[Federal Register Volume 64, Number 152 (Monday, August 9, 1999)]
[Rules and Regulations]
[Pages 43061-43063]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20325]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-189-AD, Amendment 39-11249, AD 99-16-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Airbus Model A300, A310, and A300-600 series
airplanes. This action requires a one-time inspection of the autopilot
systems for proper engagement to determine if the main electro valve
electrical connectors of the yaw, roll, and pitch autopilot actuators
are correctly installed; and corrective actions, if necessary. This
amendment is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified in this AD are intended to prevent erratic movements of the
ailerons, elevator, and/or rudder that are commanded by discrepant
autopilot actuators, which could result in reduced controllability of
the airplane.
DATES: Effective August 24, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 24, 1999.
Comments for inclusion in the Rules Docket must be received on or
before September 8, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-189-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.
[[Page 43062]]
The service information referenced in this AD may be obtained from
Airbus Industrie, Customer Services Directorate, 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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 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 all Airbus Model
A300, A310, and A300-600 series airplanes. One operator of an Airbus
Model A300-600 reported high rudder forces and uncommanded rudder
inputs during final approach. The uncommanded rudder inputs caused
deflections of the rudder control surface resulting in yawing of the
airplane. Investigation of the incident is ongoing, but preliminary
results indicate that failure of both the main valve and the clutch
valve of the autopilot yaw actuator can lead to the actuator generating
uncommanded rudder deflections. The DGAC advises that the same
autopilot actuator is used for roll and pitch control during autopilot
operation, and this failure scenario can result in uncommanded
deflections of the aileron and elevator control surfaces.
Preliminary results of the investigation of the incident airplane's
autopilot yaw actuator indicate that the electrical connectors between
the actuator's two main valves and the airplane's two flight control
computers (FCC) were crossed between side 1 and side 2. This hidden
failure in combination with a failure of the clutch valve resulted in
the autopilot yaw actuator remaining engaged when the crew disconnected
the autopilot, allowing the actuator to remain hydraulically
pressurized and provide inputs to the rudder and the rudder pedals.
This condition, if not corrected, could result in uncommanded
deflections of the ailerons, elevator, and/or rudder, which could
result in reduced controllability of the airplane.
Explanation of Relevant Service Information
Airbus Industrie has issued All Operator Telexes (AOT) A300-22A0114
(for Model A300 series airplanes), A310-22A2050 (for Model A310 series
airplanes), and A300-600-22A6039 (for Model A300-600 series airplanes);
each dated May 27, 1999. These AOT's describe procedures for a one-time
inspection of the autopilot systems for proper engagement to determine
if the main electro valve electrical connectors of the yaw, roll, and
pitch autopilot actuators are correctly installed. If autopilot systems
1 and 2 cannot be engaged, then the AOT's describe a visual inspection
of the main electro valve electrical connectors of all autopilot
actuators to determine whether any electrical connection is incorrectly
installed; and corrective action by restoring the correct installation,
if necessary. The DGAC classified these AOT's as mandatory and issued
French airworthiness directive 1999-268-292(B), dated June 30, 1999; in
order to assure the continued airworthiness of these airplanes in
France.
FAA's Conclusions
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
Sec. 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.
Explanation of Requirements of Rule
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 erratic
movements of the ailerons, elevator, and/or rudder commanded by
discrepant autopilot actuators, which could result in reduced
controllability of the airplane. This AD requires accomplishment of the
actions specified in the AOT's described previously.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
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 rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-189-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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 that it is not a ``significant
[[Page 43063]]
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 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:
99-16-14 Airbus Industrie: Amendment 39-11249. Docket 99-NM-189-AD.
Applicability: All Model A300, A310, and 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 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 erratic movements of the ailerons, elevator, and/or
rudder that are commanded by discrepant autopilot actuators, which
could result in reduced controllability of the airplane, accomplish
the following:
Inspection
(a) Within 10 days after the effective date of this AD, perform
a one-time inspection of the auto pilot systems for proper
engagement to determine if the main electro valve electrical
connectors of the yaw, roll, and pitch autopilot actuators are
correctly installed, in accordance with the procedure specified in
paragraph 4.2 of Airbus Industrie All Operators Telex (AOT) A300-
22A0114 (for Model A300 series airplanes), A310-22A2050 (for Model
A310 series airplanes), or A300-600-22A6039 (for Model A300-600
series airplanes); each dated May 27, 1999; as applicable. If
autopilot systems 1 and 2 cannot be engaged: Prior to further
flight, perform a detailed inspection of the main electro valve
electrical connectors of the yaw, roll, and pitch autopilot
actuators for proper installation, and correct any discrepancy; in
accordance with paragraph 4.2 of the applicable AOT.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc. may be used. Surface cleaning and elaborate
access procedures may be required.''
Alternative Methods of Compliance
(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, International Branch, ANM-116, 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, International
Branch, ANM-116.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(c) Special flight permits may be issued in accordance with
Secs. 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.
Incorporation by Reference
(d) The actions shall be done in accordance with Airbus All
Operators Telex A300-22A0114, dated May 27, 1999; Airbus All
Operators Telex A310-22A2050, dated May 27, 1999; and Airbus All
Operators Telex A300-600-22A6039, dated May 27, 1999; as applicable.
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, Customer Services
Directorate, 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.
Note 4: The subject of this AD is addressed in French
airworthiness directive 1999-288-292(B) dated June 30, 1999.
(e) This amendment becomes effective on August 24, 1999.
Issued in Renton, Washington, on July 30, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-20325 Filed 8-6-99; 8:45 am]
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