Special Conditions; Lancair LC41-550FG and LC42-550FG for the Protection of Systems From High Intensity Radiated Fields (HIRF), 19254-19257 [05-7427]
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19254
Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations
(a) Authority to execute, file, and
record legal instruments. Area Office
employees are authorized to execute
and file or record any legal instruments
necessary to obtain or preserve security
for loans.
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(e) Loan disbursements. Whenever a
loan disbursement is received, lost, or
destroyed, the Rural Development
Manager will take appropriate actions
outlined in Rural Development
Instruction 2018–D.
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3. Section 1942.12 is amended by
revising paragraphs (a) and (b) to read as
follows:
I
§ 1942.12
Loan cancellation.
*
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*
*
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(a) Form Rural Development 1940–10,
‘‘Cancellation of U.S. Treasury Check
and/or Obligation.’’ The Rural
Development Manager or State Director
may prepare and execute Form Rural
Development 1940–10, Cancellation of
U.S. Treasury Check and/or Obligation,
in accordance with the Forms Manual
Insert (FMI). If the disbursement has
been received or is subsequently
received in the Area Office, the Rural
Development Manager will return it as
prescribed in Rural Development
Instruction 2018–D.
(b) Notice of Cancellation. If the
docket has been forwarded to Office of
General Counsel that office will be
notified of the cancellation by copy of
Form Rural Development 1940–10. Any
application for title insurance, if
ordered, will be cancelled. The
borrower’s attorney and engineer/
architect, if any, should be notified of
the cancellation. The Rural
Development Manager may provide the
borrower’s attorney and engineer/
architect with a copy of the notification
to the applicant. The State Director will
notify the Director of Legislative Affairs
and Public Information by telephone or
electronic mail and give the reasons for
such cancellation.
4. Section 1942.15 is revised to read as
follows:
I
§ 1942.15 Delegation and redelegation of
authority.
The State Director is responsible for
implementing the authorities in this
subpart and for issuing State
supplements redelegating authorities.
Loan and grant approval authority is in
Subpart A of Part 1901 of this chapter.
Except for loan and grant approval
authority, Rural Development Manager
may redelegate their duties to qualified
staff members.
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16:30 Apr 12, 2005
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Subpart C—Fire and Rescue and Other
Small Community Facilities Projects
5. Section 1942.123 is amended by
revising paragraphs (h)(2), (h)(3), (j), and
(l) to read as follows:
I
§ 1942.123
Loan closing.
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(h) * * *
(2) The Office of the Deputy Chief
Financial Officer will prepare a
statement of account including accrued
interest through the proposed date of
retirement and also show the daily
interest accrual. The statement of
account and the interim financing
instruments will be forwarded to the
Rural Development Manager.
(3) The Rural Development Manager
will collect interest through the actual
date of the retirement and obtain the
permanent instrument(s) of debt in
exchange for the interim financing
instruments. The permanent
instruments and the cash collection will
be forwarded to the Office of the Deputy
Chief Financial Officer immediately,
except that for notes and single
instrument bonds fully registered as to
principal and interest the original will
be retained in the Area Office and a
copy will be forwarded to the Office of
the Deputy Chief Financial Officer. In
developing the permanent instruments,
the sequence of preference set out
§ 1942.19(e) of Subpart A of Part 1942
of this chapter will be followed.
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(j) Loan disbursements. Whenever a
loan disbursement is received, lost, or
destroyed, the Rural Development
Manager will take the appropriate
actions outlined in Rural Development
Instruction 2018–D.
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(1) Review of loan closing. When the
loan has been closed, the Rural
Development Manager will submit the
completed loan closing documents and
a statement showing what was done in
closing the loan to the State Director.
The State Director will review the
documents and the Rural Development
Manager’s statement to determine
whether the transaction was closed
properly. For loans to public bodies or
Indian tribes the State Director will
forward all documents, along with a
statement that all administrative
requirements have been met, to the
Regional Attorney. The Regional
Attorney will review the submitted
material to determine whether all legal
requirements have been met. The
Regional Attorney should review Rural
Development standard forms only for
proper execution, unless the State
Director brings attention to specific
PO 00000
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Fmt 4700
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questions. Facility development should
not be held up pending receipt of the
Regional Attorney opinion. When the
review of the State Director has been
completed, and for public bodies and
Indian tribes the Regional Attorney’s
opinion has been received, the State
Director must advise the Rural
Development Manager of any
deficiencies that must be corrected and
return all material that was submitted
for review.
