Statement_of_Work_(for_RFQ).pdf

STATEMENT OF WORK I SPECIFICATIONS

Electronic Standby Instrument System (ESIS)

FOR NOAA WP-3D ORION AIRCRAFT

National Oceanic and Atmospheric Administration

Marine and Aviation Operations I Aircraft Operations Center

C.2 General Scope of Work

The National Oceanic and Atmospheric Administration (NOAA), Office of Marine and Aviation

Operations (NMAO), Aircraft Operations Center (AOC) instruments, maintains and operates

WP-3D Orion and other aircraft in support of a variety of meteorological and oceanographic research projects. This requirement is for an Electronic Standby Instrument System (ESIS) for the WP-3D aircraft.

The purpose of the ESIS is to provide an independent source of attitude, air data, and navigation data for Pilot use in the event of a failure of the primary flight avionics. The NOAA WP-3D aircraft currently has an ESIS consisting of Goodrich Avionics Systems components GH-3100, Configuration Module model DCM-3100 and Magnetometer model MAG-3000A, a Jet

Electronics and Technology, Inc. model PS-850B emergency power system, a Rockwell-Collins

VIR-432 navigation receiver, and a Gables Engineering G7612-22 navigation receiver control.

Due to an upgrade of the aircraft instrumentation, the ESIS display must be moved, and the new panel location cannot support the GH-3100 instrument depth.

C.2.1 Detailed Requirements

The vendor shall provide new, current production model, Electronic Standby Instrument System

(ESIS) meeting the requirements below. The system shall interface to the existing emergency power system source and VHF navigation system. Vacuum or air pressure shall not be utilized as a power source.

a. Functionality: The ESIS shall provide pressure altitude, attitude, airspeed, VOR/ILS navigation guidance data and magnetic heading.

1) Pressure Altitude: Barometric pressure set capability selectable for InHg and hPa units. Calibrated altitude range shall exceed -1,000ft to 40,000ft. The ESIS shall be certified to meet the requirements of FAA TSO-Cl Ob or equivalent.

2) Attitude: The ESIS shall be certified to meet the requirements of FAA TSO-C4c or equivalent.

3) Airspeed: The ESIS shall be certified to meet the requirements of FAA TSO-C2d or equivalent. Airspeed maximum range shall exceed 450 knots. Airspeed awareness cues shall be in accordance with FAA Advisory Circular AC23. l 311-

1B paragraph 17.7.1 and shall be user configurable.

4) VOR/ILS: The ESIS shall accept and display navigation data (VOR/ILS) via

ARINC 429 labels from the existing Rockwell-Collins VIR-432 navigation receiver.

5) Magnetic Heading: The ESIS shall provide magnetic heading. The source of the heading may be the currently installed Magnetometer model MAG-3000A if it is approved for use as part of the proposed ESIS.

b. Lighting: Display luminance shall be automatically controlled by an ambient light sensor on the bezel of the ESIS display and/or manually controlled using the ESIS display unit controls. Display brightness shall be sunlight viewable and dimmable for levels appropriate for dark cockpit viewing.

c. Environmental: This equipment shall meet MIL-STD or equivalent commercial

Environmental and Electromagnetic Compatibility requirements (reference MIL-STD

810G/H and MIL-STD 461F) appropriate for equipment installation on the WP-3D aircraft, and the environment the aircraft is operated in, which ranges from Arctic missions in the Winter to tropical deployment in the summer. If using MIL-STD-81

OG/H Method 514.7, the WP-3D aircraft falls under Annex D, Category 13, Vibration

Level 1.2 g2/Hz in the area available for the air data unit portion of the ESIS and

Vibration Level 0.1 g /Hz in the area of the ESIS display unit(s).

d. Certifications: RTCA Software validation level at least D0-178A Level II. FAA TSO

C2d, C3e, C4c, C6e, C l Ob, C46a, C106, Cl 13.

e. Size: The minimum viewing area of the ESIS display shall be 6 in

• Maximum display dimensions (bezel) 5.5 inch wide, 3.5 inch tall, 2 inch thick (from bezel mounting surface to rear of display unit excluding connector).

f. Weight: ESIS system weight, including two display units and associated magnetometer and external electronics assembly, shall not exceed 6 pounds.

g. Power: 28Vdc. Combined power requirements for the ESIS and associated VIR-432 navigation receiver, and a Gables Engineering G7612-22 navigation receiver control

Electrical Interface shall be such that the system operates for a minimum of 60 minutes while obtaining power solely from the currently installed Jet Electronics and Technology, Inc. model PS-850B emergency power system. Current draw specifications for the proposed system shall be included in the quote package.

h. Pitot and Static Port Connectors:

1) Pitot pressure port in accordance with MS33649-04 or equivalent

2) Static Pressure port in accordance with MS33649-05 or MS33649-06 or equivalent

i. Documentation: Interface drawings, wiring requirements and limitations, continuing airworthiness requirements, operator instructions and manuals, and any other documentation necessary for installation and operation of the ESIS shall be included in the quote package.

j. The unit shall be suitable for operation with a gloved hand in an avionics setting. Knob control is preferred over multiple button controls for common in-flight operations such as adjusting the display brightness or adjusting the barometric pressure setting.

C.2.2 Terms I Acroynms

ESIS Electronic Engine Instrument System

FAA Federal Aviation Authority ft Feet hPa Hector Pascal measurement unit

ILS Instrument Landing System

InHg Inch of Mercury measurement unit

TSO Technical Standards Order

VHF Very High Frequency

C.2.3 Line Item 0001 - ESIS SYSTEM Including: Display Units (Quantity 2), Sensor Unit, Magnetic Sensing Unit (only if the WP-3D currently installed unit is not approved to be used with the proposed system), other required ESIS system components unique to the vendors proposal (example: an external configuration module), install kit, and system documentation.

Qty 2

C.2.4 Line Item 0002 -Spare ESIS components, excluding Display Unit Including: Quantity 1 of all ESIS components in Line Item 0001 excluding the display unit, installation kit, and documentation.

Qty 1

C.3 Delivery schedule

Delivery to AOC shall not exceed 180 calendar days after the vendor's receipt of a signed purchase order (PO).