34716 Federal Register / Vol. 61, No. 129 / Wednesday, July 3, 1996 / Rules and Regulations

TABLE 2.—UNIT RATES

Service 1 3 Rough rice

Brown rice

for processingMilled rice

Effective August 2, 1996

Inspection for quality (per lot, sublot, or sample inspection ............................................................. $29.20 $25.30 $18.00

Factor analysis for any single factor (per factor):

(a) Milling yield (per sample) ..................................................................................................... 22.70 22.70 ....................

(b) All other factors (per factor) ................................................................................................. 10.80 10.80 10.80

Total oil and free fatty acid ............................................................................................................... .................... 35.40 35.40

Interpretive line samples:2 .................... .................... ....................

(a) Milling degree (per set) ........................................................................................................ .................... .................... 75.80

(b) Parboiled light (per sample) ................................................................................................. .................... .................... 19.00

Extra copies of certificates (per copy) .............................................................................................. 3.00 3.00 3.00

Effective January 1, 1997

Inspection for quality (per lot, sublot, or sample inspection) ............................................................ 31.00 26.80 19.10

Factor analysis for any single factor (per factor):

(a) Milling yield (per sample) ..................................................................................................... 24.10 24.10 ....................

(b) All other factors (per factor) ................................................................................................. 17.40 11.40 11.40

Total oil and free fatty acid ............................................................................................................... .................... 37.50 37.50

Interpretive line samples: 2 .................... .................... ....................

(a) Milling degree (per set) ........................................................................................................ .................... .................... 80.30

(b) Parboiled light (per sample) ................................................................................................. .................... .................... 20.10

Extra copies of certificates (per copy) .............................................................................................. 3.00 3.00 3.00

Effective January 1, 1998

Inspection for quality (per lot, sublot, or sample inspection) ............................................................ 32.90 28.40 20.20

Factor analysis for any single factor (per factor):

(a) Milling yield (per sample) ..................................................................................................... 25.50 25.50 ....................

(b) All other factors per factor): ................................................................................................. 12.10 12.10 12.10

Total oil and free fatty acid ............................................................................................................... .................... 39.80 39.80

Interpretive line samples: 2

(a) Milling degree (per set) ........................................................................................................ .................... .................... 85.10

(b) Parboiled light (per sample) ................................................................................................. .................... .................... 21.30

Extra copies of certificates (per copy) .............................................................................................. 3.00 3.00 3.00

1Fees apply to determinations (original or appeals) for kind, class, grade, factor analysis, equal to type, milling yield, or any other quality designation as defined in the U.S. Standards for Rice or applicable instructions, whether performed singly or in combination at other than at the applicant’s facility. 2 Interpretive line samples may be purchased from the U.S. Department of Agriculture, Grain Inspection, Packers and Stockyards Administration; Technical Services Division; Board of Appeals and Review; FGIS Technical Center, 10383 North Executive Hills Boulevard, Kansas City,

MO 64153–1394. Interpretive line samples also are available for examination at selected FGIS field offices. A list of field offices may be obtained

from the Deputy Director, Field Management Division, USDA, GIPSA, FGIS, P.O. Box 96454, Washington, DC 20090–6454. The interpretive line

samples illustrate the lower limit for milling degrees only and the color limit for the factor ‘‘Parboiled Light’’ rice. 3Fees for other services not referenced in Table 2 will be based on the noncontract hourly rate listed in Section 868.90, Table 1.

Dated: June 27, 1996.

Michael V. Dunn,

Assistant Secretary, Marketing and

Regulatory Programs.

[FR Doc. 96–16993 Filed 7–2–96; 8:45 am]

BILLING CODE 3410–EN–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. NM–127; Special Conditions

No. 25–ANM–117]

Special Conditions: Cessna Model 500,

550, and S550 Airplanes; HighIntensity Radiated Fields

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final special conditions; request

for comments.

