Attachment_B_T-1A_SRD_Final_Draft.pdf

SYSTEM REQUIREMENTS DOCUMENT

T-1A AVIONICS MODIFICATION PROGRAM

1 March 2016 ii

Approved By:

DATE:

PETER K. EIDE, Col, USAF T-1A System Program Manager Chief, Training Aircraft Division Mobility Directorate

DANIEL N. MARTICELLO, JR., Colonel, USAF Chief, Simulators Division AFPEO Agile Combat Support

PHILIP W. WIELHOUWER, Col, USAF Chief, Capability Requirements Division iii

CHANGE HISTORY

Change Version Date Initial Release 0 1 May 15

Updated to reflect changes from the site visit at Randolph AFB.

1 1 Mar 16 iv

TABLE OF CONTENTS

1 SCOPE

1.1 System Identification

1.2 System Overview

1.3 System Background

1.4 System Requirements Document Overview

2 APPLICABLE DOCUMENTS

2.1 Order of Precedence

2.2 General

2.3 Government Documents

2.3.1 Specifications, Standards, and Handbooks

2.3.2 Other Government Documents, Drawings and Publications

3 AIRCRAFT REQUIREMENTS

3.1 Program Requirements

3.2 System Requirements

3.3 CSO Aircraft Integration Requirements

3.4 Built-In Test (BIT) Requirements

3.5 Indicators

3.5.1 Accelerometer Indication

3.5.2 Angle of Attack (AOA) Indication

3.5.3 Standby Instruments

3.5.4 Other

3.6 Displays

3.7 Navigation

3.7.1 Departure, En-Route, and Terminal Navigation

3.7.2 Global Positioning System (GPS)

3.7.3 Rendezvous Capability

3.7.4 Flight Management System (FMS)

3.7.5 Navigation Displays

v

3.7.6 EFIS

3.7.7 TCAS II / Transponder

3.7.8 Weather Radar

3.7.9 Radio/Radar Altimeter

3.7.10 Ground Collision Avoidance

3.8 Approach and Landing

3.9 VHF & Ultra High Frequency (UHF) Transmitters and Receivers

3.10 AutoPilot

3.11 Flight Directors

3.12 Clock

3.13 Crash Survivable Flight Data Recorder (CSFDR)

3.14 Emergency Locator Transponder (ELT)

3.15 Cockpit Lighting

3.16 Maintainability

3.17 Environmental, Safety, and Occupational Health

3.18 Human Factors

4 SIMULATOR REQUIREMENTS

4.1 OFT Requirements

4.1.26 ICS

4.1.27 Software Development

4.1.29 Environmental Conditions

4.1.30 Electromagnetic Compatibility

4.2 PTT Requirements

5 VERIFICATION PROVISION

5.1 Demonstration

5.2 Test

5.3 Analysis

5.4 Inspection

Appendix A – Acronyms and Definitions .................................................................................. A-1

Appendix B – Verification Cross Reference Table .................................................................... B-1 vi

Appendix C – Multivariate Cases to Describe Body Proportions .............................................. C-1

Appendix D – Definitions ........................................................................................................... D-1

Appendix E –Items Requiring Replacement................................................................................ E-1

1 SCOPE

This document contains the System Requirements for the T-1A Avionics Modification Program (AMP) which encompasses 178 aircraft, 16 Operational Flight Trainers (OFT), and 14 Part Task Trainers (PTT).

1.1 System Identification

This System Requirements Document (SRD) establishes the system, functional, performance, and sustainment requirements for the T-1A AMP.

1.2 System Overview

The T-1A Jayhawk is a commercial derivative aircraft acquired to support the Air Education Training Command’s (AETC) Specialized Undergraduate Pilot Training (SUPT) and Combat Systems Officer (CSO) programs. Aircraft were delivered to the Air Force from January 1992 – August 1997. Currently, 157 aircraft are used to support SUPT, and 21 aircraft are used to support CSO programs. Aircraft are stationed across 5 operating bases where intermediate level maintenance is performed by either Contract Logistics Support (CLS) or government civilian employees. All maintenance follows Air Force developed maintenance manuals. Contractor Operated Maintenance Base Supply is maintained at each operating base location and provides the necessary support/equipment required to maintain the T-1A. Management and sustainment of the T-1A aircraft is managed by the program office located at Tinker Air Force Base (AFB).

Once Air Force pilots complete primary training in the T-6A, advance training is conducted in the T-1A for those pilots who have been assigned to fly heavy aircraft (e.g. tankers and cargo aircraft). Training consists of flying pre-defined missions designed to develop airmanship skills required for follow-on assignments in other squadrons. In addition to the SUPT mission, the T- 1A is used in the training of CSO where students learn electronic warfare / navigation skills in a flight crew environment.

Two types of Aircrew Training Devices (ATD) are used to complement aircraft training: an OFT and a PTT. A total of 16 OFTs and 14 PTTs are spread across all five operating locations. The two OFTs at Naval Air Station Pensacola have been modified to support the CSO training program. The OFTs are high-fidelity non-motion simulators with full fidelity cockpits and software flight modeling that replicates aircraft response and handling characteristics. The PTTs have selective powered functional switches and gauges to allow for student avionics familiarization. Both the OFT and PTT are managed by the Ground Based Training System (GBTS) program office located at Wright Patterson AFB.

1.3 System Background

Project service life of the T-1A based on structural data is beyond 2050. In order to meet this service life, several avionic systems and subsystems require replacement. A list of known items of concern is included in Appendix E. The AMP approach is to address the projected service life by replacing the avionics suite to ensure sustainability. At a minimum, current capabilities of the aircraft will be maintained with the integration of the new avionics suite. Requirements listed in Section 3 and 4 describe the suite capabilities required for continued support of the training syllabus.

1.4 System Requirements Document Overview

Contained within the SRD are the applicable documentation, requirements, and verification which will be used for the AMP.

2 APPLICABLE DOCUMENTS

This section lists the number, title, revision, and date of all documents referenced herein. This section also identifies the source for documents not available through normal Government stocking activities.

2.1 Order of Precedence

This SRD does not require strict adherence to military specifications governing hardware, software, and testing program, technical data, handbooks or other practices associated with standard equipment design or acquisition except as otherwise noted. At no time will safety, quality, or performance of equipment be compromised or sacrificed. Particular attention will be devoted to items affecting personnel safety, structural integrity and safety of flight. The following documents will be used, where applicable, as general guides and criteria in the performance of requirements set forth in this document. The applicable issue of these documents, unless otherwise specified, is the version which is in effect on the date of this document. Federal Aviation Administration (FAA) certification requirements will take precedence over any specific military specifications and standards. If FAA certification requirements cannot be met in order to achieve the requirements of this SRD, the contractor will raise the conflict to both the United States Air Force (USAF) and the FAA for resolution.

2.2 General

Documents listed in this section are further specified in sections 3, 4, or 5 of this SRD. While every effort has been made to ensure the completeness of the listed documents, bidders are cautioned they shall meet the requirements cited in sections 3, 4, and 5 of this specification, whether or not they are listed below.

2.3 Government Documents

2.3.1 Specifications, Standards, and Handbooks

The following specifications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are as cited.

DEPARTMENT OF DEFENSE STANDARDS AND HANDBOOKS

Document Number Title Rev Date

MIL-STD-464 Electromagnetic Environmental Effects Requirements for Systems

C 01 Dec 10

MIL-STD-961 Department of Defense Standard Practice Defense and Program-Unique Specifications Format and Content

E

09 Jan 14

MIL-STD-1787 Aircraft Display Symbology C 05 Jan 01

MIL-STD-1530 Aircraft Structural Integrity Program

(ASIP)

C 03 Aug 10

MIL-STD-882 System Safety E 11 May 12

MIL-E-7016 Electrical Load and Power Source Capacity F 15 Apr 88

MIL-HDBK-454 General Guidelines for Electronic Equipment

B 15 Apr 07

(Copies of these documents are available online at http://quicksearch.dla.mil/ or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.)

2.3.2 Other Government Documents, Drawings and Publications

The following other Government documents, drawings, and publications form a part of this SRD to the extent specified herein. Unless otherwise specified, the issues of these documents are as cited.

AIR FORCE INSTRUCTIONS

Document Number Title Date

AFI 10-601 Operational Capability Requirements Development

6 Nov 13

Document Number Title Date

AFI 61-204 Disseminating Scientific and Technical Information

30 Aug 02

AFI 63-101/20-101 Integrated Life Cycle Management 21 Mar 14

AFI 99-103 Capabilities Based Test and Evaluation 16 Oct 13

AFMCI 63-1201 Implementing Operational Safety, Suitability, and Effectiveness (OSS&E) and Life Cycle Systems Engineering (LCSE)

26 Jul 12

AFMCI 99-103 Test Management 22 Nov 04

(Copies of these documents are available online at http://www.e-publishing.af.mil/.)

FEDERAL AVIATION ADMINISTRATION

FAR Part 21 Certification Procedures for Products and Parts

N/A

FAR Part 25 Airworthiness Standards: Transport Category Airplanes

N/A

14 CFR Part 91 Automatic Dependent Surveillance – Broadcast (ADS-B) Out Performance Requirements to Support Air Traffic Control (ATC) Service; Final Rule

N/A

AC 90-105 Approval Guidance for RNP Operations and Barometric Vertical Navigation in the U.S.

