Special Conditions; Diamond Aircraft Industries, EFIS and Full Authority Digital Engine Control (FADEC) on the Diamond DA-42; Protection of Systems for High Intensity Radiated Fields (HIRF), 37656-37659 [05-12882]
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37656
Federal Register / Vol. 70, No. 125 / Thursday, June 30, 2005 / Rules and Regulations
Applicability
As discussed above, these special
conditions are applicable to Raytheon
Average
Model H90 (T–44A) airplanes. Should
ARINC, Inc. apply at a later date for a
50 supplemental type certificate to modify
any other model on the same type
100 certificate to incorporate the same novel
or unusual design feature, the special
100
conditions would apply to that model as
50 well under the provisions of § 21.101.
Field Strength
(volts per meter)
Frequency
Peak
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
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
100
200
200
200
200
300
200
200
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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15:12 Jun 29, 2005
Jkt 205001
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 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 the airplane,
which is imminent, the FAA has
determined that prior public notice and
comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions 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.
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 June
22, 2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12879 Filed 6–29–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. 228, Special Condition 23–167–
SC]
Special Conditions; Diamond Aircraft
Industries, EFIS and Full Authority
Digital Engine Control (FADEC) on the
Diamond DA–42; Protection of
Systems for High Intensity Radiated
Fields (HIRF)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
SUMMARY: These special conditions are
issued to Diamond Aircraft Industries
GmbH, N.A. Otto-Strasse 5, A–2700
Wiener Neistadt, Austria; telephone: 43
Citation
2622 26 700; facsimile: 43 2622 26 780,
I The authority citation for these special
as part of the FAA Type Validation of
conditions is as follows:
the Diamond Aircraft Industries Model
DA–42. This airplane will have novel
PART 23—[AMENDED]
and unusual design features when
compared to the state of technology
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.101; and 14 CFR envisaged in the applicable
airworthiness standards. These novel
11.38 and 11.19.
and unusual design features include the
The Special Conditions
installation of a Garmin Model G–1000
electronic flight instrument system
I Accordingly, pursuant to the authority
(EFIS) display, and digital engine
delegated to me by the Administrator,
controls. The applicable regulations do
the following special conditions are
not contain adequate or appropriate
issued as part of the type certification
basis for the Raytheon Model 90 (T–44A) airworthiness standards for the
airplanes modified by ARINC, Inc. to add protection of these systems from the
effects of high intensity radiated fields
the Rockwell Collins Pro Line 21
(HIRF). These special conditions
Avionics System.
contain the additional safety standards
1. Protection of Electrical and
that the Administrator considers
Electronic Systems from High Intensity
necessary to establish a level of safety
Radiated Fields (HIRF). Each system
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Federal Register / Vol. 70, No. 125 / Thursday, June 30, 2005 / Rules and Regulations
equivalent to the airworthiness
standards applicable to these airplanes.
DATES: The effective date of these
special conditions is June 22, 2005.
Comments must be received on or
before August 1, 2005.
ADDRESSES: Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
Docket No. 228, Room 506, 901 Locust,
Kansas City, Missouri 64106. All
comments must be marked: Docket No.
228. Comments may be inspected in the
Rules Docket weekdays, except Federal
holidays, between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Wes
Ryan, Aerospace Engineer, Standards
Office (ACE–110), Small Airplane
Directorate, Aircraft Certification
Service, Federal Aviation
Administration, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone
(816) 329–4127.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of the approval and thus
delivery of the affected aircraft. In
addition, the substance of these special
conditions has been subject to the
public comment process in several prior
instances with no substantive comments
received. The FAA, therefore, finds that
good cause exists for making these
special conditions effective upon
issuance.
date stamped and returned to the
commenter.
Comments Invited
Background
Diamond Aircraft Industries (DAI)
made application through European
Aviation Safety Agency (EASA) for U.S.
