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Center of Gravity Range (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+88.4) to (+95.9) at 2150 lb. Straight line variation between points given. Empty Wt. C. G. Range None Maximum Weight 2150 lb. No. of Seats 4 (2 at +85.5, 2 at +118.1) Page 3 of 43 2A13 Maximum Baggage 125 lb. at (+142.8) on S/N 28-1 through 28-1760, and 28-1760A. See NOTE 8. 200 lb. at (+142.8) on S/N 28-1761 through 28-4377. Fuel Capacity 50 gallons at (+95) ( 2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 quarts at (+32.5) (6 quarts usable) See NOTE 1 for data on system oil. Control Surface Movements Wing flaps (± 2°) Up 0° Down 40° Ailerons (± 2°) Up 30° Down 15° Rudder (± 2°) Left 27° Right 27° Stabilator (± 1°) Up 18° Down 2° Stabilator Tab (± 1°) Up 3° Down 12° Nose Wheel Travel (± 2�) Left 30° Right 30° (Effective on S/N 28-03; 28-1 through 28-3377; and 28-1760A) (� 2�) Left 22° Right 22° (Effective on S/N 28-3378 through 28-4377) Manufacturer's Serial Nos. 28-03; 28-1 through 28-4377; and 28-1760A. III - Model PA-28-180 (Cherokee), 4 PCLM (Normal Category), Approved August 3, 1962; 2 PCLM (Utility Category), Approved December 6, 1966, for S/N 28-03; 28-671 through 28-5859; and 28-7105001 through 28-7205318. Engine Lycoming O-360-A3A or 0-360-A4A with carburetor setting 10-3878 or 10-4164-1 Fuel 91/96 minimum grade aviation gasoline Engine Limits S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573) (See NOTE 4): Maximum permissible takeoff, 2475 r.p.m. For all other operations, 2700 r.p.m. (180 hp) S/N 28-1571; 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318: For all operations, 2700 r.p.m. (180 hp) Propeller and Propeller Limits Sensenich M76EMM or 76EM8 on S/N 28-671 through 28-1760, and 28-1760A (except S/N 28-1571 and S/N 28-1573). Sensenich M76EMMS or 76EM8S5 on S/N 28-1571, 28-1573; 28-1761 through 28-5859; and 28-7105001 through 28-7205318. Static r.p.m. at maximum permissible throttle setting not over 2450 r.p.m., not under 2275 r.p.m. No additional tolerance permitted. Diameter: Not over or under 76". See NOTE 10.
2A13 Page 4 of 43 Propeller Spinner Piper P/N 14422-00 on S/N 28-671 through 28-1760, and 28-1760A. Piper P/N 63760-04 or 65805-00 on S/N 28-1761 through 28-5859; and 28-7105001 through 28-7205318. See NOTE 11. Airspeed Limits Never exceed 171 mph (148 knots) CAS Maximum structural cruising 140 mph (121 knots) CAS Maneuvering 129 mph (112 knots) CAS Flaps Extended 115 mph (100 knots) CAS Center of Gravity Range Utility Category (See NOTE 9) (+84.0) to (+86.5) at 1650 lb. or less (+85.8) to (+86.5) at 1950 lb. Normal Category (See NOTE 15) (S/N 28-671 through 28-5859) (+84.0) to (+95.9) at 1650 lb. or less (+85.9) to (+95.9) at 1975 lb. (+89.2) to (+95 9) at 2200 lb. (+92.1) to (+94.5) at 2400 lb. Normal Category (S/N 28-7105001 through 28-7205318) (+84.0) to (+95.9) at 1650 lb. or less (+87.0) to (+95.9) at 2150 lb. (+87.8) to (+95.9) at 2200 lb. (+91.0) to (+94.5) at 2400 lb. Straight Line Variation Between Points Given Lbs. Lbs. Empty Weight C. G. Range None 2400 2200 2000 1800 1600 2400 2200 2000 1800 1600 Normal & Utility Aft Limit Utility Aft Limit Normal Normal Only 84 86 88 90 92 94 96 Fuselage Station - Inches (S/N 28-671 thru 28-5859) Aft Limit Utility Normal & Utility Aft Limit Normal Normal Only 84 86 88 90 92 94 96 Fuselage Station - Inches (S/N 28-7105001 thru 28-7205318)
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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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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
Page 246 and 247: Section IV: Type Certificate Data S
Page 248 and 249: TCDS BACKGROUND INFORMATION Type Ce
Page 250 and 251: Coded Entries Many aircraft and eng
Page 252 and 253: DEPARTMENT OF TRANSPORTATION FEDERA
Page 254 and 255: I. Model 208, Caravan (cont’d) 3
Page 256 and 257: II. - Model 208B, Caravan (cont’d
Page 258 and 259: Data Pertinent to All Models (cont
Page 260: Data Pertinent to All Models (cont
Page 263 and 264: TCDS E4EA PAGE 2 IV. MODEL TYPE (se
Page 265 and 266: TCDS E4EA PAGE 4 I. MODELS (Cont.))
