munirabbasi

14 hours ago, Metalbasher said:

I think that ID plate location is only on newer boxes...(don't know timeframe) but prior to going to the date plate, it was stamped in a location that cannot be seen when the box is installed.

 

Tiny clark already mentioned  his post

Munir Abbasi

Home of hercules Pakistan

6 hours ago, Ahmer said:

To avaoid such type FOD to improve APU panel modification of intake.Direction of intake is toward ground if u little change to upward to minimize the chance of FOD.(for without door APU)

Thanks Ahmer

Lockheed martin service news  pointed out  damage of  APU compressor due debris,  do not operate APU on ground until N# 2 engine is switched off, to FOE and enhance the life of APU

Regards

Munir Abbasi

Home of Hercules Pakistan

7 hours ago, pjvr99 said:

Probably want to keep APU shut down when taxing on dirt or unprepared strips. Having

said that, the intake screen holes are big enough to let in small gravel and stones which

can and will damage the compressor when it is started again ....

Thanks Peter The blades of  first stage has sulphidation problem at particular angle.

Munir Abbasi

Home of hercules Pakistan

27 minutes ago, munirabbasi said:

Booklet of kellstrom Defense Aerospace  Ink manual Write LE49710

Regards

Munir Abbasi

Amend to read my post LE49705 instead of LE49710

Regards

Munir Abbasi

1 minute ago, Ahmer said:

Hello sir, Le49705 ,GTCP 85-180le .plz check

Booklet of kellstrom Defense Aerospace  Ink manual Write LE49710

Regards

Munir Abbasi

Hello Honeywell Expertises:-

We are facing problem of APU compressor first stage blades damaged ,any expertise can tell me expert opinion  what are reasons behind it.( APU are door less)

Munir Abbasi

Home of hercules Pakistan

On 10/29/2018 at 3:30 PM, Ahmer said:

 

Good view of the condition lever.Electronic Control Valve housing has air start switch used  when NTS SW  is selected to NTS or Valve during air start.

Regards

Munir Abbasi 

Home of hercules Pakistan

18 hours ago, eliasafr said:

In C-130B aircraft tail no 58-0754 Lockheed no 3553 right rear mlg vertical beam got cracked. According to ipc 130B-4 the part no is 373014-1 L/R we tried to replace it by 373014-3 L/R as previous part no not available.but it is found not matched with the existing one.Now can we replace it with 388482-32?

Check T.O IC-130B-4, In Lieu part No

Munir Abbasi

Home of hercules Pakistan

On 10/27/2018 at 7:38 PM, Shola said:

Please i need help.

#2 Engine failed to air-start. Engine wound down from 60 percent rpm. On landing, engine started normally. NTS switch and NTS brackets checked ok. Pump housing oil quantity normal. Need help to rectify the fault. Thanks.

See the ignitor plugs of the engine

Munir Abbasi

20 hours ago, Nate Anderson said:

During the generator ops check, the book tells you to sequentially turn on/off the generators to tell you if the generator can handle the load of the aircraft. When generator 2,3,4 are off generator #1 shows high voltage on phase B only (121 volts). Along with that, we are getting ECBU's 6,7,8 input failures. We have changed GCU, engine generator and swapped BIU's. We still are getting the same problem. Any input will help. Thanks in advance

Oh There are problem of load sharing on  B phase. Check the Cargo compartment Recirculating FAN motor how much current drawn  by the fan A & C  phase and Galley power outlets.Also Check Y  grounding/current  transformer connections polarity X1 and X2 of  The ENGINE QEC/FS 245.

Munir Abbasi 

Home of hercules Pakistan 

13 hours ago, tinyclark said:

There is a plate installed on the rear beam of the wingbox at Wing Sta 10R, W.L. 262. Not sure if that is it, or that you can get to it.

Thanks Tinyclark

Munir Abbasi

Home of hercules Pakistan

3 minutes ago, Ahmer said:

1.NTS system is checked before engine shut down in air, when its ok then shut down the engine during aircrft FCF. if NTS system not functioning u could not shut down the engine for further air start.                                                               2. The system fuction not only use during air start only,  it's work during when prop try to rotate engine.this system start functioning & increase the angle prop throu mechnically linkage NTS bracket actuate the feathering valve. This system work in only alpha range. During shut down only mechnically  linkage & NTS switch serviceability checked for next flight. 

