C-17_ROCC_SRD.pdf

SYSTEM REQUIREMENTS DOCUMENT

ROLL-ON CONFERENCE CAPSULES for the

C-17A GLOBEMASTER III AIRCRAFT

16 Apr 2018

Prepared by:

AFLCMC/WLE C-17 SYSTEM PROGRAM OFFICE

MOBILITY DIRECTORATE

235 BYRON STREET SUITE 19A

ROBINS AFB GA 31098

DRAFT

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 6

3.1 Required States and Modes 6

3.2 System of Subsystem Functional Requirements 6

3.3 System External Interface Requirements 7

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 15

4.0 Verification 18

5.0 Packaging 28

Appendix A

Table A-1 Test Matrix 29

Table A-2 Interface Connectors 58

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 up to and including crash loads in accordance with MIL-STD-516C. The ROCC shall not have any component software affecting 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 interfaces with the C-17 will be the tiedown chain bridle used for winch assisted loading as defined in MIL-STD-1791C and 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 aft of 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 government/commercial document is superseded by another document, the superseding document shall be in effect unless otherwise specified.

NOTE: When a government/commercial document is canceled with a replacement, the replacement document shall be in effect unless otherwise specified. In the event a document is canceled without a replacement, the manufacturer may submit, at their discretion, alternatives to the cancelled documents cited in this SRD. Unless the alternative is specifically approved by the Government, the cancelled 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-STD-464C Department of Defense Interface Standard Electromagnetic Environmental effects, Requirements for Systems MIL-STD-704F Department of Defense Interface Standard: Aircraft Electric Power

Characteristics MIL-STD-1791C w/ Change 1

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-209K Department of Defense Interface Standard: Lifting and Tie down Provisions MIL-STD-1366E Department of Defense Interface Standard: Transportability Criteria MIL-STD-461G Department of Defense Interface Standard: Requirements for the Control of

Electromagnetic Interference Characteristics of Subsystems and Equipment

MIL-STD-810G

w/Change 1

Department of Defense Test Method Standard – Environmental Engineering Considerations and Laboratory Tests

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-DTL-38999M w/ Amendment 2

Connectors, Electrical, Circular, Miniature, High Density, Quick Disconnect (Bayonet, Threaded or Breach Coupling), Environment Resistant with Crimp Removable Contacts or Hermetically Sealed with Fixed, Solderable Contacts, General Specification For

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

EN-SB-10-002 Rev A Crash Load Requirements For Passenger Transport Modules And Palletized Seats – Supplement to JSSG 2006

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 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) 7031843 Rev N Technical Drawing: Pallet Assembly, Cargo – HCU-6/E 7031839 Rev C Technical Drawing: Clip, Angle, Pallet Corner – HCU-6/E and HCU-12/E 7133043 Rev E Technical Drawing: Ring Assembly – Pallet, Airborne Cargo 7231258 Rev D Technical Drawing: Rail, Short – Cargo Pallet, HCU-6E 7231259 Rev B Technical Drawing: Rail, Long – Cargo Pallet, HCU-6E 7133042 Rev H Technical Drawing: Extrusion, Pallet Rail – Airborne Cargo 49 CFR Part 393 Parts and Accessories Necessary for Safe Operation

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 AS8049C Performance Standard for Seats SAE AS50881F Wiring Aerospace Vehicle SAE AIR1826A Acoustical Considerations for Aircraft Environmental Control System

Design SAE AS50151C Connectors, Electrical, Circular Threaded, AN Type, General Specification

For 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

3.0.1 Each requirement in this section corresponds to a verification paragraph in Section 4 of this document. For example, paragraph 3.2 correlates to paragraph 4.2 and paragraph 3.3 to paragraph 4.3, etc. A reference testing matrix is included in Appendix A to show the relationship between the Section 3 requirements and the Section 4 verifications.

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 maintains 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). Standard and/or common parts/materials as called out in Technical Order (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-HDBK-516C, MIL-STD-1791C, JSSG-2006 including Structures Bulletin EN-SB-10-002 Rev A (Structures Bulletin) 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-516C, Section 5.1.9 and JSSG-2006 including the Structures Bulletin. The ROCC capsule structure and fixed and removable miscellaneous equipment crash loading requirements shall use an additional analysis error factor of 1.5 in addition to the required structural crash loads called out in these documents.

3.2.1.2 MIL-HDBK-516C, Section 18.1.1 (SAE AS8049 with a 250 pounds occupant) requirements for the seat/occupant/restraint system and seat mount.

