[Federal Register Volume 65, Number 16 (Tuesday, January 25, 2000)]
[Rules and Regulations]
[Pages 3799-3801]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-1595]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-09-AD; Amendment 39-11522; AD 2000-02-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A300-600, and A310 
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 certain Airbus Model A300 and all Model A300-600 and 
A310 series airplanes. This action requires performing a pitch trim 
system test to detect any continuity defect in the autotrim function, 
and follow-on 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 a sudden change in pitch due to an out-
of-trim condition combined with an autopilot disconnect, which could 
result in reduced controllability of the airplane.

DATES:  Effective February 9, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 9, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before February 24, 2000.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-09-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD 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:  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.

[[Page 3800]]


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 certain Airbus 
Model A300 and all Model A300-600 and A310 series airplanes. The DGAC 
advises that an Airbus Model A300-600 series airplane flew with 
autopilot 1 (AP 1), pitch trim 1 (PT 1), and pitch trim 2 (PT 2) 
engaged. When the flight crew engaged the vertical speed mode and 
selected a new vertical speed in order to change the flight level, the 
vertical speed of the airplane changed but did not remain at the speed 
that had been selected by the flight crew.
    After landing, the maintenance team performed a test with the 
autopilot engaged in vertical speed mode. When the team selected a 
vertical speed, the flight director pitch bars and control columns 
moved, but the pitch trim wheels did not move. An open circuit was 
found in the connection between flight control computer 1 (FCC 1) and 
flight augmentation computer 1 (FAC 1). That connection is necessary to 
generate the autotrim function.
    With the autopilot engaged in command (CMD), the FCC command (COM) 
and monitor (MON) lanes send signals to the FAC in order to ensure the 
autotrim function. When the FAC does not receive the FCC COM signal or 
the FCC MON signal, the autotrim function is inhibited, which results 
in an out-of-trim condition. If an autopilot disconnect occurs when the 
airplane is in an out-of-trim condition, this condition, if not 
corrected, could result in a sudden change in pitch and consequent 
reduced controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telexes (AOT) A300-22A0115 (for 
Model A300 series airplanes), A300-600-22A6042 (for Model A300-600 
series airplanes), and A310-22A2053 (for Model A310 series airplanes), 
all dated December 23, 1999, which describe procedures for a pitch trim 
system test to detect any continuity defect, and follow-on corrective 
actions, if necessary. Corrective actions include repairing any 
discrepant wiring found in the pitch trim system. (The AOT's reference 
Aircraft Schematic Manual 22-27-00 as an additional source of service 
information for accomplishment of the repair.) The DGAC has classified 
these AOT's as mandatory and issued French airworthiness directive 
T2000-007-301(B), dated January 4, 2000, 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 
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.

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 a sudden 
change in pitch due to an out-of-trim condition combined with an 
autopilot disconnect, which could result in reduced controllability of 
the airplane. This AD requires performing a pitch trim system test to 
detect any continuity defect in the autotrim function, and follow-on 
corrective actions, if necessary. The actions are required to be 
accomplished in accordance with the AOT's described previously.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing additional actions that will 
positively address the unsafe condition addressed by this AD. Once 
these actions are developed, approved, and available, the FAA may 
consider additional rulemaking.

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 2000-NM-09-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 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

[[Page 3801]]

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:

2000-02-04  Airbus Industrie: Amendment 39-11522. Docket 2000-NM-09-AD.

    Applicability: Airbus Model A300 series airplanes, having 
manufacturer's serial number 159, 168, 188, 202, 205, 213, 299, or 
302; and all Model A300-600 and A310 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 (c) 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 a sudden change in pitch due to an out-of-trim 
condition combined with an autopilot disconnect, which could result 
in reduced controllability of the airplane, accomplish the 
following:

Pitch Trim System Test

    (a) Within 20 days after the effective date of this AD: Perform 
a pitch trim system test to detect any continuity defect in the 
autotrim function, in accordance with All Operators Telex (AOT) 
A300-22A0115 (for Model A300 series airplanes), A300-600-22A6042 
(for Model A300-600 series airplanes), or A310-22A2053 (for Model 
A310 series airplanes), all dated December 23, 1999, as applicable.
    (1) If no continuity defect is found, no further action is 
required by this paragraph.

Corrective Actions

    (2) If any continuity defect is found, prior to further flight, 
accomplish the actions required by paragraphs (a)(2)(i) and 
(a)(2)(ii) of this AD, in accordance with the applicable AOT.
    (i) Repair any discrepant wiring found in the pitch trim system.
    (ii) Repeat the initial pitch trim system test required by 
paragraph (a) of this AD.


    Note 2: All Operators Telexes (AOT) A300-22A0115, A300-600-
22A6042, and A310-22A2053, all dated December 23, 1999, reference 
Aircraft Schematic Manual (ASM) 22-27-00 as an additional source of 
service information to accomplish the repair.

Reporting Requirement

    (b) Within 10 days after accomplishing the pitch trim system 
test required by this AD, or within 10 days after the effective date 
of this AD, whichever occurs later: Submit a report of the 
inspection results (both positive and negative findings) to Airbus 
Customer Services, Engineering and Technical Support, Attention Mr. 
Vincent Frayssinet, AI/SE-E43; phone number 33 (0)5.62.11.04.96; 
Sita Code TLSBQ7X.

Alternative Methods of Compliance

    (c) 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

    (d) 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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Airbus All 
Operators Telex A300-22A0115, dated December 23, 1999; Airbus All 
Operators Telex A300-600-22A6042, dated December 23, 1999; or Airbus 
All Operators Telex A310-22A2053, dated December 23, 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, 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 T2000-007-301(B), dated January 4, 2000.

    (f) This amendment becomes effective on February 9, 2000.

    Issued in Renton, Washington, on January 18, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-1595 Filed 1-24-00; 8:45 am]
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