80 FR 7986 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 30 (February 13, 2015)

Page Range		7986-7989
FR Document		2015-02537
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.
Federal Register, Volume 80 Issue 30 (Friday, February 13, 2015)
[Federal Register Volume 80, Number 30 (Friday, February 13, 2015)]
[Proposed Rules]
[Pages 7986-7989]
From the Federal Register Online  [www.thefederalregister.org]
[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
Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7987

Examining the AD Docket This condition, if not corrected, in case of for compliance with an AD.
a Fan Blade Off event due to high vibration Differentiating these procedures and
You may examine the AD docket on level, could cause in-flight loss of some
the Internet at http:// tests from other tasks in the service
heavy components of the TRU, possibly
www.regulations.gov by searching for information is expected to improve an
resulting in injury to persons on the ground
and locating Docket No. FAA–2015– [or damage to airplane structure or control owner’s/operator’s understanding of
0085; or in person at the Docket surfaces, and consequent reduced crucial AD requirements and help
Management Facility between 9 a.m. controllability of the airplane]. provide consistent judgment in AD
and 5 p.m., Monday through Friday, As current hinge sleeves are not serialized, compliance. The actions specified in
it is not possible to identify the TRU hinge Airbus Service Bulletin A330–78–3021,
except Federal holidays. The AD docket sleeves which did not receive the heat Revision 03, dated October 15, 2014,
contains this proposed AD, the treatment. The part supplier has developed include procedures and tests that are
regulatory evaluation, any comments an identification procedure for these TRU
identified as RC (required for
received, and other information. The hinge sleeves in order to identify the affected
hinge sleeves, and to allow a better part compliance) because these procedures
street address for the Docket Operations
traceability in the future. have a direct effect on detecting,
office (telephone 800–647–5527) is in
For the reason described above, this preventing, resolving, or eliminating an
the ADDRESSES section. Comments will
[EASA] AD requires identification and identified unsafe condition.
be available in the AD docket shortly replacement of the affected TRU hinge As specified in a NOTE under the
after receipt. sleeves. Accomplishment Instructions of Airbus
FOR FURTHER INFORMATION CONTACT: You may examine the MCAI in the Service Bulletin A330–78–3021,
Vladimir Ulyanov, Aerospace Engineer, AD docket on the Internet at http:// Revision 03, dated October 15, 2014,
International Branch, ANM–116, www.regulations.gov by searching for procedures and tests identified as RC
Transport Airplane Directorate, FAA, and locating Docket No. FAA–2015– must be done to comply with the
1601 Lind Avenue SW., Renton, WA 0085. proposed AD. However, procedures and
98057–3356; telephone 425–227–1138; tests that are not identified as RC are
fax 425–227–1149. Related Service Information Under 1
recommended. Those procedures and
SUPPLEMENTARY INFORMATION:
CFR Part 51
tests that are not identified as RC may
Airbus has issued Service Bulletin be deviated from using accepted
Comments Invited A330–78–3021, Revision 03, dated methods in accordance with the
We invite you to send any written October 15, 2014. Aircelle has issued operators’ maintenance or inspection
relevant data, views, or arguments about Service Bulletin 78–AG924, dated program without obtaining approval of
this proposed AD. Send your comments September 26, 2012. This service an alternative method of compliance
to an address listed under the information describes procedures for (AMOC), provided the procedures and
ADDRESSES section. Include ‘‘Docket No. modifying and marking the sleeves for tests identified as RC can be done and
FAA–2015–0085; Directorate Identifier hinges number 3 and number 4 on the the airplane can be put back in a
2014–NM–078–AD’’ at the beginning of cowl doors of Rolls-Royce Trent 700 serviceable condition. Any substitutions
your comments. We specifically invite engines. The actions described in this or changes to procedures or tests
comments on the overall regulatory, service information are intended to identified as RC will require approval of
economic, environmental, and energy correct the unsafe condition identified an AMOC.
aspects of this proposed AD. We will in the MCAI. This service information is
consider all comments received by the reasonably available; see ADDRESSES for Costs of Compliance
closing date and may amend this ways to access this service information. We estimate that this proposed AD
proposed AD based on those comments. affects 24 airplanes of U.S. registry.
FAA’s Determination and Requirements We also estimate that it would take
We will post all comments we
of This Proposed AD about 29 work-hours per product to
receive, without change, to http://
www.regulations.gov, including any This product has been approved by comply with the basic requirements of
personal information you provide. We the aviation authority of another this proposed AD. The average labor
will also post a report summarizing each country, and is approved for operation rate is $85 per work-hour. Required
substantive verbal contact we receive in the United States. Pursuant to our parts would cost about $0 per product.
about this proposed AD. bilateral agreement with the State of Based on these figures, we estimate the
Design Authority, we have been notified cost of this proposed AD on U.S.
Discussion of the unsafe condition described in the operators to be $59,160, or $2,465 per
The European Aviation Safety Agency MCAI and service information product.
(EASA), which is the Technical Agent referenced above. We are proposing this In addition, we estimate that any
for the Member States of the European AD because we evaluated all pertinent necessary follow-on action would take
Union, has issued EASA Airworthiness information and determined an unsafe up to 1 work-hour and require parts
Directive 2014–0062, dated March 11, condition exists and is likely to exist or costing $0, for a cost of $85 per product.
2014 (referred to after this as the develop on other products of the same We have no way of determining the
Mandatory Continuing Airworthiness type design. number of aircraft that might need this
Information, or ‘‘the MCAI’’), to correct action.
Explanation of ‘‘RC’’ Procedures and
an unsafe condition for all Airbus
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS

Tests in Service Information Authority for This Rulemaking
Model A330–243, A330–243F, A330–
341, A330–342, and A330–343 The FAA worked in conjunction with Title 49 of the United States Code
airplanes. The MCAI states: industry, under the Airworthiness specifies the FAA’s authority to issue
Directives Implementation Aviation rules on aviation safety. Subtitle I,
A manufacturing discrepancy (lack of heat
treatment) on a batch of the N°3 and N°4
Rulemaking Committee (AD ARC), to section 106, describes the authority of
hinge sleeves installed on [a] Thrust Reverser enhance the AD system. One the FAA Administrator. ‘‘Subtitle VII:
Unit (TRU) was identified. Those parts are enhancement was a new process for Aviation Programs,’’ describes in more
only installed on A330 aeroplanes equipped annotating which procedures and tests detail the scope of the Agency’s
with Rolls-Royce (RR) Trent 700 engines. in the service information are required authority.

VerDate Sep<11>2014 13:53 Feb 12, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\13FEP1.SGM 13FEP1
7988 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules

We are issuing this rulemaking under (b) Affected ADs information identified in paragraphs (j)(1),
the authority described in ‘‘Subtitle VII, None. (j)(2), or (j)(3) of this AD, which are not
Part A, Subpart III, Section 44701: incorporated by reference in this AD.
(c) Applicability (1) Airbus Service Bulletin A330–78–3021,
General requirements.’’ Under that
This AD applies to all Airbus Model A330– dated October 17, 2012.
section, Congress charges the FAA with (2) Airbus Service Bulletin A330–78–3021,
243, A330–243F, A330–341, A330–342, and
promoting safe flight of civil aircraft in Revision 01, dated July 30, 2013.
A330–343 airplanes, certificated in any
air commerce by prescribing regulations category, all manufacturer serial numbers. (3) Airbus Service Bulletin A330–78–3021,
for practices, methods, and procedures Revision 02, dated April 17, 2014.
the Administrator finds necessary for (d) Subject
(l) Other FAA AD Provisions
safety in air commerce. This regulation Air Transport Association (ATA) of
is within the scope of that authority America Code 78, Exhaust. The following provisions also apply to this
AD:
because it addresses an unsafe condition (e) Reason (1) Alternative Methods of Compliance
that is likely to exist or develop on (AMOCs): The Manager, International
This AD was prompted by reports
products identified in this rulemaking indicating that certain hinge sleeves on the Branch, ANM–116, Transport Airplane
action. cowl doors of the thrust reverser units were Directorate, FAA, has the authority to
Regulatory Findings not heat treated. We are issuing this AD to approve AMOCs for this AD, if requested
prevent, in the event of a fan-blade-off event using the procedures found in 14 CFR 39.19.
We determined that this proposed AD due to high vibration, in-flight loss of thrust In accordance with 14 CFR 39.19, send your
would not have federalism implications reverser unit (TRU) heavy components, request to your principal inspector or local
under Executive Order 13132. This which might damage airplane structure or Flight Standards District Office, as
proposed AD would not have a control surfaces, and consequent reduced appropriate. If sending information directly
substantial direct effect on the States, on controllability of the airplane. to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
the relationship between the national (f) Compliance International Branch, ANM–116, Transport
Government and the States, or on the Comply with this AD within the Airplane Directorate, FAA, 1601 Lind
distribution of power and compliance times specified, unless already Avenue SW., Renton, WA 98057–3356;
responsibilities among the various done. telephone 425–227 1138; fax 425–227–1149.
levels of government. Information may be emailed to: 9–ANM–116–
For the reasons discussed above, I (g) Identification of TRU Part Number
AMOC–REQUESTS@faa.gov. Before using
certify this proposed regulation: Within 12 months after the effective date any approved AMOC, notify your appropriate
1. Is not a ‘‘significant regulatory of this AD: Identify the part number of the principal inspector, or lacking a principal
action’’ under Executive Order 12866; TRUs, in accordance with Aircelle Service inspector, the manager of the local flight
2. Is not a ‘‘significant rule’’ under the Bulletin 78–AG924, dated September 26, standards district office/certificate holding
