2023 HGST Study Guide PDF

References: TC 3-04.1 TC 3-04.3_C1 DEC 2020 Hydra Supplement Hellfire Supplement TM 1-1520-263-10-2 C1 NOV 2020 TM 1-1520-263-CL-2 OCT 2020 AH-64E dATM JAN...

References: TC 3-04.1 TC 3-04.3_C1 DEC 2020 Hydra Supplement Hellfire Supplement TM 1-1520-263-10-2 C1 NOV 2020 TM 1-1520-263-CL-2 OCT 2020 AH-64E dATM JAN 2022 ATP 3-09.32 (JFIRE) OCT 2019 2023 Gunnery Study Guide  Ballistics, Delivery Techniques, MISC 1. The engagement process is a systematic fires cycle and a continual process on any mission and has five tenets: Detect, Identify, Decide, Enagage, and Assess (DIDEA). ( TC 3-04.3 PG 11-1) 2. Desired Target Effect is (Destruction, Neutralization, Suppression). (TC 3-04-42 Task 2033) 3. Destruction is a decisive engagement that puts a target out of action permanently. Destruction is achieved by killing enemy personnel or destroying enemy equipment. It requires weapons to strike within lethal range of the target. Hellfire missiles are well suited for destructive fires. (TC 3-04-42 Task 2033) 4. Neutralization requires weapons effects to hit the target and cause damage to it. Unlike suppressive fire, target neutralization cannot be achieved by rounds that miss the target. Neutralizing damage to a target can temporarily remove it from the battle. High explosive (HE) and multipurpose sub-munitions (MPSM) rockets as well as 30-mm high explosive dual purpose (HEDP) are capable of target neutralization. (TC 3-04-42 Task 2033) 5. Suppression of a target limits the ability of enemy personnel to perform their mission. Suppressive fire is used to defend friendly forces from accurate enemy attack. It limits enemy movement and observation and increases friendly freedom to maneuver. Any available weapon or munition can be used to suppress the enemy. Lethal suppressive fire reduces enemy combat effectiveness by creating apprehension or surprise and causes enemy vehicle crews to button up and dismounts to seek cover. To be effective, suppressive fire must force a change in enemy behavior. Suppressive fire may be used to either fix the enemy in place or force him to move from a position. Suppressive effects may also be created by smoke or illumination rounds. Suppressive fire can be preplanned and can be used preemptively or reactively as required. All rockets and 30mm are capable of target suppression. (TC 3-04-42 Task 2033) 6. There are five techniques of fire. (TC 3-04-42 Task 2033) 7. The five techniques of fire are Hover fire, Running fire, Diving fire, Low altitude bump, and Diving/running fire initial point. (TC 3-04-42 Task 2033) 8. Hover fire. Hover fire is delivered when the helicopter is below ETL, IGE or OGE. Hover fire is used when the enemy possesses a significant anti-aircraft threat system composed of radar directed Air Defense Units (ADU) or anytime standoff must be maintained. (TC 3-04-42 Task 2033) 9. Running fire. Running fire is an effective weapons delivery technique to use during terrain flight, especially in regions where cover, concealment, and environmental conditions hamper or limit stationary weapons delivery techniques, or when air defense threats prevent the use of diving fire. Running fire is performed at airspeeds above ETL and offers a mix of aircraft survivability and weapons accuracy. (TC 3-04-42 Task 2033) 10. Diving fire. Diving fire is the most accurate type of fire for unguided ordnance. Diving fire offers the advantages of reduced vulnerability to small arms fire, increased armament load, improved accuracy, and better target acquisition and tracking capabilities. The entry altitude, entry airspeed, dive angle, and recovery altitude will depend on the threat, tactical mission profile, ambient weather conditions, aircraft gross weight, and density altitude. (TC 3-04-42 Task 2033) 11. Low-altitude bump. This profile maximizes the benefits of both running and diving fire involving a low-altitude run-in with a 300- to 1,000-foot climb (Bump) about 1,500 to 2,000 meters prior to the target. From the apex of the climb (Perch) the crew enters a diving profile in order to deliver ordnance in a nose-down angle to achieve smaller beaten zones. In 1|Page  mountainous terrain there may be no need for a Bump as the relative position of the sloping terrain provides the same effect to an aircraft in level flight. (TC 3-04-42 Task 2033) 12. Diving/running fire initial point. To provide time and space to set up a running or diving fire attack the AMC selects an Initial Point (IP). Normally the IP is selected about 8 to 10 kilometers from the target acts as a starting point for the attack run. The initial point should be either a readily identifiable terrain feature or a TSD/C-Scope icon. (TC 3-04-42 Task 2033) 13. Dispersion. The degree of scatter (or variance of range and azimuth) of these rounds is called dispersion (figure C-1). Dispersion and accuracy determine whether a particular weapon can hit an intended target. Dispersion is caused by the combination of weapons design and ballistic errors. (TC 3-04.3 Pg C-1) 14. Kinematic range is the maximum distance that the round can physically fly. (TC 3-04.3 Pg C-4) 15. RMAX is the distance at which a defined target can be hit (though not necessarily defeated). (TC 3-04.3 Pg C-4) 16. Maximum effective range (RMe) is the distance at which there is a 50-percent probability of both hitting and defeating a target. RMe is generally the most useful weapons range for tactical planning and is dependent upon munition characteristics, desired munition effects and target type. (TC 3-04.3 Pg C-4) 17. The four types of ballistics are interior, exterior, aerial, and terminal. (TC 3-04.3 Pg C-5) 18. Ballistics is the science of projectile motion and conditions affecting that motion. (TC 3-04.3 Pg C-5) 19. Interior Ballistics include: Barrel wear, Launcher tube misalignment, Thrust misalignment, Propellant charge, and projectile weight. (TC 3-04.3 Pg C-5) 20. Aircrews cannot compensate for these characteristics (interior ballistics) when firing free-flight projectiles. (TC 3-04.3 Pg C-5) 21. Exterior ballistics influence the motion of the projectile as it moves along its trajectory. The trajectory is the flight path of the projectile as it flies from the muzzle of the weapon to the point of impact. Aerial-fired weapons share the exterior ballistic characteristics associated with ground-fired weapons. (TC 3-04.3 Pg C-6) 22. Gravity, Yaw, Projectile drift and Wind drift are what types of ballistics? Exterior (TC 3-04.3 Pg C-7) 23. Yaw is the angle between a projectile’s centerline and trajectory. Yaw causes trajectory to change and drag increase. Yaw direction constantly changes in a spinning projectile. Yaw maximizes near the muzzle and gradually subsides as the projectile stabilizes. (TC 3-04.3 Pg C-7) 24. Projectile drift increases as range to target increases. Spinning projectiles act like a gyroscope and exhibit gyroscopic precession, causing the projectile to move right in a horizontal plane. (TC 3-04.3 Pg C-7) 25. Aerial-fired weapons characteristics are derived from fin or spin-stabilized munitions and whether they are fired from a fixed or flexible mode. Common errors for these munitions are rotor down-wash error, angular rate error, and turning bank error. (TC 3-04.3 Pg C-8) 26. Rotor down wash acts on the projectile as it leaves the barrel or launcher. This down wash causes a change in the projectile’s trajectory. A noticeable change in trajectory usually occurs when the helicopter is operating below effective translational lift. (TC 3-04.3 Pg C-9) 27. Although rotor down wash influences the accuracy of all weapon systems, it most affects rockets. Maximum error is induced by rotor down wash when the weapon system is fired from an aircraft hovering IGE. (TC 3-04.3 Pg C-9) 28. Projectile jump occurs when a crew fires a weapon from an aircraft in flight and the weapon’s muzzle is pointed in any direction other than into the relative wind (figure C-14). Projectile jump begins when the projectile experiences an initial yaw as it leaves the muzzle. The jump 2|Page  occurs due to the precession (change in axis of rotation) induced by crosswind. The amount of jumps is proportional to the projectile’s initial yaw. Firing to the right produces a downward jump; firing to the left produces an upward jump. (TC 3-04.3 Pg C-13) 29. Pilots should recognize that compensation for this error is accomplished automatically by the AH-64ballistics algorithms when 30. TADS is the selected sight. (weapons processor employs a TSE) 31. FCR is the selected sight. (function of scan-to-scan correlation.) a. ***NO lead-angle compensation