AC 29-2C, Chg 7 2/4/2016 Document Title AC 120-76B Guidelines for the Certification, Airworthiness, and Operational Use of Electronic Flight Bags Order 8110.49 Software Approval Guidelines,
(iv) Industry and Other Technical Documents.
(A) Radio Technical Commission for Aeronautic (RTCA) Documents:
Document Title RTCA/DO-160G Environmental Conditions and Test Procedures for Airborne Equipment RTCA/DO-178B & C Software Considerations in Airborne Systems and Equipment Certification RTCA/DO-187 Minimum Operational Performance Standards for Airborne Area Navigation Equipment using Multi-Sensor Inputs RTCA/DO-200A Standards for Processing Aeronautical Data RTCA/DO-201A Standards for Aeronautical Information RTCA/DO-254 Design Assurance Guidance for Airborne Electronic Hardware RTCA/DO-257A Minimum Operational Performance Standards for the Depiction of Navigation Information on Electronic Maps RTCA/DO-267A Minimum Aviation System Performance Standards (MASPS) for Flight Information Services-Broadcast (FIS-B) Data Link (B) Society of Automotive Engineers (SAE), International. Documents (use the current versions). The following SAE, documents are available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001 or from their website at www.sae.org.
Document Title ARP 926B Fault/Failure Analysis Procedure AIR 1093A Numeral, Letter and Symbol Dimensions for Aircraft Instrument Displays ARP 1782B Photometric and Colorimetric Measurement Procedures for Airborne Direct View CRT Displays ARP 1834A Fault/Failure Analysis for Digital Systems and Equipment ARP 1874 Design Objectives for CRT Displays for Part 25 (Transport) Aircraft Page MG 19 -4
Document Title ARP 4032B Human Engineering Considerations in the Application of Color to Electronic Aircraft Displays ARP 4033 Pilot System Integration ARP 4067 Design Objectives for CRT Displays for Part 23 Aircraft ARP 4101 Flight Deck Layout and Facilities ARP 4102 Flight Deck Panels, Controls, and Displays ARP 4102/7 Electronic Displays ARP 4103 Flight Deck Lighting for Commercial Transport Aircraft ARP 4105C Abbreviations, Acronyms, and Terms for Use on the Flight Deck ARP 4155A Human Interface Design Methodology for Integrated Display Symbology ARP 4256A Design Objectives for Liquid Crystal Displays for Part 25 (Transport) Aircraft ARP 4260A Photometric and Colorimetric Measurement Procedures for Airborne Flat Panel Displays ARP 4754A Guidelines for Development of Civil Aircraft and Systems ARP 4761 Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment ARP 5289A Electronic Aeronautical Symbols ARP 5364 Human Factor Considerations in the Design of Multifunction Display Systems for Civil Aircraft ARP 5365 Human Interface Criteria for Cockpit Display of Traffic Information AS 8034B Minimum Performance Standard for Airborne Multipurpose Electronic Displays AS 8055 Minimum Performance Standard for Airborne Head Up Display (HUD) ARD 50017 Aeronautical Charting ARD 50062 Human Factors Issues Associated With Terrain Separation Assurance Display Technology (C) Other Documents.
Document Title
DOT/FAA/CT- 03/05 Human Factors Design Standards for Acquisition of Commercial Off-The-Shelf Subsystems, Non- Developmental Items, and Developmental Systems.
DOT/FAA/OA M-TM-03-01 Multi-Function Displays A Guide for Human Factors Evaluations Page MG 19 - 5
AC 29-2C, Chg 7 2/4/2016
DOT/FAA/AA R-95/3 FAA Aircraft Certification Human Factors and Operations Checklist for Standalone GPS Receivers ICAO 8400/5 Procedures for Air Navigation Services, ICAO Abbreviations and Codes. Fifth Edition-1999.
(v) Miscellaneous Documents.
Note: The part 23 and part 25 ACs, and the GAMA publications listed below are not intended to serve as means of compliance for part 29 requirements. However, these documents may contain useful reference information that may be acceptable to the certificating authority on rotorcraft certification projects. When referencing these documents, ensure part 27 requirements are adequately addressed, particularly for part 27 IFR certifications. Coordinate early with the certificating authority if part 23, 25, or GAMA guidance is proposed to be used.
