[Federal Register Volume 65, Number 99 (Monday, May 22, 2000)]
[Rules and Regulations]
[Pages 32021-32023]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12818]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-43-AD; Amendment 39-11738; AD 2000-10-14]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) 
Model 222, 222B, 222U, and 230 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
BHTC Model 222, 222B, 222U, and 230 helicopters that requires 
inspecting each flapping bearing to yoke attachment bolt (bolt) and 
replacing each bolt that shows thread damage, shank wear, or corrosion 
pitting with an airworthy bolt. This amendment is prompted by the 
discovery of a fractured bolt during a post-flight inspection. The 
actions specified by this AD are intended to prevent a fracture of a 
bolt, failure of the bearing and yoke interface, and subsequent loss of 
control of the helicopter.

EFFECTIVE DATE: June 26, 2000.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0111, telephone (817) 222-5122, 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 for BHTC Model 
222, 222B, 222U, and 230 helicopters was published in the Federal 
Register on March 1, 2000 (65 FR 11006). That action proposed to 
require inspecting the bolts and replacing each bolt that shows thread 
damage, shank wear, or corrosion with an airworthy bolt.
    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 101 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 3 work hours per 
helicopter to accomplish the required actions, and that the average 
labor rate is $60 per work hour. Required parts will cost approximately 
$20 per bolt. Based on these figures, the total cost impact of the AD 
on U.S. operators is estimated to be $20,200.
    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 FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.

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 
to read as follows:

AD 2000-10-14  Bell Helicopter Textron Canada: Amendment 39-11738. 
Docket No. 99-SW-43-AD.

    Applicability: Model 222 helicopters, serial number (S/N) 47006 
through 47089; Model 222B helicopters, S/N 47131 through 47156; 
Model 222U helicopters, S/N 47501 through 47574; and Model 230 
helicopters, S/N 23001 through 23038 inclusive, 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 within 150 hours time-in-service, unless 
accomplished previously.
    To prevent the fracture of a flapping bearing to yoke attachment 
bolt (bolt), failure of the bearing and yoke interface, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Remove one bolt at a time and inspect each bolt located as 
shown in Figure 1.

    Note 2: For main rotor hubs installed on rotorcraft, the bolts 
may be removed, inspected, and installed one at a time.


    Note 3: Bell Helicopter Textron Canada Alert Service Bulletins 
230-98-15, 222-98-83, and 222U-98-54, all dated October 12, 1998, 
pertain to the subject of this AD.

    (i) Clean each bolt with a cloth dampened with methyl ethyl 
ketone, RHO SOLV756, Desoto 110, or equivalent.

[[Page 32022]]

    (ii) Visually inspect each bolt and discard those that have 
thread damage, shank wear, or corrosion.
    (iii) Apply corrosion preventative compound MIL-C-16173 GR2, or 
equivalent, to the shank of the bolt only.
    (iv) Install, torque, and lockwire each bolt.
    (v) Coat each bolt head and nut with corrosion preventative 
compound MIL-C-16173 GR1 or equivalent.
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    (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, Regulations Group, Rotorcraft 
Directorate, FAA. Operators shall submit their requests through an 
FAA Principal Maintenance Inspector, who may concur or comment and 
then send it to the Manager, Regulations Group.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (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) This amendment becomes effective on June 26, 2000.

    Note 5: The subject of this AD is addressed in Transport Canada 
(Canada) AD's CF-99-12 and CF-99-13, both dated April 21, 1999.


    Issued in Fort Worth, Texas, on May 15, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-12818 Filed 5-19-00; 8:45 am]
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