[Federal Register Volume 60, Number 39 (Tuesday, February 28, 1995)]
[Rules and Regulations]
[Pages 10805-10807]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3355]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-84-AD; Amendment 39-9145; AD 95-03-08]


Airworthiness Directives; Aerospatiale Model ATR42-300 and -320 
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 Aerospatiale Model ATR42-300 and -320 series 
airplanes, that requires an inspection to determine the model and 
orientation of certain flight control rods, and replacement with 
modified rods, if necessary. This amendment is prompted by reports of 
corrosion found on the pitch trim and rudder trim rods. The actions 
specified by this AD are intended to prevent problems associated with 
corrosion of the flight control rods, which could compromise the 
required strength of these items.

DATES: Effective on March 30, 1995. -
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 30, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 
03, 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:
Sam Grober, Aerospace Engineer, Standardization Branch, ANM-113, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (206) 227-1187; fax (206) 227-1100.

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 Aerospatiale Model ATR42 
series airplanes was published in the Federal Register on July 21, 1994 
(59 FR 37182). That action proposed to require an inspection to 
determine the orientation of the end of rudder trim and elevator trim 
fail-safe rods, and replacement of those rods having upwards-oriented 
ends. -
    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, Aerospatiale, requests that the compliance time 
specified in proposed paragraph (a)(1) for replacement of SARMA-type 
rods be extended to 18 months. The proposed rule would require that 
these rods be replaced prior to further flight after they are 
identified during the proposed inspection. The commenter considers this 
replacement requirement to be too restrictive. The FAA does not concur. 
The rule provides for a compliance time of 18 months for accomplishing 
the one-time inspection to determine if these types of rods are 
installed on the airplane. The FAA finds no justification for providing 
an additional time thereafter for replacement of the discrepant rods. 
The FAA does not consider the 18-month compliance time to be overly 
restrictive, since it provides ample time for operators to schedule the 
inspection during regularly scheduled maintenance and to acquire 
necessary parts for replacement. However, under the provisions of 
paragraph (b) of the final rule, if an operator were to find itself in 
a situation in which replacement parts were not immediately available, 
it could request approval for the use of an alternative method of 
compliance until parts became available. -
    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 added to this final rule to clarify this requirement. -
    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. -
    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 128 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 
[[Page 10806]] work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $30,720, or $240 per airplane. -
    The total cost impact figure discussed above is 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. -
    Should replacement of any of the flight control rods be necessary, 
the number of work hours and the cost of required parts would vary 
according to the type of replacement accomplished. In a ``worst case 
scenario'' (both subject rods needing replacement), the cost of parts 
would be approximately $6,000 per airplane. Labor necessary to 
accomplish replacement of a rod(s) would vary from 54 to 87 work hours, 
at an average labor rate of $60 per work hour. -
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended] -

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

95-03-08  Aerospatiale: Amendment 39-9145. Docket 94-NM-84-AD.

     -Applicability: Model ATR42-300 and -320 series airplanes on 
which Aerospatiale Modification 02723 has not been installed, 
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 (b) 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 problems associated with corrosion of the flight 
control rods, which could compromise the required strength of these 
items, accomplish the following: -
    (a) Within 18 months after the effective date of this AD, 
visually inspect the elevator trim and rudder trim fail-safe rods to 
determine the model and the orientation of the open end of the rod, 
in accordance with Aerospatiale Service Bulletin ATR42-27-0071, 
dated February 23, 1994. -
    (1) If a SARMA-type rod is installed at either of these 
locations, prior to further flight, replace that rod with a modified 
rod, in accordance with Aerospatiale Service Bulletin ATR42-27-0049, 
Revision 2, dated May 16, 1991. -
    (2) If a TAC-type rod is installed at either of these locations, 
and if the open end of the rod is oriented in any direction other 
than downwards, prior to further flight, accomplish the reverse 
installation procedures specified in Aerospatiale Service Bulletin 
ATR42-27-0048, Revision 2, dated May 16, 1991. -
    (b) 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.

     -(c) Special flight permits may be issued in accordance with 
Secs. 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. -
    (d) The actions shall be done in accordance with the following 
Aerospatiale Service Bulletins, which contain the specified 
effective pages:

----------------------------------------------------------------------------------------------------------------
                                                                           Revision level                       
     Service bulletin number and date                 Page No.              shown on page    Date shown on page 
----------------------------------------------------------------------------------------------------------------
ATR42-27-0071, Feb. 23, 1994..............  1-8.........................  Original........  Feb. 23, 1994.      
ATR42-27-0048 -...........................  1, 2, 4-6-..................  2...............  May 16, 1991.       
Revision 2................................  3, 8, 9.....................  Original........  June 22, 1990.      
May 16, 1991..............................  7...........................  1-..............  Nov. 21, 1990.      
ATR42-27-0049 -...........................  1, 2, 4-....................  2...............  May 16, 1991.       
Revision 2................................  3, 5, 6, 8, 11..............  Original........  Sept. 14, 1990.     
May 16, 1991..............................  7, 9, 10....................  1-..............  Nov. 21, 1990.      
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This incorporation by reference 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 Aerospatiale, 316 Route de Bayonne, 
31060 Toulouse, Cedex 03, 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. - [[Page 10807]] 
    (e) This amendment becomes effective on March 30, 1995.

    Issued in Renton, Washington, on February 6, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-3355 Filed 2-27-95; 8:45 am]
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