type certificate data sheet nº ea-9607 airbus france · type certificate data sheet nº ea-9607...

TYPE CERTIFICATE DATA SHEET Nº EA-9607

Type Certificate Holder:

AIRBUS 1, Rond-Point Maurice Bellonte 31707 Blagnac FRANCE

EA-9607-17

Sheet 01

AIRBUS

A320-211,-231, -212, -232,-214, -233, and -

271N A321-131,-112, -111, -211,-212, -213, -231 and -232 A319-111,-112,-113,-115, -114, -131, -132 and -133

A318-111, -112, -121, -122

25 August 2016

This data sheet, which is part of Type Certificate No. 9607, 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- Models A320-211, A320-231, A320-212, A320-232, A320-214 and A320-233 (Transport Category), approved 07 November 1996.

Model A32-271N (Transport Category), approved 10 June 2016 ENGINE A320-211: Two CFMI turbofan engines CFM 56-5A1 or CFM 56-

5A1/F. (See note 5) A320-212: Two CFMI turbofan engines CFM 56-5A3. A320-214: Two CFMI turbofan engines CFM 56-5B4, CFM 56-

5B4/P, CFM 56-5B4/2 or CFM 56-5B4/2P. (See note 5) A320-231: Two IAE turbofan engines V2500-A1. A320-232: Two IAE turbofan engines V2527-A5. A320-233: Two IAE turbofan engines V2527E-A5. A320-271N: Two IAE Model PW1127G-JM or PW1127GA-JM jet

engines MAXIMUM WEIGHTS A320-211, A320-212, A320-214* and A320-231:

VARIANT 000 BASIC

(MOD 20802)001

MOD 20966002

MOD 21601 003

MOD 22269Max. Ramp Weight 73 900 kg 68 400 kg 70 400 kg 75 900 kg Max. Takeoff Weight 73 500 kg 68 000 kg 70 000 kg 75 500 kg Max. Landing Weight 64 500 kg 64 500 kg 64 500 kg 64 500 kg Max. Zero Fuel Weight 60 500 kg 60 500 kg 60 500 kg 60 500 kg Minimum Weight 37 230 kg 37 230 kg 37 230 kg 37 230 kg

VARIANT 004

MOD 21532005

MOD 21711006

MOD 22436 007

MOD 23264Max. Ramp Weight 71 900 kg 67 400 kg 66 400 kg 77 400 kg Max. Takeoff Weight 71 500 kg 67 000 kg 66 000 kg 77 000 kg Max. Landing Weight 64 500 kg 64 500 kg 64 500 kg 64 500 kg Max. Zero Fuel Weight 60 500 kg 60 500 kg 60 500 kg 60 500 kg

AIRBUS 25 August 2016 EA-9607-17 Sheet 2/37

Minimum Weight 37 230 kg 37 230 kg 37 230 kg 37 230 kg

VARIANT 008 MOD 23900

009 MOD 23900MOD 22269

010** MOD 23900 MOD 23264

011 MOD 30307

Max. Ramp Weight 73 900 kg 75 900 kg 77 400 kg 75 900 kg Max. Takeoff Weight 73 500 kg 75 500 kg 77 000 kg 75 500 kg Max. Landing Weight 64 500 kg 64 500 kg 64 500 kg 66 000 kg Max. Zero Fuel Weight 61 000 kg 61 000 kg 61 000 kg 62 500 kg Minimum Weight 37 230 kg 37 230 kg 37 230 kg 37 230 kg

** See note 14.


013 MOD 31132

014 MOD 31385

016 MOD 34094

Max. Ramp Weight 77 400 kg 71 900 kg 73 900 kg 73 900 kg Max. Takeoff Weight 77 000 kg 71 500 kg 73 500 kg 73 500 kg Max. Landing Weight 66 000 kg 64 500 kg 64 500 kg 66 000 kg Max. Zero Fuel Weight 62 500 kg 61 000 kg 61 500 kg 62 500 kg Minimum Weight 37 230 kg 37 230 kg 37 230 kg 37 230 kg

* For A320-214 except WV004 (mod 21532) and WV006 (mod 22436), which are not applicable to this A/C model.

MAXIMUM WEIGHTS A320-271N:

VARIANT 054 055 056 057

Max. Ramp Weight 79 400 kg 79 400 kg 70 400 kg 70 400 kg Max. Take-off Weight 79 000 kg 79 000 kg 70 000 kg 70 000 kg Max. Landing Weight 66 300 kg 67 400 kg 66 300 kg 67 400 kg Max. Zero Fuel Weight 62 800 kg 64 300 kg 62 800 kg 64 300 kg Minimum Weight 40 300 kg 40 300 kg 40 300 kg 40 300 kg

FUEL CAPACITY (0.8 kg/l) A320-211, A320-231, A320-212, A320-232, A320-214 AND A320-233

3 TANK AIRPLANE

TANK Usable fuel liters (kg) Unusable fuel liters (kg)WING 15 609 (12 487) 58.9 (47.1)

CENTER 8 250 (6 600) 23.2 (18.6)TOTAL 23 859 (19 087) 82.1 (65.7)

FUEL CAPACITY (0.8 kg/l) A320-271N

3 TANK AIRPLANE TANK Usable fuel liters (kg) Unusable fuel liters (kg)WING 15 477 (12 428) 58.9 (47.3)

CENTER 8 248 (6 623) 23.2 (18.6)TOTAL 23 725 (19 050) 82.1 (65.9)

VARIANT 050 055 052 053 Max. Ramp Weight 73 900 kg 73 900 kg 77 400 kg 77 400 kg Max. Take-off Weight 73 500 kg 73 500 kg 77 000 kg 77 000 kg Max. Landing Weight 66 300 kg 67 400 kg 66 300 kg 67 400 kg Max. Zero Fuel Weight 62 800 kg 64 300 kg 62 800 kg 64 300 kg Minimum Weight 40 300 kg 40 300 kg 40 300 kg 40 300 kg


II- DATA PERTINENT TO A320 CEO except A320 NEO

FUEL See installation manual document CFM 2026, 2129 or document IAE-0043. Kerosene: Air 3405C, ASTM D 1655 (JET A/A1) or DERD 2494

MIL-T-83133 (JP8). Wide cut: Air 3407, ASTM D 1655 (JET B) or DERD 2454

Air 3407(TR4), MIL-T 5624 (JP 4) or DERD 2454. * High flash point: Air 3404, MIL-T 5624 (JP5) or DERD 2452 Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13, or IAE

V2500 “Installation and Operating Manual” IAE-0043 Sec 4.5. The above mentioned fuels and additives are also suitable for the APU.

ENGINE LIMITS AND OIL (2 2482 lb/daN) (See Note 15) (see Note 16)

ENGINE CFMI** IAE***

CFM56-5A1 CFM56-5A1/F

CFM56-5A3

CFM56-5B4 CFM56-5B4/2

V2500-A1 V2527-A5

V2527E-A5 Data

Sheets FAA

ANAC E28NE

EM-9604 E28NE

EM-9604 E37NE, E38NE

EM-9604 E31NE

EM-9703 E40NE

EM-9704 Static thrust at sea level: - Takeoff (5min.)* (Flat rated 30°C)

11 120 daN (25 000 lb)

11 787 daN (26 500 lb)

12 010 daN (27 000 lb)

11 031 daN (24 800 lb)

11 031 daN (24 800 lb)

- Maximum continuous (Flat rated 25ºC)

10 542 daN (23 700 lb)

10 542 daN (23 700 lb)

10 840 daN (24 370 lb)

9 893 daN (22 240 lb)

9 893 daN (22 240 lb)

Maximum engine speed: - N1 rpm (%) 5 100 (102) 5 100 (102) 5 200 (104) 5 465 (100) 5 650 (100) - N2 rpm (%) 15 183 (105) 15 183 (105) 15 183 (105) 14 915 (100) 14 950 (100) Maximum gas temperature

- Takeoff (5min.)* 890ºC 890ºC 950ºC 635ºC 610ºC - Maximum continuous 855ºC 855ºC 915ºC 610ºC 645ºC - Starting**** 725ºC 725ºC 725ºC 635ºC 650ºC Maximum oil temperature (supply pump inlet):

- Takeoff, stabilized 140ºC 140ºC 140ºC 155ºC 155ºC - Transient (15 min. max.) 155ºC 155ºC 155ºC 165ºC 165ºC Minimum oil pressure: 13 psid 13 psid 13 psid 60 psig 60 psig

Approved oils see SB CFMI 79-001-0X see doc. IAE-0043

Sect. 4.9 (MIL-L-23699) * 10 minutes at Takeoff thrust allowed only in case of engine failure (at Takeoff or during go-around) in

accordance with the engine TCDS. ** See note 7. *** See note 8. **** 4 consecutive cycles of 2 minutes each.

AUXILIARY POWER UNIT Garrett Airesearch GTCP 36-300(A) (Specification 31-5306B).

- Approved oils: see Garrett report GT-7800. APIC APS 3200 (Mod. 22562, option) (Specification ESR 0802, Rev. A). - Approved oils: MIL-L-7808, MIL-L-23699 or DERD 2487. Allied Signal 131-9[A] (Mod. 25888 or 35864) (Specification 4900 M1E 03 19 01) - Approved oils: according to Model Specification 31-12048A-3A.

AIRSPEED LIMITS Maximum operating (VMO/MMO): 350 kt/0.82 (IAS, unless otherwise stated) Design maneuvering (VA): Refer to Chapter 2.0 of the AFM.


Flaps extended (VFE): Config. Slats

/Flaps(°)VFE (kt)

Intermediate approach Takeoff

1 18/0 18/10*

230 215

Takeoff and approach 2 22/15 200 Takeoff, approach and landing 3 22/20 185 Landing Full 27/35

(27/40) for IAE engines

177

* Auto flap retraction at 210 kt in take-off configuration.

L. G. extended (VLE) 280 kt/ Mach 0.67 L. G. operation (VLO) - Extension: 250 kt AIRSPEED LIMITS (Cont.) (IAS, unless otherwise stated)

- Retraction - Tyre limit (ground speed)

220 kt 195.5 kt (225 mph)

CENTER OF GRAVITY RANGE See DGAC/EASA approved Brazilian Airplane Flight Manual. DATUM Station 0 (100 inches forward of fuselage nose). MEAN AERODYNAMIC CHORD 165.10 inches (leading edge of MAC: Sta. 700.85 inches). LEVELING MEANS Clinometer on the cabin seat track rails. MINIMUM FLIGHT CREW 2 pilots. MAXIMUM NUMBER OF PASSENGERS

180

MAXIMUM BAGGAGE Cargo Compartment Maximum Load (kg) - Forward: 3 402 - Aft: 4 536 - Rear (Bulk): 1 497 For the positions and the loading conditions authorized in each

position (references of containers, pallets and associated weights) see Weight and Balance Manual, ref. 00 D 080 A 0001 / C1S Chapter 1.10.

HYDRAULIC FLUIDS Type IV or Type V - Specification NSA 30.7110. TIRES See SB A320-32-1007. MAXIMUM OPERATING ALTITUDE 11 918 m (39 100 ft)

12 100 m (39 800 ft) if modification 30748 is embodied IMPORT REQUIREMENTS A Brazilian Certificate of Airworthiness may be issued on the basis of

on a EASA Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement: “The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate no. 9607 and in condition for safe operation”.


