C-130 Technical
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Hello T56A -15 power plant Pneumatic Expertise T56A-15 (C-130 E model) engine can provide approximately 155 pounds of air flow per minute at 635F and 125 pounds per square inch of gauge pressure. Bleed manifold pressure gauge is mounted in F/deck (direct gauge) display approximately 70 PSIG .where remaining pressure of the engine flow? Best Regards Munir Abbasi Home of Hercules Pakistan
Last reply by munirabbasi, -
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Hello Herks Hydra Expertise! 1. It has mentioned Intermediate level maintenance T.O of EDP NYAB at 3000 RPM , flow rate of pump is 6 GPM min, where pump is designed 10 GPM at 3650 RPM . when both the pumps (NYAB) In Aircraft utility system working parallel max flow ie 16.93 pressure drop to 1800 psi. how we can calculate flow rate (GPM) of both NYAB pumps when they are working parallel at 3000 RPM? 2 Just assume that aircraft hydraulic utility system ,when No 1 EDP pressure is 3000 psi and No.2 EDP pump pressure 3100 psi how the pressure act passes thru passage of single pipe after isolation check valves ? Best Regrads Munir Abbasi Ho…
Last reply by munirabbasi, -
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Hello Pneumatic expertise Identify and purpose of mark image Munir Abbasi Home of hercules Pakistan
Last reply by NATOPS1, -
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Hi guys, just curious for knowledge sake, for 3505786-1 air turbine starter, when inflight suddenly start valve light illuminate and start valve open, will the air turbine starter crank and get damaged? Thanks.
Last reply by NATOPS1, -
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good evening to everybody im experiencing a "RADAR DEGRADED" CAUTION ACAWS on a C130J with a generic diagnostic message LPCR BIT FAIL FC3442010. The radar seems to work fine but after the power up bit completes the CAUTION pops up, troubleshooting the fault isolation for this fault codes nothing looks bad. I replaced all the LRUs and the ECBUs which apply power to the system. Any hint?
Last reply by sasa71, -
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Hello Avionic Wiring Expertise! Kindly see yellow marked column of image and explain with technical reference Best Regards Munir Abbasi Home of Hercules Pakistan
Last reply by munirabbasi, -
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whenever i am running the APU, the fire warning light on both master warning light and the APU T-handle light come up and remain steady once i put ON the air condition. however, if the air condition is not running, the operation of the APU remains normal. i have tried to check for bleed leaks from he APU to the manifold and no leak was found. pls i need urgent help on what next to look up to pls
Last reply by NATOPS1, -
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Hellow friends and brothers i just wanted to know what are the reasons behind the generator shaft bearing(only front) failure in C-130B ac with T56-A-7B engine.
Last reply by Kamrul Ahsan, -
- 1 reply
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I have Prepar 3- 5v flight simulator and have watched Utube videos on start up of the C-130 but could not find an actual written check list procedure as to how to start the 4 engines. Where can I obtain a written list to preform this or any other lists for the C-130? Thanks! email: [email protected]
Last reply by hehe, -
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During the FCF of 382G “CIVIL†airplane-, The Auto pressurization mode fails to pass the “pressure controller differential valve checkâ€. Safety valve was controlling the differential pressure before or might be at the same time of pressure controller. Safety valve required to remain closed during this check. Safety valve cracked to open at 14.8 in/hg and will maintain 14.9 in/hg; while pressure controller (when isolating the safety valve) was taking over at 14.9 and maintaining 15.0 in/hg. All pneumatic lines checked, 2 pressure controllers 2 safety valves and 2 outflow valves had been changed to find a proper matching setting with no effect. Settings of…
Last reply by smax64, -
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Hello herks structure expertise If center wing is replaced with the wing of 500HRs EBH Elapsed time What will be EBH of of the aircraft??? Best Regards Munir Abbasi Home of hercules Pakistan
Last reply by munirabbasi, -
- 5 replies
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Hello Herks Hydra Expertise! B model aircraft,During Retraction cycle of landing gears with UT system (in-flight) low pressure WX light of UT suction boost pump was Flickered and extinguished when gears were up and locked. Manufacture of Suction pump is able corporation sealed type and without cooling FAN and also without modification (C-130E airplanes AF72-1288 and up and C-13OH airplanes have a suction boost by-pass circuit. The by-pass line contains a restrictor and a check valve that will continuously circulate one GPM of fluid, from the suction boost pump back to the booster system reservoir, to provide a cooler operating boost pump). FE Said operation of…
Last reply by munirabbasi, -
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Hello C130 professionals! In an E Model Hercules, Flight Director Flag (FD flag) came in view on Co Pilot side PFD on ground during normal checks. Against the defect, all associated LRUs were replaced/swapped with serviceable ones. Even the PFD was swapped with pilot side, yet the flag did not disappear. Continuity of wiring was also double checked and was found SAT. No visible issue was observed yet the flag did not disappear. Autopilot engages without any defect and is working fine. Any ideas as to what might cause this or any previous experience, please do share. Thanks!
