TCDS A26EU

Page No. 1 2 3 4 5 6 Rev. No. 6 3 6 4 4 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A26EU Revision 6 Textron Aviation F177RG January 6, 2025 WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel system component damage and is therefore prohibited on Cessna airplanes. TYPE CERTIFICATE DATA SHEET NO. A26EU This data sheet, which is a part of Type Certificate No. A26EU, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 Type Certificate A26EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, to Cessna Aircraft Company on December 11, 2006. Coincident with this transfer, the Federal Aviation Administration (FAA) has accepted responsibilities of State of Design for all airplanes, and State of Manufacture for airplanes manufactured after December 11, 2006, as defined by Annex 8 to the Convention on International Civil Aviation. Prior to December 11, 2006, products identified under Type Certificate A26EU were approved by the FAA in accordance with the Federal Aviation Regulation appropriate to Imported Products (FAR 21.29). Effective December 11, 2006, and after, these products are to be considered domestic products for the purpose of design certification, continued airworthiness, and administered under Federal Aviation Regulations §21.21. I. Model F177RG, 4 PCLM (Normal Category), Approved April 26, 1971 Engine Lycoming IO-360-A1B6 or IO-360-A1B6D *Fuel 100/130 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm (200 hp) Propeller and 1. McCauley propeller Propeller Limits Hub: B2D34C206/78TA Diameter: Not over 78 in., not under 76.5 in. Pitch at 30-inch station: Low pitch: 12.9  High pitch: 27.5  a. Hydraulic governor: (1) Woodward C210460 (IO-360-A1B6 only). (2) McCauley C290D2/T11 (IO-360-A1B6), or C290D2/T12 (IO-360-A1B6D). b. Cessna spinner: 0752637 A26EU 2 Rev. 6 I. Model F177RG (cont’d) Propeller and 2. McCauley propeller Propeller Limits (cont’d) Hub: B2D34C207/78TCA Diameter: Not over 78 in., not under 76.5 in. Pitch at 30-inch station: Low pitch: 12.9  High pitch: 27.5  a. Hydraulic governor: (1) Woodward C210460 (IO-360-A1B6 only). (2) McCauley C290D2/T11 (IO-360-A1B6), or C290D2/T12 (IO-360-A1B6D). b. Cessna spinner: 0752637 *Airspeed Limits (CAS) Never exceed 195 mph (169 knots) Maximum structural cruising 160 mph (139 knots) Maneuvering 130 mph (113 knots) Flaps extended 110 mph ( 96 knots) Landing gear operating speed 140 mph (122 knots) Landing gear extended speed 140 mph (122 knots) C.G. Range (+101.0) to (+114.7) at 2200 lb. or less (Landing gear extended) (+105.8) to (+114.7) at 2800 lb. Straight line variation between points given. Moment change due to retracting landing gear (+2776 in. -lb.) Empty Wt. C.G. Range None *Maximum Weight Normal category 2800 lb. Number of Seats Four (two at sta. +93.0, two at sta. +145.0) Maximum Baggage 120 lb. (+154.5 fwd. of wheel well, +178.5 aft of wheel well) Fuel Capacity S/N F177RG0001 thru F177RG0062 51 gal. (two 25.5 gal. fuel bays in wing at sta. +112; 50 gal. usable). S/N F177RG0063 and On: 61 gal. (two 30.5 gal. fuel bays in wing at sta. +112; 60 gal. usable). See NOTE 1 for data on unusable fuel. Oil Capacity W ithout oil filter: 8 qt. (+44), (2 qt. unusable) With oil filter: 9 qt. (+45). (3 qt. unusable; 2 qt. in sump plus 1 qt. in oil filter). See NOTE 1 for data on undrainable oil. Control surface movements Wing Flaps Down 30° + 2° -0° Aileron Up 20° + 2° Down 15° + 2° Stabilator Up 20° + 1° Down 5° + 1° Stabilator tab Up 5° + 1° Down 13° + 1° Rudder (measured Right 24° + 1° Left 24° + 1° perpendicularly to hinge line) Serial No’s Eligible F177RG0001 thru F177RG0177 Rev. 6 3 A26EU DATA PERTINENT TO ALL MODELS Datum 54.0 forward of front face of lower portion of firewall Leveling Means Jig located nutplates and screws at sta. +213.0 and sta. +238.0 on left of tailcone. Certification Basis Part 23 of the Federal Avia tion Regulations (FAR) dated February 1, 1965, as amended by 23-1 thru 23-6. Application for Type Certificate dated 26 April 1971. Type Certificate No. A26EU issued 17 May 1971, obtained by the manufacturer under delegation option procedures. Compliance for the Carry-Thru Spar Spare (P/N 171076-1) has been demonstrated in accordance with 14 CFR 23.572(a)(1)(b) as amended by Amendment 23-48. 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 item of equipment is required: Stall warning indicator, Cessna Dwg No. 2070002. 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. The certificated empty weight and the corresponding center of gravity locations must include undrainable oil of 0.0 lb. at 44.0 and unusable fuel of 6 lb. at 100.0 NOTE 2. The following placards must be displayed as indicated: 1. In full view of the pilot: “This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings, and manuals. MAXIMUMS Maneuvering speed 130 mph-CAS (113 knots) Gear extension speed 140 mph-CAS (122 knots) Gross weight 2800 lb. Flight load factor Flaps up +3.8 -1.52 Flaps down +2.0 No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery 190 ft. 