Technical Subfactor RFI submission form 21 Oct.xlsx
XLSX spreadsheet 20 KB Posted
- Attached to
- C-17 Data Recorder
- Solicitation number
- FA8526-24-R-DR
About this file
This document is a technical subfactor RFI submission form related to a federal contract opportunity for a C-17 Databus Recorder (DR) system. The key details are:
The C-17 Program Office has a requirement for a databus recording system capable of capturing all data across the aircraft's data buses and fuel quantity computers. The desired system must be a form, fit, and function line replaceable unit (LRU) hardware solution that complies with current Air Force cybersecurity standards. The technical requirements cover areas such as data recording and storage, cooling, electromagnetic compatibility, environmental conditions, maintainability, and information assurance. The government is conducting this sources sought synopsis to identify potential sources with the expertise, capabilities, and experience to meet the requirements for the development, qualification, and production of the C-17 DR system. Interested contractors or institutions are requested to review the technical requirements as a future competitive solicitation is expected.
View the file
Other files
| File | Type | Posted |
|---|---|---|
| DRAFT DBRS SOW v3.3.docx | DOCX document | |
| DBRS SRD_RFI.docx | DOCX document | |
| SRD Key Requirements_RFI.xlsx | XLSX spreadsheet | |
| Vendor Questions- Industry Day Answered 6 Mar 25.xlsx | XLSX spreadsheet | |
| Required Technical -Value Added Elements Combined 12.19.24.xlsx | XLSX spreadsheet | |
| Industry Day RFI.pdf | ||
| Required Technical -Value Added Elements-Subfactors 1 and 2 Combined 12.17.24.xlsx | XLSX spreadsheet | |
| RFI Technical Subfactors.docx | DOCX document | |
| Warranty RFI.docx | DOCX document | |
| C-17 DR SSS 27 Feb 24 FINAL to Post.docx | DOCX document |
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subfactor 1
| Subfactor | Requirement | Yes | Maybe | No | Noted Issues | Subfactor Revision |
| 1 | The DBRS shall be capable of recording 100% of the data from each bus. | |||||
| 1 | The DBRS shall provide synchronized, time-stamped data from each bus. | |||||
| 1 | Data shall be stored on a removable solid-state device (SSD). | |||||
| 1 | The SSD must be accessible without the need to remove the DBRS from the avionics rack. | |||||
| 1 | The DBRS shall not overwrite existing data when the storage capacity is reached. | |||||
| 1 | The DBRS shall have a front panel indication when it is powered on. | |||||
| 1 | The DBRS shall have a front panel indication when it is actively recording. | |||||
| 1 | The DBRS shall indicate when 10% storage capacity remains. | |||||
| 1 | The DBRS shall allow primary operation and control functions to be performed with the LRU installed in its intended use configuration without the removal of additional aircraft panels. | |||||
| 1 | The DBRS shall operate with a primary power supply of 28 Volts Direct Current IAW MIL-STD-704. | |||||
| 1 | The DBRS shall be powered by 28 VDC emergency power when primary power is unavailable. | |||||
| 1 | The DBRS shall default to a powered-on state. | |||||
| The DBRS shall default to a recording state. | ||||||
| 1 | The DBRS shall be capable of being manually shut off without removing the LRU or engaging the circuit breaker. | |||||
| 1 | If DBRS requires a flow through method of cooling, then the method shall conform to the design requirements described in ARINC 404A. | |||||
| 1 | The DBRS shall operate satisfactorily with cooling air that contains no more than 0.001 grams of solid contamination per pound of air, and 95 percent of particles less than 20 micron in size, and no particle larger than 50 micron in size without degradation in performance. | |||||
| 1 | The DBRS shall operate satisfactorily in the following cooling normal conditions: |
1. (Ground case) At cooling flow rate of 8 lbm/min x w per kilowatt of equipment maximum heat dissipation at a supply temperature of 32 degree C and an ambient pressure between 31.89 in Hg and 18.70 in Hg, where w is defined as the ratio of ambient pressure to 29.92 in Hg.
2. (Flight case) At cooling flow rate of 6.47 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 7 degree C in a pressure environment equivalent to 8,000 ft. altitude.
3. (Airdrop) For one hour during a high altitude () airdrop with fuselage depressurized, at cooling flow rate of 2.7 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 10 degree C.
1 The DBRS shall operate satisfactorily in the following cooling extreme conditions:
1. (Minimum Continuous) At cooling flow rate of 8 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of -40 degree C.
2. (Maximum Continuous) At cooling flow rate of 8 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 55 degree C.
3. (Low Flow Continuous) At cooling flow rate of 5 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 32 degree C.
