B757 RB211-535 Borescope Recurrent Training 2020

FOR REFERENCE ONLY

B757 RB211-535 Borescope Recurrent Training 2020

FOR REFERENCE ONLY

Introduction Borescope inspection is an important practice on any aircraft. Inspection requirements vary by engine type, and in-service activity. Additionally, an inspection may also be called when performance has started to lag.

Whenever you perform your inspection, a special focus needs to fall on the engine and techniques required. A modern jet engine is made to withstand extreme circumstances along with efficient and prolonged use, but they are still subject to damage and wear. Routine inspection and maintenance can help prevent most instances of engine failure and prolong the life of the engine in service. During engine borescope inspection the operator can spot issues that indicate future, or imminent failure.

During a complete inspection using a borescope, most issues can be found before they become an issue. This module has been prepared as part of your continuation training.

Remember to always refer to the correct and current issue of the AMM prior and during an inspection. For training purposes please study the information from the aircraft maintenance manual attached.

http://spiborescopes.com/industries/aviation-aerospace-borescopes/

ENGINE - INSPECTION/CHECK

1. General

A. This procedure has these tasks:

DHI 113-120 PRE SB RB211-72-C230

NOTE: The limits in this section are applicable to phase II engines only. Phase II engines

(ENG3309) have serial numbers below 31720.

DHI 101-121, 301-999 PRE SB RB211-72-C230; PHASE II COMBUSTION

(1) Borescope Equipment Preparation and Use

(2) Prepare the Airplane for the Inspection

(3) Inspection of the Intermediate Pressure (IP) Compressor

(4) Inspection of the High Pressure (HP) Compressor

(5) HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

(6) Combustion Liners Inspection

(7) High Pressure Nozzle Guide Vanes (HPNGV) Inspection

(8) Inspection of the High Pressure (HP) Turbine

(9) Intermediate (IP) Turbine Inspection

(10) Inspection of the Low Pressure (LP) Turbine

(11) Inspection of the 3rd Stage LPT Nozzle Guide Vanes

(12) Remove the Borescope Equipment

(13) Put the Airplane Back to its Usual Condition

B. It is possible to visually examine the gas generator at different positions with the use of the

borescope equipment.

C. The inspection equipment is a 110v/240v AC light box.

(1) You use this to transmit light along a flexible fiber light cable to the probe viewing instrument.

(2) You can use all of the different probe types.

(3) This will let you examine the different areas of the gas generator correctly.

(4) It is possible for you to get a photograph through the probe eyepiece.

D. You can examine the compressor and turbine rotor blades, the internal walls of the combustion liner

and the HP nozzle-guide-vanes.

E. For the inspections of other areas of the engine not given in this procedure, refer to these

procedures:

(1) LP compressor rotor blades and root dampers

(2) LP compressor case

(3) Turbine exhaust system.

TASK 72-00-00-726-210-R02

2. Borescope Equipment Preparation and Use

(Figure 601)

NOTE: This procedure is a scheduled maintenance task.

757AIRCRAFT MAINTENANCE MANUAL

RB211-535 SERIES ENGINES

72-00-00Config 2

Page 601

D633N189 Jan 20/2019ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details

DHI

DHI

DHI

DHI

EFFECTIVITYDHI 101-121, 301-999 PRE SB RB211-72-C230;PHASE II COMBUSTION

FOR REFERENCE ONLY

A. General

(1) This task provides the instructions on how to prepare and use the borescope equipment.

(2) This task lists the inspection equipment, the light-source test and the installation of the

borescope equipment used in the engine inspection.

(3) Borescope Inspection Equipment (Table 601)

Table 601/72-00-00-993-833-R00 Equipment

Supplier Part No. Description Item No. (Figure 601)

Rolls-Royce 1702322 Light source box and case

(NDT LSB-05-150) For use

with all borescopes

1 and 2

Rolls-Royce 1017358 Light source box (NDT LSB

100/ QH) used with 10120948

carrying case

1 and 2

Rolls-Royce 1702227 Cable - light guide (NDT

FLGG/10/15A)

3

Rolls-Royce 1702375 Endoprobe (Green) (NDT 8,

120, 55, 270)

4

Rolls-Royce 1702379 Endoprobe (Blue) (NDT 8,

180, 55, 270)

5

Rolls-Royce 1702374 Endoprobe (Red) (NDT 8, 90,

55 270)

6

Rolls-Royce 1702376 Endoprobe (Yellow) (NDT 8,

70, 55 270)

7


30 265F)

14


10 265F)

15

Rolls-Royce 1702368 Location Stop (NDT A3101E)

use with 1702378

-

Rolls-Royce 1702422 Location Stop (NDT 11, 90,

55, 185F)

-

Rolls-Royce 1702394 Eye Piece (EF/12) 13

Rolls-Royce 1702371 Portable light source box (NDT

KVB-MK.1) For use with all

borescope except 1702319

10

Cable (For use with

item 10)

11

Rolls-Royce 1702393 Right angle viewer (NDT

2/RA3)

12


RAV535)

18



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FOR REFERENCE ONLY

Table 601/72-00-00-993-833-R00 Equipment (Continued)

Supplier Part No. Description Item No. (Figure 601)

Rolls-Royce 1702381 Carrying Case (NDT CC/3) 21

Rolls-Royce 1702319 Flexible Borescope

Rolls-Royce HU19036/1 Impact extractor

Rolls-Royce 89200 Protective workmat

(a) Inspection lamp

(b) Clean, stiff bristled brush

(4) Use the Consumable Material below table below (Table 602):

Table 602/72-00-00-993-834-R00 Consumable Materials

Consumable British

Spec./Ref.

American

Spec./Ref

OMat

Item No.

Degreaser Fluid Acetone OR B.S.509 1964 MIL-D-6998 150

Isopropyl Alcohol OR 1/40

Cleaning Solvent Desoclean

45 P-D-680TY1

1/257

Jointing compound DTD.900/4586 PL.32 (light) - 4/46

High temperature anti-seize

compound

Rocol ASC251T - 4/62

Lockwire DTD.189A 22 S.W.G. 21 A.W.G. 238

B. References

Reference Title

72-00-00 P/B 201 ENGINE - MAINTENANCE PRACTICES

C. Procedure

SUBTASK 72-00-00-846-201-R02

(1) Prepare the equipment for the inspection.

(a) Make sure the switch at the rear of the light source box [1] is at the correct voltage.

(b) Connect the power supply to the light source box.

(c) Set the intensity switch to the lowest light position.

(d) Do a function check of the light source box.

1) Set the power supply to ON and make sure that the red indication light comes on.

2) Put the power supply switch back to the OFF position.

(e) Attach the light cable [3] to the light source box.

NOTE: The flexible borescope has an integral light cable and it is not necessary to

attach the light cable (3).

(f) If you use the portable light source, attach the cable [11] to the portable light source box

[10].

NOTE: The portable light source is used with all borescopes, but not 1702319.



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(g) Attach the applicable borescope to the light cable, or attach the flexible borescope to the

light source box.

(h) Set the power supply to the ON position.

SUBTASK 72-00-00-846-202-R02

(2) Do these steps to use the borescope inspection equipment:

NOTE: After the removal of the borescope plug, it is possible for the HPNGV support ring heat

shield to move on the support ring. There can be axial or circumferential movement

and the two are caused by deterioration of the heat shield. This movement can close

part of the borescope port 'G' on the HP turbine. You can position the heat shield

correctly with your hands to permit the borescope to be put into the port. The engine is

satisfactory with a heat shield that is loose.

(a) Put the borescope through the applicable opening for the inspection to be done.

(b) Turn the IP or the HP system for the compressor or turbine inspection

(PAGEBLOCK 72-00-00/201).

(c) Refer to the applicable inspection.

1) IP Compressor

2) HP Compressor

3) Combustion liners and HPNGV

a) If the inspection through the fuel spray nozzle aperture, do the steps that

follow:

<1> Do an inspection through the fuel spray nozzle aperture.

<a> Remove the borescope stop adapter, if it is attached.

CAUTION

MAKE SURE THE BORESCOPE DOES NOT MOVE

FORWARD OF THE HP OUTLET GUIDE VANES. IF

YOU DO NOT, THE BORESCOPE WILL HIT THE HP

COMPRESSOR STAGE 6 ROTOR BLADES WHEN

THE HP SYSTEM IS TURNED.

MAKE SURE THE FLEXIBLE BORESCOPE DOES

NOT CATCH THE INTERNAL PARTS OF THE

ENGINE.

IF YOU DO NOT DO THIS, DAMAGE TO THE

BORESCOPE COULD OCCUR. ALSO, DAMAGE TO

THE POWER PLANT COULD OCCUR IF THE

BORESCOPE BECOMES BROKEN INSIDE THE

ENGINE.

 Insert the flexible borescope through the fuel spray nozzle

aperture and pass it carefully through the outer diffuser of the

combustion liner head section. Then, pass the borescope

between the HP outer guide vanes at their inner platform.

<c> Rotate the HP system (PAGEBLOCK 72-00-00/201).



72-00-00Config 2

04



FOR REFERENCE ONLY

CAUTION


NOT CATCH THE INTERNAL DETAILS OF THE

ENGINE. IF YOU DO NOT, DAMAGE TO THE


THE POWERPLANT COULD OCCUR IF THE

BORESCOPE BECOMES CAUGHT OR BROKEN

INSIDE THE ENGINE.

<d> Refer to the HP Compressor inspection given in this procedure.

4) HP Turbine

5) IP Turbine

6) LP Turbine.

(d) Remove the borescope from the engine after the inspection.

SUBTASK 72-00-00-080-005-R00

(3) Disassemble the borescope equipment if it is necessary:

(a) Select power supply switch to OFF. Let the power supply cool for at least 30 seconds.

(b) Remove the borescope and light cable from the light source box.

(c) Disconnect the power supply from the light source box.

END OF TASK



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Cable-light guide

operated)

Portable light source box (battery

Eyepiece cover for item 18

21.

20.

19.

18.

Endoprobe (Red)

Endoprobe (Red)

Steady handle for item 18

Carrying case

Right angle viewer

Tip cover for items 14 and 15

Eyepiece cover for items 14 and 15

Eyepiece adapter

Right angle viewer

Cable - for use with item 10

15.

17.

16.

14.

13.

12.

11.

9.

10.

Tip cover for items 4,5,6 and 7

Length 10.4 inches (265.0 mm)

Diameter 0.433 inch (11.0 mm)



View lateral 90 degrees


Eyepiece cover for items 4,5,6 and 78.



Length 10.6 inches (270.0 mm.)






3.

7.

6.

5.

4.

2.

1.

View retro 70 degrees


View forward 180 degrees

Endoprobe (Gold)

Endoprobe (Red)

Endoprobe (Blue)

Carrying case for item 1

View fore oblique 120 degrees

Endoprobe (Green)

Light source box

277188 S00061280650_V2

Borescope Inspection EquipmentFigure 601/72-00-00-990-929-R02 (Sheet 1 of 3)



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Page 606


EFFECTIVITYDHI 101-121, 301-999 PRE SB RB211-72-C230

FOR REFERENCE ONLY

17

GOLD

INSPECTION

WESTBURY BLUE

14

10

90 ˚

70 ˚

180 ˚

RETROVIEW

8

SWITCH

20

46967

GREEN

RED LATERAL

FORWARD

OBLIQUE

120 ˚

FORWARD

MANUFACTURED BY -

INSTRUMENTS (NDT) LTD

3 WOODLAND IND EST

WILTS-ENGLANDTEL 0373 864287

ENDPROBE COLOR CODE

1

2

3

4

5

6

7

11

12

13

15

16

18

19

21

9POWER SUPPLY

INTENSITY SWITCH

INDICATOR LIGHT

POWER SUPPLY LEAD

POWER SUPPLY SWITCH

277189 S00061280651_V1




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FOR REFERENCE ONLY

FLEXIBLE

BORESCOPE

OPERATING

HANDLE

CONTROL

FOCUS

CABLE TO LIGHT

SOURCE BOX

A2787628357 S00061280652_V1




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FOR REFERENCE ONLY

TASK 72-00-00-866-142-R02

3. Engine Inspection Preparation

(Figure 602)


A. General

(1) This task provides the instructions on how to prepare the engine for the inspection.

B. References

Reference Title

72-03-01-024-007-R00 Compressor Fairing Removal (P/B 401)

78-31-00-912-042-R04 Open the Thrust Reverser (P/B 201)

C. Location Zones

Zone Area

410 No. 1 Powerplant


D. Engine Inspection Preparation

SUBTASK 72-00-00-860-015-R00

(1) For the left engine, open these circuit breakers and install safety tags:

Overhead Circuit Breaker Panel, P11

Row Col Number Name

D 7 C01434 ENGINES STBY IGN L 1


L 1 C01430 LEFT ENGINE IGN 1

SUBTASK 72-00-00-860-016-R00

(2) For the right engine, open these circuit breakers and install safety tags:


Row Col Number Name

D 9 C01437 ENGINES STBY IGN R 1


L 28 C01432 RIGHT ENGINE IGN 1

SUBTASK 72-00-00-860-017-R00

(3) For the left engine, open this circuit breaker and install safety tag:


Row Col Number Name

D 19 C01510 ENGINES START CONT L

SUBTASK 72-00-00-860-018-R00

(4) For the right engine, open this circuit breaker and install safety tag:


Row Col Number Name

D 20 C01511 ENGINES START CONT R



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FOR REFERENCE ONLY

SUBTASK 72-00-00-010-006-R00

WARNING

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST

REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open the thrust reversers (TASK 78-31-00-912-042-R04).

SUBTASK 72-00-00-016-146-R02

(6) Remove the lower-right compressor fairing panel (TASK 72-03-01-024-007-R00).

SUBTASK 72-00-00-016-208-R02

(7) Remove the applicable borescope access plug for the inspection.

NOTE: Use the impact extractor to withdraw the plug(s) if necessary.

NOTE: For the combustion section inspection, remove the blanking plugs at the rear of the

fuel spray nozzles. When you look from the aft of the engine, the No. 1 fuel spray

nozzle is located approximately right of top dead center (Pre SB

RB211-72-C230-Phase 11 Combustion Liners have only eighteen (18) fuel spray

nozzles).

END OF TASK

TASK 72-00-00-206-147-R02

4. Intermediate Pressure (IP) Compressor Inspection

(Figure 602)

A. General

(1) This task provides the instructions on how to examine the IP compressor blades for the

conditions that follow:

(a) Missing annulus filler

(b) Airfoil cracks, nicks, and tears

(c) Airfoil dents and bends

(d) Material missing from the airfoil leading and trailing edges

(e) Airfoil tip damage.

(2) You examine the 1st-stage compressor blades through the front of the engine.

(3) Examine the 2nd thru 6th-stage compressor blades with the borescope equipment.

(4) Use an impact extractor if it is not easy to remove the plugs.

(5) It is not possible to examine these areas of the IP compressor:

(a) The rear of the 1st-stage rotor blades

(b) The front of the 2nd-stage rotor blades

(c) The rear of the 3rd-stage rotor blades

(d) The front of the 4th-stage rotor blades

(e) The rear of the 5th-stage rotor blades

(f) The front of the 6th-stage rotor blades.

(6) Access location, the view area and the number of blades for each compressor stage are as

follows (Table 603):



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FOR REFERENCE ONLY

Table 603/72-00-00-993-809-R02 IP Compressor Inspection Access

Access View Area Number of Blades

Engine Front Front - 1st-Stage 50

IP 2S Rear - 2nd-Stage 57

Front - 3rd-Stage 48

IP 4S Rear - 4th-Stage 53

Front - 5th-Stage 49


NOTE: Borescope access bosses IP 2S, IP 4S, and IP 6S will not look in the center position of the adjacent thickened

section of the case. This is acceptable.

(7) To help you make an estimate of the damage, the acceptance zones on the blades are given

(Figure 606).

B. References

Reference Title

72-00-00-728-003-R00 Intrascope Dress Damaged IP and HP Compressor Blades

(FRS7161) (P/B 801)

72-00-00-980-801-R00 Turn the Intermediate Pressure (IP) System (P/B 201)

C. Location Zones

Zone Area



D. Prepare for the Inspection

SUBTASK 72-00-00-940-011-R00

(1) Do this task: Engine Inspection Preparation, TASK 72-00-00-866-142-R02.

SUBTASK 72-00-00-480-014-R00

(2) Attach the tool to turn the IP system (TASK 72-00-00-980-801-R00).

SUBTASK 72-00-00-080-019-R00

(3) Do this task: Borescope Equipment Preparation and Use, TASK 72-00-00-726-210-R02.

E. Intermediate Pressure (IP) Compressor Inspection

SUBTASK 72-00-00-296-245-R02

(1) Examine the IP compressor blades.

NOTE: To examine the 1st-stage IP compressor blades, use a light source through the LP and

IP compressor inlet guide vanes. Damaged or missing annulus filler is permitted.

NOTE: If you find damage which extends between different zones, compare the chordal width

of the damage in each zone to the limits for that zone.

DHI 113-120 PRE SB RB211-72-C230

NOTE: If damage exists that either requires reinspection or engine rejection, use a printed

copy of Figure 607, Sheet 2 and/or Sheet 3, as applicable, to map the location of each

damaged blade.




72-00-00Config 2

Page 611


DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

(a) Damage is permitted to the limits that follow:

1) Material missing up to a depth of 0.015 inch (0.38 mm) with no related cracks.

2) Nicks and tears from the leading and trailing edges up to 0.015 inch (0.38 mm) in

depth with no related cracks.

NOTE: If you use digital optical measuring equipment, this limit is increased to

0.025 in. (0.64 mm).

3) The material missing is from a previous repair.

NOTE: Missing material from a previous repair will have a smooth contour

appearance.

4) Dents or bends on the 1st stage compressor blades are permitted to the limits that

follow:

a) No related cracks, nicks, or tears.

b) No more than 25 blades with dents or bends along the leading edge that are

more than 1.0 inch (25.4 mm) .

c) No more than 5 blades with dents or bends that change the shape of the blade

more than 0.25 inch (6.35 mm) away from the correct airfoil position.

d) No more than 10 blades with dents or bends in an arc of 12 blades.

e) No more than 4 blades, in an arc of 12 blades, with dents that change the

shape of the blade more than 0.25 inch (6.35 mm) away from the correct airfoil

position.

f) Reject any blade that touches a different blade.

5) Dents or bends on the 2nd stage to the 6th stage compressor blades are permitted

to the limits that follow:

a) No related cracks, nicks, or tears

b) No large bends if the blade touched a different blade.

c) Heat discoloration because of blade tip rub is permitted.

d) Burrs on the training edge tip due to blade tip rub is permitted if they are on 25

percent or less of the blade chord width.

e) Bends or curls are permitted if there is no other damage.

f) Tip missing up to the limits below (30 percent thru chord width) is permitted

only if you examine the subsequent stages for damage:

<1> Stage 1: 0.89 inch (22.6 mm)

<2> Stage 2: 0.76 inch (19.3 mm)

<3> Stage 3: 0.71 inch (18.0 mm)

<4> Stage 4: 0.66 inch (16.7 mm)

<5> Stage 5: 0.66 inch (16.7 mm)

<6> Stage 6: 0.69 inch (17.5 mm).

DHI 113-120 PRE SB RB211-72-C230

6) Tip damage in Zone D.

a) Heat discoloration because of blade tip rub is permitted.

b) Burrs on the training edge tip due to blade tip rub is permitted if they are on 25




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FOR REFERENCE ONLY

DHI 113-120 PRE SB RB211-72-C230 (Continued)

c) Bends or curls are permitted if there is no other damage.

d) Tip missing up to the limits below (30 percent thru chord width) is permitted

only if you examine the subsequent stages for damage:

<1> Stage 1: 0.89 inch (22.6 mm)

<2> Stage 2: 0.76 inch (19.3 mm)

<3> Stage 3: 0.71 inch (18.0 mm)

<4> Stage 4: 0.66 inch (16.7 mm)

<5> Stage 5: 0.66 inch (16.7 mm)

<6> Stage 6: 0.69 inch (17.5 mm).


(b) Damage is permitted to the limits that follow if you do the inspection procedure:

1) Blade cracks, bends, or swirls are permitted up to the limits that follow:

a) One radial crack for each blade tip is permitted if it is not more than 10% of the

true chord width:

<1> Stage 1: 0.30 inch (7.6 mm)

<2> Stage 2: 0.25 inch (6.4 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.22 inch (5.6 mm)

<5> Stage 5: 0.22 inch (5.6 mm)

<6> Stage 6: 0.23 inch (5.8 mm).

b) The crack must not be related to other damage on the blade.

c) Axial cracks, nicks or tears on one edge in Zone A, B, and C are permitted if

the length is not more than 5% of the true chord width:

<1> Stage 1: 0.15 inch (3.8 mm)

<2> Stage 2: 0.13 inch (3.3 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.11 inch (2.8 mm)

<5> Stage 5: 0.11 inch (2.8 mm)

<6> Stage 6: 0.09 inch (2.3 mm).

d) Axial cracks, nicks or tears on the two edges in Zone A, B, and C are

permitted if the length is not more than 2.5% of the true chord width:

<1> Stage 1: 0.07 inch (1.8 mm)

<2> Stage 2: 0.06 inch (1.5 mm)

<3> Stage 3: 0.06 inch (1.5 mm)

<4> Stage 4: 0.06 inch (1.5 mm)

<5> Stage 5: 0.06 inch (1.5 mm)

<6> Stage 6: 0.06 inch (1.5 mm).

e) Axial cracks, nicks or tears on one edge in Zone D are permitted if the length

is not more than 15% of the true chord width:



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FOR REFERENCE ONLY

<1> Stage 1: 0.45 inch (11.4 mm)

<2> Stage 2: 0.38 inch (9.6 mm)

<3> Stage 3: 0.35 inch (8.8 mm)

<4> Stage 4: 0.33 inch (8.3 mm)

<5> Stage 5: 0.34 inch (8.6 mm)

<6> Stage 6: 0.35 inch (8.8 mm).

f) Axial cracks, nicks or tears on the two edges in Zone D are permitted if the

length is not more than 7.5% of the true chord width:

<1> Stage 1: 0.23 inch (5.8 mm)

<2> Stage 2: 0.19 inch (4.8 mm)

<3> Stage 3: 0.18 inch (4.5 mm)

<4> Stage 4: 0.17 inch (4.3 mm)

<5> Stage 5: 0.17 inch (4.3 mm)

<6> Stage 6: 0.17 inch (4.3 mm).

g) Bends or curls together with cracks or tears are permitted if each individual

crack or tear is not longer than 20% of the true chord width:

<1> Stage 1: 0.60 inch (15.2 mm)

<2> Stage 2: 0.50 inch (12.7 mm)

<3> Stage 3: 0.47 inch (11.9 mm)

<4> Stage 4: 0.44 inch (11.1 mm)

<5> Stage 5: 0.44 inch (11.1 mm)

<6> Stage 6: 0.46 inch (11.7 mm).

2) Do three inspections at intervals of between 250 and 350 flight hours and one

inspection at between 800 and 1,000 flight hours.

a) If there is no increase in deterioration or damage, the next inspection is

subject to airlines decision.

(c) Dress the blade by borescope blending (TASK 72-00-00-728-003-R00).

1) It is not necessary to do the inspection procedure if you repair all nicks, cracks, and

tears.

NOTE: It is permitted to do this repair once only on each blade.

NOTE: Make sure that the total number of repaired blades in both the IP and HP

compressor is not more than 10.

2) All axial cracks, nicks, or tears can be blended if they are in the limits that follow:

a) Edges that can be blended are listed below (Table 604):

Table 604/72-00-00-993-810-R02 Access to IP Compressor Blade Edges

IP Compressor Access:

Compressor Stage Leading Edge Trailing Edge

1 No No

2 No Yes

3 Yes No



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Page 614



FOR REFERENCE ONLY

Table 604/72-00-00-993-810-R02 Access to IP Compressor Blade Edges (Continued)

IP Compressor Access:


4 No Yes

5 Yes No

6 Yes Yes

3) Axial cracks, nicks, or tears with length that is not more than 5 percent of the true

chord width on one edge in Zone B can be blended:

a) Stage 1: 0.15 inch (3.8 mm)

b) Stage 2: 0.13 inch (3.2 mm)

c) Stage 3: 0.13 inch (3.2 mm)

d) Stage 4: 0.11 inch (2.8 mm)

e) Stage 5: 0.11 inch (2.8 mm)

f) Stage 6: 0.11 inch (2.8 mm).

4) Axial cracks, nicks, or tears with length that is not longer than ten percent of the true

chord width on one edge in Zones C and D can be blended:






f) Stage 6: 0.23 inch (5.8 mm).

(d) If necessary, damage limits to blades in Zone D can be increased by 50 percent of the

inspection limits for that Zone with this condition:

1) Repair before 5 cycles or 24 flight hours.

NOTE: Use the limit that occurs first.

(e) Damage more than the limits in this procedure must be repaired immediately.

F. Put the Airplane Back to Its Usual Condition

SUBTASK 72-00-00-080-045-R00

(1) Do this task: Borescope Equipment Removal, TASK 72-00-00-946-190-R02.

SUBTASK 72-00-00-080-046-R00

(2) Remove the tool you used to turn the IP system (TASK 72-00-00-980-801-R00).

SUBTASK 72-00-00-840-023-R00

(3) Do this task: Put the Engine Back to Its Usual Condition, TASK 72-00-00-846-191-R02..

