SRD_Matrix-Attachment_D.pdf

SRD REQUIREMENTS DOCUMENT MATRIX

Req # Requirement Description How Requirement is Met

Aircraft Requirements Program Requirements

3.1.1 Solution shall mitigate avionics obsolescence for 20+ years as defined in a DMSMS plan (MANDATORY).

3.1.2 The T-1A aircraft shall maintain FAA certification following the AMP modification effort (MANDATORY).

3.1.3

The modified T-1A shall provide for communication, navigation, and surveillance/air traffic management capability to allow flight operations at all times in all civil and military airspace (NAS) (MANDATORY).

System Requirements

3.2.1 The avionics suite shall use non-proprietary architecture and interfaces (MANDATORY).

3.2.2 The avionics suite shall consist of COTS items or Air Force equipment

(MANDATORY).

3.2.3

The modified aircraft shall maintain FAA certification for the installation and use of the avionics

3.2.4 All avionics shall be powered using the existing power system of the baseline aircraft (MANDATORY).

3.2.5

The integrated avionics system suite shall allow the aircraft to operate within the existing weight and balance envelope (MANDATORY).

3.2.7

The integrated avionics system suite shall fit within the pre-modified aircraft allowable space (MANDATORY). This requirement does not apply to antennas.

CSO Aircraft Integration Requirement

3.3.1

The aircraft avionics shall maintain data bus connection with the CSO platform on the 21 CSO modified aircraft (MANDATORY).

3.3.2 The T-1A AMP avionics shall not drive a group B hardware change to CSO configured aircraft (MANDATORY).

3.3.3 The CSO ICS shall be retained on CSO

configured aircraft (MANDATORY).

3.3.4 The avionics solution shall maintain STC00055MC certification

BIT Requirements

3.4.1

BIT self-diagnosis and fault isolation shall be incorporated into the avionics suite to detect at a minimum system level failures (MANDATORY).

3.4.2 The fault code shall be displayed on

the EFIS (MANDATORY).

Accelerometer Indicators

3.5.1.1

The modified T-1A aircraft shall provide an accelerometer (vertical g indicator) display with a range commensurate with the vertical acceleration limits of the aircraft

3.5.1.2

The accelerometer display shall indicate the maximum positive and negative g experienced during the flight (MANDATORY).

3.5.1.3

The accelerometer display shall provide means for a crew member to manually reset the display

3.5.1.4 The accelerometer display shall have a continuous g display capability

3.5.1.5 The accelerometer display shall be readable from the pilot, copilot, and jump seat positions (MANDATORY).

Angle of Attack (AOA) Indication

3.5.2.1

The modified T-1A aircraft shall provide an AOA instrument display that compares the relative wind to the chord line of the wing

3.5.2.2 The AOA instrument display shall be readable from both the pilot and copilot positions (MANDATORY).

3.5.2.3

The AOA indications shall be compensated for configuration changes that may affect the stall AOA indication such as flap position, landing gear position, and Mach so that the stall AOA always occurs at the same indication on the display

3.5.2.4

The AOA instrument display shall have a numerical reading with a range from 0.0 to 1.0 AOA units

Standby Instruments

3.5.3.1

Attitude, airspeed, magnetic compass, and altimeter instruments shall be provided in locations that can be read and controlled from both the pilot and copilot positions (MANDATORY).

3.5.3.2 The primary aircraft battery shall provide backup power to the standby instruments (MANDATORY).

Other

3.5.4.1

RAT, engine vibration, fuel temperature, and hydraulic pressure indication shall be provided and visible at all times from both the pilot and copilot positions (MANDATORY).

Displays

3.6.1

Avionics displays shall be visible to the flight crew (see Appendix D) throughout the entire range of operational lighting conditions, from direct sunlight to darkness

3.6.3

The displays shall incorporate redundancy such that the mission can be completed in the event of any single point failure in the EFIS

3.6.4

The pilot's and copilot's displays shall be driven by separate sources to prevent a single point failure

3.6.5

In the event of a failure in one of the sources, as stated in 3.6.4, the other shall provide all information to both sets of displays (MANDATORY).

3.6.6

The modified T-1A aircraft shall provide the capability for crew members in the pilot and copilot seats the ability to independently control the formats of their respective displays (MANDATORY).

