Extract (Pages 42–84)
Dthind Archive — Phoenix Class Reference, Rev 03
Note: Phoenix is a limited dual-mode trans-resonant vehicle optimized for high-speed atmospheric transit and short-range Nether-assisted repositioning. The vehicle is not intended for sustained interplanetary habitation. Seat configuration: two forward seats only. No built-in sanitation. Passenger survival provisions limited to standard flight packs.
Vehicle Overview
1. Purpose
1.1 The Phoenix is designed for rapid point to point travel inside a planetary gravitational well and limited translation-assisted repositioning using phase resonator alignment.
1.2 Primary mission sets: covert transit, high-speed atmospheric routing, rapid-response insertion, discrete surveillance. Secondary: short radius salvage, limited tactical engagement.
2. Physical Characteristics
2.1 Length: 4.8 meters. Width: 1.9 meters. Height: 1.2 meters (cockpit lowered). Curb weight nominal: 1,850 kg (structural composite, coherence lattice active).
2.2 Cabin: Two seats with lateral harness, integrated G support, direct neural interface port on pilot seat optional.
3. System Limitations
3.1 Net effect: Phoenix has limited Nether interaction. Navigation can perform phase jumps only within mapped Translation Layer corridors. Long-range displacements require support from Dthind class infrastructure.
3.2 Endurance: 6 hours full systems nominal in atmospheric operation before auxiliary recharge required. Nether-assist reposition consumes coherence allotment; repeated use reduces local Coherence Index resilience.
Cockpit Layout And Control Mapping
1. Primary Control Inputs (Yoke Design)
1.1 The Phoenix uses a single yoke-style control column (N-Yoke). The yoke functions as combined attitude and linear vector input. Movement mapping:
• Left/Right roll: lateral axis control (banking).
• Forward/Back pitch: pitch axis (nose up / nose down) and axial thrust modulation when in flight-assist mode.
• Combined forward+left: coordinated up and left vector translation. The control mixing algorithm resolves X, Y, Z outputs based on current flight mode.
• Twist (rotation around longitudinal axis): differential yaw input for low-speed or ground handling.
1.2 Push/pull sensitivity is configurable in the pilot profile. Default linear response is set to 25% deadband with exponential curve beyond 30% deflection.
2. Secondary Controls
2.1 Left thumb cluster: primary nav mode toggles, phase lock engage, target display select.
2.2 Right thumb cluster: weapons arming and safety, sensor override, camera control for roof mount.
2.3 Central column ring: manual inertial dampener bias control (fine), attention only for training or diagnostic override.
3. Foot Controls
3.1 Single pedal pair: differential brake / reverse thruster modulation when on ground and in APP. Top pedal surface integrates pedal pressure sensor for fine yaw inputs at low speeds.
3.2 Pedal detents include neutral, braking, and emergency reverse positions.
4. Throttle And Power Management
4.1 Central console throttle lever: proportional power allocation from Gravitic Translation Core (GTC) to Field Converters and Reactionless Vectoring Jets.
4.2 Thumb safety on throttle prevents inadvertent full-power transition. Must be depressed and held for ND-01 engage.
5. Displays And Feedback
5.1 HUD: multi-phase overlay with Physics Readout, Coherence Index, Resonance Lock quality, G load, field integrity.
5.2 Curved dash: customizable layouts. Critical readouts are: GTC output, Coherence Index (CI), Resonator lock strength (RU), hull lattice integrity (percent), inertial dampener status (on/off/derated).
5.3 Alerts: tone plus visual. Red: Critical. Amber: Caution. Green: Normal.
Izzy note: If the HUD goes orange and your stomach goes wrong, ask yourself if you wanted to be a philosophy major or a pilot.
[SYS LOG — Dave: Display mapping updated to user Izzy profile. Throttle response increased by 2.3 percent. Pilot confidence not measured.]
Flight Modes And Definitions
1. Surface Mode
1.1 Vehicle behaves like a high performance ground vehicle. Wheels active for steering. Reactionless assist disabled. Use for normal driving and ground transport.
