Aircraft

Recovery
Manual

MODEL A/C EFFECTIVITY

BD-100-1A10 (CH-300) 20003-20457

BD-100-1A10 (CH-350) 20501-20999

Publication No. CH 300 ARM

BOMBARDIER CHALLENGER* 300 and 350 (MODEL BD-100-1A10)

AIRCRAFT RECOVERY MANUAL

Bombardier Aerospace
P. O. Box 6087, Station Centre-ville
Montreal, Quebec, Canada H3C 3G9

http://www.cic.bombardier.com

For more information regarding Technical Publications please contact:

Bombardier Customer Services Business Aircraft

Customer Services Hotline (Technical Assistance & In-flight Emergencies)

North America: 1-866-JET-1247 (1-866-538-1247) [Press 1]
International: +1-514-855-2999 [Press 1]
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User Comments (Technical Publications)

North America: 1-866-JET-1247 (1-866-538-1247) [Press 4 then option 2]
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Ordering & Distribution (Technical Publications)

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Email: bbad.pubs.dist@aero.bombardier.com

To ease the ordering process, the following Document

Identification Number should be used: CH 300 ARM

It is understood that this documentation, comprising technical data and other information in any media
shall not be reproduced or disclosed in whole or in part without Bombardier's written authorization, is
proprietary and confidential to Bombardier and that all rights to patent, copyright, trademark, trade
secret and other intellectual property rights therein belong to Bombardier. Such documentation,
technical data and other information shall not be modified, translated, reverse assembled, reverse
engineered or de-compiled and shall be used solely to maintain, operate or repair the aircraft.

the evolution of mobility

Copyright © 2013 by Bombardier Inc. All rights reserved.

*Trademark of Bombardier Inc. or its subsidiaries.
Printed in Canada
 USER COMMENTS
ON ERRORS, OMISSIONS, PROCEDURES (IF APPLICABLE), ETC.

To: Bombardier Business Aircraft, Customer Support

Department 631 (Technical Publications and Information)

From: Date:
Address:

E−mail: Aircraft S/N:

Telephone No. (please print)

The following publication requires correction or clarification:

Publication: Page Date:

Chap./Sect. No. Page No. Para No. Fig. No.
Comments:

You can send your user comment as follows:

− by telephone at (514) 855−9304
− by e−mail to bbad.user.comments@aero.bombardier.com
− by fax at (514) 855−7894
− by mailing it to the address on the back of this page.
Bombardier Business Aircraft, Customer Support
P.O. Box 6087, Station Centre−ville
Montreal, Quebec, Canada H3C 3G9

Attn: User Comments Coordinator

Department 631
 USER COMMENTS
ON ERRORS, OMISSIONS, PROCEDURES (IF APPLICABLE), ETC.

To: Bombardier Business Aircraft, Customer Support

Department 631 (Technical Publications and Information)

From: Date:
Address:

E−mail: Aircraft S/N:

Telephone No. (please print)

The following publication requires correction or clarification:

Publication: Page Date:

Chap./Sect. No. Page No. Para No. Fig. No.
Comments:

You can send your user comment as follows:

− by telephone at (514) 855−9304
− by e−mail to bbad.user.comments@aero.bombardier.com
− by fax at (514) 855−7894
− by mailing it to the address on the back of this page.
Bombardier Business Aircraft, Customer Support
P.O. Box 6087, Station Centre−ville
Montreal, Quebec, Canada H3C 3G9

Attn: User Comments Coordinator

Department 631
 USER COMMENTS
ON ERRORS, OMISSIONS, PROCEDURES (IF APPLICABLE), ETC.

To: Bombardier Business Aircraft, Customer Support

Department 631 (Technical Publications and Information)

From: Date:
Address:

E−mail: Aircraft S/N:

Telephone No. (please print)

The following publication requires correction or clarification:

Publication: Page Date:

Chap./Sect. No. Page No. Para No. Fig. No.
Comments:

You can send your user comment as follows:

− by telephone at (514) 855−9304
− by e−mail to bbad.user.comments@aero.bombardier.com
− by fax at (514) 855−7894
− by mailing it to the address on the back of this page.
Bombardier Business Aircraft, Customer Support
P.O. Box 6087, Station Centre−ville
Montreal, Quebec, Canada H3C 3G9

Attn: User Comments Coordinator

Department 631
 BD−100 AIRCRAFT RECOVERY MANUAL

RECORD OF REVISIONS

A signature in the "INSERTED BY" column shows that

the publication holder has incorporated the revision.

REVISION NO. ISSUE DATE DATE INSERTED INSERTED BY

1 Jul 11/2005 Jul 11/2005 Bombardier

2 Oct 25/2007 Oct 25/2007 Bombardier

3 Jan 30/2012 Jan 30/2012 Bombardier

4 Oct 05/2012 Oct 05/2012 Bombardier

5 Jan 31/2013 Jan 31/2013 Bombardier

6 Jan 29/2014 Jan 29/2014 Bombardier

7 May 08/2014 May 08/2014 Bombardier

8 Oct 31/2014 Oct 31/2014 Bombardier

9 Dec 22/2015 Dec 22/2015 Bombardier

 BD−100 AIRCRAFT RECOVERY MANUAL

RECORD OF TEMPORARY REVISIONS

TEMPORARY SECTION AND PAGE ISSUE DATE INSERTED DATE REMOVED

REV. NO. NO. DATE INSERTED BY REMOVED BY
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BD−100 AIRCRAFT RECOVERY MANUAL

LIST OF EFFECTIVE PAGES

Title Effectivity Page Date Title Effectivity Page Date

Effective Pages 1 Dec 22/2015 20151222 Section 04 1 Jan 30/2012 20120130

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 BD−100 AIRCRAFT RECOVERY MANUAL

BD−100 AIRCRAFT RECOVERY MANUAL

TABLE OF CONTENTS

Section Page

SECTION 01 − Introduction
Scope of the Manual 1
Manual Organization
Correspondence 2
Statement of Liability
Technical Glossary
Dimensions 3

SECTION 02 − Aircraft Recovery

Quick Reference Guide 1
Planning for Aircraft Recovery 3
General
Aircraft Recovery Plan
Moving the Aircraft 5
General
Steps and Recommendations for an Efficient Aircraft Recovery 6
Terrain Consideration 21
General
Factors to Find the Most Practical Recovery Plan
Ground Conditions

SECTION 03 − Aircraft − General

Model Designation and Type 1
Aircraft Dimensions
Dangerous Areas
Doors
Composite Materials
Interior Configurations 2

SECTION 04 − Emergency Information

Emergency Access 1
Passenger Door
Overwing Emergency−Exit Door 3
Baggage Door 5
Aft Equipment−Compartment Door 7
Service Doors and Panels 9
Windshields and Windows 11

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 BD−100 AIRCRAFT RECOVERY MANUAL

Section Page

SECTION 05 − Fire Fighting

General 1
On−Board Fire−Fighting Equipment 4
Engine/APU Fire Controls 7
Electrical Control Panels and Battery Locations 16
Flammable Fluids and Gases 19
Fuel System General Layout 21
Emergency Break−In Zone 25
Tires
Composite Material Fire Precautions
General
Dangerous Effects of Free Fibers
Control of Free Fibers 26

SECTION 06 − Ground Safety

Towing the Aircraft 1
General
Towing the Aircraft with Bridle
Ground Lockpins 2
Safety Precautions 9

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 BD−100 AIRCRAFT RECOVERY MANUAL

INTRODUCTION

1. Scope of the Manual

A. Bombardier Business Aircraft Customer Support (BBACS) prepared the Aircraft

Recovery Manual to help an Airport Authority, an FBO, and/or an aircraft recovery crew if
an accident occurs with a Bombardier Challenger BD−100−1A10 model Business Jet.
Because there are many Completion Centers that do different passenger compartment
layout, it is not possible to give all the different layouts in this manual.

B. Challenger BD−100−1A10 model referred in this manual, include:

− Challenger 300
− Challenger 350

C. No aircraft recovery operation will be the same as other recovery operations because of:
− The accident or the incident itself,
− The location of the aircraft,
− The amount of aid that is available locally,
− The weather conditions when the accident/incident occurred. Also, the effects of the
weather before and during the recovery operation,
− The number of persons that are available to help with the recovery.

2. Manual Organization

A. There are six sections in this manual:

− Section 1 − INTRODUCTION
− Section 2 − AIRCRAFT RECOVERY
− Section 3 − AIRCRAFT − GENERAL
− Section 4 − EMERGENCY INFORMATION
− Section 5 − FIRE FIGHTING
− Section 6 − GROUND SAFETY

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3. Correspondence

A. Send your questions and suggestions to:

By e−mail to: SRPSA@aero.bombardier.com (preferred) or
By phone at: Customer Response Center (CRC)
Local and International: 514−855−2999
North America only: 1−866−JET−1247 (1−866−538−1247) Tool Free
Attention: Air Safety Investigation, Department 686−5

4. Statement of Liability

A. This manual is intended to be used by Aircraft Crash Recovery crews involved in the
recovery of any Bombardier BD−100−1A10 Challenger model Business Jet which
becomes involved in an accident or incident. It is also intended to help those persons
planning for the unlikely event that will require recovery actions. The actions described in
this manual are intended as recommendations only, as to how aircraft recovery tasks
should be carried out. Any omission of a task or an action, or any omission to a task or
action, shall not be interpreted as an admission of liability by Bombardier Inc., or any of
its sub−groups of affiliates or related entities.

5. Technical Glossary

A. Refer to Table 1 for a Technical Glossary of aircraft terminology and abbreviations.

Table 1− Technical Glossary

A/C Aircraft

ac Alternating Current

AFFF Aqueous Fire Fighting Foam

APU Auxiliary Power Unit

AUX Auxiliary

CBR California Bearing Ratio

dc Direct Current

DISCH Discharge

ELECT PWR Electrical Power

ENG Engine

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Table 1− Technical Glossary

EQP Equipment Bay

FBO Fixed Base Operator

FS Fuselage Station

FT/SEC Feet per second

IATP International Air Technical Pool

ICAO International Civil Aviation Organization

IIC Investigator−in−Charge

KM/H Kilometers per hour

LWR FUS Lower Fuselage

mm Millimeter

mph miles per hour

MLG Main Landing Gear

NLG Nose Landing Gear

T/E Trailing Edge

TYP Typical

6. Dimensions

A. Linear dimensions given in this manual are in inches. The metric equivalents are given in
parentheses ( ).

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AIRCRAFT RECOVERY

1. Quick Reference Guide

A. The leader of the recovery operation can use the Quick Reference Guide that follows as
a checklist for the recovery team to refer to.

(1) Do the weight and balance

(a) Find the weight and balance of the aircraft to make an estimate of the limits to
jack and tow the aircraft.

(b) Record the quantity and location of cargo and fuel to calculate the weight and
balance.

NOTE: You may have to calculate the weight and balance more than one
time during the recovery operations.

(2) Get initial data about the incident

(a) Set up interfaces with the Investigator−in−Charge (IIC), local authorities, the
aircraft manufacturer’s (Bombardier) representative, and the owner’s agent or
representative.

(b) Tell the recovery crew surveyor to make a full estimate of the site as quickly as
possible. The type of accident site can have an effect on the aircraft removal.

(c) Make a note of the slope of the terrain, the ground cover (e.g. trees, grass,
rock), and the distance from the runways, taxiways, and aprons.

(d) Make an analysis of the ground condition to calculate the bearing area
necessary to lift and move the aircraft.

(e) Choose suitable personnel (as well as the recovery crew members) and make
an estimate of the necessary equipment, and related manuals.

(f) Get accommodations, transportation, work visas (when necessary), and

money for the recovery team.

NOTE: The IIC must be at the site before this occurs.

(g) At the site, speak to local airport authorities, regulatory authorities, and
national investigating authorities.

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 BD−100 AIRCRAFT RECOVERY MANUAL

Get data on the items that follow:

− Local environment

− Climate

− Terrain structure

− Communications

− Local regulations for the defueling of the aircraft.

(3) Set Up Interfaces

(a) Make a detailed aircraft recovery plan (use a general recovery plan).

(b) Get permission from local and national authorities to continue with the
recovery operation. It is necessary for the different authorities to find the
cause(s) of an aircraft accident. You must know and follow the regulatory
authority regulations, and the laws of the country in which the accident occurs.

(c) Move personnel and equipment to the recovery site.

(d) Prepare hangar and/or parking space for the aircraft. Refer to section 3 figure
1 for aircraft dimensions.

(e) Make sure that cranes are locally available. Also, make sure that other heavy
equipment, building materials and access roads are available. Some operators
are member of an organization that share their technical facilities, services and
recovery equipment (recovery kits). The International Air Technical Pool (IATP)
is the organization that manages the recovery pool arrangement.

(f) If components are removed from the aircraft for recovery purposes, the center
of gravity weight and balance location must be re−calculated before the aircraft
is moved.

(g) If possible, remove all health risk payload (fuel, oils, dangerous materials,
catering, oxygen, squibs, galley and lavatory disposal and water) from the
aircraft.

