[Federal Register Volume 61, Number 13 (Friday, January 19, 1996)]
[Proposed Rules]
[Pages 1289-1291]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-490]
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Proposed Rules
Federal Register
________________________________________________________________________
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. 61, No. 13 / Friday, January 19, 1996 /
Proposed Rules
[[Page 1289]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-245-AD]
Airworthiness Directives; Airbus Industrie Model 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 to supersede two existing airworthiness
directives (AD), applicable to Airbus Industrie Model A310 and A300-600
series airplanes. One AD currently requires repetitive operational
tests of feel and limitation computers (FLC) 1 and 2; the other AD
requires replacement of certain FLC's on Model A300-600 series
airplanes. Those AD's were prompted by reports that the elevator
control operated with stiffness. The actions specified by those AD's
are intended to prevent stiff operation of the elevator control and
undetected loss of rudder travel limitation function, which could
adversely affect the controllability of the airplane. This action would
require installation of new FLC's, which would terminate the currently
required repetitive operational tests. This action also would revise
the applicability of the rule to delete airplanes on which these new
FLC's have been installed previously.
DATES: Comments must be received by February 21, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-245-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: Tom Groves, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-1503; fax (206) 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 94-NM-245-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-103, Attention: Rules
Docket No. 94-NM-245-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On December 28, 1993, the FAA issued AD 93-24-51, amendment 39-8783
(59 FR 507, January 5, 1994), which is applicable to all Airbus Model
A310 and A300-600 series airplanes. That AD requires repetitive
operational tests of the Feel and Limitation Computers (FLC) 1 and 2.
Any FLC that fails the operational test is required to be repaired or
replaced in accordance with a method approved by the FAA. That AD was
prompted by a report that the elevator control on a Model A300-600
series airplane operated with stiffness. The requirements of that AD
are intended to prevent stiff operation of the elevator control and
undetected loss of rudder travel limitation function, which could
adversely affect controllability of the airplane.
Subsequent to the issuance of that AD, the FAA issued AD 94-09-16,
amendment 39-8905 (59 FR 23133, May 5, 1994), applicable to certain
Model A300-600 series airplanes. That AD requires the replacement of
certain FLC's with FLC's that have been modified by an adjustment of
the ``UNDERVOLTAGE DETECTION'' signal, which will preclude stiff
operation of the elevator control. That AD was prompted by reports that
the elevator control on several in-service airplanes operated with
stiffness. The cause of the stiffness problem was found to be
associated with spurious undervoltage detection in the FLC. The
requirements of AD 94-09-16 are intended to prevent certain aspects of
stiff operation of the elevator control and undetected loss of the
rudder travel limitation function. Airplanes on which these modified
FLC's were installed were still subject to the repetitive operational
tests required by AD 93-24-51.
Since the issuance of those two AD's, the Direction Generale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France, has advised the FAA that the manufacturer has developed new
modified FLC's for installation on Model A310 and A300-600 series
airplanes that will positively address the unsafe condition associated
with stiff operation of the elevator control.
Airbus Industrie has issued the following service bulletins:
1. Service Bulletin A310-27-2068, Revision 1, dated March 16, 1994,
and
[[Page 1290]]
Revision 2, dated April 19, 1995, pertain to Model A310 series
airplanes. These service bulletins describe procedures for installing
Modification 10668, which entails a modification of the FLC to adjust
the power supply monitoring. (The power supply is optimized in order to
avoid stiff operation of the elevator due to a spurious undervoltage
detection in the FLC's.)
2. Service Bulletin A310-27-2070, dated May 5, 1994, also pertains
to Model A310 series airplanes. This service bulletin describes
procedures for installing Modification 10712, which entails a
modification of the FLC's to include improved fault detection, which is
intended to avoid possible lack of warning when the undervoltage power
supply detection is active. Accomplishment of this modification
necessitates the simultaneous or previous accomplishment of
Modification 10668.
