DA Form 2397-6 Technical Report of U.S. Army Aircraft Accident, Part Vii - in-Flight or Terrain Impact and Crash Damage Data

DA Form 2397-6 - also known as the "Technical Report Of U.s. Army Aircraft Accident, Part Vii - In-flight Or Terrain Impact And Crash Damage Data" - is a United States Military form issued by the Department of the Army.

The form - often mistakenly referred to as the DD form 2397-6 - was last revised on February 1, 2009. Download an up-to-date fillable PDF version of the DA 2397-6 down below or look it up on the Army Publishing Directorate website.

ADVERTISEMENT
TECHNICAL REPORT OF U.S. ARMY AIRCRAFT ACCIDENT
REQUIREMENTS CONTROL SYMBOL
PART VII - IN-FLIGHT OR TERRAIN IMPACT AND CRASH DAMAGE DATA
CSOCS-309
For use of this form, see DA Pamphlet 385-40; the proponent agency is OCSA.
1.
IN-FLIGHT COLLISION KINEMATICS AT INSTANT OF IMPACT
a. Airspeed at Impact (knots)
f. Obstacle Strike Sequence (Enter 1, 2, 3, etc. to show sequence of strike)
Prop/Rotor
Landing Gear
b. Vertical Speed (feet per minute)
Rotor Mast
Wing
Up
Down
Tail Rotor
Empennage
c. Flight Path Angle (degrees)
Tail Boom
WSPS
Up
Down
Windscreen
FLIR
d. In-Flight Attitude At Impact
LWR Nose/Gun Turret
Other (Specify)
(1) Pitch
(2) Roll
Angle
Angle
g. Obstacle Conspicuity
(Within accident distance from pilot's position,
the obstacle in its surroundings was obscured)
(1)
Completely
(2)
Partially
(3)
Not Obscured
Degrees
Up
Degrees
Left
h. Wire or Cable Description
Down
Right
Type
Dia In Inches
No. Struck
e. Obstacle Identity And Collision Height
(1) Power Transmission
Collision Height Above Ground
Obstacle
(feet)
(2) Telephone or TV
(1)
Birds
(3) Bracing (guy/support)
(2)
Aircraft
(4) Other (Specify)
(3)
Wires/Cables
i. WSPS (1) Installed
Yes
No
(2) Cut Wire
Yes
No
(4)
Vehicles
j. Obstacle Struck Other Than Wire (diameter in inches)
(5)
Tree
(6)
Other
2.
TERRAIN COLLISION KINEMATICS AT INSTANT OF MAJOR IMPACT
d. Indicate by Check Marks Which Two of The Three Preceding
a. Ground Speed at Impact
(knots)
Parameters (a, b, c) Are The Most Accurate
a.
b.
c.
b. Vertical Speed
(FPM)
Up
Down
c. Flight Path Angle
e. Impact Angle
(degrees)
(degrees)
Up
Down
f. Attitude at Major Impact
(1) Pitch
(2) Roll
(3) Yaw
Degrees
Up
Down
Degrees
Left
Right
Degrees
Left
Right
3.
ROTATION AFTER MAJOR IMPACT
a. Did Aircraft Rotate About Any Axis After The Above Major Impact (If yes, complete items b, c, and d)
Yes
No
Unknown
b. Roll Degrees
c. Yaw Degrees
d. Pitch Degrees
Left
Right
Degrees
Left
Right
Degrees
Up
Down
Degrees
IMPACT FORCES RELATIVE TO AIRCRAFT AXES (G's)
4.
a. Vertical (G's)
b. Longitudinal (G's)
c. Lateral (G's)
Up
Down
G's
Fore
Aft
G's
Left
Right
G's
5. CASE NO.
a. Date (YYYYMMDD)
b. Time
c. Acft Serial No.
6. OTHER ACFT SERIAL NO.
PAGE 1 OF 2
DA FORM 2397-6, FEB 2009
PREVIOUS EDITION IS OBSOLETE.
APD LC v1.01
TECHNICAL REPORT OF U.S. ARMY AIRCRAFT ACCIDENT
REQUIREMENTS CONTROL SYMBOL
PART VII - IN-FLIGHT OR TERRAIN IMPACT AND CRASH DAMAGE DATA
CSOCS-309
For use of this form, see DA Pamphlet 385-40; the proponent agency is OCSA.
1.
IN-FLIGHT COLLISION KINEMATICS AT INSTANT OF IMPACT
a. Airspeed at Impact (knots)
f. Obstacle Strike Sequence (Enter 1, 2, 3, etc. to show sequence of strike)
Prop/Rotor
Landing Gear
b. Vertical Speed (feet per minute)
Rotor Mast
Wing
Up
Down
Tail Rotor
Empennage
c. Flight Path Angle (degrees)
Tail Boom
WSPS
Up
Down
Windscreen
FLIR
d. In-Flight Attitude At Impact
LWR Nose/Gun Turret
Other (Specify)
(1) Pitch
(2) Roll
Angle
Angle
