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

Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations 68885

affected by this AD, that it will take

approximately 10 work hours per

helicopter to accomplish either

inspection, and that the average labor

rate is $60 per work hour. Required

parts, if a grip needs to be replaced, will

cost approximately $4,000 per grip

(there are two grips on each helicopter).

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $8,600,000, assuming

one inspection per helicopter and

replacement of both grips on each

helicopter.

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, 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 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. 2000–SW–

35–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, 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 39–5260 (51 FR

11300, April 2, 1986) and Amendment

39–5626 (52 FR 24135, June 29, 1987)

and by adding a new airworthiness

directive to read as follows:

2000–18–51 Bell Helicopter Textron, Inc.:

Amendment 39–11983. Docket No.

2000–SW–35–AD. Supersedes AD 86–

06–08, Amendment 39–5260, and AD

86–06–08 R1, Amendment 39–5626,

Docket No. 86–ASW–10.

Applicability: 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, with

main rotor blade 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, 47–120–

252–11, 74–120–252–11 and 74–120–135–5,

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

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 a main rotor blade

grip (grip), separation of a main rotor blade,

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Within 100 hours time-in-service (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 at

intervals not to exceed 200 hours TIS. If a

crack is detected, before further flight,

replace the cracked grip with an airworthy

grip.

(b) On or before 1200 hours TIS, replace

each grip with an airworthy grip. This AD

establishes a retirement life of 1200 hours

TIS for grips, P/N 47–120–135–2, 47–120–

135–3, 47–120–135–5, 47–120–252–1, 47–

120–252–7, 47–120–252–11, 74–120–252–11,

and 74–120–135–5.

(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, Rotorcraft

Certification Office, 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.

(d) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the helicopter to a location where

the requirements of this AD can be

accomplished.

(e) This amendment becomes effective on

November 30, 2000, to all persons except

those persons to whom it was made

immediately effective by Emergency AD

2000–18–51, issued August 31, 2000, which

contained the requirements of this

amendment.

Issued in Fort Worth, Texas, on November

2, 2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–29049 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–U