ATT 73 01-50-T34C-600-6.pdf

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

U.S. NAVY T-34C

TURBO MENTOR

CONTINUOUS INSPECTION

PROCEDURES MANUAL

March 1, 2005

ATTACHMENT 73

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

PAGE EFFECTIVITY LISTING

Summary:

• The original issue of the NAVAIR (PMA 207) 01-50-T34C-600-6, 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 Section I NA 3/1/2005 Changes Not Bar Marked Section II NA 3/1/2005 Changes Not Bar Marked Section III NA 3/1/2005 Changes Not Bar Marked Section IV NA 3/1/2005 Changes Not Bar Marked Section V NA 3/1/2005 Changes Not Bar Marked i 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.

ii 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):

Check if continuation sheets or drawings attached.

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.

iii 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.

iv March 1, 2005

SECTION I

GENERAL INFORMATION

T-34C CONTINUOUS INSPECTION PROGRAM

The BEECHCRAFT (Raytheon Aircraft Company) T-34C Maintenance Manual contains a listing of Beech, Navy and Vendor publications, which may be used to provide service, and maintenance information supplementary to that provided in the Maintenance Manual and the BEECHCRAFT T-34C Continuous Inspection Procedures Manual. Federal Aviation Regulations, Parts 43 and 91 contain the regulations pertinent to the purpose and use of the Continuous Inspection Program.

NOTE

Material contained in this manual, including the inspection intervals, may be changed at any time, with prior notification and approval, when warranted by service experience or engineering recommendations.

Information contained herein is applicable to all Model T-34C aircraft except where differences are indicated by serial effectivity.

Submit recommendations for additions, deletions or changes to the requirements of this plan to Commander Naval Air Systems Command PMA 273, Patuxent River, MD 20670 to the attention of the T-34C APMSE using a Technical Information Report, Deficiency (TIRD). A copy of the TIRD and the instructions for completing the TIRD are contained on Pages iii and iv of this document.

The first overhaul or replacement should be performed no later than the required period. The condition of the item at the end of the first period may be used as a criterion for determining subsequent periods applicable to the individual aircraft or fleet operation approved monitoring system.

The time periods for inspections noted in this manual are based on average usage and average environmental conditions.

During compliance with these inspection procedures, check for conformity with FAA or equivalent specifications, Airworthiness Directives, Service Instructions, and installation instructions. Reference should be made to applicable maintenance handbooks and vendor specifications for torque values, clearances, settings, tolerances, and other specifications. Verify that all interior and exterior placards are legible and in place. Refer to Chapters 5, 12, 91, and other appropriate chapters of the BEECHCRAFT T-34C Maintenance Manual (P/N 92-37867, dated January 30, 1997 or subsequent) for items requiring LUBRICATION, CLEANING, REPLACEMENT, or SERVICING at specific intervals; or for INSPECTION requirements at intervals other than those specified in this manual.

SPECIAL CONDITIONS CAUTIONARY NOTICE

Aircraft operated outside of the Naval Air Training Command and aircraft operated in unusual climates, etc., may need more frequent inspections for wear, corrosion, and/or lack of lubrication. In these areas, additional periodic inspections should be performed until inspection periods can be established based on operator experience.

This section, Section I, consists of General Information relative to the overall program requirements. The following sections are also contained within this publication:

Section II – Inspection Requirements Matrices.

Section III – Mandatory Scheduled Components Removal Listing.

Section IV – Authorized Deviations.

Section V - Preferred Spares Listing.

Section I - Page 1

GENERAL INFORMATION

PURPOSE AND USE

The Continuous Inspection Procedures are designed to maintain the BEECHCRAFT Model T-34C aircraft used by the Naval Air Training Command for student pilot training. Under the inspection procedures, each aircraft receives a detailed inspection every 100 hours of service time, which provides for a complete aircraft inspection every 200 hours. The intent of this method is to provide greater availability of aircraft during operating hours without sacrificing the quality of maintenance and inspection.

DEFINITIONS

Terminology pertaining to inspection procedures and their use in this manual is in accordance with Federal Aviation Regulations, Parts 43 and 91. These terms are defined as follows:

Aircraft Condition Inspection (ACI) - A thorough, comprehensive disassembly and inspection of aircraft structure and flight critical components with repair as necessary, to ensure serviceability of the affected structure or components until the next ACI. The current ACI schedule is predicated on a sixty (60) month service interval.

Continuous Inspection - A continuing airworthiness inspection of an aircraft and its various components and systems at scheduled intervals in accordance with procedures prescribed by the Federal Aviation Administration

(FAA).

Detailed Inspection - A thorough examination of the appliances, the aircraft, components and systems with such disassembly as necessary.

Flight Time – A flight begins when the aircraft first moves forward on its takeoff run and ends after airborne flight when the aircraft is on the surface and either the engine is stopped or the aircraft has been on the surface for five (5) minutes, whichever comes first.

Maintenance - Inspection, overhaul, repair, preservation and the replacement of parts, excluding preventive maintenance

Pilot in Command - The pilot responsible for the operation and safety of the aircraft during flight time.

Preventive Maintenance - Simple or minor preventative operations and the replacement of small standard parts not involving complex assembly operations.

Daily/Turnaround Checklist - A visual examination or check of the appliances, the aircraft, components and systems insofar as practicable without disassembly, including abbreviated inspection requirements that are necessary to determine the need for servicing and insure the integrity of the aircraft for flight. These inspection requirements do not require aircraft logbook entries.