NOTE: Follow the applicable local regulations concerning defueling.

(h) If possible, remove the baggage, cargo and flyaway kit.

(i) If required, remove primary components as necessary.

(j) Refer to Section 6 − GROUND SAFETY for data on the installation of the
ground lockpins. These lockpins are used, where possible, to safety the
landing gear for operations on the ground.

(k) Prepare to tether, lift and move the aircraft.

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 BD−100 AIRCRAFT RECOVERY MANUAL

(l) Complete the aircraft damage report when the aircraft recovery is completed.
The damage report is made by the Bombardier investigating team, or a
Technical Support/Engineering team that is specially assembled for the task.

2. Planning for Aircraft Recovery

A. General

CAUTION: THE SPECIAL PROBLEMS THAT ARE RELATED TO AN AIRCRAFT

RECOVERY OPERATION MAKE IT NECESSARY FOR ONE APPROVED
PERSON TO DIRECT ALL OF THE OPERATION.

(1) Refer to the International Civil Aviation Organization (ICAO) document

No. 9137−AN/898, Airport Services Manual; Part 5, "Removal Of Disabled Aircraft"
as an aid for aircraft recovery.

(2) The document gives the procedures to use for the recovery and/or the removal of a
disabled aircraft. Some advanced procedures that are necessary are as follows:

(a) When you have to move an aircraft that cannot taxi or be towed with an
approved towbar or towing bridle, use other recovery procedures. The aircraft
may be lifted with pneumatic bags or cranes and move on a trailer or dollies.

(b) Advance planning is important to make sure that the equipment and persons
with the skills to do a recovery operation are available when necessary.

(c) Prepare a full "Aircraft Recovery Plan" which may be started as soon as an
accident occurs and at the request of the IIC.

(d) Make sure to have the necessary emergency procedures. Give to the
applicable personnel, the tasks they are responsible for.

(e) Tell all major users of the airport about the airport management policies that
apply to the removal of disabled aircraft. Include applicable parts of this
document in the airport procedure.

NOTE: We recommend that a copy of this document be in the airport’s

"Aircraft Recovery Plan."

B. Aircraft Recovery Plan

(1) The Aircraft Recovery Plan includes:

(a) Guidelines for the fast removal of a disabled aircraft from airport operational
areas as well as the time necessary to prevent secondary damage to the
aircraft.

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(b) Detailed grid maps for use during aircraft recovery operations. The maps must
show the topography of the airport site, approaches and adjacent areas. They
must also show roads, ditches, gates, ground conditions and other factors that
could have an effect on the aircraft recovery operations.

(c) Details about access roads to all parts of the airport that are near overhead
power lines or bridges, specially those roads necessary for heavy equipment
such as cranes.

(d) Bombardier’s data on the Challenger Series aircraft that uses the airport. For
aircraft recovery, the important data is the weight and balance, lifting and
moving, and weight reduction numbers.

(e) The type and location of heavy or special equipment and the time necessary
for the equipment to get to the airport. Equipment to defuel aircraft must be
available to move to all areas or locations. Because of the dimensions of the
Challenger Series aircraft, cranes and slings can be used to lift the aircraft.
Because of this, you can include the availability of cranes in the recovery plan.

NOTE: If not available, try to get aircraft recovery kits from other airports as
quickly as possible.

The ICAO "Airport Services Manual", Part 5, gives a worldwide list of

aircraft recovery kits.

(f) Sources of personnel with different skills, ranging from laborers to aircraft
mechanics.

(g) The requirement for food, clothes, and shelter for the recovery crew.

(h) Flexible procedures for communications, security and safety for the recovery
operations, that are correct for the site.

(i) An active inventory of local salvage equipment that is available to the airport.
The operator can get aircraft removal equipment and crews through contracts
with airport owners, military airfields or aeronautical industries near the airport.

(j) Airport rules must make sure of the items that follow:

1 The airport owner’s right to close all or part of the airport as necessary.

2 The limits of liability and penalties for violations.

NOTE: An agreement must received from the IIC or the senior official of
the investigation team, before the airport owner can move a
disabled aircraft.

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(k) Contracts/agreements between aircraft operators and fixed base operators

must give each of them the capacity to move the types of aircraft they use or
those on which they do servicing. The movement must include minimum risk of
damage to the aircraft and to the airport. The contracts/agreements can be
with a single operator, a cooperative procedure with the airport authorities or a
joint procedure by more than one operator at the applicable airport. We
recommend that operators put their removal equipment together because of:

1 The logistical and time saving advantages of recovery kits that they own
together.

2 The economic advantages to single operators (they can buy fewer kits).

3 The improvements that come with more equipment because a larger

number of operators are together.

(l) The contracts/agreements must record the fixed base operator’s procedures
and capacity to do non−routine aircraft repairs on runways.

(m) Procedures and agreements for airports used jointly by civil and military
aviation.

(n) Analysis of data on recovery equipment, it shows that the type of recovery
equipment used does not affect the actual removal time.

(o) In the procedures for recovery equipment, look carefully at the items that
follow:

1 The full system to lift and to move the aircraft.

2 The mixture of recovery system components and the support equipment

necessary to move dangerous materials. Also, other equipment such as
cranes, dollies, and flatbed trucks.

NOTE: To move the Bombardier Challenger Series aircraft, we

recommend a tractor/trailer with a bed of equally low height.
This will decrease the height the recovery team must lift a
damaged aircraft.

3 The availability of winch equipped heavy equipment (bulldozer, tractor

etc.).

3. Moving the Aircraft

A. General

(1) The primary reason to move the aircraft is for recovery as quickly as possible
without further primary or secondary damage. An up−to−date recovery plan is the
best procedure to decrease recovery time. Procedures for the recovery, as well as
a group of trained personnel must be included in the plan.

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(2) A correct estimate of the damage to the aircraft is very important. This will help to
find, in the shortest time, the procedure to do the recovery operation.

B. Steps and Recommendations for an Efficient Aircraft Recovery

(1) Before you start a recovery operation, make sure of the correct safety precautions:

(a) Remove the aircraft batteries as quickly as possible. If it is not possible to

remove the batteries, disconnect and insulate the battery connectors. Refer to
Figure 1 for battery locations.

(b) Close oxygen bottle valve.

(c) If necessary, defuel the damaged aircraft to increase the speed of the recovery
operation.

NOTE: Follow the applicable local regulations concerning defueling.

(2) Examine how the accident occurred. This will help to make an estimate of the
damage that occurred to the aircraft.

(3) After a check of the obvious damage, examine the structural condition of the
aircraft.

(4) Look for possible damage to other areas of the aircraft. The following are
indications of damage:

(a) Bulges in the wing or fuselage skin panels, at structural joints, or heavy fittings,
are indications of internal damage.

(b) Rivets, bolts, or fasteners of all types that tilt, are cut or loose, are also
indications of damage.

(c) Torn, cracked or buckled fairings and other non−structural parts are causes for
close inspection of the structure below them. Think that damage to the
structure below these parts is possible until a close inspection shows
differently.

NOTE: A close inspection may not be possible if the aircraft is wheels−up.

(5) Make a list of missing or unserviceable items as you make an estimate of the
damage.

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(6)WARNING: FIND OUT IF THE STRUCTURE OF A DAMAGED AIRCRAFT CAN

HOLD ITS WEIGHT BEFORE YOU LOWER IT ON THE LANDING GEAR
FROM TRESTLES OR JACKS. IF YOU DO NOT DO THIS, YOU CAN
CAUSE INJURY TO PERSONS OR MORE DAMAGE TO THE
STRUCTURE.

Do an inspection of the aircraft structure before it comes off the trestles or jacks to
see if it is sufficiently strong to tow the aircraft on its landing gear. Lower the landing
gear only if:

(a) The IIC agrees.

(b) It is safe.

(c) No more damage will occur.

On Challenger 300 A/C

(7)CAUTION: DO NOT REMOVE FUEL, CARGO, OR THE ENGINES IF THEY KEEP
THE AIRCRAFT'S CENTER OF GRAVITY. THIS WILL PREVENT AN
OVERLOAD AT THE JACKING POINT.

The maximum weight of the aircraft on jacks are as follows:

NOTE: These weights are for a undamaged aircraft. The damage caused by an
accident may cause lower maximum permitted loads at the jacking points.
Refer to Figure 2 for jacking point locations. It can be better to put the
aircraft on trestles (assembled on−site) if there is structural damage.

(a) The maximum permitted weight of the aircraft on jacks is 30 650 lb

(13 902.6 kg).

(b) The maximum vertical jack loads for each jack location are as follow:
− 5 530 lb (2 505 kg) on the forward (nose) jacking point.
− 13 420 lb (6 090 kg) on each wing jacking point.

On Challenger 350 A/C

(8)CAUTION: DO NOT REMOVE FUEL, CARGO, OR THE ENGINES IF THEY KEEP
THE AIRCRAFT'S CENTER OF GRAVITY. THIS WILL PREVENT AN
OVERLOAD AT THE JACKING POINT.

The maximum weight of the aircraft on jacks are as follows:

NOTE: These weights are for a undamaged aircraft. The damage caused by an
accident may cause lower maximum permitted loads at the jacking points.
Refer to Figure 2 for jacking point locations. It can be better to put the
aircraft on trestles (assembled on−site) if there is structural damage.

(a) The maximum permitted weight of the aircraft on jacks is 31 420 lb

(14 251.87 kg).

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(b) The maximum vertical jack loads for each jack location are as follow:
− 5 327 lb (2 416kg) on the forward (nose) jacking point.
− 13 830 lb (6 273 kg) on each wing jacking point.

(9) If required, remove the baggage and cargo from the aircraft. The baggage
compartment door opens in and up.

(10) Examine the damage to the fuel system to find the best procedure to defuel the
aircraft. The single−point refuel/defuel adaptor, fuel lines and tanks can have
damage. Refer to Figure 3.

(11) Alternative procedures to defuel the aircraft are as follows:

NOTE: Follow the applicable local regulations concerning defueling.

(a) Suction defueling procedure.

1 The suction will break when one of the inlet points becomes open. This
procedure is slow and can mean that the fuel tank is not fully drained.

(b) Gravity defueling procedure.

WARNING: MAKE SURE THAT THE FUEL LEVEL IN THE TANK IS BELOW
THE OPENING OF THE GRAVITY FUELING ADAPTER. IF IT IS
NOT, FUEL WILL SPILL OUT OF THE TANK. THIS CAN CAUSE
INJURY TO PERSONS.

1 Fuel will come out from the tank(s) if the tank is higher than the gravity
fuel adaptor. To prevent this, make sure the fuel level in the tank is below
the gravity fueling adaptor before opening.

2 If available, use a gravity defueling adaptor to drain fuel from the

underwing fuel drains into approved containers. Use the suction
procedure at the single point refuel/defuel position. Use a suction hose in
the overwing and center tank gravity fueling adapter to remove the fuel if
it is not possible to remove it through the pressure refuel/defuel adaptor.

3 The quantity of fuel in the tank and the attitude of the aircraft will control
the amount of fuel you can remove.

(12)WARNING:BEFORE YOU REMOVE THE ENGINE, MAKE SURE THAT THE

AIRCRAFT IS STABLE. IF IT IS NOT STABLE, THE AIRCRAFT CAN
FALL AND CAUSE INJURY TO PERSONS AND DAMAGE TO THE
AIRCRAFT.

If the engines have to be removed to keep the weight and balance, make sure the
aircraft is level before the release of the load on the yokes. The aircraft must also
be stable to prevent movement because of an imbalance when an engine is
removed.

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

On Challenger 300 A/C

(13) In recovery operations, there are two basic situations that will occur:
− You can tow the aircraft on its landing gear.
− You must lift the aircraft on to a transport.

(a) If the landing gear stays serviceable after the aircraft has run off the runway or
taxiway, it may be possible to tow it by the main landing gear (Refer to Section
6, Figure 3).

(b) If the landing gear has flat tire(s), there are some tow limits. Refer to Figure 4
for towing restriction with flat tire.

(c) Make an estimate of the ground’s load−bearing capacity and the slope of the
terrain in the recovery area. Make the path to tow the aircraft as smooth as
possible if it does not have concrete or asphalt. Refer to Figure 5 for landing
gear measurements and tire pressures.

(d) If the landing gear is unserviceable, use pneumatic lifting bags or cranes and
slings to lift the aircraft. Then put it on dollies or on a flatbed trailer.

On Challenger 350 A/C

(14) In recovery operations, there are two basic situations that will occur:
− You can tow the aircraft on its landing gear.
− You must lift the aircraft on to a transport.

(a) If the landing gear stays serviceable after the aircraft has run off the runway or
taxiway, it may be possible to tow it by the main landing gear (Refer to Section
6, Figure 3).

(b) If the landing gear has flat tire(s), there are some tow limits. Refer to Figure 4
for towing restriction with flat tire.

(c) Make an estimate of the ground’s load−bearing capacity and the slope of the
terrain in the recovery area. Make the path to tow the aircraft as smooth as
possible if it does not have concrete or asphalt. Refer to Figure 6 for landing
gear measurements and tire pressures.

