TASK CARD
Description: LUBRICATE MLG UPLOCK ROLLER (LH & RH)
SYS
Area: MULTIPLE LOCATIONS
Labor Hours: 0.3
W/O Phase: INSP
Skills: TECH
Zones: 720
Parts: (1) AER0SHELL33, (4) MS24665-153
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
1
NOTE: BEFORE APPLYING LUBRICANT, WIPE OFF ANY DIRT AND MOISTURE WITH A
CLEAN, LINT FREE CLOTH, LIGHTLY MOISTENED WITH CLEANING SOLVENT.
AVOID EXCESSIVE USE OF LUBRICANT WHEN APPLYING BY HAND. CLEAN UP
ANY SPILLAGE IMMEDIATELY AND REMOVE EXCESS GREASE AFTER HAND
OR GREASE GUN APPLICATION.
NOTE: IF A LUBRICATION POINT DOES NOT ACCEPT GREASE, REFER TO
THE GMM, SECTION 5-20-0.
ITEM
2
INSTRUCTIONS
1.
Remove LH main gear shock strut uplock roller assembly, P/N 10165-3, clean, lubricate and
reinstall (Refer to the applicable Dash-8 AMM, Chapter 32). (See Figure 1).
NOTE: GREASE TYPE: AEROSHELL 33.
ITEM
3
ITEM
4
INSTRUCTIONS
2.
Lead mechanic must inspect the reinstallation of the LH Uplock roller assembly.
INSTRUCTIONS
3.
Remove RH main gear shock strut uplock roller assembly, P/N 10165-3, clean, lubricate and
reinstall (Refer to the applicable Dash-8 AMM, Chapter 32) (See Figure 1).
NOTE: GREASE TYPE: AEROSHELL 33.
ITEM
5
INSTRUCTIONS
4.
Lead mechanic must inspect the reinstallation of the RH MLG uplock roller assembly.
T/C:
Printed Date/Time: 2/20/2007 10:39:23
Page 1 of 2
* 3200Q0 1- 20111 *
Revision Date/Time: 9/22/2006 21:39:48
TASK CARD
FIGURE 1 – LUBRICATION OF MAIN LANDING GEAR
T/C:
Printed Date/Time: 2/20/2007 10:39:23
Page 2 of 2
* 3200Q0 1- 20111 *
Revision Date/Time: 9/22/2006 21:39:48
TASK CARD
Task Card: 3200Q01-21204
E/C:
W/O:
P/N:
Date:
S/N:
Aircraft:
A/C Pos:
NLA Pos:
Description: LUBRICATE MLG UPLOCK ROLLER (LH/RH)
Predecessors: 1200 Q03-21204
SYS
Area: MULTIPLE LOCATIONS
Labor Hours: 0.3
W/O Phase: INSP
Skills: TECH, DI9
Zones: 720, 730
Parts: (1) AER0SHELL33, (4) MS24665-153
ITEM
1
INSTRUCTIONS
1.
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
Remove main gear shock strut uplock roller assembly, P/N 10165-3, clean, lubricate and
reinstall (Refer to the applicable Dash-8 AMM, Chapter 32). (See Figure 1).
NOTE: THE FOLLOWING LANDING GEAR LUBRICATION TASKS ARE REQUIRED TO BE
ACCOMPLISHED WITHIN FOUR HOURS AFTER WASHING THE AIRCRAFT.
NOTE: BEFORE APPLYING LUBRICANT, WIPE OFF ANY DIRT AND MOISTURE WITH A
CLEAN, LINT FREE CLOTH, LIGHTLY MOISTENED WITH CLEANING SOLVENT.
AVOID EXCESSIVE USE OF LUBRICANT WHEN APPLYING BY HAND. CLEAN UP
ANY SPILLAGE IMMEDIATELY AND REMOVE EXCESS GREASE AFTER HAND
OR GREASE GUN APPLICATION.
NOTE: IF A LUBRICATION POINT WILL NOT ACCEPT GREASE, REFER TO
THE GMM, SECTION 5-20-0.
NOTE: GREASE TYPE: AEROSHELL 33.
ITEM
2
ITEM
3
ITEM
4
ITEM
5
ITEM
6
INSTRUCTIONS
2.
Perform item 1 on the LH side.
INSTRUCTIONS
3.
Perform item 1 on the RH side.
INSTRUCTIONS
4.
Inspect reinstallation of the uplock roller (See Figure 1).
INSTRUCTIONS
5.
Perform item 4 on the LH side.
INSTRUCTIONS
6.
Perform item 4 on the RH side.
T/C:
Printed Date/Time: 2/20/2007 10:40:32
Page 1 of 2
* 3200Q0 1- 21204*
Revision Date/Time: 7/18/2006 15:39:11
TASK CARD
Task Card: 3200Q01-21204
W/O:
Date:
Aircraft:
LUBRICATION OF MAIN LANDING GEAR
FIGURE 1
T/C:
Printed Date/Time: 2/20/2007 10:40:32
Page 2 of 2
* 3200Q0 1- 21204*
Revision Date/Time: 7/18/2006 15:39:11
TASK CARD
Description: INSPECT MLG AFT DOOR BUMPER TAPE FOR CONDITION AND SECURITY
SYS
Skills: DI9
Zones: 419
ITEM
1
ITEM
INSTRUCTIONS
1.
MECH
QC
MECH
QC
Inspect the MLG aft door bumper tape for condition and security.
INSTRUCTIONS
2
NOTE (1): REMOVAL OF PANELS IS NOT REQUIRED TO PERFORM THIS INSPECTION.
