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GE Aircraft Engines

CF34 TURBOFAN ENGINEMAINTENANCE MANUAL

5-11-00TIME LIMITS

Page 801Sep 30/98

LIFE LIMITS OF ROTATING ENGINE PARTS

1. General.

A. The FAA has approved service life-limit cycles (AirworthinessLimitations) for rotating parts installed in the CF34-1A/-3A/-3A2turbofan engines.

B. This chapter identifies engine parts that are life-limited as a resultof exposures to operating cycles or hours. It explains how to calculatelife-limit cycles to allow the operator to determine the number ofcycles at which a part must be removed from service.

C. Rotating parts of all turbine engines have some type of service limits.Critical rotating parts are those parts whose sudden failure couldthreaten the structural integrity of the engine. These parts, whensubjected to large repeated and/or alternating stresses, can failthrough fatigue. The material properties of a part are depleted byfatigue as a function of the number of stress cycles the partexperiences. Stress cycles of turbine engine rotating parts result fromthe transients of engine speed and temperatures occurring during normalengine operation. Therefore, the life-limit cycles provide the operatorwith a means of tracking the useful service life of a part so that thepart can be removed from service before possible fatigue failure. Theselife-limits are usually expressed in terms of cycles, and can berelated almost directly to the number of stress cycles that occurduring engine operation. It is for this reason that the limits are interms of cycles.

D. Life limits of the critical rotating parts are established throughanalysis and testing. Accumulated cycles are compared to the lifelimits to determine if the affected hardware is still serviceable. Nocomponent must be permitted to remain in service beyond its life-limitcycles. Refer to paragraph 2.A. for the definition of a cycle.

E. There are two methods (refer to paragraph 2.E.) available for countinglife-limit cycles; a primary method and an alternate method:

(1) The primary method is simpler than the alternate method, and isappropriate for most aircraft operators.

NOTE: High-utilization operators are defined as operators whosemission requirements generate higher than normal touch-and-golandings, missed approaches, or landings without an engineshutdown.

(2) The alternate method is recommended for high-utilizationoperators because it provides cycle counts more representative oftheir type of aircraft usage.

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(3) The overall cycle counts using the alternate method will be lowerthan the primary method cycle counts because the alternate methoddifferentiates between stresses experienced in different missionoperations. The primary method does not make this distinction asit is of little benefit in general aircraft use.

F. GE Aircraft Engines has completed extensive testing of the engine andits components to provide the basis for the establishment of life limitcycles. GE Aircraft Engines will continue testing and will revise thischapter when life-limit changes are justified and when substantiatingdata has been approved by the FAA.

G. Life-limited parts must be removed from service before or as soon asthe life-limit of that part (as established by this chapter) has beenreached.

CAUTION: CERTAIN ROTATING PARTS ARE LIFE-LIMITED BASED ON THE SPECIFICAPPLICATION FOR WHICH THE PART IS INTENDED. IN SOME CASES,DIFFERENT LIFE LIMITS HAVE BEEN ESTABLISHED F0R IDENTICAL GELIFE-LIMITED PARTS FOR DIFFERENT APPLICATIONS (FOR EXAMPLE,CF34-3A1 VS CF34-3B). ACCORDINGLY, THE FOLLOWING PRECAUTIONS ANDGUIDELINES MUST BE OBSERVED:

• USED LIFE-LIMITED PARTS MUST NOT BE RE-USED, UNLESS THEHISTORY OF THAT PART IS KNOWN. THIS CHAPTER CONTAINSINFORMATION FOR DETERMINING EQUIVALENT ACCUMULATED CYCLES VSTHE APPLICATION.

• IF THE APPLICATIONS IN WHICH THE PART HAS OPERATED AND THEACCUMULATED TOTAL NUMBER OF CYCLES ARE KNOWN, BUT THE NUMBEROF CYCLES OPERATED IN EACH APPLICATION ARE NOT KNOWN, THENTHE LOWEST LIFE LIMIT FOR A GIVEN PART MUST BE APPLIED (REFERTO PARAGRAPH 2.B, METHOD II). IT IS THE RESPONSIBILITY OF THEOPERATOR TO MAINTAIN ACCURATE RECORDS OF THE PART OPERATION.

2. Requirements.

A. Definitions.

A cycle is defined as a flight consisting of an engine start, takeoff,and landing. Use of thrust reverser is not included in this cyclecount. Engine starts and shutdowns for operational checks, groundmaintenance, and taxiing do not count against life-limit cycles, unlessthe engine is operated at takeoff fan speed. In that case, it counts asone cycle. Other operational procedures that affect the life-limitcycles of rotating parts are counted as follows:

(1) An air start is considered one cycle on rotating parts.

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(2) When the thrust reverser is used and the throttle is advancedbeyond 70% N2, 1/6 cycle is added to the cycle count of eachrotating part. When the thrust reverser is used, but the throttleis not advanced beyond 70% N2, no additional cycles are added.

(3) Whenever the throttle is used to set APR power, 2 cycles areadded to the cycle count of each rotating part.

(4) Each flight (takeoff and landing) counts as one cycle regardlessof whether or not the engines are shut down prior to the nexttakeoff.

(5) A touch-and-go landing counts as one cycle for each rotating partwhen using the primary cycle-counting method.

(6) A go-around counts as 2 cycles for each rotating part if APRpower is set using the throttle during the go-around. If APRpower is not set, the go-around counts as 1 cycle for eachrotating part. This applies for both the primary and thealternate cycle-counting methods .

(7) If the alternate cycle-counting method is used, additional cyclecounting must be done. For each touch-and-go landing and for eachlanding followed by a takeoff with no shutdown, record andcalculate these events as follows:

(a) The engine is divided into three sections for cyclic recordkeeping purposes. Maintain a separate cycle count for eachof the following three sections:

Section Components in Section

Cycle Count forTouch-and-Go, or

Landing With No Shutdown

1 Fan, Compressor, and allLow-Pressure Turbine (LPT)Life-Limited parts, exceptthe Stage 4 Disk

1.000

2 All High-Pressure TurbineLife-Limited parts

0.250

3 LPT Stage 4 Disk 0.525

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(b) In addition to the cycle counts calculated in step (a),also count the following cycles for each of the threesections (refer to Sample Calculations in paragraph E, step(3)(b) for an example):

• ONE CYCLE PER FLIGHT FOR THE NORMAL MISSION.• ONE CYCLE PER AIR START.• ONE-SIXTH CYCLE (0.167) EACH TIME THE THRUST REVERSER IS

ACTIVATED ABOVE 70% N2.• TWO CYCLES EACH TIME THE THROTTLE IS USED TO SET APR

POWER.

B. Calculating Cycle Count For Common CF34 Engine Parts That AreTransferred Between Different CF34 Engine Models.

(1) The different CF34 engine models have a number of life-limitedparts that are common (have the same part number). Some of thesecommon parts also have the same life limits when transferredbetween the different engine models. However, because the enginemodel series experience different operating environments, thelife limits of some of the common parts may differ when used indifferent CF34 models.

(2) When a common life-limited part is transferred from one CF34engine model series to another, it will be necessary to calculateequivalent accumulated cycles for the part, taking into accountthe application (engine model) in which the part has operated, ifthe life of the part differs between engine models. Allapplicable information should be entered into the CF34 commonlife-limited parts tracking form (refer to table 801). Thecompleted tracking form must be returned with the applicablecommon parts when those parts are transferred between differentCF34 model series. The operator must get from GEAE, or from a GEauthorized CF34 overhaul facility, the life limits for each CF34model applicable to the components service history.

