Federal Register / Vol. 62, No. 201 / Friday, October 17, 1997 / Proposed Rules 53977

FAA’s Conclusions

These airplane models are

manufactured in the Netherlands and

are type certificated for operation in the

United States under the provisions of

section 21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously.

Cost Impact

The FAA estimates that 127 Fokker

Model F28 Mark 0100 series airplanes

and 4 Fokker Model F28 Mark 0070

series airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 3 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be provided by the manufacturer

at no cost to operators. Based on these

figures, the cost impact of the proposed

AD on U.S. operators is estimated to be

$23,580, or $180 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Fokker: Docket 97-NM–245-AD.

Applicability: Model F28 Mark 0070 and

Mark 0100 series airplanes, as listed in

Fokker Service Bulletin SBF100–52–060,

dated October 10, 1995; certificated in any

category.

Note 1: This AD applies to each airplane

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 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 (b) 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 ensure that the operating handles of the

overwing emergency exits are clearly visible

during an emergency evacuation, accomplish

the following:

(a) Within 12 months after the effective

date of this AD, remove the operating handle

assemblies of the overwing emergency exits,

having part number (P/N) D32965–403, and

install new self-illuminating handle

assemblies, having P/N D32965–407, in

accordance with Fokker Service Bulletin

SBF100–52–060, dated October 10, 1995.

(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,

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.

(c) 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.

Note 3: The subject of this AD is addressed

in Netherlands airworthiness directive BLA

1995–104 (A), dated October 31, 1995.

Issued in Renton, Washington, on October

10, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–27580 Filed 10–16–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–01–AD]

Airworthiness Directives; Robinson

Helicopter Company Model R44

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

Robinson Helicopter Company

(Robinson) Model R44 helicopters. This

proposal would require removing and

replacing the cyclic control pilot’s grip

assembly (grip assembly) with an

airworthy grip assembly. This proposal

is prompted by a report of a crack in the

welded corner of a grip assembly. The

actions specified by the proposed AD

are intended to prevent use of a grip

assembly that may crack, resulting in

failure of the grip assembly and

subsequent loss of control of the

helicopter.
53978 Federal Register / Vol. 62, No. 201 / Friday, October 17, 1997 / Proposed Rules

DATES: Comments must be received by

December 16, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Regional Counsel, Southwest

Region, Attention: Rules Docket No. 97–

SW–01–AD, 2601 Meacham Blvd.,

Room 663, Fort Worth, Texas 76137.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Robinson Helicopter Company, 2901

Airport Drive, Torrance, California

90505. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr.

Fred Guerin, Aerospace Engineer, FAA,

Los Angeles Aircraft Certification

Office, Airframe Branch, 3960

Paramount Boulevard, Lakewood,

California 90712, telephone (562) 627–

5232, fax (562) 627–5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 97–SW–01–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Office of the Regional Counsel,

Southwest Region, Attention: Rules

Docket No. 97–SW–01–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

This action proposes the adoption of

a new AD that is applicable to Robinson

Model R44 helicopters. The proposed

AD would require removing the grip

assembly, part number (P/N) A756–6

Revision N (or prior), and replacing it

with an airworthy grip assembly, P/N

A756–6 Revision M (or later), within 25

hours time-in-service (TIS) or 30

calendar days after the effective date of

this AD, whichever occurs first. This

proposal is prompted by one report of

a crack in the welded corner of the grip

assembly. The actions specified in this

proposal are intended to prevent use of

a grip assembly that may crack, which

could result in failure of the grip

assembly and subsequent loss of control

of the helicopter.

The FAA has reviewed Robinson

Helicopter Company KI–112 R44 Pilot’s

Grip Assembly Upgrade Kit

instructions, dated December 20, 1996,

which describes procedures for

replacement of the grip assembly.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Robinson Model R44

helicopters of the same type design, the

proposed AD would require removing

the grip assembly, P/N A756–6 Revision

N (or prior), and replacing it with an

airworthy grip assembly, P/N A765–6

Revision M (or later), within 25 hours

TIS or 30 calendar days after the

effective date of this AD, whichever

occurs first. The actions are required to

be accomplished in accordance with the

kit instructions described previously.

The FAA estimates that 5 helicopters

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

helicopter to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $576 per

helicopter. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be $4,080.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Robinson Helicopter Company: Docket No.

97–SW–01–AD.

Applicability: Model R44 helicopters,

serial numbers (S/N) 0001 through 0159,

except S/N 0143, 0150, and 0156, with cyclic

control pilot’s grip assembly (grip assembly),

part number (P/N) A756–6 Revision N or

prior, 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 (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
Federal Register / Vol. 62, No. 201 / Friday, October 17, 1997 / Proposed Rules 53979

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: Within 25 hours time-inservice or 30 calendar days after the effective

date of this AD, whichever occurs first.

