ATTACHMENT_83_-_PWS_Encl_14_NAVAIR_01-50-T44C-600-6-3.pdf

NAVAIR (PMA 273) 01-50-T44C-600-6-3

U . S . N A V Y T - 4 4 C

P E G A S U S

5 Year / 5000 Landings Flap and Gear

TBO

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

NAVAIR (PMA273) 01-50-T44C-600-3

January 1, 2013

P A G E E F F E C T I V I T Y L I S T I N G

NAVAIR (PMA 273) 01-50-T44C-600-6-3

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 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 22 NA 1/1/2013 Changes Not Bar Marked

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

INTERIM 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-T44A-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 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 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 Whiting Field

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.

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

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

T-44C CONTINUOUS INSPECTION REQUIREMENTS

5 YEAR/5000 HOUR FLAP AND GEAR TBO REQUIREMENTS

Inspection Date: _________________________ JCN: ____________________ BUNO: ________________________

Aircraft Time: _________________________ Landings: _________________ Engine Time L/H ______ R/H _____

A. SCREEN LOG BOOKS: Maintenance Control

1. Audit Time Change Component Records.

2. Audit Technical Directive Compliance.

3. If applicable, verify QA/FCF blocks are checked with red marker on all VIDS/MAF copies, FCF is annotated with red marker in the Maint/Supply record block of all VIDS/MAF copies, and the ADB has been red flagged for

B. CABIN AND COCKPIT SEATS: CORRECTED

BY

INSPECTED

BY

1. Remove, tag, and store.

2. Inspect and record discrepancies.

C. CABIN UPHOLSTERY AND CARPET: CORRECTED

BY

INSPECTED

BY

1. Remove as necessary, tag, and store.

2. Inspect and record discrepancies.

D. INTERIOR FLOOR PANELS: CORRECTED

BY

INSPECTED

1. Remove as necessary, tag and store.

2. Inspect and record discrepancies.

E. EXTERIOR PANELS:

CORRECTED

BY

INSPECTED

BY

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

1. Remove as necessary, tag and store.

2. Inspect and record discrepancies.

CAUTION

NEVER OPERATE THE FLAPS WITH THE RIGHT HAND INBOARD FLAP

REMOVED AS THE LIMIT SWITCHES WILL BE INOPERATIVE AND SERIOUS

DAMAGE TO THE FLAPS, WINGS, AND ACTUATING SYSTEM CAN RESULT

5 YEAR/5000 LANDINGS FLAP AND GEAR TBO REQUIREMENTS

WINGTIP AILERON OUTBD FLAP INBD FLAP INBD FLAP OUTBD FLAP AILERON WINGTIP

LH WING RH WING

F. FLAP RIGGING: CHECK PRIOR TO FLAP REMOVAL

CORRECTED

BY

INSPECTED

BY

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

1. In the above drawing, record the positions of the flaps, (in the up position), relative to the bottom of the fuselage, and the ailerons in the neutral position.

Record neutral aileron positions relative to the wingtips. Identify the relative position of side-by-side components as ABOVE or BELOW, and record the measured dimensions in inches and fractions of inches.

G. FLAP REMOVAL:

CORRECTED

BY

INSPECTED

BY

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

1. Fully extend the flaps and secure the FLAP-PWR-POSN circuit breakers

2. Remove the bolt, washers, and nut securing the flap actuator to the brackets on the leading edge of the flap. DO NOT DISTURB SHAFT SCREW

EXTENSION LENGTH.

CAUTION

NEVER OPERATE THE FLAPS WITH THE RIGHT HAND INBOARD FLAP REMOVED AS THE

LIMIT SWITCHES WILL BE INOPERATIVE AND SERIOUS DAMAGE TO THE FLAPS, WINGS,

AND ACTUATING SYSTEM CAN RESULT.

