Attachment 1 - Section 3 Specifications Final.pdf

Solicitation Number 89233121RNA000098 Attachment 1

Section 3 – Description/Specifications

3.1 BACKGROUND

The National Nuclear Security Administration (NNSA) Office of Nuclear Incident Response (NA-84) is the premier technical leader in responding to and successfully resolving nuclear and radiological incidents or accidents. Technical teams are prepared to search for radioactive material and help manage the consequences of a release of radioactive material into the environment. One of these assets, NNSA's Aerial Measuring System (AMS), has specialized airborne radiation detection systems to provide real-time measurements of low levels of air and ground contamination or other material. The trained experts, equipment, and aircraft maintain a state of readiness to respond to a radiological emergency at any time. The aircraft operations are at Joint Base Andrews, MD, and Nellis Air Force Base, Las Vegas, NV.

These aerial survey flight envelopes are from fifty (50) feet to three thousand (3,000) feet above ground level (AGL), at speeds from sixty (60) to eighty (80) knots ground speed. A crew of six will consist of two (2) pilots, two (2) technical specialists that operate the detection equipment, and two (2) mission personnel. Survey flight patterns are predominately precise parallel line patterns with specific, narrow offset distances and constant (as much as practical) above ground level (AGL) altitudes, often performed over congested areas of the country. Helicopters will be operated predominately from civil or military airports, not elevated platforms.

Two (2) of the AMS aircraft, Bell 412HP helicopters, have reached the point where increasing unscheduled maintenance is adversely affecting the mission readiness posture (24-hour/365-day Emergency Response). Replacing these two helicopters with two new or used mission capable rotary wing aircraft began in Fiscal Year 2020. This document sets the requirements for these replacement aircraft.

Helicopter flight hour program is projected to be two hundred fifty (250) hours per year.

3.2 CLIN 0001 - HELICOPTER BASE CONFIGURATION – MANDATORY SPECIFICATIONS

1. Helicopter requirements and specifications are for two (2) helicopters purchased on the same contract and awarded at the same time. The subsequent helicopter must be identical in make, model, year of manufacture, avionics, power plants, and installed equipment, all to the extent possible as the initial helicopter.

2. All installed equipment on the subsequent helicopter shall be the same as the equipment installed on the first helicopter or achieve a standard of "commonality" as approved by the NNSA.

3. Systems and component quantities listed shall be installed in helicopter as specified herein and shall meet or exceed FAA certification, and/or meet US Government equivalent requirements, upon possession by NNSA.

4. Helicopter may be newly manufactured, or used, twin-turbine engine powered rotary wing aircraft.

5. Newly manufactured is zero time (nominally < 10 hours, or as necessary for standard post-production test flights, check flights, maintenance flights, and as necessary to achieve certification), no previous owner, the latest improved model in current production, as offered to commercial trade.

6. Used helicopter shall be current on all Airworthiness Directives (ADs) and have minimum seventy five percent (75%) time remaining on all airframe, power plant, and life-limited components as specified by the manufacturer.

7. Used helicopter shall have minimum seventy five percent (75%) time remaining, either flight hours or calendar period, before a major inspection is required as specified by the manufacturer.

8. Helicopter shall be 14 CFR Part 91 General Operating and Flight Rules compliant.

9. Helicopter shall have a Standard Airworthiness Certificate (FAA Form 8130-6), or other airworthiness qualification determined acceptable by NNSA.

10. Helicopter avionics and electrical systems shall be installed and approved either as part of the helicopter’s original type certification or under supplemental type on FAA Form 337 and other FAA-approved methods, and/or meet US Government equivalent requirements.

11. Helicopter shall be certified under 14 CFR Part 29 Category A and/or Category B at mission weight from civil or military airfields (not elevated helipads) or meet US Government equivalent performance capability.

12. Helicopter shall meet the requirements of 14 CFR Part 36, Noise Standards: Aircraft Type and Airworthiness Certification, Subpart H- Helicopters.

13. Helicopter shall have a temperature operating range from -40° Celsius to +50° Celsius at sea level.

14. Helicopter shall meet FAA certification requirements for Day Visual Flight Rules (VFR) Single Pilot

Operations.

