Defence nationale
.
National Défense
A-CR-CCP-402/MB-001
OPERATING MANUAL
AIR CADET GLIDING PROGRAM
2-33 SCHWEIZER
ENGLISH
(Replaces Chapter 2 Section 2 of the A-CR-CCP-242/PT-005 dated 31 Jan 2012)
Cette publication est dispo nible en fr anç ais sous A -CR-CCP-402/MB-002(F)
AIRCRAFT OPERATING INSTRUCTIONS
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. Dis clos ure not ices and han dl ing instruc t ions
originally received with the document shall continue to apply.
This document is electronically controlled and should not be
considered current when printed.
FOREWORD
Contact Officer: OC ACGPSET, 2 Cd n Air Div / Dir AF Trg
© 2016 DND/MDN Canada
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amendments, which are to be withdrawn and destroyed.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 Op s 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 Schweiz er Gli der :
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 i s appli c able for both the 2-33 and 2-33A unless i ndic ated
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 highli g ht .
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.
i
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 in fo ................................ 1
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:
ii
TABLE OF CONTENTS
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" ad ded to titl e 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 update d ................................. 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 ball as t 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 co ntr ol 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 an d 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 t o furth er addr ess
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 ON LY" 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 St ds Writing
Board ................................................ 1
iii
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 advic e remov ed fro m
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 add ed .......1
C-1 - 2nd signature block added .................. 1
Annex D now Glider Maintenance Flight Card
D-1 Card added as per 2015 MRM, items
as per Stds Os 2016 .........................1
iv
TABLE OF CONTENTS
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 Reco veries ....................................................................... 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
v
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
vi
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
piece canopy for increas ed visibility.
SECTION 1 – AIRCRAFT & SYSTEMS DESCRIPTION
GENERAL DESCRIPTION
1. The 2-33 is a conventional tw o-pl ace t andem i nt ermedi ate tr ai ni ng g lider manu fact ur ed by
Schweizer Aircraft Corpor ati on, El mir a, N ew York. Its construction is all metal w it h a fabric cover
on the fuselage and the hori zontal tail surfaces. It has a oneThe wings are tapered in the outbo ar d sec ti on and hav e s poi ler s /div e brakes i ncor por ated.
2. There are two variants of the 2-33. The 2-33A included a larger rudder w it h 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 standardiz ed t o a lar g e extent, no differentiation wil l be made
between models in this manual a nd 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 ins tal l ati o n and i nfor m ati on on acc e ptable condition.
(above para added 2016)
1-1
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
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 se at 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 o f coc kpi t.
c. Operation. Push forward and down to unlock, and pull str aight back to desired
position. The wheel brake is act uated onl y at the extreme aft position of the
spoiler/wheel-brake cont r ol handl e. Th e r earward pressure applied on the spoil er
handle controls the degree of br aki ng . Gliders may be equipped with eit her a
mechanical or a hydrauli c br ak e sy stem. The hy dr aulic system prov ides firmer br aki ng
action.
(above para amended 2016)
9. Control Column. Front and rear controls are conventional in desig n and are mounted on
a single torque tube.
10. Rudder pedals. The following are applicable:
a. Front. The conventional left and rig ht toe pedal s ar e l oc ated forward of the floorboard
and are adjustable. Some 2-33 are equi pped w i th r udder bloc ks on the front rudder
pedals that can be lifte d up and over to provide additional adjustments for leg length.
(sub para 10a amended 2016)
b. Rear. The conventional left and r i g ht t oe pedals , l ocat ed on eit her si de o f the front
seat, are not adjustable.
11. Trim Lever. One of three types of trim control i s pr ov ided i n the front cockpit, depending
on the year of manufacture of the g l i der :
a. A bungee-type control mounted on th e floor i n front of the control column; or
b. A bungee type control mounted on the left cockpit wal l bel ow t he spoiler handl e:
(1) Operation – trim can be set to one of the four notches . The pi l ot c an
adjust the trim forwar d or aft to hel p r emov e c ontr ol col umn pres sur e
(2) Trim should be set to full forward for take-off.
(3) Setting bungee type trim in cruise flight:
1-2
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
(a) Set attitude as required;
(b) Move trim handle to alleviate control column pr ess ur e; then
(c) Adjust trim as necessary for other attitudes.
c. A ratchet-type control mounted on the base of the control col umn ( St i ck Tri m). A
lever on the control column adjust s a r atc het system mounted below the cock pi t
floor.
(1) Operation of Stick Trim - The trim is operated wi th t he fing ers of the c ontr ol
column hand by aft press ure on t he loc ki ng l ev er . The contr ol sti c k is then
moved to the position that g iv es t he desi r ed atti tude at which point the
locking lever is released to eng ag e the tr i m loc k.
(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 ins tr umen t pan el i n the front c ock pit ,
and include altimeter, air s peed indi c ator , mag neti c c ompass and eit he r a VSI or variometer.
Some gliders are equipped with instrument pa nel mount ed r adi os an d t rans ponder s.
1-3
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Figure 1-2 Cockpit
Figure 1-3 Example Instrument Panel
1-4
AIRSPEED LIMITATIONS
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
SECTION 2 – LIMITATIONS
Gliders with a Max
Gross Weight of 1040
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 1 VA Manoeuvring Speed 1 66 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 2 7.0 G 2
Limit Load Factor 1 4.67 G 1
lbs
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 al low 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.
2-1
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
you can see, the faster you fly the more effect moving your contr ols
Figure 2-3 The Flight Envelope (added 2016)
UNDERSTANDING THE FLIGHT ENVELOPE
The following paragraphs ar e taken from The SGS 2-33 Sailplane Flight-Erection-Maintenance
Manual, K&L Soaring and ar e provided to assist with understandi ng Figure 2-3 Flight Envelope:
"The FAA* required design f li ght env el ope is presented on the
[graph]. On the horizontal ax is ar e indi c ated vel oc it ies i n mil es per
hour, and on the vertical axi s are l oad fac tor s expr ess ed i n "G" unit s.
The straight lines labeled [sic] "gust load factors" represent the effec t
of the FAA required 24 ft. per s econd gus t o n the sailplane as speed
varies. They diverge from the one "G" situation where the gl i der
would be at rest or in perfectl y balanc ed l evel fl i ght. T he cur v ed li nes
diverging from zero "G" r epr esent f orc es whi ch c an be induc ed by
moving the elevator (or other) control abruptl y at var i ous s peeds. A s
2-2
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
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 mov ed cont rol m eets the 4.67 l i mit load
factor. Assuming smooth and limited movements of the control s, t he
placard or "red-line" s peed occ ur s wher e gusts could meet the 4.67
limit load factor without any maneuvering [sic].
