ground handling servicing cklst

TI 4040.25GC Original, 09/96

BAe 125-800A

GROUND HANDLING AND

SERVICING CHECKLIST


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FOREWORD

This checklist provides condensed instructions for ground handling, servicing, and powerplant operation of the BAe-125-800A aircraft. These instructions do not replace detailed information contained in the Maintenance Manual, but serve as a guide to ensure that no item is overlooked while performing ground handling and servicing tasks. Personnel using this checklist for servicing operations should consult the applicable maintenance manual. LuVern D. Dokter Manager, Flight Inspection Maintenance Division, AVN-300

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TI 4040.25CG Original, 09/96

LIST OF EFFECTIVE PAGES

CHANGING THE MANUAL Changes will be issued when required. Pages contained in the change supersede like pages in the checklist. Each page in a change has a "Change" number located at the upper right corner of the page. Portions of the test affected by the change are indicated by a vertical bar adjacent to the text and in the page margin. Vertical bars will not be used when the change is the result of a rearrangement of material due to a change on a previous page. The List of Effective Pages provides the user with a guide to establish the current effective date of each page in the manual. Information included in the List of Effective Pages states the current change number for page and the dates of a Change shall be removed from the manual. Pages included in the Change shall be inserted in the manual. LET US KNOW Every effort has been made to keep this manual current. However, errors cannot be corrected unless we are apprised of the error. In this regard, it is essential that users/operators do their part. Comments, corrections and questions regarding this manual are welcomed. Date of issue for original and changed pages are: ORIGINAL .................... SEPTEMBER 1996

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C

DEFINITIONS

The following definitions apply to the terms "Normal Procedures," "Abnormal Procedure," and "Emergency Procedure."

Normal Procedure: An operating procedure for the aircraft and its systems, which may be considered routine in day-to-day operations.

Abnormal Procedure: An operating procedure requiring

the use of special systems and/or alternate use of regular systems which, if followed, will maintain an acceptable level of airworthiness or reduced operational risk resulting from a failure condition.

The following definitions apply to the words "shall," "will," "should," and "may."

Shall or Will: Instructions or procedures prefaced by "shall" or "will" are mandatory. Should: Indicates a preferred by non-mandatory method of accomplishment. May: Indicates an acceptable or suggested means of accomplishment.

This manual provides the best possible system descriptions under most circumstances but it is not a substitute for sound judgment. WARNINGS, CAUTIONS AND NOTES The following definitions apply to "Warnings, "Cautions," and "Notes" found throughout this manual.

WARNING Operating procedures, techniques, etc., which may result in personal injury or loss of life if not carefully followed.

CAUTION

Operating procedures, techniques, etc., which will result in damage to equipment of not carefully followed.

NOTE An operating procedure, technique, etc., which is considered essential to emphasize.

TI 4040.25CG Original, 09/96

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TABLE OF CONTENTS SECTION PAGE

Service Points ....................................................... III

1 Towing................................................................. 1-1

2 Parking and Mooring ........................................... 2-1

3 Refuel – Pressurized method.............................. 3-1

4 Refuel – Gravity (Overwing) Method................... 4-1

5 Ventral Tank Refuel by Transfer ......................... 5-1

6 Defuel – Suction Method..................................... 6-1

7 Fuel Transfer....................................................... 7-1

8 APU Oil ............................................................... 8-1

9 Engine Oil............................................................ 9-1

10 Hydraulics ......................................................... 10-1

11 Ice and Rain Protection..................................... 11-1

12 Landing Gear/Tires ........................................... 12-1

13 Oxygen.............................................................. 13-1

14 Toilet ................................................................. 14-1

15 Water................................................................. 15-1

16 Applying Electrical Power.................................. 16-1

17 APU Ground Operation ..................................... 17-1

18 Power Plant Ground Operation ......................... 18-1

19 Jacking and Trestling ........................................ 19-1

I



II


GROUND SERVICE POINTS

FIGURE 1 (Sheet 1 of 2)

III

TI 4040.25GC Original, 09/96 GROUND SERVICE POINTS

Figure 1 (sheet 2 of 2)

IV


AIRCRAFT EXTERNAL 28VDC SUPPLY CONNECTION

FIGURE 2

V


TOWING

A. REFERENCES

Personnel required to accomplish towing procedures shall be familiar with BAe 125-800A procedures.

B. PERSONEL REQUIRED

Minimum: Towing team supervisor coordinates tow tractor and cockpit activities from suitable location. Tractor Operator Qualified Brake Operator (Radio Operator) Towing in congested area: Two wing walkers in addition to above requirements. Backing Operations One tail walker in addition to above requirements.

C. EQUIPMENT AND MATERIALS

Tractor, Tow Tow Bar

D. TOWING PROCEDURES

1. Check for aircraft status. ( )

CAUTION Ensure correct strut and tire inflation before towing. 2. Remove external power (if used) and all

other ground equipment from vicinity of aircraft. ( )

1-1


TOWING (Con’t.)

3. Install nose leg gear (NLG) and main leg gear MLG) lock pins. ( )

4. Remove quick release pin. ( ) 5. Remove NLG steering disconnect pin. ( ) 6. Ensure NLG doors are closed. ( ) 7. Attach towbar to NLG using steering

disconnect pin. ( ) 8. If applicable, towbar safety catch. ( ) 9. Connect tractor to towbar. ( ) 10. Check emergency brake accumulator

gauge in rear equipment bay reading is 2000 psi minimum. ( )

NOTE

If necessary, top up system by operating hydraulic

hand pump.

WARNING Wing walkers will be immediately available if

emergency and normal brake systems are inoperable.

11. Flight deck brake operator in left seat. ( )

12. Close aircraft entrance door. ( ) 13. Aircraft batteries, navigation lights,

and radios (as required) on. ( ) 14. Obtain clearance from control tower

for aircraft movement. (As required) ( ) 15. Disconnect aircraft ground wire. ( ) 16. Aircraft handbrake lever to Emergency

position. ( )

1-2


TOWING (Con’t.)

17. Ensure established hand signals will be used

between brake operator and supervisor. ( ) 18. Position wing/tail walkers (as required). ( ) 19. Apply brakes, then remove chocks. ( ) 20. Release aircraft brakes. ( )

CAUTION Move aircraft in a straight line prior to starting any

sharp turns. Avoid sudden starts and stop. Use aircraft brakes for emergency stops only. Do no tow on surface grades exceeding 20%. Do not exceed towing speed of 5 mph.

21. Commence towing. ( )

CAUTION

Prior to parking, move aircraft in straight line to centralize nose wheel and relieve landing gear side loads.

22. Place aircraft brake lever to PARK position. ( ) 23. Towing complete, position chocks front

and rear of both MLG wheels. ( ) 24. If applicable, contact tower. ( ) 25. Towing completed. ( ) 26. Navigation lights, radios, and aircraft

batteries OFF. ( ) 27. Disconnect tractor from towbar. ( ) 28. Release brakes. ( ) 29. Remove towbar. ( ) 30. Install NLG steering disconnect pin. ( )

1-3


TOWING (Con’t.) 31. Install quick release pin to lock NLG

steering disconnect pin. ( ) 32. Aircraft ground wire connected. ( ) 33. If applicable, complete documentation. ( )

1-4


PARKING AND MOORING

A. REFERENCES

Personnel required to accomplish parking and mooring procedures shall be familiar with BAe 125-800A Aircraft Maintenance Manual Procedures.

B. PERSONNEL REQUIRED

Two mechanics (Minimum).


Description Quantity Stall vent plug 2 Lower static vent plug 2 Upper static vent plug 2 Pitot head cover 2 Ice detector cover 1 APU intake cover 1 APU exhaust cover 1 APU generator cooling cover 1 Jet intake left cover 1 Jet exit left cover 1 Jet intake right cover 1 Jet exit right cover 1 Main landing gear locking pin 2 Nose landing gear locking pin 1 Emergency exit locking pin 1

D. GENERAL Mooring requirements are in addition to parking requirements and are used when parked aircraft are subjected to high winds exceeding safety requirements. Parking/Mooring Expected Wind Requirement Velocities (Knots) Normal parking Up to 35 Mooring with single Tie-downs 36 to 60 Mooring with double Tie-downs 60 to 80

2-1


PARKING AND MOORING (Con't.)

NOTE

The above is based upon aircraft being fully fueled and headed into wind.

E. NORMAL AIRCRAFT PARKING

NOTE

Selected position away from other parked aircraft and if engine run is anticipated, at a safe distance from other engine exhaust. If freezing weather is anticipated, park tires on mat or sand to prevent tires adhering to parking ramp. 1. Position aircraft. ( ) 2. Centralize nose wheels ( ) 3. Place wheel chocks from and

rear main gear wheels. ( )

4. Install main and nose gear lock pins. ( )

5. Check wing flaps retracted. ( ) 6. Install aileron, elevator and rudder gust locks. ( ) 7. Check emergency brake accumulator gauge

reading is 200 psi minimum. ( )

NOTE If necessary, top up system by operating hydraulic hand pump.

8. Apply handbrake fully to PARK position. ( ) 9. Connect aircraft ground wire. ( )

2-2



NOTE

Ensure pitot heads cool before fitting covers. Insure static vents are clear of obstructions before fitting vent plugs.

