[Federal Register Volume 65, Number 59 (Monday, March 27, 2000)]
[Proposed Rules]
[Pages 16151-16153]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-7337]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 65, No. 59 / Monday, March 27, 2000 / 
Proposed Rules  

[[Page 16151]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-128-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, 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 all Airbus Model A300, A310, and 
A300-600 series airplanes. This proposal would require an inspection to 
detect damage of the electrical bonding leads in specified locations of 
the fuel tanks, and replacement of any damaged electrical bonding leads 
with serviceable electrical bonding leads. For certain airplanes, this 
proposal also would require modifying the fuel pipe couplings in 
specified locations of the fuel tank. 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 electrical arcing/discharge in the fuel tank 
due to damaged electrical bonding leads or inadequate electrical 
bonding of the fuel pipe couplings, which could result in fuel ignition 
and consequent uncontained rupture of the fuel tank.

DATES: Comments must be received by April 26, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-128-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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, FAA, 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 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 99-NM-128-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. 99-NM-128-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 all Airbus Model A300, A310, and A300-600 series 
airplanes. The DGAC advises that, during a maintenance check, an 
inspection of the inner fuel tanks revealed damage (i.e., breakage and 
corrosion) to several bonding leads. The damage is a result of normal 
aging of the bonding leads. Damaged bonding leads could create 
electrical voltage differentials between the fuel tank components, 
which could result in electrical arcing inside the fuel tanks. The DGAC 
advises that electrical arcing also could occur between certain fuel 
pipe couplings inside the fuel tanks due to their existing design. 
These conditions, if not corrected, could result in fuel ignition and 
consequent uncontained rupture of the fuel tank.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-28-0072, Revision 01, 
dated October 01, 1998, including Appendix 1, dated October 01, 1998, 
and Appendix 2, dated February 20, 1998 (for Model A300 series 
airplanes); A310-28-2128, Revision 01, dated October 01, 1998, 
including Appendix 1, dated October 01, 1998, and Appendix 2, dated 
February 20, 1998 (for Model A310 series airplanes); and A300-28-6057, 
Revision 01, dated October 01, 1998, including Appendix 1, dated 
October 01, 1998, and Appendix 2, dated February 20, 1998 (for Model 
A300-600 series airplanes). These service bulletins describe procedures 
for inspection of the electrical bonding leads in specified locations 
of the fuel tank for damage (i.e., breakage, fraying, abrasion damage, 
looseness of the outer metal braid protection in the end crimp, 
looseness of the outer metal braid protection on the bonding lead inner 
core, corrosion, or missing leads), and replacement of any damaged 
electrical bonding lead with a serviceable electrical bonding lead.
    Also, Airbus has issued Service Bulletins A300-28-0073, Revision 
01, dated October 01, 1998 (for Model A300

[[Page 16152]]

series airplanes); A310-28-2130, Revision 01, dated October 01, 1998 
(for Model A310 series airplanes); and A300-28-6058, Revision 01, dated 
October 01, 1998 (for Model A300-600 series airplanes). For certain 
airplanes these service bulletins describe procedures for modifying the 
fuel pipe couplings in specified locations of the fuel tank by removing 
one bolt from each flanged fuel pipe coupling and reinstalling it as an 
electrical bonding bolt.
    Accomplishment of the actions specified in these service bulletins 
is intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 98-174-248(B), dated April 22, 1998, 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 
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, 
except as discussed below.

Difference Between Proposed Rule and Foreign Airworthiness 
Directive

    Operators should note that, although the service bulletin and 
French airworthiness directive recommend that the modification be 
accomplished within 4 years (after the release of the service 
bulletin), the FAA has determined that an interval of 4 years would not 
address the identified unsafe condition in a timely manner.
    An electrical discharge in a fuel tank can create a spark that 
could ignite the fuel vapors inside the tank. The spark energy required 
to ignite fuel depends on the type of fuel, the fuel temperature, and 
the air pressure (altitude) inside a fuel tank. Under certain 
conditions, fuel can be ignited with spark energy levels much lower 
than the energy required to create a visible mark. Therefore, a spark 
that has enough energy to cause a mark can ignite fuel vapor under a 
wider range of fuel tank conditions.
    In developing an appropriate compliance time for this AD, the FAA 
considered not only the manufacturer's recommendation, but the degree 
of urgency associated with addressing the subject unsafe condition, the 
average utilization of the affected fleet, and the time necessary to 
perform the modification. In light of all of these factors, the FAA 
finds a 36-month compliance time for accomplishing the inspection and 
modification to be warranted, in that 36 months represent an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

