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ATR Limitations | Global Positioning System | Navigation
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2.01.00 001 NOV 99
2.01.00 2.01.01 2.01.02 2.01.03 2.01.04 2.01.05 2.01.06 2.01.07 R 2.01.08
CONTENTS GENERAL WEIGHT AND LOADING AIRSPEED AND OPERATIONAL PARAMETERS POWER PLANT SYSTEMS TCAS GPS CABIN LIGHTING
LIMITATIONS P2 GENERAL
2.01.01 001 NOV 99
MANEUVERING LIMIT LOAD FACTORS FLAPS RETRACTED = + 2.5 TO - 1 G FLAPS EXTENDED = + 2 TO 0 G GEAR DOWN = + 2 TO 0 G The corresponding positive accelerations limit the bank angle in turns and the severity of pull up maneuvers. CARGO DOOR OPERATION Do not operate cargo door with a cross wind component of more than 45 kt. DISPATCHIBILITY For dispatch in the event of equipment failure or missing equipment refer to MEL/CDL. MAXIMUM NUMBER OF PASSENGER SEATS R R R 60
LIMITATIONS P1 WEIGHT AND LOADING
2.01.02 001 NOV 98
DESIGN WEIGHT LIMITATIONS MAXIMUM WEIGHT RAMP TAKE-OFF LANDING ZERO FUEL CENTER OF GRAVITY ENVELOPE The limits of the center of gravity are given in percentage of the mean aerodynamic chord (MAC), landing gear extended. R The MAC is 2.285 meters long (89.961 in). R Station 0 is located 2.362 meters (92.992 in) forward of the fuselage nose. R The distance from station 0 to reference chord leading edge is 11.425 meters (449.803 in). KG 18770 18600 18300 16700 LB 41380 41005 40344 36817
CARGO COMPARTMENT LOADING LIMITATIONS See W.B.M. : 1.10.04 p 1
2.01.02 050 NOV 99
DESIGN WEIGHT LIMITATIONS MAXIMUM WEIGHT RAMP TAKE-OFF LANDING ZERO FUEL CENTER OF GRAVITY ENVELOPE The limits of the center of gravity are given in percentage of the mean aerodynamic chord (MAC), landing gear extended. The MAC is 2.285 meters long (89.961 in.). Station 0 located 2.362 meters (92.992 in.) forward of the fuselage nose. The distance from station 0 to reference chord leading edge is 11.425 meters (449.803 in.). KG 18770 18600 18300 16700 LB 41380 41005 40344 36817
R Mod : 5150
: 1. Station 0 located 2.) forward of the fuselage nose.10.961 in.M. landing gear extended. KG 18770 18600 18300 17000 LB 41380 41005 40344 37478
CARGO COMPARTMENT LOADING LIMITATIONS See W.).01.02 150 NOV 00
DESIGN WEIGHT LIMITATIONS MAXIMUM WEIGHT RAMP TAKE-OFF LANDING ZERO FUEL CENTER OF GRAVITY ENVELOPE The limits of the center of gravity are given in percentage of the mean aerodynamic chord (MAC).LIMITATIONS P1 WEIGHT AND LOADING
2. The distance from station 0 to reference chord leading edge is 11.B. The MAC is 2.362 meters (92.).425 meters (449.992 in.04 p 1
Mod : 5150 + 5175
.803 in.285 meters long (89.
04 p 1
ATR 42 Model : 400
. KG 18070 17900 17600 16300 LB 39837 39462 38801 35935
CARGO COMPARTMENT LOADING LIMITATIONS See W.B.961 in).M. R The distance from station 0 to reference chord leading edge is 11.01.10. R Station 0 is located 2. R The MAC is 2.425 meters (449.02 400 NOV 98
DESIGN WEIGHT LIMITATIONS MAXIMUM WEIGHT RAMP TAKE-OFF LANDING ZERO FUEL CENTER OF GRAVITY ENVELOPE The limits of the center of gravity are given in percentage of the mean aerodynamic chord (MAC).285 meters long (89.992 in) forward of the fuselage nose.362 meters (92. : 1.LIMITATIONS P1 WEIGHT AND LOADING
2. landing gear extended.803 in).
