*TM 1-15201-1520-237237-PMS PMS TECHNICAL TECHNICAL MANUAL MANUAL
PREVENTIVE MAINTENANCE SERVICES
40-H 40-HOUR OUR INSPE INSPECTI CTION ON CHECK CHECKLIS LIST T FOR
UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS
* This This manual manual superse supersedes des TM 1-15 1-1520-2 20-237-P 37-PMS, MS, dated dated 17 April April 2006, 2006, includi including ng all change changes. s. DISTRIBUTION DISTRIBUTION STATE STATEMENT MENT D: – Distribution authorized to the DOD and DOD contractors only to protect critical technology effective as of 15 June 2003. Other requests must be referred to Commander, US Army Aviati Aviation on and Missile Missile Comman Command, d, ATTN: SFAE-A SFAE-AVV-UH/L UH/L,, Redsto Redstone ne Arsenal Arsenal,, AL 35898-5 35898-5000 000.. WARNIN WARNING G – This This docume document nt contain contains s technic technical al datawhose export export is restrict restricted ed by the Arms Export Export Control Control Act (Title22, (Title22, U.S.C. U.S.C. Sec. Sec. 2751 2751 et seq.) seq.) or the Export Export Admini Administra stratio tion n Act of 1979, 1979, as amende amended, d, Title Title 50, U.S.C., U.S.C., App. App. 2401 et seq. seq. Violatio Violation n of these these export export laws laws are subjec subjectt to severe severe crimin criminal al penalt penalties ies.. Dissemina Disseminate te in accordan accordance ce with provisi provisions ons of DOD Directiv Directive e 5230.2 5230.25. 5. DESTRUCT DESTRUCTION ION NOTICE NOTICE – Destroy Destroy by any method method that that will will preven preventt disclos disclosure ure of conten contents ts or reconstr reconstructi uction on of the docume document. nt.
HEADQUARTERS, DEPARTMENT OF THE ARMY 21 MARCH ARCH 2007 2007
TM 1-1520-237-PMS 1-1520-237-PMS LIST OF EFFECTIVE EFFECTIVE PAGES/WORK AGES/WORK PACKAGES INSERT LATEST UPDATED PAGES/WORK PACKAGES. DESTROY SUPERSEDED DATA. NOTE:
On a chan change ged d page page,, the the port portio ion n of the the text text affe affect cted ed by the the late latest st chan change ge is indi indica cate ted d by a vert vertic ical al line line in the the oute outerr marg margin in of the the page page.. Chan Change ges s to illus illustra tratio tions ns are are indica indicate ted d by a verti vertica call line line in the the oute outerr margin margin of the the page page next next to the the illus illustra tratio tion n title title.. Insert Insert latest latest change change pages; pages; dispos dispose e of supers supersede eded d pages pages in accorda accordance nce with regulati regulations ons.. Dates Dates of issue issue for origina originall and changed changed pages/ pages/work work packages packages are: are:
Origin Original al ........ .......... 0....... 0.........21 ..21 March March 2007 2007 FRONT AND REAR REAR MATT MATTER ER IS 4. THE THE TOTAL OTAL THE TOTAL TOTAL NUMBER NUMBER OF PAGES AGES FOR FRONT NUMBER OF WORK PACKAGES IN THIS MANUAL IS 8 CONSISTING OF THE FOLLOWING: Page / WP *Change No. No. Title Title ...................... .................................. ........................ .............. 0 Blank..................... Blank................................. ........................0 ............0 A ...................... .................................. ........................ ................. ..... 0 B Blank.................. Blank.............................. ........................0 ............0
Page / WP *Change No. No. i - ii... ....................... ................................... ......................0 ..........0 Chp 1 title page................ page............................. ..............0 .0 WP 0001 0001 00 (4 pgs)....... pgs)........... ........ ........ ........0 ....0 Chp 2 title page................ page............................. ..............0 .0
Page / WP *Change No. No. WP 0002 0002 00 (6 pgs)...... pgs)........... ......... ........ ........0 ....0 WP 0003 0003 00 (14 pgs)....... pgs)........... ........ ........ ......0 ..0 WP 0004 0004 00 (4 pgs)...... pgs)........... ......... ........ ........0 ....0 WP 0005 0005 00 (2 pgs)...... pgs)........... ......... ........ ........0 ....0
* Zero in this column column indicat indicates es an original original page or work package package A
Page / WP *Change No. No. WP 0006 0006 00 (4 pgs)....... pgs)........... ........ ........ ........0 ....0 WP 0007 0007 00 (18 pgs)...... pgs)........... ......... ........ ......0 ..0 WP 0008 0008 00 (2 pgs)....... pgs)........... ........ ........ ........0 ....0
TM 1-1520-237-PMS PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS
HOW TO USE THIS MANUAL Inspection Requirements This manual contains complete requirements for the 40 hour PMS inspection for the UH-60A, UH-60L, EH-60A, HH-60A, and HH-60L helicopter. It does not contain instructions for repair, adjustments, or other means of rectifying conditions, nor does it contain instructions for troubleshooting to find causes for malfunctioning. Specific tolerances, limits, etc., can be found in the applicable maintenance manuals. Use of the alphabetical index in the applicable manuals will facilitate locating the required information. This manual may contain inspection requirements applicable to specific equipment not installed on individual helicopters. When this situation is met, those requirements that are not applicable should be disregarded. DA Form 2408-13-1 will be used to record all deficiencies and shortcomings discovered during the PMS/40hr inspections. A 1-inch space following each area of inspection is provided to allow insertion of special inspection items resulting from TBs, MWOs, etc., and local command inspection items. Accessing procedures and detailed inspection criteria can be found in the applicable maintenance manuals. Unless otherwise directed opened doors will be closed upon completion of each area inspection. All inspections are visual unless otherwise noted. Requests for Engineering Authorization All requests for engineering authorization, when required by this manual, will be forwarded to Commander, U.S. Army Aviation and Missile Command, ATTN: AMSRDAMR-AE-U, Redstone Arsenal, AL 35898. Urgent requests shall be clearly identified to ensure priority handling and response. The requests shall include detailed information on the problem, e.g., sketches, photographs, dimensional data, etc., to assist in the evaluation and prompt reply. Kapton Wires Some UH-60A helicopters have wires that are Kapton insulated. The outer jacket of this type wire is dark-yellow and provides a surface for wire identification. Under the dark-yellow jacket is the copper-colored Kapton insulation. Beneath the insulation is the silver-coated electrical wire. If the outer jacket wears or peels, the copper-colored insulation may become visible. Exposure of copper-colored insulation is not a failure. Wire repair/replacement is required only if the insulation is damaged and/or the electrical wire is exposed.