NOTE (2): TAIL PIPE INSPECTION IS COVERED BY A DETAILED VISUAL INSPECTION
AND IS NOT PART OF THIS INSPECTION.
T/C:
Printed Date/Time: 2/20/2007 10:42:14
Page 1 of 1
* 3210Q04- 20505*
Revision Date/Time: 12/14/2005 09:59:10
TASK CARD
Description: INSPECT MLG AFT DOOR BUMPER TAPE FOR CONDITION AND SECURITY (RH)
SYS
Skills: DI9
Zones: 429
ITEM
1
ITEM
INSTRUCTIONS
1.
MECH
QC
MECH
QC
Inspect MLG aft door bumper tape for condition and security.
INSTRUCTIONS
2
NOTE (1): REMOVAL OF PANELS IS NOT REQUIRED TO PERFORM THIS INSPECTION.
NOTE (2): TAIL PIPE INSPECTION IS COVERED BY A DETAILED VISUAL INSPECTION
AND IS NOT PART OF THIS INSPECTION.
T/C:
Printed Date/Time: 2/20/2007 10:43:14
Page 1 of 1
* 3210Q04- 20506*
Revision Date/Time: 12/15/2005 10:38:59
TASK CARD
Description: INSPECT LH & RH MLG LOCK MECHANISM
SYS
Skills: DI9, TECH, RII9
Zones: 721, 731
ITEM
1
ITEM
2
ITEM
3
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
1.
Make sure the landing gear is down and locked, install MLG ground lock pins and engage NLG
ground lock (refer to applicable Dash 8 AMM, Chapter 32).
2. Ensure pressure is released from hydraulic system.
3. Open main landing gear doors (refer to applicable Dash 8 AMM,Chapter 32).
4. Use a 0.002 inch (0.05mm) feeler gage, measure stop face gap between forward and aft stop
faces as shown (See Figure 1):
A.
If there is no gap between stop faces or if feeler gage does not go fully between stop
faces, lock mechanism is serviceable.
B. If feeler gage goes fully between stop faces, lock mechanism is unserviceable and must
be repaired or replaced.
C. Was gap found?
(1) LH:
Yes
No
(2) RH:
Yes
No
INSTRUCTIONS
5.
Perform item 1 on the LH side.
INSTRUCTIONS
6.
Perform item 1 on the RH side.
INSTRUCTIONS
4
NOTE: ENTER “NA” IN THIS SECTION IF REWORK IS NOT PERFORMED.
7.
For unserviceable lock mechanism refer to applicable Dash 8 CMM, Chapter 32. (Dowty CMM
for MLG stabilizer stay assembly) and do the following:
A.
Remove MLG stabilizer strut from aircraft (refer to applicable Dash 8 AMM, Chapter 32).
B. Disassemble MLG stabilizer stay, refer to disassembly section.
C. Do a check of all pins, bushings and sleeve/bushing sub-assemblies that affect free play in
the MLG stabilizer stay. Repair or replace as necessary; refer to:
(1) Fits and Clearances section for dimensional information.
(2) Repair section for rework information.
(3) Illustrated Parts List section for part numbers to order components (oversize bushings
or sleeve/bushing sub-assemblies are identified and ordered by the relevant CRS
number found in the Repair section).
D.
ITEM
5
ITEM
Assemble MLG stabilizer stay, refer to Assembly section.
INSTRUCTIONS
8.
Perform item 4 on the LH side.
INSTRUCTIONS
* 3210Q05- 20397*
T/C:
Printed Date/Time: 2/20/2007 10:44:10
Page 1 of 3
Revision Date/Time: 6/23/2006 21:53:45
TASK CARD
Task Card: 3210Q05-20397
6
ITEM
9.
W/O:
Date:
Aircraft:
Perform item 4 on the RH side.
INSTRUCTIONS
MECH
QC
MECH
QC
RII
MECH
QC
RII
7
NOTE: ENTER “NA” IN THIS SECTION IF REWORK IS NOT PERFORMED.
A.
ITEM
8
ITEM
9
Install serviceable MLG stabilizer strut on aircraft (refer to applicable Dash 8 AMM,
Chapter 32).
INSTRUCTIONS
10. Perform item 7 on the LH side.
INSTRUCTIONS
11. Perform item 7 on the RH side.
T/C:
Printed Date/Time: 2/20/2007 10:44:10
Page 2 of 3
* 3210Q05- 20397*
Revision Date/Time: 6/23/2006 21:53:45
TASK CARD
Page 3 of 3
T/C:
Printed Date/Time: 2/20/2007 10:44:10
* 3210Q05- 20397*
Revision Date/Time: 6/23/2006 21:53:45
TASK CARD
Description: REPLACE BRAKE SHUTTLE VALVES (LH - FWD/AFT, RH - FWD/AFT), DUE O/H
SYS
Area: NACELLE/POWERPLANT
Labor Hours: 4
W/O Phase: INSP
Skills: TECH, DI9
Zones: 410, 420
Parts: (4) 5084-4
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
1
NOTE: THERE ARE TWO BRAKE SHUTTLE VALVES PER NACELLE AND FOUR TOTAL
FOR THE ENTIRE AIRCRAFT. POSITION IDENTIFIERS ARE 1 FWD, 1AFT, AND
2FWD AND 2AFT.
1.
Prepare the aircraft for removal of the left hand and right hand nacelle FWD and AFT brake
shuttle valves.
WARNING: ENSURE THAT THE NOSE-GEAR GROUND LOCK IS ENGAGED AND THAT
THE MAIN LANDING GEAR LOCK PINS ARE INSTALLED.
A.
