Apollo Lunar Module AC Power Inverter

Rare flight version of an Apollo Lunar Module AC Power Inverter in its handling frame, measuring an overall 11" x 29.5" x 12" and weighing 41 lbs, with a NASA/Manned Spacecraft Center property tag and Hamilton Standard label on the unit: "Inverter, General Purpose Electrical Power Subsystem, Design Control No. LSC-390-6-9-7, Contract No. NAS-9-1100/2-24494-C, Unit No. 43, HS Part No. SV718452 P10, Serial No. 145." A Hamilton Standard plate on the handling frame reads: "Handling Kit, Inverter, Part No. SV714594, Serial No. HK14, HS Ref No. 19932 A." A Hamilton Watch Company "elapsed time" indicator is set into the frame. In very good to fine condition. This piece will be crated and shipped from California; the buyer is responsible for all associated costs.
Lunar Module energy management was essential to the survival of the Apollo 13 mission, as the explosion in the Service Module Fuel Cell system necessitated using the Lunar Module as a propulsive and energetic lifeboat for the crippled spacecraft.
From NASA Technical Note D-6977, 'Apollo Experience Report—Lunar Module Electrical Power Subsystem,' issued in September 1972, in part: 'The lunar module electrical power subsystem controlled, conditioned, and distributed all electrical power in the lunar module. The subsystem was required to receive direct-current power from batteries and distribute it to equipment in both direct- and alternating-current forms. The subsystem was developed to include equipment for inversion of power, circuit protection, distributed networks, controls, and monitoring functions…
The electrical power requirements were defined to provide approximately 65 kilowatt-hours at a rate of 4000 watts to satisfy a 35-hour lunar stay time. The subsystem was designed to fail-safe within the weight constraints; this requirement necessitated the use of redundant buses and isolation equipment. Inversion equipment was provided to meet the requirements of the equipment powered by alternating current (AC)…
In the AC system, two inverters (each rated at 350 volt-amperes, 400 hertz, 115 V AC, single phase) were used. The AC bus was located in the LMP power panel….CONCLUSIONS: The lunar module electrical power subsystem has fulfilled the mission requirements and no inflight failures have occurred.'
During the Apollo 13 crisis, the Lunar Module's electrical system became critical to crew survival: the cryo tank explosion on the Service Module led to impending loss of all power in the CSM. The only remaining power source in CSM were Entry/Post-Landing Batteries, and they were partly discharged. The crew used the Translunar Negative Bus to power the CSM from the LM. Although severe powerdowns on both the LM and CSM were required (at some points, less than 20% of normal power levels), the LM batteries provided power to itself and the CSM for a total of 83 hours—far exceeding the qualification/testing limits. At jettison, the LM had less than 5 hours of power left. Afterwards, an extra 'lunar battery' was added to the LM's infrastructure (coincidentally, already planned for Apollo 15 due to longer lunar stays), which could be used for extra power in an emergency scenario.