DO-160 Display Qualification — A-P14 Recording draft. No recorded voice. Timing is provisional. SLIDE 001 — CHAPTER 1 — Introduction Provisional duration: 47 s FPD.DEV — The Future of Display and Systems Development. Welcome to Chapter 1. I am Diggy Breiling. I began repairing displays and LCDs in 1992, while running a laptop computer repair depot in Austin, Texas. In 1994, I began enhancing commercial off-the-shelf LCDs by optically bonding optical enhancement filters, EMI shields and transparent heaters to them. Since 1994, I have built display products that meet or exceed applicable DO-160, MIL-STD-810 and other harsh-environment standards and application-specific requirements. This course connects that practical experience with the display, its requirements and the evidence needed for qualification. SLIDE 002 — CHAPTER 1 — Course scope and intended outcome Provisional duration: 64 s Welcome. In this course, we will build a qualification plan for an aircraft display, starting with the panel and ending with its installed use. We will look at the environmental exposure, the display behavior we need to preserve, and the evidence that connects them. The examples use DO-160G. Your program still needs its adopted edition, agreed categories and complete procedures. Keep a working qualification matrix beside you as we go. This course is a living document, and the standards it draws on evolve too. We update the lessons as standards, engineering practice and our experience develop. Enrolled learners will typically receive updates when chapters are revised. For your own project, keep using the agreed qualification baseline until a change has been reviewed and adopted. SLIDE 003 — CHAPTER 1 — Enhancing a COTS display Provisional duration: 43 s We often enhance commercial off-the-shelf displays beyond the original manufacturer specifications in selected areas. These can include usable temperature range, durability, contrast, brightness, spectral performance and touch capabilities. There are limits and tradeoffs. Added brightness can increase heat, and filters can reduce light transmission. Heaters and cooling can extend the system operating environment while keeping the LCD within its own limits. Any claimed extension needs evidence for the modified assembly, its operating conditions and service life. Enhancement does not automatically extend the original supplier rating. SLIDE 004 — CHAPTER 1 — The qualification plan you will build Provisional duration: 37 s The course has a concrete output: a plan another engineer can review. Start with the equipment boundary and installation assumptions. Then build a matrix that connects each requirement to a method, acceptance criteria and evidence. Keep open inputs visible. We will use the same bonded touch display throughout, then reconsider it for a helicopter. The narrated deck introduces the decisions. The reading, worksheets and capstone provide the deeper study and practice. SLIDE 005 — CHAPTER 1 — The running qualification matrix Provisional duration: 40 s We are bringing the matrix forward so it can organize the entire course. Start one row for each environmental section, then expand rows for distinct ports, axes or subtests. Keep the reason an exposure applies separate from whether compliance has been demonstrated. Category X records an undemonstrated condition. It does not establish that the exposure is irrelevant. When an input is missing, write unresolved and name the person who must supply it. We will complete this matrix later. SLIDE 006 — CHAPTER 1 — References and further study Provisional duration: 43 s Use the publisher's issued document and the program's agreed baseline. This course uses DO-160G section numbering. A forecast publication date for a later revision is not evidence that it has been issued or adopted by your contract. The reference shelf includes environmental qualification guidance, transport-airplane display guidance, HIRF and lightning guidance, each with its own scope. Read the complete applicable methods before writing test instructions. The table excerpts in this deck support specific commentary and do not replace a controlled copy of the standard. SLIDE 007 — CHAPTER 1 — Component, system and installed display Provisional duration: 36 s A bare LCD panel, a complete display and an installed display answer different questions. A panel report can support an allocated component requirement. It does not establish the behavior of the aircraft power converter, enclosure, touch system or mounting. At the installed level, we must show that cooling, wiring, bonding and viewing conditions preserve the assumptions behind the equipment evidence. These are engineering boundaries, rather than three separate certification classes. SLIDE 008 — CHAPTER 1 — What a qualification claim needs Provisional duration: 37 s When a supplier says DO-160 compliant, ask what was actually demonstrated. We need the edition, sections and categories, followed by the tested configuration and supporting reports. Check failures, repairs, deviations and retests. An Environmental Qualification Form is a useful summary, but the underlying evidence gives the claim its meaning. Equipment environmental testing contributes to the aircraft compliance argument. It does not, by itself, establish installation approval, service life or production acceptance. SLIDE 009 — CHAPTER 1 — Panel evidence has a defined boundary Provisional duration: 31 s A supplier gives you a temperature report for a bare LCD panel. Check the tested part, operating state, exposure and measured results. Your product adds bonded glass, touch electronics, power conversion, a housing and a mount. These additions create new interfaces and load paths. The report may support a panel requirement; it does not qualify the complete display. SLIDE 010 — CHAPTER 1 — Turn the report into an evidence plan Provisional duration: 34 s Turn the report into an evidence plan. First, compare its conditions and results with the requirement allocated to the panel. Record the scope that is supported. Next, list missing configuration, results or installation inputs and identify who will provide them. Finally, define the remaining verification for the added functions and complete assembly. Keep these three outcomes separate so another engineer can review the decision. SLIDE 011 — CHAPTER 1 — Acceptance criteria come first Provisional duration: 40 s Before we choose chamber settings, define what successful display behavior means. A screen may remain bright while the image freezes or the touch controller issues a false command. We need measurable criteria for image integrity, controls, validity indications and recovery. State when each criterion applies: during exposure, after exposure, or after an unpowered survival condition. A recovery that is acceptable for one function may be unacceptable for another. The required function and its consequences drive that decision. SLIDE 012 — CHAPTER 1 — A measurable acceptance record Provisional duration: 59 s These are illustrative customer criteria, not DO-160 limits. Cold startup needs a defined soak, power-on event and usable-image requirement, including moving information. Hot Contrast means the ambient contrast ratio while the panel is hot. This example requires at least five to one at a panel temperature of plus seventy degrees Celsius and fifty thousand lux at the screen. State the pattern, light spectrum, viewing geometry and dimming setting. Agree the uncertainty decision rule. Under a conservative rule, a measured ratio of five point one with expanded uncertainty of zero point two has a lower bound of four point nine. That result does not meet this acceptance rule. It does not prove that the true contrast is below five. SLIDE 013 — CHAPTER 1 — Hot Contrast in bright ambient light Provisional duration: 47 s Here, Hot Contrast means contrast measured while the display is at a stated elevated temperature, under specified bright ambient illumination. High-bright describes the environment: strong light falling onto the screen, such as sunlight or intense task lighting. Specify illuminance in lux at the screen, the light direction and spectrum, and the viewing geometry. That is different from display luminance in nits. LCD contrast often falls at elevated temperature, although the trend depends on the panel and drive conditions. Reflected ambient light further reduces visible contrast. Measure the combined condition on the finished optical stack. SLIDE 014 — CHAPTER 1 — Worked example: capture the transient Provisional duration: 62 s Imagine that the image flashes briefly during vibration, but the final still image looks normal. That final check cannot tell us what happened during exposure. Use a changing image with a visible sequence or time reference, record the relevant control outputs, and synchronize those observations with the test input. Choose the capture rate and instrumentation to resolve the shortest event that matters to the requirement. A camera can help, but its frame rate, exposure and viewing geometry can hide or create apparent artifacts. Correlate the image with power, backlight and data observations as needed. Define the permitted interruption, recovery behavior and decision rule before testing. We do not invent a universal allowable flash duration. Record the event first; diagnose its mechanism from the combined evidence. SLIDE 015 — CHAPTER 1 — The environmental coverage map Provisional duration: 36 s DO-160G has twenty-three environmental sections, numbered four through twenty-six. Screen all of them. That does not mean performing every test on every display. Temperature, moisture and mechanical exposures affect the physical assembly. Electrical tests challenge its aircraft interfaces and interference paths. Special hazards depend on the installation. A documented exclusion can be appropriate, while an unexplained blank remains a gap. The detailed reading keeps the complete section-by-section planning table. SLIDE 016 — CHAPTER 1 — DO-160 and MIL-STD-810 Provisional duration: 38 s DO-one-sixty and MIL-standard-eight-ten can coexist on the same display program. DO-one-sixty supplies airborne environmental categories and procedures. Eight-ten starts with environmental engineering and tailoring across the equipment life cycle. A military program may therefore specify aircraft operation plus transport, storage or handling exposures. Start with the contract and installation. Identify the adopted editions and the individual requirements. Neither standard's name alone defines the complete test plan, and there is no general category-to-method conversion. SLIDE 017 — CHAPTER 1 — Related subjects, separate procedures Provisional duration: 36 s These are related subjects, not equivalence declarations. Temperature work connects section four with the military high- and low-temperature method families. Vibration connects section eight with method five-fourteen. Humidity and salt exposure also have related military methods. Read the exact revision and procedure in the adopted edition. Compare article state, exposure and functional evaluation. A matching test title or a higher peak level can still leave a required condition untested. SLIDE 018 — CHAPTER 1 — Qualification credit across standards Provisional duration: 37 s To reuse evidence, compare the complete requirements. Start with purpose, configuration, mounting, harness and operating state. Then compare the full exposure, including the profile, duration, cycles and sequence. Finally compare monitoring and acceptance. An unpowered high-temperature storage result does not establish powered display operation. A single planned test may support more than one requirement when its records demonstrate each requirement. Document the justification and obtain the program's required acceptance of that credit. SLIDE 019 — CHAPTER 1 — Chapter 1 complete Provisional duration: 29 s You have completed Introduction. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Next we continue with Temperature and Pressure. If you are planning a custom display or embedded platform, contact FPD.DEV to discuss the application. FPD.DEV. The Future of Display and Systems Development. SLIDE 020 — CHAPTER 2 — Temperature and Pressure Provisional duration: 27 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter 2, Temperature and Pressure. We will connect the actual temperatures and pressure loads in a display to the image the operator sees. Follow the worked examples, then use the reading pages to develop measurements and acceptance criteria for your own assembly. SLIDE 021 — CHAPTER 2 — Operating state gives a limit meaning Provisional duration: 42 s A temperature range needs an operating state. Ground survival tells us what the equipment can withstand under its prescribed unpowered exposure and evaluation. Normal operation requires the specified functions at the operating condition. Short-time operation has its own sequence and timing. So, so a plus-eighty-five survival result cannot support a claim of continuous operation at plus eighty-five. The same distinction applies to acceptance criteria: the plan must say what the display does, when we observe it, and how we judge the result. SLIDE 022 — CHAPTER 2 — Reading Table 4-1 Provisional duration: 40 s This small crop shows the original table headings and the first three A categories. Follow the A-three column. Its operating low temperature is minus fifteen degrees Celsius, while the short-time operating low temperature is minus forty. Those are different requirements in the same category. The excerpt demonstrates why copying only the coldest number changes the claim. This crop omits the remainder of the table. Use the complete category definition, other conditions and associated procedures in the adopted standard. SLIDE 023 — CHAPTER 2 — Cold response and moving information Provisional duration: 43 s Cold increases liquid-crystal viscosity and slows the optical response. A static image may look acceptable while moving dials, indicators, scrolling text or maps blur, trail or