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Dated: March 9, 2005.
Russell T. Davis,
Administrator, Rural Housing Service.
[FR Doc. 05–7377 Filed 4–12–05; 8:45 am]
BILLING CODE 3410–XV–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE220, Special Condition 23–
160–SC]
Special Conditions; Lancair LC41–
550FG and LC42–550FG for the
Protection of Systems From 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 The Lancair Company, 22550
Nelson Road, Bend, Oregon 97701, for a
Type Design Change for the Lancair
LC41–550FG and LC42–550FG
airplanes. These airplanes 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 electronic flight
instrument system (EFIS) displays
Model 700–00006–XXX–()
manufactured by Avidyne Corporation
for which 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
equivalent to the airworthiness
standards applicable to these airplanes.
DATES: The effective date of these
special conditions is April 13, 2005.
Comments must be received on or
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Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations
Background
before May 13, 2005 for domestic,
August 11, 2005 for foreign.
Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
Docket No. CE220, Room 506, 901
Locust, Kansas City, Missouri 64106. All
comments must be marked: Docket No.
CE220. Comments may be inspected in
the Rules Docket weekdays, except
Federal holidays, between 7:30 a.m. and
4 p.m.
ADDRESSES:
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.
FOR FURTHER INFORMATION CONTACT:
The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of 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.
SUPPLEMENTARY INFORMATION:
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. CE220.’’ The postcard will
be date stamped and returned to the
commenter.
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16:30 Apr 12, 2005
Jkt 205001
In 2001 and 2002, The Lancair
Company, 22550 Nelson Road, Bend,
Oregon 97701, made applications to the
FAA for a Type Design Change for the
Lancair LC41–550FG and LC42–550FG
airplanes. The modification
incorporated an existing Supplemental
Type Certificate (STC) into the Type
Design as optional equipment on the
LC41–550FG and LC42–550FG. These
models are currently approved under
Type Certificate Data Sheet (TCDS) No.
A00003SE. The proposed modification
incorporates a novel or unusual design
feature, such as digital avionics
consisting of an EFIS, that is vulnerable
to HIRF external to the airplane.
Type Certification Basis
Under the provisions of 14 CFR part
21, § 21.101, The Lancair Company
must show that the LC41–550FG and
LC42–550FG aircraft meet the following
provisions, or the applicable regulations
in effect on the date of application for
the change to the two models.
For the LC41–550FG: Part 23 of the
Federal Aviation Regulations (FAR)
effective February 1, 1965, as amended
by 23–1 through 23–46, except for FAR
23.1305 and FAR 23.1359. FAR 23.1305
as amended through 23–52 and FAR
23.1359 as amended through 23–49.
FAR 36 as amended on the date of
certification. Application for type
certificate dated October 24, 2002.
Equivalent Level of Safety (ELOS)
Findings for Emergency exit
requirements of FAR 23.807 in
accordance with ELOS No. ACE–99–02,
as detailed in FAA memo dated
February 2, 1999 (FAA memo reference
no. 99–190S–64), and the terms of these
Special Conditions.
For the LC42–550FG: Part 23 of the
Federal Aviation Regulations (FAR)
effective February 1, 1965, as amended
by 23–1 through 23–46, except for FAR
23.1305 and FAR 23.1359. FAR 23.1305
as amended through 23–52 and FAR
23.1359 as amended through 23–49.
