DRAFT_SRD_-_ROCC_for_FBO.pdf

SYSTEM REQUIREMENTS DOCUMENT

ROLL-ON CONFERENCE CAPSULES for the

C-17A GLOBEMASTER III AIRCRAFT

DRAFT, as of 24 April 2017 Prepared by:

AFLCMC/WLM C-17 SYSTEM PROGRAM OFFICE

MOBILITY DIRECTORATE

235 BYRON STREET SUITE 19A

ROBINS AFB GA 31098

Authenticated by: Approved by:

Mr. Robert David Col Amanda Myers Chief Engineer System Program Director

Distribution Statement A: Approved for public release; distribution in unlimited

CHANGE HISTORY

Change Version Date

CONTENTS

Section Paragraph Page

1.0 Scope 4

2.0 Applicable Document 4

3.0 System Requirements 7

3.1 Required States and Modes 7

3.2 System of Subsystem Functional Requirements 7

3.3 System External Interface Requirements 8

3.4 Environmental, Safety, and Operational Health (ESOH) Requirements 8

3.5 Electrical Requirements 9

3.6 System Environment Requirements 10

3.7 System Quality Factors 10

3.8 Design and Construction Requirements 10

3.9 Personnel‐Related Requirements 14

3.10 Amenities 16

4.0 Verification 18

1.0 SCOPE

1.1 Scope. This document establishes the system performance, design, and deliverables requirements for the Roll-On Conference Capsule (ROCC) for the C-17A Globemaster III aircraft (hereafter referred to as the C-17 or aircraft). All elements and configuration items of the ROCC system shall conform to the requirements delineated herein.

1.2 System Identification. The ROCC is a deployable command and control, roll-on/roll-off system that is comprised of two (2) hardware capsules: a Senior Leader Suite (SLS) and a Conference Room/Staff Area (CR/SA). Each capsule shall be designed to be loaded into the cargo compartment of the C-17 with existing United States Air Force (USAF) material handling equipment (MHE). The SLS and the CR/SA capsules shall each be permanently mounted to their respective supporting platform. The SLS capsule shall provide a private enclosed work and rest environment, physically separated but accessible from the CR/SA capsule. The ROCC shall permit occupancy by personnel during all C-17 phases of flight. The ROCC will not have any component software effecting cybersecurity. The ROCC shall be designed to connect to existing USAF Steel Eagle Power and Communications Support Pallet (Steel Eagle) for all electrical power and communication capabilities.

1.2.1 The ROCC capsules shall be designed to be restrained within the C-17 Aerial Delivery System (ADS). The only other physical interface with the C-17 will be a communication port for connecting an interphone communication cord, which will allow ROCC operators or aircrew to communicate with ROCC occupants. After loading the ROCC on the aircraft, the SLS and CR/SA capsules will be joined together such that their adjoining surfaces are flush with no gaps present, in order to minimize noise intrusion from the C-17 aircraft cargo compartment. The Steel Eagle pallet is loaded on the C-17 behind the ROCC and is then connected to the ROCC by the electrical and communications cables.

1.3 System Overview.

1.3.1 The operational threat environment for the ROCC shall be the same as the C-17 aircraft.

The ROCC is not intended to provide any additional protection to its occupants over that already provided by the C-17 aircraft with respect to anti-personnel weapons; anti-aircraft weapons; laser based weapons;

electronic attack; conventional air-to-air, surface-to-air, surface-to-surface weapons; and nuclear, biological, and chemical contaminants.

2.0 APPLICABLE DOCUMENTS

2.1 General. The documents listed in this section are specified in section 3.0, or 4.0 of the System Requirements Document (SRD) (or resulting specification). This section does not include documents cited in other sections of this SRD (or resulting specification) or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in section 3.0 or 4.0 of this SRD (or resulting specification), whether or not they are listed.

2.2 Government Documents.

2.2.1 Specifications, Standards, and Handbooks. The following specification, 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.

NOTE: When a cancelled government document is superseded by another document, the superseding document will be in effect unless otherwise specified. In the event there is no superseding document, the manufacturer may submit, at their discretion, alternatives to the cancelled government documents cited in this SRD. Unless the alternative is specifically approved by the Government, the cancelled government document shall remain fully applicable.

Specifications, Standards and Handbooks (Table 1)

Specification Title

MIL-HDBK-516C Department of Defense Handbook: Airworthiness Certification

MIL-HDBK-454B Department of Defense Handbook: General Guidelines for Electronic Equipment

MIL-STD-1472G Department of Defense Design Criteria Standard: Human Engineering

MIL-S-8512D Military Specification: Specification for the Design of Support Equipment, Aeronautical, Special, General

MIL-STD-464C Department of Defense Handbook Interface Standard Electromagnetic Environmental effects, Requirements for Systems

MIL-STD-704F Department of Defense Handbook Interface Standard: Aircraft Electric Power Characteristics

MIL-STD-1791B Department of Defense Interface Standard: Designing For Internal Aerial Delivery in Fixed Wing Aircraft

MIL-STD-202H Department of Defense Test Method Standard: Electronic and Electrical Component

MIL-STD-1366 Department of Defense Test Method Standard: Transportability Criteria

MIL-E-18927E Military Specification: Environmental Control Systems, Aircraft, General Requirements

MIL-DTL-27443F Pallets, Cargo, Aircraft, Type HCU-6/E and HCU-12/E

MIL-PRF-85285E Coating: Polyurethane, Aircraft and Support Equipment

CNSSAM

TEMPEST/01-13

RED/BLACK Installation Guidance

JSSG 2009A Department of Defense Joint Services Specification Guide: Air Vehicle Subsystems

JSSG 2006 Department of Defense Joint Services Specification Guide: Aircraft Structures

FAR 25.853 Airworthiness Standards: Transport Category Airplanes: Compartment Interiors

2.2.2 Other Government Documents, Drawings, and Publications. The following other Government documents, drawings, and publications 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.

