CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
HORIZONTAL STABILIZER
1. DESCRIPTION
This section covers the horizontal airfoil of the tail section to which the elevator is attached.
EFFECTIVITY:
All
55-10
Page 1
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2. MAINTENANCE PRACTICES
A. Horizontal Stabilizer
CAUTION:
(1)
Installation and removal of the horizontal stabilizer may only be performed at an
approved Cirrus Design Repair Station.
Removal - Horizontal Stabilizer (See Figure 55-101), (See Figure 55-102)
Two methods of horizontal stabilizer removal are explained. Method #1 contains a removal procedure that salvages the existing horizontal stabilizer. The Method #2 procedure explains how to
cut the horizontal stabilizer from the airplane where reuse of the horizontal stabilizer is not possible.
(a)
Acquire necessary tools, equipment, and supplies.
Description
P/N or Spec.
Page 2
15 Apr 2007
Purpose
Oscillating Tool, Blade
FSN400E
Blade (Metal)
6-35-02-147-01-5
Oscillating Tool, 90°
12L2240-90
Cutting Disc and Arbor
14-1746
Cooper Power Tools Cutting
Method #1
Sales and Service
Lexington, SC 29071
800-845-5629
Compressed Air
-
Any Source
Cooling
Method #1
Reciprocating Saw
-
Any Source
Cutting
Method #2
Blade (Bi-Metal)
6 inch (15 cm)
Any Source
Cutting
Method #2
Any Source
Cutting
Method #2
Blunt-Edged Chisel
55-10
Supplier
-
C. & E. FEIN GMBH Cutting
D-70176 Stuttgart
Method #1
+49 (0)711 / 66 65-0
Plastic Wedge (2)
5 inches (13 cm)
Any Source
Cutting
Method #2
90° Die Grinder
-
Any Source
Removal
Metal Cut-Off Wheel and Arbor 2.0 inches (5.1 cm) Any Source
Removal
Sanding Drum
80-grit
Any Source
Abrasion
Low-Profile Orbital Sander
-
Any Source
Abrasion
Sandpaper
80-grit
Any Source
Abrasion
Vacuum
-
Any Source
Cleaning
Low-Tack Tape
M-0071 AST Black Any Source
Protective Tape
Protection
Plastic Tape, 2-inch
-
Any Source
Protection
Aluminum Tape, 4-inch
-
Any Source
Protection
Method #1
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Description
Bagging Film Breather
(b)
(c)
(d)
(h)
(i)
(Refer to 51-30)
Supplier
(Refer to 51-30)
Purpose
Protection
During horizontal stabilizer removal, do not damage bonding flange on fuselage or vertical fin.
Remove horizontal stabilizer root fairings. (Refer to 53-50)
CAUTION:
(f)
(g)
P/N or Spec.
Remove pitch trim motor assembly. (Refer to 27-30)
Remove elevator bellcrank. (Refer to 55-20)
Serials 0334 & subs w/ ice protection: Disconnect ice protection tubing:
1
Remove bulkhead 222 trim. (Refer to 25-10)
2
Remove access panel CB6. (Refer to 06-00)
3
Remove any tie wraps used to secure ice protection tubing.
4
Disconnect aft tubing from horizontal proportioning unit. (Refer to 30-05)
CAUTION:
(e)
MODEL SR22
Verify horizontal stabilizer serial number is recorded prior to cutting horizontal stabilizer to ensure that traceability of component is recorded.
Record horizontal stabilizer serial number.
Remove bolt securing ground wire to elevator hinge bracket on aft horizontal stabilizer and
stow ground wire.
Using low-tack tape, secure rudder into a fixed position.
If performing Horizontal Stabilizer Removal Method #1, verify bond gap measurement
facilitates cutting procedures.
CAUTION:
1
To facilitate Method #1 removal of the horizontal stabilizer, a bond void must
exist at the leading edge, extending aft approximately 3 inches (8 cm).
Verify bond void exists at leading edge of fuselage flange. Repeat verification on
opposite side of fuselage flange.
CAUTION:
To facilitate salvageable removal of the horizontal stabilizer, the bond
gap at the fuselage flange must be 0.05 inch (1.27 mm) or greater.
2
(j)
Measure bond gap along upper and lower flange. Repeat measurement on opposite
side of fuselage flange.
3
If measurement is less than 0.05 inch (1.27 mm), Horizontal Stabilizer Removal
Method #1 may not be performed.
4
If required bond voids exist and bond gap measurement is 0.05 inch (1.27 mm) or
greater, Horizontal Stabilizer Removal Method #1 may be performed.
Horizontal Stabilizer Removal Method #1: Remove horizontal stabilizer. (See Figure 55101)
1
At empennage perimeter of bonding flange, apply plastic tape to upper and lower
empennage surfaces.
2
At horizontal stabilizer perimeter of bonding flange, apply aluminum tape to upper
and lower horizontal stabilizer surfaces.
CAUTION:
EFFECTIVITY:
All
When cutting bonding flanges, another technician should support the
horizontal stabilizer to minimize any shifting of weight that could
stress the flanges at remaining bond lines.
55-10
Page 3
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Also, the second technician should apply compressed air to bond line
during cutting procedure to prevent heat build-up from potentially
scorching the airplane surfaces, and provide debris clean-up.
Use caution when cutting to not cause excessive damage to the horizontal stabilizer and/or fuselage bonding flange. If damage exceeds
repair specifications, contact Cirrus Design for disposition.
To prevent binding during the removal process, begin cutting with 90°
oscillating tool at the bottom bond line.
3
(k)
Using 90° oscillating tool with cutting disc at bond line, position disc flush with surface of horizontal stabilizer. Apply compressed air simultaneously to bond line when
cutting. Cut horizontal stabilizer section from empennage.
4
If necessary, use blade oscillating tool to cut remaining bond line. Once bond line
has been separated, repeat both cutting procedures on upper bond line.
5
Repeat cutting procedures on opposite side.
6
Remove horizontal stabilizer from airplane.
Horizontal Stabilizer Removal Method #2: Remove horizontal stabilizer. (See Figure 55102)
1
Draw an offset line 1.0 inch (2.54 cm) from horizontal stabilizer root around entire
surface of horizontal stabilizer. Repeat on opposite side.
CAUTION:
2
3
4
5
6
7
55-10
Page 4
15 Apr 2007
Use caution when cutting to not cause excessive damage to the fuselage bonding flange. If damage exceeds repair specifications, contact
Cirrus Design for disposition.
Using reciprocating saw with 6 inch (15 cm) blade at offset line, cut horizontal stabilizer section from empennage. Repeat on opposite side.
Using reciprocating saw, cut through spar of remnant to remove core.
Position cutting end of wedge between aft remnant and upper fuselage flange.
Strike back of wedge forward to leading edge of remnant.
Position second wedge at same position on opposite side of empennage and repeat
striking action. Alternate between driving both wedges forward to leading edge of
remnant. Repeat remnant separation at lower flange surfaces.
If leading edge of remnant is still adhered to fuselage flange, alternately position flat
end of wedge to sides of remnant and strike with hammer until remnant is loosened.
Remove horizontal stabilizer composite remnant.
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
1
2
NOTE
At empennage perimeter of bonding flange, apply plastic tape to upper and
lower empennage surfaces.
