AIRPLANE CHARACTERISTICS FOR
AIRPORT PLANNING
Including
Saab–Fairchild 340A
Saab SF 340A
Saab 340B
The technical content of this Airplane Characteristics for Airport Planning
(ACAP) is approved under the authority of DOA nr. EASA.21J.066
The content of this document is proprietary and confidential to Saab
Aircraft AB and may not:
a) be used for any purpose other than those for which it was supplied;
b) be copied or reproduced in whole or in part without the prior written
consent of Saab Aircraft AB; nor
c) be disclosed to any third party without the prior written consent of
Saab Aircraft AB
Saab Aircraft AB
SE–581 88 Linköping
Sweden
Doc. No: 72LKS 3090
Ref. No: SAAB 340 ACAP 000
Telephone: int+46 13 18 26 16
Telefax: int+46 13 18 41 83
Initial Issue:
Apr 01/88
Revision 9
Jul 01/05
Airplane Characteristics for Airport Planning
RECORD OF REVISIONS
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Airplane Characteristics for Airport Planning
TABLE OF CONTENTS
SUBJECT
CH/SE/SU
PAGE
TITLE PAGE
1
RECORD OF REVISIONS
1
L.E.P.
1
CONTENTS
1
HIGHLIGHTS
1
MANUAL USER COMMENTS
1
LIST OF CHAPTERS
1
SCOPE
Introduction
Abbreviations
Ch. 1
AIRPLANE DESCRIPTION
General Airplane Description
General Airplane Arrangements
General Airplane Characteristics
Weights
Fuel
General Airplane Dimensions
Airplane Dimensions and Ground Clearances
Typical Interior Arrangements
Typical Cargo Arrangements
Passenger Compartment Dimensions
Cargo Compartment Dimensions
Passenger Compartment Cross Section
Cargo Compartment Cross Section
Cargo Compartment Dimensions, Areas and Volumes
Entrance Door and Airstairs
Cargo Compartment Door and Tail Support Strut
Maximum Package Size passing through Door Openings
Doors and Exterior Handles
Typical Antenna Arrangement
External Lighting
Ch. 2
AIRPLANE PERFORMANCE
Take–Off Runway Length Requirements (ISA day)
Landing Runway Length Requirements (ISA day)
Payload Range
Ch. 3
GROUND MANEUVERING
Runway and Space Requirement
Pilot External Angles of View
Ch. 4
1
2
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7
8
9
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Airplane Characteristics for Airport Planning
SUBJECT
CH/SE/SU
TERMINAL SERVICING
External Servicing Arrangement
Terminal Operation
Ground Service Connections
External Ground Service Connection Data
Internal Servicing
Entry Door Sill Height Variation
Cargo Door Sill Height Variation at Different Airplane
Weights
Entry Door Sill Height Variation at Different Cargo Loads
Cargo Door Sill Height Variation at Different Cargo Loads
Ground Towing Requirements
Ch. 5
OPERATING CONDITIONS
Airport and Community Noise
Take–Off Profile
Noise Footprint
Noise during Ground Operation
Propeller Blast Velocities
Engine Exhaust Velocities and Temperatures, APU–mode
Hazard Areas
Ch. 6
PAVEMENT DATA
Gear/Tire Footprint
Main Landing Gear Loading on Ground
Airplane Classification Number (ACN)
Ch. 7
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Airplane Characteristics for Airport Planning
HIGHLIGHTS
REVISION NO. 09 Jul 01/05
Pages which are new, deleted or revised are outlined below.
SUBJECT
PAGES
Title Page
L.E.P.
Contents
List of Chapters
1–1
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5
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Editorial Changes
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Editorial Changes
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Revised Illustration
Added Mod Information
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REASON FOR CHANGE
Revised Illustration
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Revised Illustration
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Added MOD Information
New Illustration
Added Mod Information
Highlights
Page
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Airplane Characteristics for Airport Planning
To: Saab Aircraft AB
Customer Support
Technical Publications
SE–581 88 Linköping
SWEDEN
Attn:
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01/04
Airplane Characteristics for Airport Planning
LIST OF CHAPTERS
CHAPTER
CHAPTER TITLE
01
Scope
02
Airplane Description
03
Airplane Performance
04
Ground Maneuvering
05
Terminal Servicing
06
Operating Conditions
07
Pavement Data
List of Chapters
Page
1
Jul
01/05
Airplane Characteristics for Airport Planning
SCOPE
The technical content of this Airplane Characteristics for Airport Planning (ACAP) is
approved under the authority of DOA nr. EASA.21J.066.
1.1.
Introduction
The purpose of this document, which conforms to NAS 3601, is to provide the Airport Authorities
and Operators with specific SAAB 340 airplane characteristics data for their preparation and
accomplishment of general airport planning for service of the SAAB 340 airplane.
NOTE:
This manual contains information on the SAAB–FAIRCHILD 340A, SAAB SF340A and
SAAB 340B airplane. Where differences exist, reference is made to 340A or 340B.
NOTE:
This manual also contains information on the SAAB 340 Cargo. Where differences exist,
they are shown in effectivity, reference or by note.
The document is for information only and is not to be used in connection with operation or
maintenance of an airplane for which Saab Aircraft Product Support has issued specific manuals.
Should data in this document differ from data given in any official SAAB 340 MANUAL, the latter
has superior authority to this document.
As a result of airplane changes and new available options, the data in this document may alter and
must be regarded as subject to change without notice.
Revisions or Supplements are issued as required and are not issued in quarterly sequence.
For further information on the above, contact any of the following:
Saab Aircraft AB
S–581 88 LINKOPING, Sweden
Telephone:
int. + 4613182616
Telefax:
int. + 4613184183
Saab Aircraft of America LLC
Loudoun Tech. Center
21300 Ridgetop Circle
Sterling, Virginia 20166–6520
USA
Telephone:
int. + 1 703–406–7200
Telefax:
int. + 1 703–406–7222
EFFECTIVITY:
Ch. 1
Page
1
Jul
01/05
Airplane Characteristics for Airport Planning
1.2.
Abbreviations
A/C
Aircraft
ACN
Airplane Classification Number
ACP
Air Cycle Pack
APU
Auxiliary Power Unit
ATA
Air Transport Association
BEW
Basic Empty Weight
CBR
California Bearing Ratio
CG
Center of Gravity
CL
Condition Lever
dBA
A–weighted Sound Level
EPNdB
Effective Perceived Noise Level
FAR
Federal Aviation Regulations (US)
FI
Flight Idle
FWD
Forward
GI
Ground Idle
GPU
Ground Power Unit
ICAO
International Civil Aviation Organization
ISA
International Standard Atmosphere
JAR
Joint Airworthiness Requirements (Europe)
K
Subgrade Modulus (ie. dense concrete)
KCAS
Knots Calibrated Airspeed
kts
Knots
L
Liter
LCN
Load Classification Number
LDG
Landing Gear
LH
Left Hand
MEW
Manufacturer’s Empty Weight
MIL–STD
Military Standards (US)
MLG
Main Landing Gear
MLW
Maximum Design Landing Weight
MPH
Miles Per Hour
MTOW
Maximum Design Take–off Weight
MTW
Maximum Design Taxi Weight
MZFW
Maximum Design Zero Fuel Weight
EFFECTIVITY:
Ch. 1
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
Abbreviations, Cont.
NAS
National Aerospace Standard
NLG
Nose Landing Gear
OEW
Operational Empty Weight
PCN
Pavement Classification Number
PL
Power Lever
P/L
Payload
PNdB
Perceived Noise Decibels
PR
Ply Rating
PRPM
Propeller Revolutions Per Minute
RH
Right Hand
SB
Service Bulletin
S/N
Service Newsletter
STA
Fuselage Station
TO
Take Off
USG
US Gallon
V
Velocity
V2
Take–off safety speed
WL
Water Line
ZFW
Zero Fuel Weight
EFFECTIVITY:
Ch. 1
Page
3
Jul
01/04
Airplane Characteristics for Airport Planning
AIRPLANE DESCRIPTION
2.1.
General Airplane Description
The airplanes, 340A and 340B versions, which are manufactured by SAAB Aircraft AB, Linkoping,
Sweden, are twin–engined, low–wing turboprop airplanes.
Essentially, the 340B version differs from the 340A in that it is fitted with uprated engines and a
horizontal stabilizer with increased span.
The airplanes are designed for up to 37 passengers and three (3) crew members but can be
operated in a number of configurations; from 14 passengers in the corporate configuration, to all
cargo in the cargo configuration.
The fuselage is built in three major sections:
– The nose section, including flight deck, radar antenna housing and nose gear well.
– The center section including the main part of passenger compartment and space for galley and
wardrobe.
This section is circular in cross–section.
– The rear section, including toilet and cargo compartment.
The nose and rear sections are attached to the center section with riveted splices forward of the
main entry door and forward of the cargo door. The primary structure is made of large metal panels
with bonded doublers and stringers, riveted to the frames. The entire fuselage, including the rear
section with cargo compartment is pressurized, except radar antenna housing, nose gear well and
tail cap.
The main entry door is located on left side of fuselage at forward end, and has a separate
retractable airstairs, which is stowed forward of the main entry door during flight.
The wing is built in two parts with the manufacturing splice at the aircraft center line. The wing is
built up around a front spar and a rear spar, with skin panels stiffened by bonded stringers and
riveted ribs. The wing leading edges are removable and made of thick aluminum skin, and are
de–iced by flush–type pneumatic boots, actuated by engine bleed air.
