FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

P/N 140-590039-0015
for
GARRETT GTCP36-150W AUXILIARY POWER UNIT

THIS SUPPLEMENT IS APPLICABLE TO

FAA APPROVED AIRPLANE FLIGHT MANUAL
P/N 140-590039-0005
for
Airplane Serials HB-1 and After

Airplane Serial Number: .....................................................................................................

Airplane Registration Number: ...........................................................................................

Copyright © 2008 Hawker Beechcraft Corporation. All rights reserved.

Original Issue: Feb 8, 2008 Section - 7 Page 1 of 20

 FAA Approved Airplane Flight Manual Supplement

LIST OF EFFECTIVE PAGES

Supplement Status Date

Original Feb 8, 2008

Use the List Of Effective Pages to determine the current status of this supplement.

Page Page Revision

Number (s) Status Number

1 of 20 Original 0

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Page 2 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

LOG OF REVISIONS
Rev Page Date
Description FAA Approved
No. No(s) of Revision

0 1-20 Original Issue

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 FAA Approved Airplane Flight Manual Supplement

Intentionally left blank

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FAA Approved Airplane Flight Manual Supplement

CONTENTS
Page

TITLE PAGE .......................................................................................................... 1 of 20

LIST OF EFFECTIVE PAGES............................................................................. 2 of 20

LOG OF REVISIONS ........................................................................................... 3 of 20

INTRODUCTION .................................................................................................. 6 of 20

SECTION 1 - GENERAL ..................................................................................... 7 of 20

SYSTEM DESCRIPTION ..................................................................................7 of 20

Figure 1 - APU Control Panel.........................................................................9 of 20

SECTION 2 - LIMITATIONS .............................................................................. 12 of 20

OPERATING LIMITS ....................................................................................... 12 of 20

STARTING CYCLE LIMITS ............................................................................. 12 of 20

IN-FLIGHT STARTS ........................................................................................ 12 of 20

AUTOMATIC APU SHUTDOWN...................................................................... 12 of 20

MAXIMUM GENERATOR ELECTRICAL LOADS............................................ 12 of 20

COMBINED BLEED AIR OPERATIONS ......................................................... 13 of 20

OPERATION IN KNOWN ICING CONDITIONS .............................................. 13 of 20

GROUND DE-ICING PROCEDURES ............................................................. 13 of 20

ATTENDED OPERATION ................................................................................ 13 of 20

REQUIRED PLACARDS ................................................................................. 13 of 20

APU OPERATION DURING AIRPLANE REFUELING .................................... 13 of 20

WEIGHT and BALANCE.................................................................................. 13 of 20

SECTION 3 - EMERGENCY PROCEDURES ................................................ 14 of 20

APU FIRE ........................................................................................................ 14 of 20

AIRPLANE DOUBLE GENERATOR FAILURE ................................................ 14 of 20

P/N 140-590039-0015 Section - 7 Page 5 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

Page

SECTION 4 - ABNORMAL/NORMAL PROCEDURES ................................ 15 of 20

SUB-SECTION 4.05 - ABNORMAL PROCEDURES ....................................... 15 of 20

AUTOMATIC SHUTDOWN.............................................................................. 15 of 20

FAILURE TO START ....................................................................................... 15 of 20

GENERATOR FAILURE .................................................................................. 15 of 20

BLEED AIR VALVE FAILURE.......................................................................... 16 of 20

SUB-SECTION 4.10 - NORMAL PROCEDURES ............................................ 16 of 20

APU OPERATIONS......................................................................................... 16 of 20

BEFORE STARTING ON GROUND................................................................ 16 of 20

STARTING ON GROUND ............................................................................... 17 of 20

BEFORE STARTING IN FLIGHT..................................................................... 18 of 20

STARTING IN FLIGHT .................................................................................... 18 of 20

SIMULTANEOUS BLEED AIR and ELECTRICAL SYSTEM OPERATION ..... 19 of 20

BLEED AIR ONLY (ELECTRICAL LOAD REMOVED) .................................... 19 of 20

ELECTRICAL LOAD ONLY (BLEED LOAD REMOVED) ................................ 19 of 20

APU SHUTDOWN ........................................................................................... 20 of 20

SECTION 5 - PERFORMANCE ....................................................................... 20 of 20

SECTION 6 - WEIGHT & BALANCE .............................................................. 20 of 20

INTRODUCTION
The information provided in this supplement is applicable to Hawker 750 airplanes with the
Garrett GTCP36-150W Auxiliary Power System installed in accordance with the Supplemental
Type Certificate (STC) ST00459NY.

