Airworthiness Directives; Airbus Airplanes
Federal Register, Volume 77 Issue 191 (Tuesday, October 2, 2012)
Federal Register Volume 77, Number 191 (Tuesday, October 2, 2012)
Proposed Rules
Pages 60064-60072
From the Federal Register Online via the Government Printing Office www.gpo.gov
FR Doc No: 2012-24175
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Docket No. FAA-2012-1034; Directorate Identifier 2011-NM-051-AD
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model A318, A319, A320, and A321 series airplanes. The existing AD currently requires one-time and repetitive inspections of specific areas and, when necessary, corrective actions for those rudders where production rework has been identified. Since we issued that AD, we have determined that additional inspections and corrective actions are necessary to address the identified unsafe condition, and that additional airplanes with certain rudders are subject to the identified unsafe condition. This proposed AD would add airplanes with certain rudders to the AD applicability; change an inspection type for certain reinforced rudder areas; require pre-inspections and repairs if needed; and require permanent restoration of vacuum loss holes. This proposed AD would also require additional inspections for certain rudders and repair if needed; and require replacement of certain rudders with new rudders. We are proposing this AD to detect and correct extended de-bonding, which might degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the airplane.
DATES: We must receive comments on this proposed AD by November 16, 2012.
ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact Airbus, Airworthiness Office--EAS, 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 review copies of the 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; or in person at the Docket Operations office 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-2012-1034; Directorate Identifier 2011-NM-051-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
On October 26, 2010, we issued AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). That AD required actions intended to address an unsafe condition on the products listed above.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2010-0164, dated August 5, 2010 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:
Page 60065
Surface defects were visually detected on the rudder of one A319 and one A321 in-service aeroplane.
Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-
bonding between the skin and honeycomb core.
An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane.
EASA AD 2009-0141 required inspections of specific areas and, when necessary, the application of corrective actions for those rudders where production reworks have been identified.
This EASA AD retains the requirements of EASA AD 2009-0141 (addressing the populations of rudders affected by AOT A320-55-
1038), which is superseded, and requires:
-- a local ultrasonic inspection for reinforced area instead of the local thermography inspection, which is maintained for non-
reinforced areas, and
-- additional work performance for rudders on which this thermography inspection has been performed in the reinforced area, and
-- additional work performance for some rudders on which an additional area requiring inspections is defined.
This EASA AD also addresses the populations of rudders affected by AOT A320-55-1039 and Airbus SB A320-55-1035, A320-55-
1036 and A320-55-1037 which were not included in EASA AD 2009-0141.
Part number (P/N) D554 71000 020 00 serial number (S/N) TS-1494, and P/
N D554 71002 000 00 0002 S/N TS-2212 are listed in Appendix A of EASA AD 2010-0164, dated August 5, 2010. These two items are listed in table 6 of this proposed AD, because they were not listed in previous AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). This proposed AD requires the permanent restoration of vacuum loss holes and does not allow the temporary restoration with self-adhesive patches, or temporary restoration with resin that is specified in the MCAI. You may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service information.
Airbus All Operators Telex (AOT) A320-55A1038, dated April 22, 2009.
Airbus AOT A320-55A1039, dated November 4, 2009.
Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010.
Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010.
Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010.
Airbus Technical Disposition TD/K4/S2/27051/2009, Issue B, dated February 25, 2009.
Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E, dated September 17, 2009.
The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
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 the same type design.
Differences Between This AD and the MCAI or Service Information
This proposed AD requires the permanent restoration of vacuum loss holes and does not allow the temporary restoration with self-adhesive patches, or temporary restoration with resin that is specified in the MCAI.
Costs of Compliance
Based on the service information, we estimate that this proposed AD would affect about 721 products of U.S. registry.
The actions that are required by AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)), and retained in this proposed AD take about 11 work-hours per product, at an average labor rate of $85 per work hour. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the currently required actions on U.S. operators to be $674,135, or $935 per product.
We estimate that it would take about 11 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $674,135, or $935 per product.
In addition, we estimate that any necessary follow-on actions would take about 12 work-hours and require parts costing $10,000, for a cost of $11,020 per product. We have no way of determining the number of products that may need these actions.
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:
-
Is not a ``significant regulatory action'' under Executive Order 12866;
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Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
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Will not affect intrastate aviation in Alaska; and
-
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.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.
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:
Page 60066
PART 39--AIRWORTHINESS DIRECTIVES
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 Amended
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The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)), and adding the following new AD:
Airbus: Docket No. FAA-2012-1034; Directorate Identifier 2011-NM-
051-AD.
(a) Comments Due Date
We must receive comments by November 16, 2012.
(b) Affected ADs
This AD supersedes AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)).
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD; certificated in any category; all serial numbers having a rudder with a part number (P/
N) and serial number (S/N) listed in table 1, 2, 3, 4a and 4b, 5a and 5b, or 6 to paragraph (c) of this AD.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
Table 1 to Paragraph (c) of This AD
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Rudder P/N Affected rudder S/N
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D554 71000 010 00........................... TS-1069
D554 71000 010 00........................... TS-1090
D554 71000 012 00........................... TS-1227
D554 71000 014 00........................... TS-1350
D554 71000 014 00........................... TS-1366
D554 71000 014 00........................... TS-1371
D554 71000 014 00........................... TS-1383
D554 71000 014 00........................... TS-1387
D554 71000 016 00........................... TS-1412
D554 71000 018 00........................... TS-1443
D554 71000 018 00........................... TS-1444
D554 71000 018 00........................... TS-1468
D554 71000 020 00........................... TS-1480
D554 71000 020 00........................... TS-1491
D554 71000 020 00........................... TS-1495
D554 71000 020 00........................... TS-1498
D554 71000 020 00........................... TS-1499
D554 71000 020 00........................... TS-1500
D554 71000 020 00........................... TS-1505
D554 71000 020 00........................... TS-1506
D554 71000 020 00........................... TS-1507
D554 71000 020 00........................... TS-1509
D554 71000 020 00........................... TS-1515
D554 71000 020 00........................... TS-1528
D554 71000 020 00........................... TS-1530
D554 71000 020 00........................... TS-1532
D554 71000 020 00........................... TS-1535
D554 71000 020 00........................... TS-1536
D554 71000 020 00........................... TS-1538
D554 71001 000 00........................... TS-1537
D554 71001 000 00........................... TS-1540
D554 71001 000 00........................... TS-1541
D554 71001 000 00........................... TS-1543
D554 71001 000 00........................... TS-1548
D554 71001 000 00........................... TS-1549
D554 71001 000 00........................... TS-1551
D554 71001 000 00........................... TS-1554
D554 71001 000 00........................... TS-1555
D554 71001 000 00........................... TS-1556
D554 71001 000 00........................... TS-1557
D554 71001 000 00........................... TS-1559
D554 71001 000 00........................... TS-1562
D554 71001 000 00........................... TS-1563
D554 71001 000 00........................... TS-1564
D554 71001 000 00........................... TS-1565
D554 71001 000 00........................... TS-1566
D554 71001 000 00........................... TS-1567
D554 71001 000 00........................... TS-1568
D554 71001 000 00........................... TS-1569
D554 71001 000 00........................... TS-1570
D554 71001 000 00........................... TS-1573
D554 71001 000 00........................... TS-1575
D554 71001 000 00........................... TS-1578
D554 71001 000 00........................... TS-1579
D554 71001 000 00........................... TS-1580
D554 71001 000 00........................... TS-1581
D554 71001 000 00........................... TS-1582
D554 71001 000 00........................... TS-1584
D554 71001 000 00........................... TS-1593
D554 71001 000 00........................... TS-1594
D554 71001 000 00........................... TS-1596
D554 71001 000 00........................... TS-1599
D554 71001 000 00........................... TS-1603
D554 71001 000 00........................... TS-1609
D554 71001 000 00........................... TS-1621
D554 71001 000 00........................... TS-1626
D554 71001 000 00........................... TS-1627
D554 71001 000 00........................... TS-1635
D554 71001 000 00........................... TS-1637
D554 71002 000 00........................... TS-2306
D554 71002 000 00 0001...................... TS-2003
D554 71002 000 00 0001...................... TS-2005
D554 71002 000 00 0001...................... TS-2013
D554 71002 000 00 0001...................... TS-2016
D554 71002 000 00 0001...................... TS-2019
D554 71002 000 00 0001...................... TS-2020
D554 71002 000 00 0001...................... TS-2022
D554 71002 000 00 0001...................... TS-2024
D554 71002 000 00 0001...................... TS-2026
D554 71002 000 00 0001...................... TS-2031
D554 71002 000 00 0001...................... TS-2033
D554 71002 000 00 0001...................... TS-2043
D554 71002 000 00 0001...................... TS-2047
D554 71002 000 00 0001...................... TS-2048
D554 71002 000 00 0001...................... TS-2054
D554 71002 000 00 0001...................... TS-2058
D554 71002 000 00 0001...................... TS-2059
D554 71002 000 00 0001...................... TS-2064
D554 71002 000 00 0001...................... TS-2072
D554 71002 000 00 0001...................... TS-2075
D554 71002 000 00 0001...................... TS-2076
D554 71002 000 00 0001...................... TS-2079
D554 71002 000 00 0001...................... TS-2083
D554 71002 000 00 0001...................... TS-2089
D554 71002 000 00 0002...................... TS-2090
D554 71002 000 00 0002...................... TS-2095
D554 71002 000 00 0002...................... TS-2103
D554 71002 000 00 0002...................... TS-2116
D554 71002 000 00 0002...................... TS-2122
D554 71002 000 00 0002...................... TS-2133
D554 71002 000 00 0002...................... TS-2142
D554 71002 000 00 0002...................... TS-2147
D554 71002 000 00 0002...................... TS-2157
D554 71002 000 00 0002...................... TS-2158
D554 71002 000 00 0002...................... TS-2162
D554 71002 000 00 0002...................... TS-2167
D554 71002 000 00 0002...................... TS-2174
D554 71002 000 00 0002...................... TS-2176
D554 71002 000 00 0002...................... TS-2181
D554 71002 000 00 0002...................... TS-2189
D554 71002 000 00 0002...................... TS-2191
D554 71002 000 00 0002...................... TS-2203
D554 71002 000 00 0002...................... TS-2205
D554 71002 000 00 0002...................... TS-2207
D554 71002 000 00 0002...................... TS-2224
D554 71002 000 00 0002...................... TS-2229
D554 71002 000 00 0002...................... TS-2233
D554 71002 000 00 0002...................... TS-2241
D554 71002 000 00 0002...................... TS-2246
D554 71002 000 00 0002...................... TS-2249
D554 71002 000 00 0002...................... TS-2270
D554 71002 000 00 0002...................... TS-2275
D554 71002 000 00 0002...................... TS-2289
D554 71002 000 00 0002...................... TS-2290
D554 71002 000 00 0002...................... TS-2294
D554 71002 000 00 0002...................... TS-2309
D554 71002 000 00 0002...................... TS-2347
D554 71002 000 00 0002...................... TS-2348
D554 71002 000 00 0002...................... TS-2349
D554 71002 000 00 0002...................... TS-2357
D554 71002 000 00 0002...................... TS-2361
D554 71002 000 00 0002...................... TS-2380
D554 71002 000 00 0002...................... TS-2383
D554 71002 000 00 0002...................... TS-2390
D554 71002 000 00 0002...................... TS-2394
D554 71002 000 00 0002...................... TS-2396
D554 71002 000 00 0002...................... TS-2401
D554 71002 000 00 0002...................... TS-2406
D554 71002 000 00 0002...................... TS-2461
D554 71002 000 00 0002...................... TS-2468
D554 71002 000 00 0002...................... TS-2516
D554 71002 000 00 0002...................... TS-2537
D554 71002 000 00 0002...................... TS-2543
D554 71002 000 00 0002...................... TS-2546
D554 71002 000 00 0002...................... TS-2619
D554 71002 000 00 0002...................... TS-2684
D554 71002 000 00 0003...................... TS-2752
D554 71002 000 00 0003...................... TS-2869
D554 71002 000 00 0003...................... TS-2876
D554 71002 000 00 0003...................... TS-2970
D554 71002 000 00 0003...................... TS-2971
D554 71002 000 00 0003...................... TS-2987
D554 71004 000 00 0000...................... TS-3083
D554 71004 000 00 0000...................... TS-3197
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Note 1 to paragraph (c) of this AD: For table 1 to paragraph (c) of this AD, only rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069 and TS-1090, and rudder P/N D554 71000 012 00 having affected rudder S/N TS-1227, have a core
Page 60067
density of 24 kilogram (kg)/meters cubed (m\3\).
Table 2 to Paragraph (c) of This AD
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Rudder P/N Affected rudder S/N
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D554-71000-014-00........................... TS-1278
D554-71002-000-00-0001...................... TS-2081
D554-71002-000-00-0002...................... TS-2125
D554-71002-000-00-0002...................... TS-2129
D554-71002-000-00-0002...................... TS-2160
D554-71002-000-00-0002...................... TS-2201
D554-71002-000-00-0002...................... TS-2328
D554-71002-000-00-0002...................... TS-2425
D554-71002-000-00-0002...................... TS-2511
D554-71002-000-00-0003...................... TS-2768
D554-71002-000-00-0003...................... TS-2999
D554-71002-000-00-0003...................... TS-3004
D554-71002-000-00-0003...................... TS-3051
D554-71004-000-00-0001...................... TS-3288
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Table 3 to Paragraph (c) of This AD
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Rudder P/N Affected rudder S/N
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D554-71000-008-00........................... TS-1032
D554-71000-010-00........................... TS-1092
D554-71000-014-00........................... TS-1314
D554-71000-018-00........................... TS-1445
D554-71000-020-00........................... TS-1520
D554-71002-000-00-0001...................... TS-2037
D554-71002-000-00-0002...................... TS-2109
D554-71002-000-00-0002...................... TS-2123
D554-71002-000-00-0002...................... TS-2124
D554-71002-000-00-0002...................... TS-2424
D554-71002-000-00-0002...................... TS-2559
D554-71002-000-00-0003...................... TS-3061
D554-71004-000-00-0001...................... TS-3694
D554-71004-000-00-0001...................... TS-3709
D554-71004-000-00-0002...................... TS-4148
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Note 2 to paragraph (c) of this AD: For table 3 to paragraph (c) of this AD, only rudder P/N D554-71000-008-00 having affected rudder S/N TS-1032, and rudder P/N D554-71000-010-00 having affected rudder S/N TS-1092, have a core density of 24 kg/m\3\.
Table 4a to Paragraph (c) of this AD
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Rudder P/N with any S/N listed in table 4b to paragraph (c) of this AD
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D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
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Table 4b to Paragraph (c) of This AD
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Affected S/N for rudders listed in table 4a to paragraph (c) of this AD
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TS-1368 TS-1616 TS-2080 TS-2159 TS-2222 TS-2276 TS-2327
TS-1389 TS-1619 TS-2082 TS-2163 TS-2223 TS-2279 TS-2330
TS-1496 TS-1622 TS-2084 TS-2168 TS-2227 TS-2280 TS-2331
TS-1501 TS-1632 TS-2085 TS-2169 TS-2228 TS-2281 TS-2332
TS-1503 TS-1639 TS-2086 TS-2170 TS-2230 TS-2284 TS-2333
TS-1508 TS-2004 TS-2094 TS-2172 TS-2231 TS-2285 TS-2334
TS-1516 TS-2008 TS-2096 TS-2175 TS-2232 TS-2286 TS-2336
TS-1527 TS-2010 TS-2097 TS-2177 TS-2234 TS-2293 TS-2337
TS-1529 TS-2012 TS-2098 TS-2179 TS-2235 TS-2297 TS-2338
TS-1534 TS-2014 TS-2100 TS-2182 TS-2236 TS-2298 TS-2339
TS-1545 TS-2017 TS-2101 TS-2183 TS-2238 TS-2299 TS-2340
TS-1547 TS-2018 TS-2106 TS-2185 TS-2240 TS-2302 TS-2341
TS-1553 TS-2023 TS-2113 TS-2192 TS-2242 TS-2303 TS-2343
TS-1560 TS-2025 TS-2115 TS-2193 TS-2244 TS-2304 TS-2346
TS-1561 TS-2029 TS-2118 TS-2195 TS-2245 TS-2305 TS-2352
TS-1571 TS-2032 TS-2126 TS-2199 TS-2248 TS-2307 TS-2353
TS-1572 TS-2034 TS-2130 TS-2200 TS-2250 TS-2310 TS-2354
TS-1574 TS-2039 TS-2131 TS-2204 TS-2251 TS-2311 TS-2355
TS-1576 TS-2040 TS-2132 TS-2206 TS-2252 TS-2312 TS-2356
TS-1577 TS-2041 TS-2134 TS-2208 TS-2254 TS-2313 TS-2358
TS-1583 TS-2046 TS-2136 TS-2209 TS-2258 TS-2315 TS-2360
TS-1585 TS-2050 TS-2140 TS-2210 TS-2259 TS-2316 TS-2362
TS-1588 TS-2051 TS-2143 TS-2211 TS-2260 TS-2319 TS-2363
TS-1591 TS-2052 TS-2144 TS-2213 TS-2261 TS-2320 TS-2364
TS-1600 TS-2053 TS-2145 TS-2216 TS-2262 TS-2321 TS-2365
TS-1602 TS-2056 TS-2149 TS-2217 TS-2265 TS-2322 TS-2366
