[Federal Register Volume 60, Number 19 (Monday, January 30, 1995)]
[Proposed Rules]
[Pages 5599-5601]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-2178]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-98-AD]
Airworthiness Directives; Airbus Industrie Model A320-231 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Model A320-231 series
airplanes. This proposal would require 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
proposal 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 the proposed 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: Comments must be received by March 13, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-98-AD, 1601 Lind Avenue SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9 a.m. and 3 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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) 227-1320.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-98-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 94-NM-98-AD, 1601 Lind Avenue SW., Renton, Washington 98055-
4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, recently notified the FAA that an
unsafe condition may exist on certain Airbus Model A320-231 series
airplanes. The DGAC advises that, during regularly scheduled
maintenance of in-service airplanes, two operators found cracking
[[Page 5600]] of the engine fire extinguisher pipe. The cause of this
cracking has been attributed to mechanical vibration. Cracking of the
fire extinguisher agent distribution pipe between the bottle and the
nacelle could cause leakage of the fire extinguisher agent. Such
leakage, if not detected and corrected, could prevent the proper
distribution of the fire extinguishing agent within the nacelle in the
event of a fire.
Airbus has issued All Operators Telex (AOT) 26-11, dated January 3,
1994, which describes procedures for repetitive inspections to detect
leakage of fire extinguishing agent from the distribution piping of the
engine fire extinguishing system, and repair, if necessary. This AOT
also describes procedures for modification of the piping, which would
eliminate the need for the repetitive inspections.
Airbus has also issued Service Bulletin A320-26-1032, dated March
31, 1994, which describes inspection and repair procedures that are
identical to those described in the AOT. Additionally, Airbus issued
Service Bulletin A320-26-1031, dated March 31, 1994, which describes
modification procedures that are identical to those described in the
AOT. This modification involves replacement of the existing pipe with a
new pipe (Mod. 21457P1678), or repair of the pipes (Mod. 24253P3520).
The DGAC classified the AOT and the service bulletins as mandatory
and issued French airworthiness directive 94-058-053(B) R1, dated July
6, 1994, in order to assure the continued airworthiness of these
airplanes in France.
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would 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. The
actions would be required to be accomplished in accordance with the AOT
or service bulletin described previously.
As a result of recent 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 included in this notice to clarify this requirement.
The FAA estimates that 14 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 48 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would be
provided by the manufacturer at no cost to the operators. Based on
these figures, the total cost impact of the proposed 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 proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Airbus Industrie: 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 [[Page 5601]] 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
Secs. 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.
Issued in Renton, Washington, on January 24, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-2178 Filed 1-27-95; 8:45 am]
BILLING CODE 4910-13-U
