[Federal Register Volume 59, Number 3 (Wednesday, January 5, 1994)]
[Rules and Regulations]
[Pages 507-509]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-21]


[[Page Unknown]]

[Federal Register: January 5, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-208-AD; Amendment 39-8783; AD 93-24-51]

 

Airworthiness Directives; Airbus Industrie Model A310 and A300-
600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) T93-24-51 that was sent 
previously to all known U.S. owners and operators of all Airbus Model 
A310 and A300-600 series airplanes by individual telegrams. This AD 
requires repetitive operational tests of feel and limitation computers 
(FLC) 1 and 2. This amendment is prompted by a report that the pitch 
control on a Model A300-600 series airplane operated with stiffness. 
The actions specified by this AD are intended to prevent stiff 
operation of the pitch control and undetected loss of rudder travel 
limitation function.

DATES: Effective January 20, 1994, to all persons except those persons 
to whom it was made immediately effective by telegraphic AD T93-24-51, 
issued December 1, 1993, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 20, 1994.
    Comments for inclusion in the Rules Docket must be received on or 
before March 7, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 93-NM-208-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The applicable service information 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) 227-130.

SUPPLEMENTARY INFORMATION: On December 1, 1993, the FAA issued 
telegraphic airworthiness directive (AD) T93-24-51, which is applicable 
to all Airbus Model A310 and A300-600 series airplanes. That action was 
prompted by a report from an operator that the pitch control on a Model 
A300-600 series airplane operated with stiffness. Investigation into 
the cause of this stiffness revealed that the feel and limitation 
computer (FLC) failed and caused stiff operation of the pitch control. 
This condition, if not corrected, could result in stiff operation of 
the pitch control and undetected loss of rudder travel limitation 
function, which may adversely affect controllability of the airplane.
    Airbus Industrie has installed these computers on all Model A310 
and A300-600 series airplanes. Each airplane has two FLC's, designated 
FLC 1 and FLC 2. The FLC and the pitch feel fault lights are integral 
components of the pitch feel system. (The pitch feel fault lights 
indicate a failure of the FLC.)
    Currently, these airplanes are allowed to operate with one 
inoperative pitch feel system. If the airplane is operated with one 
inoperative pitch feel system, failure of the other FLC could result in 
stiff operation of the pitch control and undetected loss of rudder 
travel limitation function. This failure could also allow excessive 
elevator movement, which could expose the airplane structure to 
excessive air loads.
    Airbus Industrie has issued All Operator Telex (AOT) 27-14, dated 
November 2, 1993, applicable to all Airbus Model A310 and A300-600 
series airplanes, that describes procedures for performing repetitive 
operational tests to verify proper operation of FLC's 1 and 2. The 
Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified this AOT as mandatory 
and issued French telegraphic airworthiness directive 93-202-153(b), 
dated November 2, 1993, 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 
Sec. 21.29 of the Federal Aviation Regulations 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 the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design registered in the United 
States, the FAA issued Telegraphic AD T93-24-51 to require repetitive 
operational tests to verify proper operation of FLC's 1 and 2. The 
actions are required to be accomplished in accordance with the AOT 
previously described. Any FLC that fails the operational test is 
required to be repaired or replaced in accordance with a method 
approved by the FAA.
    The AD also prohibits operation of any airplane with an inoperative 
pitch feel system or inoperative pitch feel fault lights.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual telegrams 
issued on December 1, 1993, to all known U.S. owners and operators of 
all Airbus Model A310 and A300-600 series airplanes. These conditions 
still exist, and the AD is hereby published in the Federal Register as 
an amendment to Sec. 39.13 of part 39 of the Federal Aviation 
Regulations (FAR) to make it effective as to all persons.
    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
positively address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider additional rulemaking.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 93-NM-208-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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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 14 CFR part 
39 of the Federal Aviation Regulations 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:

93-24-51  Airbus Industrie: Amendment 39-8783. Docket 93-NM-208-AD.

    Applicability: All Airbus Model A310 and A300-600 series 
airplanes, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent stiff operation of the pitch control and undetected 
loss of rudder travel limitation function, which may adversely 
affect controllability of the airplane, accomplish the following:
    (a) Within 7 days after the effective date of this AD, perform 
an operational test to verify proper operation of feel and 
limitation computers (FLC) 1 and 2 in accordance with Airbus 
Industrie All Operator Telex 27-14, dated November 2, 1993. 
Thereafter repeat this test at intervals not to exceed 7 days.
    (b) If any FLC fails the test, prior to further flight, replace 
with a new or serviceable FLC, or repair the FLC in accordance with 
a method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (c) As of the effective date of this AD, no airplane shall be 
operated with an inoperative pitch feel system or inoperative pitch 
feel fault lights.
    (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. 
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: 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 FAR 
21.197 and 21.199 to operate the airplane to a location where the 
requirements of this AD can be accomplished.
    (f) The test shall be done in accordance with Airbus Industrie 
All Operator Telex 27-14, dated November 2, 1993. 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 January 20, 1994, to all 
persons except those persons to whom it was made immediately 
effective by telegraphic AD T93-24-51, issued December 1, 1993, 
which contained the requirements of this amendment.

    Issued in Renton, Washington, on December 28, 1993.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-21 Filed 1-4-94; 8:45 am]
BILLING CODE 4910-13-U