10. Install pitot head covers. ( ) 11. Install static vent and stall warning vent

plugs. ( )

12. Install engine and APU inlet and exhaust covers. ( )

13. Close windows. ( ) 14. Ensure emergency exit locking pin installed. ( ) 15. Close exterior doors. ( ) 16. If freezing conditions are expected:

a. Drain potable water systems. ( ) b. Purge lavatory and sink drains. ( ) c. Winterize or drain toilets. ( )

17. If high winds are anticipated, moor aircraft as per Section F. ( )

F. MOORING AIRCRAFT

NOTE

When mooring aircraft over a long period, brake pressures should be checked periodically and topped up as necessary.

a. Winds 35 to 60 knots. (Refer to Figure 2-1)

1. Check aircraft headed into wind. ( ) 2. Check maximum fuel. ( ) 3. Aircraft brake lever to PARK position. ( )

2-3



4. Front and rear chocks lashed together on

all wheels. ( ) 5. One mooring tiedown on each main gear. ( ) 6. Remove workstands and equipment from

area. ( )

b. Winds 60 to 80 knots. (Refer to figures 2-2 and 2-3.)

1. Check aircraft headed into wind. ( ) 2. Check maximum fuel. ( ) 3. Aircraft brake lever to PARK position. ( ) 4. Front and rear chocks lashed together on

all wheels. ( ) 5. One mooring tiedown on nose gear. ( ) 6. Double mooring tiedown on each main gear. ( ) 7. Remove workstands and equipment from

area. ( )

WARNING Where excessively high winds are forecast, aircraft should be flown out of area or hangared.

2-4



35 TO 60 KNOTS MOORING

Figure 2-1

2-5


PARKING AND MOORING (Con't.) 60 TO 80 KNOTS MOORING

Figure 2-2

2-6



MOORING ROPE ATTACHMENTS

Figure 2-3

2-7



2-8


REFUEL – PRESSURIZED METHOD

A. REFERENCES

Personnel required to accomplish refuel operations shall be familiar with BAe 125-800A aircraft procedures and have completed training requirements or flight crewmember must be present to oversee.

B. PERSONNEL REQUIRED Refueling Supervisor/Refueler Designated Flight Crewmember, if required.

C. GENERAL Limitations Maximum wing imbalance - 500 lb. Maximum refuel pressure (gauge) - 50 psi Maximum refuel rate - 120 US gal. min. Minimum wing tank fuel load with full ventral tank: Aircraft on ground -1000 lb. each wing Aircraft prepared for flight -3450 lb. each wing

D. PREPARATION 1. Aircraft status ( )

WARNING APU operation is not permitted while refueling or defueling operations are in progress.

CAUTION Do not position any ground equipment under aircraft during fueling operations as aircraft settles under weight of Fuel load. Fuel tank vapors, which vent at wing tips, will in increase significantly during fueling operations.

3-1


REFUEL – PRESSURIZED METHOD (Con't.)

2. Remove all unnecessary ground equipment. ( ) 3. Place wheel chocks front and rear approximately one inch away from tires. ( ) 4. Position fire extinguisher(s) ( ) 5. Confirm refueling source type and grade. ( )

CAUTION Aircraft and fueling truck must be correctly grounded before any fueling operation to prevent the possibility of fire or explosion due to discharge of static electricity. 6. Refueling equipment and aircraft grounded:

a. Ground cable from aircraft to approved common ground. ( )

b. Ground cable from fuel truck to

approved common ground. ( ) c. Ground cable from fuel truck to aircraft. ( )

CAUTION Investigate any contamination (other than water) of the drained fuel sample. 7. Drain water from fuel tanks. ( ) 8. Check fuel L and R PUMP switches OFF. ( ) 9. Select either external or battery power supply. ( ) 10. Check all unnecessary electrical loads are OFF. ( ) 11. Ensure both HP cocks are closed. ( ) 12. Open both engine LP cocks. ( ) 13. Check WING FUEL/X FEED/TRANSFER

level to WING FUEL. ( )

14. Check AUX FUEL TRANSFER lever is closed. ( )

3-2



E. PRESSURE REFUEL PROCEDURE

1. Test refuel control system. ( ) 2. Set refuel panel MASTER switch to ON and

check MASTER VALVE indicates OPEN. ( )

3. MWS FUEL ↑ annunciator lit. ( ) 4. Roof panel REFUEL ON annunciator lit. ( ) 5. Set VENTRAL, L AND R WING switches

to REFUEL as required and ensure that respective VALUE indicates OPEN. ( )

6. Connect fueling truck hose to SPR coupling. ( ) 7. Bond hose coupling to aircraft. ( )

WARNING

Stop refueling in the event of fire, fuel leakage or spillage. Switch off electrical power. 8. Adjust fuel truck pump output pressure to a

maximum of 50 psi. ( ) 9. Aircraft fuel gauges begin to increase. ( ) 10. Select each tank REFUEL switch to OFF

when associated tank FULL indicator lights or gauge indicates required contents. ( )

NOTE

Allow fuel to settle for approximately two minutes to verify satisfactory content indication. 11. Select MASTER switch OFF and check all refuel VALVE indicators show SHUT. ( ) 12. MWS FUEL annunciator out. ( ) 13. Roof panel REFUEL ON annunciator out. ( ) 14. Adjust fuel truck pump output pressure to zero. ( )

3-3



15. Check and log total fuel uplift. ( ) 16. Disconnect fuel hose from SPR coupling. ( ) 17. Install blanking cap to SPR coupling. ( ) 18. Close SPR coupling access door. ( ) 19. Carry out fuel water check. ( )

NOTE If water drain check is carried out too quickly after refueling, sample will be cloudy due to water being in suspension. Where possible, wait 30 minutes before carrying out check. 20. Close both LP cocks. ( ) 21. Remove aircraft electric power. ( )

3-4


REFUEL – GRAVITY (OVERWING) METHOD

A. REFERENCES

Personnel required to accomplish refuel operations shall be familiar with BAe 125-800A Maintenance Manual Procedures or flight crewmember must be present during this process.


Refueling Supervisor/Refueler Designated Flight Crewmember

C. GENERAL

Limitations

Maximum refuel rate - 120 US gal. min. Minimum wing tank fuel load with full ventral tank Aircraft on ground - 1000 lb. each wing. Aircraft prepared for flight - 2450 lb. each wing. Maximum wing load imbalance - 500 lb.

D. PREPARATION

1. Aircraft status.

WARNING

APU operation is not permitted while refueling or defueling operations are in progress.

CAUTION

Do not position any ground equipment under aircraft during fueling operations as aircraft settles under weight of fuel load. Fuel tank vapors, which vent at wing tips, will increase significantly during fueling operations, as well as being prevalent at the open wing tank filling points.

4-1



(Con't.)

2. Remove all unnecessary ground equipment. ( )

3. Place wheel chocks front and rear approximately one inch away from tires. ( )

4. Position fire extinguisher(s). ( )

5. Confirm refueling source, type, and grade. ( )

WARNING

Aircraft and fueling truck must be correctly grounded before any fueling operation, to prevent the possibility of fire or explosion due to discharge of static electricity. APU must not be running and no power must be applied to the aircraft while fuel tanks are open during fueling operations.

6. Refueling equipment and aircraft grounded:


b. Ground cable from fueling truck to


CAUTION

Investigate any contamination (other than water) of the drained fuel sample.

7. Drain water from fuel tanks, wing, and ventral. ( ) 8. Close both LP cocks. ( ) 9. Check WING FUEL/X FEED/TRANSFER

lever to WING FUEL. ( ) 10. Check AUX FUEL TRANSFER lever is closed. ( )

4-2



(Con't.) E. REFUELING PROCEDURES – WING TANKS TO FULL

1. Ground fuel truck hose nozzle to aircraft. ( ) 2. Unlock and remove fuel tank filler cap, insert

nozzle and refuel as required. (Both tanks simultaneously, if possible.) ( )

3. Adjust fuel truck pump output pressure for suitable flow rate. ( )

WARNING

Stop refueling in the event of fire, fuel leakage, or spillage.

NOTE

Wing tanks are full when fuel level reaches the filler neck flap valve. Allow fuel to settle for approximately two minutes to ensure satisfactory contents indication.

4. Reduce fuel truck pump output pressure to zero. ( )

5. Remove refuel hose nozzle from fuel tank, fit

and lock filler cap. ( ) 6. Disconnect fuel truck hose nozzle ground from

aircraft. ( ) 7. Check and log total fuel uplift. ( ) 8. Disconnect fuel truck ground. ( ) 9. Carry out fuel water check. ( )

NOTE

If water drain check is carried out too soon after refueling, sample will be cloudy due to water being in suspension. Where possible, wait 30 minutes before carrying out check.

4-3



4-4



A. REFERENCES

Personnel required to accomplish refuel operations shall be familiar with BAe 125-800A Maintenance Manual Procedures or flight crewmember must be present during this process.


Refueling Supervisor/Refueler Designated Flight Crewmember

C. GENERAL

Limitations

Maximum refuel rate - 120 US gal. min. Minimum wing tank fuel load with full ventral tank Aircraft on ground - 1000 lb. each wing. Aircraft prepared for flight - 2450 lb. each wing. Maximum wing load imbalance - 500 lb.

D. PREPARATION

1. Aircraft status.

WARNING

APU operation is not permitted while refueling or defueling operations are in progress.

CAUTION

Do not position any ground equipment under aircraft during fueling operations as aircraft settles under weight of fuel load. Fuel tank vapors, which vent at wing tips, will increase significantly during fueling operations, as well as being prevalent at the open wing tank filling points.

4-1



(Con't.)

2. Remove all unnecessary ground equipment. ( )

3. Place wheel chocks front and rear approximately one inch away from tires. ( )

4. Position fire extinguisher(s). ( )

5. Confirm refueling source, type, and grade. ( )

WARNING

Aircraft and fueling truck must be correctly grounded before any fueling operation, to prevent the possibility of fire or explosion due to discharge of static electricity. APU must not be running and no power must be applied to the aircraft while fuel tanks are open during fueling operations.

