SA227-CC

TABLE OF CONTENTS
ABNORMAL PROCEDURES

ITEM PAGE

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

Annunciator Panel .............................................................................................................................. 3A-1
Fuel System Malfunctions .................................................................................................................. 3A-3
Boost Pump Failure ................................................................................................................... 3A-3
Fuel Transfer Pump Caution Light On....................................................................................... 3A-3
Operation with Fuel Imbalance.................................................................................................. 3A-3
Left or Right Fuel Filter Light On ............................................................................................. 3A-3A
Fuel Balance Procedure .......................................................................................................... 3A-3A
Stall Avoidance System (SAS) Malfunctions ...................................................................................... 3A-4
Stick Shaker at Speeds Well in Excess of Normal Stall Warning Speeds
(Inadvertent Stall Warning).................................................................................................... 3A-4
SAS SERVO FAIL Light On in Flight ......................................................................................... 3A-5
SAS FAIL Light On in Flight ...................................................................................................... 3A-5
Electrical System Malfunctions .......................................................................................................... 3A-6
Excessive Ammeter Indication .................................................................................................. 3A-6
Battery Fault Light On ............................................................................................................... 3A-6
Generator Inoperative Fail Light Illuminated .......................................................................... 3A-7
Circuit Breaker Tripped ............................................................................................................. 3A-7
Inverter Inoperative AC Bus Lights Illuminated ...................................................................... 3A-7
Left Essential Bus Failure.......................................................................................................... 3A-8
Right Essential Bus Failure ....................................................................................................... 3A-8
Nonessential Bus Failure .......................................................................................................... 3A-9
Chip Light On Prior to Takeoff ............................................................................................................ 3A-9
Chip Light On During Flight ................................................................................................................ 3A-9
Weather Conditions Conducive to Severe In-flight Icing .................................................................. 3A-9A
Procedures for Exiting the Severe Icing Environment ...................................................................... 3A-9A
Inadvertent Icing Encounter ............................................................................................................. 3A-9B
Instrument Static Pressure Malfunction ........................................................................................... 3A-10
Landing Gear Squat Switch Malfunction .......................................................................................... 3A-10
Nose Wheel Steering Malfunction .................................................................................................... 3A-11
Manual Ground Start Procedures .................................................................................................... 3A-12
Starting Engines (GPU) ........................................................................................................... 3A-13
Right Engine (Recommended First) (For airplanes that have incorporated
Service Bulletin CC7-80-001) .............................................................................................. 3A-13
Left Engine (For airplanes prior to S/N DC-884 NOT modified by Service Bulletin
CC7-24-002) ........................................................................................................................ 3A-14
Left Engine (For S/N DC-884 and subsquent, and airplanes modified in accordance with
Service Bulletin CC7-24-002) ............................................................................................ 3A-14A
Right Engine (Recommended First) (For airplanes that have NOT incorporated
Service Bulletin CC7-80-001) ............................................................................................ 3A-14B
Left Engine (For airplanes prior to S/N DC-884 NOT modified by Service Bulletin
CC7-24-002) ...................................................................................................................... 3A-14C
Left Engine (For S/N DC-884 and subsquent, and airplanes modified in accordance with
Service Bulletin CC7-24-002) ............................................................................................ 3A-14D

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-i

Revised: DEC 07/07 6CC
 SA227-CC
TABLE OF CONTENTS (continued)
ABNORMAL PROCEDURES

ITEM PAGE

Battery Start .......................................................................................................................... 3A-14E

Temperature Limiter Malfunctions .................................................................................................... 3A-15
Operations with the Temperature Limiter Inoperative ............................................................. 3A-15
Operations with Temperature Limiter Inoperative (Fuel Bypass Valve Failed Open) ............. 3A-15
Operations with Temperature Limiter Inoperative (Fuel Bypass Valve Failed Closed) ........... 3A-16
SRL Computer Failure ..................................................................................................................... 3A-17
Simulated SRL Computer Failure............................................................................................ 3A-17
EGT Limit with SRL Inoperative 100% RPM ........................................................................... 3A-18
EGT Limit with SRL Inoperative 97% RPM ............................................................................. 3A-20
Preplanned Engine Shutdown/Airstart ............................................................................................. 3A-22
Preparation for Engine Shutdown ........................................................................................... 3A-22
Engine Shutdown .................................................................................................................... 3A-23
Preparation for Immediate Airstart .......................................................................................... 3A-25
Airstart ..................................................................................................................................... 3A-25
Airstart Procedure with SRL Computer Inoperative ................................................................ 3A-27
Aborted Airstart (Due to No Combustion) ................................................................................ 3A-28
Pressurization/Air Conditioning System Malfunctions ...................................................................... 3A-28
Cold Air .................................................................................................................................... 3A-28
Conditioned Air ........................................................................................................................ 3A-28
Unpressurized Flight ............................................................................................................... 3A-28
Low Suction Light On .............................................................................................................. 3A-28
High Oil Temperature ....................................................................................................................... 3A-28

3A-ii ABNORMAL PROCEDURES FAA APPROVED: DEC 02/97

6CC Revised: DEC 07/07
 SA227-CC
INTRODUCTION

The Abnormal Procedures section is an extension of the Emergency Procedures section and covers
situations of a less serious nature. Procedures identified by an asterisk are those recommended to be
accomplished by a copilot during two pilot operations. These procedures have been FAA approved.

ANNUNCIATOR PANEL

The functions of the annunciator panel amber lights are shown in the following table.

LIGHT ILLUMINATED INDICATES THAT

L or R BETA Corresponding prop pitch control oil pressure is sufficient

to command reverse operation.

L or R CHIP DET Magnetic plug in corresponding engine has detected foreign

object in oil. See page 3A-9.

L or R XFER PUMP Corresponding hopper tank fuel level is low. See page
3A-3.

L or R BAT DISC Corresponding battery switch is not on or that there has

been a feeder circuit fault. See page 3A-6.

L or R AC BUS a. Both lights on: The selected inverter has failed. See
page 3A-7.
b. One light on: The 115V bus tie has failed. Reset
circuit breaker.

L or R GEN(ERATOR) FAIL Corresponding generator switch is not on or that the

generator has failed. See page 3A-7.

LOW SUCTION There is insufficient output from the suction regulator.

See pages 3A-28 effect on Pressurization, 2-47
effect on Deice Boots and 2-21 effect on vacuum Flight
Instruments.

GPU PLUG IN The ground power unit is plugged into the aircraft. Do not
attempt to put generators on line and do not taxi.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-1

Revised: JUN 03/99 6CC
 SA227-CC
ANNUNCIATOR PANEL (continued)

LIGHT ILLUMINATED INDICATES THAT

L or R SRL OFF Corresponding engine RPM is less than 80% when SRL
power switch is normal or that the SRL computer has
failed. See page 3A-17.

NWS FAIL Flashing light indicates that the NWS system has
detected an electrical fault and has automatically
disengaged the NWS system. Steering reverts to caster
mode.

L or R SAS FAIL a. SAS computer has failed or lost power. See page
3A-5.
b. On the ground, the respective SAS vane may be blown
full up. (Check SAS indicator needle.)
c. Either pilot or copilot stall light module has been
pressed, removing power from the respective SAS
computer. See page 3A-4.

SAS SERVO (FAIL) a. Power is not available to the SAS servo (check SAS
servo switch) or SAS servo has failed. See page 3A-5.
b. Proper indication during a servo monitor (SERVO
MON) test (after an approximate two second delay)
c. Proper indication during a NO. 1 or NO. 2 g switch
test.

L or R FUEL FILTER Indicates corresponding fuel filter is being bypassed due

to filter blockage. See page 3A-4.

3A-2 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: JUN 03/99
 SA227-CC
FUEL SYSTEM MALFUNCTIONS

BOOST PUMP FAILURE

In the event of a boost pump failure, as indicated by low fuel pressure, the auxiliary boost pumps should
be selected. See Figure 1-1 for no boost pumps required flight envelope.

FUEL TRANSFER PUMP CAUTION LIGHT ON

The fuel pump caution lights illuminate when fuel quantity in the respective hopper tank is less than
approximately 70 pounds (32 kg). The light switches are actuated by a float located in each hopper
tank. Nuisance caution lights may occur following refueling if a float switch sticks in its low quantity
position. The false indication often will correct itself during taxi. Takeoff with fuel transfer pump caution
light(s) illuminated is prohibited.

With the boost pumps and transfer pumps operating, the XFER PUMP annunciator light will illuminate
when the wing tank is empty and the hopper tank fuel is below approximately 70 pounds.

With the boost pumps and/or transfer pumps not operating, fuel will gravity feed from the wing tank into
the hopper tank and the XFER PUMP annunciator will illuminate when the wing tank fuel level
reaches the hopper tank float switch level (approximately 600 700 pounds of fuel remaining in that
wing). Without a boost pump operating, approximately 75 pounds of the indicated fuel is unusable.

