20192 Federal Register / Vol. 61, No. 88 / Monday, May 6, 1996 / Proposed Rules

Paper. The basis for a waiver of the

Nonmanufacturer Rule for these

products is that there are no small

business manufacturers or processors

available to supply these products to the

Federal Government. The effect of a

waiver would be to allow an otherwise

qualified Nonmanufacturer to supply

other than the product of a domestic

small business manufacturer or

processor on a Federal contract set aside

for small businesses or awarded through

the SBA 8(a) Program. The purpose of

this notice is to solicit comments and

potential source information from

interested parties.

DATES: Comments and sources must be

submitted on or before May 29, 1996.

ADDRESSES: David Wm. Loines,

Procurement Analyst, U.S. Small

Business Administration, 409 3rd Street

SW., Washington, DC 20416, Tel: (202)

205–6475.

SUPPLEMENTARY INFORMATION: Public law

100–656, enacted on November 15,

1988, incorporated into the Small

Business Act the previously existing

regulation that recipients of Federal

contracts set-aside for small businesses

or the SBA 8(a) Program procurement

must provide the product of a small

business manufacturer or processor, if

the recipient is other than the actual

manufacturer or processor. This

requirement is commonly referred to as

the Nonmanufacturer Rule. The SBA

regulations imposing this requirement

are found at 13 CFR 121.906(b) and

121.1106(b). Section 303(h) of the law

provides for waiver of this requirement

by SBA for any ‘‘class of products’’ for

which there are no small business

manufacturers or processors in the

Federal market. To be considered

available to participate in the Federal

market on these classes of products, a

small business manufacturer must have

submitted a proposal for a contract

solicitation or received a contract from

the Federal Government within the last

24 months. The SBA defines ‘‘class of

products’’ based on two coding systems.

The first is the Office of Management

and Budget Standard Industrial

Classification Manual. The second is the

Product and Service Code established

by the Federal Procurement Data

System.

The Small Business Administration is

currently processing a request for a

waiver of the Nonmanufacturer Rule for

Tabulating Paper (computer forms,

manifold or continuous) (SIC 2761, PSC

7530) and invites the public to comment

or provide information on potential

small business manufacturers for this

product.

In an effort to identify potential small

business manufacturers, the SBA has

searched the Procurement Automated

Source System (PASS) and Thomas

Register, and the SBA will publish a

notice in the Commerce Business Daily.

The public is invited to comment or

provide source information to SBA on

the proposed waiver of the

Nonmanufacturer Rule for this class of

products.

Dated: April 29, 1996.

Judith A. Roussel,

Associate Administrator for Government

Contracting.

[FR Doc. 96–11239 Filed 5–3–96; 8:45 am]

BILLING CODE 8025–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–69]

Airworthiness Directives; Pratt &

Whitney JT9D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to Pratt

& Whitney JT9D series turbofan engines.

This proposal would require initial and

repetitive eddy current inspections (ECI)

of 14th and 15th stage high pressure

compressor (HPC) disks for cracks, and

removal of cracked disks and

replacement with serviceable parts. This

proposal is prompted by a report of a

14th stage HPC disk bore found cracked

during a shop inspection. The actions

specified by the proposed AD are

intended to prevent 14th and 15th stage

HPC disk rupture, which could result in

an uncontained engine failure and

damage to the aircraft.

DATES: Comments must be received by

July 5, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

95–ANE–69, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may also be submitted to the

Rules Docket by using the following

Internet address: ‘‘epdadcomments@mail.hq.faa.gov’’.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, Publications

Department, Supervisor Technical

Publications Distribution, M/S 132–30,

400 Main St., East Hartford, CT 06108;

telephone (860) 565–7700. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Daniel Kerman, Aerospace Engineers,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7130;

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–ANE–69.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, New England Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 95–ANE–69, 12 New
Federal Register / Vol. 61, No. 88 / Monday, May 6, 1996 / Proposed Rules 20193

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) received a report of finding

during a shop inspection a cracked 14th

stage high pressure compressor (HPC)

disk installed on a Pratt & Whitney (PW)

Model JT9D–7R4D turbofan engine. The

investigation revealed that the 14th and

15th stage disk bores can crack due to

a fatigue strength debit associated with

large unrecrystallized grain

microstructure. This material

phenomenon results in an associated

debit to the 14th and 15th stage HPC

disk low cycle fatigue life. This

condition, if not corrected, could result

in 14th and 15th stage HPC disk

rupture, which could result in an

uncontained engine failure and damage

to the aircraft.