3. Service Bulletin A300-27-6025, Revision 1, dated August 31,
1994, and Revision 2, dated April 19, 1995, pertain to Model A300-600
series airplanes. These service bulletins describe procedures for
installing Modification 10667, which entails a modification of the FLC
to adjust the power supply monitoring. The power supply is optimized in
order to avoid stiff operation of the elevator due to a spurious
undervoltage detection in the FLC's. (The original issue of this
service bulletin, dated September 15, 1993, was referenced in AD 94-09-
16 as the source for service instructions.)
4. Service Bulletin A300-27-6026, dated May 5, 1994, also pertains
to Model A300-600 series airplanes. This service bulletin describes
procedures for installing Modification 10713, which entails a
modification of the FLC's to include improved fault detection, which is
intended to avoid possible lack of warning when the undervoltage power
supply detection is active. Accomplishment of this modification
necessitates the simultaneous or previous accomplishment of
Modification 10667.
The DGAC classified these service bulletins as mandatory and issued
the following French airworthiness directives (CN) in order to assure
the continued airworthiness of these airplanes in France:
1. CN 93-202-153(B)R1, dated August 3, 1994;
2. CN 94-046-156(B)R2, dated November 9, 1994; and
3. CN 95-202-188(B), dated October 11, 1995.
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.
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 both AD 93-24-51
and AD 94-09-16. This new proposed AD would continue to require
repetitive operational tests of the FLC's until new modified FLC's are
installed. The installation would be required to be accomplished in
accordance with the service bulletins described previously.
This proposed action also would revise the applicability of the
rule to eliminate those airplanes on which the new modified FLC's have
been installed previously.
Additionally, as a result of recent communications with the Air
Transport Association (ATA) of America, the FAA has learned that, in
general, some operators may misunderstand the legal effect of AD's on
airplanes that are identified in the applicability provision of the AD,
but that have been altered or repaired in the area addressed by the AD.
The FAA points out that all airplanes identified in the applicability
provision of an AD are legally subject to the AD. If an airplane has
been altered or repaired in the affected area in such a way as to
affect compliance with the AD, the owner or operator is required to
obtain FAA approval for an alternative method of compliance with the
AD, in accordance with the paragraph of each AD that provides for such
approvals. A note has been included in this notice to clarify this
long-standing requirement.
There are approximately 55 Airbus Model A300-600 and A310 series
airplanes of U.S. registry that would be affected by this proposed AD.
The operational tests of the FLC's (which are currently required by
AD 93-24-51 and would be retained in this AD) take approximately .5
work hour per airplane to accomplish, at an average labor rate of $60
per work hour. Based on these figures, the cost impact on U.S.
operators of the tests currently required is estimated to be $1,650, or
$30 per airplane, per operational test.
Installation of the modified FLC's proposed in this AD action would
take approximately 5 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts would be
provided by the manufacturer at no cost to operators. Based on these
figures, the cost impact on U.S. operators of this proposed
installation is estimated to be $16,500, or $300 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.
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 USC 106(g), 40113, 44701.
[[Page 1291]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8783 (59 FR
507, January 5, 1994), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 94-NM-245-AD. Supersedes AD 93-24-51,
amendment 39-8783, and AD 94-09-16, amendment 39-39-8905.
Applicability: Model A310 series airplanes on which
Modifications 10712 and 10668 were not incorporated during
production, or that are equipped with Feel and Limitation Computers
(FLC) having the part numbers listed below; and Model A300-600
series airplanes on which Modifications 10713 and 10667 were not
incorporated during production, or that are equipped with FLC's
having the part numbers listed below; certificated in any category.
------------------------------------------------------------------------
Airplane model FLC part No.
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A310...................................... 35-900-1008-009
35-900-1009-011
35-900-1011-011
35-900-1011-011-A
A300-600.................................. 35-900-2000-200
35-900-2000-201
35-900-2002-201
35-900-2002-201-A
35-900-3002-302
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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 use the authority
provided in paragraph (f)(1) 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 stiff operation of the elevator control and
undetected loss of rudder travel limitation function, which may
adversely affect controllability of the airplane, accomplish the
following:
(a) For all airplanes: Within 7 days after January 20, 1994 (the
effective date of AD 93-24-51, amendment 39-8783), perform an
operational test to verify proper operation of the Feel and
Limitation Computers (FLC) 1 and 2, in accordance with Airbus
Industrie All Operator Telex 27-14, dated November 2, 1993.