(d) If the landing gear is unserviceable, use pneumatic lifting bags or cranes and
slings to lift the aircraft. Then put it on dollies or on a flatbed trailer.

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(15)CAUTION:INFLATE THE FORWARD AND AFT LIFTING BAGS SUFFICIENTLY TO

KEEP THE AIRCRAFT STABLE. PUT THE BAGS IN AREAS OF
SUFFICIENT STRENGTH TO PREVENT MORE DAMAGE TO THE
AIRCRAFT.

Lift an aircraft that is on its fuselage with lifting bags put below each wing, the
forward fuselage and the aft fuselage. Refer to Figure 7 for the recommended
position of the pneumatic bags. Keep the aircraft stable with cables while you lift it,
or while it is on the pneumatic bags. Inflate the pneumatic bags sufficiently to allow
the installation of trestles or jacks at the nose, wings and the rear fuselage support.
Put the cables at the nose jack point and the rear mooring points.

(16) Use a nose jack and normal jacking procedures to lift a nose−down aircraft around
the MLG axis.

(17) When you use cranes and slings to lift the aircraft, you must make an estimate of
the damage to the structure. This will help to find how much damage has occurred
and the location of strong frames to transmit the sling loads. Because each aircraft
recovery operation is different, Bombardier cannot recommend special sling
locations. Generally, use the nose jacking point (FS319.75), the passenger door aft
frame and the forward engine mounts to lift the aircraft. Refer to Figure 8 for the
strongest frames locations.

(18) Lift the aircraft only in periods of very light or no winds. Because of the large areas
of wing, empennage and fuselage, small gusts of wind can cause large pendulum
movements.

(19) Make the aircraft stable during the lift. To help control its movements during the lift,
attach ropes to available strong points, such as the landing gear. If the engines are
removed, attach ropes to the forward engine mounts. During the lift, first level the
aircraft then lift it sufficiently high to put it on jacks or a flatbed trailer.

(20) If the aircraft cannot move on its landing gear, move it on a flatbed trailer. Refer to
Figure 8.

(21) Cranes and slings can be faster and easier to use in the recovery of the Bombardier
Challenger Series aircraft.

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

CAR0201_001

BATTERIES

A
Aircraft Batteries
Figure 1 (Sheet 1 of 2)

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Page 11
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 BD−100 AIRCRAFT RECOVERY MANUAL

FS227.50

BATTERY
COMPARTMENT
ACCESS PANEL

CAMLOCKS

MOUNTING
TRAY
CAR0201_002

STANDBY INSTRUMENT
BATTERY
HOLD−DOWN B
SCREW
Aircraft Batteries
Figure 1 (Sheet 2 of 2)

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 BD−100 AIRCRAFT RECOVERY MANUAL

FS319.75 FS636.12 FS826.60

A A C

FUSELAGE
SUPPORT
SHORING
BL161.94 BL161.94 BEAM
B A
A A

JACKING
POINT

NYLON
PLUG

JACK
PAD

CAR0202_001

REAR FUSELAGE
TYPICAL JACK SUPPORT

A B C
Structural Jacking Points and Adapters
Figure 2

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 BD−100 AIRCRAFT RECOVERY MANUAL

A C

RIGHT
MAIN TANK

B
C
LEFT
MAIN TANK

A
C

PRESSURE REFUEL/DEFUEL ADAPTOR

B
CAR0203_031

GRAVITY FILLER CAP WATER DRAIN VALVE

A C

Aircraft Defueling
Figure 3

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 BD−100 AIRCRAFT RECOVERY MANUAL

DISTANCE
ITEM MAIN GEAR TIRE FOOTPRINT PERMITTED PERMITTED PERMITTED NOSE WHEEL
REMARKS
NO. CONDITION EXAMPLES TO TAXI? TO TOW? TO TAXI ANGLE OF TURN
AND TOW
ONLY ONE
SEE NOTES
1 FLAT TIRE YES YES UNLIMITED NORMAL
1, 2, 5
(ANY TIRE)
TWO FLAT TIRES
SEE NOTES
2 (ONE ON EACH YES YES UNLIMITED NORMAL
1, 3, 4, 5
AXLES)
YES
TWO FLAT TIRES BOTH MAIN MINIMUM TO 10 DEGREES SEE NOTES
3 YES CLEAR MAXIMUM 1, 3, 4, 5, 6
(ON ONE AXLES) GEAR ONLY
(BRIDLE) RUNWAY
YES
THREE FLAT TIRES BOTH MAIN MINIMUM TO 10 DEGREES SEE NOTES
4 YES MAXIMUM 1, 3, 4, 5, 6
(ANY COMBINATION) GEAR ONLY CLEAR
(BRIDLE) RUNWAY
YES
BOTH MAIN MINIMUM TO 10 DEGREES SEE NOTES
5 FOUR FLAT TIRES YES GEAR ONLY CLEAR MAXIMUM 1, 3, 4, 5, 6
(BRIDLE) RUNWAY

NOSE GEAR CONDITION

SEE NOTES
6 ONE FLAT TIRE YES YES UNLIMITED UNLIMITED
1, 2, 4

YES
BOTH MAIN MINIMUM TO 10 DEGREES SEE NOTES
7 TWO FLAT TIRES YES CLEAR MAXIMUM 1, 2, 5, 6
GEAR ONLY
(BRIDLE) RUNWAY

CAUTION
TO TAXI OR TO TOW WITH TWO FLAT TIRES ON
SAME GEAR CAN RESULT IN WHEEL DAMAGE.

NOTES
1 Avoid sharp turns, abrupt starts and stops.
2 Maximum speed permitted to taxi or to tow aircraft = 5 mph (8kmh).
3 Maximum to taxi or to tow = 2 mph (3kmh).
4 After you clear the runway, or if additional tire fails, the airplane should be stopped
and serviceable wheel/tire assembly(ies) installed to obtain item number 2 or 6.
5 After any tire failure or excessive heat condition the affected wheel assembly
must be inspected per applicable Goodyear Overhaul Manaul prior to futher use.
CAR02_041

6 Under a multiple failed tire condition, the affected landing gear assemblies
and linkage must be inspected for possible structural damage.

Towing/Taxiing with Flat Tires

Figure 4

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 BD−100 AIRCRAFT RECOVERY MANUAL

11.6 in
(29.46 cm)

27 ft 9 in
(8.46 m)

10 ft 6 in
(3.20 m)

17.7 in
(45.00 cm)

CHALLENGER 300

MAXIMUM RAMP WEIGHT 39,000 (17,690 kg)

109−114 PSI UNLOADED
NOSE TIRE PRESSURE
CAR0205_001

113−119 PSI LOADED

151−159 PSI UNLOADED
MAIN GEAR TIRE PRESSURE
157−165 PSI LOADED

Landing Gear Measurements

Figure 5

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 BD−100 AIRCRAFT RECOVERY MANUAL

11.6 in
(29.46 cm)

27 ft 9 in
(8.46 m)

10 ft 6 in
(3.20 m)

17.7 in
(45.00 cm)

CHALLENGER 350

MAXIMUM RAMP WEIGHT

109−114 PSI UNLOADED
NOSE TIRE PRESSURE
BAR0205_001

113−119 PSI LOADED

151−159 PSI UNLOADED
MAIN GEAR TIRE PRESSURE
157−165 PSI LOADED

Challenger 350 − Landing Gear Measurements

Figure 6

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 BD−100 AIRCRAFT RECOVERY MANUAL

CAR0206_001

AIR SUPPLY

Lifting with Pneumatic Bags

Figure 7

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 BD−100 AIRCRAFT RECOVERY MANUAL

SLING ASSEMBLY
12 in (305 mm)
WIDE STRAP

SLING ASSEMBLY
12 in (305 mm)
WIDE STRAP

A B

FS375.00
FS319.75

NOTE
12 in (305 mm) wide strap preferred,
CAR0207_001

10 in (254 mm) wide strap minimum,

check sling load rating and
use multiple slings to carry
load safely.

Aircraft Recovery with Cranes and Slings

Figure 8 (Sheet 1 of 2)

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Page 19
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 BD−100 AIRCRAFT RECOVERY MANUAL

WING JACK POINT BEAM REAR FUSELAGE SUPPORT

A B

FORWARD ENGINE
MOUNT (FS724.70)

C
CAR0207_002

Aircraft Recovery with Cranes and Slings

Figure 8 (Sheet 2 of 2)

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 BD−100 AIRCRAFT RECOVERY MANUAL

4. Terrain Consideration

A. General

(1) Type of terrain, weather conditions and structural damage to the aircraft are factors
to find the bearing area necessary to lift and move the aircraft. Get an experienced
civil engineer or earthworks contractor to make an assessment of the terrain
surface conditions, bearing loads and areas.

B. Factors to Find the Most Practical Recovery Plan

(1) Make an estimate of the general terrain to find the best routing to tow the aircraft.
Structural damage to the aircraft can occur if it moves over terrain that is not
smooth. If necessary, grade the proposed tow routing to give a smooth surface for
the aircraft and tow vehicle(s).

(2) Make an estimate of how hard and smooth the surface is. Also, the possible effect
of rainfall and drainage on the load−bearing capacity of the terrain. Find the safe
bearing load and surface area of the terrain. The ground must have the same
condition for a depth of 8 in (20.3 mm), because the force necessary to tow an
aircraft changes as a function of the strength of the terrain.

(3) The type of terrain shows the applicable procedure to lift the aircraft:

(a) Refer to Figure 2 for the use of jacks .

(b) Refer to Figure 7 for the use of pneumatic bags.

(c) Refer to Figure 8 for the use of mobile cranes and slings.

C. Ground Conditions

(1) Ground conditions are one of the primary factors in aircraft recovery operations.
Ground conditions have an effect on decisions to tow the aircraft, put tethers in the
ground, or set shoring (cribbing). From the results of ground tests, the recovery
team makes decisions about reinforcement of the terrain and the shoring (cribbing)
base.

(2) The California Bearing Ratio (CBR) is known as the standard for different ground
conditions.

(a) For ground conditions that are related to shoring the aircraft (Refer to Table 1).

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

(b) For the related bearing strength of different ground conditions (Refer to Table
2).

Table 1 − Ground Conditions To Shore the Aircraft

Surface Type Shoring (Cribbing) Necessary For Loads Shoring (Cribbing) Necessary For Loads
That Roll To Jack

Max Allowable Minimum Contact Max Allowable Minimum Contact

Contact Area Needed Contact Area Needed
Pressure Pressure

psi kPa Each Each psi kPa Each Each

2 000 141.61 2 000 141.61
lb/in² kg/cm² lb/in² kg/cm²

Soft Wet 18.0 124.0 111.0 7.8 8.0 55.0 2 500.0 175.77
Clay or
Wet
Organic
Terrain

Loose 65.0 448.0 31.0 2.18 35.0 241.0 571.0 40.15

Sand or
Sandy
Terrain

Sand with 100.0 690.0 20.0 1.41 50.0 345.0 400.0 28.12
Clay

Well 180.0 1 241. 11.0 0.77 85.0 586.0 235.0 16.52

Graded 0
Sand and
Medium
Clay

Sandy 300.0 2 6.7 0.47 165.0 1 138. 121.0 8.51

Gravel, 068.0 0
Clay−Gravel
or Dry Clay

Compacted N/A N/A N/A N/A 200.0 1 379. 100.0 7.03

Sandy 0
Clay−Gravel

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

Table 2 − California Bearing Ratio (CBR) Soil Bearing Strength

Surface Type Safe Bearing Load Approximate Bearing Area Necessary

10 000 lb 5 000 kg

psi kPa in² ft² m²

Slate or Rock 230.0 1 586.0 44.0 0.31 0.062

Concrete 156.0 1 076.0 64.0 0.54 0.091

Hard Pan and Small 138.0 951.0 72.5 0.50 0.103

Gravel or Sand

Small Gravel and Sand 100.0 689.0 100.0 0.69 0.142

Gravel, Course Sand or 62.0 427.0 161.0 1.12 0.229

Medium Clay

Loose Sand and Gravel 42.0 290.0 238.0 1.65 0.340

Mixture

Medium stiff Clay 35.0 241.0 286.0 1.98 0.407

Loose Sand 30.0 207.0 333.0 2.31 0.474

Soft Clay or Earth 15.5 107.0 645.0 4.48 0.917

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

AIRCRAFT - GENERAL

1. Model Designation and Type

A. The Bombardier Challenger Series Business Jet is made by Bombardier Aerospace. The
aircraft is swept−wing monoplane with pressurized cabin, operated by two crew.

B. The aircraft has two Honeywell AS907 Turbofan engines.

2. Aircraft Dimensions

On Challenger 300 A/C

A. Refer to Figure 1 for all basic dimensions, including ground clearances.

On Challenger 350 A/C

B. Refer to Figure 2 for all basic dimensions, including ground clearances.

3. Dangerous Areas

A. Persons who do aircraft recovery operations must know of the dangerous areas around
the engines and the APU. Refer to Figure 3.