Other Government Documents (Table 2)

Document Title

TO 1C-17A-3-1 Technical Order: Organic Maintenance- Structural Repair

TO 1C-17A-9 Technical Order: Loading Instructions Manual

TO 1C-17A-1 Flight Manual

TO 1-1-8 Technical Order: Application and Removal of Organic Coatings, Aerospace and non-Aerospace Equipment

TO 1-1-691 Technical Order: Cleaning and Corrosion Prevention and Control, Aerospace and non-Aerospace Equipment

TO 35-1-3 Corrosion Prevention and Control, Cleaning, Painting and Marking of USAF Support Equipment

TO 1-1A-9 Aerospace Metals – General Data and Usage Factors

AFMAN 17-1301 Computer Security (COMPUSEC)

TD 7031843 Rev N Drawing: Pallet Assembly, Cargo – HCU-6/E

SB-ICD-17-001 Interface Control Document, Steel Eagle/Silver Bullet (Reference Only)

2.3 Non-Government 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.

Non-Government Publications (Table 3)

Standard Title

SAE AS8049 Performance Standard for Seats

SAE AS50881 Wiring Aerospace Vehicle

SAE AIR1826A Acoustical Considerations for Aircraft Environmental Control System Design

ASTM E2638 Standard Test Method for Objective Measurement of the Speech Privacy Provided by a Closed Room

SAE AS4073A Air Cycle Air Conditioning Systems for Military Air Vehicles

SAE AMS-STD-595A Colors Used In Government Procurement

Battelle MMPDS-11 Parts 1&2

Metallic Materials Properties Development and Standardization

2.4 Order of Precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of the document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3.0 SYSTEM REQUIREMENTS

The detailed requirements for the ROCC are defined below and may be separated into two categories:

- Threshold (T) describes the minimum acceptable capability or level of performance

- Objective (O) denotes a desired capability level of performance, beyond the minimum required

The (T) and (O) annotations will follow the sentence(s) to which they apply. The Threshold (T) annotation will only be used when the requirement also has an Objective (O). Unless otherwise noted, all requirements listed in this document are threshold requirements.

3.1 Required States and Modes. The ROCC shall be designed and certified to permit occupancy and use of all integrated systems and equipment during all phases of flight in such a manner that the C-17 can maintain its airworthiness certification in accordance with (IAW) MIL-HDBK-516C.

3.2 System of Subsystem Functional Requirements. The ROCC and its internal components and subsystems shall be designed to incorporate MIL-STD-1472G requirements, and designed to accommodate a range of people from a 5th percentile female to 95th percentile male (MIL-STD-1472G, APPENDIX B, General Forces).

Where possible, standard and/or common parts/materials as called out in Technical Order (TO) 1C-17A- 3-1, TO 1-1A-9, and the Metallic Materials Properties Development and Standardization (Battelle MMPDS-11 Parts 1&2) document shall be used in the design and development of the ROCC.

3.2.1 Structures. The ROCC structures shall be designed IAW requirements called out in MIL-S-8512D and applicable amendments and be able to meet or exceed the following requirements:

3.2.1.1 Requirements for structural loading conditions in a fixed wing aircraft cargo compartment, crash loads per MIL-HDBK-516, Section 5.1.9 (4) and JSSG2006 for fixed removable equipment

3.2.1.2 MIL-HDBK-516, Section 18.1.1 (SAE AS8049 with a 250 pounds occupant) requirements for the seat, seat restraint and attachment to ROCC floor.

These requirements include but are not limited to the capsule shell structure, the seats, seat belts and seat mounts, accessory mounts, such as the TV mounts and any other wall or ceiling mounted device mounts, doors and door hardware, etc.

3.2.2 Electrical. The ROCC electrical systems shall be designed IAW requirements called out in MIL-S-8512D, CNSSAM TEMPEST/01-13 and applicable amendments and SAE AS50881.

3.3 System External Interface Requirements.

3.3.1 Aircraft Interfaces. The ROCC shall be compatible with the existing C-17 aircraft aerial delivery system (ADS) for restraint of the capsule platforms IAW MIL-STD-1791B, drawing 7031843, MIL-DTL-27443, and TO 1C-17A-9. The ROCC design shall not exceed any aircraft limitations or require any modification to the aircraft cargo compartment or the ADS to include the floor rollers, pallet locks, and tie down rings.

3.3.2 Steel Eagle Interfaces. The ROCC shall interface with the Steel Eagle Power & Communications Support Pallet (Steel Eagle) IAW the Interface Control Document (ICD) SB-ICD-17-

001. All power and communications connections for the ROCC shall come through the Steel Eagle. (See paragraph 3.8.9 of this document for the only exception)

3.3.3 Material Handling Equipment (MHE). The Senior Leader Suite (SLS) and Conference Room/Staff Area (CR/SA) capsules shall be loadable onto the C-17 aircraft using existing Air Force MHE according to MIL-STD-1791B or using common K-loaders, deployed world-wide for USAF use.

The design of the ROCC shall not require the modification of any MHE or the development of a new peculiar K-loader to load the ROCC capsules onto the C-17. The SLS and CR/SA capsules shall each have provisions for interfacing with the C-17 aircraft cargo winch to assist with loading and unloading.

3.3.4 Maintenance. The ROCC shall be capable of mating up with service vehicles/support equipment for general maintenance purposes including, but not limited to, servicing the lavatory, replenishing fresh, gray, and black water tanks, and servicing the ECS. Condensation from the ECS shall not be allowed to drip onto the aircraft floor. The designer of the ROCC shall not require the modification of any servicing equipment.

3.4 Environmental, Safety, and Operational Health (ESOH) Requirements.

3.4.1 Noise Attenuation. The ROCC shall be constructed so that the exterior walls reduce both pass-through sound and interior generated noise to a level no greater than 65 A-weighted decibels (dB(A)) in all phases of flight, except for takeoff (also see MIL-STD-1472G paragraph 5.5.4.6.2).

