AD Amdt-39-10978

[Federal Register Volume 64, Number 5 (Friday, January 8, 1999)]
[Rules and Regulations]
[Pages 1106-1108]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-50]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-07-AD; Amendment 39-10978; AD 99-01-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.


[[Page 1107]]


ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A319, A320, and A321 series 
airplanes, that requires modification of the airplane wiring to 
separate the electrical inputs sent by the engine interface units (EIU) 
to certain probe heat computers (PHC). This amendment is prompted by 
the issuance of mandatory continuing airworthiness information by a 
foreign civil airworthiness authority. The actions specified by this AD 
are intended to prevent simultaneous loss of heating to pitot probes 1 
and 3, which could result in incorrect airspeed indications to both the 
pilot's and first officer's airspeed indication systems. Malfunction of 
these systems could result in reduced controllability of the airplane.

DATES: Effective February 12, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 12, 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 A319, A320, 
and A321 series airplanes was published as a supplemental notice of 
proposed rulemaking (NPRM) in the Federal Register on October 27, 1998 
(63 FR 57263). That action proposed to require modification of the 
airplane wiring to separate the electrical inputs sent by the engine 
interface units (EIU) to certain probe heat computers (PHC).

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the three comments received.
    All of the commenters support the proposed rule.

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 as proposed.

Cost Impact

    The FAA estimates that 150 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 3 work hours per airplane to accomplish 
the required modification (including testing), at an average labor rate 
of $60 per work hour. Required parts will be provided by the 
manufacturer at no cost to the operators. Based on these figures, the 
cost impact of this AD on U.S. operators is estimated to be $27,000, or 
$180 per airplane.
    Should an operator be required to re-test modified wiring, it will 
take approximately 1 additional work hour per airplane to accomplish 
the test, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact of any necessary re-test required by this AD 
on U.S. operators is estimated to be $60 per airplane.
    The cost impact figures discussed above are 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 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:

99-01-13  Airbus Industrie: Amendment 39-10978. Docket 98-NM-07-AD.

    Applicability: Model A319, A320, and A321 series airplanes; 
excluding airplanes on which Airbus Modification 26403 or Airbus 
Service Bulletin A320-30-1036, Revision 02, dated February 4, 1998, 
has been accomplished; certificated in any category.

    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 (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 simultaneous loss of heating to pitot probes 1 and 3, 
which could result in incorrect airspeed indications to both the 
pilot's and first officer's airspeed indication systems, and reduced 
controllability of the airplane, accomplish the following:
    (a) Within 6 months after the effective date of this AD, modify 
the airplane wiring to separate the electrical inputs sent by the 
engine interface units to probe heat computers 1 and 3, and test the 
modified wiring; in accordance with the service bulletin referenced 
in paragraph (a)(1) or (a)(2) of this AD, as applicable.
    (1) For airplanes equipped with engines manufactured by CFM 
International (CFMI): Modify and test in accordance with Airbus

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Service Bulletin A320-30-1036, dated May 9, 1997; or Airbus Service 
Bulletin A320-30-1036, Revision 02, dated February 4, 1998.

    Note 2: For airplanes equipped with CFMI engines: Accomplishment 
of the modification and test in accordance with Airbus Service 
Bulletin A320-30-1036, Revision 01, dated July 7, 1997, is 
considered acceptable for compliance with paragraph (a)(1) of this 
AD.

    (2) For airplanes equipped with engines manufactured by 
International Aero Engines AG (IAE): Modify and test in accordance 
with Airbus Service Bulletin A320-30-1036, Revision 02, dated 
February 4, 1998.

    Note 3: For airplanes equipped with IAE engines: Accomplishment 
of the modification in accordance with Airbus Service Bulletin A320-
30-1036, dated May 9, 1997, or Revision 01, dated July 7, 1997, 
prior to the effective date of this AD, is considered acceptable for 
compliance with the modification specified by paragraph (a)(2) of 
this AD, provided that the modification is tested in accordance with 
the procedures specified in Airbus Service Bulletin A320-30-1036, 
Revision 02, dated February 4, 1998.

    (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 4: 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 and test shall be done in accordance with 
Airbus Service Bulletin A320-30-1036, dated May 9, 1997; or Airbus 
Service Bulletin A320-30-1036, Revision 02, dated February 4, 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 5: The subject of this AD is addressed in French 
airworthiness directives 97-203-102(B)R1 and 98-152-114(B), both 
dated April 8, 1998.

    (e) This amendment becomes effective on February 12, 1999.

    Issued in Renton, Washington, on December 28, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-50 Filed 1-7-99; 8:45 am]
BILLING CODE 4910-13-U