Special Conditions; Honda Aircraft Company, Model HA-420 HondaJet Airplane; Fire Extinguishing, 54675-54677 [E8-22154]
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Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Rules and Regulations
List of Subjects in 13 CFR Part 123
Disaster assistance, Loan programs—
business, Reporting and recordkeeping
requirements, Small businesses.
■ For the reasons set forth in the
preamble, the Small Business
Administration amends 13 CFR part 123
as follows:
§ 123.503 When can you apply for a
Military Reservist EIDL?
Your small business can apply for a
Military Reservist EIDL any time
beginning on the date your essential
employee receives notice of expected
call-up and ending one year after the
date the essential employee is
discharged or released from active duty.
The Associate Administrator for
Disaster Assistance (AA/DA) or
designee may extend the one year limit
by no more then one additional year
after finding extraordinary or
unforeseeable circumstances.
*
*
*
*
*
■ 7. Revise § 123.504(a) to read as
follows:
PART 123—DISASTER LOAN
PROGRAM
1. The authority citation for part 123
is revised to read as follows:
■
Authority: 15 U.S.C. 634(b)(6), 636(b), 636
(c); Pub. L. 102–395, 106 Stat. 1828, 1864;
and Pub. L. 103–75, 107 Stat. 739; and Pub.
L. 106–50, 113 Stat. 245; and Pub. L. 110–
186.
2. Amend § 123.3(a) by revising the
first sentence to read as follows:
■
*
§ 123.3 How are disaster declarations
made?
(a) There are five ways in which
disaster declarations are issued which
make SBA disaster loans possible:
*
*
*
*
*
■ 3. Revise § 123.11, introductory text,
to read as follows:
§ 123.11 Does SBA require collateral for
any of its disaster loans?
Generally, SBA will not require that
you pledge collateral to secure a disaster
home loan or a physical disaster
business loan of $10,000 or less, or an
economic injury disaster loan of $5,000
or less. However, for the purposes of the
Military Reservist EIDL only, as
described in section 123.513, SBA will
not generally require that you pledge
collateral to secure a loan of $50,000 or
less. For loans larger than these
amounts, you will be required to
provide available collateral such as a
lien on the damaged or replacement
property, a security interest in personal
property, or both.
*
*
*
*
*
■ 4. Revise the heading of § 123.501 to
read as follows:
§ 123.501 Under what circumstances is
your business eligible to be considered for
a Military Reservist Economic Injury
Disaster Loan?
*
*
*
*
■ 5. Revise the heading of § 123.502 to
read as follows:
jlentini on PROD1PC65 with RULES
*
§ 123.502 Under what circumstances is
your business ineligible to be considered
for a Military Reservist Economic Injury
Disaster Loan?
*
■
*
*
*
*
6. Revise § 123.503 to read as follows:
VerDate Aug<31>2005
16:35 Sep 22, 2008
Jkt 214001
§ 123.504 How do you apply for a Military
Reservist EIDL?
*
*
*
*
(a) A copy of the essential employee’s
official call-up orders for active duty
showing the date of call-up, and, if
known, the date of release from active
duty. For an essential employee who
expects to be called up and who has not
received official call-up orders, the
application shall include the notice of
the expected call-up including, if
known, the expected date of call-up and
expected date of release from active
duty;
*
*
*
*
*
■ 8. Revise § 123.506 to read as follows:
§ 123.506 How much can you borrow
under the Military Reservist EIDL Program?
You can borrow an amount equal to
the substantial economic injury you
have suffered or are likely to suffer until
normal operations resume as a result of
the absence of one or more essential
employees called to active duty, up to
a maximum of $2 million.
■ 9. Revise the heading of § 123.507, the
introductory text and paragraph (b) to
read as follows:
§ 123.507 Under what circumstances will
SBA consider waiving the $2 million loan
limit?
SBA will consider waiving the $2
million dollar limit if you can certify to
the following conditions and SBA
approves of such certification based on
the information supplied in your
application:
*
*
*
*
*
(b) Your small business is in
imminent danger of going out of
business as a result of one or more
essential employees being called up to
active duty during a period of military
conflict, and a loan in excess of $2
million is necessary to reopen or keep
open the small business; and
*
*
*
*
*
PO 00000
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Fmt 4700
Sfmt 4700
54675
10. Revise § 123.511 to read as
follows:
■
§ 123.511 How will SBA disburse Military
Reservist EIDL funds?
