Attachment 4-3000 LR60.pdf

60-00001 Tail # : (3000 LANDING INSPECTION) Work Order # :

Card #: 00001 Labor Hours: 0

Date :

Description: PRELIMINARY RECORDS CHECK (ALL D CHECKS)

Work Card Tasks TECH INSP Step Description

P 1 *Aircraft logbook and permanent records.

a. Review permanent records for service bulletins, MAD's, EO's, etc., that shall be accomplished on this inspection and assure that all items are on non-routine worksheets.

b. Determine the time change items (ADP run) that are due this inspection and assure that all items are recorded on non-routine maintenance worksheets.

c. Issue engine change and hot section inspection cards as applicable.

NOTE: The foregoing items may be accomplished by production controller (PC), project manager (PM), or leadman/foreman (L/F), or inspector (I) as dictated by local policy.

T 2 Check aircraft logbook and transfer all flight discrepancies and all carryover items to non-routine maintenance worksheets.

NOTE: Any discrepancy not cleared during the inspection will require quality control approval before being re-entered in the deferred discrepancy list.

NOTE: The foregoing items may be accomplished by inspector (I) or Technician (T) as dictated by local policy.

I 3a *Operations/normal checklist manuals update.

For aircraft located at Oklahoma City, Oklahoma, the inspector will remove the Operations Manual and the normal Checklist Manual from the aircraft for verification of current revision status and updating if required.

I 3b *Inspector will verify that all manuals are returned to the aircraft before next flight.

I 4 *If aircraft is assigned to a facility other than Oklahoma City, Oklahoma, the responsible facility will check the Operations Manual (TI 4040.25B), and normal Checklist Manual (TI 4040.25C) and make sure all current changes received have been inserted.

I 5 *Review interim maintenance/operations data in the alert envelope. If material has been issued to the effected manuals, remove data from the alert envelope; and, if applicable, remove related alert sticker from the logbook cover.

1 (Last)

60-2121004

Card #: 2121004 Labor Hours: 0

Date :

Description: POSITIVE VENTILATION CHECK VALVE - INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter /Section 5-10-25 and 21-31-04 if further information is necessary.

B MATERIALS AND SPECIAL TOOLS REQUIRED

Gasket P/N 5419052-4 2 ea.

Check Valve P/N 9519-1 1 ea.

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

D *List of calibrated test equipment used to perform task card.

TEST EQUIPMENT USED PART NUMBER SERIAL NUMBER

T 1 Remove electrical power from aircraft.

T 2 Open tailcone access door.

T 3 Loosen clamps securing sleeve to ram air adapter tube and air distribution duct. Remove sleeve.

T 4 Remove attaching parts securing ram air adapter tube, gaskets, and positive ventilation check valve to ram air adapter. Remove tube, gaskets, and check valve from aircraft and discard gaskets.

T 5 Remove positive ventilation check valve (See Figure 1.)

Card #: 2121004 Labor Hours: 0

Description: POSITIVE VENTILATION CHECK VALVE - INSPECTION

Work Card Tasks TECH INSP Step Description

T 6 Visually inspect positive ventilation check valve for:

a. Freedom of movement.

b. Condition of spring.

c. Flapper warpage and positive seating.

d. Foreign material buildup.

T 7 Clean check valve with MEK or equivalent.

T 8 Install positive ventilation check valve. (See Figure 1.)

NOTE: When installing previously removed positive ventilation check valve, perform a visual inspection of check valve.

T 9 Using new gaskets, position positive ventilation check valve, gaskets, and ram air adapter tube and secure with attaching parts.

CAUTION: UPON INSTALLATION OF POSITIVE VENTILATION CHECK VALVE ASSEMBLY,

ENSURE VALVE FLAPPER OPENS FORWARD, AND THAT FLAPPER HINGE IS LOCATED AT

THE TOP (AS CLOSE TO 12 O'CLOCK POSITION AS ALLOWABLE).

T 10 Position sleeve and secure with clamps. Torque clamps 20 inch-pounds (2.3 Nm) plus drag torque.

Ensure sleeve extends a minimum of 0.12-inch (3.05 mm) beyond clamp.

T 11 Restore electrical power to aircraft. (If required.)

T I 12 Okay to close __________.

Close tailcone access door.

Card #: 2121004Description: POSITIVE VENTILATION CHECK VALVE - INSPECTION

FIGURE 1

3 (Last)

60-2132030

Card #: 2132030 Labor Hours: 0

Date :

Description: CABIN CONDITIONED AIR CHECK VALVE - INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25 and 21-31-03 if further information is necessary.

B Associated Tasks

Note: For Removal and Installation of VCS Compressor/Condenser and Pallet use Task Card 8257.

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

NOTE: Inspect cabin (passenger) air check valves. The valves are located in the conditioned air ducts above the tailcone baggage compartment. (Refer to Figure 1.)

T 1 PARTS RETURN ALL UNUSED PARTS TO THE STOCKROOM

Disassemble coupling securing check valve and remove check valve from aircraft.

T 2 Remove coupling O-rings and discard.

Visually check conditioned air check valve for the following:

*a. Make sure that flapper is not damaged or warped.

*b. Make sure that the flapper has freedom of movement and the spring is serviceable.

*c. Make sure that there is no unwanted material buildup on the flapper or valve seat.

T 3 If need be, use a clean cloth moist with cleaning solvent and clean the flapper and valve seat.

T 4 Install new O-rings on conditional air check valve and air distribution ducts.

T 5 Position check valve in ducts and secure with couplings. Ensure check valve is positioned with rivets outboard and flow direction arrow pointing down.

T 6 Restore electrical power to aircraft (if required).

T 7 Perform leak check of the check valves with either the APU or engine bleed air.

NOTE: If using the engines, start and shut down the engines using the Airplane Flight Manual.

60-2132030

Card #: 2132030Description: CABIN CONDITIONED AIR CHECK VALVE - INSPECTION

2 (Last)

60-2132031

Card #: 2132031 Labor Hours: 0

Date :

Description: CABIN AND COCKPIT AIR CHECK VALVES - INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, Chapter/Section 5-10-25, 21-20-01 and 21-20-02 of the FIA LearJet SAMM, if further information is necessary.

B PARTS RETURN ALL UNUSED PARTS TO THE STOCKROOM

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

T 1 Inspection cabin air and cockpit air check valves. The valves are installed in the cabin and cockpit conditioned air ducts forward of the aft cabin pressure bulkhead.

a. Cabin valves removal.

(1) Loosen clamps securing sleeve to check valve and air distribution duct assembly. Slide sleeve forward on to duct to clear check valve.

(2) Disconnect coupling nut from check valve and remove check valve from aircraft.

(3) Remove coupling nut O-ring and discard.

b. Cockpit valve removal.

(1) Disassemble coupling securing check valve in cockpit air distribution ducting.

(2) Remove coupling retainer halves, O-rings, and check valve from air distribution ducting.

T 2 Visually inspect air check valves for:

a. Freedom of movement.

b. Condition of springs.

c. Flapper warpage and positive seating.

d. Foreign material buildup.

T 3 Clean check valves with MEK, or equivalent.

T 4 Cabin valves installation.

a. Install new O-ring on air distribution duct assembly.

b. Position cabin air check valve with rivets up and flow direction arrow pointing forward.

c. Secure check valve to duct with coupling nut. Tighten coupling nut hand-tight and safetywire.

d. Position sleeve between check valve and duct and secure with clamps.

Card #: 2132031 Labor Hours: 0

Description: CABIN AND COCKPIT AIR CHECK VALVES - INSPECTION

Work Card Tasks TECH INSP Step Description

T 5 Cockpit valve installation.

a. Install new O-rings on cockpit air distribution ducts.

b. Position cockpit air check valve between air distribution ducts.

