Attachment_2_Performance_Specification_Final.pdf

Remote Readout Unit Performance Specification for the

US Army Special Operations Command (USASOC) A/MH-6M Block 3.0 Avionics Management System (AMS)

Remote Readout Unit Performance Specification for the US Army Special Operations Command (USASOC)

VERSION/REVISION HISTORY

VERSION REV DESCRIPTION DATE APPROVED

N/A - Final June 17, 2015

Table of Contents

1.0 SCOPE

1.1 Document Scope

2.0 APPLICABLE DOCUMENTS

2.1 GOVERNMENT DOCUMENTS

2.1.1 Military Standards

2.1.2 Aeronautical Design Standards

2.2 NON-GOVERNMENT DOCUMENTS

3.0 REQUIREMENTS

3.1 Critical Item Definition

3.1.1 Critical Item Configuration

3.1.2 External Interface Requirements

3.2 Performance Characteristics

3.2.1 Display Format

3.2.2 Optical Performance

3.2.3 Display Defects

3.2.4 Physical Characteristics

3.2.5 Reliability

3.2.6 Maintainability

3.2.7 Environmental

3.2.8 Electromagnetic Environmental Effects

3.2.9 Nameplates and Product Markings

3.2.10 Interchangeability

3.2.11 ARINC 661

3.2.12 Software Loading

4.0 Definitions

4.1 Contrast – Day Mode

4.2 Contrast – Night (NVIS) Mode

4.3 Defects, pixel – cluster

4.4 Defects, pixel/sub-pixel – partial

4.5 Defects, pixel – stuck

4.6 Defects, pixel – stuck on

4.7 Display Readability:

4.8 Illumination, high ambient

4.9 Illumination, low ambient

4.10 Luminance, Large Area

4.11 Luminance, Small Area

4.12 Response Time

4.13 Temperature, Elevated Range

4.14 Temperature, Nominal Range

4.15 Temperature, Room

5.0 REFERENCES

5.1 Display Metrology References

5.1.1 Information Display Measurements Standard

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

List of Tables

TABLE 3-1 POWER UTILIZATION

TABLE 3-2 DIGITAL INTERFACES

TABLE 3-3 CHROMATICITY REQUIREMENTS (CIE 1976 U’, V’ COORDINATES)

TABLE 3-4 CONTRAST RATIO VS. VIEWING ANGLE LIMIT & AMBIENT ILLUMINATION LEVEL

TABLE 3-5 RESPONSE TIME GREY LEVEL START/STOP MATRIX

TABLE 3-6 ENVELOPE DIMENSIONS

TABLE 3-7 CRASH LOADS

TABLE 3-8 MTBF

TABLE 3-9 EMI TEST REQUIREMENTS

List of Figures

FIGURE 3-1 RRU VIEWING DISTANCE

FIGURE 3-2 HORIZONTAL VIEW ANGLE

FIGURE 3-3 VERTICAL VIEW ANGLE

FIGURE 3-4 CONCEPTUAL DISPLAY FORMAT

FIGURE 3-5 GUNFIRE VIBRATION PROFILE

http://eusta436401sp01/me/avionics/melb3/Shared%20Documents/Acq%20Package%20-%20RRU/archive/Blk%203%20RRU%20Performance%20Specification%20Draft%20Rev%20D.docx#_Toc419121196

1.0 SCOPE

1.1 Document Scope

The Block 3 avionics upgrade concept will utilize some existing aircraft Line Replaceable Units (LRUs), modify others, and integrate new LRUs. A new large format Multi-Function Display (MFD) and a Mission Computer (MC) with significant general purpose and graphics processing capability will provide the fundamental means of addressing the Block 3 Modernization Program objectives. Additionally, replacement of the current 10 character, single line Remote Readout Units (RRUs) with LCD displays, will provide increased SA data to the operator while minimizing heads-down, in-the-cockpit orientation. This document addresses the performance requirements for the RRU LRU.

2.0 APPLICABLE DOCUMENTS

The following documents of the issue listed form a part of this document to the extent specified herein. In the event of a conflict between the documents referenced herein and the contents of this specification, the contents of this specification take precedence.

