# Gulfstream Service Bulletin G550-32-1: No revision named

- Rights: © Gulfstream Aerospace Corporation. Filed by the FAA in regulations.gov docket FAA-2016-9070, the docket of AD 2016-18-11. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Gulfstream Service Bulletin G550-32-1](https://openairdocs.org/service-documents/gulfstream/g550-32-1.md)
- Title as filed: G550_32_1 Temp Rev
- Pages: 16
- PDF: https://openairdocs.org/files/sha256/2f/4e/2f4e97b9741f5788bfca10f8beb33346712f60106ec7b67d076183c7578073c1
- Page: https://openairdocs.org/service-documents/gulfstream/g550-32-1/file/2f4e97b9741f

## Text

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### Page 1

MAIN GEAR DOOR ACTUATOR — REMOVAL / INSTALLATION
1. Main Gear Door Actuator — Removal / Installation
A. General
The main landing gear door actuator is located on the door control arm at fuselage station 586.
B. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT
Container, Skydrol resistant ................................................................................................ Stand ard
Circuit breaker safety clip ................................................................................................... Stan dard
Protective caps and plugs .................................................................................................. Standar d
CONSUMABLES
Lubricant .......................................................................................................................... MCS-352B
Bushing .................................................................................................................. 1159LM20296-19
Bushing .................................................................................................................. 1159LM20296-21
O-ring ............................................................................................................................ NAS1612-4A
O-ring ...................................................................................................................... NAS 1612-6A (2)
Backup ring ................................................................................................................... MS 28773-04
Backup ring ............................................................................................................. MS28773- 06 (2)
Cotter pin ............................................................................................................... MS24665 -285 (2)
NOTE: When lubricant MCS-352B is not available, Skydrol ﬂuid may be used as an alternate.
(1) References
• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices
• Hydraulic System Bleeding Procedure, 29-00-00, Servicing or Code 290001
• Hydraulic System Bleed Procedure - Alternate, 29-00-00, Servicing or Code 290002
•• Hydraulic System Automatic Bleed Procedure, 29-00-00, Servicing or Code 290003
• Landing Gear Door Operation, 32-00-00, Maintenance Practices
• Landing Gear Cycling - Operational Test, 32-00-00, Adjustment / Test or Code 323906
• Main Landing Gear Door Control Links - Rigging, 32-18-01, Adjustment / Test
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance
Procedure, 20-00-00, Maintenance Practices .
(b) Open main landing gear door. See Landing Gear Door Operation, 32-00-00,
Maintenance Practices.
(c) Pull, tag and install safety clip on the following Circuit Breaker (CB):
CB NAME CB PANEL CB LOCATION
LDG GEAR CONT Pilot FLT CTRL / HYD
WARNING: FAILURE TO ENSURE ALL PERSONNEL AND EQUIPMENT ARE
CLEAR OF FLIGHT CONTROL SURFACES BEFORE OPERATING
FLIGHT CONTROLS MAY RESULT IN SERIOUS INJURY OR DEATH.
(d) Dissipate hydraulic system pressure by cycling ﬂight controls and / or operating brake
pedals several times.
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### Page 2

