Daily Rules, Proposed Rules, and Notices of the Federal Government
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
The life limits of the thrust reversers C-Ducts are not addressed by the definition of the structural life limits of Safe Life items as defined in the A330 Airworthiness Limitations Section—ALS Part 1. As a result, these life limits are covered by an Airworthiness Directive (AD).
These life limits are due to unexpected high fatigue loads (measured during certification tests) on the hinges integrated into the 12 o'clock beam, which forms the upper extreme edge of the thrust reverser C-Duct of Rolls Royce Trent 700 engines.
The aim of the [Direction Générale de l'Aviation Civile] (DGAC) France AD F-2001-528 was to mandate the life limits, depending of the modifications applied to the C-Duct.
Revision 1 of the DGAC France AD F-2001-528 deferred the accomplishment threshold of the modification to be applied in-service from 6,000 flight cycles (FC) to 6,500 FC.
Revision 2 of DGAC France AD F-2001-528 [which corresponds to FAA AD 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005)] was issued to update again the accomplishment threshold from 6,500 FC to 7,200 FC.
This [European Aviation Safety Agency (EASA)] AD retains the requirements of DGAC France AD F-2001-528 R2, which is superseded, and adds [certain] life limits.
We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR, 37829, June 25, 2012), or on the determination of the cost to the public.
We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed, except for minor editorial changes. We have determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM (77 FR 37829, June 25, 2012) for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 37829, June 25, 2012).
We estimate that this AD will affect about 17 products of U.S. registry.
We estimate that it will take about 48 work-hours per product to comply with the new 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 $69,360, or $4,080 per product.
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I,
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 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.
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
You may examine the AD docket on the Internet at
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
This airworthiness directive (AD) becomes effective October 23, 2012.
This AD supersedes AD 2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005).
This AD applies to all Airbus Model A330-243, -243F, -341, -342 and -343 airplanes, certificated in any category.
Air Transport Association (ATA) of America Code 78, Engine Exhaust.
This AD was prompted by new life limits on certain thrust reverser C-duct assemblies. We are issuing this AD to prevent fatigue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which could result in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the applicable compliance time specified in table 1 to paragraph (g) of this AD: Remove the applicable C-duct assemblies of the left- and right-hand thrust reversers, in accordance with 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). Thereafter, for any C-duct assembly of the left- and right-hand thrust reversers installed after the effective date of this AD, before the accumulation of the applicable total flight cycles specified in table 1 to paragraph (g) of this AD: Remove the C-duct assembly, in accordance with a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
The following provisions also apply to this AD:
Refer to MCAI EASA Airworthiness Directive 2011-0018, dated February 3, 2011; for related information.