[Federal Register: August 23, 2005 (Volume 70, Number 162)]
[Proposed Rules]
[Page 49213-49215]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23au05-27]
[[Page 49213]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22170; Directorate Identifier 2005-NM-073-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, and
-231 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A320-111, -211, -212, and -231 airplanes. This
proposed AD would require, for certain airplanes, modifying the cables
and access holes to the inner tank fuel pumps; and, for certain other
airplanes, inspecting the fuel pump access holes and modifying the
access holes, if necessary. This proposed AD results from fuel system
reviews conducted by the manufacturer. We are proposing this AD to
prevent chafing of the fuel pump cables, which could result in
electrical arcing and possible ignition of fuel vapors and consequent
explosion of the fuel tank.
DATES: We must receive comments on this proposed AD by September 22,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number
``Docket No. FAA-2005-22170; Directorate Identifier 2005-NM-073-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The FAA has examined the underlying safety issues involved in
recent 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'' (67 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 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 another 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. (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.
[[Page 49214]]
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A320-111, -211, -
212, and -231 airplanes. The DGAC advises that a design review of the
electrical cables and structure around the access holes to the inner
tank fuel pumps revealed that cables could be damaged by chafing
against sharp edges of the fuel pump access holes. This condition, if
not prevented, could result in electrical arcing and possible ignition
of fuel vapors and consequent explosion of the fuel tank.
Relevant Service Information
Airbus has issued, for certain Model A320-111, -211, and -231
airplanes, Service Bulletin A320-28-1008, Revision 1, dated April 10,
1989, which describes procedures for modifying the cables and access
holes to the inner tank fuel pumps. The modification includes
chamfering the edges of the fuel pump access holes, applying protective
material to the chamfered areas, installing backshells to the cable
connectors, and securing the cables to the backshells.
Airbus has also issued, for certain Model A320-211, -212, and -231
airplanes, Service Bulletin A320-28-1054, dated August 23, 1993, which
describes procedures for performing a visual inspection for correct
radius of the fuel pump access holes and, as applicable, modifying the
fuel pump access holes. The modification includes chamfering the edges
of all access holes to the inner tank fuel pumps and applying
protective material to the chamfered areas. The service bulletin also
describes procedures for reporting all findings to Airbus.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
The DGAC mandated accomplishment of the service bulletins and
issued French airworthiness directive F-2005-031, dated February 16,
2005, to ensure the continued airworthiness of these airplanes in
France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Between
Service Information and the Proposed AD.''
Difference Between French Airworthiness Directive and the Proposed AD
The applicability of French airworthiness directive F-2005-031
excludes airplanes that accomplished Airbus Service Bulletin A320-28-
1008, Revision 1, in service and airplanes that accomplished Airbus
Service Bulletin A320-28-1054 in service. However, we have not excluded
those airplanes from the applicability of this proposed AD; rather,
this proposed AD includes a requirement to accomplish the actions
specified in those service bulletins. This requirement would ensure
that the actions specified in the service bulletins and required by
this proposed AD are accomplished on all affected airplanes. Operators
must continue to operate the airplane in the configuration required by
this proposed AD unless an alternative method of compliance is
approved.
Difference Between Service Information and the Proposed AD
Although Airbus Service Bulletin A320-28-1054 describes procedures
for reporting all findings to Airbus, this proposed AD would not
require this report. The FAA does not need this information from
operators.
Clarification of Inspection Terminology
While Airbus Service Bulletin A320-28-1054 specifies a ``visual
inspection,'' this proposed AD would require a ``general visual
inspection'' to avoid any confusion about the proper type of
inspection. We have included a definition of this type of inspection in
the proposed AD.
Costs of Compliance
This proposed AD would affect about 17 airplanes of U.S. registry.
The proposed actions would be performed at an average labor rate of $65
per work hour, and any needed parts would be supplied from operator
inventory.
For about 7 U.S.-registered airplanes subject to Airbus Service
Bulletin A320-28-1008, Revision 1, dated April 10, 1989, the proposed
modification would take about 3 work hours. Based on these figures, the
estimated cost of this proposed modification for U.S. operators is
$1,365, or $195 per airplane.
For about 10 U.S.-registered airplanes subject to Airbus Service
Bulletin A320-28-1054, dated August 23, 1993, the proposed inspection
would take about 1 work hour. Based on these figures, the estimated
cost of this proposed inspection for U.S. operators is $650, or $65 per
airplane.
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 have 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 that the 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 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. See the ADDRESSES section for a location
to examine the regulatory evaluation.
[[Page 49215]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2005-22170; Directorate Identifier 2005-NM-
073-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by September
22, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A320-111, -211, -212, and -
231 airplanes, certificated in any category, that have not received
Airbus Modification 21088 or 21999 in production; and airplanes that
have received Airbus Modification 21088 in production and have
manufacturer's serial number 91 to 113 inclusive and 140 to 189
inclusive.
Unsafe Condition
(d) This AD results from fuel systems reviews conducted by the
manufacturer. We are issuing this AD to prevent chafing of the fuel
pump cables, which could result in electrical arcing and possible
ignition of fuel vapors and consequent explosion of the fuel tank.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection and Modification of Fuel Pump Access Holes
(f) Within 58 months after the effective date of this AD,
perform the actions required by paragraph (f)(1) or (f)(2) of this
AD, as applicable.
(1) For airplanes that have not received Airbus Modification
21088 or 21999 in production: Modify the cables and access holes to
the inner tank fuel pumps, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-28-1008, Revision 1,
dated April 10, 1989.
(2) For airplanes that have received Airbus Modification 21088
in production and have manufacturer's serial number 91 to 113
inclusive and 140 to 189 inclusive: Perform a general visual
inspection for the correct radius of the fuel pump access holes and
modify the access holes, if necessary, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-28-1054,
dated August 23, 1993. Do any applicable repairs before further
flight.
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
No Reporting Requirement
(g) Although Airbus Service Bulletin A320-28-1054, dated August
23, 1993, describes procedures for reporting inspection findings to
Airbus, this AD does not require such a report.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(i) French airworthiness directive F-2005-031, dated February
16, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on August 11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-16753 Filed 8-22-05; 8:45 am]
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