[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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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