Douglas DC-3 Maintenance Manual

Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions, accomplish the following: (a) Within 30 days after the effective date of this AD, accomplish the requirements of paragraphs (a)(l) and (a)(2) of this AD. Note 2: Operators should initiate action to notify and ensure that flight crewmembers are apprised of this change. (1) Revise the FAA-approved Airplane Flight Manual (AFM) by incorporating the following into the Limitations Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM. Warning Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in :freezing rain, freezing drizzle, or mixed icing conditions (super cooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane. ** During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. --Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. --Accumulation of ice on the upper surface of the wing aft of the protected area. --Accumulation of ice on the engine nacelles and propeller spinners farther aft than normally observed. AOL 3-016 AOL 4-009 Page 6 ** Since the autopilot, when installed and operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions. ** All wing icing inspection lights must be operative prior to flight into known or forecast icing conditions at night. NOTE: This supersedes any relief provided by the Master Minimum Equipment List (MMEL). (2) Revise the FAA-approved AFM by incorporating the following into the Normal Procedures Section of the AFM. This may be accomplished by inserting a copy of this AD in the AFM. The Following Weather Condition May Be Conducive to Severe In-Flight Icing ** Visible rain at temperatures below O degrees Celsius ambient air temperature. ** Droplets that splash or splatter on impact at temperatures below O degrees Celsius ambient air temperature. "Procedures for Exiting the Severe Icing Environment These procedures are applicable to all flight phases from takeoff to landing. Monitor the ambient air temperature. While severe icing may form at temperatures as cold as -18 degrees Celsius, increased vigilance is warranted at temperatures around freezing with visible moisture present. If the visual cues specified in the Limitations Section of the AFM for identifying severe icing conditions are observed, accomplish the following: ** Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated. ** Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. ** Do not engage the autopilot. ** If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot. ** If an unusual roll response or uncommanded roll control movement is observed, reduce the angle-of-attack. ** Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area. ** If the flaps are extended, do not retract them until the airframe is clear of ice. ** Report these weather conditions to Air Traffic Control." (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an appropriate FAA Operations Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. AOL 3-016 AOL 4-009 Page 7 Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) This amendment becomes effective on March 25, 1998. Issued in Renton, Washington, on February 6, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Unquote: Should additional information be required, please submit your inquiries through your local Field Service Representative or to Boeing Commercial Airplane Group - Douglas Products Division, ATTN: Technical and Fleet Support-Propulsion, Environmental, and Interiors Systems, P. 0. Box 1771, Long Beach, California 90801; SITA: TOAMD7X, ARINC: LAXMDCR, Telex 674357, FAX: (562) 593-7710, or call (562) 593-7268. THIS AOL IS FOR ADVISORY PURPOSES ONLY. NO FAA APPROVAL IS REQUIRED. ACH:mp (NAA) J-M-d. e. . ~ Fred C. Haas Director Technical AND Fleet Suport Service Engineering Customer Division AOL ALL OPERATOR LETTER PRODUCT SUPPORT ~BOEING McDonnell Douglas Corporation (MDC), a wholly owned subsidiary of The Boeing Company, proprietary rights are included in the information disclosed herein and recipient, by accepting this document, agrees that the information is proprietary to MDC. MDC authorizes recipient to reproduce such information for internal use only. To: Subject: Applicable To: Reference: March 5, 1998 L30-017-98/AOL 3-112-0 4-112-0 6-112-0 7-112-0 8-112-0-0 9-112-00-0 90-112-00-00 10-112-00-00 11-112-00-00 AOL3-015 AOL4-008 AOL6-011 AOL 7-008 AOL8-1248 AOL9-2564 AOL90.,083 AOL 10-2214 AOL 11-464 All DC-3, DC-4, DC-6, DC-7, DC-8, DC-9, C-9, MD-80, MD-90, DC-10, KC-10, KDC-10, AND MD-11 OPERATORS MANUFACTURE OF FEDERAL AVIATION ADMINISTRATION (FAA)-APPROVED REPLACEMENT PARTS All DC-3, DC-4, DC-6, DC-7, DC-8, DC-9,C-9, MD-80, MD-90, DC-10, KC-1 0A, KDC-10, and MD-11 Airplanes (a) Federal Aviation Regulation (FAR) Part 21, Subpart K - Approval of Materials, Parts, Processes, and Appliances (b) FAA Advisory Circular No. AC 20-62D, Eligibility, Quality, and· Identification of Aeronautical Replacement Parts (c) FAA Advisory Circular No. AC 21-29A, Detecting and Reporting Suspected Unapproved Parts 3855 Lakewood Blvd., Long Beach, CA 90846-0001 (562) 593-5511 TELEX 67-4357 REASON AOL3-015 AOL4-008 AOL6-011 AOL 7-008 AOLS-1248 AOL9-2564 AOL90-083 AOL 10-2214 AOL 11-464 Page2 SEVERAL OPERATORS HAVE REQUESTED CLARIFICATION ON CERTAIN TERMINOLOGY USED BY BOEING DOUGLAS PRODUCTS DIVISION (DPD) WHEN TRANSMITTING TYPE DESIGN DATA TO OWNERS, OPERATORS, AND LICENSEES, AND REGULATORY REQUIREMENTS FOR AIRWORTHINESS OF PARTS MANUFACTURED BY THEM. Boeing may provide type design data to its airline customers and to licensees to support the fleet when replacement parts are not available directly from Boeing in a timely manner. The process of providing type design data to Boeing's airline customers and licensees has been known as Authority To Manufacture (ATM). The ATM process does not imply that Boeing approves any parts manufactured by airline customers or licensees. Boeing may grant authorization to owners, operators, and licensees to use Boeing type design data, but Boeing does not, and cannot, grant authority to manufacture aircraft replacement parts. The United States (US) Federal Aviation Administration (FAA) grants authority to manufacture aircraft replacement parts for US type certificated aircraft (reference [a]). Reference (a) also exempts owners and operators from the requirements to produce modification or replacement parts pursuant to FAA Parts Manufacturer Approval (PMA) when maintaining or altering the owner's or operator's own type certificated aircraft (ref. FAR section 21 l.303[b][2]). Sections 91.403, 121.363, and 125.243 of the FAR place the responsibility for airworthiness of the type certificated product (aircraft, aircraft engines, propellers) on the owner or operator. Airworthiness for United States operators is defined in Public Law 103-272 as conforming to the (approved) type certificate, and being in a condition for safe operation. Boeing Provided Type Design Data: Type design data, as an element of the type certificate, is FAA-Approved. Boeing's type certificates are elements of Boeing's FAA-Approved Production Certificate (PC). Boeing produces parts in accordance with PC requirements (reference FAR Part 21, Subpart G - Production Certificates). Mere possession of Boeing type design data, including detail drawings, specifications, and other data, does not imply that Boeing approves the recipient as a supplier pursuant to Boeing's PC. The manufacture of parts using Boeing type design data, unless accomplished expressly in accordance with the requirements of Boeing's PC, is to be considered outside of Boeing's control and responsibility. Boeing assumes no responsibility for the quality, or the airworthiness of owner, operator, or licensee manufactured parts. Parts Marking: AOL 3-015 AOL4-008 AOL 6-011 AOL 7-008 AOL 8-1248 AOL9-2564 AOL90-083 AOL 10-2214 AOL 11-464 Page3 Boeing identifies parts in accordance with the provisions of its PC. FAR section 43.9 requires a maintenance record entry of the work performed, which only implies owner, operator, and