SUMMARY: These special conditions are

issued for the Cessna Model 500, 550,

and S550 airplanes. These airplanes, as

modified by Columbia Avionics, Inc.,

utilize new avionics/electronic systems,

such as an electronic flight information

system (EFIS), which perform critical

functions. The applicable regulations do

not contain adequate or appropriate

safety standards for the protection of

these systems from the effects of highintensity radiated fields (HIRF). These

special conditions contain the

additional safety standards that the

Administrator considers necessary to

establish a level of safety equivalent to

that established by the existing

airworthiness standards.

DATES: The effective date of these

special conditions is June 20, 1996.

Comments must be received on or

before August 2, 1996.

ADDRESSES: Comments on these special

conditions may be mailed in duplicate

to: Federal Aviation Administration,

Office of the Assistant Chief Counsel,

Attn: Rules Docket (ANM–7), Docket

No. NM–127, 1601 Lind Avenue SW.,

Renton, Washington, 98055–4056; or

delivered in duplicate to the Office of

the Assistant Chief Counsel at the above

address. Comments must be marked:

Docket No. NM–127. Comments may be

inspected in the Rules Docket

weekdays, except Federal holidays,

between 7:30 a.m. and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT:

Mark Quam, FAA, Standardization

Branch, ANM–113, Transport Airplane

Directorate, Aircraft Certification

Service, 1601 Lind Avenue SW.,

Renton, Washington, 98055–4056;

telephone (206) 227–2145; facsimile

(206) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA has determined that good

cause exists for making these special

conditions effective upon issuance;

however, interested persons are invited

to submit such written data, views, or

arguments as they may desire.

Communications should identify the
Federal Register / Vol. 61, No. 129 / Wednesday, July 3, 1996 / Rules and Regulations 34717

regulatory docket and special condition

number and be submitted in duplicate

to the address specified above. All

communications received on or before

the closing date for comments will be

considered by the Administrator. These

special conditions may be changed in

light of the comments received. All

comments submitted will be available in

the Rules Docket for examination by

interested persons, both before and after

the closing date for comments. A report

summarizing each substantive public

contact with FAA personnel concerning

this rulemaking will be filed in the

docket. Persons wishing the FAA to

acknowledge receipt of their comments

submitted in response to this request

must submit with those comments a

self-addressed, stamped postcard on

which the following statement is made:

‘‘Comments to Docket No. NM–127.’’

The postcard will be date stamped and

returned to the commenter.

Background

On April 8, 1996, Columbia Avionics,

11200 Airport Road, Columbia, MO

65201, applied for a Supplemental Type

Certificate (STC) to modify Cessna 500,

550, and S550 airplanes to incorporate

the installation of an electronic flight

instrument system (EFIS). The airplanes

are pressurized, executive transport

airplanes powered by two fuselagemounted turbofan engines.

Supplemental Type Certification Basis

Under the provisions of § 21.101 of 14

CFR part 21, Columbia Avionics must

show that the modified Cessna 500, 550,

and S550 airplanes continue to meet the

applicable provisions of the regulations

incorporated by reference in Type

Certificate A22CE, or the applicable

regulations in effect on the date of

application for the change. The

regulations incorporated by reference in

the type certificate are commonly

referred to as the ‘‘original type

certification basis.’’ The regulations

incorporated by reference in TC A22CE

include the following for the Cessna

500, 550 and S550 series: 14 CFR part

25, dated February 1, 1965, as amended

by Amendments 25–1 through 25–17,

and §§ 25.934 and 25.1091(d)(2), as

amended through Amendment 25–23. In

addition, under § 21.101(b)(1), the

following regulations apply to the EFIS

installation: §§ 25.1303, 25.1305, and

25.1322, as amended by Amendment

25–38; §§ 25.1309, 25.1321 (a), (b), (d),

and (e), 25.1331, 25.1333, and 25.1335,

as amended by Amendment 25–41; and

§ 25.1316, as amended by Amendment

25–80. These special conditions form an

additional part of the type certification

basis.

If the Administrator finds that the

applicable airworthiness regulations

(i.e., part 25, as amended) do not

contain adequate or appropriate safety

standards for the Cessna Model 500,

550, and S550 series airplanes because

of a novel or unusual design feature,

special conditions are prescribed under

the provisions of § 21.16 to establish a

level of safety equivalent to that

established in the regulations.