Funds will be disbursed only after the
essential employee has been called to
active duty, and you have provided a
copy of the essential employee’s official
call-up orders for active duty showing
the date of the call-up. SBA will
disburse your funds in quarterly
installments (unless otherwise specified
in your loan authorization agreement)
based on a continued need as
demonstrated by comparative financial
information. On or about 30 days before
your scheduled fund disbursement, SBA
will request ordinary and usual
financial statements (including balance
sheets and profit and loss statements).
Based on this information, SBA will
assess your continued need for
disbursements under this program.
Upon making such assessment, SBA
will notify you of the status of future
disbursements.
■ 11. Add § 123.513 to read as follows:
§ 123.513 Does SBA require collateral on
its Military Reservist EIDL?
SBA will not generally require you to
pledge collateral to secure a Military
Reservist EIDL of $50,000 or less. For
loans larger than $50,000, you will be
required to provide available collateral
such as a lien on business property, a
security interest in personal property, or
both. SBA will not decline a loan if you
do not have a particular amount of
collateral so long as SBA is reasonably
sure that you can repay the loan. If you
refuse to pledge the available collateral
when requested by SBA, however, SBA
may decline or cancel your loan.
Sandy K. Baruah,
Acting Administrator.
[FR Doc. E8–21995 Filed 9–22–08; 8:45 am]
BILLING CODE 8025–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE287, Special Conditions No.
23–227–SC]
Special Conditions; Honda Aircraft
Company, Model HA–420 HondaJet
Airplane; Fire Extinguishing
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
SUMMARY: This notice issues special
conditions for the Honda Aircraft
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Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Rules and Regulations
jlentini on PROD1PC65 with RULES
Company, Model HA–420 HondaJet
Airplane. This new airplane will have
novel and unusual design features not
typically associated with normal, utility,
acrobatic, and commuter category
airplanes. These design features include
turbofan engines and engine location,
for which the applicable regulations do
not contain adequate or appropriate
airworthiness standards. These special
conditions contain the additional
airworthiness standards that the
Administrator considers necessary to
establish a level of safety equivalent to
that established by the existing
airworthiness standards.
DATES: Effective Date: September 15,
2008.
FOR FURTHER INFORMATION CONTACT:
Leslie B. Taylor, Aerospace Engineer,
Standards Office (ACE–110), Small
Airplane Directorate, Aircraft
Certification Service, Federal Aviation
Administration, Room 301, 901 Locust
Street, Kansas City, Missouri 64106;
telephone (816) 329–4134, e-mail:
leslie.b.taylor@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
On October 11, 2006, Honda Aircraft
Company, Greensboro, North Carolina,
made an application to the FAA for a
new Type Certificate for the Honda
Model HA–420 HondaJet. The Honda
Model HA–420 HondaJet is an all new
very light jet, twin engine, high
performance, low wing, aft overwing
mounted turbofan engine powered
aircraft in the normal category including
flight into known icing conditions,
Reduced Vertical Separation Minima
(RVSM) and single pilot operations. The
Model HA–420 HondaJet design criteria
includes: 9963 pounds maximum gross
weight, estimated maximum speed of
258 KIAS/0.72 Mach, cruise speed of
420 KTAS at 30,000 feet, and a 43,000
foot maximum altitude.
Part 23 has historically addressed fire
protection through prevention,
identification, and containment.
Prevention has been provided through
minimizing the potential for ignition of
flammable fluids and vapors.
Identification has traditionally been
provided by the location of the engines
within the pilot’s primary field of view
and/or with the incorporation of fire
detection systems. This philosophy has
provided for both the rapid detection of
a fire and confirmation when it has been
extinguished. Containment has been
provided through the isolation of
designated fire zones through flammable
fluid shutoff valves and firewalls. The
containment philosophy also ensures
that components of the engine control
VerDate Aug<31>2005
16:35 Sep 22, 2008
Jkt 214001
system will function effectively to
permit a safe shutdown of the engine.