National Airspace System

1-23-2009

AC 90-100 CH2 U.S. Terminal and En Route Area Navigation (RNAV) Operations with Change 2

3-1-2007

AC 25-23 Airworthiness Criteria for the Installation Approval of a Terrain Awareness and Warning System (TAWS) for Part 25 Airplanes

5-22-2000

AC 120-45A Airplane Flight Training Device Qualification 02-05-1992

(Copies of these documents are available online at http://www.faa.gov/.)

http://www.faa.gov/

TECHNICAL ORDER

TO 1-1A-14 Installation and Repair Practices Volume 1 Aircraft Electric and Electronic Wiring

15 Apr 2014

(Copies of these documents are available online in the Enhanced Technical Information Management System (ETIMS) accessible through the Air Force Portal at https://www.my.af.mil/.)

3 AIRCRAFT REQUIREMENTS

This section identifies the requirements for the T-1A AMP. Subsections are grouped by similar functionality or content. A requirement with MANDATORY at the end of the sentence is defined as the minimum acceptable threshold by the Air Force. A requirement with NON- MANDATORY following the sentence is defined as a desired objective. The threshold is equal to the objective in the case where no objective is listed. Meeting NON-MANDATORY requirements will not provide any positive consideration during evaluation. Refer to Section M for evaluation criteria.

3.1 Program Requirements

3.1.1 Solution shall mitigate avionics obsolescence for 20+ years as defined in a Diminishing Manufacturing Sources and Material Shortages (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 aircraft shall have an Avionics Mission Success Rate (See Appendix D) of no less than 98.5% (MANDATORY).

3.1.4 The avionics suite shall have a Total Mean Time Between Failure (MTBF- TOTAL) of no less than 40 hours (MANDATORY). Refer to Appendix D for a definition of MTBF-TOTAL.

3.1.5 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 (National Airspace System {NAS})

(MANDATORY).

3.2 System Requirements

3.2.1 The avionics suite shall allow for non-proprietary interfaces to the newly installed system (MANDATORY).

https://www.my.af.mil/

3.2.2 The avionics suite shall consist of Commercial-Off-The-Shelf (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 (MANDATORY).

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

3.2.4.1 The selected avionics system suite shall not exceed the current power draw of the pre-modified installed equipment to an extent that at least 20% of the T-1A power budget remains for future use (MANDATORY).

3.2.4.2 The selected avionics system suite shall not exceed the current power draw of the pre-modified installed equipment, leaving at least 24% of the T-1A power budget remaining for future use (desired) (NON-

MANDATORY).

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

3.2.6 The selected avionics system suite shall not increase the cabin temperature when operating on the ground. (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.

3.3 CSO Aircraft Integration Requirements

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). Refer to Appendix D for definition of group A and group B hardware changes.

3.3.3 The CSO Intercommunication System (ICS) capability shall be retained on CSO configured aircraft (MANDATORY).

3.3.4 The avionics solution shall maintain ST00055MC certification (MANDATORY).

3.4 Built-In Test (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 Electronic Flight Instrument System

(EFIS) (MANDATORY).

3.4.2.1 BIT shall detect at least 90% of the faults within the first attempt

(MANDATORY).

3.4.2.2 BIT shall isolate the fault to the specific Line Replaceable Unit (LRU) at least 85% of the time (MANDATORY).

3.4.3 Erroneous faults detected by BIT shall not exceed 5% of the system faults detected by organizational level maintenance (MANDATORY).

3.5 Indicators

3.5.1 Accelerometer Indication

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 (MANDATORY).

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 (MANDATORY).

3.5.1.4 The accelerometer display shall have a continuous g display capability

(MANDATORY).

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

3.5.2 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

(MANDATORY).

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 (MANDATORY).

3.5.2.4 The AOA instrument display shall have a numerical reading with a range from 0.0 to 1.0 AOA units (MANDATORY).

3.5.3 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).

3.5.4 Other

3.5.4.1 Ram Air Temperature (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).

3.5.4.2 Ability to view Outside Air Temperature (OAT) is desired (NON-

MANDATORY).

3.6 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 (MANDATORY).

3.6.2 MIL-STD-1787 shall be used as a guide for EFIS symbology when FAA regulations do not specify a solution (MANDATORY).

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 (MANDATORY).

3.6.4 The pilot's and copilot's displays shall be driven by separate sources to prevent a single point failure (MANDATORY).

