IGFER1136_SEC01[1]

INSTRUCTIONS FOR GROUND FIRE
EXTINGUISHING AND RESCUE
SECTION 1AIRCRAFT GENERAL INFORMATION

1. General

A. The EMB-145( ) and EMB-135( ) models are all-metal, low-wing, monoplane, T-tail, pressurized,medium range jets manufactured by EMBRAER.They are provided with a fully retractable tricycle landing gear system with dual wheels, anti-skidbraking system, and steerable nose wheels, being powered by two rear-mounted Allisonhigh-bypass ratio turbofan engines.

B. The typical passenger configuration consists of three seats abreast, with front galley and reartoilet, allowing carrying up to 50 passengers on the EMB-145( ) models; 44 passengers onEMB-135KL and EMB-135KE models; and 37 passengers on the EMB-135LR and EMB-135ERmodels. Convenient accommodation is provided for flight crew, which includes a pilot, a copilot,a flight observer, and two flight attendants.

C. This manual is applicable to EMB-145EP, EMB-145ER, EMB-145EU, EMB-145LR, EMB-145LU,EMB-145MK, EMB-145MP, EMB-145XR, EMB-135KL, EMB-135KE, EMB-135LR andEMB-135ER models.

NOTE: • EMB-145MK models are the aircraft, which incorporated SB145-00-0006. Thismanuals is applicable to these aircraft. Affectivities ALL and MP are also applicable tothe EMB-145MK models.

• After incorporation of SB 145-00-0007 to aircraft EMB-145MK, it becomes anEMB-145MP again.

D. The following station diagrams give a reference system that shows the location of the structuralcomponents in relation to the datum planes (See Aircraft Maintenance Manual).

EMB-145 MODELS MRWlb-(kg)

MTOWlb-(kg)

MLWlb-(kg)

MZFWlb-(kg)

EMB-145LR(with AE3007 A1 engines) (1)

48722(22100)

48501(22000)

42549(19300)

39462(17900)

EMB-145LR(with AE3007 A1/1 engines)

46495(21090)

46275(20990)

42549(19300)

39462(17900)

EMB-145ER (2) 45635(20700)

45414(20600)

41226(18700)

37698(17100)

EMB-145EU 44290(20090)

44070(19990)

41226(18700)

37698(17100)

EMB-145EP (2) 46495(21090)

46275(20990)

41226(18700)

37698(17100)

EMB-145LU 48700 48479 42549 39462

Revision 10 1-1

(22090) (21990) (19300) (17900)

MRW Maximum Ramp WeightMTOW Maximum Takeoff WeightMLW Maximum Landing WeightMZFW Maximum Zero Fuel Weight

(1) For aircraft Post-Mod. SB 145-53-0068 consider, MZFW= 40564 lb (18400 kg), MTOW= 49823 lb(22600kg), and MLW= 43651 lb (19800kg).

(2) For aircraft Post-Mod. SB. 145-53-0064 consider, MZFW= 38250 lb (17350 Kg).

(3) For aircraft Post-Mod. SB. 145-00-0025 consider, MZFW= 35274 lb (16000 Kg).

EMB-145 MODELS MRWlb-(kg)

MTOWlb-(kg)

MLWlb-(kg)

MZFWlb-(kg)

EMB-145MP 46495(21090)

46275(20990)

42549(19300)

39462(17900)

EMB-145XR(with AE3007 A1E engines)

53131(24100)

52910(24000)

44092(20000)

40785(18500)

EMB-135KL 46738(21200)

46517 (21100)

41226(18700)

37699(17100)

EMB-135KE 44533(20200)

44313 (20100)

41226 (18700)

37699(17100)

EMB-135 LR 44313(20100)

44092 (20000)

40783(18500)

35274(16000)

EMB-135 ER (3) 42108(19100)

41888 (19000)

40783 (18500)

34392(15600)

1-2 Revision 10

Applicable to the EMB-145LR, EMB-145ER, EMB-145EU, EMB-145EP, EMB-145LU andEMB-145MP aircraft models

