TUI

RB 211-535-E4

BORESCOPE INSPECTION

Eng Type: / Date:
Eng Serial No: / Station:
Eng Position: / NAA Approval Ref:
Aircraft Registration:

NOTE:

This form to be used in conjunction with - boeing task cards: 72-BAL-011

*Delete as required

NOTE! THE TASKS SPECIFIED IN ITEMS 11 AND 16 SHOULD NOT BE PERFORMED BY THE SAME PERSON ON BOTH ENGINES DURING THIS MAINTENANCE CHECK & ALL DAMAGE/WEAR MUST BE CLEARLY RECORDED ON THE PICTORIAL PAGES, INCLUDING ANY THAT ARE WITHIN mAINTENANCE MANUAL LIMITS.

ITEM NO / WORK TO BE CARRIED OUT / MECH / INSP
1) / IF THIS INSPECTION IS On L/H Engine OPEN THESE Circuit Breakers on P11 Overhead Circuit breaker Panel.
a)11D7Engines Standby Ignition Left 1.
b)11D8Engines Standby Ignition Left 2.
c)11L1Left Engine Ignition 1.
d)11D19Engine Start Cont’ Left.
e)11D12Thrust Reverser.
f) 6C12 Left Eng Synch Lock.
g) 11D11 Left Eng T/R Ind.
h) 11K32 Sync Lock.
i) 11K33 T/R Cont.
2) / IF THIS INSPECTION IS On R/H Engine OPEN THESE Circuit Breakers on P11 Overhead Circuit breaker Panel.
a)11D9Engines Standby Ignition Right 1.
b)11D10Engines Standby Ignition Right 2.
c)11L28Right Engine Ignition 1.
d)11D20Engine Start Cont’ Right
e)11B30Thrust Reverser.
f) 6D12 Right Eng Synch Lock.
g) 11B29 Right Eng T/R Ind.
h) 11K32 Sync Lock.
i) 11K33 T/R Cont.

FORM No: ENG/5612 ISSUE 14PAGE 1 OF 19

Engine serial No:
ITEM NO / WORK TO BE CARRIED OUT / MECH / INSP
3) / OPEN ENGINE FAN COWL ON LEFT HAND SIDE OF ENGINE.
4) / Remove HP turbine Turning Tool Cover.
5) / open the thrust reverser c-ducts.
(NOTE:ENSURE LEADING EDGE SLATS ARE RETRACTED AND DEACTIVATED IAW 27-81-00 BEFORE OPENING THE C-DUCTS).
6) / Remove sufficient Borescope plugs (F) (G) and (H) to suit inspection requirements, place each plug in a bag and secure adjacent to its access port. Record all removed plugs on page 3 item 11 using diagram and grid as supplied.
7) / carry out borEscope inspection of hp turbine blades iaw the Boeing Task Card as indicated on Page 1.
* ACCEPT
------
* REJECT
  • Delete as required

8) / borescope inspection of hp turbine blades.
Are there burns or oxidation on the bottom of the outer shroud near the rear non-interlock faces?
(Please tick appropriate box) YES NO
NOTE: If YES perform inspection of the non-interlock faces iaw the Boeing Task Card as indicated on Page 1 and record findings.
Indicate where findings are recorded ......
9) / carry out borEscope inspection of hp turbine NGV’s iaw the Boeing Task Card as indicated on Page 1.
* ACCEPT
------
* REJECT
  • Delete as required

10) / carry out borescope inspection of combustion liner & fuel spray nozzles iaw the Boeing Task Card as indicated on Page 1.
* ACCEPT
------
* REJECT
  • Delete as required

Engine serial No:
ITEM NO / WORK TO BE CARRIED OUT
11) / fIG 1 – F PLUG LOCATIONS




















Make an impression of your stamp over the corresponding action i.e. OFF/ON in the box adjacent to the plug removed and complete relative certification below.

Note

Combustor HP Turbine NGVs access ports (F) do not have designated numbering; the adjacent fuel nozzle positions; 2, 4, 6, 8, 10, 12, 14, 16 and 18 identifies the ports.
Fuel nozzles are identified numerically, clockwise Aft Looking Forward (ALF).
REFIT BOROSCOPE PLUGS AS REQUIRED IAW BOEING TASK CARDS
warning: FAILURE TO install all of the borescope plugs will CAUSE serious DAMAGE TO THE ENGINE AND AIRCRAFT STRUCTURE.
PLUGS / REMOVED (OFF)
MECH / INSPECTOR
(OFF) / LUBRICATED AND FITTED (ON) MECH / INSPECTOR
(ON) / INDEPENDENT INSPECTION
(ON)
G1
H1
FIG 1 - F PLUGS
Engine serial No:
ITEM NO / WORK TO BE CARRIED OUT / MECH / INSP
12) / CARRY OUT LOOSE article CHECK IN C- DUCT AREA.
13) / close and secure the thrust reverser c-ducts.
14) / reactivate leading edge slats and function. 27-80-00
15) / INDEPENDENT inspection leading edge slats.
16) /
  1. install new seal & refit HP turbine Turning Tool Cover.

Part No:
Batch No:
  1. InDEPENDENT INSPECTION

17) / if this inspection is On L/H Engine close these Circuit Breakers on P11 Overhead Circuit breaker Panel.
a)11D7Engines Standby Ignition Left 1.
b)11D8Engines Standby Ignition Left 2.
c)11L1Left Engine Ignition 1.
d)11D19Engine Start Cont’ Left.
e)D12Thrust Reverser.
f) 6C12 Left Eng Synch Lock.
g) 11D11 Left Eng T/R Ind.
h) 11K32 Sync Lock.
i) 11K33 T/R Cont.
18) / if this inspection is On R/H Engine close these Circuit Breakers on P11 Overhead Circuit breaker Panel.
a)11D9Engines Standby Ignition Right 1.
b)11D10Engines Standby Ignition Right 2.
c)11L28Right Engine Ignition 1.
d)11D20Engine Start Cont’ Right.
e)B30Thrust Reverser.
f) 6D12 Right Eng Synch Lock.
g) 11B29 Right Eng T/R Ind.
h) 11K32 Sync Lock.
i) 11K33 T/R Cont.
19) / RAISE DEFECT TO Leak check gearbox breather cover DURING IDLE RUN.
20) / CARRY OUT LOOSE article CHECK IN FAN COWL AREA.
21) / close and secure Fan Cowl panels.
22) / Were any defects raised as a result of the borescope inspections.
(Please tick appropriate box)YESNO
Certificate of Release to Service
This task was carried out and completed in accordance with the requirements of the MOE Part 2
procedure 2.16.
Date: / Signature: / Stampholder:
The Stamp/Signature denotes that the work has been carried out in accordance with the above Certification.

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.600 inch (15.24 mm)

“B” = 1.000 inch (25.40 mm)

“C” = 0.800 inch (20.32 mm)

* COOLING LIPS

Front Combustion Liner Inner and Outer Walls

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.600 inch (15.24 mm)

“B” = 1.000 inch (25.40 mm)

“C” = 0.800 inch (20.32 mm)

* COOLING LIPS

Front Combustion Liner Inner and Outer Walls

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.600 inch (15.24 mm)

“B” = 1.000 inch (25.40 mm)

“C” = 0.800 inch (20.32 mm)

  • COOLING LIPS

Front Combustion Liner Inner and Outer Walls

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW

AS A GUIDE TO ASSESS ANY DAMAGE

D = 0.375 inch (9.53 mm)G = 0.900 inch (22.86 mm)

E = 1.000 inch dia. (25.4 mm)H = 1.000 inch (25.4 mm)

F = 0.700 inch dia. (17.78 mm)

  • COOLING LIPS

Front Combustion Liner and Outer

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW

AS A GUIDE TO ASSESS ANY DAMAGE

D = 0.375 inch (9.53 mm)G = 0.900 inch (22.86 mm)

E = 1.000 inch dia. (25.4 mm)H = 1.000 inch (25.4 mm)

F = 0.700 inch dia. (17.78 mm)

  • COOLING LIPS

Front Combustion Liner and Outer

COMMENTS:-

USE THE DIMENSIONS SPECIFIED BELOW

AS A GUIDE TO ASSESS ANY DAMAGE

D = 0.375 inch (9.53 mm)G = 0.900 inch (22.86 mm)

E = 1.000 inch dia. (25.4 mm)H = 1.000 inch (25.4 mm)

F = 0.700 inch dia. (17.78 mm)

  • COOLING LIPS

Front Combustion Liner and Outer

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.030 inch (0.76 mm)“E” = MUST BE CONSISTANT AT EACH

“B” = 1.500 inch (38.1 mm) POSITION AROUND THE

“C” = 0.250 inch (6.35 mm) COMBUSTION CHAMBER RELATIVE

“D” = 2.650 inch (67.36 mm) TO THE ADJACENT SHIELD. Front Combustion Liner Heatshield

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.030 inch (0.76 mm)“E” = MUST BE CONSISTANT AT EACH

“B” = 1.500 inch (38.1 mm) POSITION AROUND THE

“C” = 0.250 inch (6.35 mm) COMBUSTION CHAMBER RELATIVE

“D” = 2.650 inch (67.36 mm) TO THE ADJACENT SHIELD. Front Combustion Liner Heatshield

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

“A” = 0.030 inch (0.76 mm)“E” = MUST BE CONSISTANT AT EACH

“B” = 1.500 inch (38.1 mm) POSITION AROUND THE

“C” = 0.250 inch (6.35 mm) COMBUSTION CHAMBER RELATIVE

“D” = 2.650 inch (67.36 mm) TO THE ADJACENT SHIELD. Front Combustion Liner Heatshield

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

A = 2.952 inches (75.0 mm)

B = 0.078 inch (2.0 mm)

C = 0.236 inch (6.0 mm)

D = 0.500 inch (12.7 mm)

HP Nozzle Guide Vane

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

A = 2.952 inches (75.0 mm)

B = 0.078 inch (2.0 mm)

C = 0.236 inch (6.0 mm)

D = 0.500 inch (12.7 mm)

HP Nozzle Guide Vane

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

E = TRAILING EDGE THICKNESS 0.042 inch (1.07 mm)

F = HOLE SIZE 0.018 inch (0.46 mm) DIAMETER

USE THE DIMENSIONS SPECIFIED BELOWCOMMENTS:-

AS A GUIDE TO ASSESS ANY DAMAGE

A = 2.401 inches (61.0 mm)

B = 0.078 inch (2.0 mm) APPROXIMATELY

BETWEEN FILM COOLING AIR HOLES

C = 2.519 inches (64.0 mm)

HP Turbine Blades

FORM No: ENG/5612 ISSUE 14PAGE 1 OF 19