
[Federal Register Volume 77, Number 13 (Friday, January 20, 2012)]
[Proposed Rules]
[Pages 2928-2930]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-1131]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0033; Directorate Identifier 2011-NM-086-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 A310 series airplanes. This proposed AD was prompted by a 
report of an electrical arc and hydraulic haze in the wheel bay of the 
left-hand main landing gear (MLG) possibly resulting from chafing 
between the hydraulic high pressure hose and electrical wiring of the 
green electrical motor pump (EMP). This proposed AD would require 
prohibiting in-flight use of the green EMPs; revising the airplane 
flight manual (AFM) limitations section; installing a placard in the 
cockpit overhead panel; doing a one-time general visual inspection for 
correct condition and installation of hydraulic pressure hoses, 
electrical conduits, feeder cables, and associated clamping devices; 
and corrective action if necessary. We are proposing this AD to detect 
and correct chafing of hydraulic pressure hoses and electrical wiring 
of the green EMPs, which in combination with a system failure, could 
cause an uncontrolled and undetected fire in the MLG bay.

DATES: We must receive comments on this proposed AD by March 5, 2012.

ADDRESSES: You may send comments 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--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call (425) 227-1221.

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 this proposed AD, the

[[Page 2929]]

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; 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-2012-0033; 
Directorate Identifier 2011-NM-086-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 Community, has issued EASA 
Airworthiness Directive 2011-0071, dated April 18, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    An operator reported an electrical arc and a large hydraulic 
haze in the left hand Main Landing Gear (LH MLG) wheel bay that 
occurred during ground operation. The analysis revealed that this 
occurrence is likely the result of chafing between hydraulic high 
pressure hose and electrical wiring of the Green Electrical Motor 
Pump (EMP).
    This condition, if not detected and corrected, and in 
combination with a system failure leading to the use of the Green 
EMPs in flight, could lead to an uncontrolled and undetected fire in 
the MLG bay.
    For the reasons explained above, this AD temporarily prohibits 
the in-flight use of green EMPs, by mandating an update of the 
Aeroplane Flight Manual (AFM) limitations section and installation 
of a placard in the cockpit overhead panel. This [EASA] AD requires 
also a one-time [general] visual inspection of hydraulic pressure 
hoses and electrical wiring of Green EMPs and corrective action(s), 
depending on findings.

Corrective actions include repair or replacement of the hydraulic 
pressure hoses and electrical wiring with new hydraulic pressure hoses 
and electrical wiring. You may obtain further information by examining 
the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued All Operators Telex A310-29A2101, Revision 01, 
dated April 12, 2011; and All Operators Telex A310-29A2102, dated April 
12, 2011. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 58 products of U.S. registry. We also estimate that 
it would take about 2 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 $200 per product. Where the 
service information lists required parts costs that are covered under 
warranty, we have assumed that there will be no charge for these parts. 
As we do not control warranty coverage for affected parties, some 
parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $21,460, or $370 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, 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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2012-0033; Directorate Identifier 2011-NM-
086-AD.

[[Page 2930]]

(a) Comments Due Date

    We must receive comments by March 5, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category, 
all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 29: Hydraulic 
Power.

(e) Reason

    This AD was prompted by a report of an electrical arc and 
hydraulic haze in the wheel bay of the left-hand main landing gear 
(MLG) possibly resulting from chafing between the hydraulic high 
pressure hose and electrical wiring of the green electrical motor 
pump (EMP). We are issuing this AD to detect and correct chafing of 
hydraulic pressure hoses and electrical wiring of the green EMPs, 
which in combination with a system failure, could cause an 
uncontrolled and undetected fire in the MLG bay.

(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) Installing Placard and Revising Airplane Flight Manual

    For all airplanes, as of the effective date of this AD, the in-
flight use of green EMPs is prohibited. Before the next flight, do 
the actions specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Install in the cockpit on the hydraulic power overhead panel 
427VU, a locally manufactured self-adhesive placard prohibiting the 
in-flight use of the green EMPs, in accordance with the instructions 
in Airbus All Operators Telex A310-29A2101, Revision 01, dated April 
12, 2011 (for airplanes equipped with EATON (formerly VICKERS) 
hydraulic EMPs); or Airbus All Operators Telex A310-29A2102, dated 
April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) 
hydraulic EMPs).
    (2) Revise the Limitations section of the applicable airplane 
flight manual (AFM) to prohibit the in-flight use of the green EMPs.

    Note 1:  Inserting a copy of this AD into the AFM Limitations 
section is acceptable for complying with the requirement of 
paragraph (g)(2) of this AD.

(h) Inspecting for Damage and Chafing

    Within 500 flight hours or 4 months after the effective date of 
this AD, whichever occurs first, do a one-time general visual 
inspection for correct condition (i.e., no damage and no chafing) 
and correct installation of the hydraulic pressure hoses, electrical 
conduits, feeder cables, and associated clamping devices at frame 
54, as well as the electrical conduits and feeder cables underneath 
the clamps (including removal of the concerned clamps), in 
accordance with the instructions in Airbus All Operators Telex A310-
29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped 
with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All 
Operators Telex A310-29A2102, dated April 12, 2011 (for airplanes 
equipped with PARKER (formerly ABEX) hydraulic EMPs). If any 
incorrect installation is found, before further flight, install the 
affected parts correctly, in accordance with Airbus All Operators 
Telex A310-29A2101, Revision 01, dated April 12, 2011 (for airplanes 
equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus 
All Operators Telex A310-29A2102, dated April 12, 2011 (for 
airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).
    (1) If any damage or chafing marks are found during the 
inspection required by paragraph (h) of this AD, before further 
flight, replace or repair the affected parts (hydraulic pressure 
hoses, electrical conduits, feeder cables, clamps, and spacer, if 
installed), in accordance with the instructions in Airbus All 
Operators Telex A310-29A2101, Revision 01, dated April 12, 2011 (for 
airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or 
Airbus All Operators Telex A310-29A2102, dated April 12, 2011 (for 
airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).
    (2) Before further flight after compliance with the requirements 
of paragraph (h) of this AD, as applicable, remove the placard 
required by paragraph (g)(1) of this AD; and remove the revision of 
the Limitations section of the AFM, as required by paragraph (g)(2) 
of this AD; from the airplane and the AFM, respectively.

(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, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; 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.

(j) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0071, dated 
April 18, 2011; Airbus All Operators Telex A310-29A2101, Revision 
01, dated April 12, 2011; and Airbus All Operators Telex A310-
29A2102, dated April 12, 2011; for related information.

    Issued in Renton, Washington, on January 13, 2012.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-1131 Filed 1-19-12; 8:45 am]
BILLING CODE 4910-13-P


