TYPE CERTIFICATE DATA SHEET EA-2014T04 Type Certificate Holder: EMBRAER S.A. Av. Brigadeiro Faria Lima, 2.170 12227-901 – S.J dos Campos –SP Brazil EA-2014T04-07 Sheet 01 EMBRAER EMB-550, EMB-545 13 December 2016 This data sheet, which is part of Type Certificate No. 2014T04, prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness requirements of the Brazilian Aeronautical Regulations I – Model EMB-550 (Transport Category), approved on August 12 th , 2014. ENGINE Two turbofans Honeywell AS907-3-1E FUEL ASTM D1655, JET A and A1 Brazilian standard CNP08 or later, QAV – 1 Chinese standard GB6537-94 or later, Jet fuel No. 3 Standard MIL-DTL-83133, JP-8 Standard DEF STAN 91-91 AVTUR GOST 10227–86 (Russian RT, TS-1 Premium and TS-1 Regular) ENGINE LIMITS ITT limits Operation Conditions Operating Limits Thrust Setting State Time limit Max. ITT (°C) Ground Start - 5 s 650 Inflight ITT < 250°C and N2 < 18% [1] - - 400 All other start conditions - - 800 Takeoff power OEI Steady 10 min 955 Transient 2 min 970 AEO & WAI OFF Steady 5 min 955 Transient 2 min 970 AEO & WAI ON [2] Steady 5 min 955 Transient 2 min 970 Maximum Continuous Steady - 950 1- ITT limit remains 400°C until N2 goes above 18% during the start.
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TYPE CERTIFICATE DATA SHEET EA-2014T04
Type Certificate Holder:
EMBRAER S.A. Av. Brigadeiro Faria Lima, 2.170 12227-901 – S.J dos Campos –SP Brazil
EA-2014T04-07
Sheet 01
EMBRAER
EMB-550, EMB-545
13 December 2016
This data sheet, which is part of Type Certificate No. 2014T04, prescribes conditions and limitations under which the
product, for which the Type Certificate was issued, meets the airworthiness requirements of the Brazilian Aeronautical
Regulations
I – Model EMB-550 (Transport Category), approved on August 12th, 2014.
ENGINE Two turbofans Honeywell AS907-3-1E
FUEL ASTM D1655, JET A and A1
Brazilian standard CNP08 or later, QAV – 1
Chinese standard GB6537-94 or later, Jet fuel No. 3
Standard MIL-DTL-83133, JP-8
Standard DEF STAN 91-91 AVTUR
GOST 10227–86 (Russian RT, TS-1 Premium and TS-1 Regular)
ENGINE LIMITS
ITT limits
Operation Conditions Operating
Limits
Thrust Setting State Time
limit Max. ITT (°C)
Ground Start - 5 s 650
Inflight
s
t
a
r
t
ITT < 250°C
and N2 <
18% [1]
- - 400
All other
start
conditions
- - 800
Takeoff
power
OEI Steady 10 min 955
Transient 2 min 970
AEO & WAI
OFF
Steady 5 min 955
Transient 2 min 970
AEO & WAI
ON [2]
Steady 5 min 955
Transient 2 min 970
Maximum Continuous Steady - 950 1- ITT limit remains 400°C until N2 goes above 18% during the start.
EMBRAER 13 December 2016 EA-2014T04-07 Page 2/16
2- Below 80 KIAS, the maximum ITT is 923°C for steady state. For transient state,
the maximum ITT is 938°C.