In the event that a XFER PUMP annunciator illuminates with a boost pump ON , the other boost pump
in that tank should be selected.

CAUTION

WITH TRANSFER PUMPS OPERATIVE AND LESS THAN 70

POUNDS OF FUEL IN THE AFFECTED TANK, THE TRANSFER
PUMP CAUTION LIGHT SERVES AS A LOW FUEL WARNING.
A LANDING SHOULD BE MADE AS SOON AS PRACTICABLE.

NOTE

Whenever selecting or switching boost pumps, the same pump

(Main or Auxiliary) should be used on both sides to insure that
subsequent failure of an essential bus will cause loss of boost
pump pressure to only one engine.

OPERATION WITH FUEL IMBALANCE

Takeoff with a fuel imbalance up to 200 pounds (90 kg) is permitted using the normal performance
data contained in Section 4. During takeoff and initial climb, aileron trim and/or control wheel force in
the direction of the light wing will be required. The wheel force requirement increases with increased
imbalance and decreases with increased airspeed.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-3

6CC
 SA227-CC
FUEL SYSTEM MALFUNCTIONS (continued)

LEFT OR RIGHT FUEL FILTER LIGHT ON

Fuel is bypassing due to a blockage. Monitor engine indications for abnormalities (i.e. fluctuations in
fuel pressure or fuel flow). (See page 6B-49 Fuel Control System.)

FUEL BALANCING PROCEDURE

Prior to initiating a fuel transfer, test the fuel quantity indicating system by depressing the "Push to Test"
button. During preflight, magna sticks can be used to verify fuel quantity, but only between 30-155 gallons
per side.

Ground Operations

1. On a level surface, open the cross flow valve and observe the proper annunciation. Fuel will flow
in the desired direction (heavy to light) due to gravity. The fuel transfer process can be expedited
by utilizing local ramp/taxiway inclines.

2. When proper balance has been achieved, close the cross flow valve and note proper valve
annunciation.

In Flight Operations
WARNING
AUTOPILOT/YAW DAMPER USE DURING FUEL BALANCING IS
PROHIBITED.

1. Check aircraft is in coordinated flight.

2. Open Cross Flow Valve and observe proper annunciation. In level unaccelerated flight, fuel will flow
in the desired direction (heavy to light) due to gravity.

3. To expedite process, use aileron control and place the wing with less fuel to a lower position (no more
than 5 degrees is needed) than the wing with more fuel. Use rudder to maintain assigned heading.
Maintain a safe margin of airspeed during this slip condition.

4. When fuel balance approaches desired indications, close the cross flow valve, check for proper
annunciation, and return aircraft to trimmed condition.

5. If fuel balance cannot be achieved, or the imbalance worsens, stop the cross feed process
immediately by closing the cross flow valve. Land as soon as conditions permit, and determine
cause.

3A-3A ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: DEC 07/07
 SA227-CC

INTENTIONALLY LEFT BLANK

FAA APPROVED: DEC 07/07 ABNORMAL PROCEDURES 3A-3B

6CC
 SA227-CC
STALL AVOIDANCE SYSTEM (SAS) MALFUNCTIONS

CAUTION

WITH EITHER SAS COMPUTER OR THE SAS SERVO

TURNED OFF (OR INOPERATIVE), THE STICK PUSHER
WILL BE INOPERATIVE. STALL WARNING WILL STILL BE
PROVIDED BY ACTIVATION OF THE STICK SHAKERS 5 TO
10 KNOTS ABOVE STALL SPEED. ANGLE OF ATTACK
SHOULD BE IMMEDIATELY REDUCED TO PROVIDE AN
ADEQUATE MARGIN ABOVE STALL SPEED. IF ANGLE OF
ATTACK IS INADVERTENTLY ALLOWED TO INCREASE,
STALL RECOVERY SHOULD BE INITIATED AT THE FIRST
NATURAL OR SAS INDICATION OF STALL (GLARESHIELD
STALL LIGHT AND/OR STALL HORN).

STICK SHAKER AT SPEEDS WELL IN EXCESS OF NORMAL STALL WARNING SPEEDS

(INADVERTENT STALL WARNING)

If the stick shakers activate in unaccelerated flight at speeds well in excess of normal stall warning
speed, possible damage to a SAS vane or a system malfunction is indicated.

1. Stall Light Module (either SAS) .................................................................................. PRESS OFF

If stick shakers continue to shake, proceed with step 2.
2. Stall Light Module (operating SAS) ............................................................................ PRESS OFF
If stick shakers stop shaking, proceed with step 3.
3. Stall Light Module (first SAS disabled) ........................................................................ PRESS ON

NOTE

Pressing either stall light module will remove power immediately

from the respective SAS computer and render the SAS pusher
servo inoperative. The pilot's stall light module controls the left
SAS computer and the copilot's stall light module controls the
right SAS computer.

Both stall warning stick shakers and the stall horns and
glareshield STALL lights for the operating SAS computer
will still be operational. The stick pusher will not operate with
either SAS computer turned off.

3A-4 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: DEC 07/07
 SA227-CC
STALL AVOIDANCE SYSTEM (SAS) MALFUNCTIONS (continued)

SAS SERVO FAIL LIGHT ON IN FLIGHT

* SAS SERVO Switch .................................................. OFF (SAS FAIL LIGHT WILL REMAIN ON)

NOTE

The stall warning stick shakers, stall horns and glareshield

STALL lights will still be operational.

SAS FAIL LIGHT ON IN FLIGHT

1. Stall Light Module (for affected SAS) ................................................................................. PRESS

2. SAS Indicator Select Switch ............................................................... SELECT OPERATING SAS

NOTE

Pressing either stall light module will remove power immediately

from the respective SAS computer and render the SAS pusher
servo inoperative. The pilot's stall light module controls the left
SAS computer and the copilot's stall light module controls the
right SAS computer.

Both stall warning stick shakers and the stall horns and
glareshield STALL lights for the operating SAS computer will
still be operational. The stick pusher will not operate with
either SAS computer turned off.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-5

6CC
 SA227-CC
ELECTRICAL SYSTEM MALFUNCTIONS (See Section 3 for Total Electrical Failure)

EXCESSIVE AMMETER INDICATION

If an excessive load occurs, as indicated by an excessive ammeter indication, the malfunctioning

circuit should be identified and turned off.

1. Battery Switches ...................................................................................................................... OFF

a. If overload condition still exists, turn battery switches ON and continue to Step 2.
b. If overload condition ceases, a battery circuit malfunction exists and the malfunctioning
circuit must remain disconnected from the DC electrical bus.
Isolate the malfunctioning circuit by turning the battery switches ON individually. Leave
the switch for the malfunctioning circuit OFF.

If Step 1 did not correct the excessive ammeter indication:

2. Nonessential Bus Tie Switch ................................................................................................... OFF
a. If overload condition still exits, turn the nonessential bus switch ON and continue to Step 3.
b. If overload condition ceases, pull all circuit breakers on the nonessential bus and turn the
bus tie switch ON. Reset circuit breakers until the malfunctioning circuit is identified. Pull
circuit breaker for malfunctioning circuit and do not reset. See Note following Step 3.

If Step 2 did not correct the excessive ammeter indication:

3. Left and Right Essential Bus Tie Switches ................................................... REPEAT THE SAME
PROCEDURE FOR EACH ESSENTIAL BUS
UNTIL SOURCE OF THE PROBLEM IS
FOUND AND MALFUNCTIONING
CIRCUIT IS ISOLATED

NOTE

It may be preferable to leave the malfunctioning bus off in flight

and to troubleshoot the difficulty after landing.

BATTERY FAULT LIGHT ON

NOTE

A fault in either battery feeder circuit will cause both battery relays
to disconnect automatically from the aircraft electrical system.
Both battery relays will remain open until either battery switch is
moved to RESET, then ON.

1. Both Battery Switches ............................................................................................................. OFF

2. Left Battery Switch ....................................................................................................... RESET/ON

If no fault exists in the left feeder circuit, the battery fault light will remain off. In this case, leave the left
battery switch ON and proceed to Step 3.

3A-6 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: JUN 03/99
 SA227-CC
ELECTRICAL SYSTEM MALFUNCTIONS (continued)

BATTERY FAULT LIGHT ON (continued)

If a fault exists in the left circuit, the battery will automatically disconnect and the light will come back
on. In this case, move the left battery switch to RESET (to reset the detector circuit), then OFF and
proceed to Step 3.

3. Right Battery Switch .................................................................................................................. ON

If no fault exists in the right feeder circuit, the battery fault light will remain off. In this case, leave the
right battery switch ON.

If a fault exists in the right circuit, both batteries will automatically disconnect and the light will come
back on. In this case, move the right battery switch to RESET (to reset the detector circuit), then OFF
and turn the left battery back on.

NOTE

Either generator switch, when positioned to RESET, then ON

will also reset the battery fault detection circuit.

All electrically operated components can be operated normally

on power from the generators when the battery switches are off.