The ANAC Report H.10-1530-02, dated 15 March 2005 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See note 4)

CERTIFICATION BASIS RBHA 25 Airworthiness Requirements – Transport Airplane Category

– corresponding to 14 CFR Part 25, including amendments 25-1 through 25-56 effective 31 Jan. 83, plus the following:

JAR 25.107(e)(1)(iv) - VLOF margins; Special Conditions (SC), Harmonization Conditions (HC) and Experience Related Conditions (EC): Models A320-111, A320-211, A320-231 and A320-212 Variants 001 thru 006

EC-A3.6.1-High Lift Devices; EC-G11-General Definition; EC-S30-Autoflight System;

CERTIFICATION BASIS (Cont.) - EC-S54-Circuit Protective Devices;

- HC-A4.4-Manoeuvre Loads with High Lift Devices Deployed; - HC-A4.5-Braked Roll Conditions; - HC-A4.6-Speed Control Device; - HC-F103-ASD-TOD-TOR on Wet Runways; - HC-F114-Approach and Target Threshold Speeds; - HC-S23-Standby Gyroscopic Horizon; - HC-S24-VMO/MMO Warning (Setting); - HC-S61-Design Landing Brake Kinetic Energy; - HC-S62-Rejected Takeoff Brake Kinetic Energy; - HC-S72-Flight Recorder; - SC-A2.1.1-Certification Criteria for Aircraft Designed with

Systems Interacting with Structural Performance; - SC-A2.2.2-Design Manoeuvre Requirement; - SC-A2.2.3-Design Dive Speed; - SC-A4.3-Tuned Gust Loads;

- SC-F1-Stalling and Scheduled Operating Speeds;- SC-F3-Cockpit Control - Motion and Effect of Cockpit Control;- SC-F4-Static Longitudinal Stability; - SC-F6-Static Directional and Lateral Stability; - SC-F7-Flight Envelope Protection; - SC-F8-Normal Load Factor Limiting; - SC-F9-Dual Control System; - SC-G17-Operational Proving Flights (France); - SC-P01-Full Authority Engine Control System (FADEC); - SC-S11-Limit Pilot Forces and Torques; - SC-S33-Autothrust System; - SC-S52-Operation without Normal Electrical Power; - SC-S74-Abnormal Attitudes; - SC-S75-Lightning Protection (Indirect Effects); - SC-S76-Effect of External Radiations up on Aircraft Systems; and- SC-S77-Integrity of Signal Control

Models: A320-211, A320-231 and A320-212 Variants 007 thru 010; A320-232; A320-214; and A320-233.

- EC-A3.6.1-High Lift Devices; - EC-G11-General Definition; - EC-S30-Autoflight System; - EC-S54-Circuit Protective Devices;


- HC-A4.5-Braked Roll Conditions;- HC-A4.6-Speed Control Device; - HC-F103-ASD-TOD-TOR on Wet Runways (not applicable to

model A320-233); - HC-F114-Approach and Target Threshold Speeds; - HC-S23-Standby Gyroscopic Horizon; - HC-S24-VMO/MMO Warning (Setting); - HC-S61-Design Landing Brake Kinetic Energy (not applicable

to model A320-233); - HC-S62-Rejected Takeoff Brake Kinetic Energy (not applicable

to model A320-233); - HC-S72-Flight Recorder; - SC-A2.1.1-Certification Criteria for Aircraft Designed with

Systems Interacting with Structural Performance; - SC-A2.2.2-Design Manoeuvre Requirement; - SC-A2.2.3-Design Dive Speed; - SC-F1-Stalling and Scheduled Operating Speeds; - SC-F3-Cockpit Control - Motion and Effect of Cockpit Control

- SC-F4-Static Longitudinal Stability; - SC-F6-Static Directional and Lateral Stability; - SC-F7-Flight Envelope Protection; - SC-F8-Normal Load Factor Limiting; - SC-F9-Dual Control System; - SC-F11-Accelerate-Stop Distances and Related

Performances, Worn Breaks - CRI F2012 (applicable only to model A320-233);

- SC-G17-Operational Proving Flights (France); - SC-P01-Full Authority Engine Control System (FADEC); - SC-S11-Limit Pilot Forces and Torques; - SC-S33-Autothrust System; - SC-S52-Operation without Normal Electrical Power; - SC-S74-Abnormal Attitudes; - SC-S75-Lightning Protection (Indirect Effects); - SC-S76-Effect of External Radiations upon Aircraft Systems; - SC-S77-Integrity of Control Signal; and - SC-S79-Brakes Requirements, Qualification and Testing, CRI

SE2003 (applicable only to model A320-233)

Equivalent Safety Demonstrations: - RBHA/14 CFR Part 25.783(e)-Cargo Doors (CRI SM 2005); - RBHA/14 CFR Part 25.783(f)-Passenger Doors and Bulk

Cargo Doors (CRI SM 2004/2007); - RBHA/14 CFR Part 25.807-Maximum Number of Passengers

(CRI E2107); and - RBHA/14 CFR Part 25.933(a) – Thrust Reverser Autorestow

Function (CRI P1002). Page14 Extended Range Twin Engine Airplane Operations Technical Conditions: - CAP 513-ETOPS. - SC G-1006: ETOPS Precision Approach and Landing: - JAR AWO Change 1-All Weather Operation Airbus Industrie elect-to-comply documents:


Models: A320-211, A320-231 and A320-212 Variants 007 thru 010; A320-232; A320-214; and A320-233.

- NPA 25.C.205-Discrete Gust Requirements - Flight Profile Altitude Weighted Analysis

Noise Standard: - RBHA/14 CFR Part 36 (corresponding to ICAO Annex 16 Vol. I).

Fuel Venting and Exhaust emission: - RBHA/14 CFR Part 34 (corresponding to ICAO Annex 16 Vol. II).

MOD 160500: Special Conditions SC F-16 Static directional and lateral stability A318 SC F-5001 Stalling and scheduled operating speeds A318 SC F-5004 Static Longitudinal Stability and Low energy awareness A318 SC A-5003 Design Dive Speed Vd

MOD 158217: Special Condition EASA SC CRI SC E-34: Seats with lnflatable Restraints

REQUIRED EQUIPMENT Equipment approved for installation is listed in the Certification Standard Equipment List 00 D 000 A 0101/C1S Cabin furnishings, equipment and arrangement shall be in conformance to the following specifications: - 00 D 252 K 0004 / C01 for cabin seats; and - 00 D 252 K 0019 / C01 for galleys.

SIGNIFICANT CHANGES Model A320-214, A320-232, A320-233 can be modified as per Mod

160500 “Sharklet Installation” EASA approved on December 21st 2012. According to procedures established under RBAC 21.101 the Certification Basis is updated according to EASA application date April 8, 2010: as establish in EASA CRI A-0001-001, issue 2, 06/09/2012.

NOTES:

NOTE 1 Weight and Balance: a current weight balance report, including list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification.

NOTE 2 Markings and Placards: all markings and placards for passenger information, external markings for emergency, and load limits in cargo/baggage compartments must be presented in Portuguese or bilingual. Documents titled “A320 Family External Markings Booklet” reference n° CC1300235 and “A320 Family Aircraft Passengers, Crew Placards and Illuminated Signs” reference n° CC1300236 are approved for acceptable translation in Portuguese or English.

NOTE 3 Continuing Airworthiness: service bulletins, structural repair manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is DGAC/EASA approved, are accepted by the ANAC and are considered ANAC approved. These approvals pertain to the type design only. Limitations applicable to Safe Life Airworthiness Limitation Items are provided in the A318/A319/A320/A321 Airworthiness Limitations Section (ALS) sub-parts 1-2 and 1-3 approved by the EASA. For other limitations see the DGAC/EASA-Approved Brazilian Airplane Flight Manual.


Certification Maintenance Requirements are provided in A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 3 approved by the EASA. Limitations applicable to Damage Tolerant Airworthiness Limitation Items are provided in the A318/A319/A320/A321 Airworthiness Limitations Items document (ALS Part 2) approved by the EASA. Ageing Systems Maintenance (ASM) limitations are provided in the A318/A319/A320/A321 Airworthiness Limitations Section (ALS) Part 4 EASA approved. Fuel Airworthiness Limitations are provided in A318/A319/A320/A321 Fuel Airworthiness Limitations document (ALS Part 5) approved by the EASA.

NOTE 4 The ANAC approved Type Design corresponds to the EASA approved Type Design plus the following specific requirements: - Brazilian approved AFM - markings and placards in Portuguese or bilingual as NOTE 2 above. - Installation of Cabin Ozone Filter - Additional Flight Recorder Parameter: (i) pilot and copilot pitch controller position, pitch

control surface position , pilot and copilot roll controller position, aileron and spoiler surface position, rudder pedal position and rudder surface position; (ii) the auto-thrust system commanded thrust parameter; and (iii) actual thrust (N1/EPR), electronic control command thrust and thrust lever position for each engine installation. (if Mod 25591 is installed the FDR parameters are in compliance)

- ADF1 powered by emergency bus bar - Acceptance of internal configuration

- MMEL categorized; and the following operational requirements: floor emergency escape path marking [RBHA 121.310(c)(3)]; interior materials flammability [RBHA 121.312(a), RBHA/FAR 25 Amdt. 66)]; cargo/baggage compartment fire protection [RBHA 121.314 (a)(1)]; emergency locator transmitter TSO-C91a[RBHA 91.207]; Ground Proximity Warning System [RBHA 121.360].

NOTE 5 A320-211: CFM 56-5A1 engine can be intermixed with CFM 56-5A1/F engine (mod 23755) on the same aircraft.

A320-214: CFM 56-5B4 engine can be intermixed with CFM 56-5B4/2 engine (mod 24405) on the same aircraft (AFM supplement). CFM 56-5B/ “non-P” engine can be intermixed with CFM 56-5B/P engine (mod 25800) on the same aircraft. CFM 56-5B/2 “non-P” engine can be intermixed with CFM 56-5B/2P engine (mod 26610) on the same aircraft (AFM supplement) CFM 56-5B/P or / “non-P” engine can be intermixed with CFM 56-5B/2P engine on the same aircraft (AFM supplement).

NOTE 6 If modification 20024 is embodied on the A320-100 Series, the central wing box is used as a central fuel tank.

NOTE 7 A320-212 (CFM 56-5A3 engines) - A320-211 (CFM 56-5A1/F engines): the maximum

permissible gas temperature at Takeoff and max. continuous is extended to 915ºC and 880ºC respectively. However, the ECAM indication remains at 890ºC and 855ºC.

NOTE 8 A320-231 with modification 23872 (EGT redline increase for IAE engines): - For consolidated bump rating operation (mod 22461 or 23408), the maximum

permissible gas temperature is extended to 650ºC at Takeoff. The ECAM indication remains at 635°C.

- For non rating bump operation, the maximum permissible gas temperature is extended to 640ºC at Takeoff, the ECAM indication remains at 635ºC.


- For max. continuous and Takeoff operation, the maximum permissible gas temperature is extended to 615ºC. The ECAM indication remains at 610ºC.

A320-231 with modification 25000 (FADEC Standard SCN12C for IAE engines):- For Takeoff operation, the maximum permissible gas temperature is extended to 650ºC;

the ECAM indication remains at 635ºC. - For max. continuous operation, the maximum permissible gas temperature is extended

to 625ºC; the ECAM indication remains at 610ºC.

NOTE 9 Autoflight certification:

For models A320-211 and A320-212, modification 21038 is the minimum standard to be qualified for Cat IIIB precision approach. For model A320-231, modification 21039 is the minimum standard to be qualified for Cat IIIB precision approach. All other models are qualified for Cat IIIB precision approach per basic design definition.

NOTE 10 ETOPS certification: The Configuration, Maintenance and Procedures Standards for

extended range twin engine airplane operations are contained in the document AI/EA 4000. Certificated models are A320-211/-212/-214/-231/-232/-233.

