TM 1-1520-237-PMI_Helicopter_EH-60_UH-60_2005

* TM 1-1520-237- PMI

TECHNICAL MANUAL PHASE MAINTENANCE INSPECTIONS PERIODIC INSPECTION CHECKLIST FOR ARMY MODELS UH-60A, UH-60L, EH-60A, UH-60Q AND HH-60L HELICOPTERS WARNING – This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C. Sec. 2751 et seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et seq. Violation of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions provisions of DOD Directive 5230.25. DISTRIBUTION STATEMENT D: Distribution authorized to the DOD and DOD contractors only due to Critical Technology effective as of 15 June 2003. Other requests must be referred to Commander, US Army Aviation and Missile Command, ATTN: SFAE-AV-UH/L, Redstone Arsenal, AL 35898-5230. DESTRUCTION NOTICE – Destroy by any method that will prevent disclosure of contents or reconstruction of the document.

* This manual supersedes T M 1-1520-237-PMS-2, dated 1 May 2003, including all changes.

HEADQUARTERS, DEPARTMENT OF THE ARMY 30 APRIL 2005

TM 1-1520-237-PMI

LIST OF EFFECTIVE PAGES Insert latest change pages; dispose of superseded pages in accordance with regulations. NOTE: On a changed page, the the portion of the the text affected by the latest change change is indicated by a vertical line in the outer margin margin of the page. Changes to illustrations are indicated by a vertical line in the outer margin of the page next to the illustration title. Dates of issue for original and change pages are: Original 0........................ 0........................ 30 April 2005

The total number of pages in this manual is 124.

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UH-60-05-SOF-02 Enhanced Scheduled Maintenance (ESM) Program

221920Z MAR 05

UNCLASSIFIED MSG DTG 221920Z MAR 05 FROM CDRAMCOM, REDSTONE ARSENAL, AL //AMSAM-SF-A// SUBJECT - SAFETY OF FLIGHT (SOF), TECHNICAL, RCSCSGLD-1860 (R1), ALL UH-60A/L, EH-60A/L, UH-60Q, HH-60L, AND MH-60L SERIES AIRCRAFT, ENHANCED SCHEDULED MAINTENANCE (ESM) PROGRAM IMPLEMENTATION, UH-60-05-SOF-02 ................... NOTE ................... This message is effective until rescinded or superseded. ................... NOTE ................... This message is issued IAW AR 95-1 and has not been transmitted to units subordinate to addressees. Addressees will immediately retransmit this message to all subordinate units, activities or elements affected or concerned. MACOMs will immediately verify this transmission to the AMCOM SOF Compliance Officer (AMSAM-SF-A, [email protected]). ................... NOTE ................... MACOM commanders may authorize temporary exception from message requirements IAW AR 95-1, Ch 6. Exception may only occur when combat operations or matter of life or death in civil disasters or other emergencies are so urgent that they override the consequences of continued aircraft operation. ................... NOTE ................... Commanders who are unable to comply with the requirements of this message within the time frame specified will change the affected aircraft status symbol to a Red //X//.


221920Z MAR 05

accommodating interval. As a result, there is no airworthiness impact in implementing the ESM Program which will result in significant savings in maintenance man-hours and increase flexibility for the UH-60 maintenance community. 1.2. Message Purpose 1.2.1. Revise/Change recurring inspection intervals, established in previous safety messages and Technical Bulletins (TB). 1.2.2. Announce issuance of TB 1-1520-237-20-266 which changes the current PMS-1 inspection from a 10 Hour/14 Day to a daily (PMD) and 40 Hour inspection (PMS) and revises the current Preventative Maintenance Services schedule from 500 flight hours to 350/700 flight hours. 1.2.3. Revise recurring Special Inspection intervals. 1.2.4. Announce forthcoming changes to TBO/Retirement Life Limits of TM 1-1520-237-23 and adjust oil sampling requirements to accommodate scheduled ESM requirements of TB 1-1520-237-266. 2. END ITEMS AFFECTED - All UH-60A/L, EH-60A/L, UH-60Q, HH-60L and MH-60L series aircraft. 3. ASSEMBLIES/COMPONENTS/PARTS AFFECTED - N/A. 4. INITIAL TAMMS (THE ARMY MAINTENANCE MANAGEMENT SYSTEM) COMPLIANCE REQUIREMENTS 4.1. Upon receipt of this message, make the following entry on the DA Form 2408-13-1. Enter a Red Horizontal Dash //-// status symbol with the following statement: "Comply with requirements of UH-60-05-SOF-02 NLT 30 June 2005."

NOTE


221920Z MAR 05

5.1. Aircraft - Submit Task/Inspection Compliance Report for this message to "mailto:[email protected]" NLT 7 Jul 05. 5.2. Retail Stock (Installation level and below) - N/A. 5.3. Wholesale Stock (Including Depot stock, Depot Maintenance and Single Stock Fund) N/A. 6. SPECIAL PROVISIONS TO MESSAGE REQUIREMENTS (AIRCRAFT) 6.1. Aircraft in AVIM or Depot level maintenance (to include RESET) - Commanders, facility managers and contractors will continue to issue aircraft IAW current maintenance procedures. Aircraft issued 30 June 2005 or later must be in compliance with the ESM Program IAW para 7 of this SOF. 6.2. Aircraft currently maintained under the provisions of Airworthiness Release (AWR) 1220 are exempt from the provisions of this message. 6.3. Aircraft in Surface/Air shipment - Unit commanders in receipt of deployment/redeployment orders and unable to comply prior to the date specified in para 4.1. may defer initial requirements as follows - Comply with all message requirements within 90 days of arrival. 7. TECHNICAL PROCEDURES/INSTRUCTIONS ................... NOTE ..................... Maintenance schedules imposed by previous Safety Messages referencing 10 Hour/14 Day and Before First Flight of the Day visual inspections, have been incorporated, and will be completed during the Daily Inspection (PMD). This message is the authority to change current DA Form 2408-13-1 entry referencing compliance at 10 Hour/14 Day frequency to a Daily visual inspection ................... NOTE ................... ULLS-A users may use this message as authority to u se the updated H-60 series Inspection Code


221920Z MAR 05

The ESM program will only be implemented in its entirety at company/detachment level or above when sufficient publications are available. Each individual aircraft shall require a PMD and PMS checklist retained in the aircraft. .................... NOTE ................... Contact the Technical POC in TB 1-1520-237-20-266 concerning questions with induction/scheduling of aircraft into the ESM Program. 7.2. The PMD will be implemented as follows: 7.2.1. When in receipt of TM 1-1520-237-PMD, the PMD required entry will be entered on aircraft DA Form 2408-13 IAW DA PAM 738-751. The entry may be cleared when the Preventive Maintenance Daily Inspection (PMD) is performed in accordance with TM 11520-237-PMD, TM 1-1500-328-23, and DA PAM 738-751. The PMD may be accomplished after completion of the last flight of the mission day or prior to the first flight of the mission day. All Before First Flight inspections are contained within the PMD and do not require additional entries. The PMD inspection requirement is satisfied for 7 days if the aircraft is not flown. 7.2.2. A 10 Hour special inspection of the blade pin shall be scheduled and monitored as a DA Form 2408-18 entry as outlined in TB 1-1520-237-20-266. 7.3. The 40/Hour Preventive Maintenance Service (PMS) will be implemented as follows: 7.3.1. Add the entry to DA Form 2408-18 for PMS at a 40 hour interval since the last documented 30 Hour/42 Day inspection was performed. Delete the entries for 10 Hour/14 Day and 30 Hour/42 Day requirement. 7.3.2. Realign the 30 Hour Special Inspection requirements as outlined in TB 1-1520-237-20266 with the (PMS) 40 Hour Service. 7.4. Revise recurring Special Inspections on the DA Form 2408-18 as follows:


221920Z MAR 05

................... NOTE ..................... Units are authorized to use the current maintenance program IAW TM 1-1520-237 series with changes 1 and 2 during the implementation period (up to 30 Jun 05) until conversion to the ESM program has been fully incorporated. 7.5.2. All aircraft currently inducted into a PMS-2 maintenance inspection will complete that inspection. Refer to TB 1-1520-237-20-266 for specific examples of induction into the Enhanced Scheduled Maintenance (ESM) Program. ................... NOTE.................... The TB/TMs associated with this SOF are scheduled to be printed and distributed in April 2005. Official copies of the TB/TMs are available for download as below. These copies may be used for advance viewing and implementation at the discretion of the unit commander. 7.6. TB 1-1520-237-20-266, TM 1-1520-237-PMD/PMI/PMS checklists are available at website shown below. Enter the website addresses using lower case letters only. Access to the AMCOM Safety website requires an AKO ID and password. 7.6.1. Download TB 1-1520-237-20-266 at"https://ams14.redstone.army.mil/safety/sof/pic/u60s0502tb.pdf". 7.6.2. Download TM 1-1520-237-PMD at "https://ams14.redstone.army.mil/safety/sof/pic/u60s0502pmd.pdf". 7.6.3. Download TM 1-1520-237-PMS at "https://ams14.redstone.army.mil/safety/sof/pic/u60s0502pms.pdf". 7.6.4. Download TM 1-1520-237-PMI at "https://ams14.redstone.army.mil/safety/sof/pic/u60s0502pmi.pdf".


221920Z MAR 05

12.1.4. TM 1-1520-237-PMS-1 - Preventive Maintenance Services, 10 Hour/14 Day Inspection Checklist for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 1 May 2003. 12.1.5. TM 1-1520-237-PMS-2 - Preventive Maintenance Services, Periodic Inspection Checklist for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 1 May 2003. 12.1.6. TM 1-1520-237-PMD - Preventive Maintenance Daily, Daily Inspection Checklist for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 30 Apr 05. 12.1.7. TM 1-1520-237-PMS - Preventive Maintenance Services, 40 Hour Inspection Checklist for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 30 Apr 05. 12.1.8. TM 1-1520-237-PMI - Phase Maintenance Inspections, Periodic Inspection Checklist for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 30 Apr 05. 12.1.9. TB 1-1520-237-20-266, H-60 Series Aircraft Preventive Maintenance Daily (PMD), 40 Hour Preventive Maintenance Service (PMS) and 700 Hour Split Maintenance Inspection (PMI) Implementation". 12.1.10. TM 1-1520-237-23, Aviation Unit and Intermediate Maintenance for Army Models UH-60A, UH-60L, EH-60A, UH-60Q and HH-60L Helicopters, 1 May 2003. 12.1.11. TM 1-2840-248-23, Aviation Unit And Intermediate Maintenance Manual, Engine, Aircraft, Turboshaft Models T700-GE-700, T700-GE-701, T700-GE-701C, 1 Jun 99 12.2. Publication changes - Routine Publication changes (reference 12.1.10 and 12.1.11) are currently in progress to support this message. In the absence of revised changes, this message may be used as authority to implement the changes until official documentation


221920Z MAR 05

13.5. ULLS-A Inspection Legitimate Code File POCs are 13.5.1. Primary - Mr. San Yen Lee, AMSAM-MMC-MA-NM, DSN 746-4468 or (256) 8764468. FAX is DSN 746-4904 or (256) 876-4904. Email is "[email protected]". 13.5.2. Alternate - Mr. Morgan Evans, AMSAM-MMC-MA-NM, DSN 897-1486 or (256) 3131486. FAX is DSN 746-4904 or (256) 876-4904. Email is "[email protected]". 13.6. Safety POCs are 13.6.1. Primary - Mr. Frank Rosebery (SAIC), AMSAM-SF-A, DSN 788-8631 or (256) 8428631. Fax is DSN 897-2111 or (256) 313-2111. Email is "[email protected]". 13.6.2. Alternate - Mr. Ron Price, AMSAM-SF-A, DSN 788-8636- or (256) 842-8636, Fax is DSN 897-2111 or (256) 313-2111. Email is "[email protected]". 13.7. Foreign Military Sales POC is Mr. Ronnie W. Sammons, AMSAM-SA-AS-UT, DSN 8970875 or (256) 313-0875. Fax is DSN 897-0411 or (256) 313-0411. Email is "[email protected]". 13.8. After hours, contact the AMCOM Operations Center (AOC) DSN 897-2066/7 or (256) 313-2066/7. ................... NOTE ................... ....A listing of published safety messages can be viewed at ...."https://ams14.redstone.army.mil/safety/sof/index.html". ....This is a secured website which requires an Army Knowledge ....Online (AKO) ("www.us.army.mil") ID and password. ....