GENERATOR INOPERATIVE FAIL LIGHT ILLUMINATED

1. Generator Switch..................................................................................................OFF/RESET/ON

If the generator will not reset:

2. Generator Switch..................................................................................................................... OFF

CAUTION

DO NOT EXCEED LIMIT LOAD ON OPERATING GENERATOR.

CIRCUIT BREAKER TRIPPED

Circuit Breaker ................................................................................................... PUSH TO RESET

CAUTION

IF CIRCUIT BREAKER TRIPS AGAIN, DO NOT RESET.

INVERTER INOPERATIVE AC BUS LIGHTS ILLUMINATED

* Select other inverter.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-7

Revised: JUN 03/99 6CC
 SA227-CC
ELECTRICAL SYSTEM MALFUNCTIONS (continued)

LEFT ESSENTIAL BUS FAILURE

1. Standby Instrument Power Switch ................................ VERIFY ARMED/STBY PWR LIGHT ON

2. Left Essential Bus Tie Switch .................................................................................................. OFF
3. Bus Transfer Switches ................................................................................................RIGHT BUS

Failure of the left essential bus will activate the standby instrument power system which will
automatically power and light the following:

A. Standby attitude indicator C. Pilot's altimeter

B. Pilot's airspeed indicator

The following items automatically switch to the opposite essential bus:

A. Engine instruments C. Fire detection/extinguisher

B. Ignition D. CAWI Pump

Activating the bus transfer switches will restore power to the following systems:

A. Fuel crossflow D. Deice boots

B. Windshield heat E. Cabin pressure dump valve
C. Landing gear control and indication F. Engine intake heat

The following items can be operated by the right essential bus:

A. Pitch trim (select copilot's system) C. Left boost pump (select AUX)
B. AC power (select inverter #2)

The following items (on the affected side) can not be powered following an essential bus failure:

A. Prop deice & duct heat D. SRL & temp limiter

B. Pitot heat E. Fuel & hyd shutoffs
C. SAS

RIGHT ESSENTIAL BUS FAILURE

1. Right Essential Bus Tie Switch ............................................................................................... OFF

2. Bus Transfer Switches .................................................................................................. LEFT BUS

The following items automatically switch to the opposite essential bus:

A. Engine instruments D. CAWI Pump

B. Ignition E. Mach/airspeed warning
C. Fire detection/extinguisher

The following items can be operated by the left essential bus:

A. Pitch trim (select pilot's system) C. Right boost pump (select AUX)
B. AC power (select inverter #1)

3A-8 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC
 SA227-CC
ELECTRICAL SYSTEM MALFUNCTIONS (continued)

RIGHT ESSENTIAL BUS FAILURE (continued)

The following items (on the affected side) can not be powered following an essential bus failure:

A. Prop deice & duct heat D. SRL & temp limiter

B. Pitot heat E. Fuel & hyd shutoffs
C. SAS

NONESSENTIAL BUS FAILURE

Nonessential Bus Tie Switch ................................................................................................... OFF

The following systems can not be powered following a nonessential bus failure:

A. Flaps C. All exterior lights

B. NWS

CHIP LIGHT ON PRIOR TO TAKEOFF

If the chip light illuminates prior to takeoff, the flight should be aborted and the cause of the warning
determined.

CHIP LIGHT ON DURING FLIGHT

If the chip light illuminates and engine operation appears to be normal, continue to the first intended
landing and determine cause. The affected engine and instruments should be monitored closely
during flight.

If the chip light illuminates and engine operation does not appear to be normal, the affected engine
should be shut down (ENGINE FAILURE DURING FLIGHT) and a single engine landing accomplished.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-9

Revised: JUN 03/99 6CC
 SA227-CC
WEATHER CONDITIONS CONDUCIVE TO SEVERE IN-FLIGHT ICING:

Visible rain at temperatures below 0 degrees Celsius ambient air temperature.

Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius ambient air
temperature.

PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT:

Monitor the ambient air temperature. While severe icing may form at temperatures as cold as 18
degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture
present. If the visual cues for identifying severe icing conditions are observed, accomplish the
following:

Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude
change to exit the severe icing conditions. Avoid extended exposure to icing conditions more
severe than those for which the airplane has been certified.

Avoid abrupt and excessive maneuvering that may exacerbate control difficulties.

Do not engage the autopilot.

If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot.

If an unusual roll response or uncommanded roll control movement is observed, reduce the
angle-of-attack.

Do not extend flaps during extended operation in icing conditions. Operation with flaps extended
can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper
surfaces further aft on the wing than normal, possibly aft of the protected area.

If the flaps are extended, do not retract them until the airframe is clear of ice.

Report these weather conditions to Air Traffic Control.

3A-9A ABNORMAL PROCEDURES FAA APPROVED: JUN 03/99

6CC
 SA227-CC
INADVERTENT ICING ENCOUNTER

If icing is encountered with the ice protection systems off, the following procedure should be followed:

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

2. IGN Lights ................................................................................................................... CHECK ON
3. Left Engine Heat Switch .......................................................................... ENGINE & PROP HEAT

NOTE

Determine that the first engine operates satisfactorily before

selecting engine and prop heat for the second engine.

EGT will increase slightly and torque will decrease when engine
and propeller heat is selected. Power lever adjustment may be
required.

4. Pitot/SAS Heat Switches ..................................................................................... PITOT AND SAS

5. Windshield Heat Switch ......................................................................................................... HIGH
6. Deice Boots Switch ............................. AUTO (AT THE FIRST SIGN OF ICE FORMATION
ANYWHERE ON THE AIRCRAFT)
7. Right Engine Heat Switch ........................................................................ ENGINE & PROP HEAT

WARNING

ENGINE HEAT AND THE CONTINUOUS IGNITION SYSTEM,

IN THE AUTO/CONT MODE, MUST BE USED AFTER LEAVING
ICING CONDITIONS UNTIL THE PILOT IS CONFIDENT THAT
ANY RESIDUAL ICE ON PROPELLERS, SPINNERS, INTAKE
LIPS, OR INTAKE THROATS WILL NOT BE SHED INTO
THE ENGINES.

FAA APPROVED: JUN 03/99 ABNORMAL PROCEDURES 3A-9B

Revised: JUN 02/00 6CC
 SA227-CC
INSTRUMENT STATIC PRESSURE MALFUNCTION (PILOT'S INSTRUMENTS)

If the pilots static pressure instruments malfunction, select ALTERNATE position on the static source
selector valve. The pilots instruments will be vented to the forward baggage compartment. See
Section 4 of this manual for corrected airspeed and altimeter readings when operating on the
alternate source.

CAUTION

DO NOT DUMP PRESSURIZATION WHEN USING THE

ALTERNATE STATIC PRESSURE SOURCE.

THE ALTERNATE STATIC SOURCE ALTITUDE AND

AIRSPEED CORRECTIONS SHOWN IN SECTION 4 OF THIS
MANUAL ARE NOT VALID IF THE DUMP VALVE IS OPEN.

NOTE

The copilots static pressure instruments are not connected to

the alternate static pressure source.

LANDING GEAR SQUAT SWITCH MALFUNCTION

A squat switch on the left main landing gear controls power to the landing gear control solenoid-
operated down lock plunger. Should the squat switch malfunction after takeoff, the down lock plunger
would remain in its extended position and lock the control lever in its down position. If it is necessary to
retract the gear when the plunger is extended, move the override release lever down and counter-
clockwise and then move the landing gear control lever to its up position.

3A-10 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: JUN 03/99
 SA227-CC
NOSE WHEEL STEERING MALFUNCTION

Fault protection is provided by circuitry which automatically deactivates the nose wheel steering if
an electrical malfunction occurs. The nose wheel is then free to caster. 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 by rudder, differential braking, and/or differential power.

In the event of a flashing NWS FAIL light, an unwanted steering deflection, and/or a park light
illuminated when the park button is not depressed, the following procedure should be followed:

NOTE

It is normal for the park light to remain illuminated, but vary in

intensity, during the transition from park mode to normal mode.

1. Directional Control ............................... MAINTAIN WITH RUDDER, BRAKES, AND/OR POWER

2. Nose Wheel Steering Arm Switch ........................................................................................... OFF

NOTE

If the nose wheel steering arm switch is in the ARMED position

while an engine is being started, the system may sense a low
voltage condition and disengage the NWS system, causing a
flashing NWS FAIL light. If this occurs on the ground before
takeoff, the nose wheel steering arm switch should be cycled to
OFF and back to ARMED to reset the system.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-11

Revised: APR 28/00 6CC
 SA227-CC
MANUAL GROUND START PROCEDURES

Certain malfunctions in the engine starting system can prevent a normal, automatic engine ground
start. An example is failure of the 10% and 60% speed functions in the SRL computer. In this case,
other SRL functions could remain operative; however, an automatic start would not be obtained
because fuel and ignition sequencing controlled by the 10% and 60% speed functions would be
inoperative. A manual start can be accomplished using the appropriate speed switch select switch
located on the pilots side console. These switches enable the pilot to bypass the normally automatic
engine speed functions.

