(UNTITLED)

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP71B00590R000200030017-4
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 5
• Document Creation Date: November 16, 2016
• Document Release Date: March 16, 2000
• Sequence Number: 17
• Publication Date: May 23, 1963
• Content Type: CABLE

Aproved For Relea2000/05/05 CIA-RDP71'B0059W0
a
DIRECTOR
OSA (PS-?5)
SiCC16)
25X1A
25X1A TOR', 0125Z 350 MAY 1963
25X1A
OXC ART
1 u COL LEDFORD AND COI: (TEARY FROM
HAS SUBMITTED A SUMMARY OF BOARD PROGRESS TO DATED 29 MAY 63.
IT IS QUOTED BELON FOR YOUR INFORMATION.
A, ENt;I EESm AL l ENGINE ACCESSORIES HAVE BEEN RECOVERED
AND SENT TO UADq CONN. FOR TORO MAJOR COMPONENTS OF COM-
PRESSOR AND TURBINE F OM BOT4 ENGINES HAVE BEEN EXARINED
FOR ROTATIONAL DAMAGE',, LEFT HAND ENGINE S4OVS SUBSTANTIAL
ROTATIONAL L` ;=PAGE IND: CATIVE OF HIGH RPM All IMPACT, RIGHT HAND
ENGINE SHO V~:; LITTLE ROTATIONAL DAMAGE INDICATIVE OF LO RPM
AT IMPACT, EXTERNAL EXAMINATION OF ENGINES HAS NOT SHOWN ANY
INDICATION ENGINE FAILURE. INVESTIGATION VILL CONTINUE IN
AREA OF ACCESSORIES; BASIC ENGINE AND AFTERBURNER, AND FUEL
SYSTEM.
9m INS, AT SOME INSTANT OF TIME BEFORE IMPACT, THE INS
PLATFORM LOST REFERENCE, THE SYSTEM WAS APOARENiTLY FUNCTIONING
PROPERLY AS THE INITIAL DECELERATION BEGAN? THERE IS NO EVIDENCE
Approved,
gl ase 2000!0x/05. ; CWRDP 1 P09590
606,6300,17-4
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OF SYSTEM NALFUNC T IO OTHER THAN THE POSSIBLE LOSS OF POWER BE-
TWEEN DECELERATION AD IMPACT. ALL READOUT PANELS WERE
JAMMED AT REASONABLE VALUES AND CORRESPOND TO THE
APPROXIMATE COORDINATES OF IMPACT. JUDGING FROM THE CONDITION
OF THE PLATFORM STABLE ELEMENTS IT WAS INVERTED ON IMPACT, WHIC '
WOULD NOT BE THE CASE IF THE SYSTEM WERE FUNCTIONING PROPERLY. THE
CONDITION OF OTHER ASSOCIATED EQUIPMENT IN THE SYSTE T INDICATES
THAT IMPACT OCCURRED IN A NOSE DOWN, INVERTED ATTITUDE. THE IN-
DICATED GROUND SPEED GENERATED BY THE SYSTEM WAS JAMMED AT 308
KNOT S.
C. MAINTENANCE AND AIRCRAFT RECORDS: INSPECT ION OF AIRCRAFT
MAINTENANCE RECORDS DID NOT REVEAL ANY FACTOR WHICH IS CONSIDERED
CONTRIBUTORY TO THE CAUSE OF THE ACCIDENT.
Da OPERATIONS GROUP3 CREW RESTS PHYSICAL CONDITION, PSYC4OLO-
CICAL FACTORS AND QUALIFICATIONS HAVE BEEN STUDIED AND DO NOT
APPEAR TO BE A FACTOR IN THE ACCIDENT. WEATHER WAS AS FORECAST
AND DOES NOT APPEAR TO HAVE BEEN A PRIMARY CAUSES BUT MAY HAVE
CONTRIBUTED TO THE ACCIDENT. THE PLANNED GROUND TRACK WAS
FLOWN ESSENTIALLY AS BRIEFED WITH ALTITUDE MODIFICATIONS
DUE TO CLOUD CONDITIONS. WEATHER OVER CHECK POINTS
PRECLUDED VISUAL IDENTIFICATION OF AUSTIN9 NEVADA DURING BOTH
CIRCUITS OF THE ROUTE AND ALSO OF WENDOVER9 UTAH9 DURING THE SECOND
CIRCUIT. VISUAL IDENTIFICATION OF OTHER CHECK POINTS CONFIRMED
PROPER OPERATION OF INS. DURING LAST TURN OVER WENDOVER, UTAH
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i N X816.) PACE TH
? R D T Or PUT ER t??itsC ^: READOUT WAS OBSERVED TO INDICATE SUPER-
SONIC FLI Wf INSTINCTIVE CORRECT IONS TO REDUCE AIR SPEED WERE
AT 1 F-N" l F.D A r t3.. EF UI\/ALEN"i AIR SPEED RESULTED6 LEVEL
OFF AND THROTTLE ADI ,,CEMENT FAILED TO CHECK AIR SPEED BLEED
OFF'- MILD ~I.TCg~a CORRECTIONS FAILED TO CHECK AIR SPEED BLEED OFF
AND THE AI (CRAFT DE SC'ENDED INTO THE CLOUDS IN A WINO LEVEL A1'TI-
TUDE. LOSS OF C(ANTROL OCCURRED AT 10 KEAS AND RECOVERY EFFORTS
WERE UNSUCCESS -'?J .L AND THE PILOT ABANDONED THE AIRCRAFso OXYGEN
SYSTEMS APPEARED TO FUNCTION NORMALLY; OXYGEN MOISTURE CHECKS FROM
THE SOURCE USED O SERVICE THIS AIRCRAFT ARE NEGA`'IVE~ HOWEVER9
PURITY CHECX, ARE NOT COMPL.LETEO
E. FLIGHT CONTROLS. THE FLIGHT CONTROL SYS3'EM APPEARS TO
HAVE BEEN "> NTACT' AND OPERABLE TO THE POINT OF IMPACT. THE ELEVON
TRIM WAS RECOVERED IN THE FULL NOSE DOWN POSITION. THE COCKPIT
THROTTLE CONTROLS WERE FOUND AT THE 93 PERCENT RPM POSIT ION -
.75 INCHES FR?; M, THE 9" PERCENT POSITION.
