Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations 16073

operator nor expand the scope of the

AD.

The FAA estimates that 40 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 20

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

The aluminum swashplate support

assembly, P/N 412–010–443–101 or

–109 costs $4,526. The steel swashplate

support assembly, P/N 412–010–453–

105, costs $9,234. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$417,360, if all the swashplates in the

fleet are replaced with support

assemblies, P/N 412–010–453–105.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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

of it 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD), Amendment 39–9980, to read as

follows:

AD 27–07–06 Bell Helicopter Textron, Inc.:

Docket No. 96–SW–17–AD. Supersedes

priority letter AD 92–03–13, issued

January 31, 1992, Docket No. 92–ASW–

31.

Applicability: Model 412 helicopters, with

steel main rotor control swashplate support

assembly (steel swashplate support

assembly), part number (P/N) 412–010–453–

101, 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

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 use the authority

provided in paragraph (e) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the steel swashplate

support assembly that could result in loss of

main rotor control and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Before further flight after the effective

date of this AD, and thereafter, before the

first flight of each day, visually inspect, with

an inspection mirror and a bright light, the

forward and aft clevis areas of the steel

swashplate support assembly, part number

(P/N) 412–010–453–101, in accordance with

Part I of Bell Helicopter Textron, Inc. Alert

Service Bulletin (ASB) 412–92–57, Revision

A, dated January 30, 1992.

(b) Before further flight after the effective

date of this AD, install a red radial arc on

each airspeed indicator to prohibit airspeeds

above 110 knots. Near the pilot’s airspeed

indicator, install a placard made of material

that is not easily erased, disfigured, or

obscured that contains the following

statement in lettering that is 0.2 inch

minimum in height: ‘‘VNE not to exceed 110

KIAS or VNE from the airspeed limitation

placard, whichever is less.’’

Note 2: ASB No. 412–92–58, dated January

27, 1992, contains information on the

airspeed limitation.

(c) If a crack is found, before further flight,

replace the steel swashplate support

assembly, P/N 412–010–453–101, with an

airworthy part.

(d) Installation of an improved steel

swashplate support assembly, P/N 412–010–

453–105, or aluminum swashplate support

assembly, P/N 412–010–443–101 or -109, in

accordance with the Accomplishment

Instructions of ASB 412–92–61, dated May

14, 1992, constitutes a terminating action for

the requirements of this AD, and the red

radial arc on each airspeed indicator and the

airspeed placard installed as a result of this

AD may be removed.

(e) An alternative method of compliance or

an adjustment of the compliance time that

provides an equivalent level of safety may be

used if approved by the Manager, Rotorcraft

Certification Office. 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.

(f) 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.

(g) The inspections, installation, and

replacement, if necessary, shall be done in

accordance with Bell Helicopter Textron, Inc.

Alert Service Bulletin (ASB) 412–92–57,

Revision A, dated January 30, 1992, or ASB

412–92–61, dated May 14, 1992, as

appropriate. 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, Inc., P.O. Box

482, Fort Worth, Texas 76101. Copies may be

inspected at the FAA, FAA, Office of the

Assistant Chief Counsel, 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.

(h) This amendment becomes effective on

May 9, 1997.

Issued in Fort Worth, Texas, on March 14,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–8426 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–SW–36–AD; Amendment

39–9981; AD 97–07–07]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, A Division of

Textron Canada Ltd. Model 206L, L–1,

L–3, and L–4 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),
16074 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

applicable to Bell Helicopter Textron, A

Division of Textron Canada Ltd. (BHTC)

Model 206L, L–1, L–3, and L–4

helicopters, that requires creation of a

component history card using a

Retirement Index Number (RIN) system,

establishing a system for tracking

increases to the accumulated RIN, and

a maximum accumulated RIN for certain

main rotor masts (masts) and main rotor

trunnions (trunnions). This amendment

is prompted by fatigue analyses and

tests that show certain masts and

trunnions fail sooner than originally

anticipated because of the unanticipated

higher number of external load lifts and

takeoffs (torque events) performed with

those masts and trunnions in addition to

the time-in-service (TIS) accrued under

other operating conditions. The actions

specified by this AD are intended to

prevent fatigue failure of the mast or

trunnion, which could result in loss of

the main rotor system and subsequent

loss of control of the helicopter.

