[Federal Register Volume 65, Number 221 (Wednesday, November 15, 2000)]
[Rules and Regulations]
[Pages 68876-68878]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-28967]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-104-AD; Amendment 39-11977; AD 2000-23-07]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes 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 
amendment requires repetitive inspections of the autotrim function to 
detect such defects, and corrective actions, if necessary. This 
amendment also expands the applicability to include additional 
airplanes. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by 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 December 20, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 20, 2000.

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-02-04, 
amendment 39-11522 (65 FR 3799, January 25, 2000), which is applicable 
to certain Airbus Model A300 and all Model A300-600 and A310 series 
airplanes, was published in the Federal Register on June 12, 2000 (65 
FR 36801). The action proposed to supersede AD 2000-02-04 to continue 
to require performing a pitch trim system test to detect any continuity 
defect in the autotrim function, and follow-on corrective actions, if 
necessary. The action also proposed to require repetitive inspections 
of the autotrim function to detect such defects, and corrective 
actions, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Revise Applicability

    The manufacturer, Airbus, requests that the applicability of the 
proposed AD be revised to exclude Model A300-600 series airplanes on 
which Airbus Modification 12277 has been accomplished during 
production. In addition, since the issuance of the proposed AD, the 
Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, issued French airworthiness 
directive 2000-115-304(B) R2, dated July 12, 2000, as revised by 
Erratum, dated August 9, 2000, to exclude those airplanes from the 
applicability. The FAA concurs with the commenter's request, and has 
revised the applicability of this final rule accordingly.

Request To Revise Reporting Requirement

    The Air Transport Association (ATA) of America, on behalf of one of 
its members, requests that the reporting requirement specified in the 
proposed AD be revised to require that inspection findings be reported 
to Airbus on a monthly basis, rather than 10 days following each 
inspection. The commenter states that since any necessary corrective 
actions would occur immediately as a result of the inspection findings, 
monthly reporting would not affect the safe operation of the airplane. 
For certain airlines, monthly reporting would greatly simplify the 
administrative tasks associated with ongoing reporting.
    The FAA concurs partially. The FAA agrees that corrective actions, 
if necessary, would be required prior to further flight; therefore, 
extension of the compliance time in question will not affect the safe 
operation of the airplane. However, the FAA considers that requiring 
report submittals on a monthly basis could lead to possible 
misinterpretation as to the specific deadline for submission of each 
report.
    In light of this, the FAA has revised the final rule to require 
submission of each report within 30 days after accomplishing each 
inspection (for inspections accomplished after the effective date of 
this AD), or within 30 days after the effective date of the AD (for 
inspections accomplished prior to the effective date of this AD). 
Operators are provided with additional time to

[[Page 68877]]

submit each report, and may choose to combine submittals of all reports 
for the past 30 days, which would reduce the administrative burden. 
Paragraph (b) of this AD has been revised accordingly.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

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 will be 
affected by this AD. The inspection that is required by this AD will 
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 required action on U.S. operators is estimated to be 
$7,200, or $60 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-11522 (65 FR 
3799, January 25, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-11977, to read as follows:

2000-23-07  Airbus Industrie: Amendment 39-11977. Docket 2000-NM-
104-AD. Supersedes AD 2000-02-04, Amendment 39-11522.

    Applicability: This AD applies to the airplanes listed in Table 
1. of this AD, certificated in any category:

                         Table 1.--Applicability
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              Airbus model                         Description
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A300 B2-203 airplanes and A300-B4-203    In a forward facing cockpit
 airplanes.                               version, as listed in Airbus
                                          Service Bulletin A300-22A0115,
                                          Revision 02, dated March 7,
                                          2000.
A310 series airplanes..................  All.
A300-600 series airplanes..............  On which Airbus Modification
                                          12277 has not been
                                          accomplished during
                                          production.
------------------------------------------------------------------------


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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

[[Page 68878]]

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 30 days after performing the 
inspection.
    (2) For inspections accomplished prior to the effective date of 
this AD: Submit the report within 30 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 
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 Service 
Bulletin A300-22A6042, Revision 01, including Appendix 01, dated 
March 7, 2000; Airbus Service Bulletin A300-22A0115, Revision 02, 
including Appendix 01, dated March 7, 2000; or Airbus Service 
Bulletin A310-22A2053, Revision 01, including Appendix 01, dated 
March 7, 2000; 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 3: The subject of this AD is addressed in French 
airworthiness directive 2000-115-304(B) R2, dated July 12, 2000, as 
revised by Erratum, dated August 9, 2000.

    (f) This amendment becomes effective on December 20, 2000.

    Issued in Renton, Washington, on November 6, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-28967 Filed 11-14-00; 8:45 am]
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