| Page Range | 29440-29445 | |
| FR Document | 2017-13406 |
[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)] [Proposed Rules] [Pages 29440-29445] From the Federal Register Online [www.thefederalregister.org] [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 [email protected]; 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: [email protected]. 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 [email protected]; 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
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 14, 2017. | |
| 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. | |
| FR Citation | 82 FR 29440 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |