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Proposed Rule

Airworthiness Directives; Airbus Airplanes

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ACTION:

Notice of proposed rulemaking (NPRM).

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:

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:

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.

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

The Proposed Amendment

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

PART 39—AIRWORTHINESS DIRECTIVES

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

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

[Amended]

2. The FAA amends § 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

Rudder P/NAffected rudder S/N
D554 71000 010 00TS-1069
D554 71000 010 00TS-1090
D554 71000 012 00TS-1227
D554 71000 014 00TS-1350
D554 71000 014 00TS-1366
D554 71000 014 00TS-1371
D554 71000 014 00TS-1383
D554 71000 014 00TS-1387
D554 71000 016 00TS-1412
D554 71000 018 00TS-1443
D554 71000 018 00TS-1444
D554 71000 018 00TS-1468
D554 71000 020 00TS-1480
D554 71000 020 00TS-1491
D554 71000 020 00TS-1495
D554 71000 020 00TS-1498
D554 71000 020 00TS-1499
D554 71000 020 00TS-1500
D554 71000 020 00TS-1505
D554 71000 020 00TS-1506
D554 71000 020 00TS-1507
D554 71000 020 00TS-1509
D554 71000 020 00TS-1515
D554 71000 020 00TS-1528
D554 71000 020 00TS-1530
D554 71000 020 00TS-1532
D554 71000 020 00TS-1535
D554 71000 020 00TS-1536
D554 71000 020 00TS-1538
D554 71001 000 00TS-1537
D554 71001 000 00TS-1540
D554 71001 000 00TS-1541
D554 71001 000 00TS-1543
D554 71001 000 00TS-1548
D554 71001 000 00TS-1549
D554 71001 000 00TS-1551
D554 71001 000 00TS-1554
D554 71001 000 00TS-1555
D554 71001 000 00TS-1556
D554 71001 000 00TS-1557
D554 71001 000 00TS-1559
D554 71001 000 00TS-1562
D554 71001 000 00TS-1563
D554 71001 000 00TS-1564
D554 71001 000 00TS-1565
D554 71001 000 00TS-1566
D554 71001 000 00TS-1567
D554 71001 000 00TS-1568
D554 71001 000 00TS-1569
D554 71001 000 00TS-1570
D554 71001 000 00TS-1573
D554 71001 000 00TS-1575
D554 71001 000 00TS-1578
D554 71001 000 00TS-1579
D554 71001 000 00TS-1580
D554 71001 000 00TS-1581
D554 71001 000 00TS-1582
D554 71001 000 00TS-1584
D554 71001 000 00TS-1593
D554 71001 000 00TS-1594
D554 71001 000 00TS-1596
D554 71001 000 00TS-1599
D554 71001 000 00TS-1603
D554 71001 000 00TS-1609
D554 71001 000 00TS-1621
D554 71001 000 00TS-1626
D554 71001 000 00TS-1627
D554 71001 000 00TS-1635
D554 71001 000 00TS-1637
D554 71002 000 00TS-2306
D554 71002 000 00 0001TS-2003
D554 71002 000 00 0001TS-2005
D554 71002 000 00 0001TS-2013
D554 71002 000 00 0001TS-2016
D554 71002 000 00 0001TS-2019
D554 71002 000 00 0001TS-2020
D554 71002 000 00 0001TS-2022
D554 71002 000 00 0001TS-2024
D554 71002 000 00 0001TS-2026
D554 71002 000 00 0001TS-2031
D554 71002 000 00 0001TS-2033
D554 71002 000 00 0001TS-2043
D554 71002 000 00 0001TS-2047
D554 71002 000 00 0001TS-2048
D554 71002 000 00 0001TS-2054
D554 71002 000 00 0001TS-2058
D554 71002 000 00 0001TS-2059
D554 71002 000 00 0001TS-2064
D554 71002 000 00 0001TS-2072
D554 71002 000 00 0001TS-2075
D554 71002 000 00 0001TS-2076
D554 71002 000 00 0001TS-2079
D554 71002 000 00 0001TS-2083
D554 71002 000 00 0001TS-2089
D554 71002 000 00 0002TS-2090
D554 71002 000 00 0002TS-2095
D554 71002 000 00 0002TS-2103
D554 71002 000 00 0002TS-2116
D554 71002 000 00 0002TS-2122
D554 71002 000 00 0002TS-2133
D554 71002 000 00 0002TS-2142
D554 71002 000 00 0002TS-2147
D554 71002 000 00 0002TS-2157
D554 71002 000 00 0002TS-2158
D554 71002 000 00 0002TS-2162
D554 71002 000 00 0002TS-2167
D554 71002 000 00 0002TS-2174
D554 71002 000 00 0002TS-2176
D554 71002 000 00 0002TS-2181
D554 71002 000 00 0002TS-2189
D554 71002 000 00 0002TS-2191
D554 71002 000 00 0002TS-2203
D554 71002 000 00 0002TS-2205
D554 71002 000 00 0002TS-2207
D554 71002 000 00 0002TS-2224
D554 71002 000 00 0002TS-2229
D554 71002 000 00 0002TS-2233
D554 71002 000 00 0002TS-2241
D554 71002 000 00 0002TS-2246
D554 71002 000 00 0002TS-2249
D554 71002 000 00 0002TS-2270
D554 71002 000 00 0002TS-2275
D554 71002 000 00 0002TS-2289
D554 71002 000 00 0002TS-2290
D554 71002 000 00 0002TS-2294
D554 71002 000 00 0002TS-2309
D554 71002 000 00 0002TS-2347
D554 71002 000 00 0002TS-2348
D554 71002 000 00 0002TS-2349
D554 71002 000 00 0002TS-2357
D554 71002 000 00 0002TS-2361
D554 71002 000 00 0002TS-2380
D554 71002 000 00 0002TS-2383
D554 71002 000 00 0002TS-2390
D554 71002 000 00 0002TS-2394
D554 71002 000 00 0002TS-2396
D554 71002 000 00 0002TS-2401
D554 71002 000 00 0002TS-2406
D554 71002 000 00 0002TS-2461
D554 71002 000 00 0002TS-2468
D554 71002 000 00 0002TS-2516
D554 71002 000 00 0002TS-2537
D554 71002 000 00 0002TS-2543
D554 71002 000 00 0002TS-2546
D554 71002 000 00 0002TS-2619
D554 71002 000 00 0002TS-2684
D554 71002 000 00 0003TS-2752
D554 71002 000 00 0003TS-2869
D554 71002 000 00 0003TS-2876
D554 71002 000 00 0003TS-2970
D554 71002 000 00 0003TS-2971
D554 71002 000 00 0003TS-2987
D554 71004 000 00 0000TS-3083
D554 71004 000 00 0000TS-3197

