(UNTITLED)

Document Type: 
Collection: 
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
Case Number: 
Publication Date: 
May 23, 1963
Content Type: 
CABLE
File: 
AttachmentSize
PDF icon CIA-RDP71B00590R000200030017-4.pdf357.92 KB
Body: 
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 3933 25X1A 25X1A ROUTINE Approved For Releair2000/05/05 : CIA-RDP71 80059000200030017-4 25X1A SECRET 9733 (du PAGE TWO 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 Approved For Release 2000/05/05 : CiSA6P71 00590R000200030017-4 Approved For.Relea 2000/05/05: CIA-RDP71 BOO59 00200030017-4 25X1 A 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* Approved For Release 2000/05/05: CIA-RDP71 B00590R000200030017-4 0 9 E C R E T Approved For Relea 2000/05/05: CIA-RDP71 B0059W000200030017-4 25X1A 973' (IN 78166) S E C R-SET PAGE FOU t 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 Approved For Release 2000/05/0.%: LS16-IRD' 1 B00590R000200030017-4 Approved For ReleaW2000/05/05: CIA-RDP71 80059 000200030017-4 25X1A 9733 (ON 8 66 ) SE CRET PAGE. F I VE 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