Airglas GLH3000 Nose Ski Service manual

MANUAL REVISION (B)December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Airglas, Inc.
Instructions for Continued Airworthiness
Including
Installation, Maintenance and Service Instructions
MANUAL NO. LH4000-GA8-105
GLH3000 Nose Ski and LH4000 Main Ski
For
GA8 Series Airplanes
Cage Code 17564
Airglas Inc.®

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Record of Revision
Distribution of Changes
A copy of the revised manual or affected pages will be maintained on the Airglas, Inc.
website.
Revision
Date
Affected
Pages
Approved
Description of Revision
Original
9/23/17
All
Clifford D. Belleau
Original Document
A
3/12/18
All
Thomas Lawhorn
Installation procedures finalized
B
12/12/18
All
Jim Hammer
Clarification added

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Airworthiness Limitations
"The Airworthiness Limitations section is FAA approved and specifies maintenance required under
Sections 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has
been FAA approved."
Limitations:
None

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Table of Contents
Page
1.0 Introduction and Description
2.0 Control and Operation 5
3.0 Placards and Markings 6
4.0 Initial Installation 8-9
5.0 Removal 10
6.0 Reinstallation
7.0 Servicing Information 11
8.0 Instructions for Continued Airworthiness 12-13
9.0 Specifications 14
10.0 Trouble Shooting 15
11.0 Drawings and Diagrams 16

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
1.0 Introduction & Description
Introduction: Since 1955 Airglas, Inc. has designed and manufactured composite skis that
dramatically increase the usefulness of the aircraft by allowing it to operate on snow or frozen
surfaces. The installation of the LH4000-GA8 hydraulic wheel ski kit allows the GA8 series of aircraft
to operate on paved or hard surfaces, and snow. With the ski retracted the tires protrude allowing
normal ground operations. When desired, the skis are extended by a hydraulic cylinder on each ski
and an electric/hydraulic pump to provide operating pressure. The ski is pushed down as a sliding
door closes the opening in the ski and causes the tire to ride up on top of the door. The door closes
off the wheel opening, thus creating the performance characteristics of a “straight ski”. The simplicity
of this design allows for a low maintenance high performance ski kit. This is a design that Airglas,
Inc. started in 2004, using the LH4000 installation on Cessna 180/185 aircraft.
Description: The LH4000-GA8 ski installation consists of essentially 3 systems;
1. The Mechanical System –This includes the ski with all attaching hardware (interface to the
gear leg) and the rigging components.
2. The Hydraulic System –This includes hydraulic lines (both onboard and external), hydraulic
actuating cylinders (on the skis), all the hydraulic fittings on the skis, and the hydraulic pumps.
3. The Electrical System –This includes pressure switches, a circuit breaker, wiring, control
switches and indicator lights (the electric pumps are covered under the hydraulic system).
Instructions for installation of this kit are detailed within this manual.
2.0 Control and Operation Information:
The doors for the skis are actuated by electric/hydraulic pumps located in the fuselage aft of
the baggage compartment. The main skis are actuated by one pump and the nose ski by
another pump. Each electric/hydraulic pump is controlled via a 3 position toggle switch and
indicator lights that are located on the instrument panel.
1. When the switch is lifted up, the cylinder will extend and slide the door under the tire. While
the switch is held up a yellow indicator light will illuminate (“IN TRANSIT TO SKIS”) showing
the ski position has been selected and the pump is energized. When the pump pressure
reaches 500 psi, a green light (“SKIS LOCKED DOWN”) will illuminate and stay on to confirm
adequate pressure for deployment of the skis has been reached. The switch is released, the IN
TRANSIT TO SKIS light will extinguish, but the SKIS LOCKED DOWN light will remain lit as
long as the pressure remains above 350 psi. Visual confirmation of the ski position is required
of the operator to confirm ski position.
2. When the switch is pressed down, the door will retract and expose the tire. While the switch is
held down a yellow indicator light (“IN TRANSIT TO WHEELS”) will illuminate showing the
wheel position has been selected and the pump is energized. When the pump pressure

