[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
