33014 Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations

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 124 Model

Hawker 800XP series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 87 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

$10,440, 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.

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:

2001–12–17 Raytheon Aircraft Company:

Amendment 39–12273. Docket 2000–

NM–176–AD.

Applicability: Model Hawker 800XP series

airplanes, certificated in any category, having

the following serial numbers 258266, and

258277 through 258399 inclusive.

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 detect and correct fatigue cracking of

the fuselage skin, and consequent loss of

cabin pressurization, accomplish the

following:

Inspection and Corrective Action

(a) Within 600 flight hours or 12 months

after the effective date of this AD, whichever

occurs first: Do a one-time detailed visual

inspection to confirm the installation of

rivets at fuselage stations 251.975, 262.35,

272.725, and 283.10. Do the inspection per

the Accomplishment Instructions of

Raytheon Service Bulletin 51–3336, Revision

1, dated January 2001. If any rivet is missing,

before further flight, install a new rivet per

the Accomplishment Instructions of the

service bulletin.

Note 2: Accomplishment of the actions in

accordance with Raytheon Service Bulletin

51–3336, dated May 2000, is acceptable for

compliance with the requirements of

paragraph (a) of this AD.

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, Wichita

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

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 Raytheon Service Bulletin 51–3336,

Revision 1, dated January 2001. 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

Raytheon Aircraft Company, Department 62,

P.O. Box 85, Wichita, Kansas 67201–0085.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, Wichita,

Kansas; 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

July 25, 2001.

Issued in Renton, Washington, on June 11,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15211 Filed 6–19–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–262–AD; Amendment

39–12274; AD 2001–12–18]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA), Model CN–235 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain CASA Model CN–

Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations 33015

235 series airplanes, that requires

modification of the rigging of the engine

control cable assembly and replacement

of either the entire engine control cable

assembly or a segment of the control

cables. This amendment is prompted by

issuance of mandatory continuing

airworthiness information issued by a

foreign airworthiness authority. The

actions specified by this AD are

intended to prevent fatigue of the engine

control cables, leading to breakage of the

cables, which could result in reduced

controllability of the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective July 25, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 25,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. 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: Dan

Rodina, Aerospace Engineer, ANM–116,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2125; 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 CASA

Model CN–235 series airplanes was

published in the Federal Register on

March 19, 2001 (66 FR 15363). That

action proposed to require modification

of the rigging of the engine control cable

assembly and replacement of either the

entire engine control cable assembly or

a segment of the control cables.

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 2 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 8 work

hours per airplane to accomplish the

required modification, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the required modification on U.S.

operators is estimated to be $960, or

$480 per airplane.

The FAA estimates that it will take

approximately 47 work hours per

airplane to accomplish the required

replacement of either the engine control

cable assembly or a segment of the

control cables, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$1,444 per airplane. Based on these

figures, the cost impact of the required

modification on U.S. operators is

estimated to be $8,528, or $4,264 per

airplane.

The cost impact figures discussed

above are 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:

2001–12–18 Construcciones Aeronauticas,

S.A. (CASA): Amendment 39–12274.

Docket 2000–NM–262–AD.

Applicability: Model CN–235 series

airplanes, serial numbers C001 to C074,

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 (c) 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 fatigue of the engine control

cables, leading to breakage of the engine

control cables, which could result in reduced

controllability of the airplane, accomplish

the following:

Modification

(a) Within 15 days after the effective date

of this AD: Rig the power lever and condition

lever control stops, in accordance with CASA

COM 235–140, Revision 01, dated March 21,

2000.

Replacement

(b) Prior to the accumulation of 12,000

total flight cycles or within 6 months after

the effective date of this AD, whichever

occurs later: Replace either the entire engine

control cable assembly (part number 7–

44728–12) with a new assembly or replace a

segment of the control cable (part number

33016 Federal Register / Vol. 66, No. 119 / Wednesday, June 20, 2001 / Rules and Regulations

72830–20) with a new segment, in

accordance with CASA COM 235–140,

Revision 01, dated March 21, 2000.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. 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

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with CASA COM 235–140, Revision 01,

dated March 21, 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 Construcciones Aeronauticas,

S.A., Getafe, Madrid, Spain. 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 Spanish airworthiness directive 03/00,

dated March 2000.

Effective Date

(f) This amendment becomes effective on

July 25, 2001.

Issued in Renton, Washington, on June 11,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15210 Filed 6–19–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–320–AD; Amendment

39–12269; AD 2001–12–14]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

400 series airplanes, that requires an

inspection to detect miswiring of diodes

in the heating system of the pitot static

probes, and corrective action, if

necessary. The actions specified by this

AD are intended to prevent reduced

power to the heating system of the pitot

static probes, leading to ice

accumulation on the pitot static probes,

which could result in erroneous

airspeed or altitude indications to the

flight crew, and consequent reduced

operational safety in all phases of flight.

This action is intended to address the

identified unsafe condition.

DATES: Effective July 25, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 25,

2001.

ADDRESSES: 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

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: Don

Eiford, Aerospace Engineer, Systems

and Equipment Branch, ANM–130S,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2788; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A Notice

of Proposed Rulemaking (NPRM) to

amend part 39 of the Federal Aviation

Regulations (14 CFR part 39) to include

an airworthiness directive (AD)

applicable to certain Boeing Model 747–

400 series airplanes was published in

the Federal Register on February 21,

2001 (66 FR 10972). That action

proposed to require an inspection to

detect miswiring of diodes in the

heating system of the pitot static probes,

and corrective action, if necessary.

Editorial Change

The compliance time for rewiring of

any miswiring, detected during the

special detailed inspection required by

paragraph (a) of this AD, was

inadvertently omitted. Paragraph (a) of

this AD has been changed to require

rewiring of any miswiring prior to

further flight.

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 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 with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of this

AD.

Cost Impact

There are approximately 497 Model

747–400 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 69 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 $8,280,

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)