Attachment 2- N87 Task Cards.pdf

CL-600 - 0303

Tail # : () Work Order # :

Card #: 0303 Labor Hours: 0

Date :

Description: PORTABLE FIRE EXTINGUISHER - WEIGHT CHECK AND INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference TLMC 5-20-15 and Maintenance Manual Chapter/Section 26-25-00 and Raytheon E-Systems Green Sheet Supplements Chapter/Section 26-25-00 if further information is necessary.

B NOTE: Place all discrepancies on a non-routine card.

T 1 The Portable Fire Extinguishers have a 144 Month Hydrostatic Requirement. If the Bottle is replaced, weigh the replacement bottle before installation.

T 2 Weight Check

Remove extinguishers (1 in cockpit and 1 in cabin).

T 3 Check that the operating head is securely attached to cylinder, tamper indicator or nylon tie is not broken and nozzle is unobstructed.

T 4 Check freedom of movement of safety clamps by moving them from locked to unlocked and back to locked positions.

T 5 CAUTION: DO NOT ATTEMPT TO CORRECT CYLINDER OVERPRESSURE CONDITION BY

DISCHARGING FIREX AGENT. CYLINDERS SUBJECT TO OVERPRESSURE ARE

CONSIDERED DEFECTIVE.

Check reading on cylinder pressure gauge. If gauge indicates overpressure or underpressure, cylinder must be removed and serviceable container installed.

T 6 Check cylinder and reject if any of the following defects are noted:

a. Dents, abrasions or deep scratches are present on cylinder.

b. Any amount of corrosion is present on cylinder.

c. Container shows evidence of exposure to fire or excessive heat.

d. Evidence of repairs by soldering, welding, brazing or use of patching compounds.

e. Cylinder or shell threads are damaged.

T 7 Check extinguisher service tag. Weigh extinguisher in accordance with the instructions on the bottle, record weight, and date on service tag, VN Form 4100-16. Include bottle Date of Manufacture (DOM) on tag.

T 8 Secure Portable Fire Extinguishers in the mounting brackets provided. (1 in cockpit and 1 in cabin)

1 (Last)

CL-600 - 2321

Card #: 2321 Labor Hours: 0

Date :

Description: PASSENGER OXYGEN CYLINDER MOUNT INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference TLMC Raytheon Supplement chapter/section 5-70-10 and Raytheon Supplement data in chapter/section 35-00-00 if further information is necessary.

T 1 Open nose equipment bay doors 212 AR and 211 AL.

T 2 Remove both 115 cu. ft. cylinders from mounts located in the nose equipment bay.

T 3 Perform a close visual check utilizing the intensity light source and magnifying lens, paying particular attention to aircraft structure in the area near the fasteners holding the upper cylinder mount to the left and right buttline 6.0 bulkhead frames.

NOTE: All cracks must be repaired using FAA approved data before bottles can be re-installed.

T 4 Install oxygen cylinders and service as necessary.

T 5 Leak check oxygen cylinder connections.

T 6 Close access doors 211 AL and 212 AR.

CL-600 - 3304

Card #: 3304 Labor Hours: 0

Date :

Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

Work Card Tasks TECH INSP Step Description

A Reference TLMC 5-10-30, Challenger M/M White Pages Chapter/Section 39-11-31, Raytheon Green Sheet Supplements Chapter/Section 39-11-31, and Challenger NDT Manual PART 9 Chapter/Section 53-10-11 if further in formation is necessary.

B NOTE: Place all discrepancies on a non-routine card and in ILM.

T 1 Remove electrical power from aircraft.

T 2 Remove Pilots And Copilots Primary Flight Display

Release the three locking pawls from the unit and pull the display straight out so that the connector pins are not damaged. Identify each electrical connector. Install protective covers on all connectors and plugs.

(See Figure 1 Details B & D)(Refer to Raytheon Green Sheet Supplements 34-22-01)

T 3 Remove N1% RPM, ITT, N2%RPM, Fuel Flow indicators and identify each electrical connector and plug. Install protective covers on all connectors and plugs. (See Figure 1 Detail C Items 1, 2, 3, and 4)

T 4 Remove Pilots And Copilots Auto-Pilot Mode Select Panels

Release locking screws and pull mode select panels out. Disconnect pilots connector 1P301CA and co-pilots connector 2P301CA. Install protective covers on all connectors and plugs. Remove bonding jumper from receptacles. (See Figure 1 Detail A Item 3)(Refer to Raytheon Green Sheet Supplements 22-10-02)

T 5 Remove Glareshield Annunciator Panel

Release locking fasteners and pull glareshield annunciator panel out. Disconnect connectors P314 and J314. Install protective covers on all connectors and plugs. (See Figure 1 Detail A item 7)(Refer to Raytheon Green Sheet Supplements 22-10-03)

T 6 Remove the clamps to the air outlets and peel hose off of beaded tubes. Install protective covers over hose open ends. (See Figure 2)

T 7 Support the glareshield and remove the screws and washers around the lip. Remove the glareshield. (See Figure 2)

NOTE: Remove the remaining switches, lights, pushbuttons and switch/light as required for glareshield removal.

Protect the glareshield from scratches, high heat and liquid petroleum products or their vapors.

Card #: 3304 Labor Hours: 0

Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

Work Card Tasks TECH INSP Step Description

T 8a Pull back installation and visually check for cracks and corrosion in the windshield lower sill, for twelve inches to either side of the centerline BL 0.0, paying particular attention to the inner fillet radius of the sill.

(See Figure 3)

(Refer to Challenger NDT manual PART 9 chapter/section 53-10-11)

NOTE: Any evidence of cracking or corrosion is to be reported to AVN-340 Engineering , who will then recommend rectification action.

I 8b Ok to close.

T 9 Install glareshield in the reverse order of removal, starting from step 7 to step 1.

T 10 Apply electrical power to aircraft. Perform operational/functional test of the annunciator lights, dim/brightness switches, and systems as follows. (See Figure 1 Detail A and Figure 1 Detail F, item 1)

(Refer to Challenger White Pages 39-11-31)

Check that both MASTER CAUTION PRESS TO RESET SWITCHES flash and when pressed reset themselves. (Refer to Challenger White Pages 31-53-00).

T 11 Check that both STALL/PUSH ANNUNCIATOR systems work as follows:

(1) Move both AOA vanes full up/down and that no damage is evident. Place in horizontal position.

(2) Hydro sys ELECT PUMP 3B to ON.

(3) STALL PROTECTION PUSHER switches to On and latched.

(4) STALL PROTECT FAIL lights, both OUT.

(5) FLAPS set to 0 degrees.

(6) STALL PROTECTION TEST hold both switches to TEST simultaneously. Both ALT COMP FAIL lights on.

