T44 Mods PRF 030074B

PRF 030074B

30 January 2006

SUPERSEDING

PRF 030074A

15 November 2004

PERFORMANCE SPECIFICATION

FOR

T-44C OPERATIONAL FLIGHT TRAINER, DEVICE 2F129C,

AVIONICS UPGRADE

NAVAL AIR SYSTEMS COMMAND

TRAINING SYSTEMS DIVISION

12350 RESEARCH PARKWAY

ORLANDO, FL 32826-3275

PREPARED BY: [Authorizing Signature] DATE:

Jackie Pham

Project Engineer

AIR-4615

APPROVED BY: [Authorizing Signature] DATE:

Ismael Cotto

Branch Head

AIR-4612

Table of Contents

Para./Section Title Page 11.

SCOPE

11.1 Identification

12.

APPLICABLE DOCUMENTS

22.1 Government documents

22.2 Non-Government documents

32.2.1 Referenced drawings

32.3 Order of precedence

33.

REQUIREMENTS

33.1 Functional and performance requirements

33.1.1 Missions

43.1.2 Required states and modes

43.1.2.1 States.

43.1.2.1.1 Operate state

43.1.2.1.2 Freeze state

43.1.2.1.3 Reset state

43.1.2.2 Modes

43.1.2.2.1 Daily Readiness (DRED) test mode

53.1.2.2.2 Free Flight mode

53.1.2.2.3 Initial Conditions (ICs) mode

53.1.3 Performance requirements

53.1.3.1 Simulation performance

53.1.3.1.1 Avionics upgrade performance

63.1.3.1.1.1 Primary flight display

63.1.3.1.1.1.1 PFD bezel hardware

63.1.3.1.1.1.2 PFD controls

73.1.3.1.1.1.2.1 Display Control Panel’s Controls

83.1.3.1.1.1.3 PFD display

83.1.3.1.1.1.4 PFD functional performance

93.1.3.1.1.1.5 PFD trainer unique functions

93.1.3.1.1.1.5.1 Autopilot (AP) Flight Director (FD) button

93.1.3.1.1.1.5.2 AP command bars

93.1.3.1.1.1.5.3 Marker beacon annunciator

103.1.3.1.1.1.5.4 Radar altitude and Decision Height (DH) select window

103.1.3.1.1.1.5.5 Radar altimeter DH select mode

103.1.3.1.1.1.5.6 Tactical Air Navigation (TACAN) auxiliary Nav source

103.1.3.1.1.1.5.7 TACAN bearing indicator

103.1.3.1.1.1.5.8 FMS Nav source select

103.1.3.1.1.1.5.9 PFD AP display annunciations

113.1.3.1.1.1.5.10 PFD FMS status field

113.1.3.1.1.1.5.11 TACAN frequency select

113.1.3.1.1.1.6 PFD interoperability

123.1.3.1.1.1.6.1 PFD navigation radio interoperability

123.1.3.1.1.1.6.2 FMS interoperability

123.1.3.1.1.1.6.3 AP interoperability

133.1.3.1.1.1.6.4 Radio/FMS Nav sources interoperability

133.1.3.1.1.2 Flight Management System

133.1.3.1.1.2.1 FMS bezel hardware

143.1.3.1.1.2.2 FMS functional display

143.1.3.1.1.2.3 FMS functional keypad

143.1.3.1.1.2.4 FMS functional performance

193.1.3.1.1.2.5

193.1.3.1.1.2.5.1 FMS interoperability: fuel flow

193.1.3.1.1.2.5.2 FMS interoperability: PFD

193.1.3.1.1.2.5.3 FMS interoperability: MFD

193.1.3.1.1.2.5.4 FMS interoperability: RTU

193.1.3.1.1.2.5.5 FMS interoperability: AP

193.1.3.1.1.3 Multi-function display

203.1.3.1.1.3.1 MFD bezel hardware

203.1.3.1.1.3.2 MFD bezel replication

203.1.3.1.1.3.3 MFD functional display

203.1.3.1.1.3.4 MFD functional keys, controls, and indicators keys

213.1.3.1.1.3.5 MFD functionality

213.1.3.1.1.3.5.1 MFD moving map display

223.1.3.1.1.3.5.1.1 Maps to be depicted

223.1.3.1.1.3.5.1.2 Topographic terrain

223.1.3.1.1.3.5.1.3 Symbols, text, and graphical depictions

223.1.3.1.1.3.5.1.4 Moving map update rate

223.1.3.1.1.3.5.1.5 Displayed terrain ranges

233.1.3.1.1.3.6 MFD Enhanced Ground Proximity Warning System

233.1.3.1.1.3.6.1 Own aircraft position

233.1.3.1.1.3.6.2 EGPWS annunciators and audible warnings

233.1.3.1.1.3.6.3 EGPWS display performance

243.1.3.1.1.3.7 MFD Traffic Advisory System

243.1.3.1.1.3.8 MFD Radar

243.1.3.1.1.3.9 Storm scope

243.1.3.1.1.4 Autopilot

243.1.3.1.1.4.1 AP panel

243.1.3.1.1.4.1.1 AP Flight Guidance panel

253.1.3.1.1.4.2 AP functionality

263.1.3.1.1.4.3 AP functional modes

263.1.3.1.1.4.4 AP interoperability

263.1.3.1.1.4.4.1 PFD interoperability with the AP

273.1.3.1.1.4.4.2 FMS interoperability with the AP

273.1.3.1.1.5 Radios and Radio Tuning Unit

273.1.3.1.1.5.1 RTU-4200 bezel hardware