Special conditions, as appropriate, are

issued in accordance with 14 CFR

§ 11.49 after public notice, as required

by §§ 11.28 and 11.29(b), and become

part of the type certification basis in

accordance with § 21.101(b)(2).

Special conditions are initially

applicable to the model for which they

are issued. Should the applicant apply

for a supplemental type certificate to

modify any other model included on the

same type certificate to incorporate the

same novel or unusual design feature,

the special conditions would also apply

to the other model under the provisions

of § 21.101(a)(1).

Novel or Unusual Design Features

The Cessna Model 500, 550, and S550

airplanes incorporate new avionics/

electronic systems, such as the

electronic flight instrument system

(EFIS), that perform critical functions.

These systems may be vulnerable to

high-intensity radiated fields (HIRF)

external to the airplane.

Discussion

There is no specific regulation that

addresses protection requirements for

electrical and electronic systems from

HIRF. Increased power levels from

ground-based radio transmitters and the

growing use of sensitive electrical and

electronic systems to command and

control airplanes have made it necessary

to provide adequate protection.

To ensure that a level of safety is

achieved equivalent to that intended by

the regulations incorporated by

reference, a special condition is needed

for the Cessna Model 500, 550, and

S550, as modified by Columbia

Avionics, which requires that new

electrical and electronic systems, such

as the EFIS, that perform critical

functions be designed and installed to

preclude component damage and

interruption of function due to both the

direct and indirect effects of HIRF.

High-Intensity Radiated Fields (HIRF)

With the trend toward increased

power levels from ground-based

transmitters, plus the advent of space

and satellite communications, coupled

with electronic command and control of

the airplane, the immunity of critical

digital avionics systems, such as the

EFIS, to HIRF must be established.

It is not possible to precisely define

the HIRF to which the airplane will be

exposed in service. There is also

uncertainty concerning the effectiveness

of airframe shielding for HIRF.

Furthermore, coupling of

electromagnetic energy to cockpitinstalled equipment through the cockpit

window apertures is undefined. Based

on surveys and analysis of existing HIRF

emitters, an adequate level of protection

exists when compliance with the HIRF

protection special condition is shown

with either paragraphs 1 OR 2 below:

1. A minimum threat of 100 volts per

meter peak electric field strength from

10 KHz to 18 GHz.

a. The threat must be applied to the

system elements and their associated

wiring harnesses without the benefit of

airframe shielding.

b. Demonstration of this level of

protection is established through system

tests and analysis.

2. A threat external to the airframe of

the following field strengths for the

frequency ranges indicated.

Frequency Peak

(V/M)

Average

(V/M)

10 KHz–100 KHz ............ 50 50

100 KHz–500 KHz .......... 60 60

500 KHz–2 MHz .............. 70 70

2 MHz–30 MHz ............... 200 200

30 MHz–100 MHz ........... 30 30

100 MHz–200 MHz ......... 150 33

200 MHz–400 MHz ......... 70 70

400 MHz–700 MHz ......... 4,020 935

700 MHz–1 GHz ............. 1,700 170

1 GHz–2 GHz ................. 5,000 990

2 GHz–4 GHz ................. 6,680 840

4 GHz–6 GHz ................. 6,850 310

6 GHz–8 GHz ................. 3,600 670

8 GHz–12 GHz ............... 3,500 1,270

12 GHz–18 GHz ............. 3,500 360

18 GHz–40 GHz ............. 2,100 750

As discussed above, these special

conditions are applicable to the Cessna

Model 500, 550, and S550 airplanes, as

modified by Columbia Avionics, Inc.

Should Columbia Avionics apply at a

later date for a supplemental type

certificate to modify any other model

included on Type Certificate No. A22CE

to incorporate the same novel or

unusual design feature, this special

condition would apply to that model as

well, under the provisions of

§ 21.101(a)(1).

