Attachment_2_-_IRD.docx

Interface Reference Document (HEEWJ Capabilities IRD) Version 2.0 In support of Solicitation N00421-18-R-0009 (Attachment 2)

NAVAIR PMA-226 Contracted Air Services 18 December 2018

Distribution Statement C: Distribution authorized to U.S. Government agencies and their contractors, Critical Technology 2 March 2016. Other requests for this document shall be referred to NAVAIRSYSCOM, AIR-1.0, PMA 226, PO Box 8026 E Street, Bldg 298, Rm 200, Cherry Point, NC 28533.

WARNING - This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et seq.) or the Export Administration Act of 1979 (Title 50, U.S.C., App. 2401 et seq.), as amended. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

1. Introduction

1.1 Scope. This document includes the Government Furnished Information (GFI) required to support High Endurance Electronic Warfare Jet (HEEWJ) capability Government provided equipment aboard contractor aircraft. Unless otherwise identified as Government provided equipment, equipment identified herein will be provided by the contractor.

1.2 Purpose. This data is to be used by the contractor as a source of information required for integration of the Government equipment on the contractor aircraft.

2. Applicable Documents

2.1 Reference Documents

(a) Interface Control Document Countermeasures Set AN/ALQ-167(V), 30 November 2010

(b) AN/AST-6(V) Radar Emission Simulating Set Interface Control Document, 1 May 1997

(c) ATSO 23D-AST9-1, Interface Control Document Airborne Simulator Set AN/AST-9(V)

(d) Interface Control Document Large Area Tracking Range (LATR) Shipboard and Rotary Wing (RW) Technology Upgrade (LSRTU), 29 April 2015

(e) TCTS/P5CTS Interface Control Document

(f) LAU-7/ADU-299 (Organizational and Intermediate Level Maintenance with Illustrated Parts Breakdown Aircraft Guided Missile Launcher)

(g) URC-200 (V2) LOS Transceiver Operation and Maintenance Manual, August 2011

(h) HARRIS FALCON III® AN/PRC-158 Multi-Channel Manpack Manual

(i) AN/APX-123/A(V) Common Transponder Instrument Racks drawing for EA missions

(j) NRL 5730 Multi-Channel DRFM Installation and Operation Manual

(k) FAA Order 8300.16 w/ CHG 1, 07 December 15

2.2 Enclosures

(1) NRL MAXDRFM Dimensions and Weights

(2) DRFM Pod Horn Antenna Mount Adapter

3. Externally Mounted Equipment. The following pods are Government provided mission equipment and will be installed and operated on HEEWJ platforms:

a. ALQ-167: Countermeasures Set AN/ALQ-167(V) per reference (a).

b. ALQ-188: Countermeasures Set AN/ALQ-188(V) per Figure 1.

Electrical:

External Power Requirements

Mechanical: Weight Length Width Height Diameter Environmental:

Altitude Operating Temperature Vibration Storage Temperature Humidity

115 ±6 VAC, 400 Hz, 3–phase, 5A/phase

+28 ±3 VDC, 2A

350 lbs

113.50 inches Standard FWD/AFT

28.25 inches, including antennas

14.74 inches, including lugs

10.00 inches, canister only

0 to 40,000 ft –40 to +71° C

17.8 gs RMS (15 to 2000 Hz) –55 to +125 °C 85% RH (maximum.)

Figure 1: ALQ-188 Physical and Electrical Characteristics

c. AST-6: Radar Emission Simulating Set AN/AST-6(V) per reference (b).

d. AST-9: Airborne Simulator Set AN/AST-9(V) per reference (c).

e. ALE-43: ALE-43 Shape RF Electronics Pod per Figures 2 and 3.

Figure 2: ALE-43 Physical Specification

2.0 A average

3.5 A peak

1600 VA

Figure 3: ALE-43 Electrical Specification

f. TCTS/P5CTS). Tactical Combat Training System (TCTS) /P5CTS Pods are mounted using the LAU-7 and/or ADU-299 adapter. See Refs (e) and (f).

g. Zombie pods. Zombie pods are any empty pod shell used to house receive and/or transmit antennas.

h. DRFM Horn antenna. DRFM Pod Horn antenna universal mounting adapter is described in Enclosure 2.

3.1 External Equipment Power and Control. The pods listed in paragraph 3 above require 115VAC, 400Hz, 3 phase power along with wiring for controls and signals. Table 1 identifies the generic wiring for the pods and Dual Control Boxes (DCBs). Pigtails for ALE-43 pod/DCB will be by the Government provided mission equipment. All other pigtails must be provided by the contractor to connect the DCBs to the aircraft interior wiring and from the pylon connector to the pods. Each pod system has a different pinout and will require unique pigtails.

