–22–1090, Revision 11, dated July 20, 2004 (installation of FMGC part number (P/N) C13042BA01). (ii) Airbus Service Bulletin A320–22–1103, Revision 04, dated March 12, 2004 (installation of FMGC P/N C13043AA01). (iii) Airbus Service Bulletin A320–22– 1116, Revision 04, dated March 29, 2004 (installation of FMGC P/N C13043BA01). (iv) Airbus Service Bulletin A320–22– 1152, Revision 03, dated February 18, 2005 (installation of FMGC P/N C13043AA02). (v) Airbus Service Bulletin A320–22–1243, Revision 05, dated May 31, 2010 (installation of FMGC P/N C13043BA04). (vi) Airbus Service Bulletin A320–22– 1519, Revision 02, dated December 21, 2015 (installation of FMGC P/N C13207CA00). BILLING CODE 4910–13–P E:\FR\FM\11OCR1.SGM 11OCR1 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations 47087 Figure 1 to paragraphs (g)(l), (g)(2), (h)(l), (h)(2), and (j) of this AD -Affected FMGCs Airplanes FMGC part number B398AAM0303 B398AAM0405 B398AAM0406 B398AAM0407 B398AAM0408 B398AAM0409 B398AAM0410 B398AAM0411 B398AAM0412 B398BAM0101 B398BAM0202 B398BAM0203 B398BAM0204 B398BAM0205 B398BAM0206 B398BAM0207 B398BAM0208 B398BAM0209 B546BAM0101 B546BAM0202 B546BAM0203 B546BAM0204 B546BAM0205 B546BAM0206 B546CAM0101 B546CAM0102 B546CAM0103 B398BCM0101 B398BCM0102 B398BCM0103 B398BCM0104 B398BCM0105 B398BCM0106 B398BCM0107 B398BCM0108 B398BCM0109 B546BCM0101 B546BCM0102 B546BCM0203 B546BCM0204 B546BCM0205 B546CCM0101 B546CCM0102 B546CCM0103 A319-111, A319-112, A319-113, A319-114, A319-115, A320-211, A320-212, A320-214, A321-111, A321-112, A321-211, A321-212, and A321-213 (all CFM56) B398AAM0304 B546CCM0104 B546CCM0105 B546CCM0106 ethrower on DSK3G9T082PROD with RULES A319-131 A319-133 A320-232 A321-131 A321-232 VerDate Sep<11>2014 A319-132 A320-231 A320-233 A321-231 and (all V2500) 20:04 Oct 10, 2017 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4725 E:\FR\FM\11OCR1.SGM 11OCR1 ER11OC17.000</GPH> B546CAM0104 47088 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations Figure 2 to paragraph (g)(2) of this AD List of approved eligible FMGCs certified as of the effective date of this AD Airplanes FMGC part number C13042AA01 C13042AA02 C13042AA03 C13042AA04 C13042AA05 C13042AA06 C13042AA07 C13043AA01 A319-111, A319-112, A319-113, A319-114, A319-115, A320-211, A320-212, A320-214, A321-111, A321-112, A321-211, A321-212, and A321-213 (all CFM56) C13043AA02 C13043AA03 C13043AA04 C13043AA05 C13043AA06 G2858AAA03 Fmt 4700 Sfmt 4725 E:\FR\FM\11OCR1.SGM 11OCR1 ER11OC17.001</GPH> G2858AAA02 C13208AAOO Frm 00006 G2858AAA01 C13208AAOO PO 00000 G2858AAA03 C13208AAOO Jkt 244001 G2858AAA02 C13207CAOO 20:04 Oct 10, 2017 G2858AAA01 C13207CAOO VerDate Sep<11>2014 Flight Guidance (FG) software C13207AAOO ethrower on DSK3G9T082PROD with RULES FMGC hardware (h) Unaffected Airplanes (1) An airplane on which Airbus Modification 31896 or Airbus Modification 31897 has been embodied in production is not affected by the requirements of paragraph (g) of this AD, provided it is conclusively determined that no FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD has been installed on that airplane since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. A review of airplane maintenance records is acceptable to make this determination provided those VerDate Sep<11>2014 20:04 Oct 10, 2017 Jkt 244001 records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review. (2) An airplane on which the actions specified in paragraph (g)(2) have been done before the effective date of this AD is not affected by the requirements in paragraph (g) of this AD, provided it is conclusively determined that no FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD has been installed on that airplane since accomplishing the actions specified in paragraph (g)(2) of this AD. A review of airplane maintenance records is acceptable to PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 47089 make this determination provided those records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review. (i) Parts Installation Limitation Installation of an FMGC standard approved after the effective date of this AD on any airplane, is acceptable for compliance with the actions required by paragraph (g)(2) of this AD, provided the conditions specified in paragraphs (i)(1) and (i)(2) of this AD are accomplished. (1) The software and hardware standard, as applicable, must be approved by the E:\FR\FM\11OCR1.SGM 11OCR1 ER11OC17.002</GPH> ethrower on DSK3G9T082PROD with RULES Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations 47090 Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. (2) The installation must be accomplished using airplane modification instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. (j) Parts Installation Prohibition (k) Credit for Previous Actions As of the effective date of this AD, no person may install on any airplane an FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD. This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in