is computed or added when IHADSS is the selected sight (TC 3-04.3 Pg C-21) 32. Angular rate error is caused by the motion (pitch, roll, and/or yaw) in the launch platform as a projectile leaves the weapon. This error affects unguided weapon systems. When the weapon is fired, movement of the helicopter or rocket pod transfers motion to the rocket. The amount of error depends on range to the target and the rate of motion when weapon is fired. (TC 3- 04.3 Pg C-9) 33. The altitude from which the projectile is fired and range to target determines impact angle and fragmentation pattern. A projectile fired from nap-of-the-earth altitudes at the weapon’s midrange forms an elongated pattern, with the projectile impacting at shallow angles. Aircraft pitch attitude at launch increases as range increases resulting in steeper impact angle. Launch platform altitude also has a significant effect on impact angle. (TC 3-04.3 Pg C-14) 34. Fragmentation is historically the primary kill mechanism of explosive munitions. Fragmentation travels further than blast, and fragment-generating weapons are more versatile than shaped charges and can be produced in mass quantities at low cost. (TC 3-04.3 Pg C-14) 35. An additional type of fragmentation is produced by target structure itself. When a weapon strikes a target, impact or explosive forces release high-speed debris, or spall, that functions similarly to warhead fragments. Spall is most often produced behind armor, such as when the inside surface of an armored vehicle breaks away and releases hi-speed metal fragments that can cause considerable damage. Spall also can be very effective at damaging soft internal components and igniting internal ammunition stores off the jet shot line axis. (TC 3-04.3 Pg C- 14) 36. Faulty recoil adapters are another major source of round-to-round dispersion or aiming point biases. If either or both recoil adapters are incorrectly serviced or dysfunctional altogether, a significant variation can exist in first and subsequent round placements. (TC 3-04.3 Pg C-20) 37. Angular rate error is effectively negligible for 30-mm projectiles, but it can affect rocket accuracy if rates are appreciable. Articulating pylons induce angular rates in the pitch axis up to 10 degrees per second. (TC 3-04.3 Pg C-21) 38. Terminal ballistics describes a projectile’s characteristics and effects on a target. Projectile functioning such as blast, heat, and fragmentation are influenced by fuze and warhead functioning, impact angle, and surface condition. (TC 3-04.3 Pg C-13) 39. Rockets are more sensitive to down-wash effects than 30-mm projectiles. Hover IGE launch yields greater dispersion because the aircraft cannot apply appropriate down-wash compensation. Rockets pitch up in hover whether hover IGE or hover OGE applies because rockets turn into the relative wind source during motor burn. (TC 3-04.3 Pg C-20) 40. The AH-64 weapons processor automatically compensate for wind drift. (TC 3-04.3 Pg C-21) 41. As air mass characteristics are measured locally, the AH-64 ballistics algorithms apply wind sensitivity adjustment to the aiming point as if the munition will fly directly to the target and the measured winds will be constant from the aircraft to target. (TC 3-04.3 Pg C-21) 42. The TSE is implemented using a seven state Kalman filter to derive the filtered target range and three axis target velocities. Whenever continuous lasing is in progress and a fresh range update 3|Page  is available from the LRV, the TSE updates target states and co-variances. Otherwise, the TSE extrapolates target states based on the last valid range measurement. (TC 3-04.3 Pg C-22) 43. The TSE is utilized to derive target states using the following inputs: a. Processed range data from the laser range validator. b. TADS pitch and yaw rates from the TADS gyros. c. Aircraft body rate and velocity data from the EGI. (TC 3-04.3 Pg C-22) 44. When using the TADS LRF/D to lase targets at flat grazing angles and with minimal vertical surface area, it is important to recognize the potential for beam spill-over as a function of slant range since the laser spot diameter increases as a function of range. The LRV usually detects this condition and the flashing asterisk alerts the operator to its presence. However, if the beam is allowed to spillover consistently, the selected range receiver mode is “last”, and the background terrain is consistent from a range return perspective, the LRV may never sense the presence of the intended near-field target since it is never detected by the LRF/D. The following techniques will confirm beam spillover: 45. The LRF/D can be temporarily set to “first return” logic to confirm that the same range value is returned in both LRF/D receiver modes (assuming atmospheric conditions permit use of first return logic in a reliable manner). 46. The aim point can be depressed (slightly) to confirm that the range matches that returned with the sight positioned at the desired aim point. 47. Platform altitude can be increased to modify the aspect angle and minimize the potential for spill-over. 48. Spillover can be overcome by slightly depressing the aim point to acquire an accurate range solution and accommodate RF missile engagements. Clearly, this is not an option for SAL missile engagements. (TC 3-04.3 Pg C-23) 49. TPM-R briefing: The AMC will formulate an attack plan and transmit it to other SWT team members utilizing the air-to-air TPM-R briefing format in accordance with ATM Task 2043 and applicable SOPs. As a minimum, friendly location, as well as techniques, patterns, munitions, and ranges will be briefed and understood. (TC 3-04.42 Task 2128) 50. Attack communications. Once the AMC is given the mission to support friendly forces in contact, he or she will establish direct communication with the on scene ground commander. Direct communication between the ground commander and the AMC conducting the attack is the central tenant when conducting attacks against enemy forces in close friendly contact. It is crucial in the prevention of fratricide and to ensure destruction of the enemy. (TC 3-04.42 Task 2128) 51. The Army Attack Aviation Call for Fire (5-Line) is used to initiate attack aviation fires on the enemy. It involves communication between the ground commander and the AWT conducting the attack. The 5-Line brief is a “friendly centric” brief that does not require a JTAC. (TC 3-04.42 Task 2128) 52. TPM-R brief. The AMC formulates and briefs the attack plan to the scout weapons team (SWT) utilizing the “TPM-R” format. (TC 3-04.42 Task 2128) 53. TPMR Format: a) Techniques. Techniques of fire include running, diving, or hover fire. Type of threat, terrain, visibility, winds, DA, GWT of the aircraft, and the proximity to friendly troops will be considered when selecting a mode of fire. Another technique could be running fire with a bump to acquire targets. b) Patterns. Patterns include, but are not limited to: race track, butterfly, 45-degree attack, circular/wheel, clover leaf, figure 8 or L-pattern. Direction of turns and pull-offs must be briefed. 4|Page  c) Munitions. Munitions selected must be appropriate for the target and provide the most standoff capability. Accuracy and reliability must be considered when firing near friendly troops. Collateral damage could be another consideration in some areas of operation. d) Range. When briefing range, include distance from target where inbound engagement will initiate and at what range the pull-off will be executed to prevent over flying the target and staying outside of the enemy’s engagement range. 54. The AMC assigns team member responsibilities within the team based upon the tactical situation. Shooter/cover, Shooter/shooter, Looker/shooter (TC 3-04.42 Task 2128) 55. The AMC will select the pattern: Racetrack pattern, Butterfly pattern, 45-degree attack pattern, Circular/Wheel Pattern, Cloverleaf pattern, Figure-8 pattern, and L-pattern. (TC 3-04.42 Task 2128) 56. Table 44. Army Aviation Attack Request and SOF Gunship CFF Format 1. Observer and Warning Order. “_________________, ________________ this is, fire mission, over.” (aircraft call sign) (observer call sign) 2. Friendly Location and Mark. “My position ________________, marked by________________.” (e.g., grid) (strobe, beacon, etc.) 3. Target Location. “Target Location_____________________________________.” (bearing (magnetic) and range (meters), grid, etc.) 4. Target Description and Mark. “ _______________________, marked by________________________.” (target description) (infrared pointer, tracer, etc.) 5. Remarks: “ __________________________________________, over.” (clearance, danger close, at my command, threats, restrictions, etc.) Notes: 1. Clearance. If airspace has been cleared between the employing aircraft and the target, transmission of this brief is clearance to fire unless “danger close”, “at my command”, or an additional method of control is stated. 