ATT 77 01-50-T34C-600-6-4.2.pdf

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2

U.S. NAVY T-34C

TURBO MENTOR

2ND DETAILED

INSPECTION

Revised: March 1, 2005

Attachment 77

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2 N61340-18-FOSR-0001

i Revised: March 1, 2005

PAGE EFFECTIVITY LISTING

Summary:

• The original issue of the NAVAIR (PMA 207) 01-50-T34C-600-6-4.1, which is now a PMA 273 document, occurred in February of 2000.

• The date of this change, which is a complete reissue, is March 1, 2005.

Page(s) Change Number Date Comments Cover NA 3/1/2005 Changes Not Bar Marked i NA 3/1/2005 Changes Not Bar Marked ii NA 3/1/2005 Changes Not Bar Marked iii NA 3/1/2005 Changes Not Bar Marked iv NA 3/1/2005 Changes Not Bar Marked 1 NA 3/1/2005 Changes Not Bar Marked 2 NA 3/1/2005 Changes Not Bar Marked 3 NA 3/1/2005 Changes Not Bar Marked 4 NA 3/1/2005 Changes Not Bar Marked 5 NA 3/1/2005 Changes Not Bar Marked 6 NA 3/1/2005 Changes Not Bar Marked 7 NA 3/1/2005 Changes Not Bar Marked 8 NA 3/1/2005 Changes Not Bar Marked 9 NA 3/1/2005 Changes Not Bar Marked 10 NA 3/1/2005 Changes Not Bar Marked 11 NA 3/1/2005 Changes Not Bar Marked 12 NA 3/1/2005 Changes Not Bar Marked 13 NA 3/1/2005 Changes Not Bar Marked 14 NA 3/1/2005 Changes Not Bar Marked 15 NA 3/1/2005 Changes Not Bar Marked 16 NA 3/1/2005 Changes Not Bar Marked 17 NA 3/1/2005 Changes Not Bar Marked 18 NA 3/1/2005 Changes Not Bar Marked 19 NA 3/1/2005 Changes Not Bar Marked 20 NA 3/1/2005 Changes Not Bar Marked ii Revised: March 1, 2005

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-T34C-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.

iii Revised: March 1, 2005

TECHNICAL INFORMATION REPORT, DISCREPANCY (TIRD)

CHANGE RECOMMENDATION

(TO BE FILLED IN BY ORIGINATOR)

REPORT DATE:

FROM (Originator): ACTIVITY:

ADDRESS AND/OR E-MAIL OF ORIGINATOR:

ATTENTION:(PMA-273): JIM BALL (T-34C) OR SCOTT PINSON (T-44A)

SEND COMPLETED FORM TO:

NAVAIRSYSCOM

ATTENTION: PMA273, 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):

IMPACT:

REPORTED 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.

Check if continuation sheets or drawings attached.

iv Revised: March 1, 2005

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., L-3, 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.

Page 1 Revised: March 1, 2005

SECOND 100-HOUR INTERVAL DETAILED INSPECTION

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

• Second 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 T-34C Maintenance Manual, Part Number 92-37867

• BEECHCRAFT Model T-34C Wiring Diagram Manual, Part Number 92-37868

• Pratt & Whitney PT6A-25 Engine Maintenance Manual, Part Number 3027542

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

• NAVAIR 01-T34AAC-1, NATOPS Manual

• Maintenance Engineering Directives

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 completed immediately prior to induction of the aircraft into the Detail 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 by the appropriate person 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-34C Maintenance Manual.

NO JOB IS SO IMPORTANT AND NO SERVICE IS SO URGENT THAT WE

CAN’T TAKE TIME TO PERFORM OUR WORK SAFELY.

T-34C CONTINUOUS INSPECTION REQUIREMENTS

SECOND 100 HOUR INTERVAL DETAILED INSPECTON

Page 2 Revised: March 1, 2005

Inspection Date:

JCN: BUNO:

Aircraft Time:

Landings: Engine Time:

A. ENGINE WASH AND POWER ASSURANCE RUN

COMPLETED

BY

INSPECTED

BY

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

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

3. Apply engine wash solution to the air conditioning condenser.

4. 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.

