Passive Attack Display System rev7.docx

PASSIVE ATTACK DISPLAY (PAD)

System Requirements

1. INTRODUCTION

1.1 Scope

This specification defines the design, performance and compatibility requirements for the Passive Attack Display (PAD) for installation in the USAF F-15C/D model aircraft.

2. REFERENCED DOCUMENTS

2.1 Government Documents

MIL-STD-704A Aircraft Electric Power Characteristics Notice 1

MIL-STD-1553B Digital Time Division Command/Response Multiplex Data Bus, Interface Standard Notice 1

MIL-STD-3009 Lighting, Aircraft, Night Vision Imaging System (NIVS) Compatible

2.2 Customer Documents

2.3 Industry Documents

EIA RS-170A Video Timing Specification, Electronics Industries Association

A5690 (Rev. C) F-15 Avionics Multiplex Design Specification Commensurate with MIL-STD-1553B

MDC A7968

MCAIR Report H417

MDC Report A4246

MDA Report G667

Boeing Report MDC 97X0011

3. REQUIREMENTS

The equipment specified herein shall be designed in accordance with the requirements of this specification, including requirements covering all operating, non-operating, and storage conditions. The equipment shall meet performance, compatibility and all other requirements of this specification while installed in a complete airplane, during both ground and airborne operations, provided the environment in the airplane is no more stringent than that specified herein.

3.1 Item Definition

The PAD consists of one Line Replaceable Unit (LRU) that provides a 8x6 inch viewing area Active Matrix Liquid Crystal Display (AMLCD) screen in landscape format providing a 1024x768 resolution that is compatible with the F-15C/D Night Vision Imaging System (NVIS) in accordance with MIL-STD-3009. The PAD shall provide the capability to display three separate NTSC video sources (vid1, vid2, vid3) in EIA RS-170A format, in a 1:1 aspect ratio, on its display simultaneously. The PAD shall also generate and present symbology, either independently or overlaid on the vid1 video source, derived from external serial and discrete signals defined herein. In addition, the PAD shall have a minimum of 24 peripheral push-buttons that permit pilot interaction with other aircraft systems via a MIL-STD-1553B interface. Throughout this specification the word “display” may be used interchangeably with PAD.

3.1.1 Interface Definition

The PAD interface signals are shown below. Each interface shown in the block diagram is documented in a separate section below. Each section contains an overview of the signals described in that section, and detailed descriptions of the signals.

3.1.1.1 Interface Compatibility

The PAD shall be compatible with the equipment listed below, and shall meet all requirements when installed in the F-15C/D aircraft and operated in conjunction with the associated equipment. Such associated equipment is not to be supplied as part of the PAD covered by this specification. The performance of the PAD shall not be affected when any of the associated equipment is turned off or not installed in the aircraft, except for those functions of the PAD dependent upon input signals from the associated equipment. The PAD shall not be damaged by operation of the associated equipment when in any mode of operation (including OFF mode); nor shall the PAD be damaged in any mode of operation when any or all of the associated equipment are partially or wholly disconnected from the PAD. The performance of the associated equipment shall in no way be degraded, or interfered with, by operation of the PAD.

3.1.1.1.1 Associated Equipment

PS68-870164 Programmable Signal Data Processor PS68-870072 BIT Control Panel List all associated equipment & specs here

3.2 Characteristics

3.2.1. Display Physical Characteristics

The display shall provide an 8x6 inch viewing area Active Matrix Liquid Crystal Display (AMLCD) screen in landscape format providing a 1024x768 resolution. The display bezel shall have a minimum of 28 peripheral push-buttons arranged and with the spacing as shown below. There are two types of buttons shown: single-action push-buttons and dual-action rockers.

3.2.1.1 Bezel Push-Button Numbering

Peripheral push-button numbering shall begin on the top of the left hand side with button 1 and proceed counterclockwise around the display, ending up with push-button 24. Two bezel buttons, 14 and 17, will have constant legends next to them overlaid onto whatever window is currently present. The legend for button 14 shall be “EMD” and for button 17 shall be “RWR”; functions for these buttons are described in later paragraphs. The rocker switches are not numbered; they are to be used for controlling display functions.

3.2.1.2 Bezel Rocker Switch Functions

The switch on the top row is to be used to turn on the display (right side) and toggle between day/night brightness modes (left side). The top switch on the right side is to be used to control the brightness of the display (top side increases brightness). The bottom switch on the right side is to be used to declutter the radar warning receiver (RWR) symbology (see description of symbology in appendices B and C) with the top side of the switch; the bottom side of the switch toggles between the screen formats (see paragraph 3.2.7 for description of screen formats). The left side of the switch on the bottom row is to be used to select one of the displayed windows (identified with a bright green border), and the right side is to be used to select the video source to be shown in that window. These buttons may have symbology printed on them to provide instant identification of their functions.

3.2.2 Aircraft Power and Panel Lighting

3.2.2.1 Aircraft Power

The equipment shall meet all specified requirements of MIL-STD-704 for the types of power specified herein, and shall give specified performance when supplied with electrical power having characteristics and limits as defined in MIL-STD-704, Category B.

Aircraft +28 VDC in accordance with MIL-STD-704A will be supplied to the PAD as the only source of external power. The PAD shall generate all other necessary operating voltages internally.

3.2.2.1.1 Electrical Power Interruptions

The PAD shall recover and return to the original performance state within 5 seconds after a power interruption of up to 100 milliseconds, with up to 500 milliseconds being a design objective.

