DOC AIRBUS | TSM A320FSmoke and/or Oil Smell in the Cabin Due to an Engine Leakage
1. Possible Causes
· de-oiler carbon seal
· LP turbine shaft blind cap seal
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
(98F10103500000) 1 CHOCK-MLG,ENGINE RUN-UP
B. Referenced Information
REFERENCE DESIGNATION
79-00-00-810-838-A Elevated Oil Consumption on Engine 1
79-00-00-810-839-A Elevated Oil Consumption on Engine 2
Ref. AMM 12-13-79-610-011 Check Oil Level and Replenish
Ref. AMM 21-00-00-615-001 Decontamination of the Environmental Control System (ECS) when the
Temperature is below 24 deg.C (APU)
Ref. AMM 21-00-00-615-002 Decontamination of the Environmental Control System (ECS) when the
Temperature is above 24 deg.C (APU)
Ref. AMM 21-00-00-615-003 Decontamination of the Environmental Control System (ECS) when the
Temperature is below 24 deg.C (Engine/s)
Ref. AMM 21-00-00-615-004 Decontamination of the Environmental Control System (ECS) when the
Temperature is above 24 deg.C (Engine/s)
Ref. AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power
Ref. AMM 71-00-00-710-018 Discontinued Start, Restart and Shutdown Procedures
Ref. AMM 71-00-00-710-043 Normal Engine Automatic Start Procedure
Ref. AMM 71-00-00-710-047 Normal Engine Manual Start Procedure
Ref. AMM 71-00-00-860-010 Engine Operation Limits, Guidelines and Special Procedures (Pre SB
79-0070)
Ref. AMM 71-00-00-860-011 Table of Idle Indications
Ref. AMM 71-00-00-860-012 Engine Safety Precautions
Ref. AMM 72-00-00-100-010 Clean the Engine Gas Path for Performance Improvement (Water only)
Ref. AMM 72-00-00-200-016 Inspection of the HP Compressor
REFERENCE DESIGNATION
Ref. AMM 72-00-00-200-017 Inspection of the LP Compressor
Ref. AMM 72-38-11-000-010 Removal of the Inlet Cone
Ref. AMM 72-38-11-400-010 Installation of the Inlet Cone
Ref. AMM 72-51-41-000-012 Removal of the Low Pressure (LP) Turbine Shaft Blind Cap
Ref. AMM 72-51-41-400-012 Installation of the Low Pressure (LP) Turbine Shaft Blind Cap
Ref. AMM 72-60-31-000-010 Removal of the Seal Assembly
Ref. AMM 72-60-31-400-010 Installation of the Seal Assembly
Smoke and/or Oil Smell in the Cabin Due to an Engine Leakage
Figure 71(IAE)-00-00-991-00300-A / SHEET 1/5 - Smoke and/or Oil Smell in the Cabin Due to an
Engine Leakage not printed, as per printing preferences
Figure 71(IAE)-00-00-991-00300-A / SHEET 2/5 - Smoke and/or Oil Smell in the Cabin Due to an
Engine Leakage not printed, as per printing preferences
Figure 71(IAE)-00-00-991-00300-A / SHEET 3/5 - Smoke and/or Oil Smell in the Cabin Due to an
Engine Leakage not printed, as per printing preferences
Figure 71(IAE)-00-00-991-00300-A / SHEET 4/5 - Smoke and/or Oil Smell in the Cabin Due to an
Engine Leakage not printed, as per printing preferences
Figure 71(IAE)-00-00-991-00300-A / SHEET 5/5 - Smoke and/or Oil Smell in the Cabin Due to an
Engine Leakage not printed, as per printing preferences
3. Fault Confirmation
Subtask 71-00-00-710-050-A
A. Identify if one of the engines is suspected to be the source of the oil smell in the cabin:
(Ref. Fig. Smoke and/or Oil Smell in the Cabin Due to an Engine Leakage)
NOTE: If the LH and RH packs are contaminated, the engine position cannot be identified easily by doing
an engine run. It can be better to do the decontamination of the Environmental Control System
(ECS) before an engine run Ref. AMM 21-00-00-615-001 or Ref. AMM 21-00-00-615-002 .
(1) If one of the engines is suspected to be the source of oil smell, continue to paragraph 4 (fault
isolation).
(2) If one of the engines is not suspected to be the source of oil smell/smoke, either:
(a) Do paragraph 4 (fault isolation) on both engines, or
(b) Continue to Para 3.C to do an engine run.
Subtask 71-00-00-710-083-A
B. Energize the aircraft electrical circuits
Ref. AMM 24-41-00-861-002 .
