Federal Register / Vol. 60, No. 58 / Monday, March 27, 1995 / Rules and Regulations 15667

radioactive waste in an electronic

recordkeeping system.

(1) The manifest information that

must be electronically stored is—

(i) That required in 10 CFR part 20,

appendix G, with the exception of

shipper and carrier telephone numbers

and shipper and consignee

certifications; and

(ii) That information required in

paragraph (f) of this section.

(2) As specified in facility license

conditions, the licensee shall report the

stored information, or subsets of this

information, on a computer-readable

medium.

Dated at Rockville, MD this 20th day of

March 1995.

For the Nuclear Regulatory Commission.

John C. Hoyle,

Secretary of the Commission.

[FR Doc. 95–7302 Filed 3–24–95; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93–CE–35–AD; Amendment 39–

9180; AD 93–15–02 R1]

Airworthiness Directives; Fairchild

Aircraft SA226 and SA227 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 93–15–02,

which requires the following on

Fairchild Aircraft SA226 and SA227

series airplanes that are equipped with

a certain Simmonds-Precision pitch trim

actuator: repetitively measuring the

freeplay of the pitch trim actuator and

repetitively inspecting the actuator for

rod slippage; immediately replacing any

actuator if certain freeplay limitations

are not met or rod slippage is evident;

and eventually replacing the actuator

regardless of the inspection results. This

action maintains these requirements,

but reduces the hours time-in-service

(TIS) before the initial inspection is

required, and shortens both the time

period between repetitive inspections

and the actuator replacement

compliance time (unless the

replacement actuator is new or if the nut

tube assemblies have been replaced

during overhaul). An in-flight incident

where the referenced actuator on one of

the affected airplanes failed after

accomplishment of the 5,000-hour

initial inspection (with satisfactory

results) prompted this action. The

actions specified by this AD are

intended to prevent the horizontal

stabilizer from going nose-down or

jamming because of pitch trim actuator

failure, which could result in loss of

control of the airplane.

DATES: Effective April 17, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 17,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

June 5, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket 93–CE–35–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD may be obtained from Field

Support Engineering, Fairchild Aircraft,

P.O. Box 790490, San Antonio, Texas

78279–0490; telephone (210) 824–9421;

facsimile (210) 820–8609. This

information may also be examined at

the FAA, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Werner Koch, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone (817) 222–5150;

facsimile (817) 222–5959.

SUPPLEMENTARY INFORMATION: AD 93–

15–02, Amendment 39–8648 (59 FR

40734, July 30, 1993), currently requires

the following on Fairchild Aircraft

SA226 and SA227 series airplanes that

are equipped with a SimmondsPrecision pitch trim actuator, part

number (P/N) DL5040M5: repetitively

measuring the freeplay of the pitch trim

actuator and repetitively inspecting the

actuator for rod slippage; and, if certain

freeplay limitations are not met or rod

slippage is evident, replacing any

actuator with a new actuator of the same

part number or with a part of improved

design, P/N 27–19008–01 or 27–19008–

02. The requirements of the AD will no

longer apply when an actuator of

improved design is installed.

Accomplishment of the freeplay

measurements and inspections is in

accordance with the instructions in

Fairchild Aircraft SA226 Series Service

Letter (SL) 226–SL–005, and Fairchild

Aircraft SA227 Series SL 227–SL–011,

both Issued: April 8, 1993, Revised:

April 28, 1993, as applicable.

Accomplishment of the pitch trim

actuator replacement is in accordance

with the applicable maintenance

manual.

AD 93–15–02 was issued based on

reports of two in-flight incidents where

the above-referenced pitch trim actuator

failed on Fairchild Aircraft SA226 and

SA227 series airplanes. In one case, the

horizontal stabilizer went full-nose

down, and in the other instance, the

horizontal stabilizer jammed.

Fortunately, the pilots were able to

safely land in both of these instances.

Upon removal and inspection of each of

these pitch trim actuators, fatigued

barrel nuts were found and the actuator

usage time was well over 5,000 hours

TIS.

Since AD 93–15–02 became effective,

the FAA received a report of an in-flight

incident where the referenced actuator

on one of the affected airplanes failed.

The airplane operator had accomplished

the 5,000-hour TIS initial inspection

(with satisfactory results), but had not

reached the 6,500-hour TIS mandatory

replacement threshold.

Fairchild Aircraft has revised SA226

Series SL 226–SL–005 and SA227 Series

SL 227–SL–011 to reflect the revised

compliance times and a change to the

inspection procedure. The revision date

of this service information is March 2,

1995.

After examining the circumstances

and reviewing all available information

related to the incident described above,

the FAA has determined that AD 93–

15–02 should be revised by (1) reducing

the number of hours TIS before the

initial inspection is required; and (2)

shortening both the time period between

repetitive inspections and the actuator

replacement compliance time, unless

the replacement actuator is new or if the

tube nut assemblies have been replaced

during overhaul.