Document Title PS-ACE100-2001-004 Guidance for Reviewing Certification Plans to Address Human Factors for Certification of Part 23 Small Airplanes AC 23-23 Standardization Guide For Integrated Cockpits In Part 23 Airplanes AC 25-11A Electronic Flight Deck Displays AC 25-1322-1 Flightcrew Alerting GAMA Pub 10 (Version 1.0) Recommended Practices and Guidelines for Part 23 Cockpit/Flight Deck Design GAMA Pub 12 (Version 2.0) Recommended Practices and Guidelines for an Integrated Cockpit/Flightdeck in a Part 23 Airplane
(2) Acronyms and Descriptions.
(i) Acronyms:
Acronym Description AC Advisory Circular ACO Aircraft Certification Office ADC Air Data Computer ADI Attitude Director Indicator ADDS Aviation Digital Data Service AFM Aircraft Flight Manual AFMS Aircraft Flight Manual Supplement AHRS Attitude Heading Reference System ARD Aerospace Research Document Page MG 19 -6
Acronym Description ARP Aerospace Recommended Practice AS Aerospace Standard ASTC Amended Supplemental Type Certificate CA Certification Authority(ies) CAR Civil Air Regulations CFR Code of Federal Regulations CIP Current Icing Potential CS Certification Standard (EASA) EADI Electronic Attitude Direction Indicator EHSI Electronic Horizontal Situation Indicator EICAS Engine Indication and Crew Alert System ELOS Equivalent Level of Safety EVS Enhanced Vision Systems FAA Federal Aviation Administration FD Flight Director FHA Functional Hazard Assessment FLS Field-Loadable Software FMEA Failure Modes and Effects Analysis FOV Field-Of-View GPS Global Positioning System HIRF High Intensity Radiated Fields HUD Head-Up Display HSI Horizontal Situation Indicators ICAO International Civil Aviation Organization IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions JAR Joint Aviation Requirements LCD Liquid Crystal Displays LED Light Emitting Diodes LNAV Lateral Navigation (Used with GPS) LPV Localizer Performance Vertical (Used with GPS) METAR Meteorological Aviation Report MFD Multifunction Flight Display MG Miscellaneous Guidance Page MG 19 - 7
AC 29-2C, Chg 7 2/4/2016 Acronym Description ND Navigation Display PFD Primary Flight Display PFI Primary Flight Information POH Pilot's Operating Handbook RAIM Receiver Autonomous Integrity Monitoring (used with GPS) SAE Society of Automotive Engineers STC Supplemental Type Certificate SVS Synthetic Vision Systems TAS Traffic Advisory System HTAWS Helicopter Terrain Awareness Warning System TC Type Certificate TCAS Traffic Alert and Collision Avoidance System TSO Technical Standard Order VOR Very High Frequency Omnidirectional Range VFR Visual Flight Rules VMC Visual Meteorological Conditions WAAS Wide Area Augmentation System
(ii) Definitions. This paragraph contains definitions for terms used in this guidance. For the purposes of this guidance, a “display system” includes not only the display hardware and software components, but also the entire set of avionic devices implemented to display information to the flightcrew. Hardware and software components of other systems that affect displays, display functions, or display controls have to take into account the display aspects of this guidance. For example, this guidance would be applicable to a display used when setting the barometric correction for the altimeter, even though the barometric set function may be part of another system.
− Accuracy: A degree of conformance between the estimated or measured value and the true value.
− Adverse Operating Condition: A set of environmental or operational circumstances applicable to the aircraft, combined with a failure or other emergency that results in a significant increase in normal flight crew workload.
− Certification authority: The guidance in this FAA AC has been harmonized with that of Transport Canada, and EASA. The certification authority is that agency to which an applicant applies for airworthiness certification of their product. The term also applies when an applicant wishes to have a product validated in the U.S., Canada, or Europe.
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− Component: Any self-contained part, combination of parts, subassemblies, or units that perform a distinct function necessary for the operation of the system.
