[Federal Register Volume 65, Number 240 (Wednesday, December 13, 2000)]
[Rules and Regulations]
[Pages 77780-77782]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-31317]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-SW-49-AD; Amendment 39-12037; AD 2000-25-03]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Inc. Model
205A-1, 205B, 212, 412, and 412CF 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) for
Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and
412CF helicopters. This action requires inspecting the locking washer
on each main rotor actuator (actuator) for twisting or damage to the
tab and replacing any locking washer that has a twisted or damaged tab.
Replacing certain locking washers, regardless of condition, is also
required within a specified time period. Installing a certain airworthy
locking device on each actuator constitutes terminating action for the
requirements of this AD. This amendment is prompted by an incident in
which a damaged locking washer allowed the rod end to detach from the
collective actuator, causing loss of collective control of the main
rotor. The current locking washer is subject to mechanical damage and
failure, which allows the actuator piston to unthread itself from its
rod end. This condition, if not corrected, could cause loss of control
of the main rotor and subsequent loss of control of the helicopter.
DATES: Effective December 28, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 28, 2000.
Comments for inclusion in the Rules Docket must be received on or
before February 12, 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-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].
The service information referenced in this AD may be obtained from
HR Textron, 25200 W. Rye Canyon Road, Santa Clarita, California 91355-
1265, telephone (611) 702-5509, fax (661) 702-5970. 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: Alfred Boutin, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5157, fax (817) 222-
5783.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for BHTI
Model 205A-1, 205B, 212, 412, and 412CF helicopters. This AD requires,
within 25 hours time-in-service (TIS), inspecting the tab on the
NAS513-6 locking washer on all actuators, part number (P/N) 41105950,
serial number with an ``HR'' prefix up to and including 490 and P/N
41000470, serial numbers with a prefix of ``HR'' up to and including
10010, for a twisted or damaged tab. P/N's 41105950 and 41000470 were
assigned by the manufacturer; the BHTI P/N's are 205-076-036 and 212-
076-005. Replacing any twisted or damaged locking washer with an
airworthy NAS1193K6C locking device is required before further flight.
Replacing any NAS513-6 locking washer with an airworthy NAS1193K6C
locking device, regardless of the condition of the tab, is required
within 100 hours TIS or at the next actuator overhaul, whichever occurs
first. Installing an airworthy NAS 1193K6C locking device on all
actuators constitutes terminating action for the requirements of this
AD. This AD is prompted by the discovery of a damaged locking washer.
The damage to the locking washer was discovered when an operator
experienced a problem with a collective control while attempting to
take off. The collective control could not be moved upward from the
full down position. Further inspection revealed that the lower piston
of the actuator had unthreaded and separated from the lower rod end,
causing the piston to make contact with the rod end support assembly
and lodge itself against the rod end shank at an angle limiting any
movement of the collective control. The collective servo cylinder
assembly is used to provide irreversible collective control of the main
rotor. Because the actuator end locking washer failed, the servo lower
piston could rotate inside the lower servo head assembly and unthread
itself from the rod end. This condition, if not corrected, could cause
loss of control of the main rotor and subsequent loss of control of the
helicopter.
The FAA has reviewed HR Textron Alert Service Bulletin (ASB) No.
41000470-67A-05, Revision 1 and HR Textron ASB No. 41105950-67A-01,
Basic Issue, both dated October 19, 2000, which describe procedures for
inspecting and replacing certain locking washers. BHTI has issued ASB
No.'s 205-00-79, 205B-00-33, 212-00-109, 412-00-105, and 412CF-00-12,
all dated October 19, 2000, which include the applicable HR Textron
Alert Service Bulletins.
