37848 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations

Service Bulletin A320–22–1068, dated

December 9, 1998; and Airbus Service

Bulletin A320–22–1069, dated February 1,

1999; as applicable.

(1) The incorporation by reference of

Airbus Service Bulletin A320–22–1063,

Revision 01, dated October 8, 1999; Airbus

Service Bulletin A320–22–1064, dated

September 15, 1998; Airbus Service Bulletin

A320–22–1065, dated October 28, 1998;

Airbus Service Bulletin A320–22–1067,

Revision 01, dated July 7, 1999; Airbus

Service Bulletin A320–22–1068, dated

December 9, 1998; and Airbus Service

Bulletin A320–22–1069, dated February 1,

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

Model A319/320/321 Flight Manual

Temporary Revision 4.03.00/02, dated May

28, 1997, was approved previously by the

Director of the Federal Register as of

November 3, 1997 (62 FR 53939, October 17,

1997).

(3) Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. 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 French airworthiness directive 1999–411–

140(B), dated October 20, 1999, and Revision

1, dated May 3, 2000.

(h) 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. 00–15182 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–78–AD; Amendment

39–11794; AD 2000–12–16]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747

series airplanes, that currently requires

repetitive inspections to detect fatigue

cracking or loose or missing fasteners of

the aft torque bulkheads of the outboard

nacelle struts; and repair, if necessary.

This amendment expands the

applicability of the existing AD to

include certain additional airplanes,

and removes certain other airplanes

from the applicability of the existing

AD. For all airplanes subject to this AD,

this amendment also requires

accomplishment of a new terminating

action. This action is necessary to

prevent fatigue cracking and loose or

missing fasteners in the aft torque

bulkheads of the outboard nacelle struts,

which could result in failure of an

outboard nacelle strut diagonal brace

load path and possible separation of the

nacelle from the wing. This action is

intended to address the identified

unsafe condition.

DATES: Effective July 5, 2000.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

54A2184, Revision 1, dated May 6,

1999, as listed in the regulations, is

approved by the Director of the Federal

Register as of July 5, 2000.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

54A2184, dated July 3, 1997, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of March 18, 1999 (64 FR

10205, March 3, 1999).

Comments for inclusion in the Rules

Docket must be received on or before

August 18, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000-NM–

78-AD, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays. Comments may also be sent

via the Internet using the following

address: 9-anm-iarcomment@faa.gov.

Comments sent via the Internet must

contain ‘‘Docket No. 2000–NM–78–AD’’

in the subject line and need not be

submitted in triplicate.

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 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.

FOR FURTHER INFORMATION CONTACT:

Tamara L. Anderson, Aerospace

Engineer, Airframe Branch, ANM–120S,

FAA, Transport Airplane Directorate,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On

February 22, 1999, the FAA issued AD

99–05–06, amendment 39–11054 (64 FR

10205, March 3, 1999), applicable to

certain Boeing Model 747 series

airplanes, to require repetitive

inspections to detect fatigue cracking or

loose or missing fasteners of the aft

torque bulkheads of the outboard

nacelle struts; and repair, if necessary.

That action was prompted by a report

indicating that cracking was found in

the aft torque bulkheads of the outboard

nacelle struts, and by the availability of

new service instructions for detecting

fatigue cracking that would not have

been detected by the required actions of

the existing AD. The requirements of

that AD are intended to detect and

correct such fatigue cracking and loose

or missing fasteners, which could result

in failure of an outboard nacelle strut

diagonal brace load path and possible

separation of the nacelle from the wing.

Explanation of Relevant Service

Information

Since the issuance of AD 99–05–06,

the FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

54A2184, Revision 1, dated May 6,

1999. The alert service bulletin

describes procedures for repetitive

inspections to detect fatigue cracking or

loose or missing fasteners of the aft

torque bulkheads of the outboard

nacelle struts; and repair, if necessary.

