AD Amdt-39-9573

[Federal Register Volume 61, Number 76 (Thursday, April 18, 1996)]
[Rules and Regulations]
[Pages 16873-16874]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 96-9337]



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Federal Register / Vol. 61, No. 76 / Thursday, April 18, 1996 / Rules 
and Regulations

[[Page 16873]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-137-AD; Amendment 39-9573; AD 96-08-07]


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 FAA-approved 
Airplane Flight Manual (AFM) that warns the flight crew about certain 
consequences associated with overriding the autopilot while it is in 
the COMMAND mode or in the pitch axis. That AD also requires 
modification of certain flight control computers (FCC). This amendment 
requires replacement of the currently required revision to the AFM with 
a newly worded revision that explains the effect the modification of 
the FCC's has on the operation and performance of the autopilot and 
that clarifies the limitation for unmodified airplanes. This amendment 
is prompted by the results of an FAA review of the requirements of the 
existing AD. 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 May 23, 1996.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of November 2, 1994 (59 FR 52414, October 18, 1994).

ADDRESSES: 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 (206) 
227-2589; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-21-07, 
amendment 39-9049 (59 FR 52414, October 18, 1994), which is applicable 
to all Airbus Model A310 and A300-600 series airplanes, was published 
in the Federal Register on October 11, 1995 (60 FR 52872). The action 
proposed to require modification of certain flight control computers 
(FCC). The action also proposed to require replacement of the currently 
required revision to the Limitations Section of the FAA-approved 
Airplane Flight Manual (AFM) with a newly worded revision that explains 
the effect the modification of the FCC's has on the operation and 
performance of the autopilot and that clarifies the limitation for 
unmodified airplanes.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the three comments received.
    All of the commenters support the proposed rule.
    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.
    There are approximately 15 Model A310 series airplanes and 36 Model 
A300-600 series airplanes of U.S. registry that will be affected by 
this AD.
    The modification that is currently required by AD 94-21-07 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 the operator. 
Based on these figures, the cost impact on U.S. operators of the 
actions currently required by AD 94-21-07 is estimated to be $3,060, or 
$60 per airplane.
    The newly revised AFM limitation that is required by this AD action 
will take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts will be nominal 
in cost. Based on these figures, the cost impact on U.S. operators of 
the new requirements of this AD is estimated to be $3,060, or $60 per 
airplane.
    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.
    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:

[[Page 16874]]

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9049 (59 FR 
52414, October 18, 1994), and by adding a new airworthiness directive 
(AD), amendment 39-9573, to read as follows:

96-08-07 Airbus Industrie: Amendment 39-9573. Docket 95-NM-137-AD. 
Supersedes AD 94-21-07, Amendment 39-9049.

    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 (d) 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 may severely reduce 
controllability of the airplane, accomplish the following:
    (a) Within 10 days after the effective date of this AD, 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.''
    (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.

    Note 2: Paragraph (b) of this AD merely restates the 
requirements of paragraph (b) of AD 94-21-07, amendment 39-9049. As 
allowed by the phrase, ``unless accomplished previously,'' specified 
in the compliance statement of this AD, if those requirements of AD 
94-21-07 have already been accomplished, this AD does not require 
that those actions be repeated.

    (c) As of November 2, 1994 (the effective date of AD 94-21-07, 
amendment 39-9049), no person shall install an FCC having either P/N 
B470ABM1 or B470AAM1 on any airplane.
    (d) 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 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.

    (e) 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.
    (f) The modification 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 these 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 November 2, 
1994 (59 FR 52414, October 18, 1994). 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.
    (g) This amendment becomes effective on May 23, 1996.

    Issued in Renton, Washington, on April 10, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-9337 Filed 4-17-96; 8:45 am]
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