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Rev. 66 Page 11 of 37 3A13 VIII - Model 182N, Skylane, 4 PCLM (Normal Category), Approved September 17, 1969 Engine Continental O-470-R Continental O-470-S (See NOTE 4) *Fuel 80/87 minimum grade aviation gasoline *Engine Limits For all operations, 2600 r.p.m. (230 hp.) Propeller and 1. McCauley constant speed Propeller Limits (a) Hub 2A34C201/90DA-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: low 13°, high 24.5° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or A210452, or Garwin 34-828-01-2A, or McCauley C290D2/T1 or C290D3/T1 2. McCauley constant speed (a) Hub 2A34C66/90AT-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.5°, high 22° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or 210452, or Garwin 34-828-01, or McCauley C290D2/T1 or C290D3/T1 3. McCauley constant speed (a) Hub 2A34C203/90DCA-8 blades Diameter: not over 82 in., not under 80.5 in. Pitch settings at 30 in. sta.: low 12.5°, high 25° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or 210452, or Garwin 34-828-01, or McCauley C290D2/T1 or C290D3/T1 *Airspeed Limits Maneuvering 131 m.p.h. (114 knots) (CAS) Maximum structural cruising 160 m.p.h. (139 knots) Never exceed 198 m.p.h. (172 knots) Flaps extended 110 m.p.h. ( 96 knots) C.G. Range (+39.9) to (+47.4) at 2950 lb. (+38.4) to (+47.4) at 2800 lb. (+33.0) to (+47.4) at 2250 lb. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight 2950 lb. takeoff only, 2800 lb. landing No. of Seats 4 Front standard (2 at +36 to +49) Optional (2 at +32 to +44) Rear (2 at +74) Maximum Baggage 120 lb. (+97) (S/N 18260056 through 18260445) 120 lb. (+97) and 80 lb. (+117) (S/N 18260446 and up) Fuel Capacity 65 gal. (60 gal. usable); two 32.5 gal. tanks in wings at +48 See NOTE 1 for data on unusable fuel Oil Capacity 12 qt. (-15) (6 qt. usable) See NOTE 1 for data on undrainable oil
3A13 Page 12 of 37 Rev. 66 VIII - Model 182N (cont’d) Control Surface Wing flaps Down 40° +1°, -2° Movements Elevator tab Up 25° +2° Down 15° +1° Ailerons Up 20° +2° Down 15° +2° Elevator(rel. to stabilizer) Up 26° +1° Down 17° +1° Rudder (parallel to 0.00 W.L.) Right 24° +1° Left 24° +1° (Perpendicular to hinge line) Right 27° 13' +1° Left 27° 13' +1° Serial Nos. Eligible Model 182N: 18260056 through 18260445 (1970 Model) 18260446 through 18260825 (1971 Model) IX - Model 182P, Skylane, 4 PCLM (Normal Category), Approved October 8, 1971 Engine Continental O-470-R, Aircraft S/N 18260826 through 18263475 Continental O-470-S, Aircraft S/N 18260826 and up (See NOTE 4) *Fuel 80/87 minimum grade aviation gasoline *Engine Limits For all operations, 2600 r.p.m. (230 hp.) Propeller and 1. McCauley constant speed Propeller Limits (a) Hub 2A34C201/90DA-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 30 in. sta.: low 13°, high 24.5° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or A210452, or Garwin 34-828-01-2A, or McCauley C290D2/T1 or C290D3/T1 2. McCauley constant speed (a) Hub 2A34C66/90AT-8 blades Diameter: not over 82 in., not under 80 in. Pitch settings at 36 in. sta.: low 10.5°, high 22° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or 210452, or Garwin 34-828-01, or McCauley C290D2/T1 or C290D3/T1 3. McCauley constant speed (a) Hub 2A34C203/90DCA-8 blades Diameter: not over 82 in., not under 80.5 in. Pitch settings at 30 in. sta.: low 12.5°, high 25° (b) Cessna spinner 0752637 (c) Woodward governor 210065, 210105, 210155, 210345, or 210452, or Garwin 34-828-01, or McCauley C290D2/T1 or C290D3/T1 *Airspeed Limits (S/N 675, 18260826 through 18264295) (CAS) Maneuvering 126 m.p.h. (109 knots) Maximum structural cruising 160 m.p.h. (139 knots) Never exceed 198 m.p.h. (172 knots) Flaps extended 110 m.p.h. ( 96 knots) *Airspeed Limits (S/N 18264296 through 18265175) (IAS) Maneuvering 110 knots (See NOTE 5 on use of IAS) Maximum structural cruising 141 knots Never exceed 176 knots Flaps extended 95 knots C.G. Range (+39.5) to (+48.5) at 2950 lb. (+33.0) to (+48.5) at 2250 lb. or less Straight line variation between points given