(3) Two methods are available to establish the total life limit forlife-limited parts that are used in more than one CF34 enginemodel:

CAUTION: METHOD II MUST BE APPLIED, UNLESS THE NUMBER OF CYCLESOPERATED IN EACH ENGINE MODEL IS KNOWN AND DOCUMENTED.IT IS THE RESPONSIBILITY OF THE OPERATOR TO MAINTAINACCURATE RECORDS OF THE PART OPERATION.

(a) Method I:

If the number of cycles accumulated on one CF34 model isaccurately known and documented, the fraction of lifeconsumed can be calculated and used to determine theremaining cyclic life in a different CF34 model.

First, calculate the fraction of life used for a partinstalled in a given CF34 model, then calculate theequivalent cycles since new (CSN) for the part installed ina different CF34 model; use this procedure:

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1 Calculate the fraction of life used for a partinstalled in initial CF34 model as follows:

Fraction of lifeused

=Cycles accumulatedon CF34 model 1LCF limit forCF34 model 1

2 Use this fraction to calculate the equivalent CSN onthe part, if installed in another different CF34 model(model 2)as follows:

Equivalent CSNforCF34 model 2

= Fraction oflife used

X LCF limit forCF34 model 2

3 Determine the cycles remaining on the part installed inCF34 model 2 as follows:

Cycles remainingCF34 model 2

= LCF limitfor CF34model 2

_ Equivalent CSN for CF34 model

2

4 Example 1:

Consider a part with LCF limits in two different CF34models as follows:

CF34 Model 1 LCF limit = 15,000 cyclesCF34 Model 2 LCF limit = 20,000 cycles

The part accumulates 6,000 cycles while installed inone CF34 model (model 1), and then will be installed ina different CF34 model (model 2). Calculate theequivalent CSN for the part installed in CF34 model 2,and determine how many LCF cycles remain, as follows:

Fraction of life used = 6,000 = 0.04while installed in CF34 15,000model 1

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Equivalent CSN forCF34 model 2 = 0.40 x 20,000 = 8,000 cycles

Cycles remaining onthe part installed = 20,000 - 8,000 = 12,000 cyclesin CF34 model 2

5 Example 2:

Consider a part with LCF limits in three differentCF34 models as follows:

Model 1 LCF limit = 12,000 cyclesModel 2 LCF limit = 27,000 cyclesModel 3 LCF limit = 20,000 cycles

The part accumulates 6,000 cycles while installed inone CF34 model (model 1), in addition to 4,000 cyclesinstalled in a second CF34 model (model 2). The part isplanned to be installed in a third CF34 model(model 3). Calculate the equivalent CSN for the partinstalled in CF34 model 3, and determine how many LCFcycles remain as follows:

Fraction oflife used

=Cycles accumulatedon CF34 model 1LCF limit formodel 1

+Cycles accumulatedon CF34 model 2LCF limit formodel 2

Fraction oflife used = 6,000 + 4,000 = 0.65

12,000 27,000

EquivalentCSN for model 3 = 0.65 x 20,000 = 13,000 cycles

Cycles remaining forthe part installedin CF34 model 3 = 20,000 - 13,000 = 7,000 cycles

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(b) Method II:

If the applications in which the part has operated and thetotal number of cycles accumulated are known, but thenumber of cycles operated in each application are notknown, the lowest life limit for a given limit for a givenpart must be applied (as shown below) when calculatingfraction of life consumed and cyclic life remaining. Thismethod requires maintaining only records of the totalnumber of cycles on the part in any CF34 model and theengine models in which the part has been used.

1 Calculate the fraction of life used for a partinstalled in initial CF34 model as follows:

Fraction of life used = Total cycles accumulatedLowest published life ofall models in which thepart has operated

2 Use this fraction to calculate the equivalent CSN onthe part, if installed in another different CF34(model 2) as follows:

Equivalent CSN for = Fraction of X LCF limit forCF34 model 2 life used CF34 model 2

3 Determine the cycles remaining on the part installed inCF34 model 2 as follows:

Cycles remaining = LCF limit for - Equivalent CSNfor CF34 model 2 CF34 model 2 for CF34 model 2

4 Example 3: Consider a part with lCF limits in twodifferent CF34 models as follows:

CF34 Model 1 LCF limit = 15,000 cyclesCF34 Model 2 LCF limit = 20,000 cycles

The part has accumulated 5,000 cycles total whileinstalled for some period of time on CF34 model 1, andfor some period of time on CF34 model 2. The part willnow be installed in CF34 model 2. Calculate theequivalent CSN and cycles that remain for the partinstalled in CF34 model 2.

The lowest published life on the part (15,000 cycles)must be applied in the calculations because it is notknown exactly how many cycles the part accumulatedwhile installed in each engine model.

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Fraction of life used = Total cycles accumulated Lowest published life

Fraction of life used = 5,000 = 0.33 15,000

Equivalent CSN = 0.33 X 20,000 = 6,000 cyclesfor CF34 model 2

Cycles remaining onthe part installed = 20,000 - 6,600 = 13,400 cyclesin CF34 model 2

C. Affected Components.

CAUTION: THE LIFE-LIMITED PARTS DEFINED IN THIS SECTION MUST NOT BEOPERATED BEYOND THE ESTABLISHED LIMITS.

The engine components that are life-limited by this section are thefollowing:

• Fan Rotor Components (refer to 5-11-01).

• Compressor Rotor Components (refer to 5-11-02).

• High-Pressure Turbine Rotor Components (refer to 5-11-03).

• Low-Pressure Turbine Rotor Components (refer to 5-11-04).

• Additional Life Limits (Non-LCF) (refer to 5-11-05).

D. Cycles Recording.

(1) The operator is responsible for maintaining an accurate record ofcycles experienced during engine operation. The operator mustalso monitor the status of the parts to ensure that none of theparts listed in paragraph C exceed the established life-limitcycles.

(2) The CF34 Turbofan Engine Service Record book provides forms forrecording the cycle history of the engine.

(3) The operator and/or the Service or Overhaul Facility isresponsible for making appropriate engine logbook entries toreflect changes in components.

E. Sample Calculations for Primary and Alternate Life-Cycle CountingMethods.

(1) Chapters 5-11-01 through 5-11-05 provide cycle limits which mustbe used to establish the continued serviceability of components.Step (2) shows an example of the primary life-cycle countingmethod, and step (3) shows an example of the alternate life-cyclecounting method.

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(2) Examples of primary life-cycle counting method:

(a) During a flight, the operator makes an air start on theright-hand engine, lands using the thrust reverser, andshuts down the engines. During the thrust reverseroperation, the throttles are advanced above 70% N2.

Cycle count right-hand engine: 111/62-1/6

normal missionair startthrust reversertotal

Cycle count left-hand engine: 11/61-1/6

normal missionthrust reversertotal

(b) The operator starts the engines, takes off, and lands usingthe thrust reverser followed by engine shutdown. Theoperator makes a second takeoff and landing using thethrust reverser, but does not shut down the engines. Theoperator then makes a third takeoff and landing withoutusing the thrust reversers. The throttles were advancedbeyond 70% N2 during the thrust reverser operation. Theoperator then makes a power assurance check at takeoff fanspeed.

Cycle count left-hand and right-hand engines:

Flight plus Reverser and Shutdown 1-1/6 cyclesFlight plus Reverser and no Shutdown 1-1/6 cyclesFlight with No Reverser and Shutdown 1 cyclePower Assurance Check and Shutdown 1 cycle

4-1/3 cycles

(3) Examples of alternate life-cycle counting method:

(a) An operator starts the engines, takes off, and experiencesa missed approach and a touch-and-go before landing anddoes not shut down the engines. The operator makes a secondtakeoff, and during the flight makes an air start on theright-hand engine. The operator then experiences two moremissed approaches and another touch-and-go before making asecond landing, and again does not shut down the engines.The operator then makes a third takeoff, and during theflight makes an air start on the left-hand engine. Theoperator lands using the thrust reversers with throttleadvanced beyond 70% N2 and shuts down the engines.

