Draft AN AVS-9(V)3 Syst Spec for SSS

INCH-POUND

MIL-PRF-#######

DRAFT ONLY

09 February 2009

SUPERSEDING

NONE

PERFORMANCE SPECIFICATION

IMAGE INTENSIFIER SET, NIGHT VISION

AN/AVS-9(V)3

This specification is approved by the Department of the Air Force and is available for use by all Departments and Agencies of the Department of Defense.

1.1 Scope. This specification covers the Image Intensifier Set, Night Vision, AN/AVS-9(V)3(see 6.1). The AN/AVS-9(V)3 shall be designed to provide imagery sufficient for an aviator to complete night time missions down to starlight and extreme low light conditions in military fixed wing and rotary wing aircraft. The AN/AVS-9(V)3 shall be designed in two different versions. The AN/AVS-9(V)3G version shall be designed for use on the HGU-55/P helmet and the AN/AVS-9(V)3H shall be designed for use on the HGU-56P flight helmets.

1.2 Classification. The NVG shall be of the following types. The type of NVG to be furnished shall be as specified (see 6.2).

1.2.1 Types. The Types of NVG are as follow:

Type I – AN/AVS-9(V) 3G

Type II - AN/AVS-9(V) 3H Comments, suggestions, or questions should be addressed to 642 CBSG/GBEA 460 Richard Ray Blvd Ste 200, Robins AFB, GA 31098-1813. Since contact information can change, you may want to verify the currency of this address information using ASSIT online database at www.dodssp.daps.mil.

2. 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 documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

2.2 Government documents.

2.2.1 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

MIL-PRF-A3271099

Lens Assembly, Objective for

Image Intensifier Set, Night

Vision AN/AVS-9(V)

MIL-PRF-49427(CR)

Lens Assembly, Eyepiece for

Aviator’s Night Vision Imaging

System AN/AVS-6(V)( )

MIL-PRF-A3279602B(NVI)

Image Intensifier Assembly,18MM, Microchannel Wafer Night Vision, MX-10160C/AVS-6

MIL-PRF-49257(CR)

Coated Optical Components

MIL-L-85762A

Lighting, Aircraft, Interior, Night Vision Imaging System (NVIS) Compatible

MIL-STD-810

Environmental Test Methods & Engineering Guidelines

MIL-STD-461E

Requirements for the Control of Electromagnetic Interface Characteristics of Subsystems and Equipment

2.3 Order of precedence. 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. REQUIREMENTS

3.1 Initial production testing(IPT). When specified in the contract or purchase order, the supplier shall furnish and test systems in accordance with the requirements of 4.2.

3.2 Qualification. Unless otherwise specified by the contract or purchase order, systems furnished under this specification shall be products approved as qualified products (see 4.4).

3.3 Parts and materials. The contractor shall select parts and materials capable of meeting all of the operational and environmental requirements specified herein. Any change of a part or material after certification, requires notification of the procuring activity and submittal of proposed recertification.

3.3.1 Recycled, recovered, or environmentally preferable materials. Recycled, recovered, or environmentally preferable materials should be used to the maximum extent possible provided that the material meets the operational and maintenance requirements, and promotes economically advantageous life cycle costs.

3.4 Design. The AN/AVS-9(V)3 consists of a binocular imaging assembly (herein referred to as the binocular), helmet mount assembly (herein referred to as a mount), a power pack, a helmet modification kit, a carrying case, and ancillary equipment(see 3.5.7). The binocular consists of two monoculars and a pivot and adjustment shelf assembly, herein referred to as the PAS. Each monocular consists of a monocular housing, an objective lens assembly with a Class B Minus-blue filter optimized for HUD viewing, a light interference filter adapter, a third generation image intensifier tube assembly and an eyepiece lens assembly. The PAS provides optical alignment of the monoculars, adjustment to permit binocular view and the means of attaching the binocular to the mount. Two mount assemblies are available; one for use with the HGU-55/P helmet and the other for use with the HGU-56P flight helmet. The HGU-55/P mount assembly consists of a mounting block with an integral power pack and mounting plate, which allows the assembly to be attached to the HGU-55/P flight helmet by means of a helmet modification kit. This mount assembly is detachable from the helmet. The HGU-56P mount assembly consists of a mounting bracket, which is attached to the HGU-56P flight helmet and is used with a rear-mounted power pack. This mount assembly is fixed to the helmet. The rear-mounted power pack is attached to the helmet by means of a helmet modification kit and is detachable when not required. The mounts provide the means for aircrew to quickly remove the binocular from the helmet, using only one hand, or position the binocular into a stowed position out of the user’s line of sight while remaining attached to the helmet, and return it to the operating position again, using only one hand. Each type of power pack includes two battery compartments that accept one 3 Vdc lithium batteries. The rear-mounted power pack also accepts two 1.5 Vdc AA alkaline batteries in each compartment. The power packs contain circuitry that monitors the voltage of the battery compartment in use and triggers a low battery indicator located in the mount to blink when the battery(ies) in that compartment approach end of life. The carrying case provides protection for the binocular, power pack and ancillary equipment against the conditions associated with carrying these items in a field environment.

