{"title":"Japanese Aviation Collection","description":"\u003cp\u003eA primary-source archival collection of technical documentation from Japan's principal aircraft manufacturers and naval arsenals — Aichi Aircraft Company (Aichi Kōkūki KK), Hitachi Aircraft Company (Hitachi Kōkūki KK), Kawasaki Heavy Industries (KHI), Kawanishi Aircraft Company (Kawanishi Kōkūki KK), Kyūshū Hikōki K.K., Kokusai Aviation Company (Nippon Kokusai Kōkū Kōgyō KK), Mansyu — Manchuria Airplane Manufacturing Company, Mitsubishi Heavy Industries (MHI), Nakajima Aircraft Company, Showa Aircraft Industry Co. Ltd., Tachikawa Aircraft Company (Tachikawa Hikōki KK), and the Yokosuka Naval Air Technical Arsenal (Dai-Naigun Kōkū Gijutsushō).\u003c\/p\u003e\u003cp\u003eThis Living Collection spans one of the most technically sophisticated and historically significant aviation traditions of the twentieth century. From the Mitsubishi A6M Zero and the Nakajima Ki-84 Hayate to the Kawanishi N1K Shiden, the Aichi D3A dive bomber, and the Yokosuka MXY-7 Ohka — Japanese manufacturers and naval arsenals produced an extraordinary range of original designs under intense wartime conditions. Post-war documentation from Kawasaki and Mitsubishi extends the collection into the modern era. Documents are presented as archival, static-copy editions fixed at their original publication dates, intended for historical research, flight simulation, museum restoration, and educational use only.\u003c\/p\u003e\u003cp\u003eNot 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.\u003c\/p\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates — Please review our Disclaimer and Export Notice before purchasing.\u003c\/p\u003e","products":[{"product_id":"aichi-s1a-denko-night-fighter-technical-manuals-collection","title":"Aichi S1A Denkō — Night Fighter Technical Manuals Collection","description":"\u003cp\u003eThis Living Collection brings together primary-source technical documentation for the \u003cstrong\u003eAichi S1A Denkō (電光, \"Bolt of Light\")\u003c\/strong\u003e — factory designation \u003cstrong\u003eAM-25\u003c\/strong\u003e — the most massive fighter ever developed in Japan's naval history. Designed by Aichi Kokuki KK for the Imperial Japanese Navy (IJN) to counter B-29 Superfortress high-altitude raids, the Denkō was an experimental twin-engine night fighter of extraordinary ambition. Only two prototypes were constructed; both were destroyed by Allied bombing raids in 1945 before completion. The aircraft never flew.\u003c\/p\u003e\n\n\u003cp\u003eThis collection compiles data reconstructed from wartime design logs, the \u003cem\u003eDenkō Keikaku Setsumesho\u003c\/em\u003e (Denkō Project Explanation Manual), performance calculation sheets, and photographic records.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eCollection Contents — 2 Manuals\u003c\/h2\u003e\n\n\u003ch3\u003eS1A Aircraft Handbook (1 Manual)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eS1A Experimental 18-Shi Night Fighter Denkō Project Manual\u003c\/strong\u003e — 試製電光（十八試丙戦）計画説明書 (Japanese Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003eS1A Slides, Photos and Brochures (1 Manual)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eS1A Photographic Collection\u003c\/strong\u003e (English Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eAircraft \u0026amp; Technical Overview\u003c\/h2\u003e\n\n\u003ch3\u003eAerodynamic Architecture\u003c\/h3\u003e\n\u003cp\u003eThe Denkō's airframe represented one of the most technically sophisticated Japanese naval fighter designs of the war:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Profile:\u003c\/strong\u003e Modelled after Heinkel He 100-style structural blueprints, featuring a specialised laminar-flow wing section to reduce high-altitude parasitic drag.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDihedral Configuration — Inner Wings:\u003c\/strong\u003e Shallow 2° 30' dihedral from fuselage to engine nacelles.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDihedral Configuration — Outer Wings:\u003c\/strong\u003e Steep 6° dihedral from nacelles to clipped tips for maximum lateral stability during night interception.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFuselage Architecture:\u003c\/strong\u003e Shared development cues with the Nakajima C6N1 Saiun. Exceptionally thick metal skin over minimal internal stringers — clean aerodynamic surface, reduced structural mass, shortened production time.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAirbrakes:\u003c\/strong\u003e Integrated trailing-edge mechanical airbrakes to prevent high-speed overshoots during close-in night bomber engagements.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePowerplant — Nakajima NK9K-S Homare 22\u003c\/h3\u003e\n\u003cp\u003eTwin \u003cstrong\u003eNakajima NK9K-S Homare 22\u003c\/strong\u003e 18-cylinder air-cooled radial engines driving four-bladed constant-speed metal propellers:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eOutput:\u003c\/strong\u003e 2,000 hp at takeoff — 1,885 hp at 1,750 m — 1,620 hp at 6,400 m.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eHigh-Altitude Induction:\u003c\/strong\u003e Remote turbosuperchargers with auxiliary oxygen injection for performance above 8,000 m.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eThermal Management:\u003c\/strong\u003e Forced-cooling fans required inside tight-fitting cowlings due to chronic overheating discovered during static test runs.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEngineering Shortcoming:\u003c\/strong\u003e Remote turbocharger layout caused severe exhaust pressure drops; Navy performance parameters were never fully met. Proposed post-prototype upgrade to Mitsubishi MK9A Ru or MK10A Ru engines.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003eHandling \u0026amp; Stability\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWeight Penalty:\u003c\/strong\u003e Avionics, radar gear, and heavy armour pushed combat weight beyond 10,000 kg, with projected heavy wing-loading characteristics.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePilot Ergonomics:\u003c\/strong\u003e Highly forward-mounted teardrop canopy giving unobstructed view over wing leading edges.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eRadar Operator Position:\u003c\/strong\u003e Seated separately at the wing trailing edge under a small observation dome, managing defensive systems independently.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCentre of Gravity:\u003c\/strong\u003e Remote dorsal turret placement between crew positions required precise fuel tank balancing in the central fuselage.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDefensive Tracking:\u003c\/strong\u003e Remotely controlled top turret eliminated aerodynamic buffeting and weight of a manned turret system.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePerformance Data\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eWingspan\u003c\/td\u003e\n\u003ctd\u003e17.50 m (57 ft 5 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eLength\u003c\/td\u003e\n\u003ctd\u003e15.10 m (49 ft 6.5 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eHeight\u003c\/td\u003e\n\u003ctd\u003e4.61 m (15 ft 1.5 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWing Area\u003c\/td\u003e\n\u003ctd\u003e47.00 m² (505.9 sq ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e7,320 kg (16,138 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eGross Loaded Weight\u003c\/td\u003e\n\u003ctd\u003e10,180 kg (22,443 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e11,510 kg (25,375 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e589 km\/h (366 mph) at 8,000 m (estimated)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e444 km\/h (276 mph) at 4,000 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eClimb Rate\u003c\/td\u003e\n\u003ctd\u003e14 min 45 sec to 9,000 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e12,000 m (39,370 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Operational Range\u003c\/td\u003e\n\u003ctd\u003e2,540 km (1,580 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003ch3\u003eAvionics \u0026amp; Engineering Bulletins\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAir-Intercept Radar:\u003c\/strong\u003e Gyoku-3 AI Radar with transmission antenna in a wooden nose radome and Yagi receiver array under the nose cone.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAltimetry:\u003c\/strong\u003e Taki-11 radio altimeter with inverted 'T' dipoles under the wings.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eIFF:\u003c\/strong\u003e Taki-30 Identification Friend or Foe rod antenna on the rear spine.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eArmament — Standard Night Fighter:\u003c\/strong\u003e 2 × 30mm Type 5 cannons + 2 × 20mm Type 99 Model 2 cannons fixed forward in nose. 2 × 20mm Type 99 Model 2 in 30° Schräge Musik upward-firing layout. 2 × 20mm Type 99 Model 2 in remote dorsal turret.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003cp\u003e⚠️ Regulatory Notice: 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\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.\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":53608407695707,"sku":"OAL-JP-AICHI-S1A","price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/aichi-s1a-denk-leaderboard-banner.png?v=1784217570"},{"product_id":"aichi-d3a-val-type-99-carrier-bomber-technical-manuals-collection","title":"Aichi D3A Val — Type 99 Carrier-Based Bomber Technical Manuals Collection","description":"\u003cp\u003eThis Living Collection brings together primary-source technical documentation for the \u003cstrong\u003eAichi D3A \"Val\"\u003c\/strong\u003e (九九式艦上爆撃機, Navy Type 99 Carrier Bomber) — the Imperial Japanese Navy's premier carrier-borne dive bomber of the early Pacific War. Derived from Heinkel He 70 design influences, the D3A became highly regarded for its precision bombing accuracy and unexpected dogfight maneuverability once ordnance was released. A total of \u003cstrong\u003e1,486 units\u003c\/strong\u003e were produced by Aichi Kokuki KK.\u003c\/p\u003e\n\n\u003cp\u003eThe collection covers the \u003cstrong\u003eD3A Model 11\u003c\/strong\u003e variant with the original Japanese-language instruction manual, complemented by a curated photographic archive.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eCollection Contents — 2 Documents\u003c\/h2\u003e\n\n\u003ch3\u003eD3A Model 11 — Operating and Maintenance (1 Manual)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAichi D3A Model 11 Type 99 Carrier-Based Bomber Instruction Manual\u003c\/strong\u003e — 九九式艦上爆撃機 取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003eD3A Slides, Photos and Brochures (1 Document)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAichi D3A Photographic Collection\u003c\/strong\u003e — Quick Specs · Aircraft in Flight · Aircraft on the Ground · Cockpit (English Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eAircraft \u0026amp; Technical Overview\u003c\/h2\u003e\n\n\u003ch3\u003eAerodynamic Architecture\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Configuration:\u003c\/strong\u003e Low-mounted elliptical wings inspired directly by the German Heinkel He 70 Blitz — excellent lift-to-drag characteristics and superior handling at lower flight envelopes.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePrototype Deficiencies (1938):\u003c\/strong\u003e Severe directional instability in wide turns and high snap-roll tendency during tight banking manoeuvres.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAerodynamic Mitigations:\u003c\/strong\u003e Wingspan extended by 0.40 m, outer section airfoil profile altered, and a prominent dorsal fin strake added forward of the rudder to correct airflow detachment.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDive Brake Redesign:\u003c\/strong\u003e Original wing-mounted dive brakes induced intense structural vibrations at maximum diving speed. Resolved by replacing with reinforced multi-slotted dive brakes outboard of the main landing gear.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePowerplant Evolution\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eInitial Mockup:\u003c\/strong\u003e Nakajima Hikari 1 nine-cylinder radial (709 hp) — proven critically underpowered for carrier operations.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eD3A1 Model 11:\u003c\/strong\u003e Mitsubishi Kinsei 43 (1,000 hp) or Kinsei 44 (1,070 hp) — 14-cylinder two-row air-cooled radial.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eD3A2 Model 22:\u003c\/strong\u003e Mitsubishi Kinsei 54 (1,300 hp) with fully redesigned aerodynamically streamlined engine cowling.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCooling:\u003c\/strong\u003e Cowl flap cooling system and dynamic oil coolers tailored for sustained high-power vertical climbs after bomb deployment.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003eHandling \u0026amp; Stability\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eLow-Speed Agility:\u003c\/strong\u003e Clean wing aerodynamics and light wing loading gave the Val near-fighter dogfight handling metrics once ordnance was released.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDive Profile:\u003c\/strong\u003e Capable of 60°–90° vertical steep-angle dives. Pilot used a Type 95 telescopic gunsight; belly window allowed visual target acquisition to the dive pivot point.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eBomb Clearance:\u003c\/strong\u003e 250 kg central bomb fitted to a pivoting displacement trap gear (fork crutch) — mechanically swung the bomb downward and forward, clearing the propeller arc before release.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePerformance Data — Model 11 vs Model 22\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eD3A1 Model 11\u003c\/th\u003e\n\u003cth\u003eD3A2 Model 22\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e389 km\/h (240 mph) at 3,000 m\u003c\/td\u003e\n\u003ctd\u003e430 km\/h (266 mph) at 6,200 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e296 km\/h (184 mph)\u003c\/td\u003e\n\u003ctd\u003e299 km\/h (186 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e9,265 m (30,400 ft)\u003c\/td\u003e\n\u003ctd\u003e10,500 m (34,450 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eTime to 3,000 m\u003c\/td\u003e\n\u003ctd\u003e6 min 27 sec\u003c\/td\u003e\n\u003ctd\u003e5 min 48 sec\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eNormal Range\u003c\/td\u003e\n\u003ctd\u003e1,473 km (915 miles)\u003c\/td\u003e\n\u003ctd\u003e1,352 km (840 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e2,408 kg (5,309 lb)\u003c\/td\u003e\n\u003ctd\u003e2,570 kg (5,666 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e3,650 kg (8,047 lb)\u003c\/td\u003e\n\u003ctd\u003e3,800 kg (8,378 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003ch3\u003eEngineering Bulletins\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eFixed Undercarriage:\u003c\/strong\u003e Navy deliberately chose fixed spatted landing gear over retractable — structural weight savings and mechanical simplicity outweighed drag penalty at operational cruising speeds.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eVulnerability Directives:\u003c\/strong\u003e Built without self-sealing fuel tanks or pilot armour to maximise range. Later field bulletins introduced rudimentary CO₂ fire-extinguishing equipment into wing tanks, though efficacy against heavy-calibre fire remained low.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCarrier Stowage:\u003c\/strong\u003e Only outer wingtips folded upward (rather than full wing fold) to fit standard IJN carrier elevator dimensions.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003cp\u003e⚠️ Regulatory Notice: 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\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.\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":53608626717019,"sku":"OAL-JP-AICHI-D3A","price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/aichi-d3a-val-b-w-wartime-banner.png?v=1786069475"},{"product_id":"aichi-e13a-jake-type-zero-reconnaissance-seaplane-technical-manuals-collection","title":"Aichi E13A Jake — Type Zero Reconnaissance Seaplane Technical Manuals Collection","description":"\u003cp\u003eThis Living Collection brings together primary-source technical documentation for the \u003cstrong\u003eAichi E13A \"Jake\"\u003c\/strong\u003e (零式一號水上偵察機一型, Type Zero Reconnaissance Seaplane Model 11) — the Imperial Japanese Navy's primary long-range, three-seat maritime reconnaissance floatplane throughout World War II. Designed by Aichi Kokuki KK, the E13A represented a decisive departure from drag-heavy biplane configurations, combining cantilever monoplane engineering with exceptional overwater endurance. A total of \u003cstrong\u003e1,418 units\u003c\/strong\u003e were produced.\u003c\/p\u003e\n\n\u003cp\u003eThe collection covers the \u003cstrong\u003eE13A Model 11\u003c\/strong\u003e variant with the original Japanese-language instruction manual, complemented by a curated photographic archive.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eCollection Contents — 2 Documents\u003c\/h2\u003e\n\n\u003ch3\u003eE13A Model 11 — Operating and Maintenance (1 Manual)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAichi E13A Model 11 Type Zero Reconnaissance Seaplane Instruction Manual\u003c\/strong\u003e — 零式一號水上偵察機一型 取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003eE13A Slides, Photos and Brochures (1 Document)\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAichi E13A Photographic Collection\u003c\/strong\u003e — Quick Specs · Aircraft in Flight · Aircraft on the Ground · Seaplane on Water · Cockpit (English Language)\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch2\u003eAircraft \u0026amp; Technical Overview\u003c\/h2\u003e\n\n\u003ch3\u003eAerodynamic Architecture\u003c\/h3\u003e\n\u003cp\u003eThe E13A was structured as a low-wing, twin-float cantilever monoplane — a profound departure from the biplane configurations it replaced:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Profile:\u003c\/strong\u003e High-aspect-ratio wing, 36.0 m² (387 ft²) total area, optimising lift efficiency for long-duration overwater scouting.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDrag Management:\u003c\/strong\u003e Cantilever engineering eliminated all external wing bracing wires. Residual drag dominated by the twin-float assembly and its vertical strut networks.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eControl Surfaces:\u003c\/strong\u003e All-metal stressed-skin primary structure. Ailerons, elevator, and rudder remained fabric-covered to reduce tail-heavy moments and control circuit inertia.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePowerplant — Mitsubishi Kinsei 43\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eEngine\u003c\/td\u003e\n\u003ctd\u003eMitsubishi Kinsei 43 — 14-cylinder, air-cooled, two-row radial\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eTake-off Power\u003c\/td\u003e\n\u003ctd\u003e790 kW (1,060 hp)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRated Altitude Power\u003c\/td\u003e\n\u003ctd\u003e810 kW (1,080 hp) at 2,000 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eExhaust Engineering\u003c\/td\u003e\n\u003ctd\u003eMid-to-late production retrofits: individual thrust-type exhaust ports replacing manifold collection pipes for maximum scavenging and ambient thrust extraction\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003ch3\u003eHandling \u0026amp; Stability\u003c\/h3\u003e\n\u003cp\u003eDuring 1938 IJN evaluation trials against the competing Nakajima E12A1, the Aichi prototype demonstrated clear design dominance:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eInherent Stability:\u003c\/strong\u003e Remarkably stable despite larger footprint and heavier gross weight than predecessors — an excellent overwater camera and bombsight platform.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLow-Speed Handling:\u003c\/strong\u003e Massive wing provided forgiving stall characteristics, vital for high-load water take-offs and slow low-altitude harbour approaches.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCombat Vulnerability:\u003c\/strong\u003e Handling envelopes completely inadequate against Allied fighter interception. Absence of armour and self-sealing fuel cells caused catastrophic system failures under fire.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch3\u003ePerformance Data — E13A1\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e2,642 kg (5,825 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eNormal Gross Weight\u003c\/td\u003e\n\u003ctd\u003e3,640 kg (8,025 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e4,000 kg (8,818 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e376 km\/h (234 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Range\u003c\/td\u003e\n\u003ctd\u003e2,100 km (1,300 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e8,700 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eDefensive Armament\u003c\/td\u003e\n\u003ctd\u003e1 × 7.7 mm Type 92 machine gun (flexible, rear-firing)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eOffensive Payload\u003c\/td\u003e\n\u003ctd\u003e1 × 250 kg bomb, or 4 × 60 kg bombs, or depth charges\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003ch3\u003eEngineering Bulletins \u0026amp; Variants\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eE13A1a (Late 1944):\u003c\/strong\u003e Redesigned float-to-wing connecting struts, new propeller spinner assembly, advanced radio communications suite.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eE13A1b (Radar Integration):\u003c\/strong\u003e H-6 surface-search radar antennas along wing leading edges and rear lateral fuselage for anti-surface vessel operations.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNight Operations Mod:\u003c\/strong\u003e Anti-flame dampening exhaust shrouds masking engine exhaust signature during night harassment and ASW patrols.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eVentral Gun Mod:\u003c\/strong\u003e Lower fuselage floor modified to mount a downward-firing 20 mm Type 99 autocannon for low-altitude strafing of ground targets and small naval vessels.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003cp\u003e⚠️ Regulatory Notice: 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\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.\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":53608941781339,"sku":"OAL-JP-AICHI-E13A","price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/aichi-e13a-colour-painting-banner.png?v=1786069201"},{"product_id":"kawanishi-n1k-j-shiden-n1k2-j-shiden-kai-primary-documentation-archive","title":"Kawanishi N1K-J Shiden \u0026 N1K2-J Shiden-Kai — Primary Documentation Archive","description":"\u003ch2\u003eKawanishi N1K-J Shiden \u0026amp; N1K2-J Shiden-Kai\u003c\/h2\u003e\n\u003ch3\u003ePrimary Documentation Archive — 3 Manuals · 2 Variants\u003c\/h3\u003e\n\n\u003cp\u003eThe Kawanishi Shiden family stands among the most technically ambitious fighter programmes of the Pacific War. Born from the N1K1 Kyōfū floatplane, the land-based Shiden was transformed under extreme wartime pressure into one of the Imperial Japanese Navy's most capable interceptors — and then redesigned almost entirely as the Shiden-Kai to correct the structural and aerodynamic compromises of its predecessor. This OAL archive brings together the three surviving primary-source documents covering both variants.