FORMS AND RECORDS

The forms and records used with the Continuous Inspection Program consist of an Engine Wash and Power Assurance Run form, First and Second 100-Hour Interval forms, Continuous Inspection Work Sheet and Maintenance Action Form (VIDS/MAF, OPNAV Form 4790/60).

Engine Wash and Power Assurance Run - This form is used to record engine, propeller and environmental system checks as part of each Detail Inspection.

Section I - Page 2

100-Hour Interval Detailed Inspection Form - Two separate and individual 100-Hour Interval Detailed Inspection forms are used with the Continuous Inspection Program. Each form covers only a portion of the aircraft and is designated as 1ST or 2ND 100-Hour Interval Detailed Inspection. Completion of the 1ST and 2nd 100-Hour Interval Detailed Inspections provides a complete airworthiness inspection of the aircraft.

Continuous Inspection Work Sheet - This form is used in conjunction with each of the inspection forms to provide a list of all discrepancies found during the inspection and the corrective action taken.

OPNAV Form 4790/60 (VIDS/MAF) - This is the standard Navy form used to record maintenance discrepancies and the corrective maintenance actions taken to rectify the reported problem.

INSPECTION PROCEDURES

NOTE

Before beginning a Continuous Inspection Program, both a First and Second 100 Hour Detailed Inspection must be completed on all aircraft with previous service time.

DAILY/TURNAROUND INSPECTION

Daily Inspections are conducted as specified in the Daily Turnaround Checklist, MRC Number NAVAIR (PMA

273) 01-50-T34C-600-6.1. The inspection consists mainly of a visual inspection of major aircraft components.

The engine cowlings are the only sections of the aircraft that are physically opened to check the general condition of the engine and propeller.

Daily Inspection requirements shall be accomplished prior to the first flight of the day and are valid for seventy-two (72) hours provided the aircraft has not been flown during that period of time.

The Turnaround Inspection is accomplished prior to the first flight of the day, as part of the Daily Inspection, and between flights on the same day. An asterisk in front of those items requiring inspection indicates the Turnaround Inspection requirements.

A Turnaround Inspection must be accomplished on aircraft that have had a valid Daily Inspection completed but have not been flown and 24 or more but less then 72 clock hours have transpired since the last Daily Inspection was completed.

ENGINE WASH AND POWER ASSURANCE RUN (100-Hour Intervals) An Engine Wash and Power Assurance Run shall be conducted on each aircraft in conjunction with each Detail Inspection. This procedure checks performance of engine and propeller systems and includes environmental system checks. These inspections are to be performed by properly qualified personnel. Complete instructions for conducting an Engine Wash and Power Assurance Run is contained in Section IV of this manual.

NOTE

The Engine Wash and Power Assurance Run are to be conducted immediately prior to induction into each Detail Inspection.

DETAILED INSPECTIONS (100-Hour Intervals) A Detailed Inspection of the aircraft shall be conducted for each 100 hours of aircraft service time. A portion of the aircraft is inspected at each 100-hour interval, thereby completing a complete aircraft inspection once every 200 hours. If an item requires attention at 100-hour intervals, it is listed in the first Detailed Inspection and is repeated in the second. These inspections are to be accomplished by properly qualified maintenance personnel.

Complete instructions for conducting the 1ST and 2nd Detailed Inspections are contained in Section II and III of this manual, respectively.

Section I - Page 3

DISCREPANCIES

Discrepancies found on the aircraft during an inspection will be listed on the "Continuous Inspection Work Sheet." Two lines are provided on the work sheet for each item. Discrepancies will be entered on the top line of the entry space and the corrective action taken will be noted underneath. If more than one line is required to state the discrepancy, as many entry spaces as necessary may be used. The same method should be used for corrective action explanations requiring more than one line, except the bottom lines of the extra spaces will be used. Each separate entry on the sheet will be numbered in the "ITEM" block with the corresponding section and step numbers of the inspection package against which the discrepancy was generated. As many work sheets as necessary will be used to list all discrepancies. All discrepancies listed must be corrected or documented on a VIDS/MAF before the work sheet is routed to the aircraft file.

Discrepancies affecting airworthiness of the aircraft require completion of prescribed corrective action before the aircraft can be returned to service.

Discrepancies not affecting airworthiness of the aircraft may be carried as an outstanding/open discrepancy until such time as time and material is available to correct the problem. All discrepancies thus carried over will be retained on record as appropriate on an OPNAV Form 4790/60 (VIDS/MAF).

The pilot in command or other responsible person will record discrepancies occurring during flight utilizing a VIDS/MAF (OPNAV Form 4790/60) or other forms made available to the pilot for recording discrepancies. If another local form is used the discrepancy shall be transferred to a VIDS/MAF. At the end of the flight the form(s) are submitted to Aircraft Issue/Maintenance Control for review and distribution to the appropriate work center.

INSPECTION TIME LIMITATIONS

Inspection intervals specified in the inspection schedule shall not be exceeded by more than ten (10) percent. It can also be accomplished no more then ten (10) percent prior to its next scheduled detail inspection. In either case the next detail inspection shall be due as if no deviation has occurred.