B.
Ensure that all safety devices and warning placards are installed on the following:
(1) Landing gear controls.
(2) External AC power connection.
(3) External hydraulic connect.
(4) Other applicable positions.
Before proceeding, make sure that hydraulic power is off and that external power is
disconnected. Bleed off hydraulic system pressures by moving the aileron and rudder
controls, and by operating the Parking Brake lever approximately 10 times.
NOTE: THE REMOVAL PROCEDURES FOR THE LEFT FWD/AFT AND THE RIGHT
FWD/AFT SHUTTLE VALVES ARE THE SAME.
ITEM
2
ITEM
3
INSTRUCTIONS
2.
Remove the L/H forward and aft brake shuttle valves.
A.
Disconnect the hydraulic lines (2), (3) and (4) as follows (See Figure 1):
(1) Place a suitable container in position below the shuttle valve (1) to collect the
hydraulic fluid.
(2) Disconnect the hydraulic lines (2), (3) and (4) from the shuttle valve (1) and the
quantity limiting valve (5).
(3) Using blanking caps, seal the hydraulic lines (2), (3) and (4); the shuttle valve ports
(6) and (7); and the quantity limiting valve reducer (8).
INSTRUCTIONS
B.
Remove the clamps (9) and (10) as follows (See Figure 1):
(1) Remove the nut (11) and the washer (12) from the bolt (13).
T/C:
Printed Date/Time: 2/20/2007 10:48:36
Page 1 of 4
* 3240Q0 1- 21202*
Revision Date/Time: 9/27/2006 17:14:44
TASK CARD
Task Card: 3240Q01-21202
(2)
(3)
ITEM
W/O:
Date:
Aircraft:
Remove the bolt (13) and the spacers (14) and (15).
Remove the clamps (9) and (10) from the quantity limiting valves (5) and (16).
INSTRUCTIONS
4
C.
Remove the shuttle valve (1) as follows (See Figure 1):
(1) Hold the shuttle valve (1) and remove the bolts (17) and the washers (18).
(2) Remove the shuttle valve (1) and the quantity limiting valve (5) as a unit.
D.
Disconnect the shuttle valve (1) and the quantity limiting valve (5):
(1) Remove and discard the lockwire between the bushing (19) and the inlet port (20) of
the shuttle valve (1).
(2) Remove the shuttle valve (1) and bushing (19) from the inlet port (20) of the shuttle
valve (1).
(3) Remove the bushing (19) from the quantity limiting valve (5).
(4) Remove and discard the preformed packing (21) from the bushing (19).
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
NOTE: TAG REMOVED SHUTTLE VALVES AS “REMOVED FOR VENDOR OVERHAUL.”
ITEM
5
INSTRUCTIONS
3.
Install the L/H forward and aft brake shuttle valves.
NOTE: ENSURE THAT THE AIRCRAFT IS IN THE SAME CONFIGURATION AS IN THE
REMOVAL PORTION OF THIS TASK.
A.
ITEM
INSTRUCTIONS
6
ITEM
B.
Install the shuttle valve (1) and quantity limiting valve (5) on the nacelle structure (22) with
the bolts (17) and the washers (18).
C. Install the clamps (9) and (10) as follows (See Figure 1)
(1) Install the clamps (9) and (10) on the quantity limiting valves (5) and (16).
(2) Install the bolt (13) and the spacers (14) and (15) on the clamps (9) and (10), and the
nacelle structure (22).
(3) Install the nut (11) and the washer (12) to the bolt (13).
INSTRUCTIONS
7
ITEM
8
Connect the shuttle valve (1) and the quantity limiting valve (5) (See Figure 1):
(1) Install the preformed packing (21) on the bushing (19).
(2) Install the bushing (19) on the quantity limiting valve (5).
(3) Install the shuttle valve (1) and bushing (19) on the inlet port (20) of the shuttle valve
(1).
(4) Safety the bushing (19) to the inlet port (20) with lockwire.
D.
Remove the blanking caps from the hydraulic lines (2), (3) and (4); the shuttle valve ports
(6) and (7); and the quantity limiting valve reducer (8).
E. Connect the hydraulic lines (2), (3) and (4) to the shuttle valve ports (6) and (7) and the
quantity limiting valve reducer (8).
INSTRUCTIONS
4.
Remove and replace R/H forward and aft brake shuttle valves IAW steps 2.,A. thru 3.,E. of this
Workcard.
NOTE: TAG REMOVED SHUTTLE VALVES AS “ REMOVED FOR VENDOR OVERHAUL”
ITEM
9
INSTRUCTIONS
5.
Bleed the individual Brake System and Parking Brake System in accordance with the
T/C:
Printed Date/Time: 2/20/2007 10:48:36
Page 2 of 4
* 3240Q0 1- 21202*
Revision Date/Time: 9/27/2006 17:14:44
i
TASK CARD
Task Card: 3240Q01-21202
W/O:
Date:
Aircraft:
applicable Dash-8 AMM, Chapter 32. Replenish hydraulic system reservoirs as required.
ITEM INSTRUCTIONS
10 6.
ITEM INSTRUCTIONS
11
7.
Page 3 of 4
QC
MECH
QC
MECH
QC
Perform item 10 on the LH side.
ITEM INSTRUCTIONS
12 8.
MECH
Perform a visual inspection of the L/H and R/H forward and aft Shuttle Valves and Quantity
Limiting Valves for leaks and security of attachment. Ensure that area is clear of all tools and
equipment.
Perform item 10 on the RH side.
