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H135 Rev.012.01 (Update 10) AMM 05-60-00,6-4 P2 Printed by z00000074920 on 2024-05-13

Ground Check Run and Functional Check Flight - EC135 P2 /

P2+ - Ground Check Run and Functional Check Flight
AMM 05-60-00,6-4

REFERENCE
Documentary Unit AMM 05-60-00,6-4
References/Effectivity Ground Check Run and Functional Check Flight - EC135 P2 / P2+ - Ground
Check Run and Functional Check Flight
Language EN( en)
Issue Date 2020.11.04

EFFECTIVITY
Model EC135
Version P2
Serial Number

STATUS
Type of modification U
Description M
Reason for update Aircraft build standard changed
Maintenance work affected Yes

Additional information from O.R.I.O.N. Work card referenced in Maintenance Program

Ground Check Run and Functional Check Flight

MSM 05-60-00 P1,P2,P3,T1,T2,T3

Effectivity : P2/P2+

A. References:
AMM 10-10-00,2-3 Parking and Mooring in Extreme Weather Conditions -
Helicopter
AMM 63-51-00,5-6 Run-In - Brake Disk and Brake Linings
AMM 67-12-00,5-1 Adjustment - Collective Brake
FLM

B. Special Tools:
None.

C. Consumable Materials:
None.

D. Routine Replacement Parts:

None.

E. General:

E.1. Ground check run and functional check flight serve to check the function and
performance of systems and components of the helicopter.
Ground check run and functional check flight are required while performing inspections
and maintenance tasks. They may be individually reduced in accordance with item G.

NOTE
Before or after performing a certain maintenance task a ground run can be
required. The ground run differs from the ground check run by the fact that engine
operation time and check items are given directly by the instruction for the
maintenance task.
There is no cross-reference to this ground check run.

F. Instructions for carrying out:

CAUTION
PILOTS AND MECHANICS TO BE FAMILIAR WITH THE PROCEDURE PRIOR TO
CARRYING OUT THIS TASK ON THE AIRCRAFT TYPE.

NOTE
Area for ground check run must be clean and free of foreign matter.

F.1. Park helicopter and turn it into the wind.

F.2. Perform pre-flight check per FLM .

F.3. Tie down helicopter to the ground if ground check run is performed by instructed
maintenance personnel instead of a helicopter pilot AMM 10-10-00, 2-3.
F.4. Enter helicopter data in Helicopter Data Sheet according to item H.

F.5. Perform ground check run according to item I following the requirements of the Test
Report.
In case of deviations from the given rated values and tolerances, perform trouble
shooting and corrective action on the related system.

F.6. Perform functional check flight according to item J following the requirements of the
Test Report.
In case of deviations from the given rated values and tolerances, perform trouble
shooting and corrective action on the relevant system.

F.7. Keep Helicopter Data Sheet and Test Report in the operational records of the
corresponding helicopter.

G. Reductions:

G.1. The reductions matrix according (Figure 2: Reductions - Matrix) gives an overview of
the check items to be performed as an individually reduced ground check run or as an
individually reduced functional check flight after conduction of one of the defined
maintenance tasks.

H. Helicopter Data Sheet - EC135:

Table - Helicopter Data Sheet

Reg. Number: Model: Serial Number: Pilot: Technician
/
Mechanic:

Date Flight QNH [hPa] OAT Takeoff Landing Flying Fuel Remarks
No. [°C] Time Time Time Ballast

Empty mass .................... kg Empty center of gravity ............... mm

Crew .................... kg
Ballast .................... kg
 Ramp mass .................... kg
Fuel .................... kg
Takeoff mass .................... kg Center of gravity ............... mm

I. Ground Check Run:

I.1. Perform engine startup check and functional check of hydraulic systems:
Rated Value Actual Value ⎷

Pre-Start Check - perform according to FLM

Voltage indication on VEMD - check / record

≥ 24V
(ELEC / VEH)

FADEC-Test - perform according to FLM

Indications on CAD during - check

test

SYSTEM I MISC SYSTEM II

TRAINING TRAINING
TRAIN IDLE TRAIN IDLE
FADEC MINOR FADEC MINOR

For both systems:

FLI pointer of FLI scale - check / record 16

Numeric torque indication - check / record
on 133%
VEMD (FLI)
Numerical TOT indication - check / record
on 990°C
VEMD (FLI)

Engine startup check:

OAT indication on - record

VEMD (ELEC / VEH)
Pressure altitude of airfield - record
FUEL PUMPS PRIME I and - in the ON position
PRIME II switches for 10
sec.