6. Refueling equipment and aircraft grounded:


b. Ground cable from fueling truck to


CAUTION


7. Drain water from fuel tanks, wing, and ventral. ( ) 8. Close both LP cocks. ( ) 9. Check WING FUEL/X FEED/TRANSFER

lever to WING FUEL. ( ) 10. Check AUX FUEL TRANSFER lever is closed. ( )

4-2



(Con't.) E. REFUELING PROCEDURES – WING TANKS TO FULL

1. Ground fuel truck hose nozzle to aircraft. ( ) 2. Unlock and remove fuel tank filler cap, insert

nozzle and refuel as required. (Both tanks simultaneously, if possible.) ( )

3. Adjust fuel truck pump output pressure for suitable flow rate. ( )

WARNING

Stop refueling in the event of fire, fuel leakage, or spillage.

NOTE

Wing tanks are full when fuel level reaches the filler neck flap valve. Allow fuel to settle for approximately two minutes to ensure satisfactory contents indication.

4. Reduce fuel truck pump output pressure to zero. ( )

5. Remove refuel hose nozzle from fuel tank, fit

and lock filler cap. ( ) 6. Disconnect fuel truck hose nozzle ground from

aircraft. ( ) 7. Check and log total fuel uplift. ( ) 8. Disconnect fuel truck ground. ( ) 9. Carry out fuel water check. ( )

NOTE

If water drain check is carried out too soon after refueling, sample will be cloudy due to water being in suspension. Where possible, wait 30 minutes before carrying out check.

4-3



4-4


VENTRAL TANK REFUEL BY TRANSFER A. REFERENCES

Personnel required to accomplish ventral tank refuel by transfer operations shall be familiar with BAe 125-800A Maintenance Manual Procedures.

B. PERSONNEL REQUIRED Supervisor/Refueler Designated Flight Crewmember


External power unit 28 Volts DC with current limiter at 1100 amps.

D. GENERAL

Limitations Minimum wing tank fuel load with full ventral tank: Aircraft on ground - 1000 lb. each wing. Aircraft prepared for flight - 3450 lb. each wing. Maximum wing load imbalance - 500 lb.

E. VENTRALTANK REFUEL PROCEDURE

1. Aircraft status. ( ) 2. Remove all unnecessary ground equipment. ( ) 3. Wheel chocks in place. ( ) 4. Position fire extinguisher(s) ( ) 5. Aircraft correctly grounded. ( )

CAUTION


5-1


VENTRAL TANK REFUEL BY TRANSFER (Con't.)

6. Drain water from fuel tanks. ( ) 7. Connect external power supply. ( ) 8. External power switch to ON. ( ) 9. Check all unnecessary electrical loads OFF. ( ) 10. Check fuel load is 4000 lbs. or over. ( ) 11. Refuel MASTER VALVE switch to ON. ( ) 12. Refuel MASTER VALVE indicator OPEN. ( ) 13. MWS FUEL ↑ annunciator lit. ( ) 14. Roof panel REFUEL ON annunciator lit. ( ) 15. Refuel panel VENTRAL switch to REFUEL. ( ) 16. Ventral fuel VALVE indicator OPEN. ( ) 17. AUX FUEL TRANSFER lever selected

CLOSED. ( ) 18. WING FUEL/X FEED TRANSFER lever to

WING FUEL. ( ) 19. Both HP cocks OFF. ( ) 20. Both HP cocks ON. ( ) 21. Both fuel L PUMP and R PUMP switches to ON.( ) 22. Both FUEL LO PRESS annunciators OUT. ( ) 23. Ventral tank contents indicator from EMPTY

to cross hatched. ( ) 24. Wing fuel gauge readings start to fall. ( )

5-2


VENTRAL TANK REFUEL BY TRANSFER

(Con't.)

CAUTION

Operate fuel pump switches to maintain balance between each wing fuel load during this procedure. Do not allow either wing fuel contents to fall below 1000 lbs.

25. Ventral tank contents indicator from cross hatched to FULL and refuel panel ventral tank indicator to FULL. ( )

26. Refuel panel ventral fuel VALVE indicator

SHUT. ( )

27. Ventral tank switch to OFF. ( ) 28. Refuel MASTER switch to OFF. ( ) 29. Refuel MASTER VALUE indicator SHUT. ( ) 30. MWS FUEL ↑ annunciator OUT. ( ) 31. Roof panel REFUEL ON annunciator OUT. ( ) 32. Both fuel L PUMP and R PUMP switches to

OFF. ( ) 33. External power switch to OFF. ( ) 34. Disconnect and remove external power set. ( )

5-3



5-4


DEFUEL – SUCTION METHOD

A. REFERENCES

Personnel required to accomplish defuel operations shall be familiar with BAe 125-800A Aircraft Maintenance Manual Procedures.


Defueling Supervisor/Defueler

C. GENERAL

Limitations Maximum suction - 11.0 psi Minimum wing tank fuel load with full Ventral tank: Aircraft on ground - 1000 lb. each wing Aircraft prepared for flight - 3450 lb. each wing Maximum wing load imbalance - 500 lb.

D. PREPARATION

1. Aircraft status. ( ) 2. Remove all unnecessary ground equipment. ( ) 3. Check wheel chocks tight against tires. ( ) 4. Position fire extinguisher(s). ( ) 5. Confirm defueling truck type and grade. ( )

WARNING

APU operation is no permitted while refueling or defueling operations are in progress.

6-1


DEFUEL – SUCTION METHOD (Con't)

WARNING

Aircraft and defueling truck must be correctly grounded, before any defuel operation, to prevent the possibility of fire or explosion due to discharge of static electricity.

6. Defueling equipment and aircraft grounded:


b. Ground cable from defuel, truck to approved common ground. ( ) c. Ground cable from defuel truck to aircraft. ( )

CAUTION

Investigate any contamination (other than water) of drained sample.

7. Drain water from fuel tanks. ( ) 8. Ensure fuel L and R PUMP switches OFF. ( )

WARNING

APU cannot be used as power source for defueling.

9. Select either external or battery power supply. ( ) 10. Ensure all unnecessary electrical loads are OFF. ( ) E. DEFUELING PROCEDURE

1. Open SPR fuel coupling access cover. ( ) 2. Remove SPR fuel coupling blanking cover. ( ) 3. Connect defuel hose nozzle to SPR fuel coupling. ( ) 4. Close both engine LP cocks. ( ) 5. Set refuel control panel MASTER switch to ON. ( )

6-2



6. Check MASTER VALVE indicates OPEN. ( )

NOTE

The ventral tank must be off-loaded completely with any precise load adjustments made in wing tanks.

7. MWS FUEL ↑ annunciator lit. ( ) 8. Roof panel REFUEL ON annunciator lit. ( ) 9. Set VENTRAL REFUEL-OFF-DEFUEL

switch to DEFUEL. ( ) 10. Check ventral tank VALVE indicates OPEN. ( )

CAUTION

Do not exceed maximum defuel suction of 11 psi.

11. Adjust fuel truck suction valve to commence defuel. ( ) 12. Continue defuel until ventral tank indicates

EMPTY. ( ) 13. Check ventral tank VALVE indicates shut. ( ) 14. Set VENTRAL REFUEL-OFF-DEFUEL switch

to OFF. ( ) 15. Open both engine LP cocks. ( )

NOTE

When ground power is available, wing defueling can be assisted by switching fuel L and R PUMP switches ON.

16. Ensure MASTER VALVE indicates OPEN. ( )

6-3



NOTE Continue defuel until tank contents gauges indicate desired fuel load, or tanks are empty. If tanks defuel unequally, close LP cock on tank, which reaches desired fuel quantity first.

17. Turn off refuel control panel MASTER switch. ( ) 18. Check MASTER VALVE indicates CLOSED. ( ) 19. MWS FUEL ↑ annunciator out. ( ) 20. Roof panel REFUEL ON annunciator out. ( ) 21. Close both engine LP cocks. ( ) 22. Remove aircraft electrical power. ( ) 23. Disconnect defuel hose nozzle from SPR

coupling. ( ) 24. Install SPR coupling blanking cover. ( ) 25. Install SPR coupling access cover. ( ) 26. Check and log total fuel downloaded. ( )

6-4


FUEL TRANSFER

A. REFERENCES

Personnel required to accomplish fuel transfer operations shall be familiar with BAe 125-800A Aircraft Maintenance Manual procedures.

B. PERSONNEL REQUIRED Fuel Supervisor Refueler C. EQUIPMENT AND MATERIALS

External power unit 28 Volts DC, with current limiter at 1100 amps.

D. GENERAL Limitations Minimum wing tank fuel load with full ventral tank: Aircraft on ground - 1000 lb. each wing Aircraft prepared for flight - 3450 lb. each wing Maximum wing load imbalance - 500 lb. E. FUEL TRANSFER PREPARATION

1. Check aircraft status. ( ) 2. Check wheels chocked. ( ) 3. Position fire extinguisher(s). ( ) 4. External power unit connected and running. ( ) 5. L and R PUMP switches OFF. ( ) 6. EXT PWR switch ON. ( ) 7. Close both engine LP cocks. ( ) 8. WING FUEL/X FEED/TRANSFER cock to WING FUEL. ( )

7-1


FUEL TRANSFER (Con't.)

