# TCDS 1A20: Bombardier Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Bombardier Inc.
- Revision: 6
- Revised: March 24, 1998
- Product: Aircraft, Large Airplane
- Certification basis: Part 1, Part 25, CAR 4b
- Data sheet PDF: https://openairdocs.org/files/sha256/49/d8/49d81ecf205bbdffa145ad5d9bc282cbd8be7c4a3c17544184decf7b5e8100d3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/131EB2C409EF0A3185256722006F63BD.0001
- Page: https://openairdocs.org/tcds/1A20

## Models (2)

As the data sheet lists them.

- CL-44D4
- CL-44J

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18
Rev. No. 6 - - - - - - - - - - - - - - - - 5
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
1A20
Revision 6
Bombardier
CL-44D4
CL-44J
March 24, 1998
TYPE  CERTIFICATE  DATA SHEET NO.1A20
This data sheet which is a part of type certificate No. 1A20 prescribes conditions and limitations under which the product for
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.
Type Certificate Holder Bombardier Inc.
P.O. Box 6087, Station Centre-ville
Montreal, Quebec, Canada H3C 3G9
I - Model CL-44D4 (Transport Category), Approved 24 May 1961 by the FAA and 23 May 1961 by the Canadian Department of
Transport (DOT).
Engines 4 Rolls-Royce Tyne 515 (Turboprop)
Reduction gearing 0.064:1
Fuel For approved fuels additives and deviations to fuel specifications see DOT approved
Airplane Flight Manual.
Oil (Engine & Gearbox) Esso Aviation Turbo oil 35
Enco Turbo oil 35
Humble Turbo oil 35
Penola Turbo oil 35
Castrol 98
  (Constant Speed Drive) MIL-L-7808
Engine limits
Static Sea Level Ratings
Max. TGT °C when
Shaft    Jet Max. Engine Max. TGT Rolls Royce Modi-
Horse- Thrust     Speed     °C fication No. 1426
power    (lb.)       (r.p.m.)             is incorporated.
 LP HP
Takeoff (5 min.) 5095 1065 15250 18150   735* 665**
Max. continuous 4685   940 14500 17950   715* 645**
Max. transient for
  starting (5 sec.)   800 725
Max. Reverse Pitch:
  Braking (1 min.) 13250 16600   685* 620
* These limits are applicable at sea level.  Above sea level, the limits increase by
2 1/2°C per 1000 ft. altitude.
** TGT limits are applicable at sea level.  Above sea level the limits increase by
2 1/2°C per 1000 ft. altitude if fuel trimmer control is used, or by 1 1/2°C per
1000 ft. if fuel control is used.
il Inlet Temperature
Minimum for starting  -30°C
Minimum for opening up  -15°C
Maximum allowable:
  With Castrol 98 105°C
  With any other approved oil 100°C

1A20 2
Engine limits  (cont'd) Oil Pressure Limits:
Normal (at 90°C):  40-65 p.s.i. at 14,500 LP r.p.m.
Minimum (at 100°C): 40 p.s.i. at 14,500 LP r.p.m.
Minimum to complete flight: 38 p.s.i. at 11,000 LP r.p.m. and above,
30 p.s.i. at all r.p.m. below 11,000 LP r.p.m.
Air Turbine Starter (At ground air connection)
Maximum pressure .34 p.s.i.g.
Maximum temperature 270°C
Minimum temperature   20°C
Normal Operating Time   30 Sec.
Maximum Operating Time Limit   40 Sec.
Starter Inlet Temperature and Corresponding Pressure Limits:
Maximum 310°C (26 p.s.i.g.)
Intermediate 150°C (32 p.s.i.g.)
Minimum  -30°C (32 p.s.i.g.)
Propeller and 4 DeHavilland propellers Model PD 228/476/2, four blades
  propeller limits Diameter:  16 ft. (+0.14 in., -1.00 in.)
Pitch settings at Station 72.0 in.:
Maximum reverse - 17°
Ground Idle -   7°
Flight Idle +12°
Feather +83°
Airspeed limits
  (CAS) Maximum Operating Limitation Vmo/Mmo
Altitude
in
10,000 ft.
S.L.
to
10
10
to
15
15
to
20
20
to
25
25
to
30
Zero Fuel
Weight m.p.h. (knots) Mach
155,000 288 (250) 290 (252) 292 (254) 296 (257) .62
to (See Note 7)
160,000
153,000 290 (252) 292 (254) 294 (256) 298 (259) .62
151,000 293 (255) 296 (257) 298 (259) 301 (262) .62
149,000 296 (257) 298 (259) 300 (261) 304 (264) .62
147,000 299 (260) 301 (262) 304 (264) 307 (267) .62
145,000 301 (262) 304 (264) 306 (266) 309 (269) .62
143,000 305 (265) 307 (267) 309 (269) 313 (272) .62
141,000 307 (267) 309 (269) 312 (271) 315 (274) .62
139,000 311 (270) 313 (272) 315 (274) 319 (277) .62
137,000 313 (272) 315 (274) 317 (276) 321 (279) .62
135,000 316 (275) 319 (277) 321 (279) 324 (282) .62
or less
Vfe (Flaps extended 5°) 264 m.p.h. (230 knots)  (Mach .50)
Vfe (Flaps extended 15°) 264 m.p.h. (230 knots)
Vfe (Flaps extended 30°) 228 m.p.h. (198 knots)
Vfe (Flaps extended 45°) 172 m.p.h. (150 knots)
Va  (Maneuvering) 241 m.p.h. (210 knots)
Vlo (Landing gear operating) 207 m.p.h. (180 knots)
Vle (Landing gear extended) 211 m.p.h. (184 knots)
Vmca (Minimum control, air) S.L. ISA 118 m.p.h. (103 knots)
Maximum landing light operating speed 190 m.p.h. (165 knots)
Maximum landing light extended speed 241 m.p.h. (210 knots)
Maximum spoiler operating speed 230 m.p.h. (200 knots)
Maximum fuel dump chute extended speed 241 m.p.h. (210 knots)

3 1A20
C.G. range Center-of gravity limits, with landing gear extended, are shown in the following tables;
straight line variations exist between the quoted values.  Gear retraction moment is
+237,609 in.-lb.; retraction of the gear moves the C.G. aft approximately 1% MAC.
C.G. Envelope for Aircraft with Basic Configuration, Zero Fuel
Weight of 155,000 lb. or less.
CENTER OF GRAVITY - PERCENT M.A.C.
95
120
127.4
135
145
155
205
210
688.9 690.4 692.7 699.1 700.5 702.0 717.4 725.5
12.0 17.3 18.0 18.8 26.8 31.012.8 14.0
Zero Fuel Wt. 145,000 lb. to 155,000 lb.
Zero Fuel Wt. 135,000 lb. to 145,000 lb.
Zero Fuel Wt. 135,000 lb. or less
WEIGHT 1,000 lb.
DISTANCE FROM C.G. DATUM - INCHES
C.G. Envelope for Aircraft with Modified Swing Tail Compartment,
Zero Fuel Weight of 155,000 lbs. or less
CENTER OF GRAVITY - PERCENT M.A.C.
95
127.5
135
145
155
205
210
717.4 725.5
26.8 31.0
Zero Fuel Wt. 145,000 lb. to 155,000 lb.
Zero Fuel Wt. 135,000 lb. to 145,000 lb.
Zero Fuel Wt. 135,000 lb. or less
WEIGHT 1,000 lb.
DISTANCE FROM C.G. DATUM - INCHES
703.5 709.7
710.5
710.9
19.6 22.8
23.3
23.4

