CRUISE POWER CHART

CRUISE POWER CHART V

A.U.W. Г BASIC WT LESS ONE PILOT PAY-

WEIGHTS FUEL LOAD

FOR LOIL

I! 11 i I! 111¹111!! и 1¹! 11111! 111 s: lii;!lijiili:i!|nli PRESS. ALTITUDE: 5,000 FT;t

i[||ll!llllllli!i"lHTi^lijlHiHiTnni!;l:i]i[i!'il

FUEL REQUIRED

Ji 300 I I 400 <1 \ 500 CRUISING RANGE (STAT. MILES)

FUEL ALLOWANCE

10 MIN. WARM-UP Ac TAKE-OFF CLIMB TO 5,000 FT. FUEL FOR 45 MIN. FLIGHT AT CRUISE POWER IN RESERVE.

CRUISING SPEED (TAS): 1 14 MPH

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VI

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FUEL REQUIRED

CRUISING RANGE (STAT. MILES)

FLOOR STRENGTH___________

For uniformly distributed load

100 lb/sq.ft. For concentrated load (penetration strength)

200 lb/sq.ft.

NOTE

SAFE MOMENT LIMITS - AFT Land and Ski Plane COLUMN A Applies to aircraft in which the rigging recommendations outlined in Engineering Bulletin Ser­ies В No. 1 have not been incorpora­ted.

COLUMN В Applies to aircraft in which the rigging recommendations outlined in Engineering Bulletin Ser­ies В No. 1 have been incorporated.

BASIC WEIGHT OF AIRCRAFT. . . . LB* BASIC MOMENT *

PILOT/PASSENGER STD . WEIGHT 170 LB.

(Insert actual weight and basic ;noincnt given in weight and balance report found in envelope on inside of rear cover)

- 100

ADD TO BASIC WEIGHT AND TO BASIC MOMENT

A. PILOT(S) AND PASSENGER(S)

B. FREIGHT AND BAGGAGE

C. FUEL AND OIL

OIL TANK

CAP. 5.2 ARM

IMP. GAL. +37 .u IX .

GAL. L1»

+ 666 + 1332 + 1732

A. TAKE OFF WEIGHT IS NOT OYER 5, 100 Lb .

B. TOTAL MOMENT VALUE IS WITHIN SAFF. MOMENT LIMITS.

C. AVAILABLE TAKE OFF DISTANCE PERMITS TAKE-OFF AT THIS WF.IGiiT.

CAP. IMP.GAL. GAL. LB.

~3o

{J. 108 144

ISO 2CW

CENTRE

CAP. 29 IMP. GAL.

'JS G

VIII OPERATIONAL LOADS DIAGRAM

Supplement No 1 FLIGHT MANUAL

AIRCRAFT

Agricultural Installations

15 April 1959

SUPPLEMENT 1

AGRICULTURAL INSTALLATIONS

TABLE OF CONTENTS

PARAGRAPH No. TITLE PAGE

1 GENERAL Sl-1

2 AGRICULTURAL MODEL Sl-1

2.1 FEEDER AND SEEDER INSTALLATION Sl-1

2.2 SPRAYER INSTALLATION Sl-1

2.3 ALTERNATIVE SPRAYER INSTALLATION Sl-1

2.4 SUPPLY DROPPING INSTALLATION S1 -4

3 SPRAYER MODEL Sl-5 3.1 SPRAYER INSTALLATION Sl-5

4 OPERATION Sl-5

4.1 OPERATING LIMITS Sl-7

4.2 WEIGHT AND MOMENT TABLE Sl-7

4.3 OPERATIONAL TABLES Sl-9

LIST OF ILLUSTRATIONS

FIGURE TITLE PAGE

Sl-1 FEEDER AND SEEDER INSTALLATION SI-2

S1 -2 AGRICULTURAL MODEL SPRAYER

INSTALLATION Sl-3

Sl-3 ALTERNATIVE SPRAYER INSTALLATION SI-4

S1 -4 SUPPLY DROPPING INSTALLATION Sl-5

Sl-5 SPRAYER MODEL INSTALLATION Sl-6

AGRICULTURAL INSTALLATIONS

1. GENERAL

The de Havilland agricultural in­stallations are fitted to two types of Beaver aircraft, one being a special version of the Beaver Landplane known as the Agricultural model and the other a Standard Beaver Land- plane, seaplane or amphibian known as the Sprayer model.

