Interim Report - twa800.comtwa800.com/report/flt800.pdfInterim Report. 7/21/98 TWA Flight 800 Investigation 2 Order of Events m Introductions ... Thus far they have generated more

7/21/98 1

on the

Crash of TWA Flight 800and the

Actions of the NTSB and FBI

Cmdr. Bill Donaldson, USN/Ret.And the

Associated Retired Aviation ProfessionalsJuly 17, 1998

Interim Report

7/21/98 TWA Flight 800 Investigation 2

Order of Events

m Introductionsm Opening Statementm Formal Brief, Report Overview

» Cmdr. Donaldson

m Witness Comments & Expert Availability» Captain Mann» Captain Mundo» Mr. Gipe» Major Meyer» Mr. Goss» Cmdr. Donaldson

m Final Comments» Admiral Thomas Moorer, Former Chairman - Joint Chiefs of Staff


Introductions

m Cmdr. William S. Donaldson, USN Ret.

m Captain Howard T. Mann, TWA Ret.

m Captain Albert Mundo, TWA Ret.

m Major Fredrick Meyer, USN / ANG Ret. - Eyewitness

m Mr. Albert Gipe, Consulting Engineer - Eyewitness

m Mr. Richard Goss, Businessman - Eyewitness

m On Tape

» Mr. Paul Angelides, Consulting Engineer - Eyewitness

» Captain Randy Adams, Scallop Boat Skipper - Eyewitness

» Captain Roland Penny, Tug Skipper, Ret. - Eyewitness


Opening Statement

Two years after the crash of TWA Flight 800 the NTSB still does not have an answer asto what caused the crash. They have theorized that the Center Fuel Tankspontaneously exploded, yet they have not been able to find an ignition source, or anyother conclusive evidence that supports this theory, except the fact that the aircraftcrashed. Thus far they have generated more questions than answers. They say theyhave been looking for the “Smoking Gun” but have been unable to find it.

Our 16 month investigation has successfully correlated witness testimony to thephysical evidence. All point conclusively to one cause for the crash - a proximity fused,airbursting anti-aircraft missile exploded below and to the left of the nose of the aircraft.

Hundreds of eyewitnesses believe they saw a missile shoot down TWA Flight 800. Theyhave been ignored, intimidated and insulted by agencies of the federal governmenttrying to prove they didn’t see what they did. The CIA produced a slick video of thecrash which has been widely shown by the news media. It shows the aircraft climbing3,000’ trailing burning fuel in an attempt to explain away eyewitness statements. Theproblem with this video is that it is not only aerodynamically impossible and fails todepict what the aircraft actually did, but insults the intelligence of professionals whoknow a climbing 747 would never be described as streaking by anyone.

This report proves that the witnesses were right and the government is hiding the truth.


Contents

m Why the NTSB’s Theory is Wrong!

m Evidence Supporting a Missile

m Eyewitnesses

m Evidence of a Cover-up

m Conclusion


NTSB’s Mechanical Theory is Wrong

m Internal Ignition Impossible - Boeing Design Criteria

m 150,000 Years of Flight Time

m Fuel Properties, Aviation Fuels Handbook

m NTSB Comments on Properties of Fuel

m Contract Tests

m Flammable vs. Explosive Tank

m Hot Tank Scare - June 1997

m Videos of Explosive Tank - Hydrogen vs JetA fuel


Fuel Tank Sumps


NTSB’s Mechanical Theory is Wrong

m October 1997 Fuel Temperature Test

m Letter to Hall

m NTSB Copies Simple Fuel Temperature Test

m FBI Comment

m Verification Tests, 185° F vs. 127° F

m The Learning Channel, Government Spin

m Tank Implosion

m CW 504


Center Wing Tank Water Scavenge Pump

Captain Mundo Scavenged the Center Wing Tank


Fuel Tank Vent System


Location of CW 504


Center Wing Tank


Front Spar - Center Wing Box - looking aft.