Two 100-Hour Detailed Inspections must be accomplished within an 18-month period. Any part of the inspection that has not been accomplished will become due immediately. Completion of only the 1st or only the 2nd 100-Hour Inspection shall not be considered a complete airworthiness inspection.

NOTE

In the event that both the First 100 and Second 100 Hour Detail Inspections simultaneously the next type inspection due will always be a First 100 Hour Detail Inspection.

CONTINUOUS INSPECTION SCHEDULE OUTLINE

Aircraft Time (Hours) Type of Inspection Components Inspected

100 1st Detailed Inspection Engine wash and power assurance run; Airframe; Avionics;

Power plant; Air conditioning, heating and ventilation;

Landing gear; General servicing items; and Operational checks.

200 2nd Detailed Inspection Engine wash and power assurance run; Cockpit group;

Avionics; Flaps; Nose landing gear: Main landing gear and brakes; landing gear operational check; Airframe; Power plant; General servicing items; and Operational checks.

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

March 1, 2005

Section I - Page 4

SECTION II

INSPECTION REQUIREMENTS

MATRICES

HOURLY/CYCLE/EVENT DRIVEN REQUIREMENTS

T-34 C C

ONTIN

UOUS IN

SPECTIO

N PROCEDURES

MANUAL - N

AVAIR

(P

MA 27

3)

-50 -T

C-60

0-6

T-34 C M

AIN

TENANCE M

ANUAL

MED A

TA 32

-30

/PR-14

PRATT A

ND W

HIT

NEY M

AIN

TENANCE M

ANUAL

NAVAIR

N

ACW

S 99

1 M

AIN

T. M

ANUAL

MED A

TA 79

-00 -00

/PR-51

MED A

TA 73

-00 -00

/PR-62

MED A

TA 27

-10 -40

/PR-72

MED A

TA 52

-00 -00

/PR-77

T-34 C W

ORK IN

STRUCTIO

N N

UMBER 26

-00 -00

MED A

TA 32

-20 -00

/PR-81

MED A

TA 57

-00 -00

/PR-54

X1ST 100 HOUR SCHEDULED INSPECTION

2ND 100 HOUR SCHEDULED INSPECTION

25 HOUR ENGINE OIL SAMPLE X

100 HOUR WING BOLT RETORQUE, AFTER INITIAL INSTALL X

100 HOUR WING HINGE PIANO WIRES SECURITY INSPECTION, AFTER INSTALLATION

100 HOUR VERTICAL STABLIZER ATTACH BOLT RETORQUE AFTER INSTALLATION

100 HOUR CANOPY CENTER SECTION DRAIN INSPECTION *** X

100 HOUR HORIZONTAL STABLIZER ATTACH BOLT RETORQUE AFTER INSTALLATION

100 HOUR UPPER WING WALKWAY DELAMINATION INSPECTION * X

200 HOUR LOWER WING WALKWAY DELAMINATION INSPECTION ** X

200 HOUR HORIZONTAL STABLIZER ATTACH BOLT RETORQUE AFTER INSTALLATION *

200 HOUR ENGINE CHIP DETECTOR X

200 HOUR LANDING GEAR UPLOCK AREA MAINTENANCE INSPECTION PROCEDURES X

200 HOUR CONTROL STICK GIMBLE INSPECTION ** X

200 HOUR FIRE DETECTOR SENSITIVITY CHECK * X

300 HUNDRED HOUR STARTER GENERATOR SPLINE LUBRICATION ***** X

300 HUNDRED HOUR STARTER GENERATOR BRUSH CHECK X

300 HOUR FLAP MOTOR GEARBOX LUBE/REPACK ****** X

500 HOUR NACWS DYNAMIC SYSTEM TEST X X

500 HOUR STROBE HYPOT TEST X

500 HOUR VERTICAL STABILIZER ATTACH BOLT RETORQUE X

600 HOUR AILERON / ELEVATOR TRIM TAB FREE PLAY INSPECTION X

600 HOUR AILERON / ELEVATOR / RUDDER CABLE TENSION CHECK

600 HOUR A/C EVAPORATOR BLOWER INSPECTION X

600 HOUR COMPRESSOR TURBINE BORESCOPE INSPECTION X

600 HOUR FUEL NOZZLE INSPECTION X

600 HOUR FUEL PUMP DRIVE COUPLING INSPECTION X

600 HOUR FUEL PUMP OUTLET FILTER REPLACEMENT X

900 HOUR STARTER GENERATOR BEARING AND BRUSH CHECK X

1,000 HOUR ENGINE OIL CHANGE

1,000 HOUR REPACK FLAP ACTUATORS, L/H AND R/H X

1,000 HOUR FLIGHT CONTROL TRIM TAB ACTUATOR REPACK X

1,000 HOUR WING HINGE PIANO WIRES SECURITY INSPECTION

2,000 LANDINGS NOSE LANDING GEAR "V" BRACE INSPECTION **** X

1,800/3,600 HOUR HOT SECTION INSPECTION X

3,000 HOUR / 6 YEAR FUEL CONTROL MID-LIFE INSPECTION X

* REQUIREMENT IS ALREADY INCLUDED IN THE FIRST 100 HOUR DETAIL PACKAGE.

