CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
55-10
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EFFECTIVITY:
HORIZONTAL STABILIZER
1. DESCRIPTION
This section covers the horizontal airfoil of the tail section to which the elevator is attached.
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
15 Jun 2010
2. MAINTENANCE PRACTICES
A. Horizontal Stabilizer
CAUTION: Installation and removal of the horizontal stabilizer may only be performed at an
approved Cirrus Design Repair Station.
(1) Removal - Horizontal Stabilizer (See Figure 55-101), (See Figure 55-102)
Two methods of horizontal stabilizer removal are explained. Method #1 contains a removal pro-
cedure 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 possi-
ble.
(a) Acquire necessary tools, equipment, and supplies.
Description P/N or Spec. Supplier Purpose
Oscillating Tool, Blade FSN400E C. & E. FEIN GMBH
D-70176 Stuttgart
+49 (0)711 / 66 65-0
Cutting
Method #1
Blade (Metal) 6-35-02-147-01-5
Oscillating Tool, 90° 12L2240-90 Cooper Power Tools
Sales and Service
Lexington, SC 29071
800-845-5629
Cutting
Method #1
Cutting Disc and Arbor 14-1746
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
Blunt-Edged Chisel - Any Source Cutting
Method #2
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
Protective Tape
Any Source Protection
Plastic Tape, 2-inch - Any Source Protection
Aluminum Tape, 4-inch - Any Source Protection
Method #1
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
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EFFECTIVITY:
(b) Remove pitch trim motor assembly. (Refer to 27-30)
(c) Remove elevator bellcrank. (Refer to 55-20)
(d) Serials 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
Serials w/o FIKI: Disconnect aft tubing from horizontal proportioning unit. (Refer to
30-05), (Refer to 30-06)
5
Serials w/ FIKI: Disconnect aft tubing from tail proportioning unit. (Refer to 30-07)
CAUTION: During horizontal stabilizer removal, do not damage bonding flange on fuse-
lage or vertical fin.
(e) Remove horizontal stabilizer root fairings. (Refer to 53-50)
CAUTION: Verify horizontal stabilizer serial number is recorded prior to cutting horizon-
tal stabilizer to ensure that traceability of component is recorded.
(f) Record horizontal stabilizer serial number.
(g) Remove bolt securing ground wire to elevator hinge bracket on aft horizontal stabilizer and
stow ground wire.
(h) Using low-tack tape, secure rudder into a fixed position.
(i) If performing Horizontal Stabilizer Removal Method #1, verify bond gap measurement
facilitates cutting procedures.
CAUTION: 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).
1
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
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.
(j) Horizontal Stabilizer Removal Method #1: Remove horizontal stabilizer. (See Figure 55-
101)
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.
Bagging Film Breather (Refer to 51-30) (Refer to 51-30) Protection
Description P/N or Spec. Supplier Purpose
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
15 Jun 2010
CAUTION: 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.
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 hori-
zontal 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
Using 90° oscillating tool with cutting disc at bond line, position disc flush with sur-
face 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.
(k) Horizontal Stabilizer Removal Method #2: Remove horizontal stabilizer. (See Figure 55-
102)
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: Use caution when cutting to not cause excessive damage to the fuse-
lage bonding flange. If damage exceeds repair specifications, contact
Cirrus Design for disposition.
2
Using reciprocating saw with 6 inch (15 cm) blade at offset line, cut horizontal stabi-
lizer section from empennage. Repeat on opposite side.
3
Using reciprocating saw, cut through spar of remnant to remove core.
4
Position cutting end of wedge between aft remnant and upper fuselage flange.
5
Strike back of wedge forward to leading edge of remnant.
6
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.
7
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.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
55-10
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EFFECTIVITY:
Figure 55-101
Horizontal Stabilizer Removal - Method #1
At horizontal stabilizer perimeter of bonding flange, apply aluminum tape to
upper and lower horizontal stabilizer surfaces.
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.
At empennage perimeter of bonding flange, apply plastic tape to upper and
lower empennage surfaces.
