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Airworthiness Directives; Airbus Airplanes

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Information about this document as published in the Federal Register.

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Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. This AD requires identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to address the unsafe condition on these products.

DATES:

This AD is effective May 15, 2017.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 15, 2017.

ADDRESSES:

For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-8851.

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-2016-8851; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus Model A340-500 and -600 series airplanes. The NPRM published in the Federal Register on August 31, 2016 (81 FR 59922) (“the NPRM”). The NPRM was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. The NPRM proposed to require identification of the potentially affected inboard flap parts, a one-time eddy current inspection to identify which material the parts are made of, and, depending on findings, replacement with serviceable parts. We are issuing this AD to detect and correct structural parts of inboard flaps made of nonconforming aluminum alloy, 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 2016-0231, dated November 22, 2016 (“EASA AD 2016-0231”) (referred to after this as the Mandatory Continuing Airworthiness Information, or “the MCAI”), which superseded EASA Airworthiness Directive 2016-0082, dated April 27, 2016 (“EASA AD 2016-0082”), to correct an unsafe condition all Airbus Model A330-200 Freighter, -200, and -300 series airplanes; and Airbus Model A340-200, -300, -500 and -600 series airplanes. The MCAI states:

Following an Airbus quality control review on the final assembly line, it was discovered that non-conforming aluminium alloy was used to manufacture several structural parts on the inboard flap.

This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane.

To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A330-57-3120 and SB A340-57-5036 to provide instructions to identify and inspect the potentially affected parts.

Consequently, EASA issued AD 2016-0082 to require identification of the potentially affected inboard flap parts, a one-time special detailed inspection (SDI) [eddy current measurement] to identify which material they are made of and, depending on findings, replacement with serviceable parts.

Since EASA AD 2016-0082 was issued, it was confirmed that flaps, initially installed on A340-500 and A340-600 aeroplanes, may also have been installed in service on A340-200 or A340-300 aeroplanes. As this installation was not done during production, no SB was published for these models.

For the reason described above, this [EASA] AD retains the requirements of EASA AD 2016-0082 [which corresponded to the FAA NPRM], which is superseded, expands the Applicability to include A340-200 and A340-300 aeroplanes, corrects a typographical error in Appendix 1 of this [EASA] AD for one affected flap, Right Hand (RH) serial number (s/n) “TB 11411” in place of “TB 14411” (date of first operation: 19/04/13) and identified in bold in Appendix 1, and adds the prefix “TB” to the s/n's of all Left Hand (LH) and RH flaps, which was inadvertently omitted in Appendix 1 of [EASA] AD 2016-0082. This [EASA] AD also allows, under certain conditions, installation of an affected inboard flap on an aeroplane.

Airbus Model A340-200 and -300 series airplanes have been added to the applicability of this AD. Since there are currently no domestic operators of these added airplanes, notice and opportunity for public comment before issuing this AD are unnecessary.

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-2016-8851.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment.

Request To Account for a Superseding EASA Airworthiness Directive

Airbus commented that EASA was planning to supersede EASA AD 2016-0082 with EASA AD 2016-0231, which would update the AD applicability, correct a certain part serial number, and add the prefix “TB” to the serial Start Printed Page 17108numbers of all flaps. (These changes are described in the MCAI.)

We agree with the commenter and have revised this AD to update the applicability, correct a serial number for a right-hand flap (from TB14411 to TB11411), and add the prefix “TB” before each flap serial number.

Requests To Extend Compliance Time for Part Replacement

Airbus and American Airlines requested that the requirement to replace an affected part within 30 days after performing the eddy current inspection be changed to allow a longer compliance time. Paragraph (i) of the proposed AD states that if a part requires replacement due to a nonconforming material finding per paragraph (h) of the proposed AD, the part must be replaced within 30 days after the finding in accordance with a method approved by the FAA, EASA, or Airbus's EASA Design Organization Approval (DOA). EASA AD 2016-0082, paragraph (3), states, for the same nonconforming material finding, to contact Airbus within 30 days of the finding for approved replacement instructions, and within the compliance time(s) specified in those instructions to replace the nonconforming parts accordingly. The commenters stated that this allows more flexibility for replacement actions.

We agree that additional time can be allowed for replacement of affected parts if 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). We have revised paragraph (i) of this AD accordingly. This provision corresponds to EASA AD 2016-0231, which superseded EASA AD 2016-0082.

