[Federal Register Volume 64, Number 197 (Wednesday, October 13, 1999)]
[Rules and Regulations]
[Pages 55413-55414]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26275]
[[Page 55413]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-08-AD; Amendment 39-11366; AD 99-21-21]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-300 and A300-600R
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A310-300 and A300-600R series
airplanes, that requires 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 amendment is prompted by issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by this 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: Effective November 17, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 17, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of
the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Airbus Model A310-300 and
A300-600R series airplanes was published in the Federal Register on
July 20, 1999 (64 FR 38848). That action proposed to 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.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
Request To Determine Parts Availability
One commenter supports the intent of the proposal, assuming that
the necessary parts are available from the manufacturer. The FAA notes
that the Airbus service bulletins cited as the appropriate sources of
service information in the proposed AD state that kits will be
available 150 to 180 days after request by an operator. The FAA is not
aware of any difficulties with availability of the kits necessary to
accomplish the actions required by this AD. No change is made to the
final rule.
New Service Information
Since the issuance of the proposed AD, the manufacturer has issued
Airbus Service Bulletin A300-28-6035, Revision 03, dated August 5,
1999. This revision of the service bulletin adds references and
clarifies certain procedures and illustrations. The FAA has determined
that the changes do not add any additional burden to operators.
Paragraph (c) of this AD has been revised to cite Revision 03 of the
service bulletin as the appropriate source of service information. For
operators that may have previously accomplished the required actions in
accordance with Revision 1 or 2 of the service bulletin, ``NOTE 2'' of
the final rule has been revised to give credit for those actions. In
addition, the applicability has been revised to referenced Revision 03
of the service bulletin.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 102 Model A310-300 and A300-600R series
airplanes of U.S. registry will be affected by this AD, that it will
take approximately 20 work hours per airplane to accomplish the
required actions, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $5,710. Based on these figures,
the cost impact of the required 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 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 adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
[[Page 55414]]
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:
99-21-21 Airbus Industrie: Amendment 39-11366. 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 03, dated August 5, 1999) 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 03, dated August 5, 1999.
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 A300-28-6035, Revision 1, dated
December 4, 1992, or Revision 2, dated March 17, 1993, 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.
Incorporation by Reference
(g) The actions shall be done in accordance with Airbus Service
Bulletin A310-28-2058, Revision 2, dated February 22, 1995; and
Airbus Service A300-28-6035, Revision 03, dated August 5, 1999; as
applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may
be inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 4: The subject of this AD is addressed in French
airworthiness directive 98-354-256(B), dated September 9, 1998.
(h) This amendment becomes effective on November 17, 1999.
Issued in Renton, Washington, on October 4, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-26275 Filed 10-12-99; 8:45 am]
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