LEGEND
1. Plastic Tape
2. Aluminum Tape
2
1
Remove bolt and washer securing ground wire to elevator hinge
bracket on aft horizontal stabilizer and stow ground wire.
NOTE
SR22_MM55_2387
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
15 Jun 2010
Figure 55-102
Horizontal Stabilizer Removal - Method #2
SR22_MM55_2152
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.
Remove bolt and washer securing ground wire to elevator hinge
bracket on aft horizontal stabilizer and stow ground wire.
WEDGE
(REF)
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.
Position cutting end of wedge between aft remnant and fuselage flange.
Strike back of wedge forward to leading edge of remnant.
Using reciprocating saw with 6 inch (15 cm) blade, cut through spar of
remnant to remove core.
Using reciprocating saw with 6 inch (15 cm) blade, at offset line, cut horizontal
stabilizer section from empennage. Repeat on opposite side.
HORIZONTAL STABILIZER
COMPOSITE REMNANT
(REF)
HORIZONTAL STABILIZER
(REF)
1.0 inch (2.54 cm)
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
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EFFECTIVITY:
(l) 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: Protect skin of airplane from scuffing against vacuum nozzle using
low-tack tape as barrier between structures.
3
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
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.
(m) 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-00)
(n) 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-00)
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
15 Jun 2010
Figure 55-103
Residue Removal
SR22_MM55_2154
FUSELAGE BONDING
FLANGE
(REF)
If installed, do not remove shims from bonding flange on fuselage.
Removal of shims will require reinstallation of shim and additional
adjustments.
Protect skin of airplane from scuffing against vacuum nozzle
using low-tack tape as barrier between structures.
NOTE
Do not damage the bonding flange when removing residual material.
SHIMS
(REF)
SHIM
(REF)
ADHESIVE
(REF)
SHIM
(REF)
HORIZONTAL STABILIZER
COMPOSITE REMNANT
(REF)
SHIM
(REF)
LEGEND
1. Vacuum
2. Tape
FUSELAGE
BONDING
FLANGE
(REF)
FUSELAGE
BONDING
FLANGE
(REF)
FUSELAGE
BONDING
FLANGE
(REF)
1
2
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.
HORIZONTAL
STABILIZER
COMPOSITE
REMNANT
(REF)
Serials 22-0821 & subs,
22T-0001 & subs.
Serials 22-0002
thru 22-0820.
SHIM
(REF)
ADHESIVE
(REF)
Serials 22-0821 & subs,
22T-0001 & subs.
Serials 22-0002
thru 22-0820.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
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EFFECTIVITY:
(2) Installation - Horizontal Stabilizer
Two methods of horizontal stabilizer installation are explained. Method #1 uses a permanent
floor mounted fixture during bonding procedures. Method #2 uses a portable tool.
WARNING:
Installation of the horizontal stabilizer assembly requires a maintenance
check flight performed by a Cirrus Design authorized test pilot. Contact Cir-
rus Design prior to performing maintenance to schedule check 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 P/N or Spec. Supplier Purpose
Permanent Floor Mounted
Fixture - using Method #1
T6693 Cirrus Design
Duluth, MN 55811
218-727-2737
Bond
Horizontal to
Fuselage
Portable Tool w/ Horizontal
Stands - using Method #2
T11011 Cirrus Design
Duluth, MN 55811
218-727-2737
Bond
Horizontal to
Fuselage
Ruler Gauge (Pegged),
Forward and Aft - using
Method #2
T6320 Cirrus Design
Duluth, MN 55811
218-727-2737
Leveling
Tail Jack Stand - using
Method #2
- Any Source Leveling
Aircraft Hydraulic Jack (2) -
using Method #2
- Any Source Leveling
Transit w/ Base - Any Source Leveling
Digital Level - Any Source Leveling
Tape Measure - Any Source Leveling
Tail Cross Pin T6149 Cirrus Design
Duluth, MN 55811
218-727-2737
Leveling
Horizontal Incidence Tem-
plate, HS36, LH
T1835 Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Horizontal Incidence Tem-
plate, HS36, RH
