[Federal Register Volume 65, Number 39 (Monday, February 28, 2000)]
[Rules and Regulations]
[Pages 10385-10386]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-4371]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-SW-77-AD; Amendment 39-11598; AD 2000-04-15]
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 amendment adopts a new airworthiness directive (AD)
applicable to Bell Helicopter Textron Canada (BHTC) Model 222, 222B,
222U, and 230 helicopters. This action requires inspecting the
swashplate assembly drive pin (drive pin) for damage or looseness,
torque testing to determine if the interference fit between the drive
pin and rotating ring (ring) is adequate, and replacing any unairworthy
drive pin. This amendment is prompted by an accident investigation that
revealed fatigue failure of a drive pin. The actions specified in this
AD are intended to prevent fatigue failure of a drive pin and
subsequent loss of control of the helicopter.
DATES: Effective March 14, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 14, 2000.
Comments for inclusion in the Rules Docket must be received on or
before April 28, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 99-SW-77-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The service information referenced in this AD may be obtained from
Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec
JON1LO, telephone (800) 463-3036, fax (514) 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 76137; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aerospace Engineer, FAA,
Rotorcraft Directorate, Regulations Group, 2601 Meacham Blvd., Fort
Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: 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 an investigation into the crash of a BHTC Model 222
helicopter revealed that one of the two drive pins, part number (P/N)
222-010-455-003, had failed due to an insufficient interference fit
between the pin and the ring.
BHTC has issued Service Bulletins 230-99-16, 222U-99-55, and 222-
99-84, all dated February 15, 1999. These service bulletins describe
procedures for inspecting each drive pin, P/N 222-010-455-003, for
damage or looseness; conducting an initial torque test to determine if
the interference fit between each drive pin and ring is adequate; and
replacing any unairworthy drive pin. Transport Canada classified these
service bulletins as mandatory and issued AD No. CF-99-16, dated June
9, 1999, 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
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness 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 an unsafe condition has been identified that is likely to
exist or develop on other BHTC Model 222, 222B, 222U, and 230
helicopters of these same type designs registered in the United States,
this AD is being issued to prevent fatigue failure of a drive pin, P/N
222-010-455-003, and subsequent loss of control of the helicopter. This
AD requires inspecting each drive pin for damage or looseness, an
initial torque test to determine if the interference fit between the
drive pin and ring is adequate, and replacing any unairworthy drive
pin. The actions are required to be accomplished in accordance with the
service bulletins described previously. The short compliance time
involved is required because the previously described critical unsafe
condition can adversely affect the controllability and structural
integrity of the helicopter. Therefore, an inspection and torque test
of the drive pin is required within the next 50 hours time-in-service
(TIS) and this AD must be issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
The FAA estimates that 105 helicopters will be affected by this AD,
that it will take approximately 1 work hour to accomplish the
inspection and the torque test, and that the average labor rate is $60
per work hour. A special tool to perform the torque test will cost
approximately $196 per helicopter. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $26,880.
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, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
[[Page 10386]]
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 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. 99-SW-77-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:
AD 2000-04-15 Bell Helicopter Textron Canada: Amendment 39-11598.
Docket No. 99-SW-77-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,
with swashplate drive pin (drive pin), part number (P/N) 222-010-
455-003, 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 prevent fatigue failure of a drive pin and subsequent loss of
control of the helicopter, accomplish the following:
(a) Within the next 50 hours time-in-service (TIS), and
thereafter at intervals not to exceed 150 hours TIS, inspect for
damage or looseness and torque test any drive pin, P/N 222-010-455-
003, in accordance with the Accomplishment Instructions of Bell
Helicopter Textron Alert Service Bulletins 230-99-16, 222-99-84, or
222U-99-55, all dated February 15, 1999, as applicable. Replace any
unairworthy drive pin with an airworthy drive pin.
(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 2: 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) The inspection and torque test shall be done in accordance
with the Accomplishment Instructions of Bell Helicopter Textron
Alert Service Bulletins 230-99-16, 222-99-84, or 222U-99-55, all
dated February 15, 1999. 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 (800) 463-3036, fax (514) 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.
(e) This amendment becomes effective on March 14, 2000.
Note 3: The subject of this AD is addressed in Transport Canada
(Canada) AD CF-99-19, dated June 9, 1999.
Issued in Fort Worth, Texas, on February 16, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-4371 Filed 2-25-00; 8:45 am]
BILLING CODE 4910-13-U