Floor Beam buckled upward

CW 504

39’ 00”

38’ 20”

38’ 30”

38’ 40”

38’ 50”

39’ 10”

39’ 20”

39’ 30”

39’ 40”

39’ 50”

38’ 10”

39’ 3

0”

37’ 2

0”

37’ 3

0”

37’ 4

0”

37’ 5

0”

38’ 0

0”

38’ 1

0”

38’ 2

0”

38’ 3

0”

38’ 4

0”

38’ 5

0”

39’ 0

0”

39’ 1

0”

39’ 2

0”

39’ 4

0”

39’ 5

0”

37’ 0

0”

37’ 1

0”

36’ 5

0”

36’ 4

0”

36’ 3

0”

36’ 2

0”

36’ 1

0”

40’ 0

0”

V10 Vert Stab

#4 Engine parts

#4 Engine & StrutRW13

LW 42

LW 30

H6, HW12 Stab Skin

RW 22

#3 Engine

#4 Engine, LF 75, CW117, CW114, LW41

LW01, LW02

LF02

29 Line Items, Right Wing Spar, RW19 & 4 fuel Parts

65 Line Items, LF62, LF73A, RF106, & 12 R&L Fuselage

# 1 Engine

# 2 Engine, 8 Parts, RF45C, FS 1920-1960 plus RF26a, RF97, RF27, RF448, RF100, CW218, FS 1870-2340

CW235, 236 Lower Center Wing Skin

# 2 Engine, 4 Parts

Engine exhaust cone, Fan reverser, portion of engine, Forward belly skin

RF114a window & fuselage

Front Spar RBL65-112, CW 519

Right Wing fuselageFS1140-1390, CW105, RW08, CW8, RW03, CW202, RF17

140 Line Items Fuselage, LW49 Left wing Tip, HF antenna

RW06, Wing skin, RW29, Rw12TWA Flight 800 Debris Field

72o W. Longitude

40o N

. L

atit

ud

e

E

N

W

S

Pre Explosion Flight Path = 071o True

Pilot OP Man

11 Line items

289 Line items:Cockpit, RF18a LF22-04,LF11d, FR18c, LF07a,LF11J, RF70, LF07B,RF90, RF03d, LF07c,LF22-27, LF30f, RF85,RF18f, LF20, RF03h,LF04, RF04, RF79,RF83, LF22-34, LF08a,LF11h, Nosegear wellforward bulk, RF31, LF01,RF18f, RF82, LF11c,Nose well structure & 22more items.

Radome

RF29, FS800-860

RF20, FS940-1000CW703, SWB #2, RBL 8-30

Forward Cargo Bay, FS900

Forward Lover Cargo Bay, FS 860 Left Side

Forward Lower Cargo Bay, FS880, Center line.

2’ x 6” #3 SWB

LF 12a, FS940-820, RF87, FS 270-290, RF 84, FS 400-420, RF 89, FS360-400, RF 107, FS 300-340,RF88, FS 260.

FBM 19 Floor Assmb, 780-840 / Fuselage Skin x 3 Belly Skin

Light Frame, 4” x 4’, 3” hole.

Row 11, Seats 1,2,3

Row 12 Seats4,5,6,7

Nose Gear / Hatch / RH Wheel Well Door 6’

Row 22, Seats 4,5,6 Right Nose Gear Door

LF 43, Fwd Lower Cargo 920 Left, LF 55b

Forward Lower Cargo LEFT, FS 1000

Forward Lower Cargo Bay, FS 1000, LEFT HAND SIDE

LF 58a, ForwardLower Cargo Bay,FS 960

LF 44, LH Fwd LNR, FS 940

CW 514

RH Fwd Lower Cargo, FS 820

CW 512, RBL 66-45 CW Tank,Front Spar

Row 14, Seats 4,5,6

LW 05 / LW04 Upper & Lower Left Wing Tip Skin Row 23,Seats4,5,6

LF37a, FWDlower cargo left,FS800

Row 23 Seat 4

Row 15 Seat 1.2.3

Row 12 Seat 10

Row 15 Seat 4,5,6

Row 18 Seat 8-10

Floor Beam 800, RBL 55-70

Row 14 Seat 8,9,10

Row 21 Seat 1.2.3

Row 10 Seat 8,9,10

Row 15 Seat 8,9,10Row 11 Seat 8,9,10

CW 305 / CW 304

Gear Door

RF 07, FS 800-840

LF 05, FS 780-920

CW 515, LBL 60-95

CW 502, Wg FT Spar, LBL 20-70

CW 501, RBL 66 - LBL 28

RF 32, Right Belly FS 800-940 / LF31, FS 800-840 Center

Row 20, Seat 4,5,6,7

Galley

Wing Part, (Antenna)

RF 01, FS 760-960 // LF 14a Keel Beam // Floor Beam & PanelVictim

RF 05, R2 Door

Forward Lower Cargo Bay LH FS 900-960

LH Tube, Front Spar

#3 Air Pack

Air Conditioning Scoop

FWD L/H Cargo FS 800-840

CW 504

10,126 feet

Row 18 Seat 4,5,6,7

Row 19 Seat 8,9,10

Row 19 Seat 6,7

Row 19 Seat 4,5

1,026 ft

~ 8,000 ft.