Type Certification for the Diamond
Aircraft Model DA–42 on August 2,
2004. The Diamond DA–42 aircraft is a
new fully composite, four place, twinengine airplane with retractable gear,
cantilever low wing and T-tail. The
airplane was certified by EASA and
listed on Type Certificate No. A005
dated May 13, 2004. Certification work
was delegated to the Austrian Civil
Authority as the JAA/Primary
Certification Authority. The airplane is
powered by two Thielert Aircraft
Engines GmbH (Thielert) TAE 125–01
aircraft diesel engines (ADE). They are
listed on U.S. engine TC No. E00069EN
and incorporate two MT-propeller,
MTV–6–A–C–F/CF187–129, U.S. TC
No. P19NE. The fuel to be used for the
Thielert TAE 125–01 aircraft diesel
engine in USA is Jet A only. The Type
Certification sought is for Day VFR/IFR
operations.
As part of the FAA validation process
for issuance of a Type Certificate in the
United States for foreign applicants, the
FAA is issuing these special conditions
to address Certification Review Items
(CRI) for novel and unusual features of
the Diamond DA–42. The proposed type
design incorporates novel or unusual
design features, including the Garmin
G1000 EFIS system, and digital engine
controls that are vulnerable to HIRF
external to the airplane.
Interested persons are invited to
submit such written data, views, or
arguments, as they may desire.
Communications should identify the
regulatory docket or notice number and
be submitted in duplicate to the address
specified above. All communications
received on or before the closing date
for comments will be considered by the
Administrator. The special conditions
may be changed in light of the
comments received. All comments
received will be available in the Rules
Docket for examination by interested
persons, both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerning
this rulemaking will be filed in the
docket. Commenters wishing the FAA to
acknowledge receipt of their comments
submitted in response to this notice
must include a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. 228.’’ The postcard will be
Type Certification Basis
Based on the provisions of 14 CFR
21.17(c), 21.29 and the Austria–US
BAA, and the FAA Order 8100.14,
Interim Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness and the Type Validation
principles, the following airworthiness
requirements are applicable to this
project, and will remain active for three
years from the date of application: The
certification basis is based on the EASA/
ACG certification basis as presented in
CRI A–01, Issue 4, Joint Certification
Basis and is harmonized at JAA JAR 23
Amendment 1, which is harmonized at
14 CFR part 23 Amendment 51. The
FAA identified FAR/EASA Significant
Standards Differences (SSDs),
documented in our CRIs for the
validation.
The Garmin G1000 was originally
approved at part 23 Amendment 49 for
§ 23.1301, § 23.1309, § 23.1311,
§ 23.1322, and other applicable rules for
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37657
electronic displays, but is approved at
Amendment 51 for this installation. The
digital engine control was certified
under part 33 and Amendment 20 with
the engine, but is approved at part 23
Amendment 51 with the rest of the DA–
42 for § 23.1309 and other applicable
regulations for this installation. The
certification basis also includes any
applicable exemptions, equivalent
levels of safety, and the terms of these
special conditions.
Discussion
If the Administrator finds that the
applicable airworthiness standards do
not contain adequate or appropriate
safety standards because of novel or
unusual design features of an airplane,
special conditions are prescribed under
the provisions of § 21.16.
Special conditions, as appropriate, as
defined in § 11.19, are issued in
accordance with § 11.38 after public
notice 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 already
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.
Novel or Unusual Design Features
Diamond Aircraft, Inc. plans to
incorporate certain novel and unusual
design features into the Diamond DA–42
airplane for which the airworthiness
standards do not contain adequate or
appropriate safety standards for
protection from the effects of HIRF.
These features include the G1000 EFIS
and two digital engine controls, which
are susceptible to the HIRF environment
and were not envisaged by the existing
regulations for this type of airplane.
Though the digital engine control
systems were initially certificated to 14
CFR part 33, the regulatory
requirements in 14 CFR part 23 for
evaluating the installation of complex
systems, including electronic systems,
are contained in § 23.1309.
When § 23.1309 was developed, the
use of electronic control systems for
engines was not envisioned. The
§ 23.1309 requirements were originally
not applied to systems certificated as
part of an approved engine
(§ 23.1309(f)(1)). Also, § 23.1309(f)(1)
implies evaluation of the engine
system’s effects is not required.