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MANUAL REVISION (B) December 12, 2018
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ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
reaches 500 psi, a green light (“WHEELS LOCKED DOWN”) will illuminate and stay on to
confirm adequate pressure for deployment of the wheels has been reached. The switch is
released, the IN TRANSIT TO WHEELS light will extinguish, but the WHEELS LOCKED DOWN
light will remain lit as long as the pressure remains above 350 psi. Visual confirmation of the
ski position is required of the operator to confirm ski position.
Note:
The “Locked” lights only indicate that a preselected hydraulic pressure has been
met, not that the skis are in proper configuration. Always visually confirm correct
configuration before take-off or landing.
CAUTION
Operation of ski doors can only be done while the aircraft is stopped. Movement of ski
doors when aircraft is moving can damage skis.
3. Low speed taxiing and steering may be enhanced by applying one brake during the cycling of
the main ski door to the open position. Holding the brake will impede the actuation of the door
and allow the opposite sliding door to cycle independently. By extending only one wheel at a
time, the pilot will have increased maneuvering capability on certain snow conditions. This
would be particularly advantageous during solo operations.
CAUTION
Avoid landing on non-frozen surfaces while in the ski configuration. High friction contact
on the ski bottoms may cause high drag and increased wear to ski bottoms.
WARNING
Partial or incomplete actuation of the skis to either configuration is not recommended
during landing or take-off procedures.
3.0 Placards and Markings
The following information must be displayed in the form of composite or individual placards in
addition to those specified in the basic handbook.
A.) Markings and Placards: The airspeed indicator is marked as follows:
oThe red radial line is located at 169 MPH.
DO NOT EXCEED 169 MPH IAS
WITH AIRGLAS SKIS INSTALLED

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Place Airspeed Restriction Placard on instrument
panel immediately adjacent to Airspeed Indicator
and in full view of pilot.
P/N GLH3000-7-1-206
IN TRANSIT TO SKIS
IN TRANSIT TO WHEELS
WHEELS LOCKED DOWN
SKIS LOCKED DOWN
GREEN LEDs HERE
YELLOW LEDs HERE
NOSE
SKI
MAIN
SKI
GREEN LEDs HERE
Located at the ski selector switch.
4.0 Initial Installation
Installation of the skis requires the installation of an Airglas, Inc. nose fork under STC
SA02441AK. The main landing gear axles must be modified by installation of a stub axle and roll pin.
8.50 x 6 tires are required to be installed for this modification.
Refer to drawings:
LH4000-GA8 Sheets 1-10
Installation
LH4000-GA8-HYD Sheets 1-3
Hydraulic System
GLH3000-GA8-7
Electrical Schematic

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
Note: All hardware in this kit shall be installed and torqued IAW AC 43.13-1B Chapter 7, Par 7-40,
Table 7-1 and table 7-2 unless noted. Fluid lines shall be torqued IAW AC 43.13-1B Chapter 9, Par 9-
30, Table 9-2.
Note: Use EZ-Turn or other thread lubricant meeting SAE-AMS-G-6032 MIL-G-6032D Am I Type I on
all fluid fittings.
CAUTION
Disconnect aircraft battery and discharge the alternator excitation capacitor IAW the
appropriate GippsAero Service Manual chapter 24-00-40 before initiating the installation.
MAIN SKI RIGGING FUSELAGE ATTACH BRACKET INSTALLATIONS
1. Remove aircraft interior inspection panels at the pilots and co-pilots seats. Remove the left
hand and right hand side panel inspection panels at F.S. 44.0. Retain the panels and
hardware.
2. Refer to drawing LH4000-GA8 sheet 2 detail A. Locate the LH4000-GA8-9-1L bracket as shown
in detail A on the left hand side of the aircraft. Note the rivets that the bracket will cover. Drill
out the four existing rivets using a #30 drill bit. Enlarge the forward rivet hole using a #9 drill
bit. Install the bracket using an AN525-10R10 screw and MS21044N3 nut with one
NAS1149F0363P washer on the back side. Align the bracket so that the top is parallel to the
skin lap joint. Using a pancake drill spot locate the two rivet holes using a #30 drill bit. Do not
attempt to back drill the stainless bracket in place.