3.4.2 Lighting. The ROCC interior lighting, at maximum intensity, without the use of individual reading lights and with no external lighting, shall provide a minimum of 540 lux throughout the system. The lighting within the closet(s) shall provide a minimum of 300 lux. The ROCC lighting shall be fully controllable throughout the designed range of possible illumination levels. The lighting in the CR/SA shall be on two (2) different circuits in order to allow the lights above the monitor to be dimmed and/or turned off to better see the monitor screen when in use.

3.4.2.1 SLS Lighting. The SLS shall have an ambient lux, without lighting and compartment doors closed, no greater than 0.01.

3.4.2.2 Emergency Lighting. Each ROCC compartment shall include an emergency lighting system that is activated by the loss of power to the ROCC compartment. Each capsule shall also incorporate a ‘disarm’ feature on the emergency lighting system so the ROCC can be stored for extended periods in a non-powered state without the emergency lights activating. The disarming feature shall be well-labeled or designed so the ROCC cannot be in use while the emergency lights are disarmed.

Emergency lighting shall operate using rechargeable batteries for a minimum of 20 minutes. The rechargeable batteries shall be capable of recharging once power to the ROCC is restored using the existing power supplied by the Steel Eagle.

3.4.3 Smoke & Flammability. Materials used in the construction of the ROCC, shall meet flammability/smoke requirements IAW FAA FAR 25.853 and JSSG 2009.

3.4.3.1 Fire Extinguishers. There shall be one (1) hand-held fire extinguisher located in each capsule compartment IAW Passenger Safety Requirements, MIL-HDBK-516C. Fire extinguishers shall be NFPA 10 approved, and the proper extinguishers shall be selected based on the standards and regulations within NFPA10.

3.5 Electrical Requirements.

3.5.1 Electrical Power Source. The ROCC shall utilize the Steel Eagle as its sole electrical source. The ROCC shall not draw more power than the Steel Eagle can provide (Two (2) 50 Amp, 120VAC, 60Hz single phase circuits IAW the Steel Eagle ICD.

3.5.2 Electrical Power Quality. Power line conditioners and surge protection shall be used for the electrical power intended for use with "carry-on" devices (e.g., laptop power supplies) used within the ROCC. Power line conditioners and surge protectors shall be of the size and type to regulate voltages and protect "carry on" devices from power surges.

3.5.3 Electrical Power Distribution. All electrical devices dedicated to and mounted into or onto the ROCC and internal ROCC electrical distribution networks shall receive electrical power via a power distribution panel located either within the ROCC or externally attached to the CR/SA capsule. The ROCC’s power distribution panel shall serve as the electrical power interface between the ROCC and the Steel Eagle as specified in paragraph 3.3.2.

3.5.4 Electrical Power Protection. All electrical devices dedicated to, mounted into or onto the ROCC, and internal ROCC electrical distribution networks shall be protected by circuit breakers or similar electrical protection devices separate and apart from the C-17 aircraft electrical protection devices.

3.5.5 Electrical Appliance Outlet Requirements. The ROCC shall include a minimum of two

(2) three-prong 120VAC, 60 Hz, duplex outlet per wall in each occupied capsule capable of powering all carry-on devices without requiring modification to the existing device power plug.

3.5.5.1 The CR/SA shall have one duplex electrical outlet at each seat location for occupant use.

3.5.5.2 The ROCC shall include one (1) three-prong 120VAC, 60 Hz, duplex outlet per mounted device and one (1) for the “carry-on” printer, within four (4) feet of mounted/installed location.

Note: All ROCC electrical outlets shall comply with MIL-STD-202 and its test methods.

3.5.6 Electrical Cabling. The ROCC electrical system shall be designed and installed IAW

CNSSAM TEMPTEST/01-13.

3.5.7 Grounding and Bonding All electrical grounding and bonding shall be designed and installed in compliance to MIL-STD-464C (para 5.11 and 5.12), CNSSAM TEMPTEST/01-13, and MIL-STD-704F (para 5.4.1).

3.5.8 Wiring Design and Separation. All electrical wiring shall be designed and installed in compliance with MIL-HDBK-454B, CNSSAM TEMPTEST/01-13 and SAE AS50881.

3.5.9 Electrical Emission Security. The contractor shall follow the design requirements in CNSSAM TEMPTEST/01-13 to ensure electrical emission security for the ROCC.

3.6 System Environment Requirements.

3.6.1 Storage. The ROCC shall be designed to be stored in all weather conditions for a maximum of 3 days, with only negligible damage as defined by TO 1C-17A-3-1 to external structures, fixtures or components.

3.6.2 Protective caps shall be provided to cover all external outlets to the ROCC, to protect against water and particle intrusion. The caps shall be permanently tethered to the outlet or remain separate and stored in their own storage case/bag that remains with the ROCC at all times. If they remain separate from the outlets, a storage location within the ROCC is required.

3.6.3 The capsules shall have the capability to be transferrable using a forklift from the ground, high bay stand, or K-loader to standard ground transport vehicle/equipment/trailer upon which it can be restrained IAW MIL-STD-1366 for transport via ground transportation.

3.6.4 Operation. The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall be capable of operating in an explosive atmosphere as defined by MIL-STD-810G method 511.6 procedure I.

The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall be capable of withstanding rapid decompression as defined in MIL-STD-810G method 500.6 procedure III. The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall meet Electromagnetic Compatibility (EMC) and Electromagnetic Interference (EMI) requirements of MIL-STD-464C and MIL-STD-461G as applied to non-flight critical carry-on equipment.

3.7 System Quality Factors. The structure of the ROCC shall be designed and built to last a minimum of 35 years.

3.7.1 The Environmental Control System (ECS) shall be designed to have a Mean Time Between Failure (MTBF) of not less than 500 operating hours.

3.8 Design and Construction Requirements.

3.8.1 General Construction. The ROCC shall occupy no more than a total of five standard 463L pallet positions in the aircraft, on the 108 inch bias. The SLS shall occupy no more than two standard 463L pallet positions and the CR/SA shall occupy no more than three standard 463L pallet positions.

3.8.1.1 The maximum height of either the ROCC shall not exceed 123 inches, measured from the top of the aircraft ADS rollers to the top of the capsule.

