22496 Federal Register / Vol. 60, No. 88 / Monday, May 8, 1995 / Rules and Regulations

For purposes of Executive Order

12612, SBA certifies that this final rule

would not have Federalism implications

warranting the preparation of a

Federalism assessment.

For purposes of Executive Order

12778, SBA certifies that the final rule

is drafted, to the extent practicable, in

accordance with the standards set forth

in section 2 of that Order.

For purposes of the Regulatory

Flexibility Act, SBA certifies that this

final rule will not have a significant

economic effect on a substantial number

of small entities because, even though it

would render previously ineligible

applicants eligible for disaster loan

assistance, SBA does not expect the

number of affected applicants to be

significant.

For purposes of the Paperwork

Reduction Act, SBA certifies that this

final rule will not impose a new

recordkeeping or reporting requirement.

List of Subjects in 13 CFR Part 123

Disaster, Physical disaster and

economic injury loans.

Pursuant to the authority conferred in

section 5(b)(6) of the Small Business Act

(15 U.S.C. 634(b)(6)), SBA amends Part

123, Chapter I, Title 13, Code of Federal

Regulations, as follows:

PART 123—DISASTER—PHYSICAL

DISASTER AND ECONOMIC INJURY

LOANS

1. The authority citation for part 123

is revised to read as follows:

Authority: 15 U.S.C. 634(b)(6), 636(b), (c),

(f).

2. Section 123.2 is amended by

adding the following text at the end to

read as follows:

§ 123.2 Introduction.

* * * Under the Federal Debt

Collection Procedures Act of 1990 (28

U.S.C. 3201(e)), a debtor who owns

property which is subject to an

outstanding judgment lien for a debt

owed to the United States is not eligible

to receive certain assistance from the

Federal Government, including physical

and economic injury disaster loans

covered by this part. This restriction

against receiving disaster loans may be

waived by SBA’s Associate

Administrator for Disaster Assistance or

his/her designee (deciding official) upon

a demonstration of good cause by the

applicant for assistance. Good cause

may be demonstrated by a credible

representation under oath, which

convinces the deciding official that it is

more likely than not that the disaster for

which such assistance is requested

caused the delinquency upon which the

judgment is based, whether the debt was

incurred before or after the

commencement date for such disaster;

or such disaster prevented the debtor

from adhering to the terms of an

agreement to satisfy the judgment lien,

made with SBA or another agency in

whose favor the judgment was entered

or with any other Federal Government

entity as may be appropriate, provided

that such agency or entity certifies that,

prior to the commencement date for the

disaster, the debtor had been adhering

satisfactorily to the terms of its

agreement; or such other circumstances

exist as may demonstrate good cause

sufficient to waive the statutory

prohibition. Subject to the provisions of

§ 123.12 concerning requests for

reconsideration, a determination of the

Associate Administrator for Disaster

Assistance or his/her designee under

this section is a final, nonappealable

decision of the SBA.

Dated: March 14, 1995.

Philip Lader,

Administrator.

[FR Doc. 95–11155 Filed 5–5–95; 8:45 am]

BILLING CODE 8025–01–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–CE–06–AD; Amendment 39–

9217; AD 95–09–13]

Airworthiness Directives; Cessna

Aircraft Company Models T303, 402C,

404, 414A, and 421C Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

AD 93–05–03, which currently requires

repetitively inspecting each fuel inlet

float valve in accordance with certain

test procedures on Cessna Aircraft

Company (Cessna) Models T303, 402C,

404, 414A, and 421C airplanes, and

replacing any valve that does not pass

this test. The manufacturer has

developed fuel inlet float valves of

improved design, and the Federal

Aviation Administration (FAA) has

determined that the improved valves

should be installed to reduce the

number of repetitive tests currently

required by AD 93–05–03. This action

requires installing these fuel inlet float

valves of improved design. The actions

specified by this AD are intended to

prevent possible loss of engine power

caused by failure of a fuel inlet float

valve.

