Federal Register, Volume 64 Issue 48 (Friday, March 12, 1999)

[Federal Register Volume 64, Number 48 (Friday, March 12, 1999)]
[Rules and Regulations]
[Pages 12244-12246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-5992]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-66-AD; Amendment 39-11070; AD 99-06-06]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310 and A300-600 Series
Airplanes Equipped With General Electric CF6-80C2 Engines

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 and A300-600 series airplanes,
that requires repetitive flow checks of the hydraulic pump drain system
to ensure that the system is not clogged, and correction of any
discrepancy. This amendment also requires replacement of the existing
magnetic seals of the accessory gearbox assembly with new, improved
seals. Replacement of certain seals terminates the requirement for
repetitive flow checks. This amendment also requires replacement of the
engine drain modules with drain manifolds. 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 contamination of the engine accessory gearbox
oil with hydraulic fluid, which could result in an in-flight engine
shutdown.

DATES: Effective April 16, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 16, 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 and
A300-600 series airplanes was published in the Federal Register on
December 17, 1998 (63 FR 69571). That action proposed to require
repetitive flow checks of the hydraulic pump drain system to ensure
that the system is not clogged, and correction of any discrepancy. That
action also proposed to require replacement of the existing magnetic
seals of the accessory gearbox assembly with new, improved

[[Page 12245]]

seals. Replacement of certain seals would terminate the requirement for
repetitive flow checks. That action also proposed to require
replacement of the engine drain modules with drain manifolds.

Comments

Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.

Request to Revise Cost Impact Information

One commenter states that the cost to be incurred by the
replacement of the engine drain modules with drain manifolds will
greatly exceed the cost specified in the proposal.
The FAA infers that the commenter is requesting that the cost
estimate be revised in the final rule. The FAA does not concur. The FAA
acknowledges that the cost impact information, below, describes only
the ``direct'' costs of the specific actions required by this AD. The
estimate of 16 hours necessary to accomplish the required actions was
provided to the FAA by the manufacturer, and represents the time
necessary to perform only the actions actually required by this AD. The
FAA recognizes that, in accomplishing the requirements of any AD,
operators may incur ``incidental'' costs in addition to the ``direct''
costs. The cost analysis in AD rulemaking actions, however, typically
does not include incidental costs, such as the time required to gain
access and close up; planning time; or time necessitated by other
administrative actions. Because incidental costs may vary significantly
from operator to operator, they are almost impossible to calculate.
Therefore, attempting to estimate such costs would be futile. No change
to the final rule is necessary.

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 as proposed.

Cost Impact

The FAA estimates that 64 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 3 work hours per airplane to accomplish
the required flow checks, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the flow checks
required by this AD on U.S. operators is estimated to be $11,520, or
$180 per airplane, per flow check cycle.
It will take approximately 24 work hours per airplane (12 work
hours per engine) to accomplish the required replacement of the
magnetic seals with spring-loaded seal and ring assemblies, at an
average labor rate of $60 per work hour. Required parts for this
replacement will cost approximately $12,000 per airplane. Based on
these figures, the cost impact of this replacement required by this AD
on U.S. operators is estimated to be$860,160, or $13,440 per airplane.
It will take approximately 16 work hours per airplane (8 work hours
per engine) to accomplish the replacement of the drain modules with
drain manifolds, at an average labor rate of $60 per work hour.
Required parts for this replacement will cost approximately $13,200 per
airplane. Based on these figures, the cost impact of this replacement
required by this AD on U.S. operators is estimated to be $906,240, or
$14,160 per airplane.
The cost impact figures discussed above are 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:

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:

99-06-06 Airbus Industrie: Amendment 39-11070. Docket 96-NM-66-AD.

Applicability: Model A310 and A300-600 series airplanes;
equipped with General Electric CF6-80C2 engines; except those
airplanes on which Airbus Modifications 8952 and 10401, or Airbus
Modification 10656 has been installed; 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 (f) 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 contamination of the engine accessory gearbox oil
with hydraulic fluid, which could result in an in-flight engine
shutdown, accomplish the following:
(a) For airplanes on which Airbus Modification 8952 has not been
installed: Within 30 days after the effective date of this AD,
perform a flow check of the hydraulic pump drain system to ensure
that the system is not clogged and, prior to further flight, correct
any discrepancies, in accordance with either paragraph (a)(1) or
(a)(2) of this AD, as applicable. Repeat the flow check thereafter
at intervals not to exceed 500 flight hours until the modification
required by paragraph (b) of this AD is accomplished.
(1) For Model A310 series airplanes: Perform the flow checks and
correct any discrepancy in accordance with Airbus Service Bulletin
A310-72-2020, Revision 2, dated January 13, 1993.

[[Page 12246]]

Note 2: Flow checks and corrective actions accomplished prior to
the effective date of this AD in accordance with the original issue
of Airbus Service Bulletin A310-72-2020, dated September 14, 1992,
or Revision 1, dated November 25, 1992, are considered acceptable
for compliance with paragraph (a)(1) of this AD.

(2) For Model A300-600 series airplanes: Perform the flow checks
and correct any discrepancy in accordance with Airbus Service
Bulletin A300-72-6016, Revision 2, dated January 13, 1993.

Note 3: Flow checks and corrective actions accomplished prior to
the effective date of this AD in accordance with Airbus Service
Bulletin A300-72-6016, dated September 14, 1992, are considered
acceptable for compliance with paragraph (a)(2) of this AD.