Removal of Note From Regulatory Text

We have removed Note 2 to paragraph (h) of the proposed AD, and added text to paragraph (h) of this AD to clarify that the date of the first operation of the flap is specified in figure 1 to paragraphs (g), (j)(1), and (j)(2) of this AD.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

  • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and
  • Do not add any additional burden upon the public than was already proposed in the NPRM.

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

We reviewed Airbus Service Bulletin A330-57-3120, dated September 18, 2015; and Airbus Service Bulletin A340-57-5036, dated September 18, 2015. The service information describes procedures for inspecting inboard flaps using eddy current inspection methods to determine the materials used. These documents are distinct since they apply to different airplane models. 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.

Costs of Compliance

We estimate that this AD affects 31 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:

Estimated Costs

ActionLabor costParts costCost per productCost on U.S. operators
Inspection5 work-hours × $85 per hour = $425$0$425$13,175

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

On-Condition Costs

ActionLabor costParts costCost per product
Remove and Replace Flap60 work-hours × $85 per hour = $5,100Unavailable$5,100

According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. The cost of purchasing a flap spare is not available. As a result, we have included only labor costs in our cost estimate.

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 AD will not have federalism implications under Executive Order 13132. This AD will 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.Start Printed Page 17109

For the reasons discussed above, I certify that this AD:

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

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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

2017-06-07 Airbus: Amendment 39-18831; Docket No. FAA-2016-8851; Directorate Identifier 2016-NM-070-AD.

(a) Effective Date

This AD is effective May 15, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Model A330-223F and -243F airplanes; A330-201, -202, -203, -223, and -243 airplanes; A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; A340-211, -212, and -213 airplanes; A340-311, -312, and -313 airplanes; A340-541 airplanes; and A340-642 airplanes; certificated in any category, all manufacturer serial numbers.

(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by reports that nonconforming aluminum alloy was used to manufacture several structural parts on the inboard flap. We are issuing this AD to detect and correct structural parts of inboard flaps made of nonconforming aluminum alloy, which could result in reduced structural integrity of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) Inboard Flap Serial Number Identification

Within 24 months after the effective date of this AD: Inspect each left-hand (LH) and right-hand (RH) inboard flap, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3120, dated September 18, 2015; or Airbus Service Bulletin A340-57-5036, dated September 18, 2015; as applicable; to identify the serial number. A review of airplane delivery and maintenance records is acceptable in lieu of inspecting the inboard flaps, provided those records can be relied upon for that purpose and the serial number of the affected parts can be conclusively identified from that review. The serial numbers of affected inboard flaps are identified in figure 1 to paragraphs (g), (j)(1), and (j)(2) of this AD.

Note 1 to paragraphs (g) and (h) of this AD:

Airbus Service Bulletin A330-57-3120, dated September 18, 2015; and Airbus Service Bulletin A340-57-5036, dated September 18, 2015; list the serial numbers of potentially affected LH and RH inboard flaps and the corresponding airplane serial number on which these parts were installed during production. The airplane serial number list is for information only, as it cannot be excluded that a potentially affected inboard flap has been removed from an airplane and later re-installed on another airplane.

Figure 1 to Paragraphs (g), (j)(1), and (j)(2) of This AD—Affected Flap Serial Numbers (s/n)