5. Thoroughly rinse the air conditioning condenser with fresh water.

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

COMPLETED BY

B. COCKPIT GROUP FRONT REAR INSP

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

2. ACCESS DOORS and PANELS – Check condition, fit and attachment.

3. STRUCTURE – Check for cracks, loose rivets, corrosion and damage.

4. CANOPY – Inspect canopy, seals and sealing blocks for general condition.

4.1 Check canopy tracks and latches for condition, security and operation; clean tracks as necessary. Ensure canopy will lock open. Ensure the overhead release functions properly. Ensure that canopy security locking hole has been incorporated in the track in case a track has been changed.

4.2 Check that the canopy drain holes incorporated by MED ATA 52-00-00/PR-77 are open and free of any obstructions.

4.3 Inspect mirror assemblies for condition and security.

5. WINDSCREEN – Check condition and sealing.

5.1 Check OAT gage for condition and security.

6. SEATS AND BELTS – Inspect both seats for condition. Check condition of seat cushions. Ensure anti-chafe material is properly installed on seat back. Check restraints for proper operation and condition.

7. RELIEF TUBE SYSTEM – Check plumbing, brackets and grommets for condition and security. Inspect relief tube bracket for proper engagement of horn in the bracket and routing of the hoses.

INSPECTION CALL POINT – Verify compliance with Section B, Steps 1 through 7.

Page 3 Revised: March 1, 2005

B. COCKPIT GROUP (Continued) FRONT REAR INSP

8. CABLES and PULLEYS – Check all visible and immediately accessible control cables, pulleys, bell cranks, push-rods and associated equipment for condition, attachment, alignment, clearance and proper operation.

9. CONTROL STICKS – Check for condition, attachment, clearance and operation.

9.1 Visually inspect the control stick attach points of the gimble for suspected cracks and/or corrosion in accordance with the current issue of MED ATA 27- 10-40/PR-72. Inspect the base for evidence of corrosion.

9.2 Check front cockpit stick pawl for condition, security and adjustment.

9.3 Check flight control locks for condition, positive locking and alignment.

9.4 Apply a light coat of general-purpose lubricant to both front and rear cockpit control stick rod-ends (4 points).

10. RUDDER PEDALS – Check condition, clearance, attachment and position adjustment.

10.1 Inspect rudder interconnect rod assembly for condition and clearance.

INSPECTION CALL POINT – Verify compliance with Section B, Steps 8 through 10.1.

11. BRAKE SYSTEM – Check brake system components for leakage.

11.1 Check brake reservoir for proper servicing and ensure the filler cap is safety wired upon completion.

11.2 Inspect brake master cylinders for operation. Inspect brake line plumbing for condition and attachment. Check brake pedals for condition, operation and adjustment

11.3 Using a bright light and mirror visually inspect the brake cylinders at the attaching link point for cracks and excessive wear.

11.4 Check parking brake operation.

INSPECTION CALL POINT – Verify compliance with Section B, Steps 11 through 11.4.

12. ENGINE AND PROPELLER CONTROLS – Check operation, friction lock and linkage for condition and interference. Ensure engine and propeller control cable housings are secure and safety wired.

12.1 Check operation of micro switches actuated by linkage. Clean and carefully lubricate the mechanical portions of the switch actuator using MIL-C-81309, Type 2, Class 2 Water Displacing Thin Film.

INSPECTION CALL POINT – Verify compliance with Section B, Steps 12 and 12.1.

13. Remove the front cockpit parachute.

13.1 Remove the front cockpit seat.

13.2 Remove the front cockpit floor panel.

Page 4 Revised: March 1, 2005

B. COCKPIT GROUP (Continued) FRONT REAR INSP

14. EMERGENCY CANOPY RELEASE – Check nitrogen bottle and controls for condition and security.

14.1 Actuate system IAW T-34C Maintenance Manual “Canopy Emergency Test Procedure”.

CAUTION

Ensure all lines, caps, fittings, etc., that are loosened/disconnected to facilitate completion of the “Canopy Emergency Release Test Procedure” have been secured prior to system servicing.

14.2 Service canopy emergency release bottle IAW T-34C Maintenance Manual.

CAUTION

Ensure safety device is removed from valve/bottle assembly after servicing.

INSPECTION CALL POINT – Verify compliance with Section B, Steps 13 through 14.2.