3.2.2.2 Panel Lighting

A master cockpit dimmer circuit provides 0-5 VAC for panel edge light control. Illumination of all control switch legends and panel markings shall be provided by an integrally illuminated, lighted panel of class 1-NVIS, type VII in accordance with the requirements of SAE AS7788 with the following exception, all references to NVIS Class A and MIL-L-85762 in SAE AS7788 shall be interpreted to mean NVIS Class C and MIL-STD-3009.

The panel markings shall be white (un-illuminated) and green (night vision imaging system (NVIS) compatible) when illuminated.

The dimming, visual properties and luminance versus voltage curve for a SAE AS7788, Type VII (LED) lighting must be equivalent to MIL-P-7788F, Type V.

3.2.3 MIL-STD-1553B Interface

The PAD shall provide two channel s of dual redundant MIL-STD-1553B interface and will serve as a remote terminal on one (bus 8) and will monitor the other (bus 5), with growth provisions to become a remote terminal. The MIL-STD-1553B interfaces shall report all push button (not rocker switch) activations/selections and receive mode control and engine monitor display (EMD) data. The detailed requirements for these interfaces are contained in appendix A.

3.2.3.1 IPL Discrete

The PAD shall monitor a 12VDC/open input discrete designated as the initiate program load (IPL) line. When this line goes to 12VDC, the PAD shall accept and buffer a new firmware load over one of the MIL-STD-1553B interfaces, IAW MDC A7968. After completing the load transfer, the PAD shall install the new load into memory and reboot its internal processor to execute the new load.

3.2.3.2 Terminal address

The PAD shall provide 5 pins for each MIL-STD-1553 interface to be used to set the terminal address with aircraft wiring from 0 to 30. The pins shall be ground/open discrete inputs, with ground being the logic zero.

3.2.4 Ethernet Interface Option

The PAD shall provide one 1000BASE-T Ethernet interface.

3.2.5 Manchester Data Interface

The PAD shall provide a data request (ready for data) to the AN/ALR-56C processor and receive Manchester encoded data words from the processor. The PAD shall process the data to determine the required symbol, symbol location and symbol characteristics to display independently or overlay on the vid1 source defined in 3.2.7.1.1 below. The detailed electrical, protocol and data requirements for this interface are contained in appendix B. This data and symbol arrangement along with the EWWS data described below will hereafter be referred to as radar warning receiver (RWR) data.

3.2.6 EWWS Discrete Interface

The PAD shall continuously monitor four open/ground discrete inputs from the AN/ALQ-128 electronic warfare warning system (EWWS). Upon activation (ground) of any of these signals, the PAD shall overlay sector symbols in the appropriate location on the Manchester Data display defined in 3.2.5 above. The requirements for the symbol, symbol size and location are contained in appendix C.

3.2.7 Display Windows

The PAD will be provided NTSC video in EIA RS-170A format from three external sources, and shall create two graphics screens, one from the RWR data and one from the engine data. Each of these five data sets can be displayed in any window of any of the three display configurations. Window selection shall be made by repeated presses of the left side of the lower rocker switch; selection is indicated by drawing a bright green border around the window. The default (power-up) selection is the leftmost window in any configuration, and will proceed clockwise with repeated presses of the switch.

The windows shall be prioritized using the same pattern for determining which data sets to maintain through a transition from more windows to less windows; i.e., when going from a three-window display to a two-window display, the left and top right data sets from the three-window display shall be used for the two-window format. When going from less windows to more windows, the PAD shall ‘remember’ the last data sets displayed in the uncommitted windows and restore those. The intent is to enable the pilot to switch between display configurations without having to re-populate the windows.

3.2.7.1 Sources

The PAD shall rotate through the three video sources and a blank screen with subsequent presses of the right side of the lower rocker switch.

3.2.7.1.1 Video source one (vid1)

Vid1 is NTSC video originating in the sensor pod, but processed through the digital video recorder (DVR). If the RWR screen is currently displayed in the selected window, it will be overlaid onto this video.

3.2.7.1.2 Video source two (vid2)

Vid2 is NTSC video from the video-out port of the camera control unit for the vertical situation display (VSD) camera. Selecting this video source will replace any other data in the selected window.

3.2.7.1.3 Video source three (vid3)

Vid3 is NTSC video from the video-out port of the flat panel color display (FPCD). Selecting this video source will replace any other data in the selected window.

3.2.7.1.4 RWR Overlay

The RWR screen will be activated from a press of bezel button 17 and will then be displayed in the selected window (identified by a green border). If the selected window has vid1 displayed, the RWR screen shall be overlaid onto that video, range scaled appropriately (see appendix B). If the selected window has any other video source displayed, that video source will be removed and the RWR data will be shown on an empty background. In the absence of Manchester data from the RWR the PAD shall display “RWR OFF” in the center of the selected window, whether the vid1 source is present or not.

3.2.7.1.5 EMD Overlay

The EMD screen will be activated from a press of bezel button 14 and will then be displayed in the selected window (identified by a green border). If the selected window has any video source displayed, that video source will be removed and the EMD data will be shown on an empty background. The EMD screen shall show engine RPM, fan turbine inlet temperature (FTIT), fuel flow, nozzle position and oil pressure for each of the two engines. This screen shall be arranged as shown:

3.2.7.2 Window Formats

The PAD shall provide the three window formats described below. The desired display format will be selected by repeated presses of the bottom of the lower right-side rocker switch; the PAD shall rotate through the display configurations from the four-window to the three-window to the two-window and back to the four-window, etc, with each press of the switch. The power-up default configuration shall be the four-window configuration, with the 6x6 window selected.

