[Federal Register Volume 66, Number 231 (Friday, November 30, 2001)]
[Rules and Regulations]
[Pages 59687-59689]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29340]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-358-AD; Amendment 39-12521; AD 2001-24-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
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 A320 series airplanes, that 
currently requires modification of the autopilot mode engagement/
disengagement lever of the rudder artificial feel unit. This amendment 
requires a different modification of the lever. This amendment also 
revises the applicability to include Airbus Model A319 and A321 series 
airplanes, as well as all Model A320 series 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 reduced controllability of 
the airplane due to the failure of the rudder artificial feel unit to 
disengage properly from autopilot mode during approach and landing.

DATES: Effective January 4, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 4, 2002.

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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone: (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-21-29, 
amendment 39-11375 (64 FR 56158, October 18, 1999), which is applicable 
to certain Airbus Model A320 series airplanes, was published in the 
Federal Register on March 29, 2001 (66 FR 17125). The action proposed 
to require a new modification of the autopilot mode engagement/
disengagement lever of the rudder artificial feel unit. The action also 
proposed to revise the applicability of the existing AD to include 
Airbus Model A319 and A321 series airplanes, as well as all Model A320 
series airplanes.

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 Refer to Revised Service Information

    Two commenters request that the FAA revise paragraph (a) of the 
proposed AD to refer to Airbus Service Bulletin A320-27-1130, Revision 
01, dated November 23, 2000, instead of the original issue of that 
service bulletin, which the proposed AD specifies as the appropriate 
source of service information for the proposed modification. One of the 
commenters explains that Airbus issued Revision 01 of the service 
bulletin in response to the commenter's suggestions for improvements 
and corrections that could be made to the work instructions, as well as 
to revise the effectivity. The other commenter also asks that, in 
addition to referring to Revision 01, the proposed AD be revised to 
refer to ``any subsequently approved revision(s)'' of the service 
bulletin as appropriate sources of service information.
    The FAA partially concurs with the commenters' requests. Since the 
issuance of the proposed rule, Airbus has issued Revision 01 of the 
service bulletin, as well as Revision 02 of the service bulletin, dated 
September 6, 2001. We have determined that accomplishment of the 
modification required by this AD according to either the original 
issue, Revision 01, or Revision 02 of the service bulletin is 
acceptable. Paragraph (a) has been revised to refer to the most recent 
issue, Revision 02 of the service bulletin, and Note 2 has been added 
to this AD (and subsequent notes reordered) to state that modification 
prior to the effective date of this AD according to the original issue 
or Revision 01 of the service bulletin is acceptable for compliance 
with paragraph (a) of this AD.
    With regard to the second commenter's request to refer to ``any

[[Page 59688]]

subsequently approved revision(s)'' of the service bulletin, we do not 
concur. An AD may only refer to service documents that are submitted 
and approved by the Office of the Federal Register (OFR) for 
``incorporation by reference.'' In order for operators to use later 
revisions of the referenced document (issued after the publication of 
the AD), either the AD must be revised to refer to the specific later 
revisions, or operators must request approval for the use of them as an 
alternative method of compliance with this AD under the provisions of 
paragraph (c) of this AD. No further change to the AD is necessary in 
this regard.

Request To Revise Compliance Time

    One commenter requests that the FAA revise the compliance time for 
the proposed modification from 18 months to 24 months after the 
effective date of the AD. The commenter states that this change would 
allow operators to accomplish the modification during a regularly 
scheduled maintenance visit such as a ``C'' check, which would reduce 
the impact of the proposed modification on line operations. The 
commenter also states that an extension of the compliance time would 
make the compliance time for the proposed AD coincide with those of 
other ADs and would compensate for increased lead-time necessary for 
delivery of the kit needed to accomplish the proposed modification.
    The FAA does not concur. In developing the compliance time for the 
modification in this AD, the FAA considered not only the degree of 
urgency associated with addressing the subject unsafe condition, but 
also the time necessary to accomplish the modification (estimated at 9 
work hours per airplane), and the practical aspect of installing the 
required modification within an interval of time that parallels normal 
scheduled maintenance for the majority of affected operators. The FAA 
finds that 18 months represents an appropriate interval of time 
allowable wherein the modification can be accomplished during scheduled 
maintenance for the majority of affected operators, and an acceptable 
level of safety can be maintained. With regard to the lead-time needed 
for obtaining the necessary kits, we find that operators will have 
ample time to order and receive the kits before the compliance 
threshold. No change to the AD is necessary in this regard.

Request To Differentiate Between Assembly and Subassembly Part 
Numbers

    One commenter requests that the FAA revise paragraph (b) of the 
proposed AD to differentiate between assembly and subassembly part 
numbers. The commenter notes that paragraph (b) of the proposed AD 
contains both artificial feel unit assembly and artificial feel unit 
subassembly part numbers according to the Airbus Illustrated Parts 
Catalog.
    The FAA does not concur. All parts listed in paragraph (b) are 
prohibited from being installed on an airplane after the effective date 
of this AD. In addition, the referenced service bulletin clearly 
differentiates between artificial feel units with a solenoid and those 
without a solenoid. No change to the AD is necessary in this regard.

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.

Cost Impact

    There are approximately 291 Model A319, A320, and A321 series 
airplanes of U.S. registry that will be affected by this AD.
    The new modification that is required by this AD will take 
approximately 9 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will be provided by the 
manufacturer at no cost. Based on these figures, the cost impact of the 
requirements of this AD on U.S. operators is estimated to be $157,140, 
or $540 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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 39-11375 (64 FR 
56158, October 18, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12521, to read as follows:

2001-24-05  Airbus Industrie: Amendment 39-12521. Docket 2000-NM-
358-AD. Supersedes AD 99-21-29, Amendment 39-11375.

    Applicability: Model A319, A320, and A321 series airplanes, 
certificated in any category, on which Airbus Modification 28909 was 
not accomplished during production.

    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

[[Page 59689]]

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 reduced controllability of the airplane, due to the 
failure of the rudder artificial feel unit to disengage properly 
from autopilot mode during approach and landing, accomplish the 
following:

Modification

    (a) Within 18 months after the effective date of this AD, modify 
the autopilot mode engagement/disengagement lever of the rudder 
artificial feel unit, in accordance with paragraphs 3.B. and 3.C. of 
the Accomplishment Instructions of Airbus Service Bulletin A320-27-
1130, Revision 02, dated September 6, 2001.

    Note 2: Modification of the autopilot mode engagement/
disengagement lever of the rudder artificial feel unit prior to the 
effective date of this AD in accordance with Airbus Service Bulletin 
A320-27-1130, dated March 14, 2000, or Revision 01, dated November 
23, 2000, is acceptable for compliance with paragraph (a) of this 
AD.

Spares

    (b) As of the effective date of this AD, no person may install a 
rudder artificial feel unit having any of the following part numbers 
on any airplane:

D2727040000600
D2727040000651
D2727040000695
D2727040000696
D2727040000800
D2727040000851
D2727040001000
D2727040001051

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, 
Transport Airplane Directorate, FAA. 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 Manager, 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 A320-27-1130, Revision 02, dated September 6, 2001. 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 2000-372-151(B), dated September 6, 2000.

Effective Date

    (f) This amendment becomes effective on January 4, 2002.

    Issued in Renton, Washington, on November 19, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29340 Filed 11-29-01; 8:45 am]
BILLING CODE 4910-13-P