Piper PA-39 Twin Comanche C/R - Page 42

TWIN COMANCHE C/R
Either operation above disengages both ROLL and PITCH SECTIONS of the
ALTIMATIC from the control system and will disengage the AUTOFLITE SECTION if engaged.
as long as button remains depressed.
After the A/P “OFF” button on the control wheel has been pushed due to a
malfunction in the ROLL or PITCH SECTION. the ALTIMATIC IIIB can only be reengaged by
the actuation of the ROLL ROCKER switch and PITCH button on the console.
AUTOFLITE SECTION will automatically re-engage upon release of the A/P button.
b.
The PITCH TRIM SECTION may be overpowered manually. In the event of a
malfunction in the PITCH TRIM SECTION, pull the Electric Trim circuit breaker.
-
The AltiMatic ROLL SECTION and AUTOFLITE SECTION may be overpowered
manullly by exertion of 12 f 3 pounds of force on either control wheel. The AltiMatic PITCH
SECTION may be overpowered manually by exertion of 15 + 2 pounds of force on either control
wheel.
d. In cruise configuration, AltiMatic malfunction with a 3 second recovery delay results in
a 45 o bank and 300 foot altitude loss.
e. In approach configuration, AltiMatic malfunction with a 1 second recovery delay
results in a 28” bank and 220 foot altitude loss.
f.
In cruise configuration, AutoFlite malfunction with a 3 second recovery delay results
in a 35 ’ bank and an 80 foot altitude loss.
is.
In approach configuration, AutoFlite malfunction with a 1 second recovery delay
results in a 25” bank and 40 foot altitude loss.
6.
PLACARDS
a. On left control wheel:
x DWN UP
A v
b. On left control wheel:
A/P
OFF b
C. On instrument panel:
AutoFlite
Trim
L
R
d. On instrument panel (when radio coupler is installed):
A/P NAV SEL
ON
OFF
ON
e. On instrument panel (when Glide Slope Coupler is installed)
G/S
ENGAGED
f.
On instrument panel (when p$chL$n warning is installed):
OUT OF TRIM
.’
FAA APPROVED November 28,1969
REISSUED: June 1,197O
REVISED: March l7,1971
REPORT: 1605 PART I PAGE 29
MODEL: PA-39