SOURCES SOUGHT
28 -- Request for Information, Heavy Fuel Engines.
- Notice Date
- 4/10/2007
- Notice Type
- Sources Sought
- NAICS
- 336412
— Aircraft Engine and Engine Parts Manufacturing
- Contracting Office
- US Army Aviation and Missile Command (Missile), ATTN: AMSAM-AC, Building 5303, Martin Road, Redstone Arsenal, AL 35898-5280
- ZIP Code
- 35898-5280
- Solicitation Number
- W31P4Q-07-R-0134
- Response Due
- 5/14/2007
- Archive Date
- 7/13/2007
- Small Business Set-Aside
- N/A
- Description
- The U.S. Army Research, Development and Engineering Command (RDECOM), Aviation and Missile Research, Development, and Engineering Center (AMRDEC), Redstone Arsenal, AL, is seeking Non Developmental Item (NDI) sources of Heavy Fuel Engines (HFE) suita ble for use in the Shadow 200 TUAS airframe. The purpose of this request is to identify heavy fuel engine candidates that would fit the current Shadow 200 TUAS vehicle (http://www.aaicorp.com/New/UAS/shadowr_200.html) with little or no modification to the airframe or engine. It is desired to identify engines that are fully developed, extensively tested, and have initial evaluation units ready for possible procurement. The initial evaluation engines must cost less than $25,000 each, and be available for i mmediate purchase by the government. Listed below are areas of interest that the government will use in compiling information about the engines. Reference the section numbering convention when responding to the RFI. 1.1.0 Provide general engine overview and summary. All documents must be electronically provided in Microsoft Word or an Office compatible format. 1.2.0 Name of technical POC to whom engine inquiries may be addressed. 2.0.1 Provide complete digital sti ll photographic coverage of the engine and all major subsystems. Provide digital movie files of the engine during start up, operation, and shut down. 2.0.2 Provide engine design and application history. 2.0.3 Provide list of customers, with contact in formation, that are currently using the engine in some applicable configuration. 2.0.4 Provide list of customers, with contact information, that are currently using an engine of related design. 2.0.5 Provide number of NDI engines produced, which have l ittle or no modifications that are similar to the proposed engine. List and discuss any modifications or differences. 2.1.1 Provide test and historical data on operation with heavy fuel (JP-8, JP-5 or Diesel). Provide information that details where and how the engines have been tested or operated. 2.1.2 Provide engine performance maps which characterize maximum BHP as a function of RPM and operational altitudes. 2.1.3 Provide maximum continuous BHP. 2.1.4 Provide maximum take off BHP and duration. 2.1.5 Provide the rated BHP engine speed. 2.1.6 Provide RMS vibration data as a function of engine speed. Identify critical engine speeds within engine operating range with and without propeller. 2.1.7 Provide test data or analysis that show how engi ne BHP lapses as a function of altitude up to 20kft. 2.1.8 Provide BSFC at maximum BHP ratings. 2.1.9 Provide BSFC along propeller loading curve at all altitudes from idle to maximum RPM and power at WOT. 2.1.10 Provide the total assembled engine wei ght including the generator/alternator if it is designed to be an integrated part of the engine. Provide a detailed weight break out showing these weights and all accessories, engine cooling system, safety guards and additional protective housings, and ope rational fluids. 2.1.11 Provide curves detailing BHP as a function of density and viscosity effects of fuel at different temperatures. 2.1.12 Provide data that shows how the engine (with propeller) responds to commanded full range changes in thrust levels. Provide the maximum commanded thrust ramp rate that the engine can sustain without stalling or misfiring, idle to 100% and 100% to i dle. At that ramp rate, provide data that shows the engine RPM time response (lag) to the commanded thrust level. 2.1.13 Describe the engine cooling system including weight, air flow rate, and pressure drop requirement. If a radiator is required, provi de specifications including geometry, coolant properties, coolant flow rate, and heat rejection rate. 2.1.14 Provide information on any pre-heating requirements of the engine, as well as warm up periods. 2.2.1 Provide overhaul schedule; validate with d ata or analysis. An overhaul is defined as any servi ce not specified under the maintenance items. 2.2.2 Provide Mean Time Between Critical Failures (MTBCF) for engine. Validate with data or analysis. 2.2.3 Provide maintenance schedule; validate with data or analysis. 2.2.4 Provide list, including nam e of manufacturer and part number, of all routine maintenance replacement items, i.e spark plugs, engine oil, belts, filters, etc. 2.2.5 Provide engine endurance data, including if the engine has met the minimum endurance requirements of FAR Part 33.49. 2.2.6 Provide wear rates and expected engine life (TBO) as a function of throttle setting (BHP & RPM). Identify the life limiting components. 