FAA Approved in normal category based on 14 CFR 25. This document must be carried in the airplane at all
times, and be kept within reach of the pilot during all flight operations. This manual includes the material required
to be furnished to the pilot by 14 CFR 25 and the applicable special conditions.
COPYRIGHT © 2004
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
56XWBA-02
22 MARCH 2004
REVISION 2
1 APRIL 2009
U.S.
Printed 08.10.15 12:47. Document Revision ---
TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE
Publication Affected:
Model 560XL Citation XLS (560-5501 thru -6000) basic
FAA Approved Airplane Weight and Balance Manual,
Revision 2, dated 1 April 2009.
Airplane Serial Numbers Affected:
Airplanes 560-5501 thru -6000.
Description of Change:
Section VI, Weight and Balance Data, Manual Title Page,
remove the requirement for the manual to be carried in
the airplane for all flight operations.
Filing Instructions:
Insert this temporary change in the Model 560XL Citation
XLS (560-5501 thru -6000) basic FAA Approved Airplane
Weight and Balance Manual, Revision 2 adjacent to page
i.
Removal Instructions:
This temporary change must be removed and discarded
when Revision 3 has been collated into the basic FAA
Approved Airplane Weight and Balance Manual.
On the Title Page of the basic FAA Approved Airplane Weight and Balance Manual, Revision 2, in
the paragraph below the illustration, use a pen with indelible ink to strike through the sentence that
requires the manual to be carried in the airplane for all flight operations as follows:
This document must be carried in the airplane at all times, and be kept within reach of the pilot
during all flight operations.
56XWBA TC-R02-01
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
LOG OF EFFECTIVE PAGES
LOG OF EFFECTIVE PAGES
Use this page to determine the currency and applicability of your FAA Approved Weight and Balance
Manual. Pages affected by the current revision are indicated by an asterisk (*) preceding the pages
listed under the Page Number Column.
Following is a description of the Log of Effective Pages columns:
Page Number - FAA Approved Weight and Balance Manual page numbers.
Page Status - Indicates if the page has been added, revised or deleted by the current revision.
Revision Number - Indicates the revision number.
Configuration Code - A two-letter code to indicate Model effectivity. Refer to the basic FAA
Approved Airplane Flight Manual for a complete list of Configuration Codes.
Revision Number
Original
Date
22 March 2004
Revision 1
16 November 2006
Revision 2
1 April 2009
Page
*
*
*
*
*
*
*
*
*
*
*
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*
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Number
Title
i thru ii
Contents
6-1/6-2
6-3 thru 6-4
6-5/6-6
6-7 thru 6-11/6-12
6-13/6-14
6-15 thru 6-18
6-19/6-20
6-21 thru 6-22
6-23/6-24
6-25 thru 6-34
6-35/6-36
6-37 thru 6-47/6-48
6-49/6-50
6-51 thru 6-64
6-65/6-66
6-67 thru 6-73/6-74
6-75/6-76
6-77/6-78
Page
Status
Revision
Number
Configuration
Code
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
Revised
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
2
AA
AA
AA
AA
AA
AA
AA
AA
AA
AA
AA
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(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
U.S.
i
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
LOG OF EFFECTIVE PAGES
WEIGHT AND BALANCE DATA SHEETS
Form
Number
2157
2158
2159
2160
2161
2162
2163
2164
2165
2166
2167
2168
2169
2170
2171
2172
2332
2333
2334
2335
2336
2337
2338
2339
ii
U.S.
Original
Date
Revision
Date
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
22 March 2004
11 August 2004
12 August 2004
11 August 2004
12 August 2004
11 August 2004
11 August 2004
11 August 2004
11 August 2004
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
1 April 2009
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15
12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
TABLE OF CONTENTS
TABLE OF CONTENTS
PAGE
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1/6-2
CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-5/6-6
FUEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-13/6-14
FLUIDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-19/6-20
PERSONNEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-23/6-24
BAGGAGE AND STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-35/6-36
GROUND OPERATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-49/6-50
EXAMPLES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-65/6-66
AIRPLANE REPORTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-75/6-76
FAA APPROVED
56WBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
Contents
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
INTRODUCTION - TABLE OF CONTENTS
INTRODUCTION
TABLE OF CONTENTS
PAGE
INTRODUCTION
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3
Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3
Weight and Balance Manual Part Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-3
Revisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4
Revised Material Indicators. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-4
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-1/6-2
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
INTRODUCTION
INTRODUCTION
GENERAL
The information in this publication is based on data available at the time of publication and is
updated, supplemented, and automatically amended by Service Letters, Service Bulletins, Supplier
Service Notices, Publications Changes, Revisions, Reissues, Temporary Revisions and Temporary
Changes, which are issued through subscriptions service available from Citation Service
Information. All such amendments become part of and are specifically incorporated within this
publication. Users are urged to keep abreast of the latest amendments to this publication through
Citation Service Information subscription services and/or Citation Service Centers and Citation
Service Stations.
COVERAGE
The Weight and Balance Manual in the airplane at the time of delivery from Cessna Aircraft
Company contains information applicable only to that particular airplane.
WEIGHT AND BALANCE MANUAL PART NUMBER
Each page in the FAA Approved Weight and Balance Manual contains the part number of the manual
and the page status of each page.
Refer to the following example:
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-3
SECTION VI - WEIGHT AND BALANCE DATA
INTRODUCTION
MODEL 560XL
INTRODUCTION (Continued)
REVISIONS
As new information becomes available for your airplane, revisions will be issued to all registered
owners. It is the pilot’s responsibility to assure that this flight weight and balance manual is complete
and current at all times.
REVISED MATERIAL INDICATORS
1.
2.
3.
4.
6-4
A bar will extend the full length of deleted, new or revised text added on new or presently
existing pages. This bar will be located adjacent to the applicable text in the margin on the
left side of the page.
A bar in the footer will indicate a revision to the footer, a new page, format or spelling/
grammar changes and/or that information has slipped to or from that page.
A bar located adjacent to the figure number in the margin on the left side of the page will be
used to indicate that the figure number only has changed. An asterisk located at the end of
a figure number will be used to indicate that an illustration has been revised or is all new
material (Ex: Figure 6-1*).
All revised pages will carry the revision number opposite the page number on the applicable
page. A list of revisions is located at the beginning of the Log of Effective Pages.
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL - TABLE OF CONTENTS
CONTROL
TABLE OF CONTENTS
PAGE
CONTROL
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-7
Manual Applicability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-7
Zero Reference Datum Line . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-7
Reference Lines Control Drawings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-7
Definitions - General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-7
Definitions - Weight Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-8
Maximum Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9
Maximum Center-of-Gravity Limits (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9
Maximum Center-of-Gravity Limits (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9
Takeoff Trim Settings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9
Principle Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-10
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-5/6-6
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL
CONTROL
GENERAL
MANUAL APPLICABILITY
This manual is applicable to the Model 560XL (Serials 560-5501 thru -6000) airplane.
CAUTION
THIS MANUAL PRESENTS DATA IN BOTH U.S. AND METRIC UNITS.
MAKE SURE THAT YOU USE THE APPROPRIATE DATA IN THE WEIGHT
AND BALANCE COMPUTATIONS FOR YOUR AIRPLANE.
ZERO REFERENCE DATUM LINE
The zero reference datum line of the Model 560XL (Serials 560-5501 thru -6000) is located 221.0
inches (5613 millimeters) in front of the leveling point located aft of the cabin door frame on WL 127.3
(WL 3232). The addition of any weight in any location therefore, results in a positive moment change.
REFERENCE LINES CONTROL DRAWINGS
Cockpit and Cabin Lines Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6611560
Tailcone Lines Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6612561
Vertical Fin and Rudder Lines Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6631560
Horizontal Stabilizer and Elevator Lines Control Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . 6632560
Main Landing Gear Points Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6641560
Nose Landing Gear Points Control Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6642560
Fairing Lines Control Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6610560
DEFINITIONS - GENERAL
Standard Empty
Weight
Weight of standard airplane including standard items.
Standard Items
Equipment and fluids not an integral part of a particular airplane and not
a variation for the same type of airplane. These items may include, but
are not limited to, the following:
(1) unusable fuel
(2) engine oil
(3) toilet fluid
(4) serviced fire extinguisher
(5) all hydraulic fluid
(6) trapped fuel
Basic Empty Weight
Standard Empty Weight plus installed optional equipment. This is the
weight reflected on the Weight and Balance Data Form supplied with
the airplane.
(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-7
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL
MODEL 560XL
DEFINITIONS - GENERAL (Continued)
Ramp Weight
Operational Takeoff Weight plus fuel necessary for start, taxi and runup. It must not exceed Maximum Ramp Weight (MRW).
Operational Takeoff
Weight
This is the weight at the start of the takeoff run. It is subject to airport,
operational and related restrictions. It must not exceed Maximum
Takeoff Weight (MTOW).
Operational Landing
Weight
This is the weight at start of touchdown. It is subject to airport,
operational and related restrictions. It must not exceed Maximum
Landing Weight (MLW).
Useful Load
The difference between takeoff weight, or ramp weight if applicable,
and basic empty weight. it includes payload, usable fuel and other
usable fluids not included as standard items.
Payload
Zero fuel weight minus basic empty weight. This is the weight available
for crew, passengers, baggage and cargo.
MAC
The Mean Aerodynamic Chord (MAC) is an engineering term which
represents an airfoil’s chord in aircraft design. As such, it is a constant
length which is also used in the calculation of center-of-gravity location
in terms of percent MAC.
Usable Fuel
Fuel available for flight planning.
Unusable Fuel
Fuel remaining after a fuel run-out test has been completed in
accordance with governmental regulations.
Trapped Fuel
Fuel remaining when airplane is de-fueled by normal means using the
procedures and attitudes specified for draining the tanks.
Zero Fuel Weight
Basic empty weight plus payload. It must not exceed maximum zero
fuel weight.
DEFINITIONS - WEIGHT LIMITATIONS
Maximum Ramp Weight
(MRW)
Maximum weight for ground maneuvers as limited by airplane
strength and airworthiness requirements. It includes weight of start,
taxi and run-up fuel.
Maximum Takeoff Weight
(MTOW)
Maximum weight for takeoff as limited by airplane strength and
airworthiness requirements. This is the maximum weight approved
for the start of the takeoff run.
Maximum Landing Weight
(MLW)
Maximum weight approved for the landing touchdown.
Maximum Zero Fuel
Weight (MZFW)
Maximum weight allowed exclusive of usable fuel.
(Continued Next Page)
6-8
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL
CONTROL (Continued)
MAXIMUM WEIGHT LIMITS
Maximum Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20,400 Pounds (9253 Kilograms)
Maximum Takeoff Weight* . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20,200 Pounds (9163 Kilograms)
Maximum Landing Weight* . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .18,700 Pounds (8482 Kilograms)
Maximum Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .15,100 Pounds (6849 Kilograms)
Minimum Flight Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .12,400 Pounds (5265 Kilograms)
Maximum Tailcone Baggage Weight. . . . . . . . . . . . . . . . . . . . . . . . . . . . 700 Pounds (317 Kilograms)
* Refer to the basic FAA Approved Airplane Flight Manual for additional restrictions which may apply
due to runway pressure altitude and temperature.
MAXIMUM CENTER-OF-GRAVITY LIMITS (U.S. Units)
Forward Limit . . . . . . . . . . . . . . . . . from
318.92 inches aft of the datum (15.00 percent MAC)
at 11,500 pounds.
. . . . . . . . . . . . . . . . . . . . . . . to
324.29 inches aft of the datum (21.52 percent MAC)
at 20,400 pounds with straight line
variation between these points.
Aft Limit . . . . . . . . . . . . . . . . . . . . . .from
330.74 inches aft of the datum (29.37 percent MAC)
at 20,400 pounds to 17,800 pounds.
. . . . . . . . . . . . . . . . . . . . . . . . to
331.26 inches aft of the datum (30.00 percent MAC)
at 15,000 pounds with straight line variation
between these points.
. . . . . . . . . . . . . . . . . . . . . . and
331.26 inches aft of the datum (30.00 percent MAC)
at 15,000 pounds to 11,500 pounds.
