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25 2A4 XVII - MODEL 695 (cont’d) Propeller and Propeller Limits b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1 (cont’d) c. Governor: 2 AiResearch P/N 897410-2B or 897410-4. Airspeed Limits Maneuvering 158 m.p.h. (137K) CAS Maximum Operating 280 m.p.h. (143K) CAS .52 MACH Flaps extended - half 207 m.p.h. (180K) CAS Flaps extended - full 161 m.p.h. (140k) CAS Landing gear extended 230 m.p.h. (200K) CAS C.G. Range Forward 210.51 inches aft of datum (20.06% MAC) at 10,325 lbs. 204.70 inches aft of datum (12.03% MAC) at 7,500 lbs. 204.70 inches aft of datum (12.03% MAC) at 6,798 lbs. 215.10 inches aft of datum (26.42% MAC) at 6,240 lbs. Straight line variation between points. Aft 218.67 inches aft of datum (31.35% MAC) at 10,325 lbs. 217.88 inches aft of datum (30.25% MAC) at 6,332 lbs. Variation between points: Inches aft of datum = 219.93 - (13029/Weight) Datum 196 in. forward of wing leading edge at center section Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge. Lateral - Transverse beams at front of rear baggage compartment floor. Maximum weight Maximum takeoff 10,325 lbs. (ramp weight 10,375 lbs.) Maximum landing 9,675 lbs. Zero fuel 8,800 lbs. Maximum operating altitude 31,000 feet Maximum No. of seats 11 (Pilot + 10 passengers; pilot, co-pilot + 9 passengers) Maximum baggage 600 lb. (+260) Fuel capacity Total standard capacity 430 gal., usable 425 gal. (S/N 95000 thru 95040). Total standard capacity 482 gal., usable 474 gal. (S/N 95041 thru 95999). (See NOTE 1 for systems fuel.) Oil capacity 12.0 qts. total (6.0 qts. total each tank) (+188) 10.0 qts. usable (See NOTE 1 for system oil). Control Surface movements Elevator Up 30° ± 1 Down 10° ± 2 0 0 Elevator tab Up 3° ± 1 Down 24° ± 1 Rudder Right 20° ± 2 Left 20° ± 2 0 0 Rudder tab Right 20° ± 2 Left 20° ± 2 0 0 Aileron Up 23° ± 2 Down 15° ± 2 Flaps Down 40° ± 2 Aileron tab Up 17° ± 2.5° Down 17° ± 2.5° Serial Nos. eligible Under the delegation option, provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to: Issue Airworthiness Certificates and approve design and production changes on airplane serial numbers 95000 through 95084. (See NOTE 22.)
2A4 26 XVIII - MODEL 695A, 11 PCLM (Normal Category), Approved April 30, 1981 Engines 2 AiResearch Model TPE-331-10-501K Turboprop Engines (Rockwell P/N 610653) or 2 Garrett Model TPE-331-10-511K Turboprop Engines (Gulfstream P/N 610653) See NOTE 19. Fuel Aviation turbine fuels ASTM designation D1655-68, Types Jet A, Jet A-1, and Jet B; MIL-T-5624G-1, Grades JP-4 and JP-5; MIL-T-83133, Grade JP-8, and MIL-F-46005A(MR)-1, Types I and II. Oil MIL-L-23699B Type II (See Mfg. Data Part VIII Approved POH for List of Approved Lubricants). Engine Limits Torque RPM EGT Takeoff and Maximum continuous 102.5%(820) 101.0% 650°C Propeller and Propeller 2 Dowty-Rotol Ltd. 3-bladed feathering and reversing propellers. Limits Rockwell Assembly No. 640080. a. Dowty-Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP2926 includes B. F. Goodrich propeller de-icing kit No. 65-330-1 or Dowty Rotol Ltd. Type No. (C) R306/3-82-F/7-(c) VP 3027 includes Dowty Rotol Deice Boots 660709275 as B. F. Goodrich De-Ice Boots 4E 2598-10. See NOTE 17. Dowty-Rotol Propeller Blade Assembly P/N 660706330-XX Pitch settings at .7 radius station: Feather 83 10’ ± 20’, Reverse -13.75° ± 1.0°, Start Locks -1.25° ± 1.0°, Flight Idle 6.0° ± 0.5°. Diameter: 106 in., 1/2in. reduction per blade allowed. NOTE: Use AiResearch oil transfer tube Part No. 897458-2. NOTE: Downwind ground operation above taxi power is prohibited when airplane is stationary, must be done with the airplane headed into the wind. b. Spinner: 2 Dowty-Rotol Ltd. Type No. (C)SB7/3/1 c. Governor: 2 AiResearch P/N 897410-2B or 897410-4. Airspeed Limits Maneuvering 162 m.p.h. (141K) CAS Maximum Operating 290 m.p.h. (252K) CAS .60 MACH Flaps extended - half 207 m.p.h. (180K) CAS (S/N 96000-96055) 230 m.p.h. (200K) CAS (S/N 96056-96999) Flaps extended- full 161 m.p.h. (140K) CAS (S/N 96000-96055) 184 m.p.h. (160K) CAS (S/N 96056-96999) Landing gear extended 230 m.p.h. (200K) CAS C.G. Range Forward 209.78 inches aft of datum (19.1% MAC) at 11,200 lbs. 204.34 inches aft of datum (11.5% MAC) at 8,500 lbs. 204.34 inches aft of datum (11.5% MAC) at 7,010 lbs. 214.18 inches aft of datum (25.1% MAC) at 6,466 lbs. Straight line variation between points Aft 218.77 inches aft of datum (31.5% MAC) at 11,200 lbs. 217.95 inches aft of datum (30.4% MAC) at 6,582 lbs. Variation between points: Inches aft of datum = 219.93 - (13029/Weight) Datum 196 in forwad of wing leading edge at center section. Leveling means Longitudinal - Top of fuselage on centerline aft of wing trailing edge. Lateral - Transverse beams at front of rear baggage compartment floor.