Figure 4 to paragraph (k) of this AD. Figure 4 to paragraph (k) of this AD Service information acceptable for credit for actions in paragraph (g) (2) of this AD Airbus Service Bulletin C13042BA01 C13043AA01 C13043BA01 A320-22-1116 C13043AA02 A320-22-1152 C13043BA04 A320-22-1243 C13207CAOO A320-22-1519 March 5, 2002 April15, 2002 June 14, 2002 October 1, 2002 November 26, 2002 January 13, 2003 March 3, 2003 June 26, 2003 October 15, 2003 November 7, 2003 January 22, 2004 October 8, 2002 April 1, 2003 August 28, 2003 October 15, 2003 January 31, 2003 August 4, 2003 October 17, 2003 February 25, 2004 May 5, 2004 July 6, 2004 October 15, 2004 October 16, 2007 April1, 2008 September 10, 2008 February 17, 2009 March 3, 2010 June 26, 2015 01 A320-22-11 03 Date 00 01 02 03 04 05 06 07 08 09 10 00 01 02 03 00 01 02 03 00 01 02 00 01 02 03 04 00 A320-22-1090 Revision August 26, 2015 ethrower on DSK3G9T082PROD with RULES BILLING CODE 4910–13–C (m) Other FAA AD Provisions (l) Terminating Action for Other ADs The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found Accomplishing the actions required by paragraph (g)(1) of this AD, and, as applicable, paragraph (g)(2) of this AD, terminates all requirements of AD 2000–12– 13. VerDate Sep<11>2014 20:04 Oct 10, 2017 Jkt 244001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Section, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using E:\FR\FM\11OCR1.SGM 11OCR1 ER11OC17.003</GPH> FMGC/FG install Federal Register / Vol. 82, No. 195 / Wednesday, October 11, 2017 / Rules and Regulations 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. (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 Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. ethrower on DSK3G9T082PROD with RULES (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0122, dated June 21, 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– 2017–0624. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425– 227–1405; fax 425–227–1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–22–1090, Revision 11, dated July 20, 2004. (ii) Airbus Service Bulletin A320–22–1103, Revision 04, dated March 12, 2004. (iii) Airbus Service Bulletin A320–22– 1116, Revision 04, dated March 29, 2004. (iv) Airbus Service Bulletin A320–22– 1152, Revision 03, dated February 18, 2005. (v) Airbus Service Bulletin A320–22–1243, Revision 05, dated May 31, 2010. (vi) Airbus Service Bulletin A320–22– 1519, Revision 02, dated December 21, 2015. (3) 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. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 20:04 Oct 10, 2017 Jkt 244001 Issued in Renton, Washington, on September 20, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–21224 Filed 10–10–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0515; Product Identifier 2016–NM–171–AD; Amendment 39–19061; AD 2017–20–04] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes), and Model A310 series airplanes. This AD was prompted by reports of unreliable airspeed indications that were caused by pitot heater resistance shorted to ground. This AD requires replacement of certain parts. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 15, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 15, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet: https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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–2017– 0515. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 47091 www.regulations.gov by searching for and locating Docket No. FAA–2017– 0515; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone: 800–647– 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–2125; fax: 425– 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A300 B4– 600, B4–600R, and F4–600R series airplanes, Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes), and Model A310 series airplanes. The NPRM published in the Federal Register on June 9, 2017 (82 FR 26758) (‘‘the NPRM’’). The NPRM was prompted by reports of unreliable airspeed indications that were caused by pitot heater resistance shorted to ground. The NPRM proposed to require replacement of certain parts. We are issuing this AD to ensure proper flight crew awareness of unreliable airspeed indications. This condition, if not recognized by the flight crew, could possibly result in reduced control of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0195, dated September 30, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes), and Model A310 series airplanes. The MCAI states: An operator recently reported two events of unreliable airspeed indications. Investigations revealed that in both events, a Pitot heater resistance was shorted to ground. Pitot probes are heated to prevent ice accretion. De-icing performance of the Pitot probe might be reduced if Pitot probe heater E:\FR\FM\11OCR1.SGM 11OCR1

