WINDSHIELD REMOVAL INSTALLATION

LH WINDSHIELD REMOVAL/INSTALLATION 

Wind Shield FIN -3DG1/3DG2

Wind shield P/N-STA320-1-7-1 OR NPS165311-7

O-Ring for Spray Nozzle-

NSA8207-2 &NSA8207-3

Torque reqd for Bolts-144 TO 170 LBFT-INCH

Sealant -06AEB2,06LCG9,13GAB8

Non Aqueous cleaner-08BAA9

Aluminium Foil-05RAB9

Curing time-

Clearances reqd-Refer AMM pic below.

C/Bs reqd to be opened are -

49VU-H04

121VU-K13

122VU-W14,W13,X14,X13,

123VU-AF10,AF03

AMM REF:-5611-11-000/400-001-A

NOTE WHILE REMOVING THE WINDSHIELD,MAKE A TEMPLATE AND ENSURE INSTALLING ALL THE BOLTS,ICING TUBE ETC exactly at same locations so that while installing,you must install exactly at same locations so that this will minimise any error in installation.

(1)Once the window is placed and held in position either manually or by the help of a special tool,engage the bolts and give the Torque between 144 to 170 lbft-inch.

Follow the TQ sequence for Upper, Bottom and Mid frame as under:-

(2)Upper & Bottom plates are installed.

(3)Be cautious while installing the bolts,extra care to be given for each bolts position and follow the Torque sequence.

(4)Clearances to be measured as under at following locations:-

Ice Tube is installed from top to 6th position in place of bolt and nut is tightened from inside.

Eye balls are installed on the center arm from inside.Its plate is attached at 2nd bolt,leaving the top bolt.

Eyeballs will be attached in such a way that RED one will be at top.

Sealant will be applied at each intersection of upper,lower and center plates alongwith all the 33 bolt’s head.

Install the interior center and side fairing and wait until sealant get cured.

Sealant curing time is generally mentioned on its package as it depends sealant composition that varies with manufacturer.Usually it takes 8 to 10 hrs 

If Aircraft is routed for flight before curing,we followed the process of applying HST on each interfacing where sealants have been applied and at bolt heads.

Mention this in Techlog for GVI of Aluminium foil until curing time gets over but ensure that flying time is excluded is added in actual curing time 

🌺 Navratri Pooja at Royal Green Apartments 🌺

The auspicious occasion of Navratri was celebrated with immense joy, devotion and happiness at Royal Green Apartments.

An idol of Maa Durga was beautifully placed adjacent to Shivalaya, where daily pooja was performed, worshipping the different divine forms of Maa Durga throughout the nine sacred days. The celebrations were accompanied by Sandhya Aarti every evening, filling the atmosphere with devotion, peace and spiritual energy.

💃 Dandiya Night added colour and excitement to the festivities, as residents participated enthusiastically and enjoyed the occasion to the fullest, making it a memorable celebration for everyone.

https://drive.google.com/file/d/1L7yIg0edfaTfmLqCwX4QRZV_pDsRnSOU/view?usp=drivesdk

🙏 Today, we bid farewell to Maa Durga with heavy hearts and tears in our eyes. The ten days of devotion, togetherness and celebration have come to an end, leaving behind cherished memories and a renewed sense of faith and unity among our residents.

May Maa Durga continue to shower her blessings upon all residents and their families, bringing happiness, prosperity, good health and peace to every home.

Jai Mata Di! 🙏🌺

With warm regards,
Pramod Kumar

Replacement of AILERON SERVO ACTUATOR 

FIN  No-

33CE1/33CE2/33CE3/33CE4

WEIGHT OF SERVO is 7.4 kg Hence be careful while removing.

Trestles of 13 feet (4M),

Following jobs are to be done:-

(1)PTU isolation coupling is to be disconnected AMM REF 29-23-00-860-001

(2)Both the G and B Hydraulic system to be depressurised IAW AMM 29-10-00-864-003/-001

and following CBs are to be Open and safetied.

(3)Open the Panel at bottom and Top

(4)Aileron Collar PN-98D27104005000

is required to be installed on Servo which is not being worked upon.

(5)Remove following CBs and safetied:-

49VU-B11

121 VU-R20

105 VU-A01,A02

(6)TQ required11 to 12 lbft-ft

(7)Remove the Electrical connector and cap it prevents Hyd contamination of its contact.

Packings P/N -NAS 1611-112 & NAS1611-010 are of Hyd Pr & Return line.

Practically,it isn't required as it is the part of Aileron Servo.

Servo Actuator P/N-31073-110

AILERON SERVO ACTUATOR 

There are Two lock plate,one is at the Rear Jack of servo locking & another at Fwd jack of Servo.

The lock plate is to be placed over the head of the PIN and is to be locked.

To get access to the FWD lock Plate,open the Aileron top panel and for which one needs a long arm rachet.

After removing the rear jack PIN,remove both the Pressure & Return line,this will give slightly more access to the FWD jack.

After accomplishment of the job,noemalise the Aircraft.