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
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ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
3. Remove the bracket and drill the spot locations with a sharp #30 drill bit. Lay out the two
additional fastener locations using detail A. Pilot drill them using the #30 drill bit and then
increase the fastener holes in the bracket using the #9 drill bit. Deburr the holes.
4. Using a 100 degree countersink, countersink the aft existing hole that the bracket partially
covers. Install an MS20426AD4-X rivet in this location. Note: Rivet should be long enough to
have 1.5 diameters, beyond skin thickness.
5. Reinstall the bracket using the forward AN525-10R10 screw, NAS1149F0363P washer, and
MS21044N3 nut. Align the bracket horizontally and drill the existing #30 holes in the fuselage
out to #9 and install an AN525-10R10 screw, NAS1149F0363P washer, and MS21044N3 nut
each location. Vacuum any shavings from the aircraft.
6. Repeat the above procedure on the right hand side of the aircraft using the LH4000GA8-9-1R
bracket.
7. Remove the aircraft interior floor inspection panels between FS. 87 and FS. 170. Refer to
drawing LH4000-GA8 sheet 2 detail B. Locate the LH4000GA8-9-2L as shown in detail B on
the left hand side of the aircraft. Note the rivets that the bracket will cover. Drill out the two
existing rivets using a #30 drill bit. Enlarge the forward rivet hole using a #9 drill bit. The top
edge of the LH40009GA8-9-2L and the packer part #LH4000GA8-9-1P must be ground to fit

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
the contour of the fuselage and maintain hole edge distance. Install the bracket using an
AN525-10R10 screw and MS21044N3 nut with one NAS1149F0363P washer on the back side,
the shim part# LH4000GA8-9-1S goes under the lower 2 holes and tight to the skin lap. It
can be held in place with double face tape until all the holes have been drilled. Align the
bracket so that the top is parallel to the skin lap joint. Using a pancake drill spot locate the
remaining existing rivet hole using a #30 drill bit. Do not attempt to back drill the stainless
bracket in place.

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
8. Remove the bracket and drill the spot locations with a sharp #30 drill bit. Lay out the three
additional fastener locations. Pilot drill them using the #30 drill bit and then increase the
fastener holes in the bracket using the #9 drill bit. Deburr the holes.
9. Reinstall the bracket using the forward AN525-10R10 screw, NAS1149F0363P washer, and
MS21044N3 nut. Align the bracket horizontally and drill the existing #30 holes in the fuselage
out to #9. The lower forward hole in the bracket goes through a fuselage bulkhead that is
fluted. That flute can be flattened by putting a screw through the bracket, and using a large
area washer that has been ground flat on one side, tighten the nut until the flute has been
flattened. Remove the large area washer and install the doubler with a AN525-10R10 screw,
NAS1149F0363P washer, and MS21044N3 nut each location. Vacuum any shavings from the
aircraft.
10.Remove the right hand lower interior trim side panel from station FS 87 to FS 157. Locate the
LH4000GA8-9-2R as shown in detail C on the right hand side of the aircraft. Note the rivets
that the bracket will cover. Drill out the three existing rivets using a #30 drill bit. Enlarge the
forward rivet hole using a #9 drill bit. Install the bracket using an AN525-10R10 screw and
MS21044N3 nut with one NAS1149F0363P washer on the back side. Using a pancake drill
spot locate the two rivet holes using a #30 drill bit. Do not attempt to back drill the stainless
bracket in place.

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
11.Remove the bracket and drill the spot locations with a sharp #30 drill bit. Lay out the two
additional fastener locations using detail A. pilot drill them using the #30 drill bit and then
increase the fastener holes in the bracket using the #9 drill bit. Deburr the holes.
12.Reinstall the bracket using the AN525-10R10 screw, NAS1149F0363P washer, and
MS21044N3 nut. Align the bracket horizontally and drill the existing #30 holes in the fuselage
out to #9. Install the doubler with a AN525-10R10 screw, NAS1149F0363P washer, and
MS21044N3 nut each location. Vacuum any shavings from the aircraft.
MAIN SKI RIGGING WING ATTACH BRACKET INSTALLATIONS
1. Refer to drawing LH4000-GA8 sheet 2 details D and E. Remove the inspection panel on the left
hand wing leading edge closest to the fuselage and retain.

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MANUAL REVISION (B) December 12, 2018
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ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
2. Locate the third leading edge rib outboard at WS 23.5. Install doubler LH4000-GA8-9-3.
Carefully Cleco the doubler in place using the exist tooling hole in the wing rib. Rotate the
doubler until it nests between the leading edge flange and the spar flange on the rib. If the
doubler does not ride flush against the rib web, carefully trim the doubler until it rides flush.
You may need to lift the edge of the wire grommet(s) to allow the doubler to fit flush. Using
the doubler as a guide, drill the four .1875” diameter holes in the wing rib.
3. Remove the LH4000-GA8-9-3 and deburr the holes.
4. Install the LH4000-GA8-9-3 doubler and the LH4000-GA8-9-4L assembly in the wing, and
secure with five AN3-4A bolts, NAS1149F0363P washers, and MS21044N3 nuts.
5. Using the LH4000-GA8-9-4L as a guide, center-punch the lower skin from the inside. Using a
stepped drill bit with a 3/8” thin washer as a stop, drill a .375” diameter hole in the bottom of
the wing skin. Vacuum all shavings from wing.
6. Install an AN46-6A eye bolt into the LH3600-GA8-9-4L with one NAS1149D0632J washer.
Torque eye bolt (minimum of 95 in. lbs. maximum 190 in. lbs.) and align the tab parallel to
the slip stream. Use additional NAS1149D0632J washers if needed to align the eyebolt.
7. Repeat steps 12 thru 17 on the right side of the aircraft.
8. Reinstall all inspection panels using retained hardware.

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
MAIN SKI ATTACHMENT
1. The aircraft will need to be hoisted or jacked. Use caution and jack IAW chapter 7-10-00 of
the appropriate GippsAero service manual.
2. Remove the two AN5-23A bolts holding the main landing gear axle onto the main gear leg.
Install the LH3600-6-GA8 flange on the inside of the main landing gear. Install two AN5-26A
bolts wet with PRC 3204 B1/2 (or equivalent) with new MS21042-5 nuts to secure the flanges.
3. Deflate the main tire. Remove the axle cotter-pin, drill out the part number GA8-321023-31
axle sealing plug and remove (Note: use a ¾” stepped drill bit and it will often spin out on its
own), remove axle nut and retain. Remove the brake pad retaining bolts, and remove the
wheel (retain bolts and wheel). Install the LH3600-7-GA8 stub axle in the axle. Cross drill with
a #13 drill bit so that the roll pin is located under the outer wheel bearing (the wheel bearing
acts as a safety to prevent the roll pin from backing out). Insert a 3/16 x 1 1/2 roll pin
(MS171599) and drive flush. Lightly file any burrs off to allow the wheel to be installed.
4. Reinstall the wheel and brake assembly. Tighten the axle retaining nut until slight bearing drag
is felt when wheel is rotated. Loosen nut to nearest alignment hole and install an LW2500-21
axle nut retainer clip on the axle nut. Re-inflate the tire. Slide the ski beneath the tire. Once
the ski is positioned, the aircraft may be lowered to the ground.
5. The rod ends on the yoke can next be thru-bolted to the stub axles using the NAS1312-15
bolts. Install AN960-1216(L) and AN960-1216 washers as needed to center the tire in the ski.
Adjust the rod ends in the yoke assembly (LH3600-5-GA8) and align the skis parallel to the
aircraft centerline. (up to 1.5” toe-in is acceptable)
6. Remove the NAS1312-15 bolts and insert the nylon set screws into the inboard flange and
stub axles until the nylon screw just protrudes below the minor diameter of the ¾” threads.
Reinstall the NAS1312-15 bolts and torque to 280 to 300 ft-lbs. (Note: Subsequent
reinstallation requires new set screws)
7. Hoist or jack the aircraft until the bungee cable assembly can be attached to the wing attach
point (a bungee stretcher can also be used). Attach the tab to the I-bolt using the AN396-15
clevis and cotter pin.
8. Lower the aircraft to the ground. Attach the rear check cable and forward safety cables.
9. Hoist or jack the aircraft and confirm the skis are at +1.5° tip up in the ski position in flight
with the ski in the down position. (Measure relative to aircraft horizontal level position)
10.Make sure all hardware is installed, torqued, and cotter pinned as necessary.