Agencies

[Federal Register Volume 82, Number 195 (Wednesday, October 11, 2017)]
[Rules and Regulations]
[Pages 47084-47091]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-21224]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0624; Product Identifier 2016-NM-135-AD; Amendment 
39-19067; AD 2017-20-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, -
232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes. This AD was prompted by a runway 
excursion due to an unexpected thrust increase leading to an unstable 
approach performed using the current flight management and guidance 
computer (FMGC) standard. This AD requires identification of 
potentially affected FMGCs, replacement of any affected FMGC, and 
applicable concurrent actions. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective November 15, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 15, 
2017.

ADDRESSES: For service information identified in this final rule, 
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 Standards Branch, 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-2017-
0624.

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-2017-
0624; 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 AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A319 
series airplanes, Model A320-211, -212, -214, -231, -232, and -233 
airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. The NPRM published in the Federal Register on June 29, 
2017 (82 FR 29440) (``the NPRM''). The NPRM was prompted by a runway 
excursion due to an unexpected thrust increase leading to an unstable 
approach performed using the current FMGC standard. The NPRM proposed 
to require identification of potentially affected FMGCs, replacement of 
any affected FMGC, and applicable concurrent actions. We are issuing 
this AD to prevent unstable approaches due to an unexpected thrust 
increase, which could result in reduced

[[Page 47085]]

controllability of the airplane and runway excursions.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0122, dated June 21, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A319 
series airplanes, Model A320-211, -212, -214, -231, -232, and -233 
airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and 
232 airplanes. The MCAI states:

    Following an instrument landing system (ILS) approach, during 
night, in rainy condition, an A321 aeroplane experienced a 
longitudinal runway excursion. Investigation revealed that the 
approach was not stabilized with an overspeed of 19 knots (kts) over 
the runway threshold, followed by a long flare (18 seconds) with 
touchdown far behind the touchdown zone. The aeroplane exited the 
runway at 75 kts and came to rest around 300 meters beyond the end 
of the runway. During the final approach, at 150 feet Radio 
Altimeter (RA) altitude, the corrected airspeed of the aeroplane was 
165 kts (24 kts overspeed). Auto thrust (ATHR) commanded a transient 
N1 increase up to 70% due to the ATHR speed Mach control law.
    The ATHR system on A320 family aeroplane was designed to 
maintain accurately the aircraft speed/Mach to speed/Mach target by 
commanding the thrust, featuring also a trade-off at low altitude 
between thrust corrections to maintain speed equal to speed target 
and too large thrust corrections destabilizing the aircraft 
trajectory near the ground. The conclusions of the investigations 
were that the main contributor to this runway excursion was a non-
stabilized approach not followed by a go-around. ATHR misbehaviour 
in case of large overspeed led to an unexpected thrust increase, 
which is considered as a contributor to the long flare.
    This ATHR characteristic, reported as ``Spurious thrust increase 
during approach,'' was initially found in 1996 and a modification 
was developed and introduced in Flight Guidance (FG) 2G standard 
``C8 or I8'' (C for CFM engines and I for IAE engines) in 2001.
    Prompted by these findings, Airbus introduced a programme to 
encourage operators to replace the FMGC Legacy with the FMGC 
equipped with Flight Management System type 2 (FMS2) and FG 
standard, which introduces additional operational capabilities, 
including Runway Overrun Protection System/Runway Overrun Warning 
(ROPS/ROW) and Autopilot/Traffic Collision Avoidance System (AP/
TCAS). It was determined that the ROPS, in a scenario similar to the 
one described above, would have triggered a <> 
aural alert before touchdown. Information was made available through 
Airbus Service Information Letter (SIL) 22-039 (later superseded by 
Word In Service Experience (WISE) In Service Information 
22.83.00003), and EASA published Safety Information Bulletin (SIB) 
2013-19, recommending the FMGC upgrade.
    Since EASA SIB was published, it was determined that many 
operators have chosen not to implement the optional upgrade that 
improves the ATHR behaviour.
    More recently, prompted by a recommendation from the BEA (Bureau 
d'Enqu[ecirc]tes et d'Analyses pour la s[eacute]curit[eacute] de 
l'aviation civile) of France, to reduce the risk of further runway 
excursions due to uninterrupted unstable approaches performed with 
the legacy FMGC standard, EASA decided to require installation of at 
least the first version of the FMS2 and associated FG for legacy 
aeroplanes.
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD 1999-411-140(B)R1 [which corresponds to FAA AD 
2000-12-13, Amendment 39-11791 (65 FR 37845, June 19, 2000) (``AD 
2000-12-13'')] and AD 1998-226-119(B)R1 [which corresponds to FAA AD 
98-19-08, Amendment 39-10750 (63 FR 50503, September 22, 1998)] to 
address different unsafe conditions, requiring to install a certain 
previous FMGC standard that may be susceptible to the ``Spurious 
thrust increase during approach''.
    For the reasons described above, this [EASA] AD * * * requires 
replacement of the affected FMGC units with upgraded units [and 
applicable concurrent actions].

