Saab SB 340-27-121: No revision named, text

Text

From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document.

Query with SQL

duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = '90bdfd388ee0e932b41e9e69a14eb5e5d20a3c38ccf242007c386457529ab53e'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
WHERE p.file_sha256 = '90bdfd388ee0e932b41e9e69a14eb5e5d20a3c38ccf242007c386457529ab53e'
ORDER BY p.page

Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.

Page 1Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 1 of 24 ATA CHAPTER: 27 FLIGHT CONTROLS – STALL WARNING/IDENTIFICATION SYSTEM – ACTIVATION OF

IMPROVED STALL WARNING SYSTEM FOR ICING CONDITION (BASIC WINGTIP) Mod No. 3529

1. PLANNING INFORMATION A. EFFECTIVITY

(1) Aircraft:

Aircraft Mfg. Serial No’s SAAB SF340A – 004–159.

Aircraft Mfg. Serial No’s SAAB 340B – 160–169, 171–341, 343–361, 364–366, 368–371, 373–378, 380–384, 386–394, 396–404, 406–408, 410–430, 432–454, 456–459.

NOTE: Service Bulletin SAAB 340–27–109 (Mod No 3311, 3528, 3542) or Service Bulletin SAAB 340–27–120 (Mod No 3311, 3528) must be included before or in conjunction with this Service Bulletin.

(A/C POST Service Bulletin SAAB 340–27–120 includes A/C both PRE and POST SB340–27–097, and both PRE and POST SB340–27–116) NOTE: This Service Bulletin supersedes and cancels Service Bulletin SAAB340–27–098.

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

(A/C with Basic Wingtip are A/C PRE Service Bulletin SAAB340–57–026 and PRE Service Bulletin SAAB340–57–030 and without Option 57:01) NOTE: Implementation of this Service Bulletin require changes to procedures and performance when Engine Anti–Ice is used.

(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 or INOP label, at the push button switch 3WHC – removal of shrinkable tubing and/or cable–tie at the circuit breaker 2WHC – installation and/or activation of the circuit breaker 2WHC – installation of labels for the push button switch 3WHC and for the circuit breaker 2WHC – 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.

D. COMPLIANCE Mandatory

Page 2Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 2 of 24 Saab recommends this Service Bulletin to be performed within 18 months from release 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 (AD) 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 748/2012 Part 21A.91 and is approved by the European Aviation Safety Agency. Ref. EASA No.

10049287.

F. MANPOWER Estimated time to complete this Service Bulletin is:

2 persons required for the test procedure.

Total manhours: 8 Elapsed time (hours): 4 Labour cost at operators expense.

G. MATERIAL – COST AND AVAILABILITY Price and availability for Mod Kit. No. SAAB 340–27–121–01 will be furnished on request.

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: +60 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 24–00–00 Maintenance practice

Page 3Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 3 of 24 27–35–10 Removal / Installation 39–10–42 Maintenance practice Wiring Manual (WM) 20–00–00 Standard practices 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:

REF. FIG. 1, 2 and 3 FOR A/C 004–078

(a) At the avionics rack, remove the access panel 210AZ (Ref. AMM 06–30–00).

FOR A/C 079–459

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

FOR A/C ALL

(c) In the flight compartment, loosen the screws that attach the circuit breaker panel 10VU to the structure and lower the panel.

FOR A/C PRE SB340–27–109, or FOR A/C PRE SB340–27–116 and POST SB340–27–120

(d) In the flight compartment, loosen the screws that attach the circuit breaker panel 12VU to the structure and lower the panel.

FOR A/C ALL B. REMOVAL

(1) Removal of the stall warning computers REF. FIG. 1

(a) Remove the stall warning computer 3WH (110) (Ref. AMM 27–35–10).

Page 4Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 4 of 24

(b) Remove the stall warning computer 4WH (110) (Ref. AMM 27–35–10).

C. MODIFICATION CAUTION: BE CAREFUL WHEN YOU DO THE MODIFICATION OF THE HARNESS. MAKE

SURE THAT YOU DO NOT DAMAGE THE EXISTING WIRES WHEN NEW WIRES ARE INSTALLED. CLEAN AND INSPECT THE AFFECTED HARNESS WHEN THE MODIFICATION IS COMPLETED. DAMAGES TO THE WIRES CAN CAUSE SYSTEM MALFUNCTION.

NOTE: All wiring changes are to be performed in accordance with the procedures in the WM 20–00–00.

FOR A/C PRE SB340–27–109, or FOR A/C PRE SB340–27–116 and POST SB340–27–120

(1) Activation of the push button switch 3WHC REF. FIG. 2

(a) At the instrument panel 1VU, remove the blank label (R112) from the push button switch 3WHC.

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

(2) Installation of the circuit breaker 2WHC 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.

(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 (13) ”SW ICE IND” at position S–28.

FOR A/C POST SB340–27–109, or FOR A/C POST SB340–27–116 and POST SB340–27–120

(3) Activation of the push button switch 3WHC REF. FIG. 3

(a) At the instrument panel 1VU, remove the INOP label from the location adjacent to the push button switch 3WHC.

(b) If applicable, (if the ”ICE SPD CANCEL” label is missing or is defective), install the label (12) ”ICE SPD CANCEL” above the push button switch 3WHC.

(4) Activation of the circuit breaker 2WHC REF. FIG. 3

(a) On the RH circuit breaker panel 12VU at the position S–28, remove the cable–tie and close the circuit breaker 2WHC.

(b) If installed, remove the INOP label from the position S–28.

(c) If applicable, (if the ”SW ICE IND” label is missing or is defective), install the label (13) ”SW ICE IND” at 12VU position S–28.

Page 5Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 5 of 24

FOR A/C ALL

(5) Connection of parked and stowed wires REF. FIG. 1, 2 and 3

(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.

FOR A/C 004–078 REF. FIG. 4 and 6 FOR A/C 079–459 REF. FIG. 5 and 7

FOR A/C ALL Wire No: Class: From: Contact: To: Contact: Remarks:

WHC36–16 A 36WH:911 36WH:L/1 FOR A/C 004–078

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

– WHC16–24 – WHC17–24 – WHC18–24 – WHC39–24

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

(f) Connect these wires:

REF. FIG. 4 and 6 Wire No: Class: From: Contact: To: Contact: Remarks:

WHC16–24 A 4WH–P1:911 4WH–P1:7 WHC17–24 A 3WH–P1:911 3WH–P1:7 WHC18–24 A 4WH–P1:911 4WH–P1:15 WHC39–24 A 3WH–P1:911 3WH–P1:15 FOR A/C 079–459

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

– WHC44–24 – WHC45–24 – WHC46–24 – WHC47–24

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

(i) Connect these wires:

REF. FIG. 5 and 7 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

Page 6Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 6 of 24 Wire No: Remarks:Contact:To:Contact:From:Class:

WHC46–24 A 3WH–P1:911 3WH–P1:15 WHC47–24 A 3WH–P1:911 3WH–P1:7

FOR A/C ALL D. INSTALLATION

(1) Installation of the new stall warning computers REF. FIG. 1

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

(b) Install the stall warning computer 4WH (10) (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.

FOR A/C PRE SB340–27–109, or FOR A/C PRE SB340–27–116 and POST SB340–27–120

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

FOR A/C ALL 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.

(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

Page 7Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 7 of 24

(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 0 and 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

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

LABEL POS C/B STICK PUSHER L–4 36WH

(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 12.5 ± 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).

Page 8Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 8 of 24

(p) Make sure the measured angle from the RH calibration tool is 12.5 /C0095 ± 1/C0095.

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

(3) Do the test of the stall identification functions, flap 0 /C0095and 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.

(d) Make sure the measured angle from the RH calibration tool is 19 /C0095± 1/C0095.

(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 /C0095± 1/C0095.

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

e.g. 16/C0095. 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.

(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. 16 /C0095 and 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.

Page 9Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 9 of 24

(4) Do the test of the stall identification functions, flap 35 /C0095and non–icing condition:

(a) Set the flap selector to 35 /C0095.

(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.

(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.

(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. 16 /C0095 and 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 0 /C0095and icing condition:

(a) Set the flap selector to 0 /C0095.

(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).

Page 10Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 10 of 24

NOTE: The blue light in the push button switch will go out during the time that the push button switch is pressed.

(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 5.9 ± 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 5.9 ± 1.

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

(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 0 and 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.

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

(e) Pull the control column fully aft.

(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.

Page 11Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 11 of 24 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. 12 /C0095 and 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.

(7) Do the test of the stall warning functions, flap 35 /C0095and icing condition:

(a) Set the flap selector to 35 /C0095.

(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 5.7 /C0095 ± 1/C0095.

(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 5.7 /C0095 ± 1/C0095.

(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 35 /C0095and 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).

Page 12Open in PDF

Service Bulletin 11 July 2014

340–27–121 Page 12 of 24

(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.

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

(e) Pull the control column fully aft.

(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.

(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.

(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. 12 /C0095 and 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.

Pages 13–24 of 24