P.O. BOX 790490 • SAN ANTONIO, TEXAS 78279-0490 • (210) 824-9421

SUBJECT: REVISION 13 TO SA227-TT FAIRCHILD 312 POH/AFM

TO: ALL OPERATORS AND POH/AFM MANAGERS OF THE 12,500 POUND FAIRCHILD 

312

1. Attached is Revision 13 to Sections 0 and 3 of your POH/AFM.

2. File this transmittal letter in your AFM binder at the location most convenient to you.
P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421
FAA APPROVED: OCT 31/85 0-iii

312

SA227-TT FAIRCHILD 300 12,500 LBS

LIST OF EFFECTIVE PAGES

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

FLIGHT MANUAL

LIST OF EFFECTIVE PAGES

SECTION 0

PAGE DATE PAGE DATE

SECTION 1

PAGE DATE PAGE DATE

SECTION 2

PAGE DATE PAGE DATE

Title ......................................................MAR 28/96

0-i..........................................................OCT 31/85

0-ii .........................................................OCT 31/85

0-iii ....................................................... DEC 09/14

0-iv ....................................................... DEC 09/14

0-v......................................................... JUN 02/00

0-vi ....................................................... NOV 18/97

0-vii ...................................................... NOV 18/97

0-viii ..................................................... NOV 18/97

0-ix ........................................................ JUN 24/88

0-x........................................................ NOV 18/99

0-xi ....................................................... DEC 09/14

0-xii .......................................................MAY 11/99

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14

1-i..........................................................OCT 31/85

1-ii .........................................................OCT 31/85

1-1 ........................................................OCT 31/85

1-2 ........................................................OCT 31/85

1-3 ........................................................OCT 31/85

1-4 ........................................................OCT 31/85

1-5 ........................................................OCT 31/85

1-6 ........................................................OCT 31/85

1-7 ........................................................OCT 31/85

1-8 ........................................................ JUN 24/88

1-9 ........................................................OCT 31/85

1-10 ......................................................OCT 31/85

1-11 .......................................................OCT 31/85

1-12 ......................................................OCT 31/85

1-13 ......................................................OCT 31/85

1-14 ......................................................OCT 31/85

1-15 ......................................................OCT 31/85

1-16 ......................................................OCT 31/85

1-17 ......................................................OCT 31/85

1-18 ......................................................OCT 31/85

2-i......................................................... DEC 07/07

2-ii ......................................................... JUN 02/00

2-1 ........................................................ JUN 24/88

2-2 ........................................................ JUN 24/88

2-3 ....................................................... DEC 07/07

2-4 ....................................................... DEC 29/86

2-5 ........................................................MAY 13/97

2-6 ........................................................OCT 31/85

2-7 ........................................................OCT 31/85

2-8 ........................................................OCT 31/85

2-9 .......................................................OCT 31/85

2-10 ......................................................OCT 31/85

2-11 ...................................................... DEC 29/86

2-12 ..................................................... DEC 29/86

2-13 ......................................................OCT 31/85

2-14 ......................................................OCT 31/85

2-15 ......................................................OCT 31/85

2-16 ......................................................OCT 31/85

2-17 ......................................................OCT 31/85

2-18 ......................................................OCT 31/85

2-19 ......................................................OCT 31/85

2-20 ......................................................OCT 31/85

2-21 ..................................................... DEC 29/86

2-22 ......................................................OCT 31/85

2-23 ..................................................... NOV 18/97

2-24 ..................................................... NOV 18/97

2-25 ...................................................... JUN 02/00

2-26 ...................................................... JUN 02/00

2-27 ......................................................OCT 31/85

2-28 ......................................................OCT 31/85

2-29 ......................................................OCT 31/85

2-30 ...................................................... JUN 24/88
0-iv

312

FAA APPROVED: OCT 31/85

SA227-TT FAIRCHILD 300 12,500 LBS

LIST OF EFFECTIVE PAGES

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

FLIGHT MANUAL

LIST OF EFFECTIVE PAGES (continued)

SECTION 3

PAGE DATE PAGE DATE

SECTION 3A

PAGE DATE PAGE DATE

3-i......................................................... DEC 09/14 

3-ii ........................................................ DEC 09/14

3-1 ........................................................MAY 11/99

3-2 ........................................................MAY 11/99

3-3 ....................................................... DEC 09/14 

3-4 ........................................................APR 28/00

3-5 ....................................................... DEC 09/14

3-6 ....................................................... DEC 09/14

3-7 ....................................................... DEC 09/14

3-8 ....................................................... DEC 09/14

3-9 ....................................................... DEC 09/14

3-10 ..................................................... DEC 09/14

3-11 ...................................................... DEC 09/14

3-12 ..................................................... DEC 09/14

3-13 ..................................................... DEC 09/14

3-14 ..................................................... DEC 09/14

3-15 ..................................................... DEC 09/14

3-16 ..................................................... DEC 09/14

3-17 ..................................................... DEC 09/14

3-18 ..................................................... DEC 09/14

3-19 ..................................................... DEC 09/14

3-20 ..................................................... DEC 09/14

3-21 ..................................................... DEC 09/14

3-22 ..................................................... DEC 09/14

3-23 ..................................................... DEC 09/14

3-24 ..................................................... DEC 09/14

3-25 ..................................................... DEC 09/14

3-26 ..................................................... DEC 09/14

3-27 ..................................................... DEC 09/14

3-28 ..................................................... DEC 09/14

3-29 ..................................................... DEC 09/14

3-30 ..................................................... DEC 09/14

3-31 ..................................................... DEC 09/14

3-32 ..................................................... DEC 09/14

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14

3A-i ...................................................... DEC 07/07

3A-ii ......................................................OCT 31/85

3A-1 ......................................................OCT 31/85

3A-2 ......................................................OCT 31/85

3A-3 ...................................................... JUN 24/88

3A-3A ................................................... DEC 07/07

3A-3B................................................... DEC 07/07

3A-4 ......................................................OCT 31/85

3A-5 ..................................................... MAR 03/89

3A-6 ......................................................OCT 31/85

3A-7 ..................................................... NOV 18/97

3A-8 ...................................................... JUN 02/00 

3A-9 ..................................................... NOV 18/97

3A-10 ................................................... NOV 18/97

3A-11 ....................................................OCT 31/85

3A-12 ....................................................OCT 31/85

3A-13 ....................................................OCT 31/85

3A-14 ....................................................OCT 31/85

3A-15 ....................................................OCT 31/85

3A-16 ....................................................OCT 31/85

3A-17 ....................................................OCT 31/85

3A-18 ....................................................OCT 31/85

3A-19 ....................................................OCT 31/85

3A-20 ....................................................OCT 31/85

3A-21 ....................................................OCT 31/85

3A-22 ....................................................OCT 31/85

3A-23 ....................................................OCT 31/85

3A-24 ................................................... MAR 03/89

3A-25 ....................................................OCT 31/85

3A-26 ................................................... MAR 03/89

3A-27 ....................................................OCT 31/85

3A-28 ....................................................OCT 31/85

3A-29 ....................................................OCT 31/85

3A-30 ....................................................OCT 31/85

3A-31 ....................................................OCT 31/85

3A-32 ....................................................OCT 31/85

0-xii

312

FAA APPROVED: OCT 31/85

SA227-TT FAIRCHILD 300 12,500 LBS

LIST OF REVISIONS

LIST OF REVISIONS (continued)

Revision Pages FAA Approved 

Number Affected Description Signature Date

A black bar in the margin of a revised page shows the current change.