i
TM 1-1520-237-PMS
HOW TO USE THIS MANUAL– Continued Use Of Icon’s Inspectionintervals, rangesof helicopter effectivity, MWOs, and productionline modificationsreferenced throughout thismanualshall be identified by anicon. Icons used in this manual are described as follows: External Stores Support System ESSS > UH-60A serial numbers 82-23748 and subsequent, EH-60A, UH-60L are provisioned for ESSS. Icon shown as ESSS> . UH-60A prior to serial number 82-23748 are not provisioned for ESSS. Icon shown as W/O ESSS > . Hover Infrared Suppressor System HIRSS > . UH-60A serial numbers 86-24560 and subsequent, UH-60L, and EH- 60A, or UH-60A modi fied by MWO 1-1520-237-50-63. Icon shown as HIRSS > . UH-60A prior to serial number 86-24560 not modified by MWO 1-1520-237-50-63. Icon shown as W/O HIRSS > . Modification of Dowel Pin Retention, Main Gear box MWO 50-43 > . UH-60A serial numbers 87-27004 and subsequent, UH-60L and EH-60A serial numbers 87-24663 and subsequent, or UH-60A and EH-60A modi fied by MWO 55- 1520-237-50-43. Icon shown as MWO 50-43 > . UH-60A prior to serial number 87-27004 and EH-60A prior to serial number 87-24663 not modified by MWO 55-1520-237-50-43. Icon shown as W/O MWO 50-43 > . Roll Vibration Absorber ROLL > UH-60L serial numbers90-26278 and subsequent, or modified by MWO 1-1520-237-50-60 and EH-60A serial numbers 87-24669 and subsequent. Icon shown as ROLL >. HH-60A MEDEVAC Helicopter HH-60A > . UH-60A helicopters modified to provide MEDEVAC missions. Icon shown as HH-60A > . HH-60L MEDEVAC Helicopter H H-60L > MEDEVAC Helicopter. UH-60L helicopters modified to provide MEDEVAC missions. Icon shown as HH-60L > . Cockpit Air Bag System CABS > . UH-60 helicopters modified by MWO 1-1520-237-50-82. Icon shown as CABS > .
ii
TM 1-1520-237-PMS
CHAPTER 1 GENERAL INFORMATION, EQUIPMENT DESCRIPTION AND THEORY OF OPERATION FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS
TM 1-1520-237-PMS 0001 00 PREVENTIVE MAINTENANCE SERVICES 40–HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS GENERAL INFORMATION SCOPE The inspections prescribed by this manual will be performed at a 40 +/- 2-hour interval by AVUM activities with the assistance of AVIM activities when required. The 40 hour PMS inspection interval maybe extended to complete a scheduled flight. The inspection, when due, need not interrupt the flight during which the inspectionbecomes due. In no case will the helicopter intentionally be scheduled for a flight that will cause it to exceed the 40 hour PMS inspection by more than 2 hours. GENERAL INFORMATION
NOTE Inspection items contained in this manual are considered the minimum requirements for performing a PMS inspection and must be performed. The cumulative effects of inspection deferrals are unknown and could result in catastrophic failure or increased maintenance at a later date. The inspection requirements herein establish when certain equipment is to be inspected and what conditions are desired. The requirements must be followed, in order to make sure that damage is discovered and corrected before malfunctioning or serious trouble results. In order to arrange inspection requirements as nearly as possible according to the manner in which work will be done, the requirements in each area are divided into groups under area headings (Figure 1). An area title indicates a specific helicopter location, which may include several systems or groups of related components within this given area. Refer to Army Regulations and Operator’s Manual for personnel requirements and procedures for ground run and flight checking the helicopter. OZONE DEPLETING CHEMICAL INFORMATION. HAZARDOUS MATERIAL INFORMATION.
To be determined.
To be determined.
REPORTING OF ERRORS. Reporting Errors And Recommending Improvements. You can help improve this manual. If you findanymistakes orif you knowof a way to improve these procedures, please let us know. Mail your letter or DA Form 2028 (Recommended Changes to Publications and Blank Forms) located in the back of this manual, directly to: Commander, US Army Aviation and Missile Command, ATTN: AMSAM-MMC-MA-NP, Redstone Arsenal, AL 35898-5000. A reply will be furnished to you. You may also provide DA Form 2028 information to AMCOM via e-mail, fax, or the World Wide Web. Our fax number is: DSN 788-6546 or Commercial 256-8426546. Our e-mail address is:
[email protected]. Instructions for sending an electronic 2028 may be found at the back of this manual immediately preceding the hard copy 2028. For the World Wide Web use: https://amcom2028.redstone.army.mil. 0001 00-1
TM 1-1520-237-PMS
GENERAL INFORMATION– CONTINUED Inspection Areas Inspection Areas. Inspection areas are shown in Figure 1.
Figure 1.
Area Diagram (Sheet 1 of 2)
0001 00-2
0001 00
TM 1-1520-237-PMS 0001 00
GENERAL INFORMATION– CONTINUED
Figure 1.
Area Diagram (Sheet 2 of 2)
0001 00-3
TM 1-1520-237-PMS
0001 00
GENERAL INFORMATION– CONTINUED AREA NO. 1: Cockpit Section
All surfaces, material, components, and equipment inside and outside of the cockpit and electronics compartment, and extending rear to manufacturing break point at fuselage STA 247.0.
AREA NO. 2: Cabin Section
All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 247.0to STA 379.0 (includes, but not limited to, main landing gear, HH-60A HH-60L > rescue hoist, and medical interior < ).
AREA NO. 3: Transition Section
All surfaces,material, components, and equipment inside and outside of the fuselage, from STA 379.0 to STA 485.0.
AREA NO. 4: Tail Cone Section
All surfaces, material,components, and equipment inside and outside of the fuselage,from STA 485.0to STA 648.0.
AREA NO. 5: Tail Rotor Pylon Section
All surfaces, material, components, and equipment inside and outside rear of STA 648.0 (includes, but not limited to, horizontal stabilator, tail rotor and blades, tail gear box, intermediate gear box).
AREA NO. 6: Main Rotor Pylon
All surfaces, material, components, and equipment inside and outside, above cabin section (includes, but not limited to, main transmission, main rotor head, main rotor blades).
0001 00-4
TM 1-1520-237-PMS
CHAPTER 2 MAINTENANCE INSTRUCTIONS FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L HELICOPTERS
TM 1-1520-237-PMS 0002 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60LHELICOPTERS COCKPIT SECTION
INITIAL SETUP: Tools and Special Tools
Personnel Required
Aircraft Mechanic’s Toolkit, SC 5180-99-B01 Materials/Parts
UH-60 Helicopter Repairer MOS 15T (2) References
Brush, Cleaning, Item 59 WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00
PAM 738-751 TM 1-1520-237-23 WP 1803 00
NOTE
•
The 40 Hour inspection is normallydone by two Tactical Transport Helicopter Repairers, MOS 15T. The twoMOS 15T’s are called A and B. Each inspection item is to be done by either mechanic. A or mechanic B as called out opposite the inspection procedure. Where both A and B are called for in the same procedure, A should do theinspection on theleft side of the helicopter and B should do it on the right side. MOS 15N personnel will be required for power-onchecks. Before starting this inspection, review aircraft forms and records for discrepancies (PAM 738-751). Review cleaning requirements in TM 1-1520-237-23. Review lubrication requirements in TM 1-1520-237-23. Lubrication requirements posted in TM 1-1520-237-23 are a minimum. When operating in dry, dusty, and/or sandy conditions, special attention should be given to exposed areas particularly; the main and tail gear struts and the exposed stabilator actuator piston. Refer to TM 1-1520-237-23 for speci fic inspection procedures and accept/reject criteria.
• • • •
0002 00-1
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0002 00
MOS 15T
MH A
B
COCKPIT SECTION 1.1
Inspect nose door HH-60A HH-60L > FLIR, and nose avionics compartment as follows: < Open nose door. HH-60A UH-60L EH-60A > Inspect nose door and Doppler/GPS computer for obstructions. < Check nose door for damage and seal for adhesion, cleanness, and any deterioration. Inspect nose door hinges for cracks. In avionics compartment and avionics compartment door, inspect avionics components, electrical connectors, and wiring for excessive wear, security, and damage. HH-60A HH-60L > Remove FLIR fairing. < HH-60A HH-60L > Check condition of FLIR and fairings. Check for dents, cracks, missing hardware, corrosion, and damage. Inspect wiring for proper connection, burns, chafing, and security. < HH-60A HH-60L > Install FLIR fairing. < Inspect shock mounts for bottoming, corrosion, and security.