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003e📂 Archive Contents — 3 Documents\u003c\/h3\u003e\n\n\u003ch4\u003eVariant N1K1-J Shiden — 2 Manuals\u003c\/h4\u003e\n\u003cul\u003e\n  \u003cli\u003e\n\u003cstrong\u003eKawanishi N1K1-J Prototype Shiden Instruction Manual\u003c\/strong\u003e\u003cbr\u003e\n  試製紫電 取扱説明書 · Japanese Language\u003cbr\u003e\n  The original factory operating and maintenance instruction manual for the N1K1-J prototype land-based fighter. Covers aircraft systems, engine operation, and handling procedures as issued by Kawanishi Kōkūki.\u003c\/li\u003e\n  \u003cli\u003e\n\u003cstrong\u003eN1K1-J Shiden Photographic Collection\u003c\/strong\u003e\u003cbr\u003e\n  English Language · ~13 pages\u003cbr\u003e\n  A curated photographic archive covering the N1K1-J in operational context. Sections include: Quick Specs, Aircraft in Flight (p.4), Aircraft on the Ground (p.5–10), and Cockpit (p.11). Includes a technical data sheet with confirmed performance figures.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003ch4\u003eVariant N1K2-J Shiden-Kai — 1 Manual\u003c\/h4\u003e\n\u003cul\u003e\n  \u003cli\u003e\n\u003cstrong\u003eKawanishi N1K2-J Model 21 Shiden-Kai Technical Drawings Manual\u003c\/strong\u003e\u003cbr\u003e\n  紫電改 図面集 · Japanese Language\u003cbr\u003e\n  Factory technical drawings manual for the N1K2-J Model 21, the extensively redesigned low-wing variant. Covers structural geometry, systems layout, and engineering drawings as issued for the production Shiden-Kai.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003e⚙️ Aerodynamic \u0026amp; Engineering Notes\u003c\/h3\u003e\n\n\u003ch4\u003eWing Design \u0026amp; Aerodynamic Profile\u003c\/h4\u003e\n\u003cp\u003eThe N1K1-J retained the mid-wing configuration of the floatplane predecessor, creating aerodynamic interference at the wing-fuselage junction that required large fairings to manage airflow. The N1K2-J Shiden-Kai resolved this by adopting a low-wing layout, reducing parasitic drag and improving overall aerodynamic efficiency. Both variants used the laminar-flow \u003cstrong\u003eLB620515-6075 airfoil\u003c\/strong\u003e, which shifted the point of maximum thickness rearward along the chord — minimising boundary-layer separation and lowering the drag coefficient at high diving speeds.\u003c\/p\u003e\n\n\u003ch4\u003eAutomatic Combat Flaps\u003c\/h4\u003e\n\u003cp\u003eA defining feature of the Shiden was its automated maneuvering flap system. Driven by a mercury-switch G-meter and airspeed sensors, the system pneumatically extended the flaps up to 30° during high-G turns, regulating the lift coefficient (C\u003csub\u003eL\u003c\/sub\u003e) to achieve tighter turn radii without manual pilot input or stall risk — a capability that surprised Allied test pilots post-war.\u003c\/p\u003e\n\n\u003ch4\u003ePowerplant — Nakajima NK9H Homare 21\u003c\/h4\u003e\n\u003cp\u003ePower was delivered by the \u003cstrong\u003eNakajima NK9H Homare 21\u003c\/strong\u003e, an 18-cylinder, twin-row, air-cooled radial engine rated at \u003cstrong\u003e1,990 hp at sea level\u003c\/strong\u003e and 1,625 hp at 5,700 m. A two-speed centrifugal supercharger was linked to a water-methanol injection system to suppress detonation at maximum combat power. The engine drove a 4-bladed, constant-speed metal propeller of approximately 3 m diameter, with an automatic throttle-airscrew interconnect to ease pilot workload in combat.\u003c\/p\u003e\n\u003cp\u003eTechnical bulletins documented persistent thermal management challenges: cylinder head temperatures escalated rapidly during sustained climbs, forcing wide-open cowl flaps that increased drag. Wartime fuel quality and metallurgy frequently reduced effective high-altitude output to approximately 1,300 hp.\u003c\/p\u003e\n\n\u003ch4\u003eHandling \u0026amp; Stability\u003c\/h4\u003e\n\u003cp\u003ePost-war Allied evaluations and Japanese Navy trials confirmed excellent longitudinal and directional stability at cruise, with near-neutral lateral stability giving high roll responsiveness. The N1K2-J achieved a roll rate of \u003cstrong\u003e82° per second at 386 km\/h\u003c\/strong\u003e. The aircraft exhibited poor stall warning characteristics — a sudden port-wing drop at approximately 161 km\/h with minimal buffet — and could snap into an uncommanded spin under accelerated stall conditions. At high diving speeds, aileron loads became heavy, reducing roll authority.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003e📊 Performance Comparison\u003c\/h3\u003e\n\n\u003ctable\u003e\n  \u003cthead\u003e\n    \u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eN1K1-J Shiden\u003c\/th\u003e\n\u003cth\u003eN1K2-J Shiden-Kai\u003c\/th\u003e\n\u003c\/tr\u003e\n  \u003c\/thead\u003e\n  \u003ctbody\u003e\n    \u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e594 km\/h (369 mph) at 5,900 m\u003c\/td\u003e\n\u003ctd\u003e595 km\/h (370 mph) at 5,600 m\u003c\/td\u003e\n\u003c\/tr\u003e\n    \u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e12,500 m (41,010 ft)\u003c\/td\u003e\n\u003ctd\u003e10,760 m (35,300 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n    \u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e2,897 kg (6,387 lb)\u003c\/td\u003e\n\u003ctd\u003e2,657 kg (5,858 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n    \u003ctr\u003e\n\u003ctd\u003eGross Weight\u003c\/td\u003e\n\u003ctd\u003e3,900 kg (8,598 lb)\u003c\/td\u003e\n\u003ctd\u003e4,000 kg (8,818 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n    \u003ctr\u003e\n\u003ctd\u003eInternal Fuel\u003c\/td\u003e\n\u003ctd\u003e477 L (126 US gal)\u003c\/td\u003e\n\u003ctd\u003e511 L (135 US gal)\u003c\/td\u003e\n\u003c\/tr\u003e\n    \u003ctr\u003e\n\u003ctd\u003eOperational Range\u003c\/td\u003e\n\u003ctd\u003e1,432 km (890 mi)\u003c\/td\u003e\n\u003ctd\u003e1,295 km (805 mi) internal fuel\u003c\/td\u003e\n\u003c\/tr\u003e\n  \u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003e🔧 Structural \u0026amp; Engineering Modifications (N1K1-J → N1K2-J)\u003c\/h3\u003e\n\u003cul\u003e\n  \u003cli\u003e\n\u003cstrong\u003eLanding Gear Redesign:\u003c\/strong\u003e The mid-wing N1K1-J required exceptionally long, complex double-action retraction gear to clear the 4-bladed propeller. Engineering bulletins recorded high failure rates, wheel-casting fractures, and structural collapses on rough fields. The low-wing N1K2-J shortened the gear legs, eliminating the compression mechanism and improving structural reliability.\u003c\/li\u003e\n  \u003cli\u003e\n\u003cstrong\u003eWeight Reduction:\u003c\/strong\u003e The N1K2-J airframe was extensively rationalised — component count was reduced significantly, stripping approximately 250 kg (550 lb) of dead weight and enabling sub-assembly production in dispersed shadow factories.\u003c\/li\u003e\n  \u003cli\u003e\n\u003cstrong\u003eArmament Integration:\u003c\/strong\u003e The N1K1-J carried two of its four 20mm Type 99 Mark 2 cannon in drag-inducing underwing pods. Engineering directives for the N1K1-Ja and N1K2-J repositioned all four cannon inside the wing envelope, cleaning the lower wing surface and reducing frontal area drag.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003cp\u003e\u003cem\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.\u003c\/em\u003e\u003c\/p\u003e\n\u003cp\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":53646566850907,"sku":null,"price":35.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/kawanishi-n1k-j-shiden-leaderboard-banner.png?v=1784823674"},{"product_id":"kawasaki-ki-10-perry-army-type-95-fighter-collection","title":"Kawasaki Ki-10 \"Perry\" — Army Type 95 Fighter Collection","description":"\u003ch2\u003eKawasaki Ki-10 \"Perry\" — Army Type 95 Fighter\u003c\/h2\u003e\u003cp\u003eThe Kawasaki Ki-10 \"Perry\" (九五式戦闘機, \u003cem\u003eKyūgo-shiki Sentōki\u003c\/em\u003e) was the pinnacle of Imperial Japanese Army biplane fighter design — a machine that deliberately chose extreme maneuverability over the raw speed offered by the emerging monoplane generation. Designed under chief engineer \u003cstrong\u003eTakeo Doi\u003c\/strong\u003e, the Ki-10 remained the IJA's frontline fighter from 1935 through the early years of the Second Sino-Japanese War.\u003c\/p\u003e\u003cp\u003eThis Living Collection brings together the surviving primary-source documentation for the Ki-10 family, drawn from IJA archives, Kawasaki manufacturer records, and a rare captured evaluation report published by the \u003cstrong\u003eSoviet NII VVS in 1939\u003c\/strong\u003e — one of the most detailed external assessments of the type ever produced.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003eCollection Contents\u003c\/h3\u003e\u003ch4\u003eVariant II — Ki-10-II (Model 2)\u003c\/h4\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-10-II Technical Drawing\u003c\/strong\u003e — Ki-10-II Model 2 Type 95 Fighter Structural Drawings · 九五式戦闘機（二型）胴體骨格図 · \u003cem\u003eJapanese Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-10-II Operating \u0026amp; Maintenance\u003c\/strong\u003e — Kawasaki Ki-10-II Model 2 Type 95 Fighter Instruction Manual · 九五式戦闘機（二型）説明書 · \u003cem\u003eJapanese Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch4\u003eNo Variant — Common Documents\u003c\/h4\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-10 Engine\u003c\/strong\u003e — Kawasaki Ha-9 Type 95 Aircraft Engine Instruction Manual · 九五式ハ〇〇馬力發動機説明書 · \u003cem\u003eJapanese Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-10 Slides, Photos \u0026amp; Brochures\u003c\/strong\u003e — Ki-10 Photographic Collection · \u003cem\u003eEnglish Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003ePerformance Data\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eMetric\u003c\/th\u003e\n\u003cth\u003eKi-10-I (Model 1)\u003c\/th\u003e\n\u003cth\u003eKi-10-II (Model 2)\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e400 km\/h at 3,000 m\u003c\/td\u003e\n\u003ctd\u003e400 km\/h at 3,000 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e320 km\/h\u003c\/td\u003e\n\u003ctd\u003e320 km\/h\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e10,000 m (32,810 ft)\u003c\/td\u003e\n\u003ctd\u003e11,500 m (37,730 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRate of Climb\u003c\/td\u003e\n\u003ctd\u003e5,000 m in 5 min\u003c\/td\u003e\n\u003ctd\u003e5,000 m in 4 min 30 sec\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRange\u003c\/td\u003e\n\u003ctd\u003e1,100 km (684 mi)\u003c\/td\u003e\n\u003ctd\u003e1,100 km (684 mi)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e1,300 kg (2,866 lbs)\u003c\/td\u003e\n\u003ctd\u003e1,360 kg (2,998 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eLoaded Weight\u003c\/td\u003e\n\u003ctd\u003e1,650 kg (3,638 lbs)\u003c\/td\u003e\n\u003ctd\u003e1,740 kg (3,836 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003eAerodynamic \u0026amp; Structural Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Geometry:\u003c\/strong\u003e Sesquiplane (unequal span) configuration — all-metal structure, light alloy and fabric covering. Upper wing span 10.02 m, significantly larger than the lower wing.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eControl Surfaces:\u003c\/strong\u003e Ailerons fitted exclusively to the upper wing to reduce mechanical complexity and adverse yaw.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eParasitic Drag Reduction:\u003c\/strong\u003e Narrow-profile welded steel-tube fuselage with mixed metal\/fabric skinning; streamlined wheel spats over fixed undercarriage to clean airflow beneath the lower wing.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\u003cp\u003ePowerplant: \u003cstrong\u003eKawasaki Ha-9-IIa\u003c\/strong\u003e (Ha-9-IIb on Model 2) — 12-cylinder, liquid-cooled, 60° Vee piston engine, a highly developed evolution of licensed European inline technology.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePower Output:\u003c\/strong\u003e 850 hp (634 kW) at takeoff\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropeller:\u003c\/strong\u003e Initially two-bladed wooden; updated via technical bulletin to a three-bladed fixed-pitch metal propeller\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCooling System:\u003c\/strong\u003e Large un-ducted radiator beneath the engine cowling — effective but a primary source of frontal drag\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003cp\u003e\u003cem\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.\u003c\/em\u003e\u003c\/p\u003e\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":53690003685723,"sku":null,"price":30.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-10-banner-2-in-flight.png?v=1785427550"},{"product_id":"kawasaki-ki-64-rob-tandem-engine-fighter-collection","title":"Kawasaki Ki-64 \"Rob\" — Tandem-Engine Fighter Collection","description":"\u003ch3\u003eKawasaki Ki-64 \"Rob\" — Tandem-Engine Experimental Fighter\u003c\/h3\u003e\n\u003cp\u003eThe Kawasaki Ki-64 (Allied codename \u003cstrong\u003e\"Rob\"\u003c\/strong\u003e) stands as one of the most technically audacious aircraft designs of the Second World War — an advanced experimental heavy interceptor conceived by chief designer \u003cstrong\u003eTakeo Doi\u003c\/strong\u003e in 1939. Only a single prototype was ever completed. It flew just five times from December 1943 before a catastrophic engine fire on its fifth flight permanently ended the programme.\u003c\/p\u003e\n\u003cp\u003eDue to the project's brief operational lifespan and the destruction of Japanese archives at war's end, original Kawasaki factory engineering bulletins are virtually non-existent. The primary surviving technical record is the post-war \u003cstrong\u003eU.S. Army Air Force T-2 Technical Intelligence Report No. F-IR-100-RE\u003c\/strong\u003e, compiled at Wright Field, Dayton, Ohio — the cornerstone document of this Living Collection.\u003c\/p\u003e\n\u003chr\u003e\n\u003ch3\u003eCollection Contents\u003c\/h3\u003e\n\u003ch4\u003eNo Variant — Common Documents\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-64 Technical Publications\u003c\/strong\u003e — Kawasaki Ki-64 Tandem-Engine Fighter with Vapor-Phase Cooling · Technical Intelligence Report No. F-IR-100-RE · \u003cem\u003eEnglish Language\u003c\/em\u003e · Released August 1946 · Headquarters Air Materiel Command, Wright Field, Dayton, Ohio\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-64 Slides, Photos \u0026amp; Brochures\u003c\/strong\u003e — Ki-64 Photographic Collection · \u003cem\u003eEnglish Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eAerodynamic \u0026amp; Design Overview\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eMinimizing Drag:\u003c\/strong\u003e Designed explicitly to achieve extreme speeds by eliminating conventional drag-heavy scoop radiators entirely.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLaminar Flow Wings:\u003c\/strong\u003e Ultra-smooth advanced laminar-profile wing panels for reduced boundary-layer drag.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eSurface Evaporative Cooling:\u003c\/strong\u003e A unique 258 sq. ft. steam-condensing network embedded directly into the wing skin replaced conventional radiators.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWind Tunnel Validation:\u003c\/strong\u003e A modified Ki-61 testbed confirmed the aerodynamic skin layout delivered approximately 35 mph speed advantage over conventional cooling arrangements.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eEngine Technical Notes — Kawasaki Ha-201\u003c\/h3\u003e\n\u003cp\u003eThe Ha-201 coupled two 12-cylinder inverted-Vee engines (derived from the licensed German \u003cstrong\u003eDaimler-Benz DB 601Aa\u003c\/strong\u003e) into a single tandem powerplant of extraordinary complexity.\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eLayout:\u003c\/strong\u003e Front engine in the nose; rear engine behind the cockpit, driving forward via a long extension shaft running between the pilot's legs.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePower Output:\u003c\/strong\u003e 2,350 hp at takeoff · 2,200 hp at 12,795 ft operational altitude.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropeller System:\u003c\/strong\u003e Coaxial contra-rotating — rear engine drove the forward adjustable-pitch propeller; front engine drove the rear fixed-pitch propeller. An unfinished pitch synchronizer caused uneven rotation speeds.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCooling Cycle:\u003c\/strong\u003e Engine coolant pressurized to steam; 2% flashed to vapour and condensed through inner wing skins, recycling fluid continuously.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eHandling, Stability \u0026amp; Operational Hazards\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eSevere Overheating:\u003c\/strong\u003e Without conventional scoop radiators, the aircraft suffered extreme thermal spikes during ground idling, taxiing, and high-load climbs.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWeight Distribution:\u003c\/strong\u003e Heavy fuselage-nose and spine mass concentration produced centre-of-gravity characteristics entirely unlike agile IJA fighters such as the A6M Zero.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFatal Defect:\u003c\/strong\u003e On the fifth test flight, rear cooling lines failed, triggering a massive engine fire that forced a structural crash landing and permanently ended the programme.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003ePerformance 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\u003eTop Speed\u003c\/td\u003e\n\u003ctd\u003e429 mph (690 km\/h) at 16,404 ft (5,000 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eClimb Rate\u003c\/td\u003e\n\u003ctd\u003e16,404 ft (5,000 m) in 5 min 30 sec\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e39,370 ft (12,000 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRange\u003c\/td\u003e\n\u003ctd\u003e620 miles (1,000 km)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e8,929 lbs (4,050 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eGross Weight\u003c\/td\u003e\n\u003ctd\u003e11,244 lbs (5,100 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWing Area \/ Loading\u003c\/td\u003e\n\u003ctd\u003e300 sq. ft \/ 37.3 lb\/sq ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eProposed Armament\u003c\/td\u003e\n\u003ctd\u003e4 × 20 mm Ho-5 cannons (2 nose, 2 wing)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003chr\u003e\n\u003cp\u003e\u003cem\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.\u003c\/em\u003e\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":53690371440987,"sku":null,"price":34.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-64-banner-1-in-flight-render.png?v=1785429434"},{"product_id":"kawasaki-ki-48-lily-army-type-99-twin-engine-light-bomber-collection","title":"Kawasaki Ki-48 \"Lily\" — Army Type 99 Twin-Engine Light Bomber Collection","description":"\u003ch3\u003eKawasaki Ki-48 \"Lily\" — Army Type 99 Twin-Engine Light Bomber\u003c\/h3\u003e\n\u003cp\u003eThe Kawasaki Ki-48 (Allied codename \u003cstrong\u003e\"Lily\"\u003c\/strong\u003e, 九九式双軽爆撃機, \u003cem\u003eKyūkyū-shiki Sōkei Bakugekiki\u003c\/em\u003e) was the Imperial Japanese Army's standard twin-engine light bomber from 1940 through the final stages of the Pacific War. Designed by \u003cstrong\u003eTakeo Doi\u003c\/strong\u003e, the Ki-48 underwent continuous aerodynamic and structural refinement across its production variants, driven by hard lessons from combat deployment in China and the Pacific theater.\u003c\/p\u003e\n\u003cp\u003eThis Living Collection consolidates the surviving primary-source documentation: original Japanese technical logs, post-war Allied intelligence evaluation reports compiled by the \u003cstrong\u003eU.S. Strategic Bombing Survey (USSBS)\u003c\/strong\u003e and the \u003cstrong\u003eTechnical Air Intelligence Center (TAIC)\u003c\/strong\u003e, and engineering bulletins covering mid-war survivability retrofits.\u003c\/p\u003e\n\u003chr\u003e\n\u003ch3\u003eCollection Contents\u003c\/h3\u003e\n\u003ch4\u003eVariant Model 1-2 — Ki-48 (Models 1 \u0026amp; 2)\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-48 Operating \u0026amp; Maintenance\u003c\/strong\u003e — Kawasaki Ki-48 Model 1 and Model 2 Type 99 Supplementary Diagrams and Attachments Instruction Manual, 飛行機教程案 · 九九式双軽爆撃機（一型二型）附図 · \u003cem\u003eJapanese Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch4\u003eNo Variant — Common Documents\u003c\/h4\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-48 Slides, Photos \u0026amp; Brochures\u003c\/strong\u003e — Ki-48 Photographic Collection · \u003cem\u003eEnglish Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003ePrimary Technical Documents\u003c\/h3\u003e\n\u003cp\u003eCaptured documents translated and cataloged post-war by the USSBS and TAIC:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eTokorozawa Army Air Maintenance School Operating Manual\u003c\/strong\u003e (October 1944) — USSBS Index Section 2, Report No. 15n(13). Covers flight preparation, weight distribution, and system operation for Models 1 and 2.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eJapanese Aircraft Manual\u003c\/strong\u003e — USSBS Report No. 1o-10, Section 2, Frame Numbers 157–160. Schematic lookups and maintenance instructions for field mechanics.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTAIC Manual on Japanese Aircraft\u003c\/strong\u003e — Report No. 9-a-43, USSBS Index Section 6, Frame Numbers 123–126. Allied flight-testing intelligence summary for the Ki-48 airframe.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eAerodynamic \u0026amp; Stability Studies\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePrototypes (1939):\u003c\/strong\u003e Initial trials revealed severe tail flutter deficiencies. Five pre-production models were built to trial varying tailplane geometry adjustments before serial manufacture.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eModel II Fin Extensions (1942):\u003c\/strong\u003e Dorsal fin extension and slight fuselage lengthening to improve directional stability and counter yaw under increased payload.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eModel IIb Dive-Brakes:\u003c\/strong\u003e Structural wing reinforcements to support retractable ventral dive-brakes outboard of the engine nacelles.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\n\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eKi-48-I (Nakajima Ha-25)\u003c\/th\u003e\n\u003cth\u003eKi-48-II (Nakajima Ha-115)\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eTake-off Power\u003c\/td\u003e\n\u003ctd\u003e990 hp\u003c\/td\u003e\n\u003ctd\u003e1,150 hp\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eSupercharger\u003c\/td\u003e\n\u003ctd\u003eSingle-stage, two-speed\u003c\/td\u003e\n\u003ctd\u003eTwo-speed centrifugal\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePropeller\u003c\/td\u003e\n\u003ctd\u003e3-bladed variable pitch (2.9 m)\u003c\/td\u003e\n\u003ctd\u003e3-bladed constant-speed\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003chr\u003e\n\u003ch3\u003ePerformance Data\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum Speed:\u003c\/strong\u003e 480 km\/h (298 mph) at 3,000 m (Model I) · 505 km\/h (314 mph) at 5,600 m (Model II)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eClimb Performance:\u003c\/strong\u003e 5,000 m (16,405 ft) in 10 minutes\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eService Ceiling:\u003c\/strong\u003e 10,100 m (33,136 ft)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum Range:\u003c\/strong\u003e 2,400 km (1,491 miles)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eBomb Load:\u003c\/strong\u003e Standard 400 kg (882 lb) internal · Structural maximum 800 kg (1,764 lb) on Ki-48-II\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003ch3\u003eEngineering Bulletins — Survivability Retrofits\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eCrew Armor:\u003c\/strong\u003e 12.5 mm plate behind bombardier · 6.5 mm plate under pilot's seat · 16.5 mm plates protecting ammunition reserves.