However, the installation specifics of
the electronic engine control systems on
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Federal Register / Vol. 70, No. 125 / Thursday, June 30, 2005 / Rules and Regulations
the DA–42 requires evaluation due to
the possible effects on or by other
airplane systems (e.g., radio interference
with other airplane electronic systems,
shared engine and airplane power
sources) using § 23.1309. The integral
nature of these systems makes it
unfeasible to evaluate the airplane
portion of the system without including
the engine portion of the system. Also,
electronic control systems often require
inputs from airplane data and power
sources and outputs to other airplane
systems (e.g., automated cockpit
powerplant controls such as mixture
setting). Therefore, special conditions
are proposed to provide HIRF protection
for the EFIS and digital engine controls
and to evaluate the installation for
compliance with the requirements of
§ 23.1309(a) through (e) at Amendment
23–51 for the Diamond DA–42.
Protection of Systems From High
Intensity Radiated Fields (HIRF)
Recent advances in technology have
given rise to the application in aircraft
designs of advanced electrical and
electronic systems that perform
functions required for continued safe
flight and landing. Due to the use of
sensitive solid-state advanced
components in analog and digital
electronics circuits, these advanced
systems are readily responsive to the
transient effects of induced electrical
current and voltage caused by the HIRF.
The HIRF can degrade electronic
systems performance by damaging
components or upsetting system
functions.
Furthermore, the HIRF environment
has undergone a transformation that was
not foreseen when the current
requirements were developed. Higher
energy levels are radiated from
transmitters that are used for radar,
radio, and television. Also, the number
of transmitters has increased
significantly. There is also uncertainty
concerning the effectiveness of airframe
shielding for HIRF. Furthermore,
coupling to cockpit-installed equipment
through the cockpit window apertures is
undefined.
The combined effect of the
technological advances in airplane
design and the changing environment
has resulted in an increased level of
vulnerability of electrical and electronic
systems required for the continued safe
flight and landing of the airplane.
Effective measures against the effects of
exposure to HIRF must be provided by
the design and installation of these
systems. The accepted maximum energy
levels in which civilian airplane system
installations must be capable of
operating safely are based on surveys
and analysis of existing radio frequency
emitters. These special conditions
require that the airplane be evaluated
under these energy levels for the
protection of the electronic system and
its associated wiring harness. These
external threat levels, which are lower
than previous required values, are
believed to represent the worst case to
which an airplane would be exposed in
the operating environment.
These special conditions require
qualification of systems that perform
critical functions, as installed in aircraft,
to the defined HIRF environment in
paragraph 1 or, as an option to a fixed
value using laboratory tests, in
paragraph 2, as follows:
(2) The applicant may demonstrate
that the operation and operational
capability of the installed electrical and
electronic systems that perform critical
functions are not adversely affected
when the aircraft is exposed to the HIRF
environment defined below:
Field Strength (volts per meter)
Frequency
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
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
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15:12 Jun 29, 2005
Jkt 205001
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
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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
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Federal Register / Vol. 70, No. 125 / Thursday, June 30, 2005 / Rules and Regulations
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.
Applicability
As discussed above, these special
conditions are applicable to the
Diamond DA–42 airplane. Should
Diamond Aircraft, Inc. 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 on one model
of airplane. 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 the airplane,
which is imminent, the FAA has
determined that prior public notice and
comment are unnecessary and
impracticable, and good cause exists for
adopting these special conditions 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.
the following special conditions are
issued as part of the type validation basis
for the Diamond DA–42 airplane with a
Garmin G1000 EFIS and digital engine
control systems.
1. Protection of Electrical and
Electronic Systems from High Intensity
Radiated Fields (HIRF). Each system
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. Electronic Engine Control System.
The installation of the electronic engine
control system must comply with the
requirements of § 23.1309(a) through (e)
at Amendment 23–51. The intent of this
requirement is not to re-evaluate the
inherent hardware reliability of the
control itself, but rather determine the
effects, including environmental effects
addressed in § 23.1309(e), on the
airplane systems and engine control
system when installing the control on
the airplane. When appropriate, engine
certification data may be used when
showing compliance with this
requirement.
3. 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.
Citation
The authority citation for these special
conditions is as follows:
I
PART 23—[AMENDED]
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,
I
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SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Boeing
Model 727 airplanes equipped with an
auxiliary fuel tank having a fuel pump
installed. This AD requires revising the
airplane flight manual to include
limitations on operating the fuel pumps
for the auxiliary fuel tank. This AD is
prompted by a design review of the fuel
pump installation, which revealed a
potential unsafe condition related to the
auxiliary fuel tank(s). We are issuing
this AD to prevent dry operation of the
fuel pumps for the auxiliary fuel tank,
which could create a potential ignition
source inside the auxiliary fuel tank that
could result in a fire or explosion of the
auxiliary fuel tank.