Debris Field Length = ~ 18,138 ft.

Fwd Lower Cargo Bay, FS 800-1000

Fwd Lwr Cargo Bay, Uppr track roller

Right Belly and Cargo, FS 800-940, stringer 37R-44R

Wind Velosity Vector 24 ft/sec - 123 o T

~ 6,000 ft.

78 Line items: LF11K, LF11L FS400,LF30C FS 260-80, LF11 FS 400, RW1,S9, LF11a FS 260, LF08a FS 140,RF080 FS240-287, R1 Door top, RF113,RF18b, RF03b RS 600-640, RW07 RHwing upper skin plank, CW704, LF18Nose Wheel Well side

Rate of Fall in Feet / S

ec.

500/400 300 200 f/s 100

40 Line items: Cargo door skin, RF fwd,Cargo Floor, Right side cargo door, FS 640-760, fwd cargo door lift, cockpit debris,avionics bay, fwd portion lower right cargodoor, FS 560-670, multiple cargo bins,RF78,RF08e, LF25, RF80, LF22-02, RF92, RF06c,RF24, LF22-24, LF23, RF81, RF22-01, RF25.

Updated 5/19/98

Legend:Red = Seats & Misc.Green = Nose PartsBlue = Terminal FieldPurple = Cargo BayOrange = Center WingBrown = Wing PartsBlack Star = Nose GearRed Star = Tail Parts

Latitude

1” = 101.26 ft.10” = 1,012.60 ft.1’ = 6,076.10 ft.

Scale Longitude

1” = 76.99 ft.10” = 769.90 ft.1’ = 4,619.40 ft.

No Wind Fall Line

Row 21, Seats 4,5,6

Row 19 Seat 1,2,3

Cargo Door, 7’x3’x1’

Part of CWTFW Lower Cargo Bay, FS 920 right hand side

Beam CW rear spar, SWB#1 web, mid sparCW stiffner, CW upper skin

lowe CW skin panel, RBL 0, RBL 110, RBL 98, stringer 9,13-14 FS 920 frame, stringer 33l-35L

44 line items SWB #1, right hand closure panel

SWB #2, LBL 93.48 web, CWupper skin, 5 pieces

13 line items,SWB #1, CWstiffner, CWupper skin, rightSOB

769 ft

Part of Tire

RH NoseWheel & Tire

Nose Wheel FS 340 LH side

Horizontal Stabilizer Fairing

Center Wing Tank - Last of Three Explosions

7/17/98 Page 44TWA Flight 800 Investigation - Copyright W. S. Donaldson, III

CW 504

CWT Explosion


Bruntingthorpe - A Disaster for NTSB Theory

m 8 lbs. of Propane

m Fragmentation Patterns

m Sound Patterns

m CVR Analysis Working Group

» Not allowed to see their own test data

» Not allowed to reconvene

m Bruntingthorpe Test Data withheld from TWA & Boeing


Fuel Tank Explosion History

m 1959 Lockeed Super Constellation, Milan

m 1967 Boeing 707, Rome

m 1976 Iranian 747, Madrid

m 3 Air Force KC 135 Tankers

m 1990 Philippines Airlines 737, Manila

m NTSB’s Congressional Testimony

AVGAS

JP4

JP4

JP4

Jet A


Evidence of Warhead Burst

m Debris Field - 3 Explosionsm High Energy Breakup Sequence

» Nose, Tail & Wingm Boeing Energy Statementsm NTSB Energy Calculationsm Nose Gear Breakup - .82 mach

» Fuselage Witness Marks» Horizontal Stabilizer Impact Marks

m Left Upper Wing Skin Fragmentationm Center Tank Implosion Evidencem Aircraft Rolls Overm Vertical Stabilizer Failurem Locations of Recovered Seatsm Locations of Recovered Bodiesm High Velocity Shrapnel in Bodiesm High Velocity Holes in the Aircraft - Forward left sidem Airburst Displacement of the Aircraftm Cockpit Voice Recorderm Flight Data Recorderm Inertial Navigation Systemm Fuselage Failure - In Tension & Compression

39’ 00”

38’ 20”

38’ 30”

38’ 40”

38’ 50”

39’ 10”

39’ 20”

39’ 30”

39’ 40”

39’ 50”

38’ 10”

39’ 3

0”

37’ 2

0”

