82 FR 29440 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 124 (June 29, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 124 (June 29, 2017)
| 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
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Proposed Rules Federal Register
Vol. 82, No. 124
Thursday, June 29, 2017
This section of the FEDERAL REGISTER p.m., Monday through Friday, except will also post a report summarizing each
contains notices to the public of the proposed Federal holidays. substantive verbal contact we receive
issuance of rules and regulations. The For service information identified in about this proposed AD.
purpose of these notices is to give interested this NPRM, contact Airbus,
persons an opportunity to participate in the Discussion
Airworthiness Office—EIAS, 1 Rond
rule making prior to the adoption of the final The European Aviation Safety Agency
rules.
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 (EASA), which is the Technical Agent
96; fax +33 5 61 93 44 51; email for the Member States of the European
DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com; Union, has issued EASA Airworthiness
Internet http://www.airbus.com. You Directive 2016–0122, dated June 21,
Federal Aviation Administration may view this referenced service 2016 (referred to after this as the
information at the FAA, Transport Mandatory Continuing Airworthiness
14 CFR Part 39 Airplane Directorate, 1601 Lind Avenue Information, or ‘‘the MCAI’’), to correct
SW., Renton, WA. For information on an unsafe condition for all Airbus
[Docket No. FAA–2017–0624; Directorate Model A319 series airplanes, Model
Identifier 2016–NM–135–AD] the availability of this material at the
FAA, call 425–227–1221. A320–211, –212, –214, –231, –232, and
RIN 2120–AA64 –233 airplanes, and Model A321–111,
Examining the AD Docket –112, –131, –211, –212, –213, –231, and
Airworthiness Directives; Airbus You may examine the AD docket on –232 airplanes. The MCAI states:
Airplanes the Internet at http:// Following an instrument landing system
AGENCY: Federal Aviation www.regulations.gov by searching for (ILS) approach, during night, in rainy
Administration (FAA), DOT. and locating Docket No. FAA–2017– condition, an A321 aeroplane experienced a
ACTION: Notice of proposed rulemaking
0624; or in person at the Docket longitudinal runway excursion. Investigation
Management Facility between 9 a.m. revealed that the approach was not stabilized
(NPRM). with an overspeed of 19 knots (kts) over the
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket runway threshold, followed by a long flare
SUMMARY: We propose to adopt a new
(18 seconds) with touchdown far behind the
airworthiness directive (AD) for all contains this proposed AD, the touchdown zone. The aeroplane exited the
Airbus Model A319 series airplanes, regulatory evaluation, any comments runway at 75 kts and came to rest around 300
Model A320–211, –212, –214, –231, received, and other information. The meters beyond the end of the runway. During
–232, and –233 airplanes, and Model street address for the Docket Operations the final approach, at 150 feet Radio
A321–111, –112, –131, –211, –212, office (telephone 800–647–5527) is in Altimeter (RA) altitude, the corrected
–213, –231, and –232 airplanes. This the ADDRESSES section. Comments will airspeed of the aeroplane was 165 kts (24 kts
proposed AD was prompted by a be available in the AD docket shortly overspeed). Auto thrust (ATHR) commanded
after receipt. a transient N1 increase up to 70% due to the
runway excursion due to an unexpected
ATHR speed Mach control law.
thrust increase leading to an unstable FOR FURTHER INFORMATION CONTACT: The ATHR system on A320 family
approach performed using the current Sanjay Ralhan, Aerospace Engineer, aeroplane was designed to maintain
flight management and guidance International Branch, ANM–116, accurately the aircraft speed/Mach to speed/
computer (FMGC) standard. This Transport Airplane Directorate, FAA, Mach target by commanding the thrust,
proposed AD would require 1601 Lind Avenue SW., Renton, WA featuring also a trade-off at low altitude
identification of potentially affected 98057–3356; telephone 425–227–1405; between thrust corrections to maintain speed
FMGCs, replacement of any affected equal to speed target and too large thrust
fax 425–227–1149.