T1836 Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Horizontal Incidence Tem-
plate, HS72, LH
T1837 Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
19 Sep 2017
Horizontal Incidence Tem-
plate, HS72, RH
T1838 Cirrus Design
Duluth, MN 55811
218-727-2737
Measurement
Feeler Gauge 0.140-inch Any Source Bond line
Tolerance
Pastry Bag DPBR-18 Bakery Crafts
West Chester, OH 45071
800-543-1673
Application
Flexible Spreader 2-inch Any Source Application
Thermocouple Monitor
With Infrared-RS232 adap-
tor, serial adaptor, and 2
Type J Thermocouple
Probes
600-1050/
600-0092
Telatemp Corporation
Fullerton, California 92831
800-321-5160
Indicating and
Recording
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/
Slit), LH
T6856-1 Cirrus Design
Duluth, MN 55811
218-727-2737
Initial Curing
Initial Curing Enclosure (w/
Slit), RH
T6856-2 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
Slit), RH
T6857-2 Cirrus Design
Duluth, MN 55811
218-727-2737
Post Curing
Electronic Temperature
Control Unit
A419ABG-3C
(for 120 VAC)
Johnson Controls
Milwaukee, WI 53201
414-524-1200
Temperature
Control
A419ABC-1C
(for 240 VAC)
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
Description P/N or Spec. Supplier Purpose
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
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EFFECTIVITY:
(b) Remove rudder assembly. (Refer to 55-40)
(c) Horizontal Stabilizer Installation Method #1: Mount fuselage into permanent floor mounted
fixture. (See Figure 55-104)
1
Remove wing assembly. (Refer to 57-10)
2
Remove nose gear strut. (Refer to 32-20)
3
Hoist airplane. (Refer to 07-20)
CAUTION: Verify all primary support points on fuselage and bonding fixture are
aligned with one another and no fixture obstructions contact the fuse-
lage while lowering the fuselage onto the bonding fixture.
4
Position fuselage above bonding fixture.
5
At aft section of fixture, pivot middle elevator hinge arm outboard.
6
At forward section of fixture, center engine support base assembly.
7
Lower fuselage to fixture until nose landing gear mounts and tail cross pin hole are
within 6 inches (15 cm) of final mounting positions.
8
At RH spar tunnel, install T-bolt to secure male cone datum to bottom of fuselage
spar tunnel.
9
At LH and RH nose gear strut mounting locations on engine mount frame assembly,
insert tethered engine support pins.
10
At aft fuselage, insert tail cross pin through aft tooling hole of LH and RH empen-
nage 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 bond-
ing fixture.
Note: Mating of the cone datum at the spar tunnel should determine loca-
tion and engine support base assembly should shift as necessary.
11
Lower fuselage into V-blocks of engine support base assembly and onto tail cross
pin support.
12
Ensure male upper cone surface is mated with female lower cone surface.
13
At aft section of fuselage, insert lower rudder pin into position.
14
Verify fuselage is still correctly positioned at support V-blocks and pin locations.
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 Curing
250 W Heat Lamp(s) - Any Source Curing
Hammer - Any Source Break Sample
Chisel - Any Source Break Sample
Description P/N or Spec. Supplier Purpose
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
19 Sep 2017
Figure 55-104
Mounting Fuselage To Permanent Floor Mounted Fixture - Method #1 (Sheet 1 of 3)
SR22_MM55_2156
At aft fixture, pivot middle elevator
hinge arm outboard.
NOTE
At forward 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.
APPROVED HOISTING
METHOD
APPROVED HOISTING
METHOD
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
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EFFECTIVITY:
Figure 55-104
Mounting Fuselage To Permanent Floor Mounted Fixture - Method #1 (Sheet 2 of 3)
FEMALE CONE DATUM
(REF)
MALE CONE DATUM
(REF)
SIDE VIEW
V-BLOCKS
(REF)
T-BOLT
ENGINE SUPPORT
BASE ASSEMBLY
(REF)
SR22_MM55_2158
At LH and RH nose gear strut mounting locations on engine
mount frame assembly, insert tethered engine support pins.