MAXIMUM CENTER-OF-GRAVITY LIMITS (Metric Units)
Forward Limit. . . . . . . . . . . . . . . . . .from
8101 millimeters aft of the datum (15.00 percent MAC)
at 5216 kilograms.
. . . . . . . . . . . . . . . . . . . to
8237 millimeters aft of the datum (21.52 percent MAC)
at 9253 kilograms with straight line
variation between these points.
Aft Limit. . . . . . . . . . . . . . . . . . . . . . from
8401 millimeters aft of the datum (29.37 percent MAC)
at 9253 kilograms to 8074 kilograms.
. . . . . . . . . . . . . . . . . . . . . . . .to
8414 millimeters aft of the datum (30.00 percent MAC)
at 6804 kilograms with straight line variation
between these points.
. . . . . . . . . . . . . . . . . . . . . . and
8414 millimeters aft of the datum (30.00 percent MAC)
at 6804 kilograms to 5216 kilograms.
TAKEOFF TRIM SETTINGS
Refer to basic FAA Approved Airplane Flight Manual for takeoff trim settings in relation to airplane
center of gravity.
(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-9
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL
MODEL 560XL
CONTROL (Continued)
PRINCIPLE DIMENSIONS
Wing:
Span - Overall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55.70 Feet (16.98 Meters)
Area - Total Less Tips . . . . . . . . . . . . . . . . . . . .369.70 Square Feet (34.35 Square Meters)
Root Chord (WS 34.00) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.79 Feet (3.29 Meters)
Intermediate Chord (WS 101.07) . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.58 Feet (2.31 Meters)
Tip Chord (Construction) (WS 335.02). . . . . . . . . . . . . . . . . . . . . . . 2.79 Feet (0.85 Meters)
Dihedral . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.00 Degrees
Sweepback 35 Percent Chord . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0 Degrees
MAC (WS 136.69) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.85 Feet (2.09 Meters)
Aspect Ratio. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.95
Flaps:
Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trailing edge extensible single slotted
Tail:
Horizontal:
Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .84.84 Square Feet (7.88 Square Meters)
Dihedral . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.00 Degrees
Vertical:
Area (Exposed) . . . . . . . . . . . . . . . . . . . . . . . . . . .50.88 Square Feet (4.73 Square Meters)
Fuselage:
Height and Width
Outside - Constant
Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.80 Feet (1.77 Meters)
Interior (Stand-up) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.67 Feet (1.73 Meters)
Interior Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.57 Feet (1.70 Meters)
Length - Nose to Tail . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52.10 Feet (15.88 Meters)
6-10
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
CONTROL
Figure 6-1.* Principle Dimensions
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-11/6-12
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FUEL - TABLE OF CONTENTS
FUEL
TABLE OF CONTENTS
PAGE
FUEL
Fuel Tank Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-15
Fuel Limits, Restrictions and Loading Management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16
Fuel Loading Table (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-16
Fuel Loading Table (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-17
Unusable Fuel Table (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-18
Unusable Fuel Table (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-18
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-13/6-14
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FUEL
FUEL
FUEL TANK LOCATIONS
Figure 6-2 presents the fuel tank locations in the airplane.
Figure 6-2. Fuel Tank Locations
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-15
SECTION VI - WEIGHT AND BALANCE DATA
FUEL
MODEL 560XL
FUEL (Continued)
FUEL LIMITS, RESTRICTIONS AND LOADING MANAGEMENT
Maximum asymmetric fuel loading differential shall not exceed 400 pounds (181.44 kilograms) for
the airplane.
FUEL LOADING TABLE (U.S. Units)
Figure 6-3 (Sheet 1) presents the weight and moment in 100-pound increments of the usable fuel
which may be carried in the airplane.
Figure 6-3*. Fuel Loading Table (U.S. Units) (Sheet 1 of 2)
6-16
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FUEL
FUEL (Continued)
FUEL LOADING TABLE (Metric Units)
Figure 6-3 (Sheet 2) presents the weight and moment in 100-kilogram increments of the usable fuel
which may be carried in the airplane. Fuel weight based on 0.808 kilograms/liter.
Figure 6-3*. Fuel Loading Table (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-17
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FUEL
FUEL (Continued)
UNUSABLE FUEL TABLE
Figure 6-4 presents the unusable fuel in the airplane.
INCREMENTS
VOLUME
(GALLONS)
WEIGHT
(POUNDS)
ARM
(INCHES)
MOMENT/100
(INCH-POUNDS)
TRAPPED
UNUSABLE
0.89
6.00
346.67
20.80
DRAINABLE
UNUSABLE
4.71
31.80
333.46
106.04
TOTAL
UNUSABLE
5.60
37.80
335.56
126.84
Unusable Fuel Table (U.S. Units)
MOMENT/1000
WEIGHT
ARM
(MM(KILOGRAMS) (MILLIMETERS) KILOGRAMS)
INCREMENTS
VOLUME
(LITERS)
TRAPPED
UNUSABLE
3.4
2.7
8805
23.77
DRAINABLE
UNUSABLE
17.8
14.4
8470
121.97
TOTAL
UNUSABLE
21.2
17.1
8523
145.74
Unusable Fuel Table (Metric Units)
Figure 6-4*. Unusable Fuel Tables
6-18
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FLUIDS - TABLE OF CONTENTS
FLUIDS
TABLE OF CONTENTS
PAGE
FLUIDS
Fluid Tables. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21
Engine Oil Table (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21
Engine Oil Table (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21
APU Engine Oil Table (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21
APU Engine Oil Table (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21
Hydraulic System Fluid Table (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-22
Hydraulic System Fluid Table (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-22
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-19/6-20
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FLUIDS
FLUIDS
FLUID TABLES
ENGINE OIL TABLE
Figure 6-5 presents data for engine oil. Engine oil weight is 8.13 pounds per gallon (0.97 kilograms
per liter).
ENGINE OIL
INCREMENTS
TOTAL LEFT AND RIGHT
(FULL)
MOMENT/100
VOLUME
WEIGHT
ARM = FS
(GALLONS)
(POUNDS)
(INCHES)
(INCHPOUNDS)
3.75
30.50
433.90
132.34
Engine Oil Table (U.S. Units)
ENGINE OIL
INCREMENTS
VOLUME
TOTAL LEFT AND RIGHT
(FULL)
14.19
(LITERS)
MOMENT/
1000
WEIGHT
ARM = FS
(MM(KILOGRAMS) (MILLIMETERS) KILOGRAMS)
13.83
11,021
152.42
Engine Oil Table (Metric Units)
Figure 6-5
APU ENGINE OIL TABLE
Figure 6-6 presents data for the APU engine oil. APU Engine oil weight is 8.13 pounds per gallon
(0.97 kilograms per liter).
APU Engine Oil Table (U.S. Units)
APU ENGINE OIL
INCREMENTS
TOTAL (FULL)
VOLUME
(GALLONS)
WEIGHT
(POUNDS)
ARM=FS
(INCHES)
MOMENT/100
(INCHPOUNDS)
0.34
2.78
492.49
13.71
APU Engine Oil Table (Metric Units)
APU ENGINE OIL
INCREMENTS
TOTAL (FULL)
VOLUME
(LITERS)
1.30
MOMENT/1000
WEIGHT
ARM=FS
(MM(KILOGRAMS) (MILLIMETER) KILOGRAMS)
1.26
12,509
15.80
Figure 6-6
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-21
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
FLUIDS
FLUIDS (Continued)
HYDRAULIC SYSTEM FLUID TABLE
Figure 6-7, presents data for the hydraulic reservoir and the total hydraulic fluid in the landing gear,
brake, antiskid and flap systems. Hydraulic fluid weight is 8.0 pounds per gallon (0.96 kilograms per
liter).
RESERVOIR
INCREMENT
VOLUME
WEIGHT
(GALLONS) (POUNDS)
ARM
(INCHES)
MOMENT/100
(INCH-POUNDS)
RESERVOIR, FULL
0.93
7.44
482.15
35.87
NOSE LANDING GEAR ACTUAOR
0.09
0.68
115.35
0.78
MAIN LANDING GEAR
ACTUATORS (2)
0.48
3.81
342.88
13.06
BRAKE ACCUMULATOR
0.20
1.61
387.42
6.24
BRAKE RESERVOIR
0.42
3.33
392.53
13.07
T/R ACTUATORS (4)
0.12
0.94
475.36
4.47
SPEED BRAKE ACTUATORS (2)
0.04
0.29
362.46
1.05
FLAP ACTUATORS (2)
0.03
0.23
364.17
0.84
HYDRAULIC LINES
2.22
17.79
402.92
71.68
TOTAL HYDRAULIC SYSTEM
4.53
36.12
407.16
147.07
Hydraulic System Fluid Table (U.S. Units)
MOMENT/
1000
(MMVOLUME
WEIGHT
ARM
(LITERS) (KILOGRAMS) (MILLIMETERS) KILOGRAMS)
RESERVOIR
INCREMENT
RESERVOIR, FULL
3.52
3.37
12,247
41.32
NOSE LANDING GEAR
ACTUATOR
0.34
0.31
2930
0.90
MAIN LANDING GEAR ACTUATOR
(2)
1.82
1.73
8709
15.05
BRAKE ACCUMULATOR
0.76
0.73
9840
7.19
BRAKE RESERVOIR
1.59
1.51
9970
15.06
T/R ACTUATORS
0.45
0.43
12,074
5.15
SPEED BRAKE ACTUATORS (2)
0.15
0.13
9206
1.21
FLAP ACTUATORS (2)
0.11
0.10
9250
0.96
HYDRAULIC LINES
8.40
8.07
10,234
82.57
TOTAL HYDRAULIC SYSTEM
17.15
16.38
10,342
169.41
Hydraulic System Fluid Table (Metric Units)
Figure 6-7*
6-22
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL - TABLE OF CONTENTS
PERSONNEL
TABLE OF CONTENTS
PAGE
PERSONNEL
Crew and Passenger Arrangement Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-25
Crew and Passenger Movement Balance Effect (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . 6-25
Crew and Passenger Movement Balance Effect (Metric Units). . . . . . . . . . . . . . . . . . . . . . . 6-25
Principle Dimensions of Flight and Passenger Compartments . . . . . . . . . . . . . . . . . . . . . . . . 6-26
Crew and Passenger Weight and Moment Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-26
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-23/6-24
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
PERSONNEL
CREW AND PASSENGER ARRANGEMENT DIAGRAM
A diagram of crew and passenger seating arrangement and associated weight and balance moment
information is included in the Crew and Passenger Moment Sheets. See Figure 6-9, sheets 1 thru 6.
CREW AND PASSENGER MOVEMENT BALANCE EFFECT (U.S. UNITS)
To determine the change in moment resulting from crew or passenger movement, multiply the
person's weight (in pounds) by the difference (in inches) between the arm of the destination location
and the arm of the starting location. Use the following equation to calculate the change in moment:
ΔM = Wt(ARMD - ARMS)
Where:
ΔM = Change in moment
Wt = Weight of the person to be moved
ARMD = Arm of the person's destination location
ARMS = Arm of the person's starting location
NOTE
A negative number indicates a forward movement and a positive number indicates an
aft movement.
To determine the change in moment resulting from a seat adjustment, multiply the occupant's weight
(in pounds) by the distance (in inches) the seat is moved.
CREW AND PASSENGER MOVEMENT BALANCE EFFECT (METRIC UNITS)
To determine the change in moment resulting from crew or passenger movement multiply the
person's weight (in kilograms) by the difference (in millimeters) between the arm of the destination
location and the arm of the starting location. Use the following equation to calculate the change in
moment:
ΔM = Wt(ARMD - ARMS)
Where:
ΔM = Change in moment
Wt = Weight of the person to be moved
ARMD = Arm of the person's destination location
ARMS = Arm of the person's starting location
NOTE
A negative number indicates a forward movement and a positive number indicates an
aft movement.
To determine the change in moment resulting from a seat adjustment, multiply the occupant's weight
(in kilograms) by the distance (in millimeters) the seat is moved.