2. AGRICULTURAL MODEL

The equipment fitted to the agri­cultural model comprises a feeder and seeder installation for fertilizer and seeder applica­tion, a sprayer installation for crop spraying, and wing mounted external racks for supply dropping. Removable seats are provided for a loading crew of three, to be used when ferry­ing from base to dropping zone. Conversion to any of these roles can be accomplished readily.

NOTE

Range and endurance are reduced by ap­proximately 33% of those stated in para. 4.10.1 of the Flight Manual, since the agricultural model is not fitted with a centre fuel tank.

2.1 Feeder and Seeder Installation

(See Figure Sl-1) This installation consists of a 35 cubic foot capacity hopper which protrudes through the cabin floor and fuselage skin to an unloading chute operated by a lever at the right side of the pilot's seat. A roof hatch facilitates loading of the hopper. An emergency release catch, located aft of the chute and operated by a push button on the left grip of the pilot's con­trol wheel, enables the entire hopper load to be jettisoned in a few seconds.

2.2 Sprayer Installation

(See Figure SI-2} The sprayer installation consists of the hopper, with a rubber bag inserted to con­tain the fluid, and a sump in place of the chute used on the feeder and seeder installation. The liquid capacity of the hopper is 220 Imperial (265 U.S.) gallons, the liquid contents being released by means of a spray control lever located immediately to the left of the engine controls quadrant. Adjacent to the control lever is an adjustable stop, which can be locked at a pre-determined position with a pip-pin, en­abling movement of the control lever to be limited according to the desired amount of fluid flow.

The fluid contents are jettisonable in an emergency by depression of a push button on the left grip of the pilot's control wheel which allows a jettison door to open on the sump. A wind-driven centrifugal pump and valve system, mounted on the centre line of the aircraft forward of the sump, feeds fluid under pressure to a span length spray boom extending laterally from the pump. The boom sections, attached to the wings by vee struts and to the fuselage by brackets, can be equipped with tee jet or whirl jet type nozzles as re­quired by the operator. To prevent over-spray­ing or loss of fluid, the boom incorporates diaphragm check valves which close when the fluid pressure drops below 7 psi. A pressure gauge is connected to the boom to provide the pilot with visual indication of the fluid pres­sure being supplied to the boom and spray nozzles when the system is in operation. An idling circuit is incorporated in the valve sys­tem so that an excessive fluid pressure will not be imposed in the boom or spray nozzles. For ferrying flights, the boom sections can be stowed under the rear fuselage.

2.3 Alternative Sprayer Installation

(See Figure Sl-3)

An alternative sprayer installation to the span length boom utilizes two ICD rotor units, giving a swath width and concentration less than the boom installation. The gravity fed rotor unite are fitted to the ends of the spray booms which are braced to the airframe and extend late rally from the sump, terminating outboard of the propeller arc. Each ICD rotor unit consists of a wind-driven fan at the for­ward end of a rotor shaft, with a wire brush at the aft end which disperses the fluid from the rotor unit in droplets, at a controllable rate of 1 to 50 gallons per minute, into the airstream. The rate of dispersal of the fluid is dependent on the selected position of the spray control lever in the cockpit, the size of the wire brushes, rotor unit valve opening and the pitch and diameter of the fans which determine the rotational speed of the rotors.

UNLOADING CHUTE

OPERATING LEVER

PUSH ROD

EMERGENCY

RELEASE

CATCH

UNLOADING CHUTE IN JETTISON POSITION

DETAIL A

FIG Sl-1 FEEDER AND SEEDER INSTALLATION

FIG SI-2 AGRICULTURAL MODEL SPRAYER INSTALLATION

FIG Sl-3 ALTERNATIVE SPRAYER INSTALLATION

2. 4 Supply Dropping Installation

(See Figure SI-4}

NOTE

It is essential to check with the airwor­thiness authority of the State in which the aircraft is operating to ensure that it is permissible to carry or drop stores, us­ing external racks, within the area of their jurisdiction.

