PADSPECX201122867.docx

DOCX document 3 MB Posted May 21, 2013

Attached to: Aircraft Components and Accessories
Solicitation number: FA8505-13-R-31129
Issued by: Department of the Air Force Materiel Command Lifecycle Management Center Robins Air Force Base

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Specification 201122867

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FA850513R31129______0002.pdf	PDF	Jun 18, 2013
Q A_6_PAD.docx	DOCX document	Jun 18, 2013
Passive_Attack_Display_(PAD)_X201122867_Rev-11_Jun_13.pdf	PDF	Jun 11, 2013
FA850513R31129______0001_11_Jun_13.pdf	PDF	Jun 11, 2013
Q A_5_PAD.docx	DOCX document	Jun 5, 2013
Q A_4_PAD.docx	DOCX document	Jun 4, 2013
Q A_3_PAD.docx	DOCX document	Jun 3, 2013
Attach_5_97X0011.pdf	PDF	May 31, 2013
Attach_3_Boeing_G667-E.pdf	PDF	May 31, 2013
Attach_1_MDC_A4246_Rev_C_-_F15_Dynamic_Load_Requirements.pdf	PDF	May 31, 2013
Attach_4_Boeing_STL_00A0060.pdf	PDF	May 31, 2013
Q A_2.docx	DOCX document	May 31, 2013
Attach_2_Boeing_H417-D.pdf	PDF	May 31, 2013
PAD_Q A__1_23_May_13.docx	DOCX document	May 23, 2013
PADSOW7May13.docx	DOCX document	May 21, 2013
PADPkg.pdf	PDF	May 21, 2013
CDRLSPAD.pdf	PDF	May 21, 2013
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APPLICATION

REVISIONS

NEXT ASSY

USED ON

LTR

DESCRIPTION

DATE

APPROVED

N/A

F-15C/D

Original

20 May 2013

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DISTRIBUTION STATEMENT D. Distribution authorized to DoD and DoD contractors only. All other requests shall be referred to WR-ALC/GRME, Robins AFB, GA 31088.

DESTRUCTION NOTICE. Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

WARNING – This document contains technical data whose export is restricted by the Arms Export Control Act, as amended by Title 22, U.S.C., Sec 2751, et seq, or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App 2401, et seq. Violations of these export laws are subject to severe criminal penalties. (DOD Directive 5230.25).

UNLESS OTHERWISE SPECIFIED

DIMENSIONS ARE IN INCHES

TOLERANCES ON

FRACTIONS DECIMALS ANGLES

APPROVALS DATE

U.S. AIR FORCE

ROBINS AFB, GA

	.XX
DRAFTSMAN

K.H. Strobel

.XXX

AIR FORCE PERFORMANCE SPECIFICATION for the F-15C/D

PROJECT ENGINEER

A. Byrd

PASSIVE ATTACK DISPLAY (PAD)

CHIEF ENGINEER

J. Byrd Chief, F-15 Engineering Branch

TREATMENT

None

PROJECT AUTHORITY

R. Jansen Chief, F-15 Engineering

SIZE

A.F. CODE IDENT NO.

98752

DRAWING NO.

