[Federal Register Volume 63, Number 242 (Thursday, December 17, 1998)]
[Proposed Rules]
[Pages 69571-69573]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-33387]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-66-AD]
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: 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 and
A300-600 series airplanes. This proposal would require repetitive flow
checks of the hydraulic pump drain system to ensure that the system is
not clogged, and correction of any discrepancy. This proposal also
would require replacement of the existing magnetic seals of the
accessory gearbox assembly with new, improved seals. Replacement of
certain seals would terminate the requirement for repetitive flow
checks. This proposal also would require replacement of the engine
drain modules with drain manifolds. 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 contamination of the engine accessory gearbox
oil with hydraulic fluid, which could result in an in-flight engine
shutdown.
DATES: Comments must be received by January 19, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 96-NM-66-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 96-NM-66-AD.'' The postcard will be date stamped and
returned to the commenter.
[[Page 69572]]
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. 96-NM-66-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 Model A310 and A300-600 series
airplanes. The DGAC advises that it has received reports of
contamination of the engine oil on both of these airplane models.
Investigation revealed that the contamination was due to failure of the
seal of the green hydraulic pump shaft, which was caused by an increase
in the backflow pressure due to clogging of the hydraulic pump drain
system. Failure of the seal of the green hydraulic pump shaft, if not
corrected, could permit contamination of the engine accessory gearbox
oil, which could result in an in-flight engine shutdown.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A310-72-2020, Revision 2, dated
January 13, 1993 (for Airbus Model A310 series airplanes), and A300-72-
6016, Revision 2, dated January 13, 1993 (for Airbus Model A300-600
series airplanes). These service bulletins describe procedures for
repetitive flow checks of the hydraulic pump drain system to ensure
that the system is not clogged, and correction of any discrepancy.
Airbus also has issued Service Bulletins A310-72-2017, Revision 3,
dated August 6, 1993 (for certain Model A310 series airplanes), and
A300-72-6013, Revision 3, dated August 6, 1993 (for certain Model A300-
600 series airplanes). These service bulletins describe procedures for
replacing (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. Such replacement would reduce the
possibility for failure of the seal due to backflow pressure caused by
clogging of the hydraulic pump drain system. The replacement also would
eliminate the need for repetitive flow checks for certain airplanes.
Airbus also has issued Service Bulletins A310-72-2031, dated July
24, 1995, as revised by Change Notice O.A, dated October 12, 1995 (for
Model A310 series airplanes), and A300-72-6027, dated July 24, 1995
(for Model A300-600 series airplanes). These service bulletins describe
procedures for replacing (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. Such replacement would
reduce the possibility of failure of the seals due to backflow pressure
caused by clogging of the hydraulic pump drain system. The replacement
also would eliminate the need for repetitive flow checks for certain
airplanes.
Additionally, Airbus has issued 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 (for Model A310 series
airplanes); and A300-72-6025, Revision 1, dated June 22, 1995 (for
Model A300-600 series airplanes). These service bulletins describe
procedures for replacement of the engine drain modules with drain
manifolds. Such replacement will reduce the possibility of clogging of
the drain lines.
The DGAC classified these service bulletins as mandatory and issued
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, 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 UnitedStates.
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 64 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 3 work hours per airplane to accomplish
the proposed flow checks, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the flow checks
proposed by this AD on U.S. operators is estimated to be $11,520, or
$180 per airplane, per flow check cycle.
It would take approximately 24 work hours per airplane (12 work
hours per engine) to accomplish the proposed 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 would cost approximately $12,000 per airplane. Based on
these figures, the cost impact of this replacement proposed by this AD
on U.S. operators is estimated to be $860,160, or $13,440 per airplane.
It would 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 would cost approximately $13,200
per airplane. Based on these figures, the cost impact of this
replacement proposed 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 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,
[[Page 69573]]
on a substantial number of small entities under the criteria of the
RegulatoryFlexibility 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-66-AD.
Applicability: Model A310 and A300-600 series airplanes;
equipped with General Electric CF6-80C2 engines; except those
airplanes on which AirbusModifications 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.
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, dated August 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.
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.
Issued in Renton, Washington, on December 11, 1998.
Darrell M. Pederson, Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-33387 Filed 12-16-98; 8:45 am]
BILLING CODE 4910-13-U