NOTE
At RH spar tunnel, install T-bolt to secure male cone datum
to bottom of fuselage spar tunnel.
Lower fuselage into v-blocks of engine support base assembly.
Cone datum at spar tunnel should determine location and
engine support base assembly should shift as necessary.
ENGINE SUPPORT PIN
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
19 Sep 2017
Figure 55-104
Mounting Fuselage To Permanent Floor Mounted Fixture - Method #1 (Sheet 3 of 3)
TAIL CROSS PIN
EMPENNAGE ACCESS
(REF)
TOOLING HOLE
(REF)
TAIL CROSS
PIN SUPPORT
(REF)
VERTICAL FIN
(REF)
LOWER
RUDDER PIN
LH, BIRDSEYE VIEW OF EMPENNAGE & FIXTURE
SR22_MM55_2160
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.
NOTE
Lower fuselage onto tail cross pin support.
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EFFECTIVITY:
(d) Horizontal Stabilizer Installation Method #1: Mount horizontal stabilizer into permanent
floor mounted fixture. (See Figure 55-105)
1
Record serial number of new horizontal stabilizer and update log book.
2
At aft section of fixture, pivot LS 36 and RS 36 elevator hinge arms down.
3
Rotate trailing edge adjustment clamp lever clockwise to lower clamp.
Note: Serials w/ Ice Protection: While installing horizontal stabilizer into
fuselage, pass ice protection tubing forward and down through RH
access panel. Loop and stow forward.
4
Position horizontal stabilizer assembly in opening at aft fuselage.
5
Serials w/ Ice Protection: With ice protection tubing routed forward, center the hori-
zontal stabilizer into the aft fuselage opening.
6
At mid-span elevator hinge, pivot LS 36 arm up and position arm on horizontal stabi-
lizer hinge pin.
7
Install threaded locking pin securing LS 36 arm to horizontal stabilizer hinge pin.
8
At middle elevator hinge arm, remove threaded locking pin.
9
Pull release pin to unlock spacer on middle elevator arm.
10
Pivot middle elevator arm inboard and position arm to elevator hinge bracket.
11
Position spacer between elevator hinge bracket.
12
Rotate spacer up and engage release pin into locking position between elevator
hinge bracket.
13
Install threaded locking pin securing middle elevator arm to elevator hinge bracket.
14
At mid-span elevator hinge, pivot RS 36 arm up and position arm on horizontal sta-
bilizer hinge pin.
15
Install threaded locking pin securing RS 36 arm to horizontal stabilizer hinge pin.
16
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.
(e) Horizontal Stabilizer Installation Method #2: Mount horizontal stabilizer into portable tool.
(See Figure 55-105)
1
Using tail jack stand and ruler gauge set, longitudinally level airplane with transit
using fuselage leveling points. (Refer to 08-10)
2
Position horizontal stabilizer assembly in opening at aft fuselage.
3
Position portable tool into fuselage.
4
At vertical spar tooling hole, install lower rudder pin securing aft side of portable tool
to vertical spar.
New Horizontal Stabilizer Serial Number
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5
At RH empennage panel, install tail cross pin through RH and LH empennage
access tooling holes securing outboard sides of portable tool to empennage.
6
Install mounting bolt to forward side of portable tool.
7
Position pass-through hole of mounting bolt to elevator hinge bracket.
8
Install locking pin to secure mounting bolt to elevator hinge bracket.
9
Place aircraft hydraulic jack under LH and RH wing at jack points. (Refer to 07-10)
10
Place horizontal stands under LH and RH horizontal stabilizer approximately 12
inches (30 cm) from outboard edge.
11
Use feeler gauge to verify horizontal is centered within opening.
12
For yaw adjustment, measure with tape measure from HS72 hinge pin to forward
longitudinal leveling point on the same side. Adjust yaw position of horizontal stabi-
lizer so that distances are equal.
13
For roll adjustment, rotate rubber foot bolt on horizontal stands clockwise or counter-
clockwise as required to eliminate roll. Verify that each side of horizontal stabilizer is
perpendicular to the vertical spar.
