2._T-6A_ADS_B_Out_SRD_Final.pdf

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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

ORDER OF PRECEDENCE

3 REQUIREMENTS

SYSTEM REQUIREMENTS

3.1.1 Wiring

SYSTEM FUNCTIONAL REQUIREMENTS

3.2.1 Transponder Control

3.2.2 GPS

3.2.3 Transponder Upgrade Replacement or Addition

SAFETY REQUIREMENTS

3.3.1 System Safety Requirements

3.3.2 Occupational Health and Safety Requirements

3.3.3 Prohibited Hazardous Materials

3.3.4 Fasteners

3.3.5 Toxicity

3.3.6 Security and Privacy Requirements

SYSTEM ENVIRONMENT REQUIREMENTS

3.4.1 Electromagnetic Compatibility

3.4.2 Electromagnetic Interference

3.4.3 Grounding and Bonding

3.4.4 Vibration

3.4.5 Natural Environments

SYSTEM QUALITY FACTORS

3.5.1 Maintainability

3.5.2 Usability

3.5.3 Design and Construction Constraints

PERSONNEL RELATED REQUIREMENTS

3.6.1 Displays

3.6.2 Display Luminance

3.6.3 Display Legibility and Latency

3.6.4 Display Glare and Reflections

3.6.5 Controls and Displays Compatibility

3.6.6 System Status/Failure Annunciation

3.6.7 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 REQUIREMENTS TRACEABILITY

6 APPENDICES

APPENDIX A: ACRONYMS AND DEFINITIONS

APPENDIX B: TEST AND VERIFICATION MATRICES

Table 1 Prohibited Hazardous Materials Table 2 Test and Verification Requirements

1 SCOPE/INTRODUCTION

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

System Overview The T-6A 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 Beechcraft Defense Company, LLC (BDC), the T-6 is a military trainer that replaced the T-37B and is replacing the T-34C trainer aircraft. On May 27, 2010, the Federal Aviation Administration (FAA) published new rules governing airspace and avionics performance requirements that become effective January 1, 2020. The new rules mandate a capability called Automatic Dependent Surveillance-Broadcast Out (ADS-B) (Out). ADS-B (Out) is a cooperative surveillance technology in which an aircraft determines its position via satellite navigation and periodically broadcasts it, enabling it to be tracked. The information can be received by air traffic control ground stations as a replacement for secondary surveillance radar. The data can also be received by other aircraft to provide situational awareness and allow self-separation. The current transponder and Global Positioning System (GPS) navigation receiver on the T-6A are not compatible with ADS-B (Out) functionality. All ADS-B (Out) technical solutions must account for the current GPS navigation receiver remaining in the aircraft and functional while the current transponder must be upgraded to ADS-B (Out) capability or replaced with an ADS-B (Out) capable transponder. The current Radio Management System (RMS) can support all ADS- B (Out) transponder control and display functionality except for the ability of aircrew to enter Flight ID/call sign. The RMS will remain in the aircraft and functional to the degree required to support the ADS-B (Out) technical solution. All ADS-B (Out) 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 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 aircraft to comply with the FAA mandate for ADS-B (Out).

Errors and Omissions Every attempt has been made to ensure the information contained herein is valid at the time of publication. The United States Government (USG) however, 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.

http://en.wikipedia.org/wiki/Satellite_navigation

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 issues of these documents will be those cited in the solicitation or contract.

DOCUMENT ID TITLE DATE

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

13 December 2012

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

11 May 2012

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

11 January 2012

MIL-DTL-

81381C

Detail Specification, Wire, Electric, Polyimide- Insulated, Copper Or Copper Alloy

10 January 2008

MIL-HDBK-

454B

Department of Defense Handbook – General Guidelines for Electronic Equipment

15 April 2007

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

12 December 2014

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 issues of these documents are those cited in the solicitation or contract.

