[Federal Register Volume 63, Number 156 (Thursday, August 13, 1998)]
[Rules and Regulations]
[Pages 43297-43299]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21655]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-128-AD; Amendment 39-10711; AD 98-17-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
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 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.
That AD 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 amendment adds a new requirement to accomplish those
repetitive operational tests on other airplanes. This amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. 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 result in
severely reduced controllability of the airplane.
DATES: Effective September 17, 1998.
The incorporation by reference of certain publications, as 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).
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of October 3, 1997 (62 FR 45710, August 29,
1997).
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: 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 97-18-09,
amendment 39-10119 (62 FR 45710, August 29, 1997), which is applicable
to all Airbus Model A310 and A300-600 series airplanes, was published
in the Federal Register on June 3, 1998 (63 FR 30150). The action
proposed to supersede AD 97-18-09 to continue to require 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 proposed to continue to require
modification of certain flight control computers, and a modification to
the autopilot. For certain airplanes, that AD also proposed to continue
to require repetitive operational testing of the modified autopilot to
determine if the disconnect function operates properly, and repair, if
necessary. The action also proposed to add a new requirement to
accomplish those repetitive operational tests on other airplanes.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
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 94 airplanes of U.S. registry that will be
affected by this AD.
The AFM revision that was required previously by AD 96-08-07,
amendment 39-9573, and is 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 94-21-07, amendment 39-9049, and is 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 is currently required 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
[[Page 43298]]
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 is currently required 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 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 39-10119 (62 FR
45710, August 29, 1997), and by adding a new airworthiness directive
(AD), amendment 39-10711, to read as follows:
98-17-09 Airbus Industrie: Amendment 39-10711. 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:
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.
[[Page 43299]]
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.
(h) Except as provided by paragraph (a) of this AD, the actions
shall be done in accordance with the following Airbus service
bulletins.
(1) The incorporation by reference of Airbus Service Bulletin
A310-22-2036, dated December 14, 1993; and Airbus Service Bulletin
A300-22-6021, Revision 1, dated December 24, 1993, 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).
(2) The incorporation by reference of 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; and Airbus
Service Bulletin A300-22-6035, dated July 16, 1996; as applicable;
was approved previously by the Director of the Federal Register as
of October 3, 1997 (62 FR 45710, August 29, 1997).
(3) 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 97-373-237(B), dated December 3, 1997.
(i) This amendment becomes effective on September 17, 1998.
Issued in Renton, Washington, on August 6, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-21655 Filed 8-12-98; 8:45 am]
BILLING CODE 4910-13-U
