AD 2001-08-04

[Federal Register Volume 66, Number 75 (Wednesday, April 18, 2001)]
[Rules and Regulations]
[Pages 19850-19852]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-9498]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-06-AD; Amendment 39-12181; AD 2001-08-04]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Inc. Model 
205A-1, 205B, 212, 412, 412CF, and 412EP Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 
412, and 412CF helicopters. That AD currently 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 that AD. This amendment 
requires the same actions as the existing AD but adds the BHTI Model 
412EP helicopters to the applicability. This amendment is prompted by 
the discovery that the BHTI Model 412EP helicopter was inadvertently 
omitted from the existing AD. The actions specified by this AD are 
intended 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.

DATES: Effective May 3, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved by the Director of the Federal 
Register as of December 28, 2000 (65 FR 77780, December 13, 2000).
    Comments for inclusion in the Rules Docket must be received on or 
before June 18, 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-06-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#4e77632f3d39632f2a2d2123232b203a3d0e282f2f60292138"><span class="__cf_email__" data-cfemail="b78e9ad6c4c09ad6d3d4d8dadad2d9c3c4f7d1d6d699d0d8c1">[email&#160;protected]</span></a>.
    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 76137; 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: On November 30, 2000, the FAA issued AD 
2000-25-03, Amendment 39-12037 (65 FR 77780), to require, 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 HR 
Textron, 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 that AD. That 
action was 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 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. That condition, if not corrected, could cause loss of 
control of the main rotor and subsequent loss of control of the 
helicopter.
    Since the issuance of that AD, we discovered that we inadvertently 
omitted the BHTI Model 412EP helicopters from the applicability of the 
AD.
    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 
ASB's.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTI Model 205A-1, 205B, 212, 412, 412CF, and 
412EP helicopters of the same type designs, this AD is being issued to 
prevent an actuator piston from unthreading from

[[Page 19851]]

the rod end causing loss of collective control and subsequent loss of 
control of the helicopter. This AD requires the same actions as the 
previous AD and adds the BHTI Model 412EP helicopters to the 
applicability. 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 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 550 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 $209,000, assuming all the locking devices on all the helicopters 
are replaced without any inspections.

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-06-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 1 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 removing Amendment 39-12037 (65 FR 
77780, December 13, 2000), and by adding a new airworthiness directive 
(AD), Amendment 39-12181, to read as follows:

2001-08-04  Bell Helicopter Textron Inc.: Amendment 39-12181. Docket 
No. 2001-SW-06-AD. Supersedes AD 2000-25-03, 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, 412CF, and 412EP 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, 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.

[[Page 19852]]

    (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.

    (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 previously approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of 
December 28, 2000 (65 FR 77780, December 13, 2000). 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 May 3, 2001.

    Issued in Fort Worth, Texas, on April 10, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 01-9498 Filed 4-17-01; 8:45 am]
BILLING CODE 4910-13-U