The space between the two spars comprises an integral fuel tank, one in each wing. Access doors
and gravity filler caps are located in the upper skin panels. A single point pressure
refueling/defueling system is provided with a receptacle located in the right hand wing leading edge,
outside of the nacelle. The flaps and ailerons are hinged to the rear wing spar and are constructed
of aluminum alloy and composite material.
The horizontal stabilizer is mounted on the aft fuselage and is built up around two aluminum spars
with aluminum ribs at the end and at the elevator hinges. It is covered with aluminum sheet faced
honeycomb sandwich panels. The leading edge is made of thick aluminum skin and is de–iced by
flush type pneumatic boots. The elevators are of a design similar to the stabilizers; with a front and
a rear spar, ribs; an upper and a lower skin panel, leading edge and a tip. The spars, ribs and the
tip are made of aluminum alloy.
All other components are made of composite material, such as glassfibre and kevlar fibre
honeycomb sandwich. Each elevator has a trim tab of a honeycomb construction, hinged to the rear
spar.
The vertical stabilizer and rudder are designed in the same manner as the horizontal stabilizer and
elevator. The rudder is provided with a trim tab of similar design to the elevator trim tabs.
EFFECTIVITY:
Ch. 2
Page
1
Jul
01/04
Airplane Characteristics for Airport Planning
Each nacelle consists of a semi–monocoque structure which is attached to the wing at the front and
rear spar locations and by drag angles to the upper and lower wing skins. It houses the engine, the
exhaust system and the main landing gear, which retracts forward into the lower half of the nacelle.
The aircraft is equipped with two General Electric CT7 turboprop engines. The engine and the
propeller gearbox are mounted in the nacelle as one unit. Each engine drives a four–blade, constant
speed composite propeller. The blades are built around two carbonfibre reinforced plastic spars and
covered with glassfibre reinforced plastic. Each blade has a de–icer boot which is electrically
heated.
EFFECTIVITY:
Ch. 2
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
2.2.
General Airplane Arrangements
A23382
EFFECTIVITY:
General Airplane Arrangements
FIG. 1
Ch. 2
Page
3
Jul
01/04
Airplane Characteristics for Airport Planning
2.3.
2.3.1.
General Airplane Characteristics
Propulsion
The airplane is equipped with two General Electric turboprop engines. The engine is
structurally integrated with the propeller gearbox into one unit. The engines are complemented
by Dowty Rotol, (Hamilton Standard propeller also for 340B), four–bladed composite propellers
with full–feathering, reverse and constant speed capability.
340A, Engine type GE C7–5A2, 1735 shp maximum take off
340B, Engine type GE C7–9B, 1870 shp maximum take off
GE C7–9B engines are equipped with APR (Automatic Power Reserve) function.
2.3.2.
Accommodation
2.3.2.1.
General Airplane Arrangements
Passenger capacity, basic configuration
35 seats/30 in pitch
Cabin volume
1180 ft3 (33.4 m3)
Cargo hold volume
2.3.2.2.
with aft lavatory
240 ft3 (6.8 m3)
without aft lavatory
295 ft3 (8.3 m3)
Cargo Airplane Arrangements
Ref. FIG. 5
Cargo floor area and cargo volyme.
Floor area
2.3.3.
Volume approximately
REF.
ft2
m2
ft3
m3
A
9,49
0,88
75
2,1
B1
30,24
2,81
181
5,1
B2
35,59
3,31
213
6,0
B3
33,73
3,13
202
5,7
B4
44,67
4,15
268
7,6
C1
34,6
5,5
208
5,9
C2
17,4
1,62
123
3,5
Flight Controls
All primary flight controls are mechanical with duplicated systems in the elevator and aileron
circuits, which are so interconnected, that an override is possible. Each trim tab is operated by
an electrical trim tab actuator. The gust locks for elevator and ailerons are mechanically
controlled. The gust lock for the rudder is operated from an electrically controlled lock system.
2.3.4.
Landing Gear
Tricycle type, all with dual wheels, retracting forward. Nose gear design allows towing or
pushing of aircraft up to maximum taxi weight and angles up to 120° in both directions.
Maximum taxiing angles are 55° in both directions. Main gear is fitted with an anti–skid control
system and disc brakes, driven by independent hydraulic systems.
2.3.5.
Hydraulics
Consists of a 3000 psi (20.6 MPa) power system operating the following systems: Landing
gear Wheel brakes Nose wheel steering Flaps Propeller brake (right hand engine) There is a
hand type pump provided for emergency operation of the system. The system is powered by a
single 28V DC pump.
EFFECTIVITY:
Ch. 2
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
2.3.6.
Doors
Equipped with a forward main entrance door with retractable air stair, forward emergency exit
door, overhead escape hatch, two overwing emergency exit doors, one cargo door and
equipment access doors. All these doors, excluding main entrance door, but including
equipment access doors located in the pressurized area, are the plug type.
2.3.7.
Electrical
The electrical power supply comprises DC and AC systems.
28 VDC power is supplied by a DC starter/generator on each engine. 26/115 VAC 400 Hz
power for certain instruments and avionics is provided by a solid state inverter. Power for
de–icing and anti–icing is provided by a 115 VAC wild–frequency generator on each engine.
Two NiCad batteries provide ground power and engine start capability. An external 28V DC
connector is located on right hand side, aft fuselage wing fairing.
2.3.8.
Ice protection
Leading edges of wing and tailplane are de–iced by flush–type pneumatic boots, actuated by
engine bleed air. Propellers, windshields, pitot tubes and engine inlet ducts are electrically
heated to prevent ice forming.
2.3.9.
Pressurization
Differential
7 psi (48 kPa)
Sea level cabin altitude up to12000 ft (3660 m)
4500 ft (1370 m) cabin altitude at 25000 ft (7620 m)
Pressurization and air conditioning for the flight, passenger and cargo compartments are
provided by bleed air from the engines. Air conditioning on the ground is provided by an
external ground connector, located on right hand side, aft fuselage wing fairing or an optional
auxiliary power unit, stationary in cargo compartment.
2.3.10.
Certified Noise Levels (ICAO Annex 16)
340A
MTOW
lb
MLW
lb
340B
Pre Mod
No 3139
Post Mod
No 3139
Pre Mod No 2438
Post Mod No 2438
and A/C 380–459
28000
28500
28500
29000
28000
28500
27200
Propeller
Dowty
Dowty
Hamilton S.
Dowty
Hamilton S.
Take–
off
EPNdB
78.1
78.1
78.4
78.2
78.4
78.2
Lateral
EPNdB
85.9
85.9
85.9
86.2
85.9
86.2
Approach
EPNdB
84.5 /
91.7 *
84.5 /
91.7 *
91.8
90.1
91.8
90.1
* For 340A Approach, the two numbers reflect minimum and maximum propeller speed.
EPNdB (Effective Perceived Noise Level)
NOTE:
EFFECTIVITY:
Regarding Airport and Community Noise, see chapter 6.
Ch. 2
Page
5
Jul
01/05
Airplane Characteristics for Airport Planning
2.3.11.
Runway loading at MTOW (Maximum Take–Off Weight)
Rigid pavement LCN 10
(Load Classification Number)
Flexible pavement LCN 8.
NOTE:
EFFECTIVITY:
Regarding ACN (Airplane Classification Number), see chapter 7.
Ch. 2
Page
6
Jul
01/05
Airplane Characteristics for Airport Planning
2.4.
Weights
340A
AIRLINER TYPICAL
SPEC.
340B
pre
post
A/C 160–379
A/C 160–379
SB 340–51–026
Mod No 3139
SB 340–51–026
Mod No 3139
pre
post
SB 340–51–010
SB 340–51–010
Mod No 2438
Mod No 2438, and
WEIGHTS.1
A/C 380–459
lb
kg
lb
kg
lb
kg
lb
kg
MAX DESIGN TAXI
WEIGHT (MTW)
28300
12835
28800
13060
28800
13065
29300
13290
MAX DESIGN
TAKE–OFF
WEIGHT (MTOW)
28000
12700
28500
12930
28500
12930
29000
13155
MAX DESIGN
LANDING WEIGHT
(MLW)
27200
12340
27200
12340
28000
12700
28500
12930
MAX DESIGN
ZERO FUEL
WEIGHT (MZFW)
25700
11660
25700
11660
26000
11795
26500
12020
OPERATIONAL
EMPTY WEIGHT
(OEW)
17615
7990
17615
7990
17945
8140
17945
8140
8085
3670
8585
3895
8055
3655
8555
3880
PAYLOAD (P/L)
Weight definitions
In accordance with ATA 100 Specification, the following weight terms have been established.
MAXIMUM DESIGN TAXI WEIGHT
(MTW)
Maximum weight for ground maneuver as limited by
aircraft strength and airworthiness requirements. (It
includes weight of taxi and run–up fuel).
MAXIMUM DESIGN TAKE–OFF
TAKE OFF WEIGHT
(MTOW)
Maximum weight for take–off
take off as limited by aircraft
strength and airworthiness requirements. (This is the
maximum weight at start of take–off run).
MAXIMUM DESIGN LANDING WEIGHT
(MLW)
Maximum weight
g for landing
g as limited by
y aircraft
strength
t
th and
d airworthiness
i
thi
requirements.
i
t
MAXIMUM DESIGN ZERO FUEL WEIGHT
(MZFW)
Maximum weight allowed, before usable fuel is
loaded in defined sections of the aircraft as limited by
strength and airworthiness requirements.