283.1.3.1.1.5.2 RTU-4200 radio tuning unit

283.1.3.1.1.5.2.1 RTU-4200 Built-In Test

283.1.3.1.1.5.2.1.1 VHF communication

293.1.3.1.1.5.2.1.2 VHF navigation frequency select

293.1.3.1.1.5.2.1.3 ADF navigation radio

293.1.3.1.1.5.2.1.4 DME receiver operation

303.1.3.1.1.5.2.1.5 Transponder Mode S operation

303.1.3.1.1.5.3 RTU and radios interoperability

303.1.3.1.1.5.3.1 Audio/intercom panels interoperability

303.1.3.1.1.5.3.2 PFD interoperability

303.1.3.1.1.5.3.3

303.1.3.1.1.6 Audio/intercom control panels

313.1.3.1.1.6.1 Audio/intercom bezel hardware

313.1.3.1.1.6.2 Audio/intercom functionality

313.1.3.1.1.6.2.1 Nav radio source select

313.1.3.1.1.6.2.2 Cockpit speaker output

323.1.3.1.1.6.2.3 Headset microphone select

323.1.3.1.1.6.2.4 Volume

323.1.3.1.1.6.2.5 Intercom Voice Operated Transmitter (VOX) sensitivity

323.1.3.1.1.6.2.6 Audio warnings and annunciations

323.1.3.1.1.6.3 Electronic Standby Instrument System (ESIS)

323.1.3.1.1.6.4 ESIS bezel hardware

333.1.3.1.1.6.5 ESIS functionality

333.1.3.1.1.6.5.1 ESIS Display Data and Symbology

343.1.3.1.1.6.6 ESIS interfaces

343.1.3.1.1.7 VHF/UHF radio

353.1.3.1.1.7.1 VHF/UHF radio audio

353.1.3.1.1.7.2 VHF/UHF radio display

353.1.3.1.1.7.3 VHF/UHF radio interoperability

353.1.3.1.1.8 Hand control yoke

363.1.3.1.1.9 Circuit breaker and switch panels

363.1.3.1.1.10 Instruments to be retained and refurbished

363.1.3.1.1.11 Avionics lighting

373.1.3.1.1.11.1 Lighting controls

373.1.3.1.1.12 Instrument panel lay-outs

373.1.3.1.1.13 Simulated malfunctions

373.1.3.1.1.14 Structural modifications

373.1.3.1.1.15 Digital aural cueing and intercom system

373.1.3.1.1.15.1 Digital audio effects cueing system

383.1.3.1.1.15.2 Simulated aural sound cues

393.1.3.1.1.15.3 Trainer intercom system

393.1.3.1.1.15.4 Pilot/copilot communication control

393.1.3.1.1.16 Simulated avionics BIT

393.1.3.1.2 IOS controls and indicators

403.1.3.2 Instructor/Operator Station

403.1.3.2.1 IOS aural cue control

403.1.3.2.2 MFD TAS target control page

403.1.3.2.3 Radar weather control page

403.1.3.2.4 Audio effects and intercom control

433.1.3.2.5 Simulated avionics malfunctions page

433.1.3.3 Off-line debriefing system

433.1.3.4 Motion platform

433.1.3.5 System dynamic response

433.1.3.5.1 Throughput delay

443.1.3.6 Tolerances

443.1.4 Reliability

443.1.4.1 Power supply reliability

443.1.5 Maintainability

443.1.5.1 Maintainability improvements

453.1.6 Environmental conditions

453.1.7 Materials and processes

453.1.7.1 Parts

453.1.7.1.1 Custom designed microelectronic devices

453.1.7.1.2 Power supplies

453.1.7.1.3 Electrostatic Discharge (ESD) sensitive assemblies and equipment

453.1.7.2 Materials

463.1.7.2.1 Flammable materials

463.1.7.2.2 Fungus-inert materials

463.1.7.2.3 Hazardous materials

463.1.7.2.4 Metals

463.1.7.2.5 Ozone-Depleting Substances (ODS)

463.1.7.2.6 Wood products

473.1.7.2.7 Radioactive material

473.1.7.3 Processes

473.1.7.3.1 Protective finishes and coatings

473.1.7.3.1.1 Painting, and preparation for

473.1.7.3.1.2 Nonskid surfaces

473.1.7.3.2 Corrosion prevention

473.1.8 Electromagnetic radiation

483.1.9 Nameplates and product markings

483.1.9.1 Units, assemblies, subassemblies, and parts

483.1.9.1.1 Units

483.1.9.1.2 Auxiliary units

493.1.9.1.3 Plug-in assemblies

493.1.9.1.4 Fuse holders

493.1.9.1.5 Controls and indicating devices

493.1.9.1.6 Sockets

493.1.9.1.7 Printed wiring boards

503.1.9.1.8 Terminals, terminal blocks and strips

503.1.9.2 ESD marking

503.1.9.2.1 ESD sensitive assemblies

503.1.9.2.2 ESD sensitive equipment

513.1.9.2.3 External equipment terminals

513.1.9.3 Fluid and gaseous lines

513.1.9.4 Reference designators

513.1.9.4.1 Cable and wire markings

523.1.9.4.2 Cable marking method

523.1.9.4.3 Cable marking information

523.1.9.4.4 “W” and “P” cable designations