3.8.1.2 The maximum width for loading and unloading of each compartment is 120 inches W (+/- 60 inches from centerline), which is required to avoid impact with the C-17 aircraft’s aft fuselage strakes. The design of the ROCC must allow for visual inspection and verification of alignment into the ADS rail system and engagement of the pallet locks.

3.8.1.3 The base/pallet structure of the individual capsules shall be constructed to be able to rest on rollers of various widths and floor positions without damage or deformation to the base/pallet structure (see MIL-STD-1791B Figure A-11). NOTE: The list of 25K loaders shown in MIL-STD-1791B Figure A-11 is not a comprehensive list. Other loaders may be used in the future that may be suitable for use with the ROCC.

3.8.1.4 The capsules shall be equipped with anti-rattle devices.

3.8.1.5 The ROCC shall have D-rings installed capable of holding 7,500 pounds each installed mid-height on the exterior of the long walls of both the SLS and CR/SA capsules. These D-rings shall be attached to the main structure beams of the capsules.

3.8.2 Weight Threshold. The ROCC has a threshold maximum weight limit of not more than 13,155 pounds for the SLS and 23,022 pounds for the CR/SA. The weight limit of each capsule is a total operational weight. The SLS and CR/SA limits shall include 250 pounds for the weight of each seat occupant. The SLS shall be designed for two (2) occupants and two (2) visitors for a total of four (4) occupants, and the CR/SA shall be designed for a total of nine (9) (T) or eleven (11) (O) occupants (See paragraph 3.10.5). The following carry-on equipment that occupants will bring into the ROCC.

- Luggage: 20 pounds per person

- Laptops / other Personal Electronic Devices: 15 pounds per person

- Communication Kits (printers, routers, etc.): total for 125 pounds for each flight

- Other Mission-Required Bags: total of 80 pounds for each flight

3.8.2.1 These weight limits will allow each of the two ROCC compartments to be loaded one at a time using a 25K loader. (T) The ROCC has desired maximum weight requirement, with full fresh water tanks and serviced lavatory, of not more than 25,000 pounds combined. This would allow both capsules to be loaded simultaneously. (O)

3.8.3 Corrosion Prevention. The ROCC shall have organic protective coatings and corrosion preventive sealants applied to the structures IAW Air Force requirements listed in TO 1-1-8, TO 1-1-691, and TO 35-1-3. The required topcoat is MIL-PRF-85285E Type IV Class H, AMS-STD-595A color 36173.

3.8.3.1 There shall not be any surface treatments, primers, topcoats or other corrosion preventive compounds (CPC) containing hexavalent chromium approved for use on the ROCC.

3.8.3.2 No materials that utilize cadmium/chromium plating shall be utilized on the

ROCC.

3.8.3.3 EPA 100 list and Mil Spec reference needs to be added here.

3.8.4 Doors. Doors for ingress and egress shall be designed IAW MIL-STD-1472G paragraph

5.11.2. Each capsule compartment shall incorporate one (1) external entry/exit door that shall be capable of being secured/locked from inside the capsule.

3.8.4.1 Entry/exit doors shall be capable of being unlocked from outside the capsules without requiring the use of electrical power.

3.8.4.2 At least one (1) entry/exit door in each capsule shall open inward.

3.8.4.3 There shall be one lockable door installed between the SLS and CR/SA capsules.

3.8.5 Pressurization. The capsules shall maintain the same pressure altitude (PA) as the interior of the C-17 aircraft.

3.8.5.1 The ROCC shall have the capability to automatically neutralize the pressure differential between the capsules and the aircraft cargo compartment in the event of a rapid decompression situation. A manual capability shall be provided should the automatic capability malfunction.

3.8.5.2 When the C-17 aircraft is unpressurized, the ROCC shall maintain full operational capability to include all devices (e.g., flat screen/flat panel monitor) at PAs equal to sea-level minus 200 feet and up to and including 14,000 feet Mean Sea Level (MSL) cabin altitude under Standard Day conditions. (T) It is desired that when the aircraft is unpressurized, the ROCC shall maintain full operational capability between minus 1,000 feet and 14,000 feet MSL. (O)

3.8.5.3 The ROCC shall maintain full operational capability of all safety features and safety related sub-components (e.g., emergency lighting) at PAs equal to sea-level minus 1000 feet and up to and including the service ceiling as defined in TO 1C-17A-1-1 Part 4 using four (4) engines under Standard Day conditions.

3.8.6 Water Tanks. The ROCC fresh, gray, and black water tanks shall be designed to be compatible with standard airfield fleet service trucks and shall be capable of being serviced on board the aircraft.

3.8.6.1 The ROCC’s fresh, gray, and black water tanks shall be designed so that no damage will occur to the tanks or the associated plumbing, in the event the contents freeze.

3.8.6.2 The fresh, gray, and black water tanks shall each have an externally mounted level indicator easily observable by operators/maintainers.

3.8.6.3 Service hoses for the water tanks shall be supplied and stored within the ROCC.

The service length of the hoses shall be long enough to reach servicing vehicles positioned outside the C- 17 near the forward fuselage door or one of the paratroop doors.

3.8.7 Communications.

3.8.7.1 Communication w/ Loadmaster. Both ROCC compartments shall include a stand-alone (not connected to the aircraft intercom) push-to-talk two-way communications capability between the ROCC occupants and the C-17aircraft loadmaster.

3.8.7.2 Passenger Data Ports. The ROCC shall be equipped with communications data ports for every seated passenger plus the printer stand. All user ports shall have a network connection to an external patch panel for interfacing with the Steel Eagle.

NOTE: The ROCC shall provide access to all communications capabilities within 3 feet of each working or seating position.

3.8.7.3 Communications Equipment. The ROCC shall be equipped with secure/non-secure voice communication options that include Plain Old Telephone System (POTS), Voice over Internet Protocol (VoIP) and Integrated Services Digital Network (ISDN).

