Federal Register / Vol. 60, No. 12 / Thursday, January 19, 1995 / Rules and Regulations 3737

PART 32—SPECIFIC DOMESTIC

LICENSES TO MANUFACTURE OR

TRANSFER CERTAIN ITEMS

CONTAINING BYPRODUCT MATERIAL

1. The authority citation for 10 CFR

Part 32 continues to read as follows:

Authority: Secs. 81, 161, 182, 183, 68 Stat.

935, 948, 953, 954, as amended (42 U.S.C.

2111, 2201, 2232, 2233); sec. 201, 88 Stat.

1242, as amended (42 U.S.C. 5841).

2. In § 32.52, paragraph (a) is revised

to read as follows:

§ 32.52 Same: Material transfer reports

and records.

* * * * *

(a) Report to the Director of Nuclear

Material Safety and Safeguards, U.S.

Nuclear Regulatory Commission,

Washington, DC 20555–0001, all

transfers of such devices to persons for

use under the general license in § 31.5

of this chapter. Such reports must

identify each general licensee by name

and address, and individual by name

and/or position who may constitute a

point of contact between the

Commission and the general licensee,

the type of device transferred, and the

quantity and type of byproduct material

contained in the device. If one or more

intermediate persons will temporarily

possess the device at the intended place

of use prior to its possession by the user,

the report must include identification of

each intermediate person by name,

address, contact, and relationship to the

intended user. If no transfers have been

made to persons generally licensed

under § 31.5 of this chapter during the

reporting period, the report must so

indicate. The report must cover each

calendar quarter and must be filed

within 30 days thereafter.

* * * * *

3. Section 32.56 is revised to read as

follows:

§ 32.56 Same: Material transfer reports.

Each person licensed under § 32.53

shall file an annual report with the

Director of Nuclear Material Safety and

Safeguards, U.S. Nuclear Regulatory

Commission, Washington, D.C. 20555–

0001, which must state the total

quantity of tritium or promethium–147

transferred to persons generally licensed

under § 31.7 of this chapter. The report

must identify each general licensee by

name, state the kinds and numbers of

luminous devices transferred, and

specify the quantity of tritium or

promethium–147 in each kind of device.

Each report must cover the year ending

June 30 and must be filed within thirty

(30) days thereafter.

* * * * *

Dated at Rockville, Maryland, this 5th day

of January 1995.

For the Nuclear Regulatory Commission.

James M. Taylor,

Executive Director for Operations.

[FR Doc. 95–1270 Filed 1–18–95; 8:45 am]

BILLING CODE 7590–01–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–NM–235–AD; Amendment

39–9122; AD 94–22–10 R1]

Airworthiness Directives; De Havilland

Model DHC–8–100 and DHC–8–300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment revises an

existing airworthiness directive (AD),

applicable to certain De Havilland

Model DHC–8–100 and DHC–8–300

series airplanes, that currently requires

a revision to the Airplane Flight Manual

(AFM) to advise flight crew members

that certain cockpit indications may

reveal faulty anti-collision strobe light

units, and to provide procedures for

subsequent flight crew and maintenance

action. That AD also requires a

modification that eliminates the need

for the AFM revision. That AD was

prompted by reports that the function of

the proximity switch electronics unit

(PSEU) may be adversely affected

during operation of the white anticollision lights. The actions specified by

that AD are intended to ensure correct

operation of the PSEU and its associated

systems. This amendment revises the

applicability of the existing AD to add

one model of affected airplanes.

DATES: Effective February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

December 15, 1994 (59 FR 58765,

November 15, 1994).

Comments for inclusion in the Rules

Docket must be received on or before

March 20, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

235–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from De

Havilland, Inc., Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

Engine and Propeller Directorate, New

York Aircraft Certification Office, 181

South Franklin Avenue, Room 202,

Valley Stream, New York; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Michele Maurer, Aerospace Engineer,

Systems and Equipment Branch, ANE–

173, New York Aircraft Certification

Office, FAA, Engine and Propeller

Directorate, 181 South Franklin Avenue,

Room 202, Valley Stream, New York

11581; telephone (516) 791–6427; fax

(516) 791–9024.

SUPPLEMENTARY INFORMATION: On

October 26, 1994, the FAA issued AD

94–22–10, amendment 39–9060 (59 FR

58765, November 15, 1994), which is

applicable to certain De Havilland

Model DHC–8–100 and –300 series

airplanes. That action requires a

revision to the FAA-approved Airplane

Flight Manual (AFM) to advise the flight

crew that certain cockpit indications

may reveal faulty anti-collision strobe

light units, and to provide procedures

for subsequent flight crew and

maintenance action. It also requires the

installation of a modification that

eliminates the need for the AFM

revision.

That action was prompted by reports

indicating that the electrical power

supplies of the white anti-collision

lights may develop a fault that produces

greater than normal electrical emissions.

The cause of this fault has been

attributed to a capacitor failure in some

‘‘Grimes’’ strobe light systems. This

electromagnetic interference can

adversely affect the operation of the

proximity switch electronics unit

(PSEU) and its associated systems.