2.2.7 Provide details of how the ECU performs self diagnostics and verifies correct function of all features during all phases of engine operation. 2.2.8 Provide trade off details indicating whether the engine is more economical to overhaul or replace. Provide information comparing the percentage overhaul cost to the cost of a new engine. 2.2.9 Provide the n umber of times an engine can undergo an overhaul (if required) and still meet minimum performance requirements. 2.2.10 Provide a maximum time it takes an engine to be repaired or removed and replaced. 2.2.11 Provide any airworthiness specification your engine meets or exceeds. Provide specifics. 2.2.12 Detail corrosion prevention and control as related to material and finishes. Provide test data, if any, used to verify deterioration control. 2.2.13 Detail protective coatings or other means to allo w operation in a 100% humidity condensing environment. 2.3.1 Provide an analysis showing that the engine exhaust system configuration is compatible with a pusher configuration at airspeeds up to 140 knots. 2.3.2 Provide engine acoustic signature (dB) v ersus distance from the engine. Do not include noise generated by the propeller. Validate with data or analysis. 2.4.1 Provide details of the engine power control linkage (or electronic control interface specification) and operation specifications inclu ding interface dimensions, travel and actuation force requirements. 2.4.2 Provide details of the engine real-time fuel consumption measurement system, including data that quantifies the accuracy and reliability, along with detailed airframe interface req uirements. If no engine fuel consumption measurement is currently available, discuss in detail how one will be provided. 2.4.3 Provide details of the engine fuel pump and regulator including whether it is engine driven or accessory, operating characteri stics, flow rate, minimum and maximum inlet pressure, pump head, priming method (if required), electrical current and voltage requirements. 2.4.4 Provide details of the optimum fuel supply system. Include fuel return lines (if required). 2.4.5 Provide fuel particulate filtration requirements and acceptable contamination levels. 2.4.6 Provide maximum and minimum limiting fuel temperatures at which the engine performance is affected. 2.4.7 Provide details of the engine fuel flow and pressure inlet re quirements. 2.4.8 Provide details of the engine fuel and air induction de-icing and ice prevention method. Validate with test data or analysis. 2.4.9 Provide the details of default engine operation due to a broken power control linkage or other loss o f throttle command. 2.5.1 Provide details of the engine lubrication system, including required capacity and oil designation and performance specifications. If the engine design requires the use of a vehicle mounted oil reservoir, provide data showing oil consumption versus engine power setting (idle to max power) versus supply line size. Provide data or analysis showing that engine lubrication requirements will be met at all operating environments. 2.6.1 Provide details of engine generator/alternator a nd voltage regulator including interface requirements. If no generator, alternator or regulator is integrated, describe provisions for mounting and driving them . 2.6.2 Provide data showing excess generator/alternator output amperage versus engine power setting (idle to maximum power) at a 28 volt DC reference. 2.6.3 Provide the power requirements if the generator/alternator can be used as a starter. If an in tegrated, sole purpose starter is used, describe its electrical function in detail. 2.6.4 Describe in detail how the engine is started. Provide power and time requirements for pre-heating (if necessary). 2.7.1.1 Provide operational temperature limits. Provide historical data. 2.7.1.2 Provide non-operational (storage and transit) temperature limits. Provide historical data. 2.7.1.3 Provide operational and non-operational relative humidity limits for the engine for a non-condensing environment as sp ecified in AR 70-38 for Hot and basic climates. Provide historical data. 2.7.1.4 Provide operational rain fall intensity limits for the engine. Provide historical data. 2.7.1.5 Provide historical data that shows the engine will not incur damage or an y degradation in performance when subjected to blowing sand and dust as specified in MIL-STD-810 method 510.3, Procedure I and II. In the absence of historical data provide a mitigation plan, with supporting analysis that addresses the issue. 2.7.1.6 Pr ovide historical data that shows the engine will not incur damage or any degradation in performance when subjected to a salt spray environment within the parameters specified by MIL-STD-810, Method 509.4. This includes operational, shipping and storage. 2.7.1.7 Provide the non-operational transportation altitude (MSL) limits for the engine. Provide historical data. 2.7.1.8 Provide the operational atmospheric pressure limits for the engine. Provide historical data. 2.7.2.1 Provide the full operation al flight altitude envelope. 