2010-23-07: Stabilizers

2010-23-07 Airbus: Amendment 39-16496. Docket No. FAA-2010-0279; Directorate Identifier 2009-NM-148-AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 10, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes; certificated in any category, all manufacturer serial numbers (S/Ns), if equipped with carbon fiber reinforced plastic rudders having part numbers (P/Ns) and S/Ns as listed in Table 1 of this AD. Table 1--Rudder Part Number and Affected Rudder Serial Number Rudder P/N Affected rudder S/N 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 00 000 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 00000 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 D55471002 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 71002000 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 Note 1: Only rudder P/N D554 71000 010 00 having affected rudder S/N 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). Subject (d) Air Transport Association (ATA) of America Code 55: Stabilizers. Reason (e) The mandatory continuing airworthiness information (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. This AD requires inspections of specific areas and, when necessary, the application of corrective actions for those rudders where production reworks have been identified. Inspections include vacuum loss inspections for de-bonding of the rudders in reinforced areas and other areas (splice/lower rib/upper edge/leading edge/other specified locations), and elasticity laminate checks for de-bonding of the rudders in the trailing edge area and other areas (splice/lower rib/upper edge/leading edge/other specified locations). Corrective actions include contacting Airbus for further instruction and doing the repair. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) For rudders 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 AOT. (1) Within 200 days after the effective date of this AD, perform a vacuum loss inspection on the rudder reinforced area. (2) Within 20 months after the effective date of this AD, 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 effective date of this AD, 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 effective date of this AD, 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) For rudders that do not have a honeycomb core density of 24 kg/m3 (all rudders identified in Table 1 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 AOT. For this AD, "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 200 days after the reference date, perform a vacuum loss inspection on the rudder reinforced area. (2) Within 20 months after thereference 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) 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. (j) 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; e-mail [email protected], [email protected], or [email protected], or AIRTAC (Airbus Technical AOG Center) Customer Services; telephone +33 (0)5 61 93 34 00; fax +33 (0)5 61 93 35 00; e-mail [email protected]. 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; e-mail [email protected]. (1) For any inspection done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) For any inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (k) 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 the effective date of this AD, 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, 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) After the effective date of this AD, no rudder listed in Table 1 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. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (m) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Beforeusing any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Related Information (n) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009-0141, dated July 2, 2009, and the service information identified in Table 2 of this AD, for related information. Table 2--Airbus Service Information Document Revision/Issue Date Airbus All Operators Telex A320-55A1038 Revision 01 June 10, 2009 Airbus All Operators Telex A320-55A1038 Revision 02 September 28, 2009 Airbus Technical Disposition TD/K4/S2/27086/2009 Issue E September 17, 2009 Material Incorporated by Reference (o) You must use the service information contained in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. Table 3--Material Incorporated by Reference Document Revision/Issue Date Airbus All Operators Telex A320-55A1038* Revision 01 June 10, 2009 Airbus All Operators Telex A320-55A1038* Revision 02 September 28, 2009 Airbus Technical Disposition TD/K4/S2/27086/2009 Issue E September 17, 2009 (* The first page of these documents contain the document number, revision level, and date; no other pages contain this information.) (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (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; e-mail: [email protected]; Internet http://www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html..