At horizontal stabilizer perimeter of bonding flange, apply aluminum tape to
upper and lower horizontal stabilizer surfaces.
Remove bolt and washer securing ground wire to elevator hinge
bracket on aft horizontal stabilizer and stow ground wire.
LEGEND
1. Plastic Tape
2. Aluminum Tape
To facilitate non-destructive removal of the horizontal stabilizer, a bond void
must exist at the leading edge, extending aft approximately 3 inches (8 cm)
at upper and lower surfaces.
To facilitate non-destructive removal of the horizontal stabilizer, the bond
gap at the fuselage flange must be 0.05 inch (1.27 mm) or greater.
Using 90° oscillating tool with cutting disc at bond line, cut horizontal stabilizer
section from empennage. If necessary, use blade oscillating tool to cut remaining
bond line.
SR22_MM55_2387
Figure 55-101
Horizontal Stabilizer Removal - Method #1
EFFECTIVITY:
All
55-10
Page 5
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
1.0 inch (2.54 cm)
HORIZONTAL STABILIZER
COMPOSITE REMNANT
(REF)
HORIZONTAL STABILIZER
(REF)
WEDGE
(REF)
NOTE
Draw an offset line 1.0 inch (2.54 cm) from the horizontal
stabilizer root around entire surface of horizontal stabilizer.
Repeat on opposite side.
Using reciprocating saw with 6 inch (15 cm) blade, at offset line, cut horizontal
stabilizer section from empennage. Repeat on opposite side.
Remove bolt and washer securing ground wire to elevator hinge
bracket on aft horizontal stabilizer and stow ground wire.
Using reciprocating saw with 6 inch (15 cm) blade, cut through spar of
remnant to remove core.
Position cutting end of wedge between aft remnant and fuselage flange.
Strike back of wedge forward to leading edge of remnant.
If leading edge of remnant is still adhered to fuselage flange, alternately
position flat end of wedge to sides of remnant and strike with hammer until
remnant is loosened.
SR22_MM55_2152
Figure 55-102
Horizontal Stabilizer Removal - Method #2
55-10
Page 6
15 Apr 2007
EFFECTIVITY:
All
CIRRUS
(l)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Remove residue. (See Figure 55-103)
1
Apply low-tack tape over LH access panel opening to restrict debris from entering
empennage.
2
Plug inside of empennage with breather material to contain debris during residue
removal.
CAUTION:
3
Protect skin of airplane from scuffing against vacuum nozzle using
low-tack tape as barrier between structures.
Apply low-tack tape to airplane skin below fuselage flange where vacuum nozzle will
be positioned. Position vacuum nozzle upward and secure to empennage with tape.
Turn vacuum on.
CAUTION:
If installed, do not remove shims from bonding flange on fuselage.
Removal of shims will require reinstallation of shim and additional
adjustments.
Do not damage the bonding flange when removing residual material.
4
(m)
(n)
EFFECTIVITY:
All
Using 90° die grinder with 80-grit sanding drum, remove remaining composite and
adhesive from bonding flange on fuselage.
5
Use low-profile orbital sander for more controlled adhesive removal as majority of
residue is removed. Hand sand when necessary at leading edge until at least 70%
of original laminate surface is exposed.
6
Solvent clean bonding flange on fuselage. (Refer to 20-30)
7
Repeat residue removal at remaining fuselage flange surfaces.
Horizontal Stabilizer Removal Method #1: Inspect horizontal stabilizer for damage and
repair as necessary.
1
If extent of damage does not exceed 2 plies, perform Laminating - In Place Method
installing twice as many plies as the original lay-up. (Refer to 51-20)
2
If extent of damage is greater than 2 plies, contact Cirrus Design for disposition.
(Refer to AMM-Intro)
Inspect fuselage flange for damage and repair as necessary.
1
If extent of damage does not exceed 2 plies, no repair is necessary.
2
If extent of damage is equal to 3 - 6 plies, perform Laminating - In Place Method
installing one ply for each ply replaced in the original lay-up. (Refer to 51-20)
3
If extent of damage is greater than 6 plies, contact Cirrus Design for disposition.
(Refer to AMM-Intro)
55-10
Page 7
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
FUSELAGE BONDING
FLANGE
(REF)
FUSELAGE
BONDING
FLANGE
(REF)
ADHESIVE
(REF)
SHIM
(REF)
FUSELAGE
BONDING
FLANGE
HORIZONTAL (REF)
STABILIZER
COMPOSITE
REMNANT
ADHESIVE
(REF)
(REF)
2
1
Serials 0002 thru 0820.
SHIM
(REF)
SHIM
(REF)
Serials 0821 & subs.
HORIZONTAL STABILIZER
COMPOSITE REMNANT
(REF)
NOTE
Protect skin of airplane from scuffing against vacuum nozzle
using low-tack tape as barrier between structures.
SHIMS
(REF)
SHIM
(REF)
If installed, do not remove shims from bonding flange on fuselage.
Removal of shims will require reinstallation of shim and additional
adjustments.
Do not damage the bonding flange when removing residual material.
Using 90° die grinder with 80-grit sanding drum, remove remaining
composite and adhesive from bonding flange on fuselage. Use
low-profile orbital sander for more controlled adhesive removal as
majority of residue is removed. Hand sand when necessary at leading
edge until at least 70% of original laminate surface is exposed.
Serials 0002 thru 0820.
Serials 0821 & subs.
FUSELAGE
LEGEND
BONDING
1. Vacuum
FLANGE
2. Tape
(REF)
Figure 55-103
Residue Removal
55-10
Page 8
15 Apr 2007
EFFECTIVITY:
All
SR22_MM55_2154
CIRRUS
(2)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Installation - Horizontal Stabilizer
WARNING:
Installation of the horizontal stabilizer assembly requires a test flight performed by a Cirrus Design certified test pilot. Contact Cirrus Design prior to
performing maintenance to schedule test flight.
CAUTION:
Proper application of PTM&W ES6292-Based Structural Adhesive is critical to
obtaining full bond strength. The application procedure defined in this procedure
differs from commonly used MGS L418-Based Structural Adhesive and should be
fully understood prior to performing the installation.
(a)
Acquire necessary tools, equipment, and supplies.
Description
EFFECTIVITY:
All
P/N or Spec.
Supplier
Purpose
Bonding Fixture
T6693
Cirrus Design
Duluth, MN 55811
218-727-2737
Mount
Fuselage
Tail Cross Pin
T6149
Cirrus Design
Duluth, MN 55811
218-727-2737
Leveling
Serials 0002 thru 2437:
T1835
Horizontal Incidence Template, HS36, LH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 0002 thru 2437:
T1836
Horizontal Incidence Template, HS36, RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
T1837
Serials 0002 thru 2437:
Horizontal Incidence Template, HS72, LH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 0002 thru 2437:
T1838
Horizontal Incidence Template, HS72, RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 2438 & subs: Hori- T10100
zontal Incidence Template,
HS36, LH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 2438 & subs: Hori- T10101
zontal Incidence Template,
HS36, RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 2438 & subs: Hori- T7733
zontal Incidence Template,
HS72, LH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Serials 2438 & subs: Hori- T10102
zontal Incidence Template,
HS72, RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Feeler Gauge
Any Source
Bondline
Tolerance
0.140-inch
55-10
Page 9
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Description
P/N or Spec.
