[Federal Register: September 8, 2003 (Volume 68, Number 173)]
[Proposed Rules]
[Page 52862-52864]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08se03-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-119-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600 Series
Airplanes, Model A300 B4-600R Series Airplanes, Model A300 C4-605R
Variant F Airplanes, and Model A300 F4-605R Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A300 B4-600
Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 C4-
605R Variant F Airplanes, and Model A300 F4-605R Airplanes. This
proposal would require modification of certain components of the 115
Volts Alternating Current (VAC) supply wiring and of the fuel gauging
system. This action is necessary to prevent short circuits between 115
VAC wiring and certain fuel system electrical wire runs with subsequent
overheating of the cadensicon sensor thermistor or fuel level sensor,
which could be great enough to ignite fuel vapors in the fuel tank and
cause an explosion. This action is intended to address the identified
unsafe condition.
DATES: Comments must be received by October 8, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-119-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-119-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice
[[Page 52863]]
Bellonte, 31707 Blagnac Cedex, France. This information may be examined
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-119-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-119-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified the FAA that
an unsafe condition may exist on certain Airbus Model A300 B4-600
Series Airplanes, Model A300 B4-600R Series Airplanes, Model A300 C4-
605R Variant F Airplanes, and Model A300 F4-605R Airplanes. The DGAC
advises that review of the 115 Volts Alternating Current (VAC) supply
wiring has shown unsatisfactory separation between power supply routes
S and M. The DGAC also advises of the possibility of a short circuit
between the 115 VAC electrical lines and the cadensicon electrical
sensor circuits. If a short circuit occurs in these areas, significant
overheating of the cadensicon sensor thermistor or of a fuel level
sensor is possible. This condition, if not corrected, could result in
ignition of fuel vapors in the fuel tank and an explosion.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-28-6066, dated November 8,
2000, which describes procedures to separate, by installing spacers and
supports, electrical cable routes 2S and 2M where these cable are
routed together on the leading edge of the right-hand wing at zone 623;
and in the areas of track 4 and track 5, screwjack 3, rib 220, and rib
69. Airbus has also issued Airbus Service Bulletin A300-28-6070,
Revision 1, dated March 22, 2002, which describes procedures for
installing sleeves to separate electrical cable routes 2S and 2M in
various places, i.e., in the right-hand electronics rack 90VU, in the
forward cargo compartment, between FR38.2 and FR39, under the cabin
floor, between FR51 and FR52, in the main landing gear well and
hydraulics compartment, and in the shroud box. Accomplishment of the
actions specified in these service bulletins is intended to adequately
address the identified unsafe condition. The DGAC classified both
service bulletins as mandatory and issued French airworthiness
directives 2002-172(B), dated April 3, 2002, and 2002-171(B), dated
April 3, 2002, to ensure the continued airworthiness of these airplanes
in France.
FAA's Conclusions
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. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletins described previously.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in each
individual AD.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
The FAA estimates that 70 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 29 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $65 per work hour. Required parts would cost
approximately $8,938 per airplane. Based on these figures, the cost
impact of the proposed AD on U.S. operators is estimated to be
$757,610, or $10,823 per airplane.
The cost impact figure discussed above is based on assumptions that
no
[[Page 52864]]
operator has yet accomplished any of the proposed requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that 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) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus: Docket 2002-NM-119-AD.
Applicability: Model A300 B4-600 series airplanes, Model A300
B4-600R series airplanes, Model A300 C4-605R Variant F airplanes,
and Model A300 F4-605R airplanes; as listed in Airbus Service
Bulletin A300-28-6066, dated November 8, 2000; and Airbus Service
Bulletin A300-28-6070, Revision 1, dated March 22, 2002;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent short circuits between 115 Volts Alternating Current
(VAC) wiring and certain fuel system electrical wire runs with
subsequent overheating of the cadensicon sensor thermistor or fuel
level sensor, which could be great enough to ignite fuel vapors in
the fuel tank and cause an explosion, accomplish the following:
Modification
(a) Within 4,000 flight hours after the effective date of this
AD, modify elements of the electrical wiring to separate the
cadensicon wiring from the 115 VAC wiring, in accordance with Airbus
Service Bulletin A300-28-6066, dated November 8, 2000.
(b) Within 4,000 flight hours after the effective date of this
AD, modify elements of the electrical wiring to separate the 115 VAC
supply wiring of the fuel gauging system, in accordance with Airbus
Service Bulletin A300-28-6070, Revision 1, dated March 22, 2002.
Alternative Methods of Compliance
(c) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, is authorized
to approve alternative methods of compliance for this AD.
Note: The subject of this AD is addressed in French
airworthiness directives 2002-172(B) and 2002-171(B), both dated
April 3, 2002.
Issued in Renton, Washington, on August 29, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-22704 Filed 9-5-03; 8:45 am]
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