3.2.2 Electrical. The ROCC electrical systems shall be designed IAW requirements called out in 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-1791C, drawing 7031843, and MIL-DTL-27443. The ROCC design shall not exceed any aircraft limitations or require any modification to the aircraft computer/software systems, cargo compartment or the ADS, to include the floor rollers, pallet locks, and tie down rings.

NOTE: The C-17 Program Office does not necessarily expect the contractor to use HCU-6B (463-L) cargo pallets for the base of the ROCC. The purpose for including the HCU-6B drawings is to provide the required dimensions and location of the spaces in the platform perimeter for the engagement of the ADS locks in the contractor designed base. They are also included to provide the appropriate cross-sectional shape that is used to mate with the ADS rail system as well as other applicable design information.

3.3.2 Steel Eagle Interfaces. The ROCC shall interface with the Steel Eagle for all power and communications connections. Connection of the ROCC to the Steel Eagle shall be done using cables and wires designed and developed by the contractor. See Table A-2 for a list of connectors used on the Legacy Silver Bullet. All power and communication requirements defined in this document shall come through this interface (See paragraph 3.8.7.1 of this document for the only exception). Specific connectors and interface design will be provided at contract award, but should be quoted using Common off the Shelf (COTS) connectors and standard design practices for proposal purposes. See Table A-2 for a list of current Silver Bullet plugs and receptacles.

3.3.2.1 Walkway Impediments. There shall be no wires, cables, conduit, tubing, chains, or other types of connections between the ROCC and the aircraft or the Steel Eagle that impedes walkway traffic around the ROCC/Steel Eagle.

3.3.3 Material Handling Equipment (MHE). The SLS and CR/SA capsules shall be loadable onto the C-17 aircraft using existing Air Force MHE according to MIL-STD-1791C 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 (See 3.8.1.5).

3.3.4 Maintenance. The ROCC shall be capable of mating up with USAF 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 Environmental Control System (ECS). Servicing equipment shall not require modification to service the ROCC. Condensation from the ECS shall not be allowed to drip onto the aircraft floor. See Table A-2 for a list of lavatory and potable water connectors.

3.3.5 Ground Transportation. The capsules shall have the capability to be transferrable 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 or 49 CFR Part 393 for transport via ground transportation.

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). The ambient noise levels in the cargo bay area are listed in Table 4.

C-17 Cargo Bay Ambient Noise Levels (Table 4)

INTERNAL NOISE

Flight Condition Location/Area Max Decibels (dBA)

Ground Takeoff Power Cargo Compartment 100 Normal Cruise Cargo Compartment 86

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.

3.4.2.1 CR/SA Lighting. 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.

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

3.4.2.3 Emergency Lighting. Each ROCC capsule shall include an emergency lighting system that is activated by the loss of power to the ROCC. 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. The ROCC shall not receive power or communications capabilities 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 fully recharging over a two (2) hour period once power to the ROCC is restored using 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.

3.4.4 Emergency Egress. It is required that the ROCC be capable of meeting the egress requirements as defined by MIL-HDBK-516C paragraph 9.1.2 for occupied “control stations” being transported on the C-17A aircraft.

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). See Table A-2 for currently used connectors.

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 (1) three-prong 120VAC, 60 Hz, 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 and aerospace electrical design specifications (MIL-STD-464, MIL-STD- 704, SAE AS50881, and MIL-HDBK-454).

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, MIL- STD-704F (para 5.4.1) and SAE AS50881. The SLS and CR/SA shall be equipped with external grounding straps used to ground the modules to the aircraft.

3.5.8 Wiring Design and Separation. All electrical wiring shall be designed and installed in compliance with MIL-STD-464C, 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 and MIL-STD-464C to ensure electrical emission security for the ROCC.

The ROCC shall be required to pass Electromagnetic Compatibility/Electromagnetic Interference (EMI/EMC) testing in accordance with MIL-STD-464C.

3.6 System Environment Requirements.

3.6.1 Storage. The ROCC shall be designed to be stored in tropical, desert and CONUS (Continental United States) severe weather conditions, especially heavy rain, sleet/freezing rain and blowing dust, for a minimum of three days.

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 Operation. The ROCC, to include all integrated systems and equipment, shall be capable of withstanding rapid decompression as defined in MIL-STD-810G method 500.6 procedure III (also, see paragraph 3.8.5.1 of this document); and shall meet EMC and 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 with periotic maintenance and refurbishments.

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 approximately 5.7 standard 463L pallet positions in the aircraft, on the 108 inch bias. The SLS shall be 212 ± 6 inches or 2.4 standard 463L pallet positions long and the CR/SA shall be 292 ± 6 inches or 3.3 standard 463L pallet positions long.

