Preliminary ARP SRD Industry Survey Matrix v2.xlsx
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SRD Industry Survey ARP Preliminary SRD Verification Matrix For each candidate solution, use this table to indicate developmental areas as they map to draft requirements (add sheets to workbook for additional solutions). Utilize spaces at any level. Place "no comment" where left intentionally blank. "Not assessed" is an acceptable entry where product has not been yet been checked for compliance. Use comma to separate Configuration items in list of items that fulfill requirement. Where there is overlap or redundancy in another requirement, please repeat remarks for clarity.
Every component mentioned here should be also addressed in questions of RFI.
| Requirement ID | T-6 ARP TOP LEVEL Requirements Details | Verification Method | COTS LRU PN(s) | COTS HW meets fully as is (Y/N) | Characteristic/Function/Parameter needing LRU HW Development | COTS LRU Software PN(s), mod(s), or "controlled by HW PN(s)" | COTS SW meets as is (Y/N) | Characteristic/Function/Parameter needing Software Development | Has TSO? (Y/N) | Has PMA (Y/N)? | TRL (1-9) | Integration concerns | Verification concerns | Other comments | Y |
| - | 3.1 Certifications | Info | Y | N | |||||||||||
| TBD | 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. | I | |||||||||||||
| The design and installation of the Avionics System shall meet Title 14 CFR FAA Part 23 and Part 91 regulations. | |||||||||||||||
| The ARP system shall be FAA certified via a Supplemental Type Certificate and meet Military Airworthiness certification requirements for a USG-approved MIL-HDBK-516C Military Type Certificate. The FAA certification serves as primary basis for Military certification. | |||||||||||||||
| TBD | To simplify the Supplemental Type Certification (STC) or Amended Type Certification process, FAA Technical Standard Order Authorization (TSOA) components shall be utilized to support the ARP effort if available. | I | |||||||||||||
| TBD | The installed system shall not degrade the operation of other systems on the aircraft. | D | |||||||||||||
| TBD | The installed system shall be able to obtain Primary Flight Reference (PFR) endorsement. | I | |||||||||||||
| - | 3.2 Flight Operations | Info | |||||||||||||
| TBD | The modified T-6A shall provide for communication, navigation, and surveillance/air traffic management capability to allow flight operations at all times in all civil and military airspace (National Airspace System {NAS}). | I/D/T | |||||||||||||
| TBD | The modified T-6A shall be capable of compliance with pertinent operation instructions found in AFI 11-202 Vol 3 and AFMAN11-2T-6 Vol 3. | D/T | |||||||||||||
| TBD | The modified T-6A shall support aircrew training and evaluation criteria found in AFMAN11-2T-6 Vol 1 and Vol 2, respectively. | I/D/T | |||||||||||||
| - | 3.3 Legacy Requirements | Info | |||||||||||||
| TBD | The installed system shall retain existing T-6A capability while adding the capability defined in this description. | I/A/D/T | |||||||||||||
| TBD-PIPFS | The installed system shall comply with the Joint Primary Aircraft Training System (JPATS) Aircraft Prime Item Product Function Specification (PIPFS), except where this SRD supersedes. | See below methods by PIPFS sections | |||||||||||||
| TBD-PIPFS | 3.2.2.1 Operational Service Life | A | |||||||||||||
| TBD-PIPFS | 3.2.2.2 Aerodynamic Performance | A/D | |||||||||||||
| TBD-PIPFS | 3.2.2.3 Flying Qualities | A/D | |||||||||||||
| TBD-PIPFS | 3.2.2.4 Airframe Storage Areas | I/D | |||||||||||||
| TBD-PIPFS | 3.2.3.1 Mission Reliability | A/D | |||||||||||||
| TBD-PIPFS | 3.2.3.2 In-Flight Engine Shutdown Rate | A/D | |||||||||||||
| TBD-PIPFS | 3.2.3.3 Unscheduled Engine Removal Rate | A | |||||||||||||
| TBD-PIPFS | 3.2.4 Maintainability and Availability | A/D | |||||||||||||
| TBD-PIPFS | 3.2.5 Environmental Conditions | A/D | |||||||||||||
| TBD-PIPFS | 3.3.1 Materials Processes and Parts | I | |||||||||||||
| TBD-PIPFS | 3.3.2.1 EMC | T | |||||||||||||
| TBD-PIPFS | 3.3.2.2 EMI | T | |||||||||||||
| TBD-PIPFS | 3.3.2.3 Grounding & Bonding | I/T | |||||||||||||
| TBD-PIPFS | 3.3.2.4 ESD | A/D | |||||||||||||
| TBD-PIPFS | 3.3.2.5: Lightning Protection | A/T | |||||||||||||
| TBD-PIPFS | 3.3.2.6: HIRF | A | |||||||||||||
| TBD-PIPFS | 3.3.2.7: Radiation Hazards | A | |||||||||||||
| TBD-PIPFS | 3.3.3 Identification and Marking | I | |||||||||||||
| TBD-PIPFS | 3.3.6.1 Electrical Safety | A/I | |||||||||||||
| TBD-PIPFS | 3.3.6.2 Explosive Hazard Class | A/I | |||||||||||||
| TBD-PIPFS | 3.3.6.3 Hazardous Materials | A/I | |||||||||||||
| TBD-PIPFS | 3.3.6.4 Toxicity | A/I | |||||||||||||
| TBD-PIPFS | 3.3.7.1 Standardization | I | |||||||||||||
| TBD-PIPFS | 3.3.7.2 Equipment | I | |||||||||||||
| TBD-PIPFS | 3.3.7.3 Anthropometry | A/I/T | |||||||||||||
| TBD-PIPFS | 3.3.7.4 Cockpit Entry and Egress | I/T | |||||||||||||
| TBD-PIPFS | 3.4.1.2 General Structural Parameters and Conditions | A/I | |||||||||||||
| TBD-PIPFS | 3.4.1.3 Structural Loads | A | |||||||||||||
| TBD-PIPFS | 3.4.1.4 Vibroacoustics | A/D | |||||||||||||
| TBD-PIPFS | 3.4.1.5 Aeroelastic Stability | A/D | |||||||||||||
| TBD-PIPFS | 3.1.4.6 Airframe Tracking | I/T | |||||||||||||
| TBD-PIPFS | 3.4.9 Packaging, Handling, Storage and Transportation (PHS&T) | A | |||||||||||||
| TBD | The installed system shall be compatible with all interfaces of the replaced system. | T | |||||||||||||
| TBD | The installed system shall not interfere with or limit aircraft normal and emergency operations, including control surface actuation and electronic equipment. | A/D/T | |||||||||||||
| TBD | The installed system shall not compromise structural integrity or purpose. | A | |||||||||||||
| TBD | The removal of components shall not interfere with or limit aircraft normal and emergency operations, including control surface actuation and electronic equipment. | A/T | |||||||||||||
| TBD | The removal of components shall not compromise structural integrity or purpose. | A | |||||||||||||