37’ 3

0”

37’ 4

0”

37’ 5

0”

38’ 0

0”

38’ 1

0”

38’ 2

0”

38’ 3

0”

38’ 4

0”

38’ 5

0”

39’ 0

0”

39’ 1

0”

39’ 2

0”

39’ 4

0”

39’ 5

0”

37’ 0

0”

37’ 1

0”

36’ 5

0”

36’ 4

0”

36’ 3

0”

36’ 2

0”

36’ 1

0”

40’ 0

0”

V10 Vert Stab

#4 Engine parts

#4 Engine & StrutRW13

LW 42

LW 30

H6, HW12 Stab Skin

RW 22

#3 Engine

#4 Engine, LF 75, CW117, CW114, LW41

LW01, LW02

LF02

29 Line Items, Right Wing Spar, RW19 & 4 fuel Parts

65 Line Items, LF62, LF73A, RF106, & 12 R&L Fuselage

# 1 Engine

# 2 Engine, 8 Parts, RF45C, FS 1920-1960 plus RF26a, RF97, RF27, RF448, RF100, CW218, FS 1870-2340

CW235, 236 Lower Center Wing Skin

# 2 Engine, 4 Parts

Engine exhaust cone, Fan reverser, portion of engine, Forward belly skin

RF114a window & fuselage

Front Spar RBL65-112, CW 519

Right Wing fuselageFS1140-1390, CW105, RW08, CW8, RW03, CW202, RF17

140 Line Items Fuselage, LW49 Left wing Tip, HF antenna

RW06, Wing skin, RW29, Rw12TWA Flight 800 Debris Field

72o W. Longitude

40o N

. L

atit

ud

e

Pre Explosion Flight Path = 071o True

Pilot OP Man

11 Line items

289 Line items:Cockpit, RF18a LF22-04,LF11d, FR18c, LF07a,LF11J, RF70, LF07B,RF90, RF03d, LF07c,LF22-27, LF30f, RF85,RF18f, LF20, RF03h,LF04, RF04, RF79,RF83, LF22-34, LF08a,LF11h, Nosegear wellforward bulk, RF31, LF01,RF18f, RF82, LF11c,Nose well structure & 22more items.

Radome

RF29, FS800-860

RF20, FS940-1000CW703, SWB #2, RBL 8-30

Forward Cargo Bay, FS900

Forward Lover Cargo Bay, FS 860 Left Side

Forward Lower Cargo Bay, FS880, Center line.

2’ x 6” #3 SWB

LF 12a, FS940-820, RF87, FS 270-290, RF 84, FS 400-420, RF 89, FS360-400, RF 107, FS 300-340,RF88, FS 260.

FBM 19 Floor Assmb, 780-840 / Fuselage Skin x 3 Belly Skin

Light Frame, 4” x 4’, 3” hole.

Row 11, Seats 1,2,3

Row 12 Seats4,5,6,7

Nose Gear / Hatch / RH Wheel Well Door 6’

Row 22, Seats 4,5,6 Right Nose Gear Door

LF 43, Fwd Lower Cargo 920 Left, LF 55b

Forward Lower Cargo LEFT, FS 1000

Forward Lower Cargo Bay, FS 1000, LEFT HAND SIDE

LF 58a, ForwardLower Cargo Bay,FS 960

LF 44, LH Fwd LNR, FS 940

CW 514

RH Fwd Lower Cargo, FS 820

CW 512, RBL 66-45 CW Tank,Front Spar

Row 14, Seats 4,5,6

LW 05 / LW04 Upper & Lower Left Wing Tip Skin Row 23,Seats4,5,6

LF37a, FWDlower cargo left,FS800

Row 23 Seat 4

Row 15 Seat 1.2.3

Row 12 Seat 10

Row 15 Seat 4,5,6

Row 18 Seat 8-10

Floor Beam 800, RBL 55-70

Row 14 Seat 8,9,10

Row 21 Seat 1.2.3

Row 10 Seat 8,9,10

Row 15 Seat 8,9,10Row 11 Seat 8,9,10

CW 305 / CW 304

Gear Door

RF 07, FS 800-840

LF 05, FS 780-920

CW 515, LBL 60-95

CW 502, Wg FT Spar, LBL 20-70

CW 501, RBL 66 - LBL 28

RF 32, Right Belly FS 800-940 / LF31, FS 800-840 Center

Row 20, Seat 4,5,6,7

Galley

Wing Part, (Antenna)

RF 01, FS 760-960 // LF 14a Keel Beam // Floor Beam & PanelVictim

RF 05, R2 Door

Forward Lower Cargo Bay LH FS 900-960

LH Tube, Front Spar

#3 Air Pack

Air Conditioning Scoop

FWD L/H Cargo FS 800-840

CW 504

Row 18 Seat 4,5,6,7

Row 19 Seat 8,9,10

Row 19 Seat 6,7

Row 19 Seat 4,5

~ 8,000 ft.