corrections destabilizing the aircraft
FMGC, and applicable concurrent SUPPLEMENTARY INFORMATION: trajectory near the ground. The conclusions
actions. We are proposing this AD to of the investigations were that the main
address the unsafe condition on these Comments Invited
contributor to this runway excursion was a
products. We invite you to send any written non-stabilized approach not followed by a
DATES: We must receive comments on relevant data, views, or arguments about go-around. ATHR misbehaviour in case of
this proposed AD. Send your comments large overspeed led to an unexpected thrust
this proposed AD by August 14, 2017.
to an address listed under the increase, which is considered as a
ADDRESSES: You may send comments, contributor to the long flare.
using the procedures found in 14 CFR ADDRESSES section. Include ‘‘Docket No.
This ATHR characteristic, reported as
11.43 and 11.45, by any of the following FAA–2017–0624; Directorate Identifier ‘‘Spurious thrust increase during approach,’’
methods: 2016–NM–135–AD’’ at the beginning of was initially found in 1996 and a
• Federal eRulemaking Portal: Go to your comments. We specifically invite modification was developed and introduced
http://www.regulations.gov. Follow the comments on the overall regulatory, in Flight Guidance (FG) 2G standard ‘‘C8 or
economic, environmental, and energy I8’’ (C for CFM engines and I for IAE engines)
sradovich on DSK3GMQ082PROD with PROPOSALS
instructions for submitting comments.
• Fax: 202–493–2251. aspects of this proposed AD. We will in 2001.
• Mail: U.S. Department of consider all comments received by the Prompted by these findings, Airbus
introduced a programme to encourage
Transportation, Docket Operations, M– closing date and may amend this
operators to replace the FMGC Legacy with
30, West Building Ground Floor, Room proposed AD based on those comments. the FMGC equipped with Flight Management
W12–140, 1200 New Jersey Avenue SE., We will post all comments we System type 2 (FMS2) and FG standard,
Washington, DC 20590. receive, without change, to http:// which introduces additional operational
• Hand Delivery: Deliver to Mail www.regulations.gov, including any capabilities, including Runway Overrun
address above between 9 a.m. and 5 personal information you provide. We Protection System/Runway Overrun Warning
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![Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules 29441
(ROPS/ROW) and Autopilot/Traffic Collision A321 series airplanes. AD 98–19–08 was • Airbus Service Bulletin A320–22–
Avoidance System (AP/TCAS). It was prompted by issuance of mandatory 1519, Revision 02, dated December 21,
determined that the ROPS, in a scenario continuing airworthiness information by 2015.
similar to the one described above, would
have triggered a ‘‘RUNWAY TOO SHORT’’
a foreign civil airworthiness authority. This service information is reasonably
aural alert before touchdown. Information AD 98–19–08 requires revising the available because the interested parties
was made available through Airbus Service airplane flight manual to prohibit have access to it through their normal
Information Letter (SIL) 22–039 (later automatic landings and Category III course of business or by the means
superseded by Word In Service Experience operations on runways with a magnetic identified in the ADDRESSES section.
(WISE) In Service Information 22.83.00003), orientation of 170 through 190 degrees
and EASA published Safety Information inclusive. We issued AD 98–19–08 to FAA’s Determination and Requirements
Bulletin (SIB) 2013–19, recommending the of This Proposed AD
prevent the use of erroneous automatic
FMGC upgrade.
