AD Amdt-39-10119

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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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