201122867

FINISH

None

RELEASE AUTHORITY

G.L. Sullivan

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TABLE OF CONTENTS

Paragraph No. Title Page

TABLE OF CONTENTS	2
APPENDICES	6
1.0	SCOPE	7
2.0	REFERENCED DOCUMENTS.	7
2.1	Government Documents	7
3.0	REQUIREMENTS	7
3.1	Item Definition.	7
3.1.1	Interface Definition.	8
3.1.1.1	Interface Compatibility.	8
3.1.1.1.1	List of Associated Equipment.	8
3.2	Characteristics.	9
3.2.1	Display Physical Characteristics	9
3.2.1.1	Bezel Push-Button Numbering.	9
3.2.1.2	Bezel Rocker Switch Functions.	9
3.2.2	Aircraft Power and Panel Lighting	10
3.2.2.1	Aircraft Power.	10
3.2.2.1.1	Electrical Power Interruptions	10
3.2.2.2	Panel Lighting	10
3.2.3	MIL-STD-1553B Interface.	10
3.2.3.1	IPL Discrete.	10
3.2.3.2	Terminal address.	11
3.2.3.3	MIL-STD-1553 Security Considerations.	11
3.2.4	Ethernet Interface.	11
3.2.5	Manchester Data Interface.	11
3.2.6	EWWS Discrete Interface.	11
3.2.7	Display Windows.	11
3.2.7.1	Sources.	12
3.2.7.1.1	Video source one (vid1).	12
3.2.7.1.2	Video source two (vid2)	12
3.2.7.1.3	Video source three (vid3).	12
3.2.7.1.4	RWR Overlay.	12
3.2.7.1.5	UFC Backup Overlay.	13
3.2.7.1.6	EMD Overlay.	13
3.2.7.2	Window Formats.	14
3.2.7.2.1	Four-window.	14
3.2.7.2.2	Three-window.	15
3.2.7.2.3	Two-window.	15
3.2.7.2.4	UFC Overlay.	16
3.2.7.3	Video Out.	16
3.2.8	BIT Control Panel (BCP) /Avionics Status Panel (ASP) Interface.	16
3.2.8.1	Initiated BIT.	16
3.2.8.2	BIT Acknowledge.	16
3.2.8.3	BIT Go/NoGo.	17
3.2.8.4	Avionics Status Panel (ASP) Interface.	17
3.2.9	Engine Monitor Discrete Interface	17
3.2.9.1	Engine Monitor Activity Indications.	17
3.2.10	Processor and memory spare	17
3.2.11	Application program loading through external interface	17
3.2.12	Display Optical Characteristics.	18
3.2.12.1	Display Luminance.	18
3.2.12.1.1	Default Luminance.	18
3.2.12.1.2	Large Area Luminance Uniformity.	18
3.2.12.1.3	Small Area Luminance Uniformity.	18
3.2.12.1.4	Luminance Degradation.	19
3.2.12.2	Display Viewability in High Brightness Ambient.	19
3.2.12.3	Shades of Gray	19
3.2.12.4	Display Brightness and Contrast Stability.	19
3.2.12.5	Display Latency.	20
3.2.12.5.1	Pixel Transition Time.	20
3.2.12.6	Image Stability.	20
3.2.12.7	Night Vision Imaging System (NVIS) Compatibility.	20
3.2.12.7.1	Display NVIS Radiance.	20
3.2.12.7.2	Bezel Panel NVIS Radiance.	20
3.2.12.7.3	Knob/Switch NVIS Radiance.	20
3.2.12.7.4	Light Leakage.	21
3.2.12.7.5	OFF Pixels NVIS Requirement.	21
3.2.12.7.6	Display Day/Night Transition.	21
3.2.12.8	Visual Criteria.	21
3.2.12.8.1	Visual Defects.	21
3.2.12.8.2	Non-Uniformities.	21
3.2.12.8.3	Point and Cluster Defects.	22
3.2.12.8.4	Bright Foreign Material Defects.	22
3.2.12.9	Cone of Vision.	22
3.2.13	Detail Design Requirements.	22
3.2.13.1	Display Controls.	22
3.2.13.1.1	Brightness Control.	22
3.2.13.1.2	Off/Day/Night Mode Control.	23
3.2.13.2	Warm Up Time.	23
3.2.13.3	Useful Life	23
3.2.13.3.1	Operational Service Life.	23
3.2.13.3.2	Storage.	23
3.2.13.4	Thermal Requirements.	23
3.2.13.4.1	Heat Dissipation.	23
3.2.14	Physical Characteristics.	23
3.2.14.1	Weight.	23
3.2.14.2	Handling Provisions.	23
3.2.14.3	Strength.	23
3.2.14.4	Fatigue Design Consideration.	24
3.2.15	Reliability.	24
3.2.16	Maintainability.	24
3.2.16.1	Scheduled Maintenance.	24
3.2.16.2	Reprogramming.	24
3.3	Environmental Conditions.	24
3.3.1	Temperature-Altitude.	24
3.3.2	Explosive atmosphere.	25
3.3.3	Humidity.	25
3.3.4	Salt-Fog Atmosphere.	25
3.3.5	Fungus.	25
3.3.6	Sand and Dust.	25
3.3.7	Vibration.	25
3.3.8	Acoustic Noise.	31
3.3.9	Shock.	31
3.3.10	Design Loads.	31
3.3.10.1	Normal Operating Load Factors.	31
3.3.10.2	Limit Load Factors.	31
3.3.10.3	Ultimate Load Factors.	31
3.3.11	Explosive Decompression.	32
3.3.12	Touch Temperature.	32
3.3.13	Rain.	32
3.3.14	Solar Radiation.	32
3.4	Design and Construction.	32
3.4.1	Processes and Parts.	32
3.4.1.1	Finish and Color.	32
3.4.1.2	Parts.	33
3.4.1.2.1	Component Obsolescence.	33
3.4.1.2.2	Screws and Fasteners.	33
3.4.1.2.3	Microelectronic Circuits and Semiconductor Devices.	33
3.4.1.2.4	Internal Wiring.	33
3.4.2	Electromagnetic Interference and Compatibility (EMIC).	33
3.4.2.1	EMIC Requirements.	33
3.4.2.2	Electrostatic Discharge.	34
3.4.3	Identification of Units.	34
3.4.4	Workmanship.	34
3.4.5	Interchangeability.	34
3.4.6	Safety.	34
3.4.7	Human Performance/Human Engineering.	34
3.4.7.1	Visual Displays.	34
3.4.7.1.1	Active Matrix Liquid Crystal Display.	34
3.4.7.1.2	Instrument and Indicator Coverglass and Wedges.	35
3.4.7.2	Acoustic Noise Generation.	35
3.4.8	Overload Protection.	35
3.4.9	Elapsed Time Meter.	35
3.4.10	Cockpit Control Panels.	35
3.4.11	Modular Design.	35
3.4.12	Grounding Requirements.	35
3.4.13	Bonding.	36
3.5	Software Requirements.	36
3.6	Logistics.	36
3.6.1	Maintenance.	36
3.6.1.1	BIT Provisions.	36
3.6.1.1.1	BIT General.	37
3.6.1.1.2	BIT Methods.	37
3.6.1.1.3	BIT Performance.	37
3.6.1.1.3.1	Test Accuracy.	37
3.6.1.1.3.2	Fault Detection Capability.	37
3.6.1.1.3.3	Fault Isolation Capability.	38
3.6.1.1.3.4	BIT Test Times.	38
3.6.1.1.3.5	Fault Detection/Fault Isolation Display.	38
3.6.1.2	Intermediate and Depot Level Maintenance Provisions.	38
3.6.1.3	Access for Maintenance and Testing.	38
3.6.1.4	Adjustment Controls.	38
3.6.2	Verticality of Testing.	38
3.7	Precedence.	39
4.0	QUALITY ASSURANCE PROVISIONS.	39
4.1	General.	39
4.1.1	Responsibility for Tests.	39
4.2	Quality Conformance Inspections.	40
4.2.1	Verification.	40
4.2.1.1	Formal Qualification.	40
4.2.1.1.1	Formal Qualification – Inspection.	40
4.2.1.1.2	Formal Qualification – Analysis.	40
4.2.1.1.3	Formal Qualification – Demonstration.	40
4.2.1.1.4	Test.	40
4.2.1.1.4.1	Formal Qualification Test Part I – Under Standard Laboratory Conditions.	40
4.2.1.1.4.1.1	BIT Performance Test.	40
4.2.1.1.4.2	Formal Qualification Test Part II –Under Simulated Environmental Conditions.	41
4.2.1.1.4.2.1	Temperature – Altitude Tests (3.3.1).	41
4.2.1.1.4.2.1.1	Low Pressure (Altitude)	41
4.2.1.1.4.2.1.2	High Temperature.	41
4.2.1.1.4.2.1.3	Low Temperature.	41
4.2.1.1.4.2.1.4	Temperature Shock.	41
4.2.1.1.4.2.2	Explosive Atmosphere (3.3.2)	41
4.2.1.1.4.2.3	Humidity (3.3.3).	41
4.2.1.1.4.2.4	Salt-Fog Atmosphere (3.3.4).	41
4.2.1.1.4.2.5	Sand and Dust (3.3.6)	41
4.2.1.1.4.2.6	Vibration (3.3.7).	41
4.2.1.1.4.2.7	Acoustic Noise	41
4.2.1.1.4.2.8	Shock (3.3.9).	41
4.2.1.1.4.2.9	Design Loads (3.3.10).	42
4.2.1.1.4.2.9.1	Normal Operating Load Factors (3.3.10.1).	42
4.2.1.1.4.2.9.2	Limit Load Factors (3.3.10.2).	42
4.2.1.1.4.2.9.3	Ultimate Load Factors (3.3.10.3).	42
4.2.1.1.4.2.10	Rain (3.3.13).	42
4.2.1.1.4.2.11	Explosive Decompression (3.3.11).	42
4.2.1.1.4.2.12	Touch Temperature (3.3.12).	42
4.2.1.1.4.2.13	Solar Radiation (3.3.14).	42
4.2.1.1.4.3	Formal Qualification Test Part III – Electromagnetic Interference and Compatibility (3.4.2.1).	42
4.2.1.1.4.3.1	Electrostatic Discharge (3.4.2.2).	43
4.2.1.2	Reliability/Maintainability Verification	43
4.2.1.2.1	Reliability Development Tests.	43
4.2.1.2.2	Maintainability Verification.	43
4.2.1.3	Acceptance Verification.	43
4.2.1.3.1	Part I – Individual Acceptance.	43
4.2.1.3.1.1	Individual Acceptance – Inspection.	43
4.2.1.3.1.2	Individual Acceptance – Test.	43
4.2.1.3.1.2.1	Performance Test.	43
4.2.1.3.1.2.2	Lighting.	43
4.2.1.3.1.2.3	BIT Provisions.	43
4.2.1.3.1.3	Individual Acceptance Demonstration.	43
4.2.1.3.2	Environmental Stress Screening Tests (ESS)	44
5.0	PREPARATION FOR DELIVERY.	44

APPENDICES

APPENDIX A	43
PAD MIL-STD-1553 Multiplex Data Bus Interface Detail	43
APPENDIX B	54
PAD Manchester Data Interface Detail	54
APPENDIX C	63
PAD EWWS Discrete Interface Detail	63
APPENDIX D	67
Upfront Control (UFC) Backup Screens	67

98752	CAGE: 98752
DOC. NO.: X201122867
REV -
SHEET: 6

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.

REFERENCED DOCUMENTS.

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

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.

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 and 4 rocker switches that control internal display functions. Throughout this specification the word “display” may be used interchangeably with PAD.

The PAD shall be supplied with an operating system, a set of hardware-specific routines (herein referred to as ‘drivers’), an application programming interface (API), a test application to be used to verify the hardware performance of the PAD, and the operational software.

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.

Interface Compatibility.

List of Associated Equipment.

PS68-870164 Programmable Signal Data Processor (PSDP) PS68-870072 BIT Control Panel (BCP) PS68-870073 Avionics Status Panel (ASP) IF76301A328A455 Radar Warning Receiver (RWR) IF76301A328A418 Electronic Warfare Warning System (EWWS) F15_FDR_V1.0d_TRD F-15 Flight Data Recorder (DVR) PS68-870157 Integrated Communications Control Panel (ICCP) PS68-810073 Caution Lights Logic Unit (CLLU)

Characteristics.

Display Physical Characteristics The display shall provide an 8x6 inch viewing area Active Matrix Liquid Crystal Display (AMLCD) screen; overall dimensions cannot exceed 10.25” wide, 8” tall and 1.5” behind the mounting surface at the upper right corner (to avoid impacting the windscreen). Away from the upper right corner, the depth is not critical.

The display shall provide mounting provisions, typically at the four corners. All mounting hardware shall be captive to the display.

The display bezel shall have a minimum of 24 peripheral push-buttons and 4 rocker switches arranged and with the spacing as shown below. There are two types of buttons shown: single-action push-buttons and dual-action rockers.

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. Three bezel buttons, 14, 15 and 17, shall be dedicated-function switches with functionality described later. The rocker switches are not numbered; they are to be used for controlling internal display functions. The API shall provide a means for all bezel buttons to be configured for internal display use or reported on any of the 1553 or Ethernet interfaces.

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). These switches execute the only factory-dedicated functions, and therefore shall have appropriate symbology printed on them to provide identification of their functions. 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); the top side of the switch rotors through the declutter options; the bottom side of the switch rotors through the available window format options. The left side of the switch on the bottom row is to be used to select one of the displayed windows (identified with a pop-up window displaying the video input source for the selected window), 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. The API shall provide a means for these two rocker switches to be configured for internal display use or reported on any of the 1553 or Ethernet interfaces.

Aircraft Power and Panel Lighting

Aircraft Power.

3.2.1.1.11 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, not to exceed 4.6 amps with the heater on, in accordance with MIL-STD-704A will be supplied to the PAD as the source of external power. Normal current requirements (with the heater off) shall not exceed 3 amps. The PAD shall generate all other necessary operating voltages internally.

