Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations 66611

Issued in Renton, Washington, on October

30, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28233 Filed 11–6–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–01–AD; Amendment

39–11966; AD 2000–15–21 R1]

RIN 2120–AA64

Airworthiness Directives; 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; and Southwest Florida

Aviation SW204, SW204HP, SW205,

and SW205A–1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises an

existing airworthiness directive (AD)

that applies to Model HH–1K, TH–1F,

TH–1L, UH–1A, UH–1B, UH–1E, UH–

1F, UH–1H, UH–1L, and UH–1P; and

Southwest Florida Aviation SW204,

SW204HP, SW205, and SW205A–1

helicopters, manufactured by Bell

Helicopter Textron Inc. (BHTI) for the

Armed Forces of the United States, and

requires removing and replacing certain

main rotor mast (mast) assemblies. This

amendment corrects a part number that

was published incorrectly in the

existing AD. This amendment is

prompted by the discovery of that error.

The actions specified by this AD are

intended to prevent fatigue failure of the

mast and subsequent loss of control of

the helicopter.

EFFECTIVE DATE: November 22, 2000.

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: AD 2000–

15–21, Amendment 39–11854,

applicable to Model HH–1K, TH–1F,

TH–1L, UH–1A, UH–1B, UH–1E, UH–

1F, UH–1H, UH–1L, and UH–1P; and

Southwest Florida Aviation SW204,

SW204HP, SW205, and SW205A–1

helicopters, which were manufactured

by BHTI for the Armed Forces of the

United States, was published in the

Federal Register on August 9, 2000 (65

FR 48605). That AD requires removing

and replacing certain mast assemblies.

After that AD was issued, the FAA

discovered that the mast assembly part

numbers listed in the applicability

section are 205–011–450–001 and –005;

the correct mast assembly part numbers

are 204–011–450–001 and –005.

The FAA has determined that this

revision will neither increase the

economic burden on any operator nor

increase the scope of the AD, therefore,

no additional comments were solicited

and this AD is being issued with the

same requirements previously imposed

but with the correct part number.

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 FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas.

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

removing Amendment 39–11854 (65 FR

48605, August 9, 2000), and by adding

a new airworthiness directive to read as

follows:

2000–15–21 R1 Firefly Aviation Helicopter

Services (Previously Erickson Air Crane

Co.); Garlick Helicopters, Inc.; Hawkins

and Powers Aviation, Inc.; International

Helicopters, Inc.; Tamarack Helicopters,

Inc. (Previously Ranger Helicopter

Services, Inc.); Robinson Air Crane, Inc.;

Williams Helicopter Corporation

(Previously Scott Paper Co.); Smith

Helicopters; Southern Helicopter, Inc.;

Southwest Florida Aviation; Arrow

Falcon (Previously Utah State

University); Western International

Aviation, Inc.; and U.S. Helicopter, Inc.:

Amendment 39–11966. Docket No.

2000–SW–01–AD. Revises AD 2000–15–

21, Amendment 39–11854.

Applicability: Model HH–1K, TH–1F, TH–

1L, UH–1A, UH–1B, UH–1E, UH–1F, UH–1H,

UH–1L, and UH–1P; and Southwest Florida

Aviation SW204, SW204HP, SW205, and

SW205A–1 helicopters, manufactured by Bell

Helicopter Textron Inc. (BHTI) for the Armed

Forces of the United States, with a main rotor

mast (mast) assembly, part number (P/N)

204–011–450–001 or –005, 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 (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 within 25 hours

time-in-service, unless accomplished

previously.

To prevent fatigue failure of the mast and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Remove any mast assembly, P/N 204–

011–450–001 or –005, from service. Replace

it with an airworthy mast assembly. Neither

mast assembly, P/N 204–011–450–001 nor

204–011–450–005, is eligible for installation

on any affected helicopter.

(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) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

66612 Federal Register / Vol. 65, No. 216 / Tuesday, November 7, 2000 / Rules and Regulations

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.

(d) This amendment becomes effective on

November 22, 2000.

Issued in Fort Worth, Texas, on October 30,

2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–28437 Filed 11–7–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–204–AD; Amendment

39–11956; AD 2000–22–10]

RIN 2120–AA64

Airworthiness Directives; Empresa

Brasileira de Aeronautica S.A.