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(b) Refer to paragraph A, steps (7)(a) and (7)(b) for thedefinitions, and calculate the cycle count as follows:

CYCLE COUNT FOR EACH SECTIONOF EACH ENGINE FOR EACH EVENTTIMES QUANTITY OF EVENTS INTHAT FLIGHT

Section 1 Section 2 Section 3

One Takeoff 0.000 0.000 0.000Three Missed Approaches 3.000 0.750 1.575Two Touch-and-Go 2.000 0.500 1.050One Air Start 1.000 1.000 1.000Two Landings Followed by a Takeoff With No Shutdown Between 2.000 0.500 1.050One Thrust Reverser Application Above 70% N2 0.167 0.167 0.167One Full Stop Landing with Shutdown 1.000 1.000 1.000

Totals for this Flight 9.167 3.917 5.842

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GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or first page.

FAN ROTOR - LIFE-LIMITS

1. General.

A. This section contains the FAA approved life-limits for the fan rotorcomponents.

B. The life limit is determined by the total number of flight cycles(refer to 5-11-00, TIME LIMITS for the definitions and calculations ofcycles).

C. The operator is responsible to make sure that the cycle-limitedcomponents are not used beyond their established cycle limits.

CAUTION: IF YOU TRANSFER A LIFE-LIMITED PART FROM ONE CF34 MODEL TOANOTHER CF34 MODEL, REFER TO 5-11-00, TIME LIMITS, PARAGRAPH 2.B,FOR CALCULATING CYCLE COUNT FOR COMMON CF34 ENGINE PARTS THAT ARETRANSFERRED BETWEEN CF34 ENGINE MODELS.

2. Life Limits of Fan Rotor Components. Refer figure 801.

LOCATION(REF. FIG.

801)COMPONENTNOMENCLATURE PART NUMBER

CURRENTLY APPROVEDLIFE-LIMIT CYCLES

CF34-1A CF34-3A/-3A2

1 Fan Disk 5921T54G01 9,000 9,000 5922T01G03 13,200 13,200 5922T01G04 22,700 22,700 5922T01G05 22,700 22,700 6020T62G04 9,000 9,000 6020T62G05 9,000 9,000*6078T00G01 9,000 9,000*6078T57G02 6,000 6,000*6078T57G03 6,000 6,000 6078T57G04 24,300 24,300 6078T57G05 24,300 24,300

2 Fan Forward Shaft 6017T63P04 38,280 38,280 6017T63P05 38,280 38,280 6078T51P01 15,000 15,000 6078T51P02 15,000 15,000 6078T51P03 15,000 15,000

3 Fan Drive Shaft 6036T78P02 15,000 15,000

* Fan disk can be reworked to “0” time after reaching current limits (refer toREI-13392, latest revision) at certified overhaul shops only.

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Fan Rotor - Life Limited ComponentsFigure 801

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Page 801Sep 1/04


COMPRESSOR ROTOR - LIFE LIMITS

1. General.

A. This section contains the FAA-approved life limits for the compressorrotor components.

B. The life limit is determined by the total number of flight cycles(refer to 5-11-00, TIME LIMITS for the definitions and the calculationsof cycles).

C. The operator is responsible to make sure that the cycle-limitedcomponents are not used beyond their cycle limits.


2. Life Limits of Compressor Rotor Components. Refer to figure 801.

LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2

1 Stage 1 Disk 6040T79G016087T00G016087T00G02

6,000 15,000 15,000

6,000 15,000 15,000

2 Forward Shaft 5037T01P035037T01P04

12,300 12,300

11,740 11,740

3 Stage 2 Disk 6036T91P016036T91P02

15,000 15,000

15,000 15,000

4 Forward Spool 6036T75P026036T75P036078T56P016078T56P036078T56P046078T56P05

6,000 6,000*12,000 27,000 27,000 6,000

6,000 6,000*12,000 27,000 27,000 6,000

* Retire all forward spools PN 6078T56P01 at scheduled 6,000-hour overhaul or, if 6000-hour overhaul has been completed, at next exposure at or before 12,000 cycles.

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Compressor Rotor - Life Limited ComponentsFigure 801

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LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2

5 Rear Spool 5087T46P015087T46P026037T83P036037T83P046087T02P01

22,000 22,000 6,000 6,000 6,000

22,000 22,000 6,000 6,000 6,000

6 Rear Shaft CDPSeal

4019T38P01 15,080 14,400

7 Rear Shaft 6016T83P016087T03P016087T03P026087T03P03

6,000 6,000 6,000 23,000

6,000 6,000 6,000 23,000

8 Stage 9 Disk 6016T43P036087T01P016087T01P026087T01P03

6,000 6,000 23,000 23,000

6,000 6,000 23,000 23,000

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HIGH-PRESSURE TURBINE ROTOR - LIFE LIMITS

1. General.

A. This section contains the FAA-approved life limits for the high-pressure turbine (HPT) rotor components.




2. Life Limits of High-Pressure Turbine Rotor Components. Refer to figure 801.

LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2

1 Seal, BalancePiston Air

5025T33P023921T56P015025T33P033921T58P015025T33P045025T33P066078T90P01

7,200 7,200 7,200 7,200 7,200 7,200 6,000

7,200 7,200 7,200 7,200 7,200 7,200 6,000

2 Shaft, HPT Rotor 6017T00P046017T00P056920T61P01

6,000 6,000 6,000

6,000 6,000 6,000

3 Plate, Stage 1Front Cooling

3921T52P014027T15P024027T15P03

6,000 6,000 6,000

6,000 6,000 6,000

4 Disk, Stage 1Turbine

6031T89P013921T50P016031T89P026031T89P036078T93P016078T93P02

4,358 6,000 6,000 6,000 6,000 6,000

4,358 6,000 6,000 6,000 6,000 6,000

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LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2

5 Plate, Stage 1Aft Cooling

5041T70P01

5041T70P03

Refer to5-11-05

6,000

Refer to5-11-05

6,000

6 Plate, Stage 2Rear Cooling

3921T54P015023T97P025023T97P03

6,000 6,000 6,000

6,000 6,000 6,000

7 Disk, Stage 2Turbine

6031T90P013921T51P016031T90P026031T90P036078T94P016078T94P02

3,256 6,000 6,000 6,000 6,000 6,000

3,256 6,000 6,000 6,000 6,000 6,000

8 Plate, Stage 2Front Cooling

3921T53P015042T29P015042T29P02

6,000 6,000 6,000

6,000 6,000 6,000

9 Coupling, OuterTorque

5041T67P023921T61P01

6,000 6,000

6,000 6,000

10 Coupling, InnerTorque

5041T66P023921T55P015079T02P01

6,000 6,000 6,000

6,000 6,000 6,000

NOTE: Cycle limits apply to all PN 5041T66P02 and PN 3921T55P01 inner torquecouplings, except for the serial numbers listed below which are limitedto 4,230 cycles.