(b) For airplanes on which Airbus Modification 8952 has not been
installed and that are not operating under extended range twin-
engine operations (ETOPS): Within 3 months after the effective date
of this AD, replace (on both engines) the existing magnetic seal of
the green hydraulic system on the accessory gearbox assembly with a
new, improved spring-loaded seal and ring assembly, in accordance
with either paragraph(b)(1) or (b)(2) of this AD, as applicable.
Accomplishment of this replacement constitutes terminating action
for the repetitive flow check requirements specified in paragraph
(a) of this AD.
(1) For Model A310 series airplanes: Accomplish the replacement
in accordance with Airbus Service Bulletin A310-72-2017, Revision 3,
dated August 6, 1993.
(2) For Model A300-600 series airplanes: Accomplish the
replacement in accordance with Airbus Service Bulletin A300-72-6013,
Revision 3, datedAugust 6, 1993.
(c) For airplanes on which Airbus Modification 8952 has not been
installed and that are operating under ETOPS: Within 10 days after
the effective date of this AD, replace (on both engines) the
existing magnetic seal of the green hydraulic system on the
accessory gearbox assembly with a new, improved spring-loaded seal
and ring assembly, in accordance with either paragraph (c)(1) or
(c)(2) of this AD, as applicable. Accomplishment of this replacement
constitutes terminating action for the repetitive flow check
requirements specified in paragraph (a) of this AD.
(1) For Model A310 series airplanes: Accomplish the replacement
in accordance with Airbus Service Bulletin A310-72-2017, Revision 3,
dated August 6, 1993.
(2) For Model A300-600 series airplanes: Accomplish the
replacement in accordance with Airbus Service Bulletin A300-72-6013,
Revision 3, dated August 6, 1993.
(d) For airplanes on which Airbus Modifications 8952 and 10401
have not been installed: Within 18 months after the effective date
of this AD, replace (on both engines) the existing magnetic seals of
the yellow and blue hydraulic systems, the starter, and the
integrated drive generator on the accessory gearbox assembly with
new, improved spring-loaded seal and ring assemblies, in accordance
with either paragraph (d)(1) or (d)(2) of this AD, as applicable.
Accomplishment of this replacement constitutes terminating action
for the repetitive flow check requirements specified in paragraph
(a) of this AD.
(1) For Model A310 series airplanes: Accomplish the replacement
in accordance with Airbus Service Bulletin A310-72-2031, dated July
24, 1995, as revised by Change Notice O.A., dated October 12, 1995.
(2) For Model A300-600 series airplanes: Accomplish the
replacement in accordance with Airbus Service Bulletin A300-72-6027,
dated July 24, 1995.
(e) For airplanes on which Airbus Modification 10656 has not
been installed: Within 5 years after the effective date of this AD,
replace the drain modules with drain manifolds in accordance with
either paragraph (e)(1) or (e)(2) of this AD, as applicable.
(1) For Model A310 series airplanes: Accomplish the replacement
in accordance with Airbus Service Bulletin A310-72-2029, Revision 1,
dated June 22, 1995, as revised by Change Notice 1.A., dated March
13, 1997, and Change Notice 1.B., dated June 16, 1997.
(2) For Model A300-600 series airplanes: Accomplish the
replacement in accordance with Airbus Service Bulletin A300-72-6025,
Revision 1, dated June 22, 1995.
(f) 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.

(g) 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.
(h) The actions shall be done in accordance with the following
Airbus Service Bulletins, as applicable, which contain the specified
effective pages:

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Service bulletin referenced Revision level shown on
and date Page number page Date shown on page
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A310-72-2020, Revision 2, 1-3....................... 2......................... January 13, 1993.
January 13, 1993.
5-9....................... Original.................. September 14, 1992.
A300-72-6016, Revision 2, 1, 2...................... 2......................... January 13, 1993.
January 13, 1993.
3-7....................... Original.................. September 14, 1992.
A310-72-2017, Revision 3, 1-9....................... 3......................... August 6, 1993.
August 6, 1993.
A300-72-6013, Revision 3, 1-9....................... 3......................... August 6, 1993.
August 6, 1993.
A310-72-2031, July 24, 1995. 1-11...................... Original.................. July 24, 1995.
A310-72-2031, Change Notice 1......................... Original.................. October 12, 1995.
O.A., October 12, 1995.
A300-72-6027, July 24, 1995. 1-11...................... Original.................. July 24, 1995.
A310-72-2029, Revision 1, 1, 5, 6................... 1......................... June 25, 1995.
June 25, 1995.
2-4, 7-9.................. Original.................. December 14, 1994.
A310-72-2029, Change Notice 1......................... Original.................. March 13, 1997.
1.A., March 13, 1997.
A310-72-2029, Change Notice 1-2....................... Original.................. June 16, 1997.
1.B., June 16, 1997.
A300-72-6025, Revision 1, 1, 4...................... 1......................... June 22, 1995.
June 22, 1995.
2, 3, 5-7................. Original.................. December 14, 1994.
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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 5: The subject of this AD is addressed in French
airworthiness directives 92-230-135(B) R1, dated October 13, 1993;
95-183-185(B), dated September 27, 1995; and 95-184-186(B), dated
September 27, 1995.

(i) This amendment becomes effective on April 16, 1999.

Issued in Renton, Washington, on March 4, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-5992 Filed 3-11-99; 8:45 am]
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