Schweizer 2-33 User manual

National Défense
Defence nationale
A-CR-CCP-402/MB-001
OPERATING MANUAL
AIR CADET GLIDING PROGRAM
2-33 SCHWEIZER
AIRCRAFT OPERATING INSTRUCTIONS
ENGLISH
(Replaces Chapter 2 Section 2 of the A-CR-CCP-242/PT-005 dated 31 Jan 2012)
Cette publication est disponible en français sous A-CR-CCP-402/MB-002(F)
Issued by the Commander Royal Canadian Air Force under the authority of the Chief of
Defense Staff
OPI: 2 Canadian Air Division / Director Air Force Training 2017-01-31
NOTICE
This document has been reviewed by the technical authority and does not
contain controlled goods. Disclosure notices and handling instructions
originally received with the document shall continue to apply.
This document is electronically controlled and should not be
considered current when printed.
.

i
FOREWORD
1. 2-33 Schweizer Aircraft Operating Instructions are issued by the Commander RCAF
under the authority of the CDS.
2. This publication is effective on receipt and supersedes all previous editions and
amendments, which are to be withdrawn and destroyed.
3. Comments and suggestions should be forwarded through the appropriate Region Chain
of Command to the NCA Ops O at NATL CJCR SP GP, info 2 CDN AIR DIV / Dir AF Trg /
ACGPSET.
4. There are two manuals pertaining to the 2-33 Schweizer Glider:
a. Aircraft Operating Instructions (AOI) produced by DND; and
b. The SGS 2-33 Sailplane Flight-Erection-Maintenance Manual produced by K & L
Soaring LLC.
5. The SGS 2-33 Sailplane Flight-Erection-Maintenance Manual produced by K & L
Soaring LLC is the legal controlling document that must be carried on board the aircraft during
flight. There is no need to carry the AOIs in the glider.
6. All information in this document is applicable for both the 2-33 and 2-33A unless indicated
otherwise.
7. All speeds are IAS unless indicated otherwise.
8. Note, Caution, and Warning headings in this manual are defined as follows:
NOTE
To point out a procedure, event or practice which it is desired or
essential to highlight.
CAUTION
To emphasize operating procedures, practices, etc., which, if not
correctly followed, could result in damage to or destruction of
equipment.
WARNING
To emphasize operating procedures, practices, etc., which, if not
correctly followed, could result in personal injury or loss of life.
Contact Officer: OC ACGPSET, 2 Cdn Air Div / Dir AF Trg
© 2016 DND/MDN Canada

ii
Number Date of Amendment Entered By Date Entered
0 A-CR-CCP-242/PT-005
Chapter 2 Section 2 DOAM 31 Jan 2012
1 31 January 2017 DOAM - New Issue
Text and illustration changes are indicated by black vertical lines ( I) in the margin of the
applicable pages.
Total number of pages for this publication is: 53
Noted changes are those from 31 Jan 2012 edition of the A-CR-CCP-242/PT-005 Chapter 2
Sections 1, 2, 4, 5, 6, and 7. Change 1 consists of the following:
Page No. Change No.
Page No. Change No.
Add Cover Page, List of Effective Pages,
Document organized to meet requirements
Releasing Authority info, Note-Caution-
of RCAF Flight Publications
Warning info, and Table of Contents......1
Development Manual as much as able
for civilian pattern aircraft ......................1
Section 1 now Aircraft & Systems Description
1-1 para 2 & 3 added for clarity ..................1
1-2 para 10a - information on rudder
Figure 1-1 - tire pressures added...........1
blocks added....................................1
para 5 - solo from front only added........1
para 11b - operation of bungee type
para 6 - seating information added ........1
trim added ........................................1
1-2 para 8c - information on different
1-3 para 11c - Ratchet-lock trim information
braking action of hydraulic system
added as per page 8 of 2010
added................................................1
owner manual...................................1
Section 2 now Limitations
2-1 Figure 2-1 - Winch/Auto Launch safety
2-4 para 1 - max take-off weight updated...1
speeds added to chart
2-5 para 3a and 3b - Seat ballast info
- and - 1080 Gross Weight added.....1
added ...............................................1
Figure 2-2 - 1080 Gross Weight added..1
para 4 - information on interpreting
2-2 Figure 2-3 - updated for 1080 Gross.....1
loading graph updated to include
2-4 Figure 2-5 - chart added .......................1
seat ballast info ................................1

