AD 2002-21-12

[Federal Register Volume 67, Number 204 (Tuesday, October 22, 2002)]
[Rules and Regulations]
[Pages 64791-64792]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-26665]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-06-AD; Amendment 39-12918; AD 2002-21-12]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Agusta S.p.A. (Agusta) helicopters that requires 
establishing or reducing the life limits of various parts listed in the 
airworthiness limitations section (ALS) of the maintenance manual. This 
amendment is prompted by the results of fatigue tests and analysis to 
determine life limits for various parts. The actions specified by this 
AD are intended to establish or reduce the life limits to prevent 
failure of specified parts and subsequent loss of control of the 
helicopter.

DATES: Effective November 26, 2002.

FOR FURTHER INFORMATION CONTACT: Carroll Wright, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5120, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the Agusta Model A109E helicopters was published in 
the Federal Register on July 15, 2002 (67 FR 46425). That action 
proposed to require establishing or reducing the life limits of 
specified parts of the main transmission assembly and supports, the 
tail rotor assemblies, the main rotor control bolt, and the fuselage 
left-hand elevator, and revising the ALS of the maintenance manual 
accordingly.
    This helicopter model is manufactured in Italy and is type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. The FAA has 
reviewed all available information and determined that AD action is 
necessary for products of this type design that are certificated for 
operation in the United States.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 31 helicopters of U.S. 
registry. The total cost of the 11 parts listed in Table 1 of this AD 
is approximately $41,294. Based on these figures, the total cost impact 
of the AD on U.S. operators is estimated to be $1,280,114, assuming 
that all 11 parts are replaced on each helicopter in the entire fleet. 
There will be no additional labor costs because the parts will be 
replaced during the normal maintenance process.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

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 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

    2002-21-12 Agusta S.p.A.: Amendment 39-12918. Docket No. 2002-
SW-06-AD.
    Applicability: Model A109E helicopters, certificated in any 
category.

    Note 1: This AD applies to each helicopter 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 helicopters 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 (c) 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 within 100 hours time-in-service (TIS), 
unless accomplished previously.
    To prevent failure of specified parts of the main transmission 
assembly and supports, the tail rotor assemblies, the main rotor 
control bolt, or the fuselage left-hand elevator, and subsequent 
loss of control of the helicopter, accomplish the following:
    (a) Replace each part listed in Table 1 with an airworthy part 
on or before reaching the specified hours TIS as shown in Table 1 of 
this AD as follows:

                                 Table 1
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             Part Name                     Part Number        Hours TIS
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(1) Main transmission gear pinion..  109-0403-05-111.......        6,100
(2) Main transmission gear driver..  109-0403-04-3.........        8,300
(3) Main transmission shaft          109-0405-76-107.......       25,000
 assembly.
(4) Tail rotor retention strap       109-8131-07-1.........        1,800
 assembly.
(5) Tail rotor hub assembly........  109-0131-06-7.........        3,000
(6) Tail rotor 90-degree gearbox     109-0433-01-107.......        6,100
 pinion gear.

[[Page 64792]]

 
(7) Tail rotor 90-degree gearbox     109-0443-01-103.......       11,700
 crown gear.
(8) Main rotor control bolt........  109-0110-90-103.......        5,000
(9) Fuselage left-hand elevator....  109-0200-02-93........        4,400
(10) Main transmission support aft   109-0325-03-113.......       35,000
 rod.
(11) Main transmission support       109-0325-08-1.........       30,000
 lower fitting.
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    (b) This AD revises the airworthiness limitations section of the 
maintenance manual by establishing or reducing the life limit as 
specified in Table 1 of this AD.
    (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, Regulations Group, Rotorcraft Directorate, 
FAA. Operators shall submit their requests through an FAA Principal 
Maintenance Inspector, who may concur or comment and then send it to 
the Manager, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (d) Special flight permits will not be issued.
    (e) This amendment becomes effective on November 26, 2002.

    Issued in Fort Worth, Texas, on October 10, 2002.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-26665 Filed 10-21-02; 8:45 am]
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