1A20 4
C.G. Envelope for Aircraft with Basic Configuration of Modified
Swing Tail Compartment, Zero Fuel Weight Between 155,000 lb. and 160,000 lb.
689.7
95
120
140
160
185
205
210
696.7 699.7 704.2 711.7 717.7 723.6 725.1
12.4 14.0 17.6 19.9 23.8 27.0 30.0 30.8
DISTANCE FROM C.G. DATUM - INCHES
CENTER OF GRAVITY - PERCENT M.A.C.
WEIGHT
1,000 LB.
FORWARD LIMIT:
(a) Basic Interior Configuration:
Gross Weight  Limits
Zero Fuel   95,000 14.0% MAC (Sta. 692.7)
Weight 120,000 14.0% MAC (Sta. 692.7)
135,000 lb. 135,000 12.8% MAC (Sta. 690.4)
  or less 145,000 13.6% MAC (Sta. 692.0)
155,000 14.4% MAC (Sta. 693.5)
165,000 15.3% MAC (Sta. 695.2)
205,000 18.4% MAC (Sta. 701.2)
210,000 (see NOTE 8) 18.8% MAC (Sta. 702.0)
Zero Fuel 135,000 12.8% MAC (Sta. 690.4)
Weight 145,000 12.0% MAC (Sta. 688.9)
135,000 lb. 155,000 13.0% MAC (Sta. 690.8)
      to 165,000 13.9% MAC (Sta. 692.5)
145,000 lb. 205,000 17.6% MAC (Sta. 699.7)
210,000 (see NOTE 8) 18.0% MAC (Sta. 700.5)
Zero Fuel 145,000 12.0% MAC (Sta. 688.9)
Weight 155,000 12.0% MAC (Sta. 688.9)
145,000 lb. 165,000 13.0% MAC (Sta. 690.8)
      to 205,000 16.8% MAC (Sta. 698.1)
155,000 lb. 210,000 (see NOTE 8) 17.3% MAC (Sta. 699.1)
Zero Fuel 155,000 12.4% MAC (Sta. 689.7)
Weight 160,000 12.4% MAC (Sta. 689.7)
155,000 lb. 205,000 17.1% MAC (Sta. 698.7)
      to 210,000 17.6% MAC (Sta. 699.7)
160,000
(see NOTE 7)

5 1A20
(b) Modified Swing Tail Compartment for aircraft incorporating Canadair Service
bulletin CL-44D4-245, and CL-44D4-303.  The following limits apply when the
swing-tail cargo load is in excess of 3,000 lb. on airplanes with the standard
swing-tail compartment configuration or in excess of 1,000 lb. on airplanes with
the swing-tail compartment modified to incorporate the dropped floor with
passenger service facilities.
Gross Weight Limits
Zero Fuel   95,000 19.6% MAC (Sta. 703.5)
Weight 120,000 19.6% MAC (Sta. 703.5)
135,000 lb. 135,000 19.6% MAC (Sta. 703.5)
  or less 145,000 20.2% MAC (Sta. 704.7)
155,000 20.6% MAC (Sta. 705.9)
165,000 21.2% MAC (Sta. 706.9)
205,000 23.2% MAC (Sta. 710.5)
210,000 (see NOTE 8) 23.4% MAC (Sta. 710.9)
Zero Fuel 135,000 19.6% MAC (Sta. 703.5)
Weight 145,000 19.6% MAC (Sta. 703.5)
135,000 lb. 155,000 20.2% MAC (Sta. 704.7)
      to 165,000 20.8% MAC (Sta. 705.8)
145,000 lb. 205,000 23.0% MAC (Sta. 710.1)
210,000 (see NOTE 8) 23.3% MAC (Sta. 710.5)
Zero Fuel 145,000 19.6% MAC (Sta. 703.5)
Weight 155,000 19.6% MAC (Sta. 703.5)
145,000 lb. 165,000 20.2% MAC (Sta. 704.7)
      to 205,000 22.5% MAC (Sta. 709.1)
155,000 lb. 210,000 (see NOTE 8) 22.8% MAC (Sta. 709.7)
Zero Fuel 155,000 19.9% MAC (Sta. 704.2)
Weight 160,000 19.9% MAC (Sta. 704.2)
155,000 lb. 205,000 23.4% MAC (Sta. 710.9)
      to 210,000 23.8% MAC (Sta. 711.7)
160,000  (see NOTE 7)
AFT LIMIT:
(a) Aircraft operating with Zero Fuel Weight up to 155,000 lb.
Gross Weight Limits
  95,000 26.8% MAC (Sta. 717.4)
127,400 31.0% MAC (Sta. 725.5)
205,000 31.0% MAC (Sta. 725.5)
210,000 (See NOTE 8) 31.0% MAC (Sta. 725.5)
(b) Aircraft operating with Zero Fuel Weight between 155,000 lb.
and 160,000 lb. (See NOTE 7).
Gross Weight Limits
  95,000 27.0% MAC (Sta. 717.7)
120,000 30.0% MAC (Sta. 723.6)
185,000 30.8% MAC (Sta. 725.1)
205,000 30.8% MAC (STA. 725.1)
210,000 30.8% MAC (Sta. 725.1)
Datum The datum for the center-of-gravity limits is at Station 0, which is 633.0 inches forward
of a jig point located on the underside of the fuselage immediately forward of the front
spar on the aircraft center line.  The jig point is a Philips head screw in the skin joint.

1A20 6
Mean Aerodynamic Chord 192.86 inches (L.E. of M.A.C. is 665.72 inches aft of Station 0).
  (MAC)
Maximum weight Taxi 206,000 lb.
211,000 lb. (See NOTE 8)
Take-off 205,000 lb.
210,000 lb. (see NOTE 8)
Landing 165,000 lb.
Maximum Zero Fuel 155,000 lb.
160,000 lb. (See NOTE 7)
All weights in excess of zero fuel weight must consist of usable fuel.  See Airspeed
Limits for variation of limit airspeeds with zero-fuel weight.
Minimum crew 3:  Pilot, Co-pilot and System Operator.
Maximum passengers Certification of original type design for cargo only.  Maximum Supplemental Type
Certificate configuration approved prior to FAR 25.2 is for 178 passengers.
Maximum cargo Permissible cargo load and distribution varies with interior configuration.  See NOTE 2
for permissible loading for approved configuration.  See NOTE 4(a) for cargo
compartment classification.
Fuel capacity    Total gal.   Usable gal.
Imp. U.S. Imp. U.S. ARM
2 outboard main tanks 3810 4575 3760 4516 734.5
2 inboard main tanks 3802 4566 3736 4486 709.0
c/s auxiliary tank 1636 1965 1626 1954 695.4
2 outboard auxiliary   874 1050   870 1044 765.5
Total 10122 12156 9992 12000
See CL-44D4 NOTE 1(c) for "Systems fuel" data.
Oil capacity    Total pt.   Usable pt.
Imp. U.S. lb. Imp. U.S. lb. ARM
2 outboard engines 124 148.8 150   40 48.0 48.4 (555.0)
2 inboard engines 124 148.8 150   40 48.0 48.4 (513.0)
See CL-44D4 NOTE 1(d) for "System oil" data.
Maximum approved 30,000 ft. if suitable supplementary oxygen dispensing units are provided for
  operating altitude flight altitudes above 10,000 ft.  If no oxygen dispensing units are provided, maximum
operating flight altitude is 10,000 ft.
Other operating This aircraft must be operated in accordance with the limitations listed in the
  limitations Department of Transport Approved Airplane Flight Manual.
Control surface movements Elevators UP 30° Down 15° (from neutral)
L.H. Elevator servo tabs UP 14° Down 26° (rig 1° down)
R.H. Elevator servo tabs UP 16° Down 24° (rig 1° up)
Elevator trim tabs UP 17-1/2° Down 22-1/2° (from neutral)
Rudder Right 16° Left 16° (from neutral)
Rudder servo tabs Right 18° Left 18° (from neutral)
Rudder connected tabs UP 22° Down 18° (rig 2° up)
Aileron UP 21° Down 15° (from neutral)
Aileron servo tabs UP 25° Down 21° (rig 2° up)
Flaps UP 0° Down 45°
Spoilers UP 48° Down 0°
Tab angles measured with control surfaces neutral.