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFuel System Safety:\u003c\/strong\u003e Replacement of unprotected wing fuel cells with leak-resistant laminated rubber self-sealing tanks.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003chr\u003e\n\u003cp\u003e\u003cem\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.\u003c\/em\u003e\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":53690485801307,"sku":null,"price":28.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-48-banner-1-colour-airshow.png?v=1785430629"},{"product_id":"kawasaki-ki-32-mary-army-type-98-light-bomber-collection","title":"Kawasaki Ki-32 \"Mary\" — Army Type 98 Light Bomber Collection","description":"\u003ch2\u003eKawasaki Ki-32 \"Mary\" — Army Type 98 Light Bomber\u003c\/h2\u003e\u003cp\u003eThe Kawasaki Ki-32 (Allied codename \u003cstrong\u003e\"Mary\"\u003c\/strong\u003e, 九八式軽爆撃機, \u003cem\u003eKyūhachi-shiki Kei Bakugekiki\u003c\/em\u003e) holds a singular place in Imperial Japanese Army Air Force history as the \u003cstrong\u003elast IJAAF light bomber to use a liquid-cooled inline engine\u003c\/strong\u003e. Designed at Kawasaki's Kagamigahara bureau and entering service in 1938, the Ki-32 served extensively in the Second Sino-Japanese War before being superseded by more modern types.\u003c\/p\u003e\u003cp\u003eDue to the deliberate destruction of IJAAF technical archives in August 1945, surviving primary documentation for the Ki-32 is exceptionally rare. This Living Collection consolidates the most significant surviving artifacts: the original 1939 manufacturer operating handbook — indexed post-war by the \u003cstrong\u003eU.S. Strategic Bombing Survey (USSBS)\u003c\/strong\u003e as Report No. 15n(11) and preserved by the \u003cstrong\u003eNational Diet Library of Japan\u003c\/strong\u003e (PID: 8815752) — together with the Ha-9 engine manual and photographic archive.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003eCollection Contents\u003c\/h3\u003e\u003ch4\u003eNo Variant — Common Documents\u003c\/h4\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-32 Operating \u0026amp; Maintenance\u003c\/strong\u003e — Kawasaki Ki-32 Type 98 Light Bomber Instruction Manual · 川崎キ32 九八式軽爆撃機説明書 · \u003cem\u003eJapanese Language\u003c\/em\u003e · Imperial Japanese Army Air Headquarters (Rikugun Koku Honbu) · September 1939 · USSBS Index Section 2, Report No. 15n(11)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-32 Engine\u003c\/strong\u003e — Kawasaki Ha-9 Type 95 Aircraft Engine Instruction Manual · 九五式ハ〇〇馬力發動機説明書 · \u003cem\u003eJapanese Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-32 Slides, Photos \u0026amp; Brochures\u003c\/strong\u003e — Ki-32 Photographic Collection · \u003cem\u003eEnglish Language\u003c\/em\u003e\n\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eEngine Technical Notes — Kawasaki Ha-9-IIb\u003c\/h3\u003e\u003cp\u003eThe Ki-32 was powered by the \u003cstrong\u003eArmy Type 98 (Kawasaki Ha-9-IIb)\u003c\/strong\u003e — a V-12 liquid-cooled piston engine and the last of its type to power an IJAAF light bomber.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eTake-off Power:\u003c\/strong\u003e 850 hp (634 kW)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eSea Level:\u003c\/strong\u003e 775 hp (578 kW)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum Rating:\u003c\/strong\u003e 950 hp (709 kW) at 12,470 ft (3,800 m)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEngineering History:\u003c\/strong\u003e March 1937 flight tests revealed chronic crankshaft failures. Emergency Kawasaki bulletins mandated crankshaft reinforcement, delaying deployment relative to the competing radial-engined Mitsubishi Ki-30.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCombat Vulnerability:\u003c\/strong\u003e Coolant lines and radiators were highly exposed to ground fire; cooling system punctures caused rapid engine seizure and were a primary source of combat losses.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003ePerformance Data\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eMetric\u003c\/th\u003e\n\u003cth\u003eValue\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e263 mph (423 km\/h) at 12,925 ft (3,840 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e186 mph (300 km\/h)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRate of Climb\u003c\/td\u003e\n\u003ctd\u003e16,405 ft (5,000 m) in 10 min 55 sec\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e29,265 ft (8,920 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRange\u003c\/td\u003e\n\u003ctd\u003e826 miles (1,300 km) standard · 1,218 miles (1,965 km) maximum\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWing Loading\u003c\/td\u003e\n\u003ctd\u003e21.3 lbs\/sq ft (82 kg\/m²)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e5,179 lbs (2,349 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Take-off Weight\u003c\/td\u003e\n\u003ctd\u003e8,293 lbs (3,762 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003eHandling, Stability \u0026amp; Aerodynamic Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eDive-Bombing Capability:\u003c\/strong\u003e Mid-wing monoplane with internal bomb bay. 1937 IJAAF competitive trials confirmed superior structural rigidity over the Ki-30, permitting safe dive-bombing runs at angles up to 60 degrees.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFixed Undercarriage:\u003c\/strong\u003e Wide-track fixed cantilever gear with open-sided wheel fairings — continuous drag penalty on top speed, but highly stable and forgiving on unpaved forward airfields in China.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eArchival Note:\u003c\/strong\u003e Formal aerodynamic stability studies (elevator\/rudder moment coefficients) from the Kagamigahara design bureau are considered lost. Surviving data derives from 1939 Army performance evaluation sheets and post-war USSBS compilation.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003ePrimary Archival Sources\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eNational Diet Library (NDL), Japan\u003c\/strong\u003e — Digitized USSBS microfilms; search Japanese designation 九八式軽爆撃機 (PID: 8815752)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNational Institute for Defense Studies (NIDS), Tokyo\u003c\/strong\u003e — Surviving Imperial Army administrative and technical combat logs\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eSmithsonian NASM\u003c\/strong\u003e — Captured Japanese technical manuals cataloged by U.S. military intelligence post-WWII\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003cp\u003e\u003cem\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.\u003c\/em\u003e\u003c\/p\u003e\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":53690527187291,"sku":null,"price":28.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-32-banner-1-colour-a-154.png?v=1785431639"},{"product_id":"mitsubishi-a6m-zero-collection","title":"Mitsubishi A6M \"Zero\" — Primary-Source Documentation Collection","description":"\u003ch3\u003eMitsubishi A6M \"Zero\" — Primary-Source Documentation Collection\u003c\/h3\u003e\n\u003cp\u003eThe most iconic carrier fighter of the Pacific War, the Mitsubishi A6M \"Zero\" (零式艦上戦闘機) dominated the skies from 1940 to 1942 with a combination of extraordinary range, agility, and firepower that stunned Allied pilots. This collection assembles the original factory and intelligence documentation across three principal variants — A6M2, A6M3, and A6M5 — together with a dedicated photographic archive.\u003c\/p\u003e\n\u003ch3\u003eAerodynamic Reports \u0026amp; Structural Design\u003c\/h3\u003e\n\u003cp\u003eThe A6M's airframe was a masterclass in weight elimination. Its flush-riveted, all-metal monoplane structure used fabric-covered control surfaces and was built from \u003cstrong\u003eExtra Super Duralumin (ESD)\u003c\/strong\u003e, a then-secret ultra-lightweight alloy developed by Sumitomo. This came at a deliberate cost: no protective armor plating, no self-sealing fuel tanks. The never-exceed speed (V\u003csub\u003eNE\u003c\/sub\u003e) was structurally capped, preventing the Zero from tracking heavy Allied aircraft in steep, high-speed dives — a vulnerability that Allied tacticians exploited once it was understood.\u003c\/p\u003e\n\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M2:\u003c\/strong\u003e Nakajima Sakae 12 air-cooled radial — 940 hp\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M3 \/ A6M5:\u003c\/strong\u003e Nakajima Sakae 21\/22 — 1,130 hp with two-speed supercharger\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropeller:\u003c\/strong\u003e Three-blade constant-speed, based on licensed Hamilton Standard Hydromatic design\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eExhaust (A6M5 onwards):\u003c\/strong\u003e Individual rearward-facing thrust-augmenting stacks for reduced drag and increased top speed\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\n\u003cp\u003eBelow 200 mph (322 km\/h), the Zero yielded exceptional roll rates and a turning radius unmatched by any Allied fighter of the period. Above 216 mph (348 km\/h), aerodynamic loading stiffened the controls dramatically. Fabric-covered ailerons flexed under high dynamic pressure — a phenomenon known as \u003cstrong\u003eaileron reversal\u003c\/strong\u003e — slowing response time precisely when speed was highest.\u003c\/p\u003e\n\u003ch3\u003ePerformance Data\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\n\u003ctr\u003e\n\u003cth\u003eVariant\u003c\/th\u003e\n\u003cth\u003eEngine\u003c\/th\u003e\n\u003cth\u003eMax Speed\u003c\/th\u003e\n\u003cth\u003eClimb Rate\u003c\/th\u003e\n\u003cth\u003eService Ceiling\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eA6M2 Model 21\u003c\/td\u003e\n\u003ctd\u003eSakae 12 (940 hp)\u003c\/td\u003e\n\u003ctd\u003e331 mph \/ 14,930 ft\u003c\/td\u003e\n\u003ctd\u003e2,980 ft\/min\u003c\/td\u003e\n\u003ctd\u003e32,810 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eA6M3 Model 22\u003c\/td\u003e\n\u003ctd\u003eSakae 21 (1,130 hp)\u003c\/td\u003e\n\u003ctd\u003e336 mph \/ 19,685 ft\u003c\/td\u003e\n\u003ctd\u003e3,100 ft\/min\u003c\/td\u003e\n\u003ctd\u003e36,250 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eA6M5 Model 52\u003c\/td\u003e\n\u003ctd\u003eSakae 21 (1,130 hp)\u003c\/td\u003e\n\u003ctd\u003e351 mph \/ 19,685 ft\u003c\/td\u003e\n\u003ctd\u003e3,090 ft\/min\u003c\/td\u003e\n\u003ctd\u003e38,520 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003ch3\u003eEngineering Bulletins \u0026amp; Combat History\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003e12-Shi Specification (1937):\u003c\/strong\u003e The Imperial Japanese Navy brief demanded unparalleled maneuverability and exceptional long-range drop tank capability from a carrier-based fighter.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eThe Akutan Zero (1942):\u003c\/strong\u003e An intact A6M2 recovered in the Aleutian Islands gave Allied engineers complete diagnostic data, directly informing anti-Zero combat tactics.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eField Modifications:\u003c\/strong\u003e Armament evolved from twin 7.7 mm cowl guns with 20 mm wing cannons to specialized unit-level variants including oblique-firing night interceptor conversions.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eCollection Manifest\u003c\/h3\u003e\n\u003cp\u003e\u003cstrong\u003eVariants covered:\u003c\/strong\u003e A6M2 · A6M3 · A6M5  |  \u003cstrong\u003eTotal Manuals: 4\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M2 — Operating \u0026amp; Maintenance:\u003c\/strong\u003e Mitsubishi A6M2 Type 21 Zero — Instruction Manual, 零式艦上戦闘機二一型取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M3 — Operating \u0026amp; Maintenance:\u003c\/strong\u003e Mitsubishi A6M3 Type 32 Zero — Instruction Manual, 零式艦上戦闘機三二型取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M5 — Flight Manual:\u003c\/strong\u003e Mitsubishi A6M5 Type 52 Zero — Pilot's Flight Manual, USAAF Technical Intelligence Flight Manual for Captured Japanese Aircraft (English Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eA6M — Photo Archive:\u003c\/strong\u003e A6M Photographic Collection (English Language)\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 authorized distributor.\u003cbr\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":53726686445915,"sku":null,"price":49.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/a6m-hero.png?v=1786031190"},{"product_id":"mitsubishi-f1m-pete-collection","title":"Mitsubishi F1M \"Pete\" — Primary-Source Documentation Collection","description":"\u003ch2\u003eMitsubishi F1M \"Pete\" — Primary-Source Documentation Collection\u003c\/h2\u003e\u003cp\u003eThe Mitsubishi F1M \"Pete\" (零式観測機, Type Zero Observation Seaplane) was the Imperial Japanese Navy's most capable catapult-launched biplane floatplane of the Pacific War. Born from a troubled prototype program, the F1M evolved through a comprehensive aerodynamic and structural redesign into a versatile platform used for observation, escort, anti-submarine patrol, and air-sea rescue operations.\u003c\/p\u003e\u003ch3\u003eAerodynamic Engineering \u0026amp; Redesign\u003c\/h3\u003e\u003cp\u003eThe original F1M1 prototypes featured elliptical wings that produced severe boundary-layer airflow separation. The production F1M2 replaced these entirely with straight-tapered wings and a pronounced dihedral angle to correct rolling instability. Aerodynamic efficiency was further achieved through a single \"I\" interplane strut configuration, minimal bracing wires, a flush-riveted all-metal fuselage, and deeply integrated central float strut architecture.\u003c\/p\u003e\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eF1M1 prototype:\u003c\/strong\u003e Nakajima Hikari 1 — 9-cylinder air-cooled radial, ~820 hp. Wide cowl caused cooling issues and poor forward visibility.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eF1M2 production:\u003c\/strong\u003e Mitsubishi MK2C Zuisei 13 — 14-cylinder twin-row air-cooled radial, 875 hp (652 kW). Smaller diameter allowed aggressive nose taper, restoring pilot sightlines.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropeller:\u003c\/strong\u003e 3-blade all-metal variable-pitch assembly, optimized for both water takeoff and level flight.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\u003cp\u003eEarly 1936 flight logs described the F1M1 as virtually unusable. Engineers addressed yaw instability by enlarging the vertical fin and rudder to counter engine torque and float side-area effects. Water handling was corrected by increasing central float displacement volume and redesigning the wingtip stabilizing floats to prevent lower wing immersion during high-speed taxiing turns.\u003c\/p\u003e\u003ch3\u003eEngineering Bulletins \u0026amp; Structural Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eFuselage Stress Reinforcement:\u003c\/strong\u003e Structural telemetry during high-G combat maneuvers and rough water landings revealed extreme torsional stress on the mid-section. Engineering bulletins mandated external metal reinforcing sheets around the cockpit area to rigidify the monocoque structure.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFabric-to-Metal Transitions:\u003c\/strong\u003e Control surfaces (ailerons, elevators, rudder) remained fabric-covered over aluminum frames; primary wing boxes and fuselage skinning used stressed-metal alloys throughout.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTrainer Variant (F1M2-K):\u003c\/strong\u003e A specific engineering bulletin converted a small run of airframes into dual-control advanced seaplane trainers, aiding pilots adjusting to the high-maneuverability quirks of a float-equipped biplane.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003ePerformance Data (F1M2 Model 11)\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eValue\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e370 km\/h (230 mph) at 11,285 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eNormal Range\u003c\/td\u003e\n\u003ctd\u003e740 km (460 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e9,440 m (30,970 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e1,928 kg (4,251 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e2,856 kg (6,296 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eFixed Armament\u003c\/td\u003e\n\u003ctd\u003e2 × 7.7 mm Type 97 cowl guns\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eDefensive Armament\u003c\/td\u003e\n\u003ctd\u003e1 × 7.7 mm Type 92 flexible rear gun\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eBomb Load\u003c\/td\u003e\n\u003ctd\u003e2 × 60 kg underwing\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch3\u003eCollection Manifest\u003c\/h3\u003e\u003cp\u003e\u003cstrong\u003eVariants covered:\u003c\/strong\u003e F1M1  |  \u003cstrong\u003eTotal Manuals: 2\u003c\/strong\u003e\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eF1M1 — Operating \u0026amp; Maintenance:\u003c\/strong\u003e Mitsubishi F1M1 Type 0 Observation Seaplane — Handling Instructions Manual, 零式一號觀測機一型取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eF1M — Photo Archive:\u003c\/strong\u003e F1M Photographic Collection (English Language)\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\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\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":53726757126491,"sku":null,"price":29.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/f1m-promotional.png?v=1786032345"},{"product_id":"mitsubishi-g4m-betty-collection","title":"Mitsubishi G4M \"Betty\" — Primary-Source Documentation Collection","description":"\u003ch2\u003eMitsubishi G4M \"Betty\" — Primary-Source Documentation Collection\u003c\/h2\u003e\u003cp\u003eThe Mitsubishi G4M \"Betty\" (一式陸上攻撃機) was the Imperial Japanese Navy's principal land-based medium bomber throughout the Pacific War. Designed under chief engineer Kiro Honjo to achieve the range of a flying boat using only two engines, the G4M represented an extreme engineering tradeoff: maximum aerodynamic purity and range at the cost of armor and structural survivability — earning the Allied nickname \u003cem\u003e\"The Flying Lighter.\"\u003c\/em\u003e\u003c\/p\u003e\u003ch3\u003eAerodynamic Reports \u0026amp; Fuselage Design\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eDrag Optimization:\u003c\/strong\u003e The cylindrical \"cigar-shaped\" fuselage (Hamaki) featured flush riveting and fully retractable landing gear to minimize parasite drag across its mid-wing configuration.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTorpedo Penalty:\u003c\/strong\u003e Accommodating the Type 91 aerial torpedo internally required enlarging the fuselage cross-section, increasing wetted area and demanding high-power engines to compensate.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eIntegral Wet Wing:\u003c\/strong\u003e To achieve 3,000+ nautical mile range, the unarmored wing spar framework was sealed to act directly as fuel tanks. A single incendiary round could ignite fuel vapor instantly.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eMK4A Kasei 11 (G4M1)\u003c\/th\u003e\n\u003cth\u003eMK4P Kasei 21 (G4M2)\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eConfiguration\u003c\/td\u003e\n\u003ctd\u003e14-cylinder air-cooled radial\u003c\/td\u003e\n\u003ctd\u003e14-cylinder air-cooled radial\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eTakeoff Power\u003c\/td\u003e\n\u003ctd\u003e1,530 hp @ 2,450 RPM\u003c\/td\u003e\n\u003ctd\u003e1,800 hp\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePropeller\u003c\/td\u003e\n\u003ctd\u003e3-blade Sumitomo-Hamilton CS-3B\u003c\/td\u003e\n\u003ctd\u003e4-blade Sumitomo constant-speed\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eDry Weight\u003c\/td\u003e\n\u003ctd\u003e632 kg (1,393 lbs)\u003c\/td\u003e\n\u003ctd\u003e730 kg (1,609 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eControl Surfaces:\u003c\/strong\u003e Cantilever monoplane tail with fabric-covered elevators and rudder; metal trim tabs to manage pilot forces on long-range missions.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M2 Instability:\u003c\/strong\u003e Heavier Kasei 21 engines and upgraded turrets shifted the Center of Gravity, causing dangerous longitudinal instability during bombing runs.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M3 Correction:\u003c\/strong\u003e Engineers shortened the wingspan, moved the CG forward, and added dihedral to the horizontal stabilizer, eliminating tail-wobble at high speed.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003ePerformance Data (G4M1 Model 11)\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eValue\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e266 mph (428 km\/h) at 13,780 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e196 mph (315 km\/h) at 9,840 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e28,870 ft (8,800 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRate of Climb\u003c\/td\u003e\n\u003ctd\u003e1,800 ft\/min (9.14 m\/s)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Range\u003c\/td\u003e\n\u003ctd\u003e3,750 miles (6,035 km) unladen\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCombat Range\u003c\/td\u003e\n\u003ctd\u003e2,262 miles under normal load\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Payload\u003c\/td\u003e\n\u003ctd\u003e800 kg bombs or 1 × Type 91 torpedo\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch3\u003eEngineering Bulletins \u0026amp; Late-War Modifications\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M1 Refit (1943):\u003c\/strong\u003e Field units instructed to apply 3 mm rubber sheets to lower wing skins and wrap fuselage fuel lines in sponge rubber to suppress minor leaks.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M2e Bulletin:\u003c\/strong\u003e Structural reinforcement of the bomb bay to carry the Yokosuka MXY-7 Ohka piloted rocket bomb, including electrical release wiring — though the added weight severely degraded performance.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M3 Production Directive (1944):\u003c\/strong\u003e Completely redesigned wing with true self-sealing fuel tanks and 7.9 mm armor around crew positions. Only 60 units completed before factory disruptions ended production.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eCollection Manifest\u003c\/h3\u003e\u003cp\u003e\u003cstrong\u003eVariants covered:\u003c\/strong\u003e G4M1  |  \u003cstrong\u003eTotal Manuals: 2\u003c\/strong\u003e\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M1 — Operating \u0026amp; Maintenance:\u003c\/strong\u003e Mitsubishi G4M1 Type 1 Attack Bomber — Provisional Operating Instructions Manual, 一式陸上攻撃機一一型仓取扱説明書 (Japanese Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG4M — Photo Archive:\u003c\/strong\u003e G4M Photographic Collection (English Language)\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\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\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":53726775083355,"sku":null,"price":29.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/g4m-hero.png?v=1786033146"},{"product_id":"kokusai-ki-105-ohtori-collection","title":"Kokusai Ki-105 Ohtori — Primary-Source Documentation Collection","description":"\u003ch3\u003eKokusai Ki-105 Ohtori — Primary-Source Documentation Collection\u003c\/h3\u003e\n\u003cp\u003eThe Kokusai Ki-105 Ohtori (大鵬, \"Phoenix\") was one of the most unconventional transport aircraft produced by Japan during the Pacific War — a twin-boom, motorized derivative of the Ku-7 glider, engineered out of desperate strategic necessity to address the acute fuel crisis gripping the home islands in 1944.