[Federal Register Volume 68, Number 33 (Wednesday, February 19, 2003)]
[Rules and Regulations]
[Pages 7911-7913]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-3772]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-44-AD; Amendment 39-13052; AD 2003-04-04]
RIN 2120-AA64


Airworthiness Directives; Robinson Helicopter Company Model R22 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Robinson Helicopter Company (RHC) Model R22 helicopters that requires 
inspecting the tail rotor 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 AD requires replacing the unairworthy pitch control 
assembly with an airworthy unit. This amendment is prompted by reports 
of failure of the tail rotor pitch control assembly due to improperly 
lubricated bearings on the RHC Model R22 helicopters. The actions 
specified by this AD are intended to detect corrosion of the bearings 
and to prevent bearing failure and subsequent loss of directional 
control of the helicopter.

DATES: Effective March 26, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 26, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Robinson Helicopter Company, 2901 Airport Drive, 
Torrance, California 90505, telephone (310) 539-0508, fax (310) 539-
5198. 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: Fred Guerin, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification

[[Page 7912]]

Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 
90712, telephone (562) 627-5232, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to 
include an AD for the specified helicopters was published in the 
Federal Register on September 10, 2002 (67 FR 57349). That action 
proposed inspecting the pitch control assembly to determine roughness 
or binding of the bearings by hand-rotating the housing. If the housing 
does not rotate freely, it proposed replacing each unairworthy pitch 
control assembly with an airworthy unit.
    The FAA has reviewed RHC Service Bulletin SB-90A, Revision A, dated 
June 10, 2002 (SB), which describes procedures for inspecting the pitch 
control assembly to determine roughness or binding of the bearings by 
hand-rotating the housing. If the housing does not rotate freely, the 
SB specifies replacing each unairworthy pitch control assembly, part 
number (P/N) A031-1, with an airworthy unit in accordance with the 
maintenance manual.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter, the manufacturer, requests a change to the summary 
information to indicate that bearing failures have been reported only 
on RHC Model R22 helicopters, and they have received no reports of 
failed bearings on Model R44 helicopters. The FAA agrees and has 
changed the summary to indicate that the bearing failures have occurred 
on the RHC Model R22 helicopters only.
    The same commenter requests a change to the summary and the 
discussion sections to revise the failure sequence to indicate that 
bearing failure could result in loss of tail rotor thrust requiring a 
power-off landing. The commenter states that in all three of the 
bearing failures, the failed bearing caused the pitch control linkage 
to fail and the tail rotor to go to flat pitch, but none of the 
failures resulted in an accident. The commenter also states that there 
was no breakup of the tail rotor assembly, no tail rotor contact of the 
tailboom, and no loss of control resulting in an accident. The FAA 
agrees that the failed bearing has not resulted in breakup of the tail 
rotor assembly and contact with the tailboom, and the likelihood of 
such a breakup and contact with the tailboom may be remote. Therefore, 
we have removed the reference to the breakup of the tail rotor assembly 
and contact with the tailboom from the failure sequence. We do not 
agree that the failure sequence should state that bearing failure could 
result in loss of tail rotor thrust requiring a power-off landing. The 
loss of directional control associated with this type of failure could 
result in loss of control of the helicopter, and a successful power-off 
landing may not be possible. The term ``loss of control of the 
helicopter'', however, may be understood to mean an almost certain 
catastrophic event, such as loss of cyclic or pitch control. That is 
not our intent when we use the failure sequence in our AD's. That 
sequence states what could happen not necessarily what will happen. Our 
intent is to convey the sequence of events that we intend to prevent by 
issuing the AD to correct the unsafe condition. Therefore, we have 
changed the failure sequence to state that loss of ``directional'' 
control can result.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed with the changes 
described previously. The FAA has determined that these changes will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.
    The FAA estimates that this AD will affect 1300 helicopters of U.S. 
registry, that it will take approximately 2.3 work hours per helicopter 
to inspect and replace each pitch control assembly, and that the 
average labor rate is $60 per work hour. Required parts will cost 
approximately $800 per helicopter. Based on these figures, the total 
cost impact of the AD on U.S. operators is estimated to be $1,219,400, 
assuming the pitch control assembly is replaced on the entire fleet.
    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 adding a new airworthiness directive 
to read as follows:

2003-04-04 Robinson Helicopter Company: Amendment 39-13052. Docket 
No. 2001-SW-44-AD.

    Applicability: Model R22 helicopters, up to and including serial 
number 3328, except serial numbers 3167, 3326, and 3327, with pitch 
control assembly, part number (P/N) A031-1, Revision J 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 a tail rotor pitch control bearing 
(bearing) and to prevent bearing failure and loss of directional 
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

[[Page 7913]]

Bulletin SB-90A, 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.
    (d) The inspection of the pitch control assembly shall be done 
in accordance with Robinson Helicopter Company Service Bulletin SB-
90A, Revision A, dated June 10, 2002. 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 Robinson Helicopter Company, 2901 Airport Drive, 
Torrance, California 90505, telephone (310) 539-0508, fax (310) 539-
5198. 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 March 26, 2003.

    Issued in Fort Worth, Texas, on February 6, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-3772 Filed 2-18-03; 8:45 am]
BILLING CODE 4910-13-P