CFIT-P SRD T-6A_B 13MAR2020.pdf

SYSTEM REQUIREMENTS DOCUMENT

Controlled Flight Into Terrain – Prevention

(CFIT-P) Capability for the T-6A/B/D

13 March 2020 Revision DRAFT

Joint Primary Aircraft Training System (JPATS)

Tinker AFB, Oklahoma

Prepared by:

JPATS Avionics Integrated Product Team

Tinker AFB, Oklahoma

DISCLOSURE NOTICE - This information is furnished upon the condition that it will not be released to another nation without the specific authority of the Department of the Air Force of the United States, that it will be used for military purposes only, that individual or corporate rights originating in the information, whether patented or not, will be respected, that the recipient will report promptly to the United States, any known or suspected compromise, and that the information will be provided substantially the same degree of security afforded it by the Department of Defense of the United States. Also, regardless of any other markings on the document, it will not be downgraded or declassified without written approval of the originating United States agency.

DISTRIBUTION STATEMENT C - Distribution authorized to U.S. Government agencies and their contractors (Administrative or Operational Use) (13 Mar 2020). Other requests for this document shall be referred to AFLCMC/WLZJ, Tinker AFB, OK 73145.

Questions concerning content shall be referred to AFLCMC/WLZJ, Tinker AFB, OK 73145.

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CHANGE HISTORY

Change Version Date

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CONTENTS

1 SCOPE/INTRODUCTION

SYSTEM IDENTIFICATION

SYSTEM OVERVIEW

DOCUMENT OVERVIEW

ERRORS AND OMISSIONS

2 APPLICABLE DOCUMENTS

GENERAL

GOVERNMENT DOCUMENTATION

2.2.1 Government Specifications, Standards, and Handbooks

2.2.2 Other Government Documents, Drawings, and Publications

NON-GOVERNMENT DOCUMENTS

ORDER OF PRECEDENCE

3 SYSTEM/SUBSYSTEM REQUIREMENTS

REQUIRED STATES AND MODES

3.1.1 Powered Off State

3.1.2 Initialization State

3.1.3 Operational State

3.1.4 Maintenance State

3.1.4 Power Down State

SYSTEM FUNCTIONAL REQUIREMENTS

3.2.1 CFIT protection capability description

3.2.2 Pilot Vehicle Interface (PVI) capabilities description

3.2.3 Maintainability capabilities description

3.2.4 Database Download Requirements

3.2.5 Aural Requirements

3.2.6 Visual Requirements

SYSTEM PHYSICAL REQUIREMENTS

3.3.5 Power Requirements

3.3.6 Physical Dimensions

3.3.7 Environmental Requirements

3.3.8 Reliability Requirements

3.3.9 Computing Requirements

3.3.10 Component Obsolescence Requirements

3.3.12 Wire Harness New and Modification Requirements

SYSTEM EXTERNAL INTERFACE REQUIREMENTS

3.4.1 Interface Identification and Diagrams

3.4.2 Power Bus Interface

3.4.3 ADC Data Bus

3.4.4 IRU Data Bus

3.4.5 GPS Data Bus

3.4.6 RA Data Bus

3.4.7 Audio Output

3.4.8 Discrete Outputs Signal Interface

SYSTEM INTERNAL INTERFACE REQUIREMENTS

3.5.1 Interface Identification and Diagrams

3.5.2 TAWS Unit

3.5.2 TAWS Indicator Panel – Test

3.5.3 TAWS Indicator Panel – Terrain Inhibit

3.5.4 TAWS Indicator Panel – TAWS Warning

3.5.5 Media Device

3.5.6 Aural Alert Accommodations

ADAPTION REQUIREMENTS

SAFETY REQUIREMENTS

3.8.1 System Safety/Failure Requirements

3.8.2 Occupational Health and Safety Requirements

3.8.3 Prohibited Hazardous Materials

3.8.4 Fasteners

3.8.5 Toxicity

3.8.6 Security and Privacy Requirements

HUMAN FACTORS REQUIREMENTS

SYSTEM ENVIRONMENT REQUIREMENTS

3.10.1 Electromagnetic Compatibility

3.10.2 Electromagnetic Interference

3.10.3 Grounding and Bonding

3.10.4 Natural Environments

COMPUTER RESOURCE REQUIREMENTS

3.11.1 Computer Hardware Requirements

3.11.2 Computer Hardware Resource Utilization Requirements

3.11.3 Computer Software Requirements

SYSTEM QUALITY FACTORS

3.12.1 Maintainability

3.12.2 Usability

3.12.3 Design and Construction Constraints

3.12.4 Parts Marking

PERSONNEL RELATED REQUIREMENTS

3.13.1 System Status/Failure Annunciation

3.13.2 Human Performance

REGULATORY AND CERTIFICATION REQUIREMENTS

4 VERIFICATION PROVISIONS

VERIFICATION METHODS

4.1.1 Demonstration

4.1.2 Test

4.1.3 Analysis

4.1.4 Inspection

5 APPENDICES

APPENDIX A: ACRONYMS AND DEFINITIONS

APPENDIX B: TEST AND VERIFICATION MATRIX

TABLES

Table 1 External Interfaces Table 2 Internal Interfaces Table 3 Prohibited Hazardous Materials

FIGURES

Figure 1 CFIT-P System ................................................................ Error! Bookmark not defined.

Figure 2 CFIT-P External Interface Diagram (T-6A) Figure 3 CFIT-P External Interface Diagram (T-6B) Figure 4 CFIT-P System Internal Interface Diagram

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1 SCOPE/INTRODUCTION

System Identification This System Requirements Document (SRD) pertains to the T-6A, T-6B, and T-6D Texan II aircraft utilized by the US Navy.