GAT3189B GAT3232F GAT3665H GAT5705BGAT3191B GAT3233F GAT3666H GAT5725BGAT3193B GAT3234F GAT3667H GAT5728BGAT3194B GAT3235F GAT3668H GAT8842GGAT3196B GAT3236F GAT3669H GAT8843GGAT3197B GAT3237F GAT3670H GAT8844GGAT3226F GAT3238F GAT3671H GAT8845GGAT3227F GAT3239F GAT3672H GAT8846GGAT3228F GAT3240F GAT3673H GAT8847GGAT3229F GAT3660H GAT3674H GAT8849GGAT3230F GAT3663H GAT3675H GAT8850GGAT3231F GAT3664H GAT3676H GAT8851G

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LOW-PRESSURE TURBINE ROTOR - LIFE LIMITS

1. General.

A. This section contains the FAA-approved life limits for the low-pressureturbine (LPT) rotor components.




2. Life Limits of Low-Pressure Turbine Rotor Components. Refer to figure 801.

LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2

1 Turbine Rear Shaft 6030T72P02 39,000 39,000 4922T19P01 38,280 34,490

2 Stage 3 Disk 5026T16P01 3,828 3,440 4922T14P01 6,000 6,000 5026T16P02 6,000 6,000 6078T91P01 15,000 15,000 6078T91P02 15,000 15,000

3 Stage 3 and 4 Seal 5023T59P02 33,000 29,730 4922T20P01 33,000 29,730

4 Stage 4 Disk 5026T17P02 4,330 4,330 4922T15P01 6,000 6,000 5026T17P03 6,000 6,000 6078T02P01 15,000 15,000 6078T02P03 17,000 17,000 6078T02P04 17,000 17,000


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Low-Pressure Turbine Rotor - Life Limited ComponentsFigure 801

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LOCATION(REF. FIG.



CF34-1A CF34-3A/-3A2



8 Drive Cone 5023T40P01 15,000 15,000 4922T18P01 15,000 15,000 5023T40P03 15,000 15,000


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CF34 TURBOFAN ENGINE

MAINTENANCE MANUAL

5-11-05TIME LIMITS

Page 801

Sep 15/99

ADDITIONAL LIFE LIMITS (NON-LCF)

1. General.

This section contains additional life limits for specific non-LCF components.

2. Life Limits.

ITEM REQUIREMENT MAXIMUM INTERVAL METHOD

* * * * * FOR CF34-1A * * * * *

HPT Stage 1 Blades:

NOTE: Refer to SB 72-34 (latest revision) for the maximum interval that apply to stage 1 blades that

are installed in specific engine serial numbers.

PN 6040T72P04 Replace 3000 hours Send the HPT rotor to

PN 6040T72P07 Replace 3000 hours an authorized service

PN 6040T72P08 Replace 3000 hours or overhaul facility.

PN 6040T72P09 Replace 3000 hours


PN 6078T19 No Limit --- -----

* * * * * FOR CF34-3A/3A2 * * * * *

HPT Stage 1 Blades:

PN 6040T72P07 Replace 1000 hours Send HPT rotor to an

PN 6040T72P08 Replace 1000 hours authorized service or

PN 6040T72P09 Replace 1000 hours overhaul facility.


PN 6078T19 No Limit --- -----

GE Aircraft Engines

CF34 TURBOFAN ENGINE

MAINTENANCE MANUAL

5-11-05TIME LIMITS

Page 802

Sep 1/04GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or first page.

ITEM REQUIREMENT MAXIMUM INTERVAL METHOD

* * * * * FOR ALL * * * * *

HPT Stage 1 Aft

Cooling Plate PN

5041T70P01.

Replace 3000 hours Send the HPT rotor to an

authorized service or overhaul

facility.

HPT Stage 2 Studs

(only when

SB 72-5 is

accomplished).

Replace 6000 hours Send the HPT rotor to an

authorized service or overhaul

facility.

No. 5 Bearing Carbon

Seal Preformed

Packing (KALREZ).

Replace 3000 hours

(refer to NOTE)

Refer to 72-40-00,

REMOVAL/INSTALLATION.

NOTE: The No. 5 bearing carbon seal preformed packing must be replaced at the next 3000 hours (HSI)

inspection, and then at every 3000 hours (HSI) thereafter. If Service Bulletin 72-53 has been

complied with, refer to 5-21-00, Table 803, item Q., NOTE 6 for instructions.

Combustion Liner (PN

6063T15G01 and G04

only) (low-emission,

Type I).

Replace 750 cycles maximum

(refer to NOTE)

Refer to 72-40-00,


NOTE: Combustion liner PN 6063T15G01 and G04, that are installed in CF34-3A engines SN 350336

through 350504 (low-emission Type I), must be replaced between 600 and 750 cycles maximum

until Service Bulletin (CF34) 72-26 is complied with.

HPT Stator Stage 2

Nozzle

Retaining Ring

Sector.

Replace 3000 hours

(refer to NOTE)

Refer to 72-50-00,


NOTE: The stage 2 nozzle retaining ring sectors must be replaced at the next 3000 hours (HSI)

inspection, and then at every 3000 hours (HSI) thereafter, unless Service Bulletin 72-77 has

been complied with. If Service Bulletin 72-53 has been complied with, refer to 5-21-00, Table

803, item Q., NOTE 6 for instructions.

GE Aircraft Engines


LIST OF EFFECTIVE PAGES

* Asterisk indicates pages added, changed, or deleted by this revision.

5-11-00LIST OF EFFECTIVE PAGES

Page 1Sep 1/04


CHAPTER/SECTION PAGE DATE

List ofEffectivePages *1 Sep 1/04

Table ofContents 1 Sep 30/98

5-11-00 801 thru 811 Sep 30/98

5-11-01 801 Sep 15/02 802 Sep 30/98

5-11-02 *801 Sep 1/04 802 Sep 30/98*803 Sep 1/04

5-11-03 801 thru 803 Sep 15/00

5-11-04 *801 Sep 1/04 802 Sep 15/99*803 Sep 1/04

5-11-05 801 Sep 15/99*802 Sep 1/04


GE Aircraft Engines


5-11-00TABLE OF CONTENTS

Page 1Sep 30/98

TABLE OF CONTENTS

SUBJECTCHAPTER/SECTION PAGE

LIFE LIMITS OF ENGINE ROTATING PARTS

Life Limits of Engine Rotating Parts 5-11-00 801General 801Requirements 802Definitions 802Calculating Cycle Count For Common CF34 Engine Parts That Are Transferred Between Different CF34 Engine Models. 804Method I 804Method II 808

Affected Components 809Cycles Recording 809Sample Calculations for Primary and Alternate Life-Cycle Counting Method 809Primary Life-Cycle Counting Method 810Alternate Life-Cycle Counting Method 810

Fan Rotor - Life Limits 5-11-01 801General 801Life Limits of the Fan Rotor Components 801

Compressor Rotor - Life Limits 5-11-02 801General 801Life Limits of the Compressor Rotor Components 802

High-Pressure Turbine Rotor - Life Limits 5-11-03 801General 801Life Limits of the High-Pressure Turbine Rotor Components 801

Low-Pressure Turbine Rotor - Life Limits 5-11-04 801General 801Life Limits of the Low-Pressure Rotor Components 801

Additional Life Limits (Non-LCF) 5-11-05 801General 801Life Limits 801

GE Aircraft Engines


5-21-00CF34 ENGINE MAINTENANCE PROGRAM

Page 801Jun 30/97

SCHEDULED MAINTENANCE PROGRAM

1. General.

A. This section contains the scheduled inspection checks for the CF34-1A/-3A/-3A2 engines.

B. The scheduled Inspection and Servicing Requirements (refer to table801), or manufacturer's recommendations, consists of installed-enginerepetitive visual and borescope inspections of the engine's externaland internal components, specific maintenance checks and tasks, aperformance trend monitoring program, and compliance with life limitsas specified in Chapter/Section 5-11-00, compliance with all themanufacturer's Service Bulletins, as well as removal of the enginehot section for Hot Section Inspection (HSI).

