AVNS-DTL-10868.docx

AVNS-DTL-10868 (DRAFT)

APPENDIX A

AVNS-DTL-10868B

APPENDIX A

SUPERSEEDING

ANVS-DTL-10868A

27 AUG 2012

DETAIL SPECIFICATION

ITEM SPECIFICATION

FOR

THE AIR SOLDIER

Common Helmet Mounted Display

DISTRIBUTION STATEMENT A: Approved for public release; distribution unlimited.

DETAIL SPECIFICATION

ITEM SPECIFICATION

FOR THE

AIR SOLDIER

Common Helmet Mounted Display (CHMD)

Prepared for:

US Army Aviation and Missile Command Redstone Arsenal, Alabama 35898

Prepared by:

Product Manager – Air Warrior (PM-AW) Huntsville, Alabama 35806

REVISION HISTORY

CHANGE RECORD

This sheet is a record of each issue of this document. When the revised document is issued, the previous issue is automatically superseded.

Management Pages Changed Reason for Change

Initial Rel.

Rev. A

06/21/2012

08/27/2012 David Rabb

David Rabb

N/A

Pg. 10

N/A

Update to specification to clarify technical issues

Pg. 15

Pg. 35 Remove Ozone from list of battlefield contaminants Change verification method from test to analysis

Rev. B

Steve Sanders

Added paragraphs 3.1.2.1 and 3.1.2.2

Added paragraphs 3.3.1.1 through 3.3.1.3. Updated 3.3.1 and 3.3.2

Updated paragraphs 3.3.3 through 3.3.7. Added 3.3.5.1.1 through 3.3.5.1.3, Clarified Horizontal and Vertical

Updated paragraphs 3.3.9, 3.3.14, 3.3.16, and 3.3.19

Para. 3.6.1.3, Update to altitude requirements.

Para. 3.6.8, Update to altitude requirements.

AVNS-DTL-10868

12,23,& 32-33

Pg.12

17-18

22-23

31-32

Change of KHz to kHz

Para 3.6.10, Updated Vibration Requirement

Added Para 3.10 through 3.11

Changed requirements for Transmittance 4.3.1

Updated 4.3.2

Added Diagonal FOV

Updated Figure 9

Updated Figure 10 and added Figure 11 and Figure 12

Updated paragraph 4.3.7

Updated paragraph 4.3.19 and 4.3.20

Removed Figure 16

Par 4.6.7, add additional verification method (analysis); Para. 4.6.8, Update to altitude requirement.

Para 4.6.10, Updated Vibration Requirement

Management Pages Changed Reason for Change

38-39

36-38

39-44

49-50

Para. 4.6.8, increased altitude requirement for Combined Environmental Effects

Added Para 4.10 through 4.11

VCRM table, updated requirement 3.6.7 to allow Analysis; added First Article and Conformance Inspection; restructured columns; added requirements 3.10 through 3.11.

Added Tables III and IV

Added paragraph 6.2 and renumbered subsequent paragraphs.

Replaced Cable Interface diagram, Fig A-2

Updated Table A-VI

55-56

57-58

Appendix A

Modified A.2.3.1

Added A.2.3.2.1 and A.2.3.2.2

Added Fig A-3 and A-4

Added Table A-X and Table A-XI

Added Appendix A

Table of Contents

LIST OF TABLES

LIST OF FIGURES

APPENDIX

A HELMET DISPLAY AND TRACKING SYSTEM (HDTS) INTERFACE CONTROL DOCUMENT (ICD)………………………………………….44

AVNS-DTL-10868B

ii

1.0 SCOPE

This specification defines the requirements for the Engineering and Manufacturing Development (EMD) phase for the Common Helmet Mounted Display (CHMD). The CHMD is an advanced, see-through, high-definition, digital helmet mounted display (HMD) to support all Army Rotary Wing platforms (except the AH-64D). The display is intended to replace the current Heads Up Display (HUD). The display will be integrated onto a Rotary Wing Helmet (RWH) HGU-56/P modified to include a magnetic head tracker and other head borne Aviation Life Support Equipment (ALSE) equipment.

1.1 Background. Air Soldier is the next generation aircrew mission and protective ensemble that will replace the legacy Air Warrior (AW) system currently being used by Army rotary and select fixed wing aircrew members. Air Soldier encompasses all clothing and individual equipment worn or carried by the pilot and aircrew members, including ancillary aircraft mounted hardware and components, that serve the primary objectives of physiological sustainment, personal protection, and enhanced mission performance; while operating in all environmental and threat conditions, including crash and post-crash escape, survival and evasion scenarios. The Air Soldier System (Air SS) consists of four subsystems that provide:

· A fully integrated suite of personal electronics (PE) equipment that replaces stovepipe legacy components and provides improved data processing, control, and presentation technologies to reduce overall pilot workload while providing a minimum 30% reduction in weight and 70% reduction in bulk

· A modular integrated helmet and display system (MIHDS) featuring increased crash and laser eye protection, enhanced durability, head tracking and a high resolution display.

