Where can I find the various operating limitations of the ATR 72-500?
LIMITATIONS
  
  PAGE : 001 APR 11 EASA APPROVED
  
  Model : 212 A 
  AFM 1  
  
  
  
  2.01.01 | INTRODUCTION
  
  Observance of the limitations contained in this chapter is required by law. When
  operating in accordance with an approved appendix or supplement to
  this manual, the limitations of this basic Airplane Flight Manual
  section apply, except as altered by such an appendix or supplement.
  
  2.01.02 | KINDS OF OPERATION
  
  The airplane is certified in the
  Transport Category, JAR 25 and ICAO annex 16 for day and night
  operations, in the following conditions when the appropriate equipment
  and instruments required by the airworthiness and operating
  regulations are approved, installed and in an operable condition :
  
  
  VFR and IFR
  Flight in icing conditions.
  Reverse thrust taxi (single or twin engine) 
  
  
  2.01.03 | MINIMUM FLIGHT CREW 
  
  2 pilots
  
  2.01.04 | PERFORMANCE CONFIGURATION
  
  Refer to 6.01.03 for airplane configuration associated with certified
  performances. 
  
  2.01.05 | MAXIMUM OPERATING ALTITUDE
  
  25000 ft
  
  2.01.06 | MANEUVERING LIMIT LOAD FACTORS
  
  
  Gear and flaps retracted : + 2.5 to -- 1 g 
  Gear and/or flaps extended : + 2 to 0 g
  
  
  2.01.07 | CONFIGURATION DEVIATION LIST
  
  Refer to 7.01.02 
  
  2.01.08 | NOISE CHARACTERISTICS
  
  The aircraft meets the requirements of ICAO annex 16,
  Chapter 4 with no weight restriction. Refer to noise characteristics
  in Appendix 7.01.01 of this manual for noise levels. 
  
  2.01.09 | MAXIMUM NUMBER OF PASSENGER SEATS
  
  74 as limited by emergency exits
  configuration 
  
  2.02.01 | WEIGHTS
  
  STRUCTURAL LIMITATIONS
  
  MAXIMUM WEIGHT KG LB
  
  
  RAMP 22970 50640 
  TAKE-OFF 22800 50265 
  LANDING 22350 49273 
  ZERO FUEL 20800 45856 
  
  
  PERFORMANCE LIMITATIONS
  
  Maximum take-off weight and maximum landing weight may be reduced by performance
  requirements related to the following (see chapter 6) :
  
  
  climb performance (first and second segment, final take-off and en route, approach and landing climb)
  available runway length (take-off and landing)
  tyre limit speed
  brake energy limit, observe BRK TEMP alert for take-off
  obstacle clearance (take-off and en route)
  en route and landing weight
  
  
  2.03.01 | AIRSPEEDS
  
  
  MAXIMUM OPERATING SPEED VMO / MMO
  
  This limit must not be intentionally exceeded in any flight regime.
  
  
  VMO = 250 kt CAS
  MMO = 0.55
  
  MAXIMUM DESIGN MANEUVERING SPEED VA
  
  Full application of roll and yaw controls, as well as maneuvers that involve angles of attack near the stall
  should be confined to speeds below VA. 
  
  
  VA = 175 kt CAS 
  
  
  CAUTION: Rapidly alternating large rudder applications in combination with
  large sideslip angles may result in structural failure at any speed.
  MAXIMUM FLAPS EXTENDED OR OPERATING SPEEDS VFE 
  
  
  FLAPS 15 185 kt CAS
  FLAPS 30 150 kt CAS
  
  MAXIMUM LANDING GEAR EXTENDED OR OPERATING SPEEDS
  
  
  VLE = 185 kt CAS 
  VLO 
  lowering = 170 kt CAS 
  retracting = 160 kt CAS 
  
  
  
  2.03.02 | OPERATIONAL PARAMETERS ENVIRONMENTAL ENVELOPE
  
  Note : Refer
  to 2.04.05 for fuel temperature limitation. TAKE–OFF AND LANDING –
  Tail wind limit : 15 kt – Maximum mean runway slope : ±2 % 
  
  2.04.01 | ENGINES
  
  PRATT&amp;WHITNEY CANADA PW127F or PW127M or PW127N 
  
  Operating limits with no unscheduled maintenance action required;
  Beyond these limits refer to maintenance manual.
  
  OPERATING CONDITION TIME LIMIT TQ
  (%) ITT ($^\circ$C) NH (%) NL (%) NP (%) OIL PRESS (PSI) OIL TEMP ($^\circ$C)
  (2) 
  
  RESERVE TAKE OFF 10 mn (6) 100 (1) 800 103.2 104.2 101 55 to 65 0 to 125 
  
  NORMAL TAKE OFF 5 mn 90 (1) (5)
  101.9 101.4 101 55 to 65 0 to 125
  
  MAXIMUM CONTINUOUS none (7)
  90.9 (1) 800 103.2 104.2 101 55 to 65 0 to 125 
  
  GROUND IDLE 66 mini 40 mini (4)
  -- 40 to 125 
  
  HOTEL MODE 715 55 to 65 125 
  
  TRANSIENT 20 s 120 840 106.4 106.8 106 (3) 40 to 100 5 s 120 20 mn 140 
  
  STARTING 5 s 950 --54 mini 
  
  
  Value linked to 100 % NP. 
  Oil temperature must be maintained above 45$^\circ$C to ensure protection for 
  the engine air inlet against ice accumulation.
  Permissible for completion of flight provided TQ does not exceed 75.2 %
  during climb and 73.13 % during cruise. 
  Up to 75 % NH only. 
  ITT limits depend on outside air temperature. Refer to 2.04 page 2.
  Single engine operation only, beyond 5 mn.
  MCT rating is the max
  power certified for continuous use. In-flight emergencies are the
  only conditions for which MCT use is authorized. 
  