Three-View

Revision 6 1-3

Figure 1-1

Applicable to the EMB-135 KL and EMB-135 KE aircraft models

Three-View

1-4 Revision 5

Figure 1-1A

Applicable to the EMB-145XR only

Three-View

Revision 6 1-5

Figura 1-1B

Applicable to the EMB-135LR and EMB-135ER aircraft models

Three-View

1-6 Revision 6

Figure 1-2


Fuselage Station Diagram

Revision 6 1-7

Figure 1-3

INSTRUCTIONS FOR GROUND FIREEXTINGUISHING AND RESCUE

1-8 Revision 6


Fuselage Station DiagramFigure 1-3A

Applicable to the EMB-135KL and EMB-135KE aircraft models

Fuselage Station DiagramFigure 1-3B

Revision 6 1-9


Fuselage Station Diagram

1-10 Revision 6

Figure 1-4


Vertical Stabilizer Station Diagram

Revision 6 1-11

Figure 1-5

INSTRUCTIONS FOR GROUND FIREEXTINGUISHING AND RESCUE

1-12 Revision 6


Vertical Stabilizer Station DiagramFigure 1-5A



Revision 6 1-13

Figure 1-5B



1-14 Revision 6

Figure 1-6

Horizontal Stabilizer Station Diagram

Revision 6 1-15

Figure 1-7

Applicable to the EMB-145( ) aircraft models

Wing Station Diagram

1-16 Revision 6

Figure 1-8


Wing Station DiagramFigure 1-8A

Revision 6 1-17


Wing Station Diagram

1-18 Revision 6

Figure 1-9

Nacelle Station DiagramFigure 1-10

Revision 6 1-19

Pylon Station Diagram

1-20 Revision 6

Figure 1-11

WARNING: WHENEVER THE ENGINES OR APU ARE RUNNING, THE GROUND CREW MUSTKEEP AWAY FROM THE AREAS INDICATED IN THE FIGURE BELOW.


Hazard Areas

Revision 6 1-21

Figure 1-12

WARNING: WHENEVER THE ENGINES OR APU ARE RUNNING, THE GROUND CREW MUSTKEEP AWAY FROM THE AREAS INDICATED IN THE FIGURE BELOW.


Hazard Areas

1-22 Revision 6

Figure 1-13

2. Landing Gear Lock Pins Installation

A. Landing Gear Safety Pins must be installed for aircraft parking and during towing operation.When not in use, the safety pins are kept in a recess of the aft console, behind the pilot seat.

WARNING: DURING THE INSTALLATION OF THE SAFETY PIN, PREVENT SUDDEN ANDSTRONG MOVEMENTS OF THE AUXILIARY BRACE STRUT. THIS COULDCAUSE AN ACCIDENTAL UNLOCKING OF THE LANDING GEAR, WITHSUBSEQUENT INJURIES TO PERSONNEL AND DAMAGE TO AIRCRAFT.

(1) Make sure that the landing gear control lever is in the DOWN position.

(2) Install the safety pin at the auxiliary brace strut in each landing gear.

(3) Make sure that the red REMOVE BEFORE FLIGHT Streamer is clearly in view.

3. NLG Door Solenoid Valve Safety Pin Installation

A. The safety pin of the NLG Door Solenoid Valve must be installed when the aircraft is parked andduring maintenance procedures.

WARNING: • APPLICABLE TO AIRCRAFT PRE-MOD. S.B. 145-32-0036.ACCESS OF ANY PERSON TO THE NOSE LANDING GEARCOMPARTMENT, FOR ANY REASON, AFTER A MAINTENANCE ACTION INTHE LANDING GEAR EXTENSION/RETRACTION AND OR A FREE-FALLCONTROL LEVER ACTUATION, IS ALLOWED ONLY WITH HYDRAULICSYSTEM No. 1 UNPRESSURIZED (I.E. ENGINE No. 1 NOT RUNNING ANDELECTRICAL MOTOR-DRIVEN PUMP No. 1 TURNED OFF).

• APPLICABLE TO AIRCRAFT POST-MOD. S.B. 145-32-0036 (FIGURE 1-15).ACCESS OF ANY PERSON TO THE NOSE LANDING GEARCOMPARTMENT, FOR ANY REASON, AFTER A MAINTENANCE ACTION INTHE LANDING GEAR EXTENSION/RETRACTION AND/OR A FREE-FALLCONTROL LEVER ACTUATION, IS ALLOWED ONLY AFTER THE SAFETYPIN OF THE NLG DOOR SOLENOID VALVE IS INSTALLED AS FOLLOWS:

(1) Make sure that hydraulic system No. 1 is depressurized (I.E. engine No. 1 stopped and elec-trical motor-driven pump No. 1 turned off).

(2) Control the rudder to the left and to the right sides until the pressure of the hydraulic systemshows zero PSI on the EICAS display.

(3) Open access door 114CR (AMM 6-41-01/101).

(4) Manually push the SPOOL ACTUATING PIN.

(5) Install the safety pin of the NLG door solenoid valve.

(6) Make sure that the red REMOVE-BEFORE-FLIGHT streamer is clearly in view.

Revision 6 1-23

LG Safety Pins Installation

1-24 Revision 6

Figure 1-14

Safety Pin of the NLG Door Solenoid Valve

Revision 6 1-25

Figure 1-15

THIS PAGE LEFT BLANK INTENTIONALLY

1-26 Revision 6

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IGFER1136_SEC01[1]