MEP & Seneca Flashcards
Definition of Critical Engine
The engine which causes the greatest yawing moment in case of failure
Conditions assumed for Vmca
- Gear up
- Inoperable engine windmilling
- CoG at rearmost position
Reason for a minimum rpm for prop-feathering system
To prevent activation of anti-feathering latches
Engine control sequence for increasing power
- Enrich mixture
- Increase rpm
- Advance throttle
V(a) definition
Design (maximum) manoeuvring speed
V(lo) definition
Maximum speed for operating the gear (can be different for up and down)
V(le) definition
Maximum speed for having the gear extended
V(2) - TOSS definition
Lowest speed at which an AVERAGE PILOT can maintain control with take-off configuration and power and engine failure of critical engine.
Fuel and oil levels at BEM
Unusable fuel in tanks, no useable fuel
Full oil
Effect on critical speed of a forward moving CoG (e.g. due to fuel burn off)
It decreases (good thing)
Immediate actions after engine failure
Use rudder to prevent yaw
Use ailerons to level the wings
Effect of alternator loss in multi-engine aircraft
Can power essential services but may need to load shed
Maximum bank and resulting balance when using aileron with an engine failure
5 degrees AoB
Ball slightly towards the live engine
Asymmetric blade effect
Descending propeller travels further than the ascending blade thus generating more thrust when descending.
High pitch during engine failure exacerbates this.
Seneca prop rotation directions
Counter rotating (clockwise on left, counter-clockwise on right)
Seneca fuel capacity (US gallons)
98 US gallons
93 US gallons useable
Seneca oil capacity
8 quarts
Seneca MTOW and MLW
MTOW: 4200lb
MLW: 4000lb
Seneca tire pressures
Nose: 31psi
Main: 50psi
Seneca engine horsepower
200hp
Seneca engines
LIO-360-C1E6
Seneca stall warner system
Two detectors on left wing:
- Inboard for flaps @ 20 & 40 degrees
- Outboard for other flap positions
Seneca baggage capacity
100lbs in nose
100lbs in rear behind seats
Seneca maximum load factor
3.8g
Seneca V(lo) (up and down)
Up - 107kt
Down - 129kt
Seneca max crosswind
13kt
Seneca V(fe)
107kt [landing flap]
10 deg - 137kt
25 deg - 120kt
Seneca fuel pressure range
14 to 35 psi
Seneca cylinder head temp range
200 to 475 deg F
Seneca rpm range
500 to 2700rpm
Seneca rpm avoid continuous red range
2200 to 2400rpm
Seneca fuel tanks
2 interconnected tanks in each wing, each filled from a single point
Seneca gear horn operation
- Gear lever up whilst on the ground
- Gear lever up with MP < 14”
Feathering lock activation speed
800 rpm
Location of hydraulic reservoirs (brakes & gear)
Behind panels in the nose baggage compartment
Adverse yaw in seneca
Linkage between ailerons and rudder coordinates and reduces adverse yaw
V(mca)
68kt
V(2) - TOSS
77kt
V(r)
80kt
Our climb speed (dual engine)
100kt
V(x)
78kt
V(y)
91.5kt
V(xse)
82kt
V(yse)
89kt
Seneca cruise speed
130kt
Single engine cruise speed
105kt
Go-around speeds
- dual and single engine
Dual engine - 100kt
Single engine - 90kt
V(a)
125kt (at max weight, down to 114kt @ low weight)
V(no)
165kt
V(ne)
189kt
V(S0)
58kt
V(S1)
64kt
Fuel to “wet bottoms”
190l
Our standard fuel fill level
Wet bottoms (190l) plus 40l each side.
Total 270l
Fuel burn rate (l/hr)
70l/hr
Manifold settings for stalls
16” to configure (gear, flaps)
12” to stall
ACA
Asymmetric Commitment Altitude
250ft + threshold elevation @ stapleford
[21 - 370ft+, 3 - 430ft+]
What happens to prop if oil pressure is lost?
Will head to coarse.
Feather lock will activate as rpm degrades
Seneca electrical system voltage
14v dc
Mag drop for initial checks
100-300rpm
Purpose of initial mag drop checks
Checking for rough running engine
Max time to run starter
30 seconds
Oil type for running in engine
Non-detergent
Target speed after engine failure
(V speed)
V(YSE)
Renewal period for MEP rating
90 days before expiry (12 months)
Major source of drag with engine failure
- e.g. flaps, gear, windmilling prop, feathered prop?
Windmilling prop
MEP requirements to revalidate
10 sectors
Skill test
Every 12 months