− Continued Safe Flight and Landing: This phrase means that the aircraft is capable of continued controlled flight and landing, possibly using emergency procedures, without requiring exceptional pilot skill or strength. On landing, some aircraft damage may occur because of a Failure Condition.
− Conventional: A system is considered “conventional” if its function, the technological means to implement its function, and its intended usage are all the same as, or closely similar to, that of previously approved systems that are commonly used.
The systems that have established an adequate service history and the means of compliance for approval are generally accepted as "conventional."
− Critical: A function whose loss or failure to properly perform would prevent the continued safe flight and landing of the aircraft. would prevent the continued safe flight and landing of the aircraft. Note: The term “Critical Function” is associated with a Catastrophic Failure Condition. Newer documents may not refer specifically to the term “Critical Function.”
− Criticality: The level of hazard associated with loss of or malfunction of a system function, hardware, software, etc., either alone, in combination with other systems, or in combination with events external to aircraft systems.
− Design-Eye Box: A three-dimensional volume of space surrounding the Design Eye Reference Point that used to determine the acceptability of display and control locations.
− Design-Eye Reference Point: A designer selected single reference point in space the assumed midpoint location is between the pilot’s eyes when seated properly at the pilot’s station.
− Development Assurance: All planned and systematic actions used to substantiate, to an adequate level of confidence, that the system satisfies the applicable certification basis after correction of the identified errors in requirements, design, and implementation.
− Enhanced Vision System: An electronic means to provide a display of the forward external scene topography (the natural or manmade features of a place or region), especially in a way to show their relative positions and elevation through the use of imaging sensors such as a forward looking infrared, millimeter wave radiometry, millimeter wave radar, and low light level image intensifying.
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AC 29-2C, Chg 7 2/4/2016 − Equipment Essential to Safe Operation: Equipment installed in order to comply with the applicable certification requirements of part 29 or operational requirements of parts 91 and 135.
− Failure: An occurrence that affects the operation of a component, part, or element such that it can no longer function as intended. This includes both loss of function and malfunction. Errors may cause failures, but they are not considered failures.
− Failure Condition: A condition having a direct or consequential effect on the aircraft, its occupants, or both, and that is caused or contributed to by one or more failures or errors. Failure Conditions may be classified according to their severity. See section 29.1309 of this AC for more information on failure conditions.
− Field-of-View: Display field of view: The angular extent of the display viewable with either pilot’s eye when seated at the pilot’s station. Pilot’s field of view:
See figures AC 29 MG 19-1 and AC 29 MG 19-2 for more information on the field-of view.
− Function: The lowest defined level of a specific action of a system, equipment, or flight crew performance aboard the aircraft that, by itself, provides a complete recognizable operational capability (for example, an aircraft heading is a function). One or more systems may contain a specific function or one system may contain multiple functions.
− Functional Hazard Assessment: A systematic, comprehensive examination of aircraft and system functions to identify potential Failure Conditions that will have an impact on the aircraft, the flight crew, or the occupants.
− Fix: A generic name for a geographical position also referred to as a fix, waypoint, intersection, reporting point, etc.
− Flight Plan: A sequence of fixes interconnected by the desired path.
Flight plans may range from the simplest that include only the aircraft’s present position, the active waypoint, and the desired path in between, to more complicated plans that include departure and destination airports with multiple intermediate fixes.
− Hardware: An object that has physical being. Generally refers to circuit cards, power supplies, etc.
− Hazard: Any condition that compromises the overall safety of the aircraft or adversely effects the ability of the flight crew to cope with adverse operating conditions.
− Independent: A component, part, element, or system that does not rely on another component, part, element, or system for accomplishing its function. This design Page MG 19 -10
concept ensures that the failure of one item does not cause a failure of another item.
For redundancy, each means of accomplishing the same function need not necessarily be identical.
− Indicator: A means for displaying information of a parameter. One display could depict more than one indicator. For example, a primary flight display may have indicators for attitude, altitude, airspeed, heading, and navigation.
− Integrated Modular Avionics (IMA): Both AC 20-170 and RTCA Document DO-297 provide the following definition of an IMA system:
“Shared set of flexible, reusable, and interoperable hardware and software resources that, when integrated, form a platform that provides services.
These services are designed and verified to a defined set of safety and performance requirements, to host applications performing aircraft functions.”
− Instrument: A device that is physically contained in one unit, or a device composed of two or more physically separate units or components connected together.
(One example is a remote indicating gyroscopic direction indicator that includes a magnetic sensing element, a gyroscopic unit, an amplifier, and an indicator connected together).
− Map Orientation: The relationship between the directions on a map to the compass depiction. Thus, using a North- up depiction, the North side of the map would be toward the top of the display and the south side of the map would be at the bottom.
Using a track-up depiction, the map would be oriented so that the aircraft’s track would be vertical on the map and pointing straight up toward the top of the display.
− Map Range: The geographic extent of the map region (for example, the distance covered by the map representation in either the vertical or the horizontal direction).
− Multifunction Flight Display (MFD): Any physical display unit, other than the PFD, with a reconfigurable layout that presents a variety of information.
− Navigation: The process of planning, recording, and controlling the movement of an aircraft from one place to another.
− Navigation Display: A suite of instruments that shows navigation data to the pilot.
− Navigation Information: Information that aids the flightcrew in determining the aircraft’s location in a given environment (for example, with respect to flight plans, VORs, NDBs, features on the airport surface including taxiway, signage, etc).
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AC 29-2C, Chg 7 2/4/2016 − Primary Display: As defined in § 23.1311(c) when used for instruments, it is “the display of a parameter that is located in the instrument panel such that the pilot looks at it first when wanting to view that parameter.”
− Primary Flight Display (PFD: A single physical unit that always provides the primary display of all of the following: altitude, airspeed, aircraft heading (direction), and attitude located directly in front of the pilot in a fixed layout in accordance with § 29.1321. It may include primary navigation information in a navigation section of the same display such as an HSI, navigation source and waypoint data, wind vector, and other basic navigation data. It may also provide other information pertinent to guidance and fundamental control of flight of the aircraft, such as engagement of flight guidance mode, flight director cueing, or other information.
− Primary Flight Information (PFI): Functions or parameters, such as airspeed, altitude, attitude, and heading (direction), required by the airworthiness and operational regulations.
− Primary Function: An installed feature that provides the most pertinent controls or information instantly and directly to the pilot.
− Primary Navigation Display: Display containing the most critical navigation information, such as on an HSI or CDI. It has the capability of displaying vertical and lateral deviation and may have the digital distance indication to/from the selected fix.
− Redundancy: The presence of more than one independent means for accomplishing a given function.
− Reversionary Display: A secondary means to provide information initially presented on the PFD or MFD by the transfer of information to an alternate display, usually as the result of a failure of a primary display.
− Reverse Video (Inverse Video): Visual alert or status indication presented with the inverse of the normally displayed alert. For example, for a visual alert normally displayed with yellow letters on black background, the “reverse video” presentation would be a yellow background with black letters.
− Scale: The relative proportion of the linear dimensions of objects on a display to the dimensions of the corresponding objects and distances being represented (for example, 1 inch = 100 nautical miles).
− Secondary Display: A means to provide display of information on a display other than the Primary Display.
− Standby Instrument: A dedicated instrument that is always available, which presents primary flight information.
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− Supplemental: Any additional function beyond t hose operationally required.
− System: A combination of components, parts, and elements that ar e interconnected to perform one or more functions.
− Synthetic Vision System: A system used to create a synthetic image representing the environment external to the aircraft. An image display based entirely or partially on an internal database carried on the aircraft.
− Time-Critical Warning: The highest level of warning for conditions that require immediate flight crew response, to maintain the immediate safe operation of the aircraft. Examples of Time- Critical warnings are:
• Overspeed Warnings.
• Low Energy Warnings.
• Helicopter Terrain Awareness Warnings (HTAWS).
• TCAS Resolution Advisory.
• Predictive and Reactive Windshear Warnings.
Track: The flight path of an aircraft over the surface of the earth, also known as true course.
