TH-73A ATS _ PWS Appendix B -- Malfunctions and Systems Requirements.pdf

TH-73A ATS PWS Appendix B – Malfunctions and Systems Requirements

TH-73A

AIRCREW TRAINING SERVICES (ATS)

Appendix B

Malfunctions and Systems Requirements

TABLE OF CONTENTS

1. ENGINE MALFUNCTIONS

2. FIRES

3. FUEL SYSTEM MALFUNCTIONS

4. ROTORBRAKE MALFUNCTIONS

5. HYDRAULIC SYSTEM MALFUNCTIONS

6. FLIGHT CONTROLS MALFUNCTIONS

7. TRANSMISSION MALFUNCTIONS

8. PITOT STATIC SYSTEM MALFUNCTIONS

9. EXTERNAL OPERATIONS

10. ELECTRICAL SYSTEM MALFUCTIONS

11. AVIONICS (ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS))

12. SELECTABLE PARAMETERS

13. INDICATORS

The malfunctions and systems requirements listed in this Appendix shall be detailed during the

Technical Interchange Period. The list in this Appendix includes the desired functions based on

Government knowledge of the selected aircraft at the time of the Request for Proposal. Changes are expected as additional information is provided by the Original Equipment Manufacturer

(OEM) for the aircraft. The changes will be to account for system specific functionality that is either not supportable, or not accounted for properly in this list and will be limited to twenty additional malfunctions or systems requirements.

1. ENGINE MALFUNCTIONS

1.a. Failure of Engine

The Engine Failure should be an instantaneous engine failure that permits the restart of the engine if the pilot has time. Starter malfunctions, or an abnormal start condition may be used to prevent the re-start of the engine at the Instructor

Pilot’s (IP’s) discretion.

1.b. Malfunction of the Fuel Control System

1.c. Overspeed (increase in power)

1.d. Underspeed (decrease in power)

1.e. Gas Turbine Sensor Failure (triggering ENG OUT Light)

1.f. Electronic Engine Control (EEC) Malfunctions

1.f.1. EEC Failure (Instantaneous)

1.f.2. EEC Degraded (Warning Caution Advisory (WCA) Activation)

1.g. Engine Abnormal Starts

1.g.1. Hot Start

1.g.1.a. Normal Initiated Conditions (i.e.: Early application of throttle, low battery, starter failure during start)

1.g.2. Instructor Operator Station (IOS) Induced

1.g.3. Hung start

1.g.4. No start

1.g.5. Rotors Frozen (with corresponding indications)

1.g.6. No Engine oil Pressure Rise (Eng Oil Pump fail / Gauge Indicates Zero)

1.g.7. No Transmission oil Pressure (beyond Specified Nr, could be gauge failed)

1.g.8. Hyd Pressure no rise

1.g.9. Failed Starter

1.g.9.a. Auto-Deactivation Fail

1.g.9.b. No Response from switch (No circuit breaker (C/B) popped)

1.h. Engine Oil

1.h.1. WCA Activation (All Applicable)

1.h.2. Slow Leak (Progressive failure)

1.h.3. Ruptured Lines (Instantaneous)

1.h.4. Progressive Temperature Rise

1.i. Engine Compressor Stall

1.i.1 Latched

1.i.1.a. Able to extend flight

1.i.1.b. Level Flight Capable

1.i.1.c. Non-level flight capable

1.i.1.d. Unable to extend flight

1.i.2 Non-latched

1.j. Engine Droop Compensation Binding

1.j.1. Fixed Bind

1.j.2. Minimal Movement Binding Condition (some useable throw)

1.k. Engine Abnormal Shutdowns

1.k.1. Post Shutdown Fire

1.k.2. No Throttle Response

1.l. NR TRIM switch malfunction

1.l.1. Switch Failure

1.l.2. Range malfunction

1.l.3. EEC Nr trim Lockout Failure

2. FIRES

All actual fire simulations shall produce a visual smoke trail responsive to aircraft maneuvering that can be seen in the Visual System by other linked Flight Training Devices (FTDs). Failures that result in a FIRE indication with no actual fire condition present do not require visible smoke.

