Hydra Rocket System Integration Information

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					                                     Hydra-70 Rocket System
                                      Integration Information


   HYDRA-70 Rockets are free flight rockets which mate either unitary or cargo warheads with
the MK 66 Rocket Motor. The MK 66 motors use a longer motor tube (than the MK 40/MK 4)


fins are of a spring loaded, wrap-around design and are attached around the circumference of the
single nozzle. The propellant grain is longer and of a different formation than for the MK 40/MK
4, however, the stabilizing rod and igniter are essentially the same design. The MK 66 motors
have a substantially higher thrust, 1335 lbs, and a longer range. The current generation of the MK
66 in use by U.S. Armed Services are the MK 66 MOD 3 for the Army and the MK 66 MOD 2
The RF filter is mounted onto the igniter can and allows the aircraft’s direct current firing pulse to
May 1987 documents the HERO suitability of the MK 66 MOD 3 motor. A brass EMR shield is
used over the fin and nozzle to prevent the DC energy produced by electrical arcing encountered
inventory of available rockets.
MK 26 MOD 0 Initiator bridgewire.

Tabulated data:
       Weight, shipped: 13.6 lb                              Igniter resistance: 0.7 - 2.0 ohms
       Burn time: 1.05 - 1.10 sec                            Propellant Type: Extruded double base,
       Average thrust (77 oF): 1300 - 1370 lb                                      ethylcellulose inhibited,
       Impulse (77 oF): 1472 lb/sec                                                cartridge loaded
       Motor burnout range: 1300 ft (397 m)                  Propellant Weight: 7 lb
       Motor burnout velocity: 2425 fps                      Propellant Configuration: 8-point internal
       Launch spin rate: 10 rps                                                               burning star
       Velocity at launcher exit: 148 fps                    Temperature Limits:
       Acceleration: 60-70 G (initial),                                Storage: -65 oF to +165 oF
                      95-100 G (final)                                            (-53.35 oC to +73.15 oC)
       Range, max @ QE 43o                                             Operation: -50 oF to +150 oF
        w/ MPSM whd: 11,407 yd (10,426 m)                                            (-45 oC to +64.9 oC)
                      M151 Warhead

                              M229 Warhead

    Both the M151 and M229 use the M423 Fuze, making them High Explosive Point Detonating
(HEPD) warheads. The M151 uses 2.3 pounds of composition B-4 High Explosive. The 10
pound warhead gains lethality from the nose section which is fabricated using nodular, pearlitic
malleable, or ferritic malleable cast iron. The 17 pound M229 uses 4.8 pounds of composition B-
4 High Explosive. The performance of the M229 is roughly a 50 percent increase in lethal area
over the M151. Temperature limits for storage and firing the M151 and M229 are -65 oF to +150
 F (-53.35 oC to +64.9 oC).
    The M423 Fuze consists of four major assemblies: firing pin and body assembly; fuze body;
safe and arming (S&A) device; and the booster assembly. The S&A device consists of a rotor
housing assembly and unbalanced rotor assembly, an escapement assembly and set-back weight.
The unbalanced rotor assembly houses the primer and detonator and is maintained in the unarmed
(out-of-line) position. When the rocket motor is fired, sustained acceleration permits the set-back
(inertial mass) weight to move rearward, releasing the unbalanced rotor, which in rotating drives
the escapement and gear assembly to the armed position. The rotor reaches the armed (in line)
position when the rocket has traveled 43 to 93 meters and then is locked into the armed position
by a spring-loaded pin. The rotor will return to the unarmed position if the minimum rocket
energy (product of acceleration and time) is not sensed throughout the arming distance. Upon
impact, the firing pin body walls are crushed between the target and the oncoming fuze body. The
firing pin contained in the firing pin body then impacts the oncoming S&A mechanism within the
fuze body, initiating the explosive train. The explosive consists of the M104 primer, M85
detonator, lead, booster and warhead explosive which are initiated in sequential order. The M423
is used for launch from low speed aircraft. The M427 is a variation used for launch from high
speed aircraft and requires 180 to 426 meters rocket travel to arm. The PD fuzes do not require
an umbilical connection to the launcher.

