DOC AIRBUS | AMM A320FRemoval of Full Set Fuel Nozzles [CFML]
TASK 73-11-30-000-803-A
Removal of Full Set Fuel Nozzles
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 73-11-30-880-050-A
(1) After the first hour of soaking, shock the remaining bolts (85) bolt heads with a HAMMER - NON METALLIC and brass DRIFT - PUNCH as example.
(a) Break the torque of the bolts (85) that you remove with half a turn counterclockwise.
(b) Apply aero kroil penetrant (Material No.CP2691) again to the bolts (85). Let application soak for another one hour.
(d) If the bolts (85) become too tight, spray with aero kroil penetrant (Material No.CP2691) on the bolt shaft and in the bolt hole. Turn the bolts (85) CW for three revolutions. Apply aero kroil penetrant (Material No.CP2691) on the fuel nozzle bolt shaft and in the bolt hole again. Continue to loosen the bolts (85).
(f) Remove all bolts (85).
Subtask 73-11-30-020-077-A
[Rev.10 from 2021]
2026.04.01 03:04:05 UTC
Removal of Full Set Fuel Nozzles
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | ACCESS PLATFORM 1M(3 FT) |
| No specific | 1 | CONTAINER 5 USGAL (19 L) - FUEL RESISTANT |
| No specific | 1 | DRIFT - PUNCH |
| No specific | 1 | HAMMER - NON METALLIC |
| No specific | 1 | PLIERS - JAWED, SOFT |
| No specific | AR | TIE WRAP(S) |
| No specific | AR | WARNING NOTICE(S) |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.CP2691) | aero kroil penetrant |
| (Material No.CP5061) | temporary marking |
| (Material No.CP8002) | safetywire |
| (Material No.CP8006) | safety cable 0.032 in. (0.8 mm) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 210 | CKPT,FWD COMPT BHD TO FLT COMPT BULKHEAD |
| 400 | POWER PLANT, NACELLES AND PYLONS |
| 410 | ENG 1 PYLON BOX AND FORWARD FAIRING |
| 420 | ENG 2 PYLON BOX AND FORWARD FAIRING |
| FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2) | |
| 447AL, 448AR, 461AL, 462AR | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 30-21-51-000-804-A | Removal of the AFT Air-Intake Anti-Ice Valve (PRSOV1) |
| TASK 36-11-49-000-827-A | Removal of the Environmental Control System (ECS) Ducts from the Engine Case Ports to the Pylon Connections |
| TASK 36-11-51-000-803-A | Removal of the HP Bleed Valve (HPV) |
| TASK 70-70-00-910-804-A | Electrical Standard Practices |
| TASK 71-00-00-700-805-A | Dry-Motoring Check |
| TASK 71-13-00-010-803-A | Opening of the Fan Cowl Doors |
| TASK 75-11-05-000-801-A | Removal of the Starter Bleed/Booster Anti-Ice Valve |
| TASK 75-21-05-000-801-A | Removal of the High Pressure Turbine (HPT) Active Clearance Control (ACC) Valve |
| TASK 75-22-05-000-801-A | Removal of the Low Pressure Turbine Active Clearance Control (LPT ACC) Valve |
| TASK 75-33-05-000-801-A | Removal of the Transient Bleed Valve (TBV) |
| TASK 78-30-00-040-809-A | Deactivation of the Thrust Reverser System for Ground Maintenance |
| TASK 78-36-00-010-806-A | Opening of the Thrust Reverser Cowl Doors |
TBV and Start Bleed ValveSubtask 73-11-30-880-050-A
A. Engine Cooldown
(1) If a faster cool down is necessary, do a dry motoring for more than five minutes as soon as possible when the aircraft is grounded and ready to replace the fuel nozzles (Ref. AMM TASK 71-00-00-700-805).
Subtask 73-11-30-941-059-A (1) If a faster cool down is necessary, do a dry motoring for more than five minutes as soon as possible when the aircraft is grounded and ready to replace the fuel nozzles (Ref. AMM TASK 71-00-00-700-805).
NOTE: The dry motoring will help to cool down the engine to start the fuel nozzle replacement.
B. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put WARNING NOTICE(S) in position to tell persons not to operate:
(a) Make sure that the ON legend of the FADEC GND PWR 1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
Subtask 73-11-30-010-070-A (1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put WARNING NOTICE(S) in position to tell persons not to operate:
- The ENG/MODE selector switch
- The ENG/MASTER 1(2) control switch.
(a) Make sure that the ON legend of the FADEC GND PWR 1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).
C. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR.
Subtask 73-11-30-040-060-A (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-803):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
437AL 438AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
447AL 448AR.
D. Deactivation of the Thrust Reverser (T/R) System for Maintenance
Subtask 73-11-30-010-071-A WARNING:
YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.
(1) Do the deactivation of the T/R system for ground maintenance (Ref. AMM TASK 78-30-00-040-809). E. Get Access
(1) Open the T/R cowl doors (Ref. AMM TASK 78-36-00-010-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR.
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.
4. Procedure(1) Open the T/R cowl doors (Ref. AMM TASK 78-36-00-010-806):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENGINE 1)
451AL 452AR.
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENGINE 2)
461AL 462AR.
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.
WARNING:
BE CAREFUL NOT TO GET AIRCRAFT FUEL IN YOUR MOUTH OR IN YOUR EYES.
IF YOU GET FUEL ON YOUR SKIN OR ON YOUR CLOTHES, FLUSH IT IMMEDIATELY WITH WATER.
IF NECESSARY, GET MEDICAL HELP.
AIRCRAFT FUEL IS POISONOUS.
CAUTION:
USE TWO WRENCHES TO LOOSEN THE TUBE COUPLING NUTS. USE ONE WRENCH TO HOLD THE NIPPLE FITTING. USE THE OTHER WRENCH TO LOOSEN THE COUPLING NUT. IF THE NIPPLE FITTING TURNS, DAMAGE CAN OCCUR.
CAUTION:
USE PLIERS THAT HAVE TEFLON JAWS TO TIGHTEN OR LOOSEN THE ELECTRICAL CONNECTORS. DO NOT USE PLIERS THAT HAVE METAL JAWS. METAL JAWS CAN CAUSE DAMAGE TO THE ELECTRICAL CONNECTORS.
Subtask 73-11-30-860-051-A A. General
(1) Look at the LEAP-1A fuel nozzle removal and installation best practices video. Download it from CFM PSE (https://mycfmportal.com), under MyDownload Gadget.