2.1 GOVERNMENT DOCUMENTS

2.1.1 Military Standards

FED-STD-595B Colors Used in Government Procurement

MIL-STD-130G Identification Marking of U.S. Military Property

MIL-STD-461F Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment

MIL-STD-704F Aircraft Electrical Power Characteristics

MIL-STD-810G

w/ Change 1

Environmental Engineering Considerations and Laboratory Tests

MIL-STD-882E Standard Practice for System Safety

MIL-STD-1472E Human Engineering Design Criteria for Military Systems, Equipment and Facilities

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

MIL-38999J Connectors, Electrical, Circular, Miniature, High Density, Quick Disconnect (Bayonet, Threaded, and Breech Coupling), Environment Resistant, Removable Crimp and Hermetic Solder Contacts, General Specification for

2.1.2 Aeronautical Design Standards

ADS-37A Electromagnetic Environmental Effects (E3) Performance and Verification Requirements

ADS-71-SP Aeronautical Design Standard Practice Environmental Airworthiness and Qualification Requirements For Electronics, Avionics, and Mission Equipment Installed on Army Aircraft

2.2 NON-GOVERNMENT DOCUMENTS

ANSI/TIA/EIA-422-B RS-422 Electrical Characteristics of Balanced Voltage Differential Interface circuits

ARINC 429-15 MARK-33 Digital Information Transfer System

ARINC 615A Software Data Loader Using Ethernet Interface

ARINC 661-5 Cockpit Display System Interfaces to User Systems

DO-178C Software Considerations in Airborne Systems and Equipment Certification, RTCA

DO-254 Design Assurance Guidance for Airborne Electronic Hardware

IEEE 802.3 IEEE Standard for Ethernet

IDMS-1.03 Information Display Measurements Standard; SID, ICDM, and VESA http://store.aviation-ia.com/cf/store/catalog_detail.cfm?item_id=71

3.0 REQUIREMENTS

3.1 Critical Item Definition

The Remote Readout Unit is intended to be the a supplementary graphical interface between the operator and the avionics for the A/MH-6 air vehicle providing pertinent mission data to the operator without requiring the crew to refer to the CDU and other in-the-cockpit controls and displays. Each A/MH-6 will be equipped with two RRU LRUs. One, or both, RRUs may be utilized during operating conditions when power consumption must be kept at a minimum (I.E. Mission Computer and MFD not powered on). The RRUs will be installed in the aircraft where it will be exposed to harsh military operating environments and abnormally high temperatures. The heat generated by the RRU LRU can also adversely affect other LRUs in the aircraft. The RRU LRU must be powered by DC voltage as no AC power supply is available on this aircraft.

3.1.1 Critical Item Configuration

This specification provides the requirements for the RRU for which, utilizing ARINC-661 protocol, the RRU will provide pertinent mission data to the operator.

The RRU shall include its own internal power supply, and Input/Output (I/O). The RRU shall provide Electromagnetic Interference (EMI) filtering to protect its internal components.

3.1.2 External Interface Requirements

In the context of this specification, the term “external interface” refers to any equipment external to the RRU itself. This includes other components of the Avionics System (such as Mission Computer) and aircraft subsystems external to the Avionics Management System (such as navigation sensors). The following paragraphs identify the external interfaces required of the RRU hardware.

3.1.2.1 Electrical Interfaces

3.1.2.1.1 Aircraft Power

The RRU shall meet the requirements specified herein when provided aircraft power as defined IAW MIL-STD- 704.

Table 3-1 Power Utilization

Category Power Requirements

Operation 28 VDC

The RRU product shall operate through a 150 millisecond interruption of 28VDC. For the duration of the power interruption, the display screen is permitted to be blank, and heaters (if applicable) disengaged.

3.1.2.1.2 Power Consumption

The RRU product shall consume no more than 50 Watts max of 28VDC (T), 30 Watts (O), including any heaters at maximum load.

3.1.2.1.3 Interface Protection

The RRU shall provide protection from damage by shorts to ground or open circuits of external interfaces. The RRU shall contain circuitry which prevents damage as a result of the application of reverse voltage to the RRU primary power input.

3.1.2.2 Digital Interfaces

The RRU shall provide the digital interfaces as specified in Table 3-2. The requirements for each interface type are specified in subsequent paragraphs. The RRU digital interfaces operate at the data rates and within accuracy limits as specified in the following paragraphs.

