{"product_id":"nord-2501-noratlas-primary-source-documentation-collection","title":"Nord 2501 Noratlas — Primary-Source Documentation Collection","description":"\u003ch3\u003eNord 2501 Noratlas — Primary-Source Documentation Collection\u003c\/h3\u003e\n\u003cp\u003eThe \u003cstrong\u003eNord 2501 Noratlas\u003c\/strong\u003e was a twin-boom, high-wing tactical transport aircraft developed by the \u003cstrong\u003eSociété Nationale de Constructions Aéronautiques du Nord (SNCAN)\u003c\/strong\u003e and operated by both the \u003cem\u003eArmée de l'Air\u003c\/em\u003e and the \u003cstrong\u003eGerman Luftwaffe\u003c\/strong\u003e as a primary medium tactical airlifter throughout the 1950s and 1960s. Engineered for rear-loading cargo drops, paratroop operations, and austere-field performance, the Noratlas became one of the defining NATO tactical transports of the Cold War era. This collection assembles the original French military and German Luftwaffe documentation issued for the type — a rare bilingual primary-source archive spanning two air forces.\u003c\/p\u003e\n\u003chr\u003e\n\u003ch3\u003eEngineering \u0026amp; Technical Profile\u003c\/h3\u003e\n\u003ch4\u003e1. Aerodynamic Configuration\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Profile:\u003c\/strong\u003e NACA 23018 at root tapering to NACA 23010 at tip — prevents tip stall under high-lift conditions\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Area:\u003c\/strong\u003e 101.2 m² (1,089 sq ft) | Aspect ratio optimized for low-altitude, high-lift tactical performance\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTwin-Boom Architecture:\u003c\/strong\u003e Tail booms integrated directly into engine nacelles — straightens boundary layer airflow, reduces rear fuselage buffeting\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAileron System:\u003c\/strong\u003e Differential slotted ailerons maintain roll authority through deep high-angle-of-attack profiles\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch4\u003e2. Powerplant\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eEngines:\u003c\/strong\u003e 2× SNECMA-built Bristol Hercules 738\/739 or 759 — 14-cylinder, sleeve-valve radial\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePower Output:\u003c\/strong\u003e 2,040–2,090 metric hp (1,558 kW) per engine at takeoff\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropeller:\u003c\/strong\u003e Four-bladed, variable-pitch, fully feathering constant-speed system\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eSleeve-Valve Design:\u003c\/strong\u003e Reciprocating rotating sleeve regulates intake\/exhaust timing — eliminates traditional poppet valves\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch4\u003e3. Handling \u0026amp; Stability\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003eDual vertical fins deliver immense directional authority during asymmetric engine-out scenarios at low speed\u003c\/li\u003e\n\u003cli\u003eHigh-mounted horizontal stabilizer positioned clear of wing wake and propeller slipstream wash\u003c\/li\u003e\n\u003cli\u003eCG shift verified minimal during sequential 35-paratrooper jumps or rapid heavy cargo drops\u003c\/li\u003e\n\u003cli\u003eCertified for aggressive 25° glide slopes into hostile or confined sectors\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch4\u003e4. Performance Data\u003c\/h4\u003e\n\u003ctable\u003e\n\u003cthead\u003e\n\u003ctr\u003e\n\u003cth\u003eMetric\u003c\/th\u003e\n\u003cth\u003eImperial Unit\u003c\/th\u003e\n\u003cth\u003eMetric Unit\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e29,327 lb\u003c\/td\u003e\n\u003ctd\u003e13,302 kg\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMTOW\u003c\/td\u003e\n\u003ctd\u003e45,423 lb\u003c\/td\u003e\n\u003ctd\u003e20,603 kg\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Payload\u003c\/td\u003e\n\u003ctd\u003e18,647 lb\u003c\/td\u003e\n\u003ctd\u003e8,458 kg\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Cruise Speed\u003c\/td\u003e\n\u003ctd\u003e270 mph\u003c\/td\u003e\n\u003ctd\u003e440 km\/h\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e22,965 ft\u003c\/td\u003e\n\u003ctd\u003e7,000 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Range\u003c\/td\u003e\n\u003ctd\u003e1,600 miles\u003c\/td\u003e\n\u003ctd\u003e2,500 km\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003ch4\u003e5. Variants \u0026amp; Engineering Bulletins\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eNord 2501-D (Luftwaffe Standard):\u003c\/strong\u003e French instrumentation and avionics replaced with German-manufactured equivalents\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNord 2502 (Turbojet Boost):\u003c\/strong\u003e Two wingtip-mounted Turbomeca Marboré IIE auxiliary turbojets (400 kgp each) for hot-and-high performance\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNord 2504 (ASW Testbed):\u003c\/strong\u003e Reinforced underwing hardpoints, retractable surface-search radar, sonic buoy launch tubes\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eStructural Bulletins:\u003c\/strong\u003e Local reinforcement of main landing gear attach points and bays for unpaved runway operations\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eDocument Manifest\u003c\/h3\u003e\n\u003cp\u003eThis collection contains \u003cstrong\u003e3 unique primary-source documents\u003c\/strong\u003e issued by the French Direction Centrale du Matériel and the German Materialamt der Luftwaffe:\u003c\/p\u003e\n\u003col\u003e\n\u003cli\u003e\n\u003cstrong\u003eManuel d'Utilisation de l'Avion Nord 2501 — Partie Planches\u003c\/strong\u003e | Identification: UCD 101 | Direction Centrale du Matériel | Edition: Mars 1968 — Approuvée par DM N° 1225\/EMAA\/3\/SV du 6 Mars 1968 | Mise à jour: Janvier 1971 — Approuvée par DM N° 101 484\/DCMAA\/MT2 du 26 Janvier 1971 | Print run: 700\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eManuel d'Utilisation de l'Avion Nord 2501 — Partie Texte\u003c\/strong\u003e | Identification: UCD 101 | Direction Centrale du Matériel | Edition: Mars 1968 — Approuvée par DM N° 1225\/EMAA\/3\/SV du 6 Mars 1968 | Mise à jour: Janvier 1971 — Approuvée par DM N° 101 484\/DCMAA\/MT2 du 26 Janvier 1971 | Print run: 700\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNoratlas 2501D — Flughandbuch\u003c\/strong\u003e | Reference: GAF T.O.1C-NOR2501-1 | Materialamt der Luftwaffe | Herausgegeben mit Genehmigung des Bundesministers der Verteidigung — Führungsstab der Luftwaffe (F·L) | Date: 1 November 1969 | HFB 800\u003c\/li\u003e\n\u003c\/ol\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 authorized distributor.\u003cbr\u003e\u003cem\u003eLiving Collections with Free Lifetime Updates — Please review our Disclaimer and Export Notice before purchasing.\u003c\/em\u003e\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53659010236763,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/banner-3-luftwaffe-banking.png?v=1785070836","url":"https:\/\/onlineaviationlibrary.com\/products\/nord-2501-noratlas-primary-source-documentation-collection","provider":"Online Aviation Library","version":"1.0","type":"link"}