(2) Give adequate lighting to the left and right engine core areas.
(3) Make sure that engine panel precautions in cockpit are met and T/Rs deactivated and tagged out as per AMM and standard processes.
(4) Put the CONTAINER 5 USGAL (19 L) - FUEL RESISTANT below the engine core area (combustor area). Have rags, vinyl tape and absorbent pads in the area.
(5) When you remove the fuel nozzles (14) and components, be prepared to replace damaged case inserts, if required.
Subtask 73-11-30-110-050-A (1) Look at the LEAP-1A fuel nozzle removal and installation best practices video. Download it from CFM PSE (https://mycfmportal.com), under MyDownload Gadget.
(2) Give adequate lighting to the left and right engine core areas.
(3) Make sure that engine panel precautions in cockpit are met and T/Rs deactivated and tagged out as per AMM and standard processes.
(4) Put the CONTAINER 5 USGAL (19 L) - FUEL RESISTANT below the engine core area (combustor area). Have rags, vinyl tape and absorbent pads in the area.
(5) When you remove the fuel nozzles (14) and components, be prepared to replace damaged case inserts, if required.
B. Fuel Nozzle Bolts and Case Bolts Soaking
(1)
1 Do an initial soak of all the 76 bolts (85) with aero kroil penetrant (Material No.CP2691) at the very beginning of the job. Let the application soak for one hour. Let the capillary action of aero kroil penetrant (Material No.CP2691) penetrate while you work the external hardware removal in parallel before you break the torque of the bolts (85).
2 Do an initial soak of all the hot section bolts that follow (other than bolts (85)) with aero kroil penetrant (Material No.CP2691) at the very beginning of the job:
a For PRE SB 72-0190 configuration, bolts (9) from the forward transient bleed air tube (10) and bolts (30) from the machined valve support bracket (31) and air duct bracket (33).
b For POST SB 72-0190 configuration, bolts (76) from air duct bracket (33).
c Bolts (78) from the Environmental Control System (ECS) air duct (79).
d Bolts (130) from the High Pressure Turbine (HPT) cooling 7th stage air tube (127).
e For PRE and POST SB 72-0133 configurations, bolts (16) and self locking nuts (referred to as nuts) (17) from the electrical harnesses support bracket (15).
f Let the aero kroil penetrant soak for one hour.
Subtask 73-11-30-020-075-A (1)
NOTE: The offset hole on the case aft flange is the top vertical centerline. The first fuel nozzle (14) Clockwise (CW) and aft looking forward from the top vertical centerline is the No. 1.
(a) To prevent broken bolts and damaged inserts while you do the hardware removal process, apply aero kroil penetrant (Material No.CP2691) to the bolts and do as follows: 1 Do an initial soak of all the 76 bolts (85) with aero kroil penetrant (Material No.CP2691) at the very beginning of the job. Let the application soak for one hour. Let the capillary action of aero kroil penetrant (Material No.CP2691) penetrate while you work the external hardware removal in parallel before you break the torque of the bolts (85).
2 Do an initial soak of all the hot section bolts that follow (other than bolts (85)) with aero kroil penetrant (Material No.CP2691) at the very beginning of the job:
a For PRE SB 72-0190 configuration, bolts (9) from the forward transient bleed air tube (10) and bolts (30) from the machined valve support bracket (31) and air duct bracket (33).
b For POST SB 72-0190 configuration, bolts (76) from air duct bracket (33).
c Bolts (78) from the Environmental Control System (ECS) air duct (79).
d Bolts (130) from the High Pressure Turbine (HPT) cooling 7th stage air tube (127).
e For PRE and POST SB 72-0133 configurations, bolts (16) and self locking nuts (referred to as nuts) (17) from the electrical harnesses support bracket (15).
f Let the aero kroil penetrant soak for one hour.
C. External Hardware Removal
(2) Remove the external components at the Right Hand (RH) side of the engine, aft looking forward, as follows:
(a) For PRE and POST SB 72-0190, do as follows:
1 Disconnect the HJ8A harness (1) from the start bleed valve (2) (Ref. AMM TASK 70-70-00-910-804).
(b) Move the two HJ8A harness (1) away from the fuel nozzles removal path and hold them with TIE WRAP(S).
(c) For PRE and POST SB 72-0190, do as follows:
1 Remove the TBV (3) (Ref. AMM TASK 75-33-05-000-801) and do as follows:
a Discard all seals that are exposed.
2 Remove the start bleed valve (2) (Ref. AMM TASK 75-11-05-000-801) and do as follows:
a Discard all seals that are exposed.
END OF PRE AND POST SB 72-0190
(d) Remove the HP bleed valve (4) from the engine (Ref. AMM TASK 36-11-51-000-803).
1 Discard all seals that are exposed.
1 After the first time you soaked the bolts (9), soak the bolts (9) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts before you remove them.
2 Remove the bolts (11) from the support bracket (12).
3 Remove the bolts (5) from the TBV support bracket (referred to as support bracket) (13).
4 Remove the four bolts (9) that attach the transient bleed air tube (10) to the combustion case (6).
5 Keep orifice plate (8) for future installation.
6 Discard the metal seal ring (7).
(f) For PRE SB 72-0133 configuration, remove the support bracket (15) as follows:
1 After the first time you soaked the two bolts (16) and two nuts (17), soak the two bolts (16) and two nuts (17) again with aero kroil penetrant (Material No.CP2691) . Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Move the left T48 harness (19), the turbine center frame accelerometer (18) and the right T48 harness (22) as follows:
a Remove the two machine bolts (20) that attach the two loop clamps (21) from the right T48 harness (22) and the support bracket (15).
b Remove the two bolts (20) that attach the two loop clamps (21) from the left T48 left harness (19) and the support bracket (15).
c Remove the two bolts (20) that attach the two loop clamps (23) and the turbine center frame accelerometer (18) to the support bracket (15).
d Move the right T48 harness (22), the left T48 harness (19) and the turbine center frame accelerometer (18) away from the fuel nozzle removal path.
3 Remove the two bolts (16) and two nuts (17) and remove the support bracket (15).
END OF PRE SB 72-0133
(g) POST SB 72-0133
Remove the support bracket (15) as follows:
1 After the first time you soaked the two bolts (16) and two nuts (17), soak the two bolts (16) and the two nuts (17) again with aero kroil penetrant (Material No.CP2691) . Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Move the left T48 harness (19), the turbine center frame accelerometer (18) and the right T48 harness (22):
a Remove the two bolts (20) that attach the two loop clamps (21) and the left T48 harness (19) to the support bracket (15).
b Remove the two bolts (20) that attach the two loop clamps (23) and the turbine center frame accelerometer (18) to the support bracket (15).
c Remove the three bolts (20) that attach the three loop clamps (21) and the right T48 harness (22) to the support bracket (15).
d Move the right T48 harness (22), the left T48 harness (19) and the turbine center frame accelerometer (18) away from the fuel nozzle removal path.
