tm 55-1520-210-pmd

TM 55-1520-210-PMD

TECHNICAL MANUAL UH-1H/V HELICOPTERPREVENTATIVE MAINTENANCEDAILY INSPECTION CHECKLIST

HEADQUARTERSDEPARTMENT OF THE ARMY

11 JANUARY 1983

Distribution Statement A: Approved for public release; distribution is unlimited.

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HeadquartersDepartment of the Army

Washington, D.C.,30 April 2009

UH-1H/V HELICOPTERPREVENTATIVE MAINTENANCEDAILY INSPECTION CHECKLIST

DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.

TM 55-1520-210-PMD, 11 January 1983, is changed as follows:

1. Remove and insert pages as indicated below. New or changed text material is indicated by a vertical bar in the margin. An illustrationchange is indicated by miniature pointing hands.

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2. Retain this sheet in front of manual for reference purposes.

TECHNICAL MANUAL

By Order of the Secretary of the Army:

GEORGE W. CASEY, JR. General, United States Army

Chief of StaffOfficial:

JOYCE E. MORROW Administrative Assistant to the

Secretary of the Army0909807

Distribution:To be distributed in accordance with the initial distribution number (IDN) 311431,

requirements for TM 55-1520-210-PMD.

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Washington, D.C.,1 AUGUST 2005

UH-1H/V AND EH-1H/X AIRCRAFTPREVENTATIVE MAINTENANCEDAILY INSPECTION CHECKLIST




Remove Pages Insert PagesA and B A and B11 and 12 11 and 12


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By Order of the Secretary of the Army:PETER J. SCHOOMAKERGeneral, United States ArmyChief of Staff

OFFICIAL:

SANDRA R. RILEYAdministrative Assistant to theSecretary of the Army

0516703

DISTRIBUTION: To be distributed in accordance with Initial Distribution Number (IDN) 311431, requirements for TM 55-1520-210-PMD.

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By Order of the Secretary of the Army:PETER J. SCHOOMAKERGeneral, United States ArmyChief of Staff

OFFICIAL:

JOEL B. HUDSONAdministrative Assistant to theSecretary of the Army

0414003

DISTRIBUTION: To be distributed in accordance with Initial Distribution Number 311431, requirements for TM 55-1520-210-PMD.

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TM 55-1520-210-PMD,11 January 1983, is changed as follows:


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By Order of the Secretary of the Army:ERIC K. SHINSEKIGeneral, United States ArmyChief of Staff

OFFICIAL:


0309203


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By Order of the Secretary of the Army:ERIC K. SHINSEKIGeneral, United States ArmyChief of Staff

OFFICIAL:


0110705


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Washington, D.C.,23 February 1996





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By Order of the Secretary of the Army:DENNIS J. REIMERGeneral, United States ArmyChief of Staff

OFFICIAL:

YVONNE M. HARRISONAdministrative Assistant to the

Secretary of the Army01311

DISTRIBUTION: To be distributed in accordance with DA Form 12-31-E, block no. 1431, PM requirements for TM 55-1520-210-PMD.

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By Order of the Secretary of the Army:GORDON R. SULLIVANGeneral, United States ArmyChief of Staff

OFFICIAL:

MILTON H. HAMILTONAdministrative Assistant to theSecretary of the Army

02248

DISTRIBUTION: To be distributed in accordance with DA Form 12-31-E, block no. 1431, requirements for TM 55-1520-210-PMD

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By Order of the Secretary of the Army:CARL E. VUONOGeneral, United States ArmyChief of Staff

OFFICIAL:

WILLIAM J. MEEHAN IIBrigadier General, United States ArmyThe Adjutant General

DISTRIBUTION: To be distributed in accordance with DA Form 12-31, PM requirements for UH-1H/UH-1V Helicopter, Utility; EH-1HHelicopter, Electronic Countermeasure; EH-1X Helicopter, Electronic Countermeasure and Intercept.

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OFFICIAL:



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OFFICIAL:



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OFFICIAL:

R. L. DILWORTHBrigadier General, United States ArmyThe Adjutant General

DISTRIBUTION:To be distributed in accordance with DA Form 12-31, PM requirements for UH-1H/UH-1V Helicopter, Utility; EH-1H Helicopter,Electronic Countermeasure; EH-1X Helicopter, Electronic Countermeasure and Intercept.

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OFFICIAL:

R. L. DILWORTHBrigadier General, United States ArmyThe Adjutant General

DISTRIBUTION:To be distributed in accordance with DA Form 12-31, PM Requirements for UH-1D/H/V/EH-1H aircraft.

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By Order of the Secretary of the Army:JOHN A. WICKHAM, JR.General, United States ArmyChief of Staff

OFFICIAL:

R. L. DILWORTHMajor General, United States ArmyThe Adjutant General

DISTRIBUTION:To be distributed in accordance with DA Form 12-31, PM requirements for UH-1H/UH-1V Helicopter, Utility; EH-1H Helicopter,Electronic Countermeasure; EH-1X Helicopter, Electronic Countermeasure and Intercept.