C. AVIONICS FRONT REAR INSP

1. GLARESHIELDS – Remove both glareshields.

1.1 Inspect firewall ground point for condition and security. Check for discoloration, corrosion, loose connections and evidence of arcing.

1.2 Inspect contactor relays, current limiters and relays behind F/C instrument panel for evidence of corrosion and loose connections.

1.3 DC Electrical System – Perform primary buss blocking diode functional check as specified in Chapter 24 of the T-34C Maintenance Manual.

1.4 Inspect relays and wiring behind R/C instrument panel for evidence of corrosion and loose connections.

INSPECTION CALL POINT – Verify compliance with Section C, Steps 1 through 1.4.

2. INSTRUMENT PANELS AND INSTRUMENTS – Inspect instrument panels, sub-panels, annunciator panels, instruments, placards, associated plumbing and wiring for condition, attachment, chafing, security, etc.

3. ENVIRONMENTAL DUCTS – Check condition and security of ducts. Check operation of manual control valves.

4. ENVIRONMENTAL PLUMBING – Check all lines and hoses for condition and security.

INSPECTION CALL POINT – Verify compliance with Section C, Steps 2 through 4.

5 GLARESHIELDS – Install both glareshields.

6. DC ELECTRICAL SYSTEM RELAY CHECK – Perform Starter/Generator D-terminal relay functional check as specified in Chapter 24 of the T-34C Maintenance Manual.

Page 5 Revised: March 1, 2005

C. AVIONICS (Continued) FRONT REAR INSP

7. INVERTERS – Check operation of No. 1 and No. 2 inverter system using test procedure in Chapter 24 of T-34C Maintenance Manual.

8. ICS – Check ICS cords for security, condition and operation.

9. SWITCHES/CONTROLS – Check switches, knobs, and circuit breakers for proper operation and security.

10. INTERIOR LIGHTING – Check operation of all cockpit lights.

11. EXTERIOR LIGHTING – Check operation of all exterior lights.

12. ELT BATTERY – Check battery on emergency locator transmitter.

13. NACWS DYNAMIC SYSTEM TEST – Check operation of NACWS using the test procedures specified in the NAVAIR NACWS 991 Maintenance Manual.

INSPECTION CALL POINT – Verify compliance with Section C, Steps 6 through 13.

14. PITOT/STATIC SYSTEM – Open drain valves to remove any accumulated moisture. Ensure caps are reinstalled. Check security and attachment.

14.1 Check static port assemblies and associated plumbing for condition and

14.2 Check emergency static source tube for obstructions.

INSPECTION CALL POINT – Verify compliance with Section C, Steps 14 through 14.2.

15. AOA SYSTEM – Check aural stall warning and rudder shakers for proper

15.1 Inspect vane for condition and operation and mast for condition.

16. ACCELEROMETER READINGS: 1 2

3 4

INSPECTION CALL POINT – Verify compliance with Section C, Steps 15 and 16.

D. FLAPS LEFT RIGHT INSP

Ensure that aircraft is parked on a firm level surface prior to jacking. Failure to position aircraft on a firm level surface can result in the aircraft falling from the jack and cause damage to the aircraft and/or injure personnel.

NOTE

Before proceeding to the next step, jack aircraft using a T-34C jacking stand.

1. FLAP MOTOR – Inspect for condition, attachment and operation.

2. FLEX DRIVES - Inspect flap drive flex shafts and actuators for condition and attachment.

3. STRUCTURE - Check skins and structure for condition. Check for loose or missing rivets.

Page 6 Revised: March 1, 2005

D. FLAPS (Continued) LEFT RIGHT INSP

4. TRACKS - Check condition of tracks and rollers. Inspect flap track support structure for loose rivets and cracks.

5. ELECTRICAL - Check position transmitter, limit switches, associated linkage and wiring for condition, security and adjustment. Clean and lubricate switches using MIL-C-81309, Type 2, Class 2, Water Displacing Ultra Thin Film.

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

INSPECTION CALL POINT – Verify compliance with Section D, Steps 1 through 6.

E. NOSE LANDING GEAR COMPLETED

BY

INSPECTED

BY

1. NOSE LANDING GEAR STRUT ASSEMBLY – Inspect strut and components for condition, attachment and fluid leakage. If leakage is detected, deflate and check the fluid level.

