MPC_32014.1.pdf

U.S. COAST GUARD

ASSET COMPUTERIZED MAINTENANCE SYSTEM

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REV'D 07/25/13

ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 1

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323001 REM/INST ACTUATOR MAIN LANDING GEAR LH 65-3212-001

SCHEDULED UNSCHEDULED

P A R T

O F F

ACTUATOR MAIN GEAR SERIAL NO.

PART NO.

REASON REMOVED: TIME___ TROUBLE___ CANNIBALIZATION___ OTHER___ COMPONENT STATUS: RFI__ NON RFI__

TECHNICIAN'S TECHNICIAN'S QUALITY ASSURANCE

SIGNATURE ID SIGNATURE

P A R T

O N

ACTUATOR MAIN GEAR SERIAL NO.

PART NO.

TECHNICIAN'S TECHNICIAN'S QUALITY ASSURANCE

SIGNATURE ID SIGNATURE

* ASTERISK INDICATES QA REQUIRED *QA(1) *QA(2) *QA(3) *QA(4) *QA(5)

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS INDICATING THE REASON FOR REMOVAL ARE REQUIRED

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

Distribution Statement D: Distribution authorized to the DHS/CG/DoD and their contractors Administrative/Operational use, 07/25/13. Other requests shall be referred to the appropriate asset product line.

WARNING: This document contains technical data whose export is restricted by the Arms Export-Control Act (Title 22, U.S.C., Sec 2751, et. seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C. App 2401 et. seq. Violations of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5200.22-M, National Industrial Security Program Operating Manual, Section 5-705 or DoD 5200.1-R, Information Security Program Regulation, Chapter VI, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

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ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 1

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323002 REM/INST ACTUATOR MAIN LANDING GEAR RH 65-3212-001

SCHEDULED UNSCHEDULED

P A R T

O F F

ACTUATOR MAIN GEAR SERIAL NO.

PART NO.

REASON REMOVED: TIME___ TROUBLE___ CANNIBALIZATION___ OTHER___ COMPONENT STATUS: RFI__ NON RFI__

TECHNICIAN'S TECHNICIAN'S QUALITY ASSURANCE

SIGNATURE ID SIGNATURE

P A R T

O N

ACTUATOR MAIN GEAR SERIAL NO.

PART NO.

TECHNICIAN'S TECHNICIAN'S QUALITY ASSURANCE

SIGNATURE ID SIGNATURE

* ASTERISK INDICATES QA REQUIRED *QA(1) *QA(2) *QA(3) *QA(4) *QA(5)

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS INDICATING THE REASON FOR REMOVAL ARE REQUIRED

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

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ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 2

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323020 REPLACE ROD END MAIN LANDING GEAR ACTUATOR 65-3212-001

SCHEDULED UNSCHEDULED

PART POSITION LEFT

ACTUATOR SERIAL NO.

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS:

TECHNICIAN'S

SIGNATURE

TECHNICIAN'S

ID

* ASTERISK INDICATES QA REQUIRED QA

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

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ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 2

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323020 REPLACE ROD END MAIN LANDING GEAR ACTUATOR 65-3212-001

SCHEDULED UNSCHEDULED

PART POSITION RIGHT

ACTUATOR SERIAL NO.

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS:

TECHNICIAN'S

SIGNATURE

TECHNICIAN'S

ID

* ASTERISK INDICATES QA REQUIRED QA

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

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ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 3

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323030 INSPECT MAIN LANDING GEAR ACTUATOR 65-3212-001

SCHEDULED UNSCHEDULED

This card is used to report maintenance performed on this

MLG ACTUATOR SERIAL NO.

PART POSITION LEFT

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS:

TECHNICIAN'S

SIGNATURE

TECHNICIAN'S

ID

* ASTERISK INDICATES QA REQUIRED *QA(6) *QA(7)

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

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ASSET NUMBER OPERATING ACTIVITY MAINTENANCE ACCOMPLISHED MAINTENANCE DUE

DATE ASSET HOURS DATE ASSET HOURS

MO DAY YEAR MO DAY YEAR

ZULU DATE ZULU TIME

MO DAY YEAR

AIRCRAFT LANDINGS

SERIAL NUMBER TRACKED ITEM-ALL INFORMATION REQUIRED

ITEM 3

DUE

CMS CODE ACTION DESCRIPTION CEINUM

323030 INSPECT MAIN LANDING GEAR ACTUATOR 65-3212-001

SCHEDULED UNSCHEDULED

This card is used to report maintenance performed on this

MLG ACTUATOR SERIAL NO.