· A revolutionary personal protective clothing ensemble and gear carriage system that provides protection equal to or better than the legacy AW system, while providing a minimum 25% reduction in bulk and weight through a reduction in layering and utilization of active thermal regulation

· A fully optimized man/machine interface that maximizes the use of wireless interfaces to enhance aircrew mobility and the ability to safely ingress/egress the A/C in all mission configurations

1.2 Item description. The CHMD is part of the Air Soldier Modular Integrated Helmet and Display System (MIHDS), more specifically the Helmet Display and Tracking System (HDTS). The CHMD is a helmet mounted display system that overlays symbology onto a see-through display that allows the aviator to view pertinent flight parameters without looking down at aircraft instrumentation. The CHMD will receive power and information via an aircraft mounted Advanced Sight and Display Computer (ASDC). The CHMD will be mounted on the HGU-56/P helmet and connected to the ASDC through a quick disconnect (QDC), Common Display Interface Unit (CDIU) and associated cables that are aircraft mounted. Figure 1 provides a block diagram that shows how the CHMD will integrate into the HDTS.

Figure 1 Helmet Display and Tracking System Block Diagram

2.0 APPLICABLE DOCUMENTS

2.1 General. The documents listed in this section are specified in sections 3, 4, or 5 of this specification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

Government documents.

2.1.1 Specifications, standards, and handbooks. The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract.

DEPARTMENT OF DEFENSE SPECIFICATIONS

DEPARTMENT OF DEFENSE STANDARDS

Copies of these documents are available online at https://assist.daps.dla.mil/quicksearch/.

2.1.2 Other Government documents, drawings, and publications. The following other Government documents, drawings, and publications listed form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation or contract.

NATICK/TR-91/040 1988 Anthropometric Survey of U.S. Army Personnel: Pilot Summary Statistics.

MIL-PRF-A3279454B(CR) Performance Specification for Aviator’s Night Vision Imaging System and AN/AVS-6(V)3

Copies of these documents are available from PM Air Warrior, 6726 Odyssey Drive, Huntsville, AL.

2.2 Non-Government publications. The following documents, drawings, and publications listed form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation or contract.

2.3 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3.0

REQUIREMENTS

Physical characteristics.

3.1.1 Weight. The total head supported weight of the CHMD, mounting hardware, to include 12 inches of cable beyond the helmet, shall not exceed 1.05 lbs (0.476kg).

3.1.2 Center of Mass.

3.1.2.1 Center of Mass (Neck Fatigue) The CHMD total head borne weight and center of mass, when combined with the helmet, and other ancillary Aviation Life Support Equipment (ALSE) shall be compliant with the curve provided in Figure 2.

Figure 2 USAARL Head Work Mass Criteria for Neck Fatigue

3.1.2.2 Center of Mass (Neck Injury). The CHMD total head borne weight and center of mass, when combined with the helmet and other ancillary Aviation Life Support Equipment (ALSE) shall be compliant with the curve provided in Figure 3, or the CHMD shall be frangible under an acceleration of 10G(±2G). The frangible components shall not come in contact with the wearer’s forehead, eye sockets, or facial regions during separation.

Figure 3 USAARL Head Work Mass Criteria for Neck Injury

3.1.3 CHMD Type.

3.1.3.1 The CHMD shall have a see-through display monocular for the right eye [Threshold (T)]; switchable to either eye or biocular [Objective (O)].

3.1.3.2 The CHMD shall support both day and night operation [T]; with a single display [O].

3.1.4 Impact Protection.

3.1.4.1 Impact Protection, Headband and Crown. Modifications to the HGU-56/P helmet in order to accommodate the CHMD shall not degrade from the HGU-56/P’s impact requirements. The HGU-56/P limit peak deceleration to 150 G in the crown and 175 G in the headband area when subjected to impact velocities of 4 .88 m/sec and 6.0 m/sec respectively.

3.1.4.2 Impact Protection, Ear. Modifications to the HGU-56/P helmet in order to accommodate the CHMD shall not degrade from the HGU-56/P’s impact requirements. The HGU-56/P shall limit peak deceleration to 150 G in the earcup area when subjected to impact velocities of 6.0 m/sec.

Marking & Identification.

