[Federal Register Volume 65, Number 8 (Wednesday, January 12, 2000)]
[Proposed Rules]
[Pages 1838-1839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-598]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-28-AD]


Airworthiness Directives; Agusta Model A109C and A109K2 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD) applicable to Agusta Model A109C and 
A109K2 helicopters. That AD currently requires removing the main rotor 
pitch control link assemblies, measuring the radial play of each upper 
and lower spherical rod-end bearing (bearing), and replacing any 
unairworthy bearing. This action would require replacing the pitch 
control link assembly with an assembly that has increased durability 
and wear resistance. This proposal is prompted by reports of increased 
helicopter vibration caused by wear of bearings on certain pitch 
control link assemblies. The actions specified by the proposed AD are 
intended to eliminate the need for recurring bearing inspections and to 
prevent failure of a bearing, increased helicopter vibration, and 
subsequent reduced controllability of the helicopter.

DATES: Comments must be received on or before March 13, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-28-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Agusta, 21017 Cascina Costa di Samarate (VA), Via 
Giovanni Agusta 520, telephone (0331) 229111, fax (0331) 229605-222595. 
This information may be examined at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas.

FOR FURTHER INFORMATION CONTACT: Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice 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 comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-SW-28-AD.'' The

[[Page 1839]]

postcard will be date stamped and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-28-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

Discussion

    On January 8, 1999, the FAA issued AD 99-02-09, Amendment 39-11000 
(64 FR 2559, January 15, 1999), to require removing the main rotor 
pitch control link assemblies, measuring the radial play of the 
bearings, and replacing any unairworthy bearings. That action was 
prompted by four reports of increased helicopter vibration due to wear 
in the bearings of the pitch control link assembly. The requirements of 
that AD are intended to prevent increased helicopter vibration due to 
unairworthy bearings resulting in subsequent reduced controllability of 
the helicopter.
    Since the issuance of that AD, the FAA has received additional 
reports of unairworthy bearings and notification of the introduction of 
an upgraded pitch control link assembly. The Registro Aeronautico 
Italiano (RAI) issued AD's 95-332, dated December 15, 1995, and 95-334, 
dated December 18, 1995. Agusta S.p.A. issued Bollettino Tecnico Nos. 
109K-10 and 109-103, both dated November 22, 1995 (BT). The BT's 
specify replacing each pitch control link rod end assembly, part number 
(P/N) 109-0110-71-103 and -105, on Agusta Model A109K2 helicopters 
through serial number (S/N) 10023 (S/N 10014 excluded), and on Model 
A109C through S/N 7677, (S/N's 7633, 7654, and 7667 excluded) by 
reworking and reidentifying as pitch control link assembly, P/N 109-
0110-71-107.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Agusta Model A109C and A109K2 helicopters of 
the same type designs, the proposed AD would supersede AD 99-SW-28-AD 
to require replacing the main rotor pitch link assemblies with 
assemblies that have increased durability and wear resistance.
    The FAA estimates that 3 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 7 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $2,200 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$7,860.
    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 removing Amendment 39-11000 (64 FR 
2559, January 15, 1999, and by adding a new airworthiness directive 
(AD), to read as follows:

Agusta S.p.A.: Docket 99-SW-28-AD. Supersedes AD 99-02-09, Amendment 
39-11000, Docket 97-SW-55-AD.
    Applicability: Model A109C and A109K2 helicopters, with main 
rotor pitch control link assemblies, part number (P/N) 109-0110-71-
103 or -105, installed, 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 (b) 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 before further flight, unless accomplished 
previously.
    To prevent failure of a main rotor pitch control link rod-end 
spherical bearing, increased vibration level, and subsequent reduced 
controllability of the helicopter, accomplish the following:
    (a) Rework each main rotor pitch control link assembly, P/N 109-
0110-71-103 or -105, and reidentify as pitch control link assembly, 
P/N 109-0110-71-107, in accordance with the Compliance Instructions 
of Agusta Bollettino Tecnico 109K-10 or 109-103, both dated November 
22, 1995, as applicable.
    (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, 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.

    (c) 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 helicopter to a location where 
the requirements of this AD can be accomplished.

    Note 3: The subject of this AD is addressed in Registro 
Aeronautico Italiano (Italy) AD's 95-332, dated December 15, 1995, 
and 95-334, dated December 18, 1995.

    Issued in Fort Worth, Texas, on January 5, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 00-598 Filed 1-11-00; 8:45 am]
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