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Indication: A misfire is a rocket that has been fired but selected, prior to uncaging the missile. This feature
the launch motor does not ignite. decreases pilot workload and acts to shorten the
Proceed as follows: acquisition timeline during ATAS engagements. Slaving
mode defaults to OFF at power down.
1. Position the aircraft so that rocket is oriented
downrange for a period of 10 minutes. a. Weapon Controls. Weapon controls are shown
in figure 4-55. Control/indicator functions are shown in
2. Upon landing the aircraft Notify explosive figures 4-56 and 4-57.
ordnance disposal.
b. Weapon Configuration. The ATAS system can
be configured for operation by bumping the WEAPON
4-70. (CDS2) ISP/ R MCPU FAILURE SEL switch up selecting the WEAPONS PAGE (fig. 4-
BACKUP MODE OPERATION. 58). The CPG can call up the WEAPONS PAGE by
positioning the WPN/ASE switch momentarily to the
1. MASTER switch ARMED. WPN position on the CPG panel.
2. WEAPON SEL switch Select rockets. NOTE
3. WPN-FIRE switch Press to second detent. To completely check ATAS system, BIT
must be performed on both the MFD and
4-71. AIR-TO-AIR STINGER. PDU (if installed).
The Air-to-Air Stinger (ATAS) missile system (fig. 4-55) c. ATAS BIT. The BIT for the ATAS system can be
is an air-to-air, heat seeking missile system capable of initiated either on the PDU or the MFD. The source of
launching missiles primarily at airborne targets. It the information and where it is displayed will depend on
provides defensive and limited air-to-air combat which source is used to initiate the BIT. Figure 4-59
capability. ATAS is comprised of one or two launchers displays the control/indicator functions.
containing up to two missiles each, and the necessary
components, software, and switches to operate the (1) The PDU BIT results will be displayed on the
system. The ATAS launcher(s) can be jettisoned using PDU. A successful BIT will be indicated by the word
the JETTISON switches located on the ACP. The PASS being displayed on the PDU. An unsuccessful
weapon is electrically controlled and powered by the 28 BIT will be indicated by the word FAIL being displayed
Vdc essential bus. Circuit protection is provided by the along with a list of the failed components.
ATAS PWR and ARMT CONTR circuit breakers located (2) Initiating the ATAS BIT causes the ATAS BIT
on the aft centerpost circuit breaker panel. The ATAS MFD display to be boxed. ATAS BIT will unbox and the
launcher(s) are mounted on the ejector rack. They may BIT results will appear adjacent to L-5 when the BIT is
be installed on one or both sides. Symmetrical loading complete. A successful BIT will be indicated by
is not required. displaying IEA GO. An unsuccessful BIT will be
On helicopters equipped with Block 1 IEA, an automatic indicated by displaying IEA NO GO. If any launcher
seeker recage function is provided. This allows the pilot fails BIT (fig. 4-60), the launcher fail message is
to maintain the WPN-FIRE switch in the first detent displayed by placing an X over the missile symbols.
while the system evaluates and recages the seeker if (a) The number of missiles are indicated by a
signal threshold drops below a given level. In this way display of a like number of missile symbols without an
the system will reject cloud edge, terrain, and other X over the symbol.
false targets without the pilot having to release the
detent. This function works with any Stinger missile. (b) If there are no missiles installed, or the
Additionally, the Block 1 missile will receive a tailored launcher is not installed, the status section for that
data load from the IEA which orients the missile launcher is blank.
vertically and eliminates the need to superelevate the
helicopter prior to missile launch. All other visual and d. (CDS2) ISP/ R MCPU Failure. (CDS2) ISP/
audio firing constraints apply. Basic, Post, and RMP R MCPU failure causes the system to default
missiles still require the helicopter be super elevated allowing the ATAS to be operated in the backup mode.
before missile launch. Therefore, it is imperative during The following default conditions will exist while
preflight the crew inspects for missile type (if loaded), operating in the backup mode:
4-96
TM 1-1520-248-10
PULL
MAN
PULL
BKUP
BRT
C
ONT
300 330 N 030 060 E
W 00
000
90
0.7 NM
29T
PP
HI
100
LO
25
16
90
ATAS
ARMED
ACTIVE
N 32° 48.16´
W 97° 09.59´
VID
TIS
UNCAGE
AUTO
W
HOT
SLAVING
ON
Figure 4-55. ATAS Weapon System
4-97
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TECHNICAL MANUAL OPERATOR’S MANUAL FOR ARMY OH-58D HELICOPT(119)