licensee produced parts be identified as such. Marking requirements for parts for which a replacement time, inspection interval, or related procedure is specified in the Airworthiness Limitations section of the manufacturer's maintenance manual or Instructions for Continued Airworthiness are cited in FAR section 45.14. There is no specific regulatory requirement to mark owner, operator, or licensee manufactured parts as not manufactured by an FAA production approval holder. Once owner or operator or licensee produced parts are installed on the aircraft, they are in the stream of commerce, and if marked as if produced under an FAA-Approved production system (that is, with part numbers identical to those used in the FAA-Approved production system), might possibly be considered fraudulent (reference [a]), section 43.12). The commission by any person of an act prohibited under Section 43.12(a) is a basis for, among other things, suspending or revoking the applicable airman, or operator certificate held by that person. Owner or operator manufactured parts, for those owners or operators holding Boeing Purchase Agreement (contract) are required, by the terms of that agreement, to be marked with a part number different from the original Boeing part number to identify that the parts so produced are the product of the owner or operator, and not of Boeing. Should additional information be required, please submit your inquiries through your local Field Service Representative or to Boeing Commercial Airplane Group, ATTN: Contract Data Management, P. 0. Box 1771, Long Beach, California 90801; SITA: TOAMD7X, ARINC: LAXMDCR, Telex 674357, FAX: (562) 593-2001, or call (562) 496-9621. THIS AOL IS FOR ADVISORY PURPOSES ONLY. NO FAA APPROVAL REQUIRED. MEF:cr (NAA) F. C. Haas Director Technical and Fleet Support Service Engineering Customer Division AN 01-40NK-2 _Handb.oo-½.:i,::; ..,.:~ ,,r..,, . ·,._ • •C :, NAVY' MODELS. f,_ R·4D~8 x.R4D-8Z., ·,. . ',;) ' ;_ \': . . ·, AIR·CR/i.Fpf:· .. THIS PUBLIGft;~}bN SUPERSEDES AN 01-40NKs2 i DATED 15 M-AY ·1)952 REN IS ED 15 DECt:MrJER, 1952 ( . . . ' ' .., ·t ~. ,,,.., : • • ,1·~t··· NOTE, s1\,~R't:~'0E AN. otA<3~l-',K~2. sERv1c~ 1r-t$tftup:i]c>N:s.cFoR ,· · .·. MbD.~L~'g2\~~i~¥oitNGl~_ES,. SHO ~·:·.. "' J~ilr;'E;~:ivi/1.:f1}•.:\:;,·:' • )· ·, SECTION. V OF THIS. :HA B0t::lf<'1 .. · , ~~ ,:,. . ·) :''! 3_.:.f·t-~·- .:,:•..2~:~·· ' . · Pususl-lEo· uND:E~ d\MJ~O~rrx:: :PF. brHE sECRETARY pf.. TH,E ~t~ .. rqifo~ ., AND THE" CHtE:F ·'elf '·THE BUREAll-'<iftAE.RONAunn:s ._,,_,_,.: ·" .. . ,._~ ·. -~ 1·· • "':. Jf!::. ; .''.-. 15 April 195 3' A AN 01-40NK-2 Reproduction for non-military use of the information or illustrations contained in this publication is not permitted without specific approval of the issuing service ( BuAer or AMC). The policy for use of Classifie<l Publications is established for the Air Force in AFR 205- I and for the Navy in Navy Regulations, Article 1509. LIST OF REVISED PAGES ISSUED INSERT LATEST REVISED PAGES. DESTROY SUPERSEDED PAGES. ;-s.;OTE: The portion of the text affecced by the current re,·ision is indicated by a \'ercical line in the ourer margins of the page. ,:, The asterisk indicates pages revised, added or deleted by the current revision. ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED AS FOLLOWS: USAF ACTIVITIES.-In accordance with Technical Order No,: 00-5-2. NAVY ACTIVITIES.-Submit request to nearest supply point listed below, using form NavAer-140: NASD, Philadephia, Pa.; NAS, Alameda, Calif.; NAS, Jacksonville, Fla.; NAS, Norfolk, Va.; NAS, San Diego. Calif.; NAS, Seattle, Wash.; ASD, NSC, Guam. BuAer For listing of available material and details of distribution see Naval Aeronautics Publications Index Na\'Aer 00-500. AN 01-40NK-2 Table of Contents TABLE OF CONTENTS Page No. INTRODUCTION .......................................................... m SECTION I -GENERAL INFORMATION General Description ............................................. . 1 Aircraft Balance ................................................... . 1 Aircraft Dimensions .............................................. 1 Leading Particulars ................................................ 4 Access and Insp~ction Provisions ........................ 9 Ground Operat10n ................................................ 9 Ground Handling .................................................. 21 Servicing Aircraft ............. ..................................... 36 Lubrication Requirements .................................... -45 Special Tools and Handling Equipment ............. 45 SECTION II - AIRFRAME GROUP Airframe Group ...................................................... 67 Wing Group .......................................................... 74 Empennage .............................................................. 79 Surface Controls .................................................. .. 83 Fuselage .................................................................... 180 Alighting Gear ...................................................... 205 Airframe Group Bolt Torque Values .................. 241 SECTION Ill - HYDRAULIC AND PNEUMATIC SYSTEMS Hydraulic System .................................................. 245 Hydraulic System Bolt Torque Values ................ 260 Pneumatic System .................................................. 260 SECTION IV - UTILITY SYSTEMS Heating and Ventilating System ........................ 263 Accessory Anti-Icing Systems .............................. 284 Surface De-Icing System ...................................... 293 Windshield Wiper System .................................... 308 Oxygen System ...................................................... 311 Fire Extinguisher and Detection Systems .......... 317 Pyrotechnics ............................................................ 333 Utility System Bolt Torque Values ...................... 334 SECTION V - POWER PLANT AND RELATED SYSTEMS Page No. Power Plant ............................................................ 337 Fuel System ............................................................ 346 Oil System .............................................................. 376 Ignition System .............................. ........................ 387 Engine Starting System ........................................ 393 Air Induction and Exhaust Systems .................. 398 Propellers ................................................................ 403 Engine Cooling System ................................. :........ 409 Power Plant Controls .......................................... 413 Power Plant and Related Systems Bolt Torque Values ·········································.'·········· 449 ·SECTION VI - INSTRUMENT SYSTEMS Instrument Systems ................................................. 4 53 Pitot-Static System .................................................. 460 Warning Systems .................................................... 463 Automatic Pilot System ........................................ 464 SECTION VII - ELECTRICAL SYSTEM Electrical System ····························~······················· 481 SECTION VIII - RADIO AND RADAR Electronic System ................................_.................... 5:l5 SECTION IX - ARMAMENT AND PHOTOGRAPHIC EQUIPMENT ............................ 