NOTE 11 [RESERVED] NOTE 12 If Mod. 28722 is incorporated, the A320-214/-232/233 performance complies with IAC 3502-

121-0888 requirements for landing on the Santos Dumont Airport porous friction course runway in wet conditions.

NOTE 13 If Mod. 25615 is incorporated, the A320-214/-232/-233 is approved for operations at

airports up to 4 298 m (14 100 ft).

NOTE 14 If Mod. 28547 is incorporated, aircraft is certificated to operate with weight variants 002 or

010. (Change of weight variant in service via Service Bulletin)

NOTE 15 Introduction of CFM56-5Bx/3 “Tech Insertion” engine is done through embodiment of

modification 37147.

This modification is only applicable on CFM56-5Bx /P SAC engines.

If modification 37147 is embodied on models with CFM-5B engines, the engine denomination changes to /3.

The modification is currently applicable for: A320-214: CFM 56-5B4 (SAC) which changes to CFM 56-5B4/3

Modification 37147 has been demonstrated as having no impact on previously certified noise levels.

CFM56-5Bx/3 engine can be intermixed with CFM56-5Bx/P engine under considerations as prescribes in modification 38573.

NOTE 16 RNP AR certification: Major Change (150371) “Airplane approved to approach RNP AR

0.3 e missed approach RNP AR 1.0.” “Airplane is approved to approach RNP AR less than 0.3 and missed approach less than 1.0 when approach procedures are not established to avoid obstacles or terrain”. “The airplane operational approval for RNP AR less than 0.3 (based on Airbus RNP AR ACD) or missed approach less than 1.0 when those procedures are required to avoid


obstacles or terrain, is conditioned to the use of operational mitigation measures to be evaluated and approved for each procedure/operator/aircraft model combination”.

NOTE 17 A320-111 model has been withdrawn of this TCDS according to Airbus request.

III – Data Pertinent to A320-271N

FUEL JET A; JET A1; JP5, JP8, N°3 JET FUEL ENGINE LIMITS Net take-off (5 minutes) 12 043 kN (27 075 lb) Net Maximum Continuous 11 718kN (26 345 lb) Maximum Engine Speed

- N1 rpm (%) 10 047(105)

- N2 rpm (%) 22 300(105) APU One (1) APU

Garrett Airesearch GTCP 36-300(A) (Specification 31-5306B). - Approved oils: see Garrett report GT-7800. Pratt & Whitney Rzeszow S.A APS 3200 (Mod. 22562 or mod. 35864, option) (Specification ESR 0802, Rev. A) -Approved oils: MIL-L-7808, MIL-L-23699 or DERD 2487. Honeywell International 131-9[A] (Mod. 25888, option) (Specification4900 M1E 03 19 01).

APU LIMITS Refer to the Auxiliary Power Unit operating instructions OIL Refer to the engine operating instructions & Engine AIRSPEED LIMITS (IAS) Maximum operating (VMO): 350 kias Maximum operating (MMO): 0.82 Maneuvering (VA) - sea level: Refer to AFM Limitation section

Flaps extended (VFE) Conf Slat/Flaps/ Ailerons (°)

VFE (Kias)

Intermediate Approach (Holding) 1 18/0 230 Takeoff / Approach 1 18/10 215 Takeoff / Approach 2 22/15 200 Takeoff / Approach / Landing 3 22/20 185 Landing FULL 27/40 177 Minimum control speed - Air

(VMCA): Refer to AFM Performance section

Minimum control speed - Ground (VMCG):

Refer to AFM Performance section

L. G. operation - extend (VLO): 250 kias L. G. operation - retract (VLO): 220 kias L. G. extended (VLE): 280 kias

CG RANGE Refer to EASA-Approved Brazilian Airplane Flight Manual Limitations Section for center of gravity envelope.


DATUM The airplane reference zero datum point is located 5.34 m (210.24 in.) forward of the nose section, .127 m (5 in.) above the floor reference.

LEVELING MEANS Clinometer on the cabin seat track rails. MEAN AERODYNAMIC CHORD 4.19m MINIMUM CREW Two (2) : Pilot and Co-pilot MAXIMUM PASSENGERS 180 MAXIMUM BAGGAGE Cargo Compartment kg lb Forward 3 402 7500 Aft 4 536 10000 Rear (bulk) 1 497 3300 Baggage/ Cargo Compartment Limitation: No passenger cargo

shall be carried in the cargo compartments.

FUEL CAPACITY Tanks Liters kg WING 15476.7 12427.8 CENTER 8248.0 6623.1 TOTAL 23724.7 19050.9 Density: 0.785kg/l OIL CAPACITY 34.9 quarts/engine (33.0 liters) HYDRAULIC FLUID Type IV or Type V Specification NSA 30.7110 MAXIMUM OPERATING ALTITUDE

39800feet

TEMPERATURE OPERATING LIMITS

From -40 to 55 at 0ft altitude

From -70C to 30°C at maximum flight level

CONTROL SURFACE Elevator: Up 17 Down -20 MOVEMENTS Rudder: Right 30 Left 30 Stabilizers -3.8/2.5 Aileron: Up 25 Down -25 Aileron Droop 5 Inboard flaps: Down 0 to 40 Outboard flaps: Down 0 to 40° Slats Down 0 to 27 #1,2 Spoilers 50 50 SERIAL NUMBER ELIGIBLE A Certificate of Airworthiness for Export endorsed as noted under

"Import Requirements" must be submitted for each individual aircraft for which application for a Brazilian Certificate of Airworthiness is made.


CERTIFICATION BASIS Brazilian Type Certificate No. 2015T08 issued on 05 August 2015 based on the RBAC 25 “Requisitos De Aeronavegabilidade: Aviões Categoria Transporte”, which endorses the 14 CFR Part 25 for the affected areas, RBAC 34 and RBAC 36 [corresponding to 14 CFR Part 36 – including amendments 1 to 28 effective on 03 Feb 2006].

The certification basis for the Airbus Model A320 NEO is based on the A320 CEO airplanes with Modification 160500 installation of large wingtip device (Sharklet) plus the requirements considered as affected. The compliance of the affected requirement was verified through equivalency finding to EASA Certification Specification 25 – Large Aeroplanes including EASA issued Special Conditions, Equivalent Level of Safety accepted by ANAC and additional ANAC issued Equivalent Level of Safety and Exemptions as noted:

EASA Special Conditions (NEO Only):

NEO Only SC E-45 (Engine Cowl Retention);

NEO Only SC/IM E-37 (Water/Ice in Fuel System) - for pylon area only;

NEO Only SC E-45 (Engine Cowl Retention);

NEO Only SC F-13 (Fuel System Low Level Indication – Fuel Exhaustion);

NEO Only SC B-01 (Stalling and Scheduled Operating Speeds);

NEO Only SC B-03 (Motion and Effect of Cockpit control);

NEO Only SC B-07 (Flight envelope protection);

NEO Only SC E-48 – Fuel Tank Safety for all areas except engine and pylon areas;

Legacy SC A-5003 (Design Dive Speed Vd) and sub-paragraph (e) amended by Legacy SC A-2 (Stalling speeds for structural design);

Legacy SC A-2 - § 25.479(a);

Legacy SC/IM S-75 – Lightning protection indirect effects);

Legacy SC F9 - Dual Control System;

Legacy SC S-76 – Effects of external radiations upon aircraft systems – modified by Legacy SC S-76-1 – Protection from the effects of HIRF;

Legacy SC F-11 – Accelerate-stop distances and related performances, worn brakes.

EASA Equivalent Safety Finding (NEO Only): ESF E-43 (Thrust Reverser Testing)

ESF E-49 (Fuel Filter Location for CFM)

ESF E-44(Fan Zone non-fire zone)

ESF E-51 (Oil temperature indication)

Requirements established according to the RBAC “Requisitos De Aeronavegabilidade: Aviões Categoria Transporte”, which endorses the 14 CFR Part 25 effective 02 September 2015, as amended by 25-1 through 25-136 verified through equivalency finding to EASA


Certification Specification 25, Amendment 11 – Large Aeroplanes considered affected:

25.3, 25.23 (a) (b), 25.25 (a)(b), 25.27, 25.101, 25.109, 25.113, 25.115, 25.117, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.231, 25.233, 25.235, 25.251(a)(b)(c)(d)(e), 25.253(a)(b), 25.255, 25.301(a)(b)(c) for new or modified parts), 25.303 (for new or modified parts), 25.305 (a)(b)(c)(e)(f) (for new or modified parts), 25.307(a)(d)(for new or modified parts), 25.321 (a)(b)(c)(d), 25.331 (a)(b)(c), 25.333 (a)(b), 25.335 (a)(b)(c)(d)(e)(f), 25.337, 25.341 (a)(b), 25.343 (a)(b) (for new or modified parts), 25.345 (a)(b)(d), 25.349 (a)(b), 25.351, 25.361, 25.363, 25.365 (a)(b)(c)(d)(e)(for new or modified parts), 25.367 (a)(b), 25.371, 25.373, 25.391 (a)(b)(c)(d)(e), 25.427 (a)(b)(c)(d), 25.445 (a)(b), 25.457, 25.459, 25.471 (a)(b), 25.473, 25.479 (a)(c)(d), 25.481 (a)(c), 25.483, 25.485 (a)(b), 25.489, 25.491, 25.493 (b)(c)(d), 25.495, 25.499 (a)(b)(c)(d)(e), 25.503 (a)(b), 25.507 (a)(b)(c), 25.509 (a)(c)(d), 25.511, 25.519 (a)(b)(c), 25.563, 25.581, 25.581, 25.601 (for new or modified parts), 25.603 , 25.605, 25.607, 25.609 (for new or modified parts), 25.613, 25.619 (for new or modified parts), 25.623 (for new or modified parts), 25.625, 25.629, 25.631 (for new or modified parts), 25.651 (for new or modified parts), 25.671, 25.672(a)(b)(c), 25.683(b), 25.703(a)(b)(c), 25.721(a)(b)(c), 25.777, 25.731 (a)(b)(c), 25.733 (b)(c)(d), 25.779, 25.789, 25.801, 25.841 (a), 25.843(b), 25.851 (b), 25.855 (c), 25.863 (a)(b)(c)(d), 25.865, 25.867 (a)(b) (for new or modified parts), 25.869 (a)(b)(c), 25.901 (a)(b)(c), 25.903, 25.904, 25.933 (a), 25.934, 25.939 (a)(c), 25.943, 25.951 (a)(b)(c)(d) (for new or modified parts), 25.952 (a)(b), 25.954, 25.955 (a), 25.961, 25.963 (a)(d), 25.969, 25.971, 25.981, 25.993 (a)(b)(c)(d)(e), 25.994, 25.995 for engine and pylon areas only, 25.997 (a)(b)(c)(d), 25.999 (a)(b), 25.1001, 25.1011 (a)(b), 25.1013 (a)(b)(c)(d)(e)(f), 25.1015 (a)(b), 25.1017 (a)(b) , 25.1019 (a), 25.1021 (a)(b), 25.1023 (a)(b), 25.1025 (a)(c), 25.1041, 25.1043 (a)(b)(c), 25.1045 (a)(b)(c),25.1091 (a)(b)(c)(d)(e), 25.1093 (b), 25.1103 (b)(c)(d), 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1155, 25.1163, , 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193, 25.1195, 25.1197, 25.1199, 25.1201, 25.1203, 25.1207, 25.1301, 25.1305, 25.1309, 25.1316, 25.1337 , 25.1353 (a)(b) (for engine and pylon areas), 25.1355 (c), 25.1357 (a for newly designed systems), 25.1401 (b), 25.1403, 25.1431 , 25.1438 (for newly designed equipment), 25.1461 (for newly designed equipment), 25.1501, 25.1503, 25.1507, 25.1511, 25.1513, 25.1515, 25.1517, 25.1519, 25.1521 (a)(c)(d) , 25.1525, 25.1527, 25.1529, 25.1531, 25.1533, 25.1535, 25.1549 (a)(b)(c), 25.1553, 25.1581, 25.1583, 25.1585, 25.1587, 25.1591, 25.1701 (a), 25.1703 (a)(b)(d), 25.1705, 25.1707, 25.1709, 25.1711, 25.1713, 25.1715, 25.1717, 25.1719, 25.1723, 25.1725 , 25.1727 for engines and pylon areas, 25.1731