Last reply by munirabbasi, -
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Hello Fire extinguisher Squib Herks expertise. Life cycle of C-130B/E model aircraft Squib is not mentioned neither TOs 1C-130H-2-26JG-20-1 nor IC-130B-2-10 and IC-130B-2-7. but life of squib is mentioned in Service news in Vol 18,no1 which is not applicable in our fleet. any T.O which provides guide line for life of squib ,installed on Hercules aircraft. any expert opinion Munir Abbasi Home of Hercules Pakistan
Last reply by munirabbasi, -
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Hello Herks Hydro Expertise! Retraction cycle Timing of Right landing ( B model aircraft) is exceeded from prescribe given time sec ie ,38 seconds with UT hydraulic system but when retracting the landing gear with AUX hydraulic system on ground timing is with in limit ie 17 second . We have replaced right side of landing gear, the flow regulator, controllable restrictor valve, one way restrictor, hydraulic motor ,gear box,landing brake lock and HI.Torque two speed valve but defect was repeated again and again in every sortie. any expert opinion Best Regards Munir Abbasi Home Hercules Pakistan
Last reply by munirabbasi, -
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Hello brother peace be upon you. i am presently working in C-130B ac. For last few days, we are badly facing lots of problem regarding TCAS system. We couldn’t find the solution till now. Therefore, i thought to ask for the expert opinions in this forum. Problem : In Tcas system in flight, the traffic positioned in above, maximum time shows opposite direction incl its distance, for few days we are also didn’t found traffic in specific headings. Today for instance, one single traffic showed in 3 position. We have changed the TCAS processor but problem remained same. Again sometimes traffic shows actual position. Its getting worse day by day for…
Last reply by tinyclark, -
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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
Last reply by munirabbasi, -
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hello herky guys..has anyone heard or know about training flight touch n go cant be abort? any reference about it pls..
Last reply by mrjpc130h, -
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On approach for landing, a C130 E Model aircraft lowers landing gears only. Flaps are already down. While Lowering the landing gears, utility pressure drops to 1375 PSI and low pressure EDP light of both Engines and low pressure light of Utility Suction Boost Pump illuminated. As soon as the Landing Gears were extended completely, system pressure came back to Normal with all conditions within limit. To what component can this occurrence be attributed? Can it be the failure of Utility System Accumulator, Suction Boost Pump or EDP? And if we were to attribute this to Accumulator, is it possible for an Accumulator to suck hydraulic pressure from pressure line to fulfill its …
Last reply by munirabbasi, -
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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
Last reply by munirabbasi, -
- 1 reply
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Peace be upon you hello brothers of C-130 family I am working on C-130B ac. We are having a problem in the landing gear system. The problem nature is described below: Problem: Our right landing gear retraction and extraction time varies significantly in each operation. A few days retraction time (up time) were fol in each sorties 1st= 15sec 2nd= 17sec 3rd= 19 sec 4th = 24 sec 5th = 21 sec in all the above case nose timing was approx 13 sec and left took 16 sec approx. There is no significant change in the left and nose landing gear. However no significant delays in right landing gear and approx time is 17-18 sec w…
Last reply by hehe, -
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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
Last reply by munirabbasi, -
Hello to the Herc family. I am looking for an numerical version of the SMP 777. I am working on C130H and H30. Thanks
Last reply by Lionel, -
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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
Last reply by munirabbasi, -
DCU
by munirabbasi- 6 replies
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Hello Avionics Expertise How Data Concentration Unit Works? Munir Abbasi Home of Hercules Pakistan
Last reply by munirabbasi,
