as332l bristow tiger - finck aviation home · trim release button . avad inhibit . 4-way beeper...

AS332L BRISTOW TIGER

TECHNICAL NOTES FOR AIRCREW

Section 1 Basic Construction 1 of 22


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This study guide has been produced by G. Crookshanks with the autopilot section by T. Rolfe. It is for technical guidance during AS332L Conversion Courses and for Aircrew refresher training. Although every effort has been made to ensure the accuracy of these notes, they do not countermand the AS332L Flight Manual or Part B of the Operations Manual. These notes are for use by Bristow Helicopters employees only. If anyone has any suggestions or corrections to this manual then please contact the Aberdeen Training School. © G. K. Crookshanks

August, 2003


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Contents

Section 1 Basic Construction and Limitations Section 2 Central Warning Systems Section 3 Electrical Systems Section 4 Airframe Fuel System

Section 5 Hydraulic Systems Section 6 Undercarriage Section 7 Transmission Systems Section 8 Flying Controls Section 9 Pitot Static Systems Section 10 Ice and Rain Protection Section 11 Heating and Ventilation Section 12 Lighting Systems Section 13 Engine

A) Introduction, Limitations and General Description B) Controls and Indications C) Oil System D) Air System E) Fuel System F) Electrical System G) Fire Protection H) Engine Malfunctions

Section 14 Autopilot Section 15 Flotation Equipment Section 16 Integrated Health and Usage Monitoring System (IHUMS) Section 17 Audio Voice Alerting Device (AVAD) Section 18 Automatically Deployed Emergency Locator Transmitter (ADELT) Section 19 Performance Section 20 To Be Incorporated


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Section 1

Basic Construction, Limitations & Capacities

Light Alloy Kevlar Composite, Honeycomb-glass Cloth Titanium


Figure 1 – Aircraft Structure

1. Air Intake Cowling 2. Fire Wall 3. Engine Cowling (constructed of light alloy) 4. Transmission Deck 5. Engine Sliding Cowling 6. Upper Structure 7. Tail Drive Shaft Fixed Cowling 8. Tail Drive Shaft Opening Fairing 9. TGB Fairing 10. Pylon Fairing 11. Horizontal Stabiliser 12. Tail Skid (Steel) 13. Lower Fin 14. Tail Boom 15. Intermediate Structure

16. Loading Hatch 17. Cabin Door 18. Cabin Floor 19. Landing Gear Fairing 20. Foot Step 21. Hydraulic Line Protective Channel 22. Bottom Structure 23. Fuel Tank Compartment Trim 24. Cockpit Floor 25. Console 26. Radome 27. Co-Pilots Door 28. Canopy 29. Forward Fixed Fairing (Overhead Panel)

Sandwich Structure - Metal Hwith Metal Skin

oneycomb,

ilots ield)

Altuglass (Triplex glass for pwindsh


Intercom/Transmit Switch

Autopilot Disengage Button

Trim Release Button

AVAD Inhibit

4-Way Beeper Trim Button

Cargo Release Button

Coupler Disengage Button

2

HSI

1

CWP DME 2

HSI

1

ALT

RAD

VSI

ASI

NR

TQ

2 2 12 12 18

5

7 7

8 8

9 9

4

10

6

3 3

13

11

RADAR

14 14

15 15

16 17

ALT

RAD

VSI

ASI

NR

TQ

Figure 2 – Instrument Panel

1. Nav. Aid Switching Panel 2. Autopilot Hold selection panel 3. Marker lights 4. Co-Pilots Digital Clock 5. Collective Pitch Gauge 6. Captains Analogue Clock 7. Engine Ng Gauges 8. Engine T4 Gauges 9. Engine Oil Temperature/Pressure Gauges

10. Electrical OAT Gauge 11. Temperature & Pressure Gauges 12. Fresh Air Vents 13. Standby Artificial Horizon 14. Undercarriage ‘UP’ Warning Light 15. WARN and ALARM Attention Getters 16. Engine POWER Warning Lights 17. MAX NR and MIN NR Warning Lights 18. Compass Correction Cards

Figure 3 – Cyclic Control


FUEL PANEL

GPS AUTOPILOT GEAR

ICE DETECTOR

NAV 1

NAV 2

AP HEAT AVAD

ADF

VHF 1

VHF 2

P1 STATION BOX

P2 STATION BOX

ADELT

AFDS

FLOATS

IHUMS

P3 STATION BOX

COMPASS SLAVING

DOOR WARNINGS

XPDR EXIS

ACCESS FOR HAND PUMP

STANDBY COLLECTIVE PITCH GAUGE

COLLECTIVE FRICTION

NOSE WHEEL LOCK

FUEL ICE LIGHTS

Undercarriage Emergency Lowering Handle

Parking Brake

12 13 14 15 16

Figure 4 – Centre Consul and Cockpit Floor Area

Hoist Emergency Shear

No t

Floatation Gear Inflation Button

se Landing Ligh

AP Hydraulics

Hoist Up/Down Nose Light 4-Way Trimmer

Autopilot BARAN Release Off-set Bleeds

Windshield Wipers

Under Slung Load Emergency Release

Figure 5 – Collective Control


ELECT

Figure 6 – Overhead Cockpit Panel

1. CVR Cockpit Area Microphone 2. Utility Wander Light 3. Dinghy and Storm Lights 4. Heater Distribution Selector 5. Heater Control 6. Vertical Gyros Fast Slaving Switches 7. Crash Handles 8. Overhead Panel Lighting and Warning Light Test Button 9. Centre Console Lighting and Warning Light Test Button 10. Pilot’s Instrument Lighting Controls 11. Cabin, Cockpit, Emergency and Ordinance Lights 12. Flood Lights, Nav. Lights, Anti-collision/Strobe Lights 13. Co-Pilot’s Instrument Lighting Controls 14. Engine Intake Heater Mats Control Panel 15. Map Lights 16. Engine Speed Select Levers 17. Engine Fuel Shut-Off Levers 18. Rotor Brake Safety Lever 19. Rotor Brake Lever

RICALCH

SWIT ING

FIR EL

A L

PANEL

E EXT. PAN

ELECTRICAL MONITORING

NEP

GYROS

8

11

DOME LIGHT 4

5

3 6

2

MISSION S

14

ELECTOR

IHUMS

13

1

7 7

15 15 9

10

12

16

17 18

19


BASIC CONSTRUCTION Cockpit A light alloy welded structure with radome attachments and ventilation flap in the front section. Transparent panels are fitted in the doors and nose section. The two lateral windscreens have windscreen wipers and can be heated. Crashworthy seats are fitted for the 2 pilots and a 3rd crew member's seat may be fitted in the aisle. Under the cockpit floor are located the gyros and certain electrical and flying controls items. The nose compartment, sealed by a hinged Radome, contains the main battery, autopilot computer and various electronic printed circuit boards (PCB). Below and around the nose section is attached an inflatable flotation bag. Cockpit doors should not be used as hand holds to climb into or out of the cockpit. Micro switches on the Radome locks illuminate a warning if they are not properly secured. A retractable landing light is incorporated under the nose section. Upper Structure It is made of a semi-monocoque design manufactured in light alloy. The stressed skin panels have openings for windows and doors. The upper skin panels, constituting the transmission decking are made of titanium. The forward compartments contain hydraulic components (including autopilot hydraulic pack), and flying control linkages on the starboard side, and on the port side, the electrical control systems, transformers and rectifiers. Bottom Structure It is made of conventional semi-monocoque construction of light alloy. It is cradle shaped to accommodate fuel tanks in the lower portion. The floor is made of strengthened honeycomb sandwich type material and is bolted to lower section over the fuel tanks and has attachment points for seats or freight. Below the electrical compartment on the port side, is an access panel for external power connections. Indications are given to the crew if this panel is not secured. The top and bottom structures when riveted together form the cabin compartment with seating for 18 passengers. A standby battery is located on port side just aft of the door. Intermediate Structure This is made of a light alloy semi-monocoque construction composed of two half shells riveted together and closed at the bottom by a hinged access door. This compartment forms the baggage hold capable of carrying 920 lbs spread over 3 different loading areas. Indication is given to the crew if the cargo door is not correctly closed and locked. The above 3 sections are riveted together to form the main airframe assembly. The 'L' version of the AS332 is extended in the vicinity of the front cabin window by 765 mm. Tail Boom This is made of a light alloy semi-monocoque construction of 3 elements; horizontal structure, inclined pylon and keel, attached to intermediate section by ring of bolts. The upper surface carries bearing supports for tail rotor transmission and IGB. The pylon carries supports for TGB, tail rotor, and horizontal stabiliser.


