Section_J_Atch_3-Aircraft_System_Spec_for_APT_Program.pdf

Solicitation FA8617-17-R-6219 Section J – Attachment 3

Aircraft System Specification for the Advanced Pilot Training (APT) Program

PRF APT-ACFT-1001

9 December 2016

PERFORMANCE SPECIFICATION

SYSTEM SPECIFICATION

for the

ADVANCED PILOT TRAINING (APT)

PROGRAM

AIRCRAFT SYSTEM

Version 1.0

Prepared by:

APT Branch

Training Aircraft Division Mobility Directorate

US Air Force Life Cycle Management Center Wright-Patterson AFB, OH 45433

Aircraft System Specification for the Advanced Pilot Training (APT) Program ii

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Aircraft System Specification for the Advanced Pilot Training (APT) Program iii

TABLE OF CONTENTS

1 SCOPE

Identification System Overview Document Overview

2 APPLICABLE DOCUMENTS

General Government Documents

Specifications, Standards, and Handbooks Other Government Documents, Drawings, and Publications

Non-Government Publications Order of Precedence

3 REQUIREMENTS

Performance and Structural Characteristics

Performance Ground Rules Performance Structures

Avionics Communications Navigation Surveillance Datalink and Network Connectivity

Propulsion System Fuel Consumption Engine Starts Automatic Relight Shutdown Stall-Free Operation Thrust Control Thrust Transients

[RESERVED]

Thrust Demand and Retention

Engine Fire/Overheat Indication Engine Design Service Life Atmospheric Liquid Water Ingestion

[RESERVED]

Distortion Intensity Levels

[RESERVED]

Ice Ingestion

Vehicle Subsystems Fuel Subsystem Aerial Refueling Subsystem Growth Path (Receiver) Environmental Control Subsystem (ECS) Braking Electrical Power Subsystem

Aircraft System Specification for the Advanced Pilot Training (APT) Program iv

Hydraulic Subsystem (if utilized) Crew Systems

Human Performance and Human Engineering Cockpit Configuration Cockpit Stowage Safety Devices and Streamers Aircrew Physical Anthropometrics Anthropometric Accommodation Cockpit Reach Aircrew Workload Aircrew Alerting

Intercommunications Control System (ICS) Cockpit Controls Interior Finishes, Components and Equipment Thermal Contact Hazards Cockpit Displays Interior Lighting Exterior Lighting Interior and Exterior Visibility Aircraft Transparency/Canopy System Aircraft Entry and Exit Escape and Egress System Aircrew Flight Equipment and Pilot Personal Protection Oxygen System Ground Personnel/Maintainer Specific Considerations

Embedded Training Radar System Simulation Defensive Management System (DMS) Weapon Systems Embedded Training Presentation Overlays on SAD Tactical Datalink (TDL) System Simulation Targeting Pod System Simulation Mission Scenario Inputs Synchronized Combat Environment Geographical Area

Declutter Function Recorded Aircraft Information

Military Flight Operations Quality Assurance (MFOQA) Mishap Investigation Data Maintenance Data Mission Debrief Data

Product Support Operational Availability (AO) Materiel Availability (AM) Materiel Reliability (RM) Mean Time Between Failures (MTBF)

Aircraft System Specification for the Advanced Pilot Training (APT) Program v

Fix Rate Mean Time Between Maintenance (MTBM) Mean Time To Repair (MTTR) Turn-Around Time Diagnostics

Mean Flight Hours Between Sortie Aborting False Alarms (MFHBSAFA) Mean Flight Hours Between False Alarms (MFHBFA) Nameplates and Product Marking Maintenance Concept Support Equipment (SE) Maintenance Work Environment Manpower and Personnel

Climatic and Environmental Conditions Natural Climate Induced Environment Electromagnetic Environmental Effects (E3)

Architecture and Security Critical Program Information Cybersecurity Open Systems Architecture Computing Resources ARINC 610 Simulator Compatibility

Utility Attributes Fuel Standards Lubrication Oil Standards Space, Weight, Power and Cooling (SWaP-C) Margins Aircraft Maintenance Safety Protection Equipment (MSPE) Stowage External Stores Environment, Safety and Occupational Health (ESOH) Airworthiness Certification Geographic Intelligence (GEOINT) Barrier Rollover

Hydraulic System Fluid Mission Support

Data Transfer Mission Planning Interface Mission Scenario Generation Mission Debriefing

4 VERIFICATION

General

Overview Verification Methods

Performance and Structural Characteristics Performance Ground Rules Performance Structures

Aircraft System Specification for the Advanced Pilot Training (APT) Program vi

Avionics Communications Navigation Surveillance Datalink and Network Connectivity

Propulsion System Fuel Consumption Engine Starts Automatic Relight Shutdown Stall-Free Operation Thrust Control Thrust Transients

[RESERVED]

Thrust Demand and Retention

Engine Fire/Overheat Indication Engine Design Service Life Atmospheric Liquid Water Ingestion

[RESERVED]

Distortion Intensity Levels

[RESERVED]

Ice Ingestion

Vehicle Subsystems Fuel Subsystem Aerial Refueling Subsystem Growth Path (Receiver) Environmental Control Subsystem (ECS) Braking Electrical Power Subsystem Hydraulic Subsystem (if utilized)

Crew Systems Human Performance and Human Engineering Cockpit Configuration Cockpit Stowage Safety Devices and Streamers Aircrew Physical Anthropometrics Anthropometric Accommodation Cockpit Reach Aircrew Workload Aircrew Alerting

Intercommunications Control System (ICS) Cockpit Controls Interior Finishes, Components and Equipment Thermal Contact Hazards Cockpit Displays Interior Lighting Exterior Lighting

Aircraft System Specification for the Advanced Pilot Training (APT) Program vii

Interior and Exterior Visibility Aircraft Transparency/Canopy System Normal Aircraft Entry and Exit Escape and Egress System Aircrew Flight Equipment and Pilot Personal Protection Oxygen System Ground Personnel/Maintenance Specific Considerations

Embedded Training Radar System Simulation Defensive Management System (DMS) Weapon Systems Embedded Training Presentation Overlays on SAD Tactical Datalink (TDL) System Simulation Targeting Pod System Simulation Mission Scenario Inputs Synchronized Combat Environment Geographical Area