7 1A20
Serial Nos. eligible 9, 14 to 39.  The Canadian Department of Transport Certificate of Airworthiness for
export endorsed as noted under "Import Eligibility" must be submitted for each
individual aircraft for which application for certification is made.
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian
Department of Transport "Certificate of Airworthiness for Export" signed by the
Minister of Transport or his authorized representative. This form must contain the
following statement: This certifies that the aircraft described below has been
manufactured in conformity with data forming the basis for D.O.T. Type Approval No.
A55 (FAA Type Certificate No. 1A20)."
Certification basis CAR 4b dated 31 December 1953; amendments 4b-1 through 4b-10; amendment 4b-11
with the exception of items 6, 9, 17, 26, 27, 28, 33 and 44; and special regulation
SR-422B.  Type Certificate No. 1A20 issued 24 May 1961.  Date of Application for
Type Certificate 1 August 1957.
Compliance with the following optional requirements has been established:  Ditching,
CAR 4b.361--Structural approval only-- eligible for ditching approval when the
required ditching equipment and storage provisions are approved.  Ice Protection, CAR
4b.640.
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed in the aircraft for certification including DOT
approved Flight Manual (Canadair Service Publication No. 153 latest approved revision
for the CL44D4).  Canadair Report No. RAL-44-102 latest revised "Equipment
Qualification List for CL44D4", lists all required equipment that must be installed as
well as optional equipment installations approved by DOT.
In addition the following items of equipment are required:
Stall warning devise as follows:
Drawing No.    Part     P/N
44-53055 Transducer 44-50750-8
44-53013 Potentiometer 44-50750-10
44A-51410 Stick Shaker 44-50750-2
44D-51061 Computer 44-50750-162
II - Model CL-44J (Transport Category), Approved 28 January 1972 by the FAA and 8 July 1970 by the Canadian Department of
Transport (DOT).
Engines 4 Rolls-Royce Tyne 515 (Turboprop)
Reduction gearing 0.064:1
Fuel For approved fuels additives and deviations to fuel specifications see DOT approved
Airplane Flight Manual
Oil (Engine & Gearbox) Esso Aviation Turbo oil 35
Enco Turbo oil 35
Humble Turbo oil 35
Penola Turbo oil 35
Castrol 98
  (Constant Speed Drive) MIL-L-7808

1A20 8
Engine limits
Static Sea Level Ratings
Max. TGT °C when
Shaft    Jet Max. Engine Max. TGT Rolls Royce Modi-
Horse- Thrust     Speed     °C fication No. 1426
power    (lb.)       (r.p.m.)             is incorporated.
 LP HP
Takeoff (5 min.) 5095 1065 15250 18150   735* 665**
Max. continuous 4685   940 14500 17950   715* 645**
Max. transient for
  starting (5 sec.)   800 725
Max. Reverse Pitch:
  Braking (1 min.) 13250 16600   685* 620
*These limits are applicable at sea level.  Above sea level, the limits increase by
  2 1/2°C per 1000 ft. altitude.
**TGT limits are applicable at sea level.  Above sea level the limits increase by
  2 1/2°C per 1000 ft. altitude if fuel trimmer control is used, or by 1 1/2°C per
  1000 ft. if fuel control is used.
Oil Inlet Temperature
Minimum for starting - 30°C
Minimum for opening up  -15°C
Maximum allowable:
  With Castrol 98 105°C
  With any other approved oil 100°C
Oil Pressure Limits:
Normal (at 90°C):  40-65 p.s.i. at 14,500 LP r.p.m.
Minimum (at 100°C): 40 p.s.i. at 14,500 LP r.p.m.
Minimum to complete flight: 38 p.s.i. at 11,000 LP r.p.m. and above,
                             30 p.s.i. at all r.p.m. below
                             11,000 r.p.m.
Air Turbine Starter (At ground air connection)
Maximum pressure .34 p.s.i.g.
Maximum temperature 270°C
Minimum temperature   20°C
Normal Operating Time   30 Sec.
Maximum Operating Time Limit   40 Sec.
Starter Inlet Temperature and Corresponding Pressure Limits:
Maximum 310°C (26 p.s.i.g.)
Intermediate 150°C (32 p.s.i.g.)
Minimum -30°C (32 p.s.i.g.)
Propeller and 4 DeHavilland propellers Model PD 228/476/2, four blades
  propeller limits Diameter:  16 ft. (+0.14 in., -1.00 in.)
Pitch settings at Station 72.0 in.:
Maximum reverse -17°
Ground Idle  - 7°
Flight Idle +12°
Feather +83°

9 1A20
Airspeed limits Maximum Operating Limitation Vmo/Mmo
  (CAS) (a)  With Landing Fuel Weight of 25,000 lb. or less.
Altitude
in
10,000 ft.
S.L.
to
10
10
to
15
15
to
20
20 to 25
Lesser of
   Vmo                       Mmo
Zero Fuel
Weight m.p.h. (knots) Mach
160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62)
(b)  With Landing Fuel Weight of 25,000 lbs. or less and Canadair Service Bulletin CL44-476 Incorporated.
Altitude
in
10,000 ft.
S.L.
to
10
10
to
15
15
to
20
20 to 25
Lesser of
   Vmo                       Mmo
Zero Fuel
Weight m.p.h. (knots) Mach
160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62)
158,000 290 (252) 292 (254) 295 (256) 298 (259) (.62)
155,000 293 (255) 296 (257) 298 (259) 301 (262) (.62)
153,000 296 (257) 298 (259) 300 (261) 304 (264) (.62)
150,000 299 (260) 301 (262) 304 (264) 307 (267) (.62)
147,000 303 (263) 305 (265) 307 (267) 311 (270) (.62)
145,000 305 (265) 307 (267) 309 (269) 313 (272) (.62)
143,000 307 (267) 309 (269) 312 (271) 315 (274) (.62)
140,000 311 (270) 313 (272) 315 (274) 319 (277) (.62)
138,000 313 (272) 315 (274) 318 (276) 321 (279) (.62)
135,000 316 (275) 319 (277) 321 (279) 324 (282) (.62)
or less
(c)  With landing fuel weight between 25,000 lbs. and 30,000 lbs. (with Canadair SB CL44-477 Incorporated).
Altitude
in
10,000 ft.
S.L.
to
10
10
to
15
15
to
20
20 to 25
Lesser of
   Vmo                       Mmo
Zero Fuel
Weight m.p.h. (knots) Mach
160,000 288 (250) 290 (252) 292 (254) 296 (257) (.62)
155,000 288 (250) 290 (252) 292 (254) 296 (257) (.62)
153,000 290 (252) 292 (254) 295 (256) 298 (259) (.62)
150,000 293 (255) 296 (257) 298 (259) 301 (262) (.62)
147,000 297 (258) 299 (260) 301 (262) 305 (265) (.62)
145,000 299 (260) 301 (262) 304 (264) 307 (267) (.62)
143,000 301 (262) 304 (264) 306 (266) 309 (269) (.62)
140,000 305 (265) 307 (267) 309 (269) 313 (272) (.62)
138,000 307 (267) 309 (269) 312 (271) 315 (274) (.62)
135,000 311 (270) 313 (272) 315 (274) 319 (277) (.62)
Vfe (Flaps extended 5°) 264 m.p.h. (230 knots)  (Mach .50)
Vfe (Flaps extended 15°) 264 m.p.h. (230 knots)
Vfe (Flaps extended 30°) 228 m.p.h. (198 knots)
Vfe (Flaps extended 45°) 172 m.p.h. (150 knots)
Va  (Maneuvering) 241 m.p.h. (210 knots)
Vlo (Landing gear operating) 207 m.p.h. (180 knots)
Vle (Landing gear extended) 211 m.p.h. (184 knots)
Vmca (Minimum control, air) S.L. ISA 118 m.p.h. (103 knots)
Maximum landing light operating speed 190 m.p.h. (165 knots)
Maximum landing light extended speed 241 m.p.h. (210 knots)
Maximum spoiler operating speed 230 m.p.h. (200 knots)
Maximum fuel dump chute extended speed 241 m.p.h. (210 knots)