T 12 Check the SPS functions as test indicator pointer moves over the scale toward the red region:

(1) Pointer within blue region, check that ENG 1/ENG 2, IGN A/B lights are ON.

(2) Pointer within yellow region, check stick shakers operate.

(3) Pointer within red region, check for aural stall warning and stick pusher operates. STALL/PUSH lights flash.

(4) Pointer stops moving, check STALL PROTECT FAIL lights flash.

NOTE: The STALL PROTECT FAIL lights may flash earlier in the test sequence. This is a normal indication.

(5) Press the Control column AP/SP DISC pushbuttons and check that stick pusher disengages and re-engages when pushbutton is released.

(6) G SWITCH TEST, check that stick pusher disengages and reengages when G SWITCH is released.

(7) Release both STALL PROTECTION TEST switches, ensure that above functions cease.

Card #: 3304 Labor Hours: 0

Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

Work Card Tasks TECH INSP Step Description

T 13 Check that all other remaining lights on the glareshield, and flight displays work. (Bright/Dim and WARN LTS ) (See Figure 1 Detail F item 4)

T 14 Use the Engine Instrument Test Panel to test the following: (See Figure 1 Detail E)

Use test positions 1 and 2, the N1, N2, ITT, and Fuel Flow indicators display 888 and the analog displays full-scale reading.

T 15 Check that the ITT indicator RED overtemp warning light above the analog scale comes on.

NOTE: It is normal for the AUX PWR failure warning light located on the instrument control panel to come on.

NOTE: When the TEST switch is set and held to position 1 or 2, the test displays from 2 to 5 seconds and then resets to the pre-test display.

T 16 Check that automatic dimming of the instruments occur by varying the light level in front of the engine instrument test switch control panel photocell.

T I 17 Make appropriate logbook entries.

Card #: 3304Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

FIGURE 1

Card #: 3304Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

FIGURE 2

Card #: 3304Description: VISUAL CHECK WINDSHIELD LOWER SILL FS 209.0

FIGURE 3

6 (Last)

CL-600 - 4309

Card #: 4309 Labor Hours: 0

Date :

Description: PASSENGER OXYGEN SYSTEM MASK DROP AND VISUAL INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Supplemental Maintenance Manual, Chapter/Section 35-20-00 and KCA Interior Maintenance Manual.

B WARNING: OILS, GREASE, SOLVENTS OR ORGANIC MATTER MAY BURN OR EXPLODE

SPONTANEOUSLY WHEN IN CONTACT WITH COMPRESSED OXYGEN. EXTREME CARE

MUST BE TAKEN TO AVOID ANY CONTAMINATION OF THE OXYGEN SYSTEM AND

COMPONENTS, HANDS, TOOLS AND CLOTHING MUST BE FREE OF OIL, GREASE AND DIRT

WHEN WORKING WITH OXYGEN EQUIPMENT.

CAUTION:

*1. OPEN FLAME AND SMOKING ARE STRICTLY PROHIBITED IN THE VICINITY OF

OXYGEN EQUIPMENT DURING TEST OR SERVICING

*2. ENSURE THAT AIRCRAFT IS ELECTRICALLY GROUNDED AND WORK AREA IS CLEAN

AND WELL VENTILATED BEFORE SERVICING OXYGEN EQUIPMENT

*3. ENSURE THE ELECTRICAL POWER IS OFF BEFORE SERVICING THE OXYGEN SYSTEM

*4. ENSURE THAT ONLY APPROVED/QUALIFIED PERSONNEL ARE PERMITTED TO CARRY

OUT SERVICING AND MAINTENANCE ON OXYGEN EQUIPMENT

C NOTE: Place all discrepancies on a non-routine card and in ILM.

T 1a Manual Test:

Rotate passenger oxygen control panel knob to MANUAL, located on the co-pilot's console aft of the EROS mask, and observe.

(1) All masks should clear dropout boxes.

(2) The cabin NO SMOKING signs shall be illuminated.

(3) Annunciator CABIN OXY ON shall be illuminated in the cockpit.

(4) Warning tone shall sound in cockpit.

(5) Feature panel lights shall be illuminated.

T 1b Rotate passenger oxygen control panel knob to OFF.

T 1c Pull lanyard on one mask to vent system.

Card #: 4309 Labor Hours: 0

Description: PASSENGER OXYGEN SYSTEM MASK DROP AND VISUAL INSPECTION

Work Card Tasks TECH INSP Step Description

T 1d Inspect oxygen masks for cleanliness and condition.

Inspect the elastometric hoses should not be rigid or brittle, chafed by abrasion,or suspect to contamination by moisture or corrosion.

T 1e Repack masks.

T 2a Automatic Test:

Remove vented cap and connect pitot static test unit to ALT TEST port on passenger oxygen control panel.

T 2b Rotate passenger oxygen control panel knob to AUTO.

T 2c Increase altitude on pitot/static test unit to approximately 20,000 feet and observe.

(1) All masks should deploy at 13,500 +/- 500 feet.

(2) The cabin NO SMOKING signs shall be illuminated.

(3) Cockpit annunciator CABIN OXY ON shall be illuminated.

(4) Warning tone shall sound.

(5) Feature panel lights shall be illuminated.

T 2d Rotate passenger oxygen control panel to OFF.

T 2e Lower altitude to ground level on pitot/static test unit.

T 2f Pull lanyard on one mask to vent system.

T 2g Repack masks.

Card #: 4309Description: PASSENGER OXYGEN SYSTEM MASK DROP AND VISUAL INSPECTION

3 (Last)

CL-600 - 4313

Card #: 4313 Labor Hours: 0

Date :

Description: OXYGEN LINES LEAK TEST

Work Card Tasks TECH INSP Step Description

A Reference TLMC Raytheon Supplement 5-70-10 and Raytheon supplement section in maintenance manual chapter/section 35-20-00 if further information is necessary.

T 1a Perform an oxygen line leak test.

WARNING: OBSERVE ALL APPLICABLE SAFETY PRECAUTIONS CONCERNING

MAINTENANCE OF OXYGEN SYSTEMS WHILE ACCOMPLISHING THIS PROCEDURE.

Inspect the system to assure all system components and lines are properly installed and secure. Assure that the oxygen system has been serviced to normal operating pressure (1850 PSI at 70degF). Assure that the passenger oxygen cylinder regulators are turned ON. Passenger control panel gauge should read 1850

PSI.

T 1b After one hour, gauge shall read 1850 psi. If leak is evident, locate and repair leak then retest.

CL-600 - 4317

Card #: 4317 Labor Hours: 0

Date :

Description: CABIN INTERIOR MAINTENANCE/CHECK

Work Card Tasks TECH INSP Step Description

A Reference TLMC Manual Green Sheet Supplements, Chapter/Section 5-70-10 and M/M Chapter 11 white pages and supplements, if further information is necessary.

