34104 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available in the Rules

Docket for examination by interested

persons. A report that summarizes each

FAA-public contact concerned with the

substance of this AD will be filed in the

Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their mailed

comments submitted in response to this

rule must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2001–SW–

08–AD.’’ The postcard will be date

stamped and returned to the

commenter.

The regulations adopted herein will

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 final rule does not

have federalism implications under

Executive Order 13132.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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, under 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. FAA amends § 39.13 by adding the

following new airworthiness directive:

2001–13–04 Eurocopter France:

Amendment 39–12284. Docket No.

2001–SW–08–AD.

Applicability: Model EC 155B helicopters,

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 (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 before each flight

(takeoff and landing) with an open cabin

sliding door, unless accomplished

previously.

To prevent in-flight loss of a cabin sliding

door, impact with the main rotor or

fenestron, and subsequent loss of control of

the helicopter, accomplish the following:

(a) Visually check each cabin sliding door

in the open position to ensure that each roller

is in its rail. If any roller is outside its rail,

before further flight, replace the roller inside

the rail.

Note 2: Maintenance Manual Task 52–12–

00–061 pertains to the subject of this AD.

(b) An owner/operator (pilot) may perform

the visual check required by this AD and

must record compliance with the visual

check required by paragraph (a) of this AD

in accordance with 14 CFR 43.11 and

91.417(a)(2)(v)). This AD allows a pilot to

perform this check because it involves only

a visual check of each cabin sliding door to

detect any roller outside its rail and can be

performed equally well by a pilot or a

mechanic.

(c) This AD revises the Limitations section

of the Rotorcraft Flight Manual (RFM) by

either inserting statements prohibiting the

opening and closing of a cabin sliding door

in flight and requiring, before each flight

with an open cabin sliding door, visually

checking the open door to ensure each door

roller is inside its rail, or by inserting a copy

of this AD into the Limitations section of the

RFM.

(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, 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, Rotorcraft Directorate.

(e) A special flight permit is prohibited.

(f) This amendment becomes effective on

July 23, 2001.

Note 3: The subject of this AD is addressed

in Direction Ge ́ne ́rale De L’Aviation Civile

(France) AD No. T2001–058–001(A), dated

February 9, 2001.

Issued Fort Worth, Texas, on June 12, 2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–16045 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–48–AD; Amendment

39–12281; AD 2001–13–01]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 205A–1,

205B, 212, 412, 412EP, and 412CF

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), for

Bell Helicopter Textron, Inc. (BHTI)

Model 205A–1, 205B, 212, 412, 412EP,

and 412CF helicopters. This AD

requires removing each existing tail

rotor counterweight bellcrank

(bellcrank) retention nut (retention nut),

replacing each retention nut with a zero

hours time-in-service (TIS) retention

nut; and follow-up inspections of

installed retention nuts. This AD is

prompted by an in-flight loss of a

bellcrank due to failure of the retention

nut. The actions specified by this AD

are intended to prevent failure of the

retention nut, which could result in the

bellcrank migrating off the crosshead

spindle, loss of tail rotor control, and

subsequent loss of control of the

helicopter.

DATES: Effective August 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34105

from Bell Helicopter Textron, Inc., P.O.

Box 482, Fort Worth, Texas 76101,

telephone (817) 280–3391, fax (817)

280–6466. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

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:

Michael Kohner, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Certification Office, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5447, fax (817) 222–5783.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD for BHTI Model 205A–

1, 205B, 212, 412, 412EP, and 412CF

helicopters was published in the

Federal Register on March 8, 2001 (66

FR 13858). That action proposed to

require the following:

• Removing the two existing retention

nuts within 100 hours TIS or 90 days,

whichever occurs first;

• Installing a retention nut, part

number MS14145L6 or MS17826–6,

which is limited to a one-time

installation;

• Inspecting the corrosion preventive

compound (CPC) coating of the

retention nut for deficiencies;

• Inspecting the retention nut for

corrosion, mechanical damage, a crack,

or looseness; and

• Replacing each retention nut, when

necessary.

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.

The FAA estimates that 423

helicopters of U.S. registry will be

affected by this AD. It will take

approximately 2.5 work hours per

helicopter to replace each retention nut

and 0.5 work hour to inspect each

retention nut once. The average labor

rate is $60 per work hour. Required

parts will cost approximately $7 per

helicopter. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $155,241 to

replace the retention nuts and inspect

them once.