Declutter Function Recorded Aircraft Information

Military Flight Operations Quality Assurance (MFOQA) Mishap Investigation Data Maintenance Data Mission Debrief Data

Product Support Operational Availability (AO) Materiel Availability (AM) Materiel Reliability (RM) Mean Time Between Failures (MTBF) Fix Rate Mean Time Between Maintenance (MTBM) Mean Time To Repair (MTTR) Turn-Around Time Diagnostics

Mean Flight Hours Between Sortie Aborting False Alarms (MFHBSAFA) Mean Flight Hours Between False Alarms (MFHBFA) Nameplates and Product Marking Maintenance Concept Support Equipment (SE) Maintenance Work Environment Manpower and Personnel

Climatic and Environmental Conditions Natural Climate Induced Environment Electromagnetic Environmental Effects (E3)

Architecture and Security Critical Program Information

Aircraft System Specification for the Advanced Pilot Training (APT) Program viii

Cybersecurity Open Systems Architecture Computing Resources ARINC 610 Simulator Compatibility

Utility Attributes Fuel Standards Lubrication Oil Standards Space, Weight, Power and Cooling (SWaP-C) Margins Aircraft Maintenance Safety Protection Equipment (MSPE) Stowage External Stores Environment, Safety and Occupational Health (ESOH) Airworthiness Certification Geographic Intelligence (GEOINT) Barrier Rollover

Hydraulic System Fluid Mission Support

Data Transfer Mission Planning Interface Mission Scenario Generation Mission Debriefing

5 PACKAGING

6 NOTES

Acronyms Definitions

APPENDIX A - APT SYLLABUS MANEUVERS AND MISSION PROFILES

A.1 High G Maneuvering A.2 Flight Endurance Mission Profile A.3 Specialized Undergraduate Pilot Training (SUPT) Profile 1, Transition A.4 Specialized Undergraduate Pilot Training (SUPT) Profile 2, Instruments/Navigation ... 200 A.5 Specialized Undergraduate Pilot Training (SUPT) Profile 3, Low-Level Navigation A.6 Specialized Undergraduate Pilot Training (SUPT) Profile 4, Formation A.7 Specialized Undergraduate Pilot Training (SUPT) Profile 5, Cross-Country A.8 Introduction to Fighter Fundamentals (IFF) Profile 1, Formation A.9 Introduction to Fighter Fundamentals (IFF) Profile 2, Basic Fighter Maneuvers (BFM) 206 A.10 Introduction to Fighter Fundamentals (IFF) Profile 3, Air Combat Maneuvering A.11 Introduction to Fighter Fundamentals (IFF) Profile 4, Basic Surface Attack A.12 Introduction to Fighter Fundamentals (IFF) Profile 5, Surface Attack Tactics A.13 Introduction to Fighter Fundamentals (IFF) Profile 6, Close Air Support A.14 Mission Usage Rates

APPENDIX B - ESCAPE SYSTEM CALCULATIONS

B.1 Dynamic Response Index (DRI) B.2 Multi-axis Dynamic Response Criterion (MDRC) B.3 Head Injury B.4 Neck Injury

APPENDIX C - STRUCTURES

Aircraft System Specification for the Advanced Pilot Training (APT) Program ix

C.1 Structures Tables C.2 Discrete Gust Loads Formulas

C.2.1 Vertical Gusts on Wing and Fuselage C.2.2 Vertical Gusts on Fuselage and Horizontal Tail C.2.3 Lateral Gusts on Fuselage and Vertical Tail

C.3 Power Spectral Technique for Developing Gust Loads

APPENDIX D - TRADE SPACE

3.1.2.1 High G Maneuvering

3.1.2.6 High Angle-of-Attack (AOA) Maneuvering

3.2.3.5 Terrain Warning and Avoidance

3.2.4.5 Ground Based Training Systems (GBTS) Connectivity

3.2.4.6 Ground Support Station (GSS) Connectivity

3.4.2.1 Aerial Refueling Subsystem Full Integration (Receiver)

3.6.6 Targeting Pod System Simulation

3.8.8 Turn-Around Time

LIST OF FIGURES

Figure 3-1, Anti-G Trouser Pressurized Air Supply Figure 3-2, Oxygen Concentrations and Regulator Pressure Schedule Figure 3-3, Mask Breathing Pressure Schedule vs G Loading Figure B-1, Seat and Human Axis Coordinate System Figure B-2, Maximum allowable MDRC value vs. Ejection Seat Figure B-3, Probability of Concussion vs. Rotational and Linear Acceleration Figure B-4, Probability of Neck Injury vs. MANIC and NMIX Values Figure C-1, Ground Turning Lateral Load Factor Spectrum Figure C-2, Gust Factor

LIST OF TABLES

Table 3-1, Speed Range for Onset of Stall Warning for 1-G Stalls Table 3-2, Lift Range for Onset of Stall Warning for Accelerated Stall Table 3-3, GSS Live Monitoring Functions and Display Presentation Table 3-4, Anthropometric Cases 1-7 Table 3-5, Anthropometric Cases 1-7 (Additional Characteristics) Table 3-6, Zone 1 Required Controls Table 3-7, Zone 2 Required Controls Table 3-8, Speech Intelligibility Table 3-9, Additional Speech Intelligibility for Maintainers Table 3-10, Thermal Contact Hazards Table 3-11, Situational Awareness Display (SAD)/Navigation Display Presentation Table 3-12, Escape Envelope Table 3-13, Personal Flight Equipment Table 3-14, Survival Kit Table 3-15, Peak Inspiratory and Expiratory Flows and Mask Cavity Pressures Table 3-16, Breathing Gas Maximum Allowable Contaminant Concentration

