13416 Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations

DC–8–31

DC–8–32

DC–8–33

DC–8–41

DC–8–42

DC–8–43

DC–8–51

DC–8–52

DC–8–53

DC–8–55

DC–8–61

DC–8–61F

DC–8–62

DC–8–62F

DC–8–63

DC–8–63F

DC–8F–54

DC–8F–55

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 the pitot lines from freezing,

which could result in erroneous or total loss

of airspeed indications to the flight crew, and

consequent loss of control of the airplane,

accomplish the following:

Modification

(a) Within 30 days after the effective date

of this AD, modify the flow control system

to reroute the bleed air ducts, in accordance

with National Aircraft Service, Inc., Service

Bulletin SB–98–01R1, dated January 26,

1999.

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, Chicago

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Chicago ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Chicago ACO.

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 National Aircraft Service, Inc., Service

Bulletin SB–98–01R1, dated January 26,

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 National Aircraft Service, Inc., 9133

Tecumseh-Clinton Road, Tecumseh,

Michigan 49286. Copies may be inspected at

the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Chicago Aircraft

Certification Office, 2330 East Devon

Avenue, Room 323, Des Plaines, Illinois; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date

(e) This amendment becomes effective on

March 21, 2001.

Issued in Renton, Washington, on February

22, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–4933 Filed 3–5–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–56–AD; Amendment 39–

12130; AD 2001–04–11]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT9D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Pratt & Whitney

(PW) JT9D series turbofan engines. This

amendment requires initial and

repetitive detailed eddy current

inspections for cracks in 1st stage high

pressure turbine (HPT) disks, and, if

necessary, replacement with serviceable

parts. This amendment is prompted by

the discovery of a crack in the web of

one cooling air hole on a 1st stage HPT

disk. The actions specified by this AD

are intended to prevent 1st stage HPT

disk cracking, which could result in an

uncontained engine failure and damage

to the aircraft.

DATES: Effective May 7, 2001. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of May 7, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone 860–565–

8770, fax 860–565–4503. This

information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

Wego Wang, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: 781–238–7134,

fax: 781–238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to

certain PW JT9D series turbofan engines

was published in the Federal Register

on March 7, 2000 (65 FR 11940). That

action proposed to require initial and

repetitive detailed eddy current

inspections for cracks in 1st stage HPT

disks, and, if necessary, replacement

with serviceable parts.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Rule as Proposed

Two commenters state their support

of the notice of proposed rulemaking

(NPRM) as written.

Economic Analysis Question

One commenter states that the cost

incurred due to premature engine

removal is not captured in the NPRM

economic analysis. This cost would

adversely impact operators when an

engine must be removed prematurely in

order to perform disk inspections. The

cost would specifically impact this

operator when an engine that is not

under its maintenance program is

acquired and is inducted into its system.

The FAA does not agree. The NPRM

cost analysis is based on the costs of

parts and labor to U.S. operators needed

to perform the required initial

inspections, and is not specific to any

particular maintenance system.

However, the economic analysis is

corrected to clarify that the cost totals

are for initial inspection only.

Two Types of Compliance Times

Two commenters state that the

NPRM’s proposed compliance times are

Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations 13417

inconsistent with the compliance times

referenced in PW Alert Service Bulletins

(ASB’s) JT9D A6376, dated July 28, 1999

and JT9D–7R4–A72–563, dated July 28,

1999. Specifically, for disks that have

had a prior fluorescent penetrant

inspection, the NPRM proposed

reinspections based on cycles-since-new

(CSN) intervals. The ASB’s, however,

require reinspections based on cyclesin-service (CIS) intervals.

The FAA agrees. The compliance is

corrected as follows:

• In the JT9D series engines section,

in paragraph (a)(4)(ii) and (a)(4)(iii), the

compliance time type is changed from

CSN to CIS.

• In the JT9D–7R4 series engines

section, in paragraph (b)(4)(ii) and

(b)(4)(iii), the compliance time type is

changed from CSN to CIS.

