Service Bulletin

LETTER OF TRANSMITTAL

SERVICE BULLETIN SAAB 340–27–099

REVISION 01, 13 APRIL 2012

TO: All holders of SAAB 340 SERVICE BULLETIN.

This letter covers transmittal of the following Service Bulletin revision which should be included in the

appropriate section of your folder.

Revision 01 of Service Bulletin SAAB 340–27–099, 13 April 2012,”FLIGHT CONTROLS – STALL

WARNING/IDENTIFICATION SYSTEM – ACTIVATION OF IMPROVED STALL WARNING SYSTEM

FOR ICING CONDITION (EXTENDED WINGTIP)”, cover sheet and 20 pages.

REASON FOR ISSUE

Test corrected.

New SB is not issued because it was not possible to perform the test with acceptable result, therefor this

SB is revised only.

Saab AB (Publ) Date: 13 April 2012

Support and Services

Aircraft Services Division

Technical Communication

Rolf Jönsson
SERVICE BULLETIN

Number: SAAB 340–27–099

Date: 01 September 2011

Revision 01, 13 April 2012

Subject: FLIGHT CONTROLS – STALL WARNING/IDENTIFICATION

SYSTEM – ACTIVATION OF IMPROVED STALL WARNING SYSTEM

FOR ICING CONDITION (EXTENDED WINGTIP)

Mod. No. 3313

20 pages

The content of this document is proprietary and confidential to Saab AB and 

may not:

a) be used for any purpose other than those for which it was supplied;

b) be copied or reproduced in whole or in part without the prior written consent of 

Saab AB; nor

c) be disclosed to any third party without the prior written consent of Saab AB

Support and Services

Aircraft Services Division

SE–581 88 Linköping

Sweden Telephone: int+46 13 18 26 16 Telefax: int+46 13 18 41 83

Saab AB (Publ)
Service Bulletin

01 September 2011

Revision 01, 13 April 2012

340–27–099

Page 1 of 20

ATA CHAPTER: 27

FLIGHT CONTROLS – STALL WARNING/IDENTIFICATION SYSTEM – ACTIVATION OF

IMPROVED STALL WARNING SYSTEM FOR ICING CONDITION (EXTENDED WINGTIP)

Mod No. 3313

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Aircraft:

Aircraft Mfg. Serial No’s SAAB 340B – 360–361, 364–366, 368–371, 373–378, 380–384, 386–394,

396–404, 406–408, 410–430, 432–454, 456–459.

NOTE: This Service Bulletin is not applicable for A/C POST Service Bulletin SAAB340–27–075

(Mod No 2650) or 340–27–085 (Mod No 2650, 2859) (Ice Speed Push Button).

NOTE: This Service Bulletin is applicable for A/C with Extended Wingtip:

(A/C with Extended Wingtip are A/C POST Service Bulletin SAAB340–57–026 or POST

Service Bulletin SAAB340–57–030 or with Option 57:01 installed)

NOTE: Implementation of this Service Bulletin require changes to procedures and performance

when Engine Anti–Ice is used.

NOTE: Service Bulletin SAAB 340–27–097 (Mod No 3311) must be included before or in

conjunction with this Service Bulletin.

(2) Spares: Not affected.

B. REASON

Natural stall has in few cases been experienced in icing condition before stall warning. In order to

prevent such unsafe condition a modified stall warning system has been developed.

This Service Bulletin installs the new stall warning computers and activates the modified stall warning

system that includes stall warning curves that are optimized for operation in icing conditions. The ice

compensated stall warning curves are activated by selection of Engine Anti Ice.

C. DESCRIPTION

This Service Bulletin gives instructions for:

– removal of panels for access

– removal of the existing stall warning computers

– removal of blank label and activation of the push button switch

– installation and activation of the circuit breaker

– installation of labels for the circuit breaker and for the push button switch

– connection of parked and stowed wires

– installation of the new stall warning computers

– installation of the removed access panels

– functional test of the stall warning system.
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D. COMPLIANCE

Mandatory

To be performed within 2 years from first release date of this Service Bulletin.