2. SHIMMY DAMPENER – Inspect for condition, attachment and leakage. Check fluid quantity, remove and replace as required.

3. NOSE LANDING GEAR TURN STOP – Inspect brace assembly casting for cracks at stop block. Check stop bolts for distortion.

4. DRAG BRACE ASSEMBLY – Inspect for condition, attachment, alignment, security and excessive wear.

4.1 Check airframe attach fittings for condition and security.

4.2 Remove drag leg bolt at strut attach point, inspect area for corrosion and treat area as required. Fill the void not occupied by a bushing with grease.

Reassemble and secure bolt.

INSPECTION CALL POINT – Verify compliance with Section E, Steps 1 through 4.2.

5. FORWARD RETRACT ROD AND IDLER – Check installation for condition, security and alignment. Check for positive clearance between the nose gear retract arm and the right rudder buss arm with the nose gear up and the rudder full left.

NOTE

Access to accomplish this inspection can be gained by removing the NLG retract rod boot.

5.1 Check up-lock for condition and a minimum of 0.12” engagement. Reference for the dimension is contained in MED ATA 32-30-00/PR-14.

5.2 Lower the landing gear until positive disengagement of the up-lock hook from the engaging slot is evident. Verify a clearance of 0.06” to 0.12” between the hook and engaging slot.

Page 7 Revised: March 1, 2005

E. NOSE LANDING GEAR (Continued) COMPLETED

INSPECTED

5.3 With the landing gear fully retracted apply a downward force at the centerline of the tow pin to ensure 0.10” to 0.14” movement before the uplock restricts the movement of the gear. To accomplish this step a minimum force of 35 pounds of downward force shall be required before the gear is restricted by the uplock.

Reference for the tolerances are contained in MED ATA 32-30-00/PR-14.

5.4 Ensure that the Gladiator Shield has been reconnected.

6. RETRACT ROD - Remove nose landing gear aft retract rod.

6.1 Inspect nose landing gear aft retract rod and rod end bearings for condition and

6.2 Inspect nose landing gear aft retract rod for straightness in accordance with the dimensions contained in Section/Chapter 32-20-00, Page 210, Figure 204 of the T-34C Maintenance Manual.

INSPECTION CALL POINT – Verify compliance with Section E, Steps 6 through 6.2.

Ensure Step E 6 above has been complied with prior to performing the following step.

7. TIME DELAY RELAY - Perform in-transit gear reversal inspection on those aircraft with AFC 73 and AFC 81 installed by selecting a direction for landing gear travel (up/down) and immediately switching the direction of travel. If time delay is inoperative, refer to the T-34C Maintenance Manual for replacement instructions.

8. MOTOR DYNAMIC CHECK – With landing gear in the retracted position and the PWR and CONT circuit breakers engaged (in), select gear to the Down position. As gear travels downward pull the CONT circuit breaker and observe that the landing gear does not coast after the circuit breaker has been disengaged.

9. RETRACT ROD - Reinstall nose landing gear aft retract rod.

10. Check for proper tension of the retract rod spring while the NLG is in the down position in accordance with MED ATA 32-30-00/PR-14.

11. GEAR ACTUATOR – Check actuator for security and condition. Lubricate in accordance with Lubrication Charts.

If any hardware at the “Spider” requires replacement refer to MED ATA 32-30-00/PR-70.

12. ELECTRICAL – Check condition, security, adjustment and mechanical operation of all switches.

12.1 Check wiring for condition and attachment.

INSPECTION CALL POINT – Verify compliance with Section E, Steps 11 through 12.1.

Page 8 Revised: March 1, 2005

E. NOSE LANDING GEAR (Continued) COMPLETED

13. WHEEL AND TIRE – Check wheel for condition. Check tire for condition, wear and proper inflation. Inflation Gauge # .

13.1 Clean, inspect and/or replace and lubricate wheel bearings with SHC 100 Mobil Aviation Synthetic Grease. Lightly saturate felt seals with MIL-L-2104 30-weight oil. Coat surfaces of seals with SHC 100 Mobil Aviation Synthetic Grease.

Torque the retainer nut with the wheel being rotated clockwise to 240-inch pounds to properly seat the bearings. Back off the torque to zero and re-torque to 50-inch pounds but do not exceed 100-inch pounds to align the retaining nut to the next available cotter pin hole. Reference MED 32-40-00/PR-106. Torque Wrench # .