523.1.9.4.5 To-from designators

523.1.9.4.6 Assembly/part number

523.1.9.5 CaNDI marking

543.1.9.5.1 CaNDI identification, nameplates, and labels

543.1.9.6 Warning marking for simulated and modified equipment

543.1.9.6.1 Trainer-use-only identification

543.1.9.7 Safety markings

543.1.10 Interchangeability

553.1.11 Safety

553.1.11.1 Emergency equipment power disconnect

553.1.11.2 Temperature sensing alarms

553.1.11.3 Equipment energized from multiple power sources

553.1.12 Human engineering

563.1.13 Computer resource requirements

563.1.13.1 Computational system

563.1.13.1.1 Trainer computational system

563.1.13.1.1.1 Trainer computer system hardware

563.1.13.1.1.1.1 Computer processing requirements

563.1.13.1.1.1.2 Computer operations control function

563.1.13.1.1.1.3 Peripherals

563.1.13.1.1.1.3.1 Compatibility

563.1.13.1.1.1.3.2 Classified information

563.1.13.1.1.1.4 Open system architecture

563.1.13.1.1.1.4.1 Scaleable architecture

563.1.13.1.1.1.4.2 Hardware failure

563.1.13.1.1.1.5 Spare requirements

563.1.13.1.1.1.5.1 Spare memory

563.1.13.1.1.1.5.2 Spare mass storage

563.1.13.1.1.1.5.3 Spare processing capacity

563.1.13.1.1.1.5.3.1 Synchronous real-time functions

563.1.13.1.1.1.5.3.2 Non-synchronous functions

563.1.13.1.1.1.5.4 Spare I/O capacity

563.1.13.1.2 Trainer computer system software

563.1.13.1.2.1 Operating system

563.1.13.1.2.2 Application software

563.1.13.1.2.2.1 Application software integrity

563.1.13.1.2.3 Diagnostic software

563.1.13.1.2.3.1 Computer and peripheral diagnostic programs

563.1.13.1.2.3.2 DRED program

563.1.14 Logistics

563.1.14.1 Maintenance

563.1.14.1.1 Maintenance concept

563.1.14.1.1.1 Levels of maintenance

563.1.14.1.2 Qualitative maintainability requirements

563.1.14.1.2.1 Special tools

563.1.14.1.2.2 Built-In Test (BIT)

563.1.14.1.2.3 Lamps

563.1.14.1.2.4 Blown fuse indicator lights

563.1.14.1.2.5 Utility receptacles

563.1.14.1.2.6 Maintenance intercommunications system

563.1.14.1.2.7 Accessibility

563.1.14.1.2.7.1 Cable slack

563.1.14.1.2.7.2 Parts

563.1.14.1.2.7.3 Assemblies

563.1.14.1.2.7.4 Wiring board extender cards

563.1.14.1.2.7.5 Covers, panels, and doors

563.1.14.1.2.7.6 Handles

563.1.14.1.2.7.7 Replacement of modular assemblies

563.1.14.1.2.8 Circuit cards

563.1.14.1.2.8.1 Circuit card connectors

563.1.14.1.2.8.2 Circuit card connectors, power and ground

563.1.14.2 Facilities and facility equipment

563.1.14.2.1 Facility power

563.1.14.2.1.1 Power-line monitoring/protection

563.1.14.2.1.1.1 Under/overvoltage

563.1.14.2.1.1.2 Voltage transients

563.1.14.2.1.1.3 Under-frequency

563.1.14.2.1.1.4 Frequency transients

563.1.14.2.1.1.5 Power interruption

563.2 Interface requirements

563.2.1 External interface requirements

563.2.2 Computer hardware requirements

563.2.3 Computer communications requirements

563.3 Construction

563.3.1 Workmanship

563.3.1.1 Cleaning

563.3.1.2 Threaded fasteners

563.3.1.3 Wiring

563.3.1.4 Shielding

564.

VERIFICATION

564.1 Methods of verification

564.2 Classes of verifications

564.3 Inspections and tests

564.3.1 Visual inspections

564.3.2 Functional tests

564.3.2.1 Computer system tests

564.3.2.2 Software cold start

564.3.2.3 Trainee station

564.3.2.4 IOS tests

564.3.2.5 Motion system tests

564.3.2.6 Ancillary items tests

564.3.2.6.1 Structural changes verification

564.3.2.6.2 Electrical tests

564.3.2.6.3 Grounding and grounding systems test

564.3.2.7 DRED program test

564.3.3 Operation and mission tests

564.3.3.1 Training scenarios

564.3.3.1.1 Free play

564.3.3.2 Malfunctions tests

564.3.3.3 Database correlation tests

564.3.4 Product assurance tests

564.3.4.1 Thermal survey

564.3.4.2 ESD tests

564.3.4.3 Reliability assessment

564.3.4.4 Maintainability assessment

564.3.4.5 Nonfunctional examinations

565.

