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LANDING GEAR DOOR ACTUATORS — REMOVAL / INSTALLATION
1. Main Gear Door Actuator Assembly — Removal / Installation A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT Protective caps and plugs .................................................................................................. Standar d Skydrol resistant container ................................................................................................. Stand ard Torque wrench, 40 - 200 inch-pounds (4.52 - 22.60 Nm) ..................... GSE5100721 or equivalent
CONSUMABLES
Bushing1159LM20296-19
Bushing1159LM20296-21
Cotter pin ............................................................................................................... MS24665 -285 (2)
LubricantMCS-352B
O-ringNAS1612-4A
O-ring ...................................................................................................................... NAS 1612-6A (2) NOTE: When lubricant MCS-352B is not available, Skydrol fluid may be used as an alternate.
(1) Reference(s)
• Combined / Flight Hydraulic System Reservoir - Filling Procedures, 29-01-00, Servicing or Code 291057
• Landing Gear Cycling - Operational Check, 32-00-00, Adjustment / Test or Code 323002
• Cleaning Skydrol from Landing Gear, 32-00-00, Cleaning / Painting
• Main Gear Door Actuator - Adjustment, 32-03-04, Adjustment / Test
• Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator
(2) Aircraft Preparation WARNING: FAILURE TO DISSIPATE HYDRAULIC PRESSURE BEFORE INSTALLING
OR REMOVING ALL LANDING GEAR AND LANDING GEAR DOOR
SAFETY DEVICES SHALL CAUSE DAMAGE TO AIRCRAFT OR MAY RESULT IN SERIOUS INJURY OR DEATH.
FAILURE TO ENSURE ALL PERSONNEL AND EQUIPMENT ARE CLEAR
OF FLIGHT CONTROL SURFACES BEFORE OPERATING FLIGHT CONTROLS MAY RESULT IN SERIOUS INJURY OR DEATH.
(a) Prepare aircraft for safe ground maintenance.
(b) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake pedals several times.
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.
(c) Install all landing gear and landing gear door safety devices.
MAINTENANCE MANUAL 32-03-04 Page 401 April 29/16 TEMPORARY REVISION 32-2
B. Removal WARNING: 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.
FAILURE TO INSTALL PROPER PROTECTIVE CAPS AND PLUGS ON
ELECTRICAL CONNECTORS, LINES, TUBES, PORTS AND FITTINGS MAY RESULT IN DAMAGE TO EQUIPMENT.
(1) Remove hydraulic lines from main landing gear door actuator.
NOTE: Use suitable container to catch hydraulic fluid when removing hydraulic lines.
(2) Remove cotter pin, nut, washers, bolt and bushings securing actuator lower mount to aircraft structure. Discard cotter pin.
(3) Remove cotter pin, nut, washers, bolt and bushings securing actuator arm to door control linkage. Discard cotter pin.
(4) Remove actuator from aircraft.
(5) If actuator is to be replaced, perform the following:
(a) Remove unions from actuator.
(b) If installed, remove elbow from left actuator retract inlet on end cap.
NOTE: The earlier dash number left door actuators may have an elbow installed in the retract inlet on end cap, refer to Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator for correct installation.
(c) Remove O-rings and discard.
(6) Install protective caps and plugs on all open lines and ports.
MAINTENANCE MANUAL 32-03-04 Page 402 April 29/16 TEMPORARY REVISION 32-2
C. 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.
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.
(1) Remove protective caps and plugs from lines an ports.
(2) If a new actuator is being installed, perform the following:
(a) Apply a thin coat of lubricant to new O-rings.
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing properly.
(b) Install O-ring NAS1612-4A on No. 4 union.
(c) Install No. 4 union in emergency inlet on end cap gland.
(d) Torque No. 4 union to 105 - 115 inch-pounds (11.86 - 12.99 Nm).
(e) Install O-rings NAS1612-6A on unions and / or elbow.
NOTE: The earlier dash number left door actuators may have an elbow installed in the retract inlet on end cap, refer to Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator for correct installation.
(f) Install No. 6 elbow in retract inlet on end cap, left actuator as required.
(g) Install No. 6 union in retract inlet on end cap, as required.
(h) Install No. 6 union in extend inlet on fixed end of actuator.
(i) Torque No. 6 unions to 160 - 180 inch-pounds (18.08 - 20.33 Nm).
(3) Position actuator on aircraft.
(4) Secure actuator lower mount to aircraft structure with bushings, bolt, washers and nut removed in Step 1.B.(2).
(5) Secure nut with cotter pin.
(6) Secure actuator arm to door control linkage with bushings, bolt, washers and nut removed in Step 1.B.(3).
(7) Secure nut with cotter pin.
(8) Install hydraulic lines on actuator.
D. Follow On
(1) Inspect for presence of foreign objects.
(2) Check for proper door fit and proper position indication. If door does not fit properly, adjust
MAINTENANCE MANUAL 32-03-04 Page 403 April 29/16 TEMPORARY REVISION 32-2
door closing mechanism. See Main Gear Door Actuator - Adjustment, 32-03-04, Adjustment / Test.
(3) Perform Combined / Flight Hydraulic System Reservoir - Filling Procedures, 29-01-00, Servicing or Code 291057 , as required.
(4) Perform Landing Gear Cycling - Operational Check, 32-00-00, Adjustment / Test or Code 323002.
(5) Inspect actuator installation for hydraulic leaks.
(6) Clean any spilled hydraulic fluid from landing gear. See Cleaning Skydrol from Landing Gear, 32-00-00, Cleaning / Painting .
(7) Close main landing gear doors, as required.
(8) Record all maintenance actions in accordance with current governing authority.
MAINTENANCE MANUAL 32-03-04 Page 404 April 29/16 TEMPORARY REVISION 32-2
PIN 11/32 -1/32"+1/64"
CRANK (POSITION WITH DOOR ACTUATOR FULLY EXTENDED.
DOORS CLOSED
POSITION OF CRANK WHEN
DOOR IS IN THE FULL OPEN POSITION.
(ACTUATOR RETRACTED) PIN REF
INSPECTION HOLE LINK
TRUNNION ASSY
ROD END KBNE - 7
GAGE PIN ARM ASSY 03968C01 Main Gear Door Actuator Adjustment Figure 401
MAINTENANCE MANUAL 32-03-04 Page 405 April 29/16 TEMPORARY REVISION 32-2
2. Nose Gear Door Actuator Assembly — Removal / Installation A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT Protective caps and plugs .................................................................................................. Standar d Skydrol resistant container ................................................................................................. Stand ard
CONSUMABLES Backup ring ............................................................................................................. MS28773- 04 (2) Cotter pin ............................................................................................................... MS24665 -152 (2) Corrosion inhibiting compound ............................................................................................. Type VI Lubrication ..................................................................................................... MCS-352B (see Not e) O-ring .................................................................................................................... NAS16 12-4(A) (3) NOTE: When lubricant MCS-352B is not available, Skydrol fluid may be used as an alternate.
(1) Reference(s)
• Nose Gear Door Actuator and Door Rod - Adjustments, 32-03-04, Adjustment / Test
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance.
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.
FAILURE TO DISSIPATE HYDRAULIC PRESSURE BEFORE
INSTALLING OR REMOVING ALL LANDING GEAR AND LANDING
GEAR DOOR SAFETY DEVICES SHALL CAUSE DAMAGE TO AIRCRAFT OR MAY RESULT IN SERIOUS INJURY OR DEATH.
FAILURE TO ENSURE ALL PERSONNEL AND EQUIPMENT ARE
CLEAR OF FLIGHT CONTROL SURFACES BEFORE OPERATING FLIGHT CONTROLS MAY RESULT IN SERIOUS INJURY OR DEATH.
(b) Ensure landing gear doors are open.
(c) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake pedals several times.
(d) Install all landing gear and landing gear door safety devices.
B. Removal
(1) Remove hydraulic lines from nose gear door actuator.
NOTE: Use suitable container to catch hydraulic fluid when removing hydraulic lines.
(2) Install protective caps and plugs on all open ports and lines.
(3) Remove cotter pin, nut, washers, bolt and spacer securing fixed end of actuator to aircraft structure. Discard cotter pin.
(4) Remove cotter pin, nut, washers and bolt securing actuator rod end. Discard cotter pin.
(5) Remove door actuator.
(6) If actuator is to be replaced, remove and retain hydraulic fittings and restrictor from actuator.
Note position of fittings for installation. Discard O-rings.
MAINTENANCE MANUAL 32-03-04 Page 406 April 29/16 TEMPORARY REVISION 32-2
C. 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.
(1) If a new actuator is being installed, perform the following:
(a) Apply a thin coat of lubricant to new O-rings.
NOTE: A buildup of lubricant in the O-ring glands may prevent the O-ring from sealing properly.
(b) Install O-rings on hydraulic fittings retained in Step 2.B.(6).
(c) Install hydraulic fittings in actuator.