C. The scheduled inspection checks and servicing requirements set forthin this Chapter represents the plans and the recommendations by GEAircraft Engines. The specified time intervals are based upon enginesbeing operated at all times within approved operating limits and main-tained in accordance with GE Aircraft Engines published instructions,including compliance with the recommended inspection intervals.

D. The replacement intervals for life-limited parts (refer to Chapter/Section 5-11-00) shall take precedence over all maintenance actionscontained in this Chapter. The inspection and maintenance intervalsrecommended herein are subject to the cycle life or hourly parts limitsas described in Chapter/Section 5-11-00.

E. During the removal of engine components, and prior to the installationof any component, inspect all the components that are removed, orport ions of the components that are exposed. Inspect the componentsand the exposed areas in accordance with the published inspectioncriteria in the applicable sections in this manual.

2. Special Tools and Fixtures.

The special tools and fixtures recommended by GE Aircraft Engines arelisted in table 801. Equivalent substitutes can be used.

TABLE 801. SPECIAL TOOLS AND FIXTURES

TOOL NUMBER NOMENCLATURE

11-10792 Kit, Igniter Plug Gage(Unison Industries7575 Baymeadows WayJacksonville, FL 32256USA

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Page 802Jun 30/97

3. Consumable Materials.

The consumable materials listed in table 802 are recommended for use whendoing scheduled maintenance procedures in this section. Equivalent substi-tutes can be used for listed items.

TABLE 802. CONSUMABLE MATERIALS

DESCRIPTION MANUFACTURER

Oil, Penetrating (LPS-1) LPS Research Lab, Inc.2050 Cotner Ave.Los Angeles, CA 90025 USA

Oil, Penetrating (WD-40) WD-40 CompanyP.O. Box 80607San Diego, CA 92138USA

4. Scheduled Inspection Checks.

A. Preliminary Instructions.

(1) The inspection time categories in table 803 are divided into sixinspection intervals: Preflight or Postflight, 100-hour, 300-hour, 600-hour, 1200-hour, and 3000-hour inspection intervals.The checks in these intervals indicate the minimum inspectionrequirements for satisfactory inspection compliance.

(2) Visually inspect the engine components for the appropriateInspection Time Categories.

(3) When the condition of an engine part can not be determined, referto the inspection limits that apply to the individual part, inthe applicable inspection table in this manual.

(4) The oil filter must be inspected for contamination (refer to79-00-00, INSPECTION) when:

� There has been an indication of oil impending bypass.� The oil filter or the engine has reached its time category

interval.� The engine has been overhauled.

B. Daily Checks (Preflight or Postflight).

(1) Use a flashlight and visually inspect the engine inlet andexhaust areas (with the duct covers removed) for the conditionslisted in table 803.

(2) Inspect the ground surface area and any aircraft surfaces in theimmediate vicinity of the engine inlets for foreign debris.

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Page 803Jun 30/97

C. Periodic Inspections.

(1) A thorough visual inspection of the engine is required at regularintervals and at complete overhaul scheduled for 6000 hours.

(2) Borescope-inspect (refer to 72-00-00, INSPECTION) the compressorsection, and clean (refer to 72-00-00, CLEANING) the compressorfor performance recovery.

(3) Visually inspect the engine components for the appropriateInspec- tion Time Categories.

D. Mid-Point (3000-Hour) Hot Section Inspection Interval.

(1) Inspect the engine components listed in table 803 for the inspec-tion time category at 3000 hours. Disassemble the engine to theextent that the combustion liner can be inspected (remove onlythe engine components necessary to access the combustion liner,and be sure that all turbine parts are matchmarked before youremove them).

(2) After you remove the necessary airframe QEC parts, disassemblethe engine in the sequence given in table 804 (refer to theparagraph titled "On-Aircraft Maintenance and Inspection of HotSection" in 72-00-00, SPECIAL MAINTENANCE PRACTICES), for theprocedures to inspect the Hot Section components.

NOTE: � The swirler assemblies are replaced when the combustionliner is reworked.

� The combustion liner PN 6052T10G01 (SN GGMDP906) and up, donot require rework.

(3) Inspect the combustion liner, exposed carbon seals, and sealrunners (refer to 72-40-00 and 72-50-00, INSPECTION).

(4) Do the following for these combustion liners:

� If the combustion liner is PN 6036T69G05 or PN 6052T10G01,return it to an authorized GE Aircraft Engines overhaul facil-ity for rework. Do not return combustion liner PN 6052T10G01with SN GGMDP906 and up (this liner does not require rework).

� Combustion liner PN 6036T69G05 must be reworked to PN5921T51G01.

� Combustion liner PN 6052T10G01 (other than SN GGMDP906 and up)must be reworked to PN 5921T51G02.

(5) Inspect the transition case for missing hard coat on the slotsand inspect the transition outer liner for missing hard coat onthe lugs (refer to 72-50-00, INSPECTION). Inspect the removedparts as required in the sections of this manual.

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Page 804Jun 30/97

NOTE: It is not necessary to disassemble the major engine subassem-blies (such as the LPT rotor and stator assemblies, or the HPTturbine rotor and stator assemblies).

(6) Visually inspect all the exposed engine components and theexposed internal components that are visible, as required by theapplica- ble inspection tables.

(7) Clean the damaged Components; then repair them or replace them,if the condition indicates.

(8) Re-assemble the engine according to the instructions in theappli- cable chapters referenced in table 804.

(9) Functionally-check the engine (refer to the table titled "CHECKSREQUIRED AFTER MAINTENANCE" in 72-00-00, TESTING for the checksto be done); then, do an Engine Break-In Run (refer to 72-00-00,TESTING).

TABLE 803. INSPECTION AND SERVICING REQUIREMENTS

INSPECTION TIME CATEGORIES

ENGINE COMPONENTAND INSPECTION

Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

A. Check the inlet duct for:

(1) Deterioration, damage,and loose rivets.

X

(2) Integrity of acousticalpanels.

X

(3) Presence of foreignobjects.

X

B. Check (refer to Note 1 atthe end of this table) theexternal hoses and tubes,electrical connectors,ports, flanges, clamps, andbrackets for:

(1) Security. X

(2) Damage (visually). X

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Page 805Jun 30/97

TABLE 803. INSPECTION AND SERVICING REQUIREMENTS (Cont)



Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(3) Evidence of leakage fromexternal hoses or tubes.

X

(4) Chafing (visually). X

C. Check (refer to Note 1 at theend of this table) under thecowl for evidence of leakage(fuel, oil, air) from:

(1) Surfaces beneath theengine.

X

(2) Engine surfaces andaccessories.

X

(3) Fuel heater.* X

* Remove the cap from the bleed air tube, and check for any evidence offuel accumulation (not allowed). If fuel is found in the air tube,replace the fuel heater (73-00-00, REMOVAL/INSTALLATION). Re-installthe cap; if the cap is silver-plated, torque the cap to 85-90 lb in.(9.6-10.2 N•m); if the cap is not silver-plated, torque the cap to135-150 lb in. (15.3-16.9 N•m).

D. Check the oil system forcontamination as follows:

NOTE: A leak check (refer to 72-00-00, TESTING) must be done after any compo-nent of the oil system is disconnected or removed.

(1) Remove, inspect, andreplace the oil filterelement (79-00-00,INSPECTION) (also, referto Note 1 at the end ofthis table).