Good

Regards

Munir Abbasi

On 10/24/2018 at 3:35 PM, Ahmer said:

Hello any body knows about in which location on centre wing pt no/ s no strip is installed on C130. 

Center dry bay

Munir Abbasi

12 hours ago, NATOPS1 said:

1) The in flight check is to make sure the NTS system is adjusted correctly to prevent excessive drag and also to ensure the propeller speed or acceleration will be controlled during airstart. In flight the switch is in VALVE to "show" actual feather valve movement which causes the increase in blade angle.

2) The on the ground shutdown selection of NTS allows us to "see" the movement of the "NTS Linkage" that would normally actuate the feather valve. The linkage is camed out so it cannot actuate the feather valve but we want to make sure the system linkage is moving for the next flight.   

FRT Thanks for excellent explanation of NTS System.

Munir Abbasi

Home of hercules Pakistan

31 minutes ago, Ahmer said:

External tanks having two for each tank. One for centre compt & second for aft & fwd compt.   Regards

Thanks

Munir Abbasi

1 minute ago, Ahmer said:

 

Oh I saw my manual it shows one AFR guy pointed two

Thanks for correction

Munir Abbasi

Hello Aircraft fuel tanks expertise

Why two condensate drain valves are given in each  auxiliary fuel tank .?

Munir Abbasi home of hercules in pakistan

On 12/13/2016 at 10:57 AM, Great Above said:

1.   Pls why do we perform NTS checks on the C130?

2.   Why do we place the NTS/Valve switch to NTS before engine shutdown

To check the serviceability of NTS system in every post flight shutdown.  Three position SW is selected to NTS position before shutdown of engine because the system must  be checked either it is serviceable for next flight or not.

Munir Abbasi

Home of hercules Pakistan

20 minutes ago, Moeed hassan said:

Can u plz tell me WHAT ARE THE RPM OF ATM GEN MOTOR??? 

more over can u plz explain IF ATM MOTOR EXCEEDS ITS RPM LIMIT WHAT WIL HAPPENED??? 

I never heard ATM GEN motor . Contact me thru e-mail

Munir  Abbasi

On 10/21/2018 at 7:14 PM, Ahmer said:

I think output starter RPM is 8250 approx. Regard

Just assume that  your engaging the starter in flight ,at  what RPM Turbine of starter  is revalved?

Thanks

Munir Abbasi 

On 10/21/2018 at 9:32 PM, Ahmer said:

The limit of starter is 8250 to 8750 RPM.      Regards 

Dear as you that at what rpm engine starter become ratchet slip(disengaged)? 

Munir Abbasi

11 hours ago, Moeed hassan said:

Sir my question is which RPM u wanted to know.... I means RATED... NO LOAD CUT OUT or OUT PUT rpm??? Bcoz these all are different

Dear muddasar What is the 100 % RPM of ENG Starter?

Regards

Munir Abbasi

7 hours ago, Moeed hassan said:

On what condition???i Means at what level or stage u wanted to know the RPM??? 

Engine Starter Turbine RPM?

Munir Abbasi

19 hours ago, Moeed hassan said:

Job guides are there for fault isolation..... Ok fine with the throttle anticepation but my question is how probkem shifted to other engines if the problem was with NTS BRACKET itself... 

Moeed Hussain Sb GS/JG/FI/FR are familiar with them, how to coordinate FR with FI

Regards

Munir Abbasi

49 minutes ago, Moeed hassan said:

Pjvr99 do u know what actually happend in this case???? Look dear as mr. Muneer is saying problem shifted to No. 4 and No. 1 respectivly..... So NOW THE QUESTION IS IF NTS BRACKET WAS FAULTY THEN Y IT SHIFTED TO OTHER ENGINES???

No doubt NTS may also b the reason but only for one engine not for all. 

Dear moeed as you that what is synchrophaser stabilizing mode and throttle anticipation. Please consult T.O IC-130B-2-11. How NTS system  works?

Thanks

Regards

Munir Abbasi Home of hercules Pakistan