GST Study Guide.pdf

REFERENCES: TM 1-1520-251-10-2 (Dec 15) TM 1-1520-263-10 (Jun 16) AWS Student Handout AH-64D/E (Dec 15) ARS Student Handout AH-64D/E (Dec 15) ARS Student Handout AH-64E (Dec 15) LBHMMS Student Handout AH-64D/E (Mar 16) M-TADS Student Handout (AH-64D/E) (Nov 16) Fire Control Radar Student handout AH-64D/E (Nov 16) 1-14th AVN REGT SOP (Sep 16) GST STUDY GUIDE January 2017 Ballistics: 1. There are four types of ballistics that influence helicopter fired weapon systems. They are classified as Interior, Exterior, Aerial, and Terminal. (Student Handout AH-64D Area Weapon System DEC 2015) 2. Interior ballistics defines the characteristics that affect projectile motion inside the barrel or rocket tube. Interior ballistics affect the trajectory of the projectile regardless of the method used to acquire a target. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 3. Free-flight rockets have an inherent thrust misalignment, which is the greatest cause of error in free flight. Firing rockets at a forward airspeed above Effective Transitional Lift (ETL) provides a favorable relative wind, which helps to counteract thrust misalignment. When a rocket is fired from a hovering helicopter, the favorable relative wind is replaced by an unfavorable and turbulent wind caused by rotor downwash. This unfavorable relative wind results in a maximum thrust misalignment and a larger dispersion of rockets. (Student Handout AH- 64D/E Aerial Rocket System DEC 2015) 4. Exterior ballistics defines the characteristics that influence the motion of the projectile as it moves along its trajectory. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 5. Yaw error is largest at muzzle (or tube) exit due to tip-off, not because of lack of spin stabilization. Yaw cannot be completely compensated for, although Spin- stabilized projectiles help minimize yaw error. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 6. Rotor downwash acts on the projectile as it leaves the barrel or launcher. This downwash causes the projectile's trajectory to change. Although rotor downwash influences the accuracy of all weapon systems, it most affects the rockets. Delivery error is largest while hovering In Ground Effect (IGE), because it is harder to characterize and compensate for due to blade impulses and the random nature of induced flow pattern. In essence, IGE launch yields greater dispersion, because the aircraft cannot apply appropriate downwash compensation. Note that the real reason rockets pitch up in hover, whether IGE or OGE, is weathervaning. At approximately 33 Kts forward airspeed (indicated), the rotor disk is pitched forward such that the influence vector is moved just aft of the rocket launcher front bulkhead, thus reducing downwash to zero. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 7. The aircrafts ballistics algorithms automatically compute rotor downwash compensation for rockets based on aircraft dynamic gross weight, air density ratio, and longitudinal true airspeed. However, this compensation assumes rocket launch is initiated at OGE altitudes. Downwash compensation is not applied for the gun due to the position of the muzzle with regard to the rotor disk and the short exposure time of the 30mm projectiles. (Student Handout AH- 64D/E Aerial Rocket System DEC 2015) 8. When initiating rocket launch in crosswinds, the aircraft should be temporarily leveled for munitions release, presuming that terrain permits doing so. Automatic roll compensation of the rocket aim point (and pylon position angle) will not be What sight is selected when a lead-angle compensation is required? Why? implemented with any degree of effectiveness. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 9. Terminal ballistics defines the characteristics and effects of the projectiles at the target. (Student Handout AH-64D Area Weapon System DEC 2015) 10. When the HMD sight is employed, the Weapons Processor does not execute the target-state estimator (TSE) algorithm to estimate target velocities; therefore, no lead-angle compensation is computed. This is critical if the ownship, target, or both is moving. (Student Handout AH-64D Area Weapon System DEC 2015) 11. If several projectiles are fired from the same weapon with the same settings in elevation and deflection, their points of impact will be scattered about the mean point of impact of the group of rounds. The degree of scatter (range and azimuth) of these rounds is called dispersion. (Student Handout AH-64D Area Weapon System DEC 2015) 12. Turret bending is the single largest contributor to perceived dispersion associated with the 30mm cannon. (Student Handout AH-64D Area Weapon System DEC 2015) 13. Firing rockets at maximum ranges decreases range dispersion and normally increases accuracy. The reverse is true with other weapon systems; that is, as range increases, dispersion increases, and accuracy decreases. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 14. Longer engagement ranges do not necessarily equate to improved accuracy for aerial rockets. Do not confuse this with round to round dispersion. Firing at extended ranges reduces linear (range) dispersion but increases cross- range dispersion. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 15. Three factors known to contribute to dispersion in the AWS are vibration, sight, and boresight. (Student Handout AH-64D Area Weapon System DEC 2015) Area Weapon System 16. The purpose of the Area Weapon System (AWS) is to provide the crew with an accurate, quick response weapon for close-in, medium and long range suppressive fire on soft or medium type targets. (Student Handout AH-64D Area Weapon System DEC 2015) 17. The Internal Auxiliary Fuel Fuel System (IAFS) has a 100-gallon fuel cell and integrated ammunition storage magazine which stores 242 rounds in the magazine and 58 in the Ammunition Handling System (AHS) allowing for approximately a 300 round capacity. (Student Handout AH-64D Area Weapon System DEC 2015) 18. The M788 is a Target Practice (TP) round used for gunnery training and has no purpose other than target impact or penetration. This round can be identified by it’s blue projectile and white stripe. (Student Handout AH-64D Area Weapon System DEC 2015) What is the penetration ? 2500m, 19. The M789 is a High Explosive Dual Purpose (HEDP) round capable of piercing in excess of 2” of Rolled Homogeneous Armor at 2500 meters. (Student Handout AH-64D Area Weapon System DEC 2015) 20. The M789 round has a fragmentation radius of 4 meters for soft targets. (Student Handout AH-64D Area Weapon System DEC 2015) 21. The M789 Round can be identified by its black projectile with a yellow band below the fuze. (Student Handout AH-64D Area Weapon System DEC 2015) 22. The AWS with M789 Ammunition is very effective up to 3000m against light to moderate armor as well as personnel. (TM 1-1520-251-10-2, TM 1-1520-263-10) 23. AH-64D Only: The Train Rate Sensor provides turret displacement and acceleration feedback signals to the turret control box in all firing positions. (Student Handout AH-64D Area Weapon System DEC 2015) 24. The stow spring positions the gun cradle assembly to +11° elevation in the event of a “Utility Hydraulic Level Low” or loss of electrical power to prevent the gun from contacting the ground during landing or taxi. (Student Handout AH-64D Area Weapon System DEC 2015) 25. Under normal conditions in flight the gun azimuth and elevation limits are as follows: (Student Handout AH-64D Area Weapon System DEC 2015) 26. With the AWS and Missiles actioned (on an inboard store) the gun is limited to 52° on the side of the aircraft which the next missile will be fired. (Student Handout AH-64D Area Weapon System DEC 2015) 27. The AWS Rate of fire is 625±25 rounds per minute. (Student Handout AH-64D Area Weapon System DEC 2015) 28. The maximum effective range of the AWS is 1500-1700m. (Student Handout AH- 64D Area Weapon System DEC 2015) 29. Attempting to fire the gun at ranges exceeding 4200m may result the in “BAL LIMIT” message in the Weapon Status field of the High Action Display. To override this inhibit one must pull the weapons trigger to the second detent. (TM 1-1520-251-10-2, TM 1-1520-263-10) 30. Failure to adhere to the published gun duty cycle may result in a catastrophic failure, loss of aircraft, injury or death. (TM 1-1520-251-10-2, TM 1-1520-263-10) 31. The gun duty cycle is six 50-round bursts with 5 seconds between bursts, followed by a 10- minute cooling period. (TM 1-1520-251-10-2, TM 1-1520-263- 10) 32. For burst settings other than 50, the gun duty cycle can be generalized to mean that no more than 300 rounds are 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, TM 1-1520-263-10) 33. 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. Aircraft crewmembers should remain in the aircraft and continue positive gun control. (TM 1-1520-251-10-2, TM 1-1520-263-10) 34. A minimum of 2 tangs must be fully seated into the nut on the flash suppressor. (Student Handout AH-64D Area Weapon System DEC 2015) 35. When recoil adapters are properly serviced, the indicator groove should be visible in the witness hole. (Student Handout AH-64D Area Weapon System DEC 2015) 36. AH-64D Only: Ensure the BURST LIMIT switch on the TCB is in the ALL position. If the BURST LIMIT switch is less than the MPD WPN page burst limit selection, the gun will fire the number of rounds selected on the TCB, then fail. DMS Fault page will display Gun Rounds Decrement Fail. Recycling AWS power on the WPN UTIL page will clear this failure until the next trigger pull. (Student Handout AH-64D Area Weapon System DEC 2015) 37. The following identifies the AWS reticles in specific modes: (Student Handout AH-64D Area Weapon System DEC 2015) 38. When fixed gun is selected a LOS reticle with a circle is displayed representing the Continually Computed Impact Point (CCIP) or gun-target line. (Student Handout AH-64D Area Weapon System DEC 2015) 39. Harmonization procedures should be accomplished between 500 to 1500 meters from the target. (TM 1-1520-251-10-2, TM 1-1520-263-10) 40. The AWS will continue to follow IHADSS LOS when operating in NVS FIXED mode. (TM 1-1520-251-10-2, TM 1-1520-263-10) 41. 