APPENDIX_B_SRD.pdf

Systems Requirements Document - Aero-I SATCOM Replacement

Table of Contents 1 Scope

1.1 System Identification

1.2 System Overview

2 Applicable Documents

2.1 General

2.2 Government Documents

2.2.1 Specifications, Standards, and Handbooks

2.2.2 Other Government Documents, Drawings, and Publications

2.3 Non-Government Publications

2.4 Order of Precedence

3 System or Subsystem Requirements

3.1 Required States and Modes

3.1.1 Transmission ON/OFF Function

3.1.2 Built-In-Test (BIT) Mode

3.2 System or Subsystem Function

3.2.1 Communications

3.3 System Configuration

3.3.1 Interface Configurations

3.3.2 Electromagnetic Environment

3.3.3 System Data Requirements

3.3.4 Growth Path

3.4 Adaptation Requirements

3.4.1 Mounting Location

3.4.2 Design and Construction

3.5 Environmental, Safety, and Operational Health (ESOH) Requirements

3.6 System Environment Requirements

3.7 System Quality Factors

3.7.1 System Integrity and Supportability Considerations

3.7.2 Mean Time to Repair (MTTR)

3.7.3 Mean Time Between Failure (MTBF)

3.7.4 Supportability Features

3.7.5 Mission Reliability

3.7.6 Operational Availability

3.8 Logistics Related Requirements

3.9 Other Requirements

3.10 Statutory, Regulatory, and Certification Requirements

3.10.1 Statutory Requirements

3.10.2 Regulatory Requirements

3.10.3 Certification Requirements

4 Verification Provisions

4.1 Verification Methods

4.1.1 Demonstration

4.1.2 Test

4.1.3 Analysis

4.1.4 Inspection

4.1.5 Special Verification Methods

5 Requirements Traceability

5.1 Traceability to System Requirements

5.2 Traceability to Subsystems Requirements

6 Acronyms & Abbreviations

Appendix A: C/KC-135 Requirements Correlation Matrix

Figures Figure 1: OV-1 C/KC-135 AERO-I SATCOM

Tables

Table 1: C/ KC-135 DO-160G Test Procedures file://tinker-2k/dfs1/OCALC-LC/Data/WKDM/Avionics%20Mod%20Flight/Programs/Aero-I%20Replacement/Contracting/Single%20Award%20IDIQ/SRD%20-%20Aero-I%20V3.doc#_Toc4058321

1 Scope This Systems Requirement Document (SRD) describes attributes, performance parameters, processes, objectives and other requirements needed for a C/KC-135 satellite communication (SATCOM) replacement. The SATCOM replacement is needed to replace a third generation Inmarsat Aero-I SATCOM service which will be discontinued in FY 22. For the purposes of this SRD, the C/KC-135 fleet is defined as the active KC-135R/T Stratotankers, and the OC-135B Open Skies aircraft.

1.1 System Identification

The current Inmarsat communications system was installed as part of the C/KC-135 Global Air Traffic Management (GATM) modification. The satellite hardware system consists of a Collins SATCOM 2000 transceiver (Collins part number 822-1346-001), an electrically steered, phased array antenna (part number 822- 1369-001), as well as all wiring harnesses, connectors and mounting hardware. The satellite system interfaces with the C/KC-135 Operational Flight Program (OFP).

1.2 System Overview

The C/KC-135’s primary mission is to provide worldwide, day/night, adverse weather Aerial Refueling (AR) to receiver capable United States (U.S.) and coalition military aircraft (potentially including unmanned aircraft).

C/KC-135 aircraft are designed to provide robust, sustained AR capability to support global attack, air-bridge, deployment, sustainment, employment, redeployment, homeland defense, theater support to joint, allied, and coalition air forces, and specialized national defense missions. The C/KC-135 executes secondary missions such as cargo and/or passenger travel, aero-medical evacuation (AE) without impacting the primary AR mission.

The OC-135B Open Skies aircraft is a variant of the KC-135 which was developed to support the Treaty on Open Skies by flying unarmed observation flights over participating parties of the treaty.

The current Aero-I Inmarsat system was acquired to utilize improved Communication, Navigation and Surveillance (CNS) technologies for access to Federal Aviation Administration (FAA) Air Traffic Management (ATM). The critical satellite-based navigation technologies added with the Aero-I SATCOM system included increased use of data links for pilot/controller communication, and improved surveillance to enhance both ground and cockpit situational awareness. Aircraft without the CNS technologies are excluded from operating in airspace where separation standards and ATM procedures are implemented by civil aviation authorities. C/KC- 135 aircraft modified with an Iridium SATCOM system will mitigate capability gaps anticipated due to the planned Inmarsat discontinuation of the Aero-I satellite service after FY22.

