Special Conditions: Societe de Motorisation Aeronautiques (SMA) Engines, Inc., Cessna Models 182Q and 182R; Diesel Cycle Engine Using Turbine (Jet) Fuel, 41101-41104 [E6-11474]
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
Frequency
Field strength
(volts per meter)
Peak
10 kHz–100 kHz .......
100 kHz–500 kHz .....
500 kHz–2 MHz ........
2 MHz–30 MHz .........
30 MHz–70 MHz .......
70 MHz–100 MHz .....
100 MHz–200 MHz ...
200 MHz–400 MHz ...
400 MHz–700 MHz ...
700 MHz–1 GHz .......
1 GHz–2 GHz ...........
2 GHz–4 GHz ...........
4 GHz–6 GHz ...........
6 GHz–8 GHz ...........
8 GHz–12 GHz .........
12 GHz–18 GHz .......
18 GHz–40 GHz .......
Average
50
50
50
100
50
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
50
50
50
100
50
50
100
100
50
100
200
200
200
200
300
200
200
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The field strengths are expressed in terms
of peak root-mean-square (rms) values.
or,
(2) The applicant may demonstrate by
a system test and analysis that the
electrical and electronic systems that
perform critical functions can withstand
a minimum threat of 100 volts per
meter, electrical field strength, from 10
kHz to 18 GHz. When using this test to
show compliance with the HIRF
requirements, no credit is given for
signal attenuation due to installation.
A preliminary hazard analysis must
be performed by the applicant, for
approval by the FAA, to identify either
electrical or electronic systems that
perform critical functions. The term
‘‘critical’’ means those functions whose
failure would contribute to, or cause, a
failure condition that would prevent the
continued safe flight and landing of the
airplane. The systems identified by the
hazard analysis that perform critical
functions are candidates for the
application of HIRF requirements. A
system may perform both critical and
non-critical functions. Primary
electronic flight display systems, and
their associated components, perform
critical functions such as attitude,
altitude, and airspeed indication. The
HIRF requirements apply only to critical
functions.
Compliance with HIRF requirements
may be demonstrated by tests, analysis,
models, similarity with existing
systems, or any combination of these.
Service experience alone is not
acceptable since normal flight
operations may not include an exposure
to the HIRF environment. Reliance on a
system with similar design features for
redundancy as a means of protection
against the effects of external HIRF is
generally insufficient since all elements
of a redundant system are likely to be
exposed to the fields concurrently.
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Applicability
As discussed above, these special
conditions are applicable to one
modification to the airplane models
listed under the heading ‘‘Type
Certification Basis.’’ Should Cirrus
Design Corporation apply at a later date
for a supplemental type certificate to
modify any other model on the same
type certificate to incorporate 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 of one
modification to several models of
airplanes. It is not a rule of general
applicability and affects only the
applicant who applied to the FAA for
approval of these features on the
airplane.
The substance of these special
conditions has been subjected to the
notice and comment period 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 some airplane
models, the FAA has determined that
prior public notice and comment are
unnecessary and impracticable, and
good cause exists for adopting these
special conditions 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 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 21.101; and 14 CFR
11.38 and 11.19.
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 airplane models
listed under the ‘‘Type Certification
Basis’’ heading modified by Cirrus
Design Corporation to add an EFIS.
1. Protection of Electrical and
Electronic Systems from High Intensity
Radiated Fields (HIRF). Each system
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41101
that performs critical functions must be
designed and installed to ensure that the
operations, and operational capabilities
of these systems to perform critical
functions, are not adversely affected
when the airplane is exposed to high
intensity radiated electromagnetic fields
external to the airplane.
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 Kansas City, Missouri on July 11,
2006.
Steve W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11483 Filed 7–19–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE239; Special Condition No.
23–179–SC]
Special Conditions: Societe de
Motorisation Aeronautiques (SMA)
Engines, Inc., Cessna Models 182Q
and 182R; Diesel Cycle Engine Using
Turbine (Jet) Fuel
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
SUMMARY: These special conditions are
issued for the Cessna Models 182Q and
182R airplanes with a Societe de
Motorisation Aeronautiques (SMA)
Model SR305–230 aircraft diesel engine
(ADE). This airplane will have a novel
or unusual design feature(s) associated
with the installation of a diesel cycle
engine utilizing turbine (jet) fuel. The
applicable airworthiness regulations do
not contain adequate or appropriate
safety standards for installation of this
new technology engine. 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: July 11, 2006.
FOR FURTHER INFORMATION CONTACT:
Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Kansas City,
Missouri, 816–329–4135, fax 816–329–
4090.
