[Federal Register Volume 63, Number 93 (Thursday, May 14, 1998)]
[Proposed Rules]
[Pages 26742-26744]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-12807]
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Proposed Rules
Federal Register
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This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 63, No. 93 / Thursday, May 14, 1998 /
Proposed Rules
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-132-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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 A300, A310,
and A300-600 series airplanes. This proposal would 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. This
proposal also would require eventual modification of the free fall
control mechanism of landing gear, which constitutes terminating action
for the repetitive functional tests. 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 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: Comments must be received by June 15, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-132-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 98-NM-13-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. 98-NM-132-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 A300, A310, and
A300-600 series airplanes. The DGAC advises that during training
flights on two Airbus Model A300 series airplanes, the flight crew
reported difficulty in extending the main landing gear (MLG) by means
of the free fall control mechanism of the landing gear. The free fall
control mechanism allows the flight crew to extend the landing gear in
the event of failure of the hydraulic system that normally is used to
extend the landing gear. A functional test of the free fall control
mechanism on both airplanes revealed that this mechanism was rigged
incorrectly, which caused the cockpit control handle of the free fall
control mechanism to reach its mechanical stop before the MLG was
released for extension by free fall. Malfunction of the free fall
control mechanism, if not corrected, could result in the inability to
extend the MLG in the event of failure of the hydraulic extension
system.
Explanation of Relevant Service Information
The manufacturer has issued Airbus Industrie All operator Telex
(AOT) 32-14, dated February 3, 1997, and Revision 01, dated March 13,
1997, which describe procedures or a one-time operational test and
repetitive functional tests of the free fall control mechanism of the
landing gear, and corrective action, if necessary. Procedures for the
one-time operational test of the free fall control mechanism include
inspecting the free fall control mechanism of the MLG with the landing
gear extended and the weight of the airplane on the landing gear.
Procedures for the repetitive functional test of the free fall control
mechanism of the landing gear while the airplane is on jacks.
Corrective actions, if necessary, including readjusting the telescopic
rods of the MLG uplock of the free fall control mechanism, or
completely rerigging the free fall control mechanism by adjusting
specified components of the mechanism. The AOT also recommends that
operators of airplanes
[[Page 26743]]
on which installation of Airbus Modification 04443 is pending need not
accomplish the scheduled operational test of the free fall control
mechanism of he landing gear.
The manufacturer also has issued Airbus Industrie Service Bulletins
A300-32-0425, Revision 01; A310-32-2111, Revision 01; and A300-32-6072,
Revision 01; all dated October 10, 1997. These service bulletins
describe procedures for modification of the free fall control mechanism
of the landing gear on Airbus Model A300, A310, and A300-600 series
airplanes. The Modification includes removing telescope rods and cranks
or crank assemblies from the MLG part of the free fall control
mechanism of the landing gear, replacing the telescopic rods with new
parts, and replacing the cranks or crank assemblies with improved
parts. Accomplishment of the modification eliminates the need for the
repetitive inspections described previsously.
Accomplishment of the actions specified in the AOT's and service
bulletins described previously is intended to adequately address the
identified unsafe condition. The DGAC classified the AOT's and service
bulletins as mandatory and issued French airworthiness directive 97-
113-322(B)R1, dated December 3, 1997, 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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to 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 AOT's and the service bulletins described
previously.
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 would be affected by this proposed AD.
It would take approximately 3 work hours per airplane to accomplish
the proposed operational test, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the proposed
operational test on U.S. operators is estimated to be $22,680, or $180
per airplane.
It would take approximately 2 work hours per airplane to accomplish
the proposed functional test, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the proposed
functional test on U.S. operators is estimated to be $15,120, or $120
per airplane, per test cycle.
It would take approximately 26 work hours per airplane to
accomplish the proposed modification on the Model A300 and A300-600
series airplanes, at an average labor rate of $60 per work hour.
Required parts would cost approximately $2,630 per airplane. Based on
these figures, the cost impact of the proposed 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 would take approximately 28 work hours per airplane to
accomplish the proposed modification on the Model A310 series
airplanes, at an average labor rate of $60 per work hour. Required
parts would cost approximately $3,710 per airplane. Based on these
figures, the cost impact of the proposed 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 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 Regulatory Flexibility 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 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: 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
[[Page 26744]]
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 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 the 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 97-113-221(B)R1, dated December 3, 1997.
Issued in Renton, Washington, on May 7, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-12807 Filed 5-13-98; 8:45 am]
BILLING CODE 4910-13-U