1A20 10
C.G. range Center-of gravity limits, with landing gear extended, are shown in the following tables;
straight line variations exist between the quoted values.  Gear retraction moment is
+237,609 in.-lb.; retraction of the gear moves the C.G. aft approximately 1% MAC.
C.G. Envelope for CL-44J Cargo Configuration
             (See NOTE 4(b))
CENTER OF GRAVITY - % M.A.C.
95
120
135
145
203
210
809.9 813.7 819.5 821.5 823.5 832.5 844.6
12.0 17.0 18.0 19.0 30.814.0
Zero Fuel Wt. 160,000 lb.
Zero Fuel Wt. 145,000 lb.
Zero Fuel Wt. 135,000 lb.
W E IG H T 1 ,0 0 0 lb .
DISTANCE FROM C.G. DATUM - INCHES
160
185
165
175
23.5 30.0
846.1
FORWARD LIMIT:  (Geardown)
  Cargo Configuration  (see Note 4 (b)
Gross Weight  Limits
Zero Fuel   95,000 14.0% MAC (Sta. 813.7)
Weight 120,000 14.0% MAC (Sta. 813.7)
135,000 lb. 135,000 12.8% MAC (Sta. 811.4)
  or less 145,000 13.7% MAC (Sta. 813.1)
160,000 15.1% MAC (Sta. 815.8)
203,000 19.0% MAC (Sta. 823.5)
Zero Fuel 135,000 12.8% MAC (Sta. 811.4)
Weight 145,000 12.0% MAC (Sta. 809.9)
135,000 lb. 160,000 13.4% MAC (Sta. 812.5)
      to 203,000 17.4% MAC (Sta. 820.4)
145,000 lb. 210,000 18.0% MAC (Sta. 821.5)
Zero Fuel 145,000 12.0% MAC (Sta. 809.9)
Weight 160,000 12.0% MAC (Sta. 809.9)
145,000 lb. 203,000 16.4% MAC (Sta. 818.5)
      to 210,000 17.0% MAC (Sta. 819.7)
160,000 lb. 210,000
AFT LIMIT (Gear Down)
  Cargo Configuration  (See Note 4 (b).)
Zero Fuel   95,000 23.5% MAC (Sta. 832.5)
Weight 145,000 30.0% MAC (Sta. 844.6)
135,000 lb. 165,000 30.8% MAC (Sta. 846.1)
 or less 175,000 30.8% MAC (Sta. 846.1
185,000 30.8% MAC (Sta. 846.1)
203,000 30.8% MAC (Sta. 846.1)

11 1A20
AFT LIMIT (Gear Down)   (cont'd)
  Cargo Configuration  (See Note 4 (b).)
Zero Fuel   95,000 23.5% MAC (Sta. 832.5)
Weight 145,000 30.0% MAC (Sta. 844.6)
135,000 lb. 165,000 30.0% MAC (Sta. 844.6)
    to 175,000 30.8% MAC (Sta. 846.1)
145,000 lb. 185,000 30.8% MAC (Sta. 846.1)
Zero Fuel   95,000 23.5% MAC (Sta. 832.5)
Weight 145,000 30.0% MAC (Sta. 844.6)
145,000 lb. 165,000 30.0% MAC (Sta. 844.6)
    to 175,000 30.0% MAC (Sta. 844.6)
160,000 lb. 185,000 30.8% MAC (Sta. 846.1)
203,000 30.8% MAC (Sta. 846.1)
210,000 30.8% MAC (Sta. 846.1)
Datum The datum for the center-of-gravity limits is at Station 0, which is 754.00 inches
forward of a jig point located on the underside of the fuselage immediately forward of
the front spar on the aircraft center line.  The jig point is a Philips head screw in the
skin joint.
Mean Aerodynamic Chord 192.86 inches (L.E. of M.A.C. is 786.72 inches aft of Station 0).
  (MAC)
Maximum weight Taxi 211,000 lb.
Take-off 210,000 lb.
Landing 175,000 lb.
Maximum Zero Fuel 160,000 lb.
All weights in excess of zero fuel weight must consist of usable fuel.  See Airspeed
Limits for variation of limit airspeeds with zero-fuel weight.
Minimum crew 3:  Pilot, Co-pilot and System Operator.
Maximum passengers Certification of original type design for cargo only.
Maximum cargo Permissible cargo load and distribution varies with interior configuration.  See NOTE 2
for permissible loading for approved configuration.  See NOTE 4(b) for cargo
compartment classification.
Fuel capacity        Total Gal.       Usable Gal.
  Imp. U.S.   Imp. U.S.  ARM
2 outboard main tanks 3,810   4,575 3,760   4,516 855.5
2 inboard main tanks 3,802   4,566 3,736   4,486 830.0
2 outboard auxiliary    874         1,050            870         1,044                 786.5
Total 8,486 10,191 8,366 10,046
See CL-44J NOTE 1(c) for "System fuel" data.
Oil capacity Total Gal. Usable pt.
Imp Pts. (lb.) Imp.  Pts. (lb.) ARM
2 outboard engines 124 150 40 48.4 676.0
2 inboard engines 124 150 40 48.4 634.0
See CL-44J NOTE 1(d) for "System oil" data.
Maximum approved 25,000 ft. if suitable supplementary oxygen dispensing units are provided for flight
  operating altitude altitudes above 10,000 ft.  If no oxygen dispensing units are provided, maximum
operating flight altitude is 10,000 ft.

1A20 12
Other operating This aircraft must be operated in accordance with the limitations listed in the
  limitations Department of Transport Approved Airplane Flight Manual.
Serial Nos. eligible 9, 14 to 39.  The Canadian Department of Transport Certificate of Airworthiness for
export endorsed as noted under "Import Eligibility" must be submitted for each
individual aircraft for which application for certification is made.
Import eligibility A U.S. Airworthiness Certificate may be issued on the basis of the Canadian
Department of Transport "Certificate of Airworthiness for Export" signed by the
Minister of Transport or his authorized representative. This form must contain the
following statement: This certifies that the aircraft described below has been
manufactured in conformity with data forming the basis for D.O.T. Type Approval No.
A55 (FAA Type Certificate No. 1A20)."
Certification basis CAR 4b dated 31 December 1953; amendments 4b-1 through 4b-10; amendment 4b-11
with the exception of items 6, 9, 17, 26, 27, 28, 33 and 44; and special regulation SR-
422B.  Type Certificate No. 1A20 issued 24 May 1961.  Date of Application for Type
Certificate 1 August 1957.
Compliance with the following optional requirements has been established:  Ditching,
CAR 4b.361--Structural approval only-- eligible for ditching approval when the
required ditching equipment and storage provisions are approved.  Ice Protection, CAR
4b.640.
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed in the aircraft for certification including DOT
approved Flight Manual (Canadair Service Publication No. 188, latest approved
revision for the CL-44J).  Canadair Report No. RAL-44-102 latest revised "Equipment
Qualification List for CL-44J", lists all required equipment that must be installed as
well as optional equipment installations approved by DOT.
In addition the following items of equipment are required:
Stall warning devise as follows:
Drawing No. Part P/N
44-53055 Transducer 44-50750-8
44-53013 Potentiometer 44-50750-10
44A-51410 Stick Shaker 44-50750-2
44D-51061 Computer 44-50750-162
DATA PERTINENT TO ALL MODELS
Leveling means Plumb bob suspension point in the roof of crew compartment over a target plate fixed in
the floor, (Ref.: Sta. 198.3).
Control surface movements Elevators UP 30° Down 15° (from neutral)
L.H. Elevator servo tabs UP 14° Down 26° (rig 1° down)
R.H. Elevator servo tabs UP 16° Down 24° (rig 1° up)
Elevator trim tabs UP 17-1/2° Down 22-1/2° (from neutral)
Rudder Right 16° Left 16° (from neutral)
Rudder servo tabs Right 18° Left 18° (from neutral)
Rudder connected tabs UP 22° Down 18° (rig 2° up)
Aileron UP 21° Down 15° (from neutral)
Aileron servo tabs UP 25° Down 21° (rig 2° up)
Flaps UP 0° Down 45°
Spoilers UP 48° Down 0°
Tab angles measured with control surfaces neutral.

13 1A20
NOTE 1. Applicable to Model CL-44D4
(a) Current weight and balance report, including list of equipment included in certificated empty weight, and
loading instructions when necessary, must be in each aircraft at the time of original certification, and at
all times thereafter except in the case of operators having an approved weight control system.
(b) The airplane must be loaded so that the C.G. is within the specified limits at all times with the effects of
fuel use taken into account.  The fuel loading and consumption must be in accordance with schedule
given in Tables 1 through 4 of Section 2 of the DOT approved Flight Manual.
(c) Systems fuel, which must be included in the empty weight, is the amount of fuel required to fill the
system piping, plus the unusable fuel in the fuel tanks.  The amount of "System Fuel" is as follows:
  31.2 U.S. gal. 26.0 Imp. gal.) in the system piping (CG ARM 733.4 in.)
154.8 U.S. gal. (129.0 Imp. gal.) in the Tanks (CG ARM 723.4 in.)
186.0 (155.0 (CG ARM 725.1 in.)
(d) System oil, which must be included in empty weight, is the amount of oil normally trapped in the
propellers, plus the amount normally trapped in the engines after oil drainage.  The total amount of
"System Oil" is as follows:
61.4 U.S. pt. (51.2 Imp. Pt.) (total) in outboard engines (CG ARM 569 in.)
61.4 U.S. pt. (51.2 Imp. Pt.) (total) in inboard engines (CG ARM 527 in.)
75.6 U.S. pt. (63.0 Imp. Pt.) (total) in outboard propellers (CG ARM 534 in.)
75.6 U.S. pt. (63.0 Imp. Pt.) (total) in inboard propellers (CG ARM 492 in.)
Applicable to Model CL-44J, Cargo Variant
(a) Current weight and balance report, including list of equipment included in certificated empty weight, and
loading instructions when necessary, must be in each aircraft at the time of original certification, and at
all times thereafter except in the case of operators having an approved weight control system.
(b) The airplane must be loaded so that the C.G. is within the specified limits at all times with the effects of
fuel use taken into account.  The fuel loading and consumption must be in accordance with schedule
given in Tables 1 through 4 of Section 2 of the DOT approved Flight Manual.
(c) Systems fuel, which must be included in the empty weight, is the amount of fuel required to fill the
system piping, plus the unusable fuel in the fuel tanks.  The amount of "System Fuel" is as follows:
 31.2 U.S. gal. (  26.0 Imp. gal.) in the system piping (CG ARM 854.4 in.)
144.0 U.S. gal. (120.0 Imp. gal.) in the Tanks (CG ARM 844.4 in.)
175.2 U.S. gal. (146.0 Imp. gal.) total amount of system fuel (CG ARM 846.1 in.)
(d) System oil, which must be included in empty weight, is the amount of oil normally trapped in the
propellers, plus the amount normally trapped in the engines after oil drainage.  The total amount of
"System Oil" is as follows:
61.4 U.S. pt. (51.2 Imp. Pt.) (total) in outboard engines (CG ARM 690 in.)
61.4 U.S. pt. (51.2 Imp. Pt.) (total) in inboard engines (CG ARM 648 in.)
75.6 U.S. pt. (63.0 Imp. Pt.) (total) in outboard propellers (CG ARM 655 in.)
75.6 U.S. pt. (63.0 Imp. Pt.) (total) in inboard propellers (CG ARM 613 in.)

1A20 14
NOTE 2. Applicable to Model CL-44D4
The following placards must be displayed as indicated:
(a) Systems Operator's Panel
"FUEL JETTISONING
  MAXIMUM SPEED......................... 209 KTS. (IAS)
 CLIMB ATTITUDE ALL OTHER
 1 OR MORE FLIGHT CONDITION
 INOPERATIVE FLAPS
 ENGINES: 0° OR
 FLAPS 15° 15°
(b) Forward Lower Cargo Compartment:
 MAXIMUM CAPACITY 10,775 lb.
 ALLOWABLE FLOOR LOADING  75 lb./sq. ft.
(c) Aft Lower Cargo Compartment:
 MAXIMUM CAPACITY 11,560 LB.
 ALLOWABLE FLOOR LOADING 75 lb./sq. ft.
(d) Main Fuselage Compartment:  Permissible loads for the swing tail and aft fuselage vary with the
configuration of the swing tail compartment.  One of more of the following placards apply:
Placard No. 1 applies to the basic interior configuration.
Placard No. 2 applies when the aft section of the main fuselage compartment is modified in accordance
with Canadair Service Bulletin No. CL44D4-303.
Placard No. 3 applies to aircraft incorporating structural provisions for increased swing tail compartment
cargo capacity per Part 1 of Canadair Service Bulletin No. CL44D4-245.  The cargo load of
Compartment N may be increased above 3,000 pounds provided the following limitations are observed:
(1) The total weight of cargo in Compartment N must not exceed 4,200 lb.
(2) The center-of-gravity of the compartment load must lie between Station 1237 and 1290, and not less
than 20 inches to starboard of compartment centerline.
(3) The forward center-of-gravity limits of Page 5, Item (b), apply.
Placard No. 4 applies to those aircraft which incorporate structural provisions for increased swing tail
compartment cargo capacity per Part B of Canadair Service Bulletin No. CL44D4-245.  The cargo load of
Compartment N may be increased above 1,000 pounds provided the following limitations are observed:
(1) The total weight of cargo and passenger service facilities (i.e., galleys, toilets, partitions, etc.) in
Compartment N must not exceed 4,200 lb.
(2) Cargo in Compartment N loaded forward of Station 1303 must not exceed 3,200 lb.
(3) The total longitudinal moment of cargo and of passenger service facilities in Compartment N,
measured with respect to Station 1228.5, must not exceed 258,000 inch pounds.
(4) The total lateral moment of cargo and of passenger service facilities in Compartment N, measured
with respect to the hinge line BL 68 RH, must not exceed 201,500 inch pounds.
(5) The seat rails in Compartment N must not be used for crash restraint of cargo in excess of 1,400 lb.

