CAP Design SOW - Working.docx

ATTACHMENT 1

STATEMENT OF WORK (SOW) FOR THE

CESSNA DATA LINK SUBSYSTEM DESIGN

HEADQUATERS AIR COMBAT COMMAND TEST AND TRAINING DIVISION (ACC/A5T) LANGLEY AFB, VA

25 July 2023

Document Version #: CESSNA-DLS-DESIGN (06JUNE2023)

Controlled by: ACC/A5T Controlled by: ACC/A5T CUI Category(ies): Source Selection Distribution: F: Further dissemination only as directed by ACC/A5T, 6Jun2023 or higher DoD authority POC: TSgt Clifford Lahr, clifford.roberts.1@us.af.mil

DESTRUCTION NOTICE: Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

CUI

ii

Contents

1. PURPOSE

The purpose of this acquisition is to develop designs installing a government provided Data Link Subsystem (DLS). This DLS will be used for Air Force operations involving live fire munition testing IAW Title 10 USC.

1.1. BACKGROUND

In order to maintain mission operability for the 53d Weapon Evaluation Group (WEG), Air Combat Command (ACC) is seeking the capability of installing a DLS onto a Civil Air Patrol Cessna aircraft. The primary focus of this mission/subsystem is to receive and retransmit (i.e. airborne relay aircraft) drone command & telemetry data between the control facility and unmanned target, to support weapon systems being tested by the Air Force and Navy.

The Air Force is the leading test organization for full-scale aerial targets (QF-16) for the DoD with a strong presence in the sub-scale aerial target (BQM-167/AFSAT) as well. Mission testing occurs at Tyndall AFB, FL with the 53d WEG to generate sorties for operational testing events. These testing events are broken into three tier categories. Tier I involves Acquisitions Category (ACAT) 1 programs with Office of Secretary Defense oversight. Tier II priority includes Major Command (MAJCOM) Developmental/Operational Testing (DT/OT). Lastly, Tier III priority is for Weapon System Evaluation Program (WSEP). Upon completion of this delivery order, the designs will be given to Civil Air Patrol in order to begin installation of the system.

1.2. SCOPE

The scope of this contract is to develop the designs and instructions on how to mount the DLS & antenna, connect to aircraft +28v power, and route the RF coax, onto a Cessna without damaging the functionality of the aircraft.. This design package is to include the electrical and mechanical aspects involved for achieving this objective. Additionally, the Contractor shall include recommended techniques to remove the DLS and return the aircraft to as close to the pre-installation status as possible. Upon delivery of these designs, it will be officially considered Government property.

The Contractor shall begin this process by first inspecting the aircraft and documenting its current state. They should annotate deficiencies that will effect the design of the aircraft and immediately notify the Government contracting officer it they believe they would be unable to properly integrate the DLS system into the Cessna. (CDRL A001, A002, A008)

2. APPLICABLE DOCUMENTS

2.1. GOVERNMENT DOCUMENTS

2.1.1. SPECIFICATIONS, STANDARDS, AND HANDBOOKS

The following specifications, standards, and handbooks, of the exact revision listed below, form a part of this document to the extent specified herein.

(Copies of above document is available at: https://www.cnss.gov)

2.1.2. OTHER GOVERNMENT DOCUMENTS, DRAWINGS, AND PUBLICATIONS.

The following other Government documents, drawings, and publications, of the exact revision level shown, form a part of this document to the extent specified herein.

(Copies of above document is available at: https://www.cnss.gov)

DLS REQUIREMENTS

3.

3.1. OPERATING CONDITIONS

Temperature & Altitude – The DLS is designed to operate at -54 degrees Celsius through +55 degrees Celsius and from 0 to 50,000 feet.

Humidity – The DLS operated continually with 95% humidity, including conditions where condensation takes place in and on the equipment.

Sinusoidal Vibration – The DLS is designed to operate continuously over the vibrational environment specified in MIK-STD-810C 814.2, curve AR (5-33 Hz), and (H 33-2000Hz). Also, MIL-STD-810C method 514.2 Curve Y and W.

Acceleration & Shock – The DLS is designed to withstand the continuous acceleration test as described by MIL-STD-810C. The unit is designed to survive a 30G shock.

Electromagnetic Compatibility – The DLS meets the requirements of MIL-STD-461B, Category A1b. This is relevant since the DLS is often collocated with multiple emitter types.

Warm-Up Time – The warm-up time is less than or equal to five minutes for any combination of performance or environment.

Explosive Atmosphere – The equipment does not cause ignition of an ambient, explosive, gaseous mixture with air when operating in such an atmosphere.

3.2. POWER AND PHYSICAL CHARACTERISTICS

Physical Dimensions

· Total Height – 7.375”

· Total Width (at base) – 10.625”

· Total Depth (including fan unit) – 18.625”

· Approximate Weight – 60 lbs

*Note* The picture illustrates a 400 CPS 120vAC fan. This is not a requirement and a 28v fan will suffice

Power Requirements

DLS Input Voltage: 28(+2, -4) Volts DC from a power source capable of 8 amps or greater. Actual current draw depends on mission role. This DLS operates on a separate 15-amp circuit. The below picture illustrates the schematic of the current DLS’s +28v power connector.

Supply Voltage Cannon Plug: Part number MS27473E16B63 (NSN 5935-00-333-1532)

Cooling Fan: A minimum of +28v fan will be needed to cool the DLS. The DLS technical data package illustrates a 400 Hz, 115 Volts AC cooling fan. The subsystem can accept up to this level of cooling but is not required. (CDRL A001, A004)

3.3. ANTENNA REQUIREMENTS

Antenna connection require to DLS RF Connector: TNC male to mate with DLS Units TNC female (an adapter can be used to allow connection from other connector types such as “N” type) (CDRL A001, A004)

Antenna Type: Antenna Type: 1 or 2 element stack dipole, UB Corp part number: AODV910 (1-element), AODV-xxx (2-element). (CDRL A007)

3.4. POWER TRANSMISSION LINE

A single high power transmission line is required between the DLS and the antenna. The total insertion loss for this high power transmission line shall not exceed 1.5 dB per 100 ft.

3.5. DLS MOUNTING REQUIREMENTS

Typically the DLS unit is mounted on a shock-mount tray, or can be placed on a shelf if hard mounting. (CDRL A001)

ACRONYMS AND DEFINITIONS

The Contractor shall limit the use of acronyms to commonly utilized sayings within the Air Force and testing. If questions are had as to what a particular acronym stands for, the Contractor shall immediately ask the Government in order to ensure full understanding.

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