TM 1-1520-237-PMI (1) Space is provided on each checklist form for entering the following data: (a) The number of the periodic inspection being performed. (b) Aircraft serial number.

18. FAULTS AND/OR REMARKS. When aircraft disassembly is required to complete an inspection requirement, the maintenance related actions will be entered on a DA Form 2408-13-2/2408-13-2-E. The number "2408-13-2" shall be entered in the "Fault and/or Remarks" column on the inspection checklist. If no aircraft disassembly is required to complete the inspection, this column will be left blank.

(c) Date of the inspection. 19. ACTION TAKEN. (2) For each inspection item a column is provided for entering the following data: (a) Status. (Not Used) (b) Fault and/or Remarks. (c) Action Taken. (d) Initials/PID of person performing the inspection. b. Figure 1-2 shows examples of methods used to make entries on the periodic maintenance checklist forms. c. Additional 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. 17. STATUS SYMBOLS. This column should be left blank.

a. Upon completion of each inspection requirement task listed in the checklist, if no faults were found relating to the inspection, the person who performed the inspection will enter "Insp OK" in the "Action Taken" block of the checklist and enter their initials in the "Initial" block. b. If a deficiency or fault that is related to the inspection requirement task is discovered, the person who performed the inspection shall enter "Insp Compl" in the "Action Taken" block, enter the fault or deficiency on DA Form 2408-13-1/2408-13-1E, and then enter their initials in the "Initial" block of the checklist. If an inspection item is not applicable to the specific equipment installed on an individual aircraft, a N/A entry is required. The initials of the person making the entry shall be entered in the Initial column. 20. INITIAL. The person performing the inspection shall enter their initials/PID in the Initial column opposite the first line of the Action Taken entry.

TM 1-1520-237-PMI b. Hover Infrared Suppressor System HIRSS. UH-60A serial numbers 86-24560 and subsequent, UH-60L, and EH60A, or UH-60A modified 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. c. 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 modified by MWO 55-1520-237-50-43. Icon shown as MWO 50-43. UH60A prior to serial number 87-27004 and EH-60A prior to serial number 87-24663 not modified by MWO 55-1520237-50-43. Icon shown as W/O MWO 50-43. d. Roll Vibration Absorber ROLL. UH-60L serial numbers 90-26278 and subsequent, or modified by MWO 1-1520-237-50-60 and EH-60A serial numbers 87-24669 and subsequent. Icon shown as ROLL. e. UH-60Q MEDEVAC Helicopter UH-60Q. UH-60A helicopters modified to provide MEDEVAC missions. Icon shown as UH-60Q. f. HH-60L MEDEVAC Helicopter HH-60L. UH-60L helicopters modified to provide MEDEVAC missions. Icon shown as HH-60L

TM 1-1520-237-PMI

AREA NO. 5

AREA NO. 6

AREA NO. 4

AREA NO. 1

AREA NO. 3

AREA NO. 2

AB0947_1 SA

Figure 1: Area Diagram

TM 1-1520-237-PMI

AREA NO. 1: Cockpit Section

AREA NO. 2: Cabin Section

AREA NO. 3: Transition Section

AREA NO. 4: Tail Cone Section

AREA NO. 5: Tail Rotor Pylon Section

AREA NO. 6: Main Rotor Pylon

All surfaces, material, components, and equipment inside and outside of the cockpit and electronics compartment, and extending rear to manufacturing break point at fuselage station 247.0. All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 247.0 to STA 379.0 (includes, but not limited to, main landing gear, UH-60Q HH-60L rescue hoist, and medical interior<). All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 379.0 to STA 485.0. All surfaces, material, components, and equipment inside and outside of the fuselage, from STA 485.0 to STA 648.0. 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). 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).

TM 1-1520-237-PMI Table 1-1. Signature Sheet Signature of Person Accomplishing Necessary Work

Initial

Signature of Person Accomplishing Necessary Work

Initial


Initial


Initial


Initial


Initial


Initial


Initial


Initial

Signature of Maintenance Supervisor

Initial

Signature of Technical Inspector

Initial


Initial


Initial

Signature of Maintenance Officer

Initial

TM 1-1520-237-PMI

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

Figure 1-2. Example of Using Periodic Maintenance Checklist

TM 1-1520-237-PMI

Table 1-2. Final Records Checklist This checklist is provided to ensure the indicated forms and records have been inspected for presence, completeness, legibility, and accuracy prior to releasing the aircraft from a periodic inspection. Placing the initials of the inspector, in the appropriate initial block, will indicate verification of inspection. AIRCRAFT LOGBOOK DA FORM 2408 DA FORM 2408-12 DA FORM 2408-13 DA FORM 2408-13-1 DA FORM 2408-13-2 DA FORM 2408-14-1 DA FORM 2408-18 TM 1-1520-237-PMD TM 1-1520-237-MTF LOCALLY REQUIRED FORMS

INITIAL

HISTORICAL RECORDS DA FORM 2408-5 DA FORM 2408-5-1 DA FORM 2408-15 DA FORM 2408-15-2 DA FORM 2408-16 DA FORM 2408-16-1 DA FORM 2408-17 DA FORM 2408-19-2 DA FORM 2408-20 LOCALLY REQUIRED FORMS

INITIAL

TM 1-1520-237-PMI

Table 1-2. Final Records Checklist PRODUCTION CONTROL RECORDS FLOW CHART STATUS BOARD WORK ORDER FILE MWO FILE CONFIGURATION CHART 2405 LOG 1352 REPORTS LOCAL RECORDS

INITIAL

QUALITY CONTROL TBO FILE QA FILE SERIAL NUMBER FILE AOAP FILE INVENTORY RECORDS WEIGHT AND BALANCE MSG FILE DA FORM 2410 SUBMITTED LOCAL RECORDS

INITIAL

TM 1-1520-237-PMI

SECTION ll PHASE INSPECTION CHECKLIST PMI 27. INSPECTION PROCEDURES The following checklist is to be locally reproduced each time periodic maintenance is due.

TM 1-1520-237-PMI

PHASE INSP NO.____________ Area Name and No. 1. COCKPIT SECTION PHASE Inspection Requirements NO.

•

•

•

•

1 C

PERIODIC INSPECTION CHECKLIST Aircraft Serial No. MH

MOS Status

NOTE Before starting this inspection, review aircraft forms and records for discrepancies (PAM 738-751). Review cleaning requirements in TM 1-1520-237-23, Chapter 1, Section 4. Review lubrication requirements in TM 1-1520-237-23, Chapter 1, Section 5. Refer to TM 1-1520-237-23 for specific inspection procedures and accept/reject criteria. 1.1 Inspect exterior for cracks, distortion, delamination of reinforced plastic, and security of fasteners. −

−

−

Inspect air inlets for obstruction. Inspect cockpit tub drain holes for blockage. Inspect nose vibration absorber for wear and security.

0.05

15T

Faults and/or Remarks

Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. 1 1.2 Inspect outboard and center windshields and upper and lower window panels as follows:

MH

MOS Status

0.06

15T

1.3 Inspect windshield wiper system as 0.04 follows:

15T

−

−

−

−

1

Aircraft Serial No.

−

−

Check outboard windshield panels for damage, delamination, general clarity, loose screws, and visible signs of leakage. Check center windshield panel for damage, delamination, general clarity, loose screws, and visible signs of leakage. Check upper window panel for damage, general clarity, loose screws, and visible signs of leakage. Check lower window panel for damage, general clarity, loose screws, and visible signs of leakage.

Inspect windshield wiper blades for wear, cracks, and deterioration. Inspect wiper arms for damage and loss of tension against windshield.


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. Inspect windshield wiper converters, flex drives, and motor for damage and security.

Aircraft Serial No. MH

MOS Status

−

1

1.4 Inspect nose door as follows:

0.03

15T

1.5 Inspect controllable searchlight and 0.01 landing light as follows:

15T

−

−

−

−

−

−

1

−

−

Inspect interior and exterior of nose door for cracks, distortion, and security of fasteners. Make sure vent and duct drain line openings are free of obstructions. Inspect door seal for deterioration and loose adhesive bonds. Inspect interior for signs of leakage. Check latches for corrosion security and positive latching.

and

Check hinge fittings for cracks using 10X magnifying glass.

Inspect controllable searchlight and landing light lenses for cracks, cleanness, and looseness. Check that lights are stowed properly.


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements MH NO. 1 1.6 Inspect cockpit doors as follows: 0.24 C Perform a functional checkout of jettison mechanism on both cockpit doors.

Aircraft Serial No. MOS Status 15T

−

−

−

−

−

−

1 C

Inspect both doors for cracks, corrosion, distortion and security of fasteners. Inspect seals for deterioration, loosening of bonds, and signs of leakage. Check doors for freedom of movement and that latches operate without binding and hold securely. Inspect sliding windows for ease of operation (no binding) and proper closure. Inspect one-piece windows condition and security.

for

1.7 Inspect pilot's and copilot's seats as follows: −

Inspect pilots and copilot's seat frames, buckets, and wings for visible damage and wear on moving parts.

0.1

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. Check for wear, binding, any condition preventing proper operation, and secure locking.


MOS Status

−

−

−

1

Check security of clevis screws and lockwire on ARA seats serial numbers 0009 through 1773. Check torque stripe security detail of trunnion bolts on all Simula seats. If torque stripe indicates slippage, refer to maintenance procedures for corrective action. If torque strip not applied, refer to maintenance procedures for installation of torque stripe to trunnion bolts.

1.8 Inspect area below copilot's seats as follows: −

−

−

−

pilot's

and 0.06

Place pilot and copilot's seats in the reclining position. Remove protective fabric covers over compartments. Inspect brake lines security, and leaks.

for

chafing,

Inspect parking brake valve and slave valves for security and leakage. Inspect parking brake linkage for wear and security.

15T 15N


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. Inspect coax cables, connectors, FM coupler, ADF amplifier, and Doppler antenna for damage and security.


MOS Status

−

−

−

−

1

Inspect pitot-static lines for damage, obstructions, cleanness, and security. Install protective fabric covers over compartments. Place pilot and copilot's seats in the upright position.

1.9 Inspect engine control quadrant as 0.02 follows: −

−

−

Inspect engine control quadrant for condition. Check that NO. 1 and NO. 2 ENG POWER CONTROL and NO. 1 and NO. 2 ENG FUEL SYS levers are shut off and #1 and #2 ENG EMER OFF Thandles are fully forward. Inspect flex cable mounting bracket at STA 235 overhead for security and chafing of cables.

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements MH NO. 1.10 Inspect pilot's and copilot's cyclic 0.04 1 sticks as follows: −

−

−

−

−

−

−

−

−

Open boots at base of pilot and copilot's cyclic sticks. Remove cockpit floor panels. Inspect pilot and copilot's cyclic sticks for condition.

Inspect wiring for chafing, or damaged insulation and security of connections. Inspect stick shafts, sockets, and supports for cracks, corrosion, and security. Check that stick to yoke attachment bolt is installed with head facing to left. Check that cotter pin is installed properly and does not contact wire bundle. Check wire bundle to fuselage for proper size clamp and that wire bundle will not slip through clamp. Inspect bearings for friction and wear. Inspect lockwire on stop-bolts for proper installation and evidence of contact with wire bundle.

Aircraft Serial No. MOS Status 15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. 1 1.11 Inspect pilot's and collective sticks as follows: −

−

−

−

−

−

Aircraft Serial No. MH copilot's 0.04

MOS Status 15T

Open boots at base of pilot and copilot's collective sticks. Inspect pilot and copilot's collective sticks for condition. Inspect wiring for chafing, damaged insulation, and security.

or

Inspect stick shafts, sockets, and supports for cracks, corrosion, and security. Inspect bearings for friction and wear. Inspect copilot's collective stick for proper telescoping action.

Inspect friction lock on pilot's stick for proper action. 1.12 Inspect pilot's and copilot's yaw control pedals as follows: −

1

−

−

Open boots at base of yaw control pedals. Inspect pilot and copilot's yaw control pedal and shaft assemblies and master cylinder supports for cracks, corrosion, and security.

0.1

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. −

−

−

MH

MOS Status

Inspect bearings for friction and wear. Inspect boots at base of pedals for loose fit, cracks, splitting, and damage. Make sure there are no openings through which foreign objects may enter flight control linkage area. Inspect brake master cylinders for security and leakage.

Inspect pedal adjusters for proper operation. 1.13 Inspect flight control system 0.06 15T components as follows: −

1 C

Aircraft Serial No.

−

−

Inspect flight control rod assemblies for evidence of external corrosion. Inspect control rods, bellcranks, and flight control supports for cracks, distortion, corrosion, and security.