Figure 1 provides a graphical depiction of the communication architecture between the C/KC-135 GATM equipped aircraft, and the other systems required for full communication with the CNS/ATM.

This C/KC-135 Aero-I SATCOM Replacement SRD supports mitigating anticipated airspace restrictions within the global CNS/ATM. The SATCOM Replacement shall consist of: a SATCOM antenna, SATCOM transceiver (transmitter/receiver), and associated Group A parts. The SATCOM system shall be integrated into the KC-135 avionics. The SATCOM system shall be the primary method of transmitting Beyond Line of Sight Aircraft Communications Addressing/Reporting System (ACARS). Projected time-line for C/KC-135 SATCOM Replacement fielding is FY21 with installs continuing through FY24.

2 Applicable Documents

This section lists the number, title, revision, and date of all documents referenced herein.

2.1 General

The documents referenced in this section are specified in Sections 3 and 4 of this SRD and are applicable only to the extent specified. While every effort has been made to ensure the completeness of this list, document users

Figure 1: OV-1 C/KC-135 AERO-I SATCOM are cautioned that all specified requirements cited in Section 3 shall be met, whether or not an originating document is listed in this section. The current version of documentation as of the contract date shall apply with the exception of Military Specifications (MIL-SPECs) and Military Standards (MIL-STDs), which have specific versions listed below.

2.2 Government Documents

The following sections list government documentation applicable to this SRD.

2.2.1 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 those cited in the solicitation or contract.

MIL-HDBK-516C Airworthiness Certification Criteria

12 Dec 2014

MIL-STD-130(N) Identification Marking of U.S. Military Property

17 Dec 2007

MIL-STD-461(G) Requirements for the Control of Electromagnetic

11 Dec 2015 Interference Characteristics of Subsystems and Equipment

MIL-STD-704 (F Change 1) Aircraft Electrical Power Characteristics

5 Dec 2016

MIL-STD-810 (G Change 1) Environmental Engineering Considerations and

15 Apr 2014 Laboratory Tests

MIL-STD-961 Standard Practice for Defense Specifications

27 Oct 2015

MIL-STD-1472 (G) Human Engineering

11 Jan 2012

MIL-STD-1686 (C) Electrostatic Discharge Control Program for Protection of

25 Oct 1995 Electrical and Electronic Parts, Assemblies and Equipment (Excluding Electrically Initiated Explosive Devices) (Metric)

MIL-E-7016 (F Amendment 1) Electrical Load and Power Source Capacity, 20 Jul 1976 Aircraft, Analysis of

TM-86-01Q Air Force Technical Manual Contract Requirements (TMCR)

13 Jan 2017

2.2.2 Other Government Documents, Drawings, and Publications

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

AFI 63-137 Assurance of Communications, Navigation, Surveillance/Air Traffic

29 May 2012 Management (CNS/ATM), Navigation Safety, and Next Generation

Air Transportation System (NEXTGEN) Performance

AFMAN 63-119 Certification of System Readiness for Dedicated Operational Testing

26 April 2019

Annex: C/KC-135 AERO-I SATCOM Replacement Program (SEP)

19 June 2017

Legacy Tanker Systems Engineering Plan (SEP)

1 October 2015

DoDD 4650.01 CE-01 Policy and Procedures for Management and Use of the Electromagnetic

12 March 2014 Spectrum

DoDI 8510.01 DOD Information Assurance Certification and Accreditation Process

12 March 2014

TO 1C-135-2-11-40 Avionics System KC-135R/T and OC-135B

TO 1C-135(K)R(II) Flight Manual USAF Series KC-135R/T Aircraft [GATM]

2.3 Non-Government Publications

ASME Y-14.34 Associated Lists 1 Jan 2013

SAE AS50881 Rev. F Wiring Aerospace Vehicle May 2015

RTCA DO-160 Rev. G Environmental Conditions and Test Procedures for Airborne 8 Dec 2010 Equipment

RTCA DO-219 Minimum Operational Performance Standards for ATC 27 Aug 1993 Way Data Link Communications

2.4 Order of Precedence

Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein (except for related specification sheets), the text of this document takes precedence.

Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3 System or Subsystem Requirements The SATCOM replacement system shall meet the requirements called out in this document, which are derived from the GATM Operational Requirements Document (ORD) dated 23 Dec 1998 as amended on 14 August 2003 and 24 November 2003. Each requirement is followed with either a (T) for a threshold requirement or an

(O) for a system objective. When a requirement includes both threshold and objective values, a (T) is annotated after the threshold value and an (O) after the objective value.

The C/KC-135 SATCOM replacement system shall consist of an Iridium based SATCOM transceiver and a suitable antenna (T=O).

3.1 Required States and Modes

3.1.1 Transmission ON/OFF Function

To meet military mission requirements the C/KC-135 SATCOM replacement system transmissions shall be extinguishable from a primary crewmember position (ON/OFF Function) (T=O).

3.1.2 Built-In-Test (BIT) Mode

The SATCOM replacement system shall incorporate BIT capability for fault isolation (T=O). The resultant BIT data shall be stored and available for retrieval at a later time. (T=O). The SATCOM replacement system shall have the following BIT modes capable of fault detection and fault isolation: Power-up, and Continuous. (T).

The combination of BIT information, Technical Orders (TO) and manual test, shall be able to detect, isolate, and verify 95 percent of faults (T), with an objective of 99 percent (O). In addition, the continuous BIT function shall detect 95% of critical faults (T), with an objective of 99% (O). Critical faults are defined as degradations or failures, indicated or actual, that will prevent the system from performing its function, or jeopardize the flight worthiness of the aircraft or safety of the crew. BIT false failure indications shall not exceed 2 percent of logged failures (T), with an objective of 0 percent (O).

3.2 System or Subsystem Function

C/KC-135 SATCOM replacement shall have the following performance requirements and equipment:

3.2.1 Communications

C/KC-135 SATCOM replacement shall attain CNS/ATM platform certification (T=O).

3.2.1.1 SATCOM Voice

The Iridium SATCOM voice system shall meet International Civil Aviation Organization (ICAO) Standards and Recommended Practices (SARP) for direct pilot-to-controller voice communication (T=O). Incoming calls shall have aural and visual indicators. (T=O). Receipt of an Iridium SATCOM phone link shall be annunciated via the existing SAT instrument panel annunciation light and instrument panel chime (T=O). The annunciation light shall be illuminated when an Iridium SATCOM phone call is received extinguished after the phone call is terminated (hung up), whether or not SATCOM is de-selected (T=O).

3.2.1.2 SATCOM Datalink

To allow aircraft to operate in oceanic airspace where reduced separation standards are implemented, the system shall provide beyond-line-of-sight SATCOM datalink communication that complies with the ICAO Standards and SARP (T=O). The SATCOM shall integrate into, and maintain, the existing communication hierarchy affecting the AN/ARC-210, the SATCOM replacement, and the AN/ARC-190 (T=O). System shall provide a controller-pilot data link communication (CPDLC) application that complies with the Minimum Operational Performance Standard (MOPS) for ATC Two-Way Data Link Communications (DO-219), the Air Traffic Services System Requirements and Objectives for Future Air Navigation System (FANS)-1/A (T), and CPDLC continental operation over the Aeronautical Telecommunications Network (ATN) in accordance with the ICAO SARPs (O).

3.3 System Configuration

The Iridium SATCOM radio configuration shall provide at least one data packet channel and one voice channel to perform simultaneous voice and data links for communication (T=O).

3.3.1 Interface Configurations

3.3.1.1 Commercial Interface Standards

The system shall be compliant with ICAO SARPs, Annex 10, Volume III and the SATCOM communications interface requirements of Aeronautical Radio, Incorporated (ARINC) 741 or ARINC 761 (T=O). System shall be interoperable with ARINC 758 Communications Management Units (CMU), and ARINC 739A Control Display Units (CDU) (T=O).

3.3.1.2 C/KC-135 Legacy Interfaces

The System shall be integrated with the aircraft interphone/intercom system (T=O). SAT#1 on the Interphone Audio Control Panel (IACP) shall be used to select the replacement SATCOM service (T=O). System shall be controlled via the CDU and Interactive Multi-Functional Display (IMFD) using the Interactive Hand Controllers, and through the FMS display pages (T=O).

