* * * FOR ALL
TASK 72-22-40-200-801
1 . General.
A.This procedure gives instructions to do an inspection of the fan rotor disk (fan disk). Refer to Figure 801.
•
Fan disk (01-050 , 72-22-00) (SIN 830A0)
•
Fan disk (02-050 , 72-22-00) (SIN 830A0) (SB 72-0156).
B.Critical areas that have an effect on part life are the dovetail slots, webs, and bores.
C.There are two configurations for the fan disk. The difference is in the forward fan shaft mounting flange. The configuration 1 fan disk contains counterbores (spot faces) on the forward side of the flange. The configuration 2 fan disk does not contain counterbores (spot faces) on the forward side of the flange.
2 . Tools, Equipment, and Materials.
NOTE:
You can use equivalent alternatives for tools, equipment, and consumable materials.
A.Tools and Equipment.
(1)Special Tools. None.
(2)Standard Tools and Equipment.
 
Description
Manufacturer
 
Eddy Current Inspection Kit (GE-FQAP-428)
GE Aviation
Field Support Technology
One Neumann Way, MD: Q8
Cincinnati, Ohio 45215 USA
Email: ndttooling@ae.ge.com
Fax: (513) 552-1386
 
Sonic 1000 Series Ultrasonic Instrument
Olympus NDT Inc.
48 Woerd Avenue
Waltham, MA 02453
USA
 
USN Series Ultrasonic Instrument
GE Inspection Technologies
50 Industrial Park
Lewistown, PA 17044
USA
 
GE Aircraft Engines Inspection Kit (GE-FQAP-604) (probe)
GE Aircraft Engines
Engine Support Operations
1 Neumann Way
Cincinnati, OH 45215M/D H203
USA
 
Couplant - Glycerin or equivalent
(3)Locally Manufactured Tools.
 
Description
Figure
 
Dovetail Pressure Face Inspection Gage (Inspection Gage)
Figure 809
B.Consumable Materials. None.
C.Referenced Procedures.
 
ATA No.
Description
 
70-24-01
Swab Etching Procedure
 
70-32-02
Fluorescent Penetrant Inspection
 
70-32-06
Ultrasonic Inspection
 
70-32-10
2 MHz Eddy Current Inspection Of Bores In Inconel Alloy Rotating Engine Hardware Using Systems Under Computer, Numeric, Or Robotic Control
 
70-33-03
Special Inspection For Surface Fretting Or Galling
 
70-42-00
Blending And Removal Of High Metal Procedures
 
72-22-40
Cleaning 001
D.Expendable Parts. None.
3 . Specific Inspection Procedure.
NOTE:
Any findings beyond manual limits that may be indicative of a possible crack and/or metallurgical defect must be reported to GE through a myGEAviation Technical Inquiry.
Subtask 72-22-40-110-005
WARNING:
NEVER ADD WATER TO ACID. ADD ACID TO WATER WHILE YOU MIX THE SOLUTION. A DANGEROUS REACTION THAT WILL BURN YOU CAN OCCUR IF THE SOLUTION IS NOT MADE CORRECTLY.
A.Do a Class B etch of the pressure faces and bottoms of the slots of the dovetails. Refer to TASK 70-24-01-110-034 (SWAB ETCHING PROCEDURE) .
* * * FOR ALL
Figure 801   (Sheet 1 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 2 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 3 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 4 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 5 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 6 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 7 ) Fan Disk - Inspection
* * * FOR ALL
Figure 801   (Sheet 8 ) Fan Disk - Inspection
Subtask 72-22-40-230-001
B.Do a Class G fluorescent penetrant inspection of the fan disk. Refer to TASK 70-32-02-230-001 (FLUORESCENT PENETRANT INSPECTION). Use non-aqueous wet developer in the dovetail slots.
(1)Make sure that you do an inspection of the critical areas that follow:
•
Bores
•
Webs
•
Dovetail slots
•
Area B
•
Mounting flanges
•
Boltholes.
(2)Indications larger than 0.015 inch (0.38 mm) are not permitted.
Subtask 72-22-40-160-003
C.Do an eddy current inspection of the fan disk bore surfaces as follows:
CAUTION:
DO NOT USE METAL BRUSHES TO CLEAN THE FAN DISK BORES. METAL BRUSHES CAN CAUSE SCRATCHES. SCRATCHES CAN CAUSE THE BORE SURFACES TO BE REJECTED DURING THE EDDY CURRENT INSPECTION.
(1)Make sure that the fan disk is clean. Refer to TASK 72-22-40-100-801 (72-22-40, Cleaning 001).
Subtask 72-22-40-250-001
(2)Do an eddy current inspection of the bore surfaces. Refer to TASK 70-32-10-250-003 (2 MHZ EDDY CURRENT INSPECTION OF BORES IN ROTATING ENGINE HARDWARE USING SYSTEMS UNDER COMPUTER, NUMERIC, OR ROBOTIC CONTROL) and Figure 802.
NOTE:
This inspection can only be done by identified and approved persons. You cannot accept or reject components until you have been approved.
(a)If you change the equipment or the procedure specified in this inspection, it can have an unwanted effect on the inspection results. Before you change the equipment or the procedure, write to:
GE Aviation
Field Support Technology
One Neumann Way, MD: Q8
Cincinnati, Ohio 45215 USA
(b)The material is Titanium. Use correction factors for calibration as necessary. Refer to TASK 70-32-10-250-003 (2 MHZ EDDY CURRENT INSPECTION OF BORES IN ROTATING ENGINE HARDWARE USING SYSTEMS UNDER COMPUTER, NUMERIC, OR ROBOTIC CONTROL).
(c)Use the GE-FQAP-428inspection kit to do an inspection of the bore zones shown in Figure 802.
(d)Examine the inspection results. Use the limits that follow:
1The eddy current inspection limit is 1500 mV.
2If the amplitude of an indication is more than 1500 mV, the fan disk is not serviceable.
(e)Complete the eddy current data sheets.
(f)Make sure you complete all records during the eddy current inspection. Keep all records made during the inspection.
* * * FOR ALL
Figure 802   Fan Disk - Eddy Current Bore Inspection
Subtask 72-22-40-270-009
D.Do an ultrasonic inspection of the fan disk dovetail slots. Refer to TASK 70-32-06-270-001 (ULTRASONIC INSPECTION) .
NOTE:
This inspection will cover the dovetail slot from tangency point to tangency point. Refer to Figure 803. The inspection is an ultrasonic technique which utilizes surface waves. The inspection is accomplished using a dedicated ultrasonic transducer assembly (probe). Each slot will be inspected in two directions, from the centerline to the tangency point both clockwise and counter clockwise. Complete coverage of the slots will be accomplished in 4 scans.
NOTE:
For specific cases where the procedures or equipment described here cannot be applied in total, specific exceptions must be obtained in writing from the appropriate technical function before any inspection to hardware.
(1)Personnel Requirements:
(a)Personnel performing this inspection must be certified in accordance with NAS-410, American Society of Nondestructive Testing (ASNT-TC-1A), Air Transport Association Specification No. 105 (ATA 105), COSAC, or any equivalent certification document acknowledged by the local regulatory agencies.
(b)It is strongly recommended that personnel performing this inspection receive practical training in the use of this procedure and must demonstrate proficiency in the calibration, inspection, and evaluation routines before accept/reject authority is delegated.
