TYPE CERTIFICATE DATA SHEET NO. A13CE

III. Model 177B, Cardinal, 4 PCLM (Normal Category), 2 PCLM (Utility Category) (cont'd) G.G. Range (cont’d) Utility category: (+101.0) to (+109.0) at 2000 lbs. or less (+102.0) to (+109.0) at 2200 lbs. Empty Weight C.G. Range None *Maximum Weight Normal category 2500 lbs. Utility category 2200 lbs. Number of Seats 4 (2 at sta. +93.0), 2 at sta. +135.0) Maximum Baggage 120 lbs. (+162.0) Fuel Capacity 50 gal. (two 25 gal. fuel bays in wing at sta. +112; 49 gal. usable) See Note 1 for data on unusable fuel. Oil Capacity 8 qt. (+44) (1 at. (+45) with oil filter) (3 qt. unusable - 2 qt. in sump plus 1 qt. in oil filter) See Note 1 for data on undrainable oil. Control Surface Wing flaps Down 30! " 2!, -0! Movements Aileron Up 20! " 1! Down 15! " 2! Stabilator Up 20! " 1! Down 5! " 1! Stabilator tab Up 5! " 1! Down 13! " 1! Rudder (measured perpendicularly to hinge line) Right 24! " 1! Left 24! " 1! Serial Numbers Eligible 17701371 through 17701530, except 17701472 (1970) 17700002, 17701531 through 17701633 (1971) 17701634 through 17701773 (1972) 17701774 through 17701973 (1973) 17701974 through 17702123 (1974) 17701472, 17702124 through 17702313 (1975) 17702314 through 17702522 (1976) 17702523 through 17702672 (1977) 17702673 through 17702752 (1978) Data Pertinent to All Models Datum 54.0 forward of front face of lower portion of firewall Leveling Means Jig located nut plates and screws at sta. +213.0 and sta. +238.0 on left of tail cone Certification Basis Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1, 23-2 and 23-3. Application for Type Certificate dated June 20, 1966. Type Certificate No. A13CE issued February 16, 1967, obtained by the manufacturer under delegation option procedures. Equivalent Safety Items 17702314 and on Airspeed Indicator FAR 23.1545 (see Note 4 on use of IAS) Airspeed Limitations FAR 23.1583(a)(1) Production Basis Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates under delegation option procedures of Part 21 of the Federal Aviation Regulations. Rev. 27 Page 5 of 11 A13CE Data Pertinent to All Models (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. Stall Warning Indicator, Cessna Dwg. 1706014. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. Serial No. 17700001 through 17702313 The certificated empty weight and corresponding center of gravity location must include undrainable oil of 0.0 lb. at 44.0 and unusable fuel of 6 lb. at 100.0. Serial No. 17702314 and on The certificated empty weight and corresponding center of gravity locations must include oil of 17 lbs. at 45.0 and unusable fuel of 6 lb. at 100.0. NOTE 2. The following placards must be displayed as indicated: A. Applicable to Model 177 (S/N 661, 17700001 & 17700003 through 17701164) 1. In full view of the pilot: "This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS Normal Category Utility Category Maneuvering speed 113 mph (CAS) 113 mph (CAS) Design weight 2350 2200 Load factor Flaps up +3.8 -1.52 +4.4 -1.76 Flaps down +3.5 +3.5 Altitude loss in stall recovery 110 ft. 110 ft. Normal category No acrobatic maneuvers including spins approved Utility category Baggage compartment and rear seat must not be occupied. No acrobatic maneuvers approved except those listed below: Maneuver Maximum Entry Speed Maneuver Maximum Entry Speed Chandelles 113 mph (98 knots) Spins Slow deceleration Lazy Eights 113 mph (98 knots) Stalls (except Slow deceleration Steep turns 113 mph (98 knots) whip stalls) Spin Recovery - Opposite rudder - Neutral elevator - Slow deceleration Intentional spins with flaps extended prohibited. Airplane is controllable in 16 knots crosswind. Known icing conditions to be avoided. This airplane is certificated for the following flight operations as of date of original airworthiness certificate. (IFR - VFR - DAY - NIGHT)" (as applicable) 2. On control lock: "Control lock - remove before starting engine." 3. On fuel shutoff control (at appropriate location): "Fuel shutoff - pull off." 4. On fuel selector valve (at appropriate locations): a. "Both 48 gal." b. "Left 24 gal." c. "Right 24 gal." d. "Both on for takeoff and landing." 5. On fuel tank cap: "Service this airplane with 80/87 minimum grade aviation gasoline." "Total capacity 24.5 gal." "Capacity to white line on indicator, 21.0 gal." A13CE Page 6 of 11 Rev. 27 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) A. 6. In baggage compartment: a. "120 lb. maximum baggage and/or auxiliary seat passenger." b. "For additional loading instructions see weight and balance data." 7. Next to door ventilation windows: "Do not open window above 120 mph." 8. On airspeed indicator (CAS) a. Radial red line 185 mph b. Yellow arc 145-185 mph c. Green arc 64-145 mph d. White arc 53-105 mph 9. On oil temperature gauge a. Red line at 245! F. b. Green arc at 100! to 245! F. 10. On oil temperature gauge a. Red line at 25 psi b. Green arc 60 psi to 90 psi c. Red line at 100 psi 11. Tachometer ( S.L.) 2200 rpm - 2500 rpm (inner green arc) (5000 ft.) 2200 rpm - 2600 rpm (middle green arc) (10000 ft) 2200 rpm - 2700 rpm (outer green arc) (Maximum allowable) - 2700 rpm (red line) 12. On fuel pressure gauge a. Red lines at 2 psi and 8.0 psi. b. Green arc at 2 psi to 8.0 psi. 13. On flap control and indicator a. Up to 1/4 - T.O. (Takeoff range with blue color code and 130 mph callout, also mechanical detent at 1/4) b. 1/4 - 1/2 - 3/4 - Down (indices at these positions with white color code and 105 mph callout) c. "Avoid slips with flaps extended." B. Applicable to 177A (S/N 17701165 through 17701370) 1. In full view of the pilot: "This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS Normal Category Utility Category Maneuvering speed 113 mph (CAS) 113 mph (CAS) Design weight 2500 2200 Load factor Flaps up +3.8 -1.52 +4.4 -1.76 Flaps down +3.5 +3.5 Altitude loss in stall recovery 180 ft. 110 ft. Normal category No acrobatic maneuvers including spins approved Utility category Baggage compartment and rear seat must not be occupied. No acrobatic maneuvers approved except those listed below: Rev. 27 Page 7 of 11 A13CE Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) B. 1. Maneuver Maximum Entry Speed Maneuver Maximum Entry Speed Chandelles 117 mph (101 knots) Spins Slow deceleration Lazy Eights 117 mph (101 knots) Stalls (except Slow deceleration Steep turns 117 mph (101 knots) whip stalls) Spin Recovery - Opposite Rudder - Neutral Elevator - Slow deceleration Intentional spins with flaps extended prohibited. Airplane is controllable in 16 knots crosswind. Known icing conditions to be avoided. This airplane is certificated for the following flight operations as of date of original airworthiness certificate. (IFR - VFR - DAY - NIGHT)" (as applicable) 2. On control lock: "Control lock - remove before starting engine." 3. On fuel shutoff control (at appropriate location): "Fuel shutoff - pull off." 4. On fuel selector valve (at appropriate locations): a. "Both 48 gal." b. "Left 24 gal." c. "Right 24 gal." d. "Both on for takeoff and landing." 