Tabulated data:
       M151 HEPD Rocket w/ MK 66 MOD 3 Motor
       DODIC: H583
       Hazard Classification: Quantity-Distance Class 1.1, Storage Compatibility Group E
       UNO Serial No. 0181
       DOT Label "Explosive 1.1E", Proper Shipping Name "Rockets"

       M151 Warhead w/ M427
       NSN: 1340-00-725-8382
       DODIC: H842.

       M229 HEPD Rocket w/ MK 66 MOD 2 Motor
       NSN: 1340-01-309-8300
       DODIC: H642
       UNO Serial No. 0181
       DOT Label "Explosive 1.1E", Proper Shipping Name "Rockets with Bursting Charge".

an integral fuze, 9 submunitions, and an expulsion charge assembly. The nose cone assembly, a
of 80% M10 double base propellant and 20% Class 6 black powder. The expulsion charge is
stack of submunitions through the nose cone.
    The primary cargo warhead fuze is the M439 Fuze. It is a resistance-capacitance electronic
variable time delay fuze. The time delay is remotely set for the desired functioning distance (time)
by charging the circuit from the fire control center, providing a variable range of 0.5 to 7.2
kilometers. The fuze does not have an internal battery; instead energy is supplied from by the
aircraft setter at the time of fuze setting. The energy is stored in a capacitor and will operate the
electronic timer and fire the M84 electronic detonator. The charging cycle takes place
approximately 50 milliseconds prior to rocket motor firing. The fuze begins timing at the first
motion of the rocket and will function at the prescribed time if the Safety and Arming (S&A)
device is armed. The S&A mechanism also prevents the fuze from being charged if it is in the
partially-armed or fully-armed position. The S&A is a mechanical acceleration integrator with an
unbalanced rotor holding the M84 electric detonator and a runaway escapement. An acceleration
greater than 27G is necessary to arm the fuze. The M439 Fuze is a base mounted, forward firing
fuze. The fuze connector cable extends from the fuze, through the warhead in a lengthwise
channel, and exits the ogive for connection to the launcher by an umbilical connector.
   The HE, MPSM M73 Grenade consists of a steel body with a fragmenting wall filled with
Composition B explosive incorporating a shaped charge liner, LX14 booster, explosive lead
charge, M230 omnidirectional fuze with M55 detonator, wave shaper, and fabric drag device
(RAD). The fragmenting body produces 10 grain fragments with a maximum velocity of
approximately 5,000 feet per second. The shaped charge sprays lethal fragments nearly horizontal
360 degrees. The submunitions consistently impact within a 40-meter radius of each other.
Submunition self destruct has not been a consideration. EOD procedures obviate the need for self
destruct. Lethality (penetration) is classified and can be made available through licensed
agreement. The performance is roughly a 70 percent (SMCAR-CCH-A Memorandum, 23 Jun
1988) increase in lethal area over the M151.

Tabulated data:
       M261 MPSM Rocket w/ MK 66 MOD 3 Motor
       NSN: 1340-01-269-1447
       DODIC: H165
       Hazard Classification: Quantity-Distance Class 1.2, Storage Compatibility Group E
       UNO Serial No. 0182
       DOT Label "Explosive 1.2E", Proper Shipping Name "Rockets".
       Temperature Limits:
               Firing: -50 oF to +150 oF
               Storage: -50 oF to +160 oF

    The M255A1 Flechette Warhead is intended to be used against light material and personnel
targets. The warhead is also a cargo warhead, using the M439 Fuze, and functionally equivalent
to the M261 cargo warhead. At expulsion, 1,179 flechettes separate and form a disk-like mass
which breaks up with each flechette assuming an independent trajectory, forming a repeatable
produce the desired impact and penetration effect on the target.
Tabulated data:

       M255A1 Flechette w/ MK 66 MOD 2 Motor
       NSN: 1340-01-309-5799
       DODIC: H462
       Flechette: 60 grain, steel, phosphate coated
       Hazard Classification: Quantity-Distance Class 1.4, Storage Compatibility Group G
       UNO Serial No. 0191
       DOT Label "Explosive 1.4G", Proper Shipping Name Rockets"
    The M264 RP Smoke is also a cargo warhead. The warhead is used as a red phosphorus (RP)
filled smoke rocket propelled by the MK 66 motor and functions at a remote settable range from
1000 to 6000 meters. Upon functioning, the M439 Fuze ignites the expulsion mix which
rows of 4 each and are separated by felt pieces impregnated with a phosphine gas adsorbent
mixture, manganese dioxide/cuprous oxide.