9. Close AUX FUEL TRANSFER cock. ( ) 10. Check fuel contents gauges and ensure that

tanks can accept proposed fuel load transfer. ( )

F. VENTRAL TANK TO WING TRANSFER 1. Open AUX FUEL TRANSFER cock. ( ) 2. AUX FUEL TFR annunciator lit. ( ) 3. MWS FUEL XFD/TFR repeater annunciator lit. ( ) 4. L and R PUMP switches ON. ( ) 5. VENTRAL TANK indicator changes from

FULL to cross-hatched. ( ) 6. Check each wing contents indication increases

slowly. ( ) 7. VENTRAL TANK indicator changes from

cross-hatched to EMPTY. ( ) 8. L and R PUMP switches OFF. ( ) 9. Check left and right wing contents gauges

balanced. ( ) 10. Close AUX FUEL TRANSFER cock. ( ) 11. AUX FUEL TFR annunciator out. ( ) 12. MWS FUEL SFD/TFR repeater annunciator

out. ( )

G. WING TO WING TRANSFER

1. WING FUEL/X FEED/TRANSFER cock to TRANSFER. ( )

2. WING FUEL XFD/TFR

ANNUNCIATOR LIT. ( )

7-2


FUEL TRANSFER (Con't.)

3. MWS FUEL XFD/TFR ↑ repeater

annunciator lit. ( ) 4. Appropriate L or R PUMP switch ON. ( )

NOTE

Selection of L PUMP switch to ON transfer fuel from right wing to left wing. Selection of R PUMP switch to On transfers fuel from left wing to right wing.

5. Set L or R PUMP switch to OFF as wing

fuel loads balance. ( ) 6. WING FUEL/X FEED TRANSFER cock

to WING FUEL. ( ) 7. WING FUEL XFD/TFR annunciator out. ( ) 8. MWS FUEL XFD/TFR ↑ repeater annunciator

out. ( )

H. SHUT DOWN 1. EXT PWR switch off. ( ) 2. External power unit off. ( )

7-3



7-4


APU OIL

A. REFERENCES

Personnel required to accomplish APU oil servicing shall be familiar with BAe 125-800A Aircraft Maintenance Manual procedures.

B. PERSONNEL REQUIRED One mechanic C. EQUIPMENT AND MATERIALS

CAUTION

One type of oil shall not be mixed with any other type of oil. If the oil indication is low and the type of oil in use is not available, the oil sump must be drained completely and replenished with another oil. The oil filter element should be changed if a new element is available. The following oils meet approved specifications.

Oils to conform to MIL-L-23699. Approved engine oils: Aeroshell 500 Exxon 2380 Aeroshell 560 Mobil Jet II Castrol 5000 Mobil jet 254

D. OIL SERVICING PROCEDURE 1. Check oil level on sight gauge. ( )

NOTE

APU should be level and oil hot when checking oil level.

If oil level requires topping up, proceed with the following operations: 2. Remove APU oil filler cap. ( )

8-1


APU OIL (Con't.)

3. Top up APU oil level with the same type of

oil in use. ( )

CAUTION

Do not allow oil level to be above "full" mark on sight gauge. An overfilled sump will result in oil foaming and low oil pressure.

4. Replace APU oil filler cap. ( )

8-2


ENGINE OIL

A. REFERENCES

Personnel required to accomplish engine oil servicing shall be familiar with BAe 125-800A Aircraft Maintenance Manual procedures.

B. PERSONNEL REQUIRED Mechanic or designated flight crewmember. C. EQUIPMENT AND MATERIALS

Oils to conform to MIL-L-23699. Approved engine oils: Aeroshell 500 Exxon 2380 Aeroshell 560 Mobil Jet II Castrol 5000 Mobil Jet 254

D. GENERAL

a. Capacities

US Pints Total capacity of system Total capacity of tank Consumable

25.0 13.2 3.0

E. SERVICING ENGINE OIL SYSTEM

WARNING

Synthetic oil can be toxic – avoid prolonged contact with the skin.

CAUTION Do not allow oil to contaminate the aircraft or exterior of the engine. a. Check engine oil contents.

9-1


ENGINE OIL (Con't.)

1. Check level of oil at the oil tank sightglass visible through the viewing port in the cowling lower access door. ( )

NOTE

Check oil level within 30 minutes of engine shut down. If the oil level is not checked within this period, start the engine and run at idle for five minutes, then check the oil level. The oil level is indicated at the bottom of the sight glass float ball.

2. Record quantity. ( )

b. Replenish engine oil via oil tank (right hand engine).

1. Open cowling lower door. ( )

2. Gain access to oil tank on the right-hand side of engine. ( )

3. Push oil tank filler cap down (do not force), turn 90 degrees counter-clockwise and lift from tank. ( )

CAUTION

Ensure the oil container is clean.

4. Fill oil tank until level at the sight glass Registers FULL. ( )

5. Inspect and renew filler cap seal if

necessary. ( ) 6. Insert filler cap into tank, push down

(do not use force) and turn 90 degrees clockwise to secure. ( )

7. Close cowling lower access door. ( ) 8. Record quantity serviced. ( )

c. Replenish engine oil via filler tube (left-hand engine).

9-2


ENGINE OIL (Con't.)

1. Open cowling lower door. ( ) 2. Gain access to the oil filler tube on the left-hand side of engine. ( ) 3. Push filler cap down (do not use force),

turn 90 degrees counter-clockwise and lift out. ( )

CAUTION

Ensure the oil container is clean.

4. Fill oil tank until level at the sight glass

registers FULL. ( ) 5. Inspect and renew filler tube cap seal,

if necessary. ( ) 6. Insert filler cap into filler tube, push down,

(do not use force) and turn 90 degrees clockwise to secure cap. ( )

7. Record quantity serviced. ( ) 8. Close cowling lower access door. ( )

9-3



9-4


HYDRAULICS

A. REFERENCES Personnel required to accomplish hydraulic servicing shall

be familiar with BAe 125-800A Maintenance Manual procedures.

B. PERSONNEL REQUIRED One mechanic. C. EQUIPMENT AND MATERIALS Spanner, reservoir filler cap BAe 25Y 189A Flashlight. Hydraulic fluid MIL-H-5606E D. GENERAL

Tank capacity:

Reservoir US pints Main Auxiliary

19.22 6.01

E. HYDRAULIC SYSTEM SERVICING a. Check main system reservoir contents.

1. Ensure landing gear DOWN and

airbrakes SHUT. ( ) 2. Gain access to main reservoir in

fuselage rear equipment bay. ( ) 3. Check accumulator pressure gauges

and note readings. ( ) 4. Check fluid level in level indicator tube

against appropriate markings on adjacent label for readings noted. ( )

b. Replenish main system reservoir.

10-1


HYDRAULICS (Con't.)

WARNING

Hydraulic fluid may cause skin irritation. Avoid prolonged or repeated contact with the skin. In case of eye contact, flush the eyes with water and obtain medical aid. In case of ingestion, obtain medical aid.

CAUTION

Before replenishing, ensure that filter in filler neck is in position and undamaged. Always use clean hydraulic fluid.

1. Cut lockwire from reservoir filler cap. ( ) 2. Loosen reservoir filler cap slowly with

spanner allowing residual pressure to release and gauge reading to fall to zero. ( )

3. Replenish reservoir as necessary. ( ) 4. Check contents level. ( ) 5. Check that pressure release in filler

cap is unobstructed and that sealing ring is undamaged and correctly seated. ( )

6. Install filler cap and wirelock. ( ) 7. Clean up any spilt fluid. ( ) c. Check auxiliary system reservoir contents.

1. Release front radome fasteners. ( ) 2. Secure radome in open position. ( ) 3. Remove "Velcro" secure fabric cover on forward bulkhead. ( ) 4. Check auxiliary system reservoir fluid level in indicator tube. ( )

d. Replensih auxiliary tank.

10-2


HYDRAULICS (Con't.)

1. Cut lockwire and remove filler cap from

tank. ( ) 2. Replenish tank until fluid visible in filler

neck rises to top of level indicator tube. ( ) 3. Check that sealing ring on filler neck is

undamaged and correctly seated. ( ) 4. Install filler cap and wirelock. ( ) 5. Energize PE busbar. ( ) 6. Check that the AUX HYD LO LEVEL

annunciator on the MWS panel does not illuminate. ( )

7. De-energize PE busbar. ( ) 8. Clean up any spilt fluid. ( ) 9. Refit "Velcro" secured fabric cover on

forward bulkhead. ( ) 10. Close front radome and secure fasteners. ( )

10-3



10-4


ICE AND RAIN PROTECTION

A. REFERENCES Personnel required to accomplish ice and rain protection

servicing shall be familiar with BAe 125-800A Maintenance Manual procedures.

B. PERSONNEL REQUIRED One mechanic. More personnel may be required

depending on the severity of the conditions. C. EQUIPMENT AND MATERIALS

Fluid specification TKS fluid R328 or fluid to Specification DTD 406B or TKS P .208 (TKS 80). D. GENERAL

Tank capacity 5.5 US gallons.

E. AIRFRAME DEICING SYSTEM

a. Prime aircraft system

1. Energize PS2 busbar. ( )

2. Check that system contents gauge Indicates at least 1/4 FULL. ( )

3. Depress vent valve adjacent to tank filler cap for at least ten seconds. ( )

4. Set the WING/TAIL ANTIICE time switch

to run for two minutes. ( ) 5. Check that fluid flows from all

distributor panels. ( )

NOTE

If fluid does not flow reselect, the time switch for brief periods until flow occurs.

11-1


ICE AND RAIN PROTECTION (Con't.)

b. Replenish airframe system tank

1. Check system is fully primed. ( ) 2. Remove tank filler cap. ( ) 3. With reference to system gauge fill the tank. ( ) 4. View through filler neck and check that tank is full. ( )

NOTE Replenishing fluid should not be at a temperature lower than 0 degrees C.