Requirements, considering its amendment level, affected subjected to the RBAC 21.101(b)(3) substantiation:

25.21 Amdt. 120, 25.103 Amdt. 120, 25.105 Amdt. 120, 25.107 (except (e)(1)(iv)) Amdt 120, 25.111 Amdt. 120, 25.119 Amdt. 120, 25.121 Amdt. 120, 25.123 Amdt. 120, 25.125 Amdt. 120, 25.143 Amdt. 120, 25.145 Amdt. 97, 25.207 Amdt. 120, 25.237 Amdt. 120, 25.253(c) Amdt. 120, 25.561(a)(b)(c)(d) Amdt. 64, 25.571(a)(b)(e)(1) Amdt. 86, 25.611 Amdt. 56, 25.677(b) Amdt. 56,


25.899 Amdt. 56, 25.1317 Amdt. 56, 25.1322 Amdt. 56, 25.1329 Amdt. 56, 25.1351 Amdt. 56, 25.1419 Amdt. 120, 25.1435 Amdt. 56, 25.1459(a) Amdt. 56, Appendix H at amdt 56

Requirements of the RBAC 25 which endorses the 14 CFR Part 25 amended as indicated below per Airbus elect to comply:

25.853(a)(1) Amdt. 66, 25.853(c) at Amdt. 59

Exemptions:

The Exemptions applicable to each model as defined in TCDS remain applicable plus the following exemption applied specifically to the Airbus SA NEO models:

RBAC 25.841 (a)(2) and (a)(3) according to Decision nº 26 of 18 march of 2016

ELOS:

The following RBAC 25 requirement was verified through an Equivalent Safety Finding:

RBAC 25.779(b)(1) according to ANAC ordinance 1488/SAR

RBAC 25.811(g) according to ANAC ordinance 1937/SAR

NOTES:

NOTE 1 Weight and Balance: a current weight balance report, including list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification.

NOTE 2 Markings and Placards: all markings and placards for passenger information, external markings for emergency, and load limits in cargo/baggage compartments must be presented in Portuguese or bilingual. Documents titled “A320 Family External Markings Booklet” reference n° CC1300235 and “A320 Family Aircraft Passengers, Crew Placards and Illuminated Signs” reference n° CC1300236 are approved for acceptable translation in Portuguese or English.

NOTE 3 Continuing Airworthiness: service bulletins, structural repair manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is DGAC/EASA approved, are accepted by the ANAC and are considered ANAC approved. These approvals pertain to the type design only. Limitations applicable to Safe Life Airworthiness Limitation Items are provided in the A318/A319/A320/A321 Airworthiness Limitations Section (ALS) sub-parts 1-2 and 1-3 approved by the EASA. For other limitations see the DGAC/EASA-Approved Brazilian Airplane Flight Manual.


Certification Maintenance Requirements are provided in A319/A320/A321 NEO Airworthiness Limitations Section (ALS) Part 3 approved by the EASA. Limitations applicable to Damage Tolerant Airworthiness Limitation Items are provided in the A319/A320/A321 NEO Airworthiness Limitations Items document (ALS Part 2) approved by the EASA. Ageing Systems Maintenance (ASM) limitations are provided in the A319/A320/A321 Airworthiness Limitations Section (ALS) Part 4 EASA approved. Fuel Airworthiness Limitations are provided in A319/A320/A321 Fuel Airworthiness Limitations document (ALS Part 5) approved by the EASA.

NOTE 4 The ANAC approved Type Design corresponds to the EASA approved Type Design plus the following specific requirements: - Brazilian approved AFM - markings and placards in Portuguese or bilingual as NOTE 2 above. - Installation of Cabin Ozone Filter - Additional Flight Recorder Parameter: (i) pilot and copilot pitch controller position, pitch

control surface position , pilot and copilot roll controller position, aileron and spoiler surface position, rudder pedal position and rudder surface position; (ii) the auto-thrust system commanded thrust parameter; and (iii) actual thrust (N1/EPR), electronic control command thrust and thrust lever position for each engine installation. (if Mod 25591 is installed the FDR parameters are in compliance)

- ADF1 powered by emergency bus bar - Acceptance of internal configuration

- MMEL categorized; and the following operational requirements: floor emergency escape path marking [RBHA 121.310(c)(3)]; interior materials flammability [RBHA 121.312(a), RBAC/FAR 25 Amdt. 66)]; cargo/baggage compartment fire protection [RBHA 121.314 (a)(1)]; emergency locator transmitter TSO-C91a[RBHA 91.207]; Ground Proximity Warning System [RBHA 121.360].

IV- Models A321-131, A321-111 and A321-112 (Transport Category), approved 07 November 1996.

Models A321-211, A321-212, A321-213, A321-231 and A321-232 (Transport Category), approved 06 July 2007.

ENGINE A321-111: Two CFMI turbofan engines CFM 56-5B1 or CFM 56-5B1/2 (see note 5, 10, 11 & 16)

A321-112: Two CFMI turbofan engines CFM 56-5B2 (see note 10) A321-131: Two IAE turbofan engines V2530-A5 A321-211: Two CFMI turbofan engines CFM 56-5B3/P or CFM 56-5B3/2P A321-212: Two CFMI turbofan engines CFM 56-5B1 or CFM 56-5B1/2 (see

note 10, 11 & 16) A321-213: Two CFMI turbofan engines CFM 56-5B2 A321-231: Two IAE V2533-A5 turbofan engines A321-232: Two IAE V2530-A5 turbofan engines FUEL See installation manual document CFM 2026 or document IAE-0043. Kerosene: MIL-T-83133A (JP 8); Air 3405C, ASTM D 1655 (JET A/A1) or

DERD 2494. Wide cut: Air 3407, ASTM D 1655 (JET B) or DERD 2454; Air 3407(TR4),

MIL-T 5624 (JP 4) or DERD 2454. * High flash point: Air 3404, MIL-T-5624 (JP5) or DERD 2452 Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13, or

IAE V2500 “Installation and Operating Manual” IAE-0043 Sec 4.5. The above mentioned fuels and additives are also suitable for the APU.


ENGINE LIMITS AND OIL (2.2482 lb/daN) (See Note 15 & 16)

ENGINE

CFMI IAE

CFM56-5B2 CFM56-5B1

CFM56-5B1/2

CFM56-5B3 (/P only) CFM56-5B3/2P

V2530-A5 V2533-A5

Data Sheets

FAA ANAC

E37NE, E38NEEM-9604

E37NE, E38NE EM-9604

E40NE EM-9704

E40NE EM-9704

Static thrust at sea level: - Takeoff (5min.)*

(Flat rated 30°C) 13 789 daN (31 000 lb)

13 344 daN(30 000 lb)

14 234 daN (32 000 lb)

13 300 daN (29 900 lb)

14 055 daN (31 600 lb)


12 940 daN (29 090 lb)

12 940 daN(29 090 lb)

12 940 daN (29 090 lb)

11 988 daN (26 950 lb)

11 988 daN (26 950 lb)

Maximum engine speed: - N1 rpm (%) 5 200 (104) 5 200 (104) 5 200 (104) 5 650 (100) 5 650 (100) - N2 rpm (%) 15 183 (105) 15 183 (105) 15 183 (105) 14 950 (100) 14 950 (100)

Maximum gas temperature: - Takeoff (5min.)* 950ºC 950ºC 950°C 650ºC 670°C - Maximum continuous 915ºC 915ºC 915ºC 610ºC 610ºC - Starting** 725ºC 725ºC 725ºC 635ºC 635ºC

Maximum oil temperature (supply pump inlet):

- Takeoff, stabilized 140ºC 140ºC 155ºC - Transient (15 min. max.) 155ºC 155ºC 165ºC - Minimum oil pressure 13 psid 13 psid 60 psid

Approved oils see SB CFMI 79-001-0X see doc. IAE-0043

Sect. 4.9 MIL-L-23699

* 10 minutes at Takeoff thrust allowed only in case of engine failure (at Takeoff or during go-around) in accordance with the engine TCDS.

** 4 consecutive cycles of 2 minutes each. AUXILIARY POWER UNIT

Garrett Airesearch GTCP 36-300(A) (Specification 31-5306B). - Approved oils: see Garrett report GT-7800. APIC APS 3200 (Mod. 22562 or mod. 35864, option) (Specification ESR 0802, Rev. A) -Approved oils: MIL-L-7808, MIL-L-23699 or DERD 2487.

Allied Signal 131-9[A] (Mod. 25888, option) (Specification4900 M1E 03 19 01). -Approved oils: according to Model Specification 31-12048A-3A AIRSPEED Maximum operating (VMO/MMO): 350 kt/0.82 LIMITS Design maneuvering (VA): Refer to Chapter 2.0 of the AFM. (IAS, unless Flaps extended (VFE): Config. Slats/Flaps(°) VFE (kt) otherwise stated) Intermediate approach

Takeoff 1 18/0

18/10 230** 215**

Takeoff and approach 2 22/14 205 215*

Takeoff, approach and landing 3 22/21 195 Landing Full 27/25 190 * See note 7. ** see note 12. L. G. extended (VLE) 280 kt /Mach 0.67 L. G. operation (VLO) - Extension: 250 kt - Retraction: 220 kt Tyre limit (ground speed) 195.5 kt (225 mph)


CENTER OF GRAVITY RANGE

See ANAC approved Airplane Flight Manual.

DATUM Station 0 (100 inches forward of fuselage nose). MEAN AERODYNAMIC CHORD 165.10 inches (leading edge of MAC: Sta. 700.85 inches). LEVELING MEANS Clinometer on the cabin seat track rails. MAXIMUM WEIGHTS A321-131

VARIANT 000 BASIC

002 MOD 24178

003 MOD 24899

004 MOD 24308

Max.Takeoff Weight 83 000 kg 83 000 kg 85 000 kg 78 000 kg Max. Landing Weight 73 500 kg 74 500 kg 74 500 kg 73 500 kg Max. Zero Fuel Weight 69 500 kg 70 500 kg 70 500 kg 69 500 kg Minimum Weight 47 500 kg 47 500 kg 47 500 kg 47 500 kg

VARIANT 006

MOD 26600 007

MOD 26888 008

MOD 30334

Max.Takeoff Weight 78 000 kg 80 000 kg 89 000 kg Max. Landing Weight 74 500 kg 73 500 kg 75 500 kg Max. Zero Fuel Weight 70 500 kg 69 500 kg 71 500 kg Minimum Weight 47 500 kg 47 500 kg 47 500 kg

A321-111/-112

VARIANT 000

BASIC 002

MOD 24178 003

MOD 24899 004

MOD 24308 Max.Takeoff Weight 83 000 kg 83 000 kg 85 000 kg 78 000 kg Max. Landing Weight 73 500 kg 74 500 kg 74 500 kg 73 500 kg Max. Zero Fuel Weight 69 500 kg 70 500 kg 70 500 kg 69 500 kg Minimum Weight 47 500 kg 47 500 kg 47 500 kg 47 500 kg

VARIANT 005

MOD 25649 006

MOD 26600 007

MOD 26888 008


A321-211/231

VARIANT 000 BASIC

001 MOD 28960

002 MOD 28721

003 MOD 31613


VARIANT 004

MOD 31614 005

MOD 27553 006

MOD 31616 011



A321-212/213/232

VARIANT 000

BASIC 001

MOD 28960 002

MOD 28721 003


VARIANT 004

MOD 31614 005

MOD 31615 006

MOD 31616 007


VARIANT 008

MOD 31618 009

MOD 31619 010

MOD 31321 011


MINIMUM FLIGHT CREW 2 pilots. MAXIMUM NUMBER OF PASSENGERS

220

MAXIMUM BAGGAGE Cargo Compartment Maximum Load (kg) - Forward: 5 670 - Aft: 5 670 - Rear (Bulk): 1 497 MAXIMUM BAGGAGE (Cont.) For the positions and the loading conditions authorized in each

position (references of containers, pallets and associated weights) see Weight and Balance Manual, ref. 00 E 080 A 0001 / C1S Chapter 1.10.

