AD 2000-08-05

[Federal Register Volume 65, Number 79 (Monday, April 24, 2000)]
[Rules and Regulations]
[Pages 21634-21635]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-9817]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-28-AD; Amendment 39-11691; AD 2000-08-05]
RIN 2120-AA64


Airworthiness Directives; Agusta Model A109C and A109K2 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to Agusta Model A109C and A109K2 helicopters, that 
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 
amendment requires replacing the pitch control link assembly with an 
assembly that has increased durability and wear resistance. This 
amendment is prompted by reports of increased helicopter vibration 
caused by wear of

[[Page 21635]]

bearings on certain pitch control link assemblies. The actions 
specified by this 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: Effective May 30, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 30, 2000.

ADDRESSES: The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-02-09, 
Amendment 39-11000 (64 FR 2559), which is applicable to Agusta Model 
A109C and A109K2 helicopters, was published in the Federal Register on 
January 12, 2000 (65 FR 1838). That action proposed to require 
replacing main rotor pitch link assemblies with assemblies that have 
increased durability and wear resistance.
    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 3 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 7 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$2,200 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $7,860.
    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 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-11000 (64 FR 
2559), and by adding a new airworthiness directive (AD), Amendment 39-
11691, to read as follows:

AD 2000-08-05  Agusta S.p.A.: Amendment 39-11691. Docket No. 99-SW-
28-AD. Supersedes AD 99-02-09, Amendment 39-11000, Docket No. 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.
    (d) The modification shall be done in accordance with the 
Compliance Instructions of Agusta Bollettino Tecnico 109K-10 or 109-
103, both dated November 22, 1995. 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 
Agusta, 21017 Cascina Costa di Samarate (VA), Via Giovanni Agusta 
520, telephone (0331) 229111, fax (0331) 229605-222595. Copies may 
be inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (e) This amendment becomes effective on May 30, 2000.

    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 April 11, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-9817 Filed 4-21-00; 8:45 am]
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