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Proposed Rule

Airworthiness Directives; Airbus Airplanes

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Start Preamble Start Printed Page 29440

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.

Start Further Info

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.

End Further Info End Preamble Start Supplemental Information

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 Start Printed 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'Enquêtes et d'Analyses pour la sécurité 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 Générale 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

ActionLabor costParts costCost per productCost on U.S. operators
Inspection1 work-hour × $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.Start Printed Page 29442

On-Condition Costs

ActionLabor costParts costCost per product
Replacement9 work-hours × $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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

The Proposed Amendment

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

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

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

End Amendment Part Start Authority

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

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

End Amendment Part

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

AirplanesFMGC No.
A319-111B398AAM0303B398AAM0304B398AAM0405B398AAM0406
Start Printed Page 29443
A319-112B398AAM0407B398AAM0408B398AAM0409B398AAM0410
A319-113B398AAM0411B398AAM0412B398BAM0101B398BAM0202
A319-114B398BAM0203B398BAM0204B398BAM0205B398BAM0206
A319-115B398BAM0207B398BAM0208B398BAM0209B546BAM0101
A320-211B546BAM0202B546BAM0203B546BAM0204B546BAM0205
A320-212B546BAM0206B546CAM0101B546CAM0102B546CAM0103
A320-214B546CAM0104
A321-111
A321-112
A321-211
A321-212 and A321-213 (all CFM56)
A319-131B398BCM0101B398BCM0102B398BCM0103B398BCM0104
A319-132B398BCM0105B398BCM0106B398BCM0107B398BCM0108
A319-133B398BCM0109B546BCM0101B546BCM0102B546BCM0203
A320-231B546BCM0204B546BCM0205B546CCM0101B546CCM0102
A320-232B546CCM0103B546CCM0104B546CCM0105B546CCM0106
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

AirplanesFMGC part No.
A319-111C13042AA01
A319-112C13042AA02
A319-113C13042AA03
A319-114C13042AA04
A319-115C13042AA05
A320-211C13042AA06
A320-212C13042AA07
A320-214C13043AA01
A321-111C13043AA02
A321-112C13043AA03
A321-211C13043AA04
A321-212 andC13043AA05
A321-213 (all CFM56)C13043AA06
FMGC hardwareFlight Guidance (FG) software
C13207AA00G2858AAA01
C13207CA00G2858AAA02
C13207CA00G2858AAA03
C13208AA00G2858AAA01
C13208AA00G2858AAA02
C13208AA00G2858AAA03

Figure 3 to Paragraph (g)(2) of This AD—List of Approved Eligible FMGCs Certified as of the Effective Date of This AD

AirplanesFMGC part No.
A319-131C13042BA01
A319-132C13042BA02
A319-133C13042BA03
A320-231C13042BA04
A320-232C13042BA05
A320-233C13042BA06
A321-131C13042BA07
A321-231 andC13042BA08
A321-232 (all V2500)C13043BA01
C13043BA02
C13043BA03
C13043BA04
C13043BA05
C13043BA06
C13043BA07
Start Printed Page 29444
C13043BA08
FMGC hardware(FG) software
C13207BA00G2859AAA01
C13207DA00G2859AAA02
C13207DA00G2859AAA03
C13207DA00G2859AAA04
C13208BA00G2859AAA01
C13208BA00G2859AAA02
C13208BA00G2859AAA03
C13208BA00G2859AAA04

(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 installAirbus service bulletinRevisionDate
C13042BA01A320-22-109000March 5, 2002.
01April 15, 2002.
02June 14, 2002.
03October 1, 2002.
04November 26, 2002.
05January 13, 2003.
06March 3, 2003.
07June 26, 2003.
08October 15, 2003.
09November 7, 2003.
10January 22, 2004.
C13043AA01A320-22-110300October 8, 2002.
01April 1, 2003.
02August 28, 2003.
03October 15, 2003.
C13043BA01A320-22-111600January 31, 2003.
01August 4, 2003.
02October 17, 2003.
03February 25, 2004.
C13043AA02A320-22-115200May 5, 2004.
01July 6, 2004.
02October 15, 2004.
C13043BA04A320-22-124300October 16, 2007.
01April 1, 2008.
02September 10, 2008.
03February 17, 2009.
04March 3, 2010.
Start Printed Page 29445
C13207CA00A320-22-151900June 26, 2015.
01August 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.

Start Signature

Issued in Renton, Washington, on June 16, 2017.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2017-13406 Filed 6-28-17; 8:45 am]

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