15 1A20
(6) The forward center-of-gravity limits of Page 5, Item (b), apply.
In Placard Nos. 1 through 4, the maximum allowable floor loadings shown for all compartments except F and
G are limited by floor panel strength.  The floor supporting structure for all compartments is approved for a
maximum allowable loading equivalent to 300 lb./sq. feet.
Placard No. 1
Limits of Compartment Placard
Fwd.
(Station)
Aft
(Station) Compartment
Maximum
Capacity
(lb.)
Total Load
Forward of
Aft. Sta.
including
load in lower
cargo compart-
ment must not
exceed
Total Load
aft of Fwd.
Sta. including
load in lower
compartment
must not
 exceed
Maximum
allowable
floor
loading
lb./sq.ft.
247 331 B 7700 9160 200
331 421 C 8250 15460 200
421 511 D 8250 21760 200
511 601 E 8250 28060 200
601 691 F 8250 35160 300
691 781 G 8250 37490 300
781 871 H 8250 30060 200
871 961 J 8250 23760 200
961 1051 K 8250 17460 200
1051 1141 L 5830 11160 200
1141 1237 M 4950 6840 200
1237 1406 N 3000 3000 150
Placard No. 2
Limits of Compartment Placard
Fwd.
(Station)
Aft
(Station) Compartment
Maximum
Capacity
(lb.)
Total Load
Forward of
Aft. Sta.
including
load in lower
cargo compart-
ment must not
exceed
Total Load
aft of Fwd.
Sta. including
load in lower
compartment
must not
 exceed
Maximum
allowable
floor
loading
lb./sq.ft.
247 331 B 7700 9160 200
331 421 C 8250 15460 200
421 511 D 8250 21760 200
511 601 E 8250 28060 200
601 691 F 8250 35160 300
691 781 G 8250 37110 300
781 871 H 8250 29680 200
871 961 J 8250 23380 200
961 1051 K 8250 17080 200
1051 1141 L 5830 10780 200
1141 1237 M 4950 5800 200
1237 1303 N 1000 1000 150

1A20 16
Placard No. 3
Limits of Compartment Placard
Fwd.
(Station)
Aft
(Station) Compartment
Maximum
Capacity
(lb.)
Total Load
Forward of
Aft. Sta.
including
load in lower
cargo compart-
ment must not
exceed
Total Load
aft of Fwd.
Sta. including
load in lower
compartment
must not
exceed
Maximum
allowable
floor
loading
lb./sq.ft.
247 331 B 7700 9160 200
331 421 C 8250 15460 200
421 511 D 8250 21760 200
511 601 E 8250 28060 200
601 691 F 8250 35160 300
691 781 G 8250 38690 300
781 871 H 8250 31260 200
871 961 J 8250 24960 200
961 1051 K 8250 18660 200
1051 1141 L 5830 12360 200
1141 1237 M 4950 8040 200
1237 1406 N 3000 4200 150
Placard No. 4
Limits of Compartment Placard
Fwd.
(Station)
Aft
(Station) Compartment
Maximum
Capacity
(lb.)
Total Load
Forward of
Aft. Sta.
including
load in lower
cargo compart-
ment must not
exceed
Total Load
aft of Fwd.
Sta. including
load in lower
compartment
must not
exceed
Maximum
allowable
floor
loading
lb./sq.ft.
247 331 B 7700 9160 200
331 421 C 8250 15460 200
421 511 D 8250 21760 200
511 601 E 8250 28060 200
601 691 F 8250 35160 300
691 781 G 8250 38690 300
781 871 H 8250 31260 200
871 961 J 8250 24960 200
961 1051 K 8250 18660 200
1051 1141 L 5830 12360 200
1141 1237 M 4950 8040 200
1237 1303 N 1000 4200 150
1303 1406 40
Applicable to Model CL-44J, cargo variant
(a) Flight Crew Compartment
(1) Systems Operator's Panel
"FUEL JETTISONING
 MAXIMUM SPEED......................... 209 KTS. (IAS)
CLIMB ATTITUDE                   ALL OTHER
1 OR MORE                              FLIGHT CONDITIONS
INOPERATIVE                            FLAPS
ENGINES:                               0° OR
FLAPS 15°                              15°

17 1A20
(2) In pilot's view:
"THIS AIRCRAFT APPROVED FOR CARGO OPERATION ONLY".
(b) Forward Lower Cargo Compartment:
 MAXIMUM CAPACITY 13,000 LB.
 ALLOWABLE FLOOR LOADING 75 LB./SQ. FT.
(c) Aft Lower Cargo Compartment:
 MAXIMUM CAPACITY 13,160 LB.
 ALLOWABLE FLOOR LOADING 75 LB./SQ. FT.
(d) Main Fuselage Compartment:
Limits of Compartment Placard
Fwd.
(Station)
Aft
(Station) Compartment
Maximum
Capacity
(lb.)
Total Load
Forward of
Aft. Sta.
including
load in lower
cargo compart-
ment must not
exceed
Total Load
aft of Fwd.
Sta. including
load in lower
compartment
must not
exceed
Maximum
allowable
floor
loading
lb./sq.ft.
(Plywood floor
Panels)
159 223 A 800 800 - - - - 75
223 331 B 8360 8360 - - - - 200
331 421 C 8250 14660 - - - - 200
421 511 D 8250 20960 - - - - 200
511 601 E 8250 27260 - - - - 200
601 691 F 8250 33560 - - - - 200
691 781 G 8250 39955 - - - - 300
781 871 H 8250 48050 - - - - 300
871 963 I 8400 - - - - 36460 200
963 1053 K 8250 - - - - 30020 200
1053 1143 L 8250 - - - - 23720 200
1143 1233 M 8250 - - - - 17420 200
1233 1323 N 5900 - - - - 11120 200
1323 1413 O 5000 - - - - 6840 200
1419 1588 P 3000 - - - - 3000 150
(1) Compartment "A" is located in the lower hold and is restricted to a floor load of 150 lb./ft. run with
a maximum of 800 lb.
(2) The maximum allowable floor loadings shown for all compartments are limited by floor panel
strength.  With the exception of Compartments "A" and "P", the floor supporting structure for all
compartments is approved for a maximum allowable loading equivalent to 300 p.s.f.
NOTE 3. Special Fatigue or Retirement Considerations Applicable
(a) The basic airframe is life limited to 40,000 hours, or 13,500 landings, whichever occurs first, subject to
the special inspections of Canadair Service Information Circulars Nos. 176-CL-44D4 and 268-CL-44D4.
(b) When an airplane Model CL-44D4 is converted to a Model CL-44J, the life limit of the Model J must be
reduced by the service hours and landings accumulated on the model D4 at the time of conversion.
(c) Control rod end fittings, P/N 28-90031, of the elevator control system must be replaced at intervals of
10,000 hours in accordance with Service Bulletin No. CL-44D4-201.
(d) Airplane Models CL-44D4 and CL-44J whose serial numbers are listed in Canadair Service Information
Circular No. 380-CL44, are eligible for removal of the basic airframe life limitation, reference items (a)
and (b).  Eligibility is contingent upon compliance with the requirements of Canadair S.I.C. No. 380-
CL44, at or before the basic airframe life limitation of paragraph (a) is reached.

