A-10A Flight Manual

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_ _ - ... , .... ' '" '" - , "' ... ' ' , if - , , ... .... ' , / , , ... / l> CAM & FOlLOIVfR SIMULATE ... __ / TRIM SWITCHES (SEE 0. �- - --\ �? � y .. , .... Cj - -l '.... - , NOTE THAT THEARETWOPOWERED ELIVATORBY ACTUATORS IHYDRAULI NDEPENDENTC PRESSURE SOURCES OF .... -"' ,'" � J ARTIACISPRIAL FEELNG LOADED DEVICE; ... � -- - - - ... POSI T - - � NOSE ON ] PWR EMER8 � � DfVlNCOfE ACTUATOR/ OVERRIDE NOSE UP TRIM ACTUATOR �� � 'J ,>-TRIM TAB, 02; " CONTROL STICK If M TABS WITPRESS IS LOST, HWillElECTRO-MECH TRIACTUATORS BY NORMBElOW)OR [MERBE CONTROLlED CROSSOVERS -tIEXCESSI THER VORE LOAD BOTH, WILEAVI LL SHEAR AT NG OPPOSITE SIDE FREE I ------ � {� • 'I'@J � FEEl.

D u r i ng braking t h e system releases brake pressure t o b o t h wheels of which wheel experi ences the s k i d . The u n t i l i t senses that wheel c o n t i nu e s t o h as decreased to 10 k no t s . event that one o f t h e s quat switches fail s t o a fter touchdown, normal s k i d control i s 1 5 knots. to T h e a n t i - s k i d caution ANTI-SKI D . The • I nd icates t h e a n ti-sk i d t h e l a n d i ng gear h a n d le • I ndicates a nt i - s k i d system h a s deactivated i n r e s p o n s e t o a EMERGENCY DISCONNECT LEVER T h e emergency d i sc o nnect l ocated on the forward side below t h e gri p .

SECOND orrENT : CONTINUOUS IGN IT! J INS MARKIUPOAH @] (NOTt Il _ _ _ $ASIANTI-SKID ";ER _ _ DISCONNECT LEVER \"VIPONS RUEASE PoIR REFUEl DISCONNECT/RESET MISSILE TRACK � _ • TIME-SHARED FUNCTIONS NOT E ' I. AIRBORNE FUNCTION ONLY. , 00. -J, Figure 1 - 1 7 240 KIAS, available powered rudder travel i s auto­ matically reduced from ± 2 5 ° to ± 8 °. If aircraft speed increases through approximately 240 K1AS with rudder inputs greater than ± 8 °, rudder pedal "kicks" or "thumps" may be fell as the rudder returns \0 8°, Independent SAS signals arc electrically transmitted 10 each rudder actuator to provide automatic turn coordination.

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