| TBD | The installed system shall be compatible with all procedures performed on the USAF T-6A, providing minimal impact on functions replaced and no impact on systems outside ARP boundary. List of applicable publications are found in TO 1T-6ABD-01. | A/D | |||||||||||||
| TBD | The installed system shall not impose facility requirements upon Main Operational Bases. | A | |||||||||||||
| TBD | The Avionics Replacement Program shall replace the following; | I/A/D/T | |||||||||||||
| FWD Electronic Attitude Direction Indicator (EADI) | |||||||||||||||
| AFT Electronic Attitude Direction Indicator (EADI) | |||||||||||||||
| FWD Electronic Horizontal Situation Indicator (EHSI) | |||||||||||||||
| AFT Electronic Horizontal Situation Indicator (EHSI) | |||||||||||||||
| FWD Electronic Flight Instrument System (EFIS) Control Panel | |||||||||||||||
| AFT Electronic Flight Instrument System (EFIS) Control Panel | |||||||||||||||
| FWD Airspeed Electronic Instrument Display (EID) | |||||||||||||||
| AFT Airspeed Electronic Instrument Display (EID) | |||||||||||||||
| FWD Altimeter Electronic Instrument Display (EID) | |||||||||||||||
| FWD Altimeter Electronic Instrument Display (EID) | |||||||||||||||
| FWD Vertical Speed Electronic Instrument Display (EID) | |||||||||||||||
| AFT Vertical Speed Electronic Instrument Display (EID) | |||||||||||||||
| FWD Primary Engine Electronic Instrument Display (EID) | |||||||||||||||
| AFT Primary Engine Electronic Instrument Display (EID) | |||||||||||||||
| FWD Engine/Systems Electronic Instrument Display (EID) | |||||||||||||||
| AFT Engine/Systems Electronic Instrument Display (EID) | |||||||||||||||
| FWD Alternate Engine Electronic Instrument Display (EID) | |||||||||||||||
| AFT Alternate Engine Electronic Instrument Display (EID) | |||||||||||||||
| FWD Standby Airspeed Indicator | |||||||||||||||
| AFT Standby Airspeed Indicator | |||||||||||||||
| FWD Standby Altimeter | |||||||||||||||
| AFT Standby Altimeter | |||||||||||||||
| FWD Standby Turn Slip Indicator | |||||||||||||||
| AFT Standby Turn Slip Indicator | |||||||||||||||
| FWD Standby Compass | |||||||||||||||
| AFT Standby Compass | |||||||||||||||
| FWD Caution Warning Advisory Panel | |||||||||||||||
| AFT Caution Warning Advisory Panel | |||||||||||||||
| Attitude Heading Reference System (AHRS) | |||||||||||||||
| AHRS Control Panel (FWD only) | |||||||||||||||
| Traffic Advisory System (TAS) | |||||||||||||||
| TAS Panel | |||||||||||||||
| FWD Radio Management Unit | |||||||||||||||
| AFT Radio Management Unit | |||||||||||||||
| FWD GPS Receiver | |||||||||||||||
| AFT GPS Receiver | |||||||||||||||
| FWD Mic Amplifier | |||||||||||||||
| AFT Mic Amplifier | |||||||||||||||
| FWD Audio Control Amplifier | |||||||||||||||
| AFT Audio Control Amplifier | |||||||||||||||
| Air Data Computer (ADC) | |||||||||||||||
| UHF Communication Transceiver | |||||||||||||||
| FWD Standby UHF Control Head | |||||||||||||||
| AFT Standby UHF Control Head | |||||||||||||||
| Emergency Locator Beacon (ELT) | |||||||||||||||
| TBD | In order to accommodate the installed system, these are candidate subsystems or components for replacement based on performance, weight, cost, schedule, and/or installation impacts ; | Info | |||||||||||||
| · Mode S Transponder | |||||||||||||||
| · Flux Valve/Magnetometer | |||||||||||||||
| · Circuit Breaker Panels | |||||||||||||||
| · Instrument Panel | |||||||||||||||
| · VHF Communications Transceiver | |||||||||||||||
| · FWD Clock | |||||||||||||||
| · AFT Clock | |||||||||||||||
| TBD | ARP shall remove unnecessary components overcome by the new architecture, such as unused splitters, couplers, relays, manifolds, antenna, doublers, mounts, harnesses, and sensors. | I/A | |||||||||||||
| TBD | Any unrequired functions or equipment included in integrated design solution accepted by the government shall not compromise the system requirements defined in this document. | T | |||||||||||||
| - | 3.4 Architecture | Info | |||||||||||||
| TBD | The Avionics Replacement Program (ARP) shall leverage open systems architecture, comply with industry protocols and standards, and select sub-components widely used in the marketplace. | I/D | |||||||||||||
| TBD | The installed system shall support Integrated Modular Avionics requirements per guidance ARINC 651. | ? I | |||||||||||||
| TBD | To maximize the relevance of the T-6 ARP for the life of the aircraft, the installed system shall not be limiting whereas advisory circulars and rulemaking have superseded the capability description as written, or support equipment is divested/discontinued. | I | |||||||||||||
| TBD | The Offeror should use Modular Open Systems Approach (MOSA) to evaluate the appropriateness of implementing a modular design strategy for building systems. A primary consideration in selection of equipment to meet the design functionality will be the impact to the overall modular open systems architecture. A modular open systems approach and analysis of long term supportability, interoperability, and growth for future modifications shall be major factors in the Offeror’s final selection of equipment and integration approach. | I | |||||||||||||
| TBD | All the systems components shall facilitate future upgrades and permit incremental technology insertion to allow for incorporation of additional or higher performance elements with minimal impact on the existing systems. | I/A | |||||||||||||
| TBD | The architectural approach shall provide a viable technology insertion methodology and refresh strategy that supports application of a modular open systems approach and is responsive to changes driven by mission requirements and new technologies . | I | |||||||||||||
| TBD | The Offeror shall develop a detailed modular design and integration that includes but is not limited to the following aspects: interoperability, intra-operability, upgradeability, reconfigurability, transportability, software standards, interface standards, long term supportability, sources of supply and/or repair, business strategies, and other entities that affect application of a modular open systems approach. | I/A | |||||||||||||
