1278 Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Rules and Regulations

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–01–08 Fokker: Amendment 39–9879.

Docket 96–NM–28–AD.

Applicability: Model F27 Mark 100, 200,

300, 400, 500, 600, and 700 series airplanes,

serial numbers 10653 through 10692

inclusive; on which Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletins F27/57–68 and F27/57–70

has not been accomplished; certificated in

any category.

Note 1: This AD applies to each airplane

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

airplanes 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 loose or missing rivets at the

rib-to-stringer connections of the upper and

lower wing skin at stringers 5 and 6, which

could result in reduced structural integrity of

the wings; accomplish the following:

(a) Except as provided by paragraph (c) of

this AD: Prior to the accumulation of 10,000

total flight cycles, or within 2 months after

the effective date of this AD, whichever

occurs later, perform a one-time visual

inspection to detect missing rivet heads or

loose rivets of the applicable stringer-to-rib

connections in the upper and lower skin, in

accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/57–74, dated November

15, 1994.

(1) If no missing rivet head and no loose

rivet is detected, no further action is required

by paragraph (a) of this AD.

(2) If any missing rivet head or loose rivet

is detected, prior to further flight, repair the

affected rib-to-stringer connection, in

accordance with Part 1 of the

Accomplishment Instructions of the service

bulletin.

(b) Prior to the accumulation of 10,000

total flight cycles, or within 1 year after the

effective date of this AD, whichever occurs

later, replace rivets having part number (P/

N) MS20600AD4W2 with new rivets having

P/N CR3553P4 in all applicable rib-tostringer connections of the upper and lower

wings, in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/57–74, dated November

15, 1994.

(c) Airplanes on which the replacement

required by paragraph (b) of this AD is

performed within the compliance time

specified in paragraph (a) of this AD are not

required to accomplish the inspection

required by paragraph (a) 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,

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) The inspection, repair, and replacement

shall be done in accordance with Fokker

Service Bulletin F27/57–74, dated November

15, 1994. 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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

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.

(g) This amendment becomes effective on

February 13, 1997.

Issued in Renton, Washington, on January

2, 1997.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–362 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–03–AD; Amendment

39–9877; AD 97–01–06]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc.-Manufactured

Restricted Category Model HH–1K, TH–

1F, TH–1L, UH–1A, UH–1B, UH–1E,

UH–1F, UH–1H, UH–1L, and UH–1P

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. (BHTI)-manufactured restricted

category Model HH–1K, TH–1F, TH–1L,

UH–1A, UH–1B, UH–1E, UH–1F, UH–

1H, UH–1L, and UH–1P helicopters,

that requires a one-time inspection of

the tail rotor slider (slider) to verify that

it was manufactured with the correct

outside diameter. This amendment is

prompted by a United States (U.S.)

Army Safety of Flight message that

reports that some sliders may have been

improperly manufactured with an

undersized wall thickness by U.S. Army

vendors. The actions specified by this

AD are intended to prevent fatigue

failure of the slider, which could cause

loss of tail rotor control and subsequent

loss of control of the helicopter.

EFFECTIVE DATE: February 13, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Uday Garadi, Aerospace Engineer,

Rotorcraft Certification Office,

Rotorcraft Directorate, FAA, 2601

Meacham Blvd., Fort Worth, Texas

76137; telephone (817) 222–5157, fax

(817) 222–5961.

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 Bell Helicopter
Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Rules and Regulations 1279

Textron, Inc. (BHTI)-manufactured

restricted category Model HH–1K, TH–

1F, TH–1L, UH–1A, UH–1B, UH–1E,

UH–1F, UH–1H, UH–1L, and UH–1P

helicopters was published in the

Federal Register on September 5, 1996

(61 FR 46742). That action proposed to

require a one-time inspection of the tail

rotor slider (slider) to verify that it was

manufactured with the correct outside

diameter.

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, with one

exception. The word ‘‘barrel’’ was

added to paragraph (a) of the AD to

indicate that the splined shaft of the

slider is also known as the barrel of the

slider. This change neither increases the

costs associated with the AD nor

increases the scope of the AD.

The FAA estimates that 80 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 0.5

work hour per helicopter to accomplish

the required inspection, and that the

average labor rate is $60 per work hour.

Replacement of the slider requires 8

hours, and required parts cost

approximately $72 per helicopter. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $46,560 if replacement of the slider

is required in all of the fleet.

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, 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:

AD 97–01–06 California Department of

Forestry; Erickson Air Crane Co.;

Garlick Helicopters; Hawkins and

Powers Aviation, Inc.; International

Helicopters, Inc.; Smith Helicopters;

Southwest Florida Aviation; West Coast

Fabrications; Western International

Aviation, Inc.; Williams Helicopter

Technology, Inc.; and UNC Helicopters:

Amendment 39–9877. Docket No. 96–

SW–03–AD.

Applicability: Bell Helicopter Textron,

Inc.-manufactured Model HH–1K, TH–1F,

TH–1L, UH–1A, UH–1B, UH–1E, UH–1F,

UH–1H, UH–1L, and UH–1P helicopters,

certificated in the restricted 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 (b) 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 5 hours timein-service after the effective date of this AD,

unless accomplished previously.

To prevent fatigue failure of the tail rotor

slider (slider), which could cause loss of the

tail rotor and subsequent loss of control of

the helicopter, accomplish the following:

(a) Using a calibrated caliper or

micrometer, measure the outside diameter of

the splined shaft (barrel) of the slider, part

number (P/N) 204–010–720–3 or P/N 204–

010–720–003, at two points that are 90

degrees apart on the outside circumference of

the barrel, one-half to one inch from either

end of the slider. If the outside diameter of

the slider is less than 1.300 inches, remove

the slider and replace it, prior to further

flight, with a slider that has an outside

diameter of 1.300 inches or greater.

(b) 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.

(c) 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.

(d) 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.

(e) This amendment becomes effective on

February 13, 1997.

Issued in Fort Worth, Texas, on December

31, 1996.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–404 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

SECURITIES AND EXCHANGE

COMMISSION

17 CFR Part 240

[Release No. 34–38110; File No. S7–30–95]

RIN 3235–AG66

Order Execution Obligations

AGENCY: Securities and Exchange

Commission.

ACTION: Final rule; revised effective

date; revised compliance dates.

SUMMARY: The Securities and Exchange

Commission is revising: (1) The

effective date of Rule 11Ac1–4 (‘‘Limit

Order Display Rule’’) and amendments