68882 Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations

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 the following new airworthiness

directive:

2000–23–09 Empresa Brasileira de

Aeronautica S.A. (EMBRAER):

Amendment 39–11979. Docket 2000–

NM–133–AD.

Applicability: Model EMB–120 series

airplanes, certificated in any category, having

serial numbers listed in EMBRAER Service

Bulletin 120–29–0047, Change 01, dated

October 22, 1996.

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 (c) 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 rupture of the hydraulic line

and loss of hydraulic pressure due to chafing,

which could result in reduced controllability

of the airplane, accomplish the following:

Inspection and Corrective Actions

(a) Within 75 flight hours after the effective

date of this AD, perform a general visual

inspection to detect discrepancies (wear,

chafing, or scores) of all hydraulic pump

hoses installed in both nacelles, in

accordance with Part I of EMBRAER Service

Bulletin 120–29–0047, Change 01, dated

October 22, 1996. Prior to further flight,

perform all applicable corrective actions in

accordance with the service bulletin.

Note 2: Accomplishment, prior to the

effective date of this AD, of the inspection in

accordance with Part I of EMBRAER Service

Bulletin 120–29–0047, dated August 22,

1996, is acceptable for compliance with the

requirements of paragraph (a) of this AD.

Note 3: 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.’’

Clip Relocation

(b) Within 75 flight hours after the effective

date of this AD, relocate the clip that secures

the left forward hold-open rod of both

nacelles in accordance with Part II of

EMBRAER Service Bulletin 120–29–0047,

Change 01, dated October 22, 1996.

Alternative Methods of Compliance

(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, 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 4: 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

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with EMBRAER Service Bulletin 120–29–

0047, Change 01, dated October 22, 1996.

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 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.

Note 5: The subject of this AD is addressed

in Brazilian airworthiness directive 96–12–

01, dated December 13, 1996.

(f) This amendment becomes effective on

December 20, 2000.

Issued in Renton, Washington, on

November 6, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28964 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–293–AD; Amendment

39–11973; AD 2000–23–03]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Fokker Model F.28

Mark 1000, 2000, 3000, and 4000 series

airplanes, that requires a one-time

general visual inspection for proper

rigging of the liftdumper micro switches

installed in the left- and right-hand

sides of the pedestal; a functional check

of the micro switches; and re-rigging the

cam, if necessary. The actions specified

by this AD are intended to detect and

correct improper rigging of the

liftdumper micro switches, which could

result in inadvertent extension of the

liftdumpers during takeoff roll. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

20, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., P.O. Box

231, 2150 AE Nieuw-Vennep, the

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

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

Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations 68883

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Fokker Model

F.28 Mark 1000, 2000, 3000, and 4000

series airplanes was published in the

Federal Register on September 19, 2000

(65 FR 56509). That action proposed to

require a one-time general visual

inspection for proper rigging of the

liftdumper micro switches installed in

the left- and right-hand sides of the

pedestal; a functional check of the micro

switches; and re-rigging the cam, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 23 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 4

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $5,520, or $240 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.

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 the following new airworthiness

directive:

2000–23–03 Fokker Services B.V.:

Amendment 39–11973. Docket 2000–

NM–293–AD.

Applicability: All Model F.28 Mark 1000,

2000, 3000, and 4000 series airplanes,

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 detect and correct improper rigging of

the liftdumper micro switches, which could

result in inadvertent extension of the

liftdumpers during takeoff roll, accomplish

the following:

Inspection and Functional Check

(a) Within 2 months after the effective date

of this AD: Perform a one-time general visual

inspection for proper rigging of the

liftdumper micro switches installed in the

left- and right-hand sides of the pedestal; and

a functional check of the micro switches; as

specified in Fokker Service Bulletin F28/27–

186, including Manual Change Notification

MCNM F28–020, dated May 8, 2000. Perform

the inspection and the check in accordance

with the Accomplishment Instructions of the

service bulletin. If the micro switches are not

rigged within the specifications provided in

the service bulletin, prior to further flight, rerig the cam in accordance with the service

bulletin.

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.’’

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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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 Fokker Service Bulletin F28/27–186,

including Manual Change Notification

MCNM F28–020, dated May 8, 2000. 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 Fokker

Services B.V., P.O. Box 231, 2150 AE NieuwVennep, the Netherlands. Copies may be

inspected at the FAA, Transport Airplane

68884 Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in Dutch airworthiness directive 2000–073,

dated May 31, 2000.

Effective Date

(e) This amendment becomes effective on

December 20, 2000.

Issued in Renton, Washington, on

November 6, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28962 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–35–AD; Amendment

39–11983; AD 2000–18–51]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 47B,

47B–3, 47D, 47D–1, 47G, 47G–2,

47G2A, 47G–2A–1, 47G–3, 47G–3B,

47G–3B–1, 47G–3B–2, 47G–3B–2A,

47G–4, 47G–4A, 47G–5, 47G–5A, 47H–

1, 47J, 47J–2, 47J–2A, and 47K

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) 2000–18–51 which was

sent previously to all known U.S.

owners and operators of Bell Helicopter

Textron, Inc. (BHTI) Model 47B, 47B–3,

47D, 47D–1, 47G, 47G–2, 47G2A, 47G–

2A–1, 47G–3, 47G–3B, 47G–3B–1, 47G–

3B–2, 47G–3B–2A, 47G–4, 47G–4A,

47G–5, 47G–5A, 47H–1, 47J, 47J–2, 47J–

2A, and 47K helicopters by individual

letters. This AD requires recurring

liquid penetrant or eddy current

inspections of the main rotor blade grip

(grip) threads for a crack. If a crack is

detected, this AD requires, before

further flight, replacing the cracked grip

with an airworthy grip. This AD also

establishes a retirement life of 1,200

hours time-in-service (TIS) for each grip.

