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Rules and Regulations Federal Register

1161

Vol. 70, No. 4

Thursday, January 6, 2005

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 25

[Docket No. NM298, Special Conditions No. 

25–282–SC] 

Special Conditions: Dassault-Breguet 

Model Falcon 10 Airplane; High 

Intensity Radiated Fields (HIRF)

AGENCY: Federal Aviation 

Administration (FAA) DOT.

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for a Dassault-Breguet Model 

Falcon 10 airplane modified by Long 

Beach Avionics of Long Beach, 

California. The modified airplane will 

have novel and unusual design features 

when compared to the state of 

technology envisioned in the 

airworthiness standards for transport 

category airplanes. The modification 

incorporates the installation of a Collins 

Model ALI–80 Altimeter and Model 

MSI–80 Mach Airspeed Indicator. The 

applicable airworthiness 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 provided by the existing 

airworthiness standards.

DATES: The effective date of these 

special conditions is December 23, 

2004. Comments must be received on or 

before February 7, 2005.

ADDRESSES: Comments on these special 

conditions may be mailed in duplicate 

to: Federal Aviation Administration, 

Transport Airplane Directorate, Attn: 

Rules Docket (ANM–113), Docket No. 

NM298, 1601 Lind Avenue SW., 

Renton, Washington, 98055–4056; or 

delivered in duplicate to the Transport 

Airplane Directorate at the above 

address. All comments must be marked: 

Docket No. NM298. Comments may be 

inspected in the Rules Docket 

weekdays, except Federal holidays, 

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

FOR FURTHER INFORMATION CONTACT: Greg 

Dunn, FAA, Airplane and Flight Crew 

Interface Branch, ANM–111, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington, 98055–4056; 

telephone (425) 227–2799; facsimile 

(425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA has determined that notice 

and opportunity for prior public 

comment is impracticable, because 

these procedures would significantly 

delay certification and thus delivery of 

the affected airplane. In addition, the 

substance of these special conditions 

has been subject to the public comment 

process in several prior instances with 

no substantive comments received. The 

FAA, therefore, finds that good cause 

exists for making these special 

conditions effective upon issuance; 

however, the FAA invites interested 

persons to participate in this rulemaking 

by submitting written comments, data, 

or views. The most helpful comments 

reference a specific portion of the 

special conditions, explain the reason 

for any recommended change, and 

include supporting data. We ask that 

you send us two copies of written 

comments. 

We will file in the docket all 

comments we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning these special conditions. 

The docket is available for public 

inspection before and after the comment 

closing date. If you wish to review the 

docket in person, go to the address in 

the ADDRESSES section of this preamble 

between 7:30 a.m., and 4 p.m., Monday 

through Friday, except Federal holidays. 

We will consider all comments we 

receive on or before the closing date for 

comments. We will consider comments 

filed late, if it is possible to do so 

without incurring expense or delay. We 

may change these special conditions, 

based on the comments received. 

If you want the FAA to acknowledge 

receipt of your comments on these 

special conditions, include with your 

comments a pre-addressed, stamped 

postcard on which the docket number 

appears. We will stamp the date on the 

postcard and mail it back to you. 

Background 

On October 11, 2004, Long Beach 

Avionics of Long Beach, California, 

applied to the FAA, Los Angeles 

Aircraft Certification Office for a 

supplemental type certificate (STC) to 

modify a Dassault-Breguet Model Falcon 

10 airplane. The proposed modification 

incorporates the installation of a Collins 

Model ALI–80 Altimeter and a Model 

MSI–80 Mach Airspeed Indicator as 

primary instruments. These digital 

instruments would perform critical 

functions, that is, functions whose 

failure would prevent the continued 

safe flight and landing of the airplane. 

The Altimeter and Mach Airspeed 

Indicator to be installed in the airplane 

have the potential to be vulnerable to 

high-intensity radiated fields (HIRF) 

external to the airplane. 

Type Certification Basis 

Under the provisions of 14 CFR 

21.101, Amendment 21–69, effective 

September 16, 1991, Long Beach 

Avionics must show that the Model 

Falcon 10 airplane, as changed, 

continues to meet the applicable 

provisions of the regulations 

incorporated by reference in Type 

Certificate No. A33EU 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 Type Certificate No. A33EU 

include 14 CFR part 25, as amended by 

Amendments 25–1 through 25–20. 

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 modified DassaultBreguet Model Falcon 10 airplane 

because of a novel or unusual design 

feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Model Falcon 10 

1162 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations 

airplane must comply with the fuel vent 

and exhaust emission requirements of 

14 CFR part 34 and the noise 

certification requirements of 14 CFR 

part 36. 