  
  NOTE : Flight with an
  engine running and the propeller feathered is not permitted 
  
  2.04.02 | PROPELLERS
  
  TWO HAMILTON STANDARD HS 568 F 
   – 1 GROUND OPERATION 
  Engine run up must be performed into the wind.  Avoid static operation
  between 41.6 % and 62.5 % NP.  Avoid operation in feather above 66.6 %
  TQ. 
  
  GROUND OR FLIGHT OPERATION  If a propeller is involved in an
  overspeed or in an engine overtorque refer to the propeller
  maintenance manual. 
  
  FLIGHT OPERATION  ATR airplanes are protected
  against a positioning of power levers below the flight idle stop in
  flight by an IDLE GATE device.  It is reminded that any attempt to
  override this protection is prohibited. Such positioning may lead to
  loss of airplane control or may result in an engine overspeed
  condition and consequent loss of engine power. 
  
  04 POWER PLANT 2
  LIMITATIONS PAGE : 001 DEC 96 EASA APPROVED
  --Model : 212 A AFM 4 AUG 07 FEB 05 R JUL 06 SEP 06 R R R 
  
  2.04.03 | OILSYSTEM SPECIFICATION Refer to specification PWA 521 type II.
  
  2.04.04 | STARTER
  
  3 starts with a 1 minute 30 seconds maximum combined starter running time followed by 4 minutes OFF.
  
  2.04.05 | FUELSYSTEM
  
  Acceptable fuels : Jet A, Jet A1, JP5 and RT, TS1. Use of JP4 and Jet B is prohibited. 
  
  TEMPERATURE 
  
  
  For flight
  preparation, a minimum fuel temperature must be taken into account to
  ensure adequate relight :
  
  3 4 o C JET A, JET A1 and RT, TS1.
  2 6 o C for fuel type JP5. •Maximum temperature : 57 o C for fuel types JET A, JET A1, JP 5 and RT, TS1. 
  
  
  
  REFUELING 
  
  Maximum pressure 3.5
  bars (50 PSI) 
  
  USABLE FUEL 
  
  The total quantity of fuel usable in each
  tank is : 2500 kg (5510 lbs) 
  
  NOTE :Fuel remaining in the tanks when
  quantity indicators show zero is not usable in flight. 
  
  UNBALANCE
  
  Maximum fuel unbalance : 730 kg (1609 lbs) 
  
  FEEDING 
  
  
  Each electrical pump is able to supply one engine in the whole flight envelope. 
  One electrical pump and associated jet pump are able to supply both
  engines in the whole flight envelope 
  
  
  2.05.01 | AIR PRESSURIZATION
  
  
  Maximum differential pressure: 6.35 PSI
  Maximum negative differential pressure 0.5 PSI
  Maximum differential pressure for landing 0.35 PSI
  Maximum differential pressure for OVBD VALVE full open selection 1 PSI
  Maximum altitude for one bleed off operation 20000 ft
  
  
  2.05.02 | HYDRAULIC SYSTEM
  
  All hydraulic fluids compliant with technical
  specification : NSA 307110 Compliant fluids are listed in the AMM
  (Chapter20, 20-31-30) 
  
  2.05.03 | LANDING GEAR
  
  
  Do not perform pivoting (sharp turns) upon a landing gear with fully braked wheels except in case of emergency.
  In case of ground speed over 165 kt all tires to be replaced.
  Towbarless Towing is prohibited, unless the towbarless towing operations are performed in compliance with the appropriate
  operational requirements (JAR--OPS--1 for Commercial Air
  Transportation) using towbarless towing vehicles that are designed and
  operated to preclude damage to the aeroplane nose wheel steering
  system or which provide a reliable and unmistakable warning when
  damage to the steering system may have occurred. Towbarless towing
  vehicles that are specifically accepted for ATR aircraft are listed in
  ATR Service Letter 72--09--6001. 
  
  
  2.05.04 | FLAPS
  
  Holding with any flaps extended is prohibited in icing conditions (except for single engine operations). 
  
  2.05.05 | AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)
  
  
  Minimum height for autopilot engagement on take off : 100 ft
  NAV mode for VOR approach, using either autopilot or flight director is authorized only if :
  
  
  a co--located DME is available, and
  DME HOLD is not selected
  
  Minimum height for use of either autopilot or flight director :
  
  Except during take off or executing an approach : 1000 ft
  VS or IAS mode during approach : 160 ft
  CAT 1 APP mode : 160 ft Refer to 7.01.03 for CAT II operation 
  
  
  
  2.05.06 | INSTRUMENTS MARKING
  
  Red arc or radial line : minimum and maximum limits Yellow arc : caution area Green arc : normal area 
  
  2.05.07 | CARGO DOOR OPERATION
  
  Do not operate cargo door with a lateral wind component of more than 45 kt. 
  
  .../... 05 SYSTEMS 2 LIMITATIONS PAGE : 001 AUG 14 EASA APPROVED
  --Model : 212 A AFM 2
  
  2.05.08 | ELECTRICAL
  
  Single DC GEN operation : In flight, if OAT exceeds ISA + 25, flight level must be limited to FL200. 
  
  2.05.09 | MFC
  
  Take off with two or more failed MFC modules is prohibited 
  
  2.05.10 | COMMUNICATIONS
  
  Not applicable 
  
  2.05.11 | TCAS
  
  When installed, Refer to appendix 7.01.0