PART POSITION RIGHT

MAN HOURS: AMT___.___ AET___.___ AST___.___ PDM___.___ OTHER___.___

REMARKS:

TECHNICIAN'S

SIGNATURE

TECHNICIAN'S

ID

* ASTERISK INDICATES QA REQUIRED *QA(6) *QA(7)

REVIEWED

BY

LOG YN DATA

ENTRY

COMPLETED

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1 MAIN LANDING GEAR ACTUATOR, REMOVAL/INSTALLATION

REFERENCES:

MPC 00GCP.0

MPC 07102.1

MPC 08001.1

MPC 32008.2

TOOLS/TEST EQUIPMENT:

DC External Power Source External Hydraulic Power Source Hydraulic Hand Pump Micro Level Torque Wrench, 0 to 150 inch-pounds Torque Wrench, 0 to 1325 inch-pounds Wrench, P/N 366-TL-004-01 (2 each)

EXPENDABLES:

Cotter Pin, P/N 23310CA030035 Lockwasher, P/N 950-345 Safety Wire, P/N MS20995C32 (0.032-inch)

CONSUMABLES:

Corrosion Preventive Compound, COR-BAN 27L Degreasing Solvent, MIL-PRF-680 (Series), Type III Grease, MIL-PRF-81322 (Series) Insulating Varnish, Synthite AC-46 Sealing Compound, MIL-PRF-81733 (Series)

A PRELIMINARY STEPS (Refer to Figure 1)

1. Jack aircraft (Refer to MPC 07102.1).

2. Level aircraft (Refer to MPC 08001.1).

3. Ensure electrical and hydraulic powers are secured on aircraft.

4. Remove panel covering auxiliary flotation bottle and electrical connectors (1 and 2).

5. Prior to removal, complete the following if actuator is being reinstalled (Refer to Figure 1).

a. Inspect for play in upper mounting point bearing (16), permissible play is 0.07 to 0.93 mm.

b. Inspect for excessive play at attachment point of landing gear strut assembly (11) to actuating cylinder rod end bearing (6) by exerting pressure from front to rear of strut assembly (18). Check axial play of rod end bearing (6) by exerting pressure side to side on actuating cylinder piston rod (19).

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B REMOVAL (Refer to Figure 1)

NOTE: Unless otherwise specified, place all removed hardware in parts bag for reuse.

1. Disconnect electrical connectors (1 and 2) from the airframe structure inside the wheel well.

2. Disconnect three hydraulic lines (3, 4, and 5) from airframe structure inside the wheel well. Cap all hy-draulic lines and fittings with protective plugs.

3. Disconnect bonding braid from actuating cylinder by removing bolt and washer.

4. Disconnect actuating cylinder piston rod end (6) at strut housing (11) by removing cotter pin (7), nut (8), and washers (9 and 10) (Refer to Figure 1, Detail B). Discard cotter pin and place remaining hardware in parts bag.

5. While supporting actuating cylinder remove safety wire from upper attachment bolt (15 ). Straighten tab on lockwasher (14) and remove bolt (15) (Refer to Figure 1, Detail A).

6. Remove actuating cylinder (18) from airframe structural fitting (17) inside wheel well.

C INSTALLATION (Refer to Figure 1)

NOTE: Locate and note the serial number of the component to be installed for annotation on the appropriate MPC.

1. Prior to installation run an hourly (non-calendar in COGNOS) Maintenance Due List against the actuator being installed to ensure rod end replacement is not due. If due, replace rod end (Refer to Item 2 of this

MPC).

WARNING

DEGREASING SOLVENT, MIL-PRF-680 (SERIES), ALL TYPES,

IS FLAMMABLE. KEEP AWAY FROM ALL SOURCES OF

IGNITION AND OXIDIZERS. AVOID INHALATION, EYE, AND

SKIN CONTACT. USE IN WELL-VENTILATED AREA. USE

OF NITRILE GLOVES RECOMMENDED, AND USE OF EYE

PROTECTION REQUIRED. WASH THOROUGHLY AFTER

USE.

2. Before installation of the actuating cylinder, clean airframe structural fitting (17) and fitting on landing gear strut housing (11) with Degreasing Solvent, MIL-PRF-680 (Series), Type III.