| TBD | For those portions of hardware, firmware, or software that are driven to proprietary and/or closed system architectures by mission specific requirements, a hardware/firmware/software partitioning or other design features to mitigate the system level impacts shall be provided. | I/A | |||||||||||||
| TBD | The Offeror shall provide an orderly, planned approach to address migration of proprietary or closed system equipment or interfaces to a modular design when technological advances are available. | I | |||||||||||||
| TBD | The installed system shall preclude long term dependence on closed or proprietary interface standards, technologies, products, or architectures. | I | |||||||||||||
| TBD | The design shall provide sufficient growth and open interface standards to allow future reconfiguration and addition of new capabilities without large-scale redesign of the system. | I/A | |||||||||||||
| - | 3.5 System Requirements | Info | |||||||||||||
| - | 3.5.1 Scope Boundary Diagram | Info | |||||||||||||
| - | 3.5.2 Required States and Modes | Info | |||||||||||||
| TBD | The Installed System shall have the following minimum required states : | D/T | |||||||||||||
| · Powered-Off State | |||||||||||||||
| · Initialization State | |||||||||||||||
| · Operational State | |||||||||||||||
| · Maintenance State | |||||||||||||||
| · Power down state | |||||||||||||||
| TBD | The installed system reboot and recovery shall be verified with no degradation of data with and without battery backup. | T | |||||||||||||
| TBD | The installed system shall transition between states as depicted in Figure 2 diagram and described in statements of this section. | D/T |
| Figure 2 State Diagram | |||
| - | 3.5.2.1 Powered off state | Info | |
| TBD | In the Powered Off state, the installed system is not receiving power through the Power Bus Interface. In the Powered Off state, the installed system components shall be capable of physically removed/disconnected. | D/T | |
| - | 3.5.2.2 Initialization State | Info | |
| TBD | The installed system shall transition from the Powered Off State when power is received through the Power Bus Interface to the Initialization State. | D/T | |
| TBD | In the Initialization State, a Built In Test (BIT) shall be performed and the results shall be stored in Protected Memory. | D/T | |
| TBD | The installed system shall continuously indicate the status of the BIT, until cleared by approved means. | D/T | |
| TBD | In the Initialization State, The installed system shall determine the Aircraft Model and configure the installed system based on the configuration file(s). | T | |
| - | 3.5.2.3 Operational State | Info | |
| TBD | The installed system shall transition from the Initialization State to the Operational State upon successful BIT and configuration of the installed system. | D | |
| - | 3.5.2.4 Maintenance State | Info | |
| TBD | The installed 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/T | |
| - | 3.5.2.5 Power Down State | Info | |
| TBD | The installed 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 installed system will transition to the Powered Off State. If the power is recovered after 200 milliseconds, the installed system will transition to the Operational State. | D/T | |
| - | 3.5.3 Electrical Power | Info | |
| TBD | The installed system shall be compatible with the power system of the T-6A aircraft. | A/T | |
| TBD | The bus architecture shall not be adversely impacted or changed by the installed system. | I/A | |
| TBD | The installed system shall meet PIPFS requirements on electrical power. | I/A/D/T | |
| TBD | The installed system shall operate within the current allocations and limits for each bus the Avionics is being replaced. | A | |
| TBD | The Installed system shall have a minimum input voltage range of +28 nominal ± 4.0 VDC. | A | |
| TBD | The Installed system shall have a maximum power requirement of equal to or less than the replaced system components, to include continuous and transient power demands. | A | |
| TBD | The Installed system shall not trip the circuit breakers under normal operation. | A | |
| - | 3.5.3.1 Circuit Protection | - | |
| TBD | The installed system shall replace circuit protection devices required to comply with all requirements, regulations, and safety assessment, without affecting operation of other systems. | A | |
| - | 3.5.3.2 Main Battery Bus | - | |
| TBD | The installed system shall be powered by the Aircraft Battery Bus. | I | |
| TBD | The installed system shall not reduce the main battery emergency power time. | A (FCF D?) | |
| - | 3.5.3.3 Auxiliary Power | - | |
| TBD | The installed system shall not reduce the auxiliary battery emergency power time. | A | |
| In an emergency situation, the auxiliary battery will power the standby instruments, UHF transceiver and backup UHF control, standby instrument lighting, and FIRE 1 fire warning system for approximately 30 minutes. | |||
| - | 3.5.4 Space, Weight, and Cooling | Info | |
| - | 3.5.4.1 Physical Requirements | Info | |
| TBD | The Installed System physical dimensions shall be within envelopes defined in Figures and provided USG data, and approved by T-6 Program Office. | I | |
| - | 3.5.4.2 Weight | Info | |
| TBD | The Installed System shall have a maximum weight of the replaced system. | T | |
| TBD | The Installed System shall have a maximum weight less than the replaced system [OBJECTIVE]. | T | |
| - | 3.5.4.3 Cooling | Info | |
| TBD | The Installed System shall generate heat at a rate no greater than the replaced system. | A/T | |
| - | 3.5.4.4 Center of Gravity | Info | |
| TBD | The center of gravity of the Installed System shall be within the limitations for T-6 safe operation. | A/D | |
| TBD | The center of gravity of the Installed System shall be closer to the center of the limitation range [OBJECTIVE]. | A/D | |
| - | 3.5.5 Wire Harness New and Modification Requirements | Info | |