Resp. engine - start according to FLM ENG1 ENG2

During startup:

White rectangular beside - check

TOT on VEMD (FLI)
N1 at starter cut-out - record from VEMD (FLI)
(CAD indication STARTER > 45%
disappears)
Oil pressure increase - monitor on VEMD (ELEC
/ VEH)
N2 and NRo increase - monitor on triple RPM-
indicator
Stabilized value of N2 - record from triple rpm First Started
indicator Eng ≈ 74%
- record from VEMD Sec. Started
(SYSTEM STATUS) Eng 77 ± 3%

First started engine and all - check for leaks

dynamic systems

Hydraulic system test:

Cyclic stick - center stick with centering device

FTR switch - press (if AFCS is installed)

HYD TEST switch - switch to position SYS 1 and hold

CAD indication - check

SYSTEM I MISC SYSTEM II

HYD PRESS

Correct function of hydraulic - check with small movements of cyclic stick, longitudinal and
system lateral, collective lever and pedals
- ensure blade tips move the correct direction
- cyclic, collective: low control forces
 - pedals: higher forces

HYD TEST switch - switch to position SYS 2 and hold

CAD indication - check

SYSTEM I MISC SYSTEM II

HYD PRESS

Correct function of hydraulic - check with small movements of cyclic stick, longitudinal and
system lateral, collective lever and pedals
- cyclic, collective, pedals: low control forces

I.2. Perform ground run at power setting IDLE and overspeed check:
For the limits refer to the FLM
NRo N2.1 N2.2 N1.1 N1.2 TRQ1 TRQ2 TOT1 TOT2 ⎷
[%] [%] [%] [%] [%] [%] [%] [°C] [°C]
Rated
77 ± 3%
Value
CPDS
YES
Indication
Make sure that all are inside the limits according to the FLM
Triple
NO
Tachometer

POIL1 TOIL1 POIL TOIL POIL2 TOIL2 ⎷

[bar] [°C] XMSN XMSN [bar] [°C]
[bar] [°C]
Rated
YES
Value Make sure that all is in the normal operating range according to the
CPDS FLM
NO
Indication

NOTE
N2: max. difference between CPDS indication and triple tachometer indication ± 1
%.
N2: max difference between both triple tachometer indications ± 0.5%.
 NOTE
The normal operating range corresponds to the “normal / continuous range” in the
FLM

Rated Value Actual ⎷

Value

Overspeed check:

OVERSPEED switch - switch to position ENG 1 and hold

N2 YES
FLUCTUATING
NO
N2 (ENG 1) - check BETWEEN
IDLE AND ≈
70%

OVERSPEED switch - switch to position ENG 2 and hold

N2 YES
FLUCTUATING
NO
N2 (ENG 2) - check BETWEEN
IDLE AND ≈
70%

OVERSPEED switch - release

I.3. Check FADEC power supply from engine:

⎷

Control switch FADEC ENG I / II - switch to OFF position ENG 1 2

No change in operating condition and - check

indication

Control switch FADEC ENG I / II - switch to ON position

I.4. Perform ground run at power setting FLIGHT:
- Collective pitch lever: lowest position
For the limits refer to the FLM
NRo N2.1 N2.2 N1.1 N1.2 TRQ1 TRQ2 TOT1 TOT2 ⎷
[%] [%] [%] [%] [%] [%] [%] [°C] [°C]
Rated
97.3% ± 0.4%
Value
CPDS
YES
Indication
Make sure that all are inside the limits according to the FLM
Triple
NO
Tachometer

POIL1 TOIL1 POIL TOIL POIL2 TOIL2 ⎷

[bar] [°C] XMSN XMSN [bar] [°C]
[bar] [°C]
Rated
YES
Value Make sure that all is in the normal operating range according to
CPDS the FLM
NO
Indication

NOTE
N2: max. difference between CPDS indication and triple tachometer indication ± 1
%.
N2: max difference between both engines on CPDS ± 0.4%.
N2: max difference between both triple tachometer indications ± 0.5%.

