Airworthiness Directives; Airbus Airplanes, 29440-29445 [2017-13406]

Download as PDF 29440 Proposed Rules Federal Register Vol. 82, No. 124 Thursday, June 29, 2017 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0624; Directorate Identifier 2016–NM–135–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt 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 proposed 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 proposed AD would require identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 14, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 sradovich on DSK3GMQ082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:13 Jun 28, 2017 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Jkt 241001 You may examine the AD docket on the Internet at http:// 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 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–2017–0624; Directorate Identifier 2016–NM–135–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 E:\FR\FM\29JNP1.SGM 29JNP1 29441 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules (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 http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0624. Other Related Rulemaking On September 2, 1998, we issued AD 98–19–08, Amendment 39–10750 (63 FR 50503, September 22, 1998) (‘‘AD 98–19–08’’), for certain Airbus Model A321 series airplanes. AD 98–19–08 was prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. AD 98–19–08 requires revising the airplane flight manual to prohibit automatic landings and Category III operations on runways with a magnetic orientation of 170 through 190 degrees inclusive. We issued AD 98–19–08 to prevent the use of erroneous automatic roll-out guidance generated by the FMGC, which could result in the airplane departing the runway upon landing. On June 9, 2000, we issued AD 2000– 12–13, Amendment 39–11791 (65 FR 37845, June 19, 2000) (‘‘AD 2000–12– 13’’), for certain Airbus Model A319, A320, and A321 series airplanes. AD 2000–12–13 was prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. AD 2000–12–13 requires modification or replacement of all existing FMGC’s, as applicable. We issued AD 2000–12–13 to prevent erroneous navigational calculations, which could result in an increased risk of collision with terrain or other airplanes. 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. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Differences Between This Proposed AD and the MCAI The MCAI supersedes two DGAC ADs, which correspond to FAA AD 98– 19–08 and AD 2000–12–13. The MCAI does not retain the requirements of the DGAC ADs. This proposed AD is a stand-alone AD that specifies accomplishing the actions required by this proposed AD would terminate all requirements of AD 2000–12–13. We have determined that the actions specified in AD 2000–12–13 must continue to be required until the actions of the proposed AD are accomplished. This proposed AD does not terminate the actions specified in AD 98–19–08 because it addresses a different unsafe condition relative to installing a certain previous FMGC standard, as stated in EASA AD 2016–0122. Costs of Compliance We estimate that this proposed AD affects 1,032 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS sradovich on DSK3GMQ082PROD with PROPOSALS Action Labor cost Inspection ................... 1 work-hour × $85 per hour = $85 ..................................................... We estimate the following costs to do any necessary replacements that would VerDate Sep<11>2014 16:13 Jun 28, 2017 Jkt 241001 be required based on the results of the proposed inspection. We have no way of PO 00000 Frm 00002 Fmt 4702 Cost per product Parts cost Sfmt 4702 $0 $85 Cost on U.S. operators $87,720 determining the number of aircraft that might need these replacements. E:\FR\FM\29JNP1.SGM 29JNP1 29442 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules ON-CONDITION COSTS Action Labor cost Replacement ..................... 9 work-hours × $85 per hour = $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. sradovich on DSK3GMQ082PROD with PROPOSALS 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. $30,000 $30,765 (f) Compliance 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 Cost per product Parts cost [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2017–0624; Directorate Identifier 2016–NM–135–AD. (a) Comments Due Date We must receive comments by August 14, 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. 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 Branch, ANM–116, Transport Airplane Directorate, 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). FIGURE 1 TO PARAGRAPHS (g)(1), (g)(2), (h)(1), (h)(2), AND (j) OF THIS AD—AFFECTED FMGCS Airplanes FMGC No. A319–111 ........................................................................... VerDate Sep<11>2014 16:13 Jun 28, 2017 Jkt 241001 PO 00000 B398AAM0303 Frm 00003 Fmt 4702 B398AAM0304 Sfmt 4702 E:\FR\FM\29JNP1.SGM B398AAM0405 29JNP1 B398AAM0406 29443 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules FIGURE 1 TO PARAGRAPHS (g)(1), (g)(2), (h)(1), (h)(2), AND (j) OF THIS AD—AFFECTED FMGCS—Continued Airplanes 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). A319–131 ........................................................................... A319–132 ........................................................................... A319–133 ........................................................................... A320–231 ........................................................................... A320–232 ........................................................................... A320–233. A321–131. A321–231 and A321–232 (all V2500). B398AAM0407 B398AAM0411 B398BAM0203 B398BAM0207 B546BAM0202 B546BAM0206 B546CAM0104 B398AAM0408 B398AAM0412 B398BAM0204 B398BAM0208 B546BAM0203 B546CAM0101 B398AAM0409 B398BAM0101 B398BAM0205 B398BAM0209 B546BAM0204 B546CAM0102 B398AAM0410 B398BAM0202 B398BAM0206 B546BAM0101 B546BAM0205 B546CAM0103 B398BCM0101 B398BCM0105 B398BCM0109 B546BCM0204 B546CCM0103 B398BCM0102 B398BCM0106 B546BCM0101 B546BCM0205 B546CCM0104 B398BCM0103 B398BCM0107 B546BCM0102 B546CCM0101 B546CCM0105 B398BCM0104 B398BCM0108 B546BCM0203 B546CCM0102 B546CCM0106 FIGURE 2 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE DATE OF THIS AD Airplanes A319–111 A319–112 A319–113 A319–114 A319–115 A320–211 A320–212 A320–214 A321–111 A321–112 A321–211 A321–212 A321–213 FMGC part No. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. and .......................................................................................................................................... (all CFM56) ............................................................................................................................. C13042AA01 C13042AA02 C13042AA03 C13042AA04 C13042AA05 C13042AA06 C13042AA07 C13043AA01 C13043AA02 C13043AA03 C13043AA04 C13043AA05 C13043AA06 FMGC hardware C13207AA00 C13207CA00 C13207CA00 C13208AA00 C13208AA00 C13208AA00 Flight Guidance (FG) software G2858AAA01 G2858AAA02 G2858AAA03 G2858AAA01 G2858AAA02 G2858AAA03 FIGURE 3 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE DATE OF THIS AD sradovich on DSK3GMQ082PROD with PROPOSALS Airplanes A319–131 A319–132 A319–133 A320–231 A320–232 A320–233 A321–131 A321–231 A321–232 FMGC part No. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. .................................................................................................................................................. and .......................................................................................................................................... (all V2500) ............................................................................................................................... VerDate Sep<11>2014 16:13 Jun 28, 2017 Jkt 241001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\29JNP1.SGM C13042BA01 C13042BA02 C13042BA03 C13042BA04 C13042BA05 C13042BA06 C13042BA07 C13042BA08 C13043BA01 C13043BA02 C13043BA03 C13043BA04 C13043BA05 C13043BA06 C13043BA07 29JNP1 29444 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules FIGURE 3 TO PARAGRAPH (g)(2) OF THIS AD—LIST OF APPROVED ELIGIBLE FMGCS CERTIFIED AS OF THE EFFECTIVE DATE OF THIS AD—Continued Airplanes C13043BA08 FMGC hardware C13207BA00 C13207DA00 C13207DA00 C13207DA00 C13208BA00 C13208BA00 C13208BA00 C13208BA00 (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 Manager, International Branch, ANM–116, (FG) software G2859AAA01 G2859AAA02 G2859AAA03 G2859AAA04 G2859AAA01 G2859AAA02 G2859AAA03 G2859AAA04 Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (2) The installation must be accomplished using airplane modification instructions approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, 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. 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 ....................................................... A320–22–1090 ................................................... C13043AA01 ....................................................... A320–22–1103 ................................................... C13043BA01 ....................................................... sradovich on DSK3GMQ082PROD with PROPOSALS FMGC/FG install A320–22–1116 ................................................... C13043AA02 ....................................................... A320–22–1152 ................................................... C13043BA04 ....................................................... A320–22–1243 ................................................... VerDate Sep<11>2014 17:47 Jun 28, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\29JNP1.SGM Revision 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 29JNP1 March 5, 2002. April 15, 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. April 1, 2008. September 10, 2008. February 17, 2009. March 3, 2010. 29445 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules FIGURE 4 TO PARAGRAPH (k) OF THIS AD—SERVICE INFORMATION ACCEPTABLE FOR CREDIT FOR ACTIONS IN PARAGRAPH (g)(2) OF THIS AD—Continued FMGC/FG install Airbus service bulletin C13207CA00 ...................................................... A320–22–1519 ................................................... Issued in Renton, Washington, on June 16, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (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. sradovich on DSK3GMQ082PROD with PROPOSALS (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. BILLING CODE 4910–13–P (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 http://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 Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227 1405; fax 425–227 1149. (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 http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. VerDate Sep<11>2014 16:13 Jun 28, 2017 Jkt 241001 [FR Doc. 2017–13406 Filed 6–28–17; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0648; Directorate Identifier 2017–CE–012–AD] RIN 2120–AA64 Airworthiness Directives; Piaggio Aero Industries S.p.A. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Piaggio Aero Industries S.p.A. Model P–180 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as disbonding of the upper and lower metal skin from the honeycomb core on the elevator assembly and other flight control surfaces. We are issuing this proposed AD to require actions to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 14, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Revision Date 00 01 June 26, 2015. August 26, 2015. 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Piaggio Aero Industries S.p.A—Continued Airworthiness, Via Pionieri e Aviatori d’Italia snc—16154 Genova, Italy; Telephone: +39 010 0998046; Fax: None; email: airworthiness@ piaggioaerospace.it; Internet: www.piaggioaerospace.it/en/customersupport#care. You may review this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0648; 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 (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0648; Directorate Identifier 2017–CE–012–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 E:\FR\FM\29JNP1.SGM 29JNP1

