[Federal Register Volume 77, Number 25 (Tuesday, February 7, 2012)]
[Proposed Rules]
[Pages 6023-6026]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-2678]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0038; Directorate Identifier 2011-NM-209-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 A300 B4-600 series airplanes and Model A310-203, -204, -
221, and -222 airplanes. This proposed AD was prompted by a report of a
capacitive density condensator (cadensicon) coil overheating during
testing. This proposed AD would require an inspection to determine if a
certain fuel quantity indication computer (FQIC) is installed,
replacement of identified FQICs, and modification of the associated
wiring. We are proposing this AD to detect and correct potential
overheating of the cadensicon coil, which could create an ignition
source inside a fuel tank, which, in combination with flammable fuel
vapors, could result in a fuel tank explosion and consequent loss of
the airplane.
DATES: We must receive comments on this proposed AD by March 23, 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.,
[[Page 6024]]
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 [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, 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 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-2012-0038;
Directorate Identifier 2011-NM-209-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 2011-0186, dated September 23, 2011 (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
In view to address the scope of Special Federal Aviation
Regulation 88 (SFAR 88) (66 FR 23086, May 7, 2001) and the
equivalent JAA Internal Policy INT/POL/25/12, a safety analysis of
Fuel Quantity Indication Computers (FQIC) fitted to Wide Body
aeroplanes has been performed.
Detailed analysis has shown that on early standard FQIC, Type 1,
there is an insufficient gap on the printed circuit board between a
115V [volt] supply and a direct path to the Capacitive Density
Condensator (Cadensicon).
During tests that were carried out applying 115V to the
Cadensicon coil, measured temperature levels were in excess of the
acceptable level of 200 [deg]C. This potential overheating of the
Cadensicon coil could be a possible ignition point within the fuel
tank.
This condition, if left uncorrected, could create an ignition
source in the tank vapour space, possibly resulting in a wing fuel
tank explosion and consequent loss of the aeroplane.
For the reasons explained above, this [EASA] AD requires the
replacement of all Type 1 FQICs with Type 2 FQICs.
You may obtain further information by examining the MCAI in the AD
docket.
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 (66 FR 23086, May 7, 2001) requires
certain type design (i.e., type certificate (TC) and supplemental type
certificate (STC)) holders to substantiate that their fuel tank systems
can prevent ignition sources in the fuel tanks. This requirement
applies to type design holders for large turbine-powered transport
airplanes and for subsequent modifications to those airplanes. It
requires them to perform design reviews and to develop design changes
and maintenance procedures if their designs do not meet the new fuel
tank safety standards. As explained in the preamble to the rule, we
intended to adopt airworthiness directives to mandate any changes found
necessary to address unsafe conditions identified as a result of these
reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: Single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88 (66 FR 23086, May 7, 2001). (The JAA is an
associated body of the European Civil Aviation Conference (ECAC)
representing the civil aviation regulatory authorities of a number of
European States who have agreed to co-operate in developing and
implementing common safety regulatory standards and procedures.) Under
this regulation, the JAA stated that all members of the ECAC that hold
type certificates for transport category airplanes are required to
conduct a design review against explosion risks.
We have determined that the actions identified in this AD are
necessary to reduce 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.
Relevant Service Information
Airbus has issued Mandatory Service Bulletins A300-28-6024,
Revision 02, dated January 19, 2011; and A310-28-2039, Revision 01,
dated January 19, 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
[[Page 6025]]
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 53 products of U.S. registry. We also estimate that
it would take about 6 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 $37,630, or $710 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); and
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-2012-0038; Directorate Identifier 2011-NM-
209-AD.
(a) Comments Due Date
We must receive comments by March 23, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, and
B4-622 airplanes, and Model A310-203, -204, -221, and -222
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 a report of a capacitive density
condensator (cadensicon) coil overheating during testing. We are
issuing this AD to detect and correct potential overheating of the
cadensicon coil, which could create an ignition source inside a fuel
tank, which, in combination with flammable fuel vapors, could result
in a fuel tank explosion 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) Actions
Within 30 months after the effective date of this AD, inspect to
determine whether any fuel quantity indication computer (FQIC) Type
1, having part number (P/N) SIC5054 or P/N SIC5051 (as applicable to
the airplane model), is installed, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-28-6024, Revision 02, dated January 19, 2011; or Airbus
Mandatory Service Bulletin A310-28-2039, Revision 01, dated January
19, 2011; as applicable. A review of airplane maintenance records is
acceptable in lieu of this inspection if the part number of the FQIC
can be conclusively determined from that review. If any FQIC Type 1
having P/N SIC5054 or P/N SIC5051 is installed, within 30 months
after the effective date of this AD, replace the FQIC Type 1 with a
FQIC Type 2 having P/N SIC5055, P/N SIC5076, P/N SIC5082, or P/N
SIC5083 (as applicable to Model A310 series airplanes) or with a
FQIC Type 2 having P/N SIC5077 (as applicable to Model A300 B4-600
series airplanes), and modify the associated wiring, in accordance
with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A300-28-6024, Revision 02, dated January 19, 2011; or
Airbus Mandatory Service Bulletin A310-28-2039, Revision 01, dated
January 19, 2011; as applicable.
(h) Parts Installation
As of the effective date of this AD, no person may install any
FQIC Type 1 having P/N SIC5054 or P/N SIC5051, on any airplane.
(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: 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: [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.
[[Page 6026]]
(j) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0186, dated September 23, 2011, and the service
information specified in paragraphs (j)(1) and (j)(2) of this AD,
for related information.
(1) Airbus Mandatory Service Bulletin A300-28-6024, Revision 02,
dated January 19, 2011.
(2) Airbus Mandatory Service Bulletin A310-28-2039, Revision 01,
dated January 19, 2011.
Issued in Renton, Washington on January 12, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-2678 Filed 2-6-12; 8:45 am]
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