4. (Intermittent) For five minutes at a cooling flow rate of 8 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 71 degree C.
5. (Decompression at 50,000 ft) For five minutes at a cooling flow rate of 1 lbm/min per kilowatt of equipment maximum heat dissipation at a supply temperature of 7 degree C.
| 1 | The DBRS shall not use internal fans without USG approval. |
| 1 | The DBRS shall comply with emissions limits of MIL-STD-461 Conducted Emissions CE102, Power Leads, 10 kHz to 10 MHZ. |
| 1 | The DBRS shall comply with emissions limits of MIL-STD-461 Radiated Emissions RE102, Electrical Field (Large Fixed Wing Internal requirements); Figure RE102-3. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Conducted Susceptibility CS101, Power Leads, 30 kHz – 150 kHz. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Conducted Susceptibility CS114, Bulk Cable Injection. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Conducted Susceptibility CS115, Bulk Calbe Injection, Impulse Excitation. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Conducted Susceptibility CS116, Damped Sinusoidal Transients, Cables and Power Leads. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Conducted Susceptibility CS118, Personnel Borne Electrostatic Discharge. |
| 1 | The DBRS shall comply with conditions of MIL-STD-461 Radiated Susceptibility RS103, Electric Field, 60 V/m. |
| 1 | The DBRS shall meet the electrical bonding requirements in accordance with MIL-STD-464, paragraph 5.11 Electrical Bonding. |
| 1 | The DBRS shall withstand without degradation, while not operating, a cooling air temperature range of 54°C to +71°C |
| 1 | The DBRS shall withstand, while operating, a cooling air temperature range of +71°C to 32°C in 39 seconds during ground operation (initial cool down) and +32°C to +7°C in 25 seconds during climb. |
| 1 | The DBRS shall withstand, while operating, rates of inlet cooling air temperature change up to 60°C/min. during ground transient warm up starting from 54°C. |
| 1 | The DBRS shall not be degraded when operate at pressure altitude from -1800 ft. (31.89 in. Hg.) to 50,000 ft. Pressure altitudes are defined in MIL-E-5400 Class 1. |
| 1 | The DBRS shall meet performance standards during and following a rapid and complete loss of cabin compartment pressurization (10,300 ft.) from an airplane flight altitude of 50,000 ft. (1.69 psia) within 15 seconds, the equipment will remain operating for 5 minutes at 50,0000 ft. before being returned to normal cabin pressure. |
| 1 | DBRS components shall meet overpressure requirements of 12.1 psid for 3 minutes while not operating. |
| 1 | DBRS components shall not be damaged or degraded by humidity up to 100% including conditions where condensation is occurring in and on the equipment during operating and nonoperating conditions. |
| 1 | Materials used in DBRS components shall not become nutrients to fungus under the conditions of 95% relative humidity at 86°F for 28 days. |
| 1 | DBRS components shall not develop corrosion or electrical degradation when exposed to a salt fog concentration of 5% at 95°F for 48 hours. |
| 1 | DBRS components shall not be damaged or degraded when exposed directly to a concentration of 97%-99% SiO2 sand and dust blown on the items at a wind velocity of 300-1750 ft/min, at a concentration of 0.1 to 0.5 gram/ft3, with a grain size of 100 to 325 mesh screen, for durations of 6 hours and 22 hours at temperatures of 73°F and 145°F, respectively. |
| 1 | Acceleration testing shall be accomplished to assure the DBRS and mounts can structurally withstand steady state inertia loads and function without degradation during and after exposure to these forces. Acceleration tests also verify the DBRS and mounts do not become a hazard during and after a crash. Acceleration testing is to be accomplished per MIL STD 810. |
a. Operational test shall be accomplished per Method 513.8 Procedure II using the limit load factors listed below. Testing to be accomplished in each of the 3 major axis.
b. Crash hazard acceleration testing shall be accomplished per Method 513.8 Procedure III using the ultimate load factors listed below. Testing to be accomplished in each of the 3 major axis.