PACKAGING

566.

NOTES

566.1 Definitions

566.1.1 Chargeable failures

566.1.2 Commercial Items

566.1.3 Control Drawing

566.1.4 Interchangeable item

566.1.5 Non-chargeable failures

566.1.6 Non-developmental Items (NDI)

566.1.7 Non-relevant failures

566.1.8 Ozone-Depleting Substance (ODS)

566.1.9 Relevant failures

566.1.10 Scheduled Maintenance

566.1.11 Trainer Peculiar Equipment (TPE)

566.1.12 Unscheduled On-site Maintenance

566.1.13 Verification methods

566.1.13.1 Analysis

566.1.13.2 Demonstration

566.1.13.3 Examination

566.1.13.4 Test

FIGURES

Fig. No.

Title Page

48Figure 1.

Unit ID Plate

50Figure 2.

ESD Symbols

53Figure 3.

Examples of Cable Markings

55Figure 4.

Multiple Power Source Label

TABLES

Table Title Page

2Table I.

Referenced Documents, COTS Manuals

7Table II.

PFD Controls

7Table III.

DCP Controls

8Table IV.

PFD Graphics

10Table V.

PFD AP Display Annunciators and Symbols

11Table VI.

FMS Annunciator and Symbols on PFD

14Table VII.

CDU Display Color Table

15Table VIII.

FMS Functional Task List

20Table IX.

MFD Bezel

21Table X.

Required MFD Keys, Controls, and Indicators

24Table XI.

EGPWS Graphics

25Table XII.

Flight Control Panel Controls

26Table XIII.

AP Modes

27Table XIV.

Radio Management Components

31Table XV.

Navigation Radio Outputs Select Switches

33Table XVI.

ESIS Display Data and Symbology

34Table XVII.

Bezel Elements

36Table XVIII.

Circuit Breaker and Switch Panels

41Table XIX.

Intercom Functionality

Performance Specification

For T-44C Operational Flight Trainer, Device 2F129C, Avionics Upgrade

1. SCOPE

This specification establishes the performance and verification requirements for the modifications to be completed on the T-44A, Device 2F129A, Operational Flight Trainer (OFT) located at Naval Air Station, Corpus Christi, Texas. The scope of this specification is limited to the following trainer modifications:

a. Upgrade cockpit to reflect the same cockpit configuration associated with the upgraded avionics and Electronic Flight Instrument Systems (EFIS) in the actual aircraft.

b. Upgrade of the existing audio effects system in order to provide a more realistic replication of aircraft ambient sounds and improved audible annunciations of all aircraft systems.

c. Upgrade the existing Device 2F129A Intercom system to reflect functionality as found in the aircraft systems and facilitate improved communications between the pilot, instructor, and observer. Wire and install intercom phone, provided as Government Furnished Item, securely inside the trainer.

d. Update the existing Instructor Operator Station (IOS) as required to facilitate effective instructor interaction with the upgraded cockpit and communications systems.

e. Upgrade the off line de-briefing system to reflect the upgraded cockpit and associated avionics systems.

f. Relocate various existing electrical systems in order to enhance trainer maintainability.

The trainer currently includes a cockpit with seating, instruments, and controls for a pilot and a copilot, and an IOS. The existing trainer configuration includes a digital electronic control loader system and a hydraulic motion base, which will remain in their original configuration.

1.1 Identification

This specification and associated aural cueing and avionics systems’ replacement affects Device 2F129A OFT, Serial Number (S/N) 1 through S/N 5. These trainers are used to train Navy, Air Force, and Foreign pilots in the operation, procedures, and flight of the T-44C twin-engine turboprop aircraft. For purposes of this specification, the terms Device 2F129C, OFT, trainer, training system, and training device are equivalent.

2. APPLICABLE DOCUMENTS

The following documents of the exact issue listed form a part of this specification to the extent specified herein. This specification is designated as a first tier document. The documents referenced directly in this specification are designated as second tier documents and are considered part of this specification to the extent specified herein. Documents referenced in successive tiers are not part of this specification and are to be used for guidance only.

2.1 Government documents

Federal Regulations

Occupational Safety and Health Administration (OSHA)

2.2 Non-Government documents

American National Standards Institute (ANSI)

Electronic Industries Alliance (EIA)

Institute of Electrical and Electronics Engineers (IEEE)

IEEE 200-1975

Revision 1988

Table I below lists the Commercial Off-The-Shelf (COTS) Manuals referenced in section 3 of this specification.

Table I.

Referenced Documents, COTS Manuals

2.2.1 Referenced drawings

ARINC, Incorporated

2.3 Order of precedence

In the event of a conflict between the text of this specification and the references cited herein, the text of this specification takes precedence. Specific operability descriptions described in COTS manuals associated with specific units are to be used as reference only within this specification. Nothing in this specification, however, supersedes applicable laws and regulations, unless a specific exemption has been obtained.

3. REQUIREMENTS

The following sections describe the requirements for the avionics and aural cueing upgrade of the Device 2F129C. The specified requirements shall apply to the hardware and software associated with the avionics and aural cueing upgrade. For purposes of this specification, the term Design Basis Aircraft (DBA) shall be defined as the T-44C aircraft Tail Number 0985.