DOCUMENT ID TITLE DATE

FAA Advisory Circular (AC)- 20-165B

Airworthiness Approval of Automatic Dependent Surveillance-Broadcast (ADS-B) Out Systems

7 December 2015

Technical Standard Order (TSO)- C166b

Extended Squitter Automatic Dependent Surveillance

– Broadcast (ADS-B) and Traffic Information Service – Broadcast (TIS-B) Equipment Operating on the Radio Frequency of 1090 Megahertz (MHz)

2 December 2009

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

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

Current as of 26 May

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

Certification Procedures for Products and Parts

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

Identification and Registration Marking

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

General Operating and Flight Rules

Code of Federal Regulations (CFR), Title 14, FAA Part 91, Section 91.225

Automatic Dependent Surveillance Broadcast (ADS- B) Out Equipment and Use

1 January 2011

Code of Federal Regulations (CFR), Title 14, FAA Part 91, Section 91.227

Automatic Dependent Surveillance Broadcast (ADS- B) Out Equipment Performance Requirements

1 January 2014

Air Force Instruction (AFI) 91-203

Air Force Consolidated Occupational Safety Instruction

15 June 2012

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

Occupational Safety and Health Standards Current as of 27 May

Department of Defense Directive (DoDD) 8500.01E

Information Assurance (IA) Current as of 23 April

Department of Defense Instruction (DoDI) 8500.01

Cybersecurity 14 March 2014

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

8 December 2010

NA Joint Primary Aircraft Training Systems (JPATS) Statement Of Work For Automatic Dependent Surveillance–Broadcast Out For The T-6A Aircraft

8 February 2016

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 REQUIREMENTS

System Requirements The installed system shall adhere to the Title 14 CFR FAA Part 23 Airworthiness Standards:

Normal, Utility, Acrobatic, and Commuter Category Airplanes and Title 14 CFR FAA Part 91 General Operating and Flight Rules standards. All avionics equipment utilized to support the ADS-B (Out) effort shall have an FAA Technical Standard Order Authorization (TSOA) for the intended function if required to obtain an STC. The installed system shall not degrade the operation of other systems on the aircraft. The installed ADS-B (Out) system shall meet the requirements listed in Title 14 CFR FAA Part 91, Section 91.225 for aircraft that operate in Class A airspace.

3.1.1 Wiring

MIL-DTL-81381 wiring or any form of Kapton type wiring shall not be used.

System Functional Requirements

3.2.1 Transponder Control

The ADS-B (Out) transponder control and display technical solution must take into account the fact that the Allied King RMS-555 Radio Management System (COBHAM part # 066-04028- 1002), which is currently used for transponder control, will remain in the aircraft. The RMS provides all ADS-B Out transponder control and display functionality except for the ability for aircrew to enter Flight ID/call sign. Both on the ground and in flight, the ADS-B (Out) transponder control technical solution shall retain all current transponder control and display functionality, such as the ability to operate the transponder from either cockpit and both cockpits’ ability to view transponder functions and settings changes made by the other cockpit.

It should be noted that current RMS transponder control functionality is capable of being ‘strapped out’ or disabled.

3.2.2 GPS

An AC 20-165B compliant Wide Area Augmentation System (WAAS) GPS that is FAA-approved for unrestricted navigation in the National Airspace System shall be used for ADS-B functionality. GPS initial satellite acquisition time shall be no longer than 2 minutes. Pitch up to ±20 degrees shall not result in loss of GPS data. Bank up to ±30 degrees for one minute during normal aircraft maneuvering, including holding patterns and turns, shall not result in loss of GPS data. Temporary loss of antenna line of sight to satellites of less than 30 seconds shall not be noticeable to the crew. For signal loss duration times greater than 60 seconds, the reacquisition time shall be no more than 10 seconds.

3.2.3 Transponder Upgrade Replacement or Addition

The current MST-67A transponder shall be upgraded to FAA TSO C166b compliance or replaced with a TSO 166b compliant transponder per AC-20-165B that supports both transponder and ADS-B (Out) functions. At initial power-on, the ADS-B (Out) equipment shall automatically fill the Flight ID registers with the call sign of the previous flight. The system shall allow the flight crew to input an alternate Flight ID (such as a new radio call sign) from either cockpit before or during flight.

Safety Requirements

3.3.1 System Safety 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 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.

3.3.2 Occupational Health and Safety Requirements

3.3.2.1 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. In accordance with AFI 91-203, when Air Force Occupational Safety and Health guidance or safety criteria does not cover a situation, the contractor shall use non-Air Force standards, including national consensus standards, professional safety and health standards, or other Federal agency standards.

