[Federal Register Volume 60, Number 113 (Tuesday, June 13, 1995)]
[Rules and Regulations]
[Pages 31067-31069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-13888]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-65-AD; Amendment 39-9261; AD 95-12-11]
Airworthiness Directives; Airbus Model A340-211 and -311 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A340 series airplanes. This action
requires a one-time inspection of the fuel flow from the main fuel
supply hose/tube assembly, and repair, if necessary. This amendment is
prompted by a report of a low pressure fuel valve found with the
internal thermal relief valve assembled in the wrong position on one
airplane. The actions specified in this AD are intended to prevent
overpressurization of the fuel supply line due to the incorrect
positioning of the internal thermal relief valve. Such
overpressurization could cause the fuel pipe coupling to separate and
allow fuel to leak into the engine pylon, thus posing a fire hazard.
DATES: Effective June 28, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 28, 1995.
Comments for inclusion in the Rules Docket must be received on or
before August 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-65-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
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 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.
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: The Direction Generale de l'Aviation Civile
(DGAC), which is the airworthiness [[Page 31068]] authority for France,
recently notified the FAA that an unsafe condition may exist on certain
Airbus Model A340-211 and -311 series airplanes. The DGAC advises that
there has been a report indicating that a low pressure (LP) fuel valve,
part number HTE 900212, has been found on one test airplane with the
internal thermal relief valve assembled in the wrong position.
Additionally, an internal seal associated with this valve assembly was
found to be installed in the wrong position.
The LP fuel valve is installed in the LP fuel supply line for each
engine. Each LP fuel valve isolates its respective engine from the fuel
supply at the front spar. The internal thermal relief valve is
installed in the LP fuel valve to give protection against
overpressurization of the supply line. This relief valve is set to
release fuel from the engine side of the fuel supply line whenever
overpressurization occurs and the LP fuel valve is in the closed
position.
If the thermal relief valve and/or the internal seal is not
installed in the correct position, overpressurization can occur when
the engine is shut down. In the worst case, an overpressurization
condition can lead to separation of a fuel pipe coupling and a
subsequent leakage of fuel in the engine pylon. This situation would
pose a fire hazard.
Investigation has revealed that the incorrect installation of the
thermal relief valve and associate sealant occurred during production
of certain airplanes. Production procedures have now been changed to
ensure that all future LP valve assemblies are correctly installed.
Airbus Industrie has issued Service Bulletin A340-28-4029, Revision
1, dated September 14, 1994, which describes procedures for a one-time
inspection to determine if the internal thermal relief valve is
installed correctly. The inspection consists of a detailed visual
inspection of the flow of fuel from the main fuel supply hose/tube
assembly. If the flow of fuel is continuous, the LP fuel valve and/or
the internal seal must be replaced, and additional repairs performed if
fuel pipes have been damaged. The DGAC classified this service bulletin
as mandatory and issued French Airworthiness Directive (CN) 94-210-
011(B), dated September 14, 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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) 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, this AD is
being issued to prevent overpressurization of the fuel supply line due
to the incorrect positioning of the internal thermal relief valve. Such
overpressurization could cause the fuel pipe coupling to separate and
allow fuel to leak into the engine pylon, thus posing a fire hazard.
This AD requires a detailed visual inspection of the flow of fuel
from the main fuel supply hose/tube assembly and, if necessary,
replacement of the LP fuel valve and/or the internal seal and
additional repairs. The actions are required to be accomplished in
accordance with the 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 AD to clarify this long-standing requirement.
There currently are no Model A340 series airplanes on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 6 work hours to
accomplish the required inspection, at an average labor charge of $60
per work hour. Based on these figures, the total cost impact of this AD
would be $360 per airplane.
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
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 under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-65-AD.'' The postcard will be date stamped and
returned to the commenter.
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 [[Page 31069]] 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:
95-12-11 Airbus: Amendment 39-9261. Docket 95-NM-65-AD.
Applicability: Model A340-211 and -311 series airplanes; having
manufacturer's serial number (MSN) 005 through 019 inclusive;
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 (d) 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 overpressurization of the fuel supply line due to the
incorrect positioning of the internal thermal relief valve, which
could cause the fuel pipe coupling to separate and allow fuel to
leak into the engine pylon, thus posing a fire hazard, accomplish
the following:
(a) Within 450 hours time-in-service after the effective date of
this AD, perform a detailed visual inspection of the flow of fuel
from the main fuel supply hose/tube assembly, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A340-28-4029,
Revision 1, dated September 14, 1994.
(b) If the flow of fuel is not continuous, no further action is
required by this AD.
Note 2: Single drops of fuel are acceptable.
(c) If the flow of fuel is continuous, prior to further flight,
perform the applicable replacement and repair procedures specified
in Paragraph 2.C., ``Repair,'' of the Accomplishment Instructions of
Airbus Service Bulletin A340-28-4029, Revision 1, dated September
14, 1994.
(d) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(e) 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.
(f) The inspection, replacement, and repair procedures shall be
done in accordance with Airbus Service Bulletin A340-28-4029,
Revision 1, dated September 14, 1994, which contains the following
list of effective pages:
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Revision level shown on
Page No. page Date shown on page
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1-5, 7-11, 40-45, 47-50 1...................... September 14, 1994.
6, 12-39, 46, 51-54.... Original............... August 12, 1994.
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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.
(g) This amendment becomes effective on June 28, 1995.
Issued in Renton, Washington, on June 1, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-13888 Filed 6-12-95; 8:45 am]
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