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.

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.

MIL-STD-1553B Interface.

The PAD shall provide two channels 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. The API shall provide a means for configuring each channel and identifying specific messages to monitor, send and receive.

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.

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.

MIL-STD-1553 Security Considerations.

The PAD shall do any internal processing of received 1553 data using volatile memory and shall not have the capability of recording any data received on either of the two 1553 busses.

Ethernet Interface.

The PAD shall provide one 1000BASE-T Ethernet interface, (also known as IEEE 802.3ae), with the capability to receive and transmit data; decode, unpack and display received HD video; and to encode, pack and transmit a duplicate of the video out analog signal. This interface shall pass data to and from the communications interface unit (CIU) to populate the upfront control (UFC) backup overlay. No data passed on this interface will be stored after power down. The API shall provide a means of defining the message packets to be sent and received.

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, as well as transmit over Ethernet. The detailed electrical, protocol and data requirements for this interface are contained in appendix B. The test application provided with the PAD shall display the bits as received. This data and symbol arrangement along with the EWWS data described below will hereafter be referred to as radar warning receiver (RWR) data.

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. In addition to these discretes, the PAD shall provide a driver to control 20 other discrete I/O pins, individually programmable through the API to be either inputs or outputs configured as gnd/open, 28VDC/open or 28VDC/gnd. The test application provided with the PAD shall read a customer-supplied text-based configuration file and set up the pins to demonstrate this capability.

Display Windows.

The PAD will be provided NTSC video in EIA RS-170A format from three external sources, and shall create three graphics screens, one from the RWR data, one from the engine data and one from the CIU. Each of the first five of these data sets can be displayed in any window of any of the three delivered window formats. Window selection mode is entered by the first press of the left side of the lower rocker switch. The window to be selected shall then be made by repeated presses of the left side of the lower rocker switch; selection is indicated by a pop-up message in the selected window displaying the video source active in that window. The default selection is the leftmost window in any configuration, and subsequent window selections will proceed clockwise with repeated presses of the switch. Graphics generated from the sixth data set will serve as a backup display of the UFC; this window will contain data passed over the Ethernet interface from the CIU such as current channel/frequency data for each of the three radios. See Appendix D for UFC backup overlay information.

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.

Aside from the delivered software configuration, the PAD shall provide the ability to enable up to seven active windows on the screen, defined by data provided in a text-based configuration file. Each of these windows may contain streaming video, still image files, graphics only, or graphics overlaid onto streaming video. Application software will generate multiple graphics datasets which may be overlaid onto active video, and will provide specifications for the number of windows, the size of those windows and the content for each one.

The driver for the video processing function shall perform the following functions: level balance all windows, size the streaming video and datasets appropriately, place them on the display as specified and overlay graphics datasets onto streaming video as appropriate. The test application provided with the display shall read a customer-supplied text-based configuration file which will identify up to seven active windows and three datasets, one of which will be overlaid onto one of the video streams, and produce a composite display as specified.

Sources.

The PAD shall rotate through the three video sources, two datasets and a blank screen with subsequent presses of the right side of the lower rocker switch. The source selected will be presented in a pop-up message in the active window. Pod, VSD, FPCD, RWR, EMD or No Vid will be provided in bright green text on a black background in the middle of the window. The pop-up will timeout two seconds after the last press of the right side rocker switch. The power-up default will have vid1 in the 6x6 window, vid2 in the upper right 2x2, vid 3 in the middle 2x2 and nothing in the lower 2x2. The PAD shall not be capable of recording any of the three video sources. The PAD shall measure each analog video source and compensate for differing input levels so all display windows appear to the same brightness level.

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.

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.

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.

RWR Overlay.

The RWR screen will be activated from a press of PB17 on the right side of the display and will then be displayed in the leftmost window. If the leftmost window has vid1 displayed, the RWR screen shall be overlaid onto that video, range scaled appropriately (see appendix B). If the leftmost 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 leftmost window, whether the vid1 source is present or not. The PAD shall not be capable of recording any of the RWR data it receives via the RWR or it internally generates for the overlay.

UFC Backup Overlay.

