Federal Register / Vol. 65, No. 210 / Monday, October 30, 2000 / Rules and Regulations 64601

Total pages: 14.

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 Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860) 565–

8770, fax (860) 565–4503. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

Effective Date of This AD

(i) This amendment becomes effective on

December 4, 2000.

Issued in Burlington, Massachusetts, on

October 20, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–27507 Filed 10–27–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–202–AD; Amendment

39–11951; AD 2000–22–05]

RIN 2120–AA64

Airworthiness Directives; Short

Brothers Model SD3–60 SHERPA

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Short Brothers Model

SD3–60 SHERPA series airplanes, that

currently requires a one-time visual

inspection to determine the part number

of the power control cable assemblies

and pulleys of the engine controls; and

replacement of the power control cable

assemblies and pulleys (as applicable)

with new parts, if necessary. This

amendment requires accomplishment of

the inspection and replacement in

accordance with revised procedures.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent breakage of the

power control cable assemblies due to

the inflexible construction of the cable,

which could result in loss of engine

power and consequent reduced

controllability of the airplane.

DATES: Effective December 4, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

4, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Short Brothers, Airworthiness &

Engineering Quality, P.O. Box 241,

Airport Road, Belfast BT3 9DZ,

Northern Ireland. 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)

by superseding AD 99–03–06,

amendment 39–11020 (64 FR 5588,

February 4, 1999), which is applicable

to all Short Brothers Model SD3–60

SHERPA series airplanes, was published

in the Federal Register on June 30, 2000

(65 FR 40549). The action proposed to

require a one-time inspection to

determine the part number of the power

control cable assemblies and pulleys of

the engine controls; and replacement of

the power control cable assemblies and

pulleys (as applicable) with new parts,

if necessary.

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

approximately 28 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 15 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

$25,200, or $900 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

removing amendment 39–11020 (64 FR

5588, February 4, 1999), and by adding

a new airworthiness directive (AD),

64602 Federal Register / Vol. 65, No. 210 / Monday, October 30, 2000 / Rules and Regulations

amendment 39–11951, to read as

follows:

2000–22–05 Short Brothers, PLC:

Amendment 39–11951. Docket 2000–

NM–202–AD. Supersedes AD 99–03–06,

Amendment 39–11020.

Applicability: All Model SD3–60 SHERPA

series airplanes, 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 breakage of the power control

cable assemblies due to the inflexible

construction of the cable, which could result

in loss of engine power and consequent

reduced controllability of the airplane,

accomplish the following:

Inspection and Corrective Actions

(a) At the next scheduled heavy

maintenance inspection, but no later than

1,200 flight hours after the effective date of

this AD: Perform a one-time inspection to

determine the part number (P/N) of the

power control cable assemblies and pulleys

of the engine controls, in accordance with

Part A of the Accomplishment Instructions of

Shorts Service Bulletin SD3–60 SHERPA–76–

1, Revision 2, dated March 21, 2000.

(1) If any power control cable assembly

having P/N SD3–47–1091 or SD3–47–1094 is

found, prior to further flight, replace the

power control cable assembly with a new

power control cable assembly in accordance

with Part B of the Accomplishment

Instructions of the service bulletin.

(2) If any pulley having P/N C181605 is

found, prior to further flight, replace the

pulley with a new pulley in accordance with

Part C of the Accomplishment Instructions of

the service bulletin.

Spares

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

person shall install on the engine controls of

any airplane a cable assembly having P/N

SD3–47–1091 or SD3–47–1094, or any pulley

having P/N C181605.

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, 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 Manager, 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 Shorts Service Bulletin SD3–60

SHERPA–76–1, Revision 2, dated March 21,

2000, which contains the following list of

effective pages:

Page No. Revision level shown on page Date shown on

page

1, 3, 4, 7, 13, 27 ...................................................................................... 2 ................................................................................. Mar. 21, 2000.

2, 8, 10–12, 14–16, 23, 29 ...................................................................... 1 ................................................................................. Oct. 14, 1998.

5, 6, 9, 17–22, 24–26, 28 ........................................................................ Original ....................................................................... July 1998.

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 Short Brothers, Airworthiness &

Engineering Quality, P.O. Box 241, Airport

Road, Belfast BT3 9DZ, Northern Ireland.

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.

Effective Date

(f) This amendment becomes effective on

December 4, 2000.

Issued in Renton, Washington, on October

23, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27629 Filed 10–27–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–376–AD; Amendment

39–11949; AD 2000–22–03]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model DH.125, Model HS.125, Model

BH.125, Model BAe.125 Series 800A

(Including Major Variants C–29A and

U1–25), Model Hawker 800, Model

Hawker 800XP, and Model Hawker 1000

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

DH.125, Model HS.125, Model BH.125,

Model BAe.125 Series 800A, Model

Hawker 800, Model Hawker 800XP, and

Model Hawker 1000 series airplanes,

that requires leak checks and

inspections for corrosion of the pitot/

static and stall vent drain valves, and

replacement of certain components, if

necessary. This amendment is prompted

by reports of plugged or taped drain

valves as well as consequent corrosion

of certain drain valves. The actions

specified by this AD are intended to

prevent erroneous altimeter and

airspeed indications due to plugged or

taped pitot/static and stall vent drain

valves.

DATES: Effective December 4, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

4, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Manager-Service Engineering, Hawker

Customer Support Department, P. O.

Box 85, Wichita, Kansas 67201–0085.

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,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidVerDate 11<MAY>2000 14:32 Oct 27, 2000 Jkt 194001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\30OCR1.SGM pfrm08 PsN: 30OCR1