# Gulfstream Temporary Revision 27-3: No revision named

- Rights: © Gulfstream Aerospace Corporation. Filed by the FAA in regulations.gov docket FAA-2016-9437; AD 2017-13-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Gulfstream Temporary Revision 27-3](https://openairdocs.org/service-documents/gulfstream/tr-27-3.md)
- Title as filed: G400 TR 27-3 for MM 27-70-00
- Pages: 16
- PDF: https://openairdocs.org/files/sha256/8d/16/8d16ebfc07add395aa69670019d17388114c57d6cb525e21d44bd4e6049a5e8d
- Page: https://openairdocs.org/service-documents/gulfstream/tr-27-3/file/8d16ebfc07ad

## Text

Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

GUST LOCK — ADJUSTMENT / TEST
1. Gust Lock System — Rigging Procedure
A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT
Cable tensiometer, 10 - 200 pounds ..................................................... GSE2700321 or equivalent
Flight controls rig pin kit ......................................................................... GSE2700924 or equivalent
Cable block ............................................................................................ GSE2701039 or equivalent
Cable block and chain ....................................................................................... 50082 or equivalent
(1) Reference(s)
• Supplemental Heating - Removal / Installation, 25-27-00, Removal / Installation or
Code 252011
• Floorboard Clip Nut - Check, 53-00-00, Inspection / Check or Code 532016
CAUTION: FLIGHT CONTROL RIGGING IS PROHIBITED WHEN WIND SPEED IS
GREATER THAN 10 MILES PER HOUR.
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance.
(b) Place gust lock handle in unlocked (down) position.
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.
CAUTION: DO NOT RIG GUST LOCK SYSTEM WITH AIRCRAFT FLIGHT
CONTROL HYDRAULIC SYSTEMS PRESSURIZED OR WITH ANY
RESIDUAL PRESSURE IN THE SYSTEM.
(c) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake
pedals several times.
(d) Remove interior furnishings and carpeting as required to gain access to floorboards
being removed.
(e) Remove floor heater mats, if installed. See Supplemental Heating - Removal /
Installation, 25-27-00, Removal / Installation or Code 252011 .
(f) Remove floorboards FLR-33 and FLR-37. See Figure 501.
(g) Gain access to tail compartment.
B. Bungee Rigging
CAUTION: DO NOT RIG GUST LOCK SYSTEM WITH AIRCRAFT FLIGHT CONTROL
HYDRAULIC SYSTEMS PRESSURIZED OR WITH ANY RESIDUAL PRESSURE IN
THE SYSTEM.
NOTE: If gust lock cable system has had maintenance accomplished, perform Step 1.B1.(1) prior
to this task.
The following numbers in parenthese s()a r eu s e di nc o njunction with Figure 502.
(1) Place gust lock lever in locked (up) position.
(2) Lengthen aileron gust lock bungee assembly (9) so that gust lock latch hook fully engages
aileron gust lock bushing without compressing bungee.
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### Page 2