become difficult to interpret. This is pixel settling time, which differs from the frame refresh rate. Include representative motion and critical gray-to-gray transitions in cold-start and stabilized cold-operation checks. Define acceptable response and readable-information timing for the application. A suitable LC material, controlled heater or drive compensation may help, but verify warm-up time, power, uniformity and the actual assembly. SLIDE 024 — CHAPTER 2 — CTE: what changes, and by how much? Provisional duration: 35 s C T E means coefficient of thermal expansion. Linear C T E is the fractional change in length per degree. The simple equation multiplies the material coefficient by the initial length and the temperature change. Use it over an interval where the coefficient is approximately constant. Parts per million means a factor of one millionth. A temperature change has the same numerical value in kelvins and degrees Celsius. SLIDE 025 — CHAPTER 2 — Worked example: 0.120 mm of mismatch Provisional duration: 36 s Take the optical bonding course example: coefficients of twenty-three and eight parts per million per kelvin, a one-hundred-millimeter distance from a center constraint, and an eighty-kelvin temperature change. The coefficient difference is fifteen parts per million per kelvin. Multiplying gives zero point one two zero millimeters of relative free movement. These are teaching inputs, not glass or bezel specifications. Bonding and restraint convert incompatible free movement into deformation and stress. SLIDE 026 — CHAPTER 2 — Stiffness, force and movement Provisional duration: 76 s Stiffness describes how much force a structure develops for a given movement. Watch the left comparison. We move both joints by one millimeter. The stiffer joint develops forty newtons, while the more compliant joint develops ten. Now watch the right comparison. We apply ten newtons to each joint. The more compliant joint moves one millimeter, while the stiffer joint moves only a quarter of a millimeter. These are two different boundary conditions. A compliant bond can reduce the force caused by imposed thermal mismatch, yet allow more movement under an external force. Neither result makes softer automatically better. Material modulus and assembly stiffness are also different. For a simple axial bar, stiffness equals Young's modulus times area divided by length. For a shear bond, area and thickness matter too. These illustrative springs keep geometry fixed so we can isolate stiffness. Real display joints also depend on temperature, loading rate, damping and their exposure history. SLIDE 027 — CHAPTER 2 — Temperature and loading rate Provisional duration: 124 s Now we add time and temperature. Each specimen reaches the same final strain. Teal shows the fast ramp, completed in six tenths of a model second. Amber shows the slower ramp, completed in six seconds. The upper strips show the imposed movement. The curves below show the resulting normalized stress. The cooler example on the left relaxes slowly. The warmer example on the right relaxes more quickly. These are assumed relaxation times, not measurements of a particular adhesive. Watch the fast ramp finish. Its movement stops, but the stress continues to decrease during the hold. That is stress relaxation. The slow ramp gives the material more time to relax while it is moving, so it reaches the target strain with a lower stress in this model. Later, the fast-ramp curve can fall below the slow-ramp curve because it has already spent longer relaxing. Compare the peak stress at the end of each ramp, and distinguish that from a comparison at the same clock time. At either temperature, faster loading can make the same material appear stiffer over the event. At the warmer condition, more of the stress relaxes within the same time window. This illustrates a common viscoelastic pattern within a suitable material regime. Actual glass transitions, phase changes, cure, aging or irreversible shrinkage can change that behavior. Mechanical strain rate is not the same quantity as a chamber temperature ramp in degrees per minute. Thermal ramp rate also affects temperature gradients and the time available for relaxation. Use the actual material data and exposure history. SLIDE 028 — CHAPTER 2 — Bond thickness and shear strain Provisional duration: 84 s The two bonds now undergo the same relative movement between their faces. The upper adherend moves while the lower one stays in place. The bond at left is half a millimeter thick. The bond at right is one millimeter thick. At the illustrated displacement of fifty micrometers, the thinner bond has ten percent shear strain, while the thicker bond has five percent. Shear strain is relative displacement divided by thickness. The leaning grid lines make that difference visible. If we assume a constant shear modulus of zero point two megapascals, the simple elastic model gives twenty kilopascals and ten kilopascals of shear stress. Those are teaching inputs, not supplier values or allowable stresses. A real viscoelastic bond has a stress history that depends on temperature and loading rate, as we just saw. Thickness also affects optical spacing, cure and processing. This uniform shear model does not capture edge peel, local stress concentrations, creep or interface failure. A thicker bond is therefore a design choice to evaluate, not an automatic improvement. SLIDE 029 — CHAPTER 2 — Laminate mismatch and restraint Provisional duration: 170 s Think of a bimetal thermometer. Its joined layers would change length by different amounts if they were free. Because they stay connected, the strip bends. In the first part of this animation, the film would expand more than the glass. The longer layer lies on the outside of the curve. Compare the three arrangements. An asymmetric laminate can bend. Matching films on the front and rear can balance the bending effect, while still carrying internal stress. A support that holds the stack flat supplies a reaction moment. Flatness alone does not show that the layers are stress free. Now the film's free dimensional change reverses. It wants to shrink relative to the glass, so the free laminate bends the other way. This second case helps explain heated polarizer films. The OEM LCD is already a bonded laminate before we add a cover window. A typical polarizer includes stretched polyvinyl alcohol, or P V A, protective films and a pressure-sensitive adhesive. Heat can release stored orientation in stretched P V A, producing shrinkage while the glass expands. Direction, moisture, drying, cure and aging all affect the response. At cold temperatures, some adhesive and polymer layers stiffen and relax more slowly. Our three-layer sketch is deliberately simpler than the real LCD. It assumes perfect bonding and elastic layers, uses illustrative dimensions and moduli, and exaggerates bow so you can see the mechanism. Its stress labels are model results, not LCD predictions. The previous animation explains why a compliant adhesive changes load transfer with time and temperature. Stress can change film retardation and cause light leakage or mura. Glass bending can also alter cell-gap uniformity, but mura alone does not prove a cell-gap change. Edge peel, delamination and cracking require further analysis and testing. Inspect during hot and cold exposure and again after recovery. Some effects recover and some persist. Our Optical Bonding course explains the actual cell construction in Chapter two, then develops expansion, compliance and mura in Chapter six. SLIDE 030 — CHAPTER 2 — A display has several temperatures Provisional duration: 62 s A chamber setpoint is the target air temperature. Verify the measured air temperature near the equipment. A controller setting or chamber-wall measurement alone does not establish the exposure, and neither tells us the temperature of every part of the display. The backlight, power converter and transparent heater generate heat. The enclosure and mount conduct it away, and the optical stack can absorb sunlight. Place sensors where the requirement and the suspected failure mechanism demand them, while checking that the sensors do not disturb the optics or heat path. Record the temperatures with operating mode and input power. A claim for operation at a stated ambient temperature needs evidence that the internal parts remain within the limits adopted for the enhanced assembly. SLIDE 031 — CHAPTER 2 — Hot Contrast: a worked comparison Provisional duration: 63 s Here is an illustrative Hot Contrast comparison at a panel temperature of seventy degrees Celsius and fifty thousand lux at the display surface. All luminance values are measured in the observer direction with that ambient illumination present. These are total measured luminances, so we do not add ambient reflection again. Before enhancement, white is eight hundred and black is two hundred candelas per square metre, so contrast is four to one. After reducing reflections, white is seven hundred and twenty and black is one hundred and twenty, giving six to one. White luminance decreased, yet ambient contrast improved. These invented values explain the calculation. The actual test must define illumination geometry, spectrum, viewing direction and instrument uncertainty, then measure the real display. SLIDE 032 — CHAPTER 2 — Cold motion and heater control Provisional duration: 55 s A cold display can show a sharp stationary image while a moving pointer leaves a trail. Low temperature slows the liquid crystal optical response, so a fast video interface does not guarantee a fast visible transition. Exercise representative grey transitions and the actual symbols at the intended update rate. Record warm-up time, smear and overshoot, including any drive compensation. A transparent heater can extend the usable ambient range, but the control system needs temperature sensing, power budgeting and protection against overheating. Check a failed sensor or stuck heater command against the product safety requirements. The useful result is a demonstrated operating envelope for the complete heated display. SLIDE 033 — CHAPTER 2 — A temperature procedure has stages Provisional duration: 41 s A procedure is more than a setpoint and a dwell. Identify the conditioning, power state, stabilization rule and the event that starts each timer. Chamber air and the display assembly can reach equilibrium at different times. In the course example, the chamber reaches seventy degrees at nine, but the equipment stabilizes at nine forty. Stopping at eleven provides only eighty minutes after stabilization. It does not demonstrate a two-hour post-stabilization requirement. Keep the raw histories and the complete prescribed sequence. SLIDE 034 — CHAPTER 2 — Temperature variation and thermal lag Provisional duration: 43 s Section five assigns minimum chamber rates of ten, five and two degrees Celsius per minute to categories A, B and C. These letters belong to section five and do not replace the section four category. For an assumed transition from minus forty to plus seventy, the temperature difference is one hundred ten degrees. At exactly five degrees per minute, the ideal transition takes twenty-two minutes. That is only the ramp. The panel can lag the air, and the complete test includes additional stages and checks. SLIDE 035 — CHAPTER 2 — The complete variation sequence Provisional duration: 66 s The complete variation procedure includes stabilization, specified operation, power-off and restart stages, and the required performance checks. For A, B and C, at least two cycles are required, with additional cycles if needed to complete the checks. A large number of slow development cycles does not automatically replace the selected qualification method. The figure summarizes the noncombined sequence. Notice the power-off interval of at least two minutes at the high-temperature stage, the operation for at least one hour after low-temperature stabilization, and the thirty-minute power-off interval before the cold restart. Follow the complete sequence in section five; Page six provides a larger reading figure. If you combine sections four and five, preserve all applicable requirements of both. Keep actual temperature traces, power events and anomalies aligned in time. SLIDE 036 — CHAPTER 2 — Thermal lag changes the exposure Provisional duration: 52 s During a rapid chamber transition, the cover glass, LCD frame, bondline and housing do not change temperature at the same rate. Their transient mismatch can differ from the mismatch after equilibrium. A large metal fixture can also delay the response or provide an unintended heat sink. Use the stabilization definition and transition requirements in the adopted procedure, and record representative item temperatures as supporting evidence. Do not replace the prescribed exposure with an arbitrary wait until one convenient sensor settles. During development, instrument several locations to learn which gradient coincides with a contrast change, bond-edge defect or loss of touch accuracy. SLIDE 037 — CHAPTER 2 — Temperature evidence before and after Provisional duration: 54 s The display returns to room temperature and looks normal. That establishes recovery, but it does not erase a loss of function while hot or cold. Prepare the baseline using controlled patterns, brightness settings and measurement geometry. During the test, collect the signals needed to judge the required operating behaviour. After the specified recovery, repeat the baseline and inspect for permanent changes. A reversible contrast collapse, a temporary link reset and a permanent bond defect are different observations with different acceptance consequences. Tie each observation to the actual requirement. Preserve the time history so a later reviewer can distinguish an exposure failure from an instrument interruption. SLIDE 038 — CHAPTER 2 — Absolute pressure and altitude Provisional duration: 40 s The word absolute in this table matters. Eight thousand feet corresponds to about seventy-five point two six kilopascals absolute