NOTE
The normal operating range corresponds to the “normal / continuous range” in the
FLM

Effectivity : Mast Moment System

I.5. Check mast moment indication (optional):

Actual ⎷
Value

NOTE Steady wind ≤ 10 kts, helicopter heading into the wind

Collective lever - full down

Both engine main switches - to FLIGHT

ENG I, ENG II

P/R SAS, + AFCS, if installed - decouple

NRo ≈ 97% - record

CAUTION DO NOT EXCEED A MAX. FORWARD CYCLIC STICK DISPLACEMENT OF

70 MM (2.76 IN) FROM NEUTRAL POSITION DURING THIS CHECK.

Cyclic stick - adjust to “minimum mast moment” indication ( ≤ 6mm / 0.24

in) on VEMD (FLI) (cursor close to the left scale end)

Tape measure - adjust in a height of 475 mm (18.7 in) above the cabin floor
(commercially available) between the instrument panel and the cyclic stick

NOTE The following stick displacements are related to the front side of the cyclic stick in
a height of 475 mm (18.7 in) above the cabin floor.

NOTE Use trim system to move cyclic stick to avoid lateral inputs.

Position of cyclic stick for - measure by the distance to the

“minimum mast moment” instrument panel and record
indication (A)

Cyclic stick - move forward to a stick displacement which establishes

a mast moment indication showing the cursor inbetween
the “MM”

Position of cyclic stick for cursor in - measure by the distance to the

between “MM” instrument panel and record (B)

Cyclic stick displacement - calculate and record (A - B)

The cyclic stick displacement (A - B) must be 40 mm ± 3 mm (1.57 in ± 0.12 in).

Cyclic stick - move further forward to a stick displacement which

establishes a mast moment indication showing the cursor
at the beginning of yellow range

Position of cyclic stick for cursor at - measure by the distance to the

beginning of yellow range instrument panel and record (C)
 Cyclic stick displacement - calculate and record (B - C)

The cyclic stick displacement (B - C) must be 19 mm ± 3 mm (0.75 in ± 0.12 in).

Cyclic stick - Center stick to previous min. mast moment position with
centering device

Mast moment indication on VEMD - measure position of the cursor relative to

(FLI) the left scale end and record

The cursor shall have a distance to the left scale end of max. 6 mm (0.24 in).

I.6. Perform power check / N1-TOT check (optional):

Rated Value Actual Value ⎷

Engine to be checked - running in FLIGHT

Other engine - running in IDLE

NOTE If sandfilter is installed, refer to differing values in accordance with FLM

NOTE If the helicopter takes off at 75 % TRQ, it has to be additionally loaded

respectively.

Power Check / N1-TOT Check - perform at 75 % TRQ according to FLM

Pressure altitude and OAT - record Press. altitude:

OAT:

1 min stabilizing time - hold

ENG 1 ENG 2
TRQ1 N1.1 TOT1 N1 TOT N2.1 N1.2 TOT2 N1 TOT N2.2
(FLI) (FLI) (FLI) Norm Norm [%] (FLI) (FLI) Norm Norm [%]
[%] [%] [°C] [%] [°C] [%] [°C] [%] [°C]
75
 ENG ENG 2
1
N1 - record from VEMD ≤ N1 Norm
(FLI)
TOT - record from VEMD ≤ TOT Norm
(FLI)

Effectivity : Rotor Brake System

I.7. Check of rotor brake for function at NRo = 50 % (optional):

Rated Value Actual ⎷
Value

Engines ENG 1 and ENG 2 - shutdown

Rotor brake lever at - unlock and pull down

NRo = 50%

CAD indication ROTOR - check SYSTEM MISC SYSTEM

BRK I II
ROTOR BRK

NOTE If brake disk or friction pads are new, they have to be run in carefully before this
check AMM 63-51-00, 5-6. Otherwise the rotor run down time can be more than
45 sec.