To prevent use of a grip assembly that may

crack, resulting in failure of the grip

assembly and subsequent loss of control of

the helicopter, accomplish the following:

(a) Remove the grip assembly, P/N A756–

6 Revision N (or prior), and replace it with

an airworthy grip assembly, P/N A756–6

Revision M (or later), in accordance with KI–

112 R44 Pilot’s Grip Assembly Upgrade Kit

instructions, dated December 20, 1996.

(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, Los

Angeles Aircraft 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, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(c) 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.

Issued in Fort Worth, Texas, on October 9,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–27585 Filed 10–16–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–21–AD]

Airworthiness Directives; Eurocopter

Deutschland GmbH (ECD) Model BO

105 C and BO 105 S Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Proposed rule; withdrawal.

SUMMARY: This action withdraws a

notice of proposed rulemaking (NPRM)

that proposed a new airworthiness

directive (AD), applicable to Eurocopter

Deutschland GmbH (ECD) (Eurocopter

Deutschland) Model BO 105 C and BO

105 S helicopters. That action would

have required modifying the main relay

box by replacing the voltage regulator;

modifying the cockpit overhead panel

by installing two additional switches;

and performing a functional test of the

new voltage regulator, generators, and

new switches. Since the issuance of the

NPRM, the Federal Aviation

Administration (FAA) has determined

that the modification proposed is only

necessary for Instrument Flight Rule

(IFR) configurations, and since there is

no IFR FAA type-design approval for

the affected models, it is unnecessary to

issue an AD.

FOR FURTHER INFORMATION CONTACT: Mr.

Lance Gant, Aerospace Engineer, FAA,

Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5114, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

add a new airworthiness directive (AD),

applicable to Eurocopter Deutschland

Model BO 105 C and BO 105 S

helicopters, was published in the

Federal Register on February 13, 1997

(62 FR 6746). The proposed rule would

have required modifying the main relay

box 1VE; modifying the cockpit

overhead panel, and performing a

functional test of the new voltage

regulator, generators, and new switches

for the affected helicopters. That action

was prompted by an in-service report of

a helicopter that experienced a

generator overvoltage. The proposed

actions were intended to prevent failure

of essential electrical equipment that

could result in spatial disorientation

and subsequent loss of control of the

helicopter.

Since the issuance of that NPRM, the

FAA has determined that the need for

overvoltage protection is associated

with the IFR requirement to have certain

avionics available; however, there is no

FAA IFR type-design approval for the

affected models, therefore there is no

type design model on which to issue an

AD.

Upon further consideration and

review of this new data, the FAA has

determined that the unsafe condition no

longer exists and is extremely unlikely

to develop. Accordingly, the proposed

rule is hereby withdrawn.

Withdrawal of this notice of proposed

rulemaking constitutes only such action,

and does not preclude the agency from

issuing another notice in the future, nor

does it commit the agency to any course

of action in the future.

Since this action only withdraws a

notice of proposed rulemaking, it is

neither a proposed nor a final rule and

therefore, is not covered under

Executive Order 12866, the Regulatory

Flexibility Act, or DOT Regulatory

Policies and Procedures (44 FR 11034,

February 26, 1979).

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Withdrawal

Accordingly, the notice of proposed

rulemaking, Docket No. 96–SW–21–AD,

published in the Federal Register on

February 13, 1997 (62 FR 6746), is

withdrawn.

Issued in Fort Worth, Texas, on October 7,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–27584 Filed 10–16–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 97–ASO–22]

Proposed Establishment of Class D

Airspace; Hickory, NC

AGENCY: Federal Aviation

Administration (FAA) DOT.

ACTION: Notice or proposed rulemaking.

SUMMARY: This proposed rule would

establish Class D airspace at Hickory,

NC. A non-federal control tower will

open at Hickory Regional Airport,

Hickory, NC, on or about October 1,

1997. Class D surface area airspace is

required when the control tower is open

to accommodate current Standard

Instrument Approach Procedures (SIAP)

and for Instrument Flight Rules (IFR)

operations at the airport.

DATES: Comments must be received on

or before November 17, 1997.

ADDRESSES: Send comments on the

proposal in triplicate to: Federal

Aviation Administration, Docket No.

97–ASO–22, Manager, Airspace Branch,

ASO–520, P.O. Box 20636, Atlanta,

Georgia 30320

The official docket may be examined

in the Office of the Assistant Chief

Counsel for Southern Region, Room 550,

1701 Columbia Avenue, College Park,

Georgia 30337, telephone (404) 305–

5586. An informal docket may also be

examined during normal business hours

at the address listed above.

FOR FURTHER INFORMATION CONTACT:

Nancy B. Shelton, Airspace Branch, Air

Traffic Division, Federal

Administration, P.O. Box 20636,

Atlanta, Georgia 30320; telephone (404)

305-5491.