NOTE: Do not overtorque bolts when installing bungee. Joints should be free to rotate.
(3) Lengthen bungee three turns and install between sector assembly and latch assembly.
(4) Tighten bungee jam nut and safety, as required.
(5) Lengthen elevator gust lock bungee assembly (11) so that elevator gust lock latch hook fully
engages elevator gust lock bushing without compressing bungee.
(6) Tighten bungee jam nut and safety, as required.
(7) Lengthen bungee three turns.
(8) Install bungee between torque tube and latch assembly.
(9) Lengthen rudder gust lock bungee assembly (10) so that rudder gust lock latch hook fully
engages rudder gust lock bushing without compressing bungee.
(10) Lengthen bungee three turns and install between torque tube assemblies.
(11) Tighten bungee jam nut and safety, as required.
(12) Go to Step 1.C.(1).
B1. Cable Tension Rigging
NOTE: The following numbers in parenthese s()a r eu s e di nc onjunction with Figure 502.
(1) Place gust lock lever in locked (up) position.
(2) Insert rig pin No. 2 in sector at forward end of pedestal.
NOTE: For cable tensions at temperatures other than 70°F, see Table 501.
(3) Insert rig pins, 1/4 inch diameter at sector for aileron bungee assembly (9) and crank for
elevator bungee (11).
(4) Tension gust lock 3/32 cable assembly 30 ±5 pounds at 70°F (forward inboard cable or right
hand cable).
NOTE: Turnbuckle for forward outboard cable assembly is located under FLR-33 at FS 257.
(5) Tension gust lock 3/32 cable assembly 45 ±5 pounds at 70°F (aft inboard cable or right hand
cable).
NOTE: Turnbuckle for aft outboard cable assembly is located at FS 750 in tail compartment.
(6) Tension gust lock 3/32 cable assembly 65 ±5 pounds at 70°F (outboard cable or left hand
cable).
NOTE: Turnbuckle for inboard cable assembly is located at FS 740.
(7) Rig pins installed in Step 1.B1.(3) should be easily removed after cables are tensioned.
(8) Remove all rigging pins and check system for freedom of motion.
(9) Double check for locking action of latches versus gust lock handle motion (i.e., handle aft and
locked - latches locked).
NOTE: With gust lock system engaged, control surfaces should have the following
approximate positions:
• Elevators: 13 ±1° down
• Rudder: Preset ±3°
• Ailerons: 0 ±1.5°
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### Page 3

(10) With gust lock system engaged, a small amount of movement can be made by hand at all
control surfaces. Also, controls in cockpit can be moved a small amount with a spongy feeling
in lateral control wheel.
C. Follow On
(1) Inspect for presence of any fluid accumulations.
(2) Aircraft with floorboard clip nuts installed, perform Floorboard Clip Nut - Check, 53-00-00,
Inspection / Check or Code 532016 .
(3) Inspect for presence of foreign objects.
(4) Install floorboards removed in Step 1.A.(2)(f).
(5) Install floor heater mats removed in Step 1.A.(2)(e).S e eSupplemental Heating - Removal /
Installation, 25-27-00, Removal / Installation or Code 252011 .
(6) Install carpeting and interior furnishings removed in Step 1.A.(2)(d).
(7) Record all maintenance actions in accordance with current governing authority.
Table 501: Secondary Control System Cable Tensions
CABLE TENSION VS AIRCRAFT STEADY STATE TEMPERATURE -
3/32 INCH DIAMETER CABLE
Temperature(1)
Pretension 30
Pounds at 70°F
Pretension 45
Pounds at 70°F
Pretension 65
Pounds at 70°F
30°F 22 35 54
35°F 23 36 55
40°F 24 37 57
45°F 25 39 59
50°F 26 40 60
55°F 27 42 62
60°F 28 43 63
65°F 29 44 64
70°F 30 45 65
75°F 31 47 67
80°F 32 48 69
85°F 34 49 70
90°F 35 50 71
95°F 36 52 72
100°F 37 53 73
105°F 38 54 74
110°F 40 55 76
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### Page 4

CABLE TENSION VS AIRCRAFT STEADY STATE TEMPERATURE -
3/32 INCH DIAMETER CABLE
Temperature(1)
Pretension 30
Pounds at 70°F
Pretension 45
Pounds at 70°F
Pretension 65
Pounds at 70°F
115°F 41 57 78
120°F 42 58 79
125°F 43 60 80
130°F 44 61 81
(1) The aircraft structural temperature may be assumed to be the same as the local ambient air
temperature, provided that the aircraft has been in that ambient air environment for at least 1 hour and
provided that the direct solar effects are minimal (i.e., aircraft not parked in direct sunlight).
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### Page 5

80324C00
FLR-17 FLR-20 FLR-22 FLR-26 FLR-30
FLR-25
FLR-24
FLR-15 FLR-21 FLR-23 FLR-27
FLR-28
FLR-29
FLR-34
FLR-33
FLR-32
FLR-31
FLR-38
FLR-37
FLR-36
FLR-35
FLR-16
FLR-18 FS 133
FS 169
FS 181
FS 193
FS 193B
FS 193E
FS 235.5
FS 257
FS 287
FLR-19
AIRCRAFT 1000 THRU AIRCRAFT 1447
Cockpit / Forward Cabin Access
Figure 501 (Sheet 1 of 2)
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### Page 6

