[Federal Register Volume 60, Number 115 (Thursday, June 15, 1995)]
[Rules and Regulations]
[Pages 31386-31387]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-13506]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-98-AD; Amendment 39-9254; AD 95-12-04]


Airworthiness Directives; Airbus Industrie Model A320-231 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 Model A320-231 series airplanes, that requires 
repetitive functional checks to detect leakage of the distribution 
piping of the engine fire extinguishing system, and repair, if 
necessary; and modification of the piping, which would terminate the 
inspection requirements. This amendment is prompted by reports of 
cracking of the engine fire extinguisher pipe, which resulted in 
leakage of the fire extinguisher agent. The actions specified by this 
AD are intended to prevent leakage of the fire extinguishing agent, 
which could prevent the proper distribution of the agent within the 
nacelle in the event of a fire.

DATES: Effective July 17, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 17, 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: Stephen Slotte, 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 A320-231 
series airplanes was published in the Federal Register on January 30, 
1995 (60 FR 5599). That action proposed to require repetitive visual 
inspections to detect leakage of the distribution piping of the engine 
fire extinguishing system, and repair, if necessary; and modification 
of the piping, which would terminate the inspection requirements.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air [[Page 31387]] safety and 
the public interest require the adoption of the rule as proposed.
    The FAA estimates that 14 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 48 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 
total cost impact of the AD on U.S. operators is estimated to be 
$40,320, or $2,880 per airplane.
    The total cost impact figure discussed above 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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-12-04  Airbus Industrie: Amendment 39-9254. Docket 94-NM-98-AD.

    Applicability: Model A320-231 series airplanes; manufacturer's 
serial numbers (MSN) 028, 035, 037, 038, 043, 045 through 058 
inclusive, 064 through 067 inclusive, 074 through 077 inclusive, 080 
through 082 inclusive, 089 through 092 inclusive, 095, and 096; 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (c) 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 leakage of the fire extinguishing agent, which could 
prevent the proper distribution of the agent within the nacelle in 
the event of a fire, accomplish the following:
    (a) Within 500 flight hours after the effective date of this AD, 
perform a functional check to detect leakage of fire extinguishing 
agent from the distribution piping of the engine fire extinguishing 
system, in accordance with either Airbus All Operators Telex (AOT) 
26-11, dated January 3, 1994, or Airbus Service Bulletin A320-26-
1032, dated March 31, 1994.
    (1) If no leakage is found, or if leakage is within the limits 
specified in the AOT or the service bulletin, repeat the functional 
check thereafter at intervals not to exceed 500 flight hours.
    (2) If any leakage is beyond the limits specified in the AOT or 
the service bulletin, prior to further flight, modify the piping in 
accordance with either the AOT or Airbus Service Bulletin A320-26-
1031, dated March 31, 1994.
    (b) Within 4,000 flight hours after the effective date of this 
AD, modify the piping in accordance with either Airbus AOT 26-11, 
dated January 3, 1994, or Airbus Service Bulletin A320-26-1031, 
dated March 31, 1994. Accomplishment of this modification 
constitutes terminating action for the repetitive functional check 
requirements of this AD.
    (c) 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.

    (d) 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.
    (e) The functional checks and modification shall be done in 
accordance with either Airbus AOT 26-11, dated January 3, 1994, or 
Airbus Service Bulletin A320-26-1031, dated March 31, 1994; or 
Airbus Service Bulletin A320-26-1032, dated March 31, 1994. 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.
    (f) This amendment becomes effective on July 17, 1995.

    Issued in Renton, Washington, on May 26, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-13506 Filed 6-14-95; 8:45 am]
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