9304 Federal Register / Vol. 60, No. 33 / Friday, February 17, 1995 / Proposed Rules

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 the following new airworthiness

directive:

Bombardier Inc. (Formerly Canadair):

Docket 94–NM–239–AD.

Applicability: Model CL–600–1A11 (CL–

600) series airplanes, serial numbers 1004

through 1085 inclusive; Model CL–600–2A12

(CL–601) series airplanes, serial numbers

3001 through 3066 inclusive; Model CL–600–

2B16 (CL–601–3A, –3R) series airplanes,

serial numbers 5001 through 5150 inclusive;

Model CL–500–2B19 (Regional Jet Series 100)

series airplanes, serial numbers 7003 through

7040 inclusive; equipped with Sundstrand

air driven generator (ADG) uplock assembly

having part number 721863, 721863A, or

721863B; 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 (c) 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 failure of the shaft pin, which

could lead to the inability of the pilot to

manually deploy the air driven generator

(ADG) when necessary (i.e., when an

airplane’s primary electrical power sources

are lost and the ADG fails to deploy

automatically), accomplish the following:

(a) For Model CL–600–2B19 (Regional Jet

Series 100) series airplanes equipped with

Sundstrand ADG uplock assembly having P/

N 721863B: Accomplish paragraphs (a)(1),

(a)(2), and (a)(3), in accordance with

Canadair Alert Service Bulletin S.B. 1601R–

24–019, Revision ‘A’, dated August 9, 1994.

(1) Within 600 flight hours after the

effective date of this AD, perform an

inspection to verify the proper operation of

the uplock latch of the ADG, in accordance

with the Accomplishment Instructions of the

service bulletin. If the uplock latch cannot be

activated, prior to further flight, replace the

uplock latch with a serviceable part in

accordance with the service bulletin.

(2) Within 12 months after the effective

date of this AD, replace the uplock assembly

with a modified uplock assembly, in

accordance with the Accomplishment

Instructions of the service bulletin.

(3) After accomplishment of paragraph

(a)(1) or (a)(2) of this AD, perform a rigging

inspection in accordance with the

Accomplishment Instructions of the service

bulletin.

(b) For Model CL–600–2A12, CL–2B16,

and CL–600–1A11 series airplanes:

Accomplish paragraphs (b)(1), (b)(2), and

(b)(3), in accordance with Canadair Service

Bulletin 600–0638, dated April 25, 1994 (for

Model CL–600–1A11 series airplanes), or

Canadair Service Bulletin 601–0430, dated

April 25, 1994 (for Model CL–600–2A12 and

–2B15 series airplanes), as applicable.

(1) Within 150 flight hours after the

effective date of this AD, perform an

inspection to verify the proper operation of

the uplock latch of the ADG, in accordance

with the Accomplishment Instructions of the

applicable service bulletin. If the uplock

latch cannot be activated, prior to further

flight, replace the uplock latch with a

serviceable part, in accordance with the

applicable service bulletin.

(2) Within 12 months after the effective

date of this AD, replace the uplock assembly

with a modified uplock assembly, in

accordance with the Accomplishment

Instructions of the applicable service

bulletin.

(3) After accomplishment of paragraph

(b)(1) or (b)(2) of this AD, perform a rigging

inspection in accordance with the

Accomplishment Instructions of the

applicable service bulletin.

(c) 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), 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

(d) 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.

Issued in Renton, Washington, on February

13, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4002 Filed 2–16–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–189–AD]

Airworthiness Directives; Jetstream

Model 4101 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Jetstream Model 4101 airplanes.

This proposal would require an

inspection to determine if a travel stop

(screw) is installed at the flight control

assembly, and various follow-on

actions. This proposal is prompted by a

report of failure of the travel stop, which

allowed the elevator and aileron

disconnect handles to rotate within the

housing due to migration of the travel

stop from its position. The actions

specified by the proposed AD are

intended to prevent such migration,

which could result in the elevator and

aileron disconnect system resetting

without the use of the reset button; this

condition could lead to jamming of the

disconnect handles.

