[Federal Register Volume 64, Number 192 (Tuesday, October 5, 1999)]
[Proposed Rules]
[Pages 53953-53956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25769]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-303-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, A300-600
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Airbus Model A300,
A310, and A300-600 series airplanes, that currently 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. It also
requires eventual modification of the free fall control mechanism of
the landing gear, which constitutes terminating action for the
repetitive functional tests. That amendment was prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. This proposed AD would require, for certain
airplanes, that the modification of the free fall control mechanism of
the landing gear be accomplished in accordance with a corrected version
of the manufacturer's service bulletin. The actions specified by this
proposal 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 November 4, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-303-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
[[Page 53954]]
postcard on which the following statement is made: ``Comments to Docket
Number 98-NM-303-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-303-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On June 29, 1998, the FAA issued AD 98-14-13, amendment 39-10646
(63 FR 36832, July 8, 1998), applicable to certain Airbus Model A300,
A310, and A300-600 series airplanes, 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. It also requires eventual
modification of the free fall control mechanism of the landing gear,
which constitutes terminating action for the repetitive functional
tests. That amendment was prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The requirements of that 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.
Actions Since Issuance of Previous Rule
Since issuance of AD 98-14-13, the manufacturer and the Direction
Generale de l'Aviation Civile (DGAC), which is the airworthiness
authority for France, have advised the FAA that an error exists in
Airbus Service Bulletin A310-32-2111, Revision 01, dated October 10,
1997. That service bulletin describes procedures for modification of
the free fall control mechanism of the landing gear on Airbus Model
A310 series airplanes, and was referenced as the appropriate source of
service information for the modification of Airbus Model A310 series
airplanes required by that AD. Certain part numbers shown in that
service bulletin are incorrect for one of the two telescopic rod
assemblies of the free fall control mechanism of the MLG. This error
was corrected in Revision 02, dated June 23, 1998, of Airbus Service
Bulletin A310-32-2111.
The FAA now has determined that further rulemaking action is
necessary to require the modification of Airbus Model A310 series
airplanes, described previously, to be accomplished in accordance with
Revision 02 of Airbus Service Bulletin A310-32-2111, and, if the
modification was installed in accordance with an earlier service
bulletin revision, removal of the discrepant parts and installation of
the correct part number parts.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A300-32-0425 (for Model A300
series airplanes), A300-32-6072 (for Model A300-600 series airplanes),
and A310-32-2111 (for Model A310 series airplanes); all Revision 02;
all dated June 23, 1998. These service bulletins describe procedures
for modification of the free fall control mechanism of the landing
gear. The modification includes removing telescopic 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 previously.
The procedures for the modification in Revision 02 of the service
bulletins for Model A300 and A300-600 series airplanes are identical to
those described in Revision 01 of the service bulletins (which were
referenced in AD 98-14-13). As discussed previously, the procedures for
the modification in Revision 02 of the service bulletin for Model A310
series airplanes differ from those described in Revision 01 of the
service bulletin (which was referenced in AD 98-14-13) in that certain
part numbers for one of the two telescopic rod assemblies have been
corrected in Revision 02.
Accomplishment of the actions specified in the service bulletins
described previously is intended to adequately address the identified
unsafe condition. The DGAC classified the service bulletins as
mandatory and issued French airworthiness directive 97-113-221(B) R2,
dated August 12, 1998, 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 supersede AD 98-14-13 to
continue 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. The proposed AD would continue to require
eventual modification of the free fall control mechanism of the landing
gear, which constitutes terminating action for the repetitive
functional tests. The actions would be required to be accomplished in
accordance with the service bulletins described previously. This action
would require, for certain airplanes, that the modification of the free
fall control mechanism of the landing gear be accomplished in
accordance with a later corrected version of the manufacturer's service
bulletin.
Explanation of Compliance Time for Model A310 Series Airplanes
Operators should note that, while the appropriate source of service
information that would be required for this AD for Model A310 series
airplanes has changed, the compliance time remains the same. The FAA
has determined that the compliance time, as proposed, represents an
appropriate interval in which the modification can be accomplished in
accordance with Revision 02 of Airbus Service Bulletin A310-32-2111 in
a timely manner and still maintain an adequate level of safety.
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 currently required operational test, at an average labor rate of
$60 per work hour. Based on these figures, the cost impact of the
currently required operational test on U.S. operators is estimated to
be $22,680, or $180 per airplane.
[[Page 53955]]
It would take approximately 2 work hours per airplane to accomplish
the currently required functional test, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the currently
required 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 currently required modification on 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 currently required actions 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 modification on 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 currently required actions on U.S. operators of Model
A310 series airplanes is estimated to be $220,990, or $5,390 per
airplane.
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 removing amendment 39-10646 (63 FR
36832, July 8, 1998), and by adding a new airworthiness directive (AD),
to read as follows:
Airbus Industrie: Docket 98-NM-303-AD. Supersedes AD 98-14-13,
Amendment 39-10646.
Applicability: Model A300, A300-600, and A310 series airplanes,
certificated in any category, as identified below:
Model A300 and A300-600 series airplanes on which
Airbus Modification 02781 has been accomplished and on which neither
Airbus Modification 03433 nor 04443 has been accomplished;
Model A310 series airplanes on which Airbus
Modification 02781 has been accomplished and on which Airbus
Modification 03433 has not been accomplished; and
Model A310 series airplanes on which Airbus Service
Bulletin A310-32-2111, dated March 10, 1997, or Revision 01, dated
October 10, 1997; has been accomplished.
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:
Restatement of Actions Required by AD 98-14-13, Amendment 39-10646
(a) Within 600 flight hours after August 12, 1998 (the effective
date of AD 98-14-13, amendment 39-10646), 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 August 12, 1998, 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) or (d) 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) For Model A300 and A300-600 series airplanes: Within 66
months after August 12, 1998, modify the free fall control mechanism
of the landing gear in accordance with Airbus Industrie Service
Bulletin A300-32-0425, Revision 02 (for Model A300 series
airplanes); or A300-32-6072, Revision 02 (for Model A300-600 series
airplanes); each dated June 23, 1998; as applicable. Accomplishment
of the modification constitutes terminating action for the
repetitive functional tests required by paragraph (b) of this AD.
Note 2: Modifications accomplished in accordance with Airbus
Industrie Service Bulletin A300-32-0425, Revision 01 (for Model A300
series airplanes); or A300-32-6072, Revision 01 (for Model A300-600
series airplanes); each dated October 10, 1997; are acceptable for
compliance with the requirements of paragraph (c) of this AD.
New Actions Required by This AD
(d) For Model A310 series airplanes: Within 66 months after
August 12, 1998, modify the free fall control mechanism of the
landing gear in accordance with Airbus Industrie Service Bulletin
A310-32-2111, Revision 02, dated June 23, 1998. Accomplishment of
the modification constitutes terminating action for the repetitive
functional tests required by paragraph (b) of this AD.
Note 3: For Airbus Model A310 series airplanes, only a
modification accomplished in accordance with Airbus Industrie
Service Bulletin A310-32-2111, Revision 02, dated June 23, 1998, is
acceptable for compliance with the requirements of paragraph (d) of
this AD.
[[Page 53956]]
Alternative Methods of Compliance
(e) 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 4: 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
(f) 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 5: The subject of this AD is addressed in French
airworthiness directive 97-113-221(B) R2, dated August 12, 1998.
Issued in Renton, Washington, on September 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-25769 Filed 10-4-99; 8:45 am]
BILLING CODE 4910-13-P