5 KT FOR TAKE-OFF BLEED ON R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R R
80 –40 –30 –20 0 10 20 30 40 50
OUTSIDE AIR TEMPERATURE (DG.03 001 NOV 98
V1 limited by VMCG (FLAPS 15) R CAUTION : INCREASE BY 1. : PW127E
Eng.LIMITATIONS P3
AIRSPEED AND OPERATIONAL PARAMETERS
MAXIMUM MEAN RUNWAY SLOPE : ± 2 %
.01.03 001 MAY 98
OPERATIONAL PARAMETERS ENVIRONMENTAL ENVELOPE
TAKE-OFF AND LANDING R TAIL WIND LIMIT : 15 KT The maximum demonstrated cross wind on dry runway is 30 KT.LIMITATIONS P5
04 001 NOV 01
ENGINES ENGINE PARAMETERS Operating limits with no unscheduled maintenance action required. refer to maintenance manual. 2) Oil temperature must be maintained above 45° C to ensure protection for the engine air inlet against ice accumulation.2
NP (%) 101 101 101
OIL PRESS (PSI) 55 to 65 55 to 65 55 to 65 40 mini
OIL TEMP (°C) (2) 0 to 125 0 to 125 0 to 125 .40 to 125 125
5 mn NONE
55 to 65 40 to 100
1) Value linked to 100 % NP.4 104. 3) Permissible for completion of flight provided TQ does not exceed 85 % during climb and 84 % during cruise.54 mini TIME LIMIT 10 mn
TQ (%) 100 (1) 90 (1) 100 (1)
ITT (°C) 800
NH (%) 103.2 66 mini
NL (%) 104. 7) A qualified person is required to use engine 2 in HOTEL mode.LIMITATIONS P1 POWER PLANT
2.01. : PW127E
.3 106.2 101.01.04 p 3.5 106 (3) 120 140 . 4) Up to 75 % NH only.9 103.2 101. 5) ITT limits depend on outside air temperature.
OPERATING CONDITION RESERVE TAKE OFF NORMAL TAKE OFF MAXIMUM CONTINUOUS GROUND IDLE HOTEL (7) MODE TRANSIENT 20 s 5s 20 mn STARTING 5s 950 137.5 715 840 104. Refer to 2. R 6) Time beyond 5 mn is linked to actual single engine operations only.
Eng. Beyond these limits.
Note : Flight with an engine running and the propeller feathered is not permitted.
01.04 001 MAY 98
Eng. : PW127E
.LIMITATIONS P2 POWER PLANT
Beyond these limits. 2) Oil temperature must be maintained above 45° C to ensure protection for the engine air inlet against ice accumulation.
Eng. 6) The flight can be completed with the indicated NP speed.40 mini TIME LIMIT 10 mn (4) 5 mn NONE (4) TQ (%) 100 (1) 90 (1) 86.0 102. refer to maintenance manual. TQ must not exceed 64 %.40 to 115 120
1) Value linked to 100 % NP.1 110 120 110 (6) 130 (5) .2 102.4 (1) ITT (°C) 816 791 800 NH (%) 103.4 785 850 104.04 400 NOV 01
ENGINES ENGINE PARAMETERS Operating limits with no unscheduled maintenance action required. 5) 20 mn max.01. 3) Below FI only.6 62 mini NP (%) 101 101 101 OIL PRESS (PSI) 55 to 65 55 to 65 55 to 65 40 mini
OIL TEMP (°C) (2) 0 to 115 0 to 115 0 to 115 . : PW121A
OPERATING CONDITION RESERVE TAKE OFF NORMAL TAKE OFF MAXIMUM CONTINUOUS GROUND IDLE HOTEL (7) MODE TRANSIENT OTHER STARTING 5s 950 20 s 5s 132. Note : Flight with an engine running and the propeller feathered is not permitted. R 4) Time beyond 5 mn is linked to actual single engine operations only.LIMITATIONS P1 POWER PLANT
2. 7) A qualified person is required to use engine 2 in HOTEL mode.
