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

Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34107

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

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.

None of the Eurocopter France Model

AS332L2 helicopters affected by this AD

are on the U.S. Register. All helicopters

included in the applicability of this AD

are currently operated by non-U.S.

operators under foreign registry;

therefore, they are not directly affected

by this AD action. However, the FAA

considers that this rule is necessary to

ensure that the unsafe condition is

addressed in the event that any of these

subject helicopters are imported and

placed on the U.S. Register in the future.

Should an affected helicopter be

imported and placed on the U.S.

Register in the future, it will require

approximately 1 work hour per

helicopter to inspect the sleeve, and

either 10 work hours per helicopter to

remove, inspect, and reinstall the

current damper attachment bolt and

bushing or 10 work hours to remove,

inspect, and install a replacement

damper attachment bolt and bushing or

the sleeve if the current parts are

damaged. The average labor rate is $60

per work hour. Required parts will cost

approximately $54,549 per blade

($54,305 for a sleeve and $244 for a

bolt). Based on these figures, the total

cost impact of the AD on U.S. operators

is estimated to be $55,209 for each

helicopter, assuming each imported

helicopter would require one new

sleeve and one new bolt and bushing.

The FAA has identified an unsafe

condition that is likely to exist or

develop on other Eurocopter France

Model AS332L2 helicopters of the same

type design, which may become

registered in the United States. This AD

is being issued to detect corrosion and

cracks in the sleeve, which could result

in separation of the blade damper

assembly and subsequent loss of control

of the helicopter. This AD requires, at

specified time intervals, visually

inspecting the sleeve for cracks,

corrosion, fretting, or bonding

separation; the bearing surface of the

bushing for fretting or cracks; and the

bolt for corrosion and deterioration of

the fluorimid varnish coating. Replacing

any cracked or non-airworthy sleeve,

bushing, or bolt would also be required

before further flight. The actions must

be accomplished in accordance with the

service bulletin described previously.

Since this AD action does not affect

any helicopter that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, notice

and public procedures hereon are

unnecessary, and the amendment may

be made effective in less than 30 days

after publication in the Federal

Register.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

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–

04–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 notice

and prior public comment are

unnecessary in promulgating this

regulation; therefore, it can be issued

immediately to correct an unsafe

condition in aircraft since none of these

model helicopters are registered in the

United States. The FAA has also

determined that this regulation 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, 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:

2001–12–16 Eurocopter France:

Amendment 39–12271. Docket No.

2001–SW–04–AD.

Applicability: Model AS332L2 helicopters,

with main rotor hub sleeve, part number (P/

N) 332A31–1860–03 or –04, and sleeve-todrag damper attachment bolt, P/N 332A31–

1961–20, 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

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 (c) of this AD.

The request should include an assessment of

34108 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

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 detect corrosion on a sleeve-to-blade

damper attachment bolt (bolt) or a crack on

the main rotor blade sleeve yoke (sleeve) and

to prevent failure of the damper attachment

and subsequent loss of control of the

helicopter, accomplish the following:

(a) For sleeves with 175 or less hours timein-service (TIS), before accumulating 275

hours TIS, and thereafter at intervals not to

exceed 275 hours TIS, remove the sleeve-toblade-damper assembly in accordance with

paragraph 2.B.2 of the Accomplishment

Instructions in Eurocopter Service Bulletin

No. 05.00.53, Revision 1, dated July 6, 1999

(SB), and inspect in accordance with

paragraphs 2.B.2.1, 2.B.2.2, and 2.B.2.3 of the

SB. Returning a sleeve to the manufacturer is

not required by this AD. Replace any

unairworthy part before further flight.

(b) For sleeves with more than 175 hours

TIS that have not complied with paragraph

(a) of this AD, before the first flight of each

day, visually inspect the sleeve for a crack in

accordance with paragraph 2.B.1 of the SB.

Replace any cracked sleeve with an

airworthy sleeve before further flight. Within

the next 100 hours TIS and thereafter at

intervals not to exceed 275 hours TIS,

remove the sleeve-to-blade-damper assembly

in accordance with paragraph 2.B.2 of the SB,

and inspect in accordance with paragraphs

2.B.2.1, 2.B.2.2, and 2.B.2.3 of the SB.

Returning a sleeve to the manufacturer is not

required by this AD. Replace any

unairworthy part before further flight.

(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, 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.

(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) Removing the sleeve-to-blade damper

assembly and inspecting the sleeve shall be

done in accordance with the

Accomplishment Instructions, paragraphs

2.B.1, 2.B.2, 2.B.2.1, 2.B.2.2, and 2.B.2.3, of

Eurocopter Mandatory Service bulletin No.

05.00.53, Revision 1, dated July 6, 1999. 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

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. 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.

(f) This amendment becomes effective on

July 12, 2001.

Note 3: The subject of this AD is addressed

in Direction Ge ́ne ́rale de L’Aviation Civile

(France) AD No. 1999–260–014(A) R1, dated

July 13, 1999.

Issued in Fort Worth, Texas, on June 8,

2001.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–15792 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–06–AD; Amendment

39–12282; AD 2001–13–02]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Canada Model 407

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Bell Helicopter Textron Canada (BHTC)

Model 407 helicopters that requires

replacing certain cockpit warning horns.

This amendment is prompted by reports

that pilots have had difficulty in

distinguishing between the FADEC Fail

horn, the Engine Out horn, and the Low

Rotor RPM horn. The actions specified

by this AD are intended to assist the

pilot in properly identifying a specific

cockpit warning horn (horn) and

prevent an inappropriate pilot response

to a horn, which could cause an engine

overspeed and subsequent

uncommanded reduction to flight-idle

engine power.

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

from Bell Helicopter Textron Canada,

12,800 Rue de l’Avenir, Mirabel, Quebec

JON1LO, telephone (800) 363–8023, fax

(450) 433–0272. 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:

Sharon Miles, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Regulations Group, Fort Worth, Texas

76193, telephone (817) 222–5122, 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)

for BHTC Model 407 helicopters was

published in the Federal Register on

March 14, 2001 (66 FR 14865). That

action proposed to require replacing the

FADEC Fail horn, the Engine Out horn,

and the Low Rotor RPM horn.

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 200

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 2.5 work hours per

helicopter to replace the horns, and that

the average labor rate is $60 per work

hour. Required parts will cost

approximately $154. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $60,800 to replace the

horns in all the fleet.

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