Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49135

(3) Remove from service any cracked 4th

stage LPT hub and replace with a serviceable

part.

(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, Engine

Certification Office. Operators shall forward

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) The actions required by this AD shall

be done in accordance with the following PW

ASB:

Document No. Pages Revision Date

A6274 ............................................................................................................................................................ 1–23 1 December 9,

1996.

Total Pages: 23.

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,

Publication Department, Supervisor

Technical Publications Distribution,

M/S 132–30, 400 Main St., East

Hartford, CT 06108; telephone (860)

565–7700, fax (860) 565–4503. Copies

may be inspected at the FAA, New

England Region, Office of the Assistant

Chief 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.

(e) This amendment becomes effective

on November 18, 1997.

Issued in Burlington, Massachusetts, on

September 10, 1997.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–24796 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–35; Amendment 39–

10134; AD 97–19–13]

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)

94–23–03, applicable to Pratt & Whitney

(PW) JT8D–200 series turbofan engines,

that currently requires installation and

periodic inspection of temperature

indicators installed on the No. 4 and 5

bearing compartment scavenge oil tube

and performance of any necessary

corrective action. This amendment

requires the installation and periodic

inspection of temperature indicators to

all PW JT8D–200 series engines,

including those incorporating the

containment hardware specified in AD

93–23–10. This amendment is prompted

by a report of an uncontained turbine

failure due to a high pressure turbine

(HPT) shaft fracture on an engine that

had the containment hardware installed.

The actions specified by this AD are

intended to prevent fracture of the HPT

shaft, which can result in uncontained

release of engine fragments, engine fire,

inflight engine shutdown, or possible

aircraft damage.

DATES: Effective October 24, 1997.

The incorporation by reference of PW

Alert Service Bulletin (ASB) No. 5944,

Revision 2, dated June 8, 1992, was

previously approved by the Director of

the Federal Register as of January 31,

1995 (59 FR 61789, December 2, 1994).

The incorporation by reference of PW

ASB No. 5944, Revision 3, dated

December 16, 1994, is approved by the

Director of the Federal Register as of

October 24, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, Publication

Department, Supervisor Technical

Publications Distribution, M/S 132–30,

400 Main St., East Hartford, CT 06108;

telephone (860) 565–7700, fax (860)

565–4503. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA 01803–5299; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; 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 94–23–03,

Amendment 39–9065 (59 FR 61789,

December 2, 1994), applicable to Pratt &

Whitney (PW) JT8D–200 series turbofan

engines, was published in the Federal

Register on January 9, 1997 (62 FR

1298). That action proposed to require

installation and periodic inspection of

temperature indicators to all PW JT8D–

200 series engines, including those

incorporating the containment hardware

modifications required by AD 93–23–10.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter states that the

inspection interval should be increased

from 65 hours time in service (TIS) to

75 hours TIS, as this increased interval

could be incorporated into the service

check of that operator’s maintenance

program. The FAA disagrees. Previous

alternative methods of compliance

(AMOCs) have been approved to adjust

the inspection interval on a case-by-case

basis, and the operator is invited to

apply for an AMOC using the usual

procedure. Generally, however, the

compliance interval remains at 65 hours

TIS.

One commenter states that the

reporting requirements of the AD should

be eliminated, as the original AD

terminated reporting requirements six

months after the effective date of the

AD. The FAA concurs and has

eliminated the reporting requirements

in the final rule.

One commenter notes that the

containment hardware has been

ineffective in ensuring containment and

that costs associated with installing the

containment hardware have been

excessive. The commenter, however,

offers no objection to the proposed rule.

The indirect costs of operating engines
49136 Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations

with the containment hardware

installed are not directly related to this

proposed rule, and, therefore, are not

addressed in the economic analysis for

this rule. A full cost analysis for each

AD, including such indirect costs, is not

necessary since the FAA has already

performed a cost benefit analysis when

adopting the airworthiness requirements

to which these engines were originally

certificated. A finding that an AD is

warranted means that the original

design no longer achieves the level of

safety specified by those airworthiness

requirements, and that other required

actions are necessary, such as

containment hardware, or as in this

case, installation and inspection of

temperature indicators. Because the

original level of safety was already

determined to be cost beneficial, these

additional requirements needed to

return the engine to that level of safety

do not add any additional regulatory

burden, and, therefore, a full cost

analysis would be redundant and

unnecessary.

