[Federal Register Volume 61, Number 13 (Friday, January 19, 1996)]
[Rules and Regulations]
[Pages 1274-1276]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-258]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-229-AD; Amendment 39-9483; AD 96-01-07]
Airworthiness Directives; Airbus Model A330 and A340 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 A330 and A340 series airplanes. This
action requires a one-time inspection to verify that the attachment
screws at a pressure switch located on the trim tank fuel transfer line
are properly torqued, and that lockwires are installed. This amendment
is prompted by reports of loose screws and missing lockwires at this
attachment. The actions specified in this AD are intended to prevent
loose or missing screws, which could allow fuel
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to leak from the pressure switch connection; if a leak were to occur
during flight with a full trim tank, there would be no warning
indication to the flight crew, and the airplane may not have enough
fuel to complete the flight safely.
DATES: Effective February 5, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 5, 1996.
Comments for inclusion in the Rules Docket must be received on or
before March 19, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-229-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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2589; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile
(DGAC), which is the airworthiness authority for France, has notified
the FAA that an unsafe condition may exist on certain Airbus Model A330
and A340 series airplanes. The DGAC advises that, on several production
airplanes prior to delivery, the two screws that are used to install
pressure switch 7QC, which is located on the trim tank fuel transfer
line, were found to be loose. In two cases, the screws were neither
lockwired nor properly torqued. In two other cases, lockwires were
present, but the screws were not torqued to the correct value. This
condition, if not corrected, could allow fuel to leak from the pressure
switch connection. If a leak were to occur during flight with a full
trim tank, there would be no warning indication to the flight crew, and
the airplane may not have enough fuel to complete the flight safely.
Airbus has issued All Operators Telex 28-05, dated December 28,
1994, which describes procedures for a one-time inspection of the
attachment screws of the pressure switch at the 7QC connection for
correct torque value and proper lockwiring. The AOT also provides
instructions for correcting these discrepancies if identified during
the inspection. The DGAC classified this AOT as mandatory and issued
French airworthiness directive (CN) 95-009-007(B) (applicable to Model
A330 series airplanes), and CN 95-010-015(B) (for Model A340 series
airplanes), both dated January 18, 1995, 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 registered
in the United States, this AD is being issued to prevent fuel leakage
from the trim tank fuel transfer line due to loose attachment screws at
the pressure switch 7QC connection. This AD requires a one-time
inspection of the attachment screws of the pressure switch at the 7QC
connection for correct torque value and proper lockwiring, and
correction of any discrepancies found. The actions are required to be
accomplished in accordance with the Airbus AOT described previously.
None of the Model A330 or A340 series airplanes affected by this
action are 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 1 work hour to
accomplish the required actions, at an average labor charge of $60 per
work hour. Based on these figures, the cost impact of this AD would be
$60 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-229-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 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
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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:
96-01-07 Airbus: Amendment 39-9483. Docket 95-NM-229-AD.
Applicability: Model A330 series airplanes having manufacturer's
serial number (MSN) 030, 037, 045, 054, 055, 059, 060, 062, or 070;
and Model A340 series airplanes having MSN 005 through 009
inclusive, 011, 013 through 016 inclusive, 018 through 029
inclusive, 031, 032, 033, 035, 036, 038, 039, 040, 043, 046 through
049 inclusive, 051, 052, 053, 057, 058, 063, 074, 076, or 082;
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 (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 fuel leakage from the trim tank fuel transfer line
due to loose attachment screws at the pressure switch 7QC
connection, accomplish the following:
(a) Within 100 flight hours after the effective date of this AD,
inspect the attachment screws at the pressure switch 7QC connection
for proper torque value and lockwiring, in accordance with Airbus
All Operators Telex (AOT) 28-05, dated December 28, 1994.
(1) If any screw is not torqued to the correct value specified
in the AOT, prior to further flight, torque the screw to that value.
(2) If any lockwire is missing, prior to further flight, install
a lockwire in accordance with the AOT.
(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 inspection and correction of discrepancies shall be done
in accordance with Airbus All Operator Telex 28-05, dated December
28, 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.
(e) This amendment becomes effective on February 5, 1996.
Issued in Renton, Washington, on January 3, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-258 Filed 1-18-96; 8:45 am]
BILLING CODE 4910-13-U