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
SUPPLEMENTARY INFORMATION:
Background
On March 19, 2004, SMA Engines,
Inc., applied for a supplemental type
certificate for the installation of an SMA
Model SR305–230 ADE, type
certificated in the United States, type
certificate number E00067EN, in the
Cessna Models 182Q and 182R
airplanes. The Cessna Models 182Q and
182R airplanes, approved under Type
Certificate No. 3A13, are four-place,
single engine airplanes.
In anticipation of the reintroduction
of diesel engine technology into the
small airplane fleet, the FAA issued
Policy Statement PS–ACE100–2002–004
on May 15, 2004, which identified areas
of technological concern involving
introduction of new technology diesel
engines into small airplanes. For a more
detailed summary of the FAA’s
development of diesel engine
requirements, refer to this policy.
The general areas of concern involved
the power characteristics of the diesel
engines, the use of turbine fuel in an
airplane class that has typically been
powered by gasoline fueled engines, and
the vibration characteristics and failure
modes of diesel engines. These concerns
were identified after review of the
historical record of diesel engine used
in aircraft and a review of the 14 CFR
part 23 regulations, which identified
specific regulatory areas that needed to
be evaluated for applicability to diesel
engine installations. These concerns are
not considered universally applicable to
all types of possible diesel engines and
diesel engine installations. However,
after review of the SMA installation,
and applying the provisions of the
diesel policy, the FAA proposed these
fuel system and engine related special
conditions. Other special conditions
issued in a separate notice include
special conditions for HIRF and
application of § 23.1309 provisions to
the Full Authority Digital Engine
Control (FADEC).
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Type Certification Basis
Under the provisions of § 21.101,
SMA Engines, Inc., must show that the
Cessna Models 182Q and 182R airplanes
with the installation of an SMA Model
SR305–230 ADE meet the applicable
provisions of 14 CFR part 23, as
amended by Amendments 23–1 through
23–51 and CAR 3 thereto. In addition,
the certification basis includes special
conditions and equivalent levels of
safety for the following:
Special Conditions:
• Engine torque (Provisions similar to
§ 23.361, paragraphs (b)(1) and (c)(3)).
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• Flutter (Compliance with § 23.629,
paragraphs (e)(1) and (2)).
• Powerplant—Installation
(Provisions similar to § 23.901(d)(1) for
turbine engines).
• Powerplant—Fuel System—Fuel
system with water saturated fuel
(Compliance with § 23.951
requirements).
• Powerplant—Fuel System—Fuel
system hot weather operation
(Compliance with § 23.961
requirements).
• Powerplant—Fuel system—Fuel
tank filler connection (Compliance with
§ 23.973(f) requirements).
• Powerplant—Fuel system—Fuel
tank outlet (Compliance with § 23.977
requirements).
• Equipment—General—Powerplant
Instruments (Compliance with § 23.1305
requirements).
• Operating Limitations and
Information—Powerplant limitations—
Fuel grade or designation (Compliance
with § 23.1521(d) requirements).
• Markings And Placards—
Miscellaneous markings and placards—
Fuel, oil, and coolant filler openings
(Compliance with § 23.1557(c)(1)
requirements).
• Powerplant—Fuel system—Fuel
Freezing.
• Powerplant Installation—Vibration
levels.
• Powerplant Installation—One
cylinder inoperative.
• Powerplant Installation—High
Energy Engine Fragments.
Equivalent levels of safety for:
• Cockpit controls—23.777(d).
• Motion and effect of cockpit
controls—23.779(b).
• Ignition switches—23.1145.
The type certification basis includes
exemptions, if any; equivalent level of
safety findings, if any; and the special
conditions adopted by this rulemaking
action.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., part 23) do not contain adequate or
appropriate safety standards for the
Cessna Models 182Q and 182R airplanes
with the installation of an SMA Model
SR305–230 ADE 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 Cessna Models 182Q
and 182R airplanes with the installation
of an SMA Model SR305–230 ADE 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 appropriate, as
defined in 11.19, are issued in
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accordance with § 11.38, 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 Models 182Q and 182R
airplanes with the installation of an
SMA Model SR305–230 will incorporate
the following novel or unusual design
features:
The Cessna Models 182Q and 182R
airplanes with the installation of an
SMA Model SR305–230 will incorporate
an aircraft diesel engine utilizing
turbine (jet) fuel.
Discussion of Comments
A notice of proposed special
conditions No. 23–06–01–SC for the
Cessna Models 182Q and 182R airplanes
with a SMA Model SR305–230 ADE was
published on February 17, 2006 (71 FR
8543). No comments were received, and
the special conditions are adopted as
proposed.
Applicability
As discussed above, these special
conditions are applicable to the Cessna
Models 182Q and 182R airplanes with
an SMA Model SR305–230 ADE. Should
SMA apply at a later date for a
supplemental type certificate to modify
any other model included on Type
Certificate No. 3A13 to incorporate the
same novel or unusual design feature,
the special conditions would apply to
that model as well under the provisions
of § 21.101(a)(1).
