General Visual Inspection of the Cascades and their attachments (Requires Full Deployment of Thrust Reverser) [IAE]

TASK 78-32-19-200-010-A
General Visual Inspection of the Cascades and their attachments (Requires Full Deployment of Thrust Reverser)

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL

1. Reason for the Job
Refer to the MPD TASK: 783200-I3
GENERAL VISUAL INSPECTION OF THE CASCADES AND THEIR ATTACHMENTS (REQUIRES FULL DEPLOYMENT OF THRUST REVERSER)
This task gives the data for a general check of the thrust reverser deflector boxes without component removal.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 2M (6 FT)
No specific	AR	LIGHT SOURCE - HEAT, SPARK-PROOF
No specific	AR	WARNING NOTICE(S)

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V01-002)	cleaning fluid
(Material No.V01-438)	solvent
(Material No.V02-099)	lint free cloth
(Material No.V08-149)	epoxy syntactic

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 71-13-00-010-010-A	Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-010-A	Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 78-30-00-040-012-A	Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-440-012-A	Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-31-00-710-041-A	Operational Test of the Thrust Reverser System with the CFDS
TASK 78-31-00-710-041-A-02	Operational test of the Thrust Reverser without the CFDS and Engine Running
TASK 78-32-00-860-010-A	Manual Extension of the Thrust Reverser Translating Sleeves
TASK 78-32-00-860-011-A	Manual Retraction of the Thrust Reverser Translating Sleeves
TASK 78-32-19-300-010-A	Repair the Cascade Assembly Surface Damage - VRS2251 (for corrective action)
TASK 78-32-19-300-011-A	Remove the Damaged Blade from the Cascade Panel Assembly - VRS2253 (for corrective action)
TASK 78-32-19-300-012-A	Stop Drill the Crack on the Cascade Assembly Fairing and Blank Cascade Panel Assembly - VRS2257 (for corrective action)
TASK 78-32-19-300-013-A	Repair the Blank Cascade Panel Assembly Surface Damage - VRS2254 (for corrective action)
SRM 54500001	(for corrective action)
Thrust Reverser Deflector Boxes
Inspection of the Lower Cascade and Cascade Fairing
Thrust Reverser Deflector Boxes
Composite Panel - Blank Cascades Damage Zones

3. Job Set-up
Subtask 78-32-19-941-051-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 78-32-19-010-052-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the fan cowls doors (Ref. AMM TASK 71-13-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put the ACCESS PLATFORM 2M (6 FT) into position.

Subtask 78-32-19-040-051-A ** ON A/C NOT FOR ALL

C. Deactivate the Thrust Reverser

WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012).

Subtask 78-32-19-980-050-A ** ON A/C NOT FOR ALL

D. Manually extend the translating sleeves (Ref. AMM TASK 78-32-00-860-010).

Subtask 78-32-19-110-050-A ** ON A/C NOT FOR ALL

E. Clean the Thrust Rerverser
(1) Clean the thrust reverser deflector boxes with a lint free cloth (Material No.V02-099) made moist with cleaning fluid (Material No.V01-002) .

4. Procedure
Subtask 78-32-19-210-051-A ** ON A/C NOT FOR ALL

A. Inspection of the Cascade Assemblies

Thrust Reverser Deflector Boxes ** ON A/C NOT FOR ALL

(1) Examine the cascade assembly vanes (Location 1).
(a) Surface damage.
1 Less than or equal to 0.02 in. (0.51 mm) deep and 0.75 in. (19.1 mm) in diameter, accept it.
2 Larger than 0.02 in. (0.51 mm) deep and 0.75 in. (19.1 mm) in diameter, repair it (Ref. AMM TASK 78-32-19-300-010).
(b) Crack/delamination.
1 Less than 1.00 in. (25.4 mm) in length, repair it (Ref. AMM TASK 78-32-19-300-010).
2 Larger than 1.00 in. (25.4 mm) in length, repair it (Ref. AMM TASK 78-32-19-300-011).
(2) Examine the mounting flange or side wall (Location 2).
(a) Surface damage.
1 Less than or equal to 0.050 in. (1.27 mm) deep and 1.00 in. (25.4 mm) in diameter, accept it.
2 Larger than 0.050 in. (1.27 mm) deep and 1.00 in. (25.4 mm) in diameter, repair it (Ref. AMM TASK 78-32-19-300-010).
(b) Crack/delamination.
1 Less than 0.050 in. (1.27 mm) in length and does not reduce fastener edge distance, repair it (Ref. AMM TASK 78-32-19-300-010).
2 Larger than 0.050 in. (1.27 mm) in length, reject it.
(c) Hole damage.
1 Less than 0.315 in. (8.0 mm) in diameter, repair it (Ref. AMM TASK 78-32-19-300-010).
2 Larger than 0.315 in. (8.0 mm) in diameter, reject it.
(3) Examine the cascade assembly titanium fairings.
(a) Surface damage.
1 Any size, accept it.
(b) Crack.
1 Less than 2.0 in. (50.8 mm) in length and no more than 4 cracks in each fairing, repair it (Ref. AMM TASK 78-32-19-300-012).
2 Larger than 2.0 in. (50.8 mm) in length, reject it.
(4) Examine the cascade assembly sidewall corners (Location 3).
(a) Surface damage.
1 Less than or equal to 0.050 in. (1.27 mm) deep and 1.00 in. (25.4 mm) in diameter, repair it (Ref. AMM TASK 78-32-19-300-013).
2 Larger than 0.050 in. (1.27 mm) deep and 1.00 in. (25.4 mm) in diameter, repair it (Ref. AMM TASK 78-32-19-300-010).
(5) Inspect the lower cascade and cascade fairing for loose or missing fasteners.
(a) If any fasteners are found loose or missing, replace all 13 fasteners as per SBN 78-0240.

Inspection of the Lower Cascade and Cascade Fairing ** ON A/C NOT FOR ALL

Subtask 78-32-19-210-052-A ** ON A/C NOT FOR ALL

B. Inspection of the Blank Cascades

Thrust Reverser Deflector Boxes ** ON A/C NOT FOR ALL

(1) Examine the Aluminum Alloy Blank Cascade Panel (Location 1 and 2).
(a) Surface damage.
1 Less than or equal to 0.02 in. (0.51 mm) deep and 1.00 in. (25.4 mm) in diameter. Repair, blend per SRM 54500001.
2 Larger than step 1_, reject and remove the blank cascade.
(b) Crack.
1 Less than 2.0 in. (50.8 mm) in length, remove the blank cascade and repair in shop per CMM.
2 Larger than step 1_, reject the blank cascade.
(2) Examine the Edges of the Aluminum Alloy Blank Cascade Panel (Location 4).
(a) Edge damage:
1 Less than or equal to 0.02 in. (0.51 mm) deep and 1.00 in. (25.4 mm) distance is maintained. Blend repair per SRM 54500001.
2 Larger than step 1_, reject the blank cascade.
(b) Crack.
1 Less than 0.13 in. (3.3 mm) in length and does not reduce fastener edge distance, repair it (Ref. AMM TASK 78-32-19-300-013).
2 Larger than 0.13 in. (3.3 mm) in length but less than 0.65 in. (16.5 mm) in length and does not reduce fastener edge distance, repair it (Ref. AMM TASK 78-32-19-300-012).
3 Larger than 0.65 in. (16.5 mm) in length, reject it.
(3) Examine the blank cascade fairing supports (Location 3).
(a) Surface damage.
1 Less than or equal to 0.01 in. (0.25 mm) deep and 0.50 in. (12.7 mm) in diameter, accept it.
2 Larger than 0.01 in. (0.25 mm) deep and 0.50 in. (12.7 mm) in diameter and does not reduce fastener edge distance, repair it (Ref. AMM TASK 78-32-19-300-013).
(b) Crack in flat gusset area.
1 Less than 0.10 in. (2.54 mm) in length and does not reduce fastener edge distance, repair it (Ref. AMM TASK 78-32-19-300-013).
2 Larger than 0.10 in. (2.54 mm) in length but less than 0.40 in. (10.16 mm) in length, repair it (Ref. AMM TASK 78-32-19-300-012).
3 Larger than 0.40 in. (10.16 mm) in length and any crack in bend radius areas reject it.

