ATTACHMENT_84_-_PWS_Encl_14_T44C_SIRG_01-50-T44C-600-6-4.1.pdf

NAVAIR (PMA 273) 01-50-T44C-600-6-4.1

U.S. NAVY T-44C

PEGASUS

1st DETAILED

INSPECTION

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

NAVAIR (PMA273) 01-50-T44C-600-6-4.1

January 1, 2013

PAGE EFFECTIVITY LISTING

NAVAIR (PMA 273) 01-50-T44C-600-6-4.1

Summary:

• The original issue of the NAVAIR (PMA 273) 01-50-T44C-600-6-4.1 is dated

November 1, 2005.

• The date of this change, which is complete reissue, is January 1, 2013.

Page(s) Change Number Date Comments

Cover NA 1/1/2013 Changes Not Bar Marked i NA 1/1/2013 Changes Not Bar Marked 1 NA 1/1/2013 Changes Not Bar Marked 2 NA 1/1/2013 Changes Not Bar Marked 3 NA 1/1/2013 Changes Not Bar Marked 4 NA 1/1/2013 Changes Not Bar Marked 5 NA 1/1/2013 Changes Not Bar Marked 6 NA 1/1/2013 Changes Not Bar Marked 7 NA 1/1/2013 Changes Not Bar Marked 8 NA 1/1/2013 Changes Not Bar Marked 9 NA 1/1/2013 Changes Not Bar Marked 10 NA 1/1/2013 Changes Not Bar Marked 11 NA 1/1/2013 Changes Not Bar Marked 12 NA 1/1/2013 Changes Not Bar Marked 13 NA 1/1/2013 Changes Not Bar Marked 14 NA 1/1/2013 Changes Not Bar Marked 15 NA 1/1/2013 Changes Not Bar Marked 16 NA 1/1/2013 Changes Not Bar Marked 17 NA 1/1/2013 Changes Not Bar Marked 18 NA 1/1/2013 Changes Not Bar Marked

18.1 NA 1/1/2013 Changes Not Bar Marked

19 NA 1/1/2013 Changes Not Bar Marked 20 NA 1/1/2013 Changes Not Bar Marked 21 NA 1/1/2013 Changes Not Bar Marked

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

TERIM CHANGE NOTICE (ICN) LOG

ICN Number Page/Section/Item Date Comments/Information

Interim Change Notice information and entry requirements:

Interim Change Notices (ICNs) can be either issued in hard copy, navy message format or via E-Mail.

Each ICN will have a unique serial number assigned for tracking purposes.

When an ICN is received/issued holders of the Scheduled Inspection Requirements Guide (SIRG) will be required to enter the data in the above log in the appropriate section of the manual that it applies to; i.e., the NAVAIR (PMA-273) 01-50-T44C-600-6, 600-6-4.1, 600-6-6-4.2 or the Corrosion Control Manual.

NOTE: Changes to the Daily/Turnaround and the Seven Day Inspection MRCs will be annotated on Page ii of the applicable MRC package.

Entry information requirements in the above ICN Log are self-explanatory. All ICNs will be incorporated into the appropriate portion of the SIRG package when a formal change is to the document is issued.

Copies of ICNs shall be posted to the applicable document immediately behind the title/cover page and a notation shall be made in the appropriate/referenced area of the affected document to alert the user to the ICN that has modified or amended the requirements.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

TECHNICAL INFORMATION REPORT, DISCRPANCY (TIRD)

CHANGE RECOMMENDATION

(TO BE FILLED IN BY ORIGINATOR)

REPORT DATE: __________________________________

FROM (Originator): ________________________________ ACTIVITY: ________________________________________

ADDRESS AND/OR E-MAIL OF ORIGINATOR:________________________________________________________________

SEND COMPLETED FORM TO:

NAVAIRSYSCOM

ATTENTION: PMA-273, T-34 OR T-44 APMSE

22581 SAUFLEY ROAD, BUILDING 3258

PATUXENT RIVER, MARYLAND 20670

NAME/P/N OF MANUAL CHANGE # CHANGE DATE PAGE/SECTION/PARAGRAPH

DEFICIENCY: ____________________________________________________________________________________________

RECOMMENDATION (Be Specific): __________________________________________________________________________

________________________________________________________________________ Check if continuation sheets or drawings attached.

IMPACT: _________________________________________________________________________________________________

REPORT BY: _____________________________________________

SIGNATURE:____________________________________________

_ TITLE:________________________________________

TO BE FILLED IN BY PMA-273

FROM: _________________________________________________ DATE: ________________________________________

TO: _____________________________________________________

REFERENCE:_______________________________________________________________________________________________

Your change recommendation has been received and is currently in review for possible incorporation.