Incorrect operation of the PSEU and its

associated systems may interfere with or

distract the flight crew in carrying out

its regular duties during flight or on the

ground, and thus serve to compromise

the safe operation of the airplane. The

requirements of AD 94–22–10 are

intended to ensure the correct operation

of the PSEU and its associated systems.

The AFM revision that is required by

AD 94–22–01 is intended to advise the

flight crew of the fact that the electrical

power supplies for the white anticollision lights may fail and cause

various abnormal indications, such as:
3738 Federal Register / Vol. 60, No. 12 / Thursday, January 19, 1995 / Rules and Regulations

1. flashing of the landing gear green

locked down advisory lights during

cruise;

2. fluctuation of cabin pressurization

rate needle during cruise;

3. retraction and extension of roll and

ground spoilers during ground

operation;

4. loss of nose landing gear steering

subsequent to landing; and

5. loss of wheel brakes below 35–40

knots.

The AFM revision advises the flight

crew that, if any of these abnormal

indications are observed, they must

select the ‘‘A/COL light switch—RED,’’

and leave the switch in this position for

the remainder of the flight.

The flight crew and maintenance

procedures that are required by AD 94–

22–10 are described in De Havilland

Alert Service Bulletin S.B. A8–33–33,

dated May 31, 1993. These procedures

are intended to detect faulty power

supply units. The alert service bulletin

also describes procedures for

replacement of any faulty ‘‘Grimes’’ unit

with either a new or serviceable

‘‘Grimes’’ unit or a new ‘‘Whelan’’

system (Modification 8/1273).

The terminating modification that is

required by AD 94–22–10 is described

in De Havilland Service Bulletin S/B 8–

33–19, ‘‘Revision A’’, dated May 31,

1993. This modification (Modification

8/1273) entails replacing the existing

anti-collision strobe light system

(consisting of anti-collision strobe

lights, brackets, and power supplies) at

all three locations with a new, improved

‘‘Whelan’’ anti-collision strobe light

system. (The ‘‘Whelan’’ system includes

new dual strobes, new brackets, and

new power supplies.) This new system

is considered more durable than the

currently installed anti-collision strobe

light system. The ‘‘Whelan’’ system also

has a back-up strobe light at each

position.

Subsequent to the issuance of AD 94–

22–10, the FAA identified a

typographical error in the applicability

of the rule: The applicability statement

of the AD listed ‘‘de Havilland Model

DHC–8–302’’ as a series of airplanes that

is subject to the requirements of the

rule; however, that model should have

been listed as ‘‘de Havilland Model

DHC–8–301.’’ This airplane model is

manufactured in Canada and is type

certificated for operation in the United

States under the provisions of Section

21.29 of the Federal Aviation

Regulations and the applicable bilateral

airworthiness agreement.

Note: There is no ‘‘Model DHC–8–302’’

that is currently type certificated.

The FAA has determined that the

unsafe condition addressed by AD 94–

22–10 is likely to exist or develop in

Model DHC–8–301 series airplanes.

Therefore, AD 94–22–10 must be

revised to correctly add these airplanes

to its applicability, thereby making them

subject to its requirements.

There currently are no Model DHC–8–

301 series airplanes on the U.S. Register,

however. These airplanes are operated

currently by non-U.S. operators under

foreign registry; therefore, they are not

directly affected by this AD action.

However, the FAA considers that this

revision to the existing AD is necessary

to ensure that the unsafe condition is

addressed in the event that any of these

airplanes are imported and placed on

the U.S. Register in the future.

Should an affected Model DHC–8–301

series airplane be imported and placed

on the U.S. Register in the future, it

would require approximately 16 work

hours to accomplish the required

actions, at an average labor charge of

$60 per work hour. Required parts for

installation of Modification 8/1273 at all

three locations would cost

approximately $1,397 per airplane.

Based on these figures, the total cost

impact of this AD on an operator of a

Model DHC–8–301 series airplane

would be $2,357 per airplane.

(The current requirements of AD 94–24–

01 affect approximately 74 airplanes of

U.S. registry. Accomplishment of the

currently required actions take

approximately 16 work hours per

airplane, at an average labor rate of $60

per airplane. Required parts for

installation of Modification 8/1273 at all

three locations cost approximately

$1,397 per airplane. Based on these

figures, the total cost impact of the

current requirements of this rule on U.S.

operators is estimated to be $174,418, or

$2,357 per airplane.)

Since this revision action does not

affect any airplane that is currently on

the U.S. register, it has no adverse

economic impact and imposes no

additional burden on any person.

Therefore, notice and public procedures

hereon are unnecessary and the

amendment may be made effective in

less than 30 days after publication in the

Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified 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, 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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 94–NM–235–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.

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 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.
Federal Register / Vol. 60, No. 12 / Thursday, January 19, 1995 / Rules and Regulations 3739

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 39–9060 (59 FR

58765, November 15, 1994), and by

adding a new airworthiness directive

(AD), amendment 39–9122, to read as

follows:

94–22–10 R1 De Havilland: Amendment

39–9122. Docket 94–NM–235–AD.

