[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]
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