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 density of 24 kilogram (kg)/meters cubed (m3).

Table 2 to Paragraph (c) of This AD

Rudder P/NAffected rudder S/N
D554-71000-014-00TS-1278
D554-71002-000-00-0001TS-2081
D554-71002-000-00-0002TS-2125
D554-71002-000-00-0002TS-2129
D554-71002-000-00-0002TS-2160
D554-71002-000-00-0002TS-2201
D554-71002-000-00-0002TS-2328
D554-71002-000-00-0002TS-2425
D554-71002-000-00-0002TS-2511
D554-71002-000-00-0003TS-2768
D554-71002-000-00-0003TS-2999
D554-71002-000-00-0003TS-3004
D554-71002-000-00-0003TS-3051
D554-71004-000-00-0001TS-3288

Table 3 to Paragraph (c) of This AD

Rudder P/NAffected rudder S/N
D554-71000-008-00TS-1032
D554-71000-010-00TS-1092
D554-71000-014-00TS-1314
D554-71000-018-00TS-1445
D554-71000-020-00TS-1520
D554-71002-000-00-0001TS-2037
D554-71002-000-00-0002TS-2109
D554-71002-000-00-0002TS-2123
D554-71002-000-00-0002TS-2124
D554-71002-000-00-0002TS-2424
D554-71002-000-00-0002TS-2559
D554-71002-000-00-0003TS-3061
D554-71004-000-00-0001TS-3694
D554-71004-000-00-0001TS-3709
D554-71004-000-00-0002TS-4148

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/m3.