3.2.7.2.1 Four-window

With this format selected, the PAD shall create four windows in the 8x6 display, configured as shown below. The active (selected) window will have a green border. This shall be the power-up (default) configuration, and upon power-up will have the main 6x6 window selected.

3.2.7.2.2 Three-window

With this format selected, the PAD shall create three windows in the 8x6 display, configured as shown below. Upon entry into this format, the active (selected) window will be the main 5x6. Data sets in the left window of this configuration shall maintain a 1:1 aspect ratio and shall be positioned at the top of the 5x6 window as shown.

3.2.7.2.3 Two-window

With this format selected, the PAD shall create two 4x6 windows in the 8x6 display, configured as shown below. Upon entry into this format, the active (selected) window will be the left window. Data sets in the windows of this configuration shall maintain a 1:1 aspect ratio and shall be positioned at the top of the 4x6 windows as shown.

3.2.7.3 Video Out

An NTSC format video output representing the real-time PAD display shall be available on a BNC connector mounted on the rear of the unit. This output shall be continuously provided regardless of the window format and video sources selected and shall contain all data sets as currently displayed.

3.2.8 BIT Control Panel (BCP) /Avionics Status Panel (ASP) Interface The PAD shall provide an interface consisting of three discrete lines to the aircraft BCP for initiating and reporting the unit’s built-in-test (BIT) status and a single output line to the ASP for reporting periodic BIT status.

3.2.8.1 Initiated BIT

The initiated BIT is a 28VDC/open input discrete to the PAD used to command the performance of manually initiated BIT. In the normal state (initiated BIT not commanded) this line is open. In the BIT initiate state the discrete is 20-28.5VDC, transient limited to 40 VDC. The initiated BIT input will remain in the active state until the BIT cycle is complete. Upon detecting a transition of this input from open to 28VDC, the PAD shall commence a built-in test on its internal cards and display hardware, including setting the output discretes for left and right FTIT and engine oil pressure for five seconds. After completion of the BIT, the PAD will wait for another transition of this input from open to 28VDC before starting another initiated BIT.

3.2.8.2 BIT Acknowledge

The BIT acknowledge is a 28VDC/ground output discrete from the PAD used to verify receipt of the BIT initiate command. When BIT Initiate is received, and during the entire initiated BIT cycle, the PAD shall set and keep the BIT acknowledge line active at 28VDC, transient limited to 40 VDC with a rise time <28 msec. When BIT is complete the PAD shall return the BIT Acknowledge line to a ground state of <100 ohms to the 28 VDC return, regardless of whether the test passed or failed.

3.2.8.3 BIT Go/NoGo

The BIT NoGo is a ground/open output discrete used to report the PAD BIT status to the BCP. In the Go state the PAD shall set the output to ground (0 - 0.5 VDC @ 3 mA with <100 ohms to the 28VDC return line). In the NoGo state the PAD shall set the output open with >1megohm to the 28 VDC return line. In the open state this line shall be capable of withstanding 28VDC @ < 0.5 mA on its output. The Go/NoGo status shall be continuously reported to the BCP starting from completion of the power-on BIT until shutdown.

3.2.8.4 Avionics Status Panel (ASP) Interface

The ASP Go/NoGo is a ground/open output discrete used to report the PAD BIT status to the ASP. In the Go state the PAD shall open this output with >1M Ohm to the 28 VDC return line. In the open state this line shall be capable of withstanding 28VDC @ 0.5 mA on its output. In the NoGo state the PAD shall ground the output (0 - 0.5 VDC @ 3 mA with <100 Ohms to the 28VDC return line). The PAD shall set this line appropriately at the end of power-up BIT, initiated BIT or anytime the periodic BIT fails.

3.2.9 Engine Monitor Discrete Interface

The PAD shall monitor the bus 5 MIL-STD-1553 interface for left and right engine data to be used to create the EMD dataset described in paragraph 3.2.1.7.5 above. In addition, the FTIT and oil pressure data shall be further processed IAW appendix A to provide a discrete output for each left and right FTIT over temp and low oil pressure warning indications. In the normal (false) state the two FTIT outputs shall be open, (greater than 50kohms to ground) and in the warning (true) state the two outputs shall be 20-28.5VDC, transient limited to 40 VDC.

The low oil pressure warning discrete shall be 20-28.5VDC in the normal (false) state and open, (greater than 50kohms to ground) in the warning (true) state. The three discrete outputs shall energize in the false state upon PAD power on and not transition to the true state unless the 1553 messages dictate such action or BIT is initiated.

3.2.9.1 Engine Monitor Activity Indications

The PAD shall monitor the bus 5 MIL-STD-1553 interface for the appropriate engine data messages as defined in appendix A. In the absence of these messages the PAD shall overlay “No engine warning” in place of the “EMD” legend next to pushbutton 14 indicating the loss of engine monitor functionality.

3.2.10 Display Optical Characteristics

3.2.10.1 Display Luminance

The display shall provide a continuous night luminance range of 0.02 (maximum) to 10.0 foot-Lamberts and a day luminance range of 1 to 320 (minimum) foot-Lamberts as measured in full white. Luminance values shall be measured as area luminance of a circular area of at least 1 centimeter diameter.