(c)Any training which may be provided regarding the performance of this inspection does not imply that the personnel who receive that training have met the requirements for inspector certification in accordance with the appropriate certification document.
Subtask 72-22-40-160-007
(2)Pre-Inspection Preparation:
CAUTION:
CONTAMINATED DOVETAIL SLOTS CAN CAUSE DAMAGE TO THE PROBE. IMPURITIES CAN ALSO INTERFERE WITH INSPECTION RESULTS AND PRODUCE IRRELEVANT INDICATIONS. IT IS IMPERATIVE THAT CLEANING OCCURS BEFORE INSPECTION.
(a)Visually inspect each dovetail slot and assure test area is clean, dry, and free of any contaminants that may interfere with inspection.
(b)If necessary, clean the fan disk dovetail slots. Refer to TASK 72-22-40-100-801 (72-22-40, Cleaning 001).
(c)Locate the serial number (S/N) on the forward end of the disk, the “/” in S/N is the 12 o’clock position aft looking forward (ALF). Number each slot clockwise, forward looking aft (FLA), for reference purposes.
Subtask 72-22-40-820-001
(3)Initial equipment setup:
NOTE:
Refer to the manufacturer’s equipment manual for the particular ultrasonic instrument being utilized for this inspection if any questions arise about the use of the instrument.
(a)Connect the ultrasonic instrument to the appropriate power source and switch the instrument power on. Allow the instrument to warm up for at least 10 minutes or the manufacturer’s recommended warm up time.
(b)Connect the probe to the ultrasonic instrument.
(c)Adjust the ultrasonic instrument to the basic settings in Figure 804.
(d)Use delay control only, locate the signal from the transducer wedge and position the signal on the 0.0 division on the cathode ray tube (CRT).
* * * FOR ALL
Figure 803   Scan Zones - Inspection
* * * FOR ALL
Figure 804   Preliminary Instrument Settings
Subtask 72-22-40-820-002
(4)Equipment Calibration:
(a)Prepare ultrasonic instrument and probe according to Subtask 72-22-40-820-001 (paragraph 3.D.(3)).
(b)Refer to Figure 805 and Figure 806 for calibration.
(c)Apply a small amount of couplant to the standard and visually make sure that there will be no excess couplant in front of the transducer.
(d)Put the probe on the standard as shown in Figure 805 and make sure that the flat side of the probe is flat against the guide.
NOTE:
Response from the end of the standard will appear on the screen later in time than the response from the electrical discharge machining (EDM) notch. Refer to Figure 806.
(e)Slide the probe across the standard and locate the response from the EDM notch. Adjust the instrument gain so that the amplitude of the response is approximately 80 percent of full screen height (FSH).
(f)Adjust range and delay so that the trailing edge of the transducer wedge signal is at 0.0 on the CRT base line and the leading edge of the response from the notch is at the 5.0 on the CRT baseline.
(g)Record range and delay settings.
(h)Slide the probe along the standard and make sure that the flat side of the probe is flat against the guide. Maximize the response from the EDM notch. Adjust the gain to set the amplitude of the response to 80 percent FSH.
(i)Final screen presentation should be similar to Figure 806.
(j)Record the gain.
Subtask 72-22-40-270-010
(5)Inspection:
NOTE:
This is a surface wave inspection. It is very important that there is no couplant in front of the transducer as this could affect the response from defects.
(a)Refer to Figure 807 for inspection details.
(b)Make sure that pre-inspection preparation, initial equipment set-up, and system calibration for the area to be inspected are complete according to sections Subtask 72-22-40-820-001 (paragraph 3.D.(3)), Subtask 72-22-40-820-002 (paragraph 3.D.(4)), and Subtask 72-22-40-270-010 (paragraph 3.D.(5)).
(c)Apply couplant to the dovetail for the inspection of zone 1 and visually make sure that there will be no excess couplant in front of the transducer.
(d)Place the probe in the dovetail slot as shown in Figure 807 for inspection of zone 1.
(e)Gate from 0.5 to 7.0 on the CRT baseline.
(f)Slide the probe down the dovetail slot while you monitor the CRT.
(g)Evaluate all indications greater than or equal to 50 percent of FSH. Refer to Subtask 72-22-40-270-011 (paragraph 3.D.(7)).
(h)Repeat Subtask 72-22-40-270-010 (paragraph 3.D.(5)(c)) through Subtask 72-22-40-270-010 (paragraph 3.D.(5)(g)) for each dovetail slot for the inspection of zone 1.
(i)Apply couplant to the dovetail for the inspection of zone 2 and visually make sure that there will be no excess couplant in front of the transducer.
(j)Place the probe in the dovetail slot as shown in Figure 807 for inspection of zone 2.
(k)Gate from 0.5 to 6.0 on the CRT baseline.