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By Order of the Secretary of the Army:JOHN A. WICKHAM, JR.General, United States ArmyChief of Staff

OFFICIAL:

DONALD J. DELANDROBrigadier General, United States ArmyThe Adjutant General

DISTRIBUTION: To be distributed in accordance with DA Form 12-31, PM Maintenance Requirements for UH-1D/H/V/EH aircraft.

TM 55-1520-210-PMD

LIST OF EFFECTIVE PAGES

Insert the latest changed pages in accordance with the instructions on the transmittal sheet.

NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line in the outer margin of thepage. Changes to illustrations are indicated by a letter suffix adjacent to the identification number. Added or completely revisedchapters, sections, paragraphs, tables, etc., are indicated by a vertical line by the title.

Dates of issue for original and change pages are:

Original . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 January 1983Change 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 March 1985Change 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 September 1986Change 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 June 1988Change 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 August 1988Change 5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 October 1989Change 6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 January 1990Change 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 August 1990

Change 8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 September 1992Change 9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 February 1996Change 10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 April 2001Change 11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 April 2003Change 12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 May 2004Change 13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 August 2005Change 14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 April 2009

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 30, CONSITING OF THE FOLLOWING:

Page No. *Change No. Page No. *Change No.

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*Zero in this column indicates an original page.B Change 14

*TM 55-1520-210-PMDHEADQUARTERS

DEPARTMENT OF THE ARMYWashington, D.C., 11 January 1983

UH-1H/V HELICOPTERPREVENTIVE MAINTENANCE

DAILY INSPECTION CHECKLIST

GENERAL INFORMATION AND SCOPE

WARNING: CERTAIN INSPECTIONS ARE MANDATORY SAFETY-OF-FLIGHT REQUIREMENTS, AND THE INSPECTION INTERVALSCANNOT BE EXCEEDED. IN THE EVENT THESE INSPECTIONS CANNOT BE ACCOMPLISHED AT SPECIFIED INTERVAL, THE AIR-CRAFT CONDITION STATUS SYMBOL WILL BE IMMEDIATELY CHANGED TO A RED X. THESE TYPE INSPECTION ITEMS AREPRECEDED BY “MANDATORY SAFETY-OF-FLIGHT INSPECTION ITEM.”

NOTE: INDIVIDUAL INSPECTION ITEMS CONTAINED IN THIS MANUAL ARE CONSIDERED THE MINIMUM REQUIREMENTS FORPERFORMING A DAILY INSPECTION AND MUST BE PERFORMED. THE CUMULATIVE EFFECTS OF INSPECTION DEFERRALSARE UNKNOWN AND COULD RESULT IN CATASTROPHIC FAILURE OR INCREASED MAINTENANCE AT A LATER DATE. THERE-FORE, THE USE OF SPECIAL LETTERING TO EMPHASIZE MANDATORY SAFETY-OF-FLIGHT INSPECTION ITEMS IS NOT TO BECONSTRUED AS AUTHORITY FOR DEFERRAL OF OTHER INSPECTIONS.

*This manual supersedes TM 55-1520-210-PMD, 26 July 1979, including all changes.

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1. INSPECTION REQUIREMENTS. This manual contains com-plete requirements for daily inspection for UH—1H/V aircraft. It doesnot contain instructions for repair, adjustment, or other means of rec-tifying conditions, nor does it contain instructions for troubleshootingto find causes for malfunctioning. Specific tolerances, limits, etc.,can be found in the applicable maintenance manuals. Use of the al-phabetical index in the applicable manual will facilitate locating therequired information.

2. MAINTENANCE ACTIVITIES. The inspections prescribed bythis manual will be performed at specified periods by Aviation UnitMaintenance (AVUM) activities with assistance of Aviation Interme-diate Maintenance (AVIM) and Depot Maintenance activities whenrequired.

3. GENERAL INFORMATION.

a. The inspection requirements contained herein are statedin such a manner as to establish what conditions are desired/unde-sired. Compliance with the provisions outlined herein is required inorder to assure that proper servicing has been accomplished and la-tent defects are discovered and corrected before malfunctioning orserious trouble results. Inspection requirements are arranged, asnearly as possible, according to the manner in which they will beperformed. The requirements are divided into groups under areaheadings.