4. Doors

A. The aircraft has the doors that follow:

− Passenger/crew entrance door,
− Baggage compartment door on the left side of the aircraft,
− Aft equipment compartment door at the bottom of the rear fuselage,
− Different small service and access doors,
− Overwing emergency exit door located on the right side of the passenger
compartment.

NOTE: The entrance stairs attach to the passenger/crew door.

5. Composite Materials

A. Composite materials such as: Kevlar, Graphite, Fiberglass and Fiberlam are used in
many components of the Bombardier Challenger Series aircraft. Refer to Figure 4 for the
locations of the composite materials.

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

6. Interior Configurations

A. Internal configurations will change according to customer options installed at the

completion centers.

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 BD−100 AIRCRAFT RECOVERY MANUAL

OVER−WING 11 ft 11 in
EMERGENCY EXIT (3.63 m)
1 ft 8 in x 3 ft 14 ft 11 in 7 ft 11 in
(0.51 m x 0.76 m) (4.55 m) (2.41 m)

23 ft 9 in
(7.24 m)
7 ft 8 in
(2.34 m)
3 ft
28 ft 1 in (0.91 m)
(8.56 m)

12 ft
(3.66 m) 3 ft 9 in
(1.14 m)

NOTES
01 Measurement at manufacturer
empty weight.
10 ft 6 in
(3.20 m)
63 ft 10 in
(19.46 m) 01 20 ft
(6.10 m)
6 ft 2 in 2 ft
(1.88 m) 2 ft 6 in (0.61 m)
(0.76 m)

PASSENGER COMPARTMENT
DIMENSIONS
LENGTH 28 ft 7 in 8.71 m
4 ft 3 in 5 ft 4 in
WIDTH (1.30 m) (1.63 m)
(FLOOR LINE) 5 ft 1 in 1.55 m
27 ft 9 in
WIDTH (8.46 m)
CENTERLINE 7 ft 2 in 2.18 m
61 ft 1 in
CAR0301_001

HEIGHT 6 ft 1 in 1.85 m (18.62 m) 68 ft 9 in

VOLUME 896 ft 3 25.37 m 3
(20.96 m)
FLOOR AREA 146 ft 2 13.56 m 2

Challenger 300 − Aircraft Basic Dimensions & Ground Clearances

Figure 1

EFFECTIVITY: ALL
Page 3
SECTION 03 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

14 ft 11 in 11 ft 11 in 7 ft 11 in
(3.63 m)
7 ft 8 in (4.55 m) (2.41 m)
(2.34 m)

23 ft 9 in
(7.24 m)

2.0°

30 ft 8 in
3 ft
(9.35 m)
(0.91 m)

3 ft 9 in
(1.14 m)
12 ft
(3.66 m) NOTES
01 Measurement at manufacturer
empty weight.

10 ft 6 in
(3.20 m)
69 ft
(21.03 m) 01 20 ft
(6.10 m)
2 ft
2 ft 6 in (0.61 m)
(0.76 m)

PASSENGER COMPARTMENT
DIMENSIONS 3.5°
LENGTH 28 ft 7 in 8.71 m
WIDTH 5 ft 1 in 1.55 m 4 ft 3 in 5 ft 4 in
(FLOOR LINE) (1.30 m) (1.63 m)
WIDTH 27 ft 9 in
7 ft 2 in 2.18 m
CENTERLINE (8.46 m)
BAR0301_001

HEIGHT 6 ft 1 in 1.85 m 61 ft 1 in
VOLUME 896 ft 3 25.37 m 3 (18.62 m)
68 ft 9 in
FLOOR AREA 146 ft 2 13.56 m 2
(20.96 m)

Challenger 350 − Aircraft Basic Dimensions & Ground Clearances

Figure 2

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 BD−100 AIRCRAFT RECOVERY MANUAL

DISTANCE TO AIRPLANE CENTERLINE

FEET 40 30 20 10 C
L 10 20 30 40

(6.10)
(9.14)

(3.05)
(12.19)

(6.10)

(9.14)
(3.05)
0

(12.19)
(METERS)

IDLE KEEP OUT

RADIUS ZONE
5 ft (1.52 m)

AXIAL DISTANCE
FEET (METERS)
01
0 2 ft
(0.61 m) SIDE ACCESS
6 ft CORRIDOR
12.5 (3.81) (1.83 m)

25 (7.62)
JET EXHAUST KEEP OUT ZONES

37.5 (11.43)
SINGLE ENGINE OPERATION

50 (15.24)
GROUND IDLE THRUST

62.5 (19.05)

31 mph
75 (22.86)
(49.89 kph)

87.5 (26.67) 20 mph

(32.19 kph)

100 (30.48)
NOTE
112.5 (34.29) 01 Access in the side
CAR0302_001

corridor is only
125 (38.10) permitted during
ground idle.

Dangerous Areas − Engine Intake and Exhaust

Figure 3 (Sheet 1 of 4)

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Page 5
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 BD−100 AIRCRAFT RECOVERY MANUAL

DISTANCE TO AIRPLANE CENTERLINE

FEET 40 30 20 10 C
L 10 20 30 40

(6.10)
(9.14)

(3.05)
(12.19)

(6.10)

(9.14)
(3.05)
0

(12.19)
(METERS)

RADIUS TAKE−OFF POWER

15 ft (4.57 m) KEEP OUT ZONE

AXIAL DISTANCE
FEET (METERS) 01

0
SIDE ACCESS
6 ft CORRIDOR
12.5 (3.81) (1.83 m)

25 (7.62)
NOTE
JET EXHAUST KEEP OUT ZONES

37.5 (11.43) 01 Access in the

SINGLE ENGINE OPERATION

side corridor is
prohibited above
50 (15.24) idle power.
TAKE−OFF THRUST

62.5 (19.05)

164 mph
75 (22.86)
(263.93 kph)

87.5 (26.67)
109 mph
(175.41 kph)
100 (30.48)

112.5 (34.29) 55 mph

CAR0302_002

(88.51 kph)
125 (38.10)
TO 195 ft
(59.44 m)

Dangerous Areas − Engine Intake and Exhaust

Figure 3 (Sheet 2 of 4)

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Page 6
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 BD−100 AIRCRAFT RECOVERY MANUAL

DISTANCE TO AIRPLANE CENTERLINE

FEET 40 30 20 10 C
L 10 20 30 40

(6.10)
(9.14)

(3.05)
(12.19)

(6.10)

(9.14)
(3.05)
0

(12.19)
(METERS)

RADIUS IDLE KEEP OUT

5 ft (1.52 m) ZONE

AXIAL DISTANCE
FEET (METERS)
01
0 2 ft
(0.61 m) SIDE ACCESS
6 ft CORRIDOR
12.5 (3.81) (1.83 m)

25 (7.62)
JET EXHAUST KEEP OUT ZONES

37.5 (11.43)
TWO ENGINE OPERATION

50 (15.24)
GROUND IDLE THRUST

62.5 (19.05) 31 mph

(49.89 kph)
75 (22.86)

87.5 (26.67) 20 mph

(32.19 kph)
100 (30.48)
NOTE
112.5 (34.29) 01 Access in the side
CAR0302_003

corridor is only
permitted during
125 (38.10)
ground idle.

Dangerous Areas − Engine Intake and Exhaust

Figure 3 (Sheet 3 of 4)

EFFECTIVITY: ALL
Page 7
SECTION 03 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

DISTANCE TO AIRPLANE CENTERLINE

FEET 40 30 20 10 C
L 10 20 30 40

(6.10)
(9.14)

(3.05)
(12.19)

(6.10)

(9.14)
(3.05)
0

(12.19)
(METERS)

RADIUS TAKE−OFF POWER

15 ft (4.57 m) KEEP OUT ZONES

AXIAL DISTANCE
FEET (METERS) 01

0
SIDE ACCESS
CORRIDOR
12.5 (3.81)

25 (7.62)
NOTE
JET EXHAUST KEEP OUT ZONES

37.5 (11.43) 01 Access in the

side corridor is
TWO ENGINE OPERATION

prohibited above
50 (15.24) idle power.
TAKE−OFF THRUST

62.5 (19.05) 164 mph

(263.93 kph)
75 (22.86)

87.5 (26.67)

109 mph
100 (30.48) (175.41 kph)

112.5 (34.29) 55 mph

(88.51 kph)
CAR0302_004

125 (38.10)
TO 195 ft
(59.44 m)

Dangerous Areas − Engine Intake and Exhaust

Figure 3 (Sheet 4 of 4)

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Page 8
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 BD−100 AIRCRAFT RECOVERY MANUAL

V−STAB AFT
BULLET FAIRING,
V−STAB FORWARD AND AFT CONE ELEVATORS
BULLET FAIRING
LH AND RH FORWARD
ACCESS PANELS

VERTICAL
STABILIZER
WINGLETS LEADING EDGE

MULTI−FUNCTION DORSAL HORIZONTAL

SPOILERS FAIRING STABILIZER

GROUND RUDDER
SPOILERS
TAILCONE

CABIN THRUST REVERSER

FLOOR PIVOT DOORS
OUTER SKIN

ENGINE
COWLS
BIRD
FLAPS
STRIKE
BARRIER AILERON

AFT
NLG
DOOR STAIRS
RADOME FLAP
NOSE LANDING FAIRINGS
GEAR DOORS
(LEFT AND RIGHT) LEGEND
WHEEL
BINS KEVLAR
GRAPHITE
FIBERGLASS
HYBRID
CAR05_101

BELLY OVER−WING
FAIRINGS FAIRINGS

Composite Materials
Figure 4

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

EMERGENCY INFORMATION

1. Emergency Access

A. Passenger Door

(1) The Passenger Entrance Door is on the left side of the aircraft, just after the flight
compartment. The door serves as a Type I Emergency Exit, Refer to Figure 1.

(2) Dimensions:
− Height 6 ft 2 in (1.88 m)
− Width 2 ft 6 in (0.76 m)
− Height to the sill (one step below the floor line) 4 ft 3 in (1.30 m).

(3) To Open the Passenger Door from the external side do the following:

WARNING: FULLY RELEASE THE CABIN PRESSURE FROM THE AIRCRAFT

BEFORE YOU TRY TO OPEN THE DOORS. IF YOU DO NOT DO THIS,
THE CABIN PRESSURE CAN DECREASE SUDDENLY. THIS CAN
CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

WARNING: MAKE SURE THAT THE AREA OUTBOARD OF THE PASSENGER

DOOR IS CLEAR BEFORE YOU OPEN THE DOOR. IF YOU DO NOT
DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT AND INJURY
TO PERSONNEL.

(a) Pull the external door handle outboard and to its top released position.

NOTE: The external door handle will not release if the cabin pressure has
not lowered to the correct pressure.

(b) Let the passenger door drop by gravity to the full open position.

NOTE: The passenger door actuator will control the decent of the door.

The passenger door will open in less than 9 seconds.

The passenger door telescopic struts will stop the door at the correct
position.

EFFECTIVITY: ALL
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 BD−100 AIRCRAFT RECOVERY MANUAL

CABLE
ACTUATOR B
PASSENGER
DOOR
ACTUATOR WARNING
CABIN MAY BE PRESSURIZED.
PASSENGER
DOOR PASSENGER
DOOR KEYLOCK
EXTERNAL
HANDRAIL CYLINDER
SWITCH

EXTERNAL
SWITCH

EXTERNAL
HANDLE

SPRING−LOADED
EXTERNAL FINGER FLAP
SWITCH
ACCESS
PANEL B
CAR04_001

PASSENGER DOOR

Passenger/Crew Door
Figure 1

EFFECTIVITY: ALL
Page 2
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

B. Overwing Emergency−Exit Door

(1) The overwing emergency−exit door is on the right side of the passenger
compartment. It opens in and operates from the internal or external side the aircraft.
The door serves as a Type III Emergency Exit. Refer to Figure 2.

(2) Dimensions:
− Height 3 ft (0.91 m)
− Width 1 ft 8 in (0.52 m)

(3) To open the overwing emergency−exit door from the external side do the following:

(a) Apply hand pressure on the outside push plate and push the overwing−exit
door into the aircraft.

(4) To open the overwing emergency−exit door from the inside do as follows:

(a) Pull the upper latch handle marked EXIT PULL.

(b) Hold the overwing emergency−exit door at the lower hand grip and the upper
latch handle.

(c) Tilt the overwing emergency−exit door inboard and lift the door out of the
bottom hooks and the pin fittings.

EFFECTIVITY: ALL
Page 3
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

PUSH IN FLAP
PUSH DOOR INWARD

QUICK−RELEASE
LATCH MECHANISM

HAND GRIP

HOOK FITTINGS
CAR0402_001

B
A

Overwing Emergency−Exit Door

Figure 2

EFFECTIVITY: ALL
Page 4
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

C. Baggage Door

(1) The baggage compartment door is a plug−type access door on the left hand side of
the aft fuselage section, forward of the aft pressure bulkhead. Refer to Figure 3.

(2) Dimensions:

− Height 2 ft 6 in (0.76 m)
− Width 2 ft (0.61 m)
− Height to sill floor line 5 ft 4 in (1.62 m).