Special conditions, as defined in 14 

CFR 11.19, are issued in accordance 

with § 11.38 and become part of the type 

certification basis in accordance with 

§ 21.101. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should Long Beach Avionics 

apply at a later date for a supplemental 

type certificate to modify any other 

model included on the same type 

certificate to incorporate the same or 

similar novel or unusual design feature, 

these special conditions would also 

apply to the other model under the 

provisions of § 21.101. 

Novel or Unusual Design Features 

The Dassault-Breguet Model Falcon 

10 airplane modified by Long Beach 

Avionics will incorporate new digital 

equipment that will perform critical 

functions. These systems may be 

vulnerable to HIRF external to the 

airplane. The current airworthiness 

standards of part 25 do not contain 

adequate or appropriate safety standards 

for the protection of this equipment 

from the adverse effects of HIRF. 

Accordingly, this system is considered 

to be a novel or unusual design feature. 

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 avionics/

electronics and electrical 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 needed 

for the Dassault-Breguet Model Falcon 

10 airplane modified by Long Beach 

Avionics. These special conditions 

require that new digital equipment 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 and the advent of space and 

satellite communications, coupled with 

electronic command and control of the 

airplane, the immunity of critical digital 

avionics/electronics and electrical 

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 paragraph 1 or 2 below: 

1. A minimum threat of 100 volts rms 

(root-mean-square) per meter 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 field strengths indicated in the 

following table for the frequency ranges 

indicated. Both peak and average field 

strength components from the table are 

to be demonstrated.

Frequency 

Field strength

(volts per meter) 

Peak Average 

10 kHz–100 kHz ... 50 50 

100 kHz–500 kHz 50 50 

500 kHz–2 MHz .... 50 50 

2 MHz–30 MHz ..... 100 100 

30 MHz–70 MHz ... 50 50 

70 MHz–100 MHz 50 50 

100 MHz–200 MHz 100 100 

200 MHz–400 MHz 100 100 

400 MHz–700 MHz 700 50 

700 MHz–1 GHz ... 700 100 

1 GHz–2 GHz ....... 2000 200 

2GHz–4 GHz ........ 3000 200 

4 GHz–6 GHz ....... 3000 200 

6 GHz–8 GHz ....... 1000 200 

8 GHz–12 GHz ..... 3000 300 

12 GHz–18 GHz ... 2000 200 

18 GHz–40 GHz ... 600 200 

The field strengths are expressed in terms 

of peak of the root-mean-square (rms) over 

the complete modulation period. 

The threat levels identified above are 

the result of an FAA review of existing 

studies on the subject of HIRF, in light 

of the ongoing work of the 

Electromagnetic Effects Harmonization 

Working Group of the Aviation 

Rulemaking Advisory Committee. 

Applicability 

As discussed above, these special 

conditions are applicable to a DassaultBreguet Model Falcon 10 airplane 

modified by Long Beach Avionics. 

Should Long Beach Avionics apply at a 

later date for a supplemental type 

certificate to modify any other model 

included on Type Certificate A33EU to 

incorporate the same or similar novel or 

unusual design feature, these special 

conditions would apply to that model as 

well as under the provisions of 14 CFR 

21.101. 

Conclusion 

This action affects only certain design 

features on the Dassault-Breguet Model 

Falcon 10 airplane modified by Long 

Beach Avionics. It is not a rule of 

general applicability and affects only 

the applicant which applied to the FAA 

for approval of these features on the 

airplane. 

The substance of the special 

conditions for this airplane has been 

subjected to the notice and comment 

procedure in several prior instances and 

has been derived without substantive 

change from those previously issued. 

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. 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 record keeping requirements.

■ The authority citation for these special 

conditions 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 supplemental type 

certification basis for the modified 

Dassault-Breguet Model Falcon 10 

airplane: 

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 

Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations 1163

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, on 

December 23, 2004. 

Kevin Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–236 Filed 1–5–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 25

[Docket No. NM287; Special Conditions No. 

25–281–SC] 

Special Conditions: Airbus Model 

A330, A340–200 and A340–300 Series 

Airplanes; Lower Deck Mobile Crew 

Rest (LD–MCR) Compartment

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final special conditions.

SUMMARY: These special conditions are 

issued for the Airbus Model A330, 

A340–200, and A340–300 series 

airplanes. These airplanes will have 

novel or unusual design features 

associated with a lower deck mobile 

crew rest (LD–MCR) compartment. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

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.