Tabulated data:

       M264 RP Smoke w/ MK 66 MOD 3 Motor
       NSN: 1340-01-289-4719
       DODIC: H184
       RP: JXS-10 Smoke Composition Pellets, 0.035 kg/wedge (31.5 gms)
       UNO Serial No.
       DOT Label "Explosive 1.4G", Proper Shipping Name Rockets"
    The M257 illuminating warhead consists of an ignition system, flare, main parachute, drogue
feet at 3000 meters downrange. The M257 candle descends at 15 feet per second, burns for
    Except for the illuminent, the M278 is identical to the M257 warhead. At the aft end of the
Separation and Drogue Assembly is the Motor Adapter which is the threaded interface for the
launch rocket motor. Inside the adapter is the M442 fuze which initiates the firing sequence for
the M278 flare. The fuze must sense an acceleration of at least 17-22 G for about 1 second prior
to arming. Upon deceleration of the burnt-out rocket motor the armed fuze fires, directing its
output into a 9-second pyrotechnic delay column which in turn ignites a separation charge. The
separation charge produces a rapid increase in pressure inside the motor adapter which is reacted
by a pusher plate on top of the Drogue Housing. This shears 12 holding pins that are evenly
spaced around the circumference of the joint. The pressure also provides an accelerating force for
the flare and a decelerating force for the launching rocket motor with the Motor Adapter
attached. This ensures positive separation for the flare, and a Deflector plate pulls the expended
motor out of the flare flight path. When the Pusher Plate falls into the airstream it pulls the
Drogue Chute out of the aft end of the Drogue Housing. Attached to the shroud line bridle of the
Drogue Chute is a nylon cord which is attached to the Pull Wire “Quickmatch” of a 2-second

delay “Gas Generator.” The Quickmatch ignites the delay, which in turn fires a Secondary
Expulsion charge. This charge functions as the first, producing pressure that shears another set of
12 pins, evenly spaced around the circumference of the flare. Once again the pressure provides an
acceleration/deceleration force to the Drogue Housing and the Candle & Parachute Assembly.
Attached to the Pusher Plate is the cord for the Pilot Chute. As the Pilot Chute deploys, it pulls
the Main Chute assembly out of its housing (Parachute Insert) for Main Chute deployment.
Attached to the Main Chute support cable is a Lanyard that runs through an internal raceway in
the Candle and is attached to the Slider assembly in the Igniter assembly. As the main chute is
deployed, it pulls the Lanyard with a minimum force of 40 pounds. This force shears a shear pin
and moves the slider assembly into the firing position, cocks and releases the firing hammer and
fires the ignition primer. During launch of the Rocket, acceleration forces of at least 17 G for
duration of approximately one second withdrew the weight assembly of the “Zig-Zag” ignition
safe/arm mechanism from its saving position in the slider assembly, allowing Slider movement.
The output of the ignition primer is directed into a cavity containing boron pellets. The fire from
the boron pellets is directed on the forward face of the flare’s illuminant Candle and also on a
small propellant wafer which acts as an ignition booster. The Candle produces light in the near IR
spectrum for about 180 seconds. The main parachute allows for a descent rate of approximately
13 feet per second.

Tabulated data:

       M257 Illumination Flare w/ M442 Fuze
       Operating temperature limits: -25 oF to +140 oF
                                         (-31.35 oC to +59.40 oC)
       Candle composition: Magnesium Sodium Nitrate
       Candle weight: 5.44 lb (2.47 kg)
       Illumination intensity, visible: 817.19 CP (avg.)
                               infrared: 250.02 watts/sr (avg.)
       Illumination duration: 197.38 sec (avg.)
       Function time: 14.23 sec (avg.)
       Shipping and storage data:
                Storage class/SCG: 1.2 G
                DOT shipping class: A
                DOT designation: Rocket Ammunition with Illuminating Projectile
                Field Storage: Group D

       NSN: 1340-01-268-7175
       DODIC: H183
       UNO Serial No.