Date of first operation (dd/mm/yy)LH s/nRH s/nDate of first operation (dd/mm/yy)LH s/nRH s/nDate of first operation (dd/mm/yy)LH s/nRH s/n
29/09/10TB 11004TB 1100428/02/11TB 11202TB 1120119/12/12TB 11349TB 11349
21/07/09TB 11030TB 1102822/02/11TB 11198TB 1120217/12/12TB 11352TB 11352
17/08/09TB 11034TB 1100207/03/11TB 11203TB 1120315/11/12TB 11353TB 11353
21/05/10TB 11031TB 1103130/03/11TB 11204TB 1120430/10/12TB 11354TB 11354
09/08/10TB 11071TB 1107131/05/11TB 11205TB 1122922/10/12TB 11355TB 11355
10/07/09TB 11033TB 1105715/03/11TB 11206TB 1120631/10/12TB 11383TB 11357
06/08/10TB 11036TB 1109824/03/11TB 11208TB 1120830/10/12TB 11380TB 11356
29/07/09TB 11035TB 1103504/04/11TB 11209TB 1120926/11/12TB 11359TB 11393
19/08/09TB 11057TB 1103622/03/11TB 11210TB 1121030/11/12TB 11361TB 11361
23/12/09TB 11037TB 1103323/03/11TB 11211TB 1121316/11/12TB 11358TB 11358
14/09/09TB 11038TB 1103824/03/11TB 11212TB 1121230/11/12TB 11325TB 11360
17/09/10TB 11042TB 1103914/04/11TB 11213TB 1121412/12/12TB 11399TB 11365
23/09/09TB 11040TB 1104014/04/11TB 11229TB 1121526/11/12TB 11362TB 11362
11/09/09TB 11041TB 1104111/04/11TB 11215TB 1121709/11/12TB 11363TB 11363
12/05/10TB 11046TB 1104206/04/11TB 11216TB 1121630/11/12TB 11364TB 11364
01/10/09TB 11043TB 1104312/04/11TB 11217TB 1121923/11/12TB 11365TB 11368
01/10/09TB 11044TB 1104415/04/11TB 11218TB 1121807/12/12TB 11366TB 11366
08/09/09TB 11047TB 1104504/05/11TB 11219TB 1122106/12/12TB 11367TB 11367
07/09/09TB 11049TB 1104629/04/11TB 11220TB 1122019/12/12TB 11368TB 11370
18/09/09TB 1970TB 1104711/05/11TB 11238TB 1122211/12/12TB 11369TB 11369
30/09/09TB 11048TB 1104813/05/11TB 11222TB 1122321/12/12TB 11370TB 11372
26/10/09TB 11055TB 1104906/05/11TB 11223TB 1122413/12/12TB 11372TB 11375
03/09/10TB 11051TB 1105119/05/11TB 11224TB 1122520/12/12TB 11373TB 11373
30/10/09TB 11054TB 1105419/05/11TB 11225TB 1120521/12/12TB 11374TB 11374
19/11/09TB 11053TB 1105329/06/11TB 11226TB 1122616/01/13TB 11375TB 11377
28/10/10TB 11008TB 1101925/05/11TB 11227TB 1122711/01/13TB 11376TB 11376
27/10/09TB 11015TB 1105516/05/11TB 11228TB 1122815/01/13TB 11377TB 11350
28/10/09TB 11059TB 1105910/06/11TB 11092TB 1109205/02/13TB 11378TB 11381
29/10/09TB 11060TB 1106023/11/11TB 11231TB 1123125/01/13TB 11379TB 11379
16/11/10TB 11063TB 1106308/07/11TB 11232TB 1123218/01/13TB 11382TB 11380
23/12/09TB 11061TB 1106123/06/11TB 11234TB 1123422/03/13TB 11381TB 11382
Start Printed Page 17110
23/11/09TB 11066TB 1106622/06/11TB 11233TB 1123327/02/13TB 11371TB 11371
03/11/10TB 11070TB 1107024/06/11TB 11237TB 1123708/03/13TB 11385TB 11383
30/11/09TB 11065TB 1106515/06/11TB 11235TB 1123506/02/13TB 11384TB 11384
30/11/09TB 11032TB 1103201/07/11TB 11236TB 1123605/02/13TB 11386TB 11385
18/11/09TB 11067TB 1106712/07/11TB 11239TB 1123919/02/13TB 11406TB 11389
17/12/09TB 11072TB 1107225/11/11TB 11115TB 1111516/03/13TB 11387TB 11387
24/11/09TB 11074TB 1107429/07/11TB 11240TB 1124025/02/13TB 11388TB 11388
17/09/10TB 11147TB 1114706/10/11TB 11243TB 1124315/02/13TB 11390TB 11390
23/12/09TB 11095TB 1109529/07/11TB 11244TB 1124125/02/13TB 11392TB 11392
10/12/09TB 11075TB 1107503/08/11TB 11245TB 1124501/03/13TB 11391TB 11403
07/12/09TB 11076TB 1107629/08/11TB 11246TB 1124401/03/13TB 11394TB 11394
23/12/09TB 11077TB 1107722/08/11TB 11247TB 1124711/03/13TB 11393TB 11395
22/12/09TB 11069TB 1106920/12/11TB 11248TB 1124608/03/13TB 11397TB 11397
07/12/09TB 11079TB 1107930/08/11TB 11249TB 1124914/03/13TB 11395TB 11399
19/01/10TB 11078TB 1107825/08/11TB 11136TB 1124818/03/13TB 11396TB 11396
11/02/10TB 11081TB 1108106/09/11TB 11250TB 1125018/03/13TB 11356TB 11400