3.3.2.2 Occupational Safety Requirements

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

3.3.3 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.

Asbestos Carbon Tetrachloride (=Tetrachloromethane) 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)

Table 1 Prohibited Hazardous Materials

3.3.4 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.

3.3.5 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.

3.3.6 Security and Privacy Requirements

The proposed upgrade shall comply with Information Assurance requirements IAW DoDD 8500.01, Information Assurance (IA), and DoDI 8500.2, Information Assurance (IA) Implementation.

System Environment Requirements

3.4.1 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.

3.4.2 Electromagnetic Interference

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

3.4.3 Grounding and Bonding

All electrical and electronic items which 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.

3.4.4 Vibration

The installed system shall operate in the vibration environments that are commensurate with the required parameters of 3.4.5.1 and all combinations thereof. Vibration sources include, but are not limited to, engine operation and aerodynamic disturbances.

3.4.5 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 3.4.5.1.

3.4.5.1 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.

System Quality Factors

3.5.1 Maintainability

The installed system shall meet the maintainability criteria in MIL-STD-1472G section 5.9 for all normal and emergency 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.

3.5.2 Usability

The installed system shall not degrade operator workload in comparison to that of the current system. Operator workload shall be verified in flight test using the Bedford Workload rating scale.

3.5.3 Design and Construction Constraints

The design and installation of the upgrade shall comply with FAA AC 20-165B.

Personnel Related Requirements

3.6.1 Displays

All electronic displays shall be readable under the full range of ambient lighting from complete darkness to direct sunlight. If modifications are made to the basic displays to improve the sunlight readability characteristics (e.g., brightness, contrast, color difference, etc.) these modifications shall not noticeably reduce the fidelity and legibility of the displays. Display readability shall be met under the following lighting conditions:

• Night - 0 foot candles (fC) ambient lighting,

• Daylight (sun over the shoulder) - 10,000 fC ambient diffuse lighting on the face of the display, and 2,000 fL ambient specular lighting, and Twilight (flying into the sun)

- 500 fL ambient specular lighting incident on the display, and 10,000 fC ambient diffuse lighting directly into the pilot’s eyes.

All flight and mission functions shall be duplicated at both crew stations. The configuration, location, and actuation of all controls and displays shall be identical. Each crewmember shall receive positive indication that the other crewmember has actuated a control. Controls, displays, and instruments requiring visual access shall not be obstructed by other equipment or the glare shield, and shall be viewable from all pilot eye locations. Any labels, placards, etc., that must be read in-flight shall be legible from all pilot positions. Information presented on an electronic display shall conform to the following requirements:

• Noticeable flicker shall not be present in the display.

• Symbology shall conform to existing commercial standards.

o Symbology, graphical and alphanumeric elements shall be clearly visible, readable, and discernible from all crew member eye locations (including off-axis viewing within limited operator mobility constraints) and under all flight conditions.

o Stationary alphanumeric symbols vertically oriented to the crew member shall subtend 15 minutes of arc.

o Non-vertical or nonstationary symbols shall subtend at least 15 minutes of arc.

3.6.2 Display Luminance

The luminance and contrast of all new or modified displays shall support crew operations throughout the flight envelope and under all lighting conditions. The forward and aft instrument panels shall provide luminance such that luminance uniformity does not exceed 2:1 luminance ratio between any two displays. Luminance variation of any display shall not exceed 30 percent.

3.6.3 Display Legibility and Latency

3.6.3.1 Display Legibility

The information displayed on all new or modified displays shall be fully legible, easily interpreted, and free of distracting artifacts such as flicker, jitter, and noise under all environmental, mission and threat conditions.

3.6.3.2 Display Latency

Latency of displayed data shall be limited such that the crew does not perceive a delay between control inputs and the system’s response.

3.6.4 Display Glare and Reflections

There shall be minimal glare internal to each transparency, with minimal interference and restriction of outside visibility from the rear cockpit. Glare shields and display lighting shall be used to minimize glare and reflections on the transparencies and other reflective surfaces.

Interference with external visibility from the rear cockpit, due to glare and reflection from either cockpit shall be minimized.

3.6.5 Controls and Displays Compatibility

All new or modified controls and displays shall be compatible with Nomex Summer Flyers Gloves Type GS/FRP-2.

