77780 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

Total pages: 16.

The incorporations by reference were

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 Rolls-Royce North America, Inc., 2001

South Tibbs Ave., Indianapolis, IN 46241;

telephone: (317) 230–3995; fax: (317) 230–

4743. Copies may be inspected at the FAA,

New England Region, Office of the Regional

Counsel, 12 New England Executive Park,

Burlington, MA 01803–5299; or at the Office

of the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

February 12, 2001.

Issued in Burlington, Massachusetts, on

November 30, 2000.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–31066 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–U

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.

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: 9-asw-adcomments@faa.gov.

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

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 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.

§ 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.

77782 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

(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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–60–AD; Amendment

39–12038; AD 2000–25–04]

RIN 2120–AA64

Airworthiness Directives; Raytheon

(Beech) Model MU–300, MU–300–10,

400, 400A, and 400T Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon (Beech)

Model MU–300, MU–300–10, 400,

400A, and 400T series airplanes, that

requires a one-time inspection to detect

hydraulic fluid leakage from the B-nut

area, which attaches a hydraulic tube to

the anti-skid valve assembly, and

corrective actions, if necessary; and

installation of an additional support for

the hydraulic tube. This amendment is

intended to prevent an asymmetric

braking condition and a longer stopping

distance due to sudden loss of normal

braking to the left wheel. Such loss of

normal braking could result in the

airplane overrunning the runway

surface. This action is intended to

address the identified unsafe condition.

DATES: Effective January 17, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 17,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager Service Engineering, Beechjet/

Premier Technical Support Department,

P.O. Box 85, Wichita, Kansas 67201–

0085. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita

Aircraft Certification Office, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul

C. DeVore, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas

67209, telephone (316) 946–4142; fax

(316) 946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Raytheon

(Beech) Model MU–300, MU–300–10,

400, 400A, and 400T series airplanes

was published in the Federal Register

on August 10, 2000 (65 FR 48945). That

action proposed to require a one-time

inspection to detect hydraulic fluid

leakage from the B-nut area, which

attaches a hydraulic tube to the antiskid valve assembly, and corrective

actions, if necessary; and installation of

an additional support for the hydraulic

tube.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 567 series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

522 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 2 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $31 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $78,822, or $151 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Additionally, the manufacturer has

indicated the warranty remedies may be

available to defer the cost of the

replacement parts also associated with

accomplishing this actions required by

this AD.

Regulatory Impact

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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy