Hawker Checklist Thru Rev02 & Tr03

BAe 125-800A

AVN FLIGHT CREW PROCEDURES CHECKLIST NORMAL EMERGENCY/ABNORMAL PERFORMANCE

APPLICABLE TO: N96 -----------------------------------258134 N97 -----------------------------------258154 N98 -----------------------------------258156

AVN CFM through Change 02 AVN CHECKLIST CHANGE 02 AVN CHECKLIST TEMP REV 01 AVN CHECKLIST TEMP REV 02 AVN CHECKLIST TEMP REV 03

MARCH, 1999 JULY, 2003 JUNE, 2005 OCTOBER, 2005 JULY 2006

TI 4040.25 CHG 02, 07/03

BAe 125-800A AVN CHECKLIST

The AVN Flight Crew Procedures (abbreviated) checklist for FAA aircraft is condensed from the description Checklist contained in the Company Flight Manual (CFM). These procedures must be thoroughly understood to safely and effectively operate the aircraft. Upon receipt of an Operations Alert Directive (OAD) affecting this Checklist, write the information in the appropriate section. Changes to the checklist will be distributed after each approved checklist change. Checklist procedures may be accomplished by the “Do-Verify” method. The DV method consists of the checklist being accomplished in a variable sequence without a preliminary challenge. After all the action items on the checklist have been completed, the checklist is then read again while each item is verified. The Pilot-Not-Flying (PNF) shall read the checklist, or verify the checklist completion and will announce "________ Checklist Complete." Checklist complete must always be announced. When the Before Landing Checklist Complete is not announced prior to crossing the runway threshold, a go around is mandatory. If an item of the checklist is interrupted, that item of the checklist shall be verified or repeated. In an emergency, FLY THE AIRCRAFT. The pilot flying (PF) does not perform tasks, which detract from, or compromise, the duty to maintain control of the aircraft. The PF will ensure that the emergency checklist immediate items are completed and the emergency checklist be called for and accomplished. CHECKLIST SYMBOLS + Plus items are for through flight items. *

Asterisk items are for Battery start items. Immediate Action items in bold print and bold boxed. list text represents pause point for radio communications and crew coordination.

DEFINITIONS These definitions of flight crew positions are used throughout the FAA Flight Inspection. P-Pilot, PIC-Pilot-in-Command, SIC-Second-in-Command, LPLeft Pilot, RP-Right Pilot, PF-Pilot Flying, PNF-Pilot Not Flying ET-Electronic Technician Airborne. Request for changes, corrections or recommendations for this procedures checklist should be submitted to the Director of Operations, AVN-200.

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 02, 07/2003

CONTROL PAGE Description Cover Description Control Page List of Effective Pages

Change No 02 01 02 02

Date 07/2003 06/1999 07/2003 07/2003

NORMAL Description All pages in this Section N –21 and Administrative

Change No 01 02

Date 06/1999 07/2003

EMERGENCY/ABNORMAL Description E-i Thru E-iii, E-1 Thru E13, E-15, E-17 Thru h E19, E-21 Thru E-22, and E24 Thru E-32 E-iv, E-14, E-16, E-20, and E-23

Change No

Date

Original

03/97

01

06/99

PERFORMANCE Description P-ii Thru P-iii, and P-1 Thru P-22 P-i, P-iv, and P-23 Thru P30

A

Change No

Date

Original

03/97

01

06/99

BAe 125-800A AVN CHECKLIST

TI 4040.25.2 Temp Rev 03, July 2006

CONTROL PAGE Description Cover Description Control Page List of Effective Pages

Change No TR 03 01 TR 03 TR 03

Date 07/2006 06/1999 07/2006 07/2006

NORMAL Page No All pages in this Section N –21 and Administrative N-16

Change No 01 02 TR 03

Date 06/1999 07/2003 07/2006

EMERGENCY/ABNORMAL Page No E-i Thru E-iii, E-1 Thru E-13, E-15, E-17 Thru h E-19, E-21 Thru E-22, and E-24 Thru E32 E-iv, E-14, E-16, E-20, and E-23 E-iii, E-8, E-10, and E-11 E-iv, E-27

Change No

Date

Original

03/97

01

06/99

TR 01 TR 02

06/2005 10/2005

PERFORMANCE Page No P-ii Thru P-iii, and P-1 Thru P-22 P-i, P-iv, and P-23 Thru P-30

A

Change No

Date

Original

03/97

01

06/99

TI 4040.25 CHG 02, 07/2003

BAe 125-800A AVN CHECKLIST

LIST OF EFFECTIVE PAGES Section Page

CHG No

Cover ........... 02 Description ... 01 Control Page 02 LOEP ........... 02 NORMAL Table of Contents N-i .............. 02

N-ii........... 02 N-1 .............. 01 N-2 .............. 01 N-3 .............. 01 N-4 .............. 01 N-5 .............. 01 N-6 .............. 01 N-7 .............. 01 N-8 .............. 01 N-9 .............. 01 N-10 ............ 01 N-11 ............ 01 N-12 ............ 01 N-13 ............ 01 N-14 ............ 01 N-15 ............ 01 N-16 ............ 01 N-17 ............ 01 N-18 ............ 01 N-19 ............ 01 N-20 ............ 01 N-21 ............ 02 N-22 ............ 01 N-23............ 01 N-24............ 01

Section Page

CHG Section No Page

N-25............. 01 N-26............. 01 N-27............. 01 N-28............. 01 N-29............. 01 N-30............. 01 N-31............. 01 N-32............. 01 N-33............. 01 N-34............. 01 N-35............. 01 N-36............. 01 N-37............. 01 N-38............. 01 N-39............. 01 N-40............. 01 N-41............. 01 N-42............. 01 N-43............. 01 N-44............. 01 N-45............. 01 N-46............. 01

Emergency/ Abnormal E-i ................ 01 E-ii ............... 01 Table of Contents E-iii............... 01 E-iv .............. 01

B

CHG No

E-1 .......Original E-2 .......Original E-3 .......Original E-4 .......Original E-5 .......Original E-6 .......Original E-7 .......Original E-8 .......Original E-9 .......Original E-10 .....Original E-11 .....Original E-12 .....Original E-13 .....Original E-14 .....Original E-15 .....Original E-16 ............. 01 E-17 .....Original E-18 .....Original E-19 .....Original E-20 ............. 01 E-21 .....Original E-22 .....Original E-23 ............. 01 E-24 .....Original E-25 ...Original E-26 ...Original E-27 ...Original E-28 ...Original E-29 ...Original E-30 ...Original E-31 ...Original E-32 ...Original

TI 4040.25.2 Temp Rev 03, July 2006

BAe 125-800A AVN CHECKLIST

LIST OF EFFECTIVE PAGES Section Page

CHG No

Cover.......... TR 03 Description ....... 01 Control PageTR 03 LOEP.......... TR 03

NORMAL Table of Contents

N-i............ 02 N-ii........... 02 N-1 .............. 01 N-2 .............. 01 N-3 .............. 01 N-4 .............. 01 N-5 .............. 01 N-6 .............. 01 N-7 .............. 01 N-8 .............. 01 N-9 .............. 01 N-10 ............ 01 N-11 ............ 01 N-12 ............ 01 N-13 ............ 01 N-14 ............ 01 N-15 ............ 01 N-16 .......TR 03 N-17 ............ 01 N-18 ............ 01 N-19 ............ 01 N-20 ............ 01 N-21 ............ 02 N-22 ............ 01 N-23............ 01 N-24............ 01

Section Page

CHG Section No Page

N-25............. 01 N-26............. 01 N-27............. 01 N-28............. 01 N-29............. 01 N-30............. 01 N-31............. 01 N-32............. 01 N-33............. 01 N-34............. 01 N-35............. 01 N-36............. 01 N-37............. 01 N-38............. 01 N-39............. 01 N-40............. 01 N-41............. 01 N-42............. 01 N-43............. 01 N-44............. 01 N-45............. 01 N-46............. 01

Emergency/ Abnormal E-i ................ 01 E-ii ............... 01 Table of Contents E-iii......... TR 02 E-iv .............. 01

B

CHG No

E-1 .......Original E-2 .......Original E-3 .......Original E-4 .......Original E-5 .......Original E-6 .......Original E-7 .......Original E-8 ......... TR 01 E-9 .......Original E-10 ....... TR 01 E-11 ....... TR 01 E-12 .....Original E-13 .....Original E-14 .....Original E-15 .....Original E-16 ............. 01 E-17 .....Original E-18 .....Original E-19 .....Original E-20 ............. 01 E-21 .....Original E-22 .....Original E-23 ............. 01 E-24 .....Original E-25 ...Original E-26 ...Original E-27 ..... TR 02 E-28 ...Original E-29 ...Original E-30 ...Original E-31 ...Original E-32 ...Original

BAe 125-800A AVN CHECKLIST Section Page

CHG No

TI 4040.25 CHG 02, 07/2003 Section Page

Performance Table of Contents P-i ...... Original P-iii..... Original P-iv .... Original P-1 ......... Original P-2 ......... Original P-3 ......... Original P-4 ......... Original P-5 ......... Original P-6 ......... Original P-7 ......... Original P-8 ......... Original P-9 ......... Original P-10 ....... Original P-10 ....... Original P-11 ....... Original P-12 ....... Original P-13 ....... Original P-14 ....... Original P-15 ....... Original P-16 ....... Original P-17 ....... Original P-18 ....... Original P-19 ....... Original P-20 ....... Original P-21 ....... Original P-22 ....... Original P-23 ....... Original P-24 ....... Original P-25 ....... Original P-26 ....... Original P-27 ....... Original P-28 ....... Original P-29 ....... Original P-30 ....... Original

C

CHG No

Section Page

CHG No

TI 4040.25 CHG 02, 07/2003

BAe 125-800A AVN CHECKLIST

This Page Intentionally Left Blank

D

BAe 125-800A AVN CHECKLIST TABLE OF CONTENTS

TI 4040.25 CHG 02, 07/2003 Page 6

NORMAL PROCEDURES Before Exterior Inspection .............................................N-1 Exterior Inspection.........................................................N-1 Cabin Inspection............................................................N-5 Before Starting Engines ................................................N-5 Starting Engines ..........................................................N-10 Before Taxi..................................................................N-11 Taxi .............................................................................N-12 Before Takeoff.............................................................N-12 Lineup .........................................................................N-13 After Takeoff/Climb......................................................N-13 Cruise..........................................................................N-14 In Range/Descent........................................................N-15 Before Landing ............................................................N-16 Traffic Pattern/Before Landing ....................................N-17 After Landing...............................................................N-19 Taxi Back ....................................................................N-20 Stopping Engines ........................................................N-20

EXPANDED NORMAL Weather Radar Check.................................................N-22 Nav and Radio Check .................................................N-23 EFD Check..................................................................N-28 Autopilot Check ...........................................................N-29 Overhead Test Panel Check .......................................N-31 Engine Starting Malfunctions.......................................N-33 APS-85 Autopilot Diagnostics .....................................N-35 Passenger Briefing ......................................................N-36 Takeoff Crew Briefing/Considerations .........................N-37 Instrument Approach Review ......................................N-38 N-i

TI 4040.25 CHG 02, 07/2003 TABLE OF CONTENTS

BAe 125-800A AVN CHECKLIST Page 6

SCHEMATICS DC Power System - De-Energized Schematic ............N-39 AC Power System - Schematic ...................................N-40 DC Power Distribution - PE Bus Bar ...........................N-41 DC Power Distribution - PS1 Bus Bar .........................N-42 DC Power Distribution - PS2 Bus Bar .........................N-43 AC Power Distribution .................................................N-44 Refuel/De-fuel System Schematic...............................N-45 Hydraulic System Schematic.......................................N-46

N-ii

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

NORMAL PROCEDURES PREFLIGHT CHECKLIST Before Exterior Inspection +

1.

Chocks ..............................................IN PLACE

+

2.

Rampguard (If Applicable)...............Check OFF

+

3.

Manuals & Documents ..........................CHECK

4.

Fire Extinguisher Indicators and Switches (2) .............................Check OFF

5.

Landing Gear Handle .............................DOWN

6.

Override Gear Selector ..........................DOWN

7.

Nose Gear Downlock Indicator.............VISIBLE

8.

Aux Hyd System Selector...................... CYCLE Reset Fully IN

9.

Wheelbrake ............................................. PARK

+

Exterior Inspection Thru flight Inspection: complete all items. Fuselage Nose - Left Side 1. Airflow Angle Sensor Vane..........CHECK Movement 2.

Pitot Probe ................................... REMOVE COVER Check

3.

Static Vents (Upper/Lower) .......... REMOVE PLUGS Check

4.

Air Temp Probe .............................................CHECK

5.

Rotary Ice Detector ................................Rotor FREE

6.

Nose Wheel Well..................... AUX HYD RES FULL No Leaks

7.

Nose Gear Lock Pin ...................................REMOVE Stow

8.

Nose Wheel Doors ..................................... SECURE

NORMAL

N-1

TI 4040.25 CHG 01, 06/1999 9.

BAe 125-800A AVN CHECKLIST

Nose Steering Pin .........................................CHECK Vertical

10. Nose Strut .....................................................CHECK 11. Nose Tires & Wheels ....................................CHECK 12. Radome/Taxi Lights ................................... SECURE Check Fuselage Nose - Right Side 13. Static Vents(Upper/Lower) ............REMOVE PLUGS Check 14. Pitot Probe ................................... REMOVE COVER Check 15. Airflow Angle Sensor Vane ...........................CHECK Movement 16. Venturi Outlet ................................................CHECK 17. SAT/TAS Probe.............................................CHECK 18. Emergency Exit .............................................CHECK 19. Dorsal Air Intake.............................. REMOVE PLUG Check Right Engine - Front of Wing 20. Intake ............................................................CHECK 21. P2T2 Sensor ..................................................CHECK 22. Fan Blades....................................................CHECK 23. Starter Generator Air Intake ..........................CHECK Right Wing 24. Wing Ice Inspection Light ..............................CHECK 25. Top Surface ..................................................CHECK 26. TKS Panels ...................................................CHECK 27. Landing & Taxi Lights....................................CHECK 28. Stall Vent......................................... REMOVE PLUG Check 29. Fuel Cap .................................................... SECURE 30. Vortex Generators.........................................CHECK 31. NAV & Strobe Lights .....................................CHECK

N-2

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

32. Undersurface.................................................CHECK 33. Vent Tank Intake ...........................................CHECK 34. Static Wicks...................................................CHECK 35. Aileron & Tab ................................................CHECK 36. Flaps .............................................................CHECK 37. Airbrakes .......................................................CHECK Right Main Gear 38. Fairing & Inboard Door ..................................CHECK 39. Wheel Well ....................................................CHECK 40. Main Gear Lock Pin....................................REMOVE Stow 41. Strut...............................................................CHECK 42. Tires & Wheels..............................................CHECK 43. Brake Lines ...................................................CHECK Fuel Tanks & Keel 44. Water Drain Valves .......................................CHECK 45. Anti-Collision Light ........................................CHECK 46. Antennas .......................................................CHECK Right Engine 47. Oil Level & Filter............................................CHECK 48. Drain Mast.....................................................CHECK 49. Cowling & Latches ..................................... SECURE 50. Rear Turbine Blades & Exhaust Section ............................................CHECK Rear Fuselage 51. Pressure Refuel Cap & Door...................... SECURE 52. Aux Cooling Pack Inlet & Exhaust .................CHECK 53. Ground Power Receptacle Door ................ SECURE 54. Oxygen Charging Panel Cover................... SECURE 55. Tail Cone.......................................................CHECK Latches Secure 56. Laser Alt Inlet, Exhaust & Optics...................CHECK 57. Anti-Collision Light ........................................CHECK 58. Vertical Stabilizer & Rudder ..........................CHECK

NORMAL

N-3

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

59. Horizontal Stabilizer & Elevators ...................CHECK 60. Equipment Bay Door .................................. SECURE 61. Fire Extinguisher Indicators (3) .....................CHECK 62. Toilet Tank Drain Door ............................... SECURE Left Engine 63. Oil Level & Filter............................................CHECK 64. Drain Mast.....................................................CHECK 65. Rear Turbine Blades & Exhaust Section ............................................CHECK 66. Cowling & Latches ..................................... SECURE Left Main Gear 67. Fairing & Inboard Door..................................CHECK 68. Wheel Well....................................................CHECK 69. Main Gear Lock Pin....................................REMOVE Stow 70. Strut ..............................................................CHECK 71. Tires & Wheels..............................................CHECK 72. Brake Lines ...................................................CHECK Left Wing 73. Airbrakes.......................................................CHECK 74. Flaps .............................................................CHECK 75. Aileron & Tab ................................................CHECK 76. Vent Tank Intake ...........................................CHECK 77. Undersurface ................................................CHECK 78. NAV & Strobe Lights .....................................CHECK 79. Vortex Generators.........................................CHECK 80. Fuel Cap .................................................... SECURE 81. Stall Vent......................................... REMOVE PLUG Check 82. Landing & Taxi Lights....................................CHECK 83. TKS Panels ...................................................CHECK 84. Top Surface ..................................................CHECK 85. Wing Ice Inspection Light ..............................CHECK

N-4

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

Left Engine/Left Fuselage - Front of Wing 86. Intake ............................................................CHECK 87. P2T2 Sensor...................................................CHECK 88. Fan Blades ....................................................CHECK 89. Starter Generator Air Intake ..........................CHECK 90. Entrance Door ...............................................CHECK

Cabin Inspection Thruflight Inspection: complete (+) items only.

+

1.

Aft Baggage Compartment and Door ....CHECK Secure

2.

Lavatory ................................................CHECK

3.

Cabin Windows .....................................CHECK for Cracks/Damage

4.

Crew Seats & Tables ............................CHECK

5.

Emergency Exit ............ CLOSED Pin Removed

6.

Emergency & Survival Equipment.........CHECK

7.

Cabin Fire Extinguisher .........................CHECK

8.

First Aid Kit............................................CHECK

9.

Galley ....................................................CHECK

+

10. Baggage & Cargo Areas .................... SECURE

+

11. Refuel Panel

+

12. Circuit Breakers.....................................CHECK

Switches OFF Door Closed

BEFORE STARTING ENGINES +

Thruflight Inspection: complete plus (+) items only.

*

Battery Start: complete asterisk (*) items following the Starting Engines checklist and prior to the Taxi checklist.

**

Double asterisk (**) items indicate an expanded description is found at the end of the checklist section.

NORMAL

N-5

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

1.

Battery Isolate ........................................ NORM

+

2.

External Power Switch ............................... OFF

+

3.

Battery (B1 & B2 23V min ; B3 23.5V; PS1 & PS2 0V)............................ON

+

4.

Bus Tie Open Annunciator ...........................ON

+

5.

Navigational Lights.......................................ON

+

6.

Landing Gear Indicators.................... 3 GREEN

7.

Fuel Pumps (2) ........................... EMERG, OFF (23V MIN on PE)

+

8.

Fuel Quantity.........................................CHECK

+

9.

Oxygen............................... ON Quantity Check

+

10. TKS Contents........................................CHECK

For APU Power + 11. Engine No. 1 LP fuel cock............................ON +

12. Aux Cooling Pack....................................... OFF

+

13. APU Bleed Air ............................................ OFF

+

14. APU Master..................................................ON

+

15. APU Fire Warning and Annunciators ....... TEST and Check

+

16. Fire Extinguisher Switch

+

17. APU....................................................... START

+

18. Bus Tie.................................................. CLOSE

OFF and Guard Secured

Skip to Item 22 for APU Starts For EXT Ground Power or Battery Only Start + 19. EXT PWR.......................................... AS REQD +

20. External Battery Charge.................... AS REQD

+

21. BATT CNTCTR Annunciators (2) ................ON

+ * 22. Inverters (3)..............................Check ARM/ON + * 23. APU Bleed Air & Aux Cooling Pack..................................... AS REQD

N-6

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

Left Side + * 24. Emergency Exit Lights ............................ Check AUTO +

25. Oxygen Cabin Isolation Valve ........... AS REQD 26. Fire Extinguisher, Axe, Flashlight and Smoke Goggles..............................CHECK Stow

+ * 27. IRS .............................................................NAV 28. Oxygen Mask ............................. 100% CHECK 29. UHF Radio ...................................................ON 30. Audio Control Panel ................................... SET 31. HF Radio #1 ............................................... SBY +

32. Gust Lock & Aux Hyd Pump Handle ..REMOVE STOW

Front Panels + 33. No.1 Clock.................................................. SET +

34. Flight Annunciators .................................. TEST

+

35. Standby Instrument Emerg Power ........... TEST

+

36. Standby Attitude Indicator ..................... ERECT 37. ELT ......................................................... AUTO

+ * 38. ADS(2), EFD(2), MFD, AHRS(2) MSTRS .........................................ON +

39. Transfer Switches .................................CHECK

+

40. Fuel Contents and Flowmeters................................. Check RESET

+

41. MWS and DIM OVRD .............................. TEST

+

42. GPWS Flap Warn OVRD Annunciator ............................................... OUT

+ * 43. Weather Radar ** ............................. STANDBY 44. Marker .......................................................... LO + * 45. FMS ................................................PROGRAM + * 46. Nav Radios **............................................. SET * 47. EFD (2) **.............................................CHECK

NORMAL

N-7

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

48. XPNDR and ATNR Switches/Lights ...........OUT * 49. Avionics Lighting ............................... AS REQD + * 50. Autopilot & Yaw Damper ** ...................CHECK Disengage + * 51. IRS Heading...................................... AS REQD + * 52. Transponder Antenna ................................ ATC + * 53. FIS Power ........................................ AS REQD + * 54. 115VAC 60HZ................................... AS REQD 55. Lazer Altimeter........................................... OFF 56. Dump Valve ............................................ SHUT 57. Manual Trim ..........................................CHECK Movement 58. Electric Trim ..........................................CHECK Movement +

59. HP COCKs............................................ CLOSE

+

60. LP COCKs .............................................. OPEN

+

61. WG Fuel/X Feed/Transfer ......CLOSE Light Out

+

62. AUX Fuel Transfer .................CLOSE Light Out

+ * 63. No. 2 Clock ................................................ SET +

64. Cabin Controller .............. ALTITUDE RATE Set

+ * 65. AHRS DG Annunciators (2) .......................OUT Right Side + * 66. VHF #2....................................................... SET 67. Audio Control Panel ................................... SET + * 68. IFF (If Applicable)..................................CHECK Standby + * 69. Standby Gear Indicators (2) ................. GREEN 70. Pitot Isolation ..................................... NORMAL 71. Pressurization .................................... NORMAL 72. Manual Control........................Full DECREASE

N-8

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

73. Oxygen Mask ............................. 100% CHECK +

74. HF Radio #2 ............................................... SBY 75. Goggles, Smoke Set O2, Flashlight............................... Check STOW

Glareshield * 76. Emergency & Storm Lights (L) ................. TEST * 77. Lighting Controls (L).......................... AS REQD * 78. FD BARS, DEV & F/S Switches (L)... AS REQD * 79. GPWS ...................................................... TEST + * 80. Display Select Panel (L) .................... AS REQD + * 81. Radar Altimeters (2) .......................TEST (100’) Set (1’) + * 82. Altitude Alerter.......................................... TEST Set + * 83. Display Select Panel (R) ................... AS REQD *

84. F/S, DEV & FD BARS Switches (R) .. AS REQD

*

85. Lighting Controls (R) ......................... AS REQD

*

86. Emergency & Storm Lights (R)................. TEST

Roof Panel + * 87. TEST Panel (**)........................................ TEST Thruflight: only ENG FIRE tests required. 88. Alternators (2) ............................................ OFF +

89. External Battery Charge ............................. OFF

+

90. External Power.................................. AS REQD * 91. Cabin & Lav Lights Switch................. AS REQD * 92. TKS .................................... PRIME Check Flow 93. Ice Detector............................................. AUTO 94. Fuel Pumps (2)........................................... OFF Fuel LO Press Lights....................................ON 95. GEN Fail Annunciators (2) ...........................ON 96. No Smoking..................................................ON 97. Screen Heat (2) & Pitot Vane Heat (2) ....... OFF

NORMAL

N-9

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

98. Engine Anti-Ice (2) & Ignitions (2) .............. OFF 99. Engine Computers (2) ................................ OFF CMPTR Lights..............................................ON 100. ENG SYNC ............................................... OFF 101. Pack Valve .............................................. AUTO 102. Flood Valve ...................................... AS REQ’D 103. Pressn Valve........................................... AUTO 104. Cabin Temperature Control................ Auto SET 105. Flt Deck & Main Air Valves................. CLOSED Main Air Valve Lights .................................OUT 106. Takeoff Data .................................COMPUTED Posted

STARTING ENGINES 1.

Fasten Seat Belts Sign.........................ON

RP

2.

Seat Belts & Shoulder Harness............ON

LP/RP

3.

Wheelbrake................PARK HYDRAULIC Check

LP

4.

Aux Cooling Pack............................... OFF Recirc

LP

5.

NAV & Beacon Lights...........................ON

LP

6.

Engine Computers (2) ..................... AUTO Lights Out

LP

7.

Fuel Pumps (2) ....................................ON Lights Out

LP

8.

Start Power ..........................................ON

LP

9.

Engines 2 & 1................................ START

LP

10. External Power (If Applicable) ............ OFF Disconnect

RP

11. Start Power ........................................ OFF

LP

12. APU Generator ................................. TRIP

RP

13. DC Power......................................CHECK

RP

14. Alternators (2) ......................................ON Lights Out

LP

N-10

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

15. Screen Heat (2)....................................ON

LP

16. Pitot/Vane Heat (2)...............................ON Check

LP

17. Eng Ignitions (2) & Anti-Ice (2) .. AS REQD

LP

Set ICE DET to OVRD before taxiing in icing 18. FIS Power ................................. AS REQD

RP

19. TACAN 2 Tuning ....................... AS REQD

RP

20. Windows..................................... CLOSED

LP/RP

21. Starting Engines Checklist .... COMPLETE

RP

BEFORE TAXI 1.

IRS .....................................................NAV

LP

2.

Altimeters ........................................... SET Check

LP/RP

3.

Chocks .................................... REMOVED

LP

4.

Entrance Door ............................ LOCKED Lights Out

RP

Check CVR, FLT RCDR and ENT Door Unlocked Annunciators Out. 5.

Exterior Lights ........................... AS REQD

RP

Do not use landing lights for taxi. 6.

Taxi Area....................................... CLEAR

LP/RP

Do not move the aircraft until attitude and heading warnings have cleared. 7.

Before Taxi Checklist ............ COMPLETE

NORMAL

RP

N-11

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

TAXI 1.

Brakes...........................................CHECK

LP/RP

2.

Steering.........................................CHECK

LP

3.

Flaps .................................................. SET

RP

4.

Trims (3)............................................. SET

RP

5.

Flight Controls ...............................CHECK

PF

6.

Flight Instruments..........................CHECK

LP/RP

7.

Taxi Checklist........................ COMPLETE

RP

Before Takeoff 1.

Rudder Bias and Engine Computers ....................Check ON

LP

2.

Airbrakes......................................... SHUT

LP

3.

APR...............................................CHECK

LP

4.

Crew Brief ............................. COMPLETE

PF

5.

Nav/Radio/Flight Sys/FMS Equipment.......................................... SET

LP/RP

6.

Battery Charge .................. 20 AMPS MAX

RP

7.

Cockpit & Cabin ......................... SECURE

RP/ET

8.

Flight Deck & Main Air Valves (2) ................................ CLOSE

RP

APU Bleed Air .................................... OFF

RP

10. APU Overspeed ................................. OFF

RP

11. Before Takeoff Checklist ....... COMPLETE

RP

9.

N-12

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

LINEUP 1.

Weather Radar.......................... AS REQD

RP

2.

Transponder/ IFF ............................... SET

RP

3.

Engine Ignitions (2) ................... AS REQD

RP

4.

Engine Anti-Ice (2) & TKS ......... AS REQD

RP

5.

Exterior Lights .................................... SET

RP

6.

MWS ............................................ CHECK

LP/RP

7.

APR.............................................. ARMED

RP

8.

Lineup Checklist.................... COMPLETE

RP

AFTER TAKEOFF/CLIMB If approaches are conducted within 15 minutes of takeoff, use Traffic Pattern/Before Landing checklist in lieu of After Takeoff/Climb, Cruise, and In Range/Descent checklists. 1.

Gear ..................................................... UP

PM

2.

Main Air Valves (2) ..........................OPEN

PM

3.

Yaw Damper ..............................ENGAGE

PM

4.

Flaps .................................................... UP

PM

5.

APR............................................. DISARM

PM

6.

Engine Ignitions (2) ................... AS REQD

PM

7.

Engine Anti-Ice (2) & TKS ......... AS REQD

PM

8.

ENG SYNC ........................................ SET

PM

9.

Landing Lights....................................OFF

PM

10. Aux Cooling Pack...................... AS REQD OFF/RECIRC above 9000 ft.

PM

11. Fasten Seat Belts Sign.............. AS REQD

PM

12. Engine Instruments ...................... CHECK

PM

13. Cabin Pressure ............................ CHECK

RP

14. Altimeters (2)...................................... SET

PF/PM

15. Taxi Lights.......................... OFF at 18000'

PM

16. Fuel Balance & Aux Transfer ....... CHECK

PM

17. After Takeoff/Climb Checklist COMPLETE

PM

NORMAL

N-13

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

CRUISE 1.

Altimeters ......................................CHECK PF/PNF

2.

Cabin Pressure & Temp................CHECK

RP

3.

Engine Instruments .......................CHECK

PNF

4.

Exterior Lights .................................... SET

PNF

5.

Electrical Systems.........................CHECK

PNF

6.

Fuel Balance & Aux Transfer ........CHECK

PNF

7.

Cruise Checklist .................... COMPLETE

PNF

NOTE Before entering and every hour thereafter. MAXIMUM CRUISE N1 (N1 - %; Indicated OAT - °C) ENG ANTI-ICE OFF Applicable at all flight speeds Monitor:

FL 410 390 370 350 330 310 290 270 250 230

ENG Anti-ice ON:deduct 1% from values given

N2 not more than 100% ITT not more than 908°C

-40 98.5 97.7 97.5 97.0 96.6 96.4 97.0

-35 98.5 98.1 97.8 97.5 96.9 96.6 96.5 96.9 97.1

-30 98.2 97.9 97.7 97.5 97.4 96.9 96.7 96.6 96.8 97.1

-25 98.0 98.0 97.6 97.4 97.3 97.3 97.0 96.7 96.7 96.9

-20 97.7 97.7 97.5 97.4 97.2 97.3 97.2 96.9 96.7 96.7

-15 97.2 97.0 96.9 97.0 97.2 97.0 97.0 96.7 96.7 96.7

-10

-5

0

96.4 96.3 96.5 96.7 96.9 96.8 96.8 96.7 96.8

96.0 96.2 96.4 96.5 96.7 96.6 96.6

95.8 96.1 96.3 96.4 96.4

+5

+10

95.4 95.6 96.0 95.3 96.0 95.3

Refer to the Performance Section for the above chart in its entirety.

N-14

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

IN RANGE - DESCENT 1.

Main Air Valves (2)..................OPEN

PM

2.

Flight Deck Valve ..................CLOSE

PM

3.

Fasten Seat Belts Sign.................ON

PM

4.

Seat Belts & Shoulder Harness....ON

PF/PM

5.

ATIS/Landing Data...............OBTAIN Computed

PM

6.

Arrival Briefing............... COMPLETE

PF

7.

Nav, Radios, Display Select Panel .......................................... SET

PF/PM

8.

Ice Protection .................... AS REQD

PF/PM

9.

Cabin Altitude & Rate................. SET

RP

10. WG Fuel/Xfeed/Transfer .......CLOSE

PM

11. Altimeters ................................... SET

PF/PM

12. Taxi Lights....................................ON at 18000ft

PM

13. In Range/Descent Checklist .............. ...................................... COMPLETE

NORMAL

PM

N-15

TI 4040.25.2 Temp Rev 03, 07/13/06

BAe 125-800A AVN Checklist

BEFORE LANDING 1.

Engine Ignitions (2) ................... AS REQD

PF/PM

2.

Engine Anti-Ice (2) & TKS ......... AS REQD

PF/PM

3.

Approach Briefing & VREF ...... COMPLETE Set

PF

4.

Nav, Radios, Display Select Panel.................................................. SET

PF/PM

5.

ILS Offset .................................. AS REQD ILS Offset must be OFF for landing.

PF/PM

6.

Altimeters ........................................... SET

PF/PM

7.

Airbrakes......................................... SHUT

PF/PM

8.

Flaps ....................................................15°

PF/PM

9.

ENG SYNC ........................................ OFF

PM

10. Cockpit & Cabin ......................... SECURE

PM/ET

11. Nosewheel Steering ...................... CLEAR

PF

12. Gear ............................ DOWN / 3 GREEN

PM

13. Nosewheel Steering .............. CENTERED

PF

14. Flaps ......................................... AS REQD

PM

15. Landing Lights........................... AS REQD

PM

16. Main Air Valves (2)..................... CLOSED

PM

17. Autopilot & Yaw Damper ......DISENGAGE

PF

18. Before Landing Checklist ...... COMPLETE

PM

N-16

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

TRAFFIC PATTERN - BEFORE LANDING If approaches/landings are conducted within 15 minutes of takeoff, use the Traffic Pattern-Before Landing checklist in lieu of After Takeoff/Climb, Cruise, and In Range/Descent checklists. 1.

Gear ..................................................... UP

PNF

2.

Main Air Valves (2) .................... AS REQD

PNF

3.

Yaw Damper ..............................ENGAGE

PNF

4.

Flaps ......................................... AS REQD

PNF

5.

APR (If Applicable) ...................... DISARM

PNF

6.

Approach Briefing & VREF ...Complete SET

PF

7.

Flaps .................................................. 15

8.

Nosewheel Steering ...................... CLEAR

LP

9.

Gear ............................. DOWN, 3 GREEN

PNF

10. Brakes .......................................... CHECK

PF

11. Flaps ......................................... AS REQD

PNF

12. Landing Lights........................... AS REQD

PNF

13. Main Air Valves (2) ........................CLOSE

PNF

14. Autopilot & Yaw Damper ......DISENGAGE

PF

15. TFS Pattern/Before Landing Cklist ..................................... COMPLETE

PNF

PATTERN SPEEDS Flap Setting 0° 15° Min Maneuver Speed (kts) V+30 V+25 THR Speed (still air) V+15 V+10

25° 45° V+20 V+10 V+5 V

REFERENCE SPEED (VREF) Weight (lb x 1000) 17 18 19 20 21 VREF (Knots)

NORMAL

PNF

22

23

112 115 119 122 125 128 130

N-17

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

ABOVE MAXIMUM LANDING WEIGHTS REFERENCE SPEED (VREF) 24 25 26 27 28 Weight (lb x 1000) 133 136 138 140 142 VREF (Knots) LANDING DISTANCE REQUIRED (Factored) ZERO WIND, ISA, DRY RUNWAY Wt x 23.0 22.0 21.0 20.0 19.0 18.0 17.0 1000lbs 23.35 VREF 131 130 128 125 122 119 115 112 IAS AFLD Elev C /Feet C /Feet C /Feet C /Feet Feet Feet Feet Feet 6000

20/5300 27/5230 31/5070 35/4900 4740 4580 4400 4230

5000

30/5180 31/5120 35/4950 39/4790 4630 4470 4300 4130

4000

33/5060 34/5000 38/4840 41/4680 4520 4360 4200 4040

3000

37/4930 38/4880 41/4720 45/4570 4410 4260 4110 3950

2000

39/4810 41/4760 44/4610

4460

4310 4160 4010 3860

1000

42/4700 44/4650 47/4500

4350

4200 4060 3910 3770

SL

45/4600 46/4540 49/4400

4250

4100 3960 3820 3680

NOTES:

•

The temperature shown in the above columns for the higher weights are the landing WAT limited temperatures for that weight and altitude. (Single engine, flap 15°.)

•

Chart based on ISA. Add 3% for each 10°C above ISA.

•

Flaps 25° -- Add 10%.

•

Flaps 0° -- Reduce landing distance available by 30% and compare to landing distance required above.

•

Unfactored = dist x 0.6. (i.e., landing distance factored by 1.67)

•

No lift dump--Recommend adding at least 250 feet.

•

No lift dump or airbrakes--Recommend increasing distance by 35%.

N-18

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999 WIND CORRECTION

Tailwind 10 Kt Add ft 1000 950 900 800 750

ZeroWind Distance Ft 5500 5000 4500 4000 3500

10 Kt 300 250 250 250 250

Headwind 20 Kt 30 Kt Subtract Ft 550 850 550 800 500 750 500 750 450 700

40 Kt 1100 1050 1000 950 900

AFTER LANDING If both engines are to be shut down, accomplish the After Landing checklist. Otherwise, proceed to the Taxi Back checklist. 1.

Exterior Lights .................................... SET

RP

Landing lights, if used, should be turned off as soon as practical after landing. 2.

Airbrakes ......................................... SHUT Flaps .................................................... UP

LP/RP

3.

Pitot/Vane Heat (2).............................OFF

RP

4.

Engine Anti-Ice (2) & TKS ..................OFF

RP

5.

Engine Ignitions (2) ............................OFF

RP

6.

Weather Radar...................................OFF

RP

7.

Transponder............................. STANDBY IFF......................................................OFF

RP

8.

Laser Altimeter ...................................OFF

RP

9.

APU...........................................AS REQD

RP

10. After Landing Checklist ......... COMPLETE

RP

Proceed to Stopping Engines checklist.

NORMAL

N-19

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

TAXI BACK 1.

Exterior Lights .................................... SET

RP

Landing lights, if used, should be turned off as soon as practical after landing. 2.

Engine Ignitions (2) ................... AS REQD

RP

3.

Engine Anti-Ice (2) & TKS ......... AS REQD

RP

4.

Weather Radar.......................... AS REQD

RP

5.

Transponder/ IFF ...................... AS REQD

RP

6.

Airbrakes......................................... SHUT

LP

7.

Flaps .................................................. SET

RP

8.

Trim.................................................... SET

RP

If one engine is shut down, proceed with Starting Engines checklist, then continue with this checklist. 9.

Takeoff Data & Crew Briefing.................................. COMPLETE

PF

10. Nav/Radio/Flight Sys/FMS Equipment.......................................... SET

LP/RP

11. Flt Deck Valve & Main Air Valves (2)...................................... CLOSE

RP

12. Cockpit & Cabin ......................... SECURE

RP/ET

13. Taxi Back Checklist............... COMPLETE

RP

Proceed to Lineup Checklist.

STOPPING ENGINES 1.

Taxi Lights.......................................... OFF

RP

2.

Parking Brake .................................... SET

LP

3.

IRS ..................................................... OFF

LP

CAUTION IRS Mode Select switch must be OFF for at least 10 seconds prior to turning off acft power or the IRU Backup Battery will discharge completely.

N-20

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 02, 07/2003

4.

Screen Heat (2).................................... OFF

RP

5.

Alternators (2) ...................................... OFF

RP

6.

EFD(2), MFD, ADS(2), AHRS(2) MSTRS ................................. OFF

RP

7.

Nav/FMS Equipment ............................ OFF

RP

8.

FIS Power ....................................AS REQD RP/ET

9.

HP COCKs (2)..................................CLOSE

LP

10. Engine Computers (2) .......................... OFF

RP

11. Fuel Pumps (2)..................................... OFF

RP

12. GEN FAIL Annunciators (2).................... ON

RP

13. No Smoking and Fasten Seat Belts Signs ....................... OFF

RP

14. Oxygen and Cabin Isolation Valves (2) .................... OFF

LP

15. Flight Control Locks .....................AS REQD

LP

16. Aux Cooling Pack ................................. OFF

RP

17. APU Bleed Air ...................................... OFF

RP

18. APU Generator.................................... TRIP

RP

19. APU.................................... Overspeed OFF

RP

20. Inverters ............................................... OFF

RP

21. Cabin Emergency Lights ...................... OFF

RP

22. Radios .................................................. OFF LP/RP 23. Exterior Lights ...................................... OFF

RP

24. Battery.................................................. OFF

RP

25. Chocks ........................................ IN PLACE

RP

26. Parking Brake....................................... OFF

RP

27. CVR Circuit Breaker (B17 &18) ....................................AS REQ’D LP/RP Pull the CVR Circuit Breaker when a reportable in-flight incident ensuring data is preserved for investigation. Make a logbook entry and verbally notify maintenance. 28. Stopping Engines Checklist ... COMPLETE

NORMAL

RP

N-21

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

EXPANDED NORMAL WEATHER RADAR CHECK WARNING Do not turn the WXP-85 Weather Radar panel mode switch to any position except OFF, STBY, or TEST when the antenna will be directed toward ground personnel, nearby hangars or other large metal buildings, or other aircraft. Never operate the weather radar during fueling or de-fueling operations. If either MFD PWR or RDR buttons are OFF, the radar transmitter may still be transmitting. This can occur if the mode switch on the WXP control unit is in the WX, NORM or MAP position, and could possibly result in injury to ground personnel. To test WXP-85 for operational considerations set control unit switches as follows: MODE selector to TEST. RANGE to 25 miles. GAIN to MAX. TILT to +5°. STB button in (ON). Ensure MFD PWR is on and RDR mode selected. Confirm correct test pattern (allow 60 seconds for this to appear): 1. Four distinct colors from apex to center of screen. 2. From lower center of display, nine distinct color bands extend outwards in the following order: Green, Yellow, Red (contour band cycling to black in a one to one ratio), Magenta, Red (contour band cycling to black in a one to one ratio), Yellow, Green, Black, Yellow (alert band located at outer perimeter of the display).

N-22

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

3.

