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[Federal Register Volume 77, Number 181 (Tuesday, September 18, 2012)]
[Rules and Regulations]
[Pages 57484-57486]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-22954]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0671; Directorate Identifier 2011-NM-096-AD; 
Amendment 39-17197; AD 2012-19-02]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Airbus Model A330-243, -341, -342 and -343 airplanes. That AD 
currently requires modifying certain cowl assemblies of the left- and 
right-hand thrust reversers. This new AD requires removing certain C-
duct assemblies of the left- and right-hand thrust reversers from 
service at certain designated life limits, and also adds airplanes to 
the applicability. 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.

DATES: This AD becomes effective October 23, 2012.

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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1138; 
fax (425) 227-1149.

SUPPLEMENTARY 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 June 25, 2012 (77 FR 
37829), and proposed to supersede AD 2005-25-21, Amendment 39-14414 (70 
FR 73919, December 14, 2005). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    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 G[eacute]n[eacute]rale 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.

The action required in this AD is removing certain C-duct assemblies of 
the left- and right-hand thrust reversers from service at certain 
designated life limits. This AD also adds Model A330-243F airplanes to 
the applicability, and revises the applicability to include all 
airplanes of the affected models. The unsafe condition is 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 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 received no comments on the NPRM (77 FR, 37829, June 25, 
2012), or on the determination of the cost to the public.

Conclusion

    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).

Costs of Compliance

    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.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I,

[[Page 57485]]

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 that 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);
    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.

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 (77 FR 37829, June 25, 2012), 
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.

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

0
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]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2005-25-21, Amendment 39-14414 (70 FR 73919, December 14, 2005), and 
adding the following new AD:

2012-19-02 Airbus: Amendment 39-17197. Docket No. FAA-2012-0671; 
Directorate Identifier 2011-NM-096-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective October 23, 
2012.

(b) Affected ADs

    This AD supersedes AD 2005-25-21, Amendment 39-14414 (70 FR 
73919, December 14, 2005).

(c) Applicability

    This AD applies to all Airbus Model A330-243, -243F, -341, -342 
and -343 airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
Exhaust.

(e) Reason

    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.

(f) Compliance

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

(g) C-duct Assembly Removal

    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).

      Table 1 to Paragraph (g) of This AD--Part Removal Thresholds
------------------------------------------------------------------------
 
------------------------------------------------------------------------
Part No.--                    Compliance times at the later of the times
                               specified--
------------------------------------------------------------------------
HDTR3410L, HDTR3410R,         Before the            Within 3 months
 HDTR3411L, HDTR3411R,         accumulation of       after the effective
 HDTR3412R, HDTR3413R.         10,000 total flight   date of this AD.
                               cycles since the
                               first installation
                               of C[dash]duct on
                               the airplane.
HDTR3414L, HDTR3416R,         Before the            Within 3 months
 HDTR3417R that have been      accumulation of       after the effective
 modified in service as        10,000 total flight   date of this AD.
 specified in Airbus           cycles since the
 Mandatory Service Bulletin    first installation
 A330[dash]78[dash]3010 or     of C[dash]duct on
 Rolls-Royce Service           the airplane.
 Bulletin RB.211-78-C899 at
 7,200 total flight cycles
 or more since first
 installation on an airplane.
HDTR3414L, HDTR3416R,         Before the            Within 3 months
 HDTR3417R that have been      accumulation of       after the effective
 modified in production by     25,000 total flight   date of this AD.
 Airbus Modification 47316     cycles since the
 or that have been modified    first installation
 in service as specified in    of C[dash]duct on
 Airbus Mandatory Service      the airplane.
 Bulletin
 A330[dash]78[dash]3010 or
 Rolls-Royce Service
 Bulletin RB.211-78-C899,
 before the accumulation of
 7,200 total flight cycles
 since first installation on
 an airplane.

[[Page 57486]]

 
HDTR3412L, HDTR3416L,         Before the            Within 3 months
 HDTR3417L, HDTR3414R,         accumulation of       after the effective
 HDTR3419R, HDTR3420R.         25,000 total flight   date of this AD.
                               cycles since the
                               first installation
                               of C[dash]duct on
                               the airplane.
HDTR3413L, HDTR3415R,         Before the            Within 3 months
 HDTR3415L, HDTR3418R.         accumulation of       after the effective
                               40,000 total flight   date of this AD.
                               cycles since the
                               C[dash]duct was new.
------------------------------------------------------------------------

(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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, WA 98057-3356; telephone (425) 227-
1138; fax (425) 227-1149. Information may be emailed 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.

(i) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0018, dated 
February 3, 2011; for related information.

(j) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on September 6, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-22954 Filed 9-17-12; 8:45 am]
BILLING CODE 4910-13-P
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