3.3.1.3 Software Updates

System software changes shall be field loadable utilizing technology compatible to the current software load technology; either through the Common Interface Computer (T), or through the FMS using a Data Transfer Unit (O).

3.3.2 Electromagnetic Environment

The system shall operate to their intended operational electromagnetic environment without suffering or causing unacceptable performance degradation due to electromagnetic interference from/to other equipment (T). The system shall achieve equipment emission and susceptibility requirements IAW with MIL-STD-461G tests

CE106, CS103, CS115, CS116, RE103. (T=O).

The system shall have 100% compliance with national and international spectrum standards and guidance on the use of electromagnetic spectrum (T=O).

3.3.3 System Data Requirements

System shall support a minimum data rate of 4.8 kbit/second telephone service, 2.4 kbit/second data services (T=O).

3.3.4 Growth Path

The SATCOM replacement system shall have growth path to support ATN applications in accordance with the ICAO CNS/ATM SARPs (T=O). System shall have a growth path for additional channels (T=O). System shall have a growth path to Iridium Certus Broadband capabilities (O).

3.4 Adaptation Requirements

3.4.1 Mounting Location

The size of the legacy transceiver is L-14.930 in. nominal, W-10.210 in. nominal, H-7.380 in. nominal (ARINC 600 form factor 8 MCU).The SATCOM replacement transceiver shall be mounted in the same position as the legacy satellite transceiver in the electronics cabinet (T=O). All dimensions of the SATCOM transceiver shall be the same size or smaller than the legacy transceiver (T=O).

The SATCOM system shall allow for proper airflow and circulation to prevent overheating of the SATCOM

LRU (T=O).

The SATCOM replacement antenna shall be mounted in the same position (FS 720) as the legacy satellite antenna (T=O). The SATCOM antenna mounting plate shall attach to the current aircraft antenna mounting doublers (T=O).

3.4.2 Design and Construction

The system shall be designed and manufactured to minimize the effects of electrostatic discharge to system components IAW MIL-STD1686C (T=O).

3.4.2.1 Aircraft Compatibility

The system shall be able to operate in the presence of equipment currently installed on the aircraft with no degradation in performance to the SATCOM system (T=O). The system shall not degrade the capability of existing systems installed on the aircraft. (T=O). The system shall operate normally without interfering with the refueling capability of the Special Ops Air Refueler (SOAR) KC-135 aircraft (T=O). The system shall be integrated with existing maintenance planning and support equipment, computer resources, and other Air Mobility Command (AMC) logistics support infrastructure (T=O).

3.4.2.2 Electrical Power

The system shall perform as designed when supplied normal operation power quality in accordance with MIL- STD-704F (T=O). During operations where aircraft provided electrical power is outside of MIL-STD 704F specifications, the system shall not be damaged or permit an unsafe condition (T=O).

3.5 Environmental, Safety, and Operational Health (ESOH) Requirements

Installations in the cockpit, to include performance of maintenance, shall address human factors design requirements as defined in MIL-STD-1472G Department of Defense Design Criteria Standard Human Engineering (T=O). The system shall conform to existing human interfaces in accordance with TO 1C-135-2- 11-40 and TO 1C-135(K)R(II) (T=O).

3.6 System Environment Requirements

The system shall comply with environmental criteria established in Radio Technical Commission for Aeronautics (RTCA) DO-160G “Environmental Conditions and Test Procedures for Airborne Equipment,” tailored to the C/KC-135 environment as detailed in Table 1 (T=O). New or added components shall be tested within each test section unless otherwise specified in Table 1.

TESTS

ENVIRONMENTAL

TAILORING

DO-160G TEST

METHOD/PROCEDURE

Temperature Operating

Intermittent

Non-operating

-40 C to +55C

+70C for 30 minutes

-55C to +85C

Use Category A2 for the transceiver and Category D2 for the antenna. Test per Paragraph 4.5, Ref Table 4-1. Test per Paragraph 5.3, using 5 °C minimum variation per minute

Pressure

Maximum Continuous Minimum Maximum Rate

Sea Level 15,000

AMSL 50,000

AMSL

8,000 ft. to 50,000 ft.

within 15 seconds

Use Category A2 for the transceiver and Category D2 for the antenna, ref. Table 4-1. Test transceiver and antenna per Paragraph 4.6.1. Test transceiver per Paragraph 4.6.2, using maximum altitude as shown.

Humidity 95% with condensation Test transceiver per Paragraph 6.3.1, Category A. Test antenna per paragraph 6.3.2 category B.

