AW139 QUICK REFERENCE HANDBOOK

4 thru 6 19 7 and 8 20 9 0 10 blank 0 11 3 12 and 13 16 14 blank 0 15 16 16 0 17 4 18 and 19 0 19a and 19b 16 20 blank 0 20a 21 20b 19 21 19 22 13 23 and 24 21 24a 21 24b 15 GW1 19 GW2 20 GW3 thru GW12 19 ALT1 thru ALT6 19 25 19 26 20 26a 16 26b blank 16 27 0 28 thru 30 2 31 21 32 and 33 15 34 21 35 and 36 2 37 8 38 and 39 2 40 blank 0 41 19 42 17 43 15 44 0 45 and 46 4 47 16 48 21 48a 16 48b 21 48c 16 48d blank 16 49 and 50 2 51 13 52 10 53 and 54 16 54a 20 54b 16 54c 21 54d blank 16 55 10 56 21 56a thru 56d 21 57 thru 60 3 61 15 PAGE REVISION N° TOC, REC of REVS UNMAINTAINED COPY FOR INFORMATION ONLY AW139-QRH Record of Effective Pages Page B-2 Rev. 21 62 20 63 15 64 and 65 19 66 15 67 and 68 20 69 and 70 0 71 20 72 19 EMERGENCY AND MALFUNCTION PROCEDURES 1 and 2 0 3 19 4 thru 6 15 7 and 8 16 9 19 10 21 11 20 12 2 13 0 14 3 15 15 16 3 17 21 18 and 19 15 20 16 21 15 22 and 23 20 24 15 24a thru 24d (*) 19 25 21 26 20 27 and 28 2 29 0 30 3 31 15 32 21 33 and 34 15 35 and 36 21 PAGE REVISION N° 37 and 38 20 39 and 40 15 40a 15 40b thru 40d 21 41 15 42 21 43 20 44 and 45 15 46 0 47 20 48 21 49 7 50 21 51 and 52 15 52a 15 52b blank 15 53 20 54 16 55 21 56 16 57 0 58 and 59 16 60 and 61 0 62 15 63 and 64 20 64a and 64b 20 65 20 66 2 67 0 68 2 69 16 70 21 71 16 72 thru 74 2 75 0 76 21 77 15 78 20 PAGE REVISION N° TOC, REC of REVS UNMAINTAINED COPY FOR INFORMATION ONLY AW139-QRH Record of Effective Pages Rev. 21 Page B-1 (*) Yellow pages, T.C. only 78a 15 78b blank 15 79 and 80 0 81 20 82 5 82a and 82b 5 83 5 84 3 85 19 86 20 86a 20 86b and 86c 21 86d 15 87 20 88 16 89 thru 91 0 92 blank 0 93 thru 96 16 96a 16 96b 17 97 16 98 17 99 and 100 16 PAGE REVISION N° Page B-3 UNMAINTAINED COPY FOR INFORMATION ONLY AW139-QRH Record of Effective Pages Page B-2 Rev. 20 Page B-4 UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 19 Lims-Norm-Perf Page 1 AW139-QRH GENERAL, TYPE OF OPER, MIN CREW, WEIGHT, CG LIMITATIONS SPEED, ALTITUDE, TEMP LIMITATIONS H-V, CAT B/A LIMITATIONS ENGINE, FUEL, LUBRICANTS, HYDRAULICS LIMITATIONS MISCELLANEOUS LIMITATIONS GENERAL, FLIGHT PLANNING, EXTERNAL CHECKS PRE-START CHECKS ABORTED ENGINE START DRY MOTORING PROCEDURE ENGINE START PROCEDURE SYSTEM CHECKS TAXIING, PRE-TAKE OFF, TAKE OFF IN FLIGHT PROCEDURES APPROACH, LANDING CAT B/A POST LANDING & SHUTDOWN FLIGHT MANAGEMENT SYSTEM OPER- ATION ADVISORY CAPTIONS, PDF MESSAGES DENSITY ALTITUDE, POWER ASSUR, CAT B & A DISTANCE CHARTS HOVER CEILING, ROC, FUEL CONSUMPTION L I M I T S GENERAL, TYPE OF OPER, MIN CREW, WEIGHT, CG LIMITATIONS SPEED, ALTITUDE, TEMP LIMITATIONS H-V, CAT A/B LIMITATIONS ENGINE, FUEL, LUBRICANTS, HYDRAULICS LIMITATIONS MISCELLANEOUS LIMITATIONS (GW EXT, ALT EXT if applicable) GENERAL, FLIGHT PLANNING, EXTERNAL CHECKS PRE-START CHECKS ABORTED ENGINE START DRY MOTORING PROCEDURE ENGINE START PROCEDURE SYSTEM CHECKS TAXIING, PRE-TAKE OFF, TAKE-OFF CAT A/B IN FLIGHT PROCEDURES APPROACH, LANDING CAT A/B POST LANDING & SHUTDOWN FLIGHT DIRECTOR AND FLIGHT MANAGEMENT SYSTEM OPERATION ADVISORY CAPTIONS, PDF MESSAGES DENSITY ALTITUDE, POWER ASSUR FLYAWAY HEIGHT LOSS HOVER CEILING, ROC, FUEL CONSUMPTION GEN WT/CG SPD ALT ENG FUEL ABORT DRY MOT ENG START TAXI T-O MISC PRE START IN FD/FMS N O R M A L P R O C E D TEMP LUB HYD U R E S EXTN CAT A/B FLIGHT OPER POST LD SHT DN P E R F HVR ROC FL CONS CAPTS MSGS L I M I T S SYS CHECKS CHECKS H-V CAT A/B LAND APPR TOC, REC of REVS Hd PAV FLYAWAY UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 2 AW139-QRH USE OF WARNINGS, CAUTIONS AND NOTES Warnings, Cautions and Notes are used to emphasize important and critical instructions and are used as follows: WARNING An operating procedure, practice, etc., which, if not correctly followed, could result in personal injury or loss of life. CAUTION An operating procedure, practice, etc., which, if not strictly observed, could result in damage to, or destruction of, equipment. Note An operating procedure, condition, etc., which is essential to highlight. USE OF PROCEDURAL WORDS The concept of procedural word usage and intended meaning which has been adhered to in preparing this QRH is as follows: ”Shall” or ”Must” have been used only when application of a procedure is mandatory. ”Should” has been used only when application of a procedure is re-com- mended. ”May” has been used only when application of a procedure is optional. ”Will” has been used only to indicate future events, not to indicate a manda- tory procedure. ”Condition” has been used to determine if the item under examination pre- sents external damage which could jeopardize its safe operation. ”Secure” has been used to determine if the item under examination is cor- rectly locked, referring to doors and disconnectable items, or correctly posi- tioned and installed. UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 16 Lims-Norm-Perf Page 3 AW139-QRH LIMITATIONS GENERAL....................................................................................... 7 TYPES OF OPERATION................................................................. 7 MINIMUM FLIGHT CREW .............................................................. 7 NUMBER OF OCCUPANTS ........................................................... 7 WEIGHT AND CENTER OF GRAVITY LIMITATIONS................... 7 AIRSPEED LIMITATIONS .............................................................. 