b. The inspection intervals designated herein will not beexceeded except in actual operational emergencies as explainedherein. It is the commander’s responsibility to determine (on

an individual aircraft basis) when inspection intervals may be ex-ceeded. For this purpose, operational emergencies are conditions ofcombat, or conditions of disaster which necessitate flight to evacuateaircraft or personnel. When aircraft are operated beyond the normalinspection due-time because of such emergency situations, a CircledRed” X” status symbol, system, date and fault/remarks must be en-tered in Part I-Fault Information of DA Form 2408-13-1/2408-13-1-E(Aircraft Inspection and Maintenance Record) until such time as theinspection is complete. Since safety may be jeopardized when in-spections are delayed to meet emergency requirements, comman-der will assure that the aircraft status symbol reverts to a Red “X”and that delayed inspections are accomplished immediately upontermination of the actual emergency. When unusual local conditionsof environment, utilization, mission, experience of flight crew andmaintenance personnel, periods of inactivity, etc., are encountered,the maintenance officer will, at his discretion, increase the scopeand/or frequency of maintenance or inspections as necessary to en-sure safe flight.

c. This manual may contain inspection requirements applica-ble to specific equipment not installed on your aircraft. Those re-quirements should be disregarded.

d. DA Form 2408-13-1/2408-13-1-E will be used to record alldeficiencies or shortcomings discovered during the inspection.

e. A 1-½ inch space between each area of inspection is beingprovided to allow insertion of additional inspection items as requiredby local command inspection procedures.

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4. SPECIAL INSTRUCTIONS. A Preventative MaintenanceDaily inspection is accomplished after the last flight of the missionday, or prior to the first flight on the next mission day on which theaircraft is flown. The inspection consists of visual examination andoperational checks to determine that the aircraft can safety andefficiently perform the assigned mission.

5. REPORTING ERRORS AND RECOMMENDING IMPROVE-MENTS. You can help improve this manual. If you find anymistakes, or if you know a way to improve these procedures, pleaselet us know. Mail your letter or DA Form 2028 (RecommendedChanges to Publications and Blank Forms) located in the backof the applicable aircraft maintenance manual, (when using the2028 from the maintenance manual, insure that the publication

number and title refer to this PMD) directly to: Commander, USArmy Aviation and Missile Command, ATTN: AMSAM-MMC-MA-NP,Redstone Arsenal, AL 35898-5000. A reply will be furnished toyou. You may also provide DA Form 2028 information to AMCOMvia e-mail, fax, or the World wide Web. Our fax number is : DSN788-6546 or Commercial 256-842-6546. Our e-mail address is:[email protected]. Instructions for sending an electronic2028 may be found at the back of the aircraft maintenance manualimmediately preceding the hard copy 2028. For the World WideWeb use: htps://amcom2028.redstone.army.mil

6. INSPECTION AREAS. Inspection areas are shown in Figure1.

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Area No. 1 Nose Area All surfaces, components and equipment in nosecompartment and on exterior ahead of crew doors.

Area No. 2 Cabin Exterior and Landing Gear Left Side All surfaces, components, and equipment on cabinexterior and underside between forward sides of crewdoors and aft cabin walls. Includes landing gear, andforward fuel cell sump on cabin under side. Includescompartment in pylon island below main transmission.

Area No. 3 Engine Area Left Side All surfaces, components, and equipment associatedwith engine installation, located above engine work deckand within engine cowling, tailpipe fairing and intakefairing.

Area No. 4 Tailboom Area All surfaces, components and equipment located inor on the tailboom and vertical fin. Including accesscompartments below engine work deck and aft of cabinwalls.

Area No. 5 Engine Area Right Side All surfaces, components, and equipment associatedwith engine installation, located above engine work deckand within engine cowling, tailpipe fairing and intakefairing.

Area No. 6 Cabin Exterior and Landing Gear Right Side All surfaces, components, and equipment on cabinexterior and underside between forward sides of crewdoors and aft cabin walls. Includes landing gear, andforward fuel cell sumps on cabin underside. Includescompartment in pylon island below main transmission.

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Area No. 7 Upper Pylon Area All surfaces, components, and equipment of the mainrotor pylon group, from top of mast to the bottom of thetransmission mounts. Includes main rotor, mast androtating controls, transmission with accessories andmounts, and main (input) drive shaft. Includes top ofcabin surface and components.

Area No. 8 Lower Pylon Area(via Cabin Interior)and Interior Area

All surfaces, components, and equipment inside ofcabin area, between forward sides of crew doors andaft cabin walls and pylon island structure. Including allinstruments, equipment, seats, and accessories. Lowerpylon area including bottom of transmission, electricaland hydraulic components.

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PREVENTATIVE MAINTENANCE DAILY CHECKLIST

The Preventive Maintenance Daily Checklist will be accomplished following the last flight of the day or prior to the first flight on thenext day on which the aircraft is flown. The inspection consists of visual examination and operational checks to determine thatthe aircraft can safely and efficiently perform its assigned mission.

DAILY INSPECTION TOTAL WORK TIME:

Seq.No. Item and Procedure Seq.

No. Item and Procedure

NOSE AREA 1.6 Pilot’s and copilot’s tail rotor controls for visibledamage and security.

1.1 Inspect aircraft forms and records for recordeddiscrepancies (DA PAM 738-751).

1.7 Pilot’s and copilot’s windshields for condition andcleanliness.

1.2 Nose section exterior for visible damage. 1.8 Pilots and copilot’s windshield wiper blades fordeterioration and serviceability.

1.3 Nose compartment interior for cleanliness, equipmentfor visible damage and loose connections.

1.9 Pitot tube for obstructions, cleanliness (Nose mount).

1.4 Battery and connections for security, leakage andcleanliness. Vent lines for obstructions, kinking andsecurity. Nose compartment door for secure latching.

1.10 Static ports for obstructions, cleanliness (Nosemount).

1.5 Pilot’s and copilot’s chin bubbles for condition andcleanliness.

“FOD REMINDER”Check work area for tools and parts after completion of maintenance and inspection.

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CABIN EXTERIOR AND LANDING GEAR(LEFT SIDE)

sliders for damage, security, and proper operation.Check window emergency jettison handles for condition.Copper wire for condition and security.

2.1 Cabin exterior for obvious damage. Stencils and decalsfor legibility

2.6 Landing gear for damage and security, cross tube boltsmissing, broken, ground handling eyebolt loose. Crosstubes for visual indications of excess spread.

2.2 Crew door for positive latching, seals for deterioration,windows for cleanliness and condition, security ofhinges and proper operation. Check emergency jettisonhandles for condition. Copper safety wire for conditionand security.

2.7 Inspect bottom of cabin for cracks, buckles, wrinkles,and loose or missing rivets, particularly in cross tubeattaching areas.

2.3 Hinged cabin door for damage and positive latching.Windows for cracks, crazing and cleanliness.

2.8 Landing and search lights for security and condition.

2.4 Deleted.

2.9 Cargo suspension assembly for security, cleanlinessand freedom of operation of safety latch. Check manualrelease and inspect cable for wear. On nonswivelingtype, manually test hook for rotational play indicatingbroken shear pin.

2.5 Cargo doors for positive latching. Windows forcleanliness. Door retainers, rollers and

"FOD REMINDER"CHECK WORK AREA FOR TOOLS AND PARTS AFTER COMPLETION OF MAINTENANCE AND INSPECTION.

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MANDATORY SAFETYOF FLIGHT

INSPECTION ITEM

2.14 Position lights for condition, security and cracked lens.Night Fix - Phase I (NVG) position light covers forcondition

2.10 Control linkage, irreversible valves and hydrauliccylinders in fuselage below pylon for evidence ofleaks from cylinders and connecting lines, damageand security. Cyclic and collective cylinder caps(P/N 100621 or P/N 100621-1) for security by a feeltest. Tab washer tangs must be bent and in contactwith flats on the retainers. ENGINE AREA (LEFT SIDE)


INSPECTION ITEM

3.1 Engine cowling and fairing for security and damage, andloose or missing fasteners.

2.11 Check that all four bolts/screws through the servolever assembly have a self-locking castellatednut safetied with cotter pin. Check that nuts andbolts/screws as an assembly can be turned by hand.

3.2 Engine air inlet, engine accessories and connections fordamage and security. Check for fuel and oil leaks.

2.11.1 For servos P/N 205-076-056 check that control tubeservo bolt can be turned by hand

3.3 Electrical cables, ignition coil and lead; Fire DetectorAssembly for chafing, cracks and security. Check exciterbox for condition and security.

2.12 External stores installation for condition and security. 3.3.1 (Aircraft equipped with ODDS) check engine external oilfilter bypass buttons for extended indication.

2.13 M130 chaff bracket for damage and security. 3.3.2 Chip Detectors for physical security and damage (i.e.,broken wires)


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3.4 Main and starting fuel manifolds for leaks and security 3.13 M52 smoke generator nozzle for condition and security.Oil lines for condition, security and leakage.

3.5 Flow divider assembly inspect for leaks, damage andsecurity

3.6 Engine compressor housing visually for cracks,scratches, corrosion and security

3.7 Fuel control power lever for freedom of movementthrough full range to each stop

3.8 Engine mounts visually for cracks, damage and security. TAILBOOM AREA (LEFT SIDE)

3.9 Engine combustion chamber housing, exhaust diffuser,support cone, fireshield, firewall gaskets and seals, andtailpipe for cracks, dents, and burned or buckled areas.

4.1 Electrical compartments access doors for condition andsecurity. Electrical equipment for condition and security.Loose or missing rivets (interior). NOTE: Nothing is to bestored in either of these three electrical compartments.

3.10 Bleed air tubing for chafing and security 4.2 AC power receptacle, access door and caution lightswitch for security and condition

3.11 Second stage turbine blades; inspect through tailpipeand through exhaust diffuser for cracks, burns, dents ormissing blades.