Note: For additional definitions related to safety assessments, refer to AC 29-2, section
29.1309 and AC 29-2 MG 21 (FHA) of this AC.
c. Display Description.
(1) General.
(i) EDS displays and installations range from individual representations of ADI and HSI to fully integrated display suites combining primary flight and navigation information on a single display, a PFD and powerplant or system information on another display, or EICAS display. The flexibility allowed by the technology provides display designers wide latitude in how and where to display information to the pilot. Other displays or MFD of supplementary information may also be included in the installation.
(ii) The display layout and format of information may range from digitally rendered representations of conventional “round-dial” electromechanical gauges and instruments to tape displays to hybrid “round-dial” representations. Regardless of the format, the information displayed must be easily accessible and understandable by the pilot.
(iii) Retrofitting EDSs into existing “round-dial” or analog cockpits can create challenges due to interfaces with previously installed avionics and autopilot systems.
There should be an evaluation of these installations to ensure the pilot-system interface Page MG 19 - 13
AC 29-2C, Chg 7 2/4/2016 does not increase or significantly change the focus of pilot workload in order to manage and operate the system.
(iv) EDSs have the capability to combine the display of multiple flight, navigation, and powerplant parameters on to a single display, resulting in the loss of independence provided by individual gauges or instruments. As a result, considerations regarding loss of required information must account for a possible single failure leading to the loss of all flight, navigation, or powerplant information on a display.
(2) Basic flight and navigation information.
(i) 14 CFR 29.1303 and Appendix B to part 29 define required flight and navigation instruments.
(ii) Flight Instruments: There are different instrument requirements for VFR and IFR rotorcraft (see Appendix B to part 29, VIII). Consult operational regulations
(e.g., parts 91 and 135) for any additional flight instrument requirements. Flight instruments that are not required by § 29.1303 but are installed to satisfy either an operational requirement or to enhance safe operation of the rotorcraft should be located as close as possible to the pilots’ center line of vision. For example, radar altimeters should be installed where pilots can easily incorporate the gauge into their airspeed and altitude scan. Placing a radar altimeter or other flight instruments at the maximum extent of the pilots’ secondary field of view makes the instrument difficult to incorporate into an efficient scan and increases pilots’ workload.
(iii) Navigation information.
(A) The display of navigation information can be either on the PFD or on an EHSI Supplemental navigation information, such as moving maps, can be displayed on MFDs. . However, the EHSI or PFD should provide the pilot with course and heading adherence, coupled with the information required for the pilot to attain and maintain awareness of the rotorcraft’s position relative to navigation waypoints and action points.
(B) Navigation equipment requirements are also given in operational rules (For example, §§ 91.205 , 135.143, and 121 Subpart K). Display requirements for navigation information depend on which navigation system is installed in the rotorcraft.
Electronic display installations may affect the instruments and equipment required for flights under part 91 and part 135. These instruments and equipment include gyroscopic bank and pitch, gyroscopic direction, gyroscopic rate-of-turn, slip-skid instruments, and other required communication and navigational equipment.
(iv) Arrangement and visibility of primary flight and navigation information.
Place the primary flight and navigation information in the pilot’s primary field of view.
Figure AC 29 MG 19-1 illustrates the primary field of view. Due to rotorcraft instrument panel design, the display of some information may be located below -15° and will need Page MG 19 -14
LT 0 RT Horizontal Vertical 2/4/2016 AC 29-2C, Chg 7 flight evaluation to confirm that pilots can see the information easily without extensive eye movements.
Figure AC 29 MG 19-1 Primary Field of View
(3) Powerplant.
(i) 14 CFR 29.1305 defines the powerplant and associated instruments information that should be continuously displayed.
(ii) Powerplant indicators and information necessary to set and monitor power should display in the pilot’s primary field of view (Figure AC 29 MG 19-1).
(iii) However, the required powerplant information and indications that show engine health and ability to produce power (e.g., oil temperature and pressure), can be displayed in the pilot’s secondary field of view, depicted in Figure AC 29 MG 19-2.
Position this information within the secondary field of view where pilots can easily see it during their routine scans. A cross-cockpit location may not be acceptable depending on cockpit and instrument panel width.
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