TM 1-1510-262-10
(3) Maintain 85% N 1 or higher during simultaneous operation of the brake deice and surface deice sys-
tems. If adequate pneumatic pressure cannot be provided for simultaneous operation of the brake deice and
surface deice systems, turn off the brake deice system.
(4)
The brake deice system shall be turned off during single engine operation.
5-12. PITOT HEAT LIMITATIONS.
Pitot heat should not be used for more than 15 minutes while the aircraft is on the ground.
SECTION III. POWER LIMITS
5-13. ENGINE LIMITATIONS.
Observe limitations found in Table 5-1 during operation of this aircraft, equipped with two Pratt and Whitney of
Canada, Ltd, PT6A-67 engines. Each column is a separate limitation. The limits presented do not necessarily oc-
cur simultaneously. Whenever operating limits are exceeded, the pilot should record the value and duration of the
condition encountered, in the aircraft log. Instruments, with reference to the operating limits marked on the face of
each instrument, monitor operation of the engines.
Engine operation using only the engine-driven fuel pump without boost pump fuel pressure is lim-
ited to 10 cumulative hours. All time in this category shall be entered on DA Form 2408-13-1 for the
attention of maintenance personnel.
Table 5-1.
Engine Operating Limitations
OIL
OIL
MAXIMUM
GAS
PROP
PRESS
OPERATING
%
OBSERVED
RPM
PSI
TEMP C
CONDITION
(1)
TGT C
RPM N 1 %
N2
(10)
(2)
(3)
--
--
--
STARTING
1000 (4)
200 (Max)
-40 (Min)
--
-40 to 110
LOW IDLE
750 (5)
62 (Min)
(11)
60 (Min)
--
--
--
--
1000
HIGH IDLE
(6)
(Min)
100
840
104
1700
90 to 135
10 to 110
TAKE OFF (5 MIN)
100
830
104
1700
90 to 135
10 to 105
MAX. CONT.
810
104
90 to 135
10 to 105
MAX. CRUISE
(7) (9)
(9)
810
104
90 to 135
10 to 105
MAX. CLIMB
(9)
(9)
800
104
90 to 135
10 to 105
NORMAL CRUISE
(7) (9)
(9)
800
104
90 to 135
10 to 105
NORMAL CLIMB
(9)
(9)
75
760
88
1650
90 to 135
10 to 105
MAX. REVERSE
104
-40 to 110
TRANSIENT
138 (8)
870 (8)
1870 (8)
40 (Min)
200 (Max)
(8)
NOTE
The limits presented do not necessarily occur simultaneously. Whenever operation limits are
exceeded the pilot will record the value and duration of the condition encountered on DA Form
2408-13-1.
(1)
Torque limit applies within range of 1000 to 1700 propeller RPM (N2). Below 1000 RPM, torque is limited
to 54%.
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