END OF TASK



72-00-00Config 2

Page 615



FOR REFERENCE ONLY

BLANKING

COVER, HPNGV

BLANKING

PLUG, LP2

AND LP3

PLUG, LP1

BLANKING

PLUG, IP

BLANKING

PLUG, HPNGV

BLANKING

PIN, HP

BLANKING

AIR SUPPLY

PLATE, HP3

BLANKING

PLUG, IP

BLANKING

PLUG, HP5S

BLANKING

PLUG, HP2S

BLANKING

PLUG, HP1SBLANKING

SPACER

SEESEE B

C

SEE E

FSEE

F

SEE

SEE

SEE

SEESEE

SEE

H

G

D

A

I

J

SEE

H I JF G

EDA B C

68939A

69090

277190 S00061280667_V1

Borescope Access DetailsFigure 602/72-00-00-990-932-R02



72-00-00Config 2

Page 616



FOR REFERENCE ONLY

BLADE

ROTOR

PLATE

RETAINING

LOCKPLATE

PLATE

RETAINING

BORESCOPE

FLEXIBLE NOZZLE APERTURE

FUEL SPRAY

OUTER DIFFUSER

COMBUSTION LINER

STAGE 6 ROTOR

HP COMPRESSORGUIDE VANES

HP OUTLET

PLATFORM

BLADE

EXAMPLE FIELD OF VIEW

FROM THE REAR

SEE K

FWD

KA2785

628729 S00061280668_V1




72-00-00Config 2

Page 617



FOR REFERENCE ONLY

FWD

COMBUSTION

SUPPORT CASE

PLATE

SUPPORT

SEAL RING

PLATE

RETAINING

COMBUSTION

SUPPORT CASE

L

DEE003117

LSEE

K31184 S00061280671_V1




72-00-00Config 2

Page 618



FOR REFERENCE ONLY

97995

INLET GUIDE

VANE

ANNULUS FILLER

IP COMPRESSOR

FWD

LP COMPRESSOR

ANNULUS FILLER

A

SEE A

290486 S00061280673_V1

IP Compressor Inlet Guide Vanes and Front Bearing Housing Support InspectionFigure 605/72-00-00-990-935-R02



72-00-00Config 2

Page 619



FOR REFERENCE ONLY

STAGE 2

(VIEW IN THE FORWARD DIRECTION)

DE00067934A

2.97 INCHES (75.38 mm)

2.52 INCHES (64.08 mm)

2.36 INCHES (60.00 mm)

2.19 INCHES (55.59 mm)

2.21 INCHES (56.06 mm)

2.31 INCHES (58.79 mm)

1ST

2ND

3RD

4TH

5TH

6TH

X

ZONE A = 10% OF BLADE AIRFOIL

ZONE B = 40% OF BLADE AIRFOIL

ZONE C = 25% OF BLADE AIRFOIL

ZONE D = 25% OF BLADE AIRFOIL

DIMENSION Z (TRUE CHORD)DIMENSION X

50

57

48

53

49

46

QTYSTAGE

ZONE D

LEADING

EDGE

Z

ZONE C

ZONE B

ZONE A

5.100 INCHES (129.54 mm)

4.700 INCHES (119.38 mm)

4.300 INCHES (109.22 mm)

3.900 INCHES (99.06 mm)

3.700 INCHES (93.98 mm)

3.500 INCHES (88.9 mm)

NOTE:____

277192 S00061280674_V1

IP Compressor Blades InspectionFigure 606/72-00-00-990-936-R02



72-00-00Config 2

Page 620



FOR REFERENCE ONLY

REJECT

IN AN ARC OF 12

BLADES WITH DENTS OR BENDS

IF THERE ARE 10 OR MORE

REJECT

(6.0mm)

EXCESS OF 0.25 IN

WITH DEFLECTIONS IN

BLADES IN AN ARC OF 12


REJECT

(6.0mm)

IN EXCESS OF 0.25 INCH

BLADES WITH DEFLECTIONS


REJECT

DAMAGE

RADIAL LEADING EDGE

OF 1.0 INCH (25.0mm)

BLADES WITH AN EXCESS


REJECT

OR BENDS

BLADES WITH DENTS


DAMAGED BLADE IDENTIFICATION

THAT INCLUDE DEFLECTIONS

BLADE WITH ANY DENTS OR BENDS

THAN 0.25 INCH (6.0mm)

BLADE WITH DEFLECTIONS OF MOREBLADE WITH NO DAMAGE

BLADE WITH RADIAL LEADING EDGE DAMAGE

OF MORE THAN 1.0 INCH (25.0mm) IN LENGTH

862923 S00061280675_V1

Stage 1 IP Compressor Blades (Examples of Damage) InspectionFigure 607/72-00-00-990-937-R02 (Sheet 1 of 4)



72-00-00Config 2

Page 621


EFFECTIVITYDHI 101-112, 121, 301-999 PRE SB RB211-72-C230

FOR REFERENCE ONLY

REJECT

IN AN ARC OF 12

BLADES WITH DENTS OR BENDS


REJECT

(6.0mm)

EXCESS OF 0.25 IN

WITH DEFLECTIONS IN

BLADES IN AN ARC OF 12


REJECT

(6.0mm)

IN EXCESS OF 0.25 INCH

BLADES WITH DEFLECTIONS


REJECT

DAMAGE

RADIAL LEADING EDGE

OF 1.0 INCH (25.0mm)

BLADES WITH AN EXCESS


REJECT

OR BENDS

BLADES WITH DENTS


EXAMPLE OF STAGE 1 DAMAGED BLADE IDENTIFICATION

THAT INCLUDE DEFLECTIONS

BLADE WITH ANY DENTS OR BENDS

THAN 0.25 INCH (6.0mm)

BLADE WITH DEFLECTIONS OF MOREBLADE WITH NO DAMAGE


OF MORE THAN 1.0 INCH (25.0mm) IN LENGTH

D78617 S00061280676_V1




72-00-00Config 2

Page 622

D633N189 May 20/2018ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details

DHI

DHI

EFFECTIVITYDHI 113-120 PRE SB RB211-72-C230

FOR REFERENCE ONLY

FINDINGS:

IPC

STAGE 1

(QTY. 50)

USING THE SCHEME BELOW, MARK THE BLADES THAT HAVE DAMAGE IN

ZONES A, B OR BOTH:

IPC

STAGE 2

(QTY. 57)

IPC

STAGE 3

(QTY. 48)

NOTE: IF USED, FAX A COMPLETED COPY OF THIS PAGE TO AFW PPOE: ICS 224-1020____

- ZONE A DAMAGE

- ZONE B DAMAGE

- ZONE A AND B DAMAGE

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78689 S00061280677_V1




72-00-00Config 2

Page 623


DHI

DHI


FOR REFERENCE ONLY

FINDINGS:

IPC

STAGE 4

(QTY. 53)


ZONES A, B OR BOTH:

IPC

STAGE 5

(QTY. 49)

IPC

STAGE 6

(QTY. 46)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78731 S00061280678_V1




72-00-00Config 2

Page 624


DHI

DHI


FOR REFERENCE ONLY

TASK 72-00-00-206-154-R02

5. High Pressure (HP) Compressor Inspection

(Figure 602 and Figure 608)

A. General

(1) This task provides the instructions on the inspection of the H.P. compressor blades for the


(a) Airfoil cracks, nicks, and tears.

(b) Airfoil dents and bends.

(c) Material loss on the airfoil leading and trailing edges.

(d) Airfoil tip damage and discoloration.

(2) It is not possible to examine these areas of the H.P. compressor:

(a) The rear of the 4th-stage rotor blades.

(b) The front of the 5th-stage rotor blades.

(c) The rear of the 6th-stage rotor blades.

(3) The access location, the area that can be viewed and the number of blades for each

compressor stage are as follows and (Table 605):

Table 605/72-00-00-993-811-R02 HP Compressor Inspection Access


HP 1S Rear - Stage 1 57

Front - Stage 2 82


Front - Stage 3 94

----- Rear - Stage 3 94

Front - Stage 4 97


Front - Stage 6 74

NOTE: Borescope access bosses HP 1S and HP 2S will not look in the center position of the adjacent thickened section

of the case. This is acceptable.

(4) To help you make an estimate of the damage, refer to the acceptance zones in Figure 608.

B. References

Reference Title


(FRS7161) (P/B 801)

72-00-00-982-026-R00 Turn the High Pressure (HP) System (P/B 201)

C. Location Zones

Zone Area





72-00-00Config 2

Page 625



FOR REFERENCE ONLY

D. Procedure

SUBTASK 72-00-00-846-155-R02

(1) If not already done, do the procedure to prepare the airplane for the inspection.

SUBTASK 72-00-00-496-156-R02

(2) Attach the tool with which you turn the HP system (TASK 72-00-00-982-026-R00).

SUBTASK 72-00-00-946-199-R02

(3) If not already done, do the procedure to prepare the borescope equipment for the inspection.

SUBTASK 72-00-00-296-246-R02

(4) Examine the compressor blades for damage with the limits that follow:

NOTE: If you find damage that extends from one zone into another, compare the chord width

of the damage in each zone with the limit for that zone. All stages of the HP

compressor rotor blades are made with local bends at the tip and the root. These

bends are different to the bends or curls caused by impact damage.

DHI 113-120 PRE SB RB211-72-C230


copy of Figure 608, Sheet 5 and/or sheet 6, as applicable, to map the location of each

damaged blade.



1) Accept missing material up to a depth of 0.015 in. (0.381 mm) with no related

cracks.

2) The material missing is from a related repair.

NOTE: Material missing from a previous repair will have a smooth contour

appearance. Check the module log book.

3) Accept nicks or tears that start on the leading or trailing edges, only if:

a) There are no cracks.

b) The maximum depth of the nick or tear is 0.015 in. (0.381 mm).

NOTE: If a digital optical measurement equipment is used, the limit is

increased to 0.025 inches (0.64 mm).

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

4) Dents or bends are permitted if:

a) There are no related cracks, nicks, or tears.

b) The blade does not touch a different blade.

DHI 113-120 PRE SB RB211-72-C230

5) Dents are permitted if:

a) There are no related cracks, nicks, or tears.

NOTE: Bent blades are not permitted without concurrence from Power Plant

Engineering.


6) Blade tip damage and discoloration in zone D.

a) Accept blade tip discoloration caused by blade tip rub.



72-00-00Config 2

Page 626


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

b) Accept material that is bonded to the blade tip or leading edge.

c) Accept bends or curls that do not have related cracks or tears.

d) Tip missing up to the limits below (33 percent true chord width) is permitted

only if you examine the subsequent stages for damage.

<1> Stage 1: 0.55 inch (13.9 mm)

<2> Stage 2: 0.46 inch (11.7 mm)

<3> Stage 3: 0.40 inch (10.1 mm)

<4> Stage 4: 0.45 inch (11.4 mm)

<5> Stage 5: 0.44 inch (11.2 mm)

<6> Stage 6: 0.42 inch (10.6 mm)

e) The radial length from the tip of the missing piece has no limit. The missing tip

can go from Zone D into Zone C (Figure 608).

<1> Cracks from the tip, which are initially radial and then become axial, are

permitted.

NOTE: This condition can cause tip corner loss.

<2> Cracks which start at the leading or trailing edges and then extent

radially towards the tip are also permitted.


<3> Cracks, which start at the leading or trailing edges and then extend

radially towards the fillet radius are not permitted. For limits on the

corner material lose, see the limits above.

(b) Damage is permitted to the limits that follow if you do the inspection procedure.

1) Blade cracks, bends, or curls are permitted up to the limits that follow:

a) Axial cracks, nicks, tears and material loss on one edge in zone A, B, and C

are permitted if each length is not more than 10 percent of the true chord

width:

<1> Stage 1: 0.17 inch (4.3 mm)

<2> Stage 2: 0.14 inch (3.5 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.14 inch (3.5 mm)

<5> Stage 5: 0.13 inch (3.3 mm)

<6> Stage 6: 0.13 inch (3.3 mm)

b) Axial cracks, nicks, tears and material loss on the two edges in zone A, B, and

C are permitted if each length is not more than 5% of the true chord width:

<1> Stage 1: 0.08 inch (2.0 mm)

<2> Stage 2: 0.07 inch (1.7 mm)

<3> Stage 3: 0.06 inch (1.5 mm)

<4> Stage 4: 0.07 inch (1.7 mm)

<5> Stage 5: 0.07 inch (1.7 mm)

<6> Stage 6: 0.06 inch (1.5 mm)

c) Axial cracks, nicks, tears and material loss on one edge in zone D are

permitted if each length is not more than 20% of the true chord width:



72-00-00Config 2

Page 627



FOR REFERENCE ONLY

<1> Stage 1: 0.33 inch (8.4 mm)

<2> Stage 2: 0.28 inch (7.1 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.27 inch (6.8 mm)

<5> Stage 5: 0.27 inch (6.8 mm)

<6> Stage 6: 0.25 inch (6.4 mm)

d) Axial cracks, nicks, tears and material loss on the two edges in zone D are

permitted if each is not more than 10% of the true chord width:

<1> Stage 1: 0.17 inch (4.3 mm)

<2> Stage 2: 0.14 inch (3.5 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.14 inch (3.5 mm)

<5> Stage 5: 0.13 inch (3.3 mm)

<6> Stage 6: 0.13 inch (3.3 mm)





(c) Dress the blade by borescope blending - Refer to FRS7161

(TASK 72-00-00-728-003-R00).

1) It is not necessary to do the inspection procedure if you repair all cracks, nicks, and

tears.



Compressor is not more than 10.

NOTE: Make sure that the number of repaired blades in HP Compressor stage 1 is

not more than 10.

2) All axial cracks, nicks, or tears can be blended if they are in the limits that follow:

a) Edges that can be blended are listed below:

Table 606/72-00-00-993-812-R02 Access to HP Compressor Blade Edges

HP Compressor Access


1 No Yes

2 Yes Yes

3 Yes Yes

4 Yes No

5 No Yes

6 Yes No

3) HP Compressor stage 1 blades only:



72-00-00Config 2

Page 628



FOR REFERENCE ONLY

a) Axial cracks, nicks, or tears with length that is not more than 0.09 in.

(2.29 mm) of the true chord width on one edge in zones B and C can be

blended.

4) HP Compressor stage 2 to 6 blades only:

a) Axial cracks, nicks, or tears with length that is not more than 5 percent of the

true chord width on one edge in zone B can be blended:

<1> Stage 2: 0.07 inch (1.8 mm)

<2> Stage 3: 0.06 inch (1.5 mm)

<3> Stage 4: 0.07 inch (1.8 mm)

<4> Stage 5: 0.07 inch (1.8 mm)

<5> Stage 6: 0.06 inch (1.5 mm)

b) Axial cracks, nicks, or tears with length that is not longer than 10 percent of

the true chord width on one edge in zone C can be blended.

<1> Stage 2: 0.14 inch (3.6 mm)

<2> Stage 3: 0.12 inch (3.0 mm)

<3> Stage 4: 0.14 inch (3.6 mm)

<4> Stage 5: 0.13 inch (3.3 mm)

<5> Stage 6: 0.13 inch (3.3 mm)

5) All HP Compressor stages:

a) Axial cracks, nicks, or tears with length that is not longer than 10 percent of

the true chord width on one edge in zone D can be blended.

<1> Stage 1: 0.34 inch (8.6 mm)

<2> Stage 2: 0.28 inch (7.1 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.28 inch (7.1 mm)

<5> Stage 5: 0.26 inch (6.6 mm)

<6> Stage 6: 0.25 inch (6.4 mm)

(d) If necessary, the acceptance limits to blades in zone D can be increased if you do the

steps that follow:

1) Damage limits to blades in zone D can be increased by 50 percent of the inspection

limits for that zone.

a) Repair before 5 cycles or 25 flight hours. Use the limit that occurs first.

(e) All damage that is more than the limits given - Do not operate the engine until the engine

is repaired.

SUBTASK 72-00-00-846-159-R02

(5) Do the procedure to put the airplane back to its usual condition.

END OF TASK



72-00-00Config 2

Page 629



FOR REFERENCE ONLY

1.65 INCHES (41.91 mm)

1.35 INCHES (34.29 mm)

X

Z

LEADING

EDGE

ZONE D

STAGE QTY DIMENSION X DIMENSION Z (TRUE CHORD)

57

82

94

97

76

74

DE00067440B

1ST

2ND

3RD

4TH

5TH

6TH

2.30 INCHES (58.3 mm)

1.91 INCHES (48.4 mm)

1.57 INCHES (39.9 mm)

1.34 INCHES (34.1 mm)

1.20 INCHES (30.4 mm)

1.06 INCHES (27.0 mm)

1.39 INCHES (35.31 mm)

1.21 INCHES (30.83 mm)

1.34 INCHES (34.00 mm)

1.26 INCHES (32.13 mm)

EXAMPLE OF STAGES 4, 5 AND 6


ZONE C

ZONE B

ZONE A





NOTE:____

277193 S00061280689_V1

HP Compressor Blades InspectionFigure 608/72-00-00-990-938-R02 (Sheet 1 of 6)



72-00-00Config 2

Page 630



FOR REFERENCE ONLY

PRODUCTION TIP BENDS

STAGE 1

VIEW ON ARROW C

VIEW ON ARROW B

BC

A

VIEW ON ARROW A

LEADING EDGE

CONVEX SURFACE

TRAILING EDGE

69088277194 S00061280690_V1




72-00-00Config 2

Page 631



FOR REFERENCE ONLY

STAGES 2 THRU 6

PRODUCTION TIP BENDS

69298

C

TRAILING EDGE

CONVEX SURFACE

LEADING EDGE

VIEW ON ARROW A

A

B

VIEW ON ARROW B

VIEW ON ARROW C

277195 S00061280691_V1




72-00-00Config 2

Page 632



FOR REFERENCE ONLY

X

CONVEX SURFACELEADING EDGE

Y

EXAMPLE OF STAGE 3

EXAMPLE OF TIP RELEASE

X = 0.250 INCH (6.35 mm)

Y = 0.40 INCH (10.16 mm)

A2962A628756 S00061280692_V1




72-00-00Config 2

Page 633



FOR REFERENCE ONLY

FINDINGS:

HPC

STAGE 1

(QTY. 57)


ZONES A, B OR BOTH:

HPC

STAGE 2

(QTY. 82)

HPC

STAGE 3

(QTY. 94)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78750 S00061280693_V1




72-00-00Config 2

Page 634


DHI

DHI


FOR REFERENCE ONLY

FINDINGS:

HPC

STAGE 4

(QTY. 97)


ZONES A, B OR BOTH:

HPC

STAGE 5

(QTY. 76)

HPC

STAGE 6

(QTY. 74)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78759 S00061280694_V1




72-00-00Config 2

Page 635


DHI

DHI


FOR REFERENCE ONLY

TASK 72-00-00-726-234-R02

6. HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

(Figure 609)

A. General

(1) This task provides the instructions on how to do the inspection on the HP compressor rotor

path liners stages 1 to 4 if the engine has had a high power surge or an uncommanded engine

rundown.

NOTE: "High power surge" is defined as a surge at cruise power and above.

(2) Access locations are as follows (Table 607):

Table 607/72-00-00-993-813-R02 HP Compressor Rotor Path Liner Inspection Access

Access Location View Area

HP1S B Stage 1

HP2S C Stages 2 and 3

Blanking Plate, HP3 Air Supply D Stage 4

B. Location Zones

Zone Area



C. Prepare for the Inspection

SUBTASK 72-00-00-946-235-R02


SUBTASK 72-00-00-946-236-R02

(2) Do this task: Borescope Equipment Preparation and Use, TASK 72-00-00-726-210-R02

D. HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

SUBTASK 72-00-00-026-241-R02

(1) Remove the engine from service for these conditions:

(a) It was not possible to examine a minimum of 90% of all stages of the HP compressor

rotor path liners.

(b) On one individual stage, the liner material has a total missing area greater than 6.20 sq.

inches (4000.0 sq. mm).

(c) One individual area of material loss is greater than 2.325 sq. inches (1500.0 sq. mm).

NOTE: It is not necessary to measure individual areas of lining loss less than 0.078 sq.

inch (50 sq. mm).

NOTE: Compressor rotor path liner “drop out” can leave “cliff edge” features that are

indicated by areas of shadow.

(d) The nominal width and area between the blades of the rotor path liner are given below.

This will help to calculate the damage to the rotor path liner.



72-00-00Config 2

Page 636



FOR REFERENCE ONLY

Table 608/72-00-00-993-814-R02 Width/Area between Blades of the Rotor Path Liner

Width of Rotor Path Liner Area Between Blades

Stage No. of blades Inch mm sq. inches sq. mm

1 57 1.81 46.0 2.82 1820.0

2 82 1.42 36.0 1.52 980.0

3 94 1.06 27.0 0.99 640.0

4 97 1.06 27.0 0.96 620.0

SUBTASK 72-00-00-296-242-R02

(2) Use a 6 mm Flexible borescope to do an inspection of the stage 1 HP compressor rotor path

liner.

(a) Put the borescope through the access HP1S (Location B).

1) Move the borescope forward through the vane and feed 360 degrees in a clockwise

direction, as viewed from the rear.

(b) Slowly pull the borescope back and examine the surface of the rotor path liner.

1) Examine the tip clearance between the compressor rotor blades and the rotor path

liner from an angle.

NOTE: A large shadow that extends away from the blade tip can indicate a large tip

clearance.

2) Make sure that you examine the full width and record the dimensions of all missing

rotor path liner.

(c) Remove the borescope from the engine.

SUBTASK 72-00-00-296-243-R02

(3) Use a 6 mm flexible borescope to do an inspection of the Stage 2 HP compressor rotor path

liner.

(a) Put the borescope through the access HP2S (Location C).







clearance.


rotor path liner.


SUBTASK 72-00-00-296-239-R02

(4) Use a 6 mm flexible borescope to do an inspection of the Stage 3 HP composer rotor path

liner.

(a) Put the borescope through the access HP2S (Location C).

1) Move the borescope rearward through the vane and feed 360 degrees in a

clockwise direction, as viewed from the rear.




72-00-00Config 2

Page 637



FOR REFERENCE ONLY




clearance.

2) Make sure that the full width is examined and record the dimensions of all missing

rotor path liner.


SUBTASK 72-00-00-296-244-R02

(5) Use a 6 mm flexible borescope to do an inspection of the Stage 4 HP compressor rotor path

liner.

(a) Put the borescope through the access HP3 air supply blanking plate (Location D).







clearance.


rotor path lining.


NOTE: Do not let the borescope fall through the cooling air passages on the outer vane

ring. If this happens carefully twist the scope while it is slowly withdrawn from the

passage back into the annulus between the compressor blades and the vanes.

E. Put the Airplane Back to Its Usual Condition

SUBTASK 72-00-00-946-233-R02

(1) Do this task: Put the Engine Back to Its Usual Condition, TASK 72-00-00-846-191-R02.

END OF TASK



72-00-00Config 2

Page 638



FOR REFERENCE ONLY

HP COMPRESSOR

ROTOR BLADES

HP COMPRESSOR

ROTOR PATH

LINER

AREA OF MISSING

HP COMPRESSOR

ROTOR PATH LINER

TYPICAL VIEW THROUGH FLEXIBLE

BORESCOPE

2327024 S0000528599_V1

HP Compressor Rotor Path Liners (Stages 1 to 4) InspectionFigure 609/72-00-00-990-A07-R02 (Sheet 1 of 2)



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HP COMPRESSOR

ROTOR PATH

LINER

TYPICAL VIEW THROUGH A

FLEXIBLE BORESCOPE

HP COMPRESSOR

ROTOR BLADES

A LARGE AREA OF SHADOW

CAN INDICATE A LARGE

SPACE BETWEEN THE HP

COMPRESSOR BLADE TIP

AND THE ROTOR PATH

LINER

2327028 S0000528600_V1




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TASK 72-00-00-206-160-R02

7. Combustion Liners Inspection

(Figure 602, Figure 610, Figure 611 and Figure 612)


A. General

(1) This task provides the instructions on how to examine the combustion liners.

(2) After you do 5 inspections at the intervals given in the limits that follow, you can multiply the

inspection interval by two with this condition:

(a) There is no more deterioration and no new defects are found.

(3) To help you make an estimate of the damage, the acceptance zones on the blades are

provided in this task.

(4) This task examines these components:

(a) Front liner inner and outer walls

(b) Inner and outer ring metering panels and rear inner and outer liners

(c) Front combustion liner heatshields

(d) Fuel spray nozzles

B. References

Reference Title

71-00-00-715-049-R03 Test No. 3 - IP/HP Compressor Airflow Control Test (P/B 501)

71-00-02-004-002-R00 Power Plant Removal (Bootstrap Method) (P/B 401)

71-00-02-004-073-R00 Power Plant Removal (Single Point Sling Method) (P/B 401)

71-00-02-404-003-R00 Power Plant Installation (Bootstrap Method) (P/B 401)

71-00-02-404-004-R00 Power Plant Installation (Single Point Sling Method) (P/B 401)


73-11-05-004-001-R01 Fuel Spray Nozzles Removal (P/B 401)

73-11-05-404-006-R01 Fuel Spray Nozzles Installation (P/B 401)

C. Location Zones

Zone Area




SUBTASK 72-00-00-846-161-R02


NOTE: If you use the flexible borescope to examine the combustion liner, you must use no

less than four borescope access ports (Location 'F') that are not adjacent. At the next

scheduled borescope inspection of the combustion liner, you must use a different set

of four borescope access ports. If this is not possible, you must remove the nine

borescope access blanks.

SUBTASK 72-00-00-496-162-R02


SUBTASK 72-00-00-946-163-R02




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E. Combustion Liners Inspection

SUBTASK 72-00-00-296-223-R02

(1) Do an inspection of the borescope access holes (Location 'F') for signs of damage to the

sliding rings and the retaining plates.

(a) If you use a rigid borescope for the inspection of the combustion liner, do the steps that

follow:

1) Remove the nine borescope access port blanks (Location 'F').

2) Use the borescope to examine the access port sliding seal ring assembly for these

damages:

a) Sliding seal rings that are damaged or missing.

b) Loss of material, deformation or cracking of the retaining plate.

(b) If you use a flexible borescope for the inspection of the combustion liner, do the steps

that follow:

1) Remove no less than four borescope access port blanks that are not adjacent

(Location 'F').

2) Make a record of the access ports used.

NOTE: For subsequent inspections you must use four different access ports. If you

do not know which access ports were used, you must remove the nine

access port blanks.

3) Use the borescope to examine the access port sliding seal ring assembly for the

damage that follows:

a) Sliding seal rings that are damaged or missing.

b) Loss of material, deformation or cracking of the retaining plate.

NOTE: If you find a sliding seal ring that is damaged or missing, you must do

the inspections at all nine positions.

SUBTASK 72-00-00-296-165-R02

(2) After a known or possible birdstrike in the gas generator system, do the inspection of the heat

shields on the front combustion liner.

F. Inspection Standards

SUBTASK 72-00-00-296-224-R02

(1) Do an inspection of these components:

(a) Front liner inner and outer walls as follows:

1) Cracks

a) It is permitted to have axial or circumferential cracks in the walls or cracks

which extend from the cooling lips up to a maximum length of 1.0 inch (25.4

mm).

b) If an axial or circumferential crack is longer than 1.0 inch (25.4 mm) but less

than 1.25 inches (31.75 mm), do the inspection of the crack(s) again at

intervals of not more than 250 hours.

c) If an axial or circumferential crack is longer than 1.25 inches (31.75 mm), but

less than 1.60 inches (40.55 mm), do the steps that follow.

<1> Continue in service for 50 flight hours.



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<2> If the crack length stays the same, do the inspection at intervals of 50

flight hours but not more than 300 flight hours, then replace the engine

(TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

<3> If the crack length increases or unwanted material is found, then

replace the engine in not more than 5 flight hours


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

d) It is permitted to have axial cracks connected to circumferential cracks as

follows.

<1> The axial or circumferential cracks are not longer than 1.0 inch (25.4

mm).

<2> If the axial or circumferential cracks are longer than 1.0 inch (25.4 mm)

but less than 1.25 inches (31.75 mm), do the inspection again at

intervals of not more than 250 hours.

<3> If the axial or circumferential cracks are longer than 1.25 inches (31.75

mm) but less than 1.60 inches (40.55 mm), do the steps that follow.

<a> Continue in service for 50 flight hours.

 If the crack length stays the same, do the inspection at intervals

of 50 flight hours but not more than 300 flight hours, then replace

the engine (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00).

<c> If the crack length increases or debris is found, then replace the

engine in not more than 5 flight hours

(TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00

and TASK 71-00-02-404-003-R00 or

TASK 71-00-02-404-004-R00).

<4> Material that has extended into the gas stream must not extend more

than 0.50 inch (12.7 mm).

<a> If material has extended into the gas stream more than 0.50 inch

(12.7 mm), replace the engine in less than 100 hours

(TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00

and TASK 71-00-02-404-003-R00 or

TASK 71-00-02-404-004-R00).

<5> Each area of lifted material is not more than 0.25 sq. inch (161.3 sq.

mm).

<6> If the lifted material has released, do these steps:

<a> If the area of lifted material is more than 0.25 sq. inch (161.3 sq.

mm) but less than 0.50 sq. inch (322.6 sq. mm), do the

inspection again at intervals of not more than 250 hours.

 If the area of lifted material is more than 0.50 sq. inch (322.6 sq.

mm) but less than 1.0 sq. inch (645.2 sq. mm), do the inspection

again at intervals of not more than 130 hours.



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<c> If the area of lifted material is more than 1.0 sq. inch (645.2 sq.

mm) but less than 2.0 sq. inches (1290.3 sq. mm), replace

engine in less than 15 hours (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00).

e) It is permitted to have circumferential cracks together with axial cracks

between the two adjacent dilution chutes as follows:

NOTE: Dilution chutes in each group of three are adjacent.

<1> You examine the cracks in less than 300 hours.

<2> Material that has extended into the gas stream must not extend more

than 0.50 inch (12.7 mm).

<3> If more than the above limits, replace the engine in less than 100 hours


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

f) Cracks must not extend forward more than 0.50 inch (12.7 mm) from the

leading edge of the first row of dilution chutes on the inner or outer wall.

g) It is permitted to have cracks in the dilution chute material.

h) If a large quantity of material could be released from the location, replace the

engine in less than 50 hours (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00 or

TASK 71-00-02-404-004-R00).

2) Burns, erosion and distortion

a) It is permitted to have burns or erosion, with distortion or missing material, at

more than one position around the cooling ring lips with these conditions:

<1> The axial length of missing material is not more than 0.50 inch (12.7

mm).

<2> If the axial length of the missing material is more than 0.50 inch (12.7

mm) but less than 0.83 inch (21.00 mm), examine in less than 500

hours.

