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

SUBJECT: REVISION 29 TO SA227-TT POH/AFM

TO: ALL OPERATORS AND POH/AFM MANAGERS OF THE MERLIN IIIC

1. Attached is Revision 29 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
iii

SA227-TT MERLIN IIIC

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

FLIGHT MANUAL

REISSUE A

(S/N TT–421 AND Subsequent)

LIST OF EFFECTIVE PAGES

Page Date Page Date

SECTION 1

Page Date Page Date

 LIST OF EFFECTIVE PAGES 

Title ............................................ March 28, 1996

 i ..................................................August 7, 1981

 ii .................................................August 7, 1981

 iii .......................................... December 9, 2014

 iv .......................................... December 9, 2014 

 v ........................................... December 7, 2007 

 vi ................................................... June 2, 2000 

 vii ............................................. October 5, 1982

 viii ............................................. March 28, 1996

 ix ................................................. March 5, 1982

 x .................................................. June 10, 1983

 xi ................................................. March 3, 1989

 xii ..................................................May 11, 1999

 xiii ........................................ December 9, 2014

 xiv ................................................April 28, 2000

1-i................................................August 7, 1981

1-ii ...............................................August 7, 1981

1-1 ..............................................August 7, 1981

1-2 ..............................................August 7, 1981

1-3 ..............................................August 7, 1981

1-4 ..............................................August 7, 1981

1-5 ..............................................August 7, 1981

1-6 ..............................................August 7, 1981

1-7 ..............................................August 7, 1981

1-8 ..............................................August 7, 1981

1-9 ..............................................August 7, 1981

1-10 ............................................August 7, 1981

1-11 .............................................August 7, 1981

1-12 ............................................August 7, 1981

1-13 ............................................August 7, 1981

1-14 ............................................August 7, 1981

1-15 ............................................August 7, 1981

1-16 ............................................August 7, 1981

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014 
iv

SA227-TT MERLIN IIIC

PILOT'S OPERATING HANDBOOK

AND FAA APPROVED

FLIGHT MANUAL

REISSUE A

(S/N TT–421 AND Subsequent)

LIST OF EFFECTIVE PAGES (continued)

SECTiON 2

Page Date Page Date

SECTION 3

Page Date Page Date

2-i.......................................... December 7, 2007

2-ii ...............................................August 7, 1981

2-1 ............................................... June 10, 1983

2-2 ............................................... June 10, 1983

2-3 ................................................ May 13, 1997

2-4 ..............................................August 7, 1981

2-5 ........................................ December 7, 2007

2-6 ...................................... December 29, 1986

2-7 ..............................................August 7, 1981

2-8 ............................................. March 29, 1994

2-9 ..............................................August 7, 1981

2-10 .................................... December 17, 1985

2-11 ................................................ June 2, 2000

2-12 ........................................ January 14, 1982

2-13 ............................................. March 2, 1983

2-14 .................................... November 18, 1997

2-15 .................................... November 18, 1997

2-15A ............................................. June 2, 2000

2-15B ............................................. June 2, 2000

2-16 .................................... November 18, 1997

2-17 ........................................ October 10, 1985

2-18 ............................................August 7, 1981

2-19 ............................................August 7, 1981

2-20 ............................................August 7, 1981

2-21 ........................................ October 15, 1084

2-22 ........................................ October 15, 1984

3-i.......................................... December 9, 2014

3-ii ......................................... December 9, 2014 

3-1 .................................................May 11, 1999

3-2 .................................................May 11, 1999

3-3 ........................................ December 9, 2014

3-4 ........................................ December 9, 2014

3-5 ........................................ December 9, 2014

3-6 ........................................ December 9, 2014

3-7 ........................................ December 9, 2014

3-8 ........................................ December 9, 2014

3-9 ........................................ December 9, 2014

3-10 ...................................... December 9, 2014

3-11 ....................................... December 9, 2014

3-12 ...................................... December 9, 2014

3-13 ...................................... December 9, 2014

3-14 ...................................... December 9, 2014

3-15 ...................................... December 9, 2014

3-16 ...................................... December 9, 2014

3-17 ...................................... December 9, 2014

3-18 ...................................... December 9, 2014

3-19 ...................................... December 9, 2014

3-20 ...................................... December 9, 2014

3-21 ...................................... December 9, 2014

3-22 ...................................... December 9, 2014

3-23 ...................................... December 9, 2014

3-24 ...................................... December 9, 2014

3-25 ...................................... December 9, 2014

3-26 ...................................... December 9, 2014

3-27 ...................................... December 9, 2014

3-28 ...................................... December 9, 2014

3-29 ...................................... December 9, 2014

3-30 ...................................... December 9, 2014

3-31 ...................................... December 9, 2014

3-32 ...................................... December 9, 2014

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014

 LIST OF EFFECTIVE PAGES 

xiv

SA227-TT MERLIN IIIC

LIST OF REVISIONS (continued)

 Revision Revised FAA APPROVED

 Number Pages Description of Revision Signature Date

A black bar on a revised page shows the current change.

REVISIONS Issued: April 28, 2000
EMERGENCY PROCEDURES 3-i

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014

SA227-TT MERLIN IIIC

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 V1................................................. 3-5

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

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

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

Infl ight Relight .................................................................................................................................. 3-7

Single Engine Landing..................................................................................................................... 3-8

 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 ........................................................................................................ 3-12

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

Double Generator Failure .............................................................................................................. 3-14

Double Engine Failure (Restarts/Relights Unsuccessful) .............................................................. 3-14

Total Electrical Failure ................................................................................................................... 3-15

Smoke in Airplane.......................................................................................................................... 3-16

Wheelwell and Wing Overheat Warning Light On ......................................................................... 3-17

 Steady Light .......................................................................................................................... 3-17

 Flashing Light ....................................................................................................................... 3-17

Cabin Pressurization Malfunctions ................................................................................................ 3-18

 Low Pressure Malfunction .................................................................................................... 3-18

 High Pressure malfunction ................................................................................................... 3-18

 Excessive Rate of Pressurization ......................................................................................... 3-19

Emergency Descent Procedure..................................................................................................... 3-20

Cabin Door Warning Light On ....................................................................................................... 3-20

 Prior to Takeoff ...................................................................................................................... 3-20

 In Flight ................................................................................................................................. 3-20

Hydraulic System Failure............................................................................................................... 3-21

Landing Gear Emergency Extension ............................................................................................. 3-22

Gear Up Landings ......................................................................................................................... 3-24

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

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

 Pilot's Trim System Inoperative ............................................................................................ 3-26

 Copilot's Trim System Inoperative ........................................................................................ 3-26

 Both Pilot's and Copilot's Trim System Inoperative .............................................................. 3-26

 Go-Around with Stabilizer Trim Inoperative .......................................................................... 3-27
3-ii EMERGENCY PROCEDURES

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014

SA227-TT MERLIN IIIC

TABLE OF CONTENTS

EMERGENCY PROCEDURES

ITEM PAGE

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 ............................................................................................................. 3-30

 Power Failure ....................................................................................................................... 3-30

 Electrical Servo Runaway ..................................................................................................... 3-30

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

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

Nose Wheel Steering Hydraulic Malfunction ................................................................................. 3-32
EMERGENCY PROCEDURES 3-3 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-4 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014

ENGINE FIRE IN FLIGHT (continued)

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

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

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

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
EMERGENCY PROCEDURES 3-5 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

ENGINE FAILURE DURING TAKEOFF – TAKEOFF CONTINUED

AT OR ABOVE V1

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 (DRY OR WET)

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. If during a 

dry takeoff the 100% torque limit is not being developed and bleed 

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

OFF or by selecting continuous alcohol-water injection. Observe 

CAWI climatic operating limitations.

*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 CLIMB SPEED

136 KIAS 

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-6 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

ENGINE FAILURE DURING TAKEOFF – TAKEOFF CONTINUED

AT OR ABOVE V1 (continued)

 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. 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

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-7 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 IN- STRUMENTS 

OR EXCESSIVE VIBRATION, AN AIRSTART SHOULD NOT BE 

ATTEMPTED. AIRSTART FOLLOWING INTENTIONAL ENGINE 

SHUTDOWN IS COVERED IN SECTION 3A, ABNORMAL PROCEDURES.

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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-8 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

INFLIGHT RELIGHT (continued)

1. Power Lever ............................................APPROXIMATELY 1/4 INCH ABOVE FLIGHT IDLE

 (WARNING HORN SILENCED) 

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

 3. Airspeed .....................................................................................BETWEEN 180 and 100 KIAS

 4. RPM ................................................................................................BETWEEM 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 ONE SECOND)

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

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

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

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 Quanity .......................................................CHECK (500 LBS. MAXIMUM IMBALANCE)

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-9 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

SINGLE ENGINE LANDING (continued)

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 crossfl ow switch to balance 

fuel within tolerences.

 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

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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-10 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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

136 KIAS

 *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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-11 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-12 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

BATTERY TEMPERATURE CAUTION / WARNING LIGHTS ON

NOTE

• The amber caution light illuminates if either battery temperature 

reaches 120o ± 3oF.

• The red warning light illuminates if either battery temperature 

reaches 150o ± 3oF.

AMBER LIGHTS ILLUMINATES

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

NOTE

Either obtain a GPU or wait until the batteries have cooled.

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

AND GENERATOR LOADS

 3. Temperature Increasing to 140oF ............................................................. DO NOT TAKE OFF

 4. Temperature Increasing above 140oF ...........................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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-13 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

BATTERY TEMPERATURE CAUTION / WARNING LIGHTS ON (continued)

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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-14 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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) 13,000* 12,000 10,000 8,500 

 AIRSPEED (KIAS) 154 148 136 126

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). 

* For use with Sup 1 only.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-15 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

DOUBLE ENGINE FAILURE (RESTARTS/RELIGHTS UNSUCCESSFUL) (continued)

 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.

TOTAL ELECTRICAL FAILURE

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

NOTE

The pilot's overhead and entrance door flood lights are 

powered by the right battery relay 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. 

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-16 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

SMOKE IN AIRPLANE

 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 CONTINUED, 

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 depressuring 

procedures are begun.

 4. If Smoke in Rear of Airplane .......... 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 eliminate 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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-17 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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. 

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-18 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 differential pressure and the controller setting. 

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

desired differential pressure still cannot be attained, and excessive leak exists then it may be necessary to descend or use oxygen.

HIGH PRESSURE MALFUNCTION

If the cabin differential pressure exceeds the normal limit of 7 psi, the cabin pressurization controller 

may have failed and allowed the outfl ow to close. Open the manual control valve approximately onehalf 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 following 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 alve 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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-19 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 

acomplished:

 *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.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-20 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

EMERGENCY DESCENT PROCEDURES

If the cabin pressure is lost for any reason 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

NOTE

• A pitch attitude of approximately 10o 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.

CABIN DOOR WARNING LIGHT ON

PRIOR TO TAKEOFF

1. Do not takeoff.

IN FLIGHT

A cabin door warning during fl ight could indicate that a 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 beltsign 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 warning prior to further fl ight.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-21 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 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 133 KIAS at 12,500 

pounds gross weight. Reduce this speed by 6 KIAS for each 1,00 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 BRAKING 

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)

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-22 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 DEGREES 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 hydraulic 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 acordance 

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 faulires. 

The anti-skid caution light will be illuminated. Turn anti-skid switch 

off in these situations.

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
EMERGENCY PROCEDURES 3-23 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

LANDING GEAR EMERGENCY EXTENSION (continued)

If 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 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).

Issued: May 8, 1981

Reissued: August 7, 1981

Revised: December 9, 2014
3-24 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

Issued: January 14, 1982

Revised: December 9, 2014

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 as to bracing 

position and evacuation procedure.

• Consider removal and secure stowage of escape hatches prior to 

landing. Expect the entrance door to operate normally. It will not 

open fully after landings with the nose or left 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 contracting 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.

LANDING WITH ALL THREE GEAR UP:

 1. Use full fl aps.

 2. Approach the runway at 1.3 VS plus 5 to 10 KIAS.

 3. Do not feather propellers until landing on the runway is assured. Drag will be reduced and 

gliding distance increased after propellers are feathered.

 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 center line. Use rudder for 

directional control.
EMERGENCY PROCEDURES 3-25 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

GEAR UP LANDINGS (continued)

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. Drag will be reduced and gliding 

distance increased after propellers are feathered.

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

system until touchdown). Leave barrteries 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.

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 ................................................................OPPISITE POSITION FROM WHERE

 MALFUNCTION OCCURRED

 4. Retrim as required.

Issued: December 9, 2014
3-26 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

STABILIZER TRIM MALFUNCTIONS (continued)

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 SYSTEM 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

NOTE

Flap extension decreases push force requirements.

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

NOTE

Gear extension increases push force requirements slightly.

Issued: December 9, 2014
EMERGENCY PROCEDURES 3-27 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

STABILIZER TRIM MALFUNCTIONS (continued)

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

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 V S1.

Issued: December 9, 2014
3-28 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

STABILITY AUGMENTATION AND STALL AVOIDANCE

SYSTEM (SAS2 ) MALFUNCTIONS (continued)

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 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.

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 BECEED 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.

Issued: December 9, 2014
EMERGENCY PROCEDURES 3-29 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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. SAS 2 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 the 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.

Issued: December 9, 2014
3-30 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

YAW DAMPER MALFUNCTIONS

POWER FAILURE

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 90 degrees 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.

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 of the airplane.

Issued: December 9, 2014
EMERGENCY PROCEDURES 3-31 Issued: May 8, 1981

Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 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 intesity, 

during the 4 to 7 second transition time from park mode to normal 

mode.

On those aircraft which have been modifi ed in accordance with Fairchild Swearingen Service Bulletin 

32-006.

Issued: December 9, 2014
3-32 Issued: May 8, 1981 EMERGENCY PROCEDURES Reissued: August 7, 1981

SA227-TT MERLIN IIIC

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 speed lever 

switch will be effective if the nose wheel steering switch is OFF. 

Therefore, if 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 FINAL PART OF TAKEOFF ROLL):

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

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

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

 4. Continue with Normal Takeoff Procedures.

(IN FLIGHT 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.

Issued: December 9, 2014