System Overview The T-6 is a single engine two-seat primary trainer designed to train student pilots and navigators in basic skills common to Air Force and Naval aviation. Produced by Textron Aviation Defense, LLC (TAD), the T-6 is a military trainer that replaced the T-37B and is replacing the T-34C trainer aircraft.

In order to comply with Chief of Naval Operations letter 13210.1B dated 15 April 2014, the current T-6A/B/D Avionics capability requires an upgrade to include prevention of controlled flight into terrain. This modification will provide the aircraft with a Terrain Avoidance and Warning System that will meet the minimum TSO-C151c requirements for TAWS Class C system, with goal to meet TSO-C151c requirements for TAWS Class B system. The capability will support meeting SECDEF aircraft mishap reduction goals (ref. SECDEF memo of 22 June 06, Reducing Preventable Accidents) and preserving combat capability.

All CFIT-P technical solutions must comply with the aircraft’s existing Prime Item Product Functional Specification (PIPFS) or deviations from the PIPFS must be approved by the United States Government (USG). These systems and any other modifications to the aircraft to support the requirements in this SRD will hereafter be referred to as “the installed system.”

Document Overview This SRD establishes the functional, performance and verification requirements for upgrading the T-6A and T-6B/D aircraft to comply with the OPNAV 13210.1B letter, AFI 63-101/20-101, and SECDEF memo requirement for a Controlled Flight into Terrain Prevention (CFIT-P) system.

Errors and Omissions Every attempt has been made to ensure the information contained herein is valid at the time of publication. The USG reserves the right to make changes, corrections, and/or improvements at any time and without notice. In addition, the USG disclaims any and all liability for damages incurred directly or indirectly as a result of errors, omissions, or discrepancies.

2 APPLICABLE DOCUMENTS

General Documents listed in this section are specified in sections 3, 4, or 5 of this SRD. This section does not include documents cited in other sections of this specification or recommended for additional information, or as examples. While every effort has been made to ensure the completeness of this list, contractors are cautioned that they shall meet all specified requirements of documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

Government Documentation

2.2.1 Government Specifications, Standards, and Handbooks

The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the current issue/version of these documents is to be used for this solicitation and/or contract.

DOCUMENT ID TITLE

BS24806 JPATS Prime Item Product Function Specification (PIPFS), Rev I

MIL-STD-810G Department Of Defense Test Method Standard: Environmental Engineering Considerations And Laboratory Tests

MIL-STD-882E Department of Defense Standard Practice – System Safety

MIL-STD 1472G Department of Defense Design Criteria Standard – Human Engineering

MIL-DTL-81381C Detail Specification, Wire, Electric, Polyimide-Insulated, Copper Or Copper Alloy

MIL-HDBK-217F Department of Defense Handbook – Reliability Prediction of Electronic Equipment

MIL-HDBK-454B Department of Defense Handbook – General Guidelines for Electronic Equipment

MIL-HDBK 516C Department of Defense Handbook - Airworthiness Certification Criteria

2.2.2 Other Government Documents, Drawings, and Publications

The following Government documents, drawings, and publications form a part of this SRD to the extent specified herein. Unless otherwise specified, the current issue/version of these documents is to be used for this solicitation and/or contract.

DOCUMENT ID TITLE

Code of Federal Regulations (CFR), Title 14, FAA Part 21

Certification Procedures for Products and Parts

Code of Federal Regulations (CFR), Title 14, FAA Part 23

Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes

Code of Federal Regulations (CFR), Title 14, FAA Part 45

Identification and Registration Marking

Code of Federal Regulations (CFR), Title 14, FAA Part 91

General Operating and Flight Rules

Federal Aviation Administration (FAA), Advisory Circular 23-18

Installation of Terrain Awareness and Date: 6/14/00 AC No:

23-18 Warning System (TAWS) Approved Initiated By: ACE- 100 Change: for Part 23 Airplanes

Federal Aviation Administration (FAA), TSO-C151c

Terrain Awareness and Warning System

Air Force Instruction (AFI) 62-601

USAF Airworthiness

Air Force Instruction (AFI) 63-101/20-101

Integrated Life Cycle Management

Air Force Handbook (AFH) 63-1402

Aircraft Information Program

Air Force Instruction (AFI) 91-203

Air Force Consolidated Occupational Safety Instruction

Occupational Safety & Health Administration (OSHA) Standard 29 Code of Federal Regulations (CFR) 1910

Occupational Safety and Health Standards

Department of Defense Directive (DoDD) 8500.2

Information Assurance (IA) Implementation

Department of Defense Instruction (DoDI) 8500.1

Information Assurance

TO 01-1A-14 Installation And Repair Practices Volume 1 Aircraft Electric And Electronic Wiring

Non-Government Documents The following non-Government documents, drawings, and specifications form a part of this SRD for reference herein. Applications for copies should be addressed to the originator of each subject document. Unless otherwise specified, the current issue/version of these documents is to be used for this solicitation and/or contract.

