Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations 70781

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:

000–23–24 Saab Aircraft AB:

Amendment 39–11997. Docket 2000–NM–

221–AD.

Applicability: Model SAAB 2000 series

airplanes, certificated in any category, having

serial numbers –004 through –063 inclusive.

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 (b) 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 separation of the self-seal

couplings, which could result in loss of

engine oil pressure and a flight-crewcommanded engine shutdown, accomplish

the following:

Inspection, Installation and Corrective

Actions

(a) Within 3 months after the effective date

of this AD, perform a one-time general visual

inspection to ensure correct installation of

the air-cooled oil cooler (ACOC) self-seal

couplings in each nacelle, and install a new

clamp to the self-seal couplings, in

accordance with Saab Service Bulletin 2000–

79–005, dated May 22, 2000. If any coupling

is installed incorrectly, prior to further flight,

perform the corrective actions specified in

the service bulletin in accordance with the

procedures specified in the service bulletin.

Note 2: For the purposes 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.’’

Alternative Methods of Compliance

(b) 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

(c) 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

(d) The actions shall be done in accordance

with Saab Service Bulletin 2000–79–005,

dated May 22, 2000. 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,

Link&o ̈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 1–158,

dated May 23, 2000.

Effective Date

(e) This amendment becomes effective on

January 2, 2001.

Issued in Renton, Washington, on

November 14, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29604 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–353–AD; Amendment

39–11998; AD 2000–23–25]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, 747–200, 747–300,

747SP, and 747SR Series Airplanes

Powered by Pratt & Whitney JT9D–3

and JT9D–7 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 747–

100, 747–200, 747–300, 747SP, and

747SR series airplanes powered by Pratt

& Whitney JT9D–3 or JT9D–7 series

engines. This action requires

inspections of the vertical chords of the

aft torque bulkhead of the outboard

nacelle struts, and corrective action, if

necessary. This action also provides

optional terminating action for the

inspections. This action is necessary to

detect and correct cracking of the

vertical chords adjacent to the lower

spar fitting, which could result in

separation of the diagonal brace load

path. Continued operation with a

separated diagonal brace load path

increases loads on the upper link,

midspar fitting, and dual side links,

which could result in separation of the

strut and engine from the airplane. This

action is intended to address the

identified unsafe condition.

DATES: Effective December 13, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

13, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 29, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

353–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmVerDate 11<MAY>2000 17:55 Nov 27, 2000 Jkt 194001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\28NOR1.SGM pfrm08 PsN: 28NOR1
70782 Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations

iarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–353–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

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 Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received numerous reports of fatigue

cracking of the vertical chords of the aft

torque bulkhead of the outboard nacelle

struts on certain Boeing Model 747–100,

747–200, 747–300, 747SR, and 747SP

series airplanes powered by Pratt &

Whitney JT9D–3 or JT9D–7 series

engines. The cracks have been found

adjacent to the lower spar fitting. Such

cracking of the vertical chords adjacent

to the lower spar fitting could result in

separation of the diagonal brace load

path. Continued operation with a

separated diagonal brace load path, if

not corrected, increases loads on the

upper link, midspar fitting, and dual

side links, which could result in

separation of the strut and engine from

the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

54A2201, dated September 28, 2000,

which describes procedures for

repetitive detailed visual, ultrasonic,

and surface eddy current inspections to

detect cracking of the vertical chords of

the aft torque bulkhead of the outboard

nacelle struts. The service bulletin also

describes procedures for a modification

that involves installation of doublers on

the vertical chords, which constitutes

terminating action for the repetitive

inspections.