** REQUIREMENT IS ALREADY INCLUDED IN BOTH THE FIRST AND SECOND 100 HOUR DETAIL PACKAGES.

*** REQUIREMENT IS ALREADY INCLUDED IN EACH DETAIL PACKAGE.

**** REQUIREMENT ONLY APPLIES TO "V" BRACES THAT HAVE BEEN REPAIRED.

***** USE MOLYKOTE GREASE

****** HANDPACKED WITH MIL-G-21164 GRAPHITE LUBE GREASE

X

X X

March 1, 2005

X

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

X X

X X

X

Section II - Page 1

X

X

X

X

CALENDAR REQUIREMENTS

NAVAIR

(P

MA 27

3)

T34

C CORROSIO

N CONTROL PLAN

T-34 C M

AIN

TENANCE M

ANUAL

PRATT A

ND W

HIT

NEY M

AIN

TENANCE M

ANUAL

OPNAVIN

ST 47

.2

(SERIE

S)

MI N

-21

MED A

TA 53

-30 -00

/PR-73

MI N

-22

MED A

TA 32

-20 -00

/PR-57

NAVAIR

T34

C A

CI M

ANUAL

Allie d S ign al

GPS Pilo ts G uid e O

RS 01

NAVAIR

-01 -50

P&W

C SB 14

REVISIO

N 4

MED A

TA 32

-20 -00

/PR-81

NAVAIR

(P

MA 27

3)

-50

-T

C-60 0-6

-2

DAILY/TURN AROUND INSPECTION X

DAILY ENGINE RINSE X X X

DAILY LEVEL 1 PRESERVATION INSPECTION X X X

7 DAY LEVEL 1 PRESERVATION INSPECTION X X X

7 DAY NB 6 PARACHUTE INSPECTION X

7 DAY LUBE X X

7 DAY TIRE INFLATION X

14 DAY AIRCRAFT WASH AND LUBE X

28 DAY LEVEL 1 PRESERVATION INSPECTION X X X

28 DAY GPS PICA CARD UPDATE X

56 DAY CORROSION INSPECTION X

ANNUAL RUDDER BUSS ARM INSPECTION X X

ANNUAL WING BOLT CHECK AND LUBE X

ANNUAL LUBRICATION OF THE RUDDER BUSS SHAFT X

ANNUAL LUBRICATION OF THE RUDDER BUSS LOWER ROD ENDS X

ANNUAL CLEANING AND RE-PRESERVATION OF AIRCRAFT SLING ATTACH POINTS X

30 MONTH REPLACEMENT OF PY LINE CLAMPS * X

60 MONTH AIRCRAFT CONDITION INSPECTION X

60 MONTH WING ATTACH FITTING AND HARDWARE INSPECTION X

60 MONTH NOSE LANGING GEAR "V" BRACE INSPECTION ** X X

* NOT REQUIRED IF P&WC SB 1586, LINE WITH FLEX COUPLING, IS INCORPORATED.

** APPLIES TO ALL "V" BRACES.

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

Section II - Page 2 March 1, 2005

PILOT PERSONAL PROTECTIVE EQUIPMENT

NAVAIR

-1- 6.7

, C

HAPTER 14

NAVAIR

-1- 6.7

, C

HAPTER 13

A

NAVAIR

-1- 6.7

, C

HAPTER 7

NAVAIR

-1- 6.1

-2, CHAPTER 4

NAVAIR

-30

PRC90

-2, CHAPTER 6

NAVAIR

-1- 6.7

, C

HAPTER 5

NAVAIR

-1- 6.5

NAVAIR

-1- 6.2

NAVAIR

(P

MA 27

3)

-50

-T

C-60 0-6

-2

7 DAY NB 6 PARACHUTE INSPECTION X

30 DAY MBU-17 (V) 2/P O2 MASK INSPECTION X

90 DAY HGU-68 (V) 1/P X

90 DAY SV-2B SURVIVAL VEST INSPECTION X

90 DAY LPU-21P LIFE PRESERVER X

90 DAY PRC-90-2 RADIO INSPECTION X

90 DAY CMU-24/P LIFE VEST INSPECTION X

360 DAY FLIGHT GLOVE INSPECTION X

360 DAY FLYER'S SUMMER COVERALL INSPECTION X

360 DAY SUMMER FLYER'S JACKET INSPECTION X

365 DAY FIRST AID KIT INSPECTION X

420 DAY NB-6 PARACHUTE REPACK X

840 DAY NB-8 PARACHUTE REPACK * X

* = This parachute is qualified for use in the T-34C aircraft at the discretion of the operating command.

NAVAIR 9PMA 2730 01-50-T34C-600-6

March 1, 2005

Section II - Page 3

SECTION III

MANDATORY SCHEDULED

COMPONENTS REMOVAL

LISTING

T-34C COMPONENTS

MANDATORY SCHEDULED REMOVAL LIST

MAXIMUM OPERATING TIME (MOT)