3.8.7.4 Network Data Ports. Data ports shall include commercial Internet, Unclassified but Sensitive Internet Protocol Router Network (NIPRNet), Secret Internet Protocol Router Network (SIPRNet), and Top Secret/Sensitive Compartmented Information (TS/SCI). Data and Voice network wiring shall be installed to meet security guidelines IAW AFMAN 17-1301.

3.8.7.5 Wireless Access. The ROCC shall include a network port and provisional space, including 120V power, to accommodate an occupant-provided carry-on device with a maximum size of 12inches L x 12inches W x 2inches H, supporting wireless access point installation. The location of the access point shall permit maximum wireless coverage from end to end of the two capsules when installed together and be easily accessible by the occupants. The port shall be terminated at an external patch panel for interfacing with a wireless access point controller located in the Steel Eagle.

3.8.7.6 Communication System. The communication system shall be designed and installed IAW CNSSAM TEMPTEST/01-13. The color scheme of the wiring shall be in compliance to Table 4.

CABLE COLOR SCHEME (TABLE 4)

UNCLASSIFIED GREEN

COLLATERAL CONFIDENTIAL BLUE

COLLATERAL SECRET RED

COLLATERAL TOP SECRET ORANGE

SPECIAL CATEGORY YELLOW

3.8.7.7 Electrical Isolation BLACK lines connected to RED equipment (such as VTC or secure voice) shall follow the design requirements in CNSSAM TEMPTEST/01-13.

The electrical isolation requirement for secure voice systems shall be applied to the system as a whole, including the Intercommunication Systems (ICS), headsets/handsets, and any wiring between the system components.

3.8.7.8 Wall Mounted Monitors. Each capsule shall be equipped with a wall mounted High Definition (HD) flat screen/flat panel monitor to support IPTV/Satellite TV/ streaming television feeds, and VTC feeds from the Steel Eagle. Monitors shall be equipped with a separate/detachable high resolution camera, with the capability to be positioned up to 12 feet from the monitor. The wall-mounted monitors shall be capable of being used to play Blu-ray and DVD media formats as well as serve as a computer monitor for a secure/non-secure personal computer (PC) or tablet. There is no requirement for the monitor and playback device(s) to be a single unit. Monitor sizes should be 32-in class for SLS; 42-inch class for CR/SA (T), or 42-inch class for SLS; 52-inch class for CR/SA. (O)

3.8.7.8.1 Each wall mounted HD flat screen/flat panel monitor shall be equipped with a dedicated Blu-ray/DVD player. The monitor shall be capable of being operated using a single hand-held Infrared (IR) remote control unit which controls operation and all functions of the video playback devices as well as the monitor.

3.8.7.8.2 For security reasons, the monitors shall not have residual memory or other ability to retain displayed data after being powered off.

3.8.7.8.3 The monitors shall be in a shatterproof enclosure in event of aircraft crash. The enclosure shall be capable of enduring a 9g force impact from a small hand-sized object without shattering. The monitors themselves shall be shatter-resistant via the use of a film screen protector or some other mechanical means.

3.8.7.9 Speakers. Each capsule shall be equipped with stereo speakers capable of supporting audio playback of CD, DVD, or Blu-ray media and unsecure video teleconferencing while the aircraft is in flight. The speakers are not required to be an integral part of the wall-mounted flat screen monitors. Speakers shall be secured within the ROCC to prevent movement during aircraft operations.

3.8.7.10 Headset Jacks. Each seat in the ROCC shall include a two-way headset jack with independent volume and playback source selection control supporting IPTV, VTCs, play back of CD, DVD, Blu-ray media, and interface with the Steel Eagle phone system while the aircraft is on the ground or in flight. The jacks shall be standard dual aviation jacks.

3.9 Personnel-Related Requirements.

3.9.1 Entry/Exit. Entry and exit doors shall have placards affixed describing door operation on both sides of the door. The doors shall be capable of being secured in the open position, and doors intended for emergency exits shall be annunciated.

3.9.2 Water Requirements. The ROCC fresh, gray, and black water tanks shall be designed to support at a minimum a four-day mission at 16 hours per day for two (2) persons (T). The ROCC shall be designed to support a seven-day mission at 16 hours a day for two (2) persons (O).

3.9.3 Warning/Caution Indicators. All dangers, warnings, cautions, notices, and annunciators shall provide visual and auditory cues IAW MIL-STD-1472G paragraphs 5.7.2 and 5.3.1, where appropriate.

3.9.4 Audio/Visual Annunciators. The ROCC shall include a combination audio and visual emergency annunciator capability operated by the C-17 aircraft loadmaster to notify the ROCC occupants, and to allow the ROCC occupants to notify a member of the C-17 aircraft aircrew should the need arise.

Per MIL-STD-1472G: Alerts/warning signals in the ROCC must be at least 15 dB above the noise environment (5.3.1.2.1). In quiet areas (<45 dBA), advisory signals should be between 50 and 70 dBA.

(5.3.1.2.4).

3.9.4.1 The ROCC shall have annunciators located on at least two (2) external sides of the capsule to provide a visual warning whenever the ROCC ECS is inoperative or whenever the internal ROCC temperature is below 40° F or above 90° F.

3.9.4.2 Emergency exits, or doors intended to be used as emergency exits, shall be annunciated. Emergency exit annunciation shall be powered using rechargeable batteries. The batteries shall be capable of recharging while the ROCC is connected to the Steel Eagle.

3.9.4.3 The ROCC shall include a connection port to the aircraft’s Public Address system in order to receive instructions in the event of emergency. An existing C-17 aircraft interphone cord will be used to connect the ROCC to an aircraft ICS headset receptacle panel.

3.9.5 Control Labeling. Labeling of the controls within the ROCC shall be IAW MIL-STD- 1472G paragraph 5.1.1.5.

3.9.6 Environmental Control System (ECS). The ECS shall be designed IAW SAE AS4073, MIL-E-18927, and SAE AIR1826.

3.9.6.1 The ROCC shall include an ECS capable of maintaining an internal capsule temperature of 70° Fahrenheit (F) +/- 8° F for a minimum of one hour when the cargo compartment temperature range outside the ROCC is between 40 and 100° F. (T) The ROCC should include an ECS capable of maintaining an internal capsule temperature of 70° Fahrenheit (F) +/- 5° F for a minimum of two hours when cargo compartment temperature range outside the ROCC is between 30 and 110° F. (O)

3.9.6.2 The thermal load generated by the ROCC shall not exceed the ability of the C-17 aircraft to maintain the desired ambient temperature in the cargo compartment.