2. Atmospheric Propulsion Mode (APP)
2.1 Traditional aerodynamic flight augmented by vectoring jets and field shaping. In APP aerodynamic control surfaces and vectoring jets handle lift and maneuvering. Inertial dampeners provide up to 6 G sustained comfort envelope. Higher G values are achievable but may cause biological stress or dampener derate.
3. Sub-Orbital Mode
3.1 Combined APP and Translation Layer interaction. Vehicle attains near-space trajectories within atmosphere but remains within Translation Layer corridors for navigation assistance.
4. Nether-Assisted Navigation Mode (Phase Assist)
4.1 Limited phase alignment procedure that sequences the Phase Resonator with Translation Layer signatures. Not a true long-range jump. Use to collapse effective distance within a mapped corridor and permit rapid repositioning (e.g. intercontinental transit in minutes for short-range corridors).
4.2 Operational CI minimum: 0.85. RU lock > 0.92 recommended. See ND-01 procedure.
5. Emergency Re-Phase
5.1 Forced partial phase reinstantiation for catastrophic failure recovery. High risk of ghosting and component desync. Only execute per emergency checklist.
Propulsion Systems
1. Gravitic Translation Core (GTC)
1.1 The GTC is the primary source of phase power. It does not produce combustion. GTC manages coherence pressure throughput. Output measured in Resonance Units (RU). Nominal GTC output: 1,200 RU. Peak short burst: 1,800 RU for up to 30 seconds.
2. Field Converters
2.1 Convert RU into local field shaping for inertial dampeners and hull lattice stabilization. Field converters maintain cabin integrity and allow window opening procedures while preserving local pressurization within the coherence envelope.
3. Reactionless Vectoring Jets (RVJ)
3.1 Work in APP for attitude and low-speed thrust. In high-speed profile RVJ vectors are modulated to complement field shaping rather than provide primary acceleration.
4. Propulsion Modes And Limits
4.1 Atmospheric cruise typical: 3,200–12,000 mph depending on altitude and air density.
4.2 Surface sprint mode (wheels engaged) 0–220 mph.
4.3 Maximum safe atmospheric speed: 25,500 mph indicated for short bursts in thin atmosphere only. Sustained exposure above 20,000 mph increases hull shear risk and CI drift.
4.4 Phase assist reposition typical expense: 150–450 RU per short corridor hop depending on lock complexity.
Izzy note: If you see a town get smaller in a way that feels personal, you probably hit 10,000 mph. Smile or vomit depending on your religion.
ND-01 Procedure: Transition To Nether-Assisted Navigation (Phase Assist)
Prerequisite checks
• Coherence Index (CI) >= 0.85.
• Resonator lock map acquired and validated.
• GTC output verified and field converters nominal.
• Crew safety harness latched, HUD active.
• External environment free of large scale anomalies.
Step sequence
1. Set throttle to 0. Remove wheel lock if applied. Confirm wheels retracted if in flight.
2. Engage Phase Resonator standby (left thumb cluster). Watch RU readout stabilize to nominal 200 RU.
3. Select target node from dynamic overlay. Confirm dynamic corridor integrity and node authority.
4. Depress and hold throttle safety while nudging throttle to 10 percent. Observe initial harmonic coupling. RU trending must approach planned lock.
5. When RU lock strength > 0.92 and CI >= 0.86, move throttle forward to 40 percent. Field converters should ramp. Confirm no red fault lights.
6. If at any time resonator lock degrades by > 0.06 RU, abort and throttle to neutral. Perform lock re-acquisition.
7. At stable lock, release safety and move throttle to engage phase assist. Expect immediate reduction in perceived distance. Monitor G load and dampener status.
Abort procedure
• If any green indicators move to amber, reduce throttle to 20 percent and maintain lock attempt.
• If faults appear or CI drops below 0.82, execute immediate phase abort: hold throttle safety and pull to neutral. Engage manual APP control.
[SYS LOG — Dave: ND-01 success probability is proportional to mapping fidelity. I distrust 'probability' as a concept. Proceed with caution.]