DOCUMENT ID TITLE

American Society of Mechanical Engineers (ASME) Standard Y14.38M

Abbreviations and Acronyms for Use on Drawings and Related Documents 2013

American National Standards Institute (ANSI)/Electronic Industries Association (EIA) Standard 632

Processes for Engineering a System

ANSI/Government Electronics Information Technology Association (ANSI/GEIA) Standard 0009

Reliability Program Standard for Systems Design, Development, and Manufacturing

ARINC Specification 404A Air Transport Equipment Cases And Racking

ARINC Specification 404B-2 Connectors, Rack AND Panel, Rectangular Rear Release Crimp Contacts

ARINC Specification 429P1-18

Digital Information Transfer System (DITS) Part 1 Functional Description, Electrical Interfaces, Label Assignments And Word Formats

ARINC Specification

429 PART 2-16

Mark 33 Digital Information Transfer System (DITS) Part 2 Discrete Word Data Standards

ARINC Specification 429P3-19

Mark 33 Digital Information Transfer System (DITS) – Part 3 - File Data Transfer Techniques

ARINC Specification 429P4

Digital Information Transfer System (DITS) Part 4 Archive Of ARINC 429 Supplements

Institute of Electrical and Electronics Engineers (IEEE) Standard 802.3-2018

IEEE Standard for Ethernet

International Organization for Standards (ISO)/American Society of Quality (ASQ) ANSI/ISO/ASQ Standard 9001-

Quality Management Systems and Requirements

National Institute of Standards and Technology (NIST) Special Publication (SP) 800-60 Vol 2 Rev 1, D.11.3

Air Transportation and Information Type

NIST SP 800-30 Rev 1 Guide for Conducting Risk Assessments

NIST SP 800-53 Rev 4, Appendix E (Table E-1)

SAE International Standard

AS5553

Counterfeit Electronic Parts; Avoidance, Detection, Mitigation, and Disposition

Society of Allied Weight Engineers (SAWE) RP7

Mass Properties Management and Control for Military Aircraft, Revision D

SAE Aerospace Recommended Practices 4761

Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment

RTCA DO-160G Environmental Conditions for Test Procedures for Airborne Equipment

RTCA DO-161A

RTCA DO-178B Software Considerations in Airborne Systems and Equipment Certification

RTCA DO-254 Design Assurance Guidance for Airborne Electronic Hardware

American Society for Testing and Materials (ASTM) D3951-10

Standard Practice for Commercial Packaging

Order of Precedence Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3 SYSTEM/SUBSYSTEM REQUIREMENTS

The installed system’s certification basis shall be in accordance with (IAW) AFI 62-601 USAF Airworthiness and AFI 63-101/20-101 Integrated Life Cycle Management. The CFIT-P system itself shall meet the minimum TSO-C151c requirements for TAWS Class C system, with objective to meet TSO-C151c requirements for TAWS Class B system. All equipment utilized to support the CFIT-P effort shall have an FAA Technical Standard Order Authorization (TSOA) for the intended function if required to obtain a Supplemental Type Certification (STC). The installed system shall not degrade the operation of other systems on the aircraft.

A controlled flight into terrain avoidance capability enhances situational awareness (SA) by providing cues and warnings to prevent an airworthy aircraft, under the control of a pilot, from being flown into terrain (i.e., land, water, or obstacles). Controlled flight into terrain avoidance systems mitigate loss of SA by combining sensor information with aircraft position, velocity vectors, and local terrain topography (when available) to predict future flight-path conflicts.

These systems then give appropriate direction to the aircrew on how to best avoid the impending impact. Controlled flight into terrain results from a loss of aircrew SA generally caused by factors such as degraded visual environment, spatial disorientation, task overload, or fatigue.

Degraded visual environment is defined as the presence of obscurants (e.g., fog, dust, blowing sand, heavy rain, etc.) and/or low light conditions that reduce aircrew visibility to the point where SA is lost and aircraft control cannot be maintained as it is in visual meteorological conditions.

T-6A/B/D accommodates a pilot instructor and a pilot student. Pilot in Command may be either as directed by instructor.

Required States and Modes The CFIT-P System shall have the following minimum required states:

• Powered-Off State

• Initialization State

• Operational State

• Maintenance State

• Power down state

3.1.1 Powered Off State

The CFIT-P System is not receiving power through the Power Bus Interface. In this state, the CFIT-P System components can be physically removed/disconnected.

3.1.2 Initialization State

The CFIT-P System shall transition from the Powered Off State when power is received through the Power Bus Interface to the Initialization State. A Built In Test (BIT) shall be performed and the results shall be stored in Protected Memory. The CFIT-P System shall continuously indicate the status of the BIT. The CFIT-P System shall determine the Aircraft Model and configure the CFIT-P system based on the configuration file(s).

3.1.3 Operational State

The CFIT-P System shall transition from the Initialization State upon successful BIT and configuration of the CFIT-P System.

3.1.4 Maintenance State

The CFIT-P System shall transition to the Maintenance State when the Flight Line Computing Device is connected to the Maintenance Download/Configuration Interface and power is received through the Power Bus Interface.

3.1.5 Power Down State

The CFIT-P System shall transition to the Power Down State when power transitions from on to off/failure through the Power Bus Interface. If the power failure condition exists for more than 200 milliseconds, a graceful power down sequence will be performed and the CFIT-P System will transition to the Powered Off State. If the power is recovered after 200 milliseconds, the CFIT-P System will transition to the Operational State.

System Functional Requirements The installed system will provide three main functions; Forward-Looking Terrain Avoidance (FLTA), Premature Decent Alert (PDA) and Ground Proximity Warning. The CFIT-P system shall meet/exceed the requirements of TSO-C151c for TAWS Class C. The CFIT-P system is intended to meet the objectives in this section.

3.2.1 CFIT protection capability description

Use real-time aircraft data such as altitude, position, velocities and accelerations in all axes.

Recognize an impending collision with terrain.

Provide a warning early enough to allow the pilot to safely avoid impact.

Operate over water, level and descending terrain.

Provide protection under all weather and illumination conditions.

Provide protection throughout the entire flight regime during all normal aircraft maneuvers, to include takeoff and landing.

Additionally, forward looking protection to account for varying/rising terrain should be considered.

