[Federal Register Volume 65, Number 113 (Monday, June 12, 2000)]
[Proposed Rules]
[Pages 36801-36803]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-14794]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-104-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A300 
and all Model A300-600 and A310 series airplanes, that currently 
requires performing a pitch trim system test to detect any continuity 
defect in the autotrim function, and follow-on corrective actions, if 
necessary. This action would require repetitive inspections of the 
autotrim function to detect such defects, and corrective actions, if 
necessary. This action also would expand the applicability to include 
additional airplanes. This proposal is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by the proposed 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: Comments must be received by July 12, 2000.

[[Page 36802]]


ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-104-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: 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:

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 2000-NM-104-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-114, Attention: Rules 
Docket No. 2000-NM-104-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On January 18, 2000, the FAA issued AD 2000-02-04, amendment 39-
11522 (65 FR 3799, January 25, 2000), applicable to certain Airbus 
Model A300 and all Model A300-600 and A310 series airplanes. That AD 
requires performing a pitch trim system test to detect any continuity 
defect in the autotrim function, and follow-on corrective actions, if 
necessary. That action was prompted by issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness authority. 
The requirements of that 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.

Actions Since Issuance of Previous Rule

    Since issuance of AD 2000-02-04, the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, has advised the FAA that repetitive inspections are necessary 
to maintain the fleet in an airworthy condition, and that additional 
airplanes may be subject to the identified unsafe condition. In light 
of the DGAC's recommendation, the FAA has determined that further 
rulemaking action is necessary; this proposed AD follows from that 
determination.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-22A6042, Revision 01 (for 
Model A300-600 series airplanes); A300-22A0115, Revision 02 (for Model 
A300 series airplanes); and A310-22A2053, Revision 01 (for Model A310 
series airplanes); all dated March 7, 2000. These service bulletins 
describe procedures for repetitive inspections of the autotrim function 
by testing the integrity of the flight control computer (FCC) and 
flight augmentation computer (FAC) in logic activation of the autotrim. 
For any default found during the test, the service bulletins describe 
procedures for trouble-shooting and follow-on corrective actions, 
including replacing the FCC and/or FAC, retesting, checking the wires 
between certain FCC and FAC pins, and repairing damaged wires.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive 2000-115-304(B) R1, dated May 3, 2000, 
in order to ensure 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 Proposed 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, the proposed AD would supersede AD 2000-02-04 to 
require repetitive inspections to detect continuity defects in the 
autotrim function and to expand the applicability to include additional 
airplanes. The actions would be required to be accomplished in 
accordance with the applicable service bulletin described previously. 
The proposed AD also would require that operators report results of 
inspection findings to Airbus.

Interim Action

    This is considered to be interim action for Model A300-600 and A310 
series airplanes. 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 for 
these airplanes.

Cost Impact

    There are approximately 120 airplanes of U.S. registry that would 
be affected by this proposed AD. The inspection that is proposed by 
this AD would take approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the proposed actions on U.S. 
operators is estimated to be $7,200, or $60 per airplane, per 
inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the current or proposed 
requirements of

[[Page 36803]]

this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-11522 (65 FR 
3799, January 25, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 2000-NM-104-AD. Supersedes AD 2000-02-04, 
Amendment 39-11522.

    Applicability: Model A300 B2-203 and B4-203 series airplanes in 
a forward facing cockpit version, as listed in Airbus Service 
Bulletin A300-22A0115, Revision 02, dated March 7, 2000; 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:

Repetitive Inspections

    (a) At the applicable time specified by paragraph (a)(1) or 
(a)(2) of this AD: Perform an inspection of the autotrim function by 
testing the flight control computer (FCC)/flight augmentation 
computer (FAC) integrity in logic activation of the autotrim, in 
accordance with Airbus Service Bulletin A300-22A6042, Revision 01 
(for Model A300-600 series airplanes); A300-22A0115, Revision 02 
(for Model A300 series airplanes); or A310-22A2053, Revision 01 (for 
Model A310 series airplanes); all dated March 7, 2000; as 
applicable. If any discrepancy is found, prior to further flight, 
perform all applicable corrective actions (including trouble-
shooting, replacing the FCC and/or FAC, retesting, checking the 
wires between certain FCC and FAC pins, and repairing damaged wires) 
in accordance with the applicable service bulletin. Repeat the 
inspection thereafter at intervals not to exceed 500 flight hours.
    (1) For airplanes on which the pitch trim system test has been 
performed in accordance with the requirements of AD 2000-02-04, 
amendment 39-11522: Inspect within 500 flight hours after 
accomplishment of the test required by that AD, or within 20 days 
after the effective date of this AD, whichever occurs later.
    (2) For all other airplanes: Inspect within 20 days after the 
effective date of this AD.

Reporting Requirement

    (b) For all inspections required by paragraph (a) of this AD: At 
the applicable time specified by paragraph (b)(1) or (b)(2) of this 
AD, submit a report of the inspection results (both positive and 
negative findings) to AI/SE-D32 Technical Data and Documentation 
Services, Airbus Industrie Customer Services Directorate, 1 Rond 
Point Maurice Bellonte, 31707 Blagnac Cedex France; fax (+33) 5 61 
93 28 06.
    (1) For inspections accomplished after the effective date of 
this AD: Submit the report within 10 days after performing the 
inspection.
    (2) For inspections accomplished prior to the effective date of 
this AD: Submit the report within 10 days after the effective date 
of this AD.

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 2: 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 
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.


    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2000-115-304(B) R1, dated May 3, 2000.


    Issued in Renton, Washington, on June 6, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14794 Filed 6-9-00; 8:45 am]
BILLING CODE 4910-13-U