551 SECTION X-WIRING DATA Wiring Data ALPHABETICAL INDEX 555 637 AN 01-40NK-2 Introduction INTRODUCTION This publication covers maintenance instructions for the R4D-8 aircraft manufactured by the Douglas Air- craft Company, Inc., Santa Monica, California, under contract NOa(s) 51-012. This Maintenance Handbook contains essential information required for field main- tenance and service of the complete airframe, as well as for engines, accessories, and instruments installed in the aircraft. Instructions included in this handbook are applicable to R4D-8 aircraft as delivered. For additional informa- tion concerning the R4D-8 aircraft, consult the follow- ing publications: Handbook of Flight Operating Instructions ______________________________________ AN 01-40NK-1 Handbook of Structural Repair Instructions ___________________ :__________________ AN 01-40NK-3 Illustrated Parts Catalog ____________________ AN 01-40NK-4 --· Handbook of Inspection Requirements ____________________________________ AN 01-40NK-6 Handbook of Weight and Balance __________ AN 01-1-40 Handbook of Cargo Loading Instructions ____________________________ NavAer 0l-40NK-509 The following practices have been applied in prep- aration of the text for this handbook: Right and left, clockwise and counterclockwise, upper and lower, and similar references apply to the aircraft as viewed from the rear of the aircraft center line, looking forward. Pagination throughout this handbook is continuous with information contained herein divided into sec- tions numbered consecutively in capital Roman numer- als. The sections, in turn, are divided into paragraphs numbered consecutively with each section utilizing Arabic numbers separated by a dash. The number pre- ceding the dash indicates the section (converted from Roman to Arabic) with the number following the dash indicating the paragraph within the section. As an example, "5-4" would be the fourth paragraph of Section V. Illustrations are identified by figure number and title positioned beneath each illustration. Figures are num- bered consecutively within each section, similar to the manner of paragraph numbering. For example, "-t-15" represents the fifteenth illustration in Section IV. The Table of Contents lists the major divisions of the handbook together with related page number and par- agraph sequence. In addition, a Table of Contents pre- cedes each section to identify the material containec therein. The Alphabetical Index lists both the text and illus- tration coverage of this handbook by subject matter arranged in alphabetical order, together with the re- lated page number. For ease in reference, illustration: have been listed in italics. The aircraft described in this handbook may be identi• fied by the following Effectivity Coding Chart: Aircraft Bu A er No. Serial No. A ---------------------- 17175 B ---------------------- 39097 C _____________________ 12412 D ---------------------- 17103 1 ______________________ 17273 2 ---------------------- 17111 3 ---------------------- 12422 4 ---------------------- 17177 5 _____________________ 17116 6 ---------------------- 50762 7 ---------------------- 17171 8 ---------------------- 17124 9 ---------·-···-·------ 17150 10 ---------·------------ 12420 11 ---------------------- 39109 12 ---------------------- 12445 13 ---------------------- 39087 14 ---------------------- 12419 15 ---------------------- 50823 16 ---------------------- 17255 17 ---------------------- 12438 18 -----·---------------- 50804 19 ---------------------- 50835 20 ·------------·-··----- 50821 21 ··---------------·---- 17219 22 ··---------------·---- 50834 23 ---------------------- 39104 24 --------·-···--------- 39071 25 --·-··--·------------- 12443 26 ---------------------- 12439 27 ------------···------- 50838 28 ------------·--------- 17102 Aircraft No. B11Aer Serial No 29 ----------------- 30 ---------------------- 31 ---------------------- 32 ---------------------- 33 ---------------------- 34 ---------------------- 35 --------------------- 36 ----------------- 37 ------------------ . 38 ---------------------- 39 ---------------------- 40 ---------------------- 41 ---------------------- 42 --------------------·· 43 44 45 46 ---------------·---- _ 47 48 49 50 51 52 53 54 55 56 57 58 59 60 17160 99857 1712_1 17216 17122 17127 50772 39096 99853 17098 17165 17156 17241 39061 1715.'1 17179 17166 12410 50833 17169 12440 17194 12435 39080 39084 50801 17196 50812 17281 39070 50796 99845 Introduction Aircraft No. 61 62 6_', 64 65 66 67 68 69 .. iv BuAer Serial No. 50826 17152 17190 50782 17284 17158 I 7108 12428 17097 AN 01-40NK-2 Aircraft _"f\·o. BuAer Serial No. 70 ...................... 17287 71 17154 -, ................ [7248 -_,, ...................... !7[82 -:-4 ················ 39064 "'5 ··········-···· 1725.'1 76 17[ [9 17[9[ 78 50784 Aircraft No. BuAer Serial No. 79 ··---·-·-··--·-···---· 17092 80 _',90 72 8[ 17149 82 17188 8', 17[40 84 50786 85 1727() 86 508_,6 87 ... [244[ Aircraft No. BuAer Serial 1"\.' o. 88 ······--·············· 17258 89 172[1 90 17242 9[ 124_',7 92 50808 9', [2451 94 P''" -·L1 95 .W08l 9(, 5078(·) A AN 01-40NK-2 Section I Reproduction for non-military use of the information or illustrations contained in this publication is not permitted without specific approval of the issuing service ( BuAer or AMC). The policy for use of Classified Publications is established for the Air Force in AFR 205-1 and for the Navy in Navy Regulations, Article 1509. LIST OF REVISED PAGES ISSUED INSERT LATEST REVISED PAGES. DESTROY SUPERSEDED PAGES. NOTE: The portion of the text affected by the current revision is indicated by a vertical line in the outer margins of the page. * The asterisk indicates pages revised, added or deleted by the current revision. ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED AS FOLLOWS: USAF ACTIVITIES.-In accordance with Technical Order No. 00-5-2. NAVY ACTIVITIES.-Submit request to nearest supply point listed below, using form NavAer-140: NASD, Philadephia, Pa.; NAS, Alameda, Calif.; NAS, Jacksonville, Fla.; NAS, Norfolk, Va.; NAS, San Diego, Calif.; NAS, Seattle, Wash.; ASD, NSC, Guam. BuAer For listing of available material and details of distribution see Naval Aeronautics Publications Index NavAer 00-500. AN 01-40NK-2 Section I SECTION I GENERAL INFORMATION TABLE OF CONTENTS GENERAL DESCRIPTION AIRCRAFT BALANCE Page No. 1 GROUND HANDLING ............. . · Page No. 21 AIRCRAFT DIMENSIONS ........................................ . Description ......................................................... . Wing Group ........................................................... . Horizontal Tail Surfaces ................................. . Vertical Tail Surfaces ........ . .................. . Fuselage LEADING PARTICULARS 1 1 1 1 1 -± 4 4 Alighting Gear .......... ............ ..................... 4 Engines ........................ .. ... ................ -i Propellers ............................ . .................... . -i Tank Capacities ...................................................... 4 ACCESS AND INSPECTION PROVISIONS .............. 9 Interior Access Doors . ........ . ............ .................... 9 Exterior Access Doors Drain and Vent Holes ...... . 9 9 GROUND OPERATION.............................................. 9 Engine Operation ................................................. . Cowl Flaps ........................................................... . Prin1ing ................................................................... . Excessive Priming ................................................. . Insufficient Priming ............................................... . Backfiring ............................................................... . Over-Rich Mixture ................................................. . 9 9 9 9 9 9 9 Fuel Booster Pumps ................................................ 9 Fuel Overloading ................................ ................... 9 Idling .................................................. ..................... 18 Piston Hydraulicking ............................................ 18 Fuel System Management ....... .............................. 20 Fuel Booster Pump Check .................................... 20 Fuel Tank Selector Valve Check .......................... 20 Engine Starting Procedure ................................... . 20 Propeller Feathering Checks ................................. . 20 Propeller Feathering Procedure for Ground Operation .............................................................. 20 Ground Fire Control .............................................. 20 Engine Section Fire ................................................ 