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Rev. 77 13 3A12 VIII. Model 172N (cont'd) Control Surface Movements Wing flaps Takeoff 0� - 10� (landplane) (seaplane) Landing 0� - 40� +0�, -2� (landplane) 0� - 30� �2� (seaplane) Ailerons Up 20� �1� Down 15� �1� Elevator tab Up 28� +1�, -0� Down 13� +1�, -0� Elevator Up 28� +1�, -0� Down 23� +1�, -0� (Neutral position is with bottom of balance area flush with bottom of stabilizer.) Rudder (landplane) Right 16� �1� Left 16� �1� (landplane) (seaplane) Right 19� �1� Left 15� �1� (seaplane) (Measured parallel to W.L.) Serial Numbers Eligible 17261445, 17267585 through 17269309 (1977 model) 17261578, 17269310 through 17271034 (1978 model) (except 17270050) 17271035 through 17272884 (1979 model) 17270050, 17272885 through 17274009 (1980 model) IX. Model 172P, Skyhawk, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved May 13, 1980 Engine Lycoming O-320-D2J *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm (160 hp) Propeller and 1. Propeller Propeller Limits (a) McCauley 1C160/DTM 7557 Static rpm at maximum permissible throttle setting: Not over 2420, not under 2300 No additional tolerance permitted Diameter: not over 75 in., not under 74 in. (b) Spinner: Dwg. 0550320 2. Propeller (floatplane only) (a) McCauley 1A175/ETM 8043 Static rpm at maximum permissible throttle setting: Not over 2570, not under 2470 No additional tolerance permitted Diameter: not over 80 in., not under 78.5 in. (b) Spinner: Dwg. 0550320 *Airspeed Limits Maneuvering 99 knots (landplane) (CAS) 96 knots (floatplane) (See Note 4 on use of CAS) Maximum structural cruising 127 knots Never exceed 158 knots Flaps extended 85 knots C.G. Range Landplane: Normal category (+39.5) to (+47.3) at 2400 lbs. (+35.0) to (+47.3) at 1950 lbs. or less Utility category (+36.5) to (+40.5) at 2100 lbs. (+35.0) to (+40.5) at 1950 lbs. or less Empty Weight C.G. Range None Seaplane: (Edo 89-2000 or 89A2000 floats) Normal category (+39.8) to (+45.5) at 2220 lbs. (+36.4) to (+45.5) at 1825 lbs. or less Straight line variation between points given.
3A12 14 Rev. 77 IX. Model 172P (cont'd) *Maximum Weight Normal category: 2400 lb. (landplane); 2220 lb. (seaplane) Utility category: 2100 lb. (landplane) Number of Seats 4 (2 at +34 to +46, 2 at +73) (Occupant on child's optional jump seat at +96) Maximum Baggage 120 lb. at +95 Fuel Capacity 42 gal. total, 40 gal. usable (two 21.5 gal. tanks in wings at +48) See Note 1 <strong>for</strong> data on unusable fuel. Oil Capacity 2 gal. (-13.1), 3.5 gal. usable Control Surface Movements Wing flaps Takeoff 0� - 10� Landing 0� - 30� +0�, -2� Ailerons Up 20� �1� Down 15� �1� Elevator tab Up 28� +1�, -0� Down 13� +1�, -0� (floatplane) Up 22� +1�, -0� Down 19� +1�, -0� (landplane) Elevator Up 28� +1�, -0� Down 23� +1�, -0� (Neutral position is with bottom of balance area flush with bottom of stabilizer.) Rudder (landplane) Right 16� �1� Left 16� �1� (landplane) (seaplane) Right 19� �1� Left 15� �1� (seaplane) (Measured parallel to W.L.) Serial Numbers Eligible 17274010 through 17275034 (1981 model) 17275035 through 17275759 (1982 model) 17275760 through 17276079 (1983 model) 17276080 through 17276259 (1984 model) 17276260 through 17276516 (1985 model) 17276517 through 17276654 (1986 model) X. Model 172Q, Cutlass, 4 PCLM (Normal Category), approved October 15, 1982 Engine Lycoming O-360-A4N *Fuel 100LL/100 minimum grade aviation gasoline *Engine Limits For all operations, 2700 rpm (180 hp) Propeller and 1. Propeller Propeller Limits (a) McCauley 1A170E/JFA 7658 Static rpm at maximum permissible throttle setting: Not over 2450, not under 2350 No additional tolerance permitted Diameter: not over 76 in., not under 74.5 in. (b) Spinner: Dwg. 0509077 *Airspeed Limits Maneuvering 105 knots Maximum structural cruising 127 knots Never exceed 158 knots Flaps extended 85 knots C.G. Range Normal category (+41.0) to (+47.3) at 2550 lbs. (+35.0) to (+47.3) at 1950 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None *Maximum Weight Normal category: 2550 lb.
