Customer.aero.Bombardier.com Smartfixplus Cl605 Ch605 c

7/23/2019 Customer.aero.Bombardier.com Smartfixplus Cl605 Ch605 c

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Message Overview:

stall fail(Caution)

NO GO /or MMEL RELIEF NO GO

POSSIBLE LRU MMEL RELIEF NO GO

Pilot Action (QRH, Not Normal Procedure) ABNORM 8-2

System Description: 27-35-00

Schematic Diagram: 27-35-00

Wiring Diagram:27-35-00Pre SB 605-27-001

27-35-01Post SB 605-27-001

MMEL Dispatch:

For reference from the QRH GO/NO GO Guide.Please note: A "GO" condition still requires MMEL consultation.

Fault Logic:

The Stall Protection Computer detects single, non-single or internal failures and provides a discrete

(ground) to the DCUs, to post the STALL FAIL amber CAS message.

Possible Causes:

Loss of 28vdc to SPC (A1CG)

PUSHER switches are OFF

Loss of 28VDC to the AOA Signal Converter (A3CG LH) (A2CG RH) (Post SB 605-27-001)

Pilots Stick Shaker (B1CG)

Copilots Stick Shaker (B2CG)

AOA Vane Transducer (in flight only)

AOA Vane split 3.5 degrees or more

Pilots Lateral Accelerometer (MT3CG)

Copilots Lateral Accelerometer (MT4CG)

Lateral Accelerometer difference of 0.03 G Slip/Skid

Depressed AP/SP DISC switch on control column

Stall Protection Computer SPC (A1CG)

Flap Position Transmitters (Z2CG) and (Z1CG)

Page 1 of 7STALL FAIL

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Accelerometer Switch (MT5CG)

Associated Wiring

Troubleshooting Tips:

Advisory Wire/Service Bulletin: AW600-27-2224and SB605-27-001

Forum Articles/Infoservice/Newsletter:None

NOTE:When the aircraft is weight-on-wheels (WOW), the stall protection computer will not operate

but the SPS self-test will.

The latest Stall Protection Computers (SPCs) were recently upgraded to detect dormant internal

failures, by introducing new monitor circuits. Those added monitoring capabilities are:

1. Lateral Acceleration Compensation Monitor:

1. This monitor consists of a side-to-side comparator to detect any differences between the

accelerometers. The monitor is active on the ground and in the air, where in the previous

SPC models this was only monitored in air. When a lateral acceleration compensation

difference of 0.03g (450 mVdc) is detected,Stall Fail is annunciated.

2. Flap Compensation Monitor:

1. This monitor consists of a side-to-side comparator to detect any differences between the

left and right flap switches located in the left and right inboard flap arm assembly. The

monitor is active on the ground and in the air and any flap switches discrepancy shall

annunciate Stall Fail.

3. In addition to the monitors the SPS Self-Test was also enhanced:

1. The self-test initiate a simulated angle of attack sweep such that the test indicator needle

moves counter-clockwise through the blue sector (ignition), yellow sector (shaker) and

pass the red sector (pusher) before returning to the red sector at the end of a successful

self-test in approximately 91 seconds. In the event of a circuit failure detected within the

SPC, when performing the single and/or dual self-test, the needle will not stop in the red

sector. It will go a bit before (shown in the figure below) or after the red sector.




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During a single channel test (left or right) is activated, the SPC inhibit the associated channel altitude

input and the Alt Comp Fail and Stall Fail are annunciated. During a dual channel test the onlythe Stall Fail is annunciated.

Quick Links:

Leveling the Aircraft on jacksAMM 08-20-01-589-

801

Aligment Check of the AngleofAttack Vane TransducerAMM 27-35-04-820-

801

Functional Test of the AngleofAttack (AOA) Transducer LinearityAMM 27-35-04-720-

801

Lateral Accelerometer Ajustment (Aircraft is Level)

AMM 27-35-25-820-

801

Functional Test of the Flap and Sideslip Compensation Monitor of the Stall Protection

System

AMM 27-35-01-720-

803

Removal of the Stall Protection ComputerAMM 27-35-01-000-

801

Installation of the Stall Protection ComputerAMM 27-35-01-400-

801

Removal of the Stick ShakerAMM 27-35-07-000-

801

Installation of the Stick ShakerAMM 27-35-07-400-

801

Removal of the AngleofAttack TransducerAMM 27-35-04-000-

801

Installation of the AngleofAttack TransducerAMM 27-35-04-400-

801




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Removal of the Lateral Accelerometer AMM 27-35-25-000-

801

Installation of the Lateral AccelerometerAMM 27-35-25-400-

801

Removal of the Flap Position TransmitterAMM 27-55-01-000-

801

Installation of the Flap Position TransmitterAMM 27-55-01-400-

801

Removal of the Acceleration SwitchAMM 27-35-19-000-

801

Installation of the Acceleration SwitchAMM 27-35-19-400-

801

Wiring Repair SPM 20-12-10-02

Troubleshooting Recommendations:

If STALL FAIL is shown on the Ground and in Air proceed as follow base on the possible

cause:

1. Loss of power to the SPS computer. (AC5701-5827) Pre SB605-27-001.

1. Check both 28 Vdc inputs to the SPC.

1. Channel 1 P1CG-E 28Vdc Batt bus.

2. Channel 2 P2CG-E 28Vdc Ess Bus

2. Loss of power to the SPS computer. (AC5701-5827) Post SB605-27-001 and (AC5728-5990).

1. Check both 28 Vdc inputs to the SPC.

1. Channel 1 P1CG-E 28Vdc from LH Converter A3CG P13CG-15.

2. Channel 2 P2CG-E 28Vdc from RH Converter A2CG P12CG-15.

2. Check both 28 Vdc inputs to the Converters.

1. Channel 1 Converter A3CG P13CG-17 28Vdc Batt bus.

2. Channel 2 Converter A2CG P12CG-17 28Vdc Ess Bus.




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3. Loss of ODD parity at Discrete Calibration Input Pins of the Converter. (AC5701-5827) Post

SB605-27-001 and (AC5728-5990).

1. Channel 1 LH Converter P13CG- 3/4/5/20/21/32 To GND N595.

2. Channel 2 RH Converter P12CG- 3/4/5/20/21/32 To GND N651.

NOTE:Must have ODD number of grounds connected!

4. Failure of the stick shaker or stick pusher circuits in the SPS computer. (ALL).

1. Check Both Pusher Switches and make sure that both switches are in the ON position.

2. Verify that both shaker connectors P5CG & P6CG are hooked up properly.

3. Sticky Accelerometer Switch MT5CG.

1. With the Aircraft leveled, check presence of a Ground at JB11-PCB10 TP-A29

(WM 27-35-00 sheet 13/17).

2. Fail Relay K1CG in JB11-PCB10.

5. Failure of one or both of the angle-of-attack transducers, or a difference, exceeding 3.5 degrees,

in the compensated AOA signals. (AC5701-5827) Pre SB605-27-001.

1. 36 ohms per deg X 3.5 deg = 126 Ohms resistance difference between the L/H and the

R/H at the same position (i.e. 0 degree). Measure resistance at P1CG (P2CG)-c(+) and b

(-), if higher than 126 Ohms:

1. Perform AOA alignment check per AMM Task 27-35-04-820-801.2. Perform AOA Transducer Linearity check per AMM Task 27-35-04-720-801.

2. (AC5701-5827) Post SB605-27-001 and (AC5728-5990)

Since on those Aircraft the Vanes are digital, with Breakout Box GSE Tool PN:

CCSC2739-01 installed, measure voltage at connector P1CG (P2CG):

PIN VOLTAGE

c 15V

b Variable with angle

a 5V

VANE ANGLE (Aircraft) Voltage at pin b

-15 15V

-10 14V




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VANE ANGLE (Aircraft) Voltage at pin b

-5 13V

0 12V

5 11V

10 10V

15 9V

20 8V

25 7V

30 6V

35 5V

6. A difference, exceeding 0.03 G slide slip, in the signals from the lateral accelerometers. With

Breakout Box GSE Tool PN: CCSC2739-01 installed, do as follows:

1. Voltage input from the L/H (P1CG M & N) and R/H (P2CG M & N) accelerometer to

the SPC is 0+/- 10mv, if not adjust accelerometer per task 27-35-25-820-801 (when A/C

level) or 27-35-25-820-802 (when a/c not level).

2. Hook up a multimeter between both accelerometers P1CG-M & P2CG-M and measure

the differential voltage, the STALL FAIL will be displayed if voltage is higher then +/-

450mV corresponding to a 0.03g difference between accelerometers.

3. With the multimeter verify that the voltages of L/H and R/H accelerometer is coming

back to approximately 0 Vdc =/- 10mV after moving the a/c (shake).

4. Ensure that the voltages do not start to drift after sometime when the power is left ON for

approximately +/- 2hours.

7. Flap Switches on L/H and R/H should be identical for each Flap Setting, otherwise a Stall Fail

will be triggered by SPC, Troubleshoot according to this logic (Breakout Box GSE Tool PN:

CCSC2739-01 can be use):

Flap SettingFlap SW No

at SPC

P1CG/P2CG

Pin

Flap Switch Angle State at SPC

0

3

2

1

d

T

X

5

25

35

Ground

Ground

Ground

20

3

2

1

d

T

X

5

25

35

Open

Ground

Ground




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Flap SettingFlap SW No

at SPC

P1CG/P2CG

PinFlap Switch Angle State at SPC

30 3

2

1

d

T

X

5

25

35

Open

Open

Ground

40

3

2

1

d

T

X

5

25

35

Open

Open

Open

8. As an alternative and/or additional procedure of previous Step 6) and 7) you can simulate

Lateral Acceleration and Flap Setting at the SPC with GSE tool 27-35-05 and AMM Task

Procedure 27-35-01-720-803 Functional Test of the Flap and Side slip Compensation Monitor

of the Stall Protection System. Please refer accordingly.

9. Verification of the Weight-On-Wheel signal from the PSEU (Breakout Box GSE Tool PN:

CCSC2739-01 can be use), Follow this logic:

PSEU Output P1CG Pin P2CG Pin A/C State State at SPC

WOW 1 STALL

WarningW N/A WonW Ground

WOW 1 STALL

WarningW N/A WoffW Open

WOW 2 STALL

Warning

N/A W WonW Ground

WOW 2 STALL

WarningN/A W WoffW Open

WOW OUTPUT FAIL N/A j OK Open

WOW OUTPUT FAIL N/A j Failed Ground

10. Experience in the field has taught us that caution should be taken not to over torque the cage

during the installation of the SPS Test Indicator (M1CG & M2CG) as it may cause a binding in

SPS indicator needle.


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Customer.aero.Bombardier.com Smartfixplus Cl605 Ch605 c