Emergency Procedures for the Piper PA-34 Seneca III

AIRPLANE FLIGHT MANUAL LOG OF REVISIONS (cont) Revision Revised Pages 6 3-3 3-6 Description Revised item J. (Usable Fuel). FAA Approved Date 3-14a 7 3-6a Revised standard fuel placard desc.; added opt. fuel placard; revised windshield heat placard desc. Revised item 5. - Engine Driven Fuel Pump Failure. Ward Evans Ward Evans Oct. 20, 1975 Added Pitot Heat and Winterization Placards. Ward Evans 8 3-1 Added two propellers. 9 3-10 3-14 10 3-1 3-35 thru 3-42 Added item b. (1) (c). Added item 4. a. (3). Revised item A. (Engines). Revised Alt. IIIC Autopilot Supplement. Title Page 3-21 Added serial numbers. Revised item D, added para. Ward Evans March 19, 1976 Ward Evans Ward Evans May 13, 1976 Wand Evens Ward Evans March 30, 1977 Ward Evans Ward Evans Jan. 18, 1979 Ward Evans Ward Evans June 10, 1983 FAA APPROVED OCTOBER 20, 1975 REVISED: JUNE 10, 1983 REPORT: VB-628 PAGE 3-v MODEL: PA-34-200T SECTION I LIMITATIONS SENECA II The following limitations must be observed in the operation of this airplane: A. B. C. D. ENGINES Continental TSIO-360-E or TSIO-360-EB, Left Side & LTSIO-360-E or LTSIO-360-EB, Right Side. FUEL 100/130 Octane Aviation Gasoline (Minimum) PROPELLERS Hartzell BHC-C2YF-2CKF/FC8459-8R, Left Side & BHC-C2YF-2CLKF/FJC8459-8R, Right Side, or BHC-C2YF-2CKUF/FC8459-8R, Left Side & BHC-C2YF-2CLKUF/ FJC8459-8R, Right Side. When propeller deicing boots are installed: Hartzell BHC-C2YF-2CKF/FC8459B-8R, Left Side & BHC-C2YF-2CLKF/FJC8459B-8R, Right Side. Avoid continuous operation between 2000 and 2200 RPM above 32 In. Hg. manifold pressure. Avoid continuous ground operation between 1700 and 2100 RPM in cross and tail winds of over 10 knots. INSTRUMENT MARKINGS (POWER PLANT) OIL TEMPERATURE Green Arc (Normal Operating Range) Red Line (Maximum) OIL PRESSURE Green Arc (Normal Operating Range) Yellow Arc (Caution) Yellow Arc (Caution) Red Line (Minimum) 75° F to 240°F 240°F 30 PSI to 80 PSI 10 PSI to 30 PSI 80 PSI to 100 PSI 10 PSI 100 PSI Red Line (Maximum) TACHOMETER Green Arc (Normal Operating Range) Yellow Arc (Avoid continuous operation above 32" Hg. manifold press.) Red Line (Maximum) 500 RPM to 2000 RPM & 2200 RPM to 2575 RPM 2000 RPM to 2200 RPM 2575 RPM FAA APPROVED JULY 15, 1974 REVISED: JANUARY 18, 1979 REPORT: VB-628 PAGE 3-1 MODEL: PA-34-200T SENECA II FUEL FLOW AND FUEL PRESSURE Green Arc (Normal Operating Range) Red Line (Maximum) Red Line (Minimum) CYLINDER HEAD TEMPERATURE Green Arc (Normal Range) Red Line (Maximum) EXHAUST GAS TEMPERATURE Red Line MANIFOLD PRESSURE Green Arc (Normal Range) Red Line (Maximum) 3.5 PSI to 20 PSI 25 GPH, 20 PSI 3.5 PSI 360°F to 460°F 460°F 1650°F 10 IN. to 40 IN. HG. 40 IN. HG. E. AIRSPEED LIMITATIONS AND INDICATOR MARKINGS (Calibrated Airspeed) NEVER EXCEED SPEED MAXIMUM STRUCTURAL CRUISING SPEED DESIGN MANEUVERING SPEED MAXIMUM FLAPS EXTENDED SPEED MAXIMUM GEAR EXTENDED SPEED MAXIMUM GEAR RETRACT SPEED MINIMUM CONTROL SPEED (Single Engine) AIRSPEED INDICATOR MARKINGS Green Arc (Normal Operating Range) Yellow Arc (Caution Range - Smooth Air) White Arc (Flaps Extended Range) Radial Red Line (Never Exceed - Smooth Air) Radial Red Line (Minimum Control Speed - Single Engine) Radial Blue Line (Best R/C Speed Single Engine) F. FLIGHT LOAD FACTORS (Flaps Up) Positive Load Factor (Maximum) Negative Load Factor (Maximum) G. MAXIMUM TAKEOFF WEIGHT MAXIMUM LANDING WEIGHT MAXIMUM ZERO FUEL WEIGHT 224 MPH 190 MPH 140 MPH 125 MPH 150 MPH 125 MPH 80 MPH 76 MPH to 190 MPH 190 MPH to 224 MPH 70 MPH to 125 MPH 224 MPH 80 MPH 105 MPH 3.8 G No inverted maneuvers approved 4570 LBS. 4342 LBS. 4000 LBS. REPORT: VB-628 PAGE 3-2 MODEL: PA-34-200T FAA APPROVED JULY 15, 1974 H. C. G. RANGE Weight Pounds 3400 4570 SENECA II Forward Limit Inches Aft of Datum Aft Limit Inches Aft of Datum 82.0 90.6 94.6 94.6 NOTES 1. Straight line variation between the points given. 