Normal placard speeds are reduc ed 10% f rom des i gn speeds to
provide an extra margin of safety. Thus , on the graph, the diagonal
hatched area indicates speeds at w hi ch y ou m ust use c auti on in
maneuvers [sic]. You should neit her maneuver [sic] nor fly so fast as
to expose your ship to loads wit hin t he cr os sh at ched ar ea marked,
"NO MANEUVER"[sic].
It can be inferred from the graph that abr upt maneuvering [sic] in
gusty conditions is dangerous and c an lead to very high "G" loads.
In normal operation the major cases of high "G" loads are t ight
spirals in thermals which would n ot nor mally exceed 2 or 2.5 G's.
Winch or auto towing can produc e high l oa ds , but i f t he auto-winch
placard speed is observed, thi s wil l be withi n s afe l im i ts . T he 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 90o Crosswind 8 kts (10 mph)
Max Tailwind 5 kts (6 mph)
Wind Gusts 10 kts (12 mph)
Figure 2-4 Surface Wind Operational Limitations
2-3
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
SHOWN EXAMPLE: 10 KT wind 450 off 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
2-4
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
WEIGHT and BALANCE
1. Maximum take-off weight of the aircr aft is 104 0 pounds or 1080 pounds.
(above para updated 2016)
2. The glider must be operated within the max i mum limi t o f take-off weight, and it must be
balanced within the forw ard and rearward C of G limit. The weight and empty C of G o f eac h
glider is determined at manufact ur e or on sub s eq uent r ew eig hing 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 w i thi n appr oved limits. There are two
types of removable ball ast appr oved for use in the ACGP 2-33:
a. A ballast block installed in t he nose o f the g l i der bet ween the rudder pedals. This
ballast is far ahead of the pi lot seat and the effect of its installat ion on the C of G is
indicated on the loading gr aph.
b. A seat ballast fitted under the cus hi on or, if n eeded, th e l owest seat spacer. In this
case, the weight of the bal las t i s added t o the pi l ot's w eight . Ac cor di ngly , the
Loading Graph (Fig 2-5) does not include seat ballast informati on.
(above sub paras added 2016)
4. Loading Graph. Each ACGP 2-33 has a Loading Graph located in a visible ar ea of either
cockpit which allows the pilot to easily determine the correc t l oading, solo or dual, with or w i thout
ballast. References to Ball ast in t he Loading Graph in Figure 2-5 refer to the red remov abl e
ballast, not the Seat Ballast. Add the weig ht of the S eat B al l ast t o weight of the pilot before using
the Loading Graph.
(para updated 2016)
2-5
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
0
50
100
150
200
250
300
350
0
50 100 150 200 250 300 350
400
1. Project horizontal line at f ront seat load.
2 . Proj ec t verti c al l i ne at r ear seat l oad .
3. If int ersection of t he lines is wit hin t he
envelope, t he C.G. is within limits.
4. Gross weight must not exc eed 1040 lbs.
5. Solo f light f rom f ront seat only.
No Ballast
Ballast
Forw ard C of G Limit
Rear C of G Limit
M a x Weight Limit
C-FQON
Rear Seat Load
Front Seat Load
Kg.
Kg.
0
20
40
60
80
100
120
140
160
0 20 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.
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
2-6
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
5. Placards. Placard weights are ins tal led i n the cock pit of the 2-33. The following example
details how to interpr et the factor y placards:
Maximum weight aft pilot/220 lbs forwar d 150 lbs
Minimum weight aft pilot/100 lbs forwar d 120 lbs
Minimum weight forward pilot solo 134 lbs
Figure 2-8 Example Cockpit Placard for a 1040 lbs gross weight gl i der.
a. Maximum Weight Aft Pilot/220 For ward 150. If t he front s eat occupant,
including any seat ballast, weighs 220 lbs, then the max i mum w eig ht of the
rear seat occupant cannot be more than 1 50 lbs, since the maximum
useable load for this glider is 370 l bs ( 220 pl us 150) . Adher enc e to t his limit
is essential to ensure that the useable maximum weight of the g l i der is not
exceeded.
b. Minimum Weight Aft Pilot/100 Forward 120. If the front seat occup ant,
including any seat ballast, weighs 100 lbs, then the minimum w ei g ht of the
rear seat occupant cannot be less than 120 l b s , i n order t o proper ly balance
the glider. Adherence to this limit is ess enti al to ensur e 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 w it hin appr ov ed li mits for
solo flight. Ballast, eit her bloc k or s eat, must be added if the weig ht of the
solo pilot is less than the pl acar d mi nimum.
2-7
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Page intentionally left blank.
2-8
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
SECTION 3 – NORMAL PROCEDURES
DAILY INSPECTIONS
1. Before the glider's first flight of the day, a Daily Inspection (DI) shall be performed by
either an aircraft maintenance engineer, a qualified glider pilot, or a student qualified to carry
out DIs.
(para updated 2016)
2. Daily Inspection details follow. See Annex A for the actual Glider Daily Inspection
checklist without details.
a. Cockpit/Interior Fuselage:
(1) Check canopy attachment points for sec ur it y and condit ion of latches.
Check canopy for condi ti on and cl eanl i ness . U se pl ast ic cl eaner or soap
and water. Do not use g las s cleaner .
(2) Confirm that the radio/instrument battery is in and secure with attaching
wires clear of the feet area.
(3) Carry out a Radio Check: transmit and receive.
(4) Check condition and security of the instruments. Gently check air hose
connections behind da sh. Check altimeter setting against field elevati on.
(5) Check front ballast bracket is secure and pin is installed.
(6) Check front and rear release. Confirm there is tension, the cable is free,
and operation is smooth
.
(7) Check front and rear rudder pedals for s ecur i ty and wear. Confirm rudder
pedal springs and cable are attached and all rudder pedals have freedom
of movement.
(8) Check front and rear control col umn for free dom of movement and confirm
proper application of ailer ons and el evator.
(9) Check trim lever for freedom o f mov ement and effectiveness.
(10) Check front and rear spoiler handl es for freed om o f mov ement an d
operation.
(sub paras amended 2016)
(11) Check rear door hinge, cat ches and r ear window attachment points.
(12) Check control cables and pull eys for security and wear.
(13) Check wing pins for posit ion and wing bolts for wear.
3-1
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
(14) Check brake and spoiler connec ti ons for s ecur i ty .
(15) Check interior of fuselag e for si g ns of w ear .
(16) Check seat and back cushi ons and s pacer s for c ondit ion: not broken,
returns to shape if compressed, Velcro secure.
(17) Check front and rear seat belts for excessive wear or rips.
(sub paras amended 2016)
b. Right Wing/Fuselage:
(1) Check wing strut bolts for s ecur ity. Confirm safety/cotter pins are i n pl ace.
(2) Check out-rigger wheels for s ecur i ty and wear.
(3) Check spoiler/dive br ake hing es and c onnect ions for security and wear .
(4) Check aileron hinges, attachme nt poi nts and pus hr ods for s ecur i ty .
(5) Check condition of wing.
(6) Check canopy fairing on upper wi ng s urface i s flush and secure.
(7) Check right fuselage fabri c for wear.
c. Tail Assembly:
(1) Check right inspection port covers for security.
(2) Check rudder cable connection for security.
(3) Check all hinges and bolts on tai l ass embly for security.
(4) Check pushrod attachment to el evator horn for security .
(5) Check horizontal stabil iz er struts and st abil iz er att achme nt to fuselage for
security.
(6) Check tail wheel assembly for freed om o f movement and security.
d. Left Wing/Fuselage:
(1) Check wing strut bolts for sec ur ity .
(2) Check out-rigger wheels for s ecur i ty and wear.
(3) Check spoiler/dive br ake hing es and c onnect ions for security and wear .
(4) Check aileron hinges, attachme nt poi nts and pus hr ods for s ecur i ty .
3-2
(5) Check condition of wing .
tow, and the aiming point on approach; all without looking through the distortion associated with
(6) Check that canopy fairing on upper wing surface is flush and s ecur e.
(7) Check left fuselage fabri c for wear .
e. Nose/Wheel Area:
(1) Check skid and skid plate for sec ur ity and wear.
(2) Check tow release mechanism wear, condition, and proper engagement.
Inspect release arm and hook for damage, cracks, deformation, and
freedom of movement on pivot bolt. Inspect release arm slot for excessive
wear. Confirm snubber is in place. (Depending on operating conditions,
the unused release mechanism may be secured in place)
(3) Check wheel, tire pr es sure and br ake ar ea for wear, leaks, and condition.
inflation (15 psi if mechanical brakes, 28-30 psi if hydraulic brakes)
(4) Check pitot t ubes and s tati c vent for obs tr uct ions . D o not bl ow into the pitot
tube.
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
(sub paras amended 2016)
COCKPIT ERGONOMICS
3. Some pilots may require seat spacers and cushions to ensure the required sight line
over the nose. Incorrect installation might result in control column interference.
(para added 2016)
4. VON Marking - Vision Over the Nose (VON) refers to the ability to perform all visual
tasks required for the safe take-off, flight manoeuvres, and landing of an aircraft while acting as
pilot-in-command from the front seat.
(sub paras amended 2016)
5. The ACGP 2-33 requires a VON of 8.1 degrees to enable the front-seat pilot to see the
tow plane while preparing for launch, the tow plane while on tow, most of the tow rope during
the lowest portion of the canopy that bends to meet the metal framing.
6. To simplify this requirement and set an
achievable and measurable standard, all
ACGP 2-33 gliders have a VON mark affixed
to the pitot tube IAW Technical Order C-12382-000/CF-012. See Fig ur e 3-1.
Figure
3-1
VON
Marking
3-3
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
7. Front Seat Cockpit Fitting Guide - To meet the minimum VON of 8.1 degree
requirement and to ensure the front seat pilot has full access to all controls, a combination of
seat-spacers and cushions may be required. Figure 3-2 is to be used as an initial guide to
determine these requirements. The final configuration of spacers will depend on the individual
pilot's physique and preference – and may require changes from aircraft to aircraft. However,
in no case shall the maximum number of front seat back-spacers be exceeded.
FRONT SEAT COCKPIT FITTING GUIDE
FRONT SEAT PILOT
STATURE
5' 0" to 5' 1'
5' 1" to 5' 2"
5' 2" to 5' 3"
SEAT BACK-SPACERS and
CUSHION
One curved back-spacer, 2
flat back-spacers, and 1
cushion
One curved back-spacer, 1
flat back-spacers, and 1
cushion
One curved back-spacer and
1 cushion
SEAT PAN SPACERS and
CUSHION
One 1" seat-spacer and 1
cushion
One 1" seat-spacer and 1
cushion
One 1" seat-spacer and 1
cushion
The above are only an initial guide. The final configuration of spacers will depend on the
individual pilot's physique and preferences.
All pilots must use at least one back and on e s eat cus hi on .
5' 3" and over 1 cushion 1 cushion
Figure 3-2 Front Seat Fi tti ng Guide (updated 2016)
8. Maximum Number Of Front Seat Back-Spacers - Excessive use of spacers may
result in control column interference and reduction of seating area. Excessive use of cushions
will negate the shock absorbing benefits of the specially designed ACGP spacers. Therefore
the maximum number of front seat back spacers is one curved back-spacer, two flat backspacers, and one cushion.
9. Front Seat Spacer Usage - The following instructions amplify th ose o f C-12-382-
000MS-Z01 and shall be used for the step-by-step installation of spacers and cushions in all
ACGP 2-33 gliders:
a. The curved back-spacer is for the front seat only.
Only one curved back-spacer shall be used.
b. Installation of back-spacers shall be such that the seating area is not
compromised. Excessive reduction of the seating area may be a contributing
factor to pilots sliding under the lap belt.
NOTE
3-4
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
than one cushion in either location will negate the shock absorbing benefits of the
c. Seat-spacers can either be set to the rear of the seat-pan or against t he back
spacers - whichever placement is used, the seat-spacer cannot extend so far
forward as to prevent full motion of the control column.
NOTE
The addition of seat-spacers shall allow the pilot to grasp the
control column with the palm. If only the fingertips can grasp
the control column, positive control of the glider may be
compromised.
d. One back cushion and one seat cushion shall be used at all times. Use of more
specially designed ACGP spacers.
e. When only a back cushion i s us ed, the c urved back spacer may be instal l ed to
provide relief from the front seat bac k t op br ac e.
f. Use of back-spacers to move the pilot ahead to intercept the VON is preferred
over seat-spacers, since seat-spacers raise the pilot up and away from the
controls.
g. If a seat ballast is used, the ballast must be the first item stacked on the wooden
seat pan. In these cases, the ballast takes the place of the seat spacer.
(sub paras added 2016)
10. See Figures 3-3 to 3-7 for installation diagrams.
3-5
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Aluminum Seat-back
Fig 3-3 Correct installation of curved spacer,
Fig 3-4 Correct installation,
2" x 13" Seat-
Fig 3-6 Correct, with two seat-spacers
1" x 13"
2" x 13"
Note that both
Dependant on
condition, seating
under the lap belt
Dependant on
Fig 3-7 Use of 2nd flat back-spacer - condition and airframe dependant
Fig 3-5 Correct, with
(Fig 3-5 added 2016)
with Top Brace
18" Curved back-spacer
(note the placement is
below the top brace)
2" x 18" Flat Back Spacer
2" x 18" Flat Back Cushion
2" x 11" Seat Cushion
Wood Seat Pan
spacer
(installed
before backspacer)
single back-spacer, with back and seat cushion
with addition of a seat-spacer
seat ballast as first
item on seat pan
Seat-spacer
Seat-spacer
seat-spacers are
installed before
the back-spacer
airframe &
area might be
reduced.