3.1 Functional and performance requirements

The T-44C avionics and aural cueing upgrade for Device 2F129C shall consist of the replacement of primary systems listed below. Unless otherwise specified in this specification, the functionality of the upgraded trainer shall be based upon the functionality of the DBA defined above. This shall include an upgrade of the IOS and off-line debriefing system in order to accommodate the functionality of the following primary subsystems:

a. Cockpit avionics

b. Aural cueing

c. Audio communications/intercom system

3.1.1 Missions

Device 2F129C is an integral part of Student Navy and Air Force Aviator (SNA) training. Device 2F129C shall provide basic operation, procedures, and multi engine flight training to the Navy, Air Force, and foreign pilots.

3.1.2 Required states and modes

The replacement of the aural cueing and avionics systems shall not affect the current OFT operation states and modes associated with the trainer. Device 2F129C shall operate in multiple states and modes as stated herein.

3.1.2.1 States.

Device 2F129C shall operate in the system states specified in the following sections.

3.1.2.1.1 Operate state

In the Operate state, the Device 2F129C simulation computations shall begin at initialization or from the instant of deactivation of the previous Freeze.

3.1.2.1.2 Freeze state

The Freeze state, when initiated, shall halt mission time and maintain the pre-Freeze state of all displays, indicators, and lights of the trainee station. In addition, computer-controlled outputs shall remain fixed and shall retain all indications and system status conditions that existed at the time of Freeze. In the Freeze state, Device 2F129C shall provide the instructor with the means to relocate the mission aircraft to different geographic position, altitude, airspeed and heading. Relocation of the mission aircraft shall cause the trainee station instruments and indicators to update to the new parameters. Deactivation of the Freeze (Operate) shall restore the system to the conditions that existed at the time of the Freeze or to the new conditions with no abrupt motions and resume real-time simulation and display computations. During Freeze state, the motion system shall assume the neutral position. Control forces shall be abated at a safe rate. Any release from Freeze or initialization shall cause the flight controls and motion cueing devices to activate at a safe rate. IOS display monitor shall show an indication of the Freeze state.

3.1.2.1.3 Reset state

When Reset state is selected, the switch-indicator shall flash, the mission clock shall return to time zero, start of the mission, and the simulation computer system shall return to the set of initial conditions entered before the start of the mission plus any modified parameter(s), if applicable. After Reset processing is complete, an automatic transition to Freeze shall be made. The crash override shall be modified to retain the state set prior to selecting Reset. Currently, the trainer automatically resets the crash override to the off state. All required Reset processing shall be accomplished by a single Reset selection.

3.1.2.2 Modes

Device 2F129C shall operate in the following modes.

3.1.2.2.1 Daily Readiness (DRED) test mode

The avionics and aural cueing upgrade shall not affect the functionality of the existing DRED test mode. The DRED test mode shall provide maintenance personnel the means to check the operation of all possible input and output functions between the trainer cockpit and the host computer system.

3.1.2.2.2 Free Flight mode

In the Free Flight mode of operation, Device 2F129C shall provide training under the control of an instructor or unsupervised crew training. When under trainee control, the Free Flight mode shall provide the means to select an established set of initial conditions only. When under instructor control, the Free Flight mode shall provide the means to:

a. Select, modify, and insert initial condition data sets.

b. Select procedures (normal, emergency, and special) for display and monitoring.

c. Select malfunctions for discrete and random insertion or removal from the scenario.

d. Select navigation display formats.

3.1.2.2.3 Initial Conditions (ICs) mode

The avionics and aural cueing upgrade shall not affect the functionality of the trainer ICs mode.

3.1.3 Performance requirements

The avionics and aural cueing upgrade shall provide the performance characteristics described in the following sections. The performance characteristics described in this specification shall only apply to those systems and subsystems that are to be upgraded and all existing systems and subsystems that are directly and indirectly affected by the avionics and aural cueing upgrade.

3.1.3.1 Simulation performance

The upgraded Device 2F129C shall provide the pilot and co-pilot a realistic spatial, visual, audible, and tactile cues required to immerse the pilot and co-pilot in the simulated environment without the use of a Out The Window (OTW) visuals system. The upgraded Device 2F129C shall provide the pilot and co-pilot with the appropriate instrument response and aural cueing response to control inputs, aircraft attitude, position in space, and velocity, which shall be no less accurate than those currently simulated in the existing Device 2F129 and the requirements stated herein.

