C. Make a record of all ultrasonic signals that are less than 40% full screen height so you can refer to
these records when you do this inspection again.
D. To make sure that the ultrasonic signals are not caused by sound transfer into the wing attach fitting,
do one of the steps that follow:
(1) Lift the engine and pylon to remove the load from the fuse pin. Refer to Service Bulletin
747-54A2153 to remove the weight of the engine and the pylon from the fuse pin. Do the
inspection again. If the ultrasonic signal does not change to less than 40% full screen height,
reject the fuse pin.
(2) Remove the pin from the airplane. Do a magnetic particle inspection as specified in Service
Bulletin 747-54A2153.
E. To make sure there are cracks when you get ultrasonic indications with the fuse pin installed, do an
eddy current inspection as specified in Part 6, 51-00-00, Procedure 13. It will be necessary to first
remove all cadmium and corrosion from the inner diameter of the fuse pin. Refer to Service Bulletin
747-54A2153 for instructions on how to remove the cadmium and corrosion and how to refinish the
fuse pins after the inspection is done. To make sure there are cracks when you get ultrasonic
indications with the fuse pin removed from the airplane, do a magnetic particle inspection as specified
in Service Bulletin 747-54A2153.
Table 1: Upper Link Fuse Pins
ENGINE
CONFIGURATION
AND FUSE PIN PART
NUMBER
STRUT
*[1]
FUSE PIN BACK SURFACE SIGNAL
INTERNAL
REFLECTION
POSITION
RANGE %FSW
*[2]
TRANSDUCER
GUIDE POSITION
METAL DISTANCE POSITION
IN. MM %FSW
*[2]
JT9D-70
65B94182-4 I/B 3.643 92.5 72% 24% - 34% C
65B94182-5 O/B 3.323 84.4 66% 21% - 26% B
JT9D-XXX (EXCEPT
-70)
65B90394-8,
-11, -602, -605
I/B 3.323 84.4 66% 22% - 25% C
65B90394-8,
-11, -602, -605
O/B 3.323 84.4 66% 22% - 25% C
CF6
65B94182-1 I/B 3.323 84.4 66% 22% - 24% C
65B94182-1, -5, -11 O/B 3.323 84.4 66% 21% - 26% B
RB211
69B89612-2 I/B 3.643 92.5 72% 25% - 36% B
69B94182-5 O/B 3.323 84.4 66% 21% - 26% B
AIRPLANES RB013-
RB016
65B94182-1 I/B 3.323 84.4 66% 22% - 24% C
65B94182-1, -11 O/B 3.323 84.4 66% 21% - 26% C
REFERENCE
STANDARD NDT4115
- 4.115 104.5 82% 25% - 35% -
747
NONDESTRUCTIVE TEST MANUAL
PART 4 54-30-09
Page 4
Nov 15/2015D6-7170
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
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