DATES: Effective June 14, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 14,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

the Cessna Aircraft Company, Customer

Services, P.O. Box 1521, Wichita,

Kansas 67201. This information may

also be examined at the FAA, Central

Region, Office of the Assistant Chief

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North

Capitol Street NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles D. Riddle, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Wichita, Kansas 67209; telephone (316)

946–4144; facsimile (316) 946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

certain Cessna Models T303, 401C, 404,

414A, and 421C airplanes was

published in the Federal Register on

September 19, 1994 (59 FR 47818). The

action proposed to require replacing the

fuel inlet float valves with parts of

improved design or modifying the

existing part and periodically

accomplishing functional tests to assure

proper operation. Accomplishment of

the proposed actions would be in

accordance with the

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin

(SB) MEB93–10, dated December 3,

1993.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

Since issuance of the proposal, the

manufacturer has revised Cessna SB

MEB93–10 to incorporate editorial

corrections and add serial number 689

to the Cessna Model 402C airplane

applicability list. Cessna has informed

the FAA that improved design fuel

valves have been incorporated on this

airplane at Cessna’s maintenance

facilities.

After careful review of all available

information, the FAA has determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections and the incorporation of the

service bulletin revision. The FAA has

determined that the minor editorial
Federal Register / Vol. 60, No. 88 / Monday, May 8, 1995 / Rules and Regulations 22497

corrections and the incorporation of the

revised service bulletin will not add any

additional burden upon the public than

was already proposed. The addition of

serial number 689 of the Cessna Model

402C airplane does not add any

additional burden upon the public

because the airplane operator already

has incorporated the actions specified

by this AD.

The replacement compliance time is

presented in calendar time instead of

hours time-in-service (TIS). Operators in

commuter service can put up to 200

hours TIS in one calendar month while

a general aviation operator may not

utilize the airplane 200 hours TIS in one

year. The calendar time compliance will

allow commuter operators the option of

accomplishing the actions to coincide

with regularly scheduled maintenance.

The FAA estimates that 1,642

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 22 workhours per

airplane to accomplish the required

action, and that the average labor rate is

approximately $60 an hour. Parts cost

approximately $3,144 per airplane.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $7,329,888. This figure

is based on the assumption that no

affected airplane owner/operator has

accomplished the required valve

installation.

Cessna has informed the FAA that

enough improved fuel valves have been

sold to equip approximately 1,041 of the

affected airplanes. Assuming that these

valves are installed on Cessna Models

T303, 402C, 404, 414A, and 421C

airplanes, the cost impact upon U.S.

operators would be reduced from

$7,329,888 to $2,682,864.

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing AD 93–05–03, Amendment

39–8508 (58 FR 13406, March 11, 1993),

and by adding a new airworthiness

directive to read as follows:

95–09–13 Cessna Aircraft Company:

Amendment 39–9217; Docket No. 94–

CE–06–AD. Supersedes AD 93–05–03,

Amendment 39–8508.

Applicability: The following model and

serial number airplanes, certificated in any

category:

Model Serial Nos.

T303 T30300001 through T30300315.

402C 402C0001 through 402C1020, and

689.

404 404–0001 through 404–0859.

414A 414A0001 through 414A1212.

421C 421C0001 through 421C1807.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent possible loss of engine power

caused by failure of a fuel inlet float valve,

accomplish the following:

(a) For airplanes equipped with fuel inlet

float valve part numbers (P/N) 9910242–1,

9910242–4, 9910242–5, 9910242–6,

9910242–7, 9910242–8, 9910242–205,

9910242–206, 9910242–207, and 9910242–

208, accomplish the following:

(1) Within the next 200 hours time-inservice (TIS) after the effective date of this

AD, unless already accomplished

(compliance with AD 93–05–03), perform the

appropriate valve test in accordance with

paragraph 2. Functional Test Procedure or

paragraph 3. Installation Test Procedure in

the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. Accomplish these tests thereafter at

intervals not to exceed 200 hours TIS until

the fuel inlet float valves are replaced with

a P/N 9910242–11 or P/N 9910242–12 valve,

and then accomplish the appropriate valve

test at intervals not to exceed 600 hours TIS.

(2) Within 12 calendar months after

accumulating 1,800 hours TIS on a fuel inlet

float valve or within the next 12 calendar

months after the effective date of this AD,

whichever occurs later, replace the valve

with a P/N 9910242–11 or P/N 9910242–12

fuel inlet float valve in accordance with

paragraph 4. Valve Replacement in the

Cessna MEB93–10R1 ACCOMPLISHMENT

INSTRUCTIONS supplement to Cessna

Service Bulletin (SB) MEB93–10, Revision 1,

Original Issue: December 3, 1993; Revision 1:

March 31, 1995. Thereafter, accomplish

either the functional or installation test

required by paragraph (a)(1) of this AD at

intervals not to exceed 600 hours.

Note 1: If the number of hours TIS

accumulated on a fuel inlet float valve is

unknown, airplane hours TIS may be used.

(b) For airplanes equipped with fuel inlet

float valve, P/N 9910242–9 or P/N 9910242–

10, accomplish the following:

(1) Within the next 200 hours TIS after the

effective date of this AD, unless already

accomplished (compliance with AD 93–05–

03), perform the appropriate valve test in

accordance with paragraph 2. Functional

Test Procedure or paragraph 3. Installation

Test Procedure in the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. Accomplish the appropriate valve test

thereafter at intervals not to exceed 200 hours

TIS until the fuel inlet float valves are

modified as specified in paragraph (b)(2) of

this AD, and then accomplish the appropriate

valve test at intervals not to exceed 600 hours

TIS.

(2) Within 12 calendar months after the

effective date of this AD, install the K74D

retainer kit in accordance with PROCEDURE

No. P74D, which is included with the Cessna

MEB93–10R1 ACCOMPLISHMENT

INSTRUCTIONS supplement to Cessna

Service Bulletin (SB) MEB93–10, Revision 1,

Original Issue: December 3, 1993; Revision 1:

March 31, 1995. Thereafter, accomplish the

functional and installation tests required by

paragraph (b)(1) of this AD at intervals not to

exceed 600 hours.

Note 2: Installation of the K74D retainer kit

modifies the P/N 9910242–9 or P/N

9910242–10 fuel inlet float valves to the P/

N 9910242–11 or P/N 9910242–12

configuration.

(c) For valves failing any repetitive

installation or functional test required by

paragraph (a)(1), (a)(2), (b)(1), and (b)(2) of

this AD, prior to further flight, accomplish

the following (unless parts are not available

and then comply with the requirements of

paragraph (d) of this AD):

(1) Replace the fuel inlet float valve with

a P/N 9910242–11 or P/N 9910242–12 valve

in accordance with paragraph 4. Valve
22498 Federal Register / Vol. 60, No. 88 / Monday, May 8, 1995 / Rules and Regulations

Replacement in the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995.

(2) Accomplish the installation test

contained in paragraph 3. Installation Test

Procedure in the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. Accomplish the appropriate valve test

thereafter at intervals not to exceed 600 hours

TIS.

(d) If any fuel valve replacement is

necessary and the replacement parts are not

available, accomplish the following provided

the parts have been ordered from the

manufacturer and are installed within 25

hours TIS after availability:

(1) Incorporate the following into the

Limitations Section of the Pilots Operating

Handbook (POH) and FAA-approved

Airplane Flight Manual (AFM):

(i) For the Model T303 airplanes: Unusable

Fuel: Indicated fuel quantity below 36

pounds (6 gallons) in each main tank is

unusable.

(ii) For the Models 402C, 404, 414A, and

421C airplanes: Unusable Fuel: Indicated fuel

quantity below 90 pounds (15 gallons) in

each main tank is unusable.

(iii) For the Model 404 airplanes: Fuel

Quantity: Minimum indicated fuel quantity

for takeoff is 228 pounds (38 gallons) in each

main tank.

(iv) For the Models 402C, 414A, and 421C

airplanes: Fuel Quantity: Minimum indicated

fuel quantity for takeoff is 210 pounds (35

gallons) in each main tank.

(2) Fabricate placards, as applicable, with

the following words in letters at least 0.10-

inch in height and install these placards

within the pilot’s clear view on the

instrument panel in close proximity to the

fuel quantity gage:

(i) For Models 402C, 404, 414A, and 421C

airplanes: ‘‘UNUSABLE FUEL—INDICATED

FUEL QUANTITY BELOW 90 POUNDS (15

GALLONS) IN EACH MAIN TANK IS

UNUSABLE’’.

