Federal Register / Vol. 66, No. 122 / Monday, June 25, 2001 / Proposed Rules 33651

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the tail rotor yoke in

flight and subsequent loss of control of the

helicopter, accomplish the following:

(a) Within 100 hours time-in-service,

install a high altitude tail rotor static stop

yield indicator (indicator), P/N 206–011–

752–101, in accordance with the

Accomplishment Instructions, Part II, Bell

Helicopter Textron Alert Service Bulletin No.

206L–96–104, Revision B, dated July 24,

1998.

(b) Before each engine start, check the

indicator for damage in accordance with

Figure 1 of this AD. If damage is found,

before further flight, replace the damaged

indicator with an airworthy indicator, and

replace the tail rotor yoke, P/N 406–012–

102–107, with an airworthy tail rotor yoke.

(c) An owner/operator (pilot) holding at

least a private pilot certificate may perform

the visual check required by paragraph (b) of

this AD, and must record compliance in the

helicopter maintenance records in

accordance with 14 CFR 43.11 and

91.417(a)(2)(v)).

(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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(e) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the helicopter to a location where

the requirements of this AD can be

accomplished.

Note 3: The subject of this AD is addressed

in Transport Canada (Canada) AD CF–98–11,

dated June 16, 1998.

Issued in Fort Worth, Texas, on June 15,

2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–15797 Filed 6–22–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–SW–09–AD]

RIN 2120–AA64

Airworthiness Directives; Agusta

S.p.A. Model A109E Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: The FAA proposes the

adoption of a new airworthiness

directive (AD) for Agusta S.p.A. Model

A109E helicopters. The proposed AD

would require modifying the passenger

compartment sliding doors by installing

certain locking mechanism kits. The

proposed AD is prompted by accidental

opening of a passenger compartment

sliding door (door) inflight due to a door

locking mechanism that is too easy to

accidentally open. The actions specified

by the proposed AD are intended to

prevent accidental opening of a door in

flight and subsequent loss of objects that

could damage the rotor system.

DATES: Submit any comments on this

proposal by August 24, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2001–SW–

09–AD, 2601 Meacham Blvd., Room

33652 Federal Register / Vol. 66, No. 122 / Monday, June 25, 2001 / Proposed Rules

663, Forth Worth, Texas 76137. You

may also send comments electronically

to the Rules Docket at the following

address: 9-asw-adcomments@faa.gov.

Comments may be inspected at the

Office of the Regional Counsel between

9 a.m. and 3 p.m., Monday through

Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT:

Richard Monschke, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, Fort Worth,

Texas 76193–0110, telephone (817)

222–5116, fax (817) 222–5961.

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 will be

considered before taking action on the

proposed rule. The proposals contained

in this document 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 mailed

comments submitted in response to this

proposal must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2001–SW–

09–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. 2001–SW–09–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

Discussion

Ente Nazionale per l’Aviazione Civile

(ENAC), the airworthiness authority for

Italy, notified us that an unsafe

condition might exist on Agusta S.p.A.

Model A109E helicopters. ENAC

advises modifying the doors installed on

Agusta S.p.A. Model A109E helicopters

up to serial number (S/N) 11099

inclusive.

Agusta S.p.A. has issued Bolletino

Tecnico No. 109EP–16, dated December

21, 2000 (BT). This BT specifies

modifying the opening/closing

mechanism of the doors with the

double-action (pull and turn) system to

avoid accidental actuation of the

internal handles. ENAC classified this

BT as mandatory and issued AD No.

2001–019, dated January 5, 2001, to

ensure the continued airworthiness of

these helicopters in Italy.

This helicopter model is

manufactured in Italy and is type

certified for operation in the United

States under the provisions 14 CFR

21.29 and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

ENAC has kept the FAA informed of the

situation described above. The FAA has

examined the findings of ENAC,

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.

We have identified an unsafe

condition that is likely to exist or

develop on other Agusta S.p.A. Model

A109E helicopters of this same type

design registered in the United States.

Unintentional door opening could allow

items to be lost from the passenger

compartment, and subsequent impact

with the main or tail rotors. The

proposed AD would require modifying

the doors installed on Agusta S.p.A.

Model A109E helicopters up to an

including S/N 11099 by installing doorlocking mechanism kits, part number

109–0823–03–101 and –102, within 90

days. The actions would have to be

accomplished in accordance with the

BT described previously.

Regulatory Impact

We estimate that 11 helicopters of

U.S. registry would be affected by this

proposed AD and that it would take

approximately 8 work hours per

helicopter to modify the doors. The

average labor rate is $60 per work hour.

The manufacturer states in its ASB that

it will reimburse 8 work hours at $40

per work hour. The manufacturer also

states in its ASB that the parts will be

supplied to modify the locking

mechanism on the doors. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $1760.