Shock (Operational) 6 g 11 msec Test Per Paragraph 7.2

Crash Safety

Impulse

Sustained: 4G up, 8G down, 9G forward, 1.5 G aft, 4G lateral

Test per paragraphs 7.3.1 or

7.3.2 for Impulse.

Test per paragraph 7.3.3 using aircraft type 2, test type F, with C/KC-135 accelerations.

Vibration

Robust and Random

5 Hz to 2000 Hz

Test Per Paragraph 8.7 (Category R), Robust Vibration/Random test procedure, using Zone 2 for transceiver and Zone 1 for antenna.

TESTS

ENVIRONMENTAL

TAILORING

DO-160G TEST

METHOD/PROCEDURE

Explosive Atmosphere Non-ignition Test

Category E Equipment, para 9.3.2; hexane, para 9.4.4b +70 degree C max temp at site altitude. Max temp at 40K feet (AMSL)

Test Per Paragraph 9.6.2, or Mil-STD-810G Method 511.5, Procedure I.

Waterproofness Category R, Spray Proof Test for antenna Category Y, Condensation Test for transceiver.

Test transceiver per paragraph 10.3.1 and the antenna per paragraph 10.3.3

Fluids Susceptibility Test with Aviation Jet A Fuel and Ethyl glycol. No other fluid tests are necessary.

Test the antenna per paragraph 11.4.1 Spray Test. No test for the transceiver is necessary.

Sand and Dust Category S Test antenna and transceiver to paragraphs

12.3.1 and 12.3.2.

Salt Spray Category T Test antenna to paragraph

14.3. No test for the

transceiver is necessary.

Table 1: C/ KC-135 DO-160G Test Procedures

3.7 System Quality Factors

3.7.1 System Integrity and Supportability Considerations

The C/KC-135 SATCOM replacement system shall not degrade the reliability, mission availability, and maintainability of existing Line Replaceable Units (LRU) (T=O).

3.7.2 Mean Time to Repair (MTTR)

MTTR shall be used as a measure of system maintainability. MTTR is the required time to complete a corrective maintenance action. Corrective maintenance includes actions necessary to correct any inherent, induced, or no-defect malfunction, however it does not include the time required to obtain replacement parts/tooling. MTTR shall not exceed 60 minutes (T) with an objective of not exceeding 30 minutes (O).

3.7.3 Mean Time Between Failure (MTBF)

MTBF shall be used as a measure of logistics reliability. MTBF shall be at least 2500 hours for the satellite LRU and 4800 hours for the antenna (T=O).

3.7.4 Supportability Features

The system shall incorporate supportability design features such as captive fasteners, critical length wiring markings, scoop-proof connectors, and no safety wire (T=O).

3.7.5 Mission Reliability

The system mission reliability shall be equal to or greater than 90% (T=O) or 97% (O).

3.7.6 Operational Availability

The Operational Availability (Ao) shall be equal to or greater than 98% for Group A and 90% for Group B (T), or 98% for the entire system (O). The installation of the system and subsystems shall not degrade overall aircraft Ao (T=O).

3.8 Logistics Related Requirements

C/KC-135 SATCOM replacement system shall leverage Commercial-Off-The-Shelf (COTS) Iridium systems, and to the maximum extent possible, utilize fielded/stock listed parts (T=O). The replacement transceiver and antenna shall already be in use in a civilian or military application (T=O).

3.9 Other Requirements

The system shall have verified technical orders (TOs), delivered with operational test and evaluation, and distributed in final format prior to Initial Operating Capability (IOC) (T=O). System operation shall have 100% compliance with verified TOs (T=O).

3.10 Statutory, Regulatory, and Certification Requirements

3.10.1 Statutory Requirements

No additional statutory requirements identified except for any outlined in the previous sections.

3.10.2 Regulatory Requirements

No additional regulatory requirements identified except for any outlined in the previous sections.

3.10.3 Certification Requirements

The system shall attain airworthiness certification IAW MIL-HDBK-516C (T=O). The system shall be CNS/ATM certified in accordance with Air Force Instruction (AFI) 63-137(T=O). The system design shall be certified and accredited in accordance with the DoD Information Technology Security Risk Management Framework and use the Authority to Operate (ATO) from platform approval authority. An Interim Authority to Test (IATT) shall be acquired to perform Operational Testing (T=O). The required certifications and their respective guidance are listed below.