−

Inspect bearings for play.

−

Install cockpit floor panels.

−

Make sure all boots at base of cyclic sticks, collective sticks and yaw control pedals are securely closed.


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements MH NO. 1.14 Inspect instrument panel, upper 0.05 1 console, lower console, and circuit breaker panels for security of electrical components. −

−

−

−

−

1

−

15T

Inspect that all lettering on control panels, switches, and circuit breakers is readable. Make sure all circuit breakers are pushed in. Inspect cockpit wiring for chafing, fraying, and evidence of overheating. Inspect connectors for security.

Inspect electronic components for damage and security.

− −

MOS Status

Inspect controls and switches for binding and security.

1.15 Open door at rear of lower console. −

Aircraft Serial No.

Inspect shock mounts for bottoming, corrosion, and security. Inspect electrical connectors and wiring for chafing or damage to insulation and security of connections.

0.05

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements MH NO. Make sure louvers on side of SAS/FPS computer and exhaust ports under front of vibration isolation tray are free from obstruction.

Aircraft Serial No. MOS Status

−

−

−

1 C

Close door at rear of lower console.

1.16 Inspect cockpit interior and close up 0.02 area as follows: −

−

1

Check lower console flexible light for security and damage. Check wires for chafing and fraying, and connectors for security.

Inspect cockpit interior for general cleanness and for evidence of oil leakage from ceiling. Leave cockpit. doors.

Close

and

secure

1.17 UH60A UH60L- Inspect cockpit air bag system (C A B S) as follows: <= −

−

15T

Inspect forward and lateral modules for cracks, loose or missing hardware. Inspect glare shield, brackets, doublers, and helicopter structure for cracks and corrosion.

0.1

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 1. COCKPIT SECTION (CONT) PHASE Inspection Requirements NO. −

−

−

Tilt back copilots seat and check ECSU and mounting bracket for cracks, corrosion, and loose or missing hardware. Apply electrical power to the aircraft and check the following: Verify the SYS fault indication has no fault indication. Press the PTD button and verify all LEDs illuminate and after approximately three seconds go off.


MOS Status


Date: Action Taken

Initial

TM 1-1520-237-PMI

PHASE INSP NO.____________

PERIODIC INSPECTION CHECKLIST

Area Name and No. 2. CABIN SECTION

Aircraft Serial No.

PHASE Inspection Requirements NO. 1 2.1 Inspect left and right side cabin exterior as follows: −

−

1 C

−

−

MOS Status

0.06

15T

0.06

15T

Inspect cabin steps, hand-holds, hard points, and left and right side exterior skins for cracks, corrosion, distortion, and security of fasteners. Make sure external ICS covers are in place.

2.2 Inspect troop/cargo doors as follows: −

MH

Inspect troop/cargo doors exterior surfaces for corrosion, distortion, cracks, and for loose or missing fasteners. Open and close doors. Make sure doors travel through full range with no binding, and are secure in tracks. Check upper and lower support fittings for wear.

roller


Date: Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 2. CABIN SECTION (CONT) PHASE NO.

Inspection Requirements −

MH

MOS Status

Check front and rear door latches for positive latching.

1

2.3 Inspect gunner's windows exterior for damage, loose or missing fasteners, and seals for separation and damage.

0.04

15T

1

2.4 Inspect main landing gear shock struts as follows:

0.06

15T

−

−

Remove main landing gear fairings. Inspect exposed piston surface for nicks, scratches, scoring, and cracks.

1

2.5 Inspect left and right main landing gear shock struts for general condition of spherical bearings. Inspect painted area of shock strut assemblies for evidence of corrosion and blistering or flaking paint.

0.04

15T

1 C

2.6 Inspect main landing gear drag beams as follows:

0.1

15T

−

Remove drag beam support fairing.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

−

ROLL> Inspect roll vibration absorbers for wear and security. < Inspect main landing gear drag beam, and drag beam and axle attachment points for cracks and security. With jack pad installed and using a magnifying glass, examine the area within a 3-inch radius of the jack pad, both upper and lower holes, for evidence of cracking. No cracks allowed. Inspect ground wire on left side for security and contact w ith ground. Inspect drag beam switches for security and damage. Inspect bonding jumper for security and damage. Inspect weight on wheels bracket and surrounding area for evidence of corrosion, uneven paint, faded areas, blistering, and pitting. Check wire cutters for security, damage, and corrosion.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

1 C

−

−

−

−

−

−

MOS Status

Inspect brake and brake lines for damage and leakage. Check jackpad retention nut for the presence and alignment of a torque stripe. Inspect the tie down ring attachment bolt for security, damage and corrosion.

2.7 Inspect main landing gear wheels and brakes as follows: −

MH

Deflate main wheel tires to 20 PSI prior to removal. Remove main wheels. Check brake wear indicator pins for minimum length. Inspect brake disc drive keys for wear and security. Inspect wheels for missing or damaged hardware, paying particular attention to bolts and nuts attaching wheel halves. Inspect main landing gear axle for corrosion and damage. Inspect wheel bearings for wear, corrosion, and damage.

0.07

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.


Inspection Requirements

−

−

1 C

Inspect main wheel tires for cuts, wear, or cracks. Repack wheel bearings.

−

Install main wheels.

−

Reinflate to proper pressure.

−

Install drag beam support fairings.

−

Install main landing gear fairings.

2.8 Remove cabin soundproofing.

−

MOS Status

Inspect wheel hubs, and brake components for cracks, corrosion, and damage.

−

−

MH

Inspect cabin soundproofing for loose or missing hardware and torn or oil saturated soundproofing panels. Inspect cabin floors for damage such as buckling, corrosion, cracks, and security of fasteners. Make sure tie down rings are secure and operate freely.

0.06

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



1 C

MH

Inspect cargo hook access door for condition, security, and positive latching.

2.9 Inspect cargo hook as follows: −

−

−

−

−

−

−

MOS Status

0.03

Inspect cargo hook for damage and cleanness. Inspect cargo hook pendant for missing parts and damage, such as missing strain relief, cracked handle, and bent switch guards. Inspect support structure damage and security.

for

Operate manual release. Return load beam to closed position. Check for positive latching. Check to see that hook is free to pivot from side to side. Check explosive cartridge manufacturing/ manufacturing/ installation date. Inspect electrical connectors for security and condition. condition.

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 2. CABIN SECTION (CONT) PHASE Inspection Requirements NO. 1 2.10 Inspect cabin interior primary C structure (excluding cabin tub area beneath floor panels), skins, frames, fittings and stringers for damage, loose or missing fasteners, and corrosion.

MH

MOS Status

0.1

15T

1

2.11 Weigh fire extinguishers and make sure weight is within range s pecified on decal.

0.08

15T

1

2.12 Inspect troop/cargo doors as follows:

0.06

15T

0.04

15T

−

−

1

Inspect troop/cargo doors interior for damage, window jettison mechanism for proper operation. Inspect door seals for deterioration, damage, and separation.

2.13 Inspect interior windows as follows: −

−

of

gunner's

Inspect interior of windows for damage and signs of leakage. Open and close windows. Check for smooth operation and secure closure.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 2. CABIN SECTION (CONT) PHASE Inspection Requirements NO. 1 2.14 Inspect cabin heat/vent ducts for damage.

1

2.15 Inspect gun mounts as follows: −

−

−

−

1

−

MOS Status

0.02

15T

0.05

15T

0.2

15T

Inspect gun mounts for cracks, corrosion, and security. Inspect pintles for freedom of operation, abnormal play at mount fittings and verify that mount latch is working properly. Inspect springs for condition and security. Inspect ammunition boxes for security, damage, and proper stowage.

2.16 UH60L> UH60A Inspect troop and gunner's seats as follows: <= −

MH

Inspect shoulder harness, lap and crotch belts for corrosion, cuts, fraying, and security. Inspect gunner's seat inertia reels for proper operation.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

1

−

−

−

−

−

MOS Status

Inspect for frayed or broken cables and cleanness. Inspect tubing, attenuators, and attachment fittings for damage and security.

2.17 EH60A> Inspect operators' seat as follows: <= −

MH

mission

Inspect mission operators' seat, frames, buckets, and track/frame assemblies for visible damage and wear on moving parts. While sitting in seat, operate seats through full range of horizontal and vertical adjustments. Check for wear, binding, any condition preventing proper operation, and secure locking. Inspect latches for wear and secure locking. Inspect seat cushions for condition. Check lap belts for corrosion, cuts, fraying, and security. Check crotch belt for corrosion, cuts, fraying, and security.

0.1

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

1

Check shoulder corrosion, cuts, security.

harness fraying,

MH for and

Inspect inertia reels for proper operation.

2.18 EH60A> Inspect observer's seat as follows: <= −

−

−

MOS Status

0.02

15T

Inspect for frayed or broken cables and for cleanness. Inspect lap belts and shoulder harness for corrosion, cuts, fraying, and security. Inspect seat tubing, attenuators, attachment fittings for damage and security.

1

2.19 Inspect engine control flex cables running through upper cabin interior for chafing and distortion.

0.03

15T

1 C2

2.20 ESSS> Inspect fuel lines in cabin interior for chafing, distortion, and security. <

0.02

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 2. CABIN SECTION (CONT) PHASE Inspection Requirements NO. 2 2.21 Inspect flight control components C as follows: −

−

−

−

−

−

−

Inspect flight control rod assemblies for evidence of external corrosion. Inspect bellcranks, control rods, torque shafts, and balance springs for corrosion, distortion, cracks, security of mounting and attaching hardware. Check yaw torque shaft lower support structure straps for loose rivets. Perform torque check on bolts attaching torque shafts to lower supports using crisscross pattern. Inspect bearings that support four forward torque tubes in cabin ceiling for wear. Lift dust boot while rotating shaft and check for bearing race movement. Disconnect input and output control rods and check for free rotation and smoothness (no ratchety feeling). Connect control rods.

MH 0.1

MOS Status 15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

MH

MOS Status

Inspect yaw pushrod, quadrant, and torque shafts for corrosion, distortion, cracks, security of mounting, and attaching hardware. Inspect cable quick-disconnect cable collars and ball ends for cracks. Install cabin required.

soundproofing

as

1 C

2.22 Inspect cabin vibration absorber for wear and security.

0.03

15T

1

2.23 Inspect APU accumulator and hand pump as follows:

0.05

15T

−

−

−

−

Inspect handle socket and pivot pins for cracks and wear. Inspect accumulator/reservoir for leakage, security of hold-down clamps, and corrosion. APU start valve, lines, check valves, pressure switch, and pressure gage for leakage, corrosion, and security. Check condition of all clamps.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 2. CABIN SECTION (CONT) PHASE Inspection Requirements NO. 1 2.24 Inspect cabin electrical wiring and components as follows: −

−

MH

MOS Status

0.04

15T

0.01

15T

0.06

15T

Inspect electrical wiring for evidence of fraying, chafing, overheating (burned spots), and condition. Inspect electrical connectors for security and lockwire.

Inspect electrical components for damage, security, and proper grounding. 2.25 Inspect No. 1 and No. 2 stabilator amplifiers as follows: −

1

−

−

−

1 C

Inspect No. 1 and No. 2 stabilator amplifiers for damage and security. Inspect stabilator amplifier electrical connectors and wiring for security, condition, and evidence of fraying, or chafing. Make sure stabilator amplifier air inlets and exhausts are free of obstructions.

2.26 Inspect soundproofing panels and close up area as follows:


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

1

−

−

−

MOS Status

Inspect soundproofing panels for tears, cracks, punctures, and loose or missing fasteners. Install cabin-soundproofing panels. Make sure all flyaway equipment is secured. Check cabin interior for cleanness.

2.27 ESSS> Inspect horizontal stores supports as follows: <= −

MH

Check torque on expandable bolts with HSS installed, in the following locations: wing to fuselage attachment, strut to wing attachment, strut to fuselage attachment, and fitting to rack attachment. Remove HSS and strut. Remove strut from HSS. Remove tip, leading edge, trailing edge, and rack fairings from wing. Check fairings and hardware for wear and damage. Inspect nylon washers on strut end fittings for condition and security.

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

MH

Inspect bushings for corrosion, damage, and wear. Inspect strut for delamination and distortion. Inspect strut attachment fitting on fuselage for nicks, cracks, and loose or working rivets. Inspect spherical bearings corrosion, play, and damage.

for

Remove rack fitting and forward link from HSS store attachment fittings. Check store attachment fitting bushings for corrosion, damage, and wear. Inspect spherical bearings for corrosion, damage, and play. Inspect store attachment fitting for nicks and cracks. Inspect Hi-Loks on HSS box beam for security and surrounding structure for delamination. Inspect forward and rear spar of HSS for exterior delamination and disbonding. Inspect interior of spars for delamination and disbonding. Inspect top and bottom skins for delamination, specifically around bolted areas.