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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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 469 and 470: E-273 Page 2 Model O-470-A O-470-E
Page 471 and 472: E-273 Page 4 NOTE 3. The following
Page 473 and 474: E-273 Page 6 NOTE 13. The following
Page 475 and 476: P57GL Page 2 of 5 Maximum Diameter
Page 477 and 478: P57GL Page 4 of 5 NOTE 3. Pitch Con
Page 480 and 481: DEPARTMENT OF TRANSPORTATION P-920
Page 482 and 483: Page 3 of 12 P-920, Revision 29 Max
Page 484 and 485: Note 2: Blade Model Designation (Se
Page 486 and 487: Note 9: Special Limits Page 7 of 12
Page 488 and 489: Page 9 of 12 P-920, Revision 29 Hub
Page 490 and 491: Page 11 of 12 P-920, Revision 29 Hu
Page 492 and 493: DEPARTMENT OF TRANSPORTATION FEDERA
Page 494 and 495: 3 2A4 II. - Model 680-E (cont’d)
Page 496 and 497: 5 2A4 III. - Model 720 (cont’d) L
Page 498 and 499: V - Model 560-F, 7 PCLM (Normal Cat
Page 500 and 501: 9 2A4 VI - Model 680-FL (cont’d)
Page 502 and 503: 11 2A4 VII - MODEL 680-FL(P) (cont
Page 504 and 505: 13 2A4 IX - MODEL 680-V, 11 PCLM (N
Page 506 and 507: 15 2A4 X - MODEL 680-W (cont’d) D
Page 508 and 509: 17 2A4 XI - MODEL 681 (cont’d) Se
Page 510 and 511: 19 2A4 XIII - MODEL 685 (cont’d)
Page 512 and 513: XIV - MODEL 690A (cont’d) Maximum
Page 514 and 515: 23 2A4 XVI - MODEL 690C, 11 PCLM (N
Page 518 and 519: 27 2A4 XVIII - MODEL 695A (cont’d
Page 520 and 521: 29 2A4 XIX - MODEL 690D (cont’d)
Page 522 and 523: 31 2A4 Specifications Pertinent to
Page 524 and 525: 33 2A4 NOTE 6: Model 680FL S/N 1471
Page 526 and 527: Page No. 1 2 3 4 Rev. No. 9 9 9 9 R
Page 528 and 529: 3 E-284 NOTE 4. The "6" in the engi
Page 530 and 531: DEPARTMENT OF TRANSPORTATION FEDERA
Page 532 and 533: Page 3 of 17 A9CE II. Model A188, A
Page 534 and 535: III. Model 188A, AGwagon "A" & "B"
Page 536 and 537: V. Model 188B, AGpickup (cont'd) *E
Page 538 and 539: Page 9 of 17 A9CE VI. Model A188B (
Page 540 and 541: VII. Model T188C (cont'd) Number of
Page 542 and 543: Page 13 of 17 A9CE Reference weight
Page 544 and 545: Page 15 of 17 A9CE Fuel Flows at Fu
Page 546: NOTE 8. 14 volt electrical system 1
Page 549 and 550: 3A12 2 Rev. 77 I. Model 172 (cont'd
Page 551 and 552: 3A12 4 Rev. 77 II. Model 172A, Mode
Page 553 and 554: 3A12 6 Rev. 77 IV. Model 172D, Mode
Page 555 and 556: 3A12 8 Rev. 77 V. Model 172I, Model
Page 557 and 558: 3A12 10 Rev. 77 VI. Model 172L (con
Page 559 and 560: 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
Page 565 and 566: 3A12 18 Rev. 77 DATA PERTINENT TO A
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3A12 20 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
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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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NOTE 2. (cont’d) J. (10) Page 36
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NOTE 2. (cont’d) J. (21) Near the
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Page 42 of 43 3A21 NOTE 2. K. (26)
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A3SO Page 3 of 31 I. - Model PA-32-
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A3SO Page 5 of 31 II. - Model PA-32
Page 642 and 643:
A3SO Page 7 of 31 III. - Model PA-3
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A3SO Page 9 of 31 V. - Model PA-32R
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-
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A3SO Page 23 of 31 XIV. - Model PA-
Page 660 and 661:
A3SO Page 25 of 31 PA-32R-301, S/N
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A3SO Page 27 of 31 23.1329, 23.1351
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A3SO Page 29 of 31 AFM Supp. VB-357
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A3SO Page 31 of 31 32R-8029121, 32R
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Section V FAA FORMS • FAA Form 33
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5-3 Form Approved Electronic Tracki
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Paperwork Reduction Act Statement:
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Computer Testing Supplement for IA.indb - Aviation Supplies ...

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