Agencies

[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)]
[Proposed Rules]
[Pages 29440-29445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13406]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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

========================================================================


Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / 
Proposed Rules

[[Page 29440]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0624; Directorate Identifier 2016-NM-135-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed 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 proposed AD would require 
identification of potentially affected FMGCs, replacement of any 
affected FMGC, and applicable concurrent actions. We are proposing this 
AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 14, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
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 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-2017-0624; 
Directorate Identifier 2016-NM-135-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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

[[Page 29441]]

(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 
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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0624.

Other Related Rulemaking

    On September 2, 1998, we issued AD 98-19-08, Amendment 39-10750 (63 
FR 50503, September 22, 1998) (``AD 98-19-08''), for certain Airbus 
Model A321 series airplanes. AD 98-19-08 was prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. AD 98-19-08 requires revising the airplane 
flight manual to prohibit automatic landings and Category III 
operations on runways with a magnetic orientation of 170 through 190 
degrees inclusive. We issued AD 98-19-08 to prevent the use of 
erroneous automatic roll-out guidance generated by the FMGC, which 
could result in the airplane departing the runway upon landing.
    On June 9, 2000, we issued AD 2000-12-13, Amendment 39-11791 (65 FR 
37845, June 19, 2000) (``AD 2000-12-13''), for certain Airbus Model 
A319, A320, and A321 series airplanes. AD 2000-12-13 was prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. AD 2000-12-13 requires modification or 
replacement of all existing FMGC's, as applicable. We issued AD 2000-
12-13 to prevent erroneous navigational calculations, which could 
result in an increased risk of collision with terrain or other 
airplanes.