5. On fuel tank cap: "Service this airplane with 100/130 minimum grade aviation gasoline." "Total capacity 24.5 gal." "Capacity to line of holes on indicator, 21.0 gal." 6. In baggage compartment: a. "120 lb. maximum baggage and/or auxiliary seat passenger." b. "For additional loading instructions see weight and balance data." 7. Next to door ventilation windows: "Do not open window above 120 mph." 8. On airspeed indicator (CAS) a. Radial red line 185 mph b. Yellow arc 150-185 mph c. Green arc 66-150 mph d. White arc 56-105 mph 9. On oil temperature gauge a. Red line at 245! F. b. Green arc 100! to 245! F. 10. On oil pressure gauge a. Red line at 25 psi. b. Green arc 60 psi, to 90 psi. c. Red line at 100 psi. 11. Tachometer ( S.L.) 2200 rpm - 2500 rpm (inner green arc) (5000 ft.) 2200 rpm - 2600 rpm (middle green arc) (10000 ft) 2200 rpm - 2700 rpm (outer green arc) (Maximum allowable) - 2700 rpm (red line) 12. On fuel pressure gauge a. Red lines at 2 psi, and 8.0 psi. b. Green arc at 2 psi, to 8.0 psi. A13CE Page 8 of 11 Rev. 27 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) B. 13. On flap control and indicator a. 0! to 10! - T.O. (Takeoff range with blue color code and 130 mph callout, also mechanical detent at 10!). b. 10! -20! -30! (Indices at these positions with white color code and 105 mph callout; also, mechanical detent at 20!). C. Applicable to 177B 1. In full view of the pilot: a. 17701371 through 17702313 "This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings, and manuals." MAXIMUMS Normal Category Utility Category Maneuvering speed 117 mph (CAS) 117 mph (CAS) Gross weight 2500 2200 Load factor Flaps up +3.8 -1.52 +4.4 -1.76 Flaps down +3.5 +3.5 Altitude loss in stall recovery 180 ft. 110 ft. Normal category No acrobatic maneuvers including spins approved Utility category Baggage compartment and rear seat must not be occupied. No acrobatic maneuvers approved except those listed below: Maneuver Maximum Entry Speed Maneuver Maximum Entry Speed Chandelles 117 mph (101 knots) Spins Slow deceleration Lazy Eights 117 mph (101 knots) Stalls (except Slow deceleration Steep turns 117 mph (101 knots) whip stalls) Spin Recovery - Full Opposite Rudder - Stabilator to Neutral Position - Ailerons Neutral - Recover from Dive. Intentional spins with flaps extended prohibited. Airplane is controllable in 16 knots crosswind. Known icing conditions to be avoided. This airplane is certificated for the following flight operations as of date of original airworthiness certificate. (IFR - VFR - DAY - NIGHT)" (if applicable) b. 17702314 and up "This airplane must be operated in compliance with the operating limitations as stated in the form of placards, markings and manuals. MAXIMUMS Normal Category Utility Category Maneuvering speed 102 knots 102 knots Gross weight 2500 lb. 2200 lb. Load factor Flaps up +3.8 -1.52 +4.4 -1.76 Flaps down +3.5 +3.5 Normal category No acrobatic maneuvers including spins approved Utility category Baggage compartment and rear seat must not be occupied. NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW: Rev. 27 Page 9 of 11 A13CE Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) C. 1. b. (cont’d) Maneuver Recom. Entry Speed Maneuver Recom. Entry Speed Chandelles 100 knots Spins Slow deceleration Lazy Eights 100 knots Stalls (except Slow deceleration Steep turns 100 knots whip stalls) Altitude loss in stall recovery - 180 ft. Abrupt use of the controls prohibited above 102 knots Spin recovery - opposite rudder - forward stabilizer - neutralize controls. Intentional spins with flaps extended are prohibited. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate. DAY - NIGHT - VFR - IFR" (as applicable) 2. On control lock: "Control lock - remove before starting engine." 3. On fuel shutoff control (at appropriate location): "Fuel shutoff - pull off." 4. On fuel selector valve (at appropriate locations) a. "Both 49 gal." b. "Left 24.5 gal." c. "Right 24.5 gal." d. "Both on for takeoff and landing." 5. Aft of fuel tank cap: a. S/N 17701371 through 17702672 "Service this airplane with 91/96 minimum or 100/130 grade aviation gasoline." "Total capacity 25.0 gal." "Capacity to line of holes inside filler neck - 22 gal." b. S/N 17702673 and on "Service this airplane with 100LL or 100 aviation grade gasoline." "Total capacity 25.0 gal." "Capacity to line of holes inside filler neck - 22 gal." 6. In baggage compartment a. Without hat shelf in baggage wall (Through S/N 17702123) "120 lb. maximum baggage and/or auxiliary seat passenger." "For additional loading instructions see weight and balance data." b. With hat shelf in baggage wall (S/N 17702124 through 17702672) "120 lb. maximum baggage and/or auxiliary seat passenger including 25 lb. maximum in baggage wall hat shelf." "For additional loading instructions see weight and balance data." c. (S/N 17702673 and on) "120 lb. maximum baggage, including 12 lbs. maximum in baggage wall hat shelf." "For additional loading instructions see weight and balance data." 7. Next to door ventilation windows: a. 17701371 through 17702313 "Do not open window above 120 mph or when using alternate static source." b. 17702314 and up "Do not open window above 105 knots or when using alternate static source." A13CE Page 10 of 11 Rev. 27 Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) C. 8. On airspeed indicator a. 17701371 through 17702313 (CAS) Radial red line 185 mph Yellow arc 155-185 mph Green arc 66-155 mph White arc 56-105 mph b. 17702314 and up (IAS) Radial red line 167 knots Yellow arc 138-167 knots Green arc 54-138 knots White arc 45- 90 knots 9. On oil temperature gauge: a. Red line at 245! F. b. Green arc 100! to 245! F. 10. On oil pressure gauge: a. Red line at 25 psi b. Green arc 60 psi to 90 psi c. Red line at 100 psi 11. Tachometer a. When using 2D34C202/82PA-6 or B2D34C208/82PA-6 propeller: Normal operating 2100-2500 rpm (green arc) Caution 1700-1900 rpm (yellow arc) Maximum allowable 2700 rpm (red line) b. When using B2D34C206/78TA-0 propeller: Normal operating 2100-2500 rpm (green arc) Caution 1400-1750 rpm (yellow arc) Maximum allowable 2700 rpm (red line) c. When using B2D34C211/82PCA-6 propeller: Normal operating 2100-2500 rpm (inner green arc) 2100-2700 rpm (outer green arc) Caution 1700-1900 rpm (yellow arc) Maximum allowable 2700 rpm (red line) 12. On fuel pressure gauge: a. Red lines at 2 psi and 8.0 psi. b. Green arc at 2 psi to 8.0 psi. 13. On flap control and indicator a. 17701371 through 17702313 0 to 10! (Blue color code and 130 mph callout, also, mechanical detent at 10!) 10! - 20! - 30! (Indices at these positions with white color code and 105 mph callout; also, mechanical detent at 20!). b. 17702314 and up 0! to 10! (Blue color code and 115 knots callout; also, mechanical detent at 10!) 10! - 20! - 30! (Indices at these positions with white color code and 90 knots callout; also, mechanical detent at 20!). 