Conclusion
This action affects only certain novel
or unusual design features on the
Cessna Models 182Q and 182R airplanes
with a SMA Model SR305–230 ADE. 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.
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:
I
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.101 and 14 CFR
11.38 and 11.19.
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 the Cessna Models 182Q and
182R airplanes with an SMA Model
SR305–230 ADE.
I
1. Engine Torque (Provisions Similar to
§ 23.361, Paragraphs (b)(1) and (c)(3))
(a) For diesel engine installations, the
engine mounts and supporting structure
must be designed to withstand the
following:
(1) A limit engine torque load
imposed by sudden engine stoppage due
to malfunction or structural failure.
The effects of sudden engine stoppage
may alternately be mitigated to an
acceptable level by utilization of
isolators, dampers, clutches and similar
provisions, so that unacceptable load
levels are not imposed on the previously
certificated structure.
(b) The limit engine torque obtained
in CAR 3.195(a)(1) and (a)(2) or 14 CFR
23.361(a)(1) and (a)(2) must be obtained
by multiplying the mean torque by a
factor of four in lieu of the factor of two
required by CAR 3.195(b) and 14 CFR
23.361(c)(3).
2. Flutter—(Compliance With § 23.629
(e)(1) and (e)(2) Requirements)
The flutter evaluation of the airplane
done in accordance with 14 CFR 23.629
must include—
(a) Whirl mode degree of freedom,
which takes into account the stability of
the plane of rotation of the propeller
and significant elastic, inertial, and
aerodynamic forces, and
(b) Propeller, engine, engine mount,
and airplane structure stiffness, and
damping variations appropriate to the
particular configuration, and
(c) Showing the airplane is free from
flutter with one cylinder inoperative.
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3. Powerplant—Installation (Provisions
Similar to § 23.901(d)(1) for Turbine
Engines)
Considering the vibration
characteristics of diesel engines, the
applicant must comply with the
following:
(a) Each diesel engine installation
must be constructed and arranged to
result in vibration characteristics that—
(1) Do not exceed those established
during the type certification of the
engine; and
(2) Do not exceed vibration
characteristics that a previously
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certificated airframe structure has been
approved for—
(i) Unless such vibration
characteristics are shown to have no
effect on safety or continued
airworthiness, or
(ii) Unless mitigated to an acceptable
level by utilization of isolators,
dampers, clutches and similar
provisions, so that unacceptable
vibration levels are not imposed on the
previously certificated structure.
4. Powerplant—Fuel System—Fuel
System With Water Saturated Fuel
(Compliance With § 23.951
Requirements)
Considering the fuel types used by
diesel engines, the applicant must
comply with the following:
Each fuel system for a diesel engine
must be capable of sustained operation
throughout its flow and pressure range
with fuel initially saturated with water
at 80 °F and having 0.75cc of free water
per gallon added and cooled to the most
critical condition for icing likely to be
encountered in operation.
Methods of compliance that are
acceptable for turbine engine fuel
systems requirements of § 23.951(c) are
also considered acceptable for this
requirement.
5. Powerplant—Fuel System—Fuel Flow
(Compliance With § 23.955(c)
Requirements)
In lieu of 14 CFR 23.955(c), engine
fuel system must provide at least 100
percent of the fuel flow required by the
engine, or the fuel flow required to
prevent engine damage, if that flow is
greater than 100 percent. The fuel flow
rate must be available to the engine
under each intended operating
condition and maneuver. The
conditions may be simulated in a
suitable mockup. This flow must be
shown in the most adverse fuel feed
condition with respect to altitudes,
attitudes, and any other condition that
is expected in operation.
6. Powerplant—Fuel System—Fuel
System Hot Weather Operation
(Compliance With § 23.961
Requirements)
In place of compliance with § 23.961,
the applicant must comply with the
following:
Each fuel system must be free from
vapor lock when using fuel at its critical
temperature, with respect to vapor
formation, when operating the airplane
in all critical operating and
environmental conditions for which
approval is requested. For turbine fuel,
or for aircraft equipped with diesel
cycle engines that use turbine or diesel
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41103
type fuels, the initial temperature must
be 110 °F, ¥0°, +5° or the maximum
outside air temperature for which
approval is requested, whichever is
more critical.
The fuel system must be in an
operational configuration that will yield
the most adverse, that is, conservative
results.
To comply with this requirement, the
applicant must use the turbine fuel
requirements and must substantiate
these by flight-testing, as described in
Advisory Circular AC 23–8B, Flight Test
Guide for Certification of Part 23
Airplanes.
7. Powerplant—Fuel System—Fuel Tank
Filler Connection (Compliance With
§ 23.973(f) Requirements)
In place of compliance with
§ 23.973(e) and (f), the applicant must
comply with the following:
For airplanes that operate on turbine
or diesel type fuels, the inside diameter
of the fuel filler opening must be no
smaller than 2.95 inches.
