[Federal Register Volume 61, Number 46 (Thursday, March 7, 1996)]
[Rules and Regulations]
[Pages 9096-9098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-5079]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-34-AD; Amendment 39-9531; AD 96-05-05]
Airworthiness Directives; Airbus Model A330 and A340 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330 and A340 series airplanes. This
action requires replacement of the inlet filter in the spoiler servo-
controls and installation of a lockwire. This amendment is prompted by
reports of leakage of hydraulic fluid at the inlet filter plug of the
spoiler actuator as a result of inadequate torque of the filter plug,
and reports of broken lockwires. The actions specified in this AD are
intended to prevent loss of hydraulic fluid to the extent that a
complete failure of the associated hydraulic system could occur. Such a
loss, when combined with other hydraulic system failures, could reduce
the controllability of the airplane.
DATES: Effective March 22, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 22, 1996.
Comments for inclusion in the Rules Docket must be received on or
before May 6, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-34-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, recently
notified the FAA that an unsafe condition may exist on certain Airbus
Model A330 and A340 series airplanes. The DGAC advises that there have
been several reports of external leakage of hydraulic fluid on these
airplanes due to loose filter plugs of the spoiler actuators. Almost
all of the inspected plugs were found to have a torque value below the
necessary 69.1 Nm, and had to be re-tightened. Additionally, there have
been at least four reports of broken lockwires found on these
components. This condition, if not corrected, could result in loss of
hydraulic fluid to the extent that a complete failure of the associated
hydraulic system could occur. Such a failure, when combined with other
hydraulic system failures, could reduce the controllability of the
airplane.
[[Page 9097]]
Airbus Industrie has issued Service Bulletin A330-27-3034 (for
Model A330 series airplanes) and Service Bulletin A340-27-4041 (for
Model A340 series airplanes), both dated June 21, 1995. These service
bulletins describe procedures for replacement of the inlet filter in
each of the 12 spoiler servo-controls located at surface position 1 to
6 (left-hand and right-hand). The service bulletins also describe
procedures for securing these filters with lockwires. (These service
bulletins also refer to Feinmechanische Werke Mainz Service Bulletin
MZ4306000-27-001 for detailed installation instructions.) The actions
specified in these service bulletins will prevent leakage and loosening
of the spoiler servo-control filter and plug. The DGAC classified the
Airbus service bulletins as mandatory and issued French Airworthiness
Directive (CN) 95-149-015(B) (applicable to Model A330 series
airplanes) and CN 95-147-026(B) (applicable to Model A340 series
airplanes), both dated July 29, 1995, in order to assure the continued
airworthiness of these airplanes in France.
These airplane models are manufactured in France and are 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 the loss of
hydraulic fluid to the extent that a complete failure of the associated
hydraulic system could occur. This AD requires replacement of the inlet
filter in each of the 12 spoiler servo-controls located at surface
position 1 to 6 (left-hand and right-hand); and the installation of
associated lockwires. The actions are required to be accomplished in
accordance with the service bulletins 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 14 work hours to
accomplish the required actions, at an average labor charge of $60 per
work hour. Required parts would be provided by the manufacturer at no
charge to the operator. Based on these figures, the cost impact of this
AD would be $840 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
[[Page 9098]]
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 96-NM-34-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 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-05-05 Airbus: Amendment 39-9531. Docket 96-NM-34-AD.
Applicability: Model A330-301, -321, -322, -341, and -342 series
airplanes; and Model A340-211, -212, -311, and -312 series
airplanes; on which Airbus Modification No. 42724 or its production
equivalent has not been installed; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 request approval for an
alternative method of compliance in accordance with paragraph (b) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the loss of hydraulic fluid to the extent that a
complete failure of the associated hydraulic system could occur,
accomplish the following:
(a) Within 18 months after the effective date of this AD,
replace the inlet filter in each of the 12 spoiler servo-controls
located at surface position 1 through 6 (left-hand and right-hand),
inclusive, and secure with lockwire, in accordance with either
Airbus Service Bulletin A330-27-3034 (for Model A330 series
airplanes) or Airbus Service Bulletin A340-27-4041 (for Model A340
series airplanes), both dated June 21, 1995, as applicable.
(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 actions shall be done in accordance with Airbus Service
Bulletin A330-27-3034 (for Model A330 series airplanes), dated June
21, 1995; or Airbus Service Bulletin A340-27-4041 (for Model A340
series airplanes), dated June 21, 1995. 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 March 22, 1996.
Issued in Renton, Washington, on February 28, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-5079 Filed 3-6-96; 8:45 am]
BILLING CODE 4910-13-U