The keel is made up of ribs and light alloy skin and its lower portion contains a laminated shoe. The tail skid and its shock absorber are attached to the pylon. Cowlings The two over engine cowlings are made of light alloy and the front and rear sliding cowlings are made of a fibre glass material. The rear engine cowling (Dog House) slides rearwards and the two engine cowlings are hinged outboards to form walkways. They have a maximum load of 800 lbs. The front intake cowling, which has a lower central intake for air conditioning equipment and supports a "Chip Basket" intake guard for each engine, slides forward. Cowlings are locked by handles and quick release pins. An indication is given to the crew if cowlings are not closed correctly. This is by means of a proximity switch on the sliding cowling. Cowlings should not be opened in winds exceeding 40 kts. Cowlings along the tail boom and inclined pylon are hinged and made of Kevlar. The cowling over the tail rotor shaft at the gearbox end is made of light alloy and is bolted on. Horizontal Stabiliser This is fitted on port side it is of an inverted aerofoil shape with a positive incidence. It is composed of a spar and ribs covered with a light alloy skin. A fixed slat extends in front of the stabiliser to improve the airflow over the aerofoil. Doors The crew members doors are of light alloy framework with plastic windows and provision for map case. A sliding window is provided. The doors are jettisonable by means of guarded handles near the hinge. Correct locking is indicated by a red "Flag" on the upper framework and by micro switches on the catches. Care should be taken when opening doors in high winds and when closing doors to ensure correct location of locking catches. Plug type sliding doors are fitted to cabin on either side. These doors slide on hinged rollers, which allow the door to fit flush with airframe when closed and require a certain knack in opening and closing. The Starboard door can be jettisoned from the cockpit by means of a guarded handle on the bulkhead behind the Captains seat. Both doors can be jettisoned by guarded handles just forward and above each door in the cabin. A perspex cover is fitted over the starboard door inner handle as this door is normally only opened in an emergency, the normal passenger entry and exit being by the port door. Indication of correct closing of doors is given to the crew via series wired micro switches on each lock. All windows in the cabin may be jettisoned but the primary emergency exits are the large windows at the front of the cabin on either side, the main cabin doors and the cockpit doors. Sponsons Light alloy sponsons are attached either side and house a fixed floodlight and the main undercarriage when retracted. Each sponson supports an inflatable flotation bag with the flotation gas bottle housed in the sponson. Transmission Deck This is made of titanium and has attachment points for the engines, hydraulic reservoirs, fire bottles, oil cooler and main gearbox. The main gearbox is supported on a "Barbecue" plate made of titanium and transmits lift via 3 support struts. The engines are separated by a titanium firewall and ventilation air can enter via flaps at the front of the transmission decking. The decking is fitted with drains to allow spillage to drain away via pipelines to below the aircraft.


LIMITATIONS AND CAPACITIES Loading Limitations Maximum A.U.W. 18,960 lbs (8,600 kg) Minimum approved Wt 10,000 lbs (4,500 kg) C of G Datum 4.67 m (183.86 ins) forward of the main rotor mast Aft C of G Limits Below 15,430 lbs (7,000 kg) 4.90 m (192.9 ins)

At 18,960 lbs (8,600 kg) 4.85 m (190.9 ins) Forward C of G Limits Below 15,430 lbs (7,000 kg) 4.40 m (173.2 ins)

At 18,960 lbs (8,600 kg) 4.52 m (177.9 ins) Transverse C of G Limits 0.08 m (3.15 ins) Left 0.09 m (3.55 ins) Right Cabin Floor Loading 1.16 lbs/sq. ins (167 lbs/ft sq.) Cargo Bay Loading Upper Shelf 250 lbs (40 lbs/ft sq.) maximum

Lower Shelf 550 lbs (80 lbs/ft sq.) maximum Tail 120 lbs (15 lbs/ft sq.) maximum

Speed Limitations Power On Flight VNE. (Weights up to 18,410 lbs) 167 kts (Weights above 18,410 lbs) 150 kts VNO. VNE minus 10 kts Power OFF Flight VNE. (Weights up to 18,410 lbs) 150 kts (Weights above 18,410 lbs) 145 kts

Run on speed 40 kts Taxying speed 40 kts Braking speed 30 kts Plug doors open flight speed 150 kts maximum Plug doors operating flight speed 55 kts maximum Landing light manoeuvring speed 110 kts maximum Undercarriage lowering speed 110 kts (recommended) Autopilot altitude & heading holds 70 kts minimum

Wind Speed Limitations

Weight above 18,410 lbs 17 kts Weight below 18,410 lbs 35 kts

Maximum Hover cross/tail wind

Wind 45° ahead 40 kts Wind ahead 65 kts Wind 45° ahead 40 kts Wind abeam 30 kts

Rotor Engaging and Braking

Wind astern 25 kts


Altitude Limitations Maximum Altitude Take-off at weights greater than 18,410 lbs 4,000 ft Density Altitude Take-off at weights below 18,410 lbs 13,000 ft Density Altitude (Group A)

15,000 ft Pressure Altitude Cruise flight at weights greater than 18,410 lbs 9,500 ft Pressure altitude Cruise flight at weights less than 18,410 lbs 20,000 ft Pressure altitude Minimum Altitude -2,000 ft Pressure Altitude Maximum Altitude in icing conditions 8,000 ft Airspeed/Height envelope Refer to FM section 2.1 paragraph 12 Figure 5 Temperature Limitations ISA + 35°C (limited to +50°C max. and –30°C min.) Angle of Bank Limitations Maximum angle of bank at weights above 18,410 lbs 30° Maximum angle of bank at weights between 17,200 and 18,410 lbs 40° Maximum angle of bank at weights below 17,200 Unlimited Maximum angle of bank in icing conditions 20° Sloping Ground Limits Maximum 12° up and 8° across for landing

Maximum 10° up and 5° across for shutdown Manoeuvring Prohibited Aerobatics

Extended rearwards flight Intentional running landing on soft ground Intentional power off landing Down-wind hovering with the ‘bleed valve’ in the ‘normal’ position IMC Flight Envelope Refer to FM Section 2.1 paragraph 9.4 figure 3 Rotor RPM Limits

Normal 265 (22,850 Nf) Governed Range 245-275

Power On

Maximum 290 Maximum Transient 310 Maximum 290

220 at 100 kts & below

Power Off

Minimum 245 above 100 kts

Visual and Aural alarm activated above 290 and below 245 Nr


Collective Pitch Limitations Level Flight 15½° (However pitch may be increased up to 16° in order to

obtain 62% Torque) Climbing Maximum Limit 17° Total Travel Limit 19° Limit with Autopilot not fully functional 15½° Rotor Brake Limitations 1. Rotor brake must not be applied until the engines have been shut down. 2. Maximum Nr for brake application is 120. 3. If wind speed above 30 kts the brake must be on for starting. 4. Only one engine may be started against the brake. 5. If starting with the brake ON, the brake must be released by 23,250 Ng (105 bar brake) or as soon

as it starts slipping. 6. Running time with the brake applied is 5 minutes 7. The brake must not be applied twice within 5 minutes. If so applied, then a cooling down period of 15

minutes (including 10 minutes rotors turning) must elapse before third application. Transmission Limitations

