[Federal Register Volume 67, Number 60 (Thursday, March 28, 2002)]
[Proposed Rules]
[Pages 14884-14886]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-7503]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 67, No. 60 / Thursday, March 28, 2002 / 
Proposed Rules  

[[Page 14884]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE175]; Notice No. 23-02-02-SC


Special Conditions: Installation of Full Authority Digital Engine 
Control (FADEC) System on The Lancair Company, Model LC40-550FG-E 
Airplane

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

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

SUMMARY: This notice proposes special conditions for The Lancair 
Company, Model LC40-550FG-E Airplane, which will use a FADEC System. 
This airplane 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 proposed 
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: Comments must be received on or before April 29, 2002.

ADDRESSES: Comments on this proposal may be mailed in duplicate to: 
Federal Aviation Administration, Regional Counsel, ACE-7, Attention: 
Rules Docket, Docket No. CE175, DOT Building, 901 Locust, Kansas City, 
Missouri 64106, or delivered in duplicate to the Regional Counsel at 
the above address. Comments must be marked: Docket No. CE175. Comments 
may be inspected in the Rules Docket weekdays, except Federal holidays, 
between 7:30 a.m. and 4:00 p.m.

FOR FURTHER INFORMATION CONTACT: Ervin Dvorak, Aerospace Engineer, 
Standards Office (ACE-110), Small Airplane Directorate, Aircraft 
Certification Service, Federal Aviation Administration, 901 Locust, 
Room 301, Kansas City, Missouri 64106; telephone (816) 329-4123.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of 
these proposed special conditions by submitting such written data, 
views, or arguments as they may desire. Communications should identify 
the regulatory docket or notice number and be submitted in duplicate to 
the address specified above. All communications received on or before 
the closing date for comments will be considered by the Administrator. 
The proposals described in this notice 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. Persons wishing the FAA to acknowledge receipt of their 
comments submitted in response to this notice must include with those 
comments a self-addressed, stamped postcard on which the following 
statement is made: ``Comments to Docket No. CE175.'' The postcard will 
be date stamped and returned to the commenter.

Background

    On November 8, 2001, The Lancair Company applied to amend Type 
Certificate A0003SE for the addition of the Model LC40-550FG-E 
airplane. The Model LC40-550FG-E is a small, utility category airplane. 
The airplane is powered by one reciprocating engine equipped with an 
electronic engine control system with full authority capability in 
place of the hydromechanical control system.

Type Certification Basis

    Under the provisions of 14 CFR 21.101(c), The Lancair Company must 
show that the Model LC40-550FG-E meets the applicable provisions of the 
certification basis specified in Amendment 6 to TCDS A00003SE except as 
follows:
     FAR 23.1305 as of Amendment 52.
     FAR 23.1359 as of Amendment 49.
     Special conditions will be applied to the FADEC 
installation for protection against high intensity radiated fields 
(HIRF) and for installed system reliability (FAR 23.1309 
applicability).
    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 Model LC40-550FG-E 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 Model LC40-550FG 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, and the FAA must issue a 
finding of regulatory adequacy pursuant to section 611 of Public Law 
92-574, the ``Noise Control Act of 1972.''
    Special conditions, as appropriate, as defined in Sec. 11.19, are 
issued in accordance with Sec. 11.38 after public notice and become 
part of the type certification basis in accordance with 
Sec. 21.17(a)(2).
    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(a)(1).

Novel or Unusual Design Features

    The Lancair Company, Model LC40-550FG-E Airplane will incorporate 
the following novel or unusual design features:
    The Lancair Company, Model LC40-550FG-E Airplane will use an engine 
that includes an electronic control system with full engine authority 
capability.
    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 used on the Lancair Company, Model 
LC40-550FG-E will perform critical functions, provisions for protection 
from the effects of HIRF

[[Page 14885]]

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 the 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 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 Lancair Company, 
Model LC40-550FG-E to 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-
46.

Applicability

    As discussed above, these special conditions are applicable to the 
The Lancair Company, Model LC40-550FG-E Airplane. Should The Lancair 
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, The Lancair Company, Model LC40-550FG-E Airplane. It is 
not a rule of general applicability, and it affects only the applicant 
who applied to the FAA for approval of these features on the airplane.

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 
21.17; and 14 CFR 11.38 and 11.19.

The Proposed Special Conditions

    Accordingly, the Federal Aviation Administration (FAA) proposes the 
following special conditions as part of the type certification basis 
for The Lancair Company, Model LC40-550FG-E Airplane.
    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 critical functions, 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 critical functions.
    (1) The applicant may demonstrate that the operation and 
operational capability of the installed electrical and electronic 
systems that perform critical functions are not adversely affected when 
the aircraft is exposed to the external HIRF threat environment defined 
in the following table:

------------------------------------------------------------------------
                                             Field strength (volts per
                                                      meter)
                Frequency                -------------------------------
                                               Peak           Average
------------------------------------------------------------------------
10 kHz-100 kHz..........................              50              50
100 kHz-500 kHz.........................              50              50
500 kHz-2 MHz...........................              50              50
2 MHz-30 MHz............................             100             100
30 MHz-70 MHz...........................              50              50
70 MHz-100 MHz..........................              50              50
100 MHz-200 MHz.........................             100             100
200 MHz-400 MHz.........................             100             100
400 MHz-700 MHz.........................             700              50
700 MHz-1 GHz...........................             700             100
1 GHz-2 GHz.............................            2000             200
2 GHz-4 GHz.............................            3000             200
4 GHz-6 GHz.............................            3000             200
6 GHz-8 GHz.............................            1000             200
8 GHz-12 GHz............................            3000             300
12 GHz-18 GHz...........................            2000             200
18 GHz-40 GHz...........................             600            200
------------------------------------------------------------------------
The field strengths are expressed in terms of peak root-mean-square
  (rms) values.


[[Page 14886]]

      or,

    (2) The applicant may demonstrate by a system test and analysis 
that the electrical and electronic systems that perform critical 
functions can withstand a minimum threat of 100 volts per meter 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. 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 
Sec. 23.1309(a) through (e) at Amendment 23-46. 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 February 5, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-7503 Filed 3-27-02; 8:45 am]
BILLING CODE 4910-13-P