5 YEAR/5000 LANDINGS FLAP AND GEAR TBO REQUIREMENTS (CONT’D)

G. FLAP REMOVAL – continued

CORRECTED

BY

INSPECTED

BY

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

3. Remove flap aft roller bearing access panels from the top of all flaps, located at the inboard and outboard side of each flap’s aft roller bearing mount point at the tracks.

4. Disconnect flap bonding cables at all four (4) flaps bracket attach points.

5. Remove the bolts, washers, and nuts connecting the aft flap mount points and roller bearings to the flap track. Secure all hardware.

6. While providing support for the flap, remove the bolts, washers, and nuts securing the flap and forward roller bearing(s) at the flap track forward attach point, then remove the flap from the wing. Secure all hardware. Mechanic: initial for flap removed.

LEFT O/B: __________________LEFT I/B: ___________________

RIGHT O/B: __________________RIGHT I/B: ___________________

7. Tag and store removed flaps.

8. Remove the forward and aft roller bearings from the wing flap tracks and discard.

9. Ensure all removed parts are properly tagged and/or identified.

10. Clean all flap wells and flap tracks as required to facilitate maintenance inspection.

H. FLAPS AND SYSTEM STRUCTURE INSPECTION:

CORRECTED

BY

INSPECTED

BY

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

1. Inspect all flap assemblies for loose or missing rivets and fasteners, cracks, corrosion and excessively worn fittings.

2. Inspect and measure flap tracks. The allowable track wear on the upper and lower bearing surfaces is 0.032 inch, resulting in a maximum flap track slot dimension of

0.785 inch. The maximum wear into the track side surface (wall) is 0.050 inch.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

5 YEAR/5000 HOUR FLAP AND GEAR TBO REQUIREMENTS

FLAP TRACK MEASUREMENTS

LEFT OUTBOARD FLAP LEFT INBOARD FLAP

O/B Track I/B Track O/B Track I/B Track

L/H FWD L/H FWD L/H PME S/N

L/H AFT L/H AFT L/H PME Cal.

Due:

RIGHT OUTBOARD FLAP RIGHT INBOARD FLAP

O/B Track I/B Track O/B Track I/B Track

R/H FWD R/H

FWD

R/H PME S/N

R/H AFT R/H AFT R/H PME Cal.

Due:

NOTE

Track wear within the above limitations may be dressed smooth with light emery cloth to prevent roller blinding. To help reduce wear, it is recommended that the tracks and rollers be kept clean and lubricated.

Refer to the T-44 MIM, Chapter 12 for lubrication requirements. The

Teflon chafing washers should also be kept in good condition.

5 YEAR / 5000 LANDINGS FLAP AND GEAR TBO REQUIREMENTS

I. FLAP ACTUATOR AND CABLE REMOVAL:

INSPECTED

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

1. Remove L/H O/B Flap Actuator and Tag. S/N _______________________.

2. Remove L/H I/B Flap Actuator and Tag. S/N ________________________

3. Remove R/H I/B Flap Actuator and Tag. S/N ________________________

4. Remove R/H O/B Flap Actuator and Tag. S/N _______________________

5. Remove L/H O/B Flap Drive Cable and clamps.

6. Remove L/H I/B Flap Drive Cable and clamps.

7. Remove R/H O/B Flap Drive Cable and clamps.

8. Remove R/H I/B Flap Drive Cable and clamps.

9. Remove all drive cable pressure seals.

10. Clean all Flap Actuator Mount Areas to facilitate inspection.

11. Inspect Flap Actuator Mount Areas, and annotate any discrepancies identified on the Inspection Discrepancy Record Work sheet for further action.

12. Treat any corrosion noted, and paint as necessary.

J. FLAP MOTOR AND GEARBOX REMOVAL: CORRECTED

1. Remove Flap Motor and Tag. – S/N _________________________

2. Remove Flap Gear Box and Tag. – S/N ________________________

3. Clean area of Flap Motor and Gear Box.

4. Inspect Flap Motor and Gear Box Mount Areas, and annotate any discrepancies identified on the Inspection Discrepancy Record Work sheet for further action.