3.1.3.1.1 Avionics upgrade performance

The upgraded cockpit avionics system shall provide the pilot and co-pilot with functional replications of the aircraft avionics systems through stimulation of actual avionics system or simulation of avionics systems using replicated or actual system components. The fidelity of the simulation of the upgraded cockpit avionics shall provide the pilot and co-pilot with the perceptional cues, which shall reflect the same fidelity and configuration as the actual aircraft, and within the physical limitations of the existing trainer, unless otherwise stated. The following requirements shall apply:

a. The Avionics upgrade shall consist of the replacement of existing primary flight instruments with separate Primary Flight Displays (PFDs) and Display Control Panel (DCP) in the pilot and co-pilot positions. The existing Flight Management System (FMS) currently located in the pedestal shall be replaced with a new FMS located in the center pedestal. A Multi-Function Display (MFD) shall be added to the center of the forward instrument panel and shall provide the pilot and co-pilot with a color moving map and terrain display associated with Enhanced Ground Proximity Warning System (EGPWS). Frequency selection of communications and navigation radios shall be accomplished through an integrated Radio Tuning Unit (RTU), and remote tuning shall be accomplished through the new FMS. A new configuration of the autopilot system shall be provided with the autopilot Flight Guidance Panel (FGP). Audio control shall be functionally replicated through separate pilot and co-pilot audio control panels, which shall replicate those located in the pedestal in the new aircraft configuration. Other panels such as circuit breaker panels shall be modified to reflect the panels associated with the upgraded avionics.

b. The existing offline de-briefing system shall be upgraded to provide an active depiction of the instrument panel with a dynamic depiction of the PFD and a depiction of the integrated RTU radio control head showing a replay of all radio status and frequencies selected. The IOS shall provide the instructor with a dynamic depiction of the FMS display as well as various malfunction select pages.

c. The functional characteristics of each avionics unit and its interoperability with other units from the perspective of the flight crew shall be in accordance with (IAW) the following subparagraphs. The functional and performance characteristics described in the following sections also rely on functional descriptions provided in the referenced pilot’s manuals associated with the individual unit being designed, and an updated NATOPS and system manuals for the T‑44C aircraft.

3.1.3.1.1.1 Primary flight display

The new PFD shall provide the same functionality as the Adaptive Flight Display, Part Number (PN) 822-1084-051, for the pilot and co-pilot positions. All functions of the PFD shall be provided with the same interoperability characteristics with other avionics units as found in the actual aircraft. Additional PFD controls and settings shall be selected through the display control panels (DCPs), which shall be adjacent to the PFDs. All functions and graphical representations associated with the actual PFD shall be referenced IAW the depictions shown in the Rockwell Collins Operator’s Guide 523-0790065 and Rockwell Collins System Manual 523-0790063 as well as additional functional display features which may be unique to the PFD configuration as found in the T-44C aircraft.

3.1.3.1.1.1.1 PFD bezel hardware

The PFD Bezel shall be dimensionally accurate to within 0.125 inches. The Bezel shall have the same surface contours and color as the actual aircraft unit. The bezel shall be mounted in a portrait orientation in the same location relative to the control yoke as the actual aircraft as depicted in aircraft Drawing No. 39-11-8000-00.

3.1.3.1.1.1.2 PFD controls

The PFD control buttons and knobs shall have identical tactile characteristics as the actual aircraft PFD. Edge lighting of the controls shall have the same color and adjustable intensity as the actual unit. The PFD controls shall be provided IAW the “Controls and Indicators” section of the Rockwell Collins Operator’s Guide. PFD controls shall include the controls listed in Table II below.

Table II.

PFD Controls

3.1.3.1.1.1.2.1 Display Control Panel’s Controls

The DCP, in conjunction with the bezel-mounted switches on the flight displays, shall provide the primary pilot interface to control the flight displays. When a DCP function switch is pushed, the PFD shall show the appropriate menu as displayed in the actual aircraft’s unit. While the menu is in view, the PFD line select keys shall be active. The DCP controls shall be provided IAW the “Controls and Indicator” section of the Rockwell Collins Operator’s Guide. DCP controls shall include the controls listed in Table III below.

Table III.

DCP Controls

NOTE: While the controls listed in Table II and Table III above are to be replicated, the functionality of the controls and resultant video indications are specified in 3.1.3.1.1.1.4.

3.1.3.1.1.1.3 PFD display

The display shall provide a true color image, which shall have a minimum resolution of 800 by 600 pixels. The dimensions of the active display (viewable area) shall be 8 inches wide by 10 inches high. The brightness of the display shall be independently controllable from the display control rocker switch located on the PFD bezel.

3.1.3.1.1.1.4 PFD functional performance

The display shall provide all graphical representations of all functions of the PFD. The graphics display shall provide an update rate of 30 Hertz (Hz) as a minimum. The refresh rate of the display shall be a minimum of 60 Hz. The PFDs shall include dynamic graphical representations listed in Table IV below.

Table IV.

PFD Graphics

3.1.3.1.1.1.5 PFD trainer unique functions

The functions described in this section are functions that shall be provided, but are not described in the Rockwell Collins Operator’s Guide, and are specific to the upgraded T-44C aircraft.

3.1.3.1.1.1.5.1 Autopilot (AP) Flight Director (FD) button

A source select button shall be functionally replicated on the Flight Guidance Panel (FGP) as in the actual aircraft. The buttons, marked “FD”, located at each end of the FGP, shall provide the means for the pilot and co-pilot to select the PFD that is to be coupled to the AP when the NAV or APPR functions are selected on the Flight Guidance Panel.

3.1.3.1.1.1.5.2 AP command bars

AP command bars shall be depicted on each PFD and shall reflect the commanded aircraft roll and pitch required to maneuver the aircraft to a specific heading or vertical profile as dictated by a Navigation (Nav) source or manual selection. The command bars shall only be activated on the coupled PFD and shall only be active if the AP is in the navigation or approach mode. The shape and color of the command bar symbol shall replicate the actual aircraft command bars.