Since an unsafe condition has been

identified that is likely to exist or

develop in other Fairchild Aircraft

SA226 and SA227 series airplanes of the

same type design that are equipped with

a Simmonds-Precision pitch trim

actuator, P/N DL5040M5, this AD

requires the same repetitive inspections

and actuator replacement as AD 93–15–

02, but revises the compliance times as

previously specified. The inspections

will be accomplished in accordance

with the instructions in Fairchild

Aircraft SA226 Series Service Letter

(SL) 226–SL–005, and Fairchild Aircraft

SA227 Series SL 227–SL–011, both

Issued: April 8, 1993, Revised: March 2,

1995, as applicable.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for public prior comment
15668 Federal Register / Vol. 60, No. 58 / Monday, March 27, 1995 / Rules and Regulations

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting immediate flight safety and,

thus, was not preceded by notice and

opportunity to 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

above. 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, both before

and after the closing date for comments,

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 comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 93–CE–35–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

and that it is not considered to be

significant under Executive Order

12866. It is impracticable for the agency

to follow the procedures of Executive

Order 12866 with respect to this rule

since the rule must be issued

immediately to correct an unsafe

condition in aircraft. 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

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.

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 Amendment 39–8648 (59 FR

40734, July 30, 1993), and by adding a

new airworthiness directive to read as

follows:

93–15–02 R1 Fairchild Aircraft:

Amendment 39–9180; Docket No. 93–

CE–35–AD. Revises AD 93–15–02,

Amendment 39–8648.

Applicability: All SA226 and SA227 series

airplanes (all models and serial numbers)

that are equipped with a SimmondsPrecision pitch trim actuator, part number (P/

N) DL5040M5, 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 (d) 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 aircraft from the

applicability of this AD.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent the horizontal stabilizer from

going nose down or jamming because of pitch

trim actuator failure, which could result in

loss of control of the airplane, accomplish the

following:

Note 2: The paragraph structure of this AD

is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are

designations of the Level 1 paragraph they

immediately follow.

(a) Upon accumulating 3,000 hours timein-service (TIS) on a Simmonds-Precision

pitch trim actuator, P/N DL5040M5, or

within the next 50 hours TIS accumulated on

this type pitch trim actuator after the

effective date of this AD, whichever occurs

later, unless already accomplished, and

thereafter at intervals not to exceed 250 hours

TIS until paragraph (b) is complied with,

accomplish the following:

Note 3: If hours TIS accumulated on the

pitch trim actuator are not maintained, then

hours TIS accumulated on the airplane may

be substituted.

(1) Measure the freeplay of the pitch trim

actuator and inspect the actuator for rod

slippage in accordance with the

INSTRUCTIONS section of Fairchild Aircraft

SA226 Series Service Letter (SL) 226–SL–

005, and Fairchild Aircraft SA227 Series SL

227–SL–011, both issued: April 8, 1993,

revised: March 2, 1995, as applicable.

(2) If certain freeplay limitations specified

in the service letters are not met or rod

slippage is evident, prior to further flight,

accomplish the replacement specified in

either paragraph (b)(1) or (b)(2) of this AD.

(b) Within 500 hours TIS after the

inspection specified in paragraph (a) of this

AD or upon accumulating 5,000 hours TIS on

a Simmonds-Precision pitch trim actuator, P/

N DL5040M5, whichever occurs later,

accomplish one of the following:

(1) Replace the pitch trim actuator with a

new part of the same design and part number

in accordance with the instructions in the

applicable maintenance manual. Reinspect as

specified in paragraph (a) of this AD at

intervals not to exceed 300 hours TIS, and

replace the actuator as specified in paragraph

(b) of this AD at intervals not to exceed 6,500

hours TIS.

(2) Replace the pitch trim actuator with an

overhauled, zero-timed part of the same

design and part number. Accomplish this

replacement in accordance with the

instructions in the applicable maintenance

manual, and reinspect and replace as

specified below (paragraphs (b)(2)(i) and

(b)(2)(ii) of this AD):

(i) If both nut tube assemblies, P/N

AA56142, were replaced with new

assemblies during overhaul, reinspect as

specified in paragraph (a) of this AD at

intervals not to exceed 300 hours TIS, and
Federal Register / Vol. 60, No. 58 / Monday, March 27, 1995 / Rules and Regulations 15669

replace the actuator as specified in paragraph

(b) of this AD at intervals not to exceed 6,500

hours TIS;

(ii) If both nut tube assemblies, P/N

AA56142, were not replaced with new

assemblies during overhaul, reinspect as

specified in paragraph (a) of this AD at

intervals not to exceed 250 hours TIS, and

replace the actuator as specified in paragraph

(b) of this AD at intervals not to exceed 5,000

hours TIS.