3.8.1.1 The maximum height of 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 wide (± 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 all the locks available along the length of the ROCC (24 total).

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-1791C Figure A-11).

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

3.8.1.5 The ROCC shall have tie down provisions on the exterior wall of each of the SLS and CR/SA capsules for ground transport, MHE, and aircraft loading use only. The provisions shall permit each module to be restrained at the full unit weight without occupants, to the levels specified in 49 CFR Part 393.102 (0.8G forward, 0.5G aft/lateral and .2G up). Each provision and attachment to the unit shall be in a minimum of 7,500 pounds limit/working load (plus 2 safety factor ultimate) and the opening sized to fit two USAF aircraft 25,000 lb. tie down chains (see MIL-STD-209K). Provisions at the ends of the module that are no higher than tie down on the 463L pallet, as measured from the bottom, can also be used for winch assisted loading and unloading. Winching forces can be found in MIL-STD-1791 and tie down ring location on the 463L pallet can be found in MIL-DTL-27443.

3.8.1.6 Workmanship. Unsatisfactory workmanship, such as loose, cocked, or inadequately headed fasteners; distorted or loose bushings and pins; rough, malformed, misaligned, or improperly fabricated fittings; improper welds, etc. shall be considered as defects.

All corners shall be rounded; sharp edges, burrs, or protrusions shall not be permitted. Tie down ring attaching hardware shall be positively attached to the ROCC. All welders working on the ROCC shall be certified by the American Welders Society (AWS) and AWS D17.1 welding procedures shall be utilized for all welded items based on the material being welded.

3.8.2 Weight Threshold. The ROCC has a maximum weight limit of not more than 10,900 pounds for the SLS and 15,300 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) occupants (See paragraph 3.10.5). The following carry-on equipment shall be included in the maximum weight limit calculations.

- Luggage: 40 pounds total for the SLS

- 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. The ROCC has maximum weight requirement, with full fresh water tanks and serviced lavatory, of not more than 26,200 pounds combined.

3.8.2.2 The Center of Balance From Font End (CB FFE) along the length of the SLS and

CR/SA shall be marked on both sides of the capsules so that loadmasters can see them. The markings shall be 1 inch black lettering IAW TO 1-1-8.

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 Any materials, other than the items listed above or listed as approved in TO’s 1-1-

8, 1-1-691, or 35-1-3, that the EPA deems to be hazardous shall first be approved by C-17 engineering before being used in the manufacturing of the ROCC.

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 For egress and other safety reasons, 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.

The door shall be capable of being locked from the SLS side. For egress and other safety reasons, the door shall be capable of being unlocked from the CR/SA side.

3.8.4.4 When/If the ROCC experiences crash loads in accordance with MIL-STD-516C, the loads shall not cause the doors to open.

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 SLS and CR/SA shall have the capability to withstand and automatically equalize the pressure differential between the capsules and the aircraft cargo compartment in the event of a rapid decompression situation in accordance with JSSG 2006 paragraph 3.3.17 and MIL-STD-1791C w/ Change 1 paragraph 5.3.5.2. 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 integrated systems and equipment 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.

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 of 45,000 ft 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 from Crew. The ROCC shall include a connection port to the aircraft’s Public Address (PA) system in order to receive crew instructions. An existing C-17 aircraft interphone cord will be used to connect the ROCC to an aircraft Intercommunication Systems (ICS) headset receptacle panel. The interphone cord shall connect to the ROCC's internal speaker system such that audio is simultaneously heard in the SLS and CR/SA. PA announcements shall override all other audio signals being transmitted over the ROCC speaker system. See Table A-2 for the aircraft connector.

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 three 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, Non-Secure

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 12 inches 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.

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 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 42-in class for SLS and 52-inch class for CR/SA.

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 made shatter-resistant via the use of a film screen protector or some other mechanical means. The means used shall be capable of containing shards of broken glass greater than or equal to 0.25 inches long.

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, without having the tanks serviced, at 16 hours per day for two

(2) persons.

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.

3.9.5 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. A single Environmental Control Unit (ECU) shall be used to condition the air in the SLS and CR/SA.

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

3.9.6.2 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 of the business-class type.

3.9.7.1 All ROCC seats, excluding the divan, 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, excluding the divan, shall have multiple reclining positions down to at least 45 degrees, with a retractable (pull out mechanical) footrest.

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 that is hardwired to the ROCC 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. Each clock shall have a dimmer switch.