Page 10
15 Apr 2007
Supplier
Purpose
Pastry Bag
DPBR-18
Bakery Crafts
West Chester, OH 45071
800-543-1673
Application
Flexible Spreader
2-inch
Any Source
Application
600-1050/
Thermocouple Monitor
With Infrared-RS232 adap- 600-0092
tor, serial adaptor, and 2
Type J Thermocouple
Probes
Telatemp Corporation
Indicating and
Fullerton, California 92831 Recording
800-321-5160
Insulation Material
AR04044
Mac ARTHUR CO.
St. Paul, Mn. 55114
800-777-7507
Post Curing
Sheet Metal
-
Any Source
Post Curing
Curing, Empennage Heat
Shield
T7102
Cirrus Design
Duluth, MN 55811
218-727-2737
Curing
Initial Curing Enclosure (w/ T6856-1
Slit), LH
Cirrus Design
Duluth, MN 55811
218-727-2737
Initial Curing
Initial Curing Enclosure (w/ T6856-2
Slit), RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Initial Curing
Post Curing Enclosure
(w/o Slit), LH
T6857-1
Cirrus Design
Duluth, MN 55811
218-727-2737
Post Curing
Post Curing Enclosure (w/o T6857-2
Slit), RH
Cirrus Design
Duluth, MN 55811
218-727-2737
Post Curing
Electronic Temperature
Control Unit
Johnson Controls
Milwaukee, WI 53201
414-524-1200
Temperature
Control
A419ABG-3C
(for 120 VAC)
A419ABC-1C
(for 240 VAC)
55-10
MODEL SR22
Infrared Thermometer
MiniTemp MT4
w/ laser point
Raytek Corporation
Santa Cruz, CA 95061
800-866-5478
Measurement
Bagging Film Breather
(Refer to 51-30)
(Refer to 51-30)
Curing
Flashbreaker Tape
2.0 inches (5.0 cm)
(Refer to 51-30)
(Refer to 51-30)
Protection
Masking Tape (2 Rolls)
3.0 inches
(7.6 cm)
Any Source
Sealing
Blow Dryer (2)
1500 - 1875 Watt Any Source
EFFECTIVITY:
All
Curing
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Description
(b)
(c)
(d)
(e)
(f)
Supplier
Purpose
250 W Heat Lamp(s)
-
Any Source
Curing
Hammer
-
Any Source
Break Sample
Chisel
-
Any Source
Break Sample
Remove rudder assembly. (Refer to 55-40)
Remove wing assembly. (Refer to 57-10)
Remove nose gear strut. (Refer to 32-20)
Hoist airplane. (Refer to 07-20)
Mount fuselage into bonding fixture. (See Figure 55-104)
CAUTION:
1
2
3
4
5
6
7
8
9
10
11
EFFECTIVITY:
All
P/N or Spec.
MODEL SR22
Verify all primary support points on fuselage and bonding fixture are aligned
with one another and no fixture obstructions contact the fuselage while lowering the fuselage onto the bonding fixture.
Position fuselage above bonding fixture.
At aft section of fixture, pivot middle elevator hinge arm outboard.
At forward section of fixture, center engine support base assembly.
Lower fuselage to fixture until nose landing gear mounts and tail cross pin hole are
within 6 inches (15 cm) of final mounting positions.
At RH spar tunnel, install T-bolt to secure male cone datum to bottom of fuselage
spar tunnel.
At LH and RH nose gear strut mounting locations on engine mount frame assembly,
insert tethered engine support pins.
At aft fuselage, insert tail cross pin through aft tooling hole of LH and RH empennage access panels. Ensure pin passes through hole of both access panels.
CAUTION:
Verify tail cross pin is installed at aft fuselage and engine support pins
are installed at forward fuselage before lowering fuselage onto bonding fixture.
Note:
Mating of the cone datum at the spar tunnel should determine location and engine support base assembly should shift as necessary.
Lower fuselage into V-blocks of engine support base assembly and onto tail cross
pin support.
Ensure male upper cone surface is mated with female lower cone surface.
At aft section of fuselage, insert lower rudder pin into position.
Verify fuselage is still correctly positioned at support V-blocks and pin locations.
55-10
Page 11
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
NOTE
At aft fixture, pivot middle elevator
hinge arm outboard.
At forward fixture, center engine
support base assembly.
APPROVED HOISTING
METHOD
Lower fuselage to fixture until nose
landing gear mounts and tail cross
pin hole are within 6 inches (15 cm)
of final mounting positions.
APPROVED HOISTING
METHOD
SR22_MM55_2156
55-10
Page 12
15 Apr 2007
Figure 55-104
Mounting Fuselage To Bonding Fixture (Sheet 1 of 3)
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
MALE CONE DATUM
(REF)
T-BOLT
FEMALE CONE DATUM
(REF)
SIDE VIEW
NOTE
At LH and RH nose gear strut mounting locations on engine
mount frame assembly, insert tethered engine support pins.
Lower fuselage into v-blocks of engine support base assembly.
At RH spar tunnel, install T-bolt to secure male cone datum
to bottom of fuselage spar tunnel.
Cone datum at spar tunnel should determine location and
engine support base assembly should shift as necessary.
V-BLOCKS
(REF)
ENGINE SUPPORT PIN
ENGINE SUPPORT
BASE ASSEMBLY
(REF)
SR22_MM55_2158
Figure 55-104
Mounting Fuselage To Bonding Fixture (Sheet 2 of 3)
EFFECTIVITY:
All
55-10
Page 13
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
VERTICAL FIN
(REF)
EMPENNAGE ACCESS
(REF)
LOWER
RUDDER PIN
TOOLING HOLE
(REF)
TAIL CROSS
PIN SUPPORT
(REF)
TAIL CROSS PIN
NOTE
LH, BIRDSEYE VIEW OF EMPPENAGE & FIXTURE
At aft fuselage, insert tail cross pin through aft
tooling hole of LH and RH empennage access
panels. Ensure pin passes through hole of both
access panels.
Lower fuselage onto tail cross pin support.
SR22_MM55_2160
Figure 55-104
Mounting Fuselage To Bonding Fixture (Sheet 3 of 3)
55-10
Page 14
15 Apr 2007
EFFECTIVITY:
All
CIRRUS
(g)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Mount horizontal stabilizer into bonding fixture. (See Figure 55-105)
1
Record serial number of new horizontal stabilizer and update log book.
New Horizontal Stabilizer Serial Number
2
3
At aft section of fixture, pivot LS 36 and RS 36 elevator hinge arms down.
Rotate trailing edge adjustment clamp lever clockwise to lower clamp.
Note:
4
5
6
7
8
9
10
11
12
13
14
15
16
Serials 0334 & subs w/ ice protection: While installing horizontal stabilizer into fuselage, pass ice protection tubing forward and down
through RH access panel. Loop and stow forward.
Position horizontal stabilizer assembly in opening at aft fuselage.
Serials 0334 & subs w/ ice protection: With ice protection tubing routed forward,
center the horizontal stabilizer into the aft fuselage opening.
