ATT 78 01-50-T44A-600-6 .pdf

NAVAIR (PMA 273) 01-50-T44A-600-6

U.S. NAVY T-44A

PEGASUS

CONTINUOUS INSPECTION

PROCEDURES MANUAL

January 1, 2013

ATTACHMENT 78

NAVAIR (PMA-273) 01-50-T44A-600-6 N61340-18-FOSR-0001

PAGE EFFECTIVITY LISTING

Summary:

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

November 1, 2005.

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

Page(s) Change Number Date Comments

Cover NA 1/1/2013 Changes Not Bar Marked i NA 1/1/2013 Changes Not Bar Marked ii NA 1/1/2013 Changes Not Bar Marked iii NA 1/1/2013 Changes Not Bar Marked iv NA 1/1/2013 Changes Not Bar Marked

Section I NA 1/1/2013 Changes Not Bar Marked Section II NA 1/1/2013 Changes Not Bar Marked Section III NA 1/1/2013 Changes Not Bar Marked Section IV NA 1/1/2013 Changes Not Bar Marked Section V NA 1/1/2013 Changes Not Bar Marked

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.

TECHNICAL INFORMATION REPORT, DISCRPANCY (TIRD)

CHANGE RECOMMENDATION

(TO BE FILLED IN BY ORIGINATOR)

REPORT DATE: __________________________________

FROM (Originator): ________________________________ ACTIVITY: ________________________________________

ADDRESS AND/OR E-MAIL OF ORIGINATOR:________________________________________________________________

SEND COMPLETED FORM TO:

NAVAIRSYSCOM

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

22581 SAUFLEY ROAD, BUILDING 3258

PATUXENT RIVER, MARYLAND 20670

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

DEFICIENCY: ____________________________________________________________________________________________

RECOMMENDATION (Be Specific): __________________________________________________________________________

_________________________________________________________________________ Check if continuation sheets or drawings attached.

IMPACT: _________________________________________________________________________________________________

REPORT BY: _____________________________________________

SIGNATURE:_____________________________________________ TITLE:________________________________________

TO BE FILLED IN BY PMA-273

FROM: __________________________________________________ DATE: ________________________________________

TO: _____________________________________________________

REFERENCE:_______________________________________________________________________________________________

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

INSTRUCTIONS FOR COMPLETING THE TIRD

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

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

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

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

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

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

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

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

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

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

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

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

SECTION I

GENERAL INFORMATION

H90 (T-44A) CONTINUOUS INSPECTION PROGRAM

The BEECHCRAFT Model H90 (Navy T-44A) Maintenance Manual contains a listing of Beech, Navy and Vendor publications that may be used to provide service and maintenance information supplementary to that provided in the Maintenance Manual and the BEECHCRAFT Model H90 (Navy T-44A) Continuous Inspection Procedures Manual. The Federal Aviation Regulations Manual, Parts 43 and 91 contain the regulations concerning 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 of Beech Aircraft, when warranted by service experience or engineering recommendations. Information contained herein is applicable to all Model H90 (Navy T-44A) 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-44A 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.

The time periods for inspections noted in this manual is 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 Model H90 (Navy T-44A) Maintenance Manual (P/N 92-38879, dated June 30, 1998 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.

GENERAL INFORMATION

PURPOSE AND USE

The Continuous Inspection Procedures are designed to maintain the BEECHCRAFT Model H-90, Navy T-44A 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

The Federal Aviation Administration in accordance with Federal Aviation Regulations, Parts 43 and 91, issues terminology pertaining to inspection procedures and their use in this manual. 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 and 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 preservation 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 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 Power Assurance Run - This form is used to record engine, propeller and environmental system checks as part of each 100-Hour Detailed Inspections.

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 01-50-T44A- 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 than 72 clock hours have transpired since the last Daily Inspection was completed.

ENGINE POWER ASSURANCE RUNS (100-Hour Intervals) An Engine Power Assurance Run shall be conducted on each aircraft in conjunction with each 100-Hour Detailed Inspections. 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 a Power Assurance Run is contained in Section IV of this manual.