OPERATIONAL EMPTY WEIGHT
(OEW)
Basic empty
y weight
g or fleet empty
y weight
g plus operati
tional
l items.
it
BASIC EMPTY WEIGHT
(BEW)
Manufacturer’s empty
y weight
g plus or minus weight
g of
standard
t d d item
it
variations.
i ti
PAYLOAD
(P/L)
Weight
g of passengers,
g , cargo
g and baggage.
gg g
EFFECTIVITY:
Ch. 2
Page
7
Jul
01/05
Airplane Characteristics for Airport Planning
2.5.
Fuel
Density: 6.7 lb/US gal
MASS
VOLUME
(0.802 kg/L)
FUEL STAGE
lb
kg
US gal
L
MAX TOTAL FUEL
5800
2630
866
3280
USABLE FUEL
5690
2580
850
3220
110
50
16
60
55
25
8
30
UNUSABLE FUEL
TRAPPED FUEL
The above figures do not include tolerances for change of temperature, fuel specification or tank
measuring equipment.
(Divide by 2 for fuel quantity in each wing tank).
Fuel definitions in accordance with ATA 100 Specification
MAX TOTAL FUEL
Maximum quantity of fuel which can be contained in the two wing tanks.
USABLE FUEL
Fuel available for aircraft propulsion.
UNUSABLE FUEL
Fuel remaining
g after a fuel run–out test has been completed in accordance
with government’s
g
regulations.
g
It includes drainable unusable fuel plus
unusable portion of trapped fuel.
TRAPPED FUEL
Fuel remaining
g when aircraft is defueled by
y normal means using
g the
procedures and attitudes specified for draining the tanks.
Fuel is stored in one left hand and one right hand integral wing tank. Each wing tank contains two
compartments, one inboard and one outboard of the nacelle.
A single–point pressure refueling/defueling system is provided with receptacle in the right wing
leading edge, outboard of the nacelle. Overwing refueling caps are located in the outboard fuel
access panels of each wing tank.
Approved Fuel Types
Aviation
Low Freeze
Source
Kerosene
Kerosene
USA
JET A
JET A–1
JET B
(ASTM D–1655–75)
(ASTM D–1655–75)
(ASTM D–1655–75)
–
JP–5
JP–4
(MIL–T–5624)
(MIL–T–5624)
RT
TS–1 Regular
–
(GOST 10227)
TS–1 Premium
USA Military
Commonwealth of
Independent States
(CIS)
EFFECTIVITY:
Wide cut distillate
(GOST 10227)
Ch. 2
Page
8
Jul
01/05
Airplane Characteristics for Airport Planning
General Airplane Dimensions
1
10 ft
2
3m
7 ft
7 ft 7 in
(2.13 m) (2.31 m)
340A 28 ft 5 in (8.66 m)
0
5
70 ft 5 in (21.44 m)
0
74 ft 8 in (22.75 m) POST MOD 2571
SCALE
340B 30 ft 4 in (9.24 m)
2.6.
17.5 in (0.45 m)
∅ 11 ft (3.35 m)
19 in (0.42 m)
22 in (0.56 m)
23 ft 10 in (7.26 m)
A23383
EFFECTIVITY:
General Airplane Dimensions
FIG. 2
Ch. 2
Page
9
Jul
01/05
Airplane Characteristics for Airport Planning
2.7.
Airplane Dimensions and Ground Clearances
A23384
EFFECTIVITY:
Airplane Dimensions and Ground Clearances
FIG. 3
Ch. 2
Page
10
Jul
01/05
Airplane Characteristics for Airport Planning
2.8.
Typical Interior Arrangements
Depending on seat row pitch and furnishing, number of passenger seats may vary from 27 to 37
A23385
EFFECTIVITY:
Typical Interior Arrangements
FIG. 4
Ch. 2
Page
11
Jul
01/05
Airplane Characteristics for Airport Planning
2.9.
Typical Cargo Arrangements
A COMPARTMENT
BARRIER NET
SMOKE CURTAIN
STA 298.0
BARRIER NET
B1 COMPARTMENT
STA 363.0
BARRIER NET
B2 COMPARTMENT
STA 439.5
BARRIER NET
B3 COMPARTMENT
STA 512.0
BARRIER NET
B4 COMPARTMENT
STA 608.0
BARRIER NET
C1 COMPARTMENT
STA 686.0
C2 COMPARTMENT
A28195
EFFECTIVITY: Saab 340 Cargo
Typical Cargo Arrangements
FIG. 5
Ch. 2
Page
12
Jul
01/05
Airplane Characteristics for Airport Planning
2.10.
Passenger Compartment Dimensions
A23386
EFFECTIVITY:
Passenger Compartment Dimensions
FIG. 6
Ch. 2
Page
13
Jul
01/05
A28278
EFFECTIVITY: Saab 340 Cargo
5.58 ft
(1.70 m)
BLOCKED
EMERGENCY
DOOR
STA
215
STA
225
ENTRANCE
DOOR
STA
298
MAX CARGO VOLUME
1270 cu ft (35.8 m3)
STA
621
STA
686
STA
733
2.11.
6 ft
(1.83 m)
COCKPIT
DOOR
BLOCKED
EMERGENCY
DOORS
CARGO
DOOR
Airplane Characteristics for Airport Planning
Cargo Compartment Dimensions
Cargo Compartment Dimensions
FIG. 7
Ch. 2
Page
14
Jul
01/05
Airplane Characteristics for Airport Planning
2.12.
Passenger Compartment Cross Section
91in
(2,31m)
A12854
EFFECTIVITY:
72in
(1.83m)
Passenger Compartment Cross Section
FIG. 8
Ch. 2
Page
15
Jul
01/05
Airplane Characteristics for Airport Planning
2.13.
Cargo Compartment Cross Section
BARRIER NET INSTALLATION
TYP AT STA 298, 363, 440, 512 AND 608
A28198
EFFECTIVITY: Saab 340 Cargo
Cargo Compartment Cross Section
FIG. 9
Ch. 2
Page
16
Jul
01/05
Airplane Characteristics for Airport Planning
2.14.
Cargo Compartment Dimensions, Areas and Volumes
A23387
EFFECTIVITY:
Cargo Compartment Dimensions, Areas and Volumes
FIG. 10
Ch. 2
Page
17
Jul
01/05
Airplane Characteristics for Airport Planning
2.15.
Entrance Door and Airstairs
14ft 6in (4.42m)
60in
(1.52m)
AIRSTAIR STOWED
POSITION
26.8in
(0.68m)
CABIN FLOOR
63.7in
(1.62m)
15.5in
(0.40m)
RELEASE HOOKS
ROLLER ARM
ENTRANCE DOOR OPEN AND LOCKED
13in (0.33m) CLEARANCE TO FUSELAGE, OPEN POSITION
18in (0.45m) CRITICAL CLEARANCE LIMIT IN TRANSIT
AIRSTAIR PARTILLY RETRACTED
RELEASE HOOK
94in
(2.40m)
A23388
EFFECTIVITY:
CAUTION: THE STAIR MUST NOT BE FOLED
BEFORE THE UPPER SECTION IS
IN VERTICAL POSITION TO AVOID
DAMEGE TO THE ROLLER ARM
BELOW THE THIRD STEP.
Entrance Door and Airstairs
FIG. 11
Ch. 2
Page
18
Jul
01/05
Airplane Characteristics for Airport Planning
2.16.
Cargo Compartment Door and Tail Support Strut
A12855
EFFECTIVITY:
Cargo Compartment Door and Tail Support Strut
FIG. 12
Ch. 2
Page
19
Jul
01/05
Airplane Characteristics for Airport Planning
2.17.
Maximum Package Size passing through Door Openings
PACKAGE SIZE
LOADING LOCATION
HEIGHT
WIDTH
LENGTH
41.0 in
40.5 in
63.0 in
(1.04 m)
(1.03 m)
(1.60 m)
Cargo Compartment C1 + C2
a) Max. size, volume package that will pass
through door opening and past the toilet
installation. In this case a 6 in. higher spacer
must be used under the front end to allow for
the difference in floor levels.
b) Length limitations: max. size that may be
loaded using a 6 in. high spacer as a) above.
As b) diagonally
50.0 in
20.0 in
82.0 in
(1.27 m)
(0.51 m)
(2.08 m)
50.0 in
10.0 in
93.0 in
(1.27 m)
(0.25 m)
(2.36 m)
51.0 in
29.0 in
51.0 in
(1.30 m)
( 0.74 m)
(1.30 m)
43.0 in
44.0 in
45.0 in
(1.09 m)
(1.12 m)
(1.14 m)
55.0 in
18.0 in
64.0 in
(1.40 m)
(0.46 m)
(1.63 m)
Cargo Compartment C1
Max. size that may be loaded and tied down.
Cargo Compartment C2
Max. size that may be loaded restrained by
net.
Passenger Door Opening
Max. size that will comfortably pass through
door opening.
EFFECTIVITY:
Ch. 2
Page
20
Jul
01/05
Airplane Characteristics for Airport Planning
2.18.
Doors and Exterior Handles
NOTE:
Forward R/H and overwing emergency doors are blocked in the Saab 340 Cargo version.