NOTE: All references to switches and indicators in this supplement refer to the APU, unless
specifically called out as "airplane".

The information contained herein supplements or supersedes the basic Airplane Flight Manual
only in those areas listed within this supplement. For limitations, procedures and performance
information not listed within this supplement, consult the basic Airplane Flight Manual.

Page 6 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

SECTION 1 - GENERAL
SYSTEM DESCRIPTION
Auxiliary Power Unit Installation
The Auxiliary Power Unit (APU) is installed in the rear equipment bay to provide environmental
bleed air and DC electrical power for operating the airplane and its environmental systems
during ground and in flight operations. The unit is installed in a fire and secondary fragmentation
containment enclosure located in the rear of the equipment bay between frames 20 and 21.

The installation includes mounting structure, air inlets for the APU and generator, fuel inlet, APU
exhaust shrouding and shielding, fire detection and extinguishing. APU system drains are
located on the left and right side of the airplane below the main engine pylons. Access to the
APU oil dipstick/fill port is provided by a quick release panel located on the left side of the
enclosure.

The APU starter/generator is connected to the airplane via the STARTER and PS2 Bus systems.
APU bleed air is supplied to the airplane ECS system via the APU load control valve and check
valve which prevents main engine bleed flow through the APU.

Starter Generator
The Lucas starter/generator provides rotational starting capability to the APU when powered
from the airplane battery or from the external 28 VDC power connection, via the airplane start
bus.

When in the generating mode, the starter/generator output is normally connected to the PS2 and
PE busbars. PS1 busbar can also be energized by selecting the airplane BUS TIE switch on the
flight compartment overhead roof panel to CLOSE.

Generator outputs are monitored and displayed on the APU control panel.

Fire Detection/Extinguishing System

Fire protection is provided by a combination of detection and extinguishing systems. In the event
of a fire in the APU enclosure, a visual and audible alarm will occur.

The APU will automatically shut down and a fire extinguisher will discharge 5 seconds after the
detection of the fire alarm. Fire extinguisher thermal relief is directed into the APU enclosure and
the APU will not spool after fire extinguisher discharge or relief.

Switches and indicators for the fire control system are located on the APU control panel
(Figure 1).

P/N 140-590039-0015 Section - 7 Page 7 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

APU Control Panel (Figure 1)

The APU control panel is located on the inboard face of the pilot’s bulkhead and contains the
following switches and indicators for the operation of the APU:

Switches and Indicators Functions

Tests generator control unit’s ability to trip APU
MAIN TEST toggle switch.
generator off-line.
GEN switch - toggle switch, spring Manually controls generator function.
loaded to center.
Selecting MASTER START provides power to the APU
system and initiates the start sequence.

Selecting OFF will shutdown the APU.

MASTER switch - Pull to select.
Allow the APU to come to a complete stop before
selecting MASTER START again.

Fire extinguisher switch - Guarded Initiates action to the ECU to shut down the APU.
toggle switch. Manually discharges fire extinguisher.
RPM indicator. Indicates APU revolutions per minute.
EGT indicator. Indicates APU Exhaust Gas Temperature in °F X 100.
D.C. LOAD meter. Indicates percent of load being generated by APU.
Illuminates amber when oil pressure is less than 35
LOW OIL PRESS annunciator.
PSIG - APU shuts down.
Illuminates amber when temperature is above
HIGH OIL TEMP annunciator.
325° F - APU shuts down.
Illuminates amber if the load control valve fails to close
BLEED AIR VALVE FAIL annunciator.
when BLEED AIR switch is selected OFF.
APU GEN annunciator. Illuminates amber when generator is off-line.
BLEED AIR ON annunciator. Illuminates green when load control valve opens.
Illuminates green to indicate the APU has reached
READY TO LOAD annunciator.
operating speed.
LAMP TEST toggle switch. Ensures all panel annunciator lamps are operable.
BLEED AIR toggle switch. Opens and closes the load control valve.
STOP button. Initiates action to the ECU to shutdown the APU.
A combination switch/light which illuminates red when
fire detectors sense an over temperature condition -
Fire bell will sound.

With the APU off, pushing the switch/light tests the fire
APU FIRE switch/light.
detection circuit. APU FIRE will illuminate - Fire bell
will sound.

With the APU operating, pushing the switch/light will

shutdown the APU.

Page 8 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

APU CONTROL
APU RPM %
0 20 40 60 80 100 120 RPM indicator

RPM
APU EGT °F X 100
0 3 6 9 12 15 EGT indicator

EGT
GEN LOAD
0 .2 .4 .6 .8 1.0 1.2 D.C. LOAD meter

D.C. LOAD

APU LIMITATIONS
OPERATING 0-30,000 FT
STARTING 0-20,000 FT

LOW OIL HIGH OIL

PRESS TEMP

BLEED AIR APU

APU
VALVE FAIL GEN annunciators
BLEED AIR READY TO
ON LOAD

MAIN TEST LAMP TEST

MAIN TEST OVV TEST LAMP TEST

toggle switch toggle switch
NORM NORM

GEN switch GEN BLEED AIR

CLOSE ON BLEED AIR
• Toggle switch,
toggle switch
spring loaded TRIP OFF
to center MASTER
START
STOP push button
MASTER switch ON
switch
• Pull to select OFF STOP

Fire extinguisher
APU APU FIRE
switch
FIRE switch/light
• Guarded toggle
switch PUSH TO TEST
• APU fire warning
light
FIRE

• Fire detection
Figure 1 test switch
APU Control Panel
P/N 140-590039-0015 Section - 7 Page 9 of 20
Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

Fuel System
The APU utilizes fuel from the airplane left main fuel tank. A tap in the fuel supply tube in the left
pylon supplies fuel through shrouded fuel lines, through an APU fuel shut-off valve and a check
valve. The MASTER switch on the APU control panel (Figure 1) is used to control the operation
of the APU shut-off valve.

Drain System
APU drain lines are located below the left and right main engine pylons and at the lower fuselage.
Any fluids (fuel, oil or water) leaking from the APU enclosure, inlets or shrouded lines will drain
out the fittings through hoses/tubes to the airplane drain outlets.

APU Bleed Air

When required, the APU can be used to provide bleed air for the environmental system and or
mechanical shaft power for the 28 VDC generator. These functions can be provided
simultaneously or independently by using the APU control panel. The APU bleed air system
consists of a load control valve, air ducts and check valve which connect the APU bleed air
system to the airplane environmental system.

The life of the Hot Section Components will be extended by operating the APU at no-load
governed speed for at least two minutes prior to the application of a bleed air load. The two-
minute stabilization at no-load RPM will reduce peak stresses during start and operation by 50%.
This will substantially reduce the potential for crack initiation.

Electronic Control Unit (ECU)

An ECU (Garrett P/N 2118330-2) is mounted on the APU support beam on the left of the APU
enclosure. The control unit monitors APU speed, exhaust gas temperature, oil pressures, and
overcurrent conditions during APU starting and operation. It will automatically shut down the
APU in the event that design limitations are exceeded. Signals from switches and pick-ups
mounted to the APU power unit are relayed through the ECU to the appropriate indicator on the
APU control panel. Built-In-Test-Equipment (BITE) indicators are provided on the ECU to assist
maintenance in determining fault conditions.

Automatic ECU shutdown of the APU will occur in-flight or on the ground if any of the following
occur:

1. APU fire

2. Low oil pressure

3. High oil temperature

4. DC power interruption to ECU

5. Overcurrent to ECU

6. Loss of EGT signal

7. High EGT - above redline

8. Overspeed - in excess of 110%

9. Loss of speed signal

Page 10 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

Electrical System Description

The APU generating system can provide DC power to all the airplane busses, with the exception
of the start bus. The APU cannot be used to assist during airplane engine starts. The APU
generator can be operated in parallel with the main generators. Circuit interlocks, described
below, are incorporated and are active in certain circumstances to inhibit closure of the APU
Generator Line Contactor (GLC).

APU GLC interlock relay .........................Prevents APU generator being excited onto a
possible busbar fault while generator control switch
is set to CLOSE.
Ground power auxiliary relay ..................Inhibits GLC input supply when ground power is
being used.
Start Inhibit relay .....................................Energized to allow APU to start. Relay energizes
when battery switch is on and main battery
connectors are de-energized.

Periodically, as a maintenance function, the generator control unit is tested for its ability to trip
the generator off-line in the event of overvoltage. This test is performed by momentarily
positioning the MAIN TEST switch to the OVV position and noting that the APU GEN warning
annunciator illuminates amber and the APU ammeter drops to zero.

Positioning the GEN switch momentarily to CLOSE will bring the APU generator back on-line
and extinguish the APU GEN warning annunciator. Under normal operating conditions, the
transition from starting mode to generating mode is automatic. Manual control of the generator
function is provided by a GEN CLOSE/TRIP switch located on the APU control panel. The switch
is spring loaded against either operating position.

Circuit Breakers, Current Limiters and Fuses

Flight compartment accessible circuit breakers are located on the DA-D panel in the following
locations:

N6 ........ APU FIRE WARN ....... (Normal background)

N7 ........ APU FIRE EXT ........... (Red background)
N8 ........ APU CTL..................... (Normal background)

One 300 AMP starter/generator current limiter is located on the GA panel which requires
maintenance action if replacement is required.

Six other system protective fuses are located on the ZK-P, GA and GA-2 panels which require
maintenance action if replacement is required.

Rear Equipment Bay Switches

Two remote toggle switches are located on the right side of the aft equipment bay access hatch.

APU EMERG SHUT-OFF........................APU Stop/Disable

APU LOCK-OFF RESET.........................Fire Detection Reset

P/N 140-590039-0015 Section - 7 Page 11 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

SECTION 2 - LIMITATIONS
OPERATING LIMITS
Maximum RPM........................................110%
Maximum operating EGT ........................1350° F
Operation to ............................................0 - 30,000 ft pressure altitude
Starting to................................................0 - 20,000 ft pressure altitude

STARTING CYCLE LIMITS

The following limitations are permitted when using airplane batteries or external power.

Minimum allowable Static Air Temperature (SAT) for starting of APU - by oil type
Type II oil per MIL-L-23699 .....................-40° C
Type I oil per MIL-L-7808 ........................-55° C

Maximum transient EGT

15 seconds maximum duration ...............1400° F to 1500° F

Hung start duration

Above 50% and below 95% RPM ...........10 seconds maximum

NOTE: Shut down the APU if the READY TO LOAD light does not illuminate within 60 seconds
of start.

Starter continuous cranking limits

1st start attempt ......................................30 seconds ON - 3 minutes OFF
2nd start attempt .....................................30 seconds ON - 3 minutes OFF
3rd start attempt......................................30 seconds ON - 30 minutes OFF

IN-FLIGHT STARTS
Do not attempt an in-flight start of the APU if both main generators have failed.

Start of the APU is prohibited if No. 1 engine has been shutdown due to fire or engine failure.

AUTOMATIC APU SHUTDOWN

If the APU is shut down by the automatic protection system, no attempt must be made to restart
the APU until the cause of the shutdown has been established.

Prior to the next flight, the APU and rear equipment bay must be inspected for damage.

MAXIMUM GENERATOR ELECTRICAL LOADS

The maximum transient generator load may exceed maximum continuous load:

Maximum continuous operation ..............0.80

Transient operation..................................1.2 < 10 Seconds

Page 12 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

COMBINED BLEED AIR OPERATIONS

Simultaneous operation of APU bleed air and main engine bleed air is not permitted.

