Sa-Alc Test Systems Branch, 308 Avionics Circle Suite # 2, Kelly Afb, Texas 78241-5947

66 -- PBS 4100 (PORTABLE BALANCING SYST. SOL F41608-96-R-37551 01 POC For copy, Fax request to Buyer at (210)925-1054, For additional information contact Dupree, R/Ldkaa/(210)925-8461 Item 0001: 6635-01-431-5283DQ, PBS 4100, 27' H x 16' W x 19'' H, 90 LBS. Electronic components in a transit case to balance A-10A/B / TF34 Engines. P/N 7000-4134-24. Item 0002: 6625-01-431-7920FJ, Cable Kit,27'' L x 16'' W x 19'' H, 70 LBS. Hook up the PBS 4100 to the TF34 engine (Test Cable Kit). P/N 8900- 4005. Item 0003: Data Line item for Manuals, IAW Form 1423. SPECIFICATIONS: Function: Thiis system consisting of the PBS 4100 Portable Balancing System and its associated test cable kit dynamically balances the fan rotor and low pressure turbine (LPT) rotor of the TF34-100A engine by arriving at balance weight solutions which minimize engine vibrations, as measured at four vibration transducer locations. Unqualified sources (those not listed on the source control drawings as an approved source) will be evaluated in two parts. The first part requires the unqualified source to submit documentation to demonstrate the balancing system meets the minimum system requirements. If these requirements are met, the balancing system offered by the unqualified source will be demonstrated todetermine if it best meets the needs of the Air Force. Note: The demonstration will be at the contractor's expense. The below information summerizes the requirements, but is not complete, and does not replace the qualification requirements used to evaluate unqulaified sources. I. REQWUIREMENTS: A. OVERALL SYSTEM REQUIREMENTS: 1. The system must consist of, at minimum, data acquisition, processing and user inteface unit or units; charge amplifier, interface cabling; and portable printer. 2. The system must operate satisfactorily on ground electrical power (115 VAC, 60 Hz) or aircraft power (115 VAC, 400 Hz). The system must be protected against normal power transients and surges experienced on aircraft. 3. Total sysytem set-up time for balancing a TF34-100A engine installed on an A-10 aircraft shall not exceed 60 minute for a trained maintenance person. Set-up time is defined as time from delivery of balancing hardware to the aircraft to starting the engine for the first balance run. 4. The system must be a complete package (that is, the entire system shall be packaged and used as a single unit). 5. Total system weight, including carrying cases, must not exceed 200 pounds. No individual case, with contents, will weigh more than 100 pounds. all equipment must be stored inside carrying cases. 6. All hardware other than the computer/acquisition unit must operate satisfactorily from -65 degree F to 120 degree F. 7. All hardware must operate satisfactorily when the relative humidity is between 10 - 80%. B. Balance solution capabilities: 1. Balancing solutions calculated by the system must reduce fan frequency vibrations below 1.0 mils peak-to-peak displacement on all four vibrations transucers after final balance, when the engine is operated from 80% to 84% fan speed. 2. Must perform a dual-plane balance. That is, the system can arrive at balance solutions for the fan and LPT rotors either independantly or together. 3. Must arrive arrive at the final solution after a single engine run. 4. Must forcast engine vibrations before implementing the final balance weights, by part number, and to recognize fan disk and LPT rotor locations for weight addition or removal to achieve the balance solution. C. Vibration scan capabilities: In addition to balancing, the system must be able to track engine dynamic vibration signature or a user-selected frequency spectrum. When used for this purpose, the system must must accept a minimum of six velocity transducer inputs, P/N 4-128-0002 D. Hardware requirements: 1. Computer minimum operational capabilities: a. Temperature ratint: 32 degree F to 120 degree F. b. Data storage: Must be able to record and retrieve the size and location of balance weights, and dynamic vibration and frequency spectrum data on each engine, by serial number, for a minimum of 500 TF34-100A engines. c. Sufficiently rugged to withstand 5g loads while in operations, and 80g loads when stored. 2. Graphic display: a. Minimum of four simultaneously displayed vibrations channels. b. Minimum of two simultaneously displayed tachometer channels. (1) Must automatically locate imbedded balance phase reference signal on the fan speed signal. (2) Must incorporate isolation circuits which prevent the balancing system from affecting any aircraft or engine electrical signals. 3. When used for balancing, the system must accelerometers with a sensitivity of 5 - 250 pC/g. 4. Charge amplifier: Must accept a minimum of three simultaneous accerlometer signals. 5. Interference cables: a. Must not deteroriate when exposed to aircraft grade fuels, lubricants, and fluids. b. Mustr be protected by flexible, non-corrosive metallic armor or braiding for frquent aircraft flight line use. 6. Hardware technical data must contain: a. Operational and Maintenance procedures. b. Illustrated parts breakdown for replaceable component. c. Troubleshooting and diagnostic procedures. d. Electrical cable pin-out and schematic diagrams. E. Built in test capabilities: The system must have ameans of checking transducers and cables to ensure system integrity prior to its use, and must incorporate a calibrated built in signal for the charge amplifier. II. SUBSTANTIATION OF OPERATIONAL CAPABILITY A. Prospective source whose documentation meet the requirements of Section I above must demonstrate the operational capability of their balancing system within thirty days of notification that their documentation is satisfactory. This will be done by correcting the imbalance of a TF34 engine installed in an A/OA-10A aircraft at an operational Air Force base. The aircraft will be made available to the prospective source for a maximum of eight hours on one day only. The contractor will be responsible for the costs of this demonstration. Failure to adequately demonstrate that the contractor's systems meet the requirements of Section I in the allotted time will result in disqualification. Balancing systems previously evaluated by demonstration are not elgible for this demonstration. B. The demonstrated hardware will be scored by a team composed of Air Force maintenance personnel using the same criteria that was used at the October 1994 demonstration at at Barksdale AFB. The scores will be compared against the score of the currently approved source, Mechanical Technologies, Inc. Being awarded a score lower than that of the MTI hardware will result in disqualification. C. a prospective source which meets the requirements of Section I and paragraphs II A and II B will be designated as the approved source for procurement. It is suggested that small business firms or others interested in subcontracting opportunities in connection with the described procurement make contact with the firm(s) listed. Specifications, plans, or drawings relating to the procurement described are incomplete or not available and cannot be furnished by the Government. (0233)

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