OVERWING EMERGENCY EXITS
EMERGENCY EXITS
LH AND RH SIDE
1. LH SIDE TURN HANDLE
CLOCKWISE TO STOP
RH SIDE TURN HANDLE
COUNTER–CLOCKWISE
TO STOP
2. PUSH DOOR INWARDS
1. TURN HANDLE COUNTER–
CLOCKWISE TO STOP
2. PUSH DOOR INWARDS
EMERGENCY EXIT CREW
1. TURN HANDLE CLOCKWISE
TO STOP
2. PUSH HATCH DOWN UNTIL
FULLY OPENED
AN EXTERNAL KEY OPERATED
LOCK IS AVAILABLE FOR THE
ENTRANCE AND CARGO DOOR
CARGO DOOR
ENTRANCE DOOR
1. PULL HANDLE OUTWARDS
2. TURN HANDLE COUNTER–
CLOCKWISE TO STOP
3. PUSH DOOR FIRST INWARDS
AND THEN SLIDE UPWARDS
UNTIL FULLY OPENED
1. TURN HANDLE COUNTER–
CLOCKWISE TO STOP
2. PULL DOOR OUTWARDS
AND SLIDE TO THE LEFT
A23389
EFFECTIVITY:
Doors and Exterior Handles
FIG. 13
Ch. 2
Page
21
Jul
01/05
Airplane Characteristics for Airport Planning
2.19.
Typical Antenna Arrangement
A23390
EFFECTIVITY:
Typical Antenna Arrangement
FIG. 14
Ch. 2
Page
22
Jul
01/05
Airplane Characteristics for Airport Planning
2.20.
External Lighting
ANTI–COLLISION
BEACON (after MOD)
NAVIGATION LIGHTS
STROBE LIGHTS
ANTI–COLLISION
BEACON (before MOD)
LOGO LIGHTS
NAVIGATION LIGHTS
TAXI LIGHT
(40° BEAM SWEEP)
A12856
EFFECTIVITY:
WING INSPECTION
LIGHTS
STAIR LIGHTING
(L H WING ROOT)
LANDING LIGHTS
(WING ROOTS)
(11° BEAM SWEEP)
ANTI–COLLISION
BEACON
EMERG. ESCAPE
LIGHTS
External Lighting
FIG. 15
Ch. 2
Page
23
Jul
01/05
Airplane Characteristics for Airport Planning
AIRPLANE PERFORMANCE
3.1.
Take–Off Runway Length Requirements (ISA day)
3.1.1.
340A (CT7–A2 engines)
ISA standard day with zero wind.
Max. take–off power.
Dry paved runway with zero slope.
Flaps 15°.
Environmental control system off.
De–icing system off.
Coordinate with using airline for specific requirements prior to facility design.
JAR
FAR
REQUIREMENTS
1830
1525
7000
6000
5000
1220
4000
915
3000
610
AIRPORT
PRESSURE
ALTITUDE
TAKE OFF FIELD LENGTH–ft
TAKE OFF FIELD LENGTH–m
2135
8000 ft
(2440 m)
6000 ft
(1830 m)
4000 ft
(1220 m)
2000 ft
(610 m)
SEA LEVEL
AIRPLANE TAKE OFF WEIGHT – lb
2000
21000
22000
23000
24000
25000
26000
27000
28000
9525
9980
10430
10890
11340
11790
12245
12700
AIRPLANE TAKE OFF WEIGHT – kg
A25081
EFFECTIVITY:
Take–Off Runway Length Requirements 340A (ISA day)
FIG. 1
Ch. 3
Page
1
Jul
01/04
Airplane Characteristics for Airport Planning
3.1.2.
340B (CT7–9B engines)
ISA standard day with zero wind.
Max. take–off power.
Dry paved runway with zero slope.
Flaps 15°.
Environmental control system off.
De–icing system off.
Coordinate with using airline for specific requirements prior to facility design.
JAR
FAR
REQUIREMENTS
1830
1525
7000
6000
5000
1220
4000
915
3000
610
AIRPORT
PRESSURE
ALTITUDE
TAKE OFF FIELD LENGTH–ft
TAKE OFF FIELD LENGTH–m
2135
8000 ft
(2440 m)
WAT–LIMIT
6000 ft
(1830 m)
4000 ft
(1220 m)
2000 ft
(610 m)
SEA LEVEL
AIRPLANE TAKE OFF WEIGHT – lb
2000
22000
23000
24000
25000
26000
27000
28000
29000
9980
10430
10890
11340
11790
12245
12700
13155
AIRPLANE TAKE OFF WEIGHT – kg
A25082
EFFECTIVITY:
Take–Off Runway Length Requirements 340B (ISA day)
FIG. 2
Ch. 3
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
3.1.3.
340A (CT7–A2 engines)
ISA standard day +10°C with zero wind.
Max. take–off power.
Dry paved runway with zero slope.
Flaps 15°.
Environmental control system off.
De–icing system off.
Coordinate with using airline for specific requirements prior to facility design.
JAR
FAR
2135
7000
1830
6000
1525
5000
1220
4000
915
3000
610
AIRPORT
PRESSURE
ALTITUDE
TAKE OFF FIELD LENGTH–ft
TAKE OFF FIELD LENGTH–m
REQUIREMENTS
8000 ft
(2440 m)
6000 ft
(1830 m)
4000 ft
(1220 m)
2000 ft
(610 m)
SEA LEVEL
AIRPLANE TAKE OFF WEIGHT – lb
2000
21000
22000
23000
24000
25000
26000
27000
28000
9525
9980
10430
10890
11340
11790
12245
12700
AIRPLANE TAKE OFF WEIGHT – kg
A25083
EFFECTIVITY:
Take–Off Runway Length Requirements 340A (ISA day)
FIG. 3
Ch. 3
Page
3
Jul
01/04
Airplane Characteristics for Airport Planning
3.1.4.
340B (CT7–9B engines)
ISA standard day +10°C with zero wind.
Max. take–off power.
Dry paved runway with zero slope.
Flaps 15°.
Environmental control system off.
De–icing system off.
Coordinate with using airline for specific requirements prior to facility design.
JAR
FAR
REQUIREMENTS
1830
1525
7000
6000
5000
1220
4000
915
3000
610
2000
8000 ft
(2440 m)
AIRPORT
PRESSURE
ALTITUDE
TAKE OFF FIELD LENGTH–ft
TAKE OFF FIELD LENGTH–m
2135
6000 ft
(1830 m)
4000 ft
(1220 m)
WAT–LIMIT
2000 ft
(610 m)
SEA LEVEL
AIRPLANE TAKE OFF WEIGHT – lb
22000
23000
24000
25000
26000
27000
28000
29000
9980
10430
10890
11340
11790
12245
12700
13155
AIRPLANE TAKE OFF WEIGHT – kg
A25084
EFFECTIVITY:
Take–Off Runway Length Requirements 340B (ISA day)
FIG. 4
Ch. 3
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
3.2.
Landing Runway Length Requirements (ISA day)
3.2.1.
340A (CT7–5A2 engines)
ISA standard day with zero wind.
Dry paved runway with zero slope.
Flaps 20°.
Coordinate with using airline for specific requirements prior to facility design.
5500
1676
5000
1524
4500
1372
4000
1219
LANDING FIELD LENGTH –m
LANDING FIELD LENGTH ft
JAR REQUIREMENTS
FAR REQUIREMENTS
AIRPORT
PRESSURE
ALTITUDE
8000ft (2440 m)
6000ft (1830 m)
4000ft (1220 m)
3500
1067
2000ft (610 m)
SEA LEVEL
3000
AIRPLANE LANDING WIGHT – kg
914
8165
9072
9979
10886
11794
12701
18000
20000
22000
24000
26000
28000
AIRPLANE LANDING WEIGHT – lb
A25073
EFFECTIVITY:
Landing Runway Length Requirements 340A (ISA day)
FIG. 5
Ch. 3
Page
5
Jul
01/04
Airplane Characteristics for Airport Planning
3.2.2.
340B (CT7–9B engines)
ISA standard day with zero wind.
Dry paved runway with zero slope.
Flaps 20°.
Coordinate with using airline for specific requirements prior to facility design.
5000
1524
4500
1372
4000
3500
1219
1067
LANDING FIELD LENGTH –m
LANDING FIELD LENGTH ft
JAR REQUIREMENTS
FAR REQUIREMENTS
AIRPORT
PRESSURE
ALTITUDE
8000ft (2440 m)
6000ft (1830 m)
4000ft (1220 m)
2000ft (610 m)
SEA LEVEL
3000
914
2500
762
AIRPLANE LANDING WIGHT – kg
8165
9072
9979
10886
11794
12701
13608
18000
20000
22000
24000
26000
28000
30000
AIRPLANE LANDING WEIGHT – lb
A25072
EFFECTIVITY:
Landing Runway Length Requirements 340B (ISA day)
FIG. 6
Ch. 3
Page
6
Jul
01/04
Airplane Characteristics for Airport Planning
3.2.3.
340A (CT7–5A2 engines)
ISA standard day with zero wind.
Dry paved runway with zero slope.
Flaps 35°.
Coordinate with using airline for specific requirements prior to facility design.
5000
1524
4500
1372
4000
3500
1219
1067
LANDING FIELD LENGTH –m
LANDING FIELD LENGTH ft
JAR REQUIREMENTS
FAR REQUIREMENTS
AIRPORT
PRESSURE
ALTITUDE
8000ft (2440 m)
6000ft (1830 m)
4000ft (1220 m)
2000ft (610 m)
SEA LEVEL
3000
914
2500
762
AIRPLANE LANDING WIGHT – kg
8165
9072
9979
10886
11794
12701
18000
20000
22000
24000
26000
28000
AIRPLANE LANDING WEIGHT – lb
A25071
EFFECTIVITY:
Landing Runway Length Requirements 340A (ISA day)
FIG. 7
Ch. 3
Page
7
Jul
01/04
Airplane Characteristics for Airport Planning
3.2.4.