(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-25
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
MODEL 560XL
PERSONNEL (Continued)
PRINCIPLE DIMENSIONS OF FLIGHT AND PASSENGER COMPARTMENTS
Figure 6-8 (Sheets 1 and 2) presents the principle dimensions of flight and passenger compartments.
CREW AND PASSENGER WEIGHT AND MOMENT TABLES
Figure 6-9 (Sheets 1 thru 6) show the weight and moment tables and fuselage stations for the seats
in the standard and two optional seating configurations.
6-26
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
INTERIOR PRINCIPLE DIMENSIONS (U.S. UNITS)
Figure 6-8*. Interior Principle Dimensions (U.S. Units) (Sheet 1 of 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-27
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
MODEL 560XL
INTERIOR PRINCIPLE DIMENSIONS (METRIC UNITS)
Figure 6-8*. Interior Principle Dimensions (Metric Units) (Sheet 2)
6-28
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
Figure 6-9*. Crew and Passenger Moment (U.S. Units) (Sheet 1 of 6)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-29
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
MODEL 560XL
Figure 6-9*. Crew and Passenger Moment (Metric Units) (Sheet 2)
6-30
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
V
Figure 6-9*. Crew and Passenger Moment (U.S. Units) (Sheet 3)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-31
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
MODEL 560XL
V
Figure 6-9*. Crew and Passenger Moment (Metric Units) (Sheet 4)
6-32
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
V
Figure 6-9*. Crew and Passenger Moment (U.S. Units) (Sheet 5)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-33
SECTION VI - WEIGHT AND BALANCE DATA
PERSONNEL
MODEL 560XL
V
Figure 6-9*. Crew and Passenger Moment (Metric Units) (Sheet 6)
6-34
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
BAGGAGE AND STORAGE
TABLE OF CONTENTS
PAGE
BAGGAGE AND STORAGE
Baggage and Storage Compartments Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-37
Tailcone Baggage Compartment Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-37
Baggage and Cabinet Compartments Standard Weight and Moment Tables (U.S. Units). . . 6-37
Baggage and Cabinet Compartments Options 1 and 2
Weight and Moment Tables (Metric Units). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-37
Baggage Door Opening Dimensions (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-39
Baggage Door Opening Dimensions (Metric Units). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-39
Baggage Compartment Limits (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-39
Baggage Compartment Limits (Metric Units). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-39
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-35/6-36
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
BAGGAGE AND STORAGE
BAGGAGE AND STORAGE COMPARTMENTS DIAGRAM
Figure 6-10 (Sheet 1 of 3) presents data for baggage compartment locations in U.S. Units and
Metric Units.
TAILCONE BAGGAGE COMPARTMENT DIMENSIONS
Figure 6-10 Sheet 2 (U.S. Units) and Sheet 3 (Metric Units) presents data for tailcone baggage
compartment dimensions.
BAGGAGE DOOR OPENING DIMENSIONS
Figure 6-10 Sheet 2 (U.S. Units) and Sheet 3 (Metric Units) presents data for baggage door
openings. Page 6-38 presents data for the tailcone baggage door dimensions.
BAGGAGE COMPARTMENT LIMITS
Page 6-38 presents data for the tailcone baggage compartment capacity.
BAGGAGE AND CABINET COMPARTMENTS STANDARD WEIGHT AND MOMENT
TABLES
Figure 6-11 Sheet 1 (U.S. Units) and Sheet 2 (Metric Units) present data for baggage and storage
compartments for the standard configuration.
BAGGAGE AND CABINET COMPARTMENTS OPTIONS 1 AND 2 WEIGHT AND
MOMENT TABLES
Figure 6-11 Sheet 3 (U.S. Units) and Sheet 4 (Metric Units) present data for baggage and storage
compartments option 1 configuration.
Figure 6-11 Sheet 5 (U.S. Units) and Sheet 6 (Metric Units) present data for baggage and storage
compartments option 2 configuration.
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-37
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
MODEL 560XL
BAGGAGE DOOR OPENING DIMENSIONS
BAGGAGE DOOR OPENING DIMENSIONS (U.S. Units)
1.
2.
For baggage door opening dimensions, refer to Figure 6-10 (Sheet 2).
Baggage door opening dimensions are as follows:
a. Width - 34.00 inches.
b. Height (along contour) - 26.50 inches.
BAGGAGE DOOR OPENING DIMENSIONS (Metric Units)
1.
2.
For baggage door opening dimensions, refer to Figure 6-10 (Sheet 3).
Baggage door opening dimensions are as follows:
a. Width - 864 millimeters.
b. Height (along contour) - 673 millimeters.
BAGGAGE COMPARTMENT LIMITS
BAGGAGE COMPARTMENT LIMITS (U.S. Units)
The tailcone baggage compartment area total volume is 80 cubic feet with a maximum capacity of
700 pounds.
BAGGAGE COMPARTMENT LIMITS (Metric Units)
The tailcone baggage compartment area total volume is 2.3 cubic meters with a maximum capacity
of 317.50 kilograms.
STORAGE COMPARTMENT FLOOR LOADING LIMITS (U.S. Units)
The aft cabin storage floor loading limit is 120 pounds per square foot.
STORAGE COMPARTMENT FLOOR LOADING LIMITS (Metric Units)
The aft cabin storage floor loading limit is 585.90 kilograms per square meter.
6-38
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
BAGGAGE AND STORAGE COMPARTMENTS DIAGRAM
Figure 6-10*. Tailcone Baggage (Sheet 1 of 3)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-39
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
MODEL 560XL
TAILCONE BAGGAGE COMPARTMENTS DIMENSIONS (U.S. UNITS)
Figure 6-10*. Tailcone Baggage (U.S. Units) (Sheet 2)
6-40
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
TAILCONE BAGGAGE COMPARTMENTS DIMENSIONS (METRIC UNITS)
Figure 6-10*. Tailcone Baggage (Metric Units) (Sheet 3)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-41
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
MODEL 560XL
Figure 6-11*. Airplane Baggage and Storage Compartments (U.S. Units)
Standard Arrangement (Sheet 1 of 6)
6-42
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
Figure 6-11*. Airplane Baggage and Storage Compartments (Metric Units)
Standard Arrangement (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-43
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
MODEL 560XL
Figure 6-11*. Airplane Baggage and Storage Compartments (Metric Units)
Standard Arrangement (Sheet 3)
6-44
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
Figure 6-11*. Airplane Baggage and Storage Compartments (Metric Units)
Option 1 Arrangement (Sheet 4)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-45
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
MODEL 560XL
Figure 6-11*. Airplane Baggage and Storage Compartments (U.S. Units)
Option 2 Arrangement (Sheet 5)
6-46
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
BAGGAGE AND STORAGE
Figure 6-11*. Airplane Baggage and Storage Compartments (Metric Units)
Option 2 Arrangement (Sheet 6)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-47/6-48
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS - TABLE OF CONTENTS
GROUND OPERATIONS
TABLE OF CONTENTS
PAGE
GROUND OPERATIONS
Jack Point Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-51
Preparation and Weighing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Leveling and Weighing Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Preparation Prior to Weighing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Airplane Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Method 1: Leveling and Weighing on Jack Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-52
Method 2: Leveling and Weighing on Floor Scales. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-54
Weighing Comparison. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-55
Oleo Extension Measurements (Nose Landing Gear) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-56
Oleo Extension Measurements (Main Landing Gear). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-58
Airplane Weighing Form (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-60
Airplane Weighing Form (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-61
Lateral Moment of Wing Fuel (U.S. Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-62
Lateral Moment of Wing Fuel (Metric Units) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-63
Balance Limits for Normal Ground Loading Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-64
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-49/6-50
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS
JACK POINT LOCATIONS
Figure 6-13 presents jack point locations and maximum weight loads.
Figure 6-13*. Jack Point Locations and Maximum Weight Loads
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-51
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
MODEL 560XL
GROUND OPERATIONS (Continued)
PREPARATION AND WEIGHING
LEVELING AND WEIGHING METHODS
There are two methods to level and weigh the airplane: on jack points and on floor scales. Either of
the two methods can be used to measure the Basic Empty Weight and center of gravity for the Model
560 Citation XLS. For either method, first follow the Preparation Prior to Weighing and Airplane
Preparation procedures.
PREPARATION PRIOR TO WEIGHING
1.
2.
3.
4.
The weighing procedures should be accomplished with the airplane in a closed hangar (all
hangar doors closed), all fans off, and all air-handling equipment (HVAC equipment, etc.)
off.
Check the scale certification. Calibrate, zero and use the scales in accordance with the
scale manufacturer’s instructions. If chocks are used, zero the scales with the chocks on
the scales.
Defuel the airplane, including drainable unusable fuel through the drain valves on the lower
wing skin. Refer to Maintenance Manual, Chapter 12, Fuel -Servicing.
a. If the airplane is weighed after being defueled by the procedure outlined in the
Maintenance Manual, the drainable unusable fuel (Refer to Figure 6-4) should be
added to the “as weighed” condition. The fuel remaining in the airplane after defueling
is considered trapped fuel and is included in the Basic Empty Weight.
Thoroughly inspect the airplane for loose items, items out of place, and systems serviced.
AIRPLANE PREPARATION
1.
Check the following items and make note of overages and shortages on the airplane weigh
sheet:
a. Loose items such as tools, floor mats, spare parts, etc., should be removed.
b. All items out of place should be placed in their standard location.
c.
Crew seats should be tracked to mid-range position on the seat rails. All other seats
should be adjusted to the full forward (toward the airplane nose) position with the seat
back in the most vertical position and the seat belts crossed on the seat cushions.
d. The landing gear should be extended, the flaps retracted, and the control systems
locked in the neutral position.
e. Service the hydraulic system, fire extinguishers, oxygen, engine oil and brake
reservoir to the normally full level. No water should be in the refreshment center
reservoirs. Complete the Waste Removal and Recharge procedures to drain and fill
the serviceable toilet. Refer to Maintenance Manual, Chapter 12, Externally
Serviceable Flush Toilet - Servicing.
METHOD 1: LEVELING AND WEIGHING ON JACK POINTS
1.
2.
3.
6-52
Position the jacks, scales, and jack pads under the jack points of the airplane.
Check the scale certification, calibrate, zero, and use the scales in accordance with the
scale manufacturer’s instructions.
Raise the airplane on jacks. Refer to Maintenance Manual, Chapter 7, Lifting and Shoring.
(Continued Next Page)
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS (Continued)
PREPARATION AND WEIGHING (Continued)
METHOD 1: LEVELING AND WEIGHING ON JACK POINTS (Continued)
4.
Level the airplane.
NOTE
Always level the airplane laterally first.
a.
b.
To level the airplane laterally, attach a leveling bar in the aft most pinhole across the
inboard crew seat rails at FS 154.00 (3912 mm). Make sure the leveling bar is parallel
to the fuselage station plane and rests solidly on the seat rails. Position the leveling
tool on the leveling bar with the base parallel to the long axis of the leveling bar. Refer
to the Maintenance Manual, Chapter 8, Leveling - Maintenance Practices. Adjust the
main gear jacks to level the airplane.
To level longitudinally, put a leveling bar across the aft inboard crew seat rails at FS
154.00 (3912 mm). Make sure the leveling bar is perpendicular to the fuselage station
plane and is firmly on the leveling bar. Position the leveling tool on the leveling bar with
its base perpendicular to the long axis of the leveling bar at BL 0.00. Adjust the nose
gear jack to level the airplane.
NOTE
To level longitudinally using a long base bubble level, loosen and pull back the carpet
in the threshold of the cabin entrance door to expose the outboard floor panel parallel
to the BL plane. Adjust the nose gear jack to level the airplane.
5.
6.
Remove the drainable unusable fuel.
Weigh the airplane:
a. Record each scale reading.
b. Lower the airplane. Refer to the Maintenance Manual, Chapter 7, Lifting and Shoring.
c.
Check for scale drift.
NOTE
Scale drift is the difference in scale reading between the zero value that is adjusted
before each weighing and the value indicated after the weighing procedure. Weigh
the airplane again if any scale reading shows a scale drift of >5.0 pounds after the
weighing procedure.
d.
e.
Calculate weight including scale drift, scale correction, and overages and shortages.