Since EASA SIB was published, it was roll-out guidance generated by the This product has been approved by
determined that many operators have chosen FMGC, which could result in the the aviation authority of another
not to implement the optional upgrade that airplane departing the runway upon country, and is approved for operation
improves the ATHR behaviour. landing. in the United States. Pursuant to our
More recently, prompted by a On June 9, 2000, we issued AD 2000– bilateral agreement with the State of
recommendation from the BEA (Bureau 12–13, Amendment 39–11791 (65 FR
d’Enquêtes et d’Analyses pour la sécurité de
Design Authority, we have been notified
37845, June 19, 2000) (‘‘AD 2000–12– of the unsafe condition described in the
l’aviation civile) of France, to reduce the risk
of further runway excursions due to
13’’), for certain Airbus Model A319, MCAI and service information
uninterrupted unstable approaches A320, and A321 series airplanes. AD referenced above. We are proposing this
performed with the legacy FMGC standard, 2000–12–13 was prompted by issuance AD because we evaluated all pertinent
EASA decided to require installation of at of mandatory continuing airworthiness information and determined an unsafe
least the first version of the FMS2 and information by a foreign civil condition exists and is likely to exist or
associated FG for legacy aeroplanes. airworthiness authority. AD 2000–12–13
DGAC [Direction Générale de l’Aviation
develop on other products of these same
requires modification or replacement of type designs.
Civile] France issued AD 1999–411–140(B)R1
all existing FMGC’s, as applicable. We
[which corresponds to FAA AD 2000–12–13, Differences Between This Proposed AD
Amendment 39–11791 (65 FR 37845, June issued AD 2000–12–13 to prevent
erroneous navigational calculations, and the MCAI
19, 2000) (‘‘AD 2000–12–13’’)] and AD 1998–
226–119(B)R1 [which corresponds to FAA which could result in an increased risk The MCAI supersedes two DGAC
AD 98–19–08, Amendment 39–10750 (63 FR of collision with terrain or other ADs, which correspond to FAA AD 98–
50503, September 22, 1998)] to address airplanes.
different unsafe conditions, requiring to
19–08 and AD 2000–12–13. The MCAI
install a certain previous FMGC standard that Related Service Information Under 1 does not retain the requirements of the
may be susceptible to the ‘‘Spurious thrust CFR Part 51 DGAC ADs. This proposed AD is a
increase during approach’’. stand-alone AD that specifies
Airbus has issued the following
For the reasons described above, this accomplishing the actions required by
[EASA] AD * * * requires replacement of service information, which describes
this proposed AD would terminate all
the affected FMGC units with upgraded units procedures for replacement of any
requirements of AD 2000–12–13. We
[and applicable concurrent actions]. affected FMGC with a serviceable
have determined that the actions
Concurrent actions include the FMGC. These documents are distinct
specified in AD 2000–12–13 must
installation of certain FMGCs, wiring, since they apply to different airplane
continue to be required until the actions
display management computers, wiring configurations.
of the proposed AD are accomplished.
associated with pin programming, and • Airbus Service Bulletin A320–22–
applicable operational program 1090, Revision 11, dated July 20, 2004. This proposed AD does not terminate
configuration disks. You may examine • Airbus Service Bulletin A320–22– the actions specified in AD 98–19–08
the MCAI in the AD docket on the 1103, Revision 04, dated March 12, because it addresses a different unsafe
Internet at http://www.regulations.gov 2004. condition relative to installing a certain
by searching for and locating Docket No. • Airbus Service Bulletin A320–22– previous FMGC standard, as stated in
FAA–2017–0624. 1116, Revision 04, dated March 29, EASA AD 2016–0122.
2004. Costs of Compliance
Other Related Rulemaking • Airbus Service Bulletin A320–22–
On September 2, 1998, we issued AD 1152, Revision 03, dated February 18, We estimate that this proposed AD
98–19–08, Amendment 39–10750 (63 2005. affects 1,032 airplanes of U.S. registry.
FR 50503, September 22, 1998) (‘‘AD • Airbus Service Bulletin A320–22– We estimate the following costs to
98–19–08’’), for certain Airbus Model 1243, Revision 05, dated May 31, 2010. comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on
Action Labor cost Parts cost product U.S. operators
Inspection ................... 1 work-hour × $85 per hour = $85 ..................................................... $0 $85 $87,720
sradovich on DSK3GMQ082PROD with PROPOSALS
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacements that would proposed inspection. We have no way of might need these replacements.