       M278 IR Flare w/ M442 Fuze
       DODIC: H154
       UNO Serial No.

the 7-tube launcher continues to use a laminated stack.
experiences from the fire control is 0.06 seconds.
minimize the heat signature of the launcher after rocket firings.
                   RMS Display Unit                           RMS Operations Unit

    The M138 Rocket Management Subsystem (RMS) is a pilot-operated subsystem that
interfaces with the wing stores subsystem in the helicopter. The RMS operates from power
supplied by the aircraft and consists of one Display Unit and four Operations Units. The RMS
enables the aircraft pilot to select and launch MK 40 or MK 66 rocket motors with the desired
warhead/fuze combination from two or four 7- or 19-tube launchers mounted under the aircraft
stub wings. The RMS automatically senses the quantity and type of launcher installed and
automatically sets its firing sequence to agree with the tube numbering of the launcher on board.
Should one or more launchers be disabled, the RMS will cause the corresponding launcher on the
opposite side of the fuselage to become inactive to maintain in-flight stability by equalizing the
load of unfired rockets.
    Rockets are loaded according to type (warhead/fuze) in up to five loading zones, and the types
loaded in each zone are indicated by manually setting five 12-position thumb wheel switches on
the Display Unit panel. The switch positions are marked with two- or three-letter descriptors that
represent the available warhead/fuze configurations. When power is applied to the RMS, it
automatically inventories the rounds loaded in each zone and provides the pilot with a numeric
display of the quantities available for launching from each zone. By setting switches on the face
of the Display Unit, the pilot can select the rocket types to be launched, set the fuzes according to
the tactical situation, and determine the quantities of rockets to be launched in each volley.
Rockets are then launched when the pilot or copilot/gunner squeezes the trigger switch on the
cyclic stick. Should the trigger switch be released before the entire volley has been launched, the
numeric display on the face of the Display Unit is immediately updated to continuously reflect the
quantities of rockets remaining in each loading zone. Refer to TM 9-1090-207-13&P for
additional information pertaining to RMS components.
    The primary objectives of the remotely settable fuze concept were to use very inexpensive
components in the fuze itself, eliminate any battery required to run the electronics during the fuze
run time, and accomplish the accuracy goals throughout the total environmental range. The
solution was to select a resistance-capacitance technique wherein relatively inexpensive, broad-
tolerance (+/- 20 percent) components could be used for high-volume production of relatively
inexpensive electronic fuzes. To accurately set the capacitance-charged fuzes for the desired run
time throughout the environmental range requires a compensating setter located in the aircraft.
The setter, immediately prior to launching a rocket, determines the amount of energy required by
the fuze timing capacitor for the component variations existing along with temperature effects to
run the fuze timing circuitry for the range selected. The setter then charges the timing capacitor
and the storage capacitor used as both the power source to run the electronics and the power
source to initiate the pyrotechnic train through initiation of the electric detonator in the fuze
safeing and arming device. The setter must be capable of compensating for 20 percent variations
in component value and for variations in fuze run time due to temperature effects on individual
fuzes. Since each fuze is unique, each fuze must receive a different amount of energy in its timing
sequence, whether it be singles, pairs, or quads, fuzes must therefore receive different amounts of
energy to accomplish the same set time. Therefore, just prior to firing, the individual fuze and its
setter compose an integral subsystem which must perform its function accurately across the entire
environmental spectrum, compensating for inherent errors in individual fuzes.
    The Display Unit is a cockpit-mounted line-replaceable unit that presents the pilot with
controls and displays for inventorying and controlling the launching of aerial rockets. It also
contains the power supply and other common circuits necessary for the RMS components to
operate as a subsystem. The Display Unit transmits the electrical command signals selected by the
pilot to the Operations Units. One Operations Unit is used for each launcher and contains the
circuitry that sets the fuzes and the circuitry that provides the rocket motor squib firing pulses for
the rockets loaded into the associated launcher.
    Additional description of the RMS is contained in enclosure 1. This is an early system
description as taken from material used for training (extraneous pages have been extracted) of
what eventually became the M138 RMS. It was originally fitted into the AH-1S model of the
Cobra helicopter. The weight of the display unit is 6 pounds and of the operations unit is 2
pounds each. The NSN for the M138 RMS is 1090-01-077-8939. A variation of this system
known as the Armament Management System was fitted into the AH-1G model of the Cobra
helicopter. It uses two zones and was intended as an interim solution for an eventual upgrade to
the M138 RMS.