(3) Replace the pitch trim actuator with a

new part of improved design, P/N 27–19008–

01 or 27–19008–02, in accordance with the

instructions in the applicable maintenance

manual.

(i) This replacement eliminates the

repetitive inspection requirement of this AD.

(ii) This replacement may be accomplished

at any time to eliminate the inspection

requirement of this AD.

(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) 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, Airplane Certification Office

(ACO), FAA, 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150. The request shall

be forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Fort Worth ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(e) The inspections and modification

required by this AD shall be done in

accordance with Fairchild Aircraft SA226

Series Service Letter 226–SL–005, and

Fairchild Aircraft SA227 Series Service

Letter 227–SL–011, both Issued: April 8,

1993, Revised: March 2, 1995, as applicable.

This incorporation by reference is 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 Field

Support Engineering, Fairchild Aircraft, P.O.

Box 790490, San Antonio, Texas 78279–

0490. 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.

(f) This amendment (39–9180) becomes

effective on April 17, 1995.

Issued in Kansas City, Missouri, on March

17, 1995.

Dwight A. Young,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–7113 Filed 3–24–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 94–AGL–23]

Establishment of Class D Airspace;

Akron-Canton, OH

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule; correction.

SUMMARY: This action corrects an error

in the airspace designation of the

Akron-Canton, OH Class D airspace area

legal description published in a final

rule on February 23, 1995, (60 FR

10014) establishing Class D airspace for

Akron-Canton Regional Airport, Akron,

OH.

EFFECTIVE DATE: 0901 UTC, May 25,

1995.

FOR FURTHER INFORMATION CONTACT:

Nancy Cibic, Air Traffic Division,

System Management Branch, AGL–530,

Federal Aviation Administration, 2300

East Devon Avenue, Des Plaines, Illinois

60018, telephone (708) 294–7573.

SUPPLEMENTARY INFORMATION:

History

Federal Register Document 95–4439,

published on February 23, 1995 (60 FR

10014), established Class D airspace for

Akron-Canton Regional Airport, Akron,

Ohio. The Class D surface and radius

area indicated in the legal description

were published incorrectly. This action

corrects those errors.

Correction to Final Rule

Accordingly, pursuant to the

authority delegated to me, the airspace

designation for Akron, Ohio, Class D

airspace, as published in the Federal

Register on February 23, 1995, (60 FR

10014), (Federal Register Document 95–

4439, page 10014, column 2), is

corrected in the final rule to the

incorporation by reference 14 CFR 71.1

as follows:

§ 71.1 [Corrected]

Paragraph 5000 General

* * * * *

AGL OH D Akron-Canton, OH [Corrected]

(Lat. 40°54′59′′N., long. 81°26′32′′W.)

That airspace extending upward from the

surface to and including 5,200 feet MSL

within a 5-mile radius of the Akron-Canton

Regional Airport, OH. This Class D airspace

area is effective during the specific dates and

times established in advance by a Notice to

Airmen. The effective date and time will

thereafter be published in the Airport Facility

Directory.

* * * * *

Issued in Des Plaines, Illinois on March 16,

1995.

Roger Wall,

Manager, Air Traffic Division.

[FR Doc. 95–7498 Filed 3–24–95; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF COMMERCE

Bureau of Export Administration

15 CFR Part 777

[Docket No. 930653–4299]

RIN 0694–AA70

Exports of Certain California Crude Oil

AGENCY: Bureau of Export

Administration, Commerce.

ACTION: Final rule.

SUMMARY: The Bureau of Export

Administration (BXA) is amending the

short supply provisions of the Export

Administration Regulations (EAR) by

revising the restrictions on exports of

crude oil produced in the lower 48

states to allow exports, under individual

validated licenses, of up to 25,000

barrels per day (MB/D) of California

heavy crude oil having a gravity of 20.0

degrees API or lower.

This final rule revises the licensing

requirements and procedures that apply

to exports of California heavy crude oil

by removing a number of significant

restrictions, e.g., the prohibition against

transporting crude oil by pipeline over

rights-of-way granted pursuant to the

Mineral Leasing Act of 1920 and the

requirement that any export of crude oil

must be offset by importing an equal or

greater volume of crude oil of equal or

higher quality.

In order to minimize procedural

delays in licensing exports of California

heavy crude oil, BXA’s Office of

Chemical and Biological Controls and

Treaty Compliance (CBTC) will issue

licenses on a first-come, first-served,

basis. Based on comments received on

the March 24, 1994, proposed rule, this

rule allows CBTC to issue licenses

contingent upon the exporter

submitting, prior to any export under a

license, documentation showing that the

exporter has title to the oil (or a contract

to purchase the oil) and a contract to

export the oil. This change in

documentation requirements should

provide exporters with greater flexibility

in completing small cargo transactions

on the spot market. Such transactions

are likely to account for the bulk of

California heavy crude oil exports.

EFFECTIVE DATE: March 27, 1995.