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ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines
CFM PROPRIETARY INFORMATION The information contained in this document is CFM proprieta ry information and is disclosed in confidence. It is the property of CFM and shall not be used, disclos ed to others or reproduced without the express written consent of CFM, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of a ny repairs, modifications, spare parts, design, or configuration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given for reproduction in whole or in pa rt, this notice and the notice set forth on each page of this document shall appear in any such re production in whole or in part.
The information contained in this document may also be contr olled by U.S. export control laws.
Unauthorized export or re-export is prohibited.
All technical documentation and information contained her ein, with respect to assembly and disassembly, cleaning, inspection methods and limits, rep air methods and limits, operational limits, life limits and the like, have been developed and app roved for use with engines and parts that have been manufactured and/or approved by CFM and that h ave been maintained in accordance with CFM technical documentation and recommend ations. CFM has no contractual or legal obligation for, nor knowledge of, non-CFM-approve d parts and repairs. Accordingly, this document is not intended to apply to non-CFM-approved parts and repairs.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 1 of 25
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines
1. PLANNING INFORMATION A. Effectivity CFM56-5B1, -5B2, -5B4, -5B5, -5B6, -5B7 CFM56-5B1/P, -5B2/P, -5B3/P , -5B4/P, -5B5/P, -5B6/P, -5B7/P, -5B8/P , -5B9/P CFM56-5B3/P1, -5B4/P1
(1) This Service Bulletin affects all Turbine Rear Frames (TRF) P/N 338-102-907-0 and 338-102-908-0 installed on CFM56-5B engine model.
B. Description This Service Bulletin gives instructions for on wing or in sh op inspection of the TRF struts in order to increase the life of the TRF. The three mount strut s of the TRF have to be inspected. Refer to Figure 1.
C. Compliance Category 7 Do at customer convenience but before the TRF reaches 32,000 cycles since new for commercial engine models and 25,000 cycles for corporate jet engine models (CFM56-5B6, -5B7, -5B6/P, -5B7/P).
For TRF disposition/re-inspection intervals, refer to par agraphs 3.D.(2) and 3.E.(2).
NOTE: The Service Bulletin can be accomplished in shop or on wing.
D. Concurrent Requirements None.
E. Reason
(1) Objective:
To do an inspection.
To increase the life of the TRF. Refer to Engine Shop Manual ATA 05-12-04 for life limits and to Engine Shop Manual ATA 05-21-03 for inspections.
(2) Condition:
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 2
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines TRF may exhibit cracks, initiating at leading and trailing e dge of the mount struts, in the transition radius between the struts and in the outer rin g fillet radius.
(3) Cause:
High thermal gradient between the struts and the outer ring.
(4) Improvement:
This Service Bulletin provides the procedure and equipment to inspect the TRF mount struts.
(5) Substantiation:
Substantiation is by analysis.
F. Approval The technical content of this document is approved by the FAA and under the authority of DOA n°EASA.21J.086.
G. Manpower You will need approximately 3 man-hours for each engine to do this Service Bulletin. This estimation does not include the time needed to get access to t he inspection areas.
H. Weight and Balance Weight and Balance are not changed.
I. References CFM56-5B Engine Shop Manual , CFMI-TP.SM.9 A318/A319/A320/A321 Aircraft Maintenance Manual CFM56 Consumable Products Manual , CFMI-TP.CP.3 CFM56 Standard Practice Manual , CFMI-TP.SP .2 J. Publications Affected CFM56-5B Engine Shop Manual , CFMI-TP.SM.9 ATA 05-12-04, 05-21-03 and 72-56-01.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 3
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines K. Interchangeability The physical and the functional interchangeabilities are n ot affected.
L. Software Accomplishment Summary None.
2. MATERIAL INFORMATION A. Material - Price and Availability
(1) Parts necessary to do this Service Bulletin:
None.
(2) Other Spare Parts:
None.
(3) Consumables:
Code Number Description CP1040 Methyl Ethyl Ketone CP2189 Durite G422 CP2191 Durite G421 B. Industry Support Information None.