NOMENCLATURE PART NUMBER (HOURS, YEARS OR LANDINGS) TYPE RECORD

LANDING GEAR AND FLAP SYSTEMS

Flap Motor (Includes the Gearbox) 35-364151-7 5,000 Landings OPNAV 4790/28A Flap Actuator (L/H), Overhaul 45-521212-19 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Flap Actuator (L/H), Lubricate 45-521212-19 1,000 Hours, Disassemble OPNAV 4790/28A and Lubricate Flap Actuator (R/H), Overhaul 45-521212-20 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Flap Actuator (R/H), Lubricate 45-521212-20 1,000 Hours, Disassemble OPNAV 4790/28A and lubricate Flap Flex Drive (L/H) 12527Y63-31 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A (See Note 1) Flap Flex Drive (R/H) 12163Y63-31 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A (See Note 1) Landing Gear, Nose 104-820011-15 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Landing Gear, Main (L/H) 104-810013-9 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Landing Gear, Main (R/H) 104-810013-10 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Landing Gear Actuator 104-810014-5 8,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Assembly (Gearbox) Landing Gear Motor 96-380022-7 5,000 Landings/5 Years, Whichever Comes First OPNAV 4790/28A Nose Gear Upper Torque Knee 60-820018-5 4,000 Landings Inspection OPNAV 4790/28A Nose Gear Lower Torque Knee 96-820020-5 4,000 Landings Inspection OPNAV 4790/28A Main Gear Upper Torque Knee 104-810044-1 4,000 Landings Inspection OPNAV 4790/28A

Main Gear Lower Torque Knee 104-810044-1 4,000 Landings Inspection OPNAV 4790/28A

Nose Gear V-Brace Assembly 104-820022-3 See Note 2 OPNAV 4790/28A

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

March 1, 2005 Section III - Page 1

MAXIMUM OPERATING TIME (MOT)

NOMENCLATURE PART NUMBER (HOURS, YEARS OR LANDINGS) TYPE RECORD

HOSE ASSEMBLIES

Flammable Liquid Carrying All Every 5 years from date of installation, N/A Hoses, Airframe Related as etched on tag - (See Note 3) Flammable Liquid Carrying All On Condition as determined during Hoses, N/A Power Plant Related engine overhaul in accordance with the OEM's technical data.

Brake Hoses All On Condition N/A All Other Hoses (Drain Lines, All On Condition N/A Instrument Hoses, Etc.)

ENGINE AND ENGINE ACCESSORIES

Engine PT6A-25 4,500 Hours AESR Fuel Control Unit 3244746-5, -6, -8, -9 or -10 4,500 Hours (High time) OPNAV 4790/28A Fuel Control Unit 3244746-5, -6, -8, -9 or -10 3,000 Hours/6 Years (Mid-Life) OPNAV 4790/28A High Pressure Fuel Pump 025323-101-02 or –03 4,500 Hours OPNAV 4790/28A Torque Controller 3244749-3 and 3244756-1, 4,500 Hours OPNAV 4790/28A -2 or –4 Bleed Valve 3100829-06 4,500 Hours OPNAV 4790/28A Starter Generator 104-389000-1 900 Hours - (See Note 4) OPNAV 4790/28A Compressor Turbine Disc 3013411 16,000 Cycles (Scrap) OPNAV 4790/106A Power Turbine Disc 3022412 20,000 Cycles (Scrap) OPNAV 4790/106A Hub 3013111 19,000 Cycles (Scrap) OPNAV 4790/106A Second Compressor Stage 3013712 24,000 Cycles (Scrap) OPNAV 4790/106A Third Compressor Stage 3011713 25,000 Cycles (Scrap) OPNAV 4790/106A Impeller 3013176 19,000 Cycles (Scrap) OPNAV 4790/106A

Section III - Page 2

ENGINE AND ENGINE ACCESSORIES (Continued) Primary Propeller Governor 8210-002V 4,500 Hours OPNAV 4790/28A Propeller Overspeed Governor 97-389000-7 4,500 Hours OPNAV 4790/28A Propeller Assembly HC-B3TN-3H/T10173-11R 3,000 Hours/5 Years - (See Note 5) AESR Propeller Blades T10173-11R 9,634 Hours (Scrap) - (See Note 6) OPNAV 4790/28A

MISCELLANEOUS ITEMS

Nitrogen Cylinder, Canopy Opening 104-384003-5 or -7 Hydrostatic test every 5 years. OPNAV 4790/28A Scrap at 24 years (See Note 7).

Nitrogen Filler Valve MS28689-1 12,000 Hours (See Note 8) N/A Oxygen Cylinder 801293-09 Hydrostatic Test every 3 years. OPNAV 4790/28A Scrap at 24 years (See Note 7) or 4,380 refills, whichever occurs first - (See Note 9).

Oxygen Regulators 29255-6BA19A 210 Days - (See Note 10) OPNAV 4790/138 Forward and Aft Evaporator - 104-384002-3 and -5 600 Hours - Inspect and/or OPNAV 4790/113 Blower Motors replace the brushes. – (See Note 11) Altimeters Front and Rear Cockpit 24 Months - Recertify - (See Note 12) N/A (See Parts Catalog) Aircraft Transponder Systems N/A 24 Months Maximum – Recertify N/A Aircraft Pitot and Static Systems N/A 24 Months Maximum – Recertify N/A Emergency Locator Transmitter, 452-0130 Replace at expiration date noted on battery or N/A Battery if ELT is used more than 1 cumulative hour.

