[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]
BILLING CODE 4910-13-U