1.1 & 1.2 Physical Characteristics of the rocket system. The lengths, weights, centers of gravity
and moments of inertia of the various rockets (MK 66) as measured are as follows:

  The length of the M261 LWL was previously defined as 66.190" (max). The weight, CG and
moments for the M261 LWL are as follows:

       M261 Lightweight                                Empty                         Loaded
       Weight (lbs.)                                    82                            596
       CG aft of nose (in.)                            35.8                           28.3
       CG above center line (in.)                      0.78                           0.14
       CG left of center line (in.)                    0.033                          0.004
       Pitch moment (slug-ft2)                         7.12                           54.37
       Yaw moment (slug-ft2)                           7.28                           54.52
       Roll moment (slug-ft2)                          0.629                          3.37

                  Weight, lbs                                CG from base      Moments of Inertia, lb-in2
                         Rocket             Length       (inches)             Live                   Fired
              Warhead      Live     Fired   (inches)      Live        Fired   Axial    Transverse    Axial   Transverse
MK66 Motor      ----      13.65     6.43    41.750        18.89      15.70    15.80      2032        9.30      1371
M151           9.30       22.95    15.73    55.125        29.96      33.55    26.20      6248        19.70     5008
HE/M423 PD
w/ MK66
M229           16.87      30.43    23.19    65.240        36.55      41.20    37.60      10479       29.60     7840
HE/M423 PD
w/ MK66
M261           13.50      27.15    19.93    66.100        35.26      40.02    29.40      9868        23.30     7595
w/ MK66
M255A1/M439    13.87      27.51    20.34    66.100        35.36      40.00    28.80      9848        22.10     7529
w/ MK66
M257/M442      10.57      24.22    17.00    70.400        34.75      40.04    27.60      10607       21.70     8383
w/ MK66
M264/M439      8.00       21.65    14.43    66.100        30.84      35.11    23.70      7639        17.00     6209
w/ MK66

                                  Physical Characteristics of Rockets
    The centers of gravity for the M261 LWL when fully loaded with the following rockets are as

       Configuration                    CG (in. from front)           Weight (lbs.)
       Empty                                    35.8                       82.0
       M151/M423/MK 66                          33.1                       518
       M229/M423/MK 66                          27.2                       660
       M257/M442/MK 66                          29.0                       542
       M264/M439/MK 66                          32.4                       493
       M261/M439/MK 66                          28.5                       598
       M255A1/M439/MK 66                        28.4                       604

1.3 Aerodynamic data of the M261. Please refer to excerpts of MIL-A-8591 at enclosure 2 for
calculation and modeling methods for aerodynamic loads. An example calculation performed by
Hughes Aircraft, the designer of the LWL, is attached at the back of the enclosure. Airflow
information would be unique to the aircraft platform and should be available from the U.S. Army
Aviation and Troop Support Command (ATCOM).

1.4 Qualification standards. Specifications which control the acceptance of rockets are listed in
the chart below. The specification for the LWL is MIS-34583. The RMS is per enclosure 3.
1.5 Environmental influence to the helicopter. The MK 66 motor can eject the ignition wire upon
launch. On more rare occasions, the MK 66 MOD 2 motor can eject the stabilizing rod upon
launch. Observance of this occurrence indicates that approximately 50 percent are just after the
rocket has left the launcher. The MK 66 MOD 4 motor has a more robust design for the
stabilizing rod that should preclude ejection.
   Chemical and thermal effects are taken from IHSP 89-289. Theoretical combustion products
appear in Table IV of this document and is shown below. The exhaust-induced pressure
experienced in each launcher tube is 318 psi, measured near the aft end of the launcher.