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Computer Testing Supplement for Ins
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Table of Contents Preface .........
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• A7S0, Piper PA-34-200 • A11EA
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Section I: Title 14 of the Code of
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§ 1.1 General definitions. PART 1
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Category B, with respect to transpo
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(1) An ETOPS group 1 Significant Sy
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Glider means a heavier-than-air air
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Long-range communication system (LR
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Overseas air transportation means t
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Rated maximum continuous augmented
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(2) With respect to turbine engines
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ETOPS means extended operations. EW
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SSALS means simplified short approa
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(2) May is used in a permissive sen
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§ 23.1 Applicability. PART 23—AI
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(i) The highest weight selected by
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[Doc. No. 4080, 29 FR 17955, Dec. 1
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significantly reduce the capability
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(1) The instrument that most effect
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[Amdt. 23-1, 30 FR 8261, June 29, 1
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(2) Each exposed sight gauge used a
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[Doc. No. 4080, 29 FR 17955, Dec. 1
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(c) Main power cables (including ge
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(c) Rear position light installatio
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system is observed from a distance,
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(c) For those airplanes required to
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(d) As used in this section: (1) BT
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§23.1457 Cockpit voice recorders.
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23.1511 Flap extended speed. (a) Th
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23.1541 General. (a) The airplane m
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(1) Each fuel tank selector control
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(2) Stating that recovery must be i
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(3) Acrobatic category airplanes. A
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(4) The effect on landing distances
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ecommended at these periods. Howeve
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Subpart A—General §27.1 Applicab
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(3) The portion of the total weight
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warn the pilot of the occurrence of
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(c) Except as provided in paragraph
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(2) Compliance with paragraph (a)(1
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§27.1365 Electric cables. (a) Each
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§27.1391 Minimum intensities in th
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where: Ie=effective intensity (cand
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(2) By installing a continually ene
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§27.1505 Never-exceed speed. (a) T
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(i) The maximum value determined by
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(b) Each arc and line must be wide
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(2) Oil filler openings must be mar
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(ii) The maximum safe wind for oper
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PART 39—AIRWORTHINESS DIRECTIVES
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PART 43—MAINTENANCE, PREVENTIVE M
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§ 43.5 Approval for return to serv
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is permanently removed from use on
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(b) Rotorcraft. Each person perform
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Appendix A to Part 43—Major Alter
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(2) Powerplant major repairs. Repai
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(31) Removing and replacing self-co
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(3) Internal engine—for cylinder
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(vi) Barometric scale error. At con
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Appendix F to Part 43—ATC Transpo
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§ 45.1 Applicability. This part pr
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§ 45.14 Identification of critical
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§ 45.25 Location of marks on fixed
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§ 91.1 Applicability. PART 91—GE
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hospital, or doctor, or other perso
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§§ 91.27-91.99 [Reserved] § 91.2
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(i) Airplanes with a third attitude
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(11) On and after January 1, 2004,
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(iv) Required to be operational by
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(5) Accept necessary barometric pre
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§ 91.407 Operation after maintenan
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(g) Inspection program approved und
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(iii) The time since last overhaul
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Section II: Airworthiness Directive
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MESSERSCHMITT-BOLKOW-BLOHM-GMBH AND
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AGUSTA, COSTRUZIONI AERONAUTICHE GI
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BEECH =============================
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d. Coat entire portion of bolt that
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AIR TRACTOR, INC. =================
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BENDIX ============================
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ENSTROM ===========================
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BEECH =============================
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BEECH AIRCRAFT CORPORATION ========
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PRATT & WITHEY AIRCRAFT OF CANADA,
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(j) Install a CT stator assembly, a
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Section III: Exhibits • Exhibit 1
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Rivet identifi cation and part numb
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Aircraft rivet identification. EXHI
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Aircraft rivet identification. (con
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Thickness “t” in inches No. of
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Recommended radii for 90° bends in
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Minimum Bend Radius for Aluminum Al
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3-19 RADIUS THICKNESS 1/32 .031 1/1
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EXHIBIT 10 K-chart for determining
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. . DATUM D C.G. L . . NOSE WHEEL T
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COMPUTED WEIGHING POINT (C MAIN WHE
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NOSE SCALE 464 LBS. TARE 10 LBS. We
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FULL OIL EXHIBIT 14 Example of chec
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FULL OIL EXHIBIT 15 Example of chec
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1. GENERAL. The minimum airworthine
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Utility Category Aircraft (FAR 23)
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EXHIBIT 17 Turnbuckle safetying gui
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Straight-shank terminal dimensions
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BEND RADIUS INCHES 3 — 2 — 1
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MINIMUM BEND RADIUS (INCHES) 16 15
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211. GENERAL. This chapter contains
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differential of 5.53 in. Hg, i.e.,
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DC wire and circuit protector chart
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Where: T1 T2 TR I2 Imax TABLE 11-9.
