{"product_id":"lockheed-r6o-r6v-constitution-technical-documentation-archive","title":"Lockheed R6O \/ R6V Constitution — Technical Documentation Archive","description":"\u003ch3\u003eLockheed R6O \/ R6V Constitution — Technical Documentation Archive\u003c\/h3\u003e\n\u003cp\u003eThe \u003cstrong\u003eLockheed R6O Constitution\u003c\/strong\u003e (redesignated \u003cstrong\u003eR6V Constitution\u003c\/strong\u003e in 1950) stands as one of the most ambitious and technically singular aircraft programmes of the immediate post-war era — the largest fixed-wing type ever operated by the United States Navy. Only two airframes were ever completed (BuAer Serial Nos. 85163 and 85164), making primary-source documentation of this programme exceptionally rare.\u003c\/p\u003e\n\u003cp\u003eThis archival collection brings together the surviving technical publications issued by \u003cstrong\u003eLockheed Aircraft Corporation, Burbank, California\u003c\/strong\u003e, and published under the authority of the \u003cstrong\u003eChief of the Bureau of Aeronautics\u003c\/strong\u003e, covering the full engineering and operational lifecycle of both prototypes.\u003c\/p\u003e\n\u003chr\u003e\n\u003ch3\u003eDocuments in This Collection\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eErection and Maintenance Instructions\u003c\/strong\u003e — Navy Model XR60-1 Airplane (BuAer Serials 85163 \u0026amp; 85164) · Lockheed Aircraft Corporation · 1 June 1948, Revised 15 May 1949\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePilot's Handbook\u003c\/strong\u003e — Navy Model R60-1 Airplanes · NAVAER 01-75CLA-501 · Published by Direction of the Chief of the Bureau of Aeronautics · 1 July 1949, Revised 1 May 1950\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003e1. Aerodynamic \u0026amp; Structural Layout\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eFuselage geometry:\u003c\/strong\u003e Engineered with a unique \u003cem\u003edouble-bubble\u003c\/em\u003e (figure-eight) cross-section to maximise structural efficiency under full cabin pressurisation.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing profiles:\u003c\/strong\u003e Exceptionally thick, high-aspect-ratio wings incorporating structural internal tunnels — permitting flight engineers to access and service the powerplants while airborne.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eConfiguration:\u003c\/strong\u003e Conventional four-engine mid-wing layout with a massive single vertical stabiliser sized to offset asymmetric thrust conditions.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003e2. Engine Technical Notes\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePowerplants:\u003c\/strong\u003e Four \u003cstrong\u003ePratt \u0026amp; Whitney R-4360-22W Wasp Major\u003c\/strong\u003e 28-cylinder, four-row radial engines.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eOutput:\u003c\/strong\u003e 3,000 hp (2,237 kW) per engine; large four-blade propellers.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCooling \u0026amp; access:\u003c\/strong\u003e Advanced internal duct system within the thick wing profile for engine cooling and in-flight accessory servicing.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePower limitation:\u003c\/strong\u003e Testing definitively established the aircraft was chronically underpowered on piston engines. Planned upgrade to 5,500 hp Wright Typhoon turboprops was abandoned when that programme was cancelled.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003e3. Handling \u0026amp; Stability Studies\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eLanding gear:\u003c\/strong\u003e Specialised electric motors inside the struts pre-spun all eight main wheels to match ground speed prior to touchdown, eliminating friction stress and producing exceptionally gentle landings.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCockpit indicator:\u003c\/strong\u003e Touchdowns were so smooth that pilots could not feel them — an \u003cem\u003eAIRPLANE ON GROUND\u003c\/em\u003e indicator light was added to the instrument panel.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eControl response:\u003c\/strong\u003e Flight testing characterised handling as stable but heavy, requiring substantial pilot input across the vast control surface areas prior to hydraulic boost optimisation.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003e4. Performance Data\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\n\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e184,000 lb (83,500 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Payload\u003c\/td\u003e\n\u003ctd\u003e70,000 lb (31,900 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Cruise Speed\u003c\/td\u003e\n\u003ctd\u003e303 mph (263 kt \/ 487 km\/h)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e28,600 ft (8,700 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRate of Climb\u003c\/td\u003e\n\u003ctd\u003e700 ft\/min (3.56 m\/s)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePassenger Capacity\u003c\/td\u003e\n\u003ctd\u003eUp to 204 (two-deck troop transport)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003ch3\u003e5. Programme Fate\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eProduction:\u003c\/strong\u003e Two prototypes only — BuNo 85163 and BuNo 85164.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCivil rejection:\u003c\/strong\u003e Pan American World Airways determined the type lacked the power-to-weight efficiency required for profitable commercial routes.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eRetirement:\u003c\/strong\u003e Both airframes decommissioned by the U.S. Navy in 1953 due to high maintenance footprint and the cost of bespoke hangar infrastructure.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003cp\u003eThis is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorised distributor.\u003c\/p\u003e\n\u003cp\u003e⚠️ \u003cstrong\u003eRegulatory Notice:\u003c\/strong\u003e Under FAA 14 CFR § 43.13 and EASA Part-M, any mechanic performing maintenance on an active aircraft must use current, manufacturer-approved revision-controlled data. This archival document does not satisfy that requirement.\u003c\/p\u003e\n\u003cp\u003eLiving Collections with Free Lifetime Updates — Please review our Disclaimer and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53651616039259,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/constitution-banner-1-colorized.png?v=1784893059","url":"https:\/\/onlineaviationlibrary.com\/products\/lockheed-r6o-r6v-constitution-technical-documentation-archive","provider":"Online Aviation Library","version":"1.0","type":"link"}