FUEL CAPACITY (0.8 kg/l)

TANK

3 TANK AIRPLANE 4 or 5 TANK AIRPLANE (*) (**)

Usable fuel liters (kg)

Unusable fuel liters

(kg)

Usable fuel liters (kg)

Unusable fuel liters (kg)

WING 15 500 (12 400)

22.6 (18)

15 500 (12 400)

22.6 (18)

CENTER 8 200 (6 560)

23.2 (18.6)

8 200 (6 560)

23.2 (18.6)

ACT (*) (**)

2 900 or 2 992 / 5 984 ** (2 320) or (2 393 / 4 786) **

17 / 34 (13.6 / 27.2)

TOTAL 23 700 (18 960)

45.8 (36.6)

26 600 or 26 692 / 29 684 ** (21 280) or (21 353 / 23 746) **

62.8 / 79.8 (50.2 / 63.8)

* See notes 13 and 14 on additional center tanks (ACT) ** 1 ACT high pressure system, 2 900 liters on A321-200, 1 / 2 ACT low pressure system 2992/5984

liters on A321-200


HYDRAULIC FLUIDS Type IV or V - Specification NSA 30.7110 TIRES See SB A320-32-1007 MAXIMUM OPERATING ALTITUDE 11 918 m (39 100 ft)

12 100 m (39 800 ft) if modification 30748 is embodied IMPORT REQUIREMENTS A Brazilian Certificate of Airworthiness may be issued on the basis of

on a EASA Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement:

“The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate no. 9607 and in condition for safe operation”. The ANAC Report H.10-1530-02, dated 06 July 2007 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See note 4)

CERTIFICATION BASIS RBHA 25 Airworthiness Requirements – Transport Airplane Category

– corresponding to FAR Part 25, including amendments 25-1 through 25-56 effective 31 Jan. 83, plus the following:

1. JAR 25.107(e)(1)(iv) - VLOF margins;

2. Special Conditions (SC), Harmonization Conditions (HC) and Experience Related Conditions (EC):

RBHA 25 Airworthiness Requirements – Transport Airplane Category – corresponding to FAR Part 25, including amendments 25-1 through 25-56 effective 31 Jan. 83, plus the following:

1. JAR 25.107(e)(1)(iv) - VLOF margins; 2. Special Conditions (SC), Harmonization Conditions (HC) and

Experience Related Conditions (EC): - EC-S30-Autoflight System - HC-A4.5-Brake Roll Conditions - HC-A4.6-Speed Control Device - HC-S23-Standby Gyroscopic Horizon - HC-S24-VMO/MMO Warning (Setting) - HC-S72-Flight Recorder - SC-A1-Interaction of Systems and Structure (CRI A3001) - SC-A2-Stalling Speed for Structural Design (CRI A3002) - SC-A2.2.2-Design Manoeuvre Requirement - SC-A2.2.3-Design Dive Speed - SC-E1-Resistance to Fire Terminology (CRI E3005) - SC-E3-Exit Configuration (CRI E3001) - SC-F1-Stalling and Scheduled Operating Speeds (CRI F3001) - SC-F3-Cockpit Control - Motion and Effect of Cockpit Control - SC-F4-Static Longitudinal Stability - SC-F6-Static Directional and Lateral Stability - SC-F7-Flight Envelope Protection - SC-F8-Normal Load Factor Limiting - SC-F9-Dual Control System - SC-F10-Accelerate-Stop Distance (CRI F3002) - SC-G17-Operational Proving Flights (France) - SC-P1-FADEC (CRI P3001) - SC-S11-Limit Pilot Forces and Torques - SC-S33-Autothrust System - SC-S52-Operation without Normal Electrical Power


- SC-S54-Circuit Protective Devices- SC-S74-Abnormal Attitudes - SC-S75-Lightning Protection (Indirect Effects)

- SC-S76-Effect of External Radiations upon Aircraft Systems- SC-S77-Integrity of Control Signal - SC-S79-Brakes Requirements Qualification and Testing

(CRI SE3003) - E-3002: Reclassification of doors 2 & 3 to type III (optional)

3. Equivalent Safety Demonstrations: - FAR 25.783(f)-Passenger Doors and Bulk Cargo Doors (CRI SM

3001/3002/3004) - FAR 25.933(a) – Reversing Systems (CRI P3008)

4. Extended Range Twin Engine Airplane Operations Technical Conditions: - CRI G3006-ETOPS - CRI G3007-ETOPS - One Engine Inoperative Cruise Speed - AMJ 120-42/IL 20- - SC G-1006: ETOPS

5. Precision Approach and Landing: - JAR AWO Change 1-All Weather Operation

6. AIRBUS elect-to-comply documents: - NPA 25.BDG.244-Accelerate-Stop Distances and Associated

Performance 7. Noise Standard:

- RBHA 36 (corresponding to ICAO Annex 16 Vol. I). 8. Fuel Venting and Exaust emission:

- RBHA 34 (corresponding to ICAO Annex 16 Vol. II). MOD 160023: Special Conditions SC F-16 Static directional and lateral stability

A318 SC F-5001 Stalling and scheduled operating speeds A318 SC F-5004 Static Longitudinal Stability and Low energy awareness A318 SC A-5003 Design Dive Speed Vd

MOD 158217: Special Condition EASA SC CRI SC E-34: Installation of Inflatable Restraints

REQUIRED EQUIPMENT Equipment approved for installation is listed in the following Certification Standard Equipment List: - 00 E 000 A 0006/C1S (A321-112); - 00 E 000 A 0007/C1S (A321-111); - 00 E 000 A 0004/C0S (A321-131);

REQUIRED EQUIPMENT (Cont.) - 00 E 000 A 0211/C0S (A321-211);- 00 E 000 A 0231/C0S (A321-231); - 00 E 000 A 0212/C0S (A321-212); - 00 E 000 A 0213/C0S (A321-213); - 00 E 000 A 0232/C0S (A321-232); Cabin furnishings, equipment and arrangement shall be in conformance to the following specifications: - 00 D 252 K 0004 / C01 for cabin seats; and - 00 D 252 K 0019 / C01 for galleys.

SIGNIFICANT CHANGES Model A321-231 & A321-211 can be modified as per Mod 160023

“Sharklet Installation” EASA approved in July 30, 2013. According to procedures established under RBAC 21.101 the Certification Basis is updated according to EASA application date April 8, 2010: as establish in EASA CRI A-0001-001, issue 2, 06/09/2012.


NOTES: NOTE 1 Weight and Balance: note 1 of the A-320 series is also applicable to the A321 series. NOTE 2 Markings and Placards: note 2 of the A-320 series is also applicable to the A321 series. NOTE 3 Continuing Airworthiness: note 3 of the A-320 series is also applicable to the A321 series. NOTE 4 Note 4 of the A-320 series is also applicable to the A321 series. NOTE 5 A321-111CFM 56-5B1 engine can be intermixed with CFM 56-5B1/2 engine (mod 24404)

on the same aircraft (AFM supplement). NOTE 6 DOOR 2 and/or DOOR 3 may be derated to Type III. NOTE 7 If FWC Standard D2 and FAC Standard BAM 0510 are fitted on A321 aircraft, VFE speed

in Conf. 2 is increased from 205 kt to 215 kt (as identified by speed limitation placard installed by modification 24641).

NOTE 8 Autoflight certification: If the following modifications are embodied, the aircraft is qualified

for the applicable precision approach: Engines Precision approach category Modification Nr.

CFM Cat. III 24064 Cat. IIIB 25199 Cat. II 24173 and 22853

IAE Cat. III 24066 Cat. IIIB 25200


extended range twin engine airplane operations are contained in the document AI/EA 4000. Certificated models are A321-111/-112/-131

NOTE 10 If modification 25800 is embodied on models with CFM-5B engines, the engine performance

is improved. The engine denomination changes to /P. The modification is currently applicable for :

- A 321-111 : CFM 56-5B1 (SAC) which changes to CFM 56-5B1/P - A 321-112 : CFM 56-5B2 (SAC) which changes to CFM 56-5B2/P - A 321-212 : CFM 56-5B1 (SAC) which changes to CFM 56-5B1/P

CFM 56-5B/"non-P" engine can be intermixed with CFM 56-5B/P engine on the same aircraft. NOTE 11 If modification 26610 is embodied on models with CFM-5B/2 (DAC) engines, the engine

performance and gaseous emission levels are improved. The engine denomination changesto /2P. The modification is currently applicable for :

A 321-111 : CFM 56-5B1/2 (DAC) which changes to CFM 56-5B1/2P (DAC II C) A 321-212 : CFM 56-5B1/2 (DAC) which changes to CFM 56-5B1/2P (DAC II C)

NOTE 11 (Cont.)

CFM 56-5B/2 "non P" (DAC) engine can be intermixed with CFM 56-5B/2P (DAC II C) engine on the same aircraft (AFM supplement). CFM 56-5B/P or /"non-P" (SAC) engine can be intermixed with CFM 56-5B/2P (DAC II C)engine on the same aircraft (AFM supplement).

NOTE 12 On the series A321-200, Weight Variant 001, 002 & 011, VFE speed in Configuration 1 is

increased from 230 to 235 kt, and in Configuration 1+F increased from 215 to 225 kt (as identified by speed limitation placard installed by modification 28960 or 28721).


NOTE 13 On the series A321-200, one Additional Center Tank (ACT) in bulk version is defined by modification 25453 (high pressure system). Its approval together with structural and system provisions is subject of Major Change E2-001 (compliance to CRI P9).

NOTE 14 On the series A321-200, one or two Additional Center Tanks (ACT) in bulk version are defined

by modification 30422 (low pressure system). Their approval together with structural and system provisions is subject of Major Change E2-002 (compliance to CRI P9).

NOTE 15 NOTE 15 (cont.)

Introduction of CFM56 5Bx/3 “Tech Insertion” engine is done through embodiment of modification 37147. This modification is only applicable on CFM56 5Bx /P SAC engines. If modification 37147 is embodied on models with CFM-5B engines, the engine denomination changes to /3. The modification is currently applicable for: A321-111: CFM 56-5B1 (SAC) which changes to CFM 56-5B1/3 A321-112: CFM 56-5B2 (SAC) which changes to CFM 56-5B2/3 A321-211: CFM 56-5B3 (SAC) which changes to CFM 56-5B3/3 A321-212: CFM 56-5B1 (SAC) which changes to CFM 56-5B1/3 A321-213: CFM 56-5B2 (SAC) which changes to CFM 56-5B2/3 Modification 37147 has been demonstrated as having no impact on previously certified noise levels. CFM56 5Bx/3 engine can be intermixed with CFM56 5Bx/P engine under considerations as prescribes in modification 38573.

