Source: https://www.federalregister.gov/documents/2018/12/06/2018-26362/airworthiness-directives-airbus-sas-airplanes
Timestamp: 2018-12-11 05:10:35
Document Index: 25954274

Matched Legal Cases: ['art 39', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2', 'art 2']

A Rule by the Federal Aviation Administration on 12/06/2018
This AD is effective January 10, 2019.
83 FR 62690
62690-62693 (4 pages)
Docket No. FAA-2018-0512
Product Identifier 2017-NM-170-AD
Amendment 39-19513
AD 2018-25-02
FAA-2018-0512
2017-NM-170-AD Airbus Model A318, A319, A320 and A321 series airplanes
Request To Use the Latest Service Information
Change to Language for Previous Approved AMOCs
Removal of Terminating Action for AD 2016-09-06
(g) New Maintenance or Inspection Program Revision
(i) Terminating Action for AD 2017-22-03
https://www.federalregister.gov/d/2018-26362 https://www.federalregister.gov/d/2018-26362
We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the principal structural elements and certain life-limited parts are subject to widespread fatigue damage (WFD). This AD requires revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 10, 2019.
For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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://Start Printed Page 62691www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0512.
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0512; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A318, A319, A320 and A321 series airplanes. The NPRM published in the Federal Register on June 14, 2018 (83 FR 27724). The NPRM was prompted by an evaluation by the DAH indicating that the principal structural elements and certain life-limited parts are subject to WFD. The NPRM proposed to require revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations.
We are issuing this AD to address prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017-0231, dated November 21, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or “the MCAI”), to correct an unsafe condition for all Airbus SAS Model A318, A319, A320 and A321 series airplanes. The MCAI states:
The airworthiness limitations for the A320 family aeroplanes are currently defined and published in the Airbus A318/A319/A320/A321 Airworthiness Limitations Section (ALS) document(s). The Damage Tolerant Airworthiness Limitation Items are published in ALS Part 2, approved by EASA. The instructions contained in the ALS Part 2 have been identified as mandatory actions for continued airworthiness.
Failure to comply with these instructions could result in an unsafe condition.
Previously, EASA issued AD 2016-0239 [which corresponds to FAA AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) (“AD 2017-22-03”)] to require accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 05, and [EASA] AD 2015-0038 (later revised) [which corresponds to FAA AD 2016-09-06, Amendment 39-18504 (81 FR 26113, May 2, 2016) (“AD 2016-09-06”)] to require the implementation of reduced thresholds and intervals for the detailed inspection of the forward engine mount on both right hand and left hand sides of aeroplanes equipped with CFM56-5A/5B engines, as specified in the ALS task 712111-01.
Since those [EASA] ADs were issued, Airbus published Revision 06 of the ALS Part 2, and variations up to 6.3, including new and/or more restrictive items, and new A320 family models were certified and added to the Applicability of the ALS. The ALS Part 2 Revision 06 also includes the reduced threshold and intervals required by EASA AD 2015-0038R1.
For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016-0239 and EASA AD 2015-0038R1, which are superseded, requires accomplishment of all maintenance tasks as described in the ALS Part 2 Revision 06, and ALS Part 2 variations 6.1, 6.2 and 6.3 (hereafter collectively referred to as “the ALS” in this [EASA] AD), and maintains specific compliance times for ALS task 572021-01-1 (Wide Spread Fatigue Damage related).
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-2018-0512.
We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA's response to that comment.
Lufthansa Technik requested that we use the latest service information in the NPRM. Lufthansa Technik stated that Airbus issued A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 07, dated June 13, 2018, which is the latest revision of the document.
We disagree with the commenter's request. We, along with the EASA, have not determined that Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 07, dated June 13, 2018, is required for airplanes that do not include Revision 07 as part of the type design. In the future, should we determine that Revision 07 is required, we would consider issuing additional rulemaking at that time. However, operators may request approval to incorporate Revision 07 as an alternative method of compliance (AMOC) under the provisions of paragraph (j) of this AD. We have not changed this AD in this regard.
We have revised paragraph (j)(1)(ii) of this AD to state that AMOCs previously approved for AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (“AD 2015-05-02”), as applicable to ALS Part 2, are approved as AMOCs for the corresponding provisions of this AD. In paragraphs (j)(1)(ii)(A), (j)(1)(ii)(B), (j)(1)(ii)(C), and (j)(1)(ii)(D) of the proposed AD, we had identified specific ALS documents. However, any previously approved AMOC for AD 2015-05-02, as applicable to ALS Part 2, is acceptable for the corresponding requirements of this AD.
We have removed paragraph (i)(1) of the proposed AD, which specified that accomplishing the action required by paragraph (g) of this AD terminates the requirements of paragraphs (g) and (j) of AD 2016-09-06. However, we have determined that the actions required by this AD, do not terminate the requirements specified in AD 2016-09-06. The actions specified in paragraph (g) of AD 2016-09-06 were not incorporated into Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017, which is specified in paragraph (g) of this AD. We have coordinated this issue with EASA.
We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this Start Printed Page 62692final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:
Airbus has issued A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017. This service information describes damage tolerant airworthiness limitations.
Airbus has also issued the following variations to A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017.
A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. The service information describes ALI tasks applicable to certain Model A320-200 and A321-200 airplane configurations.
A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017. This service information describes ALI tasks applicable to Model A321-271N and -272N airplanes.
A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017. This service information describes ALI tasks associated with door stops for certain Model A318, A319, A320, and A321 series airplanes.
We estimate that this AD affects 1,180 airplanes of U.S. registry.
2018-25-02 Airbus SAS: Amendment 39-19513; Docket No. FAA-2018-0512; Product Identifier 2017-NM-170-AD.
This AD affects AD 2017-22-03, Amendment 39-19083 (82 FR 49091, October 24, 2017) (“AD 2017-22-03”).
This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category; with an original certificate of airworthiness or original export certificate of airworthiness issued on or before October 24, 2017.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, -271N, and -272N airplanes.
This AD was prompted by an evaluation by the design approval holder, which indicates that principal structural elements and certain life-limited parts are subject to widespread Start Printed Page 62693fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane.
(1) Within 90 days after the effective date of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the airworthiness limitations (ALIs) specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017; and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017. Except for ALIs identified in paragraphs (g)(2) and (g)(3) of this AD, the initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017, and Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.
(2) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.
(3) For airplanes identified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017: Concurrently with the revision required by paragraph (g)(1) of this AD, revise the existing maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017; or within 90 days after the effective date of this AD; whichever occurs later, without exceeding the inspection intervals in the ALIs required by paragraph (i) of AD 2017-22-03.
After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.
Accomplishing the applicable actions required by paragraph (g) of this AD terminates the requirements of paragraphs (g)(2) and (i) of AD 2017-22-03.
(ii) AMOCs previously approved for AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), as applicable to Airworthiness Limitations Section (ALS) Part 2, are approved as AMOCs for the corresponding provisions of this AD.
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0231, dated November 21, 2017, 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-2018-0512.
(i) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 06, dated April 10, 2017.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.1, dated May 18, 2017.
(iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.2, dated May 24, 2017.
(iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Section Part 2—Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 6.3, dated October 24, 2017.
(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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.
[FR Doc. 2018-26362 Filed 12-4-18; 8:45 am]