Att 2_Interface Reference Document.docx

UNCLASSIFIED//FOR OFFICIAL USE ONLY

Interface Reference Document (IRD) (Electronic Attack (EA)/ Target Banner Tow (TBT) Capabilities) In support of Solicitation N00421-24-R-0003 (Attachment 2)

NAVAIR PMA-226 Contracted Air Services 6 June 2023

Distribution Statement C: Distribution authorized to U.S. Government agencies and their contractors, Critical Technology 6 June 2023. Other requests for this document shall be referred to NAVAIRSYSCOM, 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 is Government Furnished Information (GFI) required to support EA/TBT aircraft capability. Equipment not identified as Government managed equipment will be provided by the contractor.

1.2 Purpose. This document is provided to aid the contractor’s understanding of the electrical power requirements, electrical signal requirements and mechanical interface requirements that pertain to the equipment the Government is providing for integration into the contractor’s aircraft. The interfaces described are required in order for the Government’s equipment to operate within their specification tolerances and to achieve their expected in-flight performance. Mention, in some sections, of contractor supplied equipment is not intended to recommend or restrict the use of any particular vendor’s hardware – only to note the mechanical and electrical characteristics of the Government’s equipment. Additionally, the Government provided equipment, listed herein, is currently approved for use on the National ranges and their features and limitations are well understood.

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) TCTS/P5CTS Interface Control Document

(e) LAU-7/ NAVAIR 11-75A-54 (Organizational and Intermediate Level Maintenance with Illustrated Parts Breakdown Aircraft Guided Missile Launcher)

(f) ADU-299 NAVAIR 11-75A-59 (Intermediate Level Maintenance With Illustrated Parts Breakdown Adapter Assembly)

(g) FAA Order 8300.16A w/ CHG 1, 11 December 2018

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

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

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

(k) AN/APX-123/A(V) Common Transponder Instrument Racks drawing for EA missions NOTE: References (e) and (f) above will be provided upon contract award.

2.2 Enclosures

(1) DRFM Pod Horn (skin mount) Antenna dimensions

3. Externally Mounted Equipment. The following pods are Government managed mission equipment and will be installed and operated on EA platforms (The design, fabrication and installation of the associated support structure, such as fairings, pylons and or bomb racks, required to carry the systems identified in this paragraph shall be provided by the contractor):

a. ALQ-167

b. ALQ-188 AST-6

c. AST-9

d. ALE-43

e. TCTS) /P5CTS

f. LAU-7

g. ADU-299

h. DRFM Horn (skin mount) antenna. The DRFM Pod Horn (skin mount) antenna dimensions are provided in Enclosure 2. An adapter must be provided by the contractor to mount the antenna to the aircraft.

3.1 External Equipment Power and Control. The pods listed in paragraph 3 require 115V 400Hz 3-phase and 28V DC power along with wiring for controls and signals. Pigtails for ALE-43 pod/DCB/ALQ-167/AST-6/9, and TCTS/P5CTS are Government managed mission equipment.

The external power wiring requirements to the wing pylons are provided in Table 1. The wing hardpoint connector must be located within 18-inches of the pylon’s aft lug to simplify securing the pigtail to the airframe.

Table 1 External Power Wiring

(MS3474L16-8S or approved equal) Signal Description

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 lists the connections within the two special Mission Power Outlets. The outlets provide power to the mission equipment and should be located near the interior fuselage equipment rack.

Table 2 Special Missions Power Outlets

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 lists the signal wiring requirements for each wing. The cable assembly begins with a connector within the interior equipment area of the fuselage and ends at a connector near each wing pylon. The wing hardpoint connector should be located within 18-inches of the pylon’s aft lug to simplify securing the pigtail to the airframe. Both the left and right wing pylon require their own hardpoint connector with power and signal paths to the mission equipment.

Table 3 Signal Wiring Requirements

CABIN INTERIOR CONNECTOR

(P/N: MS3124F22-55S or approved equal)

TYPICAL WIRE TYPE/SPECIFICATION

WING HARDPOINT CONNECTOR

(P/N: MS3474L22-55S or approved equal)

Z*

P

CABIN RF #1

WING RF #1

CABIN RF #2

WING RF #2

* Denotes lower case letter pins.

