Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations 63537

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: Compliance with this AD is

required as indicated, unless already done.

To prevent the static seal from moving

forward, which could result in contact

between the seal face and stage 2 HPT rotor,

wear, and the possibility of an uncontained

failure of the stage 2 HPT rotor, do the

following:

(a) Remove support assembly, P/N

3050860–2, –3, –5 through –9, and replace it

with a serviceable seal assembly in

accordance with the Accomplishment

instructions 2.A.(3) through 2.A.(8)(d) and

2.B.(1) through 2.B.(3) of ASB CFE738 A72–

8042, Revision 1, dated September 25, 2000,

as follows:

Engines That Have Already Been Inspected

(1) For engines that have been inspected

using CFE Company alert service bulletin

(ASB) ASB CFE738 A72–8041, dated August

21, 2000, replace the support assembly as

follows:

Operating hours time-since new (TSN) on the effective

date of this AD Replace by the earlier of—

Fewer than 500 hours TSN ............................................... 150 hours time-in-service (TIS) or 90 days after the effective date of this AD.

500 hours to 1,000 hours TSN .......................................... 250 hours TIS or 150 days after the effective date of this AD.

More than 1,000 hours TSN .............................................. 400 hours TIS or 240 days after the effective date of this AD.

Engines That Have Not Been Inspected

(2) For engines that have not been

inspected using CFE Company alert service

bulletin (ASB) ASB CFE738 A72–8041, dated

August 21, 2000, do EITHER of the following

within the earlier of 50 hours TIS or 30 days

after the effective date of this AD:

(i) Replace the support assembly with a

serviceable support assembly in accordance

with the Accomplishment instructions

2.A.(3) through 2.A.(8)(d) and 2.B.(1) through

2.B.(3) of ASB CFE738 A72–8042, and 2.A.

or 2.B. of SB CFE738–72–8043, Revision 1,

dated October 2, 2000;

(ii) Inspect the engine in accordance with

the Accomplishment Instructions 2.A.

through 2.B.(6) of ASB CFE738–A72–8041,

dated August 21, 2000, and then replace the

support assembly in accordance with the

replacement schedule in paragraph (a)(1) of

this AD.

Support Assembly Seal Break-In

(b) After the seal has been replaced, do the

support assembly seal break-in procedure in

accordance 2.A. (test cell) or 2.B. (on wing)

of SB CFE738–72–8043, Revision 1, dated

October 2, 2000.

Definition of a Serviceable Part

(c) For the purposes of this AD, a

serviceable support assembly is defined as a

support assembly with P/N 3050860–10, or

–11, P/N 3057005–1 through –5 inclusive, or

P/N 3057006–1, or –2.

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, Engine

Certification Office (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

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.

Documents That Have Been Incorporated by

Reference

(f) The actions specified in this AD must

be done in accordance with the following

CFE Company service bulletins:

Document No. Pages Revision Date

ASB CFE738–A72–8041 ...................................................................... All ............................... Original ....................... August 21, 2000.

Total pages: 26.

ASB CFE738–A72–8042 ...................................................................... All ............................... 1 ................................. September 25, 2000.

Total pages: 22.

SB CFE738–72–8043 ........................................................................... All ............................... 1 ................................. October 2, 2000.

Total pages: 28.

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 CFE Company, Data Distribution, MS

64–03/2101–201, P.O. Box 52170, Phoenix,

AZ 85972–2170; telephone (602) 365–2493,

fax (602) 365–5577. Copies may be inspected

at the FAA, New England Region, Office of

the Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700, Washington,

DC.

Effective Date of This AD

(g) This amendment becomes effective on

November 8, 2000.

Issued in Burlington, Massachusetts, on

October 16, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–26972 Filed 10–23–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–48–AD; Amendment

39–11940; AD 2000–21–08]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Pratt & Whitney

JT8D series turbofan engines, that

63538 Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations

currently requires revisions to the Time

Limits Section (TLS) of the JT8D

Turbofan Engine Manual to include

required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure. This action

adds additional critical life-limited parts

for enhanced inspection. This

amendment is prompted by focused

inspection procedures that have been

developed by the manufacturer for

additional critical life-limited parts. The

actions specified by this AD are

intended to prevent critical life-limited

rotating engine part failure, which could

result in an uncontained engine failure

and damage to the airplane.

DATES: Effective date April 23, 2001.

ADDRESSES: The information referenced

in this AD may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA 01803;

or at the Office of the Federal Register,

800 North Capitol Street, NW, suite 700,

Washington, DC 20001.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803; telephone: 781–

238–7175, fax: 781–238-7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–12–03,

Amendment 39–11187 (64 FR 30379,

June 8, 1999), which is applicable to

Pratt & Whitney (PW) JT8D turbofan

engines, was published in the Federal

Register on June 8, 1999 (64 FR 30379).