No noise present on the display (no more than six random dots).

4.

Momentarily set mode selector to WX, then back to TEST.

Press and release HLD button before completion of test pattern. Confirm that test pattern freezes on display. Confirm HOLD and TEST display alternately in upper left of MFD display. Press and release HLD button. Confirm that test pattern returns to normal updating. Set MODE selector to WX. Confirm "WX" is annunciated in upper left of MFD display. Set RANGE to 10 mi. annunciation is "5".

Confirm range mark

Adjust TILT between +15° and -15°. Observe that close in ground clutter appears at lower settings and any local detectable weather appears at higher settings. Set MODE selector to STBY.NAV and RADIOS CHECK Tune and identify the desired NAVAIDs. If a more detailed check is required, complete the following tests.

NAV and RADIO CHECK Tune and identify the desired NAVAIDs. If a more detailed check is required, complete the following tests. General 1. TACAN (2)...................... Set ON/OFF Switch To ON TEST/ON/SBY Switch To SBY 2.

V/UHF NAV (3).................... Set Mode Switch To TR

3

ATC Xpndr ......................Set Mode Switch To STBY

4

ADF ................................... Set Mode Switch To ADF

5

VHF 1 Radio................Set OFF/TR/DF Switch to TR

6.

UHF Radios (2) ...........Set Function Switch to BOTH

NORMAL

N-23

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

TACAN Equipment (2) 1. Set both NAV 1 SELECT and NAV 2 SELECT to TACAN. 2.

Set DSP (2) switches as follows: BRG to VOR 1, VOR 2 FORMAT to ROSE CRS to VOR/LOC Course arrow to 000°

3.

Set BDI Switches (4) to TACAN 1 & TACAN 2.

4

Set TEST/ON/SBY switch to TEST.

5.

Check distance warning flags on BDI show for 3 seconds and are then replaced by 00.0, accompanied by identification tone in headset.

6.

Both BDI pointers indicate 180°

7.

With DSP CRS set to north, ND gives zero bearing and deviation, and FROM indication.

8.

Set TEST/ON/SBY switch to ON or SBY as required.

VHF NAV Equipment (2) 1. Set both NAV 1 SELECT and NAV 2 SELECT to VOR/LOC. 2.

Set DSP (2) switches as follows: BRG to VOR 1, VOR 2 FORMAT to ROSE CRS to VOR/LOC Course arrow to 000°

3.

Select BDI switches (4) to VOR 1 and VOR 2.

4.

Select usable VOR/VOT frequency.

5.

Depress and hold TEST button on VHF NAV control unit and confirm the following: (a)

N-24

Active and preset display brightness varies from minimum to maximum. The preset frequency display shows 00, and active frequency display shows "----"

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

(b)

Lateral deviation warning legends appear on PFD and ND. After approximately 3 seconds, the warning legends are removed, the lateral deviation bar centers and a TO indication appears. The BDI pointers indicate approximately 000° magnetic bearing.

(c)

NAV 1 test only: marker annunciator symbols flash on left PFD. Airways marker annunciator symbol flashes on right PFD. MKR annunciators light on left and right instrument panels.

(d)

Diagnostic legends appear in the control unit displays. After approximately 15 seconds, the lateral deviation warning legends appear. After approximately another 3 seconds, the system reverts to normal operation.

(e)

Release TEST button. BDI DME’s briefly show all 8's.

6.

Set each VHF NAV control unit mode switch to HLD and check appropriate HOLD annunciator lights on BDI's, and HLD annunciator lights on control unit.

7.

The letter "H", in yellow, appears to the right of the DIST digits on the ND.

8.

The freq digits of "held" station appear on preset display.

9.

Select local localizer frequency.

10. Select course pointer under lubber line. 11. Depress and hold TEST button on the VHF NAV control unit and confirm the following: (a)

The LOC and GS warning legends displayed.

(b)

After approximately 3 seconds, the LOC and GS warning legends are removed, the lateral deviation bar deflects right approximately 1/2 full scale, and the GS pointer deflects down approximately 1/2 full scale.

NORMAL

are

N-25

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

(c)

(NAV 1 test only): marker annunciator symbols appear in sequence, flashing, on left PFD. Airways marker annunciator symbol appears, flashing, on right PFD. MKR annunciators light on left and right instrument panels.

(d)

After approximately 15 seconds, the LOC and GS warning legends reappear. After approximately another 3 seconds, the system reverts to normal operation.

(e)

Release TEST button. BDI DME displays briefly, showing all 8’s.

FAR 91.171 VOR Equipment Check 1. Perform VHF NAV Equipment steps (a) through (d) above. 2.

If using one NAV system against the other: Center each course arrow on the received radial (FROM bearing).

3.

If using a VOT signal: Center each course arrow. This should occur at or near 000°.

4.

If using a Ground Receiver Checkpoint: Align the aircraft on the checkpoint and center each course arrow.

5.

Note the bearings received in (b), (c), or (d) above. The difference must be within 4°. Enter the required data on the VOR Equipment Check form in the Aircraft Logbook.

ATC Transponder The TEST position of the selector knob is for ground use only. ADF Equipment 1. Set DSP switches (2) as follows: BRG to ADF FORMAT to ROSE 2.

N-26

Select BDI switches (2) to ADF.

NORMAL

BAe 125-800A AVN CHECKLIST 3.

TI 4040.25 CHG 01, 06/1999

Select usable local frequency and set mode switch to TONE and check the following: (a)

1 kHz tone is audible in headset.

(b)

Magenta cross ended bearing pointers on ND’s and BDI single pointers indicate relative bearing of transmitting station.

NOTE If no ADF signal is received, the bearing pointers will park at 90°. 4.

Set mode switch to ADF. Check ND and BDI pointers maintain relative bearing.

5.

Press and hold ADF TEST button. following:

Check the

(a)

Active and preset brightness varies from minimum to maximum.

(b)

ND bearing pointers and BDI pointers rotate 90 clockwise from previously valid positions.

(c)

Diagnostic legends appear in the control unit displays.

6.

Release TEST button. Check that pointers return to their previously valid positions.

7.

Set ADF mode switch to ANT. Check that ND and BDI pointers park at 90° and a 1 kHz tone is audible in the headset.

8.

Set ADF mode switch to ADF.

NORMAL

N-27

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

EFD - CHECK 1.

Right DPU switch ........................................... PRESS White ALTN legend lights

2.

Left EFIS GRND TEST .................................. PRESS and HOLD

NOTE Note that 10° is added to current values of pitch and roll and 20° is added to heading, with a positive increment added to the pilot’s side. 3.

Left and right PFD ........................................... Check Yellow PIT and ROL comparator warnings flash.

4.

Left and right ND ............................................. Check Yellow HDG comparator warning flashes.

NOTE Note that after four seconds the attitude displays on the PFD and the MFD are removed from view and that all flags associated with the PFD and ND are in view. 5.

Left EFIS GRND TEST .............................RELEASE Check altitude display normal, all comparator warnings on.

6.

CMPTR PTR (2)............................................ PRESS Check comparator warnings out.

7.

Right DPU ALTN Switch ............................... PRESS White ALTN legend out.

8.

Left DPU ALTN switch .................................. PRESS White ALTN legend lights.

9.

Right EFIS GRND TEST ............................... PRESS and Hold Repeat test for copilot's EFIS ground test. Release. Check altitude display normal, all comparator warnings on.

N-28

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

10. Both CMPTR PTR ......................................... PRESS Check comparator warnings out. 11

Left DPU ALTN ............................................. PRESS White ALTN legend out.

AUTOPILOT CHECK CAUTION Autopilot shall not be used in flight if auto-trim is unserviceable. Do not permit autopilot to drive primary controls or elevator trim onto stops. The yaw damper must not be engaged for takeoff or landing. Yaw damper may be engaged after takeoff but must be disengaged before touchdown.

NOTE When power is applied to the autopilot system, an internal self-test cycle ensures proper operation of command limiters. Autopilot and yaw damper engagement is inhibited during this 30 second cycle. 1.

Check full free movement of flight controls.

2.

Centralize and hold flying controls.

3.

Engage autopilot AP and YD levers.

4.

Push control column forward and check nose up trim wheel movement occurs in pulses and trim indicator moves to rear. Check AP TRIM EL indicator reading moves aft.

5.

After a delay, check AP TRIM annunciators lit on both pilots’ panels and E legend displayed on PFD’s.

6.

Pull control column back and check nose down trim wheel movement occurs in pulses and trim indicator moves forward. Check AP TRIM EL indicator moves forward.

7.

Check AP TRIM annunciator and PFD E legends go out, then reappear after a short delay.

8.

Center the control column.

NORMAL

N-29

TI 4040.25 CHG 01, 06/1999 9.

BAe 125-800A AVN CHECKLIST

Rotate control column wheel slightly clockwise. Check AP TRIM AIL indicator reading moves counterclockwise.

10. After a short delay, check AP TRIM annunciator lit and A legend displayed on PFD’s. 11. Rotate control column wheel slightly counterclockwise. Check AP TRIM AIL indicator reading moves clockwise. 12. Check AP TRIM annunciator and PFD A legends go out and then reappear after a short delay 13. Center the control column. 14. With autopilot engaged. Check AP DISC buttons (2), autopilot panel AP lever, and either No. 1 or No. 2 Stall Test button disengage the autopilot. Check AP annunciators flash and audio warning operates. 15. With only yaw damper engaged, check AP DISC button disengages yaw damper. 16. With autopilot engaged, press both GA buttons in turn, and check autopilot disengages, annunciators flash, audio warning operates, PFD FD bars command 12° nose up and wings level, and GA legend is displayed on PFD’s. 17. Confirm turn knob is centered.

N-30

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

OVERHEAD TEST PANEL CHECK NOTE When preparing for a Battery Only Engine Start, not all tests can be completed on battery power. Ensure Engine Fire tests are accomplished, and perform remainder of the tests after engine start.

NOTE On Thruflight, only the ENG FIRE tests are required. 1.

Press No 1 Stall Test button. Check stick shaker motors operate and IDNT 1 and MWS Stall IDENT annunciators light after a 4 to 5 second delay. Release No 1 Stall Test button. Reset MWS. Repeat for No 2 Stall Test button (IDNT 2 lights) Press No 3 Stall Test button. Stick shaker should not operate. Check IDNT 3 and MWS Stall IDENT annunciators light after 4 to 5 second delay. Release No 3 Stall Test button. Reset MWS. Press any two Stall Test buttons at the same time. Check stick shaker operates and pusher operates after a slight delay. Pilot's and copilot's Stall VLV A OPEN and Stall VLV B OPEN annunciators light. Pusher will not operate unless the yoke is held slightly back from neutral and the main hydraulic system is charged.

2.

Press and hold ENG Fire 1 Test button. ENG 1 Fire annunciator, MWS red flashers, MWS ENG 1 Fire  repeater, and No 1 HP COCK warning light all illuminate. engine fire warning bell rings. Press Bell Cancel 1. Fire warning bell stops. Bell CNCLD 1 annunciator lights.

NORMAL

N-31

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

Press Bell Cancel 1 a second time. Fire warning bell rings. Bell CNCLD 1 annunciator goes out. Release ENG Fire 1 Test button. Engine fire warning bell stops. ENG 1 Fire annunciator, MWS ENG 1 Fire  repeater, and No. 1 HP Cock warning light all extinguish. Repeat test for No. 2 engine using ENG Fire 2 Test button and corresponding No. 2 engine warning indicators. 3.

Press HP Air OVHT Test button. Check MWS HP Air 1 OVHT and HP Air 2 OVHT annunciators and MWS flashers illuminate. Release HP Air OVHT Test button. MWS HP AIR 1 OVHT and HP AIR 2 OVHT annunciators extinguish.

4.

Press ICE DET Test button. ICE DETECTD annunciator lights. MWS ICE PROT repeater annunciator flashes. Release ICE DET Test button. ICE DETECTD annunciator goes out after approx 20 seconds.

5.

With flaps up, press Cabin Alt Test button. MWS Cabin Alt annunciator lights. Steady warning horn sounds. Silence horn using Horn Isolate button on No 1 throttle. Release Cabin Alt Test button. Warnings cease.

6.

Press and hold ADS AHRS 1 TEST button. Pilot's Air Data Fail annunciator lights momentarily. MSI flag on, IAS and VMO pointer at zero, Mach blank. Altimeter flag on, pointer at 250 feet. VSI flag on, pointer at 6,000 ft/min down. SAT/TAS indicator blank. Confirm ATT and HDG warnings do not appear. Press Air Data Transfer switch in order to test the transfer function, then release after confirming operation. Release ADS AHRS 1 Test button. Check flags off. Repeat for copilot's instruments using ADS AHRS 2 test.

N-32

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

NOTE If ATT and HDG warnings appear during the ADS AHRS 1 Test procedure, the AHRS backup power is not available. This defect must be rectified before flight. If Air Data Fail annunciators remain lit for approximately 45 seconds after release of test button, ADS backup power is not available. This defect must be rectified before flight. 7.

Press VMO/MMO Test button 1 and 2 in turn and check intermittent operation of warning horn. With fuel in ventral tank, press LO VMO Test buttons 1 and 2 in turn and check intermittent operation of warning horn. Pressing and holding the LO VMO Test buttons also checks the related air data system.

ENGINE STARTING MALFUNCTIONS Abort Start Procedures Abort start by closing HP Cock immediately, then operating Press For Abort switch if any of the following conditions occur: -

No light-up within 10 secs of opening HP Cock.

-

ITT rapidly approaches 952°C.

-

Idle rpm (27% N1; 48-67% N2) not reached by 50 secs after light up.

-

Oil 2 LO Press annunciator not out before idle rpm.

-

N1 or N2 stops increasing before idle rpm.

NORMAL

N-33

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

After Aborting Engine Start If an engine fails to start and is shut down by closing the HP COCK and operating the PRESS FOR ABORT switch, proceed as follows: -

Wait 3 minutes to allow fuel to drain, or motor engine for 15 seconds (do not exceed 2 minutes of motoring).

-

Check the ignitor plugs are functioning correctly by operating the appropriate ENG IGNITION switch. The sparking of the ignitor plugs can be checked aurally by the ground crew. Reset ENG Ignition switch to OFF. If satisfactory, resume normal starting procedure.

-

If two unsuccessful attempts to start are made, the cause must be investigated and any fault rectified before making further attempts.

CAUTION Do not attempt a restart until indicated ITT is less than 200°C.

WARNING Electrical discharge from high energy units is potentially lethal. If for any reason ignitor leads are disconnected, do not handle LT leads or ignitor plugs for at least one minute after disconnecting the LT input.

N-34

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

APS-85 AUTOPILOT DIAGNOSTICS Pilot Instructions 1. If autopilot disengages during flight it is important to record the AP DIS CODE and the YD DIS CODE prior to power shutdown. 2.

If the autopilot cannot be engaged it is important to record the AP ENG CODE and the YD ENG CODE prior to power shutdown.

3.

If the EFIS "FD" flag is in view it is important to record the STEER CODE while the FD flag is displayed.

4.

If possible, allow maintenance personnel to view diagnostic data prior to power shutdown.

To Enter Diagnostics 1. Press and hold the EFIS GROUND TEST button. Then press and release the RA TEST button on the DCP (display control panel) or the TST button on the DSP (display select panel). The DCP or DSP are part of the EFIS system. 2.

Release the EFIS GROUND TEST button.

3.

Press and release the RA TEST (or TST) button 3 times, or until FCS DIAGNOSTICS appears at top of the EFIS display.

4.

Press and hold any 3 active MSP buttons for 2 seconds. The EFIS should now display REPORT MODE.

5.

Record the appropriate AP and YD DIS CODES, AP and YD ENG CODES, or the STEER CODE. If the two YD CODES or the STEER CODE are not on the screen, use the APP pitch wheel to select the codes (as described below). The codes are selectable in alphabetical order. To change codes, increment the APP pitch wheel in either direction. Hold pitch wheel out-of-detent to continuously cycle through the parameter codes.

6.

Each parameter code consists of 6 digits for both left and right side data. Record all 6 digits (in proper sequence) of both left and right columns of pertinent parameters. Include all zeros.

NORMAL

N-35

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

To Exit Diagnostics Press the AP DISC switch, or press any 3 active MSP buttons.

PASSENGER BRIEFING (Pic or Crewmember) 1. Smoking: Prohibited in FAA aircraft. Tampering, disabling, or destroying any smoke detector is prohibited. The NO SMOKING sign will be on at all times. 2.

Safety belts: This is to include specific instructions on the fastening and release of seatbelts, directions to keep the seatbelts fastened during all surface movement, takeoffs, landings, and a recommendation that seatbelts be kept fastened en route to avoid injury resulting from unexpected turbulence.

3.

Seat backs: If applicable, the placement of seat backs in the upright position while the aircraft is taxiing and during takeoff and landing operations.

4.

Passenger entry door and emergency exits: Location and means of opening the cabin door and emergency exits.

NOTE Persons who need assistance to exit the aircraft will not be carried aboard flight inspection airplanes. 5.

Fire extinguisher: extinguisher(s).

6.

Survival equipment: Location and use of survival equipment.

7.

Ditching procedures: If the flight includes extended overwater operation, ditching procedures, and the use of required flotation equipment.

8.

Oxygen: If the flight involves operations above 12,000 feet mean sea level (MSL), the normal and emergency use of oxygen.

9.

Headsets: The location of the additional headset.

N-36

Location and operation of fire

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

TAKEOFF CREW BRIEFING/CONSIDERATIONS Takeoff Briefing Crewmembers shall adhere to the following procedures. After the first flight, the term "standard briefing" may be used provided the crew positions and duties are not changed. Before taking the active runway for departure, a takeoff briefing will be accomplished by the Pilot Flying (PF). Prior to takeoff, the PF will cover the following items. (1)

Aircraft Configuration,

(2)

Power Limitations,

(3)

Engine instruments, monitor during takeoff,

(4)

V Speeds,

(5)

Emergency Procedures,

(6)

Emergency Return,

(7)

Initial altitude and heading for departure, and

(8)

Answer any questions from other crewmembers.

NORMAL

N-37

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

INSTRUMENT APPROACH REVIEW When executing any instrument approach for the purpose of landing, including a visual approach for the intention of landing, an oral briefing will be accomplished by the PF and will cover the following items, as applicable. 1.

Review the name of the Approach--i.e., ILS RWY 17R, Will Rogers Airport.

2.

Field Elevation -- _____________ MSL.

3.

Approach Altitudes - __________________ MSL (as applicable)

4.

Minimum Altitude on Approach -- DH/MDA of __________ MSL.

5.

How procedure will be flown; i.e., time, rate of descent, etc.

6.

Missed approach point and procedure.

7.

Other instructions by the PF such as:

N-38

(a)

Tuning and setting of navigation radios.

(b)

Heading changes required on approach.

(c)

Other call-out procedures as requested.

(d)

Verify systems not working applicable to the approach in use.

(e)

Verify runway conditions.

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

DC Power System – De-Energized Schematic

NORMAL

N-39

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

AC Power System - Schematic

N-40

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

DC Power Distribution - PE Bus Bar

NORMAL

N-41

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

DC Power Distribution - PS1 Bus Bar

N-42

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

DC Power Distribution - PS2 Bus Bar

NORMAL

N-43

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

AC Power Distribution

N-44

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 CHG 01, 06/1999

Refuel/De-fuel System Schematic

NORMAL

N-45

TI 4040.25 CHG 01, 06/1999

BAe 125-800A AVN CHECKLIST

Hydraulic System Schematic

N-46

NORMAL

BAe 125-800A AVN CHECKLIST

TI 4040.25 Original, 03/1997

EMERGENCY/ABNORMAL PROCEDURES IMMEDIATE ACTION Memory items (“phase one” or “boldface”) are in bold text, and are boxed and shaded. These items should be completed in as timely matter as possible consistent with controlling the aircraft on the desired flight path. Hurried action can result in a more serious situation than the emergency itself. Therefore, memory items must be accomplished with care and coordination between all crewmembers. In addition to the outlined items in the checklist procedure, the following steps are considered part of all emergency or abnormal situations: 1.

Fly the aircraft.

2.

Silence any aural warning.

3.

Identify the emergency or abnormality.

4.

Perform memory items at a safe altitude (400 ft AGL minimum).

5.

Use the appropriate checklist(s) to confirm accomplishment of memory items. Complete the checklist observing any NOTE, CAUTION , or WARNING , as applicable.

SPECIFIC PROCEDURES It is not possible to develop specific procedures to cover all possible combinations of emergency/abnormal situations. Therefore, if a situation exists for which these procedures are not adequate or applicable, the pilot’s best judgment must prevail.

