[Federal Register Volume 62, Number 168 (Friday, August 29, 1997)]
[Rules and Regulations]
[Pages 45710-45712]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-23099]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-41-AD; Amendment 39-10119; AD 97-18-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Airbus Model A310 and A300-600 series
airplanes, that currently requires a revision to the Airplane Flight
Manual (AFM) that warns the flight crew of certain consequences
associated with overriding the autopilot when it is in the pitch
control axis. That AD also requires modification of certain flight
control computers (FCC). That AD was prompted by the results of an FAA
review of the requirements of an earlier AD. This amendment requires a
modification to the autopilot that would enable the flight crew to
disconnect the autopilot when direct force is applied to the control
column, regardless of its mode and the altitude of the airplane;
accomplishment of that modification terminates the current requirement
to revise the AFM. This amendment also requires repetitive operational
testing of the modified autopilot to determine if the disconnect
function operates properly, and repair, if necessary. The actions
specified by this AD are intended to prevent an out-of-trim condition
between the trimmable horizontal stabilizer and the elevator, which
could severely reduce controllability of the airplane.
DATES: Effective October 3, 1997.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of October 3, 1997.
The incorporation by reference of certain other publications listed
in the regulations was approved previously by the Director of the
Federal Register as of May 23, 1996 (61 FR 16873, April 18, 1996).
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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2589; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 96-08-07,
amendment 39-9573 (61 FR 16873, April 18, 1996), which is applicable to
all Airbus Model A310 and A300-600 series airplanes, was published in
the Federal Register on April 9, 1997 (62 FR 17131). The action
proposed to supersede AD 96-08-07 to continue to require a revision to
the Limitations Section of the AFM that warns the flight crew of
certain consequences associated with overriding the autopilot when it
is in the pitch control axis, and modification of certain FCC's.
The action also proposed to require a modification to the autopilot
that would enable the flight crew to manually disconnect it, regardless
of the autopilot mode and the altitude of the airplane. After this
modification has been accomplished, the action proposed to require
removal of the revision to the AFM that is currently required by AD 96-
08-07. In addition, the action proposed to require repetitive
operational testing of the modified autopilot to determine if the
disconnect function operates properly, and repair, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due
[[Page 45711]]
consideration has been given to the two comments received.
Both commenters support the proposed rule.
Clarification of Requirements of the Final Rule
The FAA has revised paragraph (d)(2)(ii) of this final rule to
clarify that the operational test applies to the autopilot disconnect
feature.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 77 Airbus Model A300-600 and A310 series
airplanes of U.S. registry that will be affected by this proposed AD.
The modification of certain FCC's that is required by AD 96-08-07
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 on U.S.
operators is estimated to be $4,620, or $60 per airplane.
The AFM revision that is required by AD 96-08-07 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 $4,620, or $60 per airplane.
The modification of the autopilot that is currently required by
this new AD will take approximately 25 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts will cost approximately $1,578 per airplane. Based on these
figures, the cost impact of the new modification requirement of this AD
on U.S. operators is estimated to be $237,006, or $3,078 per airplane.
The operational test that is currently required by this new AD will
take 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 operational test requirement of
this AD on U.S. operators is estimated to be $32,340 per test cycle, 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 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 removing amendment 39-9573 (61 FR
16873, April 18, 1996), and by adding a new airworthiness directive
(AD), amendment 39-10119, to read as follows:
97-18-09 Airbus Industrie: Amendment 39-10119. Docket 97-NM-41-AD.
Supersedes AD 96-08-07, Amendment 39-9573.
Applicability: All Model A300-600 and A310 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
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 (e) 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 severely reduce
controllability of the airplane, accomplish the following:
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 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
[[Page 45712]]
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.
New actions required by this ad:
(d) For airplanes on which Modification No. 11454 [reference
Airbus Service Bulletin A310-22-2044 (for Model A310 series
airplanes) or Airbus Service Bulletin A300-22-6032 (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 the effective date of this AD, 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 (b) 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.
(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, 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.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
(g) The modification of the FCC's shall be done in accordance
with Airbus Service Bulletin A310-22-2036, dated December 14, 1993,
or Airbus Service Bulletin A300-22-6021, Revision 1, dated December
24, 1993, as applicable. The incorporation by reference of those
documents was approved previously by the Director of the Federal
Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as
of May 23, 1996 (61 FR 16873, April 18, 1996). The modification and
operational test of the autopilot shall be done in accordance with
Airbus Service Bulletin A310-22-2044, Revision 1, dated January 8,
1997; Airbus Service Bulletin A300-22-6032, Revision 1, dated
January 8, 1997; Airbus Service Bulletin A310-22-2047, dated July
16, 1996; or Airbus Service Bulletin A300-22-6035, dated July 16,
1996; as applicable. The incorporation by reference of those
documents 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.
(h) This amendment becomes effective on October 3, 1997.
Issued in Renton, Washington, on August 25, 1997.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-23099 Filed 8-28-97; 8:45 am]
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