Aircraft Compass System N/A 12 Months - (See Note 13) N/A

Section III - Page 3

WING NUTS AND BOLTS - INCONEL (Beech Mandatory Service Bulletin Number 2487) Lower Forward 104-1000-3 S Fifteen Years - (See Note 14) N/A (Kit Part Number) Lower Aft 104-1000-7 S Fifteen Years - (See Note 14) N/A (Kit Part Number) Upper Forward 104-1000-5 S Fifteen Years - (See Note 14) N/A (Kit Part Number) Upper Aft 104-1000-9 S Fifteen Years - (See Note 14) N/A (Kit Part Number) Panel Mounted “G” Meters 104-384106-1 24 Months – (See Note 15) OPNAV 4790/113 Fuel Cells All Part Numbers 17 Years – (See Note 16) N/A

MAXIMUM OPERATING TIME (MOT) NOTES

GENERAL NOTE: The Maximum Operating Time (MOT) listed for each item is the time at which the item must be removed for disposition. All items removed at the indicated MOT will be overhauled unless specifically indicated otherwise; i.e., scrap, test and check, etc.

The CALENDAR LIFE LIMIT on all items, if assigned, is calculated from the date of fabrication or overhaul. If a CALENDAR LIFE LIMIT IS NOT assigned, removal for overhaul is calculated utilizing the number of landings, cycles, events, etc. accumulated at the time of installation. Both of the foregoing rules will hold true unless otherwise indicated for a specific item.

For those items HAVING an assigned CALENDAR LIFE LIMIT, the items will continue to accumulate calendar time whether it is on the shelf or installed in an aircraft. If installed the Calendar Life continues to accumulate whether or not the aircraft is in a reporting (A30) status.

Authorized/published deviations to the foregoing statements pertaining to CALENDAR LIFE LIMITS are as noted in Notes 3 and 4 below.

NOTE 1: The five (5) year calendar limit starts from the date of installation on the aircraft NOT from the date of manufacture.

Section III - Page 4

NOTE 2: Assemblies having an “R” at the end of the serial number (ones that have been repaired) require a Non Destructive

Inspection (NDI) to be performed every 2,000 landings based upon the date of the installation following the repair. The NDI can be performed utilizing either a Liquid Dye Penetrant or Magnetic Particle Inspection Method. Mechanical stripping methods are only authorized if the assembly is to be inspected using the Magnetic Particle NDI inspection method otherwise the assembly is to be stripped utilizing a suitable approved chemical stripper.

Assemblies not identified with an “R” at the end of the serial number will be removed during ACI, will be entirely stripped and have an in-depth NDI of the total assembly performed utilizing the Magnetic Particle Inspection Method. Mechanical stripping using Plastic Media Blast is authorized when the NDI is being accomplished using the Magnetic Particle NDI inspection method.

NOTE 3: All hoses requiring identification tags to be attached that are missing, or are not readable, or hose assemblies exceeding the time limits established for a particular installation will be removed from the aircraft at the earliest convenience, but no later than the next ACI.

NOTE 4: Brushes must be inspected every 300 hours and replaced upon condition or when the maximum permissible wear point has been reached. At 900 hours the unit must be removed and the bearings inspected.

NOTE 5: Hartzell Service Letter 61U (Overhaul Periods and Service Life Limits for Hartzell Propellers and Governors) states; "Start date for calendar limit is when the propeller is first installed on an engine. Calendar limit IS NOT interrupted by subsequent removal and/or storage." The Service Letter implies that in order to get the full 5 year calendar life limit for propellers that are stored less than 2 years (ones that HAVE NOT been installed on an engine since new or overhaul), the requirements published in Hartzell's Standard Practice Manual Number 202A must be complied with prior to installation. The requirements in the 202A stipulate a review of the current technical data to ensure any mandatory requirements issued since the unit was manufactured or overhauled are complied with, and performance of a general/visual inspection and correction of any discrepancies noted.

For those propellers that have been stored in excess of 2 years, the propeller must be disassembled and inspected for internal corrosion and all seals and lubricants must be replaced. The 202A further states that an approved FAA Propeller Repair Station must perform the inspection. After that has been accomplished the propeller may be released for service.

Hartzell's Standard Practice Manual Number 202A also include "Guidelines" for packaging of assembled and disassembled propellers. "Hartzell recommends inspecting stored items every 6 months to ensure no corrosion is developing and to replace moisture retardant."

NOTE 6: In accordance with Hartzell Manuals 133C (Aluminum Blade Manual) and 118F (Steel Hub Propellers) propeller blades have the same overhaul intervals as the hubs in which they are installed.

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

Section III - Page 5

NOTE 7: The time count for the Hydrostatic Test Date for NEW MATERIAL commences at the time the item is initially placed in service/installed. For previously used material the removal date shall be calculated from the date of the last Hydrostatic Test.

The 24 year life-limit and the 5 year hydrostatic test requirement of the “NITROGEN CYLINDER” is specified in accordance with the specification number DoT-E 8299, which is a special classification, under which the Pacific Scientific part number 36200021-1 and -2 (RAC part number 104-384003-5) is registered with the DoT.

NOTE 7 (Continued): The 24-year life-limit, the 3-year hydrostatic test requirement, and the 4,380 fillings/pressurizations for the “OXYGEN CYLINDER” is as specified in specification number DoT-3HT.

NOTE 8: The valve is changed upon condition. Filler valve assemblies are not serialized or tracked as a separate item. The life limit of 12,000 hours for the filler valve indicated in the T-34C Maintenance Manual is not exceeded when considering the 18-year life-limit of the bottle. The 12,000-hour limit divided by the 18 year DoT limit equates to an average accumulation of 667 flight hours per year, providing the bottle was installed/in service continuously over 18 years. The regulator and filler valve assembly is processed as part of the assembly during the 5-year hydrostatic test.