One commenter supports the AD as

proposed on the assumption that the AD

requires diagnostic inspections should

the required oil temperature indicators

show signs that high oil temperatures

have occurred within the engine. The

AD does require troubleshooting and

diagnostic testing and corrective action

in accordance with service documents

incorporated by reference.

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.

There are approximately 2,432 series

engines of the affected design in the

worldwide fleet. The FAA estimates that

1,044 engines installed on aircraft of

U.S. registry will be affected by this AD,

that it will take approximately 1.5 work

hours per engine to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $93,960.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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

removing amendment 39–9065 (59 FR

61789, December 2, 1994) and by adding

a new airworthiness directive,

Amendment 39–10134, to read as

follows:

97–19–13 Pratt & Whitney: Amendment 39–

10134. Docket 96–ANE–35. Supersedes

AD 94–23–03, Amendment 39–9065.

Applicability: Pratt & Whitney (PW) JT8D–

209, –217, –217A, –217C, and –219 turbofan

engines, installed on but not limited to

McDonnell Douglas MD–80 series and Boeing

727 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 (d)

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 fracture of the high pressure

turbine (HPT) shaft, which can result in

uncontained release of engine fragments,

engine fire, inflight engine shutdown, or

possible aircraft damage, accomplish the

following:

(a) Install and inspect one or two

temperature indicators, part number (P/N)

810486, or a single or double set of P/N

809129 and P/N 809130 temperature

indicators, on the No. 4 and 5 bearing

compartment scavenge oil tube, as follows:

(1) Install temperature indicators on the

No. 4 and 5 bearing compartment scavenge

oil tube in accordance with Section 2.A.(1) of

the Accomplishment Instructions of PW

Alert Service Bulletin (ASB) No. 5944,

Revision 3, dated December 16, 1994, or

Revision 2, dated June 8, 1992, within 90

days after the effective date of this AD.

(2) Visually inspect temperature indicators

within 65 hours TIS of installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection.

(3) If upon inspection, the color of any

temperature indicator window(s) has turned

completely black, perform troubleshooting

and diagnostic testing and corrective action

as required, in accordance with Section

2.A.(2) (c) and (d) or (f) and (g), as applicable,

of the Accomplishment Instructions of PW

ASB No. 5944, Revision 3, dated December

16, 1994, or Revision 2, dated June 8, 1992.

Prior to returning the engine to service,

replace any temperature indicator that has

turned black and inspect in accordance with

paragraphs (a)(2) and (a)(3) of this AD.

(b) For aircraft installations utilizing one P/

N 810486 indicator or one set of P/N 809129

and 809130 indicators, and inspection

reveals a missing indicator, inspect the

remaining temperature indicator, if

applicable, to determine if the indicator

window has turned completely black. If the

indicator window has turned completely

black, perform troubleshooting and

diagnostic testing, and corrective action as

required, in accordance with paragraph (a)(3)

of this AD. If the indicator window has not

turned completely black or if there are no

additional indicators installed, then install a

new indicator in accordance with Section

2.A.(1) of the Accomplishment Instruction of

PW ASB No. 5944, Revision No. 3, dated

December 16, 1994, or Revision 2, dated June

8, 1992, prior to return to service, and

visually inspect the temperature indicator

within 65 hours TIS since installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection in

accordance with paragraphs (a)(2) and (a)(3)

of this AD.

(c) For aircraft installations utilizing two P/

N 810486 indicators or two sets of P/N

809129 and 809130 indicators, and

inspection reveals a missing indicator(s),

inspect the remaining temperature

indicator(s), if applicable, to determine if the

indicator window has turned completely

black. If the indicator window has turned

completely black, perform troubleshooting

and diagnostic testing, and corrective action
Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49137

as required, in accordance with paragraph

(a)(3) of this AD. If the indicator window has

not turned completely black, install a new

indicator(s) in accordance with Section

2.A.(1) of the Accomplishment Instructions

of PW ASB No. 5944, Revision 3, dated

December 16, 1994, or Revision 2, dated June

8, 1992, prior to return to service, and

visually inspect the temperature indicator

within 65 hours TIS since installation.

