[Federal Register Volume 62, Number 17 (Monday, January 27, 1997)]
[Proposed Rules]
[Pages 3836-3837]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-1619]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-169-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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 A310 series
airplanes. This proposal would require modification of the wiring for
certain hydraulic fire shutoff valves to the right engine to prevent
chafing. This proposal is prompted by reports indicating that a circuit
breaker to wiring in the right engine had tripped on two airplanes, the
cause of which has been attributed to chafing of the associated wire
bundle. The actions specified by the proposed AD are intended to
prevent this wiring from chafing which, if not corrected, could lead to
short circuiting of this wiring and the consequent inability to close
the hydraulic fire shutoff valves to the right engine in the event of
fire.
DATES: Comments must be received by March 4, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-169-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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2589; fax (206) 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 96-NM-169-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-103, Attention: Rules
Docket No. 96-NM-169-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, recently notified the FAA that an
unsafe condition may exist on certain Model A310 series airplanes. The
DGAC advises that it has received reports indicating that circuit
breaker 103GD had tripped on two airplanes. A subsequent technical
investigation determined that chafing of wire bundle 628VB against fire
shutoff valve 2GD had caused this circuit breaker to trip. This valve
is one of the valves that prevents the flow of hydraulic fluid to the
right engine in the event of a fire. Investigators also noted the
potential for wire bundles 626VB and 632VB to chafe. Chafing of these
wire bundles, if not prevented, could lead to short circuiting of this
wiring and the consequent inability to close the hydraulic fire shutoff
valves to the right engine in the event of fire.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A310-24-2065, dated November 30,
1995, and Revision 1, dated April 19, 1996, which describe procedures
for modification of the wiring for certain hydraulic fire shutoff
valves to the right engine to prevent chafing. This modification
entails the installation of protective conduits for wire bundles 626VB
and 628VB; re-routing these wire bundles and wire bundle 632VB; and
changing the arrangement of the clamps that attach all of these wire
bundles to the airplane structure. The DGAC classified this service
bulletin as mandatory and issued French airworthiness directive (C/N)
96-021-196(B), dated January 31, 1996, in order to assure the continued
airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France and is 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
[[Page 3837]]
States, the proposed AD would require modification of the wiring for
certain hydraulic fire shutoff valves to the right engine to prevent
chafing. This modification entails the installation of protective
conduits for wire bundles 626VB and 628VB; re-routing these wire
bundles and wire bundle 632VB; and changing the arrangement of the
clamps that attach all of these wire bundles to the airplane structure.
The actions would be required to be accomplished in accordance with the
service bulletins described previously.
Cost Impact
The FAA estimates that 20 Airbus Model A310 series airplanes of
U.S. registry would be affected by this proposed AD.
It is estimated that it would take approximately 4 work hours per
airplane to accomplish the proposed actions, at an average labor rate
of $60 per work hour. Required parts would be provided by the
manufacturer at no cost to operators. Based on these figures, the cost
impact of the proposed AD on U.S. operators is estimated to be $4,800,
or $240 per airplane.
The cost impact figure discussed above is 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 96-NM-169-AD.
Applicability: Model A310 series airplanes as listed in Airbus
Service Bulletin A310-24-2065, November 30, 1995, and Revision 1,
dated April 19, 1996; certificated in any category.
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 wire bundles for the hydraulic fire
shutoff valves to the right engine, which could lead to short
circuiting of this wiring and the consequent inability to close
these valves in the event of fire, accomplish the following:
(a) Within 60 days after the effective date of this AD, modify
the wiring for the hydraulic fire shutoff valves in wire bundles
626VB and 628VB, and modify wire bundle 632VB, in accordance with
Airbus Service Bulletin A310-24-2065, dated November 30, 1995, or
Revision 1, dated April 19, 1996, as applicable.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) 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 January 16, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-1619 Filed 1-24-97; 8:45 am]
BILLING CODE 4910-13-U