2. Datum is 78.4 inches forward of wing leading edge from the inboard edge of the inboard fuel tank. 3. I. J. It is the responsibility of the airplane owner and the pilot to assure that the airplane is properly loaded. Maximum allowable gross weight is 4570 pounds. See "Weight and Balance Section" for proper loading instructions. UNUSABLE FUEL The unusable fuel in this aircraft has been determined as 2.5 gallons in each wing in critical flight attitudes (2.5 gallons is the total per side, each side having interconnected tanks). USABLE FUEL The usable fuel in this aircraft has been determined as 46.5 gallons in each wing or a total of 93 gallons with standard fuel tanks and 61.5 gallons in each wing or a total of 123 gallons with optional fuel tanks installed. FAA APPROVED JULY 15, 1974 REVISED: OCTOBER 20, 1975 REPORT: VB-628 PAGE 3-3 MODEL: PA-34-200T * + SENECA II K. PLACARDS In full view of the pilot: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS. NO ACROBATIC MANEUVERS (INCLUDING SPINS) APPROVED. THIS AIRCRAFT APPROVED FOR V.F.R., I.F.R., DAY, NIGHT AND ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. In full view of the pilot: MAXIMUM TAKEOFF WEIGHT 4570 POUNDS MAXIMUM LANDING WEIGHT 4342 POUNDS ALL WEIGHT IN EXCESS OF 4000 POUNDS MUST CONSIST OF FUEL. On instrument panel in full view of the pilot: "DEMONSTRATED CROSSWIND COMPONENT 20 MPH" "MINIMUM SINGLE ENGINE CONTROL SPEED 80 MPH" 1. 2. 3. 4. "GEAR DOWN "GEAR UP "ROUGH AIR OR MANEUVERING SPEED 140 MPH" 150 MPH MAX" 125 MPH MAX" 150 MPH MAX" "EXTENDED Near emergency gear release: "EMERGENCY GEAR EXTENSION, PULL TO RELEASE" REPORT: VB-628 PAGE 3-4 FAA APPROVED JULY 15, 1974 MODEL: PA-34-200T Near gear selector switch: "GEAR UP "DOWN 125 MPH MAX" 150 MPH MAX" SENECA II Adjacent to upper door latch (Front and rear doors): In full view of pilot: "ENGAGE LATCH BEFORE FLIGHT" - WARNING TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT, OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On the inside of forward baggage compartment door: "MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS. SEE THE LIMITATIONS SECTION OF THE AIRPLANE FLIGHT MANUAL." On aft baggage closeout: "MAXIMUM BAGGAGE THIS COMPARTMENT 100 LBS. NO HEAVY OBJECTS ON HAT SHELF." On instrument panel: "SINGLE ENGINE STALLS NOT RECOMMENDED. CAN CAUSE 500 FT. LOSS OF ALTITUDE AND 15° PITCH ANGLE." On instrument panel: 1. Models without primer system installation* "TAKEOFF CHECK LIST Fuel Selectors On Electric Fuel Pumps Off Alternators On Engine Gauges Checked Mixtures Set Propellers Set Alt. Air Off Cowl Flaps Set Seat Backs Erect Flaps Set Trim Set (Stab. & Rudder) Fasten Belts/Harness Controls Free - Full Travel Doors Latched" "LANDING CHECK LIST Seat Backs Erect Fasten Belts/Harness Fuel Selectors On Cowl Flaps Set Electric Fuel Pumps Off Mixtures Rich Propellers Set Gear Down Flaps Set 125 MPH Max." *Ser. nos. 34-7570001 through 34-7570308 when Piper Kit No. 760 926V is not installed. FAA APPROVED JULY 15, 1974 REVISED: JULY 16, 1975 REPORT: VB-628 PAGE 3-5 MODEL: PA-34-200T X SENECA II 2. Models with primer system installation* "TAKEOFF CHECK LIST Fuel Selectors On Aux. Fuel