| TBD | The Installed 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, T.O. 01-1A-14-2, Installation and Repair Practices Volume II, Aircraft Circular Electrical Connectors and Accessories, T.O. 01-1A-14-3, Installation and Repair Practices Volume III, Aircraft Rectangular Electrical Connectors and Accessories, and T.O. 01-1A-14-4, Installation and Testing Practices Volume II, Aircraft Fiber Optic Cabling. | I | |
| TBD | Additionally, MIL-DTL-81381 wiring or any form of polyimide type wiring (i.e. DuPont brand Kapton) shall not be used. | I | |
| TBD | The installed system shall comply with AS50881. | I | |
| TBD | The design of the installed system shall be informed by EWIS Integrity Program in accordance with MIL-STD-1798C. | I | |
| - | 3.5.6 Environment | Info | |
| - | 3.5.6.1 Natural Environments | Info | |
| TBD | 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 3.6.6.1.1. | T | |
| - | 3.5.6.2 Expected Aircraft Operating Environments | Info | |
| TBD | 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, since the PIPFS doesn’t contain aircraft zonal expected environmental specifications for the avionics bay, shall be for the aircraft as defined below. Ground and flight temperature, humidity, solar radiation, in-flight icing, and lightning requirements are as follows: | I/A/D/T | |
| TBD | 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. | T | |
| TBD | The extreme ambient temperatures for in-flight operations shall be -65°F to 109°F dry bulb. | T | |
| TBD | The extreme ambient relative humidity for ground and flight operation shall be 12% to 95% relative humidity. | T | |
| TBD | Lightning protection shall be in accordance with FAR 23 section 23.1306. | T | |
| TBD | The installed system shall perform under all environmental conditions of vibration, acoustics, thermal, and shock experienced by the aircraft, systems, and equipment. | T | |
| - | 3.5.6.3 Corrosion Control | Info | |
| TBD | The contractor shall notify and obtain acceptance by USG before PDR of any materials listed as corrosive or hazardous in Material and Safety Data Sheet (MSDS) or designs cautioned to be corrosive or hazardous by industry, USAF, USN, or DoD. | I | |
| - | 3.5.6.4 Zonal Environmental Requirements | Info | |
| TBD | The components of the installed system shall meet or exceed DO-160G for installed location. | A/T | |
| - | 3.5.6.5 Storage / Shelf Life | Info | |
| TBD | The components of the installed system and all support equipment shall not require scheduled inspection or testing while in storage. | I | |
| - | 3.5.7 Adaption Requirements | Info | |
| TBD | The installed system shall be configurable via a data configuration file (Data Dictionary) to support the configuration variations defined in section xxxxx. | T | |
| TBD | The data configuration file shall be uploaded/downloaded through the T-6 Maintenance Device Interface. | T | |
| - | 3.5.8 Safety Requirements | ||
| TBD | The installed system provides critical information to the pilots and interfaces with flight control systems. The Safety Program Plan and all of the elements that support the STC is expected to result in a safe design. The installed system shall incorporate provisions as determined by a Failure Modes and Effects Analysis (FMEA) in accordance with SAE ARP4761 and approved by USG. | I/D | |
| - | 3.5.9 System Safety/Failure Requirements | Info | |
| TBD | 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. | A | |
| TBD | 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. | I/D | |
| - | 3.5.10 Occupational Health and Safety Requirements | Info | |
| - | 3.5.10.1 Occupational Health Requirements | Info | |
| TBD | 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. | A | |
| - | 3.5.10.2 Occupational Safety Requirements | Info | |
| TBD | 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. | I/A | |
| - | 3.5.11 Prohibited Hazardous Materials | Info | |
| TBD | 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. | I | |
| Table 1 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) | |||
| - | 3.5.12 Fasteners | TBD | |
| TBD | 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. | I | |
| - | 3.5.13 Toxicity | Info | |
| TBD | 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. | A | |
| - | 3.5.14 Security and Privacy Requirements | Info | |
| TBD | The Installed System shall comply with Information Assurance requirements IAW DoDD 8500.1, Information Assurance (IA), and DoDI 8500.2, Information Assurance (IA) Implementation . | ? | |
| - | 3.5.15 Electromagnetic Compatibility | Info | |
| TBD | 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. | T | |
| - | 3.5.16 Electromagnetic Interference | Info | |
| TBD | 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. | T | |
| - | 3.5.17 Grounding and Bonding | Info | |
| TBD | 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. | I/D | |
| - | 3.5.18 Reliability Requirements | Info | |
| TBD | The Installed system shall meet or exceed a Total Mean Time Between Failure (TMTBF) of 126 hours per HDBK-217Plus, Notice 1, for installed environment. | A | |
| - | 3.5.19 Future Obsolescence Requirements | Info | |
| TBD | 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 twenty-five (25) years from initial installation deployment. | I | |
| - | 3.5.20 Maintainability | Info | |
| TBD | The installed system shall meet the maintainability criteria in MIL-STD-1472G section 5.9 for all conditions. | A | |
| TBD | The removal and replacement of high failure rate Line Replaceable Units (LRUs) shall not require removal of more reliable LRUs. | I | |
| TBD | Removal and replacement of failed LRUs shall not require the use of special tools. | I | |
| TBD | Modified equipment shall preclude improper installation, mounting, or connection of LRUs, assemblies, subassemblies, cables, or lines. | I | |
| TBD | 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. | I | |
| TBD | All batteries of the installed system shall be serviceable at the Organizational level of maintenance. A battery shop at every base is able to conduct regular battery maintenance operations. | I | |
| TBD | The Installed System shall not require any periodic or initializing codec, encoding, code entry, or otherwise enabling action besides tail specific information in order to function. | I | |