3.5 Weight. The weight of the binocular shall not exceed 550 grams. The total combined weight of the HGU-55P version including the binocular, detachable helmet mount (including the integral power pack with two ½ AA size 3.5 volt batteries) and helmet modification kit shall not be greater than 790 grams. The total combined weight of the HGU-56P version including the binocular, low profile battery pack (the external power pack with four standard alkaline 1.5 volt batteries) and helmet modification kit shall not be greater than 870 grams.

3.6 Performance Characteristics.

3.6.1 Field of view(FOV). The field of view shall be 40 +1/-2 degrees.

3.6.2 Magnification(M). System magnification shall be unity (1X)(2 percent.

3.6.3 Distortion. Distortion shall be not greater than 3 percent across the total field of view.

3.6.4 Resolution.

3.6.4.1 High light level. At true infinity focus, each monocular shall have on-axis resolution (see 3.5.9) not less than 1.3 cycles per milliradian. At 14 degrees off-axis, the resolution shall be not less than 0.81 cycles per milliradian. At the infinity stop, each monocular shall have an on-axis resolution not less than 0.49 cycles per milliradian.

3.6.4.2 Low light level. The assembly shall have an on-axis resolution at the true infinity setting of not less than 0.9 cycles per milliradian at a target luminance not greater than 1.0 x 10-4 foot-Lamberts.

3.6.4.3 Brightness gain. The brightness gain (see 3.5.10) shall not be less than 5,500 fL/fL.

3.6.4.4 Collimation. When two parallel beams of collimated light are projected into the objective lenses, with the objectives adjusted to or operating in the infinity focus position and both eyepieces set at zero diopter, the conjugate beams emerging from the two eyepieces shall be collimated within 1 degree convergence and 0.3 degree divergence and dipvergence.

3.6.4.5 Off-axis veiling glare. The off-axis veiling glare (see 3.5.11) exhibited by each monocular shall not exceed the limits of Table I when a point light source illuminates the objective’s entrance pupil at a level of 2.0 ± 0.5 x 10-4 foot-candles (fc). The point source shall subtend less than 0.7 milliradians referenced from the entrance pupil. The average tube (phosphor) background luminance shall be less than or equal to 1.5 x 10-3 foot-lamberts (fL). The off-axis veiling glare requirement shall apply from 2o to 70( beyond the field-of-view (FOV) of the objective lens. The maximum background luminance cited above, and the maximum luminance values listed in Table 1 below, shall be adjusted by a multiplicative factor which equals the actual luminance gain of the tube under test (Gact) divided by 20,000 fL/fc (i.e., Gact/20,000 fL/fc).

Table I. Off-axis veiling glare.

Point Source Angle

(Degrees Beyond FOV) Maximum Intensity of Veiling Glare Image

(foot-Lamberts)

3.6.4.6 Image Stability. The system shall not exhibit any instability in the image such as flickering or flashing under all conditions of illumination and environments.

3.6.4.7 Exposure to external light sources. The binocular shall not be significantly degraded when exposed to high intensity, short duration, intermittent light sources both within and outside the FOV. Light sources include flares, weapon fire, and those typical of urban environments such as headlights and streetlights.

3.7 Environmental conditions. The system and its ancillary equipment shall not be damaged (see 3.5.1) nor suffer degradation of performance(see 3.5.2) and shall meet the performance requirements specified herein when subjected to the following environmental conditions:

3.7.1 Temperature extremes. The binocular shall not be damaged or suffer degradation of performance by continuous operation from +52(C to -32(C or after storage from +71(C to -32(C. The binocular shall not be damaged or suffer degradation of performance by sudden temperature changes from +23(C to +71(C and +23(C to -32(C occurring within 5 minutes. Soak time at each temperature extreme shall be sufficient to attain temperature stabilization.

3.7.2 Altitude Test. The binocular with mount and battery pack shall not be damaged nor suffer degradation of performance by continuous operation throughout altitudes of sea level to 20,000 feet or non-operating altitudes up to 50,000 feet.

3.7.3 Temperature Shock. The binocular with mount and power pack shall not be damaged (see 3.6.1) nor suffer degradation of performance (see 3.6.2) when subjected to sudden temperature changes of the following profiles: +85°C to 23°C; 23°C to -40°C; -54°C to +23°C, when tested in accordance with MIL-STD-810F, Method 503.4, Procedure II.

3.7.4 Humidity. The binocular shall not be damaged nor suffer degradation of performance when subjected to a relative humidity greater than 95 percent, with varying temperatures from +21(C to +65(C for exposure up to 240 hours including conditions wherein condensation takes place in and/or on the equipment during both operating and non-operating conditions. Fogging on the inside of glass or plastic elements shall not occur.

3.7.5 Vibration.

3.7.5.1 Sinusoidal vibration (room temperature). The binocular shall not be damaged nor suffer degradation of performance when subjected to vibrations within the frequency range and amplitude shown on Figure 1 at room temperature (see 3.5.4).

3.7.5.2 Sinusoidal vibration (ambient). The binocular and mount and battery pack shall not be damaged nor suffer degradation of performance when subjected to vibrations within the frequency range and amplitude shown on Figure 1 at -40oC and +52oC.

