69660 Federal Register / Vol. 65, No. 224 / Monday, November 20, 2000 / Rules and Regulations

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:

2000–22–21 McDonnell Douglas:

Amendment 39–11969. Docket 2000–

NM–345–AD.

Applicability: All Model DC–10, Model

MD–10, and Model MD–11 series airplanes;

certificated in any category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent continued arcing following a

short circuit of the fuel pump electrical

connector, which could damage the conduit

that protects the power lead inside the fuel

tank, and result in the creation of a potential

ignition source in the fuel tank, accomplish

the following:

Airplane Flight Manual (AFM) Revision

(Procedures Section)

(a) Within 14 days after the effective date

of this AD, insert applicable Interim

Operating Procedures regarding abnormal

operations for fuel pump electrical connector

failures into the Procedures Section of the

FAA-approved AFM, in accordance with

Boeing Flight Operations Bulletin DC–10–

00–01A, MD–11–00–03A, and MD–10–00–

02A, dated September 20, 2000.

Airplane Flight Manual Revision

(Limitations Section)

(b) For Model DC–10 and Model MD–11

series airplanes: Within 14 days after the

effective date of this AD, insert the following

information into the ‘‘Fuel Management’’

paragraph of the Limitations Section of the

FAA-approved AFM which may be

accomplished by inserting a copy of this AD

into the AFM.

‘‘Do not reset any tripped fuel pump circuit

breakers.’’

Note 1: If the information in paragraph (b)

of this AD is already in the ‘‘Fuel

Management’’ paragraph of the Limitations

Section of the AFM, no further action is

required by paragraph (b) of this AD.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office (ACO),

FAA. Operators shall submit their requests

through an appropriate FAA Principal

Operations Inspector, who may add

comments and then send it to the Manager,

Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

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

this AD, the AFM revision shall be done in

accordance with Boeing Flight Operations

Bulletin DC–10–00–01A, MD–11–00–03A,

and MD–10–00–02A, dated September 20,

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 Aircraft Group,

Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1-L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; at the FAA, Los

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

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

December 5, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28478 Filed 11–17–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–25–AD; Amendment 39–

11986; AD 2000–23–14]

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

JT9D series turbofan engines. This AD

will require installation of an improved

No. 4 bearing internal oil pressure tube,

initial and repetitive inspections of the

No. 4 bearing oil pressure tube for

turbine exhaust case (TEC) strut

clearance and alignment, and, if

necessary, replacement with serviceable

parts. This amendment is prompted by

loss of integrity in the oil system that

allows oil to migrate into high

temperature metal cavities in the

turbine exhaust case and cause oil fires.

The actions specified by this AD are

intended to prevent oil fires in and

around the No. 4 bearing area that could

cause excessive thermal growth of the

sixth stage low pressure turbine (LPT)

disk, liberation of the sixth stage LPT

disk, uncontained engine failure, and

damage to the airplane.

DATES: Effective date January 19, 2001.

The incorporation by reference of

certain publications listed in the rule is

approved by the Director of the Federal

Register as of January 19, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, 400 Main Street,

East Hartford, CT 06108; telephone:

(860) 565–6600, fax: (860) 565–4503.

This information may be examined at

the Federal Aviation Administration

(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:

Chris Gavriel, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: (781) 238–7147,

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

applicable to Pratt & Whitney (PW) JT9D

series turbofan engines was published

in the Federal Register on November 24,

1999 (64 FR 66118). That action

proposed to require installation of an

improved No. 4 bearing internal oil

pressure tube, initial and repetitive

inspections of the No. 4 bearing oil

pressure tube for TEC strut clearance

and alignment, and, if necessary,

replacement with serviceable parts, in

accordance with PW Service Bulletin

(SB) No. 5707, dated September 17,

1986, and in accordance with certain

sections of the PW JT9D Engine

Manuals: part numbers (P/Ns) 646028,

770407, 770408, 777210, 785059, and

754459.

Federal Register / Vol. 65, No. 224 / Monday, November 20, 2000 / Rules and Regulations 69661

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.

Reasons for This Modification and

Inspection Program

One commenter states that the reports

referenced in the NPRM focus only on

engine fires, not uncontained engine

failure and aircraft damage. Since the

commenter has been using a tube of a

design earlier to the one required by this

AD for a long time without incident, the

commenter requests that the FAA

confirm the reasons for the modification

and inspection program.

