[Federal Register Volume 60, Number 137 (Tuesday, July 18, 1995)]
[Proposed Rules]
[Pages 36747-36749]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17551]
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[[Page 36748]]
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-92-AD]
Airworthiness Directives; Airbus Model A300-600 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 all Airbus Model A300-600 series
airplanes. This proposal would require repetitive replacement of the
universal joints and steady bearings of the flap transmission system
with new parts at regular intervals. This proposal is prompted by a
report of a malfunction of a universal joint in the flap transmission
system on one wing due to fatigue failure. The actions specified by the
proposed AD are intended to ensure replacement of universal joints and
bearings of the transmission system when they have reached their
maximum life limit; failure of universal joints and bearings could lead
to an asymmetric condition of the flaps, which could adversely affect
controllability of the airplane.
DATES: Comments must be received by August 28, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-92-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 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) 227-1149.
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 95-NM-92-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. 95-NM-92-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Gonorale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, recently notified the FAA that an
unsafe condition may exist on all Airbus Model A300-600 series
airplanes. The DGAC advises that an operator has reported a malfunction
of a universal joint in the flap transmission system. The cause of this
malfunction has been attributed to fatigue. The malfunction resulted in
a disconnection of the flap transmission system on the right-hand wing.
The disconnection triggered a flap system asymmetry warning and, as
designed, the Power Control Unit (PCU) of the flap was inhibited. This
prevented further movement of the transmission system on both wings.
Fatigue failure of the universal joints and bearings, if not detected
and corrected in a timely manner, could lead to an asymmetric condition
of the flaps, which could adversely affect controllability of the
airplane.
Airbus has issued All Operator Telex (AOT) 27-17, Revision 1, dated
July 11, 1994, and Service Bulletin A300-27-6028, dated December 19,
1994, which establish a fatigue life limitation of 16,000 landings for
certain universal joints fitted to the tee and forward bevel gearboxes
of the flap transmission, and for certain steady bearings fitted to the
flap transmission system. The AOT and the service bulletin describe
procedures for performing an inspection to ensure the integrity of the
affected bearings and bevel/tee gearboxes, and replacement of parts
with new parts. The AOT and the service bulletin also describe
procedures for repetitively replacing the universal joints fitted to
the tee and forward bevel gearboxes of the flap transmission and the
steady bearings of the flap transmission system with new universal
joints and steady bearings at regular intervals. The DGAC classified
the AOT and the service bulletin as mandatory and issued French
airworthiness directive 94-206-167(B) R1, dated March 15, 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 21.29) 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
replacement of the universal joints and steady bearings with new parts
at regular intervals. The actions would be required to be accomplished
in accordance with either the AOT or the service bulletin described
previously.
The French AD requires an inspection to ensure the integrity of the
affected bearings and bevel/tee gearboxes at 500 landings after the
effective date of the French AD and replacement with new parts at 600
landings after the effective date of the French AD. The time delay
between issuance of this proposed AD and the French AD will have
already accounted for a number of accumulated landings; therefore, this
proposal will only require replacement with new parts within 16,000
total landings on the universal joints and bearings of the flap
transmission system, or within 500
[[Page 36749]]
landings after the effective date of the AD, whichever occurs later.
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 long-standing requirement.
The FAA estimates that 50 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 11 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would cost
approximately $5,000 per airplane. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$283,000, or $5,660 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 95-NM-92-AD.
Applicability: All Model A300-600 series airplanes, 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 ensure replacement of certain universal joints and bearings
of the flap transmission that have reached their maximum life limit,
accomplish the following:
(a) Prior to the accumulation of 16,000 total landings on the
universal joints and bearings of the flap transmission system, or
within 500 landings after the effective date of this AD, whichever
occurs later: Replace the universal joints and bearings of the flap
transmission system with new parts, in accordance with Airbus All
Operator Telex (AOT) 27-17, Revision 1, dated July 11, 1994, or
Airbus Service Bulletin A300-27-6028, dated December 19, 1994.
Thereafter, prior to the accumulation of 16,000 landings on the
universal joints and bearings, replace them with new parts, in
accordance with the AOT or the service bulletin.
(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. Issued in Renton,
Washington, on July 12, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-17551 Filed 7-17-95; 8:45 am]
BILLING CODE 4910-13-U