5. Check that filler cap washer is

serviceable. ( ) 6. Fit and tighten filler cap. ( ) 7. Clean off any spilt fluid. ( ) 8. De-energize PS2 busbar. ( ) F. REMOVE HOAR FROST, SNOW OR ICE

The procedures in TI 4100.30, "Aircraft Deicing/Anti- Icing/Cold Weather Ground Operation Manual, take precedence over these procedures.

WARNING Remove all snow, ice and hoar frost before flight.

a. Equipment and Materials

A power operated defrosting plant cart, of adequate fluid capacity, capable of delivering heated fluid and equipped with spray lances. Ground servicing stands, to enable an operator to direct the spray down onto the aerofoil surfaces.

11-2



WARNING

Deicing fluids have a limited period of effectiveness. Observe the safe period appropriate to the strength and properties of the fluid used. Kilfrost ABC (DTD 900/4907). Kilfrost WWF MOD2 (DTD 900/4939) for acrylic windows.

CAUTION Although the fluid passes the DTD crazing test for transparent panels, take care to prevent damage by overheating, which will occur if hot spray is concentrated on one panel for an excessive time.

b. General application

WARNING During these operations the surfaces will be very slippery due to the snow, ice or deicing fluid; use a servicing stand whenever possible. Failing this, use mainplane mats and safety belts and take other similar precautions. When applying the deicing fluids, always stand windward of the aircraft. Use goggles and wear suitable protective clothing.

CAUTION

The deicing fluid used must be to a concentration and a temperature in accordance with the fluid manufacturer's instructions provided the following limitations are not exceeded. The temperature of the fluid applied to the aircraft must not exceed 80 deg. C (176 deg.F) and if the spray rate per lance exceeds ten gallons/minute, reduce the temperature to 60 deg.C (140 deg.F).

11-3



Before applying fluid make certain that covers and blanks are fitted to the following: Static vents Pitot heads Stall detector vane. Ground the Aircraft. To prevent possible ingestion of deicing fluid, do not operate APU while deicing is in progress. After clearing snow from the surfaces, make certain the following are free from snow or ice:

(1) All air intakes.

(2) Control surface hinges.

(3) Gaps between wing trailing edge shroud and flaps, airbrakes and ailerons.

(4) Gaps between horizontal stabilizer and

elevators.

(5) Gaps between rudder and vertical stabilizer.

(6) Wheel brakes.

(7) Landing gear bays.

(8) All doors and external drains.

(9) Cold air unit ram air exhaust outlet and duct.

c. Remove hoar frost

1. Spray with deicing fluid diluted to fluid

manufacturer's instructions. ( )

NOTE

Under severe frost forming conditions after defrosting, give a further light application of the concentrated fluid to ensure the maximum hold- over period.

11-4



d. Remove sleet and freezing rain

1. Spray with undiluted deicing fluid. ( )

CAUTION

After spraying, examine surface thoroughly, as ice formed by freezing rain can be difficult to see under the deicing fluid.

e. Remove snow – Dry

CAUTION

Care should be taken to avoid damaging the vortex generators on the wing top surface. 1. Remove snow by brushing surfaces. ( ) 2. Check that no snow has been trapped in control surfaces gaps or hinges. ( )

NOTE

If the ambient temperature is above freezing, the snow can be removed by the application of a hot air blast and the cleared surfaces sprayed with diluted deicing fluid.

f. Remove Snow – Wet

1. Remove snow with rubber squeegees. ( ) 2. Check that no snow has been trapped

in control surfaces gaps or hinges. ( )

NOTE If ice formed under the snow, clear by spraying with deicing fluid.

g. Frozen snow and ice films

1. Remove loose snow. ( )

11-5



2. Apply a heavy spray of fluid per

manufacturer's instructions. ( ) 3. Brush snow as fluid is being applied. ( ) 4. Check all frozen deposits have been removed. ( ) 5. Apply a final light spray of deicing fluid. ( )

NOTE

If the ambient temperature is above freezing, ducted hot air blasts may be used to disperse the ice.

CAUTION

Do not use hot air blasts near windows. Take

extreme care to prevent damage by overheating to painted surfaces, rubber, glass, acrylic or glass fiber, hydraulic pipelines, grease or oiled surfaces.

h. Deicing windshield

1. Apply a light spray of Kilfrost deicing fluid

WWW MOD2 to windshield. ( ) 2. Clean any smearing with a warm damp rag. ( )

11-6


LANDING GEAR/TIRES

A. REFERENCES

Personnel required to accomplish landing gear or tire servicing shall be familiar with the BAe 125-800A Maintenance Manual procedures.


Two mechanics.


Nitrogen Cart Turner inflation adapter - Turner 772 Gauge (0-600 psi) - Turner F29/24/600 Gauge (0-1500 psi) - Turner F29/24/1500

WARNING

The use of high pressure nitrogen bottles is required and it is essential that a suitable pressure reducing valve is incorporated in the delivery line.

CAUTION

If nitrogen is not available, it is permissible to use dry air for inflation provided that, at the earliest opportunity, the nose or main leg is completely recharged with nitrogen. It is recommended that only nitrogen be used for inflation.

D. NOSE AND MAIN GEAR ASSEMBLIES SERVICING

a. Check nitrogen inflation pressures

1. Remove nose/main leg charging point blanking cap. ( )

2. Install inflation adapter with gauge. ( ) 3. Check nose main leg pressure. ( )

12-1


LANDING GEAR/TIRES (Con't.)

4. Check that the extension of the leg is

correct for the pressure indicated. (Figure 12-1 and Figure 12-2). ( )

NOTE

Should the leg extension be incorrect, refer to BAe 124-800A Maintenance Manual Chapter 32 – Main Leg Assembly or Nose Leg Assembly, as appropriate.

5. Remove inflation adapter. ( ) 6. Refit nose/main leg charging point

blanking cap. ( )

b. Inflate nose/main leg assemblies

1. Examine leg for signs of oil leakage. ( ) 2. Remove nose/main leg charging point blanking cap. ( ) 3. Install inflation adapter with gauge to charging point. ( ) 4. Connect nitrogen supply to inflation adapter. ( ) 5. Inflate as necessary with nitrogen until pressure/extension is within limits given. ( ) 6. Shut off charging supply. ( ) 7. Disconnect charging equipment. ( ) 8. Check for leaks. ( ) 9. Refit charging point blanking cap. ( )

12-2



MAIN GEAR PRESSURE/EXTENSION CHART

Figure 12-1

12-3


LANDING GEAR/TIRES (Con't.) NOSE GEAR PRESSURE/EXTENSION CHART

Figure 12-2

E. AIRCRAFT TIRES SERVICING

NOTE

After landing there will be a rise in main wheel tire pressure to brake heat. Allowance must be made for this pressure rise when checking tire pressures if the duration of the stop does not permit waiting for the gas in the tire to cool.

a. Check tire pressures

1. Remove dust cap. ( ) 2. Connect inflation connector. ( ) 3. Check tire pressure using inflation gauge (pressure range 0-200 psi) against Table 1. ( )

12-4



TIRE PRESSURES - psi

Main Wheels Nose Wheels

+10 137

-0

+10 100

-0

TABLE #1 NOTE

Pressures apply with aircraft weight on wheels.

4. Disconnect inflation connector. ( ) 5. Install dust cap. ( )

b. Inflate tires

CAUTION

If nitrogen is not available, it is permissible to use dry air for inflation provided that at the earliest opportunity but not later than after a further 25 flying hours, the tire is completely recharged with nitrogen.

NOTE The use of high pressure nitrogen bottles is required and it is essential that a suitable pressure reducing valve is incorporated in the delivery line. 1. Remove dust cap. ( ) 2. Connect inflation connector. ( ) 3. Connect nitrogen source. ( ) 4. Inflate tires as required. ( ) 5. Shut off nitrogen supply. ( ) 6. Disconnect nitrogen source. ( ) 7. Remove inflation connector. ( ) 8. Install dust cap. ( )

12-5



12-6


OXYGEN SERVICING

A. REFERENCES

Personnel required to accomplish oxygen servicing shall be familiar with BAe 125-800A Aircraft Maintenance Manual procedures.

B. PERSONNEL REQUIRED Two mechanics. C. EQUIPMENT AND MATERIALS

Aviator's breathing oxygen.

D. OXYGEN SYSTEM SERVICING a. Check system contents.

1. Open master SUPPLY valve on oxygen panel on left console. ( )

2. Check contents on adjacent indicator. ( ) 3. Close master SUPPLY valve. ( ) b. Replenish oxygen system

WARNING

Oil or grease in contact with oxygen forms an explosive mixture. All servicing must be effected with degreased tools and clean hands. 1. Open charging point access door on right hand side of rear fuselage. ( ) 2. Remove charging valve cap. ( )

WARNING

Never allow hose end fitting to contact ground or any other unclean surface.

3. Connect hose from oxygen cart. ( ) 4. Open delivery valve. ( )

13-1


OXYGEN SERVICING (Con't.)

WARNING This system must be charged slowly. Rapid filling will cause the automatic shut-off valve to be reset. Rapid charging will create a dangerous overheat condition in the oxygen cylinders.

5. Adjust regulator valve to charge system slowly until contents gauge reads FULL. ( ) 6. Close delivery valve and allow system to stabilize. ( ) 7. Check system contents gauge still indicates FULL. ( ) 8. Replenish system further if necessary until gauge indicates FULL when stabilized. ( )

9. Close delivery valve and open system

master SUPPLY valve. ( ) 10. Check system contents indicator on flight deck reads same as contents indicator at the charging point. ( ) 11. Close system master SUPPLY valve and check oxygen delivery valve closed. ( ) 12. Disconnect hose from oxygen cart. ( ) 13. Refit valve cover. ( ) 14. Secure oxygen charging point access panel. ( )

13-2


TOILET SERVICING A. REFERENCES

Personnel required to accomplish toilet servicing shall be familiar with BAe 125-800A Aircraft Maintenance Manual procedures.

B. PERSONNEL REQUIRED One mechanic. C. EQUIPMENT AND MATERIALS

Toilet ground servicing Tronair 10-4036-000 cart (fitted with Kaiser Roylyn special "Y" coupling Pt. No. K1052) or equivalent low level cart. Drain plug extraction handle Kaiser Roylyn T4090 Toilet deodorant Monogran DG-19 (4 ounces) Receptacle 8 gallon capacity Fresh water

NOTE

If specified ground servicing cart is not available, toilet servicing must be carried out using gravity discharge procedure (see BAe 125-800A Aircraft Maintenance Manual, Chapter 12-38).

D. SERVICE TOILET: (External servicing facility) 1. Open toilet service point access panel. ( ) See Figure 1 (Sheet 1 of 2) 2. Examine service point for signs of leakage. ( ) 3. Unlock drain cap handle. ( ) 4. Connect ground servicing cart drain hose to aircraft drain with special "Y" coupling. ( ) 5. Push "T" handle inward to engage drain plug. ( )

14-1


TOILET SERVICING (Con't.)

6. Rotate handle counter-clockwise approximately 120 degrees to release plug and pull out handle. ( ) 7. Pull and hold toilet drain valve operating handle to dump waste into sewage line. ( ) 8. Make sure toilet tank empties completely. ( ) 9. Operate lever on ground flush connection cap. ( )

10. Remove ground flush connection cap. ( )

11. Connect servicing cart water supply hose to ground flush connection. ( ) 12. With toilet drain valve in open position, pump approximately two gallons of clean water from cart to flush rinse toilet tank. 13. Allow water to drain. ( ) 14. Close drain valve operating handle. ( ) 15. Push "Y" coupling "T" handle in to insert plug. ( ) 16. Rotate "T" handle approximately 120 degrees clockwise to secure plug. 17. Remove "T" handle.

NOTE

If handle is difficult to withdraw, the drain plug is not properly locked; repeat insertion of plug.

18. Disconnect drain coupling. ( ) 19. Charge tank through ground flush connection with 1.5 US gallons of clean water. ( )

20. Press toilet flush button once. ( )

14-2


TOILET SERVICING (Con't.)

NOTE

To protect toilet recirculation system against freezing temperatures, add anti-freeze to the flush liquid in the ratio recommended by the anti-freeze manufacturer. 21. Check drain plug for signs of leakage. ( ) 22. Close hinged cap. ( ) 23. Secure drain cap handle. ( ) 24. Disconnect ground flush hose and allow pipe to drain. ( ) 25. Fit and secure ground flush connection blanking cap. ( ) 26 Close and secure service point access panel. ( )

14-3



14-4


WATER SERVICING

A. REFERENCES

Personnel required to accomplish water servicing shall be familiar with BAe 125-800A Aircraft Maintenance Manual Chapter 12-38.


Potable water cart Water container 5.10 US gallons Shallow receptacle 2.0 US gallons Water receptacle 4.5 US gallons

D. DRAIN GALLEY WATER SYSTEM 1. Ensure BREWER CONTROL (P9) and GALLEY LIGHTS (Q7) circuit breakers are closed. ( ) 2. Connect suitable length of transparent plastic tubing to multibrewer cold water output spout and rest free end of tubing on galley drain grill. ( )

NOTE

Position suitable container under aircraft external overboard drain, if required. Alternatively use longer piece of plastic tubing and feed water directly into suitable container inside the aircraft. 3. Energize PS2 busbar. ( ) 4. Push GALLEY POWER switch to on. Check lit. ( ) 5. Set multibrewer POWER switch to ON and HEATER switch to OFF. ( )

15-1


WATER SERVICING (Con't.)

6. Press and hold multibrewer COLD WATER push button and ensure that water flows from spout. ( ) 7. Release COLD WATER button when galley water tank is empty and flow ceases. ( ) 8. Set multibrewer POWER switch to OFF. ( ) 9. Remove plastic tubing from multibrewer cold water output spout. ( )

10. De-energize PS2 busbar. ( ) E. FILL AND PRIME GALLEY WATER SYSTEM

1. Remove galley drain grill. ( ) 2. Remove water tank filler cap. ( )

CAUTION During freezing conditions water systems should not be serviced. 3. Fill tank to bottom of filler neck. 4. Ensure BREWER CONTROL (P9) and GALLEY LIGHTS (Q7) circuit breakers are closed. ( ) 5. Energize PS2 busbar. ( ) 6. Push GALLEY POWER switch to on. Check lit. ( ) 7. Set multimeter POWER switch to ON and HEATER switch to OFF. ( )

8. Push and hold COLD WATER button. Release when flow of water comes from output spout. ( ) 9. Top up main water tank. ( )

15-2



10. Check condition of filler cap and sealing washer. ( ) 11. Replace filler cap. ( ) 12. Install galley drain grill. ( ) 13. Set multibrewer POWER switch to OFF. ( ) 14. De-energize PS2 busbar. ( )

F. DRAIN WASH WATER SYSTEM 1 Place suitable receptacle below waste water drain fairing on right side of rear fuselage (if required). ( ) 2. Open WATER HEATER circuit breakers (P3, P4 and P5) and ensure TOILET WASH PUMP (P6) and GALLEY LIGHTS (Q7) circuit breakers are closed. ( ) 3. Energize PS2 busbar. ( ) 4. Push GALLEY POWER and TOILET WASH WATER switches on. Check both lit. ( ) 5. Press and hold wash basin drain button. ( ) 6. Open tap knob until faucet ceases to run. ( ) 7. Release drain button and close tap knob. ( ) 8. Push TOILET WASH WATER switch off. ( ) 9. De-energize PS2 busbar. ( ) 10. Attach safety clips and flags to hold WATER heater CIRCUIT BREAKERS (P3, P4 AND P5) open to prevent use while water tank is drained. ( ) 11. Remove receptacle from below waste water drain fairing (if required). ( )

15-3



G. FILL AND PRIME WASH WATER SYSTEM

1. Place suitable receptacle below waste waster drain fairing on right side of rear fuselage (if required). ( ) 2. Remove toiletries tray from top of toilet console to gain access to tank filling point. ( )

CAUTION

During freezing conditions tank should not be serviced. 3. Remove sealing plug and fill wash water tank with clean fresh water. ( ) 4. Ensure all three WATER HEATER (P3, P4 and P5), TOILET WASH PUMP (P6) and GALLEY LIGHTS (Q7) circuit breakers are closed. ( ) 5. Energize PS2 busbar. ( ) 6. Push GALLEY POWER switch to on. Check lit. ( ) 7. Push TOILET WASH WATER switch on. ( ) 8. Open tap knob and release as soon as airfree water flows into washbasin. ( )

NOTE

Airfree water flow confirms system primed. 9. Press and hold drain button until washbasin is empty. ( ) 10. Top-up water tank. ( ) 11. Install sealing plug. ( ) 12. Replace toiletries tray. ( ) 13. Push TOILET WASH WATER switch to off. ( )

15-4



14. De-energize PS2 busbar. ( ) 15. Remove receptacle from below waste water drain fairing (if required). ( )

15-5



15-6


APPLYING ELECTRICAL POWER

A. REFERENCES

Personnel required to apply electrical power to the aircraft shall be familiar with BAe 125-800A Maintenance Manual procedures.


External power cart 28 Volts DC, with current limiter at 1100 amps.

D. APPLY EXTERNAL POWER

WARNING

Prior to applying electrical power, ensure that personnel are not removing or installing electrical/electronic equipment. High voltages can be fatal. 1. Aircraft status. ( ) 2. BATTERY switch OFF. ( ) 3. BATT ISOLATE switch centered. ( ) 4. EXT BATT CHG switch OFF. ( ) 5. EXT. POWER switch OFF. ( ) 6. AUX COOLING PACK switch OFF. ( ) 7. STBY INV switch OFF. ( ) 8. SCREEN HEAT L and R switches OFF. ( ) 9. PITOT/VANE HEAT L and R switches OFF. ( ) 10. ENG ANTIICE 1 and 2 switches OFF. ( ) 11. ENG IGNITION 1 and 2 switches OFF. ( )

16-1


APPLYING ELECTRICAL POWER (Con't.)

12. ENG CMPTR 1 and 2 switches OFF. ( ) 13. L PUMP and R PUMP switches OFF. ( ) 14. ENG SYNC switch OFF. ( ) 15. FIRE ENG 1 EXT and ENG 2 EXT switches centralized. ( ) 16. EXT 1 FIRED and EXT 2 FIRED indicators clear. ( ) 17. Connect electrical ground power cart to aircraft. ( ) 18. Switch power cart on. ( ) 19. Set aircraft EXT POWER switch ON. ( ) 20. Cancel MWS repeater flasher. ( ) 21. Check following DC POWER annunciators on: GEN 1 FAIL ( ) GEN 2 FAIL ( ) BATT 1 CNTCTR ( ) BATT 2 CNTCTR ( ) BUSTIE OPEN ( ) 22. Check busbar and battery voltages using DC VOLTS meter and switch. ( ) 23. AUX COOLING PACK switch as required. ( ) 24. FIS POWER switch as required. ( ) 25. EXT BATT CHG switch ON (as required). ( ) 26. Check batteries 1 and 2 charge current between 5 and 40 amps. ( )

16-2


APPLYING ELECTRICAL POWER (Con't.)

N O T E

Batteries will drop off-line automatically if bus voltage goes outside limits 24.5 to 29.5 volts. To reset, recycle EXT BATT CHG switch to OFF then ON.

