[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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