N1 AND N2 LIMITS
OPERATING CONDITIONS OPERATING
LIMITS
Thrust Setting State Time
Limit
N1
(%) N2 (%)
Takeoff
power
OEI Steady - 96.8 98.5
Transient 7 s 98.0 99.9
AEO & WAI
OFF or ON
Steady - 96.8 98.5
Transient 7 s 98.0 99.9
Continuous Steady - 96.8 98.0
Transient 7 s 98.0 99.9
AIRSPEED LIMITS
Maximum operating Speeds (VMO/MMO):
Altitude Speed
0 to 10 000 ft (0 a 3 048 m) 300 IAS (154 m/s)
10 000 a 30 000 ft (3 048 a 9 144 m) 320 IAS (165 m/s)
30 000 a 45 000 ft (9 144 a 13 716 m) 0.83 Mach
Maneuvering (VA): 205 IAS (105 m/s)
Flaps extended (VFE):
Flap position Speed
Flap 1 210 IAS (108 m/s)
Flap 2 185 IAS (95 m/s)
Flap 3 185 IAS (95 m/s)
Flap full 170 IAS (88 m/s)
Landing gear maximum operation/extended speed (VLO/LE):
VLO –Landing gear operation 250 IAS (129 m/s)
VLE – Landing gear extended 250 IAS (129 m/s)
APU Honeywell 36-150[EMB]
APU LIMITS
Parameter Minimum Maximum
Start
Altitude
Ground [1] [1]
In-flight - 31 000 ft
(9 449 m)
Temperature Ground [2] [2]
In-flight - 37°C [2]
EMBRAER 13 December 2016 EA-2014T04-07 Page 3/16
Parameter Minimum Maximum
Operation Altitude
Electrical
Power
Limit
- 31 000 ft
(9 449 m)
In-flight
Assisted
Engine
Start
- 23 000 ft
(7 010 m)
ECS - 20 000 ft
(6 096 m)
Temperature [2] [2]
Rotor Speed - 106%
EGT Start - 985°C
Continuous - 757°C
1- APU altitude for ground start matches the Airplane Operational
Envelope.
2- APU temperature matches the Airplane Operational Envelope
temperature.
CG RANGE See the Approved Airplane Flight Manual - AFM 3921-100
DATUM The airplane datum is a plane, perpendicular to the fuselage centerline,
located at 429.92 in (10.93 m) ahead of the wing jack points.
LEVELING MEANS Check aircraft AMM – chapter 8
MEAN AERODYNAMIC CHORD MAC lenght = 100.79 in (2.56 m)
MAXIMUM WEIGHT
Without BS 550-042-0004
lb (kg)
With BS 550-042-0004
lb (kg)
Ramp 38 096 (17 280) 38 536 (17 480)
Takeoff 37 920 (17 200) 38 360 (17 400)
Land 34 128 (15 480) 34 524 (15 660)
Zero Fuel 26 500 (12 020) 26 500 (12 020)
MINIMUM CREW 2 Pilots
MAXIMUM OCCUPANTS 12 Passengers
MAXIMUM BAGGAGE Wardrobe 88 lb. (153.15 in. aft of datum)
Internal Stowage Compartment 330 lb. (452.76 in. aft of datum)
External Cargo Compartment 881 lb. (543.30 in. aft of datum)
FUEL CAPACITY Total fuel capacity of 13 146.3 lb (5 963.1 kg.), two wing tanks 6 573.2
lb (2 981.5 kg) each, @ 367.72 in (9.34 m) aft of datum
OIL CAPACITY Tank mounted on each engine: 7.6 U.S. quarts (7.19 liter) total on each
engine
HYDRAULIC FLUID CAPACITY 109.6 lb. at 496.34 in. aft of datum
MAXIMUM OPERATING ALTITUDE
45 000 ft (13 716 m)
EMBRAER 13 December 2016 EA-2014T04-07 Page 4/16
TEMPERATURE OPERATING LIMITS
See the Approved Airplane Flight Manual - AFM 3921-100
CONTROL SURFACE MOVEMENTS
Elevator Up 25° ±1°
Down 15° ±1°
Rudder Right 30° ±1°
Left 30° ±1°
Aileron Up 25° ±0.8°
Down 15° ±0.8°
Wing Flap TO 7° ±1°
TO/Land 37° ±1.5°
Spoiler
Inboard Middle Outboard
Inflight 30° ±1.3° 30° ±1.4° 30° ±1.9°
Ground 40.5° ±1.3° 43° ±1.4° 40.5°±1.9°
Horiz. Stabilizer Up 12° ±0.5°
Down 3° ±0.5°
SERIAL NUMBER 55000001 up to 55009999, except 55000009 and 55000020
II– Model EMB-545 (Transport Category), approved on August 11th, 2015.