2.a. Engine Fire

2.a.1. WCA Faulty Indicator

2.a.2. Progression to Eng Failure (Eng Fire Bottle option if installed using

Latched/Non-latched method)

2.b. Fuselage Fire

Visual indications only, for other linked aircraft, no expectation of realization within Ownship.

3. FUEL SYSTEM MALFUNCTIONS

3.a. Fuel Gauge Control

3.b. Fuel pressure Control

3.c. Fuel Pump Failure (1 and 2)

3.d. Fuel Leak

3.e. Fuel Filter WCA

3.f. Fuel low detector failure

4. ROTORBRAKE MALFUNCTIONS

4.a. Failure (Shutdown focused)

4.b. WCA Activation

4.c. Inflight activation w/ Nr reduction

5. HYDRAULIC SYSTEM MALFUNCTIONS

5.a. Rupture (Instantaneous, each system option)

5.b. Slow Leak Progression (Each system option)

5.c. Progressive Failure (Slow pressure loss Pump failure to imminent transmission failure)

5.d. Hardover

5.e. Individual Servo Malfunction (Pitch/Roll/Yaw)

5.f. Jamming of a Servo Valve (As indicated in NATOPs)

6. FLIGHT CONTROLS MALFUNCTIONS

6.a. Cyclic

6.a.1. Binding (selectable pitch, roll, and all)

6.b. Collective

6.b.1. Binding (Selectable High or Low Power)

6.c. Main Rotor

6.c.1. Vertical

6.c.2. Lateral

6.c.3. Rotor Blade Damper Failure

6.d. Tail Rotor

6.d.1. Driveshaft Failure

6.d.2. Complete Loss of control (Linkage break)

6.d.3. Fixed Pitch

6.d.4. High Frequency Vibrations

6.d.5. Tail-Rotor Chip

6.e. AFCS

6.e.1. Complete Failure

6.e.2. Channel Fail (Selectable individual channels)

6.e.3. Force Trim Failure

6.e.4. SAS Failure

6.e.4.a. By Channel Selection (Pitch/Roll/Yaw)

6.e.4.b. Complete Failure

6.e.4.c. Oscillations (Selectable by Pitch/Roll/Yaw)

6.e.4.d. Disturbances (Selectable by Pitch/Roll/Yaw)

6.e.5. Attitude/altitude/airspeed/yaw/heading Fail (individually Selectable)

7. TRANSMISSION MALFUNCTIONS

7.a. Main transmission

7.a.1. Imminent Transmission Failure

7.a.2. Slow Leak Progressive

7.a.3. Chips

7.b. Accessory gear Box

7.b.1. Chip

7.c. Reduction Gearbox

7.c.1. Chip

7.c.2. Temp High

7.d. Sprag Clutch

7.d.1. Slippage

7.d.2. Seizure

8. PITOT STATIC SYSTEM MALFUNCTIONS

8.a. Static Port Obstruction

8.b. Pitot Heat System Failure (selectable)

9. EXTERNAL OPERATIONS

9.a. Cargo Hook

9.a.1. Indication on IDU when Pulled

9.a.2. Appropriate Aerodynamic Response to load change

9.b. Hoist

No Rear seat hoist functions required, and no Hoist Visual system requirements.

9.b.1. Display Hoist IDU Message when Switch is on.

9.b.2. Hoist CUT ARMD IDU Indication

9.b.3. HOIST CABL LKD IDU Indication, with appropriate thumb wheel response

9.b.4. Cable payout indicator and noise function

10. ELECTRICAL SYSTEM MALFUCTIONS

10.a. Complete Electrical Power Failure

10.b. Generator Failure

10.c. Aux Generator Failure

10.d. Inverter

10.d.1. Failure (Each selectable)

10.d.2. Direct Voltage Control

10.e. Bus Failure(s)

10.e.1. AC BUS 115V

10.e.2. AC BUS 26V

10.e.3. DC BUS 28V

10.e.4. GENERATOR BUS

10.e.5. EMERGENCY BUS

10.e.6. BATTERY BUS

10.f. Battery

10.f.1. Draining Battery

10.f.2. HOT Progression

10.f.3. Battery Level Direct Control

11. AVIONICS (ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS))

11.a. Integrated Display Unit (IDU)

