[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              
------------------------------------------------------------------------
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