[Federal Register Volume 60, Number 237 (Monday, December 11, 1995)]
[Rules and Regulations]
[Pages 63412-63414]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30134]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-145-AD; Amendment 39-9455; AD 95-25-09]


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 adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A310 and A300-600 series airplanes, 
that requires that certain flight control computers be modified so that 
the autopilot will disengage when the airplane is in the ``go-around'' 
mode under certain conditions. This amendment is prompted by an 
accident in which the flight crew may have initiated an inadvertent go-
around which, following several subsequent actions by the crew and 
automated system, placed the airplane in a severe out-of-trim 
condition. The actions specified by this AD are intended to prevent an 
out-of-trim condition between the trimmable horizontal stabilizer and 
the elevator, which may severely reduce controllability of the 
airplane.

EFFECTIVE DATE: Effective January 10, 1996.

ADDRESSES: Information concerning this AD may be obtained from or 
examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056.

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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A310 and 
A300-600 series airplanes was published in the Federal Register on 
October 17, 1994 (59 FR 52273). That action proposed to require 
modification of flight control computers (FCC's) having part numbers 
(P/N's) B216ABM6, B350AAM1, B350AAM2, and B350AAM3 (for Model A310 
series airplanes); and P/N's B297AAM3, B297AAM4, and B297AAM5 (for 
Model A300-600 series airplanes). -
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due 

[[Page 63413]]
consideration has been given to the comments received. -
    Two commenters support the proposed rule. -
    One commenter points out that the Discussion section of the 
preamble to the notice incorrectly stated that ``the flight crew may 
have attempted a go-around while the airplane was in an out-of-trim 
condition.'' The commenter asserts that the subject airplane was 
correctly trimmed prior to the accident. The FAA acknowledges that the 
event that prompted the AD could be described more accurately. 
Therefore, the FAA has revised the Summary section and the statement of 
unsafe condition in the final rule. -
    The FAA has recently reviewed the figures it has used over the past 
several years in calculating the economic impact of AD activity. In 
order to account for various inflationary costs in the airline 
industry, the FAA has determined that it is necessary to increase the 
labor rate used in these calculations from $55 per work hour to $60 per 
work hour. The economic impact information, below, has been revised to 
reflect this increase in the specified hourly labor rate. -
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been included in this rule to clarify this long-standing requirement. -
    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 with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD. -
    The FAA estimates that 15 Model A310 series airplanes and 36 Model 
A300-600 series airplanes of U.S. registry will be affected by this AD. 
-
    Since the manufacturer has not yet developed one specific 
modification commensurate with the requirements of this AD, the FAA is 
unable at this time to provide specific information as to the number of 
work hours or cost of parts that would be required to accomplish the 
required modification. A further problem in developing a specific cost 
estimate is the fact that modification costs are expected to vary from 
operator to operator and from airplane to airplane depending upon 
airplane configuration. The compliance time of 24 months should provide 
ample time for the development, approval, and installation of an 
appropriate modification. -
    However, based on similar modifications accomplished previously on 
other FCC's installed on other airplane models, the FAA can reasonably 
estimate that the required modification may require as few as 2 work 
hours or as many as 50 work hours to accomplish, at an average labor 
rate of $60 per work hour. The cost of required parts could range from 
a negligible amount to as much as $1,500 per airplane. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be between $6,120 ($120 per airplane) and $229,500 ($4,500 
per airplane).
    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, 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-25-09  Airbus Industrie: Amendment 39-9455. Docket 94-NM-145-AD.

    Applicability: Model A310 series airplanes equipped with flight 
control computers (FCC) having part number (P/N) B216ABM6, B350AAM1, 
B350AAM2, or B350AAM3; and Model A300-600 series airplanes equipped 
with FCC's having P/N B297AAM3, B297AAM4, or B297AAM5; 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 use the authority 
provided in paragraph (c) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    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 24 months after the effective date of this AD, modify 
the FCC's in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (b) As of 24 months after the effective date of this AD, no 
person shall install an FCC having P/N B216ABM6, B350AAM1, B350AAM2, 
or B350AAM3 on any Model A310 series airplane; and P/N B297AAM3, 
B297AAM4, or B297AAM5 on any Model A300-600 series airplane.
    (c) 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 

[[Page 63414]]
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.

    (d) 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.
    (e) This amendment becomes effective on January 10, 1996.

    Issued in Renton, Washington, on December 5, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-30134 Filed 12-8-95; 8:45 am]
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