X

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Page 806Sep 15/00




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

NOTE: � The chip detector in the accessory gearbox (AGB) should be inspectedwhen metal is found in the oil filter. If the AGB chip detector appearsnormal, or the metal in the oil filter is non-ferrous (not attracted bya magnet), then the Integrated Drive Generator (IDG) and the garlockseal should be removed to inspect the axis-BB drive bearing.

� Replace the oil filter after the first 100 hours of operation; then at600 hours, and then every 600 hours thereafter.

(2) Do a continuity check ofall the magnetic chipdetectors (refer to 72-00-00, INSPECTION). Ifthe continuity checkfails, inspect the chipdetectors for metallicparticles (refer to 72-00-00, INSPECTION).

X

(2A)Do an insulationresistance check of themagnetic chip detector(refer to 79-00-00,INSPECTION).

X

(3) Check the oil level(maintain the oil levelby actuating theaircraft oilreplenishing system).*

X

*Oil may seep from the oil tank into the gearbox when the engine isinactive and can give a false indication of a low oil level. Check theoil level within 30 minutes after engine shutdown.

GE Aircraft Engines



Page 806A/806BSep 15/00




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(4)Sample oil (refer to72-00-00,SERVICING).* Visuallyinspect the drainedoil for presence ofmetallic particles.Visually check theoil level in theengine oil tank forevidence ofoverservicing andfuel contamination.

X

* If the acid level is more than 1.5 mg KOH/g, change the oil at the nextconvenient time.

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Page 807Sep 15/00




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(5) Visually inspect allthe oil systemcomponents for leaksduring the GroundIdle Run in 72-00-00,TESTING.

X

(6) Do an oil filterbypass sensorindication test(refer to 72-00-00,TESTING).

X

(7) Visual inspection ofthe C-sump scavengescreen fittings(refer to SEI-581,79-00-00, figure 3,items 55A and 245) inthe lube and scavengepump for accumulationof coked oil build-up. If a 3000-hourHSI inspection hasalready beencompleted, do thisinspection at thenext scheduled 3000-hour inspection.

X

E. Check the fuel system(refer to 73-00-00) asfollows:

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Page 808Sep 15/99




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

NOTE: If any components of the fuel system is disconnected or replaced, a leakcheck must be done (refer to 72-00-00, TESTING).

(1) Replace the fuel filterelement.*

X

* The fuel filter element is the disposable type, and must be replacedevery 600 hours or when the element is contaminated. If the element iscontaminated, inspect and clean the fuel system (refer to 73-00-00,CLEANING).

(2) Check for the fuelfilter for a poppedbypass indication button(refer to 73-00-00,CLEANING for correctiveaction).

X

(3) Inspect the fuel filterbracket for cracks.

X

(4) Visually inspect allfuel system componentsfor leaks during theGround Idle Run in72-00-00, TESTING.

X

(5) Visually inspect (referto 79-00-00, INSPECTION)the housing of the oilcooler for chafing(caused by the loopclamp on the C-sump aftscavenge hose).

X

(6) General visualinspection of the fuelpump and the main fuelcontrol assembly.

X

F. Check the visible areasof the fan rotor, engineinlet, and front frame(refer to 72-20-00,INSPECTION) for theusable limits):

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Page 809Sep 15/99




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(1) Fan spinner for:

(a) Cracks. X

(b) Dents. X

(c) Looseness. X

(2) Fan rotor for freerotation (use yourhands to turn therotor).

X

(3) Fan vanes for dentsand cracks, and forloose or missingnuts.

X

(4) Fan rotor blades for:

(a) Unserviceable bladetip rubs (as evidencedby tip discoloration).

X

(b) Nicks and dents. X

(c) Security andcracks.

X

(d) Missing lubricanton the blade tangs(re-apply forcause only).

(5) Fan disk forprotruding bushings.*

X

(6) Aluminum componentsof the fan casing forcracks and dents.

X

* Only needed when N1 vibrations are abovethe normal operating range. The bushingsshould not be felt when you move astraightedge across the face of the disk.

GE Aircraft Engines



Page 810Sep 30/98




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(7) Abradable rub strip forunserviceable rubs.*

X

(8) Forward engine mount forsecurity and cracks.

X

(9) Front frame for cracksaround the AGB mountpads.

X

(10)Ignition exciter forsecurity and damage(refer to 74-00-00,INSPECTION).

X

(11)Visually inspect thewater drain, in theblade removal port,for blockage.

X

G. Check the compressorrotor and the statorassemblies (refer to72-30-00, INSPECTIONfor the limits) for:

(1) Nicks, dents, and curledtips on the rotor bladesthat are visible throughthe borescope.

X

(2) Cracks on rotor bladesthat are visible throughthe borescope.

X

(3) Dents and cracks invisible areas of thecompressor casings.

X

* A continuous circumferential rub more than75% or more of the rub strip is evidence ofa possible separation of the fan blade tang.

GE Aircraft Engines



Page 811Jun 30/97




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(4) Variable vanes for:

(a) Nicks and dents. X

(b) Cracks and excessivemovement.

X

(5) Missing lock tabs fromvisible variable vaneouter shank nuts.

X

(6) Rubs between variablevanes and shrouds thatare visible through theborescope.

X

(7) Distorted variable vaneactuator ring.

X

(8) Loose variable geometrysystem caused by wornbushings in rod end,actuator rings, andtorque shaft forwardbearing for migration.

X

(9) Inspect the variablegeometry feedback cableand the VG actuatorattachment points forsecurity.

X

(10)Disengaged or bentvariable vane Leverarms or turnbuckles.*

X

* If you see any disengaged or bent lever arms or turnbuckles, theengine must be sent to an authorized GE Aircraft Engines overhaul shop.

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Page 812Jun 30/97




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

WARNING: PENETRATING OIL

DO NOT LET PENETRATING OIL STAY ON YOUR SKIN. PENETRATING OIL ISDANGEROUS TO YOUR SKIN AND EYES. DO NOT BREATHE THE FUMES FROM THISOIL. MAKE SURE YOU HAVE A GOOD FLOW OF AIR. THE FUMES CAN GIVE YOUA HEADACHE AND CAN MAKE YOU DIZZY AND SICK.

CAUTION: THE VG LINKAGE ROD-END BEARINGS MUST BE LUBRICATED EVERY 300 HOURSWITH PENETRATING OIL WD-40 OR LUBRICANT LPS-1 (OR EQUIVALENT) ON THETURNBUCKLES AND THE CLEVIS ADAPTER AT 24 LOCATIONS.

(11)Lubricate the surfacesof the VG rod endbearings (refer tofigure 801, view Afor the location) withpenetrating oil WD-40or lubricant LPS-1.

X

(12)Overall condition ofthe variable geometrysystem.

X

H. Check the combustion section(refer to 72-40-00, INSPEC-TION) for:

(1) Security of the fuelmanifold connections.

X

(2) Cracks in combustionchamber frame (visibleareas).

X

(3) Nicks, dents, scratches,wear, or carbon buildupon the fuel injectorsthat are visible throughthe borescope (refer to73-00-00, INSPECTION).

X

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Page 813Jun 30/97

Variable Geometry Actuating System - InspectionFigure 801

GE Aircraft Engines



Page 814Jun 30/97




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(4) Detailed visual inspec-tion of the fuel injec-tor heat shields (referto 73-00-00, INSPEC-TION).

X

(5) Hot spots, bulges, andcracks on the combustionliner during the bores-cope inspection.

X

(6) Detailed visual inspec-tion of the stages 1 and2 nozzle assemblies.

X

(7) Visible wear on theprimary swirlers (referto 72-40-00, INSPEC-TION).