2. Danger Close. The observer or commander must accept responsibility for increased risk. State “cleared danger close” in line 5 and pass the initials of the on-scene ground commander. This clearance may be preplanned. 3. At My Command. For positive control of the aircraft, state “at my command” on line 5. The aircraft will call “ready to fire”, when ready. To command aircraft attack, the observer will say "(aircraft call sign), fire." 4. For synchronization of fires, methods of fire and control may be included in line 5. Refer to Table 3, “Methods of Fire and Control”, for additional measures. (J-Fire Pg 56) 57. When operating in proximity to friendly forces, the air mission commander or flight lead must have direct communication with the ground commander or observer on the scene to provide direct fire support. After receiving the Army attack aviation CFF from the ground forces, the aircrews must positively identify the location of the friendly element and the target prior to conducting any engagement. (J-Fire Pg 55) 5|Page 58. Table 42. RW CAS 5-line Brief 1. Observer/Warning Order/Gameplan “________________________ , _____________________, 5-line, (aircraft call sign) (JTAC/FAC(A) call sign) Type (1, 2, or 3) control, MOA (BOC or BOT), (ordnance requested).” 2. Friendly location/mark “My position _____________________, ________________ marked by “ (target reference point, grid, etc.) (beacon, IR strobe, etc.) 3. Target location “Target location,_______________________________________“ (magnetic bearing and range in meters, target reference point, grid, etc.) 4. Target description/mark “_______________________, marked by ________________________.” (target description) (IR, tracer, etc.) 5. Remarks and Restrictions (* items are restrictions): Laser-to-target line or pointer target line. Desired type and number of ordnance or weapons effects (if not previously coordinated). Surface-to-air threat, location, and type of SEAD. Additional calls requested. Additional remarks (gun-target line, weather, hazards). *Final attack headings. *Airspace coordination areas. *Danger close and initials. *Time on target/time to target. *Post launch abort coordination and considerations. Note: The rotary wing CAS 5-line should be passed as one transmission. If the restrictions portion is lengthy, it may be a separate transmission. Legend: BOC—bomb on coordinate JTAC—joint terminal attack controller BOT—bomb on target MOA—method of attack SEAD— FAC(A)—forward air controller suppression of enemy air defenses (airborne) IR—infrared 59. RW CAS Employment Considerations: a) Once approved for a CAS attack, clearance to use off-axis weapons (e.g., crew served weapons) upon ingress to and egress from the target area is implied. Fires from off-axis weapons are subject to the restrictions outlined in the CAS attack brief. b) The primary attack brief for RW CAS is the 9-line. In certain situations, RW aircraft, including Army RW aircraft conducting attacks using CAS tactics, techniques, and procedures (TTP) may have very high situational awareness due to a low operating altitude. In these instances, the RW CAS 5-line brief (table 42) can expedite fires. c) The RW CAS 5-line brief is an observer-centric CAS brief. These TTP are used for bomb- on-target attacks. 6|Page 60. Table 37. Gameplan and 9-line CAS Brief Do not transmit the numbers. Units of measure are standard unless briefed. Lines 4, 6, and any restrictions are mandatory readbacks. The joint terminal attack controller (JTAC) may request an additional readback. JTAC: “ ______________________, advise when ready for gameplan.” (call sign) JTAC: “Type (1, 2, 3) control (method of attack, effects desired or ordnance, interval). Advise when ready for 9-line.” 1. IP/BP: “___________________________________________.” 2. Heading: “__________________________________________.” (degrees magnetic, initial point or battle position-to-target) Offset: “____________________________________________.” (left or right, when requested) 3. Distance: “_________________________________________.” (initial point-to-target in nautical miles, battle position-to-target in meters) 4. Target elevation: “_________________________________________.” (in feet, mean sea level) 5. Target description: “_______________________________________.” 6. Target location: “_________________________________________.” (latitude and longitude or grid coordinates, or offsets or visual) 7. Type mark/terminal guidance: “_______________________________.” (description of the mark, if laser handoff, call sign of lasing platform and code) 8. Location of friendlies: “_____________________________________” (from target, cardinal direction and distance in meters) Position marked by: “_______________________________________.” 9. “Egress _________________________________________.” Remarks and Restrictions (*items are restrictions): *Final attack headings or attack direction. Laser-to-target line/pointer target line. Surface-to-air threat, location, and type of air defense suppression. *Airspace coordination areas. *Danger close and initials. *Post launch abort restrictions. Additional remarks (e.g., gun-to-target line, weather, hazards). Desired type and number of ordnance or weapons effects. *Time on target/time to target. Additional calls requested. *Approval out of battle position for rotary-wing aircraft. Legend: BP—battle position IP—initial point 61. For off-axis weapons, the weapons final attack heading may differ from the aircraft heading at the time of release. The aircrew should inform JTAC when this occurs and ensure weapon final attack headings comply with given restrictions. See JP 3-09.3 for more final attack heading considerations. 62. Table 38. BDA Report Size: “.” (number and type of equipment/personnel observed) Activity: “.” (movement direction, stationary, dug-in) Location: “.” Time: “.” Remarks: “.” (munitions expended, observed damage, mission number, and mission accomplished) 7|Page 63. Burst on target (BOT). BOT is the technique used to adjust fires on target (figure 12-2). This technique requires the aircrew member firing the weapon to sense projectile impacts of the weapon system and use proper technique to adjust the rounds on target. Crews use BOT with cannon, and rocket engagements. Techniques for applying BOT include recognition, milliradian relation, and laser range finder (LRF) methods. (TC 3-04.3 Pg 12-8) 64. Recognition method. The recognition method is also known as “Kentucky windage”. Effectiveness of this technique is directly proportional to the experience of aircrew member making corrections. To use this method, aircrew member fires a burst, senses its impact, and estimates amount of correction needed to adjust rounds onto target. Range changes are affected by aiming the weapon left/right and/or up/down in relation to the target. (TC 3-04.3 Pg 12-8) 65. Milliradian relation method. Using the milliradian relation method, the aircrew member should— a) Select a field of view (FOV), estimate range to target using milliradian values of the symbology, and input or adjust the range manually, noting range to target. b) Fire a burst at the target. c) Sense the impacts of the rounds and measure distance between mean point of impact (MPI) and the target using the sight symbology. d) Using the known milliradian values (see appendix E) determine weapon impact distance from the target in range and deflection. e) Make an appropriate change the range and azimuth settings and adjust the desired mean point of impact (DMPI). f) Continue engagement. (TC 3-04.3 Pg 12-8) 66. Laser range finder method. An aircrew member should— a) Select an appropriate FOV, obtain a laser range to the target, and note range to target. b) Fire a burst at target. c) Select a wider FOV on the optics while the projectiles are in flight. d) Sense the impacts of rounds. e) Obtain a laser range to the MPI. Note the range to the impacts. The difference between the laser range to target and the laser range to the MPI is the range error. f) Note the azimuth to the impact. If a deflection error is present, make minor corrections in the DMPI (aiming point) in the opposite direction of the error in relation to the target. g) Change the range to target by adding or subtracting the range error to the original range to