B NOTE: Record all discrepancies discovered during this check on a non-routine.

C RETURN ALL UNUSED PARTS TO STOCKROOM.

T 1 Visually check passenger oxygen control panel for condition and security of mounting.

T 2 Visually check the oxygen masks in the drop boxes for cleanliness and damage.

Inspect the elastometric hoses should not be rigid or brittle, chafed by abrasion, or suspect to contamination by moisture or corrosion.

T 3 Check Galley for condition and security of mounting.

Check operation of doors, drawers and latches.

* Check trash bin access and disposal doors for proper operation, fit, sealing and latching.

T 4 * Check bulkheads, storage cabinets, equipment racks and work stations, etc. for condition and security of mounting.

T 5 Check operation of cabin interior lighting.

T 6 Check operation of emergency lighting.

Emergency light battery pack for condition and security.

T 7 Perform operational check of smoke detectors (push to test light assemblies on co-pilots annunciator panel).

CL-600 - 4317

Card #: 4317 Labor Hours: 0

Description: CABIN INTERIOR MAINTENANCE/CHECK

Work Card Tasks TECH INSP Step Description

T 8 * Toilet Compartment:

Check vanity for condition and security of mounting.

Check operation of door, drawers and latches.

Check trash bin access and disposal doors for proper operation, fits, sealing, latching.

*NOTE: The potable water system has been deactivated per EO 15-09-01.

T 9 Check water system supply and drain components for condition, corrosion and security of mounting.

T 10 Check air lav toilet for condition, security of mounting and corrosion.

T 11 Check interior doors for condition, security of mountings and proper latching.

T 12 Check placards for condition and brightness.

T 13 Visually check therapeutic mask (if installed).

2 (Last)

CL-600 - 4319

Card #: 4319 Labor Hours: 0

Date :

Description: VCS CABIN INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Aero Aire Maintenance Manual if further information is necessary.

B NOTE: Place all discrepancies on non-routine cards.

T 1 EVAPORATOR PALLET INSPECTION

Remove the two access panels as shown in Figure 1.

Visually check for corrosion.

Loose or missing hardware.

Mounting flanges/brackets for damage.

Wire condition.

Wire terminals for security.

Lines and fittings for leaks.

Placard condition.

Insulation material on evaporator for condition and security.

Air leaks in cooling circuit.

Correct refrigerant level.

NOTE: Low airflow complaints only, visually check wear on fan impellers and fan for blockage.

CL-600 - 4319

Card #: 4319Description: VCS CABIN INSPECTION

CL-601 - 4330

Card #: 4330 Labor Hours: 0

Date :

Description: EMERGENCY EQUIPMENT INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Supplemental Aircraft Maintenance Manual 4109.2-2.

B All discrepancies discovered during this check must be recorded as non-routines.

Refer to TI 4100.24 General Maintenance Manual procedures.

C NOTE: Life vest are packaged in approved poly bags which are sewn shut and include dated inspection certificate cards.

If poly bag has been opened, or if date on certification card has expired or will expire within 12 months, replace the life vest. The MFD/INSP date (month/year) for each vest can be verified by looking through its translucent packaging material. A bright light source may be required.

T 1 PILOT POSTION, EMERGENCY EQUIPMENT INSPECTION:

Emergency Flashlight: Operational check, replace batteries if needed.

Inspect flashlight mount bracket for condition and security.

Return flashlight to mounting bracket and check for proper fit.

Crash Axe: Check for condition and security.

Life Vest: Inspect life vest for condition and expiration date.

Inspect life vest storage pouch for condition and security.

Return life vest to the pouch behind the pilot’s seat and secure cover.

Smoke Goggles: Replace the goggles if the lenses are cracked, if the frame is cracked, or the foam padding is deteriorated.

Return the Smoke Goggles and pouch to the storage bin at the left of the pilot’s seat.

EVAS: Visually check the EVAS for general condition, security and proper position in the cockpit.

Card #: 4330 Labor Hours: 0

Description: EMERGENCY EQUIPMENT INSPECTION

Work Card Tasks TECH INSP Step Description

T 2 COPILOT POSITION, EMERGENCY EQUIPMENT INSPECTION:

Emergency Flashlight: Operational check, replace batteries if needed.

Inspect flashlight mount bracket for condition and security.

Return flashlight to mounting bracket and check for proper fit.

Life Vest: Inspect life vest for condition and expiration date.

Inspect life vest storage pouch for condition and security.

Return life vest to the pouch behind the copilot’s seat and secure cover.

Smoke Goggles: Replace the goggles if the lenses are cracked, if the frame is cracked, or the foam padding is deteriorated.

Return the Smoke Goggles and pouch to the storage bin at the right of the copilot’s seat.

EVAS: Visually check the EVAS for general condition, security and proper position in the cockpit.

T 3 OBSERVERS POSITION, EMERGENCY EQUIPMENT INSPECTION:

The observer's smoke goggles and life vest are stored in the galley compartment.

Life Vest: Inspect life vest for condition and expiration date.

Smoke Goggles: Replace the goggles if the lenses are cracked, if the frame is cracked, or the foam padding is deteriorated.

Remove any trash or miscellaneous items from emergency equipment storage bin.

Return the smoke goggles and life vest to the galley compartment.

T 4 PROTECTIVE BREATHING EQUIPMENT(PBE)INSPECTION:

Three PBE Hoods are located in the aircraft cabin. One in the Crew Coat Closet, one on the Life Raft Stowage Container and one on the Aft Partition. Reference TI 4158.1-32-15 and EO 16-09-09.

Inspect PBE Hood storage container for condition and security.

Verify the "Replace by Date" Label date has not expired. The PBEs have a 126 Month Life Limit.

Verify each PBE Container Tamper-Evident Seals are unbroken.

Verify each PBE Humidity Indicators are Blue in color. A Humidity Indicator that has turned Pink indicates that moisture has breached the barrier pouch and the PBE is no longer serviceable.

Card #: 4330 Labor Hours: 0

Description: EMERGENCY EQUIPMENT INSPECTION

Work Card Tasks TECH INSP Step Description

T 5 MISION SPECIALIST POSITION, EMERGENCY EQUIPMENT INSPECTION:

Life Vest: Inspect life vest for condition and expiration date.

Return life vest to the storage bin at the left of the technician’s seat.

Smoke Goggles: Replace the goggles if the lenses are cracked, if the frame is cracked, or the foam padding is deteriorated.

Return the Smoke Goggles and pouch to the storage bin at the left of the technician’s seat.

T 6 PASSENGER/CABIN EMERGENCY EQUIPMENT INSPECTION:

Life Vest: Life vests are located under each passenger seat. Inspect life vests for condition and expiration date.