5. Treat any corrosion noted, and paint as necessary.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

CAUTION

TO PREVENT FLAP TRACK DAMAGE, INSTALL FLAP ROLLER BEARINGS SO

THAT THE FLANGES ARE FACING EACH OTHER (SMALL FLANGE IN FORWARD

TRACK RUNNER, AND LARGE FLANGE WITH A NYLON WASHER BETWEEN THE

FLANGE AND THE TRACK IN THE AFT TRACK RUNNER).

K. FLAP MOTOR AND GEAR BOX INSTALLATION:

BY

1. Install Flap Motor on Flap Gear Box. Flap Motor S/N _________________

2. Install Flap Gear Box. Gear Box S/N _________________

L. FLAP ACTUATOR AND DRIVE CABLE INSTALLATION:

CORRECTED

BY

INSPECTED

BY

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

1. Install L/H O/B Flap Actuator S/N ________________________

2. Install L/H I/B Flap Actuator S/N ________________________

3. Install R/H O/B Flap Actuator S/N ________________________

4. Install R/H I/B Flap Actuator S/N ________________________

5. Install L/H O/B Flap Drive Cable and clamps. S/N ________________________

6. Install L/H I/B Flap Drive Cable and clamps. S/N ________________________

7. Install R/H O/B Flap Drive Cable and clamps S/N ________________________

8. Install R/H I/B Flap Drive Cable and clamps S/N ________________________

9. Inspect all flap drive cables for security and proper routing.

M. FLAP LIMIT SWITCHES:

CORRECTED

BY

1. Inspect Flap Limit Switches and Cams for condition and annotate any discrepancies identified on the Inspection Discrepancy Record Work sheet for further action.

2. Treat any corrosion noted and paint area as required.

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

N. FLAP INSTALLATION: CORRECTED

1. Connect the ends of the bonding jumpers to the flap brackets and secure.

2. For each specific flap roller bearing installation, position the small flange roller bearing, (qty 2) in the forward runner of the flap track assemblies, and the wide flange roller bearing, with nylon washers (qty 2) in the aft runner of the flap track assembly.

LEFT Inboard _____________________ (correcting mechs initials)

LEFT Outboard _____________________ (correcting mechs initials)

RIGHT Inboard _____________________ (correcting mechs initials)

RIGHT Outboard _____________________ (correcting mechs initials)

3. For each specific flap installation, while providing support for the flap, align the flap assembly mount points with the rollers pre-installed in the tracks and install attaching hardware (bolts, washers, and nuts), securing the flap into its mounted position.

LEFT Inboard _____________________ (correcting mechs initials)

LEFT Outboard _____________________ (correcting mechs initials)

RIGHT Inboard _____________________ (correcting mechs initials)

RIGHT Outboard _____________________ (correcting mechs initials)

4. Raise and lower each flap by hand to assure freedom of movement without binding.

5. Connect the ends of the bonding jumpers to the flap wells and secure.

CAUTION

ENSURE THAT SUFFICIENT SPACE IS AVAILABLE TO OPERATE FLAP SYSTEM THROUGH ITS

COMPLETE TRAVEL RANGE WITHOUT OBSTRUCTION FROM OTHER AIRCRAFT AND/OR

SUPPORT EQUIPMENT.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

O. FLAP CONTROL SYSTEM RIGGING:

BY

1. For each specific flap installation, align the end of the actuator screw with the mount hole in the actuator-to-flap attach bracket and install bolt, washers, and nut securing the end of the actuator in place.

LEFT Outboard ___________________ (correcting mechs initials)

LEFT Inboard __________________ (correcting mechs initials)

RIGHT Inboard ___________________ (correcting mechs initials)

RIGHT Outboard _________________ __ (correcting mechs initials)

2. Remove the access plate on the R/H inboard wing trailing edge, accessing the Flap Limit Switch Adjustment Cams. NOTE - Steps 3. and 4. concern the RH I/B flap.