(ii) For Model T303 airplanes:

‘‘UNUSABLE FUEL—INDICATED FUEL

QUANTITY BELOW 36 POUNDS (6

GALLONS) IN EACH MAIN TANK IS

UNUSABLE’’.

(3) For the Model 404 airplanes, fabricate

four placards with the following in letters at

least 0.10- inch in height: ‘‘157 GAL’’. Install

these placards covering the four existing

‘‘172 GAL’’ markings on the existing placard

around the engine fuel selector handles.

(4) For the Models 402C, 414A, and 421C

airplanes, fabricate four placards with the

following in letters at least 0.10-inch in

height: ‘‘88 GAL’’. Install these placards

covering the four existing ‘‘103 GAL’’

markings on the existing placard around the

engine fuel selector handles.

(5) For the Model T303 airplanes, fabricate

the following placards in letters at least 0.10-

inch in height:

(i) ‘‘423 LBS’’ (2 placards). Install these

placards covering the two existing ‘‘459 LBS’’

markings on the existing placard around the

engine fuel selector handles.

(ii) ‘‘363 LBS’’ (1 placard). Install this

placard covering the existing ‘‘399 LBS’’

marking on the existing placard around the

engine fuel selector handles.

(6) For all affected Model airplanes,

fabricate a placard with the following words

in letters at least 0.10-inch in height and

install this placard within the pilot’s clear

view on the instrument panel: ‘‘ROLLING,

TURNING TAKEOFFS ARE PROHIBITED.’’

Note 3: The placard requirements may

already be accomplished in accordance with

either superseded AD 92–27–20 or AD 93–

05–03 (superseded by this action). These

placard requirements are eliminated upon

installation of the improved fuel valves as

required by this AD.

Note 4: The repetitive functional or

installation test is not required if parts are

not available and the requirements of

paragraph (d) of this AD (including all

subparagraphs) are complied with.

(e) Special flight permits may be issued in

accordance with §§ 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.

(f) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Manager, Wichita ACO, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas 67209. The request

shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(g) The installation, replacement, and tests

required by this AD shall be done in

accordance with the Cessna MEB93–10R1

ACCOMPLISHMENT INSTRUCTIONS

supplement to Cessna Service Bulletin (SB)

MEB93–10, Revision 1, Original Issue:

December 3, 1993; Revision 1: March 31,

1995. 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 the Cessna Aircraft Company, P.O. Box

7704, Wichita, Kansas 67277. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(h) This amendment (39–9217) supersedes

AD 93–05–03, Amendment 39–8508.

(i) This amendment (39–9217) becomes

effective on June 14, 1995.

Issued in Kansas City, Missouri, on April

26, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–10833 Filed 5–5–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–17–AD; Amendment 39–

9215; AD 95–09–11]

Airworthiness Directives; SchemppHirth Cirrus and Cirrus VTC Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Schempp-Hirth Cirrus and

Cirrus VTC sailplanes. This action

requires modifying the airbrake

actuating lever and replacing the

airbrake system coupling balls. Reports

of the coupling balls on the airbrake

actuating lever breaking at the threaded

end on several of the affected sailplanes

prompted this action. The actions

specified by this AD are intended to

prevent airbrake system failure caused

by the above condition, which, if not

detected and corrected, could result in

sailplane controllability problems.

DATES: Effective June 9, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 9,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Schempp-Hirth Flugzeubau GmbH,

Krebenstr. 25, D–7312 Kirchheim/Teck,

Germany. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Mr.

Herman C. Belderok, Project Officer,

Sailplanes, Small Airplane Directorate,

Airplane Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri 64106; telephone (816) 426–

6932; facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

Schempp-Hirth Cirrus and Cirrus VTC

sailplanes was published in the Federal

Register on December 20, 1994 (59 FR

65520). The action proposed modifying

the airbrake actuating lever and

replacing the airbrake system coupling

balls. Accomplishment of the proposed

actions would be in accordance with

Schempp-Hirth Technical Note 265–10,

dated November 5, 1992.

Interested persons have been afforded

an opportunity to participate in the