Return each life vest to the storage container below each passenger seat.

Life Line: Inspect life line at emergency exit for condition and security.

Life Rafts: Two life rafts are secured in the cabinet located aft of the AFIS Equipment rack. Inspect for general condition and security.

CL-600 - 5321

Card #: 5321 Labor Hours: 0

Date :

Description: LAIRCM 400 Hour Inspection

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual 4109.2-2 and 4109.3-3 Chapter 53, EO 05-09-10 and 4190.3, if further information is necessary.

B NOTE: Place all discrepancies on a non-routine card and in ILM.

C NOTE: APPLY FAYING AND SEAL AROUND EXTERIOR OF BLANKING PLATES TO ENSURE

MOISTURE DOES NOT ENTER FAIRINGS. USE PR-1775 CLASS B OR MIL-S-81733 MINIMUM

ADHESION SEALANT.

NOTE: TO ENSURE PROPER ELECTRICAL BONDING WHEN SENSORS ARE REINSTALLED,

DO NOT APPLY SEALANT BETEEN BLANKING PLATE AND SENSOR MOUNT.

T 1 Forward Sensors and Fairing Inspection:

(a) Remove the Sensors (001-007671-009) or Blanking Plates (4890466-201/-202), ground straps, and Sensor Fairings (4890463-801, -802 & -901).

(b) Check the Sensor and Sensor Fairing attachment fasteners, nutplates. and inserts for any signs of damage or corrosion. Use a mirror and flashlight to inspect the nutplates and inserts. Replace any corroded or damaged fastencrs, nutplates, or inserts.

(c) Visually inspect the Sensor Fairings for cracks, structural damage, and missing or damaged finish.

Pay particular attention to areas around the sensor cutout and all fastener holes. Inspect the fairings for any signs of delamillation paying particular attention to edges and areas around holes. Touch up any areas with damaged finish.

(d) Verify that the aluminum sensor Mounting Plate (4890463-6011-603) is securely bonded to the Fairing by checking for play or looseness. Visually inspect the Mounting Plate for corrosion. Contact Engineering if corrosion or damage is found. Contact Engineering if any cracks, delaminations. or other damage are found in the fairings.

(e) Inspect the grounding stud assembly. Make sure the nuts on the aft side are tight. Check for signs of corrosion on mounding stud. If corrosion is found, the grounding stud shall be replaced.

(f) Check for signs of moisture intrusion into the Wing-Body Fairing. Pay particular attention to the Sensor cutout area. Use a light and mirror to check for any internal signs of delamination or disbonding. If signs of internal or external damage are found, remove the fairing, then contact Engineering for a repair disposition. Touch up any areas with damaged finish or edge seals.

* (g) Reinstall the Sensor Fairings, ground straps, and Sensors or Blanking Plates. Renew any faying or fillet seals. Refer to step C.

Card #: 5321 Labor Hours: 0

Description: LAIRCM 400 Hour Inspection

Work Card Tasks TECH INSP Step Description

T 2 Aft Sensors, Fairings, and Mount Inspection:

(a) Remove the Sensors (001-007671-009) or Blanking Plates (4890466-203/-204) and the fairings (4890460-501/-502).

(b) Check all removed fasteners and their respective nutplates for any signs of damage or corrosion. Use a flashlight to inspect the nutplates. Replace any corroded or damaged fasteners or nutplates.

(c) Visually inspect the fairings, fillers (4890460-1009/-1010) and fittings (4890460-601/-602) for cracks. corrosion, or damage. Pay particular attention to fastener holes, areas around fasteners, areas with tight bend radii, or where two or more layers of metal are in contact. Use a mirror and light to inspect inside the Fittings. Touch up any areas where the finish is damaged.

(d) Visually inspect the exposed portion of the Doubler (4890460-701/-702) for signs of cracks, corrosion, and loose or missing fasteners. Touch up any area where the finish is damaged. Report any cracks or corrosion to Engineering.

(e) Inspect the doubler to skin interface at the sensor cutout for any signs of corrosion. Use a mirror and flashlight to check both sides. Report any corrosion to Engineering. Touch up any area where the finish is damaged.

(f) Visually inspect the inside surface of the skin under the doubler for cracks, corrosion, or damaged finish. A mirror and light can be used to accomplish this inspection through the sensor cutout.

* (g) Reinstall the Fairings and Sensors or Blanking Plates. Renew any faying or fillet seals. Refer to step C.

Card #: 5321 Labor Hours: 0

Description: LAIRCM 400 Hour Inspection

Work Card Tasks TECH INSP Step Description

T 3 SLTA Mount Inspection:

(a) Remove the SLTA (154-003432) and Fairing (4890459-2101) or the Blanking plate (4890465-201).

(b) Check the SLTA and Fairing attachment fasteners and the threads in the attachment flange (4890459-1601) for any signs of damage or corrosion. Use a flashlight to inspect the flange threads.

Replace any corroded or damaged fasteners.

(c) Visually inspect visible portions of the flange for signs of corrosion. Pay particular attention to fastener holes and areas around the flange attachment fasteners.

(d) Visually inspect the Doubler (4890459-2501) for cracks, corrosion, damaged finish, and loose or missing fasteners. Make sure that drain holes are clear. Touch up any area where the finish is damaged.

(e) Check that all the SLTA Fitting Attachment Fasteners are intact and tight. A manual check for looseness and play is adequate. This can be accomplished through the empty SLTA mounting hole or from inside the electronics bay.

(f) From inside the electronics bay, visually inspect the inside surface of the skin over the Doubler. Prior to inspection, clean any debris or residue from the inspection area. Carefully check for signs of cracks, corrosion, and damaged or missing finish. Also look for signs of moisture accumulation. Pay particular attention to areas around fasteners and along frames and stringers.

* (g) Reinstall the SLTA and Fairing or the Blanking Plate. Renew all faying and fillet seals. Refer to step C.

Card #: 5321Description: LAIRCM 400 Hour Inspection

4 (Last)

CL-600 - 5505

Card #: 5505 Labor Hours: 0

Date :

Description: PITCH TRIM ACTUATOR - BITE TEST

Work Card Tasks TECH INSP Step Description

A Reference TLMC Manual Chapter/Section 5-10-30 and Collins Report - RBS 601A109 if further information is necessary.

B NOTE: Place all discrepancies on a non-routine card and in ILM.

C NOTE: The Ground Maintenance BITE Test is part of the Build-in Test Equipment (BITE) and is generated by the BITE Module PCB when the HSTCU front panel door is open and the Push to Test switch is depressed. The Ground Maintenance BITE Test performed at every 400 flight hours will ensure that the following are verified:

a) Verify brakes integrity.

b) Ensure that no failure is recorded in Non Volatile Memory.