Possible sliding
may result
airframe &
condition, seat
cushion might
extend beyond
the wood seat
pan. Possible
control column
interference may
result
11. Proper Strap-in - The lap belt must be tig ht ened first to prevent the buckl e fro m mov ing
up toward the sternum when tightening the shoulder straps. If you cannot pull the lap belt tight
enough on your own, ask for assistance.
12. The shoulder harness is to be secured such that neither strap can slide off the shoulder,
and be "snug" enough to prevent forward body movement while still allowing enough slack to
allow a thumb to slide under the strap.
13. Final Confirmation - Once properly strapped in, always confirm that the final
combination of cushions, spacers, and rudder adjustments, allows the front seat pilot to:
a. See the VON mark, with head at the level or chin tilted upward and with the
b. Move the control column to its full forward stop;
canopy closed;
3-6
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
c. Move both rudder pe d al s forward to their full stop, with the knee still slightly bent;
d. Open and close the spoilers; and
e. Activate the release knob.
CONTROL COLUMN AND SEAT SPACERS
14. Regardless of what combination of seat cushion, seat spacer, or seat ballast is used,
and whether these combinations are used in the front or the rear cockpit, the glider pilot shall
confirm full deflection of the controls prior to take-off on every flight.
(para added 2016)
CUSHION AND SPACER CONDITION
15. The following shall be used to assess if a seat cushion is serviceable:
a. Place the seat cushion on any flat surface;
b. Press down with your palm until the cushion begins to take the shape of your
hand;
c. Remove your hand;
d. The cushion should begin to return to its original (smooth) form; and
e. If the cushion does not display the ability to mould itself to the shape of your palm,
or does not display the ability to return to its original form within 30 minutes of
being compressed, the cushion shall not be used.
16. Cushions with a broken underside shall not be used.
17. Do not use broken spacers.
18. Cushions or spacers with faulty Velcro should be replaced or repaired as soon as
practical.
(paras added 2016)
LIMITED PRE-FLIGHT INSPECTION (WALK-AROUND)
19. Prior to strapping into a glider, including after a crew change, all glider pilots will perform
a limited pre-flight inspection (walk-around), which will include an inspection of the following
items:
a. Wing leading edges – look for unreported damage;
b. Wheels and skid – tire inflation, condition, bolts, brake leaks;
c. Elevator pushr od as se mbl y – bolt, nut, and cotter pin in place; and
3-7
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
instances of the tow hook not seati ng against the release arm may indic ate a
d. Pitot/static assembly – no blockages and is aimed direct into airfl ow
(sub-para updated 2016)
PRE-TAKE-OFF CHECK (BCISTRSC)
20. Check the foll owing:
a. (B)allast. Weight limitations and ballast.
b. (C)ontrols. Controls functional; rudder ped als adjusted.
c. (I)nstruments. Instruments checked; radio and altimeter set.
d. (S)poilers. Operation, then close and lock.
e. (T)rim. Trim set full forward.
(sub-para updated 2016)
f. (R)elease. Oper ati o n and s ecur i ty.
g. (S)traps. Straps secure front and back seat.
h. (C)anopy/Door. Canopy, rear window and door closed and locked. Confirm
security of canopy latch by touch.
HOOK-UP PROCEDURE
21. Once the tow rope has been attac h ed to the release mechanism, co n fi r m the sec ur ity of
the release mechanism v i sual ly and thr ough the application of tension:
a. From a 90 degree side angle to the nose of the glider, visually confirm the step o f
the tow hook is seated agai nst t he rel eas e ar m (See F i g ur e 3-7);
(1) If the tow hook i s not s eated ag ai ns t the r el ea se ar m ( See F igure 3-8), have
the pilot activate the release mechanism and repeat the hook-up. Recurring
problem that needs to be inv es tig ated by an AME: and
(2) If the tow hook i s abl e to s li de thr oug h t he r eleas e ar m (s ee Fi g ur e 3-8), do
not continue with the flight . D o not fly t he g l ider unti l advi sed by an AME.
b. Tug on the tow rope, pull ing i t forward in line with the glider's l ongit udinal axis; and
c. Re-inspect the rel ease as sembl y t o ensur e that is has r emai ned comp l etel y clos ed.
If the release assembly has opene d, ev en par ti al ly , do not conti nue
with the launch. Do not fly the g l i der until adv ised by an A ME .
CAUTION
3-8
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Figure 3-7 Proper Engagement
Figure 3-8 Incorrect Engagements
22. See Figure 3-9 for additional diag r ams depic ting ways to identify proper and improper
tow rope hook ups.
3-9
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
CORRECT HOOK-UP
SCHWEIZER GLIDER RELEASE MECHANISM
The following diagrams depict what a correct glider hook-up should look like from outside and inside the cockpit,
and demonstrate five common indications of an incorrect glider hook-up.
The tow hook and release arm
are hooked up properly and
ready for flight.
Glider Release Arm
Glider Tow Hook
Note the method used for
protecting the rope.
During hook-up, any such
protection must be moved back
to ensure a good view of the
release mechanism.
CORRECT HOOK-UP
The front cockpit release
knob should be flush with
the instrument panel.
INCORRECT HOOK-UP
The tow hook is resting on the front left-side of the release arm.
Again, note the rope protection has been moved far enough back to view
the entire release mechanism.
INCORRECT
HOOK-UP
The tow hook step is
clearly visible; therefore
the tow hook is too far out
of the release arm.
CORRECT HOOK-UP
The rear cockpit release
knob should be flush to
the wooden stopper.
INCORRECT
HOOK-UP
The tow hook is resting
on the side of the
release arm.
INCORRECT HOOK-UP
The front cockpit release
knob is not flush with the
instrument panel.
Figure 3-9 Glider Hook-Up Examples
INCORRECT
HOOK-UP
The rear cockpit
release knob is not
flush to the wooden
stopper.
3-10
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
USE of C OF G and FORWARD TOW HOOKS
23. Always use the forward tow hook for ai r tow. Winch or auto launches may be executed
using either the forward or the C o f G tow hook , al thoug h us i ng the C of G tow hook will result in
a higher launch altitude; ther e i s no t endency to oscillate with ei ther method.
LAUNCH SPEEDS
24. Air Tow: Normal air tow speeds are 65 to 70 mph. D uri ng t r ansi ts , airs peeds may be
increased. If turbulence is encounter ed dur i n g t rans i ts, airs peed shoul d be r educed.
25. Winch and Auto Launch: Normal climb speeds are in the range of 55 to 60 mph (25
mph above the stall speed) although the airspeed mi g ht vary at each stage of launch.
26. Max Winch and Auto Launch Speeds: If the airspeed continues to increase such that
the maximum launch speed may be exceeded, immediately reduce the climb angle (i.e. reduce
the pitch angle by lowering the nose) to prevent overstressing the glider. The airspeed should
be then stabilized at a safe speed. If this procedure is unsuc ces sful:
a. But the airspeed is still within acceptabl e li mi ts, yaw the glider from side to side to
direct the winch operator to r educ e power.
b. And the airspeed exceeds or will probably exceed the launch limit abort the launch
(release the glider). Be prepared to counter an abr upt nose-up moment.
27. Winch and Auto Launch Safety Speed. The ground launch safety speed for any glider
is based on the formula: 1.5Vs. If the airspeed falls bel ow the safe climbing speed, or continues
to decrease, the launch shal l be i mmediatel y abor t ed (glider released) and a landing car r i ed out.
28. Calculating Auto Launch Speeds: Various factors affect the required speed of the auto
launch vehicle, such as glider attitude, pilot technique, wind gradi e nt , etc . The f oll owing
technique can be used to estimate the vehicle speeds required to safely auto launch a 2-33
glider:
a. Subtract the surface wind from the max imum launc h speed;
b. Subtract an additional 5 mph as safety factor ;
c. After the glider is i n safe cli mb, r educe by 10 mph;
d. Subtract the surface wind again to accomm od ate wind gradient; and
e. Continually adjust vehicle speed to com pensate for glider attit ude, pi lot techni q ue,
wind gradient, etc.
3-11
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Page intentionally left blank.
3-12
GENERAL
3.2 fps
2.6 fps
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
SECTION 4 - AIRCRAFT HANDLING
1040 lbs gross weight
1080 lbs gross weight
FLIGHT SPEEDS
DUAL SOLO DUAL SOLO
55 to 60 55 to 60
Normal ground based
climb speeds
55 to 60 55 to 60
55 mph 50 mph Slips (Forward & Turning) 55 mph 50 mph
50 mph 45 mph L/D (Best Glide Speed) 52 mph 45 mph
23:1 L/D (Best Glide Ratio) 23:1
42 mph 38 mph Min Sink Speed 42 mph 38 mph
3.1 fps
(186 fpm)
2.6 fps
(156 fpm)
Min Sink Rate
(192 fpm)
(156 fpm)
43 mph 39 mph Spiralling Speed 44 mph 39 mph
39 to 42 mph 34 to 37 mph Buffeting Spee d 40 to 43 mph 34 to 37 mph
41 mph 36.5 mph Stall Speed (30o bank) 42 mph 36.5 mph
40 mph 1 36 mph 1
Stall Speed
(spoilers open) 1
41 mph 1 36 mph 1
38 mph 34 mph Stall Speed (level flight) 39 mph 34 mph
Figure 4-1 Flight Speeds (updated 2016)
2-33 Speeds and Ratio s with Fu ll Spo iler s/D iv e B rakes E xten d ed
SPEED
(Miles/Hour)
SPEED
(Feet/Second)
SINK
(Feet/Second)
SINK
(Feet/Minute)
DIVE
ANGLE
L/D
RATIO
45 66.00 6.66 400 6o 9.5 : 1
50 73.33 9.43 566 7.4 o 7.7 : 1
60 87.99 14.28 857 9.3 o 6.1 : 1
70 2 102.66 20.00 1200 11.23 o 5 : 1
80 2 117.33 33.30 1998 16.5 o 3.4 : 1
90 2 131.99 41.66 2500 18.4 o 3 : 1
Information from: Engineering Repor t R -153 Sailplane Dive Test Dat a prepar ed by L Schweizer
11-7-78
Figure 4-2 Speeds and Ratios with Spoilers Extended (added 2016)
4-1
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
WARNING
1. It is unsafe to make an approach w i th dive brakes open in the
speed range of 36 to 43 mph, as the r ate o f descent is so great that
a proper flare for landing c annot be mad e.
CAUTION
2. Treat speeds above Va as a cautionary range. Manoeuvring
within this range should be reduced to a minimum as velocity
increases.
(SAMPLE ONLY - DO NOT USE FOR FLIGHT - see Owner Manual for actual chart)
Figure 4-3 Sample Performance Curves (added 2016)
4-2
PRE-RELEASE CHECK
(A)rea. Ensure glider is approaching the desired release area;
(A)ltitude. Ensure glider is at or is approaching the pre-briefed altitude;
(A)ttitude/Position. Ensure glider is in the proper attitude, i.e. wings level/high tow; and
(T)raffic. Check for conflicting traffic in the practice area, especially at the release point.
SAFETY CHECK
(A)ltitude. Ensure entry altitude will permit recovery by the published minimum altitudes
(S)traps. Straps secure front and back.
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
(sub-para amended 2016)
(sub-para amended 2016)
(C)anopy. Canopy, rear window, and door closed and latched. Confirm security of
canopy latch by touch.
(O)bjects. Ensure no loose objects.
(T)raffic/Terrain. Check for conflicting traffic and ensure clear of built-up areas.
PRE-LANDING CHECK
(S)poilers. Check operati on and pos it ion.
(W)ind. Assess wind speed and direction.
(A)irspeed. Calculate the approach speed.
(R)adio. Make radio call, report position and intentions.
(T)rim/Traffic. Set trim as required and check for conflicting traffic.
(sub-para amended 2016)
(sub-para amended 2016)
(S)traps. Check front and back seat harness secur i ty.
(C)anopy. Canopy, rear window, and door closed and latched. Confirm security of
canopy latch by touch.
SLIPPING
1. The 2-33 can be slipped both whil e mov i ng forward and while turning.
4-3
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
CAUTION
See Figure 4-2. Combining a forward slip with use of full spoilers
will result in a very rapid rate of descent, at times increasing to
1,000 fpm or greater. Waiting for the exact altitude before
removing the control inputs for the slip will often result in
descending below the intended altitude.
(Caution added 2016)
TOUCH DOWN
2. Touch down can be done with spoil ers open or cl os ed, al thoug h i t i s preferabl e to l an d
with them open. With spoilers open, plan the flar e tw o to fiv e feet abo ve the ground at 43-46
mph. By holding a level att it ude cl ose t o the g r ound, the glider will settle i nto a s mooth and level
touch down.
(above para added 2016)
CAUTION
If the control column is mov ed t oo far back during or after
touchdown, especially with spoilers closed, the g l ider may l i ft off
again (ballooning).
