[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)]
[Proposed Rules]
[Pages 7986-7989]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-02537]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0085; Directorate Identifier 2014-NM-078-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-243, A330-243F, A330-341, A330-342, and A330-343 
airplanes. This proposed AD was prompted by reports indicating that 
certain hinge sleeves on the cowl doors of the thrust reverser units 
(TRUs) were not heat treated. This proposed AD would require replacing 
the sleeves of certain hinges on the cowl doors of the TRUs with new 
parts. We are proposing this AD to prevent, in the event of a fan-
blade-off event due to high vibration, in-flight loss of TRU heavy 
components, which might damage airplane structure or control surfaces, 
and consequent reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by March 30, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

[[Page 7987]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0085; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, 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.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0085; 
Directorate Identifier 2014-NM-078-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0062, dated March 11, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-243, A330-243F, A330-341, A330-342, and A330-343 airplanes. The 
MCAI states:

    A manufacturing discrepancy (lack of heat treatment) on a batch 
of the N[deg]3 and N[deg]4 hinge sleeves installed on [a] Thrust 
Reverser Unit (TRU) was identified. Those parts are only installed 
on A330 aeroplanes equipped with Rolls-Royce (RR) Trent 700 engines.
    This condition, if not corrected, in case of a Fan Blade Off 
event due to high vibration level, could cause in-flight loss of 
some heavy components of the TRU, possibly resulting in injury to 
persons on the ground [or damage to airplane structure or control 
surfaces, and consequent reduced controllability of the airplane].
    As current hinge sleeves are not serialized, it is not possible 
to identify the TRU hinge sleeves which did not receive the heat 
treatment. The part supplier has developed an identification 
procedure for these TRU hinge sleeves in order to identify the 
affected hinge sleeves, and to allow a better part traceability in 
the future.
    For the reason described above, this [EASA] AD requires 
identification and replacement of the affected TRU hinge sleeves.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0085.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-78-3021, Revision 03, dated 
October 15, 2014. Aircelle has issued Service Bulletin 78-AG924, dated 
September 26, 2012. This service information describes procedures for 
modifying and marking the sleeves for hinges number 3 and number 4 on 
the cowl doors of Rolls-Royce Trent 700 engines. The actions described 
in this service information are intended to correct the unsafe 
condition identified in the MCAI. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement was a new process 
for annotating which procedures and tests in the service information 
are required for compliance with an AD. Differentiating these 
procedures and tests from other tasks in the service information is 
expected to improve an owner's/operator's understanding of crucial AD 
requirements and help provide consistent judgment in AD compliance. The 
actions specified in Airbus Service Bulletin A330-78-3021, Revision 03, 
dated October 15, 2014, include procedures and tests that are 
identified as RC (required for compliance) because these procedures 
have a direct effect on detecting, preventing, resolving, or 
eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of 
Airbus Service Bulletin A330-78-3021, Revision 03, dated October 15, 
2014, procedures and tests identified as RC must be done to comply with 
the proposed AD. However, procedures and tests that are not identified 
as RC are recommended. Those procedures and tests that are not 
identified as RC may be deviated from using accepted methods in 
accordance with the operators' maintenance or inspection program 
without obtaining approval of an alternative method of compliance 
(AMOC), provided the procedures and tests identified as RC can be done 
and the airplane can be put back in a serviceable condition. Any 
substitutions or changes to procedures or tests identified as RC will 
require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 24 airplanes of U.S. 
registry.
    We also estimate that it would take about 29 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $59,160, or $2,465 per product.
    In addition, we estimate that any necessary follow-on action would 
take up to 1 work-hour and require parts costing $0, for a cost of $85 
per product. We have no way of determining the number of aircraft that 
might need this action.

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.

[[Page 7988]]

    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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-0085; Directorate Identifier 2014-NM-
078-AD.

(a) Comments Due Date

    We must receive comments by March 30, 2015.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Subject

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

(e) Reason

    This AD was prompted by reports indicating that certain hinge 
sleeves on the cowl doors of the thrust reverser units were not heat 
treated. We are issuing this AD to prevent, in the event of a fan-
blade-off event due to high vibration, in-flight loss of thrust 
reverser unit (TRU) heavy components, which might damage airplane 
structure or control surfaces, and consequent reduced 
controllability of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Identification of TRU Part Number

    Within 12 months after the effective date of this AD: Identify 
the part number of the TRUs, in accordance with Aircelle Service 
Bulletin 78-AG924, dated September 26, 2012.

(h) Replacement of Thrust Reverser Unit Hinge Sleeves

    If the results of the part identification required by paragraph 
(g) of this AD reveal that the TRUs are affected: Within the 
compliance time defined in paragraph (g) of this AD, replace hinge 
sleeves numbers 3 and 4 of each TRU cowl door, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-78-
3021, Revision 03, dated October 15, 2014.

    Note 1 to paragraph (h) of this AD: Rolls-Royce Alert Service 
Bulletin RB.211-78-AG924, dated September 26, 2012, is an additional 
source of guidance for replacing the TRUs.

(i) Optional Terminating Action for Paragraphs (g) and (h) of this AD

    Modifying an airplane by incorporating Airbus Modification 
202463 in production terminates the requirements specified in 
paragraphs (g) and (h) of this AD for that airplane.

(j) Parts Installation Limitations

    As of the effective date of this AD, no person may install a TRU 
on any airplane unless it has been determined, using Aircelle 
Service Bulletin 78-AG924, dated September 26, 2012, that the cowl 
door hinge sleeves installed on the TRU are not affected by the 
requirements of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (h) of this AD if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraphs (j)(1), (j)(2), or (j)(3) of this AD, which are not 
incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-78-3021, dated October 17, 
2012.
    (2) Airbus Service Bulletin A330-78-3021, Revision 01, dated 
July 30, 2013.
    (3) Airbus Service Bulletin A330-78-3021, Revision 02, dated 
April 17, 2014.

(l) Other FAA AD Provisions

    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, 
WA 98057-3356; telephone 425-227 1138; fax 425-227-1149. Information 
may be emailed to: [email protected]. 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) Required for Compliance (RC): Where Airbus Service Bulletin 
A330-78-3021, Revision 03, dated October 15, 2014, contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures and tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operators' maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in a serviceable condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.
    (3) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0062, dated March 11, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-0085.

[[Page 7989]]

    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on January 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02537 Filed 2-12-15; 8:45 am]
BILLING CODE 4910-13-P