3.6.7

Pilot and co-pilot positions shall have the ability to independently control brightness of their respective displays

GPS

3.7.1.1

The modified T-1A aircraft shall include a COTS GPS that meets all the requirements for ADS-B, to include latency when combined with other aircraft systems (MANDATORY).

3.7.1.2 GPS shall have the WAAS capability

Rendezvous Capability

3.7.2.1 The modified T-1A aircraft shall provide for rendezvous using Air-to- Air TACAN (MANDATORY).

3.7.2.2 provide for rendezvousing with a similarly equipped aircraft

3.7.2.3 provide range and bearing to similarly equipped aircraft (MANDATORY).

3.7.2.4 provide for verification of range and bearing signal (MANDATORY).

3.7.2.5 provide the capability to display relative velocity between aircraft

FMS

3.7.3.1

The modified T-1A aircraft shall provide an FMS that manages the navigation process and can be accessed and used by the pilot and co-pilot during flight (MANDATORY).

3.7.3.2

Capability to display both primary and secondary flight plans on multi-functional display(s) shall be provided

3.7.3.3 The FMS shall meet NAS RNP/RNAV/RNP-RNAV navigation standards (MANDATORY).

3.7.3.4 The FMS shall provide RNP-Route, RNP 1.0 Terminal, and RNP 0.3 for approach operations (MANDATORY).

3.7.3.5 FMS shall include all navigation aids

including GPS (MANDATORY).

3.7.3.6 The FMS shall store a minimum of 20 pilot generated flight plans

3.7.3.7 The FMS shall store a minimum of 100 pilot generated waypoints

Navigation Displays

3.7.4.1

As a minimum, the modified T-1A aircraft shall provide a multicolor EADI, a multicolor EHSI, an altimeter, vertical velocity indicator, and an airspeed indicator (MANDATORY).

3.7.4.2

Capability to “bug” altitude and airspeed on display is required.

(MANDATORY). All displayed bearing pointers shall include a tail when displayed on the EHSI (MANDATORY).

3.7.4.3

A multicolor MFD(s) shall be mounted at a central location and display primary weather radar, moving map, TCAS II (MANDATORY). This display shall be used as a backup to the pilot's or copilot's displays

3.7.4.4

Weather radar data shall be displayed on a minimum of 2 displays to prevent a loss of weather radar data from a single display failure

3.7.4.5 provide for selecting navigation graphic overlays on the weather radar

EFIS

3.7.5.1 Controls for the EFIS shall be provided for both the pilot and the copilot

3.7.5.2 All EFIS displays shall be

interchangeable (MANDATORY).

3.7.5.3 provide a minimum of two independent signal generators (MANDATORY). If one signal generator fails, the remaining signal generator shall supply information to both the pilot and copilot EFIS

TCAS II / Transponder

3.7.6.1

The modified T-1A aircraft shall provide a TCAS II with a control unit located in the flight deck at a position to be controllable from the pilot and co-pilot positions (MANDATORY).

3.7.6.2 TCAS II shall be ADS-B compatible

3.7.6.3 provide an ADS-B Out transponder with modes A, C, and S

3.7.6.4 Current capability to “ident” using the existing button on the yoke shall be maintained (MANDATORY).

Weather Radar

3.7.7.1

The modified T-1A aircraft shall provide digital weather radar, stabilized in pitch and roll with a minimum of four colors

3.7.7.2 The weather radar shall provide for

selecting a range (MANDATORY).

3.7.7.3 The range of the weather radar shall be a minimum up to 300 NM

3.7.7.4 The weather radar shall provide the ability for auto tilt, sector scan, and gain adjustments (MANDATORY).

3.7.7.5 provide weather radar information to the EHSI and MFD with selectable navigation graphics overlays

Radio/Radar Altimeter

3.7.8.1

The modified T-1A aircraft shall provide a dedicated radio/radar altimeter for tracking the aircraft distance from terrain within an altitude range of 20 to 2,000 ft

3.7.8.2

The radio/radar altimeter displays shall provide for pilot and copilot adjustment to any altitude within the range of the indicator (MANDATORY).

3.7.8.3

The radio/radar altimeter shall provide independent warnings to the pilot and copilot when the pre-selected threshold is crossed in descent(MANDATORY).