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.

DISCREPANCIES

Discrepancies found on the aircraft during an inspection will be listed on the "Continuous Inspection Work Sheet." Three 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 than 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 a 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 are accomplished 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 Wings; Wing center section; Main landing gear and brakes;

Nose landing gear; Landing gear operational checks; Nose Section; Air conditioning and pressurization; Rear fuselage and empennage; Power plants; Air stair door; General servicing items; Engine wash and power assurance run; and Operational checks.

200 2nd Detailed Inspection General aircraft interior; Pilot’s compartment; landing gear, wheels and tires; Cabin section; General aircraft interior final; Fire detector/suppression: Nose section; Forward spars; Power plants; Engine wash and power assurance run;

Operational inspection; and General servicing items.

SECTION II

INSPECTION

REQUIREMENTS MATRICES

HOURLY REQUIREMENTS

T-44A CONTIN

UOUS IN

SPECTIO

N PROCEDURES M

ANUAL -

NAVAIR (P

M

A-273) 0 1-50-T44A-600-6

T-44A M

AIN

TENANCE M

ANUAL

MED ATA 27-00-00/PR-60

PRATT AND W

HITNEY M

AINTENANCE M

ANUAL

MED ATA 52-10-00/PR-47 REV A

MED ATA 79-00-00/PR-51

MED ATA 73-00-00/PR-62

MED ATA 26-10-00/PR-56

MED ATA PR32-40-00/P

R-84

MED PR-103 (F

LE

IN

SPECTIO

N)

NAVAIR (P

M

A-273) 0 1-50-T44A-600-6-3

1ST 100 HOUR SCHEDULED INSPECTION X

2ND 100 HOUR SCHEDULED INSPECTION X

25 HOUR ENGINE OIL SAMPLE X

100 HOUR WING BOLT RE-TORQUE, AFTER INTIAL INSTALL X

100 HOUR FIRE DETECTOR SENSITIVITY CHECK * X

100 HOUR WHEEL BEARING REPACK REQUIREMENT X

200 HOUR AIR STAIR DOOR FRAME INSPECTION ** X X

300 HOUR STARTER GENERATOR BRUSH INSPECTION X

300 HOUR STARTER GENERATOR SPLINE LUBRICATION X

300 HOUR STATIC WICK INSPECTION X

500 HOUR INSTRUMENT AIR FILTER REPLACEMENT X

500 HOUR FLOW CONTROL UNIT FILTER INSPECTION X

500 HOUR FUEL PUMP SPLINE CAVITY INSPECTION X

600 HOUR FUEL NOZZLE INSPECTION X

600 HOUR COMPRESSOR TURBINE BORESCOPE INSPECTION X

600 HOUR AILERON/ELEVATOR/RUDDER CABLE TENSION CHECK X

1,000 HOUR ENGINE OIL CHANGE X X

1,200 HOUR STARTER GENERATOR BRUSH AND BEARING INSPECTION X

1,200 HOUR NACELLE SPLICE PLATE INSPECTION *** X

1,800 HOUR HOT SECTION INSPECTION ***** X X

2,500 HOUR/FUEL CONTROL MID-LIFE INSPECTION = 250 hrs X

3,700 CENTER SECTION INSPECTION *** X

5,000 LANDING FLAP/LANDING GEAR TBO **** X

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

PACKAGES.

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

*** APPLIES ONLY TO AIRCRAFT THAT HAVE BEEN INSPECTED IAW REQUIREEMENTS

SPECIFIED IN MED PR-103 ALSO, ACCOMPLISHED AT EACH ACI ON THOSE AIRCRAFT THAT

HAVE HAD THE MED ACCOMPLISHED ON THEM WHETHER IT IS DUE OR NOT TO BE

ACCOMPLISHED/RENEWED. THE TIME/HOURS TO THE NEXT INSPECTION DUE ARE RESET TO

ZERO HOURS AT THE TIME OF THE INSPECTION.