20 Combustion Heater Compartment Fire .............. 20 Fire Warning Circuit Test Switches.................... 20 Engine Run-Up ...................................................... 21 Hoisting........................................... ................. . Jacking......................................... . ......... . Leveling .................................................................. . Mooring .................................................................. . Parking ................................ . Towing .............................. . Taxiing .................................. . SERVICING AIRCRAFT Servicing Provisions ................ . Fuel Servicing ..................................... . Fuel Tanks. . ....... . Filling Fuel Tanks .. ........... ................ . Draining Fuel Tanks and Sumps ..................... . Filling Oil Tanks ................................................... . Draining Oil T aoks .............................................. . Filling Alcohol Tank .......................................... . Filling Water Supply Tank (Aircraft 1 through 96) ........................................ ··· ············· Filling Water Supply Tank (Aircraft A through D) ..................................................... . Draining Water Supply Tank (Aircraft 1 through 96) ......................................................... . Draining Water Supply Tank (Aircraft A through D) ......................................................... . Filling Hydraulic Reservoir ............................... . Draining Hydraulic Reservoir ............................. . Inflating Maio Pressure Acetimt,lator ................. . Inflating Main Gear Shock Strut ......................... . Inflating Tail Gear Shock Strut ......................... . Filling Maio Gear Shock Strut ........................... . Filling Tail Gear Shock Strut. , ............................ . Inflating Maio Gear Tires ..................................... . Inflating Tail Gear Tire ....................................... . Filling Batteries ..................................................... . Servicing Hand Fire Extinguishers ..................... . Charging CO~ Cylinders ....................................... . Charging High-Pressure .Oxygen Cylinder ....... . Charging Brake Emergency Air Cylinder ......... . Servicing Toilet ..................................................... . Cleaning Aircraft Exterior .................................. •· Cleaning Aircraft Interior ................................... . LUBRICATION REQUIREMENTS ............................... . SPECIAL TOOLS AND EQUIPMENT ....................... . 40 40 40 40 41 41 41 41 42 43 43 43 43 43 43 44 44 45 45 45 45 45 45 V Section I AN 01-40NK-2 r---------------------------------------------.M vi ,_ V, Q' I.II 0 . - AN 01-40NK-2 Section I Paragraphs 1-1 through 1-11 SECTION I GENERAL INFORMATION 1-1. GENERAL DESCRIPTION. 1-2. The R4D-8 and R4D-8Z aircraft are low-wing monoplanes with full cantilever wings and tail sur- faces, semi-monocoque fuselage, and retractable alight- ing gear. Aircraft 1 through 96 are designed for use as diversified personnel, cargo, or ambulance trans- ports; aircraft A through D are designed for use as staff transports. The aircraft are pov,•ered by t'\VO R-1820-80 engines which are equipped with Hamilton Standard hydromatic propellers. For graphic presen- tations of the aircraft and the aircraft stations, see figures 1-1 through 1-7. 1-3. In aircraft I through 96, accommodations are provided for a regular crew of 1 three: pilot, co-pilot, and radio operator. Folding troop benches are installed along both sides of the main cargo compartment to accommodate 35 troops. Thirty collapsible high-den- sity personnel seats can be installed in place of the folding-type troop benches. Litters can be installed as an alternate to the folding benches or personnel seats, to accommodate 27 ambulance patients ( see figure 1-H). 1-·L In aircraft A through D, the interior arrange- ment, forward of station 97, is identical to aircraft 1 through 96. Aft of station 97, a table, desk, buffet, and a lavatory are installed for staff use. On aircraft A and B, 4 divans and 4 reclining swivel chairs are also installed, aft of station 97; on aircraft C and D, 2 divans and 8 reclining swivel chairs are,installed, aft of station 97. Two bunks are installed in the aft part of the fuselage, between stations 538 and 623, for the use of 2 crew members: for interior arrangement, see figure 2-40. 1-5. The weight empty of the aircraft is approxi- mately 20,400 pounds. The design gross weight is 31,000 pounds, and the overload gross weight is 36,800 pounds. For further information, refer to the applica, ble handbook of weight and balance instructions. 1-6. AIRCRAFT BALANCE. 1-7. The forward limit of the cg travel, with the alighting gear retracted, is 7 per cent of the MAC and the aft limit is 36 per cent of the MAC. The forward limit of the cg travel, with the alighting gear extended, is 10 per cent of the MAC and the aft limit is 37 per cent of the MAC. 1-8. AIRCRAFT DIMENSIONS. 1-9. DESCRIPTION. Span ...... 90 feet 0 ..'\ inch Length ( overall ) Height ......... . ........................ 6- feet 8.'i inches .18 feet :\ inches 1-10. WING GROUP. Span: Ailerons ( each side) ..................................... 277.0 inches Flaps ( each side) ........................................... 261.5 inches Areas: Wings ( gross. including ailerons) ...... 967.1 square feet Ailerons ( total, aft of hinge line) ........ 71." square feet Flaps ( total, both sides)............ 92.5 square feet Aileron trim tab, geared (each side) .. 2.7 square feet Chords: Wing: Chord at root (theoretical) ...................... 170.0 inches Chord at tip (theoretical) ........................ 57.0 inches Flap: Chord .......................................................... 25.5 inches Aileron: Chord ( average aft of hinge line, per cent chord line) ...................... 15.6 degrees Wing taper ratio ( outer panel) .................................... O..H7 Wing incidence at zero lift line: Root ....................................................... -.!-4 degrees Horizontal station I-i1.0 ................................. +4 degrees Tip ................................................................. +0.2 degree Wing dihedral. outer panel ( reference plane) .. 6.8 degrees Wing sweepback, outer panel ( 2 5 per cent chord line) .............................. 15.6 degrees Wing aspect ratio ............................................................ 8 ..~8 Wing MAC ......................................... 1.19.7 inches 1-11. HORIZONTAL TAIL SURFACES. Span .............................................................. .18 feet O inches Areas: Horizontal surface (gross) .................. 289.5 square feet Horizontal stabilizer ( total less movable surface area) ................ 158.5 square feet Elevator ( total, aft of hinge line) ........ 95.0 square feet Control tab ( both sides)...................... 7.8 square feet Trim tab ( both sides).......................... 9.4 square feet Chords: Root (theoretical) ........................................ 131.0 inches Tip (theoretical) .......................................... 52.5 inches Dihedral ............. ................................................. O degrees Sweepback ( 25 per cent chord line) .................. 7.5 degrees Aspect ratio .................................................................... 4.99 Horizontal stabilizer incidence of zero lift line .... O degrees 1 Section I AN 01-40NK-2 2 f.-------OVERALL LENGTH 67 FT. 8.5 IN. (812.5 IN.J ____ FUSELAGE REFERENCE PLAN:.::]__ -= 3 1N- ' . ('2'q 1N) \ . - -- ------ STATIC GROUND LINE ~::...________ 450 IN.----J •--- TAIL SPAN 38 FT. (456 IN.) --j 52.5 ~~__.__:..11 9 .87 5 ! i-----,..284 IN.---i-----398 IN.--------1 ' 60 IN. T 2 DEGREES - 1------------WING SPAN 90, FT. (1080.3 IN.)