(3) To open the baggage compartment door with the external handle do as follows:

(a) Push the external handle trigger marked PUSH to let the handle move out.

(b) Turn the external handle counterclockwise to the UNLOCKED position.

(c) Push the door in and up on its tracks until the rollers touch the track stops and
the opening is clear.

(4) To open the baggage compartment door with the internal handle do as follows:

(a) Pull the knob and turn the handle clockwise to release the latch.

(b) Pull the door in and up on the tracks until the rollers contact the track stops
and the opening is clear.

EFFECTIVITY: ALL
Page 5
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

EXTERNAL
HANDLE

A
EXTERNAL
HANDLE
TRIGGER

INTERNAL
HANDLE
CAR0403_001

Baggage Door
Figure 3

EFFECTIVITY: ALL
Page 6
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

D. Aft Equipment−Compartment Door

(1) The aft equipment compartment of the Bombardier Challenger 300 Business Jet is
a non−pressurized area. Access to the aft equipment compartment is through a
door in the aft fuselage fairing. The door has a hinge at the forward end. It opens
down and forward. Refer to Figure 4.

(2) To open the aft equipment−compartment door do as follows:

(a) Push the external handle trigger marked PUSH to let the door handle move
out.

(b) Hold the door, turn the handle clockwise through 90°, and open the door.

EFFECTIVITY: ALL
Page 7
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

DOOR
HINGES

AFT EQUIPMENT
DOOR STOP COMPARTMENT
FITTINGS DOOR

PRESSURE LATCH

EXTERNAL
HANDLE AND
TRIGGER
ROLLER
ARMS
A B
CAR0404_001

Aft Equipment−Compartment Door

Figure 4

EFFECTIVITY: ALL
Page 8
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

E. Service Doors and Panels

(1) The service doors and panels give access to equipment and systems all through
the fuselage. The service doors and panels are made from light alloy or graphite
with Nomex honeycomb material. Refer to Figure 5.

EFFECTIVITY: ALL
Page 9
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

OXYGEN FILL−
AND−INDICATOR
DOOR

APU ACCESS
PANEL
REFUEL/DEFUEL
CONTROL−PANEL
DOOR
GROUND−POWER
ACCESS DOOR AFT ACCESS
PANEL
FORWARD ACCESS
PANEL
LAVATORY−
WASTE SERVICE
DOOR

REFUEL/DEFUEL
FORWARD ACCESS DOOR
PANEL
AFT ACCESS
PANEL

COMMUNICATION
DOOR

OUTFLOW−VALVE
ACCESS DOOR

BATTERY
ACCESS
CAR0405_051

DOOR GROUND−AIR
SERVICING−
CONNECTION DOOR

Service Doors and Panels

Figure 5

EFFECTIVITY: ALL
Page 10
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

F. Windshields and Windows

(1) The flight compartment has two windshields and two side windows. The Passenger
Compartment has six windows maximum on each side. On the right side of the
fuselage, one of the windows is in the Overwing Emergency−Exit Door. All of the
other passenger windows attach permanently to their surround structure. Refer to
Figure 6.

(2) The windshields are made with layers of acrylic, polyvinyl butyl (PVB) and glass.

(3) The side windows are made with layers of acrylic and PVB.

WARNING: DO NOT TRY TO CHOP THROUGH THE WINDOWS. GO THROUGH

THE EMERGENCY BREAK-IN ZONE. IF YOU DO NOT DO THIS, YOU
CAN CAUSE INJURY TO PERSONS.

EFFECTIVITY: ALL
Page 11
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

PASSENGER
SIDE WINDOW COMPARTMENT
WINDOWS

WINDSHIELD

CAR0406_061

Windows
Figure 6

EFFECTIVITY: ALL
Page 12
SECTION 04 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

FIRE FIGHTING

1. General

WARNING: BE VERY CAREFUL NEAR THE OXYGEN BOTTLES IN THE LAVATORY

SECTION. THE STANDARD OXYGEN BOTTLE HAS A CAPACITY OF 77 FT³
(2.18M³) AND THE OPTIONAL OXYGEN BOTTLE HAS A CAPACITY OF 115 FT³
(3.26M³). IF THESE BOTTLES ARE DAMAGED AND RELEASE THE OXYGEN,
AN EXPLOSION CAN OCCUR. THIS CAN CAUSE INJURY TO PERSONS AND
DAMAGE TO EQUIPMENT.

WARNING: MAKE SURE THAT YOU DISCONNECT THE ELECTRICAL POWER TO THE
ENGINE FIRE-EXTINGUISHER BOTTLES. THE EXTINGUISHER BOTTLES
HAVE PYROTECHNIC SQUIBS. IF YOU DO NOT DISCONNECT THE
ELECTRICAL POWER, THERE CAN BE AN EXPLOSION. THIS CAN CAUSE
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

A. The sentences below give the classes used for fire fighting.
− For brake and wheel fires use only dry powder or class D fire extinguishers.
− For all other parts of the aircraft use class B or C fire extinguishers.

Aerodrome Category for Rescue and Fire Fighting

Category Regulation

International Civil Aviation 4 ICAO Annex 14 −

Organization (ICAO) Aerodrome

Federal Aviation A FAR 139.315

Administration (FAA)

Transport Canada (TC) 4 CAR 303 Supart 3

B. Refer to Figure 1 for typical fire−fighting with small equipment.

EFFECTIVITY: ALL
Page 1
SECTION 05 Jan 31/2013
 BD−100 AIRCRAFT RECOVERY MANUAL

INTERNAL ENGINE FIRE EXHAUST NOZZLE FIRE

A B

CAR05_001

AFT EQUIPMENT COMPARTMENT FIRE BRAKE FIRE

C D
Fire Fighting
Figure 1 (Sheet 1 of 2)

EFFECTIVITY: ALL
Page 2
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

E
APU
ACCESS
PANEL USE SCREWDRIVER (PHILIPS)
TO RELEASE QUICK RELEASE
FASTENER AND ACCESS PANEL

F
F

INSERT FIRE EXTINGUISHING

NOZZLE INTO APU ENCLOSURE

APU COMPARTMENT FIRE

CAR05_002

Fire Fighting
Figure 1 (Sheet 2 of 2)

EFFECTIVITY: ALL
Page 3
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

2. On−Board Fire−Fighting Equipment

A. The extinguishing system supplies fire extinguishant to the engines and auxiliary power
unit (APU) through a distribution system controlled in the flight compartment. The
extinguishing system also has a portable fire extinguisher for manual operation in the
aircraft. Refer to Figure 2.

B. The Bombardier Challenger 300 has two identical crew−operated in−flight fire−fighting
systems. Each system has a spherical fire bottle of Halon 1301 located in the aircraft aft
section. The bottles are pressurized with dry nitrogen at a pressure of 600 psi
(4 137 kPa) to push the Halon. There are three pyrotechnic squibs to discharge and
direct the Halon. One or both systems can be directed at No 1 or No 2 engine. Only No.
2 system can be directed at the APU.

C. There is a portable fire extinguisher on the flight compartment bulkhead behind the
co−pilot’s seat. The fire extinguisher contains 3.5 pounds (1.59 kg) of Halon 1211.

EFFECTIVITY: ALL
Page 4
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

APU DISCHARGE LINE APU FORWARD

FIREWALL

A
LEFT / RIGHT
ENGINE
DISCHARGE TEE

B A
PYLON
FIREWALL

TO LEFT A
ENGINE
DISCHARGE TEE DISCHARGE LINE
TO LEFT ENGINE
TWO−WAY
CHECK VALVES

CONTAINER NO. 1
CAP DISCHARGE LINE
TO RIGHT ENGINE
DISCHARGE
CARTRIDGE
DISCHARGE
HEADS
DISCHARGE
CARTRIDGE TO RIGHT
ENGINE
CONTAINER NO. 2 DISCHARGE TEE
DISCHARGE
CAR05_021

HEADS
B DISCHARGE
CARTRIDGES DISCHARGE LINE TO APU

On−Board Fire−Fighting Equipment

Figure 2 (Sheet 1 of 2)

EFFECTIVITY: ALL
Page 5
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

PORTABLE FIRE
EXTINGUISHER

CAR0502_022

On−Board Fire−Fighting Equipment

Figure 2 (Sheet 2 of 2)

EFFECTIVITY: ALL
Page 6
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

3. Engine/APU Fire Controls

On Challenger 300 A/C

A. The control and monitor panels are in the flight compartment. Refer to Figure 3
and Figure 4.

On Challenger 350 A/C

B. The control and monitor panels are in the flight compartment. Refer to Figure 3
and Figure 5.

C. To stop the engines do the following:

− On the Center Pedestal set the LEFT ENGINE RUN and/or RIGHT ENGINE RUN
switch to OFF.

− Push the LEFT ENG FIRE and/or RIGHT ENG FIRE pushbutton annunciator(s)
(PBA) in the flight compartment panel. This shuts off the applicable engine fuel,
hydraulics, electrical systems and bleed air.

D. To stop the APU:

− On the ground, the APU should stop automatically if a fire occurs. If it does not or if
you need to manually stop the APU, do the following:

− On the Center Pedestal set the APU RUN switch to OFF.

− Push the APU FIRE PBA in the flight compartment panel. This shuts off the APU fuel
and electrical system.

EFFECTIVITY: ALL
Page 7
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

ENGINE
L ENG FIRE APU FIRE R ENG FIRE

FIRE FIRE FIRE

1 FIRE EXT 2 EVENT

ARMED ARMED

AUTO
AUTO APR SYNC MACH HOLD
N1
OFF OFF N2 ON

L STARTER R STARTER
OFF OFF
IGNITION
CRANK START CRANK START

ON
CAR0503_001

Engines/APU Fire Controls

Figure 3

EFFECTIVITY: ALL
Page 8
SECTION 05 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

EFFECTIVITY
01 A/C 20001 to 20124 Pre IFIS STC
A ST01732LA−D or A/C 20003 to 20124
Pre SB100−46−06
02 A/C 20001 to 20124 Post IFIS STC
ST01732LA−D or A/C 20003 to 20124
Post SB100−46−06
B
03 A/C 20125 to 20500

AIR CONDITION / BLEED PRESSURIZATION

FUEL CONTROL CONTROL PANEL CONTROL PANEL
PANEL

FUEL AIR COND BLEED PRESSURIZATION

GRAVITY COCKPIT CABIN MAN RATE
MAN TEMP MANUAL LNDG ALT
XFLOW ALT SOURCE
SELECT
ON ON FMS
MAN

L PUMP R PUMP HOT COLD HOT DN UP

COLD
AUTO AUTO NORM EMER DEPRESS DITCHING
XFER RAM AIR
ON OFF ON OFF OFF PACK ONLY CONTROL
TRIM AIR
ON ONLY ON ON
DISPLAY
L BLEED X BLEED R BLEED UNIT
ANTI−ICE OFF

APU
OFF

CONTROL ON

PANEL
ANTI−ICE
WING
SOURCE WING PROBES
NORM L R
FROM FROM
L R
ON OFF OFF

L ENG R
WSHLD/WINDOW
L R
LIGHTING
ON ON OFF OFF CONTROL
CONTROL PANEL
ELECTRICAL
DISPLAY L BATT EXT PWR R BATT
AVAIL

UNIT OFF
ON
OFF

TUNE STBY LIGHTING

(OPTIONAL) LEFT
DISPLAYS MFD
ONLY
NORM
CDU
ONLY
RIGHT
DISPLAYS
INST
BUS TIE
WING
INSP NAV STROBE
SMKG/
BELTS B
NORM NORM B E
COM 1 OFF C
PFD MFD 121.50 MFD PFD L
REV REV REV REV L ESS R ESS N T
S
OFF OFF OFF OFF
ATT/HDG AIR DATA L AUX L MAIN R MAIN R AUX
EMER LTS LANDING
NORM NORM L R
ON N LDG/TAXI
1 2 1 2 L GEN APU GEN R GEN A T
R A
M X
OFF ON OFF
I
OFF OFF OFF OFF
CAR0504_001

REVERSION ELECTRICAL
SELECT CONTROL
PANEL 01 A PANEL

Center Pedestal − Component Location

Figure 4 (Sheet 1 of 5)

EFFECTIVITY: ALL
Page 9
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

AIR CONDITION / BLEED PRESSURIZATION

FUEL CONTROL CONTROL PANEL CONTROL PANEL
PANEL

FUEL AIR COND BLEED PRESSURIZATION

GRAVITY COCKPIT CABIN MAN RATE
MAN TEMP MANUAL LNDG ALT
XFLOW ALT SOURCE
SELECT
ON ON FMS
MAN

L PUMP R PUMP HOT COLD HOT DN UP

COLD
AUTO AUTO NORM EMER DEPRESS DITCHING
XFER RAM AIR
ON OFF ON OFF OFF PACK ONLY CONTROL
TRIM AIR
ON ONLY ON ON
DISPLAY
L BLEED X BLEED R BLEED UNIT
ANTI−ICE OFF

