[Federal Register Volume 64, Number 149 (Wednesday, August 4, 1999)]
[Proposed Rules]
[Pages 42293-42294]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20065]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-96-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319-131, A320-232 and -
233, and A321-131 and -231 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 A319-131, 
A320-232 and -233, and A321-131 and -231 series airplanes. This 
proposal would require replacement of all titanium thrust links with 
steel thrust links. 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 failure of the titanium thrust links due to the life limit of 
the thrust links, which in combination with other failures, could 
result in the separation of an engine from the airplane.

DATES: Comments must be received by September 3, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-96-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 99-NM-96-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. 99-NM-96-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, recently notified the FAA that an 
unsafe condition may exist on certain Airbus Model A319-131, A320-232 
and -233, and A321-131 and -231 series airplanes. The DGAC advises that 
fatigue tests have revealed that the fatigue life limit of the thrust 
link was not appropriate for the objective life limit of the airplane. 
Failure of the titanium thrust link in combination with other failures, 
if not corrected, could result in the separation of an engine from the 
airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-71-1020, dated May 25, 
1998, which describes procedures for replacement of all titanium thrust 
links with steel thrust links. Accomplishment of the actions specified 
in the service bulletin is intended to adequately address the 
identified unsafe condition. The Direction Generale de l'Aviation 
Civile (DGAC) classified this service bulletin as mandatory and issued 
French airworthiness directive 1999-050-126(B), dated February 10, 
1999, in order to assure the continued airworthiness of these airplanes 
in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to

[[Page 42294]]

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.

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 accomplishment of 
the actions specified in the service bulletin described previously.

Other Relevant Rulemaking

    The FAA has previously issued notice of proposed rulemaking (NPRM), 
Docket No. 98-NM-284-AD (63 FR 64654, November 23, 1998), that concerns 
the forward engine mount on certain Airbus Model A319, A320, and A321 
series airplanes. The NPRM would require a one-time inspection of the 
forward engine mount assembly of the left and right engines to verify 
that the part number on each assembly is correct; re-identification of 
the forward engine mount assembly; and follow-on actions, if necessary. 
These actions should be accomplished prior to or concurrently with the 
actions of this proposed AD. This proposed AD would not affect the 
proposed requirements of NPRM, Docket No. 98-NM-284-AD.

Cost Impact

    The FAA estimates that 65 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours per airplane to accomplish the proposed replacement, and that the 
average labor rate is $60 per work hour. Required parts would be 
supplied by the engine 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 $11,700, or $180 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 RegulatoryFlexibility 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 99-NM-96-AD.

    Applicability: Model A319-131, A320-232 and -233, and A321-131 
and -231 series airplanes; except those airplanes on which Airbus 
Modification 26506 (reference Airbus Service Bulletin A320-71-1020, 
dated May 25, 1998) has been accomplished in production; 
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 failure of the titanium thrust links due to the life 
limit of the thrust links, which in combination with other failures, 
could result in the separation of an engine from the airplane, 
accomplish the following:
    (a) Replace all titanium thrust links with steel thrust links in 
accordance with Airbus Service Bulletin A320-71-1020, dated May 25, 
1998; at the later of the times specified in paragraphs (a)(1) and 
(a)(2) of this AD.
    (1) Prior to the accumulation of the total flight cycles 
specified for each particular model in the tables of paragraph 
B.(5), ``Accomplishment Timescale,'' of the service bulletin.
    (2) Within 15 months after the effective date of this AD, or at 
the next engine removal, whichever occurs first.

Alternative Methods of Compliance

    (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 2: 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

    (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 3: The subject of this AD is addressed in French 
airworthiness directive 1999-050-126(B), dated February 10, 1999.

    Issued in Renton, Washington, on July 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-20065 Filed 8-3-99; 8:45 am]
BILLING CODE 4910-13-U