2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
** ON A/C FSN ALL
TASK 27-44-00-040-801-A
Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Electrical Motor
Personnel Required.
Minimum Number of Person 1
Manhours 0.5
Elapsed Time 0.5
WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE IN POS
ITION BEFORE YOU START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR
CAN CAUSE DAMAGE TO THE EQUIPMENT.
1. Reason for the Job
MMEL 27-40-02A
STABILIZER ACTUATOR ELECTRIC MOTOR
MMEL 27-40-02B
STABILIZER ACTUATOR ELECTRIC MOTOR
This procedure is applicable for the deactivation of the Trimmable Horizontal-Stabilizer (THS) actua
tor electrical motor and for trouble shooting.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
QT
REFERENCE DESIGNATION
Y
No specific AR SAFETY CLIP - CIRCUIT BREAKER
B. Work Zones and Access Panels
ZONE/ACCESS ZONE DESCRIPTION
120 AVIONICS COMPARTMENT
311 REAR FUSELAGE SECTION
312 REAR FUSELAGE SECTION
C. Referenced Information
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
REFERENCE DESIGNATION
Ref. 24-41-00-861-801-A Energize the Aircraft Electrical Circuits from the External Po
wer A
Ref. 24-41-00-861-801-A01 Energize the Aircraft Electrical Circuits from the APU (APU St
arted with APU BAT)
Ref. 24-41-00-861-801-A03 Energize the Aircraft Electrical Circuits from the External Po
wer A and B
Ref. 24-41-00-861-801-A04 Energize the Aircraft Electrical Circuits from the APU (APU st
arted with External power A)
Ref. 24-41-00-861-801-A05 Energize the Aircraft Electrical Circuits from the External Po
wer B
Ref. 24-41-00-862-801-A De-energize the Aircraft Electrical Circuits from the External
Power A
Ref. 24-41-00-862-801-A01 De-energize the Aircraft Electrical Circuits from the APU
Ref. 24-41-00-862-801-A03 De-energize the Aircraft Electrical Circuits from the External
Power A and B
Ref. 24-41-00-862-801-A04 De-energize the Aircraft Electrical Circuits from the External
Power B
Ref. 27-44-51-210-805-A Detailed Inspection of THSA Ballscrew Assy for Integrity of P
rimary and Secondary Load Path and Check the Gap at Seco
ndary Nut Trunnion
Ref. 27-96-00-740-801-A BITE Test of the Electrical Flight Control System (EFCS) (GN
D SCANNING)
Ref. 29-00-00-863-801-A01 Pressurize the Green Hydraulic System with the Electric Pum
p
Ref. 29-00-00-863-802-A01 Pressurize the Blue Hydraulic System with the Electric Pump
Ref. 29-00-00-863-803-A01 Pressurize the Yellow Hydraulic System with the Electric Pu
mp
Ref. 29-00-00-864-801-A01 Depressurize the Green Hydraulic System (Pressurized with
the Electric Pump)
Ref. 29-00-00-864-802-A01 Depressurize the Blue Hydraulic System (Pressurized with th
e Electric Pump)
Ref. 29-00-00-864-803-A01 Depressurize the Yellow Hydraulic System (Pressurized with
the Electric Pump)
Ref. 29-00-00-864-804-A Put the Related Hydraulic System in the Depressurized Confi
guration before Maintenance Action
Ref. 31-60-00-860-801-A EIS Start Procedure
Ref. 31-60-00-860-802-A EIS Stop Procedure
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
REFERENCE DESIGNATION
Ref. 34-10-00-860-802-A IR Alignment Procedure
3. Job Set-up
SUBTASK 27-44-00-860-059-A
A. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
Ref. AMM TASK 24-41-00-861-801.
(2) Do the Electronic Instrument System (EIS) start procedure for the EWD and SD only
Ref. AMM TASK 31-60-00-860-801.
(3) Do the IR alignment procedure Ref. AMM TASK 34-10-00-860-802.
(4) Make sure that the hydraulic systems are depressurized
Ref. AMM TASK 29-00-00-864-804.
(5) On the overhead panel, on the FLT CTL section of panel 241VU, make sure that the P
RIM 1 and SEC 1 pushbutton switches are pushed (the OFF and FAULT legends of thes
e pushbutton switches are off).
(6) On the overhead panel, on the FLT CTL section of panel 212VU, make sure that the P
RIM 2, PRIM 3 and SEC 2 pushbutton switches are pushed (the OFF and FAULT legend
s of these pushbutton switches are off).
4. Procedure
SUBTASK 27-44-00-860-066-C
A. Get access to the avionics compartment. Then open, safety and tag this(these) circuit break
er(s):
(1) To deactivate THS electrical motor 1, open circuit breaker 5CS1.
(2) To deactivate THS electrical motor 2, open circuit breaker 5CS2.
