65102 Federal Register / Vol. 66, No. 243 / Tuesday, December 18, 2001 / Rules and Regulations

(b) Applicability. (1) Paragraph (a) of

this section shall apply only with

respect to any loan made, increased,

extended, or renewed after September

22, 1995.

(2) Paragraph (a) of this section shall

not apply to any loan having an original

outstanding balance of $5,000 or less

and a repayment term of one year or

less.

§ 1773.3 Civil money penalties.

(a) In general. If an Enterprise is

determined by the Director of OFHEO to

have engaged in a pattern or practice of

purchasing loans in violation of the

procedures established pursuant to the

NFIA, as amended, or to § 1773.2, the

Director may assess civil money

penalties against such Enterprise in

such amount or amounts as deemed to

be appropriate under paragraph (c) of

this section.

(b) Notice and hearing. A civil money

penalty under this section may be

assessed only after notice and an

opportunity for a hearing on the record

has been provided under 12 CFR part

1780.

(c) Amount. A civil money penalty

under this section may not exceed $385

for each violation. The total amount of

penalties assessed under this section

against an Enterprise during any

calendar year may not exceed $110,000.

(d) Deposit of penalties. Any penalties

collected under this section shall be

paid into the National Flood Mitigation

Fund in accordance with 42 U.S.C.

4104d.

(e) Additional penalties. Any penalty

under this section shall be in addition

to, and shall not preclude, any civil

remedy or criminal penalty otherwise

available.

(f) Statute of limitations. No civil

money penalty may be imposed under

this section after the expiration of the

four-year period beginning on the date

of the occurrence of the violation for

which the penalty is authorized under

this section.

Dated: December 13, 2001.

Armando Falcon, Jr.,

Director, Office of Federal Housing Enterprise

Oversight.

[FR Doc. 01–31166 Filed 12–17–01; 8:45 am]

BILLING CODE 4220–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–SW–18–AD; Amendment

39–12561; AD 2001–25–08]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Model S–70A and S–70C Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Sikorsky Model S–70A and S–70C

helicopters. This action requires certain

inspections of each main landing gear

drag beam (beam) for a crack and

removing any cracked beam before

further flight. This action also requires

reducing the torque of the jackpad

mounting bolt retention nut (nut) of

each beam. This amendment is

prompted by failure of a beam due to

stress corrosion resulting from sustained

tensile stress due partly to excessive

torque of the nut. The actions specified

in this AD are intended to prevent

excessive torque of the nut, failure of a

beam, and subsequent loss of control of

the helicopter during takeoff or landing.

DATES: Effective January 2, 2002.

Comments for inclusion in the Rules

Docket must be received on or before

February 19, 2002.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2001–SW–

18–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:

Terry Fahr, Aviation Safety Engineer,

Boston Aircraft Certification Office, 12

New England Executive Park,

Burlington, MA 01803, telephone (781)

238–7155, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD for

Sikorsky Model S–70A and S–70C

helicopters. This action requires certain

inspections of each beam for a crack and

removing any cracked beam before

further flight. This AD also requires

reducing the torque of the nut on each

beam. This amendment is prompted by

the failure of a beam due to stress

corrosion resulting from sustained

tensile stress due partly to excessive

torque on the nut.

The FAA has reviewed Sikorsky Alert

Service Bulletin No. 70–03–2, dated July

26, 1999 (ASB). The ASB describes

procedures for reducing the torque on

each nut to 45–50 ft-lbs to reduce stress

to the beam.

We have identified an unsafe

condition that is likely to exist or

develop on other Sikorsky Model S–70A

and S–70C helicopters of the same type

designs. Therefore, this AD is being

issued to prevent excessive torque on a

nut, failure of a beam, and subsequent

loss of control of the helicopter during

takeoff or landing. The short compliance

time involved is required because the

previously described critical unsafe

condition can adversely affect the

controllability and structural integrity of

the helicopter. Therefore, within 30

hours time-in-service, the following

actions are required for the beam, and

this AD must be issued immediately:

• Visually inspect each beam for a

crack.