**** ACCOMPLISHED CONCURRENT WITH 5 YEAR FLAP/LANDING GEAR TBO.

***** WHEN PLACING A REPAIRED ENGINE BACK IN SERVICE, ENSURE THAT THE NEXT

HOT SECTION INSPECTION (HSI) DUE IS THOROUGHLY RESEARCHED IN THE ENGINE LOG

BOOK AND THE MIS IS THOROUGHLY ANNOTATED TO PROCLUDE OVERFLYING THE

INSPECTION REQUIREMENT INTERVAL.

CALENDAR REQUIREMENTS

T-4 4 M

AIN

TENANCE M

ANUAL

NAVAIR T-44A CORROSIO

N CONTROL P

LA

N

ONAVIN

ST 4790.2 (S

ERIES)

T44A COTIN

UOUS IN

SPECTIO

N PROCEDURES M

ANUAL

NAVAIR T44A/C ACI M

ANUAL

M

ED ATA 31-0

0-00/PR-110

NAVAIR 15-01-500

NAVAIR (P

M

A 273) 0 1-50-T44A-6-2

NAVAIR (P

M

A 273) 0 1-50-T44A-6-3

DAILY/TURN AROUND INSPECTION X

DAILY ENGINE RINSE X

DAILY LEVEL I PRESERVATION INSPECTION X X

7 DAY LEVEL I PRESERVATION INSPECTION X X

7 DAY LUBE X X

7 DAY TIRE INFLATION X

14 DAY AIRCRAFT WASH AND LUBE X

28 DAY LEVEL I PRESERVATION INSPECTION X X

56 DAY CORROSION INSPECTION X

ANNUAL WING BOLT TORQUE CHECK AND LUBE X

ANNUAL COMPASS WING X

ANNUAL ELT TEST X

24 MONTH AIRCRAFT ALTIMETER/PITOT STATIC SYSTEM X

5 YEAR FLAP/LANDING GEAR TBO * X

60 MONTH AIRCRAFT CONDITION INSPECTION X

*ACCOMPLISHED CONCURRENT WITH 5000 LANDINGS FLAP/LANDING GEAR TBO

AIRCREW LIFE SUPPORT SYSTEMS

NAVAIR 13-1-6.7-2

NAVAIR (P

M

A 273) 0 1-250-13-600-011-6.2

NAVAIR (P

M

A273) 0 1-250-13-600-0

16-6.2

NA13-1-6

.5

NAVAIR (P

M

A 273) 0 1-250-13-6

00-004-6.2

NAVAIR (P

M

A 273) 0 1-250-13-6

00-005-6.2

NAVAIR (P

M

A 273) T 16-13-6

00-145-6-2

2499-101 SW

EEP O

N FULL

FACE O

XYGEN M

ASK M

ANUAL

NA13-1-6

.1-2

NA16-30-P

RC-90-2

30 DAY T-44 ALSS Equipment Inspection X X

90 DAY LPU-32/P INSPECTION X

360 DAY PERSONAL FLIGHT GEAR INSPECTION (All Pilots) x

90 DAY AV-8 INSPECTION x

360 DAY LIFE RAFT INSPECTION X X X

180 DAY CABIN FIRE EXTINGUISHER INSPECTION X

90 DAY Pilot's Clipboard Inspection (Kneeboard) x

360 DAY T-44 First Aid Kit Inspection x

360 DAY T-44 Oxygen Mask Visual/Fuctional Inspection x

12 Year Replacement Full Face Oxygen Mask x

SECTION III

MANDATORY SCHEDULED

COMPONENTS REMOVAL

LISTING

January 1, 2013

T-44A COMPONENTS

MANDATORY SCHEDULED REMOVAL LIST

MAXIMUM OPERATING TIME (MOT)