However, containment has only been
required to be demonstrated for 15
minutes. In event of a fire in a
traditional part 23 airplane, the
corrective action is to land as soon as
possible. For a small, simple aircraft
originally envisioned by part 23, it is
possible to descend the aircraft to a
suitable landing site within 15 minutes.
Thus, if the fire is not extinguished, the
occupants can safely exit the aircraft
before the firewall is breached. These
simple and traditional aircraft normally
have the engine located away from
critical flight control systems and
primary structure. This has ensured
that, throughout the fire event, the pilot
can continue safe flight and control. It
has also made predicting the effects of
a fire relatively easy. Other design
features of these simple and traditional
aircraft, such as low stall speeds and
short landing distances, ensure that,
even in the event of an off-field landing,
the potential for a catastrophic outcome
has been minimized.
The certification basis for the Model
HA–420 HondaJet does require that a
fire detection system be installed.
However, due to the engine location,
fire extinguishing is also considered a
requirement. A sustained fire could
result in loss of control of the airplane
and damage to the primary structure
before an emergency landing could be
made.
Type Certification Basis
Under the provisions of 14 CFR, part
21, § 21.17, Honda Aircraft Company
must show that the Model HA–420
HondaJet meets the applicable
provisions of 14 CFR, part 23, effective
February 1, 1965, as amended by
Amendments 23–1 through Amendment
23–55, effective March 1, 2002; 14 CFR,
part 36, effective December 1, 1969,
through the amendment effective on the
date of type certification; 14 CFR, part
34; exemptions, if any; and the special
conditions adopted by this rulemaking
action.
Discussion
Special conditions, as appropriate, as
defined in § 11.19, are issued in
accordance with § 11.38, and become
part of the type certification basis in
accordance with § 21.17.
Novel or Unusual Design Features
The Honda Aircraft Company, Model
HA–420 HondaJet will incorporate the
following novel or unusual design
features:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
Engine Fire Extinguishing System
The Model HA–420 HondaJet design
includes engines mounted aft on the top
of the wings; therefore, early visual
detection of engine fires is precluded.
The applicable existing regulations do
not require fire extinguishing systems
for engines. Aft mounted engine
installations were not envisaged in the
development of part 23; therefore,
special conditions for a fire
extinguishing system with the
applicable agents, containers, and
materials for the engines of the Model
HA–420 HondaJet are appropriate.
Discussion of Comments
A notice of proposed special
conditions, Notice No. 23–08–04–SC,
for the Model HA–420 HondaJet was
published on June 25, 2008 (73 FR
35979). No comments were received,
and the special conditions are adopted
as proposed.
Applicability
As discussed above, these special
conditions are applicable to the Model
HA–420 HondaJet. Should Honda
Aircraft Company apply at a later date
for a change to the type certificate to
include another model incorporating the
same novel or unusual design feature,
the special conditions would apply to
that model as well under the provisions
of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on one model
of airplane. It is not a rule of general
applicability, and it affects only the
applicant who applied to the FAA for
approval of these features on the
airplane identified.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
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 Final Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) issues the
following special conditions as part of
the type certification basis for the
Honda Aircraft Company, Model HA–
420 HondaJet airplane:
SC 23.1195, Fire extinguishing
systems—Add the requirements of 14
CFR § 23.1195 as modified below while
deleting, ‘‘For commuter category
airplanes.’’
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23SER1
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Federal Register / Vol. 73, No. 185 / Tuesday, September 23, 2008 / Rules and Regulations
(a) Fire extinguishing systems must be
installed and compliance must be
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 the extinguishing agent, the
rate of discharge, and the discharge
distribution must be adequate to
extinguish fires. An individual ‘‘one
shot’’ system may be used except for
embedded engines where a ‘‘two-shot’’
system is required.
(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.
SC 23.1197, Fire extinguishing
agents—Add the requirement of 14 CFR
§ 23.1197 while deleting, ‘‘For
commuter category airplanes.’’
(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 builtin 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.
SC 23.1199, Extinguishing agent
containers—Add the requirements of 14
CFR § 23.1199 while deleting, ‘‘For
commuter category airplanes.’’
VerDate Aug<31>2005
16:35 Sep 22, 2008
Jkt 214001
(a) Each extinguishing agent container
must have a pressure relief to prevent
bursting of the container by excessive
internal pressures.