3.2.2 Pilot Vehicle Interface (PVI) capabilities description

3.2.2.1 Provide aural, visual, and/or tactile signal warnings.

3.2.2.2 Be audible and intelligible over all other cockpit communications and ambient noise.

3.2.2.3 Convey a sense of urgency and be easily understood by the pilot.

3.2.2.4 Voice warnings shall have the highest priority over other queued voice warnings and tones.

3.2.2.5 Persist for entire duration of the warning condition.

3.2.2.6 Require no inputs from the pilot or additional crew members for normal operation.

Be capable of pilot initiated suppression of cueing, with default to "ON" at power-up.

3.2.2.8 Provide system output data to the Crash Survivable Recording (CSR) System even when pilot cueing is suppressed.

3.2.2.9 Minimize nuisance warnings.

3.2.2.10 The system should also be directive in nature and provide appropriate actions to take for the given situation.

3.2.3 Maintainability capabilities description

3.2.3.1 A Built in test (BIT) check of all major circuits and program operations. The BIT shall be initiated by applying power to the CFIT-P computing or through the Maintenance Download/Configuration Interface by the Flight Line Computing Device. BIT results shall be stored in the Protected Memory. The CFIT-P computing shall indicate the result of the most current BIT for display in STS/BIT page.

3.2.3.2 Monitoring and detection of events. The CFIT-P system shall communicate events to the Crash Survivable Recorder (CSR) system.

3.2.3.3 The CFIT-P system shall be configurable via the Maintenance Interface.

3.2.3.4 During power-up of the CFIT-P System, the CFIT-P computing shall determine the

Aircraft Model it resides in via the System External Interface and configure the CFIT-P System for that Aircraft Model as specified in the CSR configuration file(s).

3.2.4 Database Download Requirements

The CFIT-P System shall utilize a regularly updated terrain database.

3.2.5 Aural Requirements

The CFIT-P System shall provide aural alerts to both forward and aft cockpit pilots for Forward- Looking Terrain Avoidance (FLTA), Premature Decent Alert (PDA) and Ground Proximity Warning.

3.2.6 Visual Requirements

The CFIT-P System shall provide a visual alert for Terrain Avoidance.

System Physical Requirements All CFIT-P physical specifications will be agreed upon and validated.

3.3.5 Power Requirements

The CFIT-P System shall be powered by the Aircraft Avionics Bus Power (+28 ± 4.0 VDC, 40W Max.). The CFIT-P System Installation shall include modifications to circuit breaker panel and wiring as determined by aircraft OEM.

3.3.6 Physical Dimensions

The CFIT-P components shall conform to space, accessibility, and Center of Gravity constraints of T-6A and T-6B/D.

3.3.7 Environmental Requirements

The CFIT-P hardware shall meet or exceed RTCA/DO-160G Category C2 requirements.

3.3.8 Reliability Requirements

The CFIT-P hardware shall meet or exceed a Mean Time Between Failure (MTBF) of 10,000Hrs per MIL-HDBK-217F, for an Uninhabited Fighter aircraft environment.

3.3.9 Computing Requirements

The CFIT-P System shall include the processing, memory, interfacing hardware, and peripheral supports required to effectively perform the functional requirements real-time, while minimizing pilot workload. The CFIT-P System shall include a TAWS Computer, a TAWS Indicator Panel, a Media Device, and Aural Alert Accommodations (any passive components required to interface with the Communications System). The internal interfaces for these components meet sections 3.4.2, 3.4.3, 3.4.5, and 3.4.6 respectively.

3.3.10 Component Obsolescence Requirements

The CFIT-P System should be designed to enable updates throughout its period of deployment with minimal cost and schedule impact.

The design objective is to use best practices to mitigate component obsolescence by using modern architecture and a design goal of selecting components with a projected life span and availability of ten (10) years.

3.3.12 Wire Harness New and Modification Requirements

The CFIT-P System electric and electronic wire new installation and Aircraft Wire Harness modifications shall conform to T.O 01-1A-14, Installation and Repair Practices Volume 1, Aircraft Electric and Electronic Wiring. Additionally, MIL-DTL-81381 wiring or any form of polyimide type wiring (i.e. DuPont brand Kapton) shall not be used.

System External Interface Requirements The CFIT-P system shall provide external interfacing to sensor systems, Crash Survivable Recorder, audio system, and supportable displays in Table 1.

3.4.1 Interface Identification and Diagrams

Table 1 lists the external interfaces required of the CFIT-P system. Figure 2 illustrates a top-level interface diagram for the T-6A and depicts the external interfaces. Figure 3 illustrates a top-level interface diagram for the T-6B/D and depicts the external interfaces. The sub-paragraphs that follow provide further external interface details.

Table 1 External Interfaces

Interfacing Entities & Characteristics CFIT-P System Interface

Name External System/Subsystem

Power Bus Interface 28 VDC Battery Bus T-6A / T-6B / T-6D

ADC Data Bus Air Data Computer (ADC) T-6A / T-6B / T-6D

IRU Data Bus

Attitude And Heading Reference System (AHRS) T-6A

Inertial Reference Unit (IRU) T-6B / T-6D

GPS Data Bus Global Positioning System (GPS) T-6A

Integrated Avionics Computer

(IAC) T-6B / T-6D

RA Data Bus **not available** T-6A

Radar Altimeter T-6B / T-6D

Audio Outputs*† Audio Amplifier T-6A

Audio Management Unit (AMU) T-6B / T-6D

Discrete Outputs Interface Crash Survivable Recorder (CSR) T-6A / T-6B / T-6D

*The AMU does not have CFIT-P alerts. A software upgrade will be required.

†The IAC currently communicates with the AMU by ARINC 429, and other warning systems use discretes with AMU.

Figure 1 CFIT-P External Interface Diagram (T-6A)

Figure 2 CFIT-P External Interface Diagram (T-6B/D)

3.4.2 Power Bus Interface

The CFIT-P System shall include a Power Bus Interface to interface to the 28 VDC Battery Bus in the T-6A and T-6B/D aircraft. The existing IDARS ARINC 404B-2 physical interface shall be reused to accommodate the CSR design. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.3 ADC Data Bus

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the ADC (Textron P/N’s 133-340143-3, 133-340143-0005, and 133-340143-0009) in the T-6A and T-6B/D aircraft. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.4 IRU Data Bus

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the AHRS (Litef PN 141852-1111, 141852-1122, or 145130- 6200) in the T-6A and IRU (Raytheon P/N 100-602578-000) in the T-6B/D aircraft. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.5 GPS Data Bus

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the GPS (Bendix King P/N 066-04034-0104) in the T-6A and IAC (CMC Electronics P/N’s 100-602573-000 and 100-602573-001) in the T-6B/D aircraft.

These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.6 RA Data Bus

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the Radar Altimeter (PN 100-602582-000) in the T-6A and T- 6B/D aircraft. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.7 Audio Output

The CFIT-P System shall include an Audio Outputs Interface to interface to the Communication System in the T-6A (Audio Control Amplifier PN 443 (MOD C)) and Audio Management Unit (PN 4420-000) in the T-6B/D aircraft. CFIT-P System may include accommodations in order to meet requirements for aural warning priority, decibel level, and call out definition. Where applicable, coordination with OEM may result in a configuration change for external units.

These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.4.8 Discrete Outputs Signal Interface

The CFIT-P System shall include a Discrete Outputs Signal Interface to interface to the Recorder Maintenance Annunciator in the T-6B/D aircraft. The Discrete Outputs Signal Interface shall consist of a Built-In-Test (BIT) Status Discrete, and discretes for a premature descent, alert for flight towards terrain, and ground proximity condition has been detected. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

System Internal Interface Requirements The CFIT-P System shall include internal interfaces and hardware to meet the functional, physical, and external interface requirements set forth in this document.

3.5.1 Interface Identification and Diagrams

Table 2 lists the internal interfaces required of the CFIT-P system. Figure 4 illustrates a top-level interface diagram for the T-6A and T-6B/D and depicts the internal interfaces. The sub-paragraphs that follow provide further internal interface details.

Table 2 CFIT-P System Internal Interfaces

Interfacing Entities & Characteristics From Internal

Sub-system To Internal Sub-system Aircraft Model

TAWS Computer TAWS Indicator Panel T-6A / T-6B / T-6D

TAWS Indicator Panel TAWS Computer T-6A / T-6B / T-6D

Media Device TAWS Computer T-6A / T-6B / T-6D

TAWS Computer Aural Alert Accommodations T-6A / T-6B / T-6D

Figure 3 CFIT-P System Internal Interface Diagram

3.5.2 TAWS Unit

The TAWS Unit shall receive a discrete from the TAWS Indicator Panel for self-test initiation.

The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.5.2 TAWS Indicator Panel – Test

The TAWS Unit shall receive a discrete from the TAWS Indicator Panel for self-test initiation.

The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.5.3 TAWS Indicator Panel – Terrain Inhibit

The TAWS Unit shall receive a discrete from the TAWS Indicator Panel for Terrain Inhibit. The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.5.4 TAWS Indicator Panel – TAWS Warning

The TAWS Unit shall provide an interface to TAWS Indicator Panel. The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

3.5.5 Media Device

The TAWS Unit shall be capable of downloading the latest Terrain database. This may be from another device, referred to here as Media Device for simplicity. The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

The Media Device shall provide a means, approved by JPATS program office, to load the latest Terrain database to the TAWS Unit.

3.5.6 Aural Alert Accommodations

The TAWS Unit shall accommodate the interface and capability of the communications system of T-6A and the Audio Management unit of T-6B/D. This may be harness, box, or software solutions, referred to here as Aural Alert Accommodations for simplicity. The interface shall be defined in an Interface Control Document. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

Adaption Requirements The CFIT-P system shall be compatible or configurable with both the T-6A and T-6B/D models.

Safety Requirements There are no major safety concerns with the operation of this system in that it provides no outputs to the major T-6 avionics and flight control systems.

3.7.1 System Safety/Failure Requirements

Unless otherwise specified or FAA certification requirements become more stringent, the installed system shall be fail-safe in that no single point of failure or combination of failures with a combined rate greater than 1X10-7 per flight hour can cause a critical or catastrophic mishap.

Fail-safe is defined as a design feature that ensures the aircraft and systems remain safe or, in the event of a failure, shall cause the aircraft and systems to revert to a state that shall not result in a mishap. Definitions of critical and catastrophic mishap are as defined in MIL-STD-882E, paragraph 4.3.3.

The installed system is a standalone system which monitors parameters and provides no outputs to the T-6 systems.

3.7.2 Occupational Health and Safety Requirements

3.7.2.1 Occupational Health Requirements

Any new or peculiar support equipment or procedures procured for the aircraft shall be designed in compliance with AFI 91-203, Air Force Consolidated Occupational Safety Instruction, as amended by Air Force Guidance Memorandum 3, dated 19 August 2014.

3.7.2.2 Occupational Safety Requirements

MIL-HDBK-454B Guideline 1, Safety Design Criteria – Personnel Hazards, should be used as guidance only. Personnel hazard areas to be monitored include fail-safe interlocks, electrical bonding, and grounding, exposure to high voltage, radiation, high temperature, mechanical hazards, and hazardous materials.

