[Federal Register Volume 65, Number 76 (Wednesday, April 19, 2000)]
[Proposed Rules]
[Pages 20921-20922]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-9823]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 65, No. 76 / Wednesday, April 19, 2000 / 
Proposed Rules  

[[Page 20921]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-77-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A310 series 
airplanes. This proposal would require modification of the position 1 
flap screw jack. This proposal is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by the proposed AD are intended to 
prevent fracture of the lead screw of the position 1 flap screw jack, 
which could result in failure of the tie bar and possible disconnection 
of the flap structure from the airplane.

DATES: Comments must be received by May 19, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-77-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, 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 2000-NM-77-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. 2000-NM-77-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on certain Airbus Model A310 series airplanes. The 
DGAC advises that, during routine maintenance, a fractured lead screw 
was detected in a position 1 flap screw jack. After an inspection of 
the fleet, additional occurrences of broken or cracked lead screws were 
reported. Investigation into the fractured lead screws revealed that 
the cause was attributed to interference between the ball nut and the 
trunnion fork end due to the installation of the ball nut being offset 
180 degrees after maintenance. Such interference between the ball nut 
and trunnion fork end could lead to fracture of the lead screw of the 
position 1 flap screw jack. This condition, if not corrected, could 
result in failure of the tie bar and possible disconnection of the flap 
structure from the airplane.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletin A310-27-2075, 
Revision 02, dated February 8, 2000, which describes procedures for 
modification of the position 1 flap screw jack. The modification 
involves the installation of a bracket, which will prevent incorrect 
installation of the ball nut. The DGAC classified this service bulletin 
as mandatory and issued French airworthiness directive 1999-510-299(B), 
dated December 29, 1999, in order to assure the continued airworthiness 
of these airplanes in France.
    The Airbus service bulletin references Lucas/Liebherr Service 
Bulletin 537-27-M537-15, dated May 12, 1994, as an additional source of 
service information for accomplishing the modification proposed by this 
AD.

FAA's Conclusions

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

[[Page 20922]]

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require modification of the 
position 1 flap control screw jack. The actions would be required to be 
accomplished in accordance with the Airbus service bulletin described 
previously.

Cost Impact

    The FAA estimates that 41 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours per airplane to accomplish the proposed modification, and that 
the average labor rate is $60 per work hour. Required parts would cost 
approximately $105 per airplane. Based on these figures, the cost 
impact of the proposed modification AD on U.S. operators is estimated 
to be $9,225, or $225 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 a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 2000-NM-77-AD.

    Applicability: Model A310 series airplanes, certificated in any 
category, except those airplanes on which Airbus Modification 10855 
or Airbus Service Bulletin A310-27-2075 has been accomplished.

    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 (c) 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 fracture of the lead screw of the position 1 flap 
screw jack, which could result in failure of the tie bar and 
possible disconnection of the flap structure from the airplane, 
accomplish the following:

Modification

    (a) Within 18 months after the effective date of this AD, modify 
the position 1 flap screw jack in accordance with Airbus Service 
Bulletin A310-27-2075, Revision 02, dated February 8, 2000.

    Note 2: Modifications accomplished prior to the effective date 
of this AD, in accordance with Airbus Service Bulletin A310-27-2075, 
dated November 18, 1994, or Revision 01, dated July 20, 1995, are 
considered acceptable for compliance with the modification specified 
by this AD.


    Note 3: The Airbus service bulletin references Lucas/Liebherr 
Service Bulletin 537-27-M537-15, dated May 12, 1994, as an 
additional source of service information for accomplishing the 
applicable action required by this AD.

Spares

    (b) As of the effective date of this AD, no person shall install 
on any airplane a position 1 flap screw jack having part number 
537G0000-02, unless modified in accordance with this AD.

Alternative Methods of Compliance

    (c) 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.

Special Flight Permits

    (d) 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.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 1999-510-299(B), dated December 29, 1999.



    Issued in Renton, Washington, on April 13, 2000.
Charles D. Huber,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-9823 Filed 4-18-00; 8:45 am]
BILLING CODE 4910-13-U