(Caution added 2016)
3. Once on the ground, use braking as r equired. Us e of ex tr eme hard br ak i ng or pushi ng the
glider nose into the ground shoul d be avoided unless absolutely nec ess ary to avoid obstacles.
(above para added 2016)
4-4
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
SECTION 5 - EMERGENCY HANDLING
LAUNCH EMERGENCIES
1. Should the glider pilot be requir ed to abor t a l aunc h pr emat ur ely, or should the launch
rope break, the followi ng shal l apply :
Air Tow Rope Break or Premat u re R elease: Winch or Auto Launch Rope Break or
Premature Release:
(G)lide - Set or maintain normal g l idi ng
attitude;
(A)ssess - Altitude and location; (P)ull - Release twice
(S)elect - Appropriate response and
landing area; and
(P)ull - Release twice (S)elect - Appropriate response and
CANOPY OPEN IN FLIGHT
2. Continue to safely fly the aircraft, and:
a. Assess your situation, consideri ng the phas e of flight, position, and al ti tude; and
b. If able, close the canopy. I f unable to cl ose t h e canopy, plan for sufficient al ti tude
and airspeed to compensate for the i nc r eased dr ag w hen r etur ni ng for l andi ng .
(G)lide - Set or maintain normal gli di ng
attitude;
(A)ssess - Altitude and location; and
landing area
5-1
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
UNUSUAL ATTITUDE RECOVERIES
STALL and INCIPIENT SPIN FULL SPIN SPIRAL DIVE
Simultaneously:
Release sufficient back
pressure to recover from
the stall (reduce ang le of
attack);
If spoilers are open, close
immediately;
Stop wing drop with
opposite rudder; and
Once the wings are no long er
stalled return to desired fli g ht
attitude.
Apply full rudder against the
rotation of the spin,
centralize the ailerons, and
if spoilers are open, close
immediately;
Pause momentarily;
Move the control column
steadily forward until the
spinning stops;
Centralize the rudder, look up;
and
Pull out of the dive.
NOTE
In most cases, the 233 will come out of
the spin after applying
full rudder and
centralizing ailerons –
in which case
immediately level the
wings and pull out of
the dive.
Level wings with coordinated
control movements; and
Pull out of the dive.
(above paras added 2016)
5-2
A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
increase the rate of the turn (decrease radius) simply by slowing down or standing
forward motion of the glider is slowed to a crawl. Steering with the outside wingtip
7. Several gliders may be towed forward at once in a “train” with the second and
SECTION 6 - GROUND MOVEMENTS
MOVING
1. When moving the glider for di st a nces other than from the landing area to the parking or
launching area, the controls should be locked in place. The seat belt or control locks may be
used for this purpose.
(above para added 2016)
MOVING BY HAND
2. Surfaces - Use the struts to push or pul l the g l i der . The nose handle may be used for
short distances.
(above para amended 2016)
3. Control - In most cases, control of the glider ground crew should be assumed by a
person at a wing tip. Control is announced by calling "My Wing".
4. Backward - Have someone stationed at the tail to lift when required and to assist with
avoiding obstacles.
5. Steering - It is preferable to use the wing tips for steering since the wing tip persons
have the better view and have better leverage for turning. Further:
a. When steering from the "inside" wingtip during a turn, the wing person can
still. To decrease the rate of turn (increase the radius) the inside wingtip person
can walk faster. Steering from the inside wing tip is the easiest, safest, and most
effective location during ground handing.
b. When steering from the "outside" wingtip during a turn, the wing person must
move quickly to keep up with the wing tip when the glider turns, unless the
also makes it difficult to accurately control the rate and radius of the turn; if the
crew want to increase the rate of turn (decrease the radius) the outside wing
person must move even faster.
c. Steering by the tail is acceptable, however the fragility of the horizontal stabilizer
should be considered. Placards denoting safe and unsafe handling areas shal l
be observed. Keep the tail high when moving the glider in high winds.
(sub paras amended 2016)
TOWING BY VEHICLE
6. The minimum length of rope between a tow vehicle and the glider shall be at least 30
feet.
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subsequent gliders attached to the glider’s tail tie-down point. The minim um leng th o f the se
b. Item B at Figure 6-2 depicts a tie-down method more suitable for windy conditions
ropes shall be 30 feet. To prevent structural damage to the lead glider, a maximum of six
gliders are to be towed at once and this number is to be reduced when rough terrain or wi nds
dictate.
TOWING BY TOW BAR
8. The 2-33 glider may occasionally be moved using a tow bar attached to the rear tiedown point provided there are no occupants in the glider and the terrain is smooth. Occasional
use means several times per aircraft per year vice frequent use of several times per aircraft per
day. Frequent use is prohibited. When moving the glider with a tow bar, the tow bar itself
provides the steering and braking. Normally, only one person is required at one wing tip to
maintain wings level. When manoeuvring around other aircraft or into/out of hangars,
personnel shall be positioned at each wing tip to ensure proper clearance.
9. The only tow bars authorized for ACGP use are those manufactured and identified in
accordance with Drawing QETE-00063. This tow bar has been designed to limit glider
structural damage and no tow bar modifications are authorized without approval from the
National Technical Aut hor it y (N TA).
TIE-DOWN
10. All locations where gliders are left unattended for more than a few hours are deemed to
represent a high wind hazard.
11. Based on a 600 lb empty weight, the typical 2-33 glider facing into the wind may be
subjected to lift forces ranging from 150 lbs to 3,350 lbs. See Figure 6-2 for methods used to
minimize lifting forces.
WIND LIFT NET LIFT
30 mph 750 lb 150 lb
40 mph 1 300 lb 700 lb
50 mph 2 000 lb 1 400 lb
60 mph 2 900 lb 2 300 lb
70 mph 3 950 lb 3 350 lb
Figure 6-1 Lifting Forces on a Tied Down 2-33
12. Representative Glider Tie-Down Methods. The most suitable tie-down method is
dependent upon the combination of wind conditions and length of time.
a. Item A at Figure 6-2 depicts a tie-down method suitable for calm winds or short
periods of time such as a Flight Line Tie-down. This method should not be use d
in high wind conditions because of the increased angle of attack created by
leaving the tail on the ground.
(sub-para added 2016)
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or long periods of time such as Permanent or Temporary Tie-down. Using the
areas without risk of wing tip contact.
Figure 6-3 Tie-Down Clearances
A
B
system at Item B will decrease the angle of attack and help to diminish the lift
forces outlined in Figure 6-1.
(sub-para added 2016)
Figure 6-2 Glider Tie-Down Methods
13. To ensure sufficient clearance
is provided between parked aircraft,
a minimum of 15 feet should be
maintained between glider wing tips.