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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Differences Between This Proposed AD and the MCAI

    The MCAI supersedes two DGAC ADs, which correspond to FAA AD 98-19-
08 and AD 2000-12-13. The MCAI does not retain the requirements of the 
DGAC ADs. This proposed AD is a stand-alone AD that specifies 
accomplishing the actions required by this proposed AD would terminate 
all requirements of AD 2000-12-13. We have determined that the actions 
specified in AD 2000-12-13 must continue to be required until the 
actions of the proposed AD are accomplished.
    This proposed AD does not terminate the actions specified in AD 98-
19-08 because it addresses a different unsafe condition relative to 
installing a certain previous FMGC standard, as stated in EASA AD 2016-
0122.

Costs of Compliance

    We estimate that this proposed AD affects 1,032 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
----------------------------------------------------------------------------------------------------------------
Inspection....................  1 work-hour x $85 per hour = $85              $0             $85         $87,720
----------------------------------------------------------------------------------------------------------------

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

[[Page 29442]]



                                               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.

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2017-0624; Directorate Identifier 2016-NM-
135-AD.

(a) Comments Due Date

    We must receive comments by August 14, 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 Branch, ANM-116, Transport Airplane 
Directorate, 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).

                                Figure 1 to Paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of This AD--Affected FMGCs
--------------------------------------------------------------------------------------------------------------------------------------------------------
 
--------------------------------------------------------------------------------------------------------------------------------------------------------
Airplanes                                                                                 FMGC No.
--------------------------------------------------------------------------------------------------------------------------------------------------------
A319-111.........................  B398AAM0303                   B398AAM0304                   B398AAM0405                   B398AAM0406

[[Page 29443]]

 
A319-112.........................  B398AAM0407                   B398AAM0408                   B398AAM0409                   B398AAM0410
A319-113.........................  B398AAM0411                   B398AAM0412                   B398BAM0101                   B398BAM0202
A319-114.........................  B398BAM0203                   B398BAM0204                   B398BAM0205                   B398BAM0206
A319-115.........................  B398BAM0207                   B398BAM0208                   B398BAM0209                   B546BAM0101
A320-211.........................  B546BAM0202                   B546BAM0203                   B546BAM0204                   B546BAM0205
A320-212.........................  B546BAM0206                   B546CAM0101                   B546CAM0102                   B546CAM0103
A320-214.........................  B546CAM0104
A321-111.........................
A321-112.........................
A321-211.........................
A321-212 and A321-213 (all CFM56)
A319-131.........................  B398BCM0101                   B398BCM0102                   B398BCM0103                   B398BCM0104
A319-132.........................  B398BCM0105                   B398BCM0106                   B398BCM0107                   B398BCM0108
A319-133.........................  B398BCM0109                   B546BCM0101                   B546BCM0102                   B546BCM0203
A320-231.........................  B546BCM0204                   B546BCM0205                   B546CCM0101                   B546CCM0102
A320-232.........................  B546CCM0103                   B546CCM0104                   B546CCM0105                   B546CCM0106
A320-233.........................
A321-131.........................
A321-231 and A321-232 (all V2500)
--------------------------------------------------------------------------------------------------------------------------------------------------------


 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 No.
----------------------------------------------------------------------------------------------------------------
A319-111................................                                C13042AA01
A319-112................................                                C13042AA02
A319-113................................                                C13042AA03
A319-114................................                                C13042AA04
A319-115................................                                C13042AA05
A320-211................................                                C13042AA06
A320-212................................                                C13042AA07
A320-214................................                                C13043AA01
A321-111................................                                C13043AA02
A321-112................................                                C13043AA03
A321-211................................                                C13043AA04
A321-212 and............................                                C13043AA05
A321-213 (all CFM56)....................                                C13043AA06
                                         -----------------------------------------------------------------------
                                                     FMGC hardware                      Flight Guidance
                                                                              (FG) software
                                         -----------------------------------------------------------------------
                                          C13207AA00                          G2858AAA01
                                          C13207CA00                          G2858AAA02
                                          C13207CA00                          G2858AAA03
                                          C13208AA00                          G2858AAA01
                                          C13208AA00                          G2858AAA02
                                          C13208AA00                          G2858AAA03
----------------------------------------------------------------------------------------------------------------