| - | 3.5.21 System Health Status | Info | |
| - | 3.5.21.1 System Status/Failure Annunciation | Info | |
| TBD | 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. | I/D/T | |
| - | 3.5.21.2 Built In Test (BIT) | Info | |
| TBD | The installed system shall perform Initiated Built in Tests (IBIT) to provide field services information to identify faulty Line Replaceable Units. | I/A/D | |
| TBD | The installed system shall perform Initiated Built in Tests (IBIT) to provide field services information to identify erroneous inputs and outputs. | I/A | |
| TBD | The installed system shall perform Power On Built in Tests (PBIT) to provide information to pilots to identify performance outside limits for normal operation. | As determined by CSWG | |
| TBD | The installed system shall perform Continuous (Periodic) Built in Tests (CBIT) to provide information to pilots to identify performance outside limits requiring action from pilot according to Flight manual. | As determined by CSWG | |
| TBD | The Installed System BIT capability shall encompass 100 percent of avionics LRUs with BIT. [OBJECTIVE] | I | |
| TBD | The Installed system shall record IBIT, PBIT, and CBIT for TBD flight hours in protected memory for retrieval in Powered Off state via the T-6 Maintenance Device Interfaces. | T | |
| TBD | The Installed system shall provide a fault history page accessible on display when weight on wheels. | T | |
| TBD | The recorded BIT information shall support isolation by repair vendors and Failure Review Board Working Group to a reasonable extent. | A | |
| TBD | The requirements here supersede of PIPFS section 3.4.5.8, Built-In-Test (BIT). | Info | |
| TBD | The Installed System Built in test (BIT) shall check of all major circuits and program operations. | I | |
| - | 3.5.21.3 Errors & Alert rates System Quality Factors | Info | |
| TBD | The installed system shall produce no errors due to design features unsupportable in the destined state or use. | I/A | |
| TBD | Erroneous faults detected by BIT shall not exceed 5% of the system faults detected by organizational level maintenance | A | |
| - | 3.5.22 Usability | Info | |
| TBD | The installed system shall not increase operator workload in comparison to that of the replaced system. | As determined by CSWG | |
| - | 3.5.23 Design and Construction Constraints | Info | |
| TBD | The design and installation of ARP shall comply with 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. | I/A/D/T | |
| - | 3.5.24 Parts Marking | Info | |
| TBD | 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. | I | |
| - | 3.5.25 Personnel Related Requirements | Info | |
| TBD | The installed system aural and visual indications shall be provided to both FWD and AFT cockpits. | I/D/T | |
| TBD | The installed system inputs shall be received from both FWD and AFT cockpits. | I/D/T | |
| TBD | The Installed System shall provide convenient means for loading databases and flight plans. | I/D/T | |
| - | 3.5.25.1 Human Performance | Info | |
| TBD | The installed system shall meet the human engineering criteria in MIL-STD-1472, sections 4, 5.1 through 5.5, 5.8, 5.9, 5.13, 5.14, and 5.15 for all normal and emergency conditions for all anticipated missions. | I/A | |
| NOTE: Anthropometric Characteristics are defined in BS24806, section 3.3.7.3 | |||
| TBD | The installed system shall not intrude into the ejection envelope as defined by MIL-STD-1333B (Figure 3 ejection line is 0.33” forward of forward face of the ejection seat rail with Figure 3, Note 6 dimension of 26.12”) | I/A | |
| NOTE: Anthropometric Characteristics are defined in BS24806, section 3.3.7.3 | |||
| TBD | The installed system shall not impact exterior field of view criteria in MIL-STD-850B, sections 4.1 and 5.1 | I/A/D | |
| NOTE: Anthropometric Characteristics are defined in BS24806, section 3.3.7.3 | |||
| - | 3.5.26 Support Equipment | Info | |
| TBD | All Support Equipment for the installed system shall be compatible with the aircraft. | D | |
| TBD | All Support Equipment for the installed system shall be contractor furnished. | I | |
| - | 3.5.26.1 T-6 Maintenance Device Software Requirements | Info | |
| TBD | All required support software shall be compatible with the T-6 Maintenance Device (GETAC P/N BH4CLDDABDX9) (Windows 10 Operating System). | I | |
| TBD | All required maintenance communication interfaces shall be compatible with the T-6 Maintenance Device (GETAC P/N BH4CLDDABDX9). | I | |
| - | 3.5.26.2 Configuration Software | Info | |
| TBD | The Configuration Software shall have the following minimum capabilities: | I/A/D/T | |
| • Compatible with Microsoft Windows 10 Pro operating system | |||
| • Selection of which configuration file to upload to the installed system from the T-6 Maintenance Laptop | |||
| • Selection button to start the download | |||
| • Status Display for the download indicating start of the upload, completion %, and upload complete | |||
| • Download of configuration files currently loaded on the aircraft to the T-6 Maintenance Laptop, and checksum capability. | |||
| • Log file generation identifying upload and download times and configuration file name (version). | |||
| • Compliance with ARINC 615 | |||
| - | 3.5.6.3 Configuration File Generation Software Requirements | Info | |
| TBD | The Configuration File Generation Software shall have the following minimum capabilities: | I/T | |
| • Compatible with Microsoft Windows 10 Pro operating system | |||
| • Generate and/or modify a configuration file (Data Dictionary) | |||
| • Load an existing configuration file (Data Dictionary) for modification or viewing. | |||
| - | 3.6 Subsystem Requirements | Info | |
| - | 3.6.1 Display | Info | |
| TBD | The installed system shall include display(s) in each cockpit for multifunctional use. | I/D | |
| TBD | The combined display area of the installed system shall be sized to maximum area accommodated by instrument panel, allowing space for emergency standby instrumentation and other panels and indicators as required to meet PIPFS requirements, retain legacy functionality, and meet the requirements of this SRD. | I/D | |