15. Helicopter shall meet FAA certification, and/or meet US Government equivalent requirements, for

Day, Night, Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) operations.

16. Helicopter shall be adverse-weather capable, including protection for inadvertent icing encounters and subsequent actions to exit the condition.

17. Helicopter shall be equipped with dual flight controls.

18. Helicopter shall have an Automatic Flight Control System (AFCS) with integrated digital autopilot/flight director computers, flight director mode selectors, autopilot controller, air data sensors, and navigation computers (GPS, VOR, ILS). System shall be capable of three (3) Axis autopilot-controlled cruise, approach, departure, and level- off.

19. Helicopter shall have an Electronic Flight Instrumentation System (EFIS) incorporating two (2) separate and independent Directional Gyro (DG)/Vertical Gyro (VG) systems. System shall indicate direction, airspeed, vertical speed, and altitude.

20. Helicopter shall be flyable with all avionics systems disabled.

21. Helicopter shall have Flight Management Systems (FMS) with Search and Rescue (SAR) patterns to include parallel line and creeping line, and return to point capability. Unlike SAR flights, the aerial survey work requires uniform coverage throughout the search area at a constant AGL altitude, constant ground speed, precise (± ten (10) feet lateral navigation on survey lines, and uniform line spacing. The SAR patterns are used as a pilot assist to perform the aerial survey mission.

22. Helicopter shall have one (1) Traffic Alert and Collision Advisory System (TCAS).

23. Helicopter shall have one (1) Terrain Avoidance and Warning System (TAWS).

24. The pilots shall have the ability to disable, and enable, TAWS and TCAS for mission requirements.

Other altitude or object related warnings or annunciators, (e.g., "gear down"), shall also be disabled, and enabled, by the pilots during flight.

25. Helicopter shall have Automatic Dependent Surveillance - Broadcast (ADS-B) Out installed.

26. Helicopter shall have a minimum of one (1) Multi-Function Display (MFD) integrated with weather radar, navigation data, TCAS, TAWS, moving map system, and search and rescue pattern data.

27. If helicopter is equipped with only a single MFD, the addition of stand-by instruments capable of providing full time display of heading, airspeed, altitude, and attitude to the Pilot-In-Command are required.

28. Helicopter shall have an External Cargo Hook system for wildland firefighting HELITAC operations with cockpit weight on hook indicator, control panel, and External Cargo Hook controls for both pilots. An emergency cargo hook load release system accessible to both pilots will also be installed.

The aerial survey equipment will be removed during HELITAC flight operations.

29. Helicopter shall be compatible with SEI Industries LTD, Bambi Bucket® operation. The Bambi Bucket®, Model 2024 MX, will be Customer Furnished Equipment (CFE).

30. Helicopter shall have a cargo hook minimum capacity of 3,500 pounds.

31. Helicopter main rotor blades shall be painted with a high visibility paint scheme.

32. A Wire Strike Protection System or equivalent shall be installed on the helicopter for both rotor mast and undercarriage, if applicable.

33. Protection from snow and foreign object damage shall be installed.

34. Helicopter windshields shall be high-integrity, laminated glass-type or equivalent.

35. Helicopter shall have a windshield defogging system.

36. Helicopter shall have an environmental control system including ducting to provide adequate air conditioned cooling and heating distribution throughout cockpit and cabin.

37. Helicopter shall have a cockpit mounted temperature control panel and cabin air temperature display.

38. Helicopter shall have cockpit stowage provisions for the flight manual, credit card holder, charts, and portable electronic devices(s) and equipment.

39. Helicopter shall have two (2) portable fire extinguishers, one (1) near the pilot station and one (1) in the cabin.

40. Helicopter shall have cockpit mounted flight-time recording hour-meter.

41. Mission equipment power system busing, circuit breakers, and switching shall be controlled from the cockpit.

42. An emergency mission equipment shut off shall be provided.

43. Helicopter shall have one (1) Avionics Master Switch to control all on/off avionics functions.

44. Helicopter shall have an internal communication audio system capable of managing and controlling multiple audio sources in the aircraft and is software configurable. It must be able to distribute and control all audio in the aircraft, to/from all transceivers, cockpit-call and crew-call capability, and aural alert sources and warnings. The system will have control panels with Voice Activated Transmit (VOX) Wired Jacks and Headsets. Two control panels will be in the cockpit, and four (4) in the cabin. Four (4) additional headset jacks, in addition to the audio control panels, will be available in the cabin. Control panel locations and additional headset jack locations will be determined by

NNSA.