------------1 FUSELAGE REFERENCE PLANE r-FLAT TIRE / CONDITION PLANE figure 1-2. Three-View of Aircraft 1,104 AN 01-40NK-2 ,_ N C> _,..., ' ..., ;;:, C"',I \\ C") .\:\ \~_,_., ... ..., ~~~~ - - 0 .......·- c:t: - 0 :I:Cl) ·- > "'0 Cl) "'0 0 0..)( Lu C'?.-Cl) ..:::i 0) ·- ... 3 AN 01-40NK-2 Handbook Maintenance Instructions NAVY MODELS R4D-8, R4D-8Z AIRCRAFT SECTIO I GE ERAL I FORMATIO THIS SECTION SUPERSEDES SECTION I OF AN 0l-40NK-2 DA TED 15 MAY 1952 REVISED 1 NOVEMBER 1952 PUBLISHED UNDER AUTHORITY OF THE SECRETARY OF THE AIR FORCE AND THE CHIEF OF THE BUREAU OF AERONAUTICS 15 April 195 3 Section I AN 01-40NK-2 Paragraphs 1-12 through 1-18 I. Nose Cover-Upper Section 2. Nose Cover-Lower Section 3. Outer Wing Tip 4. Aileron 5. Aileron Trim Tab 6. Outer Wing Panel 7. Outer Wing Flap 8. Auxiliary Exit ( 4) 9. Main Cargo Door ( Aircraft l through 96) 10. Fuselage 1 I. Dorsal Fin 12. Vertical Stabilizer 13. Rudder Key to Figure 1-3 14. Rudder Tab l 5. Tail Fairing Assembly l 6. Elevator Spring Control Tab 17. Elevator Trim Tab 18. Elevator 19. Horizontal Stabilizer 20. Horizontal Stabilizer Fairing 21. Tail Wheel Assembly 22. Main Cabin Door ( Aircraft A through D) 2.'\. Center Wing 24. Wing•to•Fuselage Fillet 25. Center Wing Flap 26. Aileron Spring Control Tab 27. False Rib 28. Main Gear 29. Main Gear Doors 30. Engine Mount :\ I. Inner Ring 32. Accessory Cowling Outboard Section :\3. Cowl Flaps 34. Anti•Drag Ring Outboard Segment 35. Anti•Drag Ring Bottom Segment 36. Propeller 37. Anti.Drag Ring Inboard Segment 38. Accessory Cowling Bottom Section 39. Accessory Cowling Inboard Section 40. Service Door 1-12. VERTICAL TAIL SURFACES. Tail wheel gear (Co11ti11ued): Span ................................................................... 174.0 inches Areas: Vertical surface ( total exposed excluding dorsal fin) ........................ 103.8 square feet Fin ( total exposed, excluding dorsal fin) .......................................... 5 :\.9 square feet Rudder ( aft of hinge line) .................. 36.8 square feet Trim tab, geared .................................. 4.0 square feet Chords: Root (theoretical) ........................................ 127 .6 inches Tip (theoretical) .......................................... 67.6 inches Sweepback ............................................................ 7.5 degrees 1-13. FUSELAGE. Height ( maximum cross section) ........................ 106 inches Width ( maximum cross section) ........................ 97.3 inches 1-14. LEADING PARTICULARS. 1•15. ALIGHTING GEAR. 4 Main gear-standard: Type .......................... Hydraulically actuated, retractable, dual•shock strut Tread ...................................................... 18 feet 6 inches Wheel base .............................................. 37 feet 9 inches Shock strut .................... Oleopneu.natic, Douglas 2390420 Fluid required ............................................ MIL·O•5606 Wheels ................ 17.00 x 16, Type III, Goodyear 9540547 Tires .................................. 17.00 x 16, 12•ply rating, nylon Goodrich or equivalent Tire pressure for maximum take.off gross weight ...................................... 60 psi Brakes ........................................ Goodyear, single.disc, spot Tail wheel gear: Type ............................ Hydraulically actuated, retractable Shock strut .................... Oleopneumatic, Douglas 3367199 Fluid required ........................................... MIL•O•5606 Wheel.. ............ 9.00 x 6, General 20-t·A·204M• 1, Firestone XSO 200 FM, Goodrich B·:\•648. Bendix 52058 Tire ...................................... 9.00 x 6, l 0•ply rating, nylon: Gocdrich or equirnlent Tire pressure .......................................................... 7() p,i 1-16. ENGINES. Number ............ ................................... 7 Type .................. Wright•Cyclone R• I 820~so:·9:~;:i;~·d~;:·~i;: cooled radial, single•specd supercharger Propeller•to•engine gear ratio .................................. 0.5625: 1 Engine supercharger gear ratio ................................... 7.21: 1 Fuel specification .................... MIL·F•55 72, Grade l 00 / l 30 Fuel specification, alternate permissible ............ MIL·F•5572, Grade 115/145 Oil specification ........ MIL·O·6082, Grade 1100 ( summer and winter) l•l 7. PROPELLERS. Type .................................... Hamilton Standard Hydromatic Hub ................................................................................ 23E50 Blade type .................................................................. 66 ! 5A·0 Diameter .............................. 11 feet 6¼ inches ( ± ¼ inch) Number of blades .............................................................. 3 Propeller settings at station 42.0 t~;h P;~~;h ·:::::::::::::::::::::::::::::::::::::::::::::::::::::::::~.~ ..~~~~e:; Feather .............................................................. 88 degrees 1-18. TANK CAPACITIES. Fuel tanks: Front ( 2, left and right) ........ 202 US. Rear ( 2, left and right) ........ 200 US. Outer wing ( 5, left and ( 168.19 Imp.) gallons each (166.52 Imp.) gallons each right) ........... .411 US. ( 342.20 Imp.) gallons each set Total... ... : ........... 1626 US. ( 1353.81 Imp.) gallons (Continued on Page 9) AN 01-40NK-2 Sedion I 703 733 664 690 718 609, o36 /677 553 583 1623 651 465 492 521 g39 , 568 I5r6. I 749 773 390 429 450 I4191516 I I I351 411 I I 312333 312 I 234 258 138 156 216 177 195 47 10 OPERATOR'S AND NAVIGATOR COMPARTME AIRCRAFT A THROUGH D 273294 figure 'I -4. fuselage Stations 5 117 138 CKPIT > J,f CREW'S COMPARTMENT 156 177 623 6 195 216 234 258 10 OPERATOR'S AND NAVIGATOR'S COMP ART ME 312 333 273294 390 411 351 372 609 636 553 58~96 623 492 520 568 465 506 538 429450 479 AIRCRAFT 1 THROUGH 96 LAVATORY COMPARTMENT , 07 °' m _: ~,..... ,... ,... 00 ;:: 0 m N °' \D "' ,... N N NACELLE STATIONS (TYPICAL LH AND RH) ~ N ,... m FUSELAGE ST A 222 ' CENTER LINE ()F AIRPLANE IIOAltD WING FLAP H SHOWN; H OPPOSITE) ' ~' ' _,21 ... , -'42 .. ~..:,.. ,)FUSELAGE ST A 362 J ~ "'--FRONT SPAR LEADING EDGE OF NOSE SECTION FUSELAGE STA 192 Figure 1-5. Wing Center Section and Nacelle Stations 1,10111 "' II Q. c;· :::s ► z e - Ji. e z ~ i,..) OUTER WING FLAP OUTER WING PANEL CENTER SPAR ~ / / '""'¼. O 17 / / 35 53 / / 71 9 / / ;-... REAR SPAR 8 107 / / 125138 / / "'Ii. . 3 --------- I 7 -------- 35 --------- 5 3 --------- 72 AILERON TRIM TAB ---- 89 ------ I 07 ------ 119 121 130 140 147 ------Jr_ 12P26 /r- 132 ~ 139 ~4 155 - ---i;7 180 ~O 20 I 154 162 170 -- 179 ...._ ~---;; 2 222 . - ---;34 244 - ------;55 266 -------;77 287 - -----;96 306 - ~6 326 .---------;36 3 45 152165 / /"" 179 192 206// / 219 232 / / "" VIEW OF LEFT OUTER WING PANEL, OUTER WING FLAP, AILERON, AND TRIM TAB (RH OPPOSITE) 245 / / 259 272 / / 286 300 / 315 Figure 1-6. Wing Outer Panel Stations ----------;55 364 ---..--------;74 383 ---~96 ,/ OUTER WING TIP 1,109 )> z 0 ...I ~ 0 z "I 1-J VI (1) !l. o·:I Section I VERTICAL STABILIZER 0 8 STABILIZER, LH VERTICAL ND TABS ELEVATORR: OPPOSITE SHOWN - Figure AN 01-40NK-2 27. 1932 43 64 84 102 115 218 N TAL STABILIZER HORIZO Stations 1-7. Empennage 134 -133 ELEVATOR 155 175 RUDDER TRIM TAB ELEVATONRTROL TAB CO 196 216 224 . 228 AN 01-40NK-2 Section I (Continued from Page -I) Oil tanks: Nacelle ( 1 for each engine l. ... 27•¾ US. ( 23.11 Imp.) gallons each Total ...................... 551/! US. ( 46.21 Imp.) gallons Hydraulic fluid: Fluid ......................................... Specification MIL-O-5606 Total system capacity ........... 6 US. ( 5.0 Imp.) gallons Reservoir capacity .............. 2.3 US. ( 1.91 Imp.) gallons Reserve ................................ 3.2 US. ( 2.67 Imp.) gallons Anti-icing alcohol tank: Fluid ............................. .Isopropyl alcohol conforming to Specification MIL-F-5566 Tank capacity .................... 20 US. ( 16.65 Imp.) gallons Water tank: Wash basin supply ( aircraft 1 through 96) .............................................~ US. ( 2.5 Imp.) gallons Lavatory and buffet supply ( aircraft A through D) 2 tanks ....... 