14. On manifold pressure gauge: a. When using 2D34C202/82PA-6, B2D34C208/82PA-6 or B2D34C211/82PCA-6 propeller: 15 to 24 in. Hg. (green arc) *With less than 10" manifold pressure, avoid continuous operation between 1700-1900 rpm." b. When using B2D34C206/78TA-0 propeller: 15 to 24 in. Hg. (green arc) "With less than 10" manifold pressure, avoid continuous operation between 1400-1750 rpm." Rev. 27 Page 11 of 11 A13CE Data Pertinent to All Models (cont’d) NOTE 2. (cont’d) C. 15. On cylinder head temperature gauge: a. Red line at 500! F. b. Green arc 200! to 500! F. 16. On instrument panel: a. "Do not turn off alternator in flight except in emergency." (1970 and 1971 models only) NOTE 3. The cylinder head probe location for the Model 177B is No. 3 cylinder. NOTE 4. The marking of the airspeed indicator with IAS provides an equivalent level of safety to FAR 23.1545 when approved airspeed calibration data presented in Section V of the Pilot's Operating Handbooks listed below is available to the pilot: 177B, Cessna P/N D1058-13 (S/N 17702314 through 17702522) 177B, Cessna P/N D1084-13 (S/N 17702523 through 17702672) 177B, Cessna P/N D1111-13 (S/N 17702673 through 17702752) NOTE 5. 14-volt electrical system (177 series through S/N 17702672) 28-volt electrical system (177 series, S/N 17702673 and on) In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I, II, and III of this data sheet must also be displayed by permanent markings. ....END..... DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-286 Revision 19 Lycoming Engines O-360-A1A, -A1AD, -A1C, -A1D, -A1F, -A1F6, -A1F6D, -A1G, -A1G6, -A1G6D, -A1H, -A1H6, -A1LD,-A1P, -A2A, -A2D, -A2E, -A2F, -A2G, -A2H, -A3A, -A3AD, -A3D, -A4A, -A4AD, -A4D, -A4G, -A4J, -A4K, -A4M, -A4N, -A4P,-A5AD, -B1A, -B1B, -B2A, -B2B,-B2C,-C1A, -C1C, -C1E, -C1F, -C1G, -C2A, -C2B, -C2C, -C2D, -C2E, -C4P,-C4F,-D1A, -D2A,-D2B, -E1AD, -E1A6D, -E2AD, -E1BD, -E2BD, -F1A6, -G1A6, -J2A LO-360-A1G6D, -A1H6, -E1AD, -E1A6D, -E2AD, -E1BD, -E2BD HO-360-A1A, -B1A, -B1B,-C1A December 17, 2003 TYPE CERTIFICATE DATA SHEET NO. E-286 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. 286) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Civil Air Regulations/Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer’s manual and other approved instructions. Type Certificate Holder Lycoming Engines An Operating Division of AVCO Corporation Williamsport, Pennsylvania 17701 Type Certificate Holder Record Textron Lycoming/Subsidiary of Textron, Inc. transferred TC E-286 to Lycoming Engines, An Operating Division of AVCO Corporation on December 17, 2003 Model O-360 O-360 O-360-C2D -A1A, -A1AD, -A1C, -A1D, -A1F, -A1F6, -A1F6D, -A1G, -A1G6, -A1G6D, -A1H, -A1H6, -A1LD, - A1P, -A2A, -A2D, -A2E, - A2F, -A2G, -A2H, -A3A, -A3AD, -A3D, -A4A, -A4AD, -A4D, -A4G, -A4J, -A4K, -A4M, -A4N, -A4P,-A5AD, -C1A, -C1C, -C1E, -C1F, -C1G, -C2A, -C2B, -C2C,-C2E, -C4P,-C4F, -F1A6, -G1A6, -B1A, -B1B, -B2A, -B2B, -B2C, -D1A, -D2A, -D2B LO-360-A1G6D, -A1H6 Type 4HO-A Direct Drive # # # Rating Rated Max. continuous hp., rpm, full throttle at: Sea level press. alt. 180-2700 168-2700 180-2700 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 Rev. No. 19 16 17 16 16 16 18 18 16 16 16 16 18 E-286 Page 2 of 13 Rated takeoff hp., rpm, full throttle, or in. Hg. at: Sea level press. alt. Rated press alt. (ft.) 180-2700 - 168-2700 - 180-2900-28.0 (5 min.) 180-2900-27.8-1000 (5 min.) Fuel (Min. grade aviation gaosline) 100/100LL* 80/87* 100/100LL* Carburetion See Note 9. # # Pump drive See Note 3. # # Oil, Lubrication (Lubrications should conform to the specifications as listed or to subsequent revisions thereof.) Lycoming Spec. No. 301 and Service Instruction No. 1014 Oil sump capacity, qt. 8 # # Usable oil, qt. 6 # # Ignition Dual magnetos See Note 9. # # Timing, !BTC 25 # # Spark plugs See Note 4. # # Compression Bore and stroke, in. 5.125 X 4.375 # # Displacement, cu. in. 361 # # Compression ratio See Note 9. # # Weight (dry), lb. See Note 5. # # C.G. location See Note 8. # # Propeller shaft, SAE No. See Note 9. # # Crankshaft dampers See Note 12. # - NOTES 1 through 12 1 through 12 # Model O-360-E1AD, -E1A6D, -E2AD, -E1BD, -E2BD O-360-J2A HO-360-A1A, LO-360-E1AD,-E1A6D, -E2AD, -E1BD, -E2BD Type 4HO-A Direct Drive # # # Rating Rated Max. continuous hp., rpm, full throttle at: Sea level press. alt. 180-2700 145 - 2400 thru 2700 + 26.5” Hg MP @ 2400 24.6” Hg MP @ 2700 180-2900 Rated takeoff hp., rpm, full throttle, or in. Hg. at: Sea level press. alt. 180-2700 145 - 2400 thru 2700 + 26.5” Hg MP @ 2400 24.6” Hg MP @ 2700 180-2900 Rated press. alt. (ft.) - - - Fuel (Min. grade aviation gaosline) 100/100LL* # # Carburetion See Note 9. # # Pump drive See Note 3. # # Oil, Lubrication (Lubrications should conform to the specifications as listed or to subsequent revisions thereof.) Lycoming Spec. No. 301 and Service Instruction No. 1014 Oil sump capacity, qt. 6 8 # Usable oil, qt. 4 6 # Ignition Dual magnetos See Note 9. # # Timing, !BTC 25 # # Spark plugs See Note 4. # # Compression Bore and stroke, in. 5.125 X 4.375 # # Displacement, cu. in. 361 # # Page 3 of 13 E-286 Model (cont'd) O-360-E1AD, -E1A6D, -E2AD, -E1BD, -E2BD O-360-J2A HO-360-A1A, LO-360-E1AD,-E1A6D, -E2AD, -E1BD, -E2BD Compression ratio See Note 9. # # Weight (dry), lb. See Note 5. # # C.G. location See Note 8. # # Propeller shaft, SAE No. See Note 9. # # Crankshaft dampers See Note 12. # - NOTES 1 through 12 1 through 11 1 through 11 * See latest revision of Lycoming Service Instruction No. 1070 for alternate fuel grades. # Indicates “same as preceding model.” - Indicates “does not apply” + This engine is throttle limited Model HO-360-B1A, -B1B HO-360-C1A Type 4HO-A Direct Drive # # Rating Rated Max. continuous hp., rpm, full throttle at: Sea level press. alt. 180-2900 180-2700 Rated takeoff hp., rpm, full throttle, or in. Hg. at: Sea level press. alt. 180-2900 180-2700 Rated press. alt. (ft.) - - Fuel (Min. grade aviation gaosline) 100/100LL* # Carburetion See Note 9. # Pump drive See Note 3 # Oil, Lubrication (Lubrications should conform to the specifications as listed or to subsequent revisions thereof.) Lycoming Spec. No. 301 and Service Instruction No. 1014 Oil sump capacity, qt. 8 # Usable oil, qt. 6 # Ignition Dual magnetos See Note 9. # Timing, !BTC 25 # Spark plugs See Note 4. # Compression Bore and stroke, in. 5.125 X 4.375 # Displacement, cu. in. 361 # Compression ratio See Note 9. # Weight (dry), lb. See Note 5. # C.G. location See Note 8. # Propeller shaft, SAE No. See Note 9. # Crankshaft dampers - - NOTES 1 through 11 # * See latest revision of Lycoming Service Instruction No. 1070 for alternate fuel grades. # Indicates “same as preceding model.” - Indicates “does not apply” E-286 Page 4 of 13 Certification basis: Regulations & Amendments Model Date of Application Date Type Certificate No. 286 Issued/Revised CAR 13 effective March 5, 1952 as amended by 13-1 and 13-2 O-360-A1A January 17, 1955 July 20, 1955 O-360-B1A July 13, 1955 January 17, 1956 CAR 13 effective June 15, 1956 O-360-A2A December 31, 1956 February 25, 1957 O-360-A1B April 5, 1957 April 22, 1957 (cancelled 4/19/63) O-360-B2A April 5, 1957 April 22, 1957 as amended by 13-1 O-360-C1A January 31, 1958 February 24, 1958 O-360-C2A January 31, 1958 February 24, 1958 as amended by 13-1 and 13-2 O-360-C2B July 9, 1958 August 13, 1958 as amended by 13-1, 13-2, and 13-3 O-360-D1A January 19, 1960 February 12, 1960 O-360-D2A January 19, 1960 February 12, 1960 O-360-A1D March 29, 1960 April 27, 1960 O-360-A2D March 29, 1960 April 27, 1960 O-360-C1C March 29, 1960 April 27, 1960 O-360-C2C March 29, 1960 April 27, 1960 O-360-A1C July 14, 1960 August 29, 1960 O-360-C2D July 14, 1960 August 