3.9.6.3 The ROCC shall include a means of providing aircraft cargo compartment air to the inside of the capsules, in the event of ROCC Heating, Ventilation, and Air Conditioning (HVAC) system failure.

3.9.7 Seats. All ROCC passenger seats, to include the Divan/Couch, shall be business-class seats.

3.9.7.1 All ROCC seats shall swivel and be such that the seats can be locked into a position where the longitudinal axis of the seat is parallel to the longitudinal axis of the aircraft. For other than take-off and landing the seats shall be capable of swiveling at least 180 degrees, from forward to inboard to aft, and be capable of locking into position.

3.9.7.2 All ROCC seats, including the divan, shall have a seat harnesses to restrain occupants during flight.

3.9.7.3 All ROCC seats shall have multiple reclining positions down to 45 degrees, with a retractable (pull out mechanical) footrest. (T) All ROCC seats should have multiple reclining positions including a position that is fully berthable, with a retractable (pull out mechanical) footrest. (O)

3.9.7.4 The ROCC shall contain stowage provisions near each seat for portable Emergency Passenger Oxygen System (EPOS) to be provided by the Air Force. Stowage shall be designed to accommodate a range of people from a 5th percentile female to 95th percentile male in each seat can reach the EPOS bag with the seat belt fastened. There shall also be an attached Directions for Use Card, per seat, divan, and lavatory located within the ROCC.

3.9.7.5 There shall be stowage provisions for Air Force-issued Adult/Child Life Preserver Units (LPU) IAW A-A-50652 located at each seat. The maximum dimensions of each LPU will be 14.5 inches x 8 inches x 6 inches in size. Design shall accommodate a range of people from a 5th percentile female to 95th percentile male.

3.10 Amenities.

NOTE: All installed equipment (to include monitors, Blu-Ray/DVD players, etc.) shall be mounted/secured for all phases of flight.

3.10.1 Wall Clock. Each capsule (SLS and CR/SA) shall include a digital wall clock with internal battery back-up power to maintain correct time. The clock shall be able to display three synchronized times in either standard 12 hour or 24 hour format, as selected by the user: local time at the departing airfield, GMT (Zulu) time, and local time at the destination airfield.

3.10.1.1 Batteries used to power the wall clocks shall be changeable without having to remove the clock from the wall.

3.10.1.2 The controls used to enter/correct clock time shall be located on the front of the clock or easily accessible without having to remove the clock from the wall to adjust the time.

3.10.1.3 Each wall clock shall have internal illumination to allow occupants to determine the time under any internal capsule illumination levels. (T) It is desired that the wall clocks should automatically adjust to changes in ambient light levels. (O)

3.10.2 Trash Receptacles. The ROCC shall include a trash receptacle in each occupied compartment. Trash receptacle(s) shall be capable of being secured within the ROCC; however, be easily removed for servicing with one hand.

3.10.3 Storage Container. The ROCC shall incorporate a lockable, non-GSA approved storage container, secured within the capsule, which is a minimum of 10 inches deep, 12 inches wide, and 16 inches long to provide a means for occupants to temporarily secure materials (documents and electronic media) while on board the aircraft. The container shall be marked as “Not Approved for Classified Documents/Media.”

3.10.4 Reading Lights. The capsules shall include one (1) ceiling-mounted reading lamp directly above each seat and two (2) ceiling-mounted reading lamps above each end of the divan/couch. Each lamp shall be narrowly focused and/or shrouded so as not to disturb the adjacent occupant(s). The on/off switch for each lamp shall be wall- or table-mounted and within reach (without having to stand or exit the seat) of the seat/divan/couch occupant requiring use of the lamp. Design shall accommodate a range of people from a 5th percentile female to 95th percentile male.

3.10.5 Conference Room/Staff Area (CR/SA)

3.10.5.1 Carry-on Bag Stowage. The CR/SA shall have provisions to store two (2) 22-inch x 14-inch x 9-inch “carry-on” bags in an enclosed closet. These stowage provisions are not required to be within arm’s reach of the seated occupant.

3.10.5.2 Garment Bag Stowage. The CR/SA shall have provisions to hang up two (2) 24-inch x 5-inch x 55-inch garment bags in an enclosed closet. These stowage provisions are not required to be within arm’s reach of the seated occupant.

NOTE: The Bag Stowage and Garment Bag Stowage provisions may be satisfied by a single closet.

3.10.5.3 Overhead Stowage. The CR/SA shall include a minimum of two (2) wide-body style commercial overhead stowage bins.

3.10.5.4 Thermostat. The ROCC shall include a thermostat located in the CR/SA which can display both ambient temperature as well as desired (as set) temperature.

3.10.5.5 Table & Seating. The CR/SA shall include a conference table capable of seating nine (9) individuals. The nine seats shall be usable for all phases of flight and as in-flight work stations.

(T) The CR/SA should include a conference table capable of seating eleven (11) individuals. The eleven seats shall be usable for all phases of flight and as in-flight work stations. (O)

3.10.5.6 CR/SA Mirrors. The CR/SA shall include one (1) full-length, shatterproof mirrors located on the inside of the garment bag storage closet.

3.10.5.7 CR/SA Printer Shelf. The CR/SA shall include a printer shelf/stand, with nearby data port, capable of supporting a standard, all-in-one printer/copier/scanner/fax and accompanying supplies. Note: End users will bring their own printer.

3.10.6 Senior Leader Suite (SLS).

3.10.6.1 SLS Segregation. The SLS shall be segregated from CR/SA, such that private conversations can be conducted in each capsule. Speech Privacy Class (SPC) between the SLS and CR/SA shall be no less than 75, IAW ASTM E2638.