WARNING: MAKE SURE THE AREA AROUND THE HORIZONTAL STABILIZER IS CLEAR

BEFORE PERFORMING THIS CARD.

T 1 Do the Self-test of the HSTCS as follows: (Apply external power)

a. Disengage the latches (1) that attach the front cover of the HSTCU (2).

b. Open the front cover of the HSTCU (2). Make sure that the green LED on the front panel of the HSTCU (2) starts to flash.

c. Push simultaneously the red ("A") and green ("B") pushbuttons on the front panel for 1 second (HSTCU Fault Log reset).

d. Make sure that all red LEDs located on the HSTCU front panel are OFF. If any of the red LEDs are ON, then cycle (i.e. turn off, then turn back on) aircraft power to turn them off. If the red LEDs cannot be turned off, then replace the HSTCU.

e. Push the blue ("C") pushbutton on the front panel for 1 second (Self-test initiation).

WARNING: PUSH THE RED ("A") PUSHBUTTON ON THE FRONT PANEL TO STOP THE

SELF-TEST IF AN EMERGENCY OCCURS. IF YOU DO NOT STOP THE SELF-TEST DURING

AN EMERGENCY, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO

EQUIPMENT.

f. During the self-test, the red LEDs will flash sequentially until the self-test is completed. If none of the red LEDs flash, then perform the HSTCU SELF-TEST INITIATION FAULT Check. If some of the red LEDs flash, but one or more do not flash, then replace the HSTCU because of faulty LED(s).

g. The test is completed when the red LEDs no longer flash, and the green LED starts to flash again.

Close front cover of the HSTCU (2).

I 2 Make appropriate logbook entries.

CL-600 - 5505

Card #: 5505Description: PITCH TRIM ACTUATOR - BITE TEST

CL-600 - 7128

Card #: 7128 Labor Hours: 0

Date :

Description: WING UPPER COVER VISUAL CHECK OPEN UP

Work Card Tasks TECH INSP Step Description

A Reference TLMC Manual Chapter/Section 5-10-30 and NDT Manual Part 9 VC-57-30-28, if further information is necessary.

T 1 Remove the following access panels (See Figure 1).

140-AL 140-AR 140-CL 143-CZ

140-BL 140-BR 140-CR 144-CZ

CL-600 - 7128

Card #: 7128Description: WING UPPER COVER VISUAL CHECK OPEN UP

ACCESS PANELS OPEN UP

CL-600 - 7350L

Card #: 7350L Labor Hours: 0

Date :

Description: WING UPPER COVER VISUAL CHECK

Work Card Tasks TECH INSP Step Description

A *Reference TLMC Manual Chapter/Section 5-10-30 and NDT Manual Part 9 VC-57-30-28, if further information is necessary.

B NOTE: Place discrepancies on a non-routine card and in ILM.

T 1 Visually check for cracks, deformation and corrosion in the Wing Upper Cover. (See Figure 1).

T 2 *Utilizing the borescope check the centerline splice area for cracks, deformation and corrosion.

NOTE; Any evidence of cracking or corrosion is to be reported to AVN-340 Engineering, who will then recommend rectification action as required.

T I 3 Make appropriate logbook entries.

CL-600 - 7350L

Card #: 7350LDescription: WING UPPER COVER VISUAL CHECK

CL-600 - 7628

Card #: 7628 Labor Hours: 0

Date :

Description: WING UPPER COVER VISUAL CHECK CLOSE UP

Work Card Tasks TECH INSP Step Description

A Reference TLMC Manual Chapter/Section 5-10-30 and NDT Manual Part 9 VC-57-30-28, if further information is necessary.

T 1 Leadman ok to install the following access panels. (See Figure 1).

140-AL 140-AR 140-CL 143-CZ

140-BL 140-BR 140-CR 144-CZ

T 2 Install access panels.

140-AL 140-AR 140-CL 143-CZ

140-BL 140-BR 140-CR 144-CZ

CL-600 - 7628

Card #: 7628Description: WING UPPER COVER VISUAL CHECK CLOSE UP

ACCESS PANELS, FUSELAGE/WING

CL-600 - 8306

Card #: 8306 Labor Hours: 0

Date :

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Section 26-21-11 and 26-23-11, if further information is necessary.

B NOTE: Place all discrepancies on a non-routine card and in ILM.

T 1 Visually inspect firex discharge line (18). Reference Figure 2.

T 2 Remove APU cartridge (Figure 1).

NOTE: Gain access through rear fuselage equipment bay door.

a. Open and tag APU Fire Extinguishing System circuit breaker (CBP-A 182).

WARNING: BEFORE REMOVING A CARTRIDGE BE SURE ALL CIRCUITS IN THE

ACTUATING SYSTEM ARE OPEN.

ENSURE THAT A SHUNT DEVICE IS INSTALLED ON THE CARTRIDGE OR ACTUATOR PRIOR

TO HANDLING. HANDLING A CARTRIDGE WITHOUT A SHUNT COULD RESULT IN

SERIOUS INJURY. DO NOT USE FOIL TO SHUNT PINS!

b. Disconnect electrical connector (1); and install shunt wire on cartridge contact pins and install protective cover.

WARNING: FRANGIBLE DISK ON FIREX CONTAINER IS PARTIALLY EXPOSED WHEN

CARTRIDGE IS REMOVED. INSTALL A PROTECTIVE COVER ON OPENING OF BONNET

IMMEDIATELY AFTER REMOVING CARTRIDGE.

CAUTION: AVOID APPLYING EXCESSIVE FORCE ON BONNET WHEN REMOVING

CARTRIDGE.

c. Remove cartridge (2) from bonnet (3).

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T 3 Remove APU Firex Container (Figure 2).

CAUTION: USE A WRENCH TO PREVENT THE RECHARGE AND SAFETY FITTING (8) FROM

TURNING WHEN YOU REMOVE THE UNION NUT (9). FAILURE TO DO SO COULD DAMAGE

THE FITTING OR THE CONTAINER.

a. Loosen clamp and union nut (9) from the recharge and safety fitting (8).

CAUTION: PROTECTIVE COVERS MUST BE INSTALLED ON RECHARGE AND SAFETY

FITTING AND THERMAL RELIEF LINE AFTER REMOVING THERMAL RELIEF LINE.

b. Disconnect thermal relief line (10) from recharge and safety fitting (8); and install protective covers.

CAUTION: AVOID TRANSMITTING EXCESSIVE STRESS TO BONNET WHEN REMOVING

DISCHARGE LINE.

INSTALL PROTECTIVE COVER ON BONNET AND OPEN END OF DISCHARGE LINE AFTER

REMOVING DISCHARGE LINE FROM BONNET.

c. Loosen union nut (17) and disconnect discharge line (18) from bonnet (2); and install protective covers.

d. Disconnect electrical connection (7) from pressure gauge (6); and install protective covers.

e. Loosen nuts on clamp screws (5); and remove container (12) from mounting brackets (13).

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T 4 Inspection/Check APU Firex Container (Figure 2 and 4).

a. Note ambient temperature and reading on container pressure gauge (6) __________.

NOTE: Pressure must be within limits indicated.

b. Return container to vendor and replace with serviceable item if any of the following defects are noted:

(1) Cracks, of any length, at container welds.

(2) Evidence of bulging.

(3) Dents, pitting or inclusions on container surface.

(4) Evidence of heat damage.

(5) Corrosion, over any area, resulting in a decrease in container wall thickness of 0.005 inch.

c. Remove clamps (14) and all temporary protective caps, if fitted. Weigh charged container without discharge cartridge (1) and bonnet (2) fitted.

d. Compare measured weight with original total weight stamped on identification plate. Weight loss must not exceed 0.021 pounds.

e. Record date in last "Weight Inspection" block of identification using ink stamp; and check container for leakage using soft bristle brush and soap solution at all welds, fittings and openings.

f. Rinse off soap solution with clear water and dry thoroughly; and install protective covers, if required.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T I 5 Install APU Firex Container (Figure 2).

a. Position container (12) on mounting brackets (13) to provide clear view of pressure gauge; and secure with clamps (14) by tightening nuts on clamps screws (5).

b. Remove protective covers; and connect electrical connector (7) to pressure gauge (6).

c. Remove protective covers from discharge lines (18) and bonnet (2). Lubricate threads (16) of bonnet with sealing compound.

CAUTION: DURING CONNECTION OF DISCHARGE LINE TO CONTAINER, AVOID

TRANSMITTING EXCESSIVE STRESS TO BONNET.

d. Connect discharge line (18) to bonnet (2); and torque union nut (17) to 300 to 500 pound-inches.

e. Remove protective covers from thermal discharge line (10) and recharge and safety fitting (8).

Lubricate threads of recharge and safety fitting (8) with sealing compound.

CAUTION: USE A WRENCH TO PREVENT THE RECHARGE AND SAFETY FITTING (8) FROM

TURNING WHEN YOU APPLY TORQUE TO THE UNION NUT (9). FAILURE TO DO SO COULD

DAMAGE THE FITTING OR THE CONTAINER.

f. Connect thermal discharge line (10) to recharge and safety fitting (8) and torque union nut (9) to 115 pound-inches.

g. Secure thermal discharge line (10) by tightening clamp (11).

T 6 Check APU Cartridge (Before Installation)

WARNING: REJECTED CARTRIDGES MUST BE DISPOSED OF IN ACCORDANCE WITH

LOCAL REGULATIONS GOVERNING HANDLING OF CLASS C EXPLOSIVES.

a. Check cartridge date stamp; and discard cartridges if total life has expired.

b. Check that cartridge electrical contacts and threads are clean and free from deformation; that no dents are present on cartridge casing; and that crimped parts are secure.

c. Apply external electrical power; then press and hold APU SQUIB/LO PRESS switch/light on the FIREX MONITOR panel and check that the SQUIB light does not come on.

d. Release APU SQUIB/LO PRESS switch/light; then remove external electrical power.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T I 7 Install APU Cartridge (Figure 1)

WARNING: ENSURE THAT A SHUNT DEVICE IS INSTALLED ON THE CARTRIDGE OR

ACTUATOR PRIOR TO HANDLING. HANDLING A CARTRIDGE THAT DOES NOT CONTAIN A

SHUNT COULD RESULT IN SERIOUS INJURY. DO NOT USE FOIL TO SHUNT PINS!

CARTRIDGES OR ACTUATORS ARE NOT TO BE INSTALLED UNTIL THE BONNET IS

ASSEMBLED TO THE CONTAINER, IN PREPARATION FOR USE. WHEN INSTALLING THE

CARTRIDGE, THE CONTAINER SHALL BE SECURE IN THE AIRCRAFT OR A SUITABLE

ANTI-RECOIL DEVICE SHALL BE ATTACHED TO THE BONNET.

a. Remove protective cover from bonnet (3); position cartridge (2) in bonnet; then, torque cartridge to 150 to 200 pound-inches.

WARNING: BEFORE CONNECTING ELECTRICAL CONNECTOR BE SURE ALL CIRCUITS IN

THE ACTUATING SYSTEM ARE OPEN.

CAUTION: ENSURE THAT THERE IS NO FOREIGN OBJECT OR SHUNT WIRE AT THE

CONNECTOR PINS.

b. Remove protective cover and shunt wire from cartridge contact pins (2); and connect electrical connector (1).

T 8 APU Cartridge Operational Test

a. Apply external electrical power; and ensure that APU Fire Detection and Warning and the APU Fire Extinguishing System circuit breakers are closed.

b. Check that APU LO PRESS light on FIREX MONITOR panel is off. Press APU SQUIB/LO PRESS switch/light on FIREX MONITOR panel and check that SQUIB light comes on.

c. Remove external electrical power.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T 9 Remove Power Plant Cartridges (Figure 3).

NOTE: Removal and installation procedures are similar for each of the four power plant cartridges.

WARNING: BEFORE REMOVING A CARTRIDGE, BE SURE ALL CIRCUITS IN THE

ACTUATING SYSTEM ARE OPEN.

ENSURE THAT A SHUNT DEVICE IS INSTALLED ON THE CARTRIDGE OR ACTUATOR PRIOR

TO HANDLING. HANDLING A CARTRIDGE THAT DOES NOT CONTAIN A SHUNT COULD

RESULT IN SERIOUS INJURY. DO NOT USE FOIL TO SHUNT PINS!

a. Disconnect electrical connector (1); install shunt wire on cartridge contact pins; and install protective cover.

WARNING: FRANGIBLE DISK ON FIREX CONTAINER IS PARTIALLY EXPOSED WHEN

CARTRIDGE IS REMOVED. INSTALL PROTECTIVE COVER ON OPENING OF BONNET

IMMEDIATELY AFTER REMOVING CARTRIDGE.

CAUTION: AVOID APPLYING EXCESSIVE FORCE ON BONNET WHEN REMOVING

CARTRIDGE.

b. Remove cartridge (2) from bonnet (3).

T 10 Remove both Power Plant Firex Containers (Figure 4).

CAUTION: USE A WRENCH TO PREVENT THE RECHARGE AND SAFETY FITTING (16) FROM

TURNING WHEN YOU REMOVE THE UNION NUT (17). FAILURE TO DO SO COULD

DAMAGE THE FITTING OR THE CONTAINER.

a. Loosen clamp (19) and the union nut (17) from the recharge and safety fitting (16).