8. Powerplant—Fuel System—Fuel Tank
Outlet (Compliance With § 23.977
Requirements)
In place of compliance with
§ 23.977(a)(1) and (a)(2), the applicant
will comply with the following:
There must be a fuel strainer for the
fuel tank outlet or for the booster pump.
This strainer must, for diesel engine
powered airplanes, prevent the passage
of any object that could restrict fuel flow
or damage any fuel system component.
9. Equipment—General—Powerplant
Instruments (Compliance With
§ 23.1305)
In addition to compliance with
§ 23.1305, the applicant will comply
with the following:
The following are required in addition
to the powerplant instruments required
in § 23.1305:
(a) A fuel temperature indicator.
(b) An outside air temperature (OAT)
indicator.
(c) An indicating means for the fuel
strainer or filter required by § 23.997 to
indicate the occurrence of
contamination of the strainer or filter
before it reaches the capacity
established in accordance with
§ 23.997(d).
Alternately, no indicator is required if
the engine can operate normally for a
specified period with the fuel strainer
exposed to the maximum fuel
contamination as specified in MIL–
5007D and provisions for replacing the
fuel filter at this specified period (or a
shorter period) are included in the
maintenance schedule for the engine
installation.
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Federal Register / Vol. 71, No. 139 / Thursday, July 20, 2006 / Rules and Regulations
10. Operating Limitations and
Information—Powerplant Limitations—
Fuel Grade or Designation (Compliance
With § 23.1521 Requirements)
All engine parameters that have limits
specified by the engine manufacturer for
takeoff or continuous operation must be
investigated to ensure they remain
within those limits throughout the
expected flight and ground envelopes
(e.g., maximum and minimum fuel
temperatures, ambient temperatures, as
applicable, etc.). This is in addition to
the existing requirements specified by
14 CFR 23.1521(b) and (c). If any of
those limits can be exceeded, there must
be continuous indication to the flight
crew of the status of that parameter with
appropriate limitation markings.
Instead of compliance with
§ 23.1521(d), the applicant must comply
with the following:
The minimum fuel designation (for
diesel engines) must be established so
that it is not less than that required for
the operation of the engines within the
limitations in paragraphs (b) and (c) of
§ 23.1521.
11. Markings and Placards—
Miscellaneous Markings and Placards—
Fuel, Oil, and Coolant Filler Openings
(Compliance With § 23.1557(c)(1)
Requirements)
Instead of compliance with
§ 23.1557(c)(1), the applicant must
comply with the following:
Fuel filler openings must be marked
at or near the filler cover with—
For diesel engine-powered
airplanes—
(a) The words ‘‘Jet Fuel’’; and
(b) The permissible fuel designations,
or references to the Airplane Flight
Manual (AFM) for permissible fuel
designations.
(c) A warning placard or note that
states the following or similar:
‘‘Warning—this airplane equipped
with an aircraft diesel engine, service
with approved fuels only.’’
The colors of this warning placard
should be black and white.
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12. Powerplant—Fuel System—FuelFreezing
If the fuel in the tanks cannot be
shown to flow suitably under all
possible temperature conditions, then
fuel temperature limitations are
required. These will be considered as
part of the essential operating
parameters for the aircraft and must be
limitations.
A minimum takeoff temperature
limitation will be determined by testing
to establish the minimum cold-soaked
temperature at which the airplane can
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operate. The minimum operating
temperature will be determined by
testing to establish the minimum
operating temperature acceptable after
takeoff from the minimum takeoff
temperature. If low temperature limits
are not established by testing, then a
minimum takeoff and operating fuel
temperature limit of 5 °F above the
gelling temperature of Jet A will be
imposed along with a display in the
cockpit of the fuel temperature. Fuel
temperature sensors will be located in
the coldest part of the tank if applicable.
13. Powerplant Installation—Vibration
Levels
Vibration levels throughout the
engine operating range must be
evaluated and:
(1) Vibration levels imposed on the
airframe must be less than or equivalent
to those of the gasoline engine; or
(2) Any vibration level that is higher
than that imposed on the airframe by
the replaced gasoline engine must be
considered in the modification and the
effects on the technical areas covered by
the following paragraphs must be
investigated: 14 CFR 23.251; 23.613;
23.627; 23.629 (or CAR 3.159, as
applicable to various models); 23.572;
23.573; 23.574 and 23.901.
Vibration levels imposed on the
airframe can be mitigated to an
acceptable level by utilization of
isolators, dampers, clutches, and similar
provisions, so that unacceptable
vibration levels are not imposed on the
previously certificated structure.