Locate the longitudinal center-of-gravity and percent MAC. Refer to Figure 6-15 (Sheet
1 for U.S. Units) or (Sheet 2 for Metric Units) for required formulas.
NOTE
The center of gravity is sensitive to leveling the airplane correctly.
(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-53
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS (Continued)
PREPARATION AND WEIGHING (Continued)
METHOD 2: LEVELING AND WEIGHING ON FLOOR SCALES
1.
2.
3.
Position the airplane in front of or behind the floor scales so that the airplane can be pushed
or pulled on to them.
Check the scale certification. Calibrate, zero, and use the scales in accordance with the
scale manufacturer’s instructions. If chocks are used, zero the scales with the chocks on
the scales.
Roll the airplane onto the floor scales.
NOTE
Centering the landing gear on the plates of the scales is not necessary, but full contact
with the scale surface is necessary.
4.
5.
Put the chocks around the nose landing gear (NLG) to prevent the airplane from rolling off
the scales. Do not set the parking brake. Remove the tow bar from the nose landing gear.
Level the airplane:
NOTE
Always level the airplane laterally first.
a.
b.
To level the airplane laterally, attach a leveling bar in the aft most pinhole across the
inboard crew seat rails at FS 154.00 (3912 mm). Make sure the leveling bar is parallel
to the fuselage station plane and rests solidly on the seat rails. Position the leveling
tool on the leveling bar with the base parallel to the long axis of the leveling bar. Refer
to the Maintenance Manual, Chapter 8, Leveling - Maintenance Practices. Adjust the
main gear jacks to level the airplane.
To level longitudinally, put a leveling bar across the aft inboard crew seat rails at FS
154.00 (3912 mm). Make sure the leveling bar is perpendicular to the fuselage station
plane and is firmly on the leveling bar. Position the leveling tool on the leveling bar with
its base perpendicular to the long axis of the leveling bar at BL 0.00. Adjust the nose
gear jack to level the airplane.
NOTE
To level longitudinally using a long base bubble level, loosen and pull back the carpet
in the threshold of the cabin entrance door to expose the outboard floor panel parallel
to the BL plane. Adjust the nose gear jack to level the airplane.
6.
7.
8.
Remove the drainable unusable fuel.
Accurately measure the oleo lengths. Refer to Figure 6-14 (Sheets 1 thru 4). Measure the
distance between the underside of the upper barrel and the topside of the lower cap (MLG)
or the topside of the fork (NLG). (Measure the shiny portion of the oleo).
Record the measured oleo lengths on the Airplane Weighing Form.
(Continued Next Page)
6-54
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS (Continued)
METHOD 2: LEVELING AND WEIGHING ON FLOOR SCALES (Continued)
9.
Weigh the airplane:
a. Record each scale reading.
b. Remove the airplane from the floor scales.
c.
Check the scale drift.
NOTE
Scale drift is the difference in scale reading between the zero value that is adjusted
before each weighing and the value indicated after the weighing procedure. Weigh
the airplane again if any scale reading shows a scale drift of >5.0 pounds after the
weighing procedure.
d.
e.
f.
Check for scale correction in the calibration record.
Calculate weight including scale drift, scale correction, and overages and shortages.
Calculate the center of gravity using Nose Landing Gear and Main Landing Gear
center-of-gravity locations. Refer to Figure 6-15 (Sheet 1 for U.S. Units) or (Sheet 2
for Metric Units) for required formulas.
NOTE
The center of gravity is sensitive to correct leveling.
WEIGHING COMPARISON
1.
2.
If the weight and center of gravity do not appear to be correct, based on the last weight or
continuous history, do the following steps:
a. lower the airplane, if on jacks,
b. remove the scales or load cells,
c.
rotate all three scales clockwise, and
d. weigh the airplane again.
To constitute as a good weighing, the Model 560 XLS weight and center-of-gravity
differences after the weighings must be less than the following:
a. total weight +/-120 pounds, and
b. center of gravity +/-0.5 inch.
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-55
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
MODEL 560XL
OLEO EXTENSION MEASUREMENTS
Figure 6-14*. Oleo Extensions (U.S. Units) (Sheet 1 of 4)
6-56
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
OLEO EXTENSION MEASUREMENTS (Continued)
Figure 6-14*. Oleo Extensions (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-57
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
MODEL 560XL
OLEO EXTENSION MEASUREMENTS (Continued)
Figure 6-14* Oleo Extensions (U.S. Units) (Sheet 3)
6-58
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
OLEO EXTENSION MEASUREMENTS (Continued)
Figure 6-14*. Oleo Extensions (Metric Units) (Sheet 4)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-59
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
MODEL 560XL
Figure 6-15*. Locating CG of Airplane (U.S. Units) (Sheet 1 of 2)
6-60
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
Figure 6-15*. Locating CG of Airplane (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-61
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS (Continued)
LATERAL MOMENT OF WING FUEL (U.S. Units)
Figure 6-16 (Sheet 1) presents data for the lateral moment in 200-pound increments for the left or
right wing fuel tanks.
NOTE
For asymmetric fuel differential limitations, refer to the basic FAA Approved Airplane
Flight Manual - Operating Limitations.
CAUTION
MAXIMUM ASYMMETRIC FUEL LOADING SHALL NOT EXCEED 400
POUNDS FOR TAKEOFF.
NOTE
There is no restriction for asymmetric fuel loading during normal refueling operations.
Refer to the FAA Approved Flight Manual - Operating Limitations.
Figure 6-16*. Lateral Moment of Wing Fuel Tanks (U.S. Units) (Sheet 1 of 2)
6-62
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
GROUND OPERATIONS (Continued)
LATERAL MOMENT OF WING FUEL (Metric Units)
Figure 6-16 (Sheet 2) presents data for the lateral moment in 100 Kilogram increments for the left or
right wing fuel tanks.
NOTE
For asymmetric fuel differential limitations, refer to the basic FAA Approved Airplane
Flight Manual - Operating Limitations.
CAUTION
MAXIMUM ASYMMETRIC FUEL LOADING SHALL NOT EXCEED 181
KILOGRAMS (kg) FOR TAKEOFF.
NOTE
There is no restriction for asymmetric fuel loading during normal refueling operations.
Refer to the FAA Approved Flight Manual - Operating Limitations.
Figure 6-16*. Lateral Moment of Wing Fuel Tanks (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-63
SECTION VI - WEIGHT AND BALANCE DATA
GROUND OPERATIONS
MODEL 560XL
GROUND OPERATIONS (Continued)
BALANCE LIMITS FOR NORMAL GROUND LOADING
OPERATIONS
There are no balance limits for normal ground loading operations. For example, one wing fuel tank
can be completely filled prior to adding fuel to the opposite wing fuel tank.
6-64
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES - TABLE OF CONTENTS
EXAMPLES
TABLE OF CONTENTS
PAGE
EXAMPLES
General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-67
Sample Loading Problem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-67
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-65/6-66
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
EXAMPLES
GENERAL
The contribution that any loading item makes to a shift in the airplane’s center of gravity depends on
its distance from the airplane’s Basic Empty Weight center of gravity. Any weight placed in the aft
baggage compartment will shift the center of gravity aft since it is aft of the typical Basic Empty
Weight center of gravity.
Adding fuel or passengers will shift the center of gravity forward since they are forward of the typical
Basic Empty Weight center of gravity. The exception is the addition of a passenger on the aft sidefacing seat or belted toilet; these seats are aft of the typical Basic Empty Weight center of gravity.
The magnitude of the shift for any given weight is proportional to the length of the moment arm from
the center of gravity.
SAMPLE LOADING PROBLEM
The following step-by-step procedure illustrates a logical manner in which to determine the takeoff
weight and center of gravity. Loading tables can be found in this manual and in the Weight and
Balance Data Sheets. Loading data is also available for computerized calculation in the CLCALC
application as part of the CESNAV software package.
The Example Center-of-Gravity Limits Envelope Graph (Figure 6-18) is an example plot of the fuel
burn calculated from the Example Weight and Balance Computation Form (Figures 6-17).
NOTE
For the purpose of this sample problem weights are rounded to the nearest whole
pound and moment index to two (2) decimal places for entry on the Example Weight
and Balance Computation form.
1.
2.
3.
4.
5.
6.
Enter the Basic Empty Weight, moment index (moment/100 for U.S. Units or moment/1000
for Metric Units) and center of gravity as weighed from the Airplane Weighing Form on line 1
BASIC EMPTY WEIGHT of the Example Weight and Balance Computation Form (See
Figure 6-17).
Determine the moment index for each crew member and passenger using the Crew and
Passenger Weight and Moment Tables (See Figure 6-9). Enter the weight and moment
index for each person on the PAYLOAD COMPUTATIONS side of the Weight and Balance
computation Form.
Determine the moment index for any cabinet contents using the Baggage and Cabinet
Compartments Standard Weight and Moment Tables (See Figures 6-12). Enter the weight
and moment index on the PAYLOAD COMPUTATIONS side of the Weight and Balance
Computation Form.
Determine the moment index for baggage loading in the tailcone compartment using the
Baggage and Cabinet Compartments Standard Weight and Moment Tables (Figure 6-12).
Enter the weight and moment index on the PAYLOAD COMPUTATIONS side of the Weight
and Balance Computation Form.
Total the weights and moment indices of the payload items at the bottom of the PAYLOAD
COMPUTATIONS side of the Weight and Balance computation form and enter these values
on line 2 PAYLOAD of the Weight and Balance Computation Form.
Enter the sums of the values on lines 1 and 2 onto line 3 ZERO FUEL WEIGHT of the
Weight and Balance Computation Form.
(Continued Next Page)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-67
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
EXAMPLES (Continued)
SAMPLE LOADING PROBLEM (Continued)
7.
8.
Divide the zero fuel moment index by the zero fuel weight and multiply by 100 (1000) to
determine the zero fuel weight center of gravity.
Check the zero fuel weight and center of gravity by locating them on the Example Center-ofGravity Limits Envelope Graph (see Figure 6-18).
NOTE
Approved points are located inside the envelope below the maximum zero fuel weight
line.
9.
Look up the weight of fuel to be used for the flight and the corresponding moment index in
the Fuel Loading Table (see Figure 6-3). Enter the weight and moment index on line 4 FUEL
LOADING of the Weight and Balance Computation Form.
10. Enter the sums of the values on line 3 and line 4 onto line 5 RAMP WEIGHT of the Weight
and Balance computation Form.
11. Divide the ramp moment index by the ramp weight and multiply by 100 (1000) to determine
the ramp weight center of gravity.
12. Check the ramp weight and center of gravity by locating them on the Example Center-ofGravity Limits Envelope Graph (see Figure 6-18).
NOTE
Approved points are located inside the envelope below the maximum ramp weight
line.
13. Enter the taxi fuel weight and moment index on line 6 LESS FUEL FOR TAXIING of the
Weight and Balance Computation Form. A standard 200 pound (91 kilogram) burn-off is
assumed. The moment index for taxi is the difference between the moment index of the fuel
loaded and the moment index of the fuel remaining on board after taxi.
14. Enter the differences between the values on lines 5 and 6 onto the line TAKEOFF WEIGHT
of the Weight and Balance Computation Form.
15. Divide the takeoff moment index by the Takeoff Weight and multiply by 100 (1000) to
determine the takeoff center of gravity. Enter the takeoff center of gravity on line 7 of the
Weight and Balance Computation Form.
16. Check the takeoff weight and center of gravity by locating them on the Example Center-ofGravity Limits Envelope Graph (see Figure 6-18).
NOTE
Approved points are located inside the envelope below the maximum takeoff weight
line.
17. Determine the estimated weight of the fuel to be used in flight. The moment index of the fuel
used in flight is the difference between the moment index of the fuel remaining after taxi and
the moment index of the fuel remaining after reaching the destination.
18. Enter the weight and moment index of the fuel used in flight on line 8 LESS FUEL TO
DESTINATION of the Weight and Balance Computation Form.
19. Enter the differences between the values on lines 7 and 8 onto line 9 LANDING WEIGHT of
the Weight and Balance Computation Form.