LANDING GEAR AND FLAP SYSTEMS

NOMENCLATURE PART

NUMBER

(HOURS, YEARS OR

LANDINGS) TYPE RECORD

Landing Gear, L/H Main 50-810304-677 5,000 Landings/5 Years 4790/28A Landing Gear, R/H Main 50-810304-678 5,000 Landings/5 Years 4790/28A Landing Gear, Nose 97-820000-652 5,000 Landings/5 Years 4790/28A Landing Gear Actuator, L/H Main - Overhaul

50-810164-17 5,000 Landings/5 Years 4790/28A

Landing Gear Actuator, L/H Main - Repack

50-810164-17 1,000 Landings, disassemble and lubricate IAW MED PR-28

4790/28A

Landing Gear Actuator, R/H Main - Overhaul

50-810164-18 1,000 Landings, disassemble 4790/28A

Landing Gear Actuator, Nose - Overhaul

50-820208-5 1,000 Landings, disassemble and lubricate IAW MED PR-28

4790/28A

Retract Motor 91-380002-3 5,000 Landings/5 Years 4790/28A Retract Gearbox 91-810010-3 5,000 Landings/5 Years 4790/28A Flap Motor Assembly 100-384040-3 5,000 Landings 4790/28A Flap Gearbox 100-524074-1 5,000 Landings 4790/28A Flap Actuator, L/H Inboard 50-521222-3 5,000 Landings 4790/28A Flap Actuator, R/H Inboard 50-521222-4 5,000 Landings 4790/28A Flap Actuator, L/H Outboard 50-521223-3 5,000 Landings 4790/28A Flap Actuator, R/H Outboard 50-521223-4 5,000 Landings 4790/28A Torque Knee, MLG Upper 50-810032-6 2,500 Landings – Inspect IAW MED

PR-43

4790/28A

50-810032-12 5,000 Landings 4790/28A Torque Knee, MLG Lower 50-810295-17 2,500 Landings – Inspect IAW MED

PR-43

4790/28A

50-810295-25 5,000 Landings 4790/28A Torque Knee, NLG Upper 50-810032-8 2,500 Landings – Inspect 4790/28A 50-810032-12 5,000 Landings 4790/28A Torque Knee, NLG Lower 50-810295-19 2,500 Landings – Inspect IAW MED

PR-43

4790/28A

50-8120295-29 5,000 Landings 4790/28A

HOSE ASSEMBLIES

NOMENCLATURE PART

NUMBER

(HOURS, YEARS OR

LANDINGS) TYPE RECORD

Flammable Liquid Carrying All Every 5 years from date of Hoses, Airframe Related installation, as etched on tag - (See Note 1).

N/A

MAXIMUM OPERATING TIME (MOT)

HOSE ASSEMBLIES (cont)

NOMENCLATURE PART NUMBER (HOURS, YEARS OR

LANDINGS) TYPE RECORD

Flammable Liquid Carrying Hoses, Power plant Related

All On condition as determined during engine overhaul in accordance with the OEM's technical data.

N/A

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

All On Condition N/A

ENGINES AND ACCESSORIES

NOMENCLATURE PART NUMBER (HOURS, YEARS OR

LANDINGS)

TYPE

RECORD

Engine PT6A-34B 5,000 Hours AESR Fuel Control Unit 3244777-1 5,000 Hours 4790/28A Fuel Control Unit 3244777-1 2,500 Hours Midlife Inspection (+ or

– 250 hrs) 4790/28A

High Pressure Fuel Pump 3019044E 5,000 Hours 4790/28A Start Control 3019109 2,500 Hours (+ or – 250 hrs) 4790/28A Bleed Valve 3100829-03 5,000 Hours 4790/28A Starter Generator 100-389005-11 300 Hours - (See Note 2) 4790/113 Compressor Turbine Disk 3013411/3102421-01 16,000 Cycles (Scrap) 4790/28A Power Turbine Disk 3026812 20,000 Cycles (Scrap) 4790/28A First Stage Compressor Hub 3013111 19,000 Cycles (Scrap) 4790/28A Second Stage Compressor Disk