C. Removal
WARNING: FAILURE TO INSTALL ALL LANDING GEAR AND LANDING GEAR DOOR
SAFETY DEVICES BEFORE WORKING IN ANY WHEEL WELL MAY RESULT IN
SERIOUS INJURY OR DEATH.
MANY OF THE MATERIALS SPECIFIED HAVE SIGNIFICANT OCCUPATIONAL
SAFETY, HEALTH OR ENVIRONMENTAL REQUIREMENTS RELATED TO THEIR
USE. MATERIAL SAFETY DATA SHEETS SHALL BE CONSULTED FOR ALL
MATERIALS TO DETERMINE THE MANUFACTURERS RECOMMENDATIONS
CONCERNING OCCUPATIONAL EXPOSURE PRECAUTIONS. IT IS THE SOLE
RESPONSIBILITY OF THE USER TO ENSURE PROTECTION FROM INJURY OR
EXPOSURE, SAFE APPLICATION OF MATERIALS AND COMPLIANCE WITH
ANY FEDERAL, STATE OR LOCAL REGULATIONS REGARDING THE USE OF
ANY OF THE MATERIALS SPECIFIED.
CAUTION: SKYDROL TYPE IV PHOSPHATE ESTER HYDRAULIC FLUID SHALL DAMAGE
PAINTS, RUBBER AND PLASTIC MATERIALS. FAILURE TO REMOVE RESIDUAL
SKYDROL FROM EXPOSED SURFACES MAY RESULT IN DAMAGE TO AIRCRAFT
OR EQUIPMENT.
NOTE: The following numbers in parenthese s()a r eu s e di nc onjunction with Figure 401.
(1) Remove hydraulic lines (1) from actuator (2).
NOTE: Use suitable container to catch hydraulic ﬂuid when removing hydraulic lines.
(2) Remove cotter pin (3), nut (4), washer (5) washer (6) and bolt (7) from actuator lower mount.
Discard cotter pin.
(3) Remove cotter pin (8), nut (9), washers (10, 11) and bolt (12) from actuator upper mount.
Discard cotter pin.
(4) Remove actuator (2) from aircraft.
(5) Remove bushing (13, 14).
(6) If required, remove elbows (15), unions (16), retaining nuts (17), backup rings (18) and
O-rings (19) from actuator (2). Discard backup rings and O-rings.
(7) Install protective caps and plugs on all open ports and lines.
D. Installation
WARNING: FAILURE TO INSTALL ALL LANDING GEAR AND LANDING GEAR DOOR
SAFETY DEVICES BEFORE WORKING IN ANY WHEEL WELL MAY RESULT IN
SERIOUS INJURY OR DEATH.
NOTE: The following numbers in parenthese s()a r eu s e di nc onjunction with Figure 401.
(1) Remove protective caps and plugs.
(2) If removed, install hydraulic ﬁttings as follows:
(a) Apply a thin coat of lubricant to new O-rings (19).
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing
properly.
(b) Install elbows (15), unions (16), retaining nuts (17), backup rings (18) and O-rings (19)
on actuator (2).
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### Page 3

(3) Position actuator (2) on aircraft.
(4) Install bushings (13, 14).
(5) Install bolt (12), washers (10, 11), nut (9) and cotter pin (8) in actuator (2).
(6) Install bolt (7), washers (5, 6), nut (4) and cotter pin (3) in actuator (2).
(7) Install hydraulic lines (1) on actuator (2).
E. Follow On
(1) Inspect for presence of foreign objects.
(2) Remove safety clip, tag and depress circuit breaker pulled in Step 1.B.(2)(c).
(3) Aircraft 5001 thru Aircraft 5102 not having ASC 86, perform Hydraulic System Bleeding
Procedure, 29-00-00, Servicing or Code 290001 or Hydraulic System Bleed Procedure -
Alternate, 29-00-00, Servicing or Code 290002 .
(4) Aircraft 5001 thru Aircraft 5102 having ASC 86 and Aircraft 5103 and subsequent, perform
Hydraulic System Automatic Bleed Procedure, 29-00-00, Servicing or Code 290003 .
(5) Using auxiliary hydraulic pump, close doors and check for proper door ﬁt and proper position
indication. See Landing Gear Door Operation, 32-00-00, Maintenance Practices .
(6) If door does not ﬁt properly, adjust door closing mechanism. See Main Landing Gear Door
Control Links - Rigging, 32-18-01, Adjustment / Test .
(7) Perform Landing Gear Cycling - Operational Test, 32-00-00, Adjustment / Test or Code
323906.
(8) Record all maintenance actions in accordance with current governing authority.
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### Page 4

Main Landing Gear Door Actuator
Figure 401
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### Page 5

