[Federal Register Volume 65, Number 165 (Thursday, August 24, 2000)]
[Proposed Rules]
[Pages 51560-51562]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-21465]


 ========================================================================
 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.
 
 ========================================================================
 

  Federal Register / Vol. 65, No. 165 / Thursday, August 24, 2000 / 
Proposed Rules  

[[Page 51560]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-227-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
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 A319, A320, and 
A321 series airplanes. This proposal would require a revision to the 
Airplane Flight Manual; inspection to detect damage of the wiring and 
adjacent structure along the length of the fairing of the fuel boost 
pump; corrective actions, if necessary; and modification of the fuel 
pump wire and fairing. This action is necessary to prevent electrical 
arcing of the fuel boost pump wire, which could result in wing 
structural damage, fire, and/or fuel vapor explosion. This action is 
intended to address the identified unsafe condition.

DATES: Comments must be received by September 25, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-227-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. 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. 2000-NM-227-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 for Windows or 
ASCII text.
    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.
    Submit comments using the following format:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-227-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-227-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received numerous reports of severe electrical arcing 
of the fuel boost pump wires located under the wings on Airbus Model 
A319, A320, and A321 series airplanes. In many cases, the wing skin was 
damaged by the arcing, and, in one case, approximately two-thirds of 
the thickness of the wing skin had been eroded. The exact cause of the 
arcing is unknown, although reports have indicated that the wires could 
have been damaged from being pinched by the wing fairing during 
installation and/or chafed in service from vibration. Such electrical 
arcing of the fuel boost pump wire, if not corrected, could result in 
wing structural damage, fire, and/or fuel vapor explosion.

U.S. Type Certification of the Airplanes

    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.

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:
     A revision of the FAA-approved Airplane Flight Manual to 
advise the flightcrew not to reset any tripped circuit breaker of a 
wing tank fuel boost pump.
     An initial inspection to detect damage of the wiring and 
adjacent structure along the length of the fairing of the fuel boost 
pump; conditional

[[Page 51561]]

inspections after any circuit breaker of a fuel boost pump is tripped; 
and corrective actions, if necessary.
     Modification of the fuel pump wire. The proposed AD also 
would require that operators report results of inspection findings to 
the FAA.

Cost Impact

    The FAA estimates that 306 airplanes of U.S. registry would be 
affected by this proposed AD.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed AFM revision, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the AFM revision 
proposed by this AD on U.S. operators is estimated to be $18,360, or 
$60 per airplane.
    It would take approximately 2 work hours per airplane to accomplish 
the proposed inspection (including time to remove the fairing), at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of the inspection proposed by this AD on U.S. operators is 
estimated to be $36,720, or $120 per airplane.
    Since the manufacturer has not yet developed a modification 
commensurate with the requirements of this proposal, the FAA is unable 
at this time to provide specific information as to the number of work 
hours or cost of parts that would be required to accomplish the 
proposed modification. The proposed compliance time of 18 months should 
provide ample time for the development, approval, and installation of 
an appropriate modification. As indicated earlier in this preamble, the 
FAA specifically invites the submission of comments and other data 
regarding this economic aspect of the proposal.
    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 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-227-AD.

    Applicability: All Model A319, A320, and A321 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 (f) 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 of the fuel boost pump wire, which 
could result in wing structural damage, or fire and/or fuel vapor 
explosion, accomplish the following:

AFM Revision

    (a) Within 10 days after the effective date of this AD, revise 
the Limitations Section of the FAA-approved airplane flight manual 
(AFM) to include the following. This may be accomplished by 
inserting a copy of this AD into the AFM.

``FUEL SYSTEM

    If a circuit breaker for any wing tank fuel boost pump is 
tripped, do not reset.''

Inspection

    (b) Within 90 days after the effective date of this AD: For each 
fuel boost pump, remove the fairing located on the lower wing skin 
and perform a detailed visual inspection of the wiring and the 
adjacent structure along the length of the fairing. Inspect to 
detect damage to the wires including chafed, pinched, or melted 
wires, and any signs of arcing damage to the structure. When 
replacing the fairing following the inspection, take care not to 
pinch or otherwise damage the wiring of the fuel boost pumps; 
incorrect replacement of the fairing could cause damage to the 
wiring.
    (1) If any damage to the wire is detected: Prior to further 
flight, replace the wire with new wire in accordance with the 
manufacturer's Aircraft Wiring Manual, Standard Practices, Chapter 
20. Submit a report at the time specified and in accordance with 
paragraph (d) of this AD.
    (2) If any arcing damage to the structure is detected: Prior to 
further flight, repair the damaged structure in accordance with a 
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction Generale 
de l'Aviation Civile (DGAC), which is the airworthiness authority 
for France (or its delegated agent). For a repair method to be 
approved by the Manager, International Branch, ANM-116, as required 
by this paragraph, the Manager's approval letter must specifically 
reference this AD. Submit a report at the time specified and in 
accordance with paragraph (d) of this AD.

    Note 2: For the purposes of this AD, a detailed 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 mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (c) As of the effective date of this AD: For any fuel boost pump 
on which the circuit breaker of the pump has tripped, prior to 
further use of that pump, accomplish the inspection and applicable 
corrective actions specified by paragraph (b) of this AD.

Reporting Requirement

    (d) If any damage is detected during any inspection required by 
paragraphs (b) and (c) of this AD: Within 10 days after 
accomplishing that inspection, submit a report of the inspection 
findings to the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; fax (425) 227-1149. The report must include a 
description of the damage found, the airplane serial number, and the 
number of landings and flight hours on the airplane. Information 
collection requirements contained in this regulation have been

[[Page 51562]]

approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.

Modification

    (e) Within 18 months after the effective date of this AD, modify 
the fuel pump wire and fairing, in accordance with a method approved 
by the Manager, International Branch, ANM-116.

Alternative Methods of Compliance

    (f) 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. 
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 3: 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

    (g) 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.

    Issued in Renton, Washington, on August 18, 2000.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-21465 Filed 8-23-00; 8:45 am]
BILLING CODE 4910-13-P