340B (CT7–9B engines)
ISA standard day with zero wind.
Dry paved runway with zero slope.
Flaps 35°.
Coordinate with using airline for specific requirements prior to facility design.
5000
1524
4500
1372
4000
1219
3500
1067
LANDING FIELD LENGTH –m
LANDING FIELD LENGTH ft
JAR REQUIREMENTS
FAR REQUIREMENTS
AIRPORT
PRESSURE
ALTITUDE
8000ft (2440 m)
6000ft (1830 m)
4000ft (1220 m)
2000ft (610 m)
SEA LEVEL
3000
914
2500
762
AIRPLANE LANDING WIGHT – kg
8165
9072
9979
10886
11794
12701
13608
18000
20000
22000
24000
26000
28000
30000
AIRPLANE LANDING WEIGHT – lb
A25070
EFFECTIVITY:
Landing Runway Length Requirements 340B (ISA day)
FIG. 8
Ch. 3
Page
8
Jul
01/04
Airplane Characteristics for Airport Planning
3.3.
Payload Range
3.3.1.
Payload Range 340 A
ISA standard day with zero wind.
10 minutes manoeuvre.
45 minutes holding at 5000ft (1525m).
100 nautical miles (185km) to an alternate.
OEW 17415lb (7900kg).
PAX weight assumed to be 190lb (86kg).
OEW
+
PAYLOAD
kg
11790
lb
26000
11340
25000
10885
24000
10430
23000
TAKEOFF WEIGHT
12700 kg 28000 lb
11795 kg 26000 lb
9980
22000
9525
21000
9070
20000
8620
19000
8165
18000
10885 kg 24000 lb
9980 kg 22000 lb
9070 kg 20000 lb
0
0
200
370
400
740
600
800
AIR RANGE – NAUTICAL MILES
1110
1480
1000
1200
1400
1850
2220
2590
AIR RANGE – KILOMETERS
A25085
EFFECTIVITY:
Payload Range 340 A
FIG. 9
Ch. 3
Page
9
Jul
01/04
Airplane Characteristics for Airport Planning
3.3.2.
Payload Range 340 B
ISA standard day with zero wind.
Cruise altitude 19000 ft (5800m).
10 minutes maneuvering.
45 minutes holding at 5000 ft (1525 m).
100 nautical miles (185 km) to an alternate.
OEW 17945 lb (8140 kg).
PAX weight assumed to be 190lb (86kg).
PAYLOAD
kg
lb
4082
9000
TAKEOFF WEIGHT
3629
8000
3175
7000
13154 kg 29000 lb
2722
6000
12020 kg 26500 lb
2268
5000
1814
4000
1361
3000
907
2000
454
1000
0
0
10886 kg 24000 lb
9979 kg 22000 lb
9072 kg 20000 lb
0
200
400
600
800
1000
1200
1400
AIR RANGE – NAUTICAL MILES
0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
2600
AIR RANGE – KILOMETERS
A25086
EFFECTIVITY:
Payload Range 340 B
FIG. 10
Ch. 3
Page
10
Jul
01/04
Airplane Characteristics for Airport Planning
GROUND MANEUVERING
4.1.
Runway and Space Requirement
WING TIP SWEEP 108 FT (33.3 M) POST MOD 2571
WING TIP SWEEP 104 FT (32 M) PRE MOD 2571
WHEEL SWEEP 58 FT (18 M)
STEERING
ANGLE °
TURN CENTER
58 FT (18 M)
MINIMUM PAVEMENT WIDTH
(TIRE SLIPPAGE IS NOT CONSIDERED)
A29237
EFFECTIVITY:
Runway and Space Requirement for an 180° turn with 55°
FIG. 1
Ch. 4
Page
1
Jul
01/05
Airplane Characteristics for Airport Planning
R8
A29236
NOTE:
FIG. 2
At 64.8° the INBD MLG will become turn center.
TURNING RADII
TAXIING
TOWING
55° STEERING ANGLE
90° TOWING ANGLE
ft
m
ft
m
R1
5.4
1.7
R1– 11.0
3.4
INNER MLG
R2
27.4
8.4
11.0
3.4
OUTER MLG
R3
28.6
8.7
23.4
7.1
NOSE LG
R4
34.2
10.4
30.0
9.2
A/C NOSE
R5
39.6
12.1
34.8
10.6
RUDDER TIP
R6
41.8
12.7
31.6
9.6
H. STAB. TIP
R7
51.6
15.7
35.2
10.7
WING TIP
R8 *
54.1
16.5
37.4
11.4
WING TIP*
Turning radii with 55° nose wheel angle (taxiing) and 90° nose wheel angle (towing)
* = Post Mod 2571
EFFECTIVITY:
Ch. 4
Page
2
Jul
01/05
Airplane Characteristics for Airport Planning
R3
R4
STEERING ANGLE DEGREES (TYP)
R6
20°
25°
R1
R7
30°
R2
35°
40°
TURNING CENTER
(TYPICAL)
FOR NOSE GEAR
STEERING
ANGLE AS SHOWN.
45°
50°
55°
R5
A29241
FIG. 3
Actual turning radii will be slightly greater than shown due to tire slippage during
manoeuvre. R1 measured to center of wheel pair, R2 and R3 measured to outside tire
face.
NOTE:
Steering
R1
R2
R3
R4
R5
R6
R7*
angle
(degr.)
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
20
53.4
16.3
76.4
23.3
69.3
21.1
71.1
21.7
83.9
25.6
99.6
30.4
102.0
31.1
25
39.3
12.0
62.2
19.0
56.3
17.1
58.6
17.8
70.7
21.5
85.4
26.0
87.5
26.7
30
29.6
9.0
52.6
16.0
47.7
14.5
50.5
15.4
61.9
18.9
75.8
23.1
78.0
23.8
35
22.5
6.9
45.4
13.8
41.7
12.7
45.0
13.7
55.7
17.0
68.6
20.9
70.8
21.6
40
16.9
5.2
39.9
12.1
37.3
11.4
41.0
12.5
51.0
15.5
63.1
19.2
65.2
19.9
45
12.4
3.8
35.4
10.8
33.9
10.3
38.1
11.6
47.3
14.4
58.6
17.9
61.0
18.6
50
8.7
2.6
31.6
9.6
31.4
9.6
35.9
10.9
44.3
13.5
54.8
16.7
57.1
17.4
55
(Max)
5.4
1.7
28.4
8.6
29.4
9.0
34.2
10.4
41.8
12.7
51.6
15.7
53.8
16.4
Turning radii and turn centers
* = Post Mod 2571
EFFECTIVITY:
Ch. 4
Page
3
Jul
01/05
Airplane Characteristics for Airport Planning
4.2.
Pilot External Angles of View
A23401
EFFECTIVITY:
Pilot External Angles of View
FIG. 4
Ch. 4
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
TERMINAL SERVICING
5.1.
External Servicing Arrangement
A23402
EFFECTIVITY:
External Servicing Arrangement (Typical Turnaround Station)
FIG. 1
Ch. 5
Page
1
Jul
01/04
Airplane Characteristics for Airport Planning
5.2.
Terminal Operation
FIG. 2 and 3 shows typical service times at a terminal. These charts give typical schedules for
performing service on the airplane within a given time. Service times could by rearranged to suit
availability of personnel, airplane interior configuration, and degree of service required.
The times presented reflect ideal conditions for a single airplane. Service requirements may vary
according to airplane condition and airline procedure.
Note that the charts depict the following:
– Passengers enplane and deplane using the airplanes own airstairs.
– Use of exterior power supply.
– Fuel airplane at 50 psi (345 kPa) pump pressure. Additional time is required for lower pump
pressures.
Varying airline practices and operating circumstances throughout the world will result in different
sequences and time intervals to accomplish the tasks shown. Because of this, ground operations
requirements should be coordinated with the using airlines prior to ramp planning.
EFFECTIVITY:
Ch. 5
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
A23403
EFFECTIVITY:
Terminal Operations (Typical 34 seat cabin config.)
FIG. 2
Ch. 5
Page
3
Jul
01/04
Airplane Characteristics for Airport Planning
A12857
FIG. 3
EFFECTIVITY:
Ch. 5
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
5.3.
Ground Service Connections
REAR TOILET SERVICE
MESSAGE DOOR
PILOT–GROUND
CREW
GRAVITY REFUELING
PRESSURE
REFUELING
POTABLE
WATER
(OPTION)
BATTERY
ENGINE OIL
“FUEL” GND
CONNECTION
PROP. GEAR BOX OIL
AIR CONDITION
POTABLE WATER
DC–POWER
(OPTION)
“FUEL” GND
CONNECTION
FUEL DRAIN
VALVES
OXYGEN
CONN. GROUND
CREW PILOT
FUEL DIPSTICK
FWD TOILET SERVICE
(OPTION)
A23404
EFFECTIVITY:
HYDRAUL QUANTITY
HYDRAUL REFILL
HYDRAUL AND
NITR. PRESSURE
Ground Service Connections
FIG. 4
Ch. 5
Page
5
Jul
01/04
Airplane Characteristics for Airport Planning
5.4.
External Ground Service Connection Data
Hydraulic fluid replenishment.