2.7.2.2 Provide operational engine starting temperature limits. Provide historical data. 2.7.2.3 Provide operational flight temperature limits. Provide historical data. 2.7.2.4 Provide operational humidity limits. Prov ide historical data. 2.7.2.5 Provide the maximum operating precipitation conditions. 2.7.2.6 Provide the maximum operating wind speed. 2.7.2.7 Provide the maximum roll angle (?) and roll rate and the maximum pitch angle (?) and pitch rate that the en gine can withstand and still operate normally. Provide historical data or analysis. 2.7.2.8 Provide details of the maximum allowable operational accelerations in all three axes. 2.8.1 Provide the details of the engine shock isolation mount. Provide h istorical data or analysis that shows the vibration transmitted to the air vehicle in each of the three principal axes. Provide the total combined root mean square vibration level for all three directions. 2.9.1 Provide detailed personnel hazards analys is of the engine and a detailed description, with supporting analysis, of the protective guards and the hazards they are designed to mitigate. 2.9.2 Provide a detailed catastrophic failure analysis of the engine showing that the engine housing and or pro tective guards will contain fragments produced by the failure of a high speed rotating device (excluding propeller). 2.9.3 Provide a detailed description of the means to prevent an accidental start of the engine, including a description of the visual con dition indicator provided to the operator. Provide historical data and analysis of the reliability of the system. 2.9.4 Provide the component stress factor of safety that was used in the design of all engine loaded components. Provide the basis for det ermining the allowable strength for the components. 2.9.5 Provide list of any material used in the engine that is not in compliance with applicable federal, state, and local environmental laws and regulations. Provide details of the implementation of, o r plans to implement, a Hazardous Materials Management Program (HMMP), IAW the Government-approved HMMP Plan and National Aerospace Standard (NAS) 411. 2.9.6 Provide historical data that shows the effect on the engine from a sudden stop from idle speed due to a propeller strike. Provide analysis of any engine damage that occurred and actions that had to be taken in order to return the engine to operational ser vice. 2.10.1 Define engine configuration, weight, CG's external dimensions, and all supplied engine accessories. 2.10.2 Provide electrical schematics of engine wiring, ECUs, ignition, and electrical interfaces. 2.10.3 Provide test and performance dat a for engines being delivered. 2.10.4 Provide installation manual and drawings detailing correct configuration and mounting of the engine and all engine accessories. 2.10.5 Provide operations manual detailing all operational limitations and requirement s. 2.10.6 Provide maintenance manual detailing required user level maintenance and schedules. 2.10.7 Provide overhaul manual which includes instructions for returning the engine to airworthiness condition. 2.10.8 Provide full parts list of engine, ma intenance service kits, and overhaul kits. 3.1.1 Provide specifications of any power required for the engine from the vehicle main power system. 3.1.2 Provide detailed electrical interface requirements including power requirements, control signal logic as required and connector specifications including pin-outs. 3.1.4 Provide details of the engine and ECU interface to the air vehicle flight controller. 3.2.1 Provide details of the engine mount including vibration isolation. 3.2.2 Provide detailed engine mounting and envelope drawings with dimensions and tolerances. 3.2.3 Provide details of propeller limits including acceptable weight, moment of inertia, moment load, and maximum imbalance load. 3.2.4 Provide details of engine propeller interface . 4.1.1 Provide the purchase price for the first unit used by the government for testing and evaluation. This number must be below $25,000. However, this price may not be indicative of actual LRIP or FRP costs. 4.1.2 Provide a LRIP cost for the engin e. LRIP (Low Rate Initial production) is defined as 10 units per year. Provide lead time for delivery ARO. 4.1.3 Provide FRP (Full Rate Production) costs. FRP is defined as 1,000 units per year for 10 years. Provide maximum surge capability. Provide lead times for FRP delivery ARO. Provide historical data. 4.1.4 Provide information that certifies all materials used in the engine are in compliance with the requirements specified in the Berry Amendment (10 U.S.C. 2533a). If the contractor is not in c ompliance, provide a comprehensive corrective action plan to correct the non-compliance. If the contractor asserts that compliance is impossible, the contractor shall include in the plan an explanation including a description of the market research that h as been conducted and a statement that the contractor has been unable to identify alternative domestic replacement items. 4.2.1 Provide details of what quality systems are in place (ISO, etc.). 4.2.2 Detail parts and engine inspection throughout the bu ild process. 