[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]


=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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.
------------------------------------------------------------------------
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:

------------------------------------------------------------------------
                                Frequency
-------------------------------------------------------------------------
         Field strength (volts per meter)              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 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]
BILLING CODE 4910-13-P