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Airframe Details for F-16 #88-0433

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F-16 Aircraft Profile

Aircraft: 88-0433
LM Aero T/V 1C-35
Plant General Dynamics
Local C/N
Delivered USAF 88433
F-16C Block 40B
Current USAF 88433
F-16C Block 40B
Status [w/o]

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Aircraft History

Date Status Local S/N Airforce/Unit Version Name Info
12 Oct 1989 [act] 88433 F-16C Block 40B
13 Oct 1989 [act] 88433 USAF 34 TFS 'HL' F-16C Block 40B
01 Oct 1991 [act] 88433 USAF 34 FS 'HL' F-16C Block 40B
Dec 1994 [act] 88433 USAF 74 FS 'FT' F-16C Block 40B
Mar 1996 [act] 88433 USAF 524 FS 'CC' F-16C Block 40B
Apr 2001 [act] 88433 USAF 421 FS 'HL' F-16C Block 40B
Jun 2006 [act] 88433 USAF 34 FS 'HL' F-16C Block 40B
Unknown [act] 88433 USAF 421 FS 'HL' F-16C Block 40B
04 May 2012 [msh] 88433 USAF 421 FS 'HL' F-16C Block 40B News Article
Crashed at the Utah Test and Training Range around 8:35 hours local time during an exercise. The pilot ejected safely. Investigation showed that an engine blade broke free and damaged the entire engine.
04 May 2012 [w/o] 88433 USAF 421 FS 'HL' F-16C Block 40B

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Abbreviations and symbols:
[act] Active [i/a] Instructional Airframe [sto] Stored (e.g. at AMARG)
[cld] Cancelled Order [msh] Involved in Mishap [w/o] Write-off
[con] Converted [o/o] On Order
[des] Destroyed (drone) [pre] Preserved (museum, gateguard) T/V LM Aero Type/Version (Construction) number
[emb] Embargoed [scr] Scrapped Photo Available
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Errors and Omissions
Lieven
Feb 20, 2013 - 12:36 PM
Addendum

Air Combat Command investigators released an addendum to the report on the May 2012 crash of an F-16C from Hill AFB, Utah, at the Utah Test and Training Range. In its report issued last September, ACC's accident investigation board determined that a manufacturing flaw in a blade in the first stage fan of the aircraft's engine caused the crash and loss of the fighter during ground support training.

The AIB president reopened the investigation to re-examine whether maintenance crews should have identified the manufacturing inconsistency at the base of the blade, according to ACC's Feb. 7 release. The report addendum indicates that the blade's surface inconsistency could have been detected during installation at Tinker AFB, Okla., in April 2004, states the release. However, the ability to detect the defect was limited due to the lubrication applied during machining work and the transfer of the part, it states.

Procedures also did not require an inspection, and were not typically completed at Tinker for new blades arriving from the manufacturer, noted ACC.





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