[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