TS-1607 TS-2060 TS-2152 TS-2218 TS-2268 TS-2323 TS-2367
TS-1608 TS-2069 TS-2154 TS-2220 TS-2271 TS-2325 TS-2370
TS-1614 TS-2070 TS-2155 TS-2221 TS-2272 TS-2326 TS-2371
TS-2372 TS-2483 TS-2583 TS-2665 TS-2743 TS-2813 TS-2878
TS-2373 TS-2484 TS-2584 TS-2666 TS-2744 TS-2814 TS-2879
TS-2374 TS-2486 TS-2585 TS-2667 TS-2745 TS-2815 TS-2880
TS-2377 TS-2488 TS-2586 TS-2668 TS-2747 TS-2816 TS-2881
TS-2381 TS-2491 TS-2587 TS-2671 TS-2749 TS-2818 TS-2882
TS-2382 TS-2493 TS-2590 TS-2674 TS-2751 TS-2819 TS-2885
TS-2387 TS-2494 TS-2591 TS-2675 TS-2753 TS-2821 TS-2886
TS-2388 TS-2498 TS-2592 TS-2676 TS-2754 TS-2822 TS-2890
TS-2392 TS-2499 TS-2593 TS-2677 TS-2755 TS-2823 TS-2891
TS-2393 TS-2501 TS-2596 TS-2679 TS-2756 TS-2824 TS-2892
TS-2395 TS-2505 TS-2597 TS-2680 TS-2757 TS-2826 TS-2893
TS-2397 TS-2506 TS-2601 TS-2681 TS-2758 TS-2827 TS-2896
TS-2398 TS-2508 TS-2602 TS-2682 TS-2759 TS-2828 TS-2897
TS-2399 TS-2510 TS-2603 TS-2683 TS-2760 TS-2830 TS-2898
Page 60068
TS-2407 TS-2512 TS-2605 TS-2685 TS-2762 TS-2831 TS-2899
TS-2408 TS-2514 TS-2606 TS-2688 TS-2765 TS-2832 TS-2900
TS-2409 TS-2517 TS-2611 TS-2689 TS-2771 TS-2833 TS-2903
TS-2410 TS-2518 TS-2612 TS-2691 TS-2772 TS-2834 TS-2904
TS-2411 TS-2521 TS-2614 TS-2695 TS-2773 TS-2835 TS-2906
TS-2412 TS-2522 TS-2615 TS-2697 TS-2775 TS-2836 TS-2907
TS-2415 TS-2527 TS-2616 TS-2698 TS-2776 TS-2837 TS-2908
TS-2417 TS-2529 TS-2617 TS-2699 TS-2778 TS-2838 TS-2909
TS-2421 TS-2532 TS-2620 TS-2700 TS-2779 TS-2839 TS-2910
TS-2422 TS-2536 TS-2625 TS-2701 TS-2780 TS-2840 TS-2911
TS-2423 TS-2540 TS-2626 TS-2707 TS-2782 TS-2843 TS-2913
TS-2427 TS-2544 TS-2628 TS-2710 TS-2783 TS-2844 TS-2914
TS-2428 TS-2545 TS-2629 TS-2711 TS-2784 TS-2845 TS-2916
TS-2435 TS-2547 TS-2630 TS-2712 TS-2785 TS-2846 TS-2917
TS-2437 TS-2551 TS-2631 TS-2713 TS-2786 TS-2848 TS-2919
TS-2440 TS-2552 TS-2632 TS-2714 TS-2788 TS-2849 TS-2920
TS-2444 TS-2553 TS-2634 TS-2716 TS-2790 TS-2850 TS-2922
TS-2446 TS-2554 TS-2635 TS-2717 TS-2791 TS-2851 TS-2923
TS-2447 TS-2555 TS-2636 TS-2719 TS-2792 TS-2852 TS-2924
TS-2453 TS-2558 TS-2637 TS-2722 TS-2793 TS-2853 TS-2925
TS-2455 TS-2562 TS-2640 TS-2724 TS-2794 TS-2854 TS-2927
TS-2458 TS-2563 TS-2641 TS-2725 TS-2795 TS-2855 TS-2928
TS-2460 TS-2566 TS-2642 TS-2726 TS-2796 TS-2856 TS-2929
TS-2463 TS-2568 TS-2644 TS-2727 TS-2797 TS-2857 TS-2930
TS-2466 TS-2570 TS-2647 TS-2728 TS-2799 TS-2860 TS-2932
TS-2467 TS-2571 TS-2648 TS-2732 TS-2801 TS-2861 TS-2933
TS-2471 TS-2572 TS-2650 TS-2734 TS-2803 TS-2862 TS-2934
TS-2472 TS-2573 TS-2651 TS-2735 TS-2804 TS-2863 TS-2935
TS-2474 TS-2574 TS-2653 TS-2736 TS-2805 TS-2864 TS-2937
TS-2476 TS-2575 TS-2656 TS-2738 TS-2807 TS-2865 TS-2938
TS-2477 TS-2576 TS-2657 TS-2739 TS-2808 TS-2868 TS-2939
TS-2478 TS-2579 TS-2658 TS-2740 TS-2810 TS-2872 TS-2943
TS-2481 TS-2580 TS-2659 TS-2741 TS-2811 TS-2874 TS-2944
TS-2482 TS-2581 TS-2662 TS-2742 TS-2812 TS-2877 TS-2946
TS-2948 TS-3040 TS-3113 TS-3177 TS-3249 TS-3689 TS-3928
TS-2949 TS-3043 TS-3114 TS-3178 TS-3250 TS-3690 TS-3936
TS-2950 TS-3046 TS-3116 TS-3179 TS-3251 TS-3695 TS-3939
TS-2951 TS-3049 TS-3119 TS-3180 TS-3252 TS-3699 TS-3942
TS-2953 TS-3050 TS-3120 TS-3181 TS-3253 TS-3702 TS-3950
TS-2954 TS-3052 TS-3121 TS-3182 TS-3255 TS-3703 TS-3958
TS-2955 TS-3054 TS-3122 TS-3183 TS-3256 TS-3704 TS-3961
TS-2957 TS-3055 TS-3123 TS-3184 TS-3257 TS-3706 TS-3968
TS-2958 TS-3056 TS-3124 TS-3185 TS-3259 TS-3708 TS-3987
TS-2959 TS-3058 TS-3125 TS-3186 TS-3262 TS-3710 TS-3993
TS-2960 TS-3060 TS-3126 TS-3188 TS-3271 TS-3717 TS-3995
TS-2962 TS-3065 TS-3127 TS-3189 TS-3276 TS-3718 TS-4003
TS-2964 TS-3066 TS-3129 TS-3191 TS-3278 TS-3734 TS-4027
TS-2965 TS-3071 TS-3131 TS-3193 TS-3282 TS-3743 TS-4031
TS-2968 TS-3072 TS-3132 TS-3194 TS-3286 TS-3761 TS-4087
TS-2969 TS-3074 TS-3133 TS-3195 TS-3289 TS-3772 TS-4099
TS-2973 TS-3075 TS-3134 TS-3198 TS-3290 TS-3780 TS-4118
TS-2976 TS-3076 TS-3135 TS-3200 TS-3291 TS-3789 TS-4145
TS-2980 TS-3077 TS-3138 TS-3201 TS-3292 TS-3805 TS-4146
TS-2984 TS-3078 TS-3139 TS-3202 TS-3295 TS-3820 TS-4147
TS-2985 TS-3079 TS-3140 TS-3204 TS-3297 TS-3821 TS-4163
TS-2986 TS-3080 TS-3141 TS-3205 TS-3306 TS-3822 TS-4167
TS-2988 TS-3081 TS-3142 TS-3207 TS-3309 TS-3824 TS-4175
TS-2991 TS-3082 TS-3143 TS-3210 TS-3310 TS-3825 TS-4178