\u003c\/p\u003e\n\u003ch3\u003eAerodynamic \u0026amp; Structural Design\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eTwin-Boom Layout:\u003c\/strong\u003e High-aspect-ratio main wing with a central pod nacelle housing the cockpit and cargo bay. The twin tail booms were slightly shortened from the Ku-7 glider variant to correct center of gravity with forward engine mounts.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eComposite Construction:\u003c\/strong\u003e Central nacelle in lightweight aluminum alloy; wings and tail booms primarily wood to conserve strategic metals.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLanding Gear:\u003c\/strong\u003e Fixed heavy-duty tricycle undercarriage — four non-retractable main wheels on dual axles plus a single nose wheel — maintaining a level cabin floor for loading internal fuel bladders.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePowerplant:\u003c\/strong\u003e Two Mitsubishi Ha-26-II (Ha-102) 14-cylinder twin-row air-cooled radials, 940–960 hp each.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eRejected Option:\u003c\/strong\u003e Early designs considered the 450 hp Nakajima Ha-13; abandoned immediately due to severe power deficit.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropulsion:\u003c\/strong\u003e Three-blade constant-speed metal propellers mounted to the forward section of each tail boom.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eControl Surfaces:\u003c\/strong\u003e Fabric-covered wooden ailerons, elevators, and twin rudders adapted directly from glider blueprints.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eJapanese Army Assessment (December 1944):\u003c\/strong\u003e Test pilots considered the platform remarkably stable for its size.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAllied Evaluation:\u003c\/strong\u003e Retrospective flight safety journals noted the aircraft was sluggish, aerodynamically heavy to pilot, and highly vulnerable due to its slow cruise speeds.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003ePerformance Data\u003c\/h3\u003e\n\u003ctable\u003e\n\u003cthead\u003e\n\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eValue\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eWingspan\u003c\/td\u003e\n\u003ctd\u003e35.00 m (114 ft 10 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eLength\u003c\/td\u003e\n\u003ctd\u003e19.92 m (65 ft 4 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e12,500 kg (27,600 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eNormal Freight Payload\u003c\/td\u003e\n\u003ctd\u003e3,300 kg (7,300 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e220 km\/h (140 mph \/ 120 kts)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Range\u003c\/td\u003e\n\u003ctd\u003e2,500 km (1,600 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCrew\u003c\/td\u003e\n\u003ctd\u003e2 pilots\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003ch3\u003eEngineering Bulletins \u0026amp; Logistics\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eThe Sumatran Fuel Pipeline:\u003c\/strong\u003e Engineering bulletins designated the Ki-105 as a flying fuel tanker — flying unladen to Japanese-occupied oil fields in Sumatra, loading fuel reservoirs, and returning to Japan.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEfficiency Deficit:\u003c\/strong\u003e Engineering estimates calculated that up to 80% of the loaded fuel cargo would be consumed by the engines on the return trip alone, rendering the concept operationally marginal.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eCollection Manifest\u003c\/h3\u003e\n\u003cp\u003e\u003cstrong\u003eTotal Manuals: 2\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-105 Aircraft Handbook:\u003c\/strong\u003e Kokusai Ki-105 Ohtori — Detailed Design Specifications, 設計明細書 キ一○五 (Japanese Language)\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-105 Photo Archive:\u003c\/strong\u003e Ki-105 Photographic Collection (English Language)\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 authorized distributor.\u003cbr\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":53726819025243,"sku":null,"price":29.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-105-leaderboard-sepia.png?v=1786034206"},{"product_id":"mitsubishi-mu-2-engineering-flight-operations-maintenance-documentation","title":"Mitsubishi MU-2 — Engineering, Flight Operations \u0026 Maintenance Documentation","description":"\u003cdiv style=\"background: #0a1628; color: #c9a84c; border: 2px solid #c9a84c; padding: 32px 36px; font-family: Georgia,serif; max-width: 820px; margin: 0 auto 36px auto;\"\u003e\n\u003cdiv style=\"text-align: center; margin-bottom: 8px;\"\u003e✦ ✦ ✦\u003c\/div\u003e\n\u003cdiv style=\"text-align: center; font-size: 11px; letter-spacing: 3px; text-transform: uppercase; color: #c9a84c; margin-bottom: 6px;\"\u003eOnline Aviation Library\u003c\/div\u003e\n\u003chr style=\"border: none; border-top: 1px solid #c9a84c; margin: 8px 0 16px 0;\"\u003e\n\u003cdiv style=\"text-align: center; font-size: 12px; font-style: italic; color: #c9a84c; margin-bottom: 10px;\"\u003eMitsubishi Heavy Industries, Ltd. — Nagoya, Japan\u003cbr\u003eProduct Support: Mitsubishi Heavy Industries America (MHIA), Dallas, Texas\u003c\/div\u003e\n\u003cdiv style=\"text-align: center; font-size: 13px; color: #c9a84c; margin-bottom: 18px;\"\u003e✦\u003c\/div\u003e\n\u003cdiv style=\"text-align: center; font-size: 38px; font-weight: bold; letter-spacing: 2px; color: #c9a84c; margin-bottom: 8px;\"\u003eMITSUBISHI MU-2\u003c\/div\u003e\n\u003cdiv style=\"text-align: center; font-size: 16px; font-style: italic; color: #c9a84c; margin-bottom: 18px;\"\u003eEngineering, Flight Operations \u0026amp; Maintenance Documentation\u003c\/div\u003e\n\u003chr style=\"border: none; border-top: 1px solid #c9a84c; margin: 8px 0 14px 0;\"\u003e\n\u003cdiv style=\"text-align: center; font-size: 12px; color: #c9a84c; margin-bottom: 6px;\"\u003eType Certificates: A10SW · A2PC  |  Garrett \/ Honeywell TPE331 Series\u003c\/div\u003e\n\u003cdiv style=\"text-align: center; font-size: 12px; color: #c9a84c; margin-bottom: 6px;\"\u003eLanguage: English\u003c\/div\u003e\n\u003chr style=\"border: none; border-top: 1px solid #c9a84c; margin: 14px 0 14px 0;\"\u003e\n\u003cdiv style=\"font-size: 13px; color: #c9a84c; margin-bottom: 6px;\"\u003eThis collection contains primary-source documentation across the following disciplines:\u003c\/div\u003e\n\u003col style=\"color: #c9a84c; font-size: 13px; margin: 0 0 0 18px; padding: 0; line-height: 2;\"\u003e\n\u003cli\u003eAerodynamic Reports \u0026amp; Design Architecture — Spoiler Roll Control, High Wing Loading, Wingtip Fuel Tanks\u003c\/li\u003e\n\u003cli\u003eEngine Technical Notes — TPE331 Dash-5 \/ Dash-6 \/ Dash-10, Flat-Rated Power, Negative Torque Sensing (NTS)\u003c\/li\u003e\n\u003cli\u003eHandling \u0026amp; Stability Studies — Counterclockwise Propeller Rotation, Asymmetric Thrust Management\u003c\/li\u003e\n\u003cli\u003eFAA Special Certification Reviews (SCR) — Part 23 Compliance \u0026amp; Specialized Training Profiles\u003c\/li\u003e\n\u003cli\u003ePerformance Data Sheets — Short-Body (Solitaire \/ MU-2B-40) \u0026amp; Long-Body (Marquise \/ MU-2B-60)\u003c\/li\u003e\n\u003cli\u003eEngineering \u0026amp; Service Bulletins — A10SW (MR \/ SB prefix) \u0026amp; A2PC (YET \/ numeric SB prefix)\u003c\/li\u003e\n\u003cli\u003eService Letters (SL), Service News (SN) \u0026amp; Structural Engineering Notifications — issued by MHIA\u003c\/li\u003e\n\u003c\/ol\u003e\n\u003chr style=\"border: none; border-top: 1px solid #c9a84c; margin: 14px 0 8px 0;\"\u003e\n\u003cdiv style=\"text-align: center; font-size: 13px; color: #c9a84c;\"\u003eonlineaviationlibrary.com\u003c\/div\u003e\n\u003c\/div\u003e\n\n\u003ch3\u003eMitsubishi MU-2 — Primary-Source Documentation Collection\u003c\/h3\u003e\n\u003cp\u003eThe Mitsubishi MU-2 is an engineered, high-performance twin-turboprop aircraft requiring strict adherence to specialized aerodynamic principles, rigorous factory checklists, and comprehensive maintenance bulletins. Comprehensive documentation across all requested engineering and flight operational disciplines is organized below.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eAerodynamic Reports \u0026amp; Design Architecture\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eSpoiler Roll Control:\u003c\/strong\u003e Eliminates conventional ailerons entirely. Utilizes full-span double-slotted Fowler flaps to maximize lift, allowing the aircraft to achieve exceptionally high wing loading while maintaining short-field performance capabilities.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eHigh Wing Loading:\u003c\/strong\u003e Designed explicitly to deliver a smooth ride through severe turbulence. This configuration demands precise airspeed oversight during terminal flight phases to avoid sudden stalls.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWingtip Fuel Tanks:\u003c\/strong\u003e Houses heavy tip tanks (up to 90 gallons each). These significantly alter the aircraft's roll inertia, requiring pilots to adapt to unique lateral stabilization dynamics during asymmetric fuel configurations.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropulsion System:\u003c\/strong\u003e Powered by two Garrett \/ Honeywell TPE331 turboprop engines. Variants use either the Dash-5, Dash-6, or the highly responsive Dash-10 engines depending on airframe.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFlat-Rated Power Output:\u003c\/strong\u003e The -10 engines output 1,000 shaft horsepower (shp), intentionally flat-rated to 665 shp up to 16,000 feet — sustaining excellent climb profiles through high-density altitudes.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eNegative Torque Sensing (NTS):\u003c\/strong\u003e An essential mechanical system designed to automatically check and reduce propeller drag immediately following an engine failure, preventing severe uncommanded yawing.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eCounterclockwise Propeller Rotation:\u003c\/strong\u003e Propellers turn counterclockwise when viewed from behind. This reverses standard P-factor dynamics, requiring left-rudder inputs during high-power climbs and identifying the right engine as critical.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eAsymmetric Thrust Management:\u003c\/strong\u003e Rapid drag build-up follows engine failure. Safe recovery relies entirely on immediate feathering of the dead engine and maintaining airspeed strictly above single-engine minimum control speed (V\u003csub\u003eMCA\u003c\/sub\u003e).\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eFAA Special Certification Reviews (SCR)\u003c\/h3\u003e\n\u003cp\u003eThorough safety reviews validated that while the MU-2 complies fully with Part 23 certification standards, its rapid response metrics necessitate specialized, highly regimented pilot training profiles. SCR documentation is included in this collection.\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003ePerformance Data Sheets\u003c\/h3\u003e\n\u003ctable style=\"width: 100%; border-collapse: collapse; font-size: 14px;\"\u003e\n\u003cthead\u003e\n\u003ctr style=\"background: #0a1628; color: #c9a84c;\"\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eSpecification\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eShort-Body (Solitaire \/ MU-2B-40)\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eLong-Body (Marquise \/ MU-2B-60)\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eEngines\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eHoneywell TPE331-10\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eHoneywell TPE331-10\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr style=\"background: #f9f9f9;\"\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMax Cruise Speed\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~314 knots\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~300 knots\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~9,920 lbs\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~11,575 lbs\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr style=\"background: #f9f9f9;\"\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eService Ceiling\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e30,000 ft\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e30,000 ft\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMaximum Range\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~1,400 nm\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e~1,100 nm\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eEngineering \u0026amp; Service Bulletins\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eType Certificate Tracking:\u003c\/strong\u003e Two distinct categories — A10SW airframes use manual\/bulletin prefixes \"MR\" or \"SB xxx\/xx-xxx\"; A2PC airframes use prefixes \"YET\" or straight numeric \"SB xxx\".\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eOfficial Document Access:\u003c\/strong\u003e Distributed globally on an annual subscription tier through Veryon (formerly ATP).\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eProduct Support Division:\u003c\/strong\u003e Managed by Mitsubishi Heavy Industries America (MHIA), Dallas, Texas — issuing ongoing Service Letters (SL), Service News (SN), and structural engineering notifications.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003eDocument Manifest — Current Collection\u003c\/h3\u003e\n\u003cp style=\"font-size: 13px; color: #555; margin-bottom: 12px;\"\u003eOnline Aviation Library is a \u003cstrong\u003eliving archive\u003c\/strong\u003e, not a closed catalog. This collection reflects documents available at the time of your purchase. As additional primary-source documents are located, verified, and processed, they are added to your collection at no extra charge — automatically, as part of your free lifetime update entitlement. OAL is a data publisher serving the aviation community. We are not a regulatory authority, a government institution, or an official distributor. Our mission is to make rare, primary-source aviation documentation accessible to researchers, historians, restorers, and enthusiasts worldwide — inclusively, not exclusively.\u003c\/p\u003e\n\u003ctable style=\"width: 100%; border-collapse: collapse; font-size: 13px;\"\u003e\n\u003cthead\u003e\n\u003ctr style=\"background: #0a1628; color: #c9a84c;\"\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003e#\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eDocument Title\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eReference No.\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eDate\u003c\/th\u003e\n\u003cth style=\"padding: 8px 12px; text-align: left; border: 1px solid #c9a84c;\"\u003eApplicability\u003c\/th\u003e\n\u003c\/tr\u003e\n\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e1\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2 Pilots Operating Manual\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eYET 74123\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e1 September 1974\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2B-36 (Model No. MU-2L)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr style=\"background: #f9f9f9;\"\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e2\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2B-36 Maintenance Manual\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eYET 74125\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eOriginal Issue 1 May 1974\u003cbr\u003eRevision 1 December 1991\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eS\/N 501, 655–660, 662–696\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e3\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2B-60 Illustrated Parts Catalog\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMR-0342-1\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eOriginal Issue 1 September 1978\u003cbr\u003eReissue 1 February 1984\u003cbr\u003eRevision 1 June 1993\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eS\/N 700SA, 731SA–799SA, 1501SA and subsequent\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr style=\"background: #f9f9f9;\"\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e4\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2 Structural Repair Manual\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e—\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eOriginal Issue 1 January 1972\u003cbr\u003eReissue 1 January 1997\u003cbr\u003eRevision 25 January 2002\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eAll MU-2 variants\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e5\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2B-60 Pilot Checklist\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eYET 06220A\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003e—\u003c\/td\u003e\n\u003ctd style=\"padding: 8px 12px; border: 1px solid #ccc;\"\u003eMU-2B-60 (Marquise)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\n\u003cp style=\"font-size: 12px; color: #888; margin-top: 8px;\"\u003e\u003cem\u003eThis manifest reflects the current release. Additional documents will be added as the collection expands — at no additional cost to existing customers.\u003c\/em\u003e\u003c\/p\u003e\n\n\u003chr\u003e\n\n\u003cblockquote style=\"border-left: 4px solid #b22222; padding: 16px 20px; background: #fff5f5; margin: 28px 0;\"\u003e\n\u003cp style=\"margin: 0 0 10px 0;\"\u003e\u003cstrong\u003e⚠️ Regulatory Notice\u003c\/strong\u003e\u003c\/p\u003e\n\u003cp style=\"margin: 0 0 10px 0;\"\u003eUnder 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. \u003cu\u003eThis archival collection does not satisfy that requirement.\u003c\/u\u003e These documents are provided exclusively for historical reference, flight simulation, museum restoration, and educational use. \u003cu\u003eThey do not constitute current airworthiness documentation.\u003c\/u\u003e For any maintenance, overhaul, or operational work on airworthy aircraft, always consult the current Type Certificate holder (Mitsubishi Heavy Industries America \/ MHIA) and the applicable regulatory authority.\u003c\/p\u003e\n\u003c\/blockquote\u003e\n\n\u003chr\u003e\n\n\u003ch3\u003ePurpose of This Collection\u003c\/h3\u003e\n\u003cp\u003eThis collection is designed for:\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAviation historians and researchers\u003c\/strong\u003e — primary-source documentation spanning the full lifecycle of the MU-2 family, from early production variants through FAA Special Certification Review and into current operational service.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMuseum curators and warbird restorers\u003c\/strong\u003e — original factory-issued aerodynamic, maintenance, and illustrated parts publications for reference during static display or non-airworthy restoration projects.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFlight simulation enthusiasts\u003c\/strong\u003e — authentic technical depth for simulator builders and enthusiasts seeking period-accurate performance and systems data.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEducational institutions\u003c\/strong\u003e — primary-source material for aerospace engineering studies, turboprop propulsion technology courses, and FAA certification history.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCollectors of aviation primary-source documentation\u003c\/strong\u003e — many of these publications are exceptionally rare and no longer available through official channels.\u003c\/li\u003e\n\u003c\/ul\u003e\n\n\u003chr\u003e\n\n\u003cdiv style=\"background: #f9f6ee; border: 1px solid #c9a84c; padding: 20px 24px; margin: 28px 0; font-family: Georgia, serif;\"\u003e\n\u003cp style=\"margin: 0 0 10px 0; font-size: 14px; color: #0a1628;\"\u003e\u003cstrong\u003eAbout Online Aviation Library\u003c\/strong\u003e\u003c\/p\u003e\n\u003cp style=\"margin: 0; font-size: 13px; color: #333; line-height: 1.8;\"\u003eOnline Aviation Library is a data publisher — not a regulatory authority, government institution, or official distributor. Our mission is to collect, structure, preserve, and publish surviving original aviation documentation. We operate on three principles: \u003cem\u003ePreservation before reconstruction. Authenticity before completeness. Original evidence before modern interpretation.\u003c\/em\u003e We don’t teach; we tell stories.\u003c\/p\u003e\n\u003c\/div\u003e\n\n\u003chr\u003e\n\n\u003cp style=\"font-size: 13px; color: #444;\"\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.\u003c\/p\u003e\n\u003cp style=\"font-size: 13px; color: #444;\"\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":53734856393051,"sku":null,"price":69.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/mu-2-banner-1.png?v=1786171329"},{"product_id":"mitsubishi-j2m3-raiden-operating-instructions-manual","title":"Mitsubishi J2M3 Raiden — Operating Instructions Manual","description":"\u003ch2\u003eMitsubishi J2M3 Raiden — Operating Instructions Manual\u003c\/h2\u003e\u003ch3\u003e三菱 雷電 取扱説明書\u003c\/h3\u003e\u003cp\u003eThe Mitsubishi J2M Raiden (Allied reporting name \u003cem\u003e\"Jack\"\u003c\/em\u003e) represents a decisive shift in wartime Japanese engineering philosophy — a purpose-built bomber interceptor that discarded the agility doctrine of the A6M Zero in favour of raw speed, climb rate, and energy retention. This archival edition presents the original Operating Instructions Manual for the J2M3 Model 21, the primary production variant, drawn from wartime design histories and post-war technical evaluations.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003eAerodynamic Design \u0026amp; Airframe Engineering\u003c\/h3\u003e\u003cp\u003eChief Designer \u003cstrong\u003eJiro Horikoshi\u003c\/strong\u003e engineered the Raiden around a single priority: intercept and destroy high-altitude bombers before they reached their targets.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eLaminar-Flow Airfoil:\u003c\/strong\u003e The J2M incorporated an advanced symmetrical wing profile inspired by the LB24 airfoil. Maximum thickness was pushed back to approximately 50% of the chord, minimising high-speed parasite drag and maximising dive acceleration.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTapered Fuselage \u0026amp; Bullet Nose:\u003c\/strong\u003e To reduce the frontal drag penalty of a large-displacement radial engine, Horikoshi specified a highly tapered cowling with the engine seated deep within the fuselage — creating a sharp, bullet-like nose entry. The trade-off was a severely restricted forward visibility for the pilot.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eEngine Technical Notes — Mitsubishi MK4 \"Kasei\" Radial\u003c\/h3\u003e\u003cp\u003eThe entire airframe was engineered around the heavy 14-cylinder Mitsubishi MK4 \u003cem\u003eKasei\u003c\/em\u003e radial powerplant.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eExtension Shaft \u0026amp; Forced-Draught Cooling Fan:\u003c\/strong\u003e With the engine seated deep in the fuselage and disconnected from direct ram-air flow, engineers fitted an engine-driven cooling fan directly behind the cowl inlet to prevent overheating — a technically demanding solution unique to the Raiden.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKasei 23a Power Ratings:\u003c\/strong\u003e 1,800 hp at takeoff at +450 mmHg manifold pressure \/ 2,600 RPM.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWater-Methanol Injection:\u003c\/strong\u003e The Kasei 23a was the first operational Japanese powerplant to feature a water-methanol injection system, enabling temporary combat power bursts for emergency climbs or escape manoeuvres.