3. Adjust the DOWN limit cam to actuate its switch (an audible click should be heard) just prior to the flap reaching its full down travel limit.

4. Adjust the UP limit cam to actuate its switch (an audible click should be heard) just prior to the flap reaching its full upper travel limit.

5. Synchronize the other three flaps. Fine adjustments can be made at the flap gearbox drive to each flex drive as needed to obtain exact screw length measurements. Secure drive cables at gearbox as required.

6. With APU Power (28V DC), cycle the flap system and assure that the flaps do not bottom out in either the up or down position. Adjust and secure as necessary.

7. Using a protractor on the right inboard flap, measure the position (in degrees) of the flap in the UP LIMIT position.

8. Using the protractor, measure the total flap travel (in degrees) from the full UP to full DOWN position. Flap surface travel from UP to DOWN should be 41 to 44 degrees.

Adjust as necessary to obtain required travels, and secure.

The left and right inboard flaps must fair flush with the bottom of the fuselage with the flaps up. The outboard flaps may vary from ½ inch above, to ¼ inch below, the inboard flaps at the trailing edges. When the ailerons are properly rigged and in the neutral position, the outboard flaps may be up to ½ inch below the

O. FLAP CONTROL SYSTEM RIGGING – continued

BY

9. Adjust the flap Approach Cams for the following travels:

A) From flaps full UP to APPROACH (lowering) – 15 +/- 1 (14 -16) degrees.

B) From flaps full DOWN to APPROACH (raising) – 16 +1 -0 (16 -17) degrees.

Travel – full UP to APPROACH (degrees travel) _________________________

Travel – full DOWN to APPROACH (degrees travel) _____________________

PME S/N: ______________________ PME Cal. Due: ____________________

10. Cycle the flaps to verify that all settings are correct and that all flaps do not bottom out in either full UP or full DOWN positions. Ensure flap position indicator corresponds to actual flap position. Adjust as necessary, confirm, and secure.

11. Confirm all system components disconnected for rigging adjustment have been reconnected, secured and safetied as required.

12. Install flap drive cable pressure seals (cabin interior) with appropriate sealant.

Safety all flap drive cables at gear box.

CDI CALL POINT: Verify compliance with Steps B1 – O12

QAR CALL POINT: Verify compliance with Steps K1 – O12

Inspect installation of flaps, actuators, flex drives, flap motor/gearbox, limit switches, and pressure vessel seals and sealant. Check operation, rigging, and surface travel indications of flap control system.

END - Flap Inspection

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

P. NOSE LANDING GEAR REMOVAL and INSPECTION: CORRECTED

1. Secure area and jack aircraft IAW Chapter 7-00-00, T-44 H-90 M/M.

2. Deflate, tag, and remove wheel/tire assembly. Inspect wheel and tire for wear and condition.

3. Break gear slightly over center and inspect nose landing gear doors and linkage for condition. Disconnect doors.

4. Inspect nose gear steering linkage for condition.

5. Remove drag leg assembly and steering linkage and detach the electrical harness and lights from nose gear assembly.

WARNING

FULLY RELEASE NITROGEN PRESSURE IN NOSE STRUT BEFORE REMOVING

THE STRUT VALVE ADAPTER

6. Remove nose gear strut. Remove gear door rollers from strut assembly. De-service strut of nitrogen and hydraulic fluid. Secure all hardware.

