Special Conditions: Cessna Aircraft Company Model 501 Airplanes; High Intensity Radiated Fields (HIRF), 9210-9212 [05-3614]
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9210
Federal Register / Vol. 70, No. 37 / Friday, February 25, 2005 / Rules and Regulations
boundary of sec. 15, T. 37 S., R. 25 E.;
then north along the western boundary
of sec. 15, T. 37 S., R. 25 E. to the
northwest corner of sec. 15, T. 37 S., R.
25 E.; then west approximately 1,710
feet to the southwest corner of
Multiblocks (MB) 52, 62, and 63; then
north approximately 1,221 feet to the
northwest corner of MB 52, 62, and 63;
then east approximately 366 feet to the
southwest corner of MB 51, 60, and 61;
then north approximately 6,716 feet,
crossing McIntyre Road and continuing
to the midpoint of sec. 4, T. 37 S., R. 25
E.; then east approximately 1,221 feet to
the western boundary of sec. 3, T. 37 S.,
R. 25 E.; then north approximately 977
feet to the southwest corner of MB 1, 17,
18, 19, and 20; then east approximately
2,442 feet; then north approximately
1,710 feet to the northern boundary of
sec. 3, T. 37 S., R. 25 E.; then east to the
northeast corner of sec. 2, T. 37 S., R.
25 E.; then south to the northeast corner
of sec. 11, T. 37 S., R. 25 E., the point
of beginning.
*
*
*
*
*
Lee County. * * *
(2) Pine Island quarantined area. That
portion of the county bounded by a line
drawn as follows: Beginning on the
eastern Pine Island shoreline at a point
on Cubles Drive at latitude N.
26.639400, longitude W. ¥82.106568;
then south from that point along the
eastern Pine Island shoreline to a point
defined by latitude N. 26.619100,
longitude W. ¥82.105556; then west
from that point to Birdsong Lane; then
west on Birdsong Lane to Stringfellow
Road; then north on Stringfellow Road
to latitude N. 26.619628, longitude W.
¥82.118863; then west from that point
to latitude N. 26.319436, longitude W.
¥82.123956; then north from that point
to latitude N. 26.624970, longitude W.
¥82.123990; then west from that point
to latitude N. 26.624978, longitude W.
¥82.124627; then north from that point
to latitude N. 26.626005, longitude W.
¥82.124567; then west from that point
to latitude N. 26.626088, longitude W.
¥82.125245; then north from that point
to latitude N. 26.634922, longitude W.
¥82.125165; then east from that point
to Harry Street; then north on Harry
Street to latitude N. 26.649310,
longitude W. ¥82.125209; then east
from that point to Stringfellow Road;
then north on Stringfellow Road to
Sailfish Road; then east on Sailfish Road
to Marlin Road; then north on Marlin
Road to Porpoise Road; then east on
Porpoise Road to Dolphin Road; then
north on Dolphin Road to Tarpon Road;
then east on Tarpon Road to a point on
Cristi Way at latitude N. 26.638367,
longitude W. ¥82.118612; then north
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16:17 Feb 24, 2005
Jkt 205001
from that point to latitude N. 26.638860,
longitude W. ¥82.118562; then east
from that point to a point on Sherwood
Road at latitude N. 26.638865, longitude
W. ¥82.109475; then north from that
point to the intersection of Sherwood
Road and Cubles Drive; then east on
Cubles Drive to the point of beginning.
*
*
*
*
*
Done in Washington, DC, this 18th day of
February 2005.
Elizabeth E. Gaston,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. 05–3685 Filed 2–24–05; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM302; Special Conditions No.
25–286–SC]
Special Conditions: Cessna Aircraft
Company Model 501 Airplanes; High
Intensity Radiated Fields (HIRF)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
SUMMARY: These special conditions are
issued for Cessna Aircraft Company
Model 501 airplanes modified by Garrett
Aviation Services. These airplanes will
have novel and unusual design features
when compared to the state of
technology envisioned in the
airworthiness standards for transport
category airplanes. The modification
incorporates the installation of
Electronic Flight Displays with Engine
Indication and Flight Information
Systems. The applicable airworthiness
regulations do not contain adequate or
appropriate safety 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 that established by the
existing airworthiness standards.
DATES: The effective date of these
special conditions is February 16, 2005.
Comments must be received on or
before March 28, 2005.
ADDRESSES: Comments on these special
conditions may be mailed in duplicate
to: Federal Aviation Administration,
Transport Airplane Directorate, Attn:
Rules Docket (ANM–113), Docket No.
NM302, 1601 Lind Avenue SW.,
PO 00000
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Renton, Washington, 98055–4056; or
delivered in duplicate to the Transport
Airplane Directorate at the above
address. Comments must be marked:
Docket No. NM302.
FOR FURTHER INFORMATION CONTACT: Greg
Dunn, FAA, Airplane and Flight Crew
Interface Branch, ANM–111, Transport
Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue
SW., Renton, Washington, 98055–4056;
telephone (425) 227–2799; facsimile
(425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA has determined that notice
and opportunity for prior public
comment is impracticable because these
procedures would significantly delay
certification of the airplanes 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; however, we invite interested
persons to participate in this rulemaking
by submitting written comments, data,
or views. The most helpful comments
reference a specific portion of the
special conditions, explain the reason
for any recommended change, and
include supporting data. We ask that
you send us two copies of written
comments.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning these special conditions.
The docket is available for public
inspection before and after the comment
closing date. If you wish to review the
docket in person, go to the address in
the ADDRESSES section of this preamble
between 7:30 a.m. and 4 p.m. Monday
through Friday, except Federal holidays.
We will consider all comments we
receive on or before the closing date for
comments. We will consider comments
filed late if it is possible to do so
without incurring expense or delay. We
may change these special conditions in
light of the comments received.
If you want the FAA to acknowledge
receipt of your comments on these
special conditions, include with your
comments a pre-addressed, stamped
postcard on which the docket number
appears. We will stamp the date on the
postcard and mail it back to you.
Background
On August 11, 2004, Garrett Aviation
Services, 1200 North Airport Drive,
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Federal Register / Vol. 70, No. 37 / Friday, February 25, 2005 / Rules and Regulations
Capital Airport, Springfield, IL 62707,
applied for a supplemental type
certificate (STC) to modify Cessna
Aircraft Company Model 501 airplanes.
These models are currently approved
under Type Certificate No. A27CE.
These Cessna airplane models are small
transport category airplanes. The Cessna
Model 501 is powered by two Pratt &
Whitney Aircraft of Canada, Ltd.,
JT15D–1A or JT15D–1B turbofans; has a
maximum takeoff weight of 11,850
pounds, and operates with one to twopilot crews and holds up to 9
passengers. The modification
incorporates the installation of the IDS–
3000 Integrated Display System with
EIS–3000 Engine Indication System and
IFIS–5000 Integrated Flight Information
System. The avionics/electronics and
electrical systems installed in these
airplanes have the potential to be
vulnerable to high-intensity radiated
fields (HIRF) external to the airplanes.
Type Certification Basis
Under the provisions of 14 CFR
21.101, Garrett Aviation Services must
show that the Cessna Aircraft Company
Model 501 airplanes, as changed,
continue to meet the applicable
provisions of the regulations
incorporated by reference in Type
Certificate No. A27CE, or the applicable
regulations in effect on the date of
application for the change. The
regulations incorporated by reference in
the type certificate are commonly
referred to as the ‘‘original type
certification basis.’’ The certification
basis for the Cessna Model 501 series
airplanes include part 23 of 14 CFR
effective February 1, 1965, as amended
by amendments 23–1 through 23–16
except as follows: delete §§ 23.45
through 23.77, 23.831, 23.1091(c)(2),
23.1303, 23.1323, 23.1441 through
23.1449, 23.1581 through 23.1583(f),
and 23.1583(h) through 23.1587. Add
§§ 23.1385 as amended through 23–20,
and part 25 of 14 CFR effective February
1, 1965, as amended by amendments
25–1 through 25–17; §§ 25.1195,
25.1199 and 25.1203 as amended by
amendments 25–1 through 25–37;
§§ 25.101 through 25.125, 25.831,
25.934, 25.1091(d)(2), 25.1197, 25.1201,
25.1303, 25.1305(a)(7), 25.1323, 25.1439
through 25.1453, 25.1581 through
25.1583(c)(3), and §§ 25.1583(e) through
25.1587.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., part 25, as amended) do not
contain adequate or appropriate safety
standards for modified Cessna Aircraft
Company Model 501 airplanes, because
of a novel or unusual design feature,
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16:17 Feb 24, 2005
Jkt 205001
special conditions are prescribed under
the provisions of § 21.16.
In addition to the applicable
airworthiness regulations and special
conditions, the Cessna Model 501
airplanes 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 defined in 14
CFR 11.19, are issued in accordance
with § 11.38, 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 Garrett Aviation
Services apply at a later date for a
supplemental type certificate to modify
any other model included on Type
Certificate No. A27CE to incorporate the
same novel or unusual design feature,
these special conditions would also
apply to the other model under the
provisions of § 21.101.
Novel or Unusual Design Features
As noted earlier, the Cessna Aircraft
Company Model 501 airplanes modified
by Garrett Aviation Services will
incorporate electronic displays with
Engine Indication and Flight
Information systems that will perform
critical functions. These systems may be
vulnerable to high-intensity radiated
fields external to the airplane. The
current airworthiness standards of part
25 do not contain adequate or
appropriate safety standards for the
protection of this equipment from the
adverse effects of HIRF. Accordingly,
this system is considered to be a novel
or unusual design feature.
Discussion
There is no specific regulation that
addresses protection requirements for
electronic and electrical systems from
HIRF. Increased power levels from
ground-based radio transmitters and the
growing use of sensitive avionics/
electronics and electrical systems to
command and control airplanes have
made it necessary to provide adequate
protection.
To ensure that a level of safety is
achieved equivalent to that intended by
the regulations incorporated by
reference, special conditions are needed
for the Cessna Model 501 airplanes
modified by Garrett Aviation Services.
These special conditions require that
new avionics/electronics and electrical
systems that perform critical functions
be designed and installed to preclude
component damage and interruption of
function due to both the direct and
indirect effects of HIRF.
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High-Intensity Radiated Fields (HIRF)
With the trend toward increased
power levels from ground-based
transmitters, and the advent of space
and satellite communications, coupled
with electronic command and control of
the airplane, the immunity of critical
digital avionics/electronics and
electrical systems to HIRF must be
established.
It is not possible to precisely define
the HIRF to which the airplane will be
exposed in service. There is also
uncertainty concerning the effectiveness
of airframe shielding for HIRF.
Furthermore, coupling of
electromagnetic energy to cockpitinstalled equipment through the cockpit
window apertures is undefined. Based
on surveys and analysis of existing HIRF
emitters, an adequate level of protection
exists when compliance is shown with
either HIRF protection special condition
paragraph 1 or 2 below:
1. A minimum threat of 100 volts rms
(root-mean-square) per meter electric
field strength from 10 KHz to 18 GHz.
a. The threat must be applied to the
system elements and their associated
wiring harnesses without the benefit of
airframe shielding.
b. Demonstration of this level of
protection is established through system
tests and analysis.
2. A threat external to the airframe of
the field strengths identified in the table
below for the frequency ranges
indicated. Both peak and average field
strength components from the table are
to be demonstrated.
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 .....
50
50
50
100
50
50
100
100
700
700
2000
3000
3000
1000
3000
2000
600
Average
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 of the root-mean-square (rms) over
the complete modulation period.
The threat levels identified above are
the result of an FAA review of existing
studies on the subject of HIRF, in light
of the ongoing work of the
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Federal Register / Vol. 70, No. 37 / Friday, February 25, 2005 / Rules and Regulations
Electromagnetic Effects Harmonization
Working Group of the Aviation
Rulemaking Advisory Committee.
Applicability
As discussed above, these special
conditions are applicable to the Cessna
Aircraft Company Model 501 airplanes.
Should Garrett Aviation Services apply
at a later date for a supplemental type
certificate to modify any other model
included on Type Certificate No.
A27CEU to incorporate the same or
similar novel or unusual design feature,
these 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 the
Cessna Model 501 airplanes modified by
Garrett Aviation Services. 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 the special
conditions for these airplanes has been
subjected to the notice and comment
procedure in several prior instances and
has been derived without substantive
change from those previously issued.
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 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these special
conditions is as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the supplemental type
certification basis for the Cessna Aircraft
Company Model 501 airplanes modified
by Garrett Aviation Services.
1. Protection from Unwanted Effects
of High-Intensity Radiated Fields
(HIRF). Each electronic and electrical
system that performs critical functions
must be designed and installed to
I
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16:17 Feb 24, 2005
Jkt 205001
ensure that the operation and
operational capability of these systems
to perform critical functions are not
adversely affected when the airplane is
exposed to high intensity radiated
fields.
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 Renton, Washington, on February
16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–3614 Filed 2–24–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20108; Directorate
Identifier 2005–NM–006–AD; Amendment
39–13985; AD 2005–04–13]
RIN 2120–AA64
Airworthiness Directives; Short
Brothers Model SD3–60 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Short Brothers Model SD3–60 series
airplanes. This AD requires, for certain
airplanes, repetitive inspections for
cracking of the balance weight brackets
of the elevator trim tabs, and
replacement of any cracked bracket with
a new or reworked bracket that
conforms to the approved design
standard. This AD also provides for an
optional terminating action for the
repetitive inspections. This AD is
prompted by reports indicating that
balance weight brackets have been
found cracked on both the left and right
elevator trim tabs. We are issuing this
AD to prevent failure of the balance
weight bracket for the elevator trim tab,
which could cause loss of the balance
weight. This could result in incorrect
trim during takeoff and landing, and
reduced controllability of the airplane.
DATES: Effective March 14, 2005.
The incorporation by reference of a
certain publication listed in the AD is
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approved by the Director of the Federal
Register as of March 14, 2005.
We must receive comments on this
AD by April 26, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this AD, contact Short Brothers,
Airworthiness & Engineering Quality,
P.O. Box 241, Airport Road, Belfast BT3
9DZ, Northern Ireland. You can
examine this information at the National
Archives and Records Administration
(NARA). For information on the
availability of this material at NARA,
call (202) 741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
You can examine the contents of this
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., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20108; the directorate identifier for this
docket is 2005-NM–006-AD.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
E:\FR\FM\25FER1.SGM
25FER1
]]>Agencies
[Federal Register Volume 70, Number 37 (Friday, February 25, 2005)]
[Rules and Regulations]
[Pages 9210-9212]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-3614]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM302; Special Conditions No. 25-286-SC]
Special Conditions: Cessna Aircraft Company Model 501 Airplanes;
High Intensity Radiated Fields (HIRF)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for Cessna Aircraft
Company Model 501 airplanes modified by Garrett Aviation Services.
These airplanes will have novel and unusual design features when
compared to the state of technology envisioned in the airworthiness
standards for transport category airplanes. The modification
incorporates the installation of Electronic Flight Displays with Engine
Indication and Flight Information Systems. The applicable airworthiness
regulations do not contain adequate or appropriate safety 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 that established by the
existing airworthiness standards.
DATES: The effective date of these special conditions is February 16,
2005. Comments must be received on or before March 28, 2005.
ADDRESSES: Comments on these special conditions may be mailed in
duplicate to: Federal Aviation Administration, Transport Airplane
Directorate, Attn: Rules Docket (ANM-113), Docket No. NM302, 1601 Lind
Avenue SW., Renton, Washington, 98055-4056; or delivered in duplicate
to the Transport Airplane Directorate at the above address. Comments
must be marked: Docket No. NM302.
FOR FURTHER INFORMATION CONTACT: Greg Dunn, FAA, Airplane and Flight
Crew Interface Branch, ANM-111, Transport Airplane Directorate,
Aircraft Certification Service, 1601 Lind Avenue SW., Renton,
Washington, 98055-4056; telephone (425) 227-2799; facsimile (425) 227-
1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA has determined that notice and opportunity for prior public
comment is impracticable because these procedures would significantly
delay certification of the airplanes 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; however, we invite interested persons to participate in this
rulemaking by submitting written comments, data, or views. The most
helpful comments reference a specific portion of the special
conditions, explain the reason for any recommended change, and include
supporting data. We ask that you send us two copies of written
comments.
We will file in the docket all comments we receive, as well as a
report summarizing each substantive public contact with FAA personnel
concerning these special conditions. The docket is available for public
inspection before and after the comment closing date. If you wish to
review the docket in person, go to the address in the ADDRESSES section
of this preamble between 7:30 a.m. and 4 p.m. Monday through Friday,
except Federal holidays.
We will consider all comments we receive on or before the closing
date for comments. We will consider comments filed late if it is
possible to do so without incurring expense or delay. We may change
these special conditions in light of the comments received.
If you want the FAA to acknowledge receipt of your comments on
these special conditions, include with your comments a pre-addressed,
stamped postcard on which the docket number appears. We will stamp the
date on the postcard and mail it back to you.
Background
On August 11, 2004, Garrett Aviation Services, 1200 North Airport
Drive,
[[Page 9211]]
Capital Airport, Springfield, IL 62707, applied for a supplemental type
certificate (STC) to modify Cessna Aircraft Company Model 501
airplanes. These models are currently approved under Type Certificate
No. A27CE. These Cessna airplane models are small transport category
airplanes. The Cessna Model 501 is powered by two Pratt & Whitney
Aircraft of Canada, Ltd., JT15D-1A or JT15D-1B turbofans; has a maximum
takeoff weight of 11,850 pounds, and operates with one to two-pilot
crews and holds up to 9 passengers. The modification incorporates the
installation of the IDS-3000 Integrated Display System with EIS-3000
Engine Indication System and IFIS-5000 Integrated Flight Information
System. The avionics/electronics and electrical systems installed in
these airplanes have the potential to be vulnerable to high-intensity
radiated fields (HIRF) external to the airplanes.
Type Certification Basis
Under the provisions of 14 CFR 21.101, Garrett Aviation Services
must show that the Cessna Aircraft Company Model 501 airplanes, as
changed, continue to meet the applicable provisions of the regulations
incorporated by reference in Type Certificate No. A27CE, or the
applicable regulations in effect on the date of application for the
change. The regulations incorporated by reference in the type
certificate are commonly referred to as the ``original type
certification basis.'' The certification basis for the Cessna Model 501
series airplanes include part 23 of 14 CFR effective February 1, 1965,
as amended by amendments 23-1 through 23-16 except as follows: delete
Sec. Sec. 23.45 through 23.77, 23.831, 23.1091(c)(2), 23.1303,
23.1323, 23.1441 through 23.1449, 23.1581 through 23.1583(f), and
23.1583(h) through 23.1587. Add Sec. Sec. 23.1385 as amended through
23-20, and part 25 of 14 CFR effective February 1, 1965, as amended by
amendments 25-1 through 25-17; Sec. Sec. 25.1195, 25.1199 and 25.1203
as amended by amendments 25-1 through 25-37; Sec. Sec. 25.101 through
25.125, 25.831, 25.934, 25.1091(d)(2), 25.1197, 25.1201, 25.1303,
25.1305(a)(7), 25.1323, 25.1439 through 25.1453, 25.1581 through
25.1583(c)(3), and Sec. Sec. 25.1583(e) through 25.1587.
If the Administrator finds that the applicable airworthiness
regulations (i.e., part 25, as amended) do not contain adequate or
appropriate safety standards for modified Cessna Aircraft Company Model
501 airplanes, 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 Model 501 airplanes 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 defined in 14 CFR 11.19, are issued in
accordance with Sec. 11.38, 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 Garrett Aviation Services apply at a later date
for a supplemental type certificate to modify any other model included
on Type Certificate No. A27CE to incorporate the same novel or unusual
design feature, these special conditions would also apply to the other
model under the provisions of Sec. 21.101.
Novel or Unusual Design Features
As noted earlier, the Cessna Aircraft Company Model 501 airplanes
modified by Garrett Aviation Services will incorporate electronic
displays with Engine Indication and Flight Information systems that
will perform critical functions. These systems may be vulnerable to
high-intensity radiated fields external to the airplane. The current
airworthiness standards of part 25 do not contain adequate or
appropriate safety standards for the protection of this equipment from
the adverse effects of HIRF. Accordingly, this system is considered to
be a novel or unusual design feature.
Discussion
There is no specific regulation that addresses protection
requirements for electronic and electrical systems from HIRF. Increased
power levels from ground-based radio transmitters and the growing use
of sensitive avionics/electronics and electrical systems to command and
control airplanes have made it necessary to provide adequate
protection.
To ensure that a level of safety is achieved equivalent to that
intended by the regulations incorporated by reference, special
conditions are needed for the Cessna Model 501 airplanes modified by
Garrett Aviation Services. These special conditions require that new
avionics/electronics and electrical systems that perform critical
functions be designed and installed to preclude component damage and
interruption of function due to both the direct and indirect effects of
HIRF.
High-Intensity Radiated Fields (HIRF)
With the trend toward increased power levels from ground-based
transmitters, and the advent of space and satellite communications,
coupled with electronic command and control of the airplane, the
immunity of critical digital avionics/electronics and electrical
systems to HIRF must be established.
It is not possible to precisely define the HIRF to which the
airplane will be exposed in service. There is also uncertainty
concerning the effectiveness of airframe shielding for HIRF.
Furthermore, coupling of electromagnetic energy to cockpit-installed
equipment through the cockpit window apertures is undefined. Based on
surveys and analysis of existing HIRF emitters, an adequate level of
protection exists when compliance is shown with either HIRF protection
special condition paragraph 1 or 2 below:
1. A minimum threat of 100 volts rms (root-mean-square) per meter
electric field strength from 10 KHz to 18 GHz.
a. The threat must be applied to the system elements and their
associated wiring harnesses without the benefit of airframe shielding.
b. Demonstration of this level of protection is established through
system tests and analysis.
2. A threat external to the airframe of the field strengths
identified in the table below for the frequency ranges indicated. Both
peak and average field strength components from the table are to be
demonstrated.
------------------------------------------------------------------------
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 of the root-mean-
square (rms) over the complete modulation period.
The threat levels identified above are the result of an FAA review
of existing studies on the subject of HIRF, in light of the ongoing
work of the
[[Page 9212]]
Electromagnetic Effects Harmonization Working Group of the Aviation
Rulemaking Advisory Committee.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Aircraft Company Model 501 airplanes. Should Garrett Aviation
Services apply at a later date for a supplemental type certificate to
modify any other model included on Type Certificate No. A27CEU to
incorporate the same or similar novel or unusual design feature, these
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 the Cessna Model 501 airplanes modified by Garrett Aviation
Services. 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 the special conditions for these airplanes has
been subjected to the notice and comment procedure in several prior
instances and has been derived without substantive change from those
previously issued. 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 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
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 supplemental type certification basis for the Cessna Aircraft
Company Model 501 airplanes modified by Garrett Aviation Services.
1. Protection from Unwanted Effects of High-Intensity Radiated
Fields (HIRF). Each electronic and electrical system that performs
critical functions must be designed and installed to ensure that the
operation and operational capability of these systems to perform
critical functions are not adversely affected when the airplane is
exposed to high intensity radiated fields.
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 Renton, Washington, on February 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-3614 Filed 2-24-05; 8:45 am]
BILLING CODE 4910-13-P