Conclusion

This action affects only certain design

features on the Cessna Model 500, 550,

and S550 airplanes. It is not a rule of

general applicability and affects only

the applicant who applied to the FAA
34718 Federal Register / Vol. 61, No. 129 / Wednesday, July 3, 1996 / Rules and Regulations

for approval of these features on the

airplane.

The substance of the special

conditions for this airplane has been

subject to the notice and comment

procedure in several prior instances and

has been derived without substantive

change from those previously issued. It

is unlikely that prior public comment

would result in a significant change

from the substance contained herein.

For this reason, and because a delay

would significantly affect the

certification of the airplane, which is

imminent, the FAA has determined that

prior public notice and comment are

unnecessary and impracticable, and

good cause exists for adopting these

special conditions immediately.

Therefore, these special conditions are

being made effective upon issuance. The

FAA is requesting comments to allow

interested persons to submit views that

may not have been submitted in

response to the prior opportunities for

comment described above.

List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting

and recordkeeping requirements.

The authority citation for this special

condition is as follows:

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

44702, 44704.

The Special Conditions

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the following special

conditions are issued as part of the type

certification basis for Cessna Model 500,

550, and S550 airplanes, as modified by

Columbia Avionics, Inc.

1. Protection from Unwanted Effects

of High-Intensity Radiated Fields

(HIRF). Each electrical and electronic

system that performs critical functions

must be designed and installed to

ensure that the operation and

operational capability of these systems

to perform critical functions are not

adversely affected when the airplane is

exposed to high-intensity radiated

fields.

2. For the purpose of this special

condition, the following definition

applies: Critical Functions. Functions

whose failure would contribute to or

cause a failure condition that would

prevent the continued safe flight and

landing of the airplane.

Issued in Renton, Washington, in June 20,

1996.

Gary L. Killion,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service,

ANM–100.

[FR Doc. 96–16959 Filed 7–2–96; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 39

[Docket No. 95–NM–253–AD; Amendment

39–9675; AD 96–13–07]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 100, 200, 300, 400, 500,

600, and 700 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, that currently

requires supplemental structural

inspections to detect fatigue cracks, and

repair or replacement, as necessary, to

ensure the continued airworthiness of

these airplanes. This amendment adds

and revises certain significant structural

items for which inspection and repair or

replacement is necessary. This

amendment is prompted by a structural

re-evaluation conducted by the

manufacturer, which identified

additional structural elements where

fatigue damage is likely to occur. The

actions specified by this AD are

intended to prevent reduced structural

integrity of these airplanes.

DATES: Effective August 6, 1996.

The incorporation by reference of

Fokker SIP Product Support Document

27438, Part 1, including revisions up

through August 1, 1995, as listed in the

regulations is approved by the Director

of the Federal Register as of August 6,

1996.

The incorporation by reference of

Fokker SIP Document 27438, Part 1,

including revisions up through

November 1, 1991, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

October 21, 1992 (57 FR 42693).

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Ruth E. Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 92–19–07,

amendment 39–8365 (57 FR 42693,

September 16, 1992), which is

applicable to all Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, was published in

the Federal Register on April 10, 1996

(61 FR 15906). The action proposed to

supersede AD 92–19–07 to continue to

require a program of supplemental

structural inspections (SIP) to detect

fatigue cracks, and repair or

replacement, as necessary. The action

also proposed to add and revise certain

significant structural items (SSI) for

which inspection and repair or

replacement is necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Support for the Proposal

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with as proposed.

Cost Impact

There are approximately 34 Fokker

Model F27 Mark 100, 200, 300, 400,

500, 600, and 700 series airplanes of

U.S. registry that will be affected by this

AD.

The actions that are currently

required by AD 92–19–07 take

approximately 295 work hours per

airplane per year to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

on U.S. operators relative to the

requirements of the previously-issued

AD that are retained in this new AD

action is estimated to be $601,800, or

$17,700 per airplane, annually.

The new actions that are required by

this new AD action will take

approximately 179 additional work

hours per airplane per year to

accomplish, at an average labor rate of