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" A26EU 4 Rev. 6 DATA PERTINENT TO ALL MODELS NOTE 2. (cont’d) 3. By fuel valve (at appropriate locations): a. S/N F177RG0001 thru F177RG0062: "ON - 50 GAL. OFF" b. S/N F177RG0063 and On: "BOTH - 60 GAL. LEFT - 30 GAL" RIGHT - 30 GAL. Use both for take-off and landing. When switching from a dry tank, turn auxiliar y pump on and use full rich mixture until power is restored." 4. Aft of fuel tank cap: a. S/N F177RG0001 thru F177RG0062: "Service this airplane with 100/130 grade aviation gasoline. Total capacity 25.5 gal. Capacity to line of holes inside filler neck, 22.0 gal." b. S/N F177RG0063 and On "Service this airplane with 100/130 grade aviation gasoline. Total capacity 30.5 gal. Capacity to line of holes inside filler neck, 22.0 gal." 5. In baggage compartment: a. "120 lb. maximum baggage. b. For additional loading instructio ns see weight and balance data." 6. Next to door ventilation windows: "Do not open window above 120 mph or when using alternate static source." 7. On airspeed indicator: a. "Radial red line 195 mph (CAS) b. Yellow arc 160 - 195 mph (CAS) c. Green arc 70 - 160 mph (CAS) d. White arc 60 - 110 mph (CAS)" 8. On oil temperature gage: a. “Red line at 245° F b. Green arc 100° to 245° F” 9. On oil pressure gage: a. “Red line at 25 psi b. Green arc 60 psi to 90 psi c. Red line at 100 psi” 10. Tachometer: "Normal operating 2100 - 2500 rpm (green arc) Caution 1400 - 1750 rpm (yellow arc) Maximum allowable 2700 rpm (red line)" 11. On fuel flow gage: a. “Red line at 10 psi b. Green arc 6 to 13 gph” 12. Near fuel flow gage: a. “Max. power Alt. S.L. 4000 8000 12000 b. Mixture GPH 17 15 13 10” Rev. 6 5 A26EU DATA PERTINENT TO ALL MODELS NOTE 2. (cont’d) 13. On flap control indicator: a. "0 to 10° - T.O. (Takeoff range with blue color code and 150 mph callout; also, mechanical detent at 10°)." b. "10° - 20° - 30° (Indices at these positions with white color code and 110 mph callout; also, mechanical detent at 20°)." 14. Proximity of tachometer: "Avoid continuous operation between 1400-1750 rpm with less than 10" manifold pressure." 15. On cylinder head temperature gage: a. “Red line at 475° F” b. “Green arc 200° to 475° F” 16. On instrument panel (S/N F177RG0001 thru F177RG0042 only): "Do not turn off alternator in flight except in emergency." 17. On Emergency Landing Gear Pump Handle Cover: "EMERGENCY HAND PUMP PULL UP TO EXTEND GEAR MANUALLY: a. Place gear leve r in down position. b. Extend pump handle. c. Pump approximately 40 pressure strokes. d. Stop when resistance becomes heavy. e. Verify gear is down by observing green light. IMPORTANT To permit gear retraction after hand pump use full relief valve knob for a minimum period of five seconds. Then move gear lever to the UP position." 18. On manifold pressure gage: "15 to 25 in.hg. (green arc)." NOTE 3. The cylinder head probe location for the Model F177RG is the No. 3 cylinder. In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Section I of this data sheet must also be displayed by permanent markings. NOTE 4. Aircraft manufactured in France prior to December 11, 2006, and subsequently placed on the U.S. Registry, may be granted a U.S. Airworthiness Certificate based on 14 CFR Part 21, Section 21.183(d). This will be a recurrent airworthiness certification and requires a statement or attestation of conformity to the applicable type design at the time of original manufacture be obtained from the DGAC France (e.g., the French TC / U.S. 21.29). This “baseline” conformity determination can then be used as a starting point for which to evaluate the aircraft’s present conformity of type design and condition for safe operation as required by 21.183(d) (e.g., review of all modifications and repairs, AD compliance, appropriate maintenance, etc., depending upon the current exporting authority and any applicable bilateral agreement). A26EU 6 Rev. 6 DATA PERTINENT TO ALL MODELS NOTE 5. Service Information The appropriate airplane service manual contains structural retirement lives, which may not be changed without FAA Engineering approval, for the following components: Component Part Numbe r Hours Model Numbe r Wing Carry-Thru Spar 1710706-1 23,800 177 Series a. If geophysical mapping missions have been flown, the operator must contact Textron Aviation prior to 23,800 flight hours (or within the next 300 flight hours if 23,800 hours on the carry-thru spar has been exceeded). b. Refer to Section 2A-14-22, S upplemental Inspection No. 53-11-04. ------ END ------