4.3 DC power receptacle, access door and caution lightswitch for security and condition.

3.12 Anti-collision light for condition, security, and crackedlens


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4.4 Check oil cooler vanes for obstructions, security, anddamage. Oil cooler shield assembly for security, cracks,loose or missing rivets and corrosion.


INSPECTION ITEM4.5 Check hanger assembly, driveshaft clamps, tail pipe

drain line, heat shield and electrical wiring for conditionand security.

4.10 Remove the intermediate 42 degree gearbox coverto inspect left hand vertical spar cap. Inspectvertical fin spar and vertical fin driveshaft coverattachment channel for cracks. Cleanliness ofchain, and condition of aft cables and grommets.Inspect chain/sprocket access cover attachmentrivets for looseness and condition. Inspect for looseor missing rivets attaching the 90 degree gearboxattachment fitting.


INSPECTION ITEM


INSPECTION ITEM4.6 Tail rotor driveshaft installation for damage, foreign

materials and security of hangers, coupling clampsand covers. Inspect all tail rotor driveshaft couplingsfor grease leakage. Bearing for indication ofoverheating

4.11 Tail Rotor (90 degree) gearbox for security, oil leveland leaks. Tail rotor control installation for conditionand security.

4.7 Tail rotor driveshafts for corrosion, visible damage andmissing weights

4.11.1 Chip detectors for physical security and damage (i.e.broken wires).

4.8 Inspect tailboom, synchronized elevator and vertical finexterior skin for evidence of damage, cracks, loose ormissing rivets, and corrosion.


INSPECTION ITEM

4.9 Check for radial play condition and security ofsynchronized elevator

4.12 Tail rotor hub, tail rotor retention nut split cones andblade assembly for security and visible damage.


TM 55-1520-210-PMD Change 13 11




INSPECTION ITEM

4.17

4.18

Tailboom vent for condition and security.

Check position light for condition, security,and cracked lens.

4.13 Visually inspect tail rotor crosshead to sliderretaining bolts and nuts for security.


INSPECTION ITEM TAILBOOM AREA (RIGHT SIDE)

4.14 Visually inspect pitch change link attachment boltsand nuts for security.


INSPECTION ITEM


INSPECTION ITEM

4.19 Intermediate (42 degree) gearbox for security, oillevel, and leaks.

4.15 Using a clean soft cloth, wipe blade surface. Visuallyinspect for cracks, skin separation and otherdamage, with special attention to the area on bothsides of blade between the blade doublers and four(4) to six (6) inches (10 to 15 cm) outboard of thedoublers. Internal rattling sound heard when huband blade assembly is rotated is caused by internaldebris and is not cause for rejection.

4.19.1 Chip detectors for physical security and damage (i.e.broken wires).

4.16 Check tail skid for condition and security. 4.20 Inspect tailboom, synchronized elevator and vertical finexterior skin for evidence of damage, cracks, loose ormissing rivets, and corrosion.


TM 55-1520-210-PMD Change 9 12



4.21 Check for radial play, condition and security ofsynchronized elevator.


INSPECTION ITEM4.22 Oil cooling compartment door for security and condition.

NOTE: Nothing is to be stored in this compartment.4.26 Tailboom attach bolts visually for security and

slippage marks. Fittings for cracks. Inspectlongerons up to 12 inches from the fittings forcracks.

4.23 Battery and connections, for cleanliness and security.Vent lines for obstructions, kinking and security. Batteryshelf for security of attaching points and supportingstructure for damage and cracks.


INSPECTION ITEM

4.24 Check tail rotor control servo for leakage, condition andsecurity. Hydraulic piston wiped clean.

4.27 Tail rotor control quadrant for proper installation andcondition of cables.


INSPECTION ITEM

4.28

4.29

Heater mixing valve and airduct for condition and security.

Check muff heater system and hoses for condition andsecurity.

4.25 Oil cooler turbine blower fan blades for freemovement. Screen for obstruction, security andcondition. Supporting structure and bleed air linevisually for condition and security. Connecting link(rigid structural tube), for installation.

4.30

4.31

Heater compartment doors for condition and security.Heater compartment for condition. NOTE:Nothing is to be stored in this compartment.

Visually inspect fuel level. Check fuel cap and closedcircuit refueling hardware for condition, operation andsecurity.


TM 55-1520-210-PMD Change 4 13



ENGINE AREA (RIGHT SIDE)MANDATORY SAFETY

OF FLIGHTINSPECTION ITEM

5.1 Engine cowling and fairing for security, damage andloose or missing fasteners.

5.7 Engine oil tank for security and oil level, lines forleaks or damage. Sight gages for damaged orstained glasses.

5.1.1 Main and Start fuel manifolds for leaks and security. 5.8 Exhaust thermocouple assembly for chafing, cracks andsecurity.