3.6.6 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 AC 20-165B.

3.6.7 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 ADS-B (Out) modification 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.

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 his 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.

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.

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 REQUIREMENTS TRACEABILITY

Requirements traceability shall be in accordance with the Statement of Work For Automatic Dependent Surveillance-Broadcast (Out) for the T-6A Aircraft where specified.

6 APPENDICES

Appendix A: Acronyms and Definitions AC Advisory Circular

ADS-B

AFB

AFOSH

Automatic Dependent Surveillance – Broadcast Air Force Base Air Force Occupational Safety and Health

ATC

BIT

BDC

CFR

Amended Type Certificate Built In Test Beechcraft Defense Company Code of Federal Regulations

CG

COTS

Center of Gravity Commercial Off The Shelf

EMI

FAA

FAR

fC fL

Electromagnetic Interference Federal Aviation Administration Federal Aviation Regulation Foot Candle Foot-Lambert

GPS

HF

IA

IAW

ID

JPATS

Global Positioning System High Frequency Information Assurance In Accordance With Identification Joint Primary Aircraft Training System

MIL-HDBK Military Handbook

MIL-STD

NAS

NDB

OSHA

RF

Military Standard Naval Air Station Non-Directional Beacon Occupational Safety and Health Administration Radio Frequency

SRD

STC

TSO

TSOA

UHF

USG

VHF

System Requirements Document Supplemental Type Certificate Technical Standard Order Technical Standard Order Authorization Ultra-High Frequency United States Government Very High Frequency

VOR

WAAS

VHF Omnidirectional Range Wide Area Augmentation System

Appendix B: Test and Verification Matrices Table 2: “Test and Verification Requirements” 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 of Table 2 refer to narrative that is for information only requires no verification. Verification methods indicated for each requirement shall not take precedence over FAA-required methods for certification.

Requirement JPATS-Specific Requirement Details

Verification Method Specification Reference

3.1 System

Requirements

The installed system shall adhere to the Title 14 CFR FAA Part 23 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes and Title 14 CFR FAA Part 91 General Operating and Flight Rules standards.

I 14 CFR 23

All avionics equipment utilized to support the ADS-B (Out) effort shall have an FAA Technical Standard Order Authorization (TSOA) for the intended function if required to obtain an STC.

I 14 CFR 23

The installed system shall not degrade the operation of other systems on the aircraft.

T T-6A PIPFS

The installed ADS-B (Out) system shall meet the requirements listed in Title 14 CFR FAA Part 91, Section 91.225 for aircraft that operate in Class A airspace.

T 14 CFR 91.225

3.1.1 Wiring Kapton type wiring shall not be

used. I MIL-DTL-81381

3.2 System

Functional Requirements

3.2.1 Transponder Control

The ADS-B Out transponder control and display technical solution must take into account the fact that the Allied King RMS-555 Radio Management System (COBHAM part # 066-04028- 1002), which is currently used for transponder control, will remain in the aircraft. The RMS provides all ADS-B Out transponder control and display functionality except for the ability for aircrew to enter Flight ID/call sign.

D T-6A PIPFS

Both on the ground and in flight, the ADS-B Out transponder control technical solution shall retain all current transponder control and display functionality, such as the ability to operate the transponder from either cockpit and both cockpit’s ability to view transponder functions and settings changes made by the other cockpit. It should be noted that current RMS transponder control functionality is capable of being ‘strapped out’ or disabled.

3.2.2 GPS

An AC 20-165B compliant Wide Area Augmentation System (WAAS) GPS that is FAA-approved for unrestricted navigation in the National Airspace System shall be used for ADS-B functionality.

I AC 20-165B

GPS initial satellite acquisition time shall be no longer than 2 minutes.

T T-6A PIPFS

Pitch up to ±20 degrees shall not result in loss of GPS data. T T-6A PIPFS

Bank up to ±30 degrees for one minute during normal aircraft maneuvering, including holding patterns and turns, shall not result in loss of GPS data.

Momentary loss of antenna line-of-sight to satellites of less than 30 seconds shall not be noticeable to the crew.

For signal loss duration times of 60 seconds, the reacquisition time shall be no greater than 10 seconds.

