03 — Public chapter: the complete environmental test suite
DO-160 Display Qualification | A-P02 — Draft / Not Released
Learning objective: Screen every environmental section for applicability without imposing every test on every display.
Photo: Cjp24 · Environmental chambers · CC BY-SA 3.0. Original image, displayed at reduced size.
The full DO-160 test suite for a display
Sections 1–3 establish purpose, definitions and general test conditions. Sections 4–26 contain 23 environmental test sections. Appendix A addresses identification of the environmental qualification performed. The following is a planning interpretation for display systems; use the contracted standard for exact procedures, categories and limits.
Temperature moisture and mechanical exposure
| Section and exposure | Display component considerations | Complete display and installation considerations |
|---|---|---|
| 4 — Temperature and altitude | Characterize cold startup and pixel response, hot image quality, backlight and heater behavior, bond integrity and pressure-sensitive cavities. Separate operating capability from unpowered survival. | Test applicable low/high operating and survival conditions, short-time operation, altitude, decompression, overpressure and loss of cooling. Select applicable subtests. Represent cooling, heat dissipation and mounting; substantiate the installed thermal environment. |
| 5 — Temperature variation | Look for differential-expansion damage, bond separation, flex or solder failures and changes in optical uniformity. | Verify operation through the specified changes. Use the required ramp or shock category; slow cycling does not automatically cover rapid transitions. |
| 6 — Humidity | Evaluate moisture-sensitive films, adhesives, touch layers, connectors and insulation. | Assess the assembled enclosure and required performance after or during the prescribed exposure. Include optical clouding and moisture effects in the acceptance criteria where relevant. |
| 7 — Operational shocks and crash safety | Check glass support, board retention, flex routing and connector security in representative fixtures. | Distinguish post-operational-shock functionality from crash retention and occupant safety. Crash safety does not generally mean continued display operation. Substantiate the actual mounting load path and any separate aircraft structural requirements. |
| 8 — Vibration | Investigate panel, backlight, board and connector resonances and intermittent failures. | Select profiles for the aircraft type and mounting location. Monitor image and control behavior as required, with representative mounts and harness support. Account for installed vibration and readability; one fixed-wing profile does not establish helicopter suitability. |
| 9 — Explosion proofness | Identify ignition-capable parts, hot surfaces and materials where the allocated environment makes this relevant. | Evaluate the complete equipment under the applicable flammable-atmosphere category. Determine applicability from the installation zone; do not assume every cockpit display requires this exposure. |
| 10 — Waterproofness | Develop seals and assess exposed touch, bezel and optical interfaces. | Test the defined assembly and exposure faces for the applicable condensation, drip, spray or other specified category. Installation angle, drainage and connector protection matter. A front-face claim does not qualify an unprotected rear enclosure. |
| 11 — Fluids susceptibility | Assess coatings, glass treatments, labels, plastics, elastomers and bonds against specified fluids. | Define realistic contact locations and exposure methods. Include program-specific cleaners or disinfectants when required; a generic fluids claim does not cover every cleaning product. |
| 12 — Sand and dust | Examine scratches, optical contamination, control wear and vulnerable moving or cooling parts. | Apply where the installation environment warrants it. Evaluate ingress, cooling restriction and functional effects using representative seals and openings. |
| 13 — Fungus resistance | Establish material susceptibility, including adhesives, coatings and organic parts. | Use the test or permitted material-based substantiation route applicable to the selected category. Retain evidence; absence of visible growth in normal storage is not qualification. |
| 14 — Salt spray | Investigate corrosion of terminals, coatings, conductive treatments and dissimilar-metal joints. | Evaluate the assembly for the allocated exposure, particularly maritime or exposed service. Assess bonding and connector performance as well as appearance. A protected installation may justify different applicability. |
Electrical and electromagnetic exposure
Electromagnetic compatibility (EMC) includes both the display's resistance to interference and the interference it emits. High-intensity radiated fields (HIRF) are one of the external threats considered in aircraft compliance.
| Section and exposure | Display component considerations | Complete display and installation considerations |
|---|---|---|
| 15 — Magnetic effect | Identify magnetic parts and current paths, including speakers, fans or inductors if fitted. | Evaluate the assembled operating display and record any separation restrictions. Confirm that the proposed installation respects them. |
| 16 — Power input | Characterize internal supply limits, sequencing, ripple tolerance, inrush and brownout response at the component’s own interface. | Qualify the display’s aircraft-facing power input for its AC or DC category and applicable normal/abnormal conditions, interruptions and transfers. Verify image, controls and defined recovery behavior. A nominal “28 VDC” label is insufficient. |
| 17 — Voltage spike | Establish the protection needed at the component boundary. | Apply the required spikes to applicable equipment power inputs. Assess resets, corruption and damage; do not apply aircraft-bus transients directly to an internal rail without an allocated requirement. |
| 18 — Audio frequency conducted susceptibility on power inputs | Check whether supply disturbances cause visible bands, flicker or control interference. | Test the aircraft-facing input using the selected category and frequency conditions. This concerns interference carried on power, not loudspeaker sound output. |
| 19 — Induced signal susceptibility | Assess sensitive touch, dimming, control and data interfaces. | Test applicable interconnections with representative circuits and harness arrangements. Record false controls, image disturbances and interface errors. |
| 20 — Radio frequency susceptibility | Use development tests to find vulnerable touch circuits, flex connections, power stages and enclosure openings. | Perform applicable conducted and radiated tests on the complete configuration with justified sensitive operating modes. Aircraft HIRF substantiation also needs the installation relationship; a laboratory field-strength result alone does not establish it. |
| 21 — Emission of radio frequency energy | Locate noise from pixel clocks, switching converters, backlight modulation and touch scanning. | Measure required conducted and radiated emissions with representative enclosure, cables and active modes. Verify installation compatibility where required; open-bench component results do not characterize final shielding. |
| 22 — Lightning induced transient susceptibility | Allocate residual transient requirements to circuits behind system protection, based on analysis of that protection. | Test applicable power and signal interfaces with specified waveforms, levels and injection methods. Evaluate display behavior and recovery. Link qualification to aircraft coupling, shielding, routing and bonding assumptions. |
Direct lightning icing electrostatic discharge and fire
| Section and exposure | Display component considerations | Complete display and installation considerations |
|---|---|---|
| 23 — Lightning direct effects | Component evidence is relevant only where the display design has an allocated direct-exposure function or path. | An internal cockpit display usually has a different exposure from externally mounted equipment. Address direct-effects applicability through the installation assessment. Exclusion here does not remove Section 22 obligations. |
| 24 — Icing | Assess affected optical surfaces, controls, seals and heaters where freezing moisture is credible. | Select the applicable icing conditions for the installation. Evaluate obstruction, control function and recovery. Temperature variation alone does not demonstrate icing performance. |
| 25 — Electrostatic discharge | Assess exposed touch and control surfaces and their discharge paths. Component handling ESD ratings address a different question. | Test applicable human-accessible locations on the assembled display. DO-160G Section 25 addresses air discharge and excludes connector-pin testing; other ESD methods may be separate contractual requirements. Watch for false touches, resets and persistent image faults. |
| 26 — Fire and flammability | Obtain evidence for relevant plastics, adhesives, optical materials, cables and other parts in their applicable configurations. | Determine the category and substantiation route appropriate to the display and installation. Consider exposed interior materials and applicable aircraft requirements separately. A material rating or a Section 26 result does not automatically establish every installed fire requirement. |
Section titles and coverage are based on DO-160G; the display examples and allocations are engineering guidance, not category assignments. RTCA DO-160G.
Build the first matrix
Start with one row for each Section 4–26. Mark applicability as proposed, agreed or unresolved; keep that status separate from tested, credited by evidence, or not demonstrated. Expand one section into multiple rows where subtests, axes, ports, faces or modes need different arrangements. Record the aircraft location that drives each proposed category.
Exercise: do all displays need salt spray and direct lightning?
Worked response: no universal yes/no answer follows from the word display. Exposure and installation determine applicability. Salt spray may matter in maritime or exposed service, while an interior protected location may support a different decision. Direct lightning relates to direct strike effects and exposed equipment arrangements; induced transient protection is a different section. Record the rationale and the responsible acceptance authority instead of leaving the rows blank.
The remaining lessons develop how to turn this screening matrix into a procedure and evidence package. The suite table is a planning interpretation, not a substitute for the selected section's definitions and exact procedure.
Rating
There are no comments for now.
to be the first to leave a comment.