[Federal Register Volume 63, Number 106 (Wednesday, June 3, 1998)]
[Proposed Rules]
[Pages 30150-30152]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-14610]
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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. 106 / Wednesday, June 3, 1998 /
Proposed Rules
[[Page 30150]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-128-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 the supersedure of an existing
airworthiness directive (AD), applicable to all Airbus Model A310 and
A300-600 series airplanes, that currently requires a revision of the
Airplane Flight Manual that warns the flightcrew of certain
consequences associated with overriding the autopilot when it is in the
pitch control axis. It also requires modification of certain flight
control computers, and a modification to the autopilot. For certain
airplanes, that AD also requires repetitive operational testing of the
modified autopilot to determine if the disconnect function operates
properly, and repair, if necessary. This action would add a new
requirement to accomplish those repetitive operational tests on other
airplanes. 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 an out-of-trim condition between the trimmable horizontal
stabilizer and the elevator, which could result in severely reduced
controllability of the airplane.
DATES: Comments must be received by July 6, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-128-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-128-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-128-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On August 25, 1997, the FAA issued AD 97-18-09, amendment 39-10119
(62 FR 45710, August 29, 1997), applicable to all Airbus Model A310 and
A300-600 series airplanes, to require a revision to the Airplane Flight
Manual (AFM) that warns the flightcrew of certain consequences
associated with overriding the autopilot when it is in the pitch
control axis, modification of certain flight control computers (FCC),
and modification of the autopilot, which would enable the flightcrew to
disconnect the autopilot when direct force is applied to the control
column, regardless of its mode and the altitude of the airplane. That
AD also requires repetitive operational testing of the modified
autopilot to determine if the disconnect function operates properly,
and repair, if necessary. That action was prompted by the results of an
FAA review of the requirements of an earlier AD. The requirements of
that AD are intended to prevent an out-of-trim condition between the
trimmable horizontal stabilizer and the elevator, which could result in
severely reduced controllability of the airplane.
Actions Since Issuance of Previous Rule
Since the issuance of AD 97-18-09, the Direction Generale de
l'Aviation Civile (DGAC), which is the airworthiness authority for
France, has issued French airworthiness directive 97-373-237(B), dated
December 3, 1997, which specifies that Airbus Model A310 and A300-600
series airplanes on which the modification of the autopilot (reference
Airbus Modification 11454) has been accomplished during production
should be subject to the same repetitive operational tests required to
be performed on Airbus Model A310 and A300-600 series airplanes
modified in accordance with Airbus Service Bulletin A310-22-2044,
Revision 1, or A300-22-6032, Revision 1, both dated January 8, 1997
(which were referenced by AD 97-18-09 as the appropriate sources of
service information).
In light of the criticality of the unsafe condition (an out-of-trim
condition between the trimmable horizontal stabilizer and the elevator,
which could
[[Page 30151]]
severely reduce controllability of the airplane), modification of the
autopilot alone may not provide the degree of safety assurance
necessary for the transport airplane fleet. Therefore, repetitive
operational testing of the modified autopilot to determine if the
disconnect function operates properly is necessary to ensure long term
continued operational safety, whether the modification was installed
during production or in accordance with AD 97-18-09.
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 97-18-09 to
continue to require a revision to the Limitations Section of the AFM
that warns the flightcrew of certain consequences associated with
overriding the autopilot when it is in the pitch control axis;
modification of certain FCC's; modification of the autopilot and
removal of the revision to the AFM once the modification has been
accomplished; repetitive operational testing of the modified autopilot
to determine if the disconnect function operates properly; and repair,
if necessary.
This proposed AD would add a new requirement for accomplishment of
the same repetitive operational tests on Airbus Model A310 and A300-600
series airplanes that received the modification to the autopilot during
production.
Cost Impact
There are approximately 94 airplanes of U.S. registry that would be
affected by this proposed AD.
The AFM revision that was required previously by AD 96-08-07 and
retained in this AD, takes approximately 1 work hour per airplane to
accomplish, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the currently required AFM revision
on U.S. operators is estimated to be $5,640, or $60 per airplane.
The modification of certain FCC's that was required previously by
AD 96-08-07 and retained in this AD, takes approximately 1 work hour
per airplane to accomplish, at an average labor rate of $60 per work
hour. Required parts will be supplied by the manufacturer at no cost to
operators. Based on these figures, the cost impact of the currently
required modification of FCC's on U.S. operators is estimated to be
$5,640, or $60 per airplane.
The modification of the autopilot that was required previously by
AD 97-18-09 and retained in this AD, takes approximately 25 work hours
per airplane to accomplish, at an average labor rate of $60 per work
hour. Required parts cost approximately $1,578 per airplane. Based on
these figures, the cost impact of the currently required modification
of the autopilot on U.S. operators is estimated to be $289,332, or
$3,078 per airplane.
The operational test that was required previously by AD 97-18-09
and retained in this AD, takes approximately 7 work hours per airplane,
per test cycle, to accomplish, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the currently required
operational test requirement on U.S. operators is estimated to be
$39,480, or $420 per airplane, per test cycle.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 removing amendment 39-10119 (62 FR
45710, August 29, 1997), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 98-NM-128-AD. Supersedes AD 97-18-09,
Amendment 39-10119.
