Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations 37851

repair in accordance with a method approved

by the Manager, Seattle ACO, FAA, Transport

Airplane Directorate; or in accordance with

data meeting the type certification basis of

the airplane approved by a Boeing Company

DER who has been authorized by the

Manager, Seattle ACO, to make such

findings. For a repair method to be approved

by the Manager, Seattle ACO, as required by

this paragraph, the Manager’s approval letter

must specifically reference this AD.

Repetitive NDT Inspections and Repair:

Group 5

(d) For airplanes identified as Group 5

airplanes in Boeing Alert Service Bulletin

747–54A2184, Revision 1, dated May 6, 1999:

Prior to the accumulation of 8,000 total flight

cycles, or within 90 days after the effective

date of this AD, whichever occurs later,

perform an NDT inspection of the aft torque

bulkheads of the number 1 and number 4

nacelle struts to detect fatigue cracking. The

NDT inspection shall be accomplished in

accordance with Part II of the

Accomplishment Instructions of the alert

service bulletin.

Note 5: The alert service bulletin refers to

a variety of NDT inspections, consisting of

ultrasonic inspections, surface eddy current

inspections, and open-hole eddy current

inspections. The logic diagram in Figure 1 of

the alert service bulletin states the conditions

under which each of these inspections is to

be performed.

(1) If no cracking is found, repeat the

inspection thereafter at the intervals

specified in Figure 1 of the alert service

bulletin.

(2) If any cracking is found, prior to further

flight, repair in accordance with Part III of

the alert service bulletin. Repeat the

inspection thereafter at the intervals

specified in Figure 1 of the alert service

bulletin. Where the alert service bulletin

specifies that the manufacturer may be

contacted for disposition of certain repair

conditions, repair in accordance with a

method approved by the Manager, Seattle

ACO; or in accordance with data meeting the

type certification basis of the airplane

approved by a Boeing Company DER who has

been authorized by the Manager, Seattle

ACO, to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the Manager’s approval letter must

specifically reference this AD.

Terminating Action: Groups 1, 2, and 5

(e) For airplanes identified as Group 1, 2,

and 5 airplanes in Boeing Alert Service

Bulletin 747–54A2184, Revision 1, dated

May 6, 1999: At the time specified in

paragraph (e)(1), (e)(2), or (e)(3), as

applicable, accomplish the terminating

action (installation of doublers and fillers on

the forward side of the lower spar fitting) in

accordance with the alert service bulletin.

Accomplishment of this paragraph

constitutes terminating action for the

repetitive inspections required by this AD.

Note 6: There is an error in Item 3.A.5.c.

under ‘‘Part 4—Terminating Action’’ in the

Accomplishment Instructions of Boeing Alert

Service Bulletin 747–54A2184, Revision 1.

The words, ‘‘as shown by Figure 11,’’ should

read ‘‘as shown by Figure 12.’’

(1) For airplanes in Groups 1, 2, and 5 on

which the interim repair described in Part 3

of the Accomplishment Instructions of the

alert service bulletin has NOT been

accomplished; and Groups 1 and 2 airplanes

on which the requirements of AD 95–13–05,

amendment 39–9285, have NOT been

accomplished: Accomplish the terminating

action prior to the accumulation of 8,000

total flight cycles or within 5 years after the

effective date of this AD, whichever occurs

later.

(2) For airplanes in Groups 1, 2, and 5 on

which the interim repair described in Part 3

of the Accomplishment Instructions of the

alert service bulletin HAS been

accomplished: Accomplish the terminating

action within 3,000 flight cycles after

accomplishment of the interim repair, or

within 18 months after the effective date of

this AD, whichever occurs later.

(3) For airplanes in Groups 1 and 2 on

which the requirements of AD 95–13–05,

amendment 39–9285, HAVE been

accomplished: Accomplish the terminating

action within 8,000 flight cycles after

accomplishment of the requirements of AD

95–13–05, amendment 39–9285, or within 5

years after the effective date of this AD,

whichever occurs later.

Alternative Methods of Compliance

(f)(1) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

(2) Alternative methods of compliance,

approved previously in accordance with AD

99–05–06, amendment 39–11054, are

approved as alternative methods of

compliance with this AD.

Note 7: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(g) Special flight permits may be issued in

accordance with §§ 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

(h) Except as provided in paragraphs (a)(2),

(b)(2), (c)(2), and (d)(2) of this AD, the actions

shall be done in accordance with Boeing

Alert Service Bulletin 747–54A2184, dated

July 3, 1997, or Boeing Alert Service Bulletin

747–54A2184, Revision 1, dated May 6, 1999.

(1) The incorporation by reference of

Boeing Alert Service Bulletin 747–54A2184,

Revision 1, dated May 6, 1999, is approved

by the Director of the Federal Register, in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51.