TS-2998 TS-3084 TS-3144 TS-3215 TS-3317 TS-3839 TS-4181
TS-3001 TS-3087 TS-3145 TS-3216 TS-3320 TS-3841 TS-4186
TS-3002 TS-3088 TS-3148 TS-3217 TS-3328 TS-3843 TS-4195
TS-3003 TS-3089 TS-3149 TS-3218 TS-3388 TS-3844 TS-4212
TS-3005 TS-3090 TS-3151 TS-3219 TS-3392 TS-3846 TS-4232
TS-3006 TS-3091 TS-3154 TS-3221 TS-3395 TS-3849 TS-4271
TS-3009 TS-3093 TS-3155 TS-3222 TS-3429 TS-3850 TS-4331
TS-3011 TS-3094 TS-3156 TS-3223 TS-3441 TS-3851 TS-4345
TS-3016 TS-3096 TS-3158 TS-3224 TS-3516 TS-3853 TS-4366
TS-3018 TS-3097 TS-3159 TS-3226 TS-3561 TS-3855 TS-4396
TS-3020 TS-3098 TS-3160 TS-3227 TS-3567 TS-3857 TS-4401
TS-3021 TS-3100 TS-3161 TS-3232 TS-3574 TS-3860 TS-4420
TS-3025 TS-3101 TS-3162 TS-3234 TS-3590 TS-3862 TS-4461
TS-3026 TS-3102 TS-3164 TS-3235 TS-3591 TS-3863 TS-4480
TS-3027 TS-3103 TS-3166 TS-3236 TS-3595 TS-3871 TS-4636
TS-3028 TS-3104 TS-3167 TS-3237 TS-3598 TS-3878 TS-4651
Page 60069
TS-3030 TS-3105 TS-3168 TS-3240 TS-3609 TS-3879 TS-4678
TS-3031 TS-3106 TS-3169 TS-3241 TS-3625 TS-3882 TS-4696
TS-3032 TS-3107 TS-3170 TS-3242 TS-3638 TS-3883 TS-4770
TS-3033 TS-3108 TS-3171 TS-3243 TS-3650 TS-3885 N/A
TS-3034 TS-3109 TS-3172 TS-3244 TS-3669 TS-3910 N/A
TS-3035 TS-3110 TS-3174 TS-3245 TS-3684 TS-3914 N/A
TS-3037 TS-3111 TS-3175 TS-3247 TS-3685 TS-3921 N/A
TS-3038 TS-3112 TS-3176 TS-3248 TS-3687 TS-3924 N/A
----------------------------------------------------------------------------------------------------------------
Table 5a to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N with any S/N listed in table 5b to paragraph (c) of this AD
-------------------------------------------------------------------------
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000
------------------------------------------------------------------------
Table 5b to Paragraph (c) of This AD
------------------------------------------------------------------------
-------------------------------------------------------------------------
TS-2141
TS-2269
TS-2274
TS-2295
TS-2317
TS-2664
TS-2715
------------------------------------------------------------------------
Table 6 to Paragraph (c) of This AD
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
------------------------------------------------------------------------
D554 71000 020 00........................... TS-1494
D554 71002 000 00 0002...................... TS-2212
------------------------------------------------------------------------
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason
This AD was prompted by reports of surface defects on rudders that were the result of debonding between the skin and honeycomb core. We are issuing this AD to detect and correct extended de-
bonding, which might degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Retained Repetitive Inspections of Rudders With a Core Density of 24 kg/m\3\
This paragraph restates the requirements of paragraph (g) of AD 2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). For rudders identified in table 1 to paragraph (c) of this AD with a honeycomb core density of 24 kg/m\3\ (rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069 and TS-1090, and rudder P/N D554 71000 012 00 having affected rudder S/N TS-1227), do the actions specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in accordance with Airbus All Operators Telex (AOT) A320-55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009; for the locations defined in the applicable AOT specified in this paragraph.
(1) Within 200 days after December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Perform a vacuum loss inspection on the rudder reinforced area.
(2) Within 20 months after December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Perform an elasticity laminate checker inspection on the rudder trailing edge area. Repeat the inspection two times, at intervals not to exceed 4,500 flight cycles, but not sooner than 4,000 flight cycles after the last inspection.
(3) Within 200 days after December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Perform an elasticity laminate checker inspection of the other areas (splice/lower rib/
upper edge/leading edge/other specified locations). Repeat the inspection at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.