Thereafter, inspect at intervals not to exceed

65 hours TIS since last inspection in

accordance with paragraphs (a)(2) and (a)(3)

of this AD.

(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. Operators shall forward

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative method of

compliance with this AD, if any, may be

obtained from the Engine Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The actions required by this AD shall be

done in accordance with the following PW

ASBs:

Document No. Pages Revision Date

5944 ................................................................................................................................. 1–35 3 December 16, 1994.

Total pages: 35.

5944 ................................................................................................................................. 1–44 2 June 8, 1992.

Total pages: 44.

This incorporation by reference of PW ASB

No. 5944, Revision 2, dated June 9, 1993, was

previously approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51 as of January 31,

1995 (59 FR 61789, December 2, 1994).

Copies may be obtained from Pratt &

Whitney, Publication Department, Supervisor

Technical Publications Distribution,

M/S 132–30, 400 Main St., East Hartford, CT

06108; telephone (860) 565–7700, fax (860)

565–4503. Copies may be inspected at the

FAA, New England Region, Office of the

Assistant Chief 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.

(g) This amendment becomes effective on

October 24, 1997.

Issued in Burlington, Massachusetts, on

September 10, 1997.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–24797 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–07; Amendment 39–

10135; AD 97–19–14]

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 Pratt & Whitney JT8D

series turbofan engines, that currently

requires inspections of low pressure

turbine (LPT) blade sets for blade

shroud crossnotch wear, and removal, if

necessary. In addition, the current AD

requires, as a terminating action to the

inspections, installation of improved

LPT containment hardware, and

installation of an improved No. 6

bearing scavenge pump bracket bushing.

This amendment keeps the compliance

actions of the current AD intact but

changes the compliance time for LPT

containment hardware installation from

the current calendar end-date to

December 31, 1998, for engines that

contain suspect 4th stage hubs

identified by serial number. This

amendment is prompted by a report of

a fourth stage hub manufacturing defect

that led to the failure of the hub and

subsequent release of LPT blades. The

actions specified by this AD are

intended to prevent damage to the

aircraft resulting from engine debris

following an LPT blade, shaft, or hub

failure.

DATES: Effective October 24, 1997.

The incorporation by reference of PW

Alert Service Bulletin No. A6131,

Revision 1, dated May 16, 1995; PW

Alert Service Bulletin No. A6131,

Revision 2, dated July 28, 1997; PW

Alert Service Bulletin No. A6274,

Original, dated November 7, 1996; and

PW Alert Service Bulletin No. A6274,

Revision 1, dated December 9, 1996, is

approved by the Director of the Federal

Register as of October 24, 1997.

The incorporation by reference of all

other publications listed in the

regulations was previously approved as

of November 14, 1994 (59 FR 51842,

October 13, 1994).

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney, 400 Main St., 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

Assistant Chief Counsel, 12 New

England Executive Park, Burlington, MA

01803–5299; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; 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 94–20–08,

Amendment 39–9036 (59 FR 51842,

October 15, 1994), applicable to Pratt &

Whitney (PW) JT8D–1, –1A, –1B, –7,

–7A, –7B, –9, –9A, –11, –15, –17, and

–17R series turbofan engines, was

published in the Federal Register on

April 1, 1997 (62 FR 15437). That action

proposed to require inspections of low

pressure turbine (LPT) blade sets for

blade shroud crossnotch wear, and

removal, if necessary. In addition, the

current AD requires, as a terminating

action to the inspections, installation of

improved LPT containment hardware,

and installation of an improved No. 6

bearing scavenge pump bracket bushing.

The proposal would have reduced the

compliance time for LPT containment

hardware installation from the current

calendar end-date to December 31, 1998.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due