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![29442 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement ..................... 9 work-hours × $85 per hour = $765 ....................................................................... $30,000 $30,765
Authority for This Rulemaking The Proposed Amendment (f) Compliance
Title 49 of the United States Code Comply with this AD within the
Accordingly, under the authority compliance times specified, unless already
specifies the FAA’s authority to issue delegated to me by the Administrator,
rules on aviation safety. Subtitle I, done.
the FAA proposes to amend 14 CFR part
section 106, describes the authority of 39 as follows: (g) Inspection and Replacement of Affected
the FAA Administrator. ‘‘Subtitle VII: FMGC
Aviation Programs,’’ describes in more PART 39—AIRWORTHINESS (1) Within 36 months after the effective
detail the scope of the Agency’s DIRECTIVES date of this AD: Inspect the FMGC to
authority. determine if any FMGC with an affected part
We are issuing this rulemaking under number identified in Figure 1 to paragraphs
■ 1. The authority citation for part 39 (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD
the authority described in ‘‘Subtitle VII,
continues to read as follows: is installed. A review of airplane
Part A, Subpart III, Section 44701:
General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701. maintenance records is acceptable in lieu of
section, Congress charges the FAA with inspecting the FMGC, provided those records
§ 39.13 [Amended] can be relied upon for that purpose and the
promoting safe flight of civil aircraft in part number of the FMGC can be
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding conclusively identified from that review.
for practices, methods, and procedures the following new airworthiness (2) If any affected FMGC with an affected
the Administrator finds necessary for directive (AD): part number identified in Figure 1 to
safety in air commerce. This regulation Airbus: Docket No. FAA–2017–0624; paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j)
is within the scope of that authority Directorate Identifier 2016–NM–135–AD.
of this AD is found during any inspection or
because it addresses an unsafe condition review required by paragraph (g)(1) of this
that is likely to exist or develop on (a) Comments Due Date AD: Within 36 months after the effective date
products identified in this rulemaking We must receive comments by August 14, of this AD, replace the FMGC with a
action. serviceable FMGC having a part number that
2017.
is not identified in Figure 1 to paragraphs
Regulatory Findings (b) Affected ADs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD,
This AD affects AD 2000–12–13, in accordance with the Accomplishment
We determined that this proposed AD Instructions and paragraph 1.B. (concurrent
would not have federalism implications Amendment 39–11791 (65 FR 37845, June
actions) of the applicable service information
under Executive Order 13132. This 19, 2000) (‘‘AD 2000–12–13’’).
specified in paragraphs (g)(2)(i) through
proposed AD would not have a (c) Applicability (g)(2)(vi) of this AD, or using a method
substantial direct effect on the States, on This AD applies to the Airbus airplanes,
approved by the Manager, International
the relationship between the national Branch, ANM–116, Transport Airplane
certificated in any category, identified in
Government and the States, or on the Directorate, FAA; or the European Aviation
paragraphs (c)(1) through (c)(3) of this AD, all
distribution of power and Safety Agency (EASA); or Airbus’s EASA
manufacturer serial numbers.
responsibilities among the various Design Organization Approval (DOA). Refer
(1) Airbus Model A319–111, –112, –113, to Figure 2 to paragraph (g)(2) of this AD and
levels of government. –114, –115, –131, –132, and –133 airplanes. Figure 3 to paragraph (g)(2) of this AD for the
For the reasons discussed above, I (2) Airbus Model A320–211, –212, –214, lists of approved eligible FMGCs certified as
certify this proposed regulation: –231, –232, and –233 airplanes. of the effective date of this AD.
