[Federal Register Volume 65, Number 114 (Tuesday, June 13, 2000)]
[Rules and Regulations]
[Pages 37006-37008]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-14860]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE159; Special Conditions No. 23-103-SC]
Special Conditions: Cessna Models; Diamond Model; Mooney Models;
Piper Models; Raytheon Models; Airplanes Modified by Installation of
Teledyne Continental Motors Full Authority Digital Engine Control
(FADEC) System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
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SUMMARY: These special conditions are issued for the Cessna Models 172/
K/L/M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/E/F/G/H/J/K/L/M/N/P/Q/R,
185/A/C/D/E/F, 188/A/B/C, P206/A/B/C/D/E, U206/A/B/C/D/E/F/G, TU206/A/
B/C/D/E/F/G, TP206/A/B/C/D/E, 207/A, T207/A, 210/K/L/M/N/R, T210/K/L/M/
N/R, 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/Q/R, 320/A/B/C/D/E/F/-1, 337/
A/B/C/D/E/F/G/H, 340/A, 401/A/B, 411/A, 414/A, 421/A/B/C; Diamond Model
DA20-C1; Mooney Models M20/C/D/E/F/J/K/R; Piper Models PA-28-180/-201T,
PA-28R-201T, PA-28RT-201T, PA-34-200/-200T/-220T, PA-46-310P/-350P; and
Raytheon Models F33, V35, A36, 95-C55, D55, E55, 58, 58P airplanes.
These airplanes as modified by Teledyne Continental Motors will have a
novel or unusual design feature associated with the installation of an
engine that uses an electronic engine control system in place of the
engine's mechanical 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.
EFFECTIVE DATE: July 13, 2000.
FOR FURTHER INFORMATION CONTACT: Randy Griffith, Aerospace Engineer,
Federal Aviation Administration, Aircraft Certification Service, Small
Airplane Directorate, ACE-111, 901 Locust, Kansas City, Missouri 64106;
816-329-4126, fax 816-329-4090.
SUPPLEMENTARY INFORMATION:
Background
On January 7, 2000, Teledyne Continental Motors applied for
supplemental type certificates for the installation of engines that use
an electronic engine control system in place of the hydromechanical
control system for the Cessna Models 172/K/L/M/N/P, 177/A/B/RG, 180/E/
F/G/H/J/K, 182/E/F/G/H/J/K/L/M/N/P/Q/R, 185/A/C/D/E/F, 188/A/B/C, P206/
A/B/C/D/E, U206/A/B/C/D/E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E,
207/A, T207/A, 210/K/L/M/N/R, T210/K/L/M/N/R, 310/A/B/C/D/E/F/G/H/I/J/
J-1/K/L/N/P/Q/R,320/A/B/C/D/E/F/-1, 337/A/B/C/D/E/F/G/H, 340/A, 401/A/
B, 411/A, 414/A, 421/A/B/C; Diamond Model DA20-C1; Mooney Models M20/C/
D/E/F/J/K/R; Piper Models PA-28-180/-201T, PA-28R-201T, PA-28RT-201T,
PA-34-200/-200T/-220T, PA-46-310P/-350P; and Raytheon Models F33, V35,
A36, 95-C55, D55, E55, 58, 58P airplanes. Affected airplane models are
currently approved under the following Type Certificate Numbers:
------------------------------------------------------------------------
Model Type certificate No.
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Cessna Models 172/K/L/M/N/P................. 3A12
Cessna Models 177/A/B....................... A13CE
Cessna Model 177RG.......................... A20CE
Cessna Models 180/E/F/G/H/J/K............... 5A6
Cessna Models 182/E/F/G/H/J/K/L/M/N/P/Q/R... 3A13
Cessna Models 185/A/C/D/E/F................. 3A24
Cessna Models 188/A/B/C..................... A9CE
Cessna Models P206/A/B/C/D/E, U206A/B/C/D/E/ A4CE
F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E.