1A20 18
NOTE 4. Applicable to Model CL-44D4
(a) The fuselage above the floor is approved as a Class "E" Cargo compartment provided the transparent
material of window and exits, if installed, is shielded by fire- resistant covers, Canadair P/N 44D-41754.
Applicable to Model CL-44J, Cargo Variant
(b) The fuselage above the floor is approved as a Class "E" cargo compartment provided the aircraft is
modified in accordance with Canadair Modification Summary No. CL-44D4-688.
NOTE 5. The fuselage on each production aircraft must be pressurized to 1.33 times relief valve pressure.  (Fatigue
specimen was pressurized to 1.33 time relief valve pressure prior to fatigue tests).
NOTE 6. Deleted
NOTE 7. Applicable to Model CL-44D4
Only aircraft with Canadair Service Bulletin No. CL44-227 with Supplement No. 1 and Revision "A" and
"B" and CL44-451 with Revision "A" incorporated, may operate with zero fuel weight in excess of
155,000 lb.
NOTE 8. Applicable to Model CL-44D4
Only aircraft with Canadair Service Bulletin No. CL44-227 with Supplement No. 1 and Revisions "A" and
"B" incorporated, may operate at a maximum take-off weight of up to 210,000 lb. and a taxi weight of up to
211,000 lb.
NOTE 9. Applicable to Model CL-44J, Cargo Variant
Aircraft with modification defined by Canadair Modification Summary CL-44D-688 incorporated are
approved for the carriage of cargo only.
.....END.....
```

## ADs (42, in force first)

- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011
- [AD 97-25-12](https://openairdocs.org/ad/97-25-12): AFM - Limitations Section - Power Levers · Bombardier CL-44D4 and CL-44J. Effective Jan 13, 1998
- [AD 91-06-05](https://openairdocs.org/ad/91-06-05): Supplemental Inspection Program · Bombardier CL-44D4 and CL-44J. Effective Apr 8, 1991
- [AD 89-04-07](https://openairdocs.org/ad/89-04-07): Upper Wing Skin · Bombardier CL-44D4 and CL-44J. Effective Mar 7, 1989
- [AD 68-01-06 R1](https://openairdocs.org/ad/68-01-06-R1): Main Landing Gear Bogie Beam · Bombardier CL-44D4. Effective Sep 5, 1988
- [AD 86-16-10](https://openairdocs.org/ad/86-16-10): Lugs - Main Landing Gear · Bombardier CL-44D4 and CL-44J. Effective Sep 8, 1986
- [AD 83-24-06](https://openairdocs.org/ad/83-24-06): L&R Upper MLG Eye Attachment Pins · Bombardier CL-44D4 and CL-44J. Effective Dec 20, 1983
- [AD 83-10-05](https://openairdocs.org/ad/83-10-05): Horizontal Stabilizer Rear Attachment Fittings · Bombardier CL-44D4 and CL-44J. Effective Jun 6, 1983
- [AD 81-07-05](https://openairdocs.org/ad/81-07-05): Nose Landing Gear Crossbeam · Bombardier CL-44D4 and CL-44J. Effective Mar 31, 1981
- [AD 71-20-06](https://openairdocs.org/ad/71-20-06): Horizontal Stabilizer · Bombardier CL-44D4 and CL-44J. Effective Feb 21, 1980
- [AD 79-10-12](https://openairdocs.org/ad/79-10-12): Main Landing Gear Actuating System · Bombardier CL-44D4 and CL-44J. Effective May 18, 1979
- [AD 79-10-04](https://openairdocs.org/ad/79-10-04): Fireproofing · Bombardier CL-44D4 and CL-44J. Effective May 9, 1979
- [AD 78-23-05](https://openairdocs.org/ad/78-23-05): Spline Wear On Elevator Travel · Bombardier CL-44D4 and CL-44J. Effective Nov 10, 1978
- [AD 76-15-05](https://openairdocs.org/ad/76-15-05): Nose Landing Gear Bolts · Bombardier CL-44D4 and CL-44J. Effective Apr 17, 1978
- [AD 77-17-01](https://openairdocs.org/ad/77-17-01): Structural Integrity · Bombardier CL-44D4 and CL-44J. Effective Aug 18, 1977
- [AD 77-02-10](https://openairdocs.org/ad/77-02-10): Fuselage Bonding Strips · Bombardier CL-44D4 and CL-44J. Effective Feb 4, 1977
- [AD 75-24-08](https://openairdocs.org/ad/75-24-08): Landing Gear Attach Bolts · Bombardier CL-44D4 and CL-44J. Effective Nov 25, 1975
- [AD 75-08-01](https://openairdocs.org/ad/75-08-01): Nose Landing Gear · Bombardier CL-44D4 and CL-44J. Effective Apr 7, 1975
- [AD 74-05-02](https://openairdocs.org/ad/74-05-02): Main Landing Gear Uplock Cylinder · Bombardier CL-44D4 and CL-44J. Effective Feb 26, 1974
- [AD 74-04-05](https://openairdocs.org/ad/74-04-05): Main Landing Gear Uplock Fitting · Bombardier CL-44D4 and CL-44J. Effective Feb 20, 1974
- [AD 74-04-04](https://openairdocs.org/ad/74-04-04): Main Landing Gear Attach Fitting · Bombardier CL-44D4 and CL-44J. Effective Feb 18, 1974
- [AD 72-21-05](https://openairdocs.org/ad/72-21-05): Horizontal Stabilizer · Bombardier CL-44D4 and CL-44J. Effective Oct 17, 1972
- [AD 69-12-05](https://openairdocs.org/ad/69-12-05): Cracks In Access Cutouts · Bombardier CL-44D4 and CL-44J. Effective Jun 27, 1969
- [AD 68-26-03](https://openairdocs.org/ad/68-26-03): Stabilizer Rib Cracks · Bombardier CL-44D4. Effective Dec 19, 1968
- [AD 68-10-08](https://openairdocs.org/ad/68-10-08): Main Landing Gear Actuator Attach · Bombardier CL-44D4 and CL-44J. Effective May 21, 1968
- [AD 67-19-03](https://openairdocs.org/ad/67-19-03): Front Spar Web · Bombardier CL-44D4. Effective Jun 10, 1967
- [AD 66-27-04](https://openairdocs.org/ad/66-27-04): Main Landing Gear Keel Members · Bombardier CL-44D4. Effective Nov 12, 1966
- [AD 65-04-03](https://openairdocs.org/ad/65-04-03): Elevator Antiflutter Gear Box Strut · Bombardier CL-44D4. Effective Feb 4, 1965
- [AD 64-02-04](https://openairdocs.org/ad/64-02-04): Control System Couplings · Bombardier CL-44D4. Effective Jan 23, 1964
- [AD 64-01-03](https://openairdocs.org/ad/64-01-03): Lubrication Of Sealed Couplings · Bombardier CL-44D4. Effective Jan 4, 1964
- [AD 63-18-01](https://openairdocs.org/ad/63-18-01): Elevator Hinge Bolts · Bombardier CL-44D4. Effective Sep 22, 1963
- [AD 63-03-02](https://openairdocs.org/ad/63-03-02): Rudder Balance Weight · Bombardier CL-44D4. Effective Feb 6, 1963