WARNING

AVOID EYE OR PROLONGED SKIN CONTACT WITH GREASE,

MIL-PRF-81322 (SERIES) (REPLACES MIL-G-3545) OR

AEROSHELL 22. WASH THOROUGHLY AFTER HANDLING.

3. Check condition of bores and pins. Check for wear, cracks, corrosion, or presence of sealant around bushings. Generously fill the gaps between the upper ball fitting and swivel bushings with Grease, MIL- PRF-81322 (Series) (Refer to Figure 2).

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WARNING

AVOID EYE OR SKIN CONTACT WITH SEALING COMPOUND,

MIL-PRF-81733 (SERIES). AVOID INGESTION. WASH

THOROUGHLY AFTER HANDLING.

4. Prior to installing actuator, ensure actuator upper ball fitting assembly is completely sealed at cup nut (20) and upper ball fitting (16) seams with Sealing Compound, MIL-PRF-81733 (Series), seal as necessary to prevent water intrusion (Refer to Figure 2).

WARNING

AVOID EYE AND SKIN CONTACT WITH CORROSION

PREVENTIVE COMPOUND, COR-BAN 27L. WEAR CHEMICAL

SAFETY GLASSES OR GOGGLES AND PROTECTIVE

GLOVES. MAY CAUSE IRRITATION TO THE EYES AND SKIN.

PROLONGED OR REPEATED EXPOSURE TO THE SKIN MAY

CAUSE DERMATITIS. AVOID INHALATION AND INGESTION.

USE WITH ADEQUATE VENTILATION. INGESTION MAY

CAUSE NAUSEA. WASH HANDS THOROUGHLY WITH SOAP

AND WATER AFTER HANDLING.

5. Install upper end of actuating cylinder (18) in structural fitting (17). Coat bolt (15) with Corrosion Preventive Compound, COR-BAN 27L, and install bolt (15) with new lockwasher (14), P/N 950-345. Torque bolt to 89 to 132 inch-pounds. Fold down tab of lockwasher (14) around bolt (15) and safety wire with 0.032-inch safety wire (Refer to Figure 1, Detail A).

* QA REQUIRED (1)

6. Install actuating cylinder rod end (6) on landing gear strut housing (11) as follows: Coat shaft of mount-ing point on strut housing (11) with Corrosion Preventive Compound, COR-BAN 27L, install washer (10) ensuring beveled side faces rod end (6). Install rod end (6) of actuating cylinder, washer (9), ensuring beveled side faces rod end and nut (8) (Refer to Figure 1, Detail B). Do not tighten at this time.

NOTE: Ensure actuating cylinder is fully extended.

7. Position micro level on chrome leading edge of oleo shock strut, adjust actuating cylinder piston rod at rod end bearing (6) to obtain proper strut assembly (11) angle. Final angle must be within the 90 ± 30 minute (90 ± 0.5 degree) range.

* QA REQUIRED (2)

WARNING

AVOID EYE OR SKIN CONTACT WITH HYDRAULIC

FLUID, MIL-PRF-83282 (SERIES). AVOID INHALATION AND

INGESTION. WASH THOROUGHLY AFTER HANDLING.

8. Connect extension and retraction hydraulic lines (3 and 4) to hydraulic hand pump. Retract landing gear strut assembly and ensure tire clearance in wheel well is 42 mm (1.653 inches or greater) (Refer to Figure 3, Item J2). Adjusting rod end (6) as required to achieve clearance.

9. Check the clearance between brake line flexible hose (2) and emergency flotation gear line (1) as follows (Refer to Figure 4):

a. With landing gear retracted ensure clearance between brake line flexible hose (2) and emergency flotation gear line (1) is equal to or greater than 5 mm (0.197 inches).

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b. If clearance is less than 5 mm (0.197 inches), adjust the actuator rod end (Refer to Figure 1, Item

6) to position the landing gear strut angle (Refer to Figure 3) between 90 + 20 minutes (90 + 0.333 degrees) and 90 + 30 minutes (90 + 0.5 degrees).

c. If clearance is still less than 5 mm (0.197 inches) adjust position of adel clamp on the emergency flotation gear line (Refer to Figure 4, Item 1) to obtain clearance.

* QA REQUIRED (3)

d. Extend landing gear to down and locked position.