INSTRUCTIONS FOR COMPLETING THE TIRD

1. REPORT DATE: This identifies the year, month, and day that the report was prepared and consists of six digits, e.g., 050115. The first two digits indicate the year, the second two digits indicate the month, and the remaining two digits specify the day.

2. FROM: The reporting activity originating change request. Address and/or e-mail address should be provided.

3. ACTIVITY: The activity reporting the discrepancy, e.g., contractor, NAS Corpus Christi, TX.

4. TECHNICAL MANUAL: Give the complete number assigned to the manual being reported as deficient.

5. CHANGE NUMBER: This appears on the area/page on which the deficiency is located.

6. CHANGE DATE: This appears on the area/page on which the deficiency is located.

7. SECTION/PAGE: Enter the number of the pages of the technical manual on which the deficiency is located.

8. PARAGRAPH: Enter the specific number in which the deficiency is located.

9. DEFICIENCY: Be very specific. Provide complete information regarding discrepancy, including drawings, schematics, sketches, and references. If necessary, attach copies of any reference data.

10. RECOMMENDATION: Be very specific. Provide complete information regarding the corrective action required, including drawings, schematics, sketches, and references. If necessary, attach additional pages.

11. IMPACT: Enter concise statement of the impact of this discrepancy on work load/operational readiness.

12. REPORTED BY: Name and position of person that prepared the TIRD.

FIRST 100-HUNDRED HOUR INTERVAL DETAILED INSPECTION

FORMS REQUIRED: The following forms are required to accommodate the requirements:

• First 100-Hour Detailed Inspection

• Power Assurance Run Work Sheet

• Continuous Inspection Work Sheet

• VIDS/MAF (OPNAV Form 4790/60)

REFERENCE MATERIAL: The following technical manuals/data may be required to accommodate the requirements:

• BEECHCRAFT Model H90 (T-44A) Maintenance Manual, Part Number 92-38879

• BEECHCRAFT Model H90 (T-44A) Wiring Diagram Manual, Part Number 92-38028

• Pratt & Whitney PT6A-34B Engine Maintenance Manual, Part Number 3021242

• Other publications, as required, that are listed in the Maintenance Manual Supplementary Publications List.

• NAVAIR 01-T44AAC-1, NATOPS Manual

• Maintenance Engineering Directives (MED)

• Local Engineering Specification (LES) NOTE: The Maintenance, Parts and Wiring Manuals used for the T-44C Aircraft are predominately T-44A Manuals. The peculiar T-44C data is contained in supplements to the appropriate areas of the applicable manuals.

INSPECTION PROCEDURES: The following ground rules are to be adhered to by personnel directly involved with the requirements specified for the inspection:

• The Engine Wash and Power Assurance Run (PAR) are to be performed immediately after completion of the Detailed Inspection. The PAR Sheet and the associated Sign- Off sheet are contained in the back of this package.

• Fill out heading on each form in its entirety.

• Each item on the inspection form is to be checked/initialed on the form in the spaces provided.

• List all discrepancies found during the inspection on the Continuous Inspection Work Sheet.

• Initiate VIDS/MAFs (OPNAV Form 4790/60) for all discrepancies requiring replacement of repairable components and all discrepancies that are deferred/not completed as part of the inspection.

• Each discrepancy is to be signed off when the discrepancy has been corrected.

• When the inspection has been completed, the Supervisor will sign the “INSPECTION COMPLETED” block at the end of the inspection sheet.

NOTE: In case of conflict, the lubrication data contained in the attached lubrication charts/tables takes precedence over and supercedes the data contained in Section 12-00-00 of the T-44A Maintenance Manual.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

T-44C CONTINUOUS INSPECTION REQUIREMENTS

FIRST 100 HOUR INTERVAL INSPECTION REQUIREMENTS

Inspection Date: _______________ JCN: __________________ BUNO: ______________________

Aircraft Time: ________________ Landings: ______________ Engine Time L/H _____ R/H _____

A. WINGS

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. SKIN - Inspect skin for condition and loose or missing rivets. If damage is found, check adjacent structure.

2. STRUCTURE - Check for cracks, loose rivets and concealed damage.

3. CABLES AND PULLEYS – Check control cables, pulleys and associated equipment for condition, attachment, alignment, clearance and proper operation.

4. AILERON AND TAB. Inspect skin for condition and loose or missing rivets. Check surfaces fittings for proper attachment and freedom of movement. Check trim tab actuator for proper operation, smoothness and attachment.

5. FLAPS AND ACTUATORS – Inspect flap drive and actuator for condition and attachment. Check skin and structure for condition and loose or missing rivets.