Aircraft System Specification for the Advanced Pilot Training (APT) Program x

Table 3-17, Maintainer Lifting and Carrying Limits Table 3-18, Radar Functionality, Modes, and Display Presentations Table 3-19, Target Information Table 3-20, Radar System and Display Controls Table 3-21, DMS Display Presentation and Visual Cues Table 3-22, DMS Modes and Functions Table 3-23, DMS/RWR Threat Audio Table 3-24, Expendables Systems Table 3-25, Weapons Systems Table 3-26, Simulated Tactical Information for the Overlays on SAD Table 3-27, TDL Messaging Table 3-28, Targeting Pod Functionality Table 3-29, Scenario Inputs Table 3-30, High Resolution Areas Table 3-31, Aircraft/SE Interfaces Table 3-32, Maintainer Anthropometric Cases Table 3-33, Cold Day and Hot Day Lapse Rates Table 3-34, Fuel Contaminant Mixture Table 3-35, Loadout Configurations and External Stores Table 3-36, Constructive Targets Table 4-1, Verification Cross Reference Matrix (VCRM) Table 4-2, Breathing Simulator Profiles Table A-1, Mission Usage Rates Table B-1, Natural Frequency and Damping Ratio Coefficients Table B-2, MDRC Dynamic Response Limits per Axis Table B-3, MANIC and NMIX Upper Neck Critical Values based on Body Mass Table C-1, Turbulence Parameters Table C-2, Cumulative Occurrences per Thousand Runway Landings that Load Factor NZ is Experienced at the Aircraft CG

Aircraft System Specification for the Advanced Pilot Training (APT) Program

1 SCOPE 1

This System Specification (SS) establishes the performance requirements for the United States 2 Air Force (USAF) Advanced Pilot Training (APT) Aircraft System component of the APT 3 Program. For the purposes of this SS, the “Aircraft System” includes the associated support 4 elements of the aircraft. 5

Identification 6

This SS is for the Aircraft System, Configuration Item (CI) (TBD). 7

System Overview 8

The APT Program will replace the T-38C used in the USAF’s Specialized Undergraduate Pilot 9 Training (SUPT) advanced phase fighter and bomber (F/B) track, and in the Introduction to 10 Fighter Fundamentals (IFF) course. The APT Program will provide student pilots with the 11 foundational flying skills and core competencies required to transition into current generation 12 F/B aircraft. 13

Document Overview 14

The performance requirements and verification requirements for the APT Aircraft System are 15 documented in sections 3 and 4. Note the performance requirements and verification 16 requirements for the Ground Based Training Systems (GBTS) are documented in a separate SS. 17 This APT Program SS captures and conveys the threshold requirements for the aircraft system 18 (note that the requirements designated as “trade space” identify threshold and objective 19 requirements to be traded as part of the proposed solution definition). This APT Program SS is 20 developed using guidance from DID DI-IPSC-81431A, System/Subsystem Specification Data 21 Item Description, and Military Standard (MIL-STD)-961E, Department of Defense (DoD) 22 Standard Practice for Defense Specifications. In addition to the six (6) major sections of the SS, 23 additional appendices are included as necessary to define the requirements of the aircraft system. 24

Aircraft System Specification for the Advanced Pilot Training (APT) Program

2 APPLICABLE DOCUMENTS 25

General 26

The documents listed in this section are specified in sections 3, 4, or 5. This section does not 27 include documents cited in other sections of this specification or recommended for additional 28 information or as examples. While every effort has been made to ensure the completeness of the 29 document list, document users are cautioned that they must meet all specified requirements of 30 documents cited in sections 3, 4, and 5, whether or not the documents are listed. Where a 31 revision by supplement, amendment, or notice is called out, the entire document up to and including 32 the revision is being referenced. When a revision letter or date is not shown, the issue in effect on 33 the release date of this specification applies. 34

Government Documents 35

Specifications, Standards, and Handbooks 36

The following specifications, standards, and handbooks form a part of this document to the 37 extent specified herein. Unless otherwise specified, the issues of these documents are those cited 38 in the solicitation or contract. 39

Document Number Document Title Issue Date AN6287 Valve - Air High Pressure 3/4 Hex 15 JUL 88 FED-STD-595C (1) Colors Used in Government Procurement 31 JUL 08 JSSG-2006 Aircraft Structures 30 OCT 98 JSSG-2007C Engines, Aircraft, Turbine 10 JUN 11 MIL-STD-129R Military Marking for Shipment and Storage 18 FEB 14 MIL-STD-130N (1) Identification Marking of U.S. Military Property 16 NOV 12 MIL-STD-411F Aircrew Station Alerting Systems 10 MAR 97 MIL-STD-464C Electromagnetic Environmental Effects Requirements for Systems 01 DEC 10 MIL-STD-704F Aircraft Electric Power Characteristics 12 MAR 04 MIL-STD-805B Towing Fittings and Provisions for Military Aircraft, Design

Requirements for

07 SEP 87

MIL-STD-810G (1) Environmental Engineering Considerations and Laboratory Tests 15 APR 14 MIL-STD-882E System Safety 11 MAY 12 MIL-STD-1472G Human Engineering 11 JAN 12 MIL-STD-1474E Noise Limits 15 APR 15 MIL-STD-1530C Aircraft Structural Integrity Program 01 NOV 05 MIL-STD-1568D Materials and Processes for Corrosion Prevention and Control in

Aerospace Weapons Systems

31 AUG 15

MIL-STD-1760E Aircraft/Store Electrical Interconnection System 24 OCT 07 MIL-STD-1787C Aircraft Display Symbology 05 JAN 01 MIL-STD-1797B Flying Qualities of Piloted Vehicles 15 FEB 06 MIL-STD-3009 Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible 02 FEB 01 MIL-STD-3013A Glossary of Definitions, Ground Rules, and Mission Profiles to Define

Air Vehicle Performance Capability

09 SEP 08

MIL-STD-3024 (1) Propulsion System Integrity Program 13 JUL 2015 MIL-DTL-5624W Turbine Fuel, Aviation, Grades JP-4 and JP-5 28 MAR 16

MIL-E-7016F (1)

NOT 2

Electric Load and Power Source Capacity, Aircraft, Analysis of 12 SEP 14

MIL-PRF-7808L Lubricating Oil, Aircraft Turbine Engine, Synthetic Base 02 MAY 97

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Document Number Document Title Issue Date MIL-STD-8591 (1) Airborne Stores, Suspension Equipment and Aircraft-Store Interface

(Carriage Phase)

16 NOV 12

MIL-DTL-23659F Initiators, Electric, General Design Specification for 10 JUN 10 MIL-PRF-23699G Lubricating Oil, Aircraft Turbine Engine, Synthetic Base, NATO Code