Table 4a to Paragraph (c) of this AD

Rudder P/N with any S/N listed in table 4b to paragraph (c) of this AD
D5547100000000
D5547100000200
D5547100000400
D5547100000600
D5547100000800
D5547100001000
D5547100001200
D5547100001400
D5547100001600
D5547100001800
D5547100002000
D5547100100000
D5547100200000
D5547100300000
D5547100400000

Table 4b to Paragraph (c) of This AD

Affected S/N for rudders listed in table 4a to paragraph (c) of this AD
TS-1368TS-1616TS-2080TS-2159TS-2222TS-2276TS-2327
TS-1389TS-1619TS-2082TS-2163TS-2223TS-2279TS-2330
TS-1496TS-1622TS-2084TS-2168TS-2227TS-2280TS-2331
TS-1501TS-1632TS-2085TS-2169TS-2228TS-2281TS-2332
TS-1503TS-1639TS-2086TS-2170TS-2230TS-2284TS-2333
TS-1508TS-2004TS-2094TS-2172TS-2231TS-2285TS-2334
TS-1516TS-2008TS-2096TS-2175TS-2232TS-2286TS-2336
TS-1527TS-2010TS-2097TS-2177TS-2234TS-2293TS-2337
TS-1529TS-2012TS-2098TS-2179TS-2235TS-2297TS-2338
TS-1534TS-2014TS-2100TS-2182TS-2236TS-2298TS-2339
TS-1545TS-2017TS-2101TS-2183TS-2238TS-2299TS-2340
TS-1547TS-2018TS-2106TS-2185TS-2240TS-2302TS-2341
TS-1553TS-2023TS-2113TS-2192TS-2242TS-2303TS-2343
TS-1560TS-2025TS-2115TS-2193TS-2244TS-2304TS-2346
TS-1561TS-2029TS-2118TS-2195TS-2245TS-2305TS-2352
TS-1571TS-2032TS-2126TS-2199TS-2248TS-2307TS-2353
TS-1572TS-2034TS-2130TS-2200TS-2250TS-2310TS-2354
TS-1574TS-2039TS-2131TS-2204TS-2251TS-2311TS-2355
TS-1576TS-2040TS-2132TS-2206TS-2252TS-2312TS-2356
TS-1577TS-2041TS-2134TS-2208TS-2254TS-2313TS-2358
TS-1583TS-2046TS-2136TS-2209TS-2258TS-2315TS-2360
TS-1585TS-2050TS-2140TS-2210TS-2259TS-2316TS-2362
TS-1588TS-2051TS-2143TS-2211TS-2260TS-2319TS-2363
TS-1591TS-2052TS-2144TS-2213TS-2261TS-2320TS-2364
TS-1600TS-2053TS-2145TS-2216TS-2262TS-2321TS-2365
TS-1602TS-2056TS-2149TS-2217TS-2265TS-2322TS-2366
TS-1607TS-2060TS-2152TS-2218TS-2268TS-2323TS-2367
TS-1608TS-2069TS-2154TS-2220TS-2271TS-2325TS-2370
TS-1614TS-2070TS-2155TS-2221TS-2272TS-2326TS-2371
TS-2372TS-2483TS-2583TS-2665TS-2743TS-2813TS-2878
TS-2373TS-2484TS-2584TS-2666TS-2744TS-2814TS-2879
TS-2374TS-2486TS-2585TS-2667TS-2745TS-2815TS-2880
TS-2377TS-2488TS-2586TS-2668TS-2747TS-2816TS-2881
TS-2381TS-2491TS-2587TS-2671TS-2749TS-2818TS-2882
TS-2382TS-2493TS-2590TS-2674TS-2751TS-2819TS-2885
TS-2387TS-2494TS-2591TS-2675TS-2753TS-2821TS-2886
TS-2388TS-2498TS-2592TS-2676TS-2754TS-2822TS-2890
TS-2392TS-2499TS-2593TS-2677TS-2755TS-2823TS-2891
TS-2393TS-2501TS-2596TS-2679TS-2756TS-2824TS-2892
TS-2395TS-2505TS-2597TS-2680TS-2757TS-2826TS-2893
TS-2397TS-2506TS-2601TS-2681TS-2758TS-2827TS-2896