During a manual start it is not necessary to place the SRL P/P switch in the OFF position. Confirm
that the SRL OFF light is illuminated (a normal indication whenever engine RPM is less than 80%) and
leave the SRL P/P switch in the NORM position. On aircraft that have incorporated Service Bulletin
CC7-80-001 when the speed select switch is placed in the manual position auto fuel enrichment is
disabled. Fuel enrichment must be accomplished by the pilot.

NOTE

During a manual start, start fuel enrichment can be obtained by

pressing the start button. When using the start button to manually
provide start fuel enrichment, modulate the start button and
attempt to emulate a normal automatic start. Maintain normal
engine acceleration and an EGT of approximately 685oC 695oC.

On aircraft that have not incorporated Service Bulletin CC7-80-001 when the speed select switch is
placed in the manual position the Temp Limiter is enabled and will prevent start temperatures from
exceeding 650oC. This may inhibit engine acceleration during the start (most noticeable between
35 40% RPM) and may result in a hung start and possible damage to the engine unless the start is
aborted properly. On such aircraft (Pre Service Bulletin CC7-80-001) the Temp Limiter circuit breaker
must be pulled to disable the Temp Limiter during the start and then reset after the engine has
stabilized at idle prior to accomplishment of the required SRL checks.

Start fuel enrichment, which is normally an automatic function, must be accomplished manually by
pressing the start button during a manual engine start when the SRL P/P power switch is off.

NOTE

After accomplishing a manual ground start, all SRL system

checks must be accomplished satisfactorily prior to flight, see
page 2-33.

3A-12 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: APR 28/00
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

STARTING ENGINES (GPU)

CAUTION

USE ONLY NEGATIVELY GROUNDED POWER SOURCES.

DUE TO THE POSSIBILITY OF EXCESSIVELY HIGH

CURRENT SURGE DURING ENGINE START, IT IS
RECOMMENDED THAT THE MAXIMUM STARTING
CURRENT FROM A GROUND POWER SOURCE BE
LIMITED TO 1,000 AMPERES.

RIGHT ENGINE (RECOMMENDED FIRST)

(For airplanes that have incorporated Service Bulletin CC7-80-001)

*1. Propeller ................................................................... UNFEATHERED/CLEAR (SEE PAGE 2-22)

2. Engine Start Button ........................................................................................ PRESS AND HOLD
3. Speed Switch Select Switch ..................................................................... MANUAL AT 10% RPM

NOTE

Observe illumination of IGN light and ignition of fuel as indicated

by rising EGT. Use the start button as required to provide fuel
enrichment between 10% and 60% RPM. (See NOTE Page 3A-12)

CAUTION

IF EGT RISE IS NOT OBTAINED WITHIN 10 SECONDS

AFTER REACHING 10% RPM, OR BEFORE ATTAINING 20%
RPM, PULL ENGINE STOP AND FEATHER CONTROL AND
PRESS THE STOP BUTTON. CLEAR ENGINE FOR 10
SECONDS WITH STARTER TEST SWITCH. DO NOT
ALLOW ENGINE TO OPERATE IN THE 18% TO 28% RPM
RANGE DURING START OR CLEARING OPERATIONS
EXCEPT DURING COMBUSTION ASSISTED ACCELERATION
THROUGH THAT RANGE.

4. EGT ....................................................................................................... MONITOR (770oC MAX)

CAUTION

IF RPM STOPS INCREASING AND EGT IS APPROACHING

THE START LIMIT AND RISING RAPIDLY, IMMEDIATELY
PULL ENGINE STOP AND FEATHER CONTROL AND PRESS
THE STOP BUTTON. EXCEEDING THE START EGT LIMIT
MAY SERIOUSLY DAMAGE THE ENGINE.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-13

Revised: APR 28/00 6CC
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

RIGHT ENGINE (RECOMMENDED FIRST) (continued)

(For airplanes that have incorporated Service Bulletin CC7-80-001) (continued)

5. RPM and EGT ............................................................................................................STABILIZED

6. Fuel and Oil Pressure ...................................................................... YELLOW OR GREEN ARCS
*7. Bleed Air Switch (right engine) .............................................................................. AS REQUIRED

NOTE

Check for absence of air flow through the open cooling air
eyeballs prior to turning on either bleed air system.

8. Speed Switch Select Switch ................................................................................................. AUTO

LEFT ENGINE Manual Start (If Required)

(For airplanes prior to S/N CC-884 NOT modified by Service Bulletin CC7-24-002)

9. Repeat Steps 1 Through 6 and 8 for Left Engine.

*10. Bleed Air Switch (left engine) ................................................................................ AS REQUIRED

NOTE

Verify operation of each bleed air system by selectively

operating right and left systems, both low and high.

11. GPU ..................................................... OFF/DISCONNECTED/ANNUNCIATOR CHECKED OUT

12. Generators ............................................................................ RESET/VOLTAGES CHECKED/ON

NOTE

Check generator voltages between 29 29.5 and even load

sharing.

13. Battery Disconnects and Current Limiters .......................................................................... CHECK

(SEE PAGES 2-21 AND 2-30)

NOTE

After accomplishing a manual ground start, all SRL system

checks must be accomplished satisfactorily prior to flight, see
page 2-33.

3A-14 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: APR 28/00
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

LEFT ENGINE Manual Start (If Required)

(For S/N CC-884 and subsquent, and airplanes modified in accordance with Service Bulletin
CC7-24-002)

9. Repeat Steps 1 Through 6 and 8 for Left Engine.

*10. Bleed Air Switch (left engine) ................................................................................ AS REQUIRED

NOTE

Verify operation of each bleed air system by selectively

operating right and left systems, both low and high.

11. GPU ..................................................... OFF/DISCONNECTED/ANNUNCIATOR CHECKED OUT

12. Generators .......................................... ON/CHECK VOLTS AND AMPS AND EVEN LOAD
SHARING

CAUTION

IF THE GENERATOR SWITCH IS RESET AND ON,

GENERATOR VOLTAGE IS OBSERVED, GEN FAIL
ANNUNCIATOR LIGHT IS NOT ILLUMINATED, AND THE
AMMETER READS ZERO, THE RESPECTIVE 400 AMPERE
CURRENT LIMITER IS OPEN. THE FAULTY CURRENT
LIMITER SHOULD BE REPLACED PRIOR TO FLIGHT.

13. Battery Disconnects .............................................................................. CHECK(SEE PAGE 2-30)

NOTE

After accomplishing a manual ground start, all SRL system

checks must be accomplished satisfactorily prior to flight, see
page 2-33.

FAA APPROVED: DEC 02/97 ABNORMAL PROCEDURES 3A-14A

Revised: APR 28/00 6CC
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

RIGHT ENGINE (RECOMMENDED FIRST)

(For airplanes that have NOT incorporated Service Bulletin CC7-80-001)

*1. Propeller ................................................................... UNFEATHERED/CLEAR (SEE PAGE 2-22)

2. Temperature Limiter Circuit Breaker ..................................................................................... PULL
3. Engine Start Button ........................................................................................ PRESS AND HOLD
4. Speed Switch Select Switch ..................................................................... MANUAL AT 10% RPM

NOTE

Observe illumination of IGN light and ignition of fuel as indicated

by rising EGT. Use the start button as required to provide fuel
enrichment between 10% and 60% RPM. (See NOTE Page 3A-12)

CAUTION

IF EGT RISE IS NOT OBTAINED WITHIN 10 SECONDS

AFTER REACHING 10% RPM, OR BEFORE ATTAINING 20%
RPM, PULL ENGINE STOP AND FEATHER CONTROL AND
PRESS THE STOP BUTTON. CLEAR ENGINE FOR 10
SECONDS WITH STARTER TEST SWITCH. DO NOT
ALLOW ENGINE TO OPERATE IN THE 18% TO 28% RPM
RANGE DURING START OR CLEARING OPERATIONS
EXCEPT DURING COMBUSTION ASSISTED ACCELERATION
THROUGH THAT RANGE.

5. EGT ....................................................................................................... MONITOR (770oC MAX)

CAUTION

IF RPM STOPS INCREASING AND EGT IS APPROACHING

THE START LIMIT AND RISING RAPIDLY, IMMEDIATELY
PULL ENGINE STOP AND FEATHER CONTROL AND PRESS
THE STOP BUTTON. EXCEEDING THE START EGT LIMIT
MAY SERIOUSLY DAMAGE THE ENGINE.

6. RPM and EGT ............................................................................................................STABILIZED

7. Fuel and Oil Pressure ...................................................................... YELLOW OR GREEN ARCS
*8. Bleed Air Switch (right engine) .............................................................................. AS REQUIRED

NOTE

Check for absence of air flow through the open cooling air
eyeballs prior to turning on either bleed air system.

