Leak Detection 2/3 ||Pneumatic system

Hello everyone
I have tried to cover all the relevant information about leak detection, which is important for airline written exam point of view .
Please let me know in comments or through direct messages if something left or incorrectly explained.
IG Link flying_aur_peac...
Leak detection loops detect any overheating near the hot air ducts in the fuselage, pylons, and wings.
For the pylon and APU, the sensing elements are tied to form a single loop and for the wing, a double loop.
When the two wing loops detect a leak, or when one loop detects the leak and the other one is inoperative, they activate a wing leak signal.
BMC1 and BMC2 each contain identical control logic for the system.‐
A wing leak signal causes :
• bleed valve on the related side to close automatically
• the associated FAULT light on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start)
• the APU bleed valve to close automatically if the APU bleed valve is open and if the leak concerns the left wing (except during engine start).‐
A pylon leak signal causes :
• the bleed valve on the related side to close automatically
• the FAULT light for the related engine on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start).
• the APU bleed valve to close automatically if the APU bleed valve is open and if the leak concerns the pylon 1 (except during engine start).‐
An APU leak signal causes :
• the APU bleed valve to close automatically (except during engine start).
• the FAULT light the APU BLEED pushbutton switch on the AIR COND panel to come on
• the x-bleed valve to close automatically (except during an engine start).
.
.A beautiful picture has been taken by plane spotters & Photo copy right of the A320 jet airways livery goes to
www.planespotters.net/photo/1...
#pylon
#leak
#pneumatics
#320
#a320
#crossbleed
#bmc
#failure
#detection
#wing
#apu

[@syedahmed6688]

Thanks for explaining in a very clear manner please can you also make such an explanation video for A320neo LEAP engine anti ice where there are two anti ice PRSOV involved and their ways working very confusing

[@flying_aur_peace]

Glad that you find it helpful 😄.
I don't have enough knowledge about leap engine's dual Anti-ice PRSOV.
Please accept my apology.
I Will definitely try to ask and find about it.

[@Razzeldazzle9]

Hi your videos are very helpful and informative. Could you pls do one on auto flight system. Thank you

[@flying_aur_peace]

Good to hear that these videos are helping....
Definitely I will make videos on Auto flight, but before that am working on memory items and air-conditioning, please give me some time .....I will definitely make videos on your asked system.😄

[@skyworker3698]

hi, as far as I understand, when leak happened(06.35min) the bleed valve closes, but you highlighted pack flow control valve instead of bleed valve)) anyway the video is perfect as well as explanation, thank you so much, good job))

[@FarhanKhan-fg4qu]

Hi you have explained thorough and I want to ask if engine fire 1 switch is pressed why we can not use APU bleed and manually we are closing cross bleed

[@FarhanKhan-fg4qu]

But in case Engine 2 fire switch is Pushed we can use APU bleed but we have to shut cross bleed but as per schematic apu bleed is left side of cross bleed from which source apu bleed will move and cross while cross bleed valve is shut

[@girilebronkid]

If u pressed the eng fire 1 pushbutton, BMC 1 logic thinks that u have eng 1 fire and will electrically close the APU bleed valve since the loop connect only to BMC 1. thats why u cannot use APU bleed. But if u pressed the eng 2 fire pushbutton, the APU bleed valve will not close because BMC 2 doesnt connect with APU loop, so u can use APU bleed but u have to shut the cross bleed valve in order to prevent contaminated air coming from eng 2 fire burning