Section III

Question 1

Three steps to an emergency

Answer 1

1. Maintain airplane control.
2. Analyze the situation.
3. Take coordinated corrective action.

Question 2

Land as soon as possible

Answer 2

An emergency will be declared. A landing should be accomplished at the nearest suitable airfield considering the severity of the emergency and environmental factors.

Question 3

Land as soon as practical

Answer 3

Emergency conditions are less urgent, and although the mission is to be terminated, the degree of the emergency is such that an immediate landing at the nearest adequate airfield may not be necessary.

Question 4

Ground Egress Ring

Answer 4

One long ring

Question 5

Bailout Ring

Answer 5

1. Prepare - Three short

2. Bailout - One long

Question 6

Ditching or Crash Ring

Answer 6

1. Imminent - Six short

2. One long

Question 7

12 Engine Shutdown Conditions

Answer 7

1. Engine Fire
2. Turbine Overheat
3. Start valve open light
4. Nacelle Overheat
5. Uncontrollable Power
6. Certain propeller malfunctions
7. An uncontrollable rise in TIT
8. An uncontrollable drop in oil pressure
9. An uncontrollable rise in oil temperature
10. Unusual vibration or roughness
11. Throttle control cable failure
12. Excessive visible fluid leak

Question 8

Engine Shutdown Procedure

Answer 8

1. CONDITION LEVER “FEATHER” (CP)
2. FIRE HANDLE “PULLED” (CP)
3. AGENT “DISCHARGED” (FOR FIRE OR NACELLE OVERHEAT) (CP)
4. Flaps “As required” (CP)
5. Landing gear “As required” (CP)
6. IFF master switch NORM/TA (CP)
7. Cleanup “Complete”
   a. Engine bleed air switch - OFF
   b. Engine generator switch - OFF/RESET
   c. Fuel boost pump switch - OFF
   d. Crossfeed valve switch - CLOSED
   e. Propeller governor control switch - MECH GOV
   f. Synchrophase master switch - Reset as necessary
   g. TD valve switch - NULL
   h. Throttle - Full forward
   i. Oil cooler flap switch - CLOSED, FIXED
8. Land as soon as practical

1 (W):

a. Throttle control cable failure: use the fire handle, not the condition lever
b. If the condition lever binds, pull fire handle, if the lever is left in a mid-position, and NTS inop, decoupling is possible

3 (W):
If condition persists, bleed air leak may exist, isolate the wing by closing the eng bleed valve and the divider valve. If the fire or nacelle overheat continues, discharge 2nd bottle on command of the pilot.
3 (N):
The agent should be discharged if any indication continues, or any other indication occurs which requires the agent
6 (W):
TA only will get rid of RA’s because the airplane may not be able to comply
8 (N):
Performance data should be checked

Question 9

APU Emergency Shutdown (Ground / Inflight)

Answer 9

1. FIRE HANDLE “PULLED” (E)
2. AGENT “DISCHARGED” (FOR FIRE) (E)
3. Cleanup “Complete”
   a. APU generator switch - OFF
   b. Control switch - STOP
   c. Bleed air valve switch - CLOSE

2 (W):
If conditions persist inflight, a break in the bleed air manifold may exist. Isolate #1 & 2, and close the divider valve, discharge secondary agent if necessary
2(N):
Agent should be discharged for any indication continues after handle pulled, or any other indication or malfunction that requires the agent

Question 10

Bleed Air System Failure (Ground / Inflight)
Indications:
a. Illumination of any fire warning lights
b. Erratic operation of engine instruments
c. Lower than charted engine torque (normally marked and even reduction)
d. Erratic operation of electrical equipment
e. Zero or fluctuating liquid oxygen quantity
f. Inoperative or intermittent radar operation
g. A wing overheat may occur without an accompanying leading edge overtemperature caution light(s) due to possible wiring damage
h. Reduced bleed air manifold pressure

c (N):
This torque drop may be transitory followed by near normal values

Two types of bleed air system failures:

1. An uncontrollable loss of bleed air
2. Failure of an engine bleed air regulator

Answer 10

If bleed air being lost from the system, the engineer will do:
1. Engine bleed air switches on the affected wing - OFF
2. Bleed air divider valve switch - CLOSED
If can’t be isolated, do this:
1. All engine bleed air switches - OFF
2. OBE control - OPEN
3. Land as soon as possible

3 (W):
When all bleed air switches are OFF, airflow to both A/C units are is lost, depressurizing the airplane
3 (C):
a. If an engine bleed air regulator cannot be closed (regulator closure is determined by observing torque increase or TIT decrease on the engine) and the bleed air system is leaking, it may be necessary to shut down the engine.
b. Do not open the APU bleed air valve after landing. If the uncontrolled loss of bleed air cannot be isolated, operation of the APU bleed air would repressurize the area(s) where the failure has occurred.