W DOC AIRBUS | AMM A320F

Inspection/Check of the Turbine Frame Assembly [CFMI]

TASK 72-56-00-210-001-A
Inspection/Check of the Turbine Frame Assembly

FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL
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)-ADJUSTABLE
No specific
AR
WARNING NOTICE(S)
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR, 461AL, 462AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR
 C. Referenced Information
REFERENCE
DESIGNATION
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 72-00-00-200-005-A
Over-Serviceable-Limit Extensions
TASK 72-56-00-000-003-A
Removal of the Flame Arrestor and of the Flange Assembly
TASK 72-56-00-300-001-A
Replacement of Defective Studs
TASK 72-56-00-400-003-A
Installation of the Flame Arrestor and of the Flange Assembly
TASK 78-11-11-000-040-A
Removal of the Core Nozzle Assembly
TASK 78-11-11-400-040-A
Installation of the Core Nozzle Assembly
TASK 78-11-12-000-040-A
Removal of the Centerbody
TASK 78-11-12-400-040-A
Installation of the Centerbody
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 78-36-00-010-040-A
Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-A
Closing of the Thrust Reverser Doors
SPM 703223
F Turbine Frame Struts
F Inspection of Flange Assembly
3. Job Set-up
Subtask 72-56-00-860-055-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) Make sure that the core nozzle is removed (Ref. AMM TASK 78-11-11-000-040).
   (2) Make sure that the centerbody is removed (Ref. AMM TASK 78-11-12-000-040).
Subtask 72-56-00-941-050-A ** ON A/C NOT FOR ALL
B. 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 72-56-00-010-050-A ** ON A/C NOT FOR ALL
C. Get Access
   (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
   (2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
   (3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
   (4) Put the ACCESS PLATFORM 1M (3 FT)-ADJUSTABLE in position.
Subtask 72-56-00-040-050-A ** ON A/C NOT FOR ALL
D. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041).
Subtask 72-56-00-010-052-A ** ON A/C NOT FOR ALL
E. Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040):
   (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
   (2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
4. Procedure
Subtask 72-56-00-210-050-A ** ON A/C NOT FOR ALL
A. Visual Inspection of the Turbine Frame Assembly.
F Turbine Frame Struts ** ON A/C NOT FOR ALL
F Inspection of Flange Assembly ** ON A/C NOT FOR ALL
INSPECT/CHECK
MAXIMUM SERVICEABLE LIMITS
REMARKS
1.Forward and aft outer flanges for:


  • Cracks connecting bolt holes
Not serviceable

  • Cracks extending from bolt holes to outer edge of flange
One crack, 0.20 in. (5 mm) max. per hole with a minimum 5-hole separation between cracks
  • Cracks extending from bolt holes toward casing skin
Five cracks, 0.20 in. (5 mm) max. per flange with a minimum 10-hole separation between cracks. Axial cracks only

  • Cracks in other areas of flange
Five cracks per flange, 020 in. (5 mm) long with a minimum 5 in. (127 mm) separation between any other cracks

  • Nicks, scores and scratches
Five per flange, 1 in. (25.4 mm) long, 0.01 in. (0.25 mm) deep after removal of high metal with a minimum 1 in. (25.4 mm) separation

2.Engine mounting lug areas, airframe attach points only for: (struts 1,3,14)
If in doubt about defect, do a fluorescent penetrant inspection per SPM 703223
Struts 1,3 and 14:
If crack more than 0.2 in. (5.1 mm), remove within 50 cycles

  • Cracks out of bolt holes
Not serviceable

  • Cracks in other case mounting lug areas
Not serviceable

  • Nicks, scores and scratches
Any number, 1 in. (25.4 mm) long, 0.02 in. (0.5 mm) deep after removal of high metal with a minimum 1 in. (25.4 mm) separation