(Continued Next Page)
6-68
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
EXAMPLES (Continued)
SAMPLE LOADING PROBLEM (Continued)
20. Divide the landing moment index by the landing weight and multiply by 100 (1000) to
determine the landing center of gravity. Enter the landing center of gravity on line 9 of the
Weight and Balance Computation Form.
21. Check the landing weight and center of gravity by locating them on the Example Center-ofGravity Limits Envelope Graph (see Figure 6-18).
NOTE
Approved points are located inside the envelope below the Maximum Landing Weight
line.
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-69
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
MODEL 560XL
Figure 6-17*. Example Weight and Balance Computation Form (U.S. Units) (Sheet 1 of 2)
6-70
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
Figure 6-17*. Example Weight and Balance Computation Form (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-71
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
MODEL 560XL
Figure 6-18*. Center-of-Gravity Limits Envelope (U.S. Units) (Sheet 1 of 2)
6-72
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
FAA APPROVED
56XWBA-02
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
EXAMPLES
Figure 6-18*. Example Center-of-Gravity Limits Envelope (Metric Units) (Sheet 2)
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-73/6-74
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
AIRPLANE REPORTS - TABLE OF CONTENTS
AIRPLANE REPORTS
TABLE OF CONTENTS
PAGE
AIRPLANE REPORTS
Equipment List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-77/6-78
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-75/6-76
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL
SECTION VI - WEIGHT AND BALANCE DATA
AIRPLANE REPORTS
AIRPLANE REPORTS
EQUIPMENT LIST
For installed equipment, refer to Installed Equipment List furnished with airplane papers.
FAA APPROVED
56XWBA-02
Configuration AA
Printed 08.10.15 12:47. Document Revision ---
6-77/6-78
Printed 08.10.15 12:47. Document Revision ---
WEIGHT AND
BALANCE DATA
MODEL 560XL (560-5501 THRU -6000)
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
AIRPLANE WEIGHING FORM
REFERENCE
DATUM
300
250
MAC
82.23
306.59
FS 215.00
200
150
100
NOSE JACK POINT
(FS 130.35)
230.28
A
B
360.63
50
0
0
50
100
150
200
WING JACK POINT
(FS 360.63)
450
300
350
400
250
FUSELAGE STATION (FS) - INCHES
500
NOTE
IT IS THE RESPONSIBILITY OF THE
PILOT TO MAKE SURE THAT THE
AIRPLANE IS LOADED PROPERLY.
550
600
650
700
LOCATING CG WITH AIRPLANE ON LANDING GEAR
LEGEND
DIMENSION A =
Horizontal distance from center of main landing gear axle to center of nose landing gear axle (determined by measurement
after airplane is level on scales).
DIMENSION B = Horizontal distance from reference datum to center of main landing gear axle. Obtain this distance by measuring from nose
jack point FS 130.35 to center of nose landing gear axle and subtracting this value from diminsion A and adding to
FS 130.35. (Must be measured after airplane is level on scales.)
FORMULA for Longitudinal CG
(Dimension A) X (Nose Landing
Inches
CG Arm of
Gear Net Weight)(
)
= (
) Aft of
= (Dimension B) Airplane
Nose and Main Landing Gear
Datum
Weight Totaled (
)
LEVELING PROVISIONS
LOCATING CG WITH AIRPLANE ON JACK PADS
FORMULA for Longitudinal CG
230.28 X (Nose Jack Point
Net Weight)(
)
CG Arm of
= 360.63 Airplane
Nose and Wing Jack Point
Weight Totaled (
)
=
(
)
AIRPLANE AS WEIGHED TABLE
POSITION
LOCATING PERCENT MAC
FORMULA for Percent MAC
CG Percent MAC =
(CG Arm of Airplane) - 306.59
0.8223
Inches
Aft of
Datum
LONGITUDINAL - INBOARD SEAT TRACKS
CENTER LEVEL OVER FS 215.00
LATERAL - INBOARD SEAT TRACKS
AT FS 215.00
SCALE READING
SCALE DRIFT
TARE
NET WEIGHT
LEFT WING
RIGHT WING
NOSE
AIRPLANE TOTAL AS WEIGHED
BASIC EMPTY WEIGHT AND CENTER-OF-GRAVITY TABLE
ITEM
AIRPLANE (CALCULATED OR AS WEIGHED)
(INCLUDES ALL UNDRAINABLE FLUIDS AND FULL OIL)
DRAINABLE UNUSABLE FUEL AT 6.75 POUNDS PER GALLON
WEIGHT
(POUNDS)
31.80
CG ARM
(INCHES)
333.46
MOMENT
(INCH-POUNDS/100)
106.04
BASIC EMPTY WEIGHT
CESSNA AIRCRAFT COMPANY, AIRCRAFT DIVISION, P.O. BOX 7704, WICHITA, KANSAS 67277
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2157, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
WEIGHT AND
BALANCE DATA
MODEL 560XL (560-5501 THRU -6000)
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
AIRPLANE WEIGHING FORM
REFERENCE
DATUM
7620
6350
MAC
2089
7787
FS 5861
5080
3810
2540
NOSE JACK POINT
(FS 3311)
5849
A
B
9160
1270
0
0
1270
2540
3810
5080
NOTE
WING JACK POINT
(FS 9160)
IT IS THE RESPONSIBILITY OF THE
PILOT TO MAKE SURE THAT THE
AIRPLANE IS LOADED PROPERLY.
7620
8890 10160 11430 12700
6350
FUSELAGE STATION (FS) - MILLIMETERS
13970
15240
16510 17780
LOCATING CG WITH AIRPLANE ON LANDING GEAR
LEGEND
DIMENSION A =
Horizontal distance from center of main landing gear axle to center of nose landing gear axle (determined by measurement
after airplane is level on scales).
DIMENSION B = Horizontal distance from reference datum to center of main landing gear axle. Obtain this distance by measuring from nose
jack point FS 3311 to center of nose landing gear axle and subtracting this value from diminsion A and adding to
FS 3311. (Must be measured after airplane is level on scales.)
FORMULA for Longitudinal CG
(Dimension A) X (Nose Landing
mm
CG Arm of
Gear Net Weight)(
)
= (
) Aft of
= (Dimension B) Airplane
Nose and Main Landing Gear
Datum
Weight Totaled (
)
LEVELING PROVISIONS
LOCATING CG WITH AIRPLANE ON JACK PADS
FORMULA for Longitudinal CG
5849 X (Nose Jack Point
Net Weight)(
)
CG Arm of
= 9160 Airplane
Nose and Wing Jack Point
Weight Totaled (
)
=
(
)
FORMULA for Percent MAC
CG Percent MAC =
(CG Arm of Airplane) - 7787
20.89
mm
Aft of
Datum
AIRPLANE AS WEIGHED TABLE
POSITION
LOCATING PERCENT MAC
LONGITUDINAL - INBOARD SEAT TRACKS
CENTER LEVEL OVER FS 5461
LATERAL - INBOARD SEAT TRACKS
AT FS 5461
SCALE READING
SCALE DRIFT
TARE
NET WEIGHT
LEFT WING
RIGHT WING
NOSE
AIRPLANE TOTAL AS WEIGHED
BASIC EMPTY WEIGHT AND CENTER-OF-GRAVITY TABLE
ITEM
AIRPLANE (CALCULATED OR AS WEIGHED)
(INCLUDES ALL UNDRAINABLE FLUIDS AND FULL OIL)
DRAINABLE UNUSABLE FUEL AT .81 KILOGRAMS PER LITER
WEIGHT
(KILOGRAMS)
14.44
CG ARM
(MILLIMETERS)
8470
MOMENT
(MM-KGS/1000)
122.31
BASIC EMPTY WEIGHT
CESSNA AIRCRAFT COMPANY, AIRCRAFT DIVISION, P.O. BOX 7704, WICHITA, KANSAS 67277
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2158, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CENTER-OF-GRAVITY LIMITS ENVELOPE GRAPH
21
FORWARD CG LIMIT
FS 324.29 INCHES, 21.52% MAC
MAXIMUM RAMP WEIGHT - 20,400 POUNDS
20
MAXIMUM TAKEOFF
WEIGHT 20,200 POUNDS
19
17
AFT CG
LIMIT
15,000
POUNDS
16
15
MAXIMUM ZERO FUEL WEIGHT - 15,100 POUNDS
13
12
11
10
316
12
318
14
AFT CG LIMIT
FS 331.26 INCHES, 30% MAC
14
FORWARD CG LIMIT
FS 318.92 INCHES, 15 % MAC
WEIGHT (POUNDS X 1000)
17,800 POUNDS
FS 330.74
INCHES
29.37% MAC
MAXIMUM LANDING
WEIGHT 18,700 POUNDS
18
AFT CG LIMIT
FS 330.74
INCHES, 29.37%
MAC
FORWARD CG
LIMIT 11,500 POUNDS
320
322
324
326
328
CENTER OF GRAVITY (INCHES)
16
18
20
22
24
26
330
28
332
30
334
32
CENTER OF GRAVITY - PERCENT MAC
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2159, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
WEIGHT AND
BALANCE DATA
MODEL 560XL (560-5501 THRU -6000)
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CENTER-OF-GRAVITY LIMITS ENVELOPE GRAPH
10
SI
FORWARD CG LIMIT
FS 8237 mm, 21.52% MAC
MAXIMUM RAMP WEIGHT - 9253 KG
MAXIMUM TAKEOFF
WEIGHT 9163 KG
MAXIMUM LANDING
WEIGHT 8482 KG
8074 KG
FS 8400 mm
29.37% MAC
8
AFT CG
LIMIT
6804 KG
7
6
5
80
81
11
13
15
AFT CG LIMIT
FS 8414 mm, 30% MAC
MAXIMUM ZERO FUEL WEIGHT - 6849 KG
FORWARD CG LIMIT
FS 8101 mm, 15 % MAC
WEIGHT (KILOGRAMS X 1000)
9
AFT CG LIMIT
FS 8401 mm
29.37% MAC
FORWARD CG
LIMIT 5216 KG
82
83
84
CENTER OF GRAVITY (MILLIMETER X 100)
17
19
21
23
25
27
29
85
31
33
CENTER OF GRAVITY - PERCENT MAC
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2160, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
WEIGHT AND
BALANCE DATA
MODEL 560XL (560-5501 THRU -6000)
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
STANDARD CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
WEIGHT
(POUNDS)
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
SEAT 1
OR
SEAT 2
ARM = FS
136.32 in.
68.16
81.79
95.42
109.06
122.69
136.32
149.95
163.58
177.22
190.85
204.48
218.11
231.74
245.38
259.01
272.64
286.27
299.90
313.54
327.17
340.80
354.43
368.06
381.70
395.33
408.96
422.59
436.22
449.86
463.49
SEAT 3
OR
SEAT 4
ARM = FS
234.39 in.
117.20
140.63
164.07
187.51
210.95
234.39
257.83
281.27
304.71
328.15
351.59
375.02
398.46
421.90
445.34
468.78
492.22
515.66
539.10
562.54
585.98
609.41
632.85
656.29
679.73
703.17
726.61
750.05
773.49
796.93
SEAT 5
OR
SEAT 6
ARM = FS
286.54 in.
143.27
171.92
200.58
229.23
257.89
286.54
315.19
343.85
372.50
401.16
429.81
458.46
487.12
515.77
544.43
573.08
601.73
630.39
659.04
687.70
716.35
745.00
773.66
802.31
830.97
859.62
888.27
916.93
945.58
974.24
MOMENT/100
SEAT 7
SEAT
OR
10
SEAT 8
FWD
ARM = FS ARM = FS
322.62 in. 181.24 in.
161.31
90.62
193.57
108.74
225.83
126.87
258.10
144.99
290.36
163.12
322.62
181.24
354.88
199.36
387.14
217.49
419.41
235.61
451.67
253.74
483.93
271.86
516.19
289.98
548.45
308.11
580.72
326.23
612.98
344.36
645.24
362.48
677.50
380.60
709.76
398.73
742.03
416.85
774.29
434.98
806.55
453.10
838.81
471.22
871.07
489.35
903.34
507.47
935.60
525.60
967.86
543.72
1000.12
561.84
1032.38
579.97
1064.65
598.09
1096.91
616.22
SEAT
10
AFT
ARM = FS
205.60 in.