0002 00-2
0.02
B
TM 1-1520-237-PMS 0002 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
Inspect interior ducts and lines for security. Close door and check for positive latching. Secure both latches. 1.2
0.01
Inspect cockpit exterior as follows:
B
Inspect cockpit drain holes for blockage. Inspect cockpit exterior skin for corrosion, dents, cracks, and missing rivets. Inspect wire strike guides for corrosion, security, and damage. Inspect windshield, windshield wiper arms and blades for security, wear, cracks, and deterioration. Lubricate windshield wiper studs and converters. 1.3
Inspect all AREA No. 1 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
0.04
A
B
1.4
Check pilot’s and copilot’s step assemblies for cracks, corrosion and missing hardware. Check for evidence of lightning strikes.
0.01
A
B
NOTE Evidence of a lightning strike will appear as a blackened surface, pit or hole with a burned rim. 1.5
Inspect cockpit interior as follows:
0.04
0002 00-3
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0002 00
MOS 15T
MH
Observe entire cockpit interior for general cleanness, corrosion damage and for evidence of oil leakage from ceiling, security of fasteners and structure for cracks.
A
B
A
B
A
B
Check crew doors for proper operation and damage. Inspect seals for deterioration, loosening of bonds and signs of leakage. Check armored wing panels, slide tubes, and bushings for security, damage cleanliness, and ease of operation. Check latches and hinges for condition and security. Check jettison mechanism for security.
1.6
0.01
Inspect pilot’s and copilot’s seats as follows: Check pilot and copilot’s seats for damage, security, positive movement, and locking in all positions. Inspect spherical bearing (resilient mounts) for cracks. Check lap belts for corrosion, cuts, fraying, and security. Check crotch belt for corrosion, cuts, fraying, and security. Check shoulder harness for corrosion, cuts, fraying, and security. Check inertia reel for damage, security, and positive locking and unlocking.
0002 00-4
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0002 00
MOS 15T
MH A
B
0.01
A
B
0.01
A
B
Inspect components, electrical connectors, and wiring installed under pilot’s and copilots seat for excessive wear, damage and security.
0.01
A
B
1.10
HH-60A HH-60L > Inspect Turret FLIR Unit (TFU) Scan Cavity (BIT/FIT Indication).
0.02
1.11
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
NOTE Check that No. 1 and No. 2 ENG POWER CONTROL and No. 1 and No. 2 ENG FUEL SYS levers are shut off and that #1 and #2 ENG EMER OFF T-handles are fully forward. 1.7 1.8
Inspect engine control quadrant for general condition. Inspect pilot’s and copilot’s collective sticks, cyclic sticks, and yaw control pedals as follows: Inspect pilot and copilot’s collective and cyclic sticks for general condition. Check boots at base of sticks for loose fit, cracks, splitting, or damage. Make sure that there are no openings through which foreign objects may enter flight control linkage area below. Inspect grips for cracks and loose switches, and check that all lettering is readable. Inspect pilot and copilot’s yaw control pedals for dirt or mud accumulation. Check boots at base of pedals for loose fit, cracks, splitting, or damage. Make sure that there are no openings through which foreign objects may enter flight control linkage area below. Open boots. Check brake master cylinders for leakage. Close boots.
1.9
END OF WORK PACKAGE
0002 00-5/6 blank
B
TM 1-1520-237-PMS 0003 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L CABIN SECTION
INITIAL SETUP: Tools and Special Tools
Personnel Required
Aircraft Mechanic’s Toolkit, SC 5180-99-B01
UH-60 Helicopter Repairer MOS 15T (2)
Materials/Parts
References
Brush, Cleaning, Item 59 WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00 Seq. No.
TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
A
B
CABIN SECTION 2.1
Open troop/cargo doors. Inspect exterior for corrosion, distortion, cracks, and for loose or missing fasteners. Check operation through full range with no binding and that the door remains secure in the tracks. Check jettison mechanism for damage and proper position. Check upper and lower roller support fittings for wear. Check front and rear door latches for positive latching. Inspect lower track for presence of eight wear strips each. Visually check for wear and damage.
0003 00-1
0.02
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
B
0.01
A
B
0.03
A
B
Inspect upper track for wear and damage. Inspect door seals for deterioration, damage and separation. 2.2
HH-60A UH60L EH60A > < Open and close gunners’ windows. Inspect exterior frames, transparent panel, and tracks for damage. Inspect for loose or missing fasteners and seals for separation. Check for smooth operation and secure closure.
If gun mounts and ammo boxes are installed, inspect for security, damage, and stowage. 2.3
Inspect HH-60A UH-60L > troop and gunners’ seats and OR EH-60 > observers’ seat < as follows: Inspect for frayed or broken cables and for cleanness. Check floor and ceiling attachment points for security. Check troop/observer seat lap belts and shoulder harness for corrosion, cuts, fraying, and security. Check gunner’s seat lap belts and shoulder harness for corrosion, cuts, fraying, and security. Inspect gunner’s seat inertia reels for proper operation. Inspect seat tubing and attenuators for damage and security.
0003 00-2
TM 1-1520-237-PMS 0003 00 Seq. No. 2.4
Item and Procedure EH-60 > Inspect mission operator’s seat as follows: <
MOS 15T
MH 0.1
A A
B B
0.1
A
B
0.1
A
B
Check mission operator’s seat for damage, security, positive movement, and locking in all positions. Check lap belts and shoulder harness for corrosion, cuts, fraying, and security. Check inertia reel for damage, security, and positive locking and unlocking. 2.5
HH-60A HH-60L > Inspect medical attendant’s seats as follows: < Check seats for damage, security, positive movement, and locking in all positions. Check lap belt, crotch and shoulder harness for corrosion, cuts, fraying, and security. Check inertia reel for damage, security, and positive locking and unlocking. Check seats for freedom of movement on seat tracks and positive locking.
2.6
EH60A > Inspect AN/ALQ-151 system as follows: < Check AN/ALQ-151 mission consoles and equipment racks for equipment condition, security, and cleanness. Check cable tunnel covers for security.
2.7
A
HH-60A HH-60L > Inspect cabin medical interior as follows: <
0003 00-3
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
B
0.02
A
B
0.01
A
B
Inspect overhead, left side door post, and right side door post electronic components for damage and security. Inspect medical cabinet for security of mounting. Inspect medical cabinet electronic components for damage and security. 2.8
Inspect cabin ceiling as follows: HH-60A HH-60L > Remove overhead light panel. < Lower soundproofing panels from ceiling. Inspect beaded panel for buckling and cracks. Check APU accumulator gage access cover hinge and fasteners for damage and security. Check cabin ceiling for cracks, damage, or loose rivets. Visually inspect the support beam at STA. 308 for cracks.
2.9
Inspect cargo hook as follows: Check cargo hook for positive latching. Check that hook is free to pivot from side to side. Check cargo hook electrical connectors for security and damage.
0003 00-4
TM 1-1520-237-PMS 0003 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
Check cargo hook manual release lever spring for proper installation and distortion. Make sure spring provides positive pressure on manual release lever. 2.10
Check cargo hook support structure for damage corrosion and cracks.
0.01
A
0.01
A
0.01
A
0.01
A
Visually inspect cargo hook load arm for cracks. 2.11
Inspect tail rotor control cables and pulleys as follows: Check tail rotor control cables for wear, fraying, corrosion and loose or missing plastic coating, particularly in pulley area. Inspect cable guard pins for wear. Check that cables are riding properly in pulleys and that cable guard pins are installed. Inspect tail rotor control cable pulleys for damage and security.