That action proposed to require

revisions to the Time Limits Section

(TLS) of the PW JT8D–1, –1A, –1B, –7,

–7A, –7B, –9, –9A, –11, –15, –15A, –17,

–17A, –17R, and –17AR series Turbofan

Engine Manual to include required

enhanced inspection of selected critical

life-limited parts at each piece-part

exposure.

Since the issuance of that AD,

additional focused inspection

procedures for other critical life-limited

rotating engine parts have been

developed by PW.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the four

comments received.

Request To Extend the Comment Period

One commenter requests that the FAA

extend the NPRM comment period

because the required procedures had not

been published in the engine manual

(EM). The FAA does not agree. The FAA

believes that the nature and scope of the

added inspections will not be

significantly different from existing

inspections. In addition, the effective

date of this AD has been extended to

180 days after publication to allow time

for the specific procedures to be

published. The extra time until the AD

becomes effective should also allow the

manufacturer to issue a manual

revision. Operators may submit

comments to the docket file on the

specific procedures, once they are

published, and the FAA will consider

extending the effective date further or

additional rulemaking, as necessary.

The FAA does not believe, however,

that this final rule need be delayed

pending the publication of the

inspection procedures, or the initial

compliance time extended to

accommodate the manufacturer’s

manual revision cycle.

Request To Remove Part Numbers

One commenter requests that the FAA

remove the part numbers from the

proposed AD. The commenter feels that

the part numbers are unnecessary and

that eliminating them will minimize the

administrative burden on the operators.

The FAA does not agree. The current

structure of the JT8D engine manual

does not lend itself to reference ‘‘all’’

part numbers, as does the structure of

other engine lines. However, the FAA

will discuss with Pratt and Whitney the

possibility of converting the engine

manual to incorporate the simpler

approach in future supersedures of the

JT8D enhanced inspection AD.

Request To Remove ‘‘of this chapter’’

From Paragraph (e)

One commenter requests that the FAA

remove the statement ‘‘of this chapter’’

from the first sentence of paragraph (e)

of this AD. The commenter feels that

removing the statement will improve

the clarity of the paragraph. The FAA

agrees. The statement ‘‘of this chapter’’

has been removed from the first

sentence of paragraph (e).

Request To Revise the Definition of

Piece-Part Level

One commenter requests that the FAA

revise the definition of piece-part level

to include a debladed high pressure disk

(HPT) disk that is still attached to the

HPT shaft. The commenter incorporates

an HPT blade management program that

does not require unbolting the disk from

the shaft. The FAA does not agree. The

engine manual inspections required for

an HPT disk at piece-part level do not

apply to the disk and shaft assembly.

The FAA recognizes the need to include

the disk and shaft assembly to the

critical inspection section and are

working with the manufacturer to

develop new inspection criteria. The

HPT disk and shaft assembly will be

considered in a future revision of this

enhanced inspection initiative.

Economic Analysis

No comments were received on the

economic analysis contained in the

proposed rules. Based on that analysis,

the FAA has determined that the annual

per engine cost of $60 does not create

a significant economic impact on small

entities.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order 13132, because it does 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. Accordingly, the

FAA has not consulted with state

authorities prior to publication of this

rule.

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, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations 63539

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 39–11187 (64 FR

30379, June 8, 1999) and by adding a

new airworthiness directive,

Amendment 39–11940, to read as

follows:

AD 2000–21–08 Pratt & Whitney:

Amendment 39–11940. Docket 98–ANE–

48–AD.

Applicability: Pratt & Whitney (PW) JT8D–

1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15,

–15A, –17, –17A, –17R, and –17AR series

turbofan engines, installed on but not limited

to Boeing 727 and 737 series, and McDonnell

Douglas DC–9 series airplanes.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 critical life-limited rotating

engine part failure, which could result in an

uncontained engine failure and damage to

the airplane, accomplish the following:

Inspections

(a) Within the next 30 days after the

effective date of this AD, revise the Time

Limits Section (TLS) of the JT8D–1, –1A,

–1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A,

–17, –17A, –17R, and –17AR series Turbofan

Engine Manual, and for air carrier operations

revise the approved continuous

airworthiness maintenance program, by

adding the following Critical Life Limited

Part Inspection:

‘‘A. Inspection Requirements:

(1) This section has the definitions for

individual engine piece-parts and the

inspection procedures which are necessary

when these parts are removed from the

engine.