| TBD | All displays, indications, and labels of the installed system in the cockpits shall be sunlight readable. | D | |
| TBD | All displays, indications, and labels of the installed system in the cockpits shall meet human factors for negative space, readability, natural eye movement for tasks, and consolidated or emphasized data. | I/D | |
| TBD | The installed system shall accommodate all existing T-6A flight, navigation, and radio indications, aircraft caution and warnings, oxygen system, engine, and fuel data, and 5% growth for future indications, plus 80 square inches allocated for alternate information screen area. | I/D | |
| TBD | The installed system shall feature backup modes and flexible instrumentation layout to align with follow-on trainers. The screen configuration must still meet PIPFS requirements for Avionics, only upon failure permitting the ADI and HSI to be off-center. | I/D/T | |
| TBD | The installed system shall be capable of simultaneously displaying GPS and traditional NAVAID course guidance on Horizontal Situation Indicator (HSI). | I/D | |
| TBD | The installed system shall be configurable for multiple layouts. | I/D | |
| TBD | The installed system shall have configurable pilot selectable screen options available for display on the alternate information screen area. Screen options will be determined by Crew Station Working Group after consideration of available beneficial data. | I/D | |
| TBD | The installed system shall be configurable for additional screen options in subsequent upgrades. | I/D | |
| TBD | The displays shall be visible to the flight crew (see Appendix D) throughout the entire range of operational lighting conditions, from direct sunlight to darkness. | D | |
| TBD | MIL-STD-1787 shall be used as a guide for EFIS symbology when FAA regulations do not specify a solution. | As determined by CSWG | |
| TBD | The displays shall incorporate redundancy such that the mission can be completed in the event of any single point failure in the installed system to meet Primary Flight Reference requirements. | I/A/D/T | |
| TBD | The front and rear cockpit displays shall be driven by separate sources to prevent a single point failure. | I/A/D/T | |
| TBD | In the event of a failure in one of the display sources, the other source shall provide all information to both sets of displays. | I/D | |
| TBD | The installed system shall provide the capability for crew members in the front and rear cockpits the ability to independently control the formats of their respective displays. | I/D | |
| TBD | Front and rear cockpit positions shall have the ability to independently control brightness of their respective displays. | I/D | |
| - | 3.6.1.1 Electronic Attitude Director Indicator (EADI) Unusual Attitude Symbology | Info | |
| TBD | The installed system shall change the eyebrow color on the ADI from black to red when passing through 25 degrees of pitch. | I/D | |
| - | 3.6.1.2 Abnormal Fuel Flow Indications | Info | |
| TBD | The installed system shall determine when the fuel flow reading is 800 PPH or more. | I/T | |
| TBD | The installed system shall display an amber box over the numeric fuel flow readout after a sustained exceedance. | I/D | |
| TBD | The installed system shall display a red box over the numeric fuel flow readout when the maximum transient operating limit is exceeded for 5 seconds. | I/D | |
| - | 3.6.1.3 Display Reliability Requirements | Info | |
| TBD | The Display LRUs shall meet or exceed a Mean Time Between Failure (MTBF) of 20,000 hours per HDBK-217Plus, Notice 1, for an Airborne Inhabited Fighter (AIF) aircraft environment [OBJECTIVE]. | A | |
| - | 3.6.2 Data Entry | Info | |
| TBD | The installed system shall provide data entry accessible and suitable for all T-6A instructor pilot, student pilot, and maintenance operations. | I/D | |
| TBD | The installed system shall provide depressible buttons for all data entry. Touchscreen features of the instruments are permissible, provided redundant by other physical means for functions required by this SRD. | I/D | |
| TBD | The installed system shall support pilot control and input without requiring use of handholds or aides. | I/D | |
| TBD | The installed system shall respond to pilot input by an amount acceptable to the pilot. | D | |
| - | 3.6.3 Integrated Computer System | Info | |
| TBD | The installed 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/D | |
| TBD | The installed system shall include memory for debrief use large enough for a maximum flight time of video and audio. [OBJECTIVE] | I | |
| TBD | The installed system shall allow all software field loadable per ARINC 615 or ARINC 615A. | I/D/T | |
| TBD | The integrated computer system shall be designed in compliance to ARINC 653 for partitioning support for all DAL levels. | I/D/T | |
| TBD | The integrated computer system shall support application installation by 3rd parties. | I/D | |
| - | 3.6.3.1 Computer Hardware Resource Utilization Requirements | info | |
| TBD | The Integrated Computer System shall have 50% excess capacity, under heaviest loading, in the critical areas of processor utilization, memory utilization, and data bus and network bandwidth. 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. | A / D | |
| - | 3.6.3.2 Integrated Computer System Reliability Requirements | Info | |
| TBD | The Integrated Computer System LRUs shall meet or exceed a Mean Time Between Failure (MTBF) of 2,500 hours per HDBK-217Plus, Notice 1, for an Uninhabited Fighter aircraft environment [OBJECTIVE]. | A | |
| - | 3.6.3.3 Integrated Computer System Compatibility | Info | |
| TBD | The Installed System shall include industry standard non-proprietary video graphics support for HUD. [OBJECTIVE] | I/D | |
| - | 3.6.3.4 Database Support | Info | |
| TBD | The Installed System shall support Flight Management System databases used by USAF. | I/D | |
| TBD | The Installed System shall support Flight Plans developed by USAF. | I/D | |
| - | 3.6.4 Controlled Flight into Terrain – Prevention (CFIT-P) | Info | |
