Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75609

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. FAA amends § 39.13 by adding a

new AD to read as follows:

2000–22–18 Raytheon Aircraft Company:

Amendment 39–11965; Docket No.

2000–CE–42–AD.

(a) What airplanes are affected by this AD?

This AD affects Beech Model 58 airplanes;

serial numbers TH–1389, and TH–1396

through TH–1885, that are certificated in any

category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to correct the wrong use of screws and

consequent wear in the pilot/copilot pedal

interconnect tube, which could result in loss

of rudder control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must do the following actions:

Actions Compliance times Procedures

(1) Inspect the rudder bellcrank interconnect tube

for damage and ensure the floorboard panel

screws are 3⁄4 inch or less in length. Screws that

are longer than 3⁄4 inch in length can damage

parts installed immediately below the floorboards.

Inspect within the next 6 calendar

months after December 29, 2000

(the effective date of this AD).

Do this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph

of Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron Model

58 Shop Manual.

(2) If you find no damage to the rudder bellcrank

interconnect tube, discard any self-tapping

coarse thread screw installed in the flanges that

is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(3) If you find damage to the rudder bellcrank interconnect tube, and the damage has not worn into

the aluminum interconnect tube, refinish the

interconnect tube and discard any self-tapping

coarse thread screw installed in the flanges that

is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(4) If you find damage to the rudder bellcrank interconnect tube, and the damage has worn into the

aluminum interconnect tube, you must replace

the interconnect tube and discard any self-tapping coarse thread screw installed in the flanges

that is longer than 3⁄4 inch.

Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(5) Plug the floorboard screw hole ........................... Before further flight after the inspection.Do these actions in accordance with the ACCOMPLISHMENT INSTRUCTIONS paragraph of

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000, and the Baron 58

Shop Manual.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Wichita Aircraft

Certification Office (ACO), approves your

alternative. Send your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

of this AD. You should include in the request

an assessment of the effect of the

modification, alteration, or repair on the

unsafe condition addressed by this AD; and,

if you have not eliminated the unsafe

condition, specific actions you propose to

address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Paul C. DeVore,

Aerospace Engineer, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;

telephone: (316) 946–4142; facsimile: (316)

946–4407.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can do the requirements of this

AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Raytheon Mandatory Service Bulletin SB 27–

3013, Issued: June 2000. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from Raytheon

Aircraft Company, P.O. Box 85, Wichita,

Kansas 67201–0085; telephone: (800) 429–

5372 or (316) 676–3140; or on the Internet at

<http://www.raytheon.com/rac/ servinfo/27–

3013.pdf>. This file is in Adobe Portable

Document Format. The Acrobat Reader is

available at <http://www.adobe.com/>. You

can look at copies at the FAA, Central

Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on December 29, 2000.

Issued in Kansas City, Missouri, on

October 30, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–28438 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–28–AD; Amendment

39–12016; AD 2000–24–09]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

75610 Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes,

that requires modification of the

insulation blankets in the area

surrounding the main external power

ground studs. This action is necessary to

prevent smoke and fire in the forward

cargo compartment due to burn damage

to the insulation blankets in the area

surrounding the main external power

ground studs. This action is intended to

address the identified unsafe condition.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 8,

2001.

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 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:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5350;

fax (562) 627–5210.

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 McDonnell

Douglas Model MD–11 series airplanes

was published in the Federal Register

on July 27, 2000 (65 FR 46203). That

action proposed to require modification

of the insulation blankets in the area

surrounding the main external power

ground studs.

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 indicates that it has

completed the subject modification and

has 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

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 137 Model

MD–11 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 28 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 2 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 $3,360,

or $120 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, 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:

2000–24–09 McDonnell Douglas:

Amendment 39–12016. Docket 2000–

NM–28–AD.

Applicability: Model MD–11 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD11–25A187,

Revision 01, dated January 5, 2000;

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 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.

Compliance: Required as indicated, unless

accomplished previously.

To prevent smoke and fire in the forward

cargo compartment due to burn damage to

the insulation blankets in the area

surrounding the main external power ground

studs, accomplish the following:

Modification

(a) Within one year after the effective date

of this AD, modify the insulation blankets in

the area surrounding the main external

power ground studs in accordance with

McDonnell Douglas Alert Service Bulletin

MD11–25A187, Revision 01, dated January 5,

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, Los

Angeles Aircraft Certification Office (ACO),

Federal Register / Vol. 65, No. 233 / Monday, December 4, 2000 / Rules and Regulations 75611

FAA. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with sections 21.197 and

21.12000 of the Federal Aviation Regulations

(14 CFR 21.197 and 21.12000) to operate the

airplane to a location where the requirements

of this AD can be accomplished.

Incorporation by Reference

(d) The modification shall be done in

accordance with McDonnell Douglas Alert

Service Bulletin MD11–25A187, Revision 01,

dated January 5, 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 Boeing Commercial Aircraft

Group, Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at 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.

Effective Date

(e) This amendment becomes effective on

January 8, 2001.

Issued in Renton, Washington, on

November 22, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30434 Filed 12–1–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–29–AD; Amendment

39–12017; AD 2000–24–10]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–11 series airplanes,

that requires relocating the B7–28 bus

located in the upper main circuit

breaker in the rear cockpit observer’s

station from the lower to the upper

terminals of the circuit breakers in Row

P. This action is necessary to prevent

insufficient clearance and contact

between the B7–28 bus and an adjacent

panel, which could result in arcing

damage, smoke, and/or fire in the upper

main circuit breaker panel. This action

is intended to address the identified

unsafe condition.

DATES: Effective January 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 8,

2001.

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 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:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5350;

fax (562) 627–5210.

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 McDonnell

Douglas Model MD–11 series airplanes

was published in the Federal Register

on July 27, 2000 (65 FR 46204). That

action proposed to require relocating the

B7–28 bus located in the upper main

circuit breaker in the rear cockpit

observer’s station from the lower to the

upper terminals of the circuit breakers

in Row P.

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

There are approximately 144

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

56 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 2 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 $6,720,

or $120 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.