TS-2398TS-2508TS-2602TS-2682TS-2759TS-2828TS-2897
TS-2399TS-2510TS-2603TS-2683TS-2760TS-2830TS-2898
TS-2407TS-2512TS-2605TS-2685TS-2762TS-2831TS-2899
TS-2408TS-2514TS-2606TS-2688TS-2765TS-2832TS-2900
TS-2409TS-2517TS-2611TS-2689TS-2771TS-2833TS-2903
TS-2410TS-2518TS-2612TS-2691TS-2772TS-2834TS-2904
TS-2411TS-2521TS-2614TS-2695TS-2773TS-2835TS-2906
TS-2412TS-2522TS-2615TS-2697TS-2775TS-2836TS-2907
TS-2415TS-2527TS-2616TS-2698TS-2776TS-2837TS-2908
TS-2417TS-2529TS-2617TS-2699TS-2778TS-2838TS-2909
TS-2421TS-2532TS-2620TS-2700TS-2779TS-2839TS-2910
TS-2422TS-2536TS-2625TS-2701TS-2780TS-2840TS-2911
TS-2423TS-2540TS-2626TS-2707TS-2782TS-2843TS-2913
TS-2427TS-2544TS-2628TS-2710TS-2783TS-2844TS-2914
TS-2428TS-2545TS-2629TS-2711TS-2784TS-2845TS-2916
TS-2435TS-2547TS-2630TS-2712TS-2785TS-2846TS-2917
TS-2437TS-2551TS-2631TS-2713TS-2786TS-2848TS-2919
TS-2440TS-2552TS-2632TS-2714TS-2788TS-2849TS-2920
TS-2444TS-2553TS-2634TS-2716TS-2790TS-2850TS-2922
TS-2446TS-2554TS-2635TS-2717TS-2791TS-2851TS-2923
TS-2447TS-2555TS-2636TS-2719TS-2792TS-2852TS-2924
TS-2453TS-2558TS-2637TS-2722TS-2793TS-2853TS-2925
TS-2455TS-2562TS-2640TS-2724TS-2794TS-2854TS-2927
TS-2458TS-2563TS-2641TS-2725TS-2795TS-2855TS-2928
TS-2460TS-2566TS-2642TS-2726TS-2796TS-2856TS-2929
TS-2463TS-2568TS-2644TS-2727TS-2797TS-2857TS-2930
TS-2466TS-2570TS-2647TS-2728TS-2799TS-2860TS-2932
TS-2467TS-2571TS-2648TS-2732TS-2801TS-2861TS-2933
TS-2471TS-2572TS-2650TS-2734TS-2803TS-2862TS-2934
TS-2472TS-2573TS-2651TS-2735TS-2804TS-2863TS-2935
TS-2474TS-2574TS-2653TS-2736TS-2805TS-2864TS-2937
TS-2476TS-2575TS-2656TS-2738TS-2807TS-2865TS-2938
TS-2477TS-2576TS-2657TS-2739TS-2808TS-2868TS-2939
TS-2478TS-2579TS-2658TS-2740TS-2810TS-2872TS-2943
TS-2481TS-2580TS-2659TS-2741TS-2811TS-2874TS-2944
TS-2482TS-2581TS-2662TS-2742TS-2812TS-2877TS-2946
TS-2948TS-3040TS-3113TS-3177TS-3249TS-3689TS-3928
TS-2949TS-3043TS-3114TS-3178TS-3250TS-3690TS-3936
TS-2950TS-3046TS-3116TS-3179TS-3251TS-3695TS-3939
TS-2951TS-3049TS-3119TS-3180TS-3252TS-3699TS-3942
TS-2953TS-3050TS-3120TS-3181TS-3253TS-3702TS-3950
TS-2954TS-3052TS-3121TS-3182TS-3255TS-3703TS-3958
TS-2955TS-3054TS-3122TS-3183TS-3256TS-3704TS-3961
TS-2957TS-3055TS-3123TS-3184TS-3257TS-3706TS-3968
TS-2958TS-3056TS-3124TS-3185TS-3259TS-3708TS-3987
TS-2959TS-3058TS-3125TS-3186TS-3262TS-3710TS-3993
TS-2960TS-3060TS-3126TS-3188TS-3271TS-3717TS-3995
TS-2962TS-3065TS-3127TS-3189TS-3276TS-3718TS-4003
TS-2964TS-3066TS-3129TS-3191TS-3278TS-3734TS-4027
