[Federal Register Volume 62, Number 8 (Monday, January 13, 1997)]
[Proposed Rules]
[Pages 1695-1698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-682]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-101-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 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 series
airplanes. This proposal would require repetitive checks and testing of
certain equipment that regulates the flow of fuel from wing tank 2A to
the number 2 engine. This proposal also would require replacement of
this equipment with equipment that has been designed to prevent
incorrect installation; this replacement would be terminating action
for the repetitive equipment checks and tests. This proposal is
prompted by reports indicating that the incorrect installation of this
equipment has caused the flight crew to shut off,
[[Page 1696]]
rather than open, certain valves that regulate the flow of fuel from
between this tank and engine. The actions specified by the proposed AD
are intended to detect and rectify incorrect installations, which could
result in the flight crew inadvertently shutting off the flow of fuel
to the engine, and consequent engine failure during flight.
DATES: Comments must be received by February 24, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-101-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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; 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-101-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-101-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, has notified the FAA that an unsafe
condition may exist on certain Airbus A300 series airplanes. The DGAC
advises that it has received reports indicating that the number 2
engine on some airplanes had failed because fuel from wing tank 2A was
not reaching this engine. Subsequent investigation detected the
presence of a loose control knob for the isolation valve switch that
controls the flow of fuel between this wing tank and engine, and it was
determined that the knob had been incorrectly installed. Consequently,
when the control knob was turned to the ``open'' position, it was, in
fact, closed, thereby cutting off the fuel supply to the engine. This
condition, if not corrected, could result in the flight crew
inadvertently shutting off the supply of fuel to this engine, and
consequent failure of this engine during flight.
Explanation of Relevant Service Information
Airbus has issued A300 All Operator Telex (AOT) 28-03, dated June
6, 1991, which describes procedures for conducting a physical check of
the control knobs for the isolation valve and crossfeed valve control
unit 5QB, which is located on fuel panel 52 VU in the cockpit; and
procedures for testing this control unit to determine if the control
knob settings are correct.
The DGAC classified this AOT as mandatory and issued airworthiness
directive (C/N) 91-173-126(B) R1, dated February 19, 1992, in order to
assure the continued airworthiness of these airplanes in France.
Airbus also has issued Service Bulletin A300-28-055, Revision 3,
dated December 19, 1991, as amended by Service Bulletin Change Notice
3.A., dated March 16, 1992. This service bulletin describes procedures
for replacing the isolation valve and crossfeed valve control unit 5QB
with a modified control unit. This replacement is intended to make it
impossible to incorrectly install this control unit.
Airbus also has issued Service Bulletin A300-28-0061, Revision 1,
dated March 14, 1992, which describes procedures for replacing the
control knobs on the isolation valve and crossfeed valve control unit
5QB with new knobs. The replacement knobs are designed so that they can
only be installed the correct way.
Note: The Airbus service bulletins reference the following
service bulletins, issued by L'equipment et La Construction
Electrique (ECE), as additional sources of procedural service
information for performing these actions:
------------------------------------------------------------------------
ECE Service Bulletin Number Date
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28-191............................... July 26, 1982.
28-195............................... August 31, 1983.
28-196............................... August 31, 1983.
28-228............................... November 1, 1991.
------------------------------------------------------------------------
The DGAC classified the Airbus service bulletins as optional;
accomplishment of the procedures described in these service bulletins,
however, would terminate the repetitive equipment checks and tests,
required by French CN 91-173-126(B) R1.
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 States, the proposed AD would require repetitive checks
of the control knobs on isolation valve and crossfeed valve control
unit 5QB; and repetitive tests of this control unit. As terminating
action for these repetitive checks and tests, operators would be
required to replace these knobs and this control unit with knobs and a
control unit that have been modified. These modified items prevent the
knobs and control unit from being
[[Page 1697]]
installed incorrectly. The actions would be required to be accomplished
in accordance with the service documents described previously.
Differences Between the Proposed Rule and the French CN
Operators should note that, while the proposed AD would require the
replacement of the control knobs on the isolation valve and crossfeed
valve control unit with modified units, the French DGAC, as iterated in
its CN 91-173-126(B) R1, has provided for this replacement only as an
optional action. Both the FAA and the DGAC agree, however, that
accomplishment of the replacement would terminate the requirements for
repetitive checks and tests of this equipment.