At mid-span elevator hinge, pivot LS 36 arm up and position arm on horizontal stabilizer hinge pin.
Install threaded locking pin securing LS 36 arm to horizontal stabilizer hinge pin.
At middle elevator hinge arm, remove threaded locking pin.
Pull release pin to unlock spacer on middle elevator arm.
Pivot middle elevator arm inboard and position arm to elevator hinge bracket.
Position spacer between elevator hinge bracket.
Rotate spacer up and engage release pin into locking position between elevator
hinge bracket.
Install threaded locking pin securing middle elevator arm to elevator hinge bracket.
At mid-span elevator hinge, pivot RS 36 arm up and position arm on horizontal stabilizer hinge pin.
Install threaded locking pin securing RS 36 arm to horizontal stabilizer hinge pin.
At outboard section LS 36 arm, raise locking handle for leading edge adjustment
clamp until rubber foot is in contact with the horizontal stabilizer.
If rubber foot is pressed firmly against horizontal stabilizer before locking handle can
be fully engaged, lower locking handle and rotate rubber foot bolt clockwise as
required until foot does not exceed contact requirements when locking handle is
fully engaged.
If gap exists between rubber foot and horizontal stabilizer with locking handle fully
engaged, lower locking handle and rotate rubber foot bolt counter-clockwise as
required until foot meets contact requirements when locking handle is fully engaged.
Repeat on leading edge adjustment clamp at outboard section of RS 36 arm.
(h)
Determine angle of incidence at bonding flange on fuselage.
CAUTION:
1
2
3
EFFECTIVITY:
All
Apply masking tape to template feet to protect contact locations on wing
surface.
At LH and RH sides of horizontal stabilizer, identify horizontal incidence templates
for HS36 and HS72 and position templates to horizontal stabilizer as marked.
Position digital level at each template and measure angle of incidence.
Verify angle of incidence at all template locations is measured at 0.60 ±0.20°.
55-10
Page 15
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
CAUTION:
MODEL SR22
Ensure adjustment to rubber foot positions does not bring upper or
lower gaps outside of maximum bond thickness tolerances.
If angle of incidence is not within tolerance, lower locking handle and rotate rubber
foot bolt clockwise or counter-clockwise as required to attempt adjustment for angle
of incidence. Ensure template is positioned flush with the horizontal stabilizer.
Repeat verification for angle of incidence tolerance.
If angle of incidence can not be brought within tolerance, contact Cirrus Design for
disposition.
55-10
Page 16
15 Apr 2007
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
HORIZONTAL INCIDENCE
TEMPLATE HS 36
RUBBER FOOT
HORIZONTAL INCIDENCE
TEMPLATE HS 72
LEADING EDGE
ADJUSTMENT
CLAMP
MIDDLE ELEVATOR
HINGE ARM
RELEASE PIN
ELEVATOR HINGE
BRACKET
(REF)
HORIZONTAL
HINGE PIN
LOCKING PIN
LOCKING PIN
SPACER
LS 36 ARM
NOTE
At midspan elevator hinge, pivot LS 36 and RS 36 arm up and position
arm on horizontal stabilizer hinge pin.
Rotate spacer up and engage release pin into locking position between
elevator hinge bracket.
Verify angle of incidence at all locations is measured at 0.60 ±0.20°.
TRAILING EDGE
ADJUSTMENT
CLAMP
SR22_MM55_2162A
Figure 55-105
Mounting Horizontal Stabilizer To Bonding Fixture
EFFECTIVITY:
All
55-10
Page 17
15 Apr 2007
CIRRUS
(i)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
At upper and lower gaps between horizontal stabilizer and bonding flange on fuselage,
verify gaps do not exceed 0.140 +0.0/-0.120 inch (3.556 +0.0/-3.048 mm) between 6.0
inches from leading edge to 4.0 inches from trailing edge. (See Figure 55-107)
Note:
At upper and lower gaps of horizontal stabilizer, bondline thickness requirements do not apply to forward 3.0 inches of leading edge and aft 1.0 inch of
trailing edge.
Bondline thickness requirements between 3.0 to 6.0 inches from leading
edge and between 1.0 to 4.0 inches from trailing edge must not exceed
0.200 +0.0/-0.180 inch (5.080 +0.0/-4.572 mm).
If re-positioning of trailing edge adjustment clamp lever is required, measure
gaps periodically between adjustments.
If upper or lower gap exceeds maximum bond thickness tolerances, rotate trailing edge
adjustment clamp lever. (See Figure 55-105)
1
(j)
Slowly rotate lever counter clockwise to raise trailing edge adjustment clamp as
required.
2
Verify gaps do not exceed 0.140 +0.0/-0.120 inch (3.556 +0.0/-3.048 mm).
3
Repeat angle of incidence measurements at bonding flange on fuselage.
Serials 0002 thru 0820: If re-positioning trailing edge adjustment clamp does not correct
out-of-tolerance measurements, shim upper and lower bonding flange on fuselage as follows. (See Figure 55-106)
Note:
1
If shimming at leading edge, custom shim modification is required to match
curvature of fuselage flange and horizontal stabilizer. Contact Cirrus Design
for disposition.
Acquire necessary tools, equipment, and supplies.
Description
2
P/N or Spec.
Supplier
Purpose
Pre-Cure Shim
12012-001
Cirrus Design
Meet Bondline
Duluth, MN 55811 Requirements
218-727-2737
90° Die Grinder
-
Any Source
Cutting/Abrasion
Sandpaper
80-grit
Any Source
Reduce Shim Thickness
Metal Cut-Off Wheel 2.0 inches
and Arbor
(5.1 cm)
Any Source
Cutting
Sanding Drum
Any Source
Abrasion
80-grit
Detach horizontal stabilizer assembly from fixture and remove from opening at aft
fuselage.
CAUTION:
Shims may not be installed on top of existing shims. Verify all residual
shim material has been removed before installing shims.
Do not damage the bonding flange when removing residual material.
55-10
Page 18
15 Apr 2007
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
3
4
Using 90° die grinder with 80-grit sanding drum, remove any residual shim material
existing on bonding flange.
Using sandpaper, reduce shim thickness as required to maintain bondline requirements.
Note:
5
6
7
Shims to be installed within 3.0 inches (7.6 cm) of the horizontal stabilizer leading edge may be cut 0.25 - 1.0 inch (0.64 - 2.54 cm) wide.
Using 90° die grinder with cut-off wheel, cut shim into 2.0 inches (5.1 cm) wide
pieces.
Pre-fit faying surfaces of shims to upper and lower fuselage flanges (rough-side to
bonding surface, tapered inboard) to ensure the bond fixture used will bring the
bonded surfaces into an allowable tolerance during adhesive curing. Trim shims as
required to fit fuselage flange.
Prepare PTM&W ES6292-Based Structural Adhesive. (Refer to 51-30)
Note:
8
MODEL SR22
The adhesive bead should have a high point near the center of the
bead to avoid entrapped air.
Apply approximately 0.13 - 0.25 inch (3.18 - 6.35 mm) bead of adhesive down the
center of the bond width on the faying surface of the shims. Repeat adhesive application to faying surface of the upper and lower fuselage flanges.
CAUTION:
Avoid applying, removing, and re-applying clamping pressure, as this
will cause air to become entrapped in the bond gap.