The UFC backup screen will be formatted to fit in a 1x4 overlay in the lower left corner, and to use pushbuttons 7-10 for menu selections. This overlay shall be displayed upon a press of PB15 on the right side of the screen. Details of the UFC backup screen content are provided in appendix D. The overlay will replace data underneath it (be opaque) if selected while in the 6x6 window format. The contents and size of this overlay shall be defined by a text-based configuration file. The overlay shall be deactivated by another press of PB15 (toggle on/off), and the contents (specific screen data) shall be ‘remembered’ from activation to activation. The power-up (or first activation) screen shall be the radio 1 screen as shown in appendix D.

EMD Overlay.

The EMD screen will be activated as a one-button press from a press of bezel button 14 and will then be displayed in the lower right window. If this 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:

Window Formats.

As delivered, the PAD shall provide the three window formats described below. The desired display format will be selected by repeated presses of the lower side of the bottom toggle on the right side of the display; 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.

Four-window.

With this format selected, the PAD shall create four windows in the 8x6 display, configured as shown below. This shall be the power-up (default) configuration.

Three-window.

With this format selected, the PAD shall create three windows in the 8x6 display, configured as shown below. 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.

640 x 640 pixels 384 x 384 pixels 384 x 384 pixels

Two-window.

With this format selected, the PAD shall create two 4x6 windows in the 8x6 display, configured as shown below. 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.

512 x 512 pixels 512 x 512 pixels

UFC Overlay.

Upon selection, the PAD shall position this overlay as a 1x4 opaque block in the lower left corner of the screen, with legends that align with the lower row pushbuttons 7-10. An example of this overlay in the two-window format is shown below.

Video Out.

An NTSC format video output representing the real-time PAD display shall be continuously provided regardless of the window format and video sources selected and shall contain all data sets as currently displayed, at a constant intensity level representing day mode mid-range brightness, regardless of the actual PAD intensity setting or mode. The PAD shall not be capable of recording this video output.

BIT Control Panel (BCP) /Avionics Status Panel (ASP) Interface.

As part of the delivered 24 discrete I/O lines, 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.

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, and displaying the firmware version number in the currently active window. After completion of the BIT, the PAD will wait for another transition of this input from open to 28VDC before starting another initiated BIT.

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.

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.

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 >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. 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.

Engine Monitor Discrete Interface As part of the delivered 24 I/O discretes, the PAD shall provide three with the following functions: 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.

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 the lower right corner window indicating the loss of engine monitor functionality.

Processor and memory spare The PAD as delivered shall have not less than100% spare memory for application program storage and not less than 100% spare CPU time.

Application program loading through external interface The PAD shall include a driver that can receive a new application program load through either one of the 1553 ports or the Ethernet port and permanently store, install and execute it. This capability shall be demonstrated by installing two versions of the test application delivered with the PAD.

Display Optical Characteristics.

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.

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.

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.

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.

Where:	Lmax = Maximum luminance measured at the display surface
	Lmin = Minimum luminance measured at the display surface
	Lmean = Mean luminance measured at the display surface

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

DAY/NIGHT MODE

LUMINANCE

OPERATING HOURS

DAY

320 foot-Lamberts

420

DAY

35 foot-Lamberts

DAY

7 foot-Lamberts

165

NIGHT

6.0 foot-Lamberts

225

NIGHT

0.1 foot-Lamberts

NIGHT

0.02 foot Lamberts

Total Operating Hours

1000

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.

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.

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.

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.

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

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.

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.

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.

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.

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.

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.

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.

Display Day/Night Transition.

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

Day to Night Transition

Night Mode Max ≤ Current Day Luminance	Night Mode Maximum ± 2 fL
Current Day Luminance < Night Mode Max	Maintain Luminance ± 2 fL

Night to Day Transition

Current Night Luminance ≤ Day Mode Min	Day Mode Minimum ± 2 fL
Day Mode Min ≤ Current Night Luminance	Maintain Luminance ± 2 fL

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.

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.

Non-Uniformities.

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

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.

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. This requirement will be applied to qualification units only.

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.

Detail Design Requirements.

Display Controls.

The display shall include the controls specified below.

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.

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.

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.

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.

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.

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.

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.

Heat Dissipation.

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

Physical Characteristics.

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.

Handling Provisions.

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

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.

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.

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).

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.

Scheduled Maintenance.

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

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.

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.

Temperature-Altitude.

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

+85°C

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

Explosive atmosphere.

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

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.

Salt-Fog…

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File details come from the government source that posted it. Updated Nov 14, 2017.