[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 [www.gpo.gov]
[FR Doc No: 99-50]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
[[Page 1108]]
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
