[Federal Register Volume 65, Number 114 (Tuesday, June 13, 2000)]
[Proposed Rules]
[Pages 37084-37087]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-14884]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-96-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
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 and 
A300-600 series airplanes. This proposal would require repetitive 
inspections to detect chafing and the existence of repairs of the 
harness of the high-level sensor of the fuel surge tanks, and to detect 
chafe marks on the support canisters of the magnetic level indicators; 
and follow-on corrective actions, if necessary. This proposal also 
would require modification of the harness for the high-level sensor of 
the outer wing fuel tanks, which would terminate certain repetitive 
inspections. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by the proposed AD are intended to 
prevent chafing of the harness of the high-level sensor, which could 
result in a short circuit and consequent fuel ignition source inside 
the outer wing fuel tanks.

DATES: Comments must be received by July 13, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-96-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.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; 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 notice may be changed in 
light of the comments received.
    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

[[Page 37085]]

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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-96-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. 2000-NM-96-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale 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 and A300-600 series 
airplanes. The DGAC advises that maintenance personnel found a chafed 
harness (cable) in the outer wing fuel tank. The harness is routed to 
the surge tank high-level sensor. Investigation revealed that clipping 
and routing of the cable (wiring) coupled with excessive slack of the 
cable between the ``P'' clips allows the cable to chafe against the 
support canister for the magnetic level indicator. Such chafing, if not 
corrected, could result in a short circuit and consequent fuel ignition 
source inside the outer wing fuel tank.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletins A300-28-0077 
(for Model A300 series airplanes), and A300-28-6062 (for Model A300-600 
series airplanes), each dated July 19, 1999. These service bulletins 
describe procedures for repetitive inspections to detect chafing and 
the existence of repairs of the harness of the high-level sensor of the 
fuel surge tanks, and to detect chafe marks on the support canisters of 
the magnetic level indicators; and follow-on corrective actions, if 
necessary. The follow-on corrective actions involve removing original 
repairs, if necessary, and accomplishing a splice repair and installing 
sleeves to the inner and outer cable coverings. The service bulletins 
categorize the repairs as either temporary or permanent depending upon 
the location of the repair and whether certain previous repairs were 
accomplished. In addition, the follow-on corrective actions include a 
repetitive visual inspection of the harness to ensure the integrity of 
the repair. This inspection would be performed if certain conditions 
(e.g., any temporary repairs) exist.
    The manufacturer also has issued Airbus Service Bulletins A300-28-
0058, Revision 02 (for Model A300 series airplanes), and A300-28-6020, 
Revision 01 (for Model A300-600 series airplanes), each dated September 
28, 1999. These service bulletins describe procedures for modification 
of the harness for the high-level sensor in the outer wing fuel tanks. 
The modification involves re-routing the cables and installing longer 
cleats and reversing the ``P'' clips that support the cables. This 
modification will prevent the cables from sagging and ensure adequate 
clearance between the cables and the support canisters of the magnetic 
level indicators. Accomplishment of the modification eliminates the 
need for certain repetitive inspections of the harness of the high-
level sensor of the fuel surge tanks. However, the modification does 
not eliminate the need for the 10,000-flight-hour detailed visual 
inspections specified in the follow-on corrective actions, following 
the accomplishment of any temporary repairs.
    The DGAC classified Airbus Service Bulletins A300-28-0077 and A300-
28-6062 as mandatory and issued French airworthiness directive 1999-
404-293(B), dated October 6, 1999, in order to assure 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 
Sec. 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 repetitive 
inspections to detect chafing and the existence of repairs of the wire 
harnesses of the high-level sensors; and to detect chafe marks on the 
support canisters of the magnetic level indicators; and follow-on 
corrective actions, if necessary. This proposal also would require 
modification of the harness for the high-level sensor of the outer wing 
fuel tanks, which would terminate certain repetitive inspections. The 
actions would be required to be accomplished in accordance with the 
service bulletins described previously, except as discussed below.

Difference Between Proposed AD and Related Service Information

    Operators should note that this AD proposes to mandate, within 18 
months, the modification of the harness of the high-level sensor of the 
outer wing fuel tanks described in Airbus Service Bulletin A300-28-
0058, Revision 02, or A300-28-6020, as terminating action for certain 
repetitive inspections. [Incorporation of the terminating action is 
optional in French airworthiness directive 1999-404-293(B).]
    The FAA has determined that long-term continued operational safety 
will be better assured by design changes to remove the source of the 
problem, rather than by repetitive inspections. Long-term inspections 
may not provide the degree of safety assurance necessary for the 
transport airplane fleet. This, coupled with a better understanding of 
the human factors associated with numerous continual inspections, has 
led the FAA to consider placing less emphasis on inspections and more 
emphasis on design improvements. The proposed modification requirement 
is consistent with these conditions.