DATES: Comments must be received by

March 31, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

189–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Jetstream Aircraft, Inc., P.O. Box 16029,

Dulles International Airport,

Washington, DC 20041–6029. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT: Sam

Grober, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,
Federal Register / Vol. 60, No. 33 / Friday, February 17, 1995 / Proposed Rules 9305

Washington 98055–4056; telephone

(206) 227–1187; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal 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 Number 94–NM–189–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

94–NM–189–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, recently notified

the FAA that an unsafe condition may

exist on certain Jetstream Model 4101

airplanes. The CAA advises that a report

has been received indicating that a

screw, which is used as the travel stop

in both the elevator and aileron

disconnect handles, had migrated out of

their position. This allowed the elevator

and aileron disconnect control handles

to rotate within its housing. Such

rotation bypassed the operation of the

ratchet assembly and allowed the

elevator and aileron disconnect system

to reset without the use of the reset

button. The cause of this migration is

unknown at this time; normally, the

travel stop screws are retained against

vibration (which could cause them to

become loose) by means of a screw

locking insert. Migration of the travel

stop, if not corrected, could result in the

elevator and aileron disconnect system

resetting without the use of the reset

button; this condition could lead to

jamming of the disconnect handles.

Jetstream has issued Service Bulletin

J41–27–036, dated September 2, 1994,

which describes procedures for:

1. Performing an inspection to

determine if a travel stop (screw) is

installed at the flight control assembly;

2. Installing a new travel stop, if no

travel stop is found installed;

3. Performing a rotation to determine

the security of the travel stop, if a travel

stop is installed;

4. Performing an inspection to detect

damage, if the travel stop is found to be

loose; and replacing the travel stop with

a new travel stop, if damage is found;

5. Applying Loctite Superfast 290 to

the travel stop;

6. Permanently marking the flight

control assembly; and

7. Performing a functional test of the

aileron and elevator disconnect systems

and setting them to the locked position.

The service bulletin also describes

procedures for an optional installation

of a protective spiral wrap cover. The

CAA classified the service bulletin as

mandatory.

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

an inspection to determine if a travel

stop (screw) is installed at the flight

control assembly, and various follow-on

actions. The actions would be required

to be accomplished in accordance with

the service bulletin described

previously.

The FAA estimates that 14 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 4 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to the operators. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $3,360, or $240 per

airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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.
9306 Federal Register / Vol. 60, No. 33 / Friday, February 17, 1995 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Jetstream Aircraft Limited: Docket 94–NM–

189–AD.

Applicability: Model 4101 airplanes,

constructors numbers 41004 through 41039

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 (c) 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 jamming of the elevator and

aileron disconnect handles, accomplish the

following:

(a) Within 600 flight hours after the

effective date of this AD, or within 6 months

after the effective date of this AD, whichever

occurs first, perform an inspection to

determine if a travel stop (screw) is installed

at the flight control assembly, in accordance

with Jetstream Service Bulletin J41–27–036,

dated September 2, 1994.

(1) If no travel stop is found to be installed,

prior to further flight, install a new travel

stop in accordance with the service bulletin.

After installation, accomplish paragraph

(a)(2) of this AD.

(2) If such a travel stop is installed, prior

to further flight, perform a rotation to

determine the security of the travel stop, in

accordance with the service bulletin.

(i) If the travel stop is found to be properly

secured, no further action is required by

paragraph (a) of this AD.

(ii) If the travel stop is found to be loose,

prior to further flight, remove it and perform

an inspection to detect damage in accordance

with the service bulletin. If any damage is

found, replace the travel stop with a new

travel stop, in accordance with the service

bulletin. After replacement, repeat the

requirements of paragraph (a)(2) of this AD.

