261
Federal Aviation Administration, DOT
Pt. 121, App. C
33.
Carriage of cargo in passenger compart-
ments.
Section 121.285 is not applicable to
nontransport category C–46 cargo airplanes.
34.
Carriage of cargo in cargo compartments.
A standard cargo loading and tiedown ar-
rangement set forth in the operator’s man-
ual and found acceptable to the Adminis-
trator must be used in complying with
§ 121.287.
35.
Performance data.
Performance data on
Curtiss model C–46 airplane certificated for
maximum weight of 45,000 and 48,000 pounds
for cargo-only operations.
1. The following performance limitation
data, applicable to the Curtiss model C–46
airplane for cargo-only operation, must be
used in determining compliance with
§§ 121.199 through 121.205. These data are pre-
sented in the tables and figures of this ap-
pendix.
T
ABLE
1—T
AKEOFF
L
IMITATIONS
(a) Curtiss C–46 certificated for maximum
weight of 45,000 pounds.
(1)
Effective length
of runway required when
effective length is determined in accordance
with § 121.171 (distance to accelerate to 93
knots TIAS and stop, with zero wind and
zero gradient). (Factor = 1.00)
[Distance in feet]
Standard altitude in feet
Airplane weight in pounds
39,000 42,000 45,000
1
S.L .......................................
4,110 4,290 4,570
1,000 ....................................
4,250 4,440 4,720
2,000 ....................................
4,400 4,600 4,880
3,000 ....................................
4,650 4,880 5,190
4,000 ....................................
4,910 5,170 5,500
5,000 ....................................
5,160 5,450 5,810
6,000 ....................................
5,420 5,730 6,120
7,000 ....................................
5,680 6,000 6,440
8,000 ....................................
5,940 6,280
(
1
)
1
Ref. Fig. 1(a)(1) for weight and distance for altitudes
above 7,000
′
.
(2) Actual length of runway required when
effective length,
considering obstacles, is not
determined (distance to accelerate to 93
knots TIAS and stop, divided by the factor
0.85).
[Distance in feet]
Standard altitude in feet
Airplane weight in pounds
39,000 42,000 45,000
1
S.L .......................................
4,830 5,050 5,370
1,000 ....................................
5,000 5,230 5,550
2,000 ....................................
5,170 5,410 5,740
3,000 ....................................
5,470 5,740 6,100
4,000 ....................................
5,770 6,080 6,470
5,000 ....................................
6,070 6,410 6,830
6,000 ....................................
6,380 6,740 7,200
7,000 ....................................
6,680 7,070 7,570
8,000 ....................................
6,990 7,410
(
1
)
1
Ref. Fig. 1(a)(2) for weight and distance for altitudes
above 7,000
′
.
(b) Curtiss C–46 certificated for maximum
weight 48,000 pounds.
(1)
Effective length
of runway required when
effective length is determined in accordance
with § 121.171 (distance to accelerate to 93
knots TIAS and stop, with zero wind and
zero gradient). (Factor = 1.00)
[Distance in feet]
Standard altitude
in feet
Airplane weight in pounds
39,000 42,000 45,000 48,000
1
S.L .....................
4,110 4,290 4,570 4,950
1,000 ..................
4,250 4,440 4,720 5,130
2,000 ..................
4,400 4,600 4,880 5,300
3,000 ..................
4,650 4,880 5,190 5,670
4,000 ..................
4,910 5,170 5,500 6,050
5,000 ..................
5,160 5,450 5,810 6,420
6,000 ..................
5,420 5,730 6,120 6,800
7,000 ..................
5,680 6,000 6,440
(
1
)
8,000 ..................
5,940 6,280 6,750
(
1
)
1
Ref. Fig. 1(b)(1) for weight and distance for altitudes
above 6,000
′
.
(2) Actual length of runway required when
effective length,
considering obstacles, is not
determined (distance to accelerate to 93
knots TIAS and stop, divided by the factor
0.85).
[Distance in feet]
Standard altitude
in feet
Airplane weight in pounds
39,000 42,000 45,000 48,000
1
S.L .....................
4,830 5,050 5,370 5,830
1,000 ..................
5,000 5,230 5,550 6,030
2,000 ..................
5,170 5,410 5,740 6,230
3,000 ..................
5,470 5,740 6,100 6,670
4,000 ..................
5,770 6,080 6,470 7,120
5,000 ..................
6,070 6,410 6,830 7,560
6,000 ..................
6,380 6,740 7,200 8,010
7,000 ..................
6,680 7,070 7,570
(
1
)
8,000 ..................
6,990 7,410 7,940
(
1
)
1
Ref. Fig. 1(b)(2) for weight and distance for altitudes
above 6,000
′
.
T
ABLE
2—E
N
R
OUTE
L
IMITATIONS
(a) Curtiss model C–46 certificated for max-
imum weight of 45,000 pounds (based on a
climb speed of 113 knots (TIAS)).
Weight (pounds)
Terrain
clearance
(feet)
1
Blower set-
ting
45,000 ............................................
6,450 Low.
44,000 ............................................
7,000 Do.
43,000 ............................................
7,500 Do.
42,200 ............................................
8,000 High.
41,000 ............................................
9,600 Do.
40,000 ............................................
11,000 Do.
39,000 ............................................
12,300 Do.
1
Highest altitude of terrain over which airplanes may be op-
erated in compliance with § 121.201.
Ref. Fig. 2(a).
(b) Curtiss model C–46 certificated for max-
imum weight of 48,000 pounds or with engine
installation approved for 2,550 revolutions
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