LIMITATIONS P2 POWER PLANT
2.01.04 400 MAY 98
Eng. : PW121A
01.000 ft
HYDRAULIC SYSTEM SPECIFICATION : HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING (SHARP TURNS) ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY MFC R TAKE OFF WITH MORE THAN ONE FAILED MFC MODULE IS PROHIBITED.35 PSI .5 PSI 0. flight level must be limited to FL 200 MAX LOAD 400 A 600 A 800 A 500 VA 575 VA 750 VA 20 KVA 30 KVA 40 KVA 60A 90A TIME LIMIT NONE 2 mn 8s NONE 30 mn 5 mn NONE 5 mn 5s NONE 5 mn 6.05 001 NOV 97
AIR .35 PSI 1 PSI 20.
.LIMITATIONS P1 SYSTEMS
2.0.PRESSURIZATION MAXIMUM DIFFERENTIAL PRESSURE R MAXIMUM NEGATIVE DIFFERENTIAL PRESSURE MAXIMUM DIFFERENTIAL PRESSURE FOR LANDING MAXIMUM DIFFERENTIAL PRESSURE FOR OVBD VALVE FULL OPEN SELECTION MAXIMUM ALTITUDE FOR ONE BLEED OFF OPERATION ELECTRICAL SYSTEM SOURCE DC GEN INV ACW GEN TRU SINGLE DC GEN OPERATION In flight : if OAT exceeds ISA + 25.
Provision is made to cover : .01. Note : .000 ft to 13.LIMITATIONS P2 SYSTEMS
2. the system protects the flight crew members during 15 min. R In case of smoke emission. R A 25 % pax oxygen consumption is assumed.000 ft. in flight R Minimum bottle pressure required to cover a cabin depressurization at mid-time of the R flight.000 ft within less than 4 minutes and a R flight continuation at an altitude below 13. on ground = Cabin Temperature.Ref.unusuable quantity .05 001 NOV 00
Reference Temperature = Cabin Temperature or OAT whichever is higher.normal system leakage . an emergency descent from 25. Temp errors
.At dispatch the computed flight time after decompression should be at least 1/2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher.
.PRESSURIZATION MAXIMUM DIFFERENTIAL PRESSURE R MAXIMUM NEGATIVE DIFFERENTIAL PRESSURE MAXIMUM DIFFERENTIAL PRESSURE FOR LANDING MAXIMUM DIFFERENTIAL PRESSURE FOR OVBD VALVE FULL OPEN SELECTION MAXIMUM ALTITUDE FOR ONE BLEED OFF OPERATION ELECTRICAL SYSTEM SOURCE DC GEN INV ACW GEN TRU SINGLE DC GEN OPERATION In flight : if OAT exceeds ISA + 25.35 PSI .LIMITATIONS P1 SYSTEMS
2. flight level must be limited to FL 200 MAX LOAD 400 A 600 A 800 A 500 VA 575 VA 750 VA 20 KVA 30 KVA 40 KVA 60A 90A TIME LIMIT NONE 2 mn 8s NONE 30 mn 5 mn NONE 5 mn 5s NONE 5 mn 6.01.0.05 001 NOV 97
AIR .35 PSI 1 PSI 20.5 PSI 0.000 ft
HYDRAULIC SYSTEM SPECIFICATION : HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING (SHARP TURNS) ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY MFC R TAKE OFF WITH MORE THAN ONE FAILED MFC MODULE IS PROHIBITED.
HOLDING ALTITUDE AVAILABLE TIME AFTER DECOMPRESSION
MIN BOTTLE PRESS INDICATION (PSI)
TOFA–02–01–05–002–A100AA
MINIMUM BOTTLE PRESS (STANDARD CONDITION 21°C) (PSI)
This graph gives the minimum bottle pressure required after loss of cabin pressure to provide crew members and 100 % of passengers protection with diluted oxygen during descent from FL 250 to holding level followed by descent to FL100 (rate 3000 ft/minutes). Provision is made to cover : .normal system leakage .Ref. = Cabin Temperature. in flight.
Note : . Reference Temperature = Cabin Temperature or OAT whichever is higher. on ground. : 4292
.unusuable quantity .LIMITATIONS P2 SYSTEMS
2.At dispatch the computed flight time after decompression should be at least 1/2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher.05 100 NOV 97
OXYGEN Minimum flight crew oxygen pressure with and without observer and capacity with full pax (50 cabin occupants).01.