Page 2:
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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Page 188 and 189:
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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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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
Page 350 and 351: X - Model A152 (cont’d) Page 13 o
Page 352 and 353: Data Pertinent to All Models (cont
Page 354 and 355: Page 17 of 19 3A19 Data Pertinent t
Page 356: Data Pertinent to All Models (cont
Page 359 and 360: E-295 Page 2 of 8 Model Lycoming O-
Page 361 and 362: E-295 Page 4 of 8 Certification bas
Page 363 and 364: E-295 Page 6 of 8 NOTE 5. These mod
Page 365 and 366: E-295 Page 8 of 8 NOTE 12. When equ
Page 367 and 368: A7CE Page 2 of 24 Propeller and or
Page 369 and 370: A7CE Page 4 of 24 II - Model 401, M
Page 371 and 372: A7CE Page 6 of 24 III - Model 402,
Page 373 and 374: A7CE Page 8 of 24 IV - Model 421, M
Page 375 and 376: A7CE Page 10 of 24 V - Model 414 (N
Page 377 and 378: A7CE Page 12 of 24 VI - Model 421B
Page 379 and 380: A7CE Page 14 of 24 VII - Model 421C
Page 381 and 382: A7CE Page 16 of 24 VIII - Model 414
Page 383 and 384: A7CE Page 18 of 24 IX - Model 402C
Page 385 and 386: A7CE Page 20 of 24 X - Model 425 (c
Page 387 and 388: A7CE Page 22 of 24 X - Model 425 (c
Page 389 and 390: A7CE Page 24 of 24 NOTE 3. (cont'd.
Page 391 and 392: 3A13 Page 2 of 37 Rev. 66 I - Model
Page 393 and 394: 3A13 Page 4 of 37 Rev. 66 II - Mode
Page 395 and 396: 3A13 Page 6 of 37 Rev. 66 IV - Mode
Page 397 and 398: 3A13 Page 8 of 37 Rev. 66 V - Model
Page 399: 3A13 Page 10 of 37 Rev. 66 VII - Mo
Page 403 and 404: 3A13 Page 14 of 37 Rev. 66 X - Mode
Page 405 and 406: 3A13 Page 16 of 37 Rev. 66 Model TR
Page 407 and 408: 3A13 Page 18 of 37 Rev. 66 Model 18
Page 409 and 410: 3A13 Page 20 of 37 Rev. 66 Data Per
Page 415 and 416: 3A13 Page 26 of 37 Rev. 66 Long ran
Page 417 and 418: 3A13 Page 28 of 37 Rev. 66 (3) On t
Page 421 and 422: 3A13 Page 32 of 37 Rev. 66 XIII - M
Page 423 and 424: 3A13 Page 34 of 37 Rev. 66 Special
Page 425 and 426: 3A13 Page 36 of 37 Rev. 66 Oil Capa
Page 428 and 429: DEPARTMENT OF TRANSPORTATION FEDERA
Page 430 and 431: Maximum Weight S/N 34-7250215 throu
Page 432 and 433: 5 of 16 A7SO Maximum Weight 4570 lb
Page 434 and 435: Maximum Weight 4773 lb. - Ramp 4750
Page 436 and 437: Oil Capacity 8 qts. per engine (5 q
Page 438 and 439: 11 of 16 A7SO Control Surface Movem
Page 440 and 441: 13 of 16 A7SO Equipment The basic r
Page 442 and 443: 15 of 16 A7SO The Model PA-34-200T;
Page 444 and 445: Page No. 1 2 3 4 5 6 7 8 Rev. No. 1
Page 446 and 447: Page 3 A11EA 3. McCauley Model 1A10
Page 448 and 449: 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
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19 2A4 XIII - MODEL 685 (cont’d)
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XIV - MODEL 690A (cont’d) Maximum
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23 2A4 XVI - MODEL 690C, 11 PCLM (N
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25 2A4 XVII - MODEL 695 (cont’d)
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27 2A4 XVIII - MODEL 695A (cont’d
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29 2A4 XIX - MODEL 690D (cont’d)
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31 2A4 Specifications Pertinent to
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33 2A4 NOTE 6: Model 680FL S/N 1471
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Page No. 1 2 3 4 Rev. No. 9 9 9 9 R
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3 E-284 NOTE 4. The "6" in the engi
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Page 3 of 17 A9CE II. Model A188, A
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III. Model 188A, AGwagon "A" & "B"
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V. Model 188B, AGpickup (cont'd) *E
