SOURCES SOUGHT
R -- C-5 Antiskid System Improvement Redesign - C-5 Antiskid System Improvement Redesign SSS
- Notice Date
- 6/20/2011
- Notice Type
- Sources Sought
- NAICS
- 541330
— Engineering Services
- Contracting Office
- Department of the Air Force, Air Force Materiel Command, Hill AFB OO-ALC, OO-ALC/PKXB, 6038 Aspen Ave (Bldg 1289), Hill AFB, Utah, 84056
- ZIP Code
- 84056
- Solicitation Number
- FA8251-11-C5-ASSIRD
- Point of Contact
- Shauna A. H. Lyon, Phone: 8017753801
- E-Mail Address
-
shauna.lyon@hill.af.mil
(shauna.lyon@hill.af.mil)
- Small Business Set-Aside
- N/A
- Description
- This is the same information shown in the SSS but the Table may be a bit more clearly shown in the Word format. 1.PURPOSE: The USAF will be moving forward with a Request for Proposal (RFP) for a new C-5 Antiskid Control Unit (ACU) that requires updated cost and schedule information applicable to the latest project technical requirements based on this RFI. As a result of the feasibility study phase of the C-5 Antiskid System Improvement project the Air Force has determined that an improved ACU will resolve the system deficiencies identified in the original RFI. RFP preparations for the improved C-5 ACU are in process and will be posted to FBO at a later date. The Government does not intend to award a contract on the basis of this RFI or pay for the information provided by this RFI. General Atomics Systems Integration (GA-SI) has been contracted to assist the Air Force in implementation of the improved ACU. 2.BACKGROUND: The Air Force conducted and concluded a feasibility study evaluating options to upgrade the C-5 antiskid system in September 2010. During this study a request for information (RFI) was sent to industry through the Federal Business Opportunities website (fbo.gov / solicitation #FA8251-10-C5-ASUF). Based on results of this study, the Air Force has decided to pursue an upgrade to the Antiskid Control Unit (ACU) that will be a form-fit-function replacement. The United States Air Force (USAF) C-5 Galaxy heavy cargo transport aircraft, built by Lockheed, entered operational service in 1970 and has a projected service life beyond 2040. The C-5 fleet consists of four models of aircraft (59) C-5A's, (46) C-5B's, (2) C-5C's and (4) C-5M's. The estimated fleet size for the improved ACU is 89 aircraft plus 34 spares for a total of 123 units. 3.IMPROVED C-5 ANTISKID CONTROL UNIT REQUIREMENTS SUMMARY a.Controller Design & Architecture - The improved ACU shall be a digital controller consisting of twelve (12) control channels. All 12 channels shall be powered from either one of dual redundant 28 Vdc power supplies. Each channel shall control a single antiskid servo valve dedicated to a pair of brakes on one of the four MLG providing paired wheel antiskid functionality. Each MLG has six wheels. Each of these channels shall incorporate wheel speed input and processing for two wheels, processing for skid control, fault detection, ancillary inputs, a single output valve driver, and interchannel communication. Each of the 12 control channels shall reside on a dedicated circuit card module which can be individually replaced. The ACU shall include Built-In-Test (BIT) circuitry for fault detection and fault display functions and flight deck antiskid fault light operation. The ACU is powered when the aircraft is powered and the flight deck Antiskid switch is in the ON position, including while in flight. b.ACU Envelope and Installation - The upgraded ACU shall be installed in the same location as the legacy controller using the same mounting hardware. ACU dimensions may be reduced as long as the unit is compatible with the mounting location. ACU weight shall not exceed the legacy ACU weight of 14.8 lb. c.Electrical Power - The ACU shall be compatible with the power quality requirements of the original MIL-STD-704. The ACU shall continue to function normally through power interruptions of 40 msec. d.Antiskid Features - The ACU shall interface with the hydromechanical brake system of the C-5, detect incipient skid of the MLG tires, and modulate the full range of brake pressure (70 - 2,100 psi) to prevent loss of braking effectiveness, loss of air vehicle directional control, or damage to the air vehicle due to skidding resulting from braking operations. Improved ACU dry pavement antiskid performance shall be equivalent or better than the existing C-5 system, wet pavement antiskid efficiency shall improve by 15%. The antiskid functionality shall include touchdown protection and spinup override, locked wheel protection, and hydroplane protection features. Antiskid performance requirements shall be met using the current 50 tooth wheel speed sensor / exciter ring detector, the improved 50 tooth wheel speed transducer (electrically equivalent to the detector) and antiskid servo valves (0 to 40 mA). e.Brake Life Improvement - The upgraded ACU shall incorporate a control scheme that provides at least a 20% improvement in brake life over the current 1,000 landing baseline. The brake life improvement feature shall not degrade landing, refused takeoff (RTO), or max pedal braking performance. Also, it shall not result in a dragging brake or cause undesired residual