<3> If the axial length of the missing material is more than 0.83 inch (21.00

mm), do the steps that follow.

<a> Continue in service for 50 flight hours.

 If the dimensions of the burns, erosion, distortion and missing

material stay the same, do the inspection again at intervals of 50

flight hours but not more than 250 flight hours, then replace the

engine (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00).

<c> If the dimensions of the burns, erosion, distortion and missing

material increase during the inspection, replace the engine in not

more than 10 flight hours (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00).

b) It is permitted to have burns or erosion of the dilution chutes.

c) It is permitted to have general distortion if there are no signs of holes.

3) Holes



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a) It is permitted to have a hole caused by burns and/or cracks at a maximum of

4 locations if the size of the hole is not more than 0.25 sq. inch (161.3 sq.

mm).

b) If the hole is larger than 0.25 sq. inch (161.3 sq. mm), examine the rear inner

and outer combustion liners and the HPNGV with these conditions and time

intervals:

<1> If a hole is larger than 0.25 sq. inch (161.3 sq. mm) but less than 0.50

sq. inch (322.6 sq. mm), do the inspection again before 250 hours.

<2> If a hole is larger than 0.50 sq. inch (322.6 sq. mm) but less than 1.0 sq.

inch (645.2 sq. mm), do the inspection again before 130 hours.

<3> If a hole is larger than 1.0 sq. inch (645.2 sq. mm) but less than 2.0 sq.

inches (1290.3 sq. mm), do the inspection again before 65 hours.

<4> If a hole is larger than 2.0 sq. inches (1290.3 sq. mm), replace the

engine before 15 hours (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

4) Loss of thermal barrier coating

a) Permitted

5) Tertiary splitter plates that are loose or gone

a) It is permitted to have this damage as follows:

<1> You examine the rear inner combustion liner and make sure the

damage is not more than the limits given for that inspection.

<2> You examine the HP nozzle-guide-vanes and make sure the damage is

not more than the limits given for that inspection.

<3> You examine the HP turbine blades and make sure the damage is not

more than the limits given for that inspection.

<4> You examine the rear inner combustion liner, the HP

nozzle-guide-vanes and the HP turbine blades again before 130 hours.

(b) Dilution Chutes

1) Material Loss

a) It is permitted to have up to a total of 4 inner or outer wall primary dilution

chutes missing with a maximum of 1 missing in any fuel spray nozzle group on

these conditions:

NOTE: A fuel spray nozzle group of the primary dilution chutes is made up of

3 inner and 3 outer wall primary dilution chutes. The middle one of

each group is axially in line with the fuel spray nozzle when looking

forward.

<1> The condition of the HP Nozzle Guide Vanes do not show signs of

unusual deterioration axially aft of the dilution chute loss position.

<2> You examine the combustion liner and HPNGV at 500 hour intervals.

NOTE: Make sure that you examine carefully the rear liners and HP

NGV's axially aft of the chute loss position.

<3> If you do not see unusual deterioration after the first two 500 hour

inspections, you may continue to borescope the engine at the regular

intervals.



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(c) Front liner inner and outer ring (flare) of the metering panel

1) Cracks

a) It is permitted to have axial cracks if the ring metering panel has not lifted

more than 0.20 inch (5.08 mm).

b) Circumferential cracks are permitted, not more than 1.0 inch (25.4 mm) in

length, with or without adjacent axial cracks, at a maximum of 10 locations as

follows:

<1> The ring metering panel has not lifted more than 0.20 inch (5.08 mm).

c) It is permitted to have cracks that are more than the above steps as follows:

<1> You examine the front liner, inner and outer walls and you find it

serviceable.

<2> You examine the inner and outer walls again before 500 hours of

engine operation.

<3> You examine the metering panel again before 500 hours of engine

operation.

<4> The dimension of material that could be released is not more than 1.0

inch (25.4 mm) circumferentially and 0.75 inch (19.05 mm) axially.

<5> If the dimension of material that could be released is more than 1.0 inch

(25.4 mm) circumferentially and 0.75 inch (19.05 mm) axially, replace

the engine in less than 50 hours (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

2) Burns and erosion

a) It is permitted to have burns and erosion that are not more than 3.0 inches

(76.2 mm) in length circumferentially, and are less than 0.50 inch (12.7 mm)

from the rearward lip.

b) It is permitted to have burns and erosion that are more than the above step as

follows:

<1> You examine the inner and outer walls and make sure the damage is

less than the limits given for that inspection.

<2> You examine the inner and outer walls again before 500 hours of

engine operation.

3) Distortion

a) It is permitted to have ring metering panels that have moved up from their

correct position or are bent not more than 0.20 inch (5.08 mm) as follows:

<1> You examine the inner and outer walls and obey the inspection limits.

<2> You do the inspection again after 500 hours of engine operation.

4) Missing material

a) It is permitted to have missing material (holing) as follows:

<1> Not more than 1.5 sq. inch (967.74 Sq mm) is gone at no more than 10

positions.

<2> You examine the inner and outer walls and make sure the damage is




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<3> You examine the HP nozzle-guide-vanes and make sure the damage is


b) It is permitted to have a loss of the thermal barrier layer.

(d) Rear inner and outer liners

1) Cracks

a) It is permitted to have axial cracks with these conditions:

<1> The crack length is less than 1.0 inch (25.4 mm) and the crack is

closed.

<2> There is a minimum of 1.0 inch (25.4 mm) of good material between

adjacent cracks.

b) It is permitted to have more than one crack in the cooling lip if a crack is not

more than 0.80 inch (20.32 mm) in length.

c) It is permitted to have circumferential cracks with this condition:

<1> The cracks are not less than 1.0 inch (25.4 mm) from the cooling lip and

not longer than 1.0 inch (25.4 mm) in length.

d) It is permitted to have cracks more than the limits as follows:

<1> You examine the crack again in less than 250 hours.

<2> If the material that could be released is more than 1.0 inch (25.4 mm)

circumferentially and 0.75 inch (19.05 mm) axially, replace the engine in

less than 50 hours (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

2) Burns, erosion and distortion

a) It is permitted to have burns and erosion of the cooling lip.

b) It is permitted to have distortion in one area around the cooling lip if it is not

closed fully.

3) Holes

a) It is permitted to have holes in areas 'C' or 'H' in the corrugated flares.

b) It is permitted to have holes in areas 'B' or 'E' as follows:

<1> The damaged area is less than or equal to 1.0 sq. inch (645.16 sq.

mm).

<2> If the damaged area is more than 1.0 sq. inch (645.16 sq. mm), but less

than 2.0 sq. inches (1290.32 sq. mm), do the inspection again before

500 hours of engine operation.

4) Loss of thermal barrier coating:

a) It is permitted to have loss of the thermal barrier coating.

(e) Front combustion liner heatshields

NOTE: The limits that follow are for one heatshield. Limits for loss of material and holes

are for the total amount of such damage in one heatshield.

1) Cracks

a) One crack which comes from the burner aperture at the 6:00 and 12:00 o'clock

positions and which extends across the full section of the heatshield at these

positions is permitted with these conditions:



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<1> The cracks are closed.

<2> The heatshield adjacent to the crack has not lifted.

b) It is permitted to have one crack from fuel spray nozzle opening as follows:

<1> The crack extend circumferentially At the 3:00 and 9:00 o'clock

positions.

c) Cracks more than the above two limits can be accepted with these conditions:

<1> For cracks that connect, the material must not extend more than 0.30

inch (7.62 mm) into the gas stream.

<2> Material release must not be possible in a short time.

<3> All retaining bolts must be in place with no sign that the bolt will come

out.

2) If cracks are more than the above limits, replace the engine in less than 100 hours


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

3) Radial cracks along the rear edges of the radial ramps or cracks along the inner

ramp base are permitted if you obey these limits:

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

a) The cracks are not more than 1.50 inch (38.1 mm) in length.

DHI 113-120 PRE SB RB211-72-C230

b) The cracks are not more than 1.50 inch (38.1 mm) in length.

NOTE: The total length of holes and radial cracks which are emanated from

or terminated into the holes may exceed 1.50 inches. Only the crack

segment is subject to the 1.50 inch limit.

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

c) If the cracks are more than the limits, you must do an inspection again before

130 hours.

DHI 113-120 PRE SB RB211-72-C230

d) If the cracks are more than the limits, or the adjacent retaining bolt lockwelds

are cracked and radial ramp material is lifted, you must do an inspection again

before 130 hours.


4) Circumferential cracks that are less than 0.50 inch (12.7 mm) in length are

permitted.

a) If the cracks are more than the limits, do the inspection again before 130

hours.

b) Missing retaining bolts

<1> It is permitted to have one missing retaining bolt with these conditions:

<a> You do the HPNGV inspection procedure.

 You do the HP turbine blade inspection procedure.



72-00-00Config 2

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<c> Remove the loose bolt from the engine.

NOTE: If necessary, remove the fuel spray nozzle to get to the

bolt (TASK 73-11-05-004-001-R01 and

TASK 73-11-05-404-006-R01).

<d> If you cannot remove the loose bolt, replace the engine before

250 hours or do these steps (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00):

<e> Make sure that the retaining bolt is not in the cavity behind the

heatshield.

<f> Make sure that there is no damage to the fuel spray nozzle

adjacent to the missing bolt.

<g> Make sure that there is no deterioration of the heatshield that

can cause release of the heatshield material.

<h> Do an inspection of the combustor at intervals of 500 hours.

 If more than one bolt is missing, replace the engine before 250

hours (TASK 71-00-02-004-002-R00 or

TASK 71-00-02-004-073-R00 and TASK 71-00-02-404-003-R00

or TASK 71-00-02-404-004-R00).

c) Cracks in the lockweld for the heatshield retaining bolt:

<1> It is permitted to have cracks in the heatshield retaining bolt lockwelds

with these conditions:

<a> There are no signs that the bolt has or will come out.

 If a bolt has started to come out but not released, examine the

bolt in less than 500 hours.

<c> If the bolt has released, use the limit for bolt loss.

NOTE: Be careful when you examine this area around the

retaining bolt lockwelds because it can often be

mistaken for cracks.

d) Loss of material (holing)

<1> Holes that are not more than 0.16 sq. inch (103.23 sq. mm) are

permitted.

NOTE: It is possible that soot collected on the heatshield ramps can

look like holes. A continuous line of cooling holes through the

dark area is a sign that the area is not a hole.

<2> It is permitted to have holes that are more than 0.16 sq. inch (103.23

sq. mm) but less than 0.25 sq. inch (161.3 sq. mm) if you do these

inspections before the next 130 hours:

<a> Inner and outer walls of the front liner

 Inner and outer liners of the rear liners

<c> HP nozzle-guide-vanes

<d> HP turbine blades.



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FOR REFERENCE ONLY

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

<3> If there is more than 0.25 sq. inch (161.3 sq. mm) of missing material

(holes), you must remove the engine before 30 hours.

DHI 113-120 PRE SB RB211-72-C230



NOTE: 0.25 square inches is the equivalent of a hole 0.5 inch by 0.5

inch or a hole 1 inch by 0.25 inch.


e) Corrosion or oxidation (burning)

<1> Burning or oxidation is permitted if you obey the limits that follow:

<a> When a hole is visible, use the limits for holing.

<2> It is permitted to have holes that are more than 0.16 sq. inch (103.23

sq. mm) but less than 0.25 sq. inch (161.3 sq. mm) if you do these

inspections before the next 130 hours:

<a> Inner and outer walls of the front liner

 Inner and outer liners of the rear liners

<c> HP nozzle-guide-vanes

<d> HP turbine blades.

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230



DHI 113-120 PRE SB RB211-72-C230



NOTE: 0.25 square inches is the equivalent of a hole 0.5 inch by 0.5

inch or a hole 1 inch by 0.25 inch.


f) Lifting

<1> If the dimension of gap A or gap E increases relative to the adjacent

shield (heatshield lifting) - replace the engine

.(TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00)

(f) Fuel spray nozzle

1) Missing inner and outer swirler vane

a) If the inner or outer swirler vane is gone, then examine the HP turbine blades

and the HPNGV.

<1> If the HP turbine blades and the HPNGV's are serviceable, replace the

fuel spray nozzle (TASK 73-11-05-004-001-R01 and

TASK 73-11-05-404-006-R01).



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<2> If the HP turbine blades and the HPNGV's are not serviceable, replace



TASK 71-00-02-404-004-R00).

2) Missing shroud ring

a) If the shroud ring installed in the heatshield seal is gone, do an inspection of

the HP turbine blades and the HPNGV's

<1> If the HP turbine blades and the HPNGV's are serviceable, replace the

fuel spray nozzle (TASK 73-11-05-004-001-R01 and

TASK 73-11-05-404-006-R01).

<2> If the HP turbine blades and the HPNGV's are not serviceable, replace



TASK 71-00-02-404-004-R00).

3) Make sure that the fuel spray nozzles are located correctly in the fuel spray nozzle

seals as follows:

a) Refer to the illustration in this task.

<1> If the fuel spray nozzle is not located correctly with the fuel spray nozzle

correctly installed and fastened to the engine case, replace the engine


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

b) Make sure that the fuel spray nozzles aligned with the borescope ports are

concentric with the fuel spray nozzle seals.

<1> If the fuel spray nozzles are not concentric with the fuel spray nozzles

correctly installed and fastened to the engine case, replace the engine


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(g) Combustion Support Case

1) It is permitted to have sliding seal rings missing from the borescope access port (

Location 'F') as follows:

a) There is no deterioration of the combustion liner, support case or the HPNGV's

which is different from the deterioration at the remaining locations.

b) Do a test of the bleed valves (TASK 71-00-00-715-049-R03).

NOTE: If the bleed valve test is not done immediately you must do the

inspections in the intervals listed under 'Bleed Valves Not Tested'. If

the bleed valve test has been completed, you may use the 'Bleed

Valves Serviceable' inspection interval (Table 609).

Table 609/72-00-00-993-815-R02 Combustion Support Case Inspection Criteria

Inspection Intervals

Number of Missing Sliding Seal

RingsBleed Valves Serviceable Bleed Valves Not Tested

1 Usual borescope interval Maximum 250 cycles

2 Usual borescope interval Maximum 100 cycles

3 Maximum 250 cycles Reject the engine



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Table 609/72-00-00-993-815-R02 Combustion Support Case Inspection Criteria (Continued)

Inspection Intervals

Number of Missing Sliding Seal

RingsBleed Valves Serviceable Bleed Valves Not Tested

4 Maximum 100 cycles

More than 4 Reject the engine

2) Cracks, deformation or material loss from the sliding seal ring retaining plate

NOTE: Frettage of a seal through a retaining plate can cause cracks, deformation

or material loss. You can see the damage on the outer surface of the

retaining plate.

a) Use the limits for a missing sliding seal ring (Table 609).

G. Put the Airplane Back to Its Usual Condition

SUBTASK 72-00-00-080-053-R00


SUBTASK 72-00-00-080-054-R00

(2) Remove the tool you use to turn the HP system TASK 72-00-00-982-026-R00.

SUBTASK 72-00-00-840-032-R00


END OF TASK



72-00-00Config 2

Page 652



FOR REFERENCE ONLY

COOLING LIPS

ENGINES WITHOUT RR SB 72-8239;

"A" = 0.700 INCH (17.78 mm)

"A" = 0.600 INCH (15.24 mm)

ENGINES WITH RR SB 72-8239;

USE THE DIMENSIONS SPECIFIED AS A GUIDE WHEN YOU ASSESS THE DAMAGE

"C" = 0.800 INCH (20.32 mm)

"B" = 1.000 INCH (25.40 mm)

PRIMARY OUTER WALL

DILUTION CHUTES

"C""B"

"A"

THE OUTER

WALL

VIEW ON

LINER

OUTER

REAR

METERING PANEL

OUTER RING

59364C*

"A"

***

* *

*

277196 S00061280700_V1

Front Combustion Liner Inner and Outer WallsFigure 610/72-00-00-990-939-R02 (Sheet 1 of 3)



72-00-00Config 2

Page 653



FOR REFERENCE ONLY

NOTE:____

G

F

E

D

EH

G

59536B

DIMENSIONS SPECIFIED ARE A GUIDE TO ASSESSING DAMAGE.

D = 0.375 INCH (9.53 mm)

E = 1.000 INCH DIA (25.4 mm)

F = 0.700 INCH DIA (17.78 mm)

G = 0.900 INCH (22.86 mm)

H = 1.00 INCH (25.4 mm)

* COOLING LIPS

THE INNER

WALL

*

**

*

VIEW ON

LINER

REAR INNER

METERING PANEL

INNER RING

CHUTES

DILUTION

PRIMARY INNER WALL

DILUTION CHUTES

TERTIARY

SPLITTER

PLATE

TERTIARY

SPLITTER

PLATE

277198 S00061280701_V1




72-00-00Config 2

Page 654



FOR REFERENCE ONLY

(OUTER WALL)

(INNER WALL)

PRIMARY OUTER WALL

DILUTION CHUTES

EROSIONHOLE

COOLING LIP

CRACKING AND

BURNING

COOLING LIP

CRACKING

COOLING LIP

MISSING MATERIAL

COOLING LIP

CRACKING

EROSION

HOLE

COOLING

LIP

MISSING

MATERIAL

DILUTION

CHUTES

PRIMARY INNER WALL

DILUTION CHUTES

DEE0010110

1994293 S0000388716_V1




72-00-00Config 2

Page 655



FOR REFERENCE ONLY

ADJACENT SHIELD.

THE COMBUSTION CHAMBER RELATIVE TO THE

66853C

"A" = 0.030 INCH (0.76 mm)

USE THE DIMENSIONS SPECIFIED AS A GUIDE WHEN YOU ASSESS THE DAMAGE

"C"

INNER RAMP

BASEOF THE RADIAL

RAMP

REAR EDGE

FUEL SPRAY

NOZZLE SEAL

OUTER RING

METERING PANEL

DILUTION

CHUTE

INNER

SWIRLEROUTER

SWIRLER

METERING PANEL

INNER RING

OF THE

REAR EDGE

RADIAL RAMP

BOLT

LOCK-WELD

HEATSHIELD

"D"

"B"

"A"

"A"

"E"

"B" = 1.500 INCH (38.1 mm)

"C" = 0.250 INCH (6.35 mm)

"D" = 2.650 INCH (67.36 mm)

"E" = MUST BE CONSISTENT AT EACH POSITION AROUND

277200 S00061280702_V1

Front Combustion Liner HeatshieldFigure 611/72-00-00-990-941-R02



72-00-00Config 2

Page 656



FOR REFERENCE ONLY

NOTE:____

A

E

H

J

I

K

L

M

NO

B

C

D

F

G

O

P

Q

F

C

S

R

A = 0.75 INCH (19.0 mm)

B = 0.55 INCH (14.0 mm)

C = 0.87 INCH (22.0 mm)

D = 1.89 INCH (48.0 mm)

E = 0.57 INCH (14.5 mm)

F = 1.77 INCH (45.0 mm)

G = 1.42 INCH (36.0 mm)

H = 0.71 INCH (18.0 mm)

I = 1.22 INCH (31.0 mm)

J = 2.55 INCH (65.0 mm)

K = 0.79 INCH (20.0 mm)

L = 0.51 INCH (13.0 mm)

M = 0.98 INCH (25.0 mm)

N = 4.06 INCH (103.0 mm)

O = 0.95 INCH (24.0 mm)

P = 0.83 INCH (21.0 mm)

Q = 0.20 INCH (5.0 mm)

R = 2.95 INCH (75.0 mm)

S = 0.39 INCH (10.0 mm)

DIMENSIONS SPECIFIED ARE TO BE USED

AS AN AID WHEN YOU ESTIMATE THE DAMAGE.

2287695 S0000516758_V1

Front Combustion Liner Inner and Outer WallsFigure 612/72-00-00-990-A06-R00



72-00-00Config 2

Page 657



FOR REFERENCE ONLY

TASK 72-00-00-200-802-R02

8. High Pressure Nozzle Guide Vanes (HPNGV) Inspection

(Figure 613)


A. General

(1) This task provides the instructions on how to examine the High Pressure Nozzle Guide Vanes

(HPNGV).

(2) After you do 5 inspections at the intervals given in the limits that follow, you can multiply the

inspection interval by two with this condition:

(a) There is no more deterioration and no new defects are found.

(3) To help you make an estimate of the damage, the acceptance zones on the blades are

provided in this task.

(4) It is not necessary to examine the convex surface of the HPNGV airfoil. You can see some of

the NGV convex surfaces when you do an inspection of the HP turbine blades. If damage is

seen, use the acceptance limits that are given.

B. References

Reference Title





C. Location Zones

Zone Area




SUBTASK 72-00-00-840-027-R02


SUBTASK 72-00-00-840-028-R02


E. High Pressure Nozzle Guide Vanes (HPNGV) Inspection

SUBTASK 72-00-00-200-004-R02

(1) Examine the HPNGV as follows:

(a) Cracks on the Airfoil surface

1) It is permitted to have axial cracks in the concave surface if each is not longer than

1.0 in. (25.4 mm).

a) Make sure that the material does not lift more than 0.020 in. (0.51 mm) into the

gas stream.

2) It is permitted to have radial cracks in the concave surface if each is not longer than

1.0 in. (25.4 mm).


gas stream.



72-00-00Config 2

Page 658



FOR REFERENCE ONLY

3) Accept axial or radial cracks in the concave surface which are longer than 1.0 in.

(25.4 mm) as follows.


gas stream.

b) The cracks are not together.

c) You do an inspection again in less than 500 hours.

d) If material has lifted into the gas stream more than 0.020 in. (0.51 mm),

replace the engine in less than 50 hours (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

4) Radial cracks in the airfoil convex surface

a) Accept radial cracks less than 1.0 in. (25.4 mm) long as follows:

<1> All material that has lifted into the gas stream does not lift more than

0.020 in. (0.51 mm).

<2> The surface has no bulges.

b) Accept radial cracks more than 1.0 in. (25.4 mm) long, but less than 2.0 in.

(50.8 mm) long as follows:

<1> All material that has lifted into the gas stream does not lift more than

0.020 in. (0.51 mm).

<2> The surface does not have bulges.

<3> Do an inspection at 500-hour intervals.

c) Replace the engine in less than 50 hours if the radial cracks are more than

2.0 in. (50.8 mm) long or as follows (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00):

<1> The material has lifted into the gas stream more than 0.020 in.

(0.51 mm).

<2> The surfaces have bulges.

5) Axial cracks in the vane leading edge are permitted with these conditions:

a) Each crack is not longer than 1.0 in. (25.4 mm).

b) The cracks do not extend into the film cooling holes of the convex surface.

c) The material has not lifted into the gas stream more than 0.020 in. (0.51 mm).




TASK 71-00-02-404-004-R00).

6) Radial cracks in the vane leading edge are permitted as follows:

a) Each crack is not longer than 1.0 in. (25.4 mm).

b) The cracks do not extend into the film cooling holes of the convex surface.

c) The material has not lifted into the gas stream more than 0.020 in. (0.51 mm).




TASK 71-00-02-404-004-R00).



72-00-00Config 2

Page 659



FOR REFERENCE ONLY

7) Axial or radial cracks in the vane leading edge longer than 1.0 in. (25.4 mm) are

permitted as follows:

a) The material has not lifted into the gas stream more than 0.020 in. (0.51 mm).

b) If material has lifted into the gas stream more than 0.020 in. (0.51 mm),



TASK 71-00-02-404-004-R00).

c) You must do an inspection again in less than 500 hours.

8) Axial or radial cracks in the vane leading edge that extend into the film cooling holes

of the convex surface are permitted as follows:

a) The material has not lifted into the gas stream more than 0.020 in. (0.51 mm).

b) You must do an inspection again in less than 500 hours.

c) If material has lifted into the gas stream more than 0.020 in. (0.51 mm),



TASK 71-00-02-404-004-R00).

(b) Axial cracks to convex surface

1) Accept axial cracks up to 1.0 in. (25.4 mm) with these conditions:

a) The material that has lifted into the gas stream does not lift more than

0.020 in. (0.51 mm).

b) The surface does not have bulges.

2) Accept axial cracks more than 1.0 in. (25.4 mm), but less than 2.0 in. (50.8 mm)

with these conditions:

a) All material that has lifted into the gas stream does not lift more than 0.020 in.

(0.51 mm).

b) The surface does not have bulges.

c) Do the inspection again at 500 hour intervals.

3) Replace the engine if the axial cracks are more than 2.0 in. (50.8 mm) long or as

follows (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00):

a) The material that has lifted more than 0.020 in. (0.51 mm).

b) The surface has bulges.

4) Replace the engine in less than 50 hours if the cracks connect and the material can

break away from the airfoil surface (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

(c) Cracks in the inner and outer platform

1) It is permitted to have cracks in the ceramic layer.

2) It is permitted to have cracks in the inner and outer platform if the material cannot

break away.

3) Replace the engine in less than 50 hours if the material can break away


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(d) Material decrease



72-00-00Config 2

Page 660



FOR REFERENCE ONLY

1) Replace the engine in less than 50 hours if the material has lifted into the gas

stream more than 0.020 in. (0.51 mm) or can break away from the airfoil surface


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(e) Burns or erosion

1) It is permitted to have burns, erosion and a decrease in the quantity of the ceramic

layer if they have not gone into the base material of the inner or outer platform.

a) If you find burns on the inner or outer platforms, make sure the fuel spray

nozzles are in the correct location in the heatshield seals.

b) Also, you must do an inspection of the front combustion liner.

2) Replace the engine in less than 50 hours, if burns or erosion have gone into the

base material of the inner or outer platform (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

3) Burns, erosion, or holes that go into the vane leading edge are permitted if less than

30 percent of the leading edge is gone.

a) Make sure that no more material will release.

4) Burns, erosion, or holes that go into the vane leading edge are permitted if less than

40 percent of the leading edge is gone.

a) Make sure no more material will release.

b) You must do the inspection again in less than 500 hours.

5) Replace the engine in less than 50 hours, if more than 40 percent of the leading

edge is gone (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(f) Foreign object damage

1) It is permitted to have dents in the airfoil section as follows:

a) You do an inspection of the turbine blades.

2) It is permitted to have nicks and tears in the vane trailing edge with these

conditions:

a) The nicks and tears do not extend forward of the rear row of film cooling holes.

b) You see no burns.

c) Do an inspection of the turbine blades.

3) Replace the engine in less than 50 hours if you find one or more of this condition


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00):

a) Cracks, nicks or tears in the vane leading edge that extend forward of the rear

row of film cooling holes.

NOTE: You must also do an inspection of the turbine blades.

4) Replace the engine if you see any blockage between the vanes


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).


SUBTASK 72-00-00-080-047-R02

(1) Do this task: Borescope Equipment Removal, TASK 72-00-00-946-190-R02



72-00-00Config 2

Page 661



FOR REFERENCE ONLY

SUBTASK 72-00-00-080-048-R02


END OF TASK



72-00-00Config 2

Page 662



FOR REFERENCE ONLY

A = 2.952 INCHES (75.0 mm)

D = 0.500 INCH (12.7 mm)

C = 0.236 INCH (6.0 mm)

B = 0.078 INCH (2.0 mm)

DIMENSIONS SPECIFIED ARE A GUIDE TO ASSESSING DAMAGE

DB

C

A

66855

INNER PLATFORM

(CERAMIC COATED)

OUTER PLATFORM

(CERAMIC COATED)

277202 S00061280703_V1

High Pressure Nozzle Guide Vane (HPNGV) InspectionFigure 613/72-00-00-990-A04-R00



72-00-00Config 2

Page 663



FOR REFERENCE ONLY

TASK 72-00-00-206-167-R02

9. High Pressure (HP) Turbine Inspection



A. General

(1) This task provides the instructions on the HP turbine and the limits that you can accept.


(3) To help you make an estimate of the damage, the acceptance zones on the blades are given in

the HP turbine blades figures.

(4) Examine the borescope access holes.

NOTE: Deterioration of the high pressure nozzle guide vane support ring heatshield may allow

axial and circumferential movement of the heatshield over the support ring. After

removal of the borescope plug this may partially block the HP turbine borescope hole

"G". The heatshield may be repositioned by hand to allow ease of entry of the

borescope. Looseness of the heatshield will not affect engine performance.