(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 extinguishing agent, each
container must be installed so that
temperature conditions will not cause
hazardous deterioration of the
pyrotechnic capsule.
SC 23.1201, Fire extinguishing
systems materials—Add the
requirements of § 23.1201 while
deleting, ‘‘For commuter category
airplanes.’’
Fire extinguisher system materials
must meet the following requirements:
(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
September 15, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–22154 Filed 9–22–08; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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54677
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0461; Directorate
Identifier 2008–NE–14–AD; Amendment 39–
15678; AD 2008–19–11]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Arrius 2B1, 2B1A, 2B2, and 2K1
Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
provided by the European Aviation
Safety Agency (EASA) to identify and
correct an unsafe condition on
Turbomeca S.A. Arrius 2B1, 2B1A, 2B2,
and 2K1 turboshaft engines. The MCAI
describes the unsafe condition as:
A short circuit of some tantalum capacitors
inside certain electronic control (EEC) units
may lead to an in-flight shutdown on one of
the two engines resulting from:
—Direct activation of the overspeed
electronic protection;
—Non-direct activation of the electronic
overspeed protection by lowering the
threshold,
—Spurious activation of the starting
sequence; or
—Loss of power control with no freeze of the
fuel-metering valve.
We are issuing this AD to prevent inflight engine shutdowns and possible
forced autorotation landing or accident.
DATES: This AD becomes effective
October 8, 2008.
The Director of the Federal Register
approved the incorporation by reference
of Turbomeca S.A. Mandatory Service
Bulletin No. 319 73 2835, Update No. 1,
dated December 21, 2006, listed in the
AD as of October 8, 2008.
We must receive comments on this
AD by October 23, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
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]]>Agencies
[Federal Register Volume 73, Number 185 (Tuesday, September 23, 2008)]
[Rules and Regulations]
[Pages 54675-54677]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-22154]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE287, Special Conditions No. 23-227-SC]
Special Conditions; Honda Aircraft Company, Model HA-420 HondaJet
Airplane; Fire Extinguishing
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: This notice issues special conditions for the Honda Aircraft
[[Page 54676]]
Company, Model HA-420 HondaJet Airplane. This new airplane will have
novel and unusual design features not typically associated with normal,
utility, acrobatic, and commuter category airplanes. These design
features include turbofan engines and engine location, for which the
applicable regulations do not contain adequate or appropriate
airworthiness standards. These special conditions contain the
additional airworthiness standards that the Administrator considers
necessary to establish a level of safety equivalent to that established
by the existing airworthiness standards.
DATES: Effective Date: September 15, 2008.
FOR FURTHER INFORMATION CONTACT: Leslie B. Taylor, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, Room 301, 901
Locust Street, Kansas City, Missouri 64106; telephone (816) 329-4134,
e-mail: leslie.b.taylor@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
On October 11, 2006, Honda Aircraft Company, Greensboro, North
Carolina, made an application to the FAA for a new Type Certificate for
the Honda Model HA-420 HondaJet. The Honda Model HA-420 HondaJet is an
all new very light jet, twin engine, high performance, low wing, aft
overwing mounted turbofan engine powered aircraft in the normal
category including flight into known icing conditions, Reduced Vertical
Separation Minima (RVSM) and single pilot operations. The Model HA-420
HondaJet design criteria includes: 9963 pounds maximum gross weight,
estimated maximum speed of 258 KIAS/0.72 Mach, cruise speed of 420 KTAS
at 30,000 feet, and a 43,000 foot maximum altitude.
Part 23 has historically addressed fire protection through
prevention, identification, and containment. Prevention has been
provided through minimizing the potential for ignition of flammable
fluids and vapors. Identification has traditionally been provided by
the location of the engines within the pilot's primary field of view
and/or with the incorporation of fire detection systems. This
philosophy has provided for both the rapid detection of a fire and
confirmation when it has been extinguished. Containment has been
provided through the isolation of designated fire zones through
flammable fluid shutoff valves and firewalls. The containment
philosophy also ensures that components of the engine control system
will function effectively to permit a safe shutdown of the engine.