5.2 Engine inlet housing, accessories and connections fordamage and security. Check for fuel and oil leaks.

5.9 Electrical cable assembly, ignition coil lead and firedetector assembly for chafing, cracks, and security.

5.3 Starter-generator intake and outlet ducts for deteriorationand security.

5.4 Engine compressor housing visually for cracks,scratches, corrosion and security.

5.5 Engine combustion chamber housing, exhaust diffuser,support cone, fireshield, firewall gaskets and seals, andtailpipe for cracks, dents, and burned or buckled areas.

5.5.1 NOTEAircraft with Infrared Heat Suppressor (IRS) only

CABIN EXTERIOR AND LANDING GEAR(RIGHT SIDE)

Check “V” clamp (clamp) that attaches the ForwardDuct Assembly (Bellmouth Assembly) to the InsulatedExhaust Duct Assembly for visible damage and security.

6.1 Cabin exterior for obvious damage. Stencils and decalsfor legibility.

5.6 Engine mounts visually for cracks, damage and security.


TM 55-1520-210-PMD Change 14 14



6.2 Crew door for positive latching, seals for deterioration,windows for cleanliness and condition, security of hingesand proper operation. Check emergency jettison handlesfor condition. Copper safety wire for condition andsecurity.

6.7 Inspect bottom of cabin for cracks, buckles, wrinkles, andloose or missing rivets, particularly in cross tubes areas.

6.3 Hinged cabin door for damage and positive latching,Windows for cracks, crazing and cleanliness.

6.8 External stores installation for condition and security.

6.4 Handholds and steps for cracks, corrosion and loosehardware. Step hinges for proper operation and security.

6.9 M130 chaff/flare bracket for damage and security.

6.5 Cargo door for positive latching. Windows for cleanliness.Door retainers, rollers and sliders for damage, securityand proper operation. Check window emergency jettisonhandles for condition. Copper wire for condition andsecurity.

6.10 Check position lights for condition, security and crackedlens. Night Fix — Phase I (NVG) position light coversfor condition.

6.6 Landing gear for damage and security, cross tube boltsmissing, broken ground handling eyebolt loose. Crosstubes for visual indications of excess spread.

UPPER PYLON AREA AND CABIN TOP

7.1 Pitot tube and static ports for obstruction and cleanliness(Roof Mount).


TM 55-1520-210-PMD Change 1 15



7.2 Cabin roof windows for cracks, crazing and cleanliness. MANDATORY SAFETYOF FLIGHT

INSPECTION ITEM

7.3 Cabin roof for damage, skin cracks, tear, and loose ormissing rivets. Skin for buckled areas. Paint for chippedor peeling condition.

7.9 Exterior of FOD screen for foreign material (grassor vegetation).

7.4 Transmission cowling for damage and security. EH-1H/XInspect alternator wires for chaffing.

7.5 Alternator air intake for damage and security.

7.6 Hydraulic reservoir for fluid level.


INSPECTION ITEM


INSPECTION ITEM7.7 Main (input) drive shaft couplings for evidence of

grease leakage, clamps for security.7.10 Non self-purging separator; intake screen and filter

for damage, obstructions and loose or missingfasteners. Check gaps between screen sections, notto exceed screen mesh width. Remove airframe (OD)screen, clean sand and dust separator; foam andmetal filters, inspect for damage.

7.8 Deleted

7.8.1 Inspect all lines, fittings and accessories on top half oftransmission for security, condition and leaks.


TM 55-1520-210-PMD Change 3 16




INSPECTION ITEM


INSPECTION ITEM

7.11 Self-purging separator: intake screen for damage,obstructions and loose or missing fasteners. Check flexhose for wear, discharge tube connections for security,and airframe (FOD) screen for damage. If

7.12 Sealant between rigid connecting link and clevis rodend. If adhesive bond is broken, remove tube assembly,inspect for corrosion and thread damage.

damaged, remove airframe (FOD) screen and top halfof airframe screen and the upper air filter assembly.INSPECT ENGINE INLET FOR FOD. Removeaccumulated residue from the overboard discharge tubeassembly.


INSPECTION ITEM


INSPECTION ITEM

7.13 Collective levers for cracks, corrosion, security andvisible damage. Bearings and bushings for excessiveplay.

7.11.1 Improved Particle Separator: Check missing, damaged,or obstructed vortex tubes, loose or missing fasteners,and evidence of parts entering the engine inlet. Ifexternal inspection indicates parts may have enteredengine inlet, remove Separator


INSPECTION ITEM

and INSPECT ENGINE INLET FOR FOD. Remove anyimpacted sand or dirt from exterior of Separator andSeparator air outlets.