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

−

Inspect tip closeout rib and interior ribs for delamination and disbonding. Inspect HSS aluminum root fitting for nicks and cracks. Inspect fitting to wing mounting bolts for security. Inspect bushings for corrosion, wear, and damage. Inspect mating fitting on fuselage for nicks, cracks, and loose or working rivets. 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, chafing, damage, or signs of leaks. Check horizontal stores support pneumatic hoses and pneumatic check valve for security, chafing, damage, or signs of leaks.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

1

MH

MOS Status

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. Inspect pneumatic, fuel, and electrical connectors for corrosion. Inspect rack fitting, forward link, and adapter fittings for nicks and cracks. Remove forward link from rack fitting and check bolts and pins for wear. Inspect bushings for corrosion, wear, and damage. Remove adapter fitting from rack fitting. Check mounting hardware and bushings for corrosion, wear, and damage. Assemble assemblies.

and

install

HSS

2.28 If installed, inspect external (hydraulic and electric) rescue hoist as follows:

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

−

−

−

−

−

Remove rescue assembly.

hoist

support

Check support arm attachment bolts for damage, cracks, and corrosion. Check support arm and base for cracks and corrosion (inside and outside bore). Check machined support fitting (exterior fitting) for cracks and corrosion (inside and outside bore). Install rescue assembly.

hoist

support

Check hoist rollers and level wind for wear, corrosion, and security. Check hoist hook for corrosion, and security.

cracks,

Remove rescue hoist rear cowling. Check heat exchanger for leakage, cracks, and ruptures (hydraulic equipped hoists only). Check hydraulic fittings for security and leakage (hydraulic equipped hoists only).

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

−

−

−

−

−

−

Check exhaust obstructions.

duct

MH for

Install rear cowling. Inside cabin, check RESCUE HOIST control panel for security. Check controls and switches for binding, security and lettering for readability. Check electrical connectors and wiring for security, damage, and chafing. Check RESCUE HOIST/ CARGO HOOK RELEASE pendant control for damage. Check controls and switches for binding and security and lettering for readability. Check pendant cord for fraying and connector for security. Check pendant bracket for cracks, corrosion, and damage. Check for positive latching pendant control in bracket.

of

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



1

Check cable cutter squib (firing cartridge) for manufacturing/ installation date.

2.29 If installed, inspect internal hoist as follows: −

−

−

−

−

−

Check hoist rollers and level wind for wear, corrosion, and security. Check hoist hook for corrosion, and security.

cracks,

Inside cabin, check RESCUE HOIST control panel for security. Check controls and switches for binding, security and lettering for readability. Check electrical connectors and wiring for security, damage, and chafing. Check RESCUE HOIST/ CARGO HOOK RELEASE pendant control for damage. Check controls and switches for binding and security and lettering for readability.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.


Inspection Requirements Check pendant cord for fraying and connector for security. Check pendant bracket for cracks, corrosion, and damage. Check for positive latching of pendant control in bracket.

−

−

Check cable cutter squib (firing cartridge) for manufacturing /installation date.

−

−

−

−

Remove internal hoist. Visually inspect upper aircraft hardpoint mount. Remove mount for further inspection or replacement if cracks or corrosion are present. Inspect floor mount for cracks or corrosion. Install internal hoist.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI


PERIODIC INSPECTION CHECKLIST Aircraft Serial No.

Area Name and No. 3. TRANSITION SECTION PHASE Inspection Requirements NO. 1 3.1 Inspect fuel cells as follows: C De-fuel fuel cells and drain sumps. −

−

−

−

−

−

−

UH60L> UH60A Remove rear troop seats. <= Remove soundproofing covering rear bulkhead. Remove cargo net straps. EH60A> Remove air conditioning evaporator and condenser pallets. <= If installed, remove components of the auxiliary cabin heater system as required to gain access to fuel cell area. Inspect internal portion of fuel cell for sludge and organic growth accumulation, release of selfsealing compound or punctures. Inspect for blistering of the fuel cell surface. If any damage is found refer to TM 1-1500-204-23-3.

MH 0.08

MOS Status 15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 3. TRANSITION SECTION (CONT) PHASE NO.

Aircraft Serial No.


−

−

−

−

MH

Inspect internal fuel lines, valves, and airframe to fuel cell interface connections for chafing and security. Inspect fuel and vent lines above fuel cells for chafing, distortion, leakage, and security. Inspect prime pump cracks and security. Inspect leakage.

pump

mount

connection

for

for

Inspect breakaway vent valves, main fuel breakaway valves, prime boost pump breakaway valve, and prime boost pump fuel outlet breakaway valve for visible yellow line around center of valve. If yellow line is visible, replace valve.

MOS Status


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 3. TRANSITION SECTION (CONT) PHASE NO. ALL



MOS Status

Perform fuel feed system test. Note

•

•

1

PMI-2 requires the fuel feed system test be performed for that portion above the fuel tanks. Refer to Paragraph 10-4-39.

3.2 Inspect transition section electrical wiring and components as follows: −

−

−

1

PMI-1 requires the complete fuel feed system test be performed.

0.03

15T

0.05

15T

Inspect electrical wiring for evidence of overheating, fraying, chafing, and general condition. Inspect electrical connectors for security. Inspect electrical components for security and proper grounding.

3.3 Inspect grounding receptacle for damage, security, and electrical resistance.


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 3. TRANSITION SECTION (CONT)

Aircraft Serial No.

PHASE NO.


MH

1 C

3.4 Inspect tail rotor control cables and pulleys as follows:

0.01

15T

0.06

15T

−

−

−

−

1 C

Inspect tail rotor control cables for fraying, corrosion, and loose or missing areas in plastic coating, particularly at pulleys. Inspect pulleys for corrosion, damage, security, cracks, wear, and distortion. Check that cables are riding properly in pulleys and that cable guard pins are installed. Make sure locking clips are installed on turnbuckles.

3.5 Inspect accessible interior area and exit fuel cell area as follows: −

−

−

MOS Status

Inspect accessible interior area for corrosion, damage, leakage, and loose or missing fasteners. If required, install auxiliary cabin heater components. EH60A> Install air conditioning evaporator and condenser pallets. <=


Date: Action Taken

Initial

TM 1-1520-237-PMI



−

−

−


MOS Status

UH60A> UH60L Install cargo net straps. <= Install soundproofing covering rear bulkhead. UH60L> UH60A Install rear troop seats. <=

1

3.6 Inspect behind transition fairing at STA 449 for corrosion and cleanness.

1 C

3.7 Visually inspect slippage marks on all transition section to tailcone attaching hardware.

15T

1

3.8 Check transition section to tailcone bolts for proper torque.

15T

1

3.9 Inspect Auxiliary Cabin Heater as follows: −

−

Check auxiliary cabin heater for signs of over temperature damage. Inspect muffler inlet for debris.

0.04

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI


Aircraft Serial No.


−

−

−

−

−

−

MH

Inspect muffler blower and heater for cracks and security. Inspect muffler blower and eater support for cracks and security. Inspect ducts security.

for

cracks

and

Inspect electrical bonding straps on blower and heater for condition and security. Check overheat duct sensor, harness and connector on heater support and transition duct for condition and security. Check cabin temperature sensor, harness and connector on muffler support for condition and security. Install soundproofing covering rear bulkhead.

MOS Status


Date: Action Taken

Initial

TM 1-1520-237-PMI


PERIODIC INSPECTION CHECKLIST Aircraft Serial No.

Area Name and No. 4. TAILCONE SECTION PHASE Inspection Requirements NO. 1 4.1 Inspect tail cone exterior as follows: −

−

−

MOS Status

0.08

15T

0.1

15T

0.02

15T

Open tail drive shaft cover and structural access panels at rear of tail cone. Inspect exterior skins, tail rotor drive shaft fairing, access panels, hinges, and fittings for corrosion, cracks, distortion, and security of fasteners. Inspect drain holes in tail cone bottom for blockage.

1 C

4.2 Inspect interior skins, frames, fittings, access panels, and stringers for corrosion, cracks, distortion, and security of fasteners.

1 C

4.3 Inspect hydraulic lines as follows: −

MH

Inspect hydraulic lines for evidence of chafing, damage, and condition of clamps.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.

Area Name and No. 4. TAILCONE SECTION (CONT) PHASE NO.


1 C

−

1 C

4.6 Inspect tail landing gear wheel and tire as follows:

−

15T

0.05

15T

Inspect cable quick-disconnects for damage and security.

4.5 Inspect tail landing gear shock strut exposed piston surfaces for nicks and scratches. Inspect painted area of shock strut assembly for evidence of corrosion and blistering or flaking of paint.

−

0.02

Inspect tail rotor control cables for fraying, corrosion, and loose or missing areas in plastic coating, particularly at pulleys.

1

−

MOS Status

Inspect disconnects for security and leakage.

4.4 Inspect tail rotor control cables and pulleys as follows: −

MH

Deflate tire to 20 psi. Remove tail wheel. Inspect wheel bearings for wear, corrosion, and damage. Visually


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



MH

MOS Status

inspect wheel and axle for cracks corrosion or damage. −

1 C

4.7 Inspect tail landing gear yoke and fork as follows: −

−

−

1

Inspect tire for wear, cuts, and cracks.

15T

0.04

15T

Inspect tail landing gear yoke, bushings, fork, lockpin, and actuator for damage and security. Inspection over entire yoke should be done visually using magnifying glass. Refer to TM 1-1520-237-23-3 for inspection criteria. Inspect wheel lock limit switches and wiring for security and damage. Inspect wire strike deflector for damage and security.

−

Repack tail wheel bearings.

−

Install tail wheel and inflate tire.

4.8 Inspect tail cone electrical wiring and components as follows: −

0.02

Inspect electrical wiring for signs of overheating and chafing.


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

2 C

MH

Inspect electrical connectors for corrosion, security, and lockwire. Inspect electrical components for security and proper grounding. Inspect anticollision light power supply for security and signs of overheating.

4.9 Inspect tail cone section II and III tail rotor drive shafts as follows: −

−

−

−

−

MOS Status

Disconnect section II flexible couplings and check for elongated flange boltholes. Disconnect section III flexible couplings and check for elongated flange boltholes. Inspect flexible couplings for corrosion, damage, security, cracks, buckling, wear, and lamination spread. Inspect spherical corrosion. Reconnect couplings.

section

washers

II

for

flexible

0.18

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Aircraft Serial No.



−

−

−

Reconnect couplings.

section

III

flexible

Inspect tail rotor drive shaft bearing supports for cracks and security. Inspect viscous damper bearing mount holes for elongation. Close and secure drive shaft covers and structural access panels.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI



Area Name and No. 5. TAIL ROTOR PYLON SECTION

Aircraft Serial No.

PHASE NO.


MH

2 C

5.1 Inspect exterior structure of tail rotor pylon as follows:

0.04

−

−

−

−

−

−

−

−

Open tail rotor drive shaft cover. Inspect tail rotor drive shaft cover for damage and missing fasteners. Remove fairing.

intermediate

gear

box

Inspect intermediate gear box fairing for damage and missing fasteners. Remove tail gear box fairing. Inspect tail gear box fairing for damage and missing fasteners. Inspect intermediate gear box mounting area for cracks, dents, nicks, corrosion, and security. Inspect tail rotor gear box mounting area for cracks, dents, nicks, corrosion, and security.

MOS Status 15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 5. TAIL ROTOR PYLON SECTION (CONT) PHASE NO.


−

−

2 C

−

MH

MOS Status

Inspect tail rotor gear box mount fitting for cracks around lower barrel nut holes and inside surfaces where attached to front spar cap angles. Inspect tail rotor pylon exterior skins for corrosion, cracks, distortion, and security of fasteners. Inspect popout steps for proper operation and/or damage.

5.2 Inspect interior of tail rotor pylon as follows: −

Aircraft Serial No.

Inspect interior of tail pylon for cracks, distortion, corrosion, and for loose or missing fasteners. Inspect hinge bracket and formers of tail pylon at pylon STA 120, 140, 160, and 180 for cracks and corrosion.

0.11

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 5. TAIL ROTOR PYLON SECTION (CONT) PHASE NO. ALL C


MH

5.3a Remove stabilator. −

−

−

2 C

Aircraft Serial No.

