[Federal Register Volume 63, Number 207 (Tuesday, October 27, 1998)]
[Proposed Rules]
[Pages 57263-57265]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28666]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-07-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319, A320, and A321
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking; reopening of
comment period.
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SUMMARY: This document revises an earlier proposed airworthiness
directive (AD), applicable to certain Airbus Model A319, A320, and A321
series airplanes, that would have required modification of the airplane
wiring to separate the electrical inputs sent by the engine interface
units (EIU) to certain probe heat computers (PHC). That proposal was
prompted by the issuance of mandatory continuing airworthiness
information by a foreign civil
[[Page 57264]]
airworthiness authority. This new action revises the proposed rule by
changing the procedure for testing the modified wiring of the EIU's and
PHC's for certain airplanes. The actions specified by this new proposed
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: Comments must be received by November 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-07-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-07-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-07-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to add an airworthiness directive (AD), applicable to
certain Airbus Model A319, A320, and A321 series airplanes, was
published as a notice of proposed rulemaking (NPRM) in the Federal
Register on February 23, 1998 (63 FR 8886). That NPRM would have
required modification of the airplane wiring to separate the electrical
inputs sent by the engine interface units (EIU) to certain probe heat
computers (PHC). That NPRM was prompted by the issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The existing PHC's 1 and 3 receive the same discrete
information from EIU's 1 and 2 to automatically control the pitot probe
heating. Isolation defects caused by internal corrosion of a PHC, if
not corrected, could result in 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.
Actions Since Issuance of Previous Proposal
Due consideration has been given to the comments received in
response to the NPRM.
Request to Reference Revised Service Information
One commenter (the manufacturer) requests that the FAA revise the
proposed AD to reference Revision 02 of Airbus Service Bulletin A320-
30-1036, dated February 4, 1998, instead of the original issue of that
service bulletin, dated May 9, 1997 (which was referenced as the
appropriate source of service information in the original NPRM). The
commenter states that its analysis shows that the test specified in the
original issue of the service bulletin is not adequate for airplanes
equipped with engines manufactured by International Aero Engines AG
(IAE). However, Revision 02 of the service bulletin does specify a test
procedure that is appropriate for airplanes equipped with IAE engines.
Revision 02 also retains the original test procedure for airplanes
equipped with engines manufactured by CFM International (CFMI).
The FAA concurs with the commenter's request to reference Revision
02 of the subject service bulletin. Since issuance of the NPRM, the FAA
has reviewed Revision 02 of the subject service bulletin. That service
bulletin describes procedures similar to those described in the
original issue for modification of the airplane wiring to divide
electrical inputs sent by the EIU's to PHC's 1 and 3. However, Revision
02 of the service bulletin differs from the original issue of the
service bulletin in that Revision 02 specifies a new procedure for
testing modified wiring on all Airbus Model A319, A320, and A321 series
airplanes equipped with IAE engines.
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, classified Revision 02 of the
service bulletin as mandatory for airplanes equipped with IAE engines
and issued French airworthiness directives 97-203-102(B)R1 and 98-152-
114(B), both dated April 8, 1998, in order to assure the continued
airworthiness of Airbus Model A319, A320, and A321 series airplanes in
France.
Therefore, the FAA has revised paragraph (a) of the proposed AD to
specify the original issue or Revision 02 of the service bulletin as
the appropriate source of service information for the modification and
testing of wiring on airplanes equipped with CFMI engines, and to
specify Revision 02 as the appropriate source of service information
for the modification and testing of wiring on airplanes equipped with
IAE engines.
Explanation of Applicability
The original NPRM specified that the proposed AD was applicable to
Airbus ``Model A319, A320, and A321 series airplanes, on which Airbus
Modification 26403 or Airbus Service Bulletin A320-30-1036 has not been
accomplished, certificated in any category.'' As described previously,
the procedure for testing the modification that was specified in the
original issue
[[Page 57265]]
of the service bulletin was not appropriate for all airplanes, and
airplanes that were modified in accordance with the original issue of
the service bulletin may require retesting. Therefore, the FAA has
revised the applicability of this supplemental NPRM to specify, ``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.''
Conclusion
Because these changes expand the scope of the originally proposed
rule, the FAA has determined that it is necessary to reopen the comment
period to provide additional opportunity for public comment.
Cost Impact
The FAA estimates that 150 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 3 work hours per airplane to accomplish
the proposed modification (including testing), at an average labor rate
of $60 per work hour. Required parts would be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the proposed 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 would
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 proposed by this AD
on U.S. operators is estimated to be $60 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Airbus Industrie: 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
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
Secs. 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.
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.
Issued in Renton, Washington, on October 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-28666 Filed 10-26-98; 8:45 am]
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