Follow applicable AMM,this is just a guide lines 

Manual deployment & Stowing of Blocker Door of CFM 56 Engine

Manual deployment/stowing of T/R Blocker door on CFM 56 Engine

Refer AMM 

1. T/R Manual deactivation:-

78-30-00-481-041-B

2. Manual deployment of Blocker door:-

78-32-41-860-001-A

3. Manual stow of Blocker door:-

78-32-41-860-002-A

4. Operational test of TR through CFDS:-

78-31-00-710-042-A

Deactivate T/R for maintenance by pulling HCU lever away from the flight position.

Remove the Stow pin from its Stow position and put this pin in while the lever is away from the flight position.

HCU lever is located at 1 O’ Clock  aft looking fwd.

Manual unlock Shaft:-

Manual UNLOCK SHAFT as shown in picture is accessed and unlocked by the use of a 5/16 inch wrench.

Blocker door is unlocked by getting lock released from hook and one can see the gap of about 1 inch of Blocker door from its initial Locked position.Once it is done you move to the next step to unlock manual unlock Square.

This is done only after removing the Thermal Blanket which is wire locked in 3 parts over the UNLOCK SHAFT.

There are 4 unlock Shafts and 4 Manual unlock Squares.

The process is repeated on each shaft and square to Deploy or Stow all the 4 Blocker doors in each engine.

Manual unlock Square:-

This Square is to be placed by the wrench to the UNLOCK position and at the same time BLOCKER DOOR TO BE PULLED OUT by hand and to deploy.

The blocker door gets deployed.

NOTE:- FOR STOWING THE BLOCKER DOOR MANUALLY,EACH DOOR IS PUSHED IN WHERE AS IT IS PULLED OUT WHILE MANUAL SQUARE IS PLACED IN UNLOCK POSITION.

 while it is stowed,it may not get fully flushed with a surface which gets properly seated when T/R test is conducted through MCDU.

For conducting Test follow MCDU procedure by pressurizing Electric Pump and putting the relevant engine FADEC ON.

Once the test is done T/R moves physically to Deploy and Stow position and Blocker Door seated properly.You will get Test OK or Failure msg.

This is a simple guidance to do the job,refer to the applicable manual.

Installation of Aircraft Stretcher

The basic principle is to install a 6ft stretcher without removing the seats.

This requires 3 seats to be engaged as the stretcher mechanism are installed over 3 seats (Last 3 rows of LH or RH Side)

In order to do this,two seats ie E&F in each row(fwd),except the last row,backrest are folded in forward direction.

A stretcher is installed over these 3 rows of seats.

The following is the work scope of stretcher installation 

Step 1

Open the Bolts of two seats back rest

Step 2

Remove the actuator’s bolt of these two seats

Step 3

Install the seat rails between The Two seats tracks for support of installing stretcher mechanism over it.

Step 4

Install B poles over these seat rails leaving 4 holes from both sides i.e. install this pole in 5th hole from left and also in 5th hole from Right.

Step 5

Install and assemble the platform on this two poles.

Step 6

Install the belts from the lower side of the platform and attached to the rear side of last row of two seats.

Step 7 

Attach the stretcher over the platform and keep the cushion over it.

Step 8 

Install a privacy curtain over it.

This is just a simple guidance whereas one has to follow special instructions of its manufacturer.

After removal these seats are to be disinfected before the aircraft is normalised for next flight.

Replacement of APU Lube unit fitted on A320 series of Aircraft

FIN-8080KM

P/N-413020-5

TQ RANGE-131 to 180 lbft-inch

SEALS REQD-

M83249-1-143 Seal for Lube unit

M83248-1-035 Seal of FCU

M25988-2-011 Seal for FCU line Qty 6

M25988-2-013 Seal for FCU line Qty 2

For replacement of the Lube unit AMM 49-91-45-000/400-003-A,FCU 

needed to be removed and then installed.AMM 49-31-11-000/400-003-A

FCU has 4 fuel lines,3 of which have 2 seals in one line of same P/N and one line has 2 seals of different P/N than 3 previous lines which have 6 seals.

A sequence is to follow for mounting bolts of Lube unit as given below in the pic

Torque required to be given is 180 lbft-inch

Replenish the APU oil if needed and close the APU access door.

Checked for APU performance on both load of electrical and bleed load.

This is just a maintenance tip,refer to AMM for details.

Replacement of IDG Charge and Scavenge Filter

AMM TASK 24-21-51-000/400-810-A

Torque reqd is 180 lbf-inch

Filter P/N-5909812

Packing (1) is usually available with Filter itself.

Seals of IDG Charge and scavenger filter

Seal for drain

IDG Scavenge filter 

Charge Filter

FILL THE IDG oil system IAW AMM 12-13-24-612-804

Qty of Oil required is 6Qtz

Close the Fan cowl door AMM 

TASK 71-13-00-410-803

Aircraft to be normalised

Note:-Filter Seal PN -214 usually comes installed with.

This is just a simple guidance refer applicable AMM.