Flight Dynamics And Handling
1. Inertial Dampening
1.1 The inertial dampeners translate field gradients into local acceleration compensation. Nominal dampening reduces experienced acceleration by factor of 10 compared to raw acceleration. Example: 50 G raw equals 5 G felt when dampeners within spec.
1.2 Dampener derate threshold: CI < 0.80 or field converter temperature > 85 percent will reduce compensation proportionally.
2. Handling Characteristics
2.1 At low altitude and high speed, control authority shifts from aerodynamic surfaces to field shaping. Bank and pitch inputs are moderated by flight computer to maintain lattice integrity.
2.2 Manual control mode exists for training. In manual mode pilot inputs require greater precision and produce increased feel and delayed response.
3. Stall And Recovery
3.1 Traditional aerodynamic stall is mitigated by field lift augmentation. In practice, stalls convert to loss of vectoring authority. Recovery: reduce angle of attack, increase thrust vector, re-engage field lift at 30 percent throttle.
4. Low-Level Surfing Techniques
4.1 For low-level transit at extreme speeds, maintain a minimum altitude buffer of 30 meters above surface. Use predictive field shaping to reshape airflow. Avoid canyon runs under 20 meters unless mission-authorized. Maintain lateral scan for immediate obstacle avoidance.
Izzy note: Canyon runs are fun. Do them legally and with a will written and signed in triplicate.
Sensors, Imaging And Sunroof Photography Protocol
1. External Camera Mount (Roof Z8)
1.1 Roof mount supports a stabilized Nikon Z8 class camera. Camera mount is integrated with the ship's gimbal and resonance dampening to permit ultra-low vibration shots. Use sensor mode "external stabilized" for planetary photography.
2. Sunroof Window Operation
2.1 The coherence envelope permits local window opening while maintaining cabin pressurization within the immediate field bubble. Window open procedure:
• Confirm local field integrity > 98 percent.
• Engage window actuator; HUD will display break threshold.
• Manual safety: pilot must hold window override for the duration of exposure.
2.2 Limit exposure duration to 180 seconds continuous. Risk of microdecoherence increases nonlinearly with exposure. For long exposures, alternate windows and allow field to resettle.
3. Photography Guidelines (Nikon Z8 Settings Suggested)
3.1 Planetary flyby: ISO 64, shutter 1/1000–1/2000 sec, lens 500–800 mm equivalent. Use burst stack mode.
3.2 Sunroof portraits: HDR bracketed exposures, use on-camera ND if near bright sources.
Izzy note: Roll down the window, but do not attempt to get out for a selfie. Dave will judge you silently.
Weapons And Defensive Systems (Restricted Use)
1. System Overview
1.1 Weapons systems are limited on Phoenix by design. Primary means of offense are the Nether Space Duster, a compact rail cannon, and a short-range grav-wave projector. Weapons operation requires pilot and co-pilot authorization in combination.
2. Safety And Restrictions
2.1 Engagement protocol requires three confirmations: pilot arming, co-pilot authorization, and confirm external hostile signature. Weapon arming without consent results in immediate lockdown and ethics audit.
3. Nether Space Duster — Operational Summary
3.1 Function: localized mass conversion to base elements within a limited mass envelope. Not a planetary-scale device. Typical target mass < 10 metric tons. Range limited to 2,500 meters in atmosphere. Allowable use case: precise non-attributable neutralization of kinetic threats.
4. Rail Cannon
4.1 High-velocity kinetic projectile for point defense. Requires hull lattice venting for recoil compensation. Firing times limited to single shot salvo to avoid coherence spikes.
5. Gravitational Wave Projector
5.1 Short pulse field to nudge debris or alter small mass trajectories. Useful for obstacle removal and limited salvage.
Izzy note: Use the Duster like a surgeon, not a demolition crew. And clean up afterwards.
[SYS LOG — Dave: Lethality acknowledged. Moral discomfort recorded as zero. Humans are inconsistent.]
Navigation, Mission Planning And Logs
1. Routing And Corridor Selection
1.1 Use dynamic overlay for Translation Layer corridors. Preferred corridors mapped and rated by RU stability and external traffic. Avoid unmapped corridors unless mission-critical.