FAR 36 as amended on the date of
certification. Applicable Equivalent
Level of Safety (ELOS) Findings: Stall
and spin requirements of FAR’s 23.201,
23.203, and 23.221 in accordance with
ELOS No. ACE–98–1, as detailed in the
FAA memo dated September 3, 1998
(FAA memo reference no. 98–190S–581)
and ELOS No. ACE–98–2 as detailed in
the FAA memo dated October 7, 1998
(FAA memo reference no. 98–190S–
608). Emergency exit requirements of
FAR 23.807 in accordance with ELOS
No. ACE–99–02 as detailed in FAA
memo dated February 2, 1999 (FAA
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19255
memo reference no. 99–190S–64), 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.
Special conditions are initially
applicable to the model for which they
are issued. Should the applicant apply
to modify any other model already
included on the same Type Data Sheet
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
The Lancair Company plans to
incorporate certain novel and unusual
design features into an airplane for
which the airworthiness standards do
not contain adequate or appropriate
safety standards for protection from the
effects of HIRF. These features include
EFIS, which are susceptible to the HIRF
environment, that were not envisaged
by the existing regulations for this type
of airplane.
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,
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Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations
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:
(1) 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
VerDate jul<14>2003
Average
50
50
50
50
100
50
50
50
100
50
50
50
100
100
100
100
700
700
2000
3000
3000
1000
3000
2000
50
100
200
200
200
200
300
200
16:30 Apr 12, 2005
Jkt 205001
Conclusion
This action affects only certain novel
Frequency
or unusual design features being
Peak
Average
proposed for the model(s) discussed in
18 GHz–40 GHz
600
200 this special condition. It is not a rule of
general applicability and affects only
The field strengths are expressed in terms
the applicant who applied to the FAA
of peak root-mean-square (rms) values.
for approval of these features on the
or,
airplane.
The substance of these special
(2) The applicant may demonstrate by
conditions has been subjected to the
a system test and analysis that the
notice and comment period in several
electrical and electronic systems that
perform critical functions can withstand prior instances and has been derived
without substantive change from those
a minimum threat of 100 volts per
previously issued. It is unlikely that
meter, electrical field strength, from 10
prior public comment would result in a
kHz to 18 GHz. When using this test to
significant change from the substance
show compliance with the HIRF
contained herein. For this reason, and
requirements, no credit is given for
because a delay would significantly
signal attenuation due to installation.
affect the certification of the airplane,
A preliminary hazard analysis must
which is imminent, the FAA has
be performed by the applicant, for
determined that prior public notice and
approval by the FAA, to identify either
comment are unnecessary and
electrical or electronic systems that
impracticable, and good cause exists for
perform critical functions. The term
adopting these special conditions upon
‘‘critical’’ means those functions whose
issuance. The FAA is requesting
failure would contribute to, or cause, a
comments to allow interested persons to
failure condition that would prevent the
submit views that may not have been
continued safe flight and landing of the
submitted in response to the prior
airplane. The systems identified by the
opportunities for comment described
hazard analysis that perform critical
above.
functions are candidates for the
application of HIRF requirements. A
List of Subjects in 14 CFR Part 23
system may perform both critical and
Aircraft, Aviation safety, Signs and
non-critical functions. Primary
symbols.
electronic flight display systems, and
their associated components, perform
PART 23—AIRWORTHINESS
critical functions such as attitude,
STANDARDS: NORMAL, UTILITY,
altitude, and airspeed indication. The
ACROBATIC, AND COMMUTER
HIRF requirements apply only to critical CATEGORY AIRPLANES
functions.
Citation
Compliance with HIRF requirements
may be demonstrated by tests, analysis,
I The authority citation for these special
models, similarity with existing
conditions is as follows:
systems, or any combination of these.
Authority: 49 U.S.C. 106(g), 40113 and
Service experience alone is not
44701; 14 CFR 21.16 and 21.101; and 14 CFR
acceptable since normal flight
11.38 and 11.19.
operations may not include an exposure
The Special Conditions
to the HIRF environment. Reliance on a
system with similar design features for
I Accordingly, pursuant to the authority
redundancy as a means of protection
delegated to me by the Administrator,
against the effects of external HIRF is
the following special conditions are
generally insufficient since all elements issued as part of the type certification
of a redundant system are likely to be
basis for the Lancair LC41–550FG and
exposed to the fields concurrently.