9. Speed Switch Select Switch ................................................................................................. AUTO

10. Temperature Limiter Circuit Breaker .................................................................................. RESET

3A-14B ABNORMAL PROCEDURES FAA APPROVED: APR 28/00

6CC
 SA227-CC
MANUAL GROUND START PROCEDURES (continued

LEFT ENGINE Manual Start (If Required)

(For airplanes prior to S/N CC-884 NOT modified by Service Bulletin CC7-24-002)

11. Repeat Steps 1 Through 7, 9 and 10 for Left Engine.

*12. Bleed Air Switch (left engine) ................................................................................ AS REQUIRED

NOTE

Verify operation of each bleed air system by selectively

operating right and left systems, both low and high.

13. GPU ..................................................... OFF/DISCONNECTED/ANNUNCIATOR CHECKED OUT

14. Generators ............................................................................ RESET/VOLTAGES CHECKED/ON

NOTE

Check generator voltages between 29 29.5 and even load

sharing.

15. Battery Disconnects and Current Limiters .......................................................................... CHECK

(SEE PAGES 2-21 AND 2-30)

NOTE

After accomplishing a manual ground start, all SRL system

checks must be accomplished satisfactorily prior to flight, see
page 2-33.

FAA APPROVED: APR 28/00 ABNORMAL PROCEDURES 3A-14C

6CC
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

LEFT ENGINE Manual Start (If Required)

(For S/N CC-884 and subsquent, and airplanes modified in accordance with Service Bulletin
CC7-24-002)

11. Repeat Steps 1 Through 7, 9 and 10 for Left Engine.

*12. Bleed Air Switch (left engine) ................................................................................ AS REQUIRED

NOTE

Verify operation of each bleed air system by selectively

operating right and left systems, both low and high.

13. GPU ..................................................... OFF/DISCONNECTED/ANNUNCIATOR CHECKED OUT

14. Generators .......................................... ON/CHECK VOLTS AND AMPS AND EVEN LOAD
SHARING

CAUTION

IF THE GENERATOR SWITCH IS RESET AND ON,

GENERATOR VOLTAGE IS OBSERVED, GEN FAIL
ANNUNCIATOR LIGHT IS NOT ILLUMINATED, AND THE
AMMETER READS ZERO, THE RESPECTIVE 400 AMPERE
CURRENT LIMITER IS OPEN. THE FAULTY CURRENT
LIMITER SHOULD BE REPLACED PRIOR TO FLIGHT.

15. Battery Disconnects .............................................................................. CHECK(SEE PAGE 2-30)

NOTE

After accomplishing a manual ground start, all SRL system

checks must be accomplished satisfactorily prior to flight, see
page 2-33.

3A-14D ABNORMAL PROCEDURES FAA APPROVED: APR 28/00

6CC
 SA227-CC
MANUAL GROUND START PROCEDURES (continued)

BATTERY START

Follow Starting Engines (GPU) (For airplanes that have incorporated Service Bulletin CC7-80-001)
procedures steps 1 through 10, 12 and 13; (For airplanes that have NOT incorporated Service Bulletin
CC7-80-001) procedures steps 1 through 12, 14 and 15 except as modified by the following notes:

NOTE

The series mode is recommended for use during the first start
of the day and for other battery starts when engines have
cooled to near ambient temperatures since last being operated.

If either battery temperature is above 120oF (amber caution light

illuminated), do not make a battery start. Either obtain a GPU
or wait until the batteries have cooled.

Both torque indicators will display erroneous indications during

battery starts when the starter is engaged and bus voltage is low.

The inoperative engine RPM indicator is sensitive to bus voltage

variations prior to normal engine operation and may reflect
spurious fluctuations before engine starts when operating
various aircraft systems.

Generator for the first engine should be turned on after the

first engine start. The second engine should be started in
parallel mode with assistance from the operating generator after
ammeter drops to 150 amps. If desired, stresses on the
assisting generator due to initial high current demands may be
reduced using the start procedure on page 6C-1.

FAA APPROVED: APR 28/00 ABNORMAL PROCEDURES 3A-14E

6CC
 SA227-CC

THIS PAGE LEFT BLANK INTENTIONALLY

3A-14F ABNORMAL PROCEDURES MANUFACTURER'S DATA

6CC ISSUED: APR 28/00
 SA227-CC
TEMPERATURE LIMITER MALFUNCTIONS

OPERATIONS WITH THE TEMPERATURE LIMITER INOPERATIVE

An inoperative temperature limiter circuit results in loss of automatic temperature control. When the
temperature limiter becomes inoperative the pilot must use caution in power management. The EGT
indication lags actual engine performance. The following procedures should be followed when the
temperature limiter is inoperative.

1. Do not advance power lever rapidly beyond 50% travel.

2. Set power lever carefully above 50% power to allow for EGT indication lag. Adjust power by
making small power lever position changes and allowing adequate time for EGT lag.

3. Changes in airspeed, temperature and/or altitude will produce changes in EGT. Monitor EGT
when operating the engine near the EGT limit.

OPERATIONS WITH TEMPERATURE LIMITER INOPERATIVE (FUEL BYPASS VALVE FAILED OPEN)

Failure of the fuel bypass valve in the open, or near open position, will allow fuel to be bypassed at all
times with possible low power being developed at intermediate power lever positions. A valve stuck
in a partially open position would be detected during the application of power for takeoff or during flight
at less than 650oC EGT due to the requirement for excessively split power levers at even EGTs.

CAUTION

TAKEOFF WITH A FUEL BYPASS VALVE FAILED IN THE

OPEN POSITION IS NOT APPROVED.

MAXIMUM ALTITUDE FOR PROLONGED OPERATION WITH

A FUEL BYPASS VALVE FAILED OPEN IS 15,000 FEET.

Failure in the open position while in flight might cause so much reduced fuel flow at the nozzles that, at
power lever settings near flight idle, the NTS system would activate. This potential difficulty could be
confirmed by retarding the power lever for the suspect engine to flight idle while flying at speeds near
final approach speed. If negative torquing occurs, the pilot has the options of landing with asymmetric
power levers in order to maintain even power, or of shutting down the engine with the failed fuel bypass
valve and making a single engine landing.

Temperature Limiter Circuit Breaker ..................................................................................... PULL

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-15

Revised: APR 28/00 6CC
 SA227-CC
TEMPERATURE LIMITER MALFUNCTIONS (continued)

OPERATIONS WITH TEMPERATURE LIMITER INOPERATIVE (FUEL BYPASS VALVE FAILED

CLOSED)

Takeoff and initial climb operations are conducted with power set to appropriate torque values
determined from the Takeoff Power Check Charts in Section 4. Therefore, a fuel bypass failure may
not be detected during normal operations until cruise power is set with EGT at 650oC. If fuel bypass
malfunctions are suspected after conducting the temp limiter check on page 2-34, the following ground
check will verify the status of the temperature limiting systems.

1. Speed Lever ................................................................................................................. HIGH RPM

2. Power Lever ................................................................... SET TO OBTAIN 350 PPH FUEL FLOW
3. Temp Limiter Test Switch .................... HOLD L THEN R. NOTE THAT RESPECTIVE FUEL
BYPASS LIGHTS ILLUMINATE AND THAT FUEL
FLOW FOR EACH ENGINE DROPS TO APPROXI-
MATELY 260 PPH

NOTE

It is permissible to conduct this check one engine at a time.

Failure of either engine to bypass approximately 90 PPH or

failure of either fuel bypass light to illuminate during this check
indicates a malfunction of the fuel bypass/temp limiter system.

If dry power takeoff operations are required with a fuel bypass

valve failed at its closed position, use normal takeoff, climb, and
cruise procedures taking care to not exceed 650oC EGT.

CAUTION

ENGINE OVER-TEMPERATURE AND CONSEQUENT ENGINE

DAMAGE MAY OCCUR WITH IMPROPER POWER LEVER
MANAGEMENT WHEN THE FUEL BYPASS VALVE HAS
FAILED IN THE CLOSED POSITION.

3A-16 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: APR 28/00
 SA227-CC
SRL COMPUTER FAILURE

A failure of the SRL system may be indicated by one or more of the following:

1. Illumination of an SRL OFF light with RPM above 80% which indicates loss of power to the
system, loss of signal to the computer, loss of computer output signal or that the difference
between compensated EGT and SRL value is less than 15oC.

2. A sudden change in EGT of 20oC or more with no corresponding change in other engine
parameters.

3. An erratic or fluctuating EGT indication.

4. SRL OFF light not illuminated with engine speed below 80% RPM.

5. SRL P/P power switch in the SRL OFF position.

NOTE

The SRL inoperative EGT charts in Figures 3A-1 and 3A-2

are provided only for maximum continuous power at 100% RPM
and for cruise power at 97% RPM. Cruise with SRL inoperative is
limited to between 96% and 98% or at 100% RPM.

