CIRRUS AIRPLANE MAINTENANCE MANUAL
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- Giles Holland
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1 STALL WARNING SYSTEM 1. DESCRIPTION A. Stall Warning System - Serials 05 thru 2015, 2016 & subs w/o Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack increases and the airplane approaches an aerodynamic stall, the stagnation point moves lower on the leading edge causing low pressure on the upper leading edge to increase. As low pressure passes over the stall warning port located on the leading edge of the right wing, negative pressure is sensed by a pressure switch which activates the stall warning horn. The stall warning horn, located on the top flange of the LH center console rib, is a piezo-ceramic audio indicator. Serials 05 & subs before SB 2X-27-15: When activated, the horn supplies a continuous 9 db, 200 Hz tone. Serials 05 & subs after SB 2X-27-15: When activated, the horn supplies a continuous 95 db, 2000 Hz tone. The pressure switch, located on the mid-console LH side panel, is a normally open, diaphragm-operated switch. Serials 05 thru 1267: The switch is powered by 2 VDC supplied through the 2-amp ANNUNCATOR POWER circuit breaker on the Essential Bus. In the case of emergency procedures that require the MASTER switch to be turned OFF, power is supplied to the stall warning system directly from the airplane battery on the clock circuit. In addition, this provides a ground check of the stall warning system with the power off. In the event of a total electrical failure, power for the stall warning system is supplied by the turn coordinator battery back-up by turning the EMERG. switch ON. Serials 126 thru 2015, 2016 & subs w/o Perspective Avionics: The switch is powered by 2 VDC supplied through the 2-amp STALL WARNING circuit breaker on the Essential Bus. B. Stall Warning System - Serials 2016 & subs w/ Perspective Avionics The airplane uses an electro-pneumatic stall warning system. As the angle of attack increases and the airplane approaches an aerodynamic stall, the stagnation point moves lower on the leading edge causing low pressure on the upper leading edge to increase. As low pressure passes over the stall warning port located on the leading edge of the right wing, negative pressure is sensed by a pressure switch which provides a signal to the avionics system to activate the aural stall warning and enables the Crew Alerting System (CAS) to display a STALL annunciation on the PFD. The pressure switch, located on the mid-console LH side panel, is a normally open, diaphragm-operated switch. The switch is powered by 2 VDC supplied through the 2-amp STALL WARNING circuit breaker on the Essential Bus. Page 1 15 Jun 20
2 2. MAINTENANCE PRACTICES A. Stall Warning Horn - Serials 05 thru 2015, 2016 & subs w/o Perspective Avionics (See Figure 1) (1) Removal - Stall Warning Horn (a) Remove glareshield. (Refer to 25-) (b) Remove MFD (Refer to 31-60). (c) Disconnect stall warning horn electrical connector. (d) Serials 05 & subs before SB 2X-27-15: Remove screws, washers, and nuts securing horn to console rib. Remove horn from airplane. (e) Serials 05 & subs after SB 2X-27-15: Remove bolt and nut securing horn assembly mounting bracket to console rib. Remove horn assembly from airplane. (2) Installation - Stall Warning Horn (a) Serials 05 & subs before SB 2X-27-15: Position horn to console rib and secure with screws, washers, and nuts. (b) Serials 05 & subs after SB 2X-27-15: Position horn assembly mounting bracket to console rib at a 5 o ±5 o angle and secure with bolt and nut. (c) Connect stall warning horn electrical connector. (d) Install MFD. (Refer to 31-60) (e) Install glareshield. (Refer to 25-) (f) Perform Stall Warning Operational Check - Ground. (Refer to ) (g) Perform Stall Warning Operational Check - Flight. (Refer to ) Page 2 15 Jun 20 Serials 05 thru 2015, 2016 & subs w/o Perspective Avionics
