[Federal Register Volume 67, Number 135 (Monday, July 15, 2002)]
[Proposed Rules]
[Pages 46425-46427]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-17424]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-06-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This proposal 
would require establishing or reducing the life limits of various parts 
listed in the airworthiness limitations section (ALS) of the 
maintenance manual. This proposal is prompted by the results of fatigue 
tests and analysis to determine life limits for various parts. The 
actions specified by this proposed 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: Comments must be received on or before September 13, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2002-SW-06-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

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.

[[Page 46426]]


SUPPLEMENTARY INFORMATION:   

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2002-SW-06-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    On September 7, 2001, Agusta sent the FAA a comparison between the 
May 1996 and July 2001 issues of the ALS of its maintenance manual and 
provided justification for the changes in fatigue lives of certain 
parts. The justification for changing the life limits was based on 
applying new fatigue life computations, a rescue hoist flight spectrum, 
a Category A training flight spectrum, a new operational limit, and an 
update of loads in-flight survey data.
    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.
    An unsafe condition is likely to exist or develop on other 
helicopters of the same type design registered in the United States if 
the proposed life limits are not followed. Therefore, the proposed AD 
would 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.
    The FAA estimates that 31 helicopters of U.S. registry would be 
affected by this proposed AD. One copy of each of the 11 parts listed 
in Table 1 of this proposal would cost approximately $41,294. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $1,280,114, assuming that one copy of each 
part would be replaced on the entire fleet. There would be no 
additional labor costs as the parts would be replaced during the normal 
maintenance process.
    The regulations proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Agusta S.p.A.: 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
------------------------------------------------------------------------
               Part name                      Part No.         Hours TIS
------------------------------------------------------------------------
(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 assembly..       109-0405-76-107      25,000
------------------------------------------------------------------------

[[Page 46427]]

 
(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..........................
------------------------------------------------------------------------
(7) Tail rotor 90-degree gearbox crown       109-0443-01-103      11,700
 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 rod       109-0325-03-113      35,000
------------------------------------------------------------------------
(11) Main transmission support lower           109-0325-08-1      30,000
 fitting..............................
------------------------------------------------------------------------

    (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.

    Issued in Fort Worth, Texas, on July 5, 2002.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-17424 Filed 7-12-02; 8:45 am]
BILLING CODE 4910-13-P