INVESTIGATION OFFICERS REPORT - ART 342

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP74B00447R000100010037-1
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 3
• Document Creation Date: December 12, 2016
• Document Release Date: February 5, 2002
• Sequence Number: 37
• Publication Date: March 9, 1966
• Content Type: CABLE

25X1A.
25X1A
25X1A
25X1A
'MMED IATE
_OEALIS
t, RA 8L V119 MAR to(i
VKV
N/YET
25X1A
KW CARD FO
' IUBJ: INVESTIGATION OFFICERS REPORT ART .342
a;`OLLOWI('G IS PROVISIONAL CONCLUSION OF THE INVESTIGATION
INTO ART .342 AC:: IDEN!` A14D MAY BE A ENDS 1
FTE!I INTENSIVE EXAMINATION OF I HE LEFT WING WHICH SHOULD BE
OVERED LATE 9 MARCH OR EARLY 1(. MAR(-;H.
IRE LEFT WING FAILED AT THE ROOT JUST OUTEO'ARD OF THE FIP.1
ING RIPS THE UNDER WING SKIN FAILED AT THE FINGER PLATES LEAV1:C .a
THE LOWER WING ATTACHMENT FITTINGS AND BOLTS INTACT WITH THE
FUSELAGE THE a . WING ATTACHMENTS WERE ALL SHEARED OFF OUTPOP; r J
OF T? E t 1':~CHME 1? BOLTS EXCEPT THE FIRST TWO WHICH WERE FOUN;
T' HE F,OS.TS HAVING FAILED ON THESF_.
A MAT A DER OF THE a .CRAFT - E'N PITCHED NOSE Ur
.tMPCSINF .v..I C SSIVE -G`" ON THE STRUCTUREr A HIS CAUSED THE LEFT
sGI?NE ;?A% BAT SUPFORi STRUCTURE TO FAIL AL1 OWIN 1 TH. ENGINE. TO
3REAK THROUGH THE LOWER FUSELAGE BULKHFADS. THE RIGHT ENGINE BA .. _
Approved For Release 2002/06/16 : CiR D 4 0044714000160010037 -1
ou `T iF tbl OIl' i lit
 Approved For glease 2002/06/18 : CIA-RDP74B00447Q600100010037-1
I
SLIPPED OUT O iT'S PEARINGS IND THE REAR ENGINE SUPPORTING
OLT FAILED UNDER TENSIONA THUS THE ENGINE CAME COMPLETELY FREE
= E FUSELAGE
^s ,
*;> 14"HE FIGHT WING THEN BROKE AWAY WITH A PORTICWOF THE
`,' ELAGE ATTACHED TO IT. THE COATERPART OF THE FUSELAGE WAS NOW
5 THE NOSE SECTION FORWARD OF THE WING LEADING EDGE AND THE
SECTION AFf OF THE TRAILING EDGE CAME APART AS COMPLETE SECT;ONS
.";cCEPT FOR THE LEFT HORIZONTAL ST'ABILI'ZER WHICH WAS EITHER BROKEN
.?A'E DUE TO EXCESSIVE AIR LOADING OR WAS STRUCK FY THE LEFT WING A`3
CAME OFF. THIS IS THE ONLY 'MAJOR 'PROTION NOT YET LOCATED,
ACCIDENT ALTHOUGH WITHIN THE LIMITATIONS STATED IN THE HANDBOOK
WAS IN ALL PROBABILITY THE CAUSE OF THE STRUCTURAL FAILURE OF THE
LEFT WING. WHEN A ROLLING MOMENT IS SUPERIMPOSED ON THE WING WHILE,
if IS SUBJECTED TO AN APPLIED ??G` FORCE THEN THE WING SUFFERS A
TWISTING MOMENT AS WELL AS A BENDING MOMENT. THIS HAS CAUSED
FAILURES IN THE PAST SEVERAL TYPES OF AIRCRAFT AND THE "G
LOADING THAT MAY BE APPLIED IS SEVERELY REDUCED WHENEVER IT AS
COMBINED WITH A ROLLING MANEAUVE3.
7. THE FUEL PLACEMENT WAS ADVERSELY LOCATED EVEN BEFORE THE
TIME OF THE ACCIDENT. WHICH COULD ONLY HAVE CONTRIBUTED TO THE
'NFAVORABLE WING LOADING. THIS F*UEL PLACEMENT IN THE AUXILLARY
'BANKS WAS REQUIRED FOR THE TYPE OF OPERATION THE PILOT WAS ENGAGED
;ii AND WAS IN ACCORDANCE WITH THE HANDBOOKO
UTED BY THE PILOT JUST PRIOR TO THE
25X1A
c; C T11 E T
Approved For Release 2002/06/18 : CIA-RDP74B00447R000100010037-1
R E T PAGE 2
 Approved For Fease 2002/06/18: CIA-RDP74B00447Q00100010037-1
D T`{_ATHE PILL DID NOT EXCEED THE
Scy _ riTRCRA ` AS INDTCATED IN THE FLIGHT ST'SEN1G.TH
'~. r iJS, THESE 1,11A GRAMS ;D EVE , DO NOT TAKE INTO ACCOUNT
HIh ' XCnFT A I RAIGYTFORWARD POSITIVELY APPLIED .'G" FORCE AT
a i '~ A R ~ LIP
t S. IR ~" Y t 'Q U.. 'T d)Te AT.cO~.Sf "I A,L L WEIGH SiNU
1E i O"S E' GHT FOOT WAS RIPPED IN SUCH A {TANNER THAT
aD
S S TO SUSF'FC;T A HIS OA DACE TO HAVE TEEN CAUSED PY THE CANOPY
:NG LEVER ON EJECT.1ONa
RECOh3h1ECJDATTONS9 A, A RESTRICTION BE PLACED ON POLLING
NANE,AUVERS WHILE POSITIVE "G" IS PEING APPLIED TO YD{ AIPCRI(l), "
TICULARLY AT HIGHER SPsrF.DS AS DETERMINED PY LAC.,
~. IHE FUE1. PI,A_'.~ MFN.NT NOT "`0 BE SUCH THAT A CONDITION
ARRIVED AT WN REPY THE AUXTLI 'RY TANKS ARE FULL, AND THE
ANKS E MPTY
C T' T i_;,r CONDUCT THE SERIES OF INSPECT TONS THEY DE1.!*
ADVISABLE.
RIC'F! HAND CANOPY 3,t"'?CKING LEVER FE RELOCATED SO
HAS! WHEN THE CANOPY IS JETTI SOCK;; D THE LEVER DOES NOT ROTATE TO
THE DOWNWARD POSITION THUS CAUSI"'G A I AZARD TO SAFE EJECTION.
MODIFICATI.ON PE MADE TO THE LAP BELT AND AUTOMATIC
DISCONNECT SYSTEM SUCH THAT THE PILOTS Ci,OTHTN( IS NOT SUEJECTFI)
TO :BURN DAMAGE,
r.I TEQUFST HOIRS NA}F FUR! J{T,, 1
R DISTRIBUTION OF T ITS R P
41,
DESIRED,
q- T
Approved For Release 2002/06/18 CIA-`P,6P74B 0447R000100010037-1