26/03/10TB 11080TB 1108027/09/11TB 11252TB 1125428/03/13TB 11398TB 11398
28/01/10TB 11082TB 1108228/09/11TB 11221TB 1125122/03/13TB 11401TB 11401
28/01/10TB 11084TB 1108415/09/11TB 11214TB 1125509/04/13TB 11400TB 11402
04/02/10TB 11098TB 1103020/10/11TB 11266TB 1125621/03/13TB 11404TB 11404
29/01/10TB 11085TB 1108519/12/11TB 11258TB 1125809/04/13TB 11402TB 11405
05/02/10TB 11039TB 1103719/10/11TB 11255TB 1125926/04/13TB 11403TB 11407
29/03/10TB 11086TB 1108610/11/11TB 11259TB 1126015/04/13TB 11360TB 11406
09/03/10TB 11087TB 1108705/10/11TB 11261TB 1126111/04/13TB 11407TB 11408
15/04/10TB 11088TB 1108817/10/11TB 11260TB 1126319/04/13TB 11409TB 11409
16/04/10TB 11089TB 1108910/11/11TB 11254TB 1125224/04/13TB 11410TB 11410
29/03/10TB 11090TB 1109017/11/11TB 11262TB 1126219/04/13TB 11411TB 11411
11/06/10TB 11091TB 1109116/11/11TB 11263TB 1126422/04/13TB 11408TB 11412
22/06/11TB 11230TB 1123016/11/11TB 11264TB 1126526/04/13TB 11413TB 11413
23/03/10TB 11093TB 1109325/11/11TB 11265TB 1126630/04/13TB 11414TB 11414
23/02/10TB 11094TB 1109428/11/11TB 11267TB 1126722/04/13TB 11412TB 11415
24/03/10TB 11073TB 1107305/12/11TB 11268TB 1126815/07/13TB 11416TB 11416
31/03/10TB 11096TB 1109629/11/11TB 11270TB 1127017/05/13TB 11405TB 11417
16/03/10TB 11097TB 1109706/12/11TB 11271TB 1127128/05/13TB 11415TB 11418
10/03/10TB 11101TB 1110112/12/11TB 11272TB 1127223/05/13TB 11419TB 11419
15/03/10TB 11099TB 1109907/12/11TB 11275TB 1127517/05/13TB 11417TB 11421
23/03/10TB 11100TB 1110014/12/11TB 11269TB 1126930/05/13TB 11418TB 11420
16/06/10TB 11105TB 1110515/12/11TB 11274TB 1127430/05/13TB 11357TB 11386
07/12/10TB 11102TB 1113012/12/11TB 11276TB 1127627/05/13TB 11420TB 11422
13/04/10TB 11106TB 1110611/01/12TB 11279TB 1127913/06/13TB 11421TB 11423
27/04/10TB 11104TB 1110420/01/12TB 11278TB 1127804/06/13TB 11424TB 11424
30/04/10TB 11103TB 1110319/01/12TB 11164TB 1116417/06/13TB 11426TB 11378
07/04/10TB 11108TB 1110812/01/12TB 11277TB 1127710/06/13TB 11423TB 11427
16/04/10TB 11133TB 1113319/01/12TB 11280TB 1128127/06/13TB 11428TB 11428
10/05/10TB 11114TB 1111423/01/12TB 11298TB 1128220/06/13TB 11425TB 11425
10/05/10TB 11110TB 1111017/01/12TB 11282TB 1128427/06/13TB 11429TB 11426
06/05/10TB 11116TB 1111630/01/12TB 11283TB 1128321/06/13TB 11427TB 11429
27/05/10TB 11112TB 1111201/02/12TB 11284TB 1128501/07/13TB 11434TB 11434
13/07/11TB 11241TB 1123824/02/12TB 11286TB 1128601/07/13TB 11432TB 11432
11/05/10TB 11111TB 1103417/02/12TB 11285TB 1128723/07/13TB 11430TB 11430
17/06/10TB 11118TB 1111829/02/12TB 11287TB 1128931/07/13TB 11431TB 11431
09/06/10TB 11120TB 1112022/02/12TB 11288TB 1128819/07/13TB 11436TB 11436
16/07/10TB 11122TB 1112223/02/12TB 11289TB 1129112/07/13TB 11433TB 11433
06/07/10TB 11123TB 1112324/02/12TB 11290TB 1129001/08/13TB 11437TB 11437
21/05/10TB 11124TB 1112421/02/12TB 11291TB 1129315/07/13TB 11435TB 11435
12/07/10TB 11126TB 1112604/04/12TB 11292TB 1129219/07/13TB 11438TB 11316
28/06/10TB 11127TB 1112705/04/12TB 11293TB 1129413/11/13TB 11440TB 11438
18/06/10TB 11129TB 1112920/03/12TB 11294TB 1129606/08/13TB 11441TB 11441
22/06/10TB 11130TB 1110209/03/12TB 11295TB 1129502/08/13TB 11439TB 11439
24/09/10TB 11135TB 1113530/03/12TB 11296TB 1129805/08/13TB 11442TB 11440
25/06/10TB 11132TB 1113229/03/12TB 11297TB 1129709/08/13TB 11443TB 11391
26/07/10TB E11006TB 1111116/03/12TB 11299TB 1117527/08/13TB 11446TB 11442
23/07/10TB 11138TB 1113829/03/12TB 11300TB 1130019/08/13TB 11447TB 11443
14/09/11TB 11251TB 1113618/04/12TB 11281TB 1130104/09/13TB 11444TB 11444