TABLE OF CONTENTS
iii
Section 3 now Normal Procedures
3-1 para 1 - "student qualified to carry out
3-3 para 4 - "front seat" added to para to
DIs" added........................................1
clarify that VON requirements only
para 2 a (1) to (10) - background
apply to front seat.............................1
information added.............................1
3-4 Figure 3-2 - "FRONT" added to title and
3-2 para 2 a (16) cushion and spacer
info box added..................................1
condition updated as per PM from
3-5 para 9 e - option to use a curved back
FSOM 142273 and PIF 8-13 ............1
spacer updated.................................1
para 2 a (17) seat belt condition
para 9 g - placement of seat ballast
updated as per PM from FSOM
added................................................1
142273 and PIF 8-13........................1
3-6 Figure 3-5 - seat ballast location
3-3 para 2 e (2) - background info added
added................................................1
- - - AND - - - damper info added as
3-7 para 14 - requirement to confirm full
per 2013 Stds WG Minute #24......... 1
movement of control column added..1
3-3 para 2 e (3) - Tire pressure info as per
paras 15 to 18 - CUSHION AND
K&L/NTA communication Dec 2014.1
SPACER CONDITION added as per
para 3 - added to assist clarity ..............1
PM from FSOM 142273 and National
PIF 8-13............................................1
3-7 paras 19 a,b,c, and d - background
3-11 - LAUNCH SPEEDS taken from former
information added.............................1
ACGPM Chap 2 Sec 4, 5,and 6........1
3-8 para 20 e - trim setting standardized....1
para 27 - source of ground launch
safety speed added ...........................1
Section 4 now Flight Handling
4-1 - Figure 4-1 updated to include 1080
4-3 SAFETY CHECK (A)ttitude - reference
gross weight information ..................1
removed and replaced with "the
4-2 Figure 4-2 added to further address
published minimum altitudes" as per
PM from 1010-C-GCLB 2014...........1
2016 Stds Writing Board...................1
Figure 4-3 updated for 1080 lb MTOW
PRE-LANDING CHECK - (A)irspeed - ref
and "SAMPLE ONLY" added............1
to pre-determined airspeeds replaced
4-3 PRE-RELEASE CHECK (A)rea -
by "Calculate the approach speed" as
"pre-briefed release point" now reads
per 2016 Stds Writing Board.............1
"desired release area" as per 2016
4-4 CAUTION for using spoilers with slip
Stds Writing Board ...........................1
added as per PM from 1010-C-CLB
"Pre-stall, spin, spiral check"
2014..................................................1
renamed "SAFETY CHECK" to
paras 2 and 3 and CAUTION added,
match A-CR-CCP-242 ACGPM........1
info taken from 2010 owner manual..1
Section 5 now Emergency Handling
5-2 "UNUSUAL ATTITUDE RECOVERIES"
added and Stall, Incipient Spin, Full
Spin, and Spiral Dive recoveries
updated as per 2016 Stds Writing
Board................................................ 1

iv
Section 6 now Ground Movements
6-1 para 1 - locking of controls added.........1
6-4 para 14 e - information on spoiler
para 2 - choice of pushing or pulling
settings and connection to hydraulic
on struts and nose added..................1
brakes added...................................1
para 5 a, b & c - additional steering info
Figure 6-4 added as per 2015 MRM
added................................................1
Minute #20........................................1
6-2 para 12 a & b - explanatory para of
Figure 6-5 added as per 2015 MRM
representative tie-downs and their use
Minute #20........................................1
added with diagram...........................1
para 15 d - information on spoiler
6-3 para 14 a - preventing
settings and connection to weather
sideways movements added............1
and wildlife added.............................1
6-4 para 14 d - rudder lock info added........1
6-6 para 17 - information on carabiner
type hooks and ratchets added ........1
6-6 para 18 - "Open-Air" added to title for
6-6 para 19 - now refers to owner manual..1
clarity and now refers to owner
NOTE about winds added .....................1
manual..............................................1
Annex A now Glider Daily Inspection
A-1 - comments and advice removed from
A-1 - DI sheet updated to match
DI sheet - now with information in
amendments In Chapter 3................1
Sec 3 - as per 2016 Stds WG ...........1
Annex B now Glider Open-Air Trailer Loading Check List
B-1 - "OPEN-AIR" added to checklist title...1
B-1 - 3a - "control stick" now "control push
B-1 - 2b - reference to D-ring removed .......1
rods".................................................1
Annex C now Glider Final Assembly Check List
C-1 para 2 - "test" now "first" flight..............1
C-1 - 2nd column added..............................1
C-1 - 7 a - title of owner manual added.......1
C-1 - 2nd signature block added..................1
Annex Dnow Glider Maintenance Flight Card
D-1 Card added as per 2015 MRM, items
as per Stds Os 2016 .........................1