The display brightness shall be sufficient for satisfactory direct viewing under conditions of ambient light up to 10,000 foot-lamberts with only the use of existing glare shields.

With constant input excitation, the brightness shall not vary more than ±10% over the entire display surface when viewed from the design eye position.

3.2.10.1.1 Default Luminance

The display shall have a default brightness level of 50% of maximum day or night setting, when viewed from any point in the Viewing Angle Envelopes as defined herein.

The display shall be able to be programmable to accept a default brightness level upon power on.

3.2.10.1.2 Large Area Luminance Uniformity

The display luminance uniformity shall be such that the ratio of display luminance standard deviation to the mean display luminance is less than 0.25.

This shall be verified by using test measurements made with a 10 millimeter spot size at eight or more points evenly spaced over at least 80% of the display active viewing area.

Where standard deviation, Where Bi = luminance measurement of each equally spaced point.

Where = mean value of luminance measurements.

Where n = number of luminance measurements.

Then < 0.25 maximum.

3.2.10.1.3 Small Area Luminance Uniformity

The luminance uniformity measured with a 1 millimeter spot within any 10 millimeter viewing area on the display surface shall not vary by more than ±10%.

Uniformity shall apply over the entire display viewing area, and at any angle within the viewing angle range specified herein.

3.2.10.1.4 Luminance Degradation

Display luminance degradation shall not exceed 15% of the values specified herein after 1000 hours of operation and 500 power cycles based upon the luminance operating cycle defined below.

In addition, display luminance shall not be reduced by more than 15% over the life of the unit due to display surface exposure of 500 hours at 95°C caused by high temperature and solar radiation effects.

Luminance values shall be measured in accordance with paragraph 3.2.10.1.

Luminance Operation Cycle (Total of 1,000 Operating Hours).

OPERATION CYCLE

3.2.10.2 Display Viewability in High Brightness Ambient

The display shall be viewable and have a green contrast of greater than 4.66 in high brightness ambient conditions of 10,000 fc diffuse luminance and 2,000 fL specular reflectance.

The green contrast requirement shall be met at any angle in the cone of vision defined in paragraph 3.2.10.9 herein.

Contrast shall be defined as , where:

Lt is the total luminance of the image, or brighter area, including any background or reflected light, as measured in the specified lighting conditions; and Lb is the luminance of the background, or dimmer area, including any reflected light and any stray display emissions, measured in the specified lighting conditions.

3.2.10.3 Shades of Gray

The input video signals shall be quantized into a minimum of 256 levels. The display shall be capable of displaying a minimum of 256 levels of red, green and blue image. The brightness response of the display shall be monotonic throughout the total range of input voltage. Gamma correction shall be made to the input video signal to provide for an overall linear transfer function based on a pre-correction factor of 0.6. Adjacent gray shades shall have a luminance ratio of greater than 1.002. A black level offset of up to 5.0% of peak brightness shall be allowable for zero voltage (black level).

The input signal versus output luminance for 0 – 15% of maximum luminance shall be monotonically increasing. The input signal versus output luminance for 15% to 100% of maximum luminance shall be ± 15% of nominal level.

3.2.10.4 Display Brightness and Contrast Stability

The display shall maintain the display average brightness and contrast at constant levels when switching between the window configurations.

The maximum allowable variation shall not exceed +10% of the values prior to switching.

No random bright flashes shall occur in the image during any mode of operation or during mode switching.

The display shall be flicker free under all brightness conditions.

3.2.10.5 Display Latency

Display data shall be placed and stabilized on the display within 60 milliseconds after the end of the message in which the data is received. The 60 millisecond maximum interval applies to both displaying new data and removing old data, and includes liquid crystal turn-on and turn-off response time.

3.2.10.5.1 Pixel Transition Time

Pixel transition time shall not exceed 25ms. The value specified defines the rise time (10% to 90%) and fall time (90% to 10%) as measured, normal to the display, by the transition time in display grey level when switching between full white (GL 255) and full black (GL 0).

Ton to Toff GL0 to GL255 Toff to Ton GL255 to GL0

3.2.10.6 Image Stability

With a video input meeting the requirements of the EIA RS-170A, the display shall present a stable video image jitter of less than 1 pixel.

Vertical video stability shall be with respect to the stability of the leading edge of the vertical blank signal relative to the horizontal sync signal.

Horizontal video stability shall be with respect to the leading edge of the horizontal sync signal.

3.2.10.7 Night Vision Imaging System (NVIS) Compatibility

The display shall meet MIL-STD-3009 Type I, Class C spectral radiance requirements specified below, with the intent to be compatible with the ITT F4949 Night Vision Goggles (NVG). These requirements shall be met when viewed or measured from anywhere inside the viewing angle and at any point on the active viewing surface specified herein.

3.2.10.7.1 Display NVIS Radiance

When operating in the NIGHT Mode, the display surface shall meet the requirements for Electronic and Electro-optical Display (Multi-color) listed in Table IIIa of MIL-STD-3009 for Type I, Class B goggles.

During night operations, the display shall provide the aircrew members with a capability to rapidly and accurately obtain required crew station information with unaided eye vision.

Radiance measurements shall be made by setting the illuminated display (White) level to 5.0 fL +/- 1.0 fL and scaled to 0.5 fL.

3.2.10.7.2 Bezel Panel NVIS Radiance

The bezel panel shall be compatible with ITT F4949 NVG and shall meet NVIS Class B spectral radiance of less than 1.7 x 10-10 NRb when measured at maximum intensity and scaled to 0.1 foot-Lamberts brightness per MIL-STD-3009, Table IIIa.