FAA APPROVED: MAY 11/99
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES

REVISED: DEC 09/14

3-i

312

SA227-TT FAIRCHILD 300 12,500 LBS

TABLE OF CONTENTS

EMERGENCY PROCEDURES

ITEM PAGE

Introduction ............................................................................................................................................ 3-1

Annunciator Panel ................................................................................................................................. 3-2

Engine Fire On Ground ......................................................................................................................... 3-3

Engine Fire In Flight .............................................................................................................................. 3-3

Out-of-Trim Warning .............................................................................................................................. 3-4

Engine Failure During Takeoff – Takeoff Aborted .................................................................................. 3-4

Engine Failure During Takeoff – Takeoff Continued at or Above VR ...................................................... 3-5

Engine Failure During Flight .................................................................................................................. 3-6

Engine - Propeller Uncoupling ............................................................................................................... 3-7

Airstart ................................................................................................................................................... 3-7

Infl ight Relight ........................................................................................................................................ 3-8

Single Engine Landing........................................................................................................................... 3-9

 After Touchdown ........................................................................................................................... 3-9

Single Engine Go-Around .................................................................................................................... 3-10

Engine Control Malfunction ................................................................................................................. 3-10 

No Response to Power Lever Movement .............................................................................................3-11

Battery Temperature Caution/Warning Lights On ................................................................................ 3-12

 Amber Light Illuminates .............................................................................................................. 3-10

 Red Warning Light Illuminates (Any Phase of Operations) ........................................................ 3-12 

Double Generator Failure .................................................................................................................... 3-13

Double Engine Failure (Restarts/Relights Unsuccessful) .................................................................... 3-13

Total Electrical Failure ......................................................................................................................... 3-14

Smoke In Aircraft ................................................................................................................................. 3-15

Wheelwell and Wing Overheat Warning Light On ............................................................................... 3-16

 Steady Light ................................................................................................................................ 3-16

 Flashing Light ............................................................................................................................. 3-16

Cabin Pressurization Malfunctions ...................................................................................................... 3-17

 Low Pressure Malfunction .......................................................................................................... 3-17

 High Pressure Malfunction ......................................................................................................... 3-17 

 Excessive Rate of Pressurization ............................................................................................... 3-18

Emergency Descent Procedure........................................................................................................... 3-18

Cabin Door Warning Light On ............................................................................................................. 3-19

 Prior to Takeoff ............................................................................................................................ 3-19

 In Flight ....................................................................................................................................... 3-19

Hydraulic System Failure..................................................................................................................... 3-20

Landing Gear Emergency Extension ................................................................................................... 3-21

Gear Up Landings ............................................................................................................................... 3-23

 Landing with All Three Gear Up .................................................................................................. 3-24

 Landing with Nose Gear Up ....................................................................................................... 3-24

 Landing with Nose Gear and One Main Gear Extended ............................................................ 3-24

Stabilizer Trim Malfunctions................................................................................................................. 3-25

 Stabilizer Trim System Runaway ................................................................................................ 3-25

 Pilot’s Trim System Inoperative .................................................................................................. 3-25

 Copilot’s Trim System Inoperative .............................................................................................. 3-25
3-ii EMERGENCY PROCEDURES

312

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14

SA227-TT FAIRCHILD 300 12,500 LBS

TABLE OF CONTENTS (continued)

EMERGENCY PROCEDURES

ITEM PAGE

 Both Pilot’s and Copilot’s Trim Systems Inoperative .................................................................. 3-25

 Go-Around with Stabilizer Trim Inoperative ................................................................................ 3-26

Stability Augmentation and Stall Avoidance System

 (SAS2

) Malfunctions .................................................................................................................... 3-27

 SAS Fault Light On In Flight ....................................................................................................... 3-27

 SAS2 Malfunction – Nose Down ................................................................................................. 3-28

 Aural Stall Warning at Speeds Well in Excess of Normal Stall Warning Speeds ....................... 3-29

Yaw Damper Malfunctions ................................................................................................................... 3-29

 Power Failure ............................................................................................................................. 3-29

 Electrical Servo Runaway ........................................................................................................... 3-29

Emergency Exit ................................................................................................................................... 3-30

Nose Wheel Steering Electrical Malfunction........................................................................................ 3-30

Nose Wheel Steering Hydraulic Malfunction ....................................................................................... 3-31

 Nose Steer Fail Light ON ............................................................................................................ 3-31
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-3

312

SA227-TT FAIRCHILD 300 12,500 LBS

ENGINE FIRE ON GROUND

1. ENGINE STOP AND FEATHER CONTROL (affected engine) ........................................... PULL

 2. ENGINE STOP BUTTON (affected engine) ...................................................................... PRESS

 3. FUEL SHUTOFF SWITCH (affected engine) ................................................................ CLOSED

 4. HYDRAULIC SHUTOFF SWITCH (affected engine) ..................................................... CLOSED

 5. FIRE EXTINGUISHER SWITCH (affected engine) ........................................................... PRESS

 6. Generator Switch (affected engine) ......................................................................................... OFF

NOTE

Use of start test with respective generator switch ON may cause 

a battery fault and subsequent loss of ability to motor the engine.

 7. Starter Test Switch (affected engine) ............................................................................... ENGAGE

 8. Fuel Boost Pump Switch (affected engine) .............................................................................. OFF

 9. Affected Engine .................................................................MOTOR UNTIL ENGINE IS CLEARED

ENGINE FIRE IN FLIGHT

WARNING

IN THE EVENT OF AN ENGINE FAILURE OR POWER LOSS, THE 

ENGINE NEGATIVE TORQUE SYSTEM (NTS) ONLY PROVIDES 

PARTIAL DRAG REDUCTION BUT NOT TO THE EXTENT OF A 

FULLY FEATHERED PROPELLER. 

PILOT MUST TAKE ACTION TO FULLY FEATHER THE PROPELLER (ON THE AFFECTED ENGINE) TO REDUCE PROPELLER 

DRAG.

 1. ENGINE STOP AND FEATHER CONTROL (affected engine) ........................................... PULL

 2. FUEL SHUTOFF SWITCH (affected engine) ................................................................ CLOSED

 3. HYDRAULIC SHUTOFF SWITCH (affected engine) ..................................................... CLOSED

 4. FIRE EXTINGUISHER SWITCH (affected engine) ........................................................... PRESS

 5. Fuel Boost Pump Switch (affected engine) .............................................................................. OFF

 6. Generator Switch (affected engine) ......................................................................................... OFF

 *7. Bleed Air Switch (affected engine) ........................................................................................... OFF

 8. Power Lever (operating engine) .............................................................................AS REQUIRED

 *9. Bleed Air (operating engine) ...................................................................................AS REQUIRED

NOTE

If the 100% torque limit is not being developed and bleed air is 

on, increased power may be obtained by selecting bleed air off.

 10. Trim .........................................................................................................................AS REQUIRED

 11. Generator (operating engine) ...................................................................... 300 AMPS MAXIMUM

 *12. Propeller Synchrophaser Switch (if installed) .............................................TAKEOFF & LANDING

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-4

312

FAA APPROVED: OCT 31/85

OUT-OF-TRIM WARNING

 AURAL OUT-OF-TRIM WARNING ..................................................................ABORT TAKEOFF

ENGINE FAILURE DURING TAKEOFF – TAKEOFF ABORTED

1. POWER LEVERS .................................................................................................. GROUND IDLE

NOTE

Retard power levers to ground idle as directional control 

permits. Retarding the power lever of the operating engine from 

fl ight idle to ground idle will cause the airplane to yaw toward 

the operating engine.

2. BRAKES ................................................................................................................ AS REQUIRED

 3. Nose Wheel Steering ..............................................................................................AS REQUIRED

 4. Reverse Thrust (operating engine) .........................................................................AS REQUIRED

CAUTION

REVERSE THRUST ON THE OPERATING ENGINE WILL 

CAUSE A YAWING MOMENT TOWARD THE OPERATING 

ENGINE WHICH IS PROPORTIONAL TO THE AMOUNT OF 

REVERSE THRUST APPLIED. ON WET OR ICY RUNWAYS, 

IT IS POSSIBLE TO APPLY MORE ASYMMETRIC REVERSE 

THRUST THAN CAN BE COUNTERACTED BY OPPOSITE BRAKE, 

RUDDER, AND NOSE WHEEL STEERING.