14. Powerplant Installation—One
Cylinder Inoperative
It must be shown by test or analysis,
or by a combination of methods, that the
airframe can withstand the shaking or
vibratory forces imposed by the engine
if a cylinder becomes inoperative. Diesel
engines of conventional design typically
have extremely high levels of vibration
when a cylinder becomes inoperative.
No unsafe condition will exist in the
case of an inoperative cylinder before
the engine can be shut down. The
resistance of the airframe structure,
propeller, and engine mount to shaking
moment and vibration damage must be
investigated. It must be shown by test or
analysis, or by a combination of
methods, that shaking and vibration
damage from the engine with an
inoperative cylinder will not cause a
catastrophic airframe, propeller, or
engine mount failure.
15. Powerplant Installation—High
Energy Engine Fragments
It may be possible for diesel engine
cylinders (or portions thereof) to fail
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and physically separate from the engine
at high velocity (due to the high internal
pressures). This failure mode will be
considered possible in engine designs
with removable cylinders or other nonintegral block designs. The following is
required:
(1) It must be shown by the design of
the engine that engine cylinders, other
engine components or portions thereof
(fragments) cannot be shed or blown off
of the engine in the event of a
catastrophic engine failure; or
(2) It must be shown that all possible
liberated engine parts or components do
not have adequate energy to penetrate
engine cowlings; or
(3) Assuming infinite fragment
energy, and analyzing the trajectory of
the probable fragments and components,
any hazard due to liberated engine parts
or components will be minimized and
the possibility of crew injury
eliminated. Minimization must be
considered during initial design and not
presented as an analysis after design
completion.
Issued in Kansas City, Missouri, on July 11,
2006.
Steve W. Thompson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–11474 Filed 7–19–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE244, Special Condition 23–
184A–SC]
Special Condition; Avidyne
Corporation, Inc.; Various Airplane
Models; Protection of Systems for
High Intensity Radiated Fields (HIRF)
Federal Aviation
Administration (FAA), DOT.
ACTION: Amended final special
conditions; request for comments.
AGENCY:
SUMMARY: These amended special
conditions are issued to Avidyne
Corporation, 55 Old Bedford Road,
Lincoln, MA 01773. This is an
amendment to special condition 23–
184–SC, which was published on May
23, 2006 (71 FR 29574), for installation
of an EFIS manufactured by Avidyne on
various models. The original issue left
off the Cirrus Design Corporation SR22,
which was the first model to be certified
under the STC.
The airplanes listed under this multimodel approval will have novel and
unusual design features when compared
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]]>Agencies
[Federal Register Volume 71, Number 139 (Thursday, July 20, 2006)]
[Rules and Regulations]
[Pages 41101-41104]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-11474]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE239; Special Condition No. 23-179-SC]
Special Conditions: Societe de Motorisation Aeronautiques (SMA)
Engines, Inc., Cessna Models 182Q and 182R; Diesel Cycle Engine Using
Turbine (Jet) Fuel
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Cessna Models 182Q
and 182R airplanes with a Societe de Motorisation Aeronautiques (SMA)
Model SR305-230 aircraft diesel engine (ADE). This airplane will have a
novel or unusual design feature(s) associated with the installation of
a diesel cycle engine utilizing turbine (jet) fuel. The applicable
airworthiness regulations do not contain adequate or appropriate safety
standards for installation of this new technology engine. 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: July 11, 2006.
FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4135,
fax 816-329-4090.
[[Page 41102]]
SUPPLEMENTARY INFORMATION:
Background
On March 19, 2004, SMA Engines, Inc., applied for a supplemental
type certificate for the installation of an SMA Model SR305-230 ADE,
type certificated in the United States, type certificate number
E00067EN, in the Cessna Models 182Q and 182R airplanes. The Cessna
Models 182Q and 182R airplanes, approved under Type Certificate No.
3A13, are four-place, single engine airplanes.
In anticipation of the reintroduction of diesel engine technology
into the small airplane fleet, the FAA issued Policy Statement PS-
ACE100-2002-004 on May 15, 2004, which identified areas of
technological concern involving introduction of new technology diesel
engines into small airplanes. For a more detailed summary of the FAA's
development of diesel engine requirements, refer to this policy.
The general areas of concern involved the power characteristics of
the diesel engines, the use of turbine fuel in an airplane class that
has typically been powered by gasoline fueled engines, and the
vibration characteristics and failure modes of diesel engines. These
concerns were identified after review of the historical record of
diesel engine used in aircraft and a review of the 14 CFR part 23
regulations, which identified specific regulatory areas that needed to
be evaluated for applicability to diesel engine installations. These
concerns are not considered universally applicable to all types of
possible diesel engines and diesel engine installations. However, after
review of the SMA installation, and applying the provisions of the
diesel policy, the FAA proposed these fuel system and engine related
special conditions. Other special conditions issued in a separate
notice include special conditions for HIRF and application of Sec.