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 (MANDATORY).

3.7 Navigation

3.7.1 Departure, En-Route, and Terminal Navigation

3.7.1.1 The aircraft shall comply with the following civil aviation standards for departure, en-route, and terminal area navigation: RNAV-2 Route, RNP-2 en-route, RNAV-1 Terminal Area, RNP-1 Terminal area and vertical navigation (en-route and terminal) (MANDATORY).

3.7.1.2 The modified T-1A aircraft shall include ADS-B Out using a 1090 extended squitter (MANDATORY).

3.7.1.3 The modified T-1A aircraft should provide for the system to perform

ADS-B IN (NON-MANDATORY).

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

3.7.2 Global Positioning System (GPS)

3.7.2.1 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).

3.7.2.2 GPS shall have the Wide Area Augmentation System (WAAS) capability (MANDATORY).

3.7.3 Rendezvous Capability

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

3.7.3.2 The modified T-1A aircraft shall provide for rendezvousing with a similarly equipped aircraft (MANDATORY).

3.7.3.3 The modified T-1A aircraft shall provide range and bearing to similarly equipped aircraft (MANDATORY).

3.7.3.4 The modified T-1A aircraft shall provide for verification of range and bearing signal (MANDATORY). Verification is defined as TACAN channel and distance correctly displayed on the Electronic Horizontal Situation Indicator (EHSI).

3.7.3.5 The modified T-1A aircraft shall provide the capability to display relative velocity between aircraft (MANDATORY).

3.7.4 Flight Management System (FMS)

3.7.4.1 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).

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

3.7.4.3 The FMS shall meet NAS RNP/ RNAV/RNP-RNAV navigation

standards (MANDATORY).

3.7.4.4 The FMS shall be capable of NAS Q and T (RNP 2) routes, RNAV SIDs and STARs (RNP 1), and RNAV approach operations

(MANDATORY).

3.7.4.5 FMS shall include all navigation aids including GPS

(MANDATORY).

3.7.4.6 The FMS shall store a minimum of 50 pilot generated flight plans

(MANDATORY).

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

3.7.5 Navigation Displays

3.7.5.1 As a minimum, the modified T-1A aircraft shall provide a multicolor Electronic Attitude Display Indicator (EADI), a multicolor EHSI, an altimeter, vertical velocity indicator, and an airspeed indicator

(MANDATORY).

3.7.5.2 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).

3.7.5.3 A multicolor Multi-Function Display(s) (MFD) shall be mounted at a central location and display primary weather radar, moving map, Traffic Collision Avoidance System (TCAS) II (MANDATORY).

This display shall be used as a backup to the pilot's or copilot's displays (MANDATORY).

3.7.5.4 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

(MANDATORY).

3.7.5.5 The modified T-1A aircraft shall provide for selecting navigation graphic overlays on the weather radar (MANDATORY).

3.7.6 EFIS

3.7.6.1 Controls for the EFIS shall be provided for both the pilot and the copilot (MANDATORY).

3.7.6.2 All EFIS displays shall be interchangeable (MANDATORY).

3.7.6.3 The EFIS shall incorporate redundancy such that the mission can be completed in the event of any single point failure (MANDATORY). If one signal generator fails, the remaining signal generator shall supply information to both the pilot and copilot displays (MANDATORY).

3.7.7 TCAS II / Transponder

3.7.7.1 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). Refer to Appendix D for a definition of flight deck.

3.7.7.2 TCAS II shall be ADS-B In compatible (NON-MANDATORY).

3.7.7.3 The modified T-1A aircraft shall provide an ADS-B Out transponder with modes A, C, and S (MANDATORY).

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

3.7.8 Weather Radar

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

(MANDATORY).

3.7.8.2 The weather radar shall provide for selecting a range

(MANDATORY).

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

(MANDATORY).

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

3.7.8.5 The modified T-1A aircraft shall provide weather radar information to the EHSI and MFD with selectable navigation graphics overlays

(MANDATORY).

3.7.8.6 The modified T-1A aircraft should provide information on wind shear, turbulence, and lightning intensity (NON-MANDATORY).

3.7.9 Radio/Radar Altimeter

3.7.9.1 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 (MANDATORY).

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

(MANDATORY).

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

(MANDATORY).

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

(MANDATORY).

3.7.9.5 The radio/radar altimeter accuracy shall be within 7% from 2000 feet to 500 feet Above Ground Level (AGL), within 5% from 500 to 100 AGL feet, and within 5 feet from 100 feet to 20 AGL feet

(MANDATORY).

3.7.10 Ground Collision Avoidance

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

A (MANDATORY).