LC42–550FG airplanes modified to add
an EFIS as optional equipment by the
Applicability
Lancair Company.
As discussed above, these special
1. Protection of Electrical and
conditions are applicable to the Lancair Electronic Systems from High Intensity
Company Model LC41–550FG and
Radiated Fields (HIRF). Each system
LC42–550FG airplanes. Should the
that performs critical functions must be
Lancair Company apply at a later date
designed and installed to ensure that the
for a type design change to modify any
operations, and operational capabilities
other model on the same type certificate of these systems to perform critical
to incorporate the same novel or
functions, are not adversely affected
unusual design feature, the special
when the airplane is exposed to high
conditions would apply to that model as intensity radiated electromagnetic fields
well under the provisions of § 21.101.
external to the airplane.
PO 00000
Field strength
(volts per meter)
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Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations
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 April 1,
2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–7427 Filed 4–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE221, Special Condition 23–
161–SC]
Special Conditions; Twin Commander
Aircraft Models 690C, 690D, 695, 695A,
and 695B; 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 Twin Commander Aircraft
LLC. 19010 59th DR. NE. Arlington,
WA. 98223 for a Supplemental Type
Certificate for the Twin Commander
Aircraft Models 690C, 690D, 695, 695A,
and 695B. These airplanes will have
novel and unusual design features when
compared to the state of technology
envisaged in the applicable
airworthiness standards. The novel and
unusual design features include the
installation of dual Innovative Solutions
& Support (IS&S) Air Data Display Units
(ADDU) for which 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
equivalent to the airworthiness
standards applicable to these airplanes.
DATES: The effective date of these
special conditions is April 13, 2005.
Comments must be received on or
before May 13, 2005 for domestic,
August 11, 2005 for foreign.
ADDRESSES: Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
VerDate jul<14>2003
16:30 Apr 12, 2005
Jkt 205001
Docket No. CE221, Room 506, 901
Locust, Kansas City, Missouri 64106. All
comments must be marked: Docket No.
CE221. 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. CE221.’’ The postcard will
be date stamped and returned to the
commenter.
19257
690D, 695, 695A, and 695B. The Twin
Commander Aircraft Models of concern
are approved under TCDS No. 2A4. The
proposed modification incorporates a
novel or unusual design feature, a
digital air data computer, which may be
vulnerable to HIRF external to the
airplane.
Type Certification Basis
Under the provisions of 14 CFR part
21, § 21.101, Twin Commander Aircraft
LLC. must show that the Twin
Commander Aircraft Models 690C,
690D, 695, 695A, and 695B meet the
following provisions, or the applicable
regulations in effect on the date of
application for the change. For those
areas modified or impacted by the
installation of the IS&S ADDU (Air Data
Display Unit) system, the following
paragraphs as amended by Amendments
23–1 through 23–54 must be complied
with: 23.305, 23.307, 23.365, 23.603,
23.609, 23.611, 23.613, 23.625, 23.627,
23.771, 23.773, 23.777, 23.1301,
23.1303, 23.1309, 23.1311, 23.1321,
23.1322, 23.1331, 23.1335, 23.1351,
23.1357, 23.1359, 23.1361, 23.1365,
23.1367, 23.1381, 23.1431, 23.1529,
23.1541, 23.1543, 23.1581 and the
special conditions adopted by this
rulemaking action. For systems that are
not modified or impacted by the
installation, the original certification
basis listed on TCDS No. 2A4 are still
applicable.
Background
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.
Special conditions are initially
applicable to the models 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.
On April 5, 2004, Twin Commander
Aircraft LLC. 19010 59th DR NE.
Arlington, WA. 98223, made application
to the FAA for a new Supplemental
Type Certificate for the Twin
Commander Aircraft Models 690C,
Novel or Unusual Design Features
Twin Commander Aircraft LLC. plans
to incorporate certain novel and
unusual design features into an airplane
for which the airworthiness standards
do not contain adequate or appropriate
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]]>Agencies
[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Rules and Regulations]
[Pages 19254-19257]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7427]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE220, Special Condition 23-160-SC]
Special Conditions; Lancair LC41-550FG and LC42-550FG for the
Protection of Systems From 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 The Lancair Company,
22550 Nelson Road, Bend, Oregon 97701, for a Type Design Change for the
Lancair LC41-550FG and LC42-550FG airplanes. These airplanes 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 electronic flight
instrument system (EFIS) displays Model 700-00006-XXX-( ) manufactured
by Avidyne Corporation for which 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 equivalent to the airworthiness standards applicable to
these airplanes.