2. Main Gear Door Actuator End Cap Fitting — Removal / Installation
A. General
The end cap ﬁtting is installed on the main gear door actuator which is located in the left and right
main wheel well.
B. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT
Aluminum calibration standard .................... 0.008”, 0.020” and 0.040” EDM notches or equivalent
Eddy current unit ...................................................................... Hocking Phasec 2200 or equivalent
Eddy current probe, straight, 2 mm ........................................ 614-034-001, 200 kHz or equivalent
Eddy current probe, 90°, 2 mm ............................................... 614-074-007, 200 kHz or equivalent
Thread ﬁle ......................................................................................................... -16UN or equivalent
Torque wrench, 10 - 50 inch-pounds (1.13 - 5.65 Nm) ......................... GSE5100720 or equivalent
Vibro-etching tool / metal impression stamp tool ............................................................... Standard
CONSUMABLES
Data plate ................................................................................................................. 1159F 30042-13
Drive screw ................................................................................................................ MS213 18-1 (4)
Epoxy primer ....................................................................................................... 3012 or equival ent
Epoxy topcoat (clear) .......................................................................................... 3020 or equivalent
Epoxy topcoat (white) .......................................................................................... 3013 or equivalent
Felt wiper ........................................................................................................................ MS28932-1
Gland ................................................................................................. 1159HM20140-3 (as required)
Hydraulic ﬂuid ......................................................................................... Skydrol LD-4 or equivalent
Hydraulic data plate ................................................................................................... 1159H20240 -3
Isopropyl alcohol ................................................................................................................. TT-1-735
Lint free cloth .................................................................................................................. .... Standard
Lubricant ........................................................................................................ MCS-352B (see No te)
Masking tape ....................................................................................................................... Standard
O-ring ........................................................................................................................ N AS1611-145A
O-ring ................................................................................................................... NAS1611-115A (3)
O-ring ............................................................................................................................ NAS1612-4A
O-ring ............................................................................................................................ NAS1612-6A
Retainer ................................................................................................................. MS2759 5-145 (2)
Retainer ................................................................................................................... 1159HM20183-3
Safety wire ................................................................................................................ MS209 95NC32
Shuttle valve ....................................................................................................................... See Note
Scraper .......................................................................................................................... MS28776-12
Screw ................................................................................................................. NAS1101E3 H12 (4)
Seal ............................................................................................................................. 7217FT-952-T
Snap ring ....................................................................................................................... NAS669-168
Washer ............................................................................................................. NAS1149D0316H( 4 )
NOTE: When lubricant MCS-352B is not available, Skydrol ﬂuid may be used as an alternate.
Door actuators originally equipped with 1159SCH238-5, -7, -9 or -11 shuttle valves may
reuse shuttle valve. Refer to Aircraft Illustrated Parts Catalog, 32-32-00, Fig. 4, Main
Landing Gear Door Actuator, End Cap/Rod End Fitting Replacement for correct shuttle
valve conﬁgurations.
(1) Reference(s)
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### Page 6

• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices
• Aircraft Tubing and Fitting Assemblies - Standard Practices, 20-70-10, Maintenance
Practices
• Safety Wire - Standard Practices, 20-70-41, Maintenance Practices
• Main Gear Door Actuator - Removal / Installation, 32-32-04, Removal / Installation or
Code 323041
• Main Gear Door Actuator - Bench Check, 32-32-04, Adjustment / Test or Code 323047
• Aircraft Illustrated Parts Catalog, 32-32-00, Fig. 4, Main Landing Gear Door Actuator,
End Cap/Rod End Fitting Replacement
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance
Procedure, 20-00-00, Maintenance Practices .
(b) Remove main landing gear door actuator from aircraft, if not previously removed. See
Main Gear Door Actuator - Removal / Installation, 32-32-04, Removal / Installation or
Code 323041.
C. Removal
NOTE: The following numbers in parenthesi s()a r eu s e di nc o n j u n c t i o nw i t hFigure 402.
(1) If removing serialized end cap, perform the following:
NOTE: A serialized end cap will be identi ﬁed by part number or serial number of the door
actuator by one of the following methods:
• Door actuator part number will be 1159H20264-25 for left or 1159H20264-26
for right
• Door actuator part number will be 1159H20264-7 - 1159H20264-24 and door
actuator serial number will end with a C
• Door actuator part number will be 1159H20264-701 - 1159H20264-2101 and
door actuator serial number will end with a C, 1159SB50074 added an 01 to
part numbers 1159H20264-7 - 1159H20264-21
Serialized end cap should have a part number (1159HM20178-15 for left or -16
for right) and a serial number stamped or etched on end cap. See Figure 403.
(a) Remove drive screws (2) securing door actuator data plate (1) to door actuator end cap
(10). Discard drive screws.
NOTE: Door actuator data plate could be attached to either side of the end cap. Data
plate will have the part number (1159H20264-xx) and serial number of the
door actuator.
(b) Retain door actuator data plate (1) for installation on new end cap.
(2) If removing nonserialized end cap, perform the following:
(a) Locate existing door actuator data plate (1) attached to door actuator end cap (10).
NOTE: Door actuator data plate could be attached to either side of the end cap. Data
plate will have the part number (1159H20264-xx) and serial number of the
door actuator.
(b) Using a vibro-etching or metal impression tool, transfer information (MFG BY, PART
NO., SER NO.) from existing door actuator data plate (1) to a new door actuator data
plate.
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### Page 7

NOTE: Data plate markings should be vibro-etched or metal impression stamped per
SAE AS478 / MIL-STD-130.
( c ) A d daCt oe n do fdoor actuator serial number on new data plate.
(d) Retain new door actuator data plate (1) for installation on new end cap.
(3) Remove safety wire from collar (4).
(4) Loosen collar (4) and remove locking key (5) securing rod end (6).
(5) Remove rod end (6) and collar (4).
NOTE: Retain rod end, collar and locking key.
(6) Loosen setscrew (7).
(7) Remove safety wire from cylinder nut (8).
(8) Loosen cylinder nut (8) until it turns freely.
(9) Remove safety wire from locking screw (9).
(10) Remove locking screw (9).
(11) Remove end cap (10) from door actuator cylinder body (11).
(12) Inspect threads of door actuator cylinder body (11) where end cap (10) was removed.
(13) If required, clean up threads around index hole for locking screw (9) using thread ﬁle.
(14) Remove ﬁlings and debris from threads, piston and door actuator cylinder body interior.
(15) Clean threads with lint free cloth and isopropyl alcohol.
(16) Remove shuttle valve (12) from end cap (10) as follows:
(a) Remove safety wire from screws (13), as required.
(b) Remove screws (13) and washers (14) attaching gland (15) to end cap (10). Discard
hardware.
(c) Remove gland (15) from end cap.
(d) If gland is part number 1159HM20140-1, remove hydraulic elbow (16) and discard
gland (15).
NOTE: The 1159HM20140-1 gland has a thin (0.125 inch) ﬂange, where the
1159HM20140-3 has a thicker (0.375 inch) ﬂange. See Figure 404.
(e) If gland is 1159HM20140-3, perform eddy current inspection as follows:
NOTE: This procedure is intended to provide trained and experienced NDT
inspectors with the necessary information to perform NDT inspection.
1 Calibrate probe on a 0.020 inch notch to achieve a minimum of a four grid
deﬂection:
• Mode: Absolute Display: X:Y Gain: 44.0 dB
• Frequency: 150 kHz Phase: 14.0 degrees X: -13.0 dB
• Lo-Pass: DC Hi-Pass: DC
NOTE: These are sample settings. Settings may be changed due to equipment
or operator preferences.
2 Eddy current gland ﬂange, radius and inner diameter of fastener hole for defects.
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### Page 8

3 Inspect ﬂange around screw hole and radius of gland, paying particular attention
to areas immediately around fastener hole.
4 Any indication not attributed to edge effect or geometry shall be cause for
replacement of gland.
(f) If gland (15) is retained, remove and discard O-ring (17).
(g) Remove shuttle valve (12).
(h) If shuttle valve is a 1159SCH238-1 or -3, discard shuttle valve (12).
NOTE: Part number is engraved on shuttle valve. Shuttle valve part numbers
1159SCH238-5, -7, -9 and -11 can be reused if no wear or damage is visible.
Refer to Aircraft Illustrated Parts Catalog, 32-32-00, Fig. 4, Main Landing
Gear Door Actuator, End Cap/Rod End Fitting Replacement for correct
installation.
(i) If shuttle valve (12) is retained, remove and discard O-rings (18).
(17) Remove elbow (19) from end cap (10). Remove O-ring and discard.
(18) Discard end cap (10).
NOTE: Existing O-ring retainers, O-ring, wiper ring, scraper, scraper retainer and retaining
clip / snap ring can be discard with end cap.
D. Installation
NOTE: The following numbers in parenthesi s()a r eu s e di nc o n j u n c t i o nw i t hF i g u r e402.
Installation of a serialized end cap part number 1159HM20178-15 (left) and -16 (right) is
required for tracking the Chapter 5 discard requirement.
(1) Install new O-rings, retainers, seal, felt wiper, scraper and snap ring in new serialized end cap
(10) as follows:
(a) Apply a thin coat of lubricant to new NAS1611-145A O-ring (20).
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing
properly.
(b) Install MS27595-145 retainer (21), NAS1611-145A O-ring (20) and MS27595-145
retainer (22) in end cap (10).
(c) Soak felt wiper (24) in hydraulic ﬂuid.
(d) Install seal (23), felt wiper (24), scraper (25), 1159HM20183-3 retainer (26) and snap
ring (27) in end cap (10).
(2) Lubricate actuator piston with hydraulic ﬂuid.
(3) Slide end cap (10) over actuator piston.
(4) Thread end cap (10) onto door actuator cylinder body (11) until it bottoms out.
(5) Align end cap (10) with extend inlet (28) on ﬁxed actuator end by backing end cap (10) off up
to one full turn.
(6) Verify that locking screw (9) hole in end cap (10) is aligned with hole in door actuator cylinder
body (11).
NOTE: If locking screw hole is not aligned when end cap is aligned with hydraulic port on
ﬁxed actuator, contact Gulfstream Customer Support for assistance.
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### Page 9