NOTE: Ensure cockpit air check valve alignment tangs engage properly in distribution duct slots. Ensure check valve flappers open toward the downstream flow of air (allowing airflow forward to cockpit).

c. Install coupling retainer on duct and assemble coupling securing check valve in distribution ducting.

Tighten coupling hand tight and safety.

Card #: 2132031Description: CABIN AND COCKPIT AIR CHECK VALVES - INSPECTION

Card #: 2132031Description: CABIN AND COCKPIT AIR CHECK VALVES - INSPECTION

FIGURE 2

4 (Last)

60-2813011

Card #: 2813011 Labor Hours: 0

Date :

Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25 and 28-12-00 if further information is necessary.

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

List of calibrated test equipment used to perform task card.

TEST EQUIPMENT USED PART NUMBER SERIAL NUMBER

T 1 Defuel aft fuselage fuel cell and perform fuel cell static electrical bonding resistance check. (Aircraft equipped with aft fuselage fuel tank.)

WARNING: THE FUEL CELL IS CONSIDERED A CONFINED SPACE. CONFINED SPACE ENTRY

PROCEDURES DESCRIBED IN 28-00-00 MUST BE FOLLOWED WHEN PERSONNEL ENTER

THE FUEL CELL TO ENSURE PERSONNEL SAFETY.

NOTE: The internal plumbing of the fuselage fuel cell must be installed as complete as practical, while still permitting access for bond checks. Bonding jumpers and connections to aircraft plumbing outside the fuel cell must be disconnected, or the bonding measurement may be rendered invalid.

NOTE: On fuel storage system components with bonding jumpers, perform static electrical bond check first with bonding jumper disconnected, then with bonding jumper connected. This allows the checking of redundant ground paths.

NOTE: Bonding jumpers attached to fuselage structure shall not be disconnected from the fuselage.

Bonding jumpers not attached to fuselage shall remain connected at one end. No bonding jumpers shall be disconnected at both attaching points. (Leaving them partially attached will help ensure their proper reinstallation.)

T 2 Disconnect all plumbing connections and bonding jumpers to fuel cell. Cap or plug all fuel openings. (See Figure 201.)

NOTE: Provisions must be made to collect residual fuel when opening fuel lines.

T 3 Remove fuel plumbing from large access cover at LH side of fuel cell. Cap or plug all openings.

NOTE: Provisions must be made to collect residual fuel when opening fuel lines.

T 4 Remove attaching parts securing fuselage fuel cell?s large access cover to fuselage fuel cell. Remove large access cover and gaskets from aircraft. Discard gaskets.

Card #: 2813011 Labor Hours: 0

Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

Work Card Tasks TECH INSP Step Description

T 5 Remove any residual fuel from fuel cell and ventilate fuselage fuel cell using a high-volume air remover.

CAUTION: WHEN CONDUCTING RESISTANCE TESTS, DO NOT USE A SHARP TIPPED PROBE

AS IT COULD PENETRATE THE SURFACE OF THE COMPONENTS.

T 6 Attach one lead of milliohmmeter to the specified aircraft ground and perform electrical bond check on each internal component, internal section of fuel system plumbing and internal metallic object. (See Figure 201.) Resistance readings shall not exceed 1.0 ohm. Correct any discrepancies before proceeding.

T 7 NOTE: The test points shown on Figure 202, 203, 204, 205, 206, 207 and 208 are marked with a number, an arrow (e), and a letter. The numbers is a sequential designation for all test points of the test and the letter designates the ground point to be used for that particular check (i.e. Vent Valves 5 e A; measure resistance between the vent valve and ground point A.)

Connect bonding jumpers and retest each internal component, internal section of fuel system plumbing, and internal metallic object. (See Figure 201.) Resistance readings shall not exceed 1.0 ohm. Correct any discrepancies before proceeding.

T 8 Connect all external fuel plumbing connectors.

