Microsoft Word - A9EA Rev 15.doc

DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

DHC-6-1

DHC-6-100

DHC-6-200

DHC-6-300

DHC-6-400

A9EA

Revision No.20

Viking Air Limited

(Twin Otter)

July 14, 2016

TYPE CERTIFICATE DATA SHEET NO. A9EA

This data sheet which is a part of type certificate No. A9EA prescribes conditions and limitations under which the product for

which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations.

Type Certificate Holder Viking Air Limited

1959 de Havilland Way

Sidney, British Columbia

Canada V8L 5V5

Type Certificate Holder Record Bombardier Inc.

Regional Aircraft

123 Garratt Boulevard

Downsview, Ontario, Canada M3K 1Y5

de Havilland, Inc.

123 Garratt Boulevard

Downsview, Ontario, Canada M3K 1Y5

I - Model DHC-6-1 (Prototype and four Pre-Production A/C) (Normal Category),

Approved June 22, 1966 by the FAA and April 7, 1966 by the Canadian Department of Transport (DOT)

Engines 2 United Aircraft of Canada, Limited PT6A-20

Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification

CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150

hours use in any one overhaul cycle.)

Oil Synthetic types conforming to CPWA 202, latest issue,

(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.)

Engine rating RATING E.S.H.P. S.H.P.

Take-off (5 min.) *579 *550

Max. continuous *579 *550

*Available to 70°F (21°C) Ambient Temperature

Engine limits Temperature Limits (Inter-Turbine) Take-

off 1380° F (750° C)

Max. Continuous 1380°F (750° C)

Starting (2 sec.) 1994°F (1090° C)

Torque Limits

Take-off 42.5 p.s.i. (1315 ft. lb.)

Max. Continuous 42.5 p.s.i. (1315 ft. lb.)

Gas Generator

Take-off 38,100 r.p.m. (101.5%)

Max. Continuous 38,100 r.p.m. (101.5%)

Oil Temperature

Starting -40°C Min.

Take-off 10°C to 99°C

Max. Continuous 10°C to 99°C

Page No.

Rev. No.

A9EA

Page 2

Oil Pressure

Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g.

Min. (below 28,000 r.p.m.) 40 p.s.i.g.

Propeller Hartzell

Hub HC-B3TN-3, -3B, -3BY

Blades T10173+1, T10173E+1

Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs)

Pitch Settings at 30" Station

Feather +87°

Take-off Low Pitch +17°

Idle Blade Angle +12°

Reverse Blade Angle - 9°

Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%)

Max. Continuous 2200 r.p.m. (100%)

Airspeed limits

Skiplane

(CAS)

Landplane

& Floatplane

M.P.H. Knots

(Never exceed) 232.7* 202* 210.8* 183*

(Max. structural cruising) 184.3** 160** 184.3** 160**

(Maneuvering) 149.8*** 130*** 149.8*** 130***

(Minimum control)

73.7 64 73.7 64

(Flaps extended) 115.2 100 115.2 100

0° to 20°

(Flaps extended)

97.9 85 97.9 85

20° to 40°

* Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft.

** Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft.

*** Reduce Vp - Vno above 20000 ft.

C.G. range (Landing Landplane and Skiplane

gear fixed)

Forward Limit 20% M.A.C. (STA. 203.84) at all weights up to max.

of 11000 lb.

Aft Limit 36% M.A.C. (STA. 216.32) at all weights up to max.

of 11000 lb.

Floatplane

Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max.

of 11000 lb.

Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max.

of 11000 lb.

Empty weight C.G. range None

Maximum weights Landplane

Take-off 11000 lb.

Landing 11000 lb.

Skiplane

Take-off 11000 lb. (with Item 201(a) and (b))

Landing 11000 lb. (with Item 201(a) and (b))

Floatplane

Take-off 11000 lb. (with Item 202(a))

Landing 11000 lb. (with Item 202(a))

Minimum Crew One (pilot). (+95.0 in.)

No. of seats 16 (including two at Stn. +95.0 in.) - Limited by approved seating

arrangement. (See Weight and Balance Handbook).

Max. 17 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements.

(Approval of seating arrangement is required).

Cargo loading conditions See Weight and Balance Handbook PSM 1-6-8

Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.)

500 lb. max. in rear compartment (arm +354.0 in.)

See Weight and Balance Handbook.

Page 3

A9EA

Fuel capacity *USABLE FUEL U.S. GALS. IMPERIAL GALS.

Forward Tank (+162.5 in.) 176 147

Rear Tank (+240.0 in.) 182 152

TOTAL 358 299

*See NOTE 1(b) for Weight and Balance.

Oil capacity *USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB.

Port (+177.0 in.)

1.5

1.2

Starboard (+177.0 in.)

1.5

1.2

TOTAL

3.0

2.4

* See NOTE 1(c) for Weight and Balance.

Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for

Altitude all occupants).

Control surface movements Aileron (with flaps up) Up 17.5° Down 16°

(with flaps in landing position) Up 25° Down 17.5°

Trim Tab - or + 15°

Geared Tab (flap up) Up 16° Down 17.5°

Flaps (inboard forward) 0° to 40°

(inboard trailing) 0° to 62.5°

(outboard forward) 0° to 26°

(outboard trailing) (aileron)

Elevator Up 25° Down 16°

Tab Up 20° Down 25°

Flap interconnect (flap up) Down 12°

(flap landing) Up 12°

Rudder Left 20° Right 21°

Geared Tab - or + 11°

Trim Tab - or + 25°

See Maintenance Manual PSM-1-6-2 for procedure to rig control

surface movements from stop to stop.

Serial Nos. eligible 1 to 5 inclusive. 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 or for the

Minister of Transport. 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. A-82, Issue 2, dated July 29, 1966.

(FAA Type Certificate No. A9EA)."

Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special

Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type

Certificate No. A9EA issued June 22, 1966. Not approved for use in operations under

FAR Part 135 after May 31, 1972, when FAR 135.144 becomes mandatory. (See NOTE

3). Date of application for Type Certificate April 2, 1964.

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations

(see Certification Basis) must be installed in the aircraft for certification and is given in

Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the

following item of equipment is required:

(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-61-1A.

