Airworthiness standards: Special conditions— Cessna Model 172/K/L/M/N/P airplanes, etc.,

[Federal Register: April 4, 2000 (Volume 65, Number 65)]

[Proposed Rules]

[Page 17613-17616]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr04ap00-14]

[[Page 17613]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE159; Notice No. 23-00-01-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: Notice of proposed special conditions.

SUMMARY: This notice proposes special conditions 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 as modified by Teledyne Continental Motors to include a FADEC System. These airplanes, as modified, 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 May 4, 2000.

ADDRESSES: Comments on this proposal may be mailed in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket, Docket No. CE159, 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. CE159. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4:00p.m.

FOR FURTHER INFORMATION CONTACT: Randy Griffith, Aerospace Engineer, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri, 816-329-4126, fax 816-329-4090.

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. If a comment applies to a specific airplane model, please identify the model in the comment. 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 filedin 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 CE159.'' The postcard will be date stamped and returned to the commenter.

Background

On January 7, 2000, Teledyne Continental Motors applied for supplemental type certificates for the installation of engines which 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/ 3A13 P/Q/R. 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/ A4CE B/C/D/E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/E. Cessna Models 207/A, T207/A......... A16CE Cessna Models 210/K/L/M/N/R, T210/K/ 3A21 L/M/N/R. Cessna Model 310/A/B/C/D/E/F/G/H/I/J/ 3A10 J-1/K/L/N/P/Q/R. Cessna Models 320/A/B/C/D/E/F/-1, 3A25 340/A. Cessna Model 337/A/B/C/D/E/F/G/H.... A6CE Cessna Models 401/A/B, 411/A, 414/A, A7CE 421/A/B/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- 2A13 201T, 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

[[Page 17614]]

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 following Type Certificate Numbers:

Model

Type Certificate Number

Cessna Models 172/K/L/M/N/P............... 3A12 Rev 65; Dec 15, 99 Cessna Models 177/A/B..................... A13CE Rev 23; Oct 15, 94 Cessna Model 177RG........................ A20CE Rev 18; Oct 15, 94 Cessna Models 180/E/F/G/H/J/K............. 5A6 Rev 62; Jun 15, 95 Cessna Models 182/E/F/G/H/J/K/L/M/N/P/Q/R. 3A13 Rev 56; Dec 15, 99 Cessna Models 185/A/C/D/E/F............... 3A24 Rev 36; Nov 15, 99 Cessna Models 188/A/B/C................... A9CE Rev 26; Oct 15, 95 Cessna Models P206/A/B/C/D/E, U206/A/B/C/D/ A4CE Rev 37; Dec 15, 94 E/F/G, TU206/A/B/C/D/E/F/G, TP206/A/B/C/D/ E. Cessna Models 207/A, T207/A............... A16CE Rev 20; Oct 15, 94 Cessna Models 210/K/L/M/N/R, T210/K/L/M/N/ 3A21 Rev 45; Aug 15, 96 R. Cessna Model 310/A/B/C/D/E/F/G/H/I/J/J-1/K/ 3A10 Rev 61; Nov 15, 97 L/N/P/Q/R. Cessna Models 320/A/B/C/D/E/F/-1, 340/A... 3A25 Rev 25; Aug 15, 94 Cessna Model 337/A/B/C/D/E/F/G/H.......... A6CE Rev 37; Oct 15, 94 Cessna Models 401/A/B, 411/A, 414/A, 421/A/ A7CE Rev 44; May 15, 99 B/C. Diamond Model DA20-C1..................... TA4CH Rev 4; Apr 8, 99 Mooney Models M20/C/D/E/F/J/K/R........... 2A3 Rev 46; Aug 10, 99 Piper Models PA-28-180/-201T, PA-28R-201T, 2A13 Rev 44; Oct 15, 97 PA-28RT-201T. Piper Model PA-34-200/-200T/-220T......... A7SO Rev 13; Dec 18, 96 Piper Model PA-46-310P/-350P.............. A25SO Rev 8; Mar 4, 99 Raytheon Models F33, V35, A36............. 3A15 Rev 88; Jan 15, 00 Raytheon Models 58, 95-C55, D55, E55...... 3A16 Rev 80; Jan 18, 00 Raytheon Model 58P........................ A23CE Rev 14; Apr 15,96

If the Administrator finds that the applicable airworthiness regulations (i.e., 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 (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 Cessna Models 172/K/

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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 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.

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 11.29(b).

The Proposed Special Conditions

Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis 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 modified by Teledyne Continental Motors to include an engine with a FADEC System.

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 isare 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:

   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.

   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

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   Sec. 23.1309 (a) through (e) at Amendment 23-41.

   Issued in Kansas City, Missouri on March 22, 2000. Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.

   [FR Doc. 00-8231Filed4-3-00; 8:45 am]

   BILLING CODE 4910-13-P st