(1) If the operational test is successful, repeat the test at
intervals not to exceed 7 days until the requirements of paragraph
(c) or (d) of this AD, as applicable, are accomplished.
(2) If any FLC fails the operational test, prior to further
flight, accomplish the procedures specified in either paragraph (c)
or (d) of this AD, as applicable.
(b) Except as provided by paragraphs (c) and (d) of this AD: As
of January 20, 1994 (the effective date of AD 93-24-51, amendment
39-8783), no airplane shall be operated with an inoperative pitch
feel system or inoperative pitch feel fault lights.
(c) For Model A310 series airplanes: Within 6 months after the
effective date of this AD, replace or modify the currently installed
FLC's in accordance with paragraphs (c)(1) and (c)(2) of this AD.
Installation of FLC's that incorporate both Modifications 10668 and
10712 constitutes terminating action for the repetitive operational
tests of the FLC's required by paragraph (a) of this AD, and for the
operating limitations required by paragraph (b) of this AD.
(1) Install Modification 10668 in accordance with Airbus Service
Bulletin A310-27-2068, Revision 1, dated March 16, 1994, or Revision
2, dated April 19, 1995. And
(2) Install Modification 10712 in accordance with Airbus Service
Bulletin A310-27-2070, dated May 5, 1994.
(d) For Model A300-600 series airplanes: Accomplish the
requirements of paragraphs (d)(1), and (d)(2) of this AD.
Accomplishment of these actions constitutes terminating action for
the operational tests required by paragraph (a) of this AD, and for
the operating limitations required by paragraph (b) of this AD.
(1) Within 45 days after May 20, 1994 (the effective date of AD
94-09-16, amendment 39-8905), replace the FLC's, having part number
(P/N) 35-900-2000-200 or 35-900-2000-201, serial numbers 755 and
subsequent, with an FLC that has been previously modified, in
accordance with Airbus Service Bulletin A300-27-6025, dated
September 15, 1993, or Revision 1, dated August 31, 1994.
(2) Within 6 months after the effective date of this AD, replace
or modify the FLC's in accordance with paragraphs (d)(2)(i) and
(d)(2)(ii) of this AD. Installation of FLC's that incorporate both
Modifications 10667 and 10713 constitutes terminating action for the
repetitive operational tests of the FLC's required by paragraph (a)
of this AD, and for the operating limitations required by paragraph
(b) of this AD.
(i) Install Modification 10667 in accordance with Airbus Service
Bulletin A300-27-6025, dated September 15, 1993; or Revision 1,
dated August 31, 1994; or Revision 2, dated August 19, 1995. And
(ii) Install Modification 10713 in accordance with Airbus
Service Bulletin A300-27-6026, dated May 5, 1994.
Note 2: The accomplishment of paragraph (d)(1) of this AD
entails installing FLC's that incorporate Modification 10667, as
does the accomplishment of paragraph (d)(2)(i). Paragraph (d)(2)(i)
is included in this AD because the list of part numbers of affected
FLC's in paragraph (d)(1), as well as in the parallel requirement of
AD 94-09-16, is not comprehensive. Additional affected FLC part
numbers were identified subsequent to the issuance of AD 94-09-16;
FLC's having those part numbers are subject to the requirements of
paragraph (d)(2) of this AD.
(e) As of the effective date of this AD, operational tests in
accordance with paragraph (a) of this AD may be discontinued on
modified FLC's having the part numbers listed in Table 1 of this AD.
Table 1
------------------------------------------------------------------------
Airplane model FLC part No.
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A310...................................... 35-900-1010-011
35-900-1012-011
35-900-1012-011-A
A300-600.................................. 35-900-3004-302
35-900-2001-201
35-900-2003-201
35-900-2003-201-A
------------------------------------------------------------------------
(f)(1) 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.
(2) Alternative methods of compliance, approved in accordance
with AD 93-24-51, amendment 398783; or AD 94-09-16, amendment 39-
8905, are approved as alternative methods of compliance with this
AD.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(g) 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.
Issued in Renton, Washington, on January 10, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-490 Filed 1-18-96; 8:45 am]
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