E. DISCONNECT EXTERNAL POWER

1. AUX COOLING PACK switch OFF. ( ) 2. FIS POWER switch OFF. ( ) 3. EXT BATT CHG switch OFF. ( ) 4. APU MASTER switch OFF. ( )

CAUTION The APU MASTER switch which energizes the APU fuel pump directly from No. 2 Battery should never be left in the ON position with the APU not running as fuel pump cavitation can occur with subsequent pump damage or failure. No. 2 Battery could also be drained. 5. EXT POWER switch OFF. ( ) 6. Switch power cart OFF. ( ) 7. Disconnect power cart from aircraft. ( )

16-3



16-4


APU GROUND OPERATION

A. REFERENCES

Personnel required to accomplish APU ground operation shall be familiar with BAe 125-800A Maintenance Manual procedures.

B. PERSONNEL REQUIRED 1 Operator

1 Safety observer (if required) C. EXTERNAL PREPARATION

WARNING

When using the APU for ground air conditioning keep the rear equipment bay door closed and where possible aircraft facing into wind. Failure to observe the latter requirement may result in exhaust gases entering aircraft.

1. Fuel drain outlets unobstructed. ( ) 2. Start purge collector tank drained. ( ) 3. APU fire extinguisher pressure gauge indicates 600 to 625 psi. ( ) 4. Oil contents level full. ( ) 5. Check hourmeter and start counter record start cycles and running time. ( ) 6. No evidence of damage, fuel or oil leaks around APU installation. ( ) 7. Close rear equipment bay door. ( )

17-1


APU GROUND OPERATION (Con't.)

8. APU, generator and cold air unit unobstructed, covers removed and free from foreign objects. ( ) 9. APU fire extinguisher pressure relief indicator intact. ( ) 10. Position fire extinguisher(s). ( )

D. INTERNAL PREPARATION 1. FIRE ENG 1 EXT and ENG 2 EXT switches centralized. ( ) 2. EXT 1 FIRED and EXT 2 FIRED indicators clear. ( ) 3. SCREEN HEAT L and R switches OFF. ( ) 4. PITOT/VANE HEAT L and R switches OFF. ( ) 5. ENG ANTIICE 1 and 2 switches OFF ( ) 6. ENG IGNITION1 and 2 switches OFF. ( ) 7. ENG CMPTR 1 and 2 switches OFF. ( ) 8. L PUMP and R PUMP switches OFF. ( ) 9. ENG SYNC switch OFF. ( ) 10. STBY INV switch OFF. ( ) 11. AUX COOLING PACK switch OFF. ( ) 12. EXT PWR switch OFF. ( ) 13. EXT BATT CHG switch OFF. ( ) 14. BATT ISOLATE switch centered. ( )

E. APU START

1. Check all circuit breakers are closed. ( ) 2. EXT PWR switch ON (as required). ( )

17-2



3. BATTERY switch ON. ( ) 4. Cancel MWS repeater flasher. ( ) 5. APU BLEED AIR switch OFF. ( ) 6. No. 1 engine LP COCK open ( ) 7. APU MASTER switch ON. ( ) 8. MWS APU MSTR SW ON annunciator lit. ( ) 9. APU FIRE EXT switch OFF and guarded. ( ) 10. Operate APU TEST ANNUN switch and check APU GEN OVHT, APU FAIL, APU GEN FAIL and APU FIRE annunciators light. ( ) 11. Operate APU TEST FIRE switch and check APU FIRE annunciator lights and bell sounds. ( ) 12. Check clear for starting. ( ) 13. Push APU TURBINE START switch and release. ( )

CAUTION After an aborted start, allow two minutes for fuel drainage and ensure ground is free from fuel before attempting another start. If APU fails to start after two attempts, investigate fault. After aborting a start, observe rpm indicator - if APU is not running down, immediately switch off battery and ext power; trip generator of any running main engine, investigate fault. 14. Check APU governs at 102% on APU RPM indicator. ( ) 15. Check APU EGT indicator reads less than 1000 deg.F (538 deg.C).

17-3



CAUTION

Select APU master switch to off if an automatic

shutdown does not occur within five seconds of an observed overtemperature condition. (Above 1040 to 1080 deg.F) (560 to 582 deg.C).

16. EXT POWER switch OFF. ( ) 17. APU GEN FAIL and BATT 2 CNTCTR annunciators out. ( ) 18. Close BUSTIE switch. ( ) 19. BUSTIE OPEN annunciator out. ( ) 20. BATT 1 CNTCTR annunciator out. ( ) 21. APU AMP indicator shows electrical load, less than 250 amps. ( )

N O T E

Switch either INV1 or INV2 on to operate air conditioning system. 22. APU BLEED AIR switch ON (as required). ( )

F. APU SHUTDOWN

N O T E

The APU will automatically shut down with high EGT, high oil temperature, low oil pressure, underspeed or

overspeed conditions. 1. APU BLEED AIR switch OFF. ( ) 2. Trip APU GENERATOR switch. ( ) 3. APU GEN FAIL annunciator lit. ( ) 4. BUSTIE OPEN AND BATT 1 and 2 CNTCTR annunciators lit. ( ) 5. Run APU for two minutes in unloaded condition to stabilize speed and temperature. ( )

17-4



6. Operate APU TEST OVERSPEED switch and ensure APU runs down. ( )

N O T E

If the APU fails to shut down, set the APU MASTER switch to OFF and investigate the fault. Use of the APU TEST OVERSPEED switch will give an overspeed fault code on the ESU BITE indicators. 7. Wait 30 seconds after APU has stopped then select APU MASTER switch OFF. ( )

CAUTION The APU MASTER switch which energizes the APU fuel pump directly from No. 2 Battery, should never be left in the ON position with the APU not running as fuel pump cavitation can occur with subsequent pump damage or failure. No. 2 Battery could also be drained. 8. No. 1 engine LP COCK closed. ( ) 9. BATTERY switch OFF. ( ) 10. Check APU oil level after use. ( )

N O T E Electrical power to the APU FIRE annunciator operates the APU Fire Relay which in turn initiates the APU automatic shutdown. 1. APU FIRE annunciator on and fire bell ringing. ( ) 2. APU MASTER switch OFF. ( ) 3. No. 1 engine LP COCK closed. ( ) 4. Wait ten seconds, if warning persists, lift guard and operate FIRE EXTING switch. ( )

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5. Inform ground control tower of emergency. ( ) 6. BATTERY switch OFF. ( ) 7. Check APU installation for existence of fire. ( ) 8. Apply external fire extinguisher as required. ( )

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POWER PLANT GROUND OPERATION A. REFERENCES

Personnel required to accomplish ground operation of power plant shall be familiar with BAe 125-800A Maintenance Manual procedures.

B. PERSONNEL REQUIRED 1 qualified operator (minimum) 1 safety observer (if required) C. GENERAL

The procedures contained herein are presented in the shortest practical form for use by qualified personnel and are not intended to provide full technical instructions. This checklist provides in abbreviated form, sequenced procedures for ground operation of the BAe 125-800A power plants. These procedures are derived from but do not replace the more detailed procedures contained in the amplified checklist for powerplant operation. Operators are alerted to the fact that all warning and caution notes are not included herein. When malfunctions are encountered, reference should be made to appropriate maintenance manual.

D. EXTERNAL PREPARATION 1. Aircraft status. ( ) 2. Check aircraft position and environment satisfactory for engine ground run. ( ) 3. Check nose gear centralized and MLG wheels chocked. ( ) 4. Check steering disconnect and landing gear lock pins fitted. ( ) 5. Position fire extinguisher(s). ( ) 6. Clear area of all ground equipment. ( )

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POWER PLANT GROUND OPERATION (Con't.)

7. Remove all aircraft/engine covers, blanks and static vents. ( ) 8. Check engines are unobstructed and immediate area free of foreign object debris (FOD). ( ) 9. Remove static ground wire from aircraft and stow. ( )

WARNING

No hats or loose clothing shall be worn in vicinity of running engines. Ear protectors shall be worn. Keep clear of engine intakes and exhausts. 10. Check hydraulic accumulator pressure is at least 1750 psi. Operate hydraulic hand pump as necessary. ( ) 11. Close rear equipment bay hatch. ( ) 12. Check all aircraft panels are secured for engine ground running. ( )

E. INTERNAL PREPARATION

1. FIRE ENG 1 EXT and ENG 2 EXT switches centralized. ( ) 2. EXT 1 FIRED and EXT 2 FIRED indication clear. ( ) 3. SCREEN HEAT L and R switches OFF. ( ) 4. PITOT/VANE HEAT L and R switches OFF. ( ) 5. ENG ANTICE 1 and 2 switches OFF. ( ) 6. ENG IGNITION 1 and 2 switches OFF. ( ) 7. ENG CMPTR 1 and 2 switches OFF. ( ) 8. L PUMP and R PUMP switches OFF. ( ) 9. ENG SYNC switch OFF. ( )

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10. F/DK VLV switch CLOSE. ( ) 11. MAIN AIR VLV 1 and 2 switches CLOSE. ( ) 12. STBY INV switch OFF. ( ) 13. AUX COOLING PACK switch OFF. ( ) 14. EXT PWR switch ON (as required). ( ) 15. EXT BATT CHG switch OFF. ( ) 16. BATT ISOLATE switch centered. ( ) 17. BATT switch ON. ( ) 18. Cancel MWS repeater flasher. ( ) 19. Ensure LANDING GEAR and O/RIDE levers are down. ( ) 20. Landing gear three greens indicated. ( ) 21, Hydraulic pressure gauge reading at least 1750 psi (only with EXT PWR ON). ( ) 22. Brake lever to PARK. ( ) 23. Operate ENG FIRE 1 and 2 TEST switches in turn ensuring that fire bell rings and appropriate ENG FIRE annunciators on MWS flashers light. ( ) 24. Cancel MWS flashers. ( ) 25. APR disarmed, APR OVRD and APR ARM annunciators out. ( ) 26. AUX FUEL TRANSFER valve closed. ( ) 27. WING FUEL X- FEED/TRANSFER valve closed. ( ) 28 Both LP COCKS open. ( )

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29. Both HP COCKS closed. ( )

N O T E

When starting both engines, it is normal practice to start No. 2 engine first. If it is only required to start one engine, ignore actions referring to the unwanted

engine.