29, 1960 O-360-D2B October 11, 1960 October 26, 1960 O-360-A2E July 20, 1961 August 23, 1961 as amended by 13-1, 13-2, 13-3, and 13-4 O-360-A3A June 12, 1962 July 3, 1962 HO-360-B1A September 27, 1962 October 2, 1962 HO-360-A1A October 30, 1962 December 6, 1962 HO-360-B1B March 15, 1963 March 20, 1963 O-360-B1B June 26, 1963 June 27, 1963 O-360-B2B June 26, 1963 June 27, 1963 O-360-A3D September 19, 1963 September 26, 1963 O-360-A4A March 1, 1966 March 9, 1966 O-360-A1F November 4, 1966 January 20, 1967 O-360-A2F November 4, 1966 January 20, 1967 O-360-A1G September 27, 1967 October 16, 1967 O-360-A2G September 27, 1967 October 16, 1967 O-360-A1H June 6, 1968 September 18, 1968 O-360-A2H June 6, 1968 September 18, 1968 O-360-A1F6 April 1, 1969 June 23, 1969 O-360-A4G July 11, 1969 July 18, 1969 O-360-A4J September 18, 1969 October 8, 1969 O-360-A1G6 July 21, 1970 July 31, 1970 O-360-A1F6D January 24, 1972 January 31, 1972 O-360-A4AD January 24, 1972 January 31, 1972 O-360-A5AD April 8, 1972 April 22, 1972 O-360-A1LD January 5, 1973 January 11, 1973 O-360-C2E February 4, 1974 February 4, 1974 O-360-A4K March 8, 1974 March 18, 1974 O-360-A4M October 15, 1974 November 8, 1974 O-360-A3AD April 23, 1975 April 28, 1975 O-360-A1AD September 14, 1976 September 28, 1976 O-360-A1G6D December 20, 1976 December 27, 1976 LO-360-A1G6D December 20, 1976 December 27, 1976 O-360-C1E March 15, 1977 March 22, 1977 O-360-E1AD November 19, 1976 Oct 25, 1977 (cancelled 5/24/78) O-360-E2AD November 19, 1976 Oct 25, 1977 (cancelled 5/24/78) O-360-E1BD November 19, 1976 Oct 25, 1977 (cancelled 5/24/78) O-360-E2BD November 19, 1976 Oct 25, 1977 (cancelled 5/24/78) LO-360-E1AD October 26, 1977 Nov 2, 1977 (cancelled 5/24/78) LO-360-E2AD October 26, 1977 Nov 2, 1977 (cancelled 5/24/78) Page 5 of 13 E-286 Regulations & Amendments (cont’d) Model Date of Application Date Type Certificate No. 286 Issued/Revised as amended by 13-1, 13-2, and 13-3 LO-360-E1BD October 26, 1977 Nov 2, 1977 (cancelled 5/24/78) LO-360-E2BD October 26, 1977 Nov 2, 1977 (cancelled 5/24/78) O-360-E1A6D April 24, 1978 May 5, 1978 LO-360-E1A6D April 24, 1978 May 5, 1978 O-360-C1F June 27, 1978 July 10, 1978 O-360-F1A6 September 14, 1978 November 20, 1978 O-360-A4D May 18, 1981 May 29, 1981 O-360-A4N July 14, 1982 July 29, 1982 O-360-G1A6 March 22, 1985 May 30, 1985 O-360-C1G January 16, 1986 February 10, 1986 O-360-A1H6 November 16, 1988 December 27, 1988 LO-360-A1H6 November 16, 1988 December 27, 1988 O-360-B2C September 30, 1992 October 21, 1992 O-360-A4P October 19, 1992 December 16, 1992 O-360-C4P October 19, 1992 December 16, 1992 O-360-A1P January 19, 1993 February 23, 1993 O-360-C4F February 18, 1993 March 10, 1993 HO-360-C1A March 10, 1995 April 11,1995 O-360-J2A October 9, 1995 October 16, 1995 Production basis: Production Certificate No. 3 NOTE 1. Temperature limits: (Maximum permissible) Cylinder head (well type thermocouple) 500!F Cylinder base 325!F Oil inlet 245!F NOTE 2. Pressure limits: Fuel - At inlet to carburetor, above carburetor inlet air pressure. Minimum Maximum Bendix PSH-5BD carburetor 9 p.s.i. 18 p.s.i. Facet (Marvel Schebler) MA-4, HA-6 series carb. 0.5 p.s.i. 8 p.s.i. Oil - (Normal Operation) 55 p.s.i. 95 p.s.i. (Idling) 25 p.s.i. - (Starting and Warmup) - 115 p.s.i. Minimum Maximum O-360-A4N Rear of Engine Front of Engine Rear of Engine Front of Engine Oil - (Normal Operation) 55 p.s.i. 50 p.s.i. 95 p.s.i. 90 p.s.i. (Idling) 25 p.s.i. 20 p.s.i. - - (Starting and warmup) - - 115 p.s.i. 115 p.s.i. O-360-G1A6 Minimum Maximum Oil (Normal Operation) 55 p.s.i. 95 p.s.i. (Idling) 25 p.s.i. - (Starting and warmup) - 115 p.s.i. E-286 Page 6 of 13 NOTE 3. The following accessory drive provisions are incorporated. See also Note 11. Model O-360- Accessory A1F6D A1AD A3AD A4AD A5AD A4G A4J A4K C4F C4P A Ser. A1C C1F A2G A1G A1G6 Rotating Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Static Starter - - - * - CC 13.556:1 - 450 150 Starter * * * ** * CC 16.556:1 - 450 150 Generator - - ** * - C 1.910:1 60 120 175 Generator - - ** ** - C 2.500:1 60 120 175 Alternator * * * - * C 3.250:1 60 120 175 Vacuum pump ** ** ** ** ** CC 1.300:1 70 450 25 Hydraulic pump ** - - - - C 1.300:1 100 800 40 Hydraulic pump ** - - - - C 1.300:1 180 2200 150 Fuel pump - - - * - CC 0.866:1 25 450 25 Fuel pump, plunger ** ** ** - ** - 0.500:1 - - 10 Fuel pump - - *** - - CC 1.000:1 25 450 25 Tachometer * * * * * C 0.500:1 7 50 5 Propeller governor - - (**) * ** C 0.866:1 125 1200 40 Propeller governor - - - - - C 0.895:1 125 1200 40 Propeller governor (**) - - - - C 0.850:1 125 1200 40 Freon compressor - - - - - C 1.462:1 Limited by belt Optional dual drives mounting on vacuum pump drive pad. Vacuum pump - ** ** ** ** CC 1.300:1 70 450 6 Hydraulic pump - ** ** ** ** CC 1.300:1 Total Total 10 or Vacuum pump - - (**) ** ** CC 1.300:1 70 450 6 Propeller governor - - (**) ** ** CC 1.300:1 Total Total 10 ( ) except A4A, A4AD, A4D, A4M, A4N , A4P are not eligible. *** A2E only Model O-360- Accessory A1G6D A1LD A1H6 A1H A2H B1A B1B B2A B2B B2C Rotating Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Static Starter - - - * * CC 13.556:1 - 450 150 Starter * * * ** ** CC 16.556:1 - 450 150 Generator - - - * * C 1.910:1 60 120 175 Generator - - - ** ** C 2.500:1 60 120 175 Alternator * * * - - C 3.250:1 60 120 175 Vacuum pump ** ** ** ** ** CC 1.300:1 70 450 25 Hydraulic pump - ** - - - C 1.300:1 100 800 40 Hydraulic pump - ** - - - C 1.300:1 180 2200 150 Fuel pump - - - ** ** CC 0.866:1 25 450 25 Fuel pump, plunger ** ** ** * * - 0.500:1 - - 10 Fuel pump - - - - - CC 1.000:1 25 450 25 Tachometer * * * * * C 0.500:1 7 50 5 Propeller governor - - - * - C 0.866:1 125 1200 40 Propeller governor - * (*) - - C 0.895:1 125 1200 40 Propeller governor * - - - - C 0.850:1 125 1200 40 Freon compressor - - [**] - - C 1.462:1 Limited by belt [A1H6 only] Optional dual drives mounting on vacuum pump drive pad. Vacuum pump ** - - ** ** CC 1.300:1 70 450 6 Hydraulic pump ** - - ** ** CC 1.300:1 Total Total 10 or Vacuum pump ** - - ** - CC 1.300:1 70 450 6 Propeller governor ** - - ** - CC 1.300:1 Total Total 10 - Indicates “does not apply” C Clockwise ** Optional * Standard CC Counter-clockwise ( ) Except A2H Page 7 of 13 E-286 Model O-360- Accessory C1A C1C C1E C2A C2C C2E J2A C2B C2D D1A Rotating Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Static Starter ** ** * - * CC 13.556:1 - 450 150 Starter * * - * - CC 16.556:1 - 450 150 Generator ** ** * * * C 1.910:1 60 120 175 Generator - - ** ** ** C 2.500:1 60 120 175 Alternator * * - - - C 3.250:1 60 120 175 Vacuum pump ** ** ** ** ** CC 1.300:1 70 450 25 Hydraulic pump - - - - - C 1.300:1 100 800 40 Hydraulic pump - - - - - C 1.300:1 180 2200 150 Fuel pump - - - - - CC 0.866:1 25 450 25 Fuel pump, plunger ** ** - - * - 0.500:1 - - 10 Fuel pump - - * * - CC 1.000:1 25 450 25 Tachometer * * * * * C 0.500:1 7 50 5 Propeller governor ** - - - * C 0.866:1 125 1200 40 Propeller governor - - - - - C 0.895:1 125 1200 40 Propeller governor - - - - - C 0.850:1 125 1200 25 Freon compressor - - - - - C 1.462:1 Limited by belt Optional dual drives mounting on vacuum pump drive pad. Vacuum pump ** ** ** ** ** CC 1.313:1 70 450 6 Hydraulic pump ** ** ** ** ** CC 1.313:1 Total Total 10 or Vacuum pump ** ** - - ** CC 1.300:1 70 450 6 Propeller governor ** ** - - ** CC 1.300:1 Total Total 10 Model O-360- LO-360- Accessory D2A D2B E1A6D E1AD E1BD E2AD E2BD E1A6D E1AD E1BD A1H6 E2AD E2BD Rotating Facing Drive Pad # Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Static Starter * - - - - CC 13.556:1 - 450 150 Starter - * * * * CC 16.556:1 - 450 150 Generator * - - - - C 1.910:1 60 120 175 Generator ** - - - - C 2.500:1 60 120 175 Alternator - * * * * C 3.250:1 60 120 175 Vacuum pump ** - - - - CC 1.300:1 70 450 25 Vacuum pump - ** ** ** ** C 1.300.1 70 450 25 Hydraulic pump - - - - - C 1.300:1 100 800 40 Hydraulic pump - - - - - C 1.300:1 180 2200 150 Fuel pump - - - - - CC 0.866:1 25 450 25 Fuel pump, plunger * ** ** ** ** - 0.500:1 - - 10 Fuel pump - - - - - CC 1.000:1 25 450 25 Tachometer * * * * * C 0.500:1 7 50 5 Propeller governor - - - - - C 0.866:1 125 1200 40 Propeller governor - - - - [*] C 0.895:1 125 1200 40 Propeller governor - - - - - C 0.850:1 125 1200 25 Propeller governor - ** - ** - C 1.000:1 125 1200 40 Freon compressor [**] C 1.462:1 Limited by belt [A1H6 only] Optional dual drives mounting on vacuum pump drive pad. Vacuum pump ** - - ** ** CC 1.300:1 70 450 6 Hydraulic pump ** - - ** ** CC 1.300:1 Total Total 10 or Vacuum pump ** - - ** - CC 1.300:1 70 450 6 Propeller governor ** - - ** - 1.300:1 Total Total 10 - Indicates “does not apply” C Clockwise ** Optional * Standard CC Counter-clockwise # LO models have opposite rotations E-286 Page 8 of 13 MODEL O-360 Accessory F1A6 G1A6 A1P C1G Rotating Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Static Starter - - - CC 13.556:1 - 450 150 Starter * * * CC 16.556:1 - 450 150 Generator - - - C 1.910:1 60 120 175 Generator - - - C 2.500:1 60 120 175 Alternator * * * C 3.250:1 60 120 175 Vacuum pump ** ** ** CC 1.300:1 70 450 25 Hydraulic pump ** ** ** C 1.300:1 100 800 40 Hydraulic pump - - - C 1.300:1 180 2200 150 Fuel pump - - - CC 0.866:1 25 450 25 Fuel pump, plunger ** * ** - 0.500:1 - - 10 Fuel pump - - - CC 1.000:1 25 450 25 Tachometer * * * C 0.500:1 7 50 5 Propeller governor - - - C 0.866:1 125 1200 40 Propeller governor ** * ** C 0.895.1 125 1200 40 Propeller governor - - - C 0.850.1 125 1200 25 Propeller governor C 1.000:1 125 1200 40 Freon compressor C 1.462:1 Limited by belt. Optional dual drives mounting on vacuum pump drive pad. Vacuum pump - - - CC 1.300:1 70 450 6 Hydraulic pump ** - - CC 1.300:1 Total Total 10 or Vacuum pump - - - CC 1.300:1 70 450 6 Propeller governor - - - CC 1.300:1 Total Total 10 Model HO-360- Accessory A1A B1B C1A Rotating Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in.-lb.) Max. Overhang Moment (in.-lb.) Cont. Stati c Starter - - - CC 13.556:1 - 450 150 Starter * * * CC 16.556:1 - 450 150 Generator * * - C 1.910:1 60 120 175 Generator ** ** - C 2.500:1 60 120 175 Alternator - - * C 3.250:1 60 120 175 Vacuum pump * * ** CC 1.300:1 70 450 25 Vacuum pump - - - C 1.300.1 70 450 25 Hydraulic pump - - - C 1.300:1 100 800 40 Hydraulic pump - - - C 1.300:1 180 2200 150 Fuel pump ** - - CC 0.866:1 25 450 25 Fuel pump, plunger ** - * - 0.500:1 - - 10 Fuel pump - * - CC 1.000:1 25 450 25 Tachometer * * * C 0.500:1 7 50 5 Propeller governor - - - C 0.866:1 125 1200 40 Propeller governor - - - C 0.895:1 125 1200 40 Propeller governor - - - C 0.850:1 125 1200 25 Propeller governor - - - C 1.000:1 125 1200 40 Freon compressor - C 1.462:1 Limited by belt Optional dual drives mounting on vacuum pump drive pad. Vacuum pump ** ** ** CC 1.300:1 70 450 6 Hydraulic pump ** ** ** CC 1.300:1 Total Total 10 or Vacuum pump - - - - - - - Propeller governor - - - - - - - - Indicates “does not apply” . C Clockwise **Optional * Standard CC Counter-clockwise Page 9 of 13 E-286 NOTE 4. Spark plugs: See latest revision of Lycoming Service Instruction No. 1042 for approved equipment. NOTE 5. The above models incorporate additional characteristics as follows: Models Wt. (Dry) Lb. Characteristics O-360-A1A 258 Basic Model. Four cylinder, horizontally opposed, air cooled, direct drive engine with provisions for supplying oil through propeller shaft for a single acting controllable pitch propeller. O-360-A1AD 257 Similar to O-360-A1A except is equipped with Bendix D4LN-2021 magneto instead of incorporating two single magnetos. O-360-A1C 261 Similar to O-360-A1A except has a rear mounted Bendix carburetor and 200 series magnetos. O-360-A1D 256 Similar to O-360-A1A except has Bendix 200 series magnetos. O-360-A1F 258 Similar to O-360-A1A except has Bendix 1200 impulse coupling, high altitude magnetos. O-360-A1F6 265 Similar to O-360-A1F except has counter-weighted crankshaft. O-360-A1F6D 264 Identifical to O-360-A1F6 except is equipped with one Bendix D4LN-2021 impulse coupling dual magneto instead of incorporating two single magneto O-360-A1G 262 Similar to O-360-A1F except has horizontal carburetor. O-360-A1G6 269 Identical to O-360-A1G except has crankshaft equipped with counterweights. See Note 12. O-360-A1G6D 266 Similar to O-360-A1G6 except is equipped with Bendix D4LN-2021 magneto instead of two single magnetos. O-360-A1H 263 Similar to O-360-A1G except crankcase has propeller governor drive mounted on left front instead of on engine accessory housing. O-360-A1H6 298 Similar to O-360-A1H except has crankshaft equipped with 6.3 and 8th order pendulum counterweights. Also, Slick magnetos incorporated. O-360-A1LD 259 Identical to O-360-A1A except is equipped with one Bendix D4LN-2021 impulse coupling dual magneto instead of incorporating two single magnetos. O-360-A1P 292 Same as O-360-C1G except has dynafocal engine mounts O-360-A2A 257 Similar to O-360-A1A except has no provisions for controllable pitch propeller. O-360-A2D 256 Similar to O-360-A1D except has no provisions for controllcable pitch propeller. O-360-A2E 256 Similar to O-360-A2D but has AN type fuel pump drive. O-360-A2F 258 Similar to 360-A1F except has no provisions for controllable pitch propeller. O-360-A2G 262 Similar to O-360-A1G but has no provisions for controllable pitch propeller. O-360-A2H 263 Similar to O-360-A1H except does not have propeller governor drive installed. O-360-A3A 257 Similar to O-360-A2A except has 6 special length bushings in propeller flange. O-360-A3AD 257 Identical to O-360-A3A except is equipped with Bendix D4LN-2021 magneto instead of Bendix S4LN-21 and S4LN-20 magnetos. O-360-A3D 256 Similar to O-360-A2D except has special long propeller attaching bushings for use with Sensenich fixed pitch propellers. O-360-A4A 265 Similar to O-360-A3A except has stiffer crankshaft. O-360-A4AD 265 Identical to O-360-A4A except is equipped with Bendix D4LN-2021 impulse coupling dual magneto instead of incorporating two single magnetos. O-360-A4D 297 Similar to O-360-A4A except has Bendix S4LN-200 retard breaker and S4LN-204 magnetos. O-350-A4G 270 Similar to O-360-A2G except incorporates a stiffer crankshaft and solid main bearing journals. O-360-A4J 269 Same as O-360-A4G except has different magnetos. O-360-A4K 265 Identical to O-360-A4J except is equipped with Slick 4051 and 4050 magnetos instead of with Bendix S4LN-21 and S4LN-204 magnetos. O-360-A4M 261 Identical to O-360-A4A except