g. Obstacle Conspicuity
(Within accident distance from pilot's position,
the obstacle in its surroundings was obscured)
(1)
Completely
(2)
Partially
(3)
Not Obscured
Degrees
Up
Degrees
Left
h. Wire or Cable Description
Down
Right
Type
Dia In Inches
No. Struck
e. Obstacle Identity And Collision Height
(1) Power Transmission
Collision Height Above Ground
Obstacle
(feet)
(2) Telephone or TV
(1)
Birds
(3) Bracing (guy/support)
(2)
Aircraft
(4) Other (Specify)
(3)
Wires/Cables
i. WSPS (1) Installed
Yes
No
(2) Cut Wire
Yes
No
(4)
Vehicles
j. Obstacle Struck Other Than Wire (diameter in inches)
(5)
Tree
(6)
Other
2.
TERRAIN COLLISION KINEMATICS AT INSTANT OF MAJOR IMPACT
d. Indicate by Check Marks Which Two of The Three Preceding
a. Ground Speed at Impact
(knots)
Parameters (a, b, c) Are The Most Accurate
a.
b.
c.
b. Vertical Speed
(FPM)
Up
Down
c. Flight Path Angle
e. Impact Angle
(degrees)
(degrees)
Up
Down
f. Attitude at Major Impact
(1) Pitch
(2) Roll
(3) Yaw
Degrees
Up
Down
Degrees
Left
Right
Degrees
Left
Right
3.
ROTATION AFTER MAJOR IMPACT
a. Did Aircraft Rotate About Any Axis After The Above Major Impact (If yes, complete items b, c, and d)
Yes
No
Unknown
b. Roll Degrees
c. Yaw Degrees
d. Pitch Degrees
Left
Right
Degrees
Left
Right
Degrees
Up
Down
Degrees
IMPACT FORCES RELATIVE TO AIRCRAFT AXES (G's)
4.
a. Vertical (G's)
b. Longitudinal (G's)
c. Lateral (G's)
Up
Down
G's
Fore
Aft
G's
Left
Right
G's
5. CASE NO.
a. Date (YYYYMMDD)
b. Time
c. Acft Serial No.
6. OTHER ACFT SERIAL NO.
PAGE 1 OF 2
DA FORM 2397-6, FEB 2009
PREVIOUS EDITION IS OBSOLETE.
APD LC v1.01
7.
FUSELAGE INWARD DEFORMATION OR COLLAPSE AND INJURY RELATIONSHIP
(Check appropriate boxes)
Specific Area of Deformation or Collaspse
Fuselage Deformation Produced/Contributed to Injury
Amount or Type of
Forward
Rear
Deformation or
Fuselage Area
Cockpit
Cabin
Mid Cabin
Cabin
Cockpit
Forward
Mid Cabin
Rear Cabin
Collapse
Area
Area
Area
Cabin Area
Area
Area
(1)
(2)
(3)
(4)
(5)
(6)
(7)
(8)
a. Roof
Up to 1 Foot
More Than 1 Foot But
Less Than 3 Feet
More Than 3 Feet
b. Left Side
Up to 1 Foot
More Than 1 Foot
c. Right Side
Up to 1 Foot
More Than 1 Foot
d. Nose
Up to 1 Foot
More Than 1 Foot
e. Floor
Up to 1 Foot
More Than 1 Foot
f. Floor (local
Vertical
deformation
Sideward
under seats)
Forward/Rearward
8.
LARGE COMPONENT DISPLACEMENT (Check appropriate boxes)
Cockpit
Cabin
Displaced
Torn Free
Component
Penetrated/Entered
Penetrated/Entered
(1)
(2)
(3)
(4)
a. Transmission (forward or main)
b. Transmission (rear)
c. Rotor Blade (forward or main)
d. Rotor Blade (rear or tail)
e. Landing Gear (specify location)
f. Other (specify)
9.
FLUID SPILLAGE
a. Equipped With Crashworthy
b. If So Equipped, Did
e. Amount and Type Fluid Spilled
Fuel System
Breakaway Valves Separate
Gallons
Fuel (Type)
Oil (Type)
Hyd Fluid (Type)
Other (Specify)
as Designed
0 - 1
Yes
No
Yes
No
NA
> 1 - 2
c. Flammable Fluid Spillage
d. Auxiliary Fuel Tanks Installed
> 2 - 10
Occurred
Yes
No
> 10 - 20
Yes
No
Internal
External
> 20
Crashworthy
Yes
No
10.
SPILLAGE SOURCE
Part
a.
Part Name/Nomenclature
b.
Part Number
c.
National Stock No.
(1) Cell/Tank/Reservoir
(2) Filter
(3) Fitting
(4) Fluid Line
(5) Value
(6) Breakaway Valve
(7) Other (Specify)
(8) Other (Specify)
(9) Other (Specify)
11. REMARKS
PAGE 2 OF 2
DA FORM 2397-6, FEB 2009
APD LC v1.01

Download DA Form 2397-6 Technical Report of U.S. Army Aircraft Accident, Part Vii - in-Flight or Terrain Impact and Crash Damage Data

1337 times
Rate
4.5(4.5 / 5) 80 votes
ADVERTISEMENT
Page of 2