Pulled down rotor brake - record run down time until

lever rotor stops (after the rotor
≤ 45 sec.
brake has been applied 6
times)

I.8. Signature list

Pilot: Date: Inspector Date:
Name: Signature: Stamp: Signature:

J. Functional Check Flight:

 NOTE
- Do the Exterior Check iaw.FLM
- Do the Interior Check iaw FLM
- Do the Pre-Start Check iaw FLM
- Do the Engine Start iaw FLM
- Do the Hydraulic and System Checks iaw FLM
- Do the AFCS/Avionic Pre-flight test check iaw FLM

J.1. Check Collective Friction Brake in Hover:

⎷

Pilot and Copilot collective levers installed

Pilot collective lever installed

Collective brake fully - check

released

NOTE Perform smooth first takeoff into hover

NOTE Hover at sufficient height which allows a descent

Perform a behavior
check of the collective
lever - Check collective lever setting is stable during hover flight
- Check harmonic force during up and down movement
with torque variation of 10 - 15%
No drop of collective lever by gravity is allowed

If test failed, adjust a higher collective lever brake out force AMM 67-12-00,5-1

J.2. Perform CAT.A mode check (only valid for engine type P2):
Rated Value Actual ⎷
Value

NOTE Above 4000 ft density altitude the initial N2 will be higher, hence the
subsequent N2 increase will be lower.

Collective lever - adjust to TRQ1 = TRQ2 ≈ 40%

 N2 - record from VEMD 100.0%
(SYSTEM STATUS) ± 0.2%

CAT.A switch in instrument panel - press

CAT.A switch in instrument panel - ON indicator illuminates

Increase of N2 - record from VEMD 103.0%

(SYSTEM STATUS) -0.2%/+0.5%

CAT.A switch in instrument panel - press

CAT.A switch in instrument panel - ON indicator extinguished

Decrease of N2 - record from VEMD 100.0%

(SYSTEM STATUS) ± 0.2%

Collective lever - lowest position

J.3. Perform stabilized hover flight:

For the limits refer to the FLM
NRo N2.1 N2.2 N1.1 N1.2 TRQ1 TRQ2 TOT1 TOT2 ⎷
[%] [%] [%] [%] [%] [%] [%] [°C] [°C]
Rated
100.0%
Value
CPDS
YES
Indication Make sure that all is in the normal operating range according to the
Triple FLM
NO
Tachometer

POIL1 TOIL1 POIL TOIL POIL2 TOIL2 ⎷

[bar] [°C] XMSN XMSN [bar] [°C]
[bar] [°C]
Rated 4 - 8.5 ≤ 0.5 - 0°C - 4 - 8.5 ≤
Value bar 120°C 7.8 bar 105°C bar 120°C
CPDS
Make sure that all is in the normal operating range YES
Indication
according to the FLM
NO
 NOTE
N2: max. difference between CPDS indication and triple tachometer indication ± 1
%.
N2: max difference between both engines on CPDS ± 0.4%.
N2: max difference between both triple tachometer indications ± 0.5%.

J.4. Perform HIGH NR mode check (only valid for engine type P2+):
Rated Value Actual ⎷
Value

Stabilized hover flight - perform

HIGH NR switch in instrument - press

panel

Increase of NRo - record from VEMD 103.0%

(SYSTEM STATUS) -0.2%/+0.5%

HIGH NR switch in instrument - ON indicator illuminates

panel

Advisory indication HIGH NR - check (if installed)

Flight condition: Level flight - perform

Airspeed - increase slowly to at least 60 KIAS

At 55 KIAS:

Decrease of NRo - record from VEMD 100.0%

(SYSTEM STATUS) ± 0.2%

Advisory indication HIGH NR - check off (if installed)

Airspeed - decrease slowly to 40 KIAS

At 50 KIAS:
 Increase of NRo - record from VEMD 103.0%
(SYSTEM STATUS) -0.2%/+0.5%

Advisory indication HIGH NR - check (if installed)

Stabilized hover flight - perform

HIGH NR switch in instrument - press

panel

HIGH NR switch in instrument - ON indicator extinguished

panel

Advisory indication HIGH NR - check off (if installed)

J.5. Perform quartering flight and hover flight:

⎷

The limits below should be approximated as closely as practicable.