Numbers: O-152, O-154, O-156, and O-167

13 MAR 14

MIL-PRF-25017H (1) Inhibitor, Corrosion/Lubricity Improver, Fuel Soluble (NATO S-1747) 04 AUG 11

MIL-DTL-25427B

SUP 1

Coupling Assembly, Hydraulic, Self-Sealing, Quick Disconnect, General Specification for

08 DEC 09

MIL-DTL-25677F Adapter, Cap, and Nozzle, Pressure Lubricating Oil Servicing, Aircraft, General Specification for

03 OCT 14

MIL-A-25896E Adapter, Pressure Fuel Servicing, Nominal 2.5-Inch Diameter 18 JAN 83 MIL-PRF-32239A Coating System, Advanced Performance, for Aerospace Applications 01 OCT 14 MIL-D-81980 (1) Design and Evaluation of Signal Transmission Subsystems, General

Specification for

14 AUG 75

MIL-C-83124 Cartridge Actuated Devices/Propellant Actuated Devices General Design Specification for

30 OCT 69

MIL-C-83125 Cartridges for Cartridge Actuated/Propellant Actuated Devices, General Design Specification for

10 MAR 69

MIL-P-83126A Propulsion Systems, Aircrew Escape, Design Specification for 08 FEB 80 MIL-DTL-83133J Turbine Fuel, Aviation, Kerosene Type, JP-8 (NATO F-34), NATO F-

35, and JP-8+100 (NATO F-37)

16 DEC 15

MIL-PRF-83282D (1) Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Metric, NATO Code Number H-537

10 DEC 97

MIL-DTL-85470B Inhibitor, Icing, Fuel System, High Flash NATO Code Number S-1745 15 JUN 99 MIL-PRF-87260B Foam Material, Explosion Suppression, Inherently Electrostatically

Conductive, for Aircraft Fuel Tanks

02 NOV 06

STANAG-3098 Aircraft Jacking 14 MAY 14 STANAG-3208 Air Conditioning Connections 09 SEP 09 STANAG-3209 Tyre Valve Couplings 21 OCT 14 STANAG-3237 Aperture of Terminal Ring or Link of Aircraft Lifting Slings 25 NOV 82 STANAG-3278 Aircraft Towing Attachments and Devices 05 NOV 14 STANAG-3315 Aircraft Cabin Pressurizing Test Connections 06 OCT 98 STANAG-3372 Low Pressure Air And Associated Electrical Connections for Aircraft

Engine Starting

05 NOV 14

STANAG-3595 Aircraft Fitting for Pressure Replenishment of Gas Turbine Engines with Oil

10 SEP 09

STANAG-3632 Aircraft and Ground Support Equipment Electrical Connections for Static Grounding

20 AUG 14

STANAG-3766 Grease Nipples 08 JUL 97 (Copies of these documents are available online at http://quicksearch.dla.mil)

Other Government Documents, Drawings, and Publications 40

The following other Government documents, drawings, and publications form a part of this 41 document to the extent specified herein. Unless otherwise specified, the issues of these 42 documents are those cited in the solicitation or contract. 43

Document Number Document Title Issue Date AFPD 62-6 USAF Airworthiness 11 JUN 10 AFI 62-601 USAF Airworthiness 11 JUN 10 AFH 63-1402 Aircraft Information Program 19 MAR 01

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Document Number Document Title Issue Date AFI 91-203 Air Force Consolidated Occupational Safety Instruction 15 JUN 12 AFI 91-225 Aviation Safety Programs 26 JAN 15 ATP-3.3.4.2 Air-to-Air Refueling ATP-56 NOV 13 DoDD 5030.61 DoD Airworthiness Policy 24 MAY 13 ATP-3.3.4.5 Air-to-Air (Aerial) Refueling Equipment: Boom-Receptacle System and Interface Requirements

JUN 13

Corrosion Prevention and Control Planning Guidebook for Military Systems and Equipment, Spiral 4

4 FEB 14

OMSC-TCH-01 Open Mission Systems Definition and Documentation Version 1.2 DEC 16 HQ AFFSA Whitepaper: Primary Flight Reference Endorsement

Process

16 OCT 15

TO 00-20-2 Maintenance Data Documentation 01 NOV 12

Non-Government Publications 44

The following documents form a part of this document to the extent specified herein. Unless 45 otherwise specified, the issues of these documents are those cited in the solicitation or contract. 46

Document Number Document Title Issue Date Technical Standard for Future Airborne Capability Environment

(FACE), Edition 2.1

MAY 14

ARINC 610C Guidance for Design and Integration of Aircraft Avionics Equipment in Simulators

SEP 09

ASTM-D1655 Standard Specification for Aviation Turbine Fuels 30 OCT 15 NAS411 Materials Hazardous Management Program 30 SEP 13 NAS411-1 Hazardous Material Target List 30 SEP 13 SAE-AS50881F Wiring, Aerospace Vehicle 29 MAY 15 SAE-ARP5015A Ground Equipment - 400 Hertz Ground Power Performance

Requirements

14 JAN 11

SAE-AS5440A Hydraulic Systems, Aircraft, Design and Installation Requirements For

3 JAN 11

SAE-ARP5825A Design Requirements and Test Procedures for Dual Mode Exterior Lights

6 MAY 16

SAE-AS25486B Connector, Plug, Attachable External Electric Power, Aircraft, 115/200 Volt, 400 Hertz

9 MAR 15

SAE-AS90362A Connector, Receptacle, External Electric Power, Aircraft, 115/200 Volt, 400 Hertz

21 OCT 10

Order of Precedence 47

Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this 48 document and the references cited herein, the text of this document takes precedence. Nothing in 49 this document, however, supersedes applicable laws and regulations unless a specific exemption 50 has been obtained. 51

Aircraft System Specification for the Advanced Pilot Training (APT) Program

3 REQUIREMENTS 52

Definitions in section 6.2 help to clarify and form a part of the requirements in sections 3 and 4. 53 “Italicized text” indicates existence of a definition in section 6.2. 54