in this reference. Gauge pressure uses a different reference and cannot simply be substituted. The cropped table is useful for reading the units, but it does not select your final altitude or procedure. Record the aircraft environment, initial and final absolute pressures, transition timing and required operation. Use the adopted table and tolerances when writing the laboratory procedure. SLIDE 039 — CHAPTER 2 — Decompression is a pressure transient Provisional duration: 52 s For installations where this test applies, the section four decompression method starts at ambient temperature, with the equipment operating and stabilized at eight-thousand-foot equivalent pressure. It then reduces pressure to the aircraft maximum operating-altitude equivalent within fifteen seconds. The final condition lasts at least ten minutes, or as specified, with the required operation and checks. Fifty-five thousand feet in this plot is an example. Sixty-five thousand feet is not a universal requirement. Trapped volumes, optical cavities and vent paths matter. A stabilized altitude soak and a rapid pressure transition challenge different mechanisms, so an identical endpoint does not make them equivalent. SLIDE 040 — CHAPTER 2 — Pressure-test equipment Provisional duration: 36 s This public-domain NASA image shows a large thermal-vacuum vessel. It illustrates the pressure boundary, door and test enclosure. It does not show an aircraft-display qualification setup. For our display, the specified altitude and decompression method determines the pressure range, rate, hold and operating state. Select a suitable vessel, feedthroughs and instrumentation, then record absolute pressure at the required locations. A facility's lowest achievable pressure is not the qualification requirement. SLIDE 041 — CHAPTER 2 — Altitude, decompression and trapped air Provisional duration: 56 s As external pressure falls during ascent or decompression, trapped gas may expand and gas can flow through available paths toward lower pressure. If a cavity cannot equalize quickly, a pressure difference loads its walls and bonded interfaces. A flexible air pocket may enlarge. A rigid sealed cavity may instead carry the pressure difference with little volume change. For a freely expanding ideal-gas pocket at constant temperature, halving absolute pressure doubles the equilibrium volume. That simple example is not a prediction for a restrained adhesive void or for rapid decompression, where temperature and transient flow matter. Evaluate void size, vent paths, permeability, geometry and pressure-change rate. Low outgassing and pressure resistance are separate questions. SLIDE 042 — CHAPTER 2 — Adhesive and cohesive failure Provisional duration: 57 s An expanding air pocket can impose opening and peel loads around a bonded region. If those local loads exceed the available resistance, separation may occur at an interface or a material may tear internally. Adhesive failure means separation at the interface between materials. Cohesive failure means rupture within a material, such as the silicone or another adhesive layer. The neighboring polarizer, coating or glass can also fail. Inspect both separated surfaces and identify which layer actually remains on each side. A strong optical bond does not protect every weaker layer beneath it. Record mixed failures and optical distortion as well as obvious separation. The optical bonding course develops this failure analysis in more detail. SLIDE 043 — CHAPTER 2 — Pressure effects across the adhesive system Provisional duration: 56 s Review every adhesive-containing part of the assembly, not only the optical bond. Include optical silicones and films, conductive EMI tapes, adhesive-backed gaskets, sealants, and potting or encapsulating compounds. These material families are all within the review scope. Their susceptibility is not identical. A void, a poorly vented pocket or a weak interface must be considered together with the material and pressure profile. A mechanically retained gasket also needs its own seal and cavity-pressure assessment. Control mixing, degassing, application, wetting and cure as appropriate to the qualified process. Verify representative assemblies, including adverse permissible tolerances. After exposure, inspect bubbles, edge lift and separation, and check optical performance, sealing and electrical continuity where relevant. SLIDE 044 — CHAPTER 2 — Pressure difference loads the window Provisional duration: 53 s Consider a sealed window with an exposed area of two hundred by one hundred and fifty millimetres. Its area is zero point zero three square metres. An illustrative pressure difference of twenty kilopascals creates a resultant force of six hundred newtons, using force equals pressure difference times area. This is a net load, not a prediction of glass stress or bond-edge stress. Those depend on geometry, support, stiffness and the changing internal pressure. A vent changes the pressure history, and its flow capacity matters during decompression. Use the real installation and selected pressure profile to establish loads before assessing deflection, clearances and attachment strength. SLIDE 045 — CHAPTER 2 — Vents, seals and pressure monitoring Provisional duration: 51 s A vented enclosure can still develop a pressure difference when outside pressure changes faster than air can pass through the vent. Measure internal and external pressure with enough time resolution to capture the transient, and document the tubing and sensors because they can alter the volume or flow path. Include the actual membrane, filter and mounting arrangement. A moisture-resistant vent also creates design trade-offs in ingress protection and pressure equalization. Look for window movement, trapped-bubble growth and changes in sealing after exposure. A successful slow altitude dwell does not by itself demonstrate behaviour during the specified decompression transient. SLIDE 046 — CHAPTER 2 — Chapter 2 complete Provisional duration: 28 s You have completed Temperature and Pressure. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Next we continue with Moisture and Contamination. Our Optical Bonding course develops the material and bondline mechanisms in greater detail. FPD.DEV. The Future of Display and Systems Development. SLIDE 047 — CHAPTER 3 — Moisture and Contamination Provisional duration: 27 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter 3, Moisture and Contamination. We will trace moisture and contamination from the external exposure to the optical materials, electronics and operator interface. Each topic connects the failure mechanism to a test configuration, a monitoring method and an evidence decision. SLIDE 048 — CHAPTER 3 — Humidity, water and fluids Provisional duration: 39 s These exposures answer different questions. Humidity can affect optical films, adhesives and insulation through a prescribed temperature and moisture cycle. Waterproofness evaluates selected liquid-water conditions. Fluids susceptibility concerns specified chemicals and contact methods. A sealed front face does not establish rear-connector protection, and water resistance does not establish cleaner compatibility. Map the moisture and chemical paths through the actual assembly. Define the optical, control and physical checks and when they occur, including any required recovery conditions. SLIDE 049 — CHAPTER 3 — Temperature and humidity chambers Provisional duration: 39 s These chambers show the equipment used to control temperature and humidity. The controller's display is only one part of the record. Article loading, airflow, temperature sensors and humidity measurement affect the exposure that the display actually receives. Record the prescribed cycle and the required article condition. Include the recovery and functional checks. When comparing a DO-one-sixty humidity result with a military requirement, compare the complete profiles and evaluation rather than the chamber brand or maximum rating. SLIDE 050 — CHAPTER 3 — Polarizer protection in wet environments Provisional duration: 52 s I have helped customers whose display polarizers were damaged by humidity or salt fog. One solution used optical bonding to add a protective cover glass. Another laminated PET film to the polarizer and sealed the polarizer edge. These examples give integrators concrete protection options to evaluate. Consider the face and the exposed perimeter together. Specify the materials, adhesive and assembly process, then verify the finished optical stack under the applicable exposure. Check optical performance, adhesion and edge condition. The added glass or film alone does not establish a hermetic enclosure or a qualification result. Keep the humidity, water and salt-exposure requirements separate in the plan. SLIDE 051 — CHAPTER 3 — Humidity reaches the optical stack Provisional duration: 51 s Humidity can affect a display through several paths. Water vapour can diffuse through a polymer or enter through an edge seal, while liquid condensation can form when a surface is below the local dew point. Absorbed moisture can change material dimensions and adhesive behaviour. Surface water can increase leakage or change a capacitive touch measurement. These mechanisms need different observations. A hazy bond edge, corroded connector and false touch event should not be grouped under a single description such as moisture failure. Identify the path and the affected function, then choose inspection and monitoring that can distinguish the causes. SLIDE 052 — CHAPTER 3 — A humidity test configuration Provisional duration: 52 s Build the humidity specimen as the production configuration requires, including the real sealing and vent details. Follow the selected category, cycle and operating sequence in the adopted standard. Keep chamber records and item operation on a common timeline. For a touch display, capture intended touches and uncommanded events as well as the visible image. At each required check, use the agreed inspection and functional criteria. Photograph condensation, haze and corrosion before handling changes them. Opening the enclosure or wiping the surface can destroy evidence of the failure path. Any extra investigative check must be distinguished from the formal qualification procedure. SLIDE 053 — CHAPTER 3 — Water exposure and entry paths Provisional duration: 51 s Waterproofness starts with the installation exposure and the applicable test category. A front face that tolerates a cleaning wipe does not establish protection against every water test. Water can collect at a bezel joint, run along a cable, enter a connector or reach a rear vent. Orient the specimen and arrange its connections as the selected procedure and installation require. Define what function must continue during exposure and what post-test inspection must establish. Where an ingress protection rating is also required, treat its method and acceptance as a separate requirement unless a documented comparison establishes applicable evidence credit. SLIDE 054 — CHAPTER 3 — Fluid compatibility and service cleaning Provisional duration: 52 s A coating may tolerate water while a cleaning fluid changes its surface, and an adhesive may swell without an immediate visible bond failure. Identify the specified fluids and the plausible service chemicals, then connect each to the materials it can reach. Follow the qualification method for concentration, application and exposure. Separately evaluate the approved cleaning process where the product requires it. Inspect optical transmission, haze, markings, seal integrity and touch operation as applicable. A coupon can help screen materials, but the assembly adds edges, mechanical stress and material interactions. Keep coupon evidence and complete-display evidence clearly scoped in the qualification matrix. SLIDE 055 — CHAPTER 3 — Worked case: false touches when wet Provisional duration: 53 s In this illustrative case, water on the cover causes touch events while the image remains readable. First preserve the touch event log, command output and synchronized video. Determine whether the controller generated a false coordinate, the application acted on it, or only a test tool reported an event. Compare that behaviour with the requirement for operation during the selected exposure. The display has not passed merely because it still shows an image. Possible design responses include controller tuning, cover geometry, drainage and appropriate input validation. Each change can affect dry touch or glove performance, so repeat the affected evaluations on the revised configuration. SLIDE 056 — CHAPTER 3 — Salt spray, fungus, sand and dust Provisional duration: 61 s An image can remain visible while corrosion degrades an electrical connection between chassis parts. Acceptance therefore needs the relevant electrical and physical checks as well as visual function. For salt spray category S, the course diagram shows twenty-four hours of fog followed by twenty-four hours of drying, repeated once. That gives forty-eight fog hours across ninety-six elapsed hours, before subsequent evaluation. Category T has a separate sequence. For fungus, sand and dust, consider the actual materials, openings and operating states. Keep material identity and exposure evidence traceable. Here, electrical bonding means a conductive connection for grounding or shielding. Optical bonding refers separately to the adhesive interface in the display optical stack. Salt fog can also damage the polarizer, as discussed earlier in this chapter. SLIDE 057 — CHAPTER 3 — Salt-spray test equipment Provisional duration: 38 s This salt-spray chamber illustrates the exposure enclosure and solution controls. The required method governs solution conditions, fallout collection, orientation and exposure sequence. The display's materials, fasteners, connectors and bonds need the applicable inspection and functional checks. A similar chamber may serve different standards, but the procedures and acceptance can differ. Preserve the actual exposure record and the inspection findings. Do not infer a service-life prediction from a salt-exposure photograph or a single pass. SLIDE 058 — CHAPTER 3 — Salt contamination and electrical paths Provisional duration: 52 s Salt contamination can create a conductive path when moisture is present and can promote corrosion at contacts, fasteners or shielding joints. Those effects can appear in different ways: leakage, intermittent connection, increased bond resistance or cosmetic change. Define the electrical and physical acceptance criteria before exposure. Preserve the selected salt-fog sequence and recovery conditions because drying and wetting history affect what the specimen experiences. Use post-test inspection to locate deposits and corrosion, then relate them to the functional measurements. Salt-fog qualification is evidence for that procedure. It is not a direct conversion to a number of years in coastal service. SLIDE 059 — CHAPTER 3 — Dust, sand and exposed interfaces Provisional duration: 52 s Dust and sand place different demands on a display. Fine dust can accumulate at a connector or block a cooling path, while larger abrasive particles can damage a coating or interfere with a control. The specified particle characteristics, concentration and exposure conditions matter. Assess the actual orientation, enclosure openings and operation called for by the procedure. Afterwards, inspect the exposed surfaces and interfaces before cleaning away evidence. If readability has changed, distinguish scattering from surface damage, a dirty cover or an internal optical defect. A service cleaning instruction also needs to consider whether wiping trapped abrasive particles damages the surface. SLIDE 060 — CHAPTER 3 — Fungus and material susceptibility Provisional duration: 50 s Fungus susceptibility depends on the materials and the conditions that support growth. An assembly contains more than its metal enclosure: adhesives, coatings, labels, gaskets and contaminants can matter. Review the adopted section's provisions for material evidence and testing, then document the basis used for the actual configuration. A supplier statement about one resin does not automatically cover an adhesive formulation or an assembled optical stack. Keep material substitutions under change control. If the intended service practice includes cleaning or storage controls, identify those assumptions in the product documentation without using them to silently remove a qualification requirement. SLIDE 061 — CHAPTER 3 — Chapter 3 complete Provisional duration: 23 s You have completed Moisture and Contamination. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Next we continue with Mechanical and Special Environments. FPD.DEV. The Future of Display and Systems Development. SLIDE 062 — CHAPTER 4 — Mechanical and Special Environments Provisional duration: 34 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter four, Mechanical and Special Environments. We will connect frequency, acceleration and pulse duration to the response of a complete display. We will read selected DO-160G tables, work through resonance and rotor harmonics, and use animations to compare input and response. Then we will connect the measurements to image stability, mechanical integrity and the applicable qualification decision. SLIDE 063 — CHAPTER 4 — Shock, vibration and the load path Provisional duration: 42 s The panel, optical bond, enclosure, mounts and aircraft structure form a load path. The qualification setup must represent the relevant attachment assumptions. An extra support can change the stresses in the glass even when the commanded input is correct. Keep operational shock acceptance separate from crash retention and hazard criteria. During vibration, use changing imagery and suitable event capture. A connector can create a brief corrupted frame and then look normal at the final inspection. Monitoring capability is part of the evidence. SLIDE 064 — CHAPTER 4 — Fixed-wing and helicopter vibration Provisional duration: 42 s The aircraft label alone cannot select a complete vibration test. For fixed-wing applications, use the specified standard or robust method and applicable zone. Helicopter methods address the relevant rotational-frequency basis, with defined alternatives when frequencies are unknown. A four-blade rotor at an assumed three hundred RPM has a five-hertz rotational frequency and a twenty-hertz blade-passage frequency. That calculation teaches the relationship. It is not an AW-one-thirty-nine specification or a complete test spectrum. Compare profiles, mounting, duration and performance evidence before claiming coverage. SLIDE 065 — CHAPTER 4 — Vibration and shock quantities Provisional duration: 57 s When we ask how much vibration power a display must withstand, we need to name the quantity. A sine input has a frequency and an acceleration amplitude, normally stated as peak g. Random vibration uses an acceleration power spectral density, or PSD, in g squared per hertz, together with an overall g RMS level. The word power here refers to a squared signal quantity. It does not specify watts delivered to the display. Shock uses a peak acceleration, pulse shape and duration. One standard g is approximately nine point eight one metres per second squared. Record whether an amplitude is peak, peak to peak or RMS, because these are different numbers. SLIDE 066 — CHAPTER 4 — Sine motion: frequency changes travel Provisional duration: 55 s For sinusoidal motion, multiply frequency by two pi, square that entire quantity, then multiply by peak displacement to obtain peak acceleration. At one g peak and ten hertz, the peak displacement is about two point four eight millimetres. At one hundred hertz it is only zero point zero two four eight millimetres. Peak-to-peak travel is twice those values. The higher-frequency motion looks smaller even though the acceleration is identical. For a pure sine wave, one g peak is zero point seven zero seven g RMS. These relationships help assess clearances, shaker stroke and why a connector can experience acceleration without large visible motion. SLIDE 067 — CHAPTER 4 — Random vibration: PSD and g RMS Provisional duration: 59 s The PSD tells us where the mean-square acceleration lies across frequency. Integrate it over the specified band to obtain g squared, then take the square root to obtain g RMS. For this teaching example, a flat PSD of zero point zero one g squared per hertz from twenty to five hundred hertz has an area of four point eight g squared. The overall level is therefore about two point one nine g RMS. A real DO-160 profile has specified breakpoints and slopes, so we integrate every segment. Two profiles with the same overall g RMS can stress a display differently when one puts more excitation near a structural mode. Overall RMS is not an instantaneous peak limit. SLIDE 068 — CHAPTER 4 — DO-160G random curve B Provisional duration: 60 s Here are the five breakpoints for standard random curve B in Figure eight dash one of DO-160G. The PSD is zero point zero one two at ten and forty hertz, falls to zero point zero zero two at one hundred hertz, stays there through five hundred hertz, then falls to zero point zero zero zero one three at two thousand hertz. The figure lists one point four eight g RMS. This is a curve-reading example, not a universal display qualification profile. Table eight dash one connects aircraft type, category and mounting zone to the curve. Its note distinguishes B from the lower B2 option and the large-aircraft B3 option. Use the applicable selection and the full log-log profile. SLIDE 069 — CHAPTER 4 — Resonance scans and random exposure Provisional duration: 58 s The resonance scan and the random exposure are different parts of this procedure. In section eight point five point two, the initial scan uses zero point five g peak from ten to two thousand hertz, with the equipment not operating. The sweep rate does not exceed one octave per minute. An octave means a doubling of frequency. Response peaks greater than twice the input identify resonant frequencies under this procedure. The equipment then operates during the applicable random performance profile for at least one hour per axis, with response PSD measurements. A final scan identifies changes. These conditions apply to this selected procedure. Other categories have different performance periods, endurance periods or dwells. SLIDE 070 — CHAPTER 4 — LCD cell gap and transient contrast Provisional duration: 56 s The liquid-crystal layer occupies the small gap between the cell glass substrates. Shock, vibration or mounting stress can bend the cell and vary that local gap. This changes the optical response and can reduce contrast or produce transient bright or dark flashes. The external optical bond is outside this sealed cell. Its thickness is a different dimension. Stress can also change liquid-crystal alignment or the optical response of other layers, so gap change is one possible mechanism. A flash alone does not diagnose it. Check power, backlight drive, connectors and video continuity as well. Observe the powered image during the required exposure because a transient defect may disappear before the final inspection. SLIDE 071 — CHAPTER 4 — Mounting for viewability and survival Provisional duration: 57 s Mounting should reduce harmful stress transmitted into the display while retaining the complete assembly. Follow the module supplier’s mounting provisions. Avoid forcing a twisted module flat, uneven fastener loading, concentrated pressure on the optical area and uncontrolled gasket compression. Account for the added cover mass and provide cable strain relief so the harness does not load the cell or bypass an intended isolator. Allow thermal movement where the design requires it. Suitable compliant interfaces or isolation mounts may help, but the delicate polarizer laminate should not become an unverified structural restraint. Every display and mounting configuration is different. These principles guide the design review; they do not specify the mount for a particular product. SLIDE 072 — CHAPTER 4 — Isolation depends on the complete assembly Provisional duration: 55 s Reducing harmful transmitted stress and vibration can improve both viewability and survivability. That benefit depends on selecting and verifying the mounting system. A passive isolator can amplify motion near the assembly’s natural frequency. Added glass mass, temperature-dependent stiffness, damping, cables and mechanical stops all influence the response. Select mounts against the actual shock pulse and vibration spectrum, in every required axis, with enough controlled travel and retention. Measure the fixture input and representative display response. Record image behavior at the same time, including contrast changes and flashes. Complete the required post-test inspection and functional checks. Passing a final still-image check alone can miss a usability failure that occurred during vibration. SLIDE 073 — CHAPTER 4 — Vibration fixture and installation Provisional duration: 52 s A vibration result depends on how the display attaches to the shaker. The fixture can introduce resonances or stiffness that differ from the installation. Record the mounting interfaces, fastener condition, supported mass and cable restraint. Establish the control and response measurement locations through the applicable procedure and laboratory plan. If a bracket or isolator belongs to the product, omitting it changes the system being evaluated. Conversely, an installation fixture may have to reproduce an agreed boundary rather than every part of the aircraft. Review those assumptions before the test so the qualification statement can identify exactly what the evidence covers. SLIDE 074 — CHAPTER 4 — Resonance and isolator trade-offs Provisional duration: 53 s An isolator can reduce transmitted vibration over part of the frequency range while amplifying motion near a system resonance. A softer support also allows more displacement, which affects cable strain, bezel clearance and impact against stops. Evaluate the supported mass, stiffness, damping and attachment arrangement together. Elastomer properties can change with temperature and ageing, so room-temperature behaviour may not represent the whole operating envelope. During development, compare measured input and response spectra to locate amplification. Then use the adopted qualification profile and mounting configuration for the formal test. A mount described as vibration isolating is not sufficient evidence of improved display performance. SLIDE 075 — CHAPTER 4 — Natural frequencies of a display Provisional duration: 59 s A natural frequency describes how a structure tends to vibrate after a disturbance. A simple supported mass has a natural frequency equal to one over two pi times the square root of stiffness divided by mass. A two-kilogram assembly with an effective stiffness of about one hundred ninety-seven thousand newtons per metre has a fifty-hertz natural frequency. Doubling the mass lowers that frequency by the square root of two. Doubling stiffness raises it by the same factor. A real display has many modes: cover bending, frame motion, circuit-board flex and whole-unit motion on mounts. Their frequencies are not generally integer multiples. The model helps us reason about a change, while measurements establish the actual modes. SLIDE 076 — CHAPTER 4 — Resonance: input and response Provisional duration: 59 s Watch the applied motion and the response of our illustrative fifty-hertz system. Well below its natural frequency, the supported assembly follows the base. Near the natural frequency, repeated excitation produces a much larger response. With five percent damping, the steady-state absolute acceleration ratio is about ten at fifty hertz. A zero point five g peak input would therefore predict about five point zero two g peak response in this ideal linear model. Above the resonance region, the ratio decreases. The animation slows the cycles so the motion is visible and exaggerates travel. It compares steady-state cases, not the transient response during a qualification sweep. Actual response depends on the mode, mounting, damping and nonlinear limits. SLIDE 077 — CHAPTER 4 — Damping limits resonance Provisional duration: 56 s Damping dissipates mechanical energy and limits resonant response. In this model, increasing damping from five to twenty percent reduces the ratio at the natural frequency from about ten point zero five to two point six nine. That does not mean the most damping is always the best isolator. Well above resonance, higher damping can transmit more motion through the mount. For this simple model, the absolute-motion ratio falls below one when the excitation frequency exceeds the square root of two times the natural frequency. A fifty-hertz mount therefore starts its isolation region above about seventy point seven hertz. Clearance, shock travel, temperature and cable restraint still have to be checked. SLIDE 078 — CHAPTER 4 — Harmonics and structural modes Provisional duration: 58 s A harmonic is an integer multiple of a fundamental excitation frequency. A rotor turning at three hundred sixty revolutions per minute rotates six times per second. Four equally spaced blades create a blade-passage frequency of twenty-four hertz. Its second harmonic is forty-eight hertz, which could excite a display mode near forty-eight hertz. That mode is a property of the assembly. The harmonic is a property of the forcing. They can coincide, but the second structural mode need not be twice the first. In a linear system, resonance amplifies frequencies that are already present. Nonlinear contacts, looseness or other nonlinear behaviour can generate additional harmonics. The animated amplitudes are illustrative, not a measured rotor spectrum. SLIDE 079 — CHAPTER 4 — Helicopter instrument-panel tones Provisional duration: 55 s Table eight dash two a gives the sinusoidal test frequencies for different helicopter zones. For Zone two, which includes the instrument panel, console and equipment rack, curve G uses main-rotor blade passage and twice that frequency. With our assumed six-hertz rotor and four blades, those tones are twenty-four and forty-eight hertz. The table leaves the third and fourth tone entries blank for this zone. Other zones can include tail-rotor, engine or gearbox frequencies. The known-frequency procedure sweeps each specified tone across plus or minus ten percent. The example therefore spans twenty-one point six to twenty-six point four hertz and forty-three point two to fifty-two point eight hertz. SLIDE 080 — CHAPTER 4 — Helicopter curve G acceleration Provisional duration: 55 s Now apply Table eight dash two b to those two frequencies. At twenty-four hertz, curve G performance acceleration is zero point zero four times frequency, giving zero point nine six g peak. At forty-eight hertz, the performance level is one point six g peak. The endurance level is two point five g peak for each of these frequencies. These are sinusoidal components applied with the random background, not overall RMS values. The table also states that external-airflow exposure increases the sinusoidal levels by a factor of one point five. Our instrument-panel example is internal. Keep the applicable zone, frequency range, installation and procedure attached to every quoted level. SLIDE 081 — CHAPTER 4 — Sine-on-random: two severity measures Provisional duration: 61 s A sine-on-random test combines discrete sinusoidal tones with a broadband random background. For the curve G table, the performance background reference W zero is zero point zero one g squared per hertz, with two point seven five g RMS listed for the random curve. Endurance uses zero point zero two and three point eight nine g RMS. W zero identifies a level in a shaped spectrum. It is not a flat PSD across the entire band. The listed RMS describes the random component alone. To combine independent random and sine components for an illustrative overall RMS estimate, add their mean squares, using sine peak squared divided by two, then take the square root. Never add g peak directly to g RMS. SLIDE 082 — CHAPTER 4 — Image stability during vibration Provisional duration: 52 s A display can survive vibration structurally and still produce distracting flashes or unreadable information. Cell-gap changes, optical-stack movement or an intermittent connector can cause different image symptoms. Use patterns and operating modes that expose the relevant behaviour, including moving indicators where required. A camera provides useful evidence, but its shutter, exposure and rolling readout can create bands or miss a short event. Verify the recording method against known changes and correlate it with interface logs and mechanical measurements. Record the duration and extent of each disturbance. Apply the product's agreed image stability criterion rather than deciding by memory after the test. SLIDE 083 — CHAPTER 4 — Shock survival and retained function Provisional duration: 52 s A requirement to continue operating after an operational shock differs from a requirement that equipment remain safely retained during a crash-safety exposure. Select the applicable test and category from the installation requirements. Record the pulse characteristics, axes, mounting and operating state required by the procedure. For the display, examine the glass retention, bracket load path, fasteners and heavy internal parts as well as the electronics. A functioning image alone does not establish safe retention, and damage after a survival exposure needs evaluation against that exposure's actual acceptance criteria. Avoid carrying an operating-performance assumption into a test with a different purpose. SLIDE 084 — CHAPTER 4 — DO-160G shock pulse examples Provisional duration: 53 s Section seven distinguishes operational shock from crash retention. Standard operational shock uses six g peak with an eleven-millisecond nominal terminal sawtooth pulse. The low-frequency option uses six g peak and twenty milliseconds. The procedure applies three shocks in each orientation, or the specified equivalent axis arrangement. Crash impulse uses twenty g, one shock in each of six orientations, with the applicable standard or low-frequency pulse form. Crash safety also includes sustained loading when applicable. Normal operational-shock acceptance is after the shocks, and any required monitoring during a pulse belongs in the equipment specification. Retention in a crash test does not establish continued display function. SLIDE 085 — CHAPTER 4 — Shock duration and ringing Provisional duration: 63 s A shock pulse is a transient, so it does not have a single vibration frequency. Its duration and shape determine how it excites different structural modes. Compare these ideal six-g terminal sawtooth pulses. Extending duration from eleven to twenty milliseconds increases the ideal pulse area, and therefore velocity change, from about zero point three two four to zero point five eight eight metres per second. Equal peak g does not mean equal response. A structure can ring at its damped natural frequencies after the input ends. DO-160G also notes that a twenty-millisecond pulse may be inadequate for some equipment with a lowest resonance below one hundred hertz, and says a one-hundred-millisecond pulse should be considered. That requires an appropriate test decision, not an automatic replacement. SLIDE 086 — CHAPTER 4 — Crash sustained loads: one table row Provisional duration: 59 s This selected row from Table seven dash one applies to fixed-wing transport aircraft with known, fixed equipment orientation. Its minimum sustained accelerations are three g up, six down, nine forward, one point five aft and four to either side. Section seven point three point three applies the appropriate loads for at least three seconds in each load direction. The directions are aircraft directions. A rotated display installation needs the corresponding equipment-axis interpretation. The table separately addresses unknown or random orientations and other aircraft types. Its caution says the listed levels may not satisfy the installation requirements in the regulations. Use this excerpt to understand the load definition, then check the actual aircraft and installation basis. SLIDE 087 — CHAPTER 4 — Monitoring the display response Provisional duration: 54 s Place the control accelerometer near the attachment and response sensors where the suspected modes matter. A fixture resonance or an added brace can change the result. Synchronize the acceleration record with image observation, link errors, touch events and application outputs. Look for optical flashes from cell deformation, intermittent connectors, loose fasteners and bond-edge damage. A frequency shift after exposure can indicate a stiffness or boundary-condition change, but it needs investigation. For relevant section eight procedures, the standard has a specific reading-difficulty allowance when applied input excursion exceeds half a millimetre. Preserve that provision while separately judging structural failures, electrical faults and the installation's own viewability requirements. SLIDE 088 — CHAPTER 4 — Special environments and material scope Provisional duration: 39 s Explosion proofness addresses ignition in a flammable atmosphere. It is separate from rapid decompression. Icing addresses an allocated freezing-moisture environment and its consequences for surfaces, controls and operation. Fire and flammability require their own scope and category decisions, with additional aircraft material requirements where applicable. A resin certificate does not establish every assembly or installation requirement. Record the actual formulation, thickness and configuration covered by the evidence, especially when an adhesive or optical material changes. SLIDE 089 — CHAPTER 4 — Make the applicability decision reviewable Provisional duration: 58 s For each special environment, write down the installation question before selecting a test. Could the allocated location expose the equipment to a flammable atmosphere? Is freezing moisture part of the required exposure? Which fire or flammability requirements apply to the materials and assembly? These are separate decisions. A material certificate may support a limited part of the evidence, but check the actual formulation, thickness, substrate and test configuration. Consider a change from one optical adhesive or film stack to another: identify which existing evidence still represents the construction and which assumptions need review. If the installation input is missing, record an open item and its owner. Do not treat missing information as evidence that a requirement is inapplicable. SLIDE 090 — CHAPTER 4 — Special environments: a scope record Provisional duration: 52 s Special environments need explicit decisions. For explosion proofness, determine whether the installation and equipment role bring the section into scope. For icing, establish the relevant exposure and required function. For fire and flammability, identify the applicable material or equipment requirement and its relationship to the installation certification basis. Magnetic effect concerns the effect of equipment on a magnetic compass and depends on the installed separation. A qualification matrix should name the requirement, responsible reviewer and reason for inclusion or exclusion. The phrase not applicable needs a supported installation argument, not an assumption that a cockpit display never encounters these conditions. SLIDE 091 — CHAPTER 4 — Enhancements create coupled trade-offs Provisional duration: 50 s We often improve temperature range, durability, contrast, brightness, spectral behaviour and touch capability beyond the original commercial display specification. These improvements interact. An EMI layer can change transmission and touch sensitivity. A brighter backlight can increase internal temperature. A transparent heater adds a conductive layer and a power load. Optical bonding changes interfaces, stress and pressure behaviour. Define the intended improvement, the physical limit and every affected requirement before selecting a design. Then verify the enhanced assembly over the claimed envelope. Extending the product's ambient capability does not simply change the manufacturer's limits for the unmodified component. SLIDE 092 — CHAPTER 4 — Chapter 4 complete Provisional duration: 40 s You have completed Mechanical and Special Environments. You can now distinguish sine amplitude, random acceleration PSD and shock pulse severity. Use the worked examples to trace an excitation frequency to a possible display resonance, then choose measurements that reveal its effect. The selected standard tables always need their category, installation and full procedure. Contact FPD.DEV with questions about a custom display or embedded platform. Next we continue with Power and Electrical Transients. FPD.DEV. The Future of Display and Systems Development. SLIDE 093 — CHAPTER 5 — Power and Electrical Transients Provisional duration: 27 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter 5, Power and Electrical Transients. This chapter follows the supply from the product input to the visible image and control outputs. We will examine interruptions, protection and ripple, then work through energy storage and recovery with current, valid information. SLIDE 094 — CHAPTER 5 — Aircraft power reaches the entire display Provisional duration: 40 s Follow the power path from the aircraft connector to the displayed image. A bare panel operating from a regulated five-volt bench supply does not exercise the aircraft-facing converter or protection. Section sixteen addresses power input, section seventeen voltage spikes, and section eighteen audio-frequency conducted susceptibility on power inputs. Audio frequency here describes an electrical disturbance, not loudspeaker sound. Test the allocated interfaces and modes, then observe resets, corrupted imagery, false controls, configuration retention and recovery against the agreed criteria. SLIDE 095 — CHAPTER 5 — Aircraft and vehicle power requirements Provisional duration: 37 s Military aircraft power requirements often invoke MIL-standard-seven-oh-four. The supporting handbook series provides test guidance. Compare the invoked characteristics with DO-one-sixty section sixteen and retain separately allocated electrical tests. Seven-oh-four excludes EMI and voltage spikes from its scope. A ground-vehicle derivative may instead need MIL-standard-twelve-seventy-five input-power characteristics. The shared twenty-eight-volt label does not make those interfaces equivalent. Compare disturbances at the display input terminals and observe the required operating and recovery behavior. SLIDE 096 — CHAPTER 5 — Power stimulus and electrical monitoring Provisional duration: 38 s The bench photograph shows an oscilloscope, a multimeter and a power supply. These instruments illustrate stimulus and electrical monitoring. A complete qualification setup also needs the specified disturbance source, sensing arrangement and measurement capability. Capture what reaches the display input and connect that trace to image behavior, resets, touch outputs and recovery. This photograph is general laboratory context. Its presence does not establish that the pictured bench meets a DO-one-sixty or military test procedure. SLIDE 097 — CHAPTER 5 — Power qualification at the display input Provisional duration: 52 s Begin at the input terminals of the product being qualified. Identify the applicable AC or DC supply and the category required for the installation. A display module supplied by a laboratory regulator is a different boundary from a complete unit containing its own aircraft power converter. Include the loads that can operate together, especially the backlight, heater and processing electronics. Cable impedance and current demand can change the waveform that reaches the unit, so verify the applied stimulus at the relevant measurement point. Use the connections and source conditions required by the adopted method. Preserve those details in the test record. SLIDE 098 — CHAPTER 5 — Interruptions, brownouts and restart Provisional duration: 52 s When supply voltage falls, the processor, backlight and interface circuits may stop at different times. A brief dark screen is one possible result, but a frozen image that appears valid can be more misleading. Define the required behaviour for the applicable interruption and voltage conditions before testing. Monitor internal rails where useful, the data link, visible image and any command output. Measure recovery from the specified reference point and verify that the displayed data is current. Also check retained settings and the restart state. The acceptance decision must address the complete required function rather than merely confirming that power eventually returns. SLIDE 099 — CHAPTER 5 — Hold-up energy: an initial estimate Provisional duration: 51 s For an initial estimate, suppose a twenty-watt load needs twenty milliseconds of hold-up while a capacitor falls from twenty-eight to eighteen volts. Equating load energy to the change in stored capacitor energy gives C equals two P t divided by the difference of the squared voltages. The ideal result is about one thousand seven hundred and forty microfarads. This excludes conversion loss, capacitor tolerance, ESR, ageing and the actual converter input limit. It also says nothing about recharge inrush. Use it to start the engineering analysis, then verify the real waveform and recovery behaviour with the selected power-input tests. SLIDE 100 — CHAPTER 5 — Voltage spikes and input protection Provisional duration: 53 s An input clamp limits voltage by diverting current, so its behaviour depends on the applied pulse, source impedance and physical current path. A protection component's catalogue rating alone does not describe the residual voltage at a downstream converter. Wiring inductance and layout can add voltage excursions. Follow the selected voltage-spike method and verify the applied stimulus as required. During development, measure the relevant protected node without allowing the probe arrangement to change the result. After the prescribed exposure, evaluate function and any latent change in the protection path. Keep this evidence separate from lightning transient qualification, which uses different methods and exposure definitions. SLIDE 101 — CHAPTER 5 — Audio-frequency ripple on power Provisional duration: 50 s Audio-frequency conducted susceptibility concerns interference imposed on the power input. A supply converter may reject some frequencies more effectively than others, and ripple can reach a backlight driver or a sensitive reference. Follow the selected section's injection and monitoring method rather than substituting arbitrary ripple from a bench supply. Exercise representative high-load and sensitive operating modes. Observe image modulation, touch events and communication errors while correlating them with the applied frequency and level. If a disturbance occurs, record its threshold and recovery as investigation data while retaining the required qualification result at the prescribed test conditions. SLIDE 102 — CHAPTER 5 — Heater and backlight load transitions Provisional duration: 53 s The highest average power mode is not automatically the most sensitive electrical mode. Cold start may combine heater demand with backlight start-up and processor initialization. A low-brightness mode can introduce a different switching pattern or make a small luminance fluctuation easier to see. Prepare a mode matrix showing the functions exercised, power demand and reason for selecting each case. Include credible simultaneous loads and transition states required by the product. Use development measurements to identify likely worst cases, then document the rationale for the formal test configuration. This prevents a convenient nominal mode from silently standing in for the full operating envelope. SLIDE 103 — CHAPTER 5 — Worked case: recovery with stale data Provisional duration: 52 s A display restarts within the example project's permitted recovery time, but its map position remains frozen for three seconds without an invalid-data indication. The power supply recovered, yet the end function has not necessarily met its requirement. Record input voltage, restart indication, received data timestamps and displayed updates on a common timeline. Review the requirement for data validity and annunciation, then classify the result accordingly. Possible corrections include interface restart handling or invalid-data indication, depending on the system design. The corrected unit needs the affected interruption and recovery checks again. A screenshot taken only after recovery would have missed the issue. SLIDE 104 — CHAPTER 5 — Chapter 5 complete Provisional duration: 23 s You have completed Power and Electrical Transients. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Next we continue with EMC, Lightning and ESD. FPD.DEV. The Future of Display and Systems Development. SLIDE 105 — CHAPTER 6 — EMC, Lightning and ESD Provisional duration: 25 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter 6, EMC, Lightning and ESD. We will follow interference through the enclosure, optical window and cables. The worked cases connect susceptibility, emissions, lightning and electrostatic discharge to the actual display configuration and its required functions. SLIDE 106 — CHAPTER 6 — Emissions and susceptibility Provisional duration: 40 s Susceptibility asks how the display responds to interference. Emissions asks what interference the display produces. Section fifteen also addresses magnetic effect, and section nineteen covers induced signal susceptibility. The complete enclosure, conductive coatings, shield terminations and cables affect the result. Maximum brightness may be the hottest mode, while another dimming mode produces worse electrical interference. Choose modes for each hazard. A static logo can hide a frozen image, so use controlled changes and synchronized observation to detect failures. SLIDE 107 — CHAPTER 6 — Equipment EMC and aircraft HIRF Provisional duration: 44 s Equipment RF testing contributes to HIRF substantiation, but the aircraft relationship still needs evidence. The external field, the field at the display and the current induced in its harness are different quantities. A metal enclosure alone does not establish cockpit attenuation. The applicable guidance includes a scoped approach for eligible Level A display systems, with airplane and rotorcraft distinctions. Use it within the accepted compliance plan. Also assess installed compatibility with relevant transmitters, receivers and loads. Those checks have a different purpose from repeating a laboratory exposure. SLIDE 108 — CHAPTER 6 — Equipment EMI and system E3 Provisional duration: 34 s MIL-standard-four-sixty-one addresses equipment and subsystem EMI. MIL-standard-four-sixty-four addresses electromagnetic environmental effects at the system level. Compare the allocated equipment methods with the relevant DO-one-sixty requirements, including test setup, limits, frequency coverage, modulation and acceptance. A radiated emissions result cannot stand in for susceptibility. Equipment evidence also leaves aircraft integration questions. Keep the military system allocation and civil HIRF or lightning compliance basis explicit where both apply. SLIDE 109 — CHAPTER 6 — Coupling paths through the installation Provisional duration: 51 s Interference reaches a display through physical paths. It can couple onto a cable, pass through an enclosure aperture or share impedance with a sensitive return. The optical window is part of that enclosure boundary, and its conductive layer needs an effective connection if it is intended to provide shielding. Cable shield termination, connector backshells and chassis bonding matter as a system. Record the actual construction and routing used for the test. A successful test with temporary foil, an extra bonding strap or a shorter cable does not support the unmodified production configuration unless those differences receive a justified disposition. SLIDE 110 — CHAPTER 6 — Induced signals and RF susceptibility Provisional duration: 50 s Several methods can exercise the same cable for different reasons. Induced-signal susceptibility under Section nineteen and radio-frequency susceptibility under Section twenty have distinct setups and test conditions. Select the applicable categories and follow the prescribed coupling, calibration and monitoring arrangements. During a sweep, run the display through functions that reveal the relevant susceptibility, including communication and touch where fitted. Log the applied frequency, level and mode with the observed event. Do not treat completion of one cable-related method as completion of every susceptibility requirement. A qualification matrix should keep each method and its evidence independently traceable. SLIDE 111 — CHAPTER 6 — Emissions depend on mode and harness Provisional duration: 51 s Emission testing examines what the equipment puts onto its connections or radiates into the environment. A display's spectrum can change with pixel activity, processor load, interface traffic and backlight dimming. Choose modes with a documented rationale and preserve the specified harness arrangement, terminations and measurement geometry. Confirm that the laboratory applies the required detector, bandwidth and correction factors for the selected method. Investigate an emission by correlating it with operating state before changing hardware. Any remedy, such as a filter or shielding layer, can also affect susceptibility, power behaviour or optical performance and needs an appropriate change-impact review. SLIDE 112 — CHAPTER 6 — A trustworthy EMC monitoring channel Provisional duration: 50 s The monitoring setup must function in the test environment without creating an unintended interference path. An added copper cable can change emissions or susceptibility. A camera can lose its link while the display continues to work. Plan suitable isolation, routing and monitoring methods with the laboratory, and verify that they can detect the events covered by the acceptance criteria. For a claimed fifty-millisecond interruption limit, for example, a slow status poll alone cannot establish compliance. That number is an illustrative project criterion. Correlate independent observations where practical, and preserve evidence whenever the monitoring chain itself becomes uncertain. SLIDE 113 — CHAPTER 6 — Worked case: touch commands during RF Provisional duration: 55 s During an illustrative RF sweep, a touch display issues an unintended command near one frequency even though the image remains stable. Preserve the frequency, field or injection level, modulation, operating mode and configuration. Correlate raw touch reports with application commands and the monitoring record. Investigate the coupling path through the cover, touch flex, cable shields and supply. A sensitivity adjustment that eliminates false touches may also reduce glove or edge performance. After a corrective change, repeat the affected susceptibility evaluations and the relevant touch acceptance tests. The final report should connect the symptom, design change and verification rather than simply replacing the failed run with a pass. SLIDE 114 — CHAPTER 6 — Lightning capability and installed exposure Provisional duration: 43 s Lightning-induced transients and direct strike effects require separate allocation. For an interior display, the relevant paths can include power wiring, signal bundles, shields and structural bonds. The margin illustration relates installed exposure to equipment capability. It only makes sense when the waveform, coupling path and measured quantity correspond. A voltage test level cannot be compared directly with an unrelated current peak. Passing a test also does not locate the actual upset or damage threshold. Preserve the aircraft assumptions and the equipment test evidence together. SLIDE 115 — CHAPTER 6 — Lightning level selection has a scope Provisional duration: 43 s The FAA table used in the reading belongs to the LCL A display framework. It is not a universal selection table for every display. Its installation conditions include the equipment, associated wire bundles and connected equipment. An interior metallic fuselage location cannot justify the most protected condition if wires leave that region without the required protection. Use the complete guidance and your accepted compliance method to connect the allocated transient threat to the equipment tests. Assign responsibility for closing any gap between supplier and integrator. SLIDE 116 — CHAPTER 6 — ESD includes control-output behavior Provisional duration: 40 s Map the surfaces a person can access in the installation. The glass, bezel and controls can direct discharge energy through different paths. DO-160G section twenty-five uses its air-discharge method and excludes connector-pin testing. A component handling rating answers a different question. Monitor the control output as well as the image: one unintended touch can be significant even when the display stays bright. Record locations, polarity, operating mode and events, using the production construction and the prescribed test arrangement. SLIDE 117 — CHAPTER 6 — Lightning evidence follows the interface Provisional duration: 53 s Lightning-induced transient qualification begins with the installation exposure allocated to the equipment interfaces. The applicable waveform sets, levels and methods need to match that allocation. Cable construction, shield termination and return paths influence the transient that reaches the electronics. The equipment report supplies evidence within its tested scope, while the aircraft assessment must establish that the installation is covered. FAA AC twenty dash one thirty-six C addresses aircraft electrical and electronic system lightning protection. It does not make an equipment label a complete aircraft compliance demonstration. Record the installation assumptions alongside the test evidence and revisit them when the harness or bonding changes. SLIDE 118 — CHAPTER 6 — Pin injection and cable methods Provisional duration: 52 s Section twenty-two separates two groups of tests. Pin injection assesses damage tolerance at the specified interfaces. Cable bundle tests assess functional upset tolerance and can also reveal damage. Their single-stroke, multiple-stroke and multiple-burst exposures have distinct purposes. The selected procedure determines connections, calibration and monitoring. A pass on one method does not establish every other method or waveform combination. During development, understand where protection current flows and which circuitry sees residual stress. In qualification, retain the applied conditions, configuration and acceptance results. Include the required functional checks and inspections so the evidence addresses the purpose and scope of the selected test. SLIDE 119 — CHAPTER 6 — Direct effects and induced transients Provisional duration: 52 s Direct lightning effects and induced electrical transients are separate subjects. An externally exposed assembly may have direct-effects requirements that differ from the induced transients allocated to its internal electronics. A protected cockpit display can still receive transients through its wiring without being directly attached by the lightning channel. Establish the applicable installation exposure and the boundary of the equipment being evaluated. Record a reasoned applicability decision for each section. Do not generalize a Section twenty-two result into a statement that the complete installation withstands direct lightning. Keep the aircraft protection assessment and the equipment test report connected but separately scoped. SLIDE 120 — CHAPTER 6 — ESD at the operator interface Provisional duration: 53 s Section twenty-five addresses air discharges at human-contact points accessible during normal operation or maintenance, including connector shells but excluding connector pins. Use the prescribed procedure with the actual mounting, bonding and grounding configuration. Record the discharge conditions and the display's response. A brief flash, reset, false touch and corrupted saved setting have different consequences, so define their acceptance before testing. Exercise the required modes and make the required performance checks after the pulses. Any additional requirement for uninterrupted function during exposure belongs in the equipment specification. Preserve the configuration when investigating an unexpected discharge path, and distinguish exploratory testing from the formal qualification sequence. SLIDE 121 — CHAPTER 6 — Protection changes and residual risk Provisional duration: 53 s Adding protection is a design change with consequences beyond the failed test. A suppressor can add capacitance to a high-speed interface or leakage to a sensitive circuit. A new conductive layer can alter touch sensitivity and optical transmission. A bonding strap changes where transient current flows and can also alter emissions. Review the complete change against the requirement and evidence matrix. Identify which results remain applicable and which need analysis or retest. The goal is a configuration that satisfies the whole set of requirements, with a documented basis for retained evidence, rather than a collection of unrelated fixes that each passed one laboratory setup. SLIDE 122 — CHAPTER 6 — Chapter 6 complete Provisional duration: 31 s You have completed EMC, Lightning and ESD. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Next we continue with Integration and Qualification Practice. Need a subject matter expert? Contact Colabmo. There is a good chance we have one for you. FPD.DEV. The Future of Display and Systems Development. SLIDE 123 — CHAPTER 7 — Integration and Qualification Practice Provisional duration: 26 s FPD.DEV. The Future of Display and Systems Development. Welcome to Chapter 7, Integration and Qualification Practice. We will turn the measurements into a qualification package someone else can review. The chapter develops acceptance records, measurement decisions, specimen history and change control, then applies them to a constrained display design. SLIDE 124 — CHAPTER 7 — The installed display Provisional duration: 40 s Installation verification closes the assumptions behind the equipment evidence. Check the brackets, ventilation, power, cable routing, bonds and shield terminations. Then evaluate the display from the intended eye positions with the relevant lighting, reflections, dimming and controls. A high on-axis contrast measurement at room temperature does not establish installed readability. Ground tests, flight tests, analysis and similarity follow the program's accepted compliance method. The transport-airplane display circular has a defined scope; rotorcraft programs need their applicable basis and guidance. SLIDE 125 — CHAPTER 7 — Display performance and crew use Provisional duration: 36 s Environmental capability is only part of a display specification. An invoked AS-eight-oh-three-four edition contributes airborne display-performance requirements. MIL-standard-three-thousand-nine addresses display and lighting emissions for use with NVIS. MIL-standard-fourteen-seventy-two supplies military human-engineering criteria. Determine which requirements actually apply. Connect optical, spectral, dimming and crew-use criteria to the acceptance plan, including checks during or after exposure when required. A temperature or vibration pass alone does not establish those separate performance claims. SLIDE 126 — CHAPTER 7 — Development assurance and installation Provisional duration: 35 s Software and electronic hardware require their applicable development-assurance evidence under the accepted program plan. DO-one-seventy-eight-C and DO-two-fifty-four address those scopes. The ARP-forty-seven-fifty-four and forty-seven-sixty-one families support system development and safety assessment. These activities help allocate functions, failure consequences and verification. Select the applicable revisions through the program basis. Environmental test results contribute to the overall argument, while interface-control documents, installed verification and approval requirements still need closure. SLIDE 127 — CHAPTER 7 — Qualification, production and service life Provisional duration: 42 s Environmental qualification belongs inside a wider verification program. Sunlight readability, UV aging, touch with gloves, cleaning abrasion, image retention and NVIS may need explicit additional requirements. Production acceptance checks the delivered units. Development stress tests and environmental screening serve other purposes. Passing a short environmental exposure does not establish ten years of service life. A duration claim needs a mission profile, relevant aging mechanisms and appropriate analysis or testing. Keep the purpose of each activity visible in the contract and evidence record. SLIDE 128 — CHAPTER 7 — Readability and spectral performance Provisional duration: 52 s A bright module measured normal to its surface does not describe every pilot's view through the installed cover. Establish the required viewing envelope, ambient illumination and dimming range for the application. Evaluate colour and information discrimination as well as luminance and contrast. Spectral filters, touch layers, EMI shields and heaters can all change the light reaching the observer. Where NVIS compatibility is required, use the applicable spectral criteria and operating modes rather than inferring compatibility from visible colour or low brightness. Measure the final optical assembly and preserve the conditions so an enhancement claim has a clear and repeatable scope. SLIDE 129 — CHAPTER 7 — Operating envelope and product claims Provisional duration: 52 s The product specification should say what the enhanced display actually does at each boundary. A cold ambient start with a defined warm-up period differs from immediate full performance. A temporary reduction in brightness at high temperature may be acceptable for one application and unacceptable for another. Define the permitted modes, duration and required indications, then verify them. Identify the assembly configuration, mounting, power and environmental conditions behind the claim. This makes it possible to offer capabilities beyond the original commercial module specification while acknowledging physical limits and qualification scope. Marketing language should follow those measured capabilities and the approved product requirements. SLIDE 130 — CHAPTER 7 — The test contract buys evidence Provisional duration: 42 s Two quotations can both say DO-160 and include very different work. One may buy chamber time and a certificate. Another may include procedures, raw traces, functional data, configuration records and anomaly disposition. Compare them against the same matrix before comparing price. Define article allocation, sequence, witness or conformity arrangements where required, and who can authorize deviations. Allocate retest costs and data rights. The commercial agreement should make the technical evidence deliverable clear without implying that a laboratory certificate resolves every aircraft requirement. SLIDE 131 — CHAPTER 7 — Closing a qualification matrix row Provisional duration: 40 s Return to the matrix we started in Chapter 1. A row is ready to close only when the evidence supports the current configuration and requirement. An earlier vibration report may be valid evidence, while credit for a changed bracket remains unresolved. Record that distinction. Trace the row to the procedure, raw data and report location. Include deviations and the accepted disposition. Carry forward limits on mounting, cooling, power and wiring so the integrator can preserve the demonstrated conditions. SLIDE 132 — CHAPTER 7 — A test-ready requirement record Provisional duration: 49 s A test-ready record connects the requirement to a measurement and a decision. For an illustrative hot-contrast row, name the assembly and mode, specify panel temperature and ambient illumination geometry, define white and black measurements, and state the minimum ratio with the decision rule. Link the procedure, instrument identification and uncertainty treatment. Add the result and the evidence location after execution. The adopted standard supplies the environmental method where applicable, while the product requirement supplies the functional acceptance criterion. Keeping those roles visible prevents a laboratory profile from being mistaken for a complete display performance specification. SLIDE 133 — CHAPTER 7 — Measurement uncertainty at acceptance Provisional duration: 52 s A measured value close to a limit needs a defined decision rule. Calibration uncertainty is one contribution, but optical alignment, source stability and repeatability can matter too. Agree how the laboratory will report uncertainty and apply it to the acceptance decision before the test. In an illustrative conservative rule, a contrast ratio of five point one with an expanded uncertainty of zero point three does not establish a minimum of five if acceptance requires the lower bound to exceed the limit. Other agreed rules can differ. State the rule explicitly and keep it separate from the environmental standard's prescribed test tolerances. SLIDE 134 — CHAPTER 7 — Test sequence and specimen history Provisional duration: 52 s Specimen history affects how a result can be interpreted. A seal already exposed to fluid, a connector repeatedly mated or an enclosure repaired after shock may behave differently from a new assembly. Establish the specimen allocation and test sequence using the applicable requirements and the agreed qualification plan. Record every exposure, adjustment and repair. If several specimens share the campaign, identify which configuration and serial number supports each matrix row. Avoid assembling a single clean pass narrative from different untracked units. The report must let a reviewer see both the required evidence and any limitations caused by sequence or specimen changes. SLIDE 135 — CHAPTER 7 — Changes and anomalies Provisional duration: 40 s A touch-controller change can affect emissions, ESD response, power loading and false-control behavior even when the image looks unchanged. Record the old and new configuration, identify affected mechanisms, and map them to requirements and existing evidence. Decide what can be credited and where testing is needed. If a cold-start failure receives a firmware fix, a room-temperature pass does not close the cold requirement. Retain the original failure and connect it to the correction, regression work and final disposition. SLIDE 136 — CHAPTER 7 — Worked example: changing the cover glass Provisional duration: 58 s Suppose you add bonded cover glass to protect an exposed polarizer. That may address a known moisture problem, but it also changes the product configuration. Record the glass, coatings, adhesive, thickness, mass and edge construction. Review optical transmission and reflections, thermal mismatch and heat flow, touch operation, and the mounting response to the added mass. Consider trapped voids and pressure equalization as well. This is a change-impact review, not a claim that every listed effect will require a full retest. Compare each affected requirement with the existing evidence, document the basis for any retained credit, and plan the missing verification on a representative assembly. Preserve the original configuration and results so another engineer can reconstruct the decision. SLIDE 137 — CHAPTER 7 — An anomaly record preserves the event Provisional duration: 51 s An anomaly record should begin with what happened, when it happened and the conditions at that moment. Record the specimen, software, operating mode and applied exposure. Keep an observation such as a two-frame flash separate from a proposed cause such as cell deformation. Preserve raw data, photographs and logs before repeating the test. During investigation, document each configuration change and its purpose. Once the cause and correction are understood, agree the affected retest scope and update the requirement matrix. A later successful run adds evidence, but it does not remove the need to explain and disposition the original anomaly. SLIDE 138 — CHAPTER 7 — A change-impact review across disciplines Provisional duration: 52 s Replacing a transparent heater can change more than cold performance. Its resistance and controller behaviour affect power demand. Its optical transmission and busbars affect the visible image. Its conductive structure can alter touch sensing and electromagnetic behaviour, and its bonding process can affect mechanical stress. Compare the old and new configurations against each relevant requirement and existing result. Document why an item remains covered or needs further evidence. A supplier's statement that the part is equivalent helps define the comparison but does not replace it. Close the review only when the resulting analysis, inspection or retest supports the revised assembly. SLIDE 139 — CHAPTER 7 — Capstone: the bonded touch display Provisional duration: 42 s Now apply the method. Our teaching display has a bonded cover, touch sensor, graphics processor, backlight, heater and metal enclosure. It uses nominal twenty-eight-volt aircraft power and an internal five-volt panel rail. The proposed location is a pressurized flight deck with four mounts and specified conduction plus local airflow cooling. These are scenario assumptions. The customer has temperature requests and an incomplete decompression statement, while power, vibration, RF and lightning allocations remain open. Your first job is to identify what you still need. SLIDE 140 — CHAPTER 7 — Capstone deliverables Provisional duration: 56 s Build the package in the same order as the course. Define the boundary and give missing inputs an owner. Screen all twenty-three sections and identify the information needed to finalize categories. Write cold-operation and temperature-variation outlines, preserving power state, stabilization and timing. Specify measurable display behavior and the monitoring needed to detect it. Finally, list the supplier deliverables and installation checks. The outcome is a reviewable plan, not a claim that testing has occurred. Pause here and complete the worksheets before viewing the response. In the mounting review, identify one thermal mismatch, one trapped-air volume and one vibration load path. Define how you will observe image quality and verify the proposed control. SLIDE 141 — CHAPTER 7 — Capstone review points Provisional duration: 41 s A strong response preserves the customer's temperature requests but checks their relationship to the selected category. It calculates the twenty-two-minute ideal ramp at five degrees per minute without calling that the full test duration. It asks why the decompression endpoint is sixty-five thousand feet and resolves the complete profile. It also refuses to invent missing power, RF, lightning or vibration categories. We, we keep those inputs open with named owners. The plan becomes stronger when its unresolved assumptions are explicit. SLIDE 142 — CHAPTER 7 — Second application: a helicopter Provisional duration: 42 s Propose the same display for an assumed unpressurized helicopter installation. Revisit the environment, mount and harness rather than carrying over the airplane assumptions. Isolators can improve mechanical behavior while changing the electrical bond path. Ask for the rotational-frequency basis and location-specific vibration information. Reassess EMC, HIRF, lightning, cooling and crew use. Your output is a comparison showing what evidence remains applicable, what additional work is needed, and which inputs are unresolved. This scenario is not a specification for the helicopter shown earlier. SLIDE 143 — CHAPTER 7 — Capstone: a military derivative Provisional duration: 38 s Now give the display an assumed military-aircraft application. Build the standards map before choosing tests. Consider tailored environmental exposures, equipment EMI, aircraft power and NVIS when the customer invokes them. Select one existing report and show exactly what it supports and what remains open. Then consider a military ground-vehicle derivative. Revisit power, vibration, mounting and crew use. Your deliverable is a justified comparison with owners for missing inputs, not a list of military-standard logos. SLIDE 144 — CHAPTER 7 — Capstone: a constrained design choice Provisional duration: 52 s For this capstone, assume a customer needs a readable cockpit display in bright ambient light, operation after cold soak, touch input and a fixed mounting envelope. The power budget limits heater and backlight demand. These are teaching assumptions rather than universal aviation requirements. Propose two optical and thermal configurations, then compare how each affects hot contrast, cold motion, power, EMC and mechanical behaviour. Identify the measurements needed to resolve the trade-off before choosing one. Record the uncertainties that remain and assign evidence to them. The exercise rewards a defensible decision and a coherent qualification plan, not simply the highest catalogue brightness. SLIDE 145 — CHAPTER 7 — Capstone review: what earns acceptance Provisional duration: 52 s Review the capstone as if you were accepting a supplier's qualification package. Can another engineer reproduce the test conditions and understand the decision? Does the hot-contrast claim include ambient illumination and panel temperature? Does the cold case address moving information and warm-up? Do the power and susceptibility cases include valid data and unintended commands? Check that changes to the optical stack connect to mechanical and electrical evidence. List unresolved items with an owner and a specific closure condition. A justified open item is preferable to an unsupported pass. Use the model response in the reading page to challenge your own reasoning. SLIDE 146 — CHAPTER 7 — Knowledge check Provisional duration: 42 s Pause and answer these three questions with a reason, not just yes or no. Does a panel temperature report cover the complete display? Does an unpowered survival result prove operation at that temperature? Does a radio-frequency emissions pass close aircraft HIRF compliance? For each one, name the missing boundary or evidence. The online course retains its fourteen formative questions with explanations. Use the results to revisit the corresponding matrix rows and capstone decisions rather than treating a score as a qualification certificate. SLIDE 147 — CHAPTER 7 — Knowledge check: the evidence gaps Provisional duration: 42 s The panel report can support its defined component scope, subject to a comparison. It cannot establish the complete aircraft interface or assembly response. The survival result supports its prescribed exposure and evaluation, not continuous operation. And emissions measures interference produced by the display, while susceptibility and aircraft HIRF involve different tests and installation evidence. The common lesson is to connect the claim to the function, exposure, configuration and supporting result. When one part of that connection is missing, keep the conclusion open. SLIDE 148 — CHAPTER 7 — Standards knowledge check Provisional duration: 36 s Pause and answer three questions. Can a military high-temperature storage pass automatically satisfy a DO-one-sixty operating requirement? Which standards distinguish equipment EMI from system electromagnetic effects? Does using the same chamber establish equivalent tests? Explain the missing evidence in each answer. Use the standards worksheet to trace a claim to the source, configuration, exposure and acceptance. The additional course questions provide feedback after you have made your own comparison. SLIDE 149 — CHAPTER 7 — Standards review: evidence and scope Provisional duration: 34 s The storage result leaves powered operation unproven. Four-sixty-one and four-sixty-four address equipment and system concerns respectively. And the same chamber can run very different profiles, configurations and checks. Test equipment is a means of applying and measuring the required exposure. It does not define the requirement. A sound comparison identifies supported evidence and remaining gaps, then records the program's acceptance of any proposed shared credit. SLIDE 150 — CHAPTER 7 — Chapter 7 complete Provisional duration: 30 s You have completed Integration and Qualification Practice. Use the supporting reading pages to work through the examples and record the evidence you would need for your display. Keep the requirements, configuration and evidence connected as the product changes. You are welcome to bring questions about your project to FPD.DEV. FPD.DEV. The Future of Display and Systems Development. SLIDE 151 — CHAPTER Glossary — Course glossary Provisional duration: 19 s FPD.DEV — The Future of Display and Systems Development. Welcome to the course glossary. I am Diggy Breiling. We will review qualification and evidence terms, environmental and interface terms, and materials and mounting terms. SLIDE 152 — CHAPTER Glossary — Glossary: qualification evidence Provisional duration: 38 s The equipment under test is the defined article and its relevant interfaces. The Environmental Qualification Form summarizes environmental qualification coverage and points toward the supporting evidence. Configuration includes more than a part number: hardware, software, mounting, cooling, cables and operating settings can all affect a result. Qualification credit is the justified use of existing evidence for an identified requirement and configuration. These terms help keep a concise summary connected to the detailed engineering record. SLIDE 153 — CHAPTER Glossary — Glossary: environments and interfaces Provisional duration: 35 s Electromagnetic compatibility covers the equipment's behavior in its electromagnetic environment and the disturbances it generates. HIRF concerns high-intensity radiated fields in the applicable aircraft compliance framework. ESD concerns electrostatic discharge. NVIS is pronounced en-vis and refers here to night vision imaging systems. NVIS compatibility, where required, needs its own defined display and lighting criteria. These terms identify different concerns. One successful test cannot silently close the others. SLIDE 154 — CHAPTER Glossary — Glossary: timing, pressure and margin Provisional duration: 39 s Stabilization is the defined condition used by the applicable procedure, not simply the moment the chamber display reaches its setpoint. Absolute pressure uses vacuum as its reference. For lightning, ATL means actual transient level and ETDL means equipment transient design level. Compare them only for corresponding waveforms, paths and quantities under the adopted framework. Keep these distinctions beside your qualification matrix. They are small wording differences that can change the meaning of an entire test claim. SLIDE 155 — CHAPTER Glossary — Materials and mounting terms Provisional duration: 44 s C T E means coefficient of thermal expansion. It describes fractional dimensional change per degree. Adhesive failure occurs at an interface. Cohesive failure occurs within a material. Cell gap refers to the liquid-crystal layer inside the sealed LCD, separately from the external optical bond thickness. Transmissibility compares response with excitation for a specified quantity and frequency. A value greater than one means amplification. Always state the measurement locations, axis and quantity. These terms help connect a test observation to a mechanism and a controlled design change. SLIDE 156 — CHAPTER Glossary — Glossary complete Provisional duration: 20 s Use these definitions when reviewing your qualification plan. Check the adopted standards and close the remaining evidence gaps. I am Diggy Breiling. Thank you for joining me. FPD.DEV — The Future of Display and Systems Development.