Subtask 71-00-00-710-084-A
C. Start the Engines
CAUTION: DURING GROUND RUNNING, CONCERN FOR FAN BLADE INTEGRITY PROHIBITS
STABILISED ENGINE OPERATION IN THE FOLLOWING SPEED RANGE:
- FOR PRE-SCN17/V A/C: DO NOT STABILISE THE ENGINE BETWEEN 61% TO 74%
N1 SPEED RANGE
- FOR POST-SCN17/V A/C: STABILISED OPERATION OF THE ENGINE BETWEEN APPROXIMATELY
60% TO 74% N1 SPEED RANGE (LIMITS ARE A FUNCTION OF OUTSIDE TEMPERATURE) WILL BE PROHIBITED BY THE EEC, AS THE SOFTWARE INCLUDES
THE KEEP-OUT-ZONE FOR ON-GROUND, STATIC OPERATION.
(1) Make sure that the CHOCK-MLG,ENGINE RUN-UP (98F10103500000) are in position in front of
each forward outboard MLG wheel.
NOTE: For general information refer to the engine safety precautions Ref. AMM 71-00-00-860-012
and engine operation limits, guidelines and special procedures Ref. AMM 71-00-00-860-010 .
(2) There must be two approved persons in the cockpit during an engine run. One person must monitor
the outside and the aircraft behaviour while the other person does the engine test.
(3) If the aircraft starts to move during the engine run, set all the thrust levers to idle position immediately.
NOTE: It is necessary in this test that the engine 1 and engine 2 run at the same time to give a thrust
balance on the aircraft.
NOTE: Make sure that both engine bleeds are selected OFF.
(4) Start both engines by the normal engine automatic start procedure Ref. AMM 71-00-00-710-043 or
the normal engine manual start procedure Ref. AMM 71-00-00-710-047 .
(5) Make sure that the indications of operations are in operational limits. Refer to Ref.
AMM 71-00-00-860-011 , if necessary.
Subtask 71-00-00-710-085-A
D. Engine Bleed Air Test
NOTE: It is recommended that during the test, sampling is done throughout the cabin and cockpit as the
smell may not be obvious in all areas.
NOTE: If available, an air analyser can be used.
(1) On the AIR control panel:
(a) Select ENG BLEED pushbutton switch of the tested engine ON and the ENG BLEED pushbutton
switch of the non-tested engine OFF.
(b) Select the APU BLEED pushbutton switch OFF.
(c) Select the CROSS BLEED pushbutton switch OFF.
(2) Do a check on the tested engine at idle for 10 minutes:
(a) Do a check of the cockpit/cabin air for oil smell.
(3) Move the thrust lever of the non-test engine slowly forward to equal 1.08 EPR.
(4) Increase the power of the test engine.
CAUTION: DURING GROUND RUNNING, CONCERN FOR FAN BLADE INTEGRITY PROHIBITS
STABILISED ENGINE OPERATION IN THE FOLLOWING SPEED RANGE:
- FOR PRE-SCN17/V A/C: DO NOT STABILISE THE ENGINE BETWEEN 61% TO
74% N1 SPEED RANGE
- FOR POST-SCN17/V A/C: STABILISED OPERATION OF THE ENGINE BETWEEN
APPROXIMATELY 60% TO 74% N1 SPEED RANGE (LIMITS ARE A FUNCTION
OF OUTSIDE TEMPERATURE) WILL BE PROHIBITED BY THE EEC, AS THE
SOFTWARE INCLUDES THE KEEP-OUT-ZONE FOR ON-GROUND, STATIC OPERATION.
(a) Increase the power of the test engine immediately and smoothly to 1.25 EPR (or the nearest
EPR necessary to make sure that the engine is at or above 75 percent N1) for three minutes to
let it become thermally stable:
1 Do a check of the cockpit/cabin for oil smell or smoke.
(5) Do a fast deceleration of the engine speed of the tested engine to MIN IDLE:
(a) Move the thrust lever rearwards immediately and smoothly to decrease the engine speed from
1.25 EPR to MIN IDLE.
(b) Do a check of the cockpit/cabin for oil smell or smoke.
(6) Do a quick acceleration of the test engine:
(a) Move the thrust lever forward immediately and smoothly to increase the engine speed from IDLE
to MAX CLIMB (CL) detent.
(b) Do a check of the cockpit/cabin for oil smell or smoke.
(7) Decrease the engine speed of the tested engine to MIN IDLE.
(8) Decrease the engine speed of the non-tested engine to MIN IDLE.
(9) Operate both engines at MIN IDLE for five minutes to let the engine cool.
(10) If the test confirms that the tested engine is the source of oil smell/smoke, continue with Para 4 (fault
isolation on the tested engine).
(11) If the test did not confirm that the tested engine is the source of the oil smell or smoke, do Para 3. D.
(1) to 3. D. (9) on the non-tested engine.
(12) Do a shutdown by doing the discontinued start, restart and shutdown procedure Ref.
AMM 71-00-00-710-018 .
(13) If the test of both engines did not confirm that the engine is the source of oil smell/smoke in the
cockpit/cabin, continue with Para 4.M.
4. Fault Isolation
Subtask 71-00-00-810-050-A
A. Do a check for elevated or high oil consumption on one of the engines:
(1) If the oil consumption is elevated or high, do (Ref. TSM 79-00-00-810-838) or
(Ref. TSM 79-00-00-810-839) and continue to Para 4. E.