The CHMD shall include the nomenclature, part number, serial number, National Stock Number, the manufacturer’s CAGE Code, and Date of Manufacture stamped or silk-screened on the outside of each enclosure in accordance with (IAW) the requirements for markings in MIL-STD-130. The data plate shall be marked with 2-D Item Unique Identification (IUID) data matrix, construct 2, and encoded information. The IUID data matrix shall be no less than one centimeter (1 cm) wide and no less than forty percent (40%) in contrast. All applications shall be permanently affixed, as well as human and machine-readable.

Performance Characteristics.

3.1.5 Transmittance.

3.1.5.1 D65. The CHMD combiner lens assembly shall have a D65 illuminant photopic transmittance of greater than 62%.

3.1.5.2 Visible Spectrum. The CHMD combiner lens assembly shall have a transmittance greater than 50% for all wavelengths between 450 nm and 700 nm.

3.1.5.3 P43. The CHMD combiner lens assembly shall have a transmittance of at least 75% for the P43 phosphor spectrum.

3.1.6 Color. The CHMD shall be capable of displaying tri-color (RGB) with 5 [T]; 8 [O] addressable bits per color and a minimum color separation (Δu’ and Δv’) of 0.2 between each of the primaries on the C.I.E. 1976 U.C.S. chromaticity diagram (Figure 4), where white balance falls within defined U.C.S. white locus.

Figure 4 C.I.E. 1976 U.C.S Chromaticity Diagram

3.1.7 System Resolution. The CHMD shall provide a system resolution of ≥16 cycles/deg [T]; ≥18 cycles/deg [O].

3.1.8 Field of View (FOV). The CHMD shall have a field of view, at a physical eye relief of 25mm, equal to or greater than 22.5° vertical by 30° horizontal with 37.5° diagonals[T]; 30º vertical by 40º horizontal with 50° diagonals [O]. The FOV horizontal, vertical, and diagonal requirements are as seen by the pilot’s eye as shown in Figure 5.

Figure 5 Representation of Horizontal and Vertical

3.1.9 Luminance. Day and Night Luminance requirements are defined in 3.3.5.1 through 3.3.5.3.

3.1.9.1 Day Mode Inside Visor. The CHMD, if mounted inside the day visor, shall have an adjustable luminance for white as well as for each of the red and green primaries from a minimum of ≤ 10fL x D65 combiner transmittance to a minimum peak of ≥ 5,500fL x combined visor (15%) x D65 combiner transmittance (actual measured transmittance of combiner) [T]; 6,500 fL x combined visor (15%) x D65 combiner transmittance (actual measured transmittance of combiner) [O].

3.1.9.2 Day Mode Outside Visor. The CHMD, if mounted outside the day visor, shall have an adjustable luminance for white as well as for each of the red and green primaries from a minimum of ≤ 10fL x D65 combiner transmittance to a minimum peak of ≥ 5,500fL x D65 combiner transmittance (actual measured transmittance of combiner) [T]; 6,500 fL x D65 combiner transmittance (actual measured transmittance of combiner) [O].

3.1.9.3 Night Mode. The CHMD luminance setting shall be adjustable from maximum peak luminance of 30 fL ±5fL to a minimum of ≤0.01 fL.

3.1.10 Contrast to the Eye.

3.1.10.1 White Contrast to the Eye. The CHMD shall have a contrast ratio at the eye greater than 50:1 [T], 100:1 [O] over the entire luminance range from minimum Night Mode to maximum Day Mode for the white color.

3.1.10.2 Red Contrast to the Eye. The CHMD shall have a contrast ratio at the eye greater than 50:1 [T], 100:1 [O] over the entire luminance range from minimum Night Mode to maximum Day Mode for the red primary color.

3.1.10.3 Green Contrast to the Eye. The CHMD shall have a contrast ratio at the eye greater than 50:1 [T], 100:1 [O] over the entire luminance range from minimum Night Mode to maximum Day Mode for the green primary color.

3.1.11 Eye Box. At a physical eye relief of 25mm, the CHMD eye box shall have a minimum diameter of 15mm. The contractor shall provide an optical ray trace that defines the eye box in three-dimensional space.

3.1.12 Latency. The CHMD shall have a display latency of equal to or less than 1/frame rate. The minimum frame rate shall be at least 50 hertz.

3.1.13 Focus. In the center of the CHMD field-of-view, the CHMD imagery shall be fixed at infinity (+0.125 - to - 0.25 diopter) [T]; adjustable (+0.125 to -1.0 diopter) [O].

3.1.14 Combiner Prismatic Deviation. Prismatic deviation stated herein includes the inherent prismatic power resulting from nonparallel surfaces of the material. The combiner prismatic deviation shall be no greater than 0.18 prism diopter vertical or horizontal.

3.1.15 Combiner Refractive Power. The refractive power shall not exceed ±0.125 diopters within the combiner field of view.

3.1.16 Combiner Optical Distortion. The optical distortion within the combiner field of view shall conform to the acceptable standards shown on figure 2 of MIL-DTL-43511.

3.1.17 Combiner Haze. The haze value of the combiner shall not exceed 2.0 percent.

3.1.18 ANVIS Alignment. When used with the ANVIS goggles, the CHMD active display area shall be overlaid and capable of centering within 1.0 degree of the center of the ANVIS field-of-view for all tilt adjustments of the ANVIS. Note: The ANVIS has an 8 degree range of tilt adjustment.

3.1.19 Flicker/ Jitter. There shall be no visually discernable flicker/jitter of the imagery over the adjusted intensity range of the CHMD.

3.1.20 CHMD Luminance Uniformity. Non-uniformity in luminance of the CHMD shall be within ± X [T]; ±X/2 [O], from the mean. Where X=maximum half angle field of view (diagonal measurement in degrees) expressed as a percentage (e.g., a 50-degree diagonal field-of-view must have luminance uniformity within ±25% of the mean).

3.1.21 CHMD Linear Distortion. Residual distortion shall be less than 4 % [T], ≤3% [O].

3.1.22 CHMD Field Curvature. The variation in focus across the full field of view shall deviate no more than 0.375 diopter [T]; 0.25 diopter [O].

3.1.23 CHMD Contrast Transfer Function (CTF). At the resolution requirement (≥16 cycles/deg [T]; ≥ 18 cycles/deg [O], the CHMD shall have a modulation depth or a Michaelson contrast of ≥0.2 for both the vertical and horizontal meridians as defined by the observer’s orientation. See Figure 5.

3.1.24 Day/Night Transition. The CHMD shall transition between day and night capabilities with no more than two hardware configuration changes and without interruption of the other pilot’s CHMD.

Night Vision Compatibility.

Any light emitted from the CHMD shall be compatible with a AN/AVS-6 (V)3, Class A night vision goggles (NVGs) as per the requirements of MIL-STD-3009. The lighting system shall not have an adverse effect on external unaided night vision or on the aircrew’s capability to obtain required information external to the aircraft while employing NVGs.

Interfaces.

3.1.25 HGU-56/P Helmet and ANVIS Interface.

3.1.25.1 Tool Free Mounting. The CHMD shall be attachable to the helmet (Drawing 1680-ALSE-100) without the use of tools.

3.1.25.2 Stow/Deploy. The pilot shall have the capability to stow and deploy the CHMD.

3.1.25.3 Quick Disconnect Capability. The CHMD shall have a quick disconnect capability.

3.1.25.4 CHMD Compatibility with Visors (Day Configuration). The CHMD in the day configuration shall be compatible with deploying of the helmet visors.

3.1.25.5 Non-Interference with Aviation Life Support Equipment (ALSE). The CHMD shall not interfere with the operation of the M-45 mask, the PHODS and spectacles [T]; maxillofacial shield (Drawing Number 1680-ALSE-192) and the Joint Service Aircrew Mask (JSAM) [O].

3.1.25.6 ANVIS Compatibility. The CHMD shall not affect the ANVIS (MIL-PRF-A3279454B(CR)) eye relief or the 40 degree field of view.

3.1.25.7 ANVIS Look Around Compatibility. The CHMD shall not interfere with the look around capability of the AN/AVS-6 ANVIS.

3.1.25.8 ANVIS Attribute Compatibility. The CHMD shall not adversely affect the following ANVIS attributes: eyepiece lens focusing, objective lens focusing, interpupillary distance (IPD) adjustment, vertical fore/aft adjustment, tilt adjustment, automatic breakaway and flip-up/flip-down adjustments.

3.1.25.9 ANVIS Operation with Failed CHMD. In the event of failure of the CHMD there shall be no interference with the normal function of the ANVIS system.

3.1.26 ASDC Interface. The interface between the CHMD and the ASDC shall be IAW the Appendix A (Helmet Display and Tracking System (HDTS) Interface Control Document (ICD)).

3.1.27 Non-Interference with Helmet Tracker Kit (HTK). The CHMD and its mount shall not physically or magnetically interfere with the operation of the HTK. Metal items shall be kept at least 1” away from the HTK as illustrated in Figure 6.

Figure 6 Representation of No Metal Zone around the HTK Environmental Performance.

3.1.28 Temperature.

3.1.28.1 Operating Requirements. The CHMD shall operate according to the requirements of this specification in the temperature range of -25°F to +125°F.

3.1.28.2 Transport/Storage (Non-Operating). The CHMD shall perform according to the requirements of this specification after exposure to transportation and storage temperatures ranging from -80°F to +185°F.

3.1.28.3 Operating Requirement - Altitude. The CHMD shall perform according to the requirements of this specification during operations from Mean Sea Level (MSL) up to 25,000 feet elevation.

3.1.28.4 Transport (Non-Operating) - Altitude. The CHMD shall perform according to the requirements of this specification after being transported in its non-operating configuration (with power not applied) at pressure altitudes from MSL up to 50,000 ft elevation.

3.1.28.5 Temperature Shock. The CHMD shall perform according to the threshold requirements of this specification after exposure to temperature shock from -80°F to +185°F for a minimum of 6 hours for a minimum of three temperature shock cycles.

3.1.29 Blowing Dust. The CHMD shall perform according to the requirements of this specification during and after exposure to blowing dust specified in MIL-STD-810G, Method 510.5 Procedure I with the combiner and/or eyepieces covered.

3.1.30 Dripping Rain. The CHMD shall perform according to the requirements of this specification during and after being exposed to dripping rain at a rate of 280 l/m2/hr (7 gal/ft2/hr) for a minimum of fifteen (15) minutes.

3.1.31 Blowing Rain. The CHMD shall perform according to the requirements of this specification after exposure to blowing rain at a rate of 1.7 mm/min.

3.1.32 Salt Fog. The CHMD shall perform according to the requirements of this specification after exposure to salt fog conditions of 5% NaCl with a specific gravity of 1.027 to 1.034 with each cycle consisting of a 24-hour exposure to the salt fog environment, followed by a 24-hour dry time.

3.1.33 Humidity. The CHMD shall perform according to the requirements of this specification during and after exposure, while being operated, or following storage, in a humid environment from +86 oF to +140oF, with a relative humidity of 95% ( ± 4%) for a minimum of ten 24-hour cycles.

3.1.34 Fungus. The CHMD shall not support fungal growth when exposed to the fungi specified in MIL-STD-810G, TABLE 508.6-I.

3.1.35 Combined Environmental Effects. The CHMD shall perform according to the requirements of this specification during and after exposure to the combined effects of an operational temperature of -25F to +125F, with a relative humidity of 30% to 95%, and in an altitude of Mean Sea Level (MSL) up to 25,000 feet elevation, for a minimum of ten cycles.

3.1.36 Mechanical Shock.

3.1.36.1 Transit Drop Shock. The CHMD shall perform according to the requirements of this specification after exposure to a transit drop shock environment incurred from 26 drops from a height of 48 inches ± 1.2 inches in its shipping container to a concrete surface.

3.1.36.2 Functional Shock. The CHMD shall perform according to the requirements of this specification during and after exposure to three shocks applied in each direction along three orthogonal axes of the CHMD for a maximum of 18 shocks with minimum peak acceleration of 20Gs, and with an effective duration (Te) of 15 to 23 ms, and a crossover frequency of 45 Hz.

3.1.37 Vibration. The CHMD shall perform according to the requirements of this specification during and after exposure to the vibration levels and durations specified in MIL-STD-810G, Method 514.6E-2 Procedure I CAT 24 for no less than 30 minutes per axis.

3.1.38 Explosive Atmosphere. The CHMD under normal operation at maximum loads and during switching power on and off (including quick disconnect) shall not ignite an explosive gaseous-air environment at both 14.667 Pounds per Square Inch Absolute (PSIA) and 5.083 PSIA.

Explosive atmosphere shall be defined for this requirement as a Volume of 95% n-hexane (ml) = (4.27 X 10^-4) * Net Chamber Volume *Chamber Pressure/ (Chamber temp *.655).

3.1.39 Electromagnetic Interference (EMI)/ Electromagnetic Compatibility (EMC).

3.1.39.1 EMI Emissions.

3.1.39.1.1 CE101. The CHMD shall comply with CE101 for EMI emissions IAW Figure CE101-4, limit curve #2, 30 Hz to 10 kHz of MIL-STD-461.

3.1.39.1.2 CE102. The CHMD shall comply with CE102 for EMI emissions IAW Figure CE102-1, 10 kHz to 10 MHz of MIL-STD-461.

3.1.39.1.3 RE101. The CHMD shall comply with RE101 EMI emissions IAW Figure RE101-1, 30 Hz to 100 kHz of MIL-STD-461.

3.1.39.1.4 RE102. The CHMD shall comply with RE102 EMI emissions IAW Figure RE102-3, 10 kHz to 18GHz of MIL-STD-461.

3.1.39.2 EMI Electromagnetic Susceptibility.

3.1.39.2.1 CS101. The CHMD shall meet all performance requirements when the input power line is exposed to interference levels of CS101, IAW Figure CS101-1, limit curve #2, 30 Hz to 150 kHz of MIL-STD-461.