DATES: This AD becomes effective
August 4, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Nassif Building, Room PL–401,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6501; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
DEPARTMENT OF TRANSPORTATION
You may examine the AD docket in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the street
address stated in the ADDRESSES section.
This docket number is FAA–2005–
20355; the directorate identifier for this
docket is 2004–NM–198–AD.
Federal Aviation Administration
Discussion
Issued in Kansas City, Missouri on June 22,
2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12882 Filed 6–29–05; 8:45 am]
BILLING CODE 4910–13–P
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
37659
14 CFR Part 39
[Docket No. FAA–2005–20355; Directorate
Identifier 2004–NM–198–AD; Amendment
39–14177; AD 2005–13–40]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727 Airplanes, Equipped With an
Auxiliary Fuel Tank Having a Fuel
Pump Installed
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
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The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to Boeing Model 727 airplanes
equipped with an auxiliary fuel tank
having a fuel pump installed. That
NPRM was published in the Federal
Register on February 15, 2005 (70 FR
7695). That NPRM proposed to require
revising the airplane flight manual
(AFM) to include limitations on
operating the fuel pumps for the
auxiliary fuel tank.
Comments
We provided the public the
opportunity to participate in the
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]]>Agencies
[Federal Register Volume 70, Number 125 (Thursday, June 30, 2005)]
[Rules and Regulations]
[Pages 37656-37659]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12882]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. 228, Special Condition 23-167-SC]
Special Conditions; Diamond Aircraft Industries, EFIS and Full
Authority Digital Engine Control (FADEC) on the Diamond DA-42;
Protection of Systems for High Intensity Radiated Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued to Diamond Aircraft
Industries GmbH, N.A. Otto-Strasse 5, A-2700 Wiener Neistadt, Austria;
telephone: 43 2622 26 700; facsimile: 43 2622 26 780, as part of the
FAA Type Validation of the Diamond Aircraft Industries Model DA-42.
This airplane will have novel and unusual design features when compared
to the state of technology envisaged in the applicable airworthiness
standards. These novel and unusual design features include the
installation of a Garmin Model G-1000 electronic flight instrument
system (EFIS) display, and digital engine controls. The applicable
regulations do not contain adequate or appropriate airworthiness
standards for the protection of these systems from the effects of high
intensity radiated fields (HIRF). These special conditions contain the
additional safety standards that the Administrator considers necessary
to establish a level of safety
[[Page 37657]]
equivalent to the airworthiness standards applicable to these
airplanes.
DATES: The effective date of these special conditions is June 22, 2005.
Comments must be received on or before August 1, 2005.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. 228, Room 506, 901 Locust, Kansas City, Missouri 64106. All
comments must be marked: Docket No. 228. Comments may be inspected in
the Rules Docket weekdays, except Federal holidays, between 7:30 a.m.
and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Wes Ryan, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, 901 Locust,
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4127.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
opportunity for prior public comment hereon are impracticable because
these procedures would significantly delay issuance of the approval and
thus delivery of the affected aircraft. In addition, the substance of
these special conditions has been subject to the public comment process
in several prior instances with no substantive comments received. The
FAA, therefore, finds that good cause exists for making these special
conditions effective upon issuance.
Comments Invited
Interested persons are invited to submit such written data, views,
or arguments, as they may desire. Communications should identify the
regulatory docket or notice number and be submitted in duplicate to the
address specified above. All communications received on or before the
closing date for comments will be considered by the Administrator. The
special conditions may be changed in light of the comments received.
All comments received will be available in the Rules Docket for
examination by interested persons, both before and after the closing
date for comments. A report summarizing each substantive public contact
with FAA personnel concerning this rulemaking will be filed in the
docket. Commenters wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 228.'' The postcard will be date stamped and
returned to the commenter.