A9EA

Page 4

II - Model DHC-6-100 (Normal Category), Approved August 1, 1966 by the FAA and July 29, 1966 by the

Canadian Department of Transport (DOT). (First Production Series)

Engines 2 United Aircraft of Canada, Limited PT6A-20

Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification

CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150

hours use in any one overhaul cycle.)

Oil Synthetic types conforming to CPWA 202, latest issue,

(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.)

Engine rating RATING E.S.H.P. S.H.P.

Take-off (5 min.) *579 *550

Max. continuous *579 *550

*Available to 70°F (21°C) Ambient Temperature

Engine limits Temperature Limits (Inter-Turbine)

Take-off 1380°F ( 750°C)

Max. Continuous 1380°F ( 750°C)

Starting (2 sec.) 1994°F (1090°C)

Torque Limits

Take-off

42.5 p.s.i.

(1315 ft.-lb.)

Max. Continuous

42.5 p.s.i.

(1315 ft.-lb.)

Gas Generator

Take-off

38,100 r.p.m.

(101.5%)

Max. Continuous

38,100 r.p.m.

(101.5%)

Oil Temperature

Starting -40°C Min.

Take-off 10°C to 99°C

Max. Continuous 10°C to 99°C

Oil Pressure

Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g.

Min. (below 28,000 r.p.m.) 40 p.s.i.g.

Propeller Hartzell

Hub HC-B3TN-3, -3B, -3BY

Blades T10173+1, T10173E+1

Diameter 8 ft. 6 in. nominal (8 ft. 4 in. minimum after repairs)

Pitch Settings at 30" Station

Feather +87°

Take-off Low Pitch +16°

Idle Blade Angle +12°

Reverse Blade Angle -14°

Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%)

Max. Continuous 2200 r.p.m. (100%)

Airspeed limits

Skiplane

(CAS)

Landplane

& Floatplane

M.P.H. Knots

(Never exceed) 232.7* 202* 210.8* 183*

(Max. structural cruising) 184.3** 160** 184.3** 160**

(Maneuvering) 149.8*** 130*** 149.8*** 130***

(Minimum control)

73.7 64 73.7 64

(Flaps extended) 115.2 100 115.2 100

0° to 20°

(Flaps extended)

97.9 85 97.9 85

20° to 40°

*Reduce Vne 4.6 mph (4K) per 1000 ft. above 10000 ft.

**Reduce Vno 3.5 mph (3K) per 1000 ft. above 10000 ft.

***Reduce Vp - Vno above 20000 ft.

Page 5

A9EA

GROSS WEIGHT - LB.

C.G. range (Landing Without Mod. 6/1020 - Same as Model 1

gear fixed) With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing"

LAN DP LAN E

11,579

11,400

11,000

10,000

Max Take-Off Weight

Max Landing WT Above -20°F

Max Landing WT Below -20°F

9,000

ARM

203.84

ARM

205.40

ARM

216.32

HORIZONTAL C.G. LIMIT - % MAC

SKIP LAN E

11,579

11,400

11,000

10,000

Max Take-Off Weight

Max Landing WT Above -20°F

Max Landing WT Below -20°F

9,000

ARM

203.84

22 23

ARM

206.18

ARM

216.32

FLOATPLANE

Forward Limit 25% M.A.C. (STA. 207.74) at all weights up to max.

of 11,600 lb.

Aft Limit 32% M.A.C. (STA. 213.20) at all weights up to max.

of 11,600 lb.

Empty weight C.G. range None

Maximum weights With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing"

Landplane (lb.) Skiplane (lb.) Floatplane (lb.)

(With Item 201(a)&(b)) (With Item 202(a)&(b))

Take-off 11579 11579 11600

Landing 11400* 11400* 11600

*See NOTE 5 - Temperature Limitations

Without Mod. 6/1020 - Same as Model 1.

Minimum Crew One (pilot). (+95.0 in.)

No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating

arrangement. (See Weight and Balance Handbook).

Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements.

(Approval of seating arrangement is required).

A9EA

Page 6

Cargo loading limitations See Weight and Balance Handbook PSM 1-6-8

Maximum baggage 200 lb. max. in forward compartment (arm +41.0 in.)

500 lb. max. in rear compartment (arm +354.0 in.)

See Weight and Balance Handbook.

Fuel capacity *USABLE FUEL U.S. GAL. IMPERIAL GAL.

Forward Tank (+162.5 in.) 181 151

Rear Tank (+240.0 in.) 197 164

TOTAL 378 315

*See NOTE 1(b) for Weight and Balance.

Oil capacity **USABLE OIL U.S. GAL. IMPERIAL GAL. WEIGHT LB.

Port (+177.0 in.)

1.5

11.2

Starboard (+177.0 in.)

1.5

1.2

TOTAL

3.0

2.4

** See NOTE 1(c) for Weight and Balance.

Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for

Altitude all occupants).

Control surface movements Aileron (with flaps up) Up 17.5° Down 16°

(with flaps in landing position) Up 25° Down 17.5°

Trim Tab - or + 15°

Geared Tab (flap up) Up 16° Down 17.5°

Flaps (inboard forward) 0° to 40°

(inboard trailing) 0° to 62.5°

(outboard forward) 0° to 26°

(outboard trailing) (aileron)

Elevator Up 25° Down 16°

Tab Up 20° Down 25°

Flap interconnect (flap up) Down 12°

(flap landing) Up 12°

Rudder Left 20° Right 21° *

Geared Tab - or + 11°

Trim Tab - or + 25°

See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface

movements from stop to stop.

*When Item 202(b) is incorporated then the rudder travel limits

are: Left 17° Right 21°.

Serial Nos. eligible 6 to 115 inclusive. 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

or for the Minister of Transport. 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. A-82, Issue 3, dated June 12, 1967. (FAA Type Certificate No. A9EA)."

Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special

Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type

Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate

April 2, 1964.

For this Model airplane intended for use in operations under FAR Part 135, the

additional airworthiness requirements of Special Federal Aviation Regulation (SFAR)

23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969,

are also included. See NOTES 3 and 8.

Page 7

A9EA

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations

(see Certification Basis) must be installed in the aircraft for certification and is given in

Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the

following item of equipment is required:

(a) Canadian D.O.T. approved Airplane Flight Manual, Part No.

PSM-1-61-1A.

III - Model DHC-6-200 (Normal Category), Approved April 1, 1968 by the FAA and March 29, 1968 by the

Canadian Department of Transport (DOT).

This Series may be identified by:

(1) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod. 6/1077 - Extended Nose that

Increases the Volume and Weight Capacity of the Forward Baggage Compartment; and,

(2) VAL (or BI) Mod. 6/1075 (Retrofit) or 6/1076 (New Production) -Increase in the Volume of the Rear

Baggage Compartment.

Engines 2 United Aircraft of Canada, Limited PT6A-20

Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification

CPW 46. (MIL-G-5572C Avgas (all grades) for emergency use only limited to 150

hours use in any one overhaul cycle.)

Oil Synthetic types conforming to CPWA 202, latest issue,

(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.)

Engine rating RATING E.S.H.P. S.H.P.

Take-off (5 min.) *579 *550

Max. continuous *579 *550

*Available to 70°F (21°C) Ambient Temperature

Engine limits Temperature Limits (Inter-Turbine)

Take-off 1380° F ( 750° C)

Max. Continuous 1380°F ( 750° C)

Starting (2 sec.) 1994°F (1090° C)

Torque Limits

Take-off 42.5 p.s.i. (1315 ft.-lb.)

Max. Continuous 42.5 p.s.i. (1315 ft.-lb.)

Gas Generator

Take-off 38,100 r.p.m. (101.5%)

Max. Continuous 38,100 r.p.m. (101.5%)

Oil Temperature

Starting -40°C Min.

Take-off 10°C to 99°C

Max. Continuous 10°C to 99°C

Oil Pressure

Normal (28,000 r.p.m. & above) 65 to 85 p.s.i.g.

Min. (below 28,000 r.p.m.) 40 p.s.i.g.

Propeller Hartzell

Hub HC-B3TN-3, -3B, -3BY

Blades T10173+1, T10173E+1

Diameter 8 ft. 6 in. nominal

(8 ft. 4 in. after repairs)

Pitch Settings at 30" Station

Feather +87°

Take-off Low Pitch +16°

Idle Blade Angle +12°

Reverse Blade Angle

-14°

A9EA

Page 8

GROSS WEIGHT - LB.

GROSS WEIGHT -

LB.

Propeller limits Propeller (Np) - Take-off 2200 r.p.m. (100%)

Max. Continuous 2200 r.p.m. (100%)

Landplane

Skiplane

Floatplane

Airspeed Limits (CAS)

Knots

M.P.H.

Knots

M.P.H.

Knots

M.P.H.

Vne (never exceed)

202*

232.7*

183*

211*

183*

211*

Vno (max. structural cruising)

160**

184.3**

160**

184.3**

160**

184.3**

Vp (design maneuvering)

130***

149.8***

130***

149.8***

130***

149.8***

Vmc (minimum control)

78.3

Vfe (flaps extended)

100

115.2

100

115.2

100

115.2

0° to 20°

Vfe (flaps extended) 85 97.9 85 97.9 85 97.9

20° to 40°

*Reduce Vne 4.6 m.p.h. (4K) per 1000 ft. above 10000 ft.

**Reduce Vno 3.5 m.p.h. (3K) per 1000 ft. above 10000 ft.

***Reduce Vp - Vno above 20000 ft.

C.G. range (Landing With Mod. 6/1020 - "Fuselage Beam, Front Wing Spar Reinforcing"

gear fixed) (All Model DHC-6-200 Aircraft Serial Nos. 116 to 230 inclusive have this

Mod. embodied).

11,579

11,400

11,000

10,000

9000

Max Take-Off

Weight

Max Landing WT Above

-20°F

ax Landing WT Below

-20°F

LAN

DPLAN

20 22 36

ARM

203.84

205.40

ARM

216.32

HORIZONTAL C.G. LIMIT - %

MAC

11,

579

11,

400

11,

000

10,

000

9000

Max Take-Off Weight

Max Landing WT Above -20°F

Max Landing WT Below -20°F

SKI PLANE

20 22 23

ARM

203.84

205.40

206.18

ARM

216.32

HORIZONTAL C.G. LIMIT - % MAC

Floatplane Forward Limit 25% M.A.C. (STA. 207.74) at all

weights up to max. of 11,600 lb.

Aft Limit 32% M.A.C. (STA. 213.20) at all

weights up to max. OF 11,600 lb.

Page 9

A9EA

Empty weight C.G. range None

Landplane (lb.) Skiplane (lb.) Floatplane (lb.)

(With Item 201(a)&(b)) (With Item 202(a)&(b))

Take-off 11579 11579 11600

Landing 11400* 11400* 11600

*See NOTE 5 - Temperature Limitations

Minimum Crew One (pilot). (+95.0 in.)

No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating

arrangement. (See Weight and Balance Handbook).

Max. 24 (including two at Stn. +95.0 in.) -Limited by emergency exit requirements.

(Approval of seating arrangement is required).

Cargo loading limitations See Weight and Balance Handbook (PSM 1-6-8)

Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max.

Forward - Long Nose

(Mod. 6/1077) ( +25.0 in.) 300 lb. Max.

Rear (+354.0 in.) 500 lb. Max.*

Rear Extension (+391.0 in.) 50 lb. Max.*

*Total Rear + Rear Extension not to exceed 500 lb. maximum.

Fuel capacity

*USABLE FUEL

U.S. GALS.

IMPERIAL GALS.

Forward Tank (+162.5 in.)

181

151

Rear Tank (+240.0 in.)

197

164

TOTAL

378

315

*See NOTE 1(b) for Weight and Balance.

Oil capacity **USABLE OIL U.S. GALS. IMPERIAL GALS. WEIGHT LB.

Port (+177.0 in.)

1.5

1.2

Starboard (+177.0 in.)

1.5

1.2

TOTAL

3.0

2.4

** See NOTE 1(c) for Weight and Balance.

Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for

Altitude all occupants).