(7) Tighten cylinder nut (8) against end cap (10).
(8) Tighten setscrew (7) in locking cylinder nut (8).
(9) Safety wire cylinder nut (8) to end cap (10).
NOTE: See Safety Wire - Standard Practices, 20-70-41, Maintenance Practices .
(10) Install locking screw (9). Torque to 12 - 15 inch-pounds (1.36 - 1.69 Nm).
(11) Safety wire locking screw (9) to end cap (10).
NOTE: See Safety Wire - Standard Practices, 20-70-41, Maintenance Practices .
(12) Install shuttle valve (12) as follows:
NOTE: Only shuttle valve part numbers 1159SCH238-5, -7, -9 or -11 can be used. Only
gland part number 1159HM20140-3 can be used. Refer to Aircraft Illustrated Parts
Catalog, 32-32-00, Fig. 4, Main Landing Gear Door Actuator, End Cap/Rod End
Fitting Replacement for correct installation.
(a) Apply a thin coat of lubricant to new O-rings (17, 18).
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing
properly.
(b) Install new NAS1611-115A O-ring (17) on gland (15).
(c) Install new NAS1611-115A O-rings (18) on shuttle valve (12).
(d) Install shuttle valve (12) with threaded center hole facing outward towards gland.
(e) Install gland (15) on end cap (10).
(f) Install screws (13) and washers (14) on gland (15).
(g) Torque screws (13) to 20 - 25 inch-pounds (2.26 - 2.82 Nm).
(h) Safety wire screws (13) to each other.
NOTE: See Safety Wire - Standard Practices, 20-70-41, Maintenance Practices .
(13) Install elbow (16) removed in Step 2.C.(16)(d) as follows:
(a) Apply a thin coat of lubricant to new NAS1612-4A O-ring.
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing
properly.
(b) Install NAS1612-4A O-ring on union (16).
(c) Install elbow (16) in gland (15).
NOTE: See Aircraft Tubing and Fitting Assemblies - Standard Practices, 20-70-10,
Maintenance Practices.
(14) Install elbow (19) removed in Step 2.C.(17) as follows:
(a) Apply a thin coat of lubricant to new O-ring NAS1612-6A.
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing
properly.
(b) Install NAS1612-6A O-ring on union or elbow (19).
(c) Install elbow (19) in end cap (10).
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### Page 10

NOTE: See Aircraft Tubing and Fitting Assemblies - Standard Practices, 20-70-10,
Maintenance Practices.
(15) Ensure actuator piston is fully retracted (bottomed out) in door actuator cylinder body (11).
(16) Install locking key (5) and collar (4) onto rod end (6).
(17) Thread rod end (6) into actuator piston.
(18) With piston bottomed out in actuator adjust rod end (6) to achieve dimension shown in Figure
405.
(19) Tighten collar (4) against piston.
(20) Safety wire collar (4) to locking key (5).
NOTE: See Safety Wire - Standard Practices, 20-70-41, Maintenance Practices .
(21) Apply epoxy primer and topcoat to all bare areas as follows:
NOTE: Avoid applying primer or topcoat to ports, rod end bearing, part number stamp or
exposed piston surfaces.
(a) Tape off around bare areas.
(b) Apply one coat of epoxy primer to all bare areas.
NOTE: Allow sufficient time for epoxy primer to cure.
(c) Apply one coat of white epoxy topcoat to all areas epoxy primer was applied.
NOTE: Allow sufficient time for white epoxy topcoat to cure.
(d) Remove all masking tape.
(22) Install door actuator data plates as follows:
(a) Install door actuator data plate (1) retained from Step 2.C.(1)(b) or Step 2.C.(2)(d) with
screws (2).
(b) Install new hydraulic warning data plate (3) with screws (2).
(c) Overcoat data plate (1) and hydraulic warning data plate (3) with clear epoxy topcoat.
NOTE: Allow sufficient time for epoxy to cure.
E. Follow On
(1) Inspect for presence of foreign objects.
(2) Perform Main Gear Door Actuator - Bench Check, 32-32-04, Adjustment / Test or Code
323047.
(3) Install main landing gear door actuator. See Main Gear Door Actuator - Removal / Installation,
32-32-04, Removal / Installation or Code 323041 .
(4) Record all maintenance actions in accordance with current governing authority.
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### Page 11

28
7
2
3
6
9
11
8
2
1
4 5
DETAIL A
TIL-027719G
10
Main Landing Gear Door Actuator End Cap
Figure 402 (Sheet 1 of 2)
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### Page 12

TIL-027720G
20
DETAIL B
DETAIL C
21
22
23
24
25
26 27
18
18
14
13
15
17
19
16
12
Main Landing Gear Door Actuator End Cap
Figure 402 (Sheet 2 of 2)
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### Page 13

TIL-027721G
Serialized Door Actuator End Cap
Figure 403
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TIL-027722G
1159HM20140-1
1159HM20140-3
0.125 INCHES
0.375 INCHES
Main Landing Gear Door Actuator End Cap Gland
Figure 404
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### Page 15

TIL-027723G
13.006 INCHES
13.056 INCHES
Door Actuator Rod End Adjustment
Figure 405
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### Page 16

3. Main Gear Door Actuator End Cap Fitting — Discard
A. General
The end cap ﬁtting is installed on the main gear door actuator which is located in the left and right
main wheel well.
Gulfstream recommends a review of the Main Gear Door Actuator - Bench Check, 32-32-04,
Adjustment / Test or Code 323047 procedure, which is a required follow on procedure to the Main
Gear Door Actuator End Cap Fitting - Removal / Installation, 32-32-04, Removal / Installation or
Code 323043, to ensure proper test equipment is available before proceeding.
For main gear door actuator end cap ﬁttings that are not serialized, the end cap ﬁtting must be
tracked by the main gear door actuator part number and serial number until end cap is replaced with
a serialized end cap.
B. Preparation
(1) References
• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices
• Main Gear Door Actuator - Removal / Installation, 32-32-04, Removal / Installation or
Code 323041
• Main Gear Door Actuator End Cap Fitting - Removal / Installation, 32-32-04, Removal /
Installation or Code 323043
• Main Gear Door Actuator - Bench Check, 32-32-04, Adjustment / Test or Code 323047
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance
Procedure, 20-00-00, Maintenance Practices .
(b) Remove main gear door actuator. See Main Gear Door Actuator - Removal /
Installation, 32-32-04, Removal / Installation or Code 323041 .
C. Procedure
(1) Remove end cap from main gear door actuator. See Main Gear Door Actuator End Cap Fitting
- Removal / Installation, 32-32-04, Removal / Installation or Code 323043 .
(2) Discard main gear door actuator end cap.
(3) Install a serialized end cap part number 1159HM20178-15 (left) or -16 (right) on main gear
door actuator. See Main Gear Door Actuator End Cap Fitting - Removal / Installation,
32-32-04, Removal / Installation or Code 323043 .
NOTE: Installation of a serialized end cap part number 1159HM20178-15 (left) and -16
(right) is required for tracking the Chapter 5 discard requirement.
D. Follow On
(1) Inspect for presence of foreign objects.
(2) Install main gear door actuator. See Main Gear Door Actuator - Removal / Installation,
32-32-04, Removal / Installation or Code 323041 .
(3) Record all maintenance actions in accordance with current governing authority.
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TEMPORARY REVISION 32-1

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