Both systems may be operated briefly (1 minute maximum) during change over from one system
to the other.

OPERATION IN KNOWN ICING CONDITIONS

Flight operations of the APU are not approved when the airplane is in icing conditions.

GROUND DE-ICING PROCEDURES

The APU must be shut down during ground de-icing operations of the airplane.

ATTENDED OPERATION
The APU must be attended when passengers are on board.

REQUIRED PLACARDS
On or adjacent to APU control panel:

APU LIMITATIONS
OPERATING ............................................0-30,000 FT
STARTING ..............................................0-20,000 FT

APU OPERATION DURING AIRPLANE REFUELING

Airplane refueling with the APU running is limited to single point refuel only. Gravity wing
refueling is prohibited with the APU running.

Starting of the APU while refueling is in progress is prohibited.

Airplane refueling with the APU running is prohibited if the ambient temperature is above
40° C or when the airplane contains JP4 or is being refueled with JP4.

Airplane boost pumps must be OFF prior to commencing refueling operations.

WEIGHT and BALANCE

NOTE: Removal of any of the APU components, listed in Section 6, will render the
APU inoperative.

P/N 140-590039-0015 Section - 7 Page 13 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

SECTION 3 - EMERGENCY PROCEDURES

APU FIRE
APU Panel MWS Panel

APU
Fire Bell Sounds and APU With
FIRE FIRE

STOP.......................................................Push (momentarily)
MASTER .................................................OFF
FIRE extinguisher....................................Lift guard, Select On

If Fire Warning Persists

APU FIRE WARN circuit breaker ............Pull (DA-D, N6)
NOTE: Pulling the circuit breaker will silence the warning bell and extinguish the APU FIRE
switch/light.

Subsequent Action
Land at the nearest suitable airport.

The cause of the fire warning must be investigated and corrected prior to the next flight.

WARNING: IF FIRE WARNING OCCURS DURING GROUND OPERATIONS, DO NOT

CONTINUE TO OPERATE THE AIRPLANE OR THE APU UNTIL POSSIBLE
DAMAGE HAS BEEN ASSESSED.

NOTES:
1. Do not return the MASTER switch to ON.
2. The APU FIRE annunciator will remain illuminated and the fire bell will continue to sound
until the over temperature condition falls below the system set-point and one of the
following actions are taken:

(a) Pushing the APU FIRE switch/light on the APU control panel, or
(b) Pushing the APU LOCK-OFF RESET switch located in the aft
compartment where the APU is installed.
3. When an APU fire warning occurs, the APU will immediately and automatically shut down
and the fire extinguisher will discharge after 5 seconds.

4. Activation of the APU FIRE switch/light does not illuminate the airplane
MWS flashers.

AIRPLANE DOUBLE GENERATOR FAILURE

If both main generators fail, do not start the APU. If both main generators fail and the APU is
already operating, the APU may be left on provided the APU generator is operating.

WARNING: A FAILED APU START WITH TWO INOPERATIVE MAIN GENERATORS MAY
DEPLETE THE MAIN AIRPLANE BATTERIES.

Page 14 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

SECTION 4 - ABNORMAL/NORMAL PROCEDURES

SUB-SECTION 4.05 - ABNORMAL PROCEDURES
AUTOMATIC SHUTDOWN

May be accompanied by LOW OIL and/or HIGH OIL

PRESS TEMP

MASTER................................................. OFF

WARNING: DO NOT OPERATE THE APU UNTIL CAUSE OF SHUTDOWN HAS

BEEN DETERMINED AND CORRECTED.

NOTES:
1. Automatic shutdown may occur during ground or in-flight operations.
2. Do not return the MASTER switch to ON, since this will reset the ECU and remove the
BITE indicators necessary to determine the cause of the shutdown.

