B767 CF6-80C Borescope Recurrent Training 2020cbt.altitudeglobal.aero/Files/B767 CF6...

FOR REFERENCE ONLY

B767 CF6-80C 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 contains these tasks:

(1) Borescope Inspection

(2) Continue-In-Operation Limits

(3) Unusual Condition Inspection

(4) External Engine Inspection

(5) Radiographic Engine Inspection

(6) Ultrasonic Inspection

(7) Inspection of Engines Involved in Accidents or Incidents

(8) Compressor Rear Frame (CRF) Oil Leakage Inspection

(9) Oil System Leakage Inspection

(10) Inlet Gearbox Assembly - Horizontal Bevel Gear Seal Borescope Inspection

(11) Inclement Weather Flameout Inspection.

(12) Inlet Gearbox Spline Nozzle Borescope Inspection

(13) Inlet Gearbox Spline Backlash Borescope Inspection

(14) Combustion Section Inspection (scheduled maintenance requirement)

(15) High Pressure Turbine Inspection (scheduled maintenance requirement)

(16) Volcanic Ash/Sand Ingestion Inspection.

B. The maintenance of the engine makes it necessary to do inspection checks at intervals. The

inspection requirements and limits throughout this manual are based on operation within specified

limits. In addition to the regular inspections, there are those necessary when the engine has been

operated outside of the specified limits (for example, overspeed or overtemperature). There are also

special inspections necessary for engines to which unusual conditions are applied. These include

aircraft accidents and incidents specified in ICAO Annex 13. Also included are other unusual

incidents such as a hangar or ramp fire, or an accident during engine transport, handling or storage.

This procedure gives the inspection checks necessary after an overlimit operation and the special

inspection checks necessary for engines exposed to unusual conditions.

TASK 72-00-00-206-146-H00

2. Borescope Inspection

(Figure 601, Figure 602, Figure 603, Figure 604, Figure 606, Figure 612 or Figure 613 or Figure 614 or

Figure 615, Figure 616, Figure 617, Figure 618, Figure 618, Figure 620, Figure 621, Figure 622,

Figure 623, Figure 625, Figure 626 and Figure 627)

A. General

(1) This task gives instructions to examine the internal areas of the engine along the flow of the

primary airstream.

(2) Use the borescope ports for access to examine the internal engine areas. You do not have to

disassemble the engine to do this task.

(3) During an inspection, if you find damage that is more than the maximum serviceable limits,

refer to the continue-in-operation limits to operate the airplane for additional flights.

NOTE: A 'flight' and a 'flight cycle' are identical, both terms are used to refer to one takeoff and

one landing.

767AIRCRAFT MAINTENANCE MANUAL

CF6-80C SERIES ENGINES

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Continuation Training 2020

chrisiHighlight

chrisiHighlight

B. References

Reference Title

71-11-04-712-011-H00 Open the Fan Cowl Panels (P/B 201)

71-11-04-712-012-H00 Close Fan Cowl Panels (P/B 201)

72-00-00-117-007-H00 How to Clean the Engine Core (Water Wash) (P/B 701)

72-00-00-127-044-H00 How to Clean the Engine with Coke (P/B 701)

72-00-00-982-007-H00 N2 Rotor Manually Crank (P/B 201)

72-00-00-982-024-H00 N2 Rotor Pneumatically Crank (P/B 201)

72-36-00-308-125-H00 Borescope Blending Tool - Repair of the Stage 1-14 HPC Rotor

Blades (P/B 801)

72-36-00-808-105-H00 Loosen the Shingled HPC Stage 1 Blades (P/B 801)

73-11-05-206-001-H00 Fuel Nozzle Inspection (P/B 601)

77-34-03-004-001-H00 Remove the P49 Pressure Probe (P/B 401)

77-34-03-404-007-H00 Install the P49 Pressure Probe (P/B 401)

78-31-00-002-083-H00 Open Thrust Reverser (Hand Pump Procedure) (P/B 201)

78-31-00-402-084-H00 Close Thrust Reverser (Hand Pump Procedure) (P/B 201)

C. 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-5661 Borescope - Fiber Optic, CF6-80A/A2 and CF6-80C2B Engines,

Intrinsically Safe (Approved for use in Class I, Divisions I & II

hazardous locations)

Part #: 2C6388G06 Supplier: 06083Part #: 2C6388G07 Supplier: 06083

STD-12814 Wrench - Torque

D. Consumable Materials

Reference Description Specification

B00148 Solvent - Methyl Ethyl Ketone (MEK) ASTM D740

D00006 Compound - Antiseize Pure Nickel Special -

Never-Seez NSBT

BAC5008

E. Location Zones

Zone Area

410 Left Powerplant

420 Right Powerplant

F. Borescope Inspection of Engine Stages 1-14

SUBTASK 72-00-00-986-002-H00

(1) Do the steps to manually or pneumatically turn the N2 rotor at the accessory gearbox

(TASK 72-00-00-982-007-H00 or TASK 72-00-00-982-024-H00).

NOTE: The engine manufacturer recommends to turn the N2 rotor, then stop to examine the

blade with a borescope. After you examine the condition of the blade, turn the N2 rotor,

then stop again to examine the next blade.



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SUBTASK 72-00-00-016-097-H00

CAUTION

PUT A LABEL ON THE BORESCOPE PLUGS. ENGINE DAMAGE CAN OCCUR

IF THE BORESCOPE PLUGS ARE NOT INSTALLED IN THE CORRECT

LOCATION.

(2) Remove the borescope plugs B1-0, B1-1, B1-6, and B1-12 and, as an option, B1-4, B1-5 and

B1-13 (Figure 601).

NOTE: Use borescope ports B1-0 and B1-1 to view stage 1 and borescope port B1-12 to

examine stage 12.

NOTE: Usually, it is only necessary to do a borescope inspection through the B1-0, B1-1,

B1-6, and B1-12 ports. If it is necessary, you can remove the borescope plugs from

ports B1-4, B1-5 and B1-13.

NOTE: If you cannot loosen and remove the referenced borescope plug, you can do the

borescope inspection through an adjacent port.

(a) Put labels on the borescope plugs that you removed.

SUBTASK 72-00-00-296-264-H00

(3) Visually examine the stage 1-14 compressor blades with the borescope for the conditions in

Table 601:

(a) If the stage 1-14 blades have damage that is more than the maximum serviceable limits,

do this task: Borescope Blending Tool - Repair of the Stage 1-14 HPC Rotor Blades,

TASK 72-36-00-308-125-H00.

(b) For damage to the stage 1-14 blades that is more than the maximum serviceable limits,

continue in service for a maximum of 10 flight cycles with these conditions:

1) The damage is within repairable limits for borescope blending of the HPC stage

1-14 rotor blades.

a) Do this task: Borescope Blending Tool - Repair of the Stage 1-14 HPC Rotor

Blades, TASK 72-36-00-308-125-H00.

2) There is only one engine that has damage that is more than the serviceable limits.

3) A borescope inspection of downstream HPC stages has been performed and all

blade damage is within the blend repairable limits.

Table 601/72-00-00-993-898-H00

Stages Condition Notes* Maximum Serviceable Limit

1-14 Erosion on leading and

trailing edges

All amounts that are within the HPC rotor blade

repair limits are permitted

(TASK 72-36-00-308-125-H00).

1-14 Nicks and dents on the

center panel of the blade

(Figure 604)

*[1]

*[2]

*[3]

Permitted with these conditions:

1. It does not go all the way across the blade.

2. It is at least 0.20 inch (5.1 mm) from the leading

and trailing edges of the blade.

3. It does not make a hole in the blade.

4. It is less than 0.15 inch (3.8 mm) in diameter.



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Table 601/72-00-00-993-898-H00 (Continued)


1-14 Corrosion and dirt*[2]

*[4]Permitted.

Clean the dirt with water wash or coke clean

(TASK 72-00-00-117-007-H00 or

TASK 72-00-00-127-044-H00). Water wash is

preferred.

1-14 Abrasive deposits on the

blades (usually found on

the leading edges)

*[2]

*[4]Permitted. Clean the dirt with water wash or coke

clean (TASK 72-00-00-117-007-H00 or

TASK 72-00-00-127-044-H00). Water wash is

preferred.

1-14 Blade Platform shingling*[2]

Not permitted. Replace the engine.