3.1.39.2.2 CS114. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to interference levels of CS114 IAW Figure CS 114-1, aircraft (Army Aircraft), limit curve #5, 10 kHz to 200 MHz of MIL-STD-461.

3.1.39.2.3 CS115. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to a pre-calibrated signal having rise and fall times, pulse width, and amplitude as specified in MIL-STD-461, Figure CS115-1 at a 30 Hz rate for one minute.

3.1.39.2.4 CS116. The CHMD shall meet all performance requirements when all cable bundles and power lines are exposed to interference levels IAW CS116 Figures CS116-2, 10 kHz to 100 MHz of MIL-STD-461.

3.1.39.2.5 RS101. The CHMD shall meet all performance requirements when all sides of the CHMD and all cables are exposed to a magnetic field IAW RS101 Figure RS101-2, U.S. Army limit, 30 Hz to 100 kHz of MIL-STD-461.

3.1.39.2.6 RS103. The CHMD shall demonstrate no evidence of degradation of performance when the unit and associated cables are exposed to electric fields of 200 Volts per meter over the frequency range of 2 MHz to 40 GHz using the modulations shown in ADS-37A-PRF, Table I parts A and B.

3.1.39.3 Electromagnetic Compatibility (EMC). The CHMD shall perform according to the requirements of this specification, without causing the CHMD or aircraft subsystems and equipment from meeting their specified performance requirements while operated simultaneously with any single or multiple combinations of aircraft subsystems and equipment, including ground support equipment, for all modes of operation for each subsystem and equipment required to complete the mission.

3.1.39.4 Electromagnetic Vulnerability (EMV). The CHMD shall meet all performance requirements when exposed to the worldwide electromagnetic environment defined in Table I, parts A and B, of ADS-37A-PRF. This requirement shall include electromagnetic energy coupled to the aircraft through ground support equipment, aerial re-fuelers, and any other equipment external to the aircraft.

3.1.40 Electrostatic Discharge (ESD). The CHMD shall meet all performance requirements during handling or operations associated with exposure to ESD.

Integrated Logistics Support (ILS).

3.1.41 Reliability and Maintainability (R&M).

3.1.41.1 Mean Time Between Failures (MTBF). The CHMD shall provide a MTBF of no less than 4000 hours.

3.1.41.2 Mean Time To Repair (MTTR). The CHMD shall provide a MTTR of no greater than 0.5 hours at Aviation Unit Maintenance (AVUM) Level.

3.1.41.3 Maintenance Ratio (MR). The CHMD shall provide a MR of no more than 0.059 maintenance man-hours per operating hour.

3.1.42 Maintenance.

3.1.42.1 Special Tools/Support Equipment. The CHMD shall require no new, unique, or special tools, or support equipment for CHMD maintenance. Current Aviation Life Support Equipment tools and support equipment are identified in SC 9999-01-SKO.

3.1.42.2 Aviation Maintenance Concept. The CHMD shall be maintained by the two-level Aviation Maintenance Concept of AVUM and Contractor Logistic Support (CLS) depot for selected components. The CHMD shall require no in-field intermediate maintenance actions.

3.1.42.3 Army Organic Maintenance System. The CHMD shall be maintainable within the structure of the standard Army Organic Maintenance System with functions including: cleaning, inspection, functional checkout, and repair (consisting of limited piece part replacement). The CHMD shall not require a new Military Occupational Specialty be established. The CHMD shall not increase the current manning levels of the maintenance function.

Manpower & Personnel Integration (MANPRINT).

3.1.43 System Safety. The CHMD shall comply with the safety requirements of MIL-STD-882.

3.1.44 Health Hazards. The CHMD shall not expose personnel to the following health hazards associated with: mechanical forces including shock and vibration; pressures; toxic allergenic, pathogenic organisms, or irritating substances; ionizing or non-ionizing radiation; noise or other emissions; combustion products; trauma; or extreme temperatures and humidity. The CHMD shall not introduce hazards throughout anticipated climatic conditions, either in operation, or maintenance support IAW the requirements for safety and health in MIL-STD-882.

3.1.45 Human Factors Engineering. The CHMD shall comply with the human engineering design criteria of MIL-STD-1472.

3.1.45.1 Physical Eye Relief. The CHMD shall have a minimum physical eye relief (i.e., eye clearance) of 15 mm.

3.1.45.2 Crash Injury Risk. The CHMD shall not increase the risk of injuries to pilot or aircrew members during crash or hard landing profiles.