2.12
Inspect ESSS > as follows: < Check fuel lines in cabin for security, chafing, damage, or signs of leaks. Check for security of bonding jumpers, dummy receptacles, caps, and lanyards. Check electrical harnesses in cabin for proper connection, chafing, and security. Check backshells, on connectors for damage. Check fuel management control panel on center console for damage, cleanness, and security.
2.13
Inspect APU accumulator as follows:
0003 00-5
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
B
0.2
A
B
0.01
A
Check APU accumulator for proper pressure. Inspect hydraulic handpump for security and leakage. Check APU accumulator tape for correct percentage of fluid volume. 2.14
Inspect cabin soundproofing panels for damage and fasteners for security. Secure cabin soundproo fing panels on ceiling. HH-60A HH-60L > Install overhead light panel. <
2.15
Inspect battery as follows: HH-60A UH60L EH60A > Remove battery cover. < Check electrical connector, case mounting clamps, and covers for damage, proper position, and security. HH-60A UH60L EH60A > Check vent lines for damage, cleanness, corrosion and obstructions. < HH-60A UH60L EH60A > Install battery cover. <
2.16
Inspect auxiliary cabin heater as follows: Inspect temperature controller for damage and security.
0003 00-6
TM 1-1520-237-PMS 0003 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
0.02
A
B
0.01
A
B
Inspect harness for proper connection, chafing, security, and backshell for damage. 2.17
Inspect main landing gear shock struts, drag beams, and brakes as follows: Remove main landing gear upper fairing. Inspect main landing gear shock struts upper and lower stages for dirt, corrosion, and correct inflation. Wipe clean and lube exposed main landing gear strut pistons. Inspect main landing gear shock strut attachment points for distortion and wear. Check wire cutters for security, damage and corrosion. Check ground wire for security and contact with ground. Check drag beam switches for security and damage. Check drain lines for obstruction. Check brake wear indicator pins for minimum length. Check brake and brake lines for damage or leaks. Install main landing gear upper fairing.
2.18
Visually inspect main wheels for missing or damaged hardware.
0003 00-7
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
2.19
Visually inspect main wheel tire for wear, cuts, or cracks. Check tire pressure with a gauge. Service as necessary.
2.20
Inspect cabin exterior as follows:
0003 00
MOS 15T
MH A
B
0.02
A
B
0.03
A
B
Examine cabin exterior skin for corrosion, cracks, dents, and missing rivets. Check lower cabin skin drain holes for obstruction. Check that external ICS connector covers are in place. Check external power receptacle for burned pins (right side only). Check cover for secure closure. 2.21
ESSS > Inspect W/Tanks installed as follows: < Remove HSS wing upper/lower root, front/rear VSP, trailing edge, and saddle assembly fairings. Check fuselage attachment fittings for security and cracks. Check all expandable pins for security and cracked washers. Make sure handle is securely snapped over end of pin, and that locking ring is fully visible and expanded. Check expandable pin bonding jumpers for security and corrosion. Check electrical harnesses and connectors for security and chafing.
0003 00-8
TM 1-1520-237-PMS 0003 00 Seq. No.
Item and Procedure
MOS 15T
MH A
Check breakaway lanyards for proper installation. Check root-to-fuselage fuel hose for security, chafing, damage, or signs of leaks. Check root-to-fuselage pneumatic hose for security, chafing, damage, or signs of leaks. Check horizontal stores support fuel hoses, fuel tube assembly, and fuel tee union for security, cha fing, damage, or signs of leaks. Check horizontal stores support pneumatic hoses and pneumatic check valve for security, chafing, damage, or signs of leaks. Check vertical support pylon pneumatic hose and elbow for security, chafing, damage, or signs of leaks. Check vertical support pylon fuel hose, fuel tube, and isolation check valve for security, chafing, damage, or signs of leaks. Check support struts for security, cracks, delamination, and chipping. Check clevis locknuts for security. Check support strut bonding jumpers for security and corrosion. Visually check upper and lower surfaces of horizontal stores support for cracks, chipping, or delamination. Check leading and trailing edge fairings for cracks, dents, and damage. Check vertical support pylons for security. Check that locking pin on expandable bolts is securely snapped into tab, and that locking ring is fully visible and expanded.
0003 00-9
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
B
A
B
Check fuel shutoff valves for security and leaks. Check fuel tanks for proper installation, leaks, and damage. Do torque check of sway brace locknuts. If locknut slips, retorque screws and locknuts. Install HSS wing fairings. 2.22
ESSS > W/O tanks installed inspect as follows: <
0.2
Remove upper and lower root fairings and check for cracks, dents, and damage. Remove front and rear vertical support pylon fairings, and check for cracks, dents, and damage. Check fuselage attachment fittings for security and cracks. Check all expandable pins for security and make sure handle is secure. Make sure handle is securely snapped over the end of pin, and that locking ring is fully visible and expanded. Check expandable pin bonding jumpers for security and corrosion Check root-to-fuselage electrical harness and connectors for security and chafing. Check breakaway lanyards for installation.
0003 00-10
TM 1-1520-237-PMS 0003 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
A
B
Check root-to-fuselage fuel hose for security, chafing, and damage. Check root-to-fuselage pneumatic hoses for security, chafing, and damage. Check support struts for security, cracks, delamination, and chipping. Check clevis locknuts for security. Check support strut bonding jumpers for security and corrosion. Visually check upper and lower surfaces of horizontal stores support for cracks, chipping, and delamination. Check leading and trailing edge fairings for security, cracks, dents, and damage. Check vertical support pylons for security. Check that the locking pin on the expandable bolts is securely snapped into tab, and that the locking ring is fully visible and expanded. Install fairings.
NOTE The following procedure is required when operating in dry, dusty and/or sandy environment. 2.23
Clean Horizontal Stores Support (HSS) Pneumatic Check Valves.
0003 00-11
0.5
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
2.24
HH-60A HH-60L UH-60 > Inspect external rescue hoist as follows: <
0.1
B B
0.1
B
Remove support arm fairings. Inspect rescue hoist for cracks, corrosion and security. Check hoist support for cracks, corrosion, damage, and security. Check hoist cowlings and fairings for damage and security and screw heads for corrosion. Check hook assembly for free rotation and security. Check spring bumper grommet for security. Check electrical connectors and wiring for security, damage, and chafing. Check cabin RESCUE HOIST control panels for security, controls and switches for binding, and lettering for readability. Check hydraulic fittings on hydraulic equipped hoists for signs of leakage. 2.25
UH-60 > Inspect internal hoist if installed as follows: Inspect rescue hoist for cracks, corrosion, and security. Check hoist floor and ceiling mounts for cracks corrosion, damage and security.
0003 00-12
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0003 00
MOS 15T
MH A
B
A
B
Check hook assembly for free rotation and security. Check spring bumper grommet for security. Check electrical connectors and wiring for security, damage and chafing. Check cabin RESCUE HOIST control panels for security, controls and switches for binding and lettering for readability.
2.26
Inspect all AREA No. 2 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
2.27
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0003 00-13/14 blank
0.04
TM 1-1520-237-PMS 1-1520-237-PMS 0004 0004 00 PREVENTIVE PREVENTIVE MAINTENANCE MAINTENANCE SERVICES SERVICES 40-HOUR INSPECTION CHECKLIST CHECKLIST FOR UH-60A, UH-60A, UH-60L, UH-60L, EH-60A, EH-60A, HH-60A HH-60A,, AND HH-60L HH-60L TRANSITION TRANSITION SECTION
INITIAL INITIAL SETUP: SETUP: Tools and Specia Speciall Tools ools Aircraft Aircraft Mechan Mechanic’ ic’s s Toolkit, oolkit, SC 5180-9 5180-99-B0 9-B01 1
Personnel Personnel Required Required
Materials/Parts Brus Brush, h, Clea Cleani ning ng,, Item Item 59 WP 1803 1803 00 Lubri Lubrica catin ting g Oil, Oil, Gene Genera rall Purp Purpos ose, e, Item Item 185, 185, WP 1803 1803 00 Towel, owel, Mach Machin inery ery Wipin Wiping, g, Item Item 344, 344, WP 1803 1803 00
References
Seq. No.