1-14 Blade Platform bowing*[2]


1-14 Burrs and high metal of

the blade tips

*[2]Permitted.

1-14 Tears, nicks, dents and

missing metal on the

squealer

*[2]Permitted, if the damage is only in the squealer tip

area and is 0.030 inch (.76 mm) radially from the

tip.

1, 2, 6 -14 Missing erosion coating

at the blade tip (concave

side only:

*[5]

a) Radial indications of

coating erosion

a) Permitted.

b) Cracks in coating

material

b) Permitted. Examine for cracks in blade material

by inspection of the uncoated side of the blade.

Refer to the blade material crack serviceability

limits by stage.

c) Missing coating

material

c) Permitted.

1-9 Tip curl*[2]

*[6]Permitted, if less than 1/2 of the blade tip chord is

curled and it does not. engage other parts that do

not more during operation. There must be no other

unserviceable damage (Figure 602).

1-9 Cracks in the blade tips Cracks that does not extend into the blade beyond

the squealer tip are permitted.

1-9 Bent blades*[2]

Permitted, if the blade bending does not result in

kinks in the blade edges or uneven blade tip

spacing (Figure 602).

1-2, 6-9 Nicks, dents and missing

material on the leading

and trailing edges

*[2]Permitted, if less than 0.05 inch (1.3 mm) in depth.

Damage more than the limits must be blended to

be permitted (TASK 72-36-00-308-125-H00).

1-2, 6-9 Tears, cracks and bends

on the leading and

trailing edges

*[3]Not permitted. Damage must be blended

(TASK 72-36-00-308-125-H00).



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1-2 Missing tip corners*[1]

*[6]

*[7]

Permitted, if a minimum of 3/4 tip chord length

remains between the missing tip corners (one or

two missing tip corners per blade). All edges must

be smooth except for location C (Figure 604).

You can find the description for the unserviceable

conditions when you do the rotor blade repair

(TASK 72-36-00-308-125-H00).

You must do a borescope inspection of the HPC

blade stages aft (downstream) of the blade that

has a missing tip corner.

1-2 Missing tip corners, 1/2

tip chord

*[1]

*[6]

*[7]

A maximum of four blades per stage are permitted

if a minimum of 1/2 tip chord length remains

between the missing tip corners (one or two

missing tip corners per blade). All edges must be

smooth except for location C (Figure 604).




1 Tip corner fold*[1]

*[6]

*[7]

Permitted, if no tears and cracks are present and if

the size is less than 0.75 inch (19.1 mm) axially

and 2.0 inch (51 mm) radially from the tip corner

(Figure 602).

1 Distortions on the blade

platform

Permitted.

1 Cracks on the blade

platform


1 Shingling of the

mid-span shrouds

Refer to the table below for maximum serviceable

limits for the mid-span areas.

2-14 Tip clang marks (contact

other blades)

*[2]

*[8]Permitted, if the tip is not cracked or torn

(Figure 602).

3-14 Missing tip corners*[2]

*[6]

*[7]

*[9]

Permitted, if a minimum of 3/4 tip chord length

remains between the missing tip corners (one or

two missing tip corners per blade). All edges must

be smooth except for location C (Figure 604).



has a missing tip corner. There must be no

unserviceable damage on the blades in the aft

stages. You can find the tip chord length

dimensions and the unserviceable conditions

when you do the rotor blade repair

(TASK 72-36-00-308-125-H00).



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3-14 Missing tip corners, 1/2

tip chord

*[6]In addition to the missing tip corner limit above, a

maximum of six blades per stage are permitted, if

a minimum of 1/2 tip chord length remains

between the missing tip corners (one or two

missing tip corners per blade). All edges must be

smooth except for location C (Figure 604).




CF6-80C ENGINES PRE GE SB 72-0975 AND/OR POST SB 72-1060

3,4,5 Nicks, dents and missing


and trailing edges

*[3]All nicks, dents and missing material are permitted

if less than 0.05 inch (1.3 mm) in depth and the

blade is not torn or bent. Torn or cracked edges

are not permitted.

CF6-80C ENGINES POST GE SB 72-0975


material in area X on the

leading and trailing

edges

*[3]

*[9]Not permitted in area X (Figure 602). Do the

borescope blending repair of the stage 1-14 HPC

rotor blades (TASK 72-36-00-308-125-H00).


material in area Y on the


edges

*[3]

*[9]All amounts less than 0.05 inch (1.3 mm) in depth

are permitted in area Y.

ALL CF6-80C ENGINES

3, 4, 5 Tears, cracks and bends

on the leading and

trailing edges

*[3]Not permitted. Do the borescope blending repair of

stages 1-14 HPC rotor blades

(TASK 72-36-00-308-125-H00).

10,11 Cracks on the blade tips Not permitted over the maximum serviceable

extension of 10 cycles.

10, 11, 12 Nicks, dents and missing


and the trailing edges of

the blades less than or

equal to 0.30 inch (7.6

mm) radially from the tip

*[3]Permitted, if less than 0.05 inch (1.3 mm) axially in

depth. In addition, a maximum of six blades per

stage permitted, if less than 0.120 inch (3.05 mm)

axially in depth and, less than 0.120 inch (3.05

mm) radially in length.

10, 11, 12 Nicks, dents and missing


and the trailing edges of

blades greater than 0.30

inch (7.6 mm) radially

from the tip

*[3]Permitted, if less than 0.05 inch (1.3 mm) axially in

depth.

10, 11, 12 Tears and cracks on the


edges

*[3]Not permitted. You must blend the damage. Do the

borescope blending repair of the 1-14 HPC rotor

blades (TASK 72-36-00-308-125-H00).



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10-14 Bent blades Permitted, if blade bending does not result in kinks

in the blade edges or uneven blade tip distance

(Figure 602).

Kinks and uneven distance are not , repairable,

remove the engine.

10-14 Tip Curl*[6]

*[9]Permitted, if it does not engage other parts that do

not move during operation. There must be no other

unserviceable damage, Refer to the airfoil damage

nomenclature (Figure 602).

12, 13, 14 Cracks in the blade tips Permitted, if the cracks are in a radial direction and

are less than 0.50 inch (12.7 mm) in length.

13, 14 Nicks, dents and missing


and trailing edges of the

blades

Any number permitted, if less than 0.05 inch (1.3

mm) in depth. Refer to the airfoil damage

nomenclature (Figure 602).

13, 14 Nicks, dents, missing

material, tears and

cracks on the leading

and trailing edges of the

blades less than or

equal to 0.50 inch (12.7

mm) from the blade tip

In addition to the limit above that affect all blades,

up to six blades for each stage are permitted to

have damage more than 0.05 inch (1.3 mm) in

depth but less than 0.120 inches (3.1 mm) in

depth.

13, 14 Tears, cracks and bends

on the leading and

trailing edges of the

blades greater than 0.50

inch (12.7 mm) from the

blade tip

Not permitted.

*[1] Some stage 1 blades have a bulge in the airfoil leading and trailing edge. The bulge is located in a radial line with the

mid-span shroud. This bulge is part of the blade design and not a defect or dent.

*[2] GE SB 72-1082 (New Stages 7 and 8 Blades) introduced new stages 7 and 8 rotor blades that are more contoured

than previous blades. These can be identified by the letter "N" on the platform on the concave side of the blade.

Damage and blend limits for these blades are the same as those for previous blades.

*[3] The leading and trailing edges are defined as 0.20 inch (5.1 mm) from the edge.

*[4] A large quantity of deposits can affect the engine performance.

*[5] GE SB 72-1242, 72-1243, 72-1244 Stage 1, Stage 2 and Stage 6 - 14 blade tips are coated with erosion resistant

material on concave surface (approximately 0.5 inch (12.7 mm) radially inward.

*[6] This condition can cause low engine performance and high engine vibration.

*[7] For example, if a stage 2 blade has a missing corner, the HPC blades aft of stage 2 must be inspected for signs of

impact damage because the released tip corner could impact blades in a number of aft stages.

*[8] Damage of this type is a sign of a compressor hard stall. Do the stall inspection.

*[9] GE SB 72-0975 (Stage 3, 4 and 5 Blade Replacement) blades are marked with a "T" on the blade platform on the

concave side of the blade. Over extension limits do not apply.