Remove stabilator actuator. Lubricate fully extended length of stabilator actuator pistons. Install stabilator actuator.

−

Install stabilator.

5.3b Inspect stabilator as follows:

−

−

−

−

−

15T

Inspect stabilator IAW TM 1-1520237-1, para 1-17-12.1).

−

−

MOS Status

Remove stabilator. Inspect left stabilator attachment bolt and fitting for wear. Inspect left fitting for cracks, corrosion, and security of attaching hardware. Inspect right stabilator attachment bolt for wear and damage. Inspect right stabilator attachment fitting for separation of bonded liners. Inspect fitting for cracks, corrosion, and security of attaching hardware.

0.17

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI



−

−

−

−

−

−

Remove stabilator actuator. Inspect stabilator actuator and attaching hardware for wear and damage. Inspect upper stabilator actuator attachment fitting for wear. Inspect fitting for cracks, corrosion, and security of attaching hardware. Inspect upper stabilator actuator attachment fitting bushings and bearing for wear. Inspect lower stabilator actuator attachment fitting for wear. Inspect fitting for cracks, corrosion, and security of attaching hardware. Lubricate fully extended length of stabilator actuator pistons.

−

Install stabilator actuator.

−

Remove inspection panels.

−

Inspect stabilator structure for corrosion, cracks, dents, distortion, and for loose or missing fasteners. Inspect spar for cracks using a flashlight and mirror.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI



−

−

−

−

2 C

Aircraft Serial No.

MH

Install inspection panels. Inspect elastomeric bearing wear, cracks, and disbonding.

for

Inspect limit switches for damage. Perform electrical bond resistance measurements of upper and lower actuator to rear spar.

−

Inspect double row ball bearings.

−

Install stabilator.

5.4 Inspect section IV tail rotor drive shaft as follows: −

−

MOS Status

Inspect tail pylon drive shaft sections for cracks, dents, scratches, gouges, and signs of twisting or bending. Check tail pylon drive shaft flanges and flexible couplings for cracks, corrosion, damage, loose lockbolts, and security.

0.36

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI


Aircraft Serial No.


MH

MOS Status

NOTE Corrosion between tube and flange (or stub shaft) is identified by flaking or lifting of paint, cracks, or aluminum oxide (a white powdery substance) at interface between tubes and flanges. −

−

−

−

−

2 C

Disconnect flexible coupling and check for elongated flange boltholes. Inspect flexible couplings for corrosion, damage, security, cracks, buckling, wear, and lamination spread. Inspect spherical corrosion.

washers

for

Reconnect flexible coupling. Check tail drive shaft flexible coupling self-locking nuts for proper torque.

5.5 Inspect tail rotor control cables and pulleys as follows: −

Inspect tail rotor control cables at lower end of pylon for wear, corrosion, and loose or missing areas in plastic coating, particularly at pulleys.

0.04

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI



−

−

2 C

−

−

−

−

−

MH

MOS Status

Inspect pulleys for corrosion, damage, security, cracks, wear, and distortion. Check that cables are riding properly in pulleys and that cable guard pins are installed.

5.6 Inspect intermediate and tail gear boxes as follows: −

Aircraft Serial No.

Inspect intermediate gear box flange for cracks, damage, and corrosion. Inspect intermediate gear box housing for cracks, damage, and corrosion. Inspect intermediate gear box input and output seals for leakage. Inspect tail gear box flange for cracks, damage, and corrosion. Inspect tail gear box housing for cracks, damage, and corrosion. Inspect tail gear box input and output seals for leakage.

0.05

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 5. TAIL ROTOR PYLON SECTION (CONT)

Aircraft Serial No.

PHASE NO.


MH

2 C

5.7 Inspect tail rotor control system as follows:

0.03

−

−

−

−

−

−

−

−

Inspect spring cylinders, control rod, and quadrant for corrosion, cracks, distortion, and security. Check control rod for bearing play. Inspect cables for wear, fraying, corrosion, and loose or missing areas in plastic coating, particularly in pulley area. Inspect tail rotor control cable conduits for damage or wear. Inspect pulleys for corrosion, damage, security, cracks, wear, and distortion. Check that cables are riding properly in pulleys and that cable guard pins are installed. Inspect quadrant bearings corrosion and damage.

for

Disconnect spring cylinders, control cables, and output control rod and check quadrant for free rotation and smoothness (no ratchety feeling).

MOS Status 15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI



−

−

−

2 C

−

2

−

2

−

2

2

−

−

−

MH

MOS Status

Inspect quick-disconnect cable collars and ball ends for cracks. Reconnect spring cylinders, control cables, and output control rod. Perform tail rotor cable tension check.

5.8 Inspect tail rotor components as follows:

ALL

2

Aircraft Serial No.

system

Remove tail rotor blades outboard retention plate.

and

Inspect retention plates for cracks, damage, and security. Inspect nylon shims on inboard and outboard retention plates for waviness and minimum and maximum thickness. Inspect threads of pitch beam retaining nut for thread face wear or chafing. Remove seal retention plate.

from

Inspect snapring and bushing for corrosion.

outboard

end

of

0.05

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI



NOTE ALL

ALL

2

2

2

Removal of the inboard retention plate is not required unless inboard retention plate attaching bolt torque check is below limits. Wear of tail gear box split cones will be indicated by a loss of torque on inboard retention plate attaching hardware. If torque check is below limits, the inboard retention plate should be removed and the split cones inspected for wear or damage. −

−

−

−

Perform torque check on inboard retention plate attaching bolts. Inspect pitch control rods for cracks, damage, bearing play, bearing discoloration, and security. Inspect pitch beam for cracks and damage. Visually inspect pitch beam washer for cracks. Replace washer if any cracks are present.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. 5. TAIL ROTOR PYLON SECTION (CONT) PHASE NO. 2 C

Aircraft Serial No.

Inspe Inspecti ction on Requir Requireme ements nts

MH

5.9 Inspect tail rotor servo as follows: −

−

−

−

−

−

−

−

−

−

Drain tail gear box oil. Remove tail rotor servo disconnect pitch control shaft.

and

Inspect tail rotor servo housing for leakage. Inspect tail rotor servo housing for cracks and damage. Check tail rotor servo for bent pilot valve stem. Inspect pitch control shaft link assembly bearing for axial play. Inspect linkage distortion.

for

cracks

and

Inspect linkage-attaching hardware for security. Inspect attaching hardware connecting tail rotor servo to pitch control shaft. Inspect pitch control shaft chrome plated surfaces for blistering, blistering, cracking, or flaking.

0.06

MOS Statu Status s 15T

Faults Faults and/o and/orr Remark Remarks s

Date:

Actio Action n Taken Taken

Initia Initiall

TM 1-1520-237-PMI


Inspe Inspecti ction on Requir Requireme ements nts −

−

−

−

−

−

−

−

2 C 2

2

−

2

−

MH

MOS Statu Status s

Inspect pitch control shaft pressed bushing for wear and security. Inspect bearing area for chips or debris. Inspect pitch control shaft bearing for freedom of rotation. Inspect tang for proper width. Check inside of tail gear box, especially inside diameter of input bevel pinion for buildup of sludge or debris. Flush inside of tail gear box. Install pitch control shaft and tail rotor servo. Service tail gear box.

5.10 Inspect tail rotor blades as follows: −

Aircraft Serial No.

Inspect tail rotor blades for erosion and damage. Inspect tip caps for security. Inspect tail rotor blade erosion protection kit polyurethane tape, if installed, for wear, holes, or disbonding.

0.16

15T


Date:


Initia Initiall

TM 1-1520-237-PMI



2

−

2

−

ALL

−

ALL

2

2

2

2

−

−

−

−

−

Inspect tail rotor blade tip cap erosion protection kit polyurethane coating, if installed, for wear. Inspect pitch horn and bracket for damage, cracks, corrosion, and security. Remove one boot tiedown strap and roll back boot. Inspect tail rotor blade spar for wear or damage and security as a result of contact with tail rotor horn fairing. Check for spar corner-tofairing clearance. Check for delaminations and splinters on spar in areas near fairing inner lip. Inspect tail rotor plug for cracks, disbonding, fretting, scoring, and corrosion. Inspect tail rotor pivot bearing for wear and separation. Inspect tail rotor pivot retainer for disbonding.

bearing

Inspect boots for wear or damage and security.

Aircraft Serial No.

MH

MOS Statu Status s


Date:


Initia Initiall

TM 1-1520-237-PMI

Area Name and No. 5. TAIL ROTOR PYLON SECTION (CONT) PHASE NO. ALL

−

Install boot tiedown strap.

ALL

−

Install tail rotor blades.

2 C


5.11 Inspect tail pylon electrical wiring as follows: −

−

2

2

MOS Statu Status s

0.02

15T

0.01

15T

0.01

15T

Inspect connectors for security.

−

Close pylon drive shaft cover.

−

Install intermediate gear box fairing.

−

Install tail gear box fairings.

5.13 Inspect tail rotor deice system, if installed, as follows:

−

MH

Inspect tail pylon electrical wiring for fraying, chafing, and overheating.

5.12 Close up area as follows:

−

Aircraft Serial No.

Inspect tail rotor deice slip ring for cleanness and wear. Inspect brushes for wear.


Date:


Initia Initiall

TM 1-1520-237-PMI

PHASE INSP NO.___________ NO._____ _______ _


Area Name and No. 6. MAIN ROTOR PYLON SECTION PHASE NO. 2

Aircraft Serial No.

Inspe Inspecti ction on Requir Requireme ements nts 6.1 Inspect heating system as follows: −

−

−

−

−

−

−

−

Open main cover.

rotor

and

MH

ventilating

pylon

sliding

Inspect heater ducting for cracks and damage. Inspect heating bleed-air tubes for cracks and damage. Check temperature sensing tube to heater mixing valve for security and cracks. Inspect heater mixing valve and mounting brackets for damage and security. Inspect blower housing and flange area for cracks. Inspect attaching hardware, connections connections for security.

all

Check heater mixing valve duct inlet screen for blockage.

0.03

MOS Statu Status s 15T


Date:


Initia Initiall

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT)

Aircraft Serial No.

PHASE NO.


2 C

6.2 Inspect upper deck torque shaft taper pins, levers and control rods as follows: −

−

−

MH

MOS Status 15T

Check torque shaft taper pins for tightness. Inspect levers and control rods for cracks and distortion. Inspect attaching security.

hardware

for

NOTE Inspection of cabin flight control components Seq # 2.21 due at PMI 2. 2 C

6.3 Inspect boost servo and pilot-assist module manifold baseplate as follows: −

Inspect for proper torque on mounting bolts. Special attention should be given to mounting bolts that failed torque and have black or gray residue present. If present remove base plate and check for cracks around mounting holes and adjacent areas.

15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT) PHASE NO. 2

Aircraft Serial No.


MH

6.4 Inspect yaw and collective boost servos, pitch trim assembly, and roll assembly as follows:

0.15

−

−

−

−

−

Check 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. Inspect boost servo thermal relief valves for leakage. 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 adjacent to output clevis.

MOS Status 15T


Date:

Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT) PHASE NO.


−

−

−

2 C

Aircraft Serial No.

MH

Inspect yaw and collective boost servos; yaw boost, pitch trim, and roll assembly SAS actuators for damage and security. Visually inspect castellated nut opposite output clevis for cracks. Inspect yaw and collective boost servo pressure switches and wiring for condition. Inspect input and output linkage for security and condition. Inspect rubber deterioration.

dust

boots

for

6.5 Inspect mixer assembly as follows: −

−

−

−

MOS Status

Inspect mixer work platform for security, and smooth operation. Check arm on lower track for security. Check mixing unit mounting bolts for proper torque. Inspect support brackets, levers, and bellcranks for distortion, cracks, and security of attaching hardware. Check taper pins for tightness.

0.05

15T


Date:

Action Taken

Initial



−

−

−

−

−

−

−

2

−

MH

MOS Status

Inspect for bearing play. Inspect mixer torque shaft bearings for corrosion and damage. Inspect stick position sensors for corrosion, distortion, cracks, and security of attaching hardware. Inspect electrical connectors for condition and security. Disconnect input and output control rods. Check torque shaft for free rotation and smoothness (no ratchety feeling). Connect control rods.

6.6 Inspect flight control components as follows: −

Aircraft Serial No.

system

Inspect flight control rod assemblies for evidence of external corrosion. Inspect flight control rods, bellcranks, levers, supports, and directional control torque shaft for cracks, corrosion, distortion, and security of attaching hardware.

