[Federal Register Volume 66, Number 199 (Monday, October 15, 2001)]
[Rules and Regulations]
[Pages 52313-52315]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-25692]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-49-AD; Amendment 39-12470; AD 2001-19-52]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2001-19-52 which was sent 
previously to all known U.S. owners and operators of Bell Helicopter 
Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters by 
individual letters. This AD requires removing certain serial-numbered 
main rotor pendulum weight supports from service and replacing with 
airworthy main rotor pendulum weight supports. This AD is prompted by 
the failure of a main rotor pendulum weight support (support) resulting 
in shedding of the weights and an increased level of main rotor 
vibration. The actions specified by this AD are intended to prevent 
failure of a support, loss of a weight set resulting in main rotor 
vibration, and subsequent loss of control of the helicopter.

DATES: Effective October 30, 2001, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2001-19-52, 
issued on September 21, 2001, which contained the requirements of this 
amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before December 14, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-49-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].

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas 
76193-0110, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On September 21, 2001, the FAA issued 
Emergency AD 2001-19-52, for BHTC

[[Page 52314]]

Model 222, 222B, 222U, and 230 helicopters, which requires removing 
certain serial-numbered supports from service and replacing them with 
airworthy supports. That action was prompted by the failure of a 
support resulting in shedding of the weights and an increased level of 
main rotor vibration. Subsequent investigation revealed that the failed 
support had manufacturing defects. This condition, if not corrected, 
could result in failure of a support, loss of a weight set resulting in 
main rotor vibration, and subsequent loss of control of the helicopter.
    Transport Canada, which is the airworthiness authority for Canada, 
notified the FAA that an unsafe condition may exist on BHTC Model 222, 
222B, 222U, and 230 helicopters. Transport Canada advises that due to 
manufacturing discrepancies, certain supports, if not replaced, could 
fail in flight.
    BHTC has issued Alert Service Bulletins 222-01-91, 222U-01-62, and 
230-01-24, all dated May 18, 2001, which describe procedures for 
replacing all supports identified with a serial number (S/N) having the 
prefix ``HD.'' Transport Canada classified these service bulletins as 
mandatory and issued AD CF-2001-28, dated July 24, 2001, to ensure the 
continued airworthiness of these helicopters in Canada.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada, reviewed all available information, and 
determined that AD action is necessary for products of these type 
designs that are certificated for operation in the United States.
    Since the unsafe condition described is likely to exist or develop 
on other BHTC Model 222, 222B, 222U, and 230 helicopters of the same 
type designs, the FAA issued Emergency AD 2001-19-52 to prevent failure 
of a support, loss of a weight set resulting in main rotor vibration, 
and subsequent loss of control of the helicopter. The AD requires, 
within 25 hours time-in-service (TIS) or 3 months, whichever occurs 
first, removing from service all supports, part number 222-011-114-103, 
with a S/N having the prefix ``HD'' and replacing them with airworthy 
supports. The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
structural integrity of the helicopter. Therefore, the actions 
described previously are required at the specified time intervals, and 
this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on September 21, 2001, to all known U.S. owners and operators of 
BHTC Model 222, 222B, 222U, and 230 helicopters. These conditions still 
exist, and the AD is hereby published in the Federal Register as an 
amendment to 14 CFR 39.13 to make it effective to all persons. However, 
the Emergency AD contained an error when listing the Transport Canada 
AD number. The number was incorrectly listed as AD CF-2001-2B; the 
correct number is AD CF-2001-28. There was also a comma instead of a 
period at the end of Note 4 of the Emergency AD. The FAA discovered 
these errors and posted a corrected Emergency AD on the Internet at 
http://av-info.faa.gov/ad/ad.htm. The FAA has determined that these 
changes neither increase the economic burden on an operator nor 
increase the scope of the AD.
    The FAA estimates that 112 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 6 work hours per 
helicopter to accomplish the required actions, and the average labor 
rate is $60 per work hour. The manufacturer states in its service 
bulletins that owners/operators complying with the service bulletin on 
or before December 31, 2001 will receive a special 100% warranty credit 
for the necessary parts. Based on these figures, the total cost impact 
of the AD on U.S. operators is estimated to be $20,160 ($360 per 
helicopter, assuming half the fleet has supports replaced and assuming 
the actions are accomplished by the specified date and that the 
manufacturer's instructions for receiving the credit are followed).

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available in the Rules Docket for examination by interested persons. A 
report that summarizes each FAA-public contact concerned with the 
substance of this AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-49-AD.'' The postcard will be date 
stamped and returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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, Safety.

[[Page 52315]]

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:

2001-19-52  Bell Helicopter Textron Canada: Amendment 39-12470. 
Docket No. 2001-SW-49-AD.

    Applicability: Model 222, serial number (S/N) 47006 through 
47089; Model 222B, S/N 47131 through 47156; Model 222U, S/N 47501 
through 47574; and Model 230, S/N 23001 through 23038 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 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: Within 25 hours time-in-service or 3 months, 
whichever occurs first, unless accomplished previously.
    To prevent failure of a main rotor pendulum weight support 
(support), loss of a weight set resulting in main rotor vibration, 
and subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Remove from service all supports, part number 222-011-114-
103, identified with a serial number having the prefix ``HD'' and 
replace with airworthy supports that do not have the S/N prefix 
``HD.''

    Note 2: Bell Helicopter Textron Canada Alert Service Bulletins 
222-01-91, 222U-01-62, and 230-01-24, all dated May 18, 2001, 
pertain to the subject of this AD.

    (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, 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 3: 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 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (d) Emergency AD 2001-19-52, issued September 21, 2001, becomes 
effective upon receipt.

    Note 4: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2001-28, dated July 24, 2001.

    (e) This amendment becomes effective on October 30, 2001, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-19-52, issued September 21, 2001, 
which contained the requirements of this amendment.

    Issued in Fort Worth, Texas, on October 4, 2001.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-25692 Filed 10-12-01; 8:45 am]
BILLING CODE 4910-13-U