Debris Field Length = ~ 18,138 ft.

Fwd Lower Cargo Bay, FS 800-1000

Fwd Lwr Cargo Bay, Uppr track roller

Right Belly and Cargo, FS 800-940, stringer 37R-44R

Wind Velosity Vector 24 ft/sec - 123 o T

~ 6,000 ft.

78 Line items: LF11K, LF11L FS400,LF30C FS 260-80, LF11 FS 400, RW1,S9, LF11a FS 260, LF08a FS 140,RF080 FS240-287, R1 Door top, RF113,RF18b, RF03b RS 600-640, RW07 RHwing upper skin plank, CW704, LF18Nose Wheel Well side

Rate of Fall in Feet / S

ec.

500/400 300 200 f/s 100

40 Line items: Cargo door skin, RF fwd,Cargo Floor, Right side cargo door, FS 640-760, fwd cargo door lift, cockpit debris,avionics bay, fwd portion lower right cargodoor, FS 560-670, multiple cargo bins,RF78,RF08e, LF25, RF80, LF22-02, RF92, RF06c,RF24, LF22-24, LF23, RF81, RF22-01, RF25.

Updated 5/19/98

No Wind Fall Line

Row 21, Seats 4,5,6

Row 19 Seat 1,2,3

Cargo Door, 7’x3’x1’

Part of CWTFW Lower Cargo Bay, FS 920 right hand side

Beam CW rear spar, SWB#1 web, mid sparCW stiffner, CW upper skin

lowe CW skin panel, RBL 0, RBL 110, RBL 98, stringer 9,13-14 FS 920 frame, stringer 33l-35L

44 line items SWB #1, right hand closure panel

SWB #2, LBL 93.48 web, CWupper skin, 5 pieces

13 line items,SWB #1, CWstiffner, CWupper skin, rightSOB

Part of Tire

RH NoseWheel & Tire

Nose Wheel FS 340 LH side

Horizontal Stabilizer Fairing

High Energy Breakup - Nose, Tail & Wing

7/17/98 Page 44TWA Flight 800 Investigation - Copyright W. S. Donaldson, III

CW 504

CWT Explosion

Nose

TailRearSeats

Eyewitness CaptainAdams

Nose Gear Doors


Damage to Landing Gear Doors

Nose Gear DoorsCenter Wing Tank

m Gear Doors 62 feet from Center Wing Tankm Gear Door Damage & Location in Debris Fieldm Tire Witness Marks above R3 Doorm Tire Witness Mark on Horizontal Stabilizer


Airburst - First 40 Milliseconds

20ms30.4 psi 30ms

9.0 psi

40ms3.8 psi

30.4 psi

9.0 psi

3.8 psi

30.4 psi

9.0 psi

3.8 psi


105 ms Loud Sound

Doppler location offirst shockwaveimpingement: Basedon “105ms LoudSound” on theCockpit VoiceRecorder Aircraft Station 667

Aircraft Station 738

48.1 ft.

54 ft.FromNose

Shockwave traveling aft,after first strikingfuselage at A/S 738 willproduce a 105ms soundin the cockpit.

Shockwave travelingforward, after firststriking fuselage at A/S667 will produce a105ms sound in thecockpit.


Exhibit 22 - Location of Recovered Bodies in the Debris FieldExhibit 22 - Location of Recovered Bodies in the Debris Field

The first body located in theearliest part of the debris fieldcame from Aircraft Station 615,Row 10, Seat 2.

The first body located in theearliest part of the debris fieldcame from Aircraft Station 615,Row 10, Seat 2.