target. Then manually enter the corrected range into the aircraft firing solution. g) Continue the engagement. (TC 3-04.3 Pg 12-8) 67. The following steps are intended to provide guidelines for ensuring the most consistency in rocket engagements: Use the four T’s (target, torque, trim, and target) as a cue to enhance the accuracy of the aircraft weapon systems. (TC 3-04.3 Pg 12-9) 68. Torque verified. The pilot verifies the torque required to maintain altitude and does not change it. Any torque changes during the firing sequence will adversely affect the distance rockets fly based on the induced relative wind on the rockets as they launch. (TC 3-04.3 Pg 12- 9) 69. Trim verified. The trim of the aircraft includes horizontal and vertical trim. When firing rockets, whether at a hover or in forward flight, the pilot should verify and adjust the aircraft power to eliminate any vertical drift (vertical trim.) The pilot must also ensure the aircraft is stable in pitch and roll during weapon release to eliminate the effect of angular rate error. (TC 3-04.3 Pg 12-9) 8|Page 70. Steep dive angles (>25 degrees) result in large rates of change in aircraft flight parameters and present flight safety challenges. (TC 3-04.3 Pg 12-11) 71. Target fixation may cause a pilot to fly the aircraft into the ground. Therefore, the crew must use a careful crosscheck and adhere to an appropriate minimum altitude to avoid a hazardous flight condition. High rates of descent, coupled with high flight-path speeds, require pilot to closely monitor the rate of closure with the terrain. (TC 3-04.3 Pg 12-11) 72. Steeper dive angles compress the range error for rockets significantly and result in less dispersion around the rocket aim point. (TC 3-04.3 Pg 12-11) 73. Mushing may make dive recoveries difficult. If the aircraft enters mushing, the pilot must reduce the severity of the dive recovery by reducing the amount of aft cyclic and/or reducing the collective pitch on the rotor system. Available aircraft power and G loads must be considered when planning dive recoveries. (TC 3-04.3 Pg 12-11) 74. Pilots should strive to release rockets from the same altitude on each run. Delivery from a consistent altitude will help to compensate for projectile drop by determining and applying the same sight picture adjustment for projectile drop each time. (TC 3-04.3 Pg 12-11) 75. The two types of fire are direct and indirect. “Direct” requires the target to be within the shooter’s line of sight (LOS) and “Indirect” means the shooter cannot observe the target. (TC 3- 04.3 Pg 12-1) 76. Appropriate levels of aircraft system safeing are defined as— a. Weapons trigger switch released. b. Weapons action switch deselected. c. SAFE/ARM button – SAFE. (TC 3-04.42 Task 2033) AWS 77. The rotary wing risk estimated distance for a 0.1% Pi (standing) (J-FIRE 18 Oct 2019) AH-64/ 500 55 30mm (M789) 1,000 70 1,500 100 78. What are the visual markings of the M789 30mm HEDP? 79. The 30-mm audible signature travels at approximately 331 meters per second. Engagement at greater than 2,000 meters can be heard by the dismounted personnel before the first round impacts. (TC 3-04.3 Pg 12-28) 80. What are the visual markings of the M788 30mm TP Round? Blue projectile with aluminum nosepiece and white markings 81. Conduct AWS dynamic harmonization IAW the appropriate aircraft current operator's manual/CL and the following criteria: a. Aircraft heading to target within +/- 5˚ of the TADS LOS. b. Range to target 500 – 1500 meters. 9|Page  c. Transcribe the GUN harmonization correctors to DA Form 2408-14 (paper and electronic). (TC 3-04.42 Task 2041) 82. Harmonization procedures should be accomplished between 500 to 1500 meters from the target. The preferred distance is 1000 meters. (TM 1-1520-251-CL-2 P24) 83. The projectile of the round has a shaped charge liner for piercing in excess of 2 inches of Rolled Homogenous Armor (RHA) at 2500 meters and a fragmentation radius of 4 meters for soft targets. (AWS Student handout D-16) 84. 30mm Time of flight when fired from a hover. (AWS Student handout D-17) Range to Target Time of Flight 500 0.7 1000 2.0 1500 3.7 2000 5.8 2500 8.6 3000 12.2 85. The actual fragmentation pattern of any fragmenting warhead is not equally distributed in a circular pattern. To maximize probability of hit, the round must impact so that the target is within the fragmentation pattern. When engaging vehicle targets, the DMPI should been center of mass. When engaging exposed personnel, the DMPI should be offset and/or short of the target to achieve the desired effects. (TC 3-04.3 Pg 12-28) 86. When FXD is selected by the pilot the CCIP will only be displayed in the PLT Format symbology. When FXD is selected by the CPG both crewmembers will have the CCIP displayed in their respective formats. It is important to note that the FXD gun reticle (CCIP) is not edge limited in the symbology and there is NO HAD message to indicate a crewmember has selected FXD gun. (TC 3-04.42 Task 2041) 87. The gun duty cycle is as follows: Six 50 round bursts with 5 seconds between bursts followed by a 10 minute cooling period. For BURST LIMIT settings other than 50, the cycle can be generalized as no more than 300 rounds fired within 60 seconds before allowing the gun to cool for 10 minutes, after which the cycle may be repeated. (TM 1-1520-251-10-2 PG 4-107) 88. BURST LIMIT settings for the gun. BURST LIMIT establishes the number of rounds to be fired with each trigger pull: 10, 20, 50, 100, or ALL. (TM 1-1520-251-10-2 PG 4-107) 89. 30mm Warning. If 300 or more rounds have been fired in the preceding ten minutes, and a stoppage occurs, personnel must remain clear of the aircraft for 30 minutes. Crewmembers should remain in the aircraft and continue positive gun control. (TM 1-1520-251-10-2 PG 4-109) 90. Under 30 mm gunfire, missile, and rocket firing, the TADS turret may vibrate or oscillate at a level sufficient to blur imagery and may cause the IAT to coast off the target or break lock. In the event the turret vibration or a coasted IAT causes the TADS LOS to move off the target, the trigger should be immediately released and IAT reinitiated as required. (TM 1-1520-251-10-2 PG 4-109) 91. In the event of power loss, the gun is spring driven to +11° elevation to prevent dig-in during landing. (TM 1-1520-251-10-2 PG 4-105) 92. AWS page. (TM 1-1520-251-10-2 PG 4-105) 10 | P a g e 93. The maximum effective range of the 30-millimeter varies based upon target type and desired effect. Point targets can be accurately engaged out to 1,500 to 1,700 meters. The WP/MP will provide a ballistic solution up to a range of 4,200 meters. (TC 3-04.42 TASK 2041) 94. Invalid Fixed Fixed Gun Aiming Reticle Norm (AWS Student Handout Pg D- 50) 95. The AWS will continue to follow IHADSS LOS when operating in NVS FIXED mode. (TM 1- 1520-251-10-2 PG 4-105) 96. Azimuth limits for the gun turret assembly when the gun is actioned with the next-to-shoot missile on the inboard rail of the inboard launcher. ±52 degrees. (AWS Student handout D-24) 97. Gun Fail. The gun system has been actioned but has been detected as failed. Recycle the GUN system ON/OFF power button. If the fault message clears, continue operation. (TM 1-1520- 251-10-2 PG 4-39) 98. In the event of power loss, the gun is spring driven to +11° elevation to prevent dig-in during landing. (TM 1-1520-251-10-2 PG 4-105) 11 | P a g e 99. In the event of a GUN EL MISTRACK fault, the gun will be stowed in elevation. Gun azimuth may not provide proper Wire Strike Protection due to wire cutter angle. (TM 1-1520-251-10-2 PG 4- 105) 100. The maximum capacity of the ammunition handling system is 1200 rounds. (TM 1-1520-251- 10-2 PG 4-105) 101. The amount of rounds will be reduced with the installation of the IAFS. The quantity will be proximately 94 rounds with the 130 gal fuel cell, if utilizing the uploader/downloader or proximately 58 rounds using the side loader. The 100gal fuel cell includes a 242 round munition storage magazine, making the maximum capacity about 300 rounds. (TM 1-1520-251-10-2 PG 4-105) 102. In the event of IHADSS failure with gun selected and the HMD as the selected sight, the gun will remain at its last command position. Gun firing is inhibited. When the gun is de-actioned, it will return to the stowed position. (TM 1-1520-251-10-2 PG 4-19) 103. The armament subsystem will use the following simulated weapon inventory when the weapon raining mode is selected: 888 gun rounds (TM 1-1520-251-10-2 PG 4-131) Rockets 104. The rotary wing risk estimate distance foe a 0.1% Pi (standing) 2.75 inch HE 300 110 rockets 800 135 (M151/229) 