SUBTASK 72-00-00-216-159-H00

(4) Examine the mid-span shroud areas of the 1st-stage blades for the conditions in Table 602:



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Table 602/72-00-00-993-899-H00


1 Shingling of 1st stage

blades (the midspan

shrouds are overlapped)

Not permitted. Loosen the shingled blades

(TASK 72-36-00-808-105-H00).

1 Signs that shingling

happened in flight

(scratches or gouges on

the lower or upper

mid-span shroud

surfaces)

Permitted with these conditions:

1. The blades are not shingled at this time.

2. There are no dents on the airfoil panel or the

midspan fillet directly above and below the mid-

span shrouds.

3. There are no other unserviceable damage.

1 Dents in the airfoil or the

mid-span shroud trailing

edge fillet radii

*[1]Permitted, if the dents are in the area aft of the

mid- span shroud. Dents are not permitted to

show through to the other side of the blade.

1 Mid-span shroud tip

corner damaged or

missing

*[1]Permitted, if less than 0.150 inch (3.81 mm) in

axial length (or 20% of the mid-span axial

length).

1 Cracks in the carboloy

pad

Permitted, if there is no parent metal wear.

1 A piece of the carboloy

pad is missing

Permitted, if less than 0.150 inch (3.81 mm) in

axial length (or 20% of the pad).

1 A piece of the carboloy

pad more than 0.150

inch (3.81 mm) in axial

length is missing

Permitted, if more than 0.150 inch (3.81 mm) in

axial length with these conditions:

1. There are no signs of wear in the mid-span

shroud parent metal.

2. You do an inspection before 25 flight cycles

and there no signs of new damage.

3. You do subsequent inspections each 200

(maximum) flight cycles. There must be no signs

of wear in the parent metal of the mid-span

shroud.

ENGINES PRE GE SB 72-1268 (RECESSED WEAR PAD)

1 Signs of wear in the

parent metal of the

mid-span shroud

*[2]Not permitted. Refer to the figure for the

compressor 1st-stage blade mid-span shroud

carboloy pad.

ENGINES POST GE SB 72-1268 (RECESSED WEAR PAD)

1 Signs of wear in the

parent metal of the

mid-span shroud

Permitted above the base of the carboloy pad if

the pad meets serviceable limits. Not permitted

below the carboloy pad. Do an inspection of the

inner diameter of the mid-span shroud edges to

view the condition of the carboloy pad

(Figure 603).

*[1] This type of damage is caused by contact with the mid-span shroud of the adjacent blade.

*[2] The wear of the mid-span shroud parent metal occurs because of damaged or missing carboloy pad material. This

causes the parent metal of the mid-span shroud to contact the mid-span shroud of the adjacent blade.

SUBTASK 72-00-00-296-005-H00

(5) Use the borescope to visually examine the rotor spools and the disks for the conditions in

Table 603:



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Table 603/72-00-00-993-900-H00

Condition Notes* Maximum Serviceable Limit

Rub coat that is not there*[1]

Permitted.

Spools land rubs on stages 10- 13

vane lands that show parent metal

(caused by vane tip to spool land

contact)

Permitted. Three rub spots with a maximum circumferential

length of 1.0 inch (25.4 mm) each and a minimum

separation of 2.0 inches (50.8 mm).

Permitted. Three rub spots with a maximum circumferential

length of 2.0 inches (50.8 mm) each and a minimum

separation of 6.0 inches (152.4 mm).

*[1] This can affect engine performance by a small amount.

SUBTASK 72-00-00-086-098-H00

(6) Remove the borescope.

SUBTASK 72-00-00-416-193-H00

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.

(7) Do the steps that follow to install all the borescope plugs that were removed:

(a) Apply a light layer of Never-Seez NSBT compound, D00006 on the threads and the

pressure faces of the plugs.

(b) Install the borescope plugs into the borescope ports.

(c) Use a torque wrench, STD-12814 to tighten the plugs to the torque values shown in

Figure 601.

(d) Install lockwire.

SUBTASK 72-00-00-096-099-H00

CAUTION

MAKE SURE THAT YOU INSTALL THE COVERPLATE. THE COVERPLATE

LOCATION IS DIFFICULT TO SEE DURING ENGINE MAINTENANCE. IF THE

COVERPLATE IS NOT INSTALLED OR THERE IS AN INCORRECT

INSTALLATION, THE INSTALLATION WILL CAUSE A FAST OIL LEAKAGE.

ENGINE DAMAGE CAN OCCUR WHEN THE ENGINE IS OPERATED.

(8) Remove the equipment to turn the N2 rotor (TASK 72-00-00-982-007-H00 or

TASK 72-00-00-982-024-H00).

SUBTASK 72-00-00-416-007-H00

(9) If you only do the borescope inspection of engine stages 1-14, do these steps:

WARNING

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE

THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,

INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(a) Close the thrust reversers (TASK 78-31-00-402-084-H00).

(b) Close the fan cowl panels (TASK 71-11-04-712-012-H00).



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ECS DUCT

ASEE

A

FWD

CF8-8258-00-A2A

B1-7 B1-10 B1-11

B4-2

CF8-6869-00-AF19591 S00061426291_V1

Engine Borescope Port LocationsFigure 601/72-00-00-990-803-H00 (Sheet 1 of 3)



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B

B

CF8-8257-00-A2A

1

1 NOTE:____ SOME BORESCOPE PORTS ARE BEHIND

THE EXTERNAL HARDWARE.

FWD

B

BSEE

(VIEW IN THE

FORWARD DIRECTION)

B-B

B2-1

B2-4

B2-5 CW

B2-3

B2-2

BORESCOPING)

(HP ROTOR

B5 MOTOR MOUNT

B1-3B3-2

B3-1

B1-13

B1-12

B4-1

B4-3

B4-4

B1-9

B1-8

B1-6

B1-5

B1-4

B1-1

B1-0

B1-2

IF NECESSARY, REMOVE THE ECS DUCT

AND THE BLEED AIR SENSE LINE FOR

EASIER ACCESS.F19597 S00061426294_V2




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B1-0 THROUGH B1-6

(AMM 77-21-01/401)

MANIFOLD CLAMP NUT

B1-7 (NO PLUG)

B1-8 (NO PLUG)

B1-9 (NO PLUG)

B1-11 (NO PLUG)

B1-10 AND B1-13

B1-12

(PAD COVER BOLTS)

PROBE BOLTS)

PORT

BORESCOPE

SIZE

WRENCH

(NEWTON METERS)

POUND-INCHES

TORQUE VALUE

__________COMPRESSOR

1/4 HEX. 33-37 (3.7-4.2)

40-60 (4.5-6.8)5/16 12-PT

EGT PROBES

MANIFOLD CLAMP NUT

MANIFOLD CLAMP NUT

3/4 HEX.

3/4 HEX.

1-1/8 HEX.

1-1/8 HEX.

7/8 HEX.

5/16 12-PT

5/16 12-PT

3/4 HEX.

B3-1

B3-2

B4-2

B4-3 AND B4-4

B4-1 (PAD COVER/

B2-1 THROUGH B2-5

140-160 (15.8-18.1)

50-60 (5.6-6.8)

40-60 (4.5-6.8)

40-60 (4.5-6.8)

140-160 (15.8-18.1)

50-60 (5.6-6.8)

55-70 (6.2-7.9)

55-70 (6.2-7.9)

40-60 (4.5-6.8)

90-100 (10.2-11.3)

TURBINE (LPT)

_________COMBUSTOR

HIGH PRESSURE_____________

TURBINE (HPT)_____________

LOW PRESSURE____________

_____________

7/8 HEX.

