-
Start Preamble
AGENCY:
Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION:
Final rule.
SUMMARY:
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
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.
* * * * *We are issuing this AD to require actions to correct the unsafe condition on these products.
DATES:
This AD becomes effective December 10, 2010.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 10, 2010.
ADDRESSES:
You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
Start Further InfoFOR FURTHER INFORMATION CONTACT:
Tim Dulin, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, Start Printed Page 681821601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149.
End Further Info End Preamble Start Supplemental InformationSUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 2, 2010 (75 FR 16689). That NPRM proposed 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.
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.
You may obtain further information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing this AD. We considered the comment received.
Request To Clarify Additional Work in Paragraph (k) of the Proposed AD
Airbus requested that we clarify in paragraph (k) of the proposed AD that there is additional work for operators to comply with, i.e., in Airbus All Operators Telex (AOT) A320-55A1038, Revision 02, dated September 28, 2009. Airbus explained that there is an additional ultrasonic inspection for rudders on which a temporary vacuum loss hole restoration with resin or a permanent vacuum loss hole restoration has been performed previously in the reinforced area.
We agree that additional work is included in Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009, which is referenced in the NPRM as the appropriate source of service information. However, the additional work specified in Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009, is not required by this final rule. Therefore, we have revised paragraphs (g) and (h) of the final rule to allow operators to perform the required actions of this AD in accordance with Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009; or Revision 02, dated September 28, 2009. Also, we have revised paragraph (k) of this AD by removing reference to Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009, to clarify that only the additional areas specified in Airbus AOT A320-55A1038, Revision 01, dated June 10, 2009, must be inspected. We might consider further rulemaking to address the additional work specified in Airbus AOT A320-55A1038, Revision 02, dated September 28, 2009.
Request To Include Alternative Contact Address for Positive Findings
Airbus requested that we include the Airbus Technical Aircraft on Ground (AOG) Center (AIRTAC) as a contact to report positive findings from the inspections in paragraphs (g) and (h) of the NPRM.
We agree to include the AIRTAC as a contact and have revised paragraph (j) of the final rule accordingly.
Clarification of Paragraph (l) of This AD
We have clarified the statement “unless the rudder is in compliance with this AD” in paragraph (l) of this AD by specifying that applicable inspections in paragraphs (g) or (h) of this AD must be done and applicable actions in paragraph (i) of this AD must be done.
Conclusion
We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.
We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 155 products of U.S. registry. We also estimate that it will take about 11 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $144,925, or $935 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in “Subtitle VII, Part A, Subpart III, Section 44701: General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a “significant regulatory action” under Executive Order 12866;
2. Is not a “significant rule” under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); andStart Printed Page 68183
3. 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 AD and placed it in the AD docket.
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 the NPRM, 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.
Start List of SubjectsList of Subjects in 14 CFR Part 39
- Air transportation
- Aircraft
- Aviation safety
- Incorporation by reference
- Safety
Adoption of the Amendment
Start Amendment PartAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
End Amendment Part Start PartPART 39—AIRWORTHINESS DIRECTIVES
End Part Start Amendment Part1. The authority citation for part 39 continues to read as follows:
End Amendment PartStart Amendment Part[Amended]2. The FAA amends § 39.13 by adding the following new AD:
End Amendment Part2010-23-07 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 71000 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 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-Z072 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 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 Start Printed Page 68184 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 11002 000 00 0003 TS-2971 D554 71002 000 00 0003 TS-2987 D554 11004 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 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) 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 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; e-mail 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; e-mail nicolas.seynaeve@airbus.com.
(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 Start Printed Page 68185Branch, 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. Before using 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: account.airworth-eas@airbus.com; 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.
.Start SignatureEnd Signature End Supplemental InformationIssued in Renton, Washington, on October 26, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010-27614 Filed 11-4-10; 8:45 am]
BILLING CODE 4910-13-P
Document Information
- Comments Received:
- 0 Comments
- Effective Date:
- 12/10/2010
- Published:
- 11/05/2010
- Department:
- Federal Aviation Administration
- Entry Type:
- Rule
- Action:
- Final rule.
- Document Number:
- 2010-27614
- Dates:
- This AD becomes effective December 10, 2010.
- Pages:
- 68181-68185 (5 pages)
- Docket Numbers:
- Docket No. FAA-2010-0279, Directorate Identifier 2009-NM-148-AD, Amendment 39-16496, AD 2010-23-07
- RINs:
- 2120-AA64: Airworthiness Directives
- RIN Links:
- https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
- Topics:
- Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety
- PDF File:
- 2010-27614.pdf
- CFR: (1)
- 14 CFR 39.13