Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49133

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.

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 a new airworthiness directive

(AD), Amendment 39–10026, to read as

follows:

97–19–06 Sikorsky Aircraft Corporation:

Amendment 39–10026. Docket No. 97–

SW–18–AD. Supersedes priority letter

AD 97–10–04.

Applicability: Model S–61A, D, E, L, N,

NM, R, and V helicopters, certificated in any

category, with a main rotor blade assembly

(blade), part number (P/N) S6115–20501 or

P/N 61170–20201, installed, having one of

the following four-digit or eight-digit serial

numbers:

1282–1554 3305–3106

2183 3317–3115

2380–2498 3343–3147

2495 3343–3648

2500 3364–3180

2520 3451–3239

2521 3491–3278

2644 3499–3936

2673 3511–3293

2716–2683 3512–3292

2721 3517–3311

2751 3525–3310

2781–2644 3637–3459

2800–2671 3694–3481

2817 3748–3543

2819 3752–3527

2839 3753–3528

2883 3840–3620

2919–2771 3966–3737

3008 4216–4392

3016–2850 4787–4793

3019 4800–4794

3138 4835–4790

3168–3585 5484–5363

3192–2999 5974–5816

3215–3012 5981–5813

3216–3023 7069–6583

3242–3044 7779–7033

3249–3052 8099–8054

3250–3043

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required before further flight,

unless accomplished previously.

To prevent disbonding and separation of

portions of the blade, subsequent excessive

vibrations, and loss of control of the

helicopter, accomplish the following:

(a) Inspect each blade having one of the

affected serial numbers in accordance with

Section 2A of the Accomplishment

Instructions of Sikorsky Alert Service

Bulletin (ASB) No. 61B15–29A, Revision A,

dated May 9, 1997, to determine the

anodizing date for all blade trailing edge

pocket assemblies (pocket assemblies)

installed on the blade in locations as

specified in the Planning Information

Section, paragraph 1D(3) of the ASB, that

were anodized by Poly-Metal Company.

Remove any blade having a pocket assembly

anodized by Poly-Metal Company during the

period from October 1, 1996 through

December 31, 1996, and replace the blade

with an airworthy blade.

(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, Boston

Aircraft Certification Office, FAA. Operators

shall submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Boston Aircraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(c) A one-time only special flight permit

may be issued to operate the helicopter to a

location where the requirements of this AD

can be accomplished, after inspecting all

pocket assemblies for disbonding.

(d) The inspection shall be done in

accordance with Sikorsky ASB No. 61B15–

29A, Revision A, dated May 9, 1997. 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

Sikorsky Aircraft Corporation, Attn: Mr. Paul

Dionne, CAR Office, 6900 Main Street, P.O.

Box 9729, Stratford, Connecticut 06497–

9129, telephone (203) 386–7860, fax (203)

386–4703. Copies may be inspected at the

FAA, Office of the Assistant Chief Counsel,

2601 Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(e) This amendment becomes effective on

October 6, 1997.

Issued in Fort Worth, Texas, on September

3, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–24075 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–32; Amendment 39–

10133; AD 97–19–12]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Pratt & Whitney JT8D–1,

–1A, –1B, –7, –7A, –7B, –9, –9A, –11,

–15, –17, and –17R series turbofan

engines, that requires initial and

repetitive fluorescent penetrant and

eddy current inspections of 4th stage

low pressure turbine (LPT) hubs for

cracks, and, if necessary, replacement

with serviceable parts. This amendment
49134 Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations

is prompted by a report of an

uncontained 4th stage LPT blade

release. The actions specified by this AD

are intended to prevent a 4th stage LPT

blade release due to hub cracking,

which can result in an uncontained

engine failure and damage to the

aircraft.

DATES: Effective November 18, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

18, 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; 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) to

include an airworthiness directive (AD)

that is applicable to Pratt & Whitney

JT8D–1, –1A, –1B, –7, –7A, –7B, –9,

–9A, –11, –15, –17, and –17R series

turbofan engines was published in the

Federal Register on January 9, 1997 (62

FR 1299). That action proposed to

require initial and repetitive fluorescent

penetrant inspections (FPI) and eddy

current inspections (ECI) of affected 4th

stage low pressure turbine (LPT) hubs

for cracks, and, if necessary,

replacement with serviceable parts.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Four commenters support the rule as

proposed.

One commenter states that the

inspection should be performed in less

than 5,900 cycles in service (CIS), as

that was the number of CIS between the

last FPI and the uncontained event that

prompted this AD. The FAA does not

concur. The FAA has evaluated the data

and risk management plan supplied by

PW that includes risk analysis, crack

growth analysis, and field experience

for the 4th stage LPT hubs. That data

supports the FAA conclusion that the

unsafe condition is an uncontained

release of an LPT blade. The FAA

concludes the loads introduced by the

cracking of the 4th stage hub are not

sufficient to result in an uncontained

release of the entire 4th stage hub.

Further, the analyses support the risk

management plan, which includes a

focused, ultra high sensitivity FPI and

ECI at the next piece part exposure. The

FAA has also concluded that the unsafe

condition resulting from an uncontained

blade failure can be mitigated by a

reduced compliance time for installing

LPT containment hardware on engines

in which certain 4th stage LPT hubs are

installed. The revised compliance

requirement is described in AD 97–19–

14.

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 as proposed.

The FAA estimates that 381 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will take

approximately 6 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 $137,160.

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

adding the following new airworthiness

directive:

97–19–12 Pratt & Whitney: Amendment 39–

10133. Docket 96–ANE–32.

Applicability: Pratt & Whitney (PW)

Models JT8D–1, –1A, –1B, –7, –7A, –7B, 9,

–9A, –11, –15, –17, and –17R turbofan

engines, with 4th stage low pressure turbine

(LPT) hubs identified by serial number (S/N)

in Table A of PW Alert Service Bulletin

(ASB) No. A6274, Revision 1, dated

December 9, 1996. These engines are

installed on but not limited to Boeing 727

and 737 series, and McDonnell Douglas DC–

9 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 (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 4th stage LPT blade failure due

to hub cracking, which can result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) Perform fluorescent penetrant

inspection (FPI) and eddy current inspection

(ECI) of affected 4th stage LPT hubs for

cracks, in accordance with Paragraph 2A of

PW ASB No. A6274, Revision 1, dated

December 9, 1996, as follows:

(1) Inspect at the next time after the

effective date of this AD that the hub is

removed from the module and has been

debladed.

(2) Thereafter, inspect each time the hub is

removed from the module and has been

debladed.
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