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IX - Model 152 (cont'd) Page 11 of 19 3A19 Fuel capacity 26 gal. (24.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel Oil capacity 6 qt. (-14.7; unusable 2 qt.) See NOTE 1 for data on undrainable oil Control surface movements Wing flaps Down 0° -30° ±2° Ailerons Up 20° � 2° Down 15° � 1° (aileron travel measured from 1° ±.5° droop) Elevator Up 25° ±1° Down 18° ±1° Elevator tab Up 10° ±1° Down 20° ±1° Rudder Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. eligible 15279406 through 15282031 (1978 Model) 15282032 through 15283591 (1979 Model) 15283592 through 15284541 (1980 Model) 15284542 through 15285161 (1981 Model) 15285162 through 18285594 (1982 Model) 15285595 through 15285833 (1983 Model) 15285834 through 15285939 (1984 Model) 15285940 through 15286033 (1985 Model) X - Model A152, Aerobat, 2 PCLM (Acrobatic Category), Approved March 16, 1977 Engine S/N A1500433, A1520735, 681 through A521014 Lycoming O-235-L2C S/N A1521015 and on aircraft reworked per SK152-15 or SK152-16 Lycoming O-235-N2C *Fuel 100LL/100 min. grade aviation gasoline *Engine limits S/N A1500433, A1520735, 681 through A1521014 For all operations, 2550 r.p.m. (110 hp.) S/N A1521015 and on For all operations 2550 r.p.m. (108 hp.) Propeller and 1. (a) McCauley 1A103/TCM 23.2 lb. (-36.5) propeller limits Diameter: not over 69 in., not under 67.5 in. Static rpm at full throttle (carburetor heat off and mixture leaned to maximum r.p.m.) is 2280 to 2380 r.p.m. For allowable variations in static r.p.m. at non-standard temperatures, refer to the Service Manual. (b) Spinner: Dwg. 0450073 *Airspeed Limits (IAS) Never exceed 172 knots (See NOTE 4 on Use Maximum structural cruising 125 knots of IAS) Maneuvering 108 knots Flaps extended 85 knots C.G. range (+32.65) to (+36.5) at 1670 lb. (+31.0) to (+36.5) at 1350 lb. or less Empty weight C.G. range None Leveling means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone
3A19 Page 12 of 19 X - Model A152 (cont’d) *Maximum weight 1670 lb. 1675 lb. ramp weight (S/N 681, A1520809 and on) No. of seats 2 at (+39); (for child's optional jump seat, refer to Equipment List) Maximum baggage 120 lb. (Reference weight and balance data) Fuel capacity 26 gal. (24.5 gal. usable, two 13 gal. tanks in wings at +42.0) See NOTE 1 for data on unusable fuel Oil capacity 6 qt. (-14.7; unusable 2 qt.) See NOTE 1 for data on undrainable oil Control surface movements Wing flaps Down 0° -30° ±2° Ailerons Up 20° � 1° Down 15° � 1° (aileron travel measured from 1° ±.5° droop) Elevator Up 25° ±1° Down 18° ±1° Elevator tab Up 10° ±1° Down 20° ±1° Rudder Right 23° +0°, -2° Left 23° +0°, -2° (measured perpendicularly to hinge line) Serial Nos. eligible A1500433, A1520735 through A1520808 (1978 Model) 681, A1520809 through A1520878 (1979 Model) A1520879 through A1520943 (1980 Model) A1520944 through A1520983 (1981 Model) A1520984 through A1521014 (1982 Model) A1521015 through A1521025 (1983 Model) A1521026 through A1521027 (1984 Model) A1521028 through A1521049 (1985 Model) Data Pertinent to All Models Datum Fuselage station 0.0 front face of firewall Certification basis Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-4. In addition, effective S/N 15282032 and on for 152 and S/N 681, A1520809 and on for A152, FAR 23.1559 effective March 1, 1978. FAR 36 dated December 1, 1969, plus Amendments 36-1 through 36-5 for 152 and A152 only. In addition, effective S/N 15285940 and on, and S/N A1521028 and on, FAR 23.1545(a), Amendment 23-23 dated December 1, 1978. Application for Type Certificate dated August 13, 1956. Type Certificate No. 3A19 issued July 10, 1958, obtained by the manufacturer under delegation option procedures. Equivalent Safety Items S/N 15077006 through 15079405 S/N 15279406 and on S/N A1500610 through A1500734 S/N 681, A1500433, A1520735 and on Airspeed Indicator CAR 3.757 (See NOTE 4) (S/N 15279406 through 15285939 and 681, A1500433, A1520735 through A1521027) Operating Limitations CAR 3.778(a) Production basis Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations.
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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
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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
Page 297 and 298: 2A13 Page 4 of 43 Propeller Spinner
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
Page 346 and 347: VII - Model 150M (cont’d) Page 9
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
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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
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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 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
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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
Page 561 and 562:
3A12 14 Rev. 77 IX. Model 172P (con
Page 563 and 564:
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
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3A12 28 Rev. 77 Data Pertinent to M
Page 577 and 578:
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
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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.
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
Page 613 and 614:
XVII - Model P210R (cont’d) Fuel
Page 615 and 616:
Model T210R (cont’d) Fuel Capacit
Page 617 and 618:
Page 26 of 43 3A21 NOTE 2. (cont’
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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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