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A3SO Page 3 of 31 I. - Model PA-32-260 (cont'd) No. of Seats 6 (2 at +85.5, 2 at +118.1, 2 at +155.7) 7 (2 at +85.5, 3 at +118.1, 2 at +155.7) (See NOTE 3) 6 (2 at +85.5, 2 at +118.1, 2 at +157.6) 7 (2 at +85.5, 3 at +118.1, 2 at +157.6) (See NOTE 3) 6 (2 at +85.5, *2 at +119.1, 2 at +157.6) (See NOTE 11) * - Optional Club Seats Maximum Baggage 200 lb. (100 lb. at +42.0, 100 lb. at +178.7) Fuel Capacity 84 gallons at +95.0 (4 wing tanks) See NOTE 1 for data on system fuel Oil Capacity 12 qt. at +16.6 (9-1/4 qt. usable) See NOTE 1 for data on system oil Control Surface Movements Wing Flaps Up 0� (�2�) Down 40� (�2�) Ailerons Up 30� (�2�) Down 15� (�2�) Rudder Left 27� (�2�) Right 27� (�2�) Stabilator Up 16� (�1�) Down 2� (�1�) Stabilator Tab Up 5� (�1�) Down 8� (�1�) Nose Wheel Travel S/N 32-1 through 32-1297, and 32-7100001 through 32-7300066: Left 30� (�2�) Right 30� (�2�) S/N 32-7400001 through 32-7800008: Left 24� (�2�) Right 24� (�2�) Manufacturer's Serial Nos. 32-03, 32-04, 32-1 through 32-1297, and 32-7100001 through 32-7800008. The manufacturer is authorized to issue airworthiness certificates for airplane serial numbers 32-1034 through 32-1297, and 32-7100001 through 32-7800008 under the delegation option provisions of FAR 21. II. - Model PA-32-300 (Cherokee Six 300), 6 PCLM (Normal Category), Approved May 27, 1966; 7 PCLM (Normal Category), Approved November 15, 1966. Same as Model PA-32-260 except for engine installation and fuel system. Engine Lycoming IO-540-K1A5, Bendix injector type RSA-10ED1 Lycoming IO-540-K1G5 (See NOTE 12) Flow Setting No. 2524273 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (300 hp) Propeller and Propeller Limits Hartzell constant speed Model HC-C2YK-1( ), Blade Models 8475-4 & 8475D-4, or Hartzell constant speed Model HC-C2YK-1( )F, Blade Models F8475D-4 Pitch: High 34� � 1�, Low 13.5� � .2� at 30 in. station Diameter: Not over 80 in., not under 78.5 in. Governor Assembly: Hartzell F-4-4( ) or F-4-11( ) (See NOTE 10) Spinner: P/N 68713 or P/N 66785 Spinner Tip and P/N 66786 Spinner Shell, or P/N 67790-0 Spinner, P/N 67791-0 Bulkhead, P/N 67793-0 Bulkhead, P/N 99499-0 Plate, two each P/N 67794-0 Cuff or Kit 760-452V (See NOTE 6)
A3SO Page 4 of 31 II. - Model PA-32-300 (cont'd) Propeller and Propeller Limits Hartzell constant speed Model HC-C2YK-1( ), Blade Model 8475R-0, or (continued) Hartzell constant speed Model HC-C2YK-1( )F, Blade Model F8475R-0 Pitch: High 29� � 1�, Low 12.4� � .2� at 30 in. station Diameter: Not over 84 in., not under 82.3 in. Governor Assembly: Hartzell F-4-4( ) or F-4-11( ) (See NOTE 10) Spinner: P/N 68713 or P/N 66785 Spinner Tip and P/N 66786 Spinner Shell or P/N 67790-0 Spinner, P/N 67791-0 Bulkhead, P/N 67793-0 Bulkhead, P/N 99499-0 Plate, two each P/N 67794-0 Cuff or Kit 760-452V (See NOTE 6) Airspeed Limits Never exceed 212 m.p.h. (184 knots) CAS Maximum structural cruise 168 m.p.h. (146 knots) CAS Maneuvering 149 m.p.h. (130 knots) CAS Flaps extended 125 m.p.h. (109 knots) CAS C.G. Range (gear extended) (+91.4) to (+95.5) at 3400 lb. (+90.2) to (+96.2) at 3300 lb. (+81.4) to (+96.2) at 2600 lb. (+78.0) to (+96.2) at 2060 lb. or less Straight line variation between points given. LBS. 3400 3300 2600 2060 78.0 81.4 INCHES (+91.4) to (+95.5) at 3400 lb. (+89.0) to (+96.2) at 3300 lb. (+80.0) to (+96.2) at 2900 lb. (+76.0) to (+96.2) at 2400 lb. or less Straight line variation between points given. LBS. 3400 3300 2900 2400 76.0 80.0 90.2 91.4 (S/N 32-40001 through 32-40565) INCHES 89.0 91.4 95.5 96.2 95.5 96.2 3400 3300 2600 2060 3400 3300 2900 2400 (S/N 32-40566 through 32-40974, and 32-7140001 through 32-7940290)
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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
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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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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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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
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
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’
Page 619 and 620: Page 28 of 43 3A21 NOTE 2. (4) On f
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 633 and 634: Page 42 of 43 3A21 NOTE 2. K. (26)
Page 636 and 637: DEPARTMENT OF TRANSPORTATION FEDERA
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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