DATES: The effective date of these special conditions is April 13,
2005. Comments must be received on or
[[Page 19255]]
before May 13, 2005 for domestic, August 11, 2005 for foreign.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. CE220, Room 506, 901 Locust, Kansas City, Missouri 64106.
All comments must be marked: Docket No. CE220. 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 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. CE220.'' The postcard will be date stamped and
returned to the commenter.
Background
In 2001 and 2002, The Lancair Company, 22550 Nelson Road, Bend,
Oregon 97701, made applications to the FAA for a Type Design Change for
the Lancair LC41-550FG and LC42-550FG airplanes. The modification
incorporated an existing Supplemental Type Certificate (STC) into the
Type Design as optional equipment on the LC41-550FG and LC42-550FG.
These models are currently approved under Type Certificate Data Sheet
(TCDS) No. A00003SE. The proposed modification incorporates a novel or
unusual design feature, such as digital avionics consisting of an EFIS,
that is vulnerable to HIRF external to the airplane.
Type Certification Basis
Under the provisions of 14 CFR part 21, Sec. 21.101, The Lancair
Company must show that the LC41-550FG and LC42-550FG aircraft meet the
following provisions, or the applicable regulations in effect on the
date of application for the change to the two models.
For the LC41-550FG: Part 23 of the Federal Aviation Regulations
(FAR) effective February 1, 1965, as amended by 23-1 through 23-46,
except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through
23-52 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on
the date of certification. Application for type certificate dated
October 24, 2002. Equivalent Level of Safety (ELOS) Findings for
Emergency exit requirements of FAR 23.807 in accordance with ELOS No.
ACE-99-02, as detailed in FAA memo dated February 2, 1999 (FAA memo
reference no. 99-190S-64), and the terms of these Special Conditions.
For the LC42-550FG: Part 23 of the Federal Aviation Regulations
(FAR) effective February 1, 1965, as amended by 23-1 through 23-46,
except for FAR 23.1305 and FAR 23.1359. FAR 23.1305 as amended through
23-52 and FAR 23.1359 as amended through 23-49. FAR 36 as amended on
the date of certification. Applicable Equivalent Level of Safety (ELOS)
Findings: Stall and spin requirements of FAR's 23.201, 23.203, and
23.221 in accordance with ELOS No. ACE-98-1, as detailed in the FAA
memo dated September 3, 1998 (FAA memo reference no. 98-190S-581) and
ELOS No. ACE-98-2 as detailed in the FAA memo dated October 7, 1998
(FAA memo reference no. 98-190S-608). Emergency exit requirements of
FAR 23.807 in accordance with ELOS No. ACE-99-02 as detailed in FAA
memo dated February 2, 1999 (FAA memo reference no. 99-190S-64), 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.
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply to modify any other model
already included on the same Type Data Sheet 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
The Lancair Company plans to incorporate certain novel and unusual
design features into an airplane for which the airworthiness standards
do not contain adequate or appropriate safety standards for protection
from the effects of HIRF. These features include EFIS, which are
susceptible to the HIRF environment, that were not envisaged by the
existing regulations for this type of airplane.
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,
[[Page 19256]]
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:
(1) 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 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
Lancair Company Model LC41-550FG and LC42-550FG airplanes. Should the
Lancair Company apply at a later date for a type design change 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
being proposed for the model(s) discussed in this special condition. 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.
PART 23--AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND
COMMUTER CATEGORY AIRPLANES
Citation
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.101; 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 Lancair LC41-550FG and LC42-550FG
airplanes modified to add an EFIS as optional equipment by the Lancair
Company.
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.
[[Page 19257]]
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 April 1, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-7427 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P