(4) Within 20 months after December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Perform a vacuum loss inspection of the other areas (splice/lower rib/upper edge/leading edge/other specified locations). Accomplishment of the action specified in paragraph (g)(4) of this AD terminates the requirements of paragraph (g)(3) of this AD.
(h) Retained Repetitive Inspections of Rudders Without a Core Density of 24 kg/m\3\
This paragraph restates the requirements of paragraph (h) of AD 2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). For rudders that do not have a honeycomb core density of 24 kg/m\3\ (all rudders identified in table 1 to paragraph (c) of this AD, except rudder P/N D554 71000 010 00 having affected rudder S/Ns TS-1069 and TS-1090, and rudder P/N D554 71000 012 00 having affected rudder S/N TS-1227), do the actions specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, in accordance with Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009; for the locations defined in the applicable AOT specified in this paragraph. As of the effective date of this AD, use only Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. For this paragraph, ``reference date'' is defined as December 10, 2010 (the effective date of AD 2010-23-07), or the date when the rudder will accumulate 20,000 total flight cycles from its first installation on an airplane, whichever occurs later.
(1) Within 200 days after the reference date, perform a vacuum loss inspection on the rudder reinforced area.
(2) Within 20 months after the reference date, perform an elasticity laminate checker inspection on the rudder trailing edge area. Repeat the inspection two times at intervals not to exceed 4,500 flight cycles, but not sooner than 4,000 flight cycles after the last inspection.
(3) Within 200 days after the reference date, perform an elasticity laminate checker inspection of the other areas (splice/
lower rib/upper edge/leading edge/other specified locations). Repeat the inspection at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.
(4) Within 20 months after the reference date, perform a vacuum loss inspection of the other areas (splice/lower rib/upper edge/
leading edge/other specified locations). Accomplishment of the actions specified in this paragraph terminates the requirements of paragraph (h)(3) of this AD.
(i) Retained Corrective Actions for De-Bonding
This paragraph restates the requirements of paragraph (i) of AD 2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). In case of de-bonding found during any inspection required by paragraph (g) or (h) of this AD, before further flight, contact Airbus for further instructions and apply the associated instructions and corrective actions
Page 60070
in accordance with the approved data provided, or repair the debonding using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). After the effective date of this AD, repair the debonding using only a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(j) Retained Reporting for Findings From Actions Required by Paragraphs (g) and (h) of this AD
This paragraph restates the requirements of paragraph (j) of AD 2010-23-07 Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, submit a report of the findings (both positive and negative) of each inspection required by paragraphs (g) and (h) of this AD. The report must include the inspection results, as specified in Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E, dated September 17, 2009. For positive findings, submit the report to either the Manager, Seer1/Seer2/Seer3 Customer Services, fax +33 (0)5 61 93 28 73, email region1.structurerepairsupport@airbus.com, region2.structurerepairsupport@airbus.com, or region3.structurerepairsupport@airbus.com; or AIRTAC (Airbus Technical AOG Center) Customer Services, telephone +33 (0)5 61 93 34 00, fax +33 (0)5 61 93 35 00, email airtac@airbus.com. For negative findings, submit the report to Nicolas Seynaeve, Sees1, Customer Services; telephone +33 (0)5 61 93 34 38; fax +33 (0)5 61 93 36 14; email nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Submit the report within 30 days after the inspection.
(2) For any inspection done before December 10, 2010 (the effective date of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883))): Submit the report within 30 days after December 10, 2010.
(k) Retained Inspection in Additional Areas
This paragraph restates the provisions of paragraph (k) of AD 2010-23-07, Amendment 39-16496, (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). All rudders that have passed the inspection specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3), and (h)(4) of this AD before December 10, 2010 (the effective date of AD 2010-23-07), in accordance with Airbus AOT A320-55A1038, dated April 22, 2009; or Airbus Technical Disposition TD/K4/S2/27051/2009, Issue B, dated February 25, 2009; are compliant with this AD only for the areas inspected. Additional areas defined in Section 0, ``Reason for Revision,'' of Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009; must be inspected as specified in paragraph (g) or (h) of this AD. For all areas, the repetitive inspections required by paragraph (g) or (h) of this AD remain applicable.
(l) Retained Parts Installation Limitations
This paragraph restates the requirements of paragraph (l) of AD 2010-23-07, Amendment 39-16496 (75 FR 68181, November 5, 2010; corrected December 17, 2010 (75 FR 78883)). After December 10, 2010 (the effective date of AD 2010-23-07), no rudder listed in table 1 to paragraph (c) of this AD may be installed on any airplane, unless the rudder is inspected in accordance with paragraph (g) or (h) of this AD, as applicable, and all applicable actions specified in paragraph (i) of this AD are done.
(m) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, restore the vacuum loss holes by doing a permanent restoration with resin, in accordance with Note 3 of Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. Before doing the resin injection, do a local ultrasound inspection in reinforced areas, and a thermography inspection in other areas, for damage, in accordance with Note 3 of Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. If any damage is found during any inspection required by this paragraph: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(n) New X-Ray, Elasticity Laminate Checker (ELCh), Vacuum Loss, or Thermography Inspection
For rudders identified in table 2 to paragraph (c) of this AD, do the actions specified in paragraphs (n)(1) and (n)(2) of this AD, in accordance with Airbus AOT A320-55A1039, dated November 4, 2009, for the locations defined in that AOT. For this paragraph, ``reference date'' is defined as the effective date of this AD or the date when the rudder will accumulate 20,000 total flight cycles from its first installation on an airplane, whichever occurs later.
(1) Within 20 months after the effective date of this AD, or within 200 days after the reference date, whichever occurs first: Perform X-ray, and/or ELCh, and/or vacuum loss, and/or thermography inspections for damage, as applicable to rudder part number and serial number, in accordance with the instructions of paragraph 4.2.2.1.1. of Airbus AOT A320-55A1039, dated November 4, 2009.
