63988 Federal Register / Vol. 60, No. 239 / Wednesday, December 13, 1995 / Proposed Rules

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

Minicomputers (SIC 3571, PSC 7010)

and invites the public to comment or

provide information on potential small

business sources for this product.

In an effort to identify potential small

business sources, 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: November 6, 1995.

Judith A. Roussel,

Associate Administrator for Government

Contracting.

[FR Doc. 95–30328 Filed 12–12–95; 8:45 am]

BILLING CODE 8025–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–ANE–66]

Airworthiness Directives; Hamilton

Standard 14RF and 14SF Series, and

Hamilton Standard/British Aerospace

Model 6/5500/F Propellers

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

Hamilton Standard 14RF and 14SF

series, and Hamilton Standard/British

Aerospace Model 6/5500/F propellers.

This proposal would require initial and

repetitive inspections of critical

components, and removal, and

replacement with serviceable parts, of

those critical components that do not

meet the return to service criteria. This

proposal is prompted by failure modes

effects analysis (FMEA), certification

test data, engineering analysis, and

repair actions performed at overhaul

depots. The actions specified by the

proposed AD are intended to prevent

loss of propeller control due to failure

of critical components, which could

result in loss of control of the aircraft.

DATES: Comments must be received by

February 12, 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–66, 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

Hamilton Standard, One Hamilton

Road, Windsor Locks, CT 06096–1010.

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:

Frank Walsh, Aerospace Engineer,

Boston Aircraft Certification Office,

FAA, Engine and Propeller Directorate,

12 New England Executive Park,

Burlington, MA 01803–5299; telephone

(617) 238–7158, 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–66.’’ 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–66, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) and Hamilton Standard have

identified critical aspects of the transfer

tube assembly, actuator assembly, and

propeller control unit (PCU) for

Hamilton Standard Models 14RF–9,

14RF–19, 14RF–21; 14SF–5, 14SF–7,

14SF–11, 14SF–11L, 14SF–15, 14SF–17,

14SF–19, 14SF–23; and Hamilton

Standard/British Aerospace 6/5500/F

propellers. A continuous airworthiness

requirement for inspection of those

critical aspects of the transfer tube

assembly, actuator assembly, and PCU

for wear is required to ensure continued

safe operation between inspections. The

inspection intervals and inspection

criteria have been generated by failure

modes effects analysis (FMEA),

certification test data, engineering

analysis, and repair actions performed

at overhaul depots. This condition, if

not corrected, could result in loss of

propeller control due to failure of

critical components, which could result

in loss of control of the aircraft.

The FAA has reviewed and approved

the technical contents of the following

Hamilton Standard Service Bulletins

(SB’s), all dated November 29, 1995,

that describe procedures for initial and

repetitive inspections of critical

components: 14RF–9–61–64, 14RF–19–

61–32, 14RF–21–61–51, 14SF–61–70,

and 6/5500/F–61–25.

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
Federal Register / Vol. 60, No. 239 / Wednesday, December 13, 1995 / Proposed Rules 63989

require initial and repetitive inspections

of critical aspects of the transfer tube

assembly, actuator assembly, and PCU

for wear. This AD would also require,

prior to further flight, removing and

replacement with serviceable parts

those critical components that do not

meet the return to service criteria. The

actions would be required to be

accomplished in accordance with the

SB’s described previously.

There are approximately 2,900

propellers of the affected design in the

worldwide fleet. The FAA estimates that

1,350 propellers installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 4.3 work hours per

propeller to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $348,300.

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), 40101, 40113,

44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Hamilton Standard: Docket No. 95–ANE–66.

Applicability: Hamilton Standard Models

14RF–9, 14RF–19, 14RF–21, and 14SF–5,

14SF–7, 14SF–11, 14SF–11L, 14SF–15,

14SF–17, 14SF–19, 14SF–23 and Hamilton

Standard/British Aerospace 6/5500/F

propellers installed on but not limited to

Embraer EMB–120 and EMB–120–RT;

SAAB–SCANIA SF 340B; Aerospatiale

ATR42–100, ATR42–300, ATR42–320,

ATR72; DeHavilland DHC–8–100 series,

DHC–8–300 Series; Construcciones

Aeronauticas SA (CASA) CN–235 series and

CN–235–100; Canadair CL–215T an CL–415;

and British Aerospace ATP Airplanes.

Note: This airworthiness directive (AD)

applies to each propeller 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 propellers 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 (e)

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 propeller from the

applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of propeller control due to

failure of critical components, which could

result in loss of control of the aircraft,

accomplish the following:

(a) For those propellers with transfer tube

assemblies, actuator assemblies, and

propeller control units (PCU’s) with greater

than or equal to 15,500 hours time in service

(TIS), or unknown TIS, on the effective date

of this AD, inspect for wear within 1,000

hours TIS after the effective date of this AD.

Perform inspections of the critical aspects of

these components in accordance with the

applicable service bulletins (SB’s) listed in

paragraph (d) of this AD. Thereafter, inspect

at intervals not to exceed 10,500 hours TIS

since last inspection. Prior to further flight,

remove and replace with serviceable parts

those components that do not meet the return

to service criteria defined in the applicable

SB’s.

(b) For those propellers with transfer tube

assemblies, actuator assemblies, and PCU’s

with greater than or equal to 10,500 hours

TIS but less than 15,500 hours TIS on the

effective date of this AD, inspect for wear

within 1,000 hours TIS after the effective

date of this AD, or prior to accumulating

16,500 hours TIS, whichever occurs later.

Perform inspections of the critical aspects of

these components in accordance with the

applicable SB’s listed in paragraph (d) of this

AD. Thereafter, inspect at intervals not to

exceed 10,500 hours TIS since last

inspection. Prior to further flight, remove and

replace with serviceable parts those

components that do not meet the return to

service criteria defined in the applicable

SB’s.

(c) For those propellers with transfer tube

assemblies, actuator assemblies, and PCU’s

with less than 10,500 hours TIS on the

effective date of this AD, inspect for wear

within 6,000 hours TIS after the effective

date of this AD, or prior to accumulating

10,500 hours TIS, whichever occurs later.

Perform inspections of the critical aspects of

these components in accordance with the

applicable SB’s listed in paragraph (d) of this

AD. Thereafter, inspect at intervals not to

exceed 10,500 hours TIS since last

inspection. Prior to further flight, remove and

replace with serviceable parts those

components that do not meet the return to

service criteria defined in the applicable

SB’s.

(d) Perform the inspections for wear

required by this AD in accordance with, and

use the return to service criteria defined in,

the following applicable Hamilton Standard

SB’s, all dated November 29, 1995: 14RF–9–

61–64, 14RF–19–61–32, 14RF–21–61–51,

14SF–61–70, and 6/5500/F–61–2.

(e) 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. The request

should be forwarded through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Boston Aircraft Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Boston

Aircraft Certification Office.

(f) 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.

Issued in Burlington, Massachusetts, on

December 6, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–30352 Filed 12–12–95; 8:45 am]

BILLING CODE 4910–13–U