NOTE 16 From 31 March 2008, there is no longer:

- any CFM56-5B1 non /P in field or in production. - any CFM56-5B1/2 non /P in field or in production.

NOTE 17 For all A321 models but:

- A321-211 CFM56-5B3/P, - A321-211 CFM56-5B3/P mod 27772, - A321-211 CFM56-5B3/2P mod 27727 with or without mod 27772, - A321-111 CFM56-5B1/P, - A321-111 CFM56-5B1/2P mod 26610 with or without mod 27772, - A321-112 CFM56-5B2/P, - A321-112 CFM56-5B2/P mod 27772, - A321-111 CFM56-5B1/P mod 27772, compliance with ICAO Annex 16 chapter 4 requirement is achieved when modification 36521 is embodied.

NOTE 18 RNP AR certification: Major Change (150373) “Airplane approved to approach RNP AR

0.3 e missed approach RNP AR 1.0.” “Airplane is approved to approach RNP AR less than 0.3 and missed approach less than 1.0 when approach procedures are not established to avoid obstacles or terrain”. “The airplane operational approval for RNP AR less than 0.3 (based on Airbus RNP AR ACD) or missed approach less than 1.0 when those procedures are required to avoid obstacles or terrain, is conditioned to the use of operational mitigation measures to be evaluated and approved for each procedure/operator/aircraft model combination”.

V- Models A319-111, A319-112, A319-113 and A319-114 (Transport Category), approved 07 November 1996. Models A319-131 and A319-132 (Transport Category), approved 18 January 1999.

Models A319-115 and A319-133 (Transport Category), approved 02 March 2005.


ENGINE A319-111 Two CFMI turbofan engines CFM 56-5B5. (see notes 10, 11 & 12) A319-112 Two CFMI turbofan engines CFM 56-5B6 or CFM 56-5B6/2. (see note

10, 11 & 12) A319-113 Two CFMI turbofan engines CFM 56-5A4. A319-114 Two CFMI turbofan engines CFM 56-5A5 A319-115 Two CFMI turbofan engines CFM 56-5B7 (see notes 10, 11 & 12) A319-131 Two IAE turbofan engines V2522-A5 A319-132 Two IAE turbofan engines V2524-A5 A319-133 Two IAE turbofan engines V2527M-A5 FUEL See installation manual document CFM 2026 or document IAE-0043. Kerosene

: MIL-T-83133A (JP 8); Air 3405C, ASTM D 1655 (JET A/A1) or DERD 2494.

Wide cut: ASTM D 1655 (JET B) or DERD 2454; Air 3407(TR4), MIL-T 5624 (JP 4)* or DERD 2454.

High flash point: Air 3404, MIL-T-5624 (JP5) or DERD 2452 Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13, or IAE

V2500 “Installation and Operating Manual” IAE-0043 Sec 4.5. The above mentioned fuels and additives are also suitable for the APU.

ENGINE LIMITS AND OIL (2.2482 lb/daN) (See Note 10) a) CMI Engines:

ENGINE CFM56-5A4 CFM56-5A5 CFM56-5B5 CFM56-5B6

CFM56-5B6/2 CFM56-5B7

Data Sheets

FAA ANAC

E28NE EM-9604

E28NE EM-9604

E37NE,E38NEEM-9604

E37NE,E38NE EM-9604

E37NE EM-9604

Static thrust at sea level - Takeoff (5min.)* (Flat rated 30°C)

9 786 daN (22 000 lb)

10 453 daN (23 500 lb)

9 786 daN (22 000 lb)

10 453 daN (23 500 lb)

12 010 daN(27 000 lb)

- Maximum continuous (Flatrated 25ºC)

9 195 daN (20 670 lb)

9 195 daN (20 670 lb)

9 008 daN (20 250 lb)

9 008 daN (20 250 lb)

10 840 daN(24 370 lb)

Maximum engine speed - N1 rpm (%)

5 100 (102)

5 100 (102)

5 200 (104)

5 200 (104)

5 200 (104)

- N2 rpm (%) 15 183 (105) 15 183 (105) 15 183 (105) 15 183 (105) 15 183 (105)Maximum gas temperature - Takeoff (5min.)*

890ºC

890ºC

950ºC

950ºC

950ºC

- Maximum continuous 855ºC 855ºC 915ºC 915ºC 915ºC - Starting** 725ºC 725ºC 725ºC 725ºC 725ºC Maximum oil temperature (supply pump inlet) - Takeoff, stabilized

140ºC

140ºC

140ºC

140ºC

140ºC - Transient (15 min. max.) 155ºC 155ºC 155ºC 155ºC 155ºC Minimum oil pressure 13 psid 13 psid 13 psid 13 psid 13 psid

Approved oils see SB CFMI 79-001-0X * 10 minutes at Takeoff thrust allowed only in case of engine failure (at Takeoff or during go-around)

in accordance with the engine TCDS. ** 4 consecutive cycles of 2 minutes each.

b) IAE Engines:

ENGINE V2522-A5 V2524-A5 V2527M-A5 Data

Sheets FAA

ANAC E40NE

EM 9704 E40NE

EM 9704 E40NE

EM 9704


Static thrust at sea level: - Takeoff (5min.)*

(Flat rated 30°C) - Maximum continuous

(Flat rated 25ºC)

10 249daN (23 040 lb) 8 540 daN (19 200 lb)

10 889 daN (24 480 lb) 8 540 daN (19 200 lb)

11 031 daN (24 800 lb) 9 893 daN (22 240 lb)

Maximum engine speed: - N1 rpm (%) - N2 rpm (%)

5 650 (100)

14 950 (100)

5 650 (100)

14 950 (100)

5 650 (100)

14 950 (100) Maximum gas temperature:

- Takeoff (5min.)* - Maximum continuous - Starting**

620ºC 610ºC 650ºC

620ºC 610ºC 650ºC

645ºC 610ºC 650ºC


- Takeoff, stabilized - Transient (15 min. max.)

Minimum oil pressure

155ºC 165ºC 60 psig



Approved oils see Doc. IAE-0043

Sect. 4.9 (MIL-L-23699) * 10 minutes at Takeoff thrust allowed only in case of engine failure (at Takeoff or during go-around) in accordance with the engine TCDS. ** 4 consecutive cycles of 2 minutes each.

AUXILIARY POWER UNIT Garrett Airesearch GTCP 36-300(A) (Specification 31-5306B).

- Approved oils: see Garrett report GT-7800. APIC APS 3200 (Mod. 22562 or 35864, option) (Specification ESR 0802, Rev. A) - Approved oils: MIL-L-7808, MIL-L-23699 or DERD 2487.

Allied Signal 131-9[A] (Mod. 25888, option) (Specification 4900 M1E 03 19 01) - Approved oils: according to Model Specification 31-12048A-3A.

AIRSPEED LIMITS Maximum operating (VMO/MMO): 350 kt/0.82 (IAS, unless otherwise stated) Design maneuvering (VA): Refer to Chapter 2.0 of the AFM. Flaps extended (VFE): Config. Slats/

Flaps(°) VFE (kt)

Intermediate approach Take-off

1 18/0 18/10*

230 215

Take-off and approach 2 22/15 200 Take-off, approach and landing 3 22/20 185 Landing Full 27/40 177 * Auto flap retraction at 210 kt in Takeoff configuration.

L. G. extended (VLE) 280 kt/ Mach 0.67 L. G. operation (VLO) - Extension: 250 kt - Retraction

Tire limit (ground speed) 220 kt 195.5 kt (225 mph)

CENTER OF GRAVITY RANGE See DGAC/EASA approved Brazilian Airplane Flight Manual. DATUM Station 0 (100 inches forward of fuselage nose). MEAN AERODYNAMIC CHORD 165.10 inches (leading edge of MAC: Sta. 700.85 inches). LEVELING MEANS Clinometer on the cabin seat track rails.


MAXIMUM WEIGHTS VARIANT 000

BASIC 001

MOD 25328 002*

MOD 27112 005

MOD 28136Max.Takeoff Weight 64 000 kg 70 000 kg 75 500 kg 70 000 kg Max. Landing Weight 61 000 kg 61 000 kg 62 500 kg 62 500 kg Max. Zero Fuel Weight 57 000 kg 57 000 kg 58 500 kg 58 500 kg Minimum Weight 35 400 kg 35 400 kg 35 400 kg 35 400 kg * See Note 7.

MINIMUM FLIGHT CREW 2 pilots.

MAXIMUM NUMBER OF PASSENGERS

145

MAXIMUM BAGGAGE Cargo Compartment Maximum Load (kg) - Forward: 2 268 - Aft: 3 021 - Rear (Bulk): 1 497 For the positions and the loading conditions authorized in each position

(references of containers, pallets and associated weights) see Weight and Balance Manual, ref. 00 J 080 A 0001 / C1S Chapter 1.10.

FUEL CAPACITY (0.8 kg/l)

3 – Tank Airplane

TANK Usable fuel - liters (kg) Unusable fuel - liters (kg) WING 15 609 (12 487) 58.9 (47.1)

CENTER 8 250 (6 600) 23.2 (18.6) TOTAL 23 859 (19 087) 82.1 (65.7)

4 to 9 – Tank Airplane

TANK Usable fuel - liters (kg) Unusable fuel - liters (kg) TOTAL 3-TANK

AIRPLANES23 859 (19 087) 82.1 (65.7)

ACT 1 3 121 (2 497) 17 (13.6) TOTAL 4-TANK

AIRPLANES26 980 (21 584) 99.1 (79.3)

ACT 2 3 121 (2 497) 17 (13.6) TOTAL 5-TANK

AIRPLANES30 101(24 081) 116.1 (92.9)

ACT 3 2 186 (1 749) 22 (17.6) TOTAL 6-TANK

AIRPLANES

32 287(25 830) 138.1 (110.5)

ACT 4 2 186 (1 749) 22 (17.6) TOTAL 7-TANK

AIRPLANES34 473(25 579) 160.1 (128.1)

ACT 5 3 046 (2 437) 12 (9.6) TOTAL 8-TANK

AIRPLANES37 519 (30 016) 172.1(137.7)

ACT 6 3 121 (2 497) 17 (13.6) TOTAL 40 640 (32 513) 189.1 (151.3)


9-TANK AIRPLANES

HYDRAULIC FLUIDS Type IV or Type V - Specification NSA 30.7110. TYRES See SB A320-32-1007. MAXIMUM OPERATING ALTITUDE

11 918 m (39 100 ft) 12100 m (39800ft) if modification 30748 is embodied

IMPORT REQUIREMENTS A Brazilian Certificate of Airworthiness may be issued on the basis of

on a EASA Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement: “The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate no. 9607 and in condition for safe operation”. The ANAC Report H.10-1530-02, dated 06 July 2007 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See note 4)

CERTIFICATION BASIS RBHA 25 Airworthiness Requirements – Transport Airplane Category – corresponding to 14 CFR Part 25, including amendents 25-1 through 25-56 effective 31 Jan. 83, plus the following: JAR 25.107(e)(1)(iv) - VLOF margins; Special Conditions (SC), Harmonization Conditions (HC) and Experience Related Conditions (EC):

- EC-S30-Autoflight System - EC-S54-Circuit Protective Devices - HC-A4.5-Braked Roll Conditions