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-846-168-R02


SUBTASK 72-00-00-496-169-R02


SUBTASK 72-00-00-946-170-R02


E. HP Turbine Inspection

SUBTASK 72-00-00-296-171-R02

(1) Do the inspection of the HP turbine blades as follows:

(a) Concave and convex airfoil surfaces (Area C)

1) Cracks

a) It is not permitted to have axial cracks.

b) It is permitted to have radial cracks as follow:

<1> The cracks are not more than 0.25 in. (6.35 mm) in length.

<2> The cracks are between 0.25 in. (6.35 mm) and0.5 in. (12.7 mm) in

length with no signs of burns or holes, examine them again before 100

hours.

c) If the radial cracks are longer than0.5 in. (12.7 mm) and burns or holes are not

seen, replace the engine before the next 50 hours.



72-00-00Config 2

4



FOR REFERENCE ONLY

2) Dents

a) It is permitted to have one dent with a round bottom on one of the two surfaces

if it has no related cracks or holes.

3) Replace the engine if the damage is larger than the limits given above.

(b) Shroud

1) Cracks

a) Accept circumferential cracks from the rear face if they are not longer than

0.20 inch (5.08 mm) and they do not turn in the axial direction.

b) It is permitted to have circumferential cracks from the rear face for these

conditions:

<1> The cracks are longer than0.2 in. (5.08 mm) but less than 0.25 in.

(6.35 mm), and they do not turn in the axial direction. You can accept

these cracks if you do an inspection again before 250 hours.

c) It is not permitted to have cracks that are more than the limits above before

250 hours.

d) It is permitted to have cracks that are not open, that extend from the interlock

acute corner but does not extend to the airfoil.

e) It is permitted to have cracks that are not open, that go from the interlock

acute corner but does not extend more than 0.10 inch (2.54 mm) in length to

the airfoil.

<1> The cracks must not be axial.

<2> Do an inspection again before 100 hours.

f) Replace the engine if the cracks are more than the limits given above.

g) It is not permitted to have cracks that are open or burned that extend from the

interlock acute corner.

2) Burns or oxidation

a) It is permitted to have burns or oxidation on the bottom of the outer shroud

near the rear non-interlock faces if you find these conditions:

<1> The increased clearance between the adjacent rear non-interlock faces

is not more than0.035 in. (0.89 mm) around the rotor.

<2> The increased clearance is more than0.035 in. (0.89 mm) around, but

less than 50% around the rotor.

NOTE: The loss of material caused by burns and oxidation causes the

increased clearance between the rear non-interlock faces.

NOTE: You must use a rigid borescope with a 90 degree view angle

and a 10 degree field of view.

b) Replace the engine before 100 hours if the damage from the burns or

oxidation is more than the limits given above.

3) Missing material to the outer shroud of the concave side of the blade.

a) If sections of the outer shroud are missing in Area G, replace the engine

before 25 hours of engine operation are completed.

b) It is permitted to have burning to Area G as follows:




72-00-00Config 2

Page 665



FOR REFERENCE ONLY

4) Interlock damage

a) Replace the engine before 25 hours if sections of the interlock or shroud are

gone.

(c) Leading edge (Area A)

1) Cracks and holes

a) It is permitted to have cracks that are not open, that extend from the leading

edge of the concave airfoil to the shroud fillet radius and into the forward seal

fin.

b) Accept open or burned cracks, or holes in the leading edge if you obey the

limits that follow:

<1> The crack or holes extend from the leading edge of the concave airfoil,

to the shroud fillet radius and into the forward seal fin.

<2> The blade shroud forward seal fin can be seen on each side of the

crack.

<3> The width of the crack in the forward seal fin is not more than 0.06 in.

(1.52 mm).

<4> The difference in the forward seal fin height either side of the crack is

not more than 0.04 in. (1.02 mm).

<5> The total area of open cracks and holes in the leading edge of the

concave airfoil to the shroud fillet radius, for all the blades in the set, is

not more than 0.229 in2 (147.74 mm2).

<6> The area of the open crack or holes on each blade is not more than

0.011 in2 (7.10 mm2).


c) Replace the engine before 50 hours of engine operation, if the width of the

crack in the forward seal fin is more than the above limits.

d) Replace the engine before 50 hours of engine operation, if the forward shroud

seal fin height difference either side of the crack is more than the above limits.

e) Replace the engine before 50 hours of engine operation if the area of the

holes is more than the above limit.

f) Reject axial cracks that are open.

g) It is permitted to have one radial crack if you obey the limits that follow:

<1> The crack is not more than 0.25 in. (6.35 mm) in length.

<2> The crack connects not more than four cooling holes.

<3> The crack must not extend to the airfoil fillet radius.

h) It is permitted to have radial cracks if you obey the limits that follow:


<2> The cracks do not connect more than eight cooling holes.

<3> The cracks must not extend to the radius of the aft airfoil fillet.


i) Replace the engine before 50 hours if these conditions are found:

<1> Radial cracks are more than 0.50 in. (12.70 mm).

<2> There are more than eight cooling holes that are connected.



72-00-00Config 2

Page 666



FOR REFERENCE ONLY

j) Replace the engine before 50 hours if the radial cracks are open, is burned or

extend to the airfoil fillet radius.

2) Foreign object damage (Area A)

a) It is permitted to have foreign object damage if you obey these conditions:

<1> You do not find holes or cracks caused by other damage.


b) Replace the engine before 50 hours if these conditions are found:

<1> There are holes or cracks caused by foreign object damage.

<2> Axial cracks are not permitted.

c) Replace the engine if holes or cracks with related axial cracks are found

because of foreign object damage.

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

3) Erosion (Area A)

a) It is permitted to have erosion if there are no signs of holes caused by erosion.

b) If there are signs of holes caused by erosion, other than as specified in the

limits for open or burned cracks, replace the engine before 50 hours.

DHI 113-120 PRE SB RB211-72-C230

4) Erosion (Area A)

NOTE: Be careful not to confuse deep erosion pockets with holing. Holes resulting

from erosion will expose the leading edge cooling passage of the blade.

a) It is permitted to have erosion if there are no signs of holes caused by erosion.

b) If there are signs of holes caused by erosion, other than as specified in the

limits for open or burned cracks, replace the engine before 50 hours.


(d) Trailing edge (Area B)

1) Cracks

a) Crack length must be measured from the initial position of the trailing edge to

the end of the crack.

b) It is permitted to have more than one crack in the root radius of the trailing

edge, (location xx) if they are not more than 0.125 in. (3.18 mm) in length.

NOTE: Location XX is defined as the area of the trailing edge root radius up

to the first trailing edge cooling hole.

c) It is permitted to have one crack in the root radius of the trailing edge more

than 0.125 in. (3.18 mm) location xx if you obey the limits that follow:

<1> If the crack is more than 0.125 in. (3.18 mm) in length but not more than

0.150 in. (3.81 mm) you must do an inspection again before 500 hours.

<2> If the crack is more than 0.150 in. (3.81 mm) the engine is to be

rejected in less than 50 flight cycles.

d) It is permitted to have cracks from the trailing edge at positions other than the

root or outer shroud radius if you obey the limits that follow:




72-00-00Config 2

Page 667


DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

<2> If the cracks are more than 0.050 in. (1.27 mm) but less than 0.100 in.

(2.54 mm) you must do an inspection again in less than 100 hours.

<3> If the cracks are more than 0.100 in. (2.54 mm) the engine must be

rejected in less than 50 hours.

e) It is permitted to have cracks that extend from the radius of the trailing edge

outer shroud if you obey the limits that follow:


f) It is permitted to have an axial crack that extends from the radius of the trailing

edge outer shroud if more than the above limit if you obey the limits that follow:


<2> Do an inspection before 900 hours.

g) It is permitted to have an axial crack that extends from the radius of the trailing

edge outer shroud if more than the above limit if you obey the limits that follow:


<2> Do an inspection before 450 hours.

h) Replace the engine before 50 hours if the cracks are more than the limits

given above.

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230

2) Burns and oxidation (Area B including location XX)

NOTE: Location XX is defined as the area of the trailing edge root radius up to the

first trailing edge cooling hole.

a) It is permitted to have burns and oxidation at the trailing edge if you obey the

limits that follow:

<1> It is not more than 0.400 in. (10.16 mm) axially from the trailing edge.

<2> Material missing from the trailing edge must not be more than 0.020 in.

(0.51 mm) axial length.

NOTE: Material missing is specified as the amount of material that is

fully missing. It does not refer to areas that are burned or have

oxidation, or if the thickness of the material is decreased.

b) It is permitted to have burns and oxidation more than the limits given in the

step above, if you obey the limits that follow:

<1> The material missing from the trailing edge must not be more than

0.100 in. (2.54 mm) axial length.

<2> Do an inspection before 500 flight hours if this condition occurs.

c) It is permitted to have material missing from the trailing edge of more than

0.100 in. (2.54 mm) axial length but less than 0.120 in. (3.05 mm) axial length,

if you obey the limits that follow:

<1> Do an inspection again at intervals of 100 flight hours.

<a> If no more deterioration is found in not less than three

inspections at 100 flight hour intervals do the step that follows:

 Increase the inspection interval by 100 flight hours to a minimum

of 200 flight but no more than 500 flight hours for each three

inspections if no more deterioration is found.



72-00-00Config 2

Page 668



FOR REFERENCE ONLY

DHI 101-112, 121, 301-999 PRE SB RB211-72-C230 (Continued)

<c> If more deterioration is found during a subsequent inspection you

must decrease the inspection intervals to 100 flight hours

d) Material missing from the trailing edge more than the limits above, reject the

engine before 50 flight hours.

DHI 113-120 PRE SB RB211-72-C230

3) Burns and oxidation (Area B including location XX)



NOTE: Material decrease is defined as the amount of material that is completely

missing. It does not apply to areas that are burned or have oxidation, or if

the thickness of the material is reduced.

a) It is permitted to have burns and oxidation at the trailing edge if you obey the

limits that follow:

<1> It is not more than 0.40 in. (10.16 mm) axially from the trailing edge.

<2> Material decrease from the trailing edge must not be more than 0.02 in.


b) It is permitted to have burns and oxidation more than the limits given in the

step above, if you obey the limits that follow:

<1> The material decrease from the trailing edge must not be more than

0.10 in. (2.54 mm) axial length.

<2> Do an inspection before 500 hours if this condition occurs.

c) Decrease in material from the trailing edge of more than 0.10 in. (2.54 mm)

axial length but less than 0.12 in. (3.05 mm) axial length, inspect every 100

hours.

NOTE: If no further degradation is observed after three successive

inspections at regular times as given in the above inspection criteria,

the re-inspection interval can be extended to twice its original value,

provided the new re- inspection interval does not exceed 500 hours. It

should be noted that if further degradation is subsequently observed,

the inspection interval must be reverted to 100 hours.

d) Decrease in material from the trailing edge more than the limits above, reject

the engine before 50 hours.


4) Foreign object damage (Area B)

a) It is permitted to have dents with smooth, circular bottoms if you do not see

other related holes or cracks.

b) Replace the engine before 50 hours if you see these conditions:

<1> There are dents with related holes or cracks.

<2> There must be no signs of axial cracks.

c) Replace the engine if there are signs of axial cracks caused by dents.

(e) Inner platform



72-00-00Config 2

Page 669


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

1) Missing material at the trailing edges of the inner platform (Areas A and B)

NOTE: Missing material is specified as the amount of material that is missing fully,

and it does not refer to areas of surface erosion, burns, oxidation or a

decrease in material thickness.

a) The limits for missing material between the adjacent blades and trailing edges

on all blades are as follows:

<1> The missing material between adjacent blades in Area A is not more

than 0.200 in. (5.08 mm)axially and 0.060 in. (1.52 mm)

circumferentially

<2> The missing material between adjacent blades at the trailing edge of

the inner platform is not more than 0.120 in. (3.05 mm)

<3> The total area of the missing material for the full set of blades is not

more than 0.465 in2 (300 mm2).

b) If the missing material is more than the above limits, the inspection interval

must be decreased to 500 flight hours.

<1> If the inspection interval is decreased to 500 flight hours, the limits for

the missing material between adjacent blades and the trailing edge are

as follows:

<a> The missing material between adjacent blades in Area B is not

more than 0.354 in. (9.0 mm) axial depth and 0.060 in.

(1.52 mm) circumferentially

 The missing material between adjacent blades at the inner

platform of the trailing edge is not more than 0.200 in. (5.08 mm)

<c> The total area of the missing material for the full set of blades is

not more than 1.085 in2 (700 mm2).

<2> If the axial or circumferential distance of the missing material increases

to more than 0.020 in. (0.51 mm) between inspections. The inspection

interval must be decreased to 250 flight hours.

c) If the missing material is more than the limits in b) <1>, <a>, , or <c> the

engine must be removed in not more than 30 flight cycles.

SUBTASK 72-00-00-296-248-R02

(2) Do an inspection of the borescope access hole in the vane boss of the HP nozzle guide-vane.

NOTE: Make sure you can see the bush in the vane boss. Access is through the casing hole

at location G.

(a) If the bush in the vain boss can be seen, you can accept the engine.

(b) If the bush in the vain boss is missing, you must replace the engine in less than 10 hours.

SUBTASK 72-00-00-290-003-R00

(3) Do an inspection of the borescope access hole in the vane boss of the IP nozzle guide-vane.

NOTE: Make sure you can see the bush in the vane boss. Access is through the casing hole

at location H.

(a) If the bush in the vane boss can be seen, you can accept the engine.

(b) If the bush in the vane boss is missing, you must replace the engine in less than 10

hours.



72-00-00Config 2

Page 670



FOR REFERENCE ONLY


SUBTASK 72-00-00-080-055-R00


SUBTASK 72-00-00-080-056-R00

(2) Remove the tool you use to turn the HP system (TASK 72-00-00-982-026-R00).

SUBTASK 72-00-00-840-033-R00

(3) Do this task:Put the Engine Back to Its Usual Condition, TASK 72-00-00-846-191-R02.

END OF TASK



72-00-00Config 2

Page 671



FOR REFERENCE ONLY

AREA B

AREA CAREA CAREA B

AREA A AREA A

A-A

TRAILING EDGE

AREA B CONCAVE AIRFOIL

AREA C

SURFACE

CONVEX AIRFOIL

AREA C

SURFACE

AREA A

LEADING EDGE

ENGINES PRE-RR-SB 72-9143

LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

A A

ASEE

RB211-535 DE000A7310A

DE000A7310

DE000A7310

760048 S00061280705_V1

HP Turbine Blades InspectionFigure 614/72-00-00-990-943-R02 (Sheet 1 of 9)



72-00-00Config 2

Page 672



FOR REFERENCE ONLY

ENGINES POST-RR-SB 72-9143 AND PRE-RR-SB 72-9677

LEADING EDGE

AREA A

SURFACE

AREA C

CONVEX AIRFOIL

SURFACE

AREA C

CONCAVE AIRFOILAREA B

TRAILING EDGE

B-B

AREA OF CHANGE

(SB 72-9143)

AREA OF CHANGE

(SB 72-9143)

AREA AAREA A

AREA CAREA C

AREA B

AREA B

LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

B B

ASEE

RB211-535 DE000C8222A

DE000C8222

DE000C8222

G02664 S00061280706_V1




72-00-00Config 2

Page 673



FOR REFERENCE ONLY

ENGINES POST-RR-SB 72-9677

C-C

AREA A

AREA C

AREA B

AREA C

AREA A

LEADING EDGE

AREA A

SURFACE

AREA C

SURFACE

CONCAVE AIRFOIL

TRAILING EDGE

AREA B

(SB 72-9677)

AREA C

CONVEX AIRFOIL

AREA B

DE000C8223

DE000C8223

LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

CC

ASEE

RB211-535 DEE000C8223, DEE0007047

A

G02675 S00061280707_V1




72-00-00Config 2

Page 674



FOR REFERENCE ONLY

D

D

D-Ddee9001174

INNER PLATFORM

LEADING EDGE

ADJACENT BLADE

TRAILING EDGE

AREA A

AREA B

LEADING EDGE

0.200 INCH

(5.08 mm)

0.120 INCH

(3.05 mm)

ADJACENT BLADE

0.354 INCH

(9.00 mm)

0.200 INCH

(5.08 mm)

TRAILING EDGE

LEGEND:______

2488239 S0000584415_V1




72-00-00Config 2

Page 675



FOR REFERENCE ONLY

BSEE

DE000C8224

TYPICAL FIELD

OF VIEW BLADE SHROUD

BLADE ROOT

HP TURBINE BLADES

(VIEW IN THE AFT DIRECTION)

DIMENSIONS SPECIFIED ARE A GUIDE TO ASSESSING

DAMAGE.

A = 2.401 INCHES (61.0 mm)

B = 0.078 INCH (2.0 mm) APPROXIMATELY BETWEEN

FILM COOLING AIR HOLES

C = 2.519 INCHES (64.0 mm)

HP TURBINE

BLADES

NOTE:____


A

B

C

B

G02693 S00061280708_V1




72-00-00Config 2

Page 676



FOR REFERENCE ONLY

C

SEE C

DE000C8225


DAMAGE.

A = 2.401 INCHES (61.0 mm)



C = 2.519 INCHES (64.0 mm)

D = 0.051 INCH (3.1 mm) BETWEEN TRAILING EDGE

COOLING AIR HOLES

TYPICAL FIELD

OF VIEW

BLADE ROOT

BLADE SHROUD

HP TURBINE BLADES


A

B

C

D

HP TURBINE

BLADES


NOTE:____

G02700 S00061280709_V1




72-00-00Config 2

Page 677



FOR REFERENCE ONLY

SEE D

DE000C8226

D

HP TURBINE

BLADES

BLADE SHROULD

F

E

X

HP TURBINE BLADES


(TYPICAL FIELD OF VIEW AS VIEWED THROUGH ITEM 14)

(ENDOPROBE)


E = TRAILING EDGE THICKNESS 0.042

INCH (1.07 mm)

F = HOLE SIZE 0.018 INCH (0.46 mm)

DIAMETER

X = 0.094 INCH (2.4 mm) BETWEEN

CENTER OF TRAILING EDGE COOLING

HOLES

DIMENSIONS SPECIFIED ARE A GUIDE TO

ASSESSING DAMAGE.

NOTE:____

G02716 S00061280710_V1




72-00-00Config 2

Page 678



FOR REFERENCE ONLY

DE000C8227

E

SEE E

HP TURBINE

BLADES

NOTE:____ DIMENSIONS SPECIFIED ARE A

GUIDE TO ASSESSING DAMAGE.

E = TRAILING EDGE THICKNESS

0.025 INCH (0.64 mm)


HP TURBINE BLADES



(ENDOPROBE)

BLADE SHROULD

E

G02724 S00061280711_V1




72-00-00Config 2

Page 679



FOR REFERENCE ONLY

SEE F

F

F 1

1

OPEN/BURNT CRACKING

PROPAGATING FROM

CONCAVE AIRFOIL

LEADING EDGE

HP TURBINE BLADES



(ENDOPROBE)

AREA G

DE000C8228

HP TURBINE BLADES



(ENDOPROBE)

TYPICAL INTERLOCK

ACUTE CORNER

CRACKING

TYPICAL REAR

FACE CRACKING

TYPICAL REAR

NON-INTERLOCK

FACE BURNING

AND OXIDATION

NON-INTERLOCK GAP

0.042 INCH

(1.07 mm)

INTERLOCK ACUTE

CORNER OPEN/BURNT

CRACKING

RR ENGINES PRE-SB 72-9677

HP TURBINE

BLADES

G02731 S00061280712_V2




72-00-00Config 2

Page 680



FOR REFERENCE ONLY

SEE A

A 1

2

1

A 2

TYPICAL NOZZLE GUIDE VANE

BOROSCOPE ACCESS HOLE

THIS SHOWS A TYPICAL NGV WITH THE BOROSCOPE ACCESS HOLE BUSHING

IN POSITION.


MISSING. THIS IS NOT PERMITTED.

CASING ACCESS HOLE

(SATISFACTORY)

VANE BOSS VANE BOSSBUSHING

CASING ACCESS HOLE

CASING ACCESS HOLE

(UNSATISFACTORY)

2006260 S0000394288_V2

HP Turbine Borescope Access Hole Bushing InspectionFigure 615/72-00-00-990-987-R00



72-00-00Config 2

Page 681



FOR REFERENCE ONLY

TASK 72-00-00-206-173-R02

10. Intermediate Pressure (IP) Turbine Inspection


A. General

(1) This task provides the instructions on how to inspect the Intermediate Pressure (IP) turbine.

(2) The table that follows has the access location, view area, and number of blades for each

compressor stage.

Table 610/72-00-00-993-816-R02 IP Turbine Inspection Access


LP 1S Trailing Edge - IP 112

LP 1S Leading Edge - LP1 78

(3) To help you make an estimate of the damage, the dimensions specified for the blades are

shown in the task.

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-840-003-R00

(1) If not already done, do this task: Engine Inspection Preparation, TASK 72-00-00-866-142-R02.

SUBTASK 72-00-00-940-001-R00


SUBTASK 72-00-00-480-027-R00


E. Intermediate Pressure (IP) Turbine Inspection

SUBTASK 72-00-00-296-177-R02

(1) Do an inspection of the IP turbine for the conditions that follow:

(a) Cracks

1) Not permitted

(b) Sharp or sudden changes in the leading or trailing edge contour

1) Not permitted

(c) Damage to the blade root or blade shroud platform.

1) It is not permitted to have damage less than 0.50 inch (12.7 mm) in length from the

blade root or 0.20 inch (5.08 mm) in length from the blade shroud platform.

(d) Dents

1) It is permitted to have more than one dent with a smooth bottom if you see these

conditions:



72-00-00Config 2

Page 682



FOR REFERENCE ONLY

a) Leading edge dents must not be more than 0.050 inch (1.27 mm) in length and

there must be a minimum of 0.100 inch (2.54 mm) between dents.

b) Trailing edge dents must not be more than 0.020 inch (0.51 mm) in length and

there must be a minimum of 1.50 inches (38.1 mm) between dents.

c) Airfoil dents must not be more than 0.100 inch (2.54 mm) in diameter.

2) It is permitted to have one dent with a smooth bottom in the leading edge if it is not

longer than 0.125 inch (3.18 mm).

(e) Nicks, scratches on the airfoil surface

1) It is permitted to have nicks and scratches in the airfoil surface if each is not larger

than 0.02 inch (0.51 mm) in width and is not more than 0.05 inch (1.27 mm) in

length.

2) It is permitted to have foreign object spatter.

(f) Spatter

1) Permitted

SUBTASK 72-00-00-296-247-R02

(2) Do an inspection of the borescope access hole in the vane boss of the IP nozzle guide-vane.

NOTE: Make sure you can see the bush in the vane boss.

(a) If the bush in the vane boss can be seen, you can accept the engine.

(b) If the bush in the vane boss is missing, you must replace the engine in less than 10

hours.


SUBTASK 72-00-00-080-002-R00


SUBTASK 72-00-00-080-044-R00

(2) Remove the tool you use to turn the IP system (TASK 72-00-00-980-801-R00).

SUBTASK 72-00-00-840-002-R00


END OF TASK



72-00-00Config 2

Page 683



FOR REFERENCE ONLY

B = 4.493 INCHES (114.13 mm)

A = 1.149 INCHES (29.185 mm)

VIEW IN THE FORWARD DIRECTION

A

QTY 112 BLADES

B

67962

BLADE ROOT

TRAILING EDGE

PLATFORM

SHROUD


277204 S00061280715_V1

IP Turbine Blades inspectionFigure 616/72-00-00-990-951-R02



72-00-00Config 2

Page 684



FOR REFERENCE ONLY

SEE A

A 1

2

1

A 2

TYPICAL NOZZLE GUIDE VANE

BOROSCOPE ACCESS HOLE


IN POSITION.


MISSING. THIS IS NOT PERMITTED.

CASING ACCESS HOLE

(SATISFACTORY)

VANE BOSS VANE BOSSBUSHING

CASING ACCESS HOLE

CASING ACCESS HOLE

(UNSATISFACTORY)

2006260 S0000394288_V2

IP Turbine Borescope Access Hole Bushing InspectionFigure 617/72-00-00-990-989-R00



72-00-00Config 2

Page 685



FOR REFERENCE ONLY

TASK 72-00-00-206-179-R02

11. Low Pressure (LP) Turbine Inspection

(Figure 602)

A. General

(1) This task provides the instructions on how examine the Low Pressure (LP) turbine.


(3) The table that follows has the access location, the view area and the number of blades for

each compressor stage.

Table 611/72-00-00-993-817-R02 LP Turbine Inspection Access


LP 2S Trailing Edge - LP1 78



LP3S *[1] Leading Edge - LP3 64

*[1] You can view the trailing edge of the stage 3 turbine blades through the tail bearing housing with the aid of an

inspection lamp.


the task.

B. Location Zones

Zone Area




SUBTASK 72-00-00-940-012-R00


SUBTASK 72-00-00-940-013-R00


D. Low Pressure (LP) Turbine Inspection

SUBTASK 72-00-00-296-182-R02

(1) Do an inspection of the LP turbine blades as follows:

NOTE: Use an inspection lamp through the tail bearing housing to examine the trailing edge of

the stage 3 turbine blades.

(a) Blade damage

1) Damage to the blade less than 0.50 inch (12.7 mm) from the blade root is not

permitted.

2) Damage that causes a sharp deformation to the contour of the leading and trailing

edge is not permitted.

(b) Cracks

1) Cracks are not permitted.

(c) Dents



72-00-00Config 2

Page 686



FOR REFERENCE ONLY

1) It is permitted to have one dent with a smooth bottom in the leading edge with this

condition:

a) Dents are not more than 0.25 inch (6.35 mm) in length and are not more than

0.020 inch (0.51 mm) in depth.

2) Two dents in each trailing edge are permitted as follow:

a) The dent is not more than 1.0 inch (25.4 mm) long and not more than 0.020

inch (0.51 mm) deep, with no sharp edges.

b) There is a minimum separation of 1.0 inch (25.4 mm) between the dents.

3) A dent on the surface of the airfoil, which causes a protrusion on the same surface

is permitted.as follows:

a) The maximum height of the protrusion is not more than 0.005 inch (0.13 mm).

b) The protrusion is no closer than 0.50 inch (12.7 mm) to the blade shroud or

root radius.

4) Reject all dents that are more than the limits.

(d) Nicks, scratches and spatter

1) It is permitted to have nicks and scratches to the airfoil surface with this condition:

a) Nicks and scratches are not more than 0.050 inch (1.27 mm) in length and is

not more than 0.010 inch (0.25 mm) in depth.

2) It is permitted to have foreign object spatter.

(e) Pin and gas holes

1) A maximum of two holes are permitted on each of the concave and convex airfoil

surfaces.as follows:

a) The maximum diameter of each hole is 0.080 inch (2.03 mm).

b) The holes are not on the leading or trailing edge, or the fillet radii.

c) Only one hole is in the lower 1/3 of the airfoil.


