
[Federal Register Volume 80, Number 170 (Wednesday, September 2, 2015)]
[Rules and Regulations]
[Pages 52935-52937]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21475]



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  Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / 
Rules and Regulations  

[[Page 52935]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0085; Directorate Identifier 2014-NM-078-AD; 
Amendment 39-18255; AD 2015-17-22]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-243, A330-243F, A330-341, A330-342, and A330-343 
airplanes. This 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 AD requires replacing the sleeves of 
certain hinges on the cowl doors of the TRUs with new parts. We are 
issuing 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 consequently reduce 
controllability of the airplane.

DATES: This AD becomes effective October 7, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 7, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0085 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For Airbus 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 airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. For Aircelle service information identified in this AD, 
contact Aircelle Customer support Center, BP 50042, 50, rue Pierre 
Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; fax 
+33 (0)1 64 14 84 10. 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0085.

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 by adding an AD that would apply to all Airbus Model A330-243, 
A330-243F, A330-341, A330-342, and A330-343 airplanes. The NPRM 
published in the Federal Register on February 13, 2015 (80 FR 7986).
    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/#!documentDetail;D=FAA-2015-0085-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 7986, February 13, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this 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 (80 FR 7986, February 13, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 7986, February 13, 2015).

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. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this AD.

[[Page 52936]]

Costs of Compliance

    We estimate that this AD affects 24 airplanes of U.S. registry.
    We also estimate that it will take about 29 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $0 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $59,160, or $2,465 per product.
    In addition, we estimate that any necessary follow-on action will 
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.
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-015-0085; 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 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.

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 adding the following new airworthiness 
directive (AD):

2015-17-22 Airbus: Amendment 39-18255. Docket No. FAA-2015-0085; 
Directorate Identifier 2014-NM-078-AD.

(a) Effective Date

    This AD becomes effective October 7, 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 (TRUs) 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 TRU 
heavy components, which might damage airplane structure or control 
surfaces and consequently reduce 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 the information in 
Aircelle Service Bulletin 78-AG924, dated September 26, 2012.

(h) Replacement of TRU 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 and is not incorporated by 
reference in this AD.

(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 Limitation

    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 (k)(1), (k)(2), or (k)(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: 9-ANM-116-

[[Page 52937]]

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) 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.
    (3) 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 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/#!documentDetail;D=FAA-2015-0085-0002.
    (2) Airbus service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(5) of this AD.
    (3) Rolls-Royce service information identified in this AD that 
is not incorporated by reference is available at Rolls-Royce plc, 
P.O. Box 31, Derby, DE24 8BJ, England; phone: 011-44-1332-242424; 
fax: 011-244-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-78-3021, Revision 03, dated 
October 15, 2014.
    (ii) Aircelle Service Bulletin 78-AG924, dated September 26, 
2012.
    (3) For Airbus 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 airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) For Aircelle service information identified in this AD, 
contact Aircelle Customer support Center, BP 50042, 50, rue Pierre 
Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; 
fax +33 (0)1 64 14 84 10.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 21, 2015.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-21475 Filed 9-1-15; 8:45 am]
BILLING CODE 4910-13-P