Table 3-2 Digital Interfaces

Interface Type Total Quantity Intent

Units Threshold Objective

Ethernet 1 T=O ARINC-661 command, Bezel Key depression data, status, control

3.1.2.2.1 Ethernet

The RRU product shall provide a minimum of one (1) independent Ethernet interface available external to the product. Primary intent is for transmission of ARINC-661, status, and control.

The RRU shall provide side strapping and software capability to dynamically set IP addresses based on RRU installation location on the platform.

3.2 Performance Characteristics

Unless otherwise specified, the values specified herein establish the requirements for satisfactory performance of the RRU.

3.2.1 Display Format

3.2.1.1 Display Active Viewing Area

The display shall be landscape oriented, with minimum active area viewing dimensions of 3.7 inches by 2.1 inches.

3.2.1.2 Display Resolution

The display resolution shall not be less than 480 horizontal pixels by 272 vertical pixels.

3.2.1.3 Display Bit Depth

The display bit depth shall be 24 bits (8 bits per color channel).

3.2.2 Optical Performance

3.2.2.1 RRU Viewing Distance

The viewing distance from the nominal eye position to the center of the same side display is 27.7 inches (Figure 3-1).

3.2.2.2 RRU Viewing Angle

The viewing angle performance of the RRU shall take into account the fact that the nominal viewing point of each of the pilots will be horizontally offset from the same side display center by ± 20° (Figure 3-2).

Additionally, the nominal eye position for the pilots will be 13° above the display normal (Figure 3-3). Note: The display viewing surface is tilted 3° off-vertical (away from the observer).

The eye-box tolerances for the nominal eye-point are given as:

Vertical: ± 1.70 inches (43 mm) Fore/Aft: 2.15 inches (55 mm) Interpupillary Distance: 2.05 inches to 3.07 inches (52mm to 78mm)

Pilot eyepoint to center pilot’s RRU: 27.7”

Figure 3-1 RRU Viewing Distance

Figure 3-2 Horizontal View Angle

Figure 3-3 Vertical View Angle

3.2.2.2.1 Primary Viewing Angle

The primary viewing angle limit is defined as being ± 15 degrees in the horizontal axis and 23° ± 10°in the vertical axis, as referenced from the display normal.

3.2.2.2.2 Secondary Viewing Angle

The secondary viewing angle limit is defined as being ± 30 degrees in the horizontal axis and 23° ± 20°in the vertical axis, as referenced from the display normal.

3.2.2.2.3 Peripheral Viewing Angle

The peripheral viewing angle limit is defined as being ± 60 degrees in the horizontal axis and 23° ± 30°in the vertical axis, as referenced from the display normal.

3.2.2.3 Reflectivity

3.2.2.3.1 Specular Reflectance

The maximum specular reflectivity shall be 0.7%.

3.2.2.3.2 Diffuse Reflectance (White)

The maximum diffuse reflectivity of display areas that are driven to the full-on white state (255) shall be less than 0.25%.

3.2.2.3.3 Diffuse Reflectance (Black)

The maximum diffuse reflectivity of display areas that are driven to the full-off black state (000) shall be less than 0.15%.

3.2.2.4 Chromaticity

3.2.2.4.1 Day mode chromaticity

The day mode display chromaticity shall provide a color gamut that meets or exceeds the requirements of Table 3-3 when measured along the display normal under low ambient conditions.

Table 3-3 Chromaticity requirements (CIE 1976 u’, v’ coordinates)

Nominal u’ coordinate Nominal v’ coordinate Tolerance Radius (r)

Chromaticity (white) 0.196 0.494 0.035

Chromaticity (red) 0.420 0.520 0.035

Chromaticity (green) 0.122 0.549 0.035

Chromaticity (blue) 0.180 0.170 0.035

3.2.2.4.2 Night (NVIS) mode chromaticity

The night (NVIS) mode display chromaticity shall provide a color gamut that meets or exceeds the requirements of Table 3-3 when measured along the display normal under low ambient conditions.

3.2.2.5 Day Mode Luminance

3.2.2.5.1 Day Mode Luminance

The minimum acceptable average display luminance in the day mode shall be 300 fL when driven white (255R, 255G, 255B) as measured 23° above the display normal in a low light ambient environment for all ambient temperatures (Ta) such that -40°C ≤ Ta ≤ 55°C.

3.2.2.5.2 Day Mode Luminance Dimming Range

The day mode display white (255R, 255G, 255B) luminance range shall be adjustable from ≤ 1 fL to ≥ 300 fL in either an analog continuous fashion, or in a monotonically increasing step function of not less than 64 linear increments.

3.2.2.5.3 Day Mode Large Area Luminance Non-uniformity

The day mode display white (255R, 255G, 255B) large area luminance non-uniformity NL shall be ≤ 40% across the entire display active area; with no perceptible lines of demarcation across within the display active area. The large area luminance uniformity shall be sampled using a 3x3 matrix, with the edge point centers to be located 1/10 of the vertical and horizontal screen size from the edges of the screen, and the middle points centered between the edges. Each sampling location shall have not more than a 10x10 pixel square sampling area or not more than a 10 pixel diameter circular sampling area (but not less than 5x5 pixels or 5 pixel diameter). The non-uniformity of the display N is calculated by the following relationship:

𝑁𝐿 ≤ 100% (1 −

𝐿𝑚𝑖𝑛

𝐿𝑚𝑎𝑥

Where Lmin is the lowest mean luminance across all of the sampled zones and Lmax is the highest mean luminance across all of the sampled zones, and NL is the large area non-uniformity of the display.

3.2.2.6 Night (NVIS) Mode Luminance

3.2.2.6.1 Night (NVIS) Mode Luminance

The display white luminance in the night (NVIS) mode shall be 2.2 ± 0.5 fL when driven white (255R, 255G, 255B) as measured along the display normal in a low light ambient environment for all ambient temperatures (Ta) such that -40°C ≤ Ta ≤ 55°C.

3.2.2.6.2 Night (NVIS) Mode Luminance Dimming Range

The minimum acceptable display white (255R, 255G, 255B) luminance adjustment range in the night (NVIS) mode shall be from ≤ 0.01 fL to 2.2 ± 0.5 fL in either a continuous analog fashion, or in a monotonically increasing step function of not less than 64 linear increments.

3.2.2.7 Night (NVIS) Mode Radiance

3.2.2.7.1 Night (NVIS) Mode – NVIS Radiance

The display shall meet all NVIS Class B requirements of MIL-STD-3009 for color multi-function displays.

3.2.2.7.2 Night (NVIS) Mode – Light Leakage

The display shall limit light emissions to that of intended areas such as the display active area and bezel information and/or control areas. There will be no extraneous energy detectable using either the unaided eye or an NVIS Class B image intensifier system.

3.2.2.8 Contrast Ratio

3.2.2.8.1 Contrast Ratio Under Low Ambient Illumination Conditions

The minimum contrast ratio of the display shall be 300:1, as measured normal to the display active area plane under low ambient illumination conditions and at room temperature conditions. Contrast shall decrease with viewing angle increase in a monotonic fashion with no contrast reversal being permitted.

3.2.2.8.2 Contrast Ratio Under High Ambient Illumination (10K fc) Conditions

The minimum contrast ratio shall meet the limits as defined in Table 3-4: Contrast Ratio vs. Viewing Angle Limit at Ambient Illumination Level.

Table 3-4 Contrast Ratio vs. Viewing Angle Limit & Ambient Illumination Level

Viewing Angle Limit Contrast Ratio for Ambient Temperature Range

Nominal (-40°C to 55°C) High (+56°C to 71°C)

Primary 24 12

Secondary 21 10

Peripheral 12 6

3.2.2.9 Temporal – Display Refresh Rate

The display refresh rate shall be 60 Hz, progressive.

3.2.2.10 Temporal – Display Flicker

The display shall not exhibit flicker when viewed in either day or night operating modes.

3.2.2.11 Temporal – Display Response Time

The display response time shall be tested according to Table 3-5: Response Time Grey Level Start/Stop Matrix.

Table 3-5 Response Time Grey Level Start/Stop Matrix

Step Response Stop Grey Level

0 52 98 137 169 195 217 234 247 255

S te p R e sp o n se S ta rt

G re y L ev el

0 22.9 25.3 27.1 29.1 30.1 28.5 30.6 30.2 28.7

52 5.4 20.6 24.8 28.3 29.5 30.1 28.8 30.9 28.6

98 5.1 17.6 24.5 24.6 29.1 30.7 31.6 32.4 28.5

137 4.8 17.4 19.4 28.3 28 31.6 32.5 32.7 32.3

169 4.8 17.4 21.6 21.8 25.4 30.3 30.3 31.5 31.6

195 4.3 18.1 21.7 24.1 30.9 25.6 34.7 33.7 36.1

217 4.3 18.1 21.8 35.2 29.9 31.6 26.5 30.7 36.1

234 4.6 18.3 22.6 26.2 29.5 30 20.3 26.3 41.6

247 4.3 18.5 22.4 26.5 28.7 33 33.8 40.7 44.4

255 4.0 18.7 23.4 30.2 28.0 32.9 37.3 43.9 45.3

The tested transition states shall be as given by the start (green values)/stop (red values) transition matrix.

The display response time (tR) shall meet the following limits after a 20 minute warm-up period has elapsed:

tR (minimum) ≤ 8 ms, tR (maximum) ≤ 50 ms, and tR (average) ≤ 30 ms. The response time values listed in Table 3-5 are for example only.

3.2.2.12 Warm-Up and Cool-Down

Low Temperature Conditions:

The RRU shall be readable and fully operational in less than 2 minutes after the RRU power has been switched on from -40°C (inclusive) to 0°C.

High Temperature Conditions:

The RRU shall be readable and fully operational in less than 30 seconds after the RRU power has been switched on from 0°C (inclusive) to 55°C (inclusive).

3.2.3 Display Defects

3.2.3.1 Display Cosmetic Defects

The display shall not exhibit any of the following defects, when observed from the limits of the eye design box:

bubbles, cracks, discoloration, and inclusions.

3.2.3.2 Display Pixel Defects

The display pixel defects shall be limited to following:

Single pixel stuck defect ≤ 10 pixels

Single pixel stuck-on defect ≤ 5 pixels

Single partial pixel defect ≤ 7 pixels

Cluster pixel defects = 0

3.2.4 Physical Characteristics

3.2.4.1 Physical Dimensions

The RRU physical dimensions, including bezel assembly and mounting, shall be less than or equal to the envelope specified in Table 3-6.

Table 3-6 Envelope Dimensions

Dimension

Height (inches)

Front Assembly

(T) 3.50

(O) 3.25

Width (inches) Front Assembly

Max 5.00

Depth (inches) (behind front face of mount surface)

Max 5.00

The RRU interfaces shall not be positioned in a manner such that connectors extend beyond the LRU maximum assembly width or height specified above.

Figure 3-4 Conceptual Display Format

3.2.4.2 Bezel Assembly

Equipment controls and push-buttons shall be contained within an externally mounted bezel. The bezel shall contain NVIS B compatible lighting for all control switches and panel legends. The bezel lighting shall be controlled by the cockpit lighting control system 28VDC (T), 5VDC (O).

The RRU bezel assembly shall be equipped with 1 (T), 4(O) momentary contact tactile feedback push-buttons.

Bezel key operation (I.E. depression) shall be transmitted via ARINC 661 (reference Section 3.2.11) events over Ethernet.

Additional device controls, including RRU On/Off, Brightness, Contrast, Day/Night shall also be provided.

Figure 3-4 provides a conceptual image of the display format.

3.2.4.3 Weight

The RRU shall not exceed 5 lbs (T), 3 lbs (O) when configured to meet all Section 3.0 requirements.

3.2.4.4 Mounting

The RRU product shall be configured with hard points for mounting to the aircraft structure. The mounting points shall not fail when subjected to crash loads for the A/MH-6M as shown in Table 3-7.

Table 3-7 Crash loads

Direction Maximum (Gs)

Fore/Aft 17

Lateral 6

Vertical 15

3.2.4.5 Finish

The RRU product shall have an exterior surface finish in black/corrosion resistance accordance with FED- STD-595, Color No. 37038. Those portions of the RRU which are not visible with the unit mounted normally do not need to be finished in black, but shall employ suitable corrosion protection methods.

3.2.4.6 Bonding and Grounding

The mounting surface of the RRU and its connectors shall meet Class R (2.5 mOhms) of MIL-B-5087 to allow the RRU to be grounded to the aircraft in a manner that meets EMC and protects personnel from electrical hazards. All externally exposed metal parts, and connectors shall be grounded to the chassis. If shielding gaskets are necessary they shall be used in a manner that considers the effects of dissimilar metal combinations.

3.2.4.7 Cables and Connections

The RRU shall utilize MIL-38999 connectors for connection to the aircraft wiring. The RRU shall provide a pin connected internally to chassis ground on each connector interfacing to the aircraft wiring. Connector spacing shall use MIL-STD-1472 as a guide. External connectors shall have a corrosion resistant finish of Class W or better. External connectors shall be keyed to prevent improper connection of the RRU.

3.2.4.8 Thermal Design

With no aircraft provided cooling, the RRU product shall be designed to operate continuously between temperature extremes of -40ºC and +71ºC in accordance with MIL-STD-810G.

3.2.5 Reliability

The RRU product shall have a predicted Mean Time Between Failures (MTBF) as listed below in Table 3-8.

Table 3-8 MTBF

Platform

Rotary Wing 3000 Hours(T)

5000 Hours (O)

3.2.5.1 Interface Failure Modes

N/A

3.2.5.2 Operational Stability

The RRU shall meet specified performance for a period equal in duration to one MTBF without the necessity for readjustment of controls which are inaccessible to the operation during normal use.

3.2.6 Maintainability

3.2.6.1 Preventive Maintenance

The RRU shall meet the MTBF requirement in 3.2.5 Reliability without preventive maintenance.

3.2.6.2 Adjustments

The RRU shall require no mechanical or electrical adjustments when installed in the aircraft.

3.2.6.3 Peculiar Support Equipment

The RRU shall require no peculiar support equipment for Organizational Level Maintenance.

3.2.6.4 Organizational Level Maintenance

Organizational level maintenance will be limited to isolation of a RRU failure and the removal and replacement of the RRU.

3.2.6.4.1 Special Tools

The RRU shall require no special tools for removal or replacement in the aircraft.

3.2.6.4.2 Built In Test (BIT)

The RRU shall be designed to provide the following minimum BIT related functions

a. overall display status

b. heater status (if applicable)

c. bezel status

d. backlight status

e. overheat condition

f. stale data indication (display video not updated)

3.2.6.4.2.1 Failure Detection Function

The RRU BIT shall be designed such that a combination of power-up and continuous BIT automatically detects 95% of all faults within the RRU. False alarms shall not exceed 5%.

The RRU product shall provide a BIT capability with 95% detection capability.

The RRU product shall monitor the BIT status of its I/O, and report supported BIT statuses.

3.2.7 Environmental

3.2.7.1 Temperature, humidity, altitude.

The RRU shall meet the requirements of MIL-STD-810G, Method 520.4 (Procedure III). The maximum operating altitude shall be 15,000 feet pressure altitude. The minimum operating temperature is -40°C and the maximum operating temperature is 71°C.

3.2.7.2 High Temperature Storage.

The RRU shall meet the requirements of MIL-STD-810G, Method 501.6 (Procedures I and II).

3.2.7.3 Low Temperature Storage.

The RRU shall meet the requirements of MIL-STD-810G, Method 502.6 (Procedures I and II).

3.2.7.4 Low Pressure (Altitude).

The RRU shall meet the requirements of MIL-STD-810G, Method 500.6 (Procedure I).

3.2.7.5 Temperature Shock

The RRU shall meet the performance characteristics specified here in during exposure to variable temperature conditions ( 5C/min, within the range of operating temperatures specified in paragraph above as specified in MIL-STD-810G, Method 503.6 Proc I-C, 3 cycles minimum). The RRU design is intended to withstand changes in temperature without damage due to extreme temperature military operations.

3.2.7.6 Humidity

The RRU shall meet the performance characteristics specified here in without damage or loss of function after exposure to 95% relative humidity conditions for MIL-STD-810G, Method 507.6 Procedure II.

3.2.7.7 Salt Fog

The RRU shall meet the performance characteristics specified here in without damage or loss of function after exposure to salt atmosphere or salt spray for MIL-STD-810G, Method 509.6.

3.2.7.8 Sand and Dust

The RRU shall meet the performance characteristics specified here in after exposure to blowing sand and dust for MIL-STD-810G, Method 510.6, Proc I & II. Marking, paint, and surface deterioration on control panels is permissible.

3.2.7.9 Rain

The RRU shall meet the performance characteristics specified here in without damage or loss of function during exposure to falling water for MIL-STD-810G, Method 506.6, Proc III. As an internally mounted piece of equipment the RRU design is intended to withstand leaks and aircraft washes.

3.2.7.10 Fungus

The RRU shall meet the performance characteristics specified here in without damage or loss of function during exposure to fungus MIL-STD-810G, Method 508.7. Fungus requirement may be met by analysis.

3.2.7.11 Vibration

The RRU shall provide the required performance specified here in when exposed to vibration levels and duration’s experienced in the aircraft operating environment (background vibration and rotor modulation sine tones) for MIL-STD-810G, Method 514.7, Proc I, Cat 14-Rotary Wing Aircraft – Helicopter: 1P = 7.92 Hz, 1T =

44.38 Hz, n=6, m=4, Method 516.7, Proc I, V & VI, and Method 519.7 Proc III.

3.2.7.11.1 Shock

The RRU product shall meet the requirements of MIL-STD-810G, Method 516.7 for functional shock (Procedure I), crash hazard shock (Procedure V), and bench handling test (Procedure VI).

3.2.7.11.2 Gunfire Shock

The RRU shall meet the requirements of MIL-STD-810G, Method 519.7 Procedure III, functional performance characteristics specified in Figure 3-5. The spectrum shall be applied for 3 hours per axis.

Figure 3-5 Gunfire Vibration Profile

3.2.7.12 Explosive Atmosphere

When operating in an explosive gas and air ambient mixture the RRU shall not cause ignition of the mixture for MIL-STD-810G, Method 511.6, Proc I.

3.2.7.13 Solar Radiation

The RRU product shall meet the requirements of MIL-STD-810G, Method 505.5, for effects of direct sunlight (Procedure I).

0.001

0.01

0.1

1 10 100 1000 10000

P o w e r Sp e ct ra l D e n si ty g^

/H z

Frequency, Hz

A/MH-6M Gunfire Vibration Spectrum

10 Hz, 0.01

20 Hz, 0.026 120 Hz, 0.029

60 Hz, 0.013

600 Hz, 0.03

700 Hz, 0.03

3.2.8 Electromagnetic Environmental Effects

3.2.8.1 Electromagnetic Interference (EMI)

The RRU shall meet the requirements of MIL-STD-461 for flight critical application as shown in Table 3-9.

The RRU shall be designed with hardening for narrow and wide band EMI.

Table 3-9 EMI Test Requirements

Test Requirement Description

CE101

Power Leads 30Hz to 10kHz

CE102

Power Leads 10kHz to 10MHz

RE102

Electric Field 10kHz to 18GHz

CS101

Power Leads 30Hz to 150kHz

CS114

Bulk cable injection 10kHz to 200MHz

CS115

Bulk cable/impulse 5A, 30 ns

RS103, per

ADS-37A-PRF

Table I, Parts A/B

Electric Field

CS116

Damped sinusoidal transients 10kHz to 100MHz

RE101

Magnetic field 30Hz to 100kHz

RS101 Magnetic Field, 30 Hz to 100 kHz

3.2.8.2 Static Electricity

When installed in the aircraft, the RRU shall preclude damage or upset from electrostatic discharge (ESD) due to handling of the equipment by operating or maintenance personnel.

3.2.9 Nameplates and Product Markings

The RRU nameplate format and content shall be in accordance with MIL-STD-130. Markings shall be permanent, securely fastened, and shall withstand the operational and storage environment of the aircraft, environmental testing, and cleaning procedures. Markings shall be a color which is in contrast to the color of the background surface. Markings of items shall not adversely affect the life and utility of the item. Detailed parts shall be marked with their assigned part numbers in accordance with MIL-STD-130.

