[Federal Register Volume 64, Number 197 (Wednesday, October 13, 1999)]
[Rules and Regulations]
[Pages 55414-55416]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-26274]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-96-AD; Amendment 39-11364; AD 99-21-19]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A319-131, A320-232 and -233, and 
A321-131 and -231 series airplanes, that requires replacement of all 
titanium thrust links with steel thrust links. This amendment is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
this 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: Effective November 17, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 17, 1999.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point

[[Page 55415]]

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 A319-131, 
A320-232 and -233, and A321-131 and -231 series airplanes was published 
in the Federal Register on August 4, 1999 (64 FR 42293). That action 
proposed to require replacement of all titanium thrust links with steel 
thrust links.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposal. Two commenters state that they 
are not affected by the proposed AD.

Request To Revise Certain Wording of the Compliance Section

    One commenter requests that paragraph (a) of the proposed rule be 
revised to read, ``Replace all titanium thrust links with steel thrust 
links in accordance with Airbus Service Bulletin A320-71-1020, dated 
May 25, 1998; at the earlier of the times specified in paragraphs 
(a)(1) and (a)(2) of this AD.'' The commenter states that the term 
``later'' could allow the titanium thrust links to remain in service up 
to 15 months regardless of cycle times. The commenter further states 
that, since the cycle times are the critical parameter, ``earlier'' 
would control the use of the titanium thrust links to the critical 
parameter.
    The FAA does not concur. Revising the AD as suggested by the 
commenter would result in replacement of all titanium thrust links 
``within 15 months or at the next engine removal'', even for airplanes 
having very few accumulated flight cycles. Since this AD is intended to 
correct an unsafe condition related to the fatigue life limits of the 
thrust links, the FAA has determined that the compliance time for 
replacement of the thrust links should be correlated to the total 
flight cycles on each airplane. This compliance time is also in 
consonance with that recommended by the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, in the parallel French airworthiness directive. Additionally, 
for airplanes with thrust links over the threshold of accumulated 
flight cycles, paragraph (a)(2) of the AD includes a grace period of 15 
months, which corresponds with a typical ``C-check'' interval. The ``C-
check'' interval is recommended in the Airbus service bulletin for 
accomplishment of the replacements.
    The FAA has determined that the compliance threshold and grace 
period as proposed are adequate to accomplish timely replacement of the 
thrust links, while still providing operators sufficient time to 
perform these actions on thrust links already over the allotted number 
of accumulated flight cycles. No change is made to the final 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 65 airplanes of U.S. registry will be 
affected by this AD, that it would take approximately 3 work hours per 
airplane to accomplish the required replacement, and that the average 
labor rate is $60 per work hour. Required parts will be supplied by the 
engine manufacturer at no cost to the operators. Based on these 
figures, the cost impact of the required 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 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:

99-21-19   Airbus Industrie: Amendment 39-11364. 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.

[[Page 55416]]

    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 
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.

Incorporation by Reference

    (d) The replacement shall be done in accordance with Airbus 
Service Bulletin A320-71-1020, dated May 25, 1998. 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 3: The subject of this AD is addressed in French 
airworthiness directive 1999-050-126(B), dated February 10, 1999.

    (e) This amendment becomes effective on November 17, 1999.

    Issued in Renton, Washington, on October 4, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-26274 Filed 10-12-99; 8:45 am]
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