3.7.8.4 Threshold selection can be made at the pilot and co-pilot position

3.7.8.5

The radio/radar altimeter accuracy shall be within 7% from 2000 feet to 500 feet AGL, within 5% from 500 to 100 AGL feet, and within 5 feet from 100 feet to 20 AGL feet

Ground Collision Avoidance

3.7.9.1 The modified T-1A aircraft shall meet the requirements for TAWS Class A

3.7.9.2

The modified T-1A aircraft shall provide the flight crew with visual and aural warnings to allow safe recovery of the aircraft while flying at 500 feet AGL and 330 KCAS (MANDATORY).

3.7.9.3 provide for manual, temporary inhibiting of warnings during landing with flaps less than 30 degrees and terrain avoidance (MANDATORY).

Approach and Landing

3.8.1

The modified T-1A aircraft shall provide for ILS category I, RNAV –GPS, VOR, NDB, and TACAN approaches to a position enabling safe landings

3.8.2 provide dual VOR capability

3.8.3

VOR course, bearing, and distance to station (if paired with DME) shall be displayed on EHSI when selected

3.8.4

The VOR antenna subsystem shall provide omnidirectional line of sight coverage for operation during airway navigation, approach, and landing

3.8.5 provide dual ILS Category I systems

3.8.6 ILS information (course and glideslope deviation) shall be displayed on EHSI when selected (MANDATORY).

3.8.7 The modified aircraft shall display an ILS course and a TACAN DME on the EHSI when selected (MANDATORY).

3.8.8 provide a TACAN which provides for X and Y selection (MANDATORY).

3.8.9 TACAN course, bearing, and distance to station shall be displayed on EHSI when selected (MANDATORY).

3.8.10

The modified T-1A aircraft shall provide an ADF system with digital filtering, or the equivalent, that provides a homing presentation

3.8.11 ADF bearing shall be displayed on

EHSI when selected (MANDATORY).

3.8.12

The modified T-1A shall provide a DME subsystem that incorporates a DME frequency hold function

3.8.13 provide a marker beacon system which detects and displays the inner and outer air field markers

3.8.14 provide for performing the following:

RNAV-2 routes, RNAV 1 terminal, RNAV (GPS approaches to include LPV), GPS vertical navigation (enroute and terminal areas), TCAS II and ADS- B-Out (1090ES) (MANDATORY).

3.8.16 provide for the display of NGA/DOD enroute and terminal area approach and departure charts FLIP at both the pilot and copilot positions

3.8.17

Alphanumeric identifier or channel information of the selected ground based NAVAID shall be displayed on the EHSI (MANDATORY).

VHF & UHF Transmitters and Receivers

3.9.1

The modified T-1A aircraft shall have an ICS with a minimum of one VHF communication, one UHF communication, and two VHF navigation radios (MANDATORY).

3.9.2

The VHF communication radios shall provide at minimum tuning frequencies from 118 – 151.975 MHz in 25kHz increments (MANDATORY).

3.9.3

The UHF communication radios shall provide at minimum tuning frequencies from 225 – 399.975 MHz in 25kHz increments (MANDATORY).

3.9.4 provide a narrow band UHF radio

3.9.5 provide two navigation and communication radio interface sources, controllable and accessible from the pilot and copilot seat

3.9.7

In the event of a radio interface source failure, all communication and navigation radios shall be controllable and accessible by the pilot and copilot from the second interface source location (MANDATORY).

3.9.8 provide for operating one UHF and one VHF transceiver simultaneously without causing degradation of intelligible communication

3.9.9

The antenna subsystem and installation shall provide omnidirectional coverage for air-to-air and air-to-surface communications

3.9.10 provide for operating one UHF and one VHF multi-frequency transceiver while simultaneously monitoring UHF guard frequency (243.0 MHz)

3.9.11

The UHF transceivers, VHF transceivers, and radio interface sources shall be operable using primary aircraft battery power when other power sources are not available

3.9.12

The UHF and VHF radios shall operate without degraded performance for a minimum of 30 minutes during battery operation, with a 5 percent transmit and 95 percent receive duty cycle (MANDATORY).

3.9.13

Communications and navigation receiver volume levels shall be separately adjustable at each crew position (MANDATORY).

3.9.14 provide for saving any combination of a minimum 20 VHF and UHF frequencies on the radio interface source (MANDATORY).