This amendment is prompted by the

results of an investigation of an August

1998 accident in which a grip failed on

a BHTI Model 47G–2 helicopter due to

a fatigue crack. An analysis of the field

service data revealed fatigue cracks in

70 percent of the grips inspected. The

actions specified by this AD are

intended to prevent failure of a grip,

loss of a main rotor blade, and

subsequent loss of control of the

helicopter.

DATES: Effective November 30, 2000, to

all persons except those persons to

whom it was made immediately

effective by Emergency AD 2000–18–51,

issued on August 31, 2000, which

contained the requirements of this

amendment.

Comments for inclusion in the Rules

Docket must be received on or before

January 16, 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–

35–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.

FOR FURTHER INFORMATION CONTACT:

Marc Belhumeur, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Certification Office, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5177, fax (817) 222–5783.

SUPPLEMENTARY INFORMATION: The FAA

issued AD 86–06–08R1 on May 12, 1987

(52 FR 24135, June 29, 1987), which

amended AD 86–06–08 (51 FR 11300,

April 2, 1986). Those AD’s required an

initial and repetitive fluorescent dye

penetrant inspection of each grip. On

August 31, 2000, the FAA issued

Emergency AD 2000–18–51, for BHTI

Model 47B, 47B–3, 47D, 47D–1, 47G,

47G–2, 47G2A, 47G–2A–1, 47G–3, 47G–

3B, 47G–3B–1, 47G–3B–2, 47G–3B–2A,

47G–4, 47G–4A, 47G–5, 47G–5A, 47H–

1, 47J, 47J–2, 47J–2A, and 47K

helicopters. That emergency AD

supersedes AD 86–06–08 and AD 86–

06–08R1 and requires recurring liquid

penetrant or eddy current inspections of

the grip threads for a crack. If a crack

is detected, the AD requires, before

further flight, replacing the cracked grip

with an airworthy grip. The AD also

establishes a retirement life of 1,200

hours TIS for each grip. That action was

prompted by the results of an

investigation of an August 1998

accident in which a grip failed on a

BHTI Model 47G–2 helicopter due to a

fatigue crack. An analysis of Australian

field service data revealed fatigue cracks

in the majority of the grips inspected.

Since issuance of Emergency AD 2000–

18–51, other cracked grips with less

than 1200 hours TIS have been

discovered. This condition, if not

corrected, could result in failure of a

grip, loss of a main rotor blade, and

subsequent loss of control of the

helicopter.

Since the unsafe condition described

is likely to exist or develop on other

BHTI Model 47B, 47B–3, 47D, 47D–1,

47G, 47G–2, 47G2A, 47G–2A–1, 47G–3,

47G–3B, 47G–3B–1, 47G–3B–2, 47G–

3B–2A, 47G–4, 47G–4A, 47G–5, 47G–

5A, 47H–1, 47J, 47J–2, 47J–2A, and 47K

helicopters of the same type designs, the

FAA issued Emergency AD 2000–18–51

to prevent failure of a grip, loss of a

main rotor blade, and subsequent loss of

control of the helicopter. The AD

requires the following for grips, part

number (P/N) 47–120–135–2, 47–120–

135–3, 47–120–135–5, 47–120–252–1,

47–120–252–7, and 47–120–252–11,

and for grips manufactured under Parts

Manufacturer Approval, P/N 74–120–

252–11 and 74–120–135–5:

• Within 100 hours TIS since initial

installation on any helicopter or within

10 hours TIS for grips with 100 or more

hours TIS, conduct a liquid penetrant or

eddy current inspection of the grip

threads for a crack.

• Thereafter, conduct the liquid

penetrant or eddy current inspection of

the grip threads at intervals not to

exceed 200 hours TIS.

• If a crack is detected, before further

flight, replace the cracked grip with an

airworthy grip.

• Establish a retirement life of 1200

hours time-in-service (TIS) for each grip.

The short compliance time involved is

required because the previously

described critical unsafe condition can

adversely affect the structural integrity

and controllability of the helicopter.

Therefore, the above actions are

required at the specified time intervals,

and this AD must be issued

immediately.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

letters issued on 2000–18–51 to all

known U.S. owners and operators of

BHTI Model 47B, 47B–3, 47D, 47D–1,

47G, 47G–2, 47G2A, 47G–2A–1, 47G–3,

47G–3B, 47G–3B–1, 47G–3B–2, 47G–

3B–2A, 47G–4, 47G–4A, 47G–5, 47G–

5A, 47H–1, 47J, 47J–2, 47J–2A, and 47K

helicopters. These conditions still exist,

and the AD is hereby published in the

Federal Register as an amendment to

section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

The FAA estimates that 1000

helicopters of U.S. registry will be