UH-60 UH-60 Helic Helicop opter ter Repa Repaire irerr MOS 15T 15T (2) (2)
TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
A
B
TRANSITION TRANSITION SECTION
3.1
Inspect as follows:
0.01
Remove soundproo soundproofing pane panels ls and and fuel fuel line line enclo enclosu sure re pane panell from from rear rear bulkh bulkhea ead. d. ESSS ES SS > Check flow sens sensor or pane panell for for secu securit rity y and and leaks leaks.. < Check Check fuel hoses, hoses, electri electrical cal harnes harnesses ses,, and bonding bonding jumpers jumpers for proper proper connec connection tion,, securit security y, and chafing.
0004 00-1
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0004 00
MOS 15T
MH A
B
Install Install fuel fuel line enclos enclosure ure panels panels and soundp soundproo roofing panels panels.. 3.2
Insp Inspec ectt exte externa rnall air air star startt conn connec ecto torr on left left side side as follo follows ws::
0.03
A
0.05
A
B
Inspec Inspectt externa externall air start start connec connector tor for securi security ty.. Check flapper valve for free movement. movement. Check Check access access cover cover for secure secure closure. closure.
3.3
vent line exit ports ports undern underneath eath helicop helicopter ter for obstru obstructio ction. n. Insp Inspec ectt drain drain line line and vent Check for water and contamination in both fuel tanks using siphoning sample kit or draining 1 pint of fuel from both sump drains.
3.4
Visually Visually inspect inspect exterior exterior of sump drain access access panels panels and surrounding surrounding area area for signs of fuel leakage. leakage. Check transition transition area area drains for obstruction.
0.01
A
B
3.5
Inspec Inspectt transiti transition on section section skin for corros corrosion, ion, cracks cracks,, dents, dents, or missin missing g rivets. rivets.
0.01
A
B
3.6
EH60 EH 60A A HH HH-60 -60A A HH HH60 60L L > Inspec Inspectt transiti transition on section section avionic avionics s compart compartmen mentt as follows follows:: <
0.06
A
Open avionics avionics access access door. door. Inspec Inspectt avionic avionics s access access door door and access access panels panels for conditi condition, on, damage damage,, and securit security y of latching latching..
0004 00-2
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0004 00
MOS 15T
MH A
B
A
B
Check security of ECS pallets. EH60A > Check IINS, INU, and NPU shelves for condition and security. < EH60A > Check INU, and NPU components for security in mounts. < HH-60A HH60L > Check OBOGS components for damage and security. < HH-60A HH60L > Inspect avionics components, electrical connectors, and wiring for excessive wear, security, and damage. < EH60A > Check IINS filter and cooling ducts. < EH60A > Check IINS battery for security and condition. < Close and secure avionics access door. 3.7
Inspect all area No. 3 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
3.8
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0004 00-3/4 blank
0.04
TM 1-1520-237-PMS 0005 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L TAIL CONE SECTION
INITIAL SETUP: Tools and Special Tools Aircraft Mechanic’s Toolkit, SC 5180-99-B01
Personnel Required UH-60 Helicopter Repairer MOS 15T (2)
Materials/Parts Brush, Cleaning, Item 59 WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00 Seq. No.
References TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
TAIL CONE SECTION 4.1
Inspect tail landing gear tire for wear, cuts and cracks. Check tire pressure with a gage. Service as necessary.
0.01
B
4.2
Inspect tail landing gear shock strut and yoke area as follows:
0.03
B
Check wire strike deflector for security and damage.
Remove right or left side tail cone access panel.
0005 00-1
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0005 00
MOS 15T
MH A
B
0.02
A
B
0.05
A
Inspect pylon step fitting. Inspect cable guide. Inspect shock strut for leakage, dirt, corrosion and strut under inflation.
Inspect tail landing gear shock strut attachment points for chafing damage, cracks, and security. Wipe clean and lube exposed tail landing gear strut pistons. Install access panel. 4.3
Inspect tail cone exterior as follows: Inspect tail cone skin for corrosion, dents, cracks, and missing rivets. Check tail cone skin drain hole for obstruction. Inspect tail cone anti-collision light for security. Check lens for cracks, breakage, and cleanness. Check chaff and flare dispenser payload modules and mounts for condition, security, corrosion and cleanness.
4.4
Inspect tail cone interior for condition.
0005 00-2
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
4.5
Inspect all area No. 4 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
4.6
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0005 00-3/4 blank
0005 00
MOS 15T
MH
0.04
A
B
A
B
TM 1-1520-237-PMS 0006 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L TAIL ROTOR PYLON SECTION
INITIAL SETUP: Tools and Special Tools Aircraft Mechanic’s Toolkit, SC 5180-99-B01
Personnel Required UH-60 Helicopter Repairer MOS 15T (2)
Materials/Parts Brush, Cleaning, Item 59 WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00 Seq. No.
References TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
TAIL ROTOR PYLON SECTION 5.1
Inspect intermediate gear box as follows:
0.01
Remove intermediate gear box cover. Inspect intermediate gear box, gear box mounting feet, and mounting area for cracks, dents, nicks, corrosion and security. Check intermediate gear box chip detector electrical connector for security.
0006 00-1
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0006 00
MOS 15T
MH A
B
Inspect drain holes for obstruction. Reinstall gear box cover. 5.2
Inspect tail rotor pylon area as follows:
0.01
B
0.01
B
Open tail rotor pylon drive shaft cover. Examine pylon skin for corrosion, dents, and missing rivets. Check electrical wiring for condition and security. Inspect anti-collision light and position light for security and cracked, broken, or dirty lenses. Close pylon drive shaft cover. 5.3
Inspect stabilator as follows: Remove inspection panels. Inspect spar for cracks using a flashlight and mirror. Check stabilator and actuator attachment points for cracks, corrosion, security, and play.
0006 00-2
TM 1-1520-237-PMS 0006 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
Check limit switch attachment for security. Wipe clean and lube exposed portions of stabilator actuator. Install inspection panels. 5.4
Inspect static discharge wicks for security and general condition.
0.01
A
5.5
Inspect tail rotor deice system as follows:
0.01
B
0.05
B
Check tail rotor deice slipring environmental shield, wire harness, and connectors for chafing or damaged insulation and security. Check drain holes in rotor and stator for blockage. Check tail rotor deice brushes for wear. Check tail rotor deice cable brackets for cracks. 5.6
Inspect Tail rotor pitch control rods with spherical bearings as follows: Inspect tail rotor pitch control rod end bearings for wear using 0.010- inch side of locally made plastic feeler gage.
0006 00-3
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0006 00
MOS 15T
MH A
B
A
B
NOTE Do the following inspections every 15- flight hours only on bearings that have failed the 0.010-inch feeler gage inspection. Inspect tail rotor pitch control rod end bearings for wear using 0.015- inch side of locally made plastic feeler gage.