23.1309 provisions to the Full Authority Digital Engine Control
(FADEC).
Type Certification Basis
Under the provisions of Sec. 21.101, SMA Engines, Inc., must show
that the Cessna Models 182Q and 182R airplanes with the installation of
an SMA Model SR305-230 ADE meet the applicable provisions of 14 CFR
part 23, as amended by Amendments 23-1 through 23-51 and CAR 3 thereto.
In addition, the certification basis includes special conditions and
equivalent levels of safety for the following:
Special Conditions:
Engine torque (Provisions similar to Sec. 23.361,
paragraphs (b)(1) and (c)(3)).
Flutter (Compliance with Sec. 23.629, paragraphs (e)(1)
and (2)).
Powerplant--Installation (Provisions similar to Sec.
23.901(d)(1) for turbine engines).
Powerplant--Fuel System--Fuel system with water saturated
fuel (Compliance with Sec. 23.951 requirements).
Powerplant--Fuel System--Fuel system hot weather operation
(Compliance with Sec. 23.961 requirements).
Powerplant--Fuel system--Fuel tank filler connection
(Compliance with Sec. 23.973(f) requirements).
Powerplant--Fuel system--Fuel tank outlet (Compliance with
Sec. 23.977 requirements).
Equipment--General--Powerplant Instruments (Compliance
with Sec. 23.1305 requirements).
Operating Limitations and Information--Powerplant
limitations--Fuel grade or designation (Compliance with Sec.
23.1521(d) requirements).
Markings And Placards--Miscellaneous markings and
placards--Fuel, oil, and coolant filler openings (Compliance with Sec.
23.1557(c)(1) requirements).
Powerplant--Fuel system--Fuel Freezing.
Powerplant Installation--Vibration levels.
Powerplant Installation--One cylinder inoperative.
Powerplant Installation--High Energy Engine Fragments.
Equivalent levels of safety for:
Cockpit controls--23.777(d).
Motion and effect of cockpit controls--23.779(b).
Ignition switches--23.1145.
The type certification basis includes exemptions, if any;
equivalent level of safety findings, if any; and the special conditions
adopted by this rulemaking action.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 23) do not contain adequate or appropriate
safety standards for the Cessna Models 182Q and 182R airplanes with the
installation of an SMA Model SR305-230 ADE 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 Cessna Models 182Q and 182R airplanes with the
installation of an SMA Model SR305-230 ADE 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 appropriate, as defined in 11.19, are issued
in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 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 Sec. 21.101(a)(1).
Novel or Unusual Design Features
The Cessna Models 182Q and 182R airplanes with the installation of
an SMA Model SR305-230 will incorporate the following novel or unusual
design features:
The Cessna Models 182Q and 182R airplanes with the installation of
an SMA Model SR305-230 will incorporate an aircraft diesel engine
utilizing turbine (jet) fuel.
Discussion of Comments
A notice of proposed special conditions No. 23-06-01-SC for the
Cessna Models 182Q and 182R airplanes with a SMA Model SR305-230 ADE
was published on February 17, 2006 (71 FR 8543). No comments were
received, and the special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Models 182Q and 182R airplanes with an SMA Model SR305-230 ADE.
Should SMA apply at a later date for a supplemental type certificate to
modify any other model included on Type Certificate No. 3A13 to
incorporate the same novel or unusual design feature, the special
conditions would apply to that model as well under the provisions of
Sec. 21.101(a)(1).
Conclusion
This action affects only certain novel or unusual design features
on the Cessna Models 182Q and 182R airplanes with a SMA Model SR305-230
ADE. 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.
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:
[[Page 41103]]
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.101 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 the Cessna Models 182Q and 182R
airplanes with an SMA Model SR305-230 ADE.
1. Engine Torque (Provisions Similar to Sec. 23.361, Paragraphs (b)(1)
and (c)(3))
(a) For diesel engine installations, the engine mounts and
supporting structure must be designed to withstand the following:
(1) A limit engine torque load imposed by sudden engine stoppage
due to malfunction or structural failure.
The effects of sudden engine stoppage may alternately be mitigated
to an acceptable level by utilization of isolators, dampers, clutches
and similar provisions, so that unacceptable load levels are not
imposed on the previously certificated structure.
(b) The limit engine torque obtained in CAR 3.195(a)(1) and (a)(2)
or 14 CFR 23.361(a)(1) and (a)(2) must be obtained by multiplying the
mean torque by a factor of four in lieu of the factor of two required
by CAR 3.195(b) and 14 CFR 23.361(c)(3).