14. NOSE WHEEL WELL DOORS – Check condition and security of doors and linkage.

INSPECTION CALL POINT – Verify compliance with Section E, Steps 13 through 14.

F. MAIN LANDING GEAR AND BRAKES LEFT RIGHT INSP

1. STRUT ASSEMBLY – Inspect strut and components for condition, attachment and fluid leakage. Deflate and check fluid level if leakage is detected.

1.1 Check airframe attach fittings for condition, security and corrosion.

2. DRAG BRACE ASSEMBLY – Inspect for condition, attachment, alignment and excessive looseness/wear. Check airframe attach fittings for condition, security and corrosion.

3. Lubricate the main landing gear down-lock assembly with VV-L-800.

INSPECTION CALL POINT – Verify compliance with Section F, Steps 1 through 3.

4. RETRACT RODS – Check installation for condition and security. Check for proper tension of retract rod spring while the gear is in the down position.

4.1 Lubricate main landing gear up-lock cable assembly with MIL-C-81309 along the length of the cable housing, at the wedge connecting the up-lock and down-lock cables and into each end of the cable housing. Carefully inspect the cables for fraying.

5. UP-LOCK ROLLERS – Inspect for condition, security and freedom of rotation.

Lubricate in accordance with the latest issue of MED ATA 32-30/PR-14.

6. UP-LOCK BLOCK – Inspect in accordance with MED ATA 32-30/PR-14.

Exercise down-lock assembly after lubrication to verify freedom of movement.

Place a wrench on the bolt and move slowly in both directions and ensure the down lock block does not move.

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2

Page 9 Revised: March 1, 2005

F. MAIN LANDING GEAR AND BRAKES (Continued) LEFT RIGHT INSP

INSPECTION CALL POINT – Verify compliance with Section F, Steps 5 and 7.

8. LANDING GEAR ACTUATOR – Check condition, security, adjustment and mechanical operation of switches. Clean and carefully lubricate the mechanical portions of the stack switches using MIL-C-81309, Type 2, Class 2, Water Displacing Thin Film.

8.1 Check condition of and ensure that the hardware connecting the white rods and green rods to the spider are in good condition and are configured as specified in MED ATA 32-30-00/PR-70. Particular attention is to be paid to ensure that the cotter key installation where the right MLG White Rod and the Spider are connected is installed as specified in the MED to prevent interference between the hardware and the stack switch assembly. In addition to the foregoing visually inspect the hardware to ensure adequate clearance exists between the leg of the cotter key and the entire stack switch assembly.

9. BRAKE ASSEMBLY – Remove and visually inspect brake assembly, particularly in area of the two pistons. Check lines for leakage, security and condition. Polish full length of guide pins with Scotch Brite to leave a shiny hue.

Clean bushings with a bore brush. Lightly coat the guide pins with a mixture of Molybdenum Disulfide Lubricant (MIL-M-7866) and Liquid Contact Cleaner

(ECO 2005).

9.1 Check discs and linings for amount of wear and replace as required then reassemble.

10. WHEELS AND TIRES – Check wheel for condition. Check tire for condition, wear and proper inflation. Inflation Gauge # .

10.1 Clean, inspect and/or replace and lubricate wheel bearings with SHC 100 Mobil Aviation Synthetic Grease. Lightly saturate felt seals with MIL-L-2104 30-weight oil. Coat surfaces of seals with SHC 100 Mobil Aviation Synthetic Grease.

Torque the retainer nut with the wheel being rotated clockwise to 240-inch pounds to properly seat the bearings. Back off the torque to zero and re-torque to 50-inch pounds but do not exceed 100-inch pounds to align the retaining nut to the next available cotter pin hole. Reference MED 32-40-00/PR-106. Torque Wrench # .

11. MAIN WHEEL DOORS – Check condition and security of doors and linkage.

G. LANDING GEAR SYSTEM OPERATIONAL CHECK COMPLETED

BY

INSPECTED

BY

NOTE

Since battery voltage is not sufficient to properly cycle landing gear, use an external power source capable of delivering and maintaining 28.25 ± 0.25 volts throughout the extension and retraction cycles when performing the landing gear retraction inspection.