Remove air mover and, prior to closing fuel cell, visually inspect inside of cell to ensure that no wrinkles have appeared in cell, and that cell is free from foreign matter such as lint, dust or dirt, or installation materials. If wrinkles have appeared, re-distribute fuel cell within cavity to minimize the wrinkles, If cell is not thoroughly clean, it shall be cleaned with a lint-free cloth dampened with water.

T I 9 Inspector okay to close.

Install fuselage fuel cells large access cover and new gaskets, securing with attaching parts to fuselage fuel cell.

T 10 NOTE: Ensure that bonding jumper removed from large access cover is installed.

Install fuel plumbing removed from large access cover at LH side of fuel cell.

T 11 a. Restore electrical power to aircraft. (If required.)

b. Refuel aircraft as required. (Refer to Chapter 12.)

T 12 a. Check fuel plumbing for leaks.

b. Install items removed to perform this check.

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

FIGURE 2

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

FIGURE 3

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

FIGURE 4

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

FIGURE 5

Card #: 2813011Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK

FIGURE 6

8 (Last)

60-41001

Card #: 41001 Labor Hours: 0

Date :

Description: CABIN AND COCKPIT AIR CHECK VALVE INSPECTION - OPEN-UP

Work Card Tasks TECH INSP Step Description

A Ref. Maintenance Manual, Chapter/Section 25-50-01.

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

T 1 Remove electrical power from aircraft.

T 2 Remove applicable cabin baggage compartment sidewall to expose cabin air check valves between frames 26 aft and 26A and cockpit air check valve. Ref. Maintenance Manual, Chapter/Section 25-50-01.

T 3 Remove blanket covering check valve.

T I 4 Okay to close __________.

All panel and doors opened to facilitate the completion of this task. Remove all unwanted tools and equipment.

60-41003

Card #: 41003 Labor Hours: 0

Date :

Description: PASSENGER/CREW DOOR TENSION FITTINGS INSPECTION - OPEN-UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, Chapter/Sections 5-10-25 and 25-20-01 if further information is necessary.

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

T 1 Remove required upholstery and panels from upper and lower doors to gain access to the tension fittings.

60-46001

Card #: 46001 Labor Hours: 0

Date :

Description: CABIN AND COCKPIT AIR CHECK VALVE INSPECTION - CLOSE-UP

Work Card Tasks TECH INSP Step Description

T I 1a Ok to install.

Install blanket covering check valve.

T 1b Install baggage compartment sidewall.

T I 2a Install.

Install blanket covering check valve.

T 2b Install baggage compartment sidewall.

Ref. Maintenance Manual, Chapter/Section 25-50-01.

60-46003

Card #: 46003 Labor Hours: 0

Date :

Description: PASSENGER/CREW DOOR TENSION FITTINGS INSPECTION - CLOSE-UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, Chapter/Sections 5-10-25 and 25-20-01 if further information is necessary.

T I 1 Ok to install upholstery and panels on Passenger/Crew door _________.

T 2 Install upholstery and panels.

60-51001L

Card #: 51001L Labor Hours: 0

Date :

Description: HONEYCOMB SUPPORT ANGLE SEGMENTS INSPECTION - OPEN UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual chapter/section 5-10-25 if further information is necessary.

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

T 1 Remove wing to fuselage fairings.

60-51001L

Card #: 51001LDescription: HONEYCOMB SUPPORT ANGLE SEGMENTS INSPECTION - OPEN UP

60-51001R

Card #: 51001R Labor Hours: 0

Date :

Description: HONEYCOMB SUPPORT ANGLE SEGMENTS INSPECTION - OPEN UP

Work Card Tasks TECH INSP Step Description

T 1 Remove wing to fuselage fairings.

60-51001R

Card #: 51001RDescription: HONEYCOMB SUPPORT ANGLE SEGMENTS INSPECTION - OPEN UP

60-51002

Card #: 51002 Labor Hours: 0

Date :

Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK - OPEN-UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual chapter/sections 5-10-25 and 28-12-00 if further information is necessary.

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

T 1 Remove electrical power from aircraft.