T T-6A PIPFS

3.2.3.

Transponder Upgrade Replacement or Addition

The current MST-67A transponder shall be upgraded to FAA TSO C166b compliance or replaced with a TSO 166b compliant transponder per AC-20-165B that supports both transponder and ADS-B (Out) functions.

I AC 20-165B

At initial power-on, the ADS-B (Out) equipment shall automatically fill the Flight ID registers with the call sign of the previous flight.

T AC 20-165B par 3.7.3.1

The system shall allow the flight crew to input an alternate Flight ID (such as a new radio call sign) from both cockpits before or during flight.

T AC 20-165B par 3.7.3.1, 4.2.3

3.3 Safety

3.3.1 System

Safety Requirements

Unless otherwise specified or FAA certification requirements become more stringent, the installed system shall be fail-safe such that no single point of failure or combination of failures with a rate greater than 1X10-7 per 100 thousand flight hours can cause a critical or catastrophic mishap.

A MIL-STD-882E, par 4.3.3

3.3.2 Occupational Safety and Health

3.3.2.1

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. In accordance with AFI 91-203, when AFOSH guidance or safety criteria does not cover a situation, use non-Air Force standards, including national consensus standards, professional safety and health standards, or other Federal agency standards.

I

AFI 91-203

AC 20-165B, 3.1.2

OSHA Standard 29 CFR 1910

3.3.2.2

MIL-HDBK-454 Guideline 1, Safety Design Criteria – Personnel Hazards, will be used as guidance only.

Info

3.3.3 Prohibited Hazardous Materials

The following hazardous materials are prohibited and shall not be contained in any delivered hardware, including commercial off-the-shelf hardware, and shall not be used in the operation or support of the aircraft. (See Table 1)

I T-6A PIPFS

3.3.4. 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.

I T-6A PIPFS

3.3.5. 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.

I OSHA Standard 29 CFR 1910

3.3.6. Security

and Privacy Requirements

The proposed upgrade shall comply with Information Assurance requirements IAW DoDD 8500.01, Information Assurance (IA); and DoDI 8500.2, Information Assurance (IA) Implementation.

A DoDD 8500.01 DoDD 8500.2

3.4 System

Environment

3.4.1.

Electromagneti c Compatibility

The installed system shall operate without performance degradation that detracts from the aircraft training mission during concurrent operation of any combination of the remaining subsystems and equipment.

T AC 20-165B par 4.1.4, 4.2.1

The aircraft shall have radio frequency (RF) compatibility among all antenna-connected subsystems and equipment.

T AC 20-165B par 4.1.4, 4.2.1

3.4.2 Electromagneti c Interference

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

D AC 20-165B par 4.1.1

3.4.3 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.

I

3.4.4 Vibration

The installed system shall operate in the vibration environments that are commensurate with the required parameters of 3.4.5.1 and all combinations thereof.

Vibration sources include but are not limited to engine operation and aerodynamic disturbances.

T

3.4.5 Natural

Environments

The installed system shall meet the requirements of this SRD before, during, and after exposure to the natural and induced environmental conditions defined in section 3.4.5.1.

3.4.5.1 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 defined as follows.

Ground and flight temperature, humidity, solar radiation, in-flight icing, and lightning requirements are as stated in paragraphs 3.4.5.1a, b, c, d and e.

D/A T-6A PIPFS

a. 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.

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

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

d. Lightning protection shall be in accordance with CFR 23 section 23.1306.

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

D/A T-6A PIPFS

3.5 System

Quality Factors

3.5.1 Maintainability

The installed system shall meet the maintainability criteria in MIL- STD-1472, section 5.9 for all normal and emergency conditions.

A/D MIL-STD-1472

The removal and replacement of high failure rate Line Replaceable Units (LRUs) shall not require removal of more reliable LRUs.

D

Removal and replacement of failed LRUs shall not require the use of special tools.

D

Modified equipment shall preclude improper installation, mounting, or connection of LRUs, assemblies, subassemblies, cables, or lines.

A/D

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, are clearly marked as to their correct installation, and cannot cause damage to the equipment.

I

3.5.2 Usability

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

T/A MIL-STD-1472

JPATS Requirement

Operator workload shall be verified in flight test using the Bedford Workload rating scale.