.01.35 PSI . MAX LOAD 400 A 600 A 800 A 500 VA 575 VA 750 VA 20 KVA 30 KVA 40 KVA 60A 90A TIME LIMIT NONE 2 mn 8s NONE 30 mn 5 mn NONE 5 mn 5s NONE 5 mn 6.LIMITATIONS P1 SYSTEMS
2.35 PSI 1 PSI 20.PRESSURIZATION MAXIMUM DIFFERENTIAL PRESSURE R MAXIMUM NEGATIVE DIFFERENTIAL PRESSURE MAXIMUM DIFFERENTIAL PRESSURE FOR LANDING MAXIMUM DIFFERENTIAL PRESSURE FOR OVBD VALVE FULL OPEN SELECTION MAXIMUM ALTITUDE FOR ONE BLEED OFF OPERATION ELECTRICAL SYSTEM SOURCE DC GEN INV ACW GEN TRU HYDRAULIC SYSTEM SPECIFICATION : HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING (SHARP TURNS) ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY MFC R TAKE OFF WITH MORE THAN ONE FAILED MFC MODULE IS PROHIBITED.5 PSI 0.05 400 NOV 97
R In case of smoke emission. the system protects the flight crew members during 15 min.LIMITATIONS P2 SYSTEMS
2. R A 25 % pax oxygen consumption is assumed.Ref. Note : .normal system leakage .000 ft within less than 4 minutes and a R flight continuation at an altitude below 13.At dispatch the computed flight time after decompression should be at least 1/2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher. in flight R Minimum bottle pressure required to cover a cabin depressurization at mid-time of the R flight.05 001 NOV 00
Reference Temperature = Cabin Temperature or OAT whichever is higher.01. on ground = Cabin Temperature.000 ft to 13.000 ft. Provision is made to cover : . Temp errors
.unusuable quantity . an emergency descent from 25.
LIMITATIONS P1 TCAS
2.01.06 001 NOV 98
.A. and limited to the minimum required to comply with the RA. The pilot must not initiate evasive maneuvers using information from the traffic display only or from a traffic advisory (TCAS TA) only. CAUTION : Once a non crossing RA has been issued the vertical speed should be accurately adjusted to comply with the RA. ATC guidance.06 050 NOV 01
TCAS LIMITATIONS The limitations in Part 2. 4Evasive maneuvring should be made with the autopilot disengaged. WARNING : Non compliance with a crossing RA by one airplane may result in reduced vertical separation.01 are applicable with the addition of the following: 12TCAS operation is approved for use in VFR meteorological conditions (VMC) and IFR meteorological conditions (IMC). These displays and advisories are intended only for assistance in visually locating the traffic and lack the resolution necessary for use in evasive maneuvering. Prior to perform RA's climb or increase climb. the crew should select the appropriate engine power setting on the power MGT rotary selector and. definitive visual acquisition. without visually sighting the traffic. etc) about the aircraft causing the R. The pilot must promptly return to the previous ATC clearance when the TCAS CLEAR OF CONFLICT" voice message is announced. Compliance with TCAS resolution advisory is required unless the pilot considers it unsafe to do so or unless the flight crew has better information (e. in order to avoid negating the effectiveness of a co-ordinated maneuvre by the intruder. a normal procedure of go-around should be followed including the appropriate power increase and configuration changes.g.01. if necessary. maneuvers which are in the opposite direction of the resolution advisory (TCAS RA) are extremely hazardous and are prohibited unless it is visually determined they are the only means to assure safe separation. and can maintain safe operation. safe horizontal separation must also be assured by visual means.LIMITATIONS P1 TCAS
2. When a climb or increase climb RA occurs with the airplane in the landing configuration or in the go-around phase. manually adjust CLs. However. Therefore.
ATC constraints). has the primary responsibility for avoiding mid-air collisions. TCAS may command maneuvers which may significantly reduce stall margins or result in stall warning. altitude and temperature combinations outside those noted below. with the aid of the ATC system.g. and abnormal configurations such as landing gear not retracted or stick pusher/shaker failure. In all cases. leaving aircraft in landing configuration during climb RA on approach. engine out operations. In these cases. stall warning must be given precedence over climb RA commands. weight. obstacle clearance.01.
.06 050 NOV 01
TCAS (cont'd) 7Because of the limited number of inputs to TCAS for determination of aircraft performance inhibits. however it is not possible to do so.