6. LIGHTS. Check navigation lights for broken lenses.

7. FUEL TANKS AND VENTS – Inspect fuel cells for leaks and vents for obstruction.

8. ELECTRICAL WIRING AND EQUIPMENT - Check for security, chafing, damage and attachment.

9. PLUMBING - Check for leaks, chafing or damage, and proper attachment.

10. WING BOLTS - Check for condition and security.

11. DEICER BOOTS - Check for condition and attachment.

12. ACCESS DOORS - Check for fit and attachment after installation.

13. STROBE LIGHTS - Check for proper operation, and cracked or broken lens.

14. FORWARD WING SPARS - Thoroughly inspect the upper and lower spar caps and hinge lobe areas for signs of buckling, loose or raised paint and other evidence of corrosion.

Using a strong light source, inspect visual internal structure of wing spar via already opened wing access panels for corrosion, i.e. grayish/white powder and flaking substance on or around spar area.

15. FORWARD WING SPARS SEALENT- Thoroughly inspect the condition of the sealant used to seal the hinge lobe areas of both the upper and lower spar caps.

16. STATIC WICK- Perform static wick inspection, IAW H90 MM CH 23-60-00

B. WING CENTER SECTION

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. SKIN - Inspect for condition and loose or missing rivets. If damage is found, check adjacent structure.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

January 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

B. WING CENTER SECTION (Continued)

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

2. STRUCTURE - Check for cracks, loose rivets and concealed damage.

3. FUEL TANKS, VENTS AND PUMPS – Inspect fuel cells and pumps for leaks and vents for obstruction.

4. VACUUM RELIEF VALVE – Inspect for proper installation (flow arrow towards filler neck). Inspect fuel cell cover and area for corrosion, cracks, loose rivets and damage.

5. FLAPS AND ACTUATORS – Inspect flap drive and actuator for condition and attachment. Check skin and structure for condition and loose or missing rivets. Check flap roller mounting bolts and nuts for tightness.

6. LEADING EDGE PLUMBING AND WIRING - Check for chafing, damage, security and leaks.

7. CABLES AND PULLEYS - Check control cables, pulleys, and associated equipment for condition, attachment, alignment, clearance and proper operation.

8. BATTERY COMPARTMENT – Check for general condition. Removal of the battery is not required.

9 ACCESS DOORS - Check for fit and attachment after installation.

10. ENGINE FIRE EXTINGUISHER - Check pressure of supply cylinder. Check plumbing for leakage and security of attachment.

11. FIRE DETECTORS - Check all detectors for sensitivity as outlined in MED PR-56.

CAUTION

DISCONNECT THE GROUND AND POWER WIRES PRIOR TO TESTING THE FIRE EXTINGUISHING SYSTEM.

12. FIRE BOTTLE - Inspect the firing circuits for proper operation.

C. MAIN GEAR AND BRAKES

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. CLEVELAND BRAKES

1.1 Check brake discs, linings, calipers and lines for wear, damage, corrosion and security of all units. Lining max. wear limit: 0.100” Disc max. wear limit 0.410”

1.2 Check torque plate mounting bolts for proper torque (130-150 in/lbs).

Torque Wrench # __________ Cal Date __________ Torque L/H __________ Torque R/H __________

2. WHEELS AND TIRES – Check wheels for condition and tires for wear, condition, and proper inflation. (54-60 psi) Inflator Kit # ________ Inflator Cal Date # ________ Final Tire Pressure Left __________ Final Tire Pressure Right __________

NOTE

Raytheon Aircraft Safety Communiqué Number 239 dated November 2003, which pertains to the main landing gear wheels, provides additional/alternate means for aligning the slot in the castellated nut and the cotter pin hole in the axle to preclude exceeding the maximum torque. In the case of the T-44C that torque is, 120-inch pounds of torque. If the castellated nut and the cotter pin hole can’t be aligned within the specified torque range, remove and replace the axle nut or add an additional adjusting washer P/N NAS1149C1616R, NAS1149F1616P or NAS1149G1616P and re-torque in accordance with the current established guidelines.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

January 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

C. MAIN GEAR AND BRAKES (Continued)

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

3. Clean, inspect and/or replace and lubricate wheel bearings with SHC 100 Mobil Aviation Synthetic Grease. Torque the retainer nut while the wheel is being rotated clockwise to 200-inch pounds to seat the bearings. Back off the torque to zero and re-torque to 60 to 120-inch pounds. Reference MED 32-40-00/PR-106.

Torque Wrench #___________ Cal Date ______________

Torque L/H _______________ Torque R/H ____________

4. ACTUATOR – Check actuator and support brackets for visible damage and condition.

Inspect bracket for loose or missing rivets.

5. CLEVIS BOLTS – Remove the left and right clevis bolts and inspect for wear, Re-install after inspection.

6. LANDING GEAR STRUT – Inspect shock strut and components for condition and attachment.

7. STRUT D LEVEL- Inspect struts for proper inflation and leakage.

8. DRAG LEG – Check for security of attach fittings.

9. STRUT HOUSINGS – Using a bright light and a 10X magnifying glass, visually inspect the drag link collars for cracks in the brazed areas.

10. LANDING GEAR TORQUE SHAFTS - Inspect shafts and universal joints outside pressure vessel for condition, attachment and visible damage.

D. NOSE GEAR CORRECTED

BY

INSPECTED

BY

1. WHEEL AND TIRE – Check wheels for condition and tire for wear, condition and proper inflation. (50-55psi) Inflator kit # ________ Inflator Cal Date ________ Final Tire Pressure ________

2. Clean, inspect and/or replace and lubricate wheel bearings with SHC 100 Mobil Aviation Synthetic Grease. Torque the retainer nut with the wheel being rotated clockwise to 200-inch pounds to seat the bearings. Back off the torque to zero and re-torque to 30 to 100-inch pounds. Reference MED 32-40-00/PR-106.

Torque Wrench #__________ Cal Date ____________ Torque ______________

3. NOSE GEAR DRAG LEG THROUGH BOLT – Remove lower drag brace through bolt.

Clean bosses and check for condition and corrosion. Re-install bolt and torque 200 – 400 inch/lbs. (as outlined in Chapter 32-20-00 of the BEECHCRAFT Model H90 Navy T-44A Maintenance Manual.)

Torque Wrench # ___________Cal Date _____________Torque ______________

4. SHIMMY DAMPENER – Remove and inspect dampener and bosses for condition as outlined in Chapter 32-20-00 of the BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual. Re-install after inspection.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

D. NOSE GEAR (Continued) CORRECTED

BY

INSPECTED

BY

5. ACTUATOR – Check actuator and support brackets for visible damage and condition.

Inspect bracket for loose or missing rivets.

6. STEERING LINKAGE- Check nose steering mechanism for condition, attachment and correct adjustment.

7. NOSE GEAR STRUT- Inspect strut and components for condition and attachment.

8. STRUT LEVEL- Inspect strut for proper inflation and leakage.

9. NOSE GEAR STEERING – Remove stop on nose gear casting and check lug for cracks.

Re-install after inspection

10. NOSE LANDING GEAR LIGHT – Check landing lights for broken lenses and proper focus.

11. NOSE GEAR RETRACT CHAIN – Inspect the chain external of pressure vessel for broken links, dirt and corrosion.

E. LANDING GEAR FUNCTIONAL/OPERATIONAL CHECK CORRECTED

BY

INSPECTED

BY

CAUTION

Since battery voltage is not sufficient to properly cycle the landing gear, use only an external power source capable of delivering and maintaining 28.25 + .25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection. Jack the aircraft before starting the landing gear retraction inspection.

1. RETRACT MECHANISM – Check retraction system for proper operation of all components through at least two complete cycles. Check for unusual noises and evidence of binding.

2. DOORS AND LINKAGE - Check door operation, fit, fair, and rigging.

3. POSITION INDICATORS - Check for security and adjustment of switches, loose wires, and proper indication.

4. WARNING HORN - Check for proper operation.

5. DOWN-LOCKS. Check locking mechanism for positive engagement, in extended position.

Check down-lock switch for proper adjustment.

6. LIMIT SWITCHES - Check for proper adjustment and attachment. Lube with LPS-1.

NOTE

Clean squat switches and preserve with CPC Mil-L-81039 Type III, Class I or II

7. MAIN LANDING GEAR SQUAT SWITCHES – Physically check condition and attachment.

8. R/H MAIN LANDING GEAR SQUAT SWITCH – Check for proper operation as follows:

8.1 Pull the Landing Gear Control circuit breaker.

8.2 Disconnect the R/H squat switch from the torque knee and position the switch arm to simulate a weight on wheels condition.

8.3 Ensure that the landing gear is clear. Position the Landing Gear Handle to the up position. Reset the Landing Gear Control circuit breaker.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

January 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

E. LANDING GEAR FUNCTIONAL/OPERATIONAL CHECK (Continued)

CORRECTED

BY

INSPECTED

BY

8.4 If the landing gear squat switch operates properly and the landing gear does not initiate the retract sequence, no further action/testing is required. If the landing gear starts to retract, pull the Landing Gear Control circuit breaker immediately. Check rigging and adjust the landing gear safety switch, as required, in accordance with the T-44A Maintenance Manual, Section 32-60-00, Page 201, “Rigging Gear Safety Switch”.

8.5 Pull the Landing Gear Control circuit breaker and return the Landing Gear Handle to the down position.

8.6 Reconnect the R/H squat switch.

9 ACTUATORS - Check for noise, binding, and proper rigging.

10. EMERGENCY EXTENSION – Check system for freedom of operation and positive engagement of down locks.

CAUTION

DO NOT CONTINUE OPERATION AFTER RECEIVING GEAR DOWN INDICATION. FURTHER MOVEMENT OF THE HANDLE COULD DAMAGE THE DRIVE MECHANISM AND PREVENT SUBSEQUENT ELECTRICAL GEAR

RETRACTION. THE LANDING GEAR CANNOT BE RETRACTED MANUALLY.

F. NOSE SECTION

CORRECTED

BY

INSPECTED

BY

1. VACUUM REGULATOR VALVE FILTER – Replace or clean in accordance with, Chapter 37-00-00, BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual.

2. BRAKE RESERVOIR – Inspect reservoir and fill as needed.

G. AIR CONDITIONING AND PRESSURIZATION

CORRECTED

BY

INSPECTED

BY

1. REFRIGERANT COMPRESSOR - Check for condition, attachment, and oil leaks.

2. COMPRESSOR DRIVE BELTS – Check for condition. Check adjustment as outlined in Chapter 21-50-00 of the BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual.

3. COMPRESSOR DRIVE MOTOR - Check for condition and attachment. Check that the fan blade tips clear the shroud.

4. REFRIGERANT LINES AND SERVICE VALVES- Inspect lines and valves for condition and attachment.

5. AIR CONDITIONER FILTERS – Replace filter in accordance with Chapter 12-10-00 of the BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual.

6. REFRIGERANT LEVEL - Check sight glass to ensure fluid is clear.

7. OUTFLOW AND SAFETY VALVE - Check for condition and attachment. Check safety valve screen for obstruction. Clean as outlined in Chapter 12-10-00 in the BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual if required.

8. PRESSURIZATION CONTROL FILTER - Check for cleanliness and damage in accordance with BEECHCRAFT Model H90 Navy T-44) MM 12-10-00.

9. PRESSURIZATION CONTROLLER - Check for security of attachment, condition of case and glass, and condition and operation of control knobs. Check lights and wiring for proper insulation and security of electrical connections. Inspect plumbing for condition and security of attachment. Inspect for broken safety wiring.

NAVAIR (PMA 273) 01-50-T-44A-600-6-4.1

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

G. AIR CONDITIONING AND PRESSURIZATION (Continued)

CORRECTED

BY

INSPECTED

BY

10. BLEED AIR BYPASS VALVES – Visually and aurally check bleed air bypass valves at heat exchangers for proper operation of linkage to butterfly valve and operation of actuator motor.

H. REAR FUSELAGE AND EMPENNAGE CORRECTED

INSPECTED

BY

1. SKIN – Inspect skin for condition and loose or missing rivets. If damage is found, check adjacent structure.

2. STRUCTURE – Check for cracks, loose rivets and concealed damage.

3. CABLES AND PULLEYS- Check control cables, pulleys and associated equipment for condition, attachment, alignment, clearance and proper operation.

4. ELEVATOR AND TAB- Inspect skin for condition and loose or missing rivets. Check

L/H R/H

5. RUDDER AND TAB- Inspect skin for condition and loose or missing rivets. Check

6. ELEVATOR AND RUDDER TRIM TAB ACTUATOR SERVOS- Check wiring of electric trim tab servos for connection, security of attachment and condition. Check electric trim tab servos for full travel.

6.1 Elevator Trim Cable Inspection: A thorough inspection of all T-44 elevator trim tab actuator cables will be accomplished in accordance with MM Ch 27-30-00. This procedure will include cleaning the length of the trim tab control cables through the pulleys (8 totals) with PD-680 Type 3 while simultaneously running the controls through its full travel period. The cables will be inspected for corrosion, fraying and condition. If no discrepancies are noted, lubricate cables with corrosion preventive compound Mil-C-16173 by brushing on then wiping off excess with dry cloth.

7. STATIC PORTS – Check for obstructions

8. DEICER PLUMBING - Inspect plumbing for condition and attachment

9. DEICER BOOTS – Check for condition and attachment.

10. NAVIGATION LIGHTS, STROBE LIGHTS AND ROTATING BEACONS - Check for cracked or broken lenses.

11. ACCESS DOORS - Check for fit and attachment after installation

12. AUTOPILOT- Check components for damaged cases, bent or broken pins in electrical connectors, damaged seals, poor solder connections and damaged insulation on wiring.

13. CONTROL CABLE SEALS – Check for condition, security, cleanliness and lubrication

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

January 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

H. REAR FUSELAGE AND Empennage (Continued)

CORRECTED

BY

INSPECTED

BY

14. STATIC WICK- Perform static wick inspection in accordance with MM CH 23-60-00.

MEGOHMMETER S/N_______________________ Cal Date __________________

15. VENTRAL FIN - Check for obstruction of the drain holes in the ventral fin just fore and aft of the access door on the RH underside of the fuselage. Check for obstructions of the drain holes in the base of the stringers on each side of the door at the point of juncture with the aft pressure bulkhead.