    Concurrent actions include the installation of certain FMGCs, 
wiring, display management computers, wiring associated with pin 
programming, and applicable operational program configuration disks. 
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-2017-
0624.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Air Line Pilots 
Association, International supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information, which 
describes procedures for replacement of any affected FMGC with a 
serviceable FMGC. These documents are distinct since they apply to 
different airplane configurations.
     Airbus Service Bulletin A320-22-1090, Revision 11, dated 
July 20, 2004.
     Airbus Service Bulletin A320-22-1103, Revision 04, dated 
March 12, 2004.
     Airbus Service Bulletin A320-22-1116, Revision 04, dated 
March 29, 2004.
     Airbus Service Bulletin A320-22-1152, Revision 03, dated 
February 18, 2005.
     Airbus Service Bulletin A320-22-1243, Revision 05, dated 
May 31, 2010.
     Airbus Service Bulletin A320-22-1519, Revision 02, dated 
December 21, 2015.
    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.

Costs of Compliance

    We estimate that this AD affects 1,032 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  1 work-hour x $85 per                 $0             $85         $87,720
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
required based on the results of the inspection. We have no way of 
determining the number of aircraft that might need these replacements.

[[Page 47086]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  9 work-hours x $85 per hour = $765.         $30,000         $30,765
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 adding the following new airworthiness 
directive (AD):

2017-20-10 Airbus: Amendment 39-19067; Docket No. FAA-2017-0624; 
Product Identifier 2016-NM-135-AD.

(a) Effective Date

    This AD is effective November 15, 2017.

(b) Affected ADs

    This AD affects AD 2000-12-13, Amendment 39-11791 (65 FR 37845, 
June 19, 2000) (``AD 2000-12-13'').

(c) Applicability

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

(d) Subject

    Air Transport Association (ATA) of America Code 22, Auto Flight.

(e) Reason

    This AD was prompted by a report of a runway excursion due to an 
unexpected thrust increase leading to an unstable approach performed 
using the current flight management and guidance computer (FMGC) 
standard. We are issuing this AD to prevent unstable approaches due 
to an unexpected thrust increase, which could result in reduced 
controllability of the airplane and runway excursions.

(f) Compliance

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

(g) Inspection and Replacement of Affected FMGC

    (1) Within 36 months after the effective date of this AD: 
Inspect the FMGC to determine if any FMGC with an affected part 
number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), 
(h)(2), and (j) of this AD is installed. A review of airplane 
maintenance records is acceptable in lieu of inspecting the FMGC, 
provided those records can be relied upon for that purpose and the 
part number of the FMGC can be conclusively identified from that 
review.
    (2) If any affected FMGC with an affected part number identified 
in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of 
this AD is found during any inspection or review required by 
paragraph (g)(1) of this AD: Within 36 months after the effective 
date of this AD, replace the FMGC with a serviceable FMGC having a 
part number that is not identified in Figure 1 to paragraphs (g)(1), 
(g)(2), (h)(1), (h)(2), and (j) of this AD, in accordance with the 
Accomplishment Instructions and paragraph 1.B. (concurrent actions) 
of the applicable service information specified in paragraphs 
(g)(2)(i) through (g)(2)(vi) of this AD, or using a method approved 
by the Manager, International Section, Transport Standards Branch, 
FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA). Refer to Figure 2 to paragraph 
(g)(2) of this AD and Figure 3 to paragraph (g)(2) of this AD for 
the lists of approved eligible FMGCs certified as of the effective 
date of this AD.
    (i) Airbus Service Bulletin A320-22-1090, Revision 11, dated 
July 20, 2004 (installation of FMGC part number (P/N) C13042BA01).
    (ii) Airbus Service Bulletin A320-22-1103, Revision 04, dated 
March 12, 2004 (installation of FMGC P/N C13043AA01).
    (iii) Airbus Service Bulletin A320-22-1116, Revision 04, dated 
March 29, 2004 (installation of FMGC P/N C13043BA01).
    (iv) Airbus Service Bulletin A320-22-1152, Revision 03, dated 
February 18, 2005 (installation of FMGC P/N C13043AA02).
    (v) Airbus Service Bulletin A320-22-1243, Revision 05, dated May 
31, 2010 (installation of FMGC P/N C13043BA04).
    (vi) Airbus Service Bulletin A320-22-1519, Revision 02, dated 
December 21, 2015 (installation of FMGC P/N C13207CA00).