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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
NOSE SKI ATTACHMENT
1. The aircraft will need to be hoisted or jacked to install the nose ski. Use caution and jack IAW
chapter 7-10-00 of the appropriate GippsAero service manual.
2. Referencing drawing PA32-206LA, remove the AN365-524 nuts, washers, PA32-206L-5
spacers, PA32-206L-4 axle rod and PA32-206L-6 buckets from the nose fork. (Discard) Ensure
that the MS171596 roll pins are installed in each PA32-206L-6-GLH bucket. Install the PA32-
206L-6-GLH buckets and PA32-206L-4-GLH axle rod on the PA32-206LA nose fork. Adjust the
bearing pre load of the nose wheel bearings. Slip heat shrink or rubber tubing over the
.032”safety wire where it will ride on the nose fork before and safety the buckets to the nose
fork to prevent their turning.
3. Slide the ski beneath the tire. The rod ends on the yoke can next be bolted to the PA32-206L-
6-GLH buckets with two AN6H25A bolts thru the GLH3000-NG-LR1-1L and -1R rigger brackets.
Place one NAS1149F0663P washer on each side of the rod end. Leave the bolts loose, and
install the GLH3000-NG-LR1-3(L or R) straps IAW drawing GLH3000-GA8 sheet 4. Install the
brackets using four AN6-24A bolts on the right side and AN6-25A bolts on the left, install the
MS21045-6 nuts on each bolt but just finger tight.
4. Adjust the rod ends to center the tire in the yoke assembly (GLH3000-5) and align the ski
parallel to the aircraft centerline. Move the rod ends in to provide additional clearance on the
rear of the door opening if needed.
5. Lift the ski up until the ski stops contact the rigger brackets and block it in position. Remove
the AN6-25A bolts on the top left hand side, and gently rotate the rigger bracket aft until you
can install the GLH3000-NS-14 bungee assembly using one each AN6-25A bolt, PA32-206
spacer, NAS1149F0663P washer, and MS21045-6 nut.
6. Rotate the rigger upward and install the forward safety cable assy. using one AN6-25A bolt
thru the forward hole of the GLH3000-NG-LR1-3L strap, NAS1149F0663P washer, and
MS21045-6 nut. INSERT PHOTO HERE. Install the rear safety cable using one AN6-25A bolt
thru the aft hole in the GLH3000-NG-LR1-3L strap. Secure the AN6-25A bolt with the
NAS1149F0663P washer, and MS21045-6 nut. Remove the blocking.
7. Install the rigger on the right hand side of the nose fork using the middle hole in the
GLH3000-NG-LR2-2 bracket. Place one AN970-6 washer under the bolt head and one
NAS1149F0663P washer between the rod end and the bracket. Secure with one AN6-24A bolt
NAS1149F0663P washer, and MS21045-6 nut. Torque all nuts. INSERT PHOTO HERE
8. Lower the aircraft to the ground and with the nose tire protruding, adjust the rigger until the
nose ski tail wheel tire contacts the ground with enough pressure to slightly move the ski up