(f) Determine angle of incidence at bonding flange on fuselage.
CAUTION: Apply masking tape to template feet to protect contact locations on wing
surface.
1
At LH and RH sides of horizontal stabilizer, identify horizontal incidence templates
for HS36 and HS72 and position templates to horizontal stabilizer as marked.
2
Position digital level at each template and measure angle of incidence.
3
Verify angle of incidence at all template locations is measured at 0.60°+/-0.20°.
CAUTION: Ensure adjustment to rubber foot positions does not bring upper or
lower gaps outside of maximum bond thickness tolerances.
Using Permanent Floor Mounted Fixture: If angle of incidence is not within toler-
ance, lower locking handle and rotate rubber foot bolt clockwise or counter-clock-
wise as required to attempt adjustment for angle of incidence. Ensure template is
positioned flush with the horizontal stabilizer. Repeat verification for angle of inci-
dence tolerance.
Using Portable Tool: If angle of incidence is not within tolerance, rotate knurled
adjustment knob on portable tool clockwise (to raise angle of incidence value) or
counter-clockwise (to lower angle of incidence value) as required to attempt adjust-
ment for angle of incidence.
Using Weighted Average Horizontal Incidence Equation:
Note: The equation below is only applicable for incidence measurements
taken at Horizontal Station 36 and 72.
Θ
HT
= 0.3417(
Θ
HS36L
+
Θ
HS36R
) + 0.1583(
Θ
HS72L
+
Θ
HS72R
)
Θ
HT
= Angle of incidence to set
Θ
HS36L
= Angle of incidence measured at Left Horizontal Station 36.
Θ
HS36R
= Angle of incidence measured at Right Horizontal Station 36.
Θ
HS72L
= Angle of incidence measured at Left Horizontal Station 72.
Θ
HS72R
= Angle of incidence measured at Right Horizontal Station 72.
If angle of incidence cannot be brought within tolerance (0.60°+/-0.20°), contact Cir-
rus Design for disposition.
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
55-10
Page 17
All
EFFECTIVITY:
Figure 55-105
Mounting Horizontal Stabilizer To Permanent Floor Mounted Fixture - Method #1 (Sheet 1 of 2)
MIDDLE ELEVATOR
HINGE ARM
RUBBER FOOT
TRAILING EDGE
ADJUSTMENT
CLAMP
SR22_MM55_2162A
At midspan elevator hinge, pivot LS 36 and RS 36 arm up and position
arm on horizontal stabilizer hinge pin.
NOTE
Verify angle of incidence at all locations is measured at 0.60 ±0.20°.
Rotate spacer up and engage release pin into locking position between
elevator hinge bracket.
LEADING EDGE
ADJUSTMENT
CLAMP
SPACER
LOCKING PIN
LOCKING PIN
HORIZONTAL
HINGE PIN
LS 36 ARM
HORIZONTAL INCIDENCE
TEMPLATE HS 72
HORIZONTAL INCIDENCE
TEMPLATE HS 36
ELEVATOR HINGE
BRACKET
(REF)
RELEASE PIN
19 Sep 2017
55-10
Page 18
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
19 Sep 2017
Figure 55-105
Mounting Horizontal Stabilizer To Portable Tool - Method #2 (Sheet 2 of 2)
HORIZONTAL
STAND
MOUNTING
BOLT
PORTABLE
TOOL
TAIL CROSS
PIN
SR22_MM55_3193
At vertical spar tooling hole, install lower rudder pin securing aft side of portable
tool to vertical spar.
NOTE
Verify angle of incidence at all locations is measured at 0.60 ±0.20°.
Position pass-through hole of mounting bolt to elevator hinge bracket.
Install locking pin to secure mounting bolt to elevator hinge bracket.
