[Federal Register Volume 72, Number 55 (Thursday, March 22, 2007)]
[Rules and Regulations]
[Pages 13436-13438]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-5183]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE263; Special Conditions No. 23-203-SC]


Special Conditions: Aviation Technology Group, Incorporated, 
Javelin Model No. 100; Firewalls for Fuselage Mounted Engines and Fire 
Extinguishing for Aft Fuselage Mounted Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Aviation 
Technology Group, Incorporated, Javelin Model No. 100 airplane. This 
airplane will have novel or unusual design features associated with aft 
mounted engine fire protection. 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.

DATES: Effective Date: March 12, 2007.

FOR FURTHER INFORMATION CONTACT: Leslie B. Taylor, Regulations & Policy 
Branch, ACE-111, Small Airplane Directorate, Aircraft Certification 
Service, 901 Locust, Kansas City, Missouri 64106; telephone (816) 329-
4134; facsimile (816) 329-4090, e-mail at <a href="/cdn-cgi/l/email-protection#f9959c8a95909cd79bd78d988095968bb99f9898d79e968f"><span class="__cf_email__" data-cfemail="58343d2b34313d763a762c392134372a183e3939763f372e">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Background

    On February 25, 2005, Aviation Technology Group, Incorporated 
applied for a type certificate for their new Javelin Model No. 100. The 
Javelin Model No. 100 is a two-place acrobatic airplane with two 
fuselage mounted turbofan engines.
    Part 23 historically addressed fire protection on multiengine 
airplanes based on the assumption that the engines are sufficiently 
separated to essentially eliminate the possibility of an engine fire 
spreading to another engine. On traditional multiengine airplanes, this 
has been achieved by locating engines on the wings separated by the 
fuselage. This configuration ensures that an engine fire on one side 
does not migrate to the opposite engine. This configuration also 
protects the opposite engine from heat radiating from the engine fire. 
Prevention, identification, and containment are traditional means of 
fire protection. Prevention has been provided through minimizing the 
potential for ignition of flammable fluids and vapors. Identification 
has been provided by locating engines within the pilots' primary field 
of view and/or with the incorporation of fire detection systems. This 
has provided both rapid detection of a fire and confirmation when it 
was extinguished. Containment has been provided through the isolation 
of designated fire zones through flammable fluid shutoff valves and 
firewalls. This philosophy also ensures that components of the engine 
control system will function effectively to permit a safe shutdown of 
an engine. However, containment has only been demonstrated for 15 
minutes. If a fire occurs in traditional part 23 airplanes, the 
appropriate corrective action is to land as soon as possible. For a 
small, simple airplane originally envisioned by part 23, it is possible 
to descend and land within 15 minutes. Thus, the occupants can safely 
exit the airplane before the firewall is breached. These simple 
airplanes normally have the engine located away from critical flight 
control systems and primary structure.

[[Page 13437]]

This has ensured that, throughout a fire event, a pilot can continue 
safe flight, and it has made the prediction of fire effects relatively 
easy.
    Title 14 CFR part 23, did not envision the type of configuration of 
the Javelin Model No. 100 airplane.

Type Certification Basis

    If the Administrator finds that the applicable airworthiness 
regulations in 14 CFR part 23 do not contain adequate or appropriate 
safety standards for the Javelin Model No. 100 because of a novel or 
unusual design feature, special conditions are prescribed under the 
provisions of Sec.  21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the Javelin Model No. 100 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.
    The FAA issues special conditions, as defined in Sec.  11.19, under 
Sec.  11.38 and they become part of the type certification basis under 
Sec.  21.17(a)(2).
    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 novel or 
unusual design feature, the special conditions would also apply to the 
other model under Sec.  21.101.

Novel or Unusual Design Features

    The Javelin Model No. 100 will incorporate the following novel or 
unusual design features:
    The Javelin Model No. 100 incorporates two turbofan engines located 
side-by-side in compartments in the aft fuselage.

Discussion of Comments

    Notice of proposed special conditions No. 23-07-01-SC for the 
Aviation Technology Group, Incorporated, Javelin Model No. 100 
airplanes was published on January 8, 2007 (72 FR 660). One comment was 
received. It agreed with the proposed special conditions. No change was 
requested.

Applicability

    As discussed above, these special conditions are applicable to the 
Javelin Model No. 100. Should Aviation Technology Group, Incorporated, 
apply at a later date for a change to the type certificate to include 
another model on the same type certificate incorporating the same novel 
or unusual design feature, the special conditions would apply to that 
model as well.

Conclusion

    This action affects only certain novel or unusual design features 
on one model of airplanes. It is not a rule of general applicability.

List of Subjects in 14 CFR Part 23

    Aircraft, Aviation safety, Signs and symbols.