(3) To deactivate THS electrical motor 3, open circuit breaker 5CS3.
SUBTASK 27-44-00-040-051-D
B. Deactivation of the THS-Actuator Electrical Motor
WARNING: MAKE SURE THAT THE TRAVEL RANGE OF THE RUDDER IS CLEAR AND
PREVENT ACCESS TO THE AREA WITH SAFETY BARRIERS.
MOVEMENT OF THE RUDDER CAN CAUSE INJURY AND/OR DAMAGE.
(1) Deactivation electrical motor 1 of the THS-actuator:
(a) Pressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-863-801, Ref. AMM TASK 29-00-00-863-802 and Ref.
AMM TASK 29-00-00-863-803.
NOTE: The F/CTL PRIM 1 PITCH FAULT caution is shown.
(b) On the ECAM control panel, push the F/CTL key (on the SD, the F/CTL page co
mes into view).
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
(c) On the EWD, make sure that the F/CTL PRIM 1 PITCH FAULT cautions is shown.
(d) On the overhead panel, on the FLT CTL section of panel 241VU, release the PRI
M 1 pushbutton switch (the OFF legend comes on).
(e) On the center pedestal, move the pitch trim control wheels to the fully UP posit
ion.
(f) On the overhead panel, on the FLT CTL section of panel 241VU, push the PRIM
1 pushbutton switch (the OFF legend goes off).
(g) On the center pedestal, make sure that the pitch trim control wheels do not mo
ve.
(h) On the overhead panel, on the FLT CTL section of panel 212VU, release the PRI
M 2 and PRIM 3 pushbutton switches (the OFF and FAULT legends of these pus
hbutton switches are on).
(i) On the EWD, make sure that the F/CTL STAB CTL FAULT caution comes on.
(j) Do the BITE test of the EFCS (GND SCANNING) Ref. AMM TASK 27-96-00-740-
801.
(k) Make sure that this maintenance message is shown:
- FCPC1 (2CE1)/ WRG/THS ACTR CIRCUIT BREAKER TO FCPC 1, when the
circuit breaker for THS-actuator motor 1 is open.
(l) On the overhead panel, on the FLT CTL section of panel 212VU, push the PRIM
2 and PRIM 3 pushbutton switches (the OFF legends go off).
(m) On the center pedestal, the pitch trim control wheels automatically move back
to the 4°UP position.
(n) Depressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-864-801, Ref. AMM TASK 29-00-00-864-802 and Ref.
AMM TASK 29-00-00-864-803.
(o) Do the inspection of the ballscrew assy for integrity of the primary and seconda
ry load paths Ref. AMM TASK 27-44-51-210-805.
NOTE: This step is applicable only if these displays were shown together:
- The ECAM caution PRIM 1 PITCH FAULT
- The class 1 maintenance message PITCH TRIM ACTR (1CS).
(p) Make an entry in the aircraft technical logbook.
(2) Deactivate electrical motor 2 of the THS-actuator:
(a) Pressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-863-801, Ref. AMM TASK 29-00-00-863-802 and Ref.
AMM TASK 29-00-00-863-803.
NOTE: The F/CTL PRIM 2 PITCH FAULT caution is shown.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
(b) On the ECAM control panel, push the F/CTL key (on the SD, the F/CTL page co
mes into view).
(c) On the EWD, make sure that the F/CTL PRIM 2 PITCH FAULT cautions is shown.
(d) On the overhead panel, on the FLT CTL section of panel 212VU, release the PRI
M 2 pushbutton switch (the OFF legend comes on).
(e) On the center pedestal, move the pitch trim control wheels to the fully UP posit
ion.
(f) On the overhead panel, on the FLT CTL section of panel 212VU, push the PRIM
2 pushbutton switch (the OFF legend goes off).
(g) On the center pedestal, make sure that the pitch trim control wheels do not mo
ve.
(h) On the overhead panel, on the FLT CTL section of:
- Panel 241VU, release the PRIM 1 pushbutton switch.
- Panel 212VU, release the PRIM 3 pushbutton switch.
NOTE: The OFF and FAULT legends of these pushbutton switches are on.
(i) On the EWD, make sure that the F/CTL STAB CTL FAULT caution comes on.
(j) Do the BITE test of the EFCS (GND SCANNING) Ref. AMM TASK 27-96-00-740-
801.
(k) Make sure that this maintenance message is shown:
- THS ELEK MDL(1CS)/FCPC2 (2CE2)/RLY(6CS2/23CS2), when the circuit
breakers for THS-actuator motor 2 are open.
(l) On the overhead panel, on the FLT CTL section of:
- Panel 241VU, push the PRIM 1 pushbutton switch.
- Panel 212VU, push the PRIM 3 pushbutton switch.
NOTE: The OFF legend of this pushbutton switches go off.