DISTANCE AFT
DISTANCE FROM
HEIGHT FROM
FROM A/C NOSE
A/C CENTERLINE
GROUND (APPROX)
ft
m
ft
m
ft
m
2.0
0.6
1.0 LH
0.3 LH
5.7
1.7
2.9
0.9
0.9 RH
0.3 RH
5.0
1.5
3.6
1.1
1.0 LH
0.3 LH
5.2
1.6
3.0
0.9
1.0 LH
0.3 LH
3.0
0.9
6.8
2.1
3.5 LH
1.1 LH
8.0
2.4
7.3
2.2
1.8 RH
0.6 RH
4.6
1.4
(Nose gear well)
Hydraulic and nitrogen
pressure check.
Acc. pressure: 1650 psi
(11375 kPa)
(Nose gear well)
Hydraulic fluid quantity check.
(Nose gear well)
Connection for head set
communication ground
crew–pilots.
(Nose gear well)
Door for communication
pilots–ground crew.
(Inside quick release fastener
on door)
Oxygen check and
replenishment.
Acc. pressure: 1850 psi
(12755 kPa)
Door opens inwards with 2
camlocks. (Compartment
pressurized)
EFFECTIVITY:
Ch. 5
Page
6
Jul
01/04
Airplane Characteristics for Airport Planning
External Ground Service Connection Data (Cont.)
DISTANCE AFT
DISTANCE FROM
HEIGHT FROM
FROM A/C NOSE
A/C CENTERLINE
GROUND (APPROX)
ft
m
ft
m
ft
m
10.3
3.1
3.0 RH
0.9 RH
5.2
1.6
13.2
4.0
3.6 RH
1.1 RH
5.6
1.7
45.7
13.9
3.3 RH
1.0 RH
6.1
1.9
19.6
6.0
10.4 LH
3.2 LH
6.6
2.0
11.6 RH
3.5 RH
9.5 LH
2.9 LH
6.8
2.1
11.7 RH
3.6 RH
External connection for potable
water replenishment. (Option).
FWD location:
(A/C with AFT Toilet)
FWD location:
(A/C with FWD Toilet)
AFT location:
Quick couplings 3/4”, (2
camlocks on door)
Propeller gearbox oil.
Visual check and
replenishment. (Nacelles RH, 4
camlocks)
Engine oil.
22.7
6.9
Visual check and
replenishment. (Nacelles RH, 2
quick–release fasteners on
door)
Connection for pressure
refueling/defueling.
28.0
8.5
19.0 RH
5.8 RH
6.3
1.9
28.8
8.8
5.6 LH
1.7 LH
4.1
1.3
5.6 RH
1.7 RH
Connector: Std. 2.5”.
Fueling pressure: Max 50 psi
(345 kPa). (RH wing leading
edge, 4 quick–release fasteners
on door)
Dipstick reading fuel quantity
(Underwing)
EFFECTIVITY:
Ch. 5
Page
7
Jul
01/04
Airplane Characteristics for Airport Planning
External Ground Service Connection Data (Cont.)
Draining fuel tanks (Underwing)
DISTANCE AFT
DISTANCE FROM
HEIGHT FROM
FROM A/C NOSE
A/C CENTERLINE
GROUND (APPROX)
ft
m
ft
m
ft
m
28.8
8.8
3.8 LH
1.2 LH
3.9
1.2
3.8 RH
1.2 RH
24.0 LH
7.3 LH
7.5
2.3
24.0 RH
7.3 RH
Gravity refueling caps
(Overwing)
29.8
9.1
Connection for DC–ground
power unit.
35.2
10.7
2.3 RH
0.7 RH
3.8
1.2
35.4
10.8
3.3 LH
1.0 LH
4.9
1.5
3.3 RH
1.0 RH
1.3 RH
0.4 RH
3.8
1.2
Connector: MIL.STD 3506–1
Voltage:
28VDC, Engine
starting 1400–1600
amp
(1 quick–release fastener on
door)
Battery
(2 quick–release fastener on
door)
Connection for ground air
conditioning.
36.0
11.0
Connector: Std. 8”.
Pressure:
Max 1.16 psi (8
kPa).
Temp:
Max 150°F
(+65°C)
Min40°F (+5°C)
(2 Quick–release fastener on
door)
EFFECTIVITY:
Ch. 5
Page
8
Jul
01/04
Airplane Characteristics for Airport Planning
External Ground Service Connection Data (Cont.)
DISTANCE AFT
DISTANCE FROM
HEIGHT FROM
FROM A/C NOSE
A/C CENTERLINE
GROUND (APPROX)
ft
m
ft
m
ft
m
AFT Toilet
43.7
13.3
2.5 RH
0.8
4.8
1.5
FWD Toilet (Option)
10.2
3.1
2.3 RH
0.7
4.6
1.4
Connection for toilet servicing.
Drain:
Std 4”
Flush:
Quick–coupl. 1”
Fluid
pressure:
50 psi (345 kPa)
Fluid
quantity:
1.7 gal (6.43 l)
(2 Quick–release fastener on
door)
EFFECTIVITY:
Ch. 5
Page
9
Jul
01/04
Airplane Characteristics for Airport Planning
5.5.
Internal Servicing
A23405
EFFECTIVITY:
Internal Servicing Arrangement (If applicable)
FIG. 5
Ch. 5
Page
10
Jul
01/04
Airplane Characteristics for Airport Planning
5.6.
Entry Door Sill Height Variation
340A
A23406
Entry Door Sill height variation at different airplane weights and maximum C.G. range utilization
FIG. 6
EFFECTIVITY:
Ch. 5
Page
11
Jul
01/04
Airplane Characteristics for Airport Planning
m in
29% MAC (STA 436.1)
1.70
NOTE:
66.9
TAIL TIPPING RISK
OCCURS WHEN C.G.
TRAVELS TO 47% MAC
(STA 451).
10% MAC (STA 420.5)
1.66
65.3
1.62
63.8
1.58
62.2
1.54
60.6
38% MAC (STA 443.5)
20.7 MAC (STA 429.3)
NOTE:
1.50
59.1
1.46
57.5
1.42
55.9
7260
ALL MEASUREMENTS FROM APRON
ARE APPROXIMATE. CALCULATION
IS BASED ON NORMAL STRUT AND
TIRE CONDITION.
18000
20000
22000
24000
26000
8160
9070
9980
10890
11790
28000
12700
29000lb
13150
kg
AIRPLANE WEIGHT
340B
A23407
Entry Door Sill height variation at different airplane weights and maximum C.G. range utilization
FIG. 7
EFFECTIVITY:
Ch. 5
Page
12
Jul
01/04
Airplane Characteristics for Airport Planning
5.7.
Cargo Door Sill Height Variation at Different Airplane Weights
1.70
1.66
1.62
1.58
1.54
1.50
1.46
1,42
340A
A23408
Cargo Door Sill height variation at different airplane weights and maximum C.G. range utilization
FIG. 8
EFFECTIVITY:
Ch. 5
Page
13
Jul
01/04
Airplane Characteristics for Airport Planning
m in
1.70
66.9
NOTE:
1.66
65.3
1.62
63.8
1.58
62.2
ALL MEASUREMENTS FROM APRON
ARE APPROXIMATE. CALCULATION
IS BASED ON NORMAL STRUT AND
TIRE CONDITION.
10% MAC (STA 420.5)
29% MAC (STA 436.1)
1.54
60.6
1.50
59.1
20.7 MAC (STA 429.3)
NOTE:
1.46
TAIL TIPPING RISK
OCCURS WHEN C.G.
TRAVELS TO 47% MAC
(STA 451).
57.5
38% MAC (STA 443.5)
1.42
55.9
7260
18000
20000
22000
24000
26000
8160
9070
9980
10890
11790
28000
12700
29000lb
13150
kg
AIRPLANE WEIGHT
340B
A23409
Cargo Door Sill height variation at different airplane weights and maximum C.G. range utilization
FIG. 9
EFFECTIVITY:
Ch. 5
Page
14
Jul
01/04
Airplane Characteristics for Airport Planning
5.8.
Entry Door Sill Height Variation at Different Cargo Loads
COMPARTMENT EMPTY.
A23410
EFFECTIVITY:
Entry Door Sill height variation at different cargo loads
FIG. 10
Ch. 5
Page
15
Jul
01/04
Airplane Characteristics for Airport Planning
5.9.
Cargo Door Sill Height Variation at Different Cargo Loads
A23411
EFFECTIVITY:
Cargo Door Sill height variation at different cargo loads
FIG. 11
Ch. 5
Page
16
Jul
01/04
Airplane Characteristics for Airport Planning
5.10.
Ground Towing Requirements
In order to determine the drawbar pull and traction wheel load experienced by a tow vehicle, the
airplane weight, pavement slope, engine thrust when backing, and coefficient of friction must be
known.
In the graph examples A and B, see following page, conditions are as follows:
5.10.1.
Towing airplane at 26 500 lb(12 020 kg) weight, no pavement slope, no engine thrust and wet
concrete surface.
Consider the graph as follows:
Enter graph at right side where airplane weight is 26 500 lb (12 020 kg).
Follow set curve to zero percent slope print.
Since ground idle thrust is zero, cross directly into left side graph to set curve for wet concrete.
From this point, read off at left side 1015 lbf (460 kp) drawbar pull and downwards 1800 lb (815
kg) total traction tow wheel load needed.
5.10.2.
Pushing airplane backwards at 26 500 lb (12 020 kg) weight, one percent pavement upslope,
engine idle thrust and wet concrete surface.
Consider the graph as follows:
Enter graph at right side where airplane weight is 26 500 lb (12 020 kg)
Follow set curve to one percent slope print, then transfer to center graph.
Since ground idle thrust is present, follow set curve up and into left side graph to set curve for
wet concrete. From this point read off at left side 1765 lbf (800 kp) drawbar pull and
downwards 3200 lb (1450) total traction tow wheel load needed.