5.7
Inspect all area No. 5 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
5.8
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0006 00-4
0.04
TM 1-1520-237-PMS 0007 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L MAIN ROTOR PYLON
INITIAL SETUP: Tools and Special Tools
Personnel Required
Aircraft Mechanic’s Toolkit, SC 5180-99-B01
UH-60 Helicopter Repairer MOS 15T (2)
Materials/Parts
References
Brush, Cleaning, Item 59 WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00 Seq. No.
TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
A
B
MAIN ROTOR PYLON 6.1
Inspect main rotor pylon sliding cover as follows:
0.02
Open main rotor pylon sliding cover. Inspect main rotor pylon sliding cover for cracks and distortion. Inspect rollers and tracks for damage and wear.
0007 00-1
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
0.01
A
B
0.02
A
B
Check main rotor pylon sliding cover screen for obstructions. Inspect wire strike guides and cutters for security, damage and corrosion.
Inspect pin receivers, support structure, skin, stringers, and intercostals at stations 247. 0 and 267. 0 for cracks. 6.2
Inspect pitot-static tube as follows: Inspect pitot-static tube openings for any obstructions, such as dirt or insects. Inspect for discoloration beyond that normally cause by pitot heater.
6.3
Inspect flight controls and heating/ventilation system as follows: Visually inspect all flight control rod assemblies for external corrosion. Inspect flight control rods, jamnuts, bellcranks, and supports for cracks, wear, distortion, and security of attachment. Inspect for looseness between the control tube body and jamnuts by moving the control rod assembly in any direction. Inspect flight control mixer for cracks, wear, distortion, and security of attachment. Inspect heating bleed-air tubes for cracks and damage. Check ventilation blower and heater mixing valve for damage.
0007 00-2
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
A
B
Check temperature sensing tube to heater mixing valve for security and cracks. Check heater mixing valve duct inlet screen for blockage. 6.4
Inspect primary servos, yaw, and collective boost servos, pitch trim assembly, and roll assembly as follows: Check primary servos, yaw and collective boost servos, pitch trim assembly, roll assembly, yaw boost SAS actuator, pitch trim SAS actuator, and roll assembly SAS actuator for leakage. Special attention should be given to the upper and lower surfaces of the output links. Check all SAS actuators for any visible gouging, or damage resulting from contact with safety cables or wire installed between the actuator housing and the output piston-retaining nut.
Inspect three primary servos for damage and security of mounting. Special attention should be given to the thread undercut area of all servo piston rods on the shaft immediately adjacent to output clevis.
Inspect pitch trim assembly and roll assembly for damage and security of mounting. Inspect both ends of collective boost servo for cracks at cylinder ends, and cracks on power piston shafts. Special attention should be given to the thread undercut area of all servo piston rods on the shaft immediately adjacent to output clevis.
Inspect both ends of yaw boost servo for cracks at cylinder ends, and cracks on power piston shafts. Special attention should be given to the thread undercut area of all servo piston rods on the shaft immediately
Inspect yaw boost SAS actuator, pitch trim SAS actuator, and roll assembly SAS actuator for damage and security.
0007 00-3
0.02
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
6.5
Inspect accessory module for oil seepage, paying particular attention to area around main generator.
0.01
A
B
6.6
Inspect input and accessory module housings for paint discoloration from aluminized gray to brown.
0.01
A
B
6.7
Inspect accessory module chip detector electrical connectors, Nr speed sensor electrical connector, and low oil pressure sensor electrical connector for security.
0.01
A
B
6.8
Inspect main rotor pitch control rod spherical bearings as follows:
0.02
A
B
Inspect main rotor head upper pitch control rod end bearings for wear using 0.010-inch side of locally made plastic feeler gage. Inspect main rotor head lower pitch control rod end bearing for wear using 0.010-inch side of locally made plastic feeler gage. Inspect main rotor pitch control rods for any obvious damage or deformation.
NOTE Do the following inspections every 15- flight hours only on bearings that have failed the 0.010 feeler gage inspection. Inspect main rotor head upper pitch control rod end bearings for wear using 0.015-inch side of locally made plastic feeler gage.
0007 00-4
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
0.01
A
B
0.10
A
B
Inspect main rotor head lower pitch control rod end bearing for wear using 0.015-inch side of locally made plastic feeler gage. 6.9
Main Rotor Pitch Control Rod Elastomeric Bearings.Inspect main rotor head lower pitch control rod end bearing for wear using 0.015-inch side of locally made plastic feeler gage.
NOTE Elastomeric rod end bearing plastic feeler gage should only be used if possible separation exists based on visual inspection of bearing surfaces. Inspect main rotor head upper pitch control rod end bearings for elastomeric cracks or separation, if a concentration or pileup of eraser type wear is present, if an extrusion is detected, if cracking or disbonding of elastomer from shim inner or outer member is suspected. Visually check for signs of inner member separation using hand force, shaking control rod. Check for gaps or cracks in areas other than manufactured shim gaps. Inspect main rotor head lower pitch control rod end bearings for elastomeric cracks or separation, if a concentration or pileup of eraser type wear is present, if an extrusion is detected, if cracking or disbonding of elastomer from shim inner or outer member is suspected. Visually check for signs of inner member separation using hand force, shaking control rod. Check for gaps or cracks in areas other than manufactured shim gaps.
6.10
Inspect main rotor hub and spindle as follows: Inspect main rotor hub for cracks and damage. Visually check spindle shaft shrink tubing for evidence of looseness or movement. Check inner race slippage mark for movement.
0007 00-5
TM 1-1520-237-PMS
Seq. No. 6.11
Item and Procedure
Inspect main rotor head dampers bearing as follows:
0007 00
MOS 15T
MH A
B
0.10
A
B
0.02
A
B
NOTE Removal of damper assembly is not required for feeler gage inspection. Inspect inboard and outboard main rotor head damper rod end bearings for wear using 0.010-inch side of locally made plastic feeler gage.
NOTE Do the following inspections every 15 flight hours only on bearings that have failed the 0.010-inch feeler gage inspection. Removal of damper assembly is not required for feeler gage inspection. Inspect inboard and outboard main rotor head damper rod end bearings for wear using 0.015-inch side of locally made plastic feeler gage. 6.12
Inspect droop stops as follows:
Check droop stop lugs for cracks. Check droop stop ring nut for looseness, and sleeve bearing (inner race) for cracks, on spindle assemblies 7007010030-041, 70070-10030-042, 70070-10030-045, 70070-10030-046, 70102-08200-041 through 70102-08200044, and 70102-08200-063.
Check droop stop support for cracks. Visually inspect droop stop support for cracks at upper and lower puller grooves. 0007 00-6
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
Check droop stop and droop stop retaining pin bushings for damage and security. Visually inspect droop stop spring and attaching hardware for signs of corrosion. 6.13
Inspect anti-flap assemblies as follows:
0.11
A
0.11
A
Check anti-flap assembly for damage, security, and freedom of operation. Visually inspect for interference or contact between the anti-flap cam and the anti-flap stop plate. Visually inspect for contact of the droop stop cam and horn attachment bolts. 6.14
Inspect main rotor spindle elastomeric bearings as follows:
NOTE The spindle elastomeric bearing consists of a spherical bearing and a thrust bearing. Wear of either bearing is a gradual process that will take several hundreds of hoursfrom first detection of rubber damage to point where bearingmust be replaced. Visual comparison of the bearings in the applicable technical manual is the criterion for acceptance or rejection. Using a flashlight and mirror visually inspect inner and outer surface of spherical bearing for wear, laminate separations, and cracked shims through the 2-inch diameter inspection hole.
0007 00-7
A
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
NOTE Do not remove spindle to inspect inner surface of thrust bearing.