3.10.6.2 SLS Berthing Arrangements. The SLS shall include berthing/sleeping arrangements for two (2) adults. The SLS berth shall incorporate a means to secure the occupants while sleeping.

3.10.6.3 Divan/Couch Seating Arrangements. Users shall be able to stow the berth and use it as a divan/couch when not in use for sleeping (first class airline seats shall not be used to meet this requirement). Personnel will not occupy the divan/couch during takeoff and landing.

When used as a divan/couch, seat belts shall be provided to restrain occupants during all other phases of flight.

3.10.6.4 SLS Luggage Stowage. The SLS shall contain a closet with internal lighting, door, hanging rod, and a shatterproof full-length mirror.

3.10.6.5 The SLS shall have a provisions for stowage of four (4) 24-inch x 5-inch x 55-inch garment bags, and for four (4) 22-inch x 14-inch x 9-inch “carry-on” bags.

3.10.6.6 SLS Workstation. The SLS shall contain a desk/table with two (2) 120 VAC/60 Hz duplex electrical outlets and two (2) business-class track-and-swivel seats. The desk/table work surface shall be adequately sized to fully support two (2) 17-inch laptop computers and two (2) legal pads placed side by side.

3.10.6.7 SLS Lavatory. The SLS shall contain a private lavatory that has a sink with hot and cold running water, toilet, vanity cabinet, shatterproof mirror, and lockable privacy door. The lavatory room, and gray and black water tanks shall be vented to the cargo compartment atmosphere and shall include a serviceable filtering system to minimize odors and fumes being released.

3.10.6.8 The lavatory shall include one (1) duplex electrical Ground Fault Interrupter (GFI) outlet (120VAC/60 Hz) installed in the vanity cabinet area for passenger devices.

3.10.6.9 SLS End Table(s). The SLS shall include an end table located on one end of the divan/couch. (T) The SLS should include an end table located at each end of the divan/couch. (O)

3.10.7 ROCC Treatments and Coverings. The ROCC shall include carpet, treatments, and coverings of a quality equal to or better than what is currently found in commercial airline business class compartments in form and function.

4.0 Verification

4.1 Verification testing will be required at the system, sub-system and aircraft integration level to insure all requirements are satisfied for the ROCC. When commercial, standard components are utilized, contractor redundant verification testing will not be required, if the FAA or other USG/commercial certifying agency has tested the applicable components and they meet our performance level. The Contractor shall reference the USG / commercial test report and certification document(s) in the applicable ROCC system test report submitted on the Data Accession List (DAL). 4.2 The attached matrix, “ROCC SRD Verification Test Matrix”, provides the anticipated verification level for each requirement listed within the SRD.

SRD Para Requirement *Ver Method KTR Test

Report Req’d?

SE or C‐17

Integration Test

Req'd?

Remarks

3.1

Required States and Modes

Occupancy and use of all integrated systems during all phases of flight.

(IAW MIL‐HDBK‐516C)

T Y Y(C‐17)

Flight test and demonstration witnessed by USG rep

3.2

System of Subsystem Functional Requirements

Human Factors

(5th percentile female/95th percentile male)

(MIL‐STD‐1472G)

D/A N N

Demonstration to show that the capsule can be properly occupied and used by anyone within the range of a 5th percentile female and 95th percentile male. Demonstation must be shown at both ends of this spectrum.

Analysis may be used with prior approval from USG (requires 3‐D model of occupancy).

3.2.1

Structures

ROCC structures meet or exceed

(Mil‐S‐8512D)

A Y N

3.2.1.1

Structural loading conditions‐ fixed wing aircraft cargo compartment

(MIL‐HDBK‐516C)

Fixed removeable equipment

(JSSG 2006)

T Y N

These two items will be evaluated at the dynamic crash test for fwd loads and analysis for the lateral, up, down and aft loads.

3.2.1.2 Seats, restraints and floor attachment

(MIL‐HDBK‐516 Section 18.1.1, SAE AS8049) T Y N

Testing witnessed by a USG rep. If seats already have airworthiness approval, they do not have to be retested except the attachment to the floor.

3.2.2 Electrical

(MIL‐S‐8512D, CNSSAM TEMPEST/01‐13, SAE AS50881)

I N N

DRAFT, as of 24APR17 ROCC SRD VERIFICATION ‐ TEST MATRIX

3.3 System External Interface Requirements

3.3.1

Aircraft Interfaces

Compatible with existing ADS. Platform restraints‐ no modifications.

(ADS IAW MIL‐STD‐1791B, Drawing 7031843, MIL‐DTL‐

27443, TO 1C‐17A‐9)

D N N

Combined with overall val/ver.

3.3.2 Steel Eagle Interfaces

ICD SB‐TCD‐17‐001

T Y Y(SE)

Can likely combine this testing with overall val/ver.

3.3.3

Material Handling Equipment

Loadable without modification with existing MHE.

(MIL‐STD‐1791B)

D Y Y(C‐17)

The contractor needs to demonstrate that the

ROCC can be loaded on to a Hlversen type K‐ loader and since the requirement for the winch was included, it should be loaded onto a C‐17.

3.3.4

Maintenance

Compatibility with servcing equipment without modification.

D Y Y(C‐17)

AMC to confirm req't for serving water tanks/Lav while ROCC is on C‐17.

While the ROCC is loaded on an aircraft it must demonstrate that it is capable of interfacing with servicing equipment and the contractor shall show that condensed water from the ECS will not drip on the cargo bay floor.

3.4 Environmental, Safety, and Operational Health (ESOH)

Requirements

3.4.1

Noise Attenuation

No greater than 65 dBA decibels (excluding take‐off)

( MIL‐STD‐1472G PARA 5.5.4.6.2)

T Y Y

Testing verified with USG rep

3.4.2a Lighting

ROCC Max intensity‐ minimum of 540 lux T Y N

Testing verified with USG rep

3.4.2b Lighting

Closet lighting‐ Minimum 300 lux T Y N

Testing verified with USG rep

3.4.2c

Lighting

Fully controllable, 2 different circuits allowing lights above monitors separate dimming/on‐off control.