11 GROUND SPEED LIMITATIONS ................................................... 11 WIND SPEED LIMITATIONS FOR ROTOR STARTING & STOPPING ............................................................... 12 ALTITUDE LIMITATIONS ............................................................... 12 AMBIENT AIR TEMPERATURE LIMITATIONS (OAT) .................. 12 MANOEUVRING LIMITATIONS ..................................................... 12 ICING LIMITATIONS....................................................................... 12 AUTOROTATION LIMITATIONS .................................................... 12 SLOPE LIMITATIONS .................................................................... 13 ALTITUDE AND TEMPERATURE LIMITATIONS CHART ............ 13 HEIGHT- VELOCITY LIMITATIONS ............................................... 15 CAT A MISCELLANEOUS LIMITATIONS...................................... 15 HEIGHT - VELOCITY DIAGRAM.................................................... 16 CATEGORY B OPERATION LIMITATIONS................................... 17 CATEGORY A OPERATION LIMITATIONS................................... 18 ENGINE AND TRANSMISSION DIGITAL LIMITATIONS ............ 20a ENGINE LIMITATIONS................................................................... 21 ENGINE STARTER DUTY CYCLE . . . . . . . . . . . . . . . . . . . . . . 21 POWER MARGIN TREND MONITORING . . . . . . . . . . . . . . . . 21 ENGINE TRAINING MODE LIMITATIONS . . . . . . . . . . . . . . . . 21 FUEL LIMITATIONS ....................................................................... 21 FUEL CAPACITIES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 UNUSABLE FUEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 AUTHORIZED FUEL TYPES . . . . . . . . . . . . . . . . . . . . . . . . . . 21 LUBRICANT LIMITATIONS............................................................ 22 AUTHORIZED ENGINE OILS . . . . . . . . . . . . . . . . . . . . . . . . . . 22 AUTHORIZED TRANSMISSION OIL . . . . . . . . . . . . . . . . . . . . 22 ELECTRICAL HYDRAULIC PUMP . . . . . . . . . . . . . . . . . . . . . . 22 AUTHORIZED HYDRAULIC FLUIDS . . . . . . . . . . . . . . . . . . . . 22 UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 4 Rev. 19 AW139-QRH MISCELLANEOUS LIMITATIONS................................................. 23 DC GENERATOR LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 WHEEL BRAKE LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . 23 PITOT HEATING LIMITATIONS. . . . . . . . . . . . . . . . . . . . . . . . 23 AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS. . . 23 AVIONIC LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 FLIGHT DIRECTOR LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . 24 FMS AND GPS LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . 24b TORQUE LIMITER FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . 24b ENGINE EEC LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . 24b SYNOPTIC MFD PAGE LIMITATIONS . . . . . . . . . . . . . . . . . . 24b HEADSET/HELMET LIMITATIONS . . . . . . . . . . . . . . . . . . . . . 24b INCREASED GROSS WEIGHT 6800 KG (IF APPLICABLE). GW1 T-O & LANDING ALTITUDE EXTENSION (IF APPLICABLE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALT1 NORMAL PROCEDURES GENERAL ...................................................................................... 25 FLIGHT PLANNING ....................................................................... 25 CAT B WEIGHT AND H-V DETERMINATION .......................... 25 CATEGORY A PROCEDURES................................................. 25 CATEGORY A TAKE OFF......................................................... 25 VERTICAL PROCEDURE ......................................................... 25 SHORT FIELD PROCEDURE ................................................... 25 BACK UP PROCEDURE ........................................................... 25 CLEAR AREA PROCEDURE .................................................... 25 CONFINED AREA PROCEDURE ............................................. 26 OFFSHORE HELIDECK PROCEDURE.................................... 26 CATEGORY A LANDING .......................................................... 26 HELIPORT/HELIDECK PROCEDURE...................................... 26 CLEAR AREA PROCEDURE .................................................... 26 CONFINED AREA PROCEDURE ............................................. 26 OFFSHORE HELIDECK PROCEDURE................................... 26a GROSS WEIGHT AND CENTER OF GRAVITY ........................... 26a COLD WEATHER OPERATION ................................................... 26a EXTERNAL PRE-FLIGHT CHECKS.............................................. 27 COCKPIT/ENGINE PRE-START CHECKS ................................... 31 ABORTED ENGINE START PROCEDURES ................................ 35 DRY MOTORING PROCEDURE.................................................... 36 NORMAL ENGINE START............................................................. 37 QUICK ENGINE START................................................................. 39 SYSTEM CHECKS ......................................................................... 41 TAXIING.......................................................................................... 