[Federal Register Volume 68, Number 173 (Monday, September 8, 2003)]
[Proposed Rules]
[Pages 52862-52864]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-22704]


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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: 
[email protected]. 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]
BILLING CODE 4910-13-P