3.7.3 Prohibited Hazardous Materials

The following hazardous materials are prohibited and shall not be contained in any delivered hardware, including Commercial Off The Shelf (COTS) hardware, and shall not be used in the operation or support of the aircraft with its installed system.

Table 3 Prohibited Hazardous Materials

Asbestos Carbon Tetrachloride (=Tetra chloromethane) CFCs -11, 12, 13, 111, 112, 113, 114, 115, 211, 212, 213, 214, 215, 216, and 217, and blends R-500, -501, -502, -503

Halons – 1011, 1202, 1211, 1301, 2402

Hydrazine Methyl Bromide Polychlorinated Biphenyls (PCBs) Radioactive material Trichloroethane (=Methyl Chloroform)

3.7.4 Fasteners

Fasteners that could cause foreign object damage or loss of the aircraft if they separate from the structure shall have provisions to assure they either are retained on the structure or cannot become loose.

3.7.5 Toxicity

The installed system shall maintain a safe environment for personnel and shall not cause toxic exposure in excess of the limits per OSHA Standard 29 CFR 1910, sections 1000, 1001, 1010, 1012, 1017, 1025, and 1028.

3.7.6 Security and Privacy Requirements

The CFIT-P system shall comply with Information Assurance requirements IAW DoDD 8500.1, Information Assurance (IA), and DoDI 8500.2, Information Assurance (IA) Implementation.

Human Factors Requirements The installation of CFIT-P system does not degrade human performance necessary to operate, maintain, support, and control the system. Human engineering shall consider the prevention of mistakes through the human interface.

System Environment Requirements

3.9.1 Electromagnetic Compatibility

The installed system shall operate without performance degradation to the aircraft training mission during concurrent operation of any combination of the remaining subsystems and equipment. The aircraft shall have Radio Frequency (RF) compatibility among all antenna-connected subsystems and equipment.

3.9.2 Electromagnetic Interference

Electromagnetic interference characteristics of the installed system shall be controlled to ensure electromagnetic compatibility within the system and with the external environments in accordance with DO-160G or later.

3.9.3 Grounding and Bonding

All electrical and electronic items that have the capability of producing, radiating, or responding to electromagnetic energy shall be electrically bonded to the aircraft ground system with a resistance of 2.5 milliohms direct current or less for metallic interfaces.

3.9.4 Natural Environments

The installed system shall meet the requirements of this SRD before, during, and after exposure to the following natural and induced environmental conditions defined in paragraph 3.8.4.1.

3.9.4.1 Expected Operating Environments

The aircraft with the installed system shall be capable of performing all missions including ground servicing at the expected environments at the planned operating locations except as otherwise specified herein. The expected operating environments shall be as defined below.

Ground and flight temperature, humidity, solar radiation, in-flight icing, and lightning requirements are as follows:

• The extreme ambient temperatures for ground operations shall be -9°F to 109°F dry bulb.

External heaters and coolers are not permitted in this temperature range.

• The extreme ambient temperatures for in-flight operations shall be -65°F to 109°F dry bulb.

• The extreme ambient relative humidity for ground and flight operation shall be 12% to 95% relative humidity.

• Lightning protection shall be in accordance with FAR 23 section 23.1306

• The installed system shall perform under all environmental conditions of vibration, acoustics, thermal, and shock experienced by the aircraft, systems, and equipment.

Computer Resource Requirements

3.10.1 Computer Hardware Requirements

The computing device hosting the CFIT-P capability shall meet DO-254 Design Assurance Level determined by the safety assessment.

3.10.2 Computer Hardware Resource Utilization Requirements

The computing device hosting the CFIT-P capability shall have 50% excess capacity, under heaviest loading, in the critical areas of processor utilization, memory utilization, and data bus and network bandwidth. This shall be qualified through analysis of vendor supplied documents and proven by documentation or demonstration. The contractor may utilize the operating system task manager (or commercial software tools) to provide the system operational data for correlating the hardware resource requirements.

3.10.3 Computer Software Requirements

These requirements apply to all software, firmware, and files that comprise the Operational Flight Program for the functionality required to operate properly.

3.10.3.1 CFIT-P Software

The CFIT-P System shall meet DO-278B Design Assurance Level determined by the safety assessment.

3.10.3.4 Software compatibility

The Contractor shall also demonstrate that the new hardware, and new and modified software meets the design requirements of the CFIT specification and do not degrade the current T- 6A/B/D requirements.

System Quality Factors

3.11.1 Maintainability

The installed system shall meet the maintainability criteria in MIL-STD-1472G section 5.9 for all conditions. The removal and replacement of high failure rate Line Replaceable Units (LRUs) shall not require removal of more reliable LRUs. Removal and replacement of failed LRUs shall not require the use of special tools. Modified equipment shall preclude improper installation, mounting, or connection of LRUs, assemblies, subassemblies, cables, or lines. All connections located in close proximity to each other shall be physically non-interchangeable except when the connectors are specifically designed to be interchangeable for supportability reasons; clearly marked as to their correct installation and unable to cause damage to the equipment.

3.11.2 Usability

The installed system shall not degrade operator workload in comparison to that of the current system.

3.11.3 Design and Construction Constraints

The design and installation of the upgrade shall comply with Title 14 CFR FAA Part 23 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes and Title 14 CFR FAA Part 91 General Operating.

3.11.4 Parts Marking

FAA identification and marking schemes described by FAR 21.607(d) and FAR Part 45 Subpart B shall be used as guides for marking parts. Marking by commercial practices shall be used for all parts not covered by this guidance.

Personnel Related Requirements T-6A/B/D accommodates a pilot instructor and a pilot student. Pilot in Command may be either as directed by instructor. The CFIT-P System aural and visual indications shall be provided to both FWD and AFT cockpits. The CFIT-P System inputs shall be received from both FWD and AFT cockpits.

