GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN SEES6 PROJECT A330 

REFERENCE G54RP1310441

ISSUE 1.0 DATE 6 Mar 2013

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 1 of 11 

GE CF6-80E1 - ATA 54-51-18 Fractured Bolts on Aft 

Engine Mount Upper Beam. 

TABLE OF CONTENTS 

1 DESCRIPTIONS ................................................................................................................. 2

1.1 GENERAL ........................................................................................................................... 2

1.2 PREFERRED INSPECTION ............................................................................................... 2

2 PROCEDURES ................................................................................................................... 2

2.1 TASK SUPPORTING DATA ................................................................................................ 2

2.1.1 AREA OF APPLICABILITY (SEE FIGURE 1) ............................................................ 2

2.1.2 DESCRIPTION OF POSSIBLE DAMAGE ................................................................. 2

2.1.3 REASON FOR THE JOB ........................................................................................... 2

2.1.4 JOB SET UP INFORMATION .................................................................................... 3

2.2 PROCEDURE ..................................................................................................................... 3

2.2.1 EQUIPMENT AND MATERIALS ................................................................................ 3

2.2.2 PREPARATION FOR INSPECTION .......................................................................... 3

2.2.3 INSTRUMENT ADJUSTMENT .................................................................................. 4

2.2.4 INSPECTION ............................................................................................................. 4

2.2.5 ACCEPTANCE CRITERIA ......................................................................................... 5

2.2.6 FINAL NDT REQUIREMENTS ................................................................................... 5

TABLE OF FIGURES 

Figure 1: Inspection Area. ................................................................................................................. 6

Figure 2: Example of Crack & Section C-C of bolt head. .................................................................. 7

Figure 3: Signal from V1 block with alarm gate. ................................................................................ 8

Figure 4: Probe Position .................................................................................................................... 9

Figure 5: Signal from good bolt (section C-C fig 2). ........................................................................ 10

Figure 6: Signal from cracked Bolt. ................................................................................................. 11
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 2 of 11 

1 DESCRIPTIONS 

1.1 GENERAL 

A. This procedure contains the technical information for the inspection of GE CF6-80E1– ATA 

54-51-18 Bolts (PN 1672M36P01 x4 per Engine) on Aft Engine Mount Upper Beam. 

B. This procedure is applicable for the detection of 100% cracked sheared through bolts (Fig 1 

& 2) 

1.2 PREFERRED INSPECTION 

See 

A. GE CF6-80E1 - ATA 54-51-18 Fractured Bolts on Aft Engine Mount Upper Beam

B. No alternative.

2 PROCEDURES 

2.1 TASK SUPPORTING DATA 

NTM 51-40-00 

2.1.1 AREA OF APPLICABILITY (SEE FIGURE 1) 

Bolt Part Number (PN) 1672M36P01, Aft Engine Mount Upper Beam attached to the pylon, 

2.1.2 DESCRIPTION OF POSSIBLE DAMAGE 

A. Cracks completely sheared through the bolt section (Figure 2)

2.1.3 REASON FOR THE JOB 

 See AOT A71L002-13 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 3 of 11 

2.1.4 JOB SET UP INFORMATION 

A. TOOLING: 

ID Item Designation Key Parameters 

Tooling 

Used to 

Develop 

The 

Procedure 

Vendor 

USN 60 - Ultrasonic Equipment UIDBCAB y G.E. Inspection Technologies 

- - Cable Lemo 1 to lemo 0 y G.E. Inspection Technologies 

MB2S EN 500038 - Ultrasonic search unit 2MHz Dia 10mm y G.E. Inspection Technologies 

V1 (EN12223) - Calibration Block Steel y G.E. Inspection Technologies 

NOTE: 

Any comparable Ultrasonic equipment may be used provided that it satisfies the 

requirements of this procedure and is capable of resolving the reference signal in the 

calibration standard at the required level of resolution. 

2.2 PROCEDURE 

2.2.1 EQUIPMENT AND MATERIALS 

See 2.1.4 (A) TOOLING. 