Revises AD 94–22–10, Amendment 39–

9060.

Applicability: Model DHC–8–102, –103,

–301, and –311 series airplanes, having

serial numbers 003 through 214,

inclusive; on which Modification 8/1273

(as described in De Havilland Service

Bulletin S/B No. 8–33–19, Revision ‘A’,

dated May 31, 1993) has not been

accomplished; certificated in any

category.

Compliance: Required as indicated, unless

accomplished previously.

To ensure correct operation of the

proximity switch electronics unit (PSEU) and

its associated systems, accomplish the

following:

(a) Within the applicable time specified in

paragraph (a)(1) or (a)(2) of this AD, revise

the Limitations Section of the FAA–approved

Airplane Flight Manual (AFM) to include the

following statement. The revision of the AFM

may be accomplished by inserting a copy of

this AD into the AFM.

‘‘The electrical power supplies for the

white anti-collision lights may fail and cause

the following abnormalities:

—Flashing of the landing gear green locked

down advisory lights during cruise;

—Fluctuation of cabin pressurization rate

needle during cruise; and

—Retraction and extension of roll and

ground spoilers during ground operation.

The failure may also result in loss of nose

landing gear steering subsequent to landing,

and loss of wheel brakes below 35–40 knots.

If any of these abnormal indications are

observed, select A/COL light switch—RED.

Leave the switch in this position for the

remainder of the flight.’’

(1) For Model DHC–8–102, –103, and –311

series airplanes: Accomplish the revision of

the AFM within 30 days after December 15,

1994 (the effective date of AD 94–22–01,

amendment 39–9060),

(2) For Model DHC–8–301 series airplanes:

Accomplish the revision of the AFM within

30 days after the effective date of this

amendment.

(b) If the flight crew reports the occurrence

of any of the cockpit indications stated in

paragraph (a) of this AD: Prior to the next

flight, perform the maintenance procedures

to confirm and isolate the faulty power

supply unit, in accordance with paragraph

III., Part B, Accomplishment Instructions of

de Havilland Alert Service Bulletin S.B. A8–

33–33, dated May 31, 1993.

(1) If any power supply unit is determined

to be faulty, prior to further flight, replace the

unit with a new or serviceable ‘‘Grimes’’ unit

or a new ‘‘Whelen’’ system in accordance

with the alert service bulletin.

(2) If the specific unit causing the faults

cannot be determined, prior to further flight,

replace all three units with new or

serviceable ‘‘Grimes’’ units or a new

‘‘Whelen’’ system in accordance with the

alert service bulletin. Installation of a new

‘‘Whelen’’ system at all three locations

constitutes terminating action for the

requirements of this AD and, following

installation, the AFM revision required by

paragraph (a) of this AD may be removed.

(c) Within 6 months after the effective date

of this AD, install Modification 8/1273

(which entails replacement of the existing

anti-collision strobe lights, brackets, and

power supplies with the ‘‘ ‘Whelen’ AntiCollision Strobe Light System’’) at all three

locations, in accordance with de Havilland

Service Bulletin S/B No. 8–33–19, Revision

‘A’, dated May 31, 1993. Following

installation, the AFM revision required by

paragraph (a) of this AD may be removed.

(d) 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, New York

Aircraft Certification Office (ACO), ANE–170,

FAA, Engine and Propeller Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(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) The actions shall be done in accordance

with de Havilland Alert Service Bulletin S.B.

A8–33–33, dated May 31, 1993; and de

Havilland Service Bulletin S/B No. 8–33–19,

Revision ‘A’, dated May 31, 1993; as

applicable. This incorporation by reference

was approved previously by the Director of

the Federal Register, in accordance with 5

U.S.C. 552(a) and 1 CFR part 51, as of

December 15, 1994 (59 FR 58765, November

15, 1994). Copies may be obtained from de

Havilland, Inc., Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

FAA, Engine and Propeller Directorate, New

York Aircraft Certification Office, 181 South

Franklin Avenue, Room 202, Valley Stream,

New York; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment becomes effective on

February 3, 1995.

Issued in Renton, Washington, on January

11, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–1127 Filed 1–18–95; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 39

[Docket No. 94–NM–217–AD; Amendment

39–9108; AD 94–26–13]

Airworthiness Directives; Boeing

Model 737–300, –400, and –500 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 737–

300, –400, and –500 series airplanes.

This action requires modification of the

leading edge slat access panel and

internal structure at Front Spar Station

(FSS) 250.663. This amendment is

prompted by reports that fuel leaking

from the fuel line at FSS 250.663 flowed

through a drain hole in a slat access

panel and leaked into the turbine

exhaust area. The actions specified in

this AD are intended to prevent

drainage from such a fuel leak into the

turbine exhaust area, which could cause

an external fire under the wing.

DATES: Effective on February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 3,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

March 20, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

217–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue SW.,

Renton, Washington; or at the Office of