The FAA investigated the reports of

oil fires in and around the No. 4 bearing

area on the PW JT9D series turbofan

engines and concluded that the heat

generated by the oil fires could cause

excessive thermal growth of the sixth

stage LPT disk, liberation of the sixth

stage LPT disk, uncontained engine

failure, and damage to the airplane.

Applicability Section

One commenter requests the

modification of the applicability section

of the AD to specify the BG 700 series

of the JT9D–7R4D engines. The

applicability section of the NPRM

includes the JT9D–7R4D series engines.

The PW SB JT9D–7R4–72–289, dated

March 26, 1986, applies to the BG 700

series. The commenter has the JT9D–

7R4D (BG 900) series engines and would

like the applicability section of the AD

to reflect the BG 700 series.

The FAA agrees. The applicability

section has been changed accordingly.

Another commenter requests that the

list of aircraft on which the affected

engines may be installed be expanded to

include Airbus A300 airplanes. The

FAA agrees. The FAA will add Airbus

A300 airplanes to the list, but cautions

that this AD list is advisory in nature

and does not limit the applicability of

the AD to just those engines which are

installed on the listed airplanes.

Engine Manual Part Numbers

One commenter requests that

paragraph (b) reflect the JT9D–7A

engine manual P/N 770408. The

commenter also requests that the section

title of 72–53–01 of the JT9D–59A

engine manual, P/N 754459, be revised

to reflect ‘‘Heavy Maintenance Check’’

instead of ‘‘Inspection 01.’’

The FAA agrees. The engine manual

P/Ns listed in the NPRM contain all

engine models affected. However, the

engine manufacturer has issued modelspecific versions of these manuals.

Therefore, it is possible that the operator

may only have the model-specific

version of the manual and not the allencompassing engine manuals referred

to in this AD. Revised paragraph (b)

includes references to the modelspecific JT9D engine manuals and to

correct the reference to the title of

Section 72–53–01 of P/N 754459.

Inspection Interval

Another commenter requests that the

FAA weigh the benefits of conducting

frequent inspections against the

additional risks incurred by conducting

the inspections. The commenter also

states that it has not experienced an oil

pressure tube failure due to TEC strut

misalignment. The commenter

considers an inspection interval at each

heavy engine shop visit to be adequate,

as opposed to every time the ‘‘N’’ or ‘‘P’’

flange is separated.

Two commenters recommend that the

FAA replace the word ‘‘disconnected’’

with the word ‘‘separated.’’ The phrase

‘‘at the next time when the ‘‘N’’ or ‘‘P’’

flange is disconnected’’ occurs three

times in the AD. One of the commenters

suggests that since a flange is normally

separated, not disconnected, this

language may cause some confusion.

The FAA agrees in part. The FAA has

decided to change the definition of shop

visit to better reflect the original intent

of the inspection. The original intent

was that the inspections be performed

during a complete disassembly of the

TEC; this is the frequency interval

contained in the engine manuals. The

proposed language even if the

recommended change from

‘‘disconnected’’ to ‘‘separated’’ is made,

could still be perceived as a more

frequent inspection interval than that

intended by the FAA. Based on

comments received and further

coordination with the engine

manufacturer, the FAA has developed a

more precise definition. Therefore, the

FAA has revised the phrase, ‘‘at the next

time when the ‘‘N’’ or ‘‘P’’ flange is

disconnected,’’ to read: ‘‘at the next

turbine exhaust case disassembly when

all hardware is stripped from the case.’’

These inspections are required at the

same frequency contained in the engine

manuals.

Request for Confirmation of

Terminating Action

One commenter requests that the FAA

confirm if there is a terminating action

for the repetitive clearance and

alignment check in accordance with the

engine manual. The commenter

questions if replacement of the pressure

tube in accordance with PW SB 5707

and JT9D–7R4–72–289 constitutes the

terminating action.

The FAA does not agree. There is no

terminating action for this inspection.

The inspections are required to make

sure that there is sufficient tube

clearance and that the TEC strut is

aligned correctly. This inspection is an

integral part of maintaining the

airworthiness of this tube.

