[Federal Register: June 30, 2006 (Volume 71, Number 126)]
[Proposed Rules]
[Page 37512-37515]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jn06-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25221; Directorate Identifier 2006-NM-122-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and A310 Airplanes;
and Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes,
and Model C4-605R Variant F Airplanes (Collectively Called A300-600
Series 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 all Airbus Model A300 and A310 airplanes and A300-600 series
airplanes. This proposed AD would require inspecting for discrepancies
of all electrical bundles located in the leading and trailing edges of
the wings, and performing corrective actions if necessary. This
proposed AD results from fuel system reviews conducted by the
manufacturer. We are proposing this AD to prevent an ignition source,
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 July 31, 2006.
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: Tom Stafford, Aerospace Engineer,
[[Page 37513]]
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
25221; Directorate Identifier 2006-NM-122-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
that 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 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 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. (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.
The European Aviation Safety Agency (EASA) notified us that an
unsafe condition may exist on all Airbus Model A300 and A310 airplanes;
and Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes,
and Model C4-605R Variant F airplanes (collectively called A300-600
series airplanes). The EASA advises us of the potential for
discrepancies, including but not limited to chafing, of all electrical
bundles in the leading and trailing edges of the wings of these
airplanes. This condition, if not corrected, could result in an
ignition source, which, in combination with flammable fuel vapors,
could result in a fuel tank explosion and consequent loss of the
airplane.
Relevant Service Information
Airbus has issued the service bulletins listed in the table below.
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Airbus service bulletin,
Airplane model including appendix 01 Date
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A300..................................... A300-24-0102................ December 15, 2005.
A310..................................... A310-24-2095................ December 15, 2005.
A300-600 series.......................... A300-24-6092................ December 15, 2005.
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These service bulletins describe procedures for performing detailed
inspections for discrepancies of all electrical bundles located in the
leading and trailing edges of the wings, and corrective actions if
necessary. The inspections include inspecting for the following:
Inadequate clearance between electrical wire harnesses and
adjacent components or structure, including support structure,
stringers, fasteners, pipes, bonding leads, or any metallic component
which could create a conductive path to structure.
Evidence of chafing of electrical cable harnesses.
Discrepancies of clamps (including, but not limited to,
unacceptable condition, unacceptable condition of
[[Page 37514]]
cushioning and anti-chafing devices, or evidence of chafing against
electrical cable harnesses).
Discrepancies of cable ties (including, but not limited
to, unacceptable condition, or evidence of chafing against electrical
cable harnesses).
Discrepancies of convoluted conduits (including, but not
limited to, unacceptable condition, evidence of chafing against
electrical cable harnesses, and absence of drainage holes in the
conduits).
Discrepancies of metallic conduits (including, but not
limited to, unacceptable condition, evidence of chafing against
electrical cable harnesses, and absence of or unacceptable condition of
drainage holes in the conduits).
Corrective actions include repairing any chafed electrical cable
harnesses, replacing discrepant clamps with new clamps, repairing or
replacing discrepant cable ties, installing drainage holes in
convoluted or metallic conduits, and repairing any discrepant
convoluted or metallic conduits. If clearance is not adequate between
electrical wire harnesses and adjacent components or structure, the
service bulletins specify contacting Airbus for corrective action. The
service bulletins also specify to report all findings to Airbus.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The EASA mandated
the service information and issued airworthiness directive 2006-0076,
dated April 3, 2006, to ensure the continued airworthiness of these
airplanes in the European Union.
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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products 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 ``Differences Between
the Proposed AD and Service Information.'' The proposed AD would also
require sending the inspection results to Airbus.
Differences Between the Proposed AD and Service Information
The service bulletins specify to contact the manufacturer for
instructions on how to correct inadequate clearance between electrical
wire harnesses and adjacent components or structure and repair certain
conditions, but this proposed AD would require correcting that
condition using a method that we or the EASA (or its delegated agent)
approve. In light of the type of corrective action that would be
required to address the unsafe condition, and consistent with existing
bilateral airworthiness agreements, we have determined that, for this
proposed AD, a corrective action that we or the EASA approve would be
acceptable for compliance with this proposed AD.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the EASA's AD and the Airbus service bulletins is referred to as a
``detailed inspection.'' We have included the definition for a detailed
inspection in a note in the proposed AD.
Costs of Compliance
This proposed AD would affect about 227 airplanes of U.S. registry.
The proposed actions would take about 10 work hours per airplane, at an
average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $181,600, or
$800 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 and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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-2006-25221; Directorate Identifier 2006-NM-
122-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 31,
2006.
Affected ADs
(b) None.
[[Page 37515]]
Applicability
(c) This AD applies to all Airbus Model A300 and A310 airplanes;
and all Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, F4-605R, and F4-622R airplanes, and A300 C4-605R Variant F
airplanes; certificated in any category.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent an ignition source,
which, in combination with flammable fuel vapors, could result in a
fuel tank explosion and consequent loss of the airplane.
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.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the following service bulletins, as
applicable:
(1) For Model A300 airplanes: Airbus Service Bulletin A300-24-
0102, including Appendix 01, dated December 15, 2005;
(2) For Model A310 airplanes: Airbus Service Bulletin A310-24-
2095, including Appendix 01, dated December 15, 2005; and
(3) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, and F4-622R airplanes, and A300 C4-605R Variant F
airplanes: Airbus Service Bulletin A300-24-6092, including Appendix
01, dated December 15, 2005.
Inspections and Corrective Actions
(g) Within 44 months after the effective date of this AD,
perform detailed inspections for discrepancies of all electrical
bundles located in the leading and trailing edges of the wings, and
all applicable corrective actions, by doing all of the actions in
the service bulletin, except as provided by paragraph (h) of this
AD. All corrective actions must be done before further flight.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Exception to Corrective Action Instructions
(h) If inadequate clearance is found between any electrical wire
harness and adjacent components or structure: Before further flight,
correct the inadequate clearance using a method approved by either
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent).
Reporting
(i) Within 30 days after doing the inspections required by this
AD, or within 30 days after the effective date of the AD, whichever
is later: Submit a report of the findings (both positive and
negative) of the inspections required by paragraph (g) of this AD to
Airbus Engineering, c/o SE-E54, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. The report must include the airplane serial
number or registration number, the number of flight cycles and
flight hours on the airplane, the date of the inspection, the
location of the defect, the conditions found, and the type of
repair. Submitting Appendix 01 of the service bulletin to Airbus is
acceptable for compliance with this requirement. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.),
the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
Alternative Methods of Compliance (AMOCs)
(j)(1) 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.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(k) EASA's airworthiness directive 2006-0076, dated April 3,
2006, also addresses the subject of this AD.
Issued in Renton, Washington, on June 22, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5872 Filed 6-29-06; 8:45 am]
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