43 UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 19 Lims-Norm-Perf Page 5 AW139-QRH PRE TAKE-OFF CHECKS .............................................................. 43 TAKE-OFF PROCEDURES ............................................................ 44 TAKE-OFF CATEGORY B PROCEDURE ................................. 44 CATEGORY A TAKE-OFF GENERAL........................................45 CATEGORY A TAKE-OFF VERTICAL, SHORT FIELD AND BACK UP PROCEDURE ................................................... 45 CATEGORY A TAKE-OFF CLEAR AREA PROCEDURE ......... 46 CATEGORY A TAKE-OFF CONFINED AREA PROCEDURE ...47 CATEGORY A TAKE-OFF OFFSHORE HELIDECK PROCEDURE ............................................................................48a SLOPING GROUND OPERATION................................................ 48c TAKE OFF PROCEDURE......................................................... 48c IN-FLIGHT PROCEDURES ............................................................ 49 AFTER TAKE-OFF..................................................................... 49 CLIMB CHECKS ........................................................................ 49 CRUISE CHECKS...................................................................... 49 APPROACH AND LANDING.......................................................... 51 PRE-LANDING CHECKS........................................................... 51 LANDING ........................................................................................ 52 CATEGORY B LANDING PROCEDURE................................... 52 CATEGORY A LANDING GENERAL..........................................52 CATEGORY A HELIPORT LANDING PROCEDURE................ 52 CATEGORY A CLEAR AREA LANDING PROCEDURE ........... 53 CATEGORY A CONFINED AREA LANDING PROCEDURE .... 53 CATEGORY A OFFSHORE HELIDECK LANDING PROCEDURE ........................................................................... 54a SLOPING GROUND OPERATION................................................ 54c LANDING PROCEDURE .......................................................... 54c POST LANDING AND SHUTDOWN PROCEDURES .................... 55 POST LANDING CHECKS......................................................... 55 PRE-SHUTDOWN CHECKS...................................................... 55 ENGINES AND ROTOR SHUTDOWN ...................................... 55 POST SHUTDOWN CHECKS ................................................... 56 FLIGHT DIRECTOR COUPLED AND UNCOUPLED OPERATIONS................................................................................ 56a COLLECTIVE PI LIMITING FUNCTION . . . . . . . . . . . . . . . . . 56a SAFETY FLY-UP FUNCTIONALITY WHEN FD MODES ENGAGED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56a SPECIFIC MODE INFORMATION . . . . . . . . . . . . . . . . . . . . . . 56b FMS OPERATION NORMAL PROCEDURES ............................... 57 GENERAL .................................................................................. 57 BASIC OPERATIONS ................................................................ 57 AUTOPILOT COUPLED OPERATIONS WITH FLIGHT DIRECTOR (IF FITTED) ............................................................ 59 UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 6 Rev. 19 AW139-QRH FMS ADVISORY ANNUNCIATORS.......................................... 59 ADVISORY CAPTIONS DEFINITIONS.......................................... 61 PFD MESSAGES ........................................................................... 62 PERFORMANCE DENSITY ALTITUDE CHART ........................................................ 63 PWC\PT6C-67C HOVER POWER CHART 100%NR .................... 64 PWC\PT6C-67C HOVER POWER CHART 102%NR .................... 65 HEIGHT LOSS DURING FLYAWAY MONOEUVRE .................... 66 HOVER CEILING .......................................................................... 67 RATE OF CLIMB AT 6400 kg AEO ............................................... 69 RATE OF CLIMB AT 6400 kg OEI ................................................ 69 FUEL CONSUMPTION AT 6400kg ............................................... 70 HOVER CEILING 6800 kg (if applicable) ..................................... 71 RATE OF CLIMB AT 6800 kg AEO (if applicable)....................... 71 RATE OF CLIMB AT 6800 kg OEI (if applicable) ........................ 71 FUEL CONSUMPTION AT 6800 kg (if applicable) ...................... 72 UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 20 Lims-Norm-Perf Page 7 AW139-QRH LIMITATIONS GENERAL This QRH includes: • Information from RFM Sections 1, 2, 3 and limited data from Section 4. • Optional Supplements included: Heater, Rotor Brake, Flight Director, CATEGORY A, Increased Gross Weight 6800 kg and Take Off and Landing Altitude Extension. TYPES OF OPERATION In the basic configuration the rotorcraft is approved CAT B and CAT A operations for Day/Night VFR and Day/Night IFR operations. CAT A Take Off and Landing can be carried out from the right or left hand seat. MINIMUM FLIGHT CREW See Basic Flight Manual When CAT A Take Off or Landing is carried out from left hand seat or the CAT A Offshore Helideck procedure is required, minimum flight crew is 2 pilots NUMBER OF OCCUPANTS The total number of occupants, including the crew, shall not exceed: — low density configuration 14 — high density configuration 17 — Each occupant must have a seat and seat belt. — The low density or high density configuration may have a reduced number of passenger seats installed in cabin. A minimum of 3 seats, in at least one row, must be installed. — After seat removal or installation the new empty weight and C of G position must be determined to ensure C of G limits are not exceeded. WEIGHT AND CENTER OF GRAVITY LIMITATIONS WEIGHT Minimum flight/rotor running gross weight ...................................... 4400 kg Maximum towing or taxi gross weight .............................................. 6450 kg Maximum gross weight for take-off/landing..................................... 6400 kg CAT B WAT Limitations chart ...................................................... Figure 1-5 CAT A Heliport Vertical, Short Field and Back Up Procedure WAT Limitations chart....................................................................Figure 1-6 CAT A Clear Area WAT Limitations chart ......................................Figure 1-7 CAT A Confined Area WAT Limitations chart ................................Figure 1-8 CAT A Offshore Helideck WAT Limitations chart...........................Figure 1-9 GEN WT/CG UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 8 Rev. 20 AW139-QRH CENTER OF GRAVITY Longitudinal limits ............................................................... See Figure 1-1 Lateral limits ....................................................................... See Figure 1-2 Figure 1-1 Weight and Longitudinal CG Envelope MAST 5.504 5.180 6400 4400 5.071 5.536 4400 5170 5.595 4850 4660 6400 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 4.9 5 5.1 5.2 5.3 5.4 5.5 5.6 5.7 STA [m] Weight [Kg] ICN-39-A-151000-A-A0126-0001-A-06-1 139G1580A006 issue A GEN WT/CG UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 9 AW139-QRH Figure 1-2 Weight and Lateral CG Envelope -0.088 6400 +0.090 -0.070 +0.120 4400 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 6400 -0.12 -0.08 -0.04 0 0.04 0.08 0.12 0.16 BL [m] Weight [kg] 139G0290T044/2 issue A ICN-39-A-151000-A-A0126-0002-A-05-1 GEN WT/CG UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 10 AW139-QRH This Page Left Blank Intentionally UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 3 Lims-Norm-Perf Page 11 AW139-QRH AIRSPEED LIMITATIONS Maximum airspeed with Take-Off Power .......................................... 90 KIAS Maximum airspeed with NR at 102% ............................................... 90 KIAS Maximum airspeed in sideward or rearward flight ........................ Figure 1-5 Maximum allowable tailwind and crosswind ................................. Figure 1-5 Maximum airspeed for landing gear V LO or VLE .........................150 KIAS or Vne if less Minimum airspeed for flight under IFR (Vmini) ................................ 50 KIAS Maximum airspeed for IFR approach ............................................. 150 KIAS Maximum airspeed for climb with one AP failed............................. 100 KIAS Maximum rate of climb with one AP failed...................................... 1000 fpm Maximum airspeed with one AP failed ........................................... 140 KIAS Maximum airspeed for operation of windscreen wipers ................. 140 KIAS Minimum airspeed in autorotation .................................................... 40 KIAS CAT A Take-Off & Balked Landing Safety Speed (V TOSS/VBLSS): Vertical, Short Field and Back Up Procedures............................. 40 KIAS Clear Area Procedure .................................................................. 50 KIAS Best Rate Of Climb speed (V Y) ............................Below 10000ft Hp 80 KIAS Above 10000ft Hp 70 KIAS Maximum airspeed with right cabin door locked open.................... 100 KIAS Maximum airspeed with left or both cabin doors locked open.......... 80 KIAS Maximum airspeed for opening/closing cabin doors ........................ 80 KIAS GROUND SPEED LIMITATIONS ON PAVED SURFACES Maximum taxi speed ....................................................................... 40 knots (above 20 knots nose wheel must be locked fore and aft) Maximum for emergency landing speed (nose wheel locked in fore and aft position) ................................... 60 knots Maximum towing speed .................................................... 37 km/hr(23mph) Maximum GS with PARK BRAKE ON ................................................... 5 kts ON GRASS SURFACES Maximum taxi speed (nose wheel locked fore and aft) .................. 20 knots (above 10 knots nose wheel must be locked fore and aft) Maximum speed for emergency landing (nose wheel locked fore and aft) .................................................... 40 knots SPD ALT TEMP UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 12 Rev. 16 AW139-QRH WIND SPEED LIMITATIONS FOR ROTOR STARTING & STOPPING Maximum wind speed ..................................................................... 50 knots Note Each rotor starting and stopping in wind speeds above 27kts must be recorded in the helicopter log book. ALTITUDE LIMITATIONS Maximum operating altitude ...................................................See Figure 1-3 Minimum operating altitude .................................................. See Figure 1-3 Maximum CAT B Take-Off and Landing altitude.................... See Figure 1-3 Maximum altitude for CAT A Heliport Vertical Take-Off Procedure: TDP 35ft ............................................................................ 14000ft Hp of Hd whichever comes first TDP 36ft to 70ft .................................................................... 7000ft Hp of Hd whichever comes first Maximum altitude for CAT A Short Field, Back Up and Clear Area Take-Off Procedures......................................... 14000ft Hp of Hd whichever comes first Maximum altitude for CAT A Heliport, Short Field or Clear Area Landing Procedures ........................................................... 14000ft Hp or Hd whichever comes first Maximum altitude for CAT A Confined Area Take Off and Landing ....................................................................... 10000ft Hp or Hd whichever comes first Maximum altitude for CAT A Offshore Helideck Take Off and Landing ......................................................................... 5000ft Hp or Hd whichever comes first AMBIENT AIR TEMPERATURE LIMITATIONS (OAT) Minimum temperature for ground starting ............................................ -40°C Maximum and minimum air temperature limitations ...............See Figure 1-3 MANOEUVRING LIMITATIONS Aerobatic manoeuvres are prohibited. ICING LIMITATIONS Flight into known icing conditions or freezing rain is prohibited. AUTOROTATION LIMITATIONS Practice autorotative landings are prohibited. During autorotation the ENG MODE select switch must not be retarded from FLIGHT to IDLE except in an emergency. SPD ALT TEMP UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 16 Lims-Norm-Perf Page 13 AW139-QRH SLOPE LIMITATIONS Sloped Take Off and Landing is limited to the following: Nose up ...................................................................................................... 5° Nose Down ................................................................................................. 5° Left Wing Low............................................................................................. 5° Right Wing Low .......................................................................................... 5° ALTITUDE AND TEMPERATURE LIMITATIONS CHART Figure 1-3 Altitude - Temperature Limitations ALTITUDE-OAT Envelope ICN-39-A-151000-A-A0126-00004-B-01-1 -200 0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 3000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 Pressure Altitude - [m] -50 -40 -30 -20 -10 0 10 20 30 40 50 60 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 17000 18000 19000 20000 OAT - [°C] Pressure Altitude - [ft] MIN OAT LIMIT MAX OAT LIMIT Hd LIMIT 20000 ft Hd LIMIT 20000 ft Hd LIMIT 14000 ft Cat.A ENVELOPE Hd LIMIT 10000 ft Confined Area ENVELOPE Hd LIMIT 5000 ft Off-Shore ENVELOPE SPD ALT TEMP UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 14 AW139-QRH This Page Left Blank Intentionally UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 16 Lims-Norm-Perf Page 15 AW139-QRH HEIGHT- VELOCITY LIMITATIONS The Height-Velocity diagram defines, in the event of a single engine fail- ure during take off, landing or other operation near the surface, a combi- nation of airspeed and height above ground from which a safe single engine landing on a smooth, level and hard surface cannot be assured. CAUTION Prior to the determination of the H-V envelope the CATEGORY B weight should be defined for the ambient conditions. See Flight Planning in Section 2 for use of the CAT B W.A.T. and H-V envelope charts. Height Velocity Diagram ....................................................... See Figure 1-4 CAT A MISCELLANEOUS LIMITATIONS Ground and Elevated Heliport / Helideck Size Minimum demonstrated heliport/helideck size for Vertical, Back Up and Offshore procedures .........................15 m x 15 m (50 ft x 50 ft) Diameter 15 m (50 ft) Minimum demonstrated heliport size for Confined Area procedure ...............................................................20 m x 20 m (65 ft x 65 ft) or Diameter 20 m (65 ft) Wind Limitations Maximum cross wind component must not exceed 20 kts. For the Offshore Helideck procedures for cross wind components between 10 kts and 20 kts a headwind component of at least 5 kts is required. Take Off or Landing with tail wind is prohibited. Heater Limitations Heater must be switched off for Take Off and Landing. H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 16 AW139-QRH HEIGHT - VELOCITY DIAGRAM Figure 1-4 Height Velocity Limitations 139G0040A001 issue E ICN-39-A-151000-A-A0126-00008-A-02-1 0 2000 4000 6000 8000 10000 12000 14000 Pressure altitude - ft OAT LIMIT ISA+35°C -40 -30 -20 -10 0 OAT [°C] 10 20 30 40 4800 5000 5200 5400 5600 5800 6000 6200 6400 NO H-V AREA 0 5 10 15 20 250 50 100 150 200 250 300 350 IAS - kt Height above ground - ft A B C2 C1 GROSS WEIGHT [kg] NO H-V AREA NO H-V A R E A NO H-V A R E A H V (ft) (kts) A 25 0 B 30 20 H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 4 Lims-Norm-Perf Page 17 AW139-QRH CATEGORY B OPERATION LIMITATIONS Figure 1-5 CATEGORY B - Weight Limitations WEIGHT-ALTIT UD E-TEM PERAT URE ROTOR 100 % 139G0040A001 issue G ICN-39-A-151000-A-A0126-00005-A-06-1 0 2000 4000 6000 8000 10000 12000 14000 OAT LIM I T ISA+35°C Pre ssure al titude - ft -40 -30 -20 -10 OAT 0°C 10 20 30 40 50 4500 5000 5500 6000 6500 45 KTAS and BELOW 45 KTAS40 KTAS 35 KTAS 30 KTAS 25 KTAS 20 KTAS and BELOW GW - kg for TA KE-O FF, LAN DING and IGE MANOE UVRES RELATIVE WIND AZIMUT H: 10 to 350 deg NOT E: no winds peed li mitation e xists for head wind conditions (wind a zimuth ±10 deg ) H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 18 AW139-QRH CATEGORY A OPERATION LIMITATIONS Figure 1-6 CATEGORY A Ground and Elevated Heliport/Helideck Vertical, Back Up & Short Field Procedure Weight Limitations WEIGHT-ALTITUDE-TEMPERATURE HELIPORT and SHORT FIELD 9.5 10 10.5 11 11.5 12 12.5 13 13.5 0 0.5 1 1.5 2 2.5 3 3.5 4 Pressure Altitude - [m x 1000] Gross Weight - [lb x 1000] 4.2 4.4 4.6 4.8 5 5.2 5.4 5.6 5.8 6 6.2 6.4 6.6 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Pressure Altitude - [ft x 1000] Gross Weight - [kg x 1000] -40 -30 -20 -10 0 10 20 30 40 50 MAX OAT LIMIT Hd LIMIT ICN-39-A-155000-A-A0126-12204-B-01-1 H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 19 AW139-QRH Figure 1-7 CATEGORY A Clear Area Procedure Weight Limitations WEIGHT-ALTITUDE-TEMPERATURE CLEAR AREA ICN-39-A-155000-A-A0126-12201-B-01-1 9.5 10 10.5 11 11.5 12 12.5 13 13.5 0 0.5 1 1.5 2 2.5 3 3.5 4 Pressure Altitude - [m x 1000] Gross Weight - [lb x 1000] 4.2 4.4 4.6 4.8 5 5.2 5.4 5.6 5.8 6 6.2 6.4 6.6 -1 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Pressure Altitude - [ft x 1000] Gross Weight - [kg x 1000] -40 -30 -20 -10 0 10 20 30 40 MAX OAT LIMIT Hd LIMIT H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 19a Rev. 16 AW139-QRH Figure 1-8 CATEGORY A Ground and Elevated Heliport Confined Area Procedure Weight Limitations WEIGHT-ALTITUDE-TEMPERATURE CONFINED AREA ROTOR SPEED 102% 139G1580A012 issue A ICN-39-A-155000-G-A0126-12248-A-01-1 95 100 105 110 115 120 125 130 135 140 145 0 0.5 1 1.5 2 2.5 3 Gross weight - [lb x 100] Pressure altitude- [m x 1000] 42 44 46 48 50 52 54 56 58 60 62 64 66 0 1 2 3 4 5 6 7 8 9 10 Gross Weight - [kg x 100] Pressure altitude- [ft x 1000] OAT [°C] ________ ISA+35°C --------- -40 -30 -20 -10 0 10 20 30 40 50 MAX OAT LIMIT Hd LIMIT H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 16 Lims-Norm-Perf Page 19b AW139-QRH Figure 1-9 CATEGORY A Offshore Helideck Procedure Weight Limitations WEIGHT-ALTITUDE-TEMPERATURE OFF-SHORE HELIDECK PROCEDURE ROTOR SPEED 102% 139G1580A014 issue A ICN-39-A-155000-G-A0126-12251-A-01-1 13 13.5 14 14.5 15 0 0.5 1 1.5 Gross Weight - [lb x 1000] Pressure Altitude - [m x 1000] 0 1 2 3 4 5 Pressure Altitude - [ft x 1000] -40 -30 -20 -10 0 10 20 30 40 50 MAX OAT LIMIT Hd LIMIT 5.8 6 6.2 6.4 6.6 6.8 7 0 10 20 Gross Weight - [kg x 1000] Headwind component - [kts] Operation in this area is permitted only for aircraft configured for 6800 kg (see Sup.50) H-V CAT A/B UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 20 AW139-QRH This Page Left Blank Intentionally UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 21 Lims-Norm-Perf Page 20a AW139-QRH ENGINE AND TRANSMISSION DIGITAL LIMITATIONS The following represent the digital values for PFD and MFD limitations indicated by colours NR % 90 95 110 116 ITT °C/% 869/118.2 1000/136.0 Power Off Minimum Transient Minimum Continuous Maximum Continuous Maximum Transient Engine Starting Maximum Unlimited Maximum Transient (2 secs) NR % 95 98 101 103 106* 85 90 101 103 106* Nf % 95 98 101 103 106* 85 90 101 103 106* ITT °C/% 735/100.0 775/105.4 847/115.2 775/105.4 835/113.6 847/115.2 Ng % 55.0 100.0 102.4 107.0 102.4 106.0 107.0 PI & TQ % 100 110 121 140 160 176 All Engines Operating Minimum Transient Minimum Continuous Maximum Continuous Maximum Take Off (5 min) Cautionary Maximum Transient (5 secs) One Engine Inoperative Minimum Transient Minimum Continouous Maximum Continuous Maximum 2.5 min OEI Cautionary Maximum Transient (5 secs) ENG FUEL LUB HYD * 10 second transient UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 20b Rev. 19 AW139-QRH HYDOP BAR +180 +225 +250 ESS BUS VOLTAGE 22 29 HYDOT °C -40 -20 +119 +134 MAIN BUS VOLTAGE 22 29 TGBOT °C -40 +1 +110 Minimum Normal Operation Maximum Normal Operation IGBOT °C -40 +1 +110 MGBOP BAR +2.3 +3.1 +6.0 MGBOT °C -40 +1 +110 EOP BAR +4.2 +6.3 +8.9 +10 +15.2 BATTERY LOAD AMPS -200 +200 EOT °C% -40 +10 +140 +145 +150 Minimum for Starting and GI Minimum Normal Operation Maximum Normal Operation Maximum Cautionary TQ < 60% Maximum Cautionary for eng accel OAT<0°C Maximum Cautionary Maximum for Engine Start (5 min) Maximum Transient (1 min) Maximum Battery Discharge Maximum Battery Charge ENG FUEL LUB HYD UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 19 Lims-Norm-Perf Page 21 AW139-QRH ENGINE LIMITATIONS ENGINE STARTER DUTY CYCLE 45 seconds on, 1 minute off. 45 seconds on, 1 minute off 45 seconds on, 30 minutes off POWER MARGIN TREND MONITORING Every 50 flight hours record engine power assurance check values for engine power margin trend monitoring purposes. ENGINE TRAINING MODE LIMITATIONS Selection of Engine Training Mode (OEI TNG) is permitted only for Category A Training in OEI simulated conditions. CAUTION Intentional use of actual OEI rating for training is prohibited. FUEL LIMITATIONS FUEL CAPACITIES Total Usable...................................................................................1588 litres Unusable ..........................................................................................20 litres UNUSABLE FUEL In coordinated (ball centered) flight: ................................. 