technical inspection aircrfaft appraisal …€¦ · aircrfaft appraisal and technical inspection :...

EMB120

120-350Serial #

Aircraft Type: Registration: N582SW

Bank of America / Gavin Back

AIRCRFAFT APPRAISAL AND

TECHNICAL INSPECTION

5. Airworthiness Directives: Airframe

9. Inspector’s Special Notes: Addendum 1

10. Inspector’s Aircraft Discrepancy Report: Addendum 2

11. Installed Equipment List

12. Aircraft Pictures

Engine Prop Equipment

6. Major Repairs and Alterations List

7. Service Bulletin Compliance

8. Weight and Balance Information

AIRCRAFT TECHNICAL REPORT INDEX

1. Aircraft Inspection Report

2. Technical Data

3. Life Limited Report

4. Life Limited Data and Airworthiness limitations

Operator: SkyWest Airlines Date:

Location:

Aircraft Type: Serial #:

Aircraft Model: EMB120ER Aircraft Registration: N582SW

Date of Manufacture: Apr/1999

Current Total A/C Time: 32873.0 Current Total Airframe Cycle: 45163

Hours since Major Inspection/Overhaul: Last C check CW 7-16-2014 TAT 31911.2

Maintenance Program: FAR Part 121; Continuous Airworthiness (CAMP)

Inspection Type and Interval: A1 thru A6 360 hr Last Inspection: C1 @ 31911.2interval with 4000 hr C check Date: C2 @ 28458.4

C3 @ 24029.3Operator's Representative: Mo VaqueraTitle: Director of Technical Support

Inspection Completed By: Angela Aquino

Date of Completion: 4-15-2016

Inspection Type: Off-lease

Work Order Reference: 97819

Notes:

Embraer Brasilia

Aircraft Data and Inspection Report

4/11/2016

7/16/2014

120-350

Physical inspection and records audit accomplished in Springfield, Mo at the WASI maintenance facility

N582SW SN 120-350 was inspected for return from lease in Springfield, Missouri at the Worldwide Aircraft Services maintenance facility, the following are the inspectors findings based on this limited inspection.Currently the aircraft is painted dark blue belly and white top separated by three multi colored blue stripes running the length of the aircraft. Paint condition at this time is average, minor touch up is required.The interior is configured for 30 passengers, dark blue leather covered seats, dark blue carpeting. The overhead bins are in good condition, it appears that most of the damaged areas have been repaired and the inside of the bins have been painted recently. Overhead is in good condition, seat bases need to be cleaned, seat tracks appear to be in acceptable condition other than general cleaning.The cockpit is in need of a detailed cleaning, cockpit floor covering needs replaced, the captains DV window has scratches at the lower center area, not in the direct line of sight, these scratches need to be buffed out.

Avionics currently installed are Collins four tube EFIS system, three comms, dual navs, a FlghtMax 800 in the center of the instrument panel, there is an L3 Communications CVR and Fairchild F1000 FDR, a listing of avionics can be found later in this report.Current records are kept electronically and past records have been scanned and placed in to folders on a thumb drive, numerous tasks have been accomplilshed to meet return conditions, a 2 year CPCP inspection was accomplished and numerous 4 year CPCP task were accomplished, per the Skywest program several of the CPCP tasks were accomplished during a 1C or 2C inspection.

The SkyWest program was assembled by SkyWest for there operation based on the MRB, at present there inspection program is 360 hr "A" checks with a 4000 hr "C" check program, numerous EA's and FCD's have been accomplished with all of the information and documentation in the records.

No major damage history was noted at this time, there is a statement in the records from SkyWest that states this aircraft has not been involved in any incident or accident while in there operation.Note that there are several small minor repairs via the SRM by in house engineering thru the EA or FCD process, these minor repairs are part of the FCD process or the EA process.As an overall view of this aircraft I would consider it to be in average condition, the next operator will require the records to be bridged to there program, all of the records appear to be in place at this time so this process should be relatively simple to do however it will require so time to do, this aircraft should provided the next operator good reliable service once the aircraft is placed on to there program.