• If a crack is found, remove the beam

before further flight.

• If a crack is suspected, dyepenetrant inspect the beam, and if a

crack is found, remove the beam before

further flight.

• If no crack is found, reduce the

torque on the nut.

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.

The FAA estimates that 3 helicopters

on the U.S. register will be affected by

this AD, that it will take approximately

2 work hours to inspect the beam and

to reduce the torque on each nut, and 2

work hours to replace a cracked beam.

The average labor rate is $60 per work

hour. Required parts will cost

approximately $18,600 per beam. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $56,520, assuming one beam has to

be replaced on each affected 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

Federal Register / Vol. 66, No. 243 / Tuesday, December 18, 2001 / Rules and Regulations 65103

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 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. 2001–SW–

18–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

adding a new airworthiness directive to

read as follows:

2001–25–08 Sikorsky Aircraft Corporation:

Amendment 39–12561. Docket No.

2001–SW–18–AD.

Applicability: Model S–70A helicopters,

serial numbers 700029, 701129, 701322,

701325, 701327, 701329, 701331, 701333,

701592, 701593,701594, 701595, 701613,

701614, 701825, 701835, 702127, and

702129, and Model S–70C helicopters, serial

numbers 70583, 70785, 70788, 70792, 70793,

70794, 70797, 70798, 70799, 70800, 70811,

70812, 70813, 70830, 70831, 70836, 70837,

70848, 70855, 70856, 70867, 70868, 70879,

70884, 70892, 70910, 70918, 70927, 70928,

70929, 70949, 70950, 70951, 70954, 70957,

70958, 70959, 70965, 70966, and 701029,

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 within 30 hours

time-in-service, unless accomplished

previously.

To prevent excessive torque on a jackpad

mounting bolt retention nut (nut), failure of

a main landing gear drag beam (beam), and

subsequent loss of control of the helicopter

during takeoff or landing, accomplish the

following:

(a) With jackpad installed, using a 10X or

higher magnifying glass, visually inspect

each beam, part number (P/N) 70250–32105,

for a crack at a 3.0-inch radius around the

upper and lower jackpad holes.

(1) If a crack is found, remove the beam.

(2) If a crack is suspected, dye-penetrant

inspect the beam, and if a crack is found,

remove the beam.

Note 2: Temporary Revision No. 19 of

Sikorsky Aircraft Model S–70 Maintenance

Manual, dated January 23, 2001, pertains to

the subject of this AD.

(b) If a crack is not found while

accomplishing the requirements of paragraph

(a) of this AD, retorque the nut, part number

(P/N) MS21245–L12, on each beam as

follows:

(1) Restrain the jackpad and rotate the nut

counterclockwise to release the torque on the

nut. If movement of the jackpad occurs,

remove and replace the sealant from the

lower surface of the jackpad/beam interface.

(2) Retorque the nut to 45–50 ft-lbs.

(3) Apply sealant to the nut and the

immediate area.

(4) After sealant has dried, touch up the

paint as required.

(5) After the paint has dried, apply a

slippage mark (of a contrasting color) to the

nut as follows:

(i) Wipe the area to be marked with a

clean-lint-free cloth.

(ii) Apply F1000 Sentry Seal, or equivalent,

with a width of approximately one half the

diameter of the nut (to a maximum width of

3⁄16 inch) and extending a minimum of 1⁄2

inch on the base part (or to the edge of the

part, whichever is smaller).

Note 3: Sikorsky Alert Service Bulletin No.

70–03–2, dated July 26, 1999, pertains to the

subject of this AD.

(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, Boston

Aircraft Certification Office, FAA. Operators

shall submit their requests through an FAA

Principal Inspector, who may concur or

comment and then send it to the Manager,

Boston Aircraft Certification Office.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

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

January 2, 2002.

Issued in Fort Worth, Texas, on December

11, 2001.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 01–31041 Filed 12–17–01; 8:45 am]

BILLING CODE 4910–13–U