Verify bond gap thickness of 0.060 +0.020/-0.055 inch between faying
surfaces of horizontal stabilizer and fuselage flanges.
9
10
11
12
13
14
15
(k)
Serials 0821 & subs: If re-positioning trailing edge adjustment clamp does not correct outof-tolerance measurements, shim lower bonding flange on fuselage as follows. (See Figure 55-106)
Note:
EFFECTIVITY:
All
Position shims rough-side to bond, tapered inboard and place at faying surface of
the upper and lower fuselage flanges. Verify bond gap between individual shims
does not exceed 0.2 inch (0.51 cm).
Secure parts in bond fixture, ensuring that pressure is applied uniformly.
Check edge of bondline for excess adhesive. Remove excess adhesive with cloth
dampened with isopropyl alcohol.
Cure bond. (Refer to 51-20)
Position horizontal stabilizer assembly in opening at aft fuselage and secure into
bonding position with fixture.
Repeat angle of incidence measurements at bonding flange on fuselage.
Repeat gap inspection to verify upper and lower bond gap is within tolerance.
If installation of shims does not bring gaps within tolerance, contact Cirrus Design
for disposition.
If shimming at leading edge, custom shim modification is required to match
curvature of fuselage flange and horizontal stabilizer. Contact Cirrus Design
for disposition.
55-10
Page 19
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
1
Acquire necessary tools, equipment, and supplies.
Description
2
MODEL SR22
P/N or Spec.
Supplier
Purpose
Pre-Cure Shim, Tapered
12013-001
Cirrus Design
Meet Bondline
Duluth, MN 55811 Requirements
218-727-2737
90° Die Grinder
-
Any Source
Cutting/Abrasion
Metal Cut-Off Wheel and
Arbor
2.0 inches
(5.1 cm)
Any Source
Cutting
Sanding Drum
80-grit
Any Source
Abrasion
Detach horizontal stabilizer assembly from fixture and remove from opening at aft
fuselage.
CAUTION:
Shims may not be installed on top of existing shims. Verify all residual
shim material has been removed before installing shims.
Do not damage the bonding flange when removing residual material.
3
Using 90° die grinder with 80-grit sanding drum, remove any residual shim material
existing on bonding flange.
Note:
4
5
6
7
8
Position shim rough-side to bond, tapered end forward to fuselage flange at bonding
location to transfer cutout arc on fuselage flange.
Transfer mark on shim where overlap occurs with fuselage flange cutout arc.
Using 90° die grinder with cut-off wheel, remove marked cutout portion from shim.
Pre-fit faying surfaces of shim to fuselage flange to ensure the bond fixture used will
bring the bonded surfaces into an allowable tolerance during adhesive curing. Trim
length of shim as required to fit fuselage flange.
Prepare PTM&W ES6292-Based Structural Adhesive. (Refer to 51-30)
Note:
9
11
12
13
55-10
Page 20
15 Apr 2007
The adhesive bead should have a high point near the center of the
bead to avoid entrapped air.
Apply approximately 0.13 - 0.25 inch (3.18 - 6.35 mm) bead of adhesive down the
center of the bond width on the faying surface of the shim. Repeat adhesive application to faying surface of the fuselage flange.
CAUTION:
10
Shim is installed with tapered end positioned forward. Verify installation positioning prior to cutting.
Avoid applying, removing, and re-applying clamping pressure, as this
will cause air to become entrapped in the bond gap.
Position shim rough-side to bond, tapered end forward and place at faying surface of
the fuselage flange.
Secure parts in bond fixture, ensuring that pressure is applied uniformly.
Check edge of bondline for excess adhesive. Remove excess adhesive with cloth
dampened with isopropyl alcohol.
Cure bond. (Refer to 51-20)
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
14
15
16
EFFECTIVITY:
All
MODEL SR22
Position horizontal stabilizer assembly in opening at aft fuselage and secure into
bonding position with fixture.
Repeat angle of incidence measurements at bonding flange on fuselage.
Repeat gap inspection to verify upper and lower bond gap is within tolerance.
If shims do not bring gaps within tolerance, contact Cirrus Design for disposition.
55-10
Page 21
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
1
NOTE
Using 90° die grinder with cutting wheel, cut shim into pieces
2.0 inches (5.08 cm) wide.
FUSELAGE
SKIN
(REF)
Shims to be installed within 3.0 inches (7.6 cm) of the horizontal stabilizer
leading edge may be cut 0.25 - 1.0 inch (0.64 - 2.54 cm) wide.
0.10 inch
(2.54 mm)
Pre-fit faying surfaces of shims to upper and lower fuselage flanges
(rough-side to bonding surface, tapered inboard) to ensure the bond
fixture used will bring the bonded surfaces into an allowable tolerance
during adhesive curing. Trim shims as required to fit fuselage flange.
Apply approximately 0.13 - 0.25 inch (3.18 - 6.35 mm) bead of adhesive
down the center of the bond width on the faying surface of the shims.
Repeat adhesive application to faying surface of the upper and lower
fuselage flanges.
FUSELAGE
SKIN
(REF)
Serials 0002 thru 0820.
Figure 55-106
Fuselage Flange Shim - Serials 0002 thru 0820 (Sheet 1 of 2)
55-10
Page 22
15 Apr 2007
0.10 inch
(2.54 mm)
EFFECTIVITY:
Serials 0002 thru 0820
LEGEND
1. Shim
SR22_MM55_2177A
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
1
FUSELAGE SKIN
(REF)
SHIM
(REF)
FUSELAGE SKIN
(REF)
NOTE
Apply a bead of adhesive down the center of the bond width,
approximately 0.13 - 0.25 inch (3.18 - 6.35 mm) bead for each
1.0 inch (25.4 mm) of bond width.
LEGEND
1. Shim
SR22_MM55_2166A
Figure 55-106
Fuselage Flange Shim - Serials 0821 & subs (Sheet 2 of 2)
EFFECTIVITY:
Serials 0821 & subs
55-10
Page 23
15 Apr 2007
CIRRUS
(l)
(m)
(n)
(o)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Prepare repair surfaces of bonding flange on fuselage and horizontal stabilizer. (Refer to
51-20)
Verify proper surface preparation of bond (no shiny areas, free of contaminants, and wiped
clean) at fuselage flange, horizontal stabilizer, and shims.
Mask off bonding flange on fuselage as required. Protect flight control cables with masking
tape.
Prepare PTM&W ES6292-based Structural Adhesive. (Refer to 51-30)
CAUTION:
Apply material in a continuous operation to minimize entrapped air.
Do not move the fixture or apply pressure after injection of adhesive.
(p)
(q)
Record part A and B quantities mixed, ambient air temperature and humidity at time of
repair, technician name, and aircraft information and store per 14 CFR 145.219.
Create inspection sample.
CAUTION:
Ensure that container material is non-waxy to avoid contaminating the
adhesive.
1
2
(r)
Place sample of adhesive into a container (small shallow dish or mylar paper).
Verify sample is approximately 0.5 inch (1.27 cm) thick and 2.0 inches (5.0 cm) in
diameter.
3
Label bottom of container with airplane serial number.