brake heating. Brake life improvement targets as well as antiskid performance targets shall be met with both legacy and new versions of carbon brakes (Goodrich p/n 260-385 and 2-1702). f.Built In Test - The ACU shall incorporate improved BIT capability to detect system faults, isolate them to the appropriate Line Replaceable Unit (LRU) and display the fault information. BIT shall consist of both Continuous BIT and Initiated BIT. Continuous BIT monitors 28 Vdc power (2), Wheel Speed Transducers (24), Antiskid Servo Valves (12), Pressure Switches (12), WOW (4) and ACU circuitry for failures. Initiated BIT (Flight Deck Test Switch 1) applies 28 Vdc power to only one of the 2 ACU power supplies and applies aircraft 400 Hz aircraft power (simulated wheel speed) to half of the 24 wheel speed ACU inputs causing locked wheel brake release on all 24 brakes and illumination of the flight deck "Brakes On" light (driven by the ACU using the 12 pressure switch inputs). Initiated BIT (Flight Deck Test Switch 2) applies 28 Vdc power to other ACU power supply and applies aircraft 400 Hz aircraft power (simulated wheel speed) to the other half of the 24 wheel speed ACU inputs causing locked wheel brake release on all 24 brakes and illumination of the flight deck "Brakes On" light (driven by the ACU using the 12 pressure switch inputs). g.Software - The ACU software shall be developed, implemented, tested, and documented according to the requirements of DO-178B level D. h.Environmental Requirements - The ACU shall meet typical environmental requirements for an aerospace controller of this type. These requirements include ambient temperature, altitude, humidity, salt fog, sand & dust, vibration, acceleration, shock, explosive atmosphere, EMI, and ESD. EMI testing shall include the following portions of MIL-STD-461D: CE102, CS101, CS114, CS115, CS116, RE102, and RS103. i.Life / Reliability - The ACU shall have an operating life of at least 120,000 skid control cycles plus a shelf life of 5 years. The ACU shall achieve a minimum of 2,000 landing mean cycles between failures (MCBF). j.Testing - The required ACU tests and other verification methods for the ACU are listed in the table below. GA-SI will conduct the hardware in the loop (HITL) system verification tests. The supplier will have to develop and utilize a load source box for many of the functional tests listed. Verification Dev / Qual Units Production Units Inspections (sec 4.2) First Article Inspections All Production Inspections All Demonstrations (sec 4.3) Reliability 2 minimum Remove / Replace ACU Unit a Service & Access Unit a Functional Troubleshooting Test Unit a Remove / Replace Circuit Card Module Unit a Safety Unit a Transportability Unit a Weight Measurement 2, Units a & b Acceptance Testing (sec 4.4) Insulation Resistance All All Environmental Stress Screening (ESS) All All Functional Acceptance Testing All All Qualification Testing (sec 4.5, 4.6, 4.7) Electrical Unit a Endurance Unit a Temperature Unit a Altitude Unit b Humidity Unit b Salt Fog Unit b Sand & Dust Unit a Vibration Unit a Acceleration Unit b Shock Unit b Explosive Atmosphere Unit b Electromagnetic Interference (EMI) Unit b Electrostatic Discharge (ESD) Unit a HITL Skid Control Performance Unit c HITL Skid Control Functions Unit c HITL Fault Indication Unit c k.USAF Depot Maintenance - The supplier shall provide a prototype ACU tester for Depot repair and associated technical data. 4.REQUESTED SUPPLIER INFORMATION: Suppliers that responded to the original RFI should update those packages and resubmit. a.Development Schedule: i.Provide a top-level program schedule that highlights major ACU program milestones between program launch and flight test equipment delivery. Identify program phases and deliverables and where necessary, please state assumptions. b.Retrofit: i.Provide a reasonable fleet retrofit time-frame that is supportable by normal ACU production c.Rough Estimates for Acquisition Costs and Logistics: i.Estimate the following based on your proposed improved ACU concept 1.Development Costs: a.Provide ACU development and qualification costs 2.Acquisition costs: a.Provide ACU acquisition costs 3.Spares pricing: a.Provide ACU spares pricing d.Estimated Cost of Technical Data for Unlimited Data Rights: i.Provide associated costs of ACU technical data which includes theory of operation, system test and repair procedures ii.Provide the cost of ACU manufacturing drawings and software source code. 5.This is just a request for information the Government will not pay for any cost associated with this Sources Sought Synopsis IAW FAR 15.201 (e). 6.Responses need to be sent the POC listed in this RFI NLT 01 July 2011 15:00 MTN. 7.If there are any questions about this updated RFI, submit them to the Hill AFB Contracting Office POC Shauna Lyon at shauna.lyon@hill.af.mil or via phone at 801-775-3801.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/USAF/AFMC/OOALC/FA8251-11-C5-ASSIRD/listing.html)
- Place of Performance
- Address: TBD, United States
- Record
- SN02477419-W 20110622/110620235014-8ab30be5e168b329bb80b74252697e42 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
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