7.14 Swashplate, scissors and sleeve, drive links andconnecting linkage and rod and bearings for corrosion,security and visible damage. Visually inspect control lugs(3 each) on swashplate inner rings for cracks. Inspecttrunnion bearings for radial and axial play and visuallyinspect trunnion bearing ball for cracks.


TM 55-1520-210-PMD Change 6 17




INSPECTION ITEM

7.18 Stabilizer bar connecting linkage for visible damage,security of attachment and corrosion. Pitch links and rodend bearings for play and security.

7.15 Mast and boots for visible damage, corrosion andsecurity. Visually inspect main rotor mast between hubspring support and mast plate assembly on the yoke forsurface damage. Tilt main rotor blades for maximumvisibility.

7.19 Main rotor pillow block and grip reservoirs for oil level,leakage and security; hub assembly, blade grips, pitchhorns and drag braces for visible damage and security.

7.15.1 Hub spring assembly, for security, condition, deformationand cracks in rubber bumper. NOTE

Direct particular attention to the Blade Grips in thearea Drag Brace attachment lugs for cracks.

7.16 Stabilizer dampers for full fluid level, leakage andsecurity of attachment.


INSPECTION ITEM


INSPECTION ITEM

7.20 Gain access to blades. Wipe blades upper and lowersurfaces with a clean soft cloth and inspect both surfacesand blade tip for damage, cracks and visible indicationsof voids and bond separation. Inspect for nicks and dentsin trailing edge and scarf joints for erosion and corrosion.

7.17 Stabilizer bar assembly for visible damage, corrosionand security. all pivot bolts and nuts and mounting boltsvisually for cracks and security.

7.20.1 Visually inspect composite main rotor blade for damageand security.


TM 55-1520-210-PMD Change 14 18



7.21 Cabin roof vents for obstructions and condition.

7.22 Check position lights for condition, security and crackedlens


TM 55-1520-210-PMD Change 7 18.1/(18.2 Blank)



LOWER PYLON AREA (VIA CABININTERIOR) AND INTERIOR AREA

8.5 Tachometer generator for damage and security.


INSPECTION ITEM

8.6 Hydraulic system components and lines for security,damage and evidence of leaks. Wipe clean all exposedhydraulic pistons. Hydraulic filter for appearance of redindicator button.

8.1 Transmission for security, corrosion, damage,chafing oil lines and oil leaks. Check sump for watercontamination and for oil level. External oil filterfor by-pass indication. Sight gages for damageand staining. Lift link and both attaching clevislugs on transmission for wear, cracks and properinstallation of hardware. Aircraft equipped withODDS, check physical security of debris monitorelectrical connector and condition of wires.

NOTE

If red indicator button on hydraulic modulepops before 450 hours is reached, replace fil-ter. If temperature is below 20°F (-6.7°C), allowfluid to warm up and reset button. If buttonpops again, replace filter.


INSPECTION ITEM

8.7 Output drive shaft coupling for grease leakage andsecurity.

8.2 Transmission oil line quick disconnects for excessiveplay IAW TM 55–1520-210-23

8.8 Cabin interior clean and clear of loose objects or tools.

8.3 Inspect for condition and security of transmission frictiondampers, #1 tail rotor driveshaft and all fuel and oil linesfor damage, and chaffing. Inspect for structural damage,loose and missing rivets and cracks around the resilientmounts.

8.9 First aid kits for designated location, presence ofinspection data tag, broken or missing seal and security.

8.4 Hydraulic servo cylinder mount nuts (4 each cylinder),check slippage marks.

8.10 Troop seats, seat belts and mission equipment securityinstalled or stowed.


TM 55-1520-210-PMD Change 12 19



8.11 Sound absorbing blankets securely installed with allbulkhead tiedown fittings, straps and rings outside ofblankets.

8.18 Fire extinguishers and brackets for damage and securityof installation.

8.12 Cargo tiedowns for corrosion and security. 8.19 Rifle rack bracket for damage and security.

8.13 Reinforced mounting plates (Avionics) for damage andsecurity.

8.20 All instruments for cleanliness, visible damage andproper range markings.

8.14 M52 smoke generator oil tank, oil pump and lines forvisible damage and security.

8.21 On Night Fix — Phase 1 (NVG) modified aircraft: Checklighting for corrosion and cracked or crazed lenses.Glareshield extension for security.

8.15 Crew member/mission operator seats for damage,security, and positive movement and locking in allpositions. Safety belts and shoulder harness for damage,corrosion, cuts, fraying and security. Inertia reels fordamage, security, and positive locking and unlocking.Check quick emergency release handles for security andconditions. Copper safety wire for condition and security.

8.22

8.23

Compass Correction card for availability and legibility.

Pedals checked.

8.16 Crew member/mission operator seat cushions and backcover for general condition, cuts, tears, burns, stains,fading, broken stitches and sagging.

