AD 2006-10-11

The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-200 and -300 series airplanes. This AD requires repetitive inspections for cracking of the flap transmission shafts, and replacing the transmission shafts if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of longitudinal cracks due to stress corrosion in the transmission shafts between the power control unit (PCU) and the torque limiters of the flap transmission system. We are issuing this AD to detect and correct cracking of the flap transmission shaft, which could compromise shaft structural integrity and lead to a disabled flap transmission shaft and reduced controllability of the airplane.

Final rule.

2006-10-11 Airbus: Amendment 39-14595. FAA-2006-24104; Directorate Identifier 2005-NM-231-AD.

Effective Date

(a) This AD becomes effective June 20, 2006.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category; except for airplanes on which Airbus Modification 12247 has been embodied in production.

Unsafe Condition

(d) This AD results from reports of longitudinal cracks due to stress corrosion in the transmission shafts between the power control unit (PCU) and the torque limiters of the flap transmission system. We are issuing this AD to detect and correct cracking of the flap transmission shaft, which could compromise shaft structural integrity and lead to a disabled flap transmission shaft and reduced controllability of the airplane.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Inspection and Corrective Action

(f) At the earlier of the compliance times specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection for stress corrosion cracking of the flight transmission shafts located between the PCU and the torque limiters in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27- 2092, Revision 02, dated April 11, 2005. Thereafter, repeat the inspections as required by paragraph (g) of this AD. Before further flight, replace any cracked transmission shaft discovered during any inspection required by this AD with a new or reconditioned shaft, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000.

(1) Within 2,000 flight hours after the last flap asymmetry protection test performed in accordance with Airbus A310 Maintenance Planning Document (MPD) Task 275600-01-1.(2) Within 8,000 flight cycles after the last flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1 or 800 flight cycles after the effective date of this AD, whichever comes later.

Note 1: Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27- 624, Revision 1, dated August 18, 2000, as an additional source of service information for accomplishing the inspections.

Note 2: Airbus Service Bulletin A310-27-2092, Revision 02, refers to Airbus Service Bulletin A310-27-2095, dated March 29, 2000, as a source of service information for replacing the flap transmission shafts.

Note 3: Airbus Service Bulletin A310-27-2095 refers to Lucas Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000, as an additional source of service information for replacing the flap transmission shafts.

Repetitive Inspections

(g) Repeat the inspection required by paragraph (f)of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.

(1) Before further flight after any occurrence of jamming of the flap transmission system.

(2) At intervals not to exceed 2,000 flight hours after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-01-1.

(3) At intervals not to exceed 8,000 flight cycles after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1.

Optional Terminating Action

(h) Replacing any flap transmission shaft with a new or reconditioned transmission shaft in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000, ends the inspections required for that transmission shaft only.

Actions Performed Using Previously Issued Service Information

(i) Actions performed in accordance with Airbus Service Bulletin A310-27-2092, dated April 9, 1999; or Revision 01, dated December 11, 2001, are considered acceptable for compliance with the corresponding requirements of this AD.

No Reporting

(j) Although Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

Related Information

(l) French airworthiness directive F-2005-174, dated October 26, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

(m) You must use Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005; and Airbus Service Bulletin A310-27-2095, dated March 29, 2000; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for copies of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .

Examining the Docket

You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A310-200 and -300 series airplanes. That NPRM was published in the Federal Register on March 9, 2006 (71 FR 12152). That NPRM proposed to require repetitive inspections for cracking of the flap transmission shafts, and replacing the transmission shafts if necessary. The NPRM also proposed to provide an optional terminating action for the repetitive inspections.

Comments

We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Change to NPRM

We inadvertently deleted reference to the reporting requirement stated in the Direction G n rale de l'Aviation Civile (DGAC) Airworthiness Directive and the Airbus service bulletin. This AD does not require reporting the results of the inspection to Airbus, which is a difference among the DGAC Airworthiness Directive, the service bulletin, and this AD. We have added our non-requirement as paragraph (j) of this AD and reidentified subsequent paragraphs accordingly.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

ThisAD will affect about 59 airplanes of U.S. registry. The required inspections will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $3,835, or $65 per airplane, per inspection cycle.

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 have 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 that this AD:

(1) Is not a "significant regulatory action" under Executive Order 12866;

(2) Is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

(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. See the ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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.

Sec. 39.13 [Amended]

2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by adding the following new airworthiness directive (AD):