(2) At the applicable time specified in paragraph (n)(2)(i) or (n)(2)(ii) of this AD, send the developed X-ray films and the film layout arrangement, if applicable, to Attn: SDC32 Technical Data and Documentation Services, Airbus Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com.
(i) If the inspection was done on or after the effective date of this AD: Submit the X-ray films and the film layout arrangement within 10 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the X-ray films and the film layout arrangement within 10 days after the effective date of this AD.
(3) If any damage is found during any inspection required by paragraph (n) of this AD: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(o) New ELCh Inspection, Vacuum Loss Inspection, and Repairs
For rudders identified in table 2 to paragraph (c) of this AD: Within 1,500 flight cycles or 200 days after doing the requirements of paragraph (n)(1) of this AD, whichever occurs first, do the actions specified in paragraphs (o)(1) and (o)(2) of this AD.
(1) Perform an ELCh inspection for damage on the rudder trailing edge area, in accordance with the instructions of paragraph 4.2.2.1.2. of Airbus AOT A320-55A1039, dated November 4, 2009. In case of no finding, repeat the inspection two times, at intervals not to exceed 4,500 flight cycles but not sooner than 4,000 flight cycles after the last inspection.
(2) Perform a vacuum loss inspection for damage of the other areas (splice/lower rib/upper edge/leading edge/other specified locations), in accordance with the instructions of paragraph 4.2.2.1.2. of Airbus AOT A320-55A1039, dated November 4, 2009.
(3) If any damage is found during any inspection required by paragraph (o) of this AD: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(p) New Restorations and Inspections of Certain Vacuum Loss Holes, and Repairs
If no damage is found during any inspection required by paragraph (o) of this AD: Before further flight, restore the vacuum loss holes by doing a permanent restoration with resin, in accordance with Note 3 of Airbus AOT A320-55A1039, dated November 4, 2009. Before doing the resin injection, do a local ultrasound inspection in reinforced areas, and a thermography inspection in other areas, for damage, in accordance with Note 3 of Airbus AOT A320-55A1039, dated November 4, 2009. If any damage is found during any inspection required by this paragraph: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(q) New Rudder Replacement for Rudders Identified in Table 3 to Paragraph (c) of This AD
For rudders identified in table 3 to paragraph (c) of this AD, do the actions specified in paragraphs (q)(1) and (q)(2) of this AD, in accordance with the instruction of Airbus AOT A320-55A1039, dated November 4, 2009, for the locations defined in that AOT. For this paragraph, ``reference date'' is defined as the effective date of this
Page 60071
AD or the date when the rudder will accumulate 20,000 total flight cycles from its first installation on an airplane, whichever occurs later.
(1) For rudders identified in table 3 to paragraph (c) of this AD with a honeycomb core density of 24 kg/m\3\ (rudder P/N D554-
71000-008-00 having affected rudder S/N TS-1032 and rudder P/N D554-
71000-010-00 having affected rudder S/N TS-1092): Within 200 days after the effective date of this AD, replace the rudder with a new rudder, in accordance with a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(2) For rudders identified in table 3 to paragraph (c) of this AD that do not have a honeycomb core density of 24 kg/m\3\ (all except rudder P/N D554-71000-008-00 having affected rudder S/N TS-
1032 and rudder P/N D554-71000-010-00 having affected rudder S/N TS-
1092): Within 20 months after the effective date of this AD or within 200 days after the reference date, whichever occurs first, replace the rudder with a new rudder, in accordance with a method approved by the Manager, International Branch, ANM-116.
(r) New Vacuum Loss Inspection for Reinforced Areas of Rudder Identified in Table 4 to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b to paragraph (c) of this AD: At the later of the times specified in paragraphs (r)(1) and (r)(2) of this AD, perform a vacuum loss inspection on the rudder reinforced area for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes).
(1) Before the rudder accumulates 17,000 total flight cycles from its first installation on an airplane without exceeding 20 months from the effective date of this AD.
(2) Within 200 days after the effective date of this AD.
(s) New ELCh Inspection for Rudder Trailing Edge Area
For rudders identified in tables 4a and 4b to paragraph (c) of this AD: Within 20 months after the effective date of this AD, perform an ELCh inspection for damage on the rudder trailing edge area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). Repeat the inspection two times at intervals not to exceed 4,500 flight cycles, but not sooner than 4,000 flight cycles after the last inspection.
(t) New ELCh Inspection for Additional Rudder Areas
For rudders identified in tables 4a and 4b to paragraph (c) of this AD: At the later of the times specified in paragraphs (t)(1) and (t)(2) of this AD, perform an ELCh inspection for damage of the other areas (splice/lower rib/upper edge/leading edge/other specified locations) for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). Repeat the inspection thereafter at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.
(1) Before the rudder accumulates 17,000 total flight cycles from its first installation on an airplane without exceeding 20 months from the effective date of this AD.
(2) Within 200 days after the effective date of this AD.
(u) New Vacuum Loss Inspection for Certain Areas of Rudders Identified in Tables 4a and 4b to Paragraph (c) of This AD
For rudders identified in tables 4a and 4b of this AD: Within 20 months after the effective date of this AD, perform a vacuum loss inspection for damage of the lower rib, upper edge, leading edge, and other specified locations, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). Accomplishment of the actions specified in this paragraph terminates the requirements of paragraph (t) of this AD.
(v) New Corrective Actions for Certain Inspections
In case of damage found during any inspection required by paragraph (r), (s), (t), or (u) of this AD: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(w) New Restorations and Inspections of Certain Vacuum Loss Holes, and Repairs
If no damage is found during any inspection required by paragraph (r) or (u) of this AD: Before further flight, restore the vacuum loss holes by doing a permanent restoration with resin, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). Before doing the resin injection, do a local ultrasound inspection in reinforced areas, and a thermography inspection in other areas, for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). If any damage is found during any inspection required by this paragraph: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(x) Credit for Certain Previous Actions
This paragraph provides credit for the inspections required by paragraphs (r), (s), (t), (u), and (w) of this AD only for the inspected area for rudders identified in tables 4a and 4b to paragraph (c) of this AD, if the area passed the inspection before the effective date of this AD using Airbus Service Bulletin A320-55-
1035, dated February 17, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, dated February 17, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037, dated February 17, 2010 (for Model A319 airplanes). For all other inspected areas, the repetitive inspections required by paragraph (s), (t), and (w) of this AD are still required.