10. Disconnect hydraulic hand pump.

WARNING

AVOID EYE OR SKIN CONTACT WITH SEALING COMPOUND,

MIL-PRF-81733 (SERIES). AVOID INGESTION. WASH

THOROUGHLY AFTER HANDLING.

11. Using wrench, P/N 366-TL-004-01, tighten rod end (6) on actuating cylinder with locknut (12). Prior to torquing, bend one tab of the lockwasher (13) into one of the slots of the actuator piston. Torque to 708 inch-pounds. If necessary, increase torque up to 885 inch-pounds to align lockwasher tab (13) with notches in nut (12). Bend one tab into one of the slots on nut (12). Apply a light coat of Sealing Compound, MIL-PRF-81733 (Series), to the rod end/locknut/piston interface area (Refer to Figure 1, Detail C).

12. Tighten nut (8) and torque to 89 to 110 inch-pounds. Install new cotter pin (7), P/N 23310CA030035.

* QA REQUIRED (4)

13. Coat bolt thread, nut (8), and cotter pin (7) with Sealing Compound, MIL-PRF-81733 (Series).

14. Clean, inspect, preserve, and install electrical connectors (1 and 2) (Refer to MPC 00GCP.0).

WARNING

INSULATING VARNISH, SYNTHITE AC-46 OR VERNELEC

43022 (MEETS MIL-I-24092 SPEC), IS FLAMMABLE. KEEP

AWAY FROM ALL SOURCES OF IGNITION. AVOID EYE

AND SKIN CONTACT. USE IN WELL-VENTILATED AREA.

AVOID BREATHING VAPORS. WASH THOROUGHLY AFTER

HANDLING.

15. Connect bonding braid to actuating cylinder with bolt and washer. Coat connection with Insulating Varnish, Synthite AC-46.

WARNING

AVOID EYE OR SKIN CONTACT WITH HYDRAULIC

FLUID, MIL-PRF-83282 (SERIES). AVOID INHALATION AND

INGESTION. WASH THOROUGHLY AFTER HANDLING.

16. Connect hydraulic lines (3, 4, and 5) to airframe structure fittings in wheel well.

17. Install panel covering auxiliary flotation bottle and electrical connectors (1 and 2).

18. Dry actuator piston with clean, lint-free cloth.

19. Wipe actuator piston with clean, soft cloth moistened with Hydraulic Fluid, MIL-PRF-83282 (Series).

* QA REQUIRED (5)

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D OPERATIONAL CHECK

NOTE: During operational check, check for hydraulic leaks at all hy-draulic connections in the main landing gear area.

1. Perform operational check IAW MPC 32008.2.

E FINAL STEP

1. Secure electrical power and remove from aircraft.

2. Remove aircraft from jacks (Refer to MPC 07102.1)

WARNING

AVOID EYE OR SKIN CONTACT WITH HYDRAULIC

FLUID, MIL-PRF-83282 (SERIES). AVOID INHALATION AND

INGESTION. WASH THOROUGHLY AFTER HANDLING.

3. Secure hydraulic power source to secondary system and disconnect from aircraft.

4. Check fluid level in secondary hydraulic reservoir, service as necessary with Hydraulic Fluid, MIL-PRF- 83282 (Series).

5. Record maintenance action by completing appropriate sign-off, adding pertinent remarks.

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2 ROD END MAIN LANDING GEAR ACTUATOR, REPLACE

REFERENCES:

NONE

TOOLS/TEST EQUIPMENT:

Wrench, P/N 366-TL-004-01 (2 each)

EXPENDABLES:

Lockwasher, P/N 19737

CONSUMABLES:

Corrosion Preventive Compound, COR-BAN 27L

A PRELIMINARY STEP

NOTE: Actuator rod end may be replaced with actuator attached to airframe structural fitting (19).

1. Remove main landing gear actuator or disconnect rod end from main landing strut (Refer to Item 1, step 1 A 1. through step 1 B 6. of this MPC).

B REMOVAL (Refer to Figure 1)

1. Remove actuator rod end (6) as follows (Refer to Figure 1, Detail B):

a. Remove sealant from lockwasher (13) and bend locking tabs out.

b. Using wrench, P/N 366-TL-004, loosen jam nut (12).

c. Remove rod end (6), noting number of turns, from actuator. Discard lockwasher (13), retain jam nut

(12) in parts bag.