2.1 Electrical Interface. The LWL electrical continuity shall be as specified in drawing 13048860
for the M261 launcher (Type II launcher). When a device that selectively simulates the electrical
characteristics of an electrically shorted motor of either the MK 40 or MK 66 type is loaded in a
launcher tube, the total circuit resistance from that launch tube connector pin in connector J1 to
the ground pin in the J1 connector shall not exceed 1 ohm with an applied current of not less than
1 milliampere or not more than 700 milliamperes. Resistance will be tested with both the MK 40
and MK 66 motors. The resistance of the electrical circuits between J2 and P, and J2 and ground
shall not exceed 0.20 ohm with an applied current of not greater than 700 milliamperes. The
insulation resistance between isolated circuits and ground shall be equal to or greater than
500,000 ohms at 500 volts direct current (Vdc). With the negative return connected to pin Z of
connector P, application of the system fuzing signal from the RMS to pins A through V of
connector J2 shall supply fuze set voltage to rockets loaded in tubes 1 through 19 respectively.
With the negative return of ignition circuit connected to pin Y and/or Z of connector J1, the
application of a fire signal of a minimum of 1 ampere for a minimum of 10 milliseconds from the
RMS to pins A through V of connector J1 shall supply ignition voltage to rockets loaded in tubes
1 through 19 respectively.
2.2 Description of the functional sequences. The pilot dials in the rocket type and quantity to be
fired on the RMS. The RMS designates this data to the Fire Control Computer (FCC) of the
aircraft, and the FCC selects the trajectory
data from memory. The electronic fuze setter
in the RMS will set the fuze when the pilot
depresses the firing trigger. The gunner in the
front seat of the Cobra sights in on the target
through the telescopic sight unit and lases to
obtain constantly updated range data. The
aircraft FCC processes this data along with
aircraft speed, relative wind, temperature and
flight characteristics of the rocket, and
computes the point at which the fuze must
function for the intended target. The
computer then presents a solution reticle
through the heads up display (HUD) to the
pilot in the back seat. The pilot must match the solution reticle to the boresight reticle on the
HUD by maneuvering the aircraft and firing the weapon system. The computer continues to
constantly update the solutions as the aircraft moves along. The pilot pitches the aircraft up,
aligns the boresight reticle with the solution reticle and depresses the firing trigger. The fuze
receives the latest ranging data about 50 milliseconds prior to the
rocket motor being fired. The following is a listing of Field Manuals
used in the employment of rockets:

Explosives and Demolitions                           FM 5-25
Ordnance General and Depot Support Services          FM 9-4
Ordnance Ammunition Service                          FM 9-6
Attack Helicopter Gunnery                            FM 17-40
Attack Helicopter Operations                         FM 17-50

2.3 Power consumption. The rocket management system requires
24-28 VDC.

Electromagnetic Environmental Effects (E3) Management, Design, and Test Requirements and
SARD-DO Memorandum, Subject: Army Acquisition Executive Policy Memorandum 91-3, Army
Electromagnetic Environmental Effects (E3) Program Implementation establish design
requirements. As stated previously, the MK 66 MOD 4 Rocket Motor is HERO, 300 KV and 25
therefore do not present any E3 concerns. The M255A1 and M264 warheads are recent
the potential to be affected by E3. Naval Surface Weapons Center (H22-BF/RFM) Letter, dated
22 Jan 87, Subject: Hazards of Electromagnetic Radiation to Ordnance Test Report of the Rocket
Management System showed that the M439 Fuze is “HERO SAFE ORDNANCE” and will not be
affected by the HERO environment during presence, handling and loading. The M439 Fuze was
tested for Electrostatic Discharge (ESD) susceptibility with an inert warhead and found to be
sufficiently hardened to personnel-borne ESD. As a result, there are no E3 concerns associated
with either warhead/fuze combination. While documentation does not exist for older designs,
similar results can be expected for warheads fuzed with the M439 Fuze. A fact to consider is that
the M439 Fuze is inherently shielded by the warhead case and by the motor when mated as a

3. Software Modification. Software modifications are conducted by the host aircraft and may be
discussed with the U.S. Army AMCOM. The ballistic tables are established for rounds as they are
developed by U.S. Army engineering centers and are submitted to AMCOM. Language and bus
interfaces are determined by the developer of the aircraft fire control computer.

4. Test Equipment. The Rocket Management Subsystem Test Set, M135 (RMS Test Set), is a
manually operated portable test set which automatically tests Line Replaceable Units (LRU) of the
RMS, using programmed test routines initiated, as applicable, by the test set operator. The test set
is used at the AVIM level to verify equipment failures that were detected by the built-in-test
circuits in the RMS LRUs and to isolate troubles in these units to a shop-replaceable assembly. It
is also used for verifying the performance of a unit after repair or at any other time. The
maintenance manual for the M135 is “Operator’s Aviation Unit, and Intermediate Maintenance
Manual with Repair Parts and Special Tools List for Test Set,
Rocket Management Subsystem, M135, TM9-4933-227-13&P.”

5. Rocket system electrical checks are performed in accordance
with the following procedures.