These procedures are substantially

similar to those described in Boeing

Alert Service Bulletin 747–54A2184,

dated July 3, 1997, which was

referenced in AD 99–05–06 as an

appropriate source of service

information for accomplishment of

certain requirements of that AD.

However, Revision 1 of the alert service

bulletin adds new airplanes (Group 5)

that are subject to the repetitive

inspections (and repair, if necessary)

described in the original issue of the

alert service bulletin and required by

AD 99–05–06. For certain airplanes (i.e.,

the airplanes listed in Groups 1, 2, and

5 of the alert service bulletin), the alert

service bulletin also describes

procedures for a terminating action that

eliminates the need for the repetitive

inspections described in the alert

service bulletin for affected airplanes.

The terminating action involves

installation of doublers and fillers on

the forward side of the lower spar

fitting. Accomplishment of the actions

specified in the alert service bulletin is

Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations 37849

intended to adequately address the

identified unsafe condition.

Explanation of Applicability of This AD

For airplanes listed in Groups 3 and

4 of the original issue of Boeing Alert

Service Bulletin 747–54A2184,

paragraph (c) of AD 99–05–06 describes

a detailed visual inspection to detect

fatigue cracking and loose or missing

fasteners of the aft torque bulkheads of

the number 1 and number 4 nacelle

struts. For these airplanes in Groups 3

and 4, paragraph (d) of AD 99–05–06

states, ‘‘Accomplishment of the nacelle

strut modifications required in AD 95–

13–07, amendment 39–9287 [60 FR

33336, June 28, 1995] * * * constitutes

terminating action for the requirements

of this AD.’’ Paragraph (a) of AD 95–13–

07 requires accomplishment of the

nacelle strut modifications within 56

months after July 28, 1995 (the effective

date of that AD). Considering that the

compliance time for this modification

has now passed, the FAA finds that it

is unnecessary in this AD to continue to

reference the inspection and terminating

action for airplanes listed in Groups 3

and 4 of the alert service bulletin.

Therefore, paragraphs (c) and (d) of AD

99–05–06 have not been included in

this AD, and the applicability statement

of this AD has been revised to include

only airplanes listed in Groups 1, 2, and

5 of Revision 1 of the alert service

bulletin.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, this AD supersedes AD 99–

05–06 to continue to require repetitive

inspections to detect fatigue cracking or

loose or missing fasteners of the aft

torque bulkheads of the outboard

nacelle struts; and repair, if necessary.

This AD expands the applicability of the

existing AD to include certain

additional airplanes, and removes

certain other airplanes from the

applicability of the existing AD. For all

airplanes subject to this AD, this

amendment also requires

accomplishment of a new terminating

action. The actions are required to be

accomplished in accordance with the

alert service bulletin described

previously, except as discussed below.

Differences Between Alert Service

Bulletin and This AD

Operators should note that, although

the alert service bulletin specifies that

the manufacturer may be contacted for

disposition of certain repair conditions,

this AD requires the repair of those

conditions to be accomplished in

accordance with a method approved by

the FAA, or in accordance with data

meeting the type certification basis of

the airplane approved by a Boeing

Company Designated Engineering

Representative who has been authorized

by the FAA to make such findings.

In addition, the FAA has determined

that 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.’’ ‘‘Note 6’’ has been

included in this AD to clarify this error.

Cost Impact

None of the Model 747 series

airplanes affected by this action are on

the U.S. Register. All airplanes included

in the applicability of this rule currently

are operated by non-U.S. operators

under foreign registry; therefore, they

are not directly affected by this AD

action. However, the FAA considers that

this rule is necessary to ensure that the

unsafe condition is addressed in the

event that any of these subject airplanes

are imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 15 work hours to

accomplish the required inspections, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of these inspections would be

$900 per airplane.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 45 work hours to

accomplish the required terminating

action, at an average labor rate of $60

per work hour. Required parts would

cost approximately $8,166 per airplane.