DOT Regulatory Policies and Procedures 2012. district office. The AMOC approval letter
(44 FR 11034, February 26, 1979); (h) Replacement of Thrust Reverser Unit must specifically reference this AD.
3. Will not affect intrastate aviation in Hinge Sleeves (2) Required for Compliance (RC): Where
Airbus Service Bulletin A330–78–3021,
Alaska; and If the results of the part identification Revision 03, dated October 15, 2014, contains
4. Will not have a significant required by paragraph (g) of this AD reveal procedures or tests that are identified as RC,
economic impact, positive or negative, that the TRUs are affected: Within the those procedures and tests must be done to
on a substantial number of small entities compliance time defined in paragraph (g) of comply with this AD; any procedures and
under the criteria of the Regulatory this AD, replace hinge sleeves numbers 3 and tests that are not identified as RC are
Flexibility Act. 4 of each TRU cowl door, in accordance with recommended. Those procedures and tests
the Accomplishment Instructions of Airbus that are not identified as RC may be deviated
List of Subjects in 14 CFR Part 39 Service Bulletin A330–78–3021, Revision 03, from using accepted methods in accordance
Air transportation, Aircraft, Aviation dated October 15, 2014. with the operators’ maintenance or
safety, Incorporation by reference, Note 1 to paragraph (h) of this AD: Rolls- inspection program without obtaining
Safety. Royce Alert Service Bulletin RB.211–78– approval of an AMOC, provided the
AG924, dated September 26, 2012, is an procedures and tests identified as RC can be
The Proposed Amendment additional source of guidance for replacing done and the airplane can be put back in a
the TRUs. serviceable condition. Any substitutions or
Accordingly, under the authority
changes to procedures or tests identified as
delegated to me by the Administrator, (i) Optional Terminating Action for RC require approval of an AMOC.
the FAA proposes to amend 14 CFR part Paragraphs (g) and (h) of this AD (3) Contacting the Manufacturer: For any
39 as follows: Modifying an airplane by incorporating requirement in this AD to obtain corrective
Airbus Modification 202463 in production actions from a manufacturer, the action must
PART 39—AIRWORTHINESS terminates the requirements specified in be accomplished using a method approved
DIRECTIVES paragraphs (g) and (h) of this AD for that by the Manager, International Branch, ANM–
airplane. 116, Transport Airplane Directorate, FAA; or
■ 1. The authority citation for part 39 the European Aviation Safety Agency
continues to read as follows: (j) Parts Installation Limitations (EASA); or Airbus’s EASA Design
Authority: 49 U.S.C. 106(g), 40113, 44701. As of the effective date of this AD, no Organization Approval (DOA). If approved by
person may install a TRU on any airplane the DOA, the approval must include the
§ 39.13 [Amended] unless it has been determined, using Aircelle DOA-authorized signature.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS

■ 2. The FAA amends § 39.13 by adding Service Bulletin 78–AG924, dated September
26, 2012, that the cowl door hinge sleeves (m) Related Information
the following new airworthiness (1) Refer to Mandatory Continuing
installed on the TRU are not affected by the
directive (AD): requirements of this AD. Airworthiness Information (MCAI) EASA
Airbus: Docket No. FAA–2015–0085; Airworthiness Directive 2014–0062, dated
(k) Credit for Previous Actions March 11, 2014, for related information. This
Directorate Identifier 2014–NM–078–AD.
This paragraph provides credit for the MCAI may be found in the AD docket on the
(a) Comments Due Date actions required by paragraph (h) of this AD Internet at http://www.regulations.gov by
We must receive comments by March 30, if those actions were performed before the searching for and locating Docket No. FAA–
2015. effective date of this AD using the service 2015–0085.

VerDate Sep<11>2014 13:53 Feb 12, 2015 Jkt 235001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\13FEP1.SGM 13FEP1
Document Created: 2015-12-18 13:17:46
Document Modified: 2015-12-18 13:17:46
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by March 30, 2015.
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.
FR Citation		80 FR 7986
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 7986 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 30 (February 13, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
