Mooney M22 Mustang Pilot's Operating Handbook

Carbon Monoxide 11-3 11.4 Decompression Sickness 11-4 11.5 Nitrogen Washout 11-5 Article 2 Oxygen Delivery Systems 11.6 Types of Systems 11-5 11.7 Flow Meters 11-6 11.8 Breathing Devices 11-6 11.9 Efficiency of Oxygen Delivery Systems 11-7 11.10 Pulse Oximetry 11-8 Mooney Aircraft Pilots Association Safety Foundation Pilot Proficiency Program vii Table of Contents INTRODUCTION Purpose For an aircraft to perform safely throughout its design envelope it must be properly maintained and flown by a conscientious and proficient pilot who understands the impacts of total weight and atmospheric conditions on the intended mission. The MAPA Safety Foundation (MAPASF) has structured this Pilot Proficiency Program to address all of the above factors as they apply specifically to the M20 aircraft series. This manual is intended to provide those who attend the Mooney Pilot Proficiency Program with a set of notes, which can become a part of the student's aviation library. Materials and subjects discussed during the ground school sessions are included together with selected additional references. The MAPA Safety Foundation gratefully acknowledges the generous assistance, information and publications provided by the Mooney Aircraft Corporation. Objectives Objectives of the MAPA Safety Foundation Pilot Proficiency Program are: ( viii A. To enhance Mooney pilots' safety, enjoyment, and effective use of their aircraft. ( B. To present an organized approach to the flight planning areas of Weight and Balance and Aircraft Performance. C. To improve proficiency and assist in completing flight reviews through type-specific flight instruction. 1 D. To provide information on Mooney aircraft systems, ADs, SBS, SIs, and inspection/maintenance procedures. ! MAPA Safety Foundation ( Į i Table of Contents M20 Series History and Overview Production of the M20 (Al Mooney's twentieth design) series began with the granting of the M20 Type Certificate (TC) on August 24, 1955. A 165 hp Lycoming engine was standard until 1958 when the M20A (TC: Feb. 13, 1958) became the first of a long line to use 180 hp Lycoming. The wood-winged airplane was metallized to create the M20B (TC: Dec. 14, 1960). The M20C came a year later (TC: Oct. 20, 1961), and was a refinement of the M20B. The fixed gear, fixed propeller M20D "Master" (TC: Oct 15, 1962) was introduced as an attempt to reach a lower price market, but most M20Ds have been converted to the M20C configuration. Power was increased with the installation of an injected 200 hp Lycoming in the M20E (TC: Sep. 4, 1963). Next came the M20F (TC: Jul. 25, 1965), and a fuselage ten inches longer. The long body M20G "Statesman" (TC: Nov 13, 1967) was the last Mooney to be powered by the 180 hp carbureted Lycoming. Although not in the M20 Series, the all-new pressurized M22 "Mustang" began a five-year production run in 1966, which totaled only 32 aircraft. These aircraft were powered by the turbocharged 310 hp Lycoming TIO-541-A1A engine. From 1969 to 1973, the manufacturer changed ownership several times, but the basic M20 design was retained, and in 1973 returned to the market as the M20C, E, and F models. In 1977 Roy Lopresti introduced the M20J "201" (TC: Sep 27, 1976) which attained 201 mph, still using 200 hp on the basic M20 airframe. In 1979 the M20K (TC: Nov 16, 1978) mounted a six-cylinder turbocharged 210 hp Continental under a lengthened nose and reached 231 mph. The M20L, powered by an aviation certified Porsche engine with computerized single lever power control, was introduced in 1988 although only about 50 have been produced. In 1989, the M20M "TLS", powered by a new 260 hp, 540 cubic inch turbocharged Lycoming, was introduced. This plane is the world's fastest four place production aircraft. Beginning in mid 1991, production M20J aircraft were certified at a new maximum gross weight of 2900 lb., an increase over the former 2740 lb. Some late model existing M20Js may also be re-certifiable at the higher max. gross weight. Pilot Proficiency Program ix Introduction Questions regarding re-certification of existing M20Js should be referred to Mooney Aircraft Corporation. In 1994 Mooney added the M20R `Ovation' to its product line, using the Teledyne Continental Motor (TCM) model IO-550-G5 normally aspirated engine. The basic airframe is like the TLS, however the interior had been completely up-dated. This new interior was added later to the TLS as standard equipment. In 2000 MAC added the "Ovation2" with same IO-550-G5 engine, and a new high performance two bladed McCauley propeller, replacing the 3- bladed on the previous Ovation. The avionics was up-dated to the latest Garmin 430 (530) array giving the panel a "glass cockpit look." By popular demand, the M20K was re-introduced in 1997 as the Encore. New to this model is the Teledyne Continental Motors turbocharged intercooled 220 hp. TSIO-360-SB engine. Along with this improved engine is an additional 200 lbs. to the gross weight. Depending on how the aircraft is equipped, average payload is 650 lbs. The additional weight is supported with the TLS main gear and brakes. Wing and power loading changed slightly: Wing loading - 17.7 lbs/sq. ft.; Power loading - 14.1 lbs/hp. The increased hoursepower enhanced the climb and cruise performance by about 4%. In February of 1999, Mooney introduced the M20S Eagle. This airplane is aerodynamically identical from the firewall aft to the M20R Ovation, but makes only 244 horsepower compared to the Ovation's 280 horsepower. The Eagle uses the same Continental IO-550 engine as the Ovation, but turns the engine at a maximum of 2400 rpm compared to the Ovation's 2500 rpm. Moreover, the Eagle comes with a two bladed McCauley constant speed propeller in place of the Ovations three bladed model. The M20 Eagle's maximum fuel load is 75 US gallons compared to 89 US gallons usable for the Ovation. The 305 Rocket is a conversion produced by Rocket Engineering Corp. The conversion is on the Mooney M20K (231 & 252) aircraft. Rocket replaces the stock 210 HP TSİO-360 engine with a 520 cubic inch 305 HP turbocharged intercooled Continental TSIO-520-NB engine, along with a feathering three-blade prop. The 300 Missile is also a conversion from Rocket Engineering. Based on the M20J airframe, Rocket replaces the IO-360 series engine with a Continental IO-550-A 300 HP normally aspirated engine along with a three blade full feathering prop. ( ✗ ! MAPA Safety Foundation ( First Things First CHAPTER 1. WEIGHT AND BALANCE This section addresses a critical flight planning area, the determination of payload (passengers and baggage) and usable fuel loading. Terminology is presented followed by discussions of reference datum and wing loading and a practical weight and balance problem. (A second critical flight planning area, the use of performance charts, is discussed in Chapter 3.) Terminology To minimize confusion over the definitions of various terms, we begin by. referring to the "Weight and Balance Terminology" pages found in the General Section of current Mooney Pilot Operating Handbooks (POHS). Arm Basic Empty Weight Center of Gravity (CG) CG Arm CG in % MAC CG Limits The horizontal distance from the reference datum to the center of gravity (CG) of an item or load. The actual weight of the airplane and includes all operating equipment (including optional equipment) that has a fixed location and is actually installed in the aircraft. It includes the weight of unusable fuel and full oil. Note that installed optional equipment includes loose items such as the POH or tow bar. The point at which an airplane (gear extended) would balance if suspended. CG distance from the reference datum is found by dividing the total moment by the weight of the airplane. The CG arm is obtained by adding the airplane's individual moments and dividing by total weight. Center of Gravity (location) expressed in percent of mean aerodynamic chord. The extreme center of gravity locations within which the airplane must be operated at a given weight. Pilot Proficiency Program Page 1-1 Weight and Balance MAC Maximum Weight Moment Payload Reference Datum Standard Empty Weight Station Tare Unusable Fuel Mean Aerodynamic Chord. ("Average" chord) The maximum authorized weight of the aircraft and its contents as listed in the aircraft specifications. The product of the weight of an item multiplied by its arm. (Moment divided by a constant, generally 1000, is used to simplify balance calculations by reducing the number of digits.) Weight of occupants, cargo and baggage. An imaginary vertical plane from which all horizontal distances are measured for balance purposes. (See discussion on next page) Weight of a standard airplane including unusable fuel, full operating fluids (hydraulic oil, battery acid, deicer fluid, etc) and full oil. A location along the airplane fuselage usually given in terms of distance (usually inches) from the reference datum. The weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. Fuel remaining after a run out test has been completed in accordance with government regulations. Usable Fuel Fuel available for aircraft engine combustion or flight planning. Useful Load NOTE: 100LL weighs 5.82 lb/gal The basic empty weight subtracted from the maximum weight of the aircraft. This load consists of the pilot, crew if applicable, fuel, passengers, and baggage. Page 