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11-67. METHODS FOR DETERMINING CURR
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(1) The wire run is 15.5 feet long,
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STEP 1: Refer to the “single wire
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FIGURE 11-3. Conductor chart, inter
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FIGURE 11-4b. Single copper wire in
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FIGURE 11-6. Altitude derating curv
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Minimum Equipment List Page MINIMUM
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EXHIBIT 24 Bend Allowance = 2π (R
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EXHIBIT 25 c = 2π a 2 + b 2 2 Circ
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Section IV: Type Certificate Data S
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TCDS BACKGROUND INFORMATION Type Ce
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Coded Entries Many aircraft and eng
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DEPARTMENT OF TRANSPORTATION FEDERA
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I. Model 208, Caravan (cont’d) 3
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II. - Model 208B, Caravan (cont’d
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Data Pertinent to All Models (cont
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TCDS E4EA PAGE 2 IV. MODEL TYPE (se
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TCDS E4EA PAGE 4 I. MODELS (Cont.))
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TCDS E4EA PAGE 6 I. MODELS (cont.)
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TCDS E4EA PAGE 8 II. MODELS PT6A-45
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TCDS E4EA PAGE 10 III. MODELS (cont
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TCDS E4EA PAGE 12 PT6A-28 PT6A-29 P
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TCDS E4EA PAGE 14 NOTE 1.(continued
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TCDS E4EA PAGE 16 Maximum Continuou
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TCDS E4EA PAGE 18 Accessory Drive P
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TCDS E4EA PAGE 20 NOTE 7. The maxim
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TCDS E4EA PAGE 22 NOTE 13. (Cont'd)
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P9NE 2 NOTE 2. Blade Model Designat
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P60GL Page 2 of 3 Certification Bas
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Page No. 1 2 3 Rev. No. 29 29 29 Re
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E-252 Page 3 The Model 0-200-C is s
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2A13 Page 2 of 43 Center of Gravity
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2A13 Page 4 of 43 Propeller Spinner
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2A13 Page 6 of 43 Propeller Spinner
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2A13 Page 8 of 43 VI - Model PA-28-
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2A13 Page 10 of 43 Center of Gravit
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2A13 Page 12 of 43 Empty Weight C.
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2A13 Page 14 of 43 X - Model PA-28R
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2A13 Page 16 of 43 Control Surface
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2A13 Page 18 of 43 Engine Limits Fo
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2A13 Page 20 of 43 Manufacturer's S
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2A13 Page 22 of 43 Center of Gravit
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2A13 Page 24 of 43 XVI - B. Model P
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2A13 Page 26 of 43 No. of Seats Nor
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2A13 Page 28 of 43 Airspeed Limits
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2A13 Page 30 of 43 Propeller and Pr
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2A13 Page 32 of 43 Engine Limits Fo
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2A13 Page 34 of 43 Manufacturer's S
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2A13 Page 36 of 43 PA-28-236: CAR 3
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2A13 Page 38 of 43 (Continued) MODE
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2A13 Page 40 of 43 NOTE 3 The Model
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2A13 Page 42 of 43 NOTE 20 PA-28-18
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II - Model 150D, Model 150E, Model
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IV - Model A150K, Aerobat, 2 PCLM (
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V - Model 150L (cont’d) Page 7 of
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VII - Model 150M (cont’d) Page 9
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IX - Model 152 (cont'd) Page 11 of
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X - Model A152 (cont’d) Page 13 o
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Page 17 of 19 3A19 Data Pertinent t
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E-295 Page 2 of 8 Model Lycoming O-
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E-295 Page 4 of 8 Certification bas
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E-295 Page 6 of 8 NOTE 5. These mod
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E-295 Page 8 of 8 NOTE 12. When equ
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A7CE Page 2 of 24 Propeller and or
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A7CE Page 4 of 24 II - Model 401, M
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A7CE Page 6 of 24 III - Model 402,
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A7CE Page 8 of 24 IV - Model 421, M
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A7CE Page 10 of 24 V - Model 414 (N
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A7CE Page 12 of 24 VI - Model 421B
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A7CE Page 14 of 24 VII - Model 421C
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A7CE Page 16 of 24 VIII - Model 414
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A7CE Page 18 of 24 IX - Model 402C
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A7CE Page 20 of 24 X - Model 425 (c
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A7CE Page 22 of 24 X - Model 425 (c
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A7CE Page 24 of 24 NOTE 3. (cont'd.
