Federal Register / Vol. 60, No. 26 / Wednesday, February 8, 1995 / Proposed Rules 7479

Conclusion

OFHEO has identified and

highlighted many of the significant

issues that must be addressed in

connection with development of the

stress test and the associated risk-based

capital regulation. OFHEO seeks

comment on these and any additional

issues that may be identified.

The development of the stress test and

the risk-based capital regulation is one

of the critical statutory responsibilities

of OFHEO. In carrying out this

responsibility, OFHEO is committed to

a regulatory process that will provide

the broadest possible range of opinions

from the widest array of information

sources for consideration during the

regulatory process. The development of

the stress test and the implementation of

the risk-based capital regulation will

provide regulatory and analytical

standards and tools that will safeguard

the financial safety and soundness of

the Enterprises and in turn will ensure

that the Enterprises continue to

accomplish their public missions. Given

the significance of this undertaking,

OFHEO encourages all interested parties

to analyze the issues raised in this

ANPR and submit comments on the

specific questions. OFHEO will

thoroughly analyze and carefully

consider all comments during the

course of the development of the stress

test and risk-based capital regulation.

Dated: February 2, 1995.

Aida Alvarez,

Director, Office of Federal Housing,

Enterprise, Oversight.

[FR Doc. 95–3076 Filed 2–7–95; 8:45 am]

BILLING CODE 4220–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. ANM–106; Notice No. SC–95–

2–NM]

Special Conditions: Raytheon

Corporate Jets, Inc., Model Hawker 800

Airplanes, High-Intensity Radiated

Fields

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed special

conditions.

SUMMARY: This notice proposes special

conditions for the Raytheon Corporate

Jets, Inc., Model Hawker 800 airplanes

equipped with modifications that install

Garrett TFE731–5BR–1H engines and a

mach trim system. The configuration of

these airplanes will utilize new and

revised electronic systems that perform

functions critical to the safety of the

airplane. The applicable regulations do

not contain adequate or appropriate

safety standards for the protection of

these systems from the effects of highintensity radiated fields. These

proposed 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: Comments must be received on

or before March 27, 1995.

ADDRESSES: Comments on this proposal

may be mailed in duplicate to: Federal

Aviation Administration, Transport

Airplane Directorate (ANM–100), Attn:

Docket No. NM–106, 1601 Lind Avenue

SW., Renton, Washington, 98055–4056;

or delivered in duplicate to the

Transport Airplane Directorate at the

above address. Comments must be

marked: Docket No. NM–106.

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:

William Schroeder, FAA,

Standardization Branch, ANM–113,

Transport Airplane Directorate, Aircraft

Certification Service, 1601 Lind Avenue

SW., Renton, Washington, 98055–4056.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of these

proposed special conditions by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

regulatory docket or notice 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 before further rulemaking

action is taken on these proposals. The

proposals contained in this notice may

be changed in light of 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 notice must submit

with those comments a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. NM–106.’’

The postcard will be date stamped and

returned to the commenter.

Background

On February 7, 1994, Raytheon

Corporate Jets, Inc., 3 Bishop Square, St.

Albans Road West, Hatfield,

Hertfordshire AL10 9NE, England,

applied for a revision to type certificate

number A3EU to add new engines and

a mach trim system to the model

Hawker 800 series airplanes currently

included on that TC. This revised model

Hawker 800 is a crusifix tail, low wing,

15 passenger business jet powered by

two Garrett TFE 731–5BR–1H turbofan

engines mounted on pylons extending

from the aft fuselage. The engines will

be capable of delivering 4,634 lbs. of

max continuous thrust each and 4750

pounds of thrust on the operating

engine for up to 5 minutes at automatic

power reserve (APR) power.