SUBTASK 72-00-00-840-013-R00


SUBTASK 72-00-00-840-014-R00


END OF TASK



72-00-00Config 2

Page 687



FOR REFERENCE ONLY

9.200 INCHES (233.69 mm)

6.768 INCHES (171.92 mm)

DIMENSION B

VIEW IN THE FORWARD DIRECTION

59369

11.143 INCHES (283.05 mm)1.795 INCHES (45.60 mm)3RD 64

2.265 INCHES (57.54 mm)

2.268 INCHES (57.63 mm)

2ND

1ST

DIMENSION A

64

78

QTYSTAGE


A

B

SHROUD

PLATFORM

EDGE

TRAILING

ROOT

BLADE

277205 S00061280718_V1

LP Turbine Blade InspectionFigure 618/72-00-00-990-952-R02



72-00-00Config 2

Page 688



FOR REFERENCE ONLY

FUEL SPRAY NOZZLE MUST BE

POSITIONED A SMALL DISTANCE ABOVE

FUEL SPRAY NOZZLE SEAL LOCATION

DIAMETER, NOT BEHIND THE METERING

PANEL AS SHOWN

FUEL SPRAY

NOZZLE SEAL

LOCATION

DIAMETER

REJECT THE ENGINE

DEE00084411634247 S00061280719_V1

Incorrect Location of the Fuel Spray Nozzle in the Fuel Spray Nozzle SealFigure 619/72-00-00-990-953-R02



72-00-00Config 2

Page 689



FOR REFERENCE ONLY

FUEL SPRAY NOZZLE MUST

BE POSITIONED A SMALL

DISTANCE ABOVE FUEL

SPRAY NOZZLE SEAL

LOCATION DIAMETER,

NOT INSIDE AS SHOWN

REJECT THE ENGINE

THERE MUST NOT BE

A GAP BETWEEN

FUEL SPRAY NOZZLE

AND FUEL SPRAY

NOZZLE SEAL

DEE00084421634248 S00061280720_V1

Moderately Incorrect Location of the Fuel Spray Nozzle in the Fuel Spray Nozzle SealFigure 620/72-00-00-990-954-R02



72-00-00Config 2

Page 690



FOR REFERENCE ONLY

FUEL SPRAY NOZZLE

MUST BE POSITIONED A

SMALL DISTANCE ABOVE

FUEL SPRAY NOZZLE

SEAL LOCATION

DIAMETER AS SHOWN

ACCEPT THE ENGINE

DEE00084431634249 S00061280721_V1

Correct Location of the Fuel Spray Nozzle in the Fuel Spray Nozzle SealFigure 621/72-00-00-990-955-R02



72-00-00Config 2

Page 691



FOR REFERENCE ONLY

TASK 72-00-00-206-184-R02

12. 3rd-Stage LPT Nozzle Guide Vanes Inspection

(Figure 602, Figure 618)

A. General

(1) This task provides the instructions on how to examine the 3rd stage LPT nozzle guide vanes.

(2) The table that follows has the access location, the view area and the number of blades for the

turbine 3rd-stage.

Table 612/72-00-00-993-818-R02 3rd Stage LPT Inspection Access


LP 3S Rear - 3rd-Stage 64


the task.

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-940-016-R00


SUBTASK 72-00-00-480-018-R00


E. 3rd-Stage LPT Nozzle Guide Vanes Inspection

SUBTASK 72-00-00-296-188-R02

(1) Do an inspection of the 3rd-stage nozzle-guide-vane of the LP turbine as follows:

NOTE: Use an inspection lamp through the tail bearing housing to examine the

nozzle-guide-vanes.

(a) Cracks

1) Accept axial cracks not more than 0.75 inch (19.05 mm) in length, provided the

cracks are not closer than 0.050 inch (1.27 mm) to the leading edge or the trailing

edge.

2) Replace the engine before 50 hours if the radial cracks are more than these limits:

a) Radial cracks are not more than 1.0 inch (25.4 mm) in length and are more

than or equal to 1.0 inch (25.4 mm) between them.

b) Cracks must not come together.

c) Cracks must be more than or equal to 0.50 inch (12.7 mm) from the trailing

edge.

(b) Dents and nicks

1) It is permitted to have dents and nicks as follow:



72-00-00Config 2

Page 692



FOR REFERENCE ONLY

a) The dents do not go through the vane.

b) The dents are more than or equal to 0.50 inch (12.7 mm) from the trailing

edge.

2) Replace the engine if the damage to the vanes is more than the limits given above.


SUBTASK 72-00-00-080-025-R00

(1) Remove the tool you used to turn the IP system (TASK 72-00-00-980-801-R00).

SUBTASK 72-00-00-840-015-R00


END OF TASK

TASK 72-00-00-946-190-R02

13. Borescope Equipment Removal


A. General

(1) This task provides the instructions on how remove the borescope equipment.

B. Borescope Equipment Removal

SUBTASK 72-00-00-086-204-R02

(1) Set the power supply switch to the OFF position and let the temperature decrease for 30

seconds.

SUBTASK 72-00-00-086-205-R02

(2) Remove the borescope from the light cable.

NOTE: The light cable on the flexible borescope is an integral part of the probe.

SUBTASK 72-00-00-086-206-R02

(3) Disconnect the light cable from the light source box.

SUBTASK 72-00-00-086-207-R02

(4) Disconnect the power supply from the light source box.

END OF TASK

TASK 72-00-00-846-191-R02

14. Put the Engine Back to Its Usual Condition


A. General

(1) This task provides the instructions on how to put the engine back to its usual condition.

B. References

Reference Title

70-51-00-912-001-R00 Torque Tightening Technique (P/B 201)



72-03-01-424-006-R00 Compressor Fairing Installation (P/B 401)

78-31-00-912-060-R04 Close the Thrust Reverser (P/B 201)



72-00-00Config 2

Page 693



FOR REFERENCE ONLY

C. Consumable Materials

Reference Description Specification

B00713 [OMat 1/257] Solvent - Cleaning OMat 1/257

B50009 [OMat 150] Acetone OMat 150

B50018 [OMat 1/40] Alcohol - Isopropyl OMat 1/40

D00071 Oil - Aircraft Turbine Engine, Synthetic Base MIL-PRF-7808 Grade 3

D00605 [OMat 4/46] Compound - Jointing OMat 4/46 DTD

900/4586

D50115 [OMat 4/62] Compound - Anti-seize, High Temperature OMat 4/62

G01043 Cloth - Lint-free

D. Location Zones

Zone Area



E. Put the Engine Back to Its Usual Condition

SUBTASK 72-00-00-436-193-R02

CAUTION

MAKE SURE THAT THE BORESCOPE PLUGS ARE INSTALLED IN THE

CORRECT PORT LOCATIONS. ENGINE DAMAGE CAN OCCUR IF A

BORESCOPE PLUG IS NOT INSTALLED IN THE CORRECT LOCATION.

(1) Install the access details which were removed to do the borescope inspection of the engine as

follows:

WARNING

DO NOT GET CLEANING SOLVENT IN YOUR MOUTH OR EYES OR ON

YOUR SKIN. DO NOT BREATHE THE FUMES FROM THE CLEANING

SOLVENT. PUT ON A PROTECTIVE SPLASH GOGGLE AND GLOVES

WHEN YOU USE THE CLEANING SOLVENT. KEEP THE CLEANING

SOLVENT AWAY FROM SPARKS, FLAME AND HEAT. THE CLEANING

SOLVENT IS POISONOUS AND FLAMMABLE AND CAN CAUSE INJURY

TO PERSONS OR DAMAGE TO EQUIPMENT.

CAUTION

BE CAREFUL WHEN YOU APPLY THE CLEANING FLUID TO THE

SURFACE. THE SURFACE PROTECTION CAN BE DAMAGED. IF YOU

CAUSE DAMAGE, YOU MUST APPLY NEW PROTECTION TO ALL

DAMAGED AREAS.

(a) Clean the borescope access details.

1) Make a lint-free cloth, G01043 moist with acetone, B50009 [OMat 150], isopropyl

alcohol, B50018 [OMat 1/40], or cleaning solvent, B00713 [OMat 1/257].

2) Clean the faces of the borescope access details that will touch the outer faces of

the engine case when it is assembled.

3) Clean the faces of the engine case that will touch the borescope access details

when it is assembled.

NOTE: Make sure that you remove all of the used jointing compound from the

engine case and the borescope access details.

(b) Install the access details at borescope port A as follows:



72-00-00Config 2

Page 694



FOR REFERENCE ONLY

CAUTION

DO NOT USE THE BOLTS THAT HOLD THE BLANKING PLUG TO

PULL THE PLUG INTO ITS POSITION. IF YOU USE THE BOLTS TO

PULL THE PLUG INTO ITS POSITION, DAMAGE TO THE PLUG OR

ENGINE CAN OCCUR.

1) Apply a thin layer of jointing compound, D00605 [OMat 4/46] to the mating faces of

the blanking plugs, the three spacers, and the engine case.

2) Make sure no jointing compound goes into the central passageways of the three

borescope plugs or the three spacers.

a) Let air dry for 10 minutes.

3) Apply a thin layer of high temperature anti-seize compound, D50115 [OMat 4/62] to

the location surface of the plug end.


4) Put the access details in their correct positions on the LP compressor inner case.

5) Make sure the blanking plugs are in the correct position at their inner end.

6) Make sure the blanking plug mating flanges fully touch the L.P. Compressor case.

7) Apply clean approved engine oil to the threads of the bolts.

8) Install the washers and the bolts.

9) Tighten the bolts (TASK 70-51-00-912-001-R00).

(c) Do this procedure to install the access details at borescope ports B, C, D and E:

CAUTION




ENGINE CAN OCCUR.


the access details.

2) Put the access details in their correct positions on the engine.

3) Make sure the blanking plate plugs are in the correct positions at their inner ends.

4) Make sure the blanking plug mating flanges fully touch the case.


6) Install the bolts.


(d) Do this procedure to install the access details at borescope port G:


the threads and the mating faces of the HPNGV blanking plug.

2) Install the HPNGV blanking plug and tighten to 370 pound-inches (41.81

Newton-meters).


the mating faces of the HPNGV blanking cover.

4) Put the blanking cover in the correct position on the engine.

5) Apply clean approved engine oil, D00071 to the threads of the bolts.




72-00-00Config 2

Page 695



FOR REFERENCE ONLY


DHI 113-120 PRE SB RB211-72-C230

8) Install safety wire or safety cable in any bolts that have a hole to accept safety

wire/cable.


(e) Do this procedure to install the access details at borescope ports F, H, I and J:


the mating faces of the access details.

CAUTION




ENGINE CAN OCCUR.

2) Put the access details in their correct position on the engine.


4) Make sure the blanking plug mating flanges fully touch the case.




DHI 113-120 PRE SB RB211-72-C230


wire/cable.


SUBTASK 72-00-00-080-008-R00

(2) Remove the tools used to turn the IP and HP system (TASK 72-00-00-980-801-R00 and

TASK 72-00-00-982-026-R00).

SUBTASK 72-00-00-416-209-R02

(3) Install the applicable borescope access plug.

SUBTASK 72-00-00-416-195-R02

(4) Install the lower right panel on the compressor fairing (TASK 72-03-01-424-006-R00).

SUBTASK 72-00-00-410-003-R00

(5) Close the thrust reversers (TASK 78-31-00-912-060-R04).

SUBTASK 72-00-00-860-023-R00

(6) For the left engine, remove the safety tags and close these circuit breakers:


Row Col Number Name






72-00-00Config 2

Page 696


DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

SUBTASK 72-00-00-860-024-R00

(7) For the right engine, remove the safety tags and close these circuit breakers:


Row Col Number Name




SUBTASK 72-00-00-860-025-R00

(8) For the left engine, remove the safety tag and close this circuit breaker:


Row Col Number Name


SUBTASK 72-00-00-860-026-R00

(9) For the right engine, remove the safety tag and close this circuit breaker:


Row Col Number Name


END OF TASK



72-00-00Config 2

Page 697



FOR REFERENCE ONLY

ENGINE - INSPECTION/CHECK

1. General

A. This procedure has these tasks:

(1) Borescope Equipment Preparation and Use

(2) Prepare the Engine for the Inspection

(3) Intermediate Pressure (IP) Compressor Inspection

(4) High Pressure (HP) Compressor Inspection

(5) HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

(6) Combustion Liners Inspection

(7) High Pressure Nozzle Guide Vanes (HPNGV) Inspection

(8) High Pressure (HP) Turbine Inspection

(9) Intermediate Pressure (IP) Turbine Inspection

(10) Low Pressure Turbine (LPT) Inspection

(11) LPT Stage 3 Nozzle Guide Vanes (NGV) Inspection

(12) Put the Engine Back to Its Usual Condition.

DHI 113-120 POST SB RB211-72-C230

B. The limits in this section are applicable to phase V engines only. Phase V engines (ENG5239) have

serial numbers 31720 and up.

DHI 101-121, 301-999 POST SB RB211-72-C230; PHASE V COMBUSTION

C. Borescope Equipment Preparation and Use

TASK 72-00-00-206-136-R04

2. Borescope Equipment Preparation and Use

(Figure 601)


A. General

(1) This task lists the inspection equipment, the light-source functional test, and the installation of

the borescope equipment used in the engine inspection.

(2) Borescope Inspection Equipment (Table 601).

Table 601/72-00-00-993-804-R04 Equipment

Supplier Part No. Description

Item No.

(Figure 601)

Rolls-Royce 1702322 Light source box and case

(NDT LSB-05-150) For use

with all borescopes

1 and 2

Rolls-Royce 1017358 Light source box (NDT LSB

100/ QH) used with 10120948

carrying case

1 and 2

Rolls-Royce 1702227 Cable - light guide (NDT

FLGG/10/15A)

3



72-00-00Config 4

Page 601


DHI

DHI

DHI

EFFECTIVITYDHI 101-121, 301-999 POST SB RB211-72-C230;PHASE V COMBUSTION

FOR REFERENCE ONLY

Table 601/72-00-00-993-804-R04 Equipment (Continued)

Supplier Part No. Description

Item No.

(Figure 601)

Rolls-Royce 1702375 Endoprobe (Green) (NDT 8,

120, 55, 270)

4

Rolls-Royce 1702379 Endoprobe (Blue) (NDT 8,

180, 55, 270)

5


55 270)

6

Rolls-Royce 1702376 Endoprobe (Yellow) (NDT 8,

70, 55 270)

7


30 265F)

14


10 265F)

15

Rolls-Royce 1702368 Location Stop (NDT A3101E)

use with 1702378

-

Rolls-Royce 1702422 Location Stop (NDT 11, 90,

55, 185F)

-

Rolls-Royce 1702394 Eye Piece (EF/12) 13

Rolls-Royce 1702371 Portable light source box (NDT

KVB-MK.1) For use with all

borescope except 1702319

10

Cable (For use with

item 10)

11


2/RA3)

12


RAV535)

18

Rolls-Royce 1702381 Carrying Case (NDT CC/3) 21

Rolls-Royce 1702319 Flexible Borescope

Rolls-Royce HU19036/1 Impact extractor

Rolls-Royce 89200 Protective workmat

(a) Inspection lamp

(b) Clean, stiff bristled brush

(3) Use the Consumable Material below table (Table 602):

Table 602/72-00-00-993-805-R04 Consumable Materials

Consumable British

Spec./Ref.

American

Spec./Ref

OMat

Item No.

Degreaser Fluid Acetone OR B.S.509 1964 MIL-D-6998 150



72-00-00Config 4

Page 602



FOR REFERENCE ONLY

Table 602/72-00-00-993-805-R04 Consumable Materials (Continued)

Consumable British

Spec./Ref.

American

Spec./Ref

OMat

Item No.

Isopropyl Alcohol OR 1/40

Cleaning Solvent Desoclean

45 P-D-680TY1

1/257

Jointing compound DTD.900/4586 PL.32 (light) - 4/46

High temperature anti-seize

compound

Rocol ASC251T - 4/62

Lockwire DTD.189A 22 S.W.G. 21 A.W.G. 238

B. References

Reference Title

72-00-00 P/B 201 ENGINE - MAINTENANCE PRACTICES

C. Procedure

SUBTASK 72-00-00-846-138-R04

(1) Prepare the borescope equipment:

(a) Use the switch at the rear of the light source box [1] to select the correct voltage.

(b) Connect the power supply to the light source box.

(c) Set the intensity switch to the lowest light setting.

(d) Do a functional check of the light source box.

1) Set the power supply switch to ON and make sure the red indication light comes on.

Return the switch to OFF.

(e) Attach the light cable [3] to the light source box.

NOTE: The flexible borescope has an integral light cable and does not require the

attachment of light cable [3].

(f) If you use the portable light source , attach the cable [11] to the portable light source box

[10].

NOTE: The portable light source is used with all borescopes except 1702319.

(g) Select and attach a borescope to a light cable, or attach a flexible borescope to a light

source box.

(h) Set the power supply switch to ON.

SUBTASK 72-00-00-846-140-R04

(2) Do these steps to use the borescope equipment:

NOTE: Deterioration of the HPNGV support ring heatshield may allow axial and

circumferential movement of the heatshield over the support ring, after removal of the

borescope plug. This may block access to the HP turbine borescope hole 'K'. The

heatshield may be repositioned by hand to allow ease of entry of borescope.

Looseness of the heatshield will not affect engine integrity.

(a) Put the borescope through the applicable opening for the inspection to be done.

(b) Rotate the IP or HP system (PAGEBLOCK 72-00-00/201), if you do either the

compressor or turbine system inspection.

(c) Refer to the applicable inspection task given in this procedure:



72-00-00Config 4

Page 603



FOR REFERENCE ONLY

1) IP Compressor

2) HP Compressor

3) Combustion liners and HPNGV

a) If the inspection through the fuel spray nozzle aperture, do the steps that

follow:

<1> Do an inspection through the fuel spray nozzle aperture (Figure 602).

<a> Remove the borescope stop adapter, if it is attached.

CAUTION

MAKE SURE THE BORESCOPE DOES NOT MOVE

FORWARD OF THE HP OUTLET GUIDE VANES. IF

YOU DO NOT, THE BORESCOPE WILL HIT THE HP

COMPRESSOR STAGE 6 ROTOR BLADES WHEN

THE HP SYSTEM IS TURNED.


NOT CATCH THE INTERNAL PARTS OF THE

ENGINE.

IF YOU DO NOT DO THIS, DAMAGE TO THE


THE POWER PLANT COULD OCCUR IF THE

BORESCOPE BECOMES BROKEN INSIDE THE

ENGINE.

 Insert the flexible borescope through the fuel spray nozzle

aperture and pass it carefully through the outer diffuser of the

combustion liner head section. Then, pass the borescope

between the HP outer guide vanes at their inner platform.

<c> Rotate the HP system (PAGEBLOCK 72-00-00/201).

CAUTION


NOT CATCH THE INTERNAL DETAILS OF THE

ENGINE. IF YOU DO NOT, DAMAGE TO THE


THE POWERPLANT COULD OCCUR IF THE

BORESCOPE BECOMES CAUGHT OR BROKEN

INSIDE THE ENGINE.

<d> Refer to the HP Compressor inspection given in this procedure.

4) HP Turbine

5) IP Turbine

6) LP Turbine

7) LP Turbine, stage 3 NGV.

(d) Remove the borescope from the engine after the inspection.

SUBTASK 72-00-00-846-142-R04

(3) Disassemble the borescope equipment if it is necessary:

(a) Select power supply switch to OFF. Let the power supply cool for at least 30 seconds.

(b) Remove the borescope and light cable from the light source box.



72-00-00Config 4

Page 604



FOR REFERENCE ONLY

(c) Disconnect the power supply from the light source box.

END OF TASK



72-00-00Config 4

Page 605



FOR REFERENCE ONLY

180 ˚

120 ˚

90 ˚

70 ˚

BLUE FORWARD

OBLIQUE

FORWARDGREEN

LATERALRED

RETROVIEWGOLD

ENDPROBE COLOUR CODE

TEL 0373 864287

WILTS-ENGLAND

WESTBURY

3 WOOSLAND IND EST

INSTRUMENTS(NDT)LTD

INSPECTION

MANUFACTURED BY:

DEE00046967

POWER SUPPLY SWITCH

POWER SUPPLY LEAD

INDICATOR LIGHT

11

1

3

20

INTENSITY SWITCH

SWITCH

POWER SUPPLY97

6

5

4

8

10

13

2

18

12

19

1416

1517

21

H60278 S00061280566_V1

Borescope EquipmentFigure 601/72-00-00-990-896-R04 (Sheet 1 of 2)



72-00-00Config 4

Page 606



FOR REFERENCE ONLY

SOURCE BOX

CABLE TO LIGHT

FOCUS CONTROL

HANDLE

OPERATING

BORESCOPE

FLEXIBLE

DE000A2787H60281 S00061280567_V1

Borescope EquipmentFigure 601/72-00-00-990-896-R04 (Sheet 2 of 2)



72-00-00Config 4

Page 607



FOR REFERENCE ONLY

TASK 72-00-00-846-137-R04

3. Engine Inspection Preparation

(Figure 602)


A. General

(1) This task provides the instructions on how to prepare the engine for the inspection.

B. References

Reference Title


72-03-01-024-007-R00 Compressor Fairing Removal (P/B 401)

78-31-00-912-042-R04 Open the Thrust Reverser (P/B 201)

C. Location Zones

Zone Area



D. Engine Inspection Preparation

SUBTASK 72-00-00-860-019-R00

(1) For the left engine, open these circuit breakers and install safety tags:


Row Col Number Name




SUBTASK 72-00-00-860-020-R00

(2) For the right engine, open these circuit breakers and install safety tags:


Row Col Number Name




SUBTASK 72-00-00-860-021-R00

(3) For the left engine, open this circuit breaker and install safety tag:


Row Col Number Name


SUBTASK 72-00-00-860-022-R00

(4) For the right engine, open this circuit breaker and install safety tag:


Row Col Number Name




72-00-00Config 4

Page 608



FOR REFERENCE ONLY

SUBTASK 72-00-00-010-007-R00

WARNING

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO OPEN THE THRUST

REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open the thrust reversers (TASK 78-31-00-912-042-R04).

SUBTASK 72-00-00-016-155-R04

(6) Remove the lower-right compressor fairing panel (TASK 72-03-01-024-007-R00).

SUBTASK 72-00-00-416-156-R04

(7) Install the IP and HP system turning tools (TASK 72-00-00-982-026-R00).

SUBTASK 72-00-00-016-157-R04

(8) Remove the applicable borescope plugs for the inspection.

NOTE: Use the impact extractor to withdraw the plug(s) if necessary.

NOTE: For the combustion section inspection, remove the blanking plugs at the rear of fuel

spray nozzles 2, 5, 8, 11, 14, 17, 20 and 23, which are numbered clockwise when you

look from aft of the engine. The number 1 nozzle is to the right of the engine top. Make

sure that the C-ring seals have been removed with the blanking plugs.

END OF TASK



72-00-00Config 4

Page 609



FOR REFERENCE ONLY

SEE J

SEE F

SEE E

SEE C

SEE D

SEE G

ASEE

SEE H

SEE BSEE J

J

H G F

E

D

C

B

A

SEAL

SPACER

DEE00Y2221

H60303 S00061280569_V1

Borescope Access DetailsFigure 602/72-00-00-990-898-R04 (Sheet 1 of 3)



72-00-00Config 4

Page 610



FOR REFERENCE ONLY

K

SEE K

SEE J

SEE J

SEE L L

J

SEAL

SEAL

BLANKING COVER

HP NGV

BLANKING PLUG

HP NGV

DEE00Y2222

H60312 S00061280570_V1




72-00-00Config 4

Page 611



FOR REFERENCE ONLY

-

LP1S

-

-

-

B

H

H

A

C

K

J

F

E

D

G

B

B

TURBINE LEADING EDGE

MAINTENANCE

IDENTIFATION

LP3S

LP2S

HP5S

IP6S

HP1S

HP2S

IP4S

IP2S

AREA

INSPECTION

LP2 TURBINE TRAILING EDGE LP3



LP1 TURBINE TRAILING EDGE LP2

IP TURBINE TRAILING EDGE LP1

STAGE 6 FRONT

HP COMPRESSOR, STAGE 5 REAR,


HP TURBINE TRAILING EDGE IP

HP TURBINE LEADING EDGE

STAGE 2 FRONT

IP COMPRESSOR, STAGE 6 REAR

HP COMPRESSOR, STAGE 1 REAR

LEADING EDGE

COMBUSTION CHAMBER AND HPNGV



STAGE 3 FRONT

STAGE 4 FRONT

STAGE 5 FRONT

IP COMPRESSOR, STAGE 4 REAR,

STAGE 3 FRONT

IP COMPRESSOR, STAGE 2 REAR,

ENGINE

DETAILS

LOCATION OF ACCESS

H61346 S00061280571_V1




72-00-00Config 4

Page 612



FOR REFERENCE ONLY

TASK 72-00-00-206-026-R04

4. Intermediate Pressure (IP) Compressor Inspection

(Figure 602, Figure 603 and Figure 604)

A. General

(1) This task provides the instructions on how to examine the IP compressor blades for the


(a) Missing annulus filler

(b) Airfoil cracks, nick, tears

(c) Airfoil dents, bends

(d) Airfoil tip damage

(e) Material missing from the airfoil leading and trailing edges.

(2) Examine the 1st Stage Compressor blades through the front of the engine.

(3) Examine the 2nd-through-6th stage compressor blades with the borescope equipment.

(4) Use an impact extractor if you cannot easily remove the plugs.

(5) It is not possible to examine these areas of the IP Compressor:

(a) The rear of the 1st stage rotor blades.

(b) The front of the 2nd stage rotor blades.

(c) The rear of the 3rd stage rotor blades.

(d) The front of the 4th stage rotor blades.

(e) The rear of the 5th stage rotor blades.

(f) The front of the 6th stage rotor blades.

(6) The access location, the view area, and the number of blades for each compressor stage are

as follows:


Engine Front Front - 1st-Stage 50

IP 2S Rear - 2nd-Stage 57

IP 2S Front - 3rd-Stage 48


IP 4S Front - 5th-Stage 49


NOTE: Borescope access bosses IP 2S, IP 4S, and IP6S will not look in the center position of the

adjacent thickened section of the case. This is acceptable.


Figure 604.

B. References

Reference Title


(FRS7161) (P/B 801)




72-00-00Config 4

Page 613



FOR REFERENCE ONLY

C. Location Zones

Zone Area




SUBTASK 72-00-00-940-019-R00


SUBTASK 72-00-00-480-020-R00


SUBTASK 72-00-00-940-020-R00


E. Intermediate Pressure (IP) Compressor Inspection

DHI 101-112, 121, 301-999 POST SB RB211-72-C230

SUBTASK 72-00-00-296-163-R04

(1) Examine the IP Compressor Blades:

NOTE: To examine the 1st stage IP Compressor blades, use a light source through the LP

and IP Compressor inlet guide vanes. Damaged or missing annulus filler is permitted.


of the damage in each zone to the limit for that zone.


1) Material missing up to a depth of 0.15 inch (0.38 mm) with no related cracks.

2) Nicks and tears from the leading and trailing edges up to 0.015 inch (0.38mm) in



0.025 inch (0.64mm).



appearance.


follow:

a) No related cracks, nicks or tears.


more than 1.0 inch (25.4mm)in radial length.


more than 0.25 inch (6.35mm) away from the correct airfoil position.



shape of the blade more than 0.25 inch (6.35mm) away from the correct airfoil

position.