ENGINE Two turbofans Honeywell AS907-3-1E
FUEL ASTM D1655, JET A and A1
Brazilian standard CNP08 or later, QAV – 1
Chinese standard GB6537-94 or later, Jet fuel No. 3
Standard MIL-DTL-83133, JP-8
Standard DEF STAN 91-91 AVTUR
GOST 10227–86 (Russian RT, TS-1 Premium and TS-1 Regular)
ENGINE LIMITS
ITT limits
Operation Conditions Operating
Limits
Thrust Setting State Time
limit Max. ITT (°C)
Ground Start - 5 s 650
EMBRAER 13 December 2016 EA-2014T04-07 Page 5/16
Inflight
s
t
a
r
t
ITT < 250°C
and N2 <
18% [1]
- - 400
All other
start
conditions
- - 800
Takeoff
power
OEI Steady 10 min 955
Transient 2 min 970
AEO & WAI
OFF
Steady 5 min 955
Transient 2 min 970
AEO & WAI
ON [2]
Steady 5 min 955
Transient 2 min 970
Maximum Continuous Steady - 950 1- ITT limit remains 400°C until N2 goes above 18% during the start.
2- Below 80 KIAS, the maximum ITT is 923°C for steady state. For transient state,
the maximum ITT is 938°C.
N1 AND N2 LIMITS
OPERATING CONDITIONS OPERATING
LIMITS
Thrust Setting State Time
Limit
N1
(%) N2 (%)
Takeoff
power
OEI Steady - 96.8 98.5
Transient 7 s 98.0 99.9
AEO & WAI
OFF or ON
Steady - 96.8 98.5
Transient 7 s 98.0 99.9
Continuous Steady - 96.8 98.0
Transient 7 s 98.0 99.9
AIRSPEED LIMITS
Maximum operating Speeds (VMO/MMO):
Altitude Speed
0 to 10 000 ft (0 a 3 048 m) 300 IAS (154 m/s)
10 000 a 30 000 ft (3 048 a 9 144 m) 320 IAS (165 m/s)
30 000 a 45 000 ft (9 144 a 13 716 m) 0.83 Mach
Maneuvering (VA): 205 IAS (105 m/s)
Flaps extended (VFE):
Flap position Speed
Flap 1 210 IAS (108 m/s)
Flap 2 185 IAS (95 m/s)
Flap 3 185 IAS (95 m/s)
Flap full 170 IAS (88 m/s)
Landing gear maximum operation/extended speed (VLO/LE):
EMBRAER 13 December 2016 EA-2014T04-07 Page 6/16
VLO –Landing gear operation 250 IAS (129 m/s)
VLE – Landing gear extended 250 IAS (129 m/s)
APU Honeywell 36-150[EMB]
APU LIMITS
Parameter Minimum Maximum
Start
Altitude
Ground [1] [1]
In-flight - 31 000 ft
(9 449 m)
Temperature Ground [2] [2]
In-flight - 37°C [2]
Operation Altitude
Electrical
Power
Limit
- 31 000 ft
(9 449 m)
In-flight
Assisted
Engine
Start
- 23 000 ft
(7 010 m)
ECS - 20 000 ft
(6 096 m)
Temperature [2] [2]
Rotor Speed - 106%
EGT Start - 985°C
Continuous - 757°C
1- APU altitude for ground start matches the Airplane Operational
Envelope.
2- APU temperature matches the Airplane Operational Envelope
temperature.
CG RANGE See the Approved Airplane Flight Manual - AFM 3921-400
DATUM The airplane datum is a plane, perpendicular to the fuselage centerline,
located at 404.33 in (10.27 m) ahead of the wing jack points.
LEVELING MEANS Check aircraft AMM – chapter 8
MEAN AERODYNAMIC CHORD MAC lenght = 100.79 in (2.56 m)
MAXIMUM WEIGHT
Without BS 550-042-0004
lb (kg)
With BS 550-042-0004
lb (kg)
Ramp 35 406 (16 060) 35 891 (16 280)
Takeoff 35 274 (16 000) 35 758 (16 220)
Land 32 518 (14 750) 32 518 (14 750)
Zero Fuel 25 904 (11 750) 25 904 (11 750)
MINIMUM CREW 2 Pilots
MAXIMUM OCCUPANTS 10 Passengers
EMBRAER 13 December 2016 EA-2014T04-07 Page 7/16
MAXIMUM BAGGAGE Wardrobe 88 lb. (153.15 in. aft of datum)
Internal Stowage Compartment 330 lb. (409.45 in. aft of datum)
External Cargo Compartment 881 lb. (500.00 in. aft of datum)
FUEL CAPACITY Total fuel capacity of 10 939 lb (4962 kg.), two wing tanks 5 470 lb
(2481 kg) each, @ 342.1 in (8.69 m) aft of datum for aircraft pre-mod
SB 550-28-0002 or equivalent factory-icorporated modification.