High Energy Damage


Skin Pedaled Outward


Upper Wing Skin Fragmentation


Flight Data Recorder


Angle of Attack

Airstream

Aircraft Longitudinal AxisNose Pitched up 3.6 degrees

Angle of Attack Sensor

Angle of Attack (3)

Time 20:31:11

Airstream

Aircraft Longitudinal AxisNose Pitched up 8.3 degrees

Angle of Attack (106)Moves to past the vertical

Time 20:31:12

Detonation


Shockwave Effect on Engine Pressure Ratios

25 ms

50 ms

85 ms60º

45º89º2.0 psi

2.0 psi

83º

.5 psi

12 psi


Model Demonstration

m Pitch

m Yaw

m Drift

m Nose Tire

m Witness Marks

m Horizontal Stabilizer

m Number 3 Engine

m Vertical Stabilizer


Triangulation of Witnesses Bearings

Faret & Wendell

Penny

Gipe

GabreskiAirport

TWA 800

30 K

NO

T TA

RG

ET

Last ISP TWA Beacon Return @ 2031:11.27

20 Knot Target

Meyer & Baur

Shinnecock Inlet

Moriches Inlet

SecondLaunchPoint

Bell Port Dock

Smith Pt.Cupola

Bilodeau & McBrideCurreri

Goss

223°

T

106°T

170°T

156°T

104°T

090°T

068°T

Perry

Witness X

FirstLaunchPoint

StationaryTarget

Dougherty

Adams


Anti-Aircraft Missiles

m Man Portable Air Defense Systems - MANPADS» Too small, too slow, too low.» IR guidance, erratic flight path, very small warhead» Low visibility during rocket burn» Low sound and shockwave profile» Contact fused

m Standard Sized Anti-Aircraft Weapons» 100+ lb.Warhead» 10+ mile range» Stable Flight Path» High visibility during rocket burn» Loud launch & rocket burn noises & sonic shockwave» Proximity fused

m Examples of Full Sized Anti-aircraft missiles» Phoenix» Sparrow


Location of VOR DME Transmitter Antennas


Evidence of a Cover-up

m Eyewitness Special Agent George Gabriel - Secretm Bruntingthorpe Tests Data - Secretm Debris Field Data - Secretm Eyewitness Testimony - Secretm Identification of Surface Radar Contacts - Secretm FBI Briefing of Missile Launch Position - SA Steve Bongartm White House Reaction, Kobar Towers and Flight 800 Warningm Executive Order 13039 on 11 March 1997 - 1 day after Sallingerm Falsification of Debris Field Database - Linda Kuntz Storym Radar Tape Witch Huntm Frivolous Prosecution of James Sanders & his Wifem Handling of Explosive Residues at Calvertonm NASA’s Finding of Nitrates - NTSB Stops Testingm Recovery of Flight Data Recordersm Obstruction of Justice Threats to Individuals & Corporationsm Unlawful Confiscation of Private Propertym Tampering with Witness Testimony


Conclusions

m The Center Wind Tank Scenario is Impossible

m A Large Airbursting Anti-Aircraft Missile Shot down TWAFlight 800

m The FBI was an Eyewitness

m Justice Department acted quickly to suppress evidence andsubvert Title 49 of the US Code

m The NTSB Leadership is either Incompetent or participatedin the cover-up

m The NTSB’s promotion of the mechanical failure theory isthreatening flight safety.

m The ongoing suppression of evidence is providing continuingprotection for the parties responsible.


Cmdr Donaldson’s Profile

My first official aircraft crash investigation was of an accidental air to air missileshootdown of a Navy A4 in 1977 - I am a Graduate of crash analysis training fromthe Naval Post Graduate School - I've had six Technical Articles for pilots publishedin Approach Magazine. I've got thousands of hours of tactical jet flight time - I'veinstructed advanced air combat maneuvering, air to air gunnery, towed airbornetargets for aircraft and ships, dropped thousands of bombs, flew 89 air to groundcombat missions in North Vietnam and Laos, even dueled and won with a NorthVietnam Sam Site. I've served as the Fleet Commander's observer for major Fleetexercises - I've run a multiple carrier Fleet Air Exercise as the air operations officer.I am a Graduate of Air traffic controllers school; for two years I ran the carrier airtraffic control center on CVN 59 (27 air controllers), and I was the nuclear weaponstargeting officer for the Fleet Commander in Southern Europe. For three years, Iserved as maintenance officer in a jet squadron - I served as JAG investigator forCommander in Chief Atlantic when false charges were leveled against a Navy pilotby FAA personnel. I've participated in confidential operations against terroriststates. For the record AIM has funded me on two occasions. I am not officiallyattached to the Aviation Sub-Committee in any way - what I discover is shared withthem quickly. My observations are based on hours of eyewitness conversations,including one who watched a missile all the way to detonation.

Interim Report - twa800.comtwa800.com/report/flt800.pdfInterim Report. 7/21/98 TWA Flight 800 Investigation 2 Order of Events m Introductions ... Thus far they have generated more

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