3.1.3.1.1.1.5.3 Marker beacon annunciator

A colored text box shall be displayed on the PFD, which shall reflect the proximity of the aircraft to an outer, middle, and inner marker beacons by displaying the letters “OM”, “MM”, or “IM”, accordingly. The color of the background of text box shall reflect the type of marker being received.

3.1.3.1.1.1.5.4 Radar altitude and Decision Height (DH) select window

The PFD shall provide the text box depicting radar altitude and the selected DH in the same location on the display as the actual aircraft. The radar altimeter shall reflect the height above terrain based upon the existing software solution for the existing T-44A radar altimeter function. The PFD text box shall illuminate when the selected decision height is achieved.

3.1.3.1.1.1.5.5 Radar altimeter DH select mode

The PFD altitude and barometric select function shall be updated to allow the selection of the DH by rotating the REFS knob of the DCP accordingly. Each PFD shall provide the means to select separate DHs and shall annunciate independently.

3.1.3.1.1.1.5.6 Tactical Air Navigation (TACAN) auxiliary Nav source

The PFD shall provide TACAN as an additional selection option for an “Auxiliary” Nav source. The TACAN selection shall indicate accordingly and display correct bearings and range to the TACAN station.

3.1.3.1.1.1.5.7 TACAN bearing indicator

When TACAN is selected as an auxiliary Nav source, the PFD shall activate a TACAN type bearing indicator on the Horizontal Situation Indicator (HSI). The TACAN bearing indicator shall provide the same symbology as the actual aircraft. The behavior of the TACAN bearing indicator shall replicate the behavior of the TACAN bearing indication in the existing trainer.

3.1.3.1.1.1.5.8 FMS Nav source select

The PFD shall provide the means for the pilot and co-pilot to select the FMS as a primary source of navigation by adding Global Positioning System (GPS) as a selectable source through toggling the primary Nav source button. The GPS status window shall activate upon selection.

3.1.3.1.1.1.5.9 PFD AP display annunciations

The PFD shall provide the pilot and co-pilot with display indications of the status of various AP functions. Each annunciator symbol to be displayed is listed and identified in Table V below.

Table V.

PFD AP Display Annunciators and Symbols

3.1.3.1.1.1.5.10 PFD FMS status field

The PFD shall provide the pilot and co-pilot with displayed status field, which shall indicate the modes and status of the FMS when the FMS is selected as a primary source of navigation on the pilot or co-pilot PFD. Specific modes and statuses to be annunciated on the PFD are listed in Table VI below.

Table VI.

FMS Annunciator and Symbols on PFD

Location

NO FLIGHT PLAN

MSG

FMS - DR

3.1.3.1.1.1.5.11 TACAN frequency select

The full range of simulated TACAN frequencies shall be selectable through the TACAN ARN-154 control head. Active TACAN frequencies shall be selected from an active TACAN frequency list, which shall be updated based upon those TACAN stations which are in range and valid. Validity shall be based upon own aircraft altitude and position from the station. Selection of the station audio from the audio control and TACAN panels shall result in the appropriate simulated code identifier being audible.

3.1.3.1.1.1.6 PFD interoperability

The PFD shall utilize variables found in the existing trainer host code “instrumentation” module located in the trainer host computer, which provides all computation of attitude, direction, altitude, and horizontal situation data. The dynamic graphics of the PFD shall provide the same visual representation of data from other cockpit systems as found in the PFD used in the actual aircraft. The PFD shall have interoperability with other avionics units IAW the following sections and the interoperability characteristics defined in the associated pilot guides of the other units and the functionality of the T-44C aircraft. The interfaces shall provide interoperability data from the various external units at the same update rate as the actual aircraft as a minimum.

3.1.3.1.1.1.6.1 PFD navigation radio interoperability

The PFD shall provide the means to select between various navigational systems as a reference for enroute and terminal activities. The following requirements shall apply:

a. The PFD shall provide the means to select and apply the following Nav sources and to display as a selected reference for the AP.

(1) Primary horizontal and vertical Nav source

(2) Range and bearing source

(3) Auxiliary Nav source

b. The PFD shall utilize the following sources and shall depict navigation and approach information IAW the Rockwell Collins Operator’s Guide and data collected on the DBA.

(1) GPS from the FMS

(2) Very High Frequency (VHF) Omni-Range (VOR)/ Distance Measuring Equipment (DME) from the radios

(3) TACAN from the radios

(4) Instrument Landing System (ILS) localized and glide slope from the radios

(5) Bearing Information from the Automatic Direction Finder (ADF) radios

c. Positional information depicted from radio navigational sources shall be based upon the frequency and validity of the Nav source. The source of GPS information shall be the FMS and shall be based upon the operational status of the FMS.

3.1.3.1.1.1.6.2 FMS interoperability

The pilot and co-pilot PFDs shall depict all waypoints and course lines, which have been entered into the FMS flight plan. The waypoints shall be displayed in the same coordinate set in the selected orientation relative to the own aircraft symbol on the HSI. The range of the waypoints displayed shall be independently selectable from each PFD. Waypoint identifiers shall be displayed in the appropriate proximity to the displayed waypoint symbol. Intersections, ETA, speed, altitude, long range NAV, and window option shall not be displayed.