3.2.10 Interchangeability

Any RRU product with the same part number shall be interchangeable.

3.2.11 ARINC 661

The RRU shall possess an ARINC 661 server, accepting graphical drawing commands via Ethernet utilizing the ARINC 661Cockpit Display System Interfaces to User Systems standard. As a minimum, the RRU product shall be capable of accepting ARINC 661 layer/widget commands and display of graphics symbology to include alphanumeric text strings, events, and widget list as defined in the ARINC 661 standard sections 3.1 thru 3.3, with the exception of dynamic motion and map management (including any other widgets related to map).

3.2.12 Software Loading

The RRU System Software and ARINC 661 Binary Definition Files (BDFs) shall be loadable per ARINC 615A.

4.0 Definitions

4.1 Contrast – Day Mode

Day mode contrast, otherwise known as “simple” contrast is defined as the ratio of the white driven state (255R, 255G, 255B) to the black driven state (000R, 000G, 000B) at the same display luminance setting.

4.2 Contrast – Night (NVIS) Mode

Night or NVIS mode contrast shall be as defined by MIL-STD-3009.

4.3 Defects, pixel – cluster

A cluster defect consists of two or more inoperative (stuck) pixels that are adjacent to one another (nearest neighbors) such that the defect is effectively greater than one pixel in area.

4.4 Defects, pixel/sub-pixel – partial

A partial pixel is defined as a pixel that is either stuck between the white threshold and the black threshold independent of the video signal or a pixel that has defective sub-pixels and/or area defects within the pixel such that not all areas of the pixel respond properly to the video signal. A defective partial pixel that has a fixed luminance value that is greater than 1/3 the white luminance threshold value shall be counted as a stuck-on pixel.

4.5 Defects, pixel – stuck

A stuck pixel is defined as a pixel that is non-responsive to a video signal that would normally induce a change in pixel luminance and/or chrominance.

4.6 Defects, pixel – stuck on

A stuck on pixel is defined as a pixel that fails at or near the full white state, and is non-responsive to a video signal that would normally induce a change in pixel luminance and/or chrominance. Note: a “stuck-on” pixel shall be counted against the “stuck” pixel total.

4.7 Display Readability:

Display readability is defined as meeting a 3:1 symbol contrast ratio (as defined in MIL-STD-3009) over the peripheral viewing cone under a 10,000 fc ambient lighting condition.

4.8 Illumination, high ambient

High ambient illumination is defined as incident illumination of 10K fc.

4.9 Illumination, low ambient

Low ambient illumination is defined as incident illumination of ≤ 5E-5 fc or ≤ 5E-5 fL of equivalent background luminance as measured on the display active surface area when the display is off.

4.10 Luminance, Large Area

Large area luminance is defined as the average luminance of an array of sampled display zones ~10 pixel diameter circular areas or that of ~10x10 pixel square areas. Large area luminance is used to indicate gross display luminance control (i.e. backlight uniformity).

4.11 Luminance, Small Area

Small area luminance is defined as the luminance of an area on the order of the display individual pixel size.

Small area luminance is used to indicate luminance variability at the display feature level (i.e. symbol, font and map feature legibility).

4.12 Response Time

The display response time is defined as the transition time required for the display to respond to a step-response of any specified “start” grey video level to a corresponding “stop” grey video level. The transition time is further defined to be between the 10% and 90% values of the settling states of those start/stop grey video levels.

4.13 Temperature, Elevated Range

The elevated temperature range is +56°C to +71°C.

4.14 Temperature, Nominal Range

The nominal temperature range is -40°C to +55°C.

4.15 Temperature, Room

Room temperature is defined as 20°C to 25°C.

5.0 REFERENCES

5.1 Display Metrology References

5.1.1 Information Display Measurements Standard

Unless otherwise specified within this document, or specifically authorized in writing by the Government, all test, measurement and analysis methods will coincide with current accepted industry standard practices as specified by the

Information Display Measurements Standard, Version 1.03 June 1, 2012; Society for Information Display, International

Committee for Display Metrology & Video Electronics Standards Association.

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

Unless otherwise specified within this document, or specifically authorized in writing by the Government the requirements and test methods of MIL-STD-3009, 2 February 2001 shall take precedence regarding all NVIS related display parameters.