Flight forward - perform

airspeed ≤ 20 kts

Flight backward - perform

airspeed ≤ 20 kts

Flight sideways left - perform

airspeed ≤ 20 kts

Flight sideways right - perform

airspeed ≤ 20 kts

Turn left - perform

Rate of turn: max. 60°/s

Turn right - perform

Rate of turn: max. 60°/s
J.6. Check TRAIN Mode and Topping Select Switch:
⎷

Effectivity : UP TO S/N 216 AND FROM S/N 217 PRE SB EC135-31-081

First engine ENG 1

Check of TRAIN Mode:

Trim flight condition: - stabilize and check

In level flight with 65 kts

Training Selector switch - to ARM

CAD indication TRAIN ARM - check on

SYSTEM I MISC SYSTEM II

TRAIN ARM

Engine main switch ENG I - to IDLE

FLI pointer of engine ENG 1 at zero - check

CAD indications TRAIN IDLE and - check on

TRAINING

SYSTEM I MISC SYSTEM II

TRAIN TRAINING
IDLE

Indications TRAIN IDLE (upper left) - check on

and TRAIN (upper right) on FLI
(VEMD)

Indication of a yellow T in yellow - check on

triangle in the lower mid area of the
FLI (VEMD)

NOTE Wait until the engine is in stabilized condition.

Numerical indications of TRQ, TOT - unchanged
and N1 of both engines

Check of Topping Select Button:

NOTE Pressing TOPPING button on collective lever not less than 0.25 sec. and not
more than 3 sec.

Collective pitch - adjust to FLI pointer of engine ENG 2 below MCP-

OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Topping push button - press once

Topping select triangle still at 30 sec. - check

power (long dashed red line)

Collective pitch - adjust to FLI pointer of engine ENG 2 at 30 sec.

power (long dashed red line)

CAUTION IF NRo DROPS BELOW 97 %, LOWER COLLECTIVE TO MAINTAIN NRo

BETWEEN 97 % AND NOMINAL RPM.

Red FLI-Label: OEI HI - check

Topping push button - press once

Topping select triangle at 2 min. power - check

(short dashed red line)

Amber FLI-Label: OEI LO - check

Collective pitch - adjust to FLI pointer of engine ENG 2 below MCP-

OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Engine main switch ENG I - to FLIGHT

Training Selector button - to OFF

Second engine ENG 2

Check of TRAIN Mode:

Trim flight condition: - stabilize and check

In level flight with 65 kts

Training Selector switch - to ARM

CAD indication TRAIN ARM - check on

SYSTEM I MISC SYSTEM II

TRAIN ARM

Engine main switch ENG II - to IDLE

FLI pointer of engine ENG 2 at zero - check

CAD indications TRAIN IDLE and - check on

TRAINING

SYSTEM I MISC SYSTEM II

TRAINING TRAIN IDLE

Indications TRAIN IDLE (upper right) - check on

and TRAIN (upper left) on FLI (VEMD)

Indication of a yellow T in yellow - check on

triangle in the lower mid area of the
FLI (VEMD)

NOTE Wait until the engine is in stabilized condition.

Numerical indications of TRQ, TOT - unchanged

and N1 of both engines

Check of Topping Select Button:

 NOTE Pressing TOPPING button on collective lever not less than 0.25 sec. and not
more than 3 sec.