1,500 170 2.75 inch flechette (M255) 1,000 235 5 inch HE rockets (Mk- 1,000 160 24) 1,500 175 AGR-19/20 All 105 (J-Fire Pg 149) 105. The following picture depicts the rocket loading zones. (TM 1-1520-251-10-2 Pg 4-110) 106. Use of the MK-66 MOD 2 rocket motor is prohibited. (TM 1-1520-251-10-2 Pg 4-111) 107. Firing MK66 in a hover or low speed at a height of less than 7 ft. AGL, and for all other flight conditions of 5 ft. AGL, is not authorized. (TM 1-1520-251-10-2 Pg 4-111) 12 | P a g e 108. Do not fire rockets with the M433 (Nose Mounted Resistance Capacitance) fuze in situations where they might fly closer than 51 m from other airborne helicopters. (TM 1-1520-251-10-2 Pg 4-111) 109. Due to the possibility of surging the engines, do not fire rockets from in-board stations. Fire no more than pairs with two outboard launchers every three seconds, or fire with only one outboard launcher installed without restrictions (ripples permitted). These are the only conditions permitted. (TM 1-1520-251-10-2 Pg 4-111) 110. The minimum range to target when firing Flechette rocket is 800 meters. The effective range with MK66 rocket motors is 1 to 3 Km. Effectiveness is reduced with ranges greater than 3 Km. (TM 1-1520-251-10-2 Pg 4-111) 111. Re-inventory and attempting to fire 6MP, 6FL, and 6SK rocket types, after a NO-FIRE event is not recommended due to significant impact on accuracy. The rockets should not be used for at least 10 days to allow the M439 (Base Mounted Resistance Capacitance) fuze to reset. (TM 1-1520-251-10-2 Pg 4-111) 112. The M151 warhead is an anti-personnel, anti-materiel warhead (Figure A-3 and Table A-2) that is typically referred to as the “10-pounder” due to the combined warhead/fuze weight. The M151 warhead consists of a cast iron case (6.9 mm thick) with 1.05 kg of Comp B explosive. The base section of the warhead is threaded to mate with the MK66 rocket motor. The body of the warhead is olive drab with a yellow band and yellow or black markings. (Unguided Rocket Supplement Para A-4) 113. The HYDRA-70 rocket has a large dispersion (approximately 20-25 mils). Hit probability is increased with running / diving fire and close range. (Unguided Rocket Supplement Para A-4) 114. The rocket flies a relatively flat trajectory; firing rockets at high dive angles will improve anti- personnel lethality by increasing the effective beam spray. (Unguided Rocket Supplement Para A-4) 115. The M255A1 flechette warhead is a canister round with approximately 1179, 60 grain flechettes, packaged in 9 bundles, for engaging soft targets (Figures A-9 and A-10 and Table A- 6). The flechettes are encased in a 2-part aluminum sleeve within the aluminum warhead case. The base mounted fuze initiates an expulsion charge that propels the pusher plate, ejecting the flechettes though the front (nose cone shears off). (Unguided Rocket Supplement Para A-16) 116. Red pigment is ejected with the flechettes to serve as a daytime indicator and a titanium pyrotechnic charge as a nighttime indicator. The warhead body is olive drab with white diamond markings. (Unguided Rocket Supplement Para A-18) 117. Flechettes are kinetic energy penetrators; so short range shots will result in improved penetration performance of the flechettes. Flechette velocity decreases with increased ranges parallel the rocket. Note that the ejection charge only increases flechette velocity by approximately 15-25 m/s and flechette velocity decreases during free flight due to aerodynamic drag (including tumbling). (Unguided Rocket Supplement Para A-19) 118. Flechette impact pattern is a strong function of aircraft dive angle with shallow dives resulting in a more elongated ellipse. (Unguided Rocket Supplement Para A-19) 119. Flechettes can perforate personnel in the open and is marginal against 1.5 inch plywood and a SUV (steel panel/windshield) at maximum range. (Unguided Rocket Supplement Para A-19) 120. The proper umbilical cord routing for a cargo rocket. 13 | P a g e  (Unguided Rocket Supplement Fig A-11) 121. The M257 illumination warhead is primarily used for battlefield illumination with secondary application for target marking and Electro-Optical (EO) suppression. The M257 provides approximately 1 million candle power for a minimum of 100 seconds. The M257 consists of a base mounted M442 fuze, drogue parachute, 2 second delay gas generator, expulsion charge, pilot/main parachute, and illuminate candle. The illuminate consists of 2.45 kg of magnesium sodium nitrate. The candle is deployed approximately 3500 m down range from the launch platform. The body of the warhead is olive drab with white markings. (Unguided Rocket Supplement Fig A-27) 122. Caution should be taken to address the impact point for the expended rocket motor and warhead case. Impact zone extends out between 700 and 1200 meters from deployment point. (Unguided Rocket Supplement Fig A-28) 123. The M278 Infrared (IR) illumination warhead is primarily used for battlefield illumination using Night Vision Goggles (NVG) operating in the 0.7 to 1.1 micron. Within this spectrum, the M278 provides approximately 1 million candle power for 150 to 210 seconds. (Unguided Rocket Supplement Fig A-29) 124. Do not fire any MK66 motor that has been stored continuously above 140°F for more than 24 hours or any rocket that has been dropped. (Unguided Rocket Supplement Fig A-36) 125. The following table is the list of approved fuzes for the US Army. Table A-15. HYDRA-70 Family of Fuzes Class Fuze Arm Delay Output Output Mass M423 43-92 m 0 Comp A-5 8.4 g Point M427 180-426 m 0 Comp A-5 8.4 g Detonation MK435 (Navy) 43-92 m 0 PBXN-5/PBXN-7 9g MK437 (Navy) 180-426 m 0 PBXN-5/PBXN-7 9g RC Delay M439 150-250 m Pilot Select Comp A-5 8.4 g M442 150 m 9s Black Powder (PB) 5.7 Deceleration WDU-4A/A 150 m 0 M9 (NG/NC) 3g 126. Rocket steering cursors. Normal Ground Stow Fixed Rocket Inhibited 14 | P a g e 127. Accel Limit. The vertical acceleration is less than.5 G’s and may cause the main rotor blades to obstruct the trajectory of the rockets. Safety inhibit. (TM 1-1520-251-10-2 Table 4-8) 128. The last crewmember to action a weapon has control of that weapon. Exception: If the CPG has rockets actioned via the LHG WAS and the pilot actions rockets, cooperative mode is in effect. The active LOS will be the CPG's LOS. (TM 1-1520-251-10-2 Pg 4-6) 129. The CPG's rocket mode selections will be active in cooperative mode. The pilot's type, quantity, and penetration selections will default to the CPG's selections. (TM 1-1520-251-10-2 Pg 4-6) 130. The M261 launcher is unserviceable when 4 or more tubes are defective. (Unguided Rocket Supplement Para A-52) 131. Hover-fire engagements can be achieved at a range of approximately 4,500 meters without changing aircraft pitch attitude. At ranges beyond 4,500 meters, pitch attitude changes (nose- up) may have to be made to meet firing constraints. (TC 3-04.42 TASK 2039) 132. ARS common page settings. Under normal dual display processor/mission processor operations, the PLT and CPG rocket weapon’s (WPN) pages are enabled and set independently. The only normal operation exception to the independent WPN’s page status occurs during rocket cooperative (COOP) engagements. During COOP mode, settings displayed on the PLT’s WPN’s page will change to match those selections made by the CPG. Prepare for the engagement by first selecting the RKT WPN’s page and then set the page option buttons as necessary. (TC 3-04.42 TASK 2039) 133. Sight selection. The firing crewmember will select sight most appropriate for the mode of fire and type of engagement being conducted. The PLT and CPG may utilize HMD and the FCR as lines of sight. The CPG may additionally utilize the TADS. HMD is used when conducting independent engagements in both NORM and FXD modes. The PLT will utilize HMD while the CPG utilizes TADS in the COOP mode. FCR is used as the LOS when conducting indirect rocket engagements from either station. (TC 3-04.42 TASK 2039) 134. Rocket symbology. The rocket steering cursor is a dynamic I-beam symbol which indicates the delivery mode and how to point the aircraft for the rocket delivery. The top and bottom horizontal legs of the rocket steering cursor indicate articulation constraints (+4º to -15º). The solid I-beam also indicates the helicopter orientation required to meet the WP/MP-calculated firing constraints. If the CPG has actioned rockets, the rocket steering cursor is presented on both pilot and CPG formats. If the pilot has actioned rockets, the rocket steering cursor is presented only on the pilot’s displays. The cursor moves about in the format to indicate the