DATES: Effective May 9, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 9,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bell Helicopter Textron, A

Division of Textron Canada Ltd. 12,800

Rue de L’Avenir, Mirabel, Quebec,

Canada J7J1R4, ATTN: Product Support

Engineering Light Helicopters. This

information may be examined at the

FAA, Office of the Assistant Chief

Counsel, 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: Mr.

Jurgen Priester, Aerospace Engineer,

Rotorcraft Certification Office,

Rotorcraft Directorate, FAA, 2601

Meacham Blvd., Fort Worth, Texas

76137, telephone (817) 222–5159, fax

(817) 222–5959.

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 BHTC Model 206L,

206L–1, 206L–3, and 206L–4 helicopters

was published in the Federal Register

on November 14, 1996 (61 FR 58355).

That action proposed to require, within

the next 100 hours TIS, creation of a

component history card using the RIN

system for certain masts and trunnions;

and establishing a system for tracking

increases to the accumulated RIN. That

action also proposed to establish a

retirement life for trunnions based

solely on a RIN of 24,000, and a mast

retirement life based on a maximum RIN

of 44,000 or a maximum number of

flight hours, whichever occurs first.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed, except for the

parenthetical insertion of the number of

RIN’s in paragraphs (d) and (e). The

FAA has determined that this change

will neither increase the economic

burden on any operator nor expand the

scope of the AD.

The FAA estimates that 711

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately (1) 8 work hours per

helicopter to replace the mast and 10

work hours per helicopter to replace the

trunnion due to the new method of

determining the retirement life required

by this AD; (2) 2 work hours per

helicopter to create the component

history card or equivalent record

(record); (3) 10 work hours per

helicopter to maintain the record each

year, and that the average labor rate is

$60 per work hour. Required parts will

cost approximately $9,538 per mast and

$2,083 per trunnion. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$2,016,989, and each subsequent year to

be $1,945,889. These costs assume

replacement of the mast and trunnion in

one-sixth of the fleet each year, creation

and maintenance of the records for all

the fleet the first year, and creation of

one-sixth of the fleet’s records and

maintenance of the records for all the

fleet each subsequent year.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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

of it 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

AD 97–07–07 Bell Helicopter Textron, a

Division of Textron Canada Ltd.:

Amendment 39–9981. Docket No. 95–

SW–36–AD.

Applicability: Model 206L, 206L–1, 206L–

3, and 206L–4 helicopters, with main rotor

mast (mast), part number (P/N) 206–040–

535–001, –005, –101, or –105, installed, or

main rotor trunnion (trunnion), P/N 206–

011–120–103, 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

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 use the authority

provided in paragraph (f) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required within 100 hours

time-in-service after the effective date of this

AD, unless accomplished previously.

To prevent fatigue failure of the mast or

trunnion, which could result in loss of the

main rotor system and subsequent loss of

control of the helicopter, accomplish the

following:
Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations 16075

(a) Create a component history card or an

equivalent record for the affected mast and

trunnion.

(b) Determine the accumulated Retirement

Index Number (RIN) to date based on the

number of takeoffs and external load lifts

(torque events) for parts in service in

accordance with paragraphs 1 and 2 of the

Accomplishment Instructions of Bell

Helicopter Textron, Inc. Alert Service

Bulletin (ASB) No. 206L–94–99, Revision A,

dated May 1, 1995. Record this accumulated

RIN on the component history card.

(c) After complying with paragraphs (a)

and (b) of this AD, during each operation

thereafter, maintain a count of the number of

external load lifts and the number of takeoffs

performed and at the end of each day’s

operations, increase the accumulated RIN on

the component history cards as follows:

(1) For the trunnion,

(i) Increase the RIN for the Model 206,

206L–1, and 206L–3 helicopters by 1 for each

torque event.

(ii) Increase the RIN for the Model 206L–

4 helicopters by 2 for each torque event.

(2) For the mast, increase the RIN for the

Model 206L, 206L–1, 206L–3, and 206L–4

helicopters by 1 for each torque event.

(d) Remove the trunnion from service on or

before attaining the maximum accumulated

RIN (24,000) in accordance with Table 1 of

the Accomplishment Instructions of Bell

Helicopter Textron, Inc. ASB No. 206L–94–

99, Revision A, dated May 1, 1995.

(e) Remove the mast from service on or

before attaining the maximum accumulated

RIN (44,000) or the flight hour service life

limit, whichever occurs first, in accordance

with Table 2 of the Accomplishment

Instructions of Bell Helicopter Textron, Inc.

ASB No. 206L–94–99, Revision A, dated May

1, 1995.

(f) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(g) 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.

(h) The creation of the component history

card, documentation, and removal of the

trunnion and mast shall be done in

accordance with Bell Helicopter Textron, Inc.

ASB No. 206L–94–99, Revision A, dated May

1, 1995. 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, A Division of

Textron Canada Ltd. 12,800 Rue de L’Avenir,

Mirabel, Quebec, Canada J7J1R4, ATTN:

Product Support Engineering Light

Helicopters. Copies may be inspected at the

FAA, Office of the Assistant Chief Counsel,

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.

(i) This amendment becomes effective on

May 9, 1997.

Issued in Fort Worth, Texas, on March 14,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–8425 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–ASO–29]

Establishment of Class E Airspace;

Thomson, GA, and Amendment of

Class E Airspace; Augusta, GA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes

Class E airspace at Thomson, GA, for the

Thomson-McDuffie Airport. Currently

the Class E airspace area for the airport

is included in the Augusta, GA, Class E

airspace area. The McDuffie NDB was

relocated from an off-airport to an onairport site. As a result the NDB

Standard Instrument Approach

Procedure (SIAP) has been revised. The

subsequent airspace review revealed

that less Class E airspace was now

required for the Thomson-McDuffie

Airport. As reduced the Class E airspace

area for the Thomson-McDuffie Airport

no longer intersects the remainder of the

Augusta Class E airspace area.

Therefore, it is necessary to establish

stand alone Class E airspace extending

upward from 700 feet above the surface

(AGL) at Thomson, GA, for the

Thomson-McDuffie Airport and amend

the Augusta, GA, Class E airspace area

by removing the airspace previously

required for the Thomson-McDuffie

Airport.

EFFECTIVE DATE: 0901 UTC, May 22,

1997.

FOR FURTHER INFORMATION CONTACT:

Benny L. McGlamery, Operations

Branch, Air Traffic Division, Federal

Aviation Administration, P.O. Box

20636, Atlanta, Georgia 30320;

telephone (404) 305–5570.

SUPPLEMENTARY INFORMATION:

History

On January 24, 1997, the FAA

proposed to amend Part 71 of the

Federal Aviation Regulations (14 CFR

Part 71) by establishing Class E airspace

at Thomson, GA, and amending Class E

airspace at Augusta, GA, (62 FR 3629).

This action will provide adequate Class

E airspace for IFR operations at

Thomson-McDuffie Airport.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments objecting to the proposal

were received. Designations for Class E

airspace extending upward from 700

feet or more above the surface are

published in Paragraph 6005 of FAA

Order 7400.9D dated September 4, 1996,

and effective September 16, 1996. The

Class E airspace designation listed in

this document will be published

subsequently in the Order.

The Rule

This amendment to Part 71 of the

Federal Aviation Regulations (14 CFR

part 71) establishes stand-alone Class E

airspace at Thomson, GA, for the

Thomson-McDuffie Airport and amends

Class E airspace at Augusta, GA, by

removing the airspace previously

required for the Thomson-McDuffie

Airport.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore, (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)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR Part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

Part 71 continues to read as follows:

Authority: 49 U.S.C. 106(g); 40103, 40113,

40120; EO 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389; 14 CFR 11.69.