16072 Federal Register / Vol. 62, No. 65 / Friday, April 4, 1997 / Rules and Regulations

Revision 1, dated March 14, 1992:

Within 2 years after the effective date of

this AD, replace the control knobs on

the crossfeed and isolation valve control

unit 5QB with new knobs, in

accordance with Airbus Service Bulletin

A300–28–0061, Revision 1, dated March

14, 1992.

Note 3: Airbus Service Bulletin A300–28–

0061, Revision 1, references ECE Service

Bulletins 28–191, dated July 26, 1982, and

28–228, dated November 1, 1991, as

additional sources of procedural information

for replacement of the control knobs.

(d) Accomplishment of both of the

replacements specified in paragraphs (b) and

(c) of this AD constitutes terminating action

for the repetitive checks and tests required by

paragraph (a) of this AD.

(e) 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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(g) The actions shall be done in accordance

with the following Airbus service documents,

which contain the specified list of effective

pages:

Service bulletin referenced and date Page No. Revision level

shown on page

Date shown on

page

Airbus All Operator Telex (AOT) 28–03, June 6, 1991 ........................................... 1–3 ............................ ...................... June 6, 1991

Airbus Service Bulletin A300–28–055, Revision 3, December 19, 1991 ................ 1,4 ............................. 3 ....................... Dec. 19, 1991.

2, 3, 5, 6 .................... 2 ....................... Sept. 19, 1991.

7, 9, 10, 13 ................ Original ............. Oct. 16, 1983.

8, 11, 12 .................... 1 ....................... July 2, 1991.

Airbus Service Bulletin A300–28–055, Change Notice 3.A., March 16, 1992 ........ 1–2 ............................ ...................... Mar. 16, 1992

Airbus Service Bulletin A300–28–0061, Revision 1, March 14, 1992 ..................... 1 ................................ 1 ....................... Mar. 14, 1992.

2–7 ............................ Original ............. Jan. 23, 1992.

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; 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 Renton, Washington, on March

26, 1997.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8266 Filed 4–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–17-AD;

Amendment 39–9980; AD 97–07–06]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 412

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing priority letter airworthiness

directive (AD), applicable to Bell

Helicopter Textron, Inc. Model 412

helicopters, that currently requires a

daily inspection of certain swashplate

support assemblies. It also requires a

reduction in VNE, and installation of

appropriate airspeed indicator markings

and a placard. This amendment requires

the same actions required by the

existing priority letter AD, but restricts

the applicability to the Model 412

helicopters with a certain steel main

rotor control swashplate support

assembly (steel swashplate support

assembly) installed. This amendment

also allows the installation of an

improved main rotor control swashplate

assembly that terminates the

requirements of this AD. This

amendment is prompted by reported

cracking and in-service failures of

certain steel swashplate support

assemblies. The actions specified by this

AD are intended 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.

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, Inc., P.O.

Box 482, Fort Worth, Texas 76101. 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.

Charles Harrison, Aerospace Engineer,

Federal Aviation Administration,

Southwest Region, Rotorcraft

Certification Office, ASW–170, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5447, FAX (817) 222–5959.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding priority letter AD 92–

03–13, issued January 31, 1992, which

is applicable to Bell Helicopter Textron,

Inc. Model 412 helicopters, was

published in the Federal Register on

October 25, 1996 (61 FR 55231). That

action proposed to require a daily

inspection of certain steel main rotor

control swashplate support assemblies,

a reduction in VNE, and installation of

appropriate airspeed markings and a

placard. It also proposed an optional

installation of an improved steel main

rotor control swashplate support

assembly or an aluminum swashplate

support assembly, that, when installed,

constitutes a terminating action for the

requirements of this AD.

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 with one change—a reference to

a specific part of a service bulletin was

added for clarification. The FAA has

determined that this change will neither

increase the economic burden on any
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),