Piper PA-28-161 User Manual

SECTION 3 PIPER AIRCRAFT CORPORATION
EMERGENCY PROCEDURES PA-28-161, WARRIOR II
REPORT: VB-1180 ISSUED: AUGUST 13, 1982
3-6
SECTION 3 PIPER AIRCRAFT CORPORATION
EMERGENCY PROCEDURES PA-28-161, WARRIOR II
REPORT: VB-1180 ISSUED: AUGUST 13, 1982
3-6
If alternator loads are reduced:
Electrical load .....................................................................Reduce to Minimum
Land as soon as practical.
NOTE
Due to increased system voltage and radio
frequency noise, operation with ALT switch ON
and BATT switch OFF should be made only
when required by an electrical system failure.
If alternator loads are not reduced:
ALT switch ...................................................................................................OFF
BATT switch .....................................................................................As required
Land as soon as possible. Anticipate complete electrical failure.
SPIN RECOVERY
Throttle ...........................................................................................................idle
Ailerons .....................................................................................................neutral
Rudder .........................................................................................full opposite to
direction of rotation
Control wheel ...................................................................................full forward
Rudder ............................................................................................neutral (when
rotation stops)
Control wheel .................................................................as required to smoothly
regain level flight attitude
OPEN DOOR
If both upper and lower latches are open, the door will trail slightly open and
airspeeds will be reduced slightly.
To close the door in flight:
Slow airplane to 89 KIAS
Cabin vents ..................................................................................................close
Storm window ..............................................................................................open
If alternator loads are reduced:
Electrical load .....................................................................Reduce to Minimum
Land as soon as practical.
NOTE
Due to increased system voltage and radio
frequency noise, operation with ALT switch ON
and BATT switch OFF should be made only
when required by an electrical system failure.
If alternator loads are not reduced:
ALT switch ...................................................................................................OFF
BATT switch .....................................................................................As required
Land as soon as possible. Anticipate complete electrical failure.
SPIN RECOVERY
Throttle ...........................................................................................................idle
Ailerons .....................................................................................................neutral
Rudder .........................................................................................full opposite to
direction of rotation
Control wheel ...................................................................................full forward
Rudder ............................................................................................neutral (when
rotation stops)
Control wheel .................................................................as required to smoothly
regain level flight attitude
OPEN DOOR
If both upper and lower latches are open, the door will trail slightly open and
airspeeds will be reduced slightly.
To close the door in flight:
Slow airplane to 89 KIAS
Cabin vents ..................................................................................................close
Storm window ..............................................................................................open

Piper PA-28-161 Specifications

General

Manufacturer	Piper Aircraft
Model	PA-28-161 Warrior II
Engine	Lycoming O-320-D3G
Horsepower	160 hp
Seating Capacity	4
Wingspan	35 ft (10.7 m)
Length	24 ft 0 in
Maximum Speed	127 knots
Cruise Speed	122 knots
Maximum Takeoff Weight	2, 325 lb (1, 055 kg)
Fuel Capacity	48 US gallons (182 L)