Pumps Off Alternators On Engine Gauges Checked Mixtures Set Propellers Set Alt. Air Off Cowl Flaps Set Seat Backs Erect Flaps Set Trim Set (Stab. & Rudder) Fasten Belts/Harness Controls Free Full Travel Doors Latched" "LANDING CHECK LIST Seat Backs Erect Fasten Belts/Harness Fuel Selectors On Cowl Flaps Set Aux. Fuel Pumps Off Mixtures Rich Propeller Set Gear Down Flaps Set 125 MPH Max." Adjacent to fuel tank filler cap with standard fuel tanks alone installed: "FUEL 100/130 AVIATION GRADE - USABLE CAPACITY 46.5 GAL." Adjacent to fuel tank filler cap with optional fuel tanks installed: - "FUEL 100/130 AVIATION GRADE-USABLE CAPACITY 61.5 GAL." On storm window: "DO NOT OPEN ABOVE 150 MPH" Near windshield panel heat switch with windshield heating installation: "WINDSHIELD PANEL HEAT - SEE AIRCRAFT FLIGHT MANUAL." On engine instrument panel cover to left of engine controls with windshield heating installation without the entire Ice Protection System installed: "WARNING - THIS AIRCRAFT IS NOT APPROVED FOR FLIGHT IN ICING CONDITIONS." In full view of the pilot for flight with the aft fuselage doors removed: "FOR FLIGHT WITH AFT DOORS REMOVED, CONSULT THE LIMITATIONS AND PROCEDURES SECTIONS OF THE AIRPLANE FLIGHT MANUAL." *Ser. nos. 34-7570309 and up and 34-7570001 through 34-7570308 when Piper Kit No. 760 926 V is installed. REPORT: VB-628 PAGE 3-6 MODEL: PA-34-200T FAA APPROVED JULY 15, 1974 REVISED: OCTOBER 20, 1975 Beneath the pitot heat switch: "GND. OPP. 3 MIN. MAX." On the inside of both oil filler access doors: "OIL COOLER WINTERIZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50° F." SENECA II L. GYRO PRESSURE GAUGE M. The operating limits for the pressure system are 4.5 to 5.2 inches of mercury for all operations. FLIGHT INTO KNOWN ICING CONDITIONS For flight in icing conditions the following equipment must be installed in accordance with Piper drawings or in an FAA approved manner: 1. 2. Pneumatic wing and empennage boots Electrothermal propeller boots Electric windshield panel Heated pitot head 3. 4. 5. Wing ice light 6. 7. Propeller spinners must be installed. N. HEATER OPERATION Heated stall warning transmitters 0. Operation of the combustion heater above 25,000 feet is not approved. MAXIMUM OPERATING ALTITUDE Flight above 25,000 feet is not approved. Flight up to and including 25,000 feet is approved if equipped with oxygen in accordance with FAR 23.1441 and avionics in accordance with FAR 91 or FAR 135. FAA APPROVED AUGUST 5, 1974 REPORT: VB-628 PAGE 3-6a REVISED: MARCH 19, 1976 MODEL: PA-34-200T 98-04-27 THE NEW PIPER AIRCRAFT CORPORATION Amendment 39-10339 Docket No. 97-CE-61-AI Applicability: Models PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250, PA-30, PA-39, PA-40, PA-31, PA-31-300, PA-31-325, PA-31-350, PA-34-200, PA-34-200T, PA-34-220T, PA-42, PA-42-720, PA-42-1000 airplanes (all serial numbers), certificated in any category. 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 (d) 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 already accomplished. 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) (1) 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 (supercooled 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. 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 CONDITIONS MAY BE CONDUCIVE TO SEVERE IN-FLIGHT ICING: Visible rain at temperatures below 0 degrees Celsius ambient air temperature. Droplets that splash or splatter on impact at temperatures below 0 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 00/01 100