This Service Bulletin is under EASA consideration for an Airworthiness Directive.

The final compliance terms will be set by the EASA Airworthiness Directive when issued.

E. APPROVAL

This Service Bulletin is developed and approved under the authority of DOA nr. EASA.21J.066. 

The change addressed in the bulletin is classified as ”Major” in accordance with EC regulation

1702/2003 Part 21A.91 and is approved by the European Aviation Safety Agency, 

Ref. EASA No. 10035607.

F. MANPOWER

Estimated time to complete this Service Bulletin is:

2 persons required.

Total manhours: 8

Elapsed time (hours): 4

Labour cost at operators expense.

G. MATERIAL – COST AND AVAILABILITY

Mod. Kit will be available 4 months after receipt of order.

H. TOOLING

(1) Insert tool M81969/14–01, use for insert of contacts/wires to 3WH–P1 and 4WH–P1.

(2) Angle of attack (AOA) calibration tools:

– TES–4054332–001 (LH)

– TES–4054332–002 (RH).

(3) Weight on wheels (WOW) switches operating tool, TDO 5–4650224.

I. WEIGHT AND BALANCE

None.

J. ELECTRICAL LOAD DATA

RH Bat Bus: +170 mA when ice compensated stall warning curves are active.

LH Main Bus: +60 mA when ice compensated stall warning curves are active.

RH Main Bus: +60 mA when ice compensated stall warning curves are active.

RH Bat Bus: +50 mA when lamps are in DIM mode.

RH Bat Bus: +60 mA when weight on wheel is true.

K. REFERENCES

Aircraft Maintenance Manual (AMM) 06–30–00 Description / Operation

12–00–00 Servicing
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340–27–099

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24–00–00 Maintenance practice

27–35–10 Removal / Installation

L. OTHER PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM)

Illustrated Parts Catalog (IPC)

Wiring Manual (WM)

Airplane Flight Manual (AFM)

Aircraft Operations Manual (AOM)

Master Minimum Equipment List (MMEL)

Minimum Equipment List Procedures Guide (MELPG)

2. ACCOMPLISHMENT INSTRUCTIONS

A. JOB SET–UP

(1) Before you start the SB, make sure:

– The modification kit contains the parts listed in the Service Bulletin

– The local supply items listed in the Service Bulletin are available

– The documentation is available

– The special tools are available.

(2) Make the aircraft safe for maintenance:

(a) Isolate the electrical power (Ref. AMM 24–00–00, maintenance practices).

(3) Open for access:

(a) At the avionics rack, remove the access panel 220AZ (Ref. AMM 06–30–00).

(b) In the flight compartment

1 Loosen the screws that attach the circuit breaker panel 10VU to the structure and lower

the panel.

2 Loosen the screws that attach the circuit breaker panel 12VU to the structure and lower

the panel.

B. REMOVAL

(1) Removal of the stall warning computers

REF. FIG. 1

(a) Remove the stall warning computer 3WH (111) (Ref. AMM 27–35–10).

(b) Remove the stall warning computer 4WH (111) (Ref. AMM 27–35–10).

C. MODIFICATION

(1) Activation of the push button switch 3WHC

REF. FIG. 2

(a) At the instrument panel 1VU, remove the blank label (112) from the push button switch 3WHC.

(b) At the instrument panel 1VU, install the label (12) above the push button switch 3WHC.

(2) Installation of the circuit breaker 2WHC
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REF. FIG. 2

(a) Find the stowed circuit breaker 2WHC behind the circuit breaker panel 12VU.

(b) Carefully remove the shrinkable tubing from the circuit breaker 2WHC.

(c) At the RH circuit breaker panel 12VU, remove the cover from position S–28.