FAA’s Determination

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 2,310

engines of the affected design in the

worldwide fleet. Approximately 1,183

of these engines are installed on

airplanes of U.S. registry. Review of

purchase orders indicate that

approximately 1,547 pressure tubes

have been sold to the airlines; therefore

this action will affect no more than 763

engines. It will take approximately one

work hour per engine to accomplish the

proposed actions; the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,465 per

engine. Based on these figures, the total

cost impact of the proposed AD on U.S.

operators is estimated to be no more

than $1,163,575.

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 is

69662 Federal Register / Vol. 65, No. 224 / Monday, November 20, 2000 / Rules and Regulations

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–23–14 Pratt & Whitney: Amendment

39–11986. Docket No. 99–NE–25–AD.

Applicability: Pratt & Whitney (PW) JT9D–

3A, –7, –7A, –7AH, –7H, –7F, –7J, –7Q,

–7Q3, –20, –20J, –59A, –70A, and –7R4D (BG

700) series turbofan engines, installed on but

not limited to Boeing 747 and 767, Airbus

A300, and McDonnell Douglas DC–10 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 oil fires in and around the No.

4 bearing area, which could result in

excessive growth of the sixth stage low

pressure turbine (LPT) disk, liberation of the

sixth stage LPT disk, uncontained engine

failure, and damage to the airplane,

accomplish the following:

Installation of Improved Hardware

(a) At the next disassembly of the turbine

exhaust case (TEC) when all hardware is

stripped from the case after the effective date

of this AD, install an improved No. 4 bearing

internal oil pressure tube in accordance with

PW Service Bulletin (SB) No. 5707, dated

September 17, 1986, and SB JT9D–7R4–72–

289, dated March 26, 1986.

Inspections

(b) Perform initial and repetitive

inspections of the No. 4 bearing oil pressure

tube and TEC strut for clearance and

alignment, and, if necessary, replace with

serviceable parts, in accordance with the

applicable PW JT9D Engine Manuals, part

numbers (P/Ns) 646028, 770407, 770408, and

777210, Section 72–53–01, Turbine Exhaust

Case Assembly—Inspection 01; P/N 785059,

Section 72–53–05, Turbine Exhaust Case

Assembly—Inspection/Check–01–Config–2;

and P/N 754459, Turbine Exhaust Section—

Heavy Maintenance, Section 72–53–01,

Turbine Exhaust Case Assembly—Check, as

follows:

(1) Initially inspect at the next disassembly

of the TEC when all hardware is stripped

from the case after the effective date of this

AD.

(2) Thereafter, inspect at every disassembly

of the TEC when all hardware is stripped

from the case.

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.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The replacement of the oil pressure tube

shall be done in accordance with PW Service

Bulletin No. 5707, pages 1–7, dated

September 17, 1986, and PW Service Bulletin

No. JT9D–7R4–72–289, pages 1–6, dated

March 26, 1986. The initial and repetitive

inspections shall be done in accordance with

the specified sections of the appropriate PW

JT9D Engine Manual:

P/N Section Pages Date

646028 .............................................. 72–53–01 ......................................... 805–809 ........................................... March 1, 1999.

754459 .............................................. 72–53–01 ......................................... 508 ................................................... October 15, 1999.

754459 .............................................. 72–53–01 ......................................... 508A–508D ...................................... April 15, 1999.

770407 .............................................. 72–53–01 ......................................... 805 ................................................... March 1, 1999.

770408 .............................................. 72–53–01 ......................................... 805 ................................................... March 1, 1999.

777210 .............................................. 72–53–01 ......................................... 805–806 ........................................... October 15, 1998.

777210 .............................................. 72–53–01 ......................................... 807 ................................................... April 15, 1999.

777210 .............................................. 72–53–01 ......................................... 815–818 ........................................... October 15, 1998.

785059 .............................................. 72–53–05 ......................................... 803 ................................................... March 15, 1999.

785059 .............................................. 72–53–05 ......................................... 807–810 ........................................... March 15, 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 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

January 19, 2001.

Issued in Burlington, Massachusetts, on

November 7, 2000.

Donald E. Plouffe,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–29212 Filed 11–17–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ACE–34]

Amendment to Class E Airspace;

Algona, IA

AGENCY: Federal Aviation

Administration (FAA), DOT.