The bezel panel shall not exhibit light leaks per the requirements of MIL-STD-3009, paragraph C.7.8.

3.2.10.7.3 Knob/Switch NVIS Radiance

Any illuminated knob and/or switch brightness shall be within the range of 0.35 foot-Lamberts to 1.05 foot-Lamberts. Knob and/or switch spectral radiance shall be less than 1.7 X 10-10 NRb at any brightness setting within this illumination range.

3.2.10.7.4 Light Leakage

The front of the display shall be designed as a ‘light tight” enclosure.

The apparent intensity of the unit as viewed through a monocular shall appear free of pinpoint light leaks or extreme bright spots.

Occurrence of such extreme bright spots or any areas appearing to “bloom” at radiance levels beyond those emitted by adjacent areas shall be cause for rejection.

Failed ON pixels, and similar anomalies that are otherwise allowed by these specification requirements shall not be considered to be “extreme bright spots”.

The image intensifier inspection device shall be a GEN III monocular, i.e. Hoffman Engineering Model NVG 102 or NVG 103 with a 665 nanometers minus blue cutoff filter (NVIS Class B-NRb), or an equivalent monocular approved by the USAF.

3.2.10.7.5 OFF Pixels NVIS Requirement

OFF pixel leakage NVIS radiance shall not be greater than 9 x 10-11 NRb. This requirement shall be met at any point on the display surface when measured anywhere within the viewing angle envelope with the ON pixel brightness having been set at 0.5 ± 0.1 fL.

3.2.10.7.6 Display Day/Night Transition

Display Day/Night Transition Luminance shall be as defined below:

Day to Night Transition

Night to Day Transition

3.2.10.8 Visual Criteria

Defects are not allowed in the viewing area unless defects fall in the size limitation shown below. Defects include bubbles, transparent or opaque flaws, pits, voids, delaminations, dark spots or scratches.

3.2.10.8.1 Visual Defects

At a viewing distance of 18 to 24 inches, no visible workmanship defects shall be observable. These include scratches, chips, lamination bubbles, etc.

In order to resolve potential subjective disputes, the following requirements for scratches and bubbles shall apply.

There shall be no defect of any kind whose maximum dimension exceeds 0.02”.

There shall be no scratches whose width exceeds 0.006” or whose length exceeds 0.4”, except as specified below.

There shall be no more than 6 scratches with widths between 0.002” and 0.006”.

Scratches less than 0.002” in width of any length are allowable unless visible from the specified viewing distance.

3.2.10.8.2 Non-Uniformities

Display non-uniformities (bull’s-eyes, measles, pattern defects, window frames, etc.) shall not be visible at a distance of 18 inches.

3.2.10.8.3 Point and Cluster Defects

A point defect is an element (subpixel) that is not under independent luminance transmission control (stuck on, stuck off or shorted to an adjacent pixel) or one that is more than 30% darker or lighter than the average of subpixels of the same color within a radius of 1/8 inch, in the ON and OFF states.

The maximum number of failed-on elements shall be less than 5, with no more than 2 adjacent.

The maximum number of failed-off elements shall be less than or equal to 15 elements, with no more than 3 adjacent. No two groups of failed adjacent pixels shall be allowed within 10 mm of each other. A failed-on element is a single addressable element which is permanently or sporadically in the on or partially on condition when it has not been selected to be on. A failed off element is a single addressable element which is permanently off or partially off when it has not been commanded to be off.

The display shall have no full or partial line defects.

3.2.10.8.4 Bright Foreign Material Defects

Any visual display defect introduced during the ruggedization or lamination process will be considered a lamination defect. Lamination defects may be located in either the front or rear of the LCD assembly. Lamination defects that are identified as Bright Foreign Material shall be limited to the following quantities and sizes:

• Color filter side (front):

- AD < 0.2 mm – No limit

- 0.2 mm < AD < 0.3 mm – Maximum of 3

- AD > 0.3 mm – None allowed

• TFT side (rear):

- AD ≤ 0.3 mm – No limit

- 0.3 mm < AD ≤ 0.46 mm – Maximum of 4

- AD > 0.46 mm – None allowed where AD (average diameter) is defined as (L+W)/2.

The display shall be adjusted to a minimum white luminance of 50 fL (+35/-0 fL). The display shall be inspected in a darkened room at a distance of 18" (+3/–3"), normal to the display surface by an inspector with 20/20 corrected vision. The display shall be inspected with a flat field black display.

3.2.10.9 Cone of Vision

The cone of vision shall be a minimum of ± 15degrees about a line which extends from the center of the display to the pilot's eye.

3.2.11 Detail Design Requirements

3.2.11.1 Display Controls

The display shall include the controls specified below.

3.2.11.1.1 Brightness Control

The brightness rocker switch shall be located on the right side upper corner of the display bezel and shall vary the brightness of the backlight throughout the entire day or night range specified herein.

3.2.11.1.2 Off/Day/Night Mode Control

The display shall provide a rocker switch on the right end of the top row of buttons for selection of Off and On modes to include a Night Vision Imaging System (NVIS) compatible mode and the standard daytime operating mode.

3.2.11.2 Warm Up Time

The equipment shall meet the specified performance requirements herein within 1 minute after equipment turn-on between 0 and +71 degrees C, 4 minutes between -0.1 and -18 degrees C, and 5 minutes between -40 degrees C and -18.1 degrees C.

3.2.11.3 Useful Life

The equipment shall have a useful life of not less than 10 years under any combination of operating and storage life, where the operational service life has not been exceeded.

3.2.11.3.1 Operational Service Life

The equipment shall have an operational service life of not less than 10,000 hours under any natural combination of environmenta1 conditions specified herein. Operational service life is defined as the total operating time between the start of operation and wear out. Wear out is defined as the point where overhaul or repair cost exceeds one-half of the replacement cost of equipment.

3.2.11.3.2 Storage

The equipment shall meet all requirements of this specification without component or part replacement, adjustment, or maintenance action after being in storage for a minimum of 18 months. The equipment shall be capable of satisfactory operation following prolonged storage in -54°C to +85°C environment.

3.2.11.4 Thermal Requirements

For thermal design considerations there shall be no conduction heat transfer between the LRU and its surrounding. External radiant heat transfer shall not be considered for forced air cooled equipment; radiant heat transfer may be considered for non-forced air cooled equipment. If analysis shows that radiant heat transfer is required, interfaces shall be closely coordinated with and submitted to USAF for approval.

3.2.11.4.1 Heat Dissipation

The heat dissipation of the PAD, excluding illuminated panel and LCD glass heater power, shall not exceed 45 watts.

3.2.12 Physical Characteristics

3.2.12.1 Weight

The equipment shall be designed to achieve the minimum feasible weight consistent with the total requirements as stated herein. The weight of the PAD shall not exceed 8.0 pounds.

3.2.12.2 Handling Provisions

The PAD shall be designed for ease of handling during installation and maintenance.

3.2.12.3 Strength

The equipment shall be designed in accordance with the strength requirements of MCAIR Report H417 and shall be capable of withstanding the loads and environments of this specification.

The requirements of MCAIR Report H417, with regard to avionic equipment, shall only apply to the components that provide structural integrity such as case mounts and support members.

3.2.12.4 Fatigue Design Consideration

All elements of detail design shall be properly considered in accordance with MCAIR Report H417 in order to insure maximum fatigue life.

3.2.13 Reliability

The equipment, including BIT (when operated in any mode and natural combination of environments), shall be designed to exceed a predicted Mean-Time-Between-Failure (MTBF), θp, based on MIL-HDBK-217, of 5,000 hours. The predicted MTBF (θp) is based on a lower test MTBF (θ1) of 2,000 hours, and an upper test MTBF (θ0) of 2 times θ1, exceeded by a factor of at least 1.25. (θ0, θ1 and θp shall be as defined in MIL-HDBK-781, section 3.1.4).

3.2.14 Maintainability

The design of the equipment shall be such that the Mean Maintenance Man-hours to Repair (MMTR) shall not exceed 0.25 hours for on aircraft and 1.125 hours for off aircraft maintenance.

MMTR shall include but not be limited to, the following tasks: man-hours to perform fault isolation, remove and/or replace faulty component, and verification of repair.

Off aircraft tasks include: performance test; fault isolation test; remove and/or replace faulty modules, subassemblies and parts; and complete performance verification test.

3.2.14.1 Scheduled Maintenance

The equipment shall be designed to eliminate requirements for scheduled preventive maintenance.

3.2.14.2 Reprogramming

The equipment shall be designed for on-aircraft reprogramming such that the Mean Maintenance Man-hours to Repair for programming and/or reprogramming of any internal memory device, if applicable, shall not exceed 15 minutes.

3.3 Environmental Conditions

The equipment shall meet all specified requirements and shall provide required performance, life and reliability under any natural combinations of the service conditions as outlined herein.

The equipment shall demonstrate performance meeting requirements of this specification under tests specified under Section 4 herein.

3.3.1 Temperature-Altitude

Temperature/altitude conditions shown below are applicable for continuous and transient operation.

Temperature and Altitude Requirements Continuous Operation is -19°C to +55°C @ 25,000ft and Below

3.3.2 Explosive atmosphere

The equipment shall not cause ignition of an ambient-explosive-gaseous mixture with air when operating in such an atmosphere.

3.3.3 Humidity

The equipment shall withstand the effects of humidity up to 100 percent, including conditions wherein condensation takes place in and on the equipment. The equipment shall withstand the above conditions during operating and non-operating conditions. Fogging on the inside of the cover glass of instruments shall not occur.

3.3.4 Salt-Fog Atmosphere

The equipment shall withstand, in both an operating and non-operating condition, exposure to salt-fog atmosphere.

3.3.5 Fungus

The equipment shall withstand, in both an operating and non-operating condition, exposure to fungus growth as encountered in tropical climates. In no case shall overall spraying of the equipment be necessary to meet this requirement.

3.3.6 Sand and Dust

The equipment shall withstand, in both operating and non-operating conditions, exposure to sand and dust particles as encountered in operational areas of the world.

3.3.7 Vibration

The vibration design requirements of Paragraph 3.1 of MDC Report A4246 apply except the test levels shall be as defined herein.

The vibration test procedures of paragraphs 4.2.2.2, 4.2.2.3, 4.2.2.5, 4.2.2.6, and 4.2.2.9 of Report MDC A4246 are applicable. The applicable vibration levels are listed below.

a) Endurance Level

F-15 Endurance Random Vibration

b) Performance Level

F-15 Performance Random Vibration

c) Gunfire Random Test Levels

RANDOM VIBRATION – 10 MINUTES/AXIS

G RMS OVERALL =7.20

d) Minimum Integrity Level

MINIMUM INTEGRITY –1 HR/AXIS

G RMS OVERALL = 7.70

1000-2000 -6.0 dB/oct

e) Gunfire Sinusoidal Vibration Levels

Gunfire Sinusoidal Vibration Test Levels

Gunfire Sinusoidal Vibration Test Levels(continued)

f) Environmental Stress Screening (ESS) Levels (NOTE: The USAF may allow some vibration level reduction if equipment resonances are too large.)

Modified NAVMAT Spectrum for ESS (Lateral and Longitudinal)

The PAD axes definitions are as follows:

Forces from (+) vertical load factors act down.

Forces from (+) longitudinal load factors act aft.

Forces from (+) lateral load factors act toward left side.

3.3.8 Acoustic Noise

The acoustic noise design requirements of paragraph 3.2 of MDC Report A4246 apply. Acoustic Zone 2 is the applicable acoustic zone.

3.3.9 Shock

The service shock and crash safety shock requirements of Paragraphs 3.3, 3.3.1, and 3.3.2 of MDC Report A4246 are applicable. The sawtooth waveform is applicable.

3.3.10 Design Loads

The equipment, when installed in the aircraft, shall be designed for normal operating, limit and ultimate load factors.

3.3.10.1 Normal Operating Load Factors

The equipment, when installed in the aircraft, shall meet all performance requirements of this specification during application of normal operating load factors.

Normal Operation Load Factors

3.3.10.2 Limit Load Factors

This equipment shall meet the performance requirements of this specification after application of limit load factors.

The equipment shall operate during the application of the load factors.

No physical distortion or permanent set of the equipment is permitted after application of limit load factors.

Limit Load Factors

3.3.10.3 Ultimate Load Factors

This equipment shall withstand ultimate load factors with no failure of the structural support elements and the equipment shall remain in place.

Distortion and permanent set are permitted and equipment operation is not required during or after application of ultimate loads.

Tests for condition F will be performed along the Longitudinal axis and along ± 20 degrees Off Longitudinal axis such that for two cases a component of ± vertical load is produced and in another two cases a component of ± lateral load is produced.

Ultimate Load Factors

3.3.11 Explosive Decompression

Condition I. The PAD shall be capable of full performance capability immediately after being subjected to an explosive decompression in which the surrounding air pressure varies with time in accordance with Condition I curve of Figure 14.

Condition II. The PAD shall neither deform nor disintegrate in a manner that could cause injury to a crew member or otherwise jeopardize aircraft safety when subjected t o an explosive decompression in which the surrounding air pressure varies with time in accordance with Condition II curve of Figure 14. The equipment shall not be required to function after being subjected to these conditions.

3.3.12 Touch Temperature

The maximum stabilized surface temperature of control panels, displays, and hand actuated devices and controls shall not exceed the following temperatures when the cockpit average ambient air temperature on the pilot's side of the instrument panel is between 60°F and 80°F and the average ambient air temperature on the forward side of the instrument panel is 131°F; 145°F for displays, lighted pushbutton switches, control panels, and insulated toggle switches; 135°F for insulated pull-toggle switches; and 125°F for non-insulated toggle switches, control knobs, and all other hand actuated and control devices.

3.3.13 Rain

The PAD shall be designed such that exposure to rain environment when the cockpit canopy is opened shall not degrade performance.

3.3.14 Solar Radiation

The PAD shall be designed such that exposure to a natural sunshine environment shall not degrade performance when tested in accordance with paragraph 4.2.1.1.4.2.13.

3.4 Design and Construction

The equipment shall be designed and constructed to meet all requirements of this specification over its service life so that the equipment will consistently and repeatedly perform as specified.

3.4.1 Processes and Parts

3.4.1.1 Finish and Color

The equipment and parts thereof shall be finished to withstand the environments specified herein without showing signs of corrosion. No lacquer shall be used. The exterior surfaces of the equipment exposed to the pilot shall be lusterless black, color number 37038, in accordance with FED-STD-595.

3.4.1.2 Parts

3.4.1.2.1 Component Obsolescence

Life cycle issues will be carefully considered for all microelectronics and electrical display devices selected for use. Each component will be evaluated for obsolescence status along with a projection of the anticipated length of availability. Initial obsolescence issues and corresponding mitigation strategies will be determined during the design phase. Periodic technology review assessments will be conducted throughout the life of the program to re-evaluate the issues and strategies. Components with two or more sources are preferred over single sourced components.

3.4.1.2.2 Screws and Fasteners

Screws and fasteners, which are normally removed or installed during servicing or replacing equipment on the flightline shall be subject to USAF approval. Screws used to attach the system to the aircraft shall be size No. 10 or larger unless specified otherwise herein. Mounting provisions shall be designed so that no mounting screw threads are in bearing. The use of inserts is considered to be threads in bearing. Screw threads shall conform to SAE AS8879. All screws and fasteners having cross recess type heads shall be of the Phillips recess type. Access covers not including the LRU case that must be removed for organization or intermediate level maintenance of the equipment shall be captive and shall be secured by a minimum number of captive quick-release fasteners.

3.4.1.2.3 Microelectronic Circuits and Semiconductor Devices

Microelectronic circuits and semiconductor devices used in the equipment shall conform to the maximum extent practical with MIL-PRF-38534, MIL-PRF-38535, and MIL-PRF-19500.

3.4.1.2.4 Internal Wiring

No SRU shall be hard wired to chassis or other SRU wiring.