TABLE OF CONTENTS
v
Section 1 – AIRCRAFT & SYSTEMS DESCRIPTION.................................... 1-1
General Description..................................................................................... 1-1
Specifications.............................................................................................. 1-1
Seating Configuration.................................................................................. 1-1
Flight Controls............................................................................................. 1-2
Section 2 – LIMITATIONS.............................................................................. 2-1
Airspeed Limitations.................................................................................... 2-1
Limit Load Factor......................................................................................... 2-1
Understanding the Flight Envelope ............................................................. 2-2
Surface Wind Operational Limitations......................................................... 2-3
Weight and Balance.................................................................................... 2-5
Section 3 – NORMAL PROCEDURES........................................................... 3-1
Daily Inspection........................................................................................... 3-1
Cockpit Ergonomics .................................................................................... 3-3
Control Column and Seat Spacers.............................................................. 3-7
Cushion and Spacer Condition.................................................................... 3-7
Limited Pre-Flight Inspection....................................................................... 3-7
Pre-Take-Off Check .................................................................................... 3-8
Hook-Up Procedure..................................................................................... 3-8
Schweizer Glider Release Mechanism...................................................... 3-10
Use of C of G and Forward Hooks ............................................................ 3-11
Launch Speeds ......................................................................................... 3-11
Section 4 – AIRCRAFT HANDLING............................................................... 4-1
General ....................................................................................................... 4-1
Flight Speeds .............................................................................................. 4-1
Pre-Release Check..................................................................................... 4-3
Safety Check............................................................................................... 4-3
Pre-Landing Check...................................................................................... 4-3
Slipping ....................................................................................................... 4-3
Touch Down................................................................................................ 4-4
Section 5 – EMERGENCY HANDLING.......................................................... 5-1
Launch Emergencies................................................................................... 5-1
Canopy Open in Flight................................................................................. 5-1
Unusual Attitude Recoveries....................................................................... 5-2
Section 6 – GROUND MOVEMENTS ............................................................ 6-1
Moving......................................................................................................... 6-1
Moving by Hand .......................................................................................... 6-1
Towing by Vehicle....................................................................................... 6-1
Towing by Tow Bar...................................................................................... 6-2
Tie-Downs................................................................................................... 6-2

vi
Permanent Tie-Downs .................................................................................6-3
Temporary Tie-Downs..................................................................................6-5
Flight Line Tie-Downs ..................................................................................6-5
Tie-down Ropes and Straps.........................................................................6-6
Use of Open Air Trailers...............................................................................6-6
Erection Procedure ......................................................................................6-6
Annex A - Glider Daily Inspection ...............................................................A-1
Annex B - Glider Open-Air Trailer Loading Checklist..................................B-1
Annex C - Glider Final Assembly Checklist.................................................C-1
Annex D - Glider Maintenance Flight Card..................................................D-1