Subtask 78-32-19-210-053-A ** ON A/C NOT FOR ALL

C. Inspection of the Composite Blank Cascade

Composite Panel - Blank Cascades Damage Zones ** ON A/C NOT FOR ALL

(1) Examine the Composite Blank Cascade (Locations BC1, BC2, BC3, BC4 and BC5).
(a) Delamination/Disbond.
1 No delaminations or disbonds allowed.
(b) Crack(s).
1 No crack(s) allowed.
(c) Partial Penetration/Hole.
1 No penetration allowed.
(d) Full Penetration/Hole.
1 No penetration allowed.
(2) Examine the Composite Blank Cascade for Dents.
(a) Locations BC1, BC3 and BC5.
1 No dents allowed.
(b) Locations BC2 and BC4.
1 0.40 in. (10.2 mm) maximum diameter, 0.04 in. (1.0 mm) maximum depth.
2 Maximum 3 dents per panel surface. Dents must be separated from other damage by 10 in. (254 mm).
3 Inspect damage every aircraft 20 months, 6000 flight hours or 4500 flight cycles, whichever occurs first.
(3) Examine the Composite Blank Cascade for Nicks/Gouges.
(a) Locations BC1 and BC3.
1 No nicks/gouges allowed.
(b) Location BC5.
1 No nicks/gouges allowed.
2 Clean area with solvent (Material No.V01-438) . Fill damage with epoxy syntactic (Material No.V08-149) . Use an LIGHT SOURCE - HEAT, SPARK-PROOF. Cure at 125°F (51.7°C) for 5 hours.
3 Unlimited use.
4 No inspection interval required.
(c) Locations BC2 and BC4.
1 0.40 in. (10.2 mm) maximum length, 0.014 in. (0.356 mm) maximum depth.
2 Maximum 3 gouges per panel surface. Nicks and gouges must be separated from other damage by 10 in. (254 mm).
3 Unlimited use.
4 Inspect damage every aircraft 20 months, 6000 flight hours or 4500 flight cycles, whichever occurs first.
(4) Examine the Composite Blank Cascade for Scratches.
(a) Locations BC1 and BC3.
1 No scratches allowed.
(b) Locations BC2 and BC4.
1 0.005 in. (0.127 mm) maximum depth, 0.40 in. (10.2 mm) maximum length.
2 Unlimited use.
3 No delamination from face sheet.
4 Inspect damage every aircraft 20 months, 6000 flight hours or 4500 flight cycles, whichever occurs first.
(c) Location BC5.
1 No scratches allowed.
2 Clean area with solvent (Material No.V01-438) . Fill damage with epoxy syntactic (Material No.V08-149) . Use an LIGHT SOURCE - HEAT, SPARK-PROOF. Cure at 125°F (51.7°C) for 5 hours.
3 Unlimited use.
4 No inspection interval required.

5. Close-up
Subtask 78-32-19-980-051-A ** ON A/C NOT FOR ALL

A. Manually retract the translating sleeves (Ref. AMM TASK 78-32-00-860-011).

Subtask 78-32-19-440-051-A ** ON A/C NOT FOR ALL

B. Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012).

Subtask 78-32-19-410-052-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the fan cowls doors (Ref. AMM TASK 71-13-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

Subtask 78-32-19-710-051-A ** ON A/C NOT FOR ALL

D. Operational Test
(1) Do an operational test of the thrust reverser system (Ref. AMM TASK 78-31-00-710-041).

NOTE: As an alternative procedure, you can do the operational test without the CFDS (Ref. AMM TASK 78-31-00-710-041).

[Rev.10 from 2021] 2026.04.01 03:28:16 UTC