Special Conditions; Cessna Aircraft Company Model 510 Airplane; Full Authority Digital Engine Control (FADEC) System, 34789-34790 [E6-9409]
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
compliance with the HIRF
requirements, no credit is given for
signal attenuation due to installation.
Data used for engine certification may
be used, when appropriate, for airplane
certification.
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 23–49. 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.
With respect to compliance with
§ 23.1309(e), the levels required for
compliance shall be at the levels for
catastrophic failure conditions.
The effective date of these
special conditions is June 9, 2006.
Comments must be received on or
before July 17, 2006.
DATES:
Comments may be mailed
in duplicate to: Federal Aviation
Administration, Regional Counsel,
ACE–7, Attention: Rules Docket Clerk,
Docket No. CE252, Room 506, 901
Locust Street, Kansas City, Missouri
64106. All comments must be marked:
Docket No. CE252. Comments may be
inspected in the Rules Docket
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Peter L. Rouse, Aerospace Engineer,
Standards Office (ACE–111), Small
Airplane Directorate, Aircraft
Certification Service, Federal Aviation
Administration, Room 301, 901 Locust
Street, Kansas City, Missouri 64106;
telephone (816) 329–4135, fax 816–329–
4090.
14 CFR Part 23
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 design 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.
[Docket No. CE252, Special Conditions No.
23–192–SC]
Comments Invited
Issued in Kansas City, Missouri on June 9,
2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9410 Filed 6–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Special Conditions; Cessna Aircraft
Company Model 510 Airplane; Full
Authority Digital Engine Control
(FADEC) System
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
jlentini on PROD1PC65 with RULES
AGENCY:
SUMMARY: These special conditions are
issued for the Cessna Aircraft Company,
Model 510 airplane. This airplane will
have a novel or unusual design
feature(s) associated with the use of an
electronic engine control system instead
of a traditional mechanical control
system. The applicable airworthiness
regulations do not contain adequate or
appropriate safety standards for this
design feature. 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.
VerDate Aug<31>2005
16:11 Jun 15, 2006
Jkt 208001
SUPPLEMENTARY INFORMATION:
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 specified above 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. CE252.’’ The postcard will
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
34789
be date stamped and returned to the
commenter.
Background
On January 28, 2004, Cessna Aircraft
Company; One Cessna Boulevard; Post
Office Box 7704; Wichita, KS 67277,
applied to the FAA for a new Type
Certificate for the Cessna Model 510
Mustang. The Cessna 510 will be
approved under TC No. A24CE. The
Model 510 is an all new, high
performance, low-wing, aft fuselage
mounted twin turbofan engine powered
aircraft in the Normal Category
including flight into known icing
conditions and single pilot operations.
The Model 510 is to use existing Cessna
Citation construction materials and
methods. The design criteria includes:
8,480 pounds maximum ramp weight,
8,395 pounds maximum takeoff weight,
250 KCAS/0.63 Mach VMO/MMO, and
a 41,000 foot maximum altitude. The
Model 510 airplane design includes
digital electronic engine control
systems, which were not envisaged and
are not adequately addressed in 14 CFR
part 23. The applicable existing
regulations do not address electronic
control systems since those were not
envisioned at the time. Even though the
engine control system will be
certificated as part of the engine, the
installation of an engine with an
electronic control system 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). The regulatory
requirements were not applicable to
systems certificated as part of the engine
(reference § 23.1309(f)(1)). Also,
electronic control systems often require
inputs from airplane data and power
sources and outputs to other airplane
systems. Although the parts of the
system that are not certificated with the
engine could be evaluated using the
criteria of § 23.1309, the integral nature
of systems such as these makes it not
feasible to evaluate the airplane portion
of the system without including the
engine portion of the system. However,
§ 23.1309(f)(1) again prevents complete
evaluation of the installed airplane
system since evaluation of the engine
system’s effects is not required.
Type Certification Basis
Under the provisions of 14 CFR part
21, § 21.17, Cessna Aircraft Company
must show that the applicant meets the
applicable provisions of 14 CFR part 23,
effective February 1, 1965, as amended
by Amendment 23–1 through
Amendment 23–54, effective September
14, 2000; 14 CFR part 36, effective
E:\FR\FM\16JNR1.SGM
16JNR1
34790
Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
December 1, 1969, through the
amendment effective on the date of type
certification; 14 CFR part 34;
exemptions, if any; and the special
conditions adopted by this rulemaking
action.
If the Administrator finds that the
applicable airworthiness regulations
(i.e., 14 CFR part 23) do not contain
adequate or appropriate safety standards
for the Cessna Aircraft Company Model
510 because of a novel or unusual
design feature, special conditions are
prescribed under the provisions of
§ 21.16.
Discussion
Special conditions, as appropriate, as
defined in § 11.19, are issued in
accordance with § 11.38, and become
part of the type certification basis in
accordance with § 21.17.
Special conditions are initially
applicable to the model for which they
are issued. Should the type certificate
for that model be amended later to
include any other model that
incorporates 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 Model 510 will incorporate the
following novel or unusual design
features:
Digital electronic engine control
systems. This special condition covers a
digital electronic engine control system
on the Cessna Aircraft Company Model
510 airplane.
jlentini on PROD1PC65 with RULES
Applicability
As discussed above, these special
conditions are applicable to the Cessna
Aircraft Company Model 510 airplane.
Should Cessna Aircraft Company apply
at a later date for a change to the type
certificate to include another model
incorporating the same novel or unusual
design feature, the special conditions
would apply to that model as well
under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features on one model
of airplane. It is not a rule of general
applicability and affects only the
applicant who applied to the FAA for
approval of these features on the
airplane.
Under standard practice, the effective
date of final special conditions would
be 30 days after the date of publication
in the Federal Register; however, as the
certification date for the Cessna Aircraft
Company Model 510 is imminent, the
FAA finds that good cause exists to
VerDate Aug<31>2005
16:11 Jun 15, 2006
Jkt 208001
make these special conditions effective
upon issuance.
ACTION:
List of Subjects in 14 CFR Part 23
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Raytheon Model BAe.125 series 800A
(including variants C–29A and U–125),
800B, 1000A, and 1000B airplanes and
Model Hawker 800 (including variant
U–125A) and 1000 airplanes; and for
certain Raytheon Model HS.125 series
700A and 700B airplanes and Model
Hawker 800XP airplanes. This AD
requires measuring the resistance of the
current limiters for the PE, PS1, and PS2
busses, and replacing a current limiter
with a new part if necessary. This AD
also requires reporting certain
information to the airplane
manufacturer. This AD allows a records
review for determining if suspect
current limiters were installed, which
may exempt airplanes from the required
measurement. This AD results from
reports that certain current limiters have
opened within two to four hours after
installation. We are issuing this AD to
prevent loss of all primary electrical
power, which could result in the
airplane operating only under
emergency power.
DATES: This AD becomes effective July
3, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 3, 2006.
We must receive comments on this
AD by August 15, 2006.
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 9:00 a.m. and 5:00 p.m.,
Monday through Friday, except Federal
holidays.
Contact Raytheon Aircraft Company,
Department 62, P.O. Box 85, Wichita,
Kansas 67201–0085, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Philip Petty, Aerospace Engineer,
Electrical Systems and Avionics, ACE–
Aircraft, Aviation Safety, Signs and
Symbols
Citation
The authority citation for these
Special Conditions is as follows:
I
Authority: 49 U.S.C. 106(g); 40113 and
44701; 14 CFR 21.16 and 21.17; and 14 CFR
11.38 and 11.19.
The Special Conditions
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the following special conditions are
issued as part of the type certification
basis for the Cessna Aircraft Company
Model 510 airplane.
I
1. 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 23–49. The
intent of this requirement is not to reevaluate 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.
Issued in Kansas City, Missouri on June 9,
2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9409 Filed 6–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25011; Directorate
Identifier 2006–NM–118–AD; Amendment
39–14646; AD 2006–12–20]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Model HS.125 Series 700A and 700B
Airplanes; Model BAe.125 Series 800A
(Including Variants C–29A and U–125),
800B, 1000A, and 1000B Airplanes; and
Hawker 800 (Including Variant U–
125A), 800XP, and 1000 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Final rule; request for
comments.
E:\FR\FM\16JNR1.SGM
16JNR1
Agencies
[Federal Register Volume 71, Number 116 (Friday, June 16, 2006)]
[Rules and Regulations]
[Pages 34789-34790]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9409]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE252, Special Conditions No. 23-192-SC]
Special Conditions; Cessna Aircraft Company Model 510 Airplane;
Full Authority Digital Engine Control (FADEC) System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Cessna Aircraft
Company, Model 510 airplane. This airplane will have a novel or unusual
design feature(s) associated with the use of an electronic engine
control system instead of a traditional mechanical control system. The
applicable airworthiness regulations do not contain adequate or
appropriate safety standards for this design feature. 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 June 9, 2006.
Comments must be received on or before July 17, 2006.
ADDRESSES: Comments may be mailed in duplicate to: Federal Aviation
Administration, Regional Counsel, ACE-7, Attention: Rules Docket Clerk,
Docket No. CE252, Room 506, 901 Locust Street, Kansas City, Missouri
64106. All comments must be marked: Docket No. CE252. 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: Peter L. Rouse, Aerospace Engineer,
Standards Office (ACE-111), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, Room 301, 901
Locust Street, Kansas City, Missouri 64106; telephone (816) 329-4135,
fax 816-329-4090.
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
design 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 specified above 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. CE252.'' The postcard will be date stamped and
returned to the commenter.
Background
On January 28, 2004, Cessna Aircraft Company; One Cessna Boulevard;
Post Office Box 7704; Wichita, KS 67277, applied to the FAA for a new
Type Certificate for the Cessna Model 510 Mustang. The Cessna 510 will
be approved under TC No. A24CE. The Model 510 is an all new, high
performance, low-wing, aft fuselage mounted twin turbofan engine
powered aircraft in the Normal Category including flight into known
icing conditions and single pilot operations. The Model 510 is to use
existing Cessna Citation construction materials and methods. The design
criteria includes: 8,480 pounds maximum ramp weight, 8,395 pounds
maximum takeoff weight, 250 KCAS/0.63 Mach VMO/MMO, and a 41,000 foot
maximum altitude. The Model 510 airplane design includes digital
electronic engine control systems, which were not envisaged and are not
adequately addressed in 14 CFR part 23. The applicable existing
regulations do not address electronic control systems since those were
not envisioned at the time. Even though the engine control system will
be certificated as part of the engine, the installation of an engine
with an electronic control system 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). The regulatory requirements were not
applicable to systems certificated as part of the engine (reference
Sec. 23.1309(f)(1)). Also, electronic control systems often require
inputs from airplane data and power sources and outputs to other
airplane systems. Although the parts of the system that are not
certificated with the engine could be evaluated using the criteria of
Sec. 23.1309, the integral nature of systems such as these makes it
not feasible to evaluate the airplane portion of the system without
including the engine portion of the system. However, Sec.
23.1309(f)(1) again prevents complete evaluation of the installed
airplane system since evaluation of the engine system's effects is not
required.
Type Certification Basis
Under the provisions of 14 CFR part 21, Sec. 21.17, Cessna
Aircraft Company must show that the applicant meets the applicable
provisions of 14 CFR part 23, effective February 1, 1965, as amended by
Amendment 23-1 through Amendment 23-54, effective September 14, 2000;
14 CFR part 36, effective
[[Page 34790]]
December 1, 1969, through the amendment effective on the date of type
certification; 14 CFR part 34; exemptions, if any; and the special
conditions adopted by this rulemaking action.
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 23) do not contain adequate or
appropriate safety standards for the Cessna Aircraft Company Model 510
because of a novel or unusual design feature, special conditions are
prescribed under the provisions of Sec. 21.16.
Discussion
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 21.17.
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates 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 Model 510 will incorporate the following novel or unusual
design features:
Digital electronic engine control systems. This special condition
covers a digital electronic engine control system on the Cessna
Aircraft Company Model 510 airplane.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Aircraft Company Model 510 airplane. Should Cessna Aircraft
Company apply at a later date for a change to the type certificate to
include another model incorporating the same novel or unusual design
feature, the special conditions would apply to that model as well under
the provisions of Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
on one model of airplane. It is not a rule of general applicability and
affects only the applicant who applied to the FAA for approval of these
features on the airplane.
Under standard practice, the effective date of final special
conditions would be 30 days after the date of publication in the
Federal Register; however, as the certification date for the Cessna
Aircraft Company Model 510 is imminent, the FAA finds that good cause
exists to make these special conditions effective upon issuance.
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:
Authority: 49 U.S.C. 106(g); 40113 and 44701; 14 CFR 21.16 and
21.17; and 14 CFR 11.38 and 11.19.
The Special Conditions
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for the Cessna Aircraft Company Model 510
airplane.
1. 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 23-49. 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.
Issued in Kansas City, Missouri on June 9, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9409 Filed 6-15-06; 8:45 am]
BILLING CODE 4910-13-P