 5. Engine Stop and Feather Control (failed engine) ...................................................................PULL

 6. Engine Clean Up Procedure (failed engine)

 a. Fuel shutoff switch ......................................................................................................CLOSED

 b. Hydraulic shutoff switch ..............................................................................................CLOSED

 c. Fuel boost pump switch ..................................................................................................... OFF

 d. Generator switch ................................................................................................................ OFF

 *e. Bleed air switch .................................................................................................................. OFF

 7. AWI Switch .............................................................................................................................. OFF

FAA APPROVED: OCT 31/85

REVISED: APR 28/00
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-5

312

SA227-TT FAIRCHILD 300 12,500 LBS

ENGINE FAILURE DURING TAKEOFF – TAKEOFF CONTINUED AT OR ABOVE VR

WARNING

IN THE EVENT OF AN ENGINE FAILURE OR POWER LOSS, THE 

ENGINE NEGATIVE TORQUE SYSTEM (NTS) ONLY PROVIDES 

PARTIAL DRAG REDUCTION BUT NOT TO THE EXTENT OF A 

FULLY FEATHERED PROPELLER. 

PILOT MUST TAKE ACTION TO FULLY FEATHER THE PROPELLER (ON THE AFFECTED ENGINE) TO REDUCE PROPELLER 

DRAG.

1. POWER LEVER (operating engine) ..................................................... SET MAXIMUM POWER

NOTE

• Commanding high propeller blade angle by keeping the power 

lever of the inoperative engine well forward will reduce windmilling 

propeller drag in the event that NTS failure accompanies engine 

failure.

• Set 650oC EGT or 100% torque, whichever occurs fi rst, during takeoff. If the 100% torque limit is not being developed and 

bleed air is ON, increased power may be obtained by selecting 

bleed air OFF.

*2. LANDING GEAR (after liftoff) ...................................................................................................UP

WARNING

IF THE ENGINE FAILURE IS ACCOMPANIED BY A LEFT ESSENTIAL BUS FAILURE (AS INDICATED BY LOSS OF POWER 

TO THE GEAR POSITION INDICATOR) THE LANDING GEAR 

WILL NOT RETRACT UNTIL THE LANDING GEAR CONTROL 

ESSENTIAL BUS POWER TRANSFER IS MOVED TO THE RIGHT 

BUS POSITION.

*3. FLAPS ........................................................................................................................................UP

 4. ENGINE STOP AND FEATHER CONTROL (failed engine) ................................................ PULL

 5. AIRSPEED .....................................................SINGLE ENGINE BEST RATE OF CLIMB SPEED

(SEE FIGURE 5-51)

6. Engine Clean Up Procedure (failed engine)

 a. Fuel shutoff switch ......................................................................................................CLOSED

 b. Hydraulic shutoff switch ..............................................................................................CLOSED

 c. Fuel boost pump switch ..................................................................................................... OFF

 d. Generator switch ................................................................................................................ OFF

 *e. Bleed air switch .................................................................................................................. OFF

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-6

312

FAA APPROVED: OCT 31/85

ENGINE FAILURE DURING TAKEOFF – TAKEOFF CONTINUED AT OR ABOVE VR (continued)

 7. Power Lever (operating engine) .............................................................................AS REQUIRED

 8. Trim .........................................................................................................................AS REQUIRED

 9. Generator (operating engine) ...................................................................... 300 AMPS MAXIMUM

 *10. Propeller Synchrophaser Switch (if installed) .............................................TAKEOFF & LANDING

 11. AWI Switch .............................................................................................................AS REQUIRED

ENGINE FAILURE DURING FLIGHT

WARNING

IN THE EVENT OF AN ENGINE FAILURE OR POWER LOSS, THE 

ENGINE NEGATIVE TORQUE SYSTEM (NTS) ONLY PROVIDES 

PARTIAL DRAG REDUCTION BUT NOT TO THE EXTENT OF A 

FULLY FEATHERED PROPELLER. 

PILOT MUST TAKE ACTION TO FULLY FEATHER THE PROPELLER (ON THE AFFECTED ENGINE) TO REDUCE PROPELLER 

DRAG.

1. ENGINE STOP AND FEATHER CONTROL (failed engine) ................................................ PULL

 2. Engine Clean Up Procedure (failed engine)

 a. Fuel shutoff switch ......................................................................................................CLOSED

 b. Hydraulic shutoff switch ..............................................................................................CLOSED

 c. Fuel boost pump switch ..................................................................................................... OFF

 d. Generator switch ................................................................................................................ OFF

 *e. Bleed air switch .................................................................................................................. OFF

 3. Power Lever (operating engine) .............................................................................AS REQUIRED

 *4. Bleed Air (operating engine) ...................................................................................AS REQUIRED

NOTE

If the 100% torque limit is not being developed and bleed air is 

on, increased power may be obtained by selecting bleed air off.

 5. Trim .........................................................................................................................AS REQUIRED

 6. Generator (operating engine) ...................................................................... 300 AMPS MAXIMUM

 *7. Propeller Synchrophaser Switch (if installed) .............................................TAKEOFF & LANDING

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-7

312

SA227-TT FAIRCHILD 300 12,500 LBS

ENGINE - PROPELLER UNCOUPLING

WARNING 

• IN THE EVENT OF ENGINE FAILURE IN CONJUNCTION 

WITH ENGINE UNCOUPLING, REDUCE WINDMILLING 

DRAG AS FOLLOWS:

• IF AN UNCOUPLING EVENT OCCURS WHERE THE ENGINE 

IS OPERATING AND THE PROPELLER IS STOPPED AND 

FEATHERED, RETARDING THE POWER LEVER TO FLIGHT 

IDLE MAY RESULT IN UNFEATHERING AND SUBSEQUENT 

ROTATION OF THE PROPELLER. IF THIS OCCURS, ADVANCE 

THE POWER LEVER TO MAXIMUM POWER POSITION.

• IN THE EVENT OF AN ENGINE WITH AN NTS AND/OR FEATHER VALVE MALFUNCTION, SETTING THE ASSOCIATED 

POWER LEVERS FULL FORWARD WILL DRIVE THE PROPELLER BLADES TOWARD THE FEATHER POSITION YIELDING A 

LOWER WINDMILLING PROPELLER DRAG AND PROPELLER 

SHAFT SPEED.

AIRSTART

CAUTION

IF AN ENGINE HAS BEEN SHUT DOWN BECAUSE OF AN OBVIOUS FAILURE, AS INDICATED BY THE ENGINE INSTRUMENTS 

OR EXCESSIVE VIBRATION, AN AIRSTART SHOULD NOT BE 

ATTEMPTED. AIRSTART FOLLOWING INTENTIONAL ENGINE 

SHUTDOWN IS COVERED IN SECTION 3A, ABNORMAL PROCEDURES.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-8

312

FAA APPROVED: OCT 31/85

INFLIGHT RELIGHT

CAUTION

• THIS PROCEDURE IS INTENDED FOR USE DURING FLIGHT 

ONLY.

• ATTEMPTED USE OF THIS PROCEDURE WHILE ON THE 

GROUND WITH LIMITED AIRFLOW THROUGH THE ENGINE 

COULD RESULT IN ENGINE OVER-TEMPERATURES.

• THIS PROCEDURE IS INTENDED FOR USE ONLY WHEN 

THE REASON FOR THE INADVERTENT FLAMEOUT IS 

KNOWN WITH CERTAINTY AND WHEN THE PILOT IS CERTAIN 

THAT A RELIGHT WILL NOT AGGRAVATE THE CONDITION.

 1. Power Lever .......................................APPROXIMATELY 1/4 INCH FORWARD OF FLIGHT IDLE

(UNTIL LANDING GEAR WARNING HORN IS SILENCED)

 2. Speed Lever .................................................................................... APPROXIMATELY 96% RPM

 3. Airspeed ......................................................................................... BETWEEN 180 AND 100 KIAS

 4. RPM ......................................................................................................BETWEEN 60% AND 10%

 5. Engine Start Button .................................................................................. PRESS MOMENTARILY

NOTE

• Press the start button in only long enough to obtain ignition 

and fuel fl ow and subsequent light-off.

