12406 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

Percentage

Free

percentageReserve

Zante Currant ................... 40 60

Other Seedless ................. 40 60

Dated: March 1, 1995.

Sharon Bomer Lauritsen,

Deputy Director, Fruit and Vegetable Division.

[FR Doc. 95–5542 Filed 3–6–95; 8:45 am]

BILLING CODE 3410–02–W

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–CE–07–AD; Amendment 39–

9162; AD 95–04–10]

Airworthiness Directives; Beech

Aircraft Corporation Models 34C, T–

34C, and T–34C–1 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Beech Aircraft

Corporation (Beech) Models 34C, T–

34C, and T–34C–1 airplanes. This action

requires replacing the eight wing

attachment steel bolts and hardware

with Inconel bolts and hardware. A

report of the right lower aft wing

attachment nut assembly separating in

two pieces on a Model T–34C–1

airplane prompted this action. The

actions specified by this AD are

intended to prevent the wing from

separating from the fuselage because of

failure of this assembly.

DATES: Effective April 7, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 7,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

the Beech Aircraft Corporation, P.O. Box

85, Wichita, Kansas 67201–0085. 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.

Larry Engler, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4122; 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 Beech Models 34–C, T–34C, and

T–34C–1 airplanes was published in the

Federal Register on October 25, 1994

(59 FR 53613). The action proposed to

require replacing the eight wing

attachment steel bolts and hardware

with Inconel bolts and hardware.

Accomplishment of the proposed

replacements would be in accordance

with Beech Service Bulletin No. 2487,

dated August 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.

After careful review of all information

related to the subject discussed above,

the FAA has determined that air safety

and the public interest require the

adoption of the rule as proposed except

for minor editorial corrections. The FAA

has determined that these minor

corrections will not change the meaning

of the AD or add any additional burden

upon the public than was already

proposed.

The compliance time of this AD is

presented in calendar time instead of

hours time-in-service (TIS). The FAA

has determined that a calendar time

compliance is the most desirable

method because the unsafe condition

described by this AD is caused by stress

corrosion. Stress corrosion initiates as a

result of airplane operation, but can

continue to develop regardless of

whether the airplane is in service or in

storage. Therefore, to ensure that the

above-referenced condition is detected

and corrected on all airplanes within a

reasonable period of time without

inadvertently grounding any airplanes, a

compliance schedule based upon

calendar time instead of hours TIS is

required.

The FAA estimates that 494 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

8 workhours per airplane to accomplish

the required action, and that the average

labor rate is approximately $60 an hour.

Parts cost approximately $800 per

airplane. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $632,320.

This figure is based on the assumption

that no affected airplane owner/operator

has accomplished the required

replacement.

The Beech Aircraft Company has

informed the FAA that 89 wing

attachment assembly kits have been

sold. Assuming that each of these kits is

installed on an affected airplane, this

would reduce the cost impact of the

required AD upon U.S. operators of the

affected airplanes by $113,920 from

$632,320 to $518,400.

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

adding a new airworthiness directive to

read as follows:

95–04–10 Beech Aircraft Corporation:

Amendment 39–9162; Docket No. 94–

CE–07–AD.

Applicability: The following model and

serial number airplanes, certificated in any
Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12407

category, that have steel wing attachment

assembly bolts and hardware:

Model Serial numbers

34C ...... GP–1 through GP–50.

T–34C .. GL–2 through GL–353.

T–34C–

1.

GM–1 through GM–71 and GM–78

through GM–98.

Compliance: Within whichever of the

following occurs later, unless already

accomplished:

• Four years after airplane manufacture;

• Four years after installing a new wing

attachment assembly; or

• Within the next 30 calendar days after

the effective date of this AD.

To prevent the wing from separating

from the fuselage because of failure of

the wing attachment nut assembly,

accomplish the following:

(a) Replace all eight steel wing attach

bolts and hardware with Inconel bolts

and hardware in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section in Beech Service Bulletin No.

2487, dated August 19 1993.

Note 1: Replacing all eight steel wing

attach bolts and hardware with Inconel bolts

and hardware as required by this AD

eliminates the repetitive inspection

requirements of AD 85–22–05, Amendment

39–5146, for the affected airplanes.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(d) The replacements required by this AD

shall be done in accordance with Beech

Service Bulletin No. 2487, dated August

1993. 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 Beech Aircraft Corporation, P.O.

Box 85, Wichita, Kansas 67201–0085. 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.

(e) This amendment (39–9162) becomes

effective on April 7, 1995.

Issued in Kansas City, Missouri, on

February 14, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–4367 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–132–AD; Amendment

39–9156; AD 95–04–04]

Airworthiness Directives; British

Aerospace Model Avro 146–RJ70A and

–RJ85A Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model Avro 146–RJ70A and –RJ85A

series airplanes, that requires an

inspection to identify and remove

certain cable terminals on the auxiliary

power unit (APU) starter circuit and

installation of certain new cable

terminals. This amendment is prompted

by a report that, during an inspection of

the cable terminals on the APU starter

circuit, incorrect cable terminals were

found installed on these airplanes. The

actions specified by this AD are

intended to ensure the installation of

correct starter cable terminals in the

APU; incorrect cables could lead to the

inability of the pilot to start the APU

when needed in a situation of loss of

other electrical power sources.

DATES: Effective April 6, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 6,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Holdings, Inc.,

Avro International Aerospace Division,

P.O. Box 16039, Dulles International

Airport, Washington DC 20041–6039.

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 Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

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 British

Aerospace Model Avro 146–RJ70A and

–RJ85A series airplanes was published

in the Federal Register on November 7,

1994 (59 FR 55383). That action

proposed to require a detailed visual

inspection to identify the cable

terminals fitted to cables KA47 and

KA48 on the APU starter circuit at

terminal block KA9, removal of certain

cable terminals, and installation of

certain new cable terminals.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this requirement.

The FAA has recently reviewed the

figures it has used over the past several

years in calculating the economic

impact of AD activity. In order to

account for various inflationary costs in

the airline industry, the FAA has

determined that it is necessary to

increase the labor rate used in these

calculations from $55 per work hour to

$60 per work hour. The economic

impact information, below, has been

revised to reflect this increase in the

specified hourly labor rate.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.