45. If VOX is not installed, helicopter shall have both pilot and co-pilot remote push to talk switches mounted on either the instrument panel or console for both pilot and copilot use.

46. If VOX capable audio management systems not installed, helicopter shall have cockpit and cabin Inter Communication System (ICS) with cockpit-call and crew-call indicators. A cockpit mounted switch shall be installed that will isolate the cabin ICS system from the cockpit with similar capability for the cabin to isolate the cockpit. Two (2) ICS control panels will be in the cockpit, and four (4) in the cabin. ICS control panel and switch locations will be determined by NNSA.

47. Helicopter shall have position and anti-collision lighting.

48. Helicopter shall have a pilot controllable aircraft spotlight with auto-stow (used to assist with aircraft landing ops). System shall have a cockpit “light on” advisory.

49. Helicopter shall have fire detection and suppression systems.

50. Helicopter shall have left and right cabin door opening systems.

51. Helicopter door latching mechanism operating instructions and emergency egress directions shall be clearly displayed.

52. Helicopter door latch release and door closing mechanism shall be accessible from inside the cabin.

53. Helicopter shall have a cockpit installed door position advisory system for all doors.

54. Helicopter shall have battery operated emergency egress lighting capable of providing illumination for 10 minutes at critical ambient conditions.

55. Helicopter shall have at least two (2) cockpit ceiling mounted map lights with dimming capability, one for pilot use and one for co-pilot use.

56. Helicopter shall be capable of carrying a minimum of six (6) crew members: two (2) pilots, two (2) technicians, two (2) mission personnel, and detectors and mission equipment. Total mission configuration pay load is approximately 2,400 lbs.

57. Helicopter shall be capable of 350 NM range at 7500 feet Pressure Altitude, ISA, with full mission equipment, detectors, and personnel (approximately 2,400 lbs.), with a twenty (20) minute VFR reserve.

58. Helicopter shall be capable of Hover Out of Ground Effect (HOGE) ceiling, International Standard Atmosphere (ISA), at mission weight, 7,500 feet mean sea level (msl).

59. Helicopter shall be capable of supplying avionics output to mission equipment of:

a) Radar Altimeter

b) Heading and speed

c) 3-D Orientation NNSA will provide specifications for output format, or output format acceptability.

60. Helicopter shall have onboard Wi-Fi.

61. Helicopter shall have a Satellite Communications (SATCOM) system capable of simultaneous voice and data, operable from ground level through 10,000 feet AGL to transmit aerial survey data and provide voice communications. The SATCOM system shall be capable of Background IP (also known as Standard IP or Variable Bit Rate IP) up to 300 kbps, and Streaming IP (also known as Constant Bit Rate IP) at 128 kbps within the Continental United States.

62. Helicopter shall have the capability for non-ATC phone calls using either INMARSAT or IRIDIUM assigned security phone numbers (ICAO short codes), or direct dial using commercial phone numbers and country codes. Call stations (or equivalent) will be accessible both in the cockpit and the cabin to place and receive calls.

63. Helicopter shall have a rotor track and balance and vibration analysis system.

64. Helicopter shall have mechanical system inspection and service access panels.

65. Helicopter shall have accessible electronics compartments.

66. Helicopter shall have access hydraulic system servicing provisions.

67. Helicopter instrumentation and avionics shall be mounted with sufficient extra wiring to allow easy removal.

68. Helicopter engines shall be equipped with engine wash and drain kits.

69. Helicopter shall be equipped with redundant generators and associated system components to supply required DC and AC mission equipment electrical power, with each generator supplying power to its respective primary bus.

70. Helicopter generators shall have the capacity to power the aircraft electrical system in the event of a single generator failure with the understanding that mission equipment loads shall require shedding for single generator operation.