3.7.10.2 The modified T-1A aircraft shall provide the flight crew with visual and aural warnings (MANDATORY). Refer to Appendix D for a definition of flight crew.

3.7.10.3 The modified T-1A aircraft shall provide for manual, temporary inhibiting of warnings during landing with flaps less than 30 degrees and terrain avoidance while flying at 500 feet AGL and up to 330 knots Calibrated Air Speed (KCAS) (MANDATORY).

3.8 Approach and Landing

3.8.1 The modified T-1A aircraft shall provide for Instrument Landing System (ILS) category I, LPV DA, LNAV/VNAV DA, LNAV MDA, Very High Frequency (VHF) Omni-Directional Range (VOR), Non-Directional Beacon (NDB), and TACAN approaches to a position enabling safe landings (MANDATORY).

3.8.2 The modified T-1A aircraft shall provide dual independent VOR capability

(MANDATORY).

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

(MANDATORY).

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

3.8.5 The modified T-1A aircraft shall provide dual ILS Category I systems

(MANDATORY).

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 The modified T-1A aircraft shall 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 Automatic Direction Finder (ADF) system with digital filtering, or the equivalent, that provides a homing presentation (MANDATORY).

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 (MANDATORY).

3.8.13 The modified T-1A aircraft shall provide a marker beacon system which detects and displays the inner and outer air field markers (MANDATORY).

3.8.14 The modified T-1A aircraft shall provide for the digital display of National Geospatial Intelligence Agency (NGA)/Department of Defense (DOD) enroute and terminal area approach and departure charts Flight Information Publications (FLIP) at both the pilot and copilot positions (MANDATORY).

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

3.8.16 The modified T-1A aircraft should display a second course on each EHSI as selected by the pilot or co-pilot (NON-MANDATORY).

3.8.16.1 The second course source (VOR1, VOR2 TACAN, FMS) should be independent of the primary course and be displayed on the EHSI (NON-

MANDATORY).

3.8.16.2 The actual second course (except FMS) should be selectable by the pilot or co-pilot (NON-MANDATORY).

3.9 VHF & Ultra High Frequency (UHF) Transmitters and Receivers

3.9.1 The modified T-1A aircraft shall have an ICS with a minimum of one VHF radio, one UHF radio, “hot-mic” capability in the normal operating mode, and the ability to monitor all navigational radio aids (MANDATORY). Hot-mic is defined as the Push-To-Talk is not used during inter-plane communication.

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 The modified T-1A aircraft shall provide a narrow band UHF radio

(MANDATORY).

3.9.5 The modified T-1A aircraft shall provide two navigation and communication radio interface sources, controllable and accessible from the pilot and copilot seat

(MANDATORY).

3.9.6 The modified T-1A aircraft should provide one navigation and communication radio interface source accessible from the jump seat (NON-MANDATORY).

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 The modified T-1A aircraft shall provide for operating one UHF and one VHF transceiver simultaneously without causing degradation of intelligible communication (MANDATORY).

3.9.9 The antenna subsystem and installation shall provide omnidirectional coverage for air-to-air and air-to-surface communications (MANDATORY).

3.9.10 The modified T-1A aircraft shall provide for operating one UHF and one VHF multi-frequency transceiver while monitoring UHF guard frequency (243.0 MHz)

(MANDATORY).

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 (MANDATORY).

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 The modified T-1A aircraft shall 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 (MANDATORY).

3.9.17 The ICS shall be operable from primary aircraft battery power when other power is not available (MANDATORY).

3.9.18 All crew positions shall have the ability to listen and transmit VHF and UHF radios communications (MANDATORY).

3.9.19 Intercom operations shall provide for transmission and reception of UHF and VHF communications (MANDATORY).

3.9.20 The modified T-1A aircraft shall provide for crew members in the pilot, copilot, and jump seat positions to silence all external radio signals allowing communications among themselves via headset and microphone (MANDATORY). The capability to override this functionality is required at all crew positions (MANDATORY).

3.9.21 The control for silencing all external radio signals shall be mounted on both yokes and the jump seat intercom control panel (MANDATORY).

3.9.22 The modified T-1A aircraft shall provide for crew members to communicate on all communication radios and the ICS utilizing existing Government Furnished Equipment (GFE) David Clark 1076 headsets and microphones or equivalent as a minimum (MANDATORY).

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

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

3.9.25 Headset and microphone jacks shall be compatible with existing GFE David Clark 1076 headsets and microphones (MANDATORY).

3.9.26 The ground service communication jack shall remain in its current location

(MANDATORY).