In proposing to mandate these replacement actions, the FAA
considers that, unless the equipment is replaced with the modified
equipment, the possibility of incorrect installation will always exist
whenever normal maintenance is performed. The FAA has determined that
long-term continued operational safety will be better assured by
modifications or design changes to remove the source of the problem,
rather than by repetitive checks or tests. Long-term checks or tests
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 repetitive checks and tests,
has led the FAA to consider placing less emphasis on special procedures
and more emphasis on design improvements. The proposed replacement
requirement is in consonance with these considerations.
Cost Impact
The FAA estimates that 13 Airbus Model A300 series airplanes of
U.S. registry would be affected by this proposed AD.
It would take approximately 1 work hour per airplane to accomplish
each proposed check and test cycle, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of this proposed
requirement on U.S. operators is estimated to be $780, or $60 per
airplane, per check/test cycle.
It would take approximately 1 work hour per airplane to accomplish
the proposed replacement of the control knobs and control unit, at an
average labor rate of $60 per work hour. Required parts would cost
approximately $1,043 per airplane. Based on these figures, the cost
impact of the proposed replacement action on U.S. operators is
estimated to be $14,339, or $1,103 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 96-NM-101-AD.
Applicability: Model A300 series airplanes, as listed in the
Airbus service documents referenced in paragraphs (a), (b), and (c)
of this AD; 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 (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 the flight crew from inadvertently shutting off the
flow of fuel from wing tank 2A to the number 2 engine, due to the
incorrect installation of the isolation valve and crossfeed valve
control unit 5QB, and the consequent failure of the engine,
accomplish the following:
(a) For airplanes listed in Airbus A300 All Operator Telex (AOT)
28-03, dated June 6, 1991: Within 30 days after the effective date
of this AD, perform a check and functional test of the control knob
configurations for the isolation valve and crossfeed valve control
unit 5QB, in accordance with Airbus AOT 28-03, dated June 6, 1991.
(1) Repeat the check and test thereafter at intervals not to
exceed 500 hours time-in-service, and prior to further flight after
any maintenance action is performed on the control unit.
(2) Any unit that does not successfully pass the check/
functional test, must be repaired or otherwise rectified prior to
further flight, in accordance with the AOT.
(b) For airplanes listed in Airbus Service Bulletin A300-28-055,
Revision 3, dated December 19, 1991, as amended by Service Bulletin
Change Notice 3.A., dated March 16, 1992: Within 2 years after the
effective date of this AD, replace the crossfeed and isolation valve
control unit 5QB with a modified unit, in accordance Airbus Service
Bulletin A300-28-055, Revision 3, dated December 19, 1991, as
amended by Service Bulletin Change Notice 3.A.
Note 2: Airbus Service Bulletin A300-28-055, Revision 3,
references L'equipment et La Construction Electrique (ECE) Service
Bulletins 28-195 and 28-196, both dated August 31, 1983, as
additional sources of procedural information for replacement of the
control unit.
(c) For airplanes listed in Airbus Service Bulletin A300-28-
0061, Revision 1, dated March 14, 1992: Within 2 years after the
effective date of this AD, replace the control knobs on the
crossfeed and isolation valve control unit 5QB with new knobs, in
accordance with Airbus Service Bulletin A300-28-0061, Revision 1,
dated March 14, 1992.
Note 3: Airbus Service Bulletin A300-28-0061, Revision 1,
references ECE Service Bulletins 28-191, dated July 26, 1982, and
28-228, dated November 1, 1991, as additional sources of procedural
information for replacement of the control knobs.
(d) Accomplishment of both of the replacements specified in
paragraphs (b) and
[[Page 1698]]
(c) of this AD constitutes terminating action for the repetitive
checks and tests required by paragraph (a) of this AD.
(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, 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
Issued in Renton, Washington, on January 6, 1997.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-682 Filed 1-10-97; 8:45 am]
BILLING CODE 4910-13-U
