[Federal Register Volume 64, Number 10 (Friday, January 15, 1999)]
[Rules and Regulations]
[Pages 2559-2560]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-908]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-55-AD; Amendment 39-11000; AD 99-02-09]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Model A109C and A109K2 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This 
amendment requires removing the main rotor pitch link assemblies, 
measuring the radial play of the upper and lower spherical bearings 
(bearings), and replacing any unairworthy bearings. This amendment is 
prompted by four reports of increased vibration of the helicopters 
caused by wear in the bearings of the main rotor pitch change link 
assembly. The actions specified by this AD are intended to detect

[[Page 2560]]

unairworthy bearings on the pitch change link assembly and to prevent 
increased vibration and subsequent reduced controllability of the 
helicopter.

EFFECTIVE DATE: February 19, 1999.

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) to include an AD that is 
applicable to Agusta S.p.A. Model A109C and A109K2 helicopters was 
published in the Federal Register June 5, 1998 (63 FR 30660). That 
action proposed removing the main rotor pitch link assemblies, 
measuring the radial play of the bearings, and replacing any 
unairworthy bearings.
    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 3 work hours per 
helicopter to accomplish the actions, and that the average labor rate 
is $60 per work hour. Required parts will cost approximately $1122 for 
the upper bearing and $995 for the lower bearing per helicopter. Based 
on these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $6891.
    The regulations 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 amendment will not have 
sufficient federalism implications to warrant the preparation of a 
Federalism Assessment.
    For the reasons discussed above, I certify that this 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) 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 may be obtained by 
requesting a copy from the Office of the Regional Counsel, Southwest 
Region Attention: Rules Docket No. 97-SW-55-AD, 2601 Meacham Blvd., 
Room 663, Fort Worth, Texas 76137

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 
(AD) to read as follows:

AD 99-02-09  Agusta S.p.A.: Amendment 39-11000. Docket No. 97-SW-55-
AD.

    Applicability: Models A109C and A109K2 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 
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 use the authority 
provided in paragraph (d) 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 helicopter from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent main rotor pitch change link spherical bearing axial 
play due to wear, which could result in an increase in the vibration 
level and reduced controllability of the helicopter, accomplish the 
following:
    (a) Within the next 10 hours time-in-service (TIS) and 
thereafter at intervals not to exceed 100 hours TIS, remove the 
pitch change link assembly, part number (P/N) 109-0110-71.
    (b) Measure the radial play at both the upper and lower 
spherical bearings. If the radial play of a bearing exceeds 0.2 
millimeter, or .008 inch, replace the affected bearing with an 
airworthy bearing prior to further flight.

    Note 2: Agusta Bollettino Technico Telegrafico No. 109-9, dated 
March 23, 1995, pertains to the subject of this AD.

    (c) Reinstall the pitch change link assembly.
    (d) 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, FAA, Rotorcraft Directorate, 
Rotorcraft Standards Staff. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (e) 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.
    (f) This amendment becomes effective on February 19, 1999.

    Note 4: The subject of this AD is addressed in Registro 
Aeronautico Italiano (Italy) AD's 95-082 and 95-083, both dated 
March 28, 1995.

    Issued in Fort Worth, Texas, on January 8, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-908 Filed 1-14-99; 8:45 am]
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