BILLING CODE 4910-13-P

[[Page 47087]]

[GRAPHIC] [TIFF OMITTED] TR11OC17.000


[[Page 47088]]


[GRAPHIC] [TIFF OMITTED] TR11OC17.001


[[Page 47089]]


[GRAPHIC] [TIFF OMITTED] TR11OC17.002

(h) Unaffected Airplanes

    (1) An airplane on which Airbus Modification 31896 or Airbus 
Modification 31897 has been embodied in production is not affected 
by the requirements of paragraph (g) of this AD, provided it is 
conclusively determined that no FMGC with an affected part number 
identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), 
and (j) of this AD has been installed on that airplane since the 
date of issuance of the original certificate of airworthiness or the 
original export certificate of airworthiness. A review of airplane 
maintenance records is acceptable to make this determination 
provided those records can be relied upon for that purpose and the 
part number of the FMGC can be conclusively identified from that 
review.
    (2) An airplane on which the actions specified in paragraph 
(g)(2) have been done before the effective date of this AD is not 
affected by the requirements in paragraph (g) of this AD, provided 
it is conclusively determined that no FMGC with an affected part 
number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), 
(h)(2), and (j) of this AD has been installed on that airplane since 
accomplishing the actions specified in paragraph (g)(2) of this AD. 
A review of airplane maintenance records is acceptable to make this 
determination provided those records can be relied upon for that 
purpose and the part number of the FMGC can be conclusively 
identified from that review.

(i) Parts Installation Limitation

    Installation of an FMGC standard approved after the effective 
date of this AD on any airplane, is acceptable for compliance with 
the actions required by paragraph (g)(2) of this AD, provided the 
conditions specified in paragraphs (i)(1) and (i)(2) of this AD are 
accomplished.
    (1) The software and hardware standard, as applicable, must be 
approved by the

[[Page 47090]]

Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus's EASA DOA.
    (2) The installation must be accomplished using airplane 
modification instructions approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA.

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane an FMGC with an affected part number identified in 
Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of 
this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g)(2) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
identified in Figure 4 to paragraph (k) of this AD.
[GRAPHIC] [TIFF OMITTED] TR11OC17.003

BILLING CODE 4910-13-C

(l) Terminating Action for Other ADs

    Accomplishing the actions required by paragraph (g)(1) of this 
AD, and, as applicable, paragraph (g)(2) of this AD, terminates all 
requirements of AD 2000-12-13.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Section, send it to the 
attention of the person identified in paragraph (n)(2) of this AD. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using

[[Page 47091]]

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.
    (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 
Section, Transport Standards Branch, 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 Airworthiness Directive 2016-0122, dated June 21, 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-2017-0624.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-22-1090, Revision 11, dated 
July 20, 2004.
    (ii) Airbus Service Bulletin A320-22-1103, Revision 04, dated 
March 12, 2004.
    (iii) Airbus Service Bulletin A320-22-1116, Revision 04, dated 
March 29, 2004.
    (iv) Airbus Service Bulletin A320-22-1152, Revision 03, dated 
February 18, 2005.
    (v) Airbus Service Bulletin A320-22-1243, Revision 05, dated May 
31, 2010.
    (vi) Airbus Service Bulletin A320-22-1519, Revision 02, dated 
December 21, 2015.
    (3) 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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 20, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-21224 Filed 10-10-17; 8:45 am]
 BILLING CODE 4910-13-P

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