16. ELT BATTERY INSPECTION – Perform the following:

NOTE

Leakage will show up as a white residue that normally occurs first around the battery leads.

16.1 Check visually for leakage.

16.2 Check visually for corrosion at battery terminals, PC board and components.

16.3 Check for secure battery leads.

I. POWER PLANT

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. FUEL FILTERS AND SCREENS – Inspect all fuel filters and screens for evidence of foreign matter, corrosion or microbiological growth in the fuel system.

1.1 Firewall Filter – Check for foreign matter and condition. Replace with filter that has been ultrasonically cleaned. Torque the Air Maze type filter assembly to 80 – 180-inch pounds. Torque the Purolator type filter assembly to 30 – 50-inch pounds. Leak check the filter assembly after installation using the electric boost pump.

Torque Wrench __________Cal Date__________

Torque L/H __________ Torque R/H __________

1.2 Fuel Pump Inlet Filter (Screen Filter) - Check for foreign matter or distortion. Clean and reinstall or replace as necessary. Torque cap to 180 – 220-inch pounds.

Torque Wrench #__________Cal Date__________

Torque L/H ____________ Torque R/H ____________

1.3 Fuel Pump Outlet Filter (Paper Filter) - Check for condition and foreign matter.

Install new filter. Torque cover to 180 – 220-inch pounds.

Torque Wrench # _____________ Cal Date ________ Torque L/H __________ Torque R/H ___________

NAVAIR (PMA 273) 01-50-T44C-600-4.1

JANUARY 1, 2013

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

I. POWER PLANT (Continued)

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

2. FUEL DRAIN COLLECTOR SYSTEM (EPA PUMP) – Perform the following:

2.1 Check for security of attachment of tank and pump.

2.2 Check hoses for cracks, deterioration and proper attachment.

2.3 Inspect pump screen/filter for condition. Clean and/or replace as required.

2.4 Install screen/filter, new gasket and reassemble and secure the assembly.

3. ENGINE OIL FILTER – Remove and inspect for condition and foreign matter. Replace with clean filter received from supply. Torque to 32 – 36-inch pounds.

Torque Wrench #________ Cal Date ____________ Torque L/H ____________ Torque R/H __________

4. CHIP DETECTOR - Inspect for metal accumulation prior to performing circuit test.

Reinstall and torque to 45 – 55-inch pounds

Torque Wrench #____________ Cal Date ____________

Torque L/H ______________ Torque R/H ____________

5. OIL QUALITY – Check oil level and service as required.

6. ENGINE - Inspect entire engine and nacelle area for security and general condition.

7. FLOW CONTROL UNIT - Inspect unit and associated equipment, electrical wiring, ducts and bleed airlines for condition, attachment and adequate insulation.

8. ENGINE MOUNTS – Inspect engine mounts aft of the firewall for condition and corrosion.

J. AIR STAIR DOOR CORRECTED

BY

INSPECTED

BY

1. Check/Inspect the Air Stair Door as follows:

1.1 Inspect door, seals, latching mechanism, cables and safety chain and hook for condition and security of attachment.

1.2 Check that folding steps do not engage too soon and that they fold properly without interference.

1.3 Check condition, attachment, and operation of door dampener.

1.4. Check door cable for proper length. The upper cable should be 68.8 inches long and lower cable should be 23.6 inches long as measured from the center of hole to center of hole in cable clevis ends.

1.5 Inspect doorframe assembly for cracks. Inspection and repair criteria shall be in accordance with MED PR-47.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

January 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

J. AIR STAIR DOOR (Continued) CORRECTED

BY

INSPECTED

BY

1.6 Inspect cabin door hinge for cracks, corrosion. Apply torque to hinge by moving air stair door BY HAND to check for security of hinge. Looseness of hinge suggests oversized holes or cracks in hinge.

1.7 Close all panels after inspection.

K. GENERAL SERVICE ITEMS CORRECTED

BY

INSPECTED

BY

1. CLEANING – Vacuum and clean aircraft interior. Clean windshields and windows.

NOTE

Aircraft are washed every fourteen (14) days in accordance with the provisions of the NAVAIR T-44C Corrosion Control Plan.

2. SERVICING – Aircraft and systems serviced in accordance with applicable technical data.

3. LUBRICATION – Aircraft lubricated as specified in the attached lubrication charts/tables.

L. ENGINE WASH AND POWER ASSURANCE RUN

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. Check the physical condition and alignment of the wash rings and all associated plumbing.

