Federal Aviation Administration (FAA), Department of Transportation (DOT).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B2 and B4 series airplanes. This AD requires modifying the wiring of the autopilot pitch torque limiter switch. This AD is prompted by several reports of pitch trim disconnect caused by insufficient length in the wiring to the pitch torque limiter lever. We are issuing this AD to prevent possible trim loss when the flightcrew tries to override the autopilot pitch control, which could result in uncontrolled flight of the airplane.
This AD becomes effective August 1, 2005.
The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of August 1, 2005.
For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Washington, DC. This docket number is FAA-2005-20861; the directorate identifier for this docket is 2005-NM-020-A D.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Rosanne Ryburn, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2139; fax (425) 227-1149.End Further Info End Preamble Start Supplemental Information
The FAA proposed to amend 14 CFR part 39 with an AD for certain Airbus Model A300 B2 and B4 series airplanes. That action, published in the Federal Register on April 6, 2005 (70 FR 17347), proposed to require modifying the wiring of the autopilot pitch torque limiter switch.
We provided the public the opportunity to participate in the development of this AD. We have considered the one comment that has been submitted on the proposed AD.
Support for the Proposed AD
The commenter supports the proposed AD.
Change to This AD
We have updated reference to Airbus Model A300 B2 and B4 series airplanes in paragraph (c) of this AD to match the common model designation identified in the latest revision of the type certificate data sheet.
We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
This AD affects about 20 airplanes of U.S. registry. The actions take between 8 and 11 work hours per airplane, depending on airplane configuration, at an average labor rate of $65 per work hour. Required parts cost between $1,840 and $4,280 per airplane, depending on airplane configuration. Based on these figures, the estimated cost of the AD for U.S. operators is between $47,200 and $99,900, or between $2,360 and $4,995 per airplane.
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.
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. See the ADDRESSES section for a location to examine the regulatory evaluation.Start List of Subjects
List of Subjects in 14 CFR Part 39
- Air transportation
- Aviation safety
- Incorporation by reference
Adoption of the AmendmentStart Amendment Part
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:End Amendment Part Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):End Amendment Part
2005-13-33 Airbus: Amendment 39-14170. Docket No. FAA-2005-20861; Directorate Identifier 2005-NM-020-AD.
(a) This AD becomes effective August 1, 2005.
(c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; and Model A300 B4-2C, B4-103, and B4-203 airplanes; certificated in any category; as identified in Airbus Service Bulletin A300-22-0117, dated September 7, 2004.
(d) This AD was prompted by several reports of pitch trim disconnect caused by insufficient length in the wiring to the pitch torque limiter lever. We are issuing this AD to prevent possible trim loss when the flightcrew tries to override the autopilot pitch control, which could result in uncontrolled flight of the airplane.
(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.
(f) Within 20 months after the effective date of this AD, modify the wiring of the autopilot pitch torque limiter switch, by doing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300-22-0117, dated September 7, 2004.
Alternative Methods of Compliance (AMOCs)
(g) 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.
Material Incorporated by Reference
(h) You must use Airbus Service Bulletin A300-22-0117, dated September 7, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC. To review copies of the service information, go to 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.Start Signature
Issued in Renton, Washington, on June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 05-12505 Filed 6-24-05; 8:45 am]
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