Bond horizontal stabilizer to fuselage. (See Figure 55-107)
CAUTION:
1
Do not apply any pressure to the horizontal stabilizer prior to completing the cure cycle. Disturbing the horizontal stabilizer may create
bond voids.
Pour adhesive into pastry bag.
CAUTION:
Injecting adhesive into bond area may create voids in bondline. If this
is suspected, use spreader to push out voids to opposite end of bond
joint.
Do not move the fixture or apply pressure after injection of adhesive.
2
At upper and lower gaps between horizontal stabilizer and bonding flange on fuselage, use pastry bag to squeeze a sufficient amount of adhesive into the pre-fixtured
bond gap until it is visible extruding from the opposite end of the bond joint. Repeat
on opposite side.
CAUTION:
3
Use spreader to carefully apply slow pressure to adhesive at seam.
CAUTION:
4
55-10
Page 24
15 Apr 2007
Slowly apply pressure to seam when scraping adhesive. If seam is
quickly scraped or too much force is applied, air may be introduced to
the bondline and promote the formation of bubbles.
Fill any gaps or voids immediately and remove any excess material.
Use inspection mirror at RH empennage access panel to verify adhesive at entire
bond area is continuous and free of gaps.
EFFECTIVITY:
Serials 0821 & subs
CIRRUS
AIRPLANE MAINTENANCE MANUAL
5
6
7
8
9
If voids or bubbles are identified from inside of empennage, use spreader at exterior
to carefully apply more pressure slowly at seam. Re-inspect to verify void is eliminated.
Verify no voids or bubbles exist at bondline between horizontal stabilizer and fuselage flange.
Check edge of bondline for excess adhesive and remove excess adhesive with cloth
dampened with isopropyl alcohol.
Use spreader to smooth out adhesive at seam to reduce transition between adhesive and composite surfaces.
Verify excess adhesive at bondline between horizontal stabilizer and fuselage flange
has been removed inside and outside of empennage.
CAUTION:
10
EFFECTIVITY:
Serials 0821 & subs
MODEL SR22
Do not allow inspection sample adhesive to contact any surfaces
within the empennage.
Place inspection sample inside empennage near bond area to be cured.
55-10
Page 25
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2
1
0.140 +0.0/-0.120 inch
(3.556 +0.0/-3.048mm)
MAX. UPPER / LOWER GAP
2
1
1
2
2
2
1
1
2
SHIMS
(REF)
ADHESIVE
(REF)
FUSELAGE SKIN
(REF)
ADHESIVE
(REF)
HORIZONTAL STABILIZER
(REF)
ADHESIVE
(REF)
NOTE
ADHESIVE
(REF)
SHIMS
(REF)
FUSELAGE SKIN
(REF)
Serials 0002 thru 0820.
At upper and lower gaps between horizontal stabilizer and
bonding flange on fuselage, use pastry bag to squeeze a
sufficient amount of adhesive into the pre-fixtured bond gap
until it is visible extruding from the opposite end of the bond joint.
FUSELAGE SKIN
(REF)
Serials 0821 & subs.
SHIM
(REF)
Use spreader to smooth out adhesive at seam to reduce transition
between adhesive and composite surfaces.
Do not move the fixture or apply pressure after injection of adhesive.
At upper and lower gaps of horizontal stabilizer, bondline thickness
requirements do not apply to forward 3.0 inches of leading edge and
aft 1.0 inch of trailing edge.
Bondline thickness requirements between 3.0 to 6.0 inches from leading
edge and between 1.0 to 4.0 inches from trailing edge must not exceed
0.200 +0.0/-0.180 inch (5.080 +0.0/-4.572 mm).
Figure 55-107
Bonding Horizontal Stabilizer To Fuselage
55-10
Page 26
15 Apr 2007
EFFECTIVITY:
All
LEGEND
1. Transfer Tape
2. Masking Tape
SR22_MM55_2164A
CIRRUS
(s)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Attach thermocoupling probes. (See Figure 55-108)
1
At aft RH side of airplane, attach thermocouple monitor and electronic temperature
control unit probes near repair area.
2
At interior of empennage near middle of LH bonding flange, place masking tape on
the lower bottom of the bonding flange for the first thermocouple probe location.
3
At upper RH surface of horizontal stabilizer immediately aft of the leading edge,
place masking tape on the horizontal stabilizer for the second thermocouple probe
location.
CAUTION:
Do not allow Flashbreaker tape to contact airplane finish during cure
process.
4
5
6
(t)
(u)
(v)
EFFECTIVITY:
All
Place Flashbreaker tape on top of the thermocouple probe masking tape locations.
Place thermocouple on top of Flashbreaker tape.
To prevent the thermocouple from coming loose, place Flashbreaker tape on top of
the thermocouple.
7
Place breather insulation on top of the Flashbreaker tape.
8
To prevent direct air from making contact with the thermocouple, place Flashbreaker
tape on top of the thermocouple.
Fabricate air flow enclosures. (See Figure 55-108)
1
Using sheet metal, fabricate baffle for LE1 and RE1 access panel holes to prevent
heat loss into vertical stabilizer cavity.
2
Using insulation material and flame-retardant tape, fabricate void block for inner
empennage to displace heated air volume beneath stabilizer.
Install enclosures for initial cure cycle. (See Figure 55-108)
1
Remove all tape installed around perimeter of bondline.
2
Solvent clean area where enclosures will be attached. (Refer to 20-30)
3
Between LE1 and RE1 access panel holes, position baffle across upper and aft
gaps to restrict air flow.
4
At inner empennage through RE3 access panel hole, position void block between
bulkhead FS289 and FS306.
5
Wrap empennage heat shield with breather to improve seal between shield and
fuselage.
6
Position empennage heat shield to forward opening of bulkhead FS289. Compress
excess breather material towards shield to further insulate.
7
Plug all openings with breather material to minimize heat loss.
8
Position LH enclosure (w/ slit) aft over width of horizontal stabilizer. Secure enclosure at horizontal stabilizer root to empennage and horizontal stabilizer with masking tape.
9
Attach masking tape at slit, at any open seams between enclosure and airplane surfaces, and over any holes in the aft vertical shear web to minimize heat loss.
10
Use masking tape to secure blow dryer nozzle to hot air inlet at aft section of enclosure.
11
Repeat enclosure installation on RH side of horizontal stabilizer using RH enclosure
(w/ slit).
Cure bond. (Refer to 51-20)
1
Connect the probes to the thermocouple monitor.
2
Connect RS232C cable from thermocouple monitor to computer.
3
Turn thermocouple monitor ON. Make sure the channels connected are indicating
properly and the monitor indicates the correct thermocouple type.
55-10
Page 27
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
4
5
6
7
8
9
MODEL SR22
Set thermocouple monitoring system to record temperatures once per minute.
Connect electronic temperature control unit to power.
Connect hot air dryer to electronic temperature control unit.
Connect thermocouple probes to the electronic temperature control unit.
Turn electronic temperature control unit ON. Set electronic temperature control unit
to desired shut-off temperature. Turn blow dryer on.
When cure temperature is stabilized, press the PRINT button on the thermocouple
monitor to begin recording cure cycle temperatures.
Note:
If temperature readings fall below specified cure temperature, that
time cannot be counted as part of the cure time.
10
11
12
(w)
Initial cure repair for specified time and temperature. (See Figure 51-2010)
Stop temperature recording, and turn off blow dryer.
Print recorded temperatures from computer. Title, copy, and retain temperature
printouts.
Check inspection sample.
1
Remove cured inspection sample from empennage.
2
Remove inspection sample from container. Retain container for records.
3
Place inspection sample on hard, clean surface suitable for breaking with chisel.
CAUTION:
4
5
55-10
Page 28
15 Apr 2007
To avoid shattering inspection sample into fragments too small to
analyze, use care when breaking inspection sample to slowly tap
chisel with hammer.
Use hammer and chisel to break inspection sample.
Verify cross-sectional fragments are homogenous. If dark or swirling colors are
present in the sample, the resin was not mixed properly. Contact Cirrus Design for
disposition.
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
2
1
1
7
7
6
1
3
9
8
TO ELECTRONIC
TEMPERATURE CONTROL
TO THERMOCOUPLE
MONITOR & RECORDER
7
HORIZONTAL STABILIZER
REMOVED FOR CLARITY
NOTE
Install thermocouple probe and
temperature sensor on top of right hand
stabilizer approximately 11 inches (28 cm)
forward from aft edge of horizontal stabilizer.
Install thermocouple probe and
temperature sensor on bottom of left
hand flange approximately 4 inches (10 cm)
forward from bulkhead FS289.
6
BULKHEAD FS289
(REF)
LEGEND
1. Flashbreaker Tape
2. Bagging Film Breather
3. Masking Tape
4. Blow Dryer
5. Bagging
6. Thermocouple Probe
7. Temperature Sensor
8. Thermocouple Monitor & Recorder
9. Electronic Temperature Control
Keep flashbreaker tape of airplane finish.
SR22_MM55_2174
Figure 55-108
Curing Horizontal Stabilizer Bond (Sheet 1 of 3)
EFFECTIVITY:
All
55-10
Page 29
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
BULKHEAD FS289
(REF)
BULKHEAD FS306
(REF)
13
12
4 inches
(10 cm)
4 inches
(10 cm)
4 inches
(10 cm)
11
10
6.5 inches
(16 cm)
14
4.25 inches
(11 cm)
13 inches
(33 cm)
NOTE
Using insulation material and flame-retardant tape, fabricate
void block for inner empennage to displace heated air volume
beneath stabilizer.
Using sheet metal, fabricate baffle for LE1 and RE1 access
panel holes to prevent heat loss into vertical stabilizer cavity.
Wrap empennage heat shield with breather to improve seal
between shield and fuselage.
LEGEND
10. Baffle
11. Void Block
12. Empennage Heat Shield
13. Breather
14. Flame - Retardant Tape
SR22_MM55_2170
Figure 55-108
Curing Horizontal Stabilizer Bond (Sheet 2 of 3)
55-10
Page 30
15 Apr 2007
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
13
15
17
17
4
4
POST CURE
RH SIDE
POST CURE
LH SIDE
TO
ELECTRONIC
TEMPERATURE
CONTROL
(REF)
16
4
INITIAL CURE
TO
ELECTRONIC
TEMPERATURE
CONTROL
(REF)
NOTE
With fuselage in bonding fixture, position enclosure (w/ slit) aft over
width of horizontal stabilizer. Secure enclosure at horizontal stabilizer
root to empennage and horizontal stabilizer with masking tape.
With fuselage removed from bonding fixture, position enclosure (w/o slit)
inboard over length of horizontal stabilizer. Secure enclosure at horizontal
stabilizer root to empennage and horizontal stabilizer with masking tape.
Secure enclosure to empennage with masking tape.
Wrap empennage heat shield with breather to improve seal
between shield and fuselage.
On LH side, use masking tape to secure layer of breather
material above and below seam of stabilizer.
LEGEND
4. Blow Dryer
13. Breather
15. Post Cure Enclosure (w/o Slit)
16. Initial Cure Enclosure (w/ Slit)
17. Masking Tape
SR22_MM55_2168
Figure 55-108
Curing Horizontal Stabilizer Bond (Sheet 3 of 3)
EFFECTIVITY:
All
55-10
Page 31
15 Apr 2007
CIRRUS
(x)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Detach fuselage from fixture.
Note:
1
Do not remove baffle, empennage heat shield, and breather enclosures following initial cure cycle. They are also required for post cure cycle.
Remove LH and RH enclosures from horizontal stabilizer.
Note:
Leave thermocoupling attached to airplane and insulation installed for
post cure cycle to follow fuselage removal from bonding fixture.
2
3
4
5
6
(y)
To facilitate hoisting, disconnect the probes from the thermocouple monitor.
Remove elevator locating pin and pivot LS 36 arm down.
Remove locating pin and pivot middle elevator arm outboard.
Remove elevator locating pin and pivot RS 36 arm down.
To ensure bonding operations have not altered fixtured position of horizontal stabilizer, repeat horizontal angle of incidence measurements at all template locations.
(Refer to 55-10)
7
At aft fuselage, remove lower rudder pin.
8
Hoist fuselage from fixture. (Refer to 07-20)
9
At aft fuselage, remove tail cross pin from lower installation hole of LH and RH
empennage access panels.
10
At LH and RH nose gear strut mounting locations on engine mount frame assembly,
remove tethered engine support pins.
11
Detach male cone datum from fuselage spar tunnel.
Install enclosures for post cure cycle. (See Figure 55-108)
1
Connect probes to thermocouple monitor.
2
Between LE1 and RE1 access panel holes, position baffle across upper and aft
gaps to restrict air flow.
3
At inner empennage through RE3 access panel hole, position void block between
bulkhead FS289 and FS306.
4
Wrap empennage heat shield with breather to improve seal between shield and
fuselage.
5
Position empennage heat shield to forward opening of bulkhead FS289. Compress
excess breather material towards shield to further insulate.
6
Plug all openings with breather material to minimize heat loss.
7
Position LH enclosure (w/o slit) inboard over length of horizontal stabilizer. Secure
enclosure at horizontal stabilizer root to empennage and horizontal stabilizer with
masking tape.
8
Attach masking tape at any open seams between enclosure and airplane surfaces,
and over any holes in the aft vertical shear web to minimize heat loss.
9
Use masking tape to secure blow dryer nozzle to hot air inlet at aft section of enclosure.
Note:
10
11
55-10
Page 32
15 Apr 2007
For the LH side only: Due to thermocouple placement on the RH side
of horizontal stabilizer, it is important to ensure overall part temperature is maintained by insulating the LH side with breather material.
On LH side, use masking tape to secure layer of breather material above and below
seam of stabilizer.
Repeat enclosure installation on RH side of horizontal stabilizer using RH enclosure
(w/o slit).
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
Note:
MODEL SR22
During the post cure cycle, re-assembly of airplane may continue outside of post cure area.
12
(z)
(aa)
(ab)
(ac)
(ad)
(ae)
(af)
(ag)
(ah)
(ai)
Repeat cure bond procedure for specified time and temperature required of post
cure repair. (Refer to 55-10), (See Figure 51-2010)
13
Following post cure cycle, remove all enclosures, thermocouple probes and electronic temperature control unit, tape, and insulation from empennage.
At aft elevator hinge bracket, remove LH upper bolt and washer. Secure stowed ground
wire to elevator hinge bracket with bolt and washer.
Install wing assembly. (Refer to 57-10)
Install nose gear strut. (Refer to 32-20)
Serials 0334 & subs w/ ice protection: Connect ice protection tubing.
1
Position nylon tubing forward through gap at horizontal stabilizer leading edge.
Route and connect tubing forward to horizontal proportioning unit. (Refer to 30-05)
2
Install access panel CB6. (Refer to 06-00)
3
Install bulkhead 222 carpet. (Refer to 25-10)
Paint horizontal stabilizer root. (Refer to 51-20)
Install horizontal stabilizer root fairings. (Refer to 53-50)
Install rudder assembly. (Refer to 55-40)
Install elevator bellcrank. (Refer to 55-20)
Install pitch trim motor assembly. (Refer to 27-30)
Perform Adjustment/Test - Aileron System Rigging and record values. (Refer to 27-10)
Control Surface
Degree Deflection and Cable Tension
Aileron Up
Nominal:
Trim:
Aileron Down
Nominal:
Trim:
Aileron Cable Tension
(aj)
Perform Adjustment/Test - Rudder System Rigging and record values. (Refer to 27-20)
Control Surface
Max Rudder
Degree Deflection and Cable Tension
Right:
Left:
(ak) Perform Adjustment/Test - Elevator System Rigging and record values. (Refer to 27-30)
Control Surface
Degree Deflection and Cable Tension
Elevator Up
Nominal:
Trim:
Elevator Down
Nominal:
Trim:
Elevator Cable Tension
EFFECTIVITY:
All
55-10
Page 33
15 Apr 2007
CIRRUS
(al)
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
Perform Adjustment/Test - Flap Travel and record values. (Refer to 27-50)
Control Surface
Degree Deflection and Cable Tension
Flap Up
Flap 50%
Flap 100%
WARNING:
(3)
The airplane may not be returned to service until a Cirrus Design certified test pilot has performed a flight test. Flight test may only be performed by Cirrus Design authorized personnel.
(am) Perform Functional Test - Flight Test.
Adjustment/Test - Horizontal Stabilizer Angle of Incidence (See Figure 55-109)
(a) Acquire necessary tools, equipment, and supplies.
Description
Masking Tape
55-10
Page 34
15 Apr 2007
P/N or Spec.
-
Supplier
Any Source
Purpose
Protection
Serials 0002 thru 2437: Horizontal T1835
Incidence Template, HS36, LH
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 0002 thru 2437: Horizontal T1836
Incidence Template, HS36, RH
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 0002 thru 2437: Horizontal T1837
Incidence Template, HS72, LH
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 0002 thru 2437: Horizontal T1838
Incidence Template, HS72, RH
Measurement
Cirrus Design
Duluth, MN 55811
218-727-2737
Serials 2438 & subs: Horizontal
Incidence Template, HS36, LH
T10100
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 2438 & subs: Horizontal
Incidence Template, HS36, RH
T10101
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 2438 & subs: Horizontal
Incidence Template, HS72, LH
T7733
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Serials 2438 & subs: Horizontal
Incidence Template, HS72, RH
T10102
Cirrus Design
Measurement
Duluth, MN 55811
218-727-2737
Digital Level, 0.25 Resolution
-
Any Source
EFFECTIVITY:
All
Measurement
CIRRUS
AIRPLANE MAINTENANCE MANUAL
CAUTION:
(b)
To ensure consistent and accurate readings, position digital level so that the
display faces one direction at all template locations (for example, outboard
on RH side and inboard on LH side).
Position digital level at each template and measure angle of incidence.
Note:
(d)
Apply masking tape to template feet to protect contact locations on wing
surface.
At LH and RH sides of horizontal stabilizer, identify horizontal stabilizer incidence templates for HS72 and HS36 and position templates to horizontal stabilizer as marked.
Note:
(c)
MODEL SR22
Negative readings indicate leading edge down. Positive readings indicate
leading edge up.
Verify angle of incidence at all template locations is measured at 0.6 ±0.20°. Record
obtained values.
LH
HS 72
RH
HS 72
LH
HS 36
RH
HS 36
If obtained values are not within tolerance, contact Cirrus Design for disposition.
EFFECTIVITY:
All
55-10
Page 35
15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
LH HS 72
1
3
LH HS 36
RH HS 36
4
2
5
RH HS 72
2
NOTE
Apply masking tape to template feet to protect contact locations on wing surface.
To ensure consistent and accurate readings, position digital level so that the
display faces one direction at all template locations
(for example, outboard on RH side and inboard on LH side).
LEGEND
1. LH HS72 Template
2. RH HS72 Template
3. LH HS36 Template
4. RH HS36 Template
5. Digital Level
SR22_MM55_2208
Figure 55-109
Horizontal Stabilizer Angle of Incidence
55-10
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15 Apr 2007
EFFECTIVITY:
All
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
B. Horizontal Stabilizer Inspection Hole Covers
(1)
Removal - Horizontal Stabilizer Inspection Hole Covers (See Figure 55-1010)
(a) Acquire necessary tools, equipment, and supplies.
Description
Cotton Cloth
(clean and lint free)
Isopropyl Alcohol
P/N or Spec.
Supplier
Purpose
-
Any Source
Cleaning
TT-I-735 Grade
A or B
Any Source
Cleaning
(b)
(2)
Serials 0334 & subs w/ Ice Protection System: For the horizontal stabilizer access panel:
1
Remove screws securing access panel to bottom of horizontal stabilizer.
2
Remove access panel.
(c)
For the horizontal stabilizer forward inspection hole:
1
Remove forward inspection hole cover.
2
Solvent clean area surrounding inspection hole to remove any remaining adhesive
residue. (Refer to 20-30)
(d) For the horizontal stabilizer aft inspection hole:
1
Remove aft inspection hole cover.
2
Solvent clean area surrounding inspection hole to remove any remaining adhesive
residue. (Refer to 20-30)
Install - Horizontal Stabilizer Inspection Hole Covers (See Figure 55-1010)
(a) Serials 0334 & subs w/ Ice Protection System: For the horizontal stabilizer access panel:
1
Position access panel to bottom of horizontal stabilizer.
2
Install screws securing access panel to bottom of horizontal stabilizer.
(b) For the horizontal stabilizer forward inspection hole:
1
Remove protective backing from new inspection hole cover using care not to contaminate adhesive surface.
Note:
(c)
2
Position and install inspection hole cover over forward inspection hole.
For the horizontal stabilizer aft inspection hole:
1
Remove protective backing from new inspection hole cover using care not to contaminate adhesive surface.
Note:
2
EFFECTIVITY:
All
Ensure all edges are firmly adhered.
Ensure all edges are firmly adhered.
Position and install inspection hole cover over aft inspection hole.
55-10
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15 Apr 2007
CIRRUS
AIRPLANE MAINTENANCE MANUAL
MODEL SR22
ICE PROTECTION OPTIONAL
(REF)
2
1
LEGEND
1. Access Panel
2. Inspection Hole Cover
3. Screw
3
SR22_MM55_2291
Figure 55-1010
Horizontal Stabilizer Inspection Hole Covers
55-10
Page 38
15 Apr 2007
EFFECTIVITY:
All