Applicability: All Model A310 and A300-600 series airplanes,
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 request approval for an
alternative method of compliance in accordance with paragraph (f) 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 an out-of-trim condition between the trimmable
horizontal stabilizer and the elevator, which could result in
severely reduced controllability of the airplane, accomplish the
following:
[[Page 30152]]
RESTATEMENT OF ACTIONS REQUIRED BY AD 96-08-07, AMENDMENT 39-9573
(a) Within 10 days after May 23, 1996 (the effective date of AD
96-08-07, amendment 39-9573), revise the Limitations Section of the
FAA-approved Airplane Flight Manual (AFM) to include the information
contained in paragraph (a)(1) or (a)(2) of this AD, as applicable.
This may be accomplished by inserting a copy of this AD in the AFM.
The AFM limitation required by AD 94-21-07, amendment 39-9049, may
be removed following accomplishment of the requirements of this
paragraph.
(1) For airplanes on which the flight control computers (FCC)
have not been modified in accordance with the requirements of
paragraph (b) of this AD:
``Overriding the autopilot (AP) in pitch axis does not cancel
the AP autotrim when LAND TRACK mode [green LAND on both Flight Mode
Annunciators (FMA)] or GO-AROUND mode is engaged. In these modes, if
the pilot counteracts the AP, the autotrim will trim against pilot
input. This could lead to a severe out-of-trim situation in a
critical phase of flight.''
(2) For airplanes on which the FCC's have been modified in
accordance with the requirements of paragraph (b) of this AD:
``Overriding the autopilot (AP) in pitch axis does not cancel
the AP autotrim when LAND TRACK mode (green LAND on both FMA's) is
engaged, or GO-AROUND mode is engaged below 400 feet radio altitude
(RA). In these modes, if the pilot counteracts the AP, the autotrim
will trim against pilot input. This could lead to a severe out-of-
trim situation in a critical phase of flight.''
RESTATEMENT OF ACTIONS REQUIRED BY AD 94-21-07, AMENDMENT 39-9049
(b) For airplanes equipped with FCC's having either part number
(P/N) B470ABM1 (for Model A310 series airplanes) or B470AAM1 (for
Model A300-600 series airplanes): Within 60 days after November 2,
1994 (the effective date of AD 94-21-07, amendment 39-9049), modify
the FCC's in accordance with Airbus Service Bulletin A310-22-2036,
dated December 14, 1993 (for Model A310 series airplanes), or Airbus
Service Bulletin A300-22-6021, Revision 1, dated December 24, 1993
(for Model A300-600 series airplanes), as applicable.
(c) As of November 2, 1994, no person shall install a FCC having
either P/N B470ABM1 or B470AAM1 on any airplane.
RESTATEMENT OF ACTIONS REQUIRED BY AD 97-18-09, AMENDMENT 39-10119
(d) For airplanes on which Modification No. 11454 [reference
Airbus Service Bulletin A310-22-2044, Revision 1 (for Model A310
series airplanes) or Airbus Service Bulletin A300-22-6032, Revision
1 (for Model A300-600 series airplanes)] has not been installed:
Accomplish paragraphs (d)(1), (d)(2)(i), and (d)(2)(ii) of this AD.
(1) Within 24 months after October 3, 1997 (the effective date
of AD 97-18-09, amendment 39-10119), modify the autopilot in
accordance with Airbus Service Bulletin A310-22-2044, Revision 1,
dated January 8, 1997 (for Model A310 series airplanes), or Service
Bulletin A300-22-6032, Revision 1, dated January 8, 1997 (for Model
A300-600 series airplanes), as applicable. The requirements of
paragraph (a) of AD 95-25-09, amendment 39-9455, if applicable, must
be accomplished prior to or at the same time the requirements of
this paragraph are accomplished.
(2) Prior to further flight following accomplishment of
paragraph (d)(1) of this AD:
(i) Remove the AFM revisions required by paragraph (a) of this
AD; and
(ii) Perform an operational test of this autopilot disconnect
feature to determine that it operates properly, in accordance with
Airbus Service Bulletin A310-22-2047, dated July 16, 1996 (for Model
A310 series airplanes), or Service Bulletin A300-22-6035, dated July
16, 1996 (for Model A300-600 series airplanes), as applicable. If
any discrepancy is detected, prior to further flight, repair it in
accordance with the applicable service bulletin. Repeat this test
thereafter at intervals not to exceed 18 months.
NEW ACTIONS REQUIRED BY THIS AD
(e) For airplanes on which Modification No. 11454 was installed
during production: Within 18 months after the date of manufacture of
the airplane, or within 6 months after the effective date of this
AD, whichever occurs later, accomplish the actions specified in
paragraph (d)(2)(ii) of this AD.
(f) 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.
(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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 97-373-237(B), dated December 3, 1997.
Issued in Renton, Washington, on May 27, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-14610 Filed 6-2-98; 8:45 am]
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