F. IN5TRuP EENT"s, MOST INSTRUMENTS HAVE BEEN LOCATED, BUT
READINGS CANNOT BE DETERMINED UNTIL MECHANISM DISPLACEMENTS ARE
ANALYZED.
G. OXYGEN AND PRESSUR TZAT IONA THE OXYGEN DRYNESS HAS BEEN
CHECKED OUT MIN S 95 DEGREES F DEW POINT. THE DUAL, OXYGEN" SYSTEMS
AT THIS TIME DC NOT SxOV ANY EVIDENCE OF MALFUNCTION'o OXYGEN PURI-
TY IS BEING CHECKED IN THE LABORATORY*
H, ELECTRICAL. BASED UPON THE PILOTS REPORT OF THE COCKPIT
CONDITION, NO ELECTRICAL MALFUNCTION IS EXPECTED. THE STATE OF THE
DEBRIS MAKES IT IMPOSSIBLE TO DETERMINE THIS*
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I. FUELS SAITIPnES OF TYPICAL FUEL USED IN THIS FLIGHT AND FUEL
FROM AIRPLANE 124 ARZ BEING ANALYZED FOR WATER CONTENT. THE FUEL
STRAINERS ARE SEALED FOR LABORATORY CHECK OF WATER CONTENT. THESE
SYSTEMS ARE STILL BE ..T G INVESTIGATED TO EXPLAIN LOW FUEL FLOWS
(1800 PP) .
J. S RUC?TURE,o a HE AIRCRAFT STRUCT URE, INTACT EXCEPT FOR ITEMS
LISTED BELOW STRUCK THE GROUND IN AN INVERTED ATTITUDE ." THERE
DOES NOT APPEAR TO HAVE BEEN ANY PRIMARY STRUCTURAL FAILURE..
THESE ITEMS LEFT THE STRUCTURE BEFORE IMPACT:
(1) PILO ? S CANOPY
(2) PILOT'S SEAT AND JETTISONING HARDWARE.
(3) MIS>CELLANTC)US PIECES OF COCKPIT TRIM. INSULATION.
RECORDER AND FLIGHT CORDS.
(4) SMALL FRAGMENTS OF HONEYCOMB MATERIAL.
2. RECOMMENDATIONS:
A. EVEN THOUGH THE FOLLOWING ITEMS MAY OR MAY NOT HAVE CONTRI49
BUTED TO THE ACCIDENT UNDER INVESTIGATION. IT IS RECOMMENDED THAT
THE FOLLOWING ACTIONS BE TAKEN PRIOR TO CONTINUATION OF FLYING
WITH 121 AND 124.
(1) RECONFIGURE THE ELECTRICAL SYSTEM SO THAT INVERTOR
NUMBER TWO WILL AUTOMATICALLY AND, IF NECESSARY'S MANUALLY CHANGE
OVER TO REPLACE A FAILURE ON NUMBER ONE INVERTOR, THIS IS BEING DONE.
LAC WILL GIVE BOARD A STATUS REPORT 3 JUNE ON THIS aUBJECTo
Q) INSTALL A CRASH RESISTANT FLIGHT RECORDER FOR USE
DURING TEST AND TRAINING PHASES OF THIS PROGRAM THAT WILL MEASURE
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ALL PRIMARY SOURCES ' FLIGHT DATA. LAC 1 ILL GIVE BOARD A STATUS
REPORT 3 JUNE ON THI SUBJECT..
(3) INSTALL AN ANGLE OF ATTACK INDICATOR IN ALL AIRCRAFT.
DATA ALREADY AVAILABLE IN 121. INSTALLATION OF INDICATOR WILL
BE ACCOMPLISHED,
(4) RESTRICT SUBSONIC FLIGHTS IN LOW TEMPERATURE ENVIRON
MENTAL CONDITIONS TO TIME EQUAL TO TEST FLIGHT TIMES ACCOMPLISHED
BY THE CONTRACTOR UNTIL FURTHER TESTS ARE MADE TO DETERMINE POSIT
JIVE TEMPERATURE SINE OF FUEL AT CRITICAL POINTS,*
NOTES FLIGHTS ON AIRCRAFT 124 COULD BE CONTINUED WITHOUT ACCOMPLISH-
MENT OF (2) AMD (3) ABOVE UNTIL HARDWARE IS AVAILABLE PROVIDED TWO
RATED PILOTS ARE ABOARD.
B. RECOMMENDAT DONS REGARDING 1229 1259 126 AND 127 ARE WITH
HELD PENDING FURTHER FINDINGS BY THE BOARD AND INVESTIGATIONS BY
THE CONTRACTOR OVER ",'-14E WEEKEND.
END Of MESSAGE
S E C R E T
Approved For Release 2000/05/05: CIA-RDP71 B00590R000200030017-4