Attachment 5-MLG INSP 6000.pdf
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- REQUEST FOR OFFER/SIR: Learjet 60 Scheduled Maintenance Checks Federal contract opportunity
- Solicitation number
- 6973GH-19-R-00077
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60-00001 Tail # : (MAJOR LANDING GEAR 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)
60-01003
Card #: 01003 Labor Hours: 0
Date :
Description: PRE-INSPECTION CHECKLIST FOR MAJOR LANDING GEAR INSPECTION OPEN-UP
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual Chapter/Section 5-10-26 if further information is necessary.
B *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
T 1 Defuel the aircraft. Reference procedures listed in chapter/section 12-10-10 of the Learjet white pages if necessary.
T 2 Place aircraft on jacks
T 3 Remove the nose gear, nose gear actuator and both main gears and actuators.
NOTE: Check the Component Removal Inquiry for associated landing gear components requiring replacement at this time.
60-06003
Card #: 06003 Labor Hours: 0
Date :
Description: PRE-INSPECTION CHECKLIST FOR MAJOR LANDING GEAR INSPECTION CLOSE-UP
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual Chapter/Section 5-10-26 if further information is necessary.
RII 1 Visually check the landing gears, actuators, and associated components for installation.
T 2 Prior to closing the landing gear area check to make sure all non-routine cards have been cleared.
T 3 Remove aircraft from jacks.
T 4 Refuel aircraft as necessary.
60-21001
Card #: 21001 Labor Hours: 0
Date :
Description: NOSE LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 and 32-21-00 if further information is necessary.
B NOTE: Place all discrepancies on a non-routine card and in ILM.
T 1 *Place aircraft on jacks. (Per the Learjet Maintenance Manual Chapter/Section 7-10-00)
*NOTE: BEFORE JACKING AIRCRAFT AND BEFORE LOWERING AIRCRAFT MAKE SURE ALL
TOOLS, EQUIPMENT, AND TAIL STAND (IF USED) ARE REMOVED.
T 2 WARNING: BEFORE PERFORMING THE FOLLOWING MAINTENANCE PRACTICES, ENSURE
THAT BATTERY SWITCHES ARE OFF AND THAT EXTERNAL POWER AND BOTH
BATTERIES ARE DISCONNECTED. ELECTRICAL SHORTING COULD CAUSE BODILY HARM
AND EQUIPMENT DAMAGE.
Remove electrical power from aircraft.
T 3 Depressurize hydraulic system by pumping brakes.
T 4 Disconnect door pushrod from nose gear strut.
T 5 Disconnect nose gear actuator from nose gear strut.
T 6 An electrical connector, installed on nose wheel box, connects nose gear steering wiring to aircraft wiring.
Disconnect electrical connector and remove wiring clamps as necessary to allow removal of nose gear strut.
Card #: 21001 Labor Hours: 0
Description: NOSE LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
T 7 WARNING: REMOVAL OF TRUNNION PINS RELEASES THE NOSE GEAR FROM THE
AIRCRAFT. ADEQUATE SUPPORT MUST BE GIVEN TO THE GEAR TO PREVENT IT FROM
FALLING AND CAUSING BODILY INJURY TO PERSONNEL AND/OR STRUCTURAL DAMAGE
TO THE AIRCRAFT.
Remove right and left bolts from nose gear trunnion. Insert a small punch into slot (lower side of trunnion) and slide trunnion pins inboard (toward strut) until free from nose gear strut bearing assemblies and remove strut from aircraft.
NOTE: When strut trunnion pins are slid out of nose gear strut bearing assemblies, the shims (if any) will be released. Retain these shims (if serviceable) for reinstallation of nose gear strut. To ensure proper strut and actuator alignment, reinstall shims in their original position.
Card #: 21001Description: NOSE LANDING GEAR REMOVAL - NDI
FIGURE 1
3 (Last)
60-22001
Card #: 22001 Labor Hours: 0
Date :
Description: NOSE LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 and 32-21-00 if further information is necessary.
B *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
T I 1 Ok to install nose landing gear.
T RII 2a Install nose gear shock strut. (See Figure 201.)
Prior to installation of nose gear shock strut, inspect trunnion pins and bearings for general condition.
(See Figure 202.)
NOTE: Ensure those pins and bearings that do not meet specifications are replaced.
NOTE: For information pertaining to nose gear trunnion pin bearing replacement, refer to Approved Repairs, this section.
NOTE: If nose wheel steering position sensors were disturbed then comply with Adj/Test procedures in 32-50.
