[Federal Register Volume 63, Number 130 (Wednesday, July 8, 1998)]
[Rules and Regulations]
[Pages 36832-36834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17912]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-132-AD; Amendment 39-10646; AD 98-14-13]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, A300-600
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A300, A310, and A300-600 series
airplanes. This amendment requires a one-time operational test and
repetitive functional tests of the free fall control mechanism of the
landing gear to ensure proper release of the main landing gear (MLG),
and corrective action, if necessary. This amendment also requires
eventual modification of the free fall control mechanism of the landing
gear, which constitutes terminating action for the repetitive
functional tests. 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
malfunction of the free fall control mechanism of the landing gear,
which could result in the inability to extend the MLG in the event of
failure of the hydraulic extension system.
DATES: Effective August 12, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 12, 1998.
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: 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 A300, A310,
and A300-600 series airplanes was published in the Federal Register on
May 14, 1998 (63 FR 26742). That action proposed to require a one-time
operational test and repetitive functional tests of the free fall
control mechanism of the landing gear to ensure proper release of the
main landing gear (MLG), and corrective action, if necessary. That
action also proposed to require eventual modification of the free fall
control mechanism of the landing gear, which constitutes terminating
action for the repetitive functional tests.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
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 24 Model A300 series airplanes, 41 Model
A310 series airplanes, and 61 Model A300-600 series airplanes of U.S.
registry will be affected by this AD.
It will take approximately 3 work hours per airplane to accomplish
the required operational test, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the required
operational test on U.S. operators is estimated to be $22,680, or $180
per airplane.
It will take approximately 2 work hours per airplane to accomplish
the required functional test, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the required
functional test on U.S. operators is estimated to be $15,120, or $120
per airplane, per test cycle.
It will take approximately 26 work hours per airplane to accomplish
the required modification on the Model A300 and A300-600 series
airplanes, at an average labor rate of $60 per work hour. Required
parts will cost
[[Page 36833]]
approximately $2,630 per airplane. Based on these figures, the cost
impact of the required modification on U.S. operators of Model A300 or
A300-600 series airplanes is estimated to be $356,150, or $4,190 per
airplane.
It will take approximately 28 work hours per airplane to accomplish
the required modification on the Model A310 series airplanes, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $3,710 per airplane. Based on these figures, the cost
impact of the required modification on U.S. operators of Model A310
series airplanes is estimated to be $220,990, or $5,390 per airplane.
The cost impact figures discussed above are 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:
98-14-13 Airbus Industrie: Amendment 39-10646. Docket 98-NM-132-AD.
Applicability: Model A300, A310, and A300-600 series airplanes;
on which Airbus Industrie Modification 02781 has been accomplished,
and on which Airbus Industrie Modification 03433 or 04443 has not
been accomplished; 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 (d) 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 malfunction of the free fall control mechanism of the
landing gear, which could result in the inability to extend the main
landing gear (MLG) in the event of failure of the hydraulic
extension system, accomplish the following:
(a) Within 600 flight hours after the effective date of this AD,
perform a one-time operational test of the free fall control
mechanism of the landing gear to ensure proper release of the MLG
for extension by free fall, in accordance with Airbus Industrie All
Operator Telex (AOT) 32-14, dated February 3, 1997, or Revision 01,
dated March 13, 1997. If any discrepancy is detected in the
functioning of the free fall control mechanism of the landing gear,
prior to further flight, readjust the mechanism, and repeat the
operational test in accordance with the AOT. If any discrepancy is
detected in the second operational test, prior to further flight,
rerig the free fall control mechanism in accordance with the AOT,
and accomplish the actions required by paragraph (b) of this AD.
(b) Within 10 months after the effective date of this AD,
perform a functional test of the free fall control mechanism of the
landing gear to ensure proper release of the MLG for extension by
free fall, in accordance with Airbus Industrie AOT 32-14, dated
February 3, 1997, or Revision 01, dated March 13, 1997. Thereafter,
repeat the functional test of the free fall control mechanism of the
landing gear at intervals not to exceed 12 months, until the
modification required by paragraph (c) of this AD has been
accomplished. During any test performed in accordance with paragraph
(b) of this AD, if the free fall control mechanism of the landing
gear fails to fully extend the MLG, prior to further flight,
readjust or rerig the mechanism in accordance with the AOT.
(c) Within 66 months after the effective date of this AD, modify
the free fall control mechanism of the landing gear in accordance
with Airbus Industrie Service Bulletin A300-32-0425, Revision 01
(for Model A300 series airplanes); A310-32-2111, Revision 01 (for
Model A310 series airplanes); or A300-32-6072, Revision 01 (for
Model A300-600 series airplanes); all dated October 10, 1997; as
applicable. Accomplishment of the modification constitutes
terminating action for the repetitive functional tests required by
paragraph (b) of this AD.
(d) 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.
(e) 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.
(f) The actions shall be done in accordance with the following
Airbus Industrie service information, as applicable:
All Operator Telex (AOT) 32-14, dated February 3, 1997;
All Operator Telex (AOT) 32-14, Revision 01, dated
March 13, 1997;
Service Bulletin A300-32-0425, Revision 01, dated
October 10, 1997;
Service Bulletin A310-32-2111, Revision 01, dated
October 10, 1997; or
Service Bulletin A300-32-6072, Revision 01, dated
October 10, 1997.
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 97-113-221(B)R1, dated December 3, 1997.
(g) This amendment becomes effective on August 12, 1998.
[[Page 36834]]
Issued in Renton, Washington, on June 29, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-17912 Filed 7-7-98; 8:45 am]
BILLING CODE 4910-13-P