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.

Federal Register / Vol. 65, No. 228 / Monday, November 27, 2000 / Rules and Regulations 70649

operators is estimated to be $18,180, or

$60 per airplane, per inspection cycle.

It will take approximately 2 work

hours per airplane to accomplish the

required repetitive NDT inspections, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the required NDT inspections

on U.S. operators is estimated to be

$36,360, or $120 per airplane, per

inspection cycle.

Should an operator be required or

elect to accomplish the terminating

modification, it will take approximately

92 work hours per airplane (46 work

hours per flap), at an average labor rate

of $60 per hour. Required parts will cost

$7,362 per airplane ($3,681 per flap).

Based on these figures, the cost impact

of the terminating modification on U.S.

operators is estimated to be $12,882 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

removing amendment 39–9891 (62 FR

3209, January 22, 1997), and by adding

a new airworthiness directive (AD),

amendment 39–11992, to read as

follows:

2000–23–19 SAAB Aircraft AB: Amendment

39–11992. Docket 2000–NM–76–AD.

Supersedes AD 96–25–06 R1,

Amendment 39–9891.

Applicability: Model SAAB SF340A series

airplanes, manufacturer’s serial numbers

–004 through –159 inclusive; and SAAB

340B series airplanes, manufacturer’s serial

numbers –160 through –459 inclusive;

certificated in any category; on which any

flap assembly having part number (P/N)

7257800–501 through 508 inclusive, or

7257800–851 through 7257800–856

inclusive, 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 (d) 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 high bearing stress on the

bushings in the flap fittings, which could

result in jamming of the flaps and consequent

reduced controllability of the airplane,

accomplish the following:

Visual Inspection for Serial Numbers

(a) Within 800 flight hours after the

effective date of this AD, perform a one-time

visual inspection of the flap assemblies of the

flap fittings at wing station (WS) 123.38 to

determine the flap assembly serial numbers,

in accordance with Saab Service Bulletin

340–57–035, dated January 18, 2000.

(1) If none of the serial numbers of the flap

assemblies are listed in the service bulletin,

no further action is required by this

paragraph.

(2) If the serial number of any flap

assembly is listed in the service bulletin,

prior to further flight, accomplish the

requirements of paragraph (a)(2)(i) and, at the

time specified, accomplish the requirements

of paragraph (a)(2)(ii) of this AD.

General Visual Inspection, Non-Destructive

Test (NDT) Inspection, and Replacement of

Bolts and Bushings

(i) Perform a general visual inspection of

the affected flap fittings at WS 123.38 to

detect cracking, in accordance with the

service bulletin. If no cracking is detected,

repeat the visual inspection thereafter at

intervals not to exceed 800 flight hours, until

the requirements of paragraph (a)(2)(ii) of this

AD are accomplished. If any cracking is

detected, prior to further flight, accomplish

the terminating action specified by paragraph

(c) of this AD.

(ii) Within 4,800 flight hours after the

effective date of this AD, perform a one-time

detailed visual inspection of the flap fittings

to determine the size of the inboard and

outboard holes (swaged bushing) and to

detect loose swaged bushings; and perform

an NDT inspection of the aft attachment lugs

of the flap assemblies at WS 123.38 to detect

cracking, in accordance with the service

bulletin. Accomplishment of the NDT

inspection terminates the general visual

inspection required by paragraph (a)(2)(i) of

this AD.

Note 2: For the purpose of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Note 3: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as

mirrors, magnifying lenses, etc., may be used.

Surface cleaning and elaborate access

procedures may be required.’’

(A) If all the hole sizes are within the limits

specified by the service bulletin, no loose

swaged bushings are found, and no cracking

of the aft attachment lugs is detected: Prior

to further flight, install new fasteners that

attach to the flap hinges (nuts, bolts, bushing,

and washers), in accordance with the service

bulletin.

(B) If any hole size is outside the limits

specified by the service bulletin, or any loose

swaged bushing is found, or any cracking is

70650 Federal Register / Vol. 65, No. 228 / Monday, November 27, 2000 / Rules and Regulations

detected on the aft attachment lugs: Prior to

further flight, accomplish the terminating

action specified in paragraph (c) of this AD.