EFFECTIVITY:
Ch. 5
Page
17
Jul
01/04
Airplane Characteristics for Airport Planning
A23412
EFFECTIVITY:
Ground Towing Requirements
FIG. 12
Ch. 5
Page
18
Jul
01/04
Airplane Characteristics for Airport Planning
OPERATING CONDITIONS
6.1.
6.1.1.
Airport and Community Noise
Noise during Take–off and Landing
The SAAB 340 airplane meets current ICAO Annex 16 and FAR Part 36 noise standards, with
substantial margins.
The airplane noise footprints for take–off and landing reflect the noise level frames upon a
ground level plane at the same elevation as the runway.
The noise produced at a given point on the ground by an airplane operation is dependent on a
number of factors, such as airplane weight, engine power setting, local topography and
weather.
The noise footprints for take–off and landing with SAAB 340 have been calculated using an
ISA–day as reference condition. (ISA = International Standard Atmosphere used as common
reference). Standard atmosphere defines pressure 1013.25 hPa (mb) at MSL (Mean Sea
Level) and temperature 15°C at MSL.
Further calculation assumptions are 70% relative humidity, 8 kts head wind and no runway
slope.
For the take–off, three different heights are shown, where the transition to maximum climb
power are selected.
At landing, the footprints are shown for maximum propeller speed and for minimum propeller
speed, with maximum propeller speed selected 2 km (6600 ft) from runway threshold.
The noise footprints for take–off and landing have been calculated with the airplane weights as
follow: (See also to Chapter 2, Weights).
EFFECTIVITY:
Take–off
Landing
340A
25000 lb
24000 lb
340B
28500 lb
28000 lb
Ch. 6
Page
1
Jul
01/04
Airplane Characteristics for Airport Planning
6.2.
Take–Off Profile
A23413
EFFECTIVITY:
Take–Off Profile for Noise Footprint Calculations, (340A)
FIG. 1
Ch. 6
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
A23414
EFFECTIVITY:
1650
1650
Noise Footprint
1650
6.3.
Noise Footprint – A–Weighted Sound Level, (340A)
FIG. 2
Ch. 6
Page
3
Jul
01/04
A23415
EFFECTIVITY:
1650
1650
1650
Airplane Characteristics for Airport Planning
Noise Footprint – PNL (Perceived Noise Level), (340A)
FIG. 3
Ch. 6
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
TAKE–OFF CONDITIONS:
ISA DAY
SEA LEVEL AIRPORT
8 KTS HEADWIND
NO RUNWAY SLOPE
A/C WEIGHT 28500 lb (12930 kg)
TRANSITION HEIGHT TO MAX CLIMB POWER AT 1500 ft
m
ft
HEIGHT ABOVE 1500 ft
914
3000
762
2500
610
2000
460
1500
305
1000
152
500
AT 1500 ft, ACCELERATION TO 140 KCAS
FLAPS 0°
MAX CLIMB POWER (1270 PRPM) AT 140 KCAS
140 KCAS
1500 ft
HEIGHT BELOW 1500 ft
NORMAL TAKE–OFF POWER (1384 PRPM)
FLAPS 15°
V=120.8 KCAS (V2 + 7.5)
3300
6600
1
2
9800
13100
16400
4
5
19700
23000 ft
0
0
3
6
7
km
DISTANCE FROM BRAKE RELEASE
A27977
EFFECTIVITY:
Take–Off Profile for Noise Footprint Calculations, (340B)
FIG. 4
Ch. 6
Page
5
Jul
01/04
Noise Footprint – A–Weighted Sound Level, (340B)
FIG. 5
1000
3300
600
1970
200
660
TAKE–OFF
A/C WEIGHT 28000 lb (12700 kg)
3 GLIDE SLOPE
A/C WEIGHT 28500 lb (12930 kg)
MAX PRPM
TRANSITION TO
MAX CLIMB POWER
AT 500 ft
500 ft MAX. CLIMB POWER
65
70
75
65 dBA
70
75
80
80
85
85
RUNWAY
1000
3300
600
1970
200
1000 ft
MIN PRPM
MAX PRPM SELECTED 2000 m FROM THRESHOLD
70
65
70
75
80
85
65
660
70
75
85 80
1500 ft
3300
1000
AT 1000 ft
65
AT 1500 ft
65
600
1970
200
660
70
75
85
Ch. 6
Page
6
Jul
01/04
10
9
ft
29500
km
9
8
7
6
5
4
3
26300 23000 19700 16400 13100 9800
8
7
6
5
4
3
1
0
1
2
3300
0
3300
6600
1
0
1
2
2
6600
80
2
DISTANCE TO RUNWAY THRESHOLD
3
4
5
6
7
8
9
9800 13100 16400 19700 23000 26300 29500
3
4
5
6
7
DISTANCE FROM RUNWAY THRESHOLD
(BRAKE RELEASE)
8
9
10
ft
km
Airplane Characteristics for Airport Planning
A23416
EFFECTIVITY:
APPROACH
LATERAL
DISTANCE
m
ft
1000
3300
600
1970
TAKE–OFF
A/C WEIGHT 28000 lb (12700 kg)
3 GLIDE SLOPE
A/C WEIGHT 28500 lb (12930 kg)
500 ft
MAX PRPM
MAX. CLIMB POWER
75
80
75 PNdB
85
90
80
Noise Footprint – PNL (Perceived Noise Level), (340B)
FIG. 6
200
TRANSITION TO
MAX CLIMB POWER
AT 500 ft
85
660
90
95
95
100
100
RUNWAY
1000
MIN PRPM
MAX PRPM SELECTED 2000 m FROM THRESHOLD
3300
600
1970
200
660
1000
3300
600
1970
200
660
80
85
85
90
Ch. 6
Page
7
Jul
01/04
9
ft
29500
km
9
95
100
100
1500 ft
AT 1500 ft
75
80
85
90
100
10
AT 1000 ft
75
80
75
80
85
90
95
75
1000 ft
8
7
6
5
4
3
26300 23000 19700 16400 13100 9800
8
7
6
5
4
3
1
0
1
2
3300
0
3300
6600
1
0
1
2
2
6600
95
2
DISTANCE TO RUNWAY THRESHOLD
3
4
5
6
7
8
9
9800 13100 16400 19700 23000 26300 29500
3
4
5
6
7
DISTANCE FROM RUNWAY THRESHOLD
(BRAKE RELEASE)
8
9
10
ft
km
Airplane Characteristics for Airport Planning
A23417
EFFECTIVITY:
APPROACH
LATERAL
DISTANCE
m
ft
Airplane Characteristics for Airport Planning
6.4.
Noise during Ground Operation
The values given for taxiing and static operation are the A–weighted sound level based on the result
of measurements with the microphones at a height of 63 inch (1.6 m). The measurement sites
were free from obstructions and covered mainly with short to medium length grass.
6.4.1.
Taxiing
The table as follow summarizes the average peak dBA level measured with a microphone
array on a line 426 ft (130 m) from a taxiing airplane at different power settings. The taxiing
was performed at normal taxiing speed and with use of the brakes when required to keep
speed.
NOTE:
An advance of the Power Levers just above Ground Idle (GI) to a ”quiet” position (as
judged by the pilot) will give about a 10 dB reduction compared to GI. Also, if
possible, engine shut down or propeller feathered on the engine toward a noise
sensitive area can be used to reduce the noise.
Table, Noise Measured during Taxiing (340B)
Microphones on a line 426 ft (130 m) parallel to the runway
Normal taxiing speed.
Left/Right Engine
Average Peak dBA
GI (1040 PRPM)
81
Quiet PL Position
71
Prop Feathered/GI
6.4.2.
Left Side
Right Side
77
79
Shut down/Quiet PL Position
Left Side
Right Side
65
69
Static Operation
The dBA levels, measured at 492 ft (150 m) radius around the airplane with both engines in
operation, are presented in the following two figures.
The first figure shows the noise footprint for low power operations:
– G I/propeller feathered
– GI and
– Flight Idle (FI).
The next figure shows the noise footprint for high power operations: 40, 80 and 100% torque.
NOTE:
EFFECTIVITY:
Halving of the distance will increase the noise levels 6 to 8 dBA. It should be
mentioned that the wind has a strong effect on upwind noise propagation. At 150
meter a wind velocity of 13 to 23 MPH (6 to 10 m/s) could decrease the noise some
10 dBA.
Ch. 6
Page
8
Jul
01/04
Airplane Characteristics for Airport Planning
6.4.3.
Static Operation at Low Power settings
NOTE:
80
70
dBA levels as measured at 492 ft (150 m) radius. Both engines in operation.
60
dBA
dBA
60
70
80
POWER
GI / PROP FEATHERED
GI / 1040 PRPM
FI / 1040 PRPM
A13394
EFFECTIVITY:
Noise during Static Operation at Low Power settings (340 B)
FIG. 7
Ch. 6
Page
9
Jul
01/04
Airplane Characteristics for Airport Planning
6.4.4.
Static Operation at High Power settings
NOTE:
dBA
90
dBA levels as measured at 492 ft (150 m) radius. Both engines in operation.
80
70
70
80
POWER
40% TORQUE
80%
100%
A13393
EFFECTIVITY:
90
dBA
PRPM
~ 1150
1384
1384
Noise during Static Operation at High Power settings (340 B)
FIG. 8
Ch. 6
Page
10
Jul
01/04
Airplane Characteristics for Airport Planning
6.5.