(2) It is necessary to do the inspection

procedures of the piece-parts in Paragraph B

when:

(a) The part is removed from the engine

and disassembled to the level specified in

paragraph B; and

(b) The part has accumulated more than

100 cycles since the last piece part

inspection, provided that the part is not

damaged or related to the cause of its

removal from the engine.

(3) The inspections specified in this

section do not replace or make unnecessary

other recommended inspections for these

parts or other parts.

B. Parts Requiring Inspection:

Note: Piece-part is defined as any of the

listed parts with all the blades removed.

Description

Engine manual

Section Inspection

Hub (Disk), 1st Stage Compressor

491201 ...... 72–33–31 –02, –03, –04

496501 ...... 72–33–31 –02, –03, –04

504101 ...... 72–33–31 –02, –03, –04

515201 ...... 72–33–31 –02, –03, –04

594301 ...... 72–33–31 –02, –03, –04

640501 ...... 72–33–31 –02, –03, –04

640601 ...... 72–33–31 –02, –03, –04

743301 ...... 72–33–31 –02, –03, –04

749701 ...... 72–33–31 –02, –03, –04

749801 ...... 72–33–31 –02, –03, –04

750001 ...... 72–33–31 –02, –03, –04

750101 ...... 72–33–31 –02, –03, –04

778901 ...... 72–33–31 –02, –03, –04

791401 ...... 72–33–31 –02, –03, –04

791501 ...... 72–33–31 –02, –03, –04

791601 ...... 72–33–31 –02, –03, –04

791701 ...... 72–33–31 –02, –03, –04

791801 ...... 72–33–31 –02, –03, –04

806001 ...... 72–33–31 –02, –03, –04

806101 ...... 72–33–31 –02, –03, –04

817401 ...... 72–33–31 –02, –03, –04

844401 ...... 72–33–31 –02, –03, –04

845401 ...... 72–33–31 –02, –03, –04

848001 ...... 72–33–31 –02, –03, –04

848101 ...... 72–33–31 –02, –03, –04

Disk, 2nd Stage Compressor

482502 ...... 72–33–33 –02

502502 ...... 72–33–33 –02

520602 ...... 72–33–33 –02

570302 ...... 72–33–33 –02

570402 ...... 72–33–33 –02

678202 ...... 72–33–33 –02

730202 ...... 72–33–33 –02

730302 ...... 72–33–33 –02

730402 ...... 72–33–33 –02

740502 ...... 72–33–33 –02

745702 ...... 72–33–33 –02

745902 ...... 72–33–33 –02

746002 ...... 72–33–33 –02

746802 ...... 72–33–33 –02

760402 ...... 72–33–33 –02

760502 ...... 72–33–33 –02

807502 ...... 72–33–33 –02

500240201 72–33–33 –02

790832

(Disk assembly) .. 72–33–33 –02

Turbine Disk, First Stage With Integral

Shaft

481135 ...... 72–52–04 –03

Description

Engine manual

Section Inspection

494211 ...... 72–52–04 –03

500701 ...... 72–52–04 –03

516101 ...... 72–52–04 –03

529115 ...... 72–52–04 –03

538901 ...... 72–52–04 –03

544501 ...... 72–52–04 –03

544601 ...... 72–52–04 –03

544701 ...... 72–52–04 –03

553201 ...... 72–52–04 –03

558401 ...... 72–52–04 –03

565101 ...... 72–52–04 –03

565201 ...... 72–52–04 –03

565301 ...... 72–52–04 –03

578201 ...... 72–52–04 –03

579001 ...... 72–52–04 –03

HP Turbine Disk, First Stage, Separable

587501 ...... 72–52–02 –03

5006101–

01 .......... 72–52–02 –03

578001 ...... 72–52–02 –03

5005201–

01 .......... 72–52–02 –03

696801 ...... 72–52–02 –03

742501 ...... 72–52–02 –03

752401 ...... 72–52–02 –03

767601 ...... 72–52–02 –03

792801 ...... 72–52–02 –03

856501 ...... 72–52–02 –03

832201 ...... 72–52–02 –03

855701 ...... 72–52–02 –03

856401 ...... 72–52–02 –03

5003601–

01 .......... 72–52–02 –03

5003601–

021 ........ 72–52–02 –03

5004301–

01 .......... 72–52–02 –03

(b) Except as provided in paragraph (c) of

this AD, and notwithstanding contrary

provisions in 43.16 of the Federal Aviation

Regulations (14 CFR 43.16), these mandatory

inspections shall be performed only in

accordance with the TLS of the PW JT8D–1,

–1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15,

–15A, –17, –17A, –17R, and –17AR series

Turbofan Engine Manual.

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, Engine

Certification Office (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

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 aircraft to a

location where the requirements of this AD

can be accomplished.