The supply dropping installation con­sists of up to six Mark III external racks,cap­able of carrying 300 lb each, mounted three each side of the wing under surface and out­board of the wing attachment struts. Alterna­tively, an installation consisting of four light­weight wing racks with a carrying capacity of 250 lb each, and a fuselage ventral rack with a carrying capacity of 1800 lb may be fitted, provided the total weight of the supplies to be dropped doe8 not exceed 1800 lb. Installation of the fuselage rack necessitates removal of the hopper jettison assembly. The fuselage rack may also be fitted in conjunction with the Mark III wing racks provided the total weight of the supplies to be dropped does not exceed 1800 lb. An electrical switch panel in the cabin roof permits selection of any or all of the stores to be dropped. The release of the se­lected stores is accomplished by depression of the push button on the left grip of the pilot's control wheel, provided that the RACK MASTER switch on the electrical switch panel is ON. In the event of an electrical failure, or in an emergency, the wing stores can be jettisoned by pulling the two jettison handles, one above each cockpit door.

CAUTION

To maintain the lateral trim of the air­craft, the wing stores should be released in handed pairs, never from one side only. Release of all the wing stores at the same time should be restricted to emergency jettisoning.

NOTE

The dimensions of the stores on each wing rack should not exceed 1 ft. dia­meter nor be longer than 5 ft. 6 inches. The dimensions of the stores on the fuse­lage rack should not exceed 1 ft. dia­meter or 7 ft. in length.

3 SPRAYER MODEL

The equipment fitted to the sprayer model (Standard Beaver landplane, seaplane, or amphibian) consists of a sprayer installation and, if equipped with C2-W-587A and 588A type wings, can be used for supply dropping. Removal of the sprayer equipment and replace­ment of the cabin doors permits conversion to Standard Beaver duties.

¹ 1 Sprayer Installation

(See Figure SI-5) The sprayer installation consists of a 200 Imperial (240 U.S.) gallon cylindrical tank mounted athwartships in the cabin from doorway to doorway, necessitating removal of the doors and the fitting of special panels which serve to support the tank and close off the door­ways.

A filler neck is on each side of the tank which is connected to forward facing air pressure intakes on top of the fuselage. A pipe at the bottom of the tank allows the contents to pass to a centrifugal wind-driven pressure pump and valve system under the fuselage from which a span length boom originates. The boom sections are similar to those used in the Agricultural model and have similar fittings and furnishings. The liquid contents of the tank are released and controlled by selection of a control valve between the pilot's and co-pilot's seats. The tank can be emptied in an emergency by pulling the jettison handle adjacent to the flight instrument panel, which opens the tank dump valves. A gauge in the forward face of the tank indicates the quantity of fluid in the tank. For ferrying flights the boom sections can be stowed under the rear fuselage.

4. OPERATION

Complete the checks detailed in Sec­tion II of the Flight Manual, and before any flight ensure that all equipment is properly secured.

NOTE

Ensure that theC. G. of the external wing

stores is located six inche s aft of the for­ward anchor chain of each load.

CAUTION

Before any ferrying flight on spray air­craft, the fan of the pump should be re­moved if there is no far. brake, other­wise the shaft may seize in its bearings.

The recommended airspeed during operation, with flaps at CRUISE, is 100 to 105 mph (87 to 91 knots) IAS with a maximum limit of 120 mph (104 knots) IAS. At 100 mph (87 knots) IAS, a fertilizer or feeder coverage 100 feet by 2000 feet, from an altitude of 100 feet, can be obtained at a rate of 200 to 300 lb per acre which will discharge an 1850 lb load in 10 to 15 seconds.

At an altitude of 10 feet the boom sprayer installation will give a swath width of 90 feet, using 1/2 to 3 1/2gallons of liquid per acre, depending on control lever setting and system pressure. Increase of altitude to 100 feet will increase the swath width to approxi­mately 140 feet.

NOTE

To improve aircraft handling character­istics when operating at the lower alti­tude, the flaps can be lowered to CLIMB position and the airspeed reduced to 90 mph (78 knots) IAS. This will provide a higher rate of climb when operating in hilly areas.

CAUTION

It is important to wash out the spray in­stallation daily to prevent corrosion and deterioration caused by the spray fluid. The rear of the aircraft should be washed down after spraying and after crop fertil­izing or seeding. Checking for heavy ac­cumulation of dust on the control surfaces and hinges is highly desirable.

The flight altitude during dropping of stores is dependent on local air regulations, the type of stores being dropped, and the sur­rounding terrain. Normally the air speed should be reduced to 100 mph (87 knots) IAS and the flaps lowered to CLIMB setting before the stores drop is commenced, and altitude re­duced to approximately 100 feet above ground level.

4. 1 Operating Limits

The operating limits for the Agri­cultural modeL and Sprayer model are the same as in Section IV of the Flight Manual except that in the Agricultural model removal of the centre fuel tank, to provide space for the hopper, will reduce the range and endur­ance by approximately 33%.

4. 2 WEIGHT AND

With the agricultural installations

AGRICULTURAL MODEL

Add to Basic Agricultural Aircraft

For fertilizer and seeder operation:

Hopper assembly - empty

Chute

Cockpit control levere and fittings Total

Hopper - loaded (e.g. 1600 lb) Total as flown

the aircraft basic weight is affected as follows:

Weight Arm Mom

lb in lb in

83 -25.5 -2116

20.8 -20.3 - 422

4 - 3 -____ 12

107.8 -2550

1600 -23.9 -38240

1707.8 -40790

SPRAYER MODEL

NOTE

Since some items of equipment are removed from the aircraft before installation of the agricultural equipment, reference to the weight and balance report should be made for correct basic weight and C.G. values.

CAUTION

To ensure that the gross weight of the aircraft does not exceed the gross weight permitted by local licencing authorities, restrict the fuel or cargo load as necessary.

OPERATIONAL TABLES AGRICULTURAL MODEL SPRAYING FLUID WEIGHT & MOMENT Note on Use of Table

The weights and moments shown below are for water. To obtain the weights and moments of the spraying fluid being used, multiply the weights and momenta shown below by the specific gravity of the fluid being used.

MOMENTS OF POWDER IN HOPPER To determine moment of powder in hopper:

(1) Estimate to what level on the gauge glass the surface of the powder corresponds.

(2) From the above Spraying Fluid table find the moment arm which is given for this reading on the gauge glass.

(3) Multiply the number of pounds of powder in the hopper by this arm to obtain the moment.

WING RACK LOAD MOMENTS Arm = -4.0

VENTRAL RACK LOAD MOMENTS Arm = -32.0

Total Moment lb in

Total Moment lb in

SPRAYER MODEL

SPRAYING FLUID WEIGHT & MOMENT

Note on Use of Table

The weights and moments shown below are for water. To obtain the weights and moments of the spraying fluid being used, multiply the weights and moments shown below by the specific gravity of the fluid being used.

Arm of Tank = -28.1

U.S. Gal. Imp. Gal. Weight Moment

Water Water lb lb in

10 8.3 83 - 2332

20 16.7 167 - 4693

30 25.0 250 - 7025

40 33.3 333 - 9357

50 41.6 417 -11718

60 50.0 500 -14050

70 58.3 5Я1 -16382

80 66.6 666 -18715

90 75.0 750 -21075

100 83.3 833 -23407

110 91.6 916 -25740

120 100.0 1000 -28100

Example of Use of Table

Suppose spraying fluid has specific gravity of .95

and there are 100 Imp. gal. of fluid in tank.

From the above table 100 Imp. gal. of water weigh

1000 lb and have a moment of -28100.

Thus 100 Imp. gal. of spraying fluid weigh .95 x

1000 = 950 lb and have a moment of .95 x -28100 -

-26695.

WING RACK LOAD MOMENTS

Arm = -4.0

Total Moment lb in

Total Moment lb in

- •;• г