Citation

0
The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 
21.17; and 14 CFR 11.38 and 11.19.

The Special Conditions

0
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 Aviation Technology Group, 
Incorporated, Javelin Model No. 100 airplanes.
    Title: Firewalls for Fuselage Mounted Engines and Fire 
Extinguishing for Aft Fuselage Mounted Engines.

Fire Isolation and Extinguishing

    The fire protection system of the airplane must include features to 
isolate each fire zone from any other zone and the airplane to maintain 
isolation of the engines during a fire. Therefore, these special 
conditions mandate that the firewall required by Sec.  23.1191 be 
extended to provide firewall isolation between either engine. These 
special conditions require that heat radiating from a fire originating 
in any fire zone must not affect components, airframe structure, 
systems, or flight controls in adjacent compartments in a way that 
endangers the airplane.
    Each fire zone should be ventilated to prevent the accumulation of 
flammable vapors. It must also be designed such that it will not allow 
entry of flammable fluids, vapors, or flames from other fire zones. It 
must be designed such that it does not create an additional fire hazard 
from the discharge of vapors or fluids.
    1. SC 23.1195--Add the requirements of Sec.  23.1195 while deleting 
``For commuter category,'' adding the requirement to ``minimize the 
probability of re-ignition,'' and deleting the statement ``An 
individual `one-shot' system may be used.''
23.1195, Fire Extinguishing Systems
    (a) Fire extinguishing systems must be installed and compliance 
shown with the following:
    (1) Except for combustor, turbine, and tailpipe sections of 
turbine-engine installations that contain lines or components carrying 
flammable fluids or gases for which a fire originating in these 
sections is shown to be controllable, a fire extinguisher system must 
serve each engine compartment;
    (2) The fire extinguishing system, the quantity of extinguishing 
agent, the rate of discharge, and the discharge distribution must be 
adequate to extinguish fires and minimize the probability of re-
ignition;
    (3) The fire extinguishing system for a nacelle must be able to 
simultaneously protect each compartment of the nacelle for which 
protection is provided.
    (b) If an auxiliary power unit is installed in any airplane 
certificated to this part, that auxiliary power unit compartment must 
be served by a fire extinguishing system meeting the requirements of 
paragraph (a)(2) of this section.
    2. SC 23.1197--Add the requirements of Sec.  23.1197 while deleting 
``For commuter category airplanes.''
23.1197, Fire Extinguishing Agents
    The following applies:
    (a) Fire extinguishing agents must--
    (1) Be capable of extinguishing flames emanating from any burning 
fluids or other combustible materials in the area protected by the fire 
extinguishing system; and
    (2) Have thermal stability over the temperature range likely to be 
experienced in the compartment in which they are stored.
    (b) If any toxic extinguishing agent is used, provisions must be 
made to prevent harmful concentrations of fluid or fluid vapors (from 
leakage during normal operation of the airplane or as a result of 
discharging the fire extinguisher on the ground or in flight) from 
entering any personnel compartment, even though a defect may exist in 
the extinguishing system. This must be shown by test except for built-
in carbon dioxide fuselage compartment fire extinguishing systems for 
which--
    (1) Five pounds or less of carbon dioxide will be discharged under 
established fire control procedures into any fuselage compartment; or
    (2) Protective breathing equipment is available for each flight 
crewmember on flight deck duty.
    3. SC 23.1199--Add the requirements of Sec.  23.1199 while deleting 
``For commuter category airplanes.''
23.1199, Extinguishing Agent Containers
    The following applies:
    (a) Each extinguishing agent container must have a pressure relief 
to prevent bursting of the container by excessive internal pressures.

[[Page 13438]]

    (b) The discharge end of each discharge line from a pressure relief 
connection must be located so that discharge of the fire-extinguishing 
agent would not damage the airplane. The line must also be located or 
protected to prevent clogging caused by ice or other foreign matter.
    (c) A means must be provided for each fire extinguishing agent 
container to indicate that the container has discharged or that the 
charging pressure is below the established minimum necessary for proper 
functioning.
    (d) The temperature of each container must be maintained, under 
intended operating conditions, to prevent the pressure in the container 
from--
    (1) Falling below that necessary to provide an adequate rate of 
discharge; or
    (2) Rising high enough to cause premature discharge.
    (e) If a pyrotechnic capsule is used to discharge the fire 
extinguishing agent, each container must be installed so that 
temperature conditions will not cause hazardous deterioration of the 
pyrotechnic capsule.
    4. SC 23.1201--Add the requirements of Sec.  23.1201 while deleting 
``For commuter category airplanes.''
23.1201, Fire Extinguishing System Materials
    The following apply:
    (a) No material in any fire extinguishing system may react 
chemically with any extinguishing agent so as to create a hazard.
    (b) Each system component in an engine compartment must be 
fireproof.

    Issued in Kansas City, Missouri, on March 12, 2007.
James E. Jackson,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-5183 Filed 3-21-07; 8:45 am]
BILLING CODE 4910-13-P


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