X

(8) Centering of the fuelinjectors in swirlers(refer to 72-4O-00,INSPECTION) at:

(a) Borescope inspec-tion.

X

(b) Detailed visualinspection of theswirlers after theremoval of theinjectors.

X

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Page 815Jun 30/97




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

I. Check the accessory drivesection (refer to 72-60-00,INSPECTION) for:

(1) Security of the acces-sory gearbox bracketsand the brackets on thefront frame.

X

(2) Security of the compo-nents that are installedon the gearbox.

X

SB 72-11

(3) Borescope inspection(refer to 72-00-00,INSPECTION) of the PTOcarbon sleeve (G01 andG06 assemblies only) forforward movement.

X

(4) Detailed inspection ofthe accessory gearboxmounts.

X

J. Check the condition and thesecurity of the isolators onthe control amplifier (referto 74-00-00, INSPECTION).

X

K. Check the HPT and LPTturbine sections (referto 72-50-00, INSPECTION)for:

(1) Cracks, bulges, and hotspots on the casings.

X

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Page 816Jun 30/97




Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

(2) Operational defects onthe LPT exposed areas ofthe turbine nozzles.

X

(3) Condition of thermo-couple harness (mustmeet all serviceablerequirements in74-00-00, INSPECTION).

X

(4) Borescope inspection(refer to 72-00-00,INSPECTION) of the stage1 nozzle and the HPTstage 1 blades.

X

(5) Borescope inspection ofthe outer transitionliner on enginesSN 350489 and below thathave not been modifiedto SB 72-38.

X

(6) Visual inspection of thestage 6 turbine bladesfor FOD.

X

(7) Security of the exhaustcenterbody.

X

(8) Igniter plugs (must meetall the serviceablerequirements in 74-00-00INSPECTION); also, referto the note.

XCF34-1A/-3A

only

XCF34-3A2only

GE Aircraft Engines



Page 817Sep 15/01





Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

NOTE: � For CF34-1A/-3A engines, it is recommended that one igniter plug bereplaced every 300 hours. If both igniter plugs are within theinspection limits in 74-00-00, INSPECTION, then replace the igniterplug that has been in service longer. If neither igniter plug meetsthe inspection requirements, replace both igniter plugs.

� For CF34-3A2 engines, the igniter plugs must be inspected with theigniter plug gage PN 11-10792.

(9) Detailed visualinspection of the HPTstages 1 and 2 shrouds.

X

(10) Inspect the LPT statorassembly.*

X

* If the LPT stator assembly is PN 6020T15G14, it must be returned toan authorized overhaul facility for tack welding of the pin and clipassemblies; then, after the rework, the assembly must re-identifiedfrom PN 6020T15G14 to G24.

(11) Inspect the C-sumpscavenge tube (at the 6o'clock position) andthe groove for internalcoking; clean asrequired (must bewithin the serviceablelimits in 72-50-00,INSPECTION).

X

L. Do a Power Assurance Check(refer to TESTING).

X

M. Waterwash the compressor(refer to 72-00-00,CLEANING) .*

X

* Engines with a high rate of landings (especially in locations where thereis airborne soot, dirt, or salt) may require additional cleaning intervals.Generally, if there is a performance deterioration, noted by an increasein ITT (change margin) of 15 C (27 F) (as determined by the Power Assurancecurves in 72-00-00, TESTING), the engine will require cleaning (refer to72-00-00, CLEANING).

GE Aircraft Engines



Page 818Sep 15/01





Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

* * * * * FOR ENGINES NOT MODIFIED TO SB 75-0002 * * * * *

N. Do a B-Sump PressureMeasurement (refer to72-00-00, SPECIALMAINTENANCE PRACTICES).**

X

** If any oil system component is disconnected or removed, a leak check mustbe done (refer to 72-00-00, TESTING).

* * * * * FOR ALL * * * * *

O. At each enginevisit/exposure to anyauthorized GEAE overhaulshop, do a visual inspectionof the screens inside the C-sump scavenge fitting (portsNo. 3 and No. 4) and thescreens inside the B-sumpscavenge fitting (ports No.5 and No. 6) for evidence ofcoked oil build-up. Cleanall evidence/traces of cokedoil build-up (refer toSEI-582, 72-09-01, SPECIALPROCEDURE 02).

P. Do a mid-point inspection(refer to para D).Borescope-inspect (refer to72-00-00, INSPECTION) theCompressor, and disassemblethe engine to the extent toinspect all the hot sectioncomponents, including thecombustion liner (refer to72-00-00, SPECIALMAINTENANCE PRACTICES - On-Aircraft Maintenance andInspection of Hot Section);also, refer to Notes 2 and 3at the end of this table.Also, refer to item O.

GE Aircraft Engines



Page 819Sep 1/04





Preflightor

Postflight100Hours

300Hours

600Hours

1200Hours

3000Hours(Referto

Para D)

Q. Do an engine overhaulevery 6000 hours (referto SEI-582); also, referto Notes 1 through 6 atthe end of this table.Also, refer to item O.

NOTE: 1. An additional 10%, or 45 hours, whichever is less (per interval), isallowed to provide operators with scheduling flexibility beyond thefixed limits established above.

2. For the basic engine, the mid-point inspection interval (3000 hours),or overhaul (6000 hours), is determined by the hours. Cycle lives,referenced in Chapter 5-11-00, must not be exceeded prior to reachingthe hourly inspection limit.

3. All cycle limits are given in Chapter 5-11-00.

4. A complete borescope inspection of the engine must be done every3000 hours or 10 years TSN/TSO (Time Since Overhaul), whichever occursfirst (refer to 72-00-00, INSPECTION for the borescope inspections;except, do not borescope-inspect the PTO assembly, and the inspectionsfor Troubleshooting Purposes do not apply).

5. The overhaul of accessories, at the time of engine overhaul, isrecommended by GE Aircraft Engines. However, this is an optionof the operator.

6. GE Aircraft Engines will permit a one time extension of the HotSection Inspection Interval after you (the operator) completeSB 72-53. Operators who comply with SB 72-53 before or concurrentwith Hot Section Inspection (2000-3000 hours TSN), and accomplisha Hot Section Inspection while complying with SB 72-53, will bepermitted to operate the engine to its 6000-hour overhaul pointwithout performing a second Hot Section Inspection before overhaul.If the engine has more than 3000 hours, SB 72-53 does not apply andyou must obey the Hot Section Inspection Intervals in this Chapter.

GE Aircraft Engines



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TABLE 804. HOT SECTION REMOVAL/INSPECTION REQUIREMENTS

ItemRemoval/Installation

ProceduresInspectionProcedures

A. Low-pressure turbine assembly(without fan drive shaft).

72-00-00, SPECIALMAINTENANCE PRACTICES

72-50-00,INSPECTION

B. High-pressure turbinestator/rotor assembly.

72-00-00, SPECIALMAINTENANCE PRACTICES

72-50-00,INSPECTION

NOTE: Because the combustion liner, the stages 1 and 2 turbine nozzles, andthe stages 1 and 2 HPT shrouds are more susceptible to hot sectiondistress than other engine parts, they are used as indicators of abnormaldistress. Therefore, during inspection of the hot section, if thecombustion liner, the stages 1 and 2 turbine nozzles, and the stages 1and 2 HPT shrouds are abnormally distressed, also inspect the fuelinjectors in the area of distress (refer to 73-00-00, INSPECTION).

C. Stage 1 turbine nozzle. 72-00-00, SPECIALMAINTENANCE PRACTICES

72-40-00,INSPECTION

5. CF34-1A/-3A/-3A2 Engine Maintenance Program - Shop Level MandatoryInspection Requirements.

A. This procedure is used to identify specific piece-parts that requiremandatory inspections that must be accomplished at each piece-partexposure in a GEAE authorized overhaul facility, using the applicableChapters referenced in table 805 for the inspection requirements.