0.02

15T


Date:

Action Taken

Initial



−

−

−

Aircraft Serial No.

MH

MOS Status

Inspect bearings for condition. Remove and inspect main rotor blade pitch control rods. Inspect main rotor blade pitch change links for security, corrosion, drain hole blockage, and rod end bearings for play and serviceability.

−

2 C

6.7 Inspect forward, aft, lateral bellcrank assemblies, and walking beam as follows: Inspect forward, aft, lateral bellcrank assemblies, and walking beam for bearing play and looseness. −

−

−

−

Inspect exposed portions of walking beam lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs. Inspect exposed portions of rear bellcrank lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs. Inspect exposed portions of forward bellcrank lug areas for damage and

15T


Date:

Action Taken

Initial



Aircraft Serial No.

MH

MOS Status

corrosion. Do not disconnect hardware to inspect lugs. −

2 C

Inspect exposed portions of lateral bellcrank lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs.

6.8 Inspect primary servos as follows: −

−

−

−

−

Check primary servos for leakage around seals, disconnects, and caps. Inspect 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 primary servo mounting lugs for cracks, corrosion, and security. Inspect primary servo mount bolts for broken safety wire and slippage mark alignment. Inspect servo beam rails for cracks in region of barrel nut hole.

0.05

15T


Date:

Action Taken

Initial



−

−

2

MH

−

−

Inspect bearings for play, looseness in housing. Inspect pressure switches wiring for condition.

and

−

0.05

15T

Inspect hydraulic lines for signs of leakage. Inspect hydraulic lines for chafing and condition of clamps. Inspect reservoir low-level switches and wiring for condition.

6.10 Inspect No. 1 and No. 2 transfer modules and manifolds as follows: −

MOS Status

Inspect primary servo input and output linkage for cracks, distortion, and security of attaching hardware.

6.9 Inspect No. 1 and No. 2 hydraulic pump modules as follows: −

2

Aircraft Serial No.

Inspect No. 1 and No. 2 transfer modules, manifolds, and connecting lines for signs of leakage. Inspect No. 1 and No. 2 transfer modules and manifolds for cracks and corrosion.

15T


Date:

Action Taken

Initial



−

−

2

Aircraft Serial No.

MH

Inspect pressure switches, solenoid valves, disconnect fittings, and wiring for security and condition. Inspect chafing.

connecting

lines

for

6.11 Inspect No. 2 hydraulic system pilot assist module and servo manifold as follows: −

−

−

−

MOS Status

Inspect No. 2 hydraulic system pilot assist module and servo manifold for signs of leakage. Inspect No. 2 hydraulic system pilot assist module and servo manifold for cracks and corrosion. Inspect pressure switches, solenoid valves, disconnect fittings, and wiring for security and condition. Check indicator button on pilot assist module for extension.

0.03

15T


Date:

Action Taken

Initial


2


MH

6.12 Inspect backup hydraulic pump module, utility module, rescue hoist manifold, and external hydraulic power disconnects as follows:

0.03

15T

0.32

15T

−

−

−

−

−

−

2

Aircraft Serial No.

MOS Status

Inspect switches, quickdisconnects, and wiring for security and condition. Inspect utility module for signs of leakage. Inspect utility module and rescue hoist manifold for leakage, corrosion, and security. Inspect backup system lines for signs of leakage. Inspect backup system lines for chafing and security. Inspect external hydraulic power disconnects and covers for security and condition.

6.13 Inspect hydraulic refill handpump as follows:


Date:

Action Taken

Initial



−

−

−

2 C

Aircraft Serial No.

MH

Inspect hydraulic refill handpump for cleanness, particularly under cover. Inspect cover, chain, puncher, exposed seals, boots, and gaskets for condition. Check selector valve for ease of operation. Remove and replace handpump filter element.

refill

6.14 Inspect main transmission mounts, dowel pins, and forward and rear bellcrank supports as follows: −

−

−

−

MOS Status

Inspect main transmission mounts for cracks and damage. 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 boxes with slippage strip. <= W/O MWO 50-43> Inspect sealing compound covering dowel pins for bulging, blistering, and cracking. <=

0.04

15T


Date:

Action Taken

Initial



−

−

−

−

−

2 C

Aircraft Serial No.

MH

MOS Status

Check gap between rear bellcrank support retaining angle and dowel pin. Inspect forward and rear bellcrank support mounts for cracks and damage. Inspect exposed portions of forward bellcrank support lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs. Inspect exposed portions of rear bellcrank support lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs. Inspect exposed portions of right and left tie rod lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs. Inspect exposed portions of rear tie rod and rear tie rod support lug areas for damage and corrosion. Do not disconnect hardware to inspect lugs.

6.15 Inspect main, input, and accessory modules, main module breather, and engine output shafts as follows:

0.08

15T


Date:

Action Taken

Initial



−

−

−

−

−

−

−

−

−

−

Remove engine inlet. Inspect main, input, and accessory module mating flanges and all connections for oil leakage. Inspect main generators for security and evidence of oil leakage. Inspect main module breather for cleanness. Inspect accessory module oil return screen. Remove engine output shafts. If engine output shaft, 70361-08004042, is installed, replace with engine output shaft, 70361-08004-043. Inspect installation bolts for burrs and binding in flexible coupling assembly. Inspect disc pack for cracks, nicks and lamination spread. Inspect input module flange for fretting in washer contact area. Inspect flange nutplate rivets for proper installation, looseness, and fretting on heads.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial



−

−

−

−

−

Check torque flange nut.

of

input

Aircraft Serial No.

MH

MOS Status

module

Check torque on nuts holding flexible coupling to engine output shafts. Inspect engine output shafts for damage. Inspect forward restraining rings missing rivets.

support tube for loose or

Inspect forward support tube restraining rings for missing or disbonded Zytek tape.

Inspect crotch assembly for loose or missing pins, bends, cracks, missing or damaged finish, loose or missing rivets, nick, scratches or corrosion.

2

−

Install engine output shafts.

−

Check main transmission oil level.

6.16 Inspect input module seals for leakage.

0.01

15T


Date:

Action Taken

Initial


Aircraft Serial No.


MH

2

6.17 Inspect main transmission output shaft seal for leakage.

0.01

15T

2

6.18 Inspect main transmission main rotor shaft seal for leakage.

0.01

15T

2

6.19 Inspect teeth on gust lock flange and gust lock lever for condition.

0.02

15T

2

6.20 Inspect main transmission input modules, and accessory module chip detectors, sensors, switches, and electrical wiring as follows:

0.02

15T

0.01

15T

−

−

−

2

MOS Status

Inspect main transmission input modules, and accessory module chip detectors, sensors, and switches for security of electrical connectors. Inspect main transmission wiring harness for condition. Inspect generator wiring for chafing, corrosion, and security.

6.21 Inspect main rotor pitch control rods for damage, security, and bearing play.


Date:

Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT) PHASE NO. 2 C

Inspection Requirements 6.22 Inspect spindle as follows: −

−

−

−

−

−

−

−

−

−

Remove main rotor blades. Remove spindle assemblies from hub. Remove elastomeric bearings from spindles. Inspect spindle sleeve bearing for wear, cracks, corrosion, slippage, and damage. Inspect spindle threads for dry film lubricant. Inspect spindle nut threads for dry film lubricant. Inspect elastomeric bearing for wear, damage, or laminate separation. Inspect elastomeric bearing sleeve bearing for wear, disbanding, and damage. Replace elastomeric bearing sleeve bearing. Inspect droop stop pin bushings for wear, security.

Aircraft Serial No.

MH 4.9

MOS Status 15T


Date:

Action Taken

Initial



−

−

−

−

Check torque on horn attachment bolts. Remove retaining ring and loosen and back off droop stop nut, on spindle assemblies 70070-10030041,70070-10030-042, 70070-10030045, 70070-10030-046, 70102-08200041 through 70102-08200-044, and 70102-08200-063. Inspect droop stop support inner race sleeve bearing for cracks, on spindle assemblies 70070-10030041,70070-10030-042, 70070-10030045, 70070-10030-046, 70102-08200041 through 70102-08200-044, and 70102-08200-063. Inspect droop stop nut for corrosion and cracking, on spindle assemblies 70070-10030-041, 7007010030-042, 70070-10030-045, 7007010030-046, 70102-08200-041 through 70102-08200-044, and 70102-08200063. Inspect hub ID for evidence of contact caused by retaining rod.

−

Assemble spindle assemblies.

−

Install spindle assemblies.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial


Aircraft Serial No.

PHASE NO.


MH

2 C

6.23 Inspect main rotor dampers as follows:

0.06

−

−

−

−

−

−

−

−

−

−

Inspect main rotor damper bearings for wear using feeler gage method with damper installed. Inspect main rotor damper bearings for radial and axial play with damper installed. Remove dampers from main rotor. Inspect main rotor damper bearings for damage and corrosion. Inspect dampers for corrosion, and damage.

cracks,

Check damper for evidence hydraulic fluid leakage.

of

Check damper indicator for leakage and proper fluid level (gold band visible). Inspect damper bracket for cracks, wear, and security. Check torque on damper bracket attachment bolts. Install main rotor dampers.

MOS Status 15T


Date:

Action Taken

Initial


Aircraft Serial No.


MH

2 C

6.24 Inspect main rotor rotating scissors upper and lower links, and between upper link and pressure plate lug for bearing play.

0.02

2

6.25 Inspect main rotor blade deice system as follows: −

−

−

−

−

−

Remove main rotor blade deice distributor. Remove main rotor blade deice slip ring assembly from distributor. Remove brush assembly from slip ring. Inspect slipring assembly. If the white metal surface of the ring contacts has worn through to the yellow substrates on the power circuits or signal circuits, the slipring assembly shall be replaced Inspect for metal shavings. Clean metal shavings from slip ring assembly. Assemble and install assembly to distributor.

slip

ring

MOS Status 15T

15T


Date:

Action Taken

Initial


Inspection Requirements 6.26 Inspect follows: −

−

2 C

main

rotor

MH

shaft

as

−

−

15T

Inspect all exposed portions of main rotor shaft for rust or corrosion. 1.3

15T

0.02

15T

Inspect main rotor hub and visually inspect upper and lower pressure plates for cracks and damage. Torque the following bolts: NAS bolts that hold hub to shaft extension, expandable pins, main rotor shaft nut bolts, and upper and lower pressure plate bolts. Install main distributor.

rotor

blade

de-ice

6.28 Inspect swashplate assembly as follows: −

MOS Status

Inspect inner diameter of main rotor shaft for signs of corrosion, blistering, flaking, or missing resin coating.

6.27 Inspect main rotor hub as follows: −

2 C

Aircraft Serial No.

Inspect swashplate assembly for cracks, nicks, and security.


Date:

Action Taken

Initial



−

−

−

−

−

−

2 C

Aircraft Serial No.

MH

Inspect expandable pin for correct installation of lockring and half male spacer. Inspect expandable pin nut for fractures or cracks. Inspect ball bearings between stationary swashplate and rotating swashplate for wear, ratcheting or uneven movement. Inspect large spherical bearing and socket for wear. Check clearance between swashplate guide and inner race of bearing. Inspect scissors attachment spherical bearings for wear and discoloration. Inspect forward, aft, and lateral connecting link assemblies for bearing play and looseness.

6.29 Inspect bifilar as follows: −

−

MOS Status

1.29

Remove bifilar weights from bifilar support. Remove lubricant from bushings, and washers.

pins,

15T


Date:

Action Taken

Initial


Aircraft Serial No.


−

−

−

−

−

−

MH

Inspect pins, bushings, and washers for wear, cracks, or other damage. Inspect weights for cracks in lower and upper bonded joints. If cracked paint is found at bonded joints of bifilar weights without "UT" marked in area of part number, remove paint and inspect weight base metal for cracks. Cracked paint at bonded joints of bifilar weights with "UT" marked in area of part number is acceptable. Inspect weight in areas away from bonded joints for cracks. Inspect bifilar support arm and bushings for cracks, corrosion, or other damage, particularly in weight attachment lug areas. Install bifilar support arm.

weights

Lubricate bifilar.

to

bifilar

MOS Status


Date:

Action Taken

Initial


Aircraft Serial No.


