[Federal Register Volume 60, Number 162 (Tuesday, August 22, 1995)]
[Rules and Regulations]
[Pages 43519-43521]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20371]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-143-AD; Amendment 39-9342; AD 95-17-12]
Airworthiness Directives; Airbus Model A320 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 A320 series airplanes, that requires
modification of the trimmable horizontal stabilizer (THS). This
amendment is prompted by a report of leakage from some of the hydraulic
pipe fittings after a lightning strike. The actions specified by this
AD are intended to prevent such leakage from hydraulic pipe fittings,
which could result in the loss of the pilot's ability to control the
moveable surfaces of the THS.
DATES: Effective September 21, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 21, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus Industrie, 1 Rond Point 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: Stephen Slotte, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1320.
[[Page 43520]]
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 A320 series
airplanes was published in the Federal Register on December 27, 1994
(59 FR 66491). That action proposed to require modification of the
trimmable horizontal stabilizer (THS).
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The Air Transport Association (ATA) of America, on behalf of one of
its members, requests that the compliance time for accomplishment of
the modification be extended from the proposed 3,500 flight hours to
4,500 flight hours. This commenter states that such an extension will
allow the modification to be accomplished during a regularly scheduled
``C'' check. This commenter states that it would have to special
schedule its fleet of airplanes in order to accomplish the proposed
modification within the proposed compliance time. This would entail
considerable additional expenses and schedule disruptions.
The FAA does not concur with the commenter's request to extend the
compliance time. In developing an appropriate compliance time for this
action, the FAA considered not only the degree of urgency associated
with addressing the subject unsafe condition, but the availability of
required parts and the practical aspect of installing the required
modification within a maximum interval of time allowable for all
affected airplanes to continue to operate without compromising safety.
Since maintenance schedules may vary from operator to operator, there
would be no assurance that the modification will be accomplished during
that time. The manufacturer has advised that an ample number of
required parts will be available for modification of the U.S. fleet
within the proposed compliance period. However, under the provisions of
paragraph (b) of the final rule, the FAA may approve requests for
adjustments to the compliance time if data are submitted to
substantiate that such an adjustment would provide an acceptable level
of safety.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 99 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 13 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Required parts will be supplied by the
manufacturer at no cost to the operators. Based on these figures, the
total cost impact of the AD on U.S. operators is estimated to be
$77,220, or $780 per airplane.
The total 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.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-17-12 Airbus Industrie: Amendment 39-9342. Docket 94-NM-143-AD.
Applicability: Model A320 series airplanes on which Airbus
Modification 22621 (reference Airbus Service Bulletin A320-27-1041)
and Airbus Modification 23556 (reference Airbus Service Bulletin
A320-29-1058) have not been installed, certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
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 use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the pilot's ability to control the moveable
surfaces of the THS, accomplish the following:
(a) Within 3,500 flight hours after the effective date of this
AD, modify the trimmable horizontal stabilizer in accordance with
Airbus Service Bulletin A320-29-1058, July 16, 1993, and Airbus
Service Bulletin A320-27-1041, Revision 2, dated April 20, 1994.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
(d) The modification shall be done in accordance with Airbus
Service Bulletin A320-29-1058, July 16, 1993, and Airbus Service
Bulletin A320-27-1041, Revision 2, dated April 20, 1994. This
incorporation by
[[Page 43521]]
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.
(e) This amendment becomes effective on September 21, 1995.
Issued in Renton, Washington, on August 11, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-20371 Filed 8-21-95; 8:45 am]
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