Incorrect Aircraft Model Applicability

One commenter states that under the

Applicability section in the NPRM, the

reference to Airbus Industrie A300

series aircraft is incorrect, and should

read Airbus Industrie A310 series

aircraft.

The FAA agrees. The Applicability

section is corrected in this amendment.

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.

Economic Analysis

There are approximately 330 engines

of the affected design in the worldwide

fleet. The FAA estimates that 220

engines installed on aircraft of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 4.5 work hours per

engine to accomplish the initial

inspection, and that the average labor

rate is $60 per work hour. Required

parts would cost approximately

$165,000 per engine. Based on these

figures, the total initial inspection cost

impact of the proposed AD on U.S.

operators is estimated to be $36,359,400.

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order 13132, because it would 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, 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:

2001–04–11, Pratt & Whitney: Amendment

39–12130. Docket No. 99–NE–56–AD.

Applicability: Pratt & Whitney (PW) JT9D–

7R4D, –7R4D1, –7R4E, –7R4E1 (AI–500), –7,

–7A, –7AH, –7H, –7F, and –20 series

turbofan engines, installed on but not limited

to Boeing 747 and 767 series, McDonnell

Douglas DC–10 series, and Airbus Industrie

A310 series aircraft.

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 1st stage high pressure turbine

(HPT) disk cracking, which could result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

JT9D Series

(a) For PW JT9D–7, –7A, –7AH, –7H, –7F,

and –20 series turbofan engines, with 1st

stage HPT disks, part numbers (P/Ns) 761401,

811401, 823401, 825601, 826001, and

826301:

Initial Inspection

(1) Perform the initial detailed eddy

current inspection (ECI) for cracks in

accordance with the Accomplishment

Instructions of PW Alert Service Bulletin

(ASB) No. JT9D A6367, dated July 28, 1999.

(2) Inspect at the following compliance

times, depending on whether parts have had

prior fluorescent penetrant inspections (FPI)

or not.

Initial Compliance Times

No Prior FPI

(3) The following are the initial compliance

times for parts that have had no prior FPI:

(i) For disks with more than 8,000 total

part cycles-since-new (CSN) on the effective

date of this AD, inspect within 250 cyclesin-service (CIS) after the effective date of this

AD.

(ii) For disks with at least 6,000 CSN

though no more than 8,000 total part CSN on

the effective date of this AD, inspect within

1,000 CIS after the effective date of this AD.

(iii) For disks with at least 4,000 CSN

though no more than 5,999 total part CSN on

the effective date of this AD, inspect within

2,000 CIS after the effective date of this AD.

(iv) For disks with less than 4,000 total part

CSN on the effective date of this AD, inspect

prior to accumulating 6,000 total part CSN.

Prior FPI Accomplished

(4) The following are the initial compliance

times for parts that have had a previous FPI:

(i) For disks with more than 8,000 CIS

since last FPI on the effective date of this AD,

inspect within 250 CIS after the effective date

of this AD.

(ii) For disks with at least 6,000 CIS though

no more than 8,000 CIS since last FPI on the

effective date of this AD, inspect within

1,000 CIS after the effective date of this AD.

(iii) For disks with at least 4,000 CIS

though no more than 5,999 CIS since last FPI

on the effective date of this AD, inspect

within 2,000 CIS after the effective date of

this AD.

(iv) For disks with less than 4,000 CIS

since last FPI on the effective date of this AD,

inspect prior to accumulating 6,000 CIS since

last FPI on the effective date of this AD.

Repetitive Inspections

(5) Thereafter, perform detailed ECI for

cracks:

(i) At intervals not to exceed 6,000 CIS

since last ECI.

(ii) Inspect in accordance with the

Accomplishment Instructions of PW ASB No.

JT9D A6367, dated July 28, 1999.

13418 Federal Register / Vol. 66, No. 44 / Tuesday, March 6, 2001 / Rules and Regulations

Cracked Disks

(6) Prior to further flight, replace cracked

disks with serviceable parts.