7 US. ( 5.83 Imp.) gallons each Total .......................... 14 US. ( 11.66 Imp.) gallons 1-19. ACCESS AND INSPECTION PROVISIONS. 1-20. INTERIOR ACCESS DOORS. (See figure 1-9.) Access doors and cover plates are provided in the in- terior structure of the aircraft to facilitate inspection, maintenance, and repair of controls, system compo- nents, and structural sections. 1-21. EXTERIOR ACCESS DOORS. (See figure 1-9.) Access doors and cover plates are provided in the ex- terior surfaces of the wing, nacelle, fuselage and em- pennage to facilitate inspection, maintenance, and general repair. 1-22. DRAIN AND VENT HOLES. (See figure 1-10.) Draining provisions are installed throughout the wing and fuselage structures for servicing the various fluid systems. Drain holes are provided in the flight control surfaces to permit the escape of condensation. Vent holes are provided for those systems requiring a supply of air for proper operation. 1-23. GROUND OPERATION. 1-24. ENGINE OPERATION. 1-25. COWL FLAPS. The cowl flaps must be fully open, regardless of outside air temperatures, during all ground operations, including starting, warm-up, ground testing, and taxiing. 1-26. PRIMING. The priming system functions as an aid in starting the engines and, when used properly, reduces the haLard of flooding. To avoid overloading a warm engine, 15 °C ( 59°F) or more, it is advisable to flick the primer switch intermittently. The actual amount of priming necessary will depend upon the engine installation, weather conditions, and air tem- peratures. Do not prime until the starter is actually cranking the engine. 1-27. EXCESSIVE PRIMING. Excessive priming will load the cylinders with raw fuel, making starting Paragraphs 1-19 through 1-32 difficult and tending to wash the oil film from the cylinder walls with the consequent danger of cylinder scoring or piston seizure. If the engine is allowed to stand for a day or more following unsuccessful at- tempts to start the engine, and if the cylinder surfaces are not protected by a fresh application of oil, rusting of piston rings and cylinder walls will frequently occur. Continuous use of the primer may cause the fuel to drain back through the intake pipes of primed cylinders and collect in the intake pipes of bottom cylinders without indication of fuel leakage from the supercharger drain valve. The drain valve will not indicate fuel collection forward of the supercharger impeller, or in the lower intake pipes, since it drains only from the area of the impeller inlet in the rear supercharger housing. 1-28. INSUFFICIENT PRIMING. Insufficient prim- ing during the starting operation is usually indicated by backfiring, with attendant fire hazards. Cold- weather starting requires more priming and a slightly greater throttle opening than would be required when starting in moderate or warm weather. 1-29. BACKFIRING. When an engine backfires, in- dicating too lean a mixture, it is recommended that the priming system be used to assist in keeping the engine running until fuel from the carburetor reaches all cylinders. In the event of backfiring, do not shut down, but continue cranking with the starter until backfiring ceases and the engine is running. 1-30. OVER-RICH MIXTURE. An engine receiving too rich a mixture to continue running during a start, can be revived by momentarily moving the mixture control to the IDLE CUT-OFF position. This will lean out the mixture, after which the mixture control should be returned to the AUTO-RICH or FULL-RICH position. 1-31. FUEL BOOSTER PUMPS. The engine must be started with the booster pumps ON. Refer to the applicable handbook of flight operating instructions for recommended use. 1-32. FUEL OVERLOADING. Overloading of a warm engine may be indicated by a dischar&e of fuel from the drain in the lower part of the supercharger. In this case, do not attempt to start the engine until fuel has ceased to flow from the drain. Pull the pro- peller through 6 to 8 revolutions ( 18 to 24 blades) using the starter, in the direction of rotation, with the ignition OFF, the mixture control in IDLE CUT-OFF, and the throttle wide open. Then repeat the starting procedure. The most frequent cause of overloading is failure to return the mixture control to IDLE CUT- OFF position immediately after a false start. Note The mixture control must not be moved out of the IDLE CUT-OFF position before the en- gine starts firing from fuel used in priming. (Continued on Page 18) 9 OUTER WING FUEL TANKS --~ V COMPARTMENT ,,,)---------- ..:= _ - -------- - rl_ - I I RADIO OPERA TOR'S STATION ----r~ TAIL COMPARTM PILOT'S COMPARTMENT LAVATORY COMPARTMENT CANVAS BENCHES ------------ CENTER WING FUEL TANKS AIRCRAFT 1 THROUGH 96 ''::::,, '"'-~,-~-, ', ----~-'---~-j -,jf_, ',r<":~--.-:::0, l____ 'y· J ','--J_. - ENGINE ACCESSORY COMPARTMENT OUTER WING FUEL TANKS Figure 1-8. location of Compartments and Areas . (IQ I ~ .,, ... @) (J AFT VIEW A 2)~~---\ 'i - figure 1-9 (Sheet 1 of 5 Sheets). Access Doors - Interior of Aircraft - ~ \ I ~ VIEW B • 796'.l )> z 0 ...I ~ 0 z:,;: .Iv VI (I) n :::!'. 0 :J - ~ 20) ~ ~~ "' - \ .. ® ' Figure J -9 (Sheet 2 of 3 Sheets). Access Doors - Fuselage and fmpennage, Left and Right Sides AN 01-40NK-2 95 @- 31 ·•.••... · ·.. ~46 ,, .... : [i·, @-~~ ~ 41 figure J -9 (Sheet 3 of 5 Sheets}. Access Doors - Bottom View of Aircraft Section I 58 60 59 61 7 '; .· i· .·' ' ' l 88 ! 1 ! 62 89 90 91 - - 81 ~----- d~--•_ ~ 7965 Section I AN 01-40NK-2 ~ r • -@ <II -@ ~ BOTTOM VIEW OF @) NACELLE AND WING .. CLEFT SIDE SHOWN, 10 RIGHT SIDE OPPOSITE) @ " ~ -@ @)_____ ... • @) @~ .. @) ~ @)~ figure J -9 (Sheet 4 of 5 Sheets). Access Doors - Bottom View of Leff Wing 14 127 ~ @- - @---- @)----► @1----- ~ TOP VIEW OF EMPENNAGE SECTION AN 01-40NK-2 20 TOP VIEW OF NACELLE AND WING (LEFT SIDE SHOWN, RIGHT SIDE OPPJSITEJ ' Section I 7967 figure J -9 (Sheet 5 of 5 Sheets). Access Doors - Top Views of Left Wing and Empennage 15 Section I AN 01-40NK-2 Key to Figure J-9 Access Door No. Access to Type of Door Attaching Parts Tool Used 1. Control Surface Cables, Engine Control Cables Nonstress Screw Screw Driver 2. Fire Control Valves. Emergency Shutoff Valves Nonstress Snap Hand Operated 3. Voltage Regulators Nonstress Camloc Fastener Screw Driver 4. Flight Compartment Nonstress Handle Hand Operated 5. Control Surface Cables Nonstress Screw Reed & Prince Screw Driver * 6. Main Cargo Door Stress Handle Hand Operated 7. Rear Lounge Area Nonstress Handle Hand Operated 8. Rear Compartment Door Nonstress Handle Hand Operated 9. Control Surface Cables, Elevator Torque Tube, Horizontal Stabilizer Attach Bolts Nonstress Handle Hand Operated 10. Control Cables Nonstress Camloc Fastener Screw Driver 11. Circuit Breakers Non stress Screw Screw Driver 12. Main Junction Box ( Upper Electrical, Lower Radio ) Nonstress Screw Screw Driver 13. Service Door Nonstress Handle Hand Operated 14. Inverters Nonstress Camloc Fastener Screw Driver 15. Control Cables, Hydraulic Piping Non stress Camloc Fastener Screw Driver 16. Control Cables, Electrical Wiring Stress Screw Screw Driver +17. Main Cabin Door Stress Handle Hand Operated 18. Rudder Torque Tube, Brake Torque Tube, Instruments Nonstress Screw Reed & Prince Screw Driver 19. Auxiliary Fuel Tank Liquidometer, Vent Pipes, Fuselage-to-Wing Attach Fittings Nonstress Screw Reed & Prince Screw Driver 20. Main Fuel Tank Liquidometer, Vent Pipes, Fuselage-to-Wing Attach Fittings Nonstress Screw Reed & Prince Screw Driver 21. Vertical Stabilizer Attach Bolts, Dorsal Fin Attach Bolts, Surface De-leer Piping, Electrical Conduit Nonstrcss Screw Reed & Prince Screw Driver 22. Flux Gate Compass Nonstress Camloc Fastener Screw Driver 23. Structure Nonstress Screw Reed & Prince Screw Driver 24. Rudder Trim Control Cable Drum Nonstress Screw Reed & Prince Screw Driver 25. Antenna Disconnect, Vertical Stabilizer Tip Attach Bolts Nonstress Screw Reed & Prince Screw Driver 26. Rudder Hinge and Tab Control Rod Nonstress Screw Reed & Prince Screw Driver 27. Rudder Trim Control Cable Nonstress Screw Reed & Prince Screw briver 28. Rudder-to-Rudder Torque Tube Attach Bolts Nonstress Screw Reed & Prince Screw Driver 29. Rudder Control Cables, Elevator Control Cables Nonstress Snap Hand Operated t30. Fresh Water Panel Nonstress Screw Reed & Prince Screw Driver 31. Alcohol Tank Filler Neck Nonstress Spring Latch Hand Operated 32. Elevator Torque Tube Nonstress Screw Screw Driver 33. Control Surfaces, Engine Controls Nonstress Screw Reed & Prince Screw Driver 34. Control Surfaces, Engine Controls, CO, Panel Nonstress Screw Reed & Prince Screw Driver 35. Electrical Tunnel Nonstress Screw Reed & Prince Screw Driver 36. Cockpit Warm-Air Control Rod Nonstress Spring Latch Hand Operated 37. Battery Elevator Nonstress Dzus Fastener Screw Driver 38. Battery Compartment Nonstress Spring Latch Hand Operated 39. Cabin Heater Unit Nonstress Spring Latch Hand Operated 40. No. 39 Door Handle Nonstress Spring Latch Hand Operated 41. Automatic Pilot Servo Unit, Control Surface Cables, Engine Control Cables Nonstress Spring Latch Hand Operated 42. Ground Power Receptacle and Relay Nonstress Screw Reed & Prince Screw Driver 43. ( See Door No. 42) Nonstress Spring-Loaded Hand Operated Hinged Door 44. Electrical Conduit, Ignition Junction Box Nonstress Screw Reed & Prince Screw Driver 45. Electrical Conduit, Structure Stress Screw Reed & Prince Screw Driver 46. Electrical Conduit, Structure Stress Screw Reed & Prince Screw Driver 47. Engine Accessory Section Nonstress Spring-Loaded Hand Operated Hinged Door 48. Lower Section Exhaust Stacks Nonstress Screw Reed & Prince Screw Driver 49. ( See Door No. 50) Non stress Screw Reed & Prince Screw Driver 50. Oil. Cooler Temperature Regulator Nonstress Screw Reed & Prince Screw Driver 51. Engine Instrument Piping, CO, Piping, Hydraulic Piping, Emergency Air Brake Piping Stress Screw Reed & Prince Screw Driver 52. Engine Instrument Piping, CO, Piping, Hydraulic Piping, Emergency Air Brake Piping Stress Screw Reed & Prince Screw Driver ,:, Aircraft 1 through 96. t Aircraft A through D. 16 AN 01-40NK-2 Key to Figure 1-9 (Continued) Access Door No. Access to 5.'\. Engine Instrument Piping, CO, Piping, Hydraulic Piping. Emergency Air Brake Piping; Nacelle-to- Wing Disconnects 54. Main Alighting Gear Door 55. Engine Control Cables. Alighting Gear Latch Cable, Surface De-leer Piping 56. Left Main Fuel Tank 57. ( See Door No. 'i8 \ 58. Center Wing Fuel Selector Valve, Fuel Strainers, Surface De-leer Distributor Valve. Fuel Piping. Engine Control Cables, Control Surface Cables, Surface De-leer Piping 59. Aileron Control Cables 60. Outer Wing Fuel Sump, Outer Wing Fuel Hose, Hydraulic Piping. Emergency Air Brake Piping 6 I. Left Auxiliary Fuel Tank 62. Aileron Control Cables 63. Fuel Piping, Hydraulic Piping. Alcohol Piping. Surface De-leer Piping; Control Surface Cables, Elevator Tab Control Cable, Automatic Pilot Cable Drum 64. ( See Door No. 63) 65. Aileron Control Cables 66. Structure 67. Tail Wheel Retract Hydraulic Piping, Structure 68. ( See Door No. 86) 69. Structure 70. Wing Flap Actuating Mechanism 71. Elevator Trim Tab Control Cable 72. Elevator Attach Bolts 73. Elevator Spring Control Tab Actuating Rod 74. Elevator Spring Control Tab Mechanism 75. Elevator Trim Tab Actuating Crank 76. Wing Tip Attach Bolts, Elevator Outboard Fitting 77. Structure 78. Elevator Trim Tab Cable Drum 79. Elevator Trim Tab Control Cable 80. Structure 81. Elevator Trim Tab Control Cable 82. Surface De-leer Piping Disconnects +83. Toilet Service Panel 84. Alcohol Tank Filter and Drain 85. Wing Flap Actuating Cylinder, Control Cables 86. Aileron Cross 87. Fuel Tank Sump Drain 88. Aileron and Aileron Tab Control Cables 89. ( See Door No. 90) 90. Fuel Piping, Hydraulic Piping, Alcohol Piping, Surface De-leer Piping; Control Surface Cables 91. Right Auxiliary Fuel Tank 92. Right Main Fuel Tank 93. Disconnects for Engine Instrument Piping, CO, Piping and Emergency Air Brake Piping 94. ( See Door No. 96) 95. Cabin Heater Control Unit 96. Right and Left Outer Wing Fuel Selector Valve, Right and Left Outer Wing Fuel Booster Pump, Engine Control Cables, Control Surface Cables, Surface De-leer Oil Separator, Cabin Heater Magnetic Valve t Aircraft A through D. Type of Door Attaching Parts Stress Screw Non stress Hydraulically Operated Nonstress Spring Latch Stress Screw Non stress Spring Latch Stress Screw Stress Screw Nonstress Screw Stress Screw Nonstress Snap Stress Screw Stress Screw Nonstress Screw Non stress Screw Nonstress Screw Nonstress Snap Non stress Snap Non~tress Screw Nonstress Screw Nonstress Screw Nonstress Screw Non stress Screw Non stress Screw Non stress Screw Nonstress Screw Nonstress Screw Non stress Screw Non stress Screw Nonstress Screw Non stress Screw Nonstress Spring Latch Non stress Spring Latch Non stress Screw Stress Screw Nonstress Camloc Fastener Nonstress Screw Stress Screw Stress Screw Stress Screw Stress Screw Nonstress Screw Nonstress Spring Latch Nonstress Spring Latch Nonstress Screw Section I Too/ l:sed Reed & Prince Screw Driver ································-········ Hand Operated Reed & Prince Screw Driver Hand Operated Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Hand Operated Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Hand Operated Hand Operated Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Hand Operated Hand Operated Reed & Prince Screw Driver Reed & Prince Screw Driver Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Reed & Prince Screw Driver Hand Operated Hand Operated Reed & Prince Screw Driver 17 Section I AN 01-40NK-2 Paragraphs 1-33 through 1-35 Key to Figure 1-9 (Continued) Access Door ,'-;o. Access to 97. Ground Blower 98. Ground Blower , 99. Driit Meter Tube JOO. Engine Instrument Piping, Hydraulic Piping, CO, Piping. Emergency Air Brake Piping 101. Control Surface Cables. Engine Control Cables 102. Brake Valve, Control Surfaces, Heater Ducts 103. Outer \'X'1 ing Fuel Tank Sump Drain 104. Wing Str0cture 105. Wing Structure 106. Outer Wing Fuel Vent Tank, Wing Structure 107. Landing Light Conduit Junction, Wing Structure 108. ( Set: Door No. 106) 109. Wing Flap Actuating Cylinder, Control Surface Cabies 110. Wing Vent Pipe, Wing Structure 111. W'ing Tip Attach Bolts. Navigation Light \'('iring 112. Aileron Hinge 113. Outboard Ailt:ron Bellcrank, Wing Structure 114. Aileron Control Cable, Wing Vent Tube, Structure 115. Inboard Aileron Bellcrank, Wing Structure, Landing Light, Wing Vent Pipe 116. Outer Wing Tank Vent Piping, Aileron Control Cable, Wing Structure 117. (See Door No. 118) 118. Outer Wing Fuel Connection, Outer Wing Fuel Tank Strainer Screen 119. Outer Wing Fuel Cell 120. Outer Wing Fuel Liquidometer 121. Outer Wing Fuel Cell 122. Outer Wing Fuel Tank Filler Neck 123. Outer Wing Fuel Cell 124. Alighting Gear 125. Carburetor Airscoop 126. Alighting Gear Actuating Strut Grease Fitting, Oil Tank Hose Fittings 127. Oil Tank Filler 128. Auxiliary Fuel Tank Filler Neck 129. Main Fuel Tank Filler 130. Alighting Gear Bungee Attachment 131. Nacelle Vent 132. Outer Wing Fuel Liquidometer 133. Outer Wing Fuel Cell 134. Outer Wing Fuel Cell (Continued from Page 9) 1-33. Overloading of a cold engine is not necessarily indicated by a discharge of fuel from the supercharger drain, but rather by the presence of liquid fuel, or mist, in the exhaust. A cold engine can be cleared by using the same procedure as that given for a warm engine. 