Nose Strut S/N: ___________________________

7. Verify/record removed NLG upper and lower torque knee serial numbers:

UPPER Torque Knee S/N: ______________________

LOWER Torque Knee S/N: ______________________

8. Clean and inspect NLG trunnion mount bolt holes for condition and excessive wear.

Normal Service Dimensions – 0.500 +0.001/-0.0005 Maximum Service Dimension – 0.5140

Dimensions: LEFT Keel: _______________ RIGHT Keel: _______________

PME S/N: ____________________ PME Cal. Due: _____________________

9. Inspect upper drag leg hinge pin mount holes for condition.

10. Remove forward nose gear chain and sprockets. Inspect for condition and lubrication.

11. Remove nose landing gear actuator. Actuator S/N: ______________________

12. Clean and inspect actuator support brackets and actuator drive for visible damage and condition.

13. Perform NDI on nose actuator mount brackets.

Left bracket: ___________ Right bracket: ____________

NDI Kit ________ UV Meter ______________ Cal Date __________

Q. NOSE LANDING GEAR INSTALLATION:

BY

1. Install new bearings in actuator support brackets.

2. Install NLG actuator in support bracket. Actuator S/N: ___________________

3. Install forward nose gear chain and sprockets and adjust to proper tension

IAW T-44 H-90 M/M 32-30-00.

PME S/N: ________ PME Cal. Due: __________ Actual Tension________

4. Install new down lock switch on drag leg and safety.

5. Install drag leg in upper frame in wheel well.

6. Verify upper and lower torque knee serial numbers on new NLG strut assembly.

UPPER Torque Knee S/N: _____________________

LOWER Torque Knee S/N: _____________________

7. Service nose strut to proper fluid level IAW MED 32-10-00/PR-123.

8. Position the strut in the wheel well; install the trunnion bolts, lubricate and secure.

Torque IAW T-44 H-90 M/M 32-20-00. (360 to 720. in. lbs.)

Insure free movement of NLG assembly without rotation of trunnion bolts.

STRUT S/N: _______________________

Actual Torque: L/H __________________ R/H _____________________

PME S/N: _____________________ PME Cal. Due: ____________________

9. Attach lower drag brace arm to strut fittings. Torque and secure thru bolt IAW T-44 H-90 M/M 32-20-00. (200 to 400 lbs. in.)

Actual Torque: __________________

10. Install and secure gear door rollers.

11. Attach and secure steering linkage and taxi and landing lights to strut. Secure electrical harness.

12. Perform nose gear actuator alignment check IAW T-44 H-90 M/M 32-20-00.

13. Install nose gear wheel and tire assembly IAW MED-40-00/PR-106.

Actual Torque: __________________

Q. NOSE LANDING GEAR INSTALLATION - continued CORRECTED

INSPECTED

BY

14. Service nose tire for proper inflation IAW T-44 H-90 M/M 32-40-00. (50-55psi) Actual PSI: _____________

PME S/N: ______________ PME Cal. Due: ______________

15. Service nose strut with nitrogen IAW MED 32-10-00/PR-123.

Actual PSI: _____________

PME S/N: ______________ PME Cal. Due: _______________

CDI CALL POINT: Verify compliance with Steps P1 – Q15

R. MAIN LANDING GEAR REMOVAL

CORRECTED

BY

INSPECTED

BY

LH RH LH RH

1. Remove brake assemblies. Inspect for condition and wear.

Lining maximum wear limit: .100 disc maximum wear limit: .410

Pressure Plate Lining:_______ Back Plate Lining:________ Disc:_______

2. Remove main landing gear wheel assy. Inspect wheel and tire for wear and condition

3. Inspect main landing gear doors and linkage for condition. Disconnect doors.

LEFT O/B S/N ________ RIGHT O/B S/N ________

LEFT I/B S/N- _________ RIGHT I/B S/N ________

4. Remove drag brace assemblies.

5. Inspect upper drag arm hinge bolt holes for condition and wear.

6. Disconnect main gear wheel well curtains.

WARNING

RELEASE NITROGEN PRESSURE IN STRUT ASSEMBLIES BEFORE REMOVING STRUT VALVE

ADAPTERS

R. MAIN LANDING GEAR REMOVAL - continued CORRECTED

BY

INSPECTED

LH RH LH RH

7. Remove Left and Right MLG strut assemblies. De-service strut of nitrogen and hydraulic fluid.

L/H S/N:____________________ R/H S/N:_____________________

8. Verify upper and lower Torque Knee serial numbers on removed MLG struts.

L/H Upper S/N:_____________ R/H Upper S/N:______________

L/H Lower S/N:_____________ R/H Lower S/N:______________

9. Clean and Inspect MLG trunnion mount bolt holes for condition and excessive wear.

Normal Service Dimensions – 0.750 +0.001/-0.0005 Maximum Service Dimension – 0.7610