Control surface movements Aileron (with flaps up) Up 17.5° Down 16°

(with flaps in landing position) Up 25° Down 17.5°

Trim Tab + or -15°

Geared Tab (flap up) Up 16° Down 17.5°

Flaps (inboard forward) 0° to 40°

(inboard trailing) 0° to 62.5°

(outboard forward) 0° to 26°

(outboard trailing) (aileron)

Elevator Up 25° Down 16°

Tab Up 20° Down 25°

Flap interconnect (flap up) Down 12°

(flap landing) Up 12°

Rudder Left 20° Right 21° *

(Skiplane) Left 18° Right 21°

Geared Tab + or -11°

Trim Tab + or -25°

See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface

movements from stop to stop.

* When Item 202(b) is incorporated then the rudder travel limits are:

Left 17° Right 21°.

A9EA

Page 10

Serial Nos. eligible 116 to 230 inclusive (except 130 and 210) plus any other Series aircraft that has been

modified to embody the following significant Model

Mod. 6/1020, 1075 or 1076, 1077.

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 or for the

Minister of Transport. 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. A-82, Issue 4, dated December 20,

1968 (FAA Type Certificate No. A9EA)."

Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special

Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964. Type

Certificate No. A9EA issued June 22, 1966. Date of application for Type Certificate

April 2, 1964.

For this Model airplane intended for use in operations under FAR Part 135, the

additional airworthiness requirements of Special Federal Aviation Regulation (SFAR)

23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969,

are also included. See NOTES 3 and 8.

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations

(see Certification Basis) must be installed in the aircraft for certification and is given in

Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the

following item of equipment is required:

(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-62-1A.

IV - Model DHC-6-300 (Normal Category), Approved May 8, 1969 by the FAA and April 25, 1969 by the

Canadian Department of Transport (DOT).

This is the third production series of the Type DHC-6. This series is identified

primarily on basis of:

(1) PT6A-27 engine in place of -20 engine;

(2) Increase in All-Up-Weight to the maximum allowed by CAR 3

of 12,500 lb.:

(3) Addition of two forward exits and deletion of roof exit; and,

(4) Aircraft nose configuration, See NOTE 6 for optional VAL (or BI) Mod.

6/1077 - Extended Nose that Increases the Volume and Weight

Capacity of the Forward Baggage Compartment.

Engines 2 United Aircraft of Canada, Limited PT6A-27

Fuel MIL-J-5624E, Grades JP-1, JP-4, JP-5, or Arctic Diesel Fuel to UACL Specification

CPW 46.

(MIL-G-5572C Avgas (all grades) for emergency use only - limited to 150 hours use in

any one overhaul cycle.)

Oil Synthetic types conforming to CPWA 202, latest issue.

(UACL PT6 Engine Service Bulletin No. 1 lists approved brand oils.)

Engine rating RATING E.S.H.P. S.H.P.

Take-off 652* 620*

Max. continuous 652* 620*

*Available to 91°F (33°C) Ambient Temperature (S.L.)

Page 11

A9EA

Knots

Landplane

M.P.H.

Knots

Floatplane

M.P.H.

Vmo (Max. Operating) S/L

160

184.3

160

184.3

5000 ft.

155

179

155

179

10000 ft.

150

173

150

173

15000 ft.

145

167

145

167

20000 ft.

130

149.8

130

149.8

25000 ft.

115

132.5

115

132.5

(Design maneuvering)

136*

156.7*

136*

156.7*

(Minimum control)

(Flaps extended)

0° to 10°

102

117.5

102

117.5

10° to 37-1/2°

109.5

Engine limits Temperature Limits (Inter-Turbine)

Take-off 1336°F ( 725° C)

Max. Continuous 1336°F ( 725° C)

Starting (2 sec.) 1994°F (1090° C)

Torque Limits

Take-off 50 p.s.i. (1536 ft.-lb.)

Max. Continuous 50 p.s.i. (1536 ft.-lb.)

Gas Generator

Take-off 38,100 r.p.m. (101.5%)

Max. Continuous 38,100 r.p.m. (101.5%)

Oil Temperature

Starting -40°C Minimum

Take-off 10°C to 99°C

Max. Continuous 10°C to 99°C

5 Minute Limit 104°C

Oil Pressure

Normal (28,000 r.p.m. & above) 80 to 100 p.s.i.g.

Min. (below 28,000 r.p.m.) 40 p.s.i.g.

Propeller Hartzell

Hub HC-B3TN-3D (Y)*

Blades T10282H (B)**+0

Diameter 8 ft. 6 in. nominal

(8 ft. 4 in. after repairs)

*(Y) designates Zero Thrust Latches

**(B) designates De-icing Boots.

Pitch Settings at 30" Station

Feather +87°

Take-off Low Pitch +17°

Idle Blade Angle +11°

Reverse Blade Angle -15°

Propeller limits Propeller (Np) - Take-off 2110 r.p.m. (96%)

Max. Continuous 2110 r.p.m. (96%)

Airspeed limits

(CAS)

*Reduce Vp to Vmo above 18000 ft.

A9EA

Page 12

ARM

203.84

ARM

207.74

ARM

216.32

*USABLE FUEL

U.S. GAL. IMPERIAL GAL.

Forward Tank

(+162.5 in.)

181

151

Rear Tank

(+240.0 in.)

197

164

GROSS WEIGHT - LB.

C.G. range (Landing gear fixed)

12, 500

12, 300

11, 600

11, 000

9, 000

Max Take-Off Weight

Max Landing Weight

LANDPLANE

AND

WHE E L-SKI PLANE

HORIZONTAL C.G. LIMITS - % MAC

Floatplane Forward Limit 25% M.A.C. (STA. 207.74) at all

weights up to max. of 12500 lb. Aft

Limit 32% M.A.C. (STA. 213.20) at all

weights up to max. of 12500 lb.

Empty weight C.G. range

Maximum weights

None

Landplane (lb.)

Floatplane (lb.)

Skiplane (lb.)

(With Item 201(a) or (b))

(With Item 202(a)

Take-off

12500

Landing

12300*

12500

12300*

* Main Wheel Tire Pressure

38 p.s.i.g.

(Below -20°F)

34 p.s.i.g.

Minimum Crew One pilot. (+95.0 in.)

No. of seats 22 (including two at Stn. +95.0 in.) - Limited by approved seating

arrangement. (See Weight and Balance Handbook).

Cargo loading limitations See Weight and Balance Handbook (PSM 1-63-8)

Maximum baggage Forward - Short Nose (+ 41.0 in.) 200 lb. Max.

Forward - Long Nose

(Mod. 6/1077) ( +25.0 in.) 300 lb. Max.

Rear (+354.0 in.)500 lb. Max.*

Rear Extension (+391.0 in.)150 lb. Max.*

* Total Rear + Rear Extension not to exceed 500 lb. maximum.

See Item 208(a) for approved baggage pod installation.

Fuel capacity

TOTAL 378 315

*See NOTE 1(b) for Weight and Balance.

Oil capacity *USABLE OIL U.S. GAL. IMPERIAL GAL. WEIGHT LB.

Port

(+177.0 in.)

1.5

1.2

Starboard

(+177.0 in.)

1.5

1.2

TOTAL

3.0

2.4

* See NOTE 1(c) for Weight and Balance.

Page 13

A9EA

Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for

Altitude all occupants).

Control surface movements Aileron (with flaps up) Up 17.5° Down 16°

(with flaps in landing position) Up 25° Down 17.5°

Trim Tab + or -15°

Geared Tab (flap up) Up 16° Down 17.5°

Flaps (inboard forward) 0° to 40°

(inboard trailing) 0° to 62.5°

(outboard forward) 0° to 26°

(outboard trailing) (aileron)

Elevator Up 25° Down 16°

Tab Up 20° Down 25°

Flap interconnect (flap up) Down 12°

(flap landing) Up 12°

Rudder Left 17° Right 21°

Geared Tab Left -5.5° Right +10°

Trim Tab + or -25°

See Maintenance Manual Part No. PSM-1-6-2 for procedure to rig control surface

movements from stop to stop.

Serial Nos. eligible 130, 210, 231 thru 844.

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 or for the

Minister of Transport. 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. A-82, Issue 5, dated September 10,

1969. (FAA Type Certificate No. A9EA)."

Certification basis CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special

Conditions for Multi-Engine Turbine Powered Aircraft dated

November 6, 1964.

Type Certificate No. A9EA issued June 22, 1966.

Date of Application for Type Certificate April 2, 1964.

For this Model airplane intended for use in operations under FAR Part 135, the

additional airworthiness requirements of Special Federal Aviation Regulation (SFAR)

23, dated January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969,

are also included. See NOTES 3 and 8.

For this Model airplane intended for operations in accordance with the performance

limitations of 14 CFR § 121.189 through 121.197, and Airplane Flight Manual

Supplement #37 – Supplemental Performance Data, document PSM 1-63-1A, the

following commuter category performance requirements of 14 CFR Part 23 are

included:

14 CFR §§ 23.45, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.65, 23.67, 23.75, 23.77,

23.1581, 23.1583, 23.1585, 23.1587 and 23.1589 up to and including Amendment 23-

57. See NOTES 3 and 9.

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations

(see Certification Basis) must be installed in the aircraft for certification and is given in

Viking Air Limited (or Bombardier) Report A.E.R.O.C. 6.6.G.1. In addition, the

following item of equipment is required:

(a) Canadian D.O.T. approved Airplane Flight Manual, PSM-1-63-1A.

V - Model DHC-6-400 (Normal Category), Approved June 11, 2012 by the FAA and June 24, 2010 by

Transport Canada Civil Aviation (TCCA).

This is the fourth production series of the Type DHC-6. This series is identified

primarily on the basis of:

(1) PT6A-34 engine in place of -27 engine;

(2) Fully integrated Electronic Flight Instrument System (EFIS) in place of

legacy instruments;

A9EA

Page 14

(3) Upgraded electrical system; and,

(4) Cabin safety compliance with later design standards, see “Certification basis”.

Engines 2 Pratt & Whitney Canada Inc. PT6A-34

Fuel For list of approved jet fuels refer to Pratt & Whitney Canada Inc. Service Bulletin No.

1244, latest issue.

(MIL-G-5572C Avgas (all grades) for emergency use only - limited to 150 hours use in

any one overhaul cycle.)

Oil For list of approved lubricating oils refer to Pratt & Whitney Canada Inc. Service

Bulletin No. 1001, latest issue.

Engine rating RATING E.S.H.P. S.H.P.

Take-off 652* 620*

Max. continuous 652* 620*

*Available to 108°F (42°C) Ambient Temperature (S.L.)

Engine limits Temperature Limits (Inter-Turbine)

Take-off 1454°F ( 790° C)

Max. Continuous 1454°F ( 790° C)

Starting (2 sec.) 1994°F (1090° C)

Torque Limits

Take-off 50 p.s.i. (1536 ft.-lb.)

Max. Continuous 50 p.s.i. (1536 ft.-lb.)

Gas Generator

Take-off 38,100 r.p.m. (101.5%)

Max. Continuous 38,100 r.p.m. (101.5%)

Oil Temperature

Starting -40ºF (-40°C) Minimum

Take-off 50ºF to 210.2ºF (10°C to 99°C)

Max. Continuous 50ºF to 210.2ºF (10°C to 99°C)

Oil Pressure

Normal (27,000 r.p.m. & above) 85 to 105 p.s.i.g.

Min. (below 27,000 r.p.m.) 40 p.s.i.g.

Propeller Hartzell

Hub HC-B3TN-3D (Y)*

Blades T10282H (B)**+0, T10282 (B)**+0

Diameter 8 ft. 6 in. nominal

(8 ft. 4 in. after repairs)

*(Y) designates Zero Thrust Latches

**(B) designates De-icing Boots.

Pitch Settings at 30" Station

Feather +87°

Take-off Low Pitch +17°

Idle Blade Angle +11°

Reverse Blade Angle -15°

Propeller limits Propeller (Np) - Take-off 2110 r.p.m. (96%)

Max. Continuous 2110 r.p.m. (96%)

Page 15

A9EA

ARM

203.84

ARM

207.74

ARM

216.32

*USABLE FUEL

U.S. GAL. IMPERIAL GAL.

Forward Tank

(+162.5 in.)

181

151

Rear Tank

(+240.0 in.)

197

164

TOTAL

378

315

GROSS WEIGHT - LB.

Airspeed limits

(CAS) Landplane

Knots

M.P.H.

Vmo (Max. Operating) S/L

170

196

6700 ft.

170

196

10000 ft.

160

184.3

15000 ft.

145

167

20000 ft.

130

149.8

25000 ft.

115

132.5

(Design maneuvering)

136*

156.7*

(Minimum control)

(Flaps extended)

0° to 10°

105

121.1

10° to 37°

109.5

*Reduce Vp to Vmo above 18000 ft.

C.G. range (Landing gear fixed)

12, 500

12, 300

11, 600

11, 000

9, 000

Max Take-Off Weight

Max Landing Weight

LANDPLANE

AND

WHE E L-SKI PLANE

HORIZONTAL C.G. LIMITS - % MAC

Empty weight C.G. range None

Maximum weights

Landplane (lb.)

(With Item 201(a) or (b))

Skiplane (lb.)

Take-off

Landing

12500

12300*

12500

12300*

* Main Wheel Tire Pressure

38 p.s.i.g.

(Below -20°F) 34 p.s.i.g.

Minimum Crew One pilot. (+95.0 in.)

No. of seats 21 (including two at Stn. +95.0 in.) - Limited by approved seating

arrangement. (See Weight and Balance Handbook).

Cargo loading limitations See Weight and Balance Handbook (PSM 1-64-8)

Maximum baggage Forward - Long Nose

(Mod. 6/1077) ( +25.0 in.) 300 lb. Max.

Rear (+354.0 in.)500 lb. Max.*

Rear Extension (+391.0 in.)150 lb. Max.*

* Total Rear + Rear Extension not to exceed 500 lb. maximum.

Fuel capacity

*See NOTE 1(b) for Weight and Balance.

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Page 16

Oil capacity *USABLE OIL U.S. GAL. IMPERIAL GAL. WEIGHT LB.

Port

(+177.0 in.)

1.5

1.2

Starboard

(+177.0 in.)

1.5

1.2

TOTAL

3.0

2.4

* See NOTE 1(c) for Weight and Balance.

Maximum Operating 25000 ft. (when supplementary breathing equipment is provided for

Altitude all occupants).

Control surface movements Aileron (with flaps up) Up 17.5° Down 16°

(with flaps in landing position) Up 25° Down 17.5°

Trim Tab + or -15°

Geared Tab (flap up) Up 16° Down 17.5°

Flaps (inboard forward) 0° to 40°

(inboard trailing) 0° to 62.5°

(outboard forward) 0° to 26°

(outboard trailing) (aileron)

Elevator Up 25° Down 16°

Tab Up 20° Down 25°

Flap interconnect (flap up) Down 12°

(flap landing) Up 12°

Rudder Left 17° Right 21°

Geared Tab Left -5.5° Right +10°

Trim Tab + or -25°

See Maintenance Manual Part No. PSM-1-64-2 for procedure to rig control surface

movements from stop to stop.

Serial Nos. eligible 845 and subsequent.

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 or for the

Minister of Transport. This form must contain the following statement: "The aircraft

covered by this certificate has been examined and found to comply with the type design

approved under U.S. Type Certificate No. A9EA and to be in a condition for safe

operation.”

Certification basis

A - Basic Aircraft Model:

• CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-8 inclusive, plus Special

Conditions for Multi-Engine Turbine Powered Aircraft dated November 6, 1964.

• For this Model airplane intended for use in operations under FAR Part 135, the additional

airworthiness requirements of Special Federal Aviation Regulation (SFAR) 23, dated

January 7, 1969, and Amendment 1 to SFAR 23, dated December 24, 1969, are also

included. See NOTES 3 and 8.

• 14 CFR §§23.783 (a), (b), (c)(1), (c)(3) and (c)(4), 23.785 (a), (b), (c), (f), (g)(2), (h), (i),

(j), (k) and (l), 23.787(a), (b), (c), (d), and (f) and (g), 23.803, 23.807 (a), (b), (c) and (d),

23.815 and 23.851 (a) and (b) as amended by Amdt. 23-34;

• 14 CFR §§23.853 (a), (c), (d)(3)(i) and (ii) and 23.1359(c) as amended by Amdt. 23-49.

B - For those areas of the Basic Aircraft Model affected by the installation of the EFIS Avionics Suite. The

Certification Basis will add the following 14 CFR Part 23 (Normal Category) requirements at Amdt. 23-

57, which is the latest amendment in effect on the date of application for the DHC-6-400, to those listed

above:

• Subpart D: §§23.771 – Amdt. 23-14; 23.773 – Amdt. 23-45; 23.777 and 23.779 –

Amdt. 23-51; 23.781 – Amdt. 23-33; 23.867 – Amdt. 23-49;

• Subpart E: §§23.901 – Amdt. 23-53 ; 23.963 – Amdt. 23-51;

• Subpart F: §§23.1367 and 23.1381 – Amdt. 23-0; 23.1301, 23.1327 and 23.1335 –

Amdt. 23-20; 23.1457 and 23.1459 – Amdt. 23-35; 23.1322, 23.1331 and 23.1357–

Amdt. 23-43; 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1326, 23.1329,

23.1351, 23.1353, 23.1359, 23.1361, 23.1365 and 23.1431 – Amdt. 23-49; 23.1325 –

Amdt. 23-50; 23.1337 – Amdt. 23-51; 23.1305 – Amdt. 23-52; 23.1308 – Amdt. 23-57;

Page 17

A9EA

• Subpart G: §§23.1551 – Amdt. 23-0; 23.1547 – Amdt. 23-20; 23.1501 and 23.1541 –

Amdt. 23-21; 23.1529 – Amdt. 23-26; 23.1549 and 23.1557 – Amdt. 23-45; 23.1543,

23.1545, 23.1553, 23.1555, 23.1559, 23.1581, 23.1583, 23.1585, 23.1587, and 23.1589 –

Amdt. 23-50.