Since an unsafe condition has been identified that is likely to
exist or develop on other BHTI Model 205A-1, 205B, 212, 412, and 412CF
helicopters of the same type designs, this AD is being issued to
prevent an actuator piston from unthreading itself from its rod end
causing loss of collective control and subsequent loss of control of
the helicopter. This AD requires inspecting the locking washers on all
actuators for twisting or damage to the tab and replacing any locking
washer that has a twisted or damaged tab. Replacing certain locking
washers, regardless of condition, is also required within 100 hours TIS
or at the next actuator overhaul, whichever occurs first. Installing an
airworthy NAS1193K6C locking device on all actuators constitutes
terminating action for the requirements of this AD. The actions must be
accomplished in accordance with the HR Textron service bulletins
described previously. The short compliance time involved is required
because the previously described critical unsafe condition can
[[Page 77781]]
adversely affect the controllability of the helicopter. Therefore, the
actions described previously are required at the specified time
intervals, 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 500 helicopters will be affected by this AD.
It will take approximately 1 work hour to inspect the locking washer, 6
work hours per helicopter to replace the three locking devices on each
helicopter, and the average labor rate is $60 per work hour. Required
parts will cost approximately $20 per helicopter. Based on these
figures, the total cost impact of the AD on U.S. operators is estimated
to be $190,000, assuming all the locking devices on all the helicopters
are 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.
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-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, 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:
2000-25-03 Bell Helicopter Textron Inc.: Amendment 39-12037. Docket
No. 2000-SW-49-AD.
Applicability: (a) Model 205A-1 helicopters with a hydraulic
servo actuator (actuator), part number (P/N) 41105950, serial
numbers with an ``HR'' prefix up to and including 490, installed,
certificated in any category; and
(b) Model 205A-1, 205B, 212, 412, and 412CF helicopters with an
actuator, P/N 41000470, serial numbers with an ``HR'' prefix up to
and including 10010, installed, certificated in any category.
Note 1: P/N 41105950 is the P/N assigned by HR Textron, which is
the actuator manufacturer. Bell Helicopter Textron, Inc. (BHTI) has
assigned P/N 205-076-036 to this part when fitted with a support
mount. P/N 41000470 is the P/N assigned by HR Textron; BHTI has
assigned P/N 212-076-005 to this part when fitted with a support
mount.
Note 2: 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 (d) 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 an actuator piston from unthreading from its rod end,
loss of control of the main rotor, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS), inspect the tab on
the NAS513-6 locking washer on each actuator for any twisting or
damage in accordance with the Accomplishment Instructions, paragraph
A., of HR Textron Alert Service Bulletin (ASB) No. 41000470-67A-05,
Revision 1, dated October 19, 2000 or HR Textron ASB No. 41105950-
67A-01, Basic Issue, dated October 19, 2000, as applicable to the
affected actuator P/N. Replace any twisted or damaged locking washer
with an airworthy NAS1193K6C locking device before further flight.
(b) Within 100 hours TIS or at the next actuator overhaul,
whichever occurs first, replace the NAS513-6 locking washer on each
actuator with an airworthy NAS1193K6C locking device.
(c) Installation of an airworthy NAS1193K6C locking device on
each of the three actuators constitutes terminating action for the
requirements of this AD.
(d) 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, Rotorcraft Certification Office,
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, Rotorcraft Certification
Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Certification Office.
[[Page 77782]]
(e) 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.
(f) The inspections and modifications shall be done in
accordance with the Accomplishment Instructions, paragraph A., of HR
Textron Alert Service Bulletin No. 41000470-67A-05, Revision 1 or HR
Textron ASB No. 41105950-67A-01, Basic Issue, both dated October 19,
2000, as applicable to the affected actuator P/N. 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 HR Textron, 25200 W. Rye Canyon Road, Santa Clarita,
California 91355-1265, telephone (611) 294-6000, fax (661) 259-9622.
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.
Note 4: BHTI ASB No.'s 205-00-79, 205B-00-33, 212-00-109, 412-
00-105, and 412CF-00-12, all dated October 19, 2000, pertain to the
subject of this AD and include the applicable HR Textron Alert
Service Bulletins.
(g) This amendment becomes effective on December 28, 2000.
Issued in Fort Worth, Texas, on November 30, 2000.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-31317 Filed 12-12-00; 8:45 am]
BILLING CODE 4910-13-U