1-34. IDLING. Prolonged idling at low rpm is per- missible and will not cause fouling of the spark plugs, providing that the idling fuel-air mixture is at, or near, "best power." If the mixture is too rich, fouling of the plugs will result at low rpm. The rpm for idle mixture adjustment, with cylinder head temperature at 150°C ( 302°F) minimum during adjustment, should be 700 (± 50) rpm. 18 Type of Door Atta,hi11r Parts Tool Used Non stress Camloc Fastener Screw Driver Nonstress Camloc Fastener Screw Driver Nonstress Screw Reed & Prince Screw Driver Nonstress Screw Reed & Prince Screw Driver J\,onstress Screw Reed & Prince Screw Driver Nonstress Camloc fastener Screw Driver Nonstress Spring Latch Hand Operated Nonstre:,s Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Strc,ss Screw Reed & Prince Screw Driver J\onstress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Strt:ss Screw Reed & Prince Screw Driver Nonstress Screw Reed & Prince Screw Driver Nonstress Screw Reed & Prince Screw Driver Nonstress Spring Latch Hand Operated Nonstress Spring Latch Hand Operated Nonstress Spring Latch Hand Operated Nonstress Spring Latch Hand Operated Nonstress Spring Latch Hand Operated Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Nonstress Spring Latch Hand Operated Stress Screw Reed & Prince Screw Driver Nonsttess Screw Reed & Prince Screw Driver Nonstress Screw Screw Driver Nonstress Screw Reed & Prince Screw Driver Nonstress Dzus Fastener Screw Driver Nonstress Camloc Fastener Screw Driver Nonstress Camloc Fastener Screw Driver Nonstress Screw Reed & Prince Screw Driver Nonstress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver Stress Screw Reed & Prince Screw Driver 1-35. PISTON HYDRAULICKING. If the engine has not been operated for 2 hours or longer, it is essential that the propeller be pulled through at least 4 revolutions ( 12 blades) by the starter, prior to an engine start, in order to make certain that there is no fuel or oil present in the lower cylinders. Oil and fuel are incompressible and their presence in the lower cylinders might result in a bent rod, a cracked piston, or a damaged crankshaft when the engine is started. If, when the propeller is pulled through, it seizes or binds, do not attempt to force it on around. Remove the spark plugs from the lower cylinders and drain the residual fluid. Then rotate the propeller before again installing the spark plugs. AN 01-40NK-2 figure 1-10. Drain and Vent Holes Section I 19 BOTTOM VIEW OF OUTER WING SEE.TION 1un SIDE SHOWN; RIGHT· SIDE OPPOSITE) BOTTOM VIEW OF AIRCRAFT 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. 40. 41. 42. 43. 44. 45. 46. 47. Hydraulic Drip Pan Drain Pipe Fairing Covered External Vapor Vent Holes External Vapor Vent Holes Cabin Heater Exhaust Heater Shroud Drain Combustion Heater Drain Fuel Booster Pump Vent Fuel Booster Pump Drain Engine Breather Pipe Vacuum Pump Drain Pipe Fuel Pump Drain Pipe Motor Vapor Vent Supercharger Drain Pipe Hydraulic Pump Drain Pipe Fuel Pump Vent Pipe Propeller Feathering Pump Drain Oil Tonk Scupper Drain Pipe Outer Wing Fuel Cell Sump Can Drain Aft Fuel Tonk Vent Forward Fuel Tank Vent Tank Syphon Breaker Pipe Center Wing Trailing Edge Vent Fuselage Belly Vent Toilet Floor Drain Outlet Aft Lavatory Urinal Outlet Alcohol Tank Drain Pipe Alcohol Pump Drain Pipe Alcohol Tank Vent Pipe Surface De-icer Distributer Valve Vent Pipe Surface 0e..fcer Distributer Valve Drain Pipe Surface De-icer Oil Separator Vent Pipe Fuselage Belly Vent Cabin Heater Mixing Valve Air Exhaust Hydraulic Reservoir Drain and,. Vent Pilot's Relief Tube Outlet Emergency Air Brake Exhaust Outer Wing Fuel Vapor Vent Outer Wing Fuel Vapor Vent Outer Wing Fuel Cell Filler Neck Outer Wing Vent Inlet Outer Wing Vent Inlet Outer Wing Fuel Tonk Vent Outer Wing Vent Inlet Master Junction Box Vent ~!- Radio Rack Vent Airspeed Static Pipe Vent (Left Vent .Shown, Right Vent Opposite) Lavatory Vent (Left Vent Shown, Right Vent Opposite) Section I AN 01-40NK-2 Paragraphs 1-36 through 1-49 1-36. FUEL SYSTEM MANAGEMENT. The fuel system consists of the following units: Center section tanks Outer wing tanks Selector valves ( center section tanks) Selector valves ( outer wing tanks) Strainers Electric fuel booster pumps Firewall shutoff valves Engine-driven fuel pumps Priming system 1-37. The ·fuel system is basically designed so that each engine is provided with an independent fuel supply system, including its own fuel tanks, although fuel from any of the tanks may be directed to either of the engines. Transfer of fuel between tanks is not possible. Note Fuel from the front tanks should be used for all ground operations, if all of the tanks are full; if any tank is not full, fuel from the tanks containing the most fuel should be used. Do not use the outer wing tanks for ground operations. 1-38. The inner wing tank fuel selector dials are di- vided into five positions as follows: LEFT FRONT RIGHT FRONT LEFT REAR RIGHT REAR OFF 1-39. The outer wing tank fuel selector dials are di- vided into three positions as follows: LEFT TANK RIGHT TANK OFF 1-40. Through the operation of the· selector valves in any of the above positions, fuel can be supplied to either or both of the engines from any of the inner or outer wing tanks. 1-41. FUEL BOOSTER PUMP CHECK. Before start- ing the engines, check the operation of both electric fuel booster pumps as follows: a. Place the left mixture control in IDLE CUT-OFF position. b. Place the left fuel tank selector valve in position to select the desired tank. c. Place the booster pump switch for the left booster pump in the ON position. The fuel pressure indica- tor for the left engine should read 21 ( + %) psi. d. Repeat steps a, b, and c for the right fuel booster pump. 20 1-42. FUEL TANK SELECTOR VALVE CHECK. With the engines running, check the selector valves to insure unrestricted flow through all pipes and valves in the system. 1-43. ENGINE STARTING PROCEDURE. For en- gine starting procedure, see the applicable handbook of flight operating instructions. 1-44. PROPELLER FEATHERING CHECKS. 1-45. PROPELLER FEATHERING PROCEDURE FOR GROUND OPERATION. For complete informa- tion on propeller feathering or engine isolation pro- cedures, refer to the applicable handbook of flight operating instructions. During ground check of the propeller feathering system, it is not required to shut down the engine. To make the ground check, momen- tarily depress the feathering button, located on the pilot's or co-pilot's overhead electrical panels, until a drop of 300 to 400 rpm is attained. Then pull the feathering button out and allow the propeller to return to the original rpm setting. 1-46. GROUND FIRE CONTROL. Ground fire ex- tinguishing equipment should be spotted in the im- mediate vicinity of the aircraft during ground opera- tions. Use the ground fire extinguishing equipment, if possible, rather than the aircraft's fire extinguishing system. Access holes, covered with spring-loaded doors, are located in the outboard side of each nacelle. Insert the CO:! ground fire equipment horn by pushing it against the access door. Two hand fire extinguishers are provided, one on the cockpit floor aft of the co-pilot's seat, and one in the cabin area, just forward of the main cargo door. The engine compartments and the com- bustion heater compartment fire extinguishing systems are controlled from a panel on the floor between the pilot's and co-pilot's seats. For fire extinguishing sys- tem operating procedures, see the applicable hand- book of flight operating instructions. 1-47. ENGINE SECTION FIRE. Each engine com- partment is divided into two areas, or fire zones. Zone 1 is the area forward of the inner ring and Zone 2 is the area between the inner ring and the firewall. A fire detector system is installed in each zone, but only Zone 2 is protected by CO:!. Detectors located in both zones of an engine compartment are connected to a warning light located on the pilot's side of the main instrument panel; this light will illuminate in the event of a fire. 1-48. COMBUSTION HEATER COMPARTMENT FIRE. A fire detector system is provided in the com- bustion heater compartment. Detectors, which are lo- cated in the heater ducting and throughout the com- partment, are connected to a warning light on the left overhead electrical panel. The light will be illuminated in the event of a fire. 1-49. FIRE WARNING CIRCUIT TEST SWITCHES. The fire detector circuits can be electrically tested for. normal circuit continuity prior to flight by means