59780 Federal Register / Vol. 62, No. 214 / Wednesday, November 5, 1997 / Rules and Regulations

September 30, 1997 (62 FR 51007). The

final rule amends the regulations

relating to loan underwriting in

response to comments received from the

FCA Board’s initiative to reduce

regulatory burden and in an effort to

streamline the regulations and set clear

minimum regulatory standards where

appropriate. In accordance with 12

U.S.C. 2252, the effective date of the

final rule is 30 days from the date of

publication in the Federal Register

during which either or both Houses of

Congress are in session. Based on the

records of the sessions of Congress, the

effective date of the regulations is

November 5, 1997.

EFFECTIVE DATE: The regulation

amending 12 CFR parts 614 and 619

published on September 30, 1997 (62 FR

51007) is effective November 5, 1997.

FOR FURTHER INFORMATION CONTACT:

John J. Hays, Policy Analyst, Policy

Development and Risk Control, Farm

Credit Administration, McLean, VA

22102–5090, (703) 883–4498;

or

Joy E. Strickland, Senior Attorney,

Office of General Counsel, Farm

Credit Administration, McLean, VA

22102-5090, (703) 883–4020, TDD

(703) 883–4444.

(12 U.S.C. 2252(a)(9) and (10))

Dated: October 31, 1997.

Floyd Fithian,

Secretary, Farm Credit Administration Board.

[FR Doc. 97–29272 Filed 11–4–97; 8:45 am]

BILLING CODE 6705–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–23–AD; Amendment

39–10195; AD 97–23–07]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GmbH Model MBB–BK

117 A–1, A–3, A–4, B–1, B–2 and C–1

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter Deutschland

GmbH (Eurocopter) Model MBB–BK 117

A–1, A–3, A–4, B–1, B–2, and C–1

helicopters, that establishes a new

retirement life for the clutch and

requires an entry into the Accessory

Replacement Record indicating the new

life limit. This amendment is prompted

by a recalculation of life limitations by

the part manufacturer, Warner Electric.

The clutch manufacturer used the

airframe load spectrum to establish the

new life limit of 3,600 hours time-inservice (TIS). The actions specified by

this AD are intended to prevent failure

of the clutch, loss of power to the main

rotor and a subsequent forced landing of

the helicopter.

EFFECTIVE DATE: December 10, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Lance T. Gant, Aerospace Engineer,

FAA, Rotorcraft Standards Staff,

Rotorcraft Directorate, 2601 Meacham

Blvd., Fort Worth, Texas 76137;

telephone (817) 222–5114, 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)

that is applicable to Eurocopter

Deutschland GmbH (Eurocopter) Model

MBB-BK 117 A-1, A–3, A–4, B–1, B–2,

and C–1 helicopters was published in

the Federal Register on February 4,

1997 (62 FR 5186). That action proposed

to establish a new retirement life for the

clutch and to require an entry into the

Accessory Replacement Record

indicating the new life limit.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

The one commenter asked for a delay

in the issuance of this AD until Warner

Electric established a new retirement

life on the affected clutch. The

commenter indicated that an extended

retirement life would be prepared by the

clutch manufacturer by the end of May,

1997. To date, the FAA has received no

further information about an extension

to the retirement life of the clutch.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed except

for some non-substantive word changes,

insertion of Note 3 referencing the

Luftfahrt-Bundesamt (LBA) AD, and

correction of the part number in

paragraph (b). The FAA has determined

that these changes will neither increase

the economic burden on any operator

nor increase the scope of this AD.

The FAA estimates that 130

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 12 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $6,000 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $873,600.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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.

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

adding a new airworthiness directive to

read as follows:

AD 97–23–07 Eurocopter Deutschland

GmbH: Amendment 39–10195. Docket

No. 96–SW–23–AD.

Applicability: Model MBB–BK 117 A–1, A–

3, A–4, B–1, and B–2 helicopters, serial

numbers (S/N) 7001 through 7250, and

Model MBB–BK 117 C–1 helicopters, S/N

7500 through 7520, with clutch, part number

(P/N) 4639302044 or P/N CL42067–1,

installed, certificated in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability
Federal Register / Vol. 62, No. 214 / Wednesday, November 5, 1997 / Rules and Regulations 59781

provision, regardless of whether it has been

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 use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the clutch, loss of

power to the main rotor and a subsequent

forced landing of the helicopter, accomplish

the following:

(a) Within 30 hours time-in-service (TIS)

after the effective date of this AD, make an

entry into the Accessory Replacement Record

to reflect a new life limit of 3,600 hours TIS

for the clutch, P/N 4639302044 or P/N

CL42067–1.