3 B. Stall Warning Pressure Switch (See Figure 1) (1) Removal - Stall Warning Pressure Switch (a) Switch AVIONICS and MASTER switches to OFF position. (b) Pull ANNUNCIATOR POWER circuit breaker. (c) Remove LH mid-console circuit breaker trim panel. (d) Open circuit breaker panel. (e) Disconnect pressure switch electrical connector. (f) Disconnect stall warning line from pressure switch. (g) Remove screws, washers, and nuts securing pressure switch to console. Remove pressure switch from airplane. (2) Installation - Stall Warning Pressure Switch (a) Position pressure switch on console and install screws, washers, and nuts. (b) Connect stall warning line to pressure switch. (c) Connect electrical leads to pressure switch. (d) Close circuit breaker panel. (e) Install LH mid-console circuit breaker trim panel. (f) Reset ANNUNCIATOR POWER circuit breaker. (g) Perform Stall Warning Operational Check - Ground. (Refer to ) (h) Perform Stall Warning Operational Check - Flight. (Refer to ) (3) Inspection/Check - Stall Warning Operational Check - Ground (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Suction Cup - Any Source Application of negative pressure. (b) (c) (d) (e) (f) (g) (h) Pull STARTER and FUEL PUMP circuit breakers. Set BAT 1 and AVIONICS switches to ON positions. On RH wing leading edge, clean area surrounding stall warning port. Moisten suction cup and firmly press cup over stall warning port. Activate stall warning pressure switch by sharply pulling suction cup directly away from stall warning port. Verify horn sounds audible warning signal. Set BAT 1 and AVIONICS switches to OFF positions. Reset STARTER and FUEL PUMP circuit breakers. Page 3
4 () Inspection/Check - Stall Warning Operational Check - Flight WARNING: The following Adjustment/Test must be performed by a Cirrus Design authorized pilot. (a) Remove access cap covering stall warning pressure switch located on lower portion of the left mid-console circuit breaker trim panel. (b) Perform Stall Warning Operational Check - Ground. (Refer to ) (c) Place airplane in stall attitude. (d) Record airplane speed that stall warning signal sounds. (e) Record airplane speed that stall occurred. (f) Stall warning signal should sound 5 to KIAS prior to stall. (g) If necessary, adjust stall warning pressure switch until stall warning signal sounds 5 to KIAS prior to stall. 1 Rotating the adjustment screw 1 full turn clockwise will raise the speed at which the stall warning horn sounds by approximately 2 knots. 2 Rotating the adjustment screw 1 full turn counterclockwise will lower the speed at which the stall warning horn sounds by approximately 2 knots. Page
5 CENTER CONSOLE 1 1 Serials 05 & subs w/o Perspective Avionics before SB 2X º ±5º Serials 05 & subs w/o Perspective Avionics after SB 2X LH INBOARD CONSOLE RIB 9 13 FUSELAGE Serials 2016 & subs w/ Perspective Avionics FUSELAGE 12 Serials 05 & subs w/o Perspective Avionics NOTE CABIN FLOOR Position bracket to rib at a 5º ±5º angle to the rib, and secure using bolt and nut. 7 9 LEGEND 1. Stall Warning Horn 2. Screw 3. Washer. Nut 5. Electrical Connector 6. Electro-Pneumatic Switch 7. Spring Clamp. Pneumatic Line 9. Tee Fitting. Tie Down 11. Fitting 12. Plug 13. Grommet 1. Bolt SR20_MM27_1172F Figure 1 Stall Warning System Installation (Sheet 1 of 2) Page 5
6 STALL WARNING ENCLOSURE Serials 05 thru 177, 179 thru LEADING EDGE PANEL Serials 17, 16 & subs. NOTE If thread relief is present on forward threaded end of bulkhead fitting, trim at thread relief to secure fitting flush to stall warning enclosure. LEGEND. Nut. Pneumatic Line. Tie Down 15. Bulkhead Union 16. Nylon Insert 17. O-Ring 1. Olive SR20_MM27_2760B Page 6 Figure 1 Stall Warning System Installation (Sheet 2 of 2)
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