T/C:
Printed Date/Time: 2/20/2007 10:48:36
* 3240Q0 1- 21202*
Revision Date/Time: 9/27/2006 17:14:44
TASK CARD
BRAKE SHUTTLE VALVE REMOVAL / INSTALLATION- FIGURE 1
Page 4 of 4
T/C:
Printed Date/Time: 2/20/2007 10:48:36
* 3240Q0 1- 21202*
Revision Date/Time: 9/27/2006 17:14:44
TASK CARD
Description: REPLACE THE LH AND RH MLG BRAKE HYDRAULIC FLEX HOSES
Area:
Labor Hours: 2
W/O Phase: INSP
Skills: TECH
Zones: 721, 731
Parts: (4) DSC252A4-0230
ITEM
1
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
Procedure:
1.
Ensure aircraft is chocked.
2.
Engage the nose-gear ground lock (reference DHC-8 AMM Task 10-11-00-400-801).
3.
Install the lock pins on the main landing gear
(reference DHC-8 AMM Task 10-11-00-400-802).
4. Obey all the hydraulic safety precautions
(reference DHC-8 AMM Task 29-00-00-910-801).
5.
Install the safety devices and/or the warning signs on the following:
A.
The landing gear controls.
B. Brake controls.
C. The external hydraulic connections.
D. Other applicable positions.
6.
7.
8.
Ensure that all of the hydraulic power is disconnected.
Ensure that the ac external power is disconnected.
Decrease the pressure in the hydraulic lines to zero as follows:
A.
Operate the emergency brake lever until zero pressure is shown on the park brake
hydraulic pressure indicator.
B. Set emergency brake lever in the flight compartment to off.
9.
Remove flexible hose assembly from brake to MLG strut (See Figure 1).
10. Tag and route removed hose assembly to Stores.
11. Install new flexible hose assembly.
ITEM
2
ITEM
3
ITEM
4
ITEM
5
ITEM
6
INSTRUCTIONS
12. Accomplish Item 1 (steps 1-11) on all of the following MLG brake line positions:
A.
Left outboard brake line.
INSTRUCTIONS
(1)
Bleed left outboard brake in accordance with DHC-8 AMM,
Task 32-42-00-870-802.
INSTRUCTIONS
B. Left inboard brake line.
INSTRUCTIONS
(1)
Bleed left inboard brake in accordance with DHC-8 AMM,
Task 32-42-00-870-802.
INSTRUCTIONS
C. Right outboard brake line.
T/C:
Printed Date/Time: 2/20/2007 10:50:45
Page 1 of 3
* 3240Q02- 21231*
Revision Date/Time: 2/23/2006 21:00:52
i
TASK CARD
Task Card: 3240Q02-21231
ITEM
7
ITEM
8
ITEM
9
ITEM
W/O:
Date:
Aircraft:
INSTRUCTIONS
(1)
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
Bleed right outboard brake in accordance with DHC-8 AMM,
Task 32-42-00-870-802.
INSTRUCTIONS
D. Right inboard brake line.
INSTRUCTIONS
(1)
Bleed right inboard brake in accordance with DHC-8 AMM,
Task 32-42-00-870-802.
INSTRUCTIONS
13 13. Service Hydraulic system in accordance with DHC-8 AMM, Chapter 12-12-00.
ITEM
11
INSTRUCTIONS
14. Return aircraft to standard configuration as required.
T/C:
Printed Date/Time: 2/20/2007 10:50:45
Page 2 of 3
* 3240Q02- 21231*
Revision Date/Time: 2/23/2006 21:00:52
TASK CARD
Page 3 of 3
MAIN LANDING GEAR BRAKE FLEX HOSES
FIGURE 1
T/C:
Printed Date/Time: 2/20/2007 10:50:45
* 3240Q02- 21231*
Revision Date/Time: 2/23/2006 21:00:52
TASK CARD
Description: FUNCTIONAL CHECK OF ANTI-COLLISION WHITE STROBE LIGHTS OR DISCARD ANTI-COLLISION
WHITE STROBE LIGHTS
SYS
Area:
Labor Hours: 2.5
W/O Phase:
Skills: TECH
Zones: 300, 500, 600
Tools: (1) ST-4000
Parts: (1) 01-0770417-00, (1) 02-0370418-00
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
1
NOTE: IF THE INTENSITY TESTER IS UN-AVAILABLE, N/A THE TESTING PROCEDURES
(STEP 1) AND PROCEED TO THE STROBE DISCARD PROCEDURES (STEPS 2
THRU 14) PROVIDED IN THIS WORK-CARD.
ITEM
2
INSTRUCTIONS
1.
Perform functional check of strobes as follows:
NOTE: DURING THE TEST, THE WAND MUST BE KEPT AS STRAIGHT AS POSSIBLE
(NO BOWING) AND MUST REMAIN DIRECTLY IN-LINE WITH THE STROBE
OUTPUT.
WARNING: ENSURE THE UV PROTECTIVE GLASSES (PROVIDED WITH TESTER) ARE
WORN DURING THE TEST.
NOTE: THE TEST UNIT WILL AUTOMATICALLY COMPENSATE FOR AMBIENT (MAN
MADE) LIGHTING CONDITIONS. AVOID CONDUCTING THIS TEST IN DIRECT
SUN-LIGHT.
A.
B.
C.
D.
E.
F.
G.
H.
Ensure the strobe lens is clean on the LEFT WING-TIP strobe.
Mount the intensity detector to the telescopic-wand and extend it to its full 8’ length.
Place the tip of the wand against the LEFT WING-TIP strobe light lens assembly.
Turn the Photo-Meter on by pressing the ON button of the test unit.