15/07/10TB 11062TB 1106212/04/12TB 11302TB 1118003/09/13TB 11445TB 11445
23/07/10TB 11141TB 1114126/04/12TB 11301TB 1130325/09/13TB 11449TB 11446
23/08/10TB 11145TB 1114520/04/12TB 11303TB 1130613/09/13TB 11450TB 11447
27/08/10TB 11117TB 1111724/04/12TB 11304TB 1130729/10/13TB 11448TB 11448
13/08/10TB 11146TB 1114627/04/12TB 11305TB 1130526/09/13TB 11453TB 11449
13/09/10TB 11149TB 1114925/04/12TB 11306TB 1130802/12/13TB 11454TB 11450
Start Printed Page 17111
27/09/10TB 11150TB 1115026/04/12TB 11307TB 1119625/09/13TB 11451TB 11451
14/11/11TB 11148TB 1114814/05/12TB 11308TB 1131025/09/13TB 11472TB 11464
17/09/10TB 11151TB 1115110/05/12TB 11310TB 1131227/09/13TB 11457TB 11453
28/09/10TB 11107TB 1110711/05/12TB 11312TB 1131728/10/13TB 11458TB 11454
27/09/10TB 11159TB 1115909/05/12TB 11309TB 1129922/10/13TB 11456TB 11455
25/10/10TB 11153TB 1115325/05/12TB 11311TB 1131111/10/13TB 11455TB 11456
29/09/10TB 11155TB 1115529/05/12TB 11313TB 1131325/10/13TB 11459TB 11459
08/10/10TB 11156TB 1115631/05/12TB 11314TB 1131420/11/13TB 11460TB 11458
13/10/10TB 11157TB 1115728/06/12TB 11317TB 1131517/10/13TB 11461TB 11461
15/10/10TB 11168TB 1116815/06/12TB 11316TB 1133621/10/13TB 11462TB 11460
13/10/10TB 11186TB 1116015/06/12TB 11318TB 1131823/10/13TB 11463TB 11463
22/10/10TB 11161TB 1116131/05/12TB 11319TB 1131905/11/13TB 11465TB 11462
22/10/10TB 11163TB 1116318/06/12TB 11320TB 1132004/11/13TB 11466TB 11466
25/01/12TB 11256TB 1128022/06/12TB 11321TB 1132113/11/13TB 11452TB 11473
22/11/10TB 11165TB 1116519/07/12TB 11322TB 1132204/11/13TB 11389TB 11465
10/11/10TB 11167TB 1116729/06/12TB 11323TB 1132322/11/13TB 11468TB 11457
02/12/10TB 1960TB 196011/07/12TB 11324TB 1132427/11/13TB 11467TB 11467
15/11/10TB 11169TB 1116926/06/12TB 11348TB 1132511/12/13TB 11470TB 11468
30/11/10TB 11178TB 1117009/07/12TB 11326TB 1132618/11/13TB 11469TB 11469
10/11/10TB 11171TB 1117103/07/12TB 11327TB 1132702/12/13TB 11474TB 11470
30/11/10TB 11183TB 1117212/07/12TB 11328TB 1132802/12/13TB 11471TB 11471
26/11/10TB 11173TB 1117316/07/12TB 11329TB 1132930/12/13TB 11503TB 11488
14/12/10TB 11174TB 1117424/08/12TB 11330TB 1133016/12/13TB 11476TB 11474
15/06/12TB 11175TB 1130213/07/12TB 11331TB 1133116/12/13TB 11477TB 11477
19/11/10TB 11177TB 1117723/07/12TB 11332TB 1133206/12/13TB 11475TB 11475
23/12/10TB 11172TB 1117829/08/12TB 11333TB 1133303/12/13TB 11479TB 11476
11/04/12TB 11315TB 1130410/08/12TB 11334TB 1133409/12/13TB 11480TB 11480
16/12/10TB 11181TB 1118123/07/12TB 11335TB 1133509/12/13TB 11478TB 11489
15/12/10TB 11184TB 1118330/08/12TB 11337TB 1133709/12/13TB 11481TB 11481
15/12/10TB 11187TB 1118430/07/12TB 11336TB 1130917/12/13TB 11482TB 11482
14/01/11TB 11188TB 1118831/08/12TB 11180TB 1133909/01/14TB 11483TB 11483
25/01/11TB 11189TB 1118718/09/12TB 11340TB 1134021/01/14TB 11484TB 11484
21/01/11TB 11160TB 1118930/11/12TB 11339TB 1134127/02/14TB 11486TB 11486
12/01/11TB 11190TB 1119012/09/12TB 11341TB 1134327/01/14TB 11487TB 11487
25/01/11TB 11192TB 1118615/10/12TB 11343TB 1134517/01/14TB 11485TB 11485
07/02/11TB 11191TB 1119117/09/12TB 11346TB 1134731/01/14TB 11489TB 11490
07/02/11TB 11193TB 1119228/09/12TB 11345TB 1134414/01/14TB 11490TB 11491
18/02/11TB 11195TB 1119309/10/12TB 11342TB 1134229/01/14TB 11488TB 11492
24/02/11TB 11196TB 1119524/09/12TB 11344TB 1134630/01/14TB 11492TB 11493
25/02/11TB 11199TB 1121115/10/12TB 11347TB 901524/01/14TB 11493TB 11479
25/02/11TB 11200TB 1119821/09/12TB 11338TB 1134827/02/14TB 11491TB 11494
21/02/11TB 11201TB 1119919/10/12TB 11350TB 1135916/06/14TB 11495TB 11495
14/02/11TB 11170TB 1120017/10/12TB 11351TB 1135114/02/14TB 11498TB 11498