(y) New ELCh Inspection and Repairs for Certain Rudders
For rudders identified in tables 5a and 5b to paragraph (c) of this AD: Within 4,500 flight cycles but not sooner than 4,000 flight cycles after the sampling inspection, perform an ELCh inspection for damage on the rudder trailing edge area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-
1037, Revision 01, dated July 2, 2010 (for Model A319 airplanes). Repeat the inspection within 4,500 flight cycles, but not sooner than 4,000 flight cycles after the last inspection. If any damage is found during any inspection required by paragraph (y) of this AD: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(z) Credit for Certain Other Previous Actions
This paragraph provides credit for the inspection required by paragraph (y) of this AD only for the inspected area for rudders identified in tables 5a and 5b to paragraph (c) of this AD that have passed the inspection before the effective date of this AD using Airbus Service Bulletin A320-55-1035, dated February 17, 2010 (for Model A320 airplanes); Airbus Service Bulletin A320-55-1036, dated February 17, 2010 (for Model A318 and A321 airplanes); or Airbus Service Bulletin A320-55-1037, dated February 17, 2010 (for Model A319 airplanes). For all inspection areas, the repetitive inspections required by paragraph (y) of this AD are still required.
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(aa) New Repetitive Inspections of Rudders Identified in Table 6 to Paragraph (c) of This AD
For rudders identified in table 6 to paragraph (c) of this AD, do the actions specified in paragraphs (aa)(1), (aa)(2), (aa)(3), and (aa)(4) of this AD, in accordance with Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. For this paragraph, ``reference date'' is defined as the date when the rudder will accumulate 20,000 total flight cycles from its first installation on an airplane.
(1) Within 200 days after the reference date, perform a vacuum loss inspection on the rudder reinforced area.
(2) Within 20 months after the reference date, perform an elasticity laminate checker inspection on the rudder trailing edge area. Repeat the inspection two times at intervals not to exceed 4,500 flight cycles, but not sooner than 4,000 flight cycles, after the last inspection.
(3) Within 200 days after the reference date, perform an elasticity laminate checker inspection of the other areas (splice/
lower rib/upper edge/leading edge/other specified locations). Repeat the inspection at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.
(4) Within 20 months after the reference date, perform a vacuum loss inspection of the other areas (splice/lower rib/upper edge/
leading edge/other specified locations). Accomplishment of the actions specified in this paragraph terminates the requirements of paragraph (h)(3) of this AD.
(bb) New De-Bonding Corrective Actions
In case of de-bonding found during any inspection required by paragraph (aa) of this AD: Before further flight, contact Airbus for further instructions and apply the associated instructions and corrective actions in accordance with the approved data provided.
(cc) New Restoration of Vacuum Loss Holes
If no de-bonding is found during any inspection required by paragraph (aa) of this AD: Before further flight, restore the vacuum loss holes by a permanent restoration with resin, in accordance with Note 3 of Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. Before doing the resin injection, do a local ultrasound inspection in reinforced areas, and a thermography inspection in other areas, for damage, in accordance with Note 3 of Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009. If any damage is found during any inspection required by this paragraph: Before further flight, repair the damage using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
(dd) New Reporting for Paragraphs (n), (o), (r), (s), (t), (u), (y), and (aa) of This AD
At the applicable time specified in paragraph (dd)(1) or (dd)(2) of this AD, submit a report of the findings (both positive and negative) of each inspection required by paragraphs (n), (o), (r), (s), (t), (u), (y), and (aa) of this AD. The report must include the inspection results, as specified in Airbus Technical Disposition TD/
K4/S2/27086/2009, Issue E, dated September 17, 2009. For positive findings, submit the report to either the Manager, Seer1/Seer2/Seer3 Customer Services, fax +33 (0)5 61 93 28 73, email region1.structurerepairsupport@airbus.com, region2.structurerepairsupport@airbus.com, or region3.structurerepairsupport@airbus.com; or AIRTAC (Airbus Technical AOG Center) Customer Services, telephone +33 (0)5 61 93 34 00, fax +33 (0)5 61 93 35 00, email airtac@airbus.com. For negative findings, submit the report to Nicolas Seynaeve, Sees1, Customer Services, telephone +33 (0)5 61 93 34 38, fax +33 (0)5 61 93 36 14, email nicolas.seynaeve@airbus.com.
(1) For any inspection done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(2) For any inspection done before the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
(ee) New Parts Installation Limitation
As of the effective date of this AD, no rudder listed in table 1, 2, 3, 4a, 4b, 5a, 5b, or 6 to paragraph (c) of this AD may be installed on any airplane, unless the rudder is in compliance with the requirements of this AD.
(ff) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, 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: 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. 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. The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
(gg) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2010-0164, dated August 5, 2010, and the following service information, for related information.
(i) Airbus AOT A320-55A1038, dated April 22, 2009.
(ii) Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009.
(iii) Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009.
(iv) Airbus AOT A320-55A1039, dated November 4, 2009.
(v) Airbus Service Bulletin A320-55-1035, Revision 01, dated July 2, 2010.
(vi) Airbus Service Bulletin A320-55-1036, Revision 01, dated July 2, 2010.
(vii) Airbus Service Bulletin A320-55-1037, Revision 01, dated July 2, 2010.
(viii) Airbus Technical Disposition TD/K4/S2/27051/2009, Issue B, dated February 25, 2009.
(ix) Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E, dated September 17, 2009.
(2) For service information identified in this AD, contact Airbus, Airworthiness Office--EAS, 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 review copies of the 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.
Issued in Renton, Washington, on September 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
FR Doc. 2012-24175 Filed 10-1-12; 8:45 am
BILLING CODE 4910-13-P