| TBD | The installed system shall meet SECDEF aircraft mishap reduction goals (ref. SECDEF memo of 22 June 06, Reducing Preventable Accidents) and preserving training capability. | I/A/D/T | |
| TBD | The CFIT-P system shall meet or exceed the requirements of TSO-C151c for TAWS Class C. | I/A/D/T | |
| TBD | The installed system shall meet the minimum TSO-C151c requirements for TAWS Class B system where total life cycle cost is not increased. [OBJECTIVE] | I/A/D/T | |
| TBD | The installed system will provide three main functions; Forward-Looking Terrain Avoidance (FLTA), Premature Decent Alert (PDA) and Ground Proximity Warning. | I | |
| - | 3.6.4.1 CFIT protection capability description | Info | |
| TBD | The installed system shall use real-time aircraft data such as altitude, position, velocities and accelerations in all axes. | T | |
| TBD | The installed system shall recognize an impending collision with terrain. | T | |
| TBD | The installed system shall provide a warning early enough to allow the pilot to safely avoid impact. | A/D | |
| TBD | The installed system shall operate over water, level and descending terrain. | A | |
| TBD | The installed system shall provide protection under all weather and illumination conditions. | A | |
| TBD | The installed system shall provide protection throughout the entire flight regime during all normal aircraft maneuvers, to include takeoff and landing. | A/D | |
| TBD | Additionally, forward looking protection to account for varying/rising terrain should be considered. | I | |
| - | 3.6.4.2 Pilot Vehicle Interface (PVI) capabilities description | Info | |
| TBD | The installed system CFIT-P function shall provide aural, visual, and/or tactile signal warnings. | I/D | |
| TBD | The installed system CFIT-P function shall be audible and intelligible over all other cockpit communications and ambient noise. | I/D | |
| TBD | The installed system CFIT-P function shall convey a sense of urgency and be easily understood by the pilot. | D | |
| TBD | The installed system CFIT-P function Voice warnings shall have the highest priority over other queued voice warnings and tones. | I/D/T | |
| TBD | The installed system CFIT-P function shall persist for entire duration of the warning condition. | I/T | |
| TBD | The installed system CFIT-P function shall require no inputs from the pilot or additional crew members for normal operation. | I/D | |
| TBD | The installed system CFIT-P function shall be capable of pilot initiated suppression of cueing, with default to "ON" at power-up. | I/D | |
| TBD | The installed system CFIT-P function shall provide system output data to the Crash Survivable Recording (CSR) System even when pilot cueing is suppressed. | I/T | |
| TBD | The installed system CFIT-P function shall minimize nuisance warnings. | I/A/D | |
| TBD | The installed system CFIT-P function shall also be directive in nature and provide appropriate actions to take for the given situation. | D | |
| - | 3.6.4.3 Maintainability capabilities description | Info | |
| TBD | The CFIT-P system shall communicate events to the Crash Survivable Recorder (CSR) system. | T | |
| 3.6.4.4 Database Download Requirements | Info | ||
| TBD | The CFIT-P System shall utilize a regularly updated terrain database. | I/D | |
| TBD | The Installed System shall support Terrain and obstruction databases obtainable by the T-6 USAF by the MAJCOM authorized process. | I/D | |
| - | 3.6.4.5 Aural Requirements | Info | |
| TBD | 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. | I/D | |
| - | 3.6.4.6 Visual Requirements | Info | |
| TBD | The CFIT-P System shall provide a visual alert for Terrain Avoidance. | D | |
| - | 3.6.4.7 Reliability Requirements | Info | |
| TBD | The CFIT-P LRU(s) shall meet or exceed a Mean Time Between Failure (MTBF) of 10,000Hrs per MIL-HDBK-217F, for an Airborne Uninhabited Fighter (AUF) aircraft environment. | A | |
| - | 3.6.5 Sensors | Info | |
| TBD | The Installed System shall be resilient in performance during and after aerobatic performance. [OBJECTIVE] | A/D/T | |
| TBD | The sensors shall meet applicable RTCA Minimum Operational Performance Specifications of highest categories for aided and unaided. | I/A/D/T | |
| - | 3.6.6 Navigation | Info | |
| TBD | The installed system shall provide the navigation capability required for FAA compliance in all operational airspace in Visual Meteorological Conditions (VMC) and Instrument Meteorological Conditions (IMC). | I/A/D/T | |
| TBD | The Installed System shall comply with FAA AC 90-100A guidance for Area Navigation (RNAV) routes, Instrument Departure Procedures (DPs), and Standard Terminal Arrivals (STARs); with the equipment performance meeting RNP 1/RNAV 1/RNAV 2. | I/A/D/T | |
| TBD | The Installed System shall comply with FAA AC 90-107 guidance for LPV approach. | I/A/D/T | |
| TBD | The installed system shall be compliant with Air Force Pamphlet 63-129 Air System Development and Sustainment Engineering Processes and Procedures. | I/A/D/T | |
| TBD | The installed system shall comply with RTCA/DO-200A, Standards for Processing Aeronautical Data. Database Integrity will be verified by inspection of Letters of Acceptance from FAA. Refer to Advisory Circular 20-153B, Acceptance of Aeronautical Processes and Associated Databases | I | |
| TBD | The Installed System shall be capable of hybrid approaches with transitions between precision and non-precision guidance. | I/A/D/T | |
| TBD | The Installed System shall be capable of simultaneously displaying GPS and traditional NAVAID course guidance on Horizontal Situation Indicator (HSI). | I/A/D/T | |
| TBD | The Installed System shall be capable of displaying flight planning data, aircraft surveillance data, and growth computing resources for future software increments. | I/A/D/T | |
| - | 3.6.7 Communication | Info | |
| TBD | The installed communication system shall be functionally and ergonomically equivalent to replaced system. The subsections address some of the system interactions across boundaries. | I/D | |
| - | 3.6.7.1 Radios | Info | |
| TBD | The installed system shall provide airborne and ground voice communications using UHF Communication Transceiver. | I/T | |