6.15
Using a flashlight and mirror visually inspect outer surface thrust bearing for elastomeric extrusion paying particular attention to the 6 o’clock position and surface areas furthest inboard. Replace thrust bearing within the next 30 flight hours if any elastomer debris is found.
A
Inspect thrust bearing for laminate separations and cracked shims. Cracks will appear in the edge of metal shims. No cracks allowed. (A white wax-like substance on rubber surface is normal and should not be removed.)
A
Check elastomeric bearings for surface cracking or crazing of rubber. Small hairline surface cracking or crazing of rubber is acceptable.
A
If droop stop pounding is experienced, inspect droop stop ears on spherical elastomeric bearing endplate for cracks.
A
Check thrust elastomeric bearing endplate for cracks.
A
Inspect hub arm for signs of contact with spindle retention nut.
A
Inspect bifilar as follows:
0.01
Inspect bifilar for cracks, visible damage, wear, and security. Inspect bifilar weights for cracks between and adjacent to bushing bores on both upper and lower surfaces.
0007 00-8
A
B
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
0.05
A
B
0.04
A
B
Inspect top and bottom bonded joints of bifilar weights for cracks. Clean tapered bifilar washers, bushings, and pins. Visually inspect tapered bifilar washers for wear and damage. Relubricate bifilar washers, pins, and bushings. 6.16
Inspect bifilar weights as follows: Inspect weights for nicks, gouges, and cracks in AREAS A, B, and C per applicable technical manual.
NOTE Cracked paint in area C of weights with "UT" marked in area of part number is acceptable. Inspect weight marked "UT" in area of part number for cracks in paint in AREAS A and B. Inspect weight without "UT" marked in area of part number for cracks in paint in AREAS A, B, and C. If cracks in paint are found, refer to applicable technical manual.
6.17
Inspect main rotor blades as follows: Test main rotor blade pressure indicators.
6.18
Inspect main rotor blade expandable pins for security and tension as follows:
0007 00-9
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
0.02
A
B
0.1
A
B
NOTE There must not be any binding of the expandable pin by the main rotor blade when the tension is checked. The main rotor blades and blade pins do not have to be removed for this inspection. Raise main rotor blade and remove any binding of expandable pins. Release expandable pin handle from lower nut and open handle. Pull pinout farenough fortop two expandablesegments to be visibleabove blade cuff. Verify that pin is not fractured by observing corresponding movement of lower end of core pin. DO NOT COMPLETELY REMOVE PIN. If pin is not defective, reinstall and check closing tension on handle per (applicable technical manual).
6.19
Inspect swashplate as follows: Inspect swashplate and scissors assemblies for cracks, dents, distortion, corrosion and security. Inspect swashplate uniball for cleanness.
6.20
Inspect swashplate link assemblies as follows: Make sure all electrical and hydraulic power is turned off or disconnected from the aircraft.
CAUTION Any swashplate link assembly, which exceeds or does not conform to accept/reject criteria listed in the applicable technical manual, is to be replace. 0007 00-10
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
NOTE
• The following inspection is required on helicopters, which have the swashplate link assemblies specified in following step. If these swashplate links are not installed, this inspection is not required. • Cracks of spherical bearing will be found on uniball surface usually starting at the outer lip and running parallel to the bolt axis across the bearing.
With expandable pin installed, visually inspect spherical bearings of forward longitudinal swashplate link assemblies, 70400-08110-048, 70400-08110-049, and 70400-08110-053; aft longitudinal swashplate link assemblies, 70400-08110-048, 70400-08110-050, and 70400-08110-054; and lateral swashplate link assemblies, 70400-08151-046, 70400-08151-048, and 70400-08151-050 for cracks. If no cracks are found and expandable pin is properly installed, inspection is complete.
If one crack is found, do this: Check Teflon liner for deterioration or extrusion between spherical bearing outer race. NONE ALLOWED. Replace swashplate link if liner deterioration or extrusion is found. Check spherical bearing for radial play. NONE ALLOWED. Replace swashplate link if radial play is found. Check gap under expendable pin washer using feeler gage, while pin is installed. GAPSHALL NOT EXCEED 0.002 -INCH. If gap exceeds 0.002-INCH reinstall expandable pin to obtain correct gap.
If expandable pin has passed gap check, perform torque check while pin is installed as follows: (a) Remove cotter pin from expandable pin. (b) Insert 1/4-inch Allen wrench into end of expandable pin. (c) While holding Allen wrench firmly, apply 300 inch pounds of torque to expandable pin nut. MINIMUM TORQUE OF 300 INCH-POUNDS MUST BE ACHIEVED WITHOUT MOVEMENT OF NUT. If nut moves before minimum torque is reached, replace swashplate link. (d) If minimum torque is achieved, remove Allen wrench and install new cotter pin.
0007 00-11
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
If all of the above conditions are met, swashplate link may remain in use for an additional 10 flight hours before replacement is required. 6.21
Inspect main rotor scissors as follows:
0.5
A
0.10
A
Using a dial indicator inspect scissors attachment bearings on swashplate for radial and axial play. Using a dial indicator inspect upper rotating scissors bearings for radial and axial play. Using a dial indicator inspect lower rotating scissors bearings for radial and axial play. 6.22
Inspect main transmission as follows:
B
Inspect main transmission mounting lugs for cracks, dents, nicks, corrosion, and security. Check engine input seal area for oil leaks. MWO 50-43 > Inspect dowel pin retention bolts and retaining angles for deformation and security. < W/O MWO 50-43 > Inspect dowel pins for signs of axial or rotational play on main gear box with slippage strip. < W/O MWO 50-43 > Inspect sealing compound covering dowel pins for bulging, blistering, and cracking. <
6.23
Inspect gust lock as follows:
0.01
Engage gust lock. 0007 00-12
B
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
Inspect gust lock for damage, wear, and security. Release gust lock. 6.24
Inspect oil cooler and radiator as follows:
0.04
Remove oil cooler duct access cover. Inspect oil cooler drive shaft for cracks, corrosion, damage and security. Inspect oil cooler duct interior for debris and obstructions. Inspect oil cooler fan for obstructions. Inspect fan rotor for debris trapped inside pockets between fan blades. Do not remove epoxy in pockets used for balancing rotor. Inspect radiator for dirt and debris.
Inspect support structure for cracks (pay particular attention to bulkhead attachment flanged brazed area). Inspect outer fuselage skin and external brackets of driveshaft viscous damper supports for cracks.
Inspect drive shaft bearing supports for cracks and security.
Inspect fuel crossfeed breakaway valves and tee breakaway valves for visible yellow line around center of valve.
0007 00-13
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
On helicopters with sleeve adapter, 70361-03011-105 installed, inspect slots in sleeve adapter for obstructions and debris. 6.25
Inspect oil cooler viscous damper bearing for debris, damage, or overheating as follows: Turn main rotor blades as required to gain access to oil cooler and engage gust lock.
NOTE Movement of the viscous damper bearing tube assembly is not cause for replacement of bearing. Grease purged from viscous damper bearing assembly, withno accompanying discoloration or indicationof damage to bearing, is not cause for replacement. On helicopters with sleeve adapter, 70361-03011-041, remove access panel at rear of oil cooler duct. Using an inspection mirror and flashlight, inspect area inside of duct for debris. Use flexible borescope to inspect area at forward end of viscous damper bearing and between viscous damper bearing assembly and duct.
On helicopters with sleeve adapter, 70361-03011-105, using slots in sleeve, inspect inside of duct for debris located at the forward end of viscous damper bearing, and between viscous damper bearing assembly and duct.
If debris is present at forward end of viscous damper bearing or between bearing and duct clean out debris per applicable maintenance manual. Check bearing for evidence of overheating (temperature discoloration) and debris damage. Pay particular attention to bearing seal.
