[Federal Register Volume 65, Number 170 (Thursday, August 31, 2000)]
[Proposed Rules]
[Pages 52958-52960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-22283]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-27-AD]


Airworthiness Directives; Siam Hiller Holdings, Inc. Model UH-12, 
UH-12A, UH-12B, UH-12C, UH-12D, UH-12E, UH-12E-L, UH-12L, and UH-12L4 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) for Siam Hiller Holdings, Inc. (Hiller), formerly 
Rogerson Hiller Corporation, Model UH-12, UH-12A, UH-12B, UH-12C, UH-
12D, UH-12E, UH-12E-l, UH-12L, and UH-12L4 helicopters. The AD would 
require replacing all undrilled-shank bolts at pivoting joints in the 
control system linkage with drilled-shank bolts and

[[Page 52959]]

installing castellated nuts and cotter pins. This proposal is prompted 
by an accident caused by separation of the control system linkage of a 
Model UH-12E helicopter. The actions specified by the proposed AD are 
intended to prevent separation of the control system attachments at 
pivoting points and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before October 30, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-27-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: Jon Mowery, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712-4137, telephone (562) 627-
5322, fax (562) 627-5210.

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 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 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 notice must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2000-SW-27-AD.'' The 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. 2000-SW-27-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    This document proposes the adoption of a new airworthiness 
directive (AD) for Hiller Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, 
UH-12E, UH-12E-l, UH-12L, and UH-12L4 helicopters. The AD would require 
replacing all undrilled-shank bolts at pivoting joints in control 
system linkage with drilled-shank bolts and installing castellated nuts 
and cotter pins. This proposal is prompted by an accident due to 
separation of the control system attachments at pivoting points on a 
Model UH-12E helicopter. The attachments are bolts with self-locking 
nuts that can lose the self-locking feature with repeated disassembly. 
This condition, if not corrected, could result in separation of the 
control system attachments at pivoting points and subsequent loss of 
control of the helicopter.
    The FAA has reviewed Hiller Aircraft Service Bulletin No. 10-4, 
Revision 2, dated December 20, 1999 (SB), which describes procedures 
for replacing plain bolts and self-locking nuts, used at pivoting 
joints, with drilled-shank bolts, castellated nuts, and cotter pins.
    We have identified an unsafe condition that is likely to exist or 
develop on other Hiller Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, 
UH-12E, UH-12E-L, UH-12L, and UH-12L4 helicopters of the same type 
design. The proposed AD would require at the next annual inspection or 
within 12 months, whichever occurs first, replacing all undrilled-shank 
bolts with drilled-shank bolts at pivoting joints in the control system 
linkage and installing castellated nuts and cotter pins. The actions 
would be required to be accomplished in accordance with the SB 
described previously.
    The FAA estimates that 500 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 24 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 $150 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$795,000.
    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:

Siam Hiller Holdings, Inc.: Docket No. 2000-SW-27-AD.
    Applicability: Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-
12E, UH-12E-L, UH-12L, UH-12L4 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

[[Page 52960]]

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 at the next annual inspection or within 12 
months, whichever occurs first, unless accomplished previously.
    To prevent separation of the control system attachments at 
pivoting points and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Replace all undrilled-shank bolts at pivoting joints in the 
control system linkage with drilled-shank bolts, and install 
castellated nuts and cotter pins in accordance with Hiller Aircraft 
Corporation Service Bulletin No. 10-4, Revision 2, dated December 
20, 1999.
    (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, Los Angeles 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, Los Angeles Aircraft Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles 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.

    Issued in Fort Worth, Texas, on August 24, 2000.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-22283 Filed 8-30-00; 8:45 am]
BILLING CODE 4910-13-U