- [AD 62-21-01](https://openairdocs.org/ad/62-21-01): Oil Temperature Indicating System · Bombardier CL-44D4. Effective Oct 29, 1962
- [AD 62-08-06](https://openairdocs.org/ad/62-08-06): Engine Breather Duct Overheat Detectors · Bombardier CL-44D4. Effective Apr 11, 1962
- [AD 61-26-02](https://openairdocs.org/ad/61-26-02): Tail Heater Inspection · Bombardier CL-44D4. Effective Dec 21, 1961
- [AD 61-23-02](https://openairdocs.org/ad/61-23-02): Elevator Tab Tension Rods · Bombardier CL-44D4. Effective Nov 3, 1961
- [AD 61-22-02](https://openairdocs.org/ad/61-22-02): Landing Gear Rotation Lever · Bombardier CL-44D4. Effective Nov 1, 1961
- [AD 61-22-03](https://openairdocs.org/ad/61-22-03): Elevator Hinge Fittings · Bombardier CL-44D4. Effective Nov 1, 1961
- [AD 61-21-01](https://openairdocs.org/ad/61-21-01): Tail Pipe Door · Bombardier CL-44D4. Effective Oct 17, 1961
- [AD 62-09-02](https://openairdocs.org/ad/62-09-02): Oil Line Magnetic Plug And Filter · Bombardier CL-44D4

## Registered aircraft by registry model (OpenAirDocs)

- [Canadair CL-44D4](https://openairdocs.org/model/canadair-cl-44d4): 0 aircraft (registry code 1900102)
- [Canadair CL-44J](https://openairdocs.org/model/canadair-cl-44j): 0 aircraft (registry code 1900104)

## STCs approved under this data sheet (36)

- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc.
- [STC SA1187WE](https://openairdocs.org/stc/SA1187WE): Either a Collins Radio Company or a United Data Control, Inc., cockpit voice recorder system.. Flying Tiger Line Inc
- [STC SA1236WE](https://openairdocs.org/stc/SA1236WE): Modification of elevators.. Flying Tiger Line Inc
- [STC SA1329WE](https://openairdocs.org/stc/SA1329WE): Collins 621A-3 air traffic control transponder system.. Flying Tiger Line Inc
- [STC SA1330WE](https://openairdocs.org/stc/SA1330WE): Class E cargo compartment reduced to accommodate crew rest area.. Flying Tiger Line Inc
- [STC SA1401WE](https://openairdocs.org/stc/SA1401WE): Structural modification of lower rudder.. Flying Tiger Line Inc
- [STC SA1639WE](https://openairdocs.org/stc/SA1639WE): Replacement of any of three original 40 KVA alternators with Westinghouse 40 KVA system consisting of alternator P/N 976J843-1 and regulator P/N 915F363-1.. Flying Tiger Line Inc
- [STC SA165WE](https://openairdocs.org/stc/SA165WE): 178 maximum passenger interior.. Flying Tiger Line Inc
- [STC SA1761WE](https://openairdocs.org/stc/SA1761WE): Replacement of any of three original 60 KVA alternators and voltage regulators with Westinghouse 60 KVA system.. Flying Tiger Line Inc
- [STC SA196EA](https://openairdocs.org/stc/SA196EA): Astek Mach airspeed warning switch.. Flying Tiger Line Inc
- [STC SA291WE](https://openairdocs.org/stc/SA291WE): Single Collins 860E-1 distance measuring equipment (DME) system.. Flying Tiger Line Inc
- [STC SA4-1556](https://openairdocs.org/stc/SA4-1556): Installation of United Control, Data Division, F542 Flight Recorder.. Flying Tiger Line Inc
- [STC SA4-1557](https://openairdocs.org/stc/SA4-1557): Passenger interior.. Flying Tiger Line Inc
- [STC SA457WE](https://openairdocs.org/stc/SA457WE): Passenger interior.. Flying Tiger Line Inc
- [STC SA489WE](https://openairdocs.org/stc/SA489WE): Dual Sperry C-12 compass system.. Flying Tiger Line Inc
- [STC SA518WE](https://openairdocs.org/stc/SA518WE): Dual Collins (DN-101) doppler radar and dual Collins (NC-103) navigational computer system with optional connection to Eclipse Pioneer PB-20H autopilot.. Flying Tiger Line Inc
- [STC SA535WE](https://openairdocs.org/stc/SA535WE): Passenger interior.. Flying Tiger Line Inc
- [STC SA569WE](https://openairdocs.org/stc/SA569WE): Modification for deletion of up restraint requirement in lower cargo compartments and the use of 5,000-lb. cargo fittings.. Flying Tiger Line Inc
- [STC SA576WE](https://openairdocs.org/stc/SA576WE): Extruded aluminum plank floor.. Flying Tiger Line Inc
- [STC SA577WE](https://openairdocs.org/stc/SA577WE): Aircraft Mechanics pilot and copilot seats.. Flying Tiger Line Inc
- [STC SA64EA](https://openairdocs.org/stc/SA64EA): Unfreight Mark IV cargo handling system.. American Machine & Foundry Co
- [STC SA721WE](https://openairdocs.org/stc/SA721WE): Modification of cockpit entrance door.. Flying Tiger Line Inc
- [STC SA777WE](https://openairdocs.org/stc/SA777WE): Custom Products models pilot and copilot seats.. Flying Tiger Line Inc
- [STC SA887WE](https://openairdocs.org/stc/SA887WE): 166-passenger interior.. Flying Tiger Line Inc
- [STC SA937WE](https://openairdocs.org/stc/SA937WE): Flap actuated gear warning system.. Flying Tiger Line Inc
- [STC SA378WE](https://openairdocs.org/stc/SA378WE): Installation of passenger interior.. Flying Tiger Line Inc
- [STC SA5656NM](https://openairdocs.org/stc/SA5656NM): Installation of burglar alarm system.. Thompson Harold S
- [STC SA1989SO](https://openairdocs.org/stc/SA1989SO): Installation of Canadair Marconi CMA-771 MK II Dual Omega Navigation System.. Blue Bell Inc
- [STC SA1105SO](https://openairdocs.org/stc/SA1105SO): Installation of Bendix ALA-51 radio altimeter and GPW-83 ground proximity warning system.. Blue Bell Inc
- [STC SA1086WE](https://openairdocs.org/stc/SA1086WE): Escape chutes relocated.. Slick Airways
- [STC SA215EA](https://openairdocs.org/stc/SA215EA): Airspeed aural warning system.. Seaboard World Airlines Inc
- [STC SA488EA](https://openairdocs.org/stc/SA488EA): Install Bendix brushless generators and regulators.. Seaboard World Airlines Inc
- [STC SA587EA](https://openairdocs.org/stc/SA587EA): Relocation of Fairchild Model5424-220 flight recorder.. Seaboard World Airlines Inc

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.