DOC AIRBUS | AMM A320FDetailed Visual Inspection of the Thrust Reverser [CFMI]
TASK 78-32-11-210-040-A
Detailed Visual Inspection of the Thrust Reverser
1. Reason for the Job
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 78-32-11-941-058-A ** ON A/C NOT FOR ALL
Subtask 78-32-11-210-054-A ** ON A/C NOT FOR ALL
Subtask 78-32-11-080-055-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 04:08:11 UTC
Detailed Visual Inspection of the Thrust Reverser
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | 1 | BRUSH - NON METALLIC |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 45 and 35 lbf.in (0.51 and 0.40 m.daN )  | |
| HIX3005 | 1 | SAFETY SLEEVE - PIVOTING DOOR ACTUATOR |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.CP2245) | finish paint EA4 blue 5991 |
| (Material No.CP2267) | RTV 106 |
| (Material No.CP2463) | RTV 560 |
| (Material No.CP2517) | aerodynamic tape |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 27-80-00-866-005-A | Retracting the Slats on the Ground |
| TASK 71-13-00-010-040-A | Opening of the Fan Cowl Doors |
| TASK 71-13-00-410-040-A | Closing of the Fan Cowl Doors |
| TASK 78-30-00-081-041-A | Make the Thrust Reverser Serviceable after Maintenance |
| TASK 78-30-00-481-041-A | Make the Thrust Reverser Unserviceable for Maintenance |
| TASK 78-32-11-000-040-A | Removal of the Left or Right Half Door of Thrust Reverser |
| TASK 78-32-11-000-041-A | Removal of the One or Eleven O'clock Strut and Strut Bushing |
| TASK 78-32-11-400-040-A | Installation of the Left or Right Half Door of Thrust Reverser |
| TASK 78-32-11-400-041-A | Installation of the One or Eleven O'clock Strut and Strut Bushing |
| TASK 78-32-41-080-040-A | Removal of the Safety Sleeve from Blocker Door Actuator |
| TASK 78-32-41-480-040-A | Installation of the Safety Sleeve on Blocker Door Actuator |
| TASK 78-32-41-860-040-A | Manual Deployment of the Blocker Door |
| TASK 78-32-41-860-041-A | Manual Stowing of the Blocker Door |
| TASK 78-36-00-010-040-A | Opening of the Thrust Reverser Doors |
| TASK 78-36-00-410-040-A | Closing of the Thrust Reverser Doors |
| SPM 706212 | |
Thrust ReverserSubtask 78-32-11-941-058-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
Subtask 78-32-11-869-056-A ** ON A/C NOT FOR ALL Subtask 78-32-11-010-065-A ** ON A/C NOT FOR ALL (1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
C. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.
Subtask 78-32-11-040-057-A ** ON A/C NOT FOR ALL (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put an ACCESS PLATFORM 1M(3 FT) in position.
D. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041).
4. ProcedureNOTE: Do not close the fan cowl doors.
Subtask 78-32-11-210-054-A ** ON A/C NOT FOR ALL
A. Visual Inspection
Subtask 78-32-11-010-066-A ** ON A/C NOT FOR ALL NOTE: Apply a witness line of finish paint EA4 blue 5991 (Material No.CP2245) on all nuts and connections when you have done the check of their torques.
(1) Do a visual inspection of the upper/lower cut corners, the 3/9 o'clock beams, the aft ring and the strut as follows: | INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inspect the upper/lower cut corners, the 3/9 o'clock beams and aft ring for: | | |
| A.Delamination | 1.5 in. (38.1 mm) maximum length 7.4 in. (188 mm) minimum separation, between other delaminations, holes or cracks. Five delaminations maximum per half door. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). It is recommended that all delaminations be repaired no later than airplane 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest). If the delamination is not allowable, replace the half door. |
| B.Abrasion | No carbon fiber damage allowed. | Seal surface damage (paint and surface resin only) with aerodynamic tape. Replace tape if peeled. Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| C.Crack | 1 in. (25.4 mm) maximum length in any direction. | Protect damaged area from entrance of moisture by application of appropriate sealing tape. |
| | 7.4 in. (188 mm) minimum separation, between other cracks, holes or delaminations. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| | Five cracks maximum per half door. | If the crack is not allowable, replace the half door. |
| D.Gouge | 0.008 in. (0.20 mm) maximum depth over a 8 in. (203.2 mm) length. | Protect damage from entrance of moisture by application of appropriate sealing tape. Replace tape if peeled or damaged. Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). If the gouges are not in the serviceable limits, replace the half door. |
| E.Hole | 1 in. (25.4 mm) maximum diameter | Protect damage area from entrance of moisture with sealing tape. |
| | 7.4 in. (188 mm) minimum separation, between other holes,cracks or delaminations. | Moisture at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| | Five holes maximum per half door. | If the hole is not allowable, replace the half door. |
| F.Nick, scratch | 0.008 in. (0.20 mm) maximum depth over a 8 in. (203.2 mm) length. | Protect damage from entrance of moisture with aerodynamic tape (Material No.CP2517) . Replace tape if peeled or damaged. Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). If the nick or scratch is not allowable, replace the half door. |
| 2.Inspect the internal area of the strut for: | | |
| A.Crack | None allowed. | If there is crack, replace the half door (Ref. AMM TASK 78-32-11-000-040) and (Ref. AMM TASK 78-32-11-400-040). |
B. Open the thrust reverser doors to the 45 degrees position (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 78-32-11-210-056-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
C. Do a visual inspection of the one and eleven o'clock struts as follows:
Subtask 78-32-11-980-052-A ** ON A/C NOT FOR ALL Subtask 78-32-11-480-053-A ** ON A/C NOT FOR ALL | INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inspect the strut for: | | |
| A.Crack or buckle on the part near the inner barrel | No damage is permitted | If there are cracks or buckles on the part near the inner barrel, replace the strut, |
| B.Movement: try to move the strut by hand | No movement is permitted | If there is displacement of the strut, replace the bushing or pin assembly (Ref. AMM TASK 78-32-11-000-041) and (Ref. AMM TASK 78-32-11-400-041). |
E. Install the HIX3005 SAFETY SLEEVE - PIVOTING DOOR ACTUATOR on the blocker door actuator (Ref. AMM TASK 78-32-41-480-040).
Subtask 78-32-11-210-055-A ** ON A/C NOT FOR ALL F. Do a visual inspection of the inner panels as follows:
Subtask 78-32-11-010-068-A ** ON A/C NOT FOR ALL | INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inspect the inner barrel for: | | |
| A.Delamination | 1.5 in. (38.1 mm) maximum length. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| | 7.4 in. (188 mm) minimum separation, between other delaminations, holes or cracks. | It is recommended that all delaminations be repaired no later than airplane 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest). |
| | Five delaminations maximum per half door. | If the delamination is not allowable, replace the half door. |
| B.Crack | 1 in. (25.4 mm) maximum length in any direction. | Protect damaged area from entrance of moisture with aerodynamic tape (Material No.CP2517) . |
| | 7.4 in. (188 mm) minimum separation, between other cracks, holes and delaminations. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| | Five cracks maximum per half door. | If the cracks are not in the serviceable limits, replace the half door (Ref. AMM TASK 78-32-11-000-040) and (Ref. AMM TASK 78-32-11-400-040). |
| C.Gouge, nick and scratch | 0.008 in. (0.20 mm) maximum depth over a 8 in. (203.2 mm) length. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). If gouges, nicks or scratches are not in the serviceable limits, replace the half door. |
| D.Hole | 1 in. (25.4 mm) maximum diameter | Protect damage area from entrance of moisture with aerodynamic tape (Material No.CP2517) . |
| | 7.4 in. (188 mm) minimum separation, between other holes, cracks and delaminations. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| | Five holes maximum per half door. | If the holes are not in the serviceable limits, replace the half door (Ref. AMM TASK 78-32-11-000-040) and (Ref. AMM TASK 78-32-11-400-040). |
| E.Corrosion | No limit | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). Do a new surface treatment at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest), SPM 706212. |
| 2.Inspect heat shields for: | | |
| A.Crack or hole | None permited | If there are cracks or holes, repair or replace before flight. Record location and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| B.Gouge, nick and scratch | 0.008 in. (0.2031 mm) maximum depth over an 8 in. (203.2 mm) length. | Record location and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| C.Missing or uncrimped rivets | Maximum of ten percent missing or uncrimped per row of rivets | Missing rivets must be separated by four good rivets. Missing end rivets not allowed. Record location and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| D.Bulges, gaps | | |
| (1)In exit heat shield trailing edge | 0.157 in. (4,0 mm) maximum bulges or gaps | Allowable if there is no crack or hole. If bulges or gaps are more than 0.157 in. (4,0 mm), monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest) or repair (Ref. |
| (2)Heatshield area other than trailing edge | Allowable if there is no crack or hole | Allowable if there is no crack or hole. |
| E.Heat coloration | | Allowable if there is no other damage. Record location and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| 3.Inspect heatshield pandown for: | | |
| A.Interference with aft engine mount | None allowed | Repair at next 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) (Ref SB RA32078-76). |