3.1.3.1.1.1.6.3 AP interoperability

The pilot and co-pilot PFD shall provide an interface with the AP in order to achieve the same interoperability with the AP of the actual aircraft. The PFD shall depict the AP status and shall send the AP all data required for the AP to make the required corrections to achieve horizontal and vertical positions and velocities. The state of the crew selected coupling between the pilot and co-pilot PFDs shall be indicated by the presence of command bars on the selected PFD only when the AP is in the navigation or approach modes. The AP shall control the attitude of the aircraft, using attitude and positional references from the PFD and AP, in order to achieve a specific course, altitude, or glide slope. In the event of a PFD failure, the trainer shall provide the means to manually switch the coupled PFD AP to the operational PFD. Acquisition of specific altitudes for a coupled approach shall be based upon the PFD selected Nav source or heading bug position. The PFD shall provide all displayed localizer and glide-slope data required for the AP to execute coupled hold and approach maneuvers with the selected PFD. The computed correction aircraft attitude as determined by the AP shall be displayed on each PFD through a set of AP command bars, which shall be activated through the pilot or co-pilot PFD. The AP interface shall provide the following modes for references from the PFD as described below.

a. Heading capture and hold: Intercept and fly a desired heading as indexed on the PFD through a heading bug.

b. Nav Mode: Allows the AP to intercept and track specific courses as determined by the FMS, VOR, or TACAN.

c. Appr Mode: Allows AP to use GPS or ILS localizer and glide slope as a reference through the PFD.

3.1.3.1.1.1.6.4 Radio/FMS Nav sources interoperability

The simulated Nav sources and associated radio interoperability shall have the same functional fidelity as the actual aircraft. Radio Nav sources shall be selectable by each PFD through the primary Nav source, VHF Localizer (VLOC) Nav source, and Auxiliary Nav source function keys. TACAN shall be selected by either one of the PFDs. The PFD ILS horizontal and vertical deviation indicators shall depict the aircraft position relative to the approach path. Accuracy and validity of selected Nav sources shall be simulated by the PFD based upon Nav station location, Nav source validity, aircraft position, and altitude to the extent performed by the existing trainer. The behavior of indications in response to VOR “Cone of Confusion” shall be retained with existing trainer’s functionality.

3.1.3.1.1.2 Flight Management System

The aircraft FMS provides the crew with centralized control for the GPS sensors, computer based flight planning, fuel management, and radio management. The FMS has a 5-inch diagonal, full color flat panel Liquid Crystal Display (LCD), alphanumeric and function keys, and a navigation database. Position information is accepted from up to eight navigation sensors. These navigation sensor inputs can be blended to form a single composite position. The Digital Aeronautical Flight Information File (DAFIFF) navigation database provides information on Standard Instrument Departures (SID’s) and Standard Terminal Arrival (STAR) waypoints, approaches, VHF Navigational Aids (NAVAIDS), airports, and runways. All of the functions and visual characteristics of the Rockwell Collins FMS-3000 shall be provided as an integral part of the trainer avionics upgrade as listed below in Table VIII. The FMS shall provide the same features and functionality (as modified for the T-44C aircraft) as described in the following sections with reference to the Rockwell Collins FMS Pilot’s Guide 523-0778735, Rockwell Collins System Manual 523-0790063, and data collected on the DBA. The functionality of the FMS in the trainer shall be dependent upon the interoperability of the FMS in the actual aircraft. The FMS is not required to provide inertial navigation or omega navigation functions.

3.1.3.1.1.2.1 FMS bezel hardware

The bezel hardware configuration requirement associated with the FMS shall be limited to all components of the Control Display Unit (CDU), which is part of the CDU-3000 FMS system and as depicted in the Rockwell Collins Pilot’s Guide 523-0778735. The bezel shall replicate all functional, tactile, and visual characteristics of the actual CDU-3000 bezel.

3.1.3.1.1.2.2 FMS functional display

The FMS display shall be a color display, which shall be embedded into the CDU bezel. The display shall provide a color replication of all features described in the Rockwell Collins FMS-3000 Pilot’s Guide 523-0778735 to a resolution equal to the CDU display in the actual aircraft. The brightness of the display shall be adjustable by the operator. The colors of various graphics depicted on the display shall correspond the categories listed in Table VII below.

Table VII.

CDU Display Color Table

3.1.3.1.1.2.3 FMS functional keypad

The CDU keypad, which operates the various FMS functions, shall provide the same functionality as the actual aircraft FMS unit as shown in the “Displays and Controls” section of the Rockwell Collins FMS-3000 Pilot’s Guide 523-0778735. The keypad shall have the same tactile characteristics as the actual aircraft CDU keypad. The keypad shall have the same illumination characteristics as the actual keypad and the illumination intensity shall be controlled by the cockpit lighting control.

3.1.3.1.1.2.4 FMS functional performance

The FMS shall allow the operator to program and execute the tasks listed in Table VIII below IAW the Rockwell Collins FMS Pilot’s Guide 523-0778735. (Note: In some cases the page is available but only limited functionality is provided for the FMS.)

Table VIII.

FMS Functional Task List