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Page 9 of 17 A9CE VI. Model A188B (
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VII. Model T188C (cont'd) Number of
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Page 13 of 17 A9CE Reference weight
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Page 15 of 17 A9CE Fuel Flows at Fu
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NOTE 8. 14 volt electrical system 1
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3A12 2 Rev. 77 I. Model 172 (cont'd
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3A12 4 Rev. 77 II. Model 172A, Mode
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3A12 6 Rev. 77 IV. Model 172D, Mode
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3A12 8 Rev. 77 V. Model 172I, Model
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3A12 10 Rev. 77 VI. Model 172L (con
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3A12 12 Rev. 77 VIII. Model 172N (c
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3A12 14 Rev. 77 IX. Model 172P (con
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3A12 16 Rev. 77 DATA PERTINENT TO A
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Page 567 and 568:
Page 569 and 570:
Page 571 and 572:
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3A12 26 Rev. 77 XI - Model 172R (co
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3A12 28 Rev. 77 Data Pertinent to M
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3A12 30 Rev. 77 XII - Model 172S (c
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Page 582 and 583:
3 A16CE Control Surface Movements W
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5 A16CE Data Pertinent to All Model
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7 A16CE (6) On cargo door: "Baggage
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9 A16CE (7) Near the manifold press
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11 A16CE NOTE 5. The marking of the
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Page 2 of 43 3A21 I - Model 210 (co
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Page 4 of 43 3A21 III - Model 210B,
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V - Model 210D (cont’d) Empty wt.
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Page 8 of 43 3A21 VII - Model T210F
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Page 10 of 43 3A21 IX - Model T210G
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XI - Model T210J (cont’d) Page 12
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Page 14 of 43 3A21 XIII Model 210K/
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Page 16 of 43 3A21 XIV - Model 210M
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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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Page 627 and 628:
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 633 and 634:
Page 42 of 43 3A21 NOTE 2. K. (26)
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Page 638 and 639:
A3SO Page 3 of 31 I. - Model PA-32-
Page 640 and 641:
A3SO Page 5 of 31 II. - Model PA-32
Page 642 and 643:
A3SO Page 7 of 31 III. - Model PA-3
Page 644 and 645:
A3SO Page 9 of 31 V. - Model PA-32R
Page 646 and 647:
A3SO Page 11 of 31 VI. - Model PA-3
Page 648 and 649:
A3SO Page 13 of 31 VII. - Model PA-
Page 650 and 651:
A3SO Page 15 of 31 IX. - Model PA-3
Page 652 and 653:
A3SO Page 17 of 31 X. - Model PA-32
Page 654 and 655:
A3SO Page 19 of 31 XI. - Model PA-3
Page 656 and 657:
A3SO Page 21 of 31 XII. - Model PA-
Page 658 and 659:
A3SO Page 23 of 31 XIV. - Model PA-
Page 660 and 661:
A3SO Page 25 of 31 PA-32R-301, S/N
Page 662 and 663:
A3SO Page 27 of 31 23.1329, 23.1351
Page 664 and 665:
A3SO Page 29 of 31 AFM Supp. VB-357
Page 666 and 667:
A3SO Page 31 of 31 32R-8029121, 32R
Page 668 and 669:
Section V FAA FORMS • FAA Form 33
Page 670 and 671:
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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