2. Flutter--(Compliance With Sec. 23.629 (e)(1) and (e)(2)
Requirements)
The flutter evaluation of the airplane done in accordance with 14
CFR 23.629 must include--
(a) Whirl mode degree of freedom, which takes into account the
stability of the plane of rotation of the propeller and significant
elastic, inertial, and aerodynamic forces, and
(b) Propeller, engine, engine mount, and airplane structure
stiffness, and damping variations appropriate to the particular
configuration, and
(c) Showing the airplane is free from flutter with one cylinder
inoperative.
3. Powerplant--Installation (Provisions Similar to Sec. 23.901(d)(1)
for Turbine Engines)
Considering the vibration characteristics of diesel engines, the
applicant must comply with the following:
(a) Each diesel engine installation must be constructed and
arranged to result in vibration characteristics that--
(1) Do not exceed those established during the type certification
of the engine; and
(2) Do not exceed vibration characteristics that a previously
certificated airframe structure has been approved for--
(i) Unless such vibration characteristics are shown to have no
effect on safety or continued airworthiness, or
(ii) Unless mitigated to an acceptable level by utilization of
isolators, dampers, clutches and similar provisions, so that
unacceptable vibration levels are not imposed on the previously
certificated structure.
4. Powerplant--Fuel System--Fuel System With Water Saturated Fuel
(Compliance With Sec. 23.951 Requirements)
Considering the fuel types used by diesel engines, the applicant
must comply with the following:
Each fuel system for a diesel engine must be capable of sustained
operation throughout its flow and pressure range with fuel initially
saturated with water at 80 [deg]F and having 0.75cc of free water per
gallon added and cooled to the most critical condition for icing likely
to be encountered in operation.
Methods of compliance that are acceptable for turbine engine fuel
systems requirements of Sec. 23.951(c) are also considered acceptable
for this requirement.
5. Powerplant--Fuel System--Fuel Flow (Compliance With Sec. 23.955(c)
Requirements)
In lieu of 14 CFR 23.955(c), engine fuel system must provide at
least 100 percent of the fuel flow required by the engine, or the fuel
flow required to prevent engine damage, if that flow is greater than
100 percent. The fuel flow rate must be available to the engine under
each intended operating condition and maneuver. The conditions may be
simulated in a suitable mockup. This flow must be shown in the most
adverse fuel feed condition with respect to altitudes, attitudes, and
any other condition that is expected in operation.
6. Powerplant--Fuel System--Fuel System Hot Weather Operation
(Compliance With Sec. 23.961 Requirements)
In place of compliance with Sec. 23.961, the applicant must comply
with the following:
Each fuel system must be free from vapor lock when using fuel at
its critical temperature, with respect to vapor formation, when
operating the airplane in all critical operating and environmental
conditions for which approval is requested. For turbine fuel, or for
aircraft equipped with diesel cycle engines that use turbine or diesel
type fuels, the initial temperature must be 110 [deg]F, -0[deg],
+5[deg] or the maximum outside air temperature for which approval is
requested, whichever is more critical.
The fuel system must be in an operational configuration that will
yield the most adverse, that is, conservative results.
To comply with this requirement, the applicant must use the turbine
fuel requirements and must substantiate these by flight-testing, as
described in Advisory Circular AC 23-8B, Flight Test Guide for
Certification of Part 23 Airplanes.
7. Powerplant--Fuel System--Fuel Tank Filler Connection (Compliance
With Sec. 23.973(f) Requirements)
In place of compliance with Sec. 23.973(e) and (f), the applicant
must comply with the following:
For airplanes that operate on turbine or diesel type fuels, the
inside diameter of the fuel filler opening must be no smaller than 2.95
inches.
8. Powerplant--Fuel System--Fuel Tank Outlet (Compliance With Sec.
23.977 Requirements)
In place of compliance with Sec. 23.977(a)(1) and (a)(2), the
applicant will comply with the following:
There must be a fuel strainer for the fuel tank outlet or for the
booster pump. This strainer must, for diesel engine powered airplanes,
prevent the passage of any object that could restrict fuel flow or
damage any fuel system component.
9. Equipment--General--Powerplant Instruments (Compliance With Sec.
23.1305)
In addition to compliance with Sec. 23.1305, the applicant will
comply with the following:
The following are required in addition to the powerplant
instruments required in Sec. 23.1305:
(a) A fuel temperature indicator.
(b) An outside air temperature (OAT) indicator.
(c) An indicating means for the fuel strainer or filter required by
Sec. 23.997 to indicate the occurrence of contamination of the
strainer or filter before it reaches the capacity established in
accordance with Sec. 23.997(d).
Alternately, no indicator is required if the engine can operate
normally for a specified period with the fuel strainer exposed to the
maximum fuel contamination as specified in MIL-5007D and provisions for
replacing the fuel filter at this specified period (or a shorter
period) are included in the maintenance schedule for the engine
installation.