Background
Diamond Aircraft Industries (DAI) made application through European
Aviation Safety Agency (EASA) for U.S. Type Certification for the
Diamond Aircraft Model DA-42 on August 2, 2004. The Diamond DA-42
aircraft is a new fully composite, four place, twin-engine airplane
with retractable gear, cantilever low wing and T-tail. The airplane was
certified by EASA and listed on Type Certificate No. A005 dated May 13,
2004. Certification work was delegated to the Austrian Civil Authority
as the JAA/Primary Certification Authority. The airplane is powered by
two Thielert Aircraft Engines GmbH (Thielert) TAE 125-01 aircraft
diesel engines (ADE). They are listed on U.S. engine TC No. E00069EN
and incorporate two MT-propeller, MTV-6-A-C-F/CF187-129, U.S. TC No.
P19NE. The fuel to be used for the Thielert TAE 125-01 aircraft diesel
engine in USA is Jet A only. The Type Certification sought is for Day
VFR/IFR operations.
As part of the FAA validation process for issuance of a Type
Certificate in the United States for foreign applicants, the FAA is
issuing these special conditions to address Certification Review Items
(CRI) for novel and unusual features of the Diamond DA-42. The proposed
type design incorporates novel or unusual design features, including
the Garmin G1000 EFIS system, and digital engine controls that are
vulnerable to HIRF external to the airplane.
Type Certification Basis
Based on the provisions of 14 CFR 21.17(c), 21.29 and the Austria-
US BAA, and the FAA Order 8100.14, Interim Procedures for Working with
the European Community on Airworthiness Certification and Continued
Airworthiness and the Type Validation principles, the following
airworthiness requirements are applicable to this project, and will
remain active for three years from the date of application: The
certification basis is based on the EASA/ACG certification basis as
presented in CRI A-01, Issue 4, Joint Certification Basis and is
harmonized at JAA JAR 23 Amendment 1, which is harmonized at 14 CFR
part 23 Amendment 51. The FAA identified FAR/EASA Significant Standards
Differences (SSDs), documented in our CRIs for the validation.
The Garmin G1000 was originally approved at part 23 Amendment 49
for Sec. 23.1301, Sec. 23.1309, Sec. 23.1311, Sec. 23.1322, and
other applicable rules for electronic displays, but is approved at
Amendment 51 for this installation. The digital engine control was
certified under part 33 and Amendment 20 with the engine, but is
approved at part 23 Amendment 51 with the rest of the DA-42 for Sec.
23.1309 and other applicable regulations for this installation. The
certification basis also includes any applicable exemptions, equivalent
levels of safety, and the terms of these special conditions.
Discussion
If the Administrator finds that the applicable airworthiness
standards do not contain adequate or appropriate safety standards
because of novel or unusual design features of an airplane, special
conditions are prescribed under the provisions of Sec. 21.16.
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38 after public notice 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 already 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.
Novel or Unusual Design Features
Diamond Aircraft, Inc. plans to incorporate certain novel and
unusual design features into the Diamond DA-42 airplane for which the
airworthiness standards do not contain adequate or appropriate safety
standards for protection from the effects of HIRF. These features
include the G1000 EFIS and two digital engine controls, which are
susceptible to the HIRF environment and were not envisaged by the
existing regulations for this type of airplane. Though the digital
engine control systems were initially certificated to 14 CFR part 33,
the regulatory requirements in 14 CFR part 23 for evaluating the
installation of complex systems, including electronic systems, are
contained in Sec. 23.1309.
When Sec. 23.1309 was developed, the use of electronic control
systems for engines was not envisioned. The Sec. 23.1309 requirements
were originally not applied to systems certificated as part of an
approved engine (Sec. 23.1309(f)(1)). Also, Sec. 23.1309(f)(1)
implies evaluation of the engine system's effects is not required.
However, the installation specifics of the electronic engine control
systems on
[[Page 37658]]
the DA-42 requires evaluation due to the possible effects on or by
other airplane systems (e.g., radio interference with other airplane
electronic systems, shared engine and airplane power sources) using
Sec. 23.1309. The integral nature of these systems makes it unfeasible
to evaluate the airplane portion of the system without including the
engine portion of the system. Also, electronic control systems often
require inputs from airplane data and power sources and outputs to
other airplane systems (e.g., automated cockpit powerplant controls
such as mixture setting). Therefore, special conditions are proposed to
provide HIRF protection for the EFIS and digital engine controls and to
evaluate the installation for compliance with the requirements of Sec.