3.9.27 In addition to the capabilities listed in 3.9.1 – 3.9.26, CSO modified aircraft shall have the following capability as part of the ICS:

3.9.27.1 Private channel for communications between pilot, co-pilot, jump and observer only (MANDATORY).

3.9.27.2 Private channel for communications between instructor, CSO and observer only (MANDATORY).

3.9.27.3 Private channel for communications between pilot, jump, instructor and observer only (MANDATORY).

3.9.27.4 Threat 1 and Threat 2 system audio shall be selectable at all crew stations (MANDATORY).

3.9.27.5 Call button (MANDATORY).

3.9.27.6 Selectable Hot mic/Hot listen capability (MANDATORY).

3.10 AutoPilot

3.10.1 The modified T-1A aircraft shall provide a three-axis autopilot system with automatic disengage feature (MANDATORY).

3.10.2 The modified T-1A aircraft shall provide a preflight and maintenance BIT capability for the autopilot (MANDATORY).

3.10.3 The autopilot shall provide for coupled approaches and coupled lateral and vertical enroute navigation (MANDATORY).

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

3.11 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).

3.12 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 (MANDATORY). Settable is defined as the ability to set the time on the clock which will be maintained as power is applied to the aircraft.

3.12.2 The clocks shall provide a resettable elapsed time measurement capability

(MANDATORY).

3.13 Crash Survivable Flight Data Recorder (CSFDR)

3.13.1 Current capabilities of the Flight Data Recorder (FDR) and number of recorded parameters shall be maintained as a minimum (MANDATORY).

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

(MANDATORY).

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

3.14 Emergency Locator Transponder (ELT)

3.14.1 The current ELT capability shall be retained (MANDATORY).

3.15 Cockpit Lighting

3.15.1 The flight deck panel lighting shall be balanced over the full range of adjustment (MANDATORY). Refer to Appendix D for a definition of flight deck.

3.15.2 The modified T-1A aircraft shall provide a means of turning the instrument panel lighting off (MANDATORY).

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). Refer to Appendix D for a definition of flight deck.

3.16 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 (MANDATORY).

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

3.17 Environmental, Safety, and Occupational Health

3.17.1 The avionics installed as part of the T-1A AMP effort shall provide for ground operations through takeoff in an outside ambient temperature range from -40 degrees Fahrenheit at sea level to +130 degrees Fahrenheit at sea level, including corresponding internal temperatures (MANDATORY).

3.17.2 The avionics installed as part of the T-1A AMP effort shall provide for performing missions under all vibration, temperature, and acoustic conditions induced by the operation of the air vehicle, subsystems, and equipment within the aircraft operating envelope per limitations in the USAF flight manual technical order 1T-1A-1 (MANDATORY).

3.17.3 The modified T-1A aircraft shall operate in all Electromagnetic Environmental Effects (E3) environments of exposure in flight and on the ground, without suffering or causing functional degradation (MANDATORY).

3.17.4 The avionics installed as part of the T-1A AMP shall be electromagnetically compatible with all subsystems onboard the aircraft (MANDATORY).

3.17.5 The avionics installed as part of the T-1A AMP shall meet FAA certification requirements for Electromagnetic Interference (EMI) (MANDATORY).

3.17.6 The modified T-1A aircraft shall comply with applicable environmental, pollution control, and occupational health laws and regulations, from the federal, state, and local levels (MANDATORY).

3.17.7 The operations and maintenance of the modified T-1A aircraft shall require no additional hazardous material use and disposal beyond that of the legacy system to be replaced or that of the original system (MANDATORY).

3.17.8 All modified T-1A aircraft environment, safety, and occupational health hazard risks shall be mitigated to the Acceptable level in accordance with current Radio Technical Commissions for Aeronautics / Document Number (RTCA/DO)-160

(MANDATORY).

3.17.9 No single-point failure or malfunction of a component within the modified T-1A aircraft shall cause a sequence of events leading to a catastrophic effect on the modified T-1A aircraft or personnel (MANDATORY).

3.18 Human Factors

3.18.1 The human engineering criteria of MIL-STD-1472G paragraphs 5.1 through 5.5, 5.7, 5.8, and 5.9 shall be used as a guide for new equipment, modified equipment, and new configurations of existing equipment when FAA regulations do not provide guidance (MANDATORY).

3.18.2 The modified T-1A aircraft shall take into account the existing T-1A aircrew population as reflected in the original T-1 first to ninety-ninth percentile range requirements and the T-1A Multivariate Cases values which define body proportions for that range (MANDATORY). Refer to Appendix C for the multivariate cases to describe body proportions.

