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Date: 6/29/01 AC No: 33.28-1 14 CFR §33.28, AIRCRAFT ENGINES, Initiated By: ANE-110 Change: ELECTRICAL and ELECTRONIC ENGINE CONTROL SYSTEMS

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Date: 6/29/01 AC No: 33.28-1 14 CFR §33.28, AIRCRAFT ENGINES, Initiated By: ANE-110 Change: ELECTRICAL and ELECTRONIC ENGINE CONTROL SYSTEMS Subject: COMPLIANCE CRITERIA FOR Date: 6/29/01 AC No: 33.28-1 14 CFR §33.28, AIRCRAFT ENGINES, Initiated By: ANE-110 Change: ELECTRICAL AND ELECTRONIC ENGINE CONTROL SYSTEMS 1. PURPOSE. This advisory circular (AC) provides guidance and acceptable methods, but not the only methods, that may be used to demonstrate compliance with §33.28 of Title 14 of the Code of Federal Regulations (14 CFR 33.28), Electrical and electronic engine control systems. Like all AC material, this AC is not, in itself, mandatory and does not constitute a regulation. While these guidelines are not mandatory, they are derived from extensive Federal Aviation Administration (FAA) and industry experience in determining compliance with the pertinent regulations. 2. RELATED REGULATIONS. a. Part 21. Section 21.16. b. Part 23. Sections 23.863, 23.901, 23.903, 23.1181, and 23.1309. c. Part 25. Sections 25.863, 25.901, 25.903, 25.939, 25.1181, and 25.1309. d. Part 27. Sections 27.863, 27.901, 27.903, and 27.1309. e. Part 29. Sections 29.863, 29.901, 29.903, 29.1181, and 29.1309. f. Part 33. Sections 33.4, 33.5, 33.17, 33.19, 33.27, 33.28, 33.49, 33.53, 33.75, 33.91(a), and Appendix A of part 33. AC 33.28-1 6/29/01 3. RELATED REFERENCE MATERIAL. a. ACs, Notices, and Policy. (1) AC 20-53A, Protection of Aircraft Fuel Systems Against Fuel Vapor Ignition Due to Lightning, dated April 12, 1985. (2) AC 20-115B, RTCA, Inc. Document RTCA/DO-178B, Software Considerations in Airborne Systems and Equipment Certification, dated January 11, 1993. (3) AC 20-136, Protection of Aircraft Electrical/Electronic Systems Against the Indirect Effects of Lightning, dated March 5, 1990. (4) AC 21-16D, RTCA/DO-160D, Environmental Conditions and Test Procedures for Airborne Equipment, dated July 21, 1998. (5) AC 23.1309-1C, Equipment, Systems, and Installations in Part 23 Airplanes, dated March 12, 1999. (6) AC 25.1309-1A, System Design Analysis, dated June 21, 1988. (7) AC 33-2B, Aircraft Engine Type Certification Handbook, dated June 30, 1993. (8) AIR-100 Policy, High Energy Radiated Electromagnetic Fields (HERF), Interim Policy Guidelines on Certification Issues, dated 5 December 1989. (9) Notice N8110.71, Guidance for the Certification of Aircraft Operating in High Intensity Radiated Field (HIRF) Environments, issued April 2, 1998. (10) Engine and Propeller Directorate Policy, Time Limited Dispatch (TLD) of Engines Fitted with Full Authority Digital Engine Controls (FADEC) Systems, dated June 29, 2001. (11) Engine and Propeller Directorate Policy Regarding Integrated Full Authority Digital Engine Control (FADEC) and Electronic Propeller Control (EPC) Systems, dated January 30, 1995. b. Industry Documents. (1) RTCA Document No. DO-160D (EUROCAE ED14D), Environmental Conditions and Test Procedures for Airborne Equipment, dated July 29, 1997. (2) RTCA Document No. DO-178B (EUROCAE ED12D), Software Considerations in Airborne Systems and Equipment Certification, dated December 1, 1992. (3) RTCA Document No. DO-254, Design Assurance Guidance for Airborne Electronic Hardware, dated April 19, 2000. Page ii Par 3 6/29/01 AC 33.28-1 (4) SAE ARP 926/B Fault/Failure Analysis Procedure, issued June 1997. (5) SAE ARP 1834/A Fault/Failure Analysis for Digital Systems and Equipment, issued June 1997. (6) SAE ARP 4754, Certification Considerations for Highly-Integrated or Complex Aircraft Systems, issued November 1996. (7) SAE ARP 4761, Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment, issued December 1996. (8) SAE ARP 5107, Guidelines for Time-Limited-Dispatch Analysis for Electronic Engine Control Systems, issued June 1997. (9) IEC/PAS 62239, Electronic Component Management Plans, edition 1.0, dated April 2001. (10) IEC/PAS 62240, Use of Semiconductor Devices Outside Manufacturers’ Specified Temperature Ranges, edition 1.0, dated April 2001. c. Military Specifications. (1) MIL-STD-461E, Requirements for the Control of Electromagnetic Interference Characteristics of the Subsystems and Equipment, dated August 20, 1999. (2) MIL-STD-462D, Measurement of Electromagnetic Interference Characteristics, Test Standard For, dated February 5, 1996. (3) MIL-STD-810E, Environmental Test Methods and Engineering Guidelines, dated July 31, 1995. (4) MIL-STD-5007D, Engines, Aircraft, Turbojet and Turbofan, General Specification For, dated October 15, 1973. (5) MIL-HDBK-179A, Microcircuit Acquisition Handbook, dated July 20, 1995. (6) MIL-HDBK-217F, Reliability Prediction of Electronic Equipment, dated February 28, 1995. Par 3 Page iii AC 33.28-1 6/29/01 4. APPLICABILITY. This AC applies to electrical and