3013712 24,000 Cycles (Scrap) 4790/28A

Third Stage Compressor Disk

3011713 25,000 Cycles (Scrap) 4790/28A

Impeller 3013176/3033292 19,000 Cycles (Scrap) 4790/28A Primary Propeller Governor 8210-002V 5,000 Hours 4790/28A Propeller Overspeed Governor

97-389000-3 5,000 Hours 4790/28A

Propeller Assembly HCB3TN3BT10173B8 3,000 Hours/5 Years (See Notes 3 and 4)

AESR

MISCELLANEOUS ITEMS

NOMENCLATURE PART NUMBER (HOURS, YEARS OR

LANDINGS)

TYPE

RECORD

Engine Fire Extinguisher Squib

13083-5 (M-193) 16yr (Mfg date) or 7 yr (CO date) (See Note 5)

4790/28A

Engine Fire Extinguisher Container, Bottle

2-102710-1 (WB53)

861-006

14yr (Mfg date) or 6 yr (CO date) (See Note 5)

4790/28A

Fuel Crossfeed Valve 50-389095 5 Years (See Note 6) 4790/28A

MAXIMUM OPERATING TIME (MOT)

MISCELLANEOUS ITEMS (cont)

NOMENCLATURE PART NUMBER (HOURS, YEARS OR

LANDINGS) TYPE RECORD

Firewall Shutoff Valve 101-389025-3 5 Years 4790/28A Oxygen Mask 174660-23 12 Years 4790/28A Oxygen Cylinder ZC425-49 Hydrostatic test every 3 years. Scrap at 24 years - (See Note 6) or 4,380 refills, whichever comes first - (See Note 7).

4790/28A

Altimeters Pilots and Copilots 24 Months - Re-certify (See Note 8) N/A Aircraft Transponder Systems

N/A 24 Months Maximum - Re-certify N/A

Aircraft Pitot and Static Systems

N/A 24 Months Maximum - Re-certify N/A

Emergency Locator Transmitter - Battery (121.5 MHz)

50659-0101 Replace at expiration date noted on battery.

N/A

Aircraft Compass System N/A 12 Months - (See Note 9) N/A

WING NUTS AND WING BOLTS

NOMENCLATURE PART NUMBER (HOURS, YEARS OR

LANDINGS)

TYPE

RECORD

Lower Forward 80691CF-1414 (Nut) 81784-14-46 (Bolt)

Fifteen Years - (See Note 10) N/A

Lower Aft 81791-1018 (Nut) 81786-10-18 (Bolt)

Fifteen Years - (See Note 10) N/A

Upper Forward 81791-1216 (Nut) 81785-12-23 (Bolt)

Fifteen Years - (See Note 10) N/A

Upper Aft 81791-1018 (Nut) 81786-10-18 (Bolt)

Fifteen Years - (See Note 10) N/A

Fuel Cells All Part Numbers 17 Years – (See Note 11) N/A

MAXIMUM OPERATION 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 4 and 5 below.

NOTE 1: 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 2: Brushes must be inspected every 300 hours and replaced upon condition - when the maximum permissible wear point has been reached. At 1,200 hours Equipment Operating Time (EOT) the unit must be removed and overhauled by a FAA certified repair facility.

NOTE 3: Hartzell Service Letter HC-SL-61Y, dated 5/11/2006, (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 vol.11 must be complied with prior to installation. The requirements in the 202A vol. 11 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 vol. 11 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.

NOTE 4: 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.

NOTE 5: The maximum installed life shall not exceed the Container Open Date or the Manufacture Date.

NOTE 6: The time count for the Hydrostatic Test Date for NEW MATERIAL commences at the time the item is initially placed in service/installed. For used material the removal date shall be calculated from the date of the last Hydrostatic Test.

NOTE 7: 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 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/pressurizations for the oxygen cylinder is as specified in specification number DoT-3HT.

NOTE 8: 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-110.

NOTE 9: A compass swing is also required any time the Flux Valve/Detector is changed, a dual engine change or any major component is changed that may affect the magnetic field/properties of the aircraft.

