B767 CF6-80C Borescope Recurrent Training 2020cbt.altitudeglobal.aero/Files/B767 CF6...
Transcript of B767 CF6-80C Borescope Recurrent Training 2020cbt.altitudeglobal.aero/Files/B767 CF6...
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FOR REFERENCE ONLY
B767 CF6-80C Borescope Recurrent Training 2020
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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/
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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.
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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)
Stages Condition Notes* Maximum Serviceable Limit
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]
Not permitted. Replace the engine.
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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Table 601/72-00-00-993-898-H00 (Continued)
Stages Condition Notes* Maximum Serviceable Limit
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).
You must do a borescope inspection of the HPC
blade stages aft (downstream) of the blade that
has a missing tip corner.
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
Not permitted. Replace the engine.
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).
You must do a borescope inspection of the HPC
blade stages aft (downstream) of the blade that
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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Table 601/72-00-00-993-898-H00 (Continued)
Stages Condition Notes* Maximum Serviceable Limit
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).
You must do a borescope inspection of the HPC
blade stages aft (downstream) of the blade that
has a missing tip corner.
CF6-80C ENGINES PRE GE SB 72-0975 AND/OR POST SB 72-1060
3,4,5 Nicks, dents and missing
material on the leading
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
3,4,5 Nicks, dents and missing
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).
3,4,5 Nicks, dents and missing
material in area Y on the
leading and trailing
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
material on the leading
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
material on the leading
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
leading and trailing
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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Table 601/72-00-00-993-898-H00 (Continued)
Stages Condition Notes* Maximum Serviceable Limit
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
material on the leading
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
Stages Condition Notes* Maximum Serviceable Limit
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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CF6-80C SERIES ENGINES
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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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Engine Borescope Port LocationsFigure 601/72-00-00-990-803-H00 (Sheet 2 of 3)
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CF6-80C SERIES ENGINES
72-00-00
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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
Engine Borescope Port LocationsFigure 601/72-00-00-990-803-H00 (Sheet 3 of 3)
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CF6-80C SERIES ENGINES
72-00-00
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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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Compressor Rotor Blades InspectionFigure 602/72-00-00-990-806-H00 (Sheet 2 of 5)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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B
1300487-00
UNEVEN TIP
SPACING
KINK IN BLADE EDGE
2028818 S00061426298_V1
Compressor Rotor Blades InspectionFigure 602/72-00-00-990-806-H00 (Sheet 3 of 5)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Compressor Rotor Blades InspectionFigure 602/72-00-00-990-806-H00 (Sheet 4 of 5)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Compressor Rotor Blades InspectionFigure 602/72-00-00-990-806-H00 (Sheet 5 of 5)
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CF6-80C SERIES ENGINES
72-00-00
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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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Mid-Span Shroud Inspection of the 1st-Stage BladesFigure 603/72-00-00-990-807-H00 (Sheet 2 of 4)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Mid-Span Shroud Inspection of the 1st-Stage BladesFigure 603/72-00-00-990-807-H00 (Sheet 3 of 4)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
Mid-Span Shroud Inspection of the 1st-Stage BladesFigure 603/72-00-00-990-807-H00 (Sheet 4 of 4)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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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
PUT A LABEL ON THE BORESCOPE PLUGS. ENGINE DAMAGE CAN OCCUR
IF THE BORESCOPE PLUGS ARE NOT INSTALLED IN THE CORRECT
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.
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CF6-80C SERIES ENGINES
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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.
Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00).
DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840
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.
Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00).
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840 (Continued)
Table 605/72-00-00-993-904-H00 (Continued)
INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS
DHI ALL POST SB CF6-80C2-72-0789 OR POST SB CF6-80C2-72-0840
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.
Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00).
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.
Refer to the Continue-In-Operation limits (TASK 72-00-00-206-167-H00).
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
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
Discoloration Any amount permitted
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
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(Continued)
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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.
Refer to the Continue-In-Service Limits
(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.
Refer to the Continue-In-Service Limits
(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.
Refer to the Continue-In-Service Limits
(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.
Refer to the Continue-In-Service Limits
(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).
Refer to the Continue-In-Service Limits
(TASK 72-00-00-206-167-H00).
Inner and outer band cracks Not permitted.
Refer to the Continue-In-Service Limits
(TASK 72-00-00-206-167-H00).
DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840
(c) Dome sleeve
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
Discoloration Permitted
Carbon accumulation Permitted
Distortion Permitted
DHI ALL
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
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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
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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).
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
DHI ALL PRE SB CF6-80C2-72-0789 AND PRE SB CF6-80C2-72-0840
Connected cracks Not permitted.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
DHI ALL POST SB CF6-80C2-72-0789 OR POST SB CF6-80C2-72-0840
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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).
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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-
Table 606/72-00-00-993-905-H00 (Continued)
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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.
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 0.6 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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
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 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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
Distortion Permitted if not more than 0.5 inch (12.70 mm) from original contour.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 615
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-
Table 606/72-00-00-993-905-H00 (Continued)
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
Cracks in weld on igniter tube One for each tube, up to one third of the circumference of the tube.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
Remove the engine if damage is more than the limit.
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
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-
Table 607/72-00-00-993-906-H00 (Continued)
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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.
Remove the engine if damage is more than the limit.
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
INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS
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.
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 617
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EFFECTIVITYDHI ALL
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-
FWD
5006104-00
CIRCUMFERENTIAL
RADIAL
AXIAL
2297491 S0000520867_V1
Combustion Chamber Assembly Inspection DefinitionFigure 605/72-00-00-990-885-H00
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 648
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EFFECTIVITYDHI ALL
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-
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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 649
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-
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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 650
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EFFECTIVITYDHI ALL
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-
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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 651
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-
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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 652
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-
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
CIRCUMFERENTIAL CRACK
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
CIRCUMFERENTIAL CRACK
CONNECTED WITH RADIAL
2297522 S0000520877_V1
Combustion Dome Splash Plate Cracks InspectionFigure 609/72-00-00-990-886-H00
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 653
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-
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)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 654
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-
3
4
3
4
1361517-00
THIS SPLASH PLATE HAS 10% MISSING MATERIAL AND 15 DOME PLATE COOLING HOLES
ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.
THIS SPLASH PLATE HAS 15% MISSING MATERIAL AND 20 DOME PLATE COOLING HOLES
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
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 2 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 655
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-
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.
THIS SPLASH PLATE HAS 15% MISSING MATERIAL AND 60 DOME PLATE COOLING HOLES
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
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 3 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 656
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-
7
8
7 8
1361519-00
THE SPLASH PLATE HAS 10% MISSING MATERIAL AND 40 DOME PLATE COOLING HOLES
ARE EXPOSED. ENGINE MAINTAINS SCHEDULED BORESCOPE INSPECTION INTERVAL.
THIS SPLASH PLATE HAS 20% MISSING MATERIAL AND 80 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
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 4 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 657
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-
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
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 5 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 658
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-
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.
THIS SPLASH PLATE HAS 25% MISSING MATERIAL AND 95 DOME PLATE COOLING HOLES
ARE EXPOSED. THIS CONDITION IS NOT SERVICEABLE AND THE ENGINE MUST BE REMOVED
WITHIN 25 CYCLES.2158994 S0000474082_V1
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 6 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 659
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-
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
Combustion Dome Splash Plate Missing Material for the Pre Low Emission Combustor InspectionFigure 610/72-00-00-990-878-H00 (Sheet 7 of 7)
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 660
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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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 661
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-
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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 662
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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
IF A DILUTION HOLE IS
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
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
767AIRCRAFT MAINTENANCE MANUAL
CF6-80C SERIES ENGINES
72-00-00
Page 663
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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
IF A DILUTION HOLE IS
CONTAINED IN THE DAMAGED
AREA, INCLUDE THE DILUTION
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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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
IF A DILUTION HOLE IS
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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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
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 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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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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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
Condition Maximum Serviceable Limit
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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
Condition Maximum Serviceable Limit
Radial cracks where material is not lifted All of these cracks are permitted, if no material is gone.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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Table 611/72-00-00-993-910-H00 (Continued)
Condition Maximum Serviceable Limit
Axial cracks All of these cracks are permitted, if no material is gone. Also, see limits for
leading edge cracks.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
Burns or erosion Permitted, with no maximum limit, if no material is gone, and the burns are
not fully through the metal.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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
Condition Maximum Serviceable Limit
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.
Refer to the Continue-In-Operation Limits (TASK 72-00-00-206-167-H00).
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
Condition Maximum Serviceable Limit
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
Condition Maximum Serviceable Limit
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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Table 614/72-00-00-993-913-H00 (Continued)
Condition Maximum Serviceable Limit
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