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incorporated for airplane to operate at the
maximum taxi and ramp weight of 44,750 lb I
(20,298 kg) and at the maximum take-off |
weight of 44,600 lb (20,230 kg).
2. Canadair Service Bulletin 601-0360,
Modification - Increased MTOH - 45,100 lb,
must be incorporated to operate at the
maximum taxi and ramp weight of 45,250 lb
(20,525 kg) and at the maximum take-off
weight of 45,100 lb (20,457 kg).
3. The maximum take-off weight (MTOW) and/or
maximum landing weight (MLH) may be further
limited due to tire pressures, brake kinetic
energy, tire limit speeds and/or performance
considerations (refer to LIMITATIONS - TIRE
PRESSURES, NORMAL PROCEDURES and
PERFORMANCE).
DOT Approved
Sep 25/90 LIMITATIONS
44,600 Page 1
canadair
chanenQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY (LIMITS)
The maximum permissible centre of gravity (CG) range with landing gear extended
is shown in Figure 1 and Figure 1A. The airplane must be loaded in accordance
with the loading instructions associated with the Weight and Balance Report,
Reference RAW-601-***, pertaining to the particular aircraft. The effect of
landing gear retraction on CG position is negligible.
***Each report is identified by the airplane serial number.
LIMITATIONS T
Page 2 44,600
canadair
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY LIMITS
MILLIMETRES AFT OF DATUM
46
45
44
43.
42.
41.
40.
39.
38
37.
CD
. 36.
2 35.
l
?34
o
* 3 3
32.
31,
30.
29.
28
27.
26
25
24
12
ftC
25 12
M 5
16.
776 12
03 5
0 X M
MAX
V
\
*27 12
•05 i
*X RAI
AKE (
\
\
2(
(878
»7
JP 44!
IFF 44
MAX 1
MA
Ml
.OX
12929
INCH!
50 LE
600 L
.AND If
( ZER<
JIMUM
12979
:s AFI
511
- 20
B - 2(
10 36C
> FUEL
FLICK
13030
OF D
513
298 K
)230 >
00 LB
3100
T 250
13081
ATUM
515
5 29.f
C A
- 16,
0 LB •
00 L6
1313,
517
. X
• •
\
\29 K(
- 140(
- ii;
I 1318
519
rV
\\1
11 KG
140 KC
3
\
\
35
323
521
.0
3 132C
52:
X
u
20.0
.19.0
.18.0
.17.0
16
o
o
o§
I
O
.15.0
14.0
.13.0
.12.0
.11.0
12 14 16 18 20 22 24 26 28 30 32 34 36 38 40
X M.A.C.
DOT Approved
Nov 07/89
44,600
Centre of Gravity Limits
Figure 1 LIMITATIONS
Page 3
canadair
chanencjer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY LIMITS
46
44
43.
42.
41
40.
39.
38
37
CD
8-
35
5 34.
32
31
30
29
28
27
?6
25
24
12"
5<
'25 12
II 5
16.
776 13
03 9
17.0
0 % M
*AX
"827 1
«5
X
KK RAJ
AKEOf
\
: : *
Ml
2878
M>7
IP 45:
F 451
MAX
MA
Ml
.OX
LLIME
12929
INCHI
i
509
50 LE
00 LB
LAND
< ZER(
VIMUM
TRES i
12979
IS AF1
i
511
NG 3<
> FUEl
FLIGt
KF1 OF
13030
r OF o
513
.0 *
*25 K
157 IS
•000 L
3100
T 250
' OATU
13081
ATUM
515
; 29.1
8 - 1
0 LB
00 LB
IM
1313
517
X
\
\
\
>329 1
- 140<
- ii;
I 1318
519
\
\ A
1 KG
>40 K(
3
-
35
I32J
521
:
.0
3 1321
52.
x
20.0
,19.0
.18.0
J7.0
o
o
.16.0 2
1
5
.15.0 ^
,14.0
.13.0
.12.0
.11.0
12 14 16 18 20 22 24 26 28 30 32 34 36 38 40
X M.A.C.
LIMITATIONS
Page 4
Centre of Gravity Limits
(A/C incorporating Service Bulletin 601-0360)
　
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