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
1-1
SECTION 1 – AIRCRAFT & SYSTEMS DESCRIPTION
GENERAL DESCRIPTION
1. The 2-33 is a conventional two-place tandem intermediate training glider manufactured by
Schweizer Aircraft Corporation, Elmira, New York. Its construction is all metal with a fabric cover
on the fuselage and the horizontal tail surfaces. It has a one-
piece canopy for increased visibility.
The wings are tapered in the outboard section and have spoilers/dive brakes incorporated.
2. There are two variants of the 2-33. The 2-33A included a larger rudder with an
aerodynamic balance horn. The 2-33AK came as a kit that was completed by the buyer.
(above para added 2016)
3. As all aircraft have been standardized to a large extent, no differentiation will be made
between models in this manual and 2-33 will be used to denote all variants.
(above para added 2016)
SPECIFICATIONS
Length 25 ft 9 in
Span 51 ft 0 in
Height 9 ft 3 ½ in
Wing Area 219.48 sq ft
Aspect Ratio 11.85 : 1
Tire Pressures Hydraulic Brakes: 28-30 psi Mechanical Brakes : 15 psi
Figure 1-1 Specifications
(chart updated 2016)
SEATING CONFIGURATION
4. The ACGP 2-33 Glider is a tandem two seat configuration enabling solo or dual flight.
5. Solo flight is conducted from the front seat only
(above para added 2016)
6. Some pilots may require seat spacers and cushions to ensure the required sight line
over the nose. See Section 3 NORMAL PROCEDURES - USE OF SEAT SPACERS AND
SEAT CUSHIONS for proper installation and information on acceptable condition.
(above para added 2016)

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
1-2
FLIGHT CONTROLS
7. Tow Release Knobs:
a. Front. Located at centre bottom of the instrument panel.
b. Rear. Located at top left of the front seat back.
c. Operation. To release, pull red knob out fully.
8. Spoiler and Brake Levers:
a. Front. Located on the left side of cockpit below the level of the instrument panel.
b. Rear. Located at centre of the left side of cockpit.
c. Operation. Push forward and down to unlock, and pull straight back to desired
position. The wheel brake is actuated only at the extreme aft position of the
spoiler/wheel-brake control handle. The rearward pressure applied on the spoiler
handle controls the degree of braking. Gliders may be equipped with either a
mechanical or a hydraulic brake system. The hydraulic system provides firmer braking
action.
(above para amended 2016)
9. Control Column. Front and rear controls are conventional in design and are mounted on
a single torque tube.
10. Rudder pedals. The following are applicable:
a. Front. The conventional left and right toe pedals are located forward of the floorboard
and are adjustable. Some 2-33 are equipped with rudder blocks on the front rudder
pedals that can be lifted up and over to provide additional adjustments for leg length.
(sub para 10a amended 2016)
b. Rear. The conventional left and right toe pedals, located on either side of the front
seat, are not adjustable.
11. Trim Lever. One of three types of trim control is provided in the front cockpit, depending
on the year of manufacture of the glider:
a. A bungee-type control mounted on the floor in front of the control column; or
b. A bungee type control mounted on the left cockpit wall below the spoiler handle:
(1) Operation – trim can be set to one of the four notches. The pilot can
adjust the trim forward or aft to help remove control column pressure
(2) Trim should be set to full forward for take-off.
(3) Setting bungee type trim in cruise flight:

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
1-3
(a) Set attitude as required;
(b) Move trim handle to alleviate control column pressure; then
(c) Adjust trim as necessary for other attitudes.
c. A ratchet-type control mounted on the base of the control column (Stick Trim). A
lever on the control column adjusts a ratchet system mounted below the cockpit
floor.
(1) Operation of Stick Trim - The trim is operated with the fingers of the control
column hand by aft pressure on the locking lever. The control stick is then
moved to the position that gives the desired attitude at which point the
locking lever is released to engage the trim lock.
(2) Stick Trim should be full forward for take-off.
(3) Setting Stick Trim in cruise flight:
(a) if time and altitude permit, allow the control column to move to the
trimmed position;
(b) gently squeeze and hold the Stick Trim lever back against the
control column;
(c) while holding the Stick Trim lever in position, adjust the control
column position to set the desired cruise attitude/airspeed;
(d) once established, gently release the Stick Trim lever; then
(e) give the Stick Trim lever a small push forward to positively engage
the ratchet.
(above sub paras added 2016)
12. Instruments. Flight instruments are mounted on the instrument panel in the front cockpit,
and include altimeter, airspeed indicator, magnetic compass and either a VSI or variometer.
Some gliders are equipped with instrument panel mounted radios and transponders.