3.9.15

All crew positions and the avionics rack shall have intercom panels with individual volume and on and off controls (MANDATORY).

3.9.16

The Public Announcement system shall provide audible information in all areas of the cabin during operations at maximum cabin noise levels, with the engines operating on the ground and in flight

3.9.17

The ICS shall be operable from primary aircraft battery power when other power is not available

3.9.18

All crew positions shall have the ability to listen and transmit VHF and UHF radios communications

3.9.19

Intercom operations shall provide for transmission and reception of UHF and VHF communications

3.9.20

Navigation equipment shall have sufficient range to provide for operation when used in the federal airway structure (MANDATORY).

3.9.21

The modified T-1A aircraft shall provide for crew members in the pilot, copilot, and jump seat positions to silence all extraneous radio signals allowing communications among themselves via headset and microphone (MANDATORY).

3.9.22

The control for silencing all extraneous radio signals shall be mounted on both yokes and the jump seat intercom control panel (MANDATORY). The capability to override this functionality is required at the pilot and co-pilot positions

3.9.23 provide for crew members to communicate on all communication radios and the ICS utilizing existing GFE David Clark 1076 headsets and microphones or equivalent as a minimum (MANDATORY).

3.9.24 Full communication functionality shall be maintained while oxygen mask is in use (MANDATORY).

3.9.25 Headset and microphone jacks shall be located at all crew positions and in the avionics rack (MANDATORY).

3.9.26

Headset and microphone jacks shall be compatible with existing GFE David Clark 1076 headsets and microphones

3.9.27 The ground service communication jack shall remain in its current location (MANDATORY).

AutoPilot

3.10.1

The modified T-1A aircraft shall provide a three-axis autopilot system with automatic disengage feature

3.10.2 provide a preflight and maintenance BIT capability for the autopilot

3.10.3

The autopilot shall provide for coupled approaches and coupled lateral and vertical enroute navigation

3.10.4 Capability to disengage autopilot with button on yoke shall be retained

3.10.5 The modified T-1A aircraft autopilot shall compensate for Dutch roll tendencies (MANDATORY).

Flight Directors

3.11.1 The modified T-1A aircraft shall provide dual independent flight directors (MANDATORY).

3.11.2

Flight directors shall function with the autopilot and the instrument approach subsystems to provide Category I ILS capability with separate remote course and heading selection controls and a single cue command steering presentation (MANDATORY).

Clock

3.12.1

The modified T-1A aircraft shall provide a settable 24-hour digital clock, readable at night, with continuous time display to include hour, minutes, and seconds at the pilot and co-pilot positions

3.12.2 The clocks shall provide a resettable elapsed time measurement capability

Crash Survivable Flight Data Recorder (CSFDR)

3.13.1

Current capabilities of the FDR and number of recorded parameters shall be maintained as a minimum

3.13.2 Current frequency of data capture shall be maintained as the minimum

3.13.3 All functionality in the current Aircraft Structural Integrity software program shall be maintained (MANDATORY).

Emergency Locator Transponder (ELT)

3.14.1 The current ELT capability shall be

retained (MANDATORY).

Cockpit Lighting

3.15.1 The flight deck panel lighting shall be balanced over the full range of adjustment (MANDATORY).

3.15.2 provide a means of turning the instrument panel lighting off

3.15.3

The flight deck center instrument, overhead, and side panels shall be furnished with separate intensity controls allowing control of light levels through the entire dimmable range (MANDATORY).

Maintainability

3.16.1

For LRUs installed as part of the T-1A AMP, removal of a failed LRU shall not require removal of any other LRU

3.16.2

The T-1A modified aircraft shall include provisions for quick disconnects to allow easy removal of the existing avionics rack

Simulator Requirements OFT Requirements

4.1.1

The modified OFT shall replicate the modified aircraft in functionality, appearance, and lay-out

4.1.4 A modified OFT shall still be able to operate with legacy OFT simulators in networked exercises (MANDATORY).

4.1.5 The modified OFT as a minimum shall retain current capabilities of the IOS

4.1.8 IOS space requirements shall be

retained (MANDATORY).