C - Equivalent Level of Safety (ELOS) findings:

1) Circuit Protection - 14 CFR § 23.1357(b)

2) LED Lights -14 CFR § 23.1397(c)

3) Airspeed Indicator Flap Markings - 14 CFR§ 23.1545(b)(4)

4) Engine Instrument Display - 14 CFR § 23.1549(b) & (c)

D - Exemptions:

Exemption No. 10465 with time-limited conditions granted on March 1, 2012 for engine

display colors depicting normal operating conditions, 14 CFR § 23.1549(b). This exemption

terminates on July 31, 2013, unless sooner superseded or rescinded.

Exemption No. 11059, superseding Exemption No. 10465 with time-limited conditions

granted on September 19, 2014 for engine display colors depicting normal operating

conditions, 14 CFR § 23.1549(b). This exemption terminates on July 31, 2015, unless sooner

superseded or rescinded.

E - Noise Standards:

Compliance is required for 14 CFR Part 36 at the amendment levels in effect at the date of

application for the amended TC.

F - Fuel Venting and Exhaust Emissions Standards:

Compliance is required for 14 CFR Part 34-1 thru the most current amendments in effect on

the date that the amended TC is granted.

G - Additional Requirements:

For this Model airplane intended for operations in accordance with the performance

limitations of 14 CFR § 121.189 through 121.197, and Airplane Flight Manual Supplement

#37 – Supplemental Performance Data, document PSM 1-64-1A, the following commuter

category performance requirements of 14 CFR Part 23 are included:

14 CFR §§ 23.45, 23.51, 23.53, 23.55, 23.57, 23.59, 23.61, 23.65, 23.67, 23.75, 23.77,

23.1581, 23.1583, 23.1585, 23.1587 and 23.1589 up to and including Amendment 23-57.

See NOTES 3, 10 and 11.

Type Certificate No. A9EA amended June 11, 2012.

Date of Application for amendment to Type Certificate August 12, 2008.

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification

Basis) must be installed in the aircraft for certification and is given in Viking Air Limited Report A.E.R.O.C.

6.6.G.1. In addition, the following item of equipment is required:

(a) Transport Canada approved Airplane Flight Manual, PSM-1-64-1A.

Data Pertinent to All Models

Datum Station 0 is 109.32 inches forward of a jig point which is marked by a plate attached to

the bulkhead between the cockpit and the cabin.

M.A.C. 78 inches. (The L.E. is at Station 188.24).

Leveling means The cabin floor rails provide a surface for levelling the airplane both laterally and

longitudinally. The cabin floor level is 15 inches below water line zero.

Equipment The list of approved equipment, including the basic required equipment as prescribed in

the applicable airworthiness regulations (see Certification Basis) which must be

installed in the aircraft for certification, is given in Viking Air Limited (or Bombardier)

Report A.E.R.O.C. 6.6.G.1.

Approved Installations Item 201 - Ski Installations

(a) Wheel/Ski

Model 3000 nose-wheel/ski and Model 5500 main-wheel/ski

installed to VAL (or BI) Drawing C6-US-1000, G.A. Ski Installation. Applicable

to Model DHC-6-1, -100, -200, -300, and -400 Aircraft. Aircraft to be operated

A9EA

Page 18

in accordance with appropriate DOT Approved VAL (or BI) Flight Manual

Supplement.

(b) Spring Skis

Skis installed to VAL (or BI) Installation Drawing C6-US-1001. Applicable to

Model DHC-6-1 and -100 Aircraft.

Item 202 - Float Installations

(a) CAP Model 12000 Floats on Models 1, 100 and 200 Aircraft, up to 11600 lb., or

CAP Model 12000A and 12000B Floats on Model 300 Aircraft up to 12500 lb.

installed to VAL (or BI) Drawing C6-UF-1000 G.A. Floatplane. Ref. DOT Float

Type Approval F-10.

(b) CAP Models 12000, 12000A or 12000B Floats modified in accordance with

Field Aviation Company Limited Drawing No. 84193 to provide capability of

loading and dropping water. Water Bomber aircraft are to be operated in

accordance with DOT Approved Flight Manual Amendment contained in Field

Aviation Company Report No. 6035. Water Bomber equipment is to be

maintained in accordance with Field Aviation Company Report No. 4889. The

operation of water bomber aircraft is within the following limitations:

(i) Model 100 and 200 Aircraft:

CAP 12000 Floats

Aircraft Gross Weight 11600 lb. at C.G. Limits of 25% to 32% MAC with DH

Mod. 6/1020 embodied.

Maximum Water Capacity in Two Floats 425 Imperial Gal. Total.

Maximum Fuselage Cargo 500 lb.

Rudder travel Limits are: Left 17°, Right 21°.

(ii) Model 300 Aircraft:

CAP 12000A or 12000B Floats

Aircraft Gross Weight 12500 lb. at C.G. Limits of 25% to 32% MAC.

Maximum Water Capacity in Two Floats 450 Imperial Gal. Total.

Maximum Fuselage Cargo 500 lb.

Rudder travel Limits are: Left 17°, Right 21°.

Item 203 - Intermediate Flotation Gear

(a) VAL (or BI) Intermediate Flotation Gear Installed to VAL (or BI) Drawing C6-

U-1000. Applicable to Models DHC-6-1, -100, -200, -300 and -400 Aircraft.

Aircraft to be operated in accordance with appropriate DOT Approved VAL (or

BI) Flight Manual Supplement.

Item 204 - Aircraft Ice Protection

(a) Models DHC-6-1, -100, -200, and -300 aircraft approved for operation in icing

when equipped with following VAL (or BI) Modifications:

6/1043, 6/1066, 6/1089, S.O.O. 6004, S.O.O. 6005, S.O.O. 6006, S.O.O. 6009

and either S.O.O. 6007 or 6008.

Aircraft to be operated in accordance with appropriate DOT Approved VAL (or

BI) Flight Manual Supplement.

(b) Model DHC-6-400 aircraft approved for operation in icing when equipped with

following VAL Modifications:

6/2042, 6/2045, S.O.O. 6168 and either S.O.O. 6202 or 6237.

Aircraft to be operated in accordance with appropriate TCCA Approved VAL

Flight Manual Supplement.