(2) Position actuator on aircraft.
(3) Coat actuator mounting hardware with a thin coat of corrosion inhibiting compound before installation.
(4) Secure fixed end of actuator with bolt, washers, spacer and nut removed in Step 2.B.(3).
(5) Tighten nut and secure with cotter pin.
(6) Secure actuator rod end with bolt, washers and nut removed in Step 2.B.(4). Do not tighten nut or install cotter pin at this time.
D. Follow On
(1) Perform Nose Gear Door Actuator and Door Rod - Adjustments, 32-03-04, Adjustment / Test.
(2) Tighten nut on actuator rod end and install cotter pin.
(3) Remove protective caps and plugs from hydraulic lines.
(4) Install hydraulic lines removed in Step 2.B.(1).
(5) Cycle doors using grounds service valve to verify operation.
(6) Inspect actuator installation for hydraulic leaks.
(7) Inspect for presence of foreign objects.
(8) Record all maintenance actions in accordance with current governing authority.
3. 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 toolStandard
MAINTENANCE MANUAL 32-03-04 Page 407 April 29/16 TEMPORARY REVISION 32-2
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 wiperMS28932-1
Gland ................................................................................................. 1159HM20140-3 (as required) Hydraulic fluid ......................................................................................... Skydrol LD-4 or equivalent Hydraulic data plate ................................................................................................... 1159H20240 -3
Isopropyl alcoholTT-1-735
Lint free clothStandard
Lubricant ........................................................................................................ MCS-352B (see No te)
Masking tapeStandard
O-ring ........................................................................................................................ N AS1611-145A O-ring ................................................................................................................... NAS1611-115A (3)
O-ringNAS1612-4A
O-ringNAS1612-6A
Retainer ................................................................................................................. MS2759 5-145 (2)
Retainer1159HM20183-3
Safety wire ................................................................................................................ MS209 95NC32 Shuttle valve ....................................................................................................................... See Note
ScraperMS28776-12
Screw ................................................................................................................. NAS1101E3 H12 (4)
Seal7217FT-952-T
Snap ringNAS669-168
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, 32-30-00, Fig. 3, Main Landing Gear Door Actuator, End Cap/Rod End Fitting Replacement for correct shuttle valve configurations.
(1) Reference(s)
• 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 Assembly - Removal / Installation, 32-03-04, Removal / Installation or Code 323037
• Main Gear Door Actuator - Bench Check, 32-03-04, Adjustment / Test or Code 323097
• Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator
• Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 3, Main Landing Gear Door Actuator, End Cap/Rod End Fitting Replacement
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance.
(b) Remove main landing gear door actuator from aircraft, if not previously removed. See Main Gear Door Actuator Assembly - Removal / Installation, 32-03-04, Removal / Installation or Code 323037 .
MAINTENANCE MANUAL 32-03-04 Page 408 April 29/16 TEMPORARY REVISION 32-2
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 hF i g u r e402.
(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.
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).
MAINTENANCE MANUAL 32-03-04 Page 409 April 29/16 TEMPORARY REVISION 32-2
(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 union (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.
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, 32-30-00, Fig. 3, 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).
MAINTENANCE MANUAL 32-03-04 Page 410 April 29/16 TEMPORARY REVISION 32-2
(17) Remove union (19) or elbow from end cap (10). Remove O-ring and discard.
NOTE: The earlier dash number left door actuators may have an elbow installed on the end cap, refer to Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator for correct installation.
(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.
(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:
MAINTENANCE MANUAL 32-03-04 Page 411 April 29/16 TEMPORARY REVISION 32-2
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, 32-30-00, Fig. 3, 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 union (16) removed in Step 3.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 union (16) in gland (15).
(d) Torque union (16) to 105 - 115 inch-pounds (11.86 - 12.99 Nm).
NOTE: See Aircraft Tubing and Fitting Assemblies - Standard Practices, 20-70-10, Maintenance Practices.
(14) Install union or elbow (19) removed in Step 3.C.(17) as follows:
NOTE: The earlier dash number left door actuators may have an elbow installed on the end cap, refer to Aircraft Illustrated Parts Catalog, 32-30-00, Fig. 2, Main Landing Gear Door Actuator for correct installation.
(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 in end cap (10) on left actuator, as required.
(d) Install union (19) in end cap (10), as required.
(e) If installing union (19) torque to 160 - 180 inch-pounds (18.08 - 20.33 Nm).
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).
MAINTENANCE MANUAL 32-03-04 Page 412 April 29/16 TEMPORARY REVISION 32-2