[[Page 41104]]
10. Operating Limitations and Information--Powerplant Limitations--Fuel
Grade or Designation (Compliance With Sec. 23.1521 Requirements)
All engine parameters that have limits specified by the engine
manufacturer for takeoff or continuous operation must be investigated
to ensure they remain within those limits throughout the expected
flight and ground envelopes (e.g., maximum and minimum fuel
temperatures, ambient temperatures, as applicable, etc.). This is in
addition to the existing requirements specified by 14 CFR 23.1521(b)
and (c). If any of those limits can be exceeded, there must be
continuous indication to the flight crew of the status of that
parameter with appropriate limitation markings.
Instead of compliance with Sec. 23.1521(d), the applicant must
comply with the following:
The minimum fuel designation (for diesel engines) must be
established so that it is not less than that required for the operation
of the engines within the limitations in paragraphs (b) and (c) of
Sec. 23.1521.
11. Markings and Placards--Miscellaneous Markings and Placards--Fuel,
Oil, and Coolant Filler Openings (Compliance With Sec. 23.1557(c)(1)
Requirements)
Instead of compliance with Sec. 23.1557(c)(1), the applicant must
comply with the following:
Fuel filler openings must be marked at or near the filler cover
with--
For diesel engine-powered airplanes--
(a) The words ``Jet Fuel''; and
(b) The permissible fuel designations, or references to the
Airplane Flight Manual (AFM) for permissible fuel designations.
(c) A warning placard or note that states the following or similar:
``Warning--this airplane equipped with an aircraft diesel engine,
service with approved fuels only.''
The colors of this warning placard should be black and white.
12. Powerplant--Fuel System--Fuel-Freezing
If the fuel in the tanks cannot be shown to flow suitably under all
possible temperature conditions, then fuel temperature limitations are
required. These will be considered as part of the essential operating
parameters for the aircraft and must be limitations.
A minimum takeoff temperature limitation will be determined by
testing to establish the minimum cold-soaked temperature at which the
airplane can operate. The minimum operating temperature will be
determined by testing to establish the minimum operating temperature
acceptable after takeoff from the minimum takeoff temperature. If low
temperature limits are not established by testing, then a minimum
takeoff and operating fuel temperature limit of 5 [deg]F above the
gelling temperature of Jet A will be imposed along with a display in
the cockpit of the fuel temperature. Fuel temperature sensors will be
located in the coldest part of the tank if applicable.
13. Powerplant Installation--Vibration Levels
Vibration levels throughout the engine operating range must be
evaluated and:
(1) Vibration levels imposed on the airframe must be less than or
equivalent to those of the gasoline engine; or
(2) Any vibration level that is higher than that imposed on the
airframe by the replaced gasoline engine must be considered in the
modification and the effects on the technical areas covered by the
following paragraphs must be investigated: 14 CFR 23.251; 23.613;
23.627; 23.629 (or CAR 3.159, as applicable to various models); 23.572;
23.573; 23.574 and 23.901.
Vibration levels imposed on the airframe can be mitigated to an
acceptable level by utilization of isolators, dampers, clutches, and
similar provisions, so that unacceptable vibration levels are not
imposed on the previously certificated structure.
14. Powerplant Installation--One Cylinder Inoperative
It must be shown by test or analysis, or by a combination of
methods, that the airframe can withstand the shaking or vibratory
forces imposed by the engine if a cylinder becomes inoperative. Diesel
engines of conventional design typically have extremely high levels of
vibration when a cylinder becomes inoperative.
No unsafe condition will exist in the case of an inoperative
cylinder before the engine can be shut down. The resistance of the
airframe structure, propeller, and engine mount to shaking moment and
vibration damage must be investigated. It must be shown by test or
analysis, or by a combination of methods, that shaking and vibration
damage from the engine with an inoperative cylinder will not cause a
catastrophic airframe, propeller, or engine mount failure.
15. Powerplant Installation--High Energy Engine Fragments
It may be possible for diesel engine cylinders (or portions
thereof) to fail and physically separate from the engine at high
velocity (due to the high internal pressures). This failure mode will
be considered possible in engine designs with removable cylinders or
other non-integral block designs. The following is required:
(1) It must be shown by the design of the engine that engine
cylinders, other engine components or portions thereof (fragments)
cannot be shed or blown off of the engine in the event of a
catastrophic engine failure; or
(2) It must be shown that all possible liberated engine parts or
components do not have adequate energy to penetrate engine cowlings; or
(3) Assuming infinite fragment energy, and analyzing the trajectory
of the probable fragments and components, any hazard due to liberated
engine parts or components will be minimized and the possibility of
crew injury eliminated. Minimization must be considered during initial
design and not presented as an analysis after design completion.
Issued in Kansas City, Missouri, on July 11, 2006.
Steve W. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-11474 Filed 7-19-06; 8:45 am]
BILLING CODE 4910-13-P