Collective pitch - adjust to FLI pointer of engine ENG 1 below MCP-

OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Topping push button - press once

Topping select triangle still at 30 sec. - check

power (long dashed red line)

Collective pitch - adjust to FLI pointer of engine ENG 1 at 30 sec.

power (long dashed red line)

CAUTION IF NRo DROPS BELOW 97 %, LOWER COLLECTIVE TO MAINTAIN NRo

BETWEEN 97 % AND NOMINAL RPM.

Red FLI-Label: OEI HI - check

Topping push button - press once

Topping select triangle at 2 min. power - check

(short dashed red line)

Amber FLI-Label: OEI LO - check

Collective pitch - adjust to FLI pointer of engine ENG 1 below MCP-

OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Engine main switch ENG II - to FLIGHT

Training Selector button - to OFF

Effectivity : FROM S/N 217 POST SB EC135-31-081

Engine main switches - to FLIGHT

Training Selector switch - to ARM

CAD indication TRAIN ARM - check on

SYSTEM I MISC SYSTEM II

TRAIN ARM

Training Selector switch - to SEL

CAD indication TRAINING and TRAIN - check on

IDLE

SYSTEM I MISC SYSTEM II

TRAINING TRAIN IDLE

Indications TRAINING and TRAIN - check on

IDLE on FLI (VEMD)

NOTE NRo increases approximately 3 %.

Indication of a yellow T in yellow - check on

triangle in the lower mid area of the
FLI (VEMD)

NOTE Pressing TOPPING button on collective lever not less than 0.25 sec. and
not more than 3 sec.

Collective pitch - adjust to FLI pointer of the engine ENG 2 below

MCP-OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Topping push button - press once

Topping select triangle still 30 sec. - check
power (long dashed red line)

Collective pitch - adjust to FLI pointer of engine ENG 2 at 30 sec.

power (long dashed red line)

CAUTION IF NRo DROPS BELOW 97 %, LOWER COLLECTIVE TO MAINTAIN NRo

BETWEEN 97 % AND NOMINAL RPM.

Red FLI-Label: OEI HI - check

Topping push button - press once

Topping select triangle at 2 min. power - check

(short dashed red line)

Amber FLI-Label: OEI LO - check

Collective pitch - adjust to FLI pointer of engine ENG 2 below

MCP-OEI

Topping select triangle at 30 sec. - check

power (long dashed red line)

Training Selector switch - to SEL

CAD indication TRAINING and TRAIN - check off

IDLE

SYSTEM I MISC SYSTEM II

TRAIN ARM

Indications TRAINING and TRAIN - check off

IDLE on FLI (VEMD)

NOTE NRo decreases approximately 3 %.

Training Selector switch - to SEL

CAD indication TRAIN IDLE and - check on

TRAINING
 SYSTEM I MISC SYSTEM II
TRAIN TRAINING
IDLE

Indications TRAIN IDLE and - check on

TRAINING on FLI (VEMD)

NOTE NRo increases approximately 3 %.

Training Selector switch - to SEL

CAD indication TRAIN IDLE and - check off

TRAINING

SYSTEM I MISC SYSTEM II

TRAIN ARM

Indications TRAIN IDLE and - check off

TRAINING on FLI (VEMD)

NOTE NRo decreases approximately 3 %.

Training Selector switch - to OFF

CAD indication TRAIN ARM - goes off

Effectivity : Without AFCS

J.7. Check YAW-SAS for function (optional:

⎷
⎷

Climb at 90 KIAS and MCP - stabilize

YAW-SAS - disengage

CAD indication - check

 SYSTEM I MISC SYSTEM II
YAW
SAS

Several sinusoidal pedal input left / right, - apply

approx. 10 % of total pedal travel

The induced yaw oscillation will be marginally damped.

YAW-SAS - reengage

CAD indication - check off

SYSTEM I MISC SYSTEM II

Several sinusoidal pedal input left / right, - apply

approx. 10 % of total pedal travel

The induced yaw oscillation must be well damped.