(d) At the RH circuit breaker panel 12VU, install the circuit breaker 2WHC at position S–28 (Ref.

AMM 39–10–42).

(e) Remove the cable–tie and close the circuit breaker 2WHC.

(f) At the RH circuit breaker panel 12VU, install the label SW ICE IND (13) at position S–28.

(3) Connection of parked and stowed wires

REF. FIG. 1 and 2

(a) At (behind) the circuit breaker panel 10VU, find the stowed wire WHC36–16 adjacent to the

circuit breaker 36WH.

(b) Carefully remove the shrinkable tubing from the wire and from the terminal lug.

(c) Connect this wire:

REF. FIG. 3 and 4

Wire No: Class: From: Contact: To: Contact: Remarks:

WHC36–16 A 36WH:911 36WH:L/1

(d) In the avionics rack, find these four stowed wires adjacent to 3WH–P1 and 4WH–P1.

– WHC44–24

– WHC45–24

– WHC46–24

– WHC47–24

(e) Carefully remove the shrinkable tubing from the four wires and from the contacts.

(f) Connect these wires:

REF. FIG. 3 and 4

Wire No: Class: From: Contact: To: Contact: Remarks:

WHC44–24 A 4WH–P1:911 4WH–P1: 15

WHC45–24 A 4WH–P1:911 4WH–P1:7

WHC46–24 A 3WH–P1:911 3WH–P1:15

WHC47–24 A 3WH–P1:911 3WH–P1:7

D. INSTALLATION

(1) Installation of the new stall warning computers:

REF. FIG. 1

(a) Install the stall warning computer 3WH (11) (Ref. AMM 27–35–10).

(b) Install the stall warning computer 4WH (11) (Ref. AMM 27–35–10).

(2) In the flight compartment:

(a) Put the circuit breaker panel 10VU in position at the structure and tighten the screws.
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(b) Put the circuit breaker panel 12VU in position at the structure and tighten the screws.

E. FUNCTIONAL TEST

(1) Prepare the aircraft for test:

CAUTION: BE CAREFUL WHEN YOU MOVE THE VANES. MOVE THE VANES IN A

GENTLY WAY. DAMAGE TO THE VANES CAN OCCUR IF YOU PUSH THEM

HARD TO THE OUTER POSITIONS.

(a) Fasten the Angle of Attack (AOA) calibration tools to the LH and the RH AOA transmitters:

– (LH) TES–4054332–001

– (RH) TES–4054332–002.

(b) Turn the LH AOA vane fully clockwise.

(c) Turn the RH AOA vane fully counter–clockwise.

(d) Make sure the flaps are at 0.

(e) On the LH circuit breaker panel 11VU, close the circuit breaker:

LABEL POS C/B

STAB & WING AUT CTL K–21 1HP

(f) On the overhead panel STAB & WING 18VU, set the switch AUTO CYCLING to OFF.

(g) On the overhead panel ENGINE 42VU, set the L and R Engine Anti–Ice to OFF.

(h) On the LH circuit breaker panel 9VU, open the circuit breaker:

LABEL POS C/B

STALL WARN CHAN 1 E–7 13WH

(i) On the RH circuit breaker panel 10VU, open these circuit breakers:

LABEL POS C/B

STALL WARN CHAN 2 L–6 2WH

STICK PUSHER L–4 36WH

(j) Supply the 28 VDC external power (Ref. AMM 12–00–00, servicing).

(k) At 1VU, make sure that the indication light in the ICE SPEED push–button is OFF.

(2) Do the test of the stall warning functions, flap 0and non–icing condition:

(a) On the CWP, make sure the amber caution–lights L STALL FAIL and R STALL FAIL are

illuminated.

(b) On the RH circuit breaker panel 10VU, close the circuit breaker:

LABEL POS C/B

STICK PUSHER L–4 36WH

(c) On the CWP, make sure the amber caution–lights L STALL FAIL and R STALL FAIL remains

ON.

(d) On the RH circuit breaker panel 10VU, open the circuit breaker:

LABEL POS C/B

STICK PUSHER L–4 36WH
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(e) On the LH circuit breaker panel 9VU, close the circuit breaker:

LABEL POS C/B

STALL WARN CHAN 1 E–7 13WH

(f) On the CWP, make sure the L STALL FAIL amber caution–light goes off.

(g) On the RH circuit breaker panel 10VU, close the circuit breakers:

LABEL POS C/B

STALL WARN CHAN 2 L–6 2WH

(h) On the CWP, make sure the R STALL FAIL amber caution–light goes off.

(i) On the overhead panel ENGINE 42VU, set the L and R Engine Anti Ice to ON and then back

to OFF.

(j) At the LH and the RH main landing–gear, install the WOW operating tool (TDO 5–4650224)

on the WOW switches 5GA and 6GA in flight position.

(k) Make sure to let a minimum of 6 minutes pass after the aircraft was set to flight position, then

make sure that the ICE SPEED on the instrument panel 1VU does not come on. (This is to

test that the latching relays for ice activation are reset by weight on wheels)

(l) Turn the LH AOA vane counter–clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– the stick shaker on the LH and the RH control columns

– the aural warning (continuous clacker).

(m) Make sure the measured angle from the LH calibration tool is 14.5 ± 1.

(n) Turn the LH AOA vane clockwise until the stall warning stops.

(o) Turn the RH AOA vane clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– the stick shaker on the RH and the LH control columns

– the aural warning (continuous clacker).

(p) Make sure the measured angle from the RH calibration tool is 14.5 ± 1.

(q) Turn the RH AOA vane counter–clockwise until the stall warning stops.

(3) Do the test of the stall identification functions, flap 0and non–icing condition:

(a) On the RH circuit breaker panel 10VU, close the circuit breaker:

LABEL POS C/B

STICK PUSHER L–4 36WH

(b) Make sure the PUSHER DISARM switch lights (31WH and 32WH) on the LH and RH side

panels 5VU and 6VU do not come on. 

If the PUSHER DISARM switch lights (31WH and 32WH) come on, proceed as follows:

1 Set the spring–loaded STICK PUSHER RESET switch (27WH) on the RH electrical

center 306VU to the ACTIVE position and release it. Make sure the PUSHER DISARM

lights goes off.

(c) Turn the RH AOA vane slowly clockwise until the PUSH 2 lights of the indicator lights (1WH

and 6WH) on the LH and RH instrument panels 3VU and 4VU come on. 

Make sure the PUSHER SYSTEM amber caution–light on the CWP (3WW) comes on.
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(d) Make sure the measured angle from the RH calibration tool is 19± 1.

(e) Turn back the RH AOA vane slowly until the PUSH 2 lights goes off.

(f) Pull the control column fully aft.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(g) Turn the LH AOA vane slowly counter–clockwise until the stick pusher is operated. Make sure

the PUSH 1 and the PUSH 2 lights come on at the same time.

(h) Make sure the measured angle from the LH calibration tool is 19± 1.

(i) Turn back the LH AOA vane to an angle between the stall warning and the stall identification,

e.g. 16. Make sure the PUSH 1 and the PUSH 2 lights are on.

(j) Turn the RH AOA vane fully counter–clockwise. Make sure the stick pusher is deactivated

and the PUSH 1 and the PUSH 2 lights goes off.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(k) Turn the RH AOA vane slowly clockwise until the PUSH 1 and the PUSH 2 lights come on

and the pusher is operated.

(l) Turn the RH AOA vane back to, e.g. 16and make sure the PUSH 1 and the PUSH 2 lights

are still on and the pusher is operated.

(m) Turn the LH AOA vane fully clockwise and make sure the PUSH 1 and the PUSH 2 lights goes

off and the pusher is deactivated.

(n) Turn the RH AOA vane fully counter–clockwise.