APU
OFF

CONTROL ON

PANEL
ANTI−ICE
WING
SOURCE WING PROBES
NORM L R
FROM FROM
L R
ON OFF OFF

L ENG R
WSHLD/WINDOW
L R
CURSOR
ON ON OFF OFF
CLR
CONTROL
CONTROL PANEL
ELECTRICAL
DISPLAY L BATT EXT PWR R BATT
AVAIL

UNIT OFF
ON
OFF

STBY
(OPTIONAL) UPR
MENU
ESC STAT MEM 1 CHART JSTK INST
BUS TIE
UPR
MENU
ESC STAT MEM 1 CHART JSTK

MENU DATA MENU DATA

LWR
ADV
MEM 2 OFF LWR MEM 2
MENU ADV
MENU
S
PU H L ESS R ESS S
PU H
ZOOM ZOOM
S

E
MEM 3
S

E
L EC
− + L EC MEM 3
− +
L AUX L MAIN R MAIN R AUX
UPR UPR
CKLST SKIP A/ICE ECS ELEC FLT CKLST SKIP A/ICE ECS ELEC FLT
FRMT FRMT
L GEN APU GEN R GEN
LWR LWR
FRMT TFC TR/WX FUEL HYD SUMRY TFC TR/WX FUEL HYD SUMRY
OFF ON OFF FRMT

CAS ENTER CAS ENTER

CURSOR ELECTRICAL
CONTROL CONTROL
PANEL PANEL

02
03
A
CAR0504_002

Center Pedestal − Component Location

Figure 4 (Sheet 2 of 5)

EFFECTIVITY: ALL
Page 10
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FLIGHT HYDRAULIC
L SOV R SOV
SPOILERS

CLOSED CLOSED
STOW
APR APR
FLIGHT−SPOILER 1/4 L PUMP R PUMP
TO TO AUTO AUTO HYDRAULIC
CONTROL LEVER OFF ON OFF ON

1/2
R
E
CLB CLB
PTU
AUTO
CONTROL PANEL
T OFF ON
R
A
3/4 C AUX
ALTN PUMP
T IDLE IDLE FLAPS AUTO
REV REV OFF
MAX
ON
EMER
TO/GA TO/GA

MAX MAX
REV REV
FLAP LEVER
PITCH DISC
PULL & TURN
L ENGINE R ENGINE
RUN RUN

THROTTLE P
FLAPS
OFF OFF
I
QUADRANT T
C GND/ROLL
H

D
GND SPOILERS
AUTO
ROLL SPOILERS SPOILERS
I
S
OFF MANUAL CONTROL−PANEL
PITCH C
ARM
OFF

DISCONNECT
HANDLE CAS
L R

TRIM
RUD
L R CKLST SKIP

TRIM / STALL STAB

PRI
FRMT TFC TR/WX ENTER SUMRY

CONTROL PANEL OFF

A/ICE ECS ELEC FLT FUEL HYD
SEC
CURSOR
ENGINE

STALL
L ENG FIRE APU R ENG FIRE
CONTROL PANEL
PUSHER
FIRE FIRE FIRE
PARK/EMER PARK/EMER
OFF BRAKE BRAKE
1 FIRE EXT 2 EVENT
ENGINE
EMERGENCY/ ARMED ARMED CONTROL PANEL
SYSTEMS TEST
PARKING BRAKE OFF
ANNUN A
AUTO APR AUTO SYNC
N1
MACH HOLD

HANDLE ANNUN B
OFF OFF N2 ON

PUSH
TO
TAWS TEST PROBES
L STARTER R STARTER

SYSTEMS FIRE DET STALL/RUD LIM

ICE DET
CRANK
OFF
START
IGNITION
CRANK
OFF

START
LANDING−GEAR
TEST/RESET ELT ON MANUAL−RELEASE
ON
CONTROL−PANEL ARM
HANDLE
RESET
APU
EMERGENCY COCKPIT VOICE
RECORDER
HOLD

LOCATOR 5 SEC

OFF
RUN
START LG
PUSH
TO PULL
TEST HEADSET ERASE STOW
TRANSMITTER
(ELT) PANEL APU
COCKPIT VOICE CABIN OXYGEN
CONTROL PANEL
PAX
RECORDER (CVR) DC PWR AC PWR CAB LTS ENT LTS THERAPEUTIC AUTO
DEPLOY
OFF
CONTROL PANEL OFF OFF ON ON
ON

CABIN CONTROL PAX OXYGEN

CAR0504_003

PANEL CONTROL−PANEL

01 B

Center Pedestal − Component Location

Figure 4 (Sheet 3 of 5)

EFFECTIVITY: ALL
Page 11
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FLIGHT HYDRAULIC
L SOV R SOV
SPOILERS

CLOSED CLOSED
STOW
APR APR
FLIGHT−SPOILER 1/4 L PUMP R PUMP
TO TO AUTO AUTO HYDRAULIC
CONTROL LEVER OFF ON OFF ON

1/2
R
E
CLB CLB
PTU
AUTO
CONTROL PANEL
T OFF ON
R
A
3/4 C AUX
ALTN PUMP
T IDLE IDLE FLAPS AUTO
REV REV OFF
MAX
ON
EMER
TO/GA TO/GA

MAX MAX
REV REV
FLAP LEVER
PITCH DISC
PULL & TURN
L ENGINE R ENGINE
RUN RUN

FLAPS
THROTTLE P
I
OFF OFF

QUADRANT T
C GND/ROLL
H

D
GND SPOILERS
AUTO
ROLL SPOILERS SPOILERS
I
S
OFF MANUAL CONTROL−PANEL
PITCH C
ARM
OFF

DISCONNECT
HANDLE WING
INSP
LIGHTING
NAV STROBE
SMKG/
BELTS B
TRIM
B E
RUD C L
N T
L R
S
OFF OFF OFF OFF
EMER LTS LANDING
ON L N LDG/TAXI R
TRIM / STALL STAB
PRI
A
R
T
A
M
CONTROL PANEL OFF
OFF OFF OFF
X
I
OFF
SEC

L ENG FIRE
ENGINE
R ENG FIRE
LIGHTING
APU

STALL
CONTROL PANEL
PUSHER FIRE FIRE FIRE

PARK/EMER PARK/EMER
OFF FIRE EXT
BRAKE BRAKE 1 2 EVENT ENGINE
EMERGENCY/
ARMED ARMED
CONTROL PANEL
SYSTEMS TEST AUTO APR MACH HOLD
PARKING BRAKE OFF
AUTO SYNC
N1
ANNUN A OFF OFF N2 ON
HANDLE ANNUN B
PUSH
TO L STARTER R STARTER
TAWS TEST PROBES OFF OFF
IGNITION
FIRE DET STALL/RUD LIM
ICE DET CRANK START CRANK START LANDING−GEAR
SYSTEM ON
MANUAL−RELEASE
ELT
TEST/RESET ON
HANDLE
ARM
CONTROL−PANEL RESET
APU

LEFT RIGHT
DISPLAYS EICAS DISPLAYS RUN
PUSH
EMERGENCY PFD
REV
NORM
MFD
REV
BOTH
PFDS
L MFD
R MFD MFD
REV
NORM
PFD
REV
OFF START LG TO
STOW
PULL

LOCATOR
TRANSMITTER ATT/HDG
NORM
TUNE
NORM
AIR DATA
NORM APU
MFD
(ELT) PANEL 1 2 ONLY
COM 1
121.50
CDU
ONLY
1 2
OXYGEN CONTROL PANEL
THERAPEUTIC PAX
AUTO
OFF DEPLOY
ON
REVERSION
SELECT CABIN PAX OXYGEN
DC PWR AC PWR CAB LTS ENT LTS
CONTROL−PANEL
CAR0504_004

PANEL OFF OFF ON ON

COCKPIT VOICE
RECORDER
HOLD
5 SEC

TEST HEADSET ERASE

CABIN CONTROL COCKPIT VOICE

PANEL RECORDER (CVR)
02 B CONTROL PANEL

Center Pedestal − Component Location

Figure 4 (Sheet 4 of 5)

EFFECTIVITY: ALL
Page 12
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FLIGHT HYDRAULIC
L SOV R SOV
SPOILERS

CLOSED CLOSED
STOW
APR APR
FLIGHT−SPOILER 1/4 L PUMP R PUMP
TO TO AUTO AUTO HYDRAULIC
CONTROL LEVER OFF ON OFF ON

1/2
R
E
CLB CLB
PTU
AUTO
CONTROL PANEL
T OFF ON
R
A
3/4 C AUX
ALTN PUMP
T IDLE IDLE FLAPS AUTO
REV REV OFF
MAX
ON
EMER
TO/GA TO/GA

MAX MAX
REV REV
FLAP LEVER
PITCH DISC
PULL & TURN
L ENGINE R ENGINE
RUN RUN

FLAPS
THROTTLE P
I
OFF OFF

QUADRANT T
C GND/ROLL
H

D
GND SPOILERS
AUTO
ROLL SPOILERS SPOILERS
I
S
OFF MANUAL CONTROL−PANEL
PITCH C
ARM
OFF

DISCONNECT
HANDLE WING
INSP
LIGHTING
NAV STROBE
SMKG/
BELTS B
TRIM
B E
RUD C L
N T
L R
S
OFF OFF OFF OFF
EMER LTS LANDING
ON L N LDG/TAXI R
TRIM / STALL STAB
PRI
A
R
T
A
M
CONTROL PANEL OFF
OFF OFF OFF
X
I
OFF
SEC

L ENG FIRE
ENGINE
R ENG FIRE
LIGHTING
APU

STALL
CONTROL PANEL
PUSHER FIRE FIRE FIRE

PARK/EMER PARK/EMER
OFF FIRE EXT
BRAKE BRAKE 1 2 EVENT ENGINE
EMERGENCY/
ARMED ARMED
CONTROL PANEL
AUTO APR MACH HOLD
PARKING BRAKE LEFT
EICAS
RIGHT
AUTO SYNC
N1
DISPLAYS DISPLAYS OFF OFF N2 ON
HANDLE PFD
REV
NORM
MFD
REV
BOTH
PFDS
L MFD
R MFD MFD
REV
NORM
PFD
REV
L STARTER R STARTER
OFF OFF
IGNITION
REVERSION TUNE
CRANK START CRANK START LANDING−GEAR
ATT/HDG AIR DATA
SELECT 1
NORM
2
MFD
ONLY
NORM
CDU
ONLY
1
NORM
2
ON
MANUAL−RELEASE
PANEL
COM 1
121.50
HANDLE
APU
SYSTEMS TEST
RUN
OFF PUSH
ANNUN A OFF START
LG TO PULL
STOW
SYSTEM PUSH
TO
ANNUN B

TAWS TEST PROBES

TEST/RESET FIRE DET STALL/RUD LIM
ICE DET
CONTROL−PANEL APU
ELT
ON
OXYGEN
PAX
CONTROL PANEL
EMERGENCY ARM
THERAPEUTIC AUTO
OFF DEPLOY
LOCATOR RESET
ON
COCKPIT VOICE
TRANSMITTER HOLD
5 SEC
RECORDER

(ELT) PANEL TEST HEADSET ERASE

DC PWR AC PWR
CABIN
CAB LTS ENT LTS
PAX OXYGEN
CAR0504_005

ON

COCKPIT VOICE
OFF OFF ON
CONTROL−PANEL
RECORDER (CVR) CABIN CONTROL
CONTROL PANEL 03 B PANEL

Center Pedestal − Component Location

Figure 4 (Sheet 5 of 5)

EFFECTIVITY: ALL
Page 13
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

AIR CONDITION / BLEED PRESSURIZATION

FUEL CONTROL CONTROL PANEL CONTROL PANEL
PANEL

FUEL AIR COND BLEED PRESSURIZATION

GRAVITY COCKPIT CABIN MAN RATE
MAN TEMP MANUAL LNDG ALT
XFLOW ALT SOURCE
SELECT
ON ON FMS
MAN

L PUMP R PUMP HOT COLD HOT DN UP

COLD
AUTO AUTO NORM EMER DEPRESS DITCHING
XFER RAM AIR
ON OFF ON OFF OFF PACK ONLY CONTROL
TRIM AIR
ON ONLY ON ON
DISPLAY
L BLEED X BLEED R BLEED UNIT
ANTI−ICE OFF

APU
OFF

CONTROL ON

PANEL
ANTI−ICE
WING
SOURCE WING PROBES
NORM L R
FROM FROM
L R
ON OFF OFF

L ENG R
WSHLD/WINDOW
L R
CURSOR
ON ON OFF OFF
CLR
CONTROL
CONTROL PANEL
ELECTRICAL
DISPLAY L BATT EXT PWR R BATT
AVAIL

UNIT OFF
ON
OFF

STBY
(OPTIONAL) UPR
MENU ESC STAT MEM 1 CHART JSTK INST
BUS TIE
UPR
MENU
ESC STAT MEM 1 CHART JSTK

MENU DATA MENU DATA

LWR
ADV
MEM 2 OFF LWR MEM 2
MENU ADV
MENU
S
PU H L ESS R ESS S
PU H
ZOOM ZOOM
S

E
MEM 3
S

E
L EC
− + L EC MEM 3
− +
L AUX L MAIN R MAIN R AUX
UPR UPR
FRMT CKLST SKIP A/ICE ECS ELEC FLT CKLST SKIP A/ICE ECS ELEC FLT
FRMT
L GEN APU GEN R GEN
LWR LWR
TFC TR/WX FUEL HYD SUMRY TFC TR/WX FUEL HYD SUMRY
FRMT OFF OFF FRMT
ON
CAS ENTER CAS ENTER
BAR0504_001