The FAA has reviewed and approved

the technical contents of NonDestructive Inspection Procedure No.

858 (NDIP–858), dated November 7,

1995, attached to PW Alert Service

Bulletin (ASB) No. JT9D–7R4–A72–524,

dated December 13, 1995, and ASB No.

A6232, Revision 1, dated January 11,

1996. That NDIP describes procedures

for eddy current inspections (ECI) of

14th and 15th stage HPC disks for

cracks.

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require initial and repetitive ECI of 14th

and 15th stage HPC disks for cracks, and

removal of cracked disks and

replacement with serviceable parts. The

actions would be required to be

accomplished in accordance with the

ASB’s described previously.

There are approximately 1,100

engines of the affected design in the

worldwide fleet. The FAA estimates that

170 engines installed on aircraft of U.S.

registry would be affected by this

proposed AD. The initial and repetitive

ECI would take place during regularly

scheduled maintenance, and would

therefore require no additional costs to

perform the actions required by this

proposed AD.

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

Is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Pratt & Whitney: Docket No. 95–ANE–69.

Applicability: Pratt & Whitney (PW) Model

JT9D–7R4 series, –59A, –70A, –7Q, and –7Q3

turbofan engines, with the following 14th

and 15th stage high pressure compressor

(HPC) disk installed: part numbers (P/N’s)

5000814–01, 790014, 789914, 790114,

5000815–01, 5000815–021, 704315, 704315–

001, 786215, 786215–001, 704314, 789814,

and 790214. These engines are installed on

but not limited to Airbus A300 and A310

series, Boeing 747 and 767 series, and

McDonnell Douglas DC–10 series aircraft.

Note: 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

use the authority provided in paragraph (f) to

request approval from the Federal Aviation

Administration (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 engine from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent 14th and 15th stage HPC disk

rupture, which could result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) Inspect 14th stage HPC disks, P/N

5000814–01, in accordance with NonDestructive Inspection Procedure No. 858

(NDIP–858), dated November 7, 1995,

attached to PW Alert Service Bulletin (ASB)

No. JT9D–7R4–A72–524, dated December 13,

1995, as follows:

(1) Perform an initial ECI for cracks as

follows:

(i) For disks with 7,000 or more cycles

since new (CSN), and 3,000 or more cycles

in service (CIS) since last shop visit, on the

effective date of this AD, inspect within the

next 1,000 CIS after the effective date of this

AD, or at the next shop visit, whichever

occurs first.

(ii) For disks with 7,000 or more CSN, and

less than 3,000 CIS since last shop visit, on

the effective date of this AD, inspect within

4,000 CIS since the last shop visit, or at the

next shop visit, whichever occurs first.

(iii) For disks with less than 7,000 CSN on

the effective date of this AD, inspect at the

next shop visit after the effective date of this

AD, but before exceeding 4,000 CIS since last

shop visit, or 8,000 CSN, whichever occurs

later.

(iv) For uninstalled disks on or after the

effective date of this AD, inspect prior to

installation.

(2) Thereafter, perform ECI for cracks at

intervals not to exceed 4,000 CIS since last

ECI.

(3) Prior to further flight, remove cracked

disks and replace with serviceable parts.

(b) Inspect 14th stage HPC disks, P/N’s

790014, 789914, 790114, and 15th stage HPC

disks, P/N’s 5000815–01, 5000815–021,

704315, 704315–001, 786215, and 786215–

001, in accordance with NDIP–858, dated

November 7, 1995, attached to PW ASB No.

JT9D–7R4–A72–524, dated December 13,

1995, or PW ASB No. A6232, Revision 1,

dated January 11, 1996, as applicable, as

follows:

(1) Perform an initial ECI for cracks as

follows:

(i) For disks with 6,500 or more CSN, and

3,000 or more CIS since last shop visit, on

the effective date of this AD, inspect within

the next 1,000 CIS after the effective date of

this AD, or at the next shop visit, whichever

occurs first.