71. Helicopter shall have a separate inverter for the mission equipment AC power system, if applicable.

72. Supplied mission equipment shall be connected to the helicopter AC and DC non-essential bus power system.

73. Helicopter shall have at least twelve (12) 120 VAC outlet receptacles (NEMA 5-15) in the cabin capable of delivering fifteen (15) amps maximum, in total, for mission equipment. Receptacle locations to be determined by NNSA.

74. Helicopter shall have two (2) USB charge panels in the cockpit and six (6) USB Charge panels in the cabin. Each USB charge panel shall have one (1) USB-C port rated at 100 watts, and one (1) USB3.0 Type-A port rated at 4.5 watts. Locations to be determined by NNSA.

75. Helicopter shall have at least twelve (12) 28 VDC (7.5-amp max) mil-spec circular 3-pin power outlets in cabin capable of delivering 50 amps maximum, in total, for mission equipment. The third pin will be a positive chassis ground. Power outlet locations to be determined by NNSA.

76. Helicopter electrical system shall include an electrical generator control unit and fault detection circuitry.

77. Helicopter shall have all antennas, connectors, adapters, annunciators, and mounting systems specific to all radio components. Antenna layout will require NNSA consultation prior to mounting.

78. Helicopter shall have one (1) XM Satellite Weather Information system, or equivalent, interfaced with the EFIS.

79. Helicopter shall have a Radar Altimeter which displays on both pilot and co-pilot stations, with provisions for output to mission equipment. The Radar Altimeter shall have the capability to output both analog voltages and ARINC 429 digital format to the mission equipment.

80. Helicopter shall have one (1) set of “stand alone” instruments to include one (1) attitude indicator with self-power, one (1) air speed indicator, one (1) pressure altimeter, one (1) direction/navigation indicator, and one (1) vertical speed indicator (VSI).

81. Helicopter shall have an integrated radio system including, but not limited to: two (2) VHF Communications radios, one (1) Navigation radio, one (1) Mode S Transponder, one (1) Automatic Direction Finder (ADF) radio, and one (1) DME radio and indicator.

82. Helicopter shall have one (1) GPS antenna and GPS receiver dedicated to the mission equipment in the cabin. The GPS antenna cable will be "home run" to a splitter/patch panel in the cabin. The GPS receiver will have performance equivalent to a NovAtel PwrPak7D receiver. The GPS Antenna will have performance equivalent to a NovAtel antenna Part No. GNSS-303L or an AeroAntenna Technology, Inc. AT1675-180APW-TNCF-000-RG-38-NM . GPS antenna to receiver cable specifications and performance will be equivalent to a PIC Wire and Cable UH22089. Standard polarity THC type connectors will be used. Panel location will be determined by NNSA.

83. Helicopter shall have a multi-band radio system for air to ground communications that will interface with emergency response organizations (police, fire and rescue), up to 900 megahertz, and be P25 digitally-compliant and trunk capable. There shall be one (1) control head in the cockpit and one

(1) control head in the cabin, or be controlled by the audio management system.

84. Helicopter shall have one (1) UHF communications radio or one (1) Multi- band radio covering UHF/VHF in both AM & FM spectrums).

85. Helicopter shall have exhaust covers.

86. Helicopter shall have air inlet covers.

87. Helicopter shall have pitot tube covers.

88. Helicopter shall have cargo tie-downs appropriate to the proposed model of helicopter.

89. Helicopter shall have main rotor tie-down appropriate to the proposed model of helicopter.

90. Helicopter shall have specialized Tow-Bar for helicopter.

91. Helicopter shall have two (2) modular high density, utilitarian cabin seats for airborne survey mission with all belting, backrests and headrests.

92. Helicopter shall have two (2) luxury cabin seats for airborne survey mission equipment operators with all belting, backrests and headrests, allowing for rapid re-configuration to achieve diverse mission sets.

93. Helicopter shall have a four-point restraint system for all cabin seats.

94. Access to all seat belts and shoulder harness mechanisms hidden by any structure will be by screw-mounted access panels.