5) Dents or bends on the 2nd stage to 6th stage compressor blades are permitted to

the limits that follow:



72-00-00Config 4

Page 614



FOR REFERENCE ONLY

DHI 101-112, 121, 301-999 POST SB RB211-72-C230 (Continued)



6) Tip damage in zone D


b) Burrs on the trailing edge tip due to blade tip rub is permitted if they are on 25





<1> Stage 1: 0.89 inch (22.6 mm)

<2> Stage 2: 0.76 inch (19.3 mm)

<3> Stage 3: 0.71 inch (18.0 mm)

<4> Stage 4: 0.66 inch (16.7 mm)

<5> Stage 5: 0.66 inch (16.7 mm)

<6> Stage 6: 0.69 inch (17.5 mm)


1) Blade cracks, bends or curls are permitted up to the limits that follow:

a) One radial crack from the blade tip is permitted if it is not more than 10% of the

true chord width:

<1> Stage 1: 0.30 inch (7.6 mm)

<2> Stage 2: 0.25 inch (6.4 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.22 inch (5.6 mm)

<5> Stage 5: 0.22 inch (5.6 mm)

<6> Stage 6: 0.23 inch (5.9 mm)


c) Axial cracks, nicks, or tears on one edge in Zone A, B and C are permitted if


<1> Stage 1: 0.15 inch (3.8 mm)

<2> Stage 2: 0.13 inch (3.3 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.11 inch (2.8 mm)

<5> Stage 5: 0.11 inch (2.8 mm)

<6> Stage 6: 0.09 inch (2.3 mm)

d) Accept cracks, nicks, or tears on both edges in Zone A, B and C are permitted

if the length is not more than 2.5% of the true chord width:

<1> Stage 1: 0.07 inch (1.8 mm)

<2> Stage 2: 0.06 inch (1.5 mm)

<3> Stage 3: 0.06 inch (1.5 mm)



72-00-00Config 4

Page 615



FOR REFERENCE ONLY

<4> Stage 4: 0.06 inch (1.5 mm)

<5> Stage 5: 0.06 inch (1.5 mm)

<6> Stage 6: 0.06 inch (1.5 mm)

e) Axial cracks, nicks, or tears on one edge in Zone D, are permitted if the length

is not more than 15% of the chord width:

<1> Stage 1: 0.45 inch (11.4 mm)

<2> Stage 2: 0.38 inch (9.6 mm)

<3> Stage 3: 0.35 inch (8.8 mm)

<4> Stage 4: 0.33 inch (8.3 mm)

<5> Stage 5: 0.34 inch (8.6 mm)

<6> Stage 6: 0.35 inch (8.8 mm)

f) Axial cracks, nicks, or tears on both edges within Zone D are permitted if the

individual lengths are not more than 7.5% of the true chord width:

<1> Stage 1: 0.23 inch (5.8 mm)

<2> Stage 2: 0.19 inch (4.8 mm)

<3> Stage 3: 0.18 inch (4.5 mm)

<4> Stage 4: 0.17 inch (4.3 mm)

<5> Stage 5: 0.17 inch (4.3 mm)

<6> Stage 6: 0.17 inch (4.3 mm)

g) Bends or curls together with cracks or tears are permitted if each individual

crack or tear is not longer than 20 percent of the true chord width:

<1> Stage 1: 0.60 inch (15.2 mm)

<2> Stage 2: 0.50 inch (12.7 mm)

<3> Stage 3: 0.47 inch (11.9 mm)

<4> Stage 4: 0.44 inch (11.1 mm)

<5> Stage 5: 0.44 inch (11.1 mm)

<6> Stage 6: 0.46 inch (11.6 mm)

2) Do 3 inspections at intervals of between 250 and 350 flight hours and 1 inspection

at between 800 and 1000 flight hours.




NOTE: It is permitted to do this repair one time only on each blade.



(d) It is not necessary to do the inspection procedure if you repair all nicks, cracks and tears.

1) All axial cracks, nicks or tears can be blended if they are in the limits that follow:




72-00-00Config 4

Page 616



FOR REFERENCE ONLY


IP Compressor Access


1 No No

2 No Yes

3 Yes No

4 No Yes

5 Yes No

6 Yes Yes

2) Axial cracks, nicks or tears with length that is not more than 5 percent of the true

chord width on one edge in zone B can be blended:






f) Stage 6: 0.11 inch (2.8 mm)

3) Axial cracks, nicks or tears with length that is not longer than 10 percent of the true

chord width on one edge in zone C and D can be blended.







(e) If necessary, the acceptance limits for cracks in zone D can be increased if you do the

steps that follow:




(f) Damage more than the limits in this procedure must be repaired immediately.



72-00-00Config 4

Page 617



FOR REFERENCE ONLY

DHI 113-120 POST SB RB211-72-C230

SUBTASK 72-00-00-296-200-R04

(2) Do an inspection of the IP Compressor Blades (Figure 604).

NOTE: To examine the 1st-stage IP blades, use a light source through the LP and IP

compressor inlet guide vanes.


of the damage in each zone to the limit for that zone.



damaged blade.


1) Material missing up to a depth of 0.015 inch (0.38mm) with no related cracks.

2) Nicks and tears from the leading and trailing edges up to 0.015 inch (0.38mm) in



0.025 in (0,64mm).



appearance.


follow:



more than 1.0 inch (25.4 mm) in radial length.


more than 0.25 inch (6.35 mm) away from the correct airfoil position.



shape of the blade more than 0.25 inch (6.35 mm) away from the correct airfoil

position.


5) Dents or bends on the 2nd stage to 6th stage compressor blades are permitted to

the limits that follow:



6) Tip damage in zone D


b) Burrs on the trailing edge tip due to blade tip rub is permitted if they are on 25





<1> Stage 1: 0.89 inch (22.6mm)



72-00-00Config 4

Page 618


DHI

DHI

DHI


FOR REFERENCE ONLY

DHI 113-120 POST SB RB211-72-C230 (Continued)

<2> Stage 2: 0.76 inch (19.3mm)

<3> Stage 3: 0.71 inch (18.0mm)

<4> Stage 4: 0.66 inch (16.7mm)

<5> Stage 5: 0.66 inch (16.7mm)

<6> Stage 6: 0.69 inch (17.5mm)


1) Blade cracks, bends or curls are permitted up to the limits that follow:

a) One radial crack from the blade tip is permitted if it is not more than 10% of the

true chord width:

<1> Stage 1: 0.30 inch (7.6 mm)

<2> Stage 2: 0.25 inch (6.4 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.22 inch (5.6 mm)

<5> Stage 5: 0.22 inch (5.6 mm)

<6> Stage 6: 0.23 inch (5.9 mm)


c) Axial cracks, nicks, or tears on one edge in Zone A, B and C are permitted if


<1> Stage 1: 0.15 inch (3.8 mm)

<2> Stage 2: 0.13 inch (3.2 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.11 inch (2.8 mm)

<5> Stage 5: 0.11 inch (2.8 mm)

<6> Stage 6: 0.09 inch (2.3 mm)

d) Accept cracks, nicks, or tears on both edges in Zone A, B and C are permitted

if the length is not more than 2.5% of the true chord width:

<1> Stage 1: 0.07 inch (1.8 mm)

<2> Stage 2: 0.06 inch (1.5 mm)

<3> Stage 3: 0.06 inch (1.5 mm)

<4> Stage 4: 0.06 inch (1.5 mm)

<5> Stage 5: 0.06 inch (1.5 mm)

<6> Stage 6: 0.06 inch (1.5 mm)

e) Axial cracks, nicks, or tears on one edge in Zone D, are permitted if the length

is not more than 15% of the chord width:

<1> Stage 1: 0.45 inch (11.4 mm)

<2> Stage 2: 0.38 inch (9.6 mm)

<3> Stage 3: 0.35 inch (8.8 mm)

<4> Stage 4: 0.33 inch (8.3 mm)

<5> Stage 5: 0.34 inch (8.6 mm)



72-00-00Config 4

Page 619



FOR REFERENCE ONLY

<6> Stage 6: 0.35 inch (8.8 mm)

f) Axial cracks, nicks, or tears on both edges within Zone D are permitted if the

individual lengths are not more than 7.5% of the true chord width:

<1> Stage 1: 0.23 inch (5.8 mm)

<2> Stage 2: 0.19 inch (4.8 mm)

<3> Stage 3: 0.18 inch (4.5 mm)

<4> Stage 4: 0.17 inch (4.3 mm)

<5> Stage 5: 0.17 inch (4.3 mm)

<6> Stage 6: 0.17 inch (4.3 mm)





(c) Dress the blade by borescope blending (TASK 72-00-00-728-003-R00)

1) It is not necessary to do the inspection procedure if you repair all nicks, cracks and

tears.



Compressor blades is not more than 10.



IP Compressor Access


1 No No

2 No Yes

3 Yes No

4 No Yes

5 Yes No

6 Yes Yes

3) Axial cracks, nicks or tears with length that is not more than 5 percent of the true

chord width on one edge in zone B can be blended:







4) Axial cracks, nicks or tears with length that is not longer than 10 percent of the true

chord width on one edge in zone C and D can be blended.



72-00-00Config 4

Page 620



FOR REFERENCE ONLY








(d) If necessary, the acceptance limits for cracks in zone D can be increased if you do the

steps that follow:




(e) Damage more than the limits in this procedure must be repaired immediately.



SUBTASK 72-00-00-080-027-R00

(1) Remove the borescope equipment (TASK 72-00-00-206-136-R04).

SUBTASK 72-00-00-080-029-R00


SUBTASK 72-00-00-840-017-R00


END OF TASK



72-00-00Config 4

Page 621



FOR REFERENCE ONLY

FWD

DE00097995

ANNULUS FILLER

ANNULUS FILLER LOCZTION

CROSS-SECTION SHOWING

INLET GUIDE VANE

IP COMPRESSOR

ANNULUS FILLER

INLET GUIDE VANE

LP COMPRESSOR

H60337 S00061280596_V1

IP Compressor Inlet Guide Vanes and Front Bearing Housing Support InspectionFigure 603/72-00-00-990-901-R04



72-00-00Config 4

Page 622



FOR REFERENCE ONLY

STAGE

1

2

3

4

5

6

QTY

50

57

48

53

49

46

DIMENSION X

5.100 INCHES (129.54 mm)

4.700 INCHES (119.38 mm)

4.300 INCHES (109.22 mm)

3.900 INCHES (99.06 mm)

3.700 INCHES (93.98 mm)

3.500 INCHES (88.9 mm)

DIMENSION Z (TRUE CHORD)

2.97 INCHES (75.38 mm)

2.52 INCHES (64.08 mm)

2.36 INCHES (60.00 mm)

2.19 INCHES (55.59 mm)

2.21 INCHES (56.06 mm)

2.31 INCHES (58.79 mm)





ZONE B

ZONE A

ZONE C

ZONE D

X

Z

LEADING

EDGE

67934A

STAGE 2


H60369 S00061280597_V1

IP Compressor Blade DimensionsFigure 604/72-00-00-990-902-R04



72-00-00Config 4

Page 623



FOR REFERENCE ONLY

1.0 INCH (25.0 mm) RADIAL

WITH IN EXCESS OF

DE000A9470

INCLUDING DEFLECTIONS

BLADE WITH ANY DENTS AND BENDS

THAN -.25 INCH (6.0 mm)

BLADE WITH DEFLECTION MOREB

D

MORE THAN 1.0 INCH (25.0 mm) IN LENGTH


BLADE WITH NO DAMAGE

A

EXAMPLE OF STAGE 1 DAMAGED BLADE IDENIFICATION

0.25 UNCH (6.0 mm)

IN WXCWSS OF

WITH DEFLECTIONS

IN AN ARC OF 12

4 AND OVER BLADES

REJECT

WITH DENTS OR BENDS

IN AN ARC OF 12

10 AND OVER BLADES

REJECT

IN EXCESS OF

WITH DEFLECTIONS

0.25 INCH (6.0 mm)

5 AND OVER BLADES

REJECT

REJECT

LEADING EDGE DAMAGE

15 AND OVER BLADES

REJECT

WITH DENTS OR BENDS

25 AND OVER BLADES

D78764 S00061280598_V1

IP Compressor Blades InspectionFigure 605/72-00-00-990-904-R04 (Sheet 1 of 3)



72-00-00Config 4

Page 624


EFFECTIVITYDHI 113-120 POST SB RB211-72-C230

FOR REFERENCE ONLY

FINDINGS:

IPC

STAGE 1

(QTY. 50)


ZONES A, B OR BOTH:

IPC

STAGE 2

(QTY. 57)

IPC

STAGE 3

(QTY. 48)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78769 S00061280599_V1




72-00-00Config 4

Page 625



FOR REFERENCE ONLY

FINDINGS:

IPC

STAGE 4

(QTY. 53)


ZONES A, B OR BOTH:

IPC

STAGE 5

(QTY. 49)

IPC

STAGE 6

(QTY. 46)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78770 S00061280600_V1




72-00-00Config 4

Page 626



FOR REFERENCE ONLY

TASK 72-00-00-206-038-R04

5. High Pressure (HP) Compressor Inspection


A. General

(1) This task provides the instructions on how to examine the HP compressor blades for the


(a) Airfoil cracks, nicks or tears.

(b) Airfoil dents and bends.

(c) Material loss on the airfoil leading and trailing edges.

(d) Airfoil tip damage and discoloration.

(2) It is not possible to examine these areas of the HP compressor:

(a) The rear of the 4th-stage rotor blades.

(b) The front of the 5th-stage rotor blades.

(c) The rear of the 6th-stage rotor blades.

(3) The access location, the view area, and the number of blades for each compressor stage are

as follows (Table 603):

Table 603/72-00-00-993-835-R00 HP Compressor Inspection Access


HP 1S *[1] Rear - Stage 1 57

Front - Stage 2 82

HP 2S *[1] Rear - Stage 2 82

Front - Stage 3 94

----- Rear - Stage 3 94

----- Front - Stage 4 97


Front - Stage 6 74

*[1] Borescope access bosses HP 1S and HP 2S will not look in the center position of the adjacent thickened section of

the case. This is acceptable.

(4) To help you make an estimate of the damage, go to the acceptance zones in Figure 606.

B. References

Reference Title


(FRS7161) (P/B 801)


C. Location Zones

Zone Area





72-00-00Config 4

Page 627



FOR REFERENCE ONLY


SUBTASK 72-00-00-940-021-R00


SUBTASK 72-00-00-480-021-R00

(2) Attach the tool to turn the HP system (TASK 72-00-00-982-026-R00).

E. High Pressure (HP) Compressor Inspection

SUBTASK 72-00-00-296-214-R04

(1) Do an inspection of the HP compressor blades:

NOTE: If you find damage that extends from one zone into another, compare the chord width

of the damage in each zone with the limit for that zone. All stages of the HP

compressor rotor blades are made with local bends at the tip and the root. These

bends are different to the bends or curls caused by impact damage.

NOTE: For all damage that is more than the limits, do not operate the engine until after you

repair the engine.

DHI 113-120 POST SB RB211-72-C230



damaged blade.



1) Accept missing material up to a depth of 0.015 inch (0.38mm) with no related

cracks.


NOTE: Material missing from a previous repair will have a smooth contour

appearance. Check the module log book.

3) Accept nicks or tears that start on the leading or trailing edges, only if:

a) There are no cracks.

b) The maximum depth of the nick or tear is 0.015 inch (0.38 mm).

NOTE: If digital optical measurement equipment is used, the limit is increased

to 0.025 inch (0.64mm).

DHI 101-112, 121, 301-999 POST SB RB211-72-C230

4) Dents or bends are permitted if:

a) There are no related cracks, nicks or tears.

b) The blade does not touch a different blade.

DHI 113-120 POST SB RB211-72-C230

5) Dents are permitted if:

a) There are no related cracks, nicks or tears.

NOTE: Bent blades are not permitted without concurrence from Power Plant

Engineering.


6) Blade tip damage and discoloration in zone D.



72-00-00Config 4

Page 628


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

a) Accept blade tip discoloration caused by blade tip rub.

b) Accept material that is bonded to the blade tip or leading edge.

c) Accept bends or curls that do not have related cracks or tears.



<1> Stage 1: 0.55 inch (13.9 mm)

<2> Stage 2: 0.46 inch (11.7 mm)

<3> Stage 3: 0.40 inch (10.1 mm)

<4> Stage 4: 0.45 inch (11.4 mm)

<5> Stage 5: 0.44 inch (11.1 mm)

<6> Stage 6: 0.42 inch (10.6 mm).

e) The radial length from the tip of the missing piece has no limit. The missing tip

can go from Zone D into Zone C.

<1> Cracks from the tip, which are initially radial and then become axial, are

permitted.


<2> Cracks which start at the leading or trailing edges and then extend

radially towards the tip are also permitted.


<3> Cracks which start at the leading or trailing edges and then extend

radially towards the fillet radius are not permitted.

NOTE: For limits on tip corner material lose, see the limits above.

(b) Damage is permitted to the limits that follow if you do the inspection procedure.

1) Blade cracks, bends or curls are permitted up to the limits that follow.

a) Axial cracks, nicks, tears and material loss on one edge in Zone A, B and C

are permitted if the length of each crack is not more than 10% of the true

chord width.

<1> Stage 1: 0.17 inch (4.3 mm)

<2> Stage 2: 0.14 inch (3.5 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.14 inch (3.5 mm)

<5> Stage 5: 0.13 inch (3.3 mm)

<6> Stage 6: 0.13 inch (3.3 mm).

b) Axial cracks, nicks, tears, and material loss on the two edges in Zone A, B and

C are permitted if the length is not more than 5% of the true chord width.

<1> Stage 1: 0.08 inch (2.0 mm)

<2> Stage 2: 0.07 inch (1.7 mm)

<3> Stage 3: 0.06 inch (1.5 mm)

<4> Stage 4: 0.07 inch (1.7 mm)

<5> Stage 5: 0.07 inch (1.7 mm)

<6> Stage 6: 0.06 inch (1.5 mm).



72-00-00Config 4

Page 629



FOR REFERENCE ONLY

c) Axial cracks, nicks, tears and material loss on one edge in Zone D are

permitted if the length is not more than 20% of the true chord width.

<1> Stage 1: 0.33 inch (8.4 mm)

<2> Stage 2: 0.28 inch (7.1 mm)

<3> Stage 3: 0.24 inch (6.1 mm)

<4> Stage 4: 0.27 inch (6.8 mm)

<5> Stage 5: 0.27 inch (6.8 mm)

<6> Stage 6: 0.25 inch (6.4 mm).

d) Axial cracks, nicks, tears and material loss on two edges in Zone D are

permitted if the length is not more than 10% of the true chord width

<1> Stage 1: 0.17 inch (4.3 mm)

<2> Stage 2: 0.14 inch (3.5 mm)

<3> Stage 3: 0.12 inch (3.0 mm)

<4> Stage 4: 0.14 inch (3.5 mm)

<5> Stage 5: 0.13 inch (3.3 mm)

<6> Stage 6: 0.13 inch (3.3 mm).

2) Do 3 inspections at intervals of between 250 and 350 flight hours and 1 inspection

at between 800 and 1000 flight hours.




1) It is not necessary to do the inspection procedure if you repair all cracks, nicks and

tears.




NOTE: Make sure that the number of repaired blades in HP Compressor stage 1 is

not more than 10.



HP Compressor Access


1 No Yes

2 Yes Yes

3 Yes Yes

4 Yes No

5 No Yes

6 Yes No

3) HP Compressor stage 1 blades only:



72-00-00Config 4

Page 630



FOR REFERENCE ONLY

a) Axial cracks, nicks or tears with length that is not more than 0.09 inch (2,5

mm) of the true chord width on one edge in zone B and C can be blended.

4) HP Compressor stage 2 to 6 blades only:

a) Axial cracks, nicks or tears with length that is not more than 5 percent of the

true chord width on one edge in zone B can be blended:

<1> Stage 2: 0.07 inch (1.8mm)

<2> Stage 3: 0.06 inch (1.5mm)

<3> Stage 4: 0.07 inch (1.8mm)

<4> Stage 5: 0.07 inch (1.8mm)

<5> Stage 6: 0.06 inch (1.5mm).

b) Axial cracks, nicks or tears with length that is not longer than 10 percent of the

true chord width on one edge in zone C can be blended.

<1> Stage 2: 0.14 inch (3.6mm)

<2> Stage 3: 0.12 inch (3.0mm)

<3> Stage 4: 0.14 inch (3.6mm)

<4> Stage 5: 0.13 inch (3.3mm)

<5> Stage 6: 0.13 inch (3.3mm).

5) All HP Compressor stages:

a) Axial cracks, nicks or tears with length that is not longer than 10 percent of the

true chord width on one edge in zone D can be blended.

<1> Stage 1: 0.34 inch (8.6mm)

<2> Stage 2: 0.28 inch (7.1mm)

<3> Stage 3: 0.24 inch (6.1mm)

<4> Stage 4: 0.28 inch (7.1mm)

<5> Stage 5: 0.26 inch (6.6mm)

<6> Stage 6: 0.25 inch (6.4mm).

(d) If necessary, the acceptance limits for cracks in zone D can be increased if you do the

steps that follow:



a) Repair before 5 cycles or 24 flight hours.

NOTE: Use the limit that occurs first.


SUBTASK 72-00-00-080-030-R00

(1) Remove the tool you used to turn the HP system (TASK 72-00-00-982-026-R00).

SUBTASK 72-00-00-840-018-R00


END OF TASK



72-00-00Config 4

Page 631



FOR REFERENCE ONLY

67440B

ZONE B

ZONE D

ZONE C

ZONE A

LEADING EDGE

TYPICAL STAGES 4, 5 AND 6


X

Z

STAGE

1

2

3

4

5

6

QTY

57

82

94

97

76

74

DIMENSION X

2.30 INCHES (58.3 mm)

1.91 INCHES (48.4 mm)

1.57 INCHES (39.9 mm)

1.34 INCHES (34.1 mm)

1.20 INCHES (30.4 mm)

1.06 INCHES (27.0 mm)

DIMENSION Z (TRUE CHORD)

1.65 INCHES (41.91 mm)

1.39 INCHES (35.31 mm)

1.21 INCHES (30.83 mm)

1.35 INCHES (34.29 mm)

1.34 INCHES (34.00 mm)

1.26 INCHES (32.13 mm)

ZONE A = 10% OF BLADE AIROFOIL

ZONE B = 40% OF BLADE AIROFOIL

ZONE C = 25% OF BLADE AIROFOIL

ZONE D = 25% OF BLADE AIROFOIL

H60437 S00061280616_V1




72-00-00Config 4

Page 632



FOR REFERENCE ONLY

B C

ASEE

SEE C

SEE B

A

STAGE 1 (EXAMPLE)

TRAILING EDGE

CONVEX SURFACE

LEADING EDGE

DE00069088

H60471 S00061280617_V1




72-00-00Config 4

Page 633



FOR REFERENCE ONLY

D

FE

SEE E

DSEE

SEE F

TRAILING EDGE

LEADING EDGECONVEX SURFACE

DEE00069298H60483 S00061280618_V1




72-00-00Config 4

Page 634



FOR REFERENCE ONLY

STAGE 3

Y EXAMPLE TIP RELEASE 0.40 INCH (10.16 mm)

X EXAMPLE TIP RELEASE 0.25 INCH (6.35 mm)

X

Y

CONVEX SURFACE

LEADING EDGE

386004 S00061280619_V1




72-00-00Config 4

Page 635



FOR REFERENCE ONLY

FINDINGS:

HPC

STAGE 1

(QTY. 57)


ZONES A, B OR BOTH:

HPC

STAGE 2

(QTY. 82)

HPC

STAGE 3

(QTY. 94)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78772 S00061280620_V1




72-00-00Config 4

Page 636


DHI

DHI


FOR REFERENCE ONLY

FINDINGS:

HPC

STAGE 4

(QTY. 97)


ZONES A, B OR BOTH:

HPC

STAGE 5

(QTY. 76)

HPC

STAGE 6

(QTY. 74)


- ZONE A DAMAGE

- ZONE B DAMAGE


AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

AAL

D78773 S00061280621_V1




72-00-00Config 4

Page 637


DHI

DHI


FOR REFERENCE ONLY

TASK 72-00-00-726-202-R04

6. HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

Figure 607

A. General

(1) This task provides the instructions on how to examine the HP compressor rotor path liners

(Stages 1 to 4) after the engine had a high power surge or an uncommanded engine rundown.

NOTE: "High Power Surge" is defined as a surge at cruise power and above. Top of Descent

deceleration surges are not included.

(2) Access locations are as follows:

Access Location View Area

HP1S G Stage 1

HP2S D Stages 2 and 3

Blanking Plate, HP 3 Air Supply E Stage 4

B. Tools/Equipment

NOTE: When more than one tool part number is listed under the same "Reference" number, the

tools shown are alternates to each other within the same airplane series. Tool part numbers

that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.

Reference Description

COM-4316 Borescope - Inspection, Flexible 6 mm

757-200, -200ER, -200PFPart #: IV9620GL Supplier: 32212Opt Part #: 7110561 Supplier: 32212Opt Part #: IF6C5X1-8 Supplier: 32212

C. Location Zones

Zone Area




SUBTASK 72-00-00-946-203-R04


SUBTASK 72-00-00-946-204-R04


E. HP Compressor Rotor Path Liners (Stages 1 to 4) Inspection

SUBTASK 72-00-00-026-209-R04

(1) Remove the engine from service if:

(a) It was not possible to examine a minimum of 90% of all stages of the HP compressor

rotor path liners.

(b) On one individual stage, the liner material has a total missing area greater than 6.20 sq.

inches (4000 sq. mm).



72-00-00Config 4

Page 638



FOR REFERENCE ONLY

(c) One individual area of material loss is greater than 2.325 sq. inches (1500 sq. mm).

NOTE: It is not necessary to measure individual areas of lining loss less than 0.078 sq.

inches (50 sq. mm).

NOTE: Compressor rotor path “drop out” can leave “cliff edge” features that are indicated

by areas of shadow.

(d) The nominal width and area between the blades of the rotor path liner are given below.

This will help to calculate the damage to the rotor path liner.

Width of Rotor Path Liner Area Between Blades

StageNo. of

bladesInch mm sq. inches sq. mm

1 57 1.81 46.0 2.82 1820.0

2 82 1.42 36.0 1.52 980.0

3 94 1.06 27.0 0.99 640.0

4 97 1.06 27.0 0.96 620.0

SUBTASK 72-00-00-296-212-R04

(2) Do an inspection of the Stage 1 HP compressor rotor path liner as follows:

(a) Put the 6 mm flexible borescope, COM-4316 through the access HP1S (Location G).



(b) Slowly pull the borescope back and examine the surface of the rotor path liner as follows:




clearance.


rotor path liner.


SUBTASK 72-00-00-296-211-R04


(a) Put the 6 mm flexible borescope, COM-4316 through the access HP2S (Location D).



(b) Slowly pull the borescope back and examine the surface of the rotor path liner as follows:




clearance.


rotor path liner.




72-00-00Config 4

Page 639



FOR REFERENCE ONLY

SUBTASK 72-00-00-296-213-R04

(4) Do an inspection of the Stage 3 HP compressor rotor path liner with a 6 mm flexible

borescope, COM-4316 as follows:

(a) Put the 6 mm flexible borescope, COM-4316 through the access HP2S (Location D).

1) Move the borescope rearwards through the vane and feed 360 degrees in a






clearance.


rotor path liner.


SUBTASK 72-00-00-296-207-R04


(a) Put the 6 mm flexible borescope, COM-4316 through the access HP3 air supply blanking

plate (Location E).







clearance.


rotor path lining,


NOTE: Do not let the borescope fall through the cooling air passages on the outer vane

ring. If this happens, carefully twist the scope while it is slowly withdrawn from the

passage back into the annulus between the compressor blades and the vanes.


SUBTASK 72-00-00-080-036-R00


SUBTASK 72-00-00-840-021-R00


END OF TASK



72-00-00Config 4

Page 640



FOR REFERENCE ONLY

HP COMPRESSOR

ROTOR BLADES

HP COMPRESSOR

ROTOR PATH

LINER

AREA OF MISSING

HP COMPRESSOR

ROTOR PATH LINER

TYPICAL VIEW THROUGH FLEXIBLE

BORESCOPE

2327024 S0000528599_V1




72-00-00Config 4

Page 641



FOR REFERENCE ONLY

HP COMPRESSOR

ROTOR PATH

LINER

TYPICAL VIEW THROUGH A

FLEXIBLE BORESCOPE

HP COMPRESSOR

ROTOR BLADES

A LARGE AREA OF SHADOW

CAN INDICATE A LARGE

SPACE BETWEEN THE HP

COMPRESSOR BLADE TIP

AND THE ROTOR PATH

LINER

2327028 S0000528600_V1




72-00-00Config 4

Page 642



FOR REFERENCE ONLY

TASK 72-00-00-206-049-R04

7. Combustion Liners Inspection

(Figure 606, Figure 608 and Figure 609)


A. General

(1) This task provides the instructions on how to examine the combustion liners.

(2) After 5 inspections at the times given in the limits, you can multiply the inspection interval by

two if there is no increase in the crack length and you don't find other defects.

(3) With this inspection you will examine these parts of the combustion liners:

(a) The front liner inner and outer walls

(b) Heatshields

(c) Burner seals

(d) Rear inner and outer discharge nozzles

(e) Fuel spray nozzles

(f) After a birdstrike or if you suspect a birdstrike, do these steps:

1) Carefully use a 0.32 inch (8.13 mm) diameter probe to look for damage on these

components:

a) Meter panel

b) Heatshields

c) Fuel spray nozzles

NOTE: After a birdstrike or if you suspect a birdstrike, you must also do the

HP compressor blades inspection.