MH

6.30 Inspect main rotor blades as follows: −

−

−

−

−

−

Using magnifying glass, inspect main rotor blade cuff for cracks between each bolt and leading and trailing edges of cuff on upper and lower surfaces. Inspect damage.

expandable

pins

for

Inspect main rotor blade spar region for cracks, impact damage, wear, bond separations, or other damage. (IAW TM 1-1520-237-23-3) Inspect main rotor blade honeycomb core region for cracks, impact damage, wear, bond separations, or other damage. (IAW TM 1-1520-237-23-3) Inspect main rotor blade trailing edge region for cracks, impact damage, wear, bond separations, or other damage. (IAW TM 1-1520-23723-3) Inspect main rotor blade leading edge abrasion strips for cracks, Impact damage, wear, bond separations, or other damage. (IAW TM 1-1520-237-23-3)

0.06

MOS Status

15T


Date:

Action Taken

Initial



−

−

−

−

Inspect tip cap exterior for erosion, cracks, eroded paint, missing/deteriorated caulking, disbonds, delaminations, fraying of Kevlar fabric, impact damage, hole elongation, and other damage. (IAW TM1-1520-237-23-3) Inspect tip cap retaining screws for loss of torque. Inspect tip cap drain hole on lower surface for blockage. Inspect tip caps as follows:

NOTE ALL

2

•

•

Removal of the aluminum tip cap and inspection of the tip cap interior, blade tip rib and tip block is required at both PMI1 and PMI 2 for those blades with aluminum tip caps installed. Removal of the composite tip cap and inspection of the tip cap interior, blade tip rib and tip block is only required at the PMI 2 for those blades with composite tip caps installed.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial



−

−

−

−

2

ALL

−

−

−

Inspect composite/aluminum tip cap exterior for erosion, cracks, disbonds, delaminations, hole elongation, and other damage. Inspect composite/aluminum tip cap interior for disbonded, delaminated or cracked ribs, and tip cap weights for security. Inspect composite/aluminum tip cap drain hole on outboard surface for blockage. Inspect blade tip rib for cracks and tip block for corrosion. Install composite tip cap back onto original blade. Replace #6 screw with new hardware. Serviceable hardware may be reused on remaining positions.

Install aluminum tip cap back onto original blade. Serviceable hardware may be reused. Inspect main rotor blade erosion protection kit polyurethane tape, if installed, for wear, holes, or disbonding.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial



−

−

−

2 C

Aircraft Serial No.

MH

Inspect main rotor blade tip cap erosion protection kit polyurethane coating, if installed, for wear. Inspect main rotor blade tip cap erosion protection kit polyurethane boot, if installed, for wear, holes, or disbonding. Install main rotor blades. Test main rotor blade pressure indicators.

6.31 Inspect section I tail rotor drive shaft as follows: −

−

−

−

−

MOS Status

Inspect section I tail rotor drive shaft for dents, gouges, indications of twisting or bending, and loose lockbolts. Disconnect flexible couplings and inspect for elongated flange boltholes. Inspect flexible couplings for corrosion, damage, security, cracks, buckling, wear, and lamination spread. Inspect spherical corrosion.

washers

Reconnect flexible couplings.

for

0.03

15T


Date:

Action Taken

Initial


Aircraft Serial No.

PHASE NO.


MH

2 C

6.32 Inspect oil cooler and radiator as follows:

0.07

Open oil cooler compartment and APU compartment access doors. −

Inspect hinges on airframe and APU doors for cracks, wear, and security. Inspect latch mechanisms for cracks, wear, and security. Inspect latch mechanisms for worn or loose pins. −

Inspect hinges on airframe and oil cooler compartment doors for cracks, wear, and security. Inspect latch mechanisms for cracks, wear, and security. Inspect latch mechanisms for worn or loose pins. −

NOTE ALL

Bearing replacement and the following inspections are required at PMI #1 and #2 if the aft bearing shroud is not vented. If the bearing is vented, its replacement and the following inspections are due every 700 hours (PMI 2). Remove oil cooler and radiator assembly. −

Inspect radiator for damage, dirt, debris, and signs of leakage. −

MOS Status 15T


Date:

Action Taken

Initial



−

−

−

−

−

−

−

−

Inspect radiator inlet and outlet lines for chafing and leakage. Inspect axial fan blades for distortion, cracks, evidence of contact between fan blades and shroud. Open access panel at rear of oil cooler duct. Check inside oil cooler duct for obstructions, foreign objects, and cracking. Pay particular attention to rear bearing and surrounding area for dirt and debris. Inspect oil cooler support structure for security and cracks. Remove viscous damper bearing support assembly. Perform oil cooler drive shaft run out check. Replace bearing and re-install viscous damper bearing support assembly. Inspect oil cooler drive shaft for dents, gouges, indications of twisting or bending, and loose lockbolts.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial



−

−

−

−

−

−

−

2

Aircraft Serial No.

MH

MOS Status

Inspect oil cooler drive shaft exterior for cracks and corrosion. Inspect oil cooler drive shaft ID for corrosion, pitting, loss of plating, and cracks, particularly in area of cotter pin holes. On helicopters with oil cooler axial fan, 70361-03005-103 through 70361-03005-106 installed, inspect axial fan shaft ID for corrosion, pitting, loss of plating, and cracks, particularly in area of cotter pin holes. On helicopters with oil cooler axial fan, 70361-03005-103 through 70361-03005-106 installed, check output flange retaining nut torque. Check input flange retaining nut torque. Install oil cooler duct access panel. Install oil assembly.

cooler

and

radiator

6.33 Inspect fuel selector valves for security and leakage.

0.02

15T


Date:

Action Taken

Initial


Inspection Requirements 6.34 Inspect APU as follows: −

−

−

−

−

−

−

On helicopters with APU, 116305100 through 116305-300 series, replace fuel inlet filter. On helicopters with APU, 116305100 through 116305-300 series, replace fuel pump filter. If filter is heavily contaminated, inspect per TM 55-2835-208-23. On helicopters with APU, 3800480-1 and 3800480-2, refer to Preventive Checks and Service, TM 55-2835209-23, paragraph 1-26. Check counter on APU to determine hours of operation. Inspect APU fuel lines and hoses for kinks, cracks, or leaks. Inspect APU combustor housing for cracks, tears, bulges, dents, and dark blue discoloration indicating too much heat. Inspect fuel control enclosure for leaks. Inspect fuel drain lines for condition and security. Inspect APU fuel lines and fuel control enclosure for leaks.

Aircraft Serial No.

MH 0.34

MOS Status 15T


Date:

Action Taken

Initial



−

−

−

Aircraft Serial No.

MH

MOS Status

Inspect APU start motor, pressure, and return lines for signs of leakage and security. Disconnect start motor drain line and check for evidence of seal leakage. Inspect APU supports for cracks, damage, and security. Reach through APU exhaust outlet and turn rotor by hand while pushing toward air inlet housing. Check for rubbing contact. Repeat, while pulling rotor toward combustor section.

2

6.35 Inspect bulkhead breakaway valve on APU compartment deck for visible yellow line around center of valve. If yellow line is visible, replace valve.

0.02

15T

2

6.36 Inspect engine/APU fire extinguisher and protection system as follows:

1.12

15T

−

Check engine/APU fire extinguisher containers for proper weight and gage pressure.


Date:

Action Taken

Initial



−

−

−

2 C

−

ALL

−

2

−

MH

MOS Status

Check cartridges for installation/ manufacturing date. Inspect fire extinguisher discharge lines for cracks, chafing, damage, and proper alignment. Inspect fire protection system manifold tubing for cracks, distortion, corrosion, and security. Manually actuate fire extinguishing directional control valve.

6.37 Inspect No. 1 T700-GE-700 or T700GE-701C turbine engine in periodic inspection requirements per TM 552840-248-23 as follows:

2

Aircraft Serial No.

Replace No. 1 engine load-demand spindle to collective bias tube roll pin. Check HMU P-3 fitting on Hamilton Standard HMU specific part numbers listed in para 1-64.1 TM 1-2840-248-23 Inspect particle separator blower impeller, shroud, and drive shaft for erosion, nicks, dents, and scratches.

15B


Date:

Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT) PHASE NO. ALL

−

ALL

−

2

−

Perform S-39 Circuit Checks.

2

−

Perform alternator check.

−

Perform yellow cable check.

2


ALL

−

ALL

−

ALL

−

2 C

Check torque of No. deswirl duct clamp.

1

MH

−

MOS Status

engine

Inspect control cables for chafing, corrosion, and scratches.

Remove, clean, inspect and reinstall electrical chip detector. Perform electrical chip continuity verification.

detector

Inspect engine aft mounts.

6.38 Inspect No. 1 engine control cables as follows: −

Aircraft Serial No.

Inspect No. 1 engine load-demand push/pull cable and collective bias tube linkage at mixer for damage, security, chafing, and grommet wear. Inspect No. 1 engine poweravailable push/pull cable from firewall to HMU for damage, security, chafing, and grommet wear.

0.04

15T


Date:

Action Taken

Initial



−

−

−

−

2

−

−

MH

MOS Status

Inspect No. 1 engine poweravailable push/pull cable from firewall to engine control quadrant for damage, security, chafing, and grommet wear. Inspect No. 1 engine control fuel selector valve push-pull cable for damage and security. Inspect cable-mounting brackets for security. Perform load-demand cable friction check.

push/pull

6.39 Inspect No. 1 engine starter as follows: −

Aircraft Serial No.

Inspect No. 1 engine starter for cracks, condition, and security. Drain oil from starter and re-service. Install new packing in oil filler cap and oil drain plug. Inspect start system pneumatic tubes for damage and security.

0.06

15T


Date:

Action Taken

Initial


Aircraft Serial No.


MH

2

6.40 Inspect No. 1 engine compartment breakaway valves, crossfeed breakaway valve, and tee breakaway valve for visible yellow line around center of valve. If yellow line is visible, replace valve.

0.02

15T

2

6.41 Inspect No. 1 engine flame detectors for cleanness, evidence of overheating, security, and cracked or broken shields.

0.02

15T

2

6.42 Inspect No. 1 engine compartment electrical wiring as follows:

0.04

15T

−

−

−

Inspect No. 1 engine compartment electrical wiring for evidence of fraying, chafing, overheating, and condition. Inspect all electrical connectors for security. Inspect electrical components for security and proper grounding.

MOS Status


Date:

Action Taken

Initial



−

ALL

−

2

−

ALL

ALL

2 2 2 ALL

MH

6.43 Inspect No. 2 T700-GE-700 or T700GE-701C turbine engine in periodic inspection requirements per TM 552840-248-23 as follows:

2

−

−

Replace No. 2 engine load-demand spindle to collective bias tube roll pin. Check HMU P-3 fitting on Hamilton Standard HMU specific part numbers listed in para 1-64.1 TM 12840-248-23. Inspect particle separator blower impeller, shroud, and drive shaft for erosion, nicks, dents, and scratches. Check torque of No. deswirl duct clamp.

2

Perform S-39 Circuit Checks.

−

Perform alternator check.

−

Perform yellow cable check.

−

engine

Inspect control cables for chafing, corrosion, and scratches.

−

Aircraft Serial No.

Remove, clean, inspect and reinstall electrical chip detector.

MOS Status 15B 15B


Date:

Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. 6. MAIN ROTOR PYLON SECTION (CONT) PHASE NO. ALL

−

ALL

−

2 C

Inspection Requirements Perform electrical chip continuity verification.

−

−

−

−

MH

MOS Status

detector

Inspect engine aft mounts.

6.44 Inspect No. 2 engine control cable as follows: −

Aircraft Serial No.

Inspect No. 2 engine load-demand push/pull cable and collective bias tube linkage at mixer for damage, security, chafing, and grommet wear. Inspect No. 2 engine poweravailable push/pull cable from firewall to HMU for damage, security, chafing, and grommet wear. Inspect No. 2 engine poweravailable push/pull cable from firewall to engine control quadrant for damage, security, chafing, and grommet wear. Inspect No. 2 engine control fuel selector valve push-pull cable for damage and security. Inspect cable-mounting brackets for security.

0.04

15T


Date:

Action Taken

Initial



2

Perform load-demand cable friction check.

−

−

MH

MOS Status

push/pull

6.45 Inspect No. 2 engine starter as follows: −

Aircraft Serial No.

0.06

15T

Inspect No. 2 engine starter for cracks, condition, and security. Drain oil from starter and re-service. Install new packing in oil filler cap and oil drain plug. Inspect start system pneumatic tubes for damage and security.

2

6.46 Inspect No. 2 engine compartment breakaway valves, crossfeed breakaway valve, and tee breakaway valve for visible yellow line around center of valve. If yellow line is visible, replace valve.

0.02

15T

2

6.47 Inspect No. 2 engine flame detectors for cleanness, evidence of overheating, security, and cracked or broken shields.