A

TI 4040.25 Original, 03/1997

BAe 125-800A AVN CHECKLIST

MASTER WARNING ANNUNCIATION TAB#

TAB#

AUX PACK

SMOKE

4

HP AIR 1 OVHT

6

REAR BAY 6 OVHT

ENG 1 FIRE

1/2

CABIN 5/10 ALTITUDE

OIL 1 LO PRESS

14

ELEV/AIL TRIM

HYD 1 LO PRESS

16

MAIN AIR VALVE 1 ENG 1 CMPTER

4

ENG 1 A-ICE ELECT

________

9

HP AIR 2 OVHT ENG 2 FIRE

6 1/2

OIL 2 LO PRESS 14

HYD OVHT 16

HYD 2 LO PRESS 16

AUX HYD LO LEVEL

MAIN AIR VALVE 2

EMER BRK 8 LO PRESS

ENG 2 CMPTER

FUEL

15

DUCT OVHT

ENT DOOR UNLOCKED

APU MSTR SW ON

RUDDER BIAS

ICE PROT SELECTED

FUEL XFD TFR

STALL IDENT

B

4

ENG 2 A-ICE

ICE PROT 11

TAB#

10

BAe 125-800A AVN Checklist

TI 4040.25.2 Temp Rev 01, June 2005 Table of Contents

TAB

Ground Emergencies APU Fire ...................................................................... 1 APU Failure.................................................................. 1 APU Generator Overheat............................................. 1 Engine Fire................................................................... 1 Takeoff Emergencies Rejected Takeoff.......................................................... 2 Landing Gear Retraction Fail ....................................... 2 Gear Handle Can’t Be Moved ...................................... 2 In Flight Emergencies Engine/Fire/Failure/Shutdown...................................... 2 Two Engine Failure ...................................................... 3 Starter Assisted Air Start.............................................. 3 Windmill Air Start ......................................................... 4 Compressor Stall ......................................................... 4 Engine Computer Malfunction...................................... 4 Smoke and Fumes ..................................................... 5 Smoke/Fire In Aft Baggage.......................................... 5 Smoke/Fire In Vestibule, Cabin or Cockpit..................................................................... 5 Smoke and Fume Elimination ...................................... 5 Electrical Fire ............................................................... 5 Air Conditioning Smoke/Fumes ................................... 6 Depressurization/EMERG Descent........................... 6 Rear Equipment Bay Overheat ................................. 6 High Pressure Air Overheat ......................................... 7 Landing Emergencies Landing Gear Extension Failure .................................. 7 Hydraulic system failures ............................................. 8 Main System Brake Failure.......................................... 8 Emergency brake low pressure ................................... 8 No Flap Landing........................................................... 9 Landing Emergencies Cont’d Asymmetric Airbrakes .................................................. 9 Single Engine Landing ................................................. 9 Single Engine Go Around ............................................ 9 Trim Only Landing........................................................ 9 Ditching ...................................................................... 10 Forced Landing .......................................................... 10 Air Conditioning/ Pressurization Duct Overheat............................................................ 10 Automatic Temp Control Failure ................................ 10 Failure To Pressurize................................................. 10 Automatic Pressure Control Fail ................................ 10 Auxiliary Cooling Pack Failure ................................... 10 Pressurization Regulation Failure .............................. 10

Continued Next Page

E-iii

TI 4040.25.2 Temp Rev 02, October 2005 Table of Contents

BAe 125-800A AVN Checklist TAB

Avionics/Pitot Static Air Data Computer Failure..........................................11 AP/AHRS Fan Fail PTR .............................................11 EFIS Fan Failure ........................................................11 EFIS Overheat............................................................11 DPU Failure................................................................11 PFD Failure ................................................................11 ND Failure ..................................................................11 Unreliable Airspeed ....................................................11 Pitot Heat Failure .......................................................11 Electrical Double Generator Failure...........................................12 Single Generator Failure ............................................12 Fluctuating/Abnormal Voltage ....................................12 PS2 Powered Circuits ................................................12 Generators Out of Balance.........................................13 Battery Hot .................................................................13 Battery Overheat ........................................................13 XE Failure...................................................................13 XS1 and XE Failure....................................................14 XS1 or XS2 Failure.....................................................14 Double Inverter Failure ............................................14 Single Inverter Failure..............................................14 Alternator Failure........................................................14 Double Alternator Failure ...........................................14 Engines High RPM or High ITT ................................................15 Fluctuating RPM.........................................................15 High Oil Temperature .................................................15 Oil Low Pressure ........................................................15 Flight Controls/Autopilot False Stick Shaker/Pusher .........................................15 Electric Pitch Trim Runway ........................................15 Autopilot Trim Warnings .............................................15 Fuel Auxiliary Fuel Transfer Failure ...................................16 Fuel Low Pressure .....................................................16 Engine Fuel Malfunction.............................................16 Hydraulics Hydraulic Low Pressure .............................................16 Main Hydraulic Failure................................................16 Hydraulic System Overheat............................................ Windscreen Windscreen Overheat.................................................16 Side Screen Overheat ................................................16 Windscreen Failure ....................................................16

E-iv

BAe 125-800A

TI 4040.25C Original, March 1997

EMERGENCY/ABNORMAL GROUND EMERGENCIES APU Fire 1. APU MASTER.....................OFF (Wait 10 Seconds)

RP

2. APU EXTINGUISHER...........................DISCHARGE (If Required)

RP

CAUTION If APU is not running when fire bell and annunciator are activated, discharge APU extinguisher immediately. 3. No. 1 LP Cock ................................................ CLOSE

RP

APU Failure 1. APU Master ......................................................... OFF

RP

APU Generator Overheat 1. APU Master ......................................................... OFF

RP

Do not attempt to restart APU until the problem is rectified.

Engine Fire

ENG FIRE

1. HP COCK.......................................................CLOSE

LP

2. LP COCK .......................................................CLOSE

LP

3. START PWR ....... PUSH FOR ABORT (If Required)

LP

4. EXTINGUISHER .....................SHOT 1 (If Required)

LP

5. Extinguisher.............................. SHOT 2 (If Required)

LP

6. Battery Power...................................................... OFF

LP

7. Evacuate Aircraft ..................................................ALL

NOTE 1.

Make no attempt to restart the engine after a fire warning.

2.

Closure of No. 1 LP cock will automatically shut down the APU if it is running.

E-1

TI 4040.25C Original, March 1997

BAe 125-800A

TAKEOFF EMERGENCIES Rejected Takeoff 1. Throttles ....................................................... IDLE

PF

2. Airbrakes.................................................... OPEN

PF

3. Brakes......................................... AS REQUIRED

PF

On Slippery Runways: 4. Flaps ...............................................................45°

PNF

5. Lift Dump..............................OPEN AT 45° FLAP

PF

6. Downwind Engine HP Cock..................... CLOSE (As Required)

PF

Landing Gear Retraction Failure 1. Aux Hyd Hand Pump ....SOCKET FULLY DOWN

PNF

2. Aux Hyd Pull Selector ...............................SET IN

PNF

If Gear Still Fails to Retract: 3. Ground Locks .........................CHECK STOWED

PNF

4. Landing Gear Lever ..................................DOWN

PNF

LAND AS SOON AS PRACTICAL after reducing aircraft weight to below normal landing limit of 23,350 lb.

Landing Gear Handle Cannot Be Moved If Retraction is Essential: 1. O/Ride and Landing Gear Levers ................ SELECT UP TOGETHER

E-2

PNF

BAe 125-800A

TI 4040.25C Original, March 1997

IN FLIGHT EMERGENCIES Engine Fire / Failure / Shutdown

ENG FIRE

1. HP COCK.......................................................CLOSE

PF

2. LP COCK .......................................................CLOSE

PF

3. EXTINGUISHER ...................... SHOT 1 (If required)

PF

4. Generator ........................................................... TRIP

PNF

5. Bustie ............................................................. CLOSE

PNF

6. Main Air Valve ................................................ CLOSE

PNF

7. Flight Deck Valve (No. 2 Engine Only)........... CLOSE

PNF

CAUTION If shutdown occurs during climb, close both main air valves to ensure maximum thrust from the operating engine. If shutdown is during descent, set main air valve on remaining engine to LP ON. Do not attempt to restart engine if there are any reasons to suspect mechanical malfunction or failure.

8. Engine Ignition ............................................ OFF

PNF

9. Extinguisher ....................... SHOT 2 (If required)

PNF

If warning goes out, release canceled fire bell and test fire detection system. If system does not function, confirm engine status visually.

10. Engine Sync................................................ OFF

PNF

11. Alternator .................................................... OFF

PNF

12. Generator Amps ....................................CHECK BELOW 400 UP TO 10,000 FT OR 330 ABOVE 10,000 FT

PNF

13. Wing Fuel/X Feed/Transfer ................... X FEED

PNF

14. Fuel L and R Pump Switches.. BALANCE FUEL

PNF

NOTE If engine failure occurs during normal climb, and if cruise flight is to be continued, increase power on the operating engine to maximum continuous (100% or 924°C, whichever is lower) and climb at enroute climb speed to the required cruise altitude.

E-3

TI 4040.25C Original, March 1997

BAe 125-800A

Two Engine Failure 1. THROTTLES ......................................................IDLE

PF

2. ENGINE IGNITIONS............................................. ON

PF

3. Engine Indications .....................................MONITOR

PNF

If N1 and N2 RPM do not increase within 10 seconds: or if ITT rapidly approaches 952°C: 4. HP Cock (Affected Engine)............................ CLOSE 5. Engine Ignition (Affected Engine) ........................OFF

PNF PNF

When engine(s) has successfully started: 6. Throttles .....................................SET AS REQUIRED

PF

Wait until engines have stabilized before selecting ignition(s) off, then confirm IGN ON annunciator out. If only one engine starts, leave the running engine ignition on. 7. 8. 9. 10.

Engine Ignitions ...................................................OFF Engine Indications ...................................... NORMAL Generators ..................................................... CLOSE Bustie ............................................................. CLOSE

PNF PNF PNF PNF

Check generators balanced and below 400 amps up to 10,000 ft or 330 amps above 10,000 ft. If engine does not airstart: accomplish ENGINE FIRE/FAILURE/SHUTDOWN Checklist

Airstart Envelope

30

20

COMPUTER INOPERATIVE WINDMILL

10

0

0 ALTITUDE (1000s of ft)

100 200 INDICATED AIRSPEED (knots)

E-4

300

BAe 125-800A

TI 4040.25C Original, March 1997

Starter Assisted Airstart 1. Speed and Altitude ....................WITHIN ENVELOPE 2. N1 and N2 .................................... BOTH INDICATING

PF PNF

CAUTION Do not attempt airstart if there is no indication of N1 rotation. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

HP Cock ......................................................... CLOSE LP Cock............................................................ OPEN Engine Anti-Ice .................................................... OFF Fuel Pump .............................................................ON Engine Sync ........................................................ OFF Main Air Valve ................................................ CLOSE Start Power............................................................ON Engine Starter Switch............................................ON HP Cock ...........................OPEN AT/ABOVE 10% N2 Fuel Enrichment ............... PRESS UP TO 400°C ITT Fuel Flow..................................CHECK INDICATION ITT ............................................................. MONITOR

PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF

If light up does not occur within 10 secs, or: If ITT rapidly approaches 952°C, or: If no oil pressure is indicated within 10 sec of light up: 15. HP Cock ......................................................... CLOSE 16. Start Power................................. PUSH FOR ABORT

PNF PNF

CAUTION Wait 10 seconds between airstart attempts (for fuel drainage). After Start: 17. Engine Start Switch ...... LIGHT OUT ABOVE 45% N2 18. Start Power..................................PUSH, LIGHT OUT 19. Generator .....................................................ON LINE 20. Bustie ............................................................. CLOSE 21. Engine Indications .......................................NORMAL 22. Main Air Valve ...............OPEN/LP ON (As Required) 23. Throttles .................................... SET AS REQUIRED 24. Wing Fuel/X Feed/Transfer ............... AS REQUIRED 25. Inverter ..................................................................ON 26. Alternator...............................................................ON

E-5

PNF PNF PNF PNF PNF PNF PF PNF PNF PNF

TI 4040.25C Original, March 1997

BAe 125-800A

Windmill Airstart 1. Speed and Altitude ................... WITHIN ENVELOPE 2. N1 ...........................................................INDICATING

PF PNF

CAUTION Do not attempt airstart if there is no indication of N1 rotation. 3. N2 ...................................................... 10% OR MORE 4. HP Cock......................................................... CLOSE 5. LP Cock ............................................................OPEN 6. Engine Anti-Ice ....................................................OFF 7. Fuel Pump............................................................. ON 8. Engine Sync.........................................................OFF 9. Main Air Valve................................................ CLOSE 10. Engine Ignition ...................................................... ON 11. HP Cock (when N2 at or above 10%) ...............OPEN 12. Fuel Enrichment (If Required) ..........................................PRESS UP TO 400°C ITT (Not available with engine computer inoperative) 13. Fuel Flow ................................. CHECK INDICATION 14. ITT..............................................................MONITOR

PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF

If light up does not occur within 10 secs, or: If ITT rapidly approaches 952°C, or: No oil pressure indicated within 10 secs of light up: 15. HP Cock......................................................... CLOSE

PNF

CAUTION Wait 10 seconds between airstart attempts (for fuel drainage). After Start: Check engine at self-sustaining speed above 45% N2 and stabilized. 16. Engine Ignition .....................................................OFF PNF 17. Generator..................................................... ON LINE PNF 18. Bustie ............................................................. CLOSE PNF 19. Engine Indications ...................................... NORMAL PNF 20. Main Air Valve............... OPEN/LP ON (As Required) PNF 21. Throttles .....................................SET AS REQUIRED PF 22. Wing Fuel/X Feed/Transfer................AS REQUIRED PNF 23. Inverter.................................................................. ON PNF 24. Alternator .............................................................. ON PNF

E-6

BAe 125-800A

TI 4040.25C Original, March 1997

Compressor Stall 1. Throttle ................. RETARD UNTIL STALL CEASES THEN SLOWLY ACCELERATE TO REQUIRED POWER

PF

If compressor stall cannot be eliminated, accomplish Engine Fire/Failure/Shutdown procedure. Airstart is not recommended but may be attempted if circumstances dictate. 2. Main Air Valve ................................................. LP ON

PNF

If compressor stall is due to bleed air system check valve failure, there is a risk of engine surge at high altitude cruise or at descent power. 3. ITT ............................................................. MONITOR

PNF

If compressor instability does not clear at low rpm and ITT is well within limits: 4. Engine Computer .............CYCLE AUTO/OFF/AUTO PNF

Engine Computer Malfunction

ENG CMPTER

Engine synchronizer will disengage and ENG CMPTR annunciator lights. 1. Engine Computer Switch.................... OVSPD PROT 2. Throttle .............ADJUST FOR REQUIRED RPM/ITT 3. Engine Indications ..................................... MONITOR

PNF PF PNF

Accomplish the following procedure relevant to the flight condition: TAKEOFF At Maximum Power: Below 80 KIAS, reject the takeoff. Above 80 KIAS, continue. If N1 rises, throttle back to N1RFF. At Maximum Continuous Power: Adjust throttle to achieve maximum continuous ITT, 924°C. CRUISE Set ITT of 908°C LANDING Select Engine Anti-ice OFF and Main Air Valves to CLOSE whenever possible. N1 on engine with inoperative computer should not be reduced below 60% during the approach. Delay bringing throttle to idle until after touchdown. The other engine should be operated normally.

E-7

TI 4040.25.2 Temp Rev 01, June 2005

BAe 125-800A AVN Checklist

SMOKE and FUMES

SMOKE

1.

Oxygen Masks ........................................ON/100%

ALL

2.

Passenger Oxygen.......................................PULL

LP

2a.

Communications ................................... Establish

ALL

NOTE Aircraft incorporating Engineering Order 05-25-07 (Rev 1) are modified with a MASK MIC ON/OFF toggle switch on the pilot and copilot headset jack panels. To enable the oxygen mask microphone, the audio panel toggle BOOM/MASK switch must be set to MASK and, additionally, the MASK MIC switch must be set to ON. 3.

Smoke Goggles.............................. AS REQUIRED

ALL

4.

Seat Belts Sign...................................................ON

PNF

Smoke/Fire In Aft Baggage Compartment 1.

Auxiliary Cooling Pack ..................................OFF

PNF

2.

Portable Oxygen, Goggles, Fire Extinguisher...... .............................................. DON EQUIPMENT

PNF

WARNING Insure contact is maintained with at least one other crew member in case fire fighter is overcome by fumes. 3.

Enter Toilet and Close Door.................................

PNF

4.

Aft Baggage Compartment ........................OPEN ............................... and Take Appropriate Action

PNF

Accomplish Smoke and Fume Elimination checklist.

Smoke/Fire In Vestibule, Cabin or Cockpit 1.

Auxiliary Cooling Pack ..................................OFF

PNF

2.

Portable Oxygen, Goggles, Fire Extinguisher...... .............................................. DON EQUIPMENT

PNF

Fire Extinguisher ..............................FIGHT FIRE

PNF

3.

Accomplish Smoke and Fume Elimination checklist.

Smoke and Fume Elimination 1.

Descend ...............................................................

PF

2.

Dump Valve................................................OPEN SLOWLY To Maintain Pressurization

PNF

3.

Below 15,000 ft ........................DEPRESSURIZE

PNF

Set PRESS CONTROL to GROUND TEST and MANUAL CABIN ALT CONTROL to full INCREASE. Continued Next Page

E-8

BAe 125-800A

TI 4040.25C Original, March 1997

NOTE With MAIN AIR VLV switches OPEN, selecting FLOOD may help disperse cabin smoke. 4. Dump Valve....................................... AS REQUIRED

PNF

Electrical Fire 1. 2. 3. 4. 5. 6. 7. 8. 9.

Autopilot and Yaw Damper ...................DISENGAGE Panel Lights....................EMERGENCY (If Required) Cabin & Lav Lights ............................................STBY Battery .................................................EMERGENCY Standby Inverter ................................................. ARM FIS Power............................................................ OFF Auxiliary Cooling Pack......................................... OFF Generators 1 and 2 ............................................ TRIP Engine Computers 1 and 2 ................................. OFF

PF PNF PNF PNF PNF PNF PNF PNF PNF

If smoke decreases, proceed with A: If smoke persists proceed with B: A. Fault on PS1 or PS2 Busbar: 10. Battery ...................................................................ON 11. PS1b/2b Circuit Breaker (M10, Panel D) ......... OPEN 12. Generator 2 .................................................... CLOSE If smoke recurs, fault is on PS2. 13. Generator 2 ........................................................ TRIP 14. Generator 1 .................................................... CLOSE If smoke persists, fault is also on PS1. 15. Generator 1 ........................................................ TRIP 16. Accomplish Double Generator Failure Checklist.PNF

PNF PNF PNF PNF PNF PNF

NOTE If fault is isolated to PS1 or PS2, energize good busbar and reinstate systems powered from that source. When smoke ceases it may be possible to link busbars with the bustie, and identify smoke source to particular equipment. Disconnect suspect equipment and reinstate all other equipment. Close circuit breaker M10 as required. B. Fault on PE Busbar: 10. Battery ...................................................................ON 11. Generators 1 and 2 ........................................ CLOSE 12. Bustie ............................................................. CLOSE 13. Inverters 1 and 2 ............................................ START 14. Screen Heat L ..................................................... OFF Continued Next Page

E-9

PNF PNF PNF PNF PNF

TI 4040.25.2 Temp Rev 01, June 2005

BAe 125-800A AVN Checklist

If Smoke Persists: 15. White Circuit Breakers (Panels A & D) ......OPEN

PNF

Once smoke ceases, reinstate equipment one at a time. Identify and disconnect equipment causing smoke.

Air Conditioning Smoke/Fumes Accomplish Smoke and Fumes and Smoke Elimination checklists if conditions warrant.

and

Fume

1.

Main Air Valve 2 .......................................CLOSE

PNF

2.

Flight Deck Valve .....................................CLOSE

PNF

If contaminated air still persists: 3. Main Air Valve 2 .........................................OPEN

PNF

4.

Main Air Valve 1 .......................................CLOSE

PNF

If contaminated air still persists: 5. Descend below 15,000 ft ...............................

PF

6. Main Air Valve 2 ................................CLOSE

PNF

DEPRESSURIZATION/EMERGENCY DESCENT

CABIN ALTITUDE

1.

OXYGEN MASKS................................ ON/100%

ALL

2.

PASSENGER OXYGEN .............................PULL

LP

2a.

Communications ................................... Establish

ALL

NOTE Aircraft incorporating Engineering Order 05-25-07 (Rev 1) are modified with a MASK MIC ON/OFF toggle switch on the pilot and copilot headset jack panels. To enable the oxygen mask microphone, the audio panel toggle BOOM/MASK switch must be set to MASK and, additionally, the MASK MIC switch must be set to ON. 3.

Main Air Valves .............................BOTH CLOSE

PNF

4.

Flight Deck Valve ............... OPEN (hold 10 secs)

PNF

5.

Seat Belts Sign................................................ON

PNF

6.

Cabin Altitude.......................................... CHECK

RP

If Above 15,000 ft Cabin Altitude: 7.

Throttles ....................................................... IDLE

PF

8.

Speed.........................................MMO/VMO Unless Structural Damage Suspected

PF

9.