3.7.5.3 Gunfire vibration. Both when in use and when stowed, the system shall not be damaged nor suffer degradation of performance when subjected to a minimum of 15 minutes per axis of combined random and sinusoidal vibration per the following profile which is representative of the vibration levels experienced in the cockpit as a result of gun firing: Between 30 Hz and 100 Hz, 0.02 G2/Hz; then rising linearly on a log scale to 0.03 G2/Hz at 200 Hz; then rising linearly on a log scale to 0.12 G2/Hz at 1000 Hz; then falling linearly on a log scale to 0.01 G2/Hz at 2000 Hz; below 30 Hz and above 2000 Hz, unspecified. Overlaid on this are four harmonic sinusoids: 30 Hz, 60 Hz, 90 Hz, and 120 Hz with a severity envelope of (1.6g.

3.7.6 Sand and dust. The binocular, mount and power pack assembly, with objective and eyepiece lenses covered, shall not be damaged and shall operate without degradation of performance after exposure to blowing fine sand and dust particles for 90 minutes on each side of the assembly.

3.7.7 Fungus. The system (including carrying case and ancillary equipment), which is free of all salt residue, shall neither support fungus growth, be damaged, nor suffer degradation of performance by the presence of fungus spores or adjacent fungal growth during and after a period of exposure to viable fungal spores for not less than 28 days at a relative humidity of not less than 90 percent and a temperature between +24(C and +31(C.

3.7.8 Salt fog. The binocular and power pack assembly shall not be damaged and shall operate without degradation of performance after a minimum 48 hour exposure to a salt fog atmosphere of sodium chloride containing (on a dry basis) not more than 0.1 percent sodium iodide and not more than 0.5 percent total impurities, followed by a minimum drying period of 48 hours.

3.7.9 Explosive atmosphere. The binocular with mount and power pack assembly shall not cause ignition of a gaseous air mixture when operating in an ambient explosive atmosphere.

3.7.10 Electromagnetic Interference (EMI). The binocular with mount and power pack assembly shall be capable of operating in an electromagnetic interference (EMI) rich environment. Operation of this equipment shall not cause interference or other undesirable effects in any other on-board avionics/electronic equipment, nor shall it be adversely affected itself when in proximity to other equipment or by emissions originating elsewhere in the environment. To verify this requirement, the binocular with mount and power pack assembly shall meet the following requirements when operated at light levels from 2 x 10-6 fc to 1 x 10-2 fc (Linear and ABC) and tested in a Government/industry approved facility/chamber, using suitable tools and equipment, as detailed in a test method approved by the Government. The light source used for tests need not meet the color temperature requirements of 3.4, but must provide equivalent night vision radiance as demonstrated by the system’s output gain saturation characteristic.

3.7.10.1 Radiated emissions, electrical field. The binocular with mount and power pack assembly shall not radiate E-field emissions in excess of those given in Figure 2 (Narrowband) and Figure 3 (Broadband) for the frequency range of 14 kHz to 10 Ghz, or ten times the highest frequency generated within the unit under test. Above 30 MHz, the limits shall be met for both horizontally and vertically polarized waves.

3.7.10.2 Radiated susceptibility, magnetic field, spike. The binocular with mount and power pack assembly shall not exhibit damage (see 3.5.1), permanent malfunction, degradation of performance (see 3.5.2), or susceptibility (see 3.5.3) during or after being subjected to magnetically induced test spikes having the waveform shown in Figure 4. The test spikes shall be magnetically induced in both polarizations.

3.7.10.3 Radiated susceptibility, electric field, 14 kHz to 40 Ghz. The binocular with mount and power pack assembly shall not exhibit damage (see 3.5.1), permanent malfunction, degradation of performance (see 3.5.2), or susceptibility (see 3.5.3) during or after being subjected to radiated fields under the following conditions.

a. The radiated field levels shall be 200 V/m through all frequencies from 10 kHz to 40 Ghz.

b. The radiated fields shall be performed in both vertical and horizontal polarizations. Circular polarized waves shall not be acceptable.

c. The radiated fields shall be modulated with amplitude modulation (AM) @ 50 percent 1 kHz tone.

d. The unit under test shall be subjected to the radiated fields while positioned in the following orientations:

(1) Horizontal 0( - Objective lens facing source of radiation.

(2) Horizontal 270( - Rotated clockwise around the vertical axis 270( from horizontal 0(.

(3) Vertical 90( - Rotated 90( downward from horizontal 0(.

3.8 Construction. The systems shall be constructed in accordance with the contract or purchase order and all the requirements of this specification.

3.8.1 Major components. The system shall consist of the following major components:

3.8.1.1 Binocular.

a. Objective lens assembly, 2 each, per MIL-PRF-

A3271099

b. Eyepiece lens assembly, 2 each, per MIL-PRF-

49427(CR)

c. Image intensifier assembly, 18-mm, MX-10160C/AVS-6, 2 each, per MIL-PRF-A3279602B (CR)

d. Pivot and adjustment shelf assembly

e. Monocular housing, 2 each

f. Light interference filter adapter, MX-11617/AVS-6(V), 2 each, per MIL-PRF-49257(CR)

3.8.1.2 Mount assembly. This assembly shall form the interface between the helmet and the binocular and may include the power source. The helmet mount assembly shall provide the means for vertical adjustment. There are two versions of this mount, one for the HGU-55/P and one for the HGU-56P. The mount shall provide the means for aircrew to quickly remove the binocular from the helmet, using only one hand, or position the binocular into a stowed position out of the user’s line of sight while remaining attached to the helmet, and return it to the operating position again, using only one hand. The binocular shall attach easily and securely to the mount.

3.8.1.3 Power pack assembly. The electrical power for both monoculars shall be provided by a battery or batteries with an additional battery or batteries for backup power. The battery housing shall be located in close proximity to the image intensifier to reduce electrical wiring to a minimum. The integral power pack battery housing shall have an end cap which can be removed and replaced by hand and which has a moisture resistant seal and retaining tether. Each battery or pair of batteries shall provide sufficient power to operate both monoculars for 2 hours over a temperature range of -10(C to +52(C. At +20(C, the battery endurance will be in excess of 5 hours supporting a total operational endurance of 10 hours. The battery used shall be a standard commercial or military battery which is compatible for use in aircraft operations when oxygen is in use. The rear-mounted power pack and cabling shall not interfere with or cause hazard to the helmet wearer.

3.8.1.4 Cases. A carrying case shall provide which shall provide protection for the binocular, power pack and ancillary equipment against the conditions associated with carrying these items in a field environment.

3.8.1.5 Helmet modification kit. Modification of existing helmets shall be accomplished using helmet bracket kits which shall be capable of being installed and maintained at the organizational maintenance level. No modification to existing helmets shall be made which would prevent the use of the original helmet visors during operations in which the binocular is not utilized, unless equivalent eye protection is provided as part of the modification kit. The brackets shall not interfere with use of the daytime visor. Any component of the original helmet which is removed shall be replaced with a component(s) yielding equal or greater performance. Following initial installation onto either the HGU-55/P or HGU-56P, the brackets will remain fixed to the helmet.

3.8.1.6 Ancillary equipment. Ancillary equipment is defined as any Velcro fasteners, helmet modification kits, objective and eyepiece lens caps, lens tissue, AA battery cartridges and Operator’s Manual as applicable to the design and other equipment as specified in the approved work order.

3.8.2 Safety. The system shall provide a design that is safe to operate, store, and maintain in its intended environment throughout its life cycle. The system shall not generate shock hazard voltage or discharges. The system shall not pose an electrical or explosive hazard when exposed to or submerged in water. Materials selected shall be flame resistant, shall not melt, and shall not release toxic vapors to the operator. Materials shall not be toxic to the wearer. Materials shall not cause more than 1.0% of the user population {0.05% objective} to have an allergic reaction or primary irritation of the user's skin. The system shall not contain materials that promote the creation of unsafe levels of static electricity. With the exception of batteries, the system shall not contain or produce hazardous materials. The system shall not contain materials that would require special handling or classify it as hazardous for storage or transportation. With the exception of batteries, disposal of uncontaminated components shall not produce hazardous waste. Disposal of any components during any stage of the life cycle shall not result in hazards causing risk of injury or death to humans or other species. If a battery power source is required, it shall be safe to use on ground, in water, and in aircraft. Newly developed lithium batteries shall comply with MIL-B-29595(1).

3.8.3 Finishes. All internal and external surfaces except for light transmitting elements that are exposed to light from external and internal sources shall be finished to achieve the lowest feasible light reflectance. External surfaces shall have a matte finish to minimize light reflection and shall be rust-resistant.

3.8.4 Workmanship. Each Image intensifier set shall be free from burrs, chips, dirt, grease, rust, corrosion, any embedded or surface foreign material, excessive adhesive, cracks, splits, cold flow, shrinkage, inclusions, porosity, or any similar characteristics. Threads shall be full and undamaged for their entire length or depth. Joints and seams shall be a tight fit, and electrical wiring shall be secure with unbroken insulation. All moving parts and adjustments shall move freely throughout their entire range without sticking, binding, or creeping. Optical elements shall be free from imperfections that adversely affect the prescribed performance. Optical element surface quality shall be consistent with the best commercial practices.

3.9 Operational performance requirements.

3.9.1 Controls and adjustments.

3.9.1.1 ON/OFF/ON switch. A three-position ON/OFF/ON switch shall be located on the power pack. Each ON position shall provide power to the binocular. Each ON position shall operate from a different battery compartment. In the OFF position, no power shall be provided to the binocular.

3.9.1.2 Low battery indicator. The low battery indicator light emitting diode (LED) located in the mount shall begin to blink when the voltage supplied by the battery compartment in use reaches 2.1 ( 0.1 Vdc and shall be visible to the crew member during binocular use. Battery endurance shall be as specified in 3.3.2.3. Batteries shall be capable of being changed within one minute while in flight by an operator at his/her crew station wearing flight gloves.

3.9.1.3 Objective focus range/torque. The objective focus adjustment range shall be from 16 inches to infinity. Focus through infinity shall be possible. Manual adjustment must be smooth and frictional without backlash.

3.9.1.4 Eyepiece diopter range/torque. The minimum diopter focus range shall be from +2 to -6 diopters at a 25mm eye relief. The breakaway torque required to adjust the eyepiece focus shall be not less than 10 inch-ounces nor greater than 100 inch-ounces. The eyepiece focus shall not change when the binocular is subjected to vibrations described in 3.4.4.4.1 and 3.4.4.4.2.

3.9.1.5 Interpupillary distance adjustment range. The interpupillary distance adjustment shall vary the interpupillary distance between the monoculars over a range of 51mm to 72mm. Individual interpupillary adjustment capability shall be provided which allows each monocular to be adjusted independently.

3.9.1.6 Vertical adjustment range. The vertical adjustment in the mount shall vary the vertical position of the binocular relative to the mount a distance not less than 25mm.

3.9.1.7 Fore/aft adjustment range. The fore/aft adjustment in the binocular shall vary the distance of the monoculars relative to the PAS a distance not less than 27mm.

3.9.1.8 Tilt adjustment range. The tilt adjustment in the binocular shall vary the angle of rotation of the monoculars relative to the PAS a total of not less than 10 degrees.

3.9.2 Interface

3.9.2.1 Mount/binocular interface.

3.9.2.1.1 Automatic breakaway. The minimum force required for the binocular to break away from the mount in a forward direction away from the pilot’s head shall be between 11 g and 15 g (see 3.5.6). At 15 g, the binocular shall break away from the mount within 1 second. The binocular shall not breakaway and the vertical adjustment shall not move when a downward force of 10 g is applied. The fore-aft adjustment shall not move when a forward force of 10 g is applied.

3.9.2.1.2 Flip-up/flip-down. The binocular shall move from both the operating position to the stowed position or the stowed position to the operating position with less than a 10 g force and always remain in the mount when the lock release button is activated. The binocular shall lock in position for both the operating and stowed positions. The image intensifier tubes shall not be activated when the binocular is in the stowed position. In either position, the mount and binocular shall not extend over 3 inches above the topmost part of the helmet, nor outside the parallel planes of the sides of the helmet, when the pilot is facing forward, seated in a normal vertical position, with helmet positioned normally. When in the operating position, the mount shall resist inadvertent binocular detachment as a result of hitting aircraft structures.

3.9.2.2 Aircraft Interface.

3.9.2.2.1 Ingress/egress compatibility. The system mounted on a helmet, while worn by the crewmember, shall (1) not hinder ingress into the cockpit and connection of life support equipment, (2) not prevent crewmembers from properly strapping into crew seats including ejection seats, and (3) not interfere with an aircrew member’s ability to normally egress from the aircraft or to perform an emergency ground egress.

3.9.2.2.2 Night vision lighting compatibility. The objective lens shall incorporate a minus-blue filter such that it causes the binocular to be compatible with Type I, Class B cockpit lighting per MIL-L-85762A. The filter also shall possess characteristics such that light emitted from a Heads-Up-Display (HUD) employing a P-1, P-43, or P-53 phosphor CRT shall be transmitted to the image intensifier. Any HUD shall be readable through the operating binocular.

3.9.2.2.3 Cockpit viewing. The binocular shall allow the aircrew, by moving their eyes to look under the binocular, to view the cockpit instruments/displays with their unaided eyes.

3.9.2.3 Life support equipment compatibility. The system shall be compatible with employment of the following equipment with neither modifications nor degradation to this equipment:

1. HGU-4/P Aviator Spectacles

2. MBU-12/P and MBU-5/P Oxygen Masks with M100, M101, and M169 microphone

3. LPU-9/P and LPU-10/P Life Preservers

4. HAU-6/P Flight Gloves

5. BA-18/22/29 Back-pack Parachute

6. PCU-15/P Parachute Harness with appropriate releases

7. SRU-21/P Survival Vest and associated equipment

8. SEAWARS (attachment to ACES II seat-mounted male parachute fittings may be simulated)

9. RCU-63(V)/P UWARS

10. PCU-33/P Parachute Harness

11. PCU-39/P Parachute Harness

12. GS/FRP-2 Flight Gloves

13. CWU-27/P Flight Suit

14. SV-2/P Survival Vest

15. CRU-79/P Oxygen Regulator

16. Laser Eye Protection Spectacles

17. The following combat Edge Equipment:

- KMU-511/P Helmet Modification Kit to the HGU-55/P helmet

- MBU-20/P Oxygen Mask

- CSU-17/P Counterpressure Vest

18. CSU-13B/P Anti-G Suit

19. PRU-57/P Headset(Active Noise Reduction)

3.9.3 Interchangeability.

3.9.3.1 Major component Interchangeability. The mounts, binoculars and power packs shall be physically interchangeable between systems of the same design without degradation of the ON/OFF/ON switch(3.4.1.1), flip-up/flip-down(3.4.2.1.2) and vertical adjustment range(3.4.1.6) requirements of this specification.

3.9.3.2 Subcomponent Interchangeability. The objective lens and eyepiece lens shall be physically interchangeable between binoculars without degradation of the resolution(3.4.3.4), collimation(3.4.3.6), objective focus range(3.4.1.3), eyepiece diopter range(3.4.1.4 except torque), and interpupillary distance adjustment range(3.4.1.5) requirements of this specification.

3.10 Human Engineering Requirements

3.10.1 Comfort. The system shall be capable of being worn by personnel for up to 12 hours while performing their assigned military duties without causing undue “hotspots” or other discomfort.

3.10.2 Stability. The system shall remain stable on the aircrew's head throughout the flight environments of the aircraft. The system shall provide stability such that the aircrew has acceptable field of view and acceptable use of devices which require precise eye position.

3.10.3 Mobility. The system shall not affect cockpit mobility and head maneuverability. NVG system components shall be aircrew-portable for ground transit to and from the aircraft, escape and evasion operations, and pre/post-flight operations.

3.10.4 Acceleration. The system shall remain structurally intact and meet the performance requirements of this document during and after exposure to pilot-induced accelerations of up to +9.0Gz for 15 seconds (with an onset rate of +6 Gz per second). The structural integrity of the NVG shall not be degraded by repeated cycles of in-flight accelerations from -1Gz to +9Gz. The system shall not cause any hazard to the user when operated at the conditions specified herein.

3.10.5 Head Supported Weight / Center of Gravity (CG). The NVGs center of gravity shall be within the limits specified in "Biodynamic Testing of Helmet Mounted Systems" by C.E. Perry, J.R. Buhrman, and F.S. Knox III, Proceedings of the 37th Annual Human Factors and Ergonomics Society Meeting (1993).

3.10.6 Windblast. The binocular, mount and rear-mounted power pack shall remain structurally intact while being subjected to a windblast speed, both on and off-axis, of 150 KEAS (5% for a minimum of 30 seconds. This requirement applies to the HGU-56P system only.

3.10.7 Human engineering criteria. Human engineering criteria principles and practices shall be considered as part of the NVG construction. Special emphasis shall be given, but not limited to controls, labeling, anthropometry, design for maintainability, and hazard and safety criteria, as applicable. Specifications MIL-HDBK-759 may be used for information and guidance on human factors engineering, and MIL-STD-1472 and may be used as a source for anthropomorphic data.

3.10.8 Human factors. The design shall foster effective performance of operating procedures, an effective personnel safety and health environment, and minimize factors that contribute to increased operator error. The design shall incorporate protection from toxic, electrical, thermal, mechanical, and other potential hazards. The design shall also reflect efficient arrangement of equipment and components; and feature characteristics that ensure a rapidity, safety, ease, and economy of use. The equipment shall represent the simplest design consistent with functional requirements.

3.11 Logistics.

3.11.1 Reliability. The NVG shall have a Mean Time Between Failures (MTBF) of not less than 5000 hours with a minimum reliability of 94 percent for a 24-hour mission at a confidence factor of 0.90 per guidance in MIL-HDBK-781A

3.11.2 Maintainability. The NVG system shall have a Mean Corrective Maintenance Time (MCMT) of 30 minutes. MCMT is defined as the total elapsed time (clock hours) to correct malfunctions divided by the total number of corrective maintenance actions during a given period of time. MCMT includes all maintenance actions required to correct the malfunction, including preparation for test, troubleshooting, removal and replacement of components, repair, adjustment, functional test, etc. MCMT does not include maintenance or supply delays and elapsed time for preventive maintenance or fitting/sizing.

The NVG system shall have a Mean Preventive Maintenance Time (MPMT) of 60 minutes per 6 months. MPMT is defined as the total elapsed time (clock hours) to prevent malfunctions, including inspections, detections, or corrections of incipient failures either before they occur or before they develop into major defects, divided by the total number of preventive maintenance actions during a given period of time. MPMT does not include maintenance or supply delays or fitting/sizing.

3.11.3 Availability. All variants of the system shall have an Inherent Availability (AI) of 0.999 calculated as:

AI = MTBOMFhw / (MTBOMFhw + MCMT)

3.11.4 Tools and Test Equipment. The system shall be maintained using existing DOD tools and support/test equipment.

3.11.5 Data Requirements. Data for the NVG shall be provided in accordance with Acquisition Documents. (See 6.2)

3.11.6 Quality Management Systems. The NVG shall be designed, manufactured, and tested under a quality management system in accordance with ASQ Q9001-2000 or equivalent.

3.12 Marking.

3.12.1 Binocular. The binocular shall be marked with:

Image Intensifier Set, Night Vision, AN/AVS-9(V)3

ID NO. XXXX-XXXXXXX

MFR IDENT [manufacturer’s cage code]

CONTRACT NO. [contract number]

NSN [national stock number]

SER. NO. XXXX

U.S.

WARRANTED ITEM EXPIRES [warranty expiration date]

Note: If required by contract, the binocular shall be marked with “US Government Property”.

3.12.2 Carrying case. The carrying case shall be marked with:

Image Intensifier Set, Night Vision, AN/AVS-9(V)3

ID. NO. XXXXXX

MFR IDENT: [manufacturer’s cage code]

CONTRACT NO. [contract number]

SER NO. XXXX

NSN [national stock number}

U.S.

3.12.3 Power pack assembly. Both types of power pack assemblies shall be marked with instructions for the proper insertion of the battery(ies). The rear-mounted power pack assembly shall be marked as follows:

ID NO. XXXXXX

MFR [manufacturer’s cage code]

SER. NO XXXX

3.12.4 Monocular housing. The monocular housing shall be marked with the year and month of manufacture, part number and manufacturer’s CAGEC. Year and month information shall appear as a four digit numerical code (YYMM) beginning with the last two digits of the year followed by a two digit month code (01 for January through 12 for December).

3.12.5 PAS. The PAS shall be marked with the year and month of manufacture, part number and manufacturer’s CAGEC. Year and month information shall appear as a four digit numerical code (YYMM) beginning with the last two digits of the year followed by a two digit month code (01 for January through 12 for December).

3.12.6 Mount. The mount shall be marked with the year and month of manufacture, part number and manufacturer’s CAGEC. Year and month information shall appear as a four digit numerical code (YYMM) beginning with the last two digits of the year followed by a two digit month code (01 for January through 12 for December).

3.13 Technical interpretations. The following technical interpretations shall be, when referenced in section 3 or 5, mandatory for this specification.

3.13.1 Damage. Damage is defined as a failure or malfunction including arcing, corona, flickering, flashing, intermittent operation or similar characteristics affecting operation; cracking, corrosion or failure of any surface, finish or materials; condensation, or moisture on any internal surface; failure of any hardware, connection or component; or any imperfections that adversely affect the prescribed performance.

3.13.2 Degradation of performance. Degradation of performance is defined as a change of the measured level of performance which can result in the assembly no longer meeting specified requirements, or which negatively impacts the crew member’s ability to perform the mission required.

3.13.3 Susceptibility. Susceptibility is defined as follows:

a. At E-fields of 200V/m, susceptibility is defined as a change in output brightness exceeding the limits of +/-35% from a steady state output condition.

b. For all conducted tests, and for the radiated susceptibility magnetic field test, susceptibility is defined as a change in output brightness exceeding the limits of +/-15% from a steady state output condition.

3.13.4 Room temperature. Room temperature is defined as +23(C, +10(C/-2( C.

3.13.5 Environmental tests. For the purpose of environmental testing, the unit under test shall be defined as the binocular, mount, and power pack unless otherwise stated. Each unit under test shall demonstrate its ability to perform properly after being subjected to all the post-environmental tests required.

3.13.6 “g”. A “g” is defined as a unit of gravitational force (on earth) to which an object is subjected.

3.13.7 Qualified product. A product that has successfully met all the requirements of an IPT or First Article witnessed by the Project Manager, or its designated representative. Should the supplier make substantial changes in the process used to produce a qualified product, or have not delivered the qualified product to the Federal Government within 12 months of contract award, an IPT shall be performed to the extent necessary to verify continued compliance to specification requirements for all characteristics of the product affected by the changes.

3.13.8 Resolution. Resolution is defined as:

System Resolution (cy/mr) = R(cy/mm) X EFL(mm) where

R = resolution of smallest test pattern resolvable and EFL = effective focal length of test collimator.

3.13.9 Brightness gain. Gain is defined as the output brightness divided by the input brightness.

3.13.10 Veiling glare. Veiling glare is defined as ghost image(s), crescents or other geometrically shaped images appearing in the system’s FOV when a bright point source of light is outside the FOV illuminating the entrance pupil of the objective lens.

4. VERIFICATION

4.1 Classification of inspections. The inspection requirements specified herein are classified as follows:

a.

Components qualification (see 4.2) b.

Initial production testing (see 4.3) c.

Conformance inspection (see 4.4) d.

Field evaluation test (see 4.5) 4.2 Component Qualification.

The contractor shall qualify the items below prior to conducting Initial production, conformance inspection or field evaluation testing. Failure to qualify any of the items listed below shall be cause for disapproval of IPT.

a. MIL-PRF-A3271099

Lens Assembly, Objective for

Image Intensifier Set, Night

Vision AN/AVS-9(V)

b. MIL-PRF-49427(CR) Lens Assembly, Eyepiece for

Aviator’s Night Vision Imaging

System AN/AVS-6(V)

c. MIL-PRF-A3279602B(NVI)-Image Intensifier Assembly,18MM, Microchannel Wafer Night

Vision, MX-10160C/AVS-6

4.3 Initial production testing (IPT). Unless otherwise specified, five units from the initial production lot shall be tested to verify compliance with the requirements of this specification (See 3.1). The contractor shall provide or arrange for all test equipment and facilities. Initial production testing shall include the examination of 4.6 indicated in Table I (Examination Schedule) and the test of 4.8 indicated in Table II (Test Schedule). Nonconformance to any specified requirement, the failure of any test, or the presence of one or more defects shall be cause for disapproval of IPT.

4.4 Conformance inspection. Unless otherwise specified in the contract or purchase order, each Night Vision Goggle shall be subjected to the examinations indicated in paragraph 4.6 and the conformance inspection tests indicated (Conf) in paragraph 4.8. Nonconformance to any specified requirement, the failure of any test, or the presence of one or more defects shall be cause for disapproval of IPT.

4.5 Field Evaluation Test. Unless otherwise specified in the contract or purchase order, units from the initial production lot shall be tested and evaluated in a series of examinations, tests, and analyses described in appendixes A. The Government will conduct the Field Evaluation Test as deemed necessary. Should the Government inspection/testing reveal a failure(s) in an NVG, the contractor shall correct the identified failure(s) until such time that the unit is determined to be acceptable in that it meets the standards set forth. Should the contractor make any change to a NVG that has passed Government qualification/ inspection /testing, i.e. configuration or composition, the changed NVG shall be required to be retested and reevaluated. The Government will not accept production NVGs until the first quantity of NVGs has passed Government inspection/testing.