[[Page 37007]]
Cessna Models 207/A, T207/A................. A16CE
Cessna Models 210/K/L/M/N/R, T210/K/L/M/N/R. 3A21
Cessna Model 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/ 3A10
N/P/Q/R.
Cessna Models 320/A/B/C/D/E/F/-1, 340/A..... 3A25
Cessna Model 337/A/B/C/D/E/F/G/H............ A6CE
Cessna Models 401/A/B, 411/A, 414/A, 421/A/B/ A7CE
C.
Diamond Model DA20-C1....................... TA4CH
Mooney Models M20/C/D/E/F/J/K/R............. 2A3
Piper Models PA-28-180/-201T, PA-28R-201T, 2A13
PA-28RT-201T.
Piper Model PA-34-200/-200T/-220T........... A7SO
Piper Model PA-46-310P/-350P................ A25SO
Raytheon Models F33, V35, A36............... 3A15
Raytheon Models 58, 95-C55, D55, E55........ 3A16
Raytheon Model 58P.......................... A23CE
------------------------------------------------------------------------
All the airplanes are small, normal category airplanes powered with
either single or dual reciprocating engines. The modification to the
airplanes involves replacement of the engine with a new engine model
that incorporates an electronic engine control system with full engine
authority capability. The new engine model is accomplished with either
an amended type certificate to the engine if the engine is a Teledyne
Continental engine or a supplemental type certificate to the engine if
the engine is a Lycoming engine. The airframe systems will also be
modified as necessary to accommodate the engine's new control system.
Type Certification Basis
Under the provisions of Sec. 21.101, Teledyne Continental Motors
must show that affected airplane models, as changed, continue to meet
the applicable provisions of the regulations incorporated by reference
in Type Certificate Numbers 3A12, A13CE, A20CE, 5A6, 3A13, 3A24, A9CE,
A4CE, A16CE, 3A21, 3A10, 3A25, A6CE, A7CE, TA4CH, 2A3, 2A13, A7SO,
A25SO, 3A15, 3A16, A23CE 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'' and can be found in the Type
Certificates.
If the Administrator finds that the applicable airworthiness
regulations (14 CFR part 23) do not contain adequate or appropriate
safety standards for affected airplane models because of a novel or
unusual design feature, special conditions are prescribed under the
provisions of Sec. 21.16.
Special conditions, as appropriate, are issued in accordance with
Sec. 11.49 after public notice, as required by Secs. 11.28 and
11.29(b), and become part of the type certification basis in accordance
with Sec. 21.101(b)(2).
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for a supplemental type
certificate to modify any other model included on the same type
certificate to incorporate the same novel or unusual design feature,
the special conditions would also apply to the other model under the
provisions of Sec. 21.101(a)(1).
Novel or Unusual Design Features
The Cessna Models 172/K/L/M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/
E/F/G/H/J/K/L/M/N/P/Q/R, 185/A/C/D/E/F, 188/A/B/C, P206/A/B/C/D/E,
U206/A/B/C/D/E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E, 207/A, T207/
A, 210/K/L/M/N/R, T210/K/L/M/N/R, 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/
Q/R, 320/A/B/C/D/E/F/-1, 337/A/B/C/D/E/F/G/H, 340/A, 401/A/B, 411/A,
414/A, 421/A/B/C; Diamond Model DA20-C1; Mooney Models M20/C/D/E/F/J/K/
R; Piper Models PA-28-180/-201T, PA-28R-201T, PA-28RT-201T, PA-34-200/-
200T/-220T, PA-46-310P/-350P; and Raytheon Models F33, V35, A36, 95-
C55, D55, E55, 58, 58P airplanes will incorporate an engine that
includes an electronic control system with full engine authority
capability. The airframe systems will also be modified as necessary to
accommodate the engine's new control system.