8.24 Windshield wiper motor cover guards for cracks anddamage

8.17 Fire extinguishers for proper location and seal intact.Presence of inspection data tag (DD Form 1574)

8.25 Check circuit breakers and switches set as required.


TM 55-1520-210-PMD Change 10 20



8.26 Deleted POWER ON

1.11 Battery on, check for 24 volts.

1.12 Pitot heater for operation (Nose Mount)

2.15 Exterior lights (navigation, anticollision, landing, andsearch lights) for proper operation.

2.16 Cargo hook electrical release for operation.

2.17 Windshield wiper motor pilot/co-pilot for operation.


INSPECTION ITEM

3.14 Fuel tank sump drains for water or other contamination.(Use sample jar.) (Fuel boost pumps off.) Main fuelfilter for visual indication of clogged element condition,evidence of water in filter drain sample, leakage fromlines. (Fuel boost pumps on.)

LUBRICATION 6.11 Exterior lights (navigation, anticollision, landing, searchlights) for proper operation.

ALLAREAS

Lubricate in accordance with lubrication chart containedin Chapter 1, of TM 55-1520-210-23, applicable to thedaily requirements.

7.23 Pitot heater for operation (Roof Mount).

8.27 Caution panel lights for illumination on test switchposition.


TM 55-1520-210-PMD Change 6 21



8.28 Press to test caution/warning lights. NOTE8.29 Interior lights (dome, cockpit, instrument, console, and

pedestal lights) for proper operation.If meter indicates a multiple of 2 hours, disconnect cablecutter electrical harness connector. Check internalcondition of connector and cable cutter electricalreceptacle (especially pins) for corrosion and damage.Reconnect cable cutter electrical harness connectorafter inspection.

NOTE NOTEThe following check requires main or spare inverterpower. The copilot attitude indicator must be caged andheld momentarily when inverter power is applied.

If hoist is to be removed from aircraft install aluminumshorting strip across pins in cable cutter electricalreceptacle on hoist boom and install protective cap.

8.30 Fuel quantity indicator checked with test switch. b. Cable Cut Switch.

8.31 Engine controls for free action through full range andidle stop release.

(1) Cable cut switch on control panel for securty andcondition of rubber cover.

8.32 Deleted. NOTE

8.33 High performance hoist (if installed). Perform hoistinspections, checks and test as required in applicablehoist publications.

Do not lift up cable cut switch guard to check switchunless inspection indicates that further examination isneeded.

a. Cable Cutter Connection Check. (2) Control panel and pilot’s cable cut switch guards aredown and lockwired.

(1) Cable cutter cartridge electrical connection forsecurity and damage. c. Hook and Boom Assembly Check.

(2) Electrical connection cable for damage and fraying. (1) Hook assembly for 360 ° freedom of movement aboutcable.

(3) Hoist hour meter for reading of a multiple of 2 hours(2, 4, 6, 8, 10, etc.)


TM 55-1520-210-PMD Change 10 22



(2) Carrier assembly retainer spring clip for properinstallation.

(2) V-band clamp for installation and security.

(3) Hook quick release pin for operation and security. (3) Power cable for sealant at connector and fraying.(4) Oil level should be even with mark on sight glass (2). f. Control Panel Check.(5) Boom attachment bolts for security. (1) Exterior for visible damage and mount bolts for

security.(6) Swivel of boomhead (30° each side of vertical). (2) Aircraft position switch for security. and proper

setting.d. Winch Check. AVIONICS(1) Oil level in sight glass. Perform avionics system inspection, checks and test as

required in applicable avionics publications.(2) Gear case for leakage and visible damage. ARMAMAENT(3) High temperature sensor and sensor cable forinstallation and fraying.

Perform armament system inspections, checks and testas required in applicable Armament publications.

(4) Cable drum opening for FOD and uniform windingof cable. FORMS AND RECORDS COMPLETION

(5) Cam drive - chain guard for security and damage. Ifguard is broken, make sure that chain is not damaged.

Ascertain that all entries on forms, records and worksheets have been completed or updated and new formsinitiated as required DA PAM 738-751

(6) Limit switch drive assembly box for security anddamage.

NON-STANDARD EQUIPMENT

e. Winch Motor Check.

(1) Motor for security and visible damage.

Ascertain that all installed non-standard equipmentidentified by the applicable airworthiness release’s forthe aircraft is checked for condition, damage, security asrequired by the airworthiness releases.


TM 55-1520-210-PMD Change 14 23/(24 Blank)

By Order of the Secretary of the Army:E. C. MEYERGeneral, United States ArmyChief of Staff

OFFICIAL:

ROBERT M. JOYCEMajor General, United States ArmyThe Adjutant General

DISTRIBUTION:To be distributed in accordance with DA Form 12–31, PM Maintenance requirements for UH-1D/H and EH-1H aircraft.


TM 55-1520-210-PMD

PIN: 016803-000

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