Federal Register / Vol. 62, No. 176 / Thursday, September 11, 1997 / Rules and Regulations 47753

(vi) Participants acknowledge that all

devices, decals, cards, or other Federal

Government supplied identification or

technology used to identify or inspect

persons or vessels seeking entry via this

program remain the property of the

United States Government at all times,

and must be surrendered upon request

by a Border Patrol Agent or any other

officer of a Federal Inspection Service.

(vii) The captain, charterer, master, or

owner (if aboard) of each vessel bringing

persons into the United States is

responsible for determining that all

persons aboard the vessel are in

possession of a valid, unexpired Form I–

68 or other evidence of participation in

a Service Alternative Inspections

program (INSPASS or PORTPASS) prior

to entry into the territorial waters of the

United States. If any person on board is

not in possession of such evidence, the

captain, charterer, master, or owner

must transport such person to a staffed

United States Port-of-Entry for an inperson immigration inspection.

(6) Revocation. The district director,

the chief patrol agent, or their

designated representatives may revoke

the designation of any participant who

violates any condition of this program,

as contained in paragraph (e)(5) of this

section, or who has violated any

immigration law or regulation, or a law

or regulation of the United States

Customs Service or other Federal

Inspection Service, has abandoned his

or her residence in the United States or

Canada, is inadmissible to the United

States, or who is otherwise determined

by an immigration officer to be

ineligible for continued participation in

this program. Such persons may be

subject to other applicable sanctions,

such as criminal and/or administrative

prosecution or deportation, as well as

possible seizure of goods and/or vessels.

If permission to participate is revoked,

a written request to the district director

for restoration of permission to

participate may be made. The district

director will notify the person of his or

her decision and the reasons therefore

in writing.

(7) Compliance checking.

Participation in this program does not

relieve the holder from responsibility to

comply with all other aspects of United

States Immigration, Customs, or other

Federal inspection service laws or

regulations. To prevent abuse, the

United States Immigration and

Naturalization Service retains the right

to conduct inspections or examinations

of all persons applying for admission or

readmission to or seeking transit

through the United States in accordance

with the Immigration and Nationality

Act.

* * * * *

Dated: July 30, 1997.

Doris Meissner,

Commissioner, Immigration and

Naturalization Service.

[FR Doc. 97–24124 Filed 9–10–97; 8:45 am]

BILLING CODE 4410–10–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–220–AD; Amendment

39–10121; AD 97–19–01]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB 2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

2000 series airplanes, that requires a

one-time inspection of the hydraulic

tubes and electrical harness wires of the

wing rear access door for chafing,

leakage, or wear damage; repair of any

discrepancy found; and modification of

the wing rear access door. This

amendment is prompted by reports of

interference between the wing rear

access door and the hydraulic tubes and

electrical harnesses, and chafing damage

to the hydraulic tubes. The actions

specified by this AD are intended to

prevent such interference or chafing

damage, which could lead to failure of

the number 2 hydraulic system or loss

of certain electrical and landing

systems, and resultant reduced

controllability of the airplane.

DATES: Effective October 16, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 16,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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:

Ruth Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1721; fax (425) 227–1149.

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 Saab Model

SAAB 2000 series airplanes was

published in the Federal Register on

June 24, 1997 (62 FR 34024). That action

proposed to require a one-time visual

inspection of the hydraulic tubes and

electrical harness wires of the wing rear

access door for chafing, leakage, or wear

damage; repair of any discrepancy

found; and modification of the wing rear

access door.

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.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 3 Saab Model

SAAB 2000 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 4 work hours

per airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will be provided by the manufacturer at

no cost to operators.

Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $720, or $240 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.

Regulatory Impact

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
47754 Federal Register / Vol. 62, No. 176 / Thursday, September 11, 1997 / Rules and Regulations

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.

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), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–19–01 SAAB Aircraft AB: Amendment

39–10121. Docket 96–NM–220–AD.

Applicability: Model SAAB 2000 series

airplanes, serial numbers –004 through –030

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

otherwise 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent damage to the hydraulic tubes

and electrical harnesses, which could lead to

failure of the number 2 hydraulic system or

loss of certain electrical and landing systems,

and resultant reduced controllability of the

airplane, accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a one-time visual

inspection of the hydraulic tubes and

electrical harness wires of the wing rear

access door for chafing, leakage, or wear

damage; in accordance with paragraph B. of

the Accomplishment Instructions of Saab

Service Bulletin 2000–53–010, Revision 01,

dated October 10, 1995.

(1) If any chafing or leakage of the

hydraulic tubes is detected, prior to further

flight, repair in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate.

(2) If any damage to the metal braid or wire

insulation is detected, prior to further flight,

repair in accordance with paragraph E. of the

Accomplishment Instructions of Saab Service

Bulletin 2000–53–010, Revision 01, dated

October 10, 1995.

(b) Within 60 days after the effective date

of this AD, modify the wing rear access door

and apply silicon tape to the electrical

harnesses, in accordance with paragraph C.

of the Accomplishment Instructions of Saab

Service Bulletin 2000–53–010, Revision 01,

dated October 10, 1995.

(c) As of the effective date of this AD, no

person shall install wing rear access doors,

part numbers 7353500–713/–714 or

7353500–715/–716, on any airplane, unless

the part has been modified in accordance

with Saab Service Bulletin 2000–53–010,

Revision 01, dated October 10, 1995.

(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,

Standardization Branch, ANM–113.

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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(e) 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.

(f) The inspection, modification, and

certain repairs shall be done in accordance

with Saab Service Bulletin 2000–53–010,

Revision 01, dated October 10, 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 SAAB

Aircraft AB, SAAB Aircraft Product Support,

S–581.88, Linko ̈ping, Sweden. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment becomes effective on

October 16, 1997.

Issued in Renton, Washington, on

September 3, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–23858 Filed 9–10–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94–SW–28–AD; Amendment

39–10129; AD 97–19–09]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 214ST

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. (BHTI) Model 214ST helicopters,

that requires creation of a component

history card or equivalent record using

a Retirement Index Number (RIN)

system; establishes a system for tracking

increases to the accumulated RIN; and

establishes a maximum accumulated

RIN for the pillow block bearing bolts

(bearing bolts). This amendment is

prompted by fatigue analyses and tests

that show certain bearing bolts fail

sooner than originally anticipated

because of the unanticipated high

number of takeoffs and external load

lifts utilizing high-power settings in

addition to the time-in-service (TIS)

accrued under other operating

conditions. The actions specified by this

AD are intended to prevent fatigue

failure of the bearing bolts, which could

result in failure of the main rotor system

and subsequent loss of control of the

helicopter.

EFFECTIVE DATE: October 16, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Harrison, Aerospace Engineer,

FAA, Rotorcraft Certification Office,

Rotorcraft Directorate, Fort Worth,

Texas 76193–0170, telephone (817)

222–5447, fax (817) 222–5959.

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 BHTI Model 214ST

helicopters was published in the

Federal Register on December 23, 1996

(61 FR 67503). That action proposed to

require creation of a component history