When operating with the SRL computer inoperative:

1. Temperature Limiter Circuit Breaker ..................................................................................... PULL

The temperature limiter circuit will be inoperative; therefore, all the cautions listed under the
heading TEMPERATURE LIMITER MALFUNCTIONS apply and must be followed. Pull the
temperature limiter circuit breaker; place the SRL P/P power switch in the SRL OFF position.

2. Engine Power .......................................................................................................................... SET

The maximum allowable EGT will vary with altitude, airspeed, and temperature. The pilot must
operate the engine within the maximum EGT limits by obtaining the limiting EGT from Figure
3A-1 or 3A-2 in this section and adjusting engine power accordingly. An alternative method
of ensuring proper power on the engine which has suffered SRL failure is to match its torque
with that of the engine with operable SRL system.

After landing at the next scheduled destination, the SRL system must be repaired before
further flight or operations must be conducted in accordance with Supplement 1.

SIMULATED SRL COMPUTER FAILURE

Failure of the SRL computer may be simulated in flight as follows:

1. Adjust the power lever to extinguish the fuel BYPASS OPEN light.

2. Place the SRL P/P power switch in the SRL OFF position.

3. Manually control engine temperature to the appropriate limits from Figure 3A-1 or 3A-2.

CAUTION

ENGINE OVER-TEMPERATURE CAN RESULT FROM TURNING

THE SRL OFF WITH THE FUEL BYPASS OPEN LIGHT ON.
FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-17
6CC
 SA227-CC
SRL COMPUTER FAILURE (continued)

EGT LIMIT WITH SRL INOPERATIVE

100% RPM MAXIMUM CONTINUOUS POWER

NOTE

Indicated outside air temperature (IOAT) as shown in table

includes compressibility and position errors.

Airspeeds shown are provided to permit interpolation of

EGTs. Do not exceed VMO.

Applicable to all bleed air and anti-ice conditions.

EXAMPLE:
Given: Altitude = 15,000 Feet
Airspeed = 199 KIAS (200 KCAS)
IOAT = 6oC
Obtain: Maximum EGT = 562oC

INDICATED/CALIBRATED AIRSPEED (KNOTS)

ALTITUDE ISA OAT 98/100 149/150 199/200 248/250
(FEET) (oC) (oC) IOAT EGT IOAT EGT IOAT EGT IOAT EGT
30 15 14.1 564 12.9 563 11.3 561 9.2 558
20 5 4.0 572 2.8 570 1.2 569 1.0 566
10 5 6.0 579 7.2 578 9.0 576 11.2 574
SEA LEVEL 0 15 16.0 587 17.3 586 19.1 584 21.4 582
10 25 26.1 596 27.4 595 29.3 593 31.6 590
20 35 36.1 607 37.5 606 39.4 603 41.9 600
30 45 46.1 617 47.6 616 49.5 614 52.1 611
40 55 56.2 628 57.6 627 59.7 625 62.3 622
30 25 23.8 560 22.5 558 20.7 556 18.3 553
20 15 13.8 564 12.4 563 10.5 561 8.0 558
10 5 3.8 572 2.3 570 0.3 568 2.2 565
5,000 0 5 6.3 580 7.8 578 9.8 576 12.5 573
10 15 16.3 587 17.9 586 20.0 584 22.8 581
20 25 26.4 596 28.0 595 30.2 592 33.0 589
30 35 36.4 607 38.1 605 40.4 603 43.3 600
40 45 46.5 618 48.2 616 50.5 614 53.6 610
30 35 33.6 555 32.0 553 29.9 551 27.2 547
20 25 23.5 560 21.9 558 19.7 555 16.9 552
10 15 13.5 564 11.8 562 9.5 560 6.6 556
10,000 0 5 3.4 572 1.7 570 0.7 568 3.8 564
10 5 6.6 580 8.4 578 10.9 575 14.1 572
20 15 16.7 587 18.5 586 21.1 583 24.4 580
30 25 26.7 597 28.6 595 31.3 591 34.7 588
40 35 36.8 607 38.8 605 41.5 602 45.0 598

FIGURE 3A-1
3A-18 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92
6CC
 SA227-CC
SRL COMPUTER FAILURE (continued)

EGT LIMIT WITH SRL INOPERATIVE

100% RPM MAXIMUM CONTINUOUS POWER (continued)

INDICATED/CALIBRATED AIRSPEED (KNOTS)

ALTITUDE ISA OAT 98/100 149/150 199/200 248/250
(FEET) (oC) (oC) IOAT EGT IOAT EGT IOAT EGT IOAT EGT
30 45 43.3 551 41.5 549 39.0 546 35.9 542
20 35 33.2 555 31.4 553 28.8 550 25.5 546
10 25 23.2 560 21.2 558 18.5 555 15.2 551
15,000 0 15 13.1 565 11.1 563 8.3 560 4.8 556
10 5 3.0 572 0.9 570 2.0 568 5.6 564
20 5 7.0 580 9.2 578 12.2 575 16.0 572
30 15 17.1 588 19.3 586 22.4 583 26.4 580
40 25 27.2 597 29.5 595 32.7 592 36.8 588
30 55 52.9 547 50.9 544 48.0 541 44.4 535
20 45 42.9 551 40.7 549 37.7 545 34.0 540
10 35 32.8 556 30.5 553 27.4 550 23.5 545
20,000 0 25 22.7 560 20.3 558 17.1 554 13.0 549
10 15 12.6 565 10.2 562 6.8 559 2.6 555
20 5 2.6 572 0.0 570 3.5 567 7.9 563
30 5 7.5 580 10.2 578 13.8 575 18.4
40 15 17.6 588 20.3 586 24.1 583 28.8
30 64 62.5 542 60.1 539 56.8 535 52.7 528
20 54 52.4 547 49.9 544 46.9 539 42.1 533
10 44 42.4 551 39.7 548 36.1 544 31.5
25,000 0 34 32.3 556 29.5 553 25.7 549 21.0
10 24 22.2 560 19.3 557 15.3 553 10.4
20 14 12.1 565 9.1 562 4.9 558 0.2
30 4 2.0 573 1.2 570 5.4 566 10.7
40 5 8.1 580 11.4 578 15.8 575 21.3
30 74 72.1 537 69.2 534 65.4 528 60.6
20 64 62.0 542 59.0 538 54.9 533 49.9
10 54 51.8 546 48.7 543 44.4 537 39.2
30,000 0 44 41.7 551 38.4 547 34.0 542 28.5
10 34 31.6 555 28.2 552 23.5 547 17.8
20 24 21.5 560 17.9 556 13.1 551 7.1
30 14 11.4 565 7.6 562 2.6 557 3.6
40 4 1.3 573 2.6 570 7.8 565 14.3

FIGURE 3A-1 (continued)

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-19
6CC
 SA227-CC
SRL COMPUTER FAILURE (continued)

EGT LIMIT WITH SRL INOPERATIVE

97% RPM CRUISE POWER

NOTE

Indicated outside air temperature (IOAT) as shown in table

includes compressibility and position errors.

Airspeeds shown are provided to permit interpolation of

EGTs. Do not exceed VMO.

Applicable to all bleed air and anti-ice conditions.

EXAMPLE:
Given: Altitude = 15,000 Feet
Airspeed = 199 KIAS (200 KCAS)
IOAT = 6oC
Obtain: Maximum EGT = 535oC

INDICATED/CALIBRATED AIRSPEED (KNOTS)

ALTITUDE ISA OAT 98/100 149/150 199/200 248/250
(FEET) (oC) (oC) IOAT EGT IOAT EGT IOAT EGT IOAT EGT
30 15 14.1 538 12.9 536 11.3 534 9.2 531
20 5 4.0 546 2.8 544 1.2 542 1.0 539
10 5 6.0 557 7.2 555 9.0 552 11.2 548
SEA LEVEL 0 15 16.0 567 17.3 565 19.1 563 21.4 559
10 25 26.1 576 27.4 576 29.3 573 31.6 570
20 35 36.1 587 37.5 587 39.4 584 41.9 581
30 45 46.1 597 47.6 597 49.5 595 52.1 592
40 55 56.2 608 57.6 608 59.7 606 62.3 602
30 25 23.8 530 22.5 529 20.7 526 18.3 523
20 15 13.8 538 12.4 536 10.5 534 8.0 531
10 5 3.8 546 2.3 548 0.3 542 2.2 539
5,000 0 5 6.3 557 7.8 559 9.8 552 12.5 548
10 15 16.3 567 17.9 569 20.0 562 22.8 559
20 25 26.4 578 28.0 580 30.2 573 33.0 569
30 35 36.4 589 38.1 591 40.4 584 43.3 580
40 45 46.5 599 48.2 602 50.5 595 53.6 591
30 35 33.6 524 32.0 522 29.9 519 27.2 515
20 25 23.5 530 21.9 528 19.7 525 16.9 522
10 15 13.5 538 11.8 536 9.5 533 6.6 530
10,000 0 5 3.4 546 1.7 544 0.7 541 3.8 538
10 5 6.6 557 8.4 555 10.9 551 14.1 547
20 15 16.7 568 18.5 565 21.1 562 24.4 558
30 25 26.7 578 28.6 576 31.3 573 34.7 569
40 35 36.8 589 38.8 587 41.5 584 45.0 580

FIGURE 3A-2
3A-20 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92
6CC
 SA227-CC
SRL COMPUTER FAILURE (continued)

EGT LIMIT WITH SRL INOPERATIVE

97% RPM CRUISE POWER (continued)

INDICATED/CALIBRATED AIRSPEED (KNOTS)

ALTITUDE ISA OAT 98/100 149/150 199/200 248/250
(FEET) (oC) (oC) IOAT EGT IOAT EGT IOAT EGT IOAT EGT
30 45 43.3 519 41.5 517 39.0 514 35.9 510
20 35 33.2 524 31.4 521 28.8 518 25.5 514
10 25 23.2 531 21.2 528 18.5 525 15.2 521
15,000 0 15 13.1 538 11.1 536 8.3 533 4.8 529
10 5 3.0 547 0.9 544 2.0 541 5.6 537
20 5 7.0 557 9.2 555 12.2 551 16.0 546
30 15 17.1 568 19.3 566 22.4 561 26.4 557
40 25 27.2 579 29.5 576 32.7 573 36.8 568
30 55 52.9 515 50.9 513 48.0 509 44.4 504
20 45 42.9 519 40.7 517 37.7 513 34.0 508
10 35 32.8 524 30.5 522 27.4 518 23.5 513
20,000 0 25 22.7 531 20.3 529 17.1 525 13.0 520
10 15 12.6 539 10.2 537 6.8 533 2.6 529
20 5 2.6 547 0.0 545 3.5 541 7.9 537
30 5 7.5 558 10.2 555 13.8 551 18.4
40 15 17.6 569 20.3 566 24.1 562 28.8
30 64 62.5 511 60.1 508 56.8 504 52.7 498
20 54 52.4 516 49.9 513 46.9 509 42.1 503
10 44 42.4 520 39.7 517 36.1 513 31.5
25,000 0 34 32.3 525 29.5 522 25.7 518 21.0
10 24 22.2 532 19.3 530 15.3 526 10.4
20 14 12.1 540 9.1 537 4.9 534 0.2
30 4 2.0 551 1.2 546 5.4 542 10.7
40 5 8.1 561 11.4 557 15.8 552 21.3
30 74 72.1 507 69.2 504 65.4 499 60.6
20 64 62.0 512 59.0 509 54.9 504 49.9
10 54 51.8 516 48.7 513 44.4 508 39.2
30,000 0 44 41.7 520 38.4 518 34.0 513 28.5
10 34 31.6 525 28.2 522 23.5 518 17.8
20 24 21.5 533 17.9 530 13.1 526 7.1
30 14 11.4 540 7.6 538 2.6 534 3.6
40 4 1.3 550 2.6 547 7.8 543 14.3

FIGURE 3A-2 (continued)

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-21
6CC
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART

Intentional engine shutdowns and airstarts may be required during crew training and following
maintenance or adjustment of the engine or propeller controls. Stresses due to temperature gradients
within the engine can be reduced and engine life prolonged by using the following procedure:

WARNING

IN THE EVENT OF AN ACTUAL ENGINE FAILURE OR ENGINE

FIRE, IMPLEMENT THE APPROPRIATE EMERGENCY
PROCEDURE AS STATED IN SECTION 3 OF THIS MANUAL.

PREPARATION FOR ENGINE SHUTDOWN

*1. Bleed Air Switch (selected engine) ......................................................................................... OFF

*2. Propeller Synchrophaser Switch (if installed) ............................................ TAKEOFF & LANDING
3. Power Lever (selected engine) ............................................ APPROXIMATELY 1/4 INCH (6 mm)
FORWARD OF FLIGHT IDLE
(UNTIL LANDING GEAR WARNING HORN IS SILENCED)
4. Speed Levers ................................................................................................................. 97% RPM

Allow the selected engine to cool and stabilize at low power while accomplishing steps 5, 6 and 7
as applicable. Observe torque and EGT limits on the operating engine.

5. Generators (S/N CC-884 and subsequent, and airplanes

modified IAW SB CC7-24-002) ............................................................................. CHECK AMPS

NOTE

If the generator switch is ON, the GEN FAIL annunciator light

is OFF, and the ammeter reads zero, the respective 400 amp
current limiter is open.

An open current limiter will not prevent an engine restart, but

an intentional engine shutdown with an open current limiter is
not recommended unless an engine malfunction has been
detected.

If a failed current limiter is found, the generator on that side

should be turned OFF.

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

7. Current Limiters (S/N CC-883 and earlier without SB CC7-24-002) .................................. CHECK
(SEE PAGE 2-21)

CAUTION

IF A CURRENT LIMITER HAS FAILED, AN AIRSTART MAY NOT

BE POSSIBLE. DO NOT CONTINUE WITH A PREPLANNED
ENGINE SHUTDOWN.

3A-22 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: MAR 28/95
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

ENGINE SHUTDOWN

NOTE

In order to maintain consistency in training and in reaction

patterns, this procedure follows the sequence of actions specified
in the ENGINE FAILURE DURING FLIGHT procedure contained
in Section 3 of this manual. However, certain actions are
expanded to permit symmetrical cooling of rotating parts of the
engine and to allow extended observation of the functions of
engine and propeller components such as the manual fuel
shutoff valve, negative torque sensing system, and feathering
valve.

1. Engine Stop and Feather Control (selected engine) ............................................................. PULL

Pull the control out only to the point where the fuel shutoff valve shuts off the fuel, as indicated
by fuel flow dropping to zero. Leave the control in that position for one minute or until RPM
decays to approximately 30%. Frequently, RPM will remain above 30% at the end of one
minute. Then pull the control full aft to open the feather valve and allow the propeller to feather.

CAUTION

DO NOT ALLOW ENGINE TO WINDMILL DURING RPM

DECAY LONGER THAN ONE MINUTE.

DO NOT PERMIT THE INOPERATIVE ENGINE TO WINDMILL

IN THE 18% TO 28% RPM RANGE.

2. Engine Clean Up (selected engine) ...................................................................... AS REQUIRED

a. Fuel shutoff switch
b. Hydraulic shutoff switch
c. Fuel boost pump switch
d. Generator switch
*e. Bleed air switch
3. Power Lever (operating engine) ............................................................................ AS REQUIRED
4. Trim ....................................................................................................................... AS REQUIRED
5. Generator (operating engine) ...................................................................... 300 AMPS MAXIMUM
6. Engine Stop and Feather Control ................................................................................. FORWARD
7. Unfeather Test Switch (selected engine) .............................................................. AS REQUIRED

Depending upon airspeed and ambient temperature during RPM decay, residual EGT may be above
200oC when the propeller feathers and stops rotation. If the EGT is above 200oC, use the unfeather
test switch intermittently to keep the propeller windmilling slowly (up to approximately 10% RPM) until
the EGT stabilizes at or below 200oC.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-23

6CC
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

ENGINE SHUTDOWN (continued)

NOTE

Above approximately 7% windmilling RPM, sufficient oil

pressure may be generated to sustain the unfeathering cycle
thus increasing RPM toward the 18% to 28% RPM range.
Prevent such increases in RPM by pulling the engine stop and
feather control full aft and resetting it forward when the
propeller feathers.

Repeated momentary use of the unfeather test switch to cause

very slow rotation of the feathered propeller will eventually
cause all the oil to be pumped from the oil tank, through the
propeller dome, and into the nose case. At very slow
rotation speeds, the scavenge pumps will not be able to return
the oil from the nose case to the oil tank. Avoid exhausting the
oil tank by ensuring that the propeller windmills at no less than
5% RPM. Prior to final feathering when EGT is less than
200C, allow windmilling RPM to reach approximately 15% to
ensure sufficient oil scavenging to provide a source of oil for
unfeathering.

If the supply of oil from the oil tank to the unfeathering pump is
exhausted inadvertently, it can be replenished by using the
starter test switch to cause rotation and scavenge pump
operation. However, since the electrical load on the starter
while turning a feathered propeller in flight is unknown and
variable, this procedure should not be attempted without
realizing that damage to the starter may occur. Observe the
starter duty cycle limitations.

A feathered propeller should not rotate backward at speeds

above 115 KIAS. If backward rotation occurs, either increase
airspeed or use momentary activation of unfeather pump
(engine stop and feather control forward) to stop backward
rotation.

3A-24 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

PREPARATION FOR IMMEDIATE AIRSTART

NOTE

Prepositioning controls and switches as follows will shorten the

time required to restart the engine should an immediate airstart
be required.

*1. Speed Lever ................................................................................................................... 97% RPM

NOTE

The 97% RPM speed lever position can be attained either by

setting this value prior to shutdown or by setting the operating
engine speed at 97% RPM and aligning both speed levers.

2. Power Lever ........................ APPROXIMATELY 1/4 INCH (6 mm) FORWARD OF FLIGHT IDLE
(UNTIL LANDING GEAR WARNING HORN IS SILENCED)
*3. Engine Stop and Feather Control ................................................................................. FORWARD
4. Fuel Shutoff Switch .............................................................................................................. OPEN
5. Hydraulic Shutoff Switch ...................................................................................................... OPEN
6. Fuel Boost Pump Switch ........................................................................................................... ON
7. Generator Switch..................................................................................................................... OFF
*8. Bleed Air Switch ...................................................................................................................... OFF
9. Ignition Switch ...................................................................................................................... AUTO

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.

NOTE

Satisfactory airstarts have been demonstrated up to 20,000

feet pressure altitude with the fuel boost pumps operating and up
to 12,000 feet pressure altitude without the boost pumps
operating.

When airstarting an engine at low airspeeds (100 to 110 KIAS)

significant yaw and roll into the starting engine will occur as
the engine approaches its on-speed condition. The yaw and roll
are barely noticeable during airstarts at speeds above 150 KIAS.

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-25

Revised: DEC 02/97 6CC
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

AIRSTART (continued)

*1. Speed Lever ................................................................................................................... 97% RPM

2. Power Lever ........................ APPROXIMATELY 1/4 INCH (6 mm) FORWARD OF FLIGHT IDLE
(UNTIL LANDING GEAR WARNING HORN IS SILENCED)
3. EGT ............................................................................................... BELOW 200oC (IF FEASIBLE)
4. RPM ....................................................................................................................... 10% OR LESS
5. Altitude ....................................................................................................20,000 FEET MAXIMUM
6. Airspeed .................................................................................................... 100 KIAS TO 180 KIAS
*7. Engine Stop and Feather Control ................................................................................. FORWARD
8. Fuel Shutoff Switch .............................................................................................................. OPEN
9. Hydraulic Shutoff Switch ...................................................................................................... OPEN
10. Fuel Boost Pump Switch ........................................................................................................... ON
11. Generator Switch..................................................................................................................... OFF
*12. Bleed Air Switch ...................................................................................................................... OFF
13. Ignition Switch ...................................................................................................................... AUTO
14. Engine Start Button ......................................................... PRESS AND HOLD UNTIL LIGHT OFF

NOTE

During airstarts following prolonged feathered flight at cold

outside air temperatures (oil temperature cooled to below +25oC),
increased starting fuel may be required. Depress the start
button as required to maintain normal EGT and engine
acceleration during airstarts of cold-soaked engines.

*15. Propeller .......................................................................................... OBSERVE UNFEATHERING

16. Fuel Flow ..................................................................................... SHOULD START BY 10% RPM
17. EGT ........................................................................ SHOULD INCREASE AT 10% TO 20% RPM.
IF NOT INCREASING BY 25% RPM, ABORT AIRSTART
BY PULLING ENGINE STOP AND FEATHER CONTROL
18. Fuel and Oil Pressure ............................................................................................... GREEN ARC
19. Generator Switch.......................................................................................................... RESET/ON
*20. Bleed Air Switch ........................................................................................................................ ON

NOTE

If the engine fails to accelerate within the 18% to 28% RPM

range, feather the propeller by pulling the engine stop and
feather control full aft. Use the unfeather test switch as in
ENGINE SHUTDOWN step 7 to keep the propeller rotating for a
minimum of 5 minutes. Attempt a second airstart. If this airstart is
unsuccessful, a single engine landing should be planned since
further airstart attempts could damage the engine.

3A-26 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: DEC 02/97
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

AIRSTART PROCEDURE WITH SRL COMPUTER INOPERATIVE

Two three-position speed switch select switches, located on the left cockpit console, are provided to
permit airstarts with the SRL computer inoperative. These switches bypass the normally automatic
engine speed functions controlled by the SRL computer that are required during start. The switch
positions are AUTO, OFF, and MANUAL. The airstart procedure with SRL computer inoperative is
the same as the normal airstart procedure except for the denoted changes below as indicated by the
small letter a and double asterisks.

*1. Speed Lever ................................................................................................................... 97% RPM

2. Power Lever ........................ APPROXIMATELY 1/4 INCH (6 mm) FORWARD OF FLIGHT IDLE
(UNTIL LANDING GEAR WARNING HORN IS SILENCED)
3. EGT ............................................................................................... BELOW 200oC (IF FEASIBLE)
4. RPM ....................................................................................................................... 10% OR LESS
5. Altitude ....................................................................................................20,000 FEET MAXIMUM
6. Airspeed .................................................................................................... 100 KIAS TO 180 KIAS
*7. Engine Stop and Feather Control ................................................................................. FORWARD
8. Fuel Shutoff Switch .............................................................................................................. OPEN
9. Hydraulic Shutoff Switch ...................................................................................................... OPEN
10. Fuel Boost Pump Switch ........................................................................................................... ON
11. Generator Switch..................................................................................................................... OFF
*12. Bleed Air Switch ...................................................................................................................... OFF
**a. Speed switch select switch ...................................................................................... MANUAL
13. Ignition Switch ...................................................................................................................... AUTO
14. Engine Start Button ................................................................................. PRESS MOMENTARILY
*15. Propeller .......................................................................................... OBSERVE UNFEATHERING
16. Fuel Flow ..................................................................................... SHOULD START BY 10% RPM
17. EGT ........................................................................ SHOULD INCREASE AT 10% TO 20% RPM.
IF NOT INCREASING BY 25% RPM, ABORT AIRSTART
BY PULLING ENGINE STOP AND FEATHER CONTROL
18. Engine Start Button ............................................... OBSERVE EGT AND RPM ACCELERATION.
USE START BUTTON AS REQUIRED TO PROVIDE FUEL
ENRICHMENT BETWEEN 10% AND 60% RPM

NOTE

During airstarts following prolonged feathered flight at cold

outside air temperatures (oil temperature cooled to below +25oC),
increased starting fuel may be required. Depress the start
button as required to maintain normal EGT and engine
acceleration during airstarts of cold-soaked engines.

19. Fuel and Oil Pressure ............................................................................................... GREEN ARC

**a. Speed switch select switch ............................................................. AUTO/CHECK IGNITION
LIGHT GOES OUT
20. Generator Switch.......................................................................................................... RESET/ON
*21. Bleed Air Switch ........................................................................................................................ ON

FAA APPROVED: DEC 11/92 ABNORMAL PROCEDURES 3A-27

Revised: DEC 02/97 6CC
 SA227-CC
PREPLANNED ENGINE SHUTDOWN/AIRSTART (continued)

ABORTED AIRSTART (DUE TO NO COMBUSTION)

1. Engine Stop and Feather Control .......................................................................................... PULL

2. Altitude .....................................................REDUCE BEFORE ATTEMPTING ANOTHER START

PRESSURIZATION/AIR CONDITIONING SYSTEM MALFUNCTIONS

COLD AIR

Warm or hot air flowing from cold air outlets could be caused by an air cooling turbine failure or by a
malfunctioning water separator anti-icing modulator valve. If warm air exits from cold air outlets,
isolate the source of the malfunction by turning off bleed air from the engine on the side of the aircraft
which is producing the warm air.

CONDITIONED AIR

If the automatic temperature controller fails to respond to commanded temperature changes, switch to
manual control of the hot air mixing valves. Modulate travel of the valves by selecting colder or
warmer temperatures with two to three-second pulses. Although the mixing valves will travel from
full hot to full cold in approximately eight seconds, several minutes may be required before the
conditioned air temperature stabilizes following manual changes to the position of the mixing valve.

UNPRESSURIZED FLIGHT

1. Cabin Dump Switch ..............................................................................................................DUMP

*2. Bleed Air Switches ................................................................................................... AS DESIRED

WARNING

WHEN THE AIRPLANE IS UNPRESSURIZED, THE PASSENGER

ENTRANCE DOOR SAFETY LOCK WILL NOT BE ENGAGED,
AND IT WILL BE POSSIBLE TO OPEN THE DOOR IN FLIGHT.

LOW SUCTION LIGHT ON

Less than 4.4 in. Hg suction is being produced. Monitor pressurization operation in automatic mode.
If abnormalities are noted revert to manual operation.

HIGH OIL TEMPERATURE

Elevated oil temperatures (in the caution range) on the ground are common with high ambient
temperatures. If the maximum oil temperature limit is exceeded, do not takeoff.

In flight, high oil temperature can be an indication of low oil quantity or impending engine failure. If the
oil temperature exceeds the maximum limit in flight, reduce power on the affected engine. If the oil
temperature remains out of limits and there are any other indications of pending engine failure, the
engine should be shutdown.

3A-28 ABNORMAL PROCEDURES FAA APPROVED: DEC 11/92

6CC Revised: JUN 03/99