(2) The incorporation by reference of

Boeing Alert Service Bulletin 747–54A2184,

dated July 3, 1997, was approved previously

by the Director of the Federal Register as of

March 18, 1999 (64 FR 10205, March 3,

1999).

(3) Copies may be obtained from Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. 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.

(i) This amendment becomes effective on

July 5, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15181 Filed 6–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–25–AD; Amendment

39–11792; AD 2000–12–14]

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 adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that requires a one-time

inspection to detect chafing of the wires

and harnesses in the cabin compartment

ceiling; repair, if necessary; and

installation of protective sleeving. 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 false warnings of a hot engine

exhaust tailpipe and intermittent signal

failure, which could result in the

consequent execution of unnecessary

procedures by the flightcrew.

DATES: Effective July 24, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 24,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

37852 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations

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, 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) to

include an airworthiness directive (AD)

that is applicable to certain Saab Model

SAAB SF340A and SAAB 340B series

airplanes was published in the Federal

Register on April 24, 2000 (65 FR

21677). That action proposed to require

a one-time inspection to detect chafing

of the wires and harnesses in the cabin

compartment ceiling; repair, if

necessary; and installation of protective

sleeving.

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 288 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 36

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts for the sleeving

installation will cost approximately

$358 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$725,184, or $2,518 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.

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:

2000–12–14 SAAB Aircraft AB:

Amendment 39–11792. Docket 2000–

NM–25–AD.

Applicability: Model SAAB SF340A, serial

numbers –004 through –159 inclusive; and

SAAB 340B series airplanes, serial numbers

–160 through –459 inclusive; 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 false warning of a hot engine

exhaust tailpipe and intermittent signal

failure, the consequent execution of

unnecessary procedures by the flightcrew,

accomplish the following:

(a) Prior to the accumulation of 14,000 total

flight hours, or within 4,000 flight hours after

the effective date of this AD, whichever

occurs later: Perform a detailed visual

inspection to detect chafing of the wires and

harnesses in the cabin compartment ceiling,

and install protective sleeving on all of the

harnesses routed in the inspection area; in

accordance with Saab Service Bulletin 340–

92–027, dated December 10, 1999. Except as

provided by paragraph (b) of this AD, prior

to further flight, repair any chafing in

accordance with the service bulletin.

Note 2: 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 mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(b) For any chafing detected during the

inspection required by paragraph (a) of this

AD for which the service bulletin specifies to

contact Saab for appropriate action: Prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Luftfartsverket (LFV) (or its delegated agent).

For a repair method to be approved by the

Manager, International Branch, ANM–116, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

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 3: 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 §§ 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.

Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations 37853

Incorporation by Reference

(e) Except as provided by paragraph (b) of

this AD, the actions shall be done in

accordance with Saab Service Bulletin 340–

92–027, dated December 10, 1999. 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 4: The subject of this AD is addressed

in Swedish airworthiness directive 1–149,

dated December 10, 1999.

(f) This amendment becomes effective on

July 24, 2000.

Issued in Renton, Washington, on June 9,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15184 Filed 6–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–164–AD; Amendment

39–11789; AD 2000–12–11]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 series airplanes, that

currently requires repetitive ultrasonic

inspections to detect cracks in the bolt

holes inboard and outboard of rib 9 on

the bottom booms of the front and rear

wing spars, and repair, if necessary.

This amendment requires revising the

compliance thresholds for the

inspection and requires that the

inspections be repeated at reduced

intervals. 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 fatigue cracks in the

bolt holes of the wing spars, which

could result in reduced structural

integrity of a wing spar.

DATES: Effective July 24, 2000.

The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

Revision 1, dated August 31, 1995, as

listed in the regulations, is approved by

the Director of the Federal Register as of

July 24, 2000.

The incorporation by reference of

Airbus Service Bulletin A300–57–6037,

dated August 1, 1994, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

May 10, 1995 (60 FR 17990, April 10,

1995).

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 95–07–05,

amendment 39–9187 (60 FR 17990,

April 10, 1995), which is applicable to

certain Airbus Model A300–600 series

airplanes, was published in the Federal

Register on April 20, 2000 (65 FR

21157). The action proposed to continue

to require repetitive ultrasonic

inspections to detect cracks in the bolt

holes inboard and outboard of rib 9 on

the bottom booms of the front and rear

wing spars, and repair, if necessary. The

action also proposed to revise the

compliance thresholds for the

inspection and require that the

inspections be repeated at reduced

intervals.

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 75 airplanes

of U.S. registry that will be affected by

this AD.

The inspection that is currently

required by AD 95–07–05, and retained

in this AD, takes approximately 1 work

hour per airplane to accomplish

(excluding 10 work hours for access and

close-up), at an average labor rate of $60

per work hour. Based on this figure, the

cost impact of the currently required

inspection on U.S. operators is

estimated to be $4,500, or $60 per

airplane, per inspection cycle.

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.

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: