[Federal Register Volume 64, Number 138 (Tuesday, July 20, 1999)]
[Proposed Rules]
[Pages 38848-38850]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-18411]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-08-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-300 and A300-600R
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 A310-300 and
A300-600R series airplanes. This proposal would require installation of
a new cover assembly, associated new drain and vent pipework, and a new
electrical harness on the trimmable horizontal stabilizer for the fuel
tank water scavenge motive pump. 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 from the seal of the water scavenge
pumps, which, if not corrected, could result in leakage of fuel into
fuselage areas not designed for fuel, and consequent potential for fuel
to be in contact with a fuel ignition source.
DATES: Comments must be received by August 19, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-08-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-08-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-08-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, notified the FAA that an unsafe
condition may exist on certain Airbus Model A310-300 and A300-600R
series airplanes. The DGAC advises that it has received reports of
excessive water and ice build-up in the fuel tanks, particularily in
the trim tank and inner tanks. This was occurring increasingly during
extended twin engine operations (ETOPS), when turn around times were
short, and water drainage was ineffective due to frozen drain valves.
In an attempt to reduce the need for manual sumping of the tanks, a
water scavenge system was developed. The scavenge system is powered by
a dedicated pump installed inside the tank, without canister type
outside access. The pumps are located on the rear spar of the wing and
on the horizontal stabilizer front spar in the trim tank. These pumps
provide the motive force for new jet pumps installed in the tanks. The
jet pumps will continually pick up water from the low points in the
tanks, and therefore, prevent any ice build-up.
It was found that the trim tank scavenge pump installations did not
have a double seal between the tank and fuselage section 19. If the
seal on this optionally installed pump does not perform its function,
the possibility exists that without a second, normally redundant seal,
leakage could occur into the fuselage section 19. This condition, if
not corrected, could result in leakage of fuel into fuselage areas not
designed for fuel, and consequent potential for fuel to be in contact
with a fuel ignition source.
[[Page 38849]]
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-28-6035, Revision 2, dated
March 17, 1993 (for Model A300-600R series airplanes), and Service
Bulletin A310-28-2058, Revision 2, dated February 22, 1995 (for Model
A310-300 series airplanes), which describe procedures for installation
of a new cover assembly, associated new drain and vent pipework, and a
new electrical harness on the trimmable horizontal stabilizer for the
fuel tank water scavenge motive pump. The DGAC classified these service
bulletins as mandatory and issued French airworthiness directive 98-
354-256(B), dated September 9, 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 require accomplishment of
the actions specified in the service bulletins described previously.
Cost Impact
The FAA estimates that 102 Model A310-300 and A300-600R series
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 20 work hours per airplane to accomplish
the proposed actions, and that the average labor rate is $60 per work
hour. Required parts would cost approximately $5,710. Based on these
figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $704,820, or $6,910 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 99-NM-08-AD.
Applicability: Model A310-300 and A300-600R series airplanes,
except those airplanes on which Airbus Modification 10003 (reference
Airbus Service Bulletin A310-28-2058, Revision 2, dated February 22,
1995, or A300-28-6035, Revision 2, dated March 17, 1993) has been
accomplished; 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 fuel leakage from the seal of the water scavenge
pumps, which, if not corrected, could result in leakage of fuel into
fuselage areas not designed for fuel, and consequent potential for
fuel to be in contact with a fuel ignition source, accomplish the
following:
Model A310-300 Series Airplanes: Modification
(a) For Model A310-300 series airplanes on which a water
scavenge pump has been installed prior to the effective date of this
AD, in accordance with Airbus Modification 8679 (reference Airbus
Service Bulletin A310-28-2049, dated February 6, 1992; Revision 1,
dated June 17, 1992; Revision 2, dated June 3, 1994; or Revision 3,
dated April 5, 1996): Within 18 months after the effective date of
this AD, install a new cover assembly, associated new drain and vent
pipework, and a new electrical harness, in accordance with Airbus
Service Bulletin A310-28-2058, Revision 2, dated February 22, 1995.
(b) For Model A310-300 series airplanes on which a water
scavenge pump is installed after the effective date of this AD, in
accordance with Airbus Modification 8679 (reference Airbus Service
Bulletin A310-28-2049, dated February 6, 1992; Revision 1, dated
June 17, 1992; Revision 2, dated June 3, 1994; or Revision 3, dated
April 5, 1996): The actions required by paragraph (a) of this AD
must be accomplished simultaneously with Airbus Modification 8679.
Model A300-600R Series Airplanes: Modification
(c) For Model A300-600R series airplanes on which a water
scavenge pump has been installed prior to the effective date of this
AD, in accordance with Airbus Modification 8679 (reference Airbus
Service Bulletin A300-28-6028, dated February 6, 1992; Revision 1,
dated June 5, 1992; Revision 2, dated October 14, 1993; Revision 3,
dated April 5, 1996; or Revision 4, dated April 3, 1997): Within 18
months after the effective date of this AD, install a new cover
assembly, associated new drain and vent pipework, and a new
electrical harness, in accordance with Airbus Service A300-28-6035,
Revision 2, dated March 17, 1993.
Note 2: Installation of a new cover assembly, associated new
drain and vent pipework, and a new electrical harness in accordance
with Airbus Service Bulletin
[[Page 38850]]
A300-28-6035, Revision 1, dated December 4, 1992, is considered
acceptable for compliance with the requirements specified in
paragraph (c) of this AD.
(d) For Model A300-600R series airplanes on which a water
scavenge pump is installed after the effective date of this AD, in
accordance with Airbus Modification 8679 (reference Airbus Service
Bulletin A300-28-6028, dated February 6, 1992; Revision 1, dated
June 5, 1992; Revision 2, dated October 14, 1993; Revision 3, dated
April 5, 1996; or Revision 4, dated April 3, 1997): The actions
required by paragraph (c) of this AD must be accomplished
simultaneously with Airbus Modification 8679.
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 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
(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 4: The subject of this AD is addressed in French
airworthiness directive 98-354-256(B), dated September 9, 1998.
Issued in Renton, Washington, on July 14, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-18411 Filed 7-19-99; 8:45 am]
BILLING CODE 4910-13-P