CAUTION

If it is decided to abort the engine start in the following procedures, close the HP cock immediately, then press the PWR on push for abort - engine start switch if any of the engine indications runs quickly towards its limit, or any required indication does not appear in its specified time limit.

F. NO. 2. ENGINE START

1. Obtain clearance from ground control tower to start engine. ( ) 2. Alert fireguard that No. 2 engine is about to start. ( ) 3. BEACON switch to ON. ( ) 4. ENG CMPTR 1 and 2 switches to AUTO, ENG 1 CMPTR and ENG 2 CMPTR MWS annunciators out. ( ) 5. L PUMP and R PUMP switches to ON. ( ) 6, Operate START PWR switch, check PWR ON PUSH FOR ABORT annunciator lit. ( ) 7. FUEL 1 LO PRESS and FUEL 2 LO PRESS annunciators OUT. ( )

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8. Press ENGINE START ENG 2 switch and release when OPERATING annunciator lights. ( ) 9. HP COCK 2 open when N2 registers 10% rpm. ( )

N O T E

At high altitudes or in low temperature conditions it may be necessary to enrich the fuel until the ITT

gauge reads 400 deg.C. 10. Operate FUEL ENRICH 2 switch (as required). ( ) 11. Observe light up by noting steady rise in ITT and N2 readings within 10 seconds of operating HP Cock 2. ( )

CAUTION

Abort start if any of the following conditions occur. a. No N1 rpm before 20% N2 rpm. b, N1 rpm stops increasing after 20% N2 rpm. c. ITT rapidly approaches start limit 952 deg.C. d. N1 27% idle rpm not reached 60 seconds after

light up. N2-48 to 67% rpm. e. N2 rpm stops increasing before reaching idle rpm. f. Oil 2 LO press annunciator not out before idle rpm. 12. Check ENGINE START OPERATING 2 switch annunciator out at 45% N2 rpm. ( ) 13. Check IGN ON annunciator out. ( ) 14. Check fuel flow, N1, N2, ITT and oil pressure readings stabilize. ( )

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G. NO. 1 ENGINE START 1. Carry out No. 1 engine start by using Section F Operations 1 thru 14 but using appropriate No. 1 engine controls. ( ) H. ENGINE RUNNING CONDITION 1. Engine START PWR switch OFF. ( ) 2. EXT PWR switch OFF. ( ) 3. GEN 1 and GEN 2 FAIL annunciators out. ( ) 4. BATT 1 and 2 CNCTR annunciators out. ( ) 5. Check battery charging currents initially high but reducing to below 40 amps. ( ) 6. BUSTIE switch CLOSE, BUSTIE OPEN annunciator out. ( ) I. ENGINE SHUT DOWN

N O T E

Run engines a minimum of two minutes at idle rpm prior to commencing shut down procedure. 1. Close HP cocks. ( ) 2. Check GEN 1 and GEN 2 FAIL annunciators lit as engines run down. ( ) 3. Fuel L PUMP and R PUMP switches to OFF. ( ) 4. ENG CMPTR 1 and 2 switches to OFF. ( ) 5. BEACON switch to OFF. ( ) 6. Both LP cocks closed. ( ) 7. Inform ground control tower engine run complete. ( ) 8. BATTERY switch OFF. ( )

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9. Connect aircraft ground. ( ) J. EMERGENCY ENGINE SHUT DOWN

N O T E The following actions apply to the engine appropriate to the ENG FIRE annunciator lit. 1. Operate BELL CANCEL switch. ( ) 2. ENG FIRE annunciator lit. ( ) 3. Close HP cock. ( ) 4. Operate START PWR switch PUSH FOR ABORT (Starting only). ( ) 5. Close LP Cock. ( ) IF ENG FIRE WARNING PERSISTS 6. Discharge FIRE ENG EXT SHOT 1. ( ) 7. Discharge FIRE ENG EXT SHOT 2, if required. ( ) 8. Inform ground control tower of emergency. ( ) 9. Close other HP Cock. ( ). 10. Close other LP Cock. ( ) 11. L PUMP and R PUMP switches OFF. ( ) 12. EXT PWR switch OFF. ( ) 13. BATTERY switch OFF. ( ) 14. Apply external fire extinguisher, as required. ( )

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18-8


JACKING AND TRESTLING A. REFERENCES

Personnel required to accomplish jacking and trestling shall be familiar with BAe 125-800A Maintenance Manual procedures.

B. PERSONNEL REQUIRED One supervisor One mechanic for each position C. GENERAL

1. Two types of jacking: a. Jack complete aircraft. b. Jack main or nose gear wheels.

D. EQUIPMENT AND MATERIALS Description Quantity Part No. Wing jacks 2 ME5 2321C Jack pads wing 2 25Y 67A Tail jack 1 ME4 5523 Jack pad rear 1 25Y 13A Wing trestle profile boards 1 25Y 331A, 25Y 332A Wheel jack 1 ME7 4925 E. JACK COMPLETE AIRCRAFT 1. Check maximum weight of aircraft below 25,255 lb. ( ) 2. Check wind speed less than 10 knots. ( ) 3. Check aircraft headed into wind. ( ) 4. Check aircraft to be jacked is on an approved jacking spot. ( )

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JACKING AND TRESTLING (Con't.)

5. Ensure fuel load in wings equalized. ( )

CAUTION

True air speed (TAS) probe heater will overheat and burn out if operated on ground. 6. Open TAS PROBE HEAT circuit breaker (F11) on Panel DA. ( ) 7. Unlock Camloc fasteners and open wing jack point access panels. ( ) 8. Remove rear jack point fairing on frame 25. ( ) 9. Position jacks at each wing jack point. ( ) 10. Install jack pads to wing jack sockets and adapter head to jacks. ( )

N O T E

If a four legged jack is being used, position two of the legs parallel to the aircraft center line. If a tripod jack is being used, position forward leg on and two rear legs equally disposed parallel to the aircraft center line. This gives maximum stability on aircraft longitudinal and lateral axis. 11. Align each jack with its corresponding jack pad and lift jack transporter wheels clear of the ground. 12. Check jacks stand firmly on their bases, extend jacks until adapter heads engage with jack pads and check jacks stand vertical. ( ) 13. Check jacking area (particularly above the horizontal stabilizer) clear of obstruction. ( ) 14. Check that the landing gear lock pins are installed. ( ) 15. Release aircraft brakes. ( )

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WARNING

As jack rams extend, screw down lock collars. 16. Extend wing jacks in unison until aircraft is level, both fore and aft and laterally. ( )

CAUTION Do not place rear jack in position until aircraft is level. 17. Position rear jack at rear jack point. ( ) ( ) 20. Check jack stands firmly on its legs and extend jack until adapter head engages with the jack pad. ( )

WARNING Lock jack rams by screwing down lock collars. 21. Extend all three jacks simultaneously, making sure that the aircraft remains level, until the wheels are approximately three inches clear of the ground. ( ) 22. Remove chocks. ( ) 23. Install trestles, as required. ( ) F. LOWER AIRCRAFT

CAUTION Ensure brakes are off before lowering.

1. Check fuel loads in each wing are equalized. ( )

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2. Remove trestles and all equipment that could damage the aircraft during lowering. ( ) 3. Check landing gear is locked down and lock pins installed. ( )

WARNING

Not more than one inch is allowed between jack rams and lock collars during lowering process. 4. In unison extend each jack slightly to relieve the load on the ram lock collar, then partially unscrew the collar not more than one inch. ( ) 5. Operate each jack pressure valve simultaneously to make sure that jacks retract together. ( )

CAUTION Move tail jack clear of aircraft as soon as jack is unloaded. Any difference between lowering rates at the main wing jacks causes tail movement, with the possibility that the tail jack may damage the aircraft structure. 6. When weight of aircraft is on landing gear, install chocks front and rear of main wheels.( ) 7. Apply aircraft brakes. ( ) 8. Remove jacks. ( ) 9. Remove jack pads from aircraft sockets. ( ) 10. Install wing and tail jacking access panels. ( ) 11. Close TAS PROBE HEAT circuit breaker (F11) on Panel DA. ( )

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G. JACK MAIN OR NOSE GEAR WHEELS

1, Check weight of aircraft-up to maximum takeoff weight. ( )

N O T E The jack can be placed in position if one or both tires are deflated provided the distorted tires permit its correct positioning, if not it will be necessary to raise the wheel by insertion of wooden blocks under the tires or by normal jacking. 2. Position chocks to the front and rear of wheels not being jacked. ( ) 3. Position wheel change jack to the rear of nose gear or forward of the main gear, as required. ( ) 4. Extend jack ram to engage jack head with leg jack pad. ( ) 5. Extend jack until wheels are clear of the ground. ( )

H. LOWER MAIN OR NOSE GEAR WHEELS 1. Move all equipment clear of aircraft. ( ) 2 Operate pressure release valve to retract jacks. Remove jack. ( ) 3. Place wheel chocks front and rear of main wheels. ( ) 4, Apply brakes. ( )

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ground handling servicing cklst

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