WARNING : Priority must be granted to increasing airspeed when reaching stall warning even when this requires deviation from an RA command issued by the TCAS. there are instances where inhibiting RAs would be appropriate.LIMITATIONS P2 TCAS
2. This table does not consider worst turboprop flight conditions especially operations using minimum operating airspeeds as are sometimes required (e. NOTE : TCAS is viewed as a supplement to the pilot who. The table below entitled Flight Envelope in which climb resolution advisory can be accomplished without stick pusher/shaker activation" outlines the parameters used in the development of the performance inhibits. Conditions where this may occur include operations with a bank angle (wings level is assumed).
13 VSR if defined or buffet onset
Temperature range up to ISA + 27° .13 VSR
Landing Transitioning to go around at RA Enroute
Transition from 30 to 15 Up
DN to Up Up
VAPP +10
1.06 050 NOV 01
TCAS (cont'd)
FLIGHT ENVELOPPE IN WHICH CLIMB RESOLUTION ADVISORY CAN BE ACHIEVED WITHOUT STICK PUSHER / SHAKER ACTIVATION FLIGHT REGIME
WEIGHT ALTITUDE TEMP.
1.51 VSR
1.Enroute Altitude range .LIMITATIONS P3 TCAS
2.Approach and landing Wings Level Assumed 0 0 0 25000 ft 6000 ft 7000 ft
.13 VSR
Spin up to go around power during maneuver from power for level flight Spin up to go around power during maneuver from power required for 3° Glide Slope Power for level flight increase to Max Continuous
1.Take off .01.
FAR25/JAR 25 Climb limit FAR25/JAR 25 Climb limit FAR25/JAR 25 Climb limit Critical Wt/ Alt giving 1.3G to buffet onset
AIRSPEED INITIAL
V2 + 20
MIN.13 VSR
Higher of 1.
Maneuvers based solely on information displayed on the traffic display are not authorized.06 050 NOV 01
TCAS (cont'd) 8Inhibition schemes 8.1.LIMITATIONS P4 TCAS
.Non icing conditions
CONFIGURATION FLAPS 0 FLAPS 15 TO FLAPS 25 TO FLAPS 15 Approach FLAPS 25 Approach FLAPS 25 Landing FLAPS 35 Landing RA CLIMB AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED RA INCREASE CLIMB AUTHORIZED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED
8.Icing conditions
NOTE 1 : NOTE 2 :
Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with a TCAS resolution advisory.
PROCEDURES FOLLOWING FAILURES The procedures following failures in Part 2. EMERGENCY PROCEDURES The emergency procedures in Part 2.06 050 NOV 01
TCAS (cont'd) NORMAL PROCEDURES The normal procedures in Part 2.LIMITATIONS P5 TCAS
.01.03 are applicable.05 are applicable with the addition of the following: The TCAS must be turned TA ONLY in the following cases: -Engine out operations -Stick pusher/shaker failure -Flight with landing gear down The TCAS must be turned STBY in the following cases: -ATC request -ADC 1 failure -LOSS OF RADIO ALTIMETER INFORMATION -Errors or differences between independant air data sources PERFORMANCES The performances in Part 3 are applicable.04 are applicable.
Mod : (3832 or 8259) + 5205
. EMERGENCY PROCEDURES The emergency procedures in Part 2.05 are applicable with the addition of the following: The TCAS must be turned TA ONLY in the following cases: -Engine out operations -Stick pusher/shaker failure -Flight with landing gear down The TCAS must be turned STBY in the following cases: -ATC request -LOSS OF RADIO ALTIMETER INFORMATION -Errors or differences between independant air data sources PERFORMANCES The performances in Part 3 are applicable.LIMITATIONS P5 TCAS
2.03 are applicable.04 are applicable. PROCEDURES FOLLOWING FAILURES The procedures following failures in Part 2.06 080 NOV 01
TCAS (cont'd) NORMAL PROCEDURES The normal procedures in Part 2.
LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2.01.07 P1 001 NOV 98
Data base updating must be verified before each flight. navigation must be crosschecked with usual means.07 P1 050 NOV 99
GPS GPS Bendix/King KLN 90A is installed in accordance with FAA AC 20-138 dated May 94. R en route and terminal area up to the Initial Approach Fix (IAF). R This equipment is approved for use as a VFR and IFR supplemental navigation means.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2. R The system must not be used for approaches.01.