4.2.3 Provide documented procedures for assembly and testing of completed engines. 4.2.4 Provide a system for notification of engineering changes in engine design or assembly. 4.2.5 Provide details of a system that notifies the customer of problems identified in existing engines. 4.2.6 Provide details of system which insures quality workmanship. 4.2.7 Provide details of system which insures quality soldering. 4.2.8 Provide detail of system which prevents mishandling of ESD sensitive items. 4.2.9 Provide details of a system that insures the integrity of all wiring, harnesses, and instrumentation. 4.2.10 Describe engine component marking and tracking system. 4.2.11 Provide a list of all component source suppliers and their country or orig in. 4.2.12 Provide details of system that insures the physical and functional interchangeability of like units, assemblies, subassemblies, componen ts, and replaceable parts in the engine. Provide details of system that ensures that individual items of the engine do not require handpicking for fit or performance. 4.3.1 Provide a list of critical suppliers. Provide details for any supplier not in th e United States. 4.3.2 Detail any proven manufacturing programs and capability. 4.3.3 Provide details on any military spec engines, machines, or components produced. 4.3.4 Provide details on any commercial engines, machines, or components produced. 4.3.5 Provide details of current production engines, machines, or components being produced. 4.3.6 Provide long lead time strategy and surge capability. 4.3.7 Provide details of critical manufacturing process control. 4.3.8 Provide details of the supplier management system. What fraction of the engine will be outsourced? 4.3.9 Provide details of what safety standards are in place. 4.3.10 Provide the details of in-house or external engine overhaul capabilities. 4. 4.1 Provide company details such as number of employees, technical degrees, and years in business, rate of growth. 4.4.2 Provide overall company description, certifications, security clearances, ISO status. 4.4.3 Provide description of contract effort s performed in the past relevant to TUAS applications. Provide POC's. 4.4.4 Provide strategic marketing plans, other efforts involving HFE's. 4.4.5 Provide description of engineering tools available at the company to support an engine program; basic a nalysis tools, advanced analysis tools, and personnel qualifications. ACRONYM LIST: AR, Army Regulation. ARO, After Receipt of Order. BHP, Brake Horsepower. BSFC, Brake Specific Fuel Consumption. CG, Center of Gravity. dB, Decibels. DC, Direct Curre nt. ECU, Engine Control Unit. ESD, Electrostatic Discharge. FAR, Federal Aviation Regulation. FRP, Full Rate Production. HFE, Heavy Fuel Engine. HMMP, Hazardous Materials Management Program. IAW, In Accordance With. ISO, International Standards Org anization. Kft, Kilo Feet. LRIP, Low Rate Initial Production. MIL-STD, Military Standard. MSL, Mean Sea Level. MTBCF, Mean Time Between Critical Failures. NAS, National Aerospace Standard. NDI, Non Developmental Item. POC, Point of Contact. RMS, R oot Mean Squared. RPM, Revolutions per minute. TBO, Time Between Overhauls. TUAS, Tactical Unmanned Aircraft System. WOT, Wide Open Throttle. Interested and capable sources are asked to submit a white paper containing a description of the above areas of interest. Information on available, emerging, or required technologies and how these technologies could be applied to this project should also be included. Responses should be made within thirty (30) days from publication of this notice. Responses to this request for information may not be submitted by fax; any so sent will be disregarded. All information provided pursuant to this RFI will be reviewed by Government and duly appointed government contractors. All information provided pursu ant to this RFI from foreign countries must be processed through their respective embassy. RFI correspondence should be submitted on a CD in Microsoft Word format, in English, to the attention of U.S. Army Aviation and Missile Command, AMSAM-AC-RD-RB/Buil ding 5400, Attention: Beverly Gonzales, Redstone Arsenal, AL 35898-5254. Technical questions can be addressed to Mr. Robert Milton, U.S. Army RDECOM, AMRDEC, Propulsion and Structures Directorate, Redstone Arsenal, AL, 35898, telephone: (256) 842-0104, e- mail: robert.milton@us.army.mil. This is for information purposes only. This sources sought request does not constitute an Invitation for Bids or a Request for Proposal, and it is not a commitment by the U.S. Army to procure products or services. The Go vernment does not intend to award a contract on the basis of this request for information or otherwise pay for the information solicited.
- Place of Performance
- Address: US Army Aviation and Missile Command (Missile) ATTN: AMSAM-AC, Building 5303, Martin Road Redstone Arsenal AL
- Zip Code: 35898-5280
- Country: US
- Zip Code: 35898-5280
- Record
- SN01270164-W 20070412/070410221050 (fbodaily.com)
- Source
-
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