Performance and Structural Characteristics 55

Performance Ground Rules 56

Unless otherwise specified, the Performance and Structural Characteristics (section 3.1 and 57 subparagraphs) shall be met using the following performance ground rules: 58

a. Jet A with military additives fuel grade with a density of 6.8 pounds per US gallon and 59 fuel heating value of 18,400 British Thermal Units per pound. 60

b. Two-person aircrew (average nude aircrew member weight of 200 pounds each) wearing 61 USAF Standard Personal Flight Equipment weighing 26.3 pounds (see Table 3-13). 62

c. All aircraft systems/subsystems/components operating normally. 63

d. International Standard Atmosphere model as defined by MIL-STD-3013, Appendix A. 64

e. Standard Configuration (SWaP-C margin requirements met). 65

f. No wind. 66

g. All load factors measured at the aircraft center of gravity (CG). 67

Performance 68

High G Maneuvering 69

SEE APPENDIX D. 70

Instantaneous G-onset Rate 71

The aircraft shall perform high G maneuvering with an instantaneous G-onset rate of at least 6 G 72 per second using the following additional performance ground rules: Fuel weight at 50% 73 (relative to maximum fuel capacity), pressure altitude (PA) equal to 15,000 feet, Airspeed no 74 greater than 0.9 Mach and Standard Day. The aircraft shall immediately start a return to +1.0 G 75 flight by relaxing the stick force/deflection. 76

Average G-onset Rate 77

From a steady +1.5 G trimmed level turn, using an abrupt maximum pitch control step input the 78 aircraft shall traverse from +1.5 G and pass through +7.5 G (or the angle-of-attack for CLmax) in 79

1.7 seconds without over-G or departure. The aircraft shall immediately start a return to +1.0 G 80 flight by relaxing the stick force/deflection. This shall be achieved using the following 81 additional performance ground rules: Fuel weight at 50% (relative to maximum fuel capacity), 82 PA equal to 15,000 feet, symmetric and planned asymmetric loadings, Standard Day, Corner 83 Speed ±50 KEAS. 84

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Negative and Zero G Flight 85

Negative G Flight 86

The aircraft shall fly in negative gravity for at least 10 seconds with unlimited occurrences and 87 without adverse effects to the aircraft and subsystems for all engine thrust levels. 88

Zero G Flight 89

The aircraft shall fly in zero gravity for at least 10 seconds with unlimited occurrences and 90 without adverse effects to the aircraft and subsystems for all engine thrust levels. (Note: Zero 91 gravity is defined as -0.5 to +0.5 G.) 92

Instantaneous Turn Rate 93

The aircraft shall perform instantaneous turn rate of at least 18° per second using the following 94 additional performance ground rules: Fuel weight at 50% (relative to maximum fuel capacity), 95 PA equal to 15,000 feet, Airspeed no greater than 0.9 Mach and Standard Day. 96

Sustained Turn Rate 97

The aircraft shall perform sustained turn rate of at least 12.5° per second using the following 98 additional performance ground rules: level flight, fuel weight at 50% (relative to maximum fuel 99 capacity), PA equal to 15,000 feet, airspeed no greater than 0.9 Mach and Standard Day. 100

High Angle-of-Attack (AOA) Maneuvering 101

SEE APPENDIX D. 102

Flight Endurance 103

The aircraft shall have sufficient fuel capacity to complete the unrefueled training sortie 104 illustrated and defined in section A.2. 105

Takeoff Distance 106

The aircraft (including all Technical Order takeoff and store loadout configurations) shall have a 107 total takeoff distance no greater than 6400 feet using an 8000-foot, hard-surface runway and the 108 following worst case weather conditions for performance calculations: 10 knot tailwind, wet 109 runway with Runway Condition Reading (RCR) of 12, zero runway slope, normal takeoff flap 110 setting, maximum takeoff gross weight, and Density Altitude (DA) equal to 7464 feet (DA 111 represents 97° F, dew point of 38° F, 4093 feet PA). 112

Landing Distance 113

The aircraft (including all Technical Order landing and store loadout configurations) shall have a 114 landing ground roll distance no greater than 7,000 feet that provides for flight operations on an 115 8000-foot, hard-surface runway using the following worst case weather conditions for 116 performance calculations: 10 knot tailwind, wet runway with RCR of 12, zero runway slope, all 117 possible flap settings, 80% fuel weight (relative to maximum fuel capacity), DA equal to 7464 118

Aircraft System Specification for the Advanced Pilot Training (APT) Program feet (DA represents 97° F, dew point of 38° F, 4093 feet PA), and without the use of drag 119 chute(s). 120

Takeoff and Landing in Crosswinds 121

Lateral-Directional Control in Crosswinds 122

The aircraft shall take off and land (including all Technical Order store loadout configurations) 123 with normal aircrew skill and technique in 90º crosswinds, from either side, of velocities up to 25 124 knots (to include gusts) with no worse than Level 2 handling qualities. Roll control forces shall 125 not be so large or so small as to be objectionable to the aircrew. 126

Takeoff Run and Landing Rollout in Crosswinds 127

Yaw and roll control power, in conjunction with other normal means of control, shall be 128 adequate to maintain a straight path on the ground or other landing surface during takeoff run 129 and landing rollout in calm air and in crosswinds up to 25 knots. This requirement applies on 130 dry (RCR of 23) and wet (RCR of 12) runways (including all Technical Order store loadout 131 configurations). Aerodynamic control power alone shall be sufficient to maintain control at all 132 airspeeds above 50 knots. 133

Takeoff Climb Gradient Performance 134

The aircraft (including all Technical Order store loadout configurations, and one-engine 135 inoperative situations for two-engine aircraft) shall provide a climb gradient of at least 200 feet 136 per nautical mile (NM) using the following additional performance ground rules: 8000-foot 137 runway, Instrument Flight Rules (IFR), no wind, DA equal to 7464 feet (DA represents 97° F, 138 dew point of 38° F, 4093 feet PA). 139

General Handling Characteristics (including all Technical Order store loadout 140 configurations) 141

Aircraft Flying Qualities 142

The aircraft shall exhibit flying qualities compatible with the performance, mission, flight 143 phases, and tasks of the APT syllabus maneuvers and mission profiles listed in APPENDIX A. 144