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3A13 Page 2 of 37 Rev. 66 I - Model
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3A13 Page 4 of 37 Rev. 66 II - Mode
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3A13 Page 6 of 37 Rev. 66 IV - Mode
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3A13 Page 8 of 37 Rev. 66 V - Model
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3A13 Page 10 of 37 Rev. 66 VII - Mo
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3A13 Page 12 of 37 Rev. 66 VIII - M
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3A13 Page 14 of 37 Rev. 66 X - Mode
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3A13 Page 16 of 37 Rev. 66 Model TR
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3A13 Page 18 of 37 Rev. 66 Model 18
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3A13 Page 20 of 37 Rev. 66 Data Per
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3A13 Page 26 of 37 Rev. 66 Long ran
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3A13 Page 28 of 37 Rev. 66 (3) On t
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3A13 Page 32 of 37 Rev. 66 XIII - M
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3A13 Page 34 of 37 Rev. 66 Special
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3A13 Page 36 of 37 Rev. 66 Oil Capa
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Maximum Weight S/N 34-7250215 throu
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5 of 16 A7SO Maximum Weight 4570 lb
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Maximum Weight 4773 lb. - Ramp 4750
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Oil Capacity 8 qts. per engine (5 q
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11 of 16 A7SO Control Surface Movem
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13 of 16 A7SO Equipment The basic r
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15 of 16 A7SO The Model PA-34-200T;
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Page No. 1 2 3 4 5 6 7 8 Rev. No. 1
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Page 3 A11EA 3. McCauley Model 1A10
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Oil capacity 6 qt. at (+39) (2 qt.
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UTILITY CATEGORY AA-1 AA-1A Maximum
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Page 3 of 15 1A6 Maximum Baggage50
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Page 5 of 15 1A6 Fuel Capacity 36 g
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Page 7 of 15 1A6 Fuel Capacity 36 g
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Page 9 of 15 1A6 Required Equipment
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Page 11 of 15 1A6 105. Vacuum pump
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Page 13 of 15 1A6 (w) FAA-DOA appro
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Page 15 of 15 1A6 (3) On left side
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E-273 Page 2 Model O-470-A O-470-E
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E-273 Page 4 NOTE 3. The following
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E-273 Page 6 NOTE 13. The following
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P57GL Page 2 of 5 Maximum Diameter
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P57GL Page 4 of 5 NOTE 3. Pitch Con
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DEPARTMENT OF TRANSPORTATION P-920
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Page 3 of 12 P-920, Revision 29 Max
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Note 2: Blade Model Designation (Se
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Note 9: Special Limits Page 7 of 12
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Page 9 of 12 P-920, Revision 29 Hub
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Page 11 of 12 P-920, Revision 29 Hu
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3 2A4 II. - Model 680-E (cont’d)
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5 2A4 III. - Model 720 (cont’d) L
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V - Model 560-F, 7 PCLM (Normal Cat
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9 2A4 VI - Model 680-FL (cont’d)
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11 2A4 VII - MODEL 680-FL(P) (cont
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13 2A4 IX - MODEL 680-V, 11 PCLM (N
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15 2A4 X - MODEL 680-W (cont’d) D
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17 2A4 XI - MODEL 681 (cont’d) Se