Item 205 – Auto-pilot Installation

(a) Bendix M-4C Automatic Flight Control System installed to Field Aviation Co.

Ltd. Drawing J-500 061 per STA. SA67-7 for Model DHC-6-100. Aircraft to be

operated in accordance with the April 22, 1968 issue of the M-4C Supplement to

the DHC-6 Flight Manual.

Item 206 - Interior Installation

(a) Commuter interior installation installed to Field Aviation Co., Ltd. Report 4961

dated September 25, 1968.

Item 207 - Avionics Installation

(a) Avionics equipment installed to Field Aviation Co., Ltd. Report 4962 dated

September 26, 1968.

(b) Avionics equipment installed in accordance with Technical Enterprise Limited

Report TELAIR DHC-6.

Page 19

A9EA

Item 208 - Baggage Pod Installation

(a) For Model DHC-6-300, baggage pod installation when installed and

operated in accordance with Field Aviation Co., Ltd. Report No.

6093 dated 29 March 1971.

NOTES

NOTE 1. (a) The current Weight and Balance Handbook, Part Number PSM-1-6-8, for the Models DHC-6-1, DHC-6-

100, and DHC-6-200, PSM-1-63-8 for the Model DHC-6-300, and PSM 1-64-8 for the Model DHC-6-

400, giving the list of equipment included in the empty weight and loading instructions, must be in each

aircraft except in the case of operators having an approved weight control system.

(b) The following amount of unusable fuel is included in the empty weight:

MODEL 1 ALL OTHER MODELS

U.S. GAL. IMPERIAL GAL. U.S. GAL. IMPERIAL GAL.

Unusable 7.25 6.0 3.5 3.0

and equals 54 lb. at +177 in.

NOTE 2. The following placards must be displayed in clear view of the pilot at all times:

(a) "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN

COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS,

MARKINGS AND MANUALS."

(b) "NO ACROBATIC MANEUVERS (INCLUDING SPINS) ARE APPROVED."

(d) (1) All models except Series 400: "IFR" when the aircraft is equipped in accordance with the

requirements for the operation intended, and either -

(i) Vacuum system warning light installed to VAL Mod. 6/1014 to alert pilots of low vacuum

pressure to flight instruments, or

(ii) Pressure Instrument System, VAL Mod. 6/1046, is installed, or

(iii) Electrical Directional Gyro and Altitude Indicators in list of approved

equipment as defined in Viking Air Limited Report A.E.R.O.C. 6.6.G.1. are

installed.

(2) Series 400 (all aircraft): “IFR”

(e) "THIS AIRPLANE IS EQUIPPED FOR OPERATION IN ICING CONDITIONS" when the aircraft is

equipped with Item 204.

NOTE 3. For Models DHC-6-1, -100, -200, –300, and -400 airplanes, the Structural Components Service Life Limits

recorded in the Viking Air Limited (or Bombardier) Manual PSM 1-6-11 and approved by Transport Canada

Civil Aviation, must be complied with.

For Model DHC-6-400 airplanes, the Avionics Airwothiness Limitations recorded in Viking Air Limited Manual

PSM 1-6-13 and approved by Transport Canada Civil Aviation, must be complied with.

NOTE 4. Engine fire extinguisher system for models DHC-6-1, -100, -200, -300,and -400 Series must be installed in

accordance with Viking Air Limited drawing C6SW1100 or other Transport Canada Civil Aviation approved

data.

NOTE 5. The landing weight is 11400 lb. if the airport temperature at which the landing is to be made is at or above -20°F

(-29°C). If the airport temperature is below -20°F, then the landing weight is restricted to 11000 lb.

NOTE 6. The Model DHC-6-200 or -300 aircraft may have either the long nose (VAL (or BI) Mod. 6/1077) or the original

short nose (as per the Model DHC-6-100 aircraft) in any configuration with the exception of the floatplane

version which must have a short nose.

NOTE 7. Maximum continuous single generator load is limited to:

(a) 200 amps (1.0 on loadmeter) in Flight conditions up to 125°F.

(b) 200 amps (1.0 on loadmeter) in Ground conditions up to 45°F.

NOTE 8. For Models DHC-6-100, -200 and -300 airplanes intended for use in operations under

FAR Part 135, one of the following must be accomplished:

(a) Modifications recorded in Viking Air Limited (or Bombardier) Report AEROC 6.1.G.11-DHC-6

Certified Airplanes - Basic Definitions. The appropriate DOT approved VAL (or BI) Flight

Manual Supplement is to be inserted in the Airplane Flight Manual.

A9EA

Page 20

(b) Equivalent modifications to (a) above in compliance with SFAR 23 as approved by

the Regional Chief of an Engineering and Manufacturing Branch (Aircraft

Engineering Division in Western Region) FAA.

For Model DHC-6 Series 400 airplanes:

All aircraft delivered are compliant with SFAR 23 and Amendment 23-1 as delivered.

NOTE 9. For Model DHC-6-300 airplanes intended for operations in accordance with the performance limitations of 14

CFR § 121.189 through 121.197, the Airplane Flight Manual Supplement #37 – Supplemental Performance

Data, is to be inserted in the Airplane Flight Manual, document PSM 1-63-1A.

NOTE 10. For Model DHC-6-400 airplanes intended for operations in accordance with the performance limitations of 14

CFR § 121.189 through 121.197, the Airplane Flight Manual Supplement #37 – Supplemental Performance

Data, is to be inserted in the Airplane Flight Manual, document PSM 1-64-1A.

NOTE 11. For Model DHC-6-400 airplanes:

(a) The electrical system upgrade consists of removing the AC system; replacing the starter-generator and the

DC system wiring, connectors, lights (strobe, navigation, nose wheel position indicator, and interior) and

door proximity switches, and installing an increased capacity battery, 12V DC outlets in the cockpit and

an optional pulsing landing light system.

(b) The cockpit upgrade consists of replacing the conventional primary flight instruments, engine instruments

and crew alerting system with an integrated Honeywell Primus Apex® EFIS avionics suite; the installation

of / provisions for comm/nav equipment, radar altimeter, CVR, FDR, weather radar and cabin public

address system; and related changes to the electrical system, circuit breakers and switches.

....END....