Flying Qualities in Atmospheric Disturbances 145

While complying with 3.1.2.12.1, the aircraft shall exhibit no worse than Level 1 (Satisfactory) 146 flying qualities in calm air and common atmospheric disturbances, and no worse than Level 2 147 (Tolerable) flying qualities in uncommon atmospheric disturbances and with no Pilot-in-the-loop 148 Oscillations (PIO). 149

Student Skill Level Handling Characteristics 150

The aircraft shall have levels of safety, redundancy, performance, and normal and emergency 151 procedures commensurate with the skill levels of students. 152

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Student Fault Tolerant Flight Characteristics 153

The aircraft (including all Technical Order landing and store loadout configurations) shall be 154 tolerant of common student errors. Common student errors shall include, as a minimum, low-155 airspeed departures, exceeding maximum operating speed by 20 knots, and delayed and/or 156 misapplied controls. 157

Control Margin 158

Aerodynamic control power, control surface rate, and hinge moment capability shall provide 159 adequate control margins for restoring moments throughout the combined range of all attainable 160 AOA’s (both positive and negative) and sideslip angles. 161

Safe Termination 162

For all flight conditions, control margins shall be such that all flight phases can be terminated 163 safely and a go-around can be successfully accomplished. 164

Warning and Indication of Approach to Dangerous Flight Conditions 165

When approaching dangerous flight conditions, the aircraft shall provide clear and unambiguous 166 warning and indication of approach to such conditions with sufficient time for the aircrew to 167 recognize the impending dangers and take preventive action. 168

Departure Resistance 169

The aircraft shall be resistant to departure from controlled flight, post-stall gyrations and spins 170 while conducting all APT syllabus maneuvers and the mission profiles listed in APPENDIX A. 171 Departure from controlled flight will only occur with a large and reasonably sustained 172 misapplication of pitch, roll, or yaw controls, or a combination thereof. 173

Recovery from Post-Stall Gyrations and Spins 174

The proper recovery technique(s) shall be readily apparent to the aircrew, be simple and easy to 175 apply under the motions encountered, and provide prompt recovery from all post-stall gyrations, 176 incipient spins, and developed spins. The recovery techniques for post-stall gyrations, incipient 177 spins, and developed spins shall be the same or at least compatible. 178

Stalls 179

The following stall requirements apply for all allowable aircraft loadings and configurations, in 180 straight un-accelerated flight, and in turns and pull-ups with attainable normal accelerations up to 181 the allowable limit load factor. 182

Approach to Stall 183

The onset of a stall warning shall occur within the speed limits of Table 3-1 for 1-G stalls and 184 within the lift limits of Table 3-2 for accelerated stalls. 185

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Table 3-1, Speed Range for Onset of Stall Warning for 1-G Stalls 186

Flight Phase Minimum Speed for Onset of Warning Maximum Speed for Onset of Warning Approach Higher of 1.05 Vs or Vs + 5 knots Higher of 1.10 Vs or Vs + 10 knots All Others Higher of 1.05 Vs or Vs + 5 knots Higher of 1.15 Vs or Vs + 15 knots Notes:

VS = Stall velocity

Table 3-2, Lift Range for Onset of Stall Warning for Accelerated Stall 187

Flight Phase Minimum Lift for Onset of Warning Maximum Lift for Onset of Warning Approach 82% of CL stall 90% of CL stall All Others 75% of CL stall 90% of CL stall Notes:

CL stall = Lift coefficient at stall AOA

Tactile/Physical Cues for Stall Warning 188

The aircraft shall alert the aircrew of the aircraft approach to stall through tactile/physical 189 means (other than aural or visual) consisting of shaking of the cockpit controls or aircraft 190 buffeting, or both. 191

Aural and Visual Stall Warning 192

3.1.2.12.9.3.1 Aural and Visual Cues for Stall Warning 193

The aircraft shall provide both aural and visual cues (via the head-up type display) when the 194 aircraft is approaching a stall. 195

3.1.2.12.9.3.2 Aural and Visual Stall Warning Duration 196

The aircraft shall provide aural and visual stall warnings until recovery from approach to stall. 197

3.1.2.12.9.3.3 Aural and Visual Stall Warning Conditions 198

The aircraft aural and visual stall warnings shall be limited to the following: 199

a. Conditions that replicate landing configurations at all altitudes. 200

b. Any configurations below 5,000 feet Above Ground Level (AGL). 201

Stall Recovery 202

The aircraft shall enable the aircrew to prevent and recover from a stall by simple use of the 203 pitch, roll, and yaw controls without excessive control forces, excessive loss of altitude or build-204 up of speed. 205

Buffet 206

There shall be no aircraft buffet that detracts from mission effectiveness except for stall 207 warning. 208

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Pilot-in-the-loop Oscillations (PIO) 209

The aircraft shall have no tendency for PIO. 210

Failures 211

No single failure of any component or combination of single independent failures shall result in 212 loss of control or flying qualities worse than Level 2 (Tolerable); Special Failure States are 213 excepted. 214

Flight Control System (including all store loadout configurations) 215

Augmentation Systems 216

Augmentation System Operation 217

Operation of stability augmentation and control augmentation systems and devices, including 218 any performance degradation due to saturation, shall not introduce any objectionable flight or 219 ground handling characteristics. 220

Augmentation System Performance Degradation 221

Any performance degradation of stability and control augmentation systems due to saturation of 222 components, rate limiting, or surface deflections, shall only be momentary, and shall not 223 introduce any objectionable flight or ground handling characteristics. 224

Flight Control System Operation 225

For all normal and failure states, flight control system operation shall not cause excessive 226 transients or oscillations due to configuration and mode changes that may induce PIO, flutter, 227 divergence, aeroelastic instabilities or loss of control on the ground and within the flight 228 envelope. 229

Control Surface Displacement Rates 230

Control surface deflection rates shall not limit the ability of the aircraft to perform operational 231 maneuvers in common and uncommon atmospheric disturbances. Control rates shall be adequate 232 to retain stabilization and control in extraordinary atmospheric disturbances. 233

Cockpit Controller Characteristics 234

The aircraft pitch, roll, and yaw control forces and displacement shall be well balanced, not 235 objectionable, and compatible with the aircrew ability to apply simultaneous control in all axes. 236