4 SIMULATOR REQUIREMENTS

This section identifies the requirements for the simulator modification of the T-1A AMP. This section contains two separate subsections containing requirements for the OFT and PTT. A requirement with MANDATORY at the end of the sentence is defined as the minimum acceptable threshold by the Air Force. A requirement with NON-MANDATORY following the sentence is defined as a desired objective. The threshold is equal to the objective in the case where no objective is listed. Meeting NON-MANDATORY requirements will not provide any positive consideration during evaluation. Refer to Section M for evaluation criteria.

4.1 OFT Requirements

4.1.1 The modified OFT shall replicate the modified aircraft in functionality, appearance, and lay-out (MANDATORY).

4.1.2 The modified OFT shall maintain simulator availability of 95%

(MANDATORY).

4.1.3 The modified OFT shall maintain all capabilities identified in the current version of the System Design Document (MANDATORY).

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 Instructor Operating Station (IOS) (MANDATORY).

4.1.6 Current visual system shall be retained (MANDATORY).

4.1.7 ICS capability in the CSO OFTs shall be retained (MANDATORY).

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

(MANDATORY).

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

4.1.11 The modified OFT shall retain the current aero and engine models

(MANDATORY).

4.1.12 The modified OFT shall retain all capabilities from current winds and turbulence profiles (MANDATORY).

4.1.13 The modified OFT software shall be compatible with existing software within the simulator system (MANDATORY).

4.1.14 The modified OFT shall retain the FAA AC 120-45A Level C (6) simulation fidelity capabilities (MANDATORY).

4.1.15 The modified OFT shall be operated in accordance with the tolerance specified in

FAA AC 120-45A (MANDATORY).

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 Aural Cue and Communication System (ACCS) shall work in single and network configurations (MANDATORY).

4.1.19 The modified OFT shall be programmed with a Continental United States (CONUS) Digital Aeronautical Flight Information File (DAFIF) or equivalent (MANDATORY). The DAFIF or equivalent shall be current on the date of acceptance of each article (MANDATORY).

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

4.1.21 The modified OFT shall maintain aircraft system simulation capability of the cockpit lighting system (MANDATORY).

4.1.22 Workmanship including all assemblies, parts, and accessories shall follow the guidelines of MIL-HDBK-454 (MANDATORY).

4.1.23 The modified OFT shall be in compliance with the Item Unique Identification (IUID) program (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).

4.1.25 Only fire resistant and non-hazardous (when exposed to fire) materials shall be used in cockpits, seats, shrouds cable ties cable coverings, auxiliary insulations (such as heat, electrical, sound, etc.). (MANDATORY).

4.1.26 ICS

4.1.26.1 ICS shall comply with FAA Advisory Circular No. 120-45A, qualified to level C (6) 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 (MANDATORY).

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

4.1.27 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).

4.1.28 Power

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

(MANDATORY).

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 (MANDATORY).

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

4.1.29 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 (MANDATORY).

4.1.30 Electromagnetic Compatibility

4.1.30.1 The modification shall be electromagnetically compatible with itself, between components and with other equipment in the same facility and the same operational environment (MANDATORY).

4.2 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 (MANDATORY).

4.2.2.1 The PTT shall have same tactile feel as the aircraft (MANDATORY).

4.2.3 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).

4.2.4 Displays in the PTT shall provide a dynamic response as the simulation passes over a waypoint or station (MANDATORY).

4.2.5 The PTT shall have the ability reposition to different training locations

(MANDATORY).

4.2.6 The PTT shall allow the operator to select AIR or GROUND as an initial condition to perform a mission (MANDATORY).

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

(MANDATORY).

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

4.2.9 Approach plates on the PTT and OFT shall be identical (MANDATORY).

4.2.10 The PTT shall provide a maintenance mode for troubleshooting

5 VERIFICATION PROVISION

This section defines a set of verification methods and specifies for each requirement in Section 3 the method(s) to be used to ensure the requirement has been met. A table is used to present this information and is documented in Appendix C.

5.1 Demonstration

Demonstration is defined as the operation of the system or subsystem which requires observation to demonstrate requirement compliance. This verification does not require the use of instrumentation, special test equipment, or subsequent analysis. An example would be a fit and function check.

5.2 Test

Test is defined as verification of the requirements through the application of established test procedures, usually with instrumentation, within specified environmental conditions and subsequent compliance confirmation through analysis of the data generated. This requirement may be fulfilled by submission of data which demonstrates the required test has been satisfactorily accomplished.

5.3 Analysis

Analysis is defined as processing of accumulated data obtained from other qualification methods to verify requirement compliance. Examples of analysis are reduction interpolation or extrapolation of test results. This verification requirement may be fulfilled by submission of data previously produced which demonstrates the analysis has been satisfactorily accomplished.