NOTE 10: Hardware is required to be removed every 5 years and inspected in accordance with the T-44A 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:

Raytheon Maintenance Instruction Number 97-061 R1 Dated 1 April 1998 provides detailed instructions on how to age mark the wing mounting hardware for ease of tracking and identification.

Raytheon Maintenance Number 98-067 Dated 10 November 1998 provides guidance relative to extending wing-mounting hardware in service for an additional maximum of ninety (90) days. Concurrence by both Raytheon Aircraft and NAVAIR PMA 273 to extend the hardware in service is attached to the Maintenance Instruction.

NOTE 11: If a fuel cell is removed for processing (Repair) and it is 17 years old or older do not process the fuel cell for repair, scrap it and order a new cell. (In accordance with MED PR-107)

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 was taken. Exceptions to the foregoing rule are listed below:

ITEM/INSPECTION HOURS/DAYS/LANDINGS DEVIATION

Engine 5,000 Hours + 0 or - 100 Hours

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

All Landing Gear and Flap Components

5 Years or 5,000 Landings - 30 Days or - 100 Landings

** Torque Knees 2,500 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

**Intermediate inspection requirements.

***See Note 10 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.

SECTION V

PREFERRED SPARES

LISTING

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

NOMENCLATURE OLD PART NUMBER NEW PART NUMBER AUTHORIZATION/REFERENCE

Oil Pressure Transducer 101-389023-3 APTE-7KBS-1500-200G NADOC 281231Z Nov 90

Upper Beacon 50-634261-15 HRDF-D28R T-44A AFC # 07

Lower Beacon G7740A7-24 HRDF-D28R T-44A AFC # 07

Sun Visor 50-534495-3 640328-103 T-44A AFC # 06

Landing Gear Clutch 404-188913 404-188913.3 NAVAIR 211319Z Sep 92

Fuel Quantity Indicator 100-380006-47 & 101-384151-5 117-384019-3 NAVAIR 041219Z Mar 93

Life Raft C-7 EAM-T6 NAVAIR 191119Z Oct 93

Engine Fire Detector 30-215-8 473275 See AFB # 004, Revision A

Auto Feather Low Pressure Switch

NSN 5930-00-509-2450 50-389121-1 (See Note 1) 1996 and 1997 MELR

Oxygen Mask 174010-03 174260-05 RAC Kit P/N 90-5080-1 & NAVAIR 140419Z Jul 99

O2 Mask Cup Holder 101-530649-7 119302-90 RAC Kit P/N 90-5080-1 & NAVAIR 140419Z Jul 99

Fuel Control Unit 2524440-5 3244777-1 NAVAIR 140419Z Jul 99

Starter Generator 100-389005-11 250SG1140 (See Note 2) CNATRA 311405Z Mar 00 Gasket 476284, Pump Assembly 479136 (See Note 3) NAVAIR PMA207 291711Z Jul 02 and CNATRA 051515Z Aug 02 Screen/Filter 476284, Pump Assembly 479729 (See Note 3) NAVAIR PMA207 291711Z Jul 02 and CNATRA 051515Z Aug 02 Connector DDMA50S EVD50F1000S NAVAIR PMA207 181405Z Sep 02 and CNATRA 251404Z Sep 02 Rudder Pedal Arm 50-524326-27 and 50-524326-28 50-524326-33 and 50-

524326-34 NAVAIR PMA 273211503Z Jan 04 and CNATRA 221524Z Jan 04

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

Prop pitch Control Bolt MS 21125-313 130909B209 CNATRA 281357Z Jul 08

Power Lever Bolt MS 21125-412 130909B207 CNATRA 281357Z Jul 08

Condition Lever Bolt MS 21125-310 130909B172 CNATRA 281357Z Jul 08

Landing Gear Limit Switch 1CH25 1HE1-6 CNATRA 281357Z Jul 08

Engine Fire Extinguisher Squib

13083-5 (M-193) 2-102710-1 (WB53) PMA-273T-44 APMSE Jul 09

U.S. NAVY T-44A