The regulations proposed herein

would 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 proposal

would not have federalism implications

under Executive Order 13132.

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. You can get a copy

obtained by contacting the Docket at the

mailing address listed under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, under 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:

Agusta S.p.A: Docket No. 2001–SW–09–AD.

Applicability: Model A109E helicopters,

up to and including serial number 11099,

certificated in any category.

Note 1: 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 (b) of this AD.

Your 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 within 90 days,

unless accomplished previously.

Federal Register / Vol. 66, No. 122 / Monday, June 25, 2001 / Proposed Rules 33653

To prevent accidental opening of a

passenger compartment (door) during flight,

accomplish the following:

(a) Modify each passenger compartment

sliding door by installing locking mechanism

kits, part number (P/N) 109–0823–03–101

and –102, in accordance with the

Compliance Instruction of Agusta Bollettino

Tecnico No. 109EP–16, dated December 21,

2000 (BT).

(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, Regulations

Group, 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, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(c) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the helicopter to a location where

the requirements of this AD can be

accomplished.

Note 3: The subject of this AD is addressed

in Ente Nazionale per l’Aviazione Civile

(Italy) AD 2001–019, dated January 5, 2001.

Issued in Fort Worth, Texas, on June 12,

2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–15796 Filed 6–22–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–67–AD]

RIN 2120–AA64

Airworthiness Directives; Robinson

Helicopter Company Model R44

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes

adopting a new airworthiness directive

(AD) for Robinson Helicopter Company

(RHC) Model R44 helicopters. This

proposal would require establishing a

life limit of 2200 hours time-in-service

(TIS) for affected horizontal stabilizers.

This proposal is prompted by

engineering analysis, which indicates

that certain vertical-to-horizontal

stabilizer attach channels (channels)

will crack sooner than the original life

limit of the horizontal stabilizer. The

actions specified by the proposed AD

are intended to prevent a crack through

a channel, separation of the stabilizers,

and subsequent loss of directional

control of the helicopter.

DATES: The FAA must receive any

comments on this proposal by August

24, 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–

67–AD, Meacham Blvd., Room 663, Fort

Worth, Texas 76137. You may also send

comments electronically to the Rules

Docket at the following address: 9-aswadcomments@faa.gov. Comments may

be inspected at the Office of the

Regional Counsel between 9 a.m. and 3

p.m., Monday through Friday, except

Federal holidays.

FOR FURTHER INFORMATION CONTACT: Fred

Guerin, Aviation Safety Engineer, FAA,

Los Angeles Aircraft Certification

Office, Airframe Branch, 3960

Paramount Blvd., 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 will be

considered before taking action on the

proposed rule. The proposals contained

in this document 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 mailed

comments submitted in response to this

proposal must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2000–SW–

67–AD.’’ The postcard will be date

stamped and returned to the

commenter.

Discussion

This document proposes adopting a

new AD for RHC Model R44 helicopters

to require establishing a life limit of

2200 hours TIS for affected horizontal

stabilizers and removing, inspecting,

and replacing certain channels with

airworthy channels. This proposal is

prompted by engineering analysis

which indicates that a fatigue crack may

develop through the inboard attachment

hole for the nutplate, part number (P/N)

NAS697A4, on channels, P/N D283–1

and –2, sooner than the original life

limit of 4,000 hours TIS. This condition,

if not corrected, could result in a fatigue

crack on the channels, P/N D283–1 and

–2, that attach the vertical and

horizontal stabilizers, separation of the

vertical and horizontal stabilizers after

2200 hours TIS, and subsequent loss of

directional control of the helicopter.

The FAA has reviewed RHC Service

Bulletin No. SB–39, dated September

12, 2000 (SB), which specifies replacing

affected channels during overhaul at

2200 hours TIS. The FAA agrees that

channels, P/N D283, with nutplate, P/N

NAS697A4, are considered unairworthy

after 2200 hours TIS.

We have identified an unsafe

condition that is likely to exist or

develop on other RHC Model R44

helicopters of these same type designs.

The proposed AD would require the

following before 2200 hours TIS:

• Removing the vertical stabilizer to

inspect the nutplate on channels, P/N

D283–1 and –2.

• Replacing channels installed with

nutplate, P/N NAS697A4, with

channels, P/N D296–1 and –2.

This proposal would revise the

Limitations section of the maintenance

manual by establishing a life limit of

2200 hours TIS for stabilizer, P/N

CO44–1, with channels, P/N D283–1 or

–2, installed.

Regulatory Impact

We estimate that 3 helicopters of U.S.

registry would be affected by this

proposed AD and that it would take

approximately 1⁄2 work hour per

helicopter to inspect the horizontal

stabilizer and replace channels. The

average labor rate is $60 per work hour.

The manufacturer states in the SB that

there will be no charge for the parts.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $90.

The regulations proposed herein

would 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