(EMBRAER) Model EMB–135 and

EMB–145 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain EMBRAER Model

EMB–135 and EMB–145 series

airplanes, that currently requires

various inspections to detect

discrepancies of the elevator servo tab

and spring tab hinge fittings of the

horizontal stabilizer, and follow-on

corrective actions, if necessary. This

amendment clarifies certain fiberscopic

inspection and replacement procedures,

and corrective actions; revises the

applicability of the existing AD; and

adds an inspection procedure for the

servo tab center hinge fittings to detect

the presence of washers for both

attaching fasteners, and follow-on

corrective actions, if necessary. This

amendment also provides for optional

terminating action for the repetitive

inspections. The actions specified in

this AD are intended to prevent the

linkage of the elevator servo tab or

spring tab hinge fittings from separating

from the horizontal stabilizer, which

could result in loss of control of the

airplane.

DATES: Effective November 22, 2000.

The incorporation by reference of

Embraer Service Bulletin 145–55–0024,

dated May 25, 2000, as listed in the

regulations, is approved by the Director

of the Federal Register as of November

22, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

December 7, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

204–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

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

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–204–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Empresa

Brasileira de Aeronautica S.A.

(EMBRAER), P.O. Box 343—CEP 12.225,

Sao Jose dos Campos—SP, Brazil. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Viswa Padmanabhan, Aerospace

Engineer, Airframe and Propulsion

Branch, ACE–117A, FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia 30337–2748;

telephone (770) 703–6049; fax (770)

703–6097.

SUPPLEMENTARY INFORMATION: On

February 15, 2000, the FAA issued AD

2000–04–09, amendment 39–11591 (65

FR 9217, February 24, 1000), applicable

to certain EMBRAER Model EMB–135

and EMB–145 series airplanes, to

require various inspections to detect

discrepancies of the elevator servo tab

and spring tab hinge fittings of the

horizontal stabilizer, and follow-on

corrective actions, if necessary. That

action was prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

required by that AD are intended to

prevent the linkage of the elevator servo

tab or spring tab hinge fittings from

separating from the horizontal stabilizer,

which could result in loss of control of

the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

Departmento de Aviacao Civil (DAC),

which is the airworthiness authority for

Brazil, has received new information

regarding the corrective action

necessary to address this unsafe

condition. As a result, the DAC has

issued the following Brazilian

airworthiness directives:

• 1999–09–01R2, dated May 1, 2000,

supersedes Brazilian airworthiness

directive 1999–09–01R1, dated October

25, 1999. This new revision was issued

to specify repetitive inspection intervals

and final rework of certain components.

Part III of this revision specifies that, for

certain Model EMB–135 and EMB–145

series airplanes, certain modifications of

the elevator mass balance assembly and

control column nose-up spring

modifications, in accordance with

Embraer Service Bulletin (S.B.) 145–27–

0034, must be completed before

accomplishment of the rework specified

in Part III of S.B. 145–55–0022, Change

01, dated January 25, 2000.

• 2000–05–01, dated May 25, 2000,

corrects any possible misinterpretation

of the replacement procedures included

in Brazilian airworthiness directive

1999–09–01R2, and in alert S.B. 145–

55–A022 and S.B. 145–55–0022.

Reports indicated that loose hinge

fittings were found, which was

attributed to the incorrect application of

the attachment fasteners to the tab

upper skin. It is considered that the loss

of fitting rigidity could cause damage to

the other fasteners in the tab spar.

Reports also indicated that some of the

fasteners (which attach the spring-tab

actuating arm to the tab upper skin and

the servo-tab actuating linkage hinge to

the tab lower skin) were not replaced

with fasteners having a washer, because

the collar conformation of those

fasteners was found to be correct. In

addition, maintenance records revealed

that such fasteners may not have been

replaced on certain airplanes. As a

result of these findings, the DAC issued

the previously referenced Brazilian

airworthiness directives to clarify that

all attachment fasteners must be

installed with a washer, and that the

fasteners must be replaced

independently of the installation

condition (even if the collar

conformation is found to be ‘‘correct’’).

FAA’s Conclusions

These airplane models are

manufactured in Brazil and are type

certificated for operation in the United

States under the provisions of section