95. Helicopter shall have a corrosion prevention coating.

96. Helicopter final exterior paint scheme shall be determined by NNSA and shall consist of three different Axalta Coating Systems (or equivalent) colors – an upper color Axalta Starlight Silver, 815213, Ref Value: 40, a lower color, Axalta Dark Blue 814551, Ref. Value: 6, and an accent stripe, Axalta Wildcat Yellow 765282, Ref Value: 49.

97. The DOE Seal, NNSA logo and American Flag decals for each side of each aircraft will be provided by contractor. The electronic graphics files for the DOE Seal, NNSA logo and American Flag decals will be provided by NNSA.

98. Helicopter FAA registration numbers for helicopters shall be selected by NNSA.

99. Four (4) pilot simulator training courses will be provided with each helicopter within 6 months prior to delivery of the first helicopter and within 12 months post-delivery of the second helicopter.

100. Two (2) mechanic training courses will be provided with each helicopter within 6 months prior to delivery of the first helicopter and within 12 months post-delivery of the second helicopter..

101. Vendor shall provide performance indicator data for Mean Time Between Failures, Mean Time To

Repair (corrective maintenance after a failure has occurred), and annual scheduled maintenance duration(s) with vendor proposal.

102. Helicopter shall be capable of securing (via floor rails, tracks, consoles, or equivalent), the following customer furnished detector equipment listed in Section C, Table 1 on the aircraft. The Government Furnished Detector Equipment will not become part of the aircraft.

Section C Table 1, Detector Equipment:

Detector Equipment

Length Inches

Width Inches

Height Inches

Total Area Sq. Ft.

Weight Each

Pounds

Quantity Total Weight Pounds

a) RSX-3 29.625 16.125 7 13.4 100 6 600

b) HPGe 14.5 6.5 14.5 1.3 23 2 46

c) N0 79.5 18.25 8.75 10.1 230 1 230

103. Detector equipment mounting restrictions are:

a) Equipment is not stacked.

b) Equipment has minimal aircraft structure beneath it and the ground.

c) RSX-3 and HPGe equipment are not mounted over a variable volume fuel tank.

d) Detectors shall have an unobstructed field of view, if possible. The bottom faces of all crystals must have a field of view with opening half-angle at least 70 degrees that is unobstructed by fuel tanks or significant shielding. Detector placement unable to attain this field of view will be evaluated by NNSA to determine suitability.

e) N0 Detector preferably not mounted over variable volume fuel tank.

104. Helicopter shall be capable of securing (via floor rails, tracks, consoles, or equivalent), government furnished mission equipment listed in Section C Table 2, in addition to the detector equipment, on the aircraft. The Government Furnished Mission Equipment will not become part of the aircraft.

Section C Table 2, Mission Equipment:

Mission Equipment Length (Inches)

Width (Inches)

Height (Inches)

Weight Each (lbs)

Quantity

a) RS-501 19 16 1.75 3 1

b) RS-701/705 10.375 8.125 3.625 5 6

c) Trimble Ag GPS 170 Field Computer (Steering)

7.5 9 4 7 1

d) Trimble Ag GPS 132 GPS Receiver 5.75 7.75 2 12 1

e) Laptop Computer 14 9 1.75 6 2

f) Cradlepoint router 14 6 6 5 1

g) HP Kit (Pelican case, or equivalent) 12 12 5 15 1

105. Mission equipment secured to the helicopter have the following provisions:

a) The laptops and Cradlepoint router will be accessible to the operators while in flight.

b) It is desirable to access the RS-701/705 during flight.

c) The mission equipment and detector equipment will be connected via data/signal cables.

3.3 CLIN 0002 – AIRFRAME ENHANCEMENTS

0002AA Certified for Single Pilot IFR Operations, if applicable (i.e., max gross weight less than 12,500 lbs.).

0002AB Health and Usage Monitoring System (HUMS) provisions and removable components installed.

0002AC Vibration Management System.

0002AD Crash resistant fuel system per 14 CFR §29.952 0002AE Energy-Absorbing Seats.

0002AF Energy-Absorbing Landing Gear.

0002AG Crashworthy Fuselage.

0002AH Fuselage and Rotor System Bird Strike Protection.