Type Certification Basis

Under the provisions of § 21.29 of the

FAR, Raytheon must show, except as

provided in § 25.2, that the revised

Model Hawker 800 complies with the

certification basis of record shown on

TC Data Sheet A3EU for model Hawker

800 airplanes plus, for the engine and

mach trim system installations,

§ 25.1316 as amended by Amendment

25–80, § 25.933 as amended by

Amendment 25–40, § 25.934 as

amended through Amendment 25–23,

§ 25.1309 as amended through

Amendment 25–23, parts 34 and 36 of

the FAR as amended through the latest

amendment in effect at the time of

certification of this revision to the TC

and any additional equivalent safety

findings made for this revision of the

TC. The special conditions that may be

developed as a result of this notice will

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 model Hawker 800

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 § 11.49 of the

FAR after public notice, as required by

§§ 11.28 and 11.29, and become part of

the type certification basis in

accordance with § 21.29(a)(1)(ii) and

§ 21.17(a)(2).

Special conditions are initially

applicable to the model for which they
7480 Federal Register / Vol. 60, No. 26 / Wednesday, February 8, 1995 / Proposed Rules

are issued. Should the type certificate

for that model be amended later to

include any other model that

incorporates the same novel or unusual

design feature, or should any other

model already included on the same

type certificate be modified 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 Model Hawker 800 airplanes with

TFE731–5BR–1H engines incorporate a

revised engine electronic control system

and an electronic controlled mach trim

system. These systems perform critical

to safety of flight functions and may be

vulnerable to high-intensity radiated

fields 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, special conditions are

proposed for the model Hawker 800

with TFE731–5BR–1H engines and a

mach trim system. These special

conditions require that electrical and

electronic components that perform

critical functions and are embodied in

the mach trim system or TFE731–5BR–

1H engine electronic control system be

designed and installed to ensure that

operation and operational capabilities of

these systems to perform critical

functions are not adversely affected

when the airplane is exposed to 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 electronic systems 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–2000 KHz .......... 70 70

2 MHz–30 MHz ................. 200 200

30 MHz–70 MHz ............... 30 30

70 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–1000 MHz ......... 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, the proposed

special conditions would be applicable

initially to certain components on

Hawker 800 airplanes with TFE731–5BR

engines and a mach trim system. Should

Raytheon Corporate Jets, Inc. apply at a

later date for a change to the type

certificate to add or revise electrical or

electronic equipment that performs

critical functions or to include another

model incorporating the same novel or

unusual design feature, these special

conditions 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 Hawker 800 airplane. It

is not a rule of general applicability and

affects only the manufacturer who

applied to the FAA for approval of these

features on the airplane.

List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Federal

Aviation Administration, Reporting and

recordkeeping requirements.

The authority citation for these

proposed special conditions is as

follows:

Authority: 49 U.S.C. app. 1344, 1348(c),

1352, 1354(a), 1355, 1421 through 1431,

1502, 1651(b)(2), 42 U.S.C. 1857f–10, 4321 et

seq.; E.O. 11514; and 49 U.S.C. 106(g).

The Proposed Special Conditions

Accordingly, the Federal Aviation

Administration (FAA) proposes the

following special conditions as part of

the type certification basis for Raytheon

Hawker 800 series airplanes equipped

with Garrett TFE731–5BR–1H turbo fan

engines and electronically controlled

mach trim system. These special

conditions would apply only to

electrical and electronic components

that perform critical functions and are

embodied in the mach trim system or

TFE731–5BR–1H engine electronic

control system.

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 these special

conditions, 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, Wash., on January 31,

1995.

Darrell M. Pederson,

Assistant Manager, Transport Airplane

Directorate, Aircraft Certification Service,

ANM–101.

[FR Doc. 95–3123 Filed 2–7–95; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 39

[Docket No. 94–NM–240–AD]

Airworthiness Directives; Lockheed

Model 382 Series Airplanes

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

Lockheed Model 382 series airplanes,

that currently requires a revision to the

Airplane Flight Manual to require

takeoff operation in accordance with

revised performance data. This action

would require installation of certain

valve housings for the propeller