(h) Eddy Current Conductivity Measurement

For each affected inboard flap: Within 6 years after the effective date of this AD, or within 12 years after the date of the flap first operation, as specified in figure 1 to paragraphs (g), (j)(1), and (j)(2) of this AD, whichever occurs first, accomplish an eddy current conductivity measurement, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3120, dated September 18, 2015; or Airbus Service Bulletin A340-57-5036, dated September 18, 2015; as applicable.

(i) Replacement

If a part manufactured from nonconforming material is detected during the eddy current inspection required by paragraph (h) of this AD: Within 30 days after doing the eddy current inspection, obtain replacement instructions 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); and, within the compliance time specified in those instructions, accomplish the replacement accordingly.

(j) Parts Installation Limitation

As of the effective date of this AD, an inboard flap may be installed on any airplane, provided the part is a serviceable part. A serviceable part is:

(1) A part that is not listed by serial number in figure 1 to paragraphs (g), (j)(1), and (j)(2) of this AD; or

(2) A part that has a serial number listed in figure 1 to paragraphs (g), (j)(1), and (j)(2) of this AD, and has passed an eddy current conductivity measurement within the compliance time specified in this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3120, dated September 18, 2015; or Airbus Service Bulletin A340-57-5036, dated September 18, 2015; as applicable.

(k) 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 ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. 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 Start Printed Page 17112standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(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 the European Aviation Safety Agency (EASA); or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.

(l) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0231, dated November 22, 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-2016-8851.

(m) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(i) Airbus Service Bulletin A330-57-3120, dated September 18, 2015.

(ii) Airbus Service Bulletin A340-57-5036, dated September 18, 2015.

(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com.

(4) 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.

(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.

Start Signature

Issued in Renton, Washington, on March 10, 2017.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2017-05366 Filed 4-7-17; 8:45 am]

BILLING CODE 4910-13-P