Limit load factor (G’s) Forward - 2.0 Aft - 1.5 Up - 2.3 Down - 5.5 Side - 2.5
Ultimate Load factor (G's) Forward - 9.0 Aft - 2.25 Up - 3.45 Down - 8.25 Side - 3.75
| 1 | Any new DBRS support structure components shall be analyzed to the load factors above. For ultimate loads, structure can deform but must remain in place and not block egress paths. |
| 1 | Shock testing shall be accomplished per MIL STD 810 Method 516.8 Procedure I and Procedure V. |
a. Procedure I Functional Shock shall be accomplished with the equipment operational and demonstrates it can function during and after shocks. Repeat testing for each of the 3 primary axis.
| b. | Procedure V Crash Hazard Shock shall be accomplished, testing will demonstrate the equipment will be contained during a crash and not create an egress hazard. Repeat testing for each of the 3 primary axis. | |
| 1 | Vibration testing shall be accomplished per MIL STD 810 Method 514.8 Procedure 1 at the Functional and endurance at the breakpoint levels listed below. Duration will be at least 30 mins Functional 60 mins endurance and 30 mins functional and be repeated on each of the 3 major axes. |
Frequency / Functional 5 / 0.002 G2/Hz 65 / 0.002 G2/Hz 150 / 0.01 G2/Hz 500 / 0.01 G2/Hz 2000 / 0.0006 G2/Hz
Frequency / Endurance 5 / 0.04 G2/Hz 500 / 0.04 G2/Hz 2000 / 0.0025 G2/Hz
| 1 | Exposed metal surfaces of the DBRS shall not exceed a temperature of 120°C. |
| 1 | Exposed glass surfaces of the DBRS shall not exceed a temperature of 138°C. |
| 1 | Exposed plastic surfaces of the DBRS shall not exceed a temperature of 156°C. |
| 1 | The DBRS system components shall be resistant to sprayed hydraulic fluid and engine fuel in accordance with RTCA DO-160 section 11. |
| 1 | DBRS components shall meet or exceed the indirect lighting effects threat defined as Test Waveform F of “Lightning Test Waveforms and Techniques for Aerospace Vehicles and Hardware”, Report of SAE Committee AE4L, Paragraph 3.3.2.1, scaled to a peak current of 200,000 amperes. |
| 1 | The installed system shall optimize system manpower by identifying the minimum number and type of personnel required consistent with complexity, human performance requirement, workload and safety requirement, reliability, affordability, and risk constraints IAW MIL-STD-1472H, Human Engineering, paragraph 4.2.6. |
| 1 | The installed system/unit shall meet the maintainability criteria in MIL-STD-1472H, Section 5.9 for all conditions. |
| 1 | All modified equipment shall preclude improper installation, mounting, or connection of LRUs, assemblies, subassemblies, cables, or lines IAW MIL-STD-1472. |
| 1 | The installed system/unit shall be directly interchangeable with each C-17 without requiring adjustments or special harmonization with LRUs. |
| 1 | All connections located within 6 inches of each other shall be physically non interchangeable except when the connectors are specifically designed to be interchangeable for supportability reasons; clearly marked as to their correct installation and unable to cause damage to the installed system IAW MIL-STD-1472. |
| 1 | The DBRS shall have operator and maintenance manuals to support all tasks necessary for operation, control, and maintenance of the item. |
| 1 | The instruction set for each of the computers shall be appropriate to the intended application, and addressing ranges and modes shall be adequate for the application and amount of memory employed, including expansion. |
| 1 | The instruction set for newly developed Computer Program Configuration Items and Computer Software Configuration Items shall be approved by the USG. |
| 1 | The DBRS shall be designed to perform an orderly shutdown if power is outside the specification limits per MIL-STD-704F. This will include storing of critical data and parameters. |
| 1 | The DBRS shall generate and store logs in memory. |
| 1 | The system shall ensure information integrity via cryptographic functions IAW NIST SP 800-53 without performance degradation. |
| 1 | The system shall protect data at rest using cryptographic mechanisms and/or protected media storage IAW NIST SP 800-53. |
| 1 | The system shall employ sanitization processes on media and volatile memory storage IAW NIST SP 800-53. |
| 1 | The system shall segregate classified information on any new code or functions interacted with by new design elements. |
| 1 | The DBRS shall not transmit on, nor cause any adverse impacts, the aircraft databuses or functionality. |
| 1 | The DBRS shall consist of a single Line Replaceable Unit (LRU). |
| 1 | The aircrew/maintenance interfaces shall not impact recording operations if used during ground and in-flight operation. |