(4) To help you make an estimate of the damage, the acceptance zones are provided in this task.

B. References

Reference Title





73-11-05-004-001-R02 Fuel Spray Nozzles Removal (P/B 401)

73-11-05-404-006-R02 Fuel Spray Nozzles Installation (P/B 401)

C. Location Zones

Zone Area




SUBTASK 72-00-00-846-185-R04


SUBTASK 72-00-00-946-186-R04

(2) Do this task:Borescope Equipment Preparation and Use, TASK 72-00-00-206-136-R04.



72-00-00Config 4

Page 643



FOR REFERENCE ONLY

E. Combustion Liners Inspection

SUBTASK 72-00-00-296-187-R04

(1) Do an inspection of the inner and outer walls of the front liner as follows:

(a) Cracks on the inner or outer walls of the front liner

NOTE: Look carefully at the inner walls for cracks and at the areas around the dilution

chutes.

1) Axial cracks in the cooling ring lip rearward of the cooling ring

a) Accept cracks that are less than 0.39 inch (9.91 mm) long only if they are

more than 0.20 inch (5.08 mm) apart with crack-free material between them.

b) If the cracks are less than 0.20 inch (5.08 mm) apart, you must do more

inspections regularly, less than 300 flight cycles apart.

2) Circumferential cracks that connect two dilution chutes, if there are no other cracks

that start from these chutes.

a) If there are circumferential cracks that connect adjacent dilution chutes at up

to five locations around the inner wall, you must do more inspections at regular

intervals.

<1> Do the inspections before 250 hours or 75 flight cycles.

NOTE: Use the first limit that occurs.

b) If there are circumferential cracks between adjacent dilution chutes at more

than five locations around the inner wall, schedule engine removal in not more

than 30 hours or 5 flight cycles.

NOTE: Remove the engine when the first limit occurs.

3) Isolated cracks in other areas

NOTE: Cracks are isolated if they are 0.79 inch (20 mm) apart, with crack-free

material between them.

a) Accept if the cracks are less than 0.20 inch (5.08 mm) long.

b) For axial cracks

<1> Accept if the cracks do not extend through an adjacent cooling ring lip

and do not connect.

<a> You must do more inspections regularly, less than 75 flight cycles

apart.

<2> Reject if the cracks connect or extend through an adjacent cooling ring

lip.

<a> Remove the engine in less than 10 flight cycles.

c) For circumferential cracks

<1> Accept cracks that are more than 0.20 inch (5.08 mm) long but less

than 0.79 inch (20.07 mm) long.

<a> You must do more inspections regularly, less than 300 flight

cycles apart.

<2> Accept cracks that are more than 0.79 inch (20.07 mm long but less

than 1.57 inches (39.88 mm) long.

<a> You must do more inspections regularly, less than 75 flight cycles

apart.



72-00-00Config 4

Page 644



FOR REFERENCE ONLY

<3> Reject if the cracks are more than1.57 inches (39.88 mm) long.

<a> Remove the engine in less than 10 flight cycles

(TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00

and TASK 71-00-02-404-003-R00 or

TASK 71-00-02-404-004-R00).

d) For cracks in the first section of the liner inner wall, replace the engine in less

than 10 flight cycles (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00)

<1> Reject if you cannot see clearly the end of the crack nearest to the

meter.

e) Reject cracks that are not isolated.

<1> Replace the engine in less than 10 flight cycles


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

4) Cracks in the dilution chutes

a) Accept if the cracks do not go into the liner walls.

(b) Burns or erosion of the inner or outer walls of the front liner

1) Accept burns or erosion, with related distortion or material decrease, of the cooling

ring if you obey the limits that follow:

a) The axial length must not be more than 0.39 inch (9.91 mm).

b) If the damage is more than the above limits, make an inspection of the

damage before 500 hours.

2) Burns or erosion of dilution chutes are permitted.

(c) Holes on the inner or outer walls of the front liner

1) Accept a hole caused by burns and/or cracks at a maximum of 4 locations if the size

of the hole is not more than 0.31 sq. inch (200 sq. mm).

2) If the hole is more than the limit 0.31 sq. inch (200 sq. mm), then you must do an

inspection of the rear inner and outer discharge nozzles and the HPNGV at the time

intervals that follows:

a) If the hole is greater than 0.31 sq. inch (200 sq. mm) but less than 0.62 sq.

inch (400 sq. mm), do the inspection again before 250 hours.

b) If the hole is greater than0.62 sq. inch (400 sq. mm) but less than 1.24 sq.

inches (800 sq. mm), do the inspection again before 130 hours.

c) If the hole is greater than 1.24 sq. inches (800 sq. mm) but less than 2.48 sq.

inches (1600 sq. mm), do the inspection again before 65 hours.

d) If the hole is greater than 2.48 sq. inches (1600 sq. mm), remove the engine

before 30 hours.

(d) Material decrease on the inner or outer walls of the front liner

1) If a large amount of material is loose and will possibly break away, replace the

engine (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(e) Thermal barrier layer decrease on the inner or outer walls of the front liner

1) Accept a general decrease of the thermal barrier layer.



72-00-00Config 4

Page 645



FOR REFERENCE ONLY

SUBTASK 72-00-00-296-166-R04

(2) Do an inspection of the heatshield as follows:

(a) Cracks on the heatshield

1) Accept cracks on these conditions:

a) The cracks are not more than 0.39 inch (9.91 mm) from the heatshield bore.

b) The cracks are more than 0.20 inch (5.08 mm) apart and have material with no

cracks between them.

2) Accept cracks in the inner and outer circumferential rail provided they do not extend

beyond the fillet radius.

3) Accept cracks that are longer than the limits only if you do the inspection again

before 250 hours.

(b) Burns and erosion on the heatshield

1) Accept burns and erosion only if there is no sign of holes.

(c) Holes in the heatshield

1) Accept a hole or decrease of material only if the hole is not greater than 0.09 sq.

inch (58.06 sq. mm).

2) Accept a hole or decrease of material greater than the limit only if the hole does not

extend to more than 0.23 sq. inch (148.39 sq. mm) and you obey these conditions:

a) Do an inspection of the front liner inner and outer walls before 130 hours of

operation.

b) Do an inspection of the rear inner and outer discharge nozzles before 130

hours of operation.

c) Do an inspection of the HPNGV before 130 hours of operation.

d) Do an inspection of the HP turbine before 130 hours of operation.

3) If a hole or decrease of material is greater than 0.23 sq. inch (148.39 sq. mm) , you

must replace the engine before 30 hours of operation.

(d) Lifting of the heatshield

1) If the dimension of gap A is not constant around 360 degrees at 0.08 inch (2.03 mm)

to 0.10 inch (2.54 mm), replace the engine (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

(e) Axial movement of the heatshield

1) If there is axial movement out of position between adjacent heatshields, replace the

engine (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

SUBTASK 72-00-00-296-167-R04

(3) Do an inspection of the burner seals that follow:

(a) Cracks in the burner seals

1) You can accept cracks in the conical section.

2) If there are cracks in the parallel section or forward of the nozzle tip, reject the

engine in not more than 30 flight cycles.

(b) Burns or erosion in the burner seals



72-00-00Config 4

Page 646



FOR REFERENCE ONLY

1) You can accept all burns and erosion of the conical section back to the parallel

section of the burner seal.

2) Reject the engine in not more than 30 cycles if the burns and erosion are more than

in step 1 above.

(c) Distortion of the burner seal

1) Accept distortion of the conical section.

SUBTASK 72-00-00-296-168-R04

(4) Do an inspection of the rear inner and outer discharge nozzles that follow:

(a) Cracks of the rear inner and outer discharge nozzles

1) Accept isolated cracks only if they are not greater than 0.79 inch (20.07 mm).

2) Accept cracks that are greater than the limit only if you do this inspection again

before 130 hours.

(b) Burns or erosion on the rear inner and outer discharge nozzles

1) Accept burns or erosion only if there are no holes.

(c) Thermal barrier layer decrease of the rear inner and outer discharge nozzles

1) Accept a general decrease of the thermal barrier coating.

SUBTASK 72-00-00-296-169-R04

(5) Do an inspection of the fuel spray nozzles that follow:

(a) Cracks in the fuel spray nozzle

1) If there are cracks in a fuel spray nozzle, replace the fuel spray nozzle

(TASK 73-11-05-004-001-R02 and TASK 73-11-05-404-006-R02).

(b) Material decrease on the fuel spray nozzle

1) If the inner or outer swirler vane has gone, do an inspection of the HP turbine

blades and HP NGV.

a) If the HP turbine blades and HPNGV are serviceable, replace the fuel spray

nozzle (TASK 73-11-05-004-001-R02 and TASK 73-11-05-404-006-R02).

b) If the HP turbine blades and HPNGV are not serviceable, replace the engine.

(c) Incorrect location of the fuel spray nozzle

1) If the center of the fuel spray nozzle is not at the center of the burner seal, do an

inspection of the combustion liner.

a) If the combustion liner is serviceable, replace the fuel spray nozzle

(TASK 73-11-05-004-001-R02 and TASK 73-11-05-404-006-R02).

b) If the combustion liner is not serviceable, replace the engine


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).


SUBTASK 72-00-00-080-037-R00


SUBTASK 72-00-00-840-007-R00

(2) Do this task: Put the Engine Back to Its Usual Condition, TASK 72-00-00-846-143-R04

END OF TASK



72-00-00Config 4

Page 647



FOR REFERENCE ONLY

FWD

B

A

B

A

DEE0002218

COOLING

RING LIPS

HEATSHIELD

FUEL SPRAY

NOZZLE

INNER

WALL

NOZZLE

REAR INNER

DISCHARGE

NOZZLE

DISCHARGE

REAR OUTER

OUTER WALL

DILUTION

CHUTES

PANEL

METER

DILUTION

CHUTES

COOLING

RING LIPS

BURNER SEAL

H60588 S00061280622_V1

Front Combustion Liner InspectionFigure 608/72-00-00-990-911-R04 (Sheet 1 of 5)



72-00-00Config 4

Page 648



FOR REFERENCE ONLY

COOLING RING LIPS (10 LOCATIONS)

A = 1.56 INCH (39.56 mm)

THIRD SECTION AND

REAR LOCATION RINGSECTION

SECOND

SECTION

FRONT HEAD

THIRD SECTION AND

REAR LOCATION RINGSECTION

SECONDFIRST

SECTION

B

B

D

D

G

G

A-A

FIRST

SECTION

A

F

A

C E

NOTE: DIMENSIONS SPECIFIED ARE TO BE USED____

AS AN AID WHEN YOU ESTIMATE THE DAMAGE.

C

E

B = 0.35 INCH (8.80 mm) DIAMETER

C = 0.91 INCH (23.09 mm)

D = O.60 INCH (15.20 mm) DIAMETER

E = 0.77 INCH (19.50 mm)

F = 1.58 INCH (40.13 mm DIAMETER)

G = 0.28 INCH (7.00 mm)

METER

PANEL

INNER WALL

OUTER WALL

BSEE

ASEE

DEE0004808

H60611 S00061280623_V1




72-00-00Config 4

Page 649



FOR REFERENCE ONLY

BURNS AND EROSIONFIRST COOLING

RING CRACK

DILUTION CHUTE

CRACKS

HEATSHIELD

SEGMENT

OUTER WALL

FIRST COOLING

RING RACK

............

...............................

....

LOSS

INNER WALL

HEATSHIELD

MATERIAL

(10.00 mm)

0.40 INCH

B-B

DEF0004309L76607 S00061280624_V1




72-00-00Config 4

Page 650



FOR REFERENCE ONLY

DEE0004809

LOSS OF THERMAL

BARRIER COATING

FIRST COOLING

RING CRACK

DILUTION

CHUTES

HOLE

(VIEW ON OUTER WALL)

A

M11567 S00061280625_V1




72-00-00Config 4

Page 651



FOR REFERENCE ONLY

FIRST COOLING

RING CRACK

COOLING LIP

CRACKING AND

HOLE

DILUTION

CHUTES

BURNING

EROSION

(VIEW ON INNER WALL)

DEE0004810

B

M11565 S00061280626_V1




72-00-00Config 4

Page 652



FOR REFERENCE ONLY

FWD

OUTER SWIRL

VANES

POSITION

(MUST NOT BECOME DISENGAGED

POSITION BETWEEN ADJACENT

(NO AXIAL MOVEMENT OUT OF

(CONSTANT AROUND 360 DEGREES)

(CONSTANT AROUND 360 DEGREES)

METERPANEL

ASEE

POSSIBLE FAILURE

CIRCUMFERENTIAL RAIL

BURNER SEAL

FUEL SPRAY NOZZLE

FROM BURNER SEAL)

HEATSHIELD

HEATSHIELDS)

GAP A

GAP A

DEE0002575A

A

INNER SWIRL

VANES

H60653 S00061280627_V1

Meterpanel and Heatshield InspectionFigure 609/72-00-00-990-916-R04



72-00-00Config 4

Page 653



FOR REFERENCE ONLY

TASK 72-00-00-200-801-R04

8. High Pressure Nozzle Guide Vanes (HPNGV) Inspection

(Figure 610)


A. General

(1) This task provides the instructions on how to examine the High Pressure Nozzle Guide Vanes

(HPNGV).

(2) It is not necessary to examine the convex surface of the HPNGV airfoil. You can see some of

the NGV convex areas when you do an inspection of the HP turbine blades. If damage is seen,

use the acceptance limits that are given.

(3) After 5 inspections at the times given in the limits that follow, you can multiply the inspection

interval by two if:

(a) There is no increase in crack length and you don't find other defects.

(4) To help you make an estimate of the damage, the acceptance zones are provided in this task.

B. References

Reference Title





C. Location Zones

Zone Area




SUBTASK 72-00-00-840-024-R00


SUBTASK 72-00-00-940-028-R00

(2) Do this task:Borescope Equipment Preparation and Use, TASK 72-00-00-206-136-R04.

E. High Pressure Nozzle Guide Vanes (HPNGV) Inspection

SUBTASK 72-00-00-290-004-R00

(1) Do an inspection of the HP nozzle guide vanes that follow:

(a) Cracks in the airfoil surface of the HPNGV

1) Accept axial cracks in the concave surface only if:

a) Each axial crack is not longer than 1.0 inch (25.4 mm) and there is no material

lift more than 0.020 inch (0.51 mm).

2) Accept radial cracks in the concave surface only if:

a) Each radial crack is not longer than 1.0 inch (25.4 mm) and there is no

material lift.

3) Accept axial and/or radial cracks in the concave surface that are longer than 1.0

inch (25.4 mm) only if:

a) There is no material lift that is more than 0.020 inch (0.51 mm).



72-00-00Config 4

Page 654



FOR REFERENCE ONLY

b) The cracks do not come together and you do the inspection again in less than

500 hours.

4) Axial cracks to convex surface

a) Accept axial cracks up to 1.0 inch (25.4 mm) long if:

<1> There is no material lift that is more than 0.020 inch (0.51 mm).

<2> There is no bulge.

b) Accept axial cracks that are more than 1.0 inch (25.4 mm) long but less than

2.0 inch (50.8 mm) if:


<2> Do an inspections at 500 hour intervals.

c) Replace the engine in less than 50 hours for axial cracks that have these

conditions (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00):

<1> The Axial cracks are more than 2.0 inch (50.8 mm) long.

<2> There is material lift that is more than 0.020 inch (0.51 mm).

<3> There is material that is bulged.

5) Radial cracks to the airfoil convex surface

a) Accept radial cracks that are less than 1.0 inch (25.4 mm) if:


<2> No material that has bulges

b) Accept radial cracks that are more than 1.0 inch (25.4 mm) but less than 2.0

inch (50.8 mm) long if:


<2> No material that has bulges

<3> Do an inspection at 500 hour intervals.

c) Replace the engine in less than 50 hours for radial cracks that have these

conditions (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00):

<1> The Axial cracks are more than 2.0 inch (50.8 mm) long.

<2> There is material lift that is more than 0.020 inch (0.51 mm).

<3> There is material that is bulged.

6) Accept axial cracks in the vane leading edge with these conditions:

a) Each axial crack is not longer than 1.0 inch (25.4 mm) long.

b) Cracks do not extend into the convex surface film cooling holes.

c) There is no material lift that is more than 0.020 inch (0.51 mm)..

7) Accept radial cracks in the vane leading edge with these conditions:

a) Each radial crack is not longer than 1.0 inch (25.4 mm).

b) Cracks do not extend into the convex surface film cooling holes.

c) The material has not lifted.

8) Accept axial and/or radial cracks in the vane leading edge that are longer than 1.0

inch (25.4 mm) with these conditions:



72-00-00Config 4

Page 655



FOR REFERENCE ONLY


b) Do the inspection again in less than 500 hours.

9) Accept axial and/or radial cracks in the vane leading edge that extend into the

convex surface film cooling holes with these conditions:


b) Do the inspection again in less than 500 hours.

10) Replace the engine in less than 50 hours if there is material lift that is more than

0.020 inch (0.51 mm) (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

11) Replace the engine in less than 50 hours if the cracks connect and material can

break away from the airfoil surface (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

(b) Cracks in the inner and outer platform of the HPNGV

1) Accept cracks in the ceramic layer.

2) Accept cracks in the inner and outer platform only if material cannot break away.

3) Replace the engine in less than 50 hours if material can break away


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(c) Material decrease on the HPNGV

1) Replace the engine in less than 50 hours if there is material lift that is more than

0.020 inch (0.51 mm) (TASK 71-00-02-004-002-R00 or


TASK 71-00-02-404-004-R00).

2) Replace the engine in less than 50 hours if the material can break away from the

airfoil surface

(d) Burns or erosion on the HPNGV

1) Accept burns, erosion and a decrease in the quantity of the ceramic layer with this

condition:

a) If the damage has not gone into the base material of the inner or outer

platform.

2) If you see burns to the inner or outer platform, do these steps:

a) Make sure that the fuel spray nozzles are in the correct location in the

heatshield seals.

b) Do an inspection of the front combustion liner.

3) Replace the engine in less than 50 hours if the burns or erosion have gone into the

base material of the inner or outer platform.

4) Accept burns, erosion or holes that go into the vane leading edge on these

conditions:

a) Less than 30% of the leading edge has gone

b) No more of the leading edge material will go.

5) Accept burns, erosion or holes that go into the vane leading edge on these

conditions:



72-00-00Config 4

Page 656



FOR REFERENCE ONLY

a) Less than 40% of the leading edge has gone.

b) No more of the leading edge material will go.

c) Do the inspection again in less than 500 hours.

6) Replace the engine in less than 50 hours if more than 40% of the leading edge is

gone (TASK 71-00-02-004-002-R00 or TASK 71-00-02-004-073-R00 and

TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).

(e) Foreign object damage to the HPNGV

1) Accept dents in the airfoil section only if you do an inspection of the turbine blades.

2) Accept nicks and tears in the vane trailing edge on these conditions:

a) The damage does not extend forward of the rear row of film cooling holes.

b) There is no burns.

c) Do an inspection of the turbine blades.

3) Reject the engine in less than 50 hours if cracks, nicks or tears in the vane trailing

edge extend forward of the rear row of film cooling holes.

4) Do an inspection of the turbine blades.

5) Replace the engine if you see any blockage between the vanes


TASK 71-00-02-404-003-R00 or TASK 71-00-02-404-004-R00).


SUBTASK 72-00-00-840-025-R00


SUBTASK 72-00-00-840-026-R00


END OF TASK



72-00-00Config 4

Page 657



FOR REFERENCE ONLY

D = 0.500 INCH (12.7 mm)

C = 0.236 INCH (6.0 mm)

B = 0.078 INCH (2.0 mm)

A = 2.952 INCHES (75.0 mm)


(CERAMIC COATED)

INNER PLATFORM

(CERAMIC COATED)

OUTER PLATFORM

C

D

BA

H60669 S00061280628_V1

HP Nozzle Guide Vanes InspectionFigure 610/72-00-00-990-A03-R00



72-00-00Config 4

Page 658



FOR REFERENCE ONLY

TASK 72-00-00-206-085-R04

9. High Pressure (HP) Turbine Inspection

(Figure 611)


A. General

(1) The subsequent operations give the HP turbine inspection procedure and the standards (limits)

you can accept.

(2) This task provides the instructions on how to examine the High Pressure (HP) turbine for these

conditions:

(a) Burns or oxidation

(b) Cracks

(c) Dents

(d) Erosion

(e) Foreign object damage

(f) Interlock damage.


the task.

(4) You can use an impact extractor if it is not easy to remove the access plugs for the borescope.

(5) You will do the inspection through borescope access holes.

NOTE: Deterioration of the HP NGV support ring heatshield may allow axial and

circumferential movement of the heatshield over the support ring, after removal of the

borescope plug. This may partially obscure the HP turbine borescope hole 'G'. The

heatshield may be repositioned by hand to allow ease of entry of borescope.

Looseness of the heatshield will not affect engine integrity.

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-940-026-R00

(1) Do this task: Engine Inspection Preparation, TASK 72-00-00-846-137-R04

SUBTASK 72-00-00-426-174-R04

(2) Attach the tool to turn the HP system. (TASK 72-00-00-982-026-R00)

SUBTASK 72-00-00-940-027-R00

(3) Do this task: Borescope Equipment Preparation and Use, TASK 72-00-00-206-136-R04

E. High Pressure (HP) Turbine Inspection

SUBTASK 72-00-00-296-171-R04

(1) Do an inspection of the HP turbine for the conditions that follow:

(a) Cracks in the concave and convex airfoil surfaces (Area C) of the HP turbine



72-00-00Config 4

Page 659



FOR REFERENCE ONLY

1) Axial cracks

a) Not permitted

2) Radial cracks

a) Accept radial cracks that are not more than 0.25 inch (6.35 mm) in length.

b) Accept radial cracks that are between 0.25 inch (6.35 mm) and 0.50 inch (12.7

mm) in length with no signs of burns or holes if you examine them again

before 100 hours.

c) If the radial cracks are longer than 0.50 inch (12.7 mm) and burns or holes are

not seen, replace the engine before 50 hours of engine operation is

completed.

(b) Dents in the airfoil surfaces of the HP turbine

1) Accept one dent with a round bottom on one of the two surfaces if it has no related

cracks or holes.

2) If the dent damage is larger than the limits given above, then you must replace the

engine.

(c) Cracks in the HP turbine shroud

1) Accept circumferential cracks from the rear face if they are not more than 0.20 inch

(5.08 mm) in length and they do not turn axial.

2) Accept circumferential cracks on the rear face that are between 0.20 inch (5.08 mm)

and 0.25 inch (6.35 mm) if:

a) The circumferential cracks do not run in the axial direction.

b) You do an inspection again before 250 hours of engine operation is completed.

3) If you find cracks that are more than the limits above, you must replace the engine

before 250 hours.

4) Accept cracks that run from the interlock acute corner, if:

a) Circumferential cracks do not increase into the airfoil, then become axial.

b) Axial cracks to the front shroud of the concave side of the blade do not extend

to more than 0.20 inch (5.08 mm).

c) Circumferential cracks do not extend more than 0.20 inch (5.08 mm).

d) You do an inspection again before 100 hours of engine operation is completed

5) If the cracks are more than the limits given above, you must replace the engine.

(d) Burns or Oxidation

1) Accept burns or oxidation on the bottom of the outer shroud near the rear

non-interlock faces only if you find these conditions:

a) The increased clearance between the adjacent rear non-interlock faces is not

more than 0.035 inch (0.889 mm) around the rotor.

b) The increased clearance is more than 0.035 inch (0.889 mm) around, but less

than 50% around the rotor.

NOTE: The decrease of material caused by burns and oxidation causes the

increased clearance between the rear non-interlock faces.

2) If the damage from the burns or oxidation is more than the limits given above, you

must replace the engine before 100 hours

(e) Missing material to the outer shroud of the concave side of the blade



72-00-00Config 4

Page 660



FOR REFERENCE ONLY

1) If sections of the outer shroud are missing in Area G, replace the engine before 25

hours of engine operation are completed.

2) It is permitted to have burns to Area G, if you obey the limits that follow:

a) Do an inspection before 450 hours.

(f) Interlock Damage

1) If sections of the interlock or shroud are missing, replace the engine before 25

hours of engine operation is completed.

(g) Cracks and holes in the leading edge (Area A)

1) Accept cracks that are not open, and that extend from the leading edge of the

concave airfoil to the shroud fillet radius and into the shroud forward seal fin.

2) Accept open or burned cracks, or holes in the leading edge if you obey the limits

that follow:

a) The crack or holes extend from the leading edge of the concave airfoil, to the

shroud fillet radius and into the shroud forward seal fin.

b) The blade shroud forward seal fin can be seen on each side of the crack.

c) The width of the crack in the forward seal fin is not more than 0.06 inches

(1.50 mm).

d) The difference in the forward seal fin height either side of the crack is not more

than 0.04 inches (1.00 mm).

e) The total area of open cracks and holes, in the leading edge of the concave

airfoil to the shroud fillet radius, for all the blades in the set, is not more than

0.229 sq. inch (147.742 sq. mm).

f) The area of the open crack or holes on each blade is not more than 0.011 sq.

inch (7.097 sq. mm).

g) Do an inspection again before 450 hours.

3) Replace the engine before 50 hours of engine operation, if the width of the crack in

the forward seal fin is more than the above limits.

4) Replace the engine before 50 hours of engine operation, if the forward seal fin

height difference either side of the crack is more than the limits above.

5) Replace the engine before 50 hours of engine operation if the area of the holes is

more than the above limit.

6) Reject axial cracks that are open.

7) Accept one radial crack only if you obey the limits that follow:

a) The radial crack must not be more than 0.25 inch (6.35 mm) in length; and,

b) The radial crack must not connect more than four cooling holes; and,

c) The radial crack must not extend to the airfoil fillet radius.

8) Accept radial cracks only if you obey the limits that follow:

a) The radial cracks must not be more than 0.50 inch (12.7 mm) length; and,

b) The radial cracks must not connect more than eight cooling holes; and,

c) The radial cracks must not extend to the radius of the aft airfoil fillet; and,

d) You do an inspection again before 100 hours of engine operation is completed.

9) Replace the engine before 50 hours of engine operation if you find the conditions

that follow:



72-00-00Config 4

Page 661



FOR REFERENCE ONLY

a) Radial cracks that are more than 0.50 inch (12.7 mm).

b) There are more than eight cooling holes that are connected.

10) Replace the engine before 50 hours of engine operation if you find radial cracks that

are open or burned, or that extend to the airfoil fillet radius.

(h) Foreign object damage (Area A)

1) Accept foreign object damage only if you obey the limits that follow:

a) There must not be holes or cracks caused by other damage; and,

b) You must do an inspection again before 100 hours of engine operation is

completed.

2) Replace the engine before 50 hours of engine operation if you find the conditions

that follow:

a) Holes or cracks caused by foreign object damage

b) Axial cracks.

3) Replace the engine if you find holes or cracks with related axial cracks caused by

foreign object damage.

DHI 101-112, 121, 301-999 POST SB RB211-72-C230

(i) Erosion (Area A)

1) Accept erosion if there are no signs of holes caused by erosion.

2) If you find holes caused by erosion, other than as specified in the limits for open or

burned cracks, replace the engine before 50 hours of engine operation is

completed.

DHI 113-120 POST SB RB211-72-C230

(j) Erosion (Area A)

NOTE: Be careful not to confuse deep erosion pockets with holing. Holes resulting from

erosion will expose the leading edge cooling passage of the blade.

1) Accept erosion if there are no signs of holes caused by erosion.

2) If you find holes caused by erosion, other than as specified in the limits for open or

burned cracks, replace the engine before 50 hours of engine operation is

completed.


(k) Cracks in the trailing Edge (Area B)

1) Crack length must be measured from the initial position of the trailing edge to the

end of the crack.

2) Accept more than one crack in the root radius of the trailing edge (location xx) only

if it is not more than 0.125 in. (3.18 mm) in length.