2. Perform engine wash in accordance with the Pratt and Whitney Maintenance Manual.

3. During the engine rinse evolution visually check the spray ring for proper operation to ensure a good full spray pattern is being delivered to the engine and that none of the nozzles/orifices are clogged.

4. Perform Power Assurance Run and record the results on the form provided in the back of the Detail Inspection package.

M. OPERATIONAL CHECK

CORRECTED

BY

INSPECTED

BY

L/H R/H L/H R/H

1. Perform pre-start, engine start and ground run-up in accordance with the NAVAIR 01-T-

44AAC-1.

2. Inspect engine after ground run. Check for oil and fuel leaks security, and attachment of external components.

3. Check engine oil level after ground run. Service as required.

4. Install all cowling removed during the phase inspection.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

N. CDI FINAL CORRECTED

BY

INSPECTED

BY

1. Comply with final closure inspection FOD check.

O. SCHEDULED REMOVAL COMPONENT INVENTORY CORRECTED

BY

INSPECTED

1. Comply with serial number verification sheet p. 21.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

FIRST 100 HOUR DETAILED INSPECTION LUBRICATION CHART

Air Stair Door and Flap Tracks

Index No Location Lubricant Interval Accomplished By Inspected By

1 Cabin Door Latching Mechanism

VV-L-800 General Purpose Oil

1/100 Detail

2 Flap Roller Tracks (8 Places Per Side)

Dry Slide, Synthetic Molybdenum (Spray)

1/100 and 2/100 Detail

NOTE: Index numbers may not match T-44A Maintenance Manual lube chart index numbers.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

Tabs and Wiper Arms

1 Rudder Trim Tab Tube VV-L-800 General Purpose Oil 1/100 and 2/100 Detail

2 Rudder Trim Tab Actuator Chain 30 WT. Oil 1/100 Detail

3 Rudder Trim Tab Hinge VV-L-800 General Purpose Oil 1/100 and 2/100 Detail

4 Elevator Trim Tab Actuator (2 Places) MIL-G-23827 Grease 1/100 and 2/100 Detail

5 Elevator Trim Tab Control Tubes (4 Places)

VV-L-800 General Purpose Oil 1/100 and 2/100 Detail

6 Elevator Trim Tab Hinges

VV-L-800 General Purpose Oil 1/100 and 2/100 Detail

7 Aileron Trim Tab Actuator MIL-G-23827 Grease 1/100 Detail

8 Windshield Wiper Hinges VV-L-800 Oil 1/100 and 2/100 Detail

1 2

4 5 6

NOTE: Index numbers may not match T-44A Maintenance Manual lube chart index numbers.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

Nose Landing Gear

Index No Location Lubricant Interval Accomplished By

Inspected By

1 Door Hinges and Retract Linkage

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

2 Grease Fittings

MIL-G-81322 Grease 1/100 and 2/100 Detail

3 Reserved

4 Nose Wheel Steering Mechanism

MIL-G-81322 Grease 1/100 and 2/100 Detail

5 Top Brace Assy (Grease Fittings)

Aeroshell Grease 17 (Do Not Substitute)

1/100 and 2/100 Detail

6 Grease Fittings MIL-G-81322 Grease 1/100 and 2/100 Detail

7 Drag Leg Stop Bolt Grease Fitting

MIL-G-81322 Grease 1/100 and 2/100 Detail

Main Landing Gear

Index No Location Lubricant Interval Accomplished

By Inspected

By L/H R/H L/H R/H

1 Grease Fittings MIL-G-81322 Grease 1/100 and 2/100 Detail

2 Reserved

3 Retract Grease Fittings (10 Places)

MIL-G-81322 Grease 1/100 and 2/100 Detail

4 Door Hinges and Retract Linkage (12 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

5 Yoke Assembly, Drag Brace

M77 Graphite Paste 1/100 and 2/100 Detail

NOTE: Index numbers may not match T-44A Maintenance Manual lube chart index b

1 1 6

NOTE: Index numbers may not match T-44C Maintenance Manual lube chart index b

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

Landing Gear Retract System

Index No Location Lubricant Interval Accomplished By

Inspected By

1 Emergency Extension Mechanism

VV-L-800 General Purpose Oil 1/100 and 2/100 Detail

2 Limit Switch Screw and Nut

M77 Graphite Paste. Wipe Off All Excess. 1/100 and 2/100 Detail

3 Shaft Bearings MIL-G-81322 Grease 1/100 and 2/100 Detail

4 Landing Gear Clutch Fingers M77 Graphite Paste 1/100 and 2/100 Detail

5 Nose Gear Retract Chain SAE 30W Oil 1/100 and 2/100 Detail

NOTE: Index numbers may not match T-44A Maintenance Manual lube chart index numbers.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

Engine Controls and Propeller

L/H R/H L/H R/H

1 Control Rod Ends

MIL-G-23827 Grease 1/100 and 2/100 Detail

2 Cam Plates and Pins

Lubriplate No. 130A 1/100 and 2/100

3 Propeller Hub Blade Clamps (3 Places)

Aeroshell 6 Grease

1/100 and 2/100

4. Low Pitch Stop Rods Marvel Mystery Oil 1/100 and 2/100

NOTE: Index numbers may not match T-44A Maintenance Manual lube chart index numbers.