Effectivity : Without AFCS

J.8. Check Pitch/Roll-SAS for function (optional):

⎷
⎷

Pitch/Roll-SAS and YAW-SAS - check active

Check of pitch attitude stabilizing quality:

Trim flight condition: - stabilize and check

In level flight with 120 KIAS below
5000 ft pressure altitude

Procedure: - trim helicopter in pitch attitude very carefully

- fly with “hands off” for about 1 minute
- sense the response behaviour
and restabilize flight condition
Attitude related to the pitch axis must be stable (airspeed within 120 KIAS ± 5 KIAS), in roll axis
a roll angle of ± 5° is acceptable.

Check of roll attitude stabilizing quality:

Trim flight condition: - stabilize and check

In level flight with 120 KIAS below
5000 ft pressure altitude

Procedure: - roll to the left to bank angle 30°,

“hands off”, hold for 10 sec.
- roll to the right to bank angle 30°,
“hands off”, hold for 10 sec.

Attitude related to the pitch axis must be stable (airspeed within 120 KIAS ± 5 KIAS).
The established bank angle must remain within ± 5° when flying “hands off”.

Check of pitch attitude stabilizing quality:

Flight condition: - push button SAS DCPL and reset only YAW-SAS
Level flight with 100 KIAS using switch SAS CONT

Procedure for P/R-SAS not active: - periodical cyclic input push / pull,
amplitude ≈ ± 1 cm (±1/2 inch), freq. ≈ 3 Hz
- sense the response behaviour and restabilize flight
condition

Flight condition: - reset P/R-SAS + PITCH DAMPER using switch

Level flight with 100 KIAS SAS CONT

Procedure for P/R-SAS active: - periodical cyclic input push / pull,

amplitude ≈ ± 1 cm (±1/2 inch), freq. ≈ 3 Hz
- sense the response behaviour
and restabilize flight condition

With active P/R-SAS the pitch oscillation must be noticeably reduced compared with P/R-SAS
in “OFF”-condition.

Check of roll attitude stabilizing quality:

Flight condition: - push button SAS DCPL and reset only YAW-SAS
 Slow forward flight in ground effect using switch SAS CONT
with
about 10 - 30 KIAS

Procedure for P/R-SAS not active: - periodical cyclic input left / right,
amplitude ≈ ± 1 cm (±1/2 inch), freq. ≈ 0.5 - 1Hz
- sense the response behaviour
and restabilize flight condition

Flight condition: - reset P/R-SAS + PITCH DAMPER using switch

Slow forward flight in ground effect SAS CONT
with
about 10 - 30 KIAS

Procedure for P/R-SAS active: - periodical cyclic input left / right,

amplitude ≈ ± 1 cm (±1/2 inch), freq. ≈ 0.5 - 1Hz
- sense the response behaviour
and restabilize flight condition

With active P/R-SAS control response must be noticeably reduced compared with inactive P/R-
SAS. Reset P/R-SAS with switch SAS CONT.

J.9. Check bleed air heating system:

⎷
⎷

NOTE The bleed air heating valve only opens at a cabin temperature of below approx.
+25°C. Therefore at a cabin temperature of more than approx. +25°C function
cannot be checked.

Level flight with about 60 % TRQ - perform

Rotary switch BLD HTG - turn to MAX

Knob PULL FOR HEATING / DEFOG, - pull

located on center console aft

CAD indication BLEED AIR - check on

SYSTEM I MISC SYSTEM

 II
BLEED AIR

J.10. Check high rotor RPM-warning and N2:

Rated Value Actual Value ⎷
⎷

Autorotation at approx. 75 KIAS - stabilize

Separation of N2/NRo on triple - check

≤ 106 %
RPM-indicator

Rotor speed NRo - increase slowly

Rotor speed NRo at which - record 106 %

flashing RPM warning light is ± 0.5 %
activated

Rotor speed NRo at which gong - record 106 %

is activated ± 0.5 %

Reset of gong - must be possible while limit exceeded

J.11. Check MIN FUEL Flow and 97 %-RPM-warning on ground:

Rated Value Actual Value ⎷
⎷

Engine main switches - switch to IDLE position

ENG I and ENG II

Twist grip ENG 1 and - in neutral (N) position

twist grip ENG 2

Collective pitch - full down

ENG1 ENG2

Engine main switch ENG I / II - switch to FLIGHT position

of the engine
ENG 1 / 2 to be checked
Engine main switch ENG II / I - check IDLE position
of the other engine
ENG 2 / 1

NOTE Wait until the engine is in stabilized condition.