102.80
123.36
143.92
164.48
185.04
205.60
226.16
246.72
267.28
287.84
308.40
328.96
349.52
370.08
390.64
411.20
431.76
452.32
472.88
493.44
514.00
534.56
555.12
575.68
596.24
616.80
637.36
657.92
678.48
699.04
LH
SFS
ARM = FS
357.99 in.
179.00
214.79
250.59
286.39
322.19
357.99
393.79
429.59
465.39
501.19
536.99
572.78
608.58
644.38
680.18
715.98
751.78
787.58
823.38
859.18
894.98
930.77
966.57
1002.37
1038.17
1073.97
1109.77
1145.57
1181.37
1217.17
FS 136.32
1
2
FS 181.24
10
FS 205.60
FS 234.39
3
4
5
6
7
8
FS 286.54
FS 322.62
FS 234.39
FS 286.54
FS 322.62
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS 357.99
Printed 08.10.15 12:47. Document Revision ---
T
FORM NUMBER 2161, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (METRIC UNITS)
STANDARD CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
WEIGHT
(KGS)
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
145
150
154
SEAT 1
OR
SEAT 2
Arm= F.S.
3463 mm
SEAT 3
OR
SEAT 4
Arm= F.S.
5954 mm
SEAT 5
OR
SEAT 6
Arm= F.S.
7278 mm
69.26
86.58
103.89
121.21
138.52
155.84
173.15
190.47
207.78
225.10
242.41
259.73
277.04
294.36
311.67
328.99
346.30
363.62
380.93
398.25
415.56
432.88
450.19
467.51
484.82
502.14
519.45
533.30
119.08
148.85
178.62
208.39
238.16
267.93
297.70
327.47
357.24
387.01
416.78
446.55
476.32
506.09
535.86
565.63
595.40
625.17
654.94
684.71
714.48
744.25
774.02
803.79
833.56
863.33
893.10
916.92
145.56
181.95
218.34
254.73
291.12
327.51
363.90
400.29
436.68
473.07
509.46
545.85
582.24
618.63
655.02
691.41
727.80
764.19
800.58
836.97
873.36
909.75
946.14
982.53
1018.92
1055.31
1091.70
1120.81
MOMENT/1000
SEAT 7
SEAT
OR
10
SEAT 8
FWD
Arm= F.S.
Arm= F.S.
8195 mm
4603 mm
163.90
204.88
245.85
286.83
327.80
368.78
409.75
450.73
491.70
532.68
573.65
614.63
655.60
696.58
737.55
778.53
819.50
860.48
901.45
942.43
983.40
1024.38
1065.35
1106.33
1147.30
1188.28
1229.25
1262.03
92.06
115.08
138.09
161.11
184.12
207.14
230.15
253.17
276.18
299.20
322.21
345.23
368.24
391.26
414.27
437.29
460.30
483.32
506.33
529.35
552.36
575.38
598.39
621.41
644.42
667.44
690.45
708.86
SEAT
10
AFT
Arm= F.S.
5222 mm
LH
SFS
Arm= F.S.
9093 mm
104.44
130.55
156.66
182.77
208.88
234.99
261.10
287.21
313.32
339.43
365.54
391.65
417.76
443.87
469.98
496.09
522.20
548.31
574.42
600.53
626.64
652.75
678.86
704.97
731.08
757.19
783.30
804.19
181.86
227.33
272.79
318.26
363.72
409.19
454.65
500.12
545.58
591.05
636.51
681.98
727.44
772.91
818.37
863.84
909.30
954.77
1000.23
1045.70
1091.16
1136.63
1182.09
1227.56
1273.02
1318.49
1363.95
1400.32
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS
3463
1
2
FS
4603
10
FS
5222
FS
5954
3
4
5
6
7
8
FS
7278
FS
8195
FS
9093
Printed 08.10.15 12:47. Document Revision ---
FS
5954
FS
7278
FS
8195
T
FORM NUMBER 2162, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
STANDARD CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(POUNDS)
5
10
15
MOMENT/100
NAVIGATION
CHART CASE
ARM = FS
158.10 in.
7.91
15.81
23.72
RH FORWARD
CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
56
MOMENT/100
FORWARD
CLOSET
ARM =
FS 166.38 in.
8.32
16.64
24.96
33.28
41.60
49.91
58.23
66.55
74.87
83.19
93.17
LH
REFRESHMENT
CENTER
WEIGHT
(POUNDS)
10
20
30
40
50
60
70
80
90
100
110
120
130
141
MOMENT/100
REFRESHMENT
CENTER
ARM =
FS 173.20 in.
17.32
34.64
51.96
69.28
86.60
103.92
121.24
138.56
155.88
173.20
190.52
207.84
225.16
244.21
AFT CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
55
60
65
68
MOMENT/100
AFT
CLOSET
ARM =
FS 374.00 in.
18.70
37.40
56.10
74.80
93.50
112.20
130.90
149.60
168.30
187.00
205.70
224.40
243.10
254.32
1
FS 158.10
20
40
60
80
100
120
140
160
180
200
220
240
260
280
300
320
340
360
380
400
420
440
460
480
500
520
540
560
580
600
620
640
660
680
700
MOMENT/100
TAILCONE
COMPARTMENT
ARM = FS
431.00 in.
86.20
172.40
258.60
344.80
431.00
517.20
603.40
689.60
775.80
862.00
948.20
1034.40
1120.60
1206.80
1293.00
1379.20
1465.40
1551.60
1637.80
1724.00
1810.20
1896.40
1982.60
2068.80
2155.00
2241.20
2327.40
2413.60
2499.80
2586.00
2672.20
2758.40
2844.60
2930.80
3017.00
FS 166.38
FS 172.10
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(POUNDS)
2
3
4
5
6
7
8
T
FS 374.00
FS 431.00
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2163, 22 March 2004
REVISION 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENT
WEIGHT AND MOMENT TABLES (METRIC UNITS)
STANDARD CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(KGS)
2
4
6
7
MOMENT/1000
NAVIGATION
CHART CASE
ARM =
FS 4016 mm
8.03
16.06
24.10
28.11
RH FORWARD
CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
25
MOMENT/1000
FORWARD
CLOSET
ARM =
FS 4226 mm
9.58
16.90
25.36
33.81
42.26
50.71
59.16
67.62
76.07
84.52
92.97
101.42
105.65
LH
REFRESHMENT
CENTER
WEIGHT
(KGS)
5
10
15
20
25
30
35
40
45
50
55
60
64
MOMENT/1000
REFRESHMENT
CENTER
ARM =
FS 4399 mm
19.95
43.99
65.99
87.98
109.98
131.97
153.97
175.96
197.96
219.95
241.95
263.94
281.54
AFT CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
31
MOMENT/1000
AFT
CLOSET
ARM =
FS 9500 mm
21.55
38.00
57.00
76.00
95.00
114.00
133.00
152.00
171.00
190.00
209.00
228.00
247.00
266.00
285.00
294.50
1
FS 4016
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
318
MOMENT/1000
TAILCONE
COMPARTMENT
ARM =
FS 10947 mm
109.47
218.94
328.41
437.88
547.35
656.82
766.29
875.76
985.23
1094.70
1204.17
1313.64
1423.11
1532.58
1642.05
1751.52
1860.99
1970.46
2079.93
2189.40
2298.87
2408.34
2517.81
2627.28
2736.75
2846.22
2955.69
3065.16
3174.63
3284.10
3393.57
3481.15
FS 4226
FS 4399
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(KGS)
2
3
4
5
6
7
8
T
FS 9500
FS 10,947
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2164, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
FUEL LOADING WEIGHT AND MOMENT TABLE (U.S. UNITS)
WING TANK FUEL
WEIGHT
(POUNDS)
100
200
300
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
3100
3200
3300
3400
MOMENT/100
ARM VARIES
(INCH-POUNDS)
347.51
695.02
1030.04
1356.72
1687.35
2014.57
2338.36
2658.73
2983.62
3306.85
3628.42
3948.34
4272.49
4595.89
4918.53
5240.43
5565.39
5890.05
6214.40
6538.46
6864.94
7191.38
7517.77
7844.12
8170.98
8497.84
8824.70
9151.56
9478.60
9805.65
10132.72
10459.80
10787.22
11114.67
WING TANK FUEL (CONTINUED)
WEIGHT
(POUNDS)
3500
3600
3700
3800
3900
4000
4100
4200
4300
4400
4500
4600
4700
4800
4900
5000
5100
5200
5300
5400
5500
5600
5700
5800
5900
6000
6100
6200
6300
6400
6500
6600
6700
6790
MOMENT/100
ARM VARIES
(INCH-POUNDS)
11442.15
11769.66
12097.61
12425.61
12753.67
13081.78
13410.41
13739.12
14067.91
14396.77
14726.26
15055.84
15385.53
15715.32
16046.52
16377.88
16709.40
17041.07
17374.80
17708.76
18042.94
18377.36
18712.41
19047.71
19383.26
19719.04
20054.19
20389.55
20725.12
21060.91
21396.48
21732.25
22067.29
22369.55
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2165, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
FUEL LOADING WEIGHT AND MOMENT TABLE (METRIC UNITS)
WING TANK FUEL
WEIGHT
(KILOGRAMS)
MOMENT/1000
ARM VARIES
(MM-KILOGRAMS)
100
200
300
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
3079.37
878.04
1716.81
2546.76
3366.05
4184.59
5002.92
5822.16
6644.86
7467.93
8296.06
9124.52
9954.07
10783.77
11613.83
12444.37
13275.48
14107.47
14940.07
15774.01
16608.62
17445.03
18282.80
19123.83
19967.79
20815.66
21665.44
22516.96
23368.04
24219.86
25071.73
25747.35
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2166, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
LATERAL MOMENT OF WING FUEL (U.S. UNITS)
LEFT WING FUEL TANK
RIGHT WING FUEL TANK
Fuel
Weight
(Pounds)
Lateral
Moment/100
Arm Varies
(in-lbs)
Fuel
Weight
(Pounds)
Lateral
Moment/100
Arm Varies
(in-lbs)
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
3395
26.39
73.28
134.84
219.28
325.06
454.56
605.55
776.70
965.98
1171.93
1393.37
1631.89
1897.90
2207.58
2567.72
2982.54
3450.35
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
3395
26.39
73.28
134.84
219.28
325.06
454.56
605.55
776.70
965.98
1171.93
1393.37
1631.89
1897.90
2207.58
2567.72
2982.54
3450.35
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2167, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
LATERAL MOMENT OF WING FUEL (METRIC UNITS)
LEFT WING FUEL TANK
RIGHT WING FUEL TANK
Fuel
Weight
(Kilograms)
Lateral
Moment/1000
Arm Varies
(mm-kgs)
Fuel
Weight
(Kilograms)
Lateral
Moment/1000
Arm Varies
(mm-kgs)
100
200
300
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
1539.70
35.94
98.96
185.25
302.57
450.93
630.63
839.06
1073.56
1331.67
1611.54
1914.97
2256.86
2661.75
3138.48
3692.74
3974.80
100
200
300
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
1539.70
35.94
98.96
185.25
302.57
450.93
630.63
839.06
1073.56
1331.67
1611.54
1914.97
2256.86
2661.75
3138.48
3692.74
3974.80
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2168, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
WEIGHT AND BALANCE COMPUTATION FORM
ITEM
PAYLOAD COMPUTATIONS
ITEM
ARM
WEIGHT MOMENT/
(INCHES) (POUNDS)
100
WEIGHT MOMENT/
(POUNDS)
100
1. BASIC EMPTY WEIGHT
* Airplane CG=_______
2. PAYLOAD
OCCUPANTS
PILOT
136.32
COPILOT
136.32
SEAT 3
3. ZERO FUEL WEIGHT
(sub-total)
Do not exceed maximum zero fuel
weight of 15,100 pounds.
* Airplane CG=______
SEAT 4
4. FUEL
LOADING
SEAT 5
5. RAMP WEIGHT
(sub-total) Do not exceed maximum
ramp weight of 20,400 pounds.