is equipped with Slick 4051 and 4050 magnetos instead of with Bendix S4LN-21 and S4LN-204 magnetos. O-360-A4N 296 Similar to O-360-A4M except has unmachined propeller governor pad on left front of crankcase. O-360-A4P 295 Similar to O-360-A4M except has short propeller flange bushings. E-286 Page 10 of 13 (cont’d) Models Wt. (Dry) Lb. Characteristics O-360-A5AD 265 Identical to O-360-A4AD except is equipped with six standard length propeller flange bushings instead of six special length bushings. O-360-B1A 256 Similar to O-360-A1A except has lower compression ration and power rating. O-360-B1B 255 Similar to O-360-B1A except has Bendix 200 series magnetos. O-360-B2A 256 Similar to O-360-B1A except has no provisions for controllable pitch propeller. O-360-B2B 255 Similar to O-360-B1B except has no provisions for controllable pitch propeller. O-360-B2C 288 Similar to O-360-B2A except has heavier IO-360-A crankshaft and rods. O-360-C1A 257 Similar to O-360-A1A except has crankcase machined for conical rubber mount bushings in place of dynafocal mountings. O-360-C1C 256 Similar to O-360-C1A except has Bendix 200 series magnetos. O-360-C1E 254 Identical to O-360-C1A except is equipped with Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-204 magnetos. O-360-C1F 288 Similar to O-360-A1G except has Slick 4050 and 4051 magnetos and rear type engine mounting instead of dynafocal type mount. O-360-C1G 292 Similar to O-360-C1A except propeller governor drive is located on the left front of the crankcase, location same as O-360-A1H. O-360-C2A 257 Similar to O-360-C1A except has no provision for controllable pitch propeller. O-360-C2B 261 Similar to 360-C2A except has rear mounted Bendix carburetor. O-360-C2C 256 Similar to O-360-C2A except has Bendix 200 series magnetos. O-360-C2D 260 Similar to O-360-C2B except has Bendix 200 series magnetos. O-360-C2E 254 Identical to O-360-C2A except is equipped with Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-20 magnetos. O-360-C4F 275 Similar to O-360-C1F except has a solid crankshaft and no provision for a prop governor O-360-C4P 275 Similar to O-360-A4M except has short propeller flange bushings and conical engine mounts O-360-D1A 254 Similar to O-360-B1A and -B2A respectively except has crankcase machined for conical rubber mount bushings in place of dynafocal mountings. O-360-D2B 253 Similar to O-360-D2A except has Bendix 200 series magnetos. O-360-E1AD 262 This model differs from the basic model in that it incorporates a crankcase with an integral accessory section, front mounted fuel pump, external mounted oil pump, automatic valve tappets and rocker arms and dual magneto. O-360-E1A6D 269 Identical to O-360-E1AD except is equipped with one 6.3 order and one 8th order counterweight. O-360-E2AD 262 Similar to O-360-E1AD except has no provisions for controllable pitch propeller. O-360-E1BD 262 Similar to O-360-E1AD except has Bendix D4RN-2200 retard breaker magnetos instead of Bendix D4RN-2021 impulse coupling magneto. O-360-E2BD 262 Similar to O-360-E1BD except has no provisions for controllable pitch propeller. O-360-F1A6 301 Similar to O-360-A1G6 except has two Slick 4191 magnetos, propeller governor drive on crankcase left front and oil sump designed for retracted nose wheel clearance. O-360-G1A6 303 Similar to O-360-F1A6 except has a machined pad on the right front of the crankcase for installation equipment. O-360-J2A 289 Similar to the O-360-C1C except has O-320-B2C prop flange bushings, light weight cylinders and lower power rating. HO-360-A1A 257 Similar to O-360-A1D except has dynafocal mounts and different series Marvel carburetor. HO-360-B1A 260 Similar to O-360-C2D has a different cam shaft. HO-360-B1B 260 Similar to HO-360-B1A except has Bendix 200 series retard breaker magnetos. HO-360-C1A 288 Similar to O-360-C2D except uses HA-6 carburetor in place of the PSH-5HD carburetor. LO-360-A1G6D 266 Similar to O-360-A1G6D except has counter-clockwise (reverse) rotation. LO-360-E1AD 262 Similar to O-360-E1AD except has counter-clockwise (reverse) rotation. Page 11 of 13 E-286 (cont’d) Models Wt. (Dry) Lb. Characteristics LO-360-E1A6D 269 Similar to O-360-E1A6D has counter-clockwise (reverse) rotation. LO-360-E2AD 262 Similar to O-360-E2AD except has counter-clockwise (reverse) rotation. LO-360-E1BD 262 Similar to O-360-E1BD except has counter-clockwise (reverse) rotation. LO-360-E2BD 262 Similar to O-360-E2BD except has counter-clockwise (reverse) rotation. LO-360-A1H6 298 Similar to O-360-A1H except has counter-clockwise (reverse) rotation. NOTE 6. These engines incorporate provisions for absorbing propeller thrust in both tractor and pusher type installations. NOTE 7. These engines are approved for horizontal helicopter applications and operation. NOTE 8. C.G. location (dry and without dual accessory drive). Model From Front Face of Prop. Shaft Flange, In. Off Propeller Shaft C.L., In. O-360-A series (except those listed below) 13.88 0.87 Below & 0.14 left O-360-B series 13.88 0.87 Below & 0.14 left HO-360-A1A 13.88 0.87 Below & 0.14 left O-360-C series (except -C2B, -C2D, -C1F) 13.88 0.87 Below & 0.14 left O-360-J2A 13.88 0.87 Below & 0.14 left O-360-A1G, -A2G, -A1H, -A4G, -A4J, -C1F, -C4F, -A1H6, HO-360-C1A 14.04 0.76 Below & 0.14 left O-360-A1AD, -A3AD, -A4AD, -A5AD, -A1F6D 13.77 0.82 Below & 0.30 left O-360-A1C, -C2B, -C2D 14.42 1.27 Below & 0.03 right HO-360-B1A, -B1B 14.42 1.27 Below & 0.03 right O, LO-360-A1G6D 13.93 0.71 Below & 0.30 left O-360-D1A, -D2A, -D2B 14.19 1.27 Below & 0.05 right O, LO-360-E1AD, -E1BD, -E2BD, -E1A6D 13.90 0.95 Below O-360-F1A6, -A4N, -G1A6 14.25 0.88 Below & 0.05 left NOTE 9. Model Ignition, Dual + Propeller Shaft SAE No. AS-127 Compression Ratio Carburetion O-360-A1A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1AD TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1C TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* PSH-5BD -A1D TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1F TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1F6 TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1F6D TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1G TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A1G6 TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange; Type 2 modified 8.5:1 PAC* HA-6 -A1G6D TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A1H S4LN-21; S4LN-204 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A1H6 Slick 4230; 4202 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A1LD TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A1P Slick 4373, 4370 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A2A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A2D TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A2E TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 + For alternate magnetos see latest revision of Textron Lycoming Service Instructio 1443 * Precision Airmotive (PAC) formallyFacet Aerproducts Inc. (formerly Marvel Schebler Co.) and Bendix on PSH-5BD carburetors ** Teledyne (TCM) formally Bendix E-286 Page 12 of 13 NOTE 9. (cont’d) Model Ignition, Dual + Propeller Shaft SAE No. AS-127 Compression Ratio Carburetion -A2F TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A2G TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A2H TCM** S4LN-21; S4LN-204 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A3A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A3AD TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A3D TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4A TCM** S4LN-21; S4LN-204 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4AD TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4D TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4C TCM** S4LN-1227; S4LN-1209 or S4LN-1227 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A4J TCM** S4LN-21; S4LN-204 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A4K Slick 4051; 4050 or 4051 Flange, Type 2 modified 8.5:1 PAC* HA-6 -A5AD TCM** D4LN-2021 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4M Slick 4051; 4050 or 4051 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4P Slick 4371; 4070 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -A4N Slick 4251(2) Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -B1A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -B1B, -B2B TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -B2A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -B2B TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -B2C TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -C1A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C1C TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C1E Slick 4051; 4050 or 4051 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C1F Slick 4050; 4051 Flange, Type 2 modified 8.5:1 PAC* HA-6 -C1G TCM** S4LN-21; S4LN-20 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C2A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C2B TCM** S4LN-21; S4LN-20 or S4LN-21 Flange 8.5:1 PAC* PSH-5BD -C2C TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C2D TCM** S4LN-200; S4LN-204 Flange 8.5:1 PAC* PSH-5BD -C2E Slick 4051; 4050 or 4051 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C4F Slick 4371; 4370 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -C4P Slick 4373, 4370 Flange, Type 2 modified 8.5:1 PAC* MA-4-5 -D1A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -D2A TCM** S4LN-21; S4LN-20 or S4LN-21 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 -D2B TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 7.2:1 PAC* MA-4-5 + For alternate magnetos see latest revision of Textron Lycoming Service Instructio 1443 * Precision Airmotive (PAC) formallyFacet Aerproducts Inc. (formerly Marvel Schebler Co.) and Bendix on PSH-5BD carburetors ** Teledyne (TCM) formally Bendix Page 13 of 13 E-286 NOTE 9. (cont’d) Model Ignition, Dual + Propeller Shaft SAE No. AS-127 Compression Ratio Carburetion -E1AD TCM** D4RN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E1A6D TCM** D4RN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E1BD TCM** D4RN-2200 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E2AD TCM** D4RN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E2BD TCM** D4RN-2200 Flange, Type 2 modified 9.0:1 PAC* HA-6 -F1A6 Slick 4191(2) Flange, Type 2 modified 8.5:1 PAC* HA-6 -G1A6 Slick 4251(2) Flange, Type 2 modified 8.5:1 PAC* HA-6 -J2A TCM** S4LN-200:S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4SPA HO-360-A1A TCM** S4LN-200; S4LN-204 Flange, Type 2 modified 8.5:1 PAC* MA-4-54A -B1A TCM** S4LN-200; S4LN-204 Flange 8.5:1 PAC* PSH-5BD -B1B TCM** S4LN-200; S4LN-200 Flange 8.5:1 PAC* PSH-5BD -C1A Slick 4347; 4370 Flange, Type 2 modified 8.5:1 PAC* HA-6 LO-360-A1G6D TCM** D4RN-2021 Flange, Type 2 modified 8.5:1 PAC* HA-6 -E1AD TCM** D4LN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E1A6D TCM** D4LN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E2AD TCM** D4LN-2021 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E1BD TCM** D4LN-2200 Flange, Type 2 modified 9.0:1 PAC* HA-6 -E2BD TCM** D4LN-2200 Flange, Type 2 modified 9.0:1 PAC* HA-6 -A1H6 Slick 4230; 4202 Flange, Type 2 modified 8.5:1 PAC* HA-6 + For alternate magnetos see latest revision of Textron Lycoming Service Instructio 1443 * Precision Airmotive (PAC) formallyFacet Aerproducts Inc. (formerly Marvel Schebler Co.) and Bendix on PSH-5BD carburetors ** Teledyne (TCM) formally Bendix NOTE 10. The Model O-360-A1B engine was cancelled from Engine Type Certificate No. E-286 on April 19, 1963. Models O-360-E1AD, -E2AD, -E1BD, -E2BD and LO-360-E1AD, -E2AD, -E1BD, and -E2BD were cancelled from Engine Type No. E-286 on May 24, 1978. No production models were manufactured. NOTE 11. Starters, generators, and alternators approved for use on these engines are listed in the latest revision of Textron Lycoming Service Instruction No. 1154. NOTE 12. Engines of this series incorporate no crankshaft dampers unless the digit “6” follows the model designation, i.e. -A1F “6”. Engines so designated have one 6.3 and one 8th order pendulum type counter-weight. ....END.... DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION P7EA REVISION 11 McCAULEY 2D34C B2D34C B2D37C C2D37C December 2, 2004 TYPE CERTIFICATE DATA SHEET NO. P7EA Propellers of models described herein conforming with this data sheet (which is part of Type Certificate No. P7EA) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with the pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder: McCauley Propeller Systems 7751 E. Pawnee Wichita, KS 67207 Type Constant speed; hydraulic (see Note 3) Engine Shaft SAE No. 2 flange modified (6-1/2” Mounting bolts) Hub Material Aluminum Alloy Blade Material Aluminum Alloy No. of Blades Two Hubs Eligible 2D34C8, 2D34C9, 2D34C11, B2D34C16, 2D34C53, B2D34C53, B2D34C202, B2D34C206, B2D34C207, B2D34C208, B2D34C211, B2D34C212, B2D34C213, B2D34C214, 2D34C215, B2D34C217, B2D34C218, B2D34C219, B2D34C220, B2D37C224, B2D37C229, B2D34C235, C2D37C236 Blades Eligible (See NOTE 2) Maximum Continuous HP RPM Take-Off HP RPM Diameter Limits (See NOTE 2) Approx. Max. Wt. Complete (For Ref. Only) (See NOTE 3) THREAD TYPE RETENTION Hub Models 2D34C53 or B2D34C53 74E-0 to 74E-4 180 2700 180 2700 74” – 70” (-0 to –4) 48 Lbs. Page No. 1 2 3 4 5 6 7 8 Rev. No. 11 9 11 11 11 10 10 10 P7EA Page 2 of 8 Blades Eligible (See NOTE 2) Maximum Continuous HP RPM Take-Off HP RPM Diameter Limits (See NOTE 2) Approx. Max. Wt. Complete (For Ref. Only) (See NOTE 3) Hub Model 2D34C8 78FB-0 to 78FB-6 200 2700 200 2700 78” – 72” (-0 to –6) 54 lbs. Hub Model 2D34C9 78FBM-0 to 78FBM-6 200 2700 200 2700 78” – 72” (-0 to –6) 55 lbs. Hub Model 2D34C11 or B2D34C16 84HF-0 to 84HF-12 260 2700 260 2700 84” – 72” (-0 to –12) 52 lbs. THREADLESS TYPE RETENTION Hub Model B2D34C212 78CDA-0 to 78CDA-6 200 2700 200 2700 78” – 72” (-0 to –6) 51 lbs. Hub Model B2D34C206 78TA-0 to 78PA-6 200 2700 200 2700 78” – 72” (-0 to –6) 51 lbs. Hub Model B2D34C207 78TCA-0 to 78TCA-6 200 2700 200 2700 78” – 72” (-0 to –6) 51 lbs. Hub Model B2D34C220 80VHA-0 to 80VHA-6 180 2700 180 2700 80” – 74” (-0 to –6) 52 lbs. Hub Model B2D34C202 or B2D34C208 82PA-6 to 82PA-10 180 2700 180 2700 76” – 72” (-6 to –10) 48 lbs. P7EA Page 3 of 8 Blades Eligible (See NOTE 2) Maximum Continuous HP RPM Take-Off HP RPM Diameter Limits (See NOTE 2) Approx. Max. Wt. Complete (For Ref. Only) (See