AD 2014-11-04

[Federal Register Volume 79, Number 111 (Tuesday, June 10, 2014)]
[Rules and Regulations]
[Pages 33045-33048]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-12444]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1031; Directorate Identifier 2013-NM-155-AD; 
Amendment 39-17854; AD 2014-11-04]
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 adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Model A340-200, A340-300, A340-500, and A340-600 series 
airplanes. This AD was prompted by a non-connection of the constant 
speed motor/generator (CSM/G) during a final assembly operational test. 
This AD requires a detailed inspection of the connector wires for 
connector 1XE-A of the generator control unit (GCU)-CSM/

[[Page 33046]]

G for discrepancies (evidence of arcing or overheating damage), and 
related investigative and corrective actions if necessary. We are 
issuing this AD to detect and correct incorrect locking of contacts 
into connector 1XE-A of the GCU-CSM/G, which could result in a loss of 
contact continuity and lead to the CSM/G not operating, which, in 
conjunction with an emergency electrical configuration loss of the main 
electrical system or total engine flameout, could adversely affect the 
airplane's safe flight.

DATES: This AD becomes effective July 15, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publications listed in this AD as of July 15, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-1031; 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 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 <a href="/cdn-cgi/l/email-protection#1a7b73686d75686e7273747f6969345b29292a375b292e2a5a7b7368786f6934797577"><span class="__cf_email__" data-cfemail="dcbdb5aeabb3aea8b4b5b2b9afaff29defefecf19defe8ec9cbdb5aebea9aff2bfb3b1">[email&#160;protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 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.

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 certain Airbus Model A330-
200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-
200, A340-300, A340-500, and A340-600 series airplanes. The NPRM 
published in the Federal Register on December 26, 2013 (78 FR 78294).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0175, dated August 2, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During Final Assembly Line tests on an A330 aeroplane, the 
Generator Control Unit--Constant Speed Motor/Generator (GCU-CSM/G) 
failed the operational test.
    Investigations revealed that it is due to incorrect locking of 
some contacts (pins) into the GCU-CSM/G connector 1XE-A. An 
inspection of other aeroplanes confirmed this production quality 
issue. Among the 26 pins used in GCU-CSM/G connector 1XE-A, 6 pins 
have been identified as potentially affected by this issue.
    A badly locked contact could result in a loss of continuity 
[non-connection] and lead to the non-operation of the CSM/G.
    This condition, if not detected and corrected, and in 
conjunction with either an emergency electrical configuration loss 
of main electrical system or total engine flame out, could 
jeopardize the aeroplane's safe flight.
    To address this condition, Airbus developed Alert Operator 
Transmission (AOT) A24L001-13, to provide instructions for a one-
time inspection.
    For the reasons described above, this AD requires a one-time 
[detailed] inspection of the potentially affected connector wires of 
GCU-CSM/G connector 1XE-A and, depending on [the] finding, 
accomplishment of [a related investigative action] and applicable 
corrective actions.

    You may examine the MCAI in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-1031-0002.

Revised Service Information

    Since the NPRM (78 FR 78294, December 26, 2013) was published, we 
have received Airbus Alert Operators Transmission A24L001-13, Revision 
01, dated March 6, 2014. We have determined that this service 
information does not add any additional actions to those proposed in 
the NPRM, therefore, we have revised paragraph (g) of this AD to refer 
to that service information. We have also added a new paragraph (h) to 
this AD to provide credit for actions performed before the effective 
date of this AD using Airbus Alert Operators Transmission A24L001-13, 
dated July 25, 2013, and redesignated the subsequent paragraphs 
accordingly. Additionally, we have added paragraph (k), Material 
Incorporated by Reference, to the end of this AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (78 FR 
78294, December 26, 2013) and the FAA's response to that comment.