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

4.1 Large Area Tracking Range Shipboard and Rotary Wing Technology Upgrade (LSRTU) is a Government provided GPS-based tracking system. Its characteristics are listed in Table 4 and in reference (h). It provides range tracking for aircraft participating in Naval and Joint Armed Forces exercises. It must be secured to the aircraft via an approved mounting method. Past efforts have secured the LSRTU equipment to the aircraft floor as pictured in Figure 3 using CGU-1/B cargo straps (or TSO approved cargo straps).

Table 4 LSRTU Characteristics

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 11.0 115 VAC 400 Hz single-phase (<2 amperes) or 28 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 3: Example of a LSRTU secured to aircraft floor using CGU-1/B cargo straps

4.2 Communication Relay Radios

a. AN/URC-200 Line of Sight Transceiver

b. AN/PRC-158 Multi-Channel Manpack Radio. To support encrypted communications relay, the contractor must have keymat handling procedures in place.

Note The aircraft must be configured to carry two URC-200 or up to two PRC-158 radios. To support these radios four total antennas are required, two mounted on the upper fuselage and two mounted on the lower fuselage of the aircraft.

c. Navy Common Data Link Model 600 RL (NCDL) is the new system that replaces the System for Navy Target Control (SNTC).

4.3 AN/APX-123 Common Transponder. The AN/APX-123 will be provided as GFP and will be mounted in the GME equipment rack in the aircraft. 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 an APX-123 control head that will be accessible and viewable by the aircrew in-flight. The control head’s dimensions are 5.25” high x 5.75” wide and 3.00” deep (excluding backshell connectors). A round access hole measuring a minimum of 1.5 inches will be provided for control head cable routing from the GME equipment rack.

b. The Contractor will provide aircraft Mode C altitude interface cable in accordance with (IAW) details in Table 5.

Table 5 Military IFF MODE C ALTITUDE Gillham Code Connector

Aircraft Mode C Altitude Data Connector 201358-1 (M series) AMP Corp. (or approved equal) 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 8: Military IFF MODE C ALTITUDE Gillham Code Connector

c. Aircraft IFF/TACAN/TCAS suppression bus interface will be provided by the contractor terminating in a BNC connection.

a. A top mounted GPS antenna to be provided by contractor: AT2775-41W-TNCF-000-RG-42-NM (Aero Antenna) or equivalent and connected to the GPS signal splitter defined below with RG-142 cable. The GPS antenna will be installed at the same location on all aircraft to avoid aircraft-unique lever arm corrections.

b. The Contractor will install a GPS antenna 1X4 amplified splitter system NALDCBS1X4-J1-J4DCB/10V/28WR (GPS Networking Inc.) or equivalent. The splitter will be mounted in the rear of the aircraft in such a place as to be easily accessible for connection to equipment mounted in the GME equipment racks.

d. Two Dual Control Boxes (DCBs). GME provided DCBs shall be mounted in the cockpit of the aircraft. The C-12459/AL part number (P/N) 1611AS9600-4 DCB physical dimensions can be found in the ALQ-167 or AST-9 ICD in the link provided in Section 2. A round access hole measuring a minimum of 1.5 inches will be provided for control head cable routing from the cabin wing hardpoint connection.

EA Technique Generators. All EA Technique Generators will be Government managed mission equipment to be installed in the GME equipment racks. These technique generators will require four (4) DRFM antenna mounting positions on the aircraft. These will be positioned fore and aft, top and bottom on the fuselage.

4.4 Instrument Racks

a. For EA missions, 19-inch module instrument racks (external dimensions 22 inches wide by 24 inches deep by 38 inches high) will be provided as GME. All racks will be installed in accordance with reference (g). A drawing of the EA instrument rack will be provided as GFI.

DRFM Pod Horn (skin mount) Antenna Dimensions

ALQ-167 Antenna Mounting Arm (excerpt from NAVAIRSYSCOM Drawing Number 1356AS1131) image1.png image2.png image3.emf