80314C00
FLR-17 FLR-20 FLR-22 FLR-26 FLR-30
FLR-25
FLR-24
FLR-15
FLR-21 FLR-23 FLR-27
FLR-28
FLR-29
FLR-34
FLR-33
FLR-32
FLR-31
FLR-38
FLR-37
FLR-36
FLR-35
FLR-16
FLR-18 FS 133
FS 169
FS 181
FS 193
FS 193B
FS 193E
FS 235.5
FS 257
FS 287
AIRCRAFT 1448 AND SUBSEQUENT
FLR-15A
FLR-19FLR-16A
FLR-19BFLR-19A
Cockpit / Forward Cabin Access
Figure 501 (Sheet 2 of 2)
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### Page 7

TIL-026969C
DETAIL C
SEE
DETAIL B
SEE
DETAIL A
SEE
DETAIL A
DETAIL B
DETAIL C
REVERSE THRUST LEVERS
POWER LEVERS
FUEL COCK LEVERS
COCKPIT FLOOR
RIG POINT NO. 2
RIG POINT NO. 3
RODS
CONTROL
RIG POINT NO. 1
LOWER SECTORS
133
FS
DETAIL D
SEE
LH SIDE
VIEW LOOKING FWD
UNLOCK
779.700
FS 13.00
LBL
CL
APL
10
WL 106.875
WL 101.734
12
11
1.625
RBL
HOLE
RIG PIN
SEE DETAIL E
RH SIDE
VIEW LOOKING DOWN
285.437
FS
21.937
BL
4.00
BL
9
HOLE
RIG PIN
Gust Lock System - Rigging
Figure 502 (Sheet 1 of 2)
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### Page 8

UNLOCK
DETAIL E
775.025
FS
790.812
FS
793.750
FS
RH SIDE
LOOKING FWD
113.339
WL
101.734
WL
8.560
RBL
1.625
RBL
REF
10
FWD
TIL-30671CB
DETAIL D
187.203
FS
Gust Lock System - Rigging
Figure 502 (Sheet 2 of 2)
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### Page 9

2. Gust Lock System — Operational Test
A. Procedure
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.
CAUTION: DO NOT TEST GUST LOCK WITH AIRCRAFT FLIGHT CONTROL HYDRAULIC
SYSTEMS PRESSURIZED OR WITH ANY RESIDUAL PRESSURE IN THE
SYSTEM.
(1) Ensure all power levers are aft and all controls are in neutral.
(2) Verify that gust lock lever will return from locked position to unlocked position smoothly.
(3) Advance throttles to maximum power.
(4) Move gust lock lever aft to engage gust lock and verify both throttles move toward idle.
(5) Verify that all control surfaces are locked by manually attempting to move the rudder surface
right and left, aileron surfaces up and down and elevator surfaces upward.
NOTE: The aileron surfaces will have approximately ±0.75 inches of spongy freeplay with
the gust lock engaged. This is because the gust lock latch is upstream of the aileron
actuators. Although the rudder surface gust lock may be engaged and holding the
rudder surface fixed, it will still be possible to move the rudder pedals several inches
under force against the rudder arti ficial-feel bungee. This is normal behavior and is
due to the clearance between the input and output sectors at the rudder actuator.
(6) Move gust lock lever forward to disengage gust lock.
(7) Operate aileron, rudder and elevators. They should move freely through their full range.
B. Follow On
(1) Inspect for presence of foreign objects.
(2) Record all maintenance actions in accordance with current governing authority.
3. Rudder Gust Lock Hook — Adjustment / Test
A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT
Shim stock .................................................................................................................. 1159CM20556
Flight controls rig pin kit ......................................................................... GSE2700924 or equivalent
Washers ........................................................................................................................ AN960-516L
Torque wrench, 20 - 1000 inch-pounds (22.60 - 112.98 Nm) ............... GSE5100722 or equivalent
Safety wire ................................................................................................................... MS 20995C32
CONSUMABLES
Cotter pin .................................................................................................................... MS 24665-151
Shim stock ............................................................................................................. 1159CM205 56-11
(1) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance.
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### Page 10