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2

Page 10 Revised: March 1, 2005

G. LANDING GEAR SYSTEM OPERATIONAL CHECK (Continued) COMPLETED

BY

1. RETRACT MECHANISM – Check retraction system for proper operation through at least two complete cycles placing special emphasis on the following;

a. Check for unusual noises and evidence of binding.

b. Travel - Check full down and full up limit adjustments.

c. Position Indicating – Check down-lock, up-lock and in-transit indications.

d. Warning System – Check handle lights and warning horn for proper

e. Control Handle Assembly – Inspect for condition, security and operation.

2. DOORS AND LINKAGE – Check doors for security, operation and fit.

INSPECTION CALL POINT – Verify compliance with Section G, Steps 1 and 2.

WARNING

PULL the landing gear PWR circuit breaker prior to engaging the emergency extension system to prevent injury to the operator.

3. EMERGENCY EXTENSION – Check system operation. Reset the PWR circuit breaker and retract the landing gear electrically after the manual extension.

Ensure the landing gear control handle and the landing gear is physically in the DOWN position before the aircraft is removed from the jack.

4. BOOT - Check the boot on manual gear extension cable for security and proper installation. Ensure the boot does not interfere with clutch operation.

5. INSTALL - Front cockpit floor panel.

5.1 Front cockpit seat.

Check gap between floor mounting brackets and chair frame as specified in the T-34C Maintenance Manual anytime seat is removed and reinstalled.

5.2 Front cockpit parachute.

INSPECTION CALL POINT – Verify compliance with Section G, Steps 5 through 5.2.

H. AIRFRAME

1. RUDDER – Check tab and associated linkage and hardware for excessive wear.

2. BATTERY COMPARTMENT – Check for general condition. Check tracks for proper operation. Removal of the battery is not required.

2.1 Check condition and proper placement of the anti-chafe band.

Prior to performing the function specified in Step 2.2 ensure that the battery is disconnected.

2.2 Check cables and vent lines for condition. Ensure cables are fully inserted into connector and setscrews are tight.

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2

Page 11 Revised: March 1, 2005

H. AIRFRAME (Continued) COMPLETED

BY

3. While the aircraft is on the jack and with the inboard gear doors open check the condition of the underside of both wing walkways for buckling and delamination by “Tap Testing”. If delamination is detected refer to MED ATA57-00-00/PR-54 for the limitations and repair criteria.

4. Thoroughly inspect both the upper and lower spar caps and hinge lobe areas of both wings for signs of buckling, loose or raised paint and other evidence of corrosion.

5. Thoroughly inspect the condition of the sealant used to seal the hinge lobe areas of both the upper and lower spar caps.

INSPECTION CALL POINT – Verify compliance with Section H, Steps 2 through 5.

I. POWER PLANT

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. Torque Wrench # . Leak-check the filter assembly after installation using the electric boost pump.

The firewall shut-off valve MUST be closed during removal and installation of the filter.

2. OIL FILTER ELEMENT – Remove and inspect for condition and foreign matter.

Install clean filter. Torque to 32 – 36-inch pounds. Torque Wrench # .

3. OIL QUANTITY – Motor Engine. Check and service as required.

4. IGNITERS - Check spark igniters for condition, security and operation. Torque Igniters to 300 – 360-inch pounds. Torque Wrench # .

5. P-3 FILTER - Remove and replace P-3 filter. Torque cover to 60 – 70-inch pounds. Torque Wrench # .

6. SCAVENGE PUMP - (EPA PUMP) – Perform the following:

6.1 Check for security of attachment of pump.

6.2 Check hoses for cracks, deterioration and proper attachment.

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

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

INSPECTION CALL POINT – Verify compliance with Section I, Steps 6.1 through 6.4.

J. GENERAL SERVICE ITEMS COMPLETED

INSPECTED

BY

1. Clean and service aircraft. Vacuum and clean cockpits, polish windshield and canopy.

Aircraft are washed every fourteen (14) days in accordance with the provisions of the T-34C Corrosion Control Plan.

NAVAIR (PMA 273) 01-50-T34C-600-6-4.2

Page 12 Revised: March 1, 2005

J. GENERAL SERVICE ITEMS (Continued) COMPLETED

BY

2. Ensure aircraft is lubricated as specified in the attached lubrication charts/tables.

K. OPERATIONAL CHECK COMPLETED

INSPECTED

BY

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

NAVAIR 01-T-34AAC-1B.