4.1.9 The modified OFT shall maintain all record, replay, and fly out capability

4.1.10 Current ECL System for pitch, roll, yaw flight and sticker shaker controls shall be retained (MANDATORY).

4.1.13

The modified OFT software shall be compatible with existing software within the simulator system

4.1.14 The modified OFT shall retain the FAA AC 120-40B Level C simulation fidelity capabilities (MANDATORY).

4.1.15

The modified OFT shall be operated in accordance with the tolerance specified in FAA AC 120-40B

4.1.16

The new equipment installed shall include the functionality of malfunction insertion by the instructor (MANDATORY).

4.1.17

A maximum of 5 individual malfunctions shall be active at any one time during a given mission profile (MANDATORY).

4.1.18 ACCS shall work in single and network

configurations (MANDATORY).

4.1.19

The modified OFT shall be initially programmed with a CONUS DAFIF current on the date of issue of this contract (MANDATORY).

4.1.20 The modified OFT shall include a non-proprietary procedure for updating the DAFIF (MANDATORY).

4.1.21

The modified OFT shall maintain aircraft system simulation capability of the cockpit lighting system

4.1.22

Workmanship including all assemblies, parts, and accessories shall follow the guidelines of MIL-

HDBK-454 (MANDATORY).

4.1.24

The modified OFT shall not degrade safety in the performance of any tasks associated with the operations maintenance, instruction, enhancements/modifications, and support (MANDATORY).

ICS

4.1.26.1 ICS shall comply with FAA Advisory Circular No. 120-40B, qualified to level C or better (MANDATORY).

4.1.26.2 ICS shall be compatible with the

existing ACCS (MANDATORY).

4.1.26.3

All normal and abnormal sounds which provide audio cues to the student in the cockpit during all phases of flight and ground operations shall not be degraded

4.1.26.4

Engine aural simulation shall be from start through all operational performance conditions through engine shut-down (MANDATORY).

Software Development

4.1.27.1

All new or modified software shall follow accepted commercial developmental guidelines such as

IEEE/EIA 12207 (MANDATORY).

4.1.27.2

All training system software design shall follow structured model requirements and provide for expansion capabilities (MANDATORY).

Power

4.1.28.1 Modification to the OFT shall not require changes to the facility power

4.1.28.2

Equipment installed due to modification shall be compatible with the primary electrical power of 115 VAC, 60 Hz, 30 ampere single phase or 208 VAC, 60 Hz, 3 phase

4.1.28.3

Equipment shall be compatible with the emergency power-off system and not sustain any damage during unexpected power down

Environmental Conditions

4.1.29.1 A modified OFT shall not increase the operating temperature within the simulator (MANDATORY).

4.1.29.2

All components added to the OFT shall operate in temperatures from 59 to 86 degrees F with a relative humidity between 30 to 80% non-condensing (MANDATORY).

4.1.29.3

All components added to the OFT shall be able to be stored in temperatures from 14 to 122 degrees F with a relative humidity between 10 to 80% non-condensing

PTT Requirements

4.2.1 The PTT shall provide hands-on avionics training prior to aircraft or simulator events (MANDATORY).

4.2.2

The PTT shall be a representation of the cockpit to include pilot displays, multi-function display(s), auto-pilot controls, audio controls, navigation, and communication controls

4.2.3 The PTT shall have same tactile feel as

the aircraft (MANDATORY).

4.2.4

PTT shall provide the capability to allow student training on: radio management (navigation and communication tuning), audio panel/intercom control, transponder control, display control, navigation and data entry, flight planning, auto-pilot control, heading, and course and altitude selection (MANDATORY).

4.2.5

Displays in the PTT shall provide a dynamic response as the simulation passes over a waypoint or station

4.2.6 Displays and indicators in the PTT shall simulate a scripted mission as selected by a student (MANDATORY).

4.2.7 The PTT shall have the ability reposition to different training locations (MANDATORY).

4.2.8 The PTT shall allow the operator to select AIR or GROUND to perform a scripted mission (MANDATORY).

4.2.9 The PTT shall not occupy more than 62 square feet of floor space

4.2.10

The PTT shall utilize existing VAC power distribution system and not exceed existing dedicated 115 Volts Alternating Current (VAC), 20 Ampere, 60 Hz circuit (MANDATORY).

4.2.11 Approach plates on the PTT and OFT

shall be identical (MANDATORY).

4.2.12 The PTT shall provide a maintenance mode for troubleshooting