T RII 2b Position strut in aircraft and install previously removed shims (in their original position) between nose gear strut and nose gear strut bearing assemblies. This will ensure that strut will be properly aligned to allow attachment of actuator to strut. Using a punch inserted into trunnion slot, position trunnion pins into bearing plates.
T RII 2c Install trunnion pin bolt through trunnion and trunnion pin and secure with nut.
T 2d Connect electrical connector and replace wiring clamps.
T RII 2e Attach actuator to nose gear strut.
Card #: 22001 Labor Hours: 0
Description: NOSE LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
T RII 2f Connect door pushrod to strut.
T 2g Connect aircraft batteries.
T RII 2h Check nose gear rigging.
T 2i Pressurize hydraulic system. Cycle gear, checking for proper gear indication and operation.
T 2j Service nose shock strut.
T 2k Check complete installation, proper indication, operation and rigging.
T 2l Remove aircraft from jacks. (Per the Learjet Maintenance Manual Chapter/Section 7-10-00)
NOTE: BEFORE LOWERING AIRCRAFT MAKE SURE ALL TOOLS, EQUIPMENT, AND TAIL
STAND (IF USED) ARE REMOVED.
Card #: 22001Description: NOSE LANDING GEAR - INSTALLATION
Card #: 22001Description: NOSE LANDING GEAR - INSTALLATION
FIGURE 2
4 (Last)
60-61001L
Card #: 61001L Labor Hours: 0
Date :
Description: MAIN LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 and 32-11-00 if further information is necessary.
B NOTE: Place all discrepancies on a non-routine card and in ILM.
PARTS RETURN ALL UNUSED PARTS TO THE STOCKROOM
T 1 *Place aircraft on jacks Per the Learjet Maintenance Manual Chapter/Section 7-10-00, and extend the flaps and spoilers.
*NOTE: BEFORE JACKING AIRCRAFT AND BEFORE LOWERING AIRCRAFT MAKE SURE ALL
TOOLS, EQUIPMENT, AND TAIL STAND (IF USED) ARE REMOVED.
T 2 Remove electrical power from aircraft and depressurize hydraulic system.
T 3 Remove main gear actuator and remove clamps securing electrical wiring and hydraulic hoses to gear strut.
T 4 Remove Squat Switch and landing light from strut and tie them to aircraft structure out of the immediate work area. This will eliminate the cutting and splicing of electrical wiring.
Remove nut and bolt attaching outboard door link to strut.
T 5 CAUTION: DO NOT REMOVE THE LARGE AND SMALL ELBOW FITTINGS FROM BRAKE
ASSEMBLY HOUSINGS.
Disconnect hydraulic brake hoses from brake assemblies. Cap lines and plug ports in brakes.
T 6 Loosen clamps securing brake hose support assembly and remove hydraulic lines and support assembly from main gear strut. Tie hydraulic lines and support assembly to structure out of the immediate work area.
NOTE: If desired, wheels may be removed at this point and brakes may be removed at this point. If wheel and brake removal is performed, provide protection for axle and identify brake assemblies as to position on aircraft.
Card #: 61001L Labor Hours: 0
Description: MAIN LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
T 7 Remove anti-skid transducer, identify and disconnect (unsolder) anti-skid electrical wiring from applicable anti-skid transducer electrical connectors.
a. Store anti-skid transducer electrical connector with anti-skid transducer.
b. Remove seal from anti-skid transducer electrical wiring at hub entry hole and remove electrical wiring from axle. Tie anti-skid transducer wiring to structure out of the immediate work area.
T 8 Remove access door, inboard of gear hinge point, on spar 7 to gain access to aft trunnion pin.
T 9 Remove bolt from aft side of trunnion, releasing switch striker.
WARNING: REMOVAL OF AFT TRUNNION PIN RELEASES THE MAIN GEAR FROM THE
AIRCRAFT. ADEQUATE SUPPORT MUST BE GIVEN THE GEAR TO PREVENT IT FROM
FALLING AND CAUSING BODILY INJURY TO PERSONNEL OR STRUCTURAL DAMAGE TO
THE AIRCRAFT.
T 10 Provide protection for plumbing in vicinity of aft trunnion pin. Remove round access cover located on aft side of spar 8. This access cover is located on wing spar 8 just below inboard end of spoiler and is secured by six screws.
T 11 Screw an AN8-20 bolt into aft trunnion pin.
T 12 NOTE: Proper alignment (strut support) of aft trunnion pin to strut fitting will allow easier pin removal.
