Qualifying Avionics for Certification
|
|
- Andra Moore
- 6 years ago
- Views:
Transcription
1 Qualifying Avionics for Certification John Carr AEA Regulatory Consultant AEA Convention March 25,
2 Outline 1. Objectives 2. Airworthiness Standards 3. Minimum Operational Performance Standards (MOPS) 4 Equipment Qualification 5. Installation Environment 6. RTCA & DO DO-160G Sections and Categories, with examples 8. DO-160 Identification 9. Design for the Environment 10. Summary 2
3 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/ , 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
4 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
5 Qualification Identification Should this product be installed on a rotorcraft?
6 Qualification Identification Sec 8, Cat UF = Helicopter Vibration - Unknown Frequencies
7 Qualification Identification What is the maximum altitude this equipment is qualified for?
8 Qualification Identification Sec 4, Cat B4 = 25,000ft Altitude
9 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
10 Airworthiness Standards FAR 23/27/25/ : 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
11 Airworthiness Standards FAR , 25/27/ 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.
12 Airworthiness Standards FAR 23/25/27/ : 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.
13 Airworthiness Standards FAR 23/25/ contain standards for noninterference of required electronic equipment: : (a) In showing compliance with (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
14 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
15 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
16 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
17 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
18 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
19 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
20 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
21 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
22 6. RTCA and DO-160( ) "RTCA" Originally "Radio Technical Commission for Aeronautics", formed in 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. 22
23 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
24 RTCA and DO-160( ) Background to DO-160G DO-160 issued 1975, replaced DO-138 DO-160A thru DO-160F issued 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
25 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
26 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
27 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
28 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
29 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
30 Example A: EFIS: 30
31 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
32 Example B: SatCom and Antenna: 32
33 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
34 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
35 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
36 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
37 Temperature Variation Test Profile 37
38 Temperature Test Chamber 38
39 Altitude and Rapid Decompression Chambers 39
40 6.0 Humidity Purpose: To ensure operation under humid conditions. Categories: A: Standard humidity, env controlled location: 48 hours, deg C, 95% RH. B: Severe humidity, non-env controlled location: 10 x 24 h cycles (240 hours), deg C, 95% RH. C: External environment: 6 x 24 h cycles (144 hours), deg C, 85-95% RH 40
41 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
42 Humidity Profile: 42
43 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
44 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
45 Shock Test Profile: 45
46 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
47 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
48 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
49 Vibration Profile, CAT UG (Sine-on-Random) 49
50 Small Vibration Table: 50
51 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
52 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
53 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
54 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
55 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
56 Fluids Susceptibility: EFIS: Test would not be required for cockpit equipment. SatCom: Test not required. Antenna may require testing for possible external fluids. 56
57 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
58 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
59 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
60 Fungus Resistance: EFIS: Test would not be required for cockpit equipment. SatCom: Test not required. 60
61 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
62 Salt Fog: DO-160G Sections & Categories EFIS: Cat S Test required for essential cockpit equipment. SatCom: Test not required. 62
63 Salt Fog Test: 63
64 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
65 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
66 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
67 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
68 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