Visual Inspection for Modification Status

(b) Within 800 flight hours after the

effective date of this AD, perform a one-time

visual inspection of the aft attachment lugs

(flap assemblies) of the flap fittings at wing

station (WS) 123.38 to determine the flap

assembly modification status, in accordance

with Saab Service Bulletin 340–57–037,

dated January 18, 2000.

(1) If the modification status is such that

all flap assemblies installed have thicker

lugs, as specified by Figure 1 of the service

bulletin, no further action is required by this

paragraph.

(2) If the modification status is such that

any flap assembly installed has a thinner lug,

as specified by Figure 1 of the service

bulletin, prior to further flight, accomplish

the requirements of paragraph (b)(2)(i) and, at

the time specified, accomplish the

requirements of paragraph (b)(2)(ii) of this

AD.

Visual Inspection and NDT Inspection

(i) Perform a general visual inspection of

the aft attachment lugs of the flap fittings at

WS 123.38 to detect cracking or damage, in

accordance with the service bulletin. If no

cracking or damage is detected during the

visual inspection, repeat the inspection

thereafter at intervals not to exceed 800 flight

hours, until the requirements of paragraph

(b)(2)(ii) of this AD are accomplished. If any

cracking or damage is detected during any

general visual inspection required by this

paragraph, prior to further flight, accomplish

the terminating action specified by paragraph

(c) of this AD.

(ii) Within 6,000 flight cycles after the

effective date of this AD, perform an NDT

inspection of the aft attachment lug of the

flap fittings at WS 123.38 to detect cracking,

in accordance with the service bulletin.

Accomplishment of the NDT inspection

terminates the repetitive visual inspections

required by paragraph (b)(2)(i) of this AD. If

no cracking is detected, repeat the NDT

inspection thereafter at intervals not to

exceed 6,000 flight cycles, until the actions

specified by paragraph (c) are accomplished.

If any cracking is detected during any NDT

inspection required by this paragraph, prior

to further flight, accomplish the terminating

action specified by paragraph (c) of this AD.

Terminating Action

(c) Replacement of all flap fittings at WS

123.38 with new, improved flap fittings in

accordance with Saab Service Bulletin 340–

57–038, dated January 18, 2000, terminates

all inspections required by this AD.

Alternative Methods of Compliance

(d) 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 4: 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

(e) 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

(f) The actions shall be done in accordance

with Saab Service Bulletin 340–57–035,

dated January 18, 2000; Saab Service Bulletin

340–57–037, dated January 18, 2000; and

Saab Service Bulletin 340–57–038, dated

January 18, 2000; as applicable. 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 5: The subject of this AD is addressed

in Swedish airworthiness directives No. 1–

152 and No. 1–153, each dated January 19,

2000.

Effective Date

(g) This amendment becomes effective on

January 2, 2001.

Issued in Renton, Washington, on

November 9, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29375 Filed 11–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–333–AD; Amendment

39–11995; AD 2000–23–22]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–10, –20, –30, –40,

and –50 Series Airplanes, and C–9

(Military) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–9–10, –20, –30, –40,

and –50 series airplanes and C–9

(military) airplanes, that currently

requires a one-time visual inspection to

determine if the doorstops and corners

of the doorjamb of the forward

passenger door have been modified,

various follow-on repetitive inspections,

and modification, if necessary. This

amendment requires a reduction in the

inspection threshold and repetitive

intervals for a certain doubler

configuration and an increase in the

grace period for a certain other doubler

configuration. This amendment is

prompted by a determination that

certain inspection compliance times

were incorrect. The actions specified by

this AD are intended to detect and

correct fatigue cracking, which could

result in rapid decompression of the

fuselage and consequent reduced

structural integrity of the airplane.

DATES: Effective January 2, 2001.

The incorporation by reference of

McDonnell Douglas Service Bulletin

DC9–53–280, Revision 02, dated July 26,

1999, as listed in the regulations, is

approved by the Director of the Federal

Register as of January 2, 2001.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of January 22, 1999 (63 FR

70005, December 18, 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 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:

Wahib Mina, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712–4137; telephone (562)

627–5324; fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–26–09,

amendment 39–10949 (63 FR 70005,

December 18, 1998), which is applicable