• If RPM has decayed below 10%, the start button will have to 

be held in while the unfeathering pump drives the propeller blades 

to fi ner pitch and RPM increases to above 10%. Ignition, fuel fl ow, 

and light-off should then occur.

• Engine relight will not occur if the SRL computer speed switch function has failed or if the SRL– ∆ P/P switch is in the OFF position.

 6. EGT ............................................................. MONITOR (770oC MAXIMUM FOR ONE SECOND)

 7. RPM ............................................................................................................................ STABILIZED

 8. SRL OFF Light ............................................................................................................CHECK OFF

 9. Power .........................................................................................................RESET AS REQUIRED

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-9

312

SA227-TT FAIRCHILD 300 12,500 LBS

SINGLE ENGINE LANDING

WARNING

IN THE EVENT OF AN ENGINE FAILURE OR POWER LOSS, THE 

ENGINE NEGATIVE TORQUE SYSTEM (NTS) ONLY PROVIDES 

PARTIAL DRAG REDUCTION BUT NOT TO THE EXTENT OF A 

FULLY FEATHERED PROPELLER. 

PILOT MUST TAKE ACTION TO FULLY FEATHER THE PROPELLER (ON THE AFFECTED ENGINE) TO REDUCE PROPELLER 

DRAG.

 *1. No Smoking – Fasten Seat Belt Sign ........................................................................................ ON

 2. Fuel Balance .....................................................CHECK (500 POUNDS MAXIMUM IMBALANCE)

NOTE

If excess fuel imbalance is indicated on fuel quantity gauge, 

confi rm by checking trim position as gauge may be incorrect. If excess 

imbalance exists, open fuel cross fl ow valve to balance fuel 

within tolerances.

 3. Fuel Crossfl ow Switch ......................................................... OPEN IF REQUIRED TO BALANCE,

THEN CLOSED

 4. Cabin Differential Pressure ................................................................................................... ZERO

 5. Electrical Load ......................................................................TURN OFF NONESSENTIAL ITEMS

 6. Speed Lever (operating engine) ................................................................................... HIGH RPM

 7. Flaps ............................................................................................DO NOT EXTEND BEYOND 1/2

 UNTIL LANDING IS ASSURED

 8. Landing Gear ................................................................ EXTEND WHEN LANDING IS ASSURED

 9. Nose Wheel Steering ......................................................................................................... ARMED

 10. Ignition Mode Switches ...........................................................................................AS REQUIRED

AFTER TOUCHDOWN

 1. Brakes .....................................................................................................................AS REQUIRED

 2. Nose Wheel Steering ..............................................................................................AS REQUIRED

 3. Power Levers ......................................................................................................... GROUND IDLE

NOTE

Retard power levers to ground idle as directional control 

permits. Retarding the power lever of the operating engine from 

fl ight idle to ground idle will cause the airplane to yaw toward 

the operating engine.

 4. Reverse Thrust .......................................................................................................AS REQUIRED

See CAUTION Next Page

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-10

312

FAA APPROVED: OCT 31/85

SINGLE ENGINE LANDING (continued)

CAUTION

REVERSE THRUST ON THE OPERATING ENGINE WILL 

CAUSE A YAWING MOMENT TOWARD THE OPERATING ENGINE 

WHICH IS PROPORTIONAL TO THE AMOUNT OF REVERSE 

THRUST APPLIED. ON WET OR ICY RUNWAYS, IT IS POSSIBLE 

TO APPLY MORE ASYMMETRIC REVERSE THRUST THAN CAN 

BE COUNTERACTED BY OPPOSITE BRAKE, RUDDER, AND 

NOSE WHEEL STEERING.

SINGLE ENGINE GO-AROUND

WARNING

IN THE EVENT OF AN ENGINE FAILURE OR POWER LOSS, THE 

ENGINE NEGATIVE TORQUE SYSTEM (NTS) ONLY PROVIDES 

PARTIAL DRAG REDUCTION BUT NOT TO THE EXTENT OF A 

FULLY FEATHERED PROPELLER. 

PILOT MUST TAKE ACTION TO FULLY FEATHER THE PROPELLER (ON THE AFFECTED ENGINE) TO REDUCE PROPELLER 

DRAG.

 1. Power ......................................................................................................................AS REQUIRED

 2. Landing Gear ..............................................................................................................................UP

 3. Flaps ................................................................................................. RETRACT IN INCREMENTS

 4. Airspeed ...........................................................SINGLE ENGINE BEST RATE OF CLIMB SPEED

(SEE FIGURE 5-56)

 *5. Bleed Air Switch ....................................................................................................................... OFF

 6. Engine Anti-Ice ......................................................................................OFF UNLESS REQUIRED

ENGINE CONTROL MALFUNCTION

In the event there is an indication of improper operation of a fuel control or propeller control, it is recommended that the affected engine be shut down and a single engine landing accomplished.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-11

312

SA227-TT FAIRCHILD 300 12,500 LBS

NO RESPONSE TO POWER LEVER MOVEMENT

If either engine (or both) exhibits a lack of response to the power lever after extended operation at high 

altitude with OAT below freezing, the cause may be ice blockage of the PT2 inlet sensor probe. In certain 

fl ight conditions, when engine anti-ice would not normally be ON, probe icing can occur even though visible moisture is not present. If lack of power lever response is observed, the following procedure should 

be accomplished:

 1. Ignition Switches ................................................................................................................... CONT

 2. Engine Heat Switch(es) ............................................................................ENGINE & PROP HEAT

This will introduce anti-icing air to the sensors (as well as the engine inlet) and normal power lever response 

should return within approximately 3 minutes.

After the condition has cleared and normal operation is observed, anti-ice and ignition can again be turned 

OFF.

 1. Engine Heat Switch(es) ..........................................................................................AS REQUIRED

 2. Ignition Switches ....................................................................................................................AUTO

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-12

312

FAA APPROVED: OCT 31/85

BATTERY TEMPERATURE CAUTION/WARNING LIGHTS ON

NOTE

• The amber caution light illuminates if either battery temperature 

reaches 120 degrees, plus or minus 3 degrees F.

• The red warning light illuminates if either battery temperature 

reaches 150 degrees, plus or minus 3 degrees F.

AMBER LIGHT ILLUMINATES

 1. Before Engine Start ..................................................................DO NOT MAKE BATTERY START

NOTE

Either obtain GPU or wait until the batteries have cooled.

 2. After Engine Start ............................................................. MONITOR BATTERY TEMPERATURE

 INDICATOR AND GENERATOR LOADS

 3. Temperature Increasing to 140 Degrees F ..................................................... DO NOT TAKE OFF

 4. Temperature Increasing Above 140 Degrees F .......................................... AFFECTED BATTERY

SWITCH OFF

 5. In Flight .........................................................MONITOR BATTERY TEMPERATURE INDICATOR

 AND GENERATOR LOADS/AFFECTED BATTERY

SWITCH OFF IF REQUIRED

RED WARNING LIGHT ILLUMINATES (Any Phase of Operations)

 1. Affected Battery Switch ............................................................................................................ OFF

 2. BAT DISC Light (affected battery) ................................................................................ CHECK ON

 3. Battery Temperature Indicator ...................................................................... MONITOR CLOSELY

WARNING

• WHEN ON GROUND, SHUT DOWN ENGINES AND INSPECT 

AFFECTED BATTERY AS SOON AS POSSIBLE.

• WHEN IN FLIGHT AND BATTERY TEMPERATURE(S) CONTINUE TO RISE AFTER DISCONNECT, LAND AS SOON AS 

PRACTICABLE AND INSPECT BATTERY.

• TAKEOFF AFTER A BATTERY TEMPERATURE WARNING 

(RED LIGHT) ILLUMINATES IS PROHIBITED UNTIL THE 

CAUSE OF THE OVERHEAT WARNING IS CORRECTED.