Dimensions: Left I/B Keel: ____________ Left O/B Keel: ____________

Dimensions: Right I/B Keel: ___________ Right O/B Keel: ___________

PME S/N: __________________________ PME Cal. Due: ____________

10. Remove main landing gear actuator stiffener plates.

11. Remove Left and Right main landing gear actuators.

L/H S/N:______________ R/H S/N:______________

12. Clean and inspect actuator support brackets for visible damage and condition.

13. Perform NDI on actuator mount brackets.

Left I/B bracket: ____________ Left O/B bracket: ____________

Right I/B bracket: ___________ Right O/B bracket: ___________

CDI CALL POINT: Verify compliance with Steps R1 – R13.

S. MAIN LANDING GEAR INSTALLATION

BY

INSPECTED

BY

LH RH LH RH

1. Verify upper and lower torque knee serial numbers on new MLG struts.

L/H Upper S/N:_____________ R/H Upper S/N:_____________

L/H Lower S/N:_____________ R/H Lower S/N:_____________

2. Install new bearings in actuator support brackets.

3. Install MLG actuators in the respective support brackets.

L/H S/N: _____________ R/H S/N: ____________

4. Install MLG actuator stiffener plates.

5. Service MLG struts to proper fluid levels IAW MED 32-10-00/PR-123.

6. Position Left and Right MLG assemblies in the wheel well mount points, install upper hinge mount attaching hardware, and grease mount points.

L/H S/N:____________ R/H S/N:____________

7. Torque the strut installation mount hardware IAW T-44 H-90 M/M 32-10-00 (600 - 1020 in. lbs.) as required to align nut castellation and cotter key hole. Insure MLG strut installation moves freely without rotation of trunnion bolts.

Torque: L/H Inboard:________________ R/H Inboard: _________________

Torque: L/H Outboard:______________ R/H Outboard: _________________

PME S/N: __________________ PME Cal. Due: _________________

8. Install new down lock switch on left and right drag leg, and safety.

9. Install left and right drag leg assembly.

10. Perform MLG actuator alignment IAW T-44 H-90 M/M 32-10-00.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

S. MAIN LANDING GEAR INSTALLATION-continued

INSPECTED

BY

LH RH LH RH

11. Install wheel torque plate and torque mount bolts IAW Cleveland Wheel & Brake Installation Manual. (130-150 in. lbs.)

Actual Torque: L/H ___________ Actual Torque: R/H ____________

PME S/N: _______________ PME Cal. Due: ________________

12. Install MLG wheel and tire assembly IAW MED-40-00/PR-106.

Actual Torque: L/H __________ Actual Torque: R/H _____________

PME S/N: _______________ PME Cal. Due: _________________

13. Install brake assembly IAW Cleveland Wheel & Brake Installation Manual.

(85-90 in. lbs.)

Actual Torque: L/H ___________ Actual Torque: R/H ______________

PME S/N: ______________ PME Cal. Due: __________________

14. Service MLG tire assembly IAW T-44 H-90 M/M 32-40-00. (54-60psi) L/H Actual PSI: _________ R/H Actual PSI: _________

15. Service MLG strut with nitrogen IAW MED 32-10-00/PR-123.

L/H Actual PSI: _________ R/H Actual PSI: ____________

PME S/N: ______________ PME Cal. Due: _________________

CDI CALL POINT: Verify compliance with Steps S1 – S15.