NOTE 9: For information purposes, 4,380 fillings equate to 182.5 fillings per year or 3.5 fillings per week over the 24-year life limit of the oxygen cylinder. Per a decision reached in the early eighties based upon historical filling data/cycles, fillings are not tracked.

The 24-year life-limit, the 3 year hydrostatic test requirement, and the 4,380 fillings/pressurization’s for the oxygen cylinder is as specified in specification number DoT-3HT.

NOTE 10: New oxygen regulators must be tested and checked prior to being placed in service. For new and previously used regulators, the removal time shall be calculated from the date of the last test and check or, overhaul and repair.

NOTE 11: The brushes in the 104-384002-3 units are in fact inspected and/or replaced at 600 hours. The brushes in the 104-384002-5 units cannot be removed and inspected. They are replaced when the blower fails.

NOTE 12: All altimeters are due for certification 24 months from the date of certification provided with the unit regardless of the history of the item; e.g., new, used, reconditioned, repaired or overhauled. Certification is accomplished in accordance with the requirements specified in MED PR-50.

NOTE 13: A compass swing is also required any time the Flux Valve/Detector is changed, an engine is changed or any major component is changed that may effect the magnetic field/properties of the aircraft.

NOTE 14: Hardware is required to be removed every 5 years and inspected in accordance with the T-34C Maintenance Manual. The hardware may be reused an additional 5 years, removed, inspected and reused again. The maximum life limit for the hardware (bolt and nut) is 15 years. Additional Pertinent Information:

• L-3 Vertex Maintenance Instruction Number N00-234 provides detailed instructions on method used to age mark the wing mounting hardware for ease of tracking and identification.

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

March 1, 2005 Section III - Page 6

• L-3 Vertex Maintenance Number N00-239 provides guidance relative to extending wing-mounting hardware in service for an additional ninety (90) days maximum. Concurrence by both Raytheon Aircraft and the NAVAIR T- 34C APMSE to extend the hardware in service is attached to the Maintenance Instruction.

NOTE 15: Panel Mounted “G” Meter Indicators are to be removed and sent to the vendors to be cleaned, tested and repaired as required on a 24-month interval. This applies to those indicators that have had an OPNAV 4790/113 Equipment History Record (EHR) established on them. This indicates that NAVIR PMA 273 Jim Ball Memo Serial JB04-05 and the provisions of L-3 Vertex Aerospace EZ Letter 92-04-0089 dated 31 August 2004 have been implemented.

NOTE 16: All fuel cells removed for processing may automatically be disposed of, if the date of manufacture, which is usually part of the serial number or is stamped elsewhere on the cell indicates the fuel cell is greater than 17 years old or greater from the date of manufacture. Fuel cells without any markings that indicate the date of manufacture shall be disposed of vice being processed for repair.

Section III - Page 7

SECTION IV

AUTHORIZED DEVIATIONS

AUTHORIZED DEVIATIONS

The general rule pertaining to deviations for scheduled maintenance and forced removal items is plus or minus ten percent (10 %) or plus or minus three (3) days unless otherwise delineated in their source or controlling documents. When a deviation is utilized the next like inspection is due as if no deviation were taken. Exceptions to the foregoing rule are listed below:

ITEM/INSPECTION HOURS/DAYS/LANDINGS DEVIATION

Engine 4,500 Hours + 0 or - 100 Hours or Cycles

Propeller * 3,000 Hours or 5 Years - 30 Days or - 100 Hours

All Landing Gear and Flap Components * 5 Years or 8,000 Landings - 30 Days or - 100 Landings

Torque Knees ** 4,000 Landings + 0 or - 10 %

Wing Bolts *** 5 Years + 90 Days

Aircraft Wash 14 Days + 3 or - 3 Days

Corrosion Control Inspection 56 Days + 3 or - 3 Days

Engine Oil Samples **** 25 Hours + 0 or - 5 Hours

NOTE: Calendar time for NEW and/or OVERHAULED propellers commences at the date of the initial installation. Refer to Note Number 5 in Section 3 of this document.

* = Calendar time limits are calculated from the completion date (month) of the last overhaul.

** = Intermediate inspection requirements.

*** = See Note 12 in Section III, the Mandatory Removal Schedule Listing.

**** = The meantime between oil samples is 25 hours. The only deviation allowed to the normal established interval is a minus five (- 5) hours. The next sample is due 25 hours later.

Only aircraft assigned to a cross-country flight operation may deviate from the mandated 20-25 hour requirement. These aircraft are authorized up to a maximum of 40 hours between samples.

Any aircraft returning from a cross-country flight that have exceeded 25 hours since the last sample shall be sampled immediately upon return from the flight.

If a sample has to be taken late (no later then 40 hours since last sample) as the result of a cross-country flight then the next normal sample is due a maximum of 25 hours later.

NOTE: When an engine is sent out for repair it does not always have an HSI performed on it in conjunction with the repair unless specifically requested by the Engine Manager. When placing a repaired engine back in service, ensure that the next HSI due is thoroughly researched in the records and the MIS properly annotated to preclude over flying the HSI due time of 1,800 hours, which for information purposes has a plus or minus 10 percent leeway.