MANIFOLD CLAMP NUT

115-125 (13.0-14.1)

115-125 (13.0-14.1)

55-70 (6.2-7.9)

A59251 S00061426295_V1




72-00-00

Page 637


EFFECTIVITYDHI ALL

For Training Only


FWD

SEE A

SEE C

A

A

TIP CLANG MARK

(EXAMPLE)

0.75 INCH

(19.1 mm)

MAXIMUM

2.0 INCHES

(50.8 mm)

MAXIMUM

IGV

CONTACT

DAMAGE

2/3 CHORD

TRAILING

EDGE

BENT AT THE

TIP FROM THE

CONVEX SIDE

COMPRESSOR

ROTOR BLADE

LEADING

EDGE

(EXAMPLE)

A-ATIP CURL

243630 S00061426296_V1

Compressor Rotor Blades InspectionFigure 602/72-00-00-990-806-H00 (Sheet 1 of 5)



72-00-00

Page 638


EFFECTIVITYDHI ALL

For Training Only


SEE B

A

1300486-00

BLADE FILLET RADIUS

TANGENT POINT

AREA X (BOTH SIDES)

2.0 INCH (50.8 MM)

AREA Y

AREA Y

BLADE FILLET RADIUS

TANGENT POINT

2028814 S00061426297_V1




72-00-00

Page 639


EFFECTIVITYDHI ALL

For Training Only


B

1300487-00

UNEVEN TIP

SPACING

KINK IN BLADE EDGE

2028818 S00061426298_V1




72-00-00

Page 640


EFFECTIVITYDHI ALL

For Training Only


D

C

SEE D

SEE E

1300477-00

TIP CURL OR FOLD

IGV CONTACT

EDGE EROSION

PLATFORM

DOVETAIL

DOVETAIL

ROOT FILLET RADII

(ALL AROUND)

LEADING EDGE MID SPAN

SHROUD

WEAR PAD

CARBOLOY

TRAILING EDGE

CENTER

PANEL

AXIAL CRACK OR TEAR

NICKRADIAL TIP

CRACK

TIP CORNER

MISSING OR

CORNER EROSION

DEPTH

RADIAL

TIP CLANG

NORMAL LEADING

EDGE CONTOUR

DENT DEPTH

CHORD

PERCENT

DENT

TIP

CURL

DENT WIDTH

NICK DEPTH

EDGE EROSION

NOTE: NO SHARP CORNERS AFTER BLENDING,

MINIMUM BLEND RADII IS 0.5 INCH (12.7 MM) RADIUS

100% CHORD

LENGTH

____

DENT

LENGTH

2028880 S00061426299_V2




72-00-00

Page 641


EFFECTIVITYDHI ALL

For Training Only


E

1300480-00

DIMENSION B

DIMENSION A

REMAINING TIP CHORD LENGTH

WITH 2 CORNERS MISSING

REMAINING TIP CHORD LENGTH

WITH 1 CORNER MISSING

DIMENSION A

LOCATION C

NOTE: 1. MATERIAL MISSING FROM THE BLADE TIP CORNER WITH A SEPARATION

LINE RUNNING FORM THE BLADE TIP TO THE LEADING OR TRAILING EDGE.

2. MISSING CORNER MAY BE ANY SHAPE WITHING AREA A WHERE DIMENSION A IS

EQUAL TO 1/4 THE BLADE CORD LENGTH.

3. MISSING CORNER MAY EXTEND INTO AREA B PROVIDED THE SEPARATION LINE

IS A SMOOTH CURVE (NO NOTCHES OR CUSPS) EXCEPT AT THE LEADING OR

TRAILING EDGE. LOCATION C. WHERE A TENSILE CUSP IS PERMITTED.

____

AREA B

AREA A

DIMENSION B

TIP CORNER MISSING OR

CORNER EROSION

2028894 S00061426300_V1




72-00-00

Page 642


EFFECTIVITYDHI ALL

For Training Only


CLEARANCE AND JAGGED WEAR AREA

(CARBOLOY PAD IS GONE)

TOP OF MID SPAN

BORESCOPE VIEW:

(WITH CARBOLOY WEAR PADS)

SHROUD FROM PORT B1-1

TRAILING EDGE

NO WEAR

BA

ASEE B

UNSERVICEABLE WEAR

LEADING EDGE

243634 S00061426301_V1

Mid-Span Shroud Inspection of the 1st-Stage BladesFigure 603/72-00-00-990-807-H00 (Sheet 1 of 4)



72-00-00

Page 643


EFFECTIVITYDHI ALL

For Training Only


PAD IS GONE)

CLEARANCE AND JAGGED

WEAR AREA (CARBOLOY

DC

BORESCOPE VIEW:

UP AND UNDER MID SPAN SHROUD TIPS FROM PORT B1-1

(WITH CARBOLOY WEAR PADS)

TRAILING EDGE

NO WEAR

DCSEE

UNSERVICEABLE WEAR

LEADING

EDGE

243635 S00061426302_V1




72-00-00

Page 644


EFFECTIVITYDHI ALL

For Training Only


0.6 INCH

(15.24 mm)

APPROVED AREA FOR AIRFOIL DENTS CAUSED BY THE

MID-SPAN SHROUDS OF THE ADJACENT BLADES

NO AIRFOIL DENTS PERMITTED

LEADING EDGE

A36060 S00061426303_V1




72-00-00

Page 645


EFFECTIVITYDHI ALL

For Training Only


A

BORESCOPE VIEW LOOKING DOWN

ON TOP OF MID SPAN

SHROUD FROM PORT B1-1

SEE A

TIP DAMAGE

SCRATCHES OR GOUGES

ON THE UPPER/LOWER

MID-SPAN SHROUD SURFACES

DENTS ON THE

AIRFOIL OR

AIRFOIL FILLET

ABOVE OR BELOW

THE MID-SPAN

SHROUDS

TRAILING EDGE

FILLET

A36073 S00061426304_V1




72-00-00

Page 646


EFFECTIVITYDHI ALL

For Training Only


DIMENSION B

DIMENSION A

DIMENSION A

DIMENSION B

NOTE:____

AREA A

AREA B

LOCATION C

1. MATERIAL MISSING FROM THE BLADE TIP CORNER WITH A SEPARATION

LINE RUNNING FROM THE BLADE TIP TO THE LEADING OR TRAILING EDGE.

2. MISSING CORNER MAY BE ANY SHAPE WITHIN AREA A WHERE DIMENSION A IS

EQUAL TO 1/4 THE BLADE CORD LENGTH.

3. MISSING CORNER MAY EXTEND INTO AREA B PROVIDED THE SEPARATION LINE

IS A SMOOTH CURVE (NO NOTCHES OR CUSPS) EXCEPT AT THE LEADING OR

TRAILING EDGE, LOCATION C, WHERE A TENSILE CUSP IS PERMITTED.

W85407 S00061426305_V1

HPC Blade Tip CornerFigure 604/72-00-00-990-808-H00



72-00-00

Page 647


EFFECTIVITYDHI ALL

For Training Only


G. Borescope Inspection of the Combustion Section

SUBTASK 72-00-00-016-009-H00

(1) If it is necessary, do this task: Open the Fan Cowl Panels, TASK 71-11-04-712-011-H00.

SUBTASK 72-00-00-010-002-H00

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.

(2) If it is necessary, open the thrust reversers (TASK 78-31-00-002-083-H00).

SUBTASK 72-00-00-086-156-H00

CAUTION

BEFORE YOU USE THE BORESCOPE, MAKE SURE THAT THE

TEMPERATURES OF THE INSPECTION AREAS ARE BELOW 150°F (66°C). IF

THE ADJACENT CASES ARE TOO HOT TO KEEP YOUR HAND ON, THE

INSPECTION AREAS ARE TOO HOT. IF THE INSPECTION AREA IS TOO HOT,

DAMAGE TO THE BORESCOPE CAN OCCUR.

CAUTION



LOCATION.

(3) Remove the borescope plugs B2-1 through B2-4 (Figure 601).

NOTE: Removal of the ECS duct is required for easier access to borescope plug B2-4.

(a) Optional: B2-5 can be removed as an alternative to B2-4.

(b) Put labels on the borescope plugs that you removed.

SUBTASK 72-00-00-296-013-H00

(4) Use the borescope to examine all the surfaces of the combustion section (Figure 606) for the

conditions in Table 604:

Table 604/72-00-00-993-903-H00

INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS

Discoloration Permitted.

Carbon accumulation Permitted.

SUBTASK 72-00-00-296-014-H00

(5) Use the intrinsically safe borescope, COM-5661 to examine the combustion section surfaces

that follow:

NOTE: This inspection applies to PRE LEC and LEC Combustor configurations unless

specified otherwise.

DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840

NOTE: The combustor configuration without the LEC has the dome slave. The Inner and

Outer Liner do not have dilution holes in Panel No 2.



72-00-00

Page 610


EFFECTIVITYDHI ALL

For Training Only


DHI ALL POST SB CF6-80C2-72-0789 OR POST SB CF6-80C2-72-0840

NOTE: The LEC combustor configuration does not have the dome slave. The Inner and Outer

Liner have dilution holes in Panel No 2.

DHI ALL

(a) Splash plate

Table 605/72-00-00-993-904-H00

INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS

Discoloration Permitted.

Carbon Accumulation Permitted.

Missing, chipped or spalled areas of

the thermal barrier coating

Permitted.

Distortion Permitted.

Splash plate radial cracks The radial cracks less than 0.60 in. (15.24 mm) in length are permitted.

Radial cracks that extend from missing parent material less than 0.60 in.

(15.24 mm) in length are permitted.

Radial cracks more than 0.60 in. (15.24 mm) in length are not permitted.

Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00)

Splash plate circumferential cracks Circumferential cracks less than 0.60 in. (15.24 mm) in length are permitted.

Circumferential cracks that extend from missing parent material less than 0.60 in.

(15.24 mm) in length are permitted.

Circumferential cracks more than 0.60 in. (15.24 mm) in length are not permitted.

Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00).

Splash plate connected cracks Radial cracks can be connected to circumferential cracks with these conditions:

1. The radial crack is less than 0.60 in. (15.24 mm) in length.

2. The circumferential crack is less than 0.60 in. (15.24 mm) in length.



Splash plate missing material *[1] Missing material is permitted on the splash plates as follow:

(a) The missing material is not more than 10% per splash plate or the dome plate

cooling holes that are exposed are not more than 15. The 10% missing material is

equivalent to 0.5 square inch (323 square mm).

(b) The missing material is not more than 15% to maximum of seven splash plates

or the dome plate cooling holes that are exposed are not more than 20 to

maximum of seven splash plates. The 15% missing material is equivalent to 0.8

square inch 516 square mm).

Missing material is permitted with the inspection interval reduced to 150 cycles as

follow:

(a) The missing material is not more than 15% per splash plates or the dome plate

cooling holes that are exposed are not more than 20 per splash plate. The 15%

missing material is equivalent to 0.8 square inch 516 square mm).

(b) Missing material more than 10% for the splash plates located at positions 15,

16 and igniters cups located at positions 9 and 13 is not permitted.

All missing material more than 15% or more than 20 dome plate cooling holes

exposed on each splash plate are not permitted.




72-00-00

Page 611


EFFECTIVITYDHI ALL

For Training Only


DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840 (Continued)


INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS


Splash plate missing material *[1] Missing material is permitted on the splash plates as follow:

(a) The missing material is not more than 10% per splash plate or the dome plate

cooling holes that are exposed are not more than 40. The 10% missing material is

equivalent to 0.5 square inch (323 square mm).

(b) The missing material is not more than 15% to maximum of seven splash plates

or the dome plate cooling holes that are exposed are not more than 60 to

maximum of seven splash plates. The 15% missing material is equivalent to 0.8

square inch 516 square mm).

Missing material is permitted with the inspection interval reduced to 300 cycles as

follow:

(a) The missing material is not more than 15% per splash plates or the dome plate

cooling holes that are exposed are not more than 60 per splash plate. The 15%

missing material is equivalent to 0.8 square inch 516 square mm).

(b) The missing material is not more than 20% to maximum of five splash plates or

the dome plate cooling holes that are exposed are not more than 80 to the

maximum of five splash plates. The 20% missing material is equivalent to 1.10

square inches (710 square mm).

(c) Missing material more than 10% for the splash plates located at positions 15,

16 and igniters cups located at positions 9 and 13 is not permitted.

More than five splash plates with missing material greater than 15% or above 60

exposed dome plate cooling holes are not permitted.

Splash plates with missing material greater than 20% or above 80 exposed dome

plate cooling holes per splash plate are not permitted.


Splash plate flare burn through Permitted with the inspection interval reduced to 150 cycles as follow:

(a) The total splash plate quantity with flare burn through must not be more than

five.

(b) The maximum circumferential occurrence can be up to 90 deg. arc and up to

0.04 inch (1 mm) width.

(c) There are no flare burn thru on the splash plates located at positions 15, 16

and igniters cups located at positions 9, 13.

More than five splash plates with flare burn thru up to 90 deg. arc & up to 0.04

inch width is not permitted.

Splash plates with a burn thru greater than a 90 deg. arc and greater than 0.04

inch (1 mm) width is not permitted.


DHI ALL

Missing splash plate Not permitted.

Remove the engine if there is damage that is more than the limit.

*[1] Missing material limits for the splash plates are based on the number of exposed cooling holes. As the splash plate

material erodes away, the cooling holes in the dome plate are exposed.

(b) Dome plate and, if visible, the dome plate cooling holes


Discoloration Any amount permitted



72-00-00

Page 612


EFFECTIVITYDHI ALL

For Training Only


(Continued)


Carbon accumulation Any amount permitted

Missing, chipped or spalled areas of the thermal barrier

coating

Any amount permitted

Dome plate radial cracks in the cooling holes area Any amount permitted if they do not connect with other

cracks.

Refer to the Continue-In-Service Limits

(TASK 72-00-00-206-167-H00).

Inner and outer region of dome plate radial cracks Any amount permitted if they do not connect with other

cracks.


(TASK 72-00-00-206-167-H00).

Dome plate circumferential cracks in the cooling holes area Any amount permitted if less than 0.50 in. (12.7 mm) in

length. Up to two cracks permitted if they are less than 1 in.

(25.4 mm) in length and there is 2.5 in. (63.50 mm) or more

between the cracks.


(TASK 72-00-00-206-167-H00).

Inner and outer region of dome plate circumferential

cracks

Any amount permitted if less than 0.50 in. (12.7 mm) in

length. Up to two cracks permitted if they are less than 1 in.

(25.4 mm) in length and there is 2.5 in. (63.50 mm) or more

between the cracks.


(TASK 72-00-00-206-167-H00).

Missing metal (overhangs) Five damaged areas are permitted on each dome plate

overhang, if less than 0.50 in. (12.7 mm) in radial depth and

1 in. (25.4 mm) in circumferential length.


(TASK 72-00-00-206-167-H00).

Burn through holes in the dome plate Any amount of burn through areas if the total area is not

more than 0.40 in2 (258.06 mm2) and no single burn

through area is more than 0.20 in2 (129.03 mm2).


(TASK 72-00-00-206-167-H00).

Inner and outer band cracks Not permitted.


(TASK 72-00-00-206-167-H00).


(c) Dome sleeve


Discoloration Permitted

Carbon accumulation Permitted

Distortion Permitted

DHI ALL



72-00-00

Page 613


EFFECTIVITYDHI ALL

For Training Only


SUBTASK 72-00-00-296-015-H00

(6) Use the borescope to examine the inner and outer liner panels of the combustor (Figure 606,

Figure 612 or Figure 613 or Figure 614 or Figure 615) for the conditions in Table 606:

NOTE: A closed or decreasing combustor liner overhang gap shortens the life span of the

combustor, leading to distortion, or burn through.

Table 606/72-00-00-993-905-H00


Axial cracks Any number of cracks less than one panel are permitted.

No more than 30 cracks of one panel length for each liner are permitted.

No more than seven cracks that extend across two panels for each liner are

permitted.

Any two panel cracks must have a borescope inspection every 200 cycles to

make sure the cracks do not increase.

Cracks more than two panels are not permitted.

Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).

Circumferential cracks Circumferential cracks between two dilution holes not more than three in any

one panel.

Any cracks must be separated by a minimum of three non (circumferential or

axial) cracked dilution holes.

Circumferential cracks in non-dilution hole panels not more than two in any

one panel.

Any cracks must not be more than 2.5 inches (63.50 mm) in length separated

by a minimum of 5 inches (127 mm) of non cracked material (circumferential or

axial cracks).



Connected cracks Not permitted.



Connected cracks 1. Connected cracks between dilution holes (Y-type) area permitted with these

conditions:

a) Connected cracks are located on Inner Liner Panel No. 2.

b) Individual cracks length must be within “Axial cracks” and “Circumferential

cracks” limits.

c) There are not more than three locations with connected cracks in panel No.

2.

d) Connected cracks must have a separation of a minimum of 2 dilution lands

that are not damaged.

2. Any other liner panels connected cracks are not permitted.


DHI ALL

Random, multiple cracks from dilution

hole or burned area

Not thought to be interconnected cracks. Any amount is serviceable if you refer

to axial and circumferential cracks for individual crack length.