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, TM 1-1520-263-10) 42. During preflight, and after all live fires when the AWS was used, the barrel will be inspected for cracks. Failure to inspect the barrel properly may result in a ruptured barrel and could result in catastrophic damage to the aircraft and/or injury to the crew. (TM 1-1520-251-10-2, TM 1-1520-263-10) 43. A “COINCIDENCE” message in the Weapons Status field of the High Action Display indicates that the gun is currently out of coincidence with the selected sight. This is a Safety Inhibit. (Student Handout AH-64D Area Weapon System DEC 2015) 44. The time of flight (TOF) of a M789 round varies based on multiple factors. Approximate TOF based on selected ranges is as follows: Range to Target (Meters) Time of Flight (Seconds) 500 0.7 1000 2.0 1500 3.7 2000 5.8 2500 8.6 3000 12.2 (Student Handout AH-64D Area Weapon System DEC 2015) Aerial Rocket System 45. During live fire testing shows that rockets achieve their best effectiveness between 3000 to 5000 meters. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 46. The maximum range for a MK66 rocket is 7500m. 47. The aerial rocket system can be employed independently by either crewmember or cooperatively. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 48. The fixed mode is best used during running and diving fire against targets 2000 meters or less and the aircrew should use navigation range for employment. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 49. Firing of the CRV-7 rocket is not authorized. (TM 1-1520-251-10-2, TM 1-1520- 263-10) 50. Use of the MK-66 MOD 2 rocket motor is prohibited. (TM 1-1520-251-10-2, TM 1- 1520-263-10) 51. When forward airspeed exceeds 10 KTAS, do not use M229/M423 (17 pounder PD) warhead/fuze combination for engagement of targets under 140m distance, and ensure the line of fire is clear of obstruction (trees/buildings) for at least 140m. When at a hover or forward airspeed is less than 10 KTAS, engagement distance and the requirement for line of fire to be clear of obstruction may be reduced to 110m. Firing this combination with the ballistics for the M151 (10 pounder) warhead will result in reduced rocket range. (TM 1-1520-251-10-2, TM 1-1520-263-10) 52. Firing MK66 in a hover or low speed at a height of less than 7’ AGL, and for all other flight conditions of 5’ AGL is not authorized. (TM 1-1520-251-10-2, TM 1- 1520-263-10) 53. Do not fire rockets with the M433 (Nose Mounted Resistance Capacitance) fuze in situations where they might fly closer than 51m from other airborne helicopters. (TM 1-1520-251-10-2, TM 1-1520-263-10) 54. 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, TM 1-1520-263-10) 55. 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, TM 1-1520-263- 10) 56. The minimum range to target when firing a flechette rocket is 800m. The effective range with MK66 rocket motors is 1 to 3Km. Effectiveness is reduced with ranges greater than 3Km. (TM 1-1520-251-10-2, TM 1-1520-263-10) 57. The TOTAL ROCKETS status window is displayed when there is a difference between the number of rockets available for firing and the number of rockets actually of the selected type. The status window and messages are displayed in white. The failed rockets will not be available for firing. (Student Handout AH- 64D/E Aerial Rocket System DEC 2015) 58. The INVENTORY defaults from the LMP and can be edited on the LOAD page if incorrect. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 59. Rocket Loading zones are as depicted below: (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 60. The following Rockets will be fired as “6PD” providing the correct ballistic computations when paired with the M423 (PD) fuze. a. M151 Warhead HE is anti-personnel, anti-material and referred to as the “10 pounder”. The body is olive drab with a yellow band and yellow or black markings. This warhead contains 2.3 pounds of composition B with a bursting radius of 10 meters and a lethality radius of more than 50 meters. The compatible fuze for this warhead setting (6PD) is the M423, which will arm in flight approximately 43 to 92 meters. b. M274 Warhead is a ballistic matched, spotting warhead for the M151. The warhead contains a 40-gram pyrotechnic charge that is initiated by the M423 fuze. The smoke and acoustic signature are vented out through holes in the warhead case. The base section of the warhead is threaded to mate with the MK66 rocket motor. The body of the warhead is blue. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 61. When paired with with the M433 (RC) fuze the M151 must be selected as “6RC” for appropriate “PEN” options to be selectable. The M433 arms approximately 143 meters downrange. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 62. The following rockets will be fired as “6IL” providing the correct ballistic computations. They are paired with the M442 fuze. c. M257 was designed for battlefield illumination. The body of the warhead is olive drab with white markings. The candle descends 15 feet per second and provides one million candlepower for 100-120 seconds. Preset to deploy approximately 3500 meters down range. It can illuminate approximately one square kilometer. d. M278 Infrared (IR) Illumination Warhead is designed for target illumination using NVG’s. The body of the warhead is black with white markings. The M278 puts out an equivalent of million candlepower of IR illumination. Preset to deploy approximately 3500 meters down range. The IR flare will provide IR light for approximately 180 seconds. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 63. M264 red phosphorus (RP) is a smoke-screen warhead. The body of the warhead is light green with a brown band and black markings. The warhead contains 72 RP wedges that are air-burst ejected over the intended target area. The smoke generated by 14 rockets will obscure a 300 to 400 meter front, in less than 60 seconds for 5 minutes. The smoke generated by the RP will block the entire visual spectrum as well as much of the IR spectrum. The effective range is 1000 to 6000 meters. The compatible fuze is the M439 and will be selected as “6SK.” (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 64. The M255A1 rocket is equivalent to the tanker’s canister round. The warhead body is olive drab cylinder with white diamonds and white markings. This rocket contains 1,179 60 grain steel flechettes. They are packed in a red pigment powder that can alert the crew to the point of payload deployment. The flechette warhead detonates 150 meters before the range set at launch. The flechette cloud is a cylinder of about 49.7 feet in diameter. The compatible fuze is the M439 and will be selected as “6FL.” (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 65. The following depicts the applicable rocket steering cursor by mode: (TM 1-1520-251-10-2, TM 1-1520-263-10) 66. If the message “PYLON LIMIT” is displayed in the Weapons Inhibit field of the High Action Display, it is indicating that the commanded pylon position exceeds the articulation limits of +4° to -15° in the air. This is a performance limit while airborne and can be overridden by pulling to the second detent on the weapons trigger. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 67. If the message “TYPE SELECT” is displayed in the Weapons Inhibit field of the High Action Display, it Indicates that no rocket type is selected. (multiple rocket types are available) (Student Handout AH-64D/E Aerial Rocket System DEC 2015) 68. If the message “ACCEL LIMIT” is displayed in the Weapons Inhibit field of the High Action Display, it Indicates that the vertical acceleration is less than 0.5 G’s and may cause the main rotor blades to obstruct the trajectory of the rockets. This is a safety inhibit and cannot be overridden. (Student Handout AH-64D/E Aerial Rocket System DEC 2015) Hellfire Modular Missile System 69. The AGM-114 HELLFIRE missile is a highly accurate precision guided munition (PGM). (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 70. When icing conditions exist, or are predicted, and Hellfire operations are expected, the launcher ARM/SAFE switch located on each Hellfire launcher must be manually placed in the ARM position prior to liftoff. It is possible for this switch to be rendered inoperative by icing. (TM 1-1520-251-10-2, TM 1-1520-263-10) 71. The following missile icons will be displayed on your weapons page depending on type and status of the individual missile: (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) SAL Missiles 72. The SAL missile depends on laser guidance to the designated target from the launching aircraft or from a remote designator. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 73. The following depicts the missile constraints boxes based on mode and whether the aircraft is in or out of firing constraints: (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 74. Valid PRF codes for the aircraft are within the range of 1111-1788. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 75. Underspill, Overspill, Spot Jitter, Attenuation, Beam Divergence, Boresight Error, Entrapment, Podium Effect, and Backscatter are all factors that can negatively impact the Missiles ability to find the designated target. (Student Handout AH- 64D Hellfire Modular Missile System MAR 2016) 76. Even a small number of overspilled or underspilled laser pulses can cause the missile to follow false signals. If this occurs just before missile impact, the probability of a hit is significantly degraded. To reduce the probability of this occurring, select last pulse on the laser and look for steady range returns. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 77. Backscatter occurs when the missile seeker differs from the TADS line of sight greater than 2°. This is a Safety Inhibit and cannot be overridden. To overcome Backscatter, the crew should attempt to: a. Stop lasing and attempt lasing again. b. The aircrew should reposition the aircraft and/or change altitude c. If available, use a remote designator. d. If the target distance is far enough away launch the missile in the direct trajectory, then use a minimum of 2 seconds of delayed designation from separation or 3 seconds from weapons trigger pull. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 78. When firing a SAL missile an offset of 3º to 5º to the firing side, should be used when possible to preclude the missile flying through the FOV of the TADS to prevent the video from being obscured by the missile’s exhaust. (SAL Missiles Only) (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 79. The minimum altitude to launch a SAL missile is 32 feet. (Student Handout AH- 64D Hellfire Modular Missile System MAR 2016) 80. To ensure a LOAL engagement when firing a AGM-114R model missile (DIR, FLAT, or LOFT) LOBL INHIBIT must be selected to prevent the missile from defaulting to LOBL. When in LOAL constraints condition (30°), if the target reverts to LOBL with >20° from the ADL the constraints will change to out of constraints which may cause crew confusion. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 81. The SAL 1 missiles arm at 150 to 300 meters in front of the aircraft. SAL 2 missiles typically arm at 181 meters in front of the aircraft. The AGM-114R arms when the launch acceleration exceeds 10Gs and a minimum distance of 375 meters. This arming distance was increased to address the blast fragmentation hazard generated by steel fragments. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 82. A SAL II missile (excluding AGM-114R) has 2 LOAL trajectories that can be used to fire from a masked location. The LOAL LO mode may be used when the missile is required to clear a low mask, which may have been selected by the crew for aircraft protection. In trajectory LO the missile can clear up to a 260’ mask with a minimum standoff distance of 600m. The LOAL HI trajectory may be used when the missile is required to clear a high mask, which may have been selected by the crew for aircraft protection. In trajectory HI the missile can clear up to a 1000’ mask with a minimum standoff distance of 1500m. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 83. The Minimum and maximum Effective Engagement Ranges for the AGM-114R model missile are as follows: MIN MAX MODE TRAJECTORY OFFSET RANGE RANGE 0 500 7000 LOBL 20 700 7000 0 1500 7000 DIR 30 2000 7000 0 1500 7000 LOAL FLAT 30 2000 7000 0 3500 8000 LOFT 30 3500 8000 (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) RF Missiles 84. The RF missile is inertial guided to the target area and uses an active millimeter wave RF signal to detect and terminally track the target that was received by the missile prior to launch. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 85. The RF missile is capable of engaging moving and stationary targets at a range between 0.5 and 8 km. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 86. RF Missile 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 1-1520-251-10-2, TM 1-1520-263-10) 87. The missiles can overheat if they are radiating (tracking) a target for more than 3 minutes. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 88. The LOBL INHIBIT button will inhibit the missile from radiating prior to launch. This capability reduces or eliminates the RF signature on the battlefield and allows for firing missiles at FCR LOBL targets from a defilade position. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 89. The 2ND target INHIBIT button prevents the FCR from assigning secondary target data to the missile during FCR target handover. This feature could be necessary when friendly targets are possibly near the engagement area. If friendly vehicles are in the vicinity of the target being engaged, it is possible that the missile could target the friendly vehicle if missile tracking is lost and relatively close in range to the threat target. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 90. During missile operation the RF radiation hazard area should be avoided. The area extends from the missile nose outward 1 meter and 45 either side of the missile centerline. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 91. The WP provides the RF missile target data three ways: e. FCR target handover. f. TADS target handover. g. IDM target handover (RFHO). (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 92. The FCR target symbols that are displayed do not determine the type of missile mode for launch (that is, LOBL or LOAL). Therefore, it is possible to launch a LOBL missile at a LOAL target symbol and vice versa. If the missile determines the target requires a LOBL acquisition, it will attempt to acquire it by radiating three times for approximately 3 seconds each. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 93. Although the RF missile has the final authority whether it should be launched LOAL or LOBL, it generally follows a predetermined set of rules. All moving target are processed as Moving Target Indicator (MTI) targets and should be assigned as LOBL engagements from the minimum range of 500 meters to the maximum range of 8000 meters. Stationary target assignments are processed as Stationary Target Indicator (STI) and are broken into the following three range areas: h. At a ranges of 500m-1000m, targets are too close for an LOAL engagement and must be made as a LOBL engagement. i. At ranges of 1000m-2500m, an RF missile will try to acquire (radiate) while displaying a LOAL box for targets. If the missile acquires the target, the missile defaults to a LOBL engagement with the LOBL constraints box displayed. If no acquisition is made, the missile will remain in LOAL status and can be launched. j. At ranges of 2500m-8000m, the missile will default to LOAL. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 94. If attempting to engage a target classified as a STI at ranges between 500m- 1000m, and the missile is unable to acquire/track the target, “NO ACQUIRE” will be displayed in the WEAPONS INHIBIT field of the HIGH ACTION DISPLAY. This is a safety inhibit and cannot be overridden. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 95. RF missiles can only receive target handover data from the TADS or via RFHO for a stationary target between 6000 and 8000 meters because the FCR is unable to process stationary targets at ranges greater than 6000 meters. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 96. For a LOAL engagement of a target at ranges between 2500m-8000m the missile will use Doppler Beam Sharpening (DBS) to acquire the target. DBS uses a curved trajectory to induce relative motion between a stationary target and its background by flying an off-axis flight path to the target. DBS significantly enhances the probability of detection and tracking stationary targets at long ranges. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 97. To achieve the best missile performance, it is important to keep the data latencies to a minimum. If the aircrew delays for an extended period of time, a new scan will be required for FCR target handover. For a TADS handover, a new LASER update may be necessary. The aircrew should not delay more than 15 seconds for all handovers. The exception is that of the TADS handover, where the delay should be no more than five to seven seconds after TARGET DATA? is removed from the sight status of the HAD. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) 98. When the RFHO is received via the IDM RFHO, and the mission is accepted, the target handover data represents the target North-East-Down (NED) grid coordinates relative to the receiving aircraft. The missile should be fired within 15 seconds for a moving target and 30 seconds for a stationary target. This time is after target handover is sent from the sending aircraft. The only timeout associated with a handover is the receiving aircraft must receive the RHFO within six minutes of the RFHO target data being received in the aircraft’s IDM buffer. The DATA INVALID message will be displayed in the HAD if the six minute limit is exceeded. The aircrew should never fire the missile this late after the handover. (Student Handout AH-64D Hellfire Modular Missile System MAR 2016) Sights 99. Offset boresight of the IHADSS is not authorized. (TM 1-1520-251-10-2, TM 1- 1520-263-10) 100. Some symbology is edge limited, which means that the information that the symbology represents is beyond the physical limits of the IHADSS display area, the symbology will move to the edge of the display and remain until the source of the information is back within the IHADSS FOV (e.g., Missile Constraints Box). Other symbols are not edge limited and will not be displayed if outside the current IHADSS display area(e.g., Head Tracker). (Student Handout AH-64E IHADSS DEC 2015, Student Handout AH-64D FEB 2014) 101. The LOS Reticle ﬂashes when the crewmember’s LOS is invalid or his selected NVS is at its limit. It also ﬂashes when the gun is the selected weapon and the gun system has failed and is not following the crewmember’s head. (TM 1-1520- 251-10-2, TM 1-1520-263-10) 102. The HAD (shown below) is divided into 11 status message ﬁelds and provides data independently by crew station. The messages are typically presented in priority order based on the selected sight and/or weapon system. (TM 1-1520-251-10-2, TM 1-1520-263-10) 103. The image below depicts the controls on the TEDAC Handgrips. AH-64D/E LHG AH-64D RHG AH-64E RHG (TM 1-1520-251-10-2, TM 1-1520-263-10) 104. The M-TADS system has the capability to null the turret servo drift by either of two methods: Manual or Automatic. Servo drift can be identified as happening whenever the M-TADS turret is under manual control, the CPG is not making any input with the thumbforce controller, and the reticle appears to drift off the aim point. The aim point should remain within the narrow FOV of the DTV for 30 seconds. If it does not, or a lesser amount of drift is desirable, adjustments can be made to compensate. If AUTO Drift Null does not reduce drift to desired level perform Manual Servo Drift Null Procedure. Manual Servo Drift Null may reduce TADS turret slew rates by up to 50 percent. (Student Handout AH-64D Sights MAY 2013) 105. The Laser Spot Tracker (LST) provides the CPG with the capability of searching for and tracking reflected laser energy of externally designated targets of a selected code. The LST is controlled by the 3 position LT switch on the TEDAC RHG. Placing the LT switch to the “A” (Automatic) position commands the MTADS into an automatic 4-bar scan around the MTADS LOS at the point of engagement. Placing the LT switch to the “M” (Manual) position allows the CPG to use the manual tracker to move the MTADS LOS in the area of interest until the MTADS locks on to returned laser energy. In either mode, when laser energy of the selected code is detected by the LST, it will auto-track the MTADS about the laser energy spot. Placing the LT switch to “O” (Off) will turn the LST off and release the MTADS to normal control. (TM 1-1520-251-10-2, TM 1-1520-263-10) 106. MTADS internal boresight is an aircrew activity that aligns a given sensor to the laser LOS. The crew performs this task to insure sensor alignment is in coincidence with the laser for the use during various weapons engagements. The internal boresight aligns the DTV Narrow and Zoom FOV coincident with the laser LOS (DTV Boresight). It then aligns the FLIR Narrow and Zoom FOV parallel to the DTV LOS. (Student Handout AH-64D Sights MAY 2013) 107. If DTV boresight is complete, then FLIR boresight will be performed. If DTV boresight fails, then FLIR boresight will not be performed. (Student Handout AH- 64D Sights MAY 2013) 108. Internal boresight errors can develop in flight due to temperature changes