1-2 MAPA Safety Foundation 1 ( Weight and Balance M20 Series Reference Datum For all Mooneys, the reference datum plane is at fuselage station 0.00. On "short fuselage" M20, M20A, M20B, M20C, M20D and M20E models, fuselage station 0.00 is at the nose gear support bolt centerline. On "long fuselage" models M20F, M20G, M20J, and M20K, fuselage station 0.00 is 5.00 in. aft of the centerline of the nose gear support bolts. With the new "longer fuselage" models M20L and M20M, fuselage station 0.00 is 13 in. aft of the centerline of the nose gear support bolts. The leading edge of every Mooney wing is 33.00 in. aft of fuselage station 0.00. This explains why short, long, and longer fuselage Mooneys all have similar CG ranges when expressed as "inches aft of datum." See page 1-4, "CG ENVELOPES, M20 SERIES", which compares the center of gravity envelope limits for all M20 models. (The M20J envelope will be examined in detail later in this chapter.) With its 10 in. longer fuselage, the M20F wheelbase also increased 5 in. Fuselage length grew 8 in. more with the M20J, and an additional 9 in. with the M20K, although the wheelbase remained unchanged. Mounting the M20L and M20M engines required lengthening the fuselage structure forward of station 0.00. On these models the nose wheel was moved 8 in. forward for better propeller clearance, 12 in. was added at the baggage compartment, and remotely mounted avionics and batteries were moved farther aft in the tail cone to help offset the moment of the longer nose. Wing Loading Wing loading, in pounds per square foot (lb/sq ft), is determined by dividing wing area by max gross weight. As Mooneys have gotten heavier in recent years, wing areas have also increased slightly. The M20K was introduced in 1979 with increases in wing span and mean aerodynamic chord (mac). The addition of sculptured M20J wing tips in 1981 increased its wingspan to that of the M20K. In 1991, maximum gross weight for new M20J's was increased from 2740 to 2900. A summary of wing areas, wing loading, and CG limits is shown in the table on page 1-5. Pilot Proficiency Program When down- weighing a/c it is Gear Page -When gear swings up - CG mours aft. Weight and Balance Page 1-4 AIRCRAFT WEIGHT - POUNDS Weight and Balance 3400 3200 3000 2800 1 2900-K,L 2740-F,J 3368-M i 2575-C,E 2600 2525-6 6 2450 M20,A,B 2400 2200 2000 1800 40 42 44 CG ENVELOPES M20 SERIES 46 48 50 52 CG LOCATION - INCHES AFT OF DATUM i .{ MAPA Safety Foundation wing spar x mac & wing are Weight and Balance ble the bottom side of fusiolage also provides lift. M20 SERIES - WING LOADING DATA bottom side & left due to Bottom (prop blast. CG Wing MAC Wing Max Wing Span Area Gross Loading Limits (ft-in) (in) (sq ft) (lb) (lb/sq ft) (% MAC) MODEL M20A,B 35-0 59.18 166.93 2450 14.7 15.0-8.72 M20C,E 35-0 59.18 166.93 2575 15.4 15.0-26.8 M20F 35-0 59.18 166.93 2740 16.4 13.4-28.7 M20G 35-0 59.18 166.93 •2525 15.1 12.4-28.7 M20J,77-80 35-0 59.18 166.93 2740 16.4 13.4-28.7 M20J,81-90 36-1 59.18 168.42 2740 16.3 13.4-28.7 M20J,91-on 36-1 59.18 168.42 2900 17.2 13.4-28.7 M20K 36-1 61.00 174.80 2900 16.6 16.1-30.4 M20L 36-1 61.00 174.80 2900 16.6 16.8-30.4 M20M&R 36-1 61.00 174.80 3368 19.3 16.8-33.2 Weight and Balance Records Procedures for determining loaded aircraft weight and moment for flight operations are documented in Section VI of current M20 series POHS. The POH also contains worksheets and procedures for an FAA licensed mechanic to calculate a new empty weight and moment for the aircraft when the removal or addition of equipment causes the empty weight or center of gravity to change. A comprehensive list of all Mooney equipment available at the time of original delivery is in the POH, with checks indicating those factory items installed and included in the Mooney calculation of empty weight and balance data. The FAA charges the aircraft owner and pilot with the responsibility of properly loading the aircraft for safe flight. Information presented in this section will enable you to carry out this responsibility and insure that your Mooney is loaded to operate within its prescribed weight and center of gravity (CG) limitations. At the time of delivery, Mooney Aircraft Corporation provides the actual empty weight and center of gravity data, which is to be used for the computation of loadings for each individual aircraft. This as-delivered empty weight and CG (with gear extended) is tabulated in the Owners Weight and Balance Record, contained in the POH supplied with the aircraft. FAA regulations also require that any change in the original equipment affecting the empty weight and center of gravity be recorded in the Aircraft Log Book. Pilot Proficiency Program Page 1-5