- HC-A4.6-Speed Control Device- HC-S23-Standby Gyroscopic Horizon - HC-S24-VMO/MMO Warning (Setting) - HC-S72-Flight Recorder - SC-A1-Interaction of Systems and Structure (CRI A4001) - SC-A2-Stalling Speeds for Structural Designs (CRI A4002) - SC-A2.2.2-Design Manoeuvre Requirement - SC-A2.2.3-Design Dive Speed - SC-E1-Resistance to Fire Terminology (CRI E4005) - SC-F1-Stalling and Scheduled Operating Speeds (CRI F4001) - SC-F3-Cockpit Control - Motion and Effect of Cockpit Control - SC-F4-Static Longitudinal Stability - SC-F6-Static Directional and Lateral Stability - SC-F7-Flight Envelope Protection - SC-F8-Normal Load Factor Limiting - SC-F9-Dual Control System - SC-F11-Accelerate-Stop Distances and Related Performances,

Worn Brakes (CRI F4012) - SC-G17-Operational Proving Flights (France) - SC-P1-FADEC (CRI P4001) - SC-S11-Limit Pilot Forces and Torques


- SC-S33-Autothrust System- SC-S52-Operation without Normal Electrical Power - SC-S74-Abnormal Attitudes - SC-S75-Lightning Protection (Indirect Effects) - SC-S76-Effect of External Radiations up on Aircraft Systems - SC-S77-Integrity of Control Signal - SC-S79-Brakes Requirements, Qualification and Testing

(CRI SE4003) - CRI F-8 Takeoff/Go Around Thrust – Third Rating (applicable to

A319-115/-133) Equivalent Safety Demonstrations:

- RBHA/14 CFR Part 25.783(f)-Passenger Doors and Bulk Cargo Doors (CRI SM4004);

- RBHA/14 CFR Part 25.807(c)-Passengers Emergency Exits (CRI E4001); and

- RBHA/14 CFR Part 25.933(a)-Reversing Systems (CRI P4008). Extended Range Twin Engine Airplane Operations Technical Conditions:

- CRI G4006-ETOPS; - CRI G4007-ETOPS - One Engine Inoperative Cruise Speed; and - AMJ 120-42/IL 20-. - SC G-1006: ETOPS

Precision Approach and Landing: - JAR AWO Change 1-All Weather Operation; and - CRI SE4005-Equivalent Safety Finding for JAR AWO 313 -

Minimum Approach Break-off Height. Noise Standard:

- RBHA/FAR 36 (corresponding to ICAO Annex 16 Vol. I). Fuel Venting and Exaust emission:

- RBHA/FAR 34 (corresponding to ICAO Annex 16 Vol. II). MOD 160500: Special Conditions

SC F-16 Static directional and lateral stability A318 SC F-5001 Stalling and scheduled operating speeds A318 SC F-5004 Static Longitudinal Stability and Low energy awareness A318 SC A-5003 Design Dive Speed Vd

MOD 158217: Special Condition EASA SC CRI SC E-34: Installation of Inflatable Restraints

REQUIRED EQUIPMENT Equipment approved for installation is listed in the following Certification Standard Equipment List: - 00 J 000 A 0012/C0S (A319-111); - 00 J 000 A 0004/C0S (A319-112); - 00 J 000 A 0113/C0S (A319-113);

- 00 J 000 A 0114/C0S (A319-114); - 00 J 000 A 0115/C0S (A319-115); - 00 J 000 A 0131/C0S (A319-131); - 00 J 000 A 0132/C0S (A319-132); and - 00 J 000 A 0133/C0S (A319-133)

Cabin furnishings, equipment and arrangement shall be in conformance to the following specifications: - 00 D 252 K 0004 / C01 for cabin seats; and - 00 D 252 K 0019 / C01 for galleys.

NOTES: NOTE 1 Weight and Balance: note 1 of the A-320 series is also applicable to the A319 series. NOTE 2 Markings and Placards: note 2 of the A-320 series is also applicable to the A319 series.


NOTE 3 Continuing Airworthiness: note 3 of the A-320 series is also applicable to the A319 series NOTE 4 Note 4 of the A-320 series is also applicable to the A319 series. NOTE 5 Note 5 (Cont.)

Autoflight certification: If the following modifications are embodied, the aircraft is qualified for the applicable precision approach:

Engines Precision approach category Modification Nr. CFM Cat. IIIB 25469 or 26968 IAE Cat. IIIB 26717


extended range twin engine airplane operations are contained in the document AI/EA 4000. Certificated models are A319-111/-112/-113/-114/-115/-131/-132/-133

NOTE 7 If Mod. 27770 is incorporated, aircraft is certificated to operate with weight variants 002 or

000. (Change of weight variant in service via Service Bulletin). NOTE 8 If Mod. 28471 or 28722 is incorporated, the A319-111, A319-112, A319-115, A319-131,

A319-132 and A319-133 performance shall comply with IAC 3502-121-0888 requirements for landing on the Santos Dumont Airport porous friction course runway in wet conditions.

NOTE 9 If Mod. 25615 is incorporated, the A319-115/-131/-132/-133 are approved for operations

at airports up to 4 298 m (14 100 ft). NOTE 10 If modification 25800 is embodied on models with CFM-5B engines, the engine

performance is improved. The engine denomination changes to /P. The modification is currently applicable for: A319-111: CFM 56-5B5 (SAC) which changes to CFM 56-5B5/P A319-112: CFM 56-5B6 (SAC) which changes to CFM 56-5B6/P A319-112: CFM 56-5B6/2 (DAC) which changes to CFM 56-5B6/2P A319-115: CFM 56-5B7 (SAC) which changes to CFM 56-5B7/P CFM 56-5B/"non-P" engine can be intermixed with CFM 56-5B/P engine on the same aircraft.

NOTE 11 Introduction of CFM56-5Bx/3 “Tech Insertion” engine is done through embodiment of

modification 37147.

This modification is only applicable on CFM56 5Bx /P SAC engines.

If modification 37147 is embodied on models with CFM-5B engines, the engine denomination changes to /3.

The modification is currently applicable for: A319-111: CFM 56-5B5 (SAC) which changes to CFM 56-5B5/3 A319-112: CFM 56-5B6 (SAC) which changes to CFM 56-5B6/3 A319-115: CFM 56-5B7 (SAC) which changes to CFM 56-5B7/3

Modification 37147 has been demonstrated as having no impact on previously certified noise levels.

CFM56 5Bx/3 engine can be intermixed with CFM56 5Bx/P engine under considerations as prescribes in modification 38573.

NOTE 12 From 31 March 2008, there is no longer


- any CFM56-5B5 non /P in field or in production. - any CFM56-5B6 non /P in field or in production. - any CFM56-5B7 non /P in field or in production. - any CFM56-5B6/2 non /P in field or in production

NOTE 13 For all A319 models compliance with ICAO Annex 16 chapter 4 requirements are achieved

when modification 36521 is embodied. NOTE 14 RNP AR certification: Major Change (150372) “Airplane approved to approach RNP AR

0.3 e missed approach RNP AR 1.0.” “Airplane is approved to approach RNP AR less than 0.3 and missed approach less than 1.0 when approach procedures are not established to avoid obstacles or terrain”. “The airplane operational approval for RNP AR less than 0.3 (based on Airbus RNP AR ACD) or missed approach less than 1.0 when those procedures are required to avoid obstacles or terrain, is conditioned to the use of operational mitigation measures to be evaluated and approved for each procedure/operator/aircraft model combination”.

VI- Models A318-111, A318-112, A318-121 and A318-122 (Transport Category), approved 15 March 2011.

ENGINE A318-111 Two CFMI turbofan engines CFM 56-5B8/P (see note 7) A318-112 Two CFMI turbofan engines CFM 56-5B9/P (see note 7) A318-121 Two Pratt & Whitney turbofan engines PW6122A A318-122 Two Pratt & Whitney turbofan engines PW6124A

FUEL See installation manual document CFM 2026 or document PWA-7707. Kerosene

: MIL-T-83133A (JP 8); Air 3405C, ASTM D 1655 (JET A/A1) or DERD 2494.

Wide cut: ASTM D 1655 (JET B) or DERD 2454; Air 3407(TR4), MIL-T 5624 (JP 4)* or DERD 2454.

High flash point: Air 3404, MIL-T-5624 (JP5) or DERD 2452 Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13, or Pratt

& Whitney Service Bulletin 2016. The above mentioned fuels and additives are also suitable for the APU. *Note: JP4 fuel is not suitable for double annular combustor (DAC) engines.

ENGINE LIMITS AND OIL (2.2482 lb/daN) a) CFM Engines:

ENGINE CFM56-5B8/P CFM56-5B9/P Data

Sheets FAA

ANAC E37NE, E38NE

EM-9604 E37NE, E38NE

EM-9604 Static thrust at sea level

- Takeoff (5min.)* (Flat rated 30°C)

9 608 daN (21 600 lb)

10 364 daN (23 300 lb)

- Maximum continuous (Flat rated 25ºC) 8 478 daN (19 060 lb)

9 008 daN (20 250 lb)

Maximum engine speed - N1 rpm (%)

5 200 (104)

5 200 (104)

- N2 rpm (%) Maximum gas temperature

- Takeoff (5min.)*

950ºC

950ºC - Maximum continuous 915ºC 915ºC

- Starting** 725ºC 725ºC


Maximum oil temperature (supply pump inlet)- Takeoff, stabilized

140ºC

140ºC

- Transient (15 min. max.) 155ºC 155ºC Minimum oil pressure 13 psid 13 psid

Approved oils see SB CFMI 79-001-0X * 10 minutes at Takeoff thrust allowed only in case of engine failure (at Takeoff or during go-around)

in accordance with the CFMI engine TCDS. * 5 min TO time limit can be extended to 10 min for one engine inoperative. For other engine

limitations, see the relevant engine TCDS. ** 4 consecutive cycles of 2 minutes each.

b) Pratt & Whitney Engines:

ENGINE PW6122A PW6124A Data

Sheets FAA

ANAC E00064EN

EM-2011T02 E00064EN

EM-2011T02 Static thrust at sea level:

- Takeoff (5min.)* (Flat rated 30°C)


9 830 daN (22 100 lb)

9 030 daN (20 300 lb)

10 587 daN (23 800 lb) 9 297 daN (20 900 lb)

Maximum engine speed: - N1 rpm (%) - N2 rpm (%)

6350

18850

6350

18850 Maximum gas temperature:

- Takeoff (5min.)* - Maximum continuous - Starting**

760ºC 727ºC 760ºC

760ºC 727ºC 760ºC


- Takeoff, stabilized - Transient (15 min. max.)

Minimum oil pressure



Approved oils See PW SB 238 * The 5 minute takeoff time limit may be extended to 10 minutes for one engine(s) inoperative or

shutdown of a multiengine aircraft. ** 4 consecutive cycles of 2 minutes each.


AUXILIARY POWER UNIT APIC APS 3200 (Specification ESR 0802, Rev. A). APU APIC installation defined by MOD 22562 or 35864. Approved oils: in conformance to MIL-L-7808, MIL-L-23699 or DERD 2487.

AlliedSignal 131-9[A] (Specification 4900 M1E 03 19 01) The APU AlliedSignal installation is defined by MOD 25888. Approved oils: according to Model Specification 31-12048A-3A.

AlliedSignal 131-9[A] (Specification 4900 M1E 03 19 01). The APU AlliedSignal installation is defined by MOD 25888. Approved oils: according to Model Specification 31-12048A-3A. Note: For A318 models, the APU APIC APS 3200 (Mod 35864) is the production standard from MSN 2686 and on.