Cross-Coupling 237

No controller (continuous or discrete) that affects the motion of the aircraft shall create a 238 secondary response that is objectionable (for Levels 1 and 2) or dangerous (for Level 3). 239

Control Centering 240

Pitch, roll, and yaw controls shall exhibit positive centering in flight at any normal trim setting. 241

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Control Free Play 242

The cockpit controls (stick, rudder pedals, and throttle(s)) deadband and hysteresis shall not 243 result in aircrew/aircraft interaction that may cause PIO or loss of control. 244

Control Linearity 245

There shall be no non-linearities within the integrated flight control system that may induce a 246 departure, aircrew coupling, or loss of control. 247

Over-G Condition (including all store loadout configurations) 248

Warnings of Approaching G Limit 249

For aircraft configurations with an analog flight control system, the aircraft shall provide aural 250 warnings of approaching the G limit for all aircraft configurations and weights. 251

G-limiter 252

The aircraft shall have an automatic G-limiter that prevents the aircrew from over-stressing the 253 aircraft above limit loads, throughout the flight envelope, for all aircraft configurations and 254 weights. 255

Over-G Feedback 256

The aircraft shall provide definitive feedback in the form of aural tones and visual cues in the 257 head-up type display when an over-G condition occurs. 258

Structures 259

Design Service Life 260

The design service life of the aircraft fleet shall be sufficient for 22 years of operation, assuming 261 a maximum utilization rate of 30.3 hours per month. The airframe design service life of each 262 individual aircraft shall be 8,000 flight hours for the mission profiles and usage rates contained 263 in APPENDIX A. The takeoff gross weight for each profile shall be at maximum fuel load for 264 the standard configuration as noted for the profiles in APPENDIX A. (Note: Downloading of 265 fuel for a particular mission to reduce the takeoff gross weight is not permitted.) 266

Materials, Processes, and Parts 267

MIL-STD-1530 design process shall be used for the structural design of the aircraft. The finish 268 shall be compatible with corrosion control procedures as described in the Contractor-developed 269 Corrosion Prevention and Control Plan, MIL-STD-1530, and MIL-STD-1568. 270

Fasteners 271

Fastener selection, installation, quality assurance (including screw threads and screw thread 272 quality verification techniques), and joining methods shall be commensurate with the specified 273 airframe operational and support requirements. Fasteners that could result in foreign object 274

Aircraft System Specification for the Advanced Pilot Training (APT) Program damage or loss of the aircraft if they separate from the structure shall have provisions to assure 275 they are either retained on the structure or cannot become loose. 276

Corrosion Prevention and Control 277

The aircraft system shall include corrosion prevention and control measures for all aircraft 278 structures and components as described in both MIL-STD-1530 and MIL-STD-1568 and using 279 the guidance of the Corrosion Prevention and Control Planning Guidebook for Military Systems 280 and Equipment. 281

Paint Scheme 282

The aircraft shall be painted in accordance with (IAW) an approved Air Education and Training 283 Command (AETC) paint scheme using a Non-Hexavalent Chromium paint system that meets the 284 current military aerospace applications for advanced performance requirements (in MIL-PRF-285 32239) for the outer mold line surfaces. 286

General Parameters and Conditions 287

Airframe Configurations 288

The airframe configurations shall encompass those applicable to flight and ground conditions of 289 authorized use and usage missions of the aircraft. 290

Equipment and Stores 291

The airframe shall support and react the loads and motion of all equipment and stores required 292 and expected to be carried by the aircraft. 293

Speeds 294

The ground and flight structural loads of the airframe shall include the level flight maximum 295 speed (VH), the limit speed (VL), the gust limit speed (VG), and all other attainable speeds in 296 conjunction with all configurations, gross weights, centers of gravity, thrust or power settings, 297 altitudes, and usage spectra derived from the mission profiles. 298

Altitudes 299

The ground and flight structural loads of the airframe shall include all attainable altitudes in 300 conjunction with all aircraft configurations, gross weights, centers of gravity, power, speeds, 301 type of atmosphere, and usage derived from the mission profiles. 302

Limit Loads 303

The limit loads, to be used in the analysis of elements of the airframe subject to deterministic 304 design criteria, shall be the maximum and most critical combination of loads that can result from 305 ground and flight use of the aircraft, including maintenance activity and loads whose frequency 306 of occurrence is greater than or equal to 1 x 10-7 per flight. All loads resulting from the 307 requirements of this specification are limit loads unless otherwise specified. 308

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Ultimate Loads 309

Ultimate loads shall be obtained by multiplying limit loads by a factor of safety of 1.5. These 310 ultimate loads shall be used in the design of elements of the airframe and subsystems. The 311 airframe and all subsystems shall not experience catastrophic failure when subjected to ultimate 312 loads. 313

Structural Loads 314

Flight Loads 315

The aircraft shall perform (without degradation to the aircraft structures, components, and 316 systems) to the following flight load factors. 317

Symmetric Maneuver Load Factors 318

The aircraft design limit load factor during symmetric maneuvers shall be -3.0 G to +8.0 G in 319 the aircraft body axis for all speeds up to VL. These load factors apply to the basic flight design 320 gross weight and all lesser flight weights. At weights higher than the basic flight design gross 321 weight, the design limit load factors shall be those that maintain a constant product of the 322 aforementioned limit load factors and the basic flight design gross weight. 323

Asymmetric Maneuver Load Factors 324

The aircraft design limit load factor during asymmetric maneuvers shall be 67% of the positive 325 symmetric load factor to -1 G for speeds up to VL and all flight weights up to and including the 326 basic flight design gross weight. At weights higher than the basic flight design gross weight, the 327 design limit load factors shall be those that maintain a constant product of the aforementioned 328 limit load factors and the basic flight design gross weight. 329