HORIZONTAL INCIDENCE
TEMPLATE HS 72
HORIZONTAL INCIDENCE
TEMPLATE HS 36
LOCKING
PIN
ELEVATOR HINGE
BRACKET (REF)
LOWER
RUDDER PIN
EMPENNAGE
ACCESS
TOOLING
HOLE
(REF)
VERTICAL SPAR
TOOLING HOLE
(REF)
At RH empennage panel, install tail cross pin through RH and LH empennage
access tooling holes securing outboard sides of portable tool to empennage.
HORIZONTAL
STAND
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
55-10
Page 19
All
EFFECTIVITY:
(g) 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, bond line thickness require-
ments do not apply to forward 3.0 inches of leading edge and aft 1.0 inch of
trailing edge.
Bond line 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 is required, measure gaps periodically between adjust-
ments.
Horizontal Stabilizer Installation Method #1: If upper or lower gap exceeds maximum bond
thickness tolerances, rotate trailing edge adjustment clamp lever. (See Figure 55-105)
1
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.
Horizontal Stabilizer Installation Method #2: If upper or lower gap exceeds maximum bond
thickness tolerances, lower horizontal stands (to reduce excessive lower gap) or raise hor-
izontal stands (to reduce excessive upper gap) as required to attempt adjustment for bond
thickness. Following horizontal stands adjustment, re-adjust angle of incidence using
knurled adjustment knob on portable tool.
(h) Serials 22-0002 thru 22-0820: If out-of-tolerance measurements cannot be corrected,
shim upper and lower bonding flange on fuselage as follows. (See Figure 55-106)
Note: If shimming at leading edge, custom shim modification is required to match
curvature of fuselage flange and horizontal stabilizer. Contact Cirrus Design
for disposition.
1
Acquire necessary tools, equipment, and supplies.
2 Detach horizontal stabilizer assembly from fixture/tool and remove from opening at
aft fuselage.
Description P/N or Spec. Supplier Purpose
Pre-Cure Shim 12012-001 Cirrus Design
Duluth, MN 55811
218-727-2737
Meet Bond line
Requirements
90° Die Grinder - Any Source Cutting/Abrasion
Sandpaper 80-grit Any Source Reduce Shim Thickness
Metal Cut-Off Wheel
and Arbor
2.0 inches
(5.1 cm)
Any Source Cutting
Sanding Drum 80-grit Any Source Abrasion
19 Sep 2017
55-10
Page 20
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EFFECTIVITY:
CIRRUS AIRPLANE MAINTENANCE MANUAL MODELS SR22 AND SR22T
19 Sep 2017
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.
4
Using sandpaper, reduce shim thickness as required to maintain bond line require-
ments.
Note: Shims to be installed within 3.0 inches (7.6 cm) of the horizontal sta-
bilizer leading edge may be cut 0.25 - 1.0 inch (0.64 - 2.54 cm) wide.
5
Using 90° die grinder with cut-off wheel, cut shim into 2.0 inches (5.1 cm) wide
pieces.
6
Pre-fit faying surfaces of shims to upper and lower fuselage flanges (rough-side to
bonding surface, tapered inboard) to ensure the bond fixture/tool used will bring the
bonded surfaces into an allowable tolerance during adhesive curing. Trim shims as
required to fit fuselage flange.
7
Prepare PTM&W ES6292-Based Structural Adhesive. (Refer to 51-30)
Note: The adhesive bead should have a high point near the center of the
bead to avoid entrapped air.
8
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 appli-
cation 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
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).
10
Secure parts ensuring that pressure is applied uniformly.
11
Check edge of bond line for excess adhesive. Remove excess adhesive with cloth
dampened with isopropyl alcohol.
12
Cure bond. (Refer to 51-20)
13
Position horizontal stabilizer assembly in opening at aft fuselage and secure into
bonding position with fixture/tool.
14
Repeat angle of incidence measurements at bonding flange on fuselage.
15
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.
(i) Serials 22-0821 & subs, 22T-0001 & subs: If out-of-tolerance measurements cannot be
corrected, shim lower bonding flange on fuselage as follows. (See Figure 55-106)
Note: If shimming at leading edge, custom shim modification is required to match
curvature of fuselage flange and horizontal stabilizer. Contact Cirrus Design
for disposition.
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