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Aero Precision provides OEM part support for military aircraft operators across more than 20 aircraft

munirabbasi

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  1. The suction boost pumps located near the reservoirs are used to provide a positive hydraulic pressure of 70-l 10 PSI to the suction side of each engine driven pump when turned on. This pressure prevents cavitation and helps to “prime” an engine driven pump should air get into the suction line. If the reservoir fluid level is kept within limits and correct maintenance procedures are followed, air will not enter the system. When a hydraulic component is replaced, the cavities of the new unit should be filled with system fluid (MI L-H-5606) just before installation to minimize entrapment of air.
  2. Kindly See service news VOL,10.No.2 Best Regards Munir Abbasi Home Hercules Pakistan
  3. Excellent Sir hehe Munir Abbasi Home of Hercules Pakistan
  4. Hello World Hercules Fuel & Avionic Expertise! All 14 fuel tanks electrical pumps are operated by 3 phase power supply , controlled through 3 phase (4 poles) SWs mounted on OH Fuel control & management panel, where others pumps like hydraulic ,prop feathering AUX pump , ACS recirculating fan , are controlled remotely by single wire (single pole) SWs through 3 phase relays. what is reason behind it? Best Regards Munir Abbasi Munir Abbasi Home of Hercules Pakistan Home of Hercules Pakistan
  5. Kindly See the VOL,6 -No.3 service news Munir Abbasi Home of Hercules Pakistan
  6. Sir hehe bundle of Thanks Munir Abbasi Home Hercules Pakistan
  7. Above 15 knots system working normal nothing was observed pilot Munir Abbasi Home Hercules Pakistan
  8. All 4 skidded.The electronic box of the system was checked with mark II tester at back shop found OK. The Anti-skid control valves of the system were checked at hydro shop found OK. We also checked the wiring of the system as per T.Os IC-130B-2-13 ,1-1A-14 and 1-1-8 found OK. We also consulted the service news VOL,8-1 Best Regards Munir Abbasi Home of Hercules Pakistan
  9. No UNSAT indications were observed. (INOPERATIVE & TEST PANEL LIGHTS) All brakes were released simultaneously. Best Regards Munir Abbasi Home Hercules Pakistan
  10. Hello Hydro Expertise On Aircraft MARK II system, at 10 knots of aircraft speed, brake was released it own when it is applied .Before 10 knots system operation was normal. The system was checked as per T.O 1C-130B-2-12 and 1C-130B-2-7 found OK. Sufficient Hydraulic bleeding was carried out. after completion of two mission defect was repeated again. Hydraulic bleeding of in normal Brake system was carried out but defect was repeated same manner. again. Any expert opinion. Munir Abbasi Home of Hercules Pakistan
  11. Hello Hercules APU & GTC Expertise When GTC is in starter cranking cycle (<35% RPM) Bleed & off load control valve is remain energized but APU (GTC 85-180L/LE) The valve is remain De-energized through out starting cycle till APU On speed relay is energized and the bleed control SW is mounted on APU control panel ,placed to open position. What is reason behind it. Munir Abbasi Home of Hercules Pakistan
  12. Excellent Video Munir Abbasi Home of hercules Pakistan
  13. Hello World Hercules Fuel & Avionic Expertise! All 14 fuel tanks electrical pumps are operated by 3 phase power supply , controlled through 3 phase (4 poles) SWs mounted on OH Fuel control & management panel, where others Aircraft, AC pumps are controlled remotely by single wire (single pole) SWs through 3 phase relays. what is reason behind it? Best Regards Munir Abbasi Home of Hercules Pakistan
  14. Thanks Peter I need your E mail Address. Best Regards Munir Abbasi Home of Hercules Pakistan
  15. Hello World Power plant expertise of T-56 A-15 Engine parameter cross the limitation TIT 1100 Celsius, Torque 20000 inch pounds fuel flow meter also cross limitation and could not control by throttle movement. Enine was shutdown as per procedure lay down -1 can some body explain what is the reason behind it and can we run the engine to repeat the defect without rectification. Best Regards Munir Abbasi
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