[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Proposed Rules]
[Pages 54249-54252]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26084]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-23-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A300-600, and A310
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 54250]]
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Airbus Model A300,
A300-600, and A310 series airplanes equipped with a welded auxiliary
power unit (APU) fuel feedline adapter. The existing AD currently
requires repetitive dye penetrant inspections to detect cracks,
rupture, or fuel leaks of the fuel feedline adapter, and replacement of
the adapter if necessary. That AD also provides for optional
terminating action for the repetitive inspections. This action would
require accomplishment of the previously optional terminating action.
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 fuel
leakage in the APU compartment, which could result in a fire in the APU
compartment.
DATES: Comments must be received by November 5, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-23-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-23-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-23-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On September 10, 1991, the FAA issued AD 91-20-07, amendment 39-
8041 (56 FR 47672, September 20, 1991), applicable to certain Airbus
Model A300, A300-600, and A310 series airplanes, to require repetitive
dye penetrant inspections to detect cracks, rupture, or fuel leaks of
the fuel feedline adapter, and replacement of the adapter, if
necessary. In addition, the AD requires verification of the correct
torque values of the starter motor cable terminals and the generator
cable terminals. That AD also provides for optional terminating action
for the repetitive inspections. These actions were prompted by a report
of a fuel leak in the auxiliary power unit (APU) compartment of a model
A300 series airplane, which caused a fire when the crew attempted to
start the APU. The requirements of that AD are intended to prevent a
fuel leak in the APU compartment; that condition, if not corrected,
could result in a fire in the APU compartment.
Actions Since Issuance of Previous AD
In the preamble to AD 91-20-07, the FAA indicated that the actions
required by that AD were considered ``interim action'' and that further
rulemaking action was being considered. The FAA now has determined that
further rulemaking action is indeed necessary, and this proposed AD
follows from that determination.
Explanation of New Service Information
The manufacturer has issued Airbus Service Bulletins A300-49-0049,
Revision 1; A300-49-6009, Revision 1; and A310-49-2012, Revision 1, all
dated November 28, 1991. Those service bulletins provide instructions
to replace the welded APU fuel feedline adapter with an improved non-
welded one-piece-body adapter. Accomplishment of this replacement is
intended to adequately address the identified unsafe condition.
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, classified these service bulletins
as mandatory and issued French airworthiness directive 98-480-269(B),
dated December 2, 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 supersede AD 91-20-07 to
require replacement of the welded APU fuel feedline adapter with an
improved non-welded one-piece-body adapter regardless of whether the
welded adapter has failed. In the existing AD this action is required
only if cracks, rupture, or fuel leaks are found during the inspection;
otherwise, this action is optional. The FAA has recently determined,
based on new information received, that the previously optional
terminating modification should be made mandatory. The proposed AD
would continue to require verification
[[Page 54251]]
of the correct torque values of the starter motor cable terminals and
the generator cable terminals, and corrective action if necessary. The
new replacement would be required to be accomplished in accordance with
the service bulletins described previously.
Cost Impact
There are approximately 165 airplanes of U.S. registry that would
be affected by this proposed AD.
The actions that are currently required by AD 91-20-07, and
retained in this proposed AD, take approximately 2 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the currently required
actions on U.S. operators is estimated to be $120 per airplane.
The new actions that are proposed in this AD action would take
approximately 2 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $274 per airplane. Based on these figures, the cost
impact of the proposed requirements of this AD on U.S. operators is
estimated to be $394 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 removing amendment 39-8041 (56 FR
47672, September 20, 1991), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 99-NM-23-AD. Supersedes AD 91-20-07,
Amendment 39-8041.
Applicability: Model A300, A300-600, and A310 series airplanes;
certificated in any category; equipped with an auxiliary power unit
(APU) fuel feedline adapter, P/N A4937021700000 (welded
configuration).
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 (e) 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 an APU compartment fire, accomplish the following:
Restatement of Requirements of AD 91-20-07, Amendment 39-8041
Repetitive Inspections
(a) Within 100 hours time-in-service after October 7, 1991 (the
effective date of AD 91-20-07, amendment 39-8041), and thereafter at
intervals not to exceed 400 hours time-in-service: Perform a dye
penetrant inspection to detect cracks, rupture or fuel leaks at the
weld of the fuel feedline adapter, in accordance with Airbus
Industrie All Operators Telex (AOT) 49-01, Issue 3, dated April 25,
1991. If cracks, rupture, or fuel leaks are found, replace the
adapter with an improved, non-welded one-piece-body adapter prior to
the next APU operation, or placard the APU inoperative until the
adapter is replaced with the improved adapter, in accordance with
Airbus Industrie Service Bulletin A300-49-0049, A300-49-6009, or
A310-49-2012; all dated July 12, 1991; as applicable.
(b) Within 100 hours time-in-service after October 7, 1991,
verify the correct torque values of the starter motor cable
terminals and the generator cable terminals in accordance with
Airbus Industrie All Operators Telex (AOT) 49-01, Issue 3, dated
April 25, 1991. Correct any torque value discrepancies prior to
further flight, in accordance with the AOT.
New Requirements of This AD
Installation
(c) Within 15 months after the effective date of this AD,
install an improved APU fuel feedline adapter in accordance with the
accomplishment instructions of Airbus Service Bulletin A300-49-0049,
Revision 1 (for Model A300 series airplanes); A300-49-6009, Revision
1 (for Model A300-600 series airplanes); or A310-49-2012, Revision 1
(for Model A310 series airplanes); all dated November 28, 1991; as
applicable. Such installation constitutes terminating action for the
requirements of this AD.
Spares
(d) As of the effective date of this AD, no person shall install
an APU fuel feedline adapter, P/N A4937021700000 (welded
configuration), on any airplane.
Alternative Methods of Compliance
(e) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(f) 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 3: The subject of this AD is addressed in French
airworthiness directive 98-480-269(B), dated December 2, 1998.
[[Page 54252]]
Issued in Renton, Washington, on September 30, 1999.
D.L. Riggin,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-26084 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-P