Airglas, Inc. Manual # LH4000-GA8-105
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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
stop off the rigger bracket on the left hand side. Hoist the nose ski clear of the ground and
confirm nose ski tip up angle is no greater than +3.5˚ with the ski in the retracted position
(tire protruding). (Measure relative to aircraft horizontal level position)
9. Make sure all hardware is installed, torqued, safety-tied, and cotter pinned as necessary.
10.Remove aircraft from hoist or jacks.
SPOT MIRROR INSTALLATION
1. Remove the wing access plate from the right hand wing IAW drawing LH4000-GA8 sheet 9.
2. Install the mirror on the cover plate with one screw. Reinstall the access plate on the wing.
Rotate the mounting plate to align the pilots view to contain both the main and nose ski. Drill
the second hole.
3. Remove the access plate and install the additional fastener. Reinstall the access plate.
4. Repeat for the left side, with the exception that you must install MS21078-3 nutplates. After
the alignment holes have been drilled, drill the mounting holes for the nutplates, dimple the
access panel, countersink the nutplates, and rivet them on with the AN426AD-3-4 rivets.
5. The left side requires the access panel to be in place before attaching the mirror.
HYDRAULIC PUMP & LINE ROUTING
1. Remove the fuselage interior panel at FS 170.29, retain the panel and hardware. Some
aircraft have a cargo bin in place of the interior panel, remove the bin as above. Remove
the fuselage access panel from fuselage belly between FS 195.29 and FS 207.29, retain
panel and all fasteners. Remove the fuselage floor inspection panels from FS 82.31 to FS
170.29, retain the panels and all fasteners.
2. Locate the LH3600-20-GA8 pump mounting plate in accordance with drawing LH4000-GA8-
HYD detail E.
3. Drill the MS20470AD4 rivets from the side channels, vacuum any drill shavings from the
area and place the LH3600-20-GA8 mounting plate in the fuselage. Back drill the plate
using the existing rivet holes along the sides. Cleco the plate as you go. Layout and drill a
forward, aft, row of rivets with a similar spacing and pump mounting holes IAW drawing
LH4000-GA8-HYD. Remove the mounting plate, deburr the holes, vacuum any drill
shavings. Rivet the plate to the fuselage using MS20470AD4 rivets IAW drawing LH4000-
GA8-HYD.

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MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
4. Drill a .125” diameter drain hole in the fuselage belly just aft of F.S. 182.79.
5. Install the pressure switches and hydraulic fittings on the pumps and install the pumps in
the aircraft IAW drawing LH4000-GA8-HYD. One pump is used for the main skis and one is
used for the nose ski.
6. Drill the holes for the 6 bulkhead fittings at FS 87.125 IAW drawing LH4000-GA8-HYD
detail C, and D. Install each of the AN833-4D bulkhead fittings from the outside with one
NAS1179D0763J washer on the outside and one on the inside. Secure each with one
AN924-4D nut.
7. Install two aluminum doublers at FS 157.29 bulkhead IAW drawing LH4000-GA8-HYD
figure B-B using MS20470AD4 rivets. Drill 0.4375 holes through the bulkhead and doublers.
Insert the AN832-4D bulkhead fittings thru the FS 157.29 bulkhead from aft to front. Install an
NAS1149D0763J and AN924-4D nut on the fitting and tighten.
8. Install the 5052-O ¼” x .035 aluminum tubes IAW drawing LH4000-GA8-HYD table on
sheet 3 of the hydraulics. Route the tubes IAW sheet 3 LH4000-GA8-HYD. Flare each tube
IAW AC43.13-1B chapter 9 paragraph 9-30. Confirm they are in the correct sequence and
orientation. It is easier to “TEE” the main ski tubes aft of F.S. 170 and run them forward
then to try and cross the fuselage further forward.Two tubes are installed in the left hand
side of the fuselage (LH main) and four are installed in the right hand side (RH main &
nose). The “UP” port on the pumps goes to the forward fitting on the cylinder. INSERT
PHOTO HERE
9. Secure the lines with friction tape and cushioned clamps at intervals no greater than 18”
intervals IAW drawing LH4000-GA8-HYD Sheets 1 thru 3. Ensure the tubes do not interfere
with flight controls and are not able to chafe.
10.Fabricate two tubes from the FS 82.31 lower AN833-4D fittings to the FS 0.0. Route these
tubes along the fuselage exterior skin IAW drawing LH4000-GA8-HYD figure F. Attach two
AN815-4D unions to the forward end. Secure the lines with friction tape and cushioned
clamps at intervals no greater than 18” intervals IAW drawing LH4000-GA8-HYD figure E.
11.Fabricate the 6 flexible hoses IAW drawing LH4000-GA8-HYD table 1 and AC43.13-1B
chapter 9 figure 9-8 or the hose manufacturer’s instructions.
12.Connect the nose ski hoses IAW drawing LH4000-GA8-HYD schematic 1 with the hose from
tube #1 to the forward ski hydraulic fitting and tube 2 to the aft fitting. Secure the hoses
with friction tape and cushioned clamps as shown in photo 1.

Airglas, Inc. Manual # LH4000-GA8-105
19 | P a g e
MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
13.Connect the main ski hoses IAW drawing LH4000-GA8-HYD schematic 2 with the hoses
from tubes 3 connected to the forward ski hydraulic fittings, and tube 4 to the aft fitting.
Secure the hoses with friction tape and cushioned clamps as shown in photo 2.
COCKPIT CONTROLS
1. Select an appropriate location for the control panel in the cockpit.
(Usually an unoccupied instrument hole is sufficient.)
2. Determine the lengths of wire required to reach the master side of the bus and route the wires
IAW AC 43.13 chapter 11 recommended practices. Route the pump power supply and control
wires for the pumps through the aircraft IAW AC 43.13 chapter 11 recommended practices.
3. Install the wiring IAW GLH3000-GA8-7 wiring diagram.
Installation instructions for the Parker-Electro/Hydraulic pump.
The pump direction is changed by reversing the polarity to the pump. While not intuitive, the pump must
be connected with the correct polarity and both electrically and hydraulically. The pump must be plumbed
with the “UP” port connected to the forward fitting on the ski cylinder.
1. Make sure that the polarity for the pump is correct.
BLUE 12 V or Black 24V (SKIS) GREEN 12V or Orange 24 V (WHEELS)
a. Switch sends power to blue or black wire during “Ski” selection.
This will pressurize the “UP” port of the pump.
b. Switch sends power to the green or orange wire when “Wheels” are selected.
This will pressurize the “DOWN” side of the pump.
Make sure the “UP” Port on the pump goes to the FWD fitting on the deployment
Cylinder.
2. When arranging the switch and indicator lights on the control panel, make sure that the
switch “UP” position is for Skis (green Lights) and switch “DOWN” is for Wheels (green
lights).
NOT following these instructions WILL make the system OPERATE INCORRECTLY.
FUNCTION AND LEAK CHECK
1. To prevent overfilling, top off the hydraulic reservoirs with the skis in the deployed position
(tires retracted). Use only MIL-H-5606 or equivalent.
2. Service main and nose tires to 35 psi.

Airglas, Inc. Manual # LH4000-GA8-105
20 | P a g e
MANUAL REVISION (B) December 12, 2018
THIS MANUAL INCLUDES INFORMATION PROPRIETARY TO Airglas, Inc. AND SHALL NOT BE USED TO MANUFACTURE OR REPRODUCE ANY PART OR
ASSEMBLY WITHOUT THE PRIOR WRITTEN PERMISSION OF Airglas, Inc.
3. With external power applied to the aircraft, select skis and ensure deployment of all three skis.
Confirm transit to skis lights illuminate while pumps are running. Confirm that skis locked
lights illuminate when skis reach full deployment and pumps stop. Deployment will take
approximately 90 seconds. (do not allow pumps to run dry)
4. Select wheels and ensure the doors retract and the tires protrude on all three skis. Confirm
transit lights illuminate while pumps are running. Confirm that wheels locked lights illuminate
when wheels reach full extension and pumps stop. Retraction will take approximately 90
seconds. (do not allow pumps to run dry)
5. Check for leaks of the system, and service pump reservoirs.
6. Reinstall any inspection or interior panels that were removed.
AIRCRAFT RECORDS AND WEIGHT AND BALANCE
1. Place a copy of the AFMS in the aircraft flight manual.
2. Apply the placards and markings called out in the AFMS on the instrument panel. If the
airspeed indicator is marked on the glass, ensure that a slip mark on the glass is incorporated.
3. Revise aircraft weight and balance and equipment list to reflect installation.
4. Prepare and file FAA Form 337. Make appropriate entry in the aircraft maintenance records.
6.0 Removal-
During removal, note and record the location of any packing washers between rod-ends and
axle flanges, stubs, or buckets. Retain all hardware for future reinstallation.
6.1 Main Skis
1. Hoist or jack the aircraft.
2. Remove the rigging from the fuselage attach points.
3. Disconnect and cap all hydraulic lines and fittings.
4. Remove the NAS1312 bolts form the inboard flange and stub axle.(main skis)
5. Remove the main skis from the aircraft.
6.2 Nose Ski