0002AJ Main Engine Turbine Burst Protection.

0002AK Emergency Locator Transmitter (ELT).

0002AL Intake filters shall be “cleanable”, (e.g., Inlet Barrier Filter).

0002AM Windshield and Main Engine Ice Protection/Anti-Icing System.

0002AN Lightning Protection.

0002AP High Intensity Radiated Field (HIRF) Protection.

0002AQ Gimbal Mount and/or Optical Port. Specifications to be provided by NNSA.

0002AR Downward-Facing LED Illumination (landing and/or searchlight) and Navigation Lighting Fixtures (Nav lights)

0002AS Helicopter shall have directionally controllable, high intensity lights for cabin illumination. Master light switch shall be cabin controlled with dimming capability at each light. Location of master light switch to be determined by NNSA.

0002AT Pulsing exterior lighting system. System shall pulse both recognition and landing lights with the ability to select the system either on or off by cockpit mounted switch so that the recognition and landing lights can function normally.

0002AU Pilot and co-pilot seats incorporating direct heating/cooling capability.

0002AV Five-point seat restraint system for cabin seats.

0002AW The helicopter cabin and cabin door area shall be equipped with controlled entry lighting that shall illuminate the cabin interior and exterior during loading or unloading. There shall be switches located by both cabin doors and an additional switch located on the cockpit capable of activating the lighting system.

0002AX Helicopter fuel filler cap(s) shall have means to secure them during refueling operations.

0002AY Helicopter shall have main rotor brake with cockpit indicators.

0002AZ Run-dry transmission or gearbox.

0002BA Pilot and copilot bird resistant windshield.

0002BB Graduated tint for both pilot and copilot windshield.

0002BC Helicopter shall have latching mechanisms installed to hold the cabin doors in the open position during loading, unloading, and in flight, if applicable.

0002BD Helicopter shall have common keys for all door lock mechanisms including baggage door(s).

0002BE All helicopter cabin windows shall be tinted or capable of adjustable opacity.

0002BF Helicopter shall have tinted cockpit skylight windows.

0002BG Helicopter landing gear shall be of the highest (greatest ground clearance) certificated type available by the manufacturer.

0002BH Helicopter shall have external ground operation power receptacle with a “GPU Door Open” advisory in the cockpit

3.4 CLIN 0003 – MISSION CAPABILITY ENHANCEMENTS

0003AA During ground operations provide a means where the mission equipment (15 Amps at 120VAC and 50

Amps at 28VDC) can be powered and operated separate from the aircraft specific systems. System shall be capable of both continuous mission equipment operation from ground-based power source, and aircraft based or portable power source with capacity to operate mission equipment for forty five (45) minutes when ground based power is not available.

0003AB Two (2) equipment workstations/consoles located in the cabin capable of mounting one (1) or more monitors, keyboard, audio panel, laptop, docking station, RS-701/705, and a Cradlepoint Router. Vendor proposed solution conceptual design and final design will be approved by NNSA post contract award.

0003AC The aerial survey work requires uniform coverage throughout the search area at a constant AGL altitude, constant ground speed, precise survey lines, and uniform line spacing. A "Search" navigation capability to aid the aerial survey pilot would provide the pilot an indicator with plus or minus one foot (or as technologically feasible) horizontal and vertical guidance while terrain following at altitudes as low as 50 feet AGL. May or may not be integrated with FMS. Indicator must be positioned at eye level or above the fuselage/wind shield intersection for the pilot flying, for example a heads up display (HUD), or head-wearable display (HWD). Presentation to have the ground speed and altitude displayed. (Current system is a non-integrated Trimble Agricultural light-bar display).

0003AD Provisions for Auxiliary Fuel Tanks to extend mission survey time or enhance en route performance.

0003AE TCAS II.

0003AF Full Authority Digital Engine Control (FADEC) System.

0003AG Four (4) Axis Auto Pilot System (AFCS) With Auto-Hover.

0003AH Remote camera installed on the fuselage bottom to display hook operations in the cockpit.

0003AJ One (1) battery temperature indicating system or equivalent, unless a sealed lead acid battery is used.