| 4.Inspect the thermal blanket outer foil (Configuration 2 only): | | |
| A.Any/all damage | No damage permitted | If the damage to the thermal blanket outer foil is less than 1.0 in. (25.4 mm) in diameter, (and the filler is not missing or wet), do |
| B.Security of attachment | No defect allowed | Replace damaged RTV 106 (Material No.CP2267) , and broken or loose rivets or safety wire. |
| | | |
| 5.Inspect intumescent fireproof coating for: | | |
| A.Abrasion | None allowed | If there is abrasion, repair before next flight per |
| B.Scratches | For 0.118 in. (3 mm) coating thickness, the scratch must not be greater than 0.06 in. (1.52 mm) maximum depth. For 0.177 in. (4.5 mm) coating thickness, the scratch must not be greater than 0.080 in. (2.0 mm) maximum depth. | Record location of repairs and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| C.Holes, peeling | None allowed | If there is hole or peeling repair before next flight per |
| | | Record location of repairs and monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). NOTE: For One thrust reverser half 15 repairs are allowed, and 3 repairs for an area of 140 in.2 (900 cm2). (For intumescent coating) |
| 6.Inspect attachment bracket for: | | |
| A.Crack and bend | No crack and/or bend allowed. | If there is crack or bend, replace the half door. |
| 7.Inspect drain tube for: | | |
| A.Distortion | None allowed | If there is distortion, replace before flight. |
| B.Crack | None allowed | If there is crack, replace before flight. |
| 8.Inspect ramp fairing kits for: | | |
| A.Crack | 1 in. (25.4 mm) maximum length in any direction. | Protect damaged area from entrance of moisture by application of appropriate sealing tape. |
| | 7.4 in. (188 mm) minimum separation, between other cracks, or holes. Five cracks maximum per half door. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). If the crack is not in the serviceable limits, replace the defective part. |
| B.Hole | 1 in. (25.4 mm) maximum diameter | Protect damage area from entrance of moisture by application of appropriate sealing tape. |
| | 7.4 in. (188 mm) minimum separation, between other holes or cracks. Five holes maximum . | Monitor at "A" check. If the hole is not in the serviceable limits, replace the defective part. |
| C.Gouge, nick and scratch | 0.008 in. (0.20 mm) maximum depth over a 8 in. (203.2 mm) length. | Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest). |
| 9.Inspect 12 o'clock rear fairing for : | | |
| A.Interference | None allowed | If any interference reshape 12 o'clock rear fairing per |
G. Removal of the Access Door.
(1) Remove the screws which attach the pivot access doors.
(2) Remove the access door.
(3) If necessary remove the bolts and the washer (lower blocker door) which attach the contact fingers on the blocker doors.
Subtask 78-32-11-210-057-A ** ON A/C NOT FOR ALL (1) Remove the screws which attach the pivot access doors.
(2) Remove the access door.
(3) If necessary remove the bolts and the washer (lower blocker door) which attach the contact fingers on the blocker doors.
H. Do a visual inspection of the pivot bolts and the adjacent structure as follows:
Subtask 78-32-11-410-064-A ** ON A/C NOT FOR ALL | INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inspect the pivot bolt for: | | |
| A.Damage | None allowed | If you find some damage or missing, replace the defective part. |
| 2.Inspect the pivot bolt adjacent structure for: | | |
| A.Crack | None allowed | If there is crack, replace the half door. |
I. Installation of the Contact Fingers, the Bolts and the Washer
(1) Install contact fingers, washer (lower blocker door) and bolts.
(2) TORQUE the bolts to between 45 and 35 lbf.in (0.51 and 0.40 m.daN ).
(3) Install the pivot access doors on the blocker doors and attach with screws.
(4) TORQUE screws to between 45 and 35 lbf.in (0.51 and 0.40 m.daN ).
5. Close-up(1) Install contact fingers, washer (lower blocker door) and bolts.
(2) TORQUE the bolts to between 45 and 35 lbf.in (0.51 and 0.40 m.daN )
. (3) Install the pivot access doors on the blocker doors and attach with screws.
(4) TORQUE screws to between 45 and 35 lbf.in (0.51 and 0.40 m.daN )
. Subtask 78-32-11-080-055-A ** ON A/C NOT FOR ALL
A. Remove the safety sleeve (HIX 3005) from the blocker door actuator (Ref. AMM TASK 78-32-41-080-040).
Subtask 78-32-11-980-053-A ** ON A/C NOT FOR ALL B. Bring the Blocker Doors:
Subtask 78-32-11-410-065-A ** ON A/C NOT FOR ALL CAUTION:
BLOCKER DOOR LATCH MUST BE OPENED WHEN YOU CLOSE THE BLOCKER DOOR OR DAMAGE CAN OCCUR.
(1) Bring the blocker doors to stow position manually (Ref. AMM TASK 78-32-41-860-041). C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 78-32-11-440-055-A ** ON A/C NOT FOR ALL Subtask 78-32-11-410-066-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR