[Federal Register Volume 67, Number 175 (Tuesday, September 10, 2002)]
[Proposed Rules]
[Pages 57351-57352]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-22898]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-45-AD]
RIN 2120-AA64


Airworthiness Directives; Robinson Helicopter Company Model R44 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Robinson Helicopter Company (RHC) Model R44 helicopters. The 
AD would require inspecting the pitch control assembly for roughness or 
binding of the pitch control bearings (bearings) by hand-rotating the 
pitch control bearing housing (housing). If the housing does not rotate 
freely, the proposed AD would require replacing the unairworthy pitch 
control assembly with an airworthy unit. This proposal is prompted by 
reports of failure of the tail rotor assembly due to improperly 
lubricated bearings on the RHC Model R22 and R44 helicopters. The 
actions specified by the proposed AD are intended to detect corrosion 
of the bearings and prevent bearing failure, breakup of the tail rotor 
assembly, tail rotor contact with the tailboom, and subsequent loss of 
control of the helicopter.

DATES: Comments must be received on or before November 12, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-45-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: Fred Guerin, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5232, 
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 document 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 mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-45-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    This document proposes adopting an AD for RHC Model R44 
helicopters. The AD would require inspecting the pitch control assembly 
for roughness or binding of the bearings by hand-rotating the housing. 
If the housing does not rotate freely, this AD would require replacing 
each unairworthy pitch control assembly with an airworthy unit. This 
proposal is prompted by reports of failure of the tail rotor assembly 
due to improperly lubricated bearings. This condition, if not 
corrected, could result in bearing failure, breakup of the tail rotor 
assembly, tail rotor contact with the tailboom, and subsequent loss of 
control of the helicopter.
    The FAA has reviewed RHC Service Bulletin SB-43A, Revision A, dated 
June 10, 2002, which describes procedures for inspecting the pitch 
control assembly for roughness or binding of the bearings by hand-
rotating the housing. If the housing does not rotate freely, this 
service bulletin specifies replacing each unairworthy pitch control 
assembly, part number (P/N) C031-1, with an airworthy unit in 
accordance with the maintenance manual.
    This unsafe condition is likely to exist or develop on other RHC 
Model R44 helicopters of the same type design. Therefore, the proposed 
AD would require, within a certain time and at specified intervals, 
inspecting the pitch control assembly for roughness or binding of the 
bearings by hand rotating the housing. If the housing does not rotate 
freely, this AD would require, before further flight, replacing any 
unairworthy pitch control assembly with an airworthy unit. The actions 
would be required to be accomplished in accordance with the service 
bulletin described previously.
    The FAA estimates that this proposed AD would affect 440 
helicopters of U.S. registry. The FAA estimates that it would take 
approximately 2.3 work hours per helicopter to inspect and replace a 
pitch control assembly at an average labor rate of $60 per work hour. 
Required parts would cost

[[Page 57352]]

approximately $1145 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$564,520, assuming the pitch control assembly is replaced in the entire 
fleet.
    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:

Robinson Helicopter Company: Docket No. 2001-SW-45-AD.

    Applicability: Model R44 helicopters, up to and including serial 
number 1208, except serial numbers 1143, 1165, 1183, 1189, 1192, 
1196, 1197, 1198, 1200, 1203, and 1204, with pitch control assembly, 
part number (P/N) C031-1, Revision G or prior, 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 as indicated, unless accomplished 
previously.
    To detect corrosion of the bearings and prevent bearing failure, 
breakup of the tail rotor assembly, tail rotor contact with the 
tailboom, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within 20 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 300 hours TIS or 12 months, whichever occurs 
first, inspect the pitch control assembly for roughness or binding 
of the pitch control bearings by hand rotating the pitch control 
bearing housing (housing) in accordance with Robinson Helicopter 
Company Service Bulletin SB-43A, Revision A, dated June 10, 2002. If 
the housing does not rotate freely, before further flight, replace 
the unairworthy pitch control assembly with an airworthy unit.
    (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 (LAACO), FAA. Operators shall submit their requests through 
an FAA Principal Maintenance Inspector, who may concur or comment 
and then send it to the Manager, LAACO.

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

    (c) Special flight permits may be issued in accordance with 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 28, 2002.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-22898 Filed 9-9-02; 8:45 am]
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