I come across many S-IC diagrams which, while interesting, are not so interesting that they necessarily merit their own separate page. I have created this page as a repository for such diagrams.

The F-1 Familiarization Training Manual has a diagram of the S-IC stage; this is only natural, as the S-IC stage is the only stage in which the engine was ever mounted.

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From the second unnumbered page of the F-1 Engine Familiarization Training Manual, located in the archives of the U.S. Space & Rocket Center.
Also available from University of Alabama at Huntsville's USSRC Archive [direct link to 16.8M PDF file].
Scan and cleanup by heroicrelics.

The diagram notes the overall stage dimensions as 138 feet long and 33 feet in diameter and shows the LOX tank mounted forward of the RP-1 tank, with the LOX suction lines running through the fuel tank.

The following S-IC-related information is also noted:

• Prime Contractor: Boeing
  Assembled at Michoud, LA.
• Engines: 5 Rocketdyne F-1
• Thrust: 7,500,000 lb
       Each engine: 1.5 million lbs
• Burning Time: 150 sec (2.5 min)
• Propellant: 4,400,000 lb
       RP-1 - 206,000 gals
       LOX - 340,000 gals
• Gross Wt: 4,800,000 lb
• Burnout Wt: 425,000 lb
• Altitude: 0-200,000 ft (38 miles)
• Velocity: 0-7,700 ft/sec (5,460 mph)

Structurally, the S-IC stage consisted of

• A 19.5 foot tall thrust structure, to which the engines were mounted. The thrust of the engines was transmitted to the propellant tank walls via the thrust structure.
  
  There are four holddown posts located on the periphery of the thrust structure. The entire vehicle was supported by these posts. Hold-down arms on the mobile launcher also clamped the Saturn V to the pad via these holddown posts as the S-IC's five F-1 engines built up thrust after ignition; the hold-down arms released the Saturn V once all of the engines were up to full thrust.
• Four fairings attached to the thrust structure and partially surrounded the S-IC's outboard engines. The fairings were shaped like cone halves and smoothed the air flow over the engines. A fin was attached to each fairing. The fins added to the vehicle's flight stability.
  
  Each fairing also housed two retrorockets. At stage separation, the retros fired, blowing the tips off of the fairings. The retros slowed the S-IC and prevented it from recontacting the S-II.
• A fuel, or RP-1, tank. The tank consisted of forward and aft ellipsoidal bulkheads and cylindrical tank walls and was approximately 43 feet tall. Five LOX tunnels ran through the fuel tank, carrying liquid oxygen from the LOX tank, through the fuel tank, and to the engines. Both the fuel and LOX tanks were constructed using a "Y-ring" at both the forward and aft ends of the cylindrical tank wall. The Y-rings connected the tank tank wall to both the tank bulkheads and the adjoining stage structures.
• An intertank structure, approximately 22 feet long. The upper bulkhead of the fuel tank extended up into the intertank and the lower bulkhead of the LOX tank dipped down into it. The forward and aft edges of the intertank each incorporated 216 fittings which mated the intertank to each propellant tank's Y-ring.
• An oxidizer, or LOX, tank. The LOX tank's construction was similar to that of the RP-1 tank and was 64 feet in height. LOX tunnels were connected to the tank's aft bulkhead and ran through the intertank and fuel tank to provide oxidizer to the engines.
• A forward skirt, which was approximately 10 feet long and extended past the LOX tank's forward bulkhead. It provided the connecting link for the S-IC and S-II stages. Various equipment, including telemetry, range safety, and ODOP radar tracking equipment, was mounted on the forward skirt.

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Adapted from page A-10 (p. 246 in the PDF) of Apollo/Saturn V Space Vehicle Selected Structural Element Review Report, AS-503 (alternate link).
Extraction, cleanup, and adaptation by heroicrelics.org.