Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77783

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 the following new airworthiness

directive:

2000–25–04 Raytheon Aircraft Company

(Formerly Beech): Amendment 39–

12038. Docket 2000–NM–60–AD.

Applicability: Model MU–300, MU–300–

10, 400, 400A, and 400T series airplanes; as

listed in Raytheon Aircraft Service Bulletin

SB 32–3300, dated December 1999;

certificated in any category.

Note 1: This AD applies to each airplane

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

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 prevent an asymmetric braking

condition and a longer stopping distance due

to sudden loss of normal braking to the left

wheel, which could result in the airplane

overrunning the runway surface, accomplish

the following:

General Visual Inspection

(a) Within 200 flight hours after the

effective date of this AD, perform a one-time

general visual inspection to detect hydraulic

fluid leakage from the B-nut area, which

attaches a hydraulic tube to the anti-skid

valve assembly, in accordance with Raytheon

Aircraft Service Bulletin SB 32–3300, dated

December 1999.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

(1) If no leakage is found, prior to further

flight, install an additional support (i.e., new

nutplate, clamp, and screw) for the hydraulic

tube; in accordance with the service bulletin.

(2) If any leakage is found, prior to further

flight, replace the hydraulic tube with a new

or serviceable hydraulic tube, and install an

additional support (i.e., new nutplate, clamp,

and screw) for the hydraulic tube; in

accordance with the service bulletin.

Alternative Methods of Compliance

(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, Wichita

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permit

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Raytheon Aircraft Service Bulletin SB

32–3300, dated December 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

Raytheon Aircraft Company, Manager Service

Engineering, Beechjet/Premier Technical

Support Department, P.O. Box 85, Wichita,

Kansas 67201–0085. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Effective Date

(e) This amendment becomes effective on

January 17, 2001.

Issued in Renton, Washington, on

December 4, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–31316 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–384–AD; Amendment

39–12039; AD 2000–25–05]

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 a onetime inspection of the coupling hinge

and locking fastener of the Gamah

couplings of the fuel system tubing

located in the wing dry bay to detect

discrepancies, and follow-on corrective

actions. This amendment retains those

requirements and adds a requirement to

revise the applicability of the existing

AD to add certain airplanes. The actions

specified in this AD are intended to

prevent failure of the rivets of the

Gamah couplings and consequent

separation of a Gamah coupling, which

could result in fuel leakage and

consequent fire in or around the wing.

This action is intended to address the

unsafe condition.

DATES: Effective December 28, 2000.

The incorporation by reference of a

certain publication listed in the

regulations, was approved previously by

the Director of the Federal Register as of

October 3, 2000, (65 FR 56231,

September 18, 2000).

Comments for inclusion in the Rules

Docket must be received on or before

January 12, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

384–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

77784 Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations

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–384–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:

Linda M. Haynes, 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) 703–6091; fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: On

September 8, 2000, the FAA issued AD

2000–19–03, amendment 39–11904 (65

FR 56231, September 18, 2000),

applicable to certain EMBRAER Model

EMB–135 and EMB–145 series

airplanes, to require a one-time

inspection of the coupling hinge and

locking fastener of the Gamah couplings

of the fuel system tubing located in the

wing dry bay to detect discrepancies,

and follow-on corrective actions. The

actions required by that AD are

intended to prevent failure of the rivets

of the Gamah couplings and consequent

fire in or around the wing.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

manufacturer has advised the FAA that,

certain airplanes were inadvertently not

included in the effectivity of Embraer

Alert Service Bulletin S.B. 145–28–

A014, dated August 25, 2000 (the

appropriate service information for AD

2000–19–03). Consequently, those

additional airplanes are subject to the

identified unsafe condition specified in

this rule.

U.S. Type Certification of the Airplane

These airplane models are

manufactured in Brazil 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.

Explanation of Requirements of 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, this AD supersedes AD 2000–19–

03 to continue to require a one-time

inspection of the coupling hinge and

locking fastener of the Gamah couplings

of the fuel system tubing located in the

wing dry bay to detect discrepancies,

and follow-on corrective actions. This

AD also requires the addition of certain

airplanes to the applicability of this AD.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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 shall 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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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, both before

and after the closing date for comments,

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 comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–384–AD.’’

The postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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, 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:

Federal Register / Vol. 65, No. 240 / Wednesday, December 13, 2000 / Rules and Regulations 77785

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–11904 (65 FR

56231, September 18, 2000), and by

adding a new airworthiness directive

(AD), amendment 39–12039, to read as

follows:

2000–25–05 Empresa Brasileira de

Aeronautica S.A. (Embraer):

Amendment 39–12039. Docket 2000–

NM–384–AD. Supersedes AD 2000–19–

03, Amendment 39–11904.