T. LANDING GEAR RETRACT MECHANISM REMOVAL CORRECTED

BY

INSPECTED

BY

1. Disconnect aircraft battery, hot buss and strobe pack.

2. Remove Left and Right main landing gear torque tubes.

3. Perform NDI on MLG torque tubes.

L/H Torque Tubes: _________ R/H Torque Tubes: _________

T. LANDING GEAR RETRACT MECHANISM REMOVAL-continued CORRECTED

INSPECTED

BY

4. Remove Landing Gear Motor. S/N: ______________

5. Remove Landing Gear Retract gearbox. S/N: ______________

6. Clean and inspect retract gearbox and torque shaft area for visible damage and condition.

7. Inspect emergency extension mechanism for visible damage and condition.

8. Remove 50 amp landing gear circuit breaker.

9. Remove landing gear motor relay.

10. Remove landing gear UP and DOWN travel limit switches.

CDI CALL POINT: Verify compliance with Steps T1 – T10.

U. LANDING GEAR RETRACT MECHANISM INSTALLATION: CORRECTED

BY

1. Install landing gear retract gearbox and motor.

GEARBOX S/N: ______________ MOTOR S/N: ______________

2. Perform landing gear retract gearbox alignment.

3. Install 50 Amp landing gear circuit breaker, located at cabin control pedestal Circuit Breaker panel.

4. Install landing gear motor relay.

5. Install landing gear retract UP and DOWN limit switches.

CAUTION

INSPECT THE NOSE GEAR FORWARD AND AFT CHAINS FOR ALIGNMENT ON THE DRIVE

SPROCKETS. CHAIN SIDEBARS RIDING HARD ON THE SIDE OF THE SPROCKETS WOULD

INDICATE IMPROPER INSTALLATION OF ONE OF THE SPROCKETS.

U. LANDING GEAR RETRACT MECHANISM INSTALLATION: continued

BY

INSPECTED

BY

LH RH LH RH

6. Inspect aft nose gear chain and sprockets for condition and lubrication. Inspect chain for proper tension IAW T-44H-90 M/M 32-30-00.

7. Inspect emergency extension drive chain for proper engagement and chain tension.

Adjust as needed IAW H-90 M/M 32-30-00.

8. Inspect Left and Right main landing gear torque tubes for straightness and install.

CDI CALL POINT: Verify compliance with Steps U1 – U8.

CAUTION

EXCESSIVE OPERATION OF THE LANDING GEAR MOTOR WITHOUT

PROPER COOLING MAY CAUSE DAMAGE TO THE MOTOR

V. NOSE LANDING GEAR RIGGING:

BY

1. With the nose gear disconnected at the actuator clevis, extend the main gear to the full DOWN position.

2. Move the nose gear to the full down and locked position by hand.

3. Extend the actuator screw out until the holes in the actuator clevis and the drag leg yoke are matched alongside each other, then extend the clevis OUT one half additional turn.

4. Retract the gear slightly and attach the actuator clevis to the yoke and secure.

5. Carefully extend the gear. The nose gear clevis spring must compress at least 0.060 inch, with a maximum compression of 0.250 inch from the non-compressed position.

6. Retract the gear carefully. The nose actuator travel should not bottom out.

7. Run the gear through the UP and DOWN cycles without stopping in an intermediate position. Check spring compression and UP stop tolerances.

8. CDI CALL POINT: Verify compliance with Steps V1 – V7.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

W. MAIN LANDING GEAR RIGGING:

BY

INSPECTED

BY

LH RH LH RH

1. With the affected MLG gear disconnected at the outboard pillar block universal joint, extend the other two gear to the full DOWN position.

CAUTION

GUIDE THE DISCONNECTED ACTUATOR BY HAND WHILE THE GEAR IS

BEING EXTENDED TO PREVENT STRUCTURE DAMAGE

2. Move the affected gear to the full down and locked position by hand.

3. Extend the actuator screw out until the holes in the actuator clevis and the bottom of the actuator attach point in the drag leg are aligned, and then turn the actuator shaft OUT one half additional turn.