Total accumulative crack length for multiple crack condition is 2.5 inches (64

mm).




72-00-00

Page 614


EFFECTIVITYDHI ALL

For Training Only




Inner liner holes that are burned through

or missing material *[1] *[2]Holes that are burned through or missing material is permitted on the inner

liner as follows:

a) There are no holes that are burned through or missing material on the Inner

Liner Panel No. 1.

b) There are not more than two holes in the adjacent panels at the same

o’clock position.

c) Holes must have a separation of a minimum of 2 dilution lands that are not

damaged or 3 in. (76.2 mm) circumferential direction on panels with no dilution

holes.

d) The maximum size of any hole is not more than 0.4 sq in (258 sq mm).

e) The total area of burn through is not more than 1.25 sq in (806.5 sq mm).

Holes that are burned through or missing material is permitted with the

inspection interval reduced to 150 cycles as follows:

a) There are no holes that are burned through or missing material on the Inner

Liner Panel No. 1.


o’clock position.

c) Holes must have a separation of a minimum of 2 dilution lands that are not

damaged or 3 in. (76.2 mm) circumferential direction on panels with no dilution

holes.

d) The maximum size of any hole is not more than 0.6 sq in (387 sq mm).

e) The total area of burn through is not more than 1.25 sq in (806.5 sq mm).

If the current condition is more than the above limits, the inner liner is not

serviceable.


Outer liner holes that are burned through

or missing material *[3], *[4]Holes that are burned through or missing material is permitted on the outer

liner as follow:

a) There are no holes that are burned through or missing material on the Outer

Liner Panel No. 1.


o’clock position.

c) Holes must have a separation of a minimum 3 dilution lands that are not

damaged or 5 inch (127 mm) circumferential direction on panels with no

dilution holes.

d) The maximum size of any hole is not more than 0.3 sq. inch (193.5 sq mm).

e) The total area of burn through is not more than 0.6 sq. inch (387 sq.mm).

If the current condition is more than the above limits, the outer liner is not

serviceable.


Metal that is gone from the liner

overhang

Up to fourteen damaged areas, 0.50 inch (12.70 mm) circumferential length by

0.1 inch (2.54 mm) axial length are permitted on each combustor assembly.

Three adjacent damaged panels are not permitted.


Distortion Permitted if not more than 0.5 inch (12.70 mm) from original contour.




72-00-00

Page 615


EFFECTIVITYDHI ALL

For Training Only




Decrease in the inner and the outer

combustor liner overhang gap

Permitted.

A closed or decreasing combustor liner overhang gap shortens the life span of

the combustor, leading to distortion, or burn through.

*[1] If a dilution hole is contained in the damaged area, include the dilution hole in the area created.

*[2] It is recommended at first report of inner liner burn through to do a borescope inspection of the Stage 1 high pressure

turbine nozzle.

*[3] If there is a dilution hole in the damaged area, include the dilution hole in the area created.

*[4] It is recommended at report of outer liner burn through to do a borescope inspection of the Stage 1 high pressure

turbine nozzle.

SUBTASK 72-00-00-296-016-H00

(7) Use the borescope to examine the Igniter Tube and Igniter Ferrule for the conditions in

Table 607 and Figure 606.

Table 607/72-00-00-993-906-H00


Cracks in weld on igniter tube One for each tube, up to one third of the circumference of the tube.


Cracks on igniter tube Permitted.

Metal that is gone from the igniter tube Missing material of any amount in both igniter tubes are not permitted.

If metal is gone from one igniter tube, perform the following:

1. Make sure that the inspection limits for secondary damage are met and

you do not find residual material in these locations:

a. The Combustor

b. The High Pressure Turbine

c. The Low Pressure Turbine.

2. Engine can be operated per 767 MMEL allowances if the ignition system at

the location of the missing metal from the igniter tube is considered to be

non-operational and the engine can be started using the ignition system for

the other channel using Engine Start Procedure.

Remove the engine if damage is more than the limit.

Burns in the igniter ferrule Burns in both igniter ferrules are not permitted.

Burns in one igniter ferrule are permitted as follows:

1) Engine can be operated per 767 MMEL allowances if the ignition system at

the location of the burns in the igniter ferrule is considered to be

non-operational and the engine can be started using the ignition system for

the other channel using Engine Start Procedure.




72-00-00

Page 616


EFFECTIVITYDHI ALL

For Training Only




Missing igniter ferrule Two ferrules missing. Not permitted.

If one ferrule is missing, do the steps that follow:

1. Make sure that the inspection limits for secondary damage are met and

you do not find residual material in these locations:

a. The Combustor

b. The High Pressure Turbine

c. The Low Pressure Turbine.

2. Engine can be operated per 767 MMEL allowances if the ignition system at

the location of the missing ferrule is considered to be non-operational and the

engine can be started using the ignition system for the other channel using

Engine Start Procedure.


SUBTASK 72-00-00-296-017-H00

(8) Use the borescope to examine the fuel nozzle for this condition (Figure 606):

(a) Carbon on fuel nozzle

1) Permitted

SUBTASK 72-00-00-296-254-H00

(9) Use the borescope to examine the combustor cowl for the conditions in Table 608 and

Figure 606:

Table 608/72-00-00-993-907-H00


Burns Not permitted.

Examine the fuel nozzles (TASK 73-11-05-206-001-H00).

Cracks Permitted, if less than 0.25 inch (6.35 mm) long.

Remove the engine if more than the limit.

SUBTASK 72-00-00-416-018-H00

(10) If it is necessary, do the steps that follow to install borescope plugs B2-1 through B2-4

(Figure 601):

NOTE: If you will do the borescope inspection (high pressure turbine) that follows at this time,

do not install the borescope plugs. The same borescope ports are used for the

combustion section and the high pressure turbine.

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.

(a) Apply a light layer of the Never-Seez NSBT compound, D00006 on the threads and the

pressure faces of the plugs.

(b) Use a torque wrench, STD-12814 to tighten the plugs to the torque values shown in

Figure 601.

1) Install lockwire.



72-00-00

Page 617


EFFECTIVITYDHI ALL

For Training Only


FWD

5006104-00

CIRCUMFERENTIAL

RADIAL

AXIAL

2297491 S0000520867_V1

Combustion Chamber Assembly Inspection DefinitionFigure 605/72-00-00-990-885-H00



72-00-00

Page 648


EFFECTIVITYDHI ALL

For Training Only


SEE A

CF8-B3622-01-A

IGNITER

TUBE

FUEL

NOZZLE

IGNITER

FERRULE

OUTER LINER SUPPORT

AFT RING

SEAL

SURFACE

BORE

(PRIMARY

SWIRLER)

OUTER LINEROUTER COWL

INNER LINER

AFT RINGDOME PLATE

DOME SLEEVE

SPLASH PLATE

OVERHANG

SECONDARY

SWIRLER

PANEL OVERHANG

HEIGHT

OUTER COMBUSTOR

LINER OVERHANG GAP

INNER COMBUSTOR

LINER OVERHANG GAP

INNER LINER

SUPPORT

PRIMARY

SWIRLER

INNER

COWL

BOLT

IGNITER

243636 S00061426306_V1

Combustion Chamber Assembly InspectionFigure 606/72-00-00-990-809-H00 (Sheet 1 of 2)



72-00-00

Page 649


EFFECTIVITYDHI ALL

For Training Only


FWD

A A

A

FERRULE

RETAINER

IGNITER TUBE

OUTER LINER

RETAINER

1289888-00

A-A

1950775 S00061426307_V1

Combustion Chamber Assembly InspectionFigure 606/72-00-00-990-809-H00 (Sheet 2 of 2)



72-00-00

Page 650


EFFECTIVITYDHI ALL

For Training Only


1289883-00

DOME SLEEVE

SPLASH PLATE

DOME PLATE

DIMPLE BAND

OUTER BAND

INNER BAND

DOME PLATE

DOME SLEEVE

SPLASH PLATE

OUTER BAND

243638 S00061426308_V1

Combustion Dome and Splash Plate InspectionFigure 607/72-00-00-990-873-H00



72-00-00

Page 651


EFFECTIVITYDHI ALL

For Training Only


1361513-00

4

130

27

19

24

16 15

13

9

IGNITER

PLUG

IGNITER

PLUG

B2-2

B2-3

B2-5 B2-1

B2-4

ECS

(VIEW IN THE FORWARD DIRECTION)