Applicability: Model EMB–135 and EMB–

145 series airplanes, as listed in Embraer

Alert Service Bulletin S.B. 145–28–A014,

dated August 25, 2000, and serial numbers

145301 through 145312, inclusive;

certificated in any category.

Note 1: This AD applies to each airplane

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

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 (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 as indicated, unless

accomplished previously.

To prevent failure of the rivets attaching

the Gamah coupling hinge to the fuel system

tubing and consequent separation of the

coupling, which could result in fuel leakage

and consequent fire in or around the wing,

accomplish the following:

Continuing Requirements of AD 2000–19–

03—General Visual Inspection

(a) Perform a one-time general visual

inspection of the hinge and locking fastener

of the Gamah couplings of the fuel system

tubing located in the wing dry bay to detect

discrepancies (including coupling separation,

and loose rivets on the coupling hinge or

locking fastener attaching points), in

accordance with Embraer Alert Service

Bulletin S.B. 145–28–A014, dated August 25,

2000; at the times specified in paragraphs

(a)(1) and (a)(2) of this AD, as applicable. If

no discrepancies are detected, secure the

Gamah couplings with locking wire in

accordance with the alert service bulletin.

(1) For airplanes having serial numbers

145004 through 145103 inclusive; 145105

through 145121 inclusive; 145123 through

145139 inclusive; 145141 through 145153

inclusive; 145155 through 145176 inclusive:

Within 400 flight hours after October 3, 2000

(the effective date of AD 2000–19–03,

amendment 39–11904).

(2) For airplanes having serial numbers

145177 through 145189 inclusive; 145191

through 145230 inclusive; 145232 through

145251 inclusive; 145253 through 145255

inclusive; 145258 through 145262 inclusive;

145264 through 145293 inclusive; 145295,

145296, and 145298 through 145300

inclusive: Within 50 flight hours after

October 3, 2000.

Follow-On Corrective Actions

(b) If any discrepancies (including

coupling separation, and loose rivets on the

coupling hinge or locking fastener attaching

points) are detected after accomplishment of

the inspection required by paragraph (a) of

this AD: Before further flight, replace any

affected Gamah couplings and secure the

Gamah couplings with locking wire in

accordance with Embraer Alert Service

Bulletin S.B. 145–28–A014, dated August 25,

2000. Accomplishment of this paragraph

terminates the requirements of this AD.

New Requirements of This AD—General

Visual Inspection

(c) For airplanes having serial numbers

145301 through 145312, inclusive: Perform a

one-time general visual inspection of the

hinge and locking fastener of the Gamah

couplings of the fuel system tubing located

in the wing dry bay to detect discrepancies

(including coupling separation, and loose

rivets on the coupling hinge or locking

fastener attaching points), in accordance with

Embraer Alert Service Bulletin S.B. 145–28–

A014, dated August 25, 2000, within 50 flight

hours after the effective date of this AD.

(1) If no discrepancies are detected, secure

the Gamah couplings with locking wire in

accordance with the alert service bulletin.

(2) If any discrepancy is detected, before

further flight, accomplish the requirements of

paragraph (b) of this AD.

Alternative Methods of Compliance

(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, Atlanta

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(e) 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.

Incorporation by Reference

(f) The actions shall be done in accordance

with Embraer Alert Service Bulletin S.B.

145–28–A014, dated August 25, 2000. The

incorporation by reference of that document

was approved previously by the Director of

the Federal Register as of October 3, 2000 (65

FR 56231, September 18, 2000). Copies may

be obtained from Empresa Brasileira de

Aeronautica S.A. (EMBRAER), P.O. Box

343—CEP 12.225, Sao Jose dos Campos—SP,

Brazil. Copies may be inspected 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.

Effective Date

(g) This amendment becomes effective on

December 28, 2000.

Issued in Renton, Washington, on

December 5, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–31449 Filed 12–12–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–28–AD; Amendment

39–12042; AD 2000–15–52]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 204B,

205A, 205A–1, 205B, and 212

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting superseding Airworthiness

Directive (AD) 2000–15–52, which was

sent previously to all known U.S.

owners and operators of Bell Helicopter

Textron, Inc. Model (BHTI) Model 204B,

205A, 205A–1, 205B, and 212

helicopters by individual letters. This

AD reduces the retirement index

number (RIN) life limit for the main

rotor mast (mast); increases the RIN

factor for masts and main rotor

trunnions (trunnions); applies standard

RIN factors for all external load lifts;

and requires a one-time inspection of

the snap ring groove area of the mast.

This AD also establishes RIN factors for

masts and trunnions that have been

previously installed on military or

restricted category helicopters and

removes from service those masts that

have been previously installed with a

hub spring. This amendment is

prompted by an occurrence of a cracked

mast at a lower value than the

established RIN life limit. The actions

specified by this AD are intended to

preclude the occurrence of fatigue