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

T44C CONTINUOUS INSPECTION DISCREPANCEY RECORD WORK SHEET

AIRCRAFT BUNO:________________ JCN: ________________ DATE: _______________

ITEM STATUS DISCEPANCY CORRECTIVE ACTION MECH CDI QA M/H

1. ↑↓

2. ↑↓

3. ↑↓

4. ↑↓

5. ↑↓

6. ↑↓

7. ↑↓

8. ↑↓

9. ↑↓

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

INSPECTION COMPLETED

DATE: _____ /_____ / _____ AIRCRAFT BUNO: __________MODEX: ________________

I certify that a Detailed Inspection was performed in accordance with the Continuous Inspection Program and that the aircraft is approved for return to service.

COMPLETED BY: _________________________________

QUALITY ASSURANCE REPRESENTATIVE: _____________________________

DATE: _____/_____ /_____

ALL EMPLOYEES PERFORMING TASKS ON THIS INSPECTION MUST ENTER THEIR NAMES,

SIGNATURE AND INITIALS.

EMPLOYEE NAME (PRINT) EMPLOYEE SIGNATURE EMPLOYEE

INITIALS

INSPECTION COMPLETED (Continued)

ALL EMPLOYEES PERFORMING TASKS ON THIS INSPECTION MUST ENTER THEIR NAMES,

SIGNATURE AND INITIALS.

NAVAIR (PMA 273) 01-50-T-44C-600-6-4.1

Page 18.1

POWER ASSURANCE RUN SIGN-OFF SIGNATURE AND INITIALS RECORD

Aircraft BUNO

Date Purpose Of Run Outside Air Temp Altimeter in Ft

Aircraft Hours Left Engine Time, Since Overhaul

Right Engine, Time Since Overhaul

Low Pitch Torque Check L/H Engine Target Torque

R/H Engine Target Torque

L/H Engine Observed Torque

R/H Engine Observed Torque Torque Difference in Foot Pounds

TREND MONITORING CHECK

Engine Inlet Temp in Degrees C (O.A.T) + 4.5 = ° C Observed L/H Engine Observed R/H Engine

Torque (Target) 1315 Ft. Lbs. 1315 Ft. Lbs.

Prop Speed (N2) 2200 RPM 2200 RPM

Interstage Turbine Temperature (ITT)

Gas Generator Speed (N1)

Fuel Flow (WF)

Oil Pressure

Oil Temperature

L/H Engine

Target

Observed

Difference

Allowable Difference

N1 ± 1%

ITT + 15 / -75 ° C

WF (Fuel Flow) + 15 / -75 PPH

R/H Engine

Target

Difference

Allowable Difference

N1 ± 1%

ITT + 15 / -75 ° C

WF (Fuel Flow) + 15 / -75 PPH

Inspection Completed: Time: _____________Date: ___________ Name: ____________________ (Printed)

Signature: __________________________

POWER ASSURANCE RUN SIGN-OFF SIGNATURE AND INITIALS RECORD

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

T-44 Scheduled Removal Component Inventory To be verified during Phase 2 Inspection

Aircraft ___________________________________ Modex ______________________________

Nomenclature Serial Number Mechanic Initials L&R Clerk Initials

Retract Motor Retract Gearbox Flap Motor LH INBD Flap Actuator RH INBD Flap Actuator LH OTBD Flap Actuator RH OTBD Flap Actuator LH Engine LH Fuel Control Unit LH Fuel Pump LH Start Control LH Bleed Valve LH Starter Generator LH Overspeed Governor LH Primary Prop Governor RH Engine RH Fuel Control Unit RH Fuel Pump RH Start Control RH Bleed Valve RH Starter Generator RH Overspeed Governor RH Primary Prop Governor LH Prop RH Prop Scheduled Maintenance Mechanic: ________________________________ Date: _________

Scheduled Maintenance Crew Leader / CDI: ________________________ Date: _________

Logs and Records Clerk: _______________________________________ Date: _________

Aircraft Hours and Landings this Detail:

Hours: ________________ Landings: ______________

NAVAIR (PMA 273) 01-50-T44C-600-4.1

JANUARY 1, 2013

ATTACHMENT 84

PWS Encl 14 T44C SIRG 01-50-T44C-600-6-4.1 N00019-14-R-0018

TREND MONITORING CHECK