NOTE

A battery temperature red warning light caused by a thermal 

runaway may sometimes be verifi ed by observing sustained 

and excessively high generator loads when the affected battery 

switch is on.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-13

312

SA227-TT FAIRCHILD 300 12,500 LBS

DOUBLE GENERATOR FAILURE

 1. Both Generator Switches ......................................................................................................... OFF

 2. Electrical Load ................................................................................................................. REDUCE

 3. Generator and Start Control Circuit Breakers .....................................................................CHECK

 4. Left Generator Switch ..................................................................... RESET/VOLTAGE CHECKED 

 5. Left Generator Switch ................................................................................................................ ON

 If left generator will not go on line, turn it OFF and try the right generator.

NOTE

If one of the two generators can be put on line, consideration 

should be given to continuing the fl ight with a single generator 

rather than risking a second double generator failure.

 6. Right Generator Switch ................................................................... RESET/VOLTAGE CHECKED

 7. Right Generator Switch .............................................................................................................. ON

NOTE

• If neither generator voltage is within limits, it is acceptable to 

put a single generator on line.

• If neither generator can be put on line, all electrical systems 

(except auxiliary air conditioning systems) will be functional 

on battery power. However, electrical loads should be quickly 

reduced to the minimum for existing fl ight conditions to prolong 

battery life.

WARNING

WHEN IN FLIGHT ON BATTERY POWER ALONE, LAND AS SOON 

AS PRACTICABLE TO PRECLUDE COMPLETE ELECTRICAL 

FAILURE.

DOUBLE ENGINE FAILURE (RESTARTS/RELIGHTS UNSUCCESSFUL)

1. AIRSPEED .......................................................................... MAINTAIN BEST GLIDE AIRSPEED

GLIDE AIRSPEED

 WEIGHT (POUNDS) 12,000 10,000 8,500 

 AIRSPEED (KIAS) 148 136 126 

NOTE

• Best glide airspeed is approximately 1.5 V/VS on the SAS 

indicator.

• Glide ratio at best glide airspeed is approximately 10:1 

(2NM/1,000 FT AGL).

2. GEAR .........................................................................................................................................UP

 3. FLAPS ....................................................................................................................................... UP

 4. Complete Engine Failure During Flight Checklist

 Plan for emergency gear extension and a zero fl ap landing. If altitude above ground level (AGL) 

permits, unfeathering one engine may provide suffi cient hydraulic pressure to operate the fl aps.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-14

312

FAA APPROVED: OCT 31/85

TOTAL ELECTRICAL FAILURE

 1. Entrance Light Switch ....................................................... ON (IF ILLUMINATION IS REQUIRED)

NOTE

The pilot's overhead and entrance door fl ood lights are powered 

by the left battery when the entrance light switch is in its ON position.

 2. Both Battery and Both Generator Switches ............................................................................. OFF

 3. Battery Switches (individually) ...................................................................................... RESET/ON

 4. Generator Switches (individually) ................................................................................. RESET/ON

If total electrical failure occurred as a result of lightning strike or static discharge, the aircraft should 

be thoroughly inspected for evidence of lightning damage. See the SA227 Maintenance Manual, 

Chapter 05 and the TPE 331 Maintenance Manual, Chapter 72. 

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-15

312

SA227-TT FAIRCHILD 300 12,500 LBS

SMOKE IN AIRCRAFT

1. CREW OXYGEN MASKS ...................................................................................................... DON

*2. If Smoke or Fire from Electrical Source:

 *a. Smoke or fi re from essential bus:

 (1) Bus tie switch .............................................................................................................. OFF

 (2) Bus transfer switches ..........................................................OPPOSITE ESSENTIAL BUS

 *b. Smoke or fi re from nonessential bus

 • Bus tie switch .............................................................................................................. OFF

 3. If Smoke from Bleed Air Source:

 * Bleed air switches ...........................TURN OFF ONE SOURCE. IF SMOKE CONTINUES, 

TURN BACK ON AND TURN OTHER SOURCE OFF. 

IF UNSUCCESSFUL, TURN OFF BOTH SOURCES.

NOTE

It is unlikely that both bleed air systems would malfunction simultaneously. However, if they should, closing both bleed air valves would 

prevent more smoke from entering the cockpit and cabin. But the 

outfl ow valve would then close in order to retain cabin differential 

pressure and the existing smoke would be trapped until depressurizing procedures are begun.

 4. If Smoke in Rear of Aircraft .................. USE MANUAL PRESSURIZATION AND SELECT FULL 

DECREASE. WHEN PRESSURE DIFFERENTIAL IS 

ZERO, ACTIVATE CABIN DUMP SWITCH

 *5. If Smoke is in Cockpit ..............................................................ACTIVATE CABIN DUMP SWITCH

 6. Emergency Descent ...............................................................................................AS REQUIRED

 7. Airspeed .........................................................................................................173 KIAS MAXIMUM

 8. Landing Gear ....................................................................................................................... DOWN

 *9. Fresh Air Fan ................................................................................................................OVERRIDE

NOTE

• If failure occurs in the pneumatic or electrical system of the 

bleed air control valve, the engine may have to be shut down to 

stop the fl ow of bleed air.

• If an engine must be shut down to prevent bleed air from 

entering the cockpit and cabin, the landing gear should be 

retracted to ensure adequate single engine performance.

• Whether or not smoke has dissipated, if it cannot be visibly 

verifi ed that the fi re has been extinguished following fi re suppression and/or smoke evacuation procedures, land immediately at the 

nearest suitable airport.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-16

312

FAA APPROVED: OCT 31/85

WHEELWELL AND WING OVERHEAT WARNING LIGHT ON

STEADY LIGHT (indicates brake fi re, wheelwell or air conditioning duct overheat) 

 *1. BLEED AIR SWITCH (affected side) .................................................................................... OFF

 2. LANDING GEAR ................................................................................................................. DOWN

 Leave gear extended at least three (3) minutes to allow cooling of overheated brakes in order 

to preclude a brake/tire fi re and tire explosion.

3. GENERATOR SWITCH (affected side) ................................................................................. OFF

NOTE

If the warning light extinguishes, retract the landing gear after 

three (3) minutes cooling and continue fl ight with the bleed air 

OFF; the generator may be RESET/ON. If the light reilluminates 

STEADY, extend the gear. Expect performance degradation due 

to the drag of the gear. A diversion and precautionary landing 

may be necessary. If the light changes to a FLASHING mode 

complete the wheelwell wing overheat fl ashing items.

CAUTION

IF THE WARNING LIGHT DOES NOT EXTINGUISH WITHIN 

THREE MINUTES, THE AFFECTED ENGINE SHOULD BE SHUT 

DOWN. THE LANDING GEAR MAY HAVE TO BE RETRACTED 

TO SUSTAIN FLIGHT UNTIL ARRIVING AT A SUITABLE LANDING FIELD. 

FLASHING LIGHT (indicates a wing leading edge bleed air line failure or an overheated generator wire) 

*1. BLEED AIR SWITCH (affected side) .................................................................................... OFF

2. GENERATOR SWITCH (affected side) ................................................................................. OFF

CAUTION

IF THE WARNING LIGHT DOES NOT EXTINGUISH WITHIN 

THREE MINUTES, THE AFFECTED ENGINE SHOULD BE SHUT 

DOWN. 

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-17

312

SA227-TT FAIRCHILD 300 12,500 LBS

CABIN PRESSURIZATION MALFUNCTIONS

LOW PRESSURE MALFUNCTION

The cabin altitude warning light illuminates when the cabin pressure is equivalent to a pressure 

altitude between 10,000 feet and 12,000 feet. Check cabin altitude, differential pressure and controller 

setting. If the cabin pressurization controller is not providing proper cabin pressure, change to manual 

operation. If the desired cabin altitude or differential pressure still cannot be attained, an excessive leak 

exists and it may be necessary to descend or use oxygen.

HIGH PRESSURE MALFUNCTION

If the cabin differential pressure exceeds the normal limit of 7.0 psi, the cabin pressurization 

controller may have failed and allowed the outfl ow valve to close. Open the manual control valve approximately 1/2 turn; select MANUAL position on the cabin pressure selector, and regulate pressure manually. 

If manual control is ineffective, the safety valve should relieve excess cabin pressure at 7.25 psi. Prior 

to landing, the cabin pressure differential must be eliminated by use of the manual control or the folowing 

alternate procedure:

 1. Altitude ............................................................................................................ BELOW 12,000 FEET

 *2. Bleed Air Switches ...................................................................................................................... OFF

 3. Allow cabin to depressurize to less than 1 psi differential.

 *4. Cabin Dump Switch .................................................................................................................DUMP

NOTE

If cabin pressure is dumped when a signifi cant cabin pressure differential exists, the resulting sensation may be alarming and uncomfortable to passengers. Consequently, use of the dump valve should 

normally be restricted to situations where cabin pressure differential 

is less than 1 psi or when other methods of pressure differential 

control are ineffective.

 *5. Bleed Air Switches ........................................................................................................................ ON

 6. Proceed unpressurized to airport. Air conditioning will be available.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-18

312

FAA APPROVED: OCT 31/85

CABIN PRESSURIZATION MALFUNCTIONS (continued)

EXCESSIVE RATE OF PRESSURIZATION

If an excessive rate of pressurization is experienced and it cannot be controlled by the rate knob on 

the cabin pressurization controller or by the manual control knob, the following steps should be accomplished:

 *1. Bleed Air Switches ...................................................................................................................... OFF

 If Step 1 eliminates the excessive rate of pressurization, determine the source of the malfunction by 

turning the bleed air controls on individually. If the malfunction was caused by one of the bleed air 

control valves, leave the malfunctioning side off and continue pressurized fl ight using bleed air from 

one engine.

 If the pressure surge does not decrease:

 *2. Cabin Dump Switch .................................................................................................................DUMP

NOTE

If cabin pressure is dumped when a signifi cant cabin pressure differential exists, the resulting sensation may be alarming and uncomfortable to passengers. Consequently, use of the dump valve should 

normally be restricted to situations where cabin pressure differential 

is less than 1 psi or when other methods of pressure differential 

control are ineffective.

EMERGENCY DESCENT PROCEDURE

If cabin pressure is lost while at high altitude, execute the following procedure:

*1. PASSENGER OXYGEN SWITCH ................................................................................................ ON

 2. PASSENGER AND CREW OXYGEN MASKS ......................................................................... DON

3. Speed Levers .................................................................................................................. HIGH RPM

 4. Power Levers ................................................................................................................FLIGHT IDLE

 5. Airspeed ...........................................................................................................173 KIAS MAXIMUM

 6. Landing Gear .......................................................................................................................... DOWN

 7. Flaps ................................................................................................................................ ONE-HALF

 8. Altitude .......................................................................................................................AS REQUIRED

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-19

312

SA227-TT FAIRCHILD 300 12,500 LBS

EMERGENCY DESCENT PROCEDURE (continued)

NOTE

• A pitch attitude of approximately 10 degrees nose down will 

allow the airplane to stabilize very close to the gear limit speed 

of 173 KIAS in the 1/2 fl aps confi guration.

• This procedure results in a descent from 31,000 feet to 15,000 

feet within three and three-quarter minutes when initiated 

from cruise power and airspeed.

CARGO OR CABIN DOOR WARNING LIGHT ON

PRIOR TO TAKEOFF

 1. Do not take off.

IN FLIGHT

A cabin door warning during fl ight could indicate that the cabin door handle is not fully closed, that one 

or more of the door latches is not fully extended, or that one or more of the door latch switches is 

maladjusted. The latter problem is typically annunciated when the cabin differential pressure reaches 

approximately 5 psi during climbs. Reducing cabin differential pressure to less than approximately 4 psi 

will allow the pressure vessel to defl ate, the door latch to seat the switch, and the warning light to go out. 

If the door warning light should illuminate during fl ight, conduct the following:

 1. Keep crew and passengers clear of door.

 *2. Turn seat belts sign on.

 3. Reduce cabin differential pressure until the warning light goes out.

 4. Descend as required.

 5. Land as soon as practicable.

 6. Determine cause of door warning prior to further fl ight.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-20

312

FAA APPROVED: OCT 31/85

HYDRAULIC SYSTEM FAILURE

An emergency hand pump and a cable operated manual release system are provided to extend the 

landing gear in the event of a hydraulic system failure. A stand pipe system in the hydraulic reservoir 

provides a supply of fl uid for hand pump operation. The manual release system also permits free fall 

gear extension in the event that all hydraulic fl uid is lost.

There are no emergency provisions to extend or retract the fl aps. Landing approach should be made 

at 1.3 VS1 for the existing airplane confi guration. (For fl aps up confi guration, use 134 KIAS at 13,000 

pounds gross weight. Reduce this speed by 6 KIAS for each 1,000 pounds less gross weight.)

WARNING

IN THE EVENT OF A HYDRAULIC SYSTEM MALFUNCTION, 

THE NOSE WHEEL STEERING SYSTEM MUST NOT BE ARMED. 

STEER WITH BRAKES, POWER, AND RUDDER.

CAUTION

 If Anti-Skid Installed:

• WHEEL ANTI-SKID PROTECTION WILL NOT BE AVAILABLE FOLLOWING HYDRAULIC SYSTEM FAILURE. THE 

ANTI-SKID SWITCH MUST BE TURNED OFF AND MANUAL 

BRAK-ING USED DURING GROUND OPERATIONS.

• IF THERE IS ANY INDICATION THAT BRAKE POWER IS ON AND 

THERE IS NO ANTI-SKID PROTECTION, TURN THE ANTI-SKID 

SWITCH OFF.

In case of hydraulic system failure:

 1. Prepare for emergency extension of the landing gear.

 2. Prepare for landing with existing wing fl aps confi guration.

 3. Ensure that the nose wheel steering switch is turned off and remains off.

 4. Ensure that the anti-skid switch is turned off and remains off. (If anti-skid installed)

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-21

312

SA227-TT FAIRCHILD 300 12,500 LBS

LANDING GEAR EMERGENCY EXTENSION

 1. Airspeed ...........................................................................................................173 KIAS MAXIMUM

 2. Landing Gear Handle ............................................................................................................. DOWN

 *3. Emergency Release Lever ...........................................................................................ROTATE AFT

 *4. Hand Pump Valve Handle ................................................. PULL PIP PIN/ROTATE VALVE HANDLE

90° FORWARD

 *5. Emergency Hand Pump .................................................................................PUMP AS REQUIRED

 a. Gear indicator ....................................................................................ALL DOWN AND LOCKED

 b. Hydraulic pressure gauge ..............................................................................500 PSI to 800 PSI

NOTE

• If manual extension is used because of a failure in the landing 

gear electrical control system, the hydraulic pressure gauge will 

continue to indicate approximately 2,000 psi system pressure. 

In this case, the pressure to the gear down actuators can be detected only by the effort required to move the emergency hand 

pump.

• If a failure at the bottom of the hydraulic pack allows depletion 

of all hydraulic fl uid, the emergency hand pump will not provide 

pressure. Nevertheless, Step 3 above will allow the landing gear 

to free fall to a safe, down and locked position.

• Hydraulic pressure to the nose wheel steering system will not 

be available following landing gear emergency extension required 

by either hydraulic failures or gear position selector valve electrical 

failures. Do not arm nose wheel steering.

• On those aircraft which have been modifi ed in accordance with 

Fairchild Aircraft Service Bulletin 32-013: Hydraulic pressure 

to the anti-skid brake system will not be available following landing 

gear emergency extension required by either hydraulic failures or 

gear position selector valve electrical failures. The anti-skid caution 

light will be illuminated. Turn anti-skid switch off in these situations.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-22

312

FAA APPROVED: OCT 31/85

LANDING GEAR EMERGENCY EXTENSION (continued)

If the gear does not extend, the following additional procedure may allow the gear to extend.

NOTE

Extending the landing gear in this manner requires that the 

airplane be slowed to a minimum safe airspeed. Therefore, this 

procedure must be performed at high enough altitude to ensure 

safe fl ight operation.

 1. Retract the gear.

NOTE

If the landing gear will not retract, check that the hand pump 

valve handle and the emergency release lever have been returned 

to their normal positions.

 2. Use full fl aps and slow the aircraft to just above fl ight idle stall speed.

 3. Place the landing gear handle in the down position.

 4. If the gear fails to extend, repeat the above procedure. If the gear still will not extend, repeat the 

above procedure using the emergency gear release lever instead of the landing gear handle. 

(Steps 3, 4, and 5 in Landing Gear Emergency Extension.)

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-23

312

SA227-TT FAIRCHILD 300 12,500 LBS

GEAR UP LANDINGS

NOTE

• If either main gear will not extend, land with all three gear up if 

possible. If the nose gear will not extend, land on the mains.

• Ensure that passengers are thoroughly briefed regarding 

bracing position and evacuation procedure.

• Depressurize airplane and consider removal and secure 

stowage of escape hatch prior to landing. Expect the entrance 

door to operate normally. It will not open fully after landings with 

the left main gear retracted.

• Historically, airplanes of this class have received more airframe 

damage from gear up landings on sod than from landings on 

smooth, paved surfaces.

• Propeller blades contacting the surface while turning under 

power tend to disintegrate and throw shrapnel which may puncture 

the fuselage. Blades contacting the surface when feathered, or 

nearly feathered, will bend slightly and wear away but most likely 

will not shatter and will aid in holding the wings and nacelles off 

the runway.

• The pilot may choose to feather one propeller early and save 

the other engine for last minute glide path corrections. During approaches with one main gear up and one down, it is recommended 

that the propeller on the gear up side be feathered fi rst. When a 

propeller is feathered with fl ight idle power set, drag will be reduced 

and gliding distance increased slightly.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-24

312

FAA APPROVED: OCT 31/85

GEAR UP LANDINGS (continued)

LANDING WITH ALL THREE GEAR UP:

 1. Use full fl aps.

 2. Approach the runway at normal approach speed plus 5 to 10 KIAS.

 3. Do not feather propellers until landing on the runway is assured.

 4. Shut off electrical power just prior to touchdown (this is to allow use of the pitch trim system 

until touchdown). Leave batteries on during night landings to permit use of landing lights.

 5. Allow aircraft to touch down in a relatively fl at attitude and on centerline. Use rudder for directional 

control.

LANDING WITH NOSE GEAR UP:

 1. Use normal approach technique and fl ap confi guration.

 2. Feather propellers and shut off electrical power after the mains have touched the runway. 

Leave batteries on during night landings to permit use of landing lights.

 3. Hold the nose of the aircraft off the runway as long as practical, but not so long that pitch control 

is lost. Put nose on runway gently rather than letting it drop to the runway.

LANDING WITH NOSE GEAR AND ONE MAIN GEAR EXTENDED:

 1. Attempt to retract all three gear. Check the position of the emergency gear release lever, the 

hand pump valve handle and the landing gear control circuit breaker. Transfer the landing gear 

control to the other essential bus using the transfer switch.

 2. If possible, select the runway with the fewest obstructions and fl attest terrain on the side of the unextended gear.

3. Feather propellers after landing on the runway is assured.

 4. Shut off electrical power just prior to touchdown (this is to allow use of the pitch trim system 

until touchdown). Leave batteries on during night landings to permit use of landing and taxi lights.

 5. Hold the wing with the unextended landing gear off the runway as long as possible. Use brakes and 

rudder for aircraft directional control. Expect the aircraft to turn into the low wing.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-25

312

SA227-TT FAIRCHILD 300 12,500 LBS

STABILIZER TRIM MALFUNCTIONS

STABILIZER TRIM SYSTEM RUNAWAY

The application of electrical power to the stabilizer trim actuators is indicated by an aural signal. If the 

signal occurs in fl ight when the trim system is not being operated, the following procedure should be initiated immediately:

1. ELEVATOR CONTROL ............................... OVERPOWER TO MAINTAIN AIRPLANE CONTROL

 2. TRIM SELECTOR ..................................................................................OFF (CENTER POSITION)

 3. Trim Selector .......................................................................OPPOSITE POSITION FROM WHERE

MALFUNCTION OCCURRED

 4. Retrim as required.

PILOT’S TRIM SYSTEM INOPERATIVE

 1. Trim Selector ......................................................................................................................COPILOT

 2. Pilot’s Auxiliary Trim Switch or Copilot’s Trim Switches ................................... TRIM AS REQUIRED

COPILOT’S TRIM SYSTEM INOPERATIVE

 1. Trim Selector ........................................................................................................................... PILOT

 2. Pilot’s Trim Switches ........................................................................................ TRIM AS REQUIRED

BOTH PILOT’S AND COPILOT’S TRIM SYSTEMS INOPERATIVE

 1. Trim Selector ....................................................................................................... OFF (CENTERED)

 2. Airspeed ............................................... AS REQUIRED TO MAINTAIN LOW ELEVATOR FORCES

 3. SAS2 Clutch Switch ...................................................................................................AS REQUIRED

NOTE

• Turning the SAS2 clutch switch OFF will reduce required pull 

forces by approximately 20 pounds at approach speeds.

• If the trim system fails in an extreme nose down trim position, 

do not extend fl aps unless required for landing because of 

the high pull force required to maintain level fl ight.

• If the trim system fails in an extreme nose up trim position, 

fl ap extension (below VFE) will reduce the push force required to 

maintain level fl ight.

 4. Flaps (on landing approach) ......................................................................................AS REQUIRED

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-26

312

FAA APPROVED: OCT 31/85

STABILIZER TRIM MALFUNCTIONS (continued)

NOTE

Flap extension decreases push force requirements.

 5. Landing Gear ............................................................................................. DOWN WHEN DESIRED

NOTE

Gear extension increases push force requirements slightly.

GO-AROUND WITH STABILIZER TRIM INOPERATIVE

WARNING

VERY HIGH PUSH FORCES WILL BE REQUIRED IF THE 

FLAPS ARE RETRACTED WITH THE STABILIZER TRIM IN THE 

EXTREME NOSE UP POSITION. IF A GO-AROUND OR BALKED 

LANDING IS REQUIRED WHEN THE STABILIZER TRIM IS STUCK 

IN AN EXTREME NOSE UP POSITION, DO NOT RETRACT THE 

FLAPS IMMEDIATELY.

 1. Power ........................................................................................................................AS REQUIRED

NOTE

Application of power increases push force requirements.

 2. Flaps .................................................................................................... RETRACT IN INCREMENTS

NOTE

Flap retraction increases push force requirements.

 3. Airspeed ....................................................... AS REQUIRED TO MAINTAIN LOW STICK FORCES

 4. Landing Gear ...................................................................................... RETRACT WHEN FEASIBLE

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-27

312

SA227-TT FAIRCHILD 300 12,500 LBS

STABILITY AUGMENTATION AND STALL AVOIDANCE

SYSTEM (SAS2) MALFUNCTIONS

SAS FAULT LIGHT ON IN FLIGHT

1. SAS2 CLUTCH SWITCH ........................................................................................................... OFF

 2. SAS2 Computer Power Circuit Breaker .....................................................................................PULL

CAUTION

WITH THE SAS2 DISENGAGED (OR INOPERATIVE) THE AIRPLANE WILL HAVE UNDESIRABLE STALL CHARAC-TERISTICS 

AT AFT CENTER OF GRAVITY LOADINGS. ADEQUATE MARGINS 

ABOVE THE STALL SPEED SHOULD BE MAINTAINED IN ALL 

OPERATIONS. ENSURE THAT TOUCHDOWN SPEED IS EQUAL 

TO OR GREATER THAN 1.1 VS1.

NOTE

• With SAS2 disengaged or inoperative, there will be no augmented 

stick forces. Very light elevator forces will be required to maneuver 

the airplane at airspeeds below approximately 135 KIAS, particularly 

when operating at aft c.g. loadings.

• Fault light on fl ashing indicates a stopped servo or servo clutch 

disengagement.

• Fault light on steady in fl ight indicates computer power failure, 

or computer power failure with simultaneous servo or clutch 

failure.

• With the fault light on, angle of attack and stall warning indications 

may be unreliable.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-28

312

FAA APPROVED: OCT 31/85

STABILITY AUGMENTATION AND STALL AVOIDANCE

SYSTEM (SAS2) MALFUNCTIONS (continued)

SAS2 MALFUNCTION – NOSE DOWN

In the event of a nose down malfunction (no aural tone is heard) the following procedure should 

be initiated:

1. ELEVATOR CONTROL ............................... OVERPOWER TO MAINTAIN AIRPLANE CONTROL

 *2. SAS2 CLUTCH SWITCH ........................................................................................................... OFF

 3. SAS2 Circuit Breakers ...............................................................................................................PULL

WARNING

PULL FORCES REQUIRED TO OVERPOWER THE STICK PUSHER 

MAY EXCEED 60 POUNDS.

NOTE

With SAS2 disengaged or inoperative, there will be no augmented 

stick forces. Very light elevator forces will be required to maneuver 

the airplane at airspeeds below approximately 135 KIAS, particularly 

when operating at aft c.g. loadings.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-29

312

SA227-TT FAIRCHILD 300 12,500 LBS

STABILITY AUGMENTATION AND STALL AVOIDANCE

SYSTEM (SAS2) MALFUNCTIONS (continued)

AURAL STALL WARNING AT SPEEDS WELL IN EXCESS OF NORMAL STALL WARNING SPEEDS

When an aural stall warning occurs in unaccelerated fl ight at speeds well in excess of normal stall 

warning speed, possible damage to the SAS2 vane is indicated and an inadvertent nose down push 

may occur.

 *1. SAS2 CLUTCH SWITCH ........................................................................................................... OFF

To silence the stall warning horn:

 2. Stall Warning Circuit Breaker .....................................................................................................PULL

WARNING

PULL FORCES REQUIRED TO OVERPOWER THE STICK PUSHER 

MAY EXCEED 60 POUNDS.

NOTE

With SAS2 disengaged or inoperative, there will be no augmented 

stick forces. Very light elevator forces will be required to maneuver 

the airplane at airspeeds below approximately 135 KIAS, particularly 

when operating at aft c.g. loadings.

YAW DAMPER MALFUNCTIONS

The yaw damper warning light, located on the annunciator panel, illuminates when a power failure 

occurs. If such a failure occurs, the yaw damper switch should be turned OFF and care should be 

taken to avoid extreme skidding or slipping turns.

NOTE

Maximum allowable 90o crosswind component for landing with 

yaw damper inoperative is 10 knots.

ELECTRICAL SERVO RUNAWAY

A runaway can occur when an erroneous electrical signal is transmitted to the yaw damper servo 

primary electrical clutch; however, the system is provided with a secondary mechanical clutch that 

prevents excessive rudder forces being generated. If a runaway occurs:

 1. Rudder Pedals .........................................................AS REQUIRED FOR COORDINATED FLIGHT

 2. Yaw Damper Switch .................................................................................................................... OFF

 3. Avoid extreme skidding or slipping turns.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-30

312

FAA APPROVED: OCT 31/85

EMERGENCY EXIT

There is one emergency exit on the right side of the center cabin. The hatch is of the plug type and 

opens into the cabin. To open the emergency exit:

 1. Cabin ..................................................................................................................... DEPRESSURIZE

 2. Hatch Release Handles .............................................................................PULL INBOARD AND UP

NOTE

Pull hatch inward, rotate, extend through opening, and discard 

outside the airplane. Ensure that the hatch is clear of the exit route 

from the airplane.

NOSE WHEEL STEERING ELECTRICAL MALFUNCTION

Fault protection is provided by circuitry which automatically deactivates the nose wheel steering 

system if an electrical malfunction occurs. The nose wheel is then free to caster and rudder, differential 

braking, and/or differential power can be used for steering.

If the system fails to test correctly, the arm switch should be placed in the OFF position and 

steering accomplished with rudder, differential braking, and/or differential power.

In the event of a fl ashing green NOSE STEERING light, an unwanted steering defl ection, and/or 

park light illuminated when the PARK button is not depressed:

 1. NWS Power Lever Button ..................................................................................................RELEASE

 2. Right Speed Lever ....................................................... APPROXIMATELY 1/2 INCH FWD OF LOW

 3. Directional Control ................................................................ MAINTAIN WITH RUDDER, BRAKES,

AND/OR POWER

 4. Nose Wheel Steering Arm Switch ............................................................................................... OFF

 5. Nose Wheel Steering Circuit Breaker ........................................................................................PULL

NOTE

It is normal for the park light to remain illuminated, but vary in intensity, during the 4 to 7 second transition time from park mode to 

normal mode.

FAA APPROVED: OCT 31/85

REVISED: DEC 09/14
FAA APPROVED: OCT 31/85 EMERGENCY PROCEDURES 3-31

312

SA227-TT FAIRCHILD 300 12,500 LBS

NOSE WHEEL STEERING HYDRAULIC MALFUNCTION

An illuminated NOSE STEER FAIL amber annunciator light indicates that hydraulic pressure is being supplied to the nose wheel steering actuator but the pilot is not commanding a steering signal. Illumination 

of the NOSE STEER FAIL light should alert the pilot to potentially undesirable steering actuation and that 

corrective action may be required. Corrective action depends upon the operational phase.

NOTE

The following procedures assume that the NOSE STEER FAIL 

light illuminates while the nose wheel steering switch is in its 

ARMED position. Neither the NWS power lever button nor the 

right speed lever switch will be effective if the nose wheel steering 

switch is OFF. Therefore, if the NOSE STEER FAIL light illuminates 

while the switch is OFF, corrective action must be preceded by arming the nose wheel steering system.

NOSE STEER FAIL Light ON

(During ground operations):

 1. NWS Power Lever Button ...................................................................................PRESS AND HOLD

OR:

 2. Right Speed Lever ..................................................................................................................... LOW

 3. NOSE STEER FAIL Light ............................................................................................. CHECK OUT

 4. Directional Control .........................................................................................MAINTAIN WITH NWS

 5. Do Not Take Off.

(During initial part of takeoff roll):

 1. NWS Power Lever Button ...................................................................................PRESS AND HOLD

 2. NOSE STEER FAIL Light ............................................................................................. CHECK OUT

 3. Directional Control .............................................................................................................MAINTAIN

 4. Takeoff ................................................................................................................................... ABORT

(During fi nal part of takeoff roll):

 1. NWS Power Lever Button ...................................................................................PRESS AND HOLD

 2. NOSE STEER FAIL Light ............................................................................................. CHECK OUT

 3. Directional Control .............................................................................................................MAINTAIN

Continue with normal takeoff procedures.

FAA APPROVED: DEC 09/14
EMERGENCY PROCEDURES

SA227-TT FAIRCHILD 300 12,500 LBS

3-32

312

FAA APPROVED: OCT 31/85

NOSE WHEEL STEERING HYDRAULIC MALFUNCTION (continued)

NOSE STEER FAIL Light ON (continued)

(In fl ight with gear down):

 1. NWS Power Lever Button ...................................................................................PRESS AND HOLD

 2. NOSE STEER FAIL Light ............................................................................................. CHECK OUT

NOTE

Conduct normal landing and rollout while keeping the power 

lever button depressed to avoid uncommanded steering actuation.

FAA APPROVED: DEC 09/14