within the internal components of TADS (thermal drift). The INTERNAL B/S message will be displayed in the High Action Display when the average optics temperature of the last internal boresight reaches its drift threshold. (TM 1-1520-251-10-2, TM 1-1520-263-10) 109. When designating a target, the FOV should be either Narrow or Zoom. Narrow and Zoom are the only FOVs that are boresighted. The sensor selected is up to the crew. (Student Handout AH-64D Sights MAY 2013) 110. The Activation of scene-track prior to performing a gun dynamic harmonization (DH) result in an inaccurate alignment/boresight. Disengage scene-track by engaging linear motion compensation (LMC), or point-track the intended target prior to selecting the HARMONIZATION button. (TM 1-1520-251-10-2) (Note: MTADS 8 only) 111. The LRFD has a maximum value is 9999m. The asterisk is present when the laser is ﬁring and the WP (MP for AH-64E) is receiving valid range data from the laser rangeﬁnder/designator. The asterisk ﬂashes when a multi-target condition is detected in the range data. (Student Handout AH-64D Sights MAY 2013) FCR/RFI 112. The FCR will provide reliable data while maneuvering up to 20° in roll and +20° to -15° in pitch. Flight outside these parameters may result in degraded FCR performance. (TM 1-1520-251-10-2, TM 1-1520-263-10) 113. The FCR is employed in three of the four available modes to perform targeting. Ground targeting is accomplished using GTM and RMAP. Air targeting is accomplished by using ATM. (TM 1-1520-251-10-2, TM 1-1520-263-10) 114. When initially attempting to find the threat, larger scan sizes are required. However, once the targets have been located, a smaller scan size, which directs radar energy in a smaller area, will increase the odds of detecting all targets. (Student Handout AH-64D Sights MAY 2013) 115. A maximum of 16 FCR target symbols are displayed on the FCR page for a given scan. These symbols represent the highest priority targets detected and classiﬁed for that scan. Symbols are displayed in yellow by type target, type of anticipated RF missile launch (LOAL or LOBL), and a condition of moving or stationary. RFI detected emitters which have been correlated with radar target information is displayed by class and type within the scan sector of the format to indicate the threat/target location. The following table displays the FCR target symbols that may be displayed: (TM 1-1520-251-10-2, TM 1-1520-263-10) 116. Target symbols are dimmed after a period of time to indicate that the target data is stale. Moving target symbols become stale after 5 seconds. Stationary target symbols become stale after 30 seconds. (TM 1-1520-251-10-2, TM 1-1520-263- 10) 117. Low priority targets are displayed in partial intensity yellow on the TSD page as a half-size icon. The aircraft is capable of displaying up to 256 FCR target icons on the TSD page. (TM 1-1520-251-10-2, TM 1-1520-263-10) 118. FCR target data is prioritized by the FCR and used to direct the selected weapon against targets and to enhance situational awareness. Three priority schemes are used by the FCR (options A, B, and C). All priority schemes give higher priority to targets merged with RFI emitters and vary only with respect to how unmerged targets are prioritized. FCR priority schemes are summarized as follows: a. Priority scheme A emphasizes airborne and stationary ground targets. b. Priority scheme B emphasizes stationary ground targets. c. Priority scheme C emphasizes airborne and moving ground targets. (TM 1-1520-251-10-2, TM 1-1520-263-10) 119. The NTS symbol is displayed in yellow around the highest priority FCR target symbol to indicate the most signiﬁcant target/threat data derived by the FCR. It is displayed at the completion of the ﬁrst scan of a scanburst. It can also be dis- played around a priority target symbol as selected by the crewmember. The ANTS symbol is displayed in yellow to indicate the alternate NTS target, or #2 priority target in the automatic target selection sequence. The ANTS target is updated at the end of each far bar and is not frozen (e.g., may change as per the selected priority scheme algorithm, scan to scan). Once the NTS target is frozen, and a target is detected that out-prioritizes the NTS target, the ANTS symbol will ﬂash for 3 seconds. The operator can select the cursor enter (prepositioned over NTS upon scan) to choose this target as the NTS. The Second Target Symbol indicates when a high priority target has been selected as a second target for the RF missile shot. The symbol appears in conjunction with that selected target on the display. The RF missile ﬁred uses this information should it encounter difﬁculties in acquiring the primary target, when the RF missile is actioned and a second target is passed to the RF missile. The table below depicts the NTS, ATNS, and Second Target icons. (TM 1-1520-251-10-2, TM 1-1520-263-10) 120. The AN/APR-48A Radar Frequency Interferometer (RFI) is a passive Electronic Support Measure (ESM) system that provides for the detection, acquisition, identiﬁcation, classiﬁcation, location, and prioritization of radar emitters. The RFI is primarily an offensive system providing narrow FOV target cueing for onboard sights/sensors for the accurate and timely employment of weapons. (TM 1-1520- 251-10-2, TM 1-1520-263-10) 121. RFI symbols representing RFI detected emitters are displayed on the periphery of the radar scan sector to indicate the direction to the detected threat. RFI symbols are displayed for the following conditions: d. RFI symbols are displayed in full intensity during the period when the RFI emitters are emitting plus 30 seconds after emitters cease transmissions. e. RFI symbols will be displayed in partial intensity after the emitters become inactive for 31 seconds and not displayed after 90 seconds. f. The highest priority threat symbol (home-plate symbol), or #1 emitter as determined by the system, is displayed in conjunction with the RFI Box symbol (triangle). g. RFI emitters detected within the ﬁne coverage area will be displayed by emitter type and modiﬁer number. h. RFI emitters detected within the coarse coverage area will be displayed by the modiﬁer number. (TM 1-1520-251-10-2, TM 1-1520-263-10) 122. Up to 10 RFI symbols can be displayed. The following table contains RFI icons and their status: (TM 1-1520-251-10-2, TM 1-1520-263-10) 123. The CUED search button is used to quickly orient the FCR to a RFI detected radar emitter to conduct a scan. Selecting the cued search button is a quick way to mode, point, size and initiate the FCR for a scan. (TM 1-1520-251-10-2, TM 1- 1520-263-10) 124. To display the targets the PSP sends the target data to the display processor. Information can be displayed on the FCR page, TSD, anf id C-SCP is selected, in the HDU. Display locations and quantities are: 1) TSD: NAV phase – Up to 16 prioritized targets 2) TSD: ATK phase – Up to 256 targets 3) FCR Page: Up to 16 prioritized targets 4) HDU: If C-SCP is selected, up to 16 prioritized targets FCR Student handout, AH-64D/E (Nov 16) 1-14th AVN REGT SOP 125. The Arming and Safing of the aircraft MASTER ARM will be accomplished by the crewmember not on the controls. 126. For AH-64D/E, the three step safing procedure will be taught and utilized IAW TC 3-04.42 ATM as follows: a. Weapon trigger switch released (Finger off the trigger). b. Weapon action switch deselected (WAS – Deselect weapon). c. ARM/SAFE/ button – SAFE (when time permits - pilot not on the controls). 127. Prior to every engagement, the IP will ensure the student identifies and verifies the data in the acronym SWARM. SWARM for subsequent trigger pulls on the same target without changing weapon or sight is not required. a. S – Sight/Sensor – Select (Link as appropriate). b. W – Weapon Page, WAS (Action appropriate weapon). c. A – Armed. Tgt/Nav, laser, radar, manual, automatic, d. R – Range: default DRMALT i. Range fan/Aircraft Altitude. ii. Range source. iii. Range to the target. e. M – Messages HAD, symbology, and UFD. 128. RSAILS- Students may be taught the following acronym to assist in target engagement. a. R-Recorder (verify recorder on) b. S-Search (normally medium or narrow FOV) c. A-Acquire (locate target and refine image) d. I-Identify (identify target type and confirm hostile) e. L-Lase (lase target to confirm range) f. S-Store (store the target) 129. After both student and IP have verified SWARM, the IP will verbally clear the student to fire with the term “Cleared to Fire,” “Clear to Engage,” or “Match and Shoot.” Range will be verified for each engagement. 130. Aircrews will conduct operations as per FR 95-2 and MAGRC Firing Data and Layouts. Running fire pattern for Clark, Kilo, and Matteson will be at 700 feet MSL +/- 100 feet. On the inbound leg, descend as required to complete engagement. Diving fire pattern for AH-64D/E will be at 1400 feet MSL +/- 100 feet. 131. During running and diving fire, the aircraft will not be flown closer than 300m from the target being engaged. 132. During running fire, the aircraft will not be ARMED until crossing the SFL and weapon is properly aligned within the vertical, left and right firing limits. Aircraft will be SAFED prior to crossing the CFL, anytime an unsafe condition exists or a "cease fire" is announced. 133. During diving fire “aircraft SAFED” is defined as finger off the trigger and the weapons action switch deselected. When conditions permit after the dive recovery is complete, the pilot not on the controls will place the ARM/SAFE button in the SAFE position. During the dive recovery both crewmembers will remain focused outside the aircraft. The primary consideration is aircraft control. 134. Weapon systems and lasers are restricted to the published limitations in MAGRC Firing Data and Layouts. Compliance with Minimum Safe Lasing Altitude (MSLA) for each target is mandatory. 135. Should an armed aircraft go IIMC at the range the crew will perform the steps IAW the aircraft ATM and then: a. Begin a climb to 3500 feet MSL and announce "Cease Fire" on the Molinelli tower frequency. b. If armed, ensure that Cairns is advised of any known or suspected ordinance. c. After landing, the aircraft will be parked on pads Keyhole pads 14 or 15, on a 110° heading. d. The IP/PC will remain with the aircraft until it is de-armed. e. Note: there is no safety berm at the keyholes. 136. Maximum airspeed on Molinelli route structure is 80 KTAS outbound/90 KTAS when returning to the FARP. 137. At no time will anyone be allowed in front of the arming pads. For safety purposes, assume all aircraft on the arming pads are fully armed.

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