[Federal Register Volume 77, Number 205 (Tuesday, October 23, 2012)]
[Proposed Rules]
[Pages 64765-64767]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-26078]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1105; Directorate Identifier 2012-NM-137-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 A318, A319, and A320 series airplanes. This proposed AD
was prompted by fuel system reviews conducted by the manufacturer,
which revealed that certain fuel pumps under certain conditions can
create an ignition source in the fuel tank. This proposed AD would
require modification of the center tank fuel pump control circuit by
installation of ground fault interrupters (GFIs). This proposed AD
would also require either replacement of the GFI or deactivation of the
associated fuel pump following failure of any post-modification
operational test of the GFI. We are proposing this AD to prevent the
potential of ignition sources inside fuel tanks, which, in combination
with flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.
DATES: We must receive comments on this proposed AD by December 7,
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, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email [email protected]; 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, WA. 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 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-227-
1405; 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-2012-1105;
Directorate Identifier 2012-NM-137-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
Airworthiness Directive 2012-0198, dated September 26, 2012 (which
superseded EASA AD 2012-0133, dated July 18, 2012) (referred to after
this as ``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
* * * The FAA published Special Federal Aviation Regulation
(SFAR) 88, and the Joint Aviation Authorities (JAA) published
Interim Policy INT/POL/25/12.
In the framework of these requirements, EASA have determined
that the electrical power supply circuits of certain fuel pumps,
installed on A320 family aeroplanes, for which the canisters become
uncovered during normal operation, could, under certain conditions,
create an ignition source in the tank vapour space.
This condition, if not corrected, could result in a fuel tank
explosion and consequent loss of the aeroplane.
To address this potential unsafe condition, Airbus developed a
modification which includes installing Ground Fault Interrupters
(GFI) into the centre tank fuel pump control circuit, providing
additional system protection by electrically isolating the pump in
case of a ground fault condition downstream of the GFI.
Consequently, EASA issued AD 2012-0133 to require modification
of the centre tank fuel
[[Page 64766]]
pump control circuit by installing GFI and thereafter, in case a GFI
failed an operational test, replacement of the faulty GFI, or
deactivation of the associated fuel pump in accordance with the
provisions of the applicable Master Minimum Equipment List (MMEL).
Since that [EASA] AD was issued, it was noted that,
inadvertently, the Applicability of the Final AD was incorrect (the
preceding PAD [proposed AD] 12-051 was correct) by excluding
aeroplanes on which Airbus modification 150736 has been embodied in
production. As a result, the required actions when a GFI fails an
operational test did not apply to those aeroplanes.
For the reasons described above, this [EASA] AD retains the
requirements [modification of the centre tank fuel pump control
circuit by installing GFI] of EASA AD 2012-0133, which is
superseded, and expands the Applicability to aeroplanes on which
Airbus modification 150736 has been embodied in production.
The required actions also include either replacement of the GFI or
deactivation of the associated fuel pump following failure of any post-
modification operational test of the GFI. You may obtain further
information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A320-28-1188, dated March 23,
2012. 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 755 products of U.S. registry. We also estimate that
it would take about 11 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 $3,360 per product,
depending on configuration. 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 $3,242,725, or $4,295
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-2012-1105; Directorate Identifier 2012-NM-
137-AD.
(a) Comments Due Date
We must receive comments by December 7, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; and Model A320-111, -211, -212, -214, -231, -232, and
-233 airplanes; certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Reason
This AD was prompted by fuel system reviews conducted by the
manufacturer, which revealed that certain fuel pumps under certain
conditions can create an ignition source in the fuel tank. We are
issuing this AD to prevent the potential of ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.
(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) Modification
Except as provided by paragraph (h) of this AD: Within 48 months
after the effective date of this AD, modify the center tank fuel
pump control circuit by installing ground fault interrupters (GFIs),
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-28-1188, dated March 23, 2012.
(h) Airplanes Excluded From Modification Requirement
For airplanes on which Airbus modification 150736 has been
embodied in production, and on which no GFI has been removed since
first flight, the modification specified in paragraph (g) of this AD
is not required.
[[Page 64767]]
(i) Corrective Action for Failed Post-modification Operational Test
After accomplishment of the modification specified in paragraph
(g) or (h) of this AD, each time a GFI fails an operational test,
before further flight, replace the GFI or deactivate the associated
fuel pump, in accordance with a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA.
Note 1 to paragraph (i) of this AD: Guidance on the operational
test specified in paragraph (i) of this AD can be found in Task
28.18.00/01, Operational Check of Centre Tank Fuel Pump GFI, of the
Airbus A318/A319/A320/A321 Maintenance Review Board Report or Task
281800-710-801, Operational Check of Centre Tank Fuel Pump GFI, of
the Airbus A318/A319/A320 Aircraft Maintenance Manual.
Note 2 to paragraph (i) of this AD: Guidance on the fuel pump
deactivation specified in paragraph (h) of this AD can be found in
Item 28-21-02, Center Tank Systems, of the FAA Master Minimum
Equipment List for Airbus A318/A319/A320/A321.
(j) 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: Sanjay Ralhan, Aerospace Engineer, 1601
Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-227-1405;
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) 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.
(k) Related Information
(1) Refer to MCAI EASA Airworthiness Directive 2012-0198, dated
September 26, 2012; and Airbus Service Bulletin A320-28-1188, dated
March 23, 2012; for related information.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; 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, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on October 15, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-26078 Filed 10-22-12; 8:45 am]
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