TS-2965TS-3071TS-3131TS-3193TS-3282TS-3743TS-4031
TS-2968TS-3072TS-3132TS-3194TS-3286TS-3761TS-4087
TS-2969TS-3074TS-3133TS-3195TS-3289TS-3772TS-4099
TS-2973TS-3075TS-3134TS-3198TS-3290TS-3780TS-4118
TS-2976TS-3076TS-3135TS-3200TS-3291TS-3789TS-4145
TS-2980TS-3077TS-3138TS-3201TS-3292TS-3805TS-4146
TS-2984TS-3078TS-3139TS-3202TS-3295TS-3820TS-4147
TS-2985TS-3079TS-3140TS-3204TS-3297TS-3821TS-4163
TS-2986TS-3080TS-3141TS-3205TS-3306TS-3822TS-4167
TS-2988TS-3081TS-3142TS-3207TS-3309TS-3824TS-4175
TS-2991TS-3082TS-3143TS-3210TS-3310TS-3825TS-4178
TS-2998TS-3084TS-3144TS-3215TS-3317TS-3839TS-4181
TS-3001TS-3087TS-3145TS-3216TS-3320TS-3841TS-4186
TS-3002TS-3088TS-3148TS-3217TS-3328TS-3843TS-4195
TS-3003TS-3089TS-3149TS-3218TS-3388TS-3844TS-4212
TS-3005TS-3090TS-3151TS-3219TS-3392TS-3846TS-4232
TS-3006TS-3091TS-3154TS-3221TS-3395TS-3849TS-4271
TS-3009TS-3093TS-3155TS-3222TS-3429TS-3850TS-4331
TS-3011TS-3094TS-3156TS-3223TS-3441TS-3851TS-4345
TS-3016TS-3096TS-3158TS-3224TS-3516TS-3853TS-4366
TS-3018TS-3097TS-3159TS-3226TS-3561TS-3855TS-4396
TS-3020TS-3098TS-3160TS-3227TS-3567TS-3857TS-4401
TS-3021TS-3100TS-3161TS-3232TS-3574TS-3860TS-4420
TS-3025TS-3101TS-3162TS-3234TS-3590TS-3862TS-4461
TS-3026TS-3102TS-3164TS-3235TS-3591TS-3863TS-4480
TS-3027TS-3103TS-3166TS-3236TS-3595TS-3871TS-4636
TS-3028TS-3104TS-3167TS-3237TS-3598TS-3878TS-4651
TS-3030TS-3105TS-3168TS-3240TS-3609TS-3879TS-4678
TS-3031TS-3106TS-3169TS-3241TS-3625TS-3882TS-4696
TS-3032TS-3107TS-3170TS-3242TS-3638TS-3883TS-4770
TS-3033TS-3108TS-3171TS-3243TS-3650TS-3885N/A
TS-3034TS-3109TS-3172TS-3244TS-3669TS-3910N/A
TS-3035TS-3110TS-3174TS-3245TS-3684TS-3914N/A
TS-3037TS-3111TS-3175TS-3247TS-3685TS-3921N/A
TS-3038TS-3112TS-3176TS-3248TS-3687TS-3924N/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/NAffected rudder S/N
D554 71000 020 00TS-1494
D554 71002 000 00 0002TS-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/m3

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/m3 (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/m3

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/m3 (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 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 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/m3 (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/m3 (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.

(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]

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