3 Remove the two bolts (26) and retaining strap (25) that attach the support bracket (15) to the HPT cooling 7th stage air manifold (referred to as 7th stage air manifold) (24).
4 Remove the two bolts (16) and two nuts (17) and remove the support bracket (15).
END OF POST SB 72-0133
(h) PRE SB 72-0190
Remove the support brackets (31) and (13), bracket (39) and air duct bracket (33) (as a module package) from fuel nozzles (14) No. 1 and No. 2 and fuel nozzles (14) No. 3 and No. 4 as follows:
1 Try as possible to remove this hardware as a module package.
2 After the first time you soaked the bolts (30), soak again the bolts (30) from the combustion case (6) with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts before you remove them.
3 Remove the bolts (30) from the valve support bracket (31) and the combustion case (6).
4 Remove the bolts (29) from the loop clamps (28) that attach the right T48 harness (22), the left T48 harness (19) and the support bracket (13).
5 Remove the bolts (27) from the fuel hydraulics support bracket (38), the support bracket (13) and the bracket (39).
6 Remove the bolts (30) from the air duct bracket (33) and the combustion case (6).
7 Remove the bolts (32) from air duct bracket (33) and start bleed valve support bracket (34) and do as follows:
a Keep the hardware for future installation.
8 Remove the two bolts (35) from the retaining strap (37) that attach the 4th stage air manifold (36) and bracket (39) to the support bracket (13) and do as follows:
a Keep the hardware for future installation.
9 Remove the valve support bracket (31), support bracket (13) and bracket (39) and the air duct bracket (33) as a module package and do as follows:
a Keep the module package for future installation.
(i) Remove the start bleed leg air duct (45) and the support bracket (42), as a module package as follows:
1 Try as possible to remove the start bleed leg air duct (45) and the support bracket (42) as a module package.
2 Remove the four bolts (32) that attach the support bracket (42) to the start bleed valve support bracket (47) and to the start bleed valve support bracket (34).
3 Remove the two bolts (44) that attach the support leg bracket (49) to the start bleed valve support bracket (43) and the support bracket (42).
4 Remove the two bolts (26) that attach the retaining strap (50) and 7th stage air tube (51) to the support bracket (42).
5 Remove the start bleed leg air duct (45) and the support bracket (42) as a module package and do as follows:
a Keep the module package for future installation.
(j) Remove the bolts (40) from the fuel hydraulic support bracket (41) and the start bleed valve support bracket (34) and do as follows:
1 Keep the support bracket (41) installed on the engine.
(k) Remove the hardware that follow and the module package core compartment cooling bracket (52), start bleed valve support bracket (34) and drain support bracket (referred to as support bracket) (61) as follows:
1 Try as possible to remove this hardware as a module package.
3 Remove the bolt (59) that attaches the loop clamp (60) to the drain tube (62) and support bracket (61).
4 Remove the bolt (58) that attaches the loop clamp (57) to the drain tube (62) and start bleed valve support bracket (34).
5 Remove the bolt (53) from the core compartment cooling bracket (52).
6 Remove the bolt (53) from the start bleed valve support bracket (34).
7 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (47).
8 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the air duct bracket (33).
9 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (43).
10 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (48).
11 Remove the bolts (65) from the support bracket (61).
12 Remove the bolts (40) from the start bleed valve support bracket (34).
13 Remove the bolt (56) from the start bleed valve support bracket (34).
14 Remove the module package: core compartment cooling bracket (52), start bleed valve support bracket (34) and support bracket (61) and do as follows:
a Keep the module package for future installation.
END OF PRE SB 72-0190
(l) POST SB 72-0190
Remove the start bleed valve support bracket (34) as follows:
1 Remove the two bolts (32) that attach the booster anti-ice air tube (75) to the start bleed valve support bracket (34).
2 Remove the two bolts (32) that attach the start bleed tube duct (70) to the start bleed valve support bracket (34).
3 Remove the two bolts (32) that attach the start bleed valve support bracket (34) to the air duct bracket (33).
4 Remove the four bolts (32) that attach the support bracket (42) to the start bleed valve support bracket (34).
5 Remove the bolt (68) that attaches the loop clamp (69) and the PS3 air tube (67) to the start bleed valve support bracket (34).
6 Remove the bolt (68) that attaches the loop clamp (69) and the PS3 air tube (67) to the support bracket (42).
7 Remove the bolt (59) that attaches the drain tube (62) to the start bleed valve support bracket (34).
8 Remove the two bolts (65) that attach the support bracket (66) to the start bleed valve support bracket (34):
a Keep the support bracket (66) attached to the drain tube (71) and the core control harness (74).
9 Remove the start bleed valve support bracket (34) from the engine.
(m) Remove the air duct bracket (33) as follows:
1 After the first time you soaked the bolts (76), soak the bolts (76) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts. Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Remove the bolts (76) that attach the air duct bracket (33) to the combustion case (6).
3 Remove the air duct bracket (33).
END OF POST SB 72-0190
(n) PRE AND POST SB 72-0190
Disconnect the B-nut on the PS3 air tube (67) from the PS3 tube (77) at the fuel nozzle (14) No. 7.
END OF PRE AND POST SB 72-0190
(3) Remove the external components at the Left Hand (LH) side of the engine, aft looking forward:
(a) Remove the ECS air duct (79) from the engine case at the 6:00 o’clock position, aft looking forward and do as follows (Ref. AMM TASK 36-11-49-000-827):
1 After the first time you soaked the bolts (78), soak the bolts (78) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts. Give the aero kroil penetrant (Material No.CP2691) time to soak into threads and do as follows:
a Discard all seals that are exposed.
(b) Remove the High Pressure Turbine Active Clearance Control (HPTACC) valve (82) and the Low Pressure Turbine Active Clearance Control (LPTACC) valve (81) (Ref. AMM TASK 75-21-05-000-801) and (Ref. AMM TASK 75-22-05-000-801) and do as follows:
1 Remove the HPTACC valve (82), LPTACC valve (81), brackets and the flex ducts as a module package.
2 Discard all seals that are exposed.
(c) Remove Pressure Regulating and Shut-Off Valve (PRSOV) 1 (83) and the air duct (80) (Ref. AMM TASK 30-21-51-000-804) and do as follows:
1 Try as possible to remove this hardware as a module package PRSOV 1 (83) and its associated air duct (80):
a If not possible, remove the PRSOV 1 (83) first and then remove the associated air duct (80).