T

3.5.3 Design

and Construction Constraints

The design and installation of the upgrade shall comply with FAA Advisory Circular 20-165B.

I AC 20-165B par 4.1.5

3.6 Personnel-

Related

AC 20-165B par 4.1.5

3.6.1 Displays

All electronic displays shall be readable under the full range of ambient lighting from complete darkness to direct sunlight.

If modifications are made to the basic displays to improve the sunlight readability characteristics (e.g., brightness, contrast, color difference, etc.) these modifications shall not noticeably reduce the fidelity and legibility of the displays.

Display readability shall be met under the following lighting conditions:

• Night - 0 foot candles (fC) ambient lighting,

• Daylight (sun over the shoulder) - 10,000 fC ambient diffuse lighting on the face of the display, and 2,000 fL ambient specular lighting, and

Twilight (flying into the sun) - 500 fL ambient specular lighting incident on the display and 10,000 fC ambient diffuse lighting directly into the pilot’s eyes.

All flight and mission functions shall be duplicated at both crew stations.

The configuration, location, and actuation of all controls and displays shall be identical.

Each crewmember shall receive positive indication that the other crewmember has actuated a flight control.

Controls, displays, and instruments requiring visual access shall:

• not be obstructed by other equipment or the glare shield

• be viewable from all pilot eye locations

Any labels, placards, etc., that must be read in-flight shall be legible from all pilot positions.

Information presented on an electronic display shall conform to the following requirements:

• Noticeable flicker shall not be present in the display.

• Symbology shall conform to existing commercial standards.

Symbology, graphical, and alphanumeric elements shall be clearly visible, readable, and discernible from all crew member eye locations (including off-axis viewing within limited operator mobility constraints) and under all flight conditions.

I T-6A PIPFS

Stationary alphanumeric symbols vertically oriented to the crew member shall subtend 15 minutes of arc.

AC 20-165B par 4.1.5.1

Non-vertical or nonstationary symbols shall subtend at least 15 minutes of arc.

T

T-6A PIPFS

AC 20-165B par 4.1.5.1

3.6.2 Display

Luminance

The luminance and contrast of all new or modified displays shall support crew operations throughout the flight envelope and under all lighting conditions.

AC 20-165B par 4.1.5.1

The forward and aft instrument panels shall provide luminance such that luminance uniformity does not exceed 2:1 luminance ratio between any two displays.

T AC 20-165B par 4.1.5.1 & 4.1.5.5

Luminance variation of any display shall not exceed 30 percent.

T AC 20-165B par 4.1.5.1

3.6.3 Display

Legibility and Latency

3.6.3.1

The information displayed on all new or modified displays shall be fully legible, easily interpreted, and free of distracting artifacts such as flicker, jitter, and noise under all environmental, mission, and threat conditions.

T T-6A PIPFS

AC 20-165B par 4.1.5.1

3.6.3.2

Latency of displayed data shall be limited such that the crew does not perceive a delay between control inputs and the system’s response.

A

T-6A PIPFS

AC 20-165B par 4.1.5.1 & 4.1.5.5

3.6.4 Display

Glare and Reflections

There shall be minimal glare internal to each transparency, with minimal interference and restriction of outside visibility from the rear cockpit.

T

T-6A PIPFS

AC 20-165B par 4.1.5.1& 4.

1.5.5

Glare shields and display lighting shall be used to minimize glare and reflections on the transparencies, and other reflective surfaces.

Interference with external visibility from the rear cockpit, due to glare and reflection from either cockpit shall be minimized.

T JPATS

AC 20-165B par 4.1.5

3.6.5. Controls

and Displays Compatibility

All new or modified controls and displays shall be compatible with Nomex Summer Flyers Gloves Type GS/FRP-2.

T JPATS Requirement

MIL-STD-1472

AFI 11-301 AETC Sup

3.6.6. 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 AC 20-165B.

I/D AC 20-165B PAR 3.7.2.1

3.6.7 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.

T MIL-STD-1472

3.7 Regulatory

and Certification

JPATS Requirement

3.7.1 Certification Requirements

The design and installation of the ADS-B (Out) modification 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.

I

Table 2 Test and Verification Requirements

2.3 Order of Precedence

3.7 Regulatory and Certification Requirements