2. Imaging And Science Runs
2.1 For opportunistic planetary imaging, coordinate with camera mount and phase assist scheduling to minimize RU expense. Acquire GPS time stamps and blackbox telemetry for verification.
3. Mission Logs And Blackbox
3.1 Everything recorded to encrypted immutable log. In event of incident, provide log trace per policy. Blackbox stores last 12 hours of raw data and permanent snapshots of CI and RU.
Emergency Procedures
1. Core Instability Warning (Red)
1.1 Symptoms: rapid CI decay, field converter overheating, audible lattice noise.
1.2 Immediate actions: throttle to neutral, engage emergency fields, mark position, transmit distress ping and blackbox handshake. If structural fracture imminent, proceed to emergency re-phase or pilot egress.
2. Manual Re-Phase Protocol
2.1 Used when automated systems fail. Requires manual RU injection and resonator re-tune:
• Step 1: Set field converters to auxiliary.
• Step 2: Route emergency RU through backup coil.
• Step 3: Slowly increase RU until local lock registers. Maintain for 30 seconds then transition to stable field.
3. Pilot Egress And Rescue
3.1 Standard ejection replaced by controlled dimensional split. Ejected pilot will have temporary partial data imprint for rescue. Use only when vessel non-recoverable.
4. In-Field Medical Protocols
4.1 Valkyrie external will not be available. Use emergency biological sync pack. Maintain CI with breathing regulation techniques.
Izzy note: If you ever need to use the re-phase protocol, do it slowly and curse loudly. It helps.
Maintenance, Diagnostics And Preflight Checklist
1. Preflight Quick Checklist (Pilot)
1.1 Verify CI >= 0.88.
1.2 Observe GTC RU baseline nominal.
1.3 Field converter temperature within normal.
1.4 HUD and curved display functional.
1.5 Yoke sensitivity aligned to pilot profile.
1.6 Camera mount secure.
1.7 Weapons disabled unless mission authorizes.
1.8 Blackbox connectivity verified.
2. Daily Maintenance Routines
2.1 Lattice integrity quick probe. Clean micro-pits.
2.2 Coherence engine scrub. Replace microfilament if RU efficiency drops 1.5 percent across cycles.
2.3 Environmental seals check. Window actuator lubrication under field conditions.
3. Diagnostic Tools And Readouts
3.1 Diagnostic port yields detailed CI, RU, TDF, EG values. Perform full scan if CI variances exceed 0.03 across one hour of idle operation.
Pilot Training And Minimum Qualification
1. Qualifications To Operate Phoenix
1.1 Certified atmospheric pilot or equivalent with advanced neural interface training. Minimum flight hours: 800 ground converted, 200 hours in high-speed corridor transits. Certified completion of Phoenix specific simulation training.
2. Training Syllabus (Abbreviated)
2.1 Simulator protocol: APP handling, ND-01 emergency abort, manual dampener control.
2.2 Live training: scheduled canyon run supervised, sunroof exposure procedures, limited ND-01 corridor hops under instructor.
2.3 Ethical module: Founders’ directives and weapons restraint.
Izzy note: Training includes learning not to fly angry. It helps. Mostly.
Appendix: Reference Limits And Units
• Resonance Unit (RU) nominal baseline: 1,200 RU.
• Coherence Index (CI) range: 0.00–1.00. Operating safe threshold CI >= 0.85 for ND-01.
• G felt with dampeners active: felt G = raw G / dampener factor. Dampener nominal factor 10 when fully engaged.
• Phase assist RU cost typical: 150 RU for local corridor, up to 450 RU in complex dynamic corridor.
Closing Notes
This extract provides the operational core for pilot-level control of the Phoenix. For full technical schematics, coherence engine maintenance logs, and Founder protocols, consult the Dthindmaster archive. The Phoenix is a living system. Respect the field. Respect the ethics.
Izzy (handwritten margin entry): “Manual read. Willng to test. Bring tequila for celebration and coffee for regret.”