azimuth and elevation position of the helicopter in relation to the selected sight LOS to provide steering cues to the crewmember. (TC 3-04.42 TASK 2039) 135. The cursor will be dashed when a safety or performance inhibit is in effect, indicating crew action is required prior to firing rockets. (TC 3-04.42 TASK 2039) 136. The FXD mode is best utilized in a diving or running flight profile against targets at 2000m or less. This mode allows the firing crewmember to adjust rocket fires onto target by maneuvering the aircraft and reduces errors caused by pylon articulation and LOS movement. (TC 3-04.42 TASK 2039) 137. After actioning rockets the firing crewmember maneuvers the aircraft as necessary to position the FXD rocket steering cursor’s CCIP over the target. Once aligning the CCIP over the target the firing crewmember fires rockets as desired. (TC 3-04.42 TASK 2039) 138. When rockets are WAS’d with HMD as the selected LOS, range will automatically default to the selected manual range of the firing crewmember. If NAV range is desired the crewmember must select the appropriate ACQ source after WASing rockets. (TC 3-04.42 TASK 2039) 15 | P a g e 139. If utilizing TADS the CPG will provide range to target for the engagement. During hover fire engagements 1st detent laser ranging or NAV should be used. During dynamic (target, aircraft or both moving) continuous laser ranging or NAV should be utilized. (TC 3-04.42 TASK 2039) From left to right: M278 IR Illum M151 10 Pounder M264 Red Phosphorus 140. M151 M255A1 141. 16 | P a g e  PTWS 142. The rotary wing risk estimated distance for a 0.1% Pi (standing) AGM-114 FA/K/L/ All 115 M/N(4/6)/P(2A) AGM-114R All 130 AGM-114R2 All 145 (J-FIRE Pg 149) 143. The on-call Hellfire remote engagement is the least likely and most difficult remote engagement. The on-call Hellfire remote engagement assumes that little or no known mission details are known in advance and that the crews (shooter and designator) are required to complete all planning in flight under operational time constraints. This requires a detailed call for fire to lay out all the data needed for the firing aircraft and the designator. The 5-line attack brief (table 12-6) is the format to complete the procedure and is found in ATP 3-09.32/MCRP 3-16.6A/NTTP 3-09.2/AFTTP 3-2.6. (TC 3-04.3 Pg 12-48) 144. Remote Hellfire engagements fired in support of Army forces will utilize the 5-line attack brief format according to ATP 3-09.32/MCRP 3-16.6A/NTTP 3-09.2/AFTTP 3-2.6. After the target hand over, the remote Hellfire firing sequence is completed, beginning with a read back by the firing aircraft. This ensures the correct targeting information is utilized. (TC 3-04.3 Pg 12- 48) 145. LOBL remote engagements provide a high degree of confidence that the engagement will be successful. The firing platform makes a “Capture” call when their missile has acquired coded laser energy and displays LOBL symbology. The capture call indicates the designating aircraft is in position, and has “captured” (with their sensor) the laser spot on the target. (TC 3-04.3 Pg 12-48) 146. When LOAL is used, the firing platform calls “Laser on, time flight, _____ seconds”, based on range/time of flight and required/maximum delay time. All remote designation will be done on the designating platform’s code. (TC 3-04.3 Pg 12-49) 147. The “Buddy Laser” technique is a simplified remote engagement utilized by aircraft within a flight/team. Lead/wingman Hellfire missile employment using Buddy-Lasing techniques can provide several of the advantages of remote Hellfire employment (backscatter avoidance for example) while offering much greater simplicity. (TC 3-04.3 Pg 12-49) 148. When the lasing aircraft is in close proximity to the shooting aircraft, there is virtually no possibility for the missile to track on the designator when the following guidelines are used: The Buddy Laser sequence will normally be initiated by the AMC. The shooting aircraft should be on roughly the same heading to the target as the designator’s LTL. The shooting aircraft should be positioned abeam or slightly forward of the abeam of the lasing aircraft. (TC 3-04.3 Pg 12-49) 149. Shift Cold Procedure. A typical risk avoidance method when aborting a missile engagement with a missile in flight is to smoothly change the missile’s flight path to a secondary and less critical impact point. Procedures for an abort post launch are as follows: 17 | P a g e  The PC directs the gunner to “Shift cold.” A common technique is to say, “Continue lasing, shift cold;” the justification for this technique is the gunner will want to stop lasing when hearing the word “Abort.” A timely reminder to continue lasing may help prevent that. The gunner should respond verbally that “Shifting cold” is being performed and move the laser spot smoothly to the determined shift-cold spot. It is critical to keep the laser spot visible to the missile through the remainder of the missile’s flight in order to ensure continued control of the missile’s impact point. If the abort call came from an external source (ground commander/JTAC), acknowledge the call. Note the TOF countdown. When a missile impact is observed, direct the gunner to “Mark impact and terminate laser.” (TC 3-04.3 Pg 12-50) 150. Hellfire laser delay after launch Max Delay (s) Laser Time Range Min Delay Legacy HF-II Enhanced HF-II*** on Target (km) (s) ZERO OFFSET MAX OFFSET ALL OFFSETS (s) 2 1* 2 1* 2 6 3 2 4 2 4 6 4 3 6 4 7 6 5 4 8 6 (5**) 10 6 6 4 10 (8**) 8 (6**) 12 8 7 4 12 (8**) 8 (6**) 14(12**) 10 8 4 14 (8**) 8 (6**) 15(12**) 12 NOTE: Delaying lase beyond max delay will result in decreased Phit * HELLFIRE missile software applied 1.3 second lock-on inhibit for LOAL shots **For Romeo LOAL-L (FLAT), reduced maximum laser delay ***For AGM-114R2 LOAL-H HOB, do not delay lase beyond 2 seconds (Hellfire Supplement Pg 7) 151. If the missile seeker loses sight of the laser spot during this time the HELLFIRE may miss the target. Rotating the aircraft just before launch—at least three to five degrees in the direction of the missile to be fired—prevents the missile from flying through the designator FOV. (Hellfire Supplement Pg 7) 152. Under severe backscatter conditions it may not be possible to perform LOBL. In these cases, the preferred backscatter avoidance technique is to utilize a remote designator to provide missile guidance. If remote designation is not available and the engagement must be conducted, the gunner can stop lasing the target, fire the missile LOAL and delay lasing for a minimum of two seconds after missile separation (approximately three seconds after trigger pull). (Hellfire Supplement Pg 8) 153. Back Scatter. Based on Missile Seeker vs TADS LOS, the seeker is not tracking the TADS Laser designation. Safety inhibit. (TM 1-1520-2521-10-2 Table 4-9) 154. Underspill, Spot Jitter, Attenuation, Beam Divergence, Overspill, Back Scatter, Boresight Error, Podium Effect, and Entrapment. (Hellfire Supplement Pg 8) 155. Hellfire Min and MAX range chart 18 | P a g e  Legacy HF-II Ground Range (m) for HAT::; Articulated Pylon Non-Articulated Pylon 50ft MODE (TGT OFFSET) RMIN0 (m) RMAX.,(m) ARMIN ARMAX MAXALT A 1N Affr.Ax MAX ALT LOBL (0/±20Q) 500/1200 7100 400m 400m 10 kft 800m 300m 10 kft LOAL-D/L (0/±7.SQ)* 1500/1700 7100 200m 400m 10 kft 1600m 600m 5 kft LOAL-H(0/±7.SQ) 3500/3500 8000 20m 300m 10 kft 1200m 500m 6 kft Enhanced HF-II Ground Range (m) for HAT::; Articulated Pylon Non-Articulated Pylon 50ft MODE(TGT OFFSET) RMIN0 (m) RMAX.,(m) ARMIN ARMAX MAXALT A 1N Affr.Ax MAX ALT LOBL (0/±20Q) 500/1200 7100 400m 400m 10 kft 800m 300m 10 kft LOAL-D/L (0/±30Q) 1500/2000 7100 Om 400m 10 kft 20m 400m 10 kft LOAL-H (0/±30Q) 2000/2500 8000 -100m 300m 10 kft Om 300m 10 kft **LOAL-H HOB 2500/3000 6500 -100m 250m 10 kft NA NA NA (0/±30Q) Per 1 kft increase in A/C ALT Above Target *For AGM-114K/M/N, LOAL-L RMIN0=2000 / 2500 m; RMAX.,=8000 m **AGM-114R2 with laser delay :S2 seconds only (Hellfire Supplement Pg 33) 156. The RMAX increases as the aircraft’s launch altitude above target is increased as the missile is able to glide further from a higher altitude. For each 1 kft increase in launcher altitude above target, RMAX may be adjusted by the ΔRMAX value in the table. (Hellfire Supplement Pg 33) 157. Hellfire Missile Trajectories- a. LOAL-DIR. The missile software applies minimal trajectory shaping and will engage the target with the most direct approach. For obstacle avoidance, a clear line-of-sight (LOS) to the target is required at launch. b. LOAL-LO/FLAT. i. The AGM-114K missile will pitch up immediately after launch to clear a 