The service bulletin provides for

deferment of the initial inspections if

Boeing Service Letter 747–SL–54–055,

dated April 24, 1998, has been

accomplished. That service letter

recommends accomplishment of

detailed visual and high frequency eddy

current inspections of the chords of the

aft torque bulkhead during modification

of the nacelle strut. The FAA finds that,

if the inspections recommended in

Boeing Service Letter 747–SL–54–055

were accomplished during the

modification of the nacelle strut and

wing in accordance with AD 95–10–16,

amendment 39–9233 (60 FR 27008, May

22, 1995), the initial inspections

required by this AD may be deferred

until 3,000 flight cycles after

accomplishment of Boeing Service

Letter 747–SL–54–055.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

detect and correct cracking of the

vertical chords adjacent to the lower

spar fitting, which could result in

separation of the diagonal brace load

path. This AD requires accomplishment

of the inspections specified in the

service bulletin described previously,

except as discussed below.

Interim Action

This is considered to be interim

action. The FAA is currently

considering requiring the modification

specified in the service bulletin, which

will constitute terminating action for the

repetitive inspections required by this

AD action. However, the planned

compliance time for the installation of

the modification is sufficiently long so

that notice and opportunity for prior

public comment will be practicable.

Difference Between Service Bulletin

and This AD

Operators should note that, although

the 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.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an 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–353–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.

Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Rules and Regulations 70783

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–23–25 Boeing: Amendment 39–11998.

Docket 2000–NM–353–AD.

Applicability: Model 747–100, 747–200,

747–300, 747SP, and 747SR series airplanes

powered by Pratt & Whitney JT9D–3 or JT9D–

7 series engines; listed in Boeing Alert

Service Bulletin 747–54A2201, dated

September 28, 2000; 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 (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 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 detect and correct cracking of the

vertical chords adjacent to the lower spar

fitting, which could result in separation of

the diagonal brace load path and lead to

separation of the strut and engine from the

airplane, accomplish the following:

Inspections

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

this AD, prior to the accumulation of 14,000

total flight cycles, or within 90 days after the

effective date of this AD, whichever occurs

later: Accomplish paragraphs (a)(1) and (a)(2)

of this AD.

(1) Perform a detailed visual inspection to

detect cracking of the vertical chords of the

aft torque bulkhead of the outboard nacelle

struts, in accordance with Part 2 of the

Accomplishment Instructions of Boeing Alert

Service Bulletin 747–54A2201, dated

September 28, 2000. Thereafter, repeat this

inspection at intervals not to exceed 600

flight cycles until paragraph (d) of this AD is

accomplished.

(2) Perform surface eddy current and

ultrasonic inspections to detect cracking of

the vertical chords of the aft torque bulkhead

of the outboard nacelle struts, in accordance

with Part 3 of the Accomplishment

Instructions of Boeing Alert Service Bulletin

747–54A2201, dated September 28, 2000.

Thereafter, repeat these inspections at

intervals not to exceed 1,200 flight cycles

until paragraph (d) of this AD is

accomplished.

Optional Compliance Time

(b) If Boeing Service Letter 747–54–055,

dated April 24, 1998, was accomplished on

the airplane during the modification of the

nacelle strut in accordance with AD 95–10–

16, amendment 39–9233: Accomplishment of

the initial inspection in paragraph (a) of this

AD may be deferred until 3,000 flight cycles

after accomplishment of the service letter.

Repair

(c) If any cracking is detected during any

inspection required by this AD: Prior to

further flight, repair in accordance with a

method approved by the Manager, Seattle

Aircraft Certification Office (ACO), 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 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 approval

letter must specifically reference this AD.

Optional Terminating Action

(d) Accomplishment of the modification

specified in Part 4 of Boeing Alert Service

Bulletin 747–54A2201, dated September 28,

2000, constitutes terminating action for the

repetitive inspections required by paragraph

(a) of this AD.

Alternative Methods of Compliance

(e) 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.

Note 2: 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

(f) 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

(g) Except as provided by paragraph (c) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–54A2201, dated September 28,

2000. 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 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.

Effective Date

(h) This amendment becomes effective on

December 13, 2000.

Issued in Renton, Washington, on

November 14, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29603 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–356–AD; Amendment

39–12004; AD 2000–23–31]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–82 (MD–82) and

DC–9–83 (MD–83) Series Airplanes,

and Model MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain McDonnell

Douglas Model DC–9–82 (MD–82) and

DC–9–83 (MD–83) series airplanes, and