0kg (0lb) indicated/ (8 kg(18lb)/10 litres per tank actual) Hovering in cross winds or sideways flight with sustained roll angles greater than ±15° is prohibited when fuel indication, in either tank, is less than 70kg. Cross feeding (tank with pump off, not supplying engines) ...................................................................................Maximum 228 kg/500lb Note During XFEED the unusable fuel level indication will change to grey to indicate the tank can no longer supply fuel. AUTHORIZED FUEL TYPES The fuels shown in the table below have been authorized for use with the Pratt and Whitney PT6C-67C engines: Fuel Type Applicable Specification Fuel Type Applicable Specification JET A JET A-1 JP5 JP8 ASTM D1655 ASTM D1655 DEF STAN 91-86 AVCAT/FSII MIL -PRF-5624F NATO Code F-44 DEF STAN 91-87-2002 JP8 JP8+100 GOST 10227RT GOST 10227TS1 AVTUR/FSII MIL -T-83138D NATO Code F-34 Aeroshell Performance Additive 101 GOST 10227-86 GOST 10227-86 (See RFM restrictions) ENG FUEL LUB HYD UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 22 Rev. 13 AW139-QRH LUBRICANT LIMITATIONS AUTHORIZED ENGINE OILS The oils shown in the table below have been authorized for use with the Pratt and Whitney PT6C-67C engines. Any brand approved under the applicable specification may be used. CAUTION Mixing of any oils, by type, specification or brand name, is prohibited. AUTHORIZED TRANSMISSION OIL ELECTRICAL HYDRAULIC PUMP The electrical hydraulic pump is for ground operation only. AUTHORIZED HYDRAULIC FLUIDS The hydraulic fluids shown in the table below have been authorized for use in all hydraulic components. Any brand approved under the applica- ble specifications may be used. Note MIL-PRF-5606 can be used for enhanced performance of hydraulic system in low temperature environments below -30°C. CAUTION Mixing of hydraulic liquid, by specification or brand name, is prohibited. Oil Type Applicable Specification Brand Names (For reference only) Type I (3cs) PWC 521 BP Turbo Oil 2389 Mobil Avrex S Turbo 256 Type II (5cs) PWC 521 Aero-Shell Turbine Oil 500 Castrol 5000 Mobil Jet Oil II Royco Turbine Oil 500 BP Turbo Oil 2380 Turbonycoil 525-2A Third Generation (5 cs) PWC 521 Aero Shell Turbine Oil 560 Royco Turbine Oil 560 Mobil Jet Oil 254 Applicable Specification Brand Names MIL PRF23699F BP Turbo Oil 2380 Applicable Specification Brand Names (For reference only) MIL-PRF-83282 AEROSHELL FLUID 31 Alternative: MIL-PRF-5606 (see NOTE below) AEROSHELL FLUID 41 ENG FUEL LUB HYD UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 21 Lims-Norm-Perf Page 23 AW139-QRH MISCELLANEOUS LIMITATIONS DC GENERATOR LOAD Normal Operation Range............................................................... 0 to 100% Cautionary Range (for engine starting only).............................. 101 to 155% Maximum Cautionary ........................................................................... 155% (Maximum cautionary may be exceeded for maximum of 45 seconds for engine start only) Max normal operating load up to 15000ft Hp .......... 100% (equivalent 300A) Max normal operating load above 15000ft Hp.................... reduce by 13.4% ....................................................................................................every 1000ft (See placard on RFM page 1-62 or, for aircraft fitted with EPIC S/W Phase 5 or later, Supplement 68) Max normal operating load 20000ft Hp .................................................. 33% MPOG with generator load at 75% or less ....................... No time limitations MPOG with generator load greater than 75% ...................... Max 20 minutes WHEEL BRAKE LIMITATIONS Maximum running speed for brake application.................................40 knots Parking on slopes up to 10° is permitted for a maximum of 1 hour. PITOT HEATING LIMITATIONS Pitot heating must be switched ON for conditions of visible moisture at indicated OAT of +4° C or less. Pitot heating must be switched OFF at indicated OAT of +10° C or more. AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS Minimum AFCS configuration for VFR flight.....................2 AP in SAS mode Minimum AFCS configuration for IFR flight ...................... 2 AP in ATT mode Intentional ATT MODE de-selection during IFR flight is prohibited. AVIONIC LIMITATIONS ILS Mode Limitations Maximum airspeed for glideslope up to 4 degrees........................ 150 KIAS Maximum airspeed for glideslopes between 4 and 7.5 degrees (Steep Approach) ............................................... 120 KIAS CAUTION During steep approach, take care not to use less than 5% PI MISC UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 24 Rev. 21 AW139-QRH FLIGHT DIRECTOR LIMITATIONS 4 Axis Basic and Enhanced FD system • Basic FD system only: HOV mode not operative • SAR Guidance Controller, TD/H, MOT, WTR, modes only operative for Enhanced FD with EPIC Software Phase 5, or later, SAR modes operative. • VNAV mode inoperative. • Collective modes must not be engaged if either or both engines are in MANUAL MODE • The RHT, TD, TDH, TU, MOT, WTR modes can only be engaged over flat surfaces which are clear of obstacles (EPIC Software Phase 5 or later) • The RHT must not be engaged in cruise over land (EPIC Software Phase 4 only) FLIGHT DIRECTOR MODES ENGAGEMENT LIMITS AND MINIMUM USE HEIGHT (MUH) Hold Mode Applicable Range MUH IAS* 60 KIAS to Vne less 5 KIAS 150 ft AGL or 50 ft AGL during approach HDG*/NAV* 60 KIAS to Vne 150 