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TCDS E4EA PAGE 19 NOTE 5. External airbleed shall not exceed 5.25%, except as specified in specific installation manuals. A maximum of 1.5 lbs. Per minute may be bled during starting. Bleed air meets the requirements of Paragraph 3.18 of MIL-E-5007C. NOTE 6. Maximum Allowable Torque: The Maximum allowable steady state and acceleration torque, as measured by the torquemeter, are: Model Continuous lb. Ft. Transient Acceleration lb. Ft. PT6A-11, 11AG 1194 1500 PT6A-6, 6A, 6B, 20, 20A, 20B, 6/C20, 21 25, 25A 1315 1500 PT6A-15AG, 27 1628 2100 PT6A-28 1786 2100 PT6A-29, 34, 34B, 34AG, 35, 36, 25C 1970 2100 PT6A-38 1970 2750 PT6A-40 2230 2750 PT6A-41, 41AG, 42, 42A 2230 2750 PT6A-45, 45A, 45B 3625 5100 PT6A-45R 3625 5100 PT6A-50 4860 5900 PT6A-135, 135A 2080 2400 PT6B-9 464 --- PT6A-112 1480 1900 PT6A-110 1313 1700 PT6A-60, 60A, 60AG 3625 5100 PT6A-61, 61A 2230 2750 PT6A-65B 3625 5100 PT6A-65R 4250 (3800 Alternative Takeoff 5100 PT6A-114, 114A 1980 2400 PT6A-121 1710 2200 PT6B-35F 570 658 PT6A-65AR 4400(3800 Alternative Takeoff) 5100 PT6A-116 1940 2400 PT6A-65AG 3800 5100 PT6D-114A 610 740 PT6A-52 2230 2750
TCDS E4EA PAGE 20 NOTE 7. The maximum output shaft overspeed limit is 110 percent (except 100% for PT6A-38, 41, 41AG, 42 and 42A only) at all ratings and may be employed for sustained periods in emergencies. The normal steady state output shaft operating limit speeds are defined as 2200 rpm (100%) for the PT6A-6, 6A, 6B, 6/C20, 11, 11AG, -15AG, - 20, -20A, -20B, -21, -25, -25A, -25C, -27, -28, -29, -34, -34B, -34AG, -36, 2190 rpm (99.6%) for the PT6A-35, 2000 rpm (90.7%) for the PT6A-38, -40, -41, -41AG, -42, -42A, -52, -61, and -61A, 1900 rpm (100%) for the PT6A-45,-45A,-45B,-45R,-65B,-65R,-60,-60A,-60AG,-65AR,-65AG, -135, 135A, 110, 112, 114, 114A, 121, and 116, 1210 rpm (100%) for the PT6A-50, 6230 rpm (100%) for the PT6B-9 and 6188 rpm (100%) for the PT6B-35F and PT6D-114A and is the normal steady state operating limit. The normal steady state operating limit speed rises linearly as power is decreased, reaching a maximum of 105% at idle power for the PT6B-9. 100% gas generator speed is defined as 37,468 rpm. Unlimited and limited gas generator speeds are: Model Unlimited Speed, rpm Limited Speed, rpm Duration PT6A-6,-6A,-6B,-11,-11AG,- 20,-20A,-20B,-6/C20,-21,- 25,-25A,-25C,-27,-28,-29,- 34,-34B,-34AG,-36,-38,-41 38,100 (101.7%) 38,500 (102.8%) 10 Sec PT6A-35,-110,-112,-114,- 114A,-116,-121,-135,- 135A,PT6D-114A 38,100 (101.7%) 38,500 (102.8%) 2 Sec PT6A-50 38,500 (102.8%) --- --- PT6A-40,-42,-42A 38,100 (101.7%) 39,000 (104.1%) 10 Sec PT6A-45,-45A,-45B,-45R,- 52, -60,-60A,-60AG,-61,- 61A,-62,-65B,-65R,-65AR,- 65AG 39,000 (104.1%) --- --- NOTE 8. Emergency use of MIL-G-5572, Grades 80/07, 91/98, 100/130 and 115/145 is permitted for a total time period not exceeding 150 hours during any overhaul period. It is not necessary to purge the unused fuel from the system when switching fuel type. NOTE 9. The following oils are eligible for these engines: PWC PT6 Engine Service Bulletin Nos. 1001, 1601, 3001, 4001, 12001 and 13001 list approved brand oils. NOTE 10. These engines meet FAA requirements for operation in icing conditions when the intake system conforms with the PWC Installation Manual instruction for inertial separation of snow and icing particles; when the alternative approved alcohol system is used, flight in visible moisture is restricted as specified in the PWC Installation Manual. These engines also meet FAA requirements for adequate disk integrity and rotor blade containment and do not require external armoring. NOTE 11. For reversing application the PT6A-6A and PT6A-20 engines must be equipped with Woodward Propeller Governor Type X210XXX. NOTE 12. Fuel controls approved for each engine model are listed in the applicable Parts Catalog. NOTE 13. The above models