3.12.1 System Status/Failure Annunciation

The installed system shall include a method to display its operational status to the flight crew, which is consistent with the overall flight deck design philosophy IAW Title 14 CFR FAA Part 23 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes, Title 14 CFR FAA Part 91 General Operating and Flight Rules standards.

3.12.2 Human Performance

All modifications after contract award shall meet the human engineering criteria in MIL-STD- 1472, sections 4, 5.1 through 5.5, 5.9, and 5.13 for all normal and emergency conditions for all anticipated missions.

Regulatory and Certification Requirements The design and installation of the CFIT-P system shall meet Title 14 CFR FAA Part 23 and Part 91 regulations. The CFIT-P system shall be FAA certified via a Supplemental Type Certificate and meet Military Airworthiness Validation/ Verification Provisions.

4 VERIFICATION PROVISIONS

This section defines a set of requirement verification methods. In addition, this section specifies for each requirement in Section 3 the method(s) to be used to verify the requirement has been met. A table is used to present this information and is documented in Appendix B.

Verification Methods Unless otherwise specified, the contractor is responsible for verification of all requirements specified herein. Except as otherwise specified, the vendor may use its own facilities or any commercial laboratory acceptable to the U.S. Government. The U.S. Government reserves the right to monitor or perform any inspections, demonstrations, analyses, or tests set forth in the specification where such inspections are deemed necessary to assure that parts, materials, or services conform to prescribed requirements.

4.1.1 Demonstration

Demonstration is defined as the operation of the system or subsystem that requires observation to demonstrate requirement compliance. This verification does not require the use of instrumentation, special test equipment, or subsequent analysis. An example would be a fit and function check. Some of the demonstrable functions are listed below:

Demonstrate re-configurability.

Demonstrate terrain database load.

Demonstrate audio and visual alerts for all cases in a simulated environment.

Demonstrate proper operation within customer designated MOA.

4.1.2 Test

Test is defined as verification of the requirements through the application of established test procedures, usually with instrumentation, within specified environmental conditions and subsequent compliance confirmation through analysis of the data generated. This requirement may be fulfilled by submission of data that demonstrates the required test has been satisfactorily accomplished. Some of the general test procedures are listed below:

Test input ranges.

Test proper function without failures during operational temperature range.

Measure power consumption of the installed system Test audio dynamic range and quality for all audio signals in the cockpit See Appendix B, for detail test requirements and traceability.

4.1.3 Analysis

Analysis is defined as processing of accumulated data obtained from other qualification methods to verify requirement compliance. Examples of analysis are reduction, interpolation or extrapolation of test results. This verification requirement may be fulfilled by submission of data previously produced that demonstrates the analysis has been satisfactorily accomplished.

4.1.4 Inspection

Inspection is defined as visual verification that the system, including system documentation, conforms to the requirements specified herein. Visual verification can be in the form of inspection of the physical installation and/or review of documents reflecting qualification requirements.

5 APPENDICES

Appendix A: Acronyms and Definitions

ADC Air Data Computer AFH Air Force Handbook AFI Air Force Instruction AHRS Attitude And Hearing Reference System ANSI American National Standards Institute ASIP Aircraft Structural Integrity Program ASME American Society of Mechanical Engineers ASQ American Society of Quality ASTM American Society for Testing and Materials BIT Built In Test CAC Common Access Card CFast CompactFast CFIT-P Controlled Flight into Terrain - Prevention CFR Code of Federal Regulations COTS Commercial Off The Shelf CSR Crash Survivable Recorder CSV Comma Separated Variable CVR Cockpit Voice Recorder DITS Digital Information Transfer System DoDD Department of Defense Directive DoDI Department of Defense Instruction EDM Engine Data Manager EIA Electronic Industries Association ENSIP Engine Structural Integrity Program FAA Federal Aviation Administration FDR Flight Data Recorder GEIA Government Electronics Information Technology Association GPS Global Positioning System GPWS Ground Proximity Warning System IA Information Assurance IAC Integrated Avionics Computer IAW In Accordance With IDARS Integrated Data Acquisition and Recorder System IEEE Institute of Electrical and Electronics Engineers IRU Inertial Reference Unit ISO International Organization for Standards LRU Line Replaceable Units

MFOQA Military Flight Operations Quality Assurance Program NIST National Institute of Standards and Technology OSHA Occupational Safety & Health Administration PCB Polychlorinated Biphenyls PIPFS Prime Item Product Functional Specification PUI Project Unique Identifier RAM Random Access Memory RF Radio Frequency RPM Rotations Per Minute SAWE Society of Allied Weight Engineers SECDEF Secretary of Defense SP Special Publication SRD System Requirements Document STC Supplemental Type Certification TAD Textron Aviation Defense, LLC TAS Traffic Advisory System TAWS Terrain Avoidance and Warning System TO Technical Order TSOA Technical Standard Order Authorization UHS Ultra High Speed USB Universal Serial Bus USG United States Government WOW Weight on Wheels

Appendix B: Test and Verification Matrix Appendix B contains the requirements identified in Section 3 “Requirements” and the verification method to be used to determine compliance. Definitions of Demonstration (D), Test (T), Analysis (A), and Inspection (I) are provided in Section 4.1. Entries labeled “Info” in the Verification Method column refer to narrative that is for information only and requires no verification. Verification methods indicated for each requirement shall not take precedence over FAA-required methods for certification.