Mod : 3952
. beyond IAF. No specific monitoring is required as long as the RAIM warning is OFF. If RAIM warning appears.
07 P1 090 NOV 99
Mod : 4597
.01.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
GENERAL . en route and in terminal area up to the Initial Approach Fix (IAF).The system must be used with an updated active data base and the waypoints position should be cross-checked with official charts. 2 . This statement does not constitute an operational approval.The system must not be used for approaches.01.This equipment is approved for use as a VFR and IFR supplemental navigation means.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2.07 P1 100 NOV 99
GPS 1 . . beyond IAF.The HT 1000 GNSS pilot's guide must be available on board.LIMITATIONS .This system may be used as a primary means of navigation for oceanic/remote area where only one navigation system is required. : 4654
. R . Such an authorization must be obtained by the operator from the appropriate authorities.Honeywell/Trimble GNSS 1000 is installed in compliance with FAA AC 20-138 dated May 94 and DGAC-CRI n° S-01 requirements. R R R . .
Mod.The system must operate with HT 1000-010 software version or any later approved version. .
Aircraft R operators must apply to their Authority for such an approval/ R authorization.If the RAIM function is lost.The CDI scale factor selectable in the MOD pages must not be set at the  0. .The system must not be used for approaches.07 P1 150 NOV 99
GPS R 1 . the flight crew must cross-check the aircraft position using conventional means or must revert to an alternative means of navigation. beyond IAF. R R R R R R R R R R . Dispatch must not be made in the event of predicted continuous loss of RAIM of more than 5 minutes for any part of the intended flight.complies with TSO C 129. and FAA AC 20-138 for European B-RNAV operations. (b) Traditional navigation equipment must be selected to available aids so as to allow immediate cross-checking or reversion in the event of loss of GPS navigation capability. .PROCEDURES R R R R R R R R R R R .
Mod.LIMITATIONS R Compliance with the above regulations does not constitute an R operational approval/authorization to conduct operations. : 4890
. the availability of GPS integrity (RAIM) must be confirmed for the intended flight (route and time).is installed in compliance with FAA AC 20-138 .
R 3 .01.3 NM full scale deflection value. en route and in terminal area up to the Initial Approach Fix (IAF). . using the flight director in manual mode or the autopilot.GENERAL R The GPS Bendix/King KLN90B/BRNAV : R R R R .has been demonstrated to meet the requirements of JAA TGL n° 2. .The flight must be conducted in L-NAV mode.The system must be used with an updated active data base and the waypoints position must be cross-checked with official charts. .LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
R 2 .This equipment is approved for use as a VFR and IFR supplemental navigation means. . REV1.The following procedures apply for B-RNAV operations: (a) during the pre-flight planning phase.
In the event of DGR alarm illumination the flight crew must cross-check the aircraft position using conventional means or must revert to an alternative means of navigation.complies with TSO C 129 and TSO C 115A.In addition.PROCEDURES R R R R R R R R R R R R R .
R 2 . the availability of GPS integrity (RAIM) must be confirmed for the intended flight (route and time).This equipment is approved for use as a VFR and IFR supplemental navigation means.The system must not be used for approaches.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2.01. . REV1 and FAA AC 20-138 for European B-RNAV operations and FAA Notice N8110-60 for oceanic and remote operations where only one long range navigation system is required. . the following procedures apply for B-RNAV operations : (a) during the pre-flight planning phase. en route and in terminal area up to the Initial Approach Fix (IAF). Dispatch must not be made in the event of predicted continuous loss of RAIM of more than 5 minutes for any part of the intended flight. beyond IAF. .The system must be used with an updated active data base and the waypoints position must be cross-checked with official charts. : (4654 + 4885) or 5020
. (b) Traditional navigation equipment must be selected to available aids so as to allow immediate cross-checking or reversion in the event of loss of GPS navigation capability.LIMITATIONS R Compliance with the above regulations does not constitute an R operational approval/authorization to conduct operations. . .07 P1 250 NOV 99
GPS R 1 . Aircraft R operators must apply to their Authority for such an approval/ R authorization.
