Federal Register / Vol. 60, No. 241 / Friday, December 15, 1995 / Rules and Regulations 64315

Issued in Washington, DC on December 8,

1995.

Christine A. Ervin,

Assistant Secretary, Energy Efficiency and

Renewable Energy.

10 CFR Part 440—Weatherization

Assistance Program for Low-Income

Persons

Under the authority of 42 U.S.C.

6861–6871 and 42 U.S.C. 7191, the

interim final rule amending 10 CFR Part

440, which was published on June 5,

1995 (60 FR 29469), is adopted as a final

rule without change.

[FR Doc. 95–30591 Filed 12–14–95; 8:45 am]

BILLING CODE 6450–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM–112; Special Conditions

No. 25–ANM–108]]

Special Conditions: Gulfstream

Aerospace Corporation, Model

Gulfstream V, High Altitude Operations

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final special conditions;

correction.

SUMMARY: In the October 17, 1995, issue

of the Federal Register, the Federal

Aviation Administration (FAA)

published final special conditions No.

25–ANM–108 for the Gulfstream

Aerospace Corporation, Model

Gulfstream V airplane (High Altitude

Operations). The special conditions as

published contain two errors; an

incorrect paragraph reference, and a

mistype made by the Federal Register.

This document corrects those errors.

EFFECTIVE DATE: November 16, 1995.

FOR FURTHER INFORMATION CONTACT:

Gerald Lakin, FAA, Standardization

Branch, ANM–113, Transport Airplane

Directorate, Aircraft Certification

Service, 1601 Lind Avenue SW.,

Renton, Washington 98055–4056,

telephone (206) 227–1187.

Adoption of the Correction

Special Conditions No 25–ANM–108,

published in the Federal Register on

October 17, 1995 (60 FR 53691) is

corrected as follows:

On page 53691, column 3, under

‘‘Novel or Unusual Design Features,’’

paragraph 4, second sentence, remove

‘‘grown’’ and substitute ‘‘growth’’ in its

place.

On page 53693, column 3, under ‘‘4

Pressurization,’’ subparagraph (c),

remove the reference to ‘‘paragraphs d.1.

and d.2.’’ and substitute ‘‘paragraph 4(a)

and 4(b)’’ in its place.

Issued in Renton, Washington, on

December 6, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service,

ANM–100.

[FR Doc. 95–30552 Filed 12–14–95; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 39

[Docket No. 95–NM–75–AD; Amendment

39–9450; AD 95–25–05]

Airworthiness Directives; Beech Model

400A Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Beech Model 400A

airplanes, that requires an inspection to

verify if the securing rivet is installed on

the rod end of the control push rods of

the spoiler flight control system, an

inspection to verify if the jam nut is

secure on the opposite end of the rod

end, and repair of any discrepancy. This

amendment is prompted by a report of

loss of roll control on the co-pilot’s

control wheel shortly after takeoff due

to a rivet missing from the control push

rod. The actions specified by this AD

are intended to ensure that the push rod

rivets are installed. Missing control

push rod rivets could result in the

disengagement of the push rod end from

the push rod tube; this could lead to

loss of roll control and subsequent

reduced controllability of the airplane

after takeoff.

DATES: Effective January 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 16,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Beech Aircraft Corporation,

Commercial Service Department, P.O.

Box 85, Wichita, Kansas 67201–0085.

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 FAA,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Larry Engler, Aerospace Engineer,

Airframe Branch, ACE–118W, FAA,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4122; fax (316)

946–4407.

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 certain Beech

Model 400A airplanes was published in

the Federal Register on August 10, 1995

(60 FR 40782). That action proposed to

require a one-time detailed visual

inspection to verify if the securing rivet

is installed on the push rods of the

spoiler flight control system. That action

also proposed to require an inspection

to verify if the jam nut is secure on the

opposite rod end, and repair of any

discrepancy.

No comments were submitted in

response to the proposal or the FAA’s

determination of the cost to the public.

The FAA has determined that air safety

and the public interest require the

adoption of the rule as proposed.

There are approximately 96 Model

400A airplanes of the affected design in

the worldwide fleet. The FAA estimates

that 73 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 8 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

$35,040, or $480 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 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
64316 Federal Register / Vol. 60, No. 241 / Friday, December 15, 1995 / Rules and Regulations

‘‘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), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–25–05 Beech Aircraft Corporation:

Amendment 39–9450. Docket 95–NM–

75–AD.

Applicability: Model 400A airplanes, serial

numbers RK–1 through RK–96 inclusive,

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 use the authority

provided in paragraph (b) of this AD 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 airplane from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent reduced controllability of the

airplane after takeoff, accomplish the

following:

(a) Within 50 hours time-in-service after

the effective date of this AD, perform a

detailed visual inspection to verify if the

securing rivet is installed on the control push

rods of the spoiler flight control system, and

an inspection to verify if the jam nut is

secure on the opposite rod end, in

accordance with Beechcraft Safety

Communique 400A–113, dated March 1995.

If any discrepancy is found, prior to further

flight, repair in accordance with a method

approved by the Manager, Wichita Aircraft

Certification Office (ACO), FAA, Small

Airplane Directorate.

(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, Wichita

ACO, FAA, Small 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, Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(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.

(d) The inspections shall be done in

accordance with Beechcraft Safety

Communique 400A–113, dated March 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 Beech Aircraft Corporation, Commercial

Service Department, P.O. Box 85, Wichita,

Kansas 67201–0085. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, Small Airplane

Directorate, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas; or at

the Office of the Federal Register , 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

January 16, 1996.

Issued in Renton, Washington, on

November 30, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–30533 Filed 12–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–76–AD; Amendment

39–9451; AD 95–25–06]

Airworthiness Directives; Beech Model

400, 400A, and 400T (Military T–1A)

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Beech Model 400,

400A, and 400T (military T–1A)

airplanes, that requires modification of

the standby instrument lighting system.

This amendment is prompted by a

report that, due to the design of the

standby instrument lighting system, the

lighting for the standby instruments

dimmed to an unacceptable level when

the main electrical power was turned

off. The actions specified by this AD are

intended to ensure that the standby

instrument lighting system adequately

illuminates the standby instrument, if

normal electrical power is lost or is

turned off as a result of fire or smoke in

the cockpit.

DATES: Effective January 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 16,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Beech Aircraft Corporation,

Commercial Service Department, P.O.

Box 85, Wichita, Kansas 67201–0085.

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 FAA,

Wichita Aircraft Certification Office,

Small Airplane Directorate, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Harvey Nero, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft

Certification Office, Small Airplane

Directorate, 1801 Airport Road, Room

100, Mid-Continent Airport, Wichita,

Kansas 67209; telephone (316) 946–

4137; fax (316) 946–4407.

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 certain Beech

Model 400, 400A, and 400T (military T–

1A) airplanes was published in the

Federal Register on August 28, 1995 (60

FR 44450). That action proposed to

require modification of the standby

instrument lighting system.

No comments were submitted in

response to the proposal or the FAA’s

determination of the cost to the public.

The FAA has determined that air safety

and the public interest require the

adoption of the rule as proposed.