Page 267 and 268: TCDS E4EA PAGE 6 I. MODELS (cont.)
Page 269 and 270: TCDS E4EA PAGE 8 II. MODELS PT6A-45
Page 271 and 272: TCDS E4EA PAGE 10 III. MODELS (cont
Page 273 and 274: TCDS E4EA PAGE 12 PT6A-28 PT6A-29 P
Page 275 and 276: TCDS E4EA PAGE 14 NOTE 1.(continued
Page 277 and 278: TCDS E4EA PAGE 16 Maximum Continuou
Page 279 and 280: TCDS E4EA PAGE 18 Accessory Drive P
Page 281 and 282: TCDS E4EA PAGE 20 NOTE 7. The maxim
Page 283 and 284: TCDS E4EA PAGE 22 NOTE 13. (Cont'd)
Page 285 and 286: P9NE 2 NOTE 2. Blade Model Designat
Page 287 and 288: P60GL Page 2 of 3 Certification Bas
Page 290 and 291: Page No. 1 2 3 Rev. No. 29 29 29 Re
Page 292: E-252 Page 3 The Model 0-200-C is s
Page 295: 2A13 Page 2 of 43 Center of Gravity
Page 299 and 300: 2A13 Page 6 of 43 Propeller Spinner
Page 301 and 302: 2A13 Page 8 of 43 VI - Model PA-28-
Page 303 and 304: 2A13 Page 10 of 43 Center of Gravit
Page 305 and 306: 2A13 Page 12 of 43 Empty Weight C.
Page 307 and 308: 2A13 Page 14 of 43 X - Model PA-28R
Page 309 and 310: 2A13 Page 16 of 43 Control Surface
Page 311 and 312: 2A13 Page 18 of 43 Engine Limits Fo
Page 313 and 314: 2A13 Page 20 of 43 Manufacturer's S
Page 315 and 316: 2A13 Page 22 of 43 Center of Gravit
Page 317 and 318: 2A13 Page 24 of 43 XVI - B. Model P
Page 319 and 320: 2A13 Page 26 of 43 No. of Seats Nor
Page 321 and 322: 2A13 Page 28 of 43 Airspeed Limits
Page 323 and 324: 2A13 Page 30 of 43 Propeller and Pr
Page 325 and 326: 2A13 Page 32 of 43 Engine Limits Fo
Page 327 and 328: 2A13 Page 34 of 43 Manufacturer's S
Page 329 and 330: 2A13 Page 36 of 43 PA-28-236: CAR 3
Page 331 and 332: 2A13 Page 38 of 43 (Continued) MODE
Page 333 and 334: 2A13 Page 40 of 43 NOTE 3 The Model
Page 335 and 336: 2A13 Page 42 of 43 NOTE 20 PA-28-18
Page 338 and 339: DEPARTMENT OF TRANSPORTATION FEDERA
Page 340 and 341: II - Model 150D, Model 150E, Model
Page 342 and 343: IV - Model A150K, Aerobat, 2 PCLM (
Page 344 and 345: 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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Data Pertinent to All Models (cont
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Page 17 of 19 3A19 Data Pertinent t
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Data Pertinent to All Models (cont
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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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DEPARTMENT OF TRANSPORTATION FEDERA
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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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Page 494 and 495:
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)
Page 522 and 523:
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 532 and 533:
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
Page 546:
NOTE 8. 14 volt electrical system 1
Page 549 and 550:
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
Page 559 and 560:
3A12 12 Rev. 77 VIII. Model 172N (c
Page 561 and 562:
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:
Page 573 and 574:
3A12 26 Rev. 77 XI - Model 172R (co
Page 575 and 576:
3A12 28 Rev. 77 Data Pertinent to M
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3A12 30 Rev. 77 XII - Model 172S (c
Page 580 and 581:
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/
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Page 16 of 43 3A21 XIV - Model 210M
Page 609 and 610:
Page 18 of 43 3A21 XV - Model P210N
Page 611 and 612:
Page 20 of 43 3A21 Model 210N (cont
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XVII - Model P210R (cont’d) Fuel
Page 615 and 616:
Model T210R (cont’d) Fuel Capacit
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Page 26 of 43 3A21 NOTE 2. (cont’
Page 619 and 620:
Page 28 of 43 3A21 NOTE 2. (4) On f
Page 621 and 622:
Page 623 and 624:
Page 625 and 626:
Page 627 and 628:
NOTE 2. (cont’d) J. (10) Page 36
Page 629 and 630:
NOTE 2. (cont’d) J. (21) Near the
Page 631 and 632:
Page 633 and 634:
Page 42 of 43 3A21 NOTE 2. K. (26)
Page 636 and 637:
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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