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
1-4
Figure 1-2 Cockpit
Figure 1-3 Example Instrument Panel

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-1
SECTION 2 – LIMITATIONS
AIRSPEED LIMITATIONS
Gliders with a Max
Gross Weight of 1040
lbs
Gliders with a Max
Gross Weight of 1080
lbs
98 mph VNE Never Exceed Speed 100 mph
98 mph Max Dive Speed 100 mph
98 mph Max Air Tow Speed 100 mph
98 mph Max Speed (spoilers open) 100 mph
69 mph Max Auto / Winch Speed 70 mph
65 mph 1VA Manoeuvring Speed 166 mph 1
50 mph Winch/Auto Launch Safety Speed 50 mph
Figure 2-1 Airspeed Limitations (updated 2016)
LIMIT LOAD FACTOR
Maximum Take-off Weight 1040 lbs 1080 lbs
Ultimate Load Factor 27.0 G 2
Limit Load Factor 14.67 G 1
Figure 2-2 Limit Load Factor (updated 2016)
CAUTION
1. Over 65 mph, the pilot must manoeuvre with caution.
Although the limit load factor of 4.67 G should never be exceeded,
the pilot can do so inadvertently with abrupt manoeuvres. Speeds
between 65 mph and the 98 mph (or 66 mph and 100 mph for
those gliders with gross weight of 1080 lbs) shall be treated as a
cautionary range and manoeuvring within this range should be
reduced to a minimum as velocity increases.
CAUTION
2. A safety factor of 1.5 is required for certification giving an
ultimate load factor of 7.0 G to allow for material variations and
inadvertent atmospheric conditions. Because of its light wing
loading, the 2-33 can develop very high loads if speed limitations
are not rigidly observed.

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-2
Figure 2-3 The Flight Envelope (added 2016)
UNDERSTANDING THE FLIGHT ENVELOPE
The following paragraphs are taken from The SGS 2-33 Sailplane Flight-Erection-Maintenance
Manual, K&L Soaring and are provided to assist with understanding Figure 2-3 Flight Envelope:
"The FAA* required design flight envelope is presented on the
[graph]. On the horizontal axis are indicated velocities in miles per
hour, and on the vertical axis are load factors expressed in "G" units.
The straight lines labeled [sic] "gust load factors" represent the effect
of the FAA required 24 ft. per second gust on the sailplane as speed
varies. They diverge from the one "G" situation where the glider
would be at rest or in perfectly balanced level flight. The curved lines
diverging from zero "G" represent forces which can be induced by
moving the elevator (or other) control abruptly at various speeds. As
you can see, the faster you fly the more effect moving your controls

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-3
will have. Gusts will also have more effect as speed increases.
The speed for maneuvering [sic] with caution occurs where "G"
loading from an abruptly moved control meets the 4.67 limit load
factor. Assuming smooth and limited movements of the controls, the
placard or "red-line" speed occurs where gusts could meet the 4.67
limit load factor without any maneuvering [sic].
Normal placard speeds are reduced 10% from design speeds to
provide an extra margin of safety. Thus, on the graph, the diagonal
hatched area indicates speeds at which you must use caution in
maneuvers [sic]. You should neither maneuver [sic] nor fly so fast as
to expose your ship to loads within the crosshatched area marked,
"NO MANEUVER"[sic].
It can be inferred from the graph that abrupt maneuvering [sic] in
gusty conditions is dangerous and can lead to very high "G" loads.
In normal operation the major cases of high "G" loads are tight
spirals in thermals which would not normally exceed 2 or 2.5 G's.
Winch or auto towing can produce high loads, but if the auto-winch
placard speed is observed, this will be within safe limits. The best
ground launch climb is obtained at speeds well below placard limits.
* FAA - Federal Aviation Authority, the United States government organisation equivalent to
Transport Canada.
SURFACE WIND OPERATIONAL LIMITATIONS
Max Headwind 25 kts (28 mph)
Max 90oCrosswind 8 kts (10 mph)
Max Tailwind 5 kts (6 mph)
Wind Gusts 10 kts (12 mph)
Figure 2-4 Surface Wind Operational Limitations

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-4
SHOWN EXAMPLE: 10 KT wind 450off runway heading
SOLUTION: Enter wind angle at 450, follow radial inward
to 10 KT wind speed arc. At the intersection of the radial
and the arc, read straight down for the crosswind
component and straight across for the headwind
component.
Could you fly a 2-33 in this example? YES!
Figure 2-5 Crosswind Component Chart

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-5
WEIGHT and BALANCE
1. Maximum take-off weight of the aircraft is 1040 pounds or 1080 pounds.
(above para updated 2016)
2. The glider must be operated within the maximum limit of take-off weight, and it must be
balanced within the forward and rearward C of G limit. The weight and empty C of G of each
glider is determined at manufacture or on subsequent reweighing and this information must then
be used to calculate the operational weight and balance.
3. Some pilots may need a ballast to keep the C of G within approved limits. There are two
types of removable ballast approved for use in the ACGP 2-33:
a. A ballast block installed in the nose of the glider between the rudder pedals. This
ballast is far ahead of the pilot seat and the effect of its installation on the C of G is
indicated on the loading graph.
b. A seat ballast fitted under the cushion or, if needed, the lowest seat spacer. In this
case, the weight of the ballast is added to the pilot's weight. Accordingly, the
Loading Graph (Fig 2-5) does not include seat ballast information.
(above sub paras added 2016)
4. Loading Graph. Each ACGP 2-33 has a Loading Graph located in a visible area of either
cockpit which allows the pilot to easily determine the correct loading, solo or dual, with or without
ballast. References to Ballast in the Loading Graph in Figure 2-5 refer to the red removable
ballast, not the Seat Ballast. Add the weight of the Seat Ballast to weight of the pilot before using
the Loading Graph.
(para updated 2016)

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-6
Figure 2-6 Sample 2-33 Loading Graph for a 1040 lb gross weight glider
Figure 2-7 Sample Cockpit Placards for a 1040 lbs gross weight glider
0
50
100
150
200
250
300
350
050 100 150 200 250 300 350 400
1. Project horizontal line at front seat load.
2. Project vertical line at rear seat load.
3. If intersection of the lines is within the
envelope, the C.G. is within limits.
4. Gross weight must not exceed 1040 lbs.
5. Solo flight from front seat only.
No Ballast
Ballast
Forward C of G Limit
Rear C of G Limit
Max Weight Limit
C-FQON
Lbs.
Rear Seat Load
Front Seat Load
Kg.
Kg.
0
20
40
60
80
100
120
140
160
020 40 60 80 100 120 140 160 180
1. Project horizontal line at front seat load.
2. Project vertical line at rear seat load.
3. If intersection of the lines is within the
envelope, the C.G. is within limits.
4. Gross weight must not exceed 1040 lbs.
5. Solo flight from front seat only.

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
2-7
5. Placards. Placard weights are installed in the cockpit of the 2-33. The following example
details how to interpret the factory placards:
Maximum weight aft pilot/220 lbs forward 150 lbs
Minimum weight aft pilot/100 lbs forward 120 lbs
Minimum weight forward pilot solo 134 lbs
Figure 2-8 Example Cockpit Placard for a 1040 lbs gross weight glider.
a. Maximum Weight Aft Pilot/220 Forward 150. If the front seat occupant,
including any seat ballast, weighs 220 lbs, then the maximum weight of the
rear seat occupant cannot be more than 150 lbs, since the maximum
useable load for this glider is 370 lbs (220 plus 150). Adherence to this limit
is essential to ensure that the useable maximum weight of the glider is not
exceeded.
b. Minimum Weight Aft Pilot/100 Forward 120. If the front seat occupant,
including any seat ballast, weighs 100 lbs, then the minimum weight of the
rear seat occupant cannot be less than 120 lbs, in order to properly balance
the glider. Adherence to this limit is essential to ensure that the aft C of G is
maintained within the approved limit
c. Minimum Weight Forward Pilot, Solo 134. Adherence to this placard is
essential to ensure that the C of G is maintained within approved limits for
solo flight. Ballast, either block or seat, must be added if the weight of the
solo pilot is less than the placard minimum.

A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
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