Where can I find the various operating limitations of the ATR 72-500? Is there any document that lists them?
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
2.01.04 | PERFORMANCE CONFIGURATION
Refer to 6.01.03 for airplane configuration associated with certified performances.
2.01.05 | MAXIMUM OPERATING ALTITUDE
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
MAXIMUM WEIGHT KG LB
- RAMP 22970 50640
- TAKE-OFF 22800 50265
- LANDING 22350 49273
- ZERO FUEL 20800 45856
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
- 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&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.
- 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.
Maximum pressure 3.5 bars (50 PSI)
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.
Maximum fuel unbalance : 730 kg (1609 lbs)
- 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
2.05.11 | TCAS
When installed, Refer to appendix 7.01.0