Airworthiness MIL-HDBK-516C

Authority to Operate (ATO) DoDI 8510.01

Communications, Navigation, Surveillance/ AFI 63-137

Air Traffic Management (CNS/ATM)

Operational Test and Evaluation (OT&E) Readiness Certification AFMAN 63-119

Spectrum Certification DoDD 4650.01

4 Verification Provisions Program requirements stated within this SRD shall be verified to show they have been met. The following methods shall be utilized to perform requirement verification in accordance with the Statement of Work (SOW):

Functional Configuration Audit/System Verification Review (FCA/SVR), Test Readiness Review (TRR), Technical Order (TO) Verification/Certification IAW TM-86-01Q, and the Physical Control Audit (PCA). The contractor, in conjunction with the C/KC-135 PO, shall define the verification methods and document them in the Level 3 System Test Description (STD), the System Requirements Verification Matrix (SRVM), IAW the Technical Manual Contract Requirements (TMCR).

4.1 Verification Methods

4.1.1 Demonstration

Verification by demonstration involves the operation, movement, or adjustment of an item. The item may be instrumented and its performance may be monitored, but only as an indirect function in support of the demonstration. Performance monitoring may have quantitative limits for satisfactory operation.

4.1.2 Test

Verification by test involves operation of the item with instrumentation to determine that specific quantitative performance requirements are met. These verifications shall use special test equipment or instrumentation to obtain very accurate quantitative data for analysis. The analysis of data derived from tests is an integral part of the test program.

4.1.3 Analysis

Verification by analysis shall show that the item meets specific requirements by technical evaluation of equations, charts, simulations, circuit diagrams, and other relevant data or by comparison with previously qualified equipment. The data evaluated may include specific parameters from component, module, or sub-assembly specifications, which may be subject to verification by other methods.

4.1.4 Inspection

Verification by inspection involves examination and review of descriptive documentation, including design documentation, and/or hardware or software listings to determine conformance with specified requirements.

4.1.5 Special Verification Methods

There are no special verification methods associated with the C/KC-135 SATCOM replacement system.

5 Requirements Traceability

5.1 Traceability to System Requirements

Traceability to this SRD and contractual requirements shall be provided via a requirements correlation matrix to be delivered by the contractor.

5.2 Traceability to Subsystems Requirements

Traceability to this SRD and contractual requirements shall be provided via a requirements correlation matrix to be delivered by the contractor.

6 Acronyms & Abbreviations

AE Aero-medical Evacuation

AFI Air Force Instruction

AFPD Air Force Policy Directive

AFMAN Air Force Manual

AMC Air Mobility Command

AMSL Above Mean Sea Level

Ao Operational Availability

AR Aerial Refueling

ASMC American Society of Mechanical Engineers

ATC Air Traffic Control

ATM Air Traffic Management

ATN Aeronautical Telecommunications Network

ATO Authority to Operate

BIT Built-inTest

CCA Clinger Cohen Act

CDU

Control Display Unit

CMU

Communications Management Unit

CNS Communications, Navigations, & Surveillance

COTS Commercial Off-the-shelf

CPDLC

Controller-Pilot Data Link Communication

DOD Department of Defense

DODM

Department of Defense Manual

EMC Electromagnetically Compatible

ESOH Environmental, Safety, and Operational Health

FAA Federal Aviation Association

FCA/SVR Functional Configuration Audit/System Verification Review

FMS Flight Management System

GATM Global Air Traffic Management

IACP Interphone Audio Control Panel

IAW In Accordance With

ICAO International Civil Aviation Organization

IMFD Interactive Multifunctional Display

IMS

Information Management System

KPP Key Performance Parameters

KSA Key System Attributes

LRU Line Replaceable Unit

MIL-SPEC

Military Specifications

MIL-STD Military Standards

MOPS Minimum Operational Performance Standard

MTR Mean Time To Repair

MTBF Mean Time Between Failure

OFP Operational Flight Program

OSS&E

Operational Suitability and Effectiveness

OT&E Operational Test & Evaluation

PCA Physical Configuration Audit

RTCA

Radio Technical Commission for Aeronautics

RTM Requirements Traceability Matrices

SARP Standards and Recommended Practices

SATCOM Satellite Communication

SEP Systems Engineering Plan

SOW Statement of Work

SRD Systems Requirement Document

SRVM System Requirements Verification Matrix

SSS System/Subsystem Specification

STD Software Test Description

TCTO Time Change Technical Order

TMCR Technical Manual Contract Requirements

TO Technical Order

TRR Test Readiness Review

U.S.