The aft trunnion pin may be removed by pulling on bolt while wiggling strut. If aft trunnion pin cannot be removed by hand, position aft trunnion pin removal tool through round access hole in spar 8 and over bolt head.
T 13 Extract trunnion pin by alternately using aft trunnion pin removal tool and prying on trunnion pin lip.
NOTE: As aft trunnion pin is removed, shims will be released. Be sure to retain shims for reinstallation.
T I 14 Inspect friction surfaces of trunnion pins and support bushings for out of round or abnormal wear.
Replace if necessary.
Card #: 61001LDescription: MAIN LANDING GEAR REMOVAL - NDI
60-61001R
Card #: 61001R Labor Hours: 0
Date :
Description: MAIN LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 and 32-11-00 if further information is necessary.
B NOTE: Place all discrepancies on a non-routine card and in ILM.
PARTS RETURN ALL UNUSED PARTS TO THE STOCKROOM
T 1 *Place aircraft on jacks Per the Learjet Maintenance Manual Chapter/Section 7-10-00. And extend the flaps and spoilers.
*NOTE: BEFORE JACKING AIRCRAFT AND BEFORE LOWERING AIRCRAFT MAKE SURE ALL
TOOLS, EQUIPMENT, AND TAIL STAND (IF USED) ARE REMOVED.
T 2 Remove electrical power from aircraft and depressurize hydraulic system.
T 3 Remove main gear actuator and remove clamps securing electrical wiring and hydraulic hoses to gear strut.
T 4 Remove Squat Switch and landing light from strut and tie them to aircraft structure out of the immediate work area. This will eliminate the cutting and splicing of electrical wiring.
Remove nut and bolt attaching outboard door link to strut.
T 5 CAUTION: DO NOT REMOVE THE LARGE AND SMALL ELBOW FITTINGS FROM BRAKE
ASSEMBLY HOUSINGS.
Disconnect hydraulic brake hoses from brake assemblies. Cap lines and plug ports in brakes.
T 6 Loosen clamps securing brake hose support assembly and remove hydraulic lines and support assembly from main gear strut. Tie hydraulic lines and support assembly to structure out of the immediate work area.
NOTE: If desired, wheels may be removed at this point and brakes may be removed at this point. If wheel and brake removal is performed, provide protection for axle and identify brake assemblies as to position on aircraft.
Card #: 61001R Labor Hours: 0
Description: MAIN LANDING GEAR REMOVAL - NDI
Work Card Tasks TECH INSP Step Description
T 7 Remove anti-skid transducer, identify and disconnect (unsolder) anti-skid electrical wiring from applicable anti-skid transducer electrical connectors.
a. Store anti-skid transducer electrical connector with anti-skid transducer.
b. Remove seal from anti-skid transducer electrical wiring at hub entry hole and remove electrical wiring from axle. Tie anti-skid transducer wiring to structure out of the immediate work area.
T 8 Remove access door, inboard of gear hinge point, on spar 7 to gain access to aft trunnion pin.
T 9 Remove bolt from aft side of trunnion, releasing switch striker.
WARNING: REMOVAL OF AFT TRUNNION PIN RELEASES THE MAIN GEAR FROM THE
AIRCRAFT. ADEQUATE SUPPORT MUST BE GIVEN THE GEAR TO PREVENT IT FROM
FALLING AND CAUSING BODILY INJURY TO PERSONNEL OR STRUCTURAL DAMAGE TO
THE AIRCRAFT.
T 10 Provide protection for plumbing in vicinity of aft trunnion pin. Remove round access cover located on aft side of spar 8. This access cover is located on wing spar 8 just below inboard end of spoiler and is secured by six screws.
T 11 Screw an AN8-20 bolt into aft trunnion pin.
T 12 NOTE: Proper alignment (strut support) of aft trunnion pin to strut fitting will allow easier pin removal.
The aft trunnion pin may be removed by pulling on bolt while wiggling strut. If aft trunnion pin cannot be removed by hand, position aft trunnion pin removal tool through round access hole in spar 8 and over bolt head.
T 13 Extract trunnion pin by alternately using aft trunnion pin removal tool and prying on trunnion pin lip.
NOTE: As aft trunnion pin is removed, shims will be released. Be sure to retain shims for reinstallation.
T I 14 Inspect friction surfaces of trunnion pins and support bushings for out of round or abnormal wear.
Replace if necessary.
Card #: 61001RDescription: MAIN LANDING GEAR REMOVAL - NDI
60-62001L
Card #: 62001L Labor Hours: 0
Date :
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Sections 5-10-26 and 32-11-00 if further information is necessary.