0003AK One (1) Density Altitude Indicator.

0003AL Thermal imaging system. Specifications to be provided by NNSA.

0003AM Class A Enhanced Ground Proximity Warning System (EGPWS), with look ahead alerts, altitude callouts, terrain display. Capable of providing a high-resolution database for both on and off airport/heliport operations and give callouts during an autorotation. (need to have inhibit and enable capability controlled by either pilot during flight)

0003AN Automatic Dependent Surveillance - Broadcast (ADS-B) IN and OUT

3.5 CLIN 0004 – COCKPIT ENHANCEMENTS

0004AA Multi MFD panel instrument panel with integrated with weather radar, navigation data, TCAS, moving map system, and search pattern data. Center panel(s) include engine performance data.

0004AB Wide Area Augmentation System (WAAS) capabilities.

0004AC Remote camera installed on the fuselage bottom to display hook operation in the cockpit, visible to both pilots.

0004AD Second Navigation Radio and indicator.

0004AE Helicopter mission equipment power system “on” annunciator/indicator shall be displayed in the cockpit.

3.6 CLIN 0005 – OPERATIONAL EQUIPMENT ENHANCEMENTS

0005AA Laser Altimeter with output only to operator mission equipment. (For example, a Riegl® LD90-3800VHS-

FLP, or equivalent.)

0005AB Belly tank with snorkel with both on the ground by hydrant and hover refill capability. The ground fill port will be specified by NNSA. Tank will be equipped with an emergency dump system that allows rapid drop of the entire load. System status information and controls are located in the cockpit.

3.7 CLIN 0006 – SPARES, SUSTAINMENT, AND TRAINING

0006AA Four (4) pilot simulator training courses within 6 months prior to delivery of the first helicopter and within

12 months post-delivery of the second helicopter. These are in addition to the four (4) pilot training requests per helicopter in M.8 CLIN 0001 #105, for a grand total of twelve (12) pilot simulator training courses.

0006AB Two (2) mechanic training courses within 6 months prior to delivery of the first helicopter and within 12 months post-delivery of the second helicopter. These are in addition to the mechanic training requests of two (2) per helicopter in M.8 CLIN 0001 #106, for a grand total of six (6) mechanics training courses.

0006AC Two (2) Avionics maintenance training courses.

0006AD Manufacturer’s Recommended Aircraft Spares for two separate operational locations.

0006AE Manufacturer’s Recommended Annual Inspection Spares 0006AF Manufacturer’s Recommended Time and Calendar Components 0006AG Manufacturer Maintenance plan(s).

0006AH Desktop maintenance trainer hardware and software.

3.8 CLIN 0007 –GROUND SUPPORT EQUIPMENT

0007AA One (1) Ground Power Unit per helicopter.

0007AB One (1) Hydraulics Service Cart per helicopter 0007AC One (1) Air Conditioner Service Cart per helicopter 0007AD One (1) Set of Hydraulic Aircraft Jacks per helicopter 0007AE One (1) Set of Maintenance Stands per helicopter

3.9 – Government Furnished Equipment

Vendor will have access to the GFE to ensure installation in aircraft can be validated. Equipment currently in use for securing/mounting detector and mission equipment is available as Government Furnished Equipment if it is compatible with vendor securing mechanisms or systems.

Available Equipment:

1. Neutron Pod (N0)

2. Laptops

3. RSX-3

4. Pilot Hand-Held Tablets and Mounts

5. Cradlepoint

6. GM Tube

7. RS-501

8. RS-705/701

9. HPGe

10. HPGe charging Base

11. Health Physics (HP) Kits

12. Trimble AgGPS 170 Field Computer (Steering)

13. Trimble AgGPS 132 GPS Receiver

14. Head sets

15. Helmets

16. Crew flight suits

17. Trimble Steering Bar

18. Mission Mounting Tray

19. Spot Tracker

20. First Aid Kit

21. Pedestals for Laptops and Trimble

22. Neutron pod Mount

23. Gamma Pods and Mounts

24. Detector and mission equipment power cords and cabling

25. SEI Industries LTD, Bambi Bucket®, Model 2024MX, Serial Number 10272