Table 1: Pod to Aircraft to DCB Generic Wiring Note: 22 AWG (shielded wire) can be used for modified 1553 signals

The external power wiring requirements to the wing pylons are provided in Table 2. The wing hardpoint connector must be located within a maximum of 18” from the pylon aft lug location.

12 AWG

12 AWG

A B C

115 A PHASE

115 B PHASE

115 C PHASE

12 AWG

12 AWG

D E F

PHASE A NEUTRAL

PHASE B NEUTRAL

PHASE C NEUTRAL

Table 2: External Power Wiring

Table 3, the Special Mission Power Outlets requirements, is for two connectors installed in the interior equipment area of the fuselage that provide power to rack mounted systems.

Special Mission Power Outlet

Socket B Socket C Socket D Socket E Socket F Socket G Socket H Socket V Phase A line (115VAC, 400Hz, 15A) Phase B line (115VAC, 400Hz, 15A) Phase C line (115VAC, 400Hz, 15A) Phase A return Phase B return Phase C return 28VDC (25A, special mission switched) 28VDC ground 28VDC (15A minimum, aircraft battery switched)

Table 3: Special Missions Power Outlets

Table 4, the Signal Wiring requirements, is for two sets of cables, each with a connector installed in the interior equipment area of the fuselage wired to a connector to each of the wing pylons. The wing hardpoint connector must be located within a maximum of 18” from the pylon aft lug location.

CABIN RF #1

WING RF #1

CABIN RF #2

WING RF #2

Table 4: Signal Wiring Requirements

* Denotes lower case letter pins.

3.2 DRFM Pod Horn Antenna Universal Mounting Adapter. This adapter is required when changing out pod horn antennas for different DRFM bands. Drawing of the mounting adapter is located in Enclosure 2.

4. Internal Equipment. Internal equipment will be mounted in accordance with reference (k).

4.1 Large Area Tracking Range (LATR). LATR will be Government provided mission equipment and is a GPS-based tracking system with capacity to track exercise participants. It provides mission tracking, display, and debrief systems for Naval and Joint Armed Forces exercises. It must be secured to the aircraft and may be secured to aircraft floor using FAA approved straps as illustrated in Figure 5. Additional information is provided in Figure 4 and reference (d).

Equipment Dimensions Electronic unit L x W x H (inches) Weight (pounds) Cable Case, RW L x W x H (inches) Weight (pounds) Input Power RF Power Transportability

16.6 x 12.3 x 9.4

25.78 x 24.25 x 11.0 35.0 115 Volts Alternating Current (VAC), 400 Hz, single phase (<2 amperes) or 28 Volts Direct Current (VDC) (<7.5 amperes)

433.1 Megahertz (MHz) (100-150 watts from –100C to +300C) (70 watts minimum over all environmental conditions) All elements of the AIP-RW Resize are capable of transport by truck, rail, air, or sea without further special precautions.

Figure 4: LATR Characteristics

Figure 5: Example of a LATR secured to aircraft floor using FAA approved straps

4.2 Communication Relay Radios. The below radios will be Government provided mission equipment.

a. AN/URC-200 Line of Sight Transceiver. Two VHF/UHF radios will be required for Communications Relay missions. Radios will rack mounted in standard 19-inch rack. For URC-200 data/specs, see Operation and Maintenance Manual, reference (g). Rack will be provided by contractor.

b. AN/PRC-158 Multi-Channel Manpack Radio. Two PRC-158 radios will be required for Communications Relay missions. Radios will be rack mounted. PRC-158 specs sheet and antenna requirement can be found in reference (h). Rack will be provided by contractor. This instrument rack will be used for both URC-200 and PRC-158 radios interchangeably. Only one system is used at one time.

c. System for Navy Target Control (SNTC). The SNTC Airborne Relay is a 19-inch rack mountable unit with physical and electrical characteristics as listed in Table 7. During operation the Airborne Relay requires a +28 VDC and 20 A power source through connector J3 (Figure 6). The Airborne Relay consists of two separate Relay Transponders (Relay Transponder 1 and Relay Transponder 2). The front panel has two handles, a power switch and four rotary switches. The rear panel has a power connector and two Ultra High Frequency (UHF) N-type antenna connectors operating in the frequencies listed in Table 8. J1 is an N-type antenna connector which corresponds to Relay Transponder 2. J2 is an N-type antenna connector which corresponds to Relay Transponder 1. When using a single Airborne Relay, antennas shall have a minimum spacing of 10 feet to avoid damaging the relays. Two Airborne Relays require a minimum antenna spacing of 13 feet.