incorporate the following characteristics: Model Characteristics PT6A-6 Basic model PT6A-6A Incorporates provisions for reversing propeller. PT6A-6B Incorporates provisions for reversing propeller, PT6A-20 mechanism. PT6B-9 Single stage reduction gearing. (Output shaft speed 6,230 r.p.m.) PT6A-20 Maximum continuous rating equal to takeoff. Provisions for reversing. PT6A-20A Similar to PT6A-20 except for exhaust port configuration and optional propeller reversing system. PT6A-20B Similar to PT6A-20 except for optional propeller reversing system. PT6A-11 Similar to PT6A-21 except derated.
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Computer Testing Supplement for Ins
Page 6 and 7:
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
Page 230 and 231: (1) The wire run is 15.5 feet long,
Page 232 and 233: STEP 1: Refer to the “single wire
Page 234 and 235: FIGURE 11-3. Conductor chart, inter
Page 236 and 237: FIGURE 11-4b. Single copper wire in
Page 238 and 239: FIGURE 11-6. Altitude derating curv
Page 240 and 241: Minimum Equipment List Page MINIMUM
Page 242 and 243: EXHIBIT 24 Bend Allowance = 2π (R
Page 244 and 245: 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: TCDS E4EA PAGE 18 Accessory Drive P
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 and 296: 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
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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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DEPARTMENT OF TRANSPORTATION FEDERA
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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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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.
Page 391 and 392:
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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Page 413 and 414:
Page 415 and 416:
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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Page 421 and 422:
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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Page 430 and 431:
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
Page 436 and 437:
Oil Capacity 8 qts. per engine (5 q
Page 438 and 439:
11 of 16 A7SO Control Surface Movem
Page 440 and 441:
13 of 16 A7SO Equipment The basic r
Page 442 and 443:
15 of 16 A7SO The Model PA-34-200T;
Page 444 and 445:
Page No. 1 2 3 4 5 6 7 8 Rev. No. 1
Page 446 and 447:
Page 3 A11EA 3. McCauley Model 1A10
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Oil capacity 6 qt. at (+39) (2 qt.
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UTILITY CATEGORY AA-1 AA-1A Maximum
Page 452 and 453:
Page 454 and 455:
Page 3 of 15 1A6 Maximum Baggage50
Page 456 and 457:
Page 5 of 15 1A6 Fuel Capacity 36 g
Page 458 and 459:
Page 7 of 15 1A6 Fuel Capacity 36 g
Page 460 and 461:
Page 9 of 15 1A6 Required Equipment
Page 462 and 463:
Page 11 of 15 1A6 105. Vacuum pump
Page 464 and 465:
Page 13 of 15 1A6 (w) FAA-DOA appro
Page 466:
Page 15 of 15 1A6 (3) On left side
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
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P57GL Page 2 of 5 Maximum Diameter
Page 477 and 478:
P57GL Page 4 of 5 NOTE 3. Pitch Con
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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:
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 516 and 517:
25 2A4 XVII - MODEL 695 (cont’d)
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:
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:
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
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
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 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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