WARNING: OBSERVE ALL SAFETY PRACTICES DESCRIBED IN 28-00-00. SPECIAL CARE

SHALL BE TAKEN TO PROPERLY VENTILATE THE FUEL CELL WHILE PERFORMING

STATIC ELECTRICAL BOND CHECK.

T 2 Remove tailcone baggage compartment partitions, wing fairings and other panels as required to gain outside access to fuselage fuel cell components and plumbing.

T 3 Defuel fuselage fuel cell.

60-5210030

Card #: 5210030 Labor Hours: 0

Date :

Description: PASSENGER/CREW DOOR TENSION FITTINGS INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25 and 52-10-17 and NDI Manual Chapter/Sections 52-10-01 and 53-10-01 if further information is necessary.

B List of calibrated test equipment used to perform task card.

TEST EQUIPMENT USED PART NUMBER SERIAL NUMBER

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

T 1 a. Removal of the Upper and Lower Door Adjustable Tension Fittings and Tension Plates.

b. Remove the bolts that attach the upper and lower tension plates to the forward and aft fuselage door structure and remove the tension plates.

NOTE: When removing the tension plates, note the plate locations.

T 2 Loosen the jamnut and remove the adjustable tension fittings from the forward and aft door frame.

NOTE: When removing the adjustable tension fittings, it is recommended to count the number of turns it takes to remove each adjustable tension fitting from the door frame and note each location.

T RII 3 a. Magnetic partial inspect for cracks.(Reference to Part 6, Chapter 52-10-01 and 53-10-01 of the NDI Manual.)

b. Inspect structure for corrosion.

T RII 4 Installation of the Upper and Lower Door Adjustable Tension Fittings and Tension Plates.

NOTE: You can use equivalent alternatives for these items: Use absorbent Cloth (clean and oil free), used with cleaning solvent.

Use cleaning Solvent (Commercially Available) to clean the mating surfaces, to remove excess Loctite.

Use locitie RC680 to secure parts.

a. Perform inspection of upper and lower door adjustable tension fittings and tension plates.

b. Wipe tension fitting and plate areas clean with a clean cloth dampened in cleaning solvent.

Wipe tension fitting and plate areas dry with a clean, lint-free cloth. Do not allow solvent to dry on surface.

c. Align the correct tension plates with the mating holes on the inboard and outboard upper and lower fuselage door structure. Install and tighten bolts on the tension plates.

Card #: 5210030 Labor Hours: 0

Description: PASSENGER/CREW DOOR TENSION FITTINGS INSPECTION

Work Card Tasks TECH INSP Step Description

T 5 Install the adjustable tension fittings and jamnuts into the door frame.

T RII 6 Adjust the upper and lower tension fittings, tension plates and shear plates.

WARNING: MAKE SURE ALL PERSONNEL ARE CLEAR OF THE DOOR WHEN YOU ADJUST

THE UPPER DOOR TORSION ASSEMBLY.

NOTE: Final adjustments should be conducted with the aircraft wings full of fuel and approximately 2000 - 3000 lbs. of fuel in the fuselage tank.

NOTE: necessary tools and equipment. You can use equivalent alternatives for these items:

1. Use Loctite RC680 to secure the jamnut.

2. Use torque wrench (commercially available) to torque the jamnuts.

a. Close the door and examine each adjustable tension fitting to make sure that it is centered in the tension plate.

b. Loosen the jamnut of the adjustable tension fittings that are not centered fore and aft in the tension plate.

c. Turn the adjustable tension fitting clockwise or counterclockwise to center it in the tension plate. Loctite the jamnut and torque to 310 (±10) inch-pounds.

d. Loosen the bolts that secure the tension plate for adjustable tension fittings that are not centered inboard or outboard.

T RII 7 a. Close the door and rotate the door handle to extend the latch pins into the shear plates. Check each pin as it is extended into its shear plate for correct alignment. Pins must not rub or drag.

b. When the adjustment of the door is complete, open and close the door and extend and retract the latch pins several times to make sure that they are properly adjusted and aligned.

c. The maximum load applied to the inside upper door handle to lock and unlock the door, must not exceed 25 pounds.