(b) After accomplishment of paragraph (a)

of this AD, prior to further flight, accomplish

paragraphs (b)(1), (b)(2), and (b)(3) of this AD,

in accordance with Jetstream Service Bulletin

J41–27–036, dated September 2, 1994.

(1) Apply Loctite Superfast 290 to the

travel stop;

(2) Permanently mark the flight control

assembly; and

(3) Perform a functional test of the aileron

and elevator disconnect systems and set them

to the locked position.

Note 2: Procedures for installing a

protective spiral wrap cover are contained in

Jetstream Service Bulletin J41–27–036, dated

September 2, 1994. This installation is

recommended, but is not required by this

AD.

(c) 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,

Standardization Branch, ANM–113, FAA,

Transport 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(d) 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.

Issued in Renton, Washington, on February

13, 1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4003 Filed 2–16–95; 8:45 am]

BILLING CODE 4910–13–U

Federal Highway Administration

23 CFR Part 630

[FHWA Docket No. 94–30]

RIN 2125–AD40

Federal-Aid Project Authorization

AGENCY: Federal Highway

Administration (FHWA), DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: The FHWA proposes to

amend its regulation on Federal-aid

program approval and project

authorization. In light of changes made

by the Intermodal Surface

Transportation Efficiency Act of 1991

(ISTEA) in the area of statewide

planning, and the joint FHWA/Federal

Transit Administration (FTA)

regulations implementing those

changes, this NPRM proposes to remove

all other project programming

provisions from the FHWA’s

regulations. This NPRM would also

provide more flexible funding

arrangements and make the Federal-aid

authorization process more flexible.

Changes contained in related laws are

included.

DATES: Written comments are due on or

before April 18, 1995. Comments

received after that date will be

considered to the extent practicable.

ADDRESSES: All written, signed

comments should refer to the docket

number that appears at the top of this

document and should be submitted to

Federal Highway Administration, Office

of the Chief Counsel, Room 4232, HCC–

10, 400 Seventh Street, SW.,

Washington, D.C. 20590. All comments

received will be available for

examination at the above address

between 8:30 a.m. and 3:30 p.m., e.t.,

Monday through Friday, except Federal

holidays. Those desiring notification of

receipt of comments must include a selfaddressed, stamped postcard.

FOR FURTHER INFORMATION CONTACT: Jerry

L. Poston, Office of Engineering, 202–

366–0450, or Wilbert Baccus, Office of

the Chief Counsel, 202–366–0780,

FHWA, 400 Seventh Street, SW.,

Washington, D.C. 20590. Office Hours

are from 7:45 a.m. to 4:15 p.m., e.t.,

Monday through Friday except Federal

holidays.

SUPPLEMENTARY INFORMATION: The

initiation of work for transportation

projects funded under the Federal-aid

highway program is a two-step process.

First, the State, in cooperation and

consultation with local officials, as

appropriate, through the metropolitan

and statewide planning process,

determines activities which will be

advanced with Federal funds made

available under title 23, United States

Code, and the Federal Transit Act (49

U.S.C. 5301–5338) and develops a

statewide program of projects for these

activities. Prior to passage of the ISTEA,

the requirements for developing the

program of projects were found in 23

U.S.C. 105 and the implementing

regulations in 23 CFR 630, subpart A.

With passage of the ISTEA, title 23,

U.S.C., was modified and the new

requirements concerning development

of a program of projects, now referred to

as the Statewide transportation

improvement program, are contained in

23 U.S.C. 135. The implementing

regulation for this section are at 23 CFR

450 and were initiated through previous

rulemaking actions.

Accordingly, those requirements

pertaining to a program of projects in 23

CFR 630, subpart A, no longer need to

be retained. The FHWA therefore

proposes to eliminate §§ 630.106,

630.108, 630.110 and 630.112 along

with inappropriate programming

references from the existing regulation.

The second step in initiation of work

is the project authorization process. The

State highway agency (SHA) requests

FHWA authorization to proceed with a

proposed Federal-aid highway project.