Based on these figures, the cost impact

of the required terminating action on

U.S. operators would be $10,866 per

airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this rule by submitting

such written data, views, or arguments

as they may desire. Communications

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–78–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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

37850 Federal Register / Vol. 65, No. 118 / Monday, June 19, 2000 / Rules and Regulations

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 39–11054 (64 FR

10205, March 3, 1999), and by adding a

new airworthiness directive (AD)

amendment 39–11794, to read as

follows:

2000–12–16 Boeing: Amendment 39–11794.

Docket 2000–NM–78–AD. Supersedes

AD 99–05–06, Amendment 39–11054.

Applicability: Model 747 series airplanes;

as listed in Groups 1, 2, and 5 of Boeing Alert

Service Bulletin 747–54A2184, Revision 1,

dated May 6, 1999; 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 (f)(1) 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 cracking and loose or

missing fasteners in the aft torque bulkheads

of the outboard nacelle struts, which could

result in failure of an outboard nacelle strut

diagonal brace load path and possible

separation of the nacelle from the wing,

accomplish the following:

Restatement of Requirements of AD 99–05–

06

Repetitive Detailed Visual Inspections and

Repair: Groups 1 and 2

(a) For airplanes identified as Groups 1 and

2 airplanes in Boeing Alert Service Bulletin

747–54A2184, dated July 3, 1997: Prior to the

accumulation of 8,000 total flight cycles, or

within 8,000 flight cycles since modification

in accordance with AD 95–13–05,

amendment 39–9285, or within 30 days after

March 18, 1999 (the effective date of AD 99–

05–06, amendment 39–11054), whichever

occurs latest, perform a detailed visual

inspection of the aft torque bulkheads of the

number 1 and number 4 nacelle struts to

detect fatigue cracking and loose or missing

fasteners. The inspection shall be

accomplished in accordance with Part I of

the Accomplishment Instructions of Boeing

Alert Service Bulletin 747–54A2184, dated

July 3, 1997, or Revision 1, dated May 6,

1999.

Note 2: There is a typographical error on

Sheet 3 of Figure 1 of Boeing Alert Service

Bulletin 747–54A2184, dated July 3, 1997.

The words ‘‘Group 1 airplanes’’ should read

‘‘Groups 1 and 2 airplanes.’’

(1) If no cracking, and no loose or missing

fastener, is found, repeat the inspection

thereafter at the intervals specified in Figure

1 of the alert service bulletin.

(2) If any cracking, or any loose or missing

fastener, 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

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 Aircraft Certification

Office (ACO), FAA, Transport Airplane

Directorate; or in accordance with data

meeting the type certification basis of the

airplane approved by a Boeing Company

designated engineering representative (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:

Groups 1 and 2

(b) For airplanes identified as Groups 1 and

2 airplanes in Boeing Alert Service Bulletin

747–54A2184, dated July 3, 1997: Prior to the

accumulation of 8,000 total flight cycles, or

within 8,000 flight cycles since modification

in accordance with AD 95–13–05,

amendment 39–9285, or within 30 days after

March 18, 1999, whichever occurs latest,

perform a non-destructive test (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

Boeing Alert Service Bulletin 747–54A2184,

dated July 3, 1997, or Revision 1, dated May

6, 1999.

Note 3: 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.

New Requirements of This AD

Note 4: 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.’’

Repetitive Detailed Visual Inspections and

Repair: Group 5

(c) For airplanes identified as Group 5 of

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 a

detailed visual inspection of the aft torque

bulkheads of the number 1 and number 4

nacelle struts to detect fatigue cracking and

loose or missing fasteners. The inspection

shall be accomplished in accordance with

Part I of the Accomplishment Instructions of

the alert service bulletin.

(1) If no cracking, and no loose or missing

fastener, is found, repeat the inspection

thereafter at the intervals specified in Figure

1 of the alert service bulletin.

(2) If any cracking, or any loose or missing

fastener, 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

service bulletin specifies that the

manufacturer may be contacted for

disposition of certain repair conditions,

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,