Many advanced electronic systems are prone to either upsets or
damage, or both, at energy levels lower than analog systems. The
increasing use of high power radio frequency emitters mandates
requirements for improved high intensity radiated fields (HIRF)
protection for electrical and electronic equipment. Since the
electronic engine control system developed by Teledyne Continental
Motors will perform functions in which a failure may cause an unsafe
condition, provisions for protection from the effects of HIRF fields
should be considered and, if necessary, incorporated into the airplane
design data. The FAA policy contained in Notice 8110.71, dated April 2,
1998, establishes the HIRF energy levels that airplanes will be exposed
to in service. The guidelines set forth in this Notice are the result
of an Aircraft Certification Service review of existing policy on HIRF,
in light of the ongoing work of the ARAC Electromagnetic Effects
Harmonization Working Group (EEHWG). The EEHWG adopted a set of HIRF
environment levels in November 1997 that were agreed upon by the FAA,
JAA, and industry participants. As a result, the HIRF environments in
this notice reflect the environment levels recommended by this working
group. This notice states that a full authority digital engine control
is an example of a system that should address the HIRF environments.
Even though each 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 (for example, radio interference with other airplane electronic
systems, shared engine and airplane power sources). The regulatory
requirements in 14 CFR part 23 for evaluating the installation of
complex systems, including electronic systems, are contained in
Sec. 23.1309. However, when Sec. 23.1309 was developed, the use of
electronic control systems for engines was not envisioned; therefore,
the Sec. 23.1309 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 (e.g.,
automated cockpit powerplant controls such as mixture setting) 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 unfeasible 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.
Therefore, special conditions are proposed for the Cessna Models
172/K/L/M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/E/F/G/H/J/K/L/M/N/P/Q/
R, 185/A/C/D/E/F, 188/A/B/C, P206/A/B/C/D/E, U206/A/B/C/D/E/F/G, TU206/
A/B/C/D/E/F/G, TP206/A/B/C/D/E, 207/A, T207/A, 210/K/L/M/N/R, T210/K/L/
M/N/R, 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/Q/R, 320/A/B/C/D/E/F/-1,
337/A/B/C/D/E/F/G/H, 340/A, 401/A/B, 411/A, 414/A, 421/A/B/C; Diamond
Model DA20-C1; Mooney Models M20/C/D/E/F/J/K/R; Piper Models PA-28-180/
-201T, PA-28R-201T, PA-28RT-201T, PA-34-200/-200T/-220T, PA-46-310P/-
350P; and Raytheon Models F33, V35, A36, 95-C55, D55, E55, 58, 58P
airplanes modified by Teledyne Continental Motors by installation of an
electronic engine control system to
[[Page 37008]]
provide HIRF protection and to evaluate the installation of the
electronic engine control system for compliance with the requirements
of Sec. 23.1309(a) through (e) at Amendment 23-41.
Discussion of Comments
On April 4, 2000 (65 FR 17613), the FAA published notice of
proposed special conditions No. 23-00-01-SC for Cessna Models 172/K/L/
M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/E/F/G/H/J/K/L/M/N/P/Q/R, 185/A/
C/D/E/F, 188/A/B/C, P206/A/B/C/D/E, U206/A/B/C/D/E/F/G, TU206/A/B/C/D/
E/F/G, TP206/A/B/C/D/E, 207/A, T207/A, 210/K/L/M/N/R, T210/K/L/M/N/R,
310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/Q/R, 320/A/B/C/D/E/F/-1, 337/A/B/C/
D/E/F/G/H, 340/A, 401/A/B, 411/A, 414/A, 421/A/B/C; Diamond Model DA20-
C1; Mooney Models M20/C/D/E/F/J/K/R; Piper Models PA-28-180/-201T, PA-
28R-201T, PA-28RT-201T, PA-34-200/-200T/-220T, PA-46-310P/-350P; and
Raytheon Models F33, V35, A36, 95-C55, D55, E55, 58, 58P airplanes. No
comments were received, and the special conditions are adopted as
proposed.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Models 172/K/L/M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/E/F/G/H/
J/K/L/M/N/P/Q/R, 185/A/C/D/E/F, 188/A/B/C, P206/A/B/C/D/E, U206/A/B/C/
D/E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E, 207/A, T207/A, 210/K/L/
M/N/R, T210/K/L/M/N/R, 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/Q/R, 320/A/
B/C/D/E/F/-1, 337/A/B/C/D/E/F/G/H, 340/A, 401/A/B, 411/A, 414/A, 421/A/
B/C; Diamond Model DA20-C1; Mooney Models M20/C/D/E/F/J/K/R; Piper
Models PA-28-180/-201T, PA-28R-201T, PA-28RT-201T, PA-34-200/-200T/-
220T, PA-46-310P/-350P; and Raytheon Models F33, V35, A36, 95-C55, D55,
E55, 58, 58P airplanes as modified by Teledyne Continental Motors.
Should Teledyne Continental Motors apply at a later date for a
supplemental type certificate to modify any other model included on
Type Certificate Numbers 3A12, A13CE, A20CE, 5A6, 3A13, 3A24, A9CE,
A4CE, A16CE, 3A21, 3A10, 3A25, A6CE, A7CE, TA4CH, 2A3, 2A13, A7SO,
A25SO, 3A15, 3A16, A23CE to incorporate the same novel or unusual
design feature, the special conditions would apply to that model as
well under the provisions of Sec. 21.101(a)(1).
Conclusion
This action affects only certain novel or unusual design features
on Cessna Models 172/K/L/M/N/P, 177/A/B/RG, 180/E/F/G/H/J/K, 182/E/F/G/
H/J/K/L/M/N/P/Q/R, 185/A/C/D/E/F, 188/A/B/C, P206/A/B/C/D/E, U206/A/B/
C/D/E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E, 207/A, T207/A, 210/K/
L/M/N/R, T210/K/L/M/N/R, 310/A/B/C/D/E/F/G/H/I/J/J-1/K/L/N/P/Q/R, 320/
A/B/C/D/E/F/-1, 337/A/B/C/D/E/F/G/H, 340/A, 401/A/B, 411/A, 414/A, 421/
A/B/C; Diamond Model DA20-C1; Mooney Models M20/C/D/E/F/J/K/R; Piper
Models PA-28-180/-201T, PA-28R-201T, PA-28RT-201T, PA-34-200/-200T/-
220T, PA-46-310P/-350P; and Raytheon Models F33, V35, A36, 95-C55, D55,
E55, 58, 58P airplanes. It is not a rule of general applicability. It
is only applicable to airplanes being modified by Teledyne Continental
Motors to include this engine system.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.101; and 14 CFR 11.28 and 49.
The Special Conditions
1. High Intensity Radiated Fields (HIRF), Protection. In showing
compliance with 14 CFR part 21 and the airworthiness requirements of 14
CFR part 23, protection against hazards caused by exposure to HIRF
fields for the full authority digital engine control system, which
performs functions in which a failure may cause an unsafe condition to
the airplane, must be considered. To prevent this occurrence, the
electronic engine control system must be designed and installed to
ensure that the operation and operational capabilities of this critical
system are not adversely affected when the airplane is exposed to high
energy radio fields.
At this time, the FAA and other airworthiness authorities are
unable to precisely define or control the HIRF energy level to which
the airplane will be exposed in service; therefore, the FAA hereby
defines two acceptable interim methods for complying with the
requirement for protection of systems that perform functions in which a
failure may cause an unsafe condition.
(1) The applicant may demonstrate that the operation and
operational capability of the installed electrical and electronic
systems that perform functions in which a failure may cause an unsafe
condition are not adversely affected when the aircraft is exposed to
the external HIRF threat environment defined in the following table:
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Frequency
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Field strength (volts per meter) Peak Average
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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 functions in
which a failure may cause an unsafe condition can withstand a minimum
threat of 100 volts per meter peak electrical strength, without the
benefit of airplane structural shielding, in the frequency range of 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.
2. Electronic Engine Control System. The installation items that
affect the electronic engine control system must comply with the
requirements of Sec. 23.1309(a) through (e) at Amendment 23-41.
Issued in Kansas City, Missouri on May 25, 2000.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-14860 Filed 6-12-00; 8:45 am]
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