(ii) For disks with 6,500 or more CSN, and

less than 3,000 CIS since last shop visit, on

the effective date of this AD, inspect within

4,000 CIS since the last shop visit, or at the

next shop visit, whichever occurs first.

(iii) For disks with less than 6,500 CSN on

the effective date of this AD, inspect at the

next shop visit after the effective date of this

AD, but before exceeding 4,000 CIS since last

shop visit, or 7,500 CSN, whichever occurs

later.
20194 Federal Register / Vol. 61, No. 88 / Monday, May 6, 1996 / Proposed Rules

(iv) For uninstalled disks on or after the

effective date of this AD, inspect prior to

installation.

(2) Thereafter, perform ECI for cracks at

intervals not to exceed 4,000 CIS since last

ECI.

(3) Prior to further flight, remove cracked

disks and replace with serviceable parts.

(c) Inspect 14th stage HPC disks, P/N’s

704314, 789814, and 790214, in accordance

with NDIP–858, dated November 7, 1995,

attached to PW ASB No. A6232, Revision 1,

dated January 11, 1996, as follows:

(1) Perform an initial ECI for cracks as

follows:

(i) For disks with 2,000 or more CSN, and

2,000 or more CIS since last shop visit, on

the effective date of this AD, inspect within

the next 1,000 CIS after the effective date of

this AD, or at the next shop visit, whichever

occurs first.

(ii) For disks with 2,000 or more CSN, and

less than 2,000 CIS since last shop visit, on

the effective date of this AD, inspect within

3,000 CIS since the last shop visit, or at the

next shop visit, whichever occurs first.

(iii) For disks with 2,000 or more CSN, and

no previous shop visits, inspect within 3,000

CIS after the effective date of this AD, or at

the next shop visit, whichever occurs first.

(iv) For disks with less than 2,000 CSN on

the effective date of this AD, inspect at the

next shop visit after the effective date of this

AD, but before exceeding 3,000 CSN.

(v) For uninstalled disks on or after the

effective date of this AD, inspect prior to

installation.

(2) Thereafter, perform ECI for cracks at

intervals not to exceed 3,000 CIS since last

ECI.

(3) Prior to further flight, remove cracked

disks and replace with serviceable parts.

(d) Within 30 days of inspection, report

inspection results on the form labeled ‘‘14th

and 15th Stage HPC Disk Inspection Report,’’

attached to PW NDIP–858, dated November

7, 1995, attached to PW ASB No. A6232,

Revision 1, dated January 11, 1996, and PW

ASB No. JT9D–7R4–A72–524, dated

December 13, 1995, to the office and fax

number listed on that form. Reporting

requirements have been approved by the

Office of Management and Budget and

assigned OMB control number 2120–0056.

(e) For the purpose of this AD, a shop visit

is defined as separation of the ‘‘N’’ flange.

(f) 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. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(g) 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.

Issued in Burlington, Massachusetts, on

April 18, 1996.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 96–11171 Filed 5–3–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–ANE–02]

Airworthiness Directives; Pratt &

Whitney JT8D–200 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Pratt & Whitney JT8D–200 series

turbofan engines, that currently requires

periodic inspection of fan blades for

locked rotors and foreign object damage

(FOD), unlocking of shrouds if

necessary, lubrication of fan blade

shrouds, and dimensional restoration of

the fan blade leading edge. This action

would add a requirement to install

improved design fan blades as

terminating action for the inspections.

This proposal is prompted by the

introduction into service of improved

design fan blades. The actions specified

by the proposed AD are intended to

prevent fan blade failure, which can

result in damage to the aircraft.

DATES: Comments must be received by

July 5, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–ANE–02, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule 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

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Mark A. Rumizen, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7137,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–ANE–02.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, New England Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–ANE–02, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On June 5, 1995, the Federal Aviation

Administration (FAA) issued

airworthiness directive (AD) 95–12–19,

Amendment 39–9270 (60 FR 31388,

June 15, 1995), applicable to certain

Pratt & Whitney (PW) JT8D–200 series

turbofan engines, to require a periodic

inspection of fan blades for locked

rotors and foreign object damage (FOD),

unlocking of shrouds if necessary,

lubrication of the fan blade shrouds, and

dimensional restoration of the fan blade

leading edge. That action was prompted

by the determination that fan blades can

fail due to high cycle fatigue (HCF)

cracking. This HCF cracking can be