SEAT 6
SEAT 7
* Airplane CG=______
SEAT 8
SEAT 10 FWD
6. LESS FUEL FOR TAXIING
SEAT 10 AFT
7. TAKEOFF WEIGHT * *
Do not exceed maximum takeoff
weight of 20,200 pounds.
* Airplane CG=_______* * *
TOILET/LHSFS
8. LESS FUEL TO DESTINATION
CABINET
CONTENTS
9. LANDING WEIGHT * *
Do not exceed maximum landing
weight of 18,700 pounds.
NAV CHART
CASE
* Airplane CG=________* * *
* Airplane CG=
MOMENT/100
X 100
WEIGHT
* * Totals must be within approved weight and center-of-
TAILCONE
BAGGAGE
PAYLOAD
(Sub-total)
gravity limits. It is the responsibility of the pilot to make
sure that the airplane is loaded properly. The Basic
Empty Weight CG is noted on the Airplane Weighing Form.
If the airplane has been altered, refer to the Weight and
Balance Record for information.
431.00
***
Enter on the Center-of-gravity Limits Envelope Graph to
verify airplane is loaded within approved limits.
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2169, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
WEIGHT AND BALANCE COMPUTATION FORM
ITEM
PAYLOAD COMPUTATIONS
ITEM
ARM
(MM)
OCCUPANTS
WEIGHT
(KGS)
MOMENT/
1000
WEIGHT
(KGS)
MOMENT/
1000
1. BASIC EMPTY WEIGHT
* Airplane CG=_______
2. PAYLOAD
PILOT
3463
COPILOT
3463
SEAT 3
3. ZERO FUEL WEIGHT
(sub-total)
Do not exceed maximum zero fuel
weight of 6,849 kilograms.
* Airplane CG=______
SEAT 4
4. FUEL
LOADING
SEAT 5
SEAT 6
5. RAMP WEIGHT
(sub-total) Do not exceed maximum
ramp weight of 9,253 kilograms.
SEAT 7
* Airplane CG=______
SEAT 8
6. LESS FUEL FOR TAXIING
SEAT 10 FWD
7. TAKEOFF WEIGHT * *
Do not exceed maximum takeoff
weight of 9,162 kilograms.
SEAT 10 AFT
* Airplane CG=_______* * *
TOILET/LHSFS
CABINET
CONTENTS
8. LESS FUEL TO DESTINATION
9. LANDING WEIGHT * *
Do not exceed maximum landing
weight of 8,482 kilograms.
NAV CHART
CASE
* Airplane CG=________* * *
* Airplane CG=
MOMENT/1000
X 1000
WEIGHT
* * Totals must be within approved weight and center-of-
TAILCONE
BAGGAGE
PAYLOAD
(Sub-total)
gravity limits. It is the responsibility of the pilot to make
sure that the airplane is loaded properly. The Basic
Empty Weight CG is noted on the Airplane Weighing Form.
If the airplane has been altered, refer to the Weight and
Balance Record for information.
10,947
***
Enter on the Center-of-gravity Limits Envelope Graph to
verify airplane is loaded within approved limits.
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2170, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
WEIGHT AND BALANCE RECORD
(CONTINUOUS HISTORY OF CHANGES IN STRUCTURE MODIFICATION
OR EQUIPMENT AFFECTING WEIGHT AND BALANCE)
DATE
ITEM
IN
OUT
WEIGHT CHANGE
DESCRIPTION OF
STRUCTURE
MODIFICATION
OR EQUIPMENT
ADDED (+)
BASIC
EMPTY
WEIGHT
REMOVED (-)
WEIGHT
ARM
MOMENT WEIGHT
ARM
(POUNDS) (INCHES)
/100
(POUNDS) (INCHES)
MOMENT
/100
Printed 08.10.15 12:47. Document Revision ---
WEIGHT
(POUNDS)
MOMENT
/100
FORM NUMBER 2171, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
WEIGHT AND BALANCE RECORD
(CONTINUOUS HISTORY OF CHANGES IN STRUCTURE MODIFICATION
OR EQUIPMENT AFFECTING WEIGHT AND BALANCE)
DATE
ITEM
IN
OUT
WEIGHT CHANGE
DESCRIPTION OF
STRUCTURE
MODIFICATION
OR EQUIPMENT
ADDED (+)
WEIGHT
(KGS)
ARM
(MM)
BASIC
EMPTY
WEIGHT
REMOVED (-)
MOMENT
/1000
WEIGHT
(KGS)
ARM
(MM)
MOMENT
/1000
Printed 08.10.15 12:47. Document Revision ---
WEIGHT
(KGS)
MOMENT
/1000
FORM NUMBER 2172, 22 March 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
WEIGHT AND
BALANCE DATA
MODEL 560XL (560-5501 THRU -6000)
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
OPTION 1 CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
MOMENT/100
SEAT 7
SEAT
OR
10
SEAT 8
FWD
ARM = FS ARM = FS
322.62 in. 186.68 in.
SEAT 1
OR
SEAT 2
ARM = FS
136.32 in.
SEAT 3
OR
SEAT 4
ARM = FS
234.39 in.
SEAT 5
OR
SEAT 6
ARM = FS
286.54 in.
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
68.16
81.79
95.42
109.06
122.69
136.32
149.95
163.58
177.22
190.85
204.48
218.11
231.74
245.38
259.01
272.64
286.27
299.90
313.54
327.17
340.80
354.43
368.06
381.70
395.33
408.96
422.59
436.22
117.20
140.63
164.07
187.51
210.95
234.39
257.83
281.27
304.71
328.15
351.59
375.02
398.46
421.90
445.34
468.78
492.22
515.66
539.10
562.54
585.98
609.41
632.85
656.29
679.73
703.17
726.61
750.05
143.27
171.92
200.58
229.23
257.89
286.54
315.19
343.85
372.50
401.16
429.81
458.46
487.12
515.77
544.43
573.08
601.73
630.39
659.04
687.70
716.35
745.00
773.66
802.31
830.97
859.62
888.27
916.93
161.31
193.57
225.83
258.10
290.36
322.62
354.88
387.14
419.41
451.67
483.93
516.19
548.45
580.72
612.98
645.24
677.50
709.76
742.03
774.29
806.55
838.81
871.07
903.34
935.60
967.86
1000.12
1032.38
330
340
449.86
463.49
773.49
796.93
945.58
974.24
1064.65
1096.91
WEIGHT
(POUNDS)
SEAT
10
AFT
ARM = FS
204.43 in.
LH
SFS
ARM = FS
357.99 in.
93.34
112.01
130.68
149.34
168.01
186.68
205.35
224.02
242.68
261.35
280.02
298.69
317.36
336.02
354.69
373.36
392.03
410.70
429.36
448.03
466.70
485.37
504.04
522.70
541.37
560.04
578.71
597.38
102.22
122.66
143.10
163.54
183.99
204.43
224.87
245.32
265.76
286.20
306.65
327.09
347.53
367.97
388.42
408.86
429.30
449.75
470.19
490.63
511.08
531.52
551.96
572.40
592.85
613.29
633.73
654.18
179.00
214.79
250.59
286.39
322.19
357.99
393.79
429.59
465.39
501.19
536.99
572.78
608.58
644.38
680.18
715.98
751.78
787.58
823.38
859.18
894.98
930.77
966.57
1002.37
1038.17
1073.97
1109.77
1145.57
616.04
634.71
674.62
695.06
1181.37
1217.17
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS 136.32
1
2
FS 186.68
10
FS 204.43
FS 234.39
3
4
5
6
FS 286.54
FS 322.62
FS 234.39
FS 286.54
7
FS 357.99
Printed 08.10.15 12:47. Document Revision ---
8
FS 322.62
T
FORM NUMBER 2332, 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (METRIC UNITS)
OPTION 1 CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
WEIGHT
(KGS)
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
145
150
154
SEAT 1
OR
SEAT 2
Arm= F.S.
3463 mm
SEAT 3
OR
SEAT 4
Arm= F.S.
5954 mm
SEAT 5
OR
SEAT 6
Arm= F.S.
7278 mm
69.26
86.58
103.89
121.21
138.52
155.84
173.15
190.47
207.78
225.10
242.41
259.73
277.04
294.36
311.67
328.99
346.30
363.62
380.93
398.25
415.56
432.88
450.19
467.51
484.82
502.14
519.45
533.30
119.08
148.85
178.62
208.39
238.16
267.93
297.70
327.47
357.24
387.01
416.78
446.55
476.32
506.09
535.86
565.63
595.40
625.17
654.94
684.71
714.48
744.25
774.02
803.79
833.56
863.33
893.10
916.92
145.56
181.95
218.34
254.73
291.12
327.51
363.90
400.29
436.68
473.07
509.46
545.85
582.24
618.63
655.02
691.41
727.80
764.19
800.58
836.97
873.36
909.75
946.14
982.53
1018.92
1055.31
1091.70
1120.81
MOMENT/1000
SEAT 7
SEAT
OR
10
SEAT 8
FWD
Arm= F.S.
Arm= F.S.
8195 mm
4742 mm
163.90
204.88
245.85
286.83
327.80
368.78
409.75
450.73
491.70
532.68
573.65
614.63
655.60
696.58
737.55
778.53
819.50
860.48
901.45
942.43
983.40
1024.38
1065.35
1106.33
1147.30
1188.28
1229.25
1262.03
94.84
118.55
142.26
165.97
189.68
213.39
237.10
260.81
284.52
308.23
331.94
355.65
379.36
403.07
426.78
450.49
474.20
497.91
521.62
545.33
569.04
592.75
616.46
640.17
663.88
687.59
711.30
730.27
SEAT
10
AFT
Arm= F.S.
5193 mm
LH
SFS
Arm= F.S.
9093 mm
103.86
129.83
155.79
181.76
207.72
233.69
259.65
285.62
311.58
337.55
363.51
389.48
415.44
441.41
467.37
493.34
519.30
545.27
571.23
597.20
623.16
649.13
675.09
701.06
727.02
752.99
778.95
799.72
181.86
227.33
272.79
318.26
363.72
409.19
454.65
500.12
545.58
591.05
636.51
681.98
727.44
772.91
818.37
863.84
909.30
954.77
1000.23
1045.70
1091.16
1136.63
1182.09
1227.56
1273.02
1318.49
1363.95
1400.32
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS
3463
1
2
10
FS
5954
3
4
5
6
7
8
FS
7278
FS
8195
FS
9093
Printed 08.10.15 12:47. Document Revision ---
FS
4742
FS
5193
FS
5954
FS
7278
FS
8195
T
FORM NUMBER 2333, 12 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
OPTION 1 CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(POUNDS)
5
10
15
MOMENT/100
NAVIGATION
CHART CASE
ARM =
FS 158.10 in.
7.91
15.81
23.72
RH FORWARD
CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
56
MOMENT/100
FORWARD
CLOSET
ARM =
FS 169.70 in.
8.49
16.97
25.46
33.94
42.43
50.91
59.40
67.88
76.37
84.85
95.03
LH
REFRESHMENT
CENTER
WEIGHT
(POUNDS)
10
20
30
40
50
60
70
80
90
100
110
120
130
141
MOMENT/100
REFRESHMENT
CENTER
ARM =
FS 173.20 in.
17.32
34.64
51.96
69.28
86.60
103.92
121.24
138.56
155.88
173.20
190.52
207.84
225.16
244.21
AFT CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
55
60
65
68
MOMENT/100
AFT
CLOSET
ARM =
FS 374.00 in.
18.70
37.40
56.10
74.80
93.50
112.20
130.90
149.60
168.30
187.00
205.70
224.40
243.10
254.32
1
FS 158.10
20
40
60
80
100
120
140
160
180
200
220
240
260
280
300
320
340
360
380
400
420
440
460
480
500
520
540
560
580
600
620
640
660
680
700
MOMENT/100
TAILCONE
COMPARTMENT
ARM =
FS 431.00 in.