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 Carry-On 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, that displays degrees

Fahrenheit (°F), 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 (9) seats shall be usable for all phases of flight and as in-flight work stations (Reference SRD paragraphs 3.2.1.2 and 3.9.7.1).

3.10.5.6 CR/SA Mirrors. The CR/SA shall include one (1) full-length, shatterproof mirror 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. The space shall be able to accommodate a device that is 18”L x 18”W x 14”H and has a weight of not more than 30 lbs.

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. Personnel will not occupy the berth during takeoff, landing or critical phases of flight.

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, landing or critical phases of flight. 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 heated water shall not exceed 120°F. It is permitted for the cold water to be the same temperature as what is in the potable water tank. 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.

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

4.0.1 Each requirement in this section corresponds to a requirement paragraph in Section 3 of this document. A reference testing matrix is included in Appendix A to show the relationship between the Section 3 requirements and the Section 4 verifications. 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/parts are utilized, contractor redundant verification testing will not be required, unless the component/parts does not meet the ROCC performance level. The Contractor shall reference the USG / commercial test report and certification document(s) in the applicable ROCC system test report submitted to the USG.

NOTE: A Defense Contract Management Agency (DCMA) representative shall be present for all verifications located at the contractor designated facilities other than Government facilities.

4.0.2 The contractor shall provide or arrange for all test equipment and facilities. Unless specified herein, the examinations and tests may be combined wherever practical and are not required to occur in the order listed.

4.0.3 Refer to the Statement of Work for other verification and test requirements.

The definitions for the four different verification types are as follows:

Demonstration: Operation of the system, subsystem, or a part of the system that relies on observable functional operation not requiring use of instrumentation, special test equipment, or subsequent analysis.

Test: Operation of the system, subsystem, or a part of the system, using instrumentation or other special test equipment to collect data for later analysis.

Analysis: Processing of accumulated data obtained from other qualification methods. Examples are reduction interpolation, or extrapolation of test results.

Inspection: Visual examination of system components, documentation, etc.

4.1 Required States and Modes. (Test) Verification shall be accomplished through full testing and flight demonstration to show compliance with all relevant sections of MIL-HDBK-516C.

4.2 System of Subsystem Functional Requirements. (Demonstration/Analysis) The vendor shall demonstrate, through occupancy fit testing, that the ROCC is designed to meet MIL-STD-1472G requirements for a 5th percentile female to a 95th percentile male. A 3-D model of occupancy to meet this requirement may be used with prior Government approval.

Analysis shall be conducted to show that standard parts and materials are used where possible.

4.2.1 Structures. (Analysis) The Vendor shall provide structural analysis including but not limited to Finite Element Analysis (FEA), hand calculations, etc. in the form of a detailed report.

4.2.1.1 (Analysis/Inspection) The Vendor shall provide structural analysis including but not limited to Finite Element Analysis (FEA), hand calculations, etc. in the form of a detailed report. If FAR Part 25 certified seats are used, the contractor shall submit the certification documentation as verification that the seats meet the structural requirements. (See Structures Bulletin)

4.2.1.2 (Test) Verification will be accomplished via testing per SAE AS8049. A report detailing the results of the test is required. If an item has previously been certified for a 250 lb occupant, inspection of the certification will satisfy this requirement.

4.2.2 Electrical. (Inspection) The contractor shall provide design documentation such as wiring and routing diagrams, installed equipment and wiring lists, identified qualified parts, and an assessment report demonstrating best design practices and adherence of the entire ROCC electrical design to the TEMPEST document and to aerospace electrical design specifications (MIL-STD-464, MIL-STD- 704, SAE AS50881, and MIL-HDBK-454).

4.3 System External Interface Requirements.

4.3.1 Aircraft Interfaces. (Demonstration) Verification will be accomplished by drawing/design review during PDR, CDR and inspection during installation demonstration. The vendor shall demonstrate the ROCC can be pulled into the C-17 cargo compartment, locked into the ADS rails utilizing the ADS locks. Each pallet position must be capable of using the maximum number of the ADS locks available.

4.3.2 Steel Eagle Interfaces. (Test) Verify that the ROCC and Steel Eagle interfaces are compatible and that power and communications functionality operates as intended through those interfaces to support ROCC sub-systems. This shall be accomplished during Electrical Loads Analysis activity that is part of on-aircraft Integration Testing. A test report detailing the results, analysis, and conclusions is required.

4.3.2.1 Walkway Impediments. (Inspection) After the ROCC and Steel Eagle are installed on the aircraft, verify that the walkways are clear on the forward and outboard sides of the ROCC and that no items connecting the ROCC to the aircraft or Steel Eagle hinder the aircrew/passengers access around the…