0007 00-14
0.01
B
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
0.02
A
B
0.02
A
0.01
A
Inspect bearing assembly for proper fluid level, indicated by bubbles in the fluid. Inspect viscous damper bearing for fluid leakage. Install oil cooler duct access cover. 6.26
Inspect AN/ALQ-144 IRCM transmitter as follows: Inspect AN/ALQ-144 IRCM transmitter for security, scratches, cracks, and cleanness.
Check power cables for chafing against APU access door.
Inspect shock mounts and bonding straps, mounts, and fairing for cracks and missing attachment screws.
6.27
Inspect APU AC generator as follows: Inspect APU AC generator for security of mounting, security of electrical connections, and dirt or excessive oil accumulation.
Inspect generator casing for cracks. Check generator air inlet and exhaust area for foreign object accumulation. 6.28
Inspect APU assembly as follows:
0007 00-15
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
A
B
Check APU exhaust for security and damage. Inspect accessory drive and reduction drive mating surfaces for oil leaks. Remove fuel control pan cover. Check fuel lines and fuel control enclosure for fuel leaks. Check lines for cracks and kinks. Inspect fuel tube bundle for chafing. Install fuel control pan cover. Inspect APU support mounts and attaching hardware for damage and security. 6.29
Inspect engine/APU fire extinguisher as follows:
0.01
Inspect engine/APU fire extinguisher containers for proper pressure reading on gages versus temperature. Check lines for cracks and security. Check for loose lines and fittings.
0007 00-16
TM 1-1520-237-PMS 0007 00 Seq. No.
Item and Procedure
MOS 15T
MH A
B
Manually check directional control valve flapper for freedom of movement. When tab is released, it should spring back to its original position. Check wiring at fire extinguisher container electrical connectors for damage. 6.30
Inspect APU directional valve for freedom of movement. Position cockpit switches as follows:
0.01
A
0.01
A
Fire Extinguisher: OFF. Battery: ON. Pull APU T-handle. Valve should rotate. Push APU T-handle back in. Valve should rotate back. Battery: OFF 6.31
Inspect main rotor pylon as follows:
Open engine cowlings. Inspect starter for proper oil level and leakage. Oil must be between over flow and machined step in fill port. Inspect engine cowlings for cracks and missing fasteners. Secur e engine cowlings.
0007 00-17
B
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
A
B
Check engine cowling latches for cracks, positive latching, and secure closure. Check engine air inlets for damage, missing fasteners, and foreign objects. Inspect elastomeric gimbal for separation and bolt breakage. 6.32
Elastomeric Gimbal, 70361-08001-101. Inspect elastomeric gimbal for separation and bolt breakage. Check eight Allen-head bolts for tightness using finger pressure only. If 1 to 4 bolts are loose, inspect for bond separation using a 0.005-inch feeler gage. If more than 4 bolts are loose, replace gimbal. Inspect input module seal for evidence of oil leakage. Inspect upper and rear main rotor pylon fairings for cracks and missing fasteners.
6.33
Inspect HIRSS > as follows: <
0.09
Inspect rear fairing and panel for cracks, dents, and security of attachment hardware.
0007 00-18
TM 1-1520-237-PMS
Seq. No.
Item and Procedure
0007 00
MOS 15T
MH A
B
0.09
A
B
Inspect nacelle for cracks, dents, and security of attachment hardware. Inspect exhaust extender for cracks, dents, and security of attachment hardware. Visually inspect core and baf fle for warpage and condition of emissive coating. Inspect deswirl duct for security and damage. Inspect firewall support angle, lower support fitting, and fail-safe plate for condition and security. 6.34
If standard engine exhaust modules are installed, inspect as follows: Inspect exhaust fairings for cracks and missing fasteners. Inspect exhaust ejector for damage and foreign objects.
6.35
Close and secure all access panels, doors, cowlings, and covers.
0.01
A
B
6.36
Inspect all area No. 6 antennas for cracks, dents, scratches, cleanness, and missing attachment hardware.
0.04
A
B
6.37
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0007 00-19/20 blank
TM 1-1520-237-PMS 0008 00 PREVENTIVE MAINTENANCE SERVICES 40-HOUR INSPECTION CHECKLIST FOR UH-60A, UH-60L, EH-60A, HH-60A, AND HH-60L POWER ON
INITIAL SETUP: Tools and Special Tools
Personnel Required
Aircraft Mechanic’s Toolkit, SC 5180-99-B01
UH-60 Helicopter Repairer MOS 15T (2)
Materials/Parts
References
Brush, Cleaning, Item 59 WP 1803 00 Hydraulic Fluid, Fire Resistant, Item 144, WP 1803 00 Lubricating Oil, General Purpose, Item 185, WP 1803 00 Towel, Machinery Wiping, Item 344, WP 1803 00
Seq No.
TM 1-1520-237-23 WP 1803 00
Item and Procedure
MOS 15T
MH A
B
A
B
POWER ON
NOTE Sequence Number 7.1 applies only to helicopters equipped with stabilator system test panel. 7.1
Perform actuators position comparator check part of stabilator system operational check UH-60A, UH-60L, HH-60A, HH-60L > (TM 11-1520-237-23) or EH-60 > < (TM 11-1520-249-23-2). <
0008 00-1
0.03
TM 1-1520-237-PMS
Seq No.
7.2
Item and Procedure
HH-60A HH-60L > Inspect external electrical rescue hoist as follows: <
0008 00
MOS 15T
MH A
B
0.4
A
B
0.01
A
B
Reel out entire length of rescue hoist cable. Check cable for corrosion, kinks, separated strands, wear, and broken or frayed wires. Pay particular attention to area around hook. Reel in hoist cable with gloved hand and wipe cable with clean heavy cloth. 7.3
CABS > Tilt back copilots seat. Apply electrical power to helicopter and check the following: < Verify system fault indicator has no fault indication. Press PTD button and verify all LEDS illuminate andafter 3 seconds go off.
7.4
Inspect for foreign object damage and ensure all access panels or doors opened or removed for this inspection are closed or reinstalled.
END OF WORK PACKAGE
0008 00-2
TM 1-1520-237-PMS
By Order of the Secretary of the Army:
PETER J. SCHOOMAKER
General, United States Army Chief of Staff
Official:
JOYCE E. MORROW
Administrative Assistant to the S ecretary of the Army 0704602
DISTRIBUTION: To be distributed in accordance with Initial Distribution Number (IDN)
314143
requirements for TM 1-1520-237-PMS.
These are the instructions for sending an electronic 2028 The following format must be used if submitting an electronic 2028. The subject line must be exactly the same and all fields must be included; however only the following fields are mandatory: 1, 3, 4, 5, 6, 7, 8, 9, 10, 13, 15, 16, 17, and 27. From: “Whomever”
To: [email protected] Subject: DA Form 2028
1. From: Joe Smith 2. Unit: home 3. Address: 4300 Park 4. City: Hometown 5. St: MO 6. Zip: 77777 7. Date Sent: 19--OCT--93 8. Pub. No.: 55--2840--229--23 9. Pub Title: TM 10. Publication Date: 04--JUL--85 11. Change Number: 7 12. Submitter Rank: MSG 13. Submitter Name: Joe 14. Submitter MName: T
15. Submitter LName: Smith 16. Submitter Phone: 123--123--1234 17. Problem: 1 18. Page: 2 19. Paragraph: 3 20. Line: 4 21. NSN: 5 22. Reference: 6 23. Figure: 7 24. Table: 8 25. Item: 9 26. Total: 123 27. Text: : This is the text for the problem below line 27.