C. Configuration Chart None.
D. Disposition of Parts None CFM56-5B S/B 72-0850 December 19, 2012 PAGE 4
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines E. Tooling - Price and Availability Description Supplier Nortec Model NDT 19, 19e, 19e2, 24, 1000, 1200 or -3000.
OLYMPUS NDT 421 North Quay Street WA 99336
KENEWICK USA or ANAFAB 3 avenue Marcel Dassault 78310 Coigneres FRANCE Rohman Elotest family Rohmann GmbH Rudolf-Diesel-Str.13 D-67227 Frankenthal
DEUTCHLAND or Intercontrole IC ESCOFFIER Parc d'activités de la route des lacs BP 612 27106 VAL DE REUIL FRANCE NOTE 1: Any equivalent equipment approved by Snecma/CFM can be use d instead of listed above.
Tool No. Description 856A2692G01 Eddy current inspection kit of rear frame NOTE 2: The inspection kit containing all required tooling can be o btained from CFM by contacting the following address:
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 5
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines North and South America and Asia Customers CFM Inc. Customers Europe, Middle East and Africa Customers CFM SA Customers CFM international Quality Technology Center One Neumann Way, MD:
QB Cincinnati, OH 45215 USA Attention: Brenda Tenley Phone: (513)552 4701 Fax: (513)552 4892 e-mail: brenda.tenley@ge.com CFM international Snecma Manager CFM56 Tooling Programms Site de Melun-Montereau BP 1936 77019 Melun Cedex FRANCE Phone: 33 1 64 14 80 89 Fax: 33 1 64 14 87 65 e-mail: snecma.tooling@snecma.fr
3. ACCOMPLISHMENT INSTRUCTIONS A. General WARNING: METHYL ETHYL KETONE IS TOXIC. USE PERSONAL PROTECTION EQUIPMENT. USE IN A WELL-VENTILATED AREA.
(1) Get access to the TRF for on wing inspection.
(a) Remove the primary nozzle assy. Refer to Aircraft Maintenan ce Manual (AMM), ATA 78-11-01, TASK 78-11-01-000-801.
(b) Remove the primary plug assy. Refer to AMM, ATA 78-11-02, TAS K 78-11-02-000-801.
(2) Get access to the TRF for on wing or in shop inspection.
(a) Remove the flame arrestor and the rear cover. Refer to AMM, TASK 72-56-00-000-802 or Engine Shop Manual (ESM) ATA 72-00-03 R EMOVAL 001
(3) Do a visual inspection of the areas to be inspected. Mark on th e part at the location of all blends, nicks, or other anomalies which may cause an in dication during the inspection. If needed use Methyl Ethyl Ketone (CP1040) , Dur ite G422 (CP2189) or Durite G421 (CP2191) to clean the part.
B. Eddy current calibration and inspection:
The four specific areas to be inspected on the three mounts struts position 1, 3 and 14 are detailed on Figure 1. The calibration block is described on F igure 2.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 6
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines
(1) Calibrate the eddy current instrument to the initial settin gs as follows:
(a) Permit the eddy current instrument to warm up. Refer to the in structions of the manufacturer.
(b) Set the eddy current instrument to the initial settings as below with the example of Rohmann Elotest B300 instrument.
Instrument type Frequency Range Gain Filters Elotest B300 1 to 2 MHz Preampli fier: auto LP: 100 HP: STATIC
(c) Eddy Current probe(s) from the kit, : 9970-958-574, 9970-95 8-575, 9970-958-576.
(d) Calibration block from the kit, : 9970-958-579. Refer to Fig ure 2.
(e) Apply teflon from the kit, to the probe.
(f) Put the probe of the inspection kit on the calibration standa rd away from the EDM notches and null the probe.
(2) Scan across the EDM notch at a speed equal to the one that will b e used during the inspection and adjust the instrument gain, phase and dot position so that the peak response from the EDM notch dimension 0.020 inch (0,5 mm ) x 0.004 inch (0,1 mm) has an amplitude equal to 1.5 or 2 Volts depending on t he probe. Refer to Figure 3 to Figure 5.