NOTE 3) Hub Model B2D34C211 82PCA-6 to 82PCA-10 180 2700 180 2700 76” – 72” (-6 to –10) 48.5 lbs. Hub Model B2D34C213 90DHA-12 to 90DHA-18 200 2700 200 2700 78” – 72” (-12 to –18) 49.5 lbs. Hub Model B2D34C214, B2D34C217, B2D34C218 OR B2D34C219 90DHB-12 to 90DHB-18 200 2700 200 2700 78” – 72” (-12 to –18) 49.5 lbs. 90DHB-8 to 90DHB-18 235 2400 235 2400 82” – 72” (-8 TO –18) 50.5 lbs. Hub Model 2D34C215 90DJA-12 to 90DJA-18 200 2700 200 2700 78” – 72” (-12 to –18) 50.5 lbs. Hub Model B2D37C224 90RA-2 to 90RA-12 280 2700 280 2700 88” – 74” (-2 to –16) 52 lbs. Hub Model B2D37C229 90RHC-0 to 90RHC-18 300 2700 300 2700 90” – 72” (-0 to –18) 52 lbs. Hub Model B2D34C235 90DK[X]-0 to 90DK[X]-18 285 2750 285 2750 90” – 72” (-0 to –18) 50.5 lbs. Hub Model C2D37C236 90REA-2 to 90REA-12 280 2700 280 2700 88” – 78” (-2 to –12) 52 lbs. P7EA Page 4 of 8 Certification Basis Model 2D34C53/74E: Civil Air Regulations Part 14 effective December 15, 1956. Models 2D34C8/78FB and 2D34C11/84HF: 14 CFR Part 35 with Amendment 35-1 thereto. Model B2D37C224/90RA: 14 CFR Part 35 with Amendment 35-1 to 35-5 thereto. Model B2D37C229/90RHC: 14 CFR Part 35 with Amendment 35-1 to 35-5 thereto. Model B2D34C235/90DKB: 14 CFR Part 35 with Amendment 35-1 to 35-6 thereto. Model C2D37C236/90REA: 14 CFR Part 35 with Amendments 35-1 to 35-6 thereto. All Other Models: 14 CFR Part 35 with Amendments 35-1 to 35-2 thereto. Type Certificate No. P7EA issued September 5, 1962, under the Delegation Option Authorization provisions of Regulations of the Administrator Part 410. Date of Application for Type Certificate July 11, 1962. Production Basis Production Certificate No. 3 NOTE 1. Hub Model Designation Basic Model Designation B 2 D 34 C 53 -A Minor change not affecting interchangeability or eligibility. Any change affecting eligibility (number 100 or less; thread type retention, number 200 or more; threadless type retention arrangement) C denotes constant speed model. McCauley blade shank size. SAE No. 2 flange modified (6-1/2 inch mounting bolts). Number of blades. Indicates angular location of small diameter indexing holes for mounting bolts, with respect to blade centerline, when viewing hub from flange mounting face. Blank -0! and 180! clockwise; B-150! and 330! clockwise; C-30! and 210! clockwise. P7EA Page 5 of 8 NOTE 2. Blade Model Designation Basic Model Designation S - 74 E - 0 Reduction in inches from basic diameter (As –4, diameter reduced 4 inches to 70 inches.) Blades form characteristics, i.e., activity factor, planform, pitch distribution, etc. One or more letters may be used. Basic design diameter in inches. Indicates minor changes not affecting eligibility or interchangeability. NOTE 3. Pitch Control With the following governors: Woodward Model x,210,xxx Wt. 3.5 lb. Hoof Model 1,000,007 Series Wt. 3.5 lb. McCauley Model C290D1/T[X] Wt. 2.8 lb. McCauley Model C290D2/T[X] Wt. 2.8 lb. McCauley Model C290D3/T[X] Wt. 2.8 lb. McCauley Model C290D4/T[X] Wt. 2.8 lb. McCauley Model C290D5/T[X] Wt. 2.8 lb. McCauley Model C290D[X]/T[X] Wt. 2.8 lb. McCauley Model C290D1/T[X] Wt. 2.8 lb. McCauley Model DC[X][X][X]D1/T[X] Wt. 2.8 lb. NOTE 4. Not applicable NOTE 5. Left Hand Models. The left hand version of an approved model propeller is eligible at the same rating and diameter limitations as listed for the right hand model. NOTE 6. Not applicable NOTE 7. Accessories a. Spinners (1) 2D34C53, B2D34C53 and 2D34C11 models with McCauley spinners; D-2808 Dome, D-3148 Bulkhead and Fillet Assembly, and D-2809 Installation. (2) 2D34C8 and 2D34C9 models with McCauley spinners; D-3395 Dome, D-3686 Bulkhead and Fillet Assembly, and D-3683 Installation. (3) B2D34C235 model with McCauley spinner assembly D-7267. (4) C2D37C236 model with McCauley spinner assembly D-2137. P7EA Page 6 of 8 NOTE 8. Not applicable NOTE 9. Table of Propeller-Engine Combinations Approved Vibrationwise for Use on Normal Category Single-Engine Tractor Aircraft The maximum and minimum propeller diameters that can be used from a vibration standpoint are shown below. No reduction below the minimum diameter listed is permissible, since this figure includes the diameter reduction allowable for repair purposes. Hub Model Blade Model Engine Model Damper Configuration Max. Dia. (Inches) Min. Dia. (Inches) Placards 2D34C53 or B2D34C53 74E Lycoming 0-360 & IO-360 Series (up to 180 hp. @ 2700 rpm) None 74 72.5 *Avoid continuous operation while descending between 2250 & 2550 rpm with manifold pressure settings below 15” mercury. * Ref: Airworthiness Directive No. 70-4-1 B2D34C212 78CD A Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) One 6.3 and one 8th order 74 73 * Avoid continuous operation between 1600 & 1950 rpm below 15” manifold pressure. 2D34C8 or 2D34C9 78FB 78FB M Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) None 76.5 76.5 Avoid continuous operation between 2000 & 2150 rpm above 20” manifold pressure. B2D34C206 or B2D34C207 78TA 78TCA Lycoming O-360 and IO-360 Series (up to 180 hp. @ 2700 rpm) One 6.3 and one 8th order 78 76 Avoid continuous operation between 1400 & 1700 rpm below 10” manifold pressure. 76 74 Avoid continuous operation between 1450 & 1750 rpm below 10” manifold pressure. 74 72 Avoid continuous operation between 1450 & 1800 rpm below 10” manifold pressure. P7EA Page 7 of 8 Hub Model Blade Model Engine Model Damper Configuration Max. Dia. (Inches) Min. Dia. (Inches) Placards B2D34C206 or B2D34C207 78TA 78TCA Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) One 6.3 and one 8th order 78 76.5 Avoid continuous operation between 1400 & 1750 rpm below 10” manifold pressure. B2D34C15 78W Lycoming O-360 Series (up to 180 hp. @ 2700 rpm) None 74 72.5 Avoid continuous operation between 2000 & 2250 rpm above 18” manifold pressure. 2D34C202, B2D34C208 or B2D34C211 82PA 82PA 82PCA Lycoming O-360 Series (up to 180 hp. @ 2700 rpm) One 6.3 and one 8th order 76 75 Avoid continuous operation between 1700 & 1900 rpm below 10” manifold pressure. 75 74 Avoid continuous operation between 1700 & 2000 rpm below 10” manifold pressure. 2D34C11 84HF Lycoming O-540 Series (up to 235 hp. @ 2575 rpm) One 5th and one 6th order 84 80 None B2D34C16 84HF Lycoming O-540 Series (up to 260 hp. @ 2700 rpm) One 5th and one 6th order 84 80 None B2D34C213 or B2D34C214 90DH A 90DHB Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) One 6.3 and one 8th order 74 73 Avoid continuous operation between 1500 & 1950 rpm below 15” manifold pressure. B2D34C214 90DHB Lycoming O-540 Series (up to 235 hp. @ 2400 rpm) One 4.8 and one 6.3 order 82 78 None B2D34C213 90DH A Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) One 8th and one 6.3 order 76 75 Avoid continuous operation between 1400 & 1750 rpm below 15” manifold pressure. P7EA Page 8 of 8 Hub Model Blade Model Engine Model Damper Configuration Max. Dia. (Inches) Min. Dia. (Inches) Placards B2D34C213 90DH A Lycoming IO-360 Series (up to 200 hp. @ 2700 rpm) One 8th and one 6.3 order 75 74 Avoid continuous operation between 1450 & 1850 rpm below 15” manifold pressure. NOTE 10. Special Notes. Aircraft installation must be approved as part of the aircraft certificate upon compliance with the applicable aircraft airworthiness requirements. …END…