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 cowling removed during inspection.

INSPECTION CALL POINT – Verify compliance with Section K, Steps 1 through 4.

NAVAIR 01-50-T-34C-600-6-4.2

Page 13 Revised: March 1, 2005

NOTE: Index numbers in parentheses reference the original index numbers in the T-34C Maintenance Manual lube charts.

NOTE: Index numbers in parentheses reference the original index numbers in

SECOND 100-HOUR INTERVAL DETAILED INSPECTION LUBRICATION CHART

Main Landing Gear Index No Location Lubricant Interval Accomplished By Inspected By

(26)

Main Gear Retract Brace (2 Places Per Side)

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

(28)

Main Gear Lift Leg and Uplock Rollers (1 Place Per Side)

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

(29)

Drag Leg Assembly (1 Place Per Side)

MIL-G-81322 Grease 2/100 Detail

3A (29)

Down Lock Assembly (1 Place Per Side)

MIL-G-81322 Grease 2/100 Detail

(30)

Main Gear Torque Knees (6 Places Per Side)

LPS-2 Oil 1/100 and 2/100 Detail

(33)

Main Gear Door Hinges and Linkage (5 Places Per Side)

VV-L-800 General Purpose Oil

2/100 Detail

(27)

Main Gear Attach Point Bushings (4 Places Per Side)

LPS-2 Oil 1/100 and 2/100 Detail

7 Reserved

(36A) Main Gear Door Retract Rods (2 Places Per Green Rod)

VV-L-800 General Purpose Oil

2/100 Detail

(36B)

Main Gear Idler Arm (2 Places Per Side)

LPS-2 Oil 2/100 Detail

Nose Landing Gear

(38)

Nose Gear Drag Brace (4 Places)

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

(37)

Nose Gear Attach Points (2 Places)

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

(42)

Nose Gear Door Retract Attach Points (2 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(41)

Nose Gear Swivel Bearings (2 Places)

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

14 Reserved

THINK SAFETY

3A

2 6

Page 14 Revised: March 1, 2005

NOTE: Index numbers in parentheses reference the original index numbers in the T-34C Maintenance Manual lube charts.

NOTE: Index numbers in parentheses reference the original index numbers in

Nose Landing Gear

(39)

Nose Gear Torque Knee (5 Places)

LPS-2 Oil 1/100 and 2/100 Detail

(43)

Nose Gear Retract Rod – Hand Packed (3 Places)

MIL-G-81322 Grease 2/100 Detail

(44)

Nose Gear Door Retract Rod Attach Points (4 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(48)

Nose Gear Door Hinges (6 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

Engine and Propeller

(45)

Propeller Hub Blade Clamps (3 Places)

Aeroshell 6 Grease 1/100 and 2/100 Detail

(46)

Propeller Low Pitch Stop Rods (3 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(50)

Engine Cam Plates and Pins (3 Places)

Lubriplate 130A Grease

1/100 and 2/100 Detail

(49)

Engine Control Rod Ends (2 Places)

Lubriplate 130A Grease

1/100 and 2/100 Detail

3 4

Page 15 Revised: March 1, 2005

NOTE: Index numbers in parentheses reference the original index numbers in

Flight Controls

(52)

Trim Tab Control Chains In Cockpit Area (11 Places)

MIL-L-2104

Lube Oil Grade 30

1/100 and 2/100 Detail

1A (N/A)

Aileron And Elevator Trim Box Drive Shafts In Both Cockpits (2 Places)

MIL-L-2104

Lube Oil Grade 30

1/100 and 2/100 Detail

(53)

Elevator Trim Tab Chains (3 Places)

MIL-L-2104

Lube Oil Grade 30

1/100 and 2/100 Detail

(54)

Rudder Trim Console Shaft (2 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(55)

Rudder Trim Tab Chains (2 Places)

MIL-L-2104

Lube Oil Grade 30

1/100 and 2/100 Detail

(19)

Aileron Hinges (3 Places Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

5A (19A)

Aileron Trim Tab Hinge (1 Place Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(21)

Aileron Trim Actuator Rod Assembly (4 Places Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(20)