(2) If the oil consumption is not elevated or high, continue to Para 4. B.
Subtask 71-00-00-810-086-A
B. Do a check of the oil servicing history to make sure that the engine is not over-serviced:
(1) If the engine is found over-serviced, adjust the oil level Ref. AMM 12-13-79-610-011 and continue to
Para 4. C.
(2) If the engine is not found over-serviced, continue to Para 4. C.
Subtask 71-00-00-810-087-A
C. Do an inspection of the de-oiler overboard vent:
(1) If there are signs of oil leakage, replace the de-oiler carbon seal Ref. AMM 72-60-31-000-010 and
Ref. AMM 72-60-31-400-010 and continue to Para 4. D.
(2) If there are no leaks, continue to Para 4. D.
Subtask 71-00-00-810-088-A
D. Do a visual inspection of the fuel lines, lubrication lines, pneumatic lines, fittings and accessories for leaks:
(1) If there are leaks, repair the leaks and continue to Para 4. E.
(2) If there are no leaks, continue to Para 4. E.
Subtask 71-00-00-810-089-A
E. Do a visual inspection of the fan module and fan blades for signs of oil leakage or contamination:
Subtask 71-00-00-810-090-A
F. Remove the inlet cone and visually examine the inner rim of the fan disc, stubshaft and Low Pressure (LP)
shaft for oil contamination Ref. AMM 72-38-11-000-010 :
(1) If there are signs of oil wetness or contamination:
(a) Replace the LP turbine shaft blind cap seal Ref. AMM 72-51-41-000-012 and Ref.
AMM 72-51-41-400-012 .
(b) Clean the affected areas and remove as much oil as possible.
(c) Install the inlet cone Ref. AMM 72-38-11-400-010 again.
(d) Continue to Para 4. G.
(2) If there are no signs of oil wetness or contamination, continue to Para 4. G.
Subtask 71-00-00-810-091-A
G. Examine the LP compressor IGV's and FEGV's for oil wetness or puddles at the 6'o clock position only:
(1) If there are signs of oil wetness or puddles, continue to Para 4. J.
(2) If there are no signs of oil wetness or puddles, continue to Para 4. H.
Subtask 71-00-00-810-092-A
H. Do a check if the oil leakage or contamination is identified and repaired in the steps that were done
before:
(1) If the oil leakage or contamination is identified and repaired in steps that were done before:
(a) Do a water wash of the engine to make sure that the gas path is clean Ref.
AMM 72-00-00-100-010 .
(b) Continue to Para 4. N.
(2) If the oil leakage or contamination is not identified and repaired in the steps that were done before,
continue to Para 4. J.
Subtask 71-00-00-810-093-A
J. Do a borescope inspection of the LP compressor stage 2.0, 2.3 and 2.5 vanes and 2.5 bleed port to find
signs of oil wetness or contamination Ref. AMM 72-00-00-200-017 :
(1) If there are signs of oil wetness only at LP compressor stage 2.5, do a check if the 2.5 bleed
mechanism was lubricated before the oil smell was identified:
(a) If the 2.5 bleed mechanism was lubricated before, do a water wash of the engine to make sure
that the gas path is clean Ref. AMM 72-00-00-100-010 and continue to Para 4. N.
(b) If the 2.5 bleed mechanism was not lubricated before, reject the engine.
(2) If there are signs of oil wetness or contamination not only on the LP compressor stage 2.5, reject the
engine.
(3) If there are no signs of oil wetness or contamination, continue to Para 4. K.
Subtask 71-00-00-810-094-A
K. Do a borescope inspection of the High Pressure (HP) compressor to find if there are signs of oil leakage
at the No.3 bearing rear seal. Do a check for signs of oil contamination at HP compressor stages 3 and 4
Ref. AMM 72-00-00-200-016 :
(1) If there are signs of oil wetness or contamination, reject the engine.
(2) If there are no signs of oil wetness or contamination. Continue to Para 4. L.
Subtask 71-00-00-810-095-A
L. Examine the HP compressor stage 7 bleed valve for oil wetness or contamination:
(1) If there are signs of oil wetness or contamination, reject the engine.
(2) If there are no signs of oil wetness or contamination. Continue to Para 4. M.
Subtask 71-00-00-810-096-A
M. Do an engine bleed air test (paragraph 3, fault confirmation) and do a check for oil smell or smoke if it was
not done before:
(1) If the engine test confirms that one of the engines is the source of oil smell, reject the engine.
(2) If the engine test does not confirm that one of the engines is the source of oil smell, continue to Para
4. N.
Subtask 71-00-00-810-097-A
N. Clean the Environmental Control System (ECS) Ref. AMM 21-00-00-615-003 or Ref.
AMM 21-00-00-615-004 and send the engine back to service. [Rev.6 from Feb 2017] 2026.04.04 04:35:00 UTC