C INSTALLATION (Refer to Figure 1)

WARNING

AVOID EYE AND SKIN CONTACT WITH CORROSION

PREVENTIVE COMPOUND, COR-BAN 27L. WEAR CHEMICAL

SAFETY GLASSES OR GOGGLES AND PROTECTIVE

GLOVES. MAY CAUSE IRRITATION TO THE EYES AND SKIN.

PROLONGED OR REPEATED EXPOSURE TO THE SKIN MAY

CAUSE DERMATITIS. AVOID INHALATION AND INGESTION.

USE WITH ADEQUATE VENTILATION. INGESTION MAY

CAUSE NAUSEA. WASH HANDS THOROUGHLY WITH SOAP

AND WATER AFTER HANDLING.

1. Coat threads on rod end (6) with Corrosion Preventive Compound, COR-BAN 27L. Install nut (12) and new lockwasher (13), P/N 19737, on rod end and thread into actuator piston noting the number of turns recorded in step 2 B 1.c. Do not tighten at this time.

D FINAL STEP

1. Install main landing gear actuator or reconnect rod end to main landing strut (Refer to Item 1 , step 1 C 1.

through step 1 E 5. of this MPC).

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3 MAIN LANDING GEAR ACTUATING CYLINDER INSPECTION

REFERENCES:

CGTO 1H-65C-2-1

MPC 32008.2

TOOLS/TEST EQUIPMENT:

Nonmetallic Scraper

EXPENDABLES:

Lockwasher, P/N 19737 (2 each)

CONSUMABLES:

Chemical Conversion Coating, MIL-DTL-81706 (Series) Class 1A (Alodine 1201) or Class 3 (Alodine 600) Corrosion Preventive Compound, COR-BAN 27L Degreasing Solvent, MIL-PRF-680 (Series), Type III Isopropyl Alcohol, TT-I-735 (Series) Sealing Compound, MIL-PRF-81733 (Series)

A PRELIMINARY STEPS

1. Remove main landing gear actuator (Refer to Item 1).

2. Remove actuator rod end (Refer to Item 2, steps 2 B 1.a. through 2 B 1.c.).

B INSPECT MAIN LANDING GEAR ACTUATING CYLINDERS (Refer to Figure 1)

NOTE: The following steps are identical for both the right-hand and left-hand MLG actuators.

NOTE: Unless otherwise specified, place all removed hardware in parts bag for reuse.

WARNING

DEGREASING SOLVENT, MIL-PRF-680 (SERIES), ALL TYPES,

IS FLAMMABLE. KEEP AWAY FROM ALL SOURCES OF

IGNITION AND OXIDIZERS. AVOID INHALATION, EYE, AND

SKIN CONTACT. USE IN WELL-VENTILATED AREA. USE

OF NITRILE GLOVES RECOMMENDED, AND USE OF EYE

PROTECTION REQUIRED. WASH THOROUGHLY AFTER

USE.

1. Clean main landing gear actuators with Degreasing Solvent, MIL-PRF-680 (Series), Type III.

WARNING

KEEP ISOPROPYL ALCOHOL, TT-I-735 (SERIES), AWAY

FROM ALL SOURCES OF IGNITION. AVOID CONTACT

WITH SKIN OR EYES. AVOID INHALATION OR INGESTION.

ISOPROPYL ALCOHOL MAY DAMAGE SOME FORMS OF

PLASTICS, ALUMINUM, RUBBER, AND COATINGS.

2. Utilizing a non-metallic scraper, remove sealant beads from upper ball fitting attachment cup nut (20) and actuator upper ball fitting (16) (Refer to Figure 2). Clean area using Isopropyl Alcohol, TT-I-735 (Series).

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3. Inspect upper attachment ball fitting (16) and nut (20) for visual evidence of corrosion and/or cracks. Pay close attention to where the nut contacts the ball fitting assembly base and lock wire locations. Evidence of intergranular exfoliation, pitting, or a visual crack of the nut (20) and/or upper ball fitting assembly (16) is reason for rejection/removal of the actuator. Actuators with minor surface corrosion (less than 0.05 mm) may be lightly sanded and may remain in service as long as all evidence of corrosion is removed.

* QA REQUIRED (6)

WARNING

CHEMICAL CONVERSION COATING, MIL-DTL-81706

(SERIES), CLASS 1A (ALODINE 1201) OR CLASS 3

(ALODINE 600), IS HIGHLY REACTIVE. DO NOT MIX WITH

OXIDIZABLE MATERIALS SUCH AS CLOTH, PAPER, AND

WOOD. WHEN MIXING SOLUTIONS, ADD ACID TO WATER,

NOT WATER TO ACID. CONTACT WITH POWDER CAN

CAUSE SEVERE SKIN AND EYE BURNS, SKIN ULCERS.

IF ANY LIQUID OR POWDER CONTACTS SKIN OR EYES,

IMMEDIATELY FLUSH AFFECTED AREA THOROUGHLY WITH

WATER. AVOID INGESTION. DO NOT INDUCE VOMITING.

DILUTE BY DRINKING WATER. AVOID INHALATION. USE

IN WELL-VENTILATED AREA. REMOVE CONTAMINATED

CLOTHING IMMEDIATELY. WASH THOROUGHLY AFTER

USE.

4. If paint was removed, clean areas of bare metal to a break-free surface and apply Chemical Conversion Coating, Alodine 600 or Alodine 1201, MIL-DTL-81706 (Series), Class 1A OR Class 3.

WARNING

AVOID EYE OR SKIN CONTACT WITH SEALING COMPOUND,

MIL-PRF-81733 (SERIES). AVOID INGESTION. WASH

THOROUGHLY AFTER HANDLING.

5. Apply sealant MIL-PRF-81733 to seams of actuator upper ball fitting (16) and nut (20) (Refer to Figure 2).

6. Prime and paint areas requiring touch up as well as the ball fitting attachment nut sealed seams.

7. Inspect landing gear downlock/uplock microswitch assemblies (21 and 23) as follows (Refer to Figure 1):

a. Ensure safety wire securing attaching cover bolts is intact.

b. Inspect attaching clamps (22) securing wiring to actuating cylinder (18) for condition and security.

c. Inspect condition of wiring protective cover. No cracks allowed in protective cover.

d. Inspect electrical connectors (1 and 2) and airframe receptacles for corrosion, condition, and security.

8. Inspect flexible hydraulic lines (3, 4, and 5) for cracks, leakage, chafing, swelling, excessive bending, twisting, corrosion, condition, and security.

9. Inspect rigid hydraulic line (24) for cracks, leakage, chafing, corrosion, condition, and security.

NOTE: Leakage at the piston rod is cause for actuator replacement.

Seepage is acceptable; refer to CGTO 1H-65C-2-1, Chapter 29-00- 00, for definition of terms.

10. Inspect actuating cylinder piston rod (19) for scratches, debris, absence of chrome, and corrosion. Inspect for hydraulic leakage at piston rod seal.

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11. Inspect rod end and actuator piston bore for corrosion and condition. Light surface corrosion that can be removed with a wire brush is allowable. However, any pitting or reduction in thread height is cause for rejection. Replace rod end and/or actuator if corrosion limits are exceeded.

* QA REQUIRED (7)

WARNING

AVOID EYE AND SKIN CONTACT WITH CORROSION

PREVENTIVE COMPOUND, COR-BAN 27L. WEAR CHEMICAL

SAFETY GLASSES OR GOGGLES AND PROTECTIVE

GLOVES. MAY CAUSE IRRITATION TO THE EYES AND SKIN.

PROLONGED OR REPEATED EXPOSURE TO THE SKIN MAY

CAUSE DERMATITIS. AVOID INHALATION AND INGESTION.

USE WITH ADEQUATE VENTILATION. INGESTION MAY

CAUSE NAUSEA. WASH HANDS THOROUGHLY WITH SOAP

AND WATER AFTER HANDLING.

12. Coat threads of rod end (6) with Corrosion Preventive Compound, COR-BAN 27L. Install nut (12) and new lockwasher (13), P/N 19737, on rod end (6) and thread into actuator piston noting the number of turns recorded in step 2 B 1.c. (Refer to Figure 1, Detail B). Do not tighten at this time.

13. Inspect landing gear actuator swivel bearing for corrosion and condition. If corrosion is suspected or swivel bearing is loose, contact SRR Tech Services.

C FINAL STEPS

1. Install actuator (Refer to Item 1).

2. Record maintenance action by completing appropriate sign-off, adding pertinent remarks.

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MAIN LANDING GEAR

Figure 1

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MLG ACTUATOR UPPER BALL FITTING ASSEMBLY

Figure 2

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MLG CLEARANCE CHECK

Figure 3

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MLG LINE CLEARANCE

Figure 4

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