[Federal Register Volume 60, Number 227 (Monday, November 27, 1995)]
[Rules and Regulations]
[Pages 58219-58221]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28525]
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[[Page 58220]]
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-141-AD; Amendment 39-9440; AD 95-24-08]
Airworthiness Directives; Airbus Model A320 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 A320 series airplanes, that requires
replacement of the check valves of the thrust reverser with modified
valves on certain airplanes and the replacement of the manual control
valves of the thrust reverser with modified valves on certain other
airplanes. This amendment is prompted by recent engineering analysis,
which revealed that, if the non-return valve installed on the hydraulic
return line of the thrust reverser were to jam in the closed position,
it could cause pressurization of the Hydraulic Control Unit (HCU). The
actions specified by this AD are intended to prevent such
pressurization of the HCU due to jamming of the non-return valve in the
hydraulic return line, and consequent deployment of a thrust reverser
during flight; this condition, if not corrected, could adversely affect
the controllability of the airplane.
DATES: Effective December 27, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 27, 1995.
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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 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 A320 series
airplanes was published in the Federal Register on November 14, 1994
(59 FR 56433). That action proposed to require replacing the thrust
reverser check valves with modified valves on Engine 1 and Engine 2 of
airplanes equipped with CFM series engines. It also proposed to require
replacing the thrust reverser manual control valves with modified
valves on the Engine 1 and Engine 2 of airplanes equipped with
International Aero Engines (IAE) engines.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received.
Both commenters support the proposal.
Just prior to the publication of the proposal, Airbus issued
Service Bulletin A320-29-1048, Revision 2, dated September 1, 1994.
This revision is essentially identical to Revision 1, which was cited
in the proposal as the appropriate source of service information; it
differs only in the listing of the current operators of affected
airplanes. The FAA has revised the final rule to include Revision 2 of
the service bulletin as an additional source of service information.
Additionally, as a result of communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this long-standing
requirement.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 53 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 3 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $9,540, or
$180 per airplane. This cost impact figure 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.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13--[Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-24-08 Airbus: Amendment 39-9440. Docket 94-NM-141-AD.
[[Page 58221]]
Applicability: Model A320 series airplanes; as listed in Airbus
Industrie Service Bulletin A320-29-1048, Revision 1, dated December
4, 1992, and Revision 2, dated September 1, 1994; 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 use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent deployment of a thrust reverser during flight, which
could adversely affect the controllability of the airplane,
accomplish the following:
(a) Within 5 months after the effective date of the AD,
accomplish the requirements of paragraph (a)(1) or (a)(2) of this
AD, as applicable, in accordance with Airbus Industrie Service
Bulletin A320-29-1048, Revision 1, dated December 4, 1992, or
Revision 2, dated September 1, 1994.
(1) For airplanes equipped with CFM series engines: Replace the
Engine 1 and Engine 2 check valves of the thrust reverser in the
nacelle with modified valves as specified in the service bulletin.
(2) For airplanes equipped with International Aero Engines
(IAE): Replace the Engine 1 and Engine 2 manual control valves of
the thrust reverser on the pylon with modified valves as specified
in the service bulletin.
(b) 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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) 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.
(d) The replacements shall be done in accordance with the
following Airbus service bulletins, which contain the specified list
of effective pages:
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Service bulletin No. and date Page No. Revision level shown on page Date shown on page
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A320-29-1048, Revision 2, 1-5................................... 2..................................... September 1, 1994.
September 1, 1994. 7-8, 11,.............................. 1..................................... December 4, 1992.
6, 9-10, 12-15........................ Original.............................. April 7, 1992.
A320-29-1048, Revision 1, 1-3, 5, 7-8, 11,...................... 1..................................... December 4, 1992.
December 4, 1992. 4, 6, 9-10, 12-15..................... Original.............................. April 7, 1992.
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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.
(e) This amendment becomes effective on December 27, 1995.
Issued in Renton, Washington, on November 15, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-28525 Filed 11-24-95; 8:45 am]
BILLING CODE 4910-13-U