B. Procedure
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.
CAUTION: FLIGHT CONTROL RIGGING IS PROHIBITED WHEN WIND SPEED IS GREATER
THAN 10 MILES PER HOUR.
DO NOT RIG GUST LOCK SYSTEM WITH AIRCRAFT FLIGHT CONTROL
HYDRAULIC SYSTEMS PRESSURIZED OR WITH ANY RESIDUAL PRESSURE IN
THE SYSTEM.
NOTE: The following numbers in parenthese s()a r eu s e di nc onjunction with Figure 503.
(1) Position rudder pedals in midrange by use of adjustment handle.
NOTE: Midrange should be fifth slot from either end of adjustment handle.
(2) Position arrow indicator on RUDDER TRIM wheel to zero.
NOTE: For the purpose of this procedure, there are 20 units on the RUDDER TRIM wheel
dial. Turning the wheel full left from zero to 10 is 10 equal units. Turning the wheel
full right from zero to 10 is 10 equal units.
(3) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake pedals
several times.
(4) Insert rig pin in neutral pin hole in rudder sector. See Figure 504.
(5) Apply hydraulic power to aircraft.
(6) Place gust lock lever in locked (up) position.
(7) Remove rig pin inserted in Step 3.B.(4).
CAUTION: DO NOT MOVE RUDDER PEDALS TO SET RUDDER GUST LOCK HOOK.
(8) Visually inspect / adjust relationship of rudder gust lock hook to roller as follows:
(a) If rudder gust lock bushing fully engages rudder gust lock hook, go to Step 3.B.(14).
(b) If rudder gust lock bushing is below rudder gust lock hook engagement slot, rotate
RUDDER TRIM wheel clockwise slowly until bushing is fully engaged.
(c) If rudder gust lock bushing is above rudder gust lock hook engagement slot, rotate
RUDDER TRIM wheel counterclockwise slowly until bushing is fully engaged.
NOTE: Rudder trim wheel position arrow indicator tolerance is ±0.25 units from zero
with gust lock lever in locked (up) position.
(d) Using RUDDER TRIM wheel units, determine amount of rudder trim required to have
rudder gust lock hook fully engage rudder gust lock bushing.
(e) Record measurement from Step 3.B.(8)(d) _________________. If rudder trim wheel
arrow indication is greater than ±0.25 units adjust rudder gust lock hook shim stack as
required.
(9) Place gust lock lever in unlocked (down) position.
(10) Position arrow indicator on RUDDER TRIM wheel to zero.
(11) Remove hydraulic power from aircraft.
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### Page 11

(12) Adjust shim stock to gust lock hook pedestal assembly (1) as follows:
(a) Using measurement recorded in Step 3.B.(8)(e), determine how much shim stock (9) to
add or remove for rudder gust lock hook (2) to freely engage bushings at bellcrank.
NOTE: One unit of RUDDER TRIM wheel is equal to approximately 0.060 inches of
shim.
(b) Remove cotter pin (3), washer (4) and pin (5). Discard cotter pin (3).
(c) Remove safety wire from bolt (6) and discard.
(d) Remove bolt (6) and beveled washer (7) under bolt head. Retain stack of washers (8)
under beveled washer (7) for installation.
(e) Add or remove shim stock (9) determined in Step 3.B.(12)(a).
(f) Adjust washers (8), under bolt (6) head and beveled washer (7) to achieve 0.60 ±0.03
inches from underside of bolt (6) head to top of rudder gust lock hook pedestal
assembly (1).
(g) Install shim stock (9) between gust lock hook pedestal assembly (1) and gust lock hook
(2).
(h) Install bolt (6) and beveled washer (7) under bolt (6) head and stack of washers (8).
(i) Tighten bolt (6) and verify measurement as follows:
1 If measurement is not 0.60 ±0.03 inches from underside of bolt (6) head to top of
rudder gust lock hook pedestal assembly (1), adjust as required with washers (8)
and repeat Step 3.B.(4) thru Step 3.B.(11) and verify RUDDER TRIM wheel
indication is within limits.
2 If measurement is 0.60 ±0.03 inches from underside of bolt (6) head to top of
rudder gust lock hook pedestal assembly (1), go to Step 3.B.(12)(j).
(j) Torque bolt (6) to 240 - 280 inch-pounds (27.12 - 31.64 Nm).
(13) Safety wire bolt (6) to rudder hook pedestal.
(14) Remove rig pin installed in Step 3.B.(4).
(15) Check for locking action of rudder gust lock hook versus gust lock handle motion.
NOTE: With gust lock system engaged, control surfaces should have the following
approximate positions:
• Elevators: 13 ±1° down
• Rudder: 0 ±3.0°
• Ailerons: 0 ±1.5°
C. Follow On
(1) Inspect for presence of foreign objects.
(2) Record all maintenance actions in accordance with current governing authority.
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### Page 12

TIL-027468K
SEE DETAIL A
DETAIL A
6
7
5
3
4
2
8 9
1
Gust Lock Rudder Hook
Figure 503
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### Page 13

82118C00
RUDDER DRIVE
PUSHROD
RUDDER
TORQUE
TUBE
OUTPUT
CRANK
NEUTRAL
PIN HOLE
RUDDER
DRIVE
HORN
TRIM INPUT
CRANK
ARTIFICIAL
FEEL BUNGEE
SERVO
INPUT
INPUT
CABLE
SECTOR
RUDDER
HYDRAULIC
ACTUATOR
Rudder Sector
Figure 504
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### Page 14

4. Throttle Lever Gust Lock Protection — Functional Test
NOTE: This procedure applies to Aircraft having ASC 501.
A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT
Quadrant position protractor .................................................................. GSE7600499 or equivalent
(1) Reference(s)
• Throttle Lever Gust Lock Protection - Fault Isolation, 27-70-00, Fault Isolation
• Position Protractor - Removal / Installation, 31-01-00, Removal / Installation
(2) Aircraft Preparation
(a) Prepare aircraft for safe ground maintenance.
(b) Verify electrical power is removed from aircraft.
(c) Verify hydraulic power is removed from aircraft.
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.
(d) Dissipate hydraulic system pressure by cycling flight controls and / or operating brake
pedals several times.
(e) Install quadrant position protracter. See Position Protractor - Removal / Installation,
31-01-00, Removal / Installation .
B. Procedure
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.
CAUTION: DO NOT TEST GUST LOCK WITH AIRCRAFT FLIGHT CONTROL HYDRAULIC
SYSTEMS PRESSURIZED OR WITH ANY RESIDUAL PRESSURE IN SYSTEM.
(1) Ensure all power levers are aft and all controls are in neutral.
(2) Place gust lock lever in locked (up) position.
(3) Verify gust lock lever will return from locked (up) position to unlocked (down) position
smoothly.
(4) Place gust lock lever in locked (up) position.
(5) Verify all cockpit flight controls are locked by manually attempting to move rudder pedals right
and left, aileron yoke left and right and elevator column forward and aft.
NOTE: It will still be possible to move rudder pedals several inches under force against
rudder arti ficial feel bungee. This is normal behavior and is due to clearance
between input and output sectors at rudder actuator.
Aileron surfaces will have approximately ±0.75 inches of spongy free play with gust
lock engaged due to gust lock latch being upstream of aileron actuators.
(6) Place both power levers forward and verify the following:
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### Page 15

(a) Verify movement is not more than 6° beyond 48° idle mark on quadrant position
protractor.
NOTE: If movement is more than 6° beyond 48° idle mark on quadrant position
protractor, see Throttle Lever Gust Lock Protection - Fault Isolation, 27-70-00,
Fault Isolation.
(7) Place throttle levers to IDLE.
(8) Place gust lock lever forward to unlock (down) position.
(9) Operate aileron, rudder and elevators. Verify free movement through full range.
(10) Advance throttle levers to take off and back to idle position. Verify levers move freely through
entire range.
(11) Remove quadrant position protractor. See Position Protractor - Removal / Installation,
31-01-00, Removal / Installation .
C. Follow On
(1) Inspect for presence of foreign objects.
(2) Record all maintenance actions in accordance with current governing authority.
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MAINTENANCE MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK
27-70-00
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