3) Accept one axial crack in the root radius of the trailing edge (location xx) only if you

obey the limits that follow:

a) The crack is more than 0.125 in. (3.18 mm) but not more than 0.150 in.

(3.81 mm) in length; and,

b) You do an inspection again before 500 hours of engine operation is completed.



72-00-00Config 4

Page 662


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

c) If the crack is more than 0.150 in. (3.81 mm) the engine must be rejected in

less than 50 flight cycles.

4) Accept more than one crack that extends from the trailing edge shroud radius if you

obey the limits that follow:

a) The cracks are not more than 0.050 in. (1.27 mm).

b) If the cracks are more than 0.050 in. (1.27 mm) but less than 0.100 in.

(2.54 mm) you must do an inspection again in less than 100 hours.

c) If the cracks are more than 0.100 in. (2.54 mm) the engine must be rejected in

less than 50 hours.

5) Accept a single axial crack that is longer than 0.050 in. (1.27 mm) and that extends

from the trailing edge outer shroud radius, only if you obey the limits that follow:

a) The length of the axial crack must not be more than 0.100 in. (2.54 mm).

b) You do another inspection before 900 hours of engine operation is completed.

6) Accept a single axial crack that is longer than 0.100 in. (2.54 mm) and that extends

from the trailing edge outer shroud radius, only if you obey the limits that follow:

a) The length of the axial crack must not be more than 0.150 in. (3.81 mm).


7) Accept cracks from the trailing edge at positions other than the root radius or outer

shroud radius, only if you obey the limits that follow:

a) The crack's length must not be more than 0.050 in. (1.27 mm).


8) If you find cracks in the trailing edge that are more than the above limits, you must

replace the engine before 50 hours of engine operation is completed.

9) Accept smooth, round bottomed dents only if there are no related holes or cracks.

10) If you see holes or cracks that are caused by the dents, and there is no related axial

cracking, you must replace the engine before 50 hours of engine operation is

completed.

11) If you find axial cracks related to the dents, you must replace the engine.

DHI 101-112, 121, 301-999 POST SB RB211-72-C230

(l) Burns or oxidation (Area B including location XX)

NOTE: Location XX is defined as the area of the trailing edge root radius up to the first

trailing edge cooling hole.

NOTE: Material missing is defined as the amount of material that is completely missing.

It does not apply to areas that are burned or have oxidation, or if the thickness of

the material is decreased.

1) It is permitted to have burns or oxidation at the trailing edge only if you obey the

limits that follow:

a) It is not more than 0.40 inch (10.16 mm) axially from the trailing edge.

b) The material missing from the trailing edge must not be more than 0.020 in.


2) It is permitted to have burns and oxidation with the limits given in the step above,

only if you obey the limits that follow:



72-00-00Config 4

Page 663



FOR REFERENCE ONLY

a) The material missing from the trailing edge must not be more than 0.100 in.


b) Do the inspection again in not more than before 500 flight hours of engine

operation.

c) It is permitted to have material missing from the trailing edge of more than

0.100 in. (2.54 mm) axial length, but less than 0.120 in. (3.05 mm) axial length,

if you obey the limits that follow:

<1> Do an inspection again at 100 flight hour intervals.

<a> If no more deterioration is found in not less than three

inspections at 100 flight hour intervals do the steps that follow:

 Increase the inspection interval by 100 flight hours to a minimum

of 200 flight hours to no more than 500 flight hours for each three

inspections if no more deterioration found.

<c> If more deterioration is found during an subsequent inspection

you must decrease the inspection intervals to 100 flight hours.

d) Material missing from the trailing edge of more than the limits above, reject the

engine before 50 flight hours.

3) If you find burns and oxidation, or decrease in material which is more than the limits

given above, replace the engine before 50 flight hours of engine operation is

completed.

DHI 113-120 POST SB RB211-72-C230

(m) Burns and oxidation (Area B including location XX)



NOTE: Material decrease is defined as the amount of material that is completely

missing. It does not apply to areas that are burned or have oxidation, or if the

thickness of the material is reduced.

1) It is permitted to have burns and oxidation at the trailing edge, if you obey to the

limits that follow:

a) It is not more than 0.40 inch (10.16 mm) axially from the trailing edge.

b) Material decrease from the trailing edge must not be more than 0.020 inch


2) It is permitted to have burns and oxidation more than the limits given in the step

above, if you obey the limits that follow:

a) Material decrease from the trailing edge must not be more than 0.10 inch (2.54

mm) axial length.



72-00-00Config 4

Page 664


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

b) The decrease in the material from the trailing edge of more than 0.10 inch

(2.54 mm) axial length, but less than 0.120 inch (3.048 mm) axial length,

inspect again at 100 hour intervals.

NOTE: If no further deterioration is seen after three successive inspections at

100 hour intervals, you can increase the repeat inspection interval to

twice the original value, up to a maximum of 500 hours. If further

deterioration is subsequently seen, you must decrease the repeat

inspection interval to 100 hours again.

c) Do an inspection before 500 hours, if this condition occurs.

3) Decrease in material from the trailing edge of more than 0.10 inch (2.54 mm) axial

length but less than 0.120 inch (3.048 mm) axial length, re-inspection every 100

hours.

NOTE: If no further deterioration is observed after three successive inspections at

regular times as given in the above inspection criteria, the re-inspection

interval can be extended to twice its original value, provided the new

re-inspection interval does not exceed 500 hours. It should be noted that if

further degradation is subsequently observed, the inspection interval must

be reverted to 100 hours.

4) Decrease in material from the trailing edge of more than the limits above, reject the

engine before 50 hours.


(n) Foreign object damage (Area B including location XX)



1) Accept dents with smooth, circular bottoms if you do not see other related holes or

cracks.

2) Replace the engine before 50 flight hours is completed if you see the conditions that

follow:

a) Dents with related holes or cracks

b) No axial cracks.

3) Replace the engine if you find of axial cracks caused by dents.

(o) Inner platform

1) Missing material at the trailing edges of the inner platform (Areas A and B)

NOTE: Missing material is specified as the amount of material that is missing fully,

and it does not refer to areas of surface erosion, burns, oxidation or a

decrease in material thickness.

a) The limits for missing material between the adjacent blades and trailing edges

on all blades are as follows:

<1> The missing material between adjacent blades in Area A is not more

than 0.200 in. (5.08 mm)axially and 0.060 in. (1.52 mm)

circumferentially

<2> The missing material between adjacent blades at the trailing edge of

the inner platform is not more than 0.120 in. (3.05 mm)



72-00-00Config 4

Page 665


DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

<3> The total area of the missing material for the full set of blades is not

more than 0.465 in2 (300 mm2).

b) If the missing material is more than the above limits, the inspection interval

must be decreased to 500 flight hours.

<1> If the inspection interval is decreased to 500 flight hours, the limits for

the missing material between adjacent blades and the trailing edge are

as follows:

<a> The missing material between adjacent blades in Area B is not

more than 0.354 in. (9.0 mm) axial depth and 0.060 in.

(1.52 mm) circumferentially

 The missing material between adjacent blades at the inner

platform of the trailing edge is not more than 0.200 in. (5.08 mm)

<c> The total area of the missing material for the full set of blades is

not more than 1.085 in2 (700 mm2).

<2> If the axial or circumferential distance of the missing material increases

to more than 0.020 in. (0.51 mm) between inspections. The inspection

interval must be decreased to 250 flight hours.

c) If the missing material is more than the limits in b) <1>, <a>, , or <c> the

engine must be removed in not more than 30 flight cycles.

SUBTASK 72-00-00-290-001-R00

(2) Do an inspection of the intrascope nozzle guide vane through the borescope access hole in

the IP turbine casing:

(a) Make sure you can see the bush in the vane boss.

1) If the bush can be seen, it is acceptable.

2) If the bush is missing, replace the engine before 10 hours.


SUBTASK 72-00-00-080-038-R00

(1) Remove the borescope equipment. (TASK 72-00-00-206-136-R04)

SUBTASK 72-00-00-080-039-R00

(2) Remove the tool you use to turn the HP system. (TASK 72-00-00-982-026-R00)

SUBTASK 72-00-00-840-022-R00


END OF TASK



72-00-00Config 4

Page 666



FOR REFERENCE ONLY

AREA B

AREA C

AREA C

AREA B

AREA AAREA A

A-A

TRAILING EDGE

AREA BCONCAVE AIRFOIL

AREA C

SURFACE

CONVEX AIRFOIL

AREA C

SURFACE

AREA A

LEADING EDGE


LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

A A

ASEE

RB211-535 DE000A7310A

DE000A7310

DE000A7310

H60688 S00061280630_V1




72-00-00Config 4

Page 667



FOR REFERENCE ONLY

ENGINES POST-RR-SB 72-9143 AND PRE-RR-SB 72-9677

LEADING EDGE

AREA A

SURFACE

AREA C

CONVEX AIRFOIL

SURFACE

AREA C

CONCAVE AIRFOILAREA B

TRAILING EDGE

B-B

AREA OF CHANGE

(SB 72-9143)

AREA OF CHANGE

(SB 72-9143)

AREA AAREA A

AREA C

AREA CAREA B

AREA B

LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

B B

ASEE

RB211-535 DE000C8222A

DE000C8222

DE000C8222

H60713 S00061280631_V1




72-00-00Config 4

Page 668



FOR REFERENCE ONLY


C-C

AREA A

AREA C

AREA B

AREA C

AREA A

LEADING EDGE

AREA A

SURFACE

AREA C

SURFACE

CONCAVE AIRFOIL

TRAILING EDGE

AREA B

(SB 72-9677)

AREA C

CONVEX AIRFOIL

AREA B

DE000C8223

DE000C8223

LOCATION XX

TRAILING EDGE

RADIUS

(UP TO FIRST

TRAILING EDGE

COOLING HOLE)

DEE0007047

0.30 INCH (7.62 mm)

ABOVE PLATFORM AT

ROOT TRAILING EDGE

CC

ASEE

RB211-535 DE000C8223A

H60740 S00061280632_V1




72-00-00Config 4

Page 669



FOR REFERENCE ONLY

D

D

D-Ddee9001174

INNER PLATFORM

LEADING EDGE

ADJACENT BLADE

TRAILING EDGE

AREA A

AREA B

LEADING EDGE

0.200 INCH

(5.08 mm)

0.120 INCH

(3.05 mm)

ADJACENT BLADE

0.354 INCH

(9.00 mm)

0.200 INCH

(5.08 mm)

TRAILING EDGE

LEGEND:______

2488239 S0000584415_V1




72-00-00Config 4

Page 670



FOR REFERENCE ONLY

BSEE

DE000C8224

TYPICAL FIELD

OF VIEW BLADE SHROUD

BLADE ROOT

HP TURBINE BLADES



DAMAGE.

A = 2.401 INCHES (61.0 mm)



C = 2.519 INCHES (64.0 mm)

HP TURBINE

BLADES

NOTE:____


A

B

C

B

H60757 S00061280633_V1




72-00-00Config 4

Page 671



FOR REFERENCE ONLY

C

SEE C

DE000C8225


DAMAGE.

A = 2.401 INCHES (61.0 mm)



C = 2.519 INCHES (64.0 mm)

D = 0.051 INCH (3.1 mm)BETWEEN TRAILING EDGE

COOLING AIR HOLES

TYPICAL FIELD

OF VIEW

BLADE ROOT

BLADE SHROUD

HP TURBINE BLADES


A

B

C

D

HP TURBINE

BLADES


NOTE:____

H60768 S00061280634_V1




72-00-00Config 4

Page 672



FOR REFERENCE ONLY

SEE D

DE000C8226

D

HP TURBINE

BLADES

BLADE SHROULD

F

E

X

HP TURBINE BLADES



(ENDOPROBE)


E = TRAILING EDGE THICKNESS 0.042

INCH (1.07 mm)

F = HOLE SIZE 0.018 INCH (0.46 mm)

DIAMETER

X = 0.094 INCH (2.4 mm) BETWEEN

CENTER OF TRAILING EDGE COOLING

HOLES

DIMENSIONS SPECIFIED ARE A GUIDE TO

ASSESSING DAMAGE.

NOTE:____

H61194 S00061280635_V1




72-00-00Config 4

Page 673



FOR REFERENCE ONLY

DE000C8227

E

SEE E

HP TURBINE

BLADES

NOTE:____ DIMENSIONS SPECIFIED ARE A

GUIDE TO ASSESSING DAMAGE.

E = TRAILING EDGE THICKNESS

0.025 INCH (0.64 mm)


HP TURBINE BLADES



(ENDOPROBE)

BLADE SHROULD

E

H61575 S00061280636_V1




72-00-00Config 4

Page 674



FOR REFERENCE ONLY

F

SEE F

F 1

1

HP TURBINE

BLADES

OPEN/BURNT CRACKING

PROPAGATING FROM

CONCAVE AIRFOIL

LEADING EDGE

DE000C8228

HP TURBINE BLADES



(ENDOPROBE)

HP TURBINE BLADES



(ENDOPROBE)

TYPICAL REAR

FACE CRACKING

TYPICAL REAR

NON-INTERLOCK

FACE BURNING

AND OXIDATION

NON-INTERLOCK GAP

0.042 INCH

(1.07 mm)

INTERLOCK ACUTE

CORNER OPEN/BURNT

CRACKING

AREA G

TYPICAL INTERLOCK

ACUTE CORNER

CRACKING

RR ENGINES PRE-SB 72-9677H61218 S00061280637_V2




72-00-00Config 4

Page 675



FOR REFERENCE ONLY

TASK 72-00-00-206-102-R04

10. Intermediate Pressure (IP) Turbine Inspection

(Figure 612)

A. General

(1) This task provides the instructions on how to inspect the Intermediate Pressure (IP) turbine



compressor stage.

Table 604/72-00-00-993-806-R04 IP Turbine Inspection Access


LP 1S Trailing Edge - IP 112


(4) To help you make an estimate of the damage, the dimensions specified for the blades are

shown in the task..

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-846-183-R04


SUBTASK 72-00-00-946-184-R04


SUBTASK 72-00-00-480-025-R00


E. Intermediate Pressure (IP) Turbine Inspection

SUBTASK 72-00-00-296-175-R04

(1) Do an inspection of the IP turbine for the conditions that follow:

(a) Cracks

1) Not permitted.

(b) Sharp or sudden changes in the leading or trailing edge contour

1) Not permitted.

(c) Damage to the blade root or blade shroud platform

1) It is not permitted to have damage within 0.50 inch (12.7 mm) of the blade root or

0.20 inch (5.08 mm) of the blade shroud platform.

(d) Dents



72-00-00Config 4

Page 676



FOR REFERENCE ONLY

1) It is permitted to have more than one dent with a smooth bottom if you see these

conditions:

a) Leading edge dents must not be more than 0.50 inch (12.7 mm) in length and

there must be a minimum of 0.100 inch (2.54 mm) between dents.

b) Trailing edge dents must not be more than 0.020 inch (0.51 mm) in length and

there must be a minimum of 1.500 inches (38.1 mm) between dents.

c) Airfoil dents must not be more than 0.100 inch (2.54 mm) in diameter.

2) It is permitted to have one dent with a smooth bottom in the leading edge if it is not

longer than 0.125 inch (3.18 mm).

(e) Nicks or scratches on the airfoil surface

1) It is permitted to have nicks and/or scratches on the airfoil surface if each is not

larger than 0.02 inch (0.51 mm) in width and is not more than 0.05 inch (1.27 mm)

in length.

(f) Spatter

1) Permitted.

SUBTASK 72-00-00-290-002-R00

(2) Do an inspection of the intrascope nozzle guide vane through the borescope access hole in

the IP turbine casing.

(a) Make sure you can see the bush in the vane boss.

1) If the bush can be seen, it is acceptable.

2) If the bush is missing, replace the engine before 10 hours.

SUBTASK 72-00-00-840-006-R00

(3) Do the procedure to put the airplane back to its usual condition.


SUBTASK 72-00-00-080-004-R00


SUBTASK 72-00-00-080-042-R00


SUBTASK 72-00-00-860-001-R00


END OF TASK



72-00-00Config 4

Page 677



FOR REFERENCE ONLY

B = 4.493 INCHES (114.13 mm)

A = 1.149 INCHES (29.185 mm)

THE REAR

VIEWED FROM

QUANTITY 112 BLADES


DE00067962

B

A

SHROULD PLATFORM

BLADE ROOT

TRAILING EDGE

H61267 S00061280640_V1

IP Turbine Blades InspectionFigure 612/72-00-00-990-926-R04



72-00-00Config 4

Page 678



FOR REFERENCE ONLY

TASK 72-00-00-206-115-R04

11. Low Pressure (LP) Turbine Inspection


A. General

(1) This task provides the instructions on how to examine the Low Pressure (LP) turbine.



compressor stage.

Table 605/72-00-00-993-807-R04 LP Turbine Inspection Access





LP 3S *[1] Leading Edge - LP3 64


inspection lamp.


the task.

B. Location Zones

Zone Area




SUBTASK 72-00-00-940-022-R00


SUBTASK 72-00-00-940-023-R00


D. Low Pressure (LP) Turbine Inspection

SUBTASK 72-00-00-296-176-R04

(1) Do an inspection of the LP turbine for the conditions that follow:

(a) Cracks

1) Not permitted

(b) The damages that follows are not permitted:

1) Damage less than 0.50 inch (12.7 mm) of the blade root.

2) Damage that causes a sharp deformation to the contour of the leading and trailing

edge.

(c) Dents

1) Accept a single smooth bottomed dent to leading edge only if its length is not more

than 0.25 inch (6.35 mm) and its depth is not more than 0.020 inch (0.508 mm).

2) Two dents in each trailing edge are permitted if the limits below are obeyed:



72-00-00Config 4

Page 679



FOR REFERENCE ONLY

a) The dents is not more than 1.0 inch (25.4 mm) long and not more than 0.020

inch (0.508 mm) deep, with no sharp edges.

b) The maximum permitted height of the protrusion is 0.005 inch (0.127 mm).

c) The protrusion is no closer than 0.50 inch (12.7 mm) to the blade shroud or

root radius.

3) Reject all dents that are more than the limits.

(d) Nicks or scratches to the airfoil surfaces

1) Accept nicks and/or scratches to airfoil surface only if the individual length is not

more than 0.050 inch (1.270 mm) and depth is not more than 0.010 inch (0.254

mm).

(e) Spatter

1) Accept foreign object spatter.

(f) Pin and Gas Holes

1) A maximum of two holes are permitted on each of the concave and convex airfoil

surfaces as follows:

a) The holes are not on the leading or trailing edge, or the fillet radii.

b) Only one hole is in the lower 1/3 of the airfoil.


SUBTASK 72-00-00-080-032-R00


SUBTASK 72-00-00-840-019-R00


END OF TASK



72-00-00Config 4

Page 680



FOR REFERENCE ONLY

6.768 INCHES (171.92 mm)

9.200 INCHES (233.69 mm)

DIMENSION BDIMENSION A

64

64

78

3

2

1

11.143 INCHES (283.05 mm)

2.268 INCHES (57.63 MM)

2.265 INCHES (57.54 mm)

1.795 INCHES (45.60 mm)

QTYSTAGE

SHROUD

EDGE

TRAILING


VIEWED FROM THE REAR

PLATFORM

ROOT

BLADE

B

A

DE00059369

H61277 S00061280643_V1

LP Turbine Blades InspectionFigure 613/72-00-00-990-927-R04



72-00-00Config 4

Page 681



FOR REFERENCE ONLY

TASK 72-00-00-206-126-R04

12. Low Pressure Turbine (LPT) Stage 3 Nozzle Guide Vane (NGV) Inspection

(Figure 602)

A. General

(1) This task provides the instructions on how to examine the Low Pressure Turbine (LPT) stage 3

Nozzle Guide Vane (NGV).

(2) The table that follows has the access location, view area, and number of blades for the LPT

Stage 3.

Table 606/72-00-00-993-808-R04 LPT Stage 3 Inspection Access


LP 3S *[1] Rear - Stage 3 64


inspection lamp.


the task.

B. References

Reference Title


C. Location Zones

Zone Area




SUBTASK 72-00-00-940-024-R00


SUBTASK 72-00-00-480-023-R00


SUBTASK 72-00-00-940-025-R00


E. Low Pressure Turbine (LPT) Stage 3 Nozzle Guide Vane (NGV) Inspection

SUBTASK 72-00-00-296-177-R04

(1) Do an inspection of the LPT Stage 3 NGV for the conditions that follow:

(a) Cracks

1) Permitted axial cracks not more than 0.75 inch (19.05 mm) in length and are not

closer than 0.050 inch (1.270 mm) from the leading or the trailing edge.

2) Axial cracks more than the permitted limits, replace the engine within 50 hours with

these conditions:

a) The radial cracks do not exceed 1.0 inch (25.4 mm).

b) There is a minimum of 1.0 inch (25.4 mm) between cracks.

c) The cracks are non-convergent and are not within 0.50 inch (12.7 mm) of the

trailing edge.



72-00-00Config 4

Page 682



FOR REFERENCE ONLY

(b) Nicks or dents

1) Accept dents or nicks only if they do not penetrate the vane and are not within 0.50

inch (12.7 mm) of the trailing edge.


SUBTASK 72-00-00-080-033-R00


SUBTASK 72-00-00-080-035-R00


SUBTASK 72-00-00-840-020-R00


END OF TASK

TASK 72-00-00-846-143-R04

13. Put the Engine Back to Its Usual Condition

(Figure 602)


A. General

(1) This task provides the instructions on how to put the engine back to its usual condition.

B. References

Reference Title

70-51-00-912-001-R00 Torque Tightening Technique (P/B 201)



72-03-01-424-006-R00 Compressor Fairing Installation (P/B 401)

78-31-00-912-060-R04 Close the Thrust Reverser (P/B 201)

C. Consumable Materials

Reference Description Specification

B00713 [OMat 1/257] Solvent - Cleaning OMat 1/257

B50009 [OMat 150] Acetone OMat 150

B50018 [OMat 1/40] Alcohol - Isopropyl OMat 1/40

D00071 Oil - Aircraft Turbine Engine, Synthetic Base MIL-PRF-7808 Grade 3

D00605 [OMat 4/46] Compound - Jointing OMat 4/46 DTD

900/4586

D50115 [OMat 4/62] Compound - Anti-seize, High Temperature OMat 4/62

G01043 Cloth - Lint-free

D. Location Zones

Zone Area





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FOR REFERENCE ONLY

E. Put the Engine Back to Its Usual Condition

SUBTASK 72-00-00-296-022-R04

WARNING

DO NOT GET CLEANING SOLVENT IN YOUR MOUTH OR EYES OR ON

YOUR SKIN. DO NOT BREATHE THE FUMES FROM THE CLEANING

SOLVENT. PUT ON A PROTECTIVE SPLASH GOGGLE AND GLOVES WHEN

YOU USE THE CLEANING SOLVENT. KEEP THE CLEANING SOLVENT AWAY

FROM SPARKS, FLAME AND HEAT. THE CLEANING SOLVENT IS

POISONOUS AND FLAMMABLE AND CAN CAUSE INJURY TO PERSONS OR

DAMAGE TO EQUIPMENT.

(1) Make a lint-free cloth, G01043 moist with cleaning solvent, B00713 [OMat 1/257], isopropyl

alcohol, B50018 [OMat 1/40] or acetone, B50009 [OMat 150].

SUBTASK 72-00-00-160-003-R00

(2) Clean and let dry the engine surfaces that follow:

NOTE: Make sure you remove all the used jointing compound or anti-seize compound from

the engine case and borescope access details.

(a) The borescope access details that will touch the outer faces of the engine case when

assembled.

(b) The engine case that will touch the borescope access details when they are assembled.

SUBTASK 72-00-00-296-023-R04

CAUTION

MAKE SURE THAT THE BORESCOPE PLUGS ARE INSTALLED IN THE

CORRECT PORT LOCATIONS. ENGINE DAMAGE CAN OCCUR IF A

BORESCOPE PLUG IS NOT INSTALLED IN THE CORRECT LOCATION.

(3) Install the borescope access details.

(a) Install the access details at location B:

CAUTION




ENGINE CAN OCCUR.


the plugs, the three spacers, and the engine case.

2) Make sure no jointing compound goes into the central passageways of the plugs or

spacers.


3) Apply a thin layer of high temperature anti-seize compound, D50115 [OMat 4/62] on

the location surface of the blanking plug ends.


4) Put the access details in their correct position on the LP compressor inner case.


6) Make sure the blanking plug mating flanges fully touch the compressor case.


8) Install the washers and the bolts.



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FOR REFERENCE ONLY

a) Tighten the bolts (TASK 70-51-00-912-001-R00).

CAUTION




ENGINE CAN OCCUR.


the access details.


11) Make sure the blanking plugs at locations G and F are in the correct position at their

inner end.

12) Make sure the blanking plug mating flanges at locations G and F fully touch the

compressor case.


14) Install the bolts and tighten (TASK 70-51-00-912-001-R00).

(b) Install the access details at locations G, D, E and F:

CAUTION




ENGINE CAN OCCUR.


the access details.


3) Make sure the blanking plugs at locations G and F are in the correct position at their

inner end.

4) Make sure the blanking plug mating flanges at locations G and F fully touch the

compressor case.



(c) Install the access details at location K:

WARNING

DO NOT GET THIS MATERIAL IN YOUR MOUTH, EYES, OR ON

YOUR SKIN. CLEAN BARE SKIN FULLY AFTER YOU USE THIS

MATERIAL. THIS MATERIAL CAN CAUSE INJURIES TO

PERSONNEL OR DAMAGE TO EQUIPMENT.


the threads and the mating faces of the HP NGV blanking plug.

2) Install the blanking plug and tighten to 370 pound-inches (41.81 Newton-meters).


the mating faces of the HP NGV blanking cover.

4) Put the blanking cover into the correct position on the engine.





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FOR REFERENCE ONLY

DHI 113-120 POST SB RB211-72-C230


wire/cable.


(d) Install the access details at locations J, L, C, A and H:

NOTE: At location J make sure the C-ring seals are visually satisfactory and installed

correctly to the blanking plugs.

WARNING

DO NOT GET THIS MATERIAL IN YOUR MOUTH, EYES, OR ON

YOUR SKIN. CLEAN BARE SKIN FULLY AFTER YOU USE THIS

MATERIAL. THIS MATERIAL CAN CAUSE INJURIES TO

PERSONNEL OR DAMAGE TO EQUIPMENT.

CAUTION




ENGINE CAN OCCUR.

1) Use a brush to apply a thin layer of high temperature anti-seize compound, D50115

[OMat 4/62] to the mating faces of the access details.

2) Put the access details into their correct position on the engine.


4) Make sure the blanking plug mating flanges fully touch the combustion case.



DHI 113-120 POST SB RB211-72-C230


wire/cable.

DHI 101-121, 301-999 POST SB RB211-72-C230

SUBTASK 72-00-00-080-011-R00

(4) Remove the tools you use to turn the IP and HP systems (TASK 72-00-00-980-801-R00 and

TASK 72-00-00-982-026-R00).


SUBTASK 72-00-00-296-025-R04

(5) Install the right-hand lower compressor fairing panel (TASK 72-03-01-424-006-R00).

SUBTASK 72-00-00-410-004-R00

(6) Close the thrust reversers (TASK 78-31-00-912-060-R04).

SUBTASK 72-00-00-860-027-R00

(7) For the left engine, remove the safety tags and close these circuit breakers:


Row Col Number Name






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DHI

DHI

DHI

DHI

DHI


FOR REFERENCE ONLY

SUBTASK 72-00-00-860-028-R00

(8) For the right engine, remove the safety tags and close these circuit breakers:


Row Col Number Name




SUBTASK 72-00-00-860-029-R00

(9) For the left engine, remove the safety tag and close this circuit breaker:


Row Col Number Name


SUBTASK 72-00-00-860-030-R00

(10) For the right engine, remove the safety tag and close this circuit breaker:


Row Col Number Name


END OF TASK



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FOR REFERENCE ONLY

B757 RB211-535 Borescope Recurrent Training 2020

Documents

Transcript of B757 RB211-535 Borescope Recurrent Training 2020