2158964 S0000474048_V1

Combustion Section Splash Plate InspectionFigure 608/72-00-00-990-877-H00



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EFFECTIVITYDHI ALL

For Training Only


CIRCUMFERENTIAL

DIRECTION

5006106-00

SPLASH PLATE

RADIAL CRACKS

SPLASH PLATE

CIRCUMFERENTIAL CRACKS

RADIAL

DIRECTION

SPLASH PLATE

CIRCUMFERENTIAL CRACK

EXTEND FROM A MISSING

PARENT MATERIAL

SPLASH PLATE

CIRCUMFERENTIAL

CRACKS

SPLASH PLATE


EXTEND FROM A MISSING

PARENT MATERIAL SPLASH PLATE

CRACK EXTEND FROM A

MISSING PARENT MATERIAL

SPLASH PLATE

MISSING MATERIAL

SPLASH PLATE

MISSING MATERIAL

SPLASH PLATE


CONNECTED WITH RADIAL

2297522 S0000520877_V1

Combustion Dome Splash Plate Cracks InspectionFigure 609/72-00-00-990-886-H00



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EFFECTIVITYDHI ALL

For Training Only


1

2

1

2

1361514-00

THIS SPLASH PLATE HAS NO MISSING MATERIAL AND NO DOME PLATE COOLING HOLES

ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.

THIS SPLASH PLATE HAS 5% MISSING MATERIAL AND 7 DOME PLATE COOLING HOLES

ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.2158971 S0000474062_V1

Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 1 of 7)



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EFFECTIVITYDHI ALL

For Training Only


3

4

3

4

1361517-00




ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL IF

MAXIMUM OF 7 SPLASH PLATES IS AFFECTED. THE INSPECTION INTERVAL IS REDUCED

TO 150 CYCLES IF MORE THAN 7 SPLASH PLATES ARE AFFECTED.

DOME PLATE COOLING HOLES

ARE VISIBLE AFTER SPLASH

PLATE MISSING MATERIAL

OCCURS

2158972 S0000474071_V1




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EFFECTIVITYDHI ALL

For Training Only


5

6

5 6

1361518-00

SPLASH PLATE HAS NO MISSING MATERIAL AND 32 DOME PLATE COOLING HOLES ARE

EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.


ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL IF

MAXIMUM OF 7 SPLASH PLATES IS AFFECTED. THE INSPECTION INTERVAL IS REDUCED

TO 300 CYCLES IF MORE THAN 7 SPLASH PLATES ARE AFFECTED.

32 DOME PLATE COOLING HOLES

VISIBLE WITH NO SPLASH PLATE

DISTRESS

SPLASH

PLATE

SPLASH PLATE

WITH NO DISTRESS

DOME PLATE COOLING HOLES

ARE VISIBLE AFTER SPLASH

PLATE MISSING MATERIAL

OCCURS

2158975 S0000474074_V1




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EFFECTIVITYDHI ALL

For Training Only


7

8

7 8

1361519-00

THE SPLASH PLATE HAS 10% MISSING MATERIAL AND 40 DOME PLATE COOLING HOLES



ARE EXPOSED. THE INSPECTION INTERVAL IS REDUCED TO 300 CYCLES IF MAXIMUM OF 5

SPLASH PLATES IS AFFECTED. THIS CONDITION IS NOT SERVICEABLE IF MORE THAN 5

SPLASH PLATES ARE AFFECTED.2158987 S0000474079_V1




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EFFECTIVITYDHI ALL

For Training Only


9

10

9 10

1361523-00

SPLASH PLATE HAS VISIBLE FLARE BURN THRU 100 DEGREE. ARC AND UP TO 0.06 INCH

WIDTH. THIS IS NOT SERVICEABLE AND THE ENGINE MUST BE REMOVED WITHIN 25 CYCLES.

SPLASH PLATE HAS VISIBLE FLARE BURN THRU 45 DEGREE. ARC AND UP TO 0.04 INCH

WIDTH. THE INSPECTION INTERVAL IS REDUCED TO 150 CYCLES IF MAXIMUM OF 5 SPLASH

PLATES IS AFFECTED.2158989 S0000474081_V1




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EFFECTIVITYDHI ALL

For Training Only


11

12

11 12

1361525-00

THIS SPLASH PLATE HAS 7% MISSING MATERIAL AND 40 DOME PLATE COOLING HOLES ARE

EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.


ARE EXPOSED. THIS CONDITION IS NOT SERVICEABLE AND THE ENGINE MUST BE REMOVED

WITHIN 25 CYCLES.2158994 S0000474082_V1




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EFFECTIVITYDHI ALL

For Training Only


13

14

13 14

1361529-00

THE DOME PLATE HAS A CIRCUMFERENTIAL CRACK THAT CONNECTS 4 DOME PLATE COOLING

HOLES AND IT IS SERVICEABLE. THE RADIAL CRACK CONNECTS 5 DOME PLATE COOLING HOLES

AND IT IS SERVICEABLE.

THE DOME PLATE HAS A CIRCUMFERENTIAL CRACK THAT CONNECTS WITH RADIAL CRACK. THIS

CONDITION IS NOT SERVICEABLE AND THE ENGINE MUST BE REMOVED WITHIN 25 CYCLES.

CIRCUMFERENTIAL

CRACK CONNECTS

WITH RADIAL CRACK

DOME PLATE COOLING

HOLES ARE VISIBLE

AFTER SPLASH PLATE

MATERIAL OCCURS

RADIAL CRACK

CIRCUMFERENTIAL

CRACK

CIRCUMFERENTIAL

DIRECTION

RADIAL

DIRECTION

2159000 S0000474084_V1




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EFFECTIVITYDHI ALL

For Training Only


INNER AND OUTER

REGION OF DOME

PLATE

MISSING METAL

(OVERHANGS)

INNER AND OUTER

REGION OF DOME

PLATE RADIAL CRACKSINNER AND OUTER

REGION OF DOME PLATE

CIRCUMFERENTIAL

CRACKS

BURN-THROUGH

HOLES IN THE

DOME PLATE

5021748-00

1950777 S00061426312_V4

Combustion Splash Plate Cracks, Missing Metal Caused by Cracking and Fragmenting InspectionFigure 611/72-00-00-990-811-H00



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EFFECTIVITYDHI ALL

For Training Only


FWD

PA

NE

L1

PA

NE

L2

PA

NE

L3

PA

NE

L4

PA

NE

L5

PA

NE

L6

DILUTION

HOLES

AXIAL CRACK

EXTENDING FROM

ONE PANEL INTO

ADJACENT PANEL

(TWO PANEL CRACK)

AXIAL CRACK

ACROSS ONE PANEL

(ONE PANEL CRACK)

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

IF A DILUTION HOLE IS

CONTAINED IN THE DAMAGED

AREA, INCLUDE THE DILUTION

HOLE IN THE AREA CREATEDTYPICAL

AXIAL

CRACK

2259377 S0000506498_V2

Outer Liner Inspection (for the Pre Low Emission Combustors (Pre LEC))Figure 612/72-00-00-990-881-H00



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EFFECTIVITYDHI ALL

For Training Only


FWD

PA

NE

L1

PA

NE

L2

PA

NE

L3

PA

NE

L4

PA

NE

L5

PA

NE

L6

MULTIPLE CRACKS

FROM DILUTION HOLE

CONNECTED CRACKS

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL




HOLE IN THE AREA CREATED

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

DECREASE IN THE

INNER LINER

OVERHANG GAP

DILUTION HOLES

TYPICAL AXIAL

CRACK

AXIAL CRACK EXTENDING

FROM ONE PANEL INTO

ADJACENT PANEL

(TWO PANEL CRACK)

CIRCUMFERENTIAL

CRACK

2259378 S0000506500_V1

Inner Liner Inspection (for the Pre Low Emission Combustors (Pre LEC))Figure 613/72-00-00-990-882-H00



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EFFECTIVITYDHI ALL

For Training Only


FWD

PA

NE

L1

PA

NE

L2

PA

NE

L3

PA

NE

L4

PA

NE

L5

PA

NE

L6

TYPICAL

AXIAL

CRACK

AXIAL CRACK

EXTENDING FROM

ONE PANEL INTO

ADJACENT PANEL

(TWO PANEL CRACK)