The regulations adopted herein will

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 final rule does not

have federalism implications under

Executive Order 13132.

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 a new airworthiness directive to

read as follows:

2001–13–01 Bell Helicopter Textron, Inc.:

Amendment 39–12281. Docket No.

2000–SW–48–AD.

Applicability: Model 205A–1, 205B, 212,

412, 412EP, and 412CF helicopters,

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 (f) 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 failure of the tail rotor

counterweight bellcrank (bellcrank) retention

nut, which could result in the bellcrank

migrating off the crosshead spindle, loss of

tail rotor control, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) For Model 205A–1 helicopters:

(1) Within 100 hours time-in-service (TIS)

or 90 days after the effective date of this AD,

whichever occurs first, remove the two

existing retention nuts retaining the

bellcranks, part number (P/N) 212–010–709–

001 or 212–011–705–001, and install zero

hours TIS retention nuts, P/N MS14145L6 or

MS17826–6, in accordance with paragraphs

(1) through (5) of the Accomplishment

Instructions in Bell Helicopter Textron, Inc.

Alert Service Bulletin (ASB) 205–00–77,

Revision A, September 13, 2000 (205A–1

ASB). A used nut may not be installed.

(2) At intervals not to exceed 100 hours TIS

after accomplishing paragraph (a)(1) of this

AD, inspect the retention nuts and corrosion

preventive compound (CPC) coating in

accordance with paragraph (6) of the

Accomplishment Instructions of the 205A–1

ASB. Reapply the CPC coating if deficiencies

are found in the coverage and protection of

the area. Replace any retention nut with any

corrosion, mechanical damage, a crack, or

looseness with an airworthy new retention

nut before further flight.

(b) For Model 205B helicopters:

(1) Within 100 hours TIS or 90 days after

the effective date of this AD, whichever

occurs first, remove the two existing

retention nuts retaining the bellcranks, P/N

212–011–705–001, and install retention nuts,

P/N MS14145L6 or MS17826–6, in

accordance with paragraphs (1) through (5) of

the Accomplishment Instructions in Bell

Helicopter Textron, Inc. ASB 205B–00–31,

Revision A, dated September 13, 2000 (205B

ASB). A used nut may not be installed.

(2) At intervals not to exceed 100 hours TIS

after accomplishing paragraph (b)(1) of this

AD, inspect the retention nuts and CPC

coating in accordance with paragraph (6) of

the Accomplishment Instructions in the 205B

ASB. Reapply the CPC coating if deficiencies

are found in the coverage and protection of

the area. Replace any retention nut with any

corrosion, mechanical damage, a crack, or

looseness with an airworthy new retention

nut before further flight.

(c) For Model 212 helicopters:

(1) Within 100 hours TIS or 90 days after

the effective date of this AD, whichever

occurs first, remove the two existing

retention nuts retaining the bellcranks, P/N

212–010–709–001 or 212–011–705–001, and

install retention nuts, P/N MS14145L6 or

MS17826–6, in accordance with paragraphs

(1) through (5) of the Accomplishment

Instructions in Bell Helicopter Textron, Inc.

Alert Service Bulletin 212–00–107, Revision

A, dated September 13, 2000 (212 ASB). A

used retention nut may not be installed.

(2) At intervals not to exceed 100 hours TIS

after accomplishing paragraph (c)(1) of this

AD, inspect the retention nuts and CPC

coating in accordance with paragraph (6) of

the Accomplishment Instructions in the 212

34106 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

ASB. Reapply the CPC coating if deficiencies

are found in the coverage and protection of

the area. Replace any retention nut with any

corrosion, mechanical damage, a crack, or

looseness with an airworthy new nut before

further flight.

(d) For Model 412 or 412EP helicopters:

(1) Within 100 hours TIS or 90 days after

the effective date of this AD, whichever

occurs first, remove the two existing

retention nuts retaining the bellcranks, P/N

212–011–705–001, and install retention nuts,

P/N MS14145L6 or MS17826–6, in

accordance with paragraphs (1) through (5) of

the Accomplishment Instructions in Bell

Helicopter Textron, Inc. ASB 412–00–102,

Revision A, dated September 13, 2000 (412

ASB). A used nut may not be installed.