Total fuel capacity of 12 940 lb (5870 kg.), two wing tanks 6 470 lb
(2935 kg) each, @ 339.5 in (8.62 m) aft of datum for aircraft post-mod
SB 550-28-0002 or equivalent factory-icorporated modification.
OIL CAPACITY Tank mounted on each engine: 7.6 U.S. quarts (7.19 liter) total on each
engine
HYDRAULIC FLUID CAPACITY 105.2 lb (47.7 kg) @ 467.2 in (11.9m) aft of datum
MAXIMUM OPERATING ALTITUDE
45 000 ft (13 716 m)
TEMPERATURE OPERATING LIMITS
See the Approved Airplane Flight Manual - AFM 3921-400
CONTROL SURFACE MOVEMENTS
Elevator Up 25° ±1°
Down 15° ±1°
Rudder Right 30° ±1°
Left 30° ±1°
Aileron Up 25° ±0.8°
Down 15° ±0.8°
Wing Flap TO 7° ±1°
TO/Land 37° ±1.5°
Spoiler
Inboard Middle Outboard
Inflight 30° ±1.3° 30° ±1.4° 30° ±1.9°
Ground 40.5° ±1.3° 43° ±1.4° 40.5°±1.9°
Horiz. Stabilizer Up 12° ±0.5°
Down 3° ±0.5°
SERIAL NUMBER 55000009, 55000020, 55010003 and subsequent
CERTIFICATION BASIS EMB-550
EMBRAER 13 December 2016 EA-2014T04-07 Page 8/16
1. RBAC 25 (Brazilian Airworthiness Standard: Transport Category
Aircraft), corresponding to US 14 CFR part 25, including
amendments 25-1 through 25-128 effective on 29 May 2009.
Special Conditions:
ES-01 - Sudden Engine Stoppage – according to ANAC resolution
No. 271, dated April 9th, 2013
ES-04 - Design Roll Maneuver for Electronic Flight Controls –
according to ANAC resolution No 214, dated January 25th, 2012
ES-11 - Limit Pilot Force for Side Stick Controls – according to
ANAC resolution No. 290, dated October 8th, 2013
ES-16 - Interaction of Systems and Structures – according to
ANAC resolution No. 294, dated November 26th, 2013
ES-21 - Dive Speed Definition with Speed Protection System –
according to ANAC resolution No. 282, dated September 17th,
2013
ES-23 - Landing Pitchover Condition – according to ANAC
resolution No. 298, dated December 18th of 2013
EI-07 - Single and multiple place side facing seats, and airbag
systems in the shoulder belt Electrical/Electronic Systems –
according to ANAC resolution No. 383, dated June 28th, 2016
SE-03 - Operation Without Normal Electrical Power – according to
ANAC resolution No. 295, dated November 26th, 2013
SE-15 - Systems and Data Networks Security-Isolation or
Protection From Unauthorized Passenger Domain Systems Access
– according to ANAC resolution No. 321, dated May 27th, 2014
SE-16 - Systems and Data Networks Security-Protection of
Airplane Systems and Data Networks from Unauthorized External
Access – according to ANAC resolution No. 322, dated May 29th,
2014
EV-03 - Flight Envelope Protection: Pitch and Roll and High Speed
Limiting Functions – according to ANAC resolution No. 315, dated
May 6th, 2014
EV-07 - Flight Envelope Protection: Normal Load Factor (g)
Limiting – according to ANAC resolution No. 314, dated May 6th,
2014
EV-08 - EFCS: Lateral-Directional and Longitudinal Stability and
Low Energy Awareness – according to ANAC resolution No. 289,
dated October 8th, 2013
EV-17 - Performance Credit for ATTCS during Go-Around –
according to ANAC resolution No. 287, dated September 27th, 2013
EV-25 - Flight Envelope Protection: High Incidence Protection and
situational awareness – according to ANAC resolution No. 312,
dated May 6th, 2014
EV-27 – Steep Approach Mode Functionality (SAM) - according
to ANAC resolution No. 300, dated January 7th, 2014
EMBRAER 13 December 2016 EA-2014T04-07 Page 9/16
EV-37 - Flight Envelope Protection – General – according to
ANAC resolution No. 313, dated May 6th, 2014
EV-38 - Hydrophobic Coating – according to ANAC resolution No.