260-foot terrain obstacle at 600 meters down range during midcourse. During terminal guidance, the trajectory is biased to achieve an impact angle of 20 degrees added to the target LOS. ii. The AGM-114R missile will fly a lower-flatter trajectory during midcourse (similar to LOAL-D), but during terminal guidance a flat, near horizontal, trajectory will be maintained to achieve minimal missile body angle at impact. For obstacle avoidance, a clear line-of-sight to the target is required at launch. c. LOAL-HI/LOFT/HOB. i. The AGM-114K missile will pitch up immediately after launch to clear a 1000 foot terrain obstacle at 1,500 meters down range during midcourse. During terminal guidance the trajectory is biased to achieve an impact angle of 20 degrees added to the target LOS. ii. The AGM-114R missile increases the trajectory shaping bias during terminal guidance to achieve an impact angle of 30 degrees added to the target LOS. iii. The AGM-114R2 missile with 7.12 missile software has an additional trajectory to provide steeper impact angles to maximize lethality against soft targets. The LOAL-HI HOB trajectory climbs higher than the LOAL-HI or LOFT trajectories and performs a pulldown maneuver. To employ the LOAL-HI HOB trajectory, the platform must identify the round as an R2, choose the LOAL-HI/LOFT trajectory, and select a delay mode of HOB. 19 | P a g e  (Hellfire Supplement Pg 29) 158. The SAL HELLFIRE laser seeker must be able to see the laser spot. If the missile flies into low cloud ceilings, it is possible that the seeker line of sight to the laser spot can be interrupted resulting in a break lock. The crew must ensure that the SAL HELLFIRE stays below cloud ceiling to ensure continued laser guidance to the missile. Missile apogee (Table 16) is dependent on firing mode, target range, and laser delay (LOAL). If cloud clearance is below listed altitude above firing aircraft for selected firing mode, consider repositioning launch platform to avoid penetrating cloud ceiling and losing seeker track. (Hellfire Supplement Pg 33) 159. Hellfire II Apogee / Cloud ceiling TABLE 16. HELLFIRE II APOGEE/CLOUD CEILING Cloud Clearance, ft Firing Mode Target Range, m above firing A/C (Min Laser Delay) 3000 400 LOBL 5000 650 7000 800 3000 250 LOAL-DIR 5000 450 7000 650 3000 550 LOAL-LO 5000 650 (Non-Romeo) 7000 850 3000 150 LOAL-FLAT 5000 250 (Romeo) 7000 400 3000 950 LOAL-HI/LOFT 5000 1250 7000 1500 3000 750 LOAL-H HOB 5000 1700 (500ft HAT) 7000 Not Recommended 3000 200 LOAL-H HOB 5000 800 (2kft HAT) 7000 1100 90% of missiles reach apogee below this altitude above firing A/C (Hellfire Supplement Pg 33) 160. The LOBL maximum range is 7.1 km for a target at the same altitude as the helicopter. (Hellfire Supplement Pg 36) 161. Hellfire TOF 1KM 2KM 3KM 4KM 5KM 6KM 7KM 8KM 0 4 7 10 14 19 25 31 1000 4 7 10 14 18 24 30 38 (Hellfire Supplement Pg 44) 162. Aim point selection and dive angle should be adjusted to ensure the shaped-charge jet shot line intersects these critical components. Fundamentally, placing the desired point of impact on the base of the turret yields optimal munitions effects. (Hellfire Supplement Pg 44) 20 | P a g e 163. HELLFIRE-II missiles utilize a tandem warhead with a PC and MC shaped charge warhead. The precursor warhead is initiated at missile impact and designed to initiate the explosive elements in the ERA. The MC initiation is delayed, to allow the ERA metal flyer plates to clear the shot line (delay is partially limited by system and target constraints). The MC warhead is designed to perforate the base armor and critically damage internal components. (Hellfire Supplement Pg 45) 164. Anti-personnel engagements require an understanding of the fragmentation pattern of the warhead as a function of impact angle. The AGM-114K2 missile generates a limited number of lethal fragments due to the aluminum case, which necessitated the development of the AGM- 114K2A. The fragmentation pattern becomes more uniform in dispersion as the missile impact angle increases. The use of diving fire or higher aircraft altitude above the target will increase the missile impact angle, providing a more uniform fragmentation area. (Hellfire Supplement Pg 46) 165. Multiple weapons impacts within the same area may create target obscuration and or backscatter. A dust cloud created by a missile impact typically covers a 10-square foot area. Against masonry structures, masonry dust or highly volatile materials inside the enclosure may produce too much smoke from the first missile, creating a tracking hazard for the second missile. This can affect the accuracy of subsequent missiles. (Hellfire Supplement Pg 49) 166. The AGM-114L Longbow missile is designed for use against stationary and moving vehicle targets. The missile’s radar seeker and shaped charge warhead are specifically designed to defeat armored targets. Pilots may consider using RF missiles against other target types (personnel, buildings, structures, or bunkers), but the probability of hit is unknown against these target types. (TC 3-04.3 Pg 12-45) 167. The Longbow missile radar performance is best against moving armored/vehicular targets because the Doppler separation from clutter adds another dimension for target/clutter discrimination. The Longbow missile receives target handover data from an acquisition sight (FCR or target acquisition designator sight [TADS]). This target handover data is presented as a Northeast & Down (NED) coordinate. The TADS derived target coordinate and subsequent handover to the RF missile is often easier and more accurate, but there is no indication to the aircrew that the missile is tracking or will find the correct target. The FCR target handover may provide a better indication to the aircrew of missile performance because the FCR will not only pass the target coordinate, but also determine the target type. (TC 3-04.3 Pg 12-45) 168. The AGM-114L RF Hellfire missile cannot be altered from its course or selected target after launch.Understanding the performance characteristics, capabilities, limitations, and the proper techniques for employment of the AGM-114L are essential. The crew must implement all safety precautions and be able to accurately predict the missile’s performance prior to launch. (TC 3- 04.3 Pg 12-45) 169. The following are three possible methods used to engage a target with an RF missile in LOAL mode: Using own ship FCR as the acquiring sight. Receiving a radar frequency handover (RFHO). Target acquisition and designation sight handover. (TC 3-04.3 Pg 12-45) 170. When firing a LOAL TADS HO, the crew should attempt to fire the missile no longer than five to seven seconds after the target data (TARGET DATA?) message disappears. (TC 3-04.3 Pg 12-46) 171. Transfer alignment (transfer of aircraft inertial data to missile inertial platform) occurs automatically, whether inflight or not, at missile power up with no pilot action required. The “R” in the missile icon indicates that the missile is ready to receive the target. (TM 1-1520-251- 2 Pg 4-118) 21 | P a g e 172. AGM-114L Constraints considerations 173. Missile constraint boxes 22 | P a g e  Figure 4-35. Missile Constraint Boxes 1) LOAL out-of-constraints missile box. 2) LOAL in-constraints missile box. 3) LOBL out-of-constraints missile box. 4) LOBL in-constraints missile box. (TM 1-1520-251-2 Pg 4-29) 174. The constraints box size does not directly correlate to an angle (such as seeker FOV). For 1 or 2 SAL missiles, the allowable angle is larger for LOBL (20°) than for LOAL (7.5°). The P+ and R SAL missile constraints box will be displayed as a small solid box out to 30°. If the missile receives laser energy, the box will go broken until inside 20°. For P+ and R SAL missiles, the allowable angle is 20° for LOBL and 30° for LOAL. For RF missiles in either LOAL or LOBL trajectory mode, the allowable angle is 20° except when the missile is tracking and the target range is < 1 km, the allowable angle is 5°. (TM 1-1520-251-2 Pg 4-29) 175. 2ND TARGET INHIBIT Button (L6). The 2ND TARGET INHIBIT button is used to prevent secondary target information from being handed over from the FCR to the primary RF missile during a stationary target engagement. 