INSPECTION OPERATOR LIMIT CW LAST DATE CW LAST TAT CW LAST TAC

Service Check 75 hrs DUE NOW DUE NOW DUE NOWA1 360hrs 5/18/2014 31620.0 43329A2 720 hrs 7/16/2014 31911.2 43759A3 1080 hrs 10/22/2014 32213.0 44185A4 1440 hrs 1/2/2015 32492.0 44591A5 1800 hrs 4/1/2015 32796.1 45046A6 2160 hrs 3/24/2014 31407.0 43001C1 4000 hrs 7/16/2014 31911.2 43759C2 8000 hrs 9/22/2012 28458.4 38860C3 12000 hrs 10/2/2010 24029.3 32665AVNC 12-1 12 Month 11/30/2015 32869.3 45162AVNC 12-2 12 Month 11/30/2015 32869.3 45162AVNC 12-3 12 Month 11/30/2015 32869.3 45162AVNC 12-4 12 Month 11/30/2015 32869.3 45162AVNC 24 24 Month 9/2/2014 32019.0 43913CABLE 2300 hrs 7/6/2014 31911.2 43759COMPASS SWING 24 Month 9/2/2014 32019.0 43913LH Critical Bond 30000 hrs 9/22/2012 28458.4 38860RH Critical Bond 30000 hrs 9/22/2012 28458.4 3886012 MONTH 12 Month 2/19/2015 32685.0 44873Aging Aircraft 6935 Days or 19 YRS 5/28/1999 0.0 0Pitot/static 24 Month 12/25/2014 32481.0 44573S4 20000 cyc 2/13/2013 29116.6 39804S6 32000 cyc 7/17/2010 23532.3 31981Rudder Act Health 4000 hrs 7/18/2014 31911.2 43759Vent Valve Insp 20000 hrs 11/7/2007 18124.8 24526Tank Visual insp 16000 hrs 5/18/2009 21187.6 28563Pilot Valve Insp 20000 hrs 11/7/2007 18124.8 24526NLG Attach fitting 90000 cyc 5/28/1999 0.0 0NDT UPR Fuse Skin 5625 cyc 7/18/2014 31911.2 43759MLG Fuse Att Rib 131054 cyc 5/28/1999 0.0 0MLG Fitting LH 131054 cyc 5/28/1999 0.0 0MLG Fitting RH 131054 cyc 5/28/1999 0.0 0In Tank Harness 20000 hrs 11/7/2007 18124.8 24526

SKYWEST INSPECTIONSN582SW SN 120-350 TAT:32873.0 TAC: 45163

GNS Antenna Insp 4400 cyc 7/18/2014 31911.1 43759FDR Check 12 Month 4/1/2015 32800.4 45054Hyd SOAP 600 hrs 1/26/2015 32588.2 44724

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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163

Items S/N Position Last Done Next Due

120-350 NA 75 FH Ref Insp Ref Insp










120-350 NA 3 YR 12/2015 12/8/2018

120-350 NA 1600 FH 32796.1 34396.1

120-350 NA 12 MO 8/26/2016 8/26/2017

120-350 NA 1600 FH 32796.1 34396.1

120-350 NA 12 MO NA NA

120-350 NA 2000 FH 32869.3 34869.3

Check electronic bay overtemperature warning operation for temperatures greater than 70°C (158°F)(21-21)

"2A" Inspection

"3A" Inspection

"4A" Inspection

"5A" Inspection

"C" Inspection

"2C" Inspection

"3C" Inspection

Airframe Airworthiness Limitations

Life

Registration:

Line Check

Effective Date:

All “due” times are referenced to aircraft total time and total cycles. Last Done column reflects time of last compliance with maintenance item or, in case of components which are moved with continued time, a calculation

of aircraft times which reflect, time since overhaul or last maintenance performed.

Chapter 5 Times Limits/Maintenance Checks

"A" Inspection

"4C" Inspection

Actual Reweigh

Chapter 21 Air Conditioning

Check positive pressure relief valve in both the electropneumatic & pneumatic outflow valves(21-04)

Visually check the Equalization Valve at the Cargo Compartment (21-17)

Chapter 22 Autoflight

Check relays of AHRS pitch data to AP/FD(22-02)

Replace Blow-out panels adhesive tape(21-22)

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Registration:Effective Date:

120-350 NA 2000 FH 32869.3 34869.3

120-350 NA 1200 FH 32869.3 34069.3

120-350 NA 12000 FH 24029.3 36029.3

SC25278 NA 6 YR May-14 4/29/202024 MO 8/26/2016 8/26/2018

P/N DK120

120-350 NA 1 YR 8/26/2016 8/26/2017

120.350 NA 8000 FH 32869.3 40869.3

98538 LH 1600 FH 32054.6 33654.66609 RH 1600 FH 31944.5 33544.5

98538 LH 1600 FH 32054.6 33654.66609 RH 1600 FH 31944.5 33544.5

98538 LH 800 FH 32729.5 33529.56609 RH 800 FH 32622.5 33422.5

97010 LH 2400 FH 32771.1 35171.1PN 30081-010 482 RH 2400 FH 32487.3 34887.3

97010 LH 1600 FH 32771.1 34371.1482 RH 1600 FH 32487.3 34087.3

120-350 NA 1600 FH 32796.1 34396.1

Must be done at time of S/G restoration Task (24-01)

Auxiliary Generator Restoration

Chapter 23 Communications

Chapter 24 Electrical Power

Verify starter-generator GCU

(24-04)

Inspect SMT-65 Servo Mount. Functional Check(22-06)

(23-01)

Replace CVR ULB batteryOPS Check

Check glide slope transfer relays to AP/FD(22-03)

Check navigation system test inhibitor relay (22-04)


(23-02)

Verify CVR operation on four channels

(24-03) AC pre-mod Lucas SB 23080-01x-24-02 limiter 300 hrs

Starter/Generator Restoration (15000 if Post C)(24-01)

Visually check Starter/Generator Quick Attach/Detach kit for general