Torque Maximum 100% 5 min

Twin Engine Maximum Continuous 81% - Maximum 69% 2½ min Maximum Continuous 66% - Single Engine Transient Over Torque 74% 20 sec

Lubrication Minimum Pressure 1 bar Normal Pressure Range (Main) 4 - 7 bar Normal Pressure Range (Standby) 2 – 4½ bar

Main Gearbox

Maximum Temperature 145°C IGB and TGB Maximum Temperature 120°C

Gearbox oil is Aeroshell 500


Engine Limitations

Time Ng T4 Take-off 5 min 33,200 785°C

Twin Engine Limits Max Continuous Unlimited 32,500 735°C Max Contingency 2½ min 34,000 810°C Inter Contingency Unlimited 33,200 775°C Single Engine Limits

Max Transient 20 sec 34,900 Maximum Unlimited 750°C Max Transient 5 sec 800°C Starting Limits Absolute Max 2 sec 810°C

Note – Periods at or above 33,200 Ng require Tech Log entry. Engine life is limited to a total of 15 minutes above 33,200 Ng.

Time Nf/Nr Overspeed Trip (27,420 Nf) N/A 318

Transient 20 sec 310 Nf Limits (Equivalent Nr)

Continuous Unlimited 292

Pressure Temp. Minimum Pressure 1.7 bar Maximum Pressure 6 bar Min Oil Temperature (for power application) 0°C Maximum Oil Temperature 110°C

Engine Oil

Limitations

Min Oil Temperature for Starting -40°C Miscellaneous Engine Limitations 1. Starter - Maximum of 3 Cycles then wait 20 minutes for cooling. 2. Air Bleeds (heating etc.) – not to be used during take-off and landing 3. Normal Oil consumption is 0.3 ltr. per hour 4. Engine oil used is Aeroshell 500 5. Maximum engine misalignment between both engines is 500 rpm Hydraulic System Limitations

Minimum 80 bar Normal 165-196 bar

Main System Pressure

Maximum 210 bar Minimum 80 bar Normal 100-145 bar

Auxiliary System

Maximum 190 bar Hydraulic Fluid used is Mil 83282A


Electrical System Limitations

Minimum Voltage 14V Maximum Voltage 32V

DC System

Maximum Current 150 amp Minimum Voltage 98V Maximum Voltage 132V

AC System

Maximum Current 75A Fuel System Limitations 1. Normal operating pressure – 0.15 bar - 1.2 bar. 2. Fuel anti-ice additives required if OAT in flight is below –20°C. 3. Fuel Transfer must not take place during take-off and landing. Miscellaneous Limitations 1. Windscreen Wipers – Not to be used on dry windscreen 2. Flotation Gear System Armed or Inflated – 135 kts Power On or 110 kts Power Off

Maximum altitude for arming or inflating 6,500 ft pressure altitude

Recommended inflation <80 kts and 400 ft Pressure Altitude 3. EXIS Lights – Use of switch is prohibited except for emergencies 4. ADELT – Manual deployment is prohibited except for emergencies 5. Seat Arm Rests – Must be up for take-off and landing 6. Air Intake Heating Mats – Must be OFF if OAT is greater than +10°C Icing Limitations Continuous ──────────── Maximum Pressure Altitude 8,000 ft

Minimum OAT -6°C

Maximum LWC severity 0.4 g per meter ³ Maximum build up on fixed probe 40mm

Intermittent ──────────── Maximum Pressure Altitude 8,000 ft

Minimum OAT -10°C

Maximum LWC severity 0.8 g per meter ³ Maximum build up on fixed probe 40mm

Maximum torque increase - +12% (not to exceed maximum continuous)


Fuel Capacities The following fuel capacities are specified for 0° 55’ nose up attitude.

Left hand Group Right Hand Group Litres Lbs Litres LbsLongitudinal Tank 246 428 Longitudinal Tank 236 411Transverse Tank 423 736 Transverse tank 405 7055th Tank 246 428 7th Tank 487 848- 6th Tank 324 564Left Total Capacity 915 1592 Right Total Capacity 1452 2528

Aircraft Total Fuel Capacity 2367 4120

LH Group 28 lbsNormal Unusable Fuel RH Group 16 lbsLH Group 79 lbsUnusable Fuel With Large Nose Up Attitude RH Group 228 lbs

Hydraulic Capacities

Total Capacity in each reservoir 12 ltsNormal fluid capacity right hand system 5 ltsNormal fluid capacity left hand system 8 lts

Transmission System Capacities

Minimum 17.05 ltsMain Gearbox Maximum 19.60 lts

Minimum .50 ltsIntermediate Gearbox Maximum .62 lts

Minimum 1.17 ltsTail Gearbox Maximum 1.44 lts

Note – The total capacity of oil in the MGB including the oil cooler is 21.4 lts. Engine Oil Capacity

Maximum Level 7.6 ltsMinimum Level 4.3 ltsTotal Capacity 16.5 lts

Landing Gear Tyre Pressures

Nose Wheels 7 barMain Wheels 7.2 bar


Sling Limitations

Kgs Degrees Knots Maximum Angle of Bank with load On 25° Maximum Load 4,500

< 3,500 100 3,500 – 4,000 90

Maximum Speed

> 4,000 80 1. MAUW can be increased to 9,350 kgs (20,610 lbs) providing 1000 kgs can be jettisoned. 2. If the sling is attached to the aircraft and not the gearbox, the weight limitation is 2,000 kgs. 3. The emergency release for under-slung loads is a trigger on the captain’s collective lever. Hoist Limitations

Kgs Lbs Deg Knots Maximum Angle of Bank 25° Maximum Load 272 600

Maximum Load On 65 Winching ahead or abeam 35

Max Speed

More than 4 m of cable out 35 Cycles 5 up/down then stop for 30 minutes or fly at 80 kts for 5 minutes

1. Hydraulic Supply 175 bar from Left Hand system 2. Cable length 50 meters 3. Winch Rate 0.5 m/sec = 100 ft/min 4. Controlled by selector switch in cockpit and/or operators selector switches.


Main Aircraft Dimensions All heights are given for an average gross weight of 8,000 kgs (17,637 lbs)

Metric Main Rotor Diameter 15.60 m Tail Rotor Diameter 3.05 m

Blades on aircraft centre line 18.70 m Length Blades 45° orientated 16.54 m To top of tail rotor disc 4.95 m Height To top of main rotor head dome faring 4.59 m

Width Main rotor blades in the 45° position 11.00 m Main Rotor Blade Chord 0.60 m Tail Rotor Blade Chord 0.20 m

Under Fuselage 0.43 m Under Tail Rotor Disc 1.90 m

Ground Clearance

Under Tail Rotor Skid 1.12 m Track 3.00 m Landing Gear Wheel Base 5.28 m Height 1.35 m Width - with Plug Door 1.30 m

Cargo Bay Access

Sill Height Above Ground 0.92 m Aircraft in the Kneeled-down Position

To top of tail rotor disc 4.44 m Height To top of main rotor head dome faring 4.45 m

Under Fuselage 0.25 m Under Tail Rotor Disc 1.39 m

Ground Clearance

Under Tail Rotor Skid 0.62 m


Figure 7 – Antennae Locations

BRISTOW G-

1

2

3

4 5

6 7

8 12

11

9

13

8

12 11

4 3

10 6

1. Weather Radar 2. ILS Glideslope (Inside Radome) 3. VHF 1 4. VHF Homer (2) - if fitted 5. Marker 6. Transponder 7. ADF Loop and Sense 8. GPS 9. Radalt (2 antennae) 10. DME 11. VOR/Localiser 12. VHF 2 13. VHF FM

as332l bristow tiger - finck aviation home · trim release button . avad inhibit . 4-way beeper...

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