69 Power Input Engine Start Under-voltage Test Waveform 69
70 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
71 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
72 Voltage Spike Transient: 72
73 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
74 AF Conducted Susceptibility - Power Inputs EFIS: Test required for essential equipment. SatCom: Test not required for nonrequired equipment. Category to be matched to Sec Category 74
75 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
76 Induced Signal Susceptibility EFIS: Cat C or Z Test required for essential equipment. SatCom: Susceptibility test is not required for non-required equipment. 76
77 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
78 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
79 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
80 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
81 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
82 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
83 RF Test Chamber 83
84 RF Radiated Susceptibility Test ( MHz) 84
85 RF Radiated Emissions Test Results (30 MHz to 180 MHz) 85
86 RF Radiated Emissions Test (190 KHz to 30 MHz) 86
87 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
88 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
89 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
90 Lightning Transient Cable Bundle Injection Test Setup 90
91 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
92 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
93 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
94 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
95 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
96 Electrostatic Discharge EFIS: Test required. Equipment installed in cockpit and operated by crew. SatCom: Test not required. 96
97 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
98 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
99 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
100 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
101 DO-160 Identification Environmental Qualification Form: 101
102 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
103 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
104 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
«DO160/ED14» - Jessica France
Training Workshop «DO160/ED14» - Jessica France DO160/ED14 Specificities of Mechanical and Climatic aspects Edouard ZUNDEL Systems Qualification Engineer for Mechanical and Climatic aspects 1 The reference
More informationTraining Workshop «DO160/ED14» - Jessica France
Training Workshop «DO160/ED14» - Jessica France DO160/ED14 Issue F to G Edouard ZUNDEL Systems Qualification Engineer for Mechanical and Climatic aspects 1 Overview - Temperature &Altitude Procedure clarification
More informationThe Faraday Test Centre Rochester
Rochester REAL CAPABILITY. REAL ADVANTAGE. BAE Systems is an international company engaged in the development, delivery and support of advanced defence and aerospace systems in the air, on land, at sea
More informationUnderstanding the Role of RTCA DO-160 in the Avionics Certification Process
Donald L Sweeney D.L.S. Electronic Systems, Inc & D.L.S. Conformity Assessment, Inc. Copyright D.L.S. Electronic Systems, Inc 2013, 2014 and 2015 Understanding the Role of RTCA DO-160 in the Avionics Certification
More informationSubject: Structural Certification Criteria Date: 10/11/18 Policy No: PS-AIR for Antennas, Radomes, and Other External Modifications
Policy Statement Subject: Structural Certification Criteria Date: 10/11/18 Policy No: PS-AIR-25-17 for Antennas, Radomes, and Other External Modifications Initiated By: AIR-675 Summary This policy statement
More informationAIS-360 ARINC LS/HS ADAPTER
P/N: 833610-01 REV A Shadin Avionics 6831 Oxford Street St. Louis Park, MN 55426 USA Sales: (800) 328-0584 Customer Service: (800) 388-2849 WWW.SHADIN.COM MANUAL P/N: IM833610-01 Rev: A P/N 833610-01 PAGE
More informationAEROSPACE STANDARD. Minimum Operational Performance Specification for Inflight Icing Detection Systems FOREWORD
400 Commonwealth Drive, Warrendale, PA 15096-0001 AEROSPACE STANDARD Issued 2001-10 Minimum Operational Performance Specification for Inflight Icing Detection Systems FOREWORD 1. The development of these
More informationAdvisory Circular (AC)
Advisory Circular (AC) Certification of Large Aeroplanes in the Restricted Category, Used for Special Purpose Operations File No. 5009-6-525 AC No. 525-012 RDIMS No. 1140123-V1 Issue No. 02 Issuing Branch
More informationAre you up to the Available online at: avionicsnews.net FAA-ACCEPTED This exam is available online to AEA members. TRAINING AVIONICS TRAINING
Are you up to the TEST? Take the 2015 Technical Training Exam Available online at: avionicsnews.net FAA-accepted training is available to AEA members through the pages of Avionics News. With the 2015 Technical
More informationAdvisory Circular (AC)
Advisory Circular (AC) Stall, Compliance File No. 5009-6-525 AC No. 525-020 RDIMS No. 528401-V3 Issue No. 01 Issuing Branch Aircraft Certification Effective Date 2004-12-01 1.0 INTRODUCTION... 2 1.1 Purpose...
More informationAeromedical Aircraft Certification and the use of inhaled Nitric Oxide (ino) Ian Kitson Principal Engineer - Adelaide
Aeromedical Aircraft Certification and the use of inhaled Nitric Oxide (ino) Ian Kitson Principal Engineer - Adelaide August 2011 1 Introduction Requirement Risks Regulatory Environment Demonstrating Compliance
More informationTesting of Active Flow Control actuators at harsh environment
Testing of Active Flow Control actuators at harsh environment Ionut BRINZA (INCAS) 6 th CEAS CONFERENCE 16-20 October 2017 Bucharest ROMANIA Introduction Results of the harsh environment tests Conclusions
More informationBASIC AIRCRAFT STRUCTURES
Slide 1 BASIC AIRCRAFT STRUCTURES The basic aircraft structure serves multiple purposes. Such as aircraft aerodynamics; which indicates how smooth the aircraft flies thru the air (The Skelton of the aircraft
More information204-10SDRD/S530-A3 LAMP. Features. Description. Applications. Revision 1. LifecyclePhase: Expired Period: Forever. Choice of various viewing angles
Features Choice of various viewing angles Available on tape and reel. Reliable and robust Pb free The product itself will remain within RoHS compliant version. Description The series is specially designed
More information1224SUBC/C470/S400-A4
Features Choice of various viewing angles Available on tape and reel. Reliable and robust The product itself will remain within RoHS compliant version. Compliance with EU REACH Compliance Halogen Free.(Br
More informationEuropean Technical Standard Order (ETSO)
Date: 28/11/2008 European Aviation Safety Agency European Technical Standard Order (ETSO) Subject: CREWMEMBER OXYGEN MASK 1 - Applicability This ETSO gives the requirements which the crewmember constant
More informationPegasus Series Amphenol Pcd
Pegasus Series Amphenol Pcd Amphenol Pcd is one of the world s leading suppliers of interconnect products for Military, Commercial Aerospace and Industrial applications. Located north of Boston in Beverly,
More informationAir Sensor. SAC Ex. Manual ATEX. AQ Elteknik AB
Air Sensor SAC Ex Manual AQ Elteknik AB ATEX Air Sensor SAC Ex ATEX Certified model Manual version 2.1 April 2014 AQ Elteknik AB 2 Table of contents 1. Manufacturer information... 4 Manufacture Declaration
More informationPegasus Additional buoyancy for offshore helicopters
EASA Briefing Paper Document Number R0 EASA Project Number 0010046421 ATL Certification Programme CP-13195-00001 Pegasus Additional buoyancy for offshore helicopters IP & Design Rights One Atmosphere Pty
More informationSDX Submersible Depth Transmitter User Manual
SDX Submersible Depth Transmitter User Manual July 2017 USER INFORMATION Stevens makes no warranty as to the information furnished in these instructions and the reader assumes all risk in the use thereof.
More informationPERFORMANCE SPECIFICATION SHEET MICROPHONE ASSEMBLY, M-169A/AIC
PERFORMANCE SPECIFICATION SHEET INCH-POUND MIL-PRF-26542/12C 12 September 2012 SUPERSEDING MIL-PRF-26542/12B 11 February 1999 MICROPHONE ASSEMBLY, M-169A/AIC This specification sheet is approved for use
More informationTechnical Data Sheet MF010-O-LC
Technical Data Sheet MF010-O-LC - 1 - 1. Properties The oxygen measuring system MF010-O-LC determines the oxygen content in gas mixtures up to a temperature of 250 C. It is particularly suitable for the
More informationLAMP SUGC/S400-A5
Features Choice of various viewing angles Available on tape and reel. Reliable and robust Pb free The product itself will remain within RoHS compliant version. Compliance with EU REACH Compliance Halogen
More informationSDX Submersible Depth Transmitter User Manual
SDX Submersible Depth Transmitter User Manual October 2007 USER INFORMATION Stevens makes no warranty as to the information furnished in these instructions and the reader assumes all risk in the use thereof.
More information333-2SURC/H3/S530-A4 LAMP. Features. Description. Applications. 1 Ver.:2 Release Date:12/13/2016 狀態 :Approved( 正式發行 )
Features Choice of various viewing angles Available on tape and reel. Reliable and robust Pb free The product itself will remain within RoHS compliant version. Description The series is specially designed
More informationDBI version 002 User Manual US version Free Balloon Flight Instrument
DBI version 002 User Manual US version Free Balloon Flight Instrument DBI 002 User Manual issue C7, 2005-05-25 Page 1/29 Safety The manufacturer has designed this instrument to be safe when operated. Do
More informationSR22 Airplane Flight Manual (AFM) Temporary Change
Cirrus Design TPOH AFM Temporary Change Airplane Flight Manual (AFM) Temporary Change Information in this Temporary Change adds to, supersedes, or deletes information in the basic Pilot s Operating Handbook.
More informationCP10 Sensor Installation and Maintenance Instructions
4030150/9 IM-P403-26 EMM Issue 9 CP10 Sensor Installation and Maintenance Instructions 1. Safety information 2. General product information 3. Installation 4. Maintenance 5. Spare parts Copyright 2017
More informationNext Generation Quartz Pressure Gauges
Next Generation Quartz Pressure Gauges Rick Puccio, Ph.D. Senior Scientist Quartzdyne Houston, TX March 2, 2016 Outline Quartz Pressure Gauge Introduction Gauge Size Reduction Long Term Pressure Drift
More informationEquipment Accuracy / Selection
Revision 5.0: Included the PPP program for clarification. Revision 6.0: Update references for CTL PDSH 251B to CTL DSH 251E" Added leakage current tolerances for values above 5KHz For Client Labs Purpose
More informationMIL-STD-883G METHOD
STEADY-STATE LIFE 1. PURPOSE. The steady-state life test is performed for the purpose of demonstrating the quality or reliability of devices subjected to the specified conditions over an extended time
More informationFUEL TANK SAFETY / EWIS CONTINUATION TRAINING
FUEL TANK SAFETY / EWIS CONTINUATION TRAINING Q1 & Q2 2016 Page 1 of 11 CONTENTS: 1 INTRODUCTION 2 Fuel Tank Safety 3 EWIS Page 2 of 11 1. Introduction The purpose of this module is to highlight industry
More informationEALP05RDBRA0 LAMP. Features. Description. Applications. Choice of various viewing angles. Available on tape and reel. Reliable and robust
Features Choice of various viewing angles Available on tape and reel. Reliable and robust The product itself will remain within RoHS compliant version. Compliance with EU REACH Compliance Halogen free.
More informationCIRRUS AMM TEMPORARY REVISION
CIRRUS AMM TEMPORARY REVISION SR20 AMM Temporary Revision 04-00-04 Airworthiness Limitations Affected Manuals: SR20 Airplane Maintenance Manual (12137-002) Serial Numbers: SR20 Serials 2220, 2339 & subs
More informationPolicy for Evaluation of Certification Maintenance Requirements
Circular No. 1-319 Policy for Evaluation of Certification Maintenance Requirements April 11, 2013 First Issue Airworthiness Division, Aviation Safety and Security Department Japan Civil Aviation Bureau
More informationXSL-360-5E. UV LED 5 mm TECHNICAL DATA. Absolute Maximum Ratings (T a =25 C) Specifications (If=20mA, T a =25 C) Drawing
XSL-360-5E TECHNICAL DATA UV LED 5 mm Drawing Absolute Maximum Ratings (T a =25 C) Item Symbol Value Unit DC Forward Current I F 25 ma Peak Pulse Forward Current * 1 I FP 100 ma Power Dissipation P D 100
More informationPC-21 A Damage Tolerant Aircraft. Paper presented at the ICAF 2009 Symposium by Lukas Schmid
PC-21 A Damage Tolerant Aircraft Paper presented at the ICAF 2009 Symposium by Lukas Schmid PC-21 A Damage Tolerant Aircraft 12.05.2009 2 Acknowledgment Markus Gottier, Gottier Engineering Dave Boorman,
More informationSafety Powder Spray Systems
Instruction Sheet P/N 107 952C Safety Powder Spray Systems 1. Introduction This section contains general safety instructions for using your Nordson equipment. Task- and equipment-specific warnings are
More informationProgrammable pressure and temperature transmitters PTM/RS485
Programmable pressure and temperature transmitters PTM/RS485 Version: 03-28-2012 Technical Specifications Pressure measuring range (bar) 0.1... 0.5 > 0.5 2 > 2 25 Overpressure 3 bar 3 x FS ( 3 bar) 3 x
More informationGuide for Evaluating Your Hose Assembly Supplier
Guide for Evaluating Your Hose Assembly Supplier Supplier Evaluation Checklist, and How to Clearly Define Application Requirements Safe, reliable hose assemblies require appropriate specification work
More informationLAMP 336SURSYGWS530-A3
Features Two chips are matched for uniform light output, wide viewing angle Long life-solid state reliability I.C. compatible/low power consumption The product itself will remain within RoHS compliant
More informationSECTION 6-16 FLIGHT INSTRUMENTS
SECTION 6-16 SYSTEMS DESCRIPTION Index Page Pitot-Static System... 6-16-2 Airspeed Indicator... 6-16-4 Vertical Speed Indicator... 6-16-4 Instantaneous Vertical Speed Indicator IVSI (Optional)... 6-16-5
More informationE2K-L. Liquid Level Sensor That Is Unaffected by the Color of the Pipe or Liquid. Liquid Level Sensor. Ordering Information
Liquid Level EK-L CSM_EK-L_DS_E 3 Liquid Level That Is Unaffected by the Color of the or Liquid Mount to bypass pipes. Fit a wide range of pipe diameters: 8 to mm or to mm Built-in Amplifiers to save space.
More informationLevel MEASUREMENT 1/2016
Level MEASUREMENT 1/2016 AGENDA 2 A. Introduction B. Float method C. Displacer method D. Hydrostatic pressure method E. Capacitance method G. Ultrasonic method H. Radar method I. Laser method J. Level
More information1 General. 1.1 Introduction
1 General 1.1 Introduction The contents of this book will focus on the anatomy of the aeroplane and the various systems that enable it to operate both on the ground and in the air. Flight controls Landing
More informationTR Electronic Pressure Regulator. User s Manual
TR Electronic Pressure Regulator Page 2 of 13 Table of Contents Warnings, Cautions & Notices... 3 Factory Default Setting... 4 Quick Start Procedure... 5 Configuration Tab... 8 Setup Tab... 9 Internal
More informationPre-filter for Brushless Blower Instruction Manual
Pre-filter for Brushless Blower 781-70-702 Instruction Manual Minebea Co., Ltd. Industrial Machinery Business Unit 251-8531 1-1-1 Katase,Fujisawa,kanagawa Contact Us Industrial Machinery Product Sales
More informationCONTACT INFORMATION. Wayne St. Germain Transportation Specialist U.S. Department of Transportation PHMSA Inspector Training and Qualifications
ODORIZATION ISSUES CONTACT INFORMATION Wayne St. Germain Transportation Specialist U.S. Department of Transportation PHMSA Inspector Training and Qualifications Email: wayne.stgermain@dot.gov GAS REPORTS
More informationLecture 4: Spaceflight Environment
Space Environment and Effects Previous Lecture Next Lecture Home Classes Contact Lecture 4: Spaceflight Environment 1. Gravity (see Lecture 3): Microgravity, Microgravity Simulation Launch / Landing Acceleration
More informationCertification Specifications for Normal-Category Aeroplanes CS-23
European Aviation Safety Agency Certification Specifications for Normal-Category Aeroplanes CS-23 29 March 2017 1 1 For the date of entry into force of this Amendment, please refer to Decision 2017/013/R
More informationATM.ECO - Analog Pressure Transmitter
Pressure Transmitter ATM.ECO - Analog Pressure Transmitter CUSTOMER BENEFITS Entry level series into precision pressure measurement High measurement accuracy is ensured by sophisticated digital temperature
More informationProgrammable Submersible Level Transmitters
Programmable Submersible Level Transmitters PTM/N/RS485 CUSTOMER BENEFITS High flexibility due to scalalbe pressure range Digital (RS485) and analogue (4-20mA) output signal in one sensor Available as
More informationSAFETY INFORMATION NOTICE
SAFETY INFORMATION NOTICE SUBJECT: GENERAL External load operations For the attention of AIRCRAFT CONCERNED EC120 Civil B Version(s) AS350 B, BA, BB, B1, B2, B3, D L1 AS550 AS355 AS555 EC130 E, F, F1,
More informationI/P Transducer Positioner Module
I/P Transducer Positioner Module VRC P/N: 7958032 Installation, Operation and Maintenance Instructions 2.09 [53.1] 1.30 [32.9] 2.97 [75.5] 0.78 [19.8] 0.18 [4.4] 1.42 [36.1] n.18 MOUNTING HOLES (2) PLACES
More informationProgrammable pressure and temperature transmitters PTM/RS485
Programmable pressure and temperature transmitters PTM/RS485 Version: 26.06.2014 Technical Specifications Pressure measuring range (bar) 0.1... 0.5 > 0.5 2 > 2 25 Overpressure 3 bar 3 x FS ( 3 bar) 3 x
More information973-SF 6 Analyzer. Precise and Stable SF 6 Gas Analyzer REFLECTING YOUR STANDARDS
Precise and Stable SF 6 Gas Analyzer Simultaneous measurement of humidity, SF 6 purity and SO 2 concentration Integrated gas recovery system with automatic pump back Fully automated SF 6 gas testing Fundamental
More information2 ETSO-C115c#9 Airborne Area Navigation Equipment Flight Management Systems (FMS) Using Multi-Sensor Inputs
Deviation Request ETSO-C115c#8 for an ETSO approval for CS-ETSO applicable to Airborne Area Navigation Equipment Flight Management Systems (FMS) Using Multi-Sensor Inputs (ETSO-C115c) Consultation Paper
More informationP/N 135A EASA Approved: June 23, 2011 Section 9 Initial Release Page 1 of 22
EASA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR S-TEC SYSTEM 30 AUTOPILOT INTEGRATED IN THE LIBERTY XL2 SERIES AIRCRAFT Serial No: Registration No: When installing the S-TEC System 30 Autopilot Integrated
More informationPRODUCT SPECIFICATION. SFP+ Cage and Cage Assembly 1 of 8 A
SFP+ Cage and Cage Assembly 1 of 8 A 1.0 Objective This specification defines the performance, test, quality and reliability requirements of the _Small Form-factor Pluggage (SFP+) product. 2.0 Scope This
More informationEMERGENCY EQUIPMENT Table of Contents CHAPTER 8 - EMERGENCY EQUIPMENT
Table of Contents 08 00 1 CHAPTER 8 - EMERGENCY EQUIPMENT TABLE OF CONTENTS Page TABLE OF CONTENTS DESCRIPTION General Oxygen System Components and Operation Controls and Indicators Crew Oxygen Consumption
More informationThis test shall be carried out on all vehicles equipped with open type traction batteries.
5.4. Determination of hydrogen emissions page 1 RESS-6-15 5.4.1. This test shall be carried out on all vehicles equipped with open type traction batteries. 5.4.2. The test shall be conducted following
More informationATM.1ST. Pressure transmitters CUSTOMER BENEFITS
Pressure transmitters ATM.1ST CUSTOMER BENEFITS High precision pressure sensor over the whole temperature range Electronic compensation Modular sensor structure (any process and electrical connections
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency EASA TYPE-CERTIFICATE DATA SHEET Number : E.122 Issue : 04 Date : 14 May 2014 Type : BRP Powertrain GmbH & Co KG Models Rotax 914 F2 Rotax 914 F3 Rotax 914 F4 List of effective
More informationControlling Cabin and Envelope Air Flows & Pressure Differentials
Controlling Cabin and Envelope Air Flows & Pressure Differentials To control envelope moisture and related problems Douglas S. Walkinshaw and Keith F. Preston ECHO Air Inc www.indoorair.ca 1 This paper
More informationAdvisory Circular. Runway Guard Light Installation Criteria. Aviation Safety Regulatory Framework Document No.: AC A P/A Issue No.
Advisory Circular Subject: Runway Guard Light Installation Criteria Issuing Office: PAA Sub Activity Area: Classification File No.: Standards Aviation Safety Regulatory Framework Document No.: AC 302-005
More informationAIR CONDITIONING AND PRESSURIZATION CONTROLS AND INDICATORS
AIR CONDITIONING AND PRESSURIZATION CONTROLS AND INDICATORS Air conditioning control panel 1 MIN MAX Page 1 Air conditioning control panel 2 MIN MAX Page 2 Air conditioning control panel 3 MIN MAX Page
More informationFULL SERVICE TESTING Environmental Functional Developmental
FULL SERVICE TESTING Environmental Functional Developmental AERO NAV RELIABILITY THROUGH TESTING MILITARY COMMERCIAL AUTOMOTIVE TRANSPORTATION MARINE AEROSPACE MEDICAL ENVIRONMENTAL/FUNCTIONAL/DEVELOPMENTAL
More informationED Decision 2013/012/R 12/07/2013 Annex II SUBPART A GENERAL 1. APPLICABILITY
SUBPART A GENERAL 1. APPLICABILITY 1.1 Requirements for the issue of European Technical Standard Order (ETSO) authorisations are found in Part-21, Section A, Subpart O. 1.2. Marking requirements for the
More informationA review of best practices for Selection, Installation, Operation and Maintenance of Gas meters for Flare Applications used for Managing facility
A review of best practices for Selection, Installation, Operation and Maintenance of Gas meters for Flare Applications used for Managing facility mass balance and compliance 1. What, When and Why? 2. Flare
More informationE8AA. Pressure Sensor of Stainless Steel Construction Is Ideal for a Wide Range of Applications. Pressure Sensor (Stainless Steel Diaphragm)
Pressure Sensor (Stainless Steel Diaphragm) CSM DS_E_3_1 Pressure Sensor of Stainless Steel Construction Is Ideal for a Wide Range of Applications Incorporates double diaphragms consisting of SUS316L stainless
More information5mm Infrared LED HIR7373B/L289
5mm Infrared LED Features High reliability High radiant intensity Peak wavelength λp=850nm 2.54mm Lead spacing Low forward voltage Pb Free This product itself will remain within RoHS compliant version.
More informationHASTAC High stability Altimeter SysTem for Air data Computers
HASTAC High stability Altimeter SysTem for Air data Computers André Larsen R&D Director Memscap Sensor Solution SIXTH FRAMEWORK PROGRAMME PRIORITY 4 Aeronautics and Space EC contract no. AST4-CT-2005-012334
More informationWeighing your Seabee
Weighing your Seabee Note: The following procedure must be supervised and signed off by a qualified A&P and the final paperwork must be included in the Aircraft Records. The actual weights must be included
More informationPOTENTIAL HEALTH & SAFETY HAZARDS
Number: OH&S 18.09.1 Revision Date: 2011.06 Confined Space 1. PURPOSE 2. SCOPE 1.1. To properly designate Confined Spaces (CS) at Thompson Rivers University (TRU), to provide guidance to ensure the safety
More informationTest Report #: Date: June 21, 2005
CERTIFICATE #2316.01 Test Report #: 1979-2 Date: June 21, 2005 Issued To: Bill Burks American Power Conversion 85 Rangeway Road North Billerica, MA 01862 USA 978-670-2440 Product Name/Description Uninterruptable
More informationFEATURES AND BENEFITS. Meets UL/EN/IEC , 4Th ed. For EMC*
LPS Medical FEATURES AND BENEFITS Meets UL/EN/IEC60601-1-2, 4Th ed. For EMC* Approved To EN/IEC/UL60601-1, 3rd edition With Isolation Levels Which Satisfy The 2 MOPP Requirements Meets DoE Efficiency Level
More informationHelicopter Safety Recommendation Summary for Small Operators
Helicopter Safety Recommendation Summary for Small Operators Prepared by the International Helicopter Safety Team September 2009 Introduction This document is intended to provide a summary of the initial
More informationKey Features & Advantages of JEHA MK IV (5,000 PSI Hydraulic Test Stands)
Key Features & Advantages of JEHA MK IV (5,000 PSI Hydraulic Test Stands) The key reasons why MRO Facility now requires 5,000 PSI Hydraulic Test Stand are as follows: 1) New generation commercial aircraft
More informationWS AC/ACJ for the Subpart H. Modified in Montreal Meeting #5 3/18-22/02
AC/ACJ for the Subpart H WS 41-01 Modified in Montreal Meeting #5 3/18-22/02 25HAC1701 EWIS Definition For now the group agrees that we do not need advisory material for the EWIS definition. 25.1715 (25HAC611)
More informationOPERATOR S MANUAL Ar-Gone Weld Gas Analyzer
July 2011 OPERATOR S MANUAL Ar-Gone Weld Gas Analyzer WARNING! Before operating this product, read and understand this Operator s Manual. Become familiar with the potential hazards of this unit. Contact
More informationDownloaded from Date: April 19, 2007 Initiated by: ACE-100
U.S. Department of Transportation Federal Aviation Administration Advisory Circular Subject: CERTIFICATION OF PART 23 AIRPLANES FOR FLIGHT IN ICING CONDITIONS Date: April 19, 2007 Initiated by: ACE-100
More informationSUBPART C - STRUCTURE
SUBPART C - STRUCTURE GENERAL CS 23.301 Loads (a) Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by
More informationFurther technical information is available on
1 of 5 Manufacture address : Bartec Technor AS Dusavikveien 39 4007 Stavanger Norway Further technical information is available on www.bartec-technor.no Note on instructions When working in hazardous areas,
More informationARNG WARRIOR TRAINING CENTER PATHFINDER COURSE FORT BENNING, GEORGIA 31905
ARNG WARRIOR TRAINING CENTER PATHFINDER COURSE FORT BENNING, GEORGIA 31905 071A0204 05 February 2014 HLZ SUMMARY SHEET: INSTRUCTIONAL INTENT: To enable the Pathfinder student to plan for and operate day
More informationTechnical Standard Order
Department of Transportation Federal Aviation Administration Aircraft Certification Service Washington, DC TSO-C75 Date: 9/4/63 Technical Standard Order Subject: TSO-C75, HYDRAULIC HOSE ASSEMBLIES Technical
More informationPARAVION TECHNOLOGY, INC AIRWAY AVENUE FT. COLLINS, COLORADO 80524
PARAVION TECHNOLOGY, INC. 2001 AIRWAY AVENUE FT. COLLINS, COLORADO 80524 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 407LS-100 INSTALLATION BELL 407 HELICOPTERS Cover THIS PAGE INTENTIONALLY LEFT BLANK Page
More informationPRODUCT SPECIFICATION
MINI-FIT SR. SERIES 1.0 SCOPE This specification covers the 10.00 mm / (.394 in.) centerline tin and gold plated connector series, single and dual row versions in wire to wire and wire to printed circuit
More informationCustomer Responsibilities. Important Customer Information. Cary 4000/5000/6000i UV-Vis spectrophotometer Site Preparation Checklist
Thank you for purchasing an Agilent instrument. To get you started and to assure a successful and timely installation, please refer to this specification or set of requirements. Correct site preparation
More informationAquavar SOLO 2 Frequently Asked Questions
Aquavar SOLO 2 Frequently Asked Questions How do I size the Aquavar SOLO 2 for the appropriate pump/motor combination? Can I use a 208 Volt motor? Can I run the Aquavar SOLO 2 up to 80HZ? What are the
More informationLAMP 339-9SUGSURSUBC/S1174
Features High efficiency. Selected minimum intensities. Available on tape and reel. The product itself will remain within RoHS compliant version Compliance with EU REACH Compliance Halogen free. (Br
More informationProposed Special Condition for the OEI High Ambient Take-Off Temperature rating
Proposed Special Condition for the OEI High Ambient Take-Off Temperature rating Applicable to Turbofan Engine for the approval of an additional rating. This rating, ensuring availability of increased engine
More informationGuidance on Mounting Cameras on Sailplanes and Powered Sailplanes, AIRW-D024 INTRODUCTION SCOPE
INTRODUCTION For a number of years pilots have fitted small cameras to sailplanes in Australia as evident by the many You Tube videos. These cameras have been installed by the pilots with no guidance or
More informationBT6HC Hygienic Sanitary Balanced Pressure Steam Trap for High Capacity and CIP/SIP Applications
1800350/6 IM-P180-12 ST Issue 6 BT6HC Hygienic Sanitary Balanced Pressure Steam Trap for High Capacity and CIP/SIP Applications Installation and Maintenance Instructions 1. Safety information 2. General
More informationSupplementary Operator s Manual 42/24-14 EN Rev. 3
Advance Optima Continuous Gas Analyzers AO2000 Series with Uras26, Magnos206, Caldos25, Caldos27 Designed per Category 3G for Measurement of Flammable Gases ( Safety Concept ) and Non-flammable Gases Supplementary
More informationTemperature gauge Installation Guide
Temperature gauge Installation Guide improper functioning, or damage. Additional information can be found at: CAUTION: Read this installation guide carefully before unpacking the temperature gauge. Improper
More informationPegasus Series Amphenol Pcd
is one of the world s leading suppliers of interconnect products for Military, Commercial Aerospace and Industrial applications. Located north of Boston in Beverly, Massachusetts, the company designs and
More informationFLIGHT TEST RISK ASSESSMENT THREE FLAGS METHOD
FLIGHT TEST RISK ASSESSMENT THREE FLAGS METHOD Author: Maximilian Kleinubing BS. Field: Aeronautical Engineering, Flight Test Operations Keywords: Flight Test, Safety Assessment, Flight Test Safety Assessment
More informationPressure transmitters EMP 2
Data sheet Pressure transmitters EMP 2 The high accuracy pressure transmitter EMP 2 is designed for monitoring and control in marine and industial applications and offers a reliable pressure measurement,
More informationTYPE-CERTIFICATE DATA SHEET
TYPE-CERTIFICATE DATA SHEET No. E.209 for Rotax 535 series engines Type Certificate Holder BRP-Rotax GmbH & Co. KG Rotaxstrasse 1 A-4623 Gunskirchen Austria For Models: Rotax 535 A Rotax 535 B Rotax 535
More informationInformation Sheet. About this information sheet. Floor and wall loadings. Attachment of process module to floor. PlasmaPro Estrelas100
Information Sheet PlasmaPro Estrelas100 About this information sheet This data sheet provides basic information about the installation of a PlasmaPro Estrelas100 tool. Some of the information in this sheet
More information