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eJ2M5 \/ Kasei 26a:\u003c\/strong\u003e Later variants introduced a redesigned supercharger housing with optimised ram-air passages to sustain power at high altitude.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eHandling \u0026amp; Stability — Wartime Flight Evaluations\u003c\/h3\u003e\u003cp\u003eWartime flight evaluations documented a demanding cockpit environment that contrasted sharply with the forgiving A6M Zero.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eHigh Wing Loading:\u003c\/strong\u003e Heavy armour, self-sealing fuel tanks, and the massive powerplant produced elevated wing loading. Combat flaps were essential to maintain lift during high-speed defensive manoeuvres.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eVibration \u0026amp; Shaft Harmonics:\u003c\/strong\u003e Early handling logs record severe engine\/propeller shaft harmonics requiring extensive balancing of the extension shaft damping mechanisms to prevent airframe fatigue.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eStall Characteristics:\u003c\/strong\u003e The laminar-flow wing produced abrupt, unforgiving stall entries with minimal pre-stall buffeting — demanding constant pilot vigilance during high-G tracking states.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eEngineering Bulletins \u0026amp; Structural Defects\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eVision Distortions — Windscreen Redesign:\u003c\/strong\u003e The initial J2M1 low-profile curved windscreen produced severe optical distortions in flight test. An emergency redesign introduced a steeply raked flat-panel windscreen on all production models.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFatal Landing Gear Defect:\u003c\/strong\u003e Early factory notices identified a critical mechanical fault: the tail wheel strut linkage could bind under dive loads, jamming the main elevator control runs. Several fatal crashes were attributed to this defect before the linkage was shielded on production aircraft.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eDocument Manifest — Total Manuals: 2\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eVariant\u003c\/th\u003e\n\u003cth\u003eDocument Title\u003c\/th\u003e\n\u003cth\u003eDescription\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eJ2M3\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eJ2M3 Operating and Maintenance\u003c\/td\u003e\n\u003ctd\u003eMitsubishi J2M3 Raiden Operating Instructions Manual, 三菱 雷電 取扱説明書 (Japanese Language)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eNo Variant\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eJ2M Slides, Photos and Brochures\u003c\/td\u003e\n\u003ctd\u003eJ2M Photographic Collection (English language)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003ePerformance Data Sheet — J2M3 Model 21\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e371 mph (597 km\/h) at 19,360 ft (5,900 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e219 mph (352 km\/h) at 9,840 ft (3,000 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e38,385 ft (11,770 m)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e5,423 lbs (2,460 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd\u003e8,695 lbs (3,945 kg)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eStandard Armament\u003c\/td\u003e\n\u003ctd\u003e4 × 20 mm Type 99 wing cannons\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates – Please review our Legal Notice and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53776342974811,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/j2m-raiden-allied-evaluation-banner.png?v=1786636940"},{"product_id":"mitsubishi-ki-15-karigane-operating-instructions-manual","title":"Mitsubishi Ki-15 Karigane — Operating Instructions Manual \u0026 Photo Collection","description":"\u003ch2\u003eMitsubishi Ki-15 Karigane — Operating Instructions Manual \u0026amp; Photo Collection\u003c\/h2\u003e\u003ch3\u003e三菱 九七式司令部偵察機 「雁」\u003c\/h3\u003e\u003cp\u003eThe Mitsubishi Ki-15 (Allied codename \u003cem\u003e\"Babs\"\u003c\/em\u003e, military designation Army Type 97 Command Reconnaissance Plane) was an all-metal, low-wing cantilever monoplane that, upon its introduction in 1937, was briefly the fastest production aircraft in the world. Engineered to outfly and outclimb contemporary interceptors, the Ki-15 represented a decisive leap in Japanese aeronautical engineering. This archival collection presents the original Operating Instructions Manual for the Ki-15-II Type 97 together with the Ki-15 Photographic Collection.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003eAerodynamic Profile \u0026amp; Configuration\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eDesign Precedents:\u003c\/strong\u003e All-metal stressed-skin construction drawing on engineering principles similar to the Heinkel He 70 and Northrop Alpha.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Geometry:\u003c\/strong\u003e Rectangular centre section mated to two trapezoidal outer wing panels with a distinct positive dihedral for lateral stability.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDrag Reduction:\u003c\/strong\u003e A highly streamlined fuselage narrowing linearly toward the tail, complemented by large aerodynamically clean wheel spats — balancing structural simplicity against drag constraints.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003eEngine Technical Notes \u0026amp; Variant Data\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eVariant\u003c\/th\u003e\n\u003cth\u003eEngine Model\u003c\/th\u003e\n\u003cth\u003eRated Power\u003c\/th\u003e\n\u003cth\u003eTechnical Note\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eKi-15-I\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eNakajima Ha-8 Radial\u003c\/td\u003e\n\u003ctd\u003e750 hp (560 kW) @ 4,000 m\u003c\/td\u003e\n\u003ctd\u003eLarge frontal area; limited forward visibility during taxi and takeoff.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eKi-15-II\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eMitsubishi Ha-26-I Radial\u003c\/td\u003e\n\u003ctd\u003e900 hp (671 kW)\u003c\/td\u003e\n\u003ctd\u003eSmaller engine diameter directly reduced aerodynamic drag.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eC5M2 (Navy)\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eNakajima Sakae 12 Radial\u003c\/td\u003e\n\u003ctd\u003e949 hp (708 kW)\u003c\/td\u003e\n\u003ctd\u003eAdapted for maritime reconnaissance profiles.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003eHandling \u0026amp; Stability Studies\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eLongitudinal \u0026amp; Lateral Stability:\u003c\/strong\u003e The extended full-depth glass canopy smoothed airflow across the upper fuselage, providing exceptional lateral stability at low airspeeds.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eFlight Controls:\u003c\/strong\u003e Large-chord ailerons offered highly effective roll control down to near-stall velocities. High side-surface area facilitated advanced manoeuvres such as slow rolls with minimal top-rudder deflection.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eHandling Trade-offs:\u003c\/strong\u003e Initial flight testing noted an acute loss of airspeed during aggressive high-G turns. Forward field-of-view past the cowl was significantly obscured on the ground in the Ki-15-I configuration.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003ePerformance Data Sheet\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e481 km\/h (299 mph) at 4,050 m\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd\u003e320 km\/h (200 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e11,400 m (37,400 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eOperational Range\u003c\/td\u003e\n\u003ctd\u003e2,400 km (1,500 miles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWeight Profile\u003c\/td\u003e\n\u003ctd\u003eHigh structural efficiency — footprint of a P-47 Thunderbolt at roughly one-third of its gross weight\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003eDocument Manifest — Total Manuals: 2\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eVariant\u003c\/th\u003e\n\u003cth\u003eDocument Title\u003c\/th\u003e\n\u003cth\u003eDescription\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eKi-15-II\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eKi-15-II Operating and Maintenance\u003c\/td\u003e\n\u003ctd\u003eKi-15-II Type 97 Aircraft Operating Instructions Manual, 三菱 九七式司令部偵察機 二型 説明書 (Japanese Language)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e\u003cstrong\u003eNo Variant\u003c\/strong\u003e\u003c\/td\u003e\n\u003ctd\u003eKi-15 Slides, Photos and Brochures\u003c\/td\u003e\n\u003ctd\u003eKi-15 Photographic Collection (English language)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates – Please review our Legal Notice and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53776430793051,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-15-karigane-desert-sepia-banner.png?v=1786638706"},{"product_id":"mitsubishi-j8m-shusui-japans-rocket-interceptor-primary-source-documentation-collection","title":"Mitsubishi J8M Shūsui — Japan's Rocket Interceptor: Primary-Source Documentation Collection","description":"\u003ch2\u003eMitsubishi J8M Shūsui — Japan's Rocket Interceptor\u003c\/h2\u003e\u003cp\u003e\u003cem\u003eJapanese: \"Autumn Water\" \/ \"Sharp Sword\"\u003c\/em\u003e\u003c\/p\u003e\u003cp\u003eThe Mitsubishi J8M Shūsui was an ambitious World War II rocket-powered interceptor built by Mitsubishi Heavy Industries as a joint project for the Imperial Japanese Navy (J8M) and Army (Ki-200). Because the submarine carrying a complete German Messerschmitt Me 163 Komet and its blueprint package was sunk by Allied forces, Japanese engineers were forced to reverse-engineer the entire aircraft from a single instruction\/flight manual flown in separately by Commander Eiichi Iwaya.\u003c\/p\u003e\u003cp\u003eConsequently, formal Western-style Engineering Bulletins are virtually non-existent. However, Allied intelligence, modern archival recovery, and technical analysis have reconstructed the core aerodynamic, engine, handling, and performance documentation for the aircraft.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003e📋 Performance Data Sheet (J8M1 \/ Ki-200)\u003c\/h3\u003e\u003cp\u003eThe Shūsui was optimized strictly as a point-defense interceptor targeting high-altitude B-29 Superfortress bombers.\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eSpecification Data\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eCrew\u003c\/td\u003e\n\u003ctd\u003e1 Pilot\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eLength\u003c\/td\u003e\n\u003ctd\u003e6.05 m (19 ft 10 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWingspan\u003c\/td\u003e\n\u003ctd\u003e9.50 m (31 ft 2 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eHeight\u003c\/td\u003e\n\u003ctd\u003e2.70 m (8 ft 10 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd\u003e1,505 kg (3,318 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eLoaded Weight\u003c\/td\u003e\n\u003ctd\u003e3,885 kg (8,565 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePowerplant\u003c\/td\u003e\n\u003ctd\u003e1 × Tokuro-2 (KR10) liquid-propellant rocket engine\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Thrust\u003c\/td\u003e\n\u003ctd\u003e14.7 kN (3,300 lbf \/ 1,500 kgf)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e900 km\/h (559 mph) at 10,000 m (32,808 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eClimb Rate\u003c\/td\u003e\n\u003ctd\u003e10,000 m (32,808 ft) in 3 minutes 30 seconds\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eOperational Ceiling\u003c\/td\u003e\n\u003ctd\u003e12,000 m (39,370 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eRocket Burn Endurance\u003c\/td\u003e\n\u003ctd\u003e2 minutes 30 seconds (5 min 30 sec total glide profiles)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eArmament (Navy J8M1)\u003c\/td\u003e\n\u003ctd\u003e2 × 30 mm Type 5 cannons\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eArmament (Army Ki-200)\u003c\/td\u003e\n\u003ctd\u003e2 × 30 mm Ho-105\/Ho-155 cannons\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003e📐 Aerodynamic Reports \u0026amp; Design Constraints\u003c\/h3\u003e\u003cp\u003eThe J8M shared the tailless, swept-wing design of the Me 163, relying on blended elevons for simultaneous pitch and roll control.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eAerodynamic Sufficiency:\u003c\/strong\u003e Lacking wind tunnel data from Germany, the 1st Naval Air Technical Arsenal built the MXY8 Akigusa wooden training glider. Flight logs from December 1944 proved the tailless platform was highly efficient at gliding speeds, showing exceptionally low drag coefficients.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWeight Ballast Adaptations:\u003c\/strong\u003e The heavier Ku-13 Shusui training glider was deployed with integrated water ballast tanks to record boundary-layer performance, stall speed parameters, and high-speed glide dynamics prior to powered integration.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Redesign Profile:\u003c\/strong\u003e The later-planned J8M3 \/ Ki-202 variant featured prolonged aerodynamic revisions incorporating an expanded wingspan to optimize wing loading and lift coefficients during thin-air, high-altitude interceptions.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e🚀 Engine Technical Notes: Tokuro-2 (KR10)\u003c\/h3\u003e\u003cp\u003eThe powerplant was a direct chemical replication of the Walter HWK 109-509 rocket motor.\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePropellant Composition:\u003c\/strong\u003e Ko-Liquid (O-Stoff) — 80% Hydrogen Peroxide oxidizer; Otsu-Liquid (C-Stoff) — Hydrazine Hydrate and Methanol fuel.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eThrust Deficit:\u003c\/strong\u003e Japanese metallurgy and chemical infrastructure could not perfectly reproduce German thermal tolerances. The Tokuro-2 produced 3,300 lbf — short of the German original's 3,800 lbf.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eThe Fatal Fuel Architecture:\u003c\/strong\u003e During its singular powered test flight on 7 July 1945, flown by Captain Toyohiko Inuzuka, a steep pitch-up shifted Ko-Liquid away from the tank outlet, causing catastrophic fuel starvation, line cavitation, and immediate engine flameout at 1,300 feet, destroying the prototype.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e🕹️ Handling \u0026amp; Stability Studies\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eHigh Wing Loading:\u003c\/strong\u003e The massive propellant weight made the aircraft handle like a heavy projectile during ascent, requiring precise, minimal control inputs to avoid high-G stalls.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLow-Speed Clean Gliding:\u003c\/strong\u003e Once the rocket motor was depleted, the J8M became an unpowered glider. MXY8 glider flights showed crisp, stable handling qualities without engine torque — though landing was highly hazardous.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLanding Gear Instability:\u003c\/strong\u003e True to its German inspiration, the J8M dropped its dual-wheel takeoff dolly after leaving the runway and landed on a retractable underbelly skid. Directional control during landing was highly volatile, presenting severe risk of ground-looping or tipping.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e📂 Historical Bulletins \u0026amp; Surviving Documents\u003c\/h3\u003e\u003cp\u003eBecause many official records were intentionally incinerated by Japanese forces just prior to the August 1945 surrender, true technical documentation exists primarily across two main streams:\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eU.S. Tactical Air Intelligence Unit (TAIU) Reports:\u003c\/strong\u003e Captured airframes — including the prototype now located at the Planes of Fame Air Museum in Chino, California — were extensively measured, weighed, and documented by Allied teams in late 1945. These TAIU field reports represent the most structured surviving Western-format technical record of the Shūsui's physical configuration and performance envelope.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eThe Cave Recovery Archives:\u003c\/strong\u003e In the 1960s, a damaged, incomplete J8M1 fuselage was discovered hidden inside a cave in Japan. Mitsubishi Heavy Industries utilized recovered wartime internal logs alongside this fuselage to conduct an exhaustive historical structural restoration project. This restored aircraft is currently housed within the Mitsubishi Heavy Industries Museum at the Komaki Plant in Nagoya — a rare surviving physical witness to Japan's most ambitious wartime aerospace programme.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e📚 Document Manifest\u003c\/h3\u003e\u003cp\u003eThis collection brings together three primary archival volumes comprising \u003cstrong\u003e49 document pages\u003c\/strong\u003e of surviving primary-source technical and operational material, recovered and preserved by Online Aviation Library.\u003c\/p\u003e\u003cp\u003e\u003cem\u003eArchival source: National Diet Library of Japan (国立国会図書館), digital reproduction 2024\/5\/11. Reproduced under archival access provisions; copyright status per NDL notice.\u003c\/em\u003e\u003c\/p\u003e\u003ch4\u003eVolume 1 — Technical Drawings Set (39 sheets)\u003c\/h4\u003e\u003cp\u003e\u003cem\u003eMitsubishi J8M Shūsui — 三菱 秋水 — 技術図面 | Mitsubishi Heavy Industries \/ wartime production archive | Original language: Japanese\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eSheet\u003c\/th\u003e\n\u003cth\u003eNDL Page\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003e01\u003c\/td\u003e\n\u003ctd\u003eCover\u003c\/td\u003e\n\u003ctd\u003eCollection title page and document register\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e02\u003c\/td\u003e\n\u003ctd\u003ep. 15\u003c\/td\u003e\n\u003ctd\u003eElectrical and hydraulic system routing diagram — fuselage internal layout, Ko-liquid \/ Otsu-liquid line routing, valve positions, cockpit instrument feed lines, numbered callout legend\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e03\u003c\/td\u003e\n\u003ctd\u003ep. 18\u003c\/td\u003e\n\u003ctd\u003eFuselage spar and frame structural assembly — main longitudinal spar, frame station spacing, cockpit tub structure, engine bay bulkhead, landing skid attachment points\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e04\u003c\/td\u003e\n\u003ctd\u003ep. 19\u003c\/td\u003e\n\u003ctd\u003eWing rib station plan — full-span rib numbering, spar cap cross-sections, rib pitch dimensions in mm, elevon hinge bracket fittings\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e05\u003c\/td\u003e\n\u003ctd\u003ep. 20\u003c\/td\u003e\n\u003ctd\u003eWing planform — top-down plan view, swept leading edge geometry, rib station lines, fuel bay outline, cannon bay apertures, boundary-layer fence provisions\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e06\u003c\/td\u003e\n\u003ctd\u003ep. 21\u003c\/td\u003e\n\u003ctd\u003eWing surface structural detail — upper and lower skin panel layout, stringer positions, rib spacing dimensions, skin attachment flange detail\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e07\u003c\/td\u003e\n\u003ctd\u003ep. 22\u003c\/td\u003e\n\u003ctd\u003eFuselage cross-section frames — numbered frame stations, I-beam and channel-section profiles, skin attachment flanges, internal equipment bay clearances\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e08\u003c\/td\u003e\n\u003ctd\u003ep. 23\u003c\/td\u003e\n\u003ctd\u003eElevon hinge and control surface detail — hinge bracket geometry, actuator attachment points, elevon chord and span dimensions, trailing edge profile cross-sections\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e09\u003c\/td\u003e\n\u003ctd\u003ep. 24\u003c\/td\u003e\n\u003ctd\u003ePropellant tank arrangement — Ko-liquid (forward) and Otsu-liquid (aft) tank positions, fill\/drain connections, pressurization lines, tank structural support frames\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e10\u003c\/td\u003e\n\u003ctd\u003ep. 25\u003c\/td\u003e\n\u003ctd\u003eElectrical and hydraulic system routing detail — cockpit instrument panel feed lines, valve sequencing, numbered component legend\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e11\u003c\/td\u003e\n\u003ctd\u003ep. 26\u003c\/td\u003e\n\u003ctd\u003eTakeoff dolly (離陸用投下式ドリー) assembly — front elevation, side elevation, plan view; cross-section cuts A-A’, B-B’, C-C’; wheel spec 700×200 mm; axle and release mechanism\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e12\u003c\/td\u003e\n\u003ctd\u003ep. 27\u003c\/td\u003e\n\u003ctd\u003eTokuro-2 (KR10) rocket engine four-view drawing — front, rear, side, top projections; total length 2,486.5 mm, width 980 mm; turbopump assembly, propellant control valves, exhaust nozzle cross-section\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e13\u003c\/td\u003e\n\u003ctd\u003ep. 29\u003c\/td\u003e\n\u003ctd\u003eWing leading edge arc geometry — full-scale large-radius arc layout, rib intercept points, leading edge skin attachment, boundary-layer fence cross-section; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e14\u003c\/td\u003e\n\u003ctd\u003ep. 30\u003c\/td\u003e\n\u003ctd\u003eFuselage frame station cross-sections — numbered stations, I-beam and channel profiles, skin attachment flanges, equipment bay clearances; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e15\u003c\/td\u003e\n\u003ctd\u003ep. 31\u003c\/td\u003e\n\u003ctd\u003eWing root attachment fitting — root rib cross-section, wing-to-fuselage bolted joint, spar pin detail, shear web; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e16\u003c\/td\u003e\n\u003ctd\u003ep. 32\u003c\/td\u003e\n\u003ctd\u003eFuselage spar longitudinal assembly — full-length spar elevation, numbered frame intercepts, cross-section cuts A-A’ and B-B’, material specification parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e17\u003c\/td\u003e\n\u003ctd\u003ep. 33\u003c\/td\u003e\n\u003ctd\u003eLanding skid assembly — plan view and side elevation; skid shoe geometry, pivot bracket, retraction linkage, shock-absorber attachment; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e18\u003c\/td\u003e\n\u003ctd\u003ep. 34\u003c\/td\u003e\n\u003ctd\u003eWing leading edge full-scale arc layout — swept geometry construction lines, rib intercept points, skin attachment, boundary-layer fence cross-section; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e19\u003c\/td\u003e\n\u003ctd\u003ep. 35\u003c\/td\u003e\n\u003ctd\u003eWing root and fuselage attachment frames — root rib cross-section and wing-to-fuselage attachment fitting; bolted joint, spar pin, shear web callouts; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e20\u003c\/td\u003e\n\u003ctd\u003ep. 36\u003c\/td\u003e\n\u003ctd\u003eCockpit and forward fuselage internal arrangement — instrument panel layout, seat and harness attachment, rudder pedal assembly, control column geometry; 30+ numbered equipment callouts; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e21\u003c\/td\u003e\n\u003ctd\u003ep. 41\u003c\/td\u003e\n\u003ctd\u003eFuselage structural component detail — numbered structural fittings (items 1–37+), curved spar arc geometry, bolted joint assemblies, I-beam cross-sections, oval-aperture frame cutouts; dense parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e22\u003c\/td\u003e\n\u003ctd\u003ep. 42\u003c\/td\u003e\n\u003ctd\u003eFuselage forward section and cockpit tub — side elevation, cockpit floor structure, instrument bay bulkhead, cross-section cuts C-C’ and D-D’; large circular engine bay aperture; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e23\u003c\/td\u003e\n\u003ctd\u003ep. 43\u003c\/td\u003e\n\u003ctd\u003eWing leading edge full-scale arc construction — large-radius swept arc, leading edge skin attachment fittings, cannon bay aperture detail; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e24\u003c\/td\u003e\n\u003ctd\u003ep. 44\u003c\/td\u003e\n\u003ctd\u003eWing leading edge arc and spar root detail — large-radius arc, cross-section cut A-A’ of spar root fitting; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e25\u003c\/td\u003e\n\u003ctd\u003ep. 45\u003c\/td\u003e\n\u003ctd\u003eWing spar and rib assembly — I-beam spar cross-sections, full-span rib arc plan with numbered rib stations, rib-to-spar attachment fittings, cross-section cuts A-A’ and D-D’; dense parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e26\u003c\/td\u003e\n\u003ctd\u003ep. 46\u003c\/td\u003e\n\u003ctd\u003eWing rib arc and attachment fittings — full-span rib arc plan, landing skid pivot bracket and elevon hinge fittings; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e27\u003c\/td\u003e\n\u003ctd\u003ep. 47\u003c\/td\u003e\n\u003ctd\u003eFuselage internal arrangement — top-down plan view with numbered equipment callouts and propellant system routing; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e28\u003c\/td\u003e\n\u003ctd\u003ep. 48\u003c\/td\u003e\n\u003ctd\u003eFuselage frame and bulkhead cross-sections — numbered stations, I-beam profiles, large circular engine bay aperture; cross-section cuts B-B’, C-C’, F-F’; K甲面 and F-F面 panel views; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e29\u003c\/td\u003e\n\u003ctd\u003ep. 49\u003c\/td\u003e\n\u003ctd\u003eWing spar and rib assembly (detail) — I-beam spar cross-sections, full-span rib arc plan, rib-to-spar attachment fittings; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e30\u003c\/td\u003e\n\u003ctd\u003ep. 50\u003c\/td\u003e\n\u003ctd\u003eWing rib arc and spar root detail — large-radius arc construction, spar root fitting cross-section A-A’; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e31\u003c\/td\u003e\n\u003ctd\u003ep. 51\u003c\/td\u003e\n\u003ctd\u003eWing leading edge arc construction — large-radius swept arc, rib intercept points, cannon bay aperture detail, skin attachment fittings; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e32\u003c\/td\u003e\n\u003ctd\u003ep. 52\u003c\/td\u003e\n\u003ctd\u003eFuselage forward section and cockpit tub (detail) — side elevation, cockpit floor structure, instrument bay bulkhead, engine bay aperture; numbered structural callouts; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e33\u003c\/td\u003e\n\u003ctd\u003ep. 53\u003c\/td\u003e\n\u003ctd\u003eFuselage structural component detail — numbered structural fittings, curved spar arc geometry, bolted joint assemblies, I-beam cross-sections; dense parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e34\u003c\/td\u003e\n\u003ctd\u003ep. 57\u003c\/td\u003e\n\u003ctd\u003eKo-liquid and Otsu-liquid propellant tank plan views — two elongated tank outlines with internal baffle positions, fill\/drain port callouts, pressurization line attachment points; parts table upper right\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e35\u003c\/td\u003e\n\u003ctd\u003ep. 58\u003c\/td\u003e\n\u003ctd\u003eFuselage skin panel layout — top-down plan view showing panel boundaries, stringer lines, frame intercept points, access panel cutouts, and cannon bay apertures; dense numbered callouts; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e36\u003c\/td\u003e\n\u003ctd\u003ep. 59\u003c\/td\u003e\n\u003ctd\u003eFull wing plan with cockpit pod — complete wing planform showing cockpit fairing outline (upper left), full-span rib station lines with numbered callouts, spar arc, elevon hinge line, and skin panel boundaries; parts table upper right\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e37\u003c\/td\u003e\n\u003ctd\u003ep. 60\u003c\/td\u003e\n\u003ctd\u003eDense fuselage skin panel and frame layout — top-down plan view of forward and aft fuselage sections; skin panel boundaries, frame intercepts, cockpit cutout, engine bay aperture, 40+ numbered callouts; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e38\u003c\/td\u003e\n\u003ctd\u003ep. 61\u003c\/td\u003e\n\u003ctd\u003eFuselage internal bay arrangement — top-down plan view showing cockpit bay, Ko-liquid tank bay, Otsu-liquid tank bay, engine bay, and landing skid bay with numbered structural callouts and oval engine aperture; parts table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e39\u003c\/td\u003e\n\u003ctd\u003ep. 67\u003c\/td\u003e\n\u003ctd\u003ePropellant tank plan and elevation — Ko-liquid tank top-down plan (upper left, showing internal baffle grid and fill port), two elongated tank side elevations (centre, showing rounded-end profiles, internal baffle positions, and numbered attachment points), and fuselage station grid (lower right); parts table upper right\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e40\u003c\/td\u003e\n\u003ctd\u003ep. 68\u003c\/td\u003e\n\u003ctd\u003eFull fuselage lofting and lines drawing — large-scale side elevation showing complete fuselage profile with cockpit canopy arc (upper left dome), swept wing root leading edge, numbered frame station lines (circled stations 1–12), waterline grid, and buttock line grid; cross-section table (upper right) listing frame station offsets; the primary lofting master drawing for the J8M1 fuselage\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e41\u003c\/td\u003e\n\u003ctd\u003ep. 69\u003c\/td\u003e\n\u003ctd\u003eComplete wing plan with cockpit pod and rib stations — large-scale top-down wing planform showing cockpit fairing (upper left), full-span rib station lines with circled station numbers, main spar arc, front spar arc, elevon hinge line, cannon bay apertures, and skin panel boundaries; dense numbered callouts; parts table upper right\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e42\u003c\/td\u003e\n\u003ctd\u003ep. 70\u003c\/td\u003e\n\u003ctd\u003eDense fuselage skin panel and structural layout — large-scale top-down plan of complete fuselage showing skin panel grid, frame intercept lines, cockpit cutout, engine bay aperture (oval), landing skid bay, cannon bay apertures, and 50+ numbered structural callouts; parts table upper right; the most detailed surviving fuselage skin layout drawing\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e43\u003c\/td\u003e\n\u003ctd\u003ep. 71\u003c\/td\u003e\n\u003ctd\u003eFuselage internal bay and structural arrangement — large-scale top-down plan showing cockpit bay (upper left with instrument panel outline), Ko-liquid tank bay, Otsu-liquid tank bay, engine bay (oval aperture, centre right), landing skid bay, and aft fuselage structure; numbered structural callouts throughout; parts table upper right\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch4\u003eVolume 2 — Photo Collections\u003c\/h4\u003e\u003cp\u003e\u003cem\u003eAllied TAIU field documentation \u0026amp; post-war recovery records | English \/ Japanese\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eItem\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\u003ctr\u003e\n\u003ctd\u003ePhotographic Archive\u003c\/td\u003e\n\u003ctd\u003eWartime and post-war photographic record of the J8M1 airframe, ground handling, and Allied TAIU inspection. Includes the 7 July 1945 pre-flight photograph at Yokosuka Naval Air Base — the only known image of the aircraft immediately before its fatal powered test flight.\u003c\/td\u003e\n\u003c\/tr\u003e\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch4\u003eVolume 3 — Primary Source Document (10 pages)\u003c\/h4\u003e\u003cp\u003e\u003cem\u003e三菱 局地戦闘機『秋水』[J8M] — 昭和20年 (Shōwa 20 \/ 1945) | Imperial Japanese Navy \/ Mitsubishi Heavy Industries\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eDocument Page\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003ep. 267\u003c\/td\u003e\n\u003ctd\u003eNarrative account of the J8M programme — reverse-engineering from the Me 163 manual, accelerated production timeline, and the fatal first flight. Original Japanese caption identifying the 7 July 1945 photograph.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ep. 268\u003c\/td\u003e\n\u003ctd\u003e1\/48 precision four-view drawing (J8M1 \/ Ki-200) with full Japanese callout labels and 《Shūsui》 data block: dimensions, weights, engine, armament.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ep. 275\u003c\/td\u003e\n\u003ctd\u003eTokuro-2 (KR10) rocket engine technical specification table — dimensions, thrust range, specific impulse, turbopump RPM, starter motor spec, propellant composition, mixing ratio, and fuel tank system diagram with numbered line legend.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ep. 276\u003c\/td\u003e\n\u003ctd\u003eTakeoff dolly assembly drawing — front elevation, side elevation, and plan view with cross-section cuts A-A’, B-B’, C-C’; dolly wheel spec (700×200 mm); structural commentary on directional instability during landing.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ep. 277\u003c\/td\u003e\n\u003ctd\u003eTokuro-2 (KR10) rocket engine four-view engineering drawing — front, rear, side, and top projections with full dimensional data (total length 2,486.5 mm, width 980 mm), turbopump assembly detail, propellant control valve layout, C-liquid injection system, and exhaust nozzle cross-section.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003epp. 269–274, 278–279\u003c\/td\u003e\n\u003ctd\u003eAdditional operational and structural notes, parts lists, and supplementary technical commentary recovered from the wartime archive.\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003cp\u003e\u003cem\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.\u003c\/em\u003e\u003c\/p\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates – Please review our Legal Notice and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53776614064475,"sku":null,"price":49.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/j8m-sh-sui-gold-in-flight-banner.png?v=1786645308"},{"product_id":"mitsubishi-ki-2-louise-twin-engine-light-bomber-primary-source-documentation-collection","title":"Mitsubishi Ki-2 \"Louise\" — Twin-Engine Light Bomber: Primary-Source Documentation Collection","description":"\u003ch2\u003eMitsubishi Ki-2 “Louise” — Twin-Engine Light Bomber\u003c\/h2\u003e\u003cp\u003e\u003cem\u003eJapanese: 三菱 九三式双軽爆撃機 | Allied reporting name: “Louise”\u003c\/em\u003e\u003c\/p\u003e\u003cp\u003eThe Mitsubishi Ki-2 was a 1930s twin-engine light bomber developed for the Imperial Japanese Army Air Service (IJAAS), derived directly from the German Junkers K-37 twin-engine fighter-bomber design purchased by Mitsubishi. It represented a pivotal transitional airframe in Japanese military aviation — forcing Mitsubishi factories to abandon wood-and-fabric construction methods in favour of all-metal stressed-skin production lines.\u003c\/p\u003e\u003cp\u003eBecause the IJAAS systematically destroyed its military archives at the end of World War II, primary technical literature for the Ki-2 is exceptionally scarce. This collection brings together the surviving primary-source documentation preserved in Japanese archival repositories.\u003c\/p\u003e\u003chr\u003e\u003ch3\u003e📋 Performance Data Sheet (Ki-2-I \/ Ki-2-II)\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eParameter\u003c\/th\u003e\n\u003cth\u003eKi-2-I (Model 1)\u003c\/th\u003e\n\u003cth\u003eKi-2-II (Model 2)\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003ePowerplant\u003c\/td\u003e\n\u003ctd\u003e2 × Nakajima Jupiter 9-cyl air-cooled radials\u003c\/td\u003e\n\u003ctd\u003e2 × Nakajima Ha-8 (Type 94) 9-cyl radials\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePower Output\u003c\/td\u003e\n\u003ctd\u003e450–570 hp per engine\u003c\/td\u003e\n\u003ctd\u003e750 hp per engine\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003ePropeller\u003c\/td\u003e\n\u003ctd\u003eTwo-blade fixed-pitch wooden\u003c\/td\u003e\n\u003ctd\u003eTwo-blade variable\/fixed-pitch metal\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCowling\u003c\/td\u003e\n\u003ctd\u003eTownend ring \/ open cylinder fairings\u003c\/td\u003e\n\u003ctd\u003eStreamlined low-drag NACA cowlings\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e225 km\/h (140 mph) at 3,000 m\u003c\/td\u003e\n\u003ctd\u003e283 km\/h (176 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eCruising Speed\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e150 km\/h (93 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e7,000 m (22,966 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eOperational Range\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e900 km (559 miles); ferry range 1,630 km\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eClimb Rate\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e10.5 min to 3,000 m (9,843 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eEmpty Weight\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e2,800 kg (6,173 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Takeoff Weight\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e4,550 kg (10,031 lb)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eBomb Load\u003c\/td\u003e\n\u003ctd colspan=\"2\"\u003e500 kg (1,102 lb) internal\/external racks\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003ch3\u003e📐 Aerodynamic Profile \u0026amp; Design Origin\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Structure:\u003c\/strong\u003e Junkers-style low-wing monoplane layout. The Ki-2-I used corrugated duralumin skin panels for structural rigidity — effective but generating significant parasitic drag.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-2-II Upgrades:\u003c\/strong\u003e Smooth metal wing skin panels replaced corrugated surfaces; enclosed pilot canopy added; glazed enclosed nose turret incorporated; semi-retractable landing gear folding forward into engine nacelles replaced the Ki-2-I’s fixed spat-faired undercarriage.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eTail Configuration:\u003c\/strong\u003e Twin fins and rudders for directional stability while providing clear arcs of fire for the dorsal gunner.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e🚀 Engine Technical Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-2-I:\u003c\/strong\u003e Nakajima Jupiter radials with Townend ring cowlings — adequate for the corrugated-skin airframe but limiting top speed.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-2-II:\u003c\/strong\u003e Nakajima Ha-8 (Type 94) radials producing 750 hp each, paired with streamlined NACA low-drag cowlings — delivering a 58 km\/h speed increase over the Model I.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e🕹️ Handling \u0026amp; Stability Studies\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eSingle-Engine Control:\u003c\/strong\u003e Unlike the larger Ki-1, the Ki-2 demonstrated excellent asymmetric power handling and could safely sustain altitude and maintain control on a single operating engine.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eManeuverability:\u003c\/strong\u003e Highly praised by crews for agility relative to its classification — far more maneuverable than contemporary biplane bombers such as the Kawasaki Ki-3.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eStall Vulnerability:\u003c\/strong\u003e Early flight testing suffered severe structural and aerodynamic stalls during landing configurations. One early prototype stalled on approach, resulting in a fatal fuselage snap. Production models corrected this by drastically strengthening the rear fuselage framework.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e🏆 Engineering Legacy\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eManufacturing Milestone:\u003c\/strong\u003e The Ki-2 forced Mitsubishi factories to abandon wood-and-fabric methods in favour of all-metal stressed-skin production lines — a foundational shift for all subsequent Mitsubishi military aircraft.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCivilian Record-Breaker:\u003c\/strong\u003e A highly modified aerodynamic variant named \u003cem\u003eOhtori\u003c\/em\u003e (鳳, “Phoenix”) was built for long-range civil aviation. Engineering adjustments to fuel capacity enabled a historic 9,300 km flight around China and a record 21-hour Tokyo-to-Bangkok flight in 1936.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\u003ch3\u003e📚 Document Manifest\u003c\/h3\u003e\u003cp\u003eThis collection brings together three primary archival volumes for the Mitsubishi Ki-2 “Louise”, recovered and preserved by Online Aviation Library.\u003c\/p\u003e\u003cp\u003e\u003cem\u003eArchival source: Asia Historical Documents Center (アジア歴史資料センター \/ JACAR), Imperial Japanese Army Air Service wartime production archive. Original language: Japanese.\u003c\/em\u003e\u003c\/p\u003e\u003ch4\u003eVolume 1 — Ki-2 Technical Drawings\u003c\/h4\u003e\u003cp\u003e\u003cem\u003e三菱 九三式双軽爆撃機 技術図面 | Mitsubishi Heavy Industries \/ IJAAS wartime production archive | Original language: Japanese\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eSheet\u003c\/th\u003e\n\u003cth\u003eAppendix No.\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003e01\u003c\/td\u003e\n\u003ctd\u003eCover\u003c\/td\u003e\n\u003ctd\u003eCollection title page and document register\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e02\u003c\/td\u003e\n\u003ctd\u003e附図第九 (Fig. 9)\u003c\/td\u003e\n\u003ctd\u003e中央翼 (共二) — centre section plan view: front spar (前縁框), ribs 1–4, front\/rear attachment frames, 2,800mm span; cross-sections: centre rib (中央框), front\/rear movable frame (前後別動框), outer rib (外方框), G-profile airfoil section\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e03\u003c\/td\u003e\n\u003ctd\u003e附図第二 (Fig. 2)\u003c\/td\u003e\n\u003ctd\u003e外翼 (共二) — auxiliary wing attachment bracket (補助翼取付筋帯): isometric exploded view of No. 4 rib, attachment bracket, auxiliary wing bearing, bolt assembly, circular tube spar\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e04\u003c\/td\u003e\n\u003ctd\u003e附図第三 (Fig. 3)\u003c\/td\u003e\n\u003ctd\u003e外翼翼框 (共二) — circular tube spar joint: connecting fittings (結接金具), attachment parts (都取付件), C-profile spar section; I-beam spar side elevation with bolt flange plates\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e05\u003c\/td\u003e\n\u003ctd\u003e附図第五 (Fig. 5)\u003c\/td\u003e\n\u003ctd\u003e外翼翼框 (共四) — circular tube spar with Z-section and diagonal bracing; compression rib (押抑結筋); 30×28 tube and 100×1–00×0.8 Z-material callouts\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e06\u003c\/td\u003e\n\u003ctd\u003e附図第七 (Fig. 7)\u003c\/td\u003e\n\u003ctd\u003e主翼球面節接手 — spherical ball joint cross-section (A, B, C); outer wing attachment rib cross-section with numbered positions 1–7; full material specification table\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e07\u003c\/td\u003e\n\u003ctd\u003e附図第九 (Fig. 9)\u003c\/td\u003e\n\u003ctd\u003e補助翼 — full-span plan view (4,801mm): spar positions, rib station spacings, front\/rear spar centrelines; cross-sections A-B (円管框), C-D (60×41 corrugated), E-F (60×18 corrugated), H-G (streamlined tip fairing), I (circular tube end cap)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e08–50+\u003c\/td\u003e\n\u003ctd\u003eVarious\u003c\/td\u003e\n\u003ctd\u003eSupplementary structural and systems drawings from the IJAAS\/JACAR wartime production archive — airframe, undercarriage, control surfaces, systems installations\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch4\u003eVolume 2 — Ki-2-II Operating and Maintenance Manual\u003c\/h4\u003e\u003cp\u003e\u003cem\u003e九三式双軽爆撃機(二型)説明書 | 陸軍航空本部 (Imperial Japanese Army Air Headquarters) | Original language: Japanese\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003ePage\u003c\/th\u003e\n\u003cth\u003eAppendix No.\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eCover\u003c\/td\u003e\n\u003ctd\u003e—\u003c\/td\u003e\n\u003ctd\u003e九三式双軽爆撃機(二型)説明書 — official IJAAS title page with 陸軍航空本部 stamp\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0960\u003c\/td\u003e\n\u003ctd\u003e—\u003c\/td\u003e\n\u003ctd\u003e一面図 — Ki-2-II full two-view drawing: top-down plan (wingspan 19,740mm, fuselage width 2,481mm, wheel track 4,115mm, engine centreline spacing 4,495mm) with twin NACA cowlings, corrugated wing skin, glazed nose turret, dorsal gunner position, ventral gondola, bomb racks; side elevation with 940×300mm main wheels, 400×100mm tail wheel\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0967\u003c\/td\u003e\n\u003ctd\u003e—\u003c\/td\u003e\n\u003ctd\u003e重量及重心一覧表 — Weight \u0026amp; Centre of Gravity table for 11 loading configurations: empty (4,465 kg) through special full load (6,003 kg) and 500 kg bomb load (6,311 kg); CG position X (mm) and % chord; fuselage CG reference diagram\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0973\u003c\/td\u003e\n\u003ctd\u003e—\u003c\/td\u003e\n\u003ctd\u003e備品名称員数量表 (sheet 1) — Equipment Parts Quantity Table: Ko\/A airframe, Otsu\/B engine, Hei\/C systems, Tei\/D instruments; part name, quantity, unit weight, total weight, remarks\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0974\u003c\/td\u003e\n\u003ctd\u003e—\u003c\/td\u003e\n\u003ctd\u003e備品名称員数量表 (sheet 2) — Equipment Parts Quantity Table continuation: Bo\/E electrical, Ki\/F armament, Ko\/G survival\/emergency; bomb suspension device, flare drop device, interphone, machine gun, filter, propeller components\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0978\u003c\/td\u003e\n\u003ctd\u003e附図第二 (Fig. 2)\u003c\/td\u003e\n\u003ctd\u003e胴體 (共二) — Fuselage isometric cutaway section 2: oval fuselage cross-section with auxiliary frame, flat plate skin panels, angle bracket floor stringer attachments, corrugated duralumin exterior skin, internal frame ring with riveted flanges\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0860\u003c\/td\u003e\n\u003ctd\u003e附図第四図 (Fig. 4)\u003c\/td\u003e\n\u003ctd\u003e胴體 (共四) — Fuselage bomb bay structural detail: 胴體中部覆 6附近ノ構造ヲ示ス — upper\/lower longerons, A\/B stringers, bomb suspension rack, lateral bracing, welded box; A-detail: 波板 30×10×0.4, 40×40×1.6 angle; B-detail: 40×40×2 angle, 1.5mm plate\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0982\u003c\/td\u003e\n\u003ctd\u003e附図第六 (Fig. 6)\u003c\/td\u003e\n\u003ctd\u003e胴體前端 — Glazed nose section structural drawing: isometric 3\/4 view of complete glazed nose turret dome assembly with windward rotation centre, glass panel attachment holes, upper\/lower rotation rail plates, rotation prevention fixing screw, flat cover; upper\/lower rail cross-sections\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e0984\u003c\/td\u003e\n\u003ctd\u003e附図第八 (Fig. 8)\u003c\/td\u003e\n\u003ctd\u003e主翼 (共一) 翼肂及外皮 — Main wing rib and skin structure: isometric cutaway of outer wing leading edge showing leading edge, skin panels, aileron, trailing edge, front spar, ribs 1–4, Duralumin doubler joint; A-detail cross-section with paper former and circular tube spar end cap\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1014\u003c\/td\u003e\n\u003ctd\u003e附図第三八 (Fig. 38)\u003c\/td\u003e\n\u003ctd\u003e陥著装置 (共十六) 切気圧縦 — Landing gear brake system plumbing diagram: full aircraft-wide pneumatic brake line routing with special connectors (Type Otsu), two-stage connector pipes, indicator, red lamp, pipe valves, isolator valves, upper\/lower safety valves; pipe dimension callouts\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1016\u003c\/td\u003e\n\u003ctd\u003e附図第一 (Fig. 1)\u003c\/td\u003e\n\u003ctd\u003e車輪制動装置 — Wheel brake master