JT9D–7R4 Series

(b) For PW JT9D–7R4D, –7R4D1, –7R4E,

and –7R4E1 (AI–500) series turbofan engines,

with 1st stage HPT disks, P/N 825601:

Initial Inspection

(1) Perform the initial detailed ECI for

cracks in accordance with the

Accomplishment Instructions of PW ASB No.

JT9D–7R4–A72–563, dated July 28, 1999.

(2) Inspect at the following compliance

times, depending on whether parts have had

prior FPI or not.

Initial Compliance Times

No Prior FPI

(3) The following are the initial compliance

times for parts that have had no prior FPI:

(i) For disks with more than 10,000 total

part CSN on the effective date of this AD,

inspect within 250 CIS after the effective date

of this AD.

(ii) For disks with at least 8,000 CSN

though no more than 10,000 total part CSN

on the effective date of this AD, inspect

within 1,000 CIS after the effective date of

this AD.

(iii) For disks with at least 6,000 CSN

though no more than 7,999 total part CSN on

the effective date of this AD, inspect within

2,000 CIS after the effective date of this AD.

(iv) For disks with less than 6,000 total part

CSN on the effective date of this AD, inspect

prior to accumulating 8,000 total part CSN.

Prior FPI Accomplished

(4) The following are the initial compliance

times for parts that have had a previous FPI:

(i) For disks with more than 10,000 CIS

since last FPI on the effective date of this AD,

inspect within 250 CIS after the effective date

of this AD.

(ii) For disks with at least 8,000 CIS though

no more than 10,000 CIS since last FPI on the

effective date of this AD, inspect within

1,000 CIS after the effective date of this AD.

(iii) For disks with at least 6,000 CIS

though no more than 7,999 CIS since last FPI

on the effective date of this AD, inspect

within 2,000 CIS after the effective date of

this AD.

(iv) For disks with less than 6,000 CIS

since last FPI on the effective date of this AD,

inspect prior to accumulating 8,000 CIS since

last FPI on the effective date of this AD.

Repetitive Inspections

(5) Thereafter, perform detailed ECI for

cracks:

(i) At intervals not to exceed 8,000 CIS

since last ECI.

(ii) Inspect in accordance with the

Accomplishment Instructions of PW ASB No.

JT9D–7R4–A72–563, dated July 28, 1999.

Cracked Disks

(6) Prior to further flight, replace cracked

disks with serviceable parts.

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 request 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.

Ferry Flights

(d) 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 aircraft to

a location where the inspection requirements

of this AD can be accomplished.

Incorporation by Reference

(e) The actions required by this AD must

be done in accordance with the following

Pratt & Whitney Alert Service Bulletins:

Document No. Pages Revision Date

JT9D A6367 ........................................................... 1–12 Original ................................................................. July 28, 1999.

Total pages: 12.

JT9D–7R4–A72–563 ............................................. 1–37 Original ................................................................. July 28, 1999.

Total pages: 37.

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 Pratt & Whitney, 400 Main Street, East

Hartford, CT 06108; telephone: 860 565–

6600, fax: 860 565–4503. 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

(f) This amendment becomes effective on

May 7, 2001.

Issued in Burlington, Massachusetts, on

February 21, 2001.

David A. Downey,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 01–4890 Filed 3–5–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–38–AD; Amendment

39–12136; AD 2001–04–16]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company CF6–50 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to General Electric Company

(GE) CF6–50 series turbofan engines.

That AD currently requires visual

inspection of the stage 2 low pressure

turbine (LPT) nozzle lock assemblies,

and replacement of the borescope plug

with a new design plug.

This amendment is prompted by a

report of an uncontained engine failure

on an engine that had complied with the

current AD. This amendment requires

additional inspections and provides

interim and terminating corrective

actions. The actions specified in this AD

are intended to detect cracked, loose or

missing stage 2 LPT nozzle lock

assembly studs that could lead to failure

of the locks, nozzle segment rotation,

LPT case machining, and subsequent

uncontained failure of the engine. The

actions also provide for modifications of

nozzle lock assemblies if the nozzle lock

studs are found cracked, loose, or

missing.

DATES: Effective March 21, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 21,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

May 7, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,