Energize the aircraft Strobe lights.
Press the START button on the test unit. The unit will count ten (10) flashes.
After the tenth flash, a digital readout will be displayed noting the intensity in ‘Candelas’.
Record the reading:
(Left Wing-Tip)
NOTE: THE STROBE MUST PRODUCE AN INTENSITY OF 400 CANDELAS OR MORE. IF
A READING LESS THAN 400 IS OBSERVED, REPLACE THE STROBE IAW THE
DISCARD PROCEDURES INCLUDED IN THIS WORK CARD.
ITEM
3
INSTRUCTIONS
I.
Repeat steps 1A-G on the RIGHT WING-TIP strobe.
T/C:
Printed Date/Time: 2/20/2007 10:51:59
Page 1 of 5
* 3340Q0 1- 20495*
Revision Date/Time: 1/16/2006 16:59:29
TASK CARD
Task Card: 3340Q01-20495
J.
ITEM
4
ITEM
5
ITEM
6
ITEM
7
ITEM
8
ITEM
Record the reading:
W/O:
Date:
Aircraft:
(Right Wing-tip)
NOTE: THE STROBE MUST PRODUCE AN INTENSITY OF CANDELAS OR MORE. IF
400
THE STROBE IAW THE
A READING LESS THAN 400 IS OBSERVED,
CARD.
REPLACE
INSTRUCTIONS
DISCARD PROCEDURES INCLUDED IN THIS
K. Repeat
steps 1A-G on the TAIL CONE strobe.
WORK
L. Record the reading:
(Tail Cone)
NOTE: THE STROBE MUST PRODUCE AN INTENSITY OF CANDELAS OR MORE. IF
THE STROBE IAW THE
400
CARD.
A READING LESS THAN 400 IS OBSERVED,
REPLACE
INSTRUCTIONS
DISCARD PROCEDURES INCLUDED IN THIS
WORK
NOTE: IF THE STROBE FUNCTIONAL TEST WAS ACCOMPLISHED, N/A THE
REMAINDER OF THIS WORKCARD (STEPS 2 THRU 14).
INSTRUCTIONS
2.
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
Open the access panels that follow (N/A if accomplished via panel card):
A.
628CB (access panel)
B. 628AR (wing tip lens)
INSTRUCTIONS
4.
QC
Open the access panels that follow (N/A if accomplished via panel card):
A.
528CB (access panel)
B. 528AL (wing tip lens)
INSTRUCTIONS
3.
MECH
Open the access panel that follows (N/A if accomplished via panel card):
A.
312AB (tail cone access door)
INSTRUCTIONS
9
NOTE: IF SECONDARY STROBE LIGHT IS BEING UTILIZED (EVIDENCED BY CARBON
DEPOSITS ON BULB) REMOVE & REPLACE BOTH PRIMARY & SECONDARY
BULBS.
5.
Remove Strobe Light - Left and Right Wing.
A.
On right main DC circuit breaker panel, open and clip circuit breaker EXT LTS ANTI COLL
(Q2).
B. At strobe light power supply, break lockwire on strobe light connector plug and disconnect
connector plug.
C. Remove 2 screws and washers from strobe light lens retainer and retain.
D. Remove lens retainer and gasket and retain.
E. At strobe light bracket, pull flash tube assembly out and discard.
6.
Install Strobe Light - Left and Right Wing.
A.
While replacing the Strobe Flash Tube, thoroughly clean the Strobe Light lens and the
wing lens.
NOTE: IN NORMAL OPERATION, THE PRIMARY STROBE LIGHTS ARE USED
(SEE FIGURE 1). AFTER THE REMOVAL/INSTALLATION OF A STROBE LIGHT,
ENSURE THAT THE PRIMARY STROBE LIGHT (AFT) IS CONNECTED TO THE
OUTPUT CONNECTOR ON THE STROBE LIGHT POWER SUPPLY UNIT AND THE
SECONDARY STROBE LIGHT (FORWARD) IS CONNECTED TO THE DUMMY
T/C:
Printed Date/Time: 2/20/2007 10:51:59
Page 2 of 5
* 3340Q0 1- 20495*
Revision Date/Time: 1/16/2006 16:59:29
TASK CARD
Task Card: 3340Q01-20495
W/O:
Date:
Aircraft:
CONNECTOR ON THE STROBE LIGHT POWER SUPPLY.
B.
Insert connector plug on new flash tube assembly through strobe light bracket and connect
to output receptacle on power supply and wire lock connector plug.
C. Insert gasket into lens retainer and attach lens retainer to strobe light bracket using the 2
screws and washers previously removed.
D. On right main DC circuit breaker panel, close circuit breaker EXT LTS ANTI COLL (Q2).
ITEM INSTRUCTIONS
10 7.
ITEM INSTRUCTIONS
11
8.
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
Perform item 9 on the RH side.
ITEM INSTRUCTIONS
12 9.
MECH
Perform item 9 on the LH side.
Remove Strobe Light - Tail Cone.
A.
On right main DC circuit breaker panel, open and clip circuit breaker EXT LTS ANTI COLL
(Q2).
B. At strobe light power supply, break lockwire on strobe light connector plug and disconnect
connector plug.
C. Remove sealant from around lens retainer.
D. Remove 2 screws and washers from strobe light lens retainer and retain.
E. Remove lens retainer and gasket and retain.
F. At strobe light bracket, pull flash tube assembly out and discard.
ITEM INSTRUCTIONS
13 10. Install Strobe Light - Tail Cone.
A.
While replacing the Strobe Flash Tube, thoroughly clean the Strobe Light lens and the tail
cone lens.
B. Equipment and Material:
(1) Solvent: Commercially available trichloroethane.
(2) Sealant: PRC Corp. type PR1422-B2 or equivalent.
NOTE: IN NORMAL OPERATION, THE PRIMARY STROBE LIGHTS ARE USED (SEE
FIGURE 1). AFTER THE REMOVAL/INSTALLATION OF A STROBE LIGHT,
ENSURE THAT THE PRIMARY STROBE LIGHT (LEFT) IS CONNECTED TO THE
OUTPUT CONNECTOR ON THE STROBE LIGHT POWER SUPPLY UNIT AND THE
SECONDARY STROBE LIGHT (RIGHT) IS CONNECTED TO THE DUMMY
CONNECTOR ON POWER SUPPLY.
C.
D.
E.
F.
G.
H.
Insert connector plug on new flash tube assembly through strobe light bracket and connect
to output receptacle on strobe light power supply.
Wire lock connector plug.
Clean area around strobe light bracket with solvent.
Insert gasket into lens retainer and attach lens retainer to strobe light bracket using the 2
screws and washers previously removed.
Apply sealant around lens retainer.
On right main dc circuit breaker panel, close circuit breaker EXT LTS ANTI COLL (Q2).
ITEM INSTRUCTIONS
14 11. Operational Test - Anti-collision Lights.
A.
Apply electrical power to the DC bus system.
B. On right DC circuit breaker panel, ensure ANTI COLL (Q2) circuit breaker is closed.
C. At right EXTERIOR LIGHTS panel in overhead console, set the A/COL switch to WHITE
and check the white strobe lights, located at the end of each wing tip and at the lower tip of
the tail cone, come on and flash at a rate of 50 + or - 5 flashes per minute.
D. Set the A/COL switch to OFF and check that the three white strobe lights go off.
T/C:
Printed Date/Time: 2/20/2007 10:51:59
Page 3 of 5
* 3340Q0 1- 20495*
Revision Date/Time: 1/16/2006 16:59:29
TASK CARD
Task Card: 3340Q01-20495
ITEM
W/O:
Date:
Aircraft:
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
15 12. Close the access panels that follow (N/A if accomplished via panel card):
A.
528CB (access panel - sealant required)
B.
528AL (wing tip lens)
ITEM
INSTRUCTIONS
16 13. Close the access panels that follow (N/A if accomplished via panel card):
A.
628CB (access panel – sealant required)
B.
628AR (wing tip lens)
ITEM
INSTRUCTIONS
17 14. Close the access panel that follows (N/A if accomplished via panel card):
A.
312AB (tail cone access door)
ANTI-COLLISION LIGHTS REMOVE/REPLACE
T/C:
Printed Date/Time: 2/20/2007 10:51:59
Page 4 of 5
* 3340Q0 1- 20495*
Revision Date/Time: 1/16/2006 16:59:29
TASK CARD
FIGURE 1
T/C:
Printed Date/Time: 2/20/2007 10:51:59
Page 5 of 5
* 3340Q0 1- 20495*
Revision Date/Time: 1/16/2006 16:59:29
TASK CARD
Description: HGS SYSTEM INSPECTION
SYS
Area: AVIONICS/ELECTRICAL
Skills: TECH
Zones: 210
ITEM
INSTRUCT IONS
1
NOTE: ACCESS PANELS, WITH THE EXCEPTION OF THE HGS OVERHEAD UNIT TRIM
PANEL, WILL BE REMOVED AS PART OF THE "C" CHECK ROUTINE CARDS
AND THEREFORE ARE NOT DETAILED ON THIS CARD.
1. Starting at the HGS computer tray (STA. 420), examine all connectors and clamps securing the
HIRF overbraid and connectors to the tray.
2. Physically grasp connectors at each tray and verify that it is firmly attached to the respective
mating connection with no free movement.
3. Examine connectors, clamps and overbraid for condition and security.
4. Observe that signal separation has been maintained in the wire runs. Refer to the
Dash 8 200 AMM, Chapter 34-32-00, QX Supplement 56 for details of signal separation.
5. In the wardrobe avionics section, inspect condition and security of the wire runs and braiding.
6. Remove the Trim Panel from the Overhead Unit.
7. On the Overhead Unit, inspect the condition of the Overhead Unit Desiccant through the
observation port located on the underside of the Overhead Unit.
A. A blue color is acceptable and indicates dry desiccant.
B. A blue to pink color is satisfactory for aircraft service. The desiccant will be dried by the
Overhead Unit electrical heater during normal flight operations.
C. A pink to white/yellow color indicates excessive moisture. The Overhead Unit should be
removed for service.
8. Re-install the Trim Panel.
Page 1 of 1
MECH
QC
T/C:
Printed Date/Time: 2/20/2007 10:53:33
*3424Q03-21197*
Revision Date/Time: 11/21/2005 13:33:56
TASK CARD
Description: DVI OF WEATHER RADAR WAVEGUIDE
SYS
Area: FUSELAGE EXTERIOR
Skills: DI9
Zones: 110
ITEM
1
INSTRUCT IONS
1.
MECH
Perform a Detailed visual inspection of the weather radar waveguide paying particular attention
to the following inspection criteria.
A.
Ensure that there are no cracks in the brazing connecting the flange to the waveguide.
B.
Inspect for any areas that are crushed, pinched, or that would cause deformities in the
cross-section of the waveguide.
C.
Inspect for corrosion inside of the waveguide (Utilize Borescope Inspection method).
D.
Inspect for cracks inside the waveguide (Utilize Borescope Inspection method).
NOTE: RUBBER COVERED “TWIST-O-FLEX” TYPE WAVEGUIDES CAN BECOME
DAMAGED IF THEY ARE TWISTED OR BENT AT TOO SHARP OF AN ANGLE.
THIS TYPE OF DAMAGE IS DIFFICULT TO TROUBLESHOOT BECAUSE THE
COATING MAY HIDE ANY BREAKS.
T/C:
Printed Date/Time: 2/20/2007 10:54:31
Page 1 of 1
* 3440Q0 1- 21215*
Revision Date/Time: 11/16/2005 10:51:26
QC
TASK CARD
Description: VISUAL AND ELECTRICAL INSPECTION OF THE #1 & #2 RADIO ALTIMETER ANTENNAS
SYS
Area:
Labor Hours: 6
W/O Phase:
Skills: TECH
Zones: 130
Parts: (2) S67-200222
ITEM
1
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
MECH
QC
SYSTEM #1 (See Figure 1):
1. Open, safety and tag the following circuit breaker on the avionics circuit breaker panel:
A.
RAD ALT 1 (F5)
2. Remove the radar altimeter antennas at fuselage station X141.7 and X177.4 (refer to the Dash8 200 AMM, Task 34-44-10-000-802). Inspect for damage and corrosion. Clean or replace as
required.
3. Remove old sealant from antennas.
4. Inspect antenna to fuselage bonding areas; ensure that all paint has been removed and the
area has been alodined. Perform the following steps.
A.
To provide an adequate area of electrical bonding for antenna gaskets, remove paint and
primer from the aircraft skin around antenna connector holes. Use 240 grit emery paper or
equivalent. Do not use a steel brush.
B. Wipe cleaned areas using a cloth dampened in methyl Ethyl Keytone (MEK).
C. Apply alodine solution to fully cover cleaned areas. Allow solution to remain on cleaned
areas for six to eight minutes.
D. Remove all trace of alodine solution by wiping with a cleaned cloth dampened with clean
water. Dry using a clean, lint free cloth.
INSTRUCTIONS
2
NOTE: FOR OPTIONAL COAXIAL CONNECTOR SEALING PROCEDURES, REFER TO
THE DASH-8 200 AMM, TASK 34-44-07-400-801, M C N 23485-001.
5.
6.
If required, install one new gasket (P/N S67-200222) to each antenna location.
Install radar altimeter antennas and secure with screws (refer to the Dash-8 200 AMM, Task
34-44-10-400-802). Apply fillet of sealant (P/N PR 1422/B2) around antennas.
7. Ensure that antenna base to airframe bonding check resistance is less than 20 mili-ohms.
8. Perform a resistance check of the Receiver/Transmitter COAX measured from center
conductor, to shield at transceiver end. Resistance should be less than 5 ohms.
9. Perform TDR measurement of the Transmit and Receive COAX to verify proper condition.
10. Verify that there are no pushed pins in the Transceiver, COAX mating connectors, or the rackmating interface.
ITEM
3
ITEM
4
INSTRUCTIONS
11. Remove tag and close the following circuit breaker on the avionics circuit breaker panel:
A.
RAD ALT 1 (F5)
INSTRUCTIONS
12. Perform one of the following steps to return this component to CAT III or CAT I status:
T/C:
Printed Date/Time: 2/20/2007 10:55:25
Page 1 of 3
* 3440Q04- 20670*
Revision Date/Time: 2/13/2006 23:21:25
TASK CARD
Task Card: 3440Q04-20670
A.
W/O:
Date:
Aircraft:
CAT III status: perform CAT III MTC #9340031.
NOTE: THIS STEP (12A) CAN ONLY BE ACCOMPLISHED BY CAT III AUTHORIZED
PERSONNEL.
NOTE: N/A THIS STEP IF STEP “12B” BELOW IS ACCOMPLISHED.
ITEM
5
INSTRUCTIONS
B.
MECH
QC
MECH
QC
MECH
QC
MECH
QC
MECH
QC
CAT I status: perform Self-Test / Zero Indication Test of the Radio Altimeter CAT I System
in accordance with DHC-8 AMM, Task 34-44-00-730-801.
NOTE: N/A THIS STEP IF STEP “12A” ABOVE WAS ACCOMPLISHED.
NOTE: AIRCRAFT WAS DOWNGRADED TO CAT I STATUS VIA WORKCARD ISSUED TO
THE CHECK.
ITEM
6
INSTRUCTIONS
SYSTEM #2 (See Figure 1):
13. Open, safety and tag the following circuit breaker on the avionics circuit breaker panel:
A.
RAD ALT 2 (F8)
14. Remove the radar altimeter antennas at fuselage station X282.4 and X318.4 (refer to the Dash8 200 AMM, Task 34-44-10-000-802). Inspect for damage and corrosion. Clean or replace as
required.
15. Remove old sealant from antennas.
16. Inspect antenna to fuselage bonding areas; ensure that all paint has been removed and the
area has been alodined. Perform the following steps:
A.
To provide an adequate area of electrical bonding for antenna gaskets, remove paint and
primer from the aircraft skin around antenna connector holes. Use 240 grit emery paper or
equivalent. Do not use a steel brush.
B. Wipe cleaned areas using a cloth dampened in Methyl Ethyl Keytone (MEK).
C. Apply alodine solution to fully cover cleaned areas. Allow solution to remain on cleaned
areas for six to eight minutes.
D. Remove all trace of alodine solution by wiping with a cleaned cloth dampened with clean
water. Dry using a clean, lint free cloth.