(m) On the center pedestal, the pitch trim control wheels automatically move back
to the 4°UP position.
(n) Depressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-864-801, Ref. AMM TASK 29-00-00-864-802 and Ref.
AMM TASK 29-00-00-864-803.
(o) Do the inspection of the ballscrew assy for integrity of the primary and seconda
ry load paths Ref. AMM TASK 27-44-51-210-805.
NOTE: This step is applicable only if these displays were shown together:
- The ECAM caution PRIM 2 PITCH FAULT
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
- The class 1 maintenance message PITCH TRIM ACTR (1CS).
(p) Make an entry in the aircraft technical logbook.
(3) Deactivate electrical motor 3 of the THS-actuator:
(a) Pressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-863-801, Ref. AMM TASK 29-00-00-863-802 and Ref.
AMM TASK 29-00-00-863-803.
NOTE: The F/CTL PRIM 3 PITCH FAULT caution is shown.
(b) On the ECAM control panel, push the F/CTL key (on the SD, the F/CTL page co
mes into view).
(c) On the EWD, make sure that the F/CTL PRIM 3 PITCH FAULT cautions is shown.
(d) On the overhead panel, on the FLT CTL section of panel 212VU, release the PRI
M 3 pushbutton switch (the OFF legend comes on).
(e) On the center pedestal, move the pitch trim control wheels to the fully UP posit
ion.
(f) On the overhead panel, on the FLT CTL section of panel 212VU, push the PRIM
3 pushbutton switch (the OFF legend goes off).
(g) On the center pedestal, make sure that the pitch trim control wheels do not mo
ve.
(h) On the overhead panel, on the FLT CTL section of:
- Panel 241VU, release the PRIM 1 pushbutton switch.
- Panel 212VU, release the PRIM 2 pushbutton switch.
NOTE: The OFF and FAULT legends of these pushbutton switches are on.
(i) On the EWD, make sure that the F/CTL STAB CTL FAULT caution comes on.
(j) Do the BITE test of the EFCS (GND SCANNING) Ref. AMM TASK 27-96-00-740-
801.
(k) Make sure that this maintenance message is shown:
- THS ELEK MDL(1CS)/FCPC3 (2CE3)/RLY(6CS3/23CS3), when the circuit
breaker for THS-actuator motor 3 is open.
(l) On the overhead panel, on the FLT CTL section of:
- Panel 241VU, push the PRIM 1 pushbutton switch.
- Panel 212VU, push the PRIM 2 pushbutton switch.
NOTE: The OFF legend of this pushbutton switches go off.
(m) On the center pedestal, the pitch trim control wheels automatically move back
to the 4°UP position.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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2/17/24, 7:21 AM XAX - A330 - AMM - 01-Jan-2024 - 27-44-00-040-801-A - Deactivation of the Trimmable Horizontal Stabilizer (THS)-Actuator Elect…
AIRCRAFT REVISION REVISION
CUSTOMIZATION DOCTYPES TITLE
TYPES DATE NUMBER
27-44-00-040-801-A - Deactivation of the Trimmable
XAX A330 A340 AMM 01-Jan-2024 65
Horizontal Stabilizer (THS)-Actuator Electrical Motor
TAIL NUMBER - MSN - FSN:
Print date: 2024-02-17 00:21:01
(n) Depressurize the aircraft hydraulic systems
Ref. AMM TASK 29-00-00-864-801, Ref. AMM TASK 29-00-00-864-802 and Ref.
AMM TASK 29-00-00-864-803.
(o) Do the inspection of the ballscrew assy for integrity of the primary and seconda
ry load paths Ref. AMM TASK 27-44-51-210-805.
NOTE: This step is applicable only if these displays were shown together:
- The ECAM caution PRIM 3 PITCH FAULT
- The class 1 maintenance message PITCH TRIM ACTR (1CS).
(p) Make an entry in the aircraft technical logbook.
SUBTASK 27-44-00-869-051-A
C. Cockpit Effects
(1) With THS electrical motor 1 deactivated, on the EWD the caution PRIM 1 PITCH FAULT
is shown.
(2) With THS electrical motor 2 deactivated, on the EWD the caution PRIM 2 PITCH FAULT
is shown.
(3) With THS electrical motor 3 deactivated, on the EWD the caution PRIM 3 PITCH FAULT
is shown.
5. Close-up
SUBTASK 27-44-00-860-060-A
A. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
Ref. AMM TASK 31-60-00-860-802.
(2) On the MCDU, push the line select key adjacent to the RETURN indication until the MA
INTENANCE MENU 1/2 page comes into view.
(3) Fully decrease the brightness of the MCDU screen (display off).
(4) Remove the safety barriers.
(5) De-energize the aircraft electrical circuits
Ref. AMM TASK 24-41-00-862-801.
© AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.
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