4.6 Responsibility for Inspection. Unless otherwise specified in the contract, the contractor is responsible for the performance of all inspection requirements (examinations and tests) as specified herein. Except as otherwise specified in the contract, the contractor may use his own or any other facilities suitable for the performance of the inspection requirements specified herein. The Government reserves the right to perform any of the inspections set forth in the Purchase Description where such inspections are deemed necessary to ensure supplies and services conform to prescribed requirements.

4.7 Responsibility of Compliance. All items shall meet all requirements of sections 3, 4 and 5. The inspection set forth in the Purchase Description shall become a part of the contractor’s overall inspection system or quality program. The absence of any inspection requirements in the Purchase Description shall not relieve the contractor of the responsibility of ensuring that all products or supplies submitted to the Government for acceptance comply with all requirements of the contract. Sampling Inspection, as part of manufacturing operations, is an acceptable practice to ascertain conformance to requirements, however, this does not authorize submission of defective material, either indicated or actual, nor does it commit the Government to accept defective material.

4.8 Examination. Unless otherwise specified, each NVG shall be physically examined for compliance with all the requirements specified in Section 3; particular attention shall be given to the requirements listed in Table I. Examinations shall not be limited to materials, workmanship, dimensions, markings and finishes, performance, safety, human engineering, and dimensional requirements, protective coating and their application, vendor supplied item certifications. This element of inspection shall encompass all visual examination and dimensional measurements. Verification methods shall be conducted as per indicated in Table I, by conducting visual inspection, documentation and utilizing standard inspection equipment. Noncompliance with any specified requirements, verification methods, or the presence of one or more defects preventing or lessening maximum efficiency shall constitute cause for disapproval of first article.

Table I. Examination Schedule

Doc = Documentation, SIE = Standard Inspection Equipment 4.9 Inspection conditions. Unless otherwise specified herein, operational performance requirements shall be verified under the following conditions:

a. The radiation source used shall be a tungsten filament lamp operated at a color temperature of 2856 Kelvin(K)(50 K for luminance gain measurements and 2700 K to 2900 K for all other optical measurements.

b. The resolution target shall be a 100 percent contrast USAF resolution target having black bars on a clear background.

c. Tolerances on specified radiation levels shall be (10 percent.

d. Meters used for monitoring lamp current and voltage shall have an accuracy of (0.25 percent.

e. The photometer used for brightness measurements shall be calibrated against a standard source as specified below:

(1) Tungsten filament lamp operated in conjunction with an opal glass such that the color temperature of the radiation emitted from the opal glass is 2856 (50 K.

(2) Corning spectral filters nos. 3-71 and 4-67, or equivalent.

(3) Opal glass to produce a uniform Lambertian distribution.

(4) Output brightness to be 0.1 to 1.0 foot-lambert(fL) uniformly distributed.

f. Neutral density filters used in test equipment shall have transmission characteristics within 10 percent of the nominal filter transmission from 0.35 to 1.0 micrometer.

g. Tests shall be performed at room conditions as defined in 3.5.5.

h. Test chambers used for environmental temperatures tests shall maintain the temperature with (2.0C.

i. Tests shall be performed using either lithium or AA alkaline batteries.

4.10 Test of Product. Unless otherwise specified, units from the initial production lot shall be tested to verify compliance with the requirements of this specification. No braces, sealing materials, tiedown devices, or other items that are not inherently a part of the operating NVG shall be employed. Each NVG shall be subjected to the tests in Table II.

Table II. Test Schedule

4.11 Operational Test. Unless otherwise specified, each NVG shall be started and operated at the conditions specified in paragraph 4.9 for a period of 4 hr. The NVG shall perform as specified in paragraph 4.12 and 4.13.

All components shall be checked to insure proper operation. The NVG shall be compatible with all the equipment listed in paragraph 3.9.2.3 with neither modifications nor degradation to this equipment. Failure to operate as prescribed herein; evidence of any deficiency, malfunction; the need for service of any component; or loose, disassembled, or broken items that reduce the required sufficiency of the equipment shall constitute failure of this test.

4.12 Operational performance Test. Unless otherwise specified, each NVG shall be tested to verify compliance with the operational performance requirements listed in table III. Failure to operate as prescribed herein; evidence of any deficiency, malfunction; the need for service of any component; or loose, disassembled, or broken items that reduce the required sufficiency of the equipment shall constitute failure of this test.

Operational Performance Matrix

· Each ON position shall operate from a dif battery.

· OFF position, no power shall be provided 3.9.1.1

· Battery endurance as per 3.8.1.3.

· Batteries shall be capable of being changed within 1 min while in flight wearing flight gloves.

3.9.1.2

· Focus through infinity shall be possible.

· Manual adjustment must be smooth and frictional without backlash.

3.9.1.3

· The breakaway torque shall be not less than 10 inch-ounces nor greater than 100 inch-ounces.

· The eyepiece focus shall…