B *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
T 1 Leadman, ok to install main landing gear.
T 2 Install main gear shock strut. (See Figure 1)
If forward trunnion pin was removed from shock strut, install and secure with nut and bolt.
T 3 Screw an AN8-20 bolt temporarily into aft trunnion pin to assist in aft trunnion pin installation.
T 4 Raise shock strut and insert forward trunnion pin into forward trunnion bearing.
T 5 Align shock strut with aft trunnion fitting, place shims on aft trunnion pin, and insert aft trunnion pin from aft side of spar 7, through the aft trunnion fitting. Place same number of shims as previously removed on aft trunnion pin (between aft trunnion fitting and strut).
T 6 Insert aft trunnion pin through aft trunnion fitting into shock strut, ensuring that shims are still in place and not damaged.
T 7 Align bolt hole in aft trunnion pin with hole in shock strut and temporarily install attaching trunnion pin bolt. Check tolerances as shown in Figure 1, Detail A.
T 8 Remove trunnion pin bolt and align hole in switch striker with hole aligned in step 2.f. Insert trunnion pin bolt through switch striker, shock strut, and trunnion pin and secure with nut.
Card #: 62001L Labor Hours: 0
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
T 9 Remove AN8-20 bolt from aft trunnion pin.
T I 10 Okay to close _________.
Install access door on spars 7 and 8.
T 11 CAUTION: IF REMOVED, INSTALL WHEELS AND BRAKES AT THIS POINT. REFER TO
32-40-02, REMOVAL/ INSTALLATION FOR WHEELS, AND 32-41-01, REMOVAL/
INSTALLATION FOR BRAKES.)ENSURE THAT BRAKE ASSEMBLIES ARE INSTALLED IN
THEIR PROPER LOCATION.
Install brake hydraulic hoses and clamps on main gear strut and connect hoses to brake ports. Bleed brake system.
T 12 Connect anti-skid electrical wiring.
a. Untie anti-skid electrical wiring from aircraft structure and route through entry hole in hub.
b. Identify wires and solder to anti-skid electrical wiring connector.
T 13 Install anti-skid transducer.
T 14 CAUTION: ENSURE HUB ENTRY HOLE IS SEALED TO PREVENT MOISTURE ENTRY.
Seal anti-skid electrical wiring at entry hole in hub.
a. Use Pro-Seal 890 to seal entry hole.
b. On Aircraft 60-015 and Subsequent, ensure fire sleeve is sealed at both ends. If needed, used Red RTV to seal fire sleeve. (Refer to Chapter 20)
T 15 Attach outboard door link to main gear strut and secure with bolt and nut.
T 16 Install main gear Squat Switch and landing light.
Restore electrical power to aircraft.
T 17 Adjust Squat Switch and install clamps securing electrical wiring to gear strut.
T RII 18 Install main gear actuator.
Card #: 62001L Labor Hours: 0
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
T 19 Service main gear shock strut.
T RII 20 Pressurize hydraulic system. Cycle gear while checking for proper gear indication and operation.
T 21 Check for proper clearance of landing light, hydraulic hoses, wiring and clamps.
T RII 22 Check main gear rigging.
T RII 23 Perform anti-skid functional test, landing gear retraction/extension check, and landing gear freefall/emergency brake, and blowdown check.
T 24 Remove aircraft from jacks. (Per the Learjet Maintenance Manual Chapter/Section 7-10-00)
NOTE: BEFORE LOWERING AIRCRAFT MAKE SURE ALL TOOLS, EQUIPMENT, AND TAIL
Card #: 62001LDescription: MAIN LANDING GEAR - INSTALLATION
60-62001R
Card #: 62001R Labor Hours: 0
Date :
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Sections 5-10-26 and 32-11-00 if further information is necessary.
B *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
T 1 Leadman, ok to install main landing gear.
T 2 Install main gear shock strut. (See Figure 1)
If forward trunnion pin was removed from shock strut, install and secure with nut and bolt.
T 3 Screw an AN8-20 bolt temporarily into aft trunnion pin to assist in aft trunnion pin installation.
T 4 Raise shock strut and insert forward trunnion pin into forward trunnion bearing.
T 5 Align shock strut with aft trunnion fitting, place shims on aft trunnion pin, and insert aft trunnion pin from aft side of spar 7, through the aft trunnion fitting. Place same number of shims as previously removed on aft trunnion pin (between aft trunnion fitting and strut).
T 6 Insert aft trunnion pin through aft trunnion fitting into shock strut, ensuring that shims are still in place and not damaged.
T 7 Align bolt hole in aft trunnion pin with hole in shock strut and temporarily install attaching trunnion pin bolt. Check tolerances as shown in Figure 1, Detail A.
T 8 Remove trunnion pin bolt and align hole in switch striker with hole aligned in step 2.f. Insert trunnion pin bolt through switch striker, shock strut, and trunnion pin and secure with nut.
Card #: 62001R Labor Hours: 0
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
T 9 Remove AN8-20 bolt from aft trunnion pin.
T I 10 Okay to close _________.
Install access door on spars 7 and 8.
T 11 CAUTION: IF REMOVED, INSTALL WHEELS AND BRAKES AT THIS POINT. REFER TO
32-40-02, REMOVAL/ INSTALLATION FOR WHEELS, AND 32-41-01, REMOVAL/
INSTALLATION FOR BRAKES.)ENSURE THAT BRAKE ASSEMBLIES ARE INSTALLED IN
THEIR PROPER LOCATION.
Install brake hydraulic hoses and clamps on main gear strut and connect hoses to brake ports. Bleed brake system.
T 12 Connect anti-skid electrical wiring.
a. Untie anti-skid electrical wiring from aircraft structure and route through entry hole in hub.
b. Identify wires and solder to anti-skid electrical wiring connector.
T 13 Install anti-skid transducer.
T 14 CAUTION: ENSURE HUB ENTRY HOLE IS SEALED TO PREVENT MOISTURE ENTRY.
Seal anti-skid electrical wiring at entry hole in hub.
a. Use Pro-Seal 890 to seal entry hole.
b. On Aircraft 60-015 and Subsequent, ensure fire sleeve is sealed at both ends. If needed, used Red RTV to seal fire sleeve. (Refer to Chapter 20)
T 15 Attach outboard door link to main gear strut and secure with bolt and nut.
T 16 Install main gear Squat Switch and landing light.
Restore electrical power to aircraft.
T 17 Adjust Squat Switch and install clamps securing electrical wiring to gear strut.
T RII 18 Install main gear actuator.
Card #: 62001R Labor Hours: 0
Description: MAIN LANDING GEAR - INSTALLATION
Work Card Tasks TECH INSP Step Description
T 19 Service main gear shock strut.
T RII 20 Pressurize hydraulic system. Cycle gear while checking for proper gear indication and operation.
T 21 Check for proper clearance of landing light, hydraulic hoses, wiring and clamps.
T RII 22 Check main gear rigging.
T RII 23 Perform anti-skid functional test, landing gear retraction/extension check, and landing gear freefall/emergency brake, and blowdown check.
T 24 Remove aircraft from jacks. (Per the Learjet Maintenance Manual Chapter/Section 7-10-00)
NOTE: BEFORE LOWERING AIRCRAFT MAKE SURE ALL TOOLS, EQUIPMENT, AND TAIL
Card #: 62001RDescription: MAIN LANDING GEAR - INSTALLATION
60-73010L
Card #: 73010L Labor Hours: 0
Date :
Description: MAIN LANDING GEAR PILLAR ATTACHMENT - NDI
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 if further information is necessary.
B NOTE: Place all discrepancies on a non-routine card and in ILM.
C *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
I *1 Inspect inboard attachment of main gear actuator for security, looseness, overload indications, and fatigue cracks. The pillar attachments to spars 7 and 8 are to be specifically inspected for discrepant conditions.
Pillar removal is required to facilitate definitive inspection.
I *2 Magnetic particle inspect pillar. (Refer to Part 6, Chapter 32, of the NDI Manual.)
60-73010R
Card #: 73010R Labor Hours: 0
Date :
Description: MAIN LANDING GEAR PILLAR ATTACHMENT - NDI
Work Card Tasks TECH INSP Step Description
A Reference Maintenance Manual, Chapter/Section 5-10-26 if further information is necessary.
B NOTE: Place all discrepancies on a non-routine card and in ILM.
C *List of calibrated test equipment used to perform task card.
TEST EQUIPMENT USED PART NUMBER SERIAL
NUMBER
I *1 Inspect inboard attachment of main gear actuator for security, looseness, overload indications, and fatigue cracks. The pillar attachments to spars 7 and 8 are to be specifically inspected for discrepant conditions.
Pillar removal is required to facilitate definitive inspection.
I *2 Magnetic particle inspect pillar. (Refer to Part 6, Chapter 32, of the NDI Manual.)
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