cylinder cross-section: front view (components 5–11) with upper\/lower pressure adjustment screws, left\/right wheel brake pressure connections, 50° and 3° angles; side view (components 1–4), 118mm height, 75° angle\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1018\u003c\/td\u003e\n\u003ctd\u003e附図第四一 (Fig. 41)\u003c\/td\u003e\n\u003ctd\u003e尾輪 — Tail wheel assembly: side-elevation of complete 400×100mm tail wheel and oleo strut with spherical bearing, frames 14\/15, axle strut (120° travel), stop fitting, maximum deflection\/ground static\/flight positions, rotation joint, fork fitting, rubber attachment fittings, rubber buffer posts (10mm diameter, 2 each side)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1020\u003c\/td\u003e\n\u003ctd\u003e附図第三五 (Fig. 35)\u003c\/td\u003e\n\u003ctd\u003e発動機架 (共二) C部詳細 — Engine mount section C detail: isometric exploded view of Nakajima Ha-8 radial engine mount tube joint assembly with 35×83, 35×8, and 45×18 aluminium alloy tubes, heat dissipation plate attachment, diameter 14 taper bolt\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1022\u003c\/td\u003e\n\u003ctd\u003e附図第五五 (Fig. 55)\u003c\/td\u003e\n\u003ctd\u003e発動機覆 — NACA engine cowling exploded assembly: five components in isometric exploded view — forward cowl ring (9 cylinder cutout openings), oval mounting ring, three-petal rear cowl flap assembly, three-petal front cowl flap, axial spinner\/propeller hub fairing; front attachment screws, front guard vertical plate\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1024\u003c\/td\u003e\n\u003ctd\u003e附図第七七 (Fig. 77)\u003c\/td\u003e\n\u003ctd\u003e環状框 — Fuselage ring frame: large isometric view of complete oval riveted duralumin ring frame with rectangular lightening holes, corrugated skin attachment flanges, floor attachment brackets; A-B断面 cross-section (cord bolt, plate, metal fitting); bolt joint section detail; front head receiver fitting with felt gasket pad\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1052\u003c\/td\u003e\n\u003ctd\u003e附図第七五 (Fig. 75)\u003c\/td\u003e\n\u003ctd\u003e八九式(特)眼倉取付金具 左部倉用ヲ示ス — Type 89 (Special) gun sight mounting bracket (left bay): exploded isometric of base plate D-ring, curved saddle bracket, handle, release catch lever, gun sight housing cradle, cover open\/close section, eyepiece, eyepiece cord, steel rubber bead\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1054\u003c\/td\u003e\n\u003ctd\u003e附図第七七 (Fig. 77)\u003c\/td\u003e\n\u003ctd\u003e旋回風よけ取付要領 — Rotating windscreen mounting instructions: large front-view of complete circular rotating windscreen ring assembly with rotating ring, joint cover plates, fixed ring, lower windscreen gap trim, ladder plate, horizontal ladder; forward attachment fitting detail; A and B cross-section profiles\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1056\u003c\/td\u003e\n\u003ctd\u003e附図第九一 (Fig. 91)\u003c\/td\u003e\n\u003ctd\u003e爆弾配置要領 (共一) — Bomb arrangement layout sheet 1: four-view bomb load configuration diagram — 100kg bombs (3+3 positions, two rows) and 50kg bombs (3+3+3+3 positions, four rows); rear-view elevations of both configurations\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1058\u003c\/td\u003e\n\u003ctd\u003e附図第八一 (Fig. 81)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾懸吊装置 — 15kg bomb suspension assembly: large isometric cutaway of complete bomb bay interior showing full suspension rack system in situ — bomb bays 6 and 7, rotation handle, side panels, bomb suspension rack fittings, bomb ejection tube, bomb tube, compression tube\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1059\u003c\/td\u003e\n\u003ctd\u003e附図第八二 (Fig. 82)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾懸吊装置 (共二) — 15kg bomb suspension rack side elevation: bomb bay door, open\/close latch, equipment box, safety pin device bracket, flight direction arrow\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1060\u003c\/td\u003e\n\u003ctd\u003e附図第八三 (Fig. 83)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾吊装置蓋開閉操作概要 — 15kg bomb bay door open\/close operation overview: three-view — side elevation (operating lever 515mm), front elevation (packing\/gasket, plates, bolt piece), isometric 3\/4 view of door mechanism\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1061\u003c\/td\u003e\n\u003ctd\u003e附図第九 (Fig. 9)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾倉蓋開閉器集造装置 — Bomb bay door open\/close mechanism: four-view of door actuator with pilot seat safety device, electrical circuit connection diagram, dimension callouts\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1062\u003c\/td\u003e\n\u003ctd\u003e附図第八三 (Fig. 83)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾吊装置蓋開操作把手 — 15kg bomb bay door opening operation handle: side elevation of ratchet lever handle (45mm, 18mm, gear teeth); front view of circular ratchet plate (106mm diameter, 4 bolt holes at 90°, 3 ratchet positions 甲\/乙\/丙, 8.60° angle)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1063\u003c\/td\u003e\n\u003ctd\u003e附図第八六 (Fig. 86)\u003c\/td\u003e\n\u003ctd\u003e一五璤爆弾横吊装置 — 15kg bomb horizontal suspension: isometric view showing attachment fittings, Type Otsu electromagnetic lock (Model 2), bomb bay door, electromagnetic lock seat, vertical hook\/bombing panel, Type 19 electromagnetic connector, flight direction\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1065\u003c\/td\u003e\n\u003ctd\u003e附図第八八 (Fig. 88)\u003c\/td\u003e\n\u003ctd\u003e中央翼左下五〇璤爆弾懸吊架構造要領 — 50kg bomb suspension rack structural overview: isometric view of centre wing left lower 50kg bomb rack with Type Ko electromagnetic lock, electromagnetic lock seat, flight direction\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1069\u003c\/td\u003e\n\u003ctd\u003e附図第九 (Fig. 9)\u003c\/td\u003e\n\u003ctd\u003e爆撃電気接続装置図 — Bombing electrical connection system diagram: full wiring schematic — port\/starboard Type 15 electromagnetic connectors, Type 2 electromagnetic locks, bombing panel, release electromagnetic lock, safety device\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1090\u003c\/td\u003e\n\u003ctd\u003e附図第一一一 (Fig. 111)\u003c\/td\u003e\n\u003ctd\u003e主間開部構造及装著配置要領 — Main hatch structure \u0026amp; installation layout: front elevation of main hatch panel (rectangular with oval cutout, 42×46mm, bolt pattern); isometric 3\/4 view of hatch locking lever mechanism (325mm, 45mm); top-down plan of oval hatch opening; side elevation cross-section; tail fin\/rudder outline plan\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1092\u003c\/td\u003e\n\u003ctd\u003e附図第一一〇 (Fig. 110)\u003c\/td\u003e\n\u003ctd\u003e著陸燈・視認燈・警燈・信號燈及機除遥蔽装著要領 — Complete aircraft lighting installation layout: full aircraft 3\/4 isometric perspective view of Ki-2-II showing all external lighting positions with candlepower ratings — landing light 10CP (port wing), rotating lights 10CP (both engine nacelles), position light 10CP (nose), rotating light 10CP (starboard wing), tail rotating light 10CP, signal light 240CP (ventral), emergency light 240CP\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1094\u003c\/td\u003e\n\u003ctd\u003e附図第一一四 (Fig. 114)\u003c\/td\u003e\n\u003ctd\u003e尾部制除燈及尾燈応燈近装置配置要領 — Tail navigation light \u0026amp; tail light installation layout: B-B cross-section of tail light bar assembly (Type 1 aluminium alloy plate, Type 1\/2 lamp bulbs No. 171, front shield 113, 87mm); top-down plan of tail light housing (large oval, two circular lamp positions); side elevation showing front\/rear plates, lamp centre, shield plates\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1095\u003c\/td\u003e\n\u003ctd\u003e附図第三六 (Fig. 36)\u003c\/td\u003e\n\u003ctd\u003e警戒構造及装着配置要領 — Glazed nose turret structural layout: top-down plan of oval eye-shaped glazed turret panel with rivet pattern and fuselage centreline; A-A cross-section (10-type 2-bulb lamp in dome); B-B cross-section (hollow glass, spruce frame, aluminium alloy plate, flight direction); outer wing rib station profile\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1096\u003c\/td\u003e\n\u003ctd\u003e附図第一七 (Fig. 17)\u003c\/td\u003e\n\u003ctd\u003e信號燈構造及装著配置要領 — Signal light structure \u0026amp; installation layout: top-down plan of large oval ventral signal light housing (HP dimension, rivet pattern grid); A-A cross-section (Type 1 aluminium alloy plate, spruce frame, glass dome, Type 2 illumination lamp bulb No. 172); tail fin profile with aileron, ribs 1–4, leading edge light position\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1097\u003c\/td\u003e\n\u003ctd\u003e附図第三八 (Fig. 38)\u003c\/td\u003e\n\u003ctd\u003e機銃設情高及装着配置要領 — Machine gun installation height \u0026amp; mounting layout: B-B and A-A cross-sections (spruce, glass, aluminium alloy plate, outer wing rib stations, inner bilateral electrical seat); plan view showing ventral window (large oval); outer wing rib station plan with ribs 1–5, front\/rear wing\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1098\u003c\/td\u003e\n\u003ctd\u003e附図第一九 (Fig. 19)\u003c\/td\u003e\n\u003ctd\u003e機上著陸燈構造及装著配置要領 — Airborne landing light structure \u0026amp; installation layout: A-A cross-section (164mm height, 153mm width, 16mm depth, 30-60-30mm base, 70mm total width); isometric 3\/4 view of complete landing light assembly (parabolic reflector, 35° and 3° angles, rubber mount, illumination direction arrow); front view (170mm diameter ring); outer wing plan with aileron, ribs 1–4, leading edge light position\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1099\u003c\/td\u003e\n\u003ctd\u003e附図第一一〇 (Fig. 110)\u003c\/td\u003e\n\u003ctd\u003e席房燈・移動燈及非常燈装着配置要領 — Cabin lights, portable lights \u0026amp; emergency lights installation: isometric cutaway of full fuselage interior showing all lighting positions — emergency light dry battery, cabin light dimmer, portable light storage; symbol legend for cabin light, portable light, emergency light\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1100\u003c\/td\u003e\n\u003ctd\u003e附図第一一一 (Fig. 111)\u003c\/td\u003e\n\u003ctd\u003e非常燈構造要領 — Emergency light structure: isometric 3\/4 view of portable dome-shaped emergency light (open\/close handle, glass dome, circular base plate with 4 mounting holes); wiring diagram (dry battery, on\/off switch, emergency light circuit); cross-section (shell, lamp bulb, 4\/7\/5\/3mm dimensions); top-down plan (52mm and 26mm base)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1101\u003c\/td\u003e\n\u003ctd\u003e附図第一一一 (Fig. 111)\u003c\/td\u003e\n\u003ctd\u003e九〇式小圆照明弾投下装置 (共一) — Type 90 small round illumination flare drop device: isometric view of port wing showing flare chute from cockpit through wing structure — section 1 (cockpit end with operating handle), 6×1 flush coating, powder\/flare, flight direction\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1103\u003c\/td\u003e\n\u003ctd\u003e附図第三三四 (Fig. 334)\u003c\/td\u003e\n\u003ctd\u003e通話器装置要領 — Speaking tube interphone system layout: isometric cutaway of fuselage showing speaking tube routing — tube mouthpieces at stations 1, 3, 4; speaking tube running along fuselage floor; bottle\/junction; numbered stations 1–4\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003e1105\u003c\/td\u003e\n\u003ctd\u003e附図第三六 (Fig. 36)\u003c\/td\u003e\n\u003ctd\u003e貨車積載及荷造要領 — Railway freight loading \u0026amp; packing instructions: side elevation of Type Chiki No. 19 military flatcar loaded with Ki-2 disassembled — fuselage, tail\/aileron\/parts, outer wings (×2); three crate cross-section dimension drawings: fuselage crate (2,900×2,250mm), tail\/aileron crate (3,300×2,250mm), outer wing crate (2,300mm wide)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch4\u003eVolume 3 — Ki-2 Photo Collections\u003c\/h4\u003e\u003cp\u003e\u003cem\u003eAllied TAIU field documentation, IJAAS operational photography \u0026amp; post-war recovery records | English \/ Japanese\u003c\/em\u003e\u003c\/p\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eItem\u003c\/th\u003e\n\u003cth\u003eContent\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\u003ctr\u003e\n\u003ctd\u003ePhotographic Archive\u003c\/td\u003e\n\u003ctd\u003eSurviving photographic record of the Ki-2 airframe in operational service, ground handling, and Allied post-war inspection. Includes colourised period photographs of Ki-2 aircraft at Japanese airfields with ground crew.\u003c\/td\u003e\n\u003c\/tr\u003e\u003c\/tbody\u003e\n\u003c\/table\u003e\u003chr\u003e\u003cp\u003e\u003cem\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.\u003c\/em\u003e\u003c\/p\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates – Please review our Legal Notice and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53776683401563,"sku":null,"price":45.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-2-classic-navy-aviation-art.png?v=1786649596"},{"product_id":"mitsubishi-ki-1-army-type-93-heavy-bomber-operating-manual-photo-collection","title":"Mitsubishi Ki-1 — Army Type 93 Heavy Bomber | Operating Manual \u0026 Photo Collection","description":"\u003ch2\u003eMitsubishi Ki-1 — Army Type 93 Heavy Bomber\u003c\/h2\u003e\u003cp\u003eThe Mitsubishi Ki-1 (Army Type 93 Heavy Bomber) was an early 1930s twin-engine Japanese bomber — a scaled-up derivative of the German Junkers K 37 design, retaining the signature corrugated-skin, low-wing cantilever monoplane architecture of the Junkers lineage. A total of 118 airframes were manufactured by Mitsubishi between March 1933 and April 1936. The type saw brief front-line service before being deemed fully obsolete by 1937 and withdrawn from service by 1938. Very little archival documentation survived the destruction of military records at the end of World War II.\u003c\/p\u003e\u003cp\u003eThis collection brings together the surviving primary-source documentation for the Ki-1, presented as an archival edition fixed at its original publication date.\u003c\/p\u003e\u003chr\u003e\u003ch2\u003eDocument Manifest\u003c\/h2\u003e\u003ch3\u003eVariant II — 1 Manual\u003c\/h3\u003e\u003cul\u003e\u003cli\u003e\n\u003cstrong\u003eKi-1-II Operating and Maintenance\u003c\/strong\u003e\u003cbr\u003eMitsubishi Ki-1-II Type 93 Heavy Bomber Operating Instructions Manual Corrigenda\u003cbr\u003e\u003cem\u003e三菱 九三式 重爆撃機 二型 取扱説明書 正誤表\u003c\/em\u003e (Japanese Language)\u003c\/li\u003e\u003c\/ul\u003e\u003ch3\u003eNo Variant — 1 Manual\u003c\/h3\u003e\u003cul\u003e\u003cli\u003e\n\u003cstrong\u003eKi-1 Slides, Photos and Brochures\u003c\/strong\u003e\u003cbr\u003eKi-1 Photographic Collection (English language)\u003c\/li\u003e\u003c\/ul\u003e\u003ch3\u003eTotal Manuals: 2\u003c\/h3\u003e\u003chr\u003e\u003ch2\u003eAircraft Technical Overview\u003c\/h2\u003e\u003ch3\u003ePerformance Data\u003c\/h3\u003e\u003ctable\u003e\n\u003cthead\u003e\u003ctr\u003e\n\u003cth\u003eCharacteristic\u003c\/th\u003e\n\u003cth\u003eKi-1-I\u003c\/th\u003e\n\u003cth\u003eKi-1-II\u003c\/th\u003e\n\u003c\/tr\u003e\u003c\/thead\u003e\n\u003ctbody\u003e\n\u003ctr\u003e\n\u003ctd\u003eCrew\u003c\/td\u003e\n\u003ctd\u003e4 (Pilot, Co-pilot, 2 Gunners)\u003c\/td\u003e\n\u003ctd\u003e4 (Pilot, Co-pilot, 2 Gunners)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMaximum Speed\u003c\/td\u003e\n\u003ctd\u003e220 km\/h (140 mph)\u003c\/td\u003e\n\u003ctd\u003e230 km\/h (143 mph)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eService Ceiling\u003c\/td\u003e\n\u003ctd\u003e5,000 m (16,400 ft)\u003c\/td\u003e\n\u003ctd\u003e5,000 m (16,400 ft)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eWingspan\u003c\/td\u003e\n\u003ctd\u003e26.50 m (86 ft 11 in)\u003c\/td\u003e\n\u003ctd\u003e26.50 m (86 ft 11 in)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eMax Take-Off Weight\u003c\/td\u003e\n\u003ctd\u003e8,100 kg (17,857 lbs)\u003c\/td\u003e\n\u003ctd\u003e8,100 kg (17,857 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003ctr\u003e\n\u003ctd\u003eNormal Bomb Load\u003c\/td\u003e\n\u003ctd\u003eUp to 1,500 kg (3,307 lbs)\u003c\/td\u003e\n\u003ctd\u003eUp to 1,500 kg (3,307 lbs)\u003c\/td\u003e\n\u003c\/tr\u003e\n\u003c\/tbody\u003e\n\u003c\/table\u003e\u003ch3\u003eAerodynamic Profile \u0026amp; Configuration\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eDesign Lineage:\u003c\/strong\u003e Scaled up approximately 30% from the German Junkers K 37. Retained the angular, corrugated-skin aesthetic of classical Junkers aircraft.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing Configuration:\u003c\/strong\u003e Low-wing cantilever monoplane. Wing panels lacked modern aerodynamic fairings, resulting in high parasitic drag.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEmpennage:\u003c\/strong\u003e Double-fin and twin-rudder tail assembly for directional stability behind the wide fuselage profile.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLanding Gear:\u003c\/strong\u003e Entirely fixed and non-retractable main undercarriage — a significant aerodynamic penalty on cruise velocity.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eEngine Technical Notes\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eVariant I Powerplant:\u003c\/strong\u003e Two Mitsubishi Ha-2-2 V-12 water-cooled engines, 940 hp (701 kW) each at takeoff.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eVariant II Powerplant:\u003c\/strong\u003e Upgraded to Mitsubishi Ha-2-3 water-cooled engines, 970 hp (723 kW) each — introduced to address the chronic underpowered performance of the Variant I.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eOperational Defects:\u003c\/strong\u003e The Ha-2 series became notorious within the Imperial Japanese Army Air Force for extreme mechanical unreliability.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eHandling and Stability Summary\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003ePower-to-Weight Deficiency:\u003c\/strong\u003e Severely underpowered for its large bulk. Flight evaluations revealed sluggish control response across all three axes.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eSingle-Engine Control Failure:\u003c\/strong\u003e Asymmetric thrust on engine failure could not be safely countered. The remaining engine could not maintain altitude, frequently forcing emergency landings or resulting in airframe loss.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eDefensive Stations:\u003c\/strong\u003e Tandem cockpit canopy, semi-enclosed nose and dorsal turrets, and a retractable ventral \"dustbin\" turret to minimise drag when not in use.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eHistorical Disposition\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003eProduction run: 118 airframes, March 1933 – April 1936.\u003c\/li\u003e\n\u003cli\u003eDeemed fully obsolete by 1937. The Imperial Japanese Army hastily procured Italian-made Fiat BR.20 bombers as a stopgap until the Mitsubishi Ki-21 entered full service.\u003c\/li\u003e\n\u003c\/ul\u003e\u003chr\u003e\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.\u003c\/p\u003e\u003cp\u003eLiving Collections with Free Lifetime Updates – Please review our Legal Notice and Export Notice before purchasing.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53781419721051,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/mitsubishi-ki-1-leaderboard-banner.png?v=1786680586"},{"product_id":"mitsubishi-ki-67-hiryu-peggy-manuals","title":"Mitsubishi Ki-67 Hiryū “Peggy”","description":"\u003ch3\u003eMitsubishi Ki-67 Hiryū “Peggy” Technical Manual Collection\u003c\/h3\u003e\n\u003cp\u003eA focused collection of five Japanese-language manuals and one English-language photographic collection documenting the Mitsubishi Ki-67 Hiryū, Allied reporting name “Peggy”, the Imperial Japanese Army Air Service’s advanced twin-engine heavy bomber of the Second World War.\u003c\/p\u003e\n\u003cp\u003eThe Ki-67 was developed as a powerful departure from Japan’s traditional lightweight, long-range bomber philosophy. Its mid-wing cantilever monoplane layout, streamlined fuselage, self-sealing fuel tanks, robust structure, large balanced control surfaces, and heavy defensive armament supported an aircraft noted for its speed, agility, and low-altitude handling.\u003c\/p\u003e\n\u003ch3\u003eTechnical and operational reference points\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003eWing area: 65.85 m² (708.8 sq ft).\u003c\/li\u003e\n\u003cli\u003ePowerplant: twin Mitsubishi Ha-104 18-cylinder, two-row, air-cooled radial engines with four-blade constant-speed metal propellers.\u003c\/li\u003e\n\u003cli\u003eOutput: 1,900 hp for takeoff, 1,810 hp at 2,200 m, and 1,610 hp at 6,100 m.\u003c\/li\u003e\n\u003cli\u003eMaximum speed: 537 km\/h (334 mph) at 6,090 m.\u003c\/li\u003e\n\u003cli\u003eCruising speed: 400 km\/h (249 mph) at an operational altitude of 8,000 m.\u003c\/li\u003e\n\u003cli\u003eClimb: 6,000 m in 14 minutes 30 seconds.\u003c\/li\u003e\n\u003cli\u003eService ceiling: 9,470 m (31,070 ft).\u003c\/li\u003e\n\u003cli\u003eStandard range: 3,800 km (2,360 miles).\u003c\/li\u003e\n\u003cli\u003ePayload: 800 kg (1,764 lb) of internal bomb-bay ordnance or one Type 91 centerline aerial torpedo.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eCollection contents\u003c\/h3\u003e\n\u003cp\u003e\u003cstrong\u003eArmament\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003eMitsubishi Ki-67 Hiryu T-2 AMC: Gun Turret Operating Instructions Manual Supplement, 三式砲塔（キ67用）取扱説明書附録 (Japanese language).\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003cp\u003e\u003cstrong\u003eOperating and maintenance\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003eMitsubishi Ki-67 Hiryu Maintenance Instructions, キ67取扱参考資料 (Japanese language).\u003c\/li\u003e\n\u003cli\u003eMitsubishi Ki-67 Hiryu T-2 AMC, Maintenance Reference Material, キ六七取扱參考 (Japanese language).\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003cp\u003e\u003cstrong\u003eEquipment\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003eMitsubishi Ki-67 Hiryu Type 4 Heavy Bomber Oxygen Equipment Installation Manual, 四式重爆撃機酸素裝備法 (Japanese language).\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003cp\u003e\u003cstrong\u003eSlides, photographs and brochures\u003c\/strong\u003e\u003c\/p\u003e\n\u003cul\u003e\n\u003cli\u003eKi-67 Photographic Collection (English language).\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch3\u003eVariants and modifications represented in the reference material\u003c\/h3\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-67-I (Ko \/ Otsu):\u003c\/strong\u003e standard production bomber with a dorsal 20 mm Ho-5 cannon and four 12.7 mm Type 1 machine guns.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-67-I Kai:\u003c\/strong\u003e specialized anti-shipping naval version adapted for long-range torpedo operations.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-67-II:\u003c\/strong\u003e high-performance prototype upgrade with dual 2,400 hp Mitsubishi Ha-214 radial engines.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-109:\u003c\/strong\u003e heavy day\/night interceptor variant with the bomb bay removed for a fixed 75 mm Type 88 nose cannon.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003e“To-Gō” kamikaze:\u003c\/strong\u003e stripped defensive turrets with plywood fairings and a 2,900 kg Sakura-dan shaped charge.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003cp\u003eOwning this collection means holding a compact research record of the Hiryū’s airframe design, powerplant installation, oxygen equipment, armament systems, maintenance practice, and photographic appearance. It is suited to collectors, historians, model researchers, and anyone studying Japanese wartime aircraft engineering through original-language technical material.\u003c\/p\u003e\n\u003cp\u003e\u003cem\u003eCollection size: 5 manuals and photographic references. No variant grouping.