Section CFIT-P System Requirements Details Verification Method

3.1

The CFIT-P System shall have the following minimum required states:

Powered-Off State Iniitialization State Operational State Maintenance State Power Down State

D

3.1.1

Powered-Off State:

The CFIT-P System is not receiving power through the Power Bus

Interface. In this state, the CFIT-P System components can be physically removed/disconnected.

D

3.1.2

Initialization State:

The CFIT-P System shall transition from the Powered Off State when power is received through the Power Bus Interface to the

Initialization State. A Built In Test (BIT) shall be performed and the results shall be stored in Protected Memory. The CFIT-P System shall continuously indicate the status of the BIT. The CFIT-P System shall determine the Aircraft Model and configure the CFIT-P system based on the configuration file(s).

D

3.1.3 Operational State:

The CFIT-P System shall transition from the Initialization State upon successful BIT and configuration of the CFIT-P System.

D

3.1.4

Maintenance State:

The CFIT-P System shall transition to the Maintenance State when the Flight Line Computing Device is connected to the Maintenance

Download/Configuration Interface and power is received through the Power Bus Interface.

D

3.1.5

Power Down State:

The CFIT-P System shall transition to the Power Down State when power transitions from on to off/failure through the Power Bus Interface. If the power failure condition exists for more than 200 milliseconds, a graceful power down sequence will be performed and the CFIT-P System will transition to the Powered Off State. If the power is recovered after 200 milliseconds, the CFIT-P System will transition to the Operational State.

D

3.2

The installed system will provide three main functions; Forward- Looking Terrain Avoidance (FLTA), Premature Decent Alert (PDA) and Ground Proximity Warning. The CFIT-P system shall meet/exceed the requirements of TSO-C151c for TAWS Class C.

I, A

3.2.4 The CFIT-P System shall utilize a regularly updated terrain database. D

3.2.5 The CFIT-P System shall provide aural alerts to both forward and aft cockpit pilots for Forward-Looking Terrain Avoidance (FLTA), Premature Decent Alert (PDA) and Ground Proximity Warning.

D

3.2.6 The CFIT-P System shall provide a visual alert for Terrain

Avoidance. D

3.3.5

The CFIT-P System shall be powered by the Aircraft Avionics Bus Power (+28 ± 4.0 VDC, 40W Max.). The CFIT-P System

Installation shall include modifications to circuit breaker panel and wiring as determined by aircraft OEM.

I

3.3.6 The CFIT-P components shall conform to space, accessibility, and

Center of Gravity constraints of T-6A and T-6B/D. I

3.3.7 The CFIT-P hardware shall meet or exceed RTCA/DO-160G

Category C2 requirements. T

3.3.8 The CFIT-P hardware shall meet or exceed a Mean Time Between

Failure (MTBF) of 10,000Hrs per MIL-HDBK-217F, for an Uninhabited Fighter aircraft environment.

A

3.3.9

The CFIT-P System shall include the processing, memory, interfacing hardware, and peripheral supports required to effectively perform the functional requirements real-time, while minimizing pilot workload.

I

The CFIT-P System shall include a TAWS Computer, a TAWS Indicator Panel, a Media Device, and Aural Alert Accommodations

(any passive components required to interface with the Communications System). The internal interfaces for these components meet sections 3.4.2, 3.4.3, 3.4.5, and 3.4.6 respectively.

I

3.3.10 The CFIT-P System should be designed to enable updates throughout its period of deployment with minimal cost and schedule impact. I

3.3.12

The CFIT-P System electric and electronic wire new installation and Aircraft Wire Harness modifications shall conform to T.O 01-1A-14, Installation and Repair Practices Volume 1, Aircraft Electric and Electronic Wiring. Additionally, MIL-DTL-81381 wiring or any form of polyimide type wiring (i.e. DuPont brand Kapton) shall not be used.

I

3.4

The CFIT-P system shall provide external interfacing to sensor systems, Crash Survivable Recorder, audio system, and supportable displays in Table 1.

Interfacing Entities & Characteristics

CFIT-P System Interface Name

External System/Subsystem

Power Bus Interface 28 VDC Battery Bus T-6A / T-6B / T- 6D

ADC Data Bus Air Data Computer

(ADC)

T-6A / T-6B / T- 6D

IRU Data Bus

Attitude And Heading Reference System

(AHRS)

T-6A

Inertial Reference Unit

(IRU) T-6B / T-6D

GPS Data Bus

Global Positioning System (GPS) T-6A

Integrated Avionics Computer (IAC) T-6B / T-6D

RA Data Bus **not available** T-6A

Radar Altimeter T-6B / T-6D

Audio Outputs*† Audio Amplifier T-6A

Audio Management Unit (AMU) T-6B / T-6D

Discrete Outputs Interface

Crash Survivable Recorder (CSR)

T-6A / T-6B / T- 6D

I, T

3.4.2

The CFIT-P System shall include a Power Bus Interface to interface to the 28 VDC Battery Bus in the T-6A and T-6B/D aircraft. The existing IDARS ARINC 404B-2 physical interface shall be reused to accommodate the CSR design. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

I,T

3.4.3

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the ADC (Textron P/N’s 133-340143-3, 133-340143-0005, and 133-340143- 0009) in the T-6A and T-6B/D aircraft. These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

I,T

3.4.4

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the AHRS (Litef PN 141852-1111, 141852-1122, or 145130-6200) in the T-6A and IRU (Raytheon P/N 100-602578-000) in the T-6B/D aircraft.

These requirements will be qualified by demonstration, inspection, testing, and/or analysis.

I,T

3.4.5

The CFIT-P System shall include a Data Bus Interface, which meets ARINC specification 429 Part 1 thru Part 4, to interface to the GPS (Bendix King P/N 066-04034-0104) in the T-6A and IAC (CMC

Electronics P/N’s…