T 8 Remove all tools, equipment, and unwanted materials from the work area.

Card #: 5210030Description: PASSENGER/CREW DOOR TENSION FITTINGS INSPECTION

3 (Last)

60-5321020

Card #: 5321020 Labor Hours: 0

Date :

Description: AFT PRESSURE BULKHEAD VISUAL INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, Chapter/Section 5-10-25 and 25-50-01 if further information is necessary.

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

T 1 Visually inspect aft pressure bulkhead for evidence of fatigue cracks, working fasteners, corrosion, and general condition.

T 2 Tap-test floor panel, which supports the electrical equipment, to check for unbonding of upper surface plates from the honeycomb core structure.

T 3 Visually inspect for corrosion, particularly in the area of the threaded inserts. Check for loose threaded inserts and any other damage to floor panel. Removal of all electrical equipment mounted to floor panel is required.

T 4 Remove all tools, equipment, and unwanted materials from the work area.

60-5321020

Card #: 5321020Description: AFT PRESSURE BULKHEAD VISUAL INSPECTION

60-5321040

Card #: 5321040 Labor Hours: 0

Date :

Description: HONEYCOMB SUPPORT ANGLE SEGMENTS INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual, Chapter/Section 5-10-25 if further information is necessary.

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

T 1 With wing/fuselage fairings removed, use flashlight and mirror to visually inspect the honeycomb support angle segments at the outboard ends of the divan seat floor and forward baggage floor for fatigue cracks, corrosion, fastener security, and general condition.

T 2 Inspect all accessible components, lines, control cables and attachments, pulleys, and electrical installations for leaks, chafing, wear, condition, and security.

T 3 Inspect all accessible structure, keel structure, and skin for cracks, corrosion, loose fasteners, and cleanliness.

T 4 Remove all tools, equipment, and unwanted materials from the work area.

60-5323162

Card #: 5323162 Labor Hours: 0

Date :

Description: LONGITUDINAL AND CIRCUMFERENTIAL SKIN SPLICES EXTERNAL INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Section 5-10-25 if further information is necessary.

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

T 1 Externally visually inspect longitudinal and circumferential skin splices for the following:

a. Cracks.

b. Working rivets.

c. Corrosion.

d. General condition.

I 2 Confirm suspect condition with supporting x-rays. (Ref. NDI Manual, Chapter 53, Part 2.)

T 3 Remove all tools, equipment, and unwanted materials from the work area.

60-56001L

Card #: 56001L Labor Hours: 0

Date :

Description: HONEYCOMB SUPPORT ANGLE SEGMENT INSPECTION - CLOSE-UP

Work Card Tasks TECH INSP Step Description

T 1 Ok to install wing to fuselage fairings.

T 2 Install wing to fuselage fairings.

60-56001R

Card #: 56001R Labor Hours: 0

Date :

Description: HONEYCOMB SUPPORT ANGLE SEGMENT INSPECTION - CLOSE-UP

Work Card Tasks TECH INSP Step Description

T 1 Ok to install wing to fuselage fairings.

T 2 Install wing to fuselage fairings.

60-56002

Card #: 56002 Labor Hours: 0

Date :

Description: AFT FUEL CELL STATIC ELECTRICAL BONDING RESISTANCE CHECK - CLOSE-UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25 and 28-12-00 if further information is necessary.

T 1 Ok to install tailcone baggage compartment partitions, wing fairings, and other panels removed to gain outside access to fuselage fuel cell components and plumbing. Restore aircraft to normal.

T 2 Install tailcone compartment partitions, wing fairings, and panels.

60-5710065

Card #: 5710065 Labor Hours: 0

Date :

Description: NDI INSPECT TRUNNION FITTINGS

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Section 5-10-25 if further information is necessary.