  • Porosities
Any amount

3.Cracks in outer casing skin area connecting with struts excepted mounting lug area
F Turbine Frame Struts ** ON A/C NOT FOR ALL
detail D.
If in doubt about defect, do a fluorescent penetrant inspection per SPM 703223.
Cumulative crack length
  • Struts 5 to 12 (maximum 3 non-consecutive struts)
    Less than 4 in. (101.6 mm): inspect every 1600 cycles
    More than 4 in. but less than 6 in. (152.4 mm): inspect every 400 cycles
    More than 6 in. (152.4 mm): not serviceable
  • Struts 2,4,13,15,16 (maximum 1 strut)
    Less than 2 in. (50.8 mm): inspect every 1600 cycles
    More than 2 in. but less than 3 in. (76.2 mm): inspect every 400 cycles
    More than 3 in. (76.2 mm): not serviceable
See overserviceable limits max. extension (Ref. AMM TASK 72-00-00-200-005)
4.All other areas of outer casing skin for:


  • Cracks
Not serviceable
  • Nicks, scores and scratches.
Any number, 1 in. (25.4 mm) long, 0.03 in. (0.75 mm) deep after removal of high metal and 1 in. (25.4 mm) minimum apart

  • Cracks in weld bead junction of the cover plate on the outer case at eleven and one o'clock positions.
With a maximum of one crack in each weld bead, 3.9 in. (100 mm) cumulative length serviceable.

5.Oil supply and scavenge tubes for:


  • Cracks
Not serviceable

  • Nicks, scratches
Any number, 0.01 in. (0.25 mm) deep after removal of high metal

  • Dents
Two per tube, smooth contour, 0.05 in. (1.27 mm) deep

  • Oil marks
Any amount

6.Struts for:


  • Cracks
Not serviceable

  • Nicks, scores and scratches.
Any number, any length, 0.02 in. (0.5 mm) deep after removal of high metal

  • Dents
Any number, smooth contour, 0.02 in. (0.50 mm) deep

  • Broken stud or damaged threads
Three (3) maximum:
  • If not adjacent to each other: 500hrs/500cycles
  • If two (2) non-serviceable studs are adjacent, but the third one is separated from them by two (2) serviceable studs: 500hrs/500cycles
Replace stud (Ref. AMM TASK 72-56-00-300-001) within 500 hours/500 cycles
7.No. 7 and No. 10 struts (oil supply and scavenge tubes) bulkheads for:


  • Cracks in the bulkhead wall
Two cracks, any length on each bulkhead

  • Cracks from the bulkhead, extending in the outer hub skin
Not serviceable

8.Sump flooding boss area for:


  • Cracks in the hub
Two cracks, no longer than 1 in. (25.4 mm) and 1 in. (25.4 mm) apart, minimum

Flame arrestor for:


  • Cracks in all areas including the retaining metal strip
Any number

  • Missing retaining strips
Serviceable, if one strip remains

  • Honeycomb grid plug for clogging
Any area up to 50 percent of clogging
  • Honeycomb missing
Not serviceable
Replace the flame arrestor within the next 10 cycles (Ref. AMM TASK 72-56-00-000-003) (Ref. AMM TASK 72-56-00-400-003)
9.Thermal insulation blankets


  • Missing or protuding blanket in the flowpath
Not serviceable
Install a new blanket. See overserviceable limit extension (Ref. AMM TASK 72-00-00-200-005).
10.Guide bushing for the oil supply tube for:


  • Worn area
No more than 0.06 in. (1.52 mm)

  • Flush with the LPT bore
Not serviceable
600 cycles or 750 hours max. serviceable extension is allowed with less than 0.06 in. (1.52 mm). 25 cycles or 50 hours max. serviceable extension is allowed with more than 0.06 in. (1.52 mm)
11.Flange assembly for:

  • Dent
Any amount if the ratio of the depth of the dent over the minimal length of the dent is 10% or less

5. Close-up
Subtask 72-56-00-410-050-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the centerbody (Ref. AMM TASK 78-11-12-400-040).
   (3) Install the core nozzle (Ref. AMM TASK 78-11-11-400-040).
   (4) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
     (a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
     (b) FOR [1000EM1] (ENGINE-1)
461AL 462AR
Subtask 72-56-00-440-050-A ** ON A/C NOT FOR ALL
B. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).
Subtask 72-56-00-410-052-A ** ON A/C NOT FOR ALL
C. Close Access
   (1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
   (2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
   (3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
   (4) Remove the access platform(s).
   (5) Remove the WARNING NOTICE(S).
[Rev.10 from 2021] 2026.04.01 02:40:01 UTC
"Aviabrain" 2025