NOTE 1: Repeat the steps 3.B.(1)(e), 3.B.(1)(f) and 3.B.(2) for ea ch probe CFM56-5B S/B 72-0850 December 19, 2012 PAGE 7
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines NOTE 2: Personnel performing these inspections must be certi fied to one of the following: NAS 410 / EN4179 level 2 minimum or any equival ent standard as recognized by the airworthiness authority of the personnel.
Personnel performing this inspections should receive prac tical training in the use of this procedure and must demonstrate pro ficiency in the calibration, inspection and evaluation routines before ac cept/reject authority is delegated.
Training, which can be provided regarding the performance o f this inspection, does not imply that personnel who receive that t raining have met the requirements of inspector certification in accordance with note 2 above.
Contact your customer team if you think you need such a traini ng.
(3) Inspection.
(a) See locations and dimensions of the areas to be inspected:
– Location A, refer to Figure 6, – Location B1, refer to Figure 7, – Location B2, refer to Figure 8.
(b) Inspect 3 areas as follows:
1 Using the appropriate probe, scan in two directions of all th e areas as it is shown on each figure. Pay special attention near the variation of shapes.
– Probe 9970-958-576, Figure 6 location A.
– Probe 9970-958-574, Figure 7 location B1.
– Probe 9970-958-575, Figure 8 location B2.
(c) In case of indication over the limits of the screen (for examp le due to cracks which pass through the thickness of the flange) reduce the amplitude by steps of 6 db as much time as it is necessary to reach an interpretabl e signal.
NOTE: As we perform a manual inspection, the way to inspect has to b e the closest to the theoretic scanning shown on the figures (not strictly).
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 8
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines 1 Evaluate the horizontal and vertical indications that are e qual to or more than half of calibration level for each probe.
9970-958-574 and 9970-958-576 : 750 millivolts or 1.5 divis ions.
9970-958-575: 1,000 millivolts or 2 divisions, 2 Clean and re-inspect the area in different scanning directi ons to check the indication.
3 After completion of the indication evaluation procedure, i f the indication is still equal to or more than 1,000 millivolts or 750 millivolt s (depending on the probe used), note the place of the indication on the part.
4 Scan perpendicularly to the defect to determine its length. Refer to Figure
9.
(4) Calibration check.
Do a calibration/check after each area inspection (and or ea ch probe) as follows:
NOTE: The calibration check must be done with initial calibratio n settings.
(a) Do a calibration check after each inspection, when a system c omponent or inspector is changed, or when the inspector suspects a chang e may have occurred in the inspection.
(b) If the peak notch response is within 10% more or less, the cali bration is acceptable.
(c) If the amplitude of the response from the EDM notch has decrea sed by more than 10%, re-calibrate and re-inspect all areas inspected s ince the previous calibration.
(d) If the amplitude of the response from the EDM notch has increa sed by more than 10%, re-calibrate and re-inspect any areas which were p reviously found to be rejected since the previous calibration.
C. Alternative Procedure. Fluorescent Penetrant Inspection (FPI) at piece part level.
CAUTION: PARTS MUST BE THOROUGHLY CLEANED BEFORE BEING SUBJECTED
TO THE FLUORESCENT PENETRANT INSPECTION TO ACCOMPLISH
A PROPER INSPECTION AND TO PREVENT CONTAMINATION OF THE INSPECTION MATERIALS.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 9
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines CAUTION: PAY PARTICULAR ATTENTION TO THE AREAS TO BE INSPECTED. IF THERE IS ANY DOUBT, PERFORM THE EDDY CURRENT INSPECTION.
(1) Perform a FPI according to Standard Practice Manual (SPM) 70 -32-14 on the areas to be inspected:
– Location A, refer to Figure 6 – Location B1, refer to Figure 7 – Location B2, refer to Figure 8.