[SYS LOG — Dave: Noted. Supply chain updated for tequila. Coffee remains pilot responsibility.]
Phoenix Operational Addendum
Pages 85–112 — Flight and Systems Deep Dive
Atmosphere Flight Dynamics
1. Flight Envelope and Limits
1.1 Indicated airspeed regimes (nominal)
• Ground taxi to 220 mph: wheel mode.
• Low altitude cruise: 220–3,200 mph.
• High altitude cruise (thin atmosphere): 3,200–12,000 mph.
• Transient supersonic bursts: up to Vne indicated 25,500 mph for thin-atmosphere hops only.
1.2 Structural and lattice limits
• Hull shear limit: sustained dynamic pressure above 12 kPa increases microfissure risk.
• CI drift tolerance: sustained CI below 0.80 during high dynamic pressure is immediate derate.
1.3 Aerodynamic coefficients
• Effective lift augmentation via field shaping yields lift coefficient Cl effective up to 3.6 equivalent in fusion with vectoring. Monitor Cl readout on HUD.
2. Angle Of Attack Control And Stall Management
2.1 The Phoenix maintains AoA protection through active field shaping. AoA limit for safe recovery: 12 degrees in APP when above 1,500 mph equivalent.
2.2 Stall becomes vector authority loss. Recovery technique: reduce AoA by decreasing pitch input by 3–5 degrees, increase RVJ vectoring by 12 percent and reapply field lift at 40 percent throttle.
3. High G Manoeuvres And Dampener Interaction
3.1 Dampener factor nominal 10. At CI > 0.92 dampeners are full spectrum. If CI falls below 0.85 expect dampener derate to factor 6.
3.2 Sustained manoeuvre G limits: pilot comfort envelope 6 G sustained, physiological safety 9 G with anti G straining and neural sync enabled. Use SPG (strain pulse guide) on HUD to manage onset.
4. Low Altitude Tactics (Surfing And Canyon Runs)
4.1 Minimum operational altitude for canyon runs: 20 meters recommended. Below 20 meters risk of wake turbulence, ground effect anomalies, and sudden micro-decoherence patches.
4.2 Lattice predictive shaping must be engaged for any <100 meter pass. Use predictive LIDAR overlays and terrain correlator in the HUD.
Exoatmospheric And Translation Layer Flight
1. Transition Procedure Summary (APP to Sub-Orbital)
1.1 Climb in APP to transitional altitude as defined by mission corridor. Align translation target in HUD overlay. Maintain CI >= 0.88.
1.2 Incrementally increase field converter output while monitoring RU lock strength. Expect transient sensor dropout as translation algorithms re-index.
2. Sub-Orbital Handling Characteristics
2.1 At translation boundary, control authority shifts from control surfaces to field shaping. Expect lag in tactile response. Pilot input should be anticipatory rather than reflexive.
2.2 Use feedforward inputs: small, early corrections rather than large, late inputs. HUD attitude predictive lead enabled by default.
3. Out Of Atmosphere Operating Limits
3.1 Phoenix may sustain short vacuum exposure within its coherence envelope. For extended exoatmosphericoperations, maintain hull lattice integrity percent > 92.
3.2 Thermal management: field converter thermal venting required after two consecutive ND-01 uses.
Nether Space Transition Profile (Pilot Sensory And System Effects)
1. Transition Phenomenology (Subjective)
1.1 Sensation description: brief nonexistence pulse followed by high energy clarity. Subjective span 1–2 seconds subjective time. Some pilots report a simultaneous feeling of being “absent and ultra-present.”
1.2 Izzy margin note: “You think you blinked. Then you realize your knuckles are imprinted in the yoke and your chest is singing. It is equal parts terrified and ecstatic.”
2. System Indicators During Transition
2.1 CI ramp must be monotonic. Successful phase fade shows CI glide curve: 0.88 rising to 0.93 at peak lock then settling to mission CI post-lock.
2.2 Audible cues: harmonic hum shift, subtle high frequency overtones. Visual cues: HUD starfield recomposition; external sky wash.
2.3 Safety: do not attempt manual overrides during initial fade unless immediate hazard. Manual injection can create partial instantiation or temporal ghosting.
3. Crew Procedures For Transition
3.1 Secure every loose item. Engage harness auto-lock. HUD set to minimal distraction. Confirm co-pilot ready and verbalized intent.
3.2 Monitor SPG and CO2; neural interface handshake must confirm pilot cognitive sync. Abort criteria: CI trending downward by 0.03 within 4 seconds, RU lock dropping > 0.05 RU, or onboard TDF spike.
Road Mode And Concealment Procedures
1. Vehicle Disguise Systems Overview
1.1 Phoenix supports a multi-layer concealment suite for public roads: passive profile projection, license mimic overlay, emission signature cloaking, and wheel rim folding. These systems are tuned to local traffic patterns and legal aesthetic norms.
1.2 Civilian Mode toggles: Visual mimic (paint/reflectivity modulation), Audio dampening, and thermal profile smoothing.
2. Practical Road Driving Tips For Concealment
2.1 Select mimic profile to match local high-end sports car standards. Ensure license mimic is registered to validated shell identity.
2.2 Use low profile wheel mode for urban roads. Fold venting flaps to hide lattice shimmer. Avoid high rev audible slips under 3,000 rpm equivalent as it creates low probability detection spikes.
3. Driving Dynamics On Roads
3.1 Suspension modes: Sport, Comfort, Covert. Covert reduces ride height by 30 mm and damps lattice micro-bloom.
3.2 Takeoff from urban roads to APP: deploy vectoring jets and field shaping only after retraction lane verified. Avoid sudden acceleration (surge) while in mimic profile to prevent visual mismatch.
Izzy note: CarPlay, Android Auto, and CD. Yes, really. CD is an antique mode only for smugness and terrible playlists. The ship supports all three, but if you actually put a tape in the CD slotwe will have words.
Underwater Operation Addendum (Aftermarket Modification)
1. Capability Summary
1.1 The Phoenix hull structure is inherently water resistant within its lattice envelope. Underwater high speedoperation is physically possible given proper hull venting and external radiative cooling modifications. This configuration is not factory standard.
2. Michael Modification Caveat
2.1 Aftermarket kit developed by operator Michael supports high speed hydrodynamic mode via modified hull skirts, seawater radiator loop, and external cathodic coherence stabilizers. This kit is not approved by Founder archive or Dthind standards.
3. Warranty And Ethical Notice
3.1 Use of Michael modification voids standard Dthindfactory warranty with respect to hull and coherence engine lifetime. Operator assumes risk of electrochemical lattice corrosion and potential resonance misalignment.
3.2 Dave system note: [SYS LOG — Dave: Warranty void flag set. Michael may be recruited for piracy. Recommend insurance clause: bonding by tequila and signed waiver.]
4. Operational Limits (Aftermarket Mode)
4.1 Maximum underwater speed recommended: 280 knots equivalent; sustained exposure at high speed increases hull shear risk. Use only in calm water and mapped bathymetric corridors. Avoid salt storm conditions.
Pilot And Co-Pilot HUD Configuration
1. HUD Architecture Overview
1.1 Primary pillars: Nav, Weapons, Defense, Stealth, Grav Guidance. HUD panes are modular and reflow by priority. Each pane has a persistent microstrip with RU, CI, timestamp, and alert ribbon.
2. Pilot HUD Presets (Pilot Priority)
2.1 Navigation Mode (Default)
• Elements: flight vector reticle, predicted trajectory, corridor lock strength, altitude, airspeed, AoA, Cl effective.
• Subsystems: terrain correlator, obstacle prediction, lead intercept cues.
2.2 Weapons Mode
• Elements: target acquisition, firing solution, Duster mass envelope view, collateral heatmap, sequence arming ticks.
• Safety interlocks: 3-factor arming widget requiring co-pilot token.
2.3 Defense Mode
• Elements: shield modulation, incoming vector map, debris avoidance matrix, EVA bubble integrity.
• Auto countermeasure triggers flagged.
2.4 Stealth Mode
• Elements: emission signature readout, mimic overlay sample, thermal dampen readout.
