Airworthiness Directives; Airbus Model A330-201, -202, -203, -223, and -243 Airplanes, A330-300 Series Airplanes, A340-200 Series Airplanes, and A340-300 Series Airplanes

2. The FAA amends § 39.13 by adding the following new AD:

Airbus: Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-222-AD.

Comments Due Date

(a) We must receive comments by June 17, 2011.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category, all manufacturer serial numbers, if equipped with rudders having part numbers and serial numbers as identified in table 1, table 2, or table 3 of this AD.

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 * * * [an] in-service aeroplane during scheduled maintenance.

Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the surface 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.

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.

Inspections

(g) For rudders identified in table 1 and table 2 of this AD, within the compliance time in paragraph (g)(1) or (g)(2) of this AD as applicable, do a vacuum loss inspection on the rudder non-ventilated area (Area 1) for damage including de-bonding between the skin and honeycomb core of the rudder, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable.

(1) For rudders identified in table 1 of this AD: Within 1,800 flight hours after the effective date of this AD.

(2) For rudders identified in table 2 of this AD: Within 21 months after the effective date of this AD.

(h) For rudders identified in table 1 and table 2 of this AD, within 21 months after the effective date of this AD, do an elasticity laminate checker inspection on the trailing edge area (Area 2) for damage including de-bonding between the skin and honeycomb core of the rudder, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable. Thereafter, repeat the inspection two more times at intervals not to exceed 4,500 flight cycles but not less than 4,000 flight cycles from the most recent inspection.

(i) For rudders identified in table 3 of this AD, within 4,500 flight cycles but not less than 4,000 flight cycles from the date of the sampling inspection identified in table 4 of this AD, or within 30 days after the effective date of this AD, whichever occurs later, do an elasticity laminate checker inspection on the trailing edge area for damage including de-bonding between the skin and honeycomb core of the rudder, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable. Repeat the inspection once within 4,500 flight cycles after doing the inspection but not less than 4,000 flight cycles from the last inspection.

Corrective Actions

(j) If damage is found during any inspection required by paragraph (g), (h), (i), or (k)(1) of this AD, before further flight, repair the damage 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).

Restoration

(k) If no damage is found during any inspection required by paragraph (g) of this AD, before further flight, restore the vacuum loss holes by doing a temporary restoration with self-adhesive disks or tapes, a temporary restoration with resin, or a permanent restoration with resin, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable. Do the applicable actions specified in paragraph (k)(1) or (k)(2) of this AD.

(1) For airplanes on which a temporary restoration with self-adhesive disks or tapes is done, within 900 flight hours after doing the restoration, do a detailed inspection for loose or missing self-adhesive disks or tapes and repeat the inspection thereafter at intervals not to exceed 900 flight hours until the permanent restoration is done, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable. If any loose or missing self-adhesive disks or tapes are found during any inspection required by this AD, before further flight, close the holes, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable. Do the permanent restoration within 21 months after doing the temporary restoration, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable.

(2) For airplanes on which a temporary restoration with resin is done: Within 21 months after doing the temporary restoration, do the permanent restoration, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both dated April 22, 2010, as applicable.

Reporting Requirements

(l) Submit a report of the findings (positive and negative) of the first inspection required by paragraphs (g), (h), and (i) of this AD to Airbus, at the applicable time specified in paragraph (l)(1) or (l)(2) of this AD. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane.

(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

Parts Installation

(m) As of the effective date of this AD, no person may install any affected rudder listed in table 1, table, 2, or table 3 of this AD, on any airplane, unless the rudder is inspected as specified in paragraphs (g), (h), and (i) of this AD, as applicable, and all applicable corrective actions specified in paragraph (j) of this AD and applicable restoration specified in paragraph (k) of this AD are done.

FAA AD Differences

Note 1:

This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(n) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to Attn: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. Information may be e-mailed 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.

Related Information

(o) Refer to MCAI EASA Airworthiness Directive 2010-0127, dated June 23, 2010; Airbus Mandatory Service Bulletin A330-55-3042, dated April 22, 2010; and Airbus Mandatory Service Bulletin A340-55-4038, dated April 22, 2010; for related information.

Issued in Renton, Washington, on April 20, 2011.

Kalene C. Yanamura,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011-10624 Filed 5-2-11; 8:45 am]

BILLING CODE 4910-13-P