AIRSPEED LIMITS Maximum operating (VMO/MMO): 350 kt/0.82 (IAS, unless otherwise stated) Design maneuvering (VA): Refer to Chapter 2.0 of the AFM. Flaps extended (VFE): Config. Slats/

Flaps(°) VFE (kt)


1 18/0 18/10*

230 215

Take-off and approach 2 22/15 200 Take-off, approach and landing 3 22/20 185 Landing Full 27/40 177 * Auto flap retraction at 210 kt in Takeoff configuration. AIRSPEED LIMITS Maximum operating (VMO/MMO): 350 kt/0.82 (IAS, unless otherwise stated) Design maneuvering (VA): Refer to Chapter 2.0 of the AFM. Flaps extended (VFE): Config. Slats/

Flaps(°) VFE (kt)


1 18/0 18/10*

230 215

Take-off and approach 2 22/15 200 Take-off, approach and landing 3 22/20 185 Landing Full 27/40 177 * Auto flap retraction at 210 kt in Takeoff configuration. L. G. extended (VLE) 280 kt/ Mach 0.67 L. G. operation (VLO) - Extension: 250 kt - Retraction

Tire limit (ground speed) 220 kt 195.5 kt (225 mph)

CENTER OF GRAVITY RANGE See DGAC/EASA approved Brazilian Airplane Flight Manual. DATUM Station 0 (100 inches forward of fuselage nose). MEAN AERODYNAMIC CHORD 165.10 inches (leading edge of MAC: Sta. 700.85 inches). LEVELING MEANS Clinometer on the cabin seat track rails.


MAXIMUM WEIGHTS

VARIANT 000 BASIC

001 MOD 31672

002 MOD 31673

003 MOD 31674



005 MOD 31676

006 MOD 33235

007 MOD 33126


VARIANT 008

MOD 33128

Max.Takeoff Weight 64 000 kg Max. Landing Weight 56 000 kg Max. Zero Fuel Weight 53 000 kg Minimum Weight 34 500 kg

MINIMUM FLIGHT CREW 2 pilots. MAXIMUM NUMBER OF PASSENGERS

136

MAXIMUM BAGGAGE Cargo Compartment Maximum Load (kg) - Forward: 1 614 - Aft: 2 131 MAXIMUM BAGGAGE (Cont.) - Rear (Bulk): 1 372 For the positions and the loading conditions authorized in each position

(references of containers, pallets and associated weights) see Weight and Balance Manual, ref. 00 P 080 A 0001 / C1S Chapter 1.10.

FUEL CAPACITY (0.8 kg/l) 3 – Tank Airplane

TANK Usable fuel - liters (kg) Unusable fuel - liters (kg) WING 15 609 (12 487) 58.9 (47.1)

CENTER 8 250 (6 600) 23.2 (18.6) TOTAL 23 859 (19 087) 82.1 (65.7)

HYDRAULIC FLUIDS Type IV or Type V - Specification NSA 30.7110. TYRES See SB A320-32-1007. MAXIMUM OPERATING ALTITUDE

12100 m (39800ft)


IMPORT REQUIREMENTS A Brazilian Certificate of Airworthiness may be issued on the basis of on a EASA Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement: “The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate no. 9607 and in condition for safe operation”. The ANAC Report H10-02411-(), dated March 14, 2011 or further revisions, contains the Brazilian requirements for the acceptance of these airplanes. (See note 4)

CERTIFICATION BASIS CERTIFICATION BASIS (Cont.)

A) RBHA 25, which corresponds to the FAA FAR Part 25 effective 01 February 1965 as amended by 25-1 through 25-56 thereto. a) Plus the following sections of RBHA 25 corresponding to the FAA Part 25 as amendments 25-1 through 25-97 applied per ANAC derivative aircraft process to the changes and areas affected by the changes for all A318 models: 25.21, 25.23, 25.25, 25.27, 25.29, 25.31, 25.101, 25.103, 25.105, 25.107, 25.109, 25.111, 25.113, 25.115, 25.117, 25.119, 25.121, 25.123, 25.125, 25.143, 25.145, 25.147, 25.149, 25.161, 25.171, 25.173, 25.175, 25.177, 25.181, 25.201, 25.203, 25.207, 25.231, 25.233, 25.235, 25.237, 25.251(e), 25.253, 25.255, 25.571 (welded structure only), 25.801, 25.803, 25.807, 25.809, 25.810, 25.811, 25.812, 25.813, 25.855, 25.857, 25.858, 25.1501, 25.1517, 25.1583, 25.1587. b) Plus the following sections of RBHA 25 corresponding to the FAA Part 25 as amended by amendments 25-1 through 25-105 applied per the FAA derivative aircraft process to the changes and areas affected by the changes for the A318-121, and -122 models: 25.361, 25.363, 25.367, 25.371, 25.901, 25.903, 25.933, 25.934, 25.939, 25.941, 25.943, 25.945, 25.1041, 25.1043, 25.1045, 25.1091, 25.1093, 25.1103, 25.1105, 25.1107, 25.1121, 25.1123, 25.1125, 25.1127, 25.1141, 25.1143, 25.1163, 25.1165, 25.1167, 25.1181, 25.1182, 25.1183, 25.1185, 25.1187, 25.1189, 25.1191, 25.1193.

c) Plus the following sections of RBHA 25 corresponding to the FAA Part 25 amended as indicated below per Airbus elect to comply:

25.305 Amdt. 86

25.321 Amdt. 86

25.331 Amdt. 91

25.333 Amdt. 86

25.335 Amdt. 91

25.341 Amdt. 86

25.343 Amdt 86

25.345 Amdt 91

25.349 Amdt. 86

25.351 Amdt. 91

25.363 Amdt 91

25.371 Amdt 91

25.373 Amdt 86

25.391 Amdt 86

25.415 Amdt 91

25.427 Amdt 86

25.445 Amdt 86

25.473 Amdt 91

25.479 Amdt 91

25.481 Amdt 91

25.483 Amdt 91

25.485 Amdt 91

25.491 Amdt 91

25.499 Amdt 91

25.561(c) Amdt 91

25.571 Amdt 86*

25.735 Amdt 92

25.853 Amdt 83

25.1533 Amdt 92

* Not applicable to welded structure


CERTIFICATION BASIS (Cont.)

d) Plus RBHA/FAA section 25.772 & 25.795 correspondent to FAA Part 25 amendment 25-106 per Airbus elect to comply. e) Plus portions of RBHA/FAA section 25.562, correspondent to FAA Part 25 amendment 64, for the passenger seats only per Airbus elect to comply. RBHA/FAR paragraphs 25.562(c)(5), (c)(6) do not apply.

B) RBHA 34 correspondent to the FAA 14 CFR Part 34, effective September 10, 1990, including Amendments 34-1 through 34-3 thereto.

C) RBHA 36 correspondent to the FAA 14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-26 thereto.

D) Based on RBAC 21 section 21.29(a) for new import Type Certificates (TCs), or section 21.101(g) for changes to TCs, applicable provisions of RBAC 26 are included in the certification basis. For any future RBAC 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections.

E) The following A320 Special Conditions, Experience Related Conditions and Harmonization Conditions which are kept for the A318:

Reminder: Within the scope of the establishment of the A320 Joint Certification Basis, three types of special conditions were developed:

• Special conditions: raised to cover novel or unusual features not addressed by the JAR. • Experience related conditions: raised to record an agreed text for the A320 Joint Certification Basis when evolution of JAR was in progress under the NPA procedure. • Harmonization conditions: to record, for the purpose of the A320 Joint Certification Basis, a common understanding with respect to National variant. This should not be confused with the FAA/JAA harmonized regulations.

(DGAC-F) SC-G17 (CAA-UK) SC-G17 SC-F3 SC-F6 SC-F7 SC-F8 SC-F9 SC-A2.2.2 SC-S11 SC-S33 SC-S52 SC-S74 SC-S75 SC-S77 HC-A4.6 HC-S23 HC- S24 HC-S72

Operational proving flights Operational flight before certification Cockpit control - motion and effect of cockpit control Static directional and lateral stability Flight envelope protection Normal load factor limiting Dual control system Design manoeuvre requirements Limit pilot forces and torques Auto-thrust system Operation without normal electrical power Abnormal attitudes Lightning protection indirect effects Integrity of control signal Speed control device Standby gyroscopic horizon VMO/MMO warning (setting) Flight recorder



EC-G11 EC-S30 EC-S54

General definition Autoflight system Circuit protective devices

The following A319 Special Conditions, are kept for the A318:

SC-A2 SC-F11 SC-A1 SC-P1 SC-S79

Stalling speeds for structural design Accelerate-stop distances and relates performances, worn brakes Interaction of systems and structure FADEC for CFM56 and AMJ20X-1 change 14 for PW6000 Brakes requirements, qualification and testing

The following A319/A320/A321 Special Conditions are kept for the A318:

SC-IM76 Effect of external radiations upon aircraft systems (modified by CRI SE14)

The following Special Conditions developed for the A318:

SC-F5001 SC-F5004 SC-A5001 SC-A5003 SC-P5004 SC-SE5002

Stalling and scheduled operation speed Static longitudinal stability and low energy awareness Engine Failure Loads (PW engine only) Design Dive Speed Engine Sustained Imbalance (PW engine only) AFM – RVR limits

Exemption:

No exemptions.

Equivalent Safety findings:

Equivalent Safety findings to the following requirements are granted, as documented in relevant CRIs:

JAR 25.783(f) JAR 25.807(d) JAR 25.813(c)(1) JAR 25.831(a) JAR 25.933(a)(1) JAR AWO 313 JAR AWO 236

"Doors (see A319 CRI SM 4004 "passenger doors") "Passenger emergency exits" (see CRI E 5004 "Exit” configuration" similar to A319 CRI E 4001) "Emergency exit access" (see CRI E 5005 "Type III overwing emergency exit access")"Ventilation" (see CRI E 5006 "Packs Off Operation") "Reversing systems" (see A319 CRI P 4008 "Thrust Reverser Auto restow")



NPA AWO 10 "Minimum Approach Break-Off Height" (see A319 CRI SE 4005 "Minimum Approach Break-Off Height") "Excess Deviation Alerts" (see CRI SE 5005 "Cat III Operation – Excess Deviation Alert") “Airworthiness Harmonization package n°2” (see CRI SE-5002“ AFM – RVR limits”)

JAR AWO Change 1 for autoland and operations in low visibility.

Environmental requirements:

ICAO Annex 16:

Vol. I, Part II, Chapter 3 Vol. II, Part I I Vol. II, Part III Chapter 2

Noise Requirements (see also notes 4.3.3 and 4.3.4) Fuel Venting Emissions

For the Extended Twin Engine Airplane Operations the applicable technical conditions are contained in AMJ 120-42/IL 20 and the A318 ETOPS CRI:

CRI G-22 ETOPS One engine inoperative cruise speed.

SC G-1006: ETOPS

REQUIRED EQUIPMENT See the Type Design Definition references:

- D03006056 Issue 6 for A318-111 - D03006716 Issue 2 for A318-112 - D05028326 Issue 5 for A318-121 - D05028327 Issue 5 for A318-122

Cabin furnishings, equipment and arrangement shall be in

conformance to the following specifications: - 00 D 252 K 0004 / C01 for cabin seats; and - 00 D 252 K 0019 / C01 for galleys.

NOTES: NOTE 1 Weight and Balance: note 1 of the A-320 series is also applicable to the A318 series. NOTE 2 Markings and Placards: note 2 of the A-320 series is also applicable to the A318 series. NOTE 3 Continuing Airworthiness: note 3 of the A-320 series is also applicable to the A318 series NOTE 4 Note 4 of the A-320 series is also applicable to the A318 series. NOTE 5 Autoflight certification: If the following modifications are embodied, the aircraft is qualified

for the applicable precision approach:

Engines Precision approach category Modification Nr.

CFM Cat. IIIB 32997, 33310 and 33299 PW Cat. IIIB Included in the Type