1. Is not a ‘‘significant regulatory (3) Airbus Model A321–111, –112, –131, (i) Airbus Service Bulletin A320–22–1090,
action’’ under Executive Order 12866; –211, –212, –213, –231, and –232 airplanes. Revision 11, dated July 20, 2004 (installation
2. Is not a ‘‘significant rule’’ under the of FMGC part number (P/N) C13042BA01).
(d) Subject
DOT Regulatory Policies and Procedures (ii) Airbus Service Bulletin A320–22–1103,
(44 FR 11034, February 26, 1979); Air Transport Association (ATA) of Revision 04, dated March 12, 2004
3. Will not affect intrastate aviation in America Code 22, Auto Flight. (installation of FMGC P/N C13043AA01).
Alaska; and (e) Reason (iii) Airbus Service Bulletin A320–22–
4. Will not have a significant 1116, Revision 04, dated March 29, 2004
This AD was prompted by a report of a (installation of FMGC P/N C13043BA01).
economic impact, positive or negative, runway excursion due to an unexpected
on a substantial number of small entities (iv) Airbus Service Bulletin A320–22–
thrust increase leading to an unstable 1152, Revision 03, dated February 18, 2005
under the criteria of the Regulatory approach performed using the current flight (installation of FMGC P/N C13043AA02).
Flexibility Act. management and guidance computer (FMGC) (v) Airbus Service Bulletin A320–22–1243,
List of Subjects in 14 CFR Part 39 standard. We are issuing this AD to prevent Revision 05, dated May 31, 2010 (installation
unstable approaches due to an unexpected of FMGC P/N C13043BA04).
Air transportation, Aircraft, Aviation thrust increase, which could result in (vi) Airbus Service Bulletin A320–22–
sradovich on DSK3GMQ082PROD with PROPOSALS
safety, Incorporation by reference, reduced controllability of the airplane and 1519, Revision 02, dated December 21, 2015
Safety. runway excursions. (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
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![Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Proposed Rules 29445
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 Revision Date
C13207CA00 ...................................................... A320–22–1519 ................................................... 00 June 26, 2015.
01 August 26, 2015.
(l) Terminating Action for Other ADs Issued in Renton, Washington, on June 16, 30, West Building Ground Floor, Room
Accomplishing the actions required by 2017. W12–140, 1200 New Jersey Avenue SE.,
paragraph (g)(1) of this AD, and, as Michael Kaszycki, Washington, DC 20590, between 9 a.m.
applicable, paragraph (g)(2) of this AD, Acting Manager, Transport Airplane and 5 p.m., Monday through Friday,
terminates all requirements of AD 2000–12– Directorate, Aircraft Certification Service. except Federal holidays.
13. For service information identified in
[FR Doc. 2017–13406 Filed 6–28–17; 8:45 am]
(m) Other FAA AD Provisions BILLING CODE 4910–13–P this proposed AD, contact Piaggio Aero
The following provisions also apply to this Industries S.p.A—Continued
AD: Airworthiness, Via Pionieri e Aviatori
(1) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION d’Italia snc—16154 Genova, Italy;
(AMOCs): The Manager, International Telephone: +39 010 0998046; Fax:
Branch, ANM–116, Transport Airplane Federal Aviation Administration None; email: airworthiness@
Directorate, FAA, has the authority to
piaggioaerospace.it; Internet:
approve AMOCs for this AD, if requested 14 CFR Part 39
using the procedures found in 14 CFR 39.19. www.piaggioaerospace.it/en/customer-
In accordance with 14 CFR 39.19, send your [Docket No. FAA–2017–0648; Directorate support#care. You may review this
request to your principal inspector or local Identifier 2017–CE–012–AD] referenced service information at the
Flight Standards District Office, as FAA, Small Airplane Directorate, 901
appropriate. If sending information directly RIN 2120–AA64
Locust, Kansas City, Missouri 64106.
to the International Branch, send it to the For information on the availability of
attention of the person identified in Airworthiness Directives; Piaggio Aero
Industries S.p.A. Airplanes this material at the FAA, call (816) 329–
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC- 4148.