Pressurization 330

The pressure differentials applied in the pressurized portions of the airframe, including fuel 331 tanks, shall be the maximum pressure differentials attainable during flight within the flight 332 envelope, during ground maintenance, and during ground storage or transportation of the 333 aircraft. The following pressurization load factors shall be applied: 334

a. For normal operations (level flight), the maximum pressure differentials attainable shall 335 be increased by a factor not less than 1.33 when acting separately and when in 336 combination with 1 G level flight loads and fuel inertia. The maximum pressure 337 differentials attainable shall include effects of undetectable and uncontrollable pressure 338 regulation system failures occurring with a probability of >10-5 per flight. 339

b. For normal operations (maneuver and gust), the maximum pressure differentials 340 attainable shall be increased by a factor not less than 1.00 when acting separately and 341 when in combination with maximum and minimum flight loads and fuel inertia and shall 342 include effects of undetectable and uncontrollable pressure regulation system failures 343 occurring with a probability of >10-5 per flight. 344

c. For normal ground operations including maintenance, the maximum pressure differentials 345 attainable shall be increased by a factor not less than 1.33. 346

Aircraft System Specification for the Advanced Pilot Training (APT) Program

The primary structure shall withstand the effects of sudden release of pressure. The structure 347 (including nonstructural panels, doors, etc.) shall not cause injury to properly restrained aircrew 348 when such a rapid release of pressure occurs. Failures shall not degrade, damage, or cause to 349 fail any other components of the flight control, fuel, hydraulic, or electrical systems. 350

Discrete Gust Loads 351

Discrete gust loads shall be included in the analysis of the structural capability of the aircraft. 352 For discrete gust analysis, the aircraft shall be considered in straight, level, unyawed flight with 353 the appropriate balancing horizontal tail load and trim vertical tail load. The aircraft shall 354 encounter discrete vertical and lateral gust of design velocity at the specified speeds and critical 355 weights. Design gust velocities shall be the following: 356

a. 66 feet per second (EAS) from 0 to 20,000 feet PA at VG. 357

b. 50 feet per second (EAS) from 0 to 20,000 feet PA at VH. 358

c. 25 feet per second (EAS) from 0 to 20,000 feet PA at VL. 359

d. From 20,000 to 50,000 feet PA, reduce the limit gust velocities linearly from 66 feet per 360 second (EAS) to 38 feet per second (EAS), 50 feet per second (EAS) to 25 feet per 361 second (EAS), and 25 feet per second (EAS) to 12.5 feet per second (EAS). 362

3.1.3.6.1.4.1 Discrete Gust Formulas 363

Aircraft loads derived from the discrete gust approach shall not include possible benefits that 364 may be derived from a stability augmentation system. Loads on aircraft components shall be 365 derived using the gust load formulas specified in section C.2. These loads shall be balanced 366 through the aircraft by linear and rotational inertial forces. 367

Ground Loads 368

The aircraft shall have sufficient structural integrity to operate, takeoff, and land on the ground 369 under the appropriate parameters and conditions in attainable combinations. Required and 370 expected to be encountered combinations of other applicable parameters of section 3.1.3 shall be 371 considered. Lesser values of the following subsections are applicable in determining attainable 372 combinations. 373

Landing Sink Speeds 374

The maximum landing touchdown vertical sink speeds of the aircraft center of gravity (CG) for 375 the airframe and landing gear designs shall not be less than 13 feet per second for the landing 376 design gross weight and 10 feet per second for the maximum landing design weight. 377

Ground Wind Loads 378

3.1.3.6.2.2.1 Mooring 379

The aircraft shall withstand a 70 knot wind from any horizontal direction relative to the aircraft 380 with the aircraft secured in the static attitude using the appropriate equipment (e.g., chocks, gust 381 locks, tie downs) without damage to the aircraft, for all aircraft weights. The aircraft shall be 382 equipped with airworthy permanently installed tie down points. The aircraft shall have 383 provisions for control surface gust locks necessary to meet the above mooring wind requirement. 384

Aircraft System Specification for the Advanced Pilot Training (APT) Program

3.1.3.6.2.2.2 Doors, Canopy, and Windshield 385

The transparency system, storage compartment doors, avionics bay doors, and engine cowling 386 doors shall be capable of being maintained in their open position and shall withstand the loads 387 resulting from a 35-knot steady wind from any horizontal direction combined with a vertical load 388 factor (at the center of gravity) of 1.0 G ±0.5 G and horizontal load factor (in the most critical 389 direction) of 0.5 G’s. In addition, operation of the transparency system under the above 390 conditions shall not result in detrimental effects upon the airframe. 391

3.1.3.6.2.2.3 Crosswinds Loads 392

The loads due to crosswinds at landing, take-off, or touch-and-go shall be those loads resulting 393 from components of surface winds perpendicular to the runway centerline with the values stated 394 in section 3.1.2.10. 395

Repeated Loads 396

All sources of repeated loads shall be considered and included in the development of the service 397 loads spectra and shall not detract from the airframe design service life. Service Loads spectra 398 shall be based on the mission usage profiles in APPENDIX A. Significant sources of repeated 399 loads shall include, but are not limited to, the following six subsections for operational and 400 maintenance conditions. 401

Maneuvers 402

The aircraft maneuver loads spectra shall be generated and based on a flight segmented mission 403 approach utilizing the mission segment data documented in APPENDIX A. Each segmented 404 mission profile shall be analyzed on the basis of the provided mission segment load factors with 405 a rational distribution of weight, center of gravity, speed, altitude, and other significant 406 parameters included. The spectrum shall be proportioned between symmetrical and 407 asymmetrical maneuvers based on the mission mix and load factor exceedance data documented 408 in APPENDIX A. The roll rate exceedance spectrum for asymmetric maneuvers shall be based 409 on 20% of the symmetric maneuver segment. 410

Gusts 411

The gust loads spectra shall be based on the gust environment while flying the specified mission 412 profiles in APPENDIX A and the gust loads spectra shall be determined utilizing the turbulence 413 parameters in Table C-1 and the power spectral technique for developing gust loads as described 414 in section C.3. 415

Landings 416

The landing loads shall be based on the number of landings (touch and go and full stop) 417 documented in APPENDIX A. A rational analysis shall be used to determine and distribute 418 (among the landing sink speed cumulative occurrences) the landing weights commensurate with 419 the mission profiles in APPENDIX A. 420

Aircraft System Specification for the Advanced Pilot Training (APT) Program

Other Ground Loads 421

The taxi, braking, brake release, pivoting, turning, towing, and miscellaneous ground loads 422 spectra shall include vertical, lateral, and longitudinal loads resulting from ground operation at 423 operational weights.