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

B List of calibrated test equipment used to perform task card.

TEST EQUIPMENT USED PART NUMBER SERIAL NUMBER

I 1 Complete task on both Left and Right sides. Eddy current inspection areas D and E around fasteners common to trunnion fittings in accordance with NDI manual Part 3, 57-12-01.

60-5710065

Card #: 5710065Description: NDI INSPECT TRUNNION FITTINGS

60-5750047

Card #: 5750047 Labor Hours: 0

Date :

Description: FLAP VISUAL AND NDI INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25, 5-10-29 and 27-50-01 if further information is necessary.

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

B List of calibrated test equipment used to perform task card.

TEST EQUIPMENT USED PART NUMBER SERIAL NUMBER

T 1 Remove flap from wing and visually inspect the flap support structure for security, corrosion, fatigue cracks, wear, evidence of interference, and general condition.

T 2 Visually inspect the flap sector and supporting bracketry for evidence of overload or fatigue cracks.

T 3 a. Visually inspect the flap surface for permanent deformation, corrosion, cracks in skin, unusually heavy chafing, and other wear or interference indication.

b. Use a light source and a 10X magnification and visually inspect the flap track attachment fittings/area for overload or fatigue cracks.

T 4 Visually inspect the nose roller support structure and the actuator pushrod attachment area for similar discrepancies.

T 5 Visually check all bearings, bushings, and rollers for looseness, roughness, seizure, or wear.

I 6 Remove flap tracks and pushrod from flap assembly and magnetic particle inspect for cracks in accordance with NDI Part 6, 57-70-01 and 57-71-01.

I 7 Eddy current inspect flap track attach fittings for fatigue cracks in accordance with NDI Part 3, 57-40-01.

T RII 8 Re-install the flap.

T 9 Remove all tools, equipment, and unwanted materials from the work area.

60-5750047

Card #: 5750047Description: FLAP VISUAL AND NDI INSPECTION

60-81001

Card #: 81001 Labor Hours: 0

Date :

Description: CABIN CONDITIONED AIR CHECK VALVES - OPEN-UP

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25 and 21-31-03 if further information is necessary.

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

T 1 Remove electrical power from aircraft.

T 2 Open tailcone baggage door and gain access to conditioned air check valves through baggage compartment ceiling panel.

T I 3 Okay to close __________.

All panel and doors opened to facilitate the completion of this task. Remove all unwanted tools and equipment.

60-83003

Card #: 83003 Labor Hours: 0

Date :

Description: AIR DISTRIBUTION CHECK VALVES - INSPECTION

Work Card Tasks TECH INSP Step Description

A Reference Maintenance Manual Chapter/Sections 5-10-25, 21-60-00 and 21-60-10 if further information is necessary.

PARTS RETURN ALL UNUSED PARTS TO THE STOCKROOM

B NOTE: Removal and installation procedure for both cockpit and cabin air distribution check valves are identical.

T 1 Remove air distribution check valves as follows: (See Figure 1.)

a. Remove electrical power from aircraft.

b. Open tailcone access door.

c. Remove batteries from aircraft.

d. Remove attaching parts, gaskets, and air distribution check valve from duct. Discard old gaskets.

e. Visually check air duct flanges.

T 2 Install air distribution check valves as follows: (See Figure 1.)

a. Using new gaskets, position gaskets and air distribution check valve and secure with attaching parts. Ensure flappers open in the forward direction.

b. Install batteries in aircraft. (Refer to Chapter 24.)

c. Restore electrical power to aircraft (if required).

T 3 * Perform operational check of temperature control system. May be complied with inconjunction with Lear task card 0526, if issued.

T 4 * Start left or right aircraft engine or APU. (Refer to the appropriate FAA Approved Airplane Flight Manual.

T 5 * Ensure at least one Bleed Air source is switched ON.

T 6 * With Air Ducts Pressurized perform a leak check on the Air Distribution Check Valves.

Card #: 83003 Labor Hours: 0

Description: AIR DISTRIBUTION CHECK VALVES - INSPECTION

Work Card Tasks TECH INSP Step Description

T 7 * Set the Cabin Control Mode Switch to MAN.

Rotate Cabin Temperature Selector full clockwise to HOT position. Cabin temperature control valve indicator shall move to full HOT position and cabin temperature control valve shall more to full open position.

T 8 * If cabin temperature control valve indicator does not indicate full HOT, perform temperature control valve indicator adjustment. (Refer to Adjustment/Test, Lear Green Sheet Supplement, Chapter/Section 21-60-00.)

T 9 * Rotate Cabin Temperature Selector full counterclockwise to COLD position. Cabin temperature control valve indicator shall move to full COLD position and cabin temperature control valve shall move to full closed position.

T 10 * If cabin temperature control valve indicator does not indicate full COLD, perform temperature control valve indicator adjustment. (Refer to Adjustment/Test, Lear Green Sheet Supplement, Chapter/Section 21-60-00.)

T 11 * Set Crew Control Mode Switch to MAN position.

T 12 * Rotate Crew Temperature Selector full clockwise to HOT position. Crew temperature control valve indicator shall move to full HOT position and cockpit temperature control valve shall move to full open position.

T 13 * If crew temperature control valve indicator does not indicate full HOT, perform temperature control valve indicator adjustment. (Refer to Adjustment/Test, Lear Green Sheet Supplement, Chapter/Section 21-60-00.)

T 14 * Rotate Crew Temperature Selector full counterclockwise to COLD position. Crew temperature control valve indicator shall move to full COLD position and cockpit temperature control valve shall move to full closed position.

T 15 * If crew temperature control valve indicator does not indicate full COLD, perform temperature control valve indicator adjustment. (Refer to Adjustment/Test, Lear Green Sheet Supplement, Chapter/Section 21-60-00.)

T 16 * Set Cabin Control Mode Switch to AUTO.

NOTE: With temperature control system in automatic mode and interior aircraft temperature beyond 70 deg. to 90 deg. F (21 deg. to 32 deg. C) range, temperature control valves may move in one direction only.

For example, a cold interior will allow temperature control valves to open but not close.

T 17 * Rotate Cabin Temperature Selector full clockwise to HOT position. Cabin temperature control valve indicator shall move to full HOT position and cabin temperature control valve shall move to full open position.

Card #: 83003 Labor Hours: 0

Description: AIR DISTRIBUTION CHECK VALVES - INSPECTION

Work Card Tasks TECH INSP Step Description

T 18 * Rotate Cabin Temperature Selector full counterclockwise to COLD position. Cabin temperature control valve indicator shall move to full COLD position and cabin temperature control valve shall move to full closed position.

T 19 * Set Crew Control Mode Switch to AUTO.

T 20 * Rotate Crew Temperature Selector full clockwise to HOT position. Crew temperature control valve indicator shall move to full HOT position and cockpit temperature control valve shall move to full open position.

T 21 * Rotate Crew Temperature Selector full counterclockwise to COLD position. Crew temperature control valve indicator shall move to full COLD position and cockpit temperature control valve shall move to full closed position.

T 22 * Set CREW and CABIN controls to mid range and toggle switches to AUTO.

T 23 * Shut down aircraft engine or APU. (Refer to the appropriate FAA Approved Airplane Flight Manual.)

Card #: 83003Description: AIR DISTRIBUTION CHECK VALVES - INSPECTION

4 (Last)

60-86001

Card #: 86001 Labor Hours: 0

Date :

Description: CABIN CONDITIONAL AIR CHECK VALVE - CLOSE-UP

Work Card Tasks TECH INSP Step Description

T 1 Okay to install.

Baggage compartment ceiling panel.

T 2 Close tailcone baggage compartment door.

T 3 Install.

Baggage compartment ceiling panel. (Reference Maintenance Manual, Chapter/Section 25-50-05.)

T 4 Close tailcone baggage compartment door.