\u003c\/em\u003e\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53963086561627,"sku":null,"price":48.85,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/image_41e5ea76-20a8-4f1c-b168-4daaaaed871a.png?v=1788439342"},{"product_id":"mitsubishi-ki-51-sonia-aircraft-manuals-collection","title":"Mitsubishi Ki-51 “Sonia” Aircraft Manuals Collection","description":"\u003ch3\u003eA compact technical library for the Mitsubishi Ki-51 “Sonia”\u003c\/h3\u003e\n\u003cp\u003eThe Mitsubishi Ki-51, known to the Allies by the reporting name \u003cstrong\u003e“Sonia”\u003c\/strong\u003e, was the Imperial Japanese Army Air Force’s Type 99 Assault Plane, also operated in a tactical reconnaissance role. Designed for close support, low-level battlefield work and operation from demanding forward airfields, the Ki-51 was a notably rugged aircraft, with fixed landing gear, outer-wing leading-edge slats and protection for its crew and vital systems.\u003c\/p\u003e\n\u003cp\u003eThis focused three-document collection brings together Japanese-language operating and engine material with an English-language photographic reference. It is an excellent starting point for researchers studying the Ki-51’s machinery, maintenance practice, crew environment, production history and wartime appearance.\u003c\/p\u003e\n\u003ch2\u003eCollection contents\u003c\/h2\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-51 Engine\u003c\/strong\u003e\u003cbr\u003eMitsubishi Ha-26, also identified as the Zuisei Model 11, Aircraft Engine Handling Instructions, \u003cem\u003e瑞星発動機一一型取扱須知\u003c\/em\u003e. Japanese language.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-51 Operating and Maintenance\u003c\/strong\u003e\u003cbr\u003eKi-51 Type 99 Aircraft Instruction Manual, covering the Type 99 Army Reconnaissance Aircraft and Type 99 Assault Aircraft, \u003cem\u003e九九式軍偵察機 九九式襲撃機 説明書\u003c\/em\u003e. Japanese language.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-51 Slides, Photos and Brochures\u003c\/strong\u003e\u003cbr\u003eKi-51 Photographic Collection. English language, with visual reference material for identifying the aircraft, its details and its historical context.\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch2\u003eWhat the technical material covers\u003c\/h2\u003e\n\u003cp\u003eThe Ki-51 was derived from the Mitsubishi Ki-30 “Ann”, but redesigned around the realities of low-altitude assault operations. The move to a low-wing arrangement removed the internal bomb bay and created a more direct, robust landing-gear structure. Fixed tail-dragger undercarriage legs were enclosed in aerodynamic trouser fairings, trading some speed for durability and easier field servicing. Fixed leading-edge slats on the outer wing sections helped retain control during slow, tight turns close to the stall.\u003c\/p\u003e\n\u003cp\u003ePower came from the fourteen-cylinder, two-row, air-cooled Mitsubishi Ha-26-II radial, commonly associated with the Ha-31 or Zuisei 15 designation in variant references. The engine delivered approximately 950 horsepower at takeoff through a three-blade, constant-speed metal propeller. Baffled cooling and adjustable cowling gills supported sustained low-speed, high-power work, while the engine access arrangements were intended to make servicing practical with basic field equipment.\u003c\/p\u003e\n\u003cp\u003eUnlike many lightweight Japanese combat aircraft, the Ki-51 incorporated meaningful protection for an aircraft expected to operate directly over the battlefield. Technical and engineering references describe armour around the engine sump, oil tanks and crew floor areas, together with a compact tandem cockpit arrangement that kept the crew close to the aircraft’s centre of gravity. The type was produced in assault and reconnaissance forms, with later changes affecting wing armament, camera installation and external ordnance arrangements.\u003c\/p\u003e\n\u003ch2\u003eReference specification\u003c\/h2\u003e\n\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eWingspan:\u003c\/strong\u003e 12.10 m \/ 39 ft 8.5 in\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eLength:\u003c\/strong\u003e 9.21 m \/ 30 ft 3 in\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eHeight:\u003c\/strong\u003e 2.73 m \/ 8 ft 11.5 in\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eWing area:\u003c\/strong\u003e 24.02 m² \/ 258.5 sq ft\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEmpty weight:\u003c\/strong\u003e 1,873 kg \/ 4,129 lb\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eGross loaded weight:\u003c\/strong\u003e 2,798 kg \/ 6,169 lb\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum takeoff weight:\u003c\/strong\u003e 2,920 kg \/ 6,415 lb\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum speed:\u003c\/strong\u003e approximately 424 km\/h at 3,000 m \/ 263 mph at 9,845 ft\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCruising speed:\u003c\/strong\u003e approximately 320 km\/h \/ 200 mph\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eService ceiling:\u003c\/strong\u003e approximately 8,270 m \/ 27,130 ft\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eOperational range:\u003c\/strong\u003e approximately 1,060 km \/ 660 miles\u003c\/li\u003e\n\u003c\/ul\u003e\n\u003ch2\u003eA rewarding addition to a serious aviation library\u003c\/h2\u003e\n\u003cp\u003eOpen these documents together and the Ki-51 becomes more than a silhouette or a name in an aircraft register. The engine instructions reveal the practical heart of the machine; the operating and maintenance manual places the aircraft in the hands of its crews and ground personnel; and the photographic collection supplies the visual evidence needed to recognise fittings, finishes and configuration differences. For collectors of Japanese military aviation, researchers of the Pacific War and model builders looking beyond secondary summaries, this is a compact but unusually useful reference set.\u003c\/p\u003e\n\u003cp\u003e\u003cstrong\u003eTotal manuals: 3.\u003c\/strong\u003e No variant selection is required for this collection.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53963307352411,"sku":null,"price":30.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-51-sonia-banner.png?v=1788441815"},{"product_id":"mitsubishi-ki-46-dinah-manuals-collection","title":"Mitsubishi Ki-46 “Dinah” Manuals Collection","description":"\u003ch2\u003eMitsubishi Ki-46 “Dinah” Manuals Collection\u003c\/h2\u003e\u003cp\u003eA compact historical reference collection covering the Mitsubishi Ki-46 Type 100 “Dinah,” the elegant Japanese Army strategic reconnaissance aircraft developed for speed, range, and low aerodynamic drag.\u003c\/p\u003e\u003cp\u003eThis digital collection brings together three historical documents and visual-reference materials in Japanese, Russian, and English. It is intended for aviation historians, aircraft researchers, collectors, and enthusiasts studying the Ki-46 and its wartime technical record.\u003c\/p\u003e\u003ch3\u003eCollection contents\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-46 Type 100 Aircraft Technical Drawings\u003c\/strong\u003e — \u003cem\u003e一〇〇式司令部偵察機附図\u003c\/em\u003e, Japanese language.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-46 (Type 100) Ground Testing Report No. 147\u003c\/strong\u003e — \u003cem\u003eОтчет №147 по результатам наземных испытаний трофейного японского самолета Мицубиси “Р-100”\u003c\/em\u003e, Russian language.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-46 Photographic Collection\u003c\/strong\u003e — slides, photographs, and brochure material, English language.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eEngine technical notes and propulsion\u003c\/h3\u003e\u003cp\u003eThe Ki-46 developed through several engine configurations as the design was adapted for high-altitude reconnaissance:\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eMitsubishi Ha-102, Ki-46-II:\u003c\/strong\u003e twin 14-cylinder, two-row, air-cooled radial engines, reported at approximately 1,080 hp each.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMitsubishi Ha-112-II, Ki-46-III:\u003c\/strong\u003e upgraded direct fuel-injection engines, reported at approximately 1,500 hp each.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eEjector exhaust:\u003c\/strong\u003e wartime modifications replaced the conventional collector arrangement with individual ejector pipes. Historical notes associate the change with an increase in top speed of roughly 12 km\/h.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-46-IV prototypes:\u003c\/strong\u003e the late-war Ha-112-II Ru installation is described with exhaust-driven turbo-supercharging and water-methanol injection for improved high-altitude performance.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eHandling and stability studies\u003c\/h3\u003e\u003cp\u003eHistorical flight-test and engineering notes describe stable high-altitude cruise characteristics alongside operational limitations. At extreme altitudes, aileron response and elevator authority could become less effective. The landing-gear struts were also reported as vulnerable to snapping or buckling during hard landings on rough forward airfields, even after reinforcing changes. Later production aircraft incorporated modest stabilizer-area changes associated with pitch stability.\u003c\/p\u003e\u003ch3\u003eReported Ki-46-III performance figures\u003c\/h3\u003e\u003cp\u003ePost-war testing and intelligence evaluations reported the following approximate figures for the Ki-46-III, with results varying by aircraft condition, fuel, configuration, and test method:\u003c\/p\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum speed:\u003c\/strong\u003e approximately 630 km\/h at 6,000 m, with some reports of up to 684 km\/h using high-octane fuel.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eCruising speed:\u003c\/strong\u003e approximately 400 km\/h.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eService ceiling:\u003c\/strong\u003e approximately 10,500 m.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eMaximum range:\u003c\/strong\u003e approximately 4,000 km with full internal and wing-tank capacity.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eClimb:\u003c\/strong\u003e approximately 17 minutes 58 seconds to 8,000 m in the cited test data.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eEngineering bulletins and combat conversions\u003c\/h3\u003e\u003cp\u003eAs the strategic situation changed, historical engineering notes describe Ki-46-III KAI conversion work intended to provide a limited defensive-interceptor capability. The reported changes included reduced forward fuel capacity, reintroduction of a stepped nose to accommodate two forward-firing 20 mm Ho-5 cannon, and an obliquely mounted 37 mm Ho-203 cannon in the upper fuselage. These conversions were reported to suffer from reduced climb performance, limiting their usefulness against high-altitude bomber formations.\u003c\/p\u003e\u003ch3\u003eHistorical reference notice\u003c\/h3\u003e\u003cp\u003eThe Ki-46 is remembered for its exceptionally clean aerodynamic design, closely cowled radial engines, narrow fuselage, and, in the Ki-46-III, a continuous glazed nose. These materials provide documentary evidence and visual context for research into the aircraft, its testing, and its development.\u003c\/p\u003e\u003cp\u003e\u003cstrong\u003eImportant:\u003c\/strong\u003e This is historical and reference material, not current approved airworthiness data, maintenance approval, or operating instruction. Language and document condition vary by item. Please verify provenance, rights, and distribution status before any further use or reproduction.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53968400875867,"sku":null,"price":30.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/ki-46-dinah-manuals-banner.png?v=1788494561"},{"product_id":"mitsubishi-ki-21-sally-gwen-manuals-photographic-collection","title":"Mitsubishi Ki-21 “Sally” \/ “Gwen” Manuals and Photographic Collection","description":"\u003ch2\u003eMitsubishi Ki-21 “Sally” \/ “Gwen” Manual Collection\u003c\/h2\u003e\u003cp\u003eA two-item historical reference collection covering the Mitsubishi Ki-21, officially designated the Army Type 97 Heavy Bomber and known by the Allied reporting names “Sally” and “Gwen”. It brings together Japanese operating documentation and an English-language photographic archive.\u003c\/p\u003e\u003ch3\u003eCollection contents\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-21-II Type 97 Heavy Bomber Operating Instructions Manual\u003c\/strong\u003e (Japanese language), 九七式重爆撃機 二型 取扱説明書.\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-21 Photographic Collection\u003c\/strong\u003e (English language), containing slides, photographs and brochure material.\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eHistorical and technical scope\u003c\/h3\u003e\u003cp\u003eThe reference material discusses the aircraft’s all-metal cantilever mid-wing layout, control surfaces, aerodynamic development, engine and propeller installations, handling and stability changes, performance data, defensive modifications, armour, bullet-resistant glazing and self-sealing fuel protection. It follows the evolution from the Ki-21-I with Nakajima Ha-5-Kai engines to the Ki-21-II series with Mitsubishi Ha-101 engines, including the later dorsal-turret configuration associated with the “Gwen” designation.\u003c\/p\u003e\u003cp\u003eThe Ki-21 was Japan’s principal heavy bomber during the late 1930s and the early years of the Second World War. Its surviving documentation offers a useful window into Japanese bomber design, operation and wartime modification practice.\u003c\/p\u003e\u003cp\u003e\u003cstrong\u003eImportant:\u003c\/strong\u003e This is historical and reference material. It is not current approved airworthiness data, maintenance approval or operational guidance. Please assess provenance, rights and distribution status before use.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":53968453271899,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/oal-aviation-archive-banner.png?v=1788496682"},{"product_id":"mitsubishi-ki-109-hiryu-peggy-manuals-collection","title":"Mitsubishi Ki-109 Hiryu “Peggy” Manuals Collection","description":"\u003ch2\u003eMitsubishi Ki-109 Hiryu “Peggy” manuals\u003c\/h2\u003e\u003cp\u003eA compact historical reference collection on the Mitsubishi Ki-109 heavy interceptor, the wartime development of the Ki-67 airframe for high-altitude bomber interception. This digital collection contains two unique manuals in Japanese and English, supported by an archival technical synthesis covering the aircraft’s structure, propulsion, handling and production history.\u003c\/p\u003e\u003ch3\u003eCollection contents\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-109, Training Device Test Plan with Mounted Gun\u003c\/strong\u003e, 「キ一〇九」搭載砲用内謄砲試験計画, Japanese\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eKi-109 Photographic Collection\u003c\/strong\u003e, English\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eTechnical reference\u003c\/h3\u003e\u003cp\u003eThe supplied synthesis presents the Ki-109 with a 73 ft 9¾ in wingspan, 58 ft 10¾ in length, 708.8 sq ft wing area, an approximate empty weight of 16,367 lb and loaded weight of 23,810 lb. It gives a reference maximum speed of 342 mph at 19,980 ft, cruising speed of 249 mph at 26,245 ft, service ceiling of 31,070 ft and operational range of approximately 1,367 miles.\u003c\/p\u003e\u003cp\u003eThe report examines the blunt, faired nose replacing the Ki-67 greenhouse, the removal or fairing-over of selected waist gun blisters and dorsal turrets, and reinforcement of the forward fuselage bulkheads and longerons for the 75 mm Type 88 cannon. It reports a peak recoil impulse of approximately four tons and describes the resulting structural and aerodynamic compromises.\u003c\/p\u003e\u003cp\u003eThe Ki-109 is described with twin Mitsubishi Ha-104 Army Type 4 18-cylinder radial engines. Supplied power figures are 1,900 hp takeoff, 1,810 hp military power at 7,220 ft, and 1,610 hp high-altitude power at 20,015 ft. The synthesis discusses the mechanical two-speed supercharger’s limitations above 23,000 ft and reports that the proposed Ha-104 Ru turbo-supercharged development was discontinued after exhaust-manifold cracking and cooling problems.\u003c\/p\u003e\u003cp\u003eHandling notes cover the forward centre-of-gravity shift from the 75 mm cannon and 15-round ammunition magazine, the need for nose-up elevator trim, and the reported longitudinal deceleration and downward pitching moment when firing. The supplied production notes identify the canceled Ki-109a\/Ki-109b weapon concept, the turret-deletion directive in Bulletins Ki-109-01 and Ki-109-04, retention of a 12.7 mm Type 1 tail gun for self-defense, and a reported total of 22 operational production aircraft.\u003c\/p\u003e\u003ch3\u003eHistorical reference notice\u003c\/h3\u003e\u003cp\u003eThis collection is intended for aviation history, research, restoration and archival study. It is not current approved airworthiness data, operating approval, weapons guidance or maintenance authorization. The technical figures and interpretations are reproduced as supplied archival reference material and have not been independently verified here. Users must verify provenance, rights and applicability before relying on any document or report.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":54028510298459,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/mitsubishi-ki-109-hiryu-peggy-banner.png?v=1789091629"},{"product_id":"nakajima-c6n-saiun-myrt-manuals-collection","title":"Nakajima C6N Saiun “Myrt” Manuals Collection","description":"\u003ch2\u003eNakajima C6N Saiun “Myrt” manuals\u003c\/h2\u003e\u003cp\u003eA historical reference collection on the Nakajima C6N Saiun carrier-based reconnaissance aircraft, known by the Allied reporting name “Myrt”. This digital collection brings together two unique manuals in Japanese and English, supported by a supplied technical-intelligence reconstruction covering aerodynamic design, propulsion, handling, conversions and post-war evaluation.\u003c\/p\u003e\u003ch3\u003eCollection contents\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eC6N1 User Manual\u003c\/strong\u003e, 「彩雲」艦上偵察機 C6N1 仮取扱説明書, Japanese\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eC6N Photographic Collection\u003c\/strong\u003e, English\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eTechnical reference\u003c\/h3\u003e\u003cp\u003eThe supplied report describes a tightly packaged, low-drag fuselage around the 18-cylinder Nakajima Homare radial engine, a high-wing-loading laminar-flow wing, and interconnected high-lift devices combining Fowler flaps, split flaps and automatic leading-edge slats. It also discusses the carrier-elevator constraints that influenced the tail layout and the three-person crew arrangement.\u003c\/p\u003e\u003cp\u003eThe report identifies the production powerplant as the Nakajima NK9H Homare 21, with a supplied takeoff rating of 1,990 hp and a three-bladed constant-speed propeller. It presents reference figures of 610 km\/h maximum speed at 6,100 m, 390 km\/h cruising speed at 4,000 m, 5,300 km operational range with a 730-litre auxiliary tank, 10,470 m service ceiling, 2,968 kg empty structural weight and 5,260 kg maximum takeoff weight.\u003c\/p\u003e\u003cp\u003eFurther sections discuss reported high-altitude oil-pressure and power losses, the C6N2 turbocharger testbed, carrier approach handling, load sequencing, and the C6N1-S land-based night-fighter conversion. The report also summarizes post-war United States Technical Air Intelligence Center flight evaluations and presents a claimed 663 km\/h test speed after the captured engine was serviced with high-grade American fuel and lubricants.\u003c\/p\u003e\u003ch3\u003eHistorical reference notice\u003c\/h3\u003e\u003cp\u003eThis collection is intended for aviation history, research, restoration and archival study. It is not current approved airworthiness data, operating approval, maintenance authorization or weapons guidance. The technical figures, conversion descriptions and TAIC interpretations are reproduced as supplied archival research and have not been independently verified here. Users must verify provenance, rights, export requirements and applicability before relying on any document or report, particularly material identified as confidential or military archival material.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":54028534612315,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/nakajima-c6n-saiun-myrt-banner.png?v=1789093107"},{"product_id":"nakajima-g8n-renzan-rita-manuals-collection","title":"Nakajima G8N Renzan “Rita” Manuals Collection","description":"\u003ch2\u003eNakajima G8N Renzan “Rita” manuals\u003c\/h2\u003e\u003cp\u003eA historical reference collection on the Nakajima G8N Renzan heavy bomber, known by the Allied reporting name “Rita”. This digital collection contains two unique manuals, including a Japanese prototype ground-vibration test report and an English photographic collection, supported by a supplied technical profile.\u003c\/p\u003e\u003ch3\u003eCollection contents\u003c\/h3\u003e\u003cul\u003e\n\u003cli\u003e\n\u003cstrong\u003eG8N1 Renzan Prototype No. 1 Ground Vibration Test Report\u003c\/strong\u003e, 試製連山 第1號機 地上振動試驗, Japanese\u003c\/li\u003e\n\u003cli\u003e\n\u003cstrong\u003eG8N Photographic Collection\u003c\/strong\u003e, English\u003c\/li\u003e\n\u003c\/ul\u003e\u003ch3\u003eTechnical reference\u003c\/h3\u003e\u003cp\u003eThe supplied profile describes an all-metal mid-wing airframe with a high-aspect-ratio wing, laminar-flow design priorities and a single-fin tail. It identifies four Nakajima NK9K-L Homare 24 18-cylinder radial engines with a reported 2,000 hp takeoff rating and Hitachi Type 92 turbosupercharger systems, while also discussing the cooling and thermal-management challenges attributed to the tight cowl installation.\u003c\/p\u003e\u003cp\u003eReference figures supplied in the report include a maximum speed of 592 km\/h at 8,000 m, cruising speed of 360–390 km\/h, service ceiling of 10,200 m, ferry range of 7,464 km, combat radius of 3,700 km, empty weight of 17,400 kg and maximum takeoff weight of 32,150 kg.\u003c\/p\u003e\u003cp\u003eAdditional sections summarize the aircraft’s powered defensive-turret layout, post-war Allied technical evaluation of prototype FE-2210 \/ T2-2210, and a comparative discussion of the G8N and Boeing B-29 in areas including pressurization, turret control, wing architecture, bomb load and structural weight.\u003c\/p\u003e\u003ch3\u003eHistorical reference notice\u003c\/h3\u003e\u003cp\u003eThis collection is intended for aviation history, research, restoration and archival study. It is not current approved airworthiness data, operating approval, maintenance authorization or weapons guidance. The technical figures, defensive-layout descriptions and Allied-evaluation claims are reproduced as supplied archival research and have not been independently verified here. Users must verify provenance, rights, export requirements and applicability before relying on any document or report, particularly material identified as confidential or military archival material.\u003c\/p\u003e","brand":"Online Aviation Library","offers":[{"title":"Default Title","offer_id":54028548964699,"sku":null,"price":25.0,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/files\/corrected-g8n-renzan-rita-banner.png?v=1789094098"}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0955\/4788\/3867\/collections\/japanese-aviation-banner.png?v=1782815396","url":"https:\/\/onlineaviationlibrary.com\/collections\/japanese-aviation-collection.oembed?page=2","provider":"Online Aviation Library","version":"1.0","type":"link"}