R 3 .has been demonstrated to meet the requirements of JAA TGL n° 2. .
R Mod.is installed in compliance with FAA AC 20-138 and DGAC CRI S-01.GENERAL R The Honeywell/Trimble GNSS 1000 : R R R R R R . . R R R R R R R R R .The system must operate with HT 1000-05H software version or any later approved version. where the coupled DME option is not installed or if the coupled DME is not operative.The HT 1000 pilot's guide must be available on board.
: 5176 ATR 42 Model : 400/500
. .LIMITATIONS Compliance with the above regulations does not constitute an operational approval/authorization to conduct operations. . the availability of GPS integrity (RAIM) must be confirmed for the intended flight (route and time). . where the coupled DME option is not installed or if the coupled DME is not operative.is installed in compliance with FAA AC 20-129. Aircraft operators must apply to their Authority for such an approval authorization. NOTE : VDEV function must be permanently monitored.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2. . AC 20-130A. .
Mod. Dispatch must not be made in the event of predicted continuous loss of RAIM of more than 5 minutes for any part of the intended flight. .In the event of DGR alarm illumination the flight crew must cross-check the aircraft position using conventional means or must revert to an alternative means of navigation.PROCEDURES .has been demonstrated to meet the requirements of JAA TGL n°2.This equipment is approved for use as : . (b) Traditional navigation equipment must be selected to available aids so as to allow immediate cross-checking or reversion in the event of loss of GPS navigation capability.The system must be used with an updated active data base and the waypoints position must be cross-checked with official charts. 2 . AC 20-138 and DGAC CRI S-9902.primary navigation means for oceanic and remote operations when only one long range navigation system is required. 3 .In addition. in terminal area and for non precision approach operations until the missed approach point with respect of the MDA.advisory VNAV means. NOTE : Stand alone GPS approach is not approved.supplemental navigation means.GENERAL The Honeywell/Trimble GNSS 1000 : . REV1 and FAA AC 20-138 and FAA Notice N8110-60.The HT 1000 pilot's guide must be available on board.The system must operate with HT 1000-060 software version or any later approved version. .01. .07 P1 270 NOV 00
GPS 1 . the following procedures apply for B-RNAV operations : (a) during the pre-flight planning phase. . en route. Conventional means must be permanently cross-checked during the approach.complies with TSO C 129 and TSO C 115B.
The system must be used with an updated active data base and the waypoints position must be cross-checked with official charts.The CDI scale factor selectable in the MOD pages must not be set at the  0. beyond IAF. en route and in terminal area up to the Initial Approach Fix (IAF).If the RAIM function is lost.3 NM full scale deflection value.PROCEDURES .The following procedures apply for B-RNAV operations: (a) during the pre-flight planning phase. 2 .07 P1 280 NOV 00
GPS 1 . . .complies with TSO C 129.The system must not be used for approaches. : (4890 + 5022) or 5021
Mod. . . and FAA AC 20-138 for European B-RNAV operations. REV1. 3 . (b) Traditional navigation equipment must be selected to available aids so as to allow immediate cross-checking or reversion in the event of loss of GPS navigation capability. Dispatch must not be made in the event of predicted continuous loss of RAIM of more than 5 minutes for any part of the intended flight.This equipment is approved for use as a VFR and IFR supplemental navigation means. the availability of GPS integrity (RAIM) must be confirmed for the intended flight (route and time). . Aircraft operators must apply to their Authority for such an approval/ authorization.LIMITATIONS GLOBAL POSITIONING SYSTEM GPS
2.GENERAL The GPS Bendix/King KLN90B/BRNAV : .is installed in compliance with FAA AC 20-138 . .has been demonstrated to meet the requirements of JAA TGL n° 2.LIMITATIONS Compliance with the above regulations does not constitute an operational approval/authorization to conduct operations. the flight crew must cross-check the aircraft position using conventional means or must revert to an alternative means of navigation.01.
LIMITATIONS P1 CABIN LIGHTING
2.01.08 001 NOV 99
CABIN LIGHTING NOT APPLICABLE
08 100 NOV 99
CABIN LIGHTING The general cabin illumination system must be used during not less than 15 minutes before each flight.LIMITATIONS P1 CABIN LIGHTING
Mod : 5067 or 5171
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