Airbrakes ....................................................OPEN

PF

10.

Dump Valve................................................ SHUT

PNF

11.

Manual Altitude Control........FULLY DECREASE

RP

E-10

BAe 125-800A AVN Checklist

TI 4040.25.2 Temp Rev 01, June 2005

When Below 10,000 ft Cabin Altitude: 12. Cabin Altitude ....................CHECK STABILIZED

RP

13.

Flight Deck Valve..................................... CLOSE

PNF

14.

Dump Valve ................................ AS REQUIRED

PNF

It should now be possible for crew/passengers to remove masks.

REAR EQUIPMENT BAY OVERHEAT

REAR BAY OVHT

1.

Main Air Valves ...........................BOTH CLOSE

PF

2.

Flight Deck Valve ..................................... OPEN

PF

If warning persists (after 10 seconds): 3. Flight Deck Valve..................................... CLOSE

PNF

4.

Oxygen Masks ................................................ON

ALL

4a.

Communications................................... Establish

ALL

NOTE Aircraft incorporating Engineering Order 05-25-07 (Rev 1) are modified with a MASK MIC ON/OFF toggle switch on the pilot and copilot headset jack panels. To enable the oxygen mask microphone, the audio panel toggle BOOM/MASK switch must be set to MASK and, additionally, the MASK MIC switch must be set to ON. 5.

Passenger Oxygen ..................................... PULL

LP

6.

Descend................. 15,000 Ft Cabin Alt or Lower

PF

7.

Throttles ....................................................... IDLE

PF

8.

Speed..................................................... MMO/VMO Unless Structural Damage Suspected

PF

9.

Airbrakes.................................................... OPEN

PF

10.

Dump Valve ................................ AS REQUIRED

PNF

11.

LAND AS SOON AS POSSIBLE

If warning ceases: 12. DESCEND ..................................... As Necessary To Maintain Comfortable Cabin Conditions

PF

If closing hot engine bleed air resolves emergency indication, flight may be continued at a lower altitude in an unpressurized condition.

E-11

TI 4040.25C Original, March 1997

BAe 125-800A

High Pressure Air Overheat

HP AIR OVHT

1. Main Air Valve...............................................CLOSE

PNF

2. Flight Deck Valve (If HP AIR 2 OVHT) .........CLOSE

PNF

When warning ceases: 3. Main Air Valve................................................ LP ON

PNF

4. Flight Deck Valve............................. AS REQUIRED

PNF

E-12

BAe 125-800A

TI 4040.25C Original, March 1997

LANDING EMERGENCIES Landing Gear Extension Failure Switch off all electrical loads just prior to landing. 1. 2.

Horn ............................... PULL CIRCUIT BREAKER GPWS (if fitted) .............. PULL CIRCUIT BREAKER

RP RP

All gear locked down shown by standby indicators? Yes Make a normal landing No AUX HYD SYSTEM........................................... Pull Handle HAND PUMP...................... Operate, (see NOTES a and b) Proceed according to how many gear legs are locked down (see NOTE c). All gear legs locked down Only two gear legsLocked down (see NOTE d) Only one gear leg locked down

No gear legs locked down

Landing Gear Handle.........................CONFIRM DOWN Make a normal landing

OR

Landing Gear Handle.........................CONFIRM DOWN Go to Prepare for Landing procedure Ensure all landing gear are fully retracted by: Hand Pump ...................... FULLY DOWN AUX HYD System ..... PUSH HANDLE IN Landing Gear Handle ...........SELECT UP All Gear Locked Up ................. CONFIRM Go To Prepare For Landing Procedure

NOTE a.

Vigorous pumping mist be needed if gear is stuck in partially lowered position.

b.

After three greens are seen, continue pumping until significant resistance is felt.

c.

The position of the landing gear shall be established by checking the normal (green) and standby indicators.

d.

The flight crew has the choice to land with the gear down OR to retract the gear and perform an all gear up landing. Although an all gear up landing should result in less damage to the aircraft than landing with two gears locked down, passengers will experience an unpleasant landing impact and a longer period of time may be required to clear the aircraft from the runway. Continued Next Page

E-13

TI 4040.25C CHG 01, June 1999

BAe 125-800A

Preparing for Landing 3. Passengers .... BRIEF FOR EMERGENCY LANDING 4. Loose equipment .........................................SECURE 5. Emergency exit .............................CONFIRM CLEAR 6. MAIN AIR VLVs .................................. CLOSE BOTH 7. DUMP VALVE...................................................OPEN

RP ALL TECH RP RP

Landing 8. Flaps ..................................................................45O

RP

NOTE a.

Land at as low a weight as possible.

b.

Touchdown at as low a speed as practicable.

c.

Do not use lift dump.

After Touchdown With Two Gear Legs Locked Down

NOTE a. Keep the unsupported wing or nose off the ground until at a low speed, but lower wing or nose before control is lost. b. After lowering the unsupported wing or nose, use wheel brakes and nosewheel steering, if appropriate, to keep in a straight line. If the Nose Gear is Not Locked Down 9. HP COCKS at touchdown............................CLOSED

RP

With All Gear Up 10. HP COCKS at touchdown............................CLOSED

RP

E-14

BAe 125-800A

TI 4040.25C Original, March 1997

Hydraulic System Failures Landing Gear Lowering Using the Auxiliary Hydraulic System 1. Operate AUX HYD SYSTEM ...........................PULL 2. HAND PUMP.................... OPERATE (see NOTE a) 3. LANDING GEAR Lever ................................. DOWN

LP RP RP

NOTE a.

After three greens are seen, continue pumping until significant resistance is felt.

b.

Lowering of the landing gear (or flaps) by means of the auxiliary hydraulic hand pump system will not be possible until item 1 has been completed.

c.

The hand pump cannot be used to raise the landing gear.

d.

Following a main hydraulic system failure, the AUX HYD SYSTEM PULL handle must not be reset in flight.

Main System Brake Failure If main braking system failure is suspected but not confirmed before landing, the emergency system should only be selected if complete failure of the normal system is confirmed after touchdown. 1. Brake Pedals ..............................................RELEASE 2. Brake Lever ................................................... EMERG

PF PF

WARNING Do not set wheel brake to PARK position when setting lever to EMER as this will cause the brakes to lock with possibile tire failure 3. Brake Pedals ................................APPLY GENTLY

PF

Shut down one engine, where possible, to reduce required braking. The aircraft should not be taxied as differential braking is now the only means of aircraft steering.

Emergency Brake Low Pressure

EMER BRK LO PRESS

1. Brake Pedals ..................................... Apply Sparingly

CAUTION Apply brakes gently and use as few applications as possible. Aircraft should not be taxied as only differential braking will be available for aircraft steering.

E-15

PF

TI 4040.25C CHG 01, June 1999

BAe 125-800A

No Flap Landing 1. 2. 3. 4. 5.

GPWS FLAP WARN OVRD ..................... OPERATE Gear ................................................................ DOWN Approach KIAS .............................. VREF + 30 KNOTS Threshold KIAS.............................. VREF + 15 KNOTS Nosewheel .................................................................. ............. LOWER IMMEDIATELY ON TOUCHDOWN 6. Airbrakes...........................................................OPEN

PNF PF/PNF PF PF PF PF

CAUTION With hydraulic failure, airbrakes may not open.

Asymmetric Airbrakes 1. Airbrakes........................................................... SHUT 2. If Airbrakes Asymmetric or Out................................... .......................... ACCOMPLISH NO FLAP LANDING

PF PF

Single Engine Landing 1. APR....................................................AS REQUIRED

PNF

2. Ignition .................................................................. ON

PNF

3. Approach Flaps .......................................................... .......................... 25° (Precision), 15° (Non-Precision)

PF/PNF

4. Landing Flaps ................. 45° (LANDING ASSURED)

PF/PNF

Single Engine Go Around 1. Throttle................................................................ MAX

PF

2. Airspeed...................... VREF + 5 KIAS OR GREATER

PF

3. Flaps ..................................................................... 15°

PF/PNF

4. Gear .......................................................................UP

PF/PNF

5. APR....................................................AS REQUIRED

PNF

6. FLAPS................................................AS REQUIRED

PF/PNF

WARNING Airworthiness requirements do not ensure positive climb performance in the final landing configuration with one engine inoperative. The decision to discontinue the approach should be made before the flaps are extended to 45°.

E-16

BAe 125-800A

TI 4040.25C Original, March 1997

Trim Only Landing

ELEV/AIL TRIM

A. Elevator Failure: 1. Trim Indicator .................................................CHECK 2. Autopilot ................................................DISENGAGE 3. Airspeed ...................................................... 160 KIAS 4. Flaps......................................................................15° 5. Gear ................................................................DOWN

PF PF PF PF/PNF PF/PNF

Final Approach: 6. Flaps......................................................................45° 7. Airspeed .............................................VREF + 10 KIAS 8. Airspeed Control............................ ELEVATOR TRIM 9. Rate of Descent Control .......................... THROTTLE

PF/PNF PF PF PF

B. Rudder, Elevator and Single Engine Failure: 1. Airspeed ...................................................... 160 KIAS 2. Flaps......................................................................15° 3. Gear ................................................................DOWN

PF PF/PNF PF/PNF

Final Approach: 4. Flaps......................................................................25° 5. Airspeed .............................................VREF + 20 KIAS

PF/PNF PF

Maintain VREF + 20 KIAS to threshold and land with flaps 25°. C. Aileron Failure: 1. Trim Indicator .................................................CHECK 2. Autopilot ................................................DISENGAGE 3. Airspeed ...................................................... 160 KIAS 4. Flaps........................................................................0° 5. GPWS FLAP WARN OVRD...................... OPERATE 6. Gear ................................................................DOWN

PF PF PF PF/PNF PNF PF/PNF

Final Approach: 7. Lateral Control..............RUDDER or AILERON TRIM 8. Flaps.................................................. AS REQUIRED

PF PF/PNF

Should lateral control be seriously impaired, it is recommended the landing be made with flaps 0°. 9. Airspeed .......................... VREF + 25 KIAS MINIMUM Greater airspeed may be necessary to retain lateral control.

E-17

PF

TI 4040.25C Original, March 1997

BAe 125-800A

Ditching 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14.

Crewmembers .............................................. ADVISE Surface Stations & Ships .............................. NOTIFY Loose Equipment.........................................SECURE Life Vests ............................................................DON Aircraft Weight ............................................ REDUCE Cabin............... DEPRESSURIZE BELOW 10,000 FT Main Air Valves (2) ........................................ CLOSE Flight Deck Valve........................................... CLOSE Overwing Escape Hatch ................STOW IN TOILET Dump Valve ................................................... CLOSE If required, open dump valve to confirm depressurized, then close. Exterior Lights....................................................... ON Cockpit & Cabin Interior Lights ..................... EMERG Circuit Breakers: Gear Horn (K1 on Panel D), and GPWS (H19 on Panel A) ...........................OPEN Determine Direction of Ditching ..................................

PF PNF ALL ALL PF PNF PNF PNF PNF/ET PNF PNF PNF PNF PF

Ditching Imminent: 15. Autopilot ................................................ DISENGAGE 16. Gear .......................................................................UP 17. Flaps ..................................................................... 45° 18. Give Final Warning ................. BRACE FOR IMPACT

PF PF/PNF PF/PNF PF

After Ditching: 19. Life Raft......................................... LAUNCH, BOARD

ALL

Forced Landing 1. 2. 3. 4. 5. 6. 7. 8. 9.

Advise Crewmembers................................................. Ground Emergency Facilities........................ NOTIFY Loose Equipment.........................................SECURE Aircraft Weight ............................................ REDUCE Cabin............... DEPRESSURIZE BELOW 10,000 FT Main Air Valves (2) ........................................ CLOSE Flight Deck Valve........................................... CLOSE Overwing Escape Hatch ................STOW IN TOILET Dump Valve ......................................................OPEN

PF PNF ALL PF PNF PNF PNF PNF/ET PNF

If Gear Up: 10. Circuit Breakers: Gear Horn (K1 on Panel D), and GPWS (H19 on Panel A) ...........................OPEN

PNF

Crash 11. 12. 13. 14. 15. 16. 17. 18. 19.

Landing Imminent: Autopilot ...................... DISENGAGE ABOVE 150 FT Gear ...................................................AS REQUIRED Flaps ..................................................................... 45° Give Final Warning ................. BRACE FOR IMPACT Generators 1 & 2 ................................................TRIP Battery..................................................................OFF Throttles ..............................................................IDLE HP Cocks (2) ................................................. CLOSE LP Cocks (2) .................................................. CLOSE

After Landing: 20. Evacuate Aircraft .....................................................

E-18

PF PF/PNF PF/PNF PF PNF PNF PF PNF PNF ALL

BAe 125-800A

TI 4040.25C Original, March 1997

AIR CONDITIONING / PRESSURIZATION Duct Overheat

DUCT OVHT

1. Cabin Temp Selector.................................................. ..................................MANUAL, HOLD FULLY COOL

PNF

If Warning Ceases: 2. Cabin Temp Selector...............USE MANUAL MODE

PNF

If Warning Persists: 2. Cabin Temp Selector................AUTO, FULLY COOL

PNF

Automatic Temperature Control Failure 1. Cabin Temp Selector.................................................. ........................ MANUAL, COOL OR HOT AS REQD

Failure To Pressurize

PNF

CABIN ALTITUDE

1. Main Air Valves .................................. CHECK/OPEN 2. Dump Valve...................................................... SHUT 3. Pressurization Switch .......................................OVRD

PNF PNF PNF

Automatic Pressure Control Failure 1. Manual Alt Control.................TURN SLOWLY UNTIL CABIN ALT INCREASES SLIGHTLY PNF 2. Pressurization Valve.........................GROUND TEST PNF 3. Manual Alt Control....... CONTROL AS NECESSARY PNF If this is ineffective, use dump valve to control pressurization.

Auxiliary Cooling Pack Failure 1. Aux Cooling Pack Switch .................................... OFF

AUX PACK PNF

CONTINUE FLIGHT.

Pressurization Regulation Failure 1. Main Air Valve 2 ............................................. CLOSE 2. No. 2 Throttle............................REDUCE TO 85% N1 3. Main Air Valve 2 ............................................... OPEN

PNF PF PNF

A. If Main Air Valve 2 Annunciator NOT Lit: CONTINUE FLIGHT B. If Main Air Valve 2 Annunciator Lit: 4. Main Air Valve 2 ............................................. CLOSE LAND AS SOON AS PRACTICAL

E-19

PNF

TI 4040.25C CHG 01, June 1999

BAe 125-800A

AVIONICS / PITOT STATIC Air Data Computer Failure 1. Relevant Flight Instruments .................. CHECK FOR FAILURE FLAGS

PF/PNF

2. Failed Instruments .............................................TEST PF/PNF (to determine whether air data computer or instrument failed) If MSI And Altimeter Are Both Inoperative: 3. Relevant Air Data Transfer Switch ........... OPERATE

PF/PNF

AP/AHRS Fan Fail PTR 1. AP/AHRS FAN FAIL PTR Switch PRESS TO RESET

PNF

CONTINUE FLIGHT

EFIS Fan Failure 1. No pilot action ............................ CONTINUE FLIGHT

PF

This may lead to subsequent EFIS OVHT warning.

EFIS Overheat Warning On Left Hand Panel Only: 1. EFIS OVHT indicators below ND1............. EXAMINE

PF

If EFD Overheat Annunciator Lit: 2. Left EFD Master Switch .......................................OFF

PF

If MFD Overheat Annunciator Lit: 2. MFD Master Switch .............................................OFF

PF

If MPU Overheat Annunciator Lit: 2. MFD Master Switch .............................................OFF 3. Circuit Breaker H4 (MPU 2 on Panel A) ...........OPEN

PF PNF

Warning On Right Hand Panel Only: 1. Right EFD Master Switch ....................................OFF

PNF

Warning On Both Panels: 1. Both EFD Master & MFD Master Switches .........OFF

PF/PNF

E-20

BAe 125-800A

TI 4040.25C Original, March 1997

DPU Failure 1. DPU Transfer Switch...................................PRESS (White "ALTN" legend lit)

PF/PNF

PFD Failure 1. Relevant PFD to ND Switch ......................... PRESS (White "TO ND" legend lit)

PF/PNF

If PFD Displayed On ND: CONTINUE IN THIS CONDITION If PFD Not Displayed On ND: 2. Relevant PFD to ND Switch ......................... PRESS (White "TO ND" legend not lit) 3. DPU ALTN Switch ........................................ PRESS (White "ALTN" legend lit)

PF/PNF PF/PNF

ND Failure 1. ND to MFD Switch.......................................... PRESS (White "TO MFD" legend lit)

PF

If ND Displayed On MFD: CONTINUE IN THIS CONDITION If ND Not Displayed On MFD: 2. ND to MFD Switch.......................................... PRESS (White "TO MFD" legend out) 3. DPU ALTN Switch .......................................... PRESS (White "ALTN" legend lit)

PF PF

Unreliable Airspeed 1. Pitot Isolation Control ................................ ISOLATE

RP

Pitot Heat Failure 1. Pitot/Vane Heat Switches (2) .................. CHECK ON

PNF

2. Pitot Amps ........................CHECK L & R READINGS

PNF

3. Associated Instruments............................. MONITOR

PNF

E-21

TI 4040.25C Original, March 1997

BAe 125-800A

ELECTRICAL

ELECT

Double Generator Failure 1. 2. 3. 4. 5. 6. 7. 8. 9.

Panel Lights ...................... EMERGENCY (IF REQD) Battery................................................. EMERGENCY Standby Inverter ..........................ARM/XE FAIL OUT Engine Computers (2)..........................................OFF Engine Anti-Ice (2) ................................................ ON DC Volts................................................................. PE Electrical Loads ......................................... MINIMIZE Emergency Lighting .............................................OFF Circuit Breakers A13, A17, B11, B13, B14 and H19 on Panel A..........................................OPEN 10. Emerg Lighting......... MANUAL, ONLY WHEN REQD

PNF PNF PNF PNF PNF PNF PNF PNF PNF PNF

After completing checklist, the following major systems ARE AVAILABLE: (if PE & XE buses are powered): - STBY ADI with ILS capability (Batt 3 backup) - Pilot's BDI (NO DME) with ADF & VOR capability (from AHRS 2) - #1 NAV Radio (NO DME); Localizer, VOR, MKR BCNS - Pilot's VSI, CSI, ALTIMETER - VHF 1 & UHF 1 - STBY ALTM (Batt 3 backup) - ATC Transponder and IFF - Fuel Qty (L & R) - Altitude Alerter - Lights: Nav, Left Landing Light, Left Wing Taxi Light

-

IMPACT ON NORMAL PROCEDURES: No TACAN or DME required approaches Fly instruments from left seat Radar ALT is inop GPWS is unreliable and disabled by pulling H-19, Panel A FLAP and AIRBRAKE position indicators are inop Brake supply/pressure gage is inop, but HYD 1/2 LO PRESS, EMERG BRK LO PRESS and AUX HYD LO LVL lights work TKS and ICE DETECT are inop Shot 2 of Fire Ext system is inop

Single Generator Failure 1. Failed Generator.................................................TRIP 2. Bustie ............................................................. CLOSE 3. Generator Amps ....................... CHECK BELOW 400 UP TO 10,000 FT OR 330 ABOVE 10,000 FT 4. Volts ...................................... CHECK PSI, PS2 & PE

E-22

PNF PNF PNF PNF

BAe 125-800A

TI 4040.25C CHG 01, June 1999

Fluctuating / Abnormal Voltage If Fluctuating: 1. Bustie ............................................................... OPEN Continue with Steps 2 thru 5 If Abnormal (Above 29.5 / Below 24.5): 2. DC volts.........................................CHECK PS1, PS2 3. Affected Generator ............................................. TRIP 4. Bustie ............................................................. CLOSE 5. Generator Amps ....................... CHECK BELOW 400 UP TO 10,000 FT OR 330 ABOVE 10,000 FT

PNF

PNF PNF PNF PNF

PS2 POWERED CIRCUITS FLIGHT INSTRUMENTS NAV EQUIPMENT Right VSI + Right CSI FMS #2 + DME #2 Right Altimeter Right BDI AP/FD Computer Fan NAV #2 (ILS/VOR/MKR) ANTI-ICE SYSTEMS TKS Pump ICE Detection circuit R Pitot Heat+ Fwd Static Plate Heat Half of Rudder Bias Heat Drain Heater

EFIS As long as PSB1-PSB2 Tie CB (white outline M-10) doesn't trip, Right side EFIS will be powered via the PS1 bus thru PSB1. The #2 ADS will also get power this way.