| - | 3.6.7.2 Radio Management and Control | Info | |
| TBD | The Installed system shall include a radio management capability to select transmitting frequencies, receiving frequencies, monitor health, and the UHF Communications Transceiver, the VHF Communications Transceiver, the Transponder, the Navigation radio, and the DME via ARINC bus. | I/D/T | |
| TBD | The installed system shall have a backup UHF Control Head. | I | |
| TBD | The installed system shall allow pilot to use the UHF/VHF key on the Power Control Lever (PCL). The UHF/VHF key is placed to the up position to select the UHF transmitter and to the down position to select the VHF transmitter. | I/D | |
| TBD | The installed system shall have a dedicated transponder ident switch used to command the transponder to transmit the identification pulse when requested by ATC.” | I/D | |
| - | 3.6.7.3 Audio System / Intercom | Info | |
| TBD | The installed system shall allow both pilots to communicate between each other and the ground crew . | I/D | |
| TBD | The installed system shall allow each pilot to monitor and independently select incoming audio signals, while communicating between cockpits. | I/D | |
| TBD | The T-6A provides a static discharging system to remove static electricity from the aircraft. Static discharging is necessary to prevent damage to equipment and to decrease static in the radio systems. The static discharging system consists of 17 static dischargers located on the trailing edges of the ailerons, elevator, and rudder. The installed system shall not compromise this existing aircraft capability. | I | |
| TBD | The installed system shall allow pilots to select transceiver to monitor on the respective Audio Control Panel. | I/D | |
| The installed system shall allow pilot mute and key interphone by existing buttons on the Power Control Lever (PCL). | I/D |
Figure 3 Power Control Lever Interphone keys
| 3.6.8 CFIT-P Audio | Info | |
| TBD | The installed system shall include an interface between the CFIT-P computing and the Communication System. | I |
| - | 3.6.8.1 Aural Warning Tones | Info |
| TBD | No changes from replaced T-6A warning tones. | D |
| - | 3.6.8.2 Traffic Advisory System | Info |
| TBD | The installed system shall include comply with AC 20-151c for TCAS II with Change 7.1, as a minimum. | I/A/D/T |
| TBD | Capability to select Normal/Below/Above using the existing button on the Pilot Control Stick shall be maintained. | I/D |
| Figure 4 Normal/Above/Below Selector Switch on Pilot Control Stick (FWD & AFT) | ||||
| - | 3.6.9 Standby Instrumentation | Info | ||
| TBD | The installed system shall provide functional redundancy as required for safe civil operation and uninterrupted training mission. | I/T | ||
| TBD | The installed system shall meet PIPFS section 3.4.5.1.10 with a single standby instrument in each cockpit. | I/A/D/T | ||
| TBD | The Standby Instrument shall integrate attitude, heading, turn & bank, altitude, and airspeed indication. | I/D | ||
| TBD | The Standby Instrumentation shall be similar in presentation of data and location as follow on aircraft. | As determined by CSWG | ||
| - | 3.6.10 Emergency Locator Beacon (ELT) | Info | ||
| TBD | The installed system shall provide an emergency location beacon with TSO-c126b certification, TSO-C142b certification, and PMA approval for T-6. | I | ||
| - | 3.7 System External Interface Requirements | Info | ||
| TBD | The Installed System shall provide external interfacing to equipment not replaced but required for operational performance of the requirements in PIPFS and this document. | I | ||
| TBD | The Installed System shall provide interface for off-board communications supported by legacy components being replaced. | I/D | ||
| - | 3.7.1.1 External Interface Identification | Info | ||
| TBD | The installed system shall interface with the external interfaces listed in Table 2 at minimum. The sub-paragraphs that follow provide additional information. | I | ||
| Table 2 External Interfaces | ||||
| External System/Subsystem | Location | |||
| 28 VDC Battery Bus | Onboard | |||
| Engine Data Manager (EDM) | Onboard | |||
| FWD Pilot Control Stick TAS Switch | Onboard | |||
| AFT Pilot Control Stick TAS Switch | Onboard | |||
| Communication Jacks - FWD Pilot, AFT Pilot, and Ground Crew | Onboard | |||
| UHF/VHF key on the FWD Power Control Lever (PCL) | Onboard | |||
| UHF/VHF key on the AFT Power Control Lever (PCL) | Onboard | |||
| FWD Audio Control Panel | Onboard | |||
| AFT Audio Control Panel | Onboard | |||
| Any switch and indicator panels remaining on aircraft interfaced by legacy components being replaced | Onboard | |||
| Primary Pitot | Onboard | |||
| Primary Static | Onboard | |||
| Secondary Pitot | Onboard | |||
| Secondary Static | Onboard | |||
| FWD Pitot / Static Manifold | Onboard | |||
| AFT Pitot / Static Manifold | Onboard | |||
| Flux / Magnetic Compass | Onboard | |||
| Trim Aid Device (TAD) | Onboard | |||
| Power Management Unit (PMU) | Onboard | |||
| Transponder | Onboard | |||
| VHF Communications Radio | Onboard | |||
| VOR/ILS/GS | Onboard | |||
| Crash Survivable Recorder | Onboard | |||
| T-6 Maintenance Device | Off-board | |||
| Air Traffic Control (ATC) | Off-board | |||
| Other Aircraft equipped with ADS-B In | Off-board | |||
| Global Positioning System satellites | Off-board | |||
| Air and Ground UHF Radios for Aeronautical use | Off-board | |||
| Rescue Services | Off-board | |||
| - | 3.7.1.2 External Interface diagram and definitions | Info | ||
| - | 3.7.1.3 Existing T-6A Interfaces | Info | ||
| - | 3.7.1.4 Interface Growth Provisions | Info | ||
| TBD | The installed system shall additional external interface provisions for each integrated computer. [OBJECTIVE] Interfaces of interest are shown in Table 5. This will support T-6A video needs for the life of the aircraft, where training may expand. | I | ||
| Table 5 Interface Growth Provisions | ||||
| Signal Type | Signal Characteristics | Qty | ||
| Input Discrete 28V/OPEN | 28V/OPEN | 6 |
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