(b) Remove the clutch, P/N 4639302044 or

P/N CL42067–1, from service on or before

reaching 3,600 hours TIS. This AD revises

the Airworthiness Limitations section of the

maintenance manual by establishing a new

retirement life for the clutch, P/N

4639302044 or P/N CL42067–1, of 3,600

hours TIS.

(c) Replacement of the clutch, P/N

4639302044 or P/N CL42067–1, with a

clutch, P/N 4639202011, constitutes a

terminating action for the requirements of

this AD.

(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, Rotorcraft

Standards Staff, 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 Standards Staff.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(f) This amendment becomes effective on

December 10, 1997.

Note 3: The subject of this AD is addressed

in Luftfahrt-Bundesamt (Germany) AD 95–

242, dated June 13, 1995.

Issued in Fort Worth, Texas, on October 30,

1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–29238 Filed 11–4–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–SW–05–AD; Amendment

39–10194; AD 97–23–06]

RIN 2120–AA64

Airworthiness Directives; Schweizer

Aircraft Corporation Model 269A, A–1,

B, and C, and TH–55A Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Schweizer Aircraft

Corporation Model 269A, A–1, B, and C,

and TH–55A helicopters, with a certain

main rotor transmission ring gear (ring

gear) installed, that requires inspections

of the ring gear teeth for surface

deterioration which includes pitting,

excessive wearing, cracking or

corrosion, and replacement of the ring

gear if such ring gear teeth surface

deterioration is found; and also requires

creating a main rotor transmission

component log card (log card), if none

is available, and making a notation on

the log card if a ring gear is changed.

This amendment is prompted by reports

of failures of the ring gear due to single

tooth distress as a result of improper

gear tooth spacing during the

manufacturing of the ring gear. The

actions specified by this AD are

intended to prevent failure of the ring

gear, loss of drive to the main rotor

gearbox, and a subsequent forced

landing.

DATES: Effective December 10, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

10, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Schweizer Aircraft Corporation,

P.O. Box 147, Elmira, NY 14902, ATTN:

Publications Dept. 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: Mr.

Raymond Reinhardt, Aerospace

Engineer, New York Aircraft

Certification Office, FAA, 10 Fifth

Street, 3rd Floor, Valley Stream, New

York 11581, telephone (516) 256–7532,

fax (516) 568–2716.

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 Schweizer Aircraft

Corporation Model 269A, A–1, B, and C,

and TH–55A helicopters was published

in the Federal Register on November 4,

1996 (61 FR 56640). That action

proposed to require inspections of the

ring gear teeth for pitting, wearing,

cracking or corrosion, and replacement

of the ring gear if such ring gear teeth

surface deterioration is found. The

proposed inspections would be

accomplished before further flight if

clicking, tapping, or other unusual

noises, or unusual vibration is detected

while operating the helicopter, or if

metal particles are found on the

magnetic drain plug during routine

maintenance; or, upon installation of

replacement transmissions with the

affected ring gear; and within the next

50 hours time-in-service (TIS) or at the

next annual inspection, whichever

occurs first. Thereafter, the notice

proposes repetitive inspections at

intervals not to exceed 50 hours TIS in

accordance with the manufacturer’s

service bulletin.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

The one commenter states that all ring

gears, P/N 269A5104–005, should not be

affected by the AD, but that only ring

gears, P/N 269A5104–005,

manufactured by Eastern Gear

Corporation (EGC) and ACR Industries

(ACR), should be affected. The same

commenter also states that the use of the

term ‘‘wearing’’ in the proposed AD

needs further amplification because all

gear teeth will exhibit wear after some

time in service. This wear is normally

very minor, but the inference of the

proposed AD could lead one to believe

that ANY wear is unacceptable. The

FAA concurs with both comments and

the requirements of this AD are changed

accordingly. The applicability

paragraph has been revised to specify

only those gears manufactured by EGS

and ACR. The word ‘‘excessive’’ has

been added before the word ‘‘wearing’’

since all gears will experience some

wear after some time in service. The

inspection for wear, including what

constitutes ‘‘excessive wear’’, is

contained in the Basic Helicopter

Maintenance Instructions, Section 10,

which is referenced in Schweizer