United States

USAF United States Air Force

Appendix A: C/KC-135 Requirements Correlation Matrix

The following requirements were extracted or derived from the Key Performance Parameters (KPP) and the Requirements Correlation Matrix Part I listed in the Air Mobility Command (AMC) C/KC-135 GATM Operational Requirements Document (ORD), AMC 007-97-B, dated 23 December 1998.

Requirement Description Paragraph 1 SATCOM Voice Iridium SATCOM voice system that meets ICAO SARPs for direct pilot-to-controller voice communication.

3.2.1.1 SATCOM Voice

2 SATCOM Voice Visual and aural indication of incoming calls. 3.2.1.1 SATCOM Voice

3 SATCOM Datalink CPDLC Compliant with DO-219 and ATS. 3.2.1.2 SATCOM Datalink

4 Beyond Line of Sight Data Link

Independent beyond-line of sight data link communication system that comply with ICAO SARPs is required. Minimum configuration is one SATCOM data link.

3.2.1.2 SATCOM

Datalink

5 Air Worthiness The system shall maintain platform airworthiness certification in accordance with AFPD 62-6.

3.11.3 Certification

Requirements

2 Software Loading Loading and verifying SATCOM LRU software updates in the field shall be accomplished by using existing maintenance equipment and interfaces.

3.3.1.1 Software Updates

3 Interoperability The system shall be able to operate in the presence of equipment currently installed on the aircraft with no degradation in performance to the SATCOM system.

3.4.2.1 Aircraft

Compatibility

4 Capability Reduction

The system shall not degrade the capability of existing systems installed on the aircraft.

3.4.2.1 Aircraft

Compatibility

5 Mean Time Between Failure –

The minimum shall be: SATCOM LRU: 2500 hours Antenna: 4000 hours

3.7.3 Mean Time Between

Failure (MTBF)

6 Mean Time To Repair

SATCOM replacement repairs shall be completed within one (1.0) hour.

3.7.2 Mean Time To

Repair (MTTR)

7 Mission Reliability

Mission reliability shall equal to or greater than 90% 3.7.5 Mission Reliability

8 Operational Availability

Ao for System shall not degrade overall aircraft operational availability. The Operational Availability shall be calculated and reported as required by AFI 21-101 Aircraft and Equipment Maintenance Management. Ao for Group A kits shall be at least 98%. Ao for Group B kits shall be at least 90%.

3.7.6 Operational

Availability

9 Human Systems Integration

The system shall apply human systems integration to applicable domains (manpower, personnel, training, human factors engineering, ESOH, personnel survivability, and habitability).

3.5 Environmental, Safety, and Operational Health (ESOH) Requirements

10 Operator Workload

The system shall not increase flight deck workload. 3.5 Environmental, Safety, and Operational Health (ESOH) Requirements

C/KC-135 Aero-I SATCOM Replacement Correlation Matrix

12 Supportability The system shall be fully integrated with existing maintenance planning and support equipment, computer resources, human systems integration, and other AMC logistics support infrastructure.

3.4.2.1 Aircraft

Compatibility

C/KC-135 Aero-I SATCOM Replacement Correlation Matrix Requirement Description Paragraph 13 Electromagnetic Environmental Effects (E3) and Spectrum Supportability

Systems shall operate in their intended operational electromagnetic environment without suffering or causing unacceptable performance degradation due to electromagnetic interference from/to other equipment in the same environment.

3.3.2 Electromagnetic

Environment

14 Frequency Management -

All applicable equipment shall comply with national and international spectrum standards and guidance on the use of the electromagnetic spectrum.

3.3.2 Electromagnetic

Environment

15 Aircraft Interface

Supports the following interfaces: Interface to CMUs: ARINC 758, Interface to CDUs: ARINC 739A

3.3.1 Interface

Configurations

16 Aircraft Interface

Supports the following interfaces: SATCOM communications interface ARINC 741 or ARINC 761

3.3.1 Interface

Configurations

17 Aircraft Interface

Supports the interface with C/KC-135 OFP 3.3.1 Interface Configurations

18 Technical Orders - Verified TOs shall be delivered concurrent with operational test and evaluation and be distributed in final format prior to IOC. System shall have 100% compliance with verified TOs.

3.9 Other Requirements