[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:

----------------------------------------------------------------------------------------------------------------
 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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