| 1 | All potentially hazardous materials used in the systems shall be managed following AFI 63-101/20-101 paragraph 5.4.11. In addition, the materials are prohibited from use in all delivered hardware, including Commercial Off the Shelf (COTS) hardware, and in the operational support of the aircraft with its installed system. Asbestos, Carbon Tetrachloride(=Tetra chloromethane), CFCs (-11, 12, 13, 111, 112, 113, 114, 115, 211, 212, 213, 214, 215, 216, and 217), CFC blends (R-500, 501, 502, and 503), hydrazine, methyl bromide, Polychlorinated Biphenyls (PCBs), Radioactive material, Trichloroethane (=methyl chloroform), Halons (-1011, 1202, 1211, 1301, and 2402). |
| 1 | Materials and processes shall be in accordance with MIL-STD-1587 Material and Process Requirements for Aerospace Weapons Systems and MIL-STD-1568D Materials and Processes for Corrosion Prevention and Control in Aerospace Weapon System. |
| 1 | Magnesium parts shall be protected IAW T.O. 1-1-691 and coated with 3 mils of corrosion resistant primer and 6 mils of polyurethane topcoat. |
| 1 | Adhesive sealants used to seal and/or protect terminations shall conform to MIL-A 46146B (or equivalent) and C-17 AVS, MDC S002, Vol. 1, Par. 3.3.1.2.7.1. |
| 1 | Conformal coating shall conform to MIL-I 46058C (or equivalent), C-17 System Specification, MDC S001, paragraph 3.3.1.3.e, and AVS MDC S002, Vol. 1, paragraph 3.3.1.1. |
| 1 | All newly developed support equipment (SE) shall be designed in accordance with MIL-S-8512 including Amendment 2 (MIL-S-8512(s)), MIL-STD-46855, MIL-PRF-28800, and MIL-STD-1472. |
| 1 | All newly developed electrical/electronic test equipment shall be selected/designed and constructed in accordance with the requirements stated in MIL-PRF-28800; MIL-HDBK-454 shall be used as guidance in the development of electronic SE. |
| 1 | All newly developed electrical, mechanical, pneumatic, and hydraulic SE shall be selected/designed and constructed in accordance with the requirements stated in MIL-S-8512(2). |
| 1 | All newly developed designed support equipment shall use standard military or industrial parts, components, materials, and processes. Including, but not limited to, National Aerospace Standards (NAS), International Organization for Standardization (ISO), IEEE, American Society of Mechanical Engineers (ASME), and Military Standard (MS) standard parts, components, materials, and processes. Exceptions to this requirement must be approved by AFLCMC/WLME. |
| 1 | All newly developed parts, components, materials, and processes deemed proprietary by the data owner shall not be used in the design and development of support equipment, with the exception of selected COTS support equipment. |
| 1 | All newly developed Electronic Test Equipment shall meet the electromagnetic requirements in accordance with MIL-STD-464C. |
subfactor 2
| Subfactor | Requirement | Yes | Maybe | No | Noted Issues | Subfactor Revision |
| 2 | The DBRS shall be capable of recording data from at least (9) MIL-STD-1553 buses, (8) ARINC 429 buses, and (2) EIA-422 buses simultaneously. | |||||
| 2 | Storage capacity of the SSD shall be 4 TB or 1,000 flight hours, whichever is greater. | |||||
| 2 | Data shall be recorded in an industry standard format. | |||||
| 2 | The DBRS shall be expandable to record additional buses in the future. | |||||
| 2 | The DBRS shall be modifiable to provide wireless download in the future. | |||||
| 2 | The DBRS shall not require air flow greater than 8 lbm/min for cooling. | |||||
| 2 | If DBRS requires a flow through method of cooling, then total pressure loss through the DBRS shall be no greater than 25.4 mm of water with a design goal of 5.1 mm of water when supplied with a flow rate of 8 lbm/min per kilowatt at 32 degrees C and 14.7 psia. | |||||
| 2 | Predicted Mean Time Between Failure (MTBF) shall be calculated IAW MIL-HDBK-217F, Reliability Prediction of Electronic Equipment. | |||||
| 2 | The system components shall have a minimum of 40% spare installed memory. | |||||
| 2 | The system computers shall have at least 30% spare throughput/processor utilization under heaviest loading conditions. | |||||
| 2 | The DBRS shall initiate an orderly recovery within five seconds upon return to normal power conditions without operator intervention. | |||||
| 2 | The DBRS shall provide the capability to recover to a known state in near real time. | |||||
| 2 | The DBRS shall include, at a minimum, external interfaces compatible D38999/26WJ35SN and D38999/26WJ35SA connectors IAW MIL-DTL-38999. | |||||
| 2 | The DBRS shall have an output interface that allows in-flight transfer of recorded data in near real-time. | |||||
| 2 | The DBRS shall have an aircrew/maintenance interface that can be used during ground and in-flight operation. | |||||
| 2 | The DBRS shall not exceed the physical dimensions (width, height) of an ARINC 404A ½ ATR case, with an L2 length of 12.62 in. | |||||
| 2 | SRD 6-7 - | The DBRS shall mount securely to the C-17 avionics rack |
a. Threshold: using a tray provided by the vendor.
| b. | Objective: using standard ARINC 404A Type A hold down in the front and solid pin/hole in the rear. | |
| 2 | The DBRS and any necessary components for mounting shall weigh no more than 13 pounds. |
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