I N N

Inspection verified with USG rep

3.4.2.1 SLS Lighting

Ambient lux no greater than 0.01. Lights off, doors closed.

T Y N

Testing verified with USG rep

3.4.2.2a Emergency Lighting

Loss of ROCC power activation D N N

Demonstration verified with USG rep

3.4.2.2b

Emergency Lighting

Disarm feature‐ long term storage. Labeled or designed so

ROCC can not be used while Emergency Lighting System is disarmmed.

I N N

Inspection verified with USG rep

3.4.2.2c

Emergency Lighting

Rechargeable batteries (20 minutes minimum)

Batteries recharge once power restored to ROCC from Steel

Eagle.

T Y N

Can likely combine this testing with overall val/ver.

3.4.3

Smoke and Flammability

Construction compatible with specs.

IAW FAA 25.853 and JSSG 2009

T/I Y/N N

If the materials used are already FAA certified, inspection of the certification document is sufficient. Otherwise, testing

IAW the FAA regulation is required with a test report.

3.4.3.1 Fire Extinguishers

Each capsule MIL‐HDBK‐516C. NFPA 10 approved I N N

Verified by inspection

3.5 Electrical Requirements

3.5.1

Electrical Power Source

Steel Eagle sole source.

Two 50 amp 120VAC, 60 Hz single phase circuits

T Y Y(SE)

SME ok with KTR using equivalent power source from within his manuf. Facility

Integration test with ROCC getting power from steel Eagle and all DV Travel Team electronic equipment being operated in the SLS & CR/SA.

3.5.2

Electrical Power Quality

Power line conditioners and surge protectors to protect carry on devices.

A Y N

Inspection followed by analysis to verify that the protection devices are suitable

Include in Electrical system test report.

3.5.3

Electrical Power Distribution

Power distribution panel, as Steel Eagle interface, for all dedicated and mounted ROCC devices.

I N N

3.5.4

Electrical Power Protection

Circuit breakers or similar‐ separate from C‐17 aircraft electrical protection devices.

I N N

3.5.5

Electrical Appliance Outlet Requirements

Minimum 2 three prong 120VAC 60 Hz duplex outlets per wall in each capsule.

T Y Y(SE)

Integration test with ROCC getting power from steel Eagle and all DV Travel Team electronic equipment being operated in the SLS & CR/SA.

3.5.5.1 One duplex outlet at each seat location I N N

3.5.5.2a

One three prong, 120VAC, 60 Hz, duplex outlet per per mounted device.

(MIL‐STD‐202)

I N N

3.5.5.2b

One three prong, 120VAC, 60 Hz, duplex outlet within four feet of the printer stand.

(MIL‐STD‐202)

I N N

3.5.6

Electric Cabling

Design and installed per spec.

(CNSSAM TEMPEST/01‐13)

I N N

SM pretty sure there are other specs out there unrelated to TEMPEST that tell the

KTR how to design/install the cabling ‐ KC

3.5.7

Grounding and Bonding

Design and installed per spec.

(MIL‐STD‐464C, MIL‐STD‐704F, CNSSAM TEMPEST/01‐13)

3.5.8

Wiring Design and Separation

Design and installed per spec.

(MIL‐HDBK‐454B, SAE AS50881, CNSSAM TEMPEST/01‐13)

I N N

3.5.9

Electrical Emission and Security

Design and installed per spec.

(CNSSAM TEMPEST/01‐13)

I N N

3.6 System Environment Requirements

3.6.1

Storage

3 Days maximum outdoor storage‐ Negligible damage

(TO 1C‐17A‐3‐1)

A or D

(SVM?)

Y N

Analysis/Demonstration shall show that rain, quarter size hail and blowing dust

(30 mph for 8 hrs) will not damage the

ROCC beyond negligible limits

3.6.2

Protective caps

Exterior outlets must be capped. Caps tethered or bagged and stored within ROCC.

I N N

Verification must be witnessed by SME or authorized USG rep.

3.6.3

ROCC capable of being transferrable using a forklift from the ground, high bay stand, or K‐loader to standard ground transport vehicle.

(IAW MIL‐STD‐1366)

D N N

Fork lift & transfer truck ‐Verification must be witnessed by SME or authorized

USG rep.

3.6.4a

Operation. The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall be capable of operating in an explosive atmosphere as defined by MIL-STD-810G method 511.6 procedure I.

T/A Y N

3.6.4b

Operation. The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall be capable of withstanding rapid decompression as defined in MIL-STD- 810G method 500.6 procedure III.

T/A Y N

3.6.4c

Operation. The ROCC, to include all devices (e.g., flat screen/flat panel monitor), shall meet Electromagnetic Compatibility (EMC) and Electromagnetic Interference (EMI) requirements of MIL-STD-464C and MIL-STD- 461G as applied to non-flight critical carry-on equipment.

T/A Y N

3.7

System Quality Factors

Service life minimum 35 years. SVM/D Y N

Since the bottom of the ROCC will see the most weatr and tear as it rolls along the floor, we need to determine how often the SB is used per year and comeup with an accelerated test to determine how long the bottom of the pallet will last before it will need to be repaired.

3.7.1

Environment Control System

Mean Time To Failure not less than 500 operating hours. A Y N

3.8 Design and Construction Requirements

3.8.1a

General Construction

The ROCC shall occupy no more than five standard 463L pallet positions on aircraft, on the 108 inch bias.

D N N

Combined with overall val/ver.

3.8.1b

General Construction

The SLS shall occupy no more than two standard 463L pallet positions on aircraft.

D N N

Combined with overall val/ver. Reviewed drawings

3.8.1c

General Construction

The CR\SA shall occupy no more than three standard 463L pallet positions on aircraft.

D N N

Combined with overall val/ver. Reviewed drawings

3.8.1.1 Maximum height shall not exceed 123 inches from top of

ADS rollers to top of ROCC D N N Combined with overall val/ver. Reviewed drawings

3.8.1.2a Maximum loading\unloading width is 120 inches (+/‐ 60 inches on…