2 Discard all seals that are exposed.
(d) Remove the module package (support brackets (89) and (84)) at fuel nozzle (14) No. 16 as follows:
2 For POST SB 72-0036 and PRE SB 72-0133 configurations, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (88) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) from the support brackets (87) and (89).
d Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0036 AND PRE SB 72-0133
3 For POST SB 72-0133 and PRE SB 72-0205 configurations, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (93) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) that attach the support brackets (87) and (89).
d Remove the bolt (92) that attaches the support brackets (91) and (89).
e Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0133 AND PRE SB 72-0205
4 For POST SB 72-0205 configuration, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (93) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) that attach support brackets (87) and (89).
d Remove the two bolts (96) and retaining strap (95) that attach the 4th stage air manifold (94) to the support brackets (91) and (89).
e Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0205
(4) Removal of the external components at the bottom of the engine (6:00 o’clock position), aft looking forward:
(a) PRE SB 72-0211
Remove all the hinged cushioned loop clamps that follow from the oil tubes support bracket (referred to as bracket) (97) that attach the oil supply/scavenge tubes (referred to as tubes) (104), (102), (101) and (99) at the 5:00 o’clock position, aft looking forward, as follows:
2 Remove the bolt (100) from the loop clamp (103) and from the bracket (97).
3 Remove the bolts (100) from the loop clamps (98) and from the bracket (97).
END OF PRE SB 72-0211
(b) POST SB 72-0211
Remove all the loop clamps that follow from the bracket (97) that attach the tubes (104), (102), (101) and (99) at the 5:00 o’clock position, aft looking forward, as follows:
2 Remove the bolt (100) from the loop clamp (103) and from the bracket (97).
3 Remove the bolt (100) from the loop clamp (98) and from the bracket (97).
4 Remove the bolt (100) from the loop clamp (106) and from the bracket (97).
END OF POST SB 72-0211
(c) PRE SB 72-0211
Remove the module package: Bracket (110) and oil tubes support brackets (108) and (112) at the 5:00 o’clock position, aft looking forward, as follows:
1 Try as possible to remove this hardware as a module package.
2 Remove the two bolts (85) from fuel nozzle (14) No. 9 as specified in Para. 4.E and from the bracket (108).
3 Remove the three bolts (85) from fuel nozzle (14) No. 8 as specified in Para. 4.E and from the bracket (110).
4 Remove the bolt (107) from the loop clamp (109) and from the brackets (110) and (112).
5 Remove the bolt (100) from the loop clamp (103) and from the bracket (110).
6 Remove the bolt (100) from the loop clamp (98) and from the bracket (110).
7 Remove the bolt (107) from the cushioned loop clamp (111) and from brackets (110) and (112).
8 Remove the module package of brackets (110), (108) and (112).
END OF PRE SB 72-0211
(d) POST SB 72-0211
1 Remove the module package: Brackets (110), (108) and (112) at the 5:00 o’clock position, aft looking forward, as follows:
a Try as possible to remove this hardware as a module package.
b Remove the two bolts (85) from fuel nozzle (14) No. 9 as specified in Para. 4.E and from the bracket (108).
c Remove the three bolts (85) from fuel nozzle (14) No. 8 as specified in Para. 4.E and from the bracket (110).
d Remove the bolt (100) from the loop clamp (98) and from the bracket (112).
e Remove the bolt (107) from the loop clamp (106) and from brackets (110) and (112).
f Remove the bolt (100) from the loop clamp (103) and from the bracket (110).
g Remove the bolt (113) from the loop clamp (105) and from brackets (110).
h Remove the module package of brackets (110), (108) and (112).
END OF POST SB 72-0211
(e) Loosen the module package: 4th and 7th stage air tube bracket (referred to as air tube bracket) (124), HPTACC drain support bracket (125) and bracket (114) at the 6:00 o’clock position, aft looking forward, as follows:
2 Remove the bolt (115) from the loop clamp (116) and from the bracket (114).
3 Remove the bolt (26) from the retaining strap (50) and from the air tube bracket (124).
4 Remove the bolt (72) from the loop clamp (46) and from the bracket (114).
5 Remove the bolt (123) from the retaining strap (37) and from the air tube bracket (124).
6 Remove the bolt (121) from the loop clamp (120) and from the air tube bracket (124).
7 Move away the module package from the fuel nozzle removal path.
(f) Remove the 7th stage air tube (127) located at the 6:00 o’clock position, aft looking forward, as follows:
2 Remove the bolts (130) from the 7th stage air duct (127).
3 Remove the 7th stage air retainers (129).
4 Discard the metal seal ring (128).
Subtask 73-11-30-680-051-A CAUTION:
WHEN YOU BREAK THE TORQUE FROM THE BOLTS IN THE CASES, BE CAREFUL NOT TO CAUSE DAMAGE TO OR BREAK THE INSERTS.
CAUTION:
PUT PLUGS OR CAPS ON THE OPEN HOLES OF ALL THE REMOVED TUBES, DUCTS AND MANIFOLDS. IF YOU DO NOT OBEY THIS INSTRUCTION, FOREIGN MATERIAL CAN GO INTO THEM AND CAUSE DAMAGE OR BLOCKAGE.
CAUTION:
MAKE SURE THAT:
- CAPS AND COVERS ARE INSTALLED IN ALL PORTS, OPENINGS AND MATING SURFACES, AND
- THE CASES ARE PROTECTED FROM POSSIBLE DAMAGE WHEN YOU MOVE THEM, OR FOREIGN OBJECT DAMAGE.
(1) If the bolts (85) get tight for removal, apply aero kroil penetrant (Material No.CP2691) as specified in Para. 4.B.(2) Remove the external components at the Right Hand (RH) side of the engine, aft looking forward, as follows:
(a) For PRE and POST SB 72-0190, do as follows:
1 Disconnect the HJ8A harness (1) from the start bleed valve (2) (Ref. AMM TASK 70-70-00-910-804).
NOTE: Only if necessary, PLIERS - JAWED, SOFT can be used to disconnect the HJ8A harness (1).
2 Disconnect the HJ8A harness (1) from the Transient Bleed Valve (TBV) (3) (Ref. AMM TASK 70-70-00-910-804). NOTE: Only if necessary, PLIERS - JAWED, SOFT can be used to disconnect the HJ8A harness (1).
END OF PRE AND POST SB 72-0190(b) Move the two HJ8A harness (1) away from the fuel nozzles removal path and hold them with TIE WRAP(S).
(c) For PRE and POST SB 72-0190, do as follows:
1 Remove the TBV (3) (Ref. AMM TASK 75-33-05-000-801) and do as follows:
a Discard all seals that are exposed.
2 Remove the start bleed valve (2) (Ref. AMM TASK 75-11-05-000-801) and do as follows:
a Discard all seals that are exposed.
END OF PRE AND POST SB 72-0190
(d) Remove the HP bleed valve (4) from the engine (Ref. AMM TASK 36-11-51-000-803).
1 Discard all seals that are exposed.
NOTE: Only if necessary, use the PLIERS - JAWED, SOFT to disconnect the electrical connector.
(e) For PRE SB 72-0190 configuration, remove the transient bleed air tube (10) as follows:1 After the first time you soaked the bolts (9), soak the bolts (9) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts before you remove them.
2 Remove the bolts (11) from the support bracket (12).
3 Remove the bolts (5) from the TBV support bracket (referred to as support bracket) (13).
4 Remove the four bolts (9) that attach the transient bleed air tube (10) to the combustion case (6).
5 Keep orifice plate (8) for future installation.
6 Discard the metal seal ring (7).
NOTE: For POST SB 72-0190, it is not required to remove the transient bleed air tube (10).
END OF PRE SB 72-0190(f) For PRE SB 72-0133 configuration, remove the support bracket (15) as follows:
1 After the first time you soaked the two bolts (16) and two nuts (17), soak the two bolts (16) and two nuts (17) again with aero kroil penetrant (Material No.CP2691) . Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Move the left T48 harness (19), the turbine center frame accelerometer (18) and the right T48 harness (22) as follows:
a Remove the two machine bolts (20) that attach the two loop clamps (21) from the right T48 harness (22) and the support bracket (15).
b Remove the two bolts (20) that attach the two loop clamps (21) from the left T48 left harness (19) and the support bracket (15).
c Remove the two bolts (20) that attach the two loop clamps (23) and the turbine center frame accelerometer (18) to the support bracket (15).
d Move the right T48 harness (22), the left T48 harness (19) and the turbine center frame accelerometer (18) away from the fuel nozzle removal path.
3 Remove the two bolts (16) and two nuts (17) and remove the support bracket (15).
END OF PRE SB 72-0133
(g) POST SB 72-0133
Remove the support bracket (15) as follows:
1 After the first time you soaked the two bolts (16) and two nuts (17), soak the two bolts (16) and the two nuts (17) again with aero kroil penetrant (Material No.CP2691) . Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Move the left T48 harness (19), the turbine center frame accelerometer (18) and the right T48 harness (22):
a Remove the two bolts (20) that attach the two loop clamps (21) and the left T48 harness (19) to the support bracket (15).
b Remove the two bolts (20) that attach the two loop clamps (23) and the turbine center frame accelerometer (18) to the support bracket (15).
c Remove the three bolts (20) that attach the three loop clamps (21) and the right T48 harness (22) to the support bracket (15).
d Move the right T48 harness (22), the left T48 harness (19) and the turbine center frame accelerometer (18) away from the fuel nozzle removal path.
3 Remove the two bolts (26) and retaining strap (25) that attach the support bracket (15) to the HPT cooling 7th stage air manifold (referred to as 7th stage air manifold) (24).
4 Remove the two bolts (16) and two nuts (17) and remove the support bracket (15).
END OF POST SB 72-0133
(h) PRE SB 72-0190
Remove the support brackets (31) and (13), bracket (39) and air duct bracket (33) (as a module package) from fuel nozzles (14) No. 1 and No. 2 and fuel nozzles (14) No. 3 and No. 4 as follows:
1 Try as possible to remove this hardware as a module package.
2 After the first time you soaked the bolts (30), soak again the bolts (30) from the combustion case (6) with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts before you remove them.
3 Remove the bolts (30) from the valve support bracket (31) and the combustion case (6).
4 Remove the bolts (29) from the loop clamps (28) that attach the right T48 harness (22), the left T48 harness (19) and the support bracket (13).
5 Remove the bolts (27) from the fuel hydraulics support bracket (38), the support bracket (13) and the bracket (39).
6 Remove the bolts (30) from the air duct bracket (33) and the combustion case (6).
7 Remove the bolts (32) from air duct bracket (33) and start bleed valve support bracket (34) and do as follows:
a Keep the hardware for future installation.
8 Remove the two bolts (35) from the retaining strap (37) that attach the 4th stage air manifold (36) and bracket (39) to the support bracket (13) and do as follows:
a Keep the hardware for future installation.
9 Remove the valve support bracket (31), support bracket (13) and bracket (39) and the air duct bracket (33) as a module package and do as follows:
a Keep the module package for future installation.
(i) Remove the start bleed leg air duct (45) and the support bracket (42), as a module package as follows:
1 Try as possible to remove the start bleed leg air duct (45) and the support bracket (42) as a module package.
2 Remove the four bolts (32) that attach the support bracket (42) to the start bleed valve support bracket (47) and to the start bleed valve support bracket (34).
3 Remove the two bolts (44) that attach the support leg bracket (49) to the start bleed valve support bracket (43) and the support bracket (42).
4 Remove the two bolts (26) that attach the retaining strap (50) and 7th stage air tube (51) to the support bracket (42).
5 Remove the start bleed leg air duct (45) and the support bracket (42) as a module package and do as follows:
a Keep the module package for future installation.
(j) Remove the bolts (40) from the fuel hydraulic support bracket (41) and the start bleed valve support bracket (34) and do as follows:
1 Keep the support bracket (41) installed on the engine.
(k) Remove the hardware that follow and the module package core compartment cooling bracket (52), start bleed valve support bracket (34) and drain support bracket (referred to as support bracket) (61) as follows:
1 Try as possible to remove this hardware as a module package.
NOTE: The best practice is to loosen all the smaller brackets for the free movement of the whole module package.
2 Remove the bolt (63) that attaches the loop clamp (60) to the drain tube (62) and start bleed valve support bracket (34).3 Remove the bolt (59) that attaches the loop clamp (60) to the drain tube (62) and support bracket (61).
4 Remove the bolt (58) that attaches the loop clamp (57) to the drain tube (62) and start bleed valve support bracket (34).
5 Remove the bolt (53) from the core compartment cooling bracket (52).
6 Remove the bolt (53) from the start bleed valve support bracket (34).
7 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (47).
8 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the air duct bracket (33).
9 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (43).
10 Remove the bolts (32) that attach the start bleed valve support bracket (34) to the start bleed valve support bracket (48).
11 Remove the bolts (65) from the support bracket (61).
12 Remove the bolts (40) from the start bleed valve support bracket (34).
13 Remove the bolt (56) from the start bleed valve support bracket (34).
14 Remove the module package: core compartment cooling bracket (52), start bleed valve support bracket (34) and support bracket (61) and do as follows:
a Keep the module package for future installation.
END OF PRE SB 72-0190
(l) POST SB 72-0190
Remove the start bleed valve support bracket (34) as follows:
1 Remove the two bolts (32) that attach the booster anti-ice air tube (75) to the start bleed valve support bracket (34).
2 Remove the two bolts (32) that attach the start bleed tube duct (70) to the start bleed valve support bracket (34).
3 Remove the two bolts (32) that attach the start bleed valve support bracket (34) to the air duct bracket (33).
4 Remove the four bolts (32) that attach the support bracket (42) to the start bleed valve support bracket (34).
5 Remove the bolt (68) that attaches the loop clamp (69) and the PS3 air tube (67) to the start bleed valve support bracket (34).
6 Remove the bolt (68) that attaches the loop clamp (69) and the PS3 air tube (67) to the support bracket (42).
7 Remove the bolt (59) that attaches the drain tube (62) to the start bleed valve support bracket (34).
8 Remove the two bolts (65) that attach the support bracket (66) to the start bleed valve support bracket (34):
a Keep the support bracket (66) attached to the drain tube (71) and the core control harness (74).
9 Remove the start bleed valve support bracket (34) from the engine.
(m) Remove the air duct bracket (33) as follows:
1 After the first time you soaked the bolts (76), soak the bolts (76) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts. Give the aero kroil penetrant (Material No.CP2691) time to soak into threads.
2 Remove the bolts (76) that attach the air duct bracket (33) to the combustion case (6).
3 Remove the air duct bracket (33).
END OF POST SB 72-0190
(n) PRE AND POST SB 72-0190
Disconnect the B-nut on the PS3 air tube (67) from the PS3 tube (77) at the fuel nozzle (14) No. 7.
END OF PRE AND POST SB 72-0190
(3) Remove the external components at the Left Hand (LH) side of the engine, aft looking forward:
(a) Remove the ECS air duct (79) from the engine case at the 6:00 o’clock position, aft looking forward and do as follows (Ref. AMM TASK 36-11-49-000-827):
1 After the first time you soaked the bolts (78), soak the bolts (78) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts. Give the aero kroil penetrant (Material No.CP2691) time to soak into threads and do as follows:
a Discard all seals that are exposed.
(b) Remove the High Pressure Turbine Active Clearance Control (HPTACC) valve (82) and the Low Pressure Turbine Active Clearance Control (LPTACC) valve (81) (Ref. AMM TASK 75-21-05-000-801) and (Ref. AMM TASK 75-22-05-000-801) and do as follows:
1 Remove the HPTACC valve (82), LPTACC valve (81), brackets and the flex ducts as a module package.
2 Discard all seals that are exposed.
(c) Remove Pressure Regulating and Shut-Off Valve (PRSOV) 1 (83) and the air duct (80) (Ref. AMM TASK 30-21-51-000-804) and do as follows:
1 Try as possible to remove this hardware as a module package PRSOV 1 (83) and its associated air duct (80):
a If not possible, remove the PRSOV 1 (83) first and then remove the associated air duct (80).
2 Discard all seals that are exposed.
(d) Remove the module package (support brackets (89) and (84)) at fuel nozzle (14) No. 16 as follows:
NOTE: The best practice is to loosen all the smaller brackets for the free movement of the whole module package.
1 Try as possible to remove this hardware as a module package. 2 For POST SB 72-0036 and PRE SB 72-0133 configurations, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (88) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) from the support brackets (87) and (89).
d Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0036 AND PRE SB 72-0133
3 For POST SB 72-0133 and PRE SB 72-0205 configurations, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (93) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) that attach the support brackets (87) and (89).
d Remove the bolt (92) that attaches the support brackets (91) and (89).
e Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0133 AND PRE SB 72-0205
4 For POST SB 72-0205 configuration, do as follows:
a Remove the two bolts (85) from fuel nozzle (14) No. 16 as specified in Para. 4.E.
b Remove the two bolts (93) that attach the block clamp (86) to the support bracket (89).
c Remove the two bolts (90) that attach support brackets (87) and (89).
d Remove the two bolts (96) and retaining strap (95) that attach the 4th stage air manifold (94) to the support brackets (91) and (89).
e Remove the support brackets (89) and (84) together and keep them for future installation.
END OF POST SB 72-0205
(4) Removal of the external components at the bottom of the engine (6:00 o’clock position), aft looking forward:
(a) PRE SB 72-0211
Remove all the hinged cushioned loop clamps that follow from the oil tubes support bracket (referred to as bracket) (97) that attach the oil supply/scavenge tubes (referred to as tubes) (104), (102), (101) and (99) at the 5:00 o’clock position, aft looking forward, as follows:
NOTE: This adds flexibility for the fuel nozzle removal and replacement.
1 Remove the bolt (100) from the loop clamp (105) and from the bracket (97). 2 Remove the bolt (100) from the loop clamp (103) and from the bracket (97).
3 Remove the bolts (100) from the loop clamps (98) and from the bracket (97).
END OF PRE SB 72-0211
(b) POST SB 72-0211
Remove all the loop clamps that follow from the bracket (97) that attach the tubes (104), (102), (101) and (99) at the 5:00 o’clock position, aft looking forward, as follows:
NOTE: This adds flexibility for the fuel nozzle (14) removal and replacement.
1 Remove the bolt (100) from the loop clamp (105) and from the bracket (97). 2 Remove the bolt (100) from the loop clamp (103) and from the bracket (97).
3 Remove the bolt (100) from the loop clamp (98) and from the bracket (97).
4 Remove the bolt (100) from the loop clamp (106) and from the bracket (97).
END OF POST SB 72-0211
(c) PRE SB 72-0211
Remove the module package: Bracket (110) and oil tubes support brackets (108) and (112) at the 5:00 o’clock position, aft looking forward, as follows:
1 Try as possible to remove this hardware as a module package.
2 Remove the two bolts (85) from fuel nozzle (14) No. 9 as specified in Para. 4.E and from the bracket (108).
3 Remove the three bolts (85) from fuel nozzle (14) No. 8 as specified in Para. 4.E and from the bracket (110).
4 Remove the bolt (107) from the loop clamp (109) and from the brackets (110) and (112).
5 Remove the bolt (100) from the loop clamp (103) and from the bracket (110).
6 Remove the bolt (100) from the loop clamp (98) and from the bracket (110).
7 Remove the bolt (107) from the cushioned loop clamp (111) and from brackets (110) and (112).
8 Remove the module package of brackets (110), (108) and (112).
END OF PRE SB 72-0211
(d) POST SB 72-0211
1 Remove the module package: Brackets (110), (108) and (112) at the 5:00 o’clock position, aft looking forward, as follows:
a Try as possible to remove this hardware as a module package.
b Remove the two bolts (85) from fuel nozzle (14) No. 9 as specified in Para. 4.E and from the bracket (108).
c Remove the three bolts (85) from fuel nozzle (14) No. 8 as specified in Para. 4.E and from the bracket (110).
d Remove the bolt (100) from the loop clamp (98) and from the bracket (112).
e Remove the bolt (107) from the loop clamp (106) and from brackets (110) and (112).
f Remove the bolt (100) from the loop clamp (103) and from the bracket (110).
g Remove the bolt (113) from the loop clamp (105) and from brackets (110).
h Remove the module package of brackets (110), (108) and (112).
END OF POST SB 72-0211
(e) Loosen the module package: 4th and 7th stage air tube bracket (referred to as air tube bracket) (124), HPTACC drain support bracket (125) and bracket (114) at the 6:00 o’clock position, aft looking forward, as follows:
NOTE: This adds flexibility for the fuel nozzle (14) No. 10 removal and replacement.
1 Remove the bolt (72) from the loop clamp (73) and from the bracket (125).2 Remove the bolt (115) from the loop clamp (116) and from the bracket (114).
3 Remove the bolt (26) from the retaining strap (50) and from the air tube bracket (124).
4 Remove the bolt (72) from the loop clamp (46) and from the bracket (114).
5 Remove the bolt (123) from the retaining strap (37) and from the air tube bracket (124).
6 Remove the bolt (121) from the loop clamp (120) and from the air tube bracket (124).
7 Move away the module package from the fuel nozzle removal path.
(f) Remove the 7th stage air tube (127) located at the 6:00 o’clock position, aft looking forward, as follows:
NOTE: This adds flexibility for the fuel nozzle removal and replacement.
1 After the first time you soaked the bolts (130), soak the bolts (130) again with aero kroil penetrant (Material No.CP2691) to prevent damage to the inserts before you remove the bolts (130). 2 Remove the bolts (130) from the 7th stage air duct (127).
3 Remove the 7th stage air retainers (129).
4 Discard the metal seal ring (128).
D. Drain the Fuel Manifolds
(1) Loosen the fuel manifold B-nuts (131) of the primary fuel manifold (134) and secondary fuel manifold (139) as follows:
(a) Put a CONTAINER 5 USGAL (19 L) - FUEL RESISTANT under the fuel nozzles (14) and fuel manifolds.
CP8006 safety cable 0.032 in. (0.8 mm)
(c) Loosen three of the fuel manifold B-nuts (131) at the bottom of the engine, 6:00 o’clock position, aft looking forward and do as follows:
1 Completely remove the fuel manifold B-nuts (131) from the fuel nozzle (14).
(d) Loosen one fuel manifold B-nut (131) at the top of the engine, 12:00 o’clock position, aft looking forward.
(e) Let all the fuel drain into the CONTAINER 5 USGAL (19 L) - FUEL RESISTANT.
(f) Loosen the remaining fuel manifold B-nuts (131) from the fuel nozzles (14).
Subtask 73-11-30-020-076-A (1) Loosen the fuel manifold B-nuts (131) of the primary fuel manifold (134) and secondary fuel manifold (139) as follows:
(a) Put a CONTAINER 5 USGAL (19 L) - FUEL RESISTANT under the fuel nozzles (14) and fuel manifolds.
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL SAFETYWIRE. EACH TIME YOU CUT SAFETYWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE SAFETYWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
WARNING:
USE GOGGLES WHEN YOU REMOVE OR INSTALL SAFETY CABLE. EACH TIME YOU CUT SAFETY CABLE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE SAFETY CABLE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
(b) Remove all the safetywire (Material No.CP8002) or (c) Loosen three of the fuel manifold B-nuts (131) at the bottom of the engine, 6:00 o’clock position, aft looking forward and do as follows:
1 Completely remove the fuel manifold B-nuts (131) from the fuel nozzle (14).
(d) Loosen one fuel manifold B-nut (131) at the top of the engine, 12:00 o’clock position, aft looking forward.
(e) Let all the fuel drain into the CONTAINER 5 USGAL (19 L) - FUEL RESISTANT.
(f) Loosen the remaining fuel manifold B-nuts (131) from the fuel nozzles (14).
NOTE: It is not necessary to remove the fuel manifold drain plugs.
CAUTION:
WHEN YOU HIT THE BOLTS, BE CAREFUL NOT TO CAUSE DAMAGE TO THE CASE OR THE ADJACENT COMPONENTS.
E. Removal of the Fuel Nozzle Bolts (1) After the first hour of soaking, shock the remaining bolts (85) bolt heads with a HAMMER - NON METALLIC and brass DRIFT - PUNCH as example.
NOTE: This shock can help to break loose any material buildup on bolt (85), shank, threads or bolt point.
(2) Remove the bolts (85), as follows: (a) Break the torque of the bolts (85) that you remove with half a turn counterclockwise.
(b) Apply aero kroil penetrant (Material No.CP2691) again to the bolts (85). Let application soak for another one hour.
CAUTION:
USE A RATCHET AND TURN THE BOLTS SLOWLY. DO NOT USE POWER TOOLS. IF YOU REMOVE THE BOLTS TOO QUICKLY, THE BOLTS CAN GET HOT AND SEIZE.
(c) After the second hour of soaking, start to remove the bolts (85). (d) If the bolts (85) become too tight, spray with aero kroil penetrant (Material No.CP2691) on the bolt shaft and in the bolt hole. Turn the bolts (85) CW for three revolutions. Apply aero kroil penetrant (Material No.CP2691) on the fuel nozzle bolt shaft and in the bolt hole again. Continue to loosen the bolts (85).
NOTE: If necessary, use a ratchet and turn the bolts (85) slowly. If you remove the bolts (85) too fast, they can get hot and seize.
(e) If the bolts (85) become too tight again, do Para. 4.E.(2) (d) again until you remove the bolts (85). (f) Remove all bolts (85).
CAUTION:
DO NOT USE THE BOLTS AGAIN. IF YOU DO NOT OBEY THIS INSTRUCTION, BOLT SEIZURE AND DAMAGE TO THE INSERTS CAN OCCUR DURING THE SUBSEQUENT REMOVAL.
(g) Discard the bolts (85). F. Removal of the Fuel Nozzles
(1) Correct sequence order to remove the fuel nozzles (14):
(a) Keep the brackets that are attached to the fuel nozzles (14) in position after the fuel nozzle (14) is removed from the engine. If necessary, loosen all bolts that attach any hardware from the bracket assembly (clamps, retaining straps, tube, duct or other bracket) to make the bracket flexible and help the bracket be moved away from the fuel nozzle removal path.
(b) If it is necessary to remove all support brackets that are attached to the fuel nozzle (14). Before you start to remove brackets and fuel nozzles (14), do a temporary position mark on the associated bracket to the associated fuel nozzle (14) position. Use the temporary marking (Material No.CP5061) .
(c) 1 You can work the left, right and bottom sides of engine in parallel as halves or thirds (dependent on manpower).
1 Half 1, RH side, aft looking forward includes fuel nozzles (14) No. 3, No. 2, No. 1, No. 4, No. 5, No. 7, No. 6, No. 8 and No. 9 removed at the 1:00 to 5:00 o’clock positions:
a Move the fuel nozzles (14) forward to disengage the swirl cup, then do as follows:
a Move fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
1 Third 1, LH side, aft looking forward includes the fuel nozzles (14) No. 17, No. 19, No. 18, No. 15 and No. 16 removed at the 9:00 to 12:00 o’clock positions:
a Move the fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
a Move the fuel nozzle (14) forward to disengage swirl cup, then do as follows:
a Move fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
(g) Get and discard all the 19 removed combustion chamber fuel nozzle seal assemblies (132).
(h) Record the serial number and the respective cup position of the removed fuel nozzles (14), engine time since new and cycles since new. Send the removed fuel nozzles (14) and these records to:
Advanced Atomization Technologies L.L.C.
Customer Support
7777 North Glen Harbor Blvd.
Glendale, AZ 85307
Phone: +1 (623) 872-6160
U.S.A.
(1) Correct sequence order to remove the fuel nozzles (14):
(a) Keep the brackets that are attached to the fuel nozzles (14) in position after the fuel nozzle (14) is removed from the engine. If necessary, loosen all bolts that attach any hardware from the bracket assembly (clamps, retaining straps, tube, duct or other bracket) to make the bracket flexible and help the bracket be moved away from the fuel nozzle removal path.
(b) If it is necessary to remove all support brackets that are attached to the fuel nozzle (14). Before you start to remove brackets and fuel nozzles (14), do a temporary position mark on the associated bracket to the associated fuel nozzle (14) position. Use the temporary marking (Material No.CP5061) .
(c) 1 You can work the left, right and bottom sides of engine in parallel as halves or thirds (dependent on manpower).
NOTE: The removal sequence is only for reference and can be changed for best achievement, such as a top-down removal sequence.
NOTE: A close coordination with fellow technicians is recommended on the intersection of the fuel nozzle removal paths.
(d) If removed in halves, remove fuel nozzles (14) as follows:1 Half 1, RH side, aft looking forward includes fuel nozzles (14) No. 3, No. 2, No. 1, No. 4, No. 5, No. 7, No. 6, No. 8 and No. 9 removed at the 1:00 to 5:00 o’clock positions:
a Move the fuel nozzles (14) forward to disengage the swirl cup, then do as follows:
- Fuel nozzle No. 3 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 2 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 1 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 4 - turn UP and rotate out of the case.
- Fuel nozzle No. 5 - turn UP and rotate out of the case.
- Fuel nozzle No. 7 - turn UP and rotate out of the case.
- Fuel nozzle No. 6 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 8 - turn UP and rotate out of the case.
- Fuel nozzle No. 9 - turn UP and rotate out of the case.
a Move fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
- Fuel nozzle No. 17 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 19 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 18 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 15 - turn UP and rotate out of the case.
- Fuel nozzle No. 16 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 10 - turn UP and rotate out of the case.
- Fuel nozzle No. 13 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 11 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 12 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 14 - turn LEFT and rotate out of the case.
1 Third 1, LH side, aft looking forward includes the fuel nozzles (14) No. 17, No. 19, No. 18, No. 15 and No. 16 removed at the 9:00 to 12:00 o’clock positions:
a Move the fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
- Fuel nozzle No. 17 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 19 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 18 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 15 - turn UP and rotate out of the case.
- Fuel nozzle No. 16 - turn DOWN and rotate out of the case.
a Move the fuel nozzle (14) forward to disengage swirl cup, then do as follows:
- Fuel nozzle No. 3 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 2 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 1 - turn RIGHT and rotate out of the case.
- Fuel nozzle No. 4 - turn UP and rotate out of the case.
- Fuel nozzle No. 5 - turn UP and rotate out of the case.
a Move fuel nozzle (14) forward to disengage the swirl cup, then do as follows:
- Fuel nozzle No. 7 - turn UP and rotate out of the case.
- Fuel nozzle No. 6 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 8 - turn UP and rotate out of the case.
- Fuel nozzle No. 9 - turn UP and rotate out of the case.
- Fuel nozzle No. 10 - turn UP and rotate out of the case.
- Fuel nozzle No. 13 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 11 - turn DOWN and rotate out of the case.
- Fuel nozzle No. 12 - turn LEFT and rotate out of the case.
- Fuel nozzle No. 14 - turn LEFT and rotate out of the case.
(g) Get and discard all the 19 removed combustion chamber fuel nozzle seal assemblies (132).
(h) Record the serial number and the respective cup position of the removed fuel nozzles (14), engine time since new and cycles since new. Send the removed fuel nozzles (14) and these records to:
Advanced Atomization Technologies L.L.C.
Customer Support
7777 North Glen Harbor Blvd.
Glendale, AZ 85307
Phone: +1 (623) 872-6160
U.S.A.