[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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