Cost Impact

    The FAA estimates that 37 series airplanes of U.S. registry would 
be affected by this proposed AD, that it would take approximately 1 
work hour per airplane to accomplish the proposed repetitive detailed 
visual inspections, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be $2,220, or $60 per airplane, per 
inspection cycle.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed modification, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be $2,220, or $60 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of

[[Page 37086]]

the proposed requirements of this AD action, and that no operator would 
accomplish those actions in the future if this AD were not adopted.

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 Industrie: Docket 2000-NM-96-AD.

    Applicability: Model A300 and A300-600 series airplanes, 
certificated in any category; except those airplanes on which Airbus 
Modification 04489 has been installed during production.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing of the wire harnesses of the high-level 
sensors, which could result in a short circuit and consequent fuel 
ignition source inside the outer wing fuel tanks, accomplish the 
following:

Detailed Visual Inspection

    (a) Within 500 flight hours after the effective date of this AD, 
perform a detailed visual inspection to detect chafing and the 
existence of repairs of the harness (cable) of the high-level sensor 
of the fuel surge tanks, and to detect chafe marks on the support 
canisters of the magnetic level indicators; in accordance with 
Airbus Service Bulletin A300-28-0077 (for Model A300 series 
airplanes), or A300-28-6062 (for Model A300-600 series airplanes), 
each dated July 19, 1999, as applicable.
    (1) For airplanes on which modification of the harness in 
accordance the Airbus Service Bulletin A300-28-0058 (for Model A300 
series airplanes), or A300-28-6020 (for Model A300-600 series 
airplanes), as applicable; has NOT been accomplished: Accomplish the 
requirements of paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Repeat the detailed visual inspection thereafter at 
intervals not to exceed 500 flight hours until the requirements of 
paragraph (a)(1)(ii) of this AD are accomplished. If any wire 
chafing, chafe mark, or existing repair is detected during any 
inspection, prior to further flight, determine the appropriate 
repair and/or condition of repair as specified in Inspection Table 1 
of the Accomplishment Instructions of Airbus Service Bulletin A300-
28-0077 or A300-28-6062, as applicable. At the times specified in 
Inspection Table I, accomplish corrective actions (e.g., temporary 
or permanent repairs and follow-on inspections and repairs), in 
accordance with the applicable service bulletin. If any discrepancy 
is found during any follow-on inspection, prior to further flight, 
repair the discrepancy in accordance with the applicable service 
bulletin.
    (ii) Within 18 months after the effective date of this AD, 
modify the harness of the high-level sensor in the outer wing fuel 
tanks, in accordance with Airbus Service Bulletin A300-28-0058, 
Revision 02 (for Model A300 series airplanes), or A300-28-6020, 
Revision 01 (for Model A300-600 series airplanes); each dated 
September 28, 1999. Accomplishment of the modification terminates 
the 500-flight-hour repetitive inspection required by paragraph 
(a)(1) of this AD. However, if a temporary repair is installed, the 
10,000-flight-hour detailed visual inspection specified in the 
follow-on corrective actions of Table 1 continues to be required by 
this AD.
    (2) For airplanes on which modification of the harness in 
accordance with Airbus Service Bulletin A300-28-0058 (for Model A300 
series airplanes), or A300-28-6020 (for Model A300-600 series 
airplanes); as applicable; HAS been accomplished: Accomplish the 
requirements of paragraph (a)(2)(i) or (a)(2)(ii), as applicable.
    (i) If no wire chafing, chafe marks, or existing repairs are 
detected, no further action is required by this AD.
    (ii) If any wire chafing, chafe mark, or existing repair is 
detected, prior to further flight, determine the appropriate repair 
and/or condition of repair as specified in Inspection Table 2 of the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-0077 
or A300-28-6062, as applicable. At the times specified in Inspection 
Table 2, accomplish corrective actions (e.g., temporary or permanent 
repairs and follow-on inspections), in accordance with the 
applicable service bulletin. If any discrepancy is found during any 
follow-on inspection, prior to further flight, repair the 
discrepancy in accordance with the applicable service bulletin.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirrors, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Modification accomplished prior to the effective date of 
this AD, in accordance with Airbus Service Bulletin A300-28-0058, 
dated December 15, 1988, Revision 01, dated October 1, 1991 (for 
Model A300 series airplanes), or A300-28-6020, dated December 15, 
1988 (for Model A300-600 series airplanes), is considered acceptable 
for compliance with the action specified in paragraph (a)(1)(ii) of 
this AD.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with Secs.  
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.


[[Page 37087]]


    Note 5: The subject of this AD is addressed in French 
airworthiness directive 1999-404-293(B), dated October 6, 1999.


    Issued in Renton, Washington, on June 7, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14884 Filed 6-12-00; 8:45 am]
BILLING CODE 4910-13-U