11.a.1. Self-Test Maintenance Sequences

11.a.2. Individual IDU Fails (Selectable)

11.a.3. IDU Degradation

11.a.4. IDU Overtemp (By IDU)

11.a.5. IDS FAN Failure

11.b. RADALT

11.b.1. Failure

11.b.2. Offset

11.c. Flight Director Malfunctions

11.c.1. Individual Component Failures

11.c.2. Individual Function Issues

11.d. GPS/SBAS

11.d.1. RAIM

11.d.2. SBAS/GPS Box Fail (each independently controllable)

11.d.3. Antenna Failure (Each independently controllable)

11.d.4. GPS MISCOMP Alert

11.e. Audio Management Unit Failure

11.f. DME/TACAN

11.f.1. Failed DME only

11.f.2. Failed Tacan only

11.f.3. Full TACAN/DME Failure

11.g. Mode-S/ADS-B in/out (Transponder)

11.g.1. Mode-S Failure

11.g.2. ADS-B In

11.g.2.a. Complete Failure

11.g.2.b. FIS-B Fail

11.g.2.c. TIS-B Fail

11.g.3. ADS-B Out Failure

11.h. Com/Nav Transceiver

11.h.1. VOR/LOC Receiver Failure

11.h.2. Glideslope receiver failure

11.h.3. Marker beacon Failure

11.h.4. DME Failure

11.h.5. VHF Radio Failure (Independently Selectable; ADR-7050 Fail)

11.h.6. UHF Radio Failure (Independently Selectable ADR-7050 Fail)

11.h.7. ADF (Normal/Failed)

11.h.8. GS MISCOMP Alert

11.h.9. LOC MISCOMP Alert

11.i. ACP51 Audio panel

11.i.1. ICS Failure By Station (Pilot/Copilot/Rear Cabin)

11.j. ADAHRS (Normal/Fail)

11.j.1. Each System Selectable

11.j.2. ATT MISCOMP Alert

11.k. ADC

11.k.1. Failure (selectable by system)

11.k.2. ALT MISCOMP Alert

11.l. ESIS

11.l.1. Complete Failure

11.l.2. Air Data Failure

11.l.3. Gyro Failure

11.m. OAT

11.m.1. OAT Sensor Failure

11.n. Doors

11.n.1. DOOR OPEN WCA activation

11.o. Lights

11.o.1. Instrument Panel Lights Failure (Complete)

11.o.2. Instrument Panel Lights Failure (Selectable)

11.o.3. Circuit Breaker Panel Lights Failure

11.o.4. Searchlight Failure (IR and Overt)

11.o.5. Formation Lights Failure

11.o.6. Navigation Lights Failure

12. SELECTABLE PARAMETERS

The Government requires the ability to affect listed systems, indications, and failures on individual IDU screens in accordance with EFIS system architecture.

12.a. Heading

12.a.1. Failure (With HDG Fail Alert)

12.a.2. HDG MISCOMP (By IDU)

12.a.3. Airspeed

12.a.4. VSI

12.a.5. Baralt

12.a.6. Radalt

12.a.7. Needles (individually Selectable)

12.a.8. Synthetic vision

12.a.9. Moving map

12.a.10. Attitude Indication

12.a.11. CDI

12.a.12. Glideslope

12.a.12.a. Failure

12.a.12.b. GS MISCOMP (By IDU)

12.a.13. Traffic

12.a.14. TAWS

12.a.14.a. Failure

12.a.14.b. TAWS MISCOMP (By IDU)

12.a.15. Pilot/Copilot MISCOMPARE

13. INDICATORS

All Aircraft system performance indications shall have an IOS capability to directly manipulate values via direct entry, and/or offset, and/or slider style interface based on Government feedback for each indicator.

For any flight performance or aircraft systems indicator the IOS shall provide the capability to initiate a failure (i.e.: Failed Gauge), or select a value with a range as either an offset from the normal indications or a specific value to display.