REQUESTS@faa.gov. Before using any AGENCY: Federal Aviation
Administration (FAA), Department of Examining the AD Docket
approved AMOC, notify your appropriate
principal inspector, or lacking a principal Transportation (DOT). You may examine the AD docket on
inspector, the manager of the local flight ACTION: Notice of proposed rulemaking the Internet at http://
standards district office/certificate holding (NPRM). www.regulations.gov by searching for
district office. and locating Docket No. FAA–2017–
(2) Contacting the Manufacturer: For any SUMMARY: We propose to adopt a new 0648; or in person at the Docket
requirement in this AD to obtain corrective
airworthiness directive (AD) for Piaggio Management Facility between 9 a.m.
actions from a manufacturer, the action must
be accomplished using a method approved Aero Industries S.p.A. Model P–180 and 5 p.m., Monday through Friday,
by the Manager, International Branch, ANM– airplanes. This proposed AD results except Federal holidays. The AD docket
116, Transport Airplane Directorate, FAA; or from mandatory continuing contains this proposed AD, the
EASA; or Airbus’s EASA DOA. If approved airworthiness information (MCAI) regulatory evaluation, any comments
by the DOA, the approval must include the originated by an aviation authority of received, and other information. The
DOA-authorized signature. another country to identify and correct street address for the Docket Office
(n) Related Information an unsafe condition on an aviation (telephone (800) 647–5527) is in the
(1) Refer to Mandatory Continuing product. The MCAI describes the unsafe ADDRESSES section. Comments will be
Airworthiness Information (MCAI) EASA condition as disbonding of the upper available in the AD docket shortly after
Airworthiness Directive 2016–0122, dated and lower metal skin from the receipt.
June 21, 2016, for related information. This honeycomb core on the elevator FOR FURTHER INFORMATION CONTACT:
MCAI may be found in the AD docket on the assembly and other flight control
Internet at http://www.regulations.gov by
Mike Kiesov, Aerospace Engineer, FAA,
surfaces. We are issuing this proposed Small Airplane Directorate, 901 Locust,
searching for and locating Docket No. FAA–
AD to require actions to address the Room 301, Kansas City, Missouri 64106;
2017–0624.
(2) For more information about this AD, unsafe condition on these products. telephone: (816) 329–4144; fax: (816)
contact Sanjay Ralhan, Aerospace Engineer, DATES: We must receive comments on 329–4090; email: mike.kiesov@faa.gov.
International Branch, ANM 116, Transport this proposed AD by August 14, 2017. SUPPLEMENTARY INFORMATION:
Airplane Directorate, FAA, 1601 Lind ADDRESSES: You may send comments by
Avenue SW., Renton, WA 98057–3356; Comments Invited
telephone 425–227 1405; fax 425–227 1149. any of the following methods:
(3) For service information identified in • Federal eRulemaking Portal: Go to We invite you to send any written
this AD, contact Airbus, Airworthiness http://www.regulations.gov. Follow the relevant data, views, or arguments about
Office—EIAS, 1 Rond Point Maurice instructions for submitting comments. this proposed AD. Send your comments
sradovich on DSK3GMQ082PROD with PROPOSALS
Bellonte, 31707 Blagnac Cedex, France; • Fax: (202) 493–2251. to an address listed under the
telephone +33 5 61 93 36 96; fax +33 5 61 • Mail: U.S. Department of ADDRESSES section. Include ‘‘Docket No.
93 44 51; email account.airworth-eas@ Transportation, Docket Operations, M– FAA–2017–0648; Directorate Identifier
airbus.com; Internet http://www.airbus.com.
You may view this service information at the
30, West Building Ground Floor, Room 2017–CE–012–AD’’ at the beginning of
FAA, Transport Airplane Directorate, 1601 W12–140, 1200 New Jersey Avenue SE., your comments. We specifically invite
Lind Avenue SW., Renton, WA. For Washington, DC 20590. comments on the overall regulatory,
information on the availability of this • Hand Delivery: U.S. Department of economic, environmental, and energy
material at the FAA, call 425–227–1221. Transportation, Docket Operations, M– aspects of this proposed AD. We will
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Document Created: 2018-11-14 10:16:51
Document Modified: 2018-11-14 10:16:51
| 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 |
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