4. Retract the gear slightly, then lubricate, install and secure the clevis bolt.

5. Carefully extend the gear. The main gear clevis spring must compress to a total length of 0.780 inch or less, while maintaining 0.020 inch clearance between the active coils of the spring.

6. Run the gear through the UP and DOWN cycles without stopping in an intermediate position. Check spring compression and UP stop clearances.

7. Ensure proper installation of Left and Right torque tube attaching hardware. (nuts, bolts, cotter-keys, etc.)

CAUTION

DO NOT CONTINUE EMERGENCY EXTENSION OPERATION AFTER ALLTHREE (3) GEAR

DOWN INDICATORS ARE LIT. FURTHER MOVEMENT OF THE EMERGENCY EXTENSION

HANDLE COULD DAMAGE THE DRIVE MECHANISM AND PREVENT SUBSEQUENT

ELECTRICAL GEAR RETRACTION. THE GEAR CANNOT BE RETRACTED MANUALLY.

8. Perform LDG Emergency Extension and confirm proper operation and rigging.

9. Ensure emergency extension cable is properly routed on all three pulleys.

10. Re-connect nose and main landing gear doors.

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

W. MAIN LANDING GEAR RIGGING: continued

BY

INSPECTED

BY

LH RH LH RH

11. Inspect all doors for operation, fit, fair and rigging.

12. Inspect the LDG Warning System for proper operation with the gear and flap systems in the following configuration:

A – Gear UP, Flaps UP B – Gear UP, Flaps APPROACH C – Gear UP, Flaps DOWN D – Gear DOWN, Flaps DOWN

CDI CALL POINT: Verify compliance with Steps W1 – W12.

QAR CALL POINT:

Verify compliance with Steps Q1 – Q15 Verify compliance with Steps S1 – S15

Verify compliance with Steps U1 – W12

Inspect Left and Right MLG and NLG and attaching hardware for proper installation. Inspect actuators and torque tubes for proper installation. Inspect NLG chains, retract motor/gearbox, relay, and limit switches for proper installation.

Verify operation of LDG retraction and warning system for proper rigging.

X. HYDRAULIC BRAKE SYSTEM:

BY

INSPECTED

BY

LH RH LH RH

1. Install new brake flex hose on Left and Right struts.

2. Service and bleed brake system.

Y. AIRCRAFT RECONFIGURATION:

CORRECTED

BY

INSPECTED

BY

LH RH

1. Ensure that all accessible areas opened for inspection are FOD free prior to installation of access panels and reinstall panels.

2. Secure strobe pack and hot buss panel. Ensure battery is connected and secure access panel.

3. Secure wheel well curtains.

4. Secure seats and all panels including flap patch plates.

5. Prior to lowering aircraft ensure the landing gear is in the down and locked position and lower aircraft IAW H-90 M/M 7-00-00.

T-44C 5 YEAR/5000 LANDINGS FLAP AND GEAR TBO CONTINUOUS

INSPECTION DISCREPANCY RECORD WORK SHEET

USE ADDITIONAL SHEETS AS REQUIRED

ITEM STATUS DISCREPANCY CORRECTIVE ACTION

MECH

CDI QA M/H

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

12.

13.

14.

15.

T-44A/C CONTINUOUS INSPECTION REQUIREMENTS

SIGN-OFF SHEET

All Employees performing tasks on this inspection must enter their employee information prior to starting work.

Identification Section

Close Out Section

EMPLOYEE

NUMBER

EMPLOYEE NAME

(Print) EMPLOYEE SIGNATURE EMPLOYEE

INITIALS

DATE CORRECTED BY

(Signature)

SUPERVISOR’S

SIGNATURE

QAR/CDI

STAMP

5 Year/5000 Landing Inspection Complete

Logs/Records Entry Complete

ATTACHMENT 83

PWS Encl 14 NAVAIR 01-50-T44C-600-6-3 N00019-14-R-0018

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