CURSOR ELECTRICAL
CONTROL A CONTROL
PANEL PANEL

Center Pedestal − Component Location

Figure 5 (Sheet 1 of 2)

EFFECTIVITY: ALL
Page 14
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FLIGHT HYDRAULIC
L SOV R SOV
SPOILERS

CLOSED CLOSED
STOW
APR APR
FLIGHT−SPOILER 1/4 L PUMP R PUMP
TO TO AUTO AUTO HYDRAULIC
CONTROL LEVER OFF ON OFF ON

1/2
R
E
CLB CLB
PTU
AUTO
CONTROL PANEL
T OFF ON
R
A
3/4 C AUX
ALTN PUMP
T IDLE IDLE FLAPS AUTO
REV REV OFF
MAX
ON
EMER
TO/GA TO/GA

MAX MAX
REV REV
FLAP LEVER
PITCH DISC
PULL & TURN
L ENGINE R ENGINE
RUN RUN

FLAPS
THROTTLE P
I
OFF OFF

QUADRANT T
C GND/ROLL
H

D
GND SPOILERS
AUTO
ROLL SPOILERS SPOILERS
I
S
OFF MANUAL CONTROL−PANEL
PITCH C
ARM
OFF

DISCONNECT
HANDLE WING
INSP
LIGHTING
NAV STROBE
SMKG/
BELTS B
TRIM
B E
RUD C L
N T
L R
S
OFF OFF OFF OFF
EMER LTS LANDING
ON L N LDG/TAXI R
TRIM / STALL STAB
PRI
A
R
T
A
M
CONTROL PANEL OFF
OFF OFF OFF
X
I
OFF
SEC

L ENG FIRE
ENGINE
R ENG FIRE
LIGHTING
APU

STALL
CONTROL PANEL
PUSHER FIRE FIRE FIRE

PARK/EMER PARK/EMER
OFF FIRE EXT
BRAKE BRAKE 1 2 EVENT ENGINE
EMERGENCY/
ARMED ARMED
CONTROL PANEL
AUTO APR MACH HOLD
PARKING BRAKE LEFT
EICAS
RIGHT
AUTO SYNC
N1
DISPLAYS DISPLAYS OFF OFF N2 ON
HANDLE PFD
REV
NORM
MFD
REV
BOTH
PFDS
L MFD
R MFD MFD
REV
NORM
PFD
REV
L STARTER R STARTER
OFF OFF
IGNITION
REVERSION TUNE
CRANK START CRANK START LANDING−GEAR
ATT/HDG AIR DATA
SELECT 1
NORM
2
MFD
ONLY
NORM
CDU
ONLY
1
NORM
2
ON
MANUAL−RELEASE
PANEL
COM 1
121.50
HANDLE
APU
SYSTEMS TEST
RUN
OFF PUSH
ANNUN A OFF START
LG TO PULL
STOW
SYSTEM PUSH
TO
ANNUN B

TAWS TEST PROBES

TEST/RESET FIRE DET STALL/RUD LIM
ICE DET
CONTROL−PANEL APU
ELT
ON
OXYGEN
PAX
CONTROL PANEL
EMERGENCY ARM
THERAPEUTIC AUTO
OFF DEPLOY
LOCATOR RESET
ON
COCKPIT VOICE
TRANSMITTER HOLD
5 SEC
RECORDER

(ELT) PANEL TEST HEADSET ERASE

DC PWR AC PWR
CABIN
CAB LTS ENT LTS
PAX OXYGEN
BAR0504_002

ON

COCKPIT VOICE
OFF OFF ON
CONTROL−PANEL
RECORDER (CVR) CABIN CONTROL
CONTROL PANEL B PANEL

Center Pedestal − Component Location

Figure 5 (Sheet 2 of 2)

EFFECTIVITY: ALL
Page 15
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

4. Electrical Control Panels and Battery Locations

A. Refer to Figure 6 and Figure 12 for aircraft and Integrated Standby Instrument (ISI)
battery locations.

B. To isolate electrical power do the following:

− If engines are running select the L GEN and/or R GEN switch(es) to OFF.

− Push the L BATTERY and/or R BATTERY PBA to OFF.

− Push the STBY INST battery PBA to OFF.

C. To disconnect main battery do the following:

− Open the aft compartment access door.

− Disconnect the battery power connector from the battery.

− Disconnect the electrical connector from the battery.

D. To disconnect Integrated Standby Instrument (ISI) battery:

− In the Nose Landing Gear Wheelwell, remove the access door 121ALZ. Refer to
Figure 12.

− Disconnect the battery connector from the battery.

EFFECTIVITY: ALL
Page 16
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

ELECTRICAL
L BATT EXT PWR R BATT
AVAIL
OFF OFF
ON

STBY
INST
BUS TIE
OFF
L ESS R ESS

L AUX L MAIN R MAIN R AUX

L GEN APU GEN R GEN

OFF ON OFF

CAR0505_001

Electrical Control Panel and Battery Locations

Figure 6 (Sheet 1 of 2)

EFFECTIVITY: ALL
Page 17
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

CAR0505_002

BATTERIES

Electrical Control Panel and Battery Locations

Figure 6 (Sheet 2 of 2)

EFFECTIVITY: ALL
Page 18
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

5. Flammable Fluids and Gases

Table 2 lists all flammable fluids and gases carried on the aircraft. The table also gives the
specifications and the commercial grades and capacities. Refer to Figure 7 for locations of
the reservoirs and tanks.

Table 2 − Flammable Fluids and Gases

CAPACITY Specification or
Commercial Grades
Cubic U.S Imperial Liters Weight
Inches Gallons Gallons

Fuel — 2 096 1 745 7 934 14 150 lbs ASTM D1655

System 6 424 kg Jet A
Total @6.75 Jet A−1
Capacity lb/usg Jet B
JP− 4

Engine Oil — Left: 1.26 Left: 1.03 Left: 4.7 — MIL−PRF−23699

Tanks Right: 1.51 Right: 1.19 Right: 5.7 Type 2
Mobil Jet Engine Oil II

Hydraulic RH−52.5 2.27 — 8.60 — CMS 564−03 Type IV

Reservoirs LH−75 3.25 12.30
AUX−15 0.65 2.46

APU Oil — 0.50 0.42 1.9 — MIL−PRF−23699

Tanks Type 2
Mobil Jet Engine Oil II

Oxygen Basic: — — Basic: 2 180 — Therapeutic Oxygen

Bottle 77 FT³ option: 3 256 MIL−PRF−27210
System option: Type 1
Pressure 115 FT³
1850 PSI

EFFECTIVITY: ALL
Page 19
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

DUAL HYDRAULIC
RESERVOIRS
ENGINE OIL
TANK

OXYGEN
BOTTLES
APU AND GENERATOR
ADAPTER OIL TANKS

RIGHT FUEL
TANK
ENGINE OIL
TANK

LEFT FUEL
TANK

CAR0506_001

Flammable Fluids and Gasses

Figure 7

EFFECTIVITY: ALL
Page 20
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

6. Fuel System General Layout

A. The wing fuel is contained in a wet wing−box structure. The structure is divided in two
wing tanks at the wing center line. The fuel is contained between the front and the rear
spars in the left and the right tanks., Refer to Figure 8.

B. Feed/collector tanks are integrally contained within each tank. Baffles in each wing tank
restrict fuel sloshing thus limiting center of gravity shifts with changes in aircraft attitude.
Swing check valves on the baffles allow fuel flow in the inboard direction only. Flush,
self−closing dual seal water drain valves are located at all the low points of the system.

C. Refer to Figure 9 for the fuel system indication in the flight compartment, .

EFFECTIVITY: ALL
Page 21
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

A C

RIGHT
MAIN TANK

B
C
LEFT
MAIN TANK

A
C

PRESSURE REFUEL/DEFUEL ADAPTOR

B
CAR0507_071

GRAVITY FILLER CAP WATER DRAIN VALVE

A C

Fuel System Layout

Figure 8

EFFECTIVITY: ALL
Page 22
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FUEL
GRAVITY
XFLOW

L PUMP R PUMP
AUTO AUTO
OFF ON XFER OFF ON

CAR0508_001

Fuel Controls in the Flight Compartment

Figure 9 (Sheet 1 of 2)

EFFECTIVITY: ALL
Page 23
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

85.0 MCT 85.0 MCT TRIM LEFT ENGINE FIRE

T
OV
STAB AIL PARKING BRAKE
93.0 61.0
NI NU BRAKE OVERHEAT
FIRE GEAR DISAGREE
MACH
HOLD 6.6 FUEL IMBALANCE
LWD RWD DISPLAY COOL
VIB VIB RUD 12345678901234567890
ND
12345678901234567890
L R
12345678901234567890
600 600 GEAR 12345678901234567890
FLAPS 0
ITT 12345678901234567890
DN 12345678901234567890
UP 12345678901234567890
IGN IGN 12345678901234567890
S 84.7 N2 84.7 S SPOLIERS 12345678901234567890
T OIL PRESS 46 T
46 12345678901234567890
A A
R 115 OIL TEMP 115 R 12345678901234567890
T 7300 FF PPH 7300 T 12345678901234567890
12345678901234567890
APU RPM 300 12345678901234567890
APU EGT 250 12345678901234567890
12345678901234567890
FUEL QTY LBS CAB ALT 7300 12345678901234567890
TOTAL 12000 CAB RATE 1000
6000 6000 PAGE 1/4

FUEL
TOTAL FUEL FUEL USED
9700 LBS 3900 LBS

P P 43 ° C

4870 LBS 4870 LBS

135 ° C 135 ° C

APU
MFD CONTROL
CONTROL

COM1 NAV1 ATC1/TCAS ADF1 HF1 COM3 COM2

118.000 TX 108.00 1200 1799.5 2.0000 AM 118.000 118.000
118.000 108.00 STBY 190.0 2.0000 118.000 118.000
ABV 25 25
CAR0508_002

Fuel Controls in the Flight Compartment

Figure 9 (Sheet 2 of 2)

EFFECTIVITY: ALL
Page 24
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

7. Emergency Break−In Zone

A. The emergency break−in−zone on the Challenger 300 is 16 in (406 mm) wide by 30 in

(762 mm) long. The emergency break−in−zone is located between FS345.00 and
FS375.00 and between LBL8.00 and RBL8.00. Refer to Figure 10.

8. Tires

A. If the wheels on the aircraft become hotter than usual (for example, because of hard
braking or under−inflation), there is a possibility that the fusible plugs can melt. This will
release tire pressure quickly. It is important for persons not to approach the wheels from
the sides. Refer to Figure 1.

9. Composite Material Fire Precautions

A. General

(1) With the new generation aircraft, composite materials are widely used. These
materials are made by bonding layers of fiber together in a "criss−cross" pattern
with resins, epoxies and phenols. Refer to Figure 11 for the locations of the
composite structures on the Bombardier Challenger 300.

B. Dangerous Effects of Free Fibers

(1) In the case of an aircraft fire, the bonding agents (resins, epoxies and phenols) can
become unstable and break down. This releases dangerous gases into the
atmosphere. Fire fighters and other personnel should avoid the downwind area of
the fire, specially when they do not use self−contained breathing equipment. As well
as dangerous gases, the fire also releases small particles of free fibers.

EFFECTIVITY: ALL
Page 25
SECTION 05 Dec 22/2015
 BD−100 AIRCRAFT RECOVERY MANUAL

(2) When the fire is extinguished and the structure becomes cool, the bonding agents
stop the release of these free fibers. However, the hazards due to the release of
free fibers continues and can become a long term problem. This is because:
− When The free fibers come in contact with fire, the fibers tend to break into
shorter lengths and smaller diameters. This makes them light and easily
airborne. The free fibers also absorb pyrolytic acid. This poisonous material is
picked up from the burned materials. The smoke from the fire can carry the free
fibers and can therefore send the contamination over a large area.

− Without correct protection, personnel can breathe in the free fibers and they can
bond to a person’s respiratory system. They can also move to other internal
organs and cause damage. The free fibers are very stable and there is no
deterioration of the fibers in the body.
− They will burn the eyes.
− The ends of the fibers are very sharp. This will let them pass through clothing
and skin. If you rub the affected area, you can cause dermatitis which will
require medical treatment.

C. Control of Free Fibers

(1) As soon as the fire fighting and medical activities are completed, take steps to limit
the spread of the free fibers. This is important when you move the damaged
aircraft.

(2) Treat the components that can release free fibers as follows:
− Keep the materials wet with Aqueous Fire Fighting Foam (AFFF) or water. With
the AFFF, wet the materials every six hours

NOTE: Light oil, clear liquid furniture wax, polyacrylic acid or strippable paint, are
all good materials to contain free fibers. These liquids are not considered
to be a problem to future investigations.