ft AGL or 50 ft AGL during approach APP*/BC*/GA* 60 KIAS to Vne 50 ft AGL VS* 60 KIAS to Vne within -1500 fpm and 2000 fpm 150 ft AGL ALT 0 KIAS to Vne 300 ft AGL (airspeed greater than 55 KIAS 50ft AGL in HOV or airspeed less than 55 KIAS (Enhanced FD system only) DCL* 60 KIAS to Vne 50 ft AGL ALTA* 60 KIAS to Vne 150 ft AGL RHT 0 to Vne 15 ft to 2000 ft AGL 150 ft AGL (airspeed greater than 55 KIAS) 30 ft AGL in HOV or air- speed less than 55 KIAS) GA 60 KIAS to Vne 0 to 2000 ft AGL N/A HOV Enhanced FD systems only Groundspeed — less than 60 kts forward — less than 40 kts lateral or aft with IAS less than 75 KIAS 30 ft AGL TU Enhanced FD Phase 5, or later 0 KIAS to 60 KIAS 0 to 2000 ft AGL 150 ft AGL (airspeed greater than 55KIAS) 30 ft AGL in HOV (air- speed less than 55 KIAS) MISC UNMAINTAINED COPY FOR INFORMATION ONLY Rev. 21 Lims-Norm-Perf Page 24a AW139-QRH For operations on the sea the MUH must be increased by one half the maxi- mum reported/observed wave height. Note* — Automatic disengagement of these modes below 55 KIAS. — VS engagement above 2000 fpm or below -1500 fpm will result in the mode returning the aircraft to the maximum rates quoted (2000 fpm or -1500 fpm). SAR Limitations Flight below 50 KIAS (Vmini) in IMC is only permitted when coupled to a SAR mode. FD VOR Limitations In case of invalid DME/FMS distance, select: - VOR APP at ranges below 10 nm - VOR NAV at ranges greater than 10 nm VGP Limitations When being radar vectored or autonomously flying to the final approach course, the VECTORS approach transition and/or ACT VECTORS function must be used to program the FMS for the approach and the flight crew must ensure that published altitudes are complied with. FD ILS APPROACH MODE LIMITATION The helicopter is certified to carry out CAT 1 ILS approaches up to 7.5 deg glideslope. Maximum recommended Localizer Intercept angle................................. 45° ................................................................................................ ranges greater ...................................................................................................... than 10nm Maximum recommended Localizer Intercept angle................................. 30° ......................................................................................................ranges less ....................................................................................................... than 10nm In case of invalid DME and FMS distance and with both Rad Alt signals invalid an ILS approach must be initiate at a distance of not less than 10 nm. The following modes only available with Enhanced FD Phase 5, or later, and SAR modes installed TD 60 KIAS to Vne 135 ft to 2000 ft AGL 150 ft AGL TDH 0 KIAS to 90 KIAS 50 ft to 300 ft AGL 50 ft AGL MOT 0 KIAS to Vne 50 ft to 2000 ft AGL PTH - 50 ft AGL VPTH - 250 ft AGL VRHT - 150 ft AGL DCL - 50 ft AGL WTR HOV Mode engaged 30 ft AGL FLIGHT DIRECTOR MODES ENGAGEMENT LIMITS AND MINIMUM USE HEIGHT (MUH) MISC UNMAINTAINED COPY FOR INFORMATION ONLY Lims-Norm-Perf Page 24b Rev. 15 AW139-QRH FMS AND GPS LIMITATIONS 1. The software status stated in the Honeywell Flight Management System (FMS) Pilot’s Manual for the Agusta AW139 must match that displayed on the equipment MCDU page at power up. 2. IFR en route and terminal navigation is prohibited unless the pilot verifies the currency of the Navigation Data Base (NDB) or verifies each selected waypoint for accuracy by reference to current approved data. 3. Instrument approaches must be carried out in accordance with approved instrument approach procedures that are retrieved from the FMS data base. The FMS data base must incorporate the current update cycle. — For instrument approaches GPS integrity monitoring (RAIM) must be available at the Final Approach Fix. Note The Pilot must not continue an instrument approach inside the Final Approach Fix (FAF), unless the ‘APP’ advisory is displayed on the PFD. If during an instrument approach the amber ‘DGR’ advisory in displayed, the pilot must initiate a missed approach. — Use of ILS, LOC, LOC-BC, LDA, (landing directional aid), SDF(simplified directional facility) and MLS (microwave landing system) approaches are not authorized. — When an alternate airport is required by the applicable operat- ing rules, it must be served by an approach based on other than GPS navigation and the aircraft must have operational equip- ment capable of using that navigation aid, and the required nav- igation aid must be operational. 4. The aircraft must have other approved navigation equipment installed and operating appropriate to the route of flight. TORQUE LIMITER FUNCTION If TORQUE LIMITER is set, max AEO TQ available is 114%/114% ENGINE EEC LIMITATIONS In ambient conditions above 43°C, if the aircraft is to be parked with engine off, internal or external electrical power must not be supplied. Electrical power may be supplied for Pre Start Checks and Engine Start. For maintenance checks refer to AW139 Maintenance Publication Docu- ment No. 39-A-AMP-00-P. SYNOPTIC MFD PAGE LIMITATIONS In case of MAU1(2) failure, do not refer to the electrical and hydraulic synop- tic page. The information presented is not reliable. HEADSET/HELMET LIMITATIONS Headset/Helmet type used in the aircraft must be of the same electrical char- acteristics and authorised by Aircraft Manufacturer. MISC