Federal Register / Vol. 65, No. 228 / Monday, November 27, 2000 / Rules and Regulations 70647

Actions Compliance times Procedures

(1) Accomplish both an external and internal inspection of the forward, aft, and auxiliary

wing spars for cracks.

Initially inspect upon accumulating 10,000

hours total time-in-service (TIS) on the airplane or within the next 25 hours TIS after

June 21, 1999 (the effective date of AD 99–

11–13), whichever occurs later. Repetitively

inspect thereafter within 110 hours TIS after

the last inspection required by this AD or

Ad 99–11–13, whichever is applicable, and

thereafter at intervals not to exceed 110

hours TIS.

Accomplish these inspections in accordance

with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin

MEB99–3, dated May 6, 1999.

(2) If any crack is found on any forward, aft, or

auxiliary wing spar during any inspection required by this AD, accomplish the following:

(i) Obtain an FAA-approved repair scheme

from the Cessna Aircraft Company, P.O.

Box 7706, Wichita, Kansas 67277; telephone: (316) 941–7550, facsimile: (316)

942–9008; and.

(ii) Incorporate this repair scheme .............. Prior to further flight after the inspection

where the crack is found.

Not applicable.

Note 1: The 110-hour TIS interval

repetitive inspection time is established to

allow this action to be accomplished with

regular maintenance. The FAA initially

determined that 100-hour TIS intervals

would provide the safety intent, but has since

determined that the 110-hour TIS intervals

would provide the same safety intent while

providing a 10-percent time flexibility in

scheduling to coincide with regular

maintenance.

Note 2: The compliance times specified in

Cessna Service Bulletin MEB99–3, dated May

6, 1999, are different than those required by

this AD. The times in this AD take

precedence over those in the service bulletin.

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

way? 

(1) You may use an alternative method of

compliance or adjust the compliance time if:

(i) Your alternative method of compliance

provides an equivalent level of safety; and

(ii) The Manager, Wichita Aircraft

Certification Office (ACO), approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO, 1801 Airport Road,

Room 100, Mid-Continent Airport, Wichita,

Kansas 67209.

(2) Alternative methods of compliance that

were approved in accordance with AD 99–

11–13 are considered approved as alternative

methods of compliance for this AD.

Note 3: 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. 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 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 Eual Conditt, Aerospace

Engineer, FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209,

telephone: (316) 946–4128; 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 accomplish 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

Cessna Service Bulletin MEB99–3, dated May

6, 1999. The Director of the Federal Register

previously approved this incorporation by

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

part 51, as of June 21, 1999 (64 FR 29781;

June 3, 1999). You can get copies from the

Cessna Aircraft Company, P.O. Box 7706,

Wichita, Kansas 67277. 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) Does this AD action affect any existing

AD actions? This amendment supersedes AD

99–11–13, Amendment 39–11184.

(j) When does this amendment become

effective? This amendment becomes effective

on December 21, 2000.

Issued in Kansas City, Missouri, on

November 2, 2000.

Michael K. Dahl,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–28831 Filed 11–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–11–AD; Amendment

39–11912; AD 2000–20–01]

RIN 2120–AA64

Airworthiness Directives; Turbomeca

Arriel 1 Series Turboshaft Engines;

Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction

SUMMARY: This document makes a

correction to Airworthiness Directive

(AD) 2000–20–01 applicable to

Turbomeca Arriel 1 series turboshaft

engines that was published in the

Federal Register on October 2, 2000 (65

FR 58640). The listing of helicopters on

which the affected engines might be

installed in the table in the

Applicability section is incorrect. This

document corrects that listing. In all

other respects, the original document

remains the same.

EFFECTIVE DATE: October 17, 2000.

FOR FURTHER INFORMATION CONTACT:

James Rosa, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7152, fax

(781) 238–7199 .

SUPPLEMENTARY INFORMATION: A final

rule airworthiness directive (FR Doc 00–

24900) applicable to Turbomeca Arriel 1

series turboshaft engines, was published

in the Federal Register on October 2,

2000 (65 FR 58640). The following

correction is needed:

70648 Federal Register / Vol. 65, No. 228 / Monday, November 27, 2000 / Rules and Regulations

§ 39.13 [Corrected]

On page 58641, in the second column,

in the APPLICABILITY Section, the

table in the third paragraph from the top

of the column,

Eurocopter AS 356 C ...................................................... Eurocopter AS 365 C1 .................................................... Eurocopter AS 350 BA.

Eurocopter AS 356 N2 .................................................... Eurocopter AS 350 B ...................................................... Eurocopter AS 350 B2N.

Eurocopter AS 350 D ...................................................... Eurocopter AS 550 U2 .................................................... Augusta A109K2.

Sikorsky S76A ................................................................. Sikorsky 76A ................................................................... Sikorsky 76A.

Sikorsky S76C’’.

is corrected to read ‘‘

Eurocopter SA 365 C; ..................................................... Eurocopter SA 365 C1; ................................................... Eurocopter AS 350 BA;

Eurocopter AS 365 N2; ................................................... Eurocopter AS 350 B; ..................................................... Eurocopter AS 350 B2;

Sikorsky S76C; ................................................................ Augusta A109K2’’.

Issued in Burlington, MA, on September

21, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–28959 Filed 11–24–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–76–AD; Amendment

39–11992; AD 2000–23–19]

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 supersedes

an existing airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that currently requires

inspections to detect damage or cracking

of the forward and aft attachment lugs

of the flap fittings at wing station (WS)

123.38; an inspection to verify that the

sizes of the holes of the flap fittings are

within specified limits and to ensure

that the swaged bushings are not loose;

and modification of the flap fittings.

This amendment requires repetitive

accomplishment of the inspections

using improved inspection methods; a

one-time visual and repetitive general

visual and detailed visual inspections;

new repetitive non-destructive test

(NDT) inspections; and corrective and

follow-on actions, as necessary. This

amendment also provides for

terminating action for all repetitive

inspections and revises the applicability

of the existing AD. The actions specified

by this AD are intended to prevent high

bearing stress on the bushings of the

flap fittings, which could result in wear

on the bushings, cracking of the flap

fittings, and breakage of the lugs; these

conditions could result in jamming of

the flaps and consequent reduced

controllability of the airplane.

DATES: Effective January 2, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 2,

2001.

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:

Norman B. Martenson, Manager,

International Branch, ANM–116,

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 96–25–06 R1,

amendment 39–9891 (62 FR 3209,

January 22, 1997), which is applicable

to certain Saab Model SAAB SF340A

and SAAB 340B series airplanes, was

published in the Federal Register on

July 31, 2000 (65 FR 46667). The action

proposed to continue to require

inspections to detect damage or cracking

of the forward and aft attachment lugs

of the flap fittings at wing station (WS)

123.38; an inspection to verify that the

sizes of the holes of the flap fittings are

within specified limits and to ensure

that the swaged bushings are not loose;

and modification of the flap fittings. The

action also proposed to require

repetitive accomplishment of the

inspections using improved inspection

methods; a one-time visual and

repetitive general visual and detailed

visual inspections; new repetitive nondestructive test (NDT) inspections; and

corrective and follow-on actions, as

necessary. Additionally, the action also

proposed to provide for terminating

action for all repetitive inspections and

to revise the applicability of the existing

AD.

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 303 airplanes

of U.S. registry will be affected by this

AD.

It will take approximately 1 work

hour per airplane to accomplish the

required repetitive general visual

inspections, at an average labor rate of

$60 per work hour.

Based on these figures, the cost

impact of the required general visual

inspections on U.S. operators is

estimated to be $18,180, or $60 per

airplane, per inspection cycle.

It will take approximately 1 work

hour per airplane to accomplish the

required one-time general visual

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the required

general visual inspection on U.S.

operators is estimated to be $18,180, or

$60 per airplane.

It will take approximately 1 work

hour per airplane to accomplish the

required repetitive detailed visual

inspections, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the required

detailed visual inspections on U.S.