3.1.45.3 Inadvertent Activation. The CHMD controls shall not be susceptible to inadvertent activation.

3.1.45.4 Don and Doffing. The CHMD shall be donned or doffed in less than 30 seconds [T]; 15 seconds [O].

3.1.45.5 Cold Flyer Glove. The CHMD controls shall be identifiable and meet human size and strength limitations by aircrew member with and without Intermediate Cold, HAU-15/P Flyer’s Glove MIL-DTL-32173 IAW section 5.1 “Controls” of MIL-STD-1472. Arrangement, size, shape, spacing, and grouping of the controls shall permit tactile identification and use under all light conditions, with and without gloves.

3.1.45.6 Incorrect Connectivity. The CHMD connectors shall be keyed to prevent incorrect insertion.

3.1.45.7 Ingress/Egress. The CHMD shall not impede the aircrew member’s ability to ingress/egress in normal operations, snag/interfere with components, or impede the ability for each aircrew member to emergency egress the aircraft within 30 seconds using half the exits.

3.1.45.8 5th-95th Percentile Accommodation. The CHMD shall accommodate and be operable by the anthropometric range of 5th percentile female pilot to 95th percentile male pilot as defined in Natick/TR-91/040, 1988 Anthropometric Survey of U.S. Army Personnel: Pilot Summary Statistics.

3.1.45.8.1 Fore/Aft Adjustment. The CHMD shall allow for fore-aft adjustment range of at least 15 mm.

3.1.45.8.2 IPD Adjustment. The CHMD shall allow for interpupillary adjustment of 55 mm to 72 mm.

3.1.45.8.3 Vertical Adjustment. The CHMD shall allow for vertical adjustment range of at least 15 mm.

3.1.45.9 Signatures. Visible, infrared, RF, optical/radar cross section and noise signatures of the CHMD components shall be inspected and tested to demonstrate that the external surface camouflage, optical/radar cross section, infrared/RF emission and noise reductions are detected less than 10% of the time.

Materials.

3.1.46 Resistance to Battlefield Contaminants. The CHMD shall perform according to the requirements of this specification, during and after a 24-hour exposure to any of the battlefield contaminants listed below:

· MIL-PRF-83282, Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Metric, NATO Code Number H-537

· MIL-PRF-87257, Hydraulic Fluid, fire Resistant; low temperature, synthetic hydrocarbon base, aircraft and missile

· A-A-52557, Fuel Oil, Diesel; For Posts, Camps and Stations

· MIL-DTL-5624, Turbine Fuel, Aviation Grades JP-4 and JP-5

· MIL-DTL-83133, Turbine Fuel, Aviation, Kerosene Types, NATO F-34 (JP-8), NATO F-35, and JP-8 + 100

· MIL-PRF-7808, Lubricating Oil, Aircraft Turbine Engine Synthetic Base

· Methylethyl Ketone

· Varsol Naphtha

· M291/M295, NBC Cleaner Kit

· Engine Waterwash Solution R-MC-G-21-Premix, (P/N 4070)

Classification of Inspection.

3.1.47 Qualification. When specified (see 6.2), a sample shall be subject to qualification in accordance with (IAW) 4.10.1

3.1.48 First Article. When specified (see 6.2), a sample shall be subject to first article inspection in accordance with (IAW) 4.10.2.

3.1.49 Conformance Inspection. When specified (see 6.2), a sample shall be subject to conformance inspection in accordance with (IAW) 4.10.3.

3.1.50 Classification of Defects. Defects to CHMD components shall be classified as critical, major, or minor IAW Table III and assigned a defect code.

General Workmanship.

CHMD components shall be free from irregularities or defects that could adversely affect performance or durability.

4.0 VERIFICATION

This section establishes the verification requirements to verify the Section 3 requirements. The verification methods shall be those shown in the Verification Cross Reference Matrix, Table I. Verification methods shall be limited to the following.

Table I Verification Cross Reference Matrix

4.1 Physical Characteristics.

4.1.1 Weight. Verification of requirement 3.1.1 shall be by examination.

4.1.2 Center of Mass.

4.1.2.1 Center of Mass (Neck Fatigue). Verification of requirement 3.1.2.1 shall be by test in a lab environment in accordance with the procedures identified in USAARL Report 98-22. Center of Mass shall be verified in both a day configuration and a night configuration. Both configurations shall be done on a medium size HGU-56/P helmet. The day configuration shall be defined as: medium HGU-56/P with dual visor assembly and ANVIS mount, CEPS, and the CHMD and mounting hardware in the deployed configuration. Cabling for the communications and the CHMD shall be cut 12 inches beyond the edge of the helmet. The night configuration shall be the same as the day configuration but with the addition of a deployed set of ANVIS and low profile battery pack attached via hook and loop to the rear of the helmet.

4.1.2.2 Center of Mass (Neck Injury). Verification of requirement 3.1.2.2 shall be by test in a lab environment in accordance with the procedures identified in USAARL Report 98-22. Center of Mass shall be verified in both a day configuration and a night configuration. Both configurations shall be done on a medium size HGU-56/P helmet. The day configuration shall be defined as: medium HGU-56/P with dual visor assembly and ANVIS mount, CEPS, and the CHMD and mounting hardware in the deployed configuration. Cabling for the communications and the CHMD shall be cut 12 inches beyond the edge of the helmet. The night configuration shall be the same as the day configuration but with the addition of a deployed set of ANVIS and low profile battery pack attached via hook and loop to the rear of the helmet.

4.1.3 CHMD Type.

4.1.3.1 Verification of requirement 3.1.3.1 shall be by demonstration that the display is see-through, monocular and mountable to the right eye or that the display is biocular and mountable to either eye.

4.1.3.2 Verification of requirement 3.1.3.2 shall be by demonstration that the CHMD operates in day mode and in night mode.

4.1.4 Impact Protection.

4.1.4.1 Impact Protection, Headband and Crown. Verification of requirement 3.1.4.1 shall be by test in a lab environment in accordance with AIHS-FS-0002. The Government reserves the right to define the impact location based on the design of the CHMD.

4.1.4.2 Impact Protection, Ear. Verification of requirement 3.1.4.2 shall be by test in a lab environment in accordance with AIHS-FS-0002. The Government reserves the right to define the impact location based on the design of the CHMD

4.2 Marking & Identification. Verification of requirement 3.2 shall be by examination to show that the nomenclature, part number, serial number, NSN, the manufacturer’s CAGE Code and date of manufacture is stamped or silk-screened on the outside of the CHMD IAW MIL-STD-130. Verification of the data plate marked with a 2-D Item Unique Identification (IUID) data matrix encoded information IAW paragraph 3.2 shall be by demonstration using IUID scanning.

4.3 Performance Characteristics.

4.3.1 Transmittance.

4.3.1.1 D65. Verification of see-through transmittance (TP) of the combiner lens assembly as required in 3.3.1.1 shall be by test in a lab environment for light with a 6500K color temperature (SD65). Using a broad band light source (e.g. tungsten), measure the light transmittance with a calibrated spectrophotometer over the range from 400nm to 700nm (in a minimum of 5-nm increments) where light transmittance is defined as filtered light/unfiltered light. Once the transmittance is calculated for a broadband light source, the photopically weighted D65 light spectrum is calculated by multiplying the D65 spectrum with the normalized visual response function (Vλ) spectrum and using this spectrum with the measured broadband transmittance (TC) of the see-through combiner. The normalized D65 phosphor spectral radiance can be found in Figure 7 and Table II.

4.3.1.2 Visible Spectrum. Verification of see-through transmittance (TP) of the combiner lens assembly as required in 3.3.1.2 shall be by test in a lab environment by measuring transmittance between 450 nm and 700nm. Using a broad band light source (e.g. tungsten), measure the light transmittance with a calibrated spectrophotometer over the range from 450nm to 700nm (in a minimum of 5-nm increments) where light transmittance is defined as filtered light/unfiltered light.

4.3.1.3 P43. Verification of see-through transmittance (TP) of the combiner lens assembly as required in 3.3.1.3 shall be by test in a lab environment for light with the color spectrum of a P43 phosphor (SP43) (i.e. ANVIS light output). Using a broad band light source (e.g. tungsten), measure the light transmittance with a calibrated spectrophotometer over the range from 400nm to 700nm (in a minimum of 5-nm increments) where light transmittance is defined as filtered light/unfiltered light. The normalized P43 phosphor spectral radiance can be found in Figure 7 and Table II.

Figure 7 Normalized D65 and P43 Phosphor Spectral Radiance

Table II Normalized D65 and P43 Phosphor Spectral Radiance

Illuminant D65 and P43 normalized normalized normalized

4.3.2 Color. Verification of threshold requirement 3.3.2 shall be by demonstration in a lab environment. Verification of objective requirement 3.3.2 shall be by test through the use of a calibrated colorimeter. Drive the display to maximum day and maximum night luminance for each of the three primary red, green, and blue color channels, measuring u’ and v’ coordinates for each primary color. Compute Δu’ and Δv’ as the vector distance between each of the primary colors.