[Federal Register Volume 59, Number 144 (Thursday, July 28, 1994)]
[Unknown Section]
[Page ]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-17869]


[Federal Register: July 28, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-SW-09-AD; Amendment 39-8944; AD 94-13-04]


Airworthiness Directives: Schweizer Aircraft Corporation and 
Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A 
Series Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to Schweizer Aircraft Corporation and Hughes Helicopters, 
Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series helicopters, 
that requires mandatory replacement of all the clevis pins associated 
with the belt drive clutch control installation. This amendment is 
prompted by an accident involving the separation of the belt drive 
clutch control spring assembly (spring assembly) from the idler pulley 
assembly. The actions specified by this AD are intended to prevent 
separation of the spring assembly from the idler pulley assembly, loss 
of power to the main rotor system, and a subsequent forced landing.

DATES: Effective September 1, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 1, 1994.

ADDRESSES: The service information referenced in this AD may be 
obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New 
York 14902. This information may be examined at the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, 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: Mr. Raymond Reinhardt, Aerospace 
Engineer, New York Aircraft Certification Office, FAA, Propulsion 
Branch, ANE-174, New England Region, 181 South Franklin Avenue, Valley 
Stream, New York 11581, telephone (516) 791-7421, fax (516) 791-9024.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Schweizer Aircraft Corporation and 
Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A 
series helicopters was published in the Federal Register on August 4, 
1993 (58 FR 41444). That action proposed to require replacement of all 
clevis pins associated with the belt drive clutch control installation.
    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 with one change. The AD proposed 
compliance on or before January 13, 1994, or within the next 400 hours' 
time-in-service (TIS), whichever comes first. Since January 13, 1994, 
has passed, the AD has been changed to now require compliance within 30 
days after the effective date of the AD or within 400 hours' TIS, 
whichever comes first.
    The FAA estimates that 1,100 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately \1/2\ work hour 
per helicopter to accomplish the required actions, and that the average 
labor rate is $55 per work hour. Required parts will cost approximately 
$10 per helicopter. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $41,250.
    The regulations adopted 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

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

AD 94-13-04 Schweizer Aircraft Corporation and Hughes Helicopters, 
Inc.: Amendment 39-8944. Docket Number 93-SW-09-AD.

    Applicability: Model 269A, 269A-1, 269B, and TH-55A series 
helicopters, and Model 269C series helicopters with serial numbers 
(S/N) prior to S/N 1632, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of the belt drive clutch control spring 
assembly (spring assembly) from the idler pulley assembly, loss of 
power to the main rotor system, and a subsequent forced landing, 
accomplish the following:
    (a) Within the next 400 hours' time-in-service, or on or before 
30 days after the effective date of this AD, whichever comes first, 
replace the clevis pins in the spring assembly with bolts in 
accordance with Part II of Schweizer Aircraft Corporation Service 
Bulletin B-256.2, dated June 11, 1993.
    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used when approved by the Manager, New York Aircraft Certification 
Office, FAA. Operators shall submit their requests through an FAA 
Principal Maintenance Inspector, who may concur or comment and then 
send it to the Manager, New York Aircraft Certification Office.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York Aircraft Certification Office.

    (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 replacement shall be done in accordance with Schweizer 
Aircraft Corporation Service Bulletin B-256.2, dated June 11, 1993. 
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 Schweizer Aircraft Corporation, P.O. 
Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, 
Office of the Assistant Chief Counsel, 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 September 1, 1994.

    Issued in Fort Worth, Texas, on June 14, 1994.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-17869 Filed 7-27-94; 8:45 am]
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