283, dated September 17th, 2013
EV-46 - Credit for Robust Envelope Protection in Icing Conditions
– according to ANAC resolution No. 311, dated May 6th, 2014
EV-47 – Synthetic Vision System (SVS) and Enhanced Flight
Vision Systems (EFVS) on Head Up Display (HUD) – according
to ANAC resolution 384, dated June 28th, 2016
SM-01 - Flight control system multiple modes of operation –
according to ANAC resolution No. 286, dated September 27th, 2013
SM-02 - EFCS: Flight Control Surface Position Awareness –
according to ANAC resolution No. 285, dated September 27th, 2013
SM-06 - Side Stick Controllers – according to ANAC resolution
No. 292, dated October 31st, 2013
SM-09 - Electrical/Electronic Equipment Bay Fire Detection and
Smoke Penetration – according to ANAC resolution No. 301, dated
January 14th, 2014
SM-17 - Stowage Compartment Fire Protection – according to
according to ANAC Decision No. 134, dated November 26th, 2013
EI-25 - Passenger Information Signs RBAC 25.791(a) – Granted
according to ANAC Decision No. 151, dated December 16th, 2013
EI-27 - Overwing Outside View Means RBAC 25.809(a) – Granted
according to ANAC Decision No. 25, dated March 25th, 2014
EI-38 - Temporary non-compliance with Leg flail requirement
RBAC 25.562(a), 25.785(b) e itens (b)(5) e (b)(7) da SC No. 25-
033 – Granted according to ANAC Decision No. 175 dated
December 5th, 2016
SE-01 - Lightning Protection of Fuel Tank Structure 25.981(a)(3)
– Granted according to ANAC Decision No. 119, dated November
5th, 2013
2. RBAC 34 - Requisitos para drenagem de combustível e emissões
de escapamento de aviões com motores a turbine (Fuel Venting and
Exhaust Emission Requirements for Turbine Engine Powered),
corresponding to the 14 CFR Part 34, as amended on the Type
Certificate issuance date
3. RBAC 36 - Requisitos de ruído para aeronave. (Noise Standard for
aircrafts) corresponding to the 14 CFR Part 36, including
amendments 36-1 through 36-28 effective on February 3rd, 2006.
4. Optional Icing requirements 25.1403 e 25.1419 compliant.
5. Not approved for ditching, 25.1411 e 25.1415 compliant.
6. The aircraft is RVSM capable from S/N 55000009 and on. Each
operator must obtain RVSM operating approval according to local
operational regulations.
NOTES: EMB-545
NOTE 1 Weight and balance.
Current weight and balance report, including the list of equipment that
are part of the certificated basic empty weight and loading instructions,
must be provided for each aircraft at the time of original certification.
EMBRAER 13 Decembef 2016 EA-2014T04-07 Pago 16/16
The certificated empty weight and corresponding conter of gravitylocation musa include:
NOTE 2 Markines and placards
Al] marking and placards required by the applicable certificationrequirements (see. certification basics) and by the operationalrequirements musa be installed in the apprópriated locations. Requiredplacards and marking are listed in chapter Elevcn (11) of the Aircraftlllustrated Paras Catalog(AIPC).
NOTE 3 Continuing Airworthiness
See Maintenance - Manual, Chapter Four (4), "AirworthinessLimitations" for Systems Airworthiness Limitations, StructureAirworthiness Limitations (ALI) and Lide-Limited ltems (LLI).
The bife limit for rotating parts on the AS907-3-IE engine is in engineLight Maintenance Manual, Airworthiness Limitations Section
NOTE 4 Airplanesmust be operated according to the ANAC Approved AirplaneFlight Manual (AFM), pari óumber AFM-3921-400 dated August 11'h,2015 or laser appl.oved révisions
NOTE 5 The EMB-545 is often referred to in Embraer marketing literatura asthe "Legacy 450". This is strictly a marketing designation and is notpart of the official modem designation
Original in the Portuguese language signed by:
MACIO IGAWAGerente-Geral de Cehificação de Produto Aeronáutico
(Manager, AeronLJtical Product Certification)
/ ê
Unusable fuGI 88.6 lb (40.2 kg) at 330:70 in. (8.04 m) aft ofdatum
Full engine oil 48.5 lb (22 kg) at 519.70 in. (13.20 m) aft ofdatum
APU oil 4.4 lb (2 kg) at 631.20 in.'(16.00 m) aft ofdatum
Hydraulic Fluid 105.2 lb (47.7 kg) at 467.20 in (11.90 m) aftof datum