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL




HOLE IN THE AREA CREATED

DILUTION

HOLES

AXIAL CRACK

ACROSS ONE PANEL

(ONE PANEL CRACK)

AXIAL CRACK

EXTENDING FROM

ONE PANEL INTO

ADJACENT PANELS

(THREE PANEL CRACK)

2259380 S0000506503_V2

Outer Liner Inspection (for the Low Emission Combustors (LEC))Figure 614/72-00-00-990-883-H00



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EFFECTIVITYDHI ALL

For Training Only


FWD

5054889-00

PA

NE

L1

PA

NE

L2

PA

NE

L3

PA

NE

L4

PA

NE

L5

PA

NE

L6

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

MULTIPLE CRACKS

FROM DILUTION

HOLE

TYPICAL AXIAL CRACK

DILUTION HOLES

AXIAL CRACK EXTENDING

FROM ONE PANEL INTO

ADJACENT PANEL

(TWO PANEL CRACK)

CONNECTED CRACKS

BETWEEN DILUTION

HOLES (Y - TYPE)

CIRCUMFERENTIAL

CRACK

CONNECTED

CRACKS


CONTAINED IN THE

DAMAGED AREA,

INCLUDE THE DILUTION

HOLE IN THE AREA

CREATED

HOLES THAT ARE

BURNED THROUGH OR

MISSING MATERIAL

DECREASE IN THE

INNER LINER

OVERHANG GAP

2259382 S0000506505_V2

Inner Liner Inspection (for the Low Emission Combustors (LEC))Figure 615/72-00-00-990-884-H00



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EFFECTIVITYDHI ALL

For Training Only


SUBTASK 72-00-00-416-021-H00

(11) If you only do the combustion section inspection, do these steps:

WARNING

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO CLOSE THE

THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS,

INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(a) Close the thrust reversers (TASK 78-31-00-402-084-H00).

(b) Close the fan cowl panels (TASK 71-11-04-712-012-H00).

H. Borescope Inspection of the High Pressure Turbine

SUBTASK 72-00-00-986-022-H00

(1) Do the steps to manually or pneumatically turn the N2 rotor at the accessory gearbox

(TASK 72-00-00-982-007-H00 or TASK 72-00-00-982-024-H00).

NOTE: The engine manufacturer recommends to turn the N2 rotor, then stop to examine the

blade with a borescope. After you examine the condition of the blade, turn the N2 rotor,

then stop again to examine the next blade.

SUBTASK 72-00-00-266-195-H00

CAUTION

BEFORE YOU USE THE BORESCOPE, MAKE SURE THAT THE

TEMPERATURES OF THE INSPECTION AREAS ARE BELOW 150°F (66°C). IF

THE ADJACENT CASES ARE TOO HOT TO KEEP YOUR HAND ON, THE

INSPECTION AREAS ARE TOO HOT. IF THE INSPECTION AREA IS TOO HOT,

DAMAGE TO THE BORESCOPE CAN OCCUR.

CAUTION



LOCATION.

(2) Remove the borescope plugs B2-1 through B2-5 (Figure 601) to examine the 1st-stage nozzle

vanes.

(a) Remove the ECS duct to get easier access to borescope plug B2-4.

NOTE: This step is optional.

SUBTASK 72-00-00-266-196-H00

CAUTION

MAKE SURE COMPONENTS OF THE BORE SCOPE PLUG ASSEMBLY ARE

IN GOOD CONDITION. THE PLUG TIP AND SPRING CAN FALL INTO THE

ENGINE IF TACK WELDS ON THE PLUG TIP (UNDER WASHER) CRACK AND

SEPARATE.

(3) Remove borescope plugs B3-1 and B3-2 to examine the 1st and the 2nd-stage rotors

(Figure 601).

(a) Ports B3-1 and B3-2 are used to examine the 1st and the 2nd-stage rotors and shrouds,

and the 2nd-stage nozzle.

NOTE: You may see wear and dents on the B3-1 borescope plug sleeve. This is

permitted if the damage is not through the sleeve and you can install the plug

without difficulty.

SUBTASK 72-00-00-866-127-H00

(4) Put labels on all the borescope plugs that have been removed.



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EFFECTIVITYDHI ALL

For Training Only


SUBTASK 72-00-00-296-024-H00

(5) Use the borescope to examine the leading edge of the vane airfoils on the 1st-stage HPT

nozzle (Figure 616 and Figure 617) for the conditions in Table 609:

Table 609/72-00-00-993-908-H00

Condition Maximum Serviceable Limit

Cracks that connect the nose holes Permitted.

Cracks that connect the nose holes and

extend into the concave and/or convex

surface

Permitted, if the crack does not extend past the 6th film row of cooling holes

on the concave side and does not extend past the 2nd film row of cooling

holes on the convex side, with no material gone.


Cracks that go out from the nose holes, but

not attached to other nose holes

Permitted.

Burns or erosion not fully through the metal Permitted.

Material that has gone fully through the

metal

Permitted, not more than 0.3 square inch (194 square mm) for each vane. A

maximum of four damaged vane in a 90 degree arc.


SUBTASK 72-00-00-296-025-H00

(6) Use the borescope to examine the concave surface of the vane airfoils on the 1st-stage HPT

nozzle (Figure 616) for the conditions in Table 610:

Table 610/72-00-00-993-909-H00


Radial cracks out of the film holes Permitted.

Other cracks, not in the film hole rows Permitted.

Burns, spalls or erosion (no holes through

the base metal)

Permitted.

Missing material (through the base metal) Permitted, if the total damage is not more than 0.1 square inch (64.5

square mm) for each vane.


Radially oriented cracks in the fillet area

adjacent to the inner and the outer platforms

Permitted.

SUBTASK 72-00-00-296-026-H00

(7) Use the borescope to examine the convex surface of the vane airfoil on the 1st-stage HPT

nozzle (Figure 616) for the conditions in Table 611:

Table 611/72-00-00-993-910-H00


Radial cracks where material is not lifted All of these cracks are permitted, if no material is gone.


Radial cracks where material is lifted one

side of the crack in relation to the other side

Permitted, if the material is lifted less than the thickness of the airfoil wall

and no material is gone.




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EFFECTIVITYDHI ALL

For Training Only




Axial cracks All of these cracks are permitted, if no material is gone. Also, see limits for

leading edge cracks.


Burns or erosion Permitted, with no maximum limit, if no material is gone, and the burns are

not fully through the metal.


Cracks in the fillet area that is adjacent to the

inner and the outer platforms

All of these cracks are permitted, if there is no sign of material that is gone.


SUBTASK 72-00-00-296-027-H00

(8) Use the borescope to examine the trailing edge of the vane airfoil on the 1st-stage HPT nozzle

(Figure 616) for the conditions in Table 612:

Table 612/72-00-00-993-911-H00


Axial cracks that start at the slots

adjacent to the trailing edge

All of these cracks are permitted.

Buckling or bowing Permitted.

Material that is gone The total area of material that is gone must not be more than 6.0 square inches

(39 square cm.) on each assembly. Each airfoil can have 1.5 square inches (10

square cm.) of material that is gone.


SUBTASK 72-00-00-296-028-H00

(9) Use the borescope to examine all the areas of the vane airfoil on the 1st-stage HPT nozzle for

the conditions in Table 613:

Table 613/72-00-00-993-912-H00


Craze cracks *[1] Permitted.

Nicks, scores, scratches and dents Permitted.

Metal splatter Permitted.

*[1] Craze cracks are surface cracks that do not do all the way through the coating.

SUBTASK 72-00-00-296-029-H00

(10) Use the borescope to examine the inner and the outer platform on the 1st-stage HPT nozzle

for the conditions in Table 614:

Table 614/72-00-00-993-913-H00


Cracks in the parent metal This type of damage is permitted without a quantity limit.

See limit for missing material.

Nicks, scores, scratches and dents All of this type of damage is permitted without a quantity limit.



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EFFECTIVITYDHI ALL

For Training Only




Burns or erosion Any quantity of material may be burnt or missing if it has not gone all the

way through the platform.

See limit for missing mate

B767 CF6-80C Borescope Recurrent Training 2020cbt.altitudeglobal.aero/Files/B767 CF6...

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