2.2.2 PREPARATION FOR INSPECTION 

A. Make sure the Access Panel has been removed refer to AOT A71L002-13.. 

B. Make sure that the surface to be inspected is clean and smooth. 

C. Check the inspection area for any visible damage or discontinuities. 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 4 of 11 

2.2.3 INSTRUMENT ADJUSTMENT 

 Set the data given below on the instrument: 

Frequency: 2 MHz 

Range: 200 mm 

Delay: 0.000μs 

MTL Velocity: 5960 m/s (0.126 in. /μs) 

Rectification mode: full wave 

A. Connect appropriate search unit MB2S EN 500038 to instrument. 

B. Couple the search unit to the V1 block (A330 NTM Figure 51-00-991-102A) on the 100mm 

section (Figure 3), 

C. Adjust the position of the search unit to get a reflection at 50 divisions on the time base and 

the repeat echo at 100 divisions (See Fig 3). 

D. Adjust the instrument gain control to give a 100 % Full Screen Height (FSH) signal. 

E. Set the Gate Start Marker to 50 mm. 

F. Set the Gate Marker width to 60 mm 

G. Set Gate to 30%, full Screen Height 

Caution: 

CONFIRM THE V1 BLOCK MATCHES EN 12223 IN RESPECT OF THE 100MM SECTION 

AND THE MATERIAL VELOCITY OF 5920MM/S. THE BOLT MATERIAL IS INCONEL AND 

THE VELOCITY WILL NOT EXACTLY MATCH THE V1 BLOCK. THIS IS TAKEN INTO 

ACCOUNT WITH THE GATE SETTINGS. THE INTENTION OF THE PROCEDURE IS TO 

IDENTIFY 100% SHEARED BOLTS IN THE ANTICIPATED LOCATION, NOT TO GIVE A 

PRECISE MEASUREMENT OF THE OVERALL LENGTH. 

2.2.4 INSPECTION 

A. Couple the search unit on the threaded end of the bolt. (Fig 4 & 5) 

B. Adjust the position of the search unit until you achieve the signal (Fig 5) 

Note: 

Figure 2 shows the section view of the reflecting face of the bolt head. Expected beam path 

approx 110mm (4.311”). The bolt head has more than one possible configuration (see fig 2 

detail C-C) when interpreting the backwall echo this should be taken into account. 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 5 of 11 

C. Record all indications > 30 % on the Time base, within the length of the bolt (Fig 6) 

D. Repeat Steps A to C for the remaining bolts to be inspected. 

2.2.5 ACCEPTANCE CRITERIA 

A. Reject all bolts which show indications within the length of the bolt > 30 % FSH (Fig 6) and 

record them as cracked. 

B. Report all cracked bolts to Airbus. 

2.2.6 FINAL NDT REQUIREMENTS 

Remove couplant and clean the inspection surface.
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 6 of 11 

Annex of Figures 

Rib 8D1: 

Bolts to be inspected 1 thru 4. 

 

Figure 1: Inspection Area. 

 

1

2 

3

4 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 7 of 11 

Figure 2: Example of Crack & Section C-C of bolt head. 

Search unit position 

for inspection 

Typical sheared bolt (Through Crack)

C

C

C C 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 8 of 11 

Figure 3: Signal from V1 block with alarm gate. 

 

Gate 30%, 50mm start 60mm width 

100 mm 

section 

First Repeat Echo 

from 100 mm 

section 

Echo from 100 mm Section 

100% FSH 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 9 of 11 

Figure 4: Probe Position 

Probe Position Center of Bolt threaded end 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 10 of 11 

Figure 5: Signal from good bolt (section C-C fig 2). 

 

Gate 30%, 50mm start 60mm width 
GE CF6-80E1 - ATA 54-51-18 FRACTURED BOLTS ON AFT ENGINE MOUNT 

UPPER BEAM 

Technical Report 

ORIGIN PROJECT A330 

REFERENCE

ISSUE 1.0 DATE 

© AIRBUS OPERATIONS S.A.S. 2013. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 11 of 11 

Figure 6: Signal from cracked Bolt. 

Gate 30%, 50mm start 60mm width