− Move the damaged aircraft the minimum distance possible and keep it on paved
surfaces when possible. This will make the removal of the contamination more
efficient.

(3) All personnel that work in the free fiber contaminated area must wear disposable
paper coveralls, heavy boots, thick leather gloves, goggles, and a dust mask. They
must discard the paper coveralls and dust mask when they leave the contaminated
area.

EFFECTIVITY: ALL
Page 26
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FS345.00

FS375.00

RBL8.00
LBL8.00

EMERGENCY
BREAK−IN−ZONE
LOCATION

WARNING
DO NOT ATTEMPT TO CHOP
THROUGH WINDOWS
CAR05_091

Emergency Break−in−zone
Figure 10

EFFECTIVITY: ALL
Page 27
SECTION 05 Dec 22/2015
 BD−100 AIRCRAFT RECOVERY MANUAL

V−STAB AFT
BULLET FAIRING,
V−STAB FORWARD AND AFT CONE ELEVATORS
BULLET FAIRING
LH AND RH FORWARD
ACCESS PANELS

VERTICAL
STABILIZER
WINGLETS LEADING EDGE

MULTI−FUNCTION DORSAL HORIZONTAL

SPOILERS FAIRING STABILIZER

GROUND RUDDER
SPOILERS
TAILCONE

CABIN THRUST REVERSER

FLOOR PIVOT DOORS
OUTER SKIN

ENGINE
COWLS
BIRD
FLAPS
STRIKE
BARRIER AILERON

AFT
NLG
DOOR STAIRS
RADOME FLAP
NOSE LANDING FAIRINGS
GEAR DOORS
(LEFT AND RIGHT) LEGEND
WHEEL
BINS KEVLAR
GRAPHITE
FIBERGLASS
HYBRID
CAR05_101

BELLY OVER−WING
FAIRINGS FAIRINGS

Composite Materials
Figure 11

EFFECTIVITY: ALL
Page 28
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FS227.50

BATTERY
COMPARTMENT
ACCESS PANEL
121ALZ

CAMLOCKS

CAR0511_001

STANDBY INSTRUMENT
BATTERY

A
Standby Instrument Battery
Figure 12

EFFECTIVITY: ALL
Page 29
SECTION 05 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

GROUND SAFETY

1. Towing the Aircraft

A. General

(1) If the aircraft cannot be taxied, push or tow the aircraft to move it.

(2) To push or tow the aircraft, attach the towbar to the nose wheel axle with the lugs
on the towbar. Let the two vehicules control movement of the aircraft. If the aircraft
is being pushed and you apply the aircraft brakes hard, this can cause the nose
gear to come off the ground.

On Challenger 300 A/C

(3) Refer to Figure 1 and Figure 2 for the tow bar installation and turn radii.

On Challenger 350 A/C

(4) Refer to Figure 1 and Figure 3 for the tow bar installation and turn radii.

B. Towing the Aircraft with Bridle

Table 1 − Towing Equipment

Reference Designation

TBD Towing Bridle

23X−51−01 Headset with Microphone and Lead

23−00−02 Headset Extension Cord

(1) Installation of Towing Bridle

CAUTION: DO NOT INSTALL THE WIRE ROPE ASSEMBLIES ON TOP OF THE

BRAKE LINES OR WIRING HARNESS. MAKE SURE THAT ONLY THE
LEATHER BINDING OF THE WIRE ROPE ASSEMBLIES TOUCHES
THE MAIN LANDING GEAR. IF YOU DO NOT OBEY THESE
INSTRUCTIONS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.

(a) Attach the rope assemblies around each main landing gear as follows:

1 To tow the aircraft forward, release the clamps that hold the brake lines to
the main beam. Put the wire rope assemblies behind the brake lines on
the main beam, then around the main beam. Refer to Figure 4.

EFFECTIVITY: ALL
Page 1
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

2 To tow the aircraft rearward, put the wire rope assemblies over the trailing
arm link and below the axle of each MLG. Refer to Figure 4.

NOTE: Loosen or remove the retaining clips to put the wire rope
assembly between the MLG and the brake lines and the wire
harness.

WARNING: MAKE SURE THAT THERE ARE NO KINKS IN THE WIRE

ROPE ASSEMBLIES. KINKS CAN CAUSE THE WIRE ROPE
ASSEMBLIES TO BREAK. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO THE EQUIPMENT.

3 Tow the aircraft. Obey all the safety precautions (Refer to Paragraph D).

(2) Removal of Towing Bridle

(a) Disconnect the wire rope assemblies from the anchor shackles.

(b) Remove the wire rope assemblies from the MLG.

(c) Clean, lubricate, and put the towing bridle into storage.

C. Ground Lockpins

(1) Refer to Figure 5 and Figure 6 for landing gear ground lockpins installation.

EFFECTIVITY: ALL
Page 2
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

TOWBAR

SHEAR PIN

UPPER
TORQUE
LINK

LOWER
TORQUE
LINK

TOWBAR
CAR0601_001

AXLE
A ENGAGEMENT
PIN

Equipment to Tow the Aircraft

Figure 1

EFFECTIVITY: ALL
Page 3
SECTION 06 Jul 11/2005
 BD−100 AIRCRAFT RECOVERY MANUAL

FS 0.00

R37 FT 4 IN
27 FT 9 IN (11.40 m)
(8.46 m)

BL 0.00

65.0°
21 FT
(6.40 m) 95 FT 6 IN
R20.0 FT (29.11 m)
(6.10 m)
TURN 58 FT
R31 FT 6 IN CENTER (17.68 m)
(9.60 m) MIN PAVEMENT
WIDTH 180 DEGREES
R38 FT 4 IN TURN. WITH 5FT (1.52m)
(11.70 m)
MARGIN OF
SAFETY

NOTES
MAXIMUM STEERING
SYMMETRICAL & IDLE THRUST
NO DIFFERENTIAL BRAKING
65 DEGREES STEERING ANGLE
3 DEGREES SLIP
DRY RUNWAY
SLOW CONTINUOUS TURN
MAX AIRCRAFT WEIGHT
CAR06_021

AFT CENTER OF GRAVITY.

Challenger 300 − Turn Radii

Figure 2

EFFECTIVITY: ALL
Page 4
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

FS 0.00

R 37 ft 5 in
27 ft 10 in (11.40 m)
(8.47 m)

BL 0.00

62 DEGREES 21 ft
(6.40 m) 101 ft 1 in
R 20 ft (30.82 m)
(6.10 m)
TURN
R 31 ft 6 in CENTER
(9.60 m) 53 ft (16.15 m) MINIMUM
PAVEMENT WIDTH
R 38 ft 5 in 180 DEGREES TURN
(11.70 m) WITH 5 ft (1.52 m)
MARGIN OF SAFETY

NOTES
Maximum steering
Symmetrical and idle thrust
No differential braking
65 Degrees steering angle
3 Degrees slip
Dry runway
BAR06_001

Slow continuous turn

Maximum aircraft weight
Aft center of gravity.

Challenger 350 − Turn Radii

Figure 3

EFFECTIVITY: ALL
Page 5
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

MAIN BEAM

A LEATHER
BINDING

ANCHOR
SHACKLE

WIRE ROPE
ASSEMBLY

TOWING AIRCRAFT FORWARD

A
B
ANCHOR
SHACKLE
LEATHER
BINDING
WARNING
BEFORE THE AIRCRAFT IS TOWED,
MAKE SURE THAT ALL THE BOLTS
AND PINS ARE ATTACHED SAFELY.
ALSO MAKE SURE THAT THERE WIRE ROPE
ARE NO KINKS IN THE WIRE ROPE ASSEMBLY
ASSEMBLIES. YOU CAN CAUSE
INJURIES TO PERSONS AND DAMAGE
TO EQUIPMENT.

CAUTION
MAKE SURE THAT THE WIRE ROPE
ASSEMBLIES DO NOT TOUCH THE
BRAKE LINES OR THE WIRING LEATHER
HARNESSES. ALSO MAKE SURE THAT BINDING
ONLY THE LEATHER BINDINGS OF
THE WIRE ROPE ASSEMBLIES TRAILING
ARM LINK
CAR06_031

TOUCH THE LANDING GEAR. YOU

CAN CAUSE DAMAGE TO THE BRAKE TOWING AIRCRAFT REARWARD
LINES, THE WIRING HARNESSES, OR
THE LANDING GEAR. B

Towing by MLG
Figure 4

EFFECTIVITY: ALL
Page 6
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

GROUND
LOCKING PIN

CAR06_041

Main Landing−Gear (MLG) Lockpin

Figure 5

EFFECTIVITY: ALL
Page 7
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

GROUND
LOCKING PIN

CAR06_051

Nose Landing−Gear (NLG) Lockpin

Figure 6

EFFECTIVITY: ALL
Page 8
SECTION 06 Oct 31/2014
 BD−100 AIRCRAFT RECOVERY MANUAL

D. Safety Precautions

CAUTION: WHEN YOU TOW THE AIRCRAFT, OBEY THE PRECAUTIONS THAT
FOLLOW:
- OBEY ALL LOCAL AIRPORT REGULATIONS.
- APPLY TOWBAR LOADS SLOWLY AND CAREFULLY.
- MAKE ALL CHANGES TO THE SPEED OR THE DIRECTION SLOWLY.
- KEEP THE TURNS AS LARGE AS POSSIBLE.
- DO NOT USE THE AIRCRAFT BRAKES TO STOP THE AIRCRAFT
UNLESS THERE IS AN EMERGENCY.
- DO NOT TOW THE AIRCRAFT IN A FORWARD DIRECTION AT MORE
THAN 5 MPH (8 KM/H).
- DO NOT MOVE THE AIRCRAFT REARWARD AT MORE THAN 3 MPH (5
KM/H).
- MAKE SURE THAT YOU PUT THE NOSEWHEEL IN THE CENTER
POSITION BEFORE THE AIRCRAFT IS PARKED.

IF YOU DO NOT OBEY THESE PRECAUTIONS, DAMAGE TO THE

EQUIPMENT CAN OCCUR.

(1) Make sure that the tires are correctly inflated, if possible.

(2) Make sure that lockpins are installed in the NLG and MLG. Refer to Figure 5
and Figure 6.

(3) Remove all items from around the aircraft, such as ground equipment, that can
prevent the movement of the aircraft.

(4) Make sure that the nosewheel steering is turned off.

CAUTION: BEFORE YOU TOW THE AIRCRAFT, MAKE SURE THAT THERE IS A
MINIMUM LOAD OF 1 050 LB (476.2 KG) ON THE NOSEWHEEL. IF
YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO THE
AIRCRAFT.

(5) A minimum load of 1000 lbs (454 kg) is necessary on the nose wheel before you
tow the aircraft. Refer to the Bombardier Challenger Series aircraft Weight and
Balance Manual to determine the load on the nose wheel. Add the applicable
ballast as necessary.

(6) Make sure that the landing gear selector−handle is set to the DN position.

(7) Put a qualified technician in the flight compartment to monitor the brake system
pressure and operate the aircraft brakes.

EFFECTIVITY: ALL
Page 9
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 BD−100 AIRCRAFT RECOVERY MANUAL

WARNING: WHEN YOU PREPARE THE AIRCRAFT FOR TOWING, OBEY THE
PRECAUTIONS THAT FOLLOW:
- MAKE SURE THAT THE NOSEWHEEL STEERING IS SET TO THE
OFF POSITION.
- MAKE SURE THAT THE NOSEWHEEL IS IN THE CENTER
POSITION.
- MAKE SURE THAT THE EXTERNAL SERVICING EQUIPMENT IS
DISCONNECTED.
- MAKE SURE THAT ALL EXTERNAL DOORS AND PANELS ARE
CLOSED AND LATCHED.

IF YOU DO NOT OBEY THESE PRECAUTIONS, INJURY TO PERSONS

AND DAMAGE TO EQUIPMENT CAN OCCUR.

(8) If possible, put the Battery Master switch to ON.

(9) Connect the intercom system between the driver of the tow vehicule and the
technician in the flight compartment.

(10) In an area that has little space, have a person at each wingtip to make sure of
sufficient clearance from objects and the aircraft.

(11) Before you move the aircraft rearward, have a person at the tail to make sure of
sufficient clearance from objects and the aircraft.

(12) Remove the chocks and release the parking brake.

(13) Tow the aircraft not more than 5 MPH (8 KM/H) or push the aircraft not more than
3 MPH (5 KM/H).

(14) After the tow operation, make sure the nose wheels are put to the center position.
Do the operations that follow:

(a) Apply the parking brake.

(b) Chock the wheels.

(c) Release the parking brake.

(d) Disconnect the tow vehicule.

(e) Remove the tow bar or the towing bridle and park the aircraft.

NOTE: In some cases, after a tow operation there is a difference between

the MLG strut heights. A qualified technician can make sure the
servicing of the struts is correct.

EFFECTIVITY: ALL
Page 10
SECTION 06 Oct 31/2014