3. After shutdown, all annunciator lights will extinguish unless caused by fire.

4. Prior to the next flight, the APU and rear equipment bay must be inspected for damage.

FAILURE TO START
If the APU fails to start within 10 seconds after setting the MASTER switch to start
STOP...................................................... Push (momentarily)
MASTER................................................. OFF

CAUTION: WAIT 3 MINUTES TO ALLOW FUEL TO DRAIN BEFORE ATTEMPTING

ANOTHER START.

GENERATOR FAILURE

APU
GEN

GEN........................................................ CLOSE (momentarily)

NOTE: A maximum of two reset attempts is permissible.

If annunciator remains illuminated

GEN........................................................ TRIP (momentarily)

If annunciator extinguishes
Continue APU operations.

P/N 140-590039-0015 Section - 7 Page 15 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

BLEED AIR VALVE FAILURE

BLEED AIR
VALVE FAIL

BLEED AIR .............................................OFF

CAUTION: DO NOT OPEN THE AIRPLANE MAIN AIR VALVES UNTIL THE APU LOAD
CONTROL VALVE MALFUNCTION IS CORRECTED.

SUB-SECTION 4.10 - NORMAL PROCEDURES

APU OPERATIONS
NOTES:
1. The APU may be started using either the airplane batteries or an external ground power
source.
2. If the fire extinguisher pressure is depleted, the APU will not spool.

BEFORE STARTING ON GROUND

Fire extinguisher gauge...........................Check at or above:
300 psig at - 40° F
575 psig at + 70° F
Circuit breakers .......................................Set
MASTER .................................................OFF
Airplane Battery ......................................ON
Airplane External power..........................ON (if desired)
MAIN TEST .............................................NORM
LAMP TEST ............................................NORM
GEN ........................................................CLOSE (momentarily)
BLEED AIR .............................................OFF
FIRE EXTINGUISHER ............................Covered by guard
APU FIRE switch/light .............................Push
(check APU FIRE illuminates and fire bell sounds).

Page 16 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

STARTING ON GROUND
Airplane left LP fuel cock.........................OPEN
MASTER .................................................ON
DC LOAD meter ......................................Reads zero
RPM indicator..........................................Reads zero
EGT indicator ..........................................Reads approximately ambient
Airplane LH fuel pump.............................ON,
EMERG (when using airplane batteries).
FUEL 1 LO PRESS annunciator
(airplane overhead roof panel) ................Extinguished

LOW OIL PRESS annunciator.................Illuminated

APU GEN annunciator ............................Illuminated
MASTER .................................................START (momentarily)
RPM indicator..........................................Shows rotation
EGT indicator ..........................................Shows rise within 10 seconds after rotation
APU indicators.........................................Monitor start cycle
LOW OIL PRESS annunciator.................Extinguished
READY TO LOAD annunciator ................Illuminated
APU GEN annunciator ............................Extinguished
DC LOAD meter ......................................Indicates load
RPM indicator..........................................Check 100%
EGT indicator ..........................................Check within limits
Airplane BUS TIE ....................................CLOSE

CAUTION: IF THE AIRPLANE IS LEFT UNATTENDED WITH THE APU OPERATING, THE
MAIN AIRPLANE BATTERIES SHOULD BE LEFT ON.

THIS WILL ALLOW THE APU FIRE EXTINGUISHER TO DISCHARGE IN THE

EVENT OF AN AUTOMATIC SHUTDOWN DUE TO AN APU FIRE.

P/N 140-590039-0015 Section - 7 Page 17 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

BEFORE STARTING IN FLIGHT

MASTER .................................................OFF
Airplane Battery ......................................ON
MAIN TEST .............................................NORM
LAMP TEST ............................................NORM
GEN ........................................................CLOSE (momentarily)
BLEED AIR .............................................OFF
FIRE EXTINGUISHER ............................Covered by guard
APU FIRE switch/light .............................Push,
(check APU FIRE illuminates and fire bell sounds).