(2) At intervals not to exceed 100 hours TIS

after accomplishing paragraph (d)(1) of this

AD, inspect the retention nuts and CPC

coating in accordance with paragraph (6) of

the Accomplishment Instructions in the 412

ASB. Reapply the CPC coating if deficiencies

are found in the coverage and protection of

the area. Replace any retention nut with any

corrosion, mechanical damage, a crack, or

looseness with an airworthy new retention

nut before further flight.

(e) For Model 412CF helicopters:

(1) Within 100 hours TIS or 90 days after

the effective date of this AD, whichever

occurs first, remove the two existing

retention nuts retaining the bellcranks, P/N

212–011–705–001, and install retention nuts,

P/N MS14145L6 or MS17826–6, in

accordance with paragraphs (1) through (5) of

the Accomplishment Instructions in Bell

Helicopter Textron, Inc. ASB 412CF–00–10,

Revision A, September 13, 2000 (412CF

ASB). A used nut may not be installed.

(2) At intervals not to exceed 100 hours TIS

after accomplishing paragraph (e)(1) of this

AD, inspect the retention nuts and CPC

coating in accordance with paragraph (6) of

the Accomplishment Instructions in the

412CF ASB. Reapply the CPC coating if

deficiencies are found in the coverage and

protection of the area. Replace any retention

nut with any corrosion, mechanical damage,

a crack, or looseness with an airworthy new

nut before further flight.

(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 modifications and inspections shall

be done in accordance with paragraphs (1)

through (6) of the Accomplishment

Instructions in the following Bell Helicopter

Textron, Inc. Alert Service Bulletins: No.

205–00–77, Revision A, dated September 13,

2000; No. 205B–00–31, Revision A, dated

September 13, 2000; No. 212–00–107,

Revision A, dated September 13, 2000; No.

412–00–102, Revision A, dated September

13, 2000; or No. 412CF–00–10, Revision A,

September 13, 2000, as applicable. 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, telephone (817) 280–

3391, fax (817) 280–6466. Copies may be

inspected at the FAA, Office of the Regional

Counsel, Southwest Region, 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

August 1, 2001.

Issued in Fort Worth, Texas, on June 13,

2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–15794 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–SW–04–AD; Amendment

39–12271; AD 2001–12–16]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model AS332L2 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Eurocopter France Model AS332L2

helicopters. This AD requires, at

specified time intervals, visually

inspecting the main rotor blade sleeve

yoke (sleeve) for cracks, corrosion,

fretting, or bonding separation; the

bearing surface of the metal bushing

(bushing) for fretting or cracks; and the

sleeve-to-damper attachment bolt (bolt)

for corrosion and deterioration of the

fluorimid varnish coating. Replacing

any cracked or nonairworthy sleeve,

bushing, or bolt is also required before

further flight. This AD is prompted by

the discovery of extensive deterioration

of the fluorimid varnish coating on the

bolt; cracks in the bushing; and fretting

and corrosion of the sleeve. The actions

specified in this AD are intended to

detect corrosion and cracks in the yoke,

which could result in separation of the

blade damper assembly and subsequent

loss of control of the helicopter.

DATES: Effective July 12, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 12,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

August 27, 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–

04–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

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

The service information referenced in

this AD may be obtained from American

Eurocopter Corporation, 2701 Forum

Drive, Grand Prairie, Texas 75053–4005,

telephone (972) 641–3460, fax (972)

641–3527. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

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: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5490, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: The

Direction Ge ́ne ́rale de L’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA

that an unsafe condition may exist on

Eurocopter France Model AS332L2

helicopters. The DGAC advises that

cracks in the yokes of the damper

attachment sleeves may result in loss of

the damper attachment and the

occurrence of vibrations, leading to loss

of control of the helicopter.

Eurocopter issued Eurocopter Service

Bulletin No. 05.00.53, Revision 1, dated

July 6, 1999, which specifies checking

the sleeve yoke for cracks and the

damper attachment for damage. The

DGAC classified this service bulletin as

mandatory and issued AD No. 1999–

260–014(A) R1, dated July 13, 1999, to

ensure the continued airworthiness of

these helicopters in France.

This helicopter model is

manufactured in France and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation