Qualifying Avionics for Certification

Qualifying Avionics for Certification John Carr AEA Regulatory Consultant AEA Convention March 25, 2013 1

Outline 1. Objectives 2. Airworthiness Standards 3. Minimum Operational Performance Standards (MOPS) 4 Equipment Qualification 5. Installation Environment 6. RTCA & DO-160 7. DO-160G Sections and Categories, with examples 8. DO-160 Identification 9. Design for the Environment 10. Summary 2

1. Objectives To describe the performance and environmental qualification needed to support certification of avionics installations. This session will look at the certification requirements of Part 23/25/27/29.1301, 1306/1316 and 1309, and how qualification of equipment to Minimum Operational Performance Standards (MOPS) under environmental test conditions provides data that will support certification of systems and equipment functions and reliability under environmental conditions appropriate to the aircraft operating environment. 3

Acknowledgements RTCA Inc: - DO-160G Northern Airborne Technology Ltd. - Nameplate - Test data and photographs Electronics Test Centre (ETC) - Test photographs CKC Labs: - Test photographs 4

Qualification Identification Should this product be installed on a rotorcraft?

Qualification Identification Sec 8, Cat UF = Helicopter Vibration - Unknown Frequencies

Qualification Identification What is the maximum altitude this equipment is qualified for?

Qualification Identification Sec 4, Cat B4 = 25,000ft Altitude

2. Airworthiness Standards FAR 23/25/27/29 contain standards for functional performance of installed equipment under environmental conditions:.1301 Function and Installation.1306 /1316 System Lightning Protection.1309 Equipment, Systems, and Installations.1431 Electronic Equipment 9

Airworthiness Standards FAR 23/27/25/29.1301: Function and Installation (a) "Each item of installed equipment must - (1) Be of a kind and design appropriate to its intended function. (3) Be installed according to limitations specified for the equipment (4) Function properly when installed

Airworthiness Standards FAR 23.1306, 25/27/29.1316 Electrical and electronic system lightning protection. (a) Each electrical and electronic system that performs a function, for which failure would prevent the continued safe flight and landing of the airplane, must be designed and installed so that-- (1) The function is not adversely affected during and after the time the airplane is exposed to lightning; and (2) The system automatically recovers normal operation of that function in a timely manner after the airplane is exposed to lightning.

Airworthiness Standards FAR 23/25/27/29.1309: Equipment, systems, and installations. (a) The equipment, systems, and installations whose functioning is required by this subchapter, must be designed to ensure they perform their intended functions under any foreseeable operating condition.

Airworthiness Standards FAR 23/25/29.1431 contain standards for noninterference of required electronic equipment: 25.1431: (a) In showing compliance with 25.1309(a) and (b) with respect to radio and electronic equipment and their installations, critical environmental conditions must be considered. (c) Radio and electronic equipment, controls, and wiring must be installed so that operation of any one unit or system of units will not adversely affect the simultaneous operation of any other radio or electronic unit, or system of units, required by this chapter. (d) Electronic equipment must be designed and installed such that it does not cause essential loads to become inoperative as a result of electrical power supply transients or transients from other causes. 13

Airworthiness Standards Non-required equipment need not meet performance standards under environmental conditions but must not operate or fail such that required equipment or aircraft operation is adversely affected. Refer to FAA/TCCA/EASA for current policy on non-required equipment. 14

Airworthiness Standards Equipment approval standards include performance and environmental qualification standards: Avionics, mechanical equipment, personnel equipment, seats, etc. FAA Technical Standard Order (TSO) Authorizations: Granted for equipment performance, but... Does not confer installation approval: Installation must be approved via TC/STC or Modification approval; Environmental qualification must match installation environment. Ditto for TCCA CAN-TSO and EASA ETSO design approvals. 15

3. Performance Standards Minimum Operational Performance Standards (MOPS) Specified in TSOs Usually by reference to RTCA standard, e.g: DO-260, Minimum Operational Performance Standards for 1090 MHz Automatic Dependent Surveillance Broadcast (ADS-B) DO-262A, Minimum Operational Performance Standards for Avionics Supporting Next Generation Satellite Systems (NGSS) DO-300, Minimum Operational Performance Standards (MOPS) for Traffic Alert and Collision Avoidance System II (TCAS II) Hybrid Surveillance

4. Equipment Qualification Qualification of equipment is testing of that equipment to determine that it performs its intended functions (MOPS) and/or does not fail in a manner that hazards the aircraft, under specified environmental conditions; Common standards for environmental qualification have been accepted by the FAA, EASA, TCCA, etc.; RTCA / DO-160( ) and equivalent EUROCAE ED-14. Enabled by Advisory Circulars and TSO Standards 17

Equipment Qualification "Environmental" includes: Physical environment: Temperature, Altitude, Humidity, Vibration, Shock, Waterproofness, Sand & Dust, Salt Fog, etc. Electrical environment: Electrical power supply characteristics. Electro-magnetic environment: EM interference, EM susceptibility, lightning, static electricity. Flammability 18

Equipment Qualification Qualification is accomplished by testing in laboratories that have appropriate test equipment and test personnel; Test labs do not have to be approved or accredited by Airworthiness Authority; Test lab has to demonstrate required environmental test procedures can be accomplished Equipment manufacturer has to demonstrate that required performance tests can be accomplished. 19

5. Equipment Installation Environment Relate environmental qualification to intended function of equipment and operational environment of aircraft, e.g: Pressurized / non-pressurized airframe Maximum operating altitude Equipment location and mounting Need for equipment function during emergency operating conditions, e.g.: Rapid decompression and emergency descent Emergency electrical system voltage conditions Potential for equipment exposure to contaminating fluids, sand and dust, salt fog, etc. 20

Equipment Installation Environment STC Certification Plan: Compliance to FAR 2x.1301(a), 2x.1306/1316, 2x.1309(a), 2x.1431(a), (c), (d); Compliance to applicable Special Conditions (e.g. HIRF) Identify equipment DO-160( ) test Sections and Categories; State reason for acceptance of Categories for particular installation: Intended function and criticality of equipment Location of equipment in aircraft Aircraft operating envelope / environment 21

6. RTCA and DO-160( ) "RTCA" Originally "Radio Technical Commission for Aeronautics", formed in 1935. Set up as Federal Advisory Organization in response to request by US Civil Aeronautics Board (CAB) for organization to develop radio and navigation performance and equipment standards. Now just "RTCA, Inc." Responds to requests from US FAA for aviation Minimum Operational Performance Standards (MOPS), for airborne systems and equipment. www.rtca.org 22

RTCA and DO-160( ) Special Committees (SC) are formed to: Study and recommend Minimum Operational Performance Standards (MOPS); Develop technical guidance documents (e.g. DO-178B, Guidelines for Software Aspects of Certification) SC Members: FAA (Designated Federal Employee) Other CAAs, e.g. TCCA, EASA. Industry volunteers FAA DERs 23

RTCA and DO-160( ) Background to DO-160G DO-160 issued 1975, replaced DO-138 DO-160A thru DO-160F issued 1980-2007 DO-160G issued December 2010: Enabled by FAA AC 21-16G for TSO, TC and STC applicants as acceptable means (but not only means) for environmental qualification of airborne equipment. 24

RTCA and DO-160( ) FAA AC 21-16G: If you are an applicant installing equipment, you may use RTCA/DO-160, any version, to support compliance with the applicable airworthiness requirements. When possible, we recommend that you use RTCA/DO-160G as it provides the most clear and complete test procedures. 25

RTCA and DO-160( ) DO-160 Revision applicable to TC/STCs: Aircraft TCDS does not specify applicable DO-160 revision AC21-16( ) would be applicable at date of application for aircraft TC, but: Installed equipment could be approved to existing TSO that calls up earlier revision of DO-160, or even DO-138. May not be record of applicability or FAA/TCCA decision. 26

RTCA and DO-160( ) Applicable DO-160 Revision: For STCs, engineer / designee / delegate must assess qualification of equipment to DO-160 Revision, Sections and Categories for acceptability to particular installation: Relate to intended function of equipment and operational environment of aircraft; Identify in Certification Plan and agree with Certifying Authority; Provide substantiating data: TSO Authorization and Environmental Qualification Form Qualification test data if not TSO'd 27

7. DO-160G Sections & Categories 4.0 Temperature & Altitude 16.0 Power Input 5.0 Temperature Variation 17.0 Voltage Spike 6.0 Humidity 18.0 Audio Freq Susceptibility 7.0 Op Shock & Crash Safety 19.0 Induced Susceptibility 8.0 Vibration 20.0 RF Susceptibility 9.0 Explosion Proofness 21.0 RF Emissions 10.0 Waterproofness 22.0 Lightning Susceptibility 11.0 Fluids Susceptibility 23.0 Lightning Direct Effects 12.0 Sand & Dust 24.0 Icing 13.0 Fungus Resistance 25.0 Electro-Static Discharge 14.0 Salt Fog 26.0 Fire, Flammability 15.0 Magnetic Effect 28

Equipment Example A Electronic Flight Instrument System (EFIS): Primary Flight display (PFD); Approved under multiple TSOs for flight and nav information; Installed in cockpit of pressurized FAR 25 aircraft; Required equipment functions: Must perform intended function under all possible adverse environmental conditions, including: HIRF, lightning; Rapid decompression (for emergency descent); Low power voltage conditions (for elect generation failures) 29

Example A: EFIS: 30

Equipment Example B Satellite Communication System (SatCom): No applicable TSOs; Transceiver installed in avionics bay of non-pressurized FAR 23 aircraft; Antenna installed on upper skin of aircraft; Non-Required equipment: Need not perform intended function under adverse environmental conditions, but: Must not operate or fail in a manner that will have an adverse impact on required equipment. 31

Example B: SatCom and Antenna: 32

4.0 Temperature & Altitude: Purpose: To ensure operation under temperature and altitude. Categories A1-4, B1-4, C1-4, D1-3, E1-2, F1-3: Temp: Controlled, partially controlled, uncontrolled: Op hi & lo, short-term op hi & lo, ground survival hi and lo. Alt: Pressurized, non-pressurized: to 15,000', 25,000', 35,000', 50,000', 70,000' Location: Within airframe, within powerplant compartment. Rapid decompression: 8,000' (cabin pressure) to max op altitude in < 15 secs. Overpressure: -15,000', for overpressure during cabin pressurization testing. 33

Temperature and Altitude: EFIS: Max and min operating temperatures; Ground survival temps for start-up environment; Altitude for pressurized cabin; Rapid decompression for availability under loss of pressurization at max operating altitude and emergency descent. SatCom: Max and min operating temperatures to ensure components do not fail and emit smoke; Altitude for pressurized cabin or non-pressurized location if transceiver contains sealed components or enclosures. May not be necessary if simple components. 34

5.0 Temperature Variation Purpose: To ensure operation under changing temperature conditions. Categories A, B, C, S1,2: Temperature variations of 2, 5, or 10 deg C per minute. Test combine with temperature tests in one test profile. 35

Temperature Variation: EFIS: Include in test profile for max and min operating temperatures. SatCom: Include in test profile for max and min operating temperatures. 36

Temperature Variation Test Profile 37

Temperature Test Chamber 38

Altitude and Rapid Decompression Chambers 39

6.0 Humidity Purpose: To ensure operation under humid conditions. Categories: A: Standard humidity, env controlled location: 48 hours, 38-50 deg C, 95% RH. B: Severe humidity, non-env controlled location: 10 x 24 h cycles (240 hours), 38-50 deg C, 95% RH. C: External environment: 6 x 24 h cycles (144 hours), 30-50 deg C, 85-95% RH 40

Humidity: EFIS: Test for standard humidity conditions (cockpit environment) unless customer requires severe conditions. SatCom: Test not necessary. Unlikely that exposure to humidity will cause condition within equipment that could hazard other equipment. May be required by customer, or for marketing reasons. 41

Humidity Profile: 42

7.0 Operational Shock & Crash Safety Purpose: Op Shock. To ensure equipment operates under shock conditions experienced in aircraft operations. (Taxying, landing, gusts) Crash Safety. To ensure equipment does not hazard occupants during survivable crash landing conditions. (Detachment from mountings) Categories: A: Standard op shocks (6g, 11ms saw-tooth impulse) B: Standard op shocks + crash safety (impulse or sustained) D: Low frequency op shocks (6g, 20ms saw-tooth impulse) E: Low frequency op shocks + crash safety (impulse or sustained) 43

Operational Shock and Crash Safety: EFIS: Test for standard op shock and crash safety (cockpit mounted equipment). SatCom: Test for Op shock to ensure equipment does not fail in manner that could cause hazard (e.g. component failure causing smoke, fire). Crash Safety test not necessary. Equipment is not mounted in cockpit or cabin. 44

Shock Test Profile: 45

8.0 Vibration Purpose: To ensure equipment operates under vibration conditions. Categories: Many combinations of: Aircraft Types: Helicopter (known or unknown rotor frequency). Fixed wing turbojet or fan, reciprocating or turboprop. FAR 23 multiple or single engine. Equipment Location: Fuselage, instrument panel, equipment rack, nacelle/pylon, engine gearbox, wing or wheel well, landing gear, empennage. 46

8.0 Vibration (contd.) Vibration profile: Sine, random, or combination (sine on random). Equipment tested in 3 axes. Test Equipment: Vibration profiles stored in computer (available pre-loaded); Vertical drive table for smaller equipment (avionics); Horizontal slider table for large equipment (seats, hydraulic equipment, etc.) Test fixture with equipment fastened per installation instructions; Test fixture attached to table surface. 47

Vibration: DO-160G Sections & Categories EFIS: Test for vibration profiles appropriate to cockpit location and type of aircraft/engine. May test to multiple environments, e.g. fixed wing and rotorcraft. SatCom: Test for vibration profiles appropriate to installed location and type of aircraft/engine. Equipment must not fail in manner that could hazard aircraft, e.g. smoke or fire from transceiver due to component failures, or failure of antenna that could cause detachment from airframe. 48

Vibration Profile, CAT UG (Sine-on-Random) 49

Small Vibration Table: 50

9.0 Explosion Proofness Purpose: To determine negligible risk that equipment will cause explosion of flammable gas or vapour within declared environment. Declared Environments: I: Uncovered fluids or vapours; II: Fluids or vapours caused by spillage or leakage; III: Fire zone Categories: A: Ignition contained, external temp not capable of ignition; E: Ignition not contained, ext temp not capable of ignition; H: Non-spark producing, ext temp not capable of ignition. 51

Explosion Proofness: EFIS: Test not required for cockpit equipment. SatCom: Test not required unless equipment is to be mounted in location where flammable fluids or vapours may exist (Ref Sec 9.0 Environments). 52

10.0 Waterproofness Purpose: To ensure equipment can withstand the effects of liquid water spray or water falling on equipment. Test not required for hermetically sealed equipment. Categories: Y: Condensing water locations; W: Falling water locations (from condensation); R: Rain or spray exposure; S: Heavy stream of water from washing or spraying. 53

Waterproofness: EFIS: Cat W Test (drip proof) required for essential cockpit equipment. SatCom: Test not required for transceiver. Cat S test optional for antenna 54

11.0 Fluids Susceptibility Purpose: To determine if equipment materials can withstand effects of fluid contaminents from ground and airborne operations. Category: F: Spray and immersion test. Test Fluids: Fuels, hydraulic fluids, oils, solvents, de-icing fluids, coolants, insecticides, fire extinguishant, etc. Only test to fluids applicable to installation; Tested fluids to be identified on Environmental Qualification Form. 55

Fluids Susceptibility: EFIS: Test would not be required for cockpit equipment. SatCom: Test not required. Antenna may require testing for possible external fluids. 56

12.0 Sand & Dust Purpose: To determine resistance of equipment to effects of blowing sand and dust: Categories: Adverse effects on moving parts, electrical parts, fluids. D: Blowing dust S: Blowing sand and dust 57

Sand and Dust: EFIS: Test would not be required for cockpit equipment. SatCom: Test not required. Antenna may be tested for sand and dust effects to support reliability claims. 58

13.0 Fungus Resistance Purpose: To determine if equipment is adversely affected by fungi under conditions favourable for their development. Categories: F: Equipment installed in environment where exposed to severe fungus contamination. Test is not required if analysis of materials shows they are non-nutrient for growth of fungus. Analysis statement would be made in Environmental Qualification Form. 59

Fungus Resistance: EFIS: Test would not be required for cockpit equipment. SatCom: Test not required. 60

14.0 Salt Fog Purpose: To determine effects of equipment of prolonged exposure to a salt atmosphere or salt fog, e.g. Categories: Corrosion, clogging of moving parts, insulation breakdown, damage to electrical contacts or exposed wire. S: Subject to salt atmosphere of normal operations; T: Severe environment, e.g. hovering above ocean. 61

Salt Fog: DO-160G Sections & Categories EFIS: Cat S Test required for essential cockpit equipment. SatCom: Test not required. 62

Salt Fog Test: 63

15.0 Magnetic Effect Purpose: To ensure operation of equipment does not cause magnetic interference with nearby equipment. Categories Y: Magnetic deflection immediately adjacent to equipment Z: Magnetic deflection at < 0.3 m A: Magnetic deflection at 0.3 to 1.0 m B: Magnetic deflection at 1.0 m to 3.0 m C: Magnetic deflection at > 3.0 m 64

Magnetic Effect: EFIS: Cat Z Test required for equipment installed in cockpit due to proximity to compass equipment and other potentially affected equipment. SatCom: Cat A Test required if transceiver installed in avionics bay. Cat B may be acceptable if installed away from other avionics equipment. 65

16.0 Power Input Purpose: To ensure equipment functions under appropriate electrical power input conditions. Categories: A( ): Primary AC generation with DC from TRUs: (CF) - constant freq. (NF) - variable freq., narrow range; (WF) - variable freq., wide range. B: Primary DC generation, with AC from inverters. Z: DC powered equipment from any type of power source 66

16.0 Power Input (Contd.) AC Test Conditions: Normal and abnormal voltage and frequency; Normal and abnormal frequency transients; Normal and abnormal surge voltage; Momentary under-voltage. DC Test Conditions: Steady state and low voltage; Ripple voltage; Normal and abnormal surge voltage; Momentary power interruption; Engine start under-voltage; Momentary under-voltage; Dc current ripple (if required): additional Letter (R or X) Inrush current (if required): additional letter (I or X) 67

Power Input: EFIS: Cat A( ) or Cat Z( - - )Test with all test conditions is appropriate for essential equipment. SatCom: Cat A( ) or Cat B( - - )Test required for non-required equipment to ensure equipment does not fail under high voltage or transient voltage conditions such that components fail and cause smoke or fire. 68

Power Input Engine Start Under-voltage Test Waveform 69

17.0 Voltage Spike Purpose: To determine if equipment can withstand effects of voltage spikes (AC or DC). Categories: A: High standard of protection is required; B: Lower standard of protection is acceptable. Test Conditions: +ve and -ve spikes Cat A: 600v AC or DC Cat B: 2 x line voltage AC(rms) or DC 70

Voltage Spike: EFIS: Cat A protection required for essential equipment. SatCom: Cat B protection acceptable. Equipment may fail, but failure must not result in component damage that causes smoke or fire. 71

Voltage Spike Transient: 72

18.0 Audio Freq. Conducted Susceptibility Purpose: Power Inputs (Ripple) To ensure equipment will operate when subjected to harmonic frequency components of power source. Categories: R( ): Primary AC generation with DC from TRUs: (CF), (NF), (WF) same as Section 16.0 B: Primary DC generation, with AC from inverters. K: AC generation with high distortion levels. 73

AF Conducted Susceptibility - Power Inputs EFIS: Test required for essential equipment. SatCom: Test not required for nonrequired equipment. Category to be matched to Sec. 16.0 Category 74

19.0 Induced Signal Susceptibility Purpose: To determine if equipment interconnect wiring is susceptible to magnetic or electric field induced voltages from other equipment or systems. Categories: C( ): Interference-free operation required, long wire runs. Z( ): Interference-free operation required. A( ): Interference-free operation desireable. B( ): Interference free operation controlled to acceptable level. ( ) letter assigned for type of power supply. 75

Induced Signal Susceptibility EFIS: Cat C or Z Test required for essential equipment. SatCom: Susceptibility test is not required for non-required equipment. 76

20.0 Radio Frequency Susceptibility Purpose: To determine if equipment will operate within specifications when equipment and interconnect wiring is exposed to RF fields (radiated or conducted into wiring). Categories: B thru O: High Intensity Radiated Field (HIRF) levels: per FAA AC on HIRF for Certification Environment. R: HIRF level (normal)- bench test acceptable. S: Interference-free operation desireable. T: Typical aircraft internal EMI environment (no HIRF from external sources) 77

Test Conditions: Test conducted in RF anechoic chamber; Radiated susceptibility by exposing equipment and interconnect wiring to radiation from various antenna (per frequency range); Conducted susceptibility by clamping electric field probes around power and signal interconnect wiring. Test Frequencies: A - L: 1 MHz to 18 GHz R: 1 MHz to 8 GHz S: 1 MHz to 2 GHz T: 1 MHz to 8 GHz 78

RF Susceptibility EFIS: HIRF test category required for essential equipment installed in cockpit if Certification Basis of aircraft has HIRF Special Condition. SatCom: Susceptibility test not required for non-required equipment. EFIS STC may have HIRF SC imposed. 79

21.0 Emission of Radio Frequency Energy Purpose: To determine that equipment does not emit undesired RF noise that could affect other systems and equipment. Categories: B: Emissions controlled to tolerable levels; L: Equipment and wiring located far from windows or antenna (installed in equipment bay); M: Equipment and wiring located where apertures (windows) are RF significant; H: Equipment located in direct view of receiving antenna; P: Equipment located close to HF, VHF or GPS antenna. 80

21.0 Emission of RF Energy (Contd.) Test Conditions: Test conducted in RF anechoic chamber; Radiated emissions measured with probe antenna; Conducted emissions measured with clamp-on cable probe. 81

Emission of RF Energy: EFIS: Cat M Test required for equipment installed in cockpit due to large window apertures and potential to interfere with other cockpit equipment and external antenna. SatCom: Test required to ensure nonrequired equipment does not cause interference to required equipment. Cat L would be acceptable for equipment installed in equipment bay. 82

RF Test Chamber 83

RF Radiated Susceptibility Test (100 1215 MHz) 84

RF Radiated Emissions Test Results (30 MHz to 180 MHz) 85

RF Radiated Emissions Test (190 KHz to 30 MHz) 86

22.0 Lightning Induced Transient Susceptibility Purpose: To verify capability of equipment to withstand effects of lightning induced transients. Categories: NOT direct lightning strike damage effect. XX: Connector pin injection test waveforms & levels (100v to 3200v) YYY: Cable bundle injection test waveforms & levels (50v to 3200v) e.g. [A3C33] 87

22.0 Lightning Induced Transient Susceptibility (Contd.) Waveform Sets (A thru K): Based on interconnect wiring installation and type of airframe construction (metal or composite); Test Levels (1 thru 5): Based on aircraft internal e-m environment; Equipment manufacturer should test for most probable installation scenario, unless known. 88

Lightning Induced Transient Susceptibility EFIS: Test required for essential equipment. SatCom: Test not required for nonrequired equipment. Waveforms and levels to be chosen for airframe construction type and cockpit environment. 89

Lightning Transient Cable Bundle Injection Test Setup 90

23.0 Lightning Direct Effects Purpose: To determine ability of externally mounted equipment to withstand effects of direct lightning strike, e.g.: Categories: Antennae, lights, sensors, probes. 1A/B, 2A/B, 3: Depending on aircraft lightning zone for location of equipment. "F" added for fuel vapour region testing. 91

Lightning Direct Effects EFIS: Test not required for equipment installed inside airframe SatCom: Test not required for equipment installed inside airframe. Antenna may be tested for reliability/survivability or marketing reasons. 92

24.0 Icing Purpose: To determine characteristics of equipment that must operate when exposed to icing conditions. Categories: A: Extenally mounted equipment, no de-icing; B: Equipment with moving parts that may be affected by freezing condensation; C: External equipment, to determine when de-icing is needed. Tests conducted by cycles of temperature and humidity. 93

Icing EFIS: Test not required for equipment installed in cockpit. SatCom: Test not required for equipment installed inside airframe. Antenna may be tested to Cat A for reliability/survivability or marketing reasons. 94

25.0 Electrostatic Discharge Purpose: To determine the immunity of equipment to static electricity discharge from human contact. Category: A: All equipment. Test required for sensitive avionics equipment that is touched regularly by aircraft crew. 95

Electrostatic Discharge EFIS: Test required. Equipment installed in cockpit and operated by crew. SatCom: Test not required. 96

26.0 Fire, Flammability Purpose: To determine resistance to fire, and flammability characteristics. Categories: A: Fire-proof. (Fire zone equipment) Must keep safety related functions for 15 minutes. B: Fire Resistant. (Fire zone equipment) Must survive 5 minutes with no structural degradation. C: Flammability (Installed in non-fire zone. Dimension > 50mm): Flammability test same as FAR 25 App.F. 97

Fire, Flammability EFIS: Flammability test necessary for essential cockpit equipment, unless small parts analysis & equipment case venting design accepted by authority. SatCom: Test not required. 98

8. DO-160 Identification DO-160 Identification: DO-160G Appendix A: Environmental Qualification Form (EQF) Tests, categories, details, applicability to equipment. To be included with TSO data package and available to installers. Individual environmental categories may be identified on the equipment by DO-160( ) environmental string,e.g: DO-160D: B4-BAB[(SBM)(UF)]XXXXXXZBABB[TTX]MXXXX One character set per Section X indicates no test was conducted 99

DO-160 Identification EFIS: DO-160G Env Cat: B4-BBB[(SBM)(UG)]XWXXXSY[Z(RI)]AB[Z(B)]BM[A3C33]XXAC SATCOM: DO-160G Env Cat: B4-AXA[SBM]XXXXXXA[B(XX)]BBXXLXXXXC 100

DO-160 Identification Environmental Qualification Form: 101

9. Design for the Environment Equipment Design Experience counts! Equipment manufacturers must be aware of applicable Minimum Operational Performance Standards (MOPS) and latest (DO-160G) qualification requirements and relationship to anticipated aircraft installation environments; Designers must understand design implications of DO-160 tests; Designers must consider installation interfaces (electrical and mechanical) 102

Design for the Environment Installation Design: Installation designer must have knowledge of equipment qualification categories and limitations; Consider alleviating factors in design: Mounting attitude and orientation; Shock mounting; Wire routing for EMI considerations; Drip covers; Venting; Controlled vs. uncontrolled environment; Cooling. 103

10. Summary Designers, Designees and Delegates must review DO-160 qualification of equipment for applicability to installation approval: Equipment approval (e.g. TSO) does not confer installation approval; Ask for equipment Environmental Qualification Form to see any limitations; Potential for adverse impact on reliability and safety if qualification of equipment does not meet installed environment. 104