Switch ENGINE MODE SEL - switch to MAN position

ENG I / ENG II of the engine
ENG I / II to be checked

CAUTION DO NOT EXCEED 104% N2

CAD indication ENG - check

MANUAL
Twist grip ENG 1 / 2 of the - turn slowly out of neutral to decrease fuel flow
engine
ENG 1 / 2 to be checked

CAD indication TWIST GRIP, - check

ENG MANUAL
N1, N2, TOT - monitor during fuel flow decrease

LOW-RPM-WARNING - record 97%

Warning light ROTOR RPM - check
Beeping tone (800 Hz) - check
LOW-RPM-WARNING - check, if reset possible

MIN FUEL STOP of the - check by slowly turning the twist grip ENG 1 / 2 from neutral
engine (N) position to minimum fuel override button ENG 1 / 2
ENG 1 / 2 to be checked

NOTE The engine ENG 1 / 2 must not flame out at MIN FUEL STOP.
ENG OIL PRESS indication may appear.

CAUTION DO NOT TURN TWIST GRIP PAST THE NEUTRAL POSITION.

Twist grip ENG 1 / 2 of the - turn to neutral (N) position to increase fuel flow (turn slowly
engine to be checked until NRo ≈ 97 % and then rapidly into neutral (N) position)

CAD indication TWIST GRIP - check off

 Switch - switch to NORM position
ENGINE MODE SEL ENG I /
ENG II

CAD indication ENG - check off

MANUAL

J.12. Check CAUTION indication ENG FAIL, Automatic Bleed Air Shut-Off and engine
shut down using the twist grip:
⎷
⎷

Engine main switches - switch to FLIGHT position

ENG I and ENG II

Switch BLD HTG - switch to NORM position

Rotary switch BLD HTG - turn switch to MAX

Knob - pull
PULL FOR HEATING /
DEFOG

CAD indication BLEED - check on SYSTEM I MISC SYSTEM

AIR II
BLEED AIR

CAUTION AVOID PROLONGED OPERATION BELOW 70 % N2.

ENG 1

Twist grip ENG 1 - turn slightly to min.-positon and shutdown engine ENG 1
(ENG 2 running in using the twist grip ENG 1
FLIGHT)

At N1 ≈ 50%:

CAD indication BLEED - check off

AIR
CAD indication ENG FAIL - check

SYSTEM I MISC SYSTEM

II
ENG FAIL

Switch BLD HTG - switch to EMER position

CAD indication BLEED - check

AIR

SYSTEM I MISC SYSTEM

II
ENG FAIL BLEED AIR

ENG 2

Twist grip ENG 2 - turn slightly to min.-position and shutdown engine ENG 2
using the twist grip ENG 2

At N1 ≈ 50%:

CAD indication BLEED - remains on

AIR

SYSTEM I MISC SYSTEM

II
ENG FAIL BLEED AIR

CAD indication ENG FAIL - check

SYSTEM I MISC SYSTEM

II
ENG FAIL BLEED AIR ENG FAIL

Switch BLD HTG - switch to NORM position

CAD indication BLEED - check off

AIR
 SYSTEM I MISC SYSTEM
II

ENG FAIL ENG FAIL

Engine main switches - switch to OFF position

ENG I and ENG II

Twist grip ENG 1 and - in neutral (N) position

twist grip ENG 2

At N1 < 5%:

Switches FADEC ENG I / - switch to OFF position

II

Engines ENG 1 and ENG - restart in accordance with FLM

2

Knob - push again if necessary

PULL FOR HEATING /
DEFOG

J.13. Signature list

Pilot: Date: Inspector Date:
Name: Signature: Stamp: Signature:

© Copyright - Airbus
Density Altitude Diagram
Figure 1/2
C1350560M100100EN01
Reductions - Matrix
Figure 2/2
C1350560M700600MU02