COMM EQUIPMENT NONE

LIGHTS Beacon Right Landing + Taxi Lights Right Panel Light Storm Lights Right MSP Mode Lights Right Reading Light

STALL WARNING Right Stall Warning Motor INDICATORS Stby gear indicators Chime Air brake indicator Hydr Supply Press gage (bottom) Cabin Temperature gauge MISC. Stby Inst Emerg Power Chrg Right Fuel Pump (PE backup) Right Rud Bias on/off Valve Galley Power 115 V 60 Hz Power Toilet Flush (airborne) Wash Basin pump/heater

SWITCHING CNTRL FOR... Right Screen Heat Aux Cool Pack Auto Cabin Temp Control Flood Flow Valve AC & PRESSURIZATION Aux Cool Pack Valve Aux Cool Pack Evaporators Aux Cool Pack Annunciator Auto Cabin Temp Control Press Reg Control Valve Recirc Fan FIRE SYSTEMS FIRE EXT SHOT 2

E-23

TI 4040.25C Original, March 1997

BAe 125-800A

Generators Out Of Balance Generator Amps Differ By More Than 40 Amps: 1. Bustie ................................................................OPEN

PNF

2. Gen Amps ...........CHECK, PROCEED WITH A OR B

PNF

A. Higher Load Above 400 Amps Up To 10,000 ft, or 330 Amps Above 10,000 ft: 3. Associated Generator .........................................TRIP

PNF

4. Bustie ............................................................. CLOSE

PNF

5. Generator Amps .................CHECK BELOW 400 UP TO 10,000 FT OR 330 ABOVE 10,000 FT

PNF

6. Electrical Loads ......................SHED AS REQUIRED

PNF

If Excessive Load Persists: 7. Bustie ................................................................OPEN

PNF

CONTINUE FLIGHT with one busbar failed B. Higher Load Below 400 Amps Up To 10,000 ft, or 330 Amps Above 10,000 ft: 3. DC volts ........................................ CHECK PS1, PS2

PNF

Proceed with C or D: C. Voltages Normal (24.5 to 29.5): 4. Bustie ............................................................. CLOSE

PNF

CONTINUE FLIGHT with out of balance condition 5. DC Volts & Amps ........... MONITOR PERIODICALLY

PNF

D. One Voltage Abnormal (Outside 24.5 to 29.5): 4. Associated Generator .........................................TRIP

PNF

5. Bustie ............................................................. CLOSE

PNF

6. Generator Amps ....................... CHECK BELOW 400 UP TO 10,000 FT OR 330 ABOVE 10,000 FT

PNF

7. Electrical Loads .............................. SHED AS REQD CONTINUE FLIGHT with one busbar failed

E-24

PNF

BAe 125-800A

TI 4040.25C Original, March 1997

Battery Hot

BATT HOT

If Battery Hot Annunciator Lit: 1. Affected Battery Amps....................................CHECK

PNF

Proceed with A or B: A. Battery Amps Decreasing: 2. Battery Amps, Temperature .........MONITOR EVERY 5 MINUTES UNTIL WARNING CEASES

PNF

B. Battery Amps Steady or Increasing: 2. Battery Amps, Temperature .........MONITOR EVERY 5 MINUTES

PNF

If Amps or emperature Increase: 3. Affected Battery........................................... ISOLATE 4. BATT CNTCTR Annunciators (2).......................... LIT

PNF PNF

Battery Overheat

BATT OVHT

If Battery Overheat Annunciator Lit In The Air: 1. Battery .................................................EMERGENCY

PNF

LAND AS SOON AS PRACTICAL If Battery Overheat Annunciator Lit On The Ground: 1. Battery ................................................................. OFF 2. Engines & APU...................................... SHUTDOWN 3. External Power (If Connected) ........... DISCONNECT

XE Failure 1. AC Voltmeter ..............................XE, CHECK VOLTS

PNF PNF PNF

XE FAIL PNF

Proceed with A or B: A. XE Supplies Available: NO FURTHER ACTION B. XE Supplies Not Available: 2. Each White, Panel D AC (XE Supplied) Circuit Breakers.................................... TRIP, RESET 3. If Tripping Any Circuit Breaker Causes XE FAIL Annunciator To Extinguish .............. DO NOT RESET

PNF PNF

CONTINUE FLIGHT If XE FAIL persists: 5. Standby Inverter .................................................. OFF CONTINUE FLIGHT

E-25

PNF

TI 4040.25C Original, March 1997

BAe 125-800A

XS1 and XE Failure

XS1 FAIL

XE FAIL

1. XE BUS PROT Circuit Breaker (A1 on Panel D) ................................................OPEN

PNF

2. STBY INV Circuit Breaker (B9 on Panel D) ............................................. CLOSE

PNF

3. Standby Inverter .................................................ARM

PNF

4. XE FAIL Annunciator ..................................... CHECK

PNF

Proceed With A or B: A. XE FAIL Annunciator Still Lit: 5. Accomplish XE FAILURE Checklist............................

PNF

B. XE FAIL Annunciator Out: 5. XE FAIL BUS PROT Circuit Breaker (A1 on Panel D) ..............................................RESET

PNF

6. XS1 FAIL Annunciator ................................... CHECK

PNF

If XS1 Still Lit: 7. Accomplish XS1 FAILURE Checklist..........................

PNF

XS1 or XS2 Failure

XS1 FAIL

1. AC Voltmeter .................. SET TO FAILED BUSBAR, CHECK VOLTS

E-26

XS2 FAIL PNF

BAe 125-800A

TI 4040.25C Original, March 1997

Double Inverter Failure 1. Inverter 1 ................... SELECT START FOR 30 SEC

PNF

2. AC Supply Annunciators ................................CHECK

PNF

If XS1 FAIL and INV FAIL Annunciators Still Lit: 3. Inverter 2 ................... SELECT START FOR 30 SEC

PNF

CONTINUE FLIGHT

Single Inverter Failure 1. Failed Inverter ................................................ START

PNF

Alternator Failure 1. Failed Alternator ................................OFF, THEN ON

PNF

If Warning Persists: 2. Alternator............................................................. OFF

PNF

CONTINUE FLIGHT

Double Alternator Failure If both alternators fail, causing total loss of windscreen heating: 1. SCREEN HEAT Switches ........................ BOTH OFF

PNF

2. Alternators ........ BOTH OFF THEN ON(wait 10 secs)

PNF

Proceed with A or B: A. If either ALTR FAIL light is on: 3. Wait another 20 seconds; SCREEN HEAT........................................ BOTH ON

PNF

B. If an ALTR FAIL light is not on: 3. L SCREEN HEAT switch............... ON (wait 10 secs)

PNF

4. If ALTR FAIL comes on: L SCREEN HEAT................................................ OFF ALTERNATOR Switches........BOTH OFF, THEN ON R SCREEN HEAT .................................................ON Do not reselect L SCREEN HEAT. With these switch selections, available power is fed to right ‘A’ screen and left ‘B’ screen. Continued Next Page

E-27

PNF

TI 4040.25C Original, March 1997

BAe 125-800A

5. If the L ALTR FAIL light is not on, do not reselect R SCREEN HEAT. With these switch selections, available power is fed to left ‘A’ screen and right ‘B’ screen.

NOTE In the case of repeated tripping, repeat resets only if windscreen heat is operationally essential.

ENGINES High RPM or High ITT 1. Throttle................................................................IDLE

PF

If Indications Not Controlled Within Limits: 2. Accomplish Engine Fire/Failure/Shutdown ChecklistPNF

Fluctuating RPM 1. Engine Computer................................ OVSPD PROT

PNF

2. Throttle............ADJUST TO KEEP REQUIRED RPM

PF

3. ITT..............................................................MONITOR

PNF

High Oil Temperature 1. Accomplish Engine Fire/Failure/. Shutdown Checklist

PNF

2. Note Maximum Temperature & Duration....................

PNF

Oil Low Pressure

OIL LO PRESS

1. Oil Pressure ...................... CHECK GAGE READING If Below 25 psi: 2. Accomplish Engine Fire/Failure/Shutdown Checklist

E-28

PNF

PNF

BAe 125-800A

TI 4040.25C Original, March 1997

FLIGHT CONTROLS False Stick Shaker / Pusher

STALL IDENT

1. STALL IDENT 1 & 2 ......... PUSH BOTH TOGETHER

PNF

If Stick Shake Persists: 2. STALL WARN MOTOR L and R Circuit Breakers (B6/B7 on Panel D)................ OPEN

PNF

CONTINUE FLIGHT WITH CAUTION

Electric Pitch Trim Runaway 1. Control Column ........................................ RESTRAIN

PF

2. Trim Wheel ............................................... RESTRAIN

PF

3. Autopilot ................................................DISENGAGE

PF

4. Trim Switch................................................ OPERATE

PF

5. ELECT PITCH TRIM Circuit Breaker (B10 on Panel D).............................................. OPEN

PNF

Autopilot Trim Warnings 1. PFD Mistrim Warning .........CK A OR E INDICATION

PF

2. Appropriate Trim Wheel ..............ZERO AUTOPILOT OUT OF TRIM INDICATION

PF

If Mistrim Indication Still Present: 3. Autopilot ................................................DISENGAGE

PF

Anticipate heavy out-of-trim loads

E-29

TI 4040.25C Original, March 1997

BAe 125-800A

FUEL

FUEL

Auxiliary Fuel Transfer Failure 1. Wing Fuel Contents ....................................... CHECK

PNF

Wing Fuel Contents Decreasing: LAND AS SOON AS POSSIBLE Wing Contents Increasing: CONTINUE FLIGHT

Fuel Low Pressure 1. Wing Fuel/X Feed/Transfer Valve .................X FEED

PNF

2. FUEL LO PRESS Annunciator ............. CHECK OUT

PNF

3. Failed Fuel Pump.................................................OFF

PNF

Ventral Tank Not Empty: 4. Aux Fuel Transfer Valve ...... SELECT OPEN/CLOSE TO MAINTAIN WING FUEL BALANCE WITHIN 500 LBS

PNF

Ventral Tank Empty: 4. Wing Fuel/X Feed/Transfer Valve ......... TRANSFER, THEN X FEED ALTERNATELY

PNF

Engine Fuel Malfunction 1. Throttle................................. REDUCE TO MINIMUM POWER TO COMPLETE FLIGHT If Warning Persists, Accompanied By Engine Malfunction: 2. Accomplish Engine Fire/Failure/Shutdown Checklist

E-30

PF

PNF

BAe 125-800A

TI 4040.25C Original, March 1997

HYDRAULICS Hydraulic Low Pressure

HYD LO PRESS

CONTINUE FLIGHT

Main Hydraulic Failure CONTINUE FLIGHT Landing Gear and Flaps Lowering: 1. Aux Hyd System Handle .....PULL (DO NOT RESET) 2. Aux Hyd Pump Handle .................. OPERATE UNTIL GEAR DOWN/LIGHTS ON 3. Gear ................................................................DOWN 4. Flaps.................................................................... SET 5. Aux Hyd Pump Handle .................. OPERATE UNTIL DESIRED FLAP POSITION ACHIEVED

PNF PNF PF/PNF PF/PNF PNF

Before Landing: 6. Brake Lever ............................... LEAVE IN NORMAL (FORWARD) POSITION

PNF

Actions On Landing: 7. Wheelbrakes ................................... APPLY GENTLY

PF

WARNING Do not dissipate brake pressure needlessly by applying brakes with pumping action. Apply slow steady pressure. If Normal Braking Fails: 8. Brake Pedals ..............................................RELEASE 9. Brake Lever ................................................... EMERG

PF PF

WARNING Do not set wheel brake to PARK position when setting lever to EMER as this will cause the brakes to lock and possible tire failure 10. Brake Pedals ................................... APPLY GENTLY 11. Steering ........... USE FLIGHT CONTROLS, BRAKES

E-31

PF PF

TI 4040.25C CHG 01, June 1999

BAe 125-800A

Hydraulic System Overheat

HYD OVHT

CONTINUE FLIGHT

WINDSCREEN Windscreen Overheat 1. Screen Heat Switch............. OFF, THEN ON

PNF

CONTINUE FLIGHT

Sidescreen Overheat 1. L or R Screen Heat Switch .............. OFF, THEN ON TO IDENTIFY AFFECTED SCREEN

PNF

CONTINUE FLIGHT

Windscreen Failure Outer Acrylic Single Crack: 1. Screen Heat .......................................... OFF

E-32

PN

BAe 125-800A

TI 4040.25C CHG 01, June 1999

PERFORMANCE TEMPERATURE CONVERSION TABLE

P-iii

TABULATED TAKEOFF DATA

P-1

SINGLE ENGINE NET GRADIENT REQUIRED

P-1

FLAPS 15° - APR

P-2

FLAPS 0° - APR

P-5

TAKEOFF REFERENCE N1% - ENG ANTICE OFF

P-8

TAKEOFF REFERENCE N1% - ENG ANTICE ON

P-9

TAKEOFF REFERENCE N1% - LOW PRESS ALTITUDES

P-10

MAXIMUM CRUISE N1%

P-11

MAX TAKEOFF WEIGHT FOR CRUISING ALTITUDE

P-12

MIN CRUISING SPEED AND MAX CRUISING ALTITUDE

P-13

MAXIMUM CRUISING WEIGHT

P-14

MAX ALTITUDE FOR MAX LIFT COEFFICIENT

P-15

INTERMEDIATE SPEED CRUISE

P-16

LONG RANGE CRUISE SPEED

P-23

SHORT RANGE AND DIVERSION FUEL AND TIME

P-26

HOLDING ON TWO ENGINES (ANTI-ICING OFF)

P-27

HOLDING IN ICING CONDITIONS

P-28

WIND COMPONENT

P-29

SUMMARY OF SINGLE-ENGINE CEILINGS DRIFT DOWN

P-30

P-i

TI 4040.25C Original, March 1997

BAe 125-800A

This Page Intentionally Left Blank

P-ii

BAe 125-800A

TI 4040.25C Original, March 1997

TEMPERATURE CONVERSION TABLE °F -148.0 -146.2 -144.4 -142.6 -140.8 -139.0 -137.2 -135.4 -133.6 -131.8 -130.0 -128.2 -126.4 -124.6 -122.8 -121.0 -119.2 -117.4 -115.6 -113.8 -112.0 -110.2 -108.4 -106.6 -104.8 -103.0 -101.2 -99.4 -97.6 -95.8 -94.0 -92.2 -90.4 -88.6 -86.8 -85.0 -83.2 -81.4 -79.6 -77.8 -76.0 -74.2 -72.4 -70.6 -68.8 -67.0 -65.2 -63.4 -61.6 -59.8 -58.0 -56.2 -54.4 -52.6 -50.8 -49.0 -47.2 -45.4 -43.6 -41.8 -40.0 -38.2 -36.4 -34.6 -32.8 -31.0 -29.2 -27.4 -25.6 -23.8 -22.0 -20.2 -18.4 -16.6 -14.8 -13.0 -11.2 -9.4 -7.6 -5.8 -4.0 -2.2 -0.4 1.4 3.2

-100 -99 -98 -97 -96 -95 -94 -93 -92 -91 -90 -89 -88 -87 -86 -85 -84 -83 -82 -81 -80 -79 -78 -77 -76 -75 -74 -73 -72 -71 -70 -69 -68 -67 -66 -65 -64 -63 -62 -61 -60 -59 -58 -57 -56 -55 -54 -53 -52 -51 -50 -49 -48 -47 -46 -45 -44 -43 -42 -41 -40 -39 -38 -37 -36 -35 -34 -33 -32 -31 -30 -29 -28 -27 -26 -25 -24 -23 -22 -21 -20 -19 -18 -17 -16

°C -73.3 -72.8 -72.2 -71.7 -71.1 -70.6 -70.0 -69.4 -68.9 -68.3 -67.8 -67.2 -66.7 -66.1 -65.6 -65.0 -64.4 -63.9 -63.3 -62.8 -62.2 -61.7 -61.1 -60.6 -60.0 -59.4 -58.9 -58.3 -57.8 -57.2 -56.7 -56.1 -55.6 -55.0 -54.4 -53.9 -53.3 -52.8 -52.2 -51.7 -51.1 -50.6 -50.0 -49.4 -48.9 -48.3 -47.8 -47.2 -46.7 -46.1 -45.6 -45.0 -44.4 -43.9 -43.3 -42.8 -42.2 -41.7 -41.1 -40.6 -40.0 -39.4 -38.9 -38.3 -37.8 -37.2 -36.7 -36.1 -35.6 -35.0 -34.4 -33.9 -33.3 -32.8 -32.2 -31.7 -31.1 -30.6 -30.0 -29.4 -28.9 -28.3 -27.8 -27.2 -26.7

°F 5.0 6.8 8.6 10.4 12.2 14.0 15.8 17.6 19.4 21.2 23.0 24.8 26.6 28.4 30.2 32.0 33.8 35.6 37.4 39.2 41.0 42.8 44.6 46.4 48.2 50.0 51.8 53.6 55.4 57.2 59.0 60.8 62.6 64.4 66.2 68.0 69.8 71.6 73.4 75.2 77.0 78.8 80.6 82.4 74.2 86.0 87.8 89.6 91.4 93.2 95.0 96.8 98.6 100.4 102.2 104.0 105.4 107.6 109.4 111.2 113.0 114.8 116.6 118.4 120.2 122.0 123.8 125.6 127.4 129.2 131.0 132.8 134.6 136.4 138.2 140.0 141.8 143.6 145.4 147.2 149.0 150.8 152.6 154.4 156.2

-15 -14 -13 -12 -11 -10 -9 -8 -7 -6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 6 67 68 69

P-iii

°C -26.1 -25.6 -25.0 -24.4 -23.9 -23.3 -22.8 -22.2 -21.7 -21.1 -20.6 -20.0 -19.4 -18.9 -18.3 -17.8 -17.2 -16.7 -16.1 -15.6 -15.0 -14.4 -13.9 -13.3 -12.8 -12.2 -11.7 -11.1 -10.6 -10.0 -9.4 -8.9 -8.3 -7.8 -7.2 -6.7 -6.1 -5.6 -5.0 -4.4 -3.9 -3.3 -2.8 -2.2 -1.7 -1.1 -0.6 0.0 0.6 1.1 1.7 2.2 2.8 3.3 3.9 4.4 5.0 5.6 6.1 6.7 7.2 7.8 8.3 8.9 9.4 10.0 10.6 11.1 11.7 12.2 12.8 13.3 13.9 14.4 15.0 15.6 16.1 16.7 17.2 17.8 18.3 18.9 19.4 20.0 20.6

°F 158.0 159.8 161.6 163.4 165.2 167.0 168.8 170.6 172.4 174.2 176.0 177.8 179.6 181.4 183.2 185.0 186.8 188.6 190.4 192.2 194.0 195.8 197.6 199.4 201.2 203.0 204.8 206.6 208.4 210.2 212.0 213.8 215.6 217.4 219.2 221.0 222.8 224.6 226.4 228.2 230.0 231.8 233.6 235.4 237.2 239.0 240.8 242.6 244.4 246.2 248.0 249.8 251.6 253.4 255.2 257.0 258.8 260.6 262.4 264.2 266.0 267.8 269.6 271.4 273.2 275.0 276.8 278.6 280.4 282.2 284.0 285.8 287.6 289.4 291.2 293.0 294.8 296.6 298.4 300.2

70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149

°C 21.1 21.7 22.2 22.8 23.3 23.9 24.4 25.0 25.6 26.1 26.7 27.2 27.8 28.3 28.9 29.4 30.0 30.6 31.1 31.7 32.2 32.8 33.3 33.9 34.4 35.0 35.6 36.1 36.7 37.2 37.8 38.3 38.9 39.4 40.0 40.6 41.1 41.7 42.2 42.8 43.3 43.9 44.4 45.0 45.6 46.1 46.7 47.2 47.8 48.3 48.9 49.4 50.0 50.6 51.1 51.7 52.2 52.8 53.3 53.9 54.4 55.0 55.8 56.1 57.7 57.2 57.3 58.3 58.9 59.4 60.0 60.6 61.1 61.7 62.2 62.8 63.3 63.9 64.4 65.0

TI 4040.25C CHG 01, June 1999

BAe 125-800A

EFFECT OF RUNWAY CONDITION READING ON ACCELERATE - STOP DISTANCE

P-iv

BAe 125-800A

TI 4040.25C Original, March 1997

TABULATED TAKEOFF DATA 1. Enter with pressure altitude (round up to next higher). 2. Do not use with tailwind or up slope. 3. Do not interpolate horizontally or vertically between boxes or between numbers within shaded areas. 4. "Distance" is paved runway length only. 5. The lowest temperature for each altitude is ISA. 6. The highest temperature shown in the shaded area in each block is either the WAT limit or the temperature determined by a distance of 8,400 feet, below which brake energy limitations will not apply. For distances exceeding 8,400 feet, brake energy may be limiting, and V1 may be lower than VR; for these cases the Flight Manual graphs must be used. 7. The second temperature in the shaded area (15° takeoff) is that at which VR and V2 start to rise sharply, or ISA if higher. Within the shaded area tabulation is not sufficiently accurate for interpolation; refer to the Flight Manual. 8. When engine anti-ice is used, add 10° to the actual temperature before entering the table. SINGLE ENGINE NET GRADIENT REQUIRED OBSTACLE HEIGHT. X 100 = % GRADIENT DIST TO OBSTACLE 97 ft = 1.6%

6076 ft = 1 NM

146 2.4

150 2.5

°C °F

-40 -40

TEMPERATURE CONVERSION TABLE -35 -30 -25 -20 -15 -10 -5 0 -31 -22 -13 -4 5 14 23 32

°C °F

10 50

ft/nm %Grad

15 59

200 250 300 350 3.3 4.1 4.9 5.8

20 68

25 77

30 86

P-1

375 6.2

35 95

400 6.6

425 7.1

450 7.4

500 8.3

5 41

40 45 50 55 104 113 122 131

TI 4040.25C Original, March 1997

BAe 125-800A

FLAPS 15° - APR ZERO WIND AND GRADIENT A/C Wt lb PRESS OAT Dist ALT - ft °C ft

28,000 VR V2 kt kt

V1 = VR OAT Dist ft °C

27,000 26,000 VR V2 OAT Dist VR V2 kt kt ft kt kt °C 15 14 10 3

8400 7960 7260 6540

135 133 132 132

136 134 134 134

140 136 136 136

19 18 10 5 24 22 20 10 7

8400 7800 6620 6210 8400 7610 7240 6110 5930

135 133 132 132 137 133 133 132 132

137 134 134 134 138 134 134 134 134

139 135 134 133

141 136 136 136

28 26 20 9

8400 7550 6550 5650

139 133 132 131

140 134 134 134

8400 7450 6460 5830

140 134 134 133

141 136 136 136

8400 7200 5990 5730 8400 7180 6600 5750 5690

143 134 134 133 142 134 134 133 133

144 136 136 136 144 136 136 136 136

32 29 20 11 35 32 30 20 13 39 36 30 20 15

8400 7270 6040 5500 8400 7000 6660 5640 5400 8300 7030 6120 5400 5340

140 133 132 131 139 133 133 132 131 143 133 132 131 131

142 134 134 134 141 134 134 134 134 145 134 134 134 134

6000

7 6 3

8400 138 8100 136 7600 136

140 138 138

11 10 3

8400 137 138 8050 134 136 7020 134 136

5000

12 10 5

8400 139 7900 136 7150 136

141 138 138

15 14 10 5

8400 7770 7160 6630

137 134 134 134

138 136 136 136

17 15 10 7

8400 7850 7050 6800

141 136 136 136

143 138 138 138

20 18 10 7

8400 7610 6520 6300

139 134 135 133

22 19 15 9

8400 7700 7000 6400

143 136 136 135

145 138 138 138

24 22 20 9

8400 7560 7140 6010

26 23 20 11

8400 7600 7050 6200

146 136 136 135

148 138 138 138

28 26 20 11

30 26 20 13 33 30 25 20 15

8400 7350 6450 6100 8400 7350 6550 6050 5950

148 136 136 135 148 136 136 136 135

150 138 138 138 151 138 138 138 138

32 29 20 13 35 33 30 20 15

4000

3000

2000

1000

S-L

VFTO kt

170

169

166

VERC kt

187

183

180

VREF kt

142

140

138

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-2

BAe 125-800A

TI 4040.25C Original, March 1997

FLAPS 15° - APR ZERO WIND AND GRADIENT A/C Wt lb PRESS OAT Dist ALT - ft °C ft 6000

5000

4000

3000

2000

1000

S-L

V1 = VR

25,000 VR kt

V2 kt

19 18 10 3 23 22 20 10 5

8400 7800 6630 6100 8400 7600 7270 6130 5790

133 131 130 129 134 131 131 130 129

135 132 132 132 135 132 132 132 132

27 26 20 10 7

8400 7480 6580 5700 5530

133 131 130 129 129

135 132 132 132 132

31 29 20 9 35 33 30 20 11

8400 7210 6040 5330 8400 7170 6650 5620 5150

135 131 130 129 137 131 130 129 129

137 132 132 132 139 132 132 132 132

38 36 30 20 13

8400 7000 6110 5310 5100

136 131 130 129 129

138 132 132 132 132

42 39 30 20 15

8250 6810 5700 5100 5000

140 131 130 129 129

143 132 132 132 132

OAT Dist ft °C

24,000

23,000

VR kt

V2 OAT Dist kt ft °C

VR kt

V2 kt

130 126 125 124 124 132 126 125 124 124 133 126 125 125 124 123 133 126 125 124 123 136 126 125 124 123 132 126 125 124 123 123 132 126 125 124 123 123

132 127 127 127 127 134 127 127 127 127 135 127 127 127 127 127 135 127 127 127 127 139 127 127 127 127 134 127 127 127 127 127 134 127 127 127 127 127

23 22 20 10 33 27 26 20 10 5

8400 7660 7280 6130 5650 8400 7550 6590 5690 5400

131 128 128 127 127 131 128 128 127 127

132 130 130 130 130 132 130 130 130 130

31 29 20 10 7 35 33 30 20 9 39 36 30 20 11

8400 7260 6040 5330 5200 8400 7240 6650 5620 5000 8350 7000 6070 5260 4830

131 128 128 127 126 134 128 128 127 126 137 128 128 127 126

133 130 130 130 130 135 130 130 130 130 139 130 130 130 130

42 39 30 20 13 45 43 40 30 20 15

8130 6810 5660 4960 4790 7950 6830 6320 5320 4790 4700

137 128 127 126 126 138 130 128 127 126 126

139 130 130 130 130 140 131 130 130 130 130

28 26 20 10 3 32 30 20 10 5 36 33 30 20 10 7 39 37 30 20 9 43 40 30 20 11 45 43 40 30 20 13 48 46 40 30 20 15

8400 7430 6550 5640 5260 8400 7310 6000 5270 5030 8400 7020 6600 5560 4970 4820 8400 7000 6050 5200 4660 8400 6900 5600 4940 4510 7480 6730 6240 5230 4660 4500 7500 6570 5760 4950 4500 4410

VFTO kt

164

160

157

VERC kt

176

172

168

VREF kt

136

133

130

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-3

TI 4040.25C Original, March 1997

BAe 125-800A

FLAPS 15° - APR ZERO WIND AND GRADIENT

V1 = VR

A/C Wt lb 22,000 PRESS OAT Dist VR V2 OAT Dist ALT - ft °C ft kt kt ft °C 6000

5000

4000

3000

2000

1000

S-L

32 30 20 10 3 36 34 30 20 10 5 40 37 30 20 10 7 43 40 30 20 9 46 43 40 30 20 11 48 46 40 30 20 13 50 49 40 30 20 15

8400 7230 5870 5200 4850 8120 7140 6510 5530 4900 4700 8300 6860 5960 5150 4630 4550 8100 6730 5540 4860 4400 7900 6510 6130 5170 4600 4260 7180 6460 5660 4860 4400 4300 6700 6370 5300 4600 4260 4210

127 123 122 121 121 129 123 123 122 121 120 131 123 122 121 120 121 132 123 122 121 122 130 123 123 122 121 122 127 123 122 121 120 122 124 123 122 121 122 122

129 124 124 124 124 130 124 124 124 124 124 133 124 124 125 124 125 134 124 124 124 126 132 124 124 124 124 126 128 124 124 124 124 126 126 124 124 124 126 126

21,000 VR kt

V2 kt

36 34 30 20 10 3 39 38 30 20 10 5 42 41 30 20 10 7 44 40 30 20 9

7650 6970 6400 5460 4950 4700 7320 6940 5830 5140 4700 4540 7080 6730 5440 4860 4500 4400 6550 5970 5110 4630 4220

124 120 120 119 118 117 123 120 119 118 117 119 122 120 119 118 119 121 120 120 119 118 122

125 121 121 121 121 121 124 121 121 121 121 123 124 121 121 121 123 125 121 121 121 121 126

46 40 30 20 11

6250 5550 4890 4460 4150

123 119 118 118 122

48 40 30 20 13

5960 5200 4630 4300 4150

50 40 30 20 15

5850 4910 4450 4110 4090

20,000 OAT Dist ft °C

VR kt

V2 kt

38 30 20 10 3

6520 5760 5200 4800 4560

117 116 115 114 117

118 118 118 118 121

40 30 20 10 5 42 40 30 20 10 7 44 40 30 20 9

6250 5440 4970 4560 4400 6040 5810 5150 4700 4360 4270 5730 5470 4910 4500 4140

117 116 115 117 119 117 117 116 115 119 121 117 116 115 116 122

118 118 118 121 123 118 118 118 118 123 125 118 118 118 119 126

121 121 121 122 126

46 40 30 20 11

5600 5190 4700 4310 4030

117 116 115 122 121

118 118 118 126 126

120 119 118 120 122

121 121 121 124 126

48 40 30 20 13

5400 4940 4500 4160 4020

116 116 114 120 122

118 118 118 124 126

120 119 117 122 122

121 121 121 126 126

50 40 30 20 15

5290 4720 4340 4030 3970

116 115 116 122 122

118 118 120 126 126

VFTO kt

154

150

146

VERC kt

164

159

155

VREF kt

128

125

122

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-4

BAe 125-800A

TI 4040.25C Original, March 1997

FLAPS 0° - APR ZERO WIND AND GRADIENT A/C Wt lb PRESS OAT Dist ALT - ft °C ft

14 8400 144 146 10 7930 144 146 5 7460 143 146

19 8400 142 144 10 7420 142 144 5 7010 141 144

16 8400 146 148 10 7900 145 148 7 7650 145 148

19 8400 144 146 10 7390 143 146 7 7140 143 146

24 20 10 7

20 8400 146 148 15 7850 145 148 9 7250 144 148

24 8400 144 146 20 7770 144 146 9 6770 142 146

29 8400 143 144 20 7290 142 144 9 6380 140 144

25 8400 146 148 20 7850 145 148 11 7000 144 148

29 8400 144 146 20 7240 143 146 11 6510 142 146

33 30 20 11

8400 7860 6800 6100

144 142 141 140

144 144 144 144

30 25 20 13

8400 7800 7250 6800

146 145 145 144

148 148 148 148

33 30 20 13

8400 7760 6740 6450

144 144 143 142

146 146 146 146

34 30 20 15

8400 7900 6800 6700

146 146 144 144

148 148 148 148

37 30 20 15

8400 7230 6400 6300

144 144 142 142

146 146 146 146

37 30 20 13 41 40 30 20 15

8400 7230 6330 6070 8400 8100 6770 6000 5930

143 142 141 140 143 143 142 140 140

144 144 144 144 144 144 144 144 144

4000

S-L

26,000 VR V2 kt kt

10 8400 145 148 5 7950 145 148

5000

1000

27,000 VR V2 OAT Dist kt kt °C ft

13 8400 142 144 10 7970 142 144 3 7340 141 144

4 3

2000

28,000 VR V2 OAT Dist kt kt ft °C

8400 144 146 7830 144 146

6000

3000

V1 = VR

8400 145 148 8350 145 148

8 3

8400 7860 6920 6650

143 142 141 141

VFTO kt

170

169

166

VERC kt

187

183

180

VREF kt

142

140

138

144 144 144 144

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-5

TI 4040.25C Original, March 1997

BAe 125-800A

FLAPS 0° - APR ZERO WIND AND GRADIENT

V1 = VR

A/C Wt lb 25,000 PRESS OAT Dist VR V2 OAT Dist ALT - ft °C ft kt kt ft °C 6000

5000

4000

3000

2000

1000

S-L

18 8400 140 142 10 7400 139 142 3 6830 139 142 24 20 10 5

8400 7860 6910 6540

140 140 139 138

142 142 142 142

28 20 10 7

8400 7300 6470 6280

140 139 138 138

142 142 142 142

33 30 20 9

8400 7840 6800 5970

140 140 139 138

142 142 142 142

37 30 20 11 41 40 30 20 13 44 40 30 20 15

8400 7260 6340 5700 8250 8080 6750 5930 5670 8160 7400 6320 5610 5540

140 140 139 138 141 141 139 138 138 141 140 139 138 138

142 142 142 142 142 142 142 142 142 142 142 142 142 142

24,000 VR V2 OAT Dist kt kt °C ft

23,000 VR V2 kt kt

23 20 10 3

8400 7880 6850 6370

138 137 139 139

139 139 139 139 139 139 139 139 139 139 139 139 139

28 20 10 3 33 30 20 10 5 37 30 20 10 7

8400 7250 6370 5890 8350 7860 6720 5970 5660 8259 7200 6270 5580 5400

135 134 133 132 135 135 133 132 131 135 134 133 132 131

136 136 136 136 136 136 136 136 136 136 136 136 136 136

28 20 10 5 33 30 20 10 7

8400 7250 6440 6110 8400 7860 6750 6000 5810

138 137 136 135 138 138 136 135 135

37 30 20 9 41 40 30 20 11 44 40 30 20 13 47 40 30 20 15

8270 7210 6300 5550 8270 8060 6750 5910 5300 8030 7350 6300 5500 5260 7930 6850 5880 5200 5140

138 137 136 134 138 138 137 135 134 138 138 136 135 134 138 137 136 134 134

139 139 139 139 139 139 139 139 139 139 139 139 139 139 139 139 139 139 139

40 30 20 9 43 40 30 20 11 46 40 30 20 13 49 40 30 20 15

7970 6690 5850 5160 7760 7310 6270 5480 4900 7550 6750 5840 5110 4900 7470 6320 5450 4870 4800

135 134 132 131 135 135 133 132 131 135 134 133 131 131 135 134 132 131 131

136 136 136 136 136 136 136 136 136 136 136 136 136 136 136 136 136 136 136

VFTO kt

164

160

157

VERC kt

176

172

168

VREF kt

136

133

130

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-6

BAe 125-800A

TI 4040.25C Original, March 1997

FLAPS 0° - APR ZERO WIND AND GRADIENT A/C Wt lb PRESS OAT ALT - ft °C 33 30 6000 20 10 3 36 30 5000 20 10 5 4000

3000

2000

1000

S-L

40 30 20 10 7 43 40 30 20 9 46 40 30 20 11 48 40 30 20 13 50 40 30 20 15

Dist ft 8210 7730 6670 5880 5400 7930 7120 6200 5500 5200 7820 6600 5800 5120 4950 7590 7180 6160 5400 4750 7390 6660 5760 5050 4540 7110 6210 5380 4730 4540 6830 5830 5020 4500 4450

V1 = VR

22,000 21,000 20,000 VR V2 OAT Dist VR V2 OAT Dist VR V2 kt kt ft kt kt ft kt kt °C °C 132 133 36 7710 128 130 38 7160 125 126 131 133 30 7000 128 130 30 6400 124 126 130 133 20 6090 127 130 20 5580 123 126 129 133 10 5390 125 130 10 4900 121 126 128 133 3 4970 125 130 3 4800 120 126 132 133 39 7460 128 130 40 6840 125 126 131 133 30 6490 128 130 30 5950 124 126 130 133 20 5700 126 130 20 5200 122 126 129 133 10 5020 125 130 10 4730 121 126 128 133 5 4800 124 130 5 4560 121 127 42 7270 128 130 42 6600 125 126 132 133 40 7020 128 130 40 6400 124 126 131 133 30 6060 127 130 30 5540 123 126 129 133 20 5320 126 130 20 4860 122 126 128 133 10 4750 124 130 10 4560 120 127 128 133 7 4600 124 130 7 4450 122 128 132 133 44 6960 128 130 44 6340 124 126 131 133 40 6530 128 130 40 5950 124 126 130 133 30 5660 127 130 30 5170 123 126 129 133 20 4960 125 130 20 4600 121 126 127 133 9 4410 124 130 9 4300 124 130 132 133 46 6610 128 130 46 6100 124 126 131 133 40 6090 127 130 40 5570 124 126 130 133 30 5310 126 130 30 4850 122 126 128 133 20 4660 124 130 20 4450 120 126 127 133 11 4220 124 130 11 4110 124 130 132 133 48 6440 128 130 48 5900 124 126 131 133 40 5700 127 130 40 5210 123 126 129 133 30 4960 125 130 30 4520 121 126 128 133 20 4350 124 130 20 4240 122 128 127 133 13 4200 124 130 13 4090 124 130 132 133 50 6230 128 130 50 5700 124 126 130 133 40 5350 127 130 40 4900 123 126 129 133 30 4650 125 130 30 4370 121 126 127 133 20 4180 124 130 20 4060 124 130 127 133 15 4130 124 130 15 4020 124 130

VFTO kt

154

150

146

VERC kt

164

159

155

VREF kt

128

125

122

1. When data is in shaded area refer to Flight Manual performance graphs; either WAT limited, brake energy limited, or tabulation not sufficiently accurate. 2. When ice prevention bleeds are in use add 10 deg C to the actual air temperature before entering the table. 3. Distances are balanced field length or greater.

P-7

TI 4040.25C Original, March 1997

BAe 125-800A

P-8

BAe 125-800A

TI 4040.25C Original, March 1997

P-9

TI 4040.25C Original, March 1997

BAe 125-800A

P-10

BAe 125-800A

TI 4040.25C Original, March 1997

P-11

TI 4040.25C Original, March 1997

BAe 125-800A

P-12

BAe 125-800A

TI 4040.25C Original, March 1997

P-13

TI 4040.25C Original, March 1997

BAe 125-800A

P-14

BAe 125-800A

TI 4040.25C Original, March 1997

MAXIMUM ALTITUDE FOR MAXIMUM DEMONSTRATED LIFT COEFFICIENT

P-15

TI 4040.25C Original, March 1997

BAe 125-800A

INTERMEDIATE SPEED CRUISE 5000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-20 -15 -7

-15 -10 -2

-10 -5 3

-5 0 8

0 5 13

5 10 18

10 15 23

15 20 29

20 25 34

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1850 280

286 1900 280

289 1900 280

291 1900 280

294 1950 280

297 1950 280

299 2000 280

302 2000 280

304 2050 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1850 280

286 1850 280

289 1850 280

291 1900 280

294 1900 280

297 1950 280

299 1950 280

302 2000 280

304 2000 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1800 280

286 1800 280

289 1850 280

291 1850 280

294 1900 280

297 1900 280

299 1950 280

302 1950 280

304 2000 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1750 280

286 1800 280

289 1800 280

291 1850 280

294 1850 280

297 1850 280

299 1900 280

302 1900 280

304 1950 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1750 280

286 1750 280

289 1800 280

291 1800 280

294 1850 280

297 1850 280

299 1850 280

302 1900 280

304 1900 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-20 -19 -11

-15 -14 -6

-10 -9 -1

-5 -4 5

0 1 10

5 6 15

10 11 20

15 16 25

20 21 30

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

291 1850 280

294 1850 280

297 1900 280

300 1900 280

303 1900 280

305 1950 280

308 1950 280

311 2000 280

314 2050 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

291 1850 280

294 1800 280

297 1850 280

300 1850 280

303 1900 280

305 1900 280

308 1950 280

311 1950 280

314 2000 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

291 1750 280

294 1800 280

297 1800 280

300 1850 280

303 1850 280

305 1900 280

308 1900 280

311 1950 280

314 1950 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

291 1750 280

294 1750 280

297 1800 280

300 1800 280

303 1850 280

305 1850 280

308 1850 280

311 1900 280

314 1900 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

283 1700 280

294 1750 280

297 1750 280

300 1800 280

303 1800 280

305 1850 280

308 1850 280

311 1900 280

314 1900 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-20 -23 -14

-15 -18 -9

-10 -13 4

-5 -8 1

0 -3 6

5 2 11

10 7 17

15 12 22

20 17 27

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

300 1800 280

303 1800 280

306 1850 280

309 1850 280

312 1900 280

315 1900 280

318 1950 280

320 1950 280

323 2000 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

300 1750 280

303 1800 280

306 1800 280

309 1850 280

312 1850 280

315 1900 280

318 1900 280

320 1950 280

323 1950 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

300 1750 280

303 1750 280

306 1800 280

309 1800 280

309 1850 280

315 1850 280

318 1900 280

320 1900 280

323 1950 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

300 1700 280

303 1750 280

306 1750 280

309 1800 280

309 1800 280

315 1850 280

318 1850 280

320 1850 280

323 1900 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

300 1700 280

303 1700 280

306 1750 280

309 1750 280

309 1800 280

315 1800 280

318 1850 280

320 1850 280

323 1900 280

9C411

7000 FT

9C412

9000 FT

9C413

P-16

BAe 125-800A

TI 4040.25C Original, March 1997

INTERMEDIATE SPEED CRUISE 11000 FT CRUISING WEIGHT LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

24000

-20 -27 -18

-15 -22 -13

-10 -17 -8

-5 -12 -2

0 -7 3

5 -2 8

10 3 13

15 8 18

20 13 24

(KT) 309 (LB/HR) 1800 (KT) 280

312 1800 280

315 1850 280

318 1850 280

321 1850 280

324 1900 280

327 1900 280

330 1950 280

333 2000 280

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 309 (LB/HR) 1750 (KT) 280

312 1750 280

315 1800 280

318 1800 280

321 1850 280

324 1850 280

327 1900 280

330 1900 280

333 1950 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 309 (LB/HR) 1700 (KT) 280