Propeller Blast Velocities
Ground Idle
NOTE:
Power setting: GI
Condition Lever: Max
Flaps: 15°
Standard day
At the power setting Ground Idle the propeller blast velocities are below 11 Miles Per Hour (5
meters per second) behind the aircraft.
Flight Idle
Power setting: FI
Condition Lever: Max
Flaps: 15°
Standard day
NOTE:
The breakaway point is normally at a power setting between GI and FI.
ft
50
m
15
40
30
20
13–23 MPH
(6–10 m/s)
10
5
24–34 MPH
(11–15 m/s)
10
50
100
150
200 ft
0
10
20
30
40
50
60 m
AFT END OF A/C
A7360
EFFECTIVITY:
Propeller blast velocities, Flight Idle
FIG. 9
Ch. 6
Page
11
Jul
01/04
Airplane Characteristics for Airport Planning
Take Off Power
NOTE:
Power setting: TO
Condition Lever: Max
Flaps: 15°
Standard day
ft
m
50
15
40
30
10
20
5
10
46–58 MPH
(21–26 m/s)
35–45 MPH
(16–20 m/s)
50
100
150
24–34 MPH
(11–15 m/s)
200
250 ft
0
10
20
30
40
50
60
70
80 m
AFT END OF A/C
A7359
EFFECTIVITY:
Propeller blast velocities, Take Off Power
FIG. 10
Ch. 6
Page
12
Jul
01/04
Airplane Characteristics for Airport Planning
6.6.
Engine Exhaust Velocities and Temperatures, APU–mode
The diagram below shows the estimated temperature and velocity profiles behind the engine
running in max APU–mode.
The engine exhaust will meet the smoke limit according to the Proposed Rule in the U.S Federal
Register, March 24, 1978. (40 CFR Part 87).
MAXIMUM AUXILIARY POWER UNIT (APU) AT 93°F (34°C) AMBIENT TEMPERATURE.
m
ft
2.4
8
1.8
6
1.2
4
0.6
2
0
0
0.6
2
1.2
4
1.8
6
2.4
8
ft 0
m 0
A7354
EFFECTIVITY:
TOTAL TEMPERATURE
°F °C
115– 45
140– 60
240– 115
340– 170
540– 280
VELOCITY
ft/s
m/s
8
25
15
50
100
30
20
6
40
12
60
18
80 100 120 140 160 180 200
24 31 37 43 49 55 61
DISTANCE AFT OF ENGINE
Engine Exhaust Velocities and Temperatures, APU–mode
FIG. 11
Ch. 6
Page
13
Jul
01/04
Airplane Characteristics for Airport Planning
6.7.
Hazard Areas
The hazard areas is the areas within which special care must be taken during start and motor–
running of the aircraft engines.
The forward hazard area is a very dangerous area. The suctions from the propellers can pull
persons and equipment into the propellers.
The rear hazard area is a dangerous area. The force of the air behind the propellers and the engine
exhaust gases can cause injury and damage. Heat, stones, sand and other objects can cause injury
to persons or damage to equipment.
PROPELLER AND TURBINE
INFLOW DANGER AREA
15 ft
(4.5 m)
PROPELLER BLAST AND
ENGINE EXHAUST DANGER AREA
98 ft (30m)
3.5 ft
(1m)
A7358
EFFECTIVITY:
Hazard Areas
FIG. 12
Ch. 6
Page
14
Jul
01/04
Airplane Characteristics for Airport Planning
LOADING ON PAVEMENT
7.1.
Gear/Tire Footprint
A7310
Gear/Tire footprint
FIG. 1
TYPICAL MAX DESIGN WEIGHTS, SEE SECTION 2.
LOAD ON MAIN GEAR
Ref. para 7.2.
NOSE GEAR TIRE SIZE
17.5x6.25–6 8 PR TYPE THREEPART
NOSE GEAR TIRE PRESSURE
55 PSI (3.8 BAR)
MAIN GEAR TIRE SIZE
24x7.7 14 PR TYPE VII
MAIN TIRE PRESSURE
115 PSI (7.9 BAR)
EFFECTIVITY:
Ch. 7
Page
1
Jul
01/04
Airplane Characteristics for Airport Planning
7.2.
Main Landing Gear Loading on Ground
340A
A23418
EFFECTIVITY:
Main Landing Gear loading on ground
FIG. 2
Ch. 7
Page
2
Jul
01/04
Airplane Characteristics for Airport Planning
340B
A23419
EFFECTIVITY:
Main Landing Gear loading on ground
FIG. 3
Ch. 7
Page
3
Jul
01/04
Airplane Characteristics for Airport Planning
7.3.
Airplane Classification Number (ACN)
7.3.1.
General
7.3.2.
The ACN data are prepared according to the ACN–PCN system described in ICAO Aerodrome
Design Manual, Part 3 – Pavements, second edition – 1983, appendix 2.
– ACN (Airplane Classification Number) is a number expressing the effect of an airplane on a
pavement.
– PCN (Pavement Classification Number) express the bearing strength of a paved runway for
unrestricted operations.
ACN/PCN method
An airplane with an ACN equal or less than the reported PCN can operate without restrictions
on that runway.
All runways are classified in the Aeronautical Information Publication (AIP) or evaluated of the
airport.
7.3.3.
PCN
7.3.3.1.
Paved runways are divided into two types:
7.3.3.2.
F
Runways with flexible pavement (usually asphalt).
R
Runways with rigid pavement (usually concrete).
PCN values for flexible pavements. The four subgrade categories:
7.3.3.3.
A
High Strength
CBR 15
B
Medium Strength
CBR 10
C
Low Strength
CBR 6
D
Ultra Low Strength
CBR 3
PCN values for rigid pavements. The four subgrade categories:
A
High Strength
K = 150 MN/m3 (550 pci)
B
Medium Strength
K = 80 MN/m3
(300 pci)
K = 40
MN/m3
(150 pci)
K = 20
MN/m3
(75 pci)
C
D
Low Strength
Ultra Low Strength
PAVEMENT
TYPE
PCN
F
R
Flexible
Rigid
SUBGRADE
CATEGORY
A
B
C
D
High
Medium
Low
Ultra Low
TIRE–PRESSURE
CATEGORY
W
X
Y
Z
No Limit
To 1.5 MPa (217 psi)
To 1.0 MPa (145 psi)
To 0.5 MPa (73 psi)
EVALUATION
METHOD
T
U
Technical
Using airplane
PCN Table 1
EFFECTIVITY:
Ch. 7
Page
4
Jul
01/04
Airplane Characteristics for Airport Planning
7.3.4.
Example
Find the ACN (Airplane Classification Number) of an airplane on a pavement.
Information:
– One runway have PCN 21 F/B/X/T
– The airplane gross weight is 12000 Kg
– The pavement type is flexible (F)
– The subgrade category is medium (B)
Procedure:
7.3.5.
1
Go to FIG. 4, Flexible Pavement (F)
2
Find airplane gross weight 12000 Kg
3
Follow the line 12000 up, until you cross the CBR 10 (B) line
4
Follow the horizontal line to the left, until you cross ACN line
5
You find ACN 6
6
The ACN 6 is less than PCN 21, the aircraft can be operate the runway without restrictions.
Abbreviations used:
EFFECTIVITY:
ACN
Airplane Classification Number
PCN
Pavement Classification Number
CBR
California Bearing Ratio; system for assessing ability of soft surfaces to support
airplane operations.
K
Subgrade strength.
MN/m3
Mega Newton per cubic meter
pci
Pounds per cubic inch
Ch. 7
Page
5
Jul
01/04
Airplane Characteristics for Airport Planning
NOTE:
ACN
ACN DETERMINED AS REFERENCED IN ICAO AERODROME DESIGN MANUAL
PART 3 – PAVEMENTS, SECOND EDITION 1983, APPENDIX 2
93% LOAD ON MAIN GEAR. TO DETERMINE MAIN GEAR LOADING, SEE 7.02
STANDARD TIRES WITH STANDARD INFLATION PRESSURE.
10
SUBGRADE CLASSES
9
8
CBR 3 (ULTRA LOW)
CBR 6 (LOW)
CBR 10 (MEDIUM)
CBR 15 (HIGH)
7
6
5
4
3
2
1
21000
22000
9525
10000
23000
10500
24000
11000
25000
26000
11500
27000
12000
28000
12500
29000 lb
13000 kg
AIRPLANE GROSS WEIGHT
A23421
EFFECTIVITY:
Airplane Classification Number (ACN) – Flexible Pavement
FIG. 4
Ch. 7
Page
6
Jul
01/04
Airplane Characteristics for Airport Planning
NOTE:
ACN
10
ACN DETERMINED AS REFERENCED IN ICAO AERODROME DESIGN MANUAL
PART 3 – PAVEMENTS, SECOND EDITION 1983, APPENDIX 2
93% LOAD ON MAIN GEAR. TO DETERMINE MAIN GEAR LOADING, SEE 7.02
STANDARD TIRES WITH STANDARD INFLATION PRESSURE.
SUBGRADE CLASSES
9
8
K=20 (ULTRA LOW)
K=40 (LOW)
K=80 (MEDIUM)
K=150 (HIGH)
7
6
5
4
3
2
1
21000
9525
22000
10000
23000
10500
24000
11000
25000
26000
11500
27000
12000
28000
12500
29000lb
13000 kg
AIRPLANE GROSS WEIGHT
A23420
EFFECTIVITY:
Airplane Classification Number (ACN) – Rigid Pavement
FIG. 5
Ch. 7
Page
7
Jul
01/04