86.20
172.40
258.60
344.80
431.00
517.20
603.40
689.60
775.80
862.00
948.20
1034.40
1120.60
1206.80
1293.00
1379.20
1465.40
1551.60
1637.80
1724.00
1810.20
1896.40
1982.60
2068.80
2155.00
2241.20
2327.40
2413.60
2499.80
2586.00
2672.20
2758.40
2844.60
2930.80
3017.00
FS 169.70
FS 173.20
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(POUNDS)
2
3
4
5
6
7
8
T
FS 374.00
FS 431.00
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2334 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENTS
WEIGHT AND MOMENT TABLES (METRIC UNITS)
OPTION 1 CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(KGS)
2
4
6
7
MOMENT/1000
NAVIGATION
CHART CASE
ARM =
FS 4016 mm
8.03
16.06
24.10
28.11
RH FORWARD
CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
25
MOMENT/1000
FORWARD
CLOSET
ARM =
FS 4310 mm
9.77
17.24
25.86
34.48
43.10
51.72
60.34
68.96
77.58
86.20
94.82
103.44
107.75
LH
REFRESHMENT
CENTER
WEIGHT
(KGS)
5
10
15
20
25
30
35
40
45
50
55
60
64
MOMENT/1000
REFRESHMENT
CENTER
ARM =
FS 4399 mm
19.95
43.99
65.99
87.98
109.98
131.97
153.97
175.96
197.96
219.95
241.95
263.94
281.54
AFT CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
31
MOMENT/1000
AFT
CLOSET
ARM =
FS 9500 mm
21.55
38.00
57.00
76.00
95.00
114.00
133.00
152.00
171.00
190.00
209.00
228.00
247.00
266.00
285.00
294.50
1
FS 4016
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
318
MOMENT/1000
TAILCONE
COMPARTMENT
ARM =
FS 10947 mm
109.47
218.94
328.41
437.88
547.35
656.82
766.29
875.76
985.23
1094.70
1204.17
1313.64
1423.11
1532.58
1642.05
1751.52
1860.99
1970.46
2079.93
2189.40
2298.87
2408.34
2517.81
2627.28
2736.75
2846.22
2955.69
3065.16
3174.63
3284.10
3393.57
3481.15
FS 4310
FS 4399
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(KGS)
2
3
4
5
6
7
8
T
FS 9500
FS 10,947
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2335, 12 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
OPTION 2 CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
MOMENT/100
SEAT 5
SEAT 7
OR
OR
SEAT 6
SEAT 8
ARM = FS ARM = FS
286.54 in.
322.62 in.
SEAT 1
OR
SEAT 2
ARM = FS
136.32 in.
SEAT 3
OR
SEAT 4
ARM = FS
234.39 in.
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
68.16
81.79
95.42
109.06
122.69
136.32
149.95
163.58
177.22
190.85
204.48
218.11
231.74
245.38
259.01
272.64
286.27
299.90
313.54
327.17
340.80
354.43
368.06
381.70
395.33
408.96
422.59
436.22
117.20
140.63
164.07
187.51
210.95
234.39
257.83
281.27
304.71
328.15
351.59
375.02
398.46
421.90
445.34
468.78
492.22
515.66
539.10
562.54
585.98
609.41
632.85
656.29
679.73
703.17
726.61
750.05
143.27
171.92
200.58
229.23
257.89
286.54
315.19
343.85
372.50
401.16
429.81
458.46
487.12
515.77
544.43
573.08
601.73
630.39
659.04
687.70
716.35
745.00
773.66
802.31
830.97
859.62
888.27
916.93
330
340
449.86
463.49
773.49
796.93
945.58
974.24
WEIGHT
(POUNDS)
SEAT
10
ARM = FS
205.60 in.
LH
SFS
ARM = FS
357.99 in.
161.31
193.57
225.83
258.10
290.36
322.62
354.88
387.14
419.41
451.67
483.93
516.19
548.45
580.72
612.98
645.24
677.50
709.76
742.03
774.29
806.55
838.81
871.07
903.34
935.60
967.86
1000.12
1032.38
102.80
123.36
143.92
164.48
185.04
205.60
226.16
246.72
267.28
287.84
308.40
328.96
349.52
370.08
390.64
411.20
431.76
452.32
472.88
493.44
514.00
534.56
555.12
575.68
596.24
616.80
637.36
657.92
179.00
214.79
250.59
286.39
322.19
357.99
393.79
429.59
465.39
501.19
536.99
572.78
608.58
644.38
680.18
715.98
751.78
787.58
823.38
859.18
894.98
930.77
966.57
1002.37
1038.17
1073.97
1109.77
1145.57
1064.65
1096.91
678.48
699.04
1181.37
1217.17
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS 136.32
FS 234.39
1
2
10
FS 205.60
3
4
FS 234.39
5
6
7
8
FS 286.54
FS 322.62
FS 357.99
Printed 08.10.15 12:47. Document Revision ---
FS 286.54
FS 322.62
T
FORM NUMBER 2336, 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
CREW AND PASSENGERS COMPARTMENTS
WEIGHT AND MOMENT TABLES (METRIC UNITS)
OPTION 2 CENTER CLUB SEAT ARRANGEMENT
CREW AND PASSENGER
MOMENT ARMS
CREW AND PASSENGER
WEIGHT
(KGS)
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
145
150
154
SEAT 1
OR
SEAT 2
Arm= F.S.
3463 mm
SEAT 3
OR
SEAT 4
Arm= F.S.
5954 mm
69.26
86.58
103.89
121.21
138.52
155.84
173.15
190.47
207.78
225.10
242.41
259.73
277.04
294.36
311.67
328.99
346.30
363.62
380.93
398.25
415.56
432.88
450.19
467.51
484.82
502.14
519.45
533.30
119.08
148.85
178.62
208.39
238.16
267.93
297.70
327.47
357.24
387.01
416.78
446.55
476.32
506.09
535.86
565.63
595.40
625.17
654.94
684.71
714.48
744.25
774.02
803.79
833.56
863.33
893.10
916.92
MOMENT/1000
SEAT 5
SEAT 7
OR
OR
SEAT 6
SEAT 8
Arm= F.S.
Arm= F.S.
7278 mm
8195 mm
145.56
181.95
218.34
254.73
291.12
327.51
363.90
400.29
436.68
473.07
509.46
545.85
582.24
618.63
655.02
691.41
727.80
764.19
800.58
836.97
873.36
909.75
946.14
982.53
1018.92
1055.31
1091.70
1120.81
163.90
204.88
245.85
286.83
327.80
368.78
409.75
450.73
491.70
532.68
573.65
614.63
655.60
696.58
737.55
778.53 4
819.50
860.48
901.45
942.43
983.40
1024.38
1065.35
1106.33
1147.30
1188.28
1229.25
1262.03
SEAT
10
Arm= F.S.
5222 mm
LH
SFS
Arm= F.S.
9093 mm
104.44
130.55
156.66
182.77
208.88
234.99
261.10
287.21
313.32
339.43
365.54
391.65
417.76
443.87
469.98
96.09
522.20
548.31
574.42
600.53
626.64
652.75
678.86
704.97
731.08
757.19
783.30
804.19
181.86
227.33
272.79
318.26
363.72
409.19
454.65
500.12
545.58
591.05
636.51
681.98
727.44
772.91
818.37
863.84
909.30
954.77
1000.23
1045.70
1091.16
1136.63
1182.09
1227.56
1273.02
1318.49
1363.95
1400.32
FS 3463
FS 5954
1
2
10
FS 5222
3
4
FS 5954
5
6
7
8
FS 7278
FS 8195
FS 7278
FS 8195
NOTE: UNBELTED TOILET MAY BE INSTALLED ON RH SIDE.
BELTED TOILET OR SEAT IS ON LH SIDE ONLY.
FS 9093
Printed 08.10.15 12:47. Document Revision ---
T
FORM NUMBER 2337, 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENTS
WEIGHT AND MOMENT TABLES (U.S. UNITS)
OPTION 2 CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(POUNDS)
5
10
15
MOMENT/100
NAVIGATION
CHART CASE
ARM =
FS 158.10 in.
7.91
15.81
23.72
LH
REFRESHMENT
CENTER
WEIGHT
(POUNDS)
10
20
30
40
50
60
70
80
90
100
110
120
130
141
MOMENT/100
REFRESHMENT
CENTER
ARM =
FS 173.20 in.
17.32
34.64
51.96
69.28
86.60
103.92
121.24
138.56
155.88
173.20
190.52
207.84
225.16
244.21
RH FORWARD
CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
56
MOMENT/100
FORWARD
CLOSET
ARM =
FS 177.00 in.
8.85
17.70
26.55
35.40
44.25
53.10
61.95
70.80
79.65
88.50
99.12
AFT CLOSET
WEIGHT
(POUNDS)
5
10
15
20
25
30
35
40
45
50
55
60
65
68
MOMENT/100
AFT
CLOSET
ARM =
FS 374.00 in.
18.70
37.40
56.10
74.80
93.50
112.20
130.90
149.60
168.30
187.00
205.70
224.40
243.10
254.32
1
FS 158.10
FS 173.20
20
40
60
80
100
120
140
160
180
200
220
240
260
280
300
320
340
360
380
400
420
440
460
480
500
520
540
560
580
600
620
640
660
680
700
MOMENT/100
TAILCONE
COMPARTMENT
ARM =
FS 431.00 in.
86.20
172.40
258.60
344.80
431.00
517.20
603.40
689.60
775.80
862.00
948.20
1034.40
1120.60
1206.80
1293.00
1379.20
1465.40
1551.60
1637.80
1724.00
1810.20
1896.40
1982.60
2068.80
2155.00
2241.20
2327.40
2413.60
2499.80
2586.00
2672.20
2758.40
2844.60
2930.80
3017.00
FS 177.00
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(POUNDS)
2
3
4
5
6
7
8
T
FS 374.00
FS 431.00
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2338, 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---
MODEL 560XL (560-5501 THRU -6000)
WEIGHT AND
BALANCE DATA
Cessna
A Textron Company
SERIAL NUMBER_________________REGISTRATION NUMBER_______________________DATE___________
BAGGAGE AND CABINET COMPARTMENTS
WEIGHT AND MOMENT TABLES (METRIC UNITS)
OPTION 2 CENTER CLUB SEAT ARRANGEMENT
LH & RH
CHART CASES
WEIGHT
(KGS)
2
4
6
7
MOMENT/1000
NAVIGATION
CHART CASE
ARM =
FS 4016 mm
8.03
16.06
24.10
28.11
LH
REFRESHMENT
CENTER
WEIGHT
(KGS)
5
10
15
20
25
30
35
40
45
50
55
60
64
MOMENT/1000
REFRESHMENT
CENTER
ARM =
FS 4399 mm
19.95
43.99
65.99
87.98
109.98
131.97
153.97
175.96
197.96
219.95
241.95
263.94
281.54
RH FORWARD
CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
25
MOMENT/1000
FORWARD
CLOSET
ARM =
FS 4496 mm
10.20
17.98
26.98
35.97
44.96
53.95
62.94
71.94
80.93
89.92
98.91
107.90
112.40
AFT CLOSET
WEIGHT
(KGS)
2
4
6
8
10
12
14
16
18
20
22
24
26
28
30
31
MOMENT/1000
AFT
CLOSET
ARM =
FS 9500 mm
21.55
38.00
57.00
76.00
95.00
114.00
133.00
152.00
171.00
190.00
209.00
228.00
247.00
266.00
285.00
294.50
1
FS 4016
FS 4399
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
318
MOMENT/1000
TAILCONE
COMPARTMENT
ARM =
FS 10947 mm
109.47
218.94
328.41
437.88
547.35
656.82
766.29
875.76
985.23
1094.70
1204.17
1313.64
1423.11
1532.58
1642.05
1751.52
1860.99
1970.46
2079.93
2189.40
2298.87
2408.34
2517.81
2627.28
2736.75
2846.22
2955.69
3065.16
3174.63
3284.10
3393.57
3481.15
FS 4496
10
BAGGAGE
COMPARTMENT
CONTENTS
WEIGHT
(KGS)
2
3
4
5
6
7
8
T
FS 9500
FS 10,947
TAILCONE
CARGO
Printed 08.10.15 12:47. Document Revision ---
FORM NUMBER 2339, 11 August 2004
REVISED 1 April 2009
Printed 08.10.15 12:47. Document Revision ---