312 1750 280

315 1750 280

318 1800 280

321 1800 280

324 1850 280

327 1850 280

330 1900 280

333 1900 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 309 (LB/HR) 1700 (KT) 280

312 1700 280

315 1750 280

318 1750 280

321 1800 280

324 1800 280

327 1850 280

330 1850 280

333 1900 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 309 (LB/HR) 1650 (KT) 280

312 1700 280

315 1700 280

318 1750 280

321 1750 280

324 1800 280

327 1800 280

330 1850 280

333 1850 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -26 -16

-10 -21 -11

-5 -16 -6

0 -11 -1

5 -6 5

10 -1 10

15 4 15

20 9 20

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 318 (LB/HR) 1750 (KT) 280

321 1800 280

324 1800 280

327 1850 280

330 1850 280

334 1900 280

337 1900 280

340 1900 280

343 1950 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 318 (LB/HR) 1700 (KT) 280

321 1750 280

324 1750 280

327 1800 280

330 1800 280

334 1850 280

337 1850 280

340 1900 280

343 1900 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 318 (LB/HR) 1700 (KT) 280

321 1700 280

324 1750 280

327 1750 280

330 1800 280

334 1800 280

337 1850 280

340 1850 280

343 1900 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 318 (LB/HR) 1650 (KT) 280

321 1700 280

324 1700 280

327 1750 280

330 1750 280

334 1800 280

337 1800 280

340 1850 280

343 1850 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 318 (LB/HR) 1650 (KT) 280

321 1650 280

324 1700 280

327 1700 280

330 1750 280

334 1750 280

337 1800 280

340 1800 280

343 1850 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -30 -20

-10 -2 -14

-5 -20 -8

0 -15 -4

5 -10 1

10 -5 6

15 0 12

20 5 17

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 327 (LB/HR) 1750 (KT) 280

330 1750 280

334 1800 280

337 1800 280

340 1850 280

344 1850 280

347 1900 280

350 1900 280

353 1900 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 327 (LB/HR) 1700 (KT) 280

330 1700 280

334 1750 280

337 1750 280

340 1800 280

344 1800 280

347 1850 280

350 1850 280

353 1900 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 327 (LB/HR) 1650 (KT) 280

330 1700 280

334 1700 280

337 1750 280

340 1750 280

344 1800 280

347 1800 280

350 1850 280

353 1850 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 327 (LB/HR) 1650 (KT) 280

330 1650 280

334 1700 280

337 1700 280

340 1750 280

344 1750 280

347 1800 280

350 1800 280

353 1800 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 327 (LB/HR) 1600 (KT) 280

330 1650 280

334 1650 280

337 1700 280

340 1700 280

344 1750 280

347 1750 280

350 1800 280

353 1800 280

9C414

13000 FT -20 -31 -21

9C415

15000 FT -20 -35 -25

9C416

P-17

TI 4040.25C Original, March 1997

BAe 125-800A

INTERMEDIATE SPEED CRUISE 17000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

24000

-20 -39 -28

-15 -34 -23

-10 -29 -18

-5 -24 -12

0 -19 -7

5 -14 -2

10 -9 3

15 -4 8

20 5 14

(KT) 337 (LB/HR) 1700 (KT) 280

341 1750 280

344 1750 280

348 1800 280

351 1800 280

354 1850 280

358 1850 280

361 1900 280

365 1900 280

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 337 (LB/HR) 1650 (KT) 280

341 1700 280

344 1700 280

348 1750 280

351 1750 280

354 1800 280

358 1800 280

361 1850 280

365 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 337 (LB/HR) 1650 (KT) 280

341 1650 280

344 1700 280

348 1700 280

351 1750 280

354 1750 280

358 1800 280

361 1800 280

365 1850 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 337 (LB/HR) 1600 (KT) 280

341 1650 280

344 1650 280

348 1700 280

351 1700 280

354 1750 280

358 1750 280

361 1750 280

365 1800 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 337 (LB/HR) 1600 (KT) 280

341 1600 280

344 1650 280

348 1650 280

351 1700 280

354 1700 280

358 1750 280

361 1750 280

365 1750 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -38 -26

-10 -33 -21

-5 -28 -16

0 -23 -10

5 -18 -5

10 -13 0

15 -8 5

20 -3 11

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 348 (LB/HR) 1700 (KT) 280

351 1700 280

355 1750 280

359 1750 280

362 1800 280

366 1800 280

369 1850 280

373 1850 280

377 1900 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 348 (LB/HR) 1650 (KT) 280

351 1700 280

355 1700 280

359 1750 280

362 1750 280

366 1750 280

369 1800 280

373 1800 280

377 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 348 (LB/HR) 1600 (KT) 280

351 1650 280

355 1650 280

359 1700 280

362 1700 280

366 1750 280

369 1750 280

373 1800 280

377 1800 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 348 (LB/HR) 1600 (KT) 280

351 1600 280

355 1650 280

359 1650 280

362 1700 280

366 1700 280

369 1750 280

373 1750 280

377 1800 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 348 (LB/HR) 1550 (KT) 280

351 1600 280

355 1600 280

359 1650 280

362 1650 280

366 1700 280

369 1700 280

373 1750 280

377 1750 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -42 -29

-10 -37 -24

-5 -32 -19

0 -27 -14

5 -22 -8

10 -17 -3

15 -12 2

20 -7 7

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 358 (LB/HR) 1650 (KT) 280

362 1700 280

366 1750 280

370 1750 280

374 1750 280

377 1800 280

381 1800 280

385 1850 280

388 1900 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 358 (LB/HR) 1650 (KT) 280

362 1650 280

366 1700 280

370 1700 280

374 1750 280

377 1750 280

381 1800 280

385 1800 280

388 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 358 (LB/HR) 1600 (KT) 280

362 1650 280

366 1650 280

370 1700 280

374 1700 280

377 1700 280

381 1750 280

385 1750 280

388 1800 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 358 (LB/HR) 1550 (KT) 280

362 1600 280

366 1650 280

370 1650 280

374 1650 280

377 1700 280

381 1700 280

385 1750 280

388 1750 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 358 (LB/HR) 1550 (KT) 280

362 1600 280

366 1600 280

370 1650 280

374 1650 280

377 1650 280

381 1700 280

385 1700 280

388 1750 280

9C417

19000 FT -20 -43 -31

9C418

21000 FT -20 -47 -35

9C419

P-18

BAe 125-800A

TI 4040.25C Original, March 1997

INTERMEDIATE SPEED CRUISE 23000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

24000

-20 -50 -38

-15 -45 -33

-10 -40 -27

-5 -35 -22

0 -30 -17

5 -25 -12

10 -20 -6

15 -15 -1

20 -10 4

(KT) 369 (LB/HR) 1650 (KT) 280

373 1700 280

377 1700 280

381 1750 280

385 1750 280

389 1800 280

393 1800 280

397 1850 280

401 1900 280

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 369 (LB/HR) 1650 (KT) 280

373 1650 280

377 1700 280

381 1700 280

385 1750 280

389 1750 280

393 1800 280

397 1800 280

401 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 369 (LB/HR) 1600 (KT) 280

373 1600 280

377 1650 280

381 1650 280

385 1700 280

389 1700 280

393 1750 280

397 1750 280

401 1800 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 369 (LB/HR) 1550 (KT) 280

373 1600 280

377 1600 280

381 1650 280

385 1650 280

389 1700 280

393 1700 280

397 1750 280

401 1750 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 369 (LB/HR) 1550 (KT) 280

373 1550 280

377 1600 280

381 1600 280

385 1650 280

389 1650 280

393 1700 280

397 1700 280

401 1750 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -49 -36

-10 -44 -30

-5 -39 -25

0 -34 -20

5 -29 -15

10 -24 -9

15 -19 -4

20 -14 1

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 380 (LB/HR) 1650 (KT) 280

385 1700 280

389 1700 280

393 1750 280

397 1750 280

401 1800 280

405 1800 280

410 1850 280

414 1850 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 380 (LB/HR) 1650 (KT) 280

385 1650 280

389 1650 280

393 1700 280

397 1750 280

401 1750 280

405 1800 280

410 1800 280

414 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 380 (LB/HR) 1600 (KT) 280

385 1600 280

389 1650 280

393 1650 280

397 1700 280

401 1700 280

405 1750 280

410 1750 280

414 1800 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 380 (LB/HR) 1550 (KT) 280

385 1600 280

389 1600 280

393 1650 280

397 1650 280

401 1700 280

405 1700 280

410 1750 280

414 1750 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 380 (LB/HR) 1550 (KT) 280

385 1550 280

389 1600 280

393 1600 280

397 1650 280

401 1650 280

405 1700 280

410 1700 280

414 1750 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -53 -39

-10 -48 -34

-5 -43 -28

0 -38 -23

5 -33 -18

10 -28 -12

15 -23 -7

20 -18 -2

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 393 (LB/HR) 1700 (KT) 280

397 1700 280

402 1750 280

406 1800 280

410 1800 280

415 1850 280

419 1850 280

423 1850 280

428 1900 280

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 393 (LB/HR) 1650 (KT) 280

397 1700 280

402 1700 280

406 1750 280

410 1750 280

415 1800 280

419 1800 280

423 1800 280

428 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 393 (LB/HR) 1600 (KT) 280

397 1650 280

402 1650 280

406 1700 280

410 1700 280

415 1750 280

419 1750 280

423 1750 280

428 1800 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 393 (LB/HR) 1600 (KT) 280

397 1600 280

402 1650 280

406 1650 280

410 1700 280

415 1700 280

419 1700 280

423 1750 280

428 1750 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 393 (LB/HR) 1550 (KT) 280

397 1600 280

402 1600 280

406 1600 280

410 1650 280

415 1700 280

419 1700 280

423 1700 280

428 1750 280

9C420

25000 FT -20 -54 -41

9C421

27000 FT -20 -58 -44

9C422

P-19

TI 4040.25C Original, March 1997

BAe 125-800A

INTERMEDIATE SPEED CRUISE 29000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

24000

-20 -62 -47

-15 -57 -42

-10 -52 -36

-5 -47 -31

0 -42 -26

5 -37 -20

10 -32 -15

15 -27 -10

20 -22 -4

(KT) 406 (LB/HR) 1750 (KT) 280

411 1750 280

415 1800 280

420 1800 280

425 1850 280

429 1850 280

434 1900 280

438 1950 280

431 1850 280

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 406 (LB/HR) 1700 (KT) 280

411 1700 280

415 1750 280

420 1800 280

425 1800 280

429 1850 280

434 1850 280

438 1900 280

437 1850 280

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 406 (LB/HR) 1650 (KT) 280

411 1700 280

415 1700 280

420 1750 280

425 1750 280

429 1800 280

434 1800 280

438 1850 280

443 1850 280

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 406 (LB/HR) 1600 (KT) 280

411 1650 280

415 1650 280

420 1700 280

425 1750 280

429 1750 280

434 1750 280

438 1800 280

443 1850 280

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 406 (LB/HR) 1600 (KT) 280

411 1600 280

415 1650 280

420 1650 280

425 1700 280

429 1700 280

434 1750 280

438 1750 280

443 1800 280

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -61 -45

-10 -56 -39

-5 -51 -34

0 -46 -29

5 -41 -23

10 -36 -18

15 -31 -13

20 -26 -8

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 416 (LB/HR) 1750 (KT) 278

421 1800 278

426 1850 278

431 1850 278

436 1850 278

441 1900 278

441 1900 275

435 1800 268

428 1750 261

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 416 (LB/HR) 1700 (KT) 278

421 1750 278

426 1800 278

431 1800 278

436 1850 278

441 1850 278

446 1900 278

441 1800 272

435 1750 265

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 416 (LB/HR) 1700 (KT) 278

421 1700 278

426 1750 278

431 1750 278

436 1800 278

441 1800 278

446 1850 278

447 1850 276

441 1750 269

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 416 (LB/HR) 1650 (KT) 278

421 1650 278

426 1700 278

431 1750 278

436 1750 278

441 1800 278

446 1800 278

450 1850 278

446 1750 273

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 416 (LB/HR) 1600 (KT) 278

421 1650 278

426 1650 278

431 1700 278

436 1750 278

441 1750 278

446 1750 278

450 1800 278

450 1750 275

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -65 -49

-10 -60 -44

-5 -55 -38

0 -50 -33

5 -45 -28

10 -40 -22

15 -35 -17

20 -30 -12

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 413 (LB/HR) 1650 (KT) 267

418 1700 267

423 1700 267

428 1750 267

433 1750 267

437 1800 267

438 1750 264

432 1700 257

424 1650 249

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 413 (LB/HR) 1600 (KT) 267

418 1650 267

423 1650 267

428 1700 267

433 1700 267

437 1750 267

442 1750 267

439 1700 262

431 1650 254

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 413 (LB/HR) 1550 (KT) 267

418 1600 267

423 1650 267

428 1650 267

433 1650 267

437 1700 267

442 1700 267

445 1750 265

438 1650 258

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 413 (LB/HR) 1550 (KT) 267

418 1550 267

423 1600 267

428 1600 267

433 1650 267

437 1650 267

442 1650 267

447 1700 267

444 1650 262

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 413 (LB/HR) 1500 (KT) 267

418 1500 267

423 1550 267

428 1550 267

433 1600 267

437 1600 267

442 1650 267

447 1650 267

449 1650 265

9C423

31000 FT -20 -66 -50

9C424

33000 FT -20 -70 -54

9C425

P-20

BAe 125-800A

TI 4040.25C Original, March 1997

INTERMEDIATE SPEED CRUISE 35000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

24000

-20 -74 -59

-15 -69 -53

-10 -64 -48

-5 -59 -43

0 -54 -37

5 -49 -32

10 -44 -26

15 -39 -21

20 -34 -16

(KT) 409 (LB/HR) 1550 (KT) 255

414 1600 255

419 1600 255

424 1650 255

429 1650 255

434 1700 255

433 1650 252

426 1600 244

414 1500 235

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 409 (LB/HR) 1500 (KT) 255

414 1550 255

419 1550 255

424 1600 255

429 1600 255

434 1650 255

439 1650 255

435 1600 250

426 1550 242

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 409 (LB/HR) 1450 (KT) 255

414 1500 255

419 1500 255

424 1550 255

429 1550 255

434 1600 255

439 1600 255

441 1600 254

434 1550 247

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 409 (LB/HR) 1450 (KT) 255

414 1450 255

419 1450 255

424 1500 255

429 1500 255

434 1550 255

439 1550 255

443 1600 255

441 1550 251

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 409 (LB/HR) 1400 (KT) 255

414 1400 255

419 1450 255

424 1450 255

429 1500 255

434 1500 255

439 1500 255

443 1550 255

447 1550 255

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -72 -56

-10 -67 -50

-5 -62 -45

0 -57 -40

5 -52 -34

10 -47 -29

15 -42 -24

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1500 (KT) 244

412 1500 244

417 1550 244

422 1550 244

427 1600 244

428 1600 241

420 1500 234

407 1450 223

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1400 (KT) 244

412 1450 244

417 1500 244

422 1500 244

427 1500 244

432 1550 244

433 1550 242

426 1500 235

414 1400 225

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1350 (KT) 244

412 1400 244

417 1450 244

422 1450 244

427 1450 244

432 1500 244

437 1500 244

435 1500 240

427 1400 232

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1350 (KT) 244

412 1350 244

417 1400 244

422 1400 244

427 1450 244

432 1450 244

437 1450 244

441 1500 244

436 1450 238

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1300 (KT) 244

412 1300 244

417 1350 244

422 1350 244

427 1400 244

432 1400 244

437 1400 244

441 1450 244

443 1450 242

CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

-15 -72 -56

-10 -67 -50

-5 -62 -45

0 -57 -40

5 -52 -34

10 -47 -29

15 -42 -24

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1450 (KT) 232

412 1500 232

417 1550 232

416 1500 228

408 1450 221

394 1400 210

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1400 (KT) 232

412 1400 232

417 1450 232

422 1450 232

427 1500 232

423 1450 227

412 1400 218

396 1300 206

22000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1300 (KT) 232

412 1350 232

417 1350 232

422 1400 232

427 1400 232

432 1450 232

429 1400 228

421 1350 221

410 1300 212

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1250 (KT) 232

412 1300 232

417 1300 232

422 1350 232

427 1350 232

432 1400 232

437 1400 232

433 1350 227

426 1300 220

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1200 (KT) 232

412 1250 232

417 1250 232

422 1300 232

427 1300 232

432 1350 232

437 1350 232

441 1350 232

435 1300 226

9C426

37000 FT -20 -77 -61

20 -37 -18

9C427

39000 FT -20 -77 -61

9C428

P-21

20 -37 -19

TI 4040.25C Original, March 1997

BAe 125-800A

INTERMEDIATE SPEED CRUISE 41000 FT CRUISING WEIGHT (LB)

TEMP. REL. TO ISA AMBIENT TEMP. O.A.T GAUGE

(DEG C) (DEG C) (DEG C)

26000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) (LB/HR) (KT)

24000

T.A.S. TOTAL FUEL FLOW I.A.S.

22000

-20 -77 -61

-15 -72 -56

-10 -67 -50

-5 -62 -45

0 -57 -40

(KT) 399 (LB/HR) 1400 (KT) 214

404 1400 214

409 1400 214

408 1350 213

398 1300 205

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1300 (KT) 221

412 1300 221

417 1350 221

422 1350 221

20000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1200 (KT) 221

412 1250 221

417 1250 221

18000

T.A.S. TOTAL FUEL FLOW I.A.S.

(KT) 407 (LB/HR) 1150 (KT) 221

412 1200 221

417 1200 221

9C429

P-22

5 -52 -34

10 -47 -29

15 -42 -24

20 -37 420

424 1350 220

416 1300 213

404 1250 203

422 1300 221

427 1300 221

432 1350 221

427 1300 216

419 1250 209

408 1200 201

422 1250 221

427 1250 221

432 1300 221

436 1300 221

431 1250 216

425 1200 210

BAe 125-800A

TI 4040.25C CHG 01, June 1999

LONG RANGE CRUISE SPEED UP TO 31,000 FT

P-23

TI 4040.25C CHG 01, June 1999

BAe 125-800A

LONG RANGE CRUISE SPEED 33,000 FT, 35,000 FT

P-24

BAe 125-800A

TI 4040.25C CHG 01, June 1999

LONG RANGE CRUISE SPEED 37,000 FT, 39,000 FT

LONG RANGE CRUISE SPEED 41,000 FT

P-25

TI 4040.25C CHG 01, June 1999

BAe 125-800A

P-26

BAe 125-800A

TI 4040.25C CHG 01, June 1999

P-27

TI 4040.25C CHG 01, June 1999

BAe 125-800A

P-28

BAe 125-800A

TI 4040.25C CHG 01, June 1999

WIND COMPONENT

P-29

TI 4040.25C CHG 01, June 1999

BAe 125-800A

SUMMARY OF SINGLE-ENGINE CEILINGS DRIFT DOWN IAS KTS

ENG ANTIICING

ISA-15

ISA

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

180 210 240 240

OFF OFF OFF ON

23000 23000 19000 17000

21000 19000 15000 11000

18000 16000 10000 7000

13000 9000 3000 2000

25,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

176 206 235 235

OFF OFF OFF ON

24000 24000 21000 18000

22000 21000 17000 12000

19000 18000 12000 8000

15000 12000 5000 3000

24,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

172 202 230 230

OFF OFF OFF ON

26000 25000 22000 19000

23000 22000 18000 14000

21000 19000 14000 10000

17000 14000 7000 5000

23,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

168 198 225 225

OFF OFF OFF ON

27000 26000 23000 21000

24000 23000 20000 16000

22000 20000 16000 12000

18000 16000 9000 6000

22,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

164 194 220 220

OFF OFF OFF ON

28000 27000 25000 22000

26000 25000 21000 17000

24000 22000 18000 14000

20000 18000 12000 9000

21,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

159 189 215 215

OFF OFF OFF ON

29000 28000 26000 24000

27000 26000 23000 19000

25000 24000 20000 16000

22000 20000 15000 10000

20,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

155 185 210 210

OFF OFF OFF ON

30000 30000 27000 25000

28000 28000 25000 21000

27000 25000 22000 18000

23000 22000 17000 13000

19,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

150 180 205 205

OFF OFF OFF ON

31000 31000 29000 26000

30000 29000 26000 22000

28000 27000 23000 20000

25000 24000 19000 15000

18,000

E.R.CLIMB MIN CRUISE L.R.CRUISE L.R.CRUISE

145 175 200 198

OFF OFF OFF ON

33000 32000 30000 27000

31000 30000 28000 24000

30000 29000 25000 21000

27000 26000 21000 16000

WEIGHT (LB)

SPEED

26,000

SINGLE-ENGINE CEILING AT ISA+10 ISA+20

NOTE: The ceilings in this table are based on average performance on maximum continuous power. To check obstacle clearance, use the enroute net gradient in the performance manual. Enroute net ceiling is 5000 to 8000 feet below the average ceiling given above at enroute climb speed.

P-30