• Discrete mode: minimal HUD noncritical elements visible to reduce EM footprint.
2.5 Gravitational Guidance Mode
• Elements: mass field map, gravitational wells, push/pull emitter vectoring, salvage corridor planner.
• Use for asteroid nudging, debris re-route operations, and controlled compaction.
3. Co-Pilot HUD Responsibilities
3.1 Co-pilot HUD defaults to mission systems and weapons oversight. It mirrors pilot primary nav pane but allows for independent control of weapons, sensors, and system overrides. Co-pilot can inject a veto or confirm actions via the dual authorization system.
4. User Customization And Pilot Profiles
4.1 Pilot profiles store sensitivity curves, HUD overlays, voice command lexicon, and warning thresholds. Profiles are protected by biometric and neural handshake. Shared profiles may be loaded but require re-calibration.
5. Jargon And Display Readouts (Examples)
5.1 RU lock strength indicator shows fractional RU with color bands. Lock delta is shown in RU per second.
5.2 CI trend graph shows immediate 30 second moving window.
5.3 TDF readout displays temporal drift factor in milliseconds per minute. High values suggest Translation Layer turbulence.
5.4 Bingo RU is the emergency minimal RU reserve indicating the last viable point for safe re-phase.
Pilot Jargon And Tactical Shorthand
1. Common Terms For Crew Use
• Bingo RU: minimal RU reserve for safe re-phase.
• Spike: sudden RU or CI transient that indicates interference.
• Lock Up: RU lock strength exceeding mission nominal.
• Fade: the brief nonexistence sensation during phase assist.
• Ghosting: incomplete instantiation or partial re-materialization artifact.
• Bandit: hostile acquisition on radar/sensor network.
• Bingo Fuel: crossover term for propellant or system reserve thresholds; used colloquially for resource minima.
2. Tactical Callsigns And Procedures
2.1 If Bandit acquired: “Bandit bearing X, range Y, prepare arms two.” Co-pilot confirms: “Arming two confirmed.”
2.2 If Spike: “Spike at RU +0.08, CI dip 0.04, initiating hold.” Pilot reduces throttle, attempts re-lock.
2.3 Emergency Re-Phase call: “Mayday Re-Phase, executing manual injection,” followed by coordinate pings and blackbox dump.
Expanded Checklists
1. Pre-Phase Checklist (10 Items)
1.1 CI >= 0.88.
1.2 RU map loaded and validated.
1.3 Field converters nominal, temps < 80 percent.
1.4 Crew harness locked and neural handshake confirmed.
1.5 HUD set to minimal distraction.
1.6 Weapons safe and verified.
1.7 Camera mounts secured.
1.8 External environment cleared of heavy traffic.
1.9 Blackbox ready and encryption key active.
1.10 Abort vector pre-briefed.
2. Emergency Abort Steps (Condensed)
2.1 Throttle to neutral.
2.2 Activate phase abort.
2.3 Re-engage APP controls and stabilize.
2.4 Transmit distress handshake.
2.5 If hull breach, seal cabin and apply local field patch.
Human Factors And Crew Resource Management
1. Cognitive Load Management
1.1 During Net-Assist transitions reduce comms to essential only. Excess chatter increases cognitive resonance variance.
1.2 Use procedural callouts. Two-word confirmations for critical events.
2. Fatigue And Recovery
2.1 Limit consecutive ND-01 ops to two within 24 hours without extended CI recovery protocol. Extended operations require rest, increased hydration, controlled caffeine intake, and a neural cool-down sequence.
Izzy note: The fade is beautiful. Do not text your ex while in fade mode. Bad idea and the universe will judge you twice.
[SYS LOG — Dave: Noted. Universe judgement parameter logged. Exes remain unhelpable.]
Appendix Reference Cross Links
• See Appendix B: Mapping Standards for preferred Translation Layer corridors and RU cost tables.
• See Appendix D: Medical Recovery Protocol for post-phase cognitive recalibration.
• See Appendix F: Michael Modification Registry for aftermarket underwater kit documentation and warranty impacts.