 Figure 3 to Paragraph (g)(2) of This AD--List of Approved Eligible FMGCs Certified as of the Effective Date of
                                                     This AD
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
Airplanes                                                              FMGC part No.
----------------------------------------------------------------------------------------------------------------
A319-131................................                                C13042BA01
A319-132................................                                C13042BA02
A319-133................................                                C13042BA03
A320-231................................                                C13042BA04
A320-232................................                                C13042BA05
A320-233................................                                C13042BA06
A321-131................................                                C13042BA07
A321-231 and............................                                C13042BA08
A321-232 (all V2500)....................                                C13043BA01
                                                                        C13043BA02
                                                                        C13043BA03
                                                                        C13043BA04
                                                                        C13043BA05
                                                                        C13043BA06
                                                                        C13043BA07

[[Page 29444]]

 
                                                                        C13043BA08
                                         -----------------------------------------------------------------------
                                                     FMGC hardware                       (FG) software
                                         -----------------------------------------------------------------------
                                          C13207BA00                          G2859AAA01
                                          C13207DA00                          G2859AAA02
                                          C13207DA00                          G2859AAA03
                                          C13207DA00                          G2859AAA04
                                          C13208BA00                          G2859AAA01
                                          C13208BA00                          G2859AAA02
                                          C13208BA00                          G2859AAA03
                                          C13208BA00                          G2859AAA04
----------------------------------------------------------------------------------------------------------------

(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 Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
    (2) The installation must be accomplished using airplane 
modification instructions approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, 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.

 Figure 4 to Paragraph (k) of this AD--Service Information Acceptable for Credit for Actions in Paragraph (g)(2)
                                                   of This AD
----------------------------------------------------------------------------------------------------------------
         FMGC/FG install           Airbus service bulletin     Revision                     Date
----------------------------------------------------------------------------------------------------------------
C13042BA01......................  A320-22-1090............              00  March 5, 2002.
                                                                        01  April 15, 2002.
                                                                        02  June 14, 2002.
                                                                        03  October 1, 2002.
                                                                        04  November 26, 2002.
                                                                        05  January 13, 2003.
                                                                        06  March 3, 2003.
                                                                        07  June 26, 2003.
                                                                        08  October 15, 2003.
                                                                        09  November 7, 2003.
                                                                        10  January 22, 2004.
C13043AA01......................  A320-22-1103............              00  October 8, 2002.
                                                                        01  April 1, 2003.
                                                                        02  August 28, 2003.
                                                                        03  October 15, 2003.
C13043BA01......................  A320-22-1116............              00  January 31, 2003.
                                                                        01  August 4, 2003.
                                                                        02  October 17, 2003.
                                                                        03  February 25, 2004.
C13043AA02......................  A320-22-1152............              00  May 5, 2004.
                                                                        01  July 6, 2004.
                                                                        02  October 15, 2004.
C13043BA04......................  A320-22-1243............              00  October 16, 2007.
                                                                        01  April 1, 2008.
                                                                        02  September 10, 2008.
                                                                        03  February 17, 2009.
                                                                        04  March 3, 2010.

[[Page 29445]]

 
C13207CA00......................  A320-22-1519............              00  June 26, 2015.
                                                                        01  August 26, 2015.
----------------------------------------------------------------------------------------------------------------

(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 Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to the attention of 
the person identified in paragraph (n)(2) of this AD. 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.
    (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.

(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 http://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 Branch, ANM 116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227 1405; fax 425-227 1149.
    (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 http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on June 16, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-13406 Filed 6-28-17; 8:45 am]
 BILLING CODE 4910-13-P