Boeing 747 - Page 61

Table 2: Upper Link - Fuse Pin Back Surface and Crack Signal Locations
ENGINE
CONFIGURATION
FUSE
PIN
*[1]
STRUT
*[2]
FUSE PIN
BACK SURFACE SIGNAL CRACK LOCATION
*[3]
METAL
DISTANCE
POSITION
%FSW
*[4]
METAL
DISTANCE
POSITION
%FSW
*[4]
IN. MM IN. MM
JT9D-70
-8 I/B 3.56 90.4 95% 0.80 20.3 21%
-4 O/B 3.24 82.3 86% 0.70 17.8 19%
JT9D-XXX (EXCEPT
-70)
-7 I/B 3.24 82.3 86% 0.75 19.1 20%
-7 O/B 3.24 82.3 86% 0.75 19.1 20%
CF6-45, -50
-3 I/B 3.24 82.3 86% 0.75 19.1 20%
-4 O/B 3.24 82.3 86% 0.70 17.8 19%
RB211
(B), (C), (D)
-9 I/B 3.56 90.4 95% 0.80 20.3 21%
-4 O/B 3.24 82.3 86% 0.70 17.8 19%
RB211
(G), (H)
-9 I/B 3.56 90.4 95% 0.80 20.3 21%
-21 O/B 3.24 82.3 86% 0.70 17.8 19%
AIRPLANES
RB013-RB016
-3 I/B 3.24 82.3 86% 0.75 19.1 20%
-4 O/B 3.24 82.3 86% 0.70 17.8 19%
*[1]
BOEING PART NUMBER 69B90909
*[2]
I/B = INBOARD; O/B = OUTBOARD
*[3]
APPROXIMATE LOCATIONS WHERE WE THINK CRACKS WILL START. SEE Figure 1, FLAGNOTE 3.
*[4] %FSW = POSITION OF THE SIGNAL AS A PERCENTAGE OF FULL SCREEN WIDTH
747
NONDESTRUCTIVE TEST MANUAL
PART 4 54-30-08
Page 5
Nov 15/2015D6-7170
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ALL