[Federal Register Volume 64, Number 10 (Friday, January 15, 1999)]
[Rules and Regulations]
[Pages 2551-2552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-813]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-67-AD; Amendment 39-10993; AD 99-02-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 and A321 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 and A321 series airplanes. This 
amendment requires modification of the slat and flap control computer 
(SFCC) in the aft electronics rack. 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 failure of the SFCC caused by computer software 
anomalies or contamination by conductive dust. This condition, if not 
corrected, could result in uncommanded slat retraction during takeoff 
and consequent insufficient wing lift available to complete a 
successful takeoff.

DATES: Effective February 19, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 19, 1999.

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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A320 and A321 
series airplanes was published in the Federal Register on April 6, 1998 
(63 FR 16709). That action proposed to require modification of the slat 
and flap control computer (SFCC) in the aft electronics rack.

Comments Received

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

Support for the Proposal

    Two commenters support the proposed rule.

Request to Reference Additional Service Bulletin Revisions

    One commenter, an operator, states that it has already started 
accomplishment of Airbus Service Bulletin A320-27-1096, dated March 14, 
1996, for its Airbus Model A320 series airplanes. Therefore, the 
operator requests that the proposed rule be revised to reference the 
original issue of that service bulletin, as well as Revision 01.
    The FAA does not concur that the final rule should be revised. 
Airbus Service Bulletin A320-27-1096, dated March 14, 1996, and 
Revision 01, dated January 14, 1998, were both referenced in paragraph 
(a) of the proposal as appropriate sources of service information and 
are retained as such in the final rule. Therefore, no change to the 
final rule is necessary.

Additional Service Bulletin Reference

    The FAA has reviewed Airbus Service Bulletin A320-27-1103, Revision 
01, dated January 26, 1998 (for Airbus Model A321 series airplanes). 
The FAA has determined that the technical procedures described in that 
revision are equivalent to the technical procedures described in Airbus 
Service Bulletin A320-27-1103, dated June 14, 1996 (the appropriate 
service information for Airbus Model A321 series airplanes referenced 
in the proposed rule). Therefore, the FAA has revised paragraph (a) of 
this AD to include Revision 01 of that service bulletin as an 
additional source of service information.

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 change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 118 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to operators. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $7,080, 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 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.
    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

[[Page 2552]]

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:

99-02-04  Airbus Industrie: Amendment 39-10993. Docket 98-NM-67-AD.

    Applicability: Model A320 series airplanes, as listed in Airbus 
Service Bulletin A320-27-1096, Revision 01, dated January 14, 1998; 
and Model A321 series airplanes, as listed in Airbus Service 
Bulletin A320-27-1103, dated June 14, 1996; 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 failure of the slat and flap control computer 
(SFCC), which could result in uncommanded slat retraction during 
takeoff and consequent insufficient wing lift available to complete 
a successful takeoff, accomplish the following:
    (a) Within 24 months after the effective date of this AD, modify 
the SFCC 1 and SFCC 2 in the aft electronics rack, in accordance 
with Airbus Service Bulletin A320-27-1096, dated March 14, 1996, or 
Revision 01, dated January 14, 1998 (for Model A320 series 
airplanes); or Airbus Service Bulletin A320-27-1103, dated June 14, 
1996, or Revision 01, dated January 26, 1998 (for Model A321 series 
airplanes); as applicable.

    Note 2: After accomplishment of the modification required by 
paragraph (a) of this AD, Temporary Revision No. 4.02.00/02 may be 
removed from the Airbus Model A320 and A321 Airplane Flight Manuals.
    (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.

    (c) 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.
    (d) The modification shall be done in accordance with Airbus 
Service Bulletin A320-27-1096, dated March 14, 1996; Airbus Service 
Bulletin A320-27-1096, Revision 01, dated January 14, 1998; Airbus 
Service Bulletin A320-27-1103, dated June 14, 1996; or Airbus 
Service Bulletin A320-27-1103, Revision 01, dated January 26, 1998; 
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 97-085-099(B), dated March 12, 1997.

    (e) This amendment becomes effective on February 19, 1999.

    Issued in Renton, Washington, on January 7, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-813 Filed 1-14-99; 8:45 am]
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