However, containment has only been required to be demonstrated for 15
minutes. In event of a fire in a traditional part 23 airplane, the
corrective action is to land as soon as possible. For a small, simple
aircraft originally envisioned by part 23, it is possible to descend
the aircraft to a suitable landing site within 15 minutes. Thus, if the
fire is not extinguished, the occupants can safely exit the aircraft
before the firewall is breached. These simple and traditional aircraft
normally have the engine located away from critical flight control
systems and primary structure. This has ensured that, throughout the
fire event, the pilot can continue safe flight and control. It has also
made predicting the effects of a fire relatively easy. Other design
features of these simple and traditional aircraft, such as low stall
speeds and short landing distances, ensure that, even in the event of
an off-field landing, the potential for a catastrophic outcome has been
minimized.
The certification basis for the Model HA-420 HondaJet does require
that a fire detection system be installed. However, due to the engine
location, fire extinguishing is also considered a requirement. A
sustained fire could result in loss of control of the airplane and
damage to the primary structure before an emergency landing could be
made.
Type Certification Basis
Under the provisions of 14 CFR, part 21, Sec. 21.17, Honda
Aircraft Company must show that the Model HA-420 HondaJet meets the
applicable provisions of 14 CFR, part 23, effective February 1, 1965,
as amended by Amendments 23-1 through Amendment 23-55, effective March
1, 2002; 14 CFR, part 36, effective December 1, 1969, through the
amendment effective on the date of type certification; 14 CFR, part 34;
exemptions, if any; and the special conditions adopted by this
rulemaking action.
Discussion
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.17.
Novel or Unusual Design Features
The Honda Aircraft Company, Model HA-420 HondaJet will incorporate
the following novel or unusual design features:
Engine Fire Extinguishing System
The Model HA-420 HondaJet design includes engines mounted aft on
the top of the wings; therefore, early visual detection of engine fires
is precluded. The applicable existing regulations do not require fire
extinguishing systems for engines. Aft mounted engine installations
were not envisaged in the development of part 23; therefore, special
conditions for a fire extinguishing system with the applicable agents,
containers, and materials for the engines of the Model HA-420 HondaJet
are appropriate.
Discussion of Comments
A notice of proposed special conditions, Notice No. 23-08-04-SC,
for the Model HA-420 HondaJet was published on June 25, 2008 (73 FR
35979). No comments were received, and the special conditions are
adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Model HA-420 HondaJet. Should Honda Aircraft Company apply at a later
date for a change to the type certificate to include another model
incorporating the same novel or unusual design feature, the special
conditions would apply to that model as well under the provisions of
Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
on one model of airplane. It is not a rule of general applicability,
and it affects only the applicant who applied to the FAA for approval
of these features on the airplane identified.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
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 Final Special Conditions
Accordingly, the Federal Aviation Administration (FAA) issues the
following special conditions as part of the type certification basis
for the Honda Aircraft Company, Model HA-420 HondaJet airplane:
SC 23.1195, Fire extinguishing systems--Add the requirements of 14
CFR Sec. 23.1195 as modified below while deleting, ``For commuter
category airplanes.''
[[Page 54677]]
(a) Fire extinguishing systems must be installed and compliance
must be 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 the
extinguishing agent, the rate of discharge, and the discharge
distribution must be adequate to extinguish fires. An individual ``one
shot'' system may be used except for embedded engines where a ``two-
shot'' system is required.
(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.
SC 23.1197, Fire extinguishing agents--Add the requirement of 14
CFR Sec. 23.1197 while deleting, ``For commuter category airplanes.''
(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.
SC 23.1199, Extinguishing agent containers--Add the requirements of
14 CFR Sec. 23.1199 while deleting, ``For commuter category
airplanes.''
(a) Each extinguishing agent container must have a pressure relief
to prevent bursting of the container by excessive internal pressures.
(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 extinguishing
agent, each container must be installed so that temperature conditions
will not cause hazardous deterioration of the pyrotechnic capsule.
SC 23.1201, Fire extinguishing systems materials--Add the
requirements of Sec. 23.1201 while deleting, ``For commuter category
airplanes.''
Fire extinguisher system materials must meet the following
requirements:
(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 September 15, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-22154 Filed 9-22-08; 8:45 am]
BILLING CODE 4910-13-P