Page 510 and 511: 19 2A4 XIII - MODEL 685 (cont’d)
Page 512 and 513: XIV - MODEL 690A (cont’d) Maximum
Page 514 and 515: 23 2A4 XVI - MODEL 690C, 11 PCLM (N
Page 516 and 517: 25 2A4 XVII - MODEL 695 (cont’d)
Page 518 and 519: 27 2A4 XVIII - MODEL 695A (cont’d
Page 520 and 521: 29 2A4 XIX - MODEL 690D (cont’d)
Page 522 and 523: 31 2A4 Specifications Pertinent to
Page 524 and 525: 33 2A4 NOTE 6: Model 680FL S/N 1471
Page 526 and 527: Page No. 1 2 3 4 Rev. No. 9 9 9 9 R
Page 528 and 529: 3 E-284 NOTE 4. The "6" in the engi
Page 530 and 531: DEPARTMENT OF TRANSPORTATION FEDERA
Page 532 and 533: Page 3 of 17 A9CE II. Model A188, A
Page 534 and 535: III. Model 188A, AGwagon "A" & "B"
Page 536 and 537: V. Model 188B, AGpickup (cont'd) *E
Page 538 and 539: Page 9 of 17 A9CE VI. Model A188B (
Page 540 and 541: VII. Model T188C (cont'd) Number of
Page 542 and 543: Page 13 of 17 A9CE Reference weight
Page 544 and 545: Page 15 of 17 A9CE Fuel Flows at Fu
Page 546: NOTE 8. 14 volt electrical system 1
Page 549 and 550: 3A12 2 Rev. 77 I. Model 172 (cont'd
Page 551 and 552: 3A12 4 Rev. 77 II. Model 172A, Mode
Page 553 and 554: 3A12 6 Rev. 77 IV. Model 172D, Mode
Page 555 and 556: 3A12 8 Rev. 77 V. Model 172I, Model
Page 557 and 558: 3A12 10 Rev. 77 VI. Model 172L (con
Page 559: 3A12 12 Rev. 77 VIII. Model 172N (c
Page 563 and 564: 3A12 16 Rev. 77 DATA PERTINENT TO A
Page 573 and 574: 3A12 26 Rev. 77 XI - Model 172R (co
Page 575 and 576: 3A12 28 Rev. 77 Data Pertinent to M
Page 577 and 578: 3A12 30 Rev. 77 XII - Model 172S (c
Page 580 and 581: DEPARTMENT OF TRANSPORTATION FEDERA
Page 582 and 583: 3 A16CE Control Surface Movements W
Page 584 and 585: 5 A16CE Data Pertinent to All Model
Page 586 and 587: 7 A16CE (6) On cargo door: "Baggage
Page 588 and 589: 9 A16CE (7) Near the manifold press
Page 590: 11 A16CE NOTE 5. The marking of the
Page 593 and 594: Page 2 of 43 3A21 I - Model 210 (co
Page 595 and 596: Page 4 of 43 3A21 III - Model 210B,
Page 597 and 598: V - Model 210D (cont’d) Empty wt.
Page 599 and 600: Page 8 of 43 3A21 VII - Model T210F
Page 601 and 602: Page 10 of 43 3A21 IX - Model T210G
Page 603 and 604: XI - Model T210J (cont’d) Page 12
Page 605 and 606: Page 14 of 43 3A21 XIII Model 210K/
Page 607 and 608: Page 16 of 43 3A21 XIV - Model 210M
Page 609 and 610: Page 18 of 43 3A21 XV - Model P210N
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Page 20 of 43 3A21 Model 210N (cont
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XVII - Model P210R (cont’d) Fuel
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Model T210R (cont’d) Fuel Capacit
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Page 26 of 43 3A21 NOTE 2. (cont’
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Page 28 of 43 3A21 NOTE 2. (4) On f
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Page 623 and 624:
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NOTE 2. (cont’d) J. (10) Page 36
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NOTE 2. (cont’d) J. (21) Near the
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Page 42 of 43 3A21 NOTE 2. K. (26)
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A3SO Page 3 of 31 I. - Model PA-32-
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A3SO Page 5 of 31 II. - Model PA-32
Page 642 and 643:
A3SO Page 7 of 31 III. - Model PA-3
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A3SO Page 9 of 31 V. - Model PA-32R
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A3SO Page 11 of 31 VI. - Model PA-3
Page 648 and 649:
A3SO Page 13 of 31 VII. - Model PA-
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A3SO Page 15 of 31 IX. - Model PA-3
Page 652 and 653:
A3SO Page 17 of 31 X. - Model PA-32
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A3SO Page 19 of 31 XI. - Model PA-3
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A3SO Page 21 of 31 XII. - Model PA-
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A3SO Page 23 of 31 XIV. - Model PA-
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A3SO Page 25 of 31 PA-32R-301, S/N
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A3SO Page 27 of 31 23.1329, 23.1351
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A3SO Page 29 of 31 AFM Supp. VB-357
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A3SO Page 31 of 31 32R-8029121, 32R
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Section V FAA FORMS • FAA Form 33
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5-3 Form Approved Electronic Tracki
Page 672 and 673:
Paperwork Reduction Act Statement:
Page 674 and 675:
END OF SECTION 5 5-7
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