DO-160 Capabilities
These tests determine the performance characteristics of equipment when exposed to
the temperatures, altitudes, and pressures that will be experienced during storage
and operation.
The tests in this section are "susceptibility" tests, meaning the units being tested
are the "victims" of the environment.
Our facilities have full DO-160G capabilities for categories A, B, C, D, E, and F.
Our facilities include:
- A Tenny 27 cu.ft Temp/Humidity/Altitude chamber and a 3'X3'x3.5' high altitude
- Explosive decompression chamber.
Determine performance characteristics of the equipment during temperature variations between high and low operating temperature extremes.
Not intended to address wet or icing conditions, or condensation (humidity control to prevent condensation in the test chamber is allowed)
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capabilities for categories A,B,C, S1, and S2.
Our facilities include:
-
Tenny 27 cu.ft Temp/Humidity/Altitude chamber
-
Tenny 16 cu.ft Temp/Humidity chamber
-
Thermotron 37 cu.ft Temp/Humidity chamber
-
2 Cincinnati Sub Zero 8 cu.ft Temp/Humidity chambers
-
2 Russels 8 cu.ft Temp chambers
-
Large 12鈥橶x10鈥橦x48鈥橪 (-40F to +150F) Temp chamber
This test determines the ability of the equipment to withstand either natural or induced humid atmospheres.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capabilities for categories A, B, and C.
Our facilities include:
-
Tenny 27 cu.ft Temp/Humidity/Altitude chamber
-
Tenny 16 cu.ft Temp/Humidity chamber
-
Thermotron 37 cu.ft Temp/Humidity chamber
-
2 Cincinnati Sub Zero 8 cu.ft Temp/Humidity chambers
This test verifies that the equipment will continue to function after exposure to
shocks experienced during normal aircraft operations. These shocks may occur during
taxiing, landing, and when the aircraft encounters sudden gusts in flight.
This test applies to all equipment installed on fixed-wing aircraft and helicopters.
Verify that certain equipment will not detach from its mountings or separate in a
manner that presents a hazard during an emergency landing.
This test applies to equipment installed in compartments and other areas of the aircraft
where equipment detached during emergency landing could present a hazard to occupants,
fuel systems or emergency evacuation equipment.
These tests do not satisfy CFR requirements for all equipment, e.g. seats and seat
restraints, or safety/egress related equipment that must remain functional after crash
loads.
Demonstrate that the equipment operates properly during and after being subjected
to vibration levels for the specified installation.
These tests are applicable to equipment installed on:
- Fixed-wing propeller aircraft
- Fixed-wing turbojet aircraft
- Fixed-wing turbofan aircraft
- Fixed-wing prop fan aircraft
- Helicopters
Our facilities include:
- Data Physics 12,000 lbf 3-axis - 24"x24" vibration table
- Sustained G Rate Table to 50 lbs
- Shaker Model: V5344/DSA4-48k
- 12,000 Maximum Sine force and Random Force pounds and 25,440 Maximum Shock force
- Max Rate: 1000 deg/sec
- Max Acceleration: 200 deg/sec
To determine if the Equipment Under Test (EUT) will be an ignition source if installed
in an area with explosive vapors.
This information can be used in conjunction with single and double fault analysis
to assist in certification.
To some degree, the tests in this section are "emissions" tests, meaning the units
being tested are the "sources" of the environment.
Our facilities have full DO-160G capability for categories A, E, and H.
These tests determine whether the equipment can withstand the effects of liquid water being sprayed, falling onto, or the effects of condensation.
These tests are not intended to verify performance of hermetically sealed equipment. Therefore, hermetically sealed equipment may be considered to have met all waterproofness requirements without further testing. Equipment shall be considered hermetically sealed when the seal is permanent and airtight.
Our facilities have full DO-160G capability.
These tests determine whether the materials used in the construction of the equipment can withstand the deleterious effects of fluid contaminants.
Fluids susceptibility tests should only be performed when the equipment will be installed in areas where fluid contamination could be commonly encountered.
Many parts of the aircraft can be exposed to fluids, such as cleaning fluids, insecticides, fuels, deicing fluids, soft drinks, etc.
In many cases, the tests in this section apply more to the material than to the functioning unit. In these cases, a material test alone may suffice.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capability.
Fluids dependent on EUT requirements can be ordered as needed.
This test determines the resistance of the equipment to the effects of blowing sand and dust where carried by air movement at moderate speeds.
The main adverse effects to be anticipated are penetration into cracks, crevices, bearings and joints, causing fouling and/or clogging of moving parts, relays, filters, etc.; formation of electrically conductive bridges; action as nucleus for the collection of water vapor, including secondary effects of possible corrosion; and pollution of fluids.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities are available to coordinate with other sources to provide complete testing services.
These tests determine whether equipment material is adversely affected by fungi under conditions favorable for their development, namely, high humidity, warm atmosphere, and presence of inorganic salts.
In many cases, the tests in this section apply more to the material than to the functioning unit. In these cases, a material test alone may suffice.
Analysis to show that the material does not have any nutrients to support fungal growth may also be a viable alternative to testing.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities are available to coordinate with other sources to provide complete testing services.
This test determines the effects on the equipment of prolonged exposure to a salt atmosphere or to salt fog experienced in normal operations. The main adverse effects to be anticipated are corrosion of metals; clogging or binding of moving parts as a result of salt deposits; insulation fault; damage to contacts and uncoated wiring.
Our facilities have full DO-160G capability for categories S and T.
Our facilities include:
- 2 Auto Technology 15 cu.ft. Salt Fog Chambers
- Singleton 30 cu.ft. Salt Fog Chamber
This test determines the magnetic effect of the equipment and is mainly intended for finding or proving the closest distance to compasses or compass sensors at which that unit is allowed to be installed. This test ensures that equipment can operate properly without interference which may affect the nearby equipment, determining equipment compliance with the applicable equipment preface standard, or assisting the installer in choosing the proper location of the equipment in the aircraft.
The tests in this section are 鈥渆missions鈥� tests, meaning the units being tested are the 鈥渟ources鈥� of the environment.
Our facilities have full DO-160G capability for categories Y, Z, A, B, and C.
The tests in this section determine if the Equipment Under Test will operate properly with the fluctuations and noise seen on a typical electrical power bus in a aircraft, and determines if the equipment is adversely affecting the electrical power system. The power bus types included are 14 VDC, 28 VDC, 270 VDC, and 115 Vrms AC and 230 Vrms AC, at 400 HZ or variable frequency
Some of the tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment. Other tests in this section are 鈥渆missions鈥� tests, meaning the units being tested are the 鈥渟ources鈥� of the environment.
This section does not test the electrical power system on the aircraft. It is advisable that you do know what the performance of your aircraft electrical power system is.
Our facilities have full DO-160G capability for categories A, B, and Z.
Our facilities include:
- California Instruments AC/DC Programmable Power Supply (3 phase, 45kW)
- Elgar SW5250 AC/DC Programmable Power Supply (1 phase, 45 Amps)
- Techron Amplifiers - 3 Amplifiers - DC 鈥� 50kHz, 100 Amp Peak Power
This test determines whether the equipment can withstand the effects of voltage spikes arriving at the equipment on its power leads, either ac or dc.
Our facilities have full DO-160G capability for categories A and B.
This test determines whether the equipment will accept frequency components of a magnitude normally expected when the equipment is installed in the aircraft. These frequency components are normally harmonically related to the power source fundamental frequency.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capability for categories B, Z, and K.
Our facilities include three 50 kHz DC, 100Amp Peak Power Techron Amplifiers
This test determines whether the equipment interconnect circuit configuration will accept a level of induced voltages caused by the installation environment. This section relates specifically to interfering signals related to the power frequency and its harmonics, audio frequency signals, and electrical transients that are generated by other on board equipment or systems and coupled to sensitive circuits within the EUT through its interconnecting wiring. Power leads tested under section 18 are exempt from this test.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capability for categories C, Z, A, and B
Our facilities include three 50 kHz DC, 100Amp Peak Power Techron Amplifiers
These tests determine whether equipment will operate within performance specifications when the equipment and its interconnecting wiring are exposed to a level of RF modulated power, either by a radiated RF field or by injection probe induction onto power lines and interface circuit wiring.
Two test procedures are used: 1) From 10 kHz to 400 MHz, the equipment under test (EUT) is subjected to RF signals coupled by means of injection probes into its cable bundles, and 2) for frequencies between 100MHz and the upper frequency limit, the EUT is subjected to radiated RF fields. There is an intentional overlap of the tests from 100 to 400 MHz.
Equipment with special signal, frequency, modulation, or bandpass characteristics may require test variations as specified by the applicable performance standards.
The result of these tests can be used to determine equipment response to various RF threats such as HIRF, T-PEDs, and installed system's emissions, and to permit categories to be assigned defining the conducted and radiated RF test levels of the equipment.
These tests are sufficient to obtain environmental qualification for radio frequency susceptibility of the equipment. Additional tests may be necessary to certify the installation of systems in an aircraft dependent on the functions performed.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capability for both conducted (for categories M, O, R, S, T, W, and Y) and radiated (for categories B, D, F, G, R, S, T, W, and Y) susceptibility tests.
Our facilities include:
- 17鈥� x 20鈥� x 12鈥� Semi-Anechoic Chamber
- 20鈥� x 17鈥� x 11鈥� Reverb (mode-stir) Chamber
- 25鈥� x 20鈥� x 15鈥� Reverb (mode-stir) Chamber
- 6鈥� x 8鈥� x 6鈥� Reverb (mode-stir) Chamber (For High field strength testing)
- 30鈥� x 50鈥� x 25鈥橦 Anechoic Chamber
These tests determine that the equipment does not emit undesired RF noise in excess
of the levels specified in DO-160G, Section 21. The notches specified in the radiated
emissions limits are included to protect aircraft RF sensors operating frequencies.
Both Conducted and Radiated Emissions are measured.
The tests in this section are "emissions" tests, meaning the units being tested are
the "sources" of the environment. Subjecting EUT to this test helps control the electromagnetic
environment on the aircraft.
This section does not measure or control spurious signals conducted out of the antenna
terminals of receivers or transmitters. That control should be specified in the equipment
performance standard for that receiver or transmitter.
Our facilities have full DO-160G capabilities for categories B, L, M, H, P, and Q.
Our facilities include:
- 17' x 20' x 12' Semi-Anechoic Chamber
- 20' x 17' x 11' Reverb (mode-stir) Chamber
- 25' x 20' x 15' Reverb (mode-stir) Chamber
- 6' x 8' x 6' Reverb (mode-stir) Chamber (For High field strength testing)
- 30' x 50' x 25'H Anechoic Chamber
These test methods and procedures are provided to verify the capability of equipment to withstand a selection of test transients defined in this section which are intended to represent the induced effects of lightning.
The waveforms and levels, and the pass/fail criteria for equipment performance during the test shall be listed in the applicable equipment specification.
Two groups of tests may be used for equipment qualification.
A damage assessment test performed using pin injection
Evaluate the functional upset tolerance of equipment when transients are applied to interconnecting cable bundles.
Cable bundle tests include:
- Multiple stroke
- Multiple burst
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities are capable of all pin injection and all cable bundle test waveforms up to level 5 (EUT specific at level 5)
Our facilities include:
- Component Indirect Effects Lightning; Wave Forms 1-5A, Voltages and Currents to Level 5 (setup dependent)
- Full Aircraft Lightning Transient Analysis (LTA) testing (SAE ARP-5416 Section 6.1), Component A and Component H
To determine the ability of externally mounted equipment to withstand the direct effects of a lightning strike.
The term "externally mounted equipment" refers to all equipment mounted externally to the main skin of the aircraft. Also included are all such equipment that is covered only by a dielectric skin or fairing that is an integral part of the equipment. It also includes connecting cables and associated terminal equipment furnished by the equipment manufacturer as a part of the equipment.
The tests described herein specifically exclude the effects on the tested equipment
of voltages and currents induced into the externally mounted equipment and its associated
circuitry by means of magnetic or electric field coupling. These indirect effects
are covered in Section 22.
Types of test included are:
- High Voltage (attachment) test
- Shows where an attachment may occur
- Also shows if a dielectric puncture may occur
- Does not indicate the level of damage expected
- High current tests
- Physical damage
- Fuel ignition
- Sparking at joints
- Arcing or conduction to electrical conductors
- Adequacy of protection
Our facilities are available to coordinate with other sources to provide complete testing services.
These tests determine performance characteristics for equipment that must operate when exposed to icing conditions that would be encountered under conditions of rapid changes in temperature, altitude, and humidity.
This section does not cover ice accumulations on external surfaces, or flight into 鈥渋cing conditions鈥�.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160G capabilities for categories A and C
Our facilities include:
- Tenny 27 cu.ft Temp/Humidity/Altitude
- Tenny 16 cu.ft Temp/Humidity
- Thermotron 37 cu.ft Temp/Humidity
- Large 12鈥橶x10鈥橦x48鈥橪 (-40F to +150F) Temp chamber
The electrostatic discharge test is designed to determine the immunity or the ability of equipment to perform its intended function without permanent degradation of performance as a result of an air discharged electrostatic pulse.
The tests in this section are 鈥渟usceptibility鈥� tests, meaning the units being tested are the 鈥渧ictims鈥� of the environment.
Our facilities have full DO-160 Capabilities
Fixture Capabilities
- Fits 24"x24"x1/4" test panels
- 4Gs of acceleration
- +6 PSI positive pressure differential
- 0 to 1200 feet per minute back side airflow with positive pressure differential
- 0 to -5.5 PSI negative pressure differential
- 0 to 100 feet per minute back side airflow with negative pressure differential
- Alternate non pressure fixture available, along with custom fixture design if necessary
Burner Capabilities
- Jet-A fuel
- 2000鈩�
- 4500 BTU/hr
- Methane Bunsen Burner for Interior Burn testing
Testing Capabilities
- FAA Interior Burn per FAR 23.851/25.853
- Firewall/Cowl/Pylon Burn Testing per FAR 23/25 standards
- Developmental Testing (fire proof and fire resistant)
- Certification Testing (fire proof and fire resistant)