electronic engine control (EEC) systems used on aircraft engines certificated under 14 CFR part 33 and intended for use in aircraft certificated under parts 23, 25, 27, and 29. This document also applies to any electrical or electronic systems that control an engine function, for example overspeed or temperature limiting systems. In some cases, controls for functions not normally covered under part 33 or required for engine control are integrated into the EEC (for example, propeller controls regulated under part 35). In these cases, this document also applies to those functions integrated into the EEC system, but only to the extent that those functions affect part 33 requirements. Although sections of this AC provide guidance for compliance with §33.28 for all EECs, the FAA is developing specific guidance for reciprocating engine controls. Original Signed by JJP on 6/29/01 Jay J. Pardee Manager, Engine and Propeller Directorate, Aircraft Certification Service Page iv Par 4 6/29/01 AC 33.28-1 CONTENTS Paragraph Page CHAPTER 1. GENERAL 1-1. Background............................................................................................................. 1-1 1-2. Introduction............................................................................................................. 1-1 1-3. Definitions...............................................................................................................1-2 CHAPTER 2. SECTION 33.28(a) 2-1. Rule Text.................................................................................................................2-1 2-2. Intent of Rule .......................................................................................................... 2-1 2-3. Compliance with §33.28(a)..................................................................................... 2-1 a. Control System Description ........................................................................... 2-1 b. Interface Description...................................................................................... 2-2 c. Operational Description.................................................................................. 2-2 d. Substantiating Data ........................................................................................ 2-3 e. Fault Accommodation Logic Data ................................................................. 2-4 CHAPTER 3. SECTION 33.28(b) 3-1. Rule Text.................................................................................................................3-1 3-2. Intent of Rule .......................................................................................................... 3-1 a. Unacceptable Change in Power or Thrust...................................................... 3-1 b. Continued Safe Operation of the Engine........................................................ 3-1 CHAPTER 4. COMPLIANCE WITH §33.28(b): FAILURE OF AIRCRAFT-SUPPLIED DATA 4-1. Failure of Aircraft-Supplied Data ........................................................................... 4-1 4-2. System Configurations............................................................................................ 4-1 a. Dual Sources................................................................................................... 4-1 b. Synthesized Engine Parameters ..................................................................... 4-1 c. Third Source ................................................................................................... 4-1 4-3. Complete Loss of ADC Inputs................................................................................ 4-2 4-4. Common Mode Faults............................................................................................. 4-2 4-5. System Integration .................................................................................................. 4-3 a. Integration Activities...................................................................................... 4-3 b. Certification Activities ................................................................................... 4-5 4-6. Fault Accommodation Logic .................................................................................. 4-7 4-7. Control System Elements Mounted in the Aircraft................................................. 4-7 Page v AC 33.28-1 6/29/01 CHAPTER 5. COMPLIANCE WITH §33.28(b): FAILURE OF AIRCRAFT-SUPPLIED POWER 5-1. Failure of Aircraft-Supplied Power ........................................................................ 5-1 5-2. All Engine Out Restart Requirement ...................................................................... 5-1 5-3. Exceptions............................................................................................................... 5-1 5-4. Aircraft-Supplied Power as Backup Power ...........................................................
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