CAUTION: A PROTECTIVE COVER MUST BE INSTALLED ON RECHARGE AND SAFETY

FITTING AFTER REMOVING DISCHARGE LINE.

b. Disconnect thermal discharge line (18) from recharge and safety fitting (16); and install protective covers.

CAUTION: AVOID TRANSMITTING EXCESSIVE STRESS TO BONNET WHEN REMOVING

DISCHARGE LINES. INSTALL PROTECTIVE COVERS ON OPEN ENDS OF DISCHARGE LINES

AND BONNETS AFTER REMOVAL FROM BONNETS.

c. Loosen union nuts (1) and (10); then, remove discharge lines (2) and (9) from bonnets (12) and install protective covers.

d. Disconnect electrical connector (7) from pressure gauge (8); and install protective covers.

e. Remove bolts (6) and washers (5); then, remove container (3) from bracket assembly (4).

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T 11 Inspection/Check of Power Plant Firex Container.

a. Note ambient temperature and reading on container pressure gauge (8) __________.

NOTE: Pressure must be within limits indicated (Reference Figure 205).

b. Return container to vendor and replace with serviceable item if any of the following defects are noted:

(1) Cracks, of any length, at container welds.

(2) Evidence of bulging.

(3) Dents, pitting or inclusions on container surface.

(4) Evidence of heat damage.

(5) Corrosion, over any area, resulting in a decrease in container wall thickness of 0.005 inch.

c. Ensure all protective covers are removed; then, weigh charged container without discharge cartridges (11), and bonnets (12) fitted.

d. Compare measured weight with original total weight stamped on identification plate.

NOTE: Weight loss must not exceed 0.040 pounds.

e. Record date in last "Weight Inspection" block of identification plate using ink stamp; and check container for leakage using soft bristle brush and soap solution at all welds, fittings and openings.

f. Rinse off soap solution with clear water and dry thoroughly. Install temporary protective caps, if required.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T I 12 Install Power Plant Firex Container (Figure 4).

a. Position container (3) on bracket assembly (4) to provide clear view of pressure gauge (8); then, install washers (5) and bolts (6) and torque to 70 to 90 pound-inches.

b. Remove protective covers from bonnets and discharge lines (2) and (9); then, coat exposed threads of bonnet assemblies (12) with sealing compound.

CAUTION: DURING CONNECTION OF DISCHARGE LINES, AVOID TRANSMITTING

EXCESSIVE STRESS TO BONNETS.

c. Connect discharge lines (2) and (9) to bonnets; and torque union nuts (1) and (10) to 650 to 800 pound-inches.

d. Remove protective covers from discharge line (18) and recharge and safety fitting (16); then apply sealing compound to threads of recharge and safety fitting (16).

CAUTION: USE A WRENCH TO PREVENT THE RECHARGE AND SAFETY FITTING (16) FROM

TURNING WHEN YOU APPLY TORQUE TO THE UNION NUT (17). FAILURE TO DO SO

COULD DAMAGE THE FITTING OR THE CONTAINER.

e. Connect thermal discharge line (18) to recharge and safety fitting (16); and torque union nut (17) to 115 pound-inches.

f. Secure thermal discharge line (18) to APU support fuselage structure by tightening clamp (19); then, remove protective covers from the electrical connector (7) and the pressure gauge (8); and connect electrical connector (7) to pressure gauge (8).

T 13 Check Power Plant Cartridge (Before Installation)

WARNING: REJECTED CARTRIDGES MUST BE DISPOSED OF IN ACCORDANCE WITH

LOCAL REGULATIONS GOVERNING HANDLING OF CLASS C EXPLOSIVES.

a. Check cartridge date stamp; and discard cartridges if total life has expired.

b. Check that cartridge electrical contacts and threads are clean and free from deformation and that no dents are present on cartridge casing and that crimped parts are secure.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T I 14 Install Power Plant Cartridges (Figure 3).

WARNING: BEFORE INSTALLING A CARTRIDGE, BE SURE ALL CIRCUITS IN THE

ACTUATING SYSTEM ARE OPEN.

ENSURE THAT A SHUNT DEVICE IS INSTALLED ON THE CARTRIDGE OR ACTUATOR PRIOR

TO HANDLING. HANDLING A CARTRIDGE THAT DOES NOT CONTAIN A SHUNT COULD

RESULT IN SERIOUS INJURY. DO NOT USE FOIL TO SHUNT PINS!

CARTRIDGES OR ACTUATORS ARE NOT TO BE INSTALLED UNTIL THE BONNET IS

ASSEMBLED TO THE CONTAINER, IN PREPARATION FOR USE. WHEN INSTALLING THE

CARTRIDGE, THE CONTAINER SHALL BE SECURE IN THE AIRCRAFT OR A SUITABLE

ANTI-RECOIL DEVICE SHALL BE ATTACHED TO THE BONNET.

a. Remove protective cover from bonnet (3); then, position cartridge (2) in bonnet (3); and torque cartridge to 150 to 200 pound-inches.

T 15 CAUTION: ENSURE THAT THERE IS NO FOREIGN OBJECT OR SHUNT WIRE AT THE

CONNECTOR PINS.

NOTES: Do not remove protective cover and shunt wire from cartridge contact pins at this time.

Do not connect electrical connector (1) at this time.

Perform steps 9 through 14 for the remaining Power Plant Firex container.

Card #: 8306 Labor Hours: 0

Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Work Card Tasks TECH INSP Step Description

T 16 Power Plant Cartridge Functional Test

NOTE: The following procedure ensures correct installation of the system electrical connectors to the associated cartridges.

WARNING: DURING TEST, CONTACT PINS OF CARTRIDGES MUST BE SHORTED OUT WITH

SHUNT WIRE AND PROTECTIVE COVERS INSTALLED. DO NOT USE FOIL TO SHUNT PINS.

a. Ensure that electrical connectors P5WF, P6WF, P7WF and P8WF from cartridges on both FIREX containers are disconnected; that contact pins of each cartridge are shunted; and that protective covers are installed.

* b. Apply external electrical power; remove tags; and close Engine Fire Extinguishing System circuit breakers.

c. On FIREX MONITOR panel, press and hold BOTTLE NO. 1 and BOTTLE NO. 2 L SQUIB/R SQUIB switch/lights. Check that L SQUIB/R SQUIB legends do not come on; then release switch/lights.

d. Remove external electrical power.

e. Remove protective covers from electrical connectors P5WF and P7WF and shunt wires from respective cartridges. Connect electrical connector P5WF to the outboard cartridge of FIREX container NO. 1 located on left side of aircraft; and connect electrical connector P7WF to the inboard cartridge of FIREX container NO. 2 located on right side of aircraft.

f. Apply external electrical power.

g. Press and hold BOTTLE NO. 1 and BOTTLE NO. 2 L SQUIB/R SQUIB switch/lights; and check that both L SQUIB legends come on, then release switch/lights.

h. Remove external electrical power.

i. Remove protective covers from electrical connectors P6WF and P8WF and shunt wires from respective cartridges; then, connect electrical connector P6WF to the inboard cartridge of FIREX container No. 1 located on left side of aircraft. Connect electrical P8WF to the outboard cartridge of FIREX container No. 2 located on right side of aircraft.

j. Apply external electrical power.

* k. Press and hold BOTTLE NO. 1 and BOTTLE NO. 2 L SQUIB/R SQUIB switch/lights. Check that all four L SQUIB/R SQUIB legends come on, then release switch/lights.

* l. Remove external electrical power.

Card #: 8306Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Card #: 8306Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

Card #: 8306Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

FIGURE 3

Card #: 8306Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

FIGURE 4

Card #: 8306Description: APU AND ENGINE FIREX CONTAINER - INSPECTION

FIGURE 5

15 (Last)

CL-600 - 8323

Card #: 8323 Labor Hours: 0

Date :

Description: 300 APU HOUR INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference PATS APU Maintenance Manual (TI4158.1-49-51) and SMM (TI4109.2-2 Chapter 5) if further information is necessary.

PARTS RETURN ALL UNUSED PARTS TO STOCK ROOM.

1 NOTE: Place all discrepancies on a non-routine card and in ILM.

T 2 Remove the APU front enclosure panel. See figure 1.

a. Visually check APU oil cooler intake and exhaust ducting, from outer aircraft skin thru APU enclosure and out the cooling air exhaust duct for proper clamping, correct installation, condition and security.

b. No duct damage or cracks are allowed.

c. Visually check the inner and outer skin aircraft skin at the cooling duct inlet and exhaust.

d. Visually check APU oil system Delta Pressure indicator. Replace filter if indicator is shown.

e. Visually check fuel system Delta Pressure indicator. Replace filter if indicator is shown.

T 3 Do the visual check of the magnetic drain plug.

a. Push in and turn the magnetic element counterclockwise to remove it from the drain plug.

b. Examine the magnetic drain plug for unwanted ferrious material. If found, refer to the GTCP36-150[RJ] Maintenance Manual.

c. Replace the preformed packing on the magnetic element.

d. Reinstall the magnetic element, push in and turn clockwise to lock.

e. Make sure there is no leak at the drain plug.

f. Check oil level and replinish as needed.

T 4 Perform a general visual inspection of the APU fuel system components, seals, lines and interface connections, within the APU enclosure, for security of installation, leaks or chafing.

Card #: 8323 Labor Hours: 0

Description: 300 APU HOUR INSPECTION

Work Card Tasks TECH INSP Step Description

T 5 CLOSE OUT:

a. Remove all tools, equipment, and unwanted materials from the work area.

b. Install APU enclosure panel. Restore aircraft as required.

T I 6 TASK SIGN OFF IN ILM:

APU S/N ____________

APU HOURS ____________(From the "ECU")

APU STARTS ____________

Enter this information in the 'ACTION' text block located in the 'Task Description' section when clearing this task card in ILM.

Card #: 8323Description: 300 APU HOUR INSPECTION

CL-600 - 8396

Card #: 8396 Labor Hours: 0

Date :

Description: VCS AFT EQUIPMENT BAY INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Aero Aire Maintenance Manual TI 4158.1-21-2, if further information is necessary.

B NOTE: Place all discrepancies on a non-routine card and in ILM.

T 1 CONDENSER PALLET ASSEMBLY INSPECTION

Gain access to the AFT equipment bay. (See Figures 1 and 2)

Visually check condenser for corrosion.

Wear on the fan impellers.

Fan blockage.

Loose or missing hardware.

Mounting flanges/brackets for damage.

Wire condition and wire terminals for security.

Lines and fittings for leaks.

placard condition.

Insulation material on evaporator for condition and security.

Air leaks in cooling circuit.

T 2 COMPRESSOR PALLET ASSEMBLY INSPECTION

Visually check compressor for corrosion.

Loose or missing hardware.

Mounting flanges/brackets for damage.

Stress cracks in pallet.

Bending or warping of pallet due to vibration.

Wire condition and wire terminals for security.

Lines and fittings for leaks.

Placard condition.

Card #: 8396Description: VCS AFT EQUIPMENT BAY INSPECTION

Card #: 8396Description: VCS AFT EQUIPMENT BAY INSPECTION

CL-600 - 9240

Card #: 9240 Labor Hours: 0

Date :

Description: AVIONICS COOLING SYSTEM FUNCTIONAL CHECK

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, 4109.2 Chapter/Section 21-27-11.

T 1 Apply external power to aircraft.

T 2 Verify the following cooling fans are operational.

PFD 1 CBP-A 134 MFD 1 CBP-A 64

PFD 2 CBP-B 115 MFD 2 CBP-B 103

RAD ALT CBP-A 34 CABIN EQUIPMENT RACK (ADF)

TCAS CBP-B 131 IRS 1 CBP-C 30

IRS 2 CBP-C 31 IRS 3 CBP-C 32

ATC XPDR 1 CBP-C 34 ATC XPDR 2 CBP-B 130

PILOT AUX FAN CBP-A 35 COPILOT AUX FAN CBP-B 133

IAPS-LT CBP-A 130 IAPS-RT CBP-B 125

T 3 Verify proper indication of a No. 1 PFD fan failure by pulling the PFD 1 FAN circuit breaker (CBP-A

134) and observing a COOL AIR FAIL annunciation on each pilot's panel and NO AIR 1 PFD on the AVIONICS COOLING panel.

T 4 Reset the fan circuit breaker and verify that all annunciations return to normal.

T 5 Verify proper indication of a No. 2 PFD fan failure by pulling the PFD 2 FAN circuit breaker (CBP-B

115) and observing a COOL AIR FAIL annunciation on each pilot's panel and NO AIR 2 PFD on the AVIONICS COOLING panel.

T 6 Reset the fan circuit breaker and verify that all annunciations return to normal.

T 7 Verify proper indication of a No. 1 MFD fan failure by pulling the MFD 1 FAN circuit breaker (CBP-A

64) and observing a COOL AIR FAIL annunciation on each pilot's panel and NO AIR 1 MFD on the AVIONICS COOLING panel.

T 8 Reset the fan circuit breaker and verify that all annunciations return to normal.

T 9 Verify proper indication of a No. 2 MFD fan failure by pulling the MFD 2 FAN circuit breaker (CBP-B

103) and observing a COOL AIR FAIL annunciation on each pilot's panel and NO AIR 2 MFD on the AVIONICS COOLING panel.

T 10 Reset the fan circuit breaker and verify that all annunciations return to normal.

Card #:…