(4) Do the test of the stall identification functions, flap 35and non–icing condition:

(a) Set the flap selector to 35.

(b) Make sure that the PUSHER DISARM switch lights (31WH and 32WH) on the left and the

right side panels 5VU and 6VU not are on. 

If the PUSHER DISARM switch lights (31WH and 32WH) are on, proceed as follows:

1 Set the spring–loaded STICK PUSHER RESET switch (27WH) on the RH electrical

center 306VU to the ACTIVATE position and release it. Make sure the PUSHER

DISARM lights goes off.

(c) Turn the RH AOA vane slowly clockwise until the PUSH 2 lights of the indicator lights (1WH

and 6WH) on the left and right instrument panels 3VU and 4VU come on. 

Make sure the PUSHER SYSTEM amber caution–light on the CWP (3WW) comes on.

(d) Make sure the measured angle from the RH calibration tool is 20° ± 1°.

(e) Turn back the RH AOA vane slowly until the PUSH 2 lights goes off.

(f) Pull the control column fully aft.
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CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(g) Turn the LH AOA vane slowly counter–clockwise until the stick pusher is operated. Make sure

the PUSH 1 and PUSH 2 lights come on at the same time.

(h) Make sure the measured angle from the LH calibration tool is 20° ± 1°.

(i) Turn back the LH AOA vane to an angle between the stall warning and the stall identification,

e.g. 16°. Make sure the PUSH 1 and the PUSH 2 lights are on.

(j) Turn the RH AOA vane fully counter–clockwise. Make sure the stick pusher is deactivated

and the PUSH 1 and PUSH 2 lights goes off.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(k) Turn the RH AOA vane slowly clockwise until the PUSH 1 and the PUSH 2 lights come on

and the pusher is operated.

(l) Turn the RH AOA vane back to, e.g. 16and make sure the PUSH 1 and the PUSH 2 lights

are still on and the pusher is operated.

(m) Turn the LH AOA vane fully clockwise and make sure the PUSH 1 and the PUSH 2 lights goes

off and the pusher is deactivated.

(n) Turn the RH AOA vane fully counter–clockwise.

(5) Do the test of the stall warning functions, flap 0and icing condition:

(a) Set the flap selector to 0.

(b) Make sure that a minimum of 6 minutes has passed after weight off wheel and after power

up. On the overhead panel ENGINE 42VU, set the Left Engine Anti Ice to ON. 

Make sure that the push button switch ICE SPEED on the instrument panel 1VU comes on

(blue light).

(c) Momentarily press the push button switch ICE SPEED and make sure that the blue light NOT

goes out.

(d) Turn the LH AOA vane counter–clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– the stick shaker on the LH and the RH control columns

– the aural warning (continuous clacker).

(e) Make sure the measured angle from the LH calibration tool is 7.0± 1.

(f) Turn the LH AOA vane clockwise until the stall warning stops.

(g) Turn the RH AOA vane clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– the stick shaker on the RH and the LH control columns

– the aural warning (continuous clacker).

(h) Make sure the measured angle from the RH calibration tool is 7.0± 1.

(i) Turn the RH AOA vane counter–clockwise until the stall warning stops.
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(j) On the overhead panel ENGINE 42VU, set the Left Engine Anti Ice to OFF. 

Make sure that the blue indication light in the ICE SPEED push button, on the instrument

panel 1VU, is still ON.

(k) Press the push button switch ICE SPEED and make sure the indication light in the switch goes

off.

(6) Do the test of the stall identification functions, flap 0and icing condition.

(a) Make sure that a minimum of 6 minutes has passed after weight off wheel and after power

up. On the overhead panel ENGINE 42VU, set the Left Engine Anti Ice to ON. 

Make sure that the push button switch ICE SPEED on the instrument panel 1VU comes on

(blue light).

(b) Turn the RH AOA vane slowly clockwise until the PUSH 2 lights of the indicator lights (1WH

and 6WH) on the LH and RH instrument panels 3VU and 4VU come on. 

Make sure the PUSHER SYSTEM amber caution–light on CWP (3WW) comes on.

(c) Make sure the measured angle from the RH calibration tool is 19± 1.

(d) Turn back the RH AOA vane slowly until the PUSH 2 lights goes off.

(e) Pull the control column fully aft.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(f) Turn the LH AOA vane slowly counter–clockwise until the stick pusher is operated. Make sure

the PUSH 1 and the PUSH 2 lights come on at the same time.

(g) Make sure the measured angle from the LH calibration tool is 19± 1.

(h) Turn back the LH AOA vane to an angle between the stall warning and the stall identification,

e.g. 12. Make sure the PUSH 1 and the PUSH 2 lights are on.

(i) Turn the RH AOA vane fully counter–clockwise. Make sure the stick pusher is deactivated

and the PUSH 1 and the PUSH 2 lights goes off.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(j) Turn the RH AOA vane slowly clockwise until the PUSH 1 and the PUSH 2 lights come on

and the pusher is operated.

(k) Turn the RH AOA vane back to, e.g. 12and make sure the PUSH 1 and the PUSH 2 lights

are still on and the pusher is operated.

(l) Turn the LH AOA vane fully clockwise and make sure the PUSH 1 and the PUSH 2 lights goes

off and the pusher is deactivated.

(m) Turn the RH AOA vane fully counter–clockwise.

(n) On the overhead panel ENGINE 42VU, set the Left Engine Anti Ice to OFF. 

Make sure that the blue indication light in the ICE SPEED push button, on the instrument

panel 1VU is still ON.

(o) Press the push button switch ICE SPEED and make sure the indication light in the switch goes

off.
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(7) Do the test of the stall warning functions, flap 35and icing condition:

(a) Set the flap selector to 35.

(b) Make sure that a minimum of 6 minutes has passed after weight off wheel and after power

up. On the overhead panel ENGINE 42VU, set the Right Engine Anti Ice to ON. 

Make sure that the push button switch ICE SPEED on the instrument panel 1VU comes on

(blue light).

(c) Turn the LH AOA vane counter–clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– the stick shaker on the LH and the RH control columns

– the aural warning (continuous clacker).

(d) Make sure the measured angle from the LH calibration tool is 6.7 ± 1.

(e) Turn the LH AOA vane clockwise until the stall warning stops.

(f) Turn the RH AOA vane clockwise until the stall warning is activated. Make sure these

warnings and cautions operate:

– The stick shaker on the RH and the LH control columns.

– The aural warning (continuous clacker).

(g) Make sure the measured angle from the RH calibration tool is 6.7 ± 1.

(h) Turn the RH AOA vane counter–clockwise until the stall warning system stops.

(i) On the overhead panel ENGINE 42VU, set the Right Engine Anti Ice to OFF. 

Make sure that the blue indication light in the ICE SPEED push button, on the instrument

panel 1VU is still ON.

(j) Press the push button switch ICE SPEED and make sure the indication light in the switch goes

off.

(8) Do the test of the stall identification functions, flap 35and icing condition:

(a) Make sure that a minimum of 6 minutes has passed after weight off wheel and after power

up. On the overhead panel ENGINE 42VU, set the Right Engine Anti Ice to ON. 

Make sure that the push button switch ICE SPEED on the instrument panel 1VU comes on

(blue light).

(b) Turn the RH AOA vane slowly clockwise until the PUSH 2 lights of the indicator lights (1WH

and 6WH) on the left and right instrument panels 3VU and 4VU comes on. 

Make sure the PUSHER SYSTEM amber caution–light on CWP (3WW) comes on.

(c) Make sure the measured angle from the RH calibration tool is 20° ± 1°.

(d) Turn back the RH AOA vane slowly until the PUSH 2 lights goes off.

(e) Pull the control column fully aft.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(f) Turn the LH AOA vane slowly counter–clockwise until the stick pusher is operated. Make sure

the PUSH 1 and PUSH 2 lights comes on at the same time.

(g) Make sure the measured angle from the LH calibration tool is 20° ± 1°.

(h) Turn back the LH AOA vanes to an angle between the stall warning and the stall identification,

e.g. 12°. Make sure the PUSH 1 and the PUSH 2 lights are on.
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(i) Turn the RH AOA vane fully counter–clockwise. Make sure the stick pusher is deactivated

and the PUSH 1 and PUSH 2 lights goes off.

CAUTION: DO NOT OPERATE THE STALL WARNING PUSHER SYSTEM FOR MORE

THAN A MAXIMUM OF 10 SECONDS CONTINUOUSLY. ALLOW THE

SYSTEM A MINIMUM OF 1 MINUTE OF NON–OPERATION BEFORE YOU

CONTINUE THE TEST. IF YOU RUN THE PUSHER SYSTEM FOR MORE

THAN 10 SECONDS, THE PUSHER SERVO ACTUATORS CAN

OVERHEAT.

(j) Turn the RH AOA vane slowly clockwise until the PUSH 1 and the PUSH 2 lights comes on

and the pusher is operated.

(k) Turn the RH AOA vane back to, e.g. 12and make sure the PUSH 1 and the PUSH 2 lights

are still on and the pusher is operated.

(l) Turn the LH AOA vane fully clockwise and make sure the PUSH 1 and the PUSH 2 lights goes

off and the pusher is deactivated.

(m) Turn the RH AOA vane fully counter–clockwise.

(n) On the overhead panel ENGINE 42VU, set the Right Engine Anti Ice to OFF. 

Make sure that the blue indication light in the ICE SPEED push button, on the instrument

panel 1VU is still ON.

(o) Press the push button switch ICE SPEED and make sure the indication light in the switch goes

off.

(9) Do the test of the test functions:

(a) Remove the WOW operating tool from the LH and the RH WOW switches 5GA and 6GA. (to

make the aircraft in ground configuration).

(b) Set and hold the STALL 1 switch on the TEST 1 panel (19VU) to the up position for at least

6 seconds:

– make sure that the aural warning starts and the two stick shakers start to operate

– make sure that the PUSH 1 lights and the PUSHER SYSTEM caution light come on.

(c) Set and hold the STALL 2 switch on the TEST 1 panel (19VU) to the up position for at least

6 seconds:

– make sure that the aural warning starts and the two stick shakers start to operate

– make sure that the PUSH 2 lights and the PUSHER SYSTEM caution light come on.

(d) Pull the control column aft and, at the same time, set the STALL 1 and the STALL 2 switches

on the TEST 1 panel to the up position:

– make sure that the aural warning starts and the two stick shakers start to operate

– make sure that the PUSH 1 and PUSH 2 lights come on

– make sure that the pusher starts to operate the control columns forward.

NOTE: PUSHER SYSTEM caution light may come on during this test depending on the

pusher actuator. This does not indicate a failure.

(e) Pull the control column aft and, at the same time, set the STALL 1 and the STALL 2 switches

on the TEST 1 panel to their lower position.

– make sure that the aural warning starts and the two stick shakers start to operate

(In this mode, the servo–actuator internal G–switch is tested, the operation of the stick pusher

is not started.)

NOTE: PUSHER SYSTEM caution light may come on during this test depending on the

pusher actuator. This does not indicate a failure.
Service Bulletin

01 September 2011

Revision 01, 13 April 2012

340–27–099

Page 12 of 20

(10) Do the test of the deactivating function:

(a) Push the PUSHER DISARM switch light (31WH) on the left side panel 5VU. 

Make sure the LH and the RH PUSHER DISARM switch lights (31WH and 32WH) on the left

and the right side panels 5VU and 6VU come on.

(b) Set the STALL 1 and the STALL 2 switches (29WH and 30WH) on the TEST 1 panel 19VU

to the up position. 

Make sure there is no PUSH 1 or PUSH 2 indication on the left and the right instrument panels

3VU and 4VU.

(c) Set the spring–loaded STICK PUSHER RESET switch (27WH) on the RH electrical center

306VU to the ACTIVATE position and release it. 

Make sure the PUSHER DISARM lights goes off.

(d) Push the PUSHER DISARM switch light (32WH) on the right side panel 6VU. 

Make sure the LH and the RH PUSHER DISARM switch lights (31WH and 32WH) on the left

and the right side panels 5VU and 6VU come on.

(e) Set the spring–loaded STICK PUSHER RESET switch (27WH) on the RH electrical center

306VU to the ACTIVATE position and release it. 

Make sure the PUSHER DISARM lights goes off.

(11) Do the test of the ICE SPEED push–button lamp:

(a) On the TEST 1 panel 19VU, set the lamp test switch to the LWR position and make sure that

the blue indication light in the ICE SPEED push–button comes on.

(b) When the ICE SPEED push–button lamp is on:

– set the DIM/BRT switch on the INT LIGHT panel 30VU to DIM and make sure that the

button light is dimmed

– set the DIM/BRT switch on the INT LIGHT panel 30VU to BRT and make sure that the

button light goes to bright.

F. JOB CLOSE–UP

(1) Remove the electrical power (Ref. AMM 12–00–00).

(2) Remove the AOA calibration tools from the LH and the RH AOA transmitters.

(3) Close the access:

(a) Remove all the tools and equipment from the work area. Make sure the work area is clean.

(b) At the avionics rack, install the access panel 220AZ.
Service Bulletin

01 September 2011

Revision 01, 13 April 2012

340–27–099

Page 13 of 20

3. MATERIAL INFORMATION

A. Modification Kit No SAAB 340–27–099–01 contains:

Item Part Number Qty Nomenclature Designation Remarks

11 0020AK7 2 Stall warning computer3WH, 4WH –

12 7292183–007 1 Label – At 1VU

13 7292183–005 1 Label – At 12VU S–28

B. Local supply

Item Part Number Qty Nomenclature Designation Remarks

– – AR Lacing cord – –

C. Removal

Item Part Number Qty Nomenclature Designation Remarks

111 0020AK3 MOD 1 2 Stall warning Computer3WH, 4WH –

112 7292183–009 1 Blank label – At 1VU

– 716306 1 C/B Cover – At 12VU S–28
Service Bulletin

01 September 2011

Revision 01, 13 April 2012

340–27–099

Page 14 of 20

A30723

Stall Warning Computers – Removal and Installation

FIG. 1
Service Bulletin

01 September 2011

Revision 01, 13 April 2012

340–27–099

Page 15 of 20

A30956 B

RHS C/B PANEL 12VU

13

C

RHS C/B PANEL 10VU

A

C

B

POST MOD

A

12

PRE MOD

A

112

Flight Compartment – Activation of Parked System

FIG. 2
Service Bulletin

01 September 2011

Revision 1, 13 April 2012

340–27–099

Page 16 of 20

THIS PAGE INTENTIONALLY LEFT BLANK
Service Bulletin

01 September 2011Revision 01, 13 April 2012

340–27–099

Page 17/18 of 20

A30950

	

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Wiring Diagram – PRE MOD for A/C 079–459

FIG. 3
Service Bulletin

Date Month Year

Revison X, Date Month Year

340–XX–XXX

Page 18
Service Bulletin

01 September 2011Revision 01, 13 April 2012

340–27–099

Page 19/20 of 20

A30945

	

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Wiring Diagram – POST MOD for A/C 079–459

FIG. 4
Service Bulletin

Date Month Year

Revison X, Date Month Year

340–XX–XXX

Page 20