Table 7: Airborne Relay Physical and Electrical Characteristics

Figure 6: SNTC Power Connector J3 Pinout

Table 8: SNTC Frequency Settings

4.3 AN/APX-123 Common Transponder. The AN/APX-123 will be provided as GFP and will be mounted in the cabin of the aircraft. The APX-123 data sheet, reference (i), includes physical characteristics and power. Two D band antennas are required and will be installed on the upper and lower center line of the aircraft.

a. The aircraft will be provisioned to install APX-123 control head with the following dimensions: 5.25” height x 5.75” width x 3.00” depth in the cockpit.

b. The Contractor will provide aircraft Mode C altitude interface cable in accordance with (IAW) details in Table 9.

Aircraft Mode C Altitude Data Connector 201358-1 (M series) AMP Corp.

Socket M Socket N Socket P Socket R Socket S Socket T Socket U Socket V Socket W Socket X Mode C altitude bit D4 Mode C altitude bit A1 Mode C altitude bit A2 Mode C altitude bit A4 Mode C altitude bit B1 Mode C altitude bit B2 Mode C altitude bit B4 Mode C altitude bit C1 Mode C altitude bit C2 Mode C altitude bit C4

Table 9: Military IFF MODE C ALTITUDE Gilliam Code Connector

c. Aircraft IFF/TACAN/TCAS suppression bus interface cable will be provided by the contractor. This can be a BNC male connector on the end of a coaxial cable or a BNC female connector on an interior aircraft panel.

4.4 Ashtech GPS Data Collection Package. The Contractor will install a GFP Ashtech GPS data collection package. The data collection package must be located no further than 10 feet from the GPS 1X4 amplified splitter and must be mounted to enable access to the memory card.

a. GPS Antenna to be provided by contractor: AT2775-41W-TNCF-000-RG-42-NM (Aero Antenna) or equivalent w/RG-142 cable w/TNC(m) type coaxial connectors. The GPS antenna will be installed at the same location on all aircraft to avoid lever arm adjustments. The antenna will have the following characteristics:

1. Frequency: L1 – 1575 MHz (+/- 10 MHz) L2 – 1227 MHz (+/- 10 MHz)

2. Polarization: Right Hand Circular, Axial Ratio: 3 dB max at boresight

3. LNA: Gain – 42 dB, Noise Figure - 2.5 dB max, VSWR – less than 2.0:1 at L1 and L2, Band Rejection – 35 dB, and must operate on +9 VDC coaxial bias voltage.

b. GPS Antenna 1X4 Amplified Splitter System: The Contractor will install antenna 1X4 amplified splitter system.

c. GPS 1X4 Splitter: NALDCBS1X4-J1-J4DCB/10V/28WR (GPS Networking Inc.) or equivalent with the following characteristics:

1. GPS Signal ports – 4 ports are required; the connectors must be N type female and they must be DC blocked (200 ohm standard).

2. GPS Antenna port – 1 port is required; the connector must be N type female and the port must have a +9 VDC coaxial bias voltage.

3. Splitter Power – 28 VDC (1A) aircraft battery power must be applied to the splitter.

d. GPS 1X4 Splitter Power Connector w/28VDC power: MS3106A10SL-4P (Amphenol) or equivalent.

4.5 Two Dual Control Boxes (DCBs). Will be mounted in the cockpit of the aircraft. The C-12459/AL part number (P/N) 1611AS9600-4 DCB physical dimensions and power can be found in the ALQ-167 or AST-9 ICD in the link provided in Section 2. Wiring to the DCBs will be in accordance with Table 1, Pods Generic Wiring.

4.6 Safe. Required for both Electronic Attack (EA) and Stand-Off-Jammer (SOJ) missions, a GSA approved single-drawer security container (12.5” x 16” x 17”) will be installed in the cabin of the aircraft.

4.7 AN/USQ-113 Radio Countermeasures Set. This system will be provided for Standoff Jammer (SOJ) missions in a standard 19-inch GFP rack, approximately 50 inches tall (separate racks may be used if interconnecting wiring is modified to allow for increased separation between individual equipment). Power requirements and antennas information can be found in Figure 7. They system is comprised of one receive and two transmit antennas. The receive antenna must be mounted on the bottom of the aircraft. The two transmit antennas must be installed on the top of the aircraft with one forward and one aft. The receive and one of the transmit antennas will be 20-100 MHz and the second transmit antenna will be 100-500 MHz, with both capable of transmitting at least 400W of power. Cable harnesses will be provided as GFP. Wiring and functional diagram is provided in Figure 8. The equipment rack will be installed in accordance with reference (k).

ELECTRICAL CHARACTERISTICS

Power Input AEB Equipment Cockpit Equipment

115 VAC, 3 Phase, 400 Hz, 4900 Watts @ 115 VAC 28 VDC, 110 Watts @ 28 Vdc

PHYSICAL CHARACTERISTICS

Radio Countermeasures Set AN/USQ−113(V)3

Controller, Radio Countermeasures Set CD−149/USQ−113A(V) (System Controller Unit)

Converter, Block CV−4342/USQ−113A(V) (2 Ea.)

±0.125 in high

Set, Radio RT−1747B/ARC−210 (2 Ea.)

Mounting Base, Electrical Equipment MT−7154/USQ−113A(V)

±0.125 in high

Power Supply Assembly PP−8475/USQ−113A(V)

Input Protection Module (IPM)

Transmit Attenuator (TA)

Figure 7: AN/USQ-113(V) Technical Characteristics

PHYSICAL CHARACTERISTICS (cont)

AM−7433/USQ−113(V) Radio Frequency Amplifier

Control, Radio−Countermeasures Set C−12577/ USQ−113A(V) (Improved Operator Control Panel)

MT−6803/USQ−113(V)

AS−3767/ARC−182(V) Antenna

AN/313A Antenna

Laptop

CP−2620/A EBoard

ENVIRONMENTAL CHARACTERISTICS

Temperature Operating

−20C to 50C.

Altitude AEB Equipment Cockpit Equipment

Sea Level to 25,000 feet Sea Level to 10,000 feet

NOTE:

The figures listed above are test specification limits.

Figure 7a: AN/USQ-113(V) Technical Characteristics (CONT)

Figure 8: AN/USQ-113(V) Functional Diagram

Figure 8a: AN/USQ-113(V) Functional Diagram (CONT)

Figure 8b: AN/USQ-113(V) Functional Diagram (CONT)

Figure 8c: AN/USQ-113(V) Functional Diagram (CONT)

4.8 Digital Radio Frequency Memory (DRFM). DRFM jammers will be Government provided mission equipment and are multi-channel airborne radar jamming systems. The systems tie into the aircraft signal receiver antennas and transmitters. In operation, DRFM receives incoming radar signals and then develops and sends jamming waveforms to the transmitters. These systems, as shown in reference (j), consist of four independent Technique Generators (TG). These TGs generate jamming signals for the following radar bands: C/D, E/F/G and I/J. Below are simplified DRFM system block diagrams (Figures 10 and 12) for the SOJ and EA platform. For the SOJ missions, a mission computer which has a DRFM GUI software package to control individual TGs. This capability is not required for the EA platform currently. The green components in the Simplified Block Diagrams indicate that it will be Government provided mission equipment while the blue components indicate CFE.

a. SOJ Mission DRFM Configuration. Figure 9 provides the RF handling requirements to support Government provided DRFMs. Figure 10 provides a simple nominal configuration for reference.

Figure 9: DRFM RF Handling Capabilities for SOJ Missions

Pwr Amplifier Tx Antenna System

2 total 3 total Mission Computer I/J band Rx antenna E/F/G band Rx antenna C/D band Rx antenna B band Rx antenna Receiver System (ADF) C/D band DRFM TG 2 I/J band DRFM TG 3 E/F/G band DRFM TG B band DRFM TG

4 LNAs total (if required)

Figure 10: Simplified Nominal SOJ DRFM system Block Diagram

1. MCDRFM: Design and interface details of the MCDRFM are provided in reference (h).

2. MAXDRFM: The MAXDRFM box physical characteristics and power requirement are provided in Enclosure 1.

b. EA Mission DRFM Configuration. Figure 11 provides the RF handling requirements to support Government provided DRFMs. Figure 12 provides a simple nominal configuration for reference.

Figure 11: DRFM RF Handling Capabilities for EA Missions

Rx antenna LNA (if required) Pwr Amp Tx antennaB, C, E/F/G or I/J Band Technique Generator

E/F/G Band Technique Generator

Zombie Pod

Figure 12: Simplified Nominal EA DRFM Block Diagram

Note that there could be two DRFM bands being operated simultaneously. A Zombie pod is used to mount receive and/or transmit antennas instead of mounting them on aircraft fuselage. This is done to provide better antenna isolation.

DRFMs will be installed on the EA platform. The MAXDRFM box physical characteristics and power requirement are provided in Enclosure 1.

4.9 Instrument Racks

a. For EA missions, instrument racks (22 inches wide by 24 inches deep by 38 inches high) will be provided as GFP. SNTC relay instrument rack will be provided by the contractor. All racks will be installed in accordance with reference (k). A drawing of the EA instrument rack will be provided as GFI.

b. For SOJ missions, instrument racks will be provided by the contractor except for the USQ-113 rack and the DRFM rack which are depicted in paragraphs 4.7 and 4.8 accordingly. All racks will be installed in accordance with reference (k).

Attachment 2 - HEEWJ Capability IRD v2.0 N00421-18-R-0009

UNCLASSIFIED//FOR OFFICIAL USE ONLY

UNCLASSIFIED//FOR OFFICIAL USE ONLY

Enclosure 1 NRL MAXDRFM Dimensions and Weights

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