D. Inspection intervals for CFM56-5B commercial engine appli cations:
Mandatory inspection interval for TRF P/N 338-102-907/-90 8-0
(1) If no crack is found on any of the three mount struts, the TRF is serviceable and must be re-inspected at 2,500 cycles repetitive intervals.
(2) If cracks are found on the mount struts, the TRF must be re-ins pected according to the following repetitive intervals:
Total cumulated crack length at each location Re-inspection interval within L < 0.20 (5)
0.20 (5) ≤ L < 0.25 (6,5) L ≥ 0.25 (6,5) 2,500 cycles 370 cycles Immediately remove the turbine frame Repetitive inspection interval of every location is driven by the minimum reduced interval.
NOTE 1: Dimensions are in inches with millimeters in parentheses.
NOTE 2: For each mount strut:
– If one single crack, measure crack length.
– If multiple cracks, cumulate crack length.
NOTE 3: After TRF removal, cracks may be repairable using the limit s provided in Engine Shop Manual ATA 72-56-01 Inspection 001. Even afte r the cracks are repaired, the TRF must still be re-inspected u sing the intervals above.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 10
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines NOTE 4: Three inspection locations on mounts struts (1, 3 and 14):
– Location A: leading edge top end strut, pressure side and suc tion side.
– Location B1: the outer casing fillet radius close to rear flange at mount area (flow path side).
– Location B2: the outer casing fillet radius close to rear flange at mount area (opposite to the flow path).
E. Inspection intervals for CFM56-5B Corporate Jet applicati ons:
Mandatory inspection interval for TRF P/N 338-102-907/908 -0
(1) If no crack is found on any of the three mount struts, the TRF is serviceable and must be re-inspected at next 1,670 cycles repetitive interv als.
(2) If cracks are found on the mount struts, the TRF must be re-ins pected according to the following repetitive intervals:
Total cumulated crack length at each location Re-inspection interval within L < 0.20 (5)
0.20 (5) ≤ L < 0.25 (6,5) L ≥ 0.25 (6,5) 1,670 cycles 280 cycles Immediately remove the turbine frame Repetitive inspection interval of every location is driven by the minimum reduced interval NOTE 1: Dimensions are in inches with millimeters in parentheses.
NOTE 2: For each mount strut:
– If one single crack, measure crack length.
– If multiple cracks, cumulate crack length.
NOTE 3: After TRF removal, cracks may be repairable using the limit s provided in Engine Shop Manual ATA 72-56-01 Inspection 001. Even afte r the cracks are repaired, the TRF must still be re-inspected u sing the intervals above.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 11
ENGINE - LPT Frame Assembly (72-56-00) - Inspection of Turbine Rear Frame on CFM56-5B Engines NOTE 4: Three inspection locations on mounts struts (1, 3 and 14):
– Location A: leading edge top end strut, pressure side and suc tion side.
– Location B1: the outer casing fillet radius close to rear flange at mount area (flow path side).
– Location B2: the outer casing fillet radius close to rear flange at mount area (opposite to the flow path).
F. Installation after the inspection, if the TRF is serviceabl e:
(1) Installation on wing or in shop:
(a) Install the rear cover and the flame arrestor. Refer to AMM, TASK 72-56-00-400-001 or Engine Shop Manual ATA 72-00-03 INSTALLATION 001.
(2) Installation on wing only:
(a) Install the primary plug assy. Refer to AMM, ATA 78-11-12, TA SK 78-11-12-400-041.
(b) Install the primary nozzle assy. Refer to AMM, ATA 78-11-11, TASK 78-11-01-400-041.
G. Quality assurance.
(1) For Eddy Current inspection process:
(a) Record inspection results on the provided inspection sheet report and return it to CFM field representative. Refer to Figure 10.
(b) All probes, block calibration and materials used for this in spection must be supplied or validated by CFM.
(c) Keep all inspection records with the permanent record of the Turbine Rear Frame.
(2) For Fluorescent Penetrant inspection process:
(a) Record inspection results on the provided inspection sheet report and return it to CFM field representative. Refer to Figure 11.
CFM56-5B S/B 72-0850 December 19, 2012 PAGE 12