23.1309(a) through (e) at Amendment 23-51 for the Diamond DA-42.
Protection of Systems From High Intensity Radiated Fields (HIRF)
Recent advances in technology have given rise to the application in
aircraft designs of advanced electrical and electronic systems that
perform functions required for continued safe flight and landing. Due
to the use of sensitive solid-state advanced components in analog and
digital electronics circuits, these advanced systems are readily
responsive to the transient effects of induced electrical current and
voltage caused by the HIRF. The HIRF can degrade electronic systems
performance by damaging components or upsetting system functions.
Furthermore, the HIRF environment has undergone a transformation
that was not foreseen when the current requirements were developed.
Higher energy levels are radiated from transmitters that are used for
radar, radio, and television. Also, the number of transmitters has
increased significantly. There is also uncertainty concerning the
effectiveness of airframe shielding for HIRF. Furthermore, coupling to
cockpit-installed equipment through the cockpit window apertures is
undefined.
The combined effect of the technological advances in airplane
design and the changing environment has resulted in an increased level
of vulnerability of electrical and electronic systems required for the
continued safe flight and landing of the airplane. Effective measures
against the effects of exposure to HIRF must be provided by the design
and installation of these systems. The accepted maximum energy levels
in which civilian airplane system installations must be capable of
operating safely are based on surveys and analysis of existing radio
frequency emitters. These special conditions require that the airplane
be evaluated under these energy levels for the protection of the
electronic system and its associated wiring harness. These external
threat levels, which are lower than previous required values, are
believed to represent the worst case to which an airplane would be
exposed in the operating environment.
These special conditions require qualification of systems that
perform critical functions, as installed in aircraft, to the defined
HIRF environment in paragraph 1 or, as an option to a fixed value using
laboratory tests, in paragraph 2, as follows:
(2) The applicant may demonstrate that the operation and
operational capability of the installed electrical and electronic
systems that perform critical functions are not adversely affected when
the aircraft is exposed to the HIRF environment defined below:
------------------------------------------------------------------------
Field Strength (volts per
meter)
Frequency -------------------------------
Peak Average
------------------------------------------------------------------------
10 kHz-100 kHz.......................... 50 50
100 kHz-500 kHz......................... 50 50
500 kHz-2 MHz........................... 50 50
2 MHz-30 MHz............................ 100 100
30 MHz-70 MHZ........................... 50 50
70 MHz-100 MHz.......................... 50 50
100 MHz-200 MHz......................... 100 100
200 MHz-400 MHz......................... 100 100
400 MHz-700 MHz......................... 700 50
700 MHz-1 GHz........................... 700 100
1 GHz-2 GHz............................. 2000 200
2 GHz-4 GHz............................. 3000 200
4 GHz-6 GHz............................. 3000 200
6 GHz-8 GHz............................. 1000 200
8 GHz-12 GHz............................ 3000 300
12 GHz-18 GHz........................... 2000 200
18 GHz-40 GHz........................... 600 200
-----------------------------------------
The field strengths are expressed in terms of peak 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
[[Page 37659]]
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.
Applicability
As discussed above, these special conditions are applicable to the
Diamond DA-42 airplane. Should Diamond Aircraft, Inc. 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 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
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 the airplane,
which is imminent, the FAA has determined that prior public notice and
comment are unnecessary and impracticable, and good cause exists for
adopting these special conditions 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
0
The authority citation for these special conditions is as follows:
PART 23--[AMENDED]
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 validation basis for the Diamond DA-42 airplane with a Garmin
G1000 EFIS and digital engine control systems.
1. Protection of Electrical and Electronic Systems from High
Intensity Radiated Fields (HIRF). Each system 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. Electronic Engine Control System. The installation of the
electronic engine control system must comply with the requirements of
Sec. 23.1309(a) through (e) at Amendment 23-51. The intent of this
requirement is not to re-evaluate the inherent hardware reliability of
the control itself, but rather determine the effects, including
environmental effects addressed in Sec. 23.1309(e), on the airplane
systems and engine control system when installing the control on the
airplane. When appropriate, engine certification data may be used when
showing compliance with this requirement.
3. 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 June 22, 2005.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12882 Filed 6-29-05; 8:45 am]
BILLING CODE 4910-13-P
