[Federal Register Volume 66, Number 32 (Thursday, February 15, 2001)]
[Rules and Regulations]
[Pages 10361-10363]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3561]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-54-AD; Amendment 39-12105; AD 2001-01-51]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, 222U, 230, and 430 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) 2001-01-51, which was sent 
previously to all known U.S. owners and operators of Bell Helicopter 
Textron Canada (BHTC) Model 222, 222B, 222U, 230, and 430 helicopters 
by individual letters. This AD requires visually inspecting the main 
rotor hydraulic actuator support (support) to verify the presence of 
all dowel pins and sealant between the support and transmission and 
verifying the proper torque of each attaching nut (nut). This amendment 
is prompted by the failure of a support resulting in an accident of a 
BHTC Model 222U helicopter. All retaining studs and shear pins were 
found sheared or pulled out at the junction between the support and the 
transmission case. The actions specified by this AD are intended to 
prevent failure of the support and subsequent loss of control of the 
helicopter.

DATES: Effective March 2, 2001, to all persons except those persons to 
whom it was made immediately effective by Emergency AD 2001-01-51, 
issued on January 5, 2001, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 2, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before April 16, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-54-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].
    The applicable service information may be obtained from Bell 
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
JON1LO, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272. 
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: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Regulations Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5490, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: On January 5, 2001, the FAA issued Emergency 
AD 2001-01-51 for BHTC Model 222, 222B, 222U, 230, and 430 helicopters 
which requires visually inspecting the support to verify the presence 
of all dowel pins and sealant between the support and the transmission 
and verifying the proper torque of each nut. That action was prompted 
by the failure of a support resulting in an accident of a BHTC Model 
222U helicopter. All retaining studs and shear pins were found sheared 
or pulled out at the junction between the support and the transmission 
case. This condition, if not detected, could result in failure of the 
support and subsequent loss of control of the helicopter.
    The FAA has reviewed BHTC Alert Service Bulletin Nos. 222-00-86, 
222U-00-57, 230-00-18, and 430-00-17, all dated May 19, 2000 (ASB's), 
which specify, within 25 hours time-in-service (TIS), conducting a one-
time inspection of the support installation by accomplishing a torque 
check of the nuts. In addition, a revision to the maintenance manual 
will introduce a recurring torque check of the nuts. Transport Canada, 
which is the airworthiness authority for Canada, classified these ASB's 
as mandatory and issued AD No. CF-2000-29 dated September 6, 2000, to 
ensure the continued airworthiness of these helicopters in Canada.
    Since the unsafe condition described is likely to exist or develop 
on other BHTC Model 222, 222B, 222U, 230, and 430 helicopters of the 
same type designs, the FAA issued Emergency AD 2001-01-51 to prevent 
failure of the support and subsequent loss of control of the 
helicopter. The AD requires, at specified time intervals, visually 
inspecting the support to verify the presence of all dowel pins and 
sealant between the support and transmission and verifying the proper 
torque of each nut. Repairing or replacing any unairworthy support, 
transmission case, stud, or dowel pin and retorquing to proper torque 
are required before further flight. The actions must be accomplished in 
accordance with the ASB's described previously. 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 previously listed are required 
within 25 hours TIS, 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 January 5, 2001, to all known U.S. owners and operators of 
BHTC Model 222, 222B, 222U, 230, and 430 helicopters. These conditions 
still exist, and the AD is hereby published in the Federal Register as 
an amendment to section 39.13 of the Federal Aviation Regulations (14 
CFR 39.13) to make it effective to all persons.
    The FAA estimates that 145 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately \1/2\ work hour 
per helicopter to inspect for proper torque, and that the average labor 
rate is $60 per work hour. The cost for the inspection is estimated to 
be $4,350. Assuming 15 helicopters require removing the support for 
additional inspections, it would take approximately 6 additional work 
hours at $60 per work hour and $50 for parts at an additional total 
cost of $410 per helicopter. Based on these figures, the total cost 
impact of this AD on U.S. operators is estimated to be $10,500, 
assuming no supports have to be replaced.

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.

[[Page 10362]]

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. 2000-SW-54-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, 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:

2001-01-51  Bell Helicopter Textron Canada: Amendment 39-12105. 
Docket No. 2000-SW-54-AD.

    Applicability: Model 222, 222B, 222U, 230, and 430 helicopters, 
with a main rotor hydraulic actuator support (support), part number 
(P/N) 222-040-125-001, 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 (c) 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 prevent failure of the support and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 25 hours TIS and thereafter at intervals not to 
exceed 600 hours TIS, accomplish the following:
    (1) Visually inspect the support for the presence of all dowel 
pins and for sealant between the support and the transmission. If 
any pin is missing, or if no sealant is visible, before further 
flight, remove the support and further inspect the support, 
transmission case, studs, and dowel pins in accordance with the 
Accomplishment Instructions, paragraphs 5 through 7, of the 
applicable Bell Helicopter Textron Alert Service Bulletin Nos. 222-
00-86, 222U-00-57, 230-00-18, or 430-00-17, all dated May 19, 2000 
(ASB's). Repair or replace any unairworthy support, transmission 
case, stud, or dowel pin before further flight.
    (2) Verify the torque of the support attaching nuts (nuts). 
Upper nuts must not rotate at a torque less than 40 in-lbs. Lower 
nuts must not rotate at a torque less than 90 in-lbs.
    (i) If two or more upper nuts rotate at a torque less than 40 
in-lbs. or two or more lower nuts rotate at a torque less than 90 
in-lbs., before further flight, remove the support and further 
inspect the support, transmission case, studs, and dowel pins in 
accordance with the Accomplishment Instructions, paragraph 5 through 
7, of the applicable ASB's. Repair or replace any unairworthy 
support, transmission case, stud, or dowel pin before further 
flight.
    (ii) If less than two upper nuts rotate at a torque less than 40 
in-lbs. or less than two lower nuts rotate at a torque less than 90 
in-lbs., before further flight, retorque the upper nut to 50 to 70 
in-lbs. plus tare and the lower nut to 100 to 140 in-lbs. plus tare.
    (b) At not less than 20 hours TIS nor more than 30 hours TIS 
after reinstalling a support for any reason, verify the torque of 
the nuts in accordance with paragraph (a)(2) of this AD.
    (c) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (d) 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.
    (e) The inspections shall be done in accordance with the 
Accomplishment Instructions, paragraphs 5 through 7, of the 
applicable Bell Helicopter Textron Alert Service Bulletin Nos. 222-
00-86, 222U-00-57, 230-00-18, or 430-00-17, all dated May 19, 2000. 
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 Bell Helicopter Textron Canada, 
12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, telephone (450) 437-
2862 or (800) 363-8023, fax (450) 433-0272. 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.
    (f) This amendment becomes effective on March 2, 2001, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-01-51, issued January 5, 2001, which 
contained the requirements of this amendment.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-2000-29, dated September 6, 2000.



[[Page 10363]]


    Issued in Fort Worth, Texas, on February 2, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-3561 Filed 2-14-01; 8:45 am]
BILLING CODE 4910-13-U