70296 Federal Register / Vol. 65, No. 226 / Wednesday, November 22, 2000 / Rules and Regulations

Issued in Renton, Washington, on

November 6, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28963 Filed 11–21–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–213–AD; Amendment

39–11987; AD 2000–23–15]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B 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

SF340A and SAAB 340B series

airplanes, that requires inspecting the

connector on the refuel/defuel panel

and the electrical connector on the

illuminated placard to detect signs of

fluid ingression or corrosion, and

corrective actions. The actions specified

by this AD are intended to prevent

electrical shorts or arcing at the

illuminated placard connector at the

refuel/defuel panel, which could result

in a potential ignition source for fuel

vapors during fueling procedures. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 27, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

27, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linkping,

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 SF340A and SAAB 340B series

airplanes was published in the Federal

Register on September 19, 2000 (65 FR

56507). That action proposed to require

inspecting the connector on the refuel/

defuel panel and the electrical

connector on the illuminated placard to

detect signs of fluid ingression or

corrosion, and corrective actions.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

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 289 Model

SAAB SF340A and SAAB 340B 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. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$69,360, 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2000–23–15 Saab Aircraft AB: Amendment

39–11987. Docket 2000–NM–213–AD.

Applicability: Model SAAB SF340A series

airplanes, serial numbers –004 through –159

inclusive; and Model SAAB 340B series

airplanes, serial numbers –160 through –459

inclusive; certificated in any category; on

which a refuel/defuel panel having part

number 7239160–505 is installed.

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 request approval for an

alternative method of compliance in

accordance with paragraph (b) 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.

Federal Register / Vol. 65, No. 226 / Wednesday, November 22, 2000 / Rules and Regulations 70297

Compliance: Required as indicated, unless

accomplished previously.

To prevent electrical shorts or arcing at the

illuminated panel connector at the refuel/

defuel panel, which could result in a

potential ignition source for fuel vapors

during fueling procedures, accomplish the

following:

Inspection and Corrective Actions

(a) Within 6 months after the effective date

of this AD, inspect the electrical connector

on the refuel/defuel panel and the electrical

connector on the illuminated placard to

detect signs of fluid ingression or corrosion;

and accomplish applicable corrective actions

(including a sealing procedure, a cleaning/

sealing procedure, and repair of corrosion on

the refuel/defuel panel mounting plate); in

accordance with Saab Service Bulletin 340–

28–022, dated February 25, 2000.

Alternative Methods of Compliance

(b) 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Saab Service Bulletin 340–28–022,

dated February 25, 2000. 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.

Note 3: The subject of this AD is addressed

in Swedish airworthiness directive 1–156,

dated February 28, 2000.

Effective Date

(e) This amendment becomes effective on

December 27, 2000.

Issued in Renton, Washington, on

November 8, 2000.

Donald L. Riggin,

Acting Manager,, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29213 Filed 11–21–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–243–AD; Amendment

39–11990; AD 2000–23–17]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 and MD–11F

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 and MD–11F

series airplanes, that currently requires

opening the circuit breaker of the

pneumatic sense line heater tape,

installing an inoperative ring, and

coiling and stowing the electrical wire

to the circuit breaker of the pneumatic

sense line heater tape. That AD also

provides for an optional inspection,

which, if accomplished, constitutes

terminating action for deactivation of

the pneumatic sense line heater tape.

This amendment requires repetitive

inspections of the subject area and

corrective actions, if necessary, and

provides for an optional terminating

modification(s) for the repetitive

inspection requirements. This

amendment is prompted by the FAA’s

determination that the one-time

optional terminating inspection in the

existing AD does not adequately detect

chafing, electrical arcing, or inadequate

clearance of the subject area. The

actions specified by this AD are

intended to detect and correct such

inadequate clearance, which could

result in a hole in the fuel feed pipe

caused by electrical arcing, and

consequent fuel leakage and possible

ignition of the fuel vapors.

DATES: Effective December 27, 2000.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of December

27, 2000.

The incorporation by reference of

McDonnell Douglas Alert Service

Bulletin MD11–36A030, dated April 2,

1998, as listed in the regulations, was

approved previously by the Director of

the Federal Register as of April 28, 1998

(63 FR 20066, April 23, 1998).

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Aircraft

Group, Long Beach Division, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). 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 the FAA,

Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Stephen Kolb, Senior Aerospace

Engineer, Propulsion Branch, ANM–

140L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (562) 627–5244; fax (562)

627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–08–11,

amendment 39–10491 (63 FR 20066,

April 23, 1998), which is applicable to

certain McDonnell Douglas Model MD–

11 and MD–11F series airplanes, was

published in the Federal Register on

July 13, 2000 (65 FR 43265). The action

proposed to continue to require opening

the circuit breaker of the pneumatic

sense line heater tape, installing an

inoperative ring, and coiling and

stowing the electrical wire to the circuit

breaker of the pneumatic sense line

heater tape. The action also proposed to

require repetitive inspections of the

subject area and corrective actions, if

necessary, and would provide for an

optional terminating modification(s) for

the repetitive inspection requirements.

Comments

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 states no objection to

the proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air