EFFECTIVE DATE: December 23, 2004.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, FAA, International Branch, 

ANM–116, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue SW., 

Renton, Washington, 98055–4056; 

telephone (425) 227–2797; facsimile 

(425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Background 

On March 20, 2003, Airbus applied 

for a change to Type Certificate 

Numbers A46NM and A43NM to permit 

installation of an LD–MCR compartment 

in Airbus Model A330, A340–200, and 

A340–300 series airplanes. 

The LD–MCR compartment will be 

located under the passenger cabin floor 

in the aft cargo compartment of Airbus 

Model A330, A340–200, and A340–300 

series airplanes. It will be the size of a 

standard airfreight container and will be 

removable from the cargo compartment. 

The LD–MCR compartment will be 

occupied in flight but not during taxi, 

takeoff, or landing. No more than seven 

crewmembers at a time will be 

permitted to occupy it. The LD–MCR 

compartment will have a smoke 

detection system, a fire suppression 

system, and an oxygen system. 

The LD–MCR compartment will be 

accessed from the main deck via a 

‘‘stairhouse.’’ The floor within the 

stairhouse has a hatch that leads to 

stairs which occupants use to descend 

into the LD–MCR compartment. An 

interface will keep this hatch open 

when the stairhouse door is open. In 

addition, there will be an emergency 

hatch which opens directly into the 

main passenger cabin. The LD–MCR 

compartment has a maintenance door. 

This door is intended to be used to 

allow maintenance personnel and cargo 

handlers to enter the LD–MCR from the 

cargo compartment when the airplane is 

not in flight. 

Type Certification Basis 

Under the provisions of § 21.101, 

Airbus must show that Airbus Model 

A330, A340–200, and A340–300 series 

airplanes, as changed, continue to meet 

(1) the applicable provisions of the 

regulations incorporated by reference in 

A46NM (for Airbus Model A330) and in 

A43NM (for Airbus Model A340–200 

and A340–300 series airplanes) or (2) 

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 A46NM 

and A43NM are as follows: 

The certification basis for Airbus 

Models A330–300, A340–200, and 

A340–300 series airplanes is 14 CFR 

part 25, as amended by Amendments 

25–1 through 25–63; certain regulations 

at later Amendments 25–65, 25–66, and 

25–77; and Amendment 25–64 with 

exceptions. Refer to Type Certificate 

Data Sheet (TCDS) A46NM or A43NM, 

as applicable, for a complete description 

of the certification basis for these 

models, including certain special 

conditions that are not relevant to these 

proposed special conditions. 

The certification basis for Airbus 

Model A330–200 series airplanes is 14 

CFR part 25, as amended by 

Amendments 25–1 through 25–63, 25–

65, 25–66, 25–68, 25–69, 25–73, 25–75, 

25–77, 25–78, 25–81, 25–82, 25–84 and 

25–85; certain regulations at 

Amendments 25–72 and 25–74; and 

Amendment 25–64 with exceptions. 

Refer to TCDS A46NM for a complete 

description of the certification basis for 

that model, including certain special 

conditions that are not relevant to these 

proposed special conditions. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for Airbus Model A330, A340–200, and 

A340–300 series airplanes because of a 

novel or unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, Airbus Model A330, A340–

200, and A340–300 series airplanes 

must comply with the fuel vent and 

exhaust emission requirements of 14 

CFR part 34 and the noise certification 

requirements of 14 CFR part 36. 

Special conditions, as defined in 

§ 11.19, are issued in accordance with 

§ 11.38 and become part of the type 

certification basis in accordance with 

§ 21.101. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same or similar novel 

or unusual design feature, or should any 

other model already included on the 

same type certificate be modified to 

incorporate the same or similar novel or 

unusual design feature, the special 

conditions would also apply to the other 

model under the provisions of § 21.101.

Novel or Unusual Design Features 

While the installation of a crew rest 

compartment is not a new concept for 

large transport category airplanes, each 

crew rest compartment has unique 

features based on design, location, and 

use on the airplane. The LD–MCR 

compartment is novel in terms of part 

25 in that it will be located below the 

passenger cabin floor in the aft cargo 

compartment of Airbus Model A330, 

A340–200, and A340–300 series 

airplanes. Due to the novel or unusual 

features associated with the installation 

of a LD–MCR compartment, special 

conditions are considered necessary to 

provide a level of safety equal to that 

established by the airworthiness 

regulations incorporated by reference in 

the type certificates of these airplanes. 

These special conditions do not negate 

the need to address other applicable 

part 25 regulations.