0.02

15T


Date:

Action Taken

Initial



MH

6.48 Inspect No. 2 engine compartment electrical wiring as follows:

0.04

15T

3.14

15T

−

−

−

2

Aircraft Serial No.

Inspect No. 2 engine compartment electrical wiring for evidence of fraying, chafing, overheating, and condition. Inspect all electrical connectors for security. Inspect electrical components for security and proper grounding.

6.49 HIRSS> Inspect as follows: <= −

−

−

−

−

MOS Status

Remove HIRSS helicopter.

modules

from

Disassemble cores from modules and remove baffles from cores. Inspect rear fairing and panel for cracks, dents, and security of attachment hardware. Inspect nacelle for cracks, dents, and security of attachment hardware. Inspect suppressor and nacelle support mounts for cracks or damaged bearings (TM 1-1520-23723).


Date:

Action Taken

Initial



−

−

−

−

−

−

−

−

2

Aircraft Serial No.

MOS Status

Inspect module bulkhead for cracks. Inspect titanium/steel structure for cracks, and broken spot welds and rivets. Inspect finger seals for loose rivets or bonds. Inspect core assembly for cracks and erosion of emissive coating. Inspect deswirl ducts for damage and deswirl duct clamps for cracks or damage. Inspect HIRSS mount strut attachment nut plates, struts, and mount hardware for corrosion, cracks, and proper installation. Assemble baffles in cores install cores in modules.

and

Install modules on helicopter.

6.50 If modules follows: −

MH

standard engine exhaust are installed, inspect as

Inspect exhaust fairings for cracks and missing or corroding fasteners.

0.01

15T


Date:

Action Taken

Initial



−

2

Aircraft Serial No.

−

−

−

−

−

MOS Status

Inspect exhaust ejectors for damage and foreign objects.

6.51 Inspect follows: −

MH

main

rotor

pylon

as

Inspect main rotor pylon structure, engine cowlings, air inlet fairings, and engine air inlets for cracks and missing or corroding fasteners. Inspect APU air inlet screens for debris or foreign object damage (FOD). Check main rotor pylon sliding cover screens for obstruction. Inspect main rotor pylon sliding cover rollers and tracks for damage and wear. Inspect engine air inlets for foreign objects and foreign object damage. Inspect upper and rear main rotor pylon fairings for cracks and missing fasteners.

0.06

15T


Date:

Action Taken

Initial



−

−

Inspect engine-cowling latches for cracks, positive latching, and secure closure. Close and open cover. Check for smooth operation with no binding. Close and secure main rotor pylon sliding cover, oil cooler compartment doors, and APU compartment doors.

Aircraft Serial No.

MH

MOS Status


Date:

Action Taken

Initial

TM 1-1520-237-PMI



Area Name and No. AVIONICS/ ANTENNAS PHASE NO. 1

Aircraft Serial No.


MH

1. Inspect all antennas as follows: −

−

−

−

MOS Status

1.00

15N

Inspect antennas, gaskets (where installed), and connectors for damage, cracks, security, and cleanness. Inspect insulators for cracks and burn marks. Inspect antenna lead-ins and connectors for signs of overheating and damage. Inspect wiring security.

for

fraying

and

1

2. Inspect IR countermeasures set transmitter and shock mounts and mounting support and shroud for security, cracks, and damage.

0.02

15N

1

3. Inspect chaff and flare dispenser installation provisions for security, cracks, and damage.

0.02

15N


Date:

Action Taken

Initial

TM 1-1520-237-PMI

PHASE INSP NO._______


Area Name and No. POWER ON INSPECTIONS PHASE NO.

Aircraft Serial No.


MH

MOS Status

NOTE Procedures for the following operational checks are in TM 1-1520237-23 or TM 11-1520-237-23 unless otherwise noted. 1

1. Do an operational instrument panel lights.

check

of

0.01

15F

1

2. Do an operational check of upper and lower console lighting.

0.01

15F

1

3. Do an operational check of all cabin dome lights.

0.01

15F

1

4. Do an operational check of cockpit, flood, and secondary lights.

0.01

15F

1

5. Do an operational check of utility and maintenance lights.

0.01

15F

1

6. Do an operational check of instrument panel and console lights dimming.

0.01

15F

1

7. Do an operational check of formation lights.

0.01

15F


Date: Action Taken

Initial

TM 1-1520-237-PMI

Area Name and No. POWER ON INSPECTIONS (CONT) PHASE NO.



MOS Status

1

8. Do an operational check of controllable searchlight.

0.01

15F

1

9. Do an operational check of position lights.

0.01

15F

1

10. Do an operational check of retractable landing light.

0.01

15F

1

11. Do an operational check of anticollision lights.

0.01

15F

1

12. Do an operational check of cargo hook lights.

0.01

15F

2

13. Do an operational check of No. 1 engine fuel filter bypass warning system.

0.12

15F

2

14. Do an operational check of No. 2 engine fuel filter bypass warning system.

0.12

15F

2

15. Do an operational check of No. 1 engine oil filter bypass warning system.

0.05

15F

2

16. Do an operational check of no. 2 engine oil filter bypass warning system.

0.05

15F

2

17. Do an operational check of engine fire detection system.

2.0

15F


Date: Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. POWER ON INSPECTIONS (CONT)

Aircraft Serial No.

PHASE NO.


MH

1

18. Do an operational check of fuel quantity indicating system. Check system for accuracy.

1.55

15F

ALL C

19. Do an operational check of engine, main transmission, intermediate gear box, and tail gear box chip detector and temperature sensor systems.

1.00

15F

2

20. Do an operational check of No. 1 engine TGT indicating system.

0.13

15F 15B

2

21. Do an operational check of No. 2 engine TGT indicating system.

0.13

15F 15B

1

22. Do an operational check of pitot tube heater.

0.1

15F

1

23. Do an operational check windshield anti-ice system.

of

0.1

15T

1

24. Do an operational check of cargo hook emergency release test circuit.

0.24

15F

2

25. Do an operational check of fire extinguishing system.

0.50

15F

2

26. Do an operational stabilator system.

4.0

15F

check

of

MOS Status


Date: Action Taken

Initial


Aircraft Serial No.

PHASE NO.


MH

MOS Status

2

27. Do an operational check of digital automatic flight control units.

1.0

15N

1

28. Do an operational check of pitotstatic system.

1.0

15F

ALL

29. Do an operational check of all transmission instruments and oil warning systems.

3.0

15N

1

30. Do an operational check gyromagnetic compass set.

of

1.0

15N

1

31. Perform Hydraulic Logic Module Test (Para 7-2-1)

0.24

15T

1

32. Do an operational check of communications / navigation equipment.

1.0

15T

1

33. UH-60Q/HH-60LTilt back co-pilots seat. Apply electrical power to helicopter and check the following: <=

0.10

15T

−

Verify system default indicator has no fault indication. Press PTD button and verify all LEDS illuminate and after 3 seconds go off.


Date: Action Taken

Initial


Aircraft Serial No.

PHASE NO.


MH

2

34. Check flight control system for binding. If binding occurs, check flight control bolt installation. Check tail rotor servo for bent input pilot valve stem.

0.15

15T

2

35. Do the hydraulic leak test portion of the hydraulic systems operational check only.

0.4

15T

2

36. Do an operational check of APU and APU electronic sequence unit.

0.43

15T

2

37. Do an operational check of main and tail rotor blade deice systems.

0.5

15T

0.43

15T

ALL

Make sure all doors, covers, panels, fairings, etc. opened during the periodic inspection are closed and secured before performing operational check of the No. 1, 2, and APU generators, oil cooler vibration check, or engine output shaft vibration check.

ALL C

38. Perform engine vibration check.

output

shaft

MOS Status


Date: Action Taken

Initial

TM 1-1520-237-PMI Area Name and No. POWER ON INSPECTIONS (CONT) PHASE NO.

Aircraft Serial No.


MH

MOS Status

Install engine air inlets before flight.

ALL C

39. Perform Idle Speed check both engines.

Leakage

0.4

ALL C

40. Perform oil cooler vibration check.

0.4

2

41. Do an operational check of the No.1, 2, and APU generators.

5.1

15F

ALL

42. Do tail rotor vibration check due to removal/installation of tail rotor blades.

0.50

15T

1

43. UH-60Q/HH-60L Perform an operational check of the ECS systems. <=

0.24

15T


Date: Action Taken

Initial

TM 1-1520-237-PMI

By Order of the Secretary of the Army: PETER J. SCHOOMAKER General, United States Army Chief of Staff Official:

SANDRA R. RILEY Administrative Assistant to the Secretary of the Army 0504704

DISTRIBUTION: To be distributed in accordance with Initial Distribution (IDN) IDN 314144 requirements for TM 1-1520-237-PMI

T h e s e ar e t h e in s t r u c t i o n s f o r s e n d i n g a n e l ec t r o n i c 2 02 8 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. F r o m : Joe Smith 2. Unit: home 3. A d d r e s s : 4300 Park 4. C i t y : 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. S u b m i t t e r N a m e : Joe 14. Submitter MName: T

15. S u b m i t t e r L N a m e : Smith 16. S u b m i t t e r P h o n e : 123--123--1234 17. P r o b l e m : 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.

The Metric System and Equivalents L inear Measu re L iquid Measu re 1 centimeter = 10 millimeters = .39 inch 1 centileter = 1 milliliters = .34 fl. ounce 1 decimeter = 10 centimeters = 3.94 inches 1 deciliter = 10 centiliters = 3.38 ounces 1 meter = 10 decimeters = 39. 37 inches 1 liter = 10 deciliters = 33. 81 fl. ounces 1 dekameter = 10 meters = 32. 8 feet 1 dekaliter = 10 liters = 2.64 gallons 1 hectometer = 10 deka meters = 328. 08 feet 1 hectoliter = 10 dekaliters = 26. 42 gallons 1 kilometer = 10 hectometers = 3,280. 8 feet 1 kiloliter = 10 hectoliters = 264. 18 gallons Weights 1 c entigram = 10 milligrams = 1.5 grain 1 hectogram = 10 dekagrams = 3.52 ounces 1 decigram = 10 centigrams = 1.54 grains 1 kilogram = 10 hectograms = 2.2 pounds 1 gram = 10 decigrams = .035 ounce 1 quintal = 100 kilograms = 220. 46 pounds 1 dekagram = 10 grams = .35 ounce 1 metric ton = 10 quintals = 1.1 short tons

S quare Measu re 1 sq. centimeter = 100 sq. millimeters = .155 sq. inch 1 s q. decimeter = 100 s q. centimeters = 15. 5 sq. inches 1 sq. meter (centare) = 100 s q. decimeters = 10. 76 sq. feet 1 sq. dekameter (are) = 100 sq. meters = 1,076. 4 feet 1 s q. hectometer (hectare) = 100 sq. dekameters = 2.47 ac res 1 sq. kilometer = 100 sq. hectometers = .386 sq. mile Cu bic Measu re 1 cu. centimeter = 1000 cu. millimeters = .06 cu. inch 1 cu. dec imeter = 1000 cu. c entimeters = 61. 02 cu. inches 1 cu. meter = 100 cu. decimeters = 35. 31 feet

Approximate Conversion Factors To C ha nge inches feet yards miles square inches s quare feet square yards s quare miles ac res cubic feet cubic yards fluid ounces pints quarts gallons ounces pounds short tons pound--feet pound-- inc hes

To Mult iply B y centimeters 2.540 meters .305 meters .914 kilometers 1.609 s quare centimeters 6.451 s quare meters .093 s quare meters .836 s quare kilometers 2. 590 s quare hec tometers .405 cubic meters .028 cubic meters .765 mililiters 29. 573 liters .473 liters .946 liters 3.785 grams 28. 349 kilograms .454 metric tons .907 newton--meters 1. 356 newton-- me te rs . 11296

To C ha nge ounce--inches centimeters meters meters kilometers s quar e centimeters square meters s quar e meters square kilometers square hec tometers cubic meters cubic meters milliliters liters liters liters grams kilograms metric tons

Temperature (Exact)

To newton--meters inches feet yards miles s quar e inches s quare feet s quar e yar ds s quare miles ac res cubic feet cubic yards fluid ounces pints quarts gallons ounces pounds s hort tons

Mult iply B y .007062 .394 3. 280 1.094 .621 . 155 10. 764 1. 196 .386 2.471 35. 315 1. 308 .034 2. 113 1. 057 .264 .035 2. 205 1. 102

TM 1-1520-237-PMI_Helicopter_EH-60_UH-60_2005

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