2ND TARGET INHIBIT is common to both Crew Stations. (TM 1-1520-251-2 Pg 4-124) FCR 176. The FCR can be operated in the following selectable modes: Ground Targeting Mode (PPI format) Radar Map (B Scope format) Air Targeting Mode (PPI format) Terrain Profiles Mode (PPI format) (TM 1-1520-251-2 Pg 4-54) 177. The RFHO button is used for transmission of the FCR NTS (Figure 4-47) target data via the IDM to another AFAPD capable system. Selecting the RFHO button will display the Subscriber Identifier buttons based on the selected IDM network. (TM 1-1520-251-2 Pg 4-57) 178. RFI symbols representing RFI detected emitters are displayed on the periphery of the radar scan sector to indicate the direction to the detected threat. Up to 10 RFI symbols can be displayed. (TM 1-1520-251-2 Pg 4-58) 179. Ground Targeting Mode 23 | P a g e 180. FCR Target Symbols (TM 1-1520-251-2 Pg 4-58) 181. NTS, ANTS, Second Target Symbol (TM 1-1520-251-2 Pg 4-59) 24 | P a g e 182. GTM Formats (TM 1-1520-251-2 Pg 4-60) 183. RMAP Formats (TM 1-1520-251-2 Pg 4-61) 184. FCR Footprint. The GTM/RMAP scan sectors are displayed in full intensity and are based on the selected scan size: Wide, Medium, Narrow, and Zoom. RMAP and GTM format scan sectors dimensions are the same. Format scan sectors are as follows: Wide scan represents 90° (45° either side of FCR centerline). Medium scan represents 45° (22.5° either side of FCR centerline). Narrow scan represents 30° (15° either side of FCR centerline). Zoom scan represents 15° (7.5° either side of FCR centerline). (TM 1-1520-251- 2 Pg 4-61) 25 | P a g e 185. The FCR can be operated in the Air Surveillance mode or the Air Targeting mode. The Air Surveillance mode will not prioritize detected aircraft. (TM 1-1520-251-2 Pg 4-62) Fratricide 186. Fratricide is the employment of friendly weapons and munitions with the intent to kill the enemy or destroy his equipment or facilities, which results in unforeseen and unintentional death or injury to friendly personnel. (TC 3-04.3 Pg 10-1) 187. Many factors (or preconditions) contribute to fratricide. a. Mission Command b. Enemy c. Terrain and environmental conditions d. Troops and equipment e. Time (TC 3-04.3 Pg 10-2) 188. Fratricide prevention. Aviation units must incorporate doctrine as their baseline for all operations. The execution of operations is completed using practiced TTPs which work within the guidelines of doctrine. Unit SOPs must reflect a thorough understanding of fratricide and must focus on the TTPs which the Soldiers understand, innovate, refine and practice frequently. The following initiatives can help establish and refine unit SOPs. (TC 3-04.3 Pg 10-3) 189. Direct-fire weapons control measures a. Marking target reference points. b. Weapons control status for direct fires. c. Rules of engagement. d. Control measures. (TC 3-04.3 Pg 10-3) 190. Control measure and graphic training. Units must train each crew member on the different types of control measures used and their graphic portrayal. Crews must ensure that their graphics and control measures are replicated accurately within their mission software and on their maps. A one or two-kilometer error could be catastrophic. (TC 3-04.3 Pg 10-3) Brevity 191. ANCHOR [location] - Orbit about a specific point. 192. ANGELS - Height of FRIENDLY aircraft in thousands of feet from mean sea level (MSL). 193. CHERUBS - Height of a FRIENDLY aircraft in hundreds of feet above surface. 194. Cleared Hot – 1. [A/S] Type 1 and 2 close air support terminal attack control clearance to release ordnance on this pass. 2. [A/S] Training range operations: the range control officer or range safety officer authorizes ordnance release. 195. Cleared to Engage – 1. **[A/S] Type 3 close air support, terminal attack control clearance. Attack aircraft or flight may initiate attacks within the parameters imposed by the joint terminal attack controller. 2. **[A/A] [A/S] Clearance to fire on designated GROUP or target. 196. Continue – Continue present maneuver. This does not imply a change in clearance to engage or expend ordnance. 197. Continue Dry - [A/S] Continue present maneuver, ordnance release not authorized. Used to provide approval to aircraft to continue the pass without expending ordnance during type 1, 2, 26 | P a g e  or 3 control. (The joint terminal attack controller must use “Type 3, CONTINUE DRY” for dry type 3 control.) Simulated weapons deliveries may be performed. 198. Danger Close - **[A/S] [S/S] FRIENDLY troops are within 0.1% probability of incapacitation from the target (determined by the weapon or munition that is delivered or fired). 199. Engagement Complete - [A/S] Mandatory call from the attack aircraft to the joint terminal attack controller or forward air controller, during type 3 close air support terminal control, indicating completion of ordnance release. 200. Lowdown - A request for the tactical ground picture in an area of interest. 201. In - Entering terminal phase of an air-to ground attack. Opposite of OFF. 202. Off - Attack is terminated, and aircraft maneuvering to the indicated direction. 203. Offset - Maneuver in a specified direction with reference to the target. 204. Red - Aircraft is at a weapon or fuel state that is insufficient to continue execution of the mission. 205. Remington - No ordnance remaining except gun or self-protect ammunition. 206. Rifle - FRIENDLY A/S missile launch. Option to add follow-on modifiers for the number of munitions or time of flight. 207. Ripple - Two or more munitions will be released or fired in close succession. Associated with number and type of weapon with release interval. (Normally discussed during the prestrike gameplan between aircraft or between aircraft and ground tactical controller.) 208. Shrew - Persistent interference from an undetermined source that is degrading situational awareness on the current radio channel. 209. Splash – 1. *[A/A] [S/A] Target destroyed. 2. [A/S] Weapons impact. 3. *[S/S] [S/A] Informative call to observer or spotter 5 seconds prior to estimated time of impact. 210. Wagon (Left/Right) - [A/S] Rotary wing directive call to orbit around the target (e.g., “Taz 31, WAGON left”). 211. Weapons Status – Weapons control status. Fire only: 1. **(FREE): at targets not identified as FRIENDLY in accordance with current ROE. 2. **(TIGHT): at targets positively identified as HOSTILE in accordance with current ROE. 3. **(HOLD/SAFE): in self-defense or in response to a formal order. 212. Winchester - No ordnance remaining. 213. Blind - No visual contact with FRIENDLY aircraft, ship or ground position. Opposite of VISUAL. 214. Contact – 1. Sensor information at the stated position. 2. [A/S] Acknowledges sighting of a specified reference point (either visually or via sensor). 215. Looking - Aircrew does not have the ground or surface object, reference point, or target in sight (opposite of CONTACT). 216. No Joy - Aircrew does not have visual contact with the TARGET or BANDIT. Opposite of TALLY. 217. Padlocked - Aircrew cannot take eyes off an aircraft, ground target, or surface position without risk of losing TALLY or VISUAL. 218. Tally - Sighting a target, non-friendly aircraft, or enemy position. Opposite of NO JOY. 219. Visual - Sighting of a FRIENDLY aircraft or ground position or ship. Opposite of BLIND. 220. Buddy Lase - Request or informative communications to have guidance of a weapon from a source other than the delivering aircraft. 221. Deadeye - The laser designator system is inoperative. 27 | P a g e 222. Laser On - Directive call to start lasing. 223. Negative Laser - The speaker is firing the laser in response to LASER ON. 224. Spot – 1. [A/S] Acquisition of laser designation. 2. Platform is laser spot tracker capable. 225. Stare - Cue the laser spot search or tracker function on the specified laser code in relation to the specified reference point. The reference point may include the following: steerpoint, geographic reference, bearing and range, or data link point. TEN SECONDS [A/S] Standby for LASER ON 226. Check Capture - Target appears to be no longer tracked by sensor. 227. Check Focus - Sensor image appears to be out of focus. 228. Handshake - Video data link established. 229. Hollow - Lost video data link. 230. Restake - Drive a new STAKE at the target centroid reported with direction of travel and elevation. Initiated by the aircrew. 231. Set - 1. Set (or have set) a particular speed. May be indicated in knots or mach. 2. No longer slewing sensor and awaiting further updates. 3. **Overwatch aircraft is in position. 232. Shadow - Follow indicated TARGET. 233. Stake - Reference point for A/S targeting operations. 234. Zoom (In / Out) - Increase or decrease the sensor’s focal length. Operational Terms and Graphics 235. Unit Size Indicators 236. Basic Unit Symbols Friendly Enemy Neutral Unknown 28 | P a g e 237. Cover, Guard, and Screen. 238. Attack Helicopter axis of advance 239. Radar 240. Maintenance 241. UAV 242. Cavalry 243. Air defense 244. Armor 245. Rotary Wing Aviation 246. Infantry 29 | P a g e