Aileron Tab Actuator Chains (1 Place)

MIL-L-2104

Lube Oil Grade 30

1/100 and 2/100 Detail

8 Reserved

9 Reserved

(23) Flap Actuator Pivot Points, Piston Plug and Bushing (3 Places Per Side)

VV-L-800 General

2/100 Detail

5A

6 7

1A

Page 16 Revised: March 1, 2005

NOTE: Index numbers in parentheses reference the original index numbers in

Flight Controls (Continued)

(14)

Elevator Hinge (3 Places Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

11A (14A)

Elevator Trim Tab Hinge (1 Place Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(16)

Elevator Trim Tab Rod Assembly (2 Places Per Side)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(9)

Rudder Hinge and Bellcrank (3 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

13A (9A)

Rudder Trim Tab Hinge (1 Place)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(10)

Rudder Trim Tab Rod Assembly (2 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(51)

Flap Position Transmitter Arm Roller (1 Place)

Lubriplate 130A Grease

2/100 Detail

(13)

Elevator Control Rod Ends (4 Places)

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

(3)

Rudder Buss Upper Rod Ends (2 Places)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(5)

Rudder Pedal Adjusting Screw (2 Places Per Pedal)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(6)

Brake Master Cylinder Extension (1 Place Per Pedal)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(7)

Rudder Pedal Adjust 90° Drive Assembly (1 Place Per Pedal)

VV-L-800 General Purpose Oil

1/100 and 2/100 Detail

(8)

Rudder Control Cable Ends (2 Places)

VV-L-800 General

2/100 Detail

13A

11A

19 20

T-34C CONTINUOUS INSPECTION DISCREPANCY RECORD WORK SHEET

Page 17 Revised: March 1, 2005

AIRCRAFT BUNO: Date: JCN:

DISCREPANCY

DISCREPANCY/CORRECTIVE ACTION

ITEM CORRECTIVE ACTION

COMP

INSP

QA

NOTE: In the “ITEM” Block, annotate with the corresponding Section and Step Number against which the discrepancy was generated.

DETAIL INSPECTION SIGN-OFF SIGNATURE AND INITIALS RECORD

Page 18 Revised: March 1, 2005

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

T-34C POWER ASSURANCE RUN WORKSHEET/RECORD

Page 19 Revised: March 1, 2005

BUNO: PURPOSE:

DATE: ENGINE TIME SINCE OVERHAUL:

OPERATIONAL CHECK

Perform operational check and record readings. Follow procedures outlined in

NAVAIR 01-T34AAC-1B for pre-start, engine start and ground run-up.

COMPLETED

1. Maximum torque check – Accomplish torque check as specified in T-34C Maintenance

Manual (P/N 92-37867). Record:

OAT __________ Max Torque __________ Fuel Flow __________

ITT __________ N1 __________ Press. Alt. __________

EPL Max. Torque __________ Acceleration check __________ seconds

Torque Controller Setting __________ (1315 max)

2. Set 950 torque and 2200 RPM. Record:

ITT __________ N1 __________ Fuel Flow __________

3. Perform and record:

Low idle __________ Beta Range of Operation RPM __________ Torque __________

Set N1 at 75%. Record Oil Pressure __________ Auto Ignition Torque __________

Primary governor check – Max Governing RPM __________

Primary Low Pitch Torque at 2000 RPM __________ Min Governing RPM __________

Overspeed governor check RPM __________

4. Inertial Separator – Check operation by observing torque meter drop during actuation.

5. Environmental System Check

a. Check bleed air heating, defog and ventilation.

b. Air conditioner systems for condenser blower operation, and air conditioner output.

Check blowers in both cockpits.

6. Perform and Record:

Manual Feather RPM __________

7. Check engine shutdown from rear cockpit.

SUPERVISOR _________________________ QUALITY ASSURANCE REPRESENATIVE _________________________

All employees performing PAR tasks must record their name, signature and initials on the PAR work record.

POWER ASSURANCE RUN SIGN-OFF SIGNATURE AND INITIALS RECORD

NAVAIR 01-50-T-34C-600-6-4.1

Page 20 Revised: March 1, 2005

EMPLOYEE NAME (PRINT)

EMPLOYEE SIGNATURE

EMPLOYEE

INITIALS