5.4 Inspection

Inspection is defined as visual verification the system, including system documentation, conforms to the requirements specified herein. Visual verification can be in the form of inspection of the physical installation, and/or review of documents reflecting qualification requirements.

A-1

Appendix A – Acronyms and Definitions

AC Advisory Circular ACCS Aural Cue and Communication System ADF Automatic Direction Finder ADS-B Automatic Dependent Surveillance – Broadcast AETC Air Education Training Command AFB Air Force Base AFI Air Force Instruction AFMCI Air Force Materiel Command Instruction AGL Above Ground Level AMP Avionics Modification Program AOA Angle of Attack APR April ASIP Aircraft Structural Integrity Program ATC Air Traffic Control ATD Aircrew Training Devices AUG August BIT Built In Test CFR Code of Federal Regulations CLS Contract Logistic Support CONUS Continental United States COTS Commercial Off The Shelf CSFDR Crash Survivable Flight Data Recorder CSO Combat Systems Officer DAFIF Digital Aeronautical Flight Information File DEC December DME Distance Measurement Equipment DMSMS Diminishing Manufacturing Sources and Material

Shortages DOD Department of Defense E3 Electromagnetic Environmental Effects EADI Electronic Attitude Display Indicator ECL Electronic Control Loading EFIS Electronic Flight Information System EHSI Electronic Horizontal Situation Indicators ELT Emergency Location Transponder EMI Electromagnetic Interference ETIMS Enhanced Technical Information Management System FAA Federal Aviation Administration FAR Federal Aviation Regulation FDR Flight Data Recorder FLIP Flight Information Publications FMS Flight Management System GBTS Ground Base Training System

A-2

GFE Government Furnished Equipment GPS Global Positioning System Hz Hertz ICS Intercommunication System ILS Instrument Landing System IOS Instructor Operating Station IUID Item Unique Identification JAN January JUL July KCAS Knots Calibrated Air Speed kHz Kilohertz LCSE Life Cycle Systems Engineering LNAV DA Lateral Navigation Decision Altitute LNAV MDA Lateral Navigation Minimum Descent Altitute LPV Localizer Performance with Vertical Guidance LRU Line Replaceable Unit MAR March MBTF-TOTAL Mean Time Between Failure - Total MFD Multi-Functional Display MHz Mega Hertz MIL Military MIL-HDBK Military Handbook MIL-STD Military Standard NAS National Air Space NAS Q National Air Space Q Route NDB Non-Directional Beacon NGA National Geospatial Intelligence Agency NM Nautical Miles NOV November OAT Outside Air Temperature OCT October OFT Operational Flight Trainers OSS&E Operational Safety, Suitability, and Effectiveness PTT Part Task Trainers RAT Ram Air Temperature RNAV Area Navigation RNP Required Navigation Performance RTCA/DO Radio Technical Commissions for Aeronautics / Document

Number SIDS Standard Insttrument Depature SRD System Requirements Document STARS Standard Termerinal Arrivals SUPT Specialized Undergraduate Pilot Training TAWS Terrain Awareness and Warning System TACAN Tactical Air Navigation

A-3

TCAS Traffic Collision Avoidance System TO Technical Order UHF Ultra High Frequency USAF United States Air Force VAC Volts Alternating Current VHF Very High Frequency VOR VHF Omni-Directional Range WAAS Wide Area Augmentation System

B-1

Appendix B – Verification Cross Reference Table

Table 5-1Table 5-1 contains the requirements identified in Section 3 and 4 and the corresponding verification method to be used in determining compliance. Definitions of Demonstration (D), Test (T), Analysis (A), and Inspection (I) are provided in Section 5. Verification methods contained for each requirement shall not take precedence over FAA required methods for certification.

Table 5-1: Verification Table

Req # Requirement Description D T A I Aircraft Requirements

Program Requirements

3.1.1 Solution shall mitigate avionics obsolescence for 20+

years as defined in a DMSMS plan (MANDATORY). X X

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

(MANDATORY).

X

3.1.3 The modified T-1A aircraft shall have an Avionics Mission Success Rate (See Appendix D) of no less than 98.5% (MANDATORY).

X X

3.1.4 The avionics suite shall have a MTBF-TOTAL of no less than 40 hours (MANDATORY). Refer to Appendix D for a definition of MTBF-TOTAL.

X

3.1.5

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).

X

System Requirements

3.2.1 The avionics suite shall allow for non-proprietary interfaces to the newly installed system

(MANDATORY).

X

3.2.2 The avionics suite shall consist of COTS items or Air

Force equipment (MANDATORY). X X

3.2.