This will permit ease of movement of
aircraft into and out of tie-down
The clearance also provides some
protection in the case of an adjacent
aircraft partially breaking loose from
its tie-down.
PERMANENT TIE-DOWNS
14. When required to use Permanent Tie-Downs, the following standard shall be met:
a. The glider tail shall be supported on a stand that is high enough to reduce the
angle of attack as much as possible. See Figure 6-2 B. Consideration should
also be given to preventing the tail from moving sideways once on the tail stand;
(sub-para amended 2016)
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b. At least one tie-down to a ground anchor shall be provided at each wing, the tail
and the nose such that the angle between the tie-down rope and the vertical is at
least 30 degrees. In lieu of the nose tie-down, two ground anchors may be
provided at the tail, each on opposite sides of the longitudinal axis;
c. Individual ground anchors, either provided or constructed, shall be capable of
withstanding an upward vertical force at least equal to the average tensile
strength of the tie-down rope/strap;
d. In-cockpit rudder and control locks shall be used to prevent movement during
unattended periods (See Figures 6-4 an d 6-5); and
(sub-para added 2016)
e. For those gliders with hydraulic brakes, avoid leaving the spoilers deployed as
this results in undue fatigue on the wheel brake components.
(sub-para added 2016)
Control Column Lock - Used in rear cockpit onl y .
Installation:
Ensure the threaded rod is modified such
that the wing nut cannot be threaded off.
Back wing nuts off to end of threaded rod.
Angle/Tilt the block and slide the block
over control column.
Slide the block around the far front seat
support tube.
Lower the block around the nearest front
seat support tube.
Lower the entire block until level while
seating the support tubes into the block.
Push the block together.
Finger tight only.
Do not use a wrench.
Figure 6-4 Control Column Lock (figure added 2016)
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A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
Must use two units. One for each rudder pedal.
Loosen wing nut. Set flat head into hole in floorboard (just ahead of the seat ). Rest the
mid-pedal bar inside the u-shaped portion of the lock. Repeat for the next rudder pedal.
Finger tighten only. Do not use a wrench.
Figure 6-5 Rudder Locks (figure added 2016)
TEMPORARY TIE-DOWNS (OVERNIGHT, DEPLOYMENTS)
15. If permanent tie-downs are neither available nor practical to construct, the following
standard shall be met:
a. Steel “tent-peg” style tie-down anchors shall be used. They shall be at least 42
inches in length and at least 1/2-inch in diameter and constructed so that a
smooth, circular attachment point is available for the tie-down rope/strap;
b. Two tie-down anchors shall be provided for each wing and the tail;
c. The tie-down rope/strap angle (angle from the glider attachment point to the
tie-down anchor) shall be at least 30 degrees from the vertical;
d. The use of portable tail stands is recommended (Using a tail stand alleviates the
need to leave spoilers open, however if the need to leave spoilers open exists,
give consideration to preventing weather and wildlife from entering the interior of
the wing);
(sub-para amended 2016)
e. Controls and control surfaces shall be locked to prevent inadvertent movement
during unattended periods; and
FLIGHT LINE TIE-DOWN (HOURS)
16. When leaving the glider unattended for a short period of time, and when no high winds
are expected, the following minimum standard shall be met:
a. One wing shall be tied down with a rope/strap to a ground anchor;
b. One other attachment point (nose, tail, or other wing) shall be tied down with a
rope/strap to prevent pivoting;
c. Controls shall be immobilized; and
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down ropes and straps shall have an average minimum strength of 2700 lb. Whether
duly qualified for elementary work and independent checks by the
d. Spoilers shall be deployed.
TIE-DOWN ROPES AND STRAPS
17. Tierope or strap, the physical pull of a single pilot is sufficient for applying tension. Use of
carabiner style hooks is preferred over open face hooks since wing rocking during heavy winds
can cause open style hooks to release. Use of ratchets to tighten straps or ropes can lead to
over-tensioning due to mechanical advantage. Use of ratchets should be restricted to very
experienced crews.
(para updated 2016)
USE OF OPEN-AIR TRAILERS
18. When using open-air trailers, refer to the 2-33 Sailplane Flight-Erection-Maintenance
Manual. When loading, confirm all checks are completed by using Annex B Glider Open-Air
Trailer Loading Checklist.
(para added 2016)
ERECTION PROCEDURE
19. Refer to the 2-33 Sailplane Flight-Erection-Maintenance Manual for assembl y.
Considering that the glider may be disassembled and asse mbled r ather frequently, the number of
bolted attachments is kept to a mini mum. Ho wever, all of the attachment fittings may be made
with the appropriate AN bolts , nuts and cott er pins specified in the mai ntenanc e manual. The LS 1 safety pin is an acceptable al ter nate for the No. 1 and 2 commercia l safety pi ns.
NOTE
Carefully consider how winds wil l i nter ac t with wi ngs and fus el ag e
during assembly and disass embly.
(NOTE added 2016)
20. Post-Assembly Independent Inspection.
a. Complete and sign GLIDER FINAL ASSEMBLY CHECKLIST - ANNEX C.
NOTE
Ensure that two entries are made in the journey log. Suggested
entries as follows: “Aircraft assembled in compliance with the 2-33
parts and maintenance manual section A” (Signature)
“Flight controls checked for correct assembly, locking and sense of
operation” (Signature)
These signatures do not have to be done by an AME but by persons
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RCA Ops O or RC Eng O.
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ACGP 2-33 GLIDER DAILY INSPECTION
(amended 2016)
Complete before the glider’s first flight of the day.
Registration: Date: .
DOCUMENTATION / COCKPIT CHECK OFF
1. Journey Log: snags, time on the airframe ( )
2. Battery: in & secure, wires away from the feet area ( )
3. Radio Check: transmit & receive ( )
4. Canopy: attachment points, latches, cleanliness ( )
5. Front Release Knob: tension, cable is free, operation ( )
6. Instruments: condition & security, air hose connections, check alt against field elevation ( )
7. Ballast: bracket secure, pin installed ( )
8. Rudder Pedals: springs, cables, freedom of movement ( )
9. Control Column & Trim: freedom of obstructions, correct movement of control surfaces ( )
10. Spoilers & Brake Control: freedom of movement, wheel brake operation ( )
11. Publications Pouch: installed, contents
12. Front Seat Belt: condition ( )
13. Frt Seat Cushions and Spacers: condition ( )
14. Rear Door & Rear Windows: condition, latches, attachment points ( )
15. Rear Release Knob: tension, cable is free, operation ( )
16. Rear Rudder Pedals: movement, cables free ( )
17. Rear Control Column: freedom of obstructions, correct movement of control surfaces ( )
18. Rear Seat Belt: condition, secure if not in use ( )
19. Rr Seat Cushions and Spacers: condition ( )
20. Forward Wing Attachment Bolts: in & safetied ( )
21. Spoiler Disconnect: pin in & safetied ( )
22. Aileron Disconnect: bolts, nuts, cotter pins in & safetied ( )
23. Control Cables: security & wear ( )
24. Rear Fuselage Interior: condition ( )
FORWARD FUSELAGE
25. Main Wheel & Tire: condition, wear, inflation ( )
26. Skid & Skid Plates: c on dit i on, wear plate no t worn thr ough ( )
27. Tow Hook: wear, condition, proper engagement, freedom of movement, snubber in place ( )
28. Nose Cone: condition ( )
29. Pitot/Static: condition, no obstructions ( )
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A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
LEFT WING
30. Wing Strut: condition ( )
31. Wing Strut Bolts: in, castle nuts on & safetied, washers as required ( )
32. Dive Brake: hinges, connections, security & wear ( )
33. Wing Skin: condition ( )
34. Outrigger Wheel & Spring: condition & wear ( )
35. Ailerons & Pushrods: condition, movement & security ( )
36. Spoilers: springs, condition, movement, security ( )
REAR FUSELAGE
37. Centre Section Fairing: condition, fasteners secure ( )
38. Wing Attachment Bolts: in & safetied, washers, spacers & castle nuts ( )
39. Fabric: condition, inspection covers ( )
EMPENNAGE
40. Vertical Stabiliz e r: condition, security ( )
41. Horizontal Stabilizer: condition, security ( )
42. Horizontal Stabilizer Lift Struts: attachment & safetied ( )
43. Tail Wheel Assembly: condition, attachment, security, wear, rotation ( )
44. Rudder & Elevator: condition, movement, security ( )
45. Rudder Cable & Elevator Push Rod: condition, security ( )
46. Inspection Plate Cover: secure ( )
RIGHT WING
47. Spoilers: spring, condition, movement, security ( )
48. Ailerons & Pushrods: condition, movement & security ( )
49. Outrigger Wheel & Spring: condition & wear ( )
50. Wing Skin: condition ( )
51. Dive Brake: hinges, connections for security & wear ( )
52. Wing Strut: condition ( )
53. Wing Strut Bolts: in, castle nuts on & safetied, washer ( )
Enter all major & minor unserviceabilities in the journey log defect column.
SIGNATURE: LICENCE NO:
Remark: This inspection sheet should be reproduced locally on an 8 ½” by 14” sheet.
(Glider DI Sheet amended 2016)
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ANNEX B - GLIDER OPEN-AIR TRAILER LOADING CHECKLIST
1. FUSELAGE:
a. Centre ali g ned
b. Wing pins secur ed
c. Turnbuckles secured
d. Safety/C otter pi ns i nst alled
2. TAIL:
a. Centre ali g ned
b. Secured
c. Secure horizontal stabilizer to trailer
3. COCKPIT:
a. Control push r ods - Secured
b. Canopy sec ur ed
c. Pitot tube covered
4. Struts secure
5. WINGS:
a. Small bolt top fitti ng
b. Shoulder of bolts up
c. Bolts (two per wing)
(1) Left wing bolts installed
(2) Right wing bolts installed
(3) Safety/Cotter pins installed (4)
d. Fuselage and Wing Surface clearance
e. Wing root openings covered
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6. AILERON LOCKS SECURED
7. RUDDER LOCK SECURED
8. D-TUBES COVERED
9. TRAILER:
a. Hitch safety pin
b. Safety chain secured
c. Lights
(1) signal
(2) brake
(3) park
GLIDER REGISTRATION: DATE:
SIGNATURE:
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A-CR-CCP-402/MB-001 SCHWEIZER 2-33 AOIs
1. WINGS
1ST
2ND
(1) Fuselage (LH & RH) – hardware install ed
(3) Aileron locks (LH & RH) - removed
2. SPAR BOLTS, SPACERS, NUTS & PINS
4. AILERON CONTROLS
a. bolts, nuts, and cotter pins
hardware
7. LOG BOOK ENTRIES (2) COMPLETED
ANNEX C - GLIDER FINAL ASSEMBLY CHECKLIST
1. A final check shall be carried out after a ful l ass embly. This check should be performed by
more than one person to ensure that al l ass em bly points are double-checked.
2. A Daily Inspection shall also be complete d pri or to t he first flight.
a. Surfaces checked
b. Strut attachment bolts, washers, nuts and safety/cotter pins:
(2) Wings (LH & RH) - hardware installed
a. Forward Spar (LH & RH) – hardware installed
b. Rear Spar (LH & RH) – hardware installed
c. Spacers – installed under nuts & can be rotated by hand
3. SPOILER CONTROL
a. Pin and safety/cotter pin – hardware install ed
5. ELEVATOR CONTROL
a. Push rod, bolt, nut and safety/cotter pin – hardware installed
6. TAIL SECTION – HORIZONTAL STABILIZER
a. Horizontal stabilizer & strut attachment bolts, washers, nuts, cotter pins:
(1) Horizontal stabilizer attachment – hardware install ed
(2) Struts - fuselage attachment (LH & RH) – hardware installed
(3) Struts - horizontal stabilizer attachment (LH & RH) –
installed
a. Aircraft assembled in compliance with the SGS 2-33 Sailplane
Flight - Erection - Maint enanc e Ma nual .
b. Flight controls checked for correct assembly, locking and sense of
operation (must be an independent check)
GLIDER REGISTRATION: DATE:
NAME & SIGNATURE (1
NAME & SIGNATURE (2
ST
):
ND
):
Place document in the aircraft logbook when completed
(Checklist updated 2016)
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ANNEX D - GLIDER MAINTENANCE FLIGHT CARD
ACGP 2-33 SCHWEIZER GLIDER MAINTENANCE FLIGHT CARD
PILOT:_________________ LIC # ________________ DATE: ________________
AC REG: ______________ TIME UP: _____________ TIME DOWN: __________
AIRCRAFT LOG BOOKS (confirm no open maintenance items) ___________________________
Launch Type: ______________________
Use the following topics and/or the space provided below to note specific items.
RELEASE: Stiff - Normal - Loose TRIM: Effective - Non-Effective
Hands Off @ 50MPH:_________________ Hands Off @ 38MPH: _________________
Stall Speed Level Flt: _________________ Stall Wing Drop: _____________________
Stall Speed Spoilers Open ____ Clsd ____ Spoilers can open & close @ VNE _______
3600 Left Turn: ______________________ 3600 Right Turn: _____________________
Left Spin: __________________________ Right Spin: _________________________
RCA En g O direc tions / Pilot Comment s:
Pilot Signature: RCA Eng O Signature:
(Flight Card added 2016)
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