Cost Impact

    The FAA estimates that 116 airplanes of U.S. registry would be 
affected by this proposed AD.
    It would take between 70 and 80 work hours per airplane to 
accomplish the proposed inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the proposed 
inspection on U.S. operators is estimated to be between $487,200 and 
$556,800, or between $4,200 and $4,800 per airplane.
    It would take between 77 and 103 work hours per airplane to 
accomplish the proposed modification, at an average labor rate of $60 
per work hour. Required parts would cost approximately $104 per 
airplane. Based on these figures, the cost impact of the proposed 
modification on U.S. operators is estimated to be between $547,984 and 
$728,944, or between $4,724 and $6,284 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no 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.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 99-NM-128-AD.

    Applicability: All Model A300, A310, and A300-600 series 
airplanes, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (d) 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 electrical arcing/discharge in the fuel tank due to 
damaged

[[Page 16153]]

electrical bonding leads or inadequate electrical bonding of the 
fuel pipe couplings, which could result in fuel ignition and 
consequent uncontained rupture of the fuel tank, accomplish the 
following:
    (a) Within 36 months after the effective date of this AD, 
perform a one-time inspection to detect damage (i.e., breakage, 
fraying, abrasion damage, looseness of the outer metal braid 
protection in the end crimp, looseness of the outer metal braid 
protection on the bonding lead inner core, corrosion, or missing 
leads) of the electrical bonding leads in specified locations of the 
fuel tanks, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletins A300-28-0072, Revision 01, dated October 
01, 1998, including Appendix 1, dated October 01, 1998, and Appendix 
2, dated February 20, 1998 (for Model A300 series airplanes); A310-
28-2128, Revision 01, dated October 01, 1998, including Appendix 1, 
dated October 01, 1998, and Appendix 2, dated February 20, 1998 (for 
Model A310 series airplanes); or A300-28-6057, Revision 01, dated 
October 01, 1998, including Appendix 1, dated October 01, 1998, and 
Appendix 2, dated February 20, 1998 (for Model A300-600 series 
airplanes); as applicable.

    Note 2: Inspection of the area specified in paragraph (a) of 
this AD accomplished prior the effective date of this AD in 
accordance with Airbus Service Bulletins A300-28-0072, A310-28-2128, 
or A300-28-6057; all dated February 20, 1998; as applicable; is 
considered acceptable for compliance with the requirements of 
paragraph (a) of this AD.

    (b) If any electrical bonding lead is damaged, prior to further 
flight, replace the bonding lead with a serviceable bonding lead in 
accordance with the applicable service bulletin specified in 
paragraph (a) of this AD.
    (c) For airplanes on which Airbus Industrie Modification 11847 
(for Model A310 series airplanes) or 11848 (for Model A300/A300-600 
series airplanes) has not been accomplished, within 36 months after 
the effective date of this AD, modify the fuel pipe couplings in the 
specified locations of the fuel tank in accordance with the 
Accomplishment Instructions of Airbus Service Bulletins A300-28-
0073, Revision 01, dated October 01, 1998 (for Model A300 series 
airplanes); A310-28-2130, Revision 01, dated October 01, 1998 (for 
Model A310 series airplanes); or A300-28-6058, Revision 01, dated 
October 01, 1998 (for Model A300-600 series airplanes); as 
applicable.

    Note 3: Modification of the fuel pipe couplings accomplished 
prior to the effective date of this AD in accordance with Airbus 
Service Bulletins A300-28-0073, A310-28-2130, or A300-28-6058; all 
dated February 20, 1998; as applicable; is considered acceptable for 
compliance with the requirements of paragraph (c) of this AD.

    (d) 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

    (e) Special flight permits may be issued in accordance with 
sections 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.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 98-174-248(B), dated April 22, 1998.


    Issued in Renton, Washington, on March 20, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-7337 Filed 3-24-00; 8:45 am]
BILLING CODE 4910-13-U