RTCA/DO-160 Section 16 (Power Input) and Section 17 (Voltage Spike) testing verify that avionics equipment operates correctly across the full range of power conditions an aircraft electrical system can present. Aircraft power systems operate at frequencies and waveform characteristics specific to aviation, which puts genuinely different demands on the test power source than commercial grid simulation. (See RTCA/DO-160 explained for background.)
Why Aircraft Power Differs From Commercial Grid Power
Aircraft electrical systems commonly operate at 400Hz, and modern aircraft increasingly use variable-frequency power systems. A grid simulator built primarily for commercial-frequency testing may not reach the frequency range DO-160 Section 16 testing requires. The CORTEX AC high-frequency variant addresses this, supporting output bandwidth to 5kHz.
Section 16 — Power Input Testing
Section 16 verifies equipment tolerates normal and abnormal voltage/frequency variations, requiring:
- Steady-state voltage and frequency variation testing across the operating envelope
- Voltage and frequency transient testing — simulating bus transfer events or generator load shedding
- Abnormal/emergency operation conditions — extended operation outside normal range
The test source needs sufficiently fast slew rate to actually produce the transient conditions specified, not just steady-state levels.
Section 17 — Voltage Spike Testing
Section 17 verifies equipment tolerates voltage spikes — fast, high-amplitude transient events representative of switching transients. This requires generating controlled, repeatable spike waveforms with precise timing control relative to the underlying AC waveform. The CORTEX AC series specifies voltage slew rate above 3V/μs.
Single-Phase, Three-Phase, and Phase Independence
DO-160 testing needs to accommodate whichever architecture applies, and for three-phase equipment, independent control of each phase is often required. The CORTEX AC series provides single-phase and three-phase channels with independent phase angle control (0–359.9°, 0.1° resolution).
DC Power Testing — Sections 16/17 for DC Aircraft Systems
Some aircraft systems operate on DC power, and DO-160 Sections 16/17 testing extends to DC power input and spike conditions too. A test system with both AC and DC programmable output in the same platform simplifies validating equipment across both power architectures, increasingly common in more-electric and hybrid-electric aircraft.
Practical Specification Checklist
1. Confirm output frequency range covers 400Hz and any variable-frequency requirement, not just commercial 50/60Hz.
2. Confirm voltage slew rate against the standard's transient and spike requirements.
3. Confirm phase configuration support matches the equipment's actual bus interface.
4. Check whether the program needs both AC and DC power input testing on one platform.
5. Confirm the specific DO-160 revision and equipment category before finalising parameters.