Output Number
Approval Date
Published Date Time
Recommendation type
Mode
Date released

The Bureau of Air Safety Investigation recommends that
Australian operators of Boeing 737 note the above safety deficiency
and interim recommendations and take appropriate action as
considered necessary to ensure the integrity of Boeing 737 main
landing gear trunnion pin assemblies.



As a result of the investigation of this safety deficiency, the
Bureau simultaneously issues the following interim
recommendations:



IR990046



The Bureau of Air Safety Investigation recommends that Boeing
Commercial Airplane Group alert Boeing 737 operators to this safety
deficiency and implement an appropriate inspection program.



IR990047



The Bureau of Air Safety Investigation recommends that Boeing
Commercial Airplane Group review the effectiveness of Service
Bulletin 737-32A1198 revision 2.



IR990048



The Bureau of Air Safety Investigation recommends that the Federal
Aviation Administration note the above safety deficiency and
interim recommendations and take appropriate action as considered
necessary to ensure the integrity of Boeing 737 main landing gear
trunnion pin assemblies.



IR990049



The Bureau of Air Safety Investigation recommends that the Civil
Aviation Safety Authority note the above safety deficiency and
interim recommendations and initiate appropriate action to ensure
the integrity of Australian Boeing 737 main landing gear trunnion
pin assemblies.

Organisation Response
Date Received
Organisation
Qantas Airways Limited
Response Text

Qantas issued Engineering Instruction (EI) No. 737-032-0105 on
06 May 1999 to address this issue. Pertinent sections of the EI
were as follows:



EI 737-032-0105



1. Title: TRUNNION PIN - INSPECTION OF ACTUATOR ATTACH LUGS



2. Reason: ULTRASONIC INSPECTION OF TRUNNION PIN LUGS FOLLOWING LUG
FAILURE ON INSERVICE QANTAS AIRCRAFT.



3. S.L. Ref: 81205 SB 737-32-1198 02/NSC06



4. Applicability: 737-376, 476, 3Q8, 4Q8, 4L7



12. Accomplishment Instructions:



INTRODUCTION



Qantas aircraft VH-TAK suffered a fracture of the actuator attach
lugs of the trunnion pin on the right gear on the 4th April 1999.
Subsequent inspection of the failure surface and surrounding
material revealed corrosion. This caused pitting and development of
a fatigue crack and eventual failure. This EI targets pins that
have accumulated approximately 10,000 cyc since new or overhaul,
for an ultrasonic examination of the lugs.



12.1 Ensure all gear locks are installed per AMM 32-00-01.



12.2 Ultrasonically inspect the Trunnion Pin part no. 65C32964-(),
65-46113-(), 737R32-06-01-() and 737R32-28-01-() for cracking per
NDT technique U-42



If cracks are detected, replace the trunnion pin prior to further
flight.



12.3 NDT inspector to notify Principal Mech. Systems Eng'r if
cracks are found.