Piper SENECA III - Page 365

PIPER
AIRCRAFT
CORPORATION SECTION
9
PA-34-220T,
SENECA
IH
SUPPLEMENT 18
(3)
Single
Engine
Operations:
a.
Engine
failure during
an
autopilot
approach
operation:
Disengage
autopilot,
conduct
remainder
of
approach
manually.
b.
Engine
failure during
normal climb,
cruise,
descent:
Retrim
aircraft,
perform
normal
aircraft
engine
out
procedures,
c.
Maíntain
aircraft
yaw
trim throughout
all single engine
operations.
NOTE
Single
engine
operations
below Single
Engine
Best
Rate
of
Climb Speed
(Blue
Line)
may
require
manual rudder
application
to
maintain
directional
trim
depending
upon
aircraft
configuratiori and
power
applied.
(4)
Altitude
Loss
During
Malfunction:
a.
An
autopilot
malfunction
during
climb,
cruise
or
descent
with
a
3 second
delay
in
recovery
initiation
could result
in
I
as
much
as
60° bank and 700'
altitude
loss. Maximum
altitude loss
measured
at
180
KIAS
during
descent
at
high
altitude.
b.
An
autopilot
malfunction
during
an
approach with
one
second
delay
in
recovery
initiation
could
result
in
as
much
as
30° bank
and
100'altitudeloss. Maximumaltitudeloss
measured
with
one
notch
(10
degrees)
flaps,
gear
down,
and
operating
either
coupled
or
uncoupled,
single
or
multi-
engine,
(b)
COMPASS
SYSTEM
(1)
Emergency
Operation
with
Optional NSD 360A
(HSI) Slaved
and
or
Non-Slaved:
NSD 360A
a.
Appearance
of HDG Flag:
1.
Check
air supply
gauge
(vac
or
pressure)
for
adequate
air
supply
(4
in. Hg.
min.).
2.
Check
compass
circuit
breaker.
3.
Observe
display for
proper
operation.
ISSUED:
APRIL 21,
1981 REPORT:
VB-1110
REVISED:
FEBRUARY
25, 1982 3 of 12, 9-115