Section IV – Page 1

SECTION V

PREFERRED SPARES

LISTING

PREFERRED SPARES FOR T-34C AIRCRAFT

NOMENCLATURE OLD PART NUMBER NEW PART NUMBER AUTHORIZATION/REFERENCE

Emergency Locator Transmitter (ELT) ELT 10 ELT 110-6-003 SI # T-34C-0185, Revision 1 Wet Compass C2400L4P1AC C2475-L4P-24B CNATRA Letter 4330/N231B1, Feb 91 Course Deviation Indicator (CDI) 622-2955-001/002 066-03034-0026 NAVAIR 111219Z Sep 92 Oil Pressure Transducer 101-389023-1 APTE-7KBS-1500-200G NADOC 231431Z Mar 90 Flux Detector 522-4945-001 2594484 NAVAIR 201119 Aug 93 Transponder Board Interface Connector Electro Enterprise, Inc. P/N DDMA-50 EVD50F-1000S NAVAIR 151219Z Jun 94 Aircraft Battery M83769/4-1, NSN 6140-00-135-0229

Flooded Lead Acid (FLA) RG-390E Sealed Lead Acid (SLA) NAVAIR 221219Z JUN 00 and

CNATRA 051605Z Jul 00 255 Bulkhead With SI-186 Reinforcement Channel Included

45-410377-10/-601 45-410377-18 RAC Change Order Number G85600 and G85601

Air-Conditioning High Pressure Switch 26PS101BA380K280W 29PSL012-219 RAC Change Order Number G86155 For Drawing 104-555010

Auto Ignition Switch NSN 5930-00-509-2450 50-389121-1 (See Note 1) 1996 and 1997 MELR MLG Uplock Roller Bearing NAS 505-6 or NSN 3110-00-227-2802 MS 24461-6 (Advice Code 2B) CNATRA 231405Z Oct 98 ICS Cord Material 131085-22D6 M5898-WM85U5, NSN 6145-00-635-1536 CNATRA 161450Z Mar 98 ICS Cord Amplifier CE655TR CP-03225 CNATRA 311405Z Mar 00 MLG Uplock Roller Bearing and Mounting Bolt

MS-24461-6 and 60-810026-53 KRP205106VTZ and NAS464-6-28, NSN 5306-00-576-5913

CNATRA 151405Z Aug 00

MED ATA 32-30-00/PR-14

Attitude Indicator 104-384022-3 129920-5 (See Note 2) NAVAIR 011219Z Sep 02 Landing Gear Power Circuit Breaker 507-230-101 (30 Amp) MS25244-15 (15 Amp) AFC 82 - NAVAIR 170819Z Oct 00 Fire Detector 30-215-8 473275 NAVAIR 152101Z Nov 01 and

CNATRA 101615Z Dec 01 Brake Assembly Bolts 103-11600 AN4H17A NAVAIR 111827Z Apr 01 and

CNATRA 031605Z May 01 Landing Gear Integrated Circuit Chip LM2905M LM122H NAVAIR 271655Z Aug 01 and

CNATRA 121405Z Oct 01 60 Ampere Utility Circuit Breaker 109-260-101 MS25361-60 NAVAIR 221922Z Mar 01

CNATRA 311625Z May 01 Inertial Reel MA-6/MA-8 or 45-534153

NSN 1680-00-775-4182

MA-16 or 015-870145-3-16

NSN 1680-01-437-0396

AFC 83 – NAVAIR Letter Code 4790 Serial PMA 207.5E1/061of 26 Apr 02

Section V – Page 1

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

Section V – Page 2

PREFERRED SPARES FOR T-34C AIRCRAFT (Continued)

NOMENCLATURE OLD PART NUMBER NEW PART NUMBER AUTHORIZATION/REFERENCE

Brake Master Cylinder VVI-15-750 CM6000-2 and 104-384061-3 AFB 60 – NAVAIR 291800Z Aug 01 Master Cylinder Supply Line Fitting 4C50X-S NA921D04 AFB 60 – NAVAIR 291800Z Aug 01 Starter Generator 104-389001-1 200SG116Q-1 (See Note 3) STC SA01198NY Parachute NB 6 NB 8 (See Note 4) Memo JB02-18 Dated 11 June 2002 Gasket 476284, Pump Assembly 479136 (See Note 5) NAVAIR PMA207 291711Z Jul 02 and

CNATRA 051515Z Aug 02 Screen/Filter 476284, Pump Assembly 479729 (See Note 5) NAVAIR PMA207 291711Z Jul 02 and

CNATRA 051515Z Aug 02 Environmental Fuel Pump 476284, 133-920010-1 or 133-920010-3

Pump Assembly CA476284E PEOASWASM Patuxent River, MD

061833Z Jul 04 and CNATRA 271454Z Jul 04

NOTE 1: When ordering NSN, ensure Advise Code 2B (Do Not Substitute) is utilized. Before installing verify part number on data plate of the unit.

NOTE 2: Astronautics part number approved for use but never manufactured.

NOTE 3: The Aircraft Parts Corporation starter was qualified on the aircraft for use in the event that the original starter no longer can be procured or overhauled at a reasonable price.

NOTE 4: This parachute is qualified for use in the T-34C aircraft and for use at the discretion of the operating command.

NOTE 5: Gasket and Filter are procured in lieu of a new Pump Assembly.

DEFINITIONS

INSPECTION PROCEDURES

HOSE ASSEMBLIES

ENGINE AND ENGINE ACCESSORIES

MISCELLANEOUS ITEMS