63540 Federal Register / Vol. 65, No. 206 / Tuesday, October 24, 2000 / Rules and Regulations

Continuous Airworthiness Maintenance

Program

(e) FAA-certificated air carriers that have

an approved continuous airworthiness

maintenance program in accordance with the

record keeping requirement of 121.369 (c) of

the Federal Aviation Regulations (14 CFR

121.369 (c)) must maintain records of the

mandatory inspections that result from

revising the TLS of the PW JT8D–1, –1A,

–1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A,

–17, –17A, –17R, and –17AR series Turbofan

Engine Manual, and the air carrier’s

continuous airworthiness program.

Alternately, certificated air carriers may

establish an approved system of record

retention that provides a method for

preservation and retrieval of the maintenance

records that include the inspections resulting

from this AD, and include the policy and

procedures for implementing this alternate

method in the air carrier’s maintenance

manual required by 121.369 (c) of the Federal

Aviation Regulations (14 CFR 121.369 (c));

however, the alternate system must be

accepted by the appropriate PMI and require

the maintenance records be maintained

either indefinitely or until the work is

repeated. Records of the piece-part

inspections are not required under 121.380

(a)(2)(vi) of the Federal Aviation Regulations

(14 CFR 121.380 (a)(2)(vi)). All other

operators must maintain the records of

mandatory inspections required by the

applicable regulations governing their

operations.

Note 3: The requirements of this AD have

been met when the engine manual changes

are made and air carriers have modified their

continuous airworthiness maintenance plans

to reflect the requirements in the PW JT8D–

1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15,

–15A, –17, –17A, –17R, and –17AR series

Turbofan Engine Manual.

(f) This amendment becomes effective on

April 23, 2001.

Issued in Burlington, Massachusetts, on

October 16, 2000.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–26971 Filed 10–23–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–43–AD; Amendment

39–11939; AD 2000–21–07]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D–200 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Pratt & Whitney

JT8D–200 series turbofan engines, that

currently requires revisions to the Time

Limits Section (TLS) of the JT8D–200

Turbofan Engine Manual to include

required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure. This AD adds

additional critical life-limited parts for

enhanced inspection. This proposal is

prompted by additional focused

inspection procedures that have been

developed by the manufacturer. The

actions specified by this proposed AD

are intended to prevent critical lifelimited rotating engine part failure,

which could result in an uncontained

engine failure and damage to the

airplane.

DATES: Effective date April 23, 2001.

ADDRESSES: The information referenced

in this AD may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803; telephone 781–

238–7175, fax 781–238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–12–04,

Amendment 39–11188 (64 FR 30382,

June 8, 1999), which is applicable to

Pratt & Whitney (PW) JT8D–200

turbofan engines, was published in the

Federal Register on October 7, 1999 (64

FR 54598). to require revisions to the

Time Limits Section (TLS) of the PW

JT8D–200 series Turbofan Engine

Manual to include required enhanced

inspection of selected critical lifelimited parts at each piece-part

exposure.

Since the issuance of that AD,

additional focused inspection

procedures for other critical life-limited

rotating engine parts have been

developed by PW.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Request To Extend the Comment Period

One comment requests that the FAA

extend the NPRM comment period

because the required procedures had not

been published in the engine manual

(EM). The FAA does not agree.

The FAA believes that the nature and

scope of the added inspections will not

be significantly different from existing

inspections. In addition, the effective

date of this AD has been extended to

180 days after publication to allow time

for the specific procedures to be

published. The extra time until the AD

becomes effective should also allow the

manufacturer to issue a manual

revision. Operators may submit

comments to the docket file on the

specific procedures, once they are

published, and the FAA will consider

extending the effective date further or

additional rulemaking, as necessary.

The FAA does not believe, however,

that this final rule need be delayed

pending the publication of the

inspection procedures, or the initial

compliance time extended to

accommodate the manufacturer’s

manual revision cycle.

Request to Remove Part Numbers

One comment requests that the FAA

remove the part numbers from the

proposed AD. The commenter states

that the part numbers are unnecessary,

and eliminating them will minimize the

administrative burden on the operators.

The FAA does not agree. The current

structure of the JT8D–200 engine

manual does not lend itself to reference

‘‘all’’ part numbers as does the structure

of other engine lines. However, the FAA

will discuss the possibility of converting

the engine manual to incorporate the

simpler approach in future supersedures

of the JT8D–200 enhanced inspection

AD.

No comments were received on the

economic analysis contained in the

proposed rules. Based on that analysis,

the FAA has determined that the annual

per engine cost of $60 does not create

a significant economic impact on small

entities.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

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