STARTING IN FLIGHT
Airplane left LP fuel cock.........................OPEN (left main engine operating)
MASTER .................................................ON
DC LOAD meter ......................................Reads zero
RPM indicator..........................................Reads zero
EGT indicator ..........................................Reads approximately ambient or 0 if ambient is
lower.
Airplane LH fuel pump ............................ON
FUEL 1 LO PRESS annunciator
(airplane overhead roof panel) ................Extinguished

LOW OIL PRESS annunciator ................Illuminated

APU GEN annunciator ............................Illuminated
MASTER .................................................START (momentarily)
RPM indicator..........................................Shows rotation
EGT indicator ..........................................Shows rise within 10 seconds after rotation
APU indicators ........................................Monitor start cycle
LOW OIL PRESS annunciator ................Extinguished
READY TO LOAD annunciator................Illuminated
APU GEN annunciator ............................Extinguished
DC LOAD meter ......................................Indicates load
RPM indicator..........................................Check 100%
EGT indicator ..........................................Check within limits
Airplane BUS TIE ....................................CLOSE

Page 18 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008
FAA Approved Airplane Flight Manual Supplement

SIMULTANEOUS BLEED AIR and ELECTRICAL SYSTEM OPERATION

APU ........................................................ Operating
RPM and EGT indicators ........................ Within limits
READY TO LOAD annunciator ............... Illuminated
BLEED AIR ............................................. ON
BLEED AIR ON annunciator................... Illuminated
Airplane Environmental Controls ............ As required
RPM indicator ......................................... Check 100%
EGT indicator.......................................... Check within limits
DC LOAD meter...................................... Check loading within limits

BLEED AIR ONLY (ELECTRICAL LOAD REMOVED)

GEN ........................................................ TRIP (momentarily)
APU GEN annunciator............................ Illuminated
READY TO LOAD annunciator ............... Illuminated
DC LOAD meter...................................... Check reads zero
BLEED AIR ............................................. ON
BLEED AIR ON annunciator................... Illuminated

ELECTRICAL LOAD ONLY (BLEED LOAD REMOVED)

BLEED AIR ............................................. OFF
BLEED AIR ON annunciator................... Extinguished
BLEED AIR VALVE FAIL annunciator ..... Extinguished

NOTE: If the BLEED AIR VALVE FAIL annunciator remains illuminated, refer to the
BLEED AIR VALVE FAILURE procedure in the ABNORMAL PROCEDURES,
Sub-section 4.05 of this supplement.

READY TO LOAD annunciator ............... Illuminated

GEN ........................................................ CLOSE (momentarily)
APU GEN annunciator............................ Extinguished

P/N 140-590039-0015 Section - 7 Page 19 of 20

Original Issue: Feb 8, 2008
 FAA Approved Airplane Flight Manual Supplement

APU SHUTDOWN
NOTE: For shutdown, electrical and bleed loads should remain as they have been. Changing
these loads, just prior to APU shutdown, exposes the hot section components to
additional thermal gradient changes that will increase potential for crack propagation.

If APU accessory loads are changed, allow a minimum of 3 minutes to elapse prior to shutdown.

STOP.......................................................Push (momentarily)
RPM indicator..........................................Check decrease in RPM
EGT indicator ..........................................Check decrease in temperature
MASTER .................................................OFF when RPM indicates zero

SECTION 5 - PERFORMANCE
No Change.

SECTION 6 - WEIGHT & BALANCE

Airplane delivery empty weight includes the APU installation as follows:

ITEM LBS X STA = IN LBS

651-1-331-101.......APU INSTALLATION ...... 304.8............. 449.04.......136,868

The following serialized major components are included in the above total:

ITEM LBS X STA = IN LBS

651-1-348-101.......APU BUILDUP ............... 175.0............. 458.9 .........80,308

23080-005 .............STARTER/GEN ................ 36.1............. 458.9 .........16,566

51539-006H ..........GCU ................................... 2.4............. 477.5 ............1146

211833D-2 ............ECU.................................... 6.1............. 454.0 ............2769

109512-9 ...............LCV .................................... 5.2............. 473.3 ............2461

4190-1 ...................FIRE BOTTLE .................... 7.7............. 469.3 ............3614

Page 20 of 20 Section - 7 P/N 140-590039-0015

Original Issue: Feb 8, 2008