ITEM
INSTRUCTIONS
7
NOTE: FOR OPTIONAL COAXIAL CONNECTOR SEALING PROCEDURES, REFER TO
THE DASH-8 200 AMM, TASK 34-44-07-400-801, M C N 23485-001.
17. If required, install one new gasket (P/N S67-200222) to each antenna location.
18. Install radar altimeter antennas and secure with screws (refer to the Dash-8 200 AMM, Task
34-44-10-400-802). Apply fillet of sealant (P/N PR 1422/B2) around antennas.
19. Repeat steps 7, 8, 9, and 10 that were previously accomplished for System #1.
ITEM
8
ITEM
9
INSTRUCTIONS
20. Remove tag and close the following circuit breaker on the avionics circuit breaker panel:
A.
RAD ALT 2 (F8)
INSTRUCTIONS
21. Perform one of the following steps to return this component to CAT III or CAT I status:
A.
CAT III status: perform CAT III MTC #9340031.
NOTE: THIS STEP (21A) CAN ONLY BE ACCOMPLISHED BY CAT III AUTHORIZED
PERSONNEL.
* 3440Q04- 20670*
T/C:
Printed Date/Time: 2/20/2007 10:55:25
Page 2 of 3
Revision Date/Time: 2/13/2006 23:21:25
TASK CARD
Task Card: 3440Q04-20670
W/O:
Date:
Aircraft:
NOTE: N/A THIS STEP IF STEP “21 B” BELOW IS ACCOMPLISHED.
ITEM
10
INSTRUCT IONS
B.
MECH
CAT I status: perform Self-Test / Zero Indication Test of the Radio Altimeter CAT I System
in accordance with DHC-8 AMM, Task 34-44-00-730-801.
NOTE: N/A THIS STEP IF STEP “21A” ABOVE WAS ACCOMPLISHED.
NOTE: AIRCRAFT WAS DOWNGRADED TO CAT I STATUS VIA WORKCARD ISSUED TO
THE CHECK.
PIC WIRE AND C ABLE P/N T556124
DHC-8 200 SYSTEM #1 AND SYSTEM #2
Impedance (Ohms)
Capacitance (pF/ft.)
Velocity of propagation (%)
Time Delay (ns/ft.)
Attenuation (db/100 ft.)
50
29
70
1.44
1.0 GHz 5.7
1.5 GHz 7.1
5.0 GHz 14.2
FIGURE 1
T/C:
Printed Date/Time: 2/20/2007 10:55:25
Page 3 of 3
* 3440Q04- 20670*
Revision Date/Time: 2/13/2006 23:21:25
QC
TASK CARD
Description: VISUAL INSPECTION OF THE UPPER & LOWER TCAS ANTENNAS & ADAPTER PLATES FOR
CONDITION, SECURITY & CORROSION
SYS
Area: FUSELAGE EXTERIOR
Skills: TECH
Zones: 140, 800
ITEM
1
ITEM
2
ITEM
3
INSTRUCTIONS
1.
INSTRUCTIONS
2.
Comply with TCAS Operational check/test in accordance with the following maintenance task
card:
A.
For Dash-8 200: Use MTC 9344002.
T/C:
Printed Date/Time: 2/20/2007 10:56:35
Page 1 of 1
QC
MECH
QC
MECH
QC
Re-install the upper and lower TCAS Antennas IAW the Dash-8 200 AMM,
Chapter 34-47-00, QX Supplement 1.
INSTRUCTIONS
3.
MECH
Perform a visual inspection of the upper and lower TCAS antennas.
A.
Remove the upper and lower TCAS Antennas IAW the Dash-8 200 AMM,
Chapter 34-47-00, QX Supplement 1.
B. Perform a visual inspection of the Antennas and Adapter Plates paying particular attention
to condition, security, and corrosion.
C. Perform a visual inspection of the Antenna Cable Connectors paying particular attention to
condition, security, corrosion, and the presence of moisture.
* 3440Q05- 20670*
Revision Date/Time: 12/8/2005 09:01:07
TASK CARD
Description: CAT III; DOWN-GRADE (PRE-DOCK), UP-GRADE AND SYSTEM TEST (POST-DOCK). (HEAVY CHECKS
ONLY)
SYS
Skills: TECH
Zones: 211
ITEM
INSTRUCTIONS
MECH
QC
MECH
QC
MECH
QC
1
NOTE: THIS WORKCARD IS INTENDED FOR C CHECKS ONLY.
ITEM
2
ITEM
INSTRUCTIONS
1.
Pre-dock:
A.
Change Cockpit Category Placard to display Category I status.
B. Open an aircraft logbook discrepancy with the following statement: “Aircraft
downgraded to Category I for scheduled heavy maintenance check.”
INSTRUCTIONS
3
NOTE: THIS STEP CAN ONLY BE ACCOMPLISHED BY CAT III AUTHORIZED
PERSONNEL.
NOTE: N/A THIS STEP IF AIRCRAFT IS NOT TO BE RETURNED TO CAT III STATUS.
2.
Post-dock:
A.
Perform Category III 1200 hour System Test IAW MTC 9340044.
B. Change Cockpit Category Placard to display Category III status.
C. Clear aircraft logbook discrepancy opened during pre-dock procedure above.
D. Clear with the following statement:
“Performed Category III 1200 hour system test IAW MTC 9340044. Reference C check
WC 211AV34 21177, dated (note printed date in WC header). Aircraft now Category III
qualified. Placard changed to CAT III.”
T/C:
Printed Date/Time: 2/20/2007 10:57:35
Page 1 of 1
* 3450Q04- 21177*
Revision Date/Time: 2/21/2006 23:23:39