Request To Clarify What Prompted the NPRM (78 FR 78294, December 26, 
2013)

    Airbus requested clarification in the SUMMARY section and paragraph 
(e) of the NPRM (78 FR 78294, December 26, 2013). Airbus stated that it 
was not ``failure of the generator control unit-constant speed motor/
generator during a final assembly operational test'' that caused the 
unsafe condition, but a non-connection of the CSM/G during an 
operational test in the final assembly line. Investigations revealed an 
incorrect locking of some contacts into connector 1XE-A of the GCU-CSM/
G.
    We agree to revise the SUMMARY section and paragraph (e) of this 
final rule to state that this AD was prompted by a non-connection of 
the CSM/G during a final assembly operational test.

Changes to This Final Rule

    Paragraphs (g)(1) and (g)(2) in the NPRM (78 FR 78294, December 26, 
2013) have been combined into paragraph (g) in this final rule.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (78 FR 78294, December 26, 2013) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 78294, December 26, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 76 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour 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 $6,460, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 1 work-hour and require parts costing up to $17,314, for a 
cost of up

[[Page 33047]]

to $17,399 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 <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2013-1031; 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):

2014-11-04 Airbus: Amendment 39-17854. Docket No. FAA-2013-1031; 
Directorate Identifier 2013-NM-155-AD.

(a) Effective Date

    This AD becomes effective July 15, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, -
343 airplanes; and A340-211, -212, -213, -311, -312, -313, -541, and 
-642 airplanes; certificated in any category; manufacturer serial 
numbers (MSNs) 1 through 1391 inclusive, except MSNs 0925 and 1382.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power.

(e) Reason

    This AD was prompted by a non-connection of the constant speed 
motor/generator (CSM/G) during a final assembly operational test. We 
are issuing this AD to detect and correct incorrect locking of 
contacts into connector 1XE-A of the generator control unit (GCU)-
CSM/G, which could result in a loss of contact continuity and lead 
to the CSM/G not operating, which, in conjunction with an emergency 
electrical configuration loss of the main electrical system or total 
engine flameout, could adversely affect the airplane's safe flight.

(f) Compliance

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

(g) Inspections and Corrective Actions

    Within 1,000 flight hours after the effective date of this AD: 
Do a detailed inspection for discrepancies (proper engagement and 
evidence of arcing or overheating) of the affected connector wires 
of connector 1XE-A of the GCU-CSM/G, in accordance with Airbus Alert 
Operators Transmission A24L001-13, Revision 01, dated March 6, 2014. 
If any discrepancy is detected during the inspection, before further 
flight, do all applicable related investigative and corrective 
actions, in accordance with Airbus Alert Operators Transmission 
A24L001-13, Revision 01, dated March 6, 2014.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Alert Operators Transmission 
A24L001-13, dated July 25, 2013, which is not incorporated by 
reference in this AD.

(i) 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: <a href="/cdn-cgi/l/email-protection#b28b9ff3fcff9f8383849ff3fffdf19fe0f7e3e7f7e1e6e1f2d4d3d39cd5ddc4"><span class="__cf_email__" data-cfemail="536a7e121d1e7e6262657e121e1c107e0116020616000700133532327d343c25">[email&#160;protected]</span></a>. 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, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0175, dated August 2, 2013, for related information. This MCAI may 
be found in the AD docket on the Internet at <a href="http://www.regulations.gov/#!documentDetail">http://www.regulations.gov/#!documentDetail</a>;D=FAA-2013-1031-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (k)(3) and (k)(4) of this AD.

(k) 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.

[[Page 33048]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission A24L001-13, Revision 01, 
dated March 6, 2014.
    (ii) Reserved.
    (3) 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 <a href="/cdn-cgi/l/email-protection#7918100b0e160b0d1110171c0a0a57384a4a4954384a4d493918100b1b0c0a571a1614"><span class="__cf_email__" data-cfemail="0e6f677c79617c7a6667606b7d7d204f3d3d3e234f3d3a3e4e6f677c6c7b7d206d6163">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) 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.
    (5) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


    Issued in Renton, Washington, on May 16, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12444 Filed 6-9-14; 8:45 am]
BILLING CODE 4910-13-P