(l)Slide the probe down the dovetail slot while observing the CRT.
(m)Evaluate all indications greater than or equal to 50 percent of FSH. Refer to Subtask 72-22-40-270-011 (paragraph 3.D.(7)).
(n)Repeat Subtask 72-22-40-270-010 (paragraph 3.D.(5)(i)) thru Subtask 72-22-40-270-010 (paragraph 3.D.(5)(m)) for each dovetail slot for the inspection of zone 2.
(o)Use an approved solvent, clean each dovetail slot to remove couplant.
(p)Repeat Subtask 72-22-40-270-010 (paragraph 3.D.(5)(c)) thru Subtask 72-22-40-270-010 (paragraph 3.D.(5)(n)) with the probe facing the opposite direction for the inspection of zone 3 and zone 4.
* * * FOR ALL
Figure 805   Probe and Calibration Standard
* * * FOR ALL
Figure 806   Screen Display - Calibration
* * * FOR ALL
Figure 807   Probe Placement - Inspection
Subtask 72-22-40-820-003
(6)Calibration Check:
(a)A calibration check must be performed after inspection. Also, check calibration whenever any system component or operator is changed, after any loss of power, and at any time the operator suspects a change in the system.
(b)If the amplitude of the response from the EDM notch has increased by more than 15 percent FSH above the calibration amplitude, the system must be recalibrated before the inspection of additional hardware. It will be necessary to re-inspect any rejected hardware examined since the last acceptable calibration once correct calibration has been achieved.
(c)If the amplitude of the response from the EDM notch has decreased by more than 15 percent FSH below the calibration amplitude, the system must be recalibrated and all hardware inspected since the last acceptable calibration or calibration check must be re-inspected.
Subtask 72-22-40-270-011
(7)Indication Evaluation:
(a)Any indication(s) that equals or exceeds 50 percent FSH must be evaluated as follows:
1Check calibration to verify it is acceptable. Refer to Subtask 72-22-40-820-002 (paragraph 3.D.(4)). Re-inspect the area to verify that the signal is repeatable. If the indication does not exceed 50 percent then the indication is acceptable, if the indication exceeds 50 percent proceed as follows:
aPerform a visual inspection on the dovetail slot for any surface defects and geometry changes that could cause indications.
bIf the signal repeats, clean area with approved solvents and then re-inspect.
cIf the signal repeats, do Subtask 72-22-40-110-005 (paragraph 3.A.) and Subtask 72-22-40-230-001 (paragraph 3.B.) again in the specific area of indication.
dIf the signal equals or exceeds 50 percent FSH, and is outside of zone 2 and 4 as referenced in Figure 803, view B, then this area is indiscernible and the disk is rejectable.
eRecord the results on the data sheet Form 2032-1. Reference indication location by dovetail number and axial position from the forward end of the slot and provide to GE for review.
fIf the signal equals or exceeds 50 percent FSH in any zone 1-4, the disk is rejectable.
gRecord the results on the data sheet Form 2032-1. Reference indication location by dovetail number and axial position from the forward end of the slot and provide to GE for review.
Subtask 72-22-40-270-012
(8)Documentation:
(a)All calibration and inspection data must be recorded on the appropriate operator logs (2032-1). Refer to Figure 808.
(b)Document all inspection results on the operator logs.
(c)It is the inspection facilities responsibility to maintain all inspection records. The inspection records should be maintained with the permanent record of the part and must be maintained for the life of the part.
* * * FOR ALL
Figure 808   Operator Calibration Log and Scan Log
4 . Visual Inspection.
Refer to Figure 801.
Subtask 72-22-40-220-003
A.Do an inspection of all areas of the fan disk for:
(1)Cracks:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-017
(2)Discoloration that is a result of a shotpeen procedure (rust color):
Maximum serviceable limit:
Any amount.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-018
(3)Nicks, dents, and scratches (all areas unless identified in other paragraphs):
Maximum serviceable limit:
Any amount, 0.004 inch (0.10 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Maximum repairable limit:
Deleted.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-004
(4)Nicks, dents, and scratches in the web areas:
Maximum serviceable limit:
• Any amount, 0.004 inch (0.10 mm) in depth, 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
• The minimum distance between damage areas on a web surface must not be less than 2.00 inches (50.8 mm).
Maximum repairable limit:
Deleted.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-005
(5)Nicks, dents, scratches, and fretting (on the seal aft face only):
Maximum serviceable limit:
Any amount, 0.003 inch (0.08 mm) in depth.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-019