3.4.2 Electromagnetic Interference and Compatibility (EMIC)

The design shall use AFSC Handbook DH 1-4 as a guide and shall comply with the requirements of the following paragraphs.

3.4.2.1 EMIC Requirements

All general requirements of MIL-STD-461 apply. Specific applicable requirements are as follows: CE102, CS101, CS114, CS115, CS116, RE102, and RS103. These requirements shall include the conditions below:

a) CS114 - Figure CS114-1, Curve 3 Internal (AF).

b) RE102 - The external RE102 limit shall apply to those LRU surfaces that are visible on the cockpit side of the aircraft console. The internal RE102 limit for aircraft <25 m in length shall apply to the cables and those LRU surfaces located inside the console. The applicable frequency range is 2 MHz to 18 GHz.

c) RS103 - The limits of 5.19.1(a) of MIL-STD-461 for the frequency range from 2 MHz to 30 MHz apply. Limits above 18 GHz in 5.19.1(d) of MIL-STD-461 do not apply. The external RS103 limit shall apply to those LRU surfaces that are visible on the cockpit side of the aircraft console. The internal RS103 limit shall apply to the cables and LRU surfaces located inside the console.

3.4.2.2 Electrostatic Discharge

Each external connector pin shall withstand an electrostatic discharge pulse from a source of 100 picofarads charged to 4,000 volts and discharged through 1,500 ohms resistance to the pin.

3.4.3 Identification of Units

A nameplate conforming to the requirements of MIL-STD-130M, to include the Universal Identification 2D bar code, shall be permanently attached to each unit of equipment. Nomenclature for units will be supplied by the USAF. An LRU ID resistor shall be accessible via an external connector. The location and value shall be subject to USAF approval.

3.4.4 Workmanship

Workmanship shall conform to the requirements of paragraph 4.2.33 of MIL-HDBK-5400.

3.4.5 Interchangeability

All parts, subassemblies, assemblies, units, etc., having the same manufacturer’s part number shall be directly and completely interchangeable with each other with respect to installation and performance. Changes in manufacturer’s part numbers shall be governed by the requirements of ASME Y14.100.

3.4.6 Safety

To assure optimum safety, the equipment shall meet the safety requirements of MIL-HDBK-454. MIL-STD-1472 shall apply to the equipment design except as noted herein.

3.4.7 Human Performance/Human Engineering

The PAD shall incorporate the detailed Human Factors requirements of MIL-STD-1472, MIL-STD-3009, SAE AS7788, and specific criteria established herein. Any non-compliances or deviations shall be identified and coordinated with the USAF for resolution and approval.

3.4.7.1 Visual Displays

The displayed data shall meet the requirements stated herein. The input signals to the indicators shall be consistent with this requirement. The information displayed to the operator shall be limited to that which is necessary to perform the specific action or make the decisions required. Information shall be displayed only to the degree of specificity and accuracy needed to meet performance requirements. The information shall be presented in a directly usable form. Requirements for decoding, transposing, computing, interpolating, etc. shall be minimized. The data displayed and the necessary markings and scales shall be of sufficient size and shall have sufficient brightness and contrast so that the operator can readily detect, read, and understand the displayed data under day and night conditions. Panel or instrument lighting, when required, shall be adequate for day and night use. Control/display ratios used shall be adequate to ensure operator recognition of control changes on the displays. Necessary controls and adjustments shall be arranged for operator convenience and ease of use. Readjustment of controls or displays shall not be required when switching ranges or modes.

3.4.7.1.1 Active Matrix Liquid Crystal Display

The resolution, brightness, and contrast of the Active Matrix Liquid Crystal Display (AMLCD) shall be adequate for day or night use under normal cockpit or crew station conditions. Extraneous information displayed shall be minimized with respect to the desired signal. Signals of equal characteristics shall be displayed with the same uniformity over the viewing area. Smears, spokes, skips and other undesirable indications shall be absent.

3.4.7.1.2 Instrument and Indicator Coverglass and Wedges

The instrument coverglass and any other transparent element between the glass and the display, such as a lighting wedge, shall be provided with a reflection reducing coating which enables the PAD to meet all contrast requirements stated herein. In addition, the coating shall withstand the environmental conditions of the PS.

3.4.7.2 Acoustic Noise Generation

Equipment shall not generate acoustic noise in excess of the levels specified in paragraph 3.2 of MDC Report A4246. The equipment in cockpit curve requirement of Figure 62 of MDC Report A4246 is applicable.

3.4.8 Overload Protection

The equipment shall be protected from chain reaction failures including those resulting from external overloads (shorts) caused by inadvertent grounding of external wiring during installation, test, or other causes. No damage to an LRU shall result from open circuits or grounding of wiring external to the LRU. The use of fuses shall be kept to the minimum necessary to meet requirements and shall be coordinated with and approved by the USAF in writing.

3.4.9 Elapsed Time Meter

The equipment shall provide a time totalizing method which will indicate unit “power on” time and shall be incapable of being reset. This method can be man or machine readable. If the man readable option is selected, a non-resettable 9999 hour Elapsed Time Indicator (ETI), shall be utilized and located on the rear of the unit. The type and location of the ETI will be coordinated with and approved by the USAF. If the machine readable option is selected, the protocol and method used to access the operating time shall be coordinated with and approved by the USAF.

3.4.10 Cockpit Control Panels

Control units shall exclude moisture encountered when cockpit canopies are open. Seals, baffles, and good placement of internal components shall be used to improve moisture protection.