B. Piece-part exposure is defined as follows:

(1) For engines that utilize the “On Condition” maintenancerequirements:

The part is considered completely disassembled when done inaccordance with the disassembly instructions in the GEAE engineauthorized overhaul Shop Manual and:

The part has accumulated more than 100 cycles in service sincethe last piece-part opportunity inspection and the part isreturned to the overhaul facility, provided that the part was notdamaged or related to the cause for its removal from the engine.

GE Aircraft Engines



Page 821Sep 15/00

(2) For engines that utilize the “Hard Time” maintenancerequirements:

The part is considered completely disassembled when done inaccordance with the disassembly instructions used in the “MinorMaintenance” or “Overhaul” instructions in the GEAE engineauthorized Maintenance or Shop Manual, and:

The part has accumulated more than 100 cycles in service sincethe last piece-part opportunity inspection and the part isreturned to the overhaul facility, provided that the part was notdamaged or related to the cause for its removal from the engine.

C. Refer to table 805 for the mandatory inspection requirements.

TABLE 805. MANDATORY INSPECTION REQUIREMENTS

PART NAME/PART NUMBERMANUAL

CHAPTER/SECTION/SUBJECT MANDATORY INSPECTION

Fan Disk (all) SEI-58272-21-00, INSPECTION

All areas (FPI) 1

Bores (ECI) 2

Stage 1 HPT Rotor Disk (PN 6031T89, PN 6078T93, and all reworked PN rotor disks)

SEI-58272-52-00, INSPECTION

All areas (FPI) 1

Bore (ECI) 2

Boltholes (ECI) 2

Air Holes (ECI) 2

Stage 2 HPT Rotor Disk (PN 6031T90, PN 6078T94, and all reworked PN rotor disks)


All areas (FPI) 1

Bore (ECI) 2

Boltholes (ECI) 2

Air Holes (ECI) 2

HPT Rotor Outer TorqueCoupling PN 5041T67and all reworked PNouter torque couplings)


All areas (FPI) 1

Bore (ECI) 2

1 FPI = Fluorescent Penetrant Inspection Method2 ECI = Eddy Current Inspection Method

GE Aircraft Engines



Page 822Apr 1/03


6. CF34-1A/-3A/-3A2 Engine Maintenance Program - Shop Level Requirements.

A. During the disassembly of any engine component, and before theinstallation of any component, inspect all the components that areremoved, or portions of the components that are exposed. Inspect thecomponents and exposed areas referred to in the published inspectioncriteria in the applicable section in this manual.

B. The replacement intervals for life-limited parts (refer toChapter/Section 5-11-00) must take precedence over all maintenanceactions contained in the Engine Maintenance Program - Shop LevelRequirements. The inspection and maintenance intervals herein aresubject to the cycle life or hourly parts limits as described inChapter/Section 5-11-00.

C. Table 806 contains important time- or cycle-driven shop levelmaintenance actions which are recommended to be done if the engine isremoved from the aircraft for any cause. Based upon enginerefurbishment findings, GE Aircraft Engines will work with operators torecommend additional preventative refurbishment action that must beconsidered.

D. Go to Table 806.

TABLE 806. CF34-1A/-3A/-3A2 ENGINE MAINTENANCE PROGRAM - SHOP LEVELREQUIREMENTS

Inspection/Maintenance Interval

Inspection/MaintenanceRequirements Reference

Inspection of thefan bladeretaining pinholes for:

NOTE: If the cycle since new (CSN) of a used fan blade is not known, use thiscriteria:

� For fan blade serial numbers that are within an operator's fleet,assign to the fan blade the highest CSN of any engine in theoperator's fleet.

� If the blade is not originally owned by the operator, use the highest CSN engine in the CF34 fleet (this information can be obtained from GEAE Product Support Engineering by contacting your technical representative).

GE Aircraft Engines



Page 823Apr 1/03


TABLE 806. CF34-1A/-3A/-3A2 ENGINE MAINTENANCE PROGRAM - SHOP LEVELREQUIREMENTS (Cont)

Inspection/Maintenance Interval

Inspection/MaintenanceRequirements Reference

(1) Fan bladeswithoutbushings.

At 15,000 cycles(but not to exceed15,000 cycles),and every 3,000cycles after the15,000 cycleinspection (referto theNOTE forestablishingcycles).

If the fan blades willnot be reworked, byinstallation of the fanblade retaining pinhole bushing, do anEddy Current Inspection(ECI) of all threeholes of each fanblade.

or

SEI-582,72-00-00,SPECIALPROCEDURES.Inspect per72-21-00,INSPECTION,Table 804.

If the fan blades willbe reworked, byinstallation of the fanblade retaining pin holebushing, send the fanblades to a GEAEapproved repair source.

SEI-582,72-21-00,INSPECTION,Table 804.

(2) Fan bladeswithbushings(PN4923T56).

At 18,000 cyclessince rework bybushinginstallation (butnot to exceed18,000 cycles).Cycles must beestablished fromthe time ofinitial bushinginstallation.

Remove the blades fromservice and scrap thepart.

72-00-00,SPECIALMAINTENANCEPRACTICES.

GE Aircraft Engines


5-11-00HIGHLIGHTSPage 1 of 1

Sep 1/04GE PROPRIETARY INFORMATION - Subject to the restrictions on the cover or first page.

REVISION NO. 29, DATED SEP 1/04

CHAPTER/SECTION DESCRIPTION OF CHANGE PAGE (S)

5-11-02TIME LIMITS

Added forward spool PN 6078T56P05 andits life limits in paragraph 2.

801

5-11-02TIME LIMITS

Revised the life limits for rear spoolPN 5087T46P01/P02 and stage 9 disk PN6087T01P03.

803

5-11-04TIME LIMITS

Added new life limits for stages 3, 4,5, and 6 disks.

801, 803

5-11-05TIME LIMITS

Added a NOTE to clarify the life limitsof the No. 5 bearing carbon sealpreformed packing in paragraph 2.

802

GE Aircraft Engines


LIST OF EFFECTIVE PAGES

* Asterisk indicates pages added, changed, or deleted by this revision.

5-21-00LIST OF EFFECTIVE PAGES

Page 1Sep 1/04



List ofEffectivePages *1 Sep 1/04

Table ofContents 1 Apr 1/03

5-21-00 801 thru 805 Jun 30/97 806 Sep 15/00 806A/806B Sep 15/00 807 Sep 15/00 808 thru 809 Sep 15/99 810 Sep 30/98 811 thru 816 Jun 30/97 817 thru 818 Sep 15/01*819 Sep 1/04 820 thru 821 Sep 15/00 822 thru 823 Apr 1/03


GE Aircraft Engines


5-21-00TABLE OF CONTENTS

Page 1Sep 15/99

TABLE OF CONTENTS

SUBJECTCHAPTER/SECTION PAGE

SCHEDULED MAINTENANCE PROGRAM 5-21-00

General 801Special Tools and Fixtures 801Consumable Materials 802Scheduled Inspection Checks 802

Preliminary Instructions 802Daily Checks (Preflight or Postflight) 802Periodic Inspections 803Mid-Point (3000-Hour) Hot Section Inspection Interval 803

CF34-1A/-3A/-3A2 Engine Maintenance Program - Shop Level Mandatory Inspection Requirements 820

cf34 turbofan engine · cf34 turbofan engine maintenance manual 5-11-00 time limits page 803 sep...

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