(6)Nicks, dents, scratches, and fretting (in the retainer grooves only):
Maximum serviceable limit:
Any amount, 0.003 inch (0.08 mm) in depth.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-020
(7)Nicks, dents, scratches, and fretting (on the seal aft face, surface D, and surface E only):
Maximum serviceable limit:
Any amount, 0.004 inch (0.10 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Maximum repairable limit:
Deleted.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-036
(8)Gouges on the seal aft face, surface D, and surface E:
Maximum serviceable limit:
Not serviceable.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-030
(9)Nicks, dents, and scratches (on the spinner aft support ring flange mating face chamfer (area F)):
Maximum serviceable limit:
Any amount, to a maximum of 0.010 inch (0.25 mm) in depth and 0.100 inch (2.54 mm) in width.
Repair method:
Repair. Refer to TASK 72-22-40-300-801 (72-22-40, REPAIR 001) .
Subtask 72-22-40-220-037
(10)Nicks, dents, and scratches in area B (do not include the web areas). Refer to Figure 801.
Maximum serviceable limit:
Visual defects with the appearance of scratches, nicks, dents, and other surface conditions of 0.001 inch (0.02 mm) in depth are permitted, if there is no adjacent high metal and there is a shotpeened surface on the visual condition.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-042
(11)Nicks, dents, and scratches in area B bores. Refer to Figure 801.
Maximum serviceable limit:
Visual defects with the appearance of scratches, nicks, dents, and other surface conditions of 0.001 inch (0.02 mm) in depth are permitted, if there is no adjacent high metal and there is a shotpeened surface on the visual condition.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-006
B.Do an inspection of the boltholes on the fan disk for:
(1)Cracks:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-021
(2)Nicks, dents, and scratches:
Maximum serviceable limit:
0.002 inch (0.05 mm) in depth after the removal of high metal, if the scratches are not on more than 50 percent of the circumference of each hole. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Maximum repairable limit:
Deleted.
Repair method:
Repair. Refer to TASK 72-22-40-300-803 (72-22-40, REPAIR 004).
Subtask 72-22-40-220-038
(3)Galling:
Maximum serviceable limit:
Not serviceable.
Repair method:
Repair. Refer to TASK 72-22-40-300-803 (72-22-40, REPAIR 004).
Subtask 72-22-40-220-007
C.Do an inspection of the dovetail slots for:
(1)Nicks, dents, scratches, and fretting on the pressure faces:
Maximum serviceable limit:
0.003 inch (0.08 mm) in depth, if the damage is not on more than 60 percent of the pressure face.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-022
(2)Nicks, dents, scratches, and fretting on the radius below and adjacent to the pressure faces:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-023
(3)Nicks, dents, scratches, and fretting on the bottom of the slots:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-043
(4)Wear/fretting on the bottom of the dovetail slots aft disk because of contact with the dovetail key (20-180 , 72-00-00) (SIN 8300B):
Maximum serviceable limit:
Any amount, less than 0.002 inch (0.05 mm) in depth, within area X.
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-024
(5)Nicks, dents, and scratches on the corners of the leading and trailing edges of the dovetail:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-008
D.Do an inspection of the forward and aft surfaces of the booster spool mounting flange, the flange of the forward fan shaft, and the spinner flange mating face for:
(1)Cracks:
Maximum serviceable limit:
Not serviceable.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-032
(2)Nicks, dents, and scratches in area V. Refer to Figure 801.
Maximum serviceable limit:
Any amount, 0.006 inch (0.15 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Maximum repairable limit:
Deleted
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
Subtask 72-22-40-220-034
(3)Nicks, dents, and scratches on the forward face of the posts (area F not included):
Maximum serviceable limit:
Any amount less than 0.003 inch (0.08 mm) in depth, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Maximum repairable limit:
One blend per post to a maximum of 0.006 inch (0.15 mm) in depth, after blending.
Repair method:
Blend. Blends must be 0.250 inch (6.35 mm) away form the bolthole. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Subtask 72-22-40-220-025
(4)Nicks, dents, and scratches (all other locations):
Maximum serviceable limit:
Any amount less than 0.001 inch (0.03 mm) in depth, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-009
(5)Fretting:
Maximum serviceable limit:
Any amount if in the limits of TASK 70-33-03-220-006 (SPECIAL INSPECTION FOR SURFACE FRETTING OR GALLING) .
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-010
(6)Rub marks on the booster spool mounting flange from contact with the balance weights:
Maximum serviceable limit:
Any amount.
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-041
(7)Nicks, dents, scratches, and fretting on the forward and aft surfaces of forward fan shaft mounting flange in 0.210 inch (5.33 mm) of the boltholes:
Maximum serviceable limit:
Any amount, 0.004 inch (0.10 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-039
(8)Nicks, dents, scratches, and fretting in area G. Refer to Figure 801.
Maximum serviceable limit:
Any amount, 0.004 inch (0.10 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-040
(9)Nicks, dents, scratches, and fretting on the forward and aft surfaces of the forward fan shaft mounting flange (but not in 0.210 inch (5.34 mm) of the boltholes and area G).
Maximum serviceable limit:
Any amount, 0.004 inch (0.10 mm) in depth and 0.020 inch (0.50 mm) in width, after removal of high metal. Refer to TASK 70-42-00-350-002 (BLENDING AND REMOVAL OF HIGH METAL PROCEDURES) .
Repair method:
Repair. Refer to TASK 72-22-40-300-802 (72-22-40, REPAIR 002).
5 . Dimensional Inspection.
Refer to Figure 801.
Subtask 72-22-40-220-011
A.Do an inspection of the diameters that follow:
(1)Diameter G (shaft mounting flange bolthole):
Maximum serviceable limit:
• 15 holes - 0.7555 inch (19.190 mm)
• 8 holes - 0.7559 inch (19.200 mm)
• 3 holes - 0.7579 inch (19.251 mm)
NOTE:
In any group of five consecutive holes, no more than three holes can have a diameter G that measures more than the nominal hole diameter plus 0.0003 inch (0.008 mm). Nominal hole diameter dimension is 0.7552 inch (19.182 mm).
Repair method:
Repair. Refer to TASK 72-22-40-300-803 (72-22-40, REPAIR 004).
Subtask 72-22-40-220-026
(2)Diameter H (booster spool mounting flange bolthole):
Maximum serviceable limit:
• 11 holes - 0.6364 inch (16.165 mm)
• 5 holes - 0.6368 inch (16.175 mm)
• 2 holes - 0.6388 inch (16.226 mm)
NOTE:
In any group of five consecutive holes, no more than three can be larger than the nominal hole diameter plus 0.0003 inch (0.008 mm).
Repair method:
Replace the fan disk.
Subtask 72-22-40-220-027
(3)Diameter AR:
NOTE:
The measurement of diameter AR is only necessary when there is an overspeed condition. The measurement of the diameter must be made at the marked tang, at room temperature, and 3.51 inches (89.2 mm) aft of the forward face of the fan disk. The fan disk must be less than 0.005 inch (0.13 mm) of the OD marked on the fan disk tang.
Minimum serviceable limit:
Refer to Note.
Maximum serviceable limit:
Refer to Note.
Repair method:
Replace the fan disk.
6 . Dovetail Slot Pressure Faces - Inspection.
Refer to Figure 809.
Subtask 72-22-40-930-001
A.Make the Dovetail Pressure Face Inspection Gage (Inspection Gage). Refer to Figure 809.
* * * FOR ALL
Figure 809   Dovetail Pressure Face Inspection Gage (Inspection Gage)
Subtask 72-22-40-220-012
B.Do an inspection of the dovetail pressure faces as follows:
(1)Use the inspection gage to do an inspection of the pressure faces in dovetail slot No. 1 as follows:
NOTE:
The fan disk dovetail slots locations are numbered CCW, forward looking aft. The number 1 is stamped on each side of the No. 1 dovetail slot, on the forward side of the fan disk. The number 5 is stamped on both sides of the fan disk to show the No. 5 dovetail slot. If the No. 5 dovetail is not marked use a Marks-a-Lot or other approved marker, and label each side of the dovetail. The fifth slot is CCW, forward looking aft from the No. 1 dovetail.
Subtask 72-22-40-220-013
CAUTION:
DO NOT SCRATCH OR DAMAGE THE FAN DISK WITH THE DOVETAIL PRESSURE FACE INSPECTION GAGE. IF THE GAGE IS DROPPED ON THE FAN DISK OR IF THE FAN DISK IS SCRATCHED, THE FAN DISK COULD BECOME UNSERVICEABLE.
(a)Put the inspection gage in the dovetail slot and push surface A against the pressure face on one side of the slot. Make sure that surface A is between the tangency points. Refer to Figure 810.
(b)Put a bright light behind the inspection gage. If the light shows between the inspection gage and the pressure face, measure the gap with a gage wire.
(c)The fan disk is serviceable if the gap is not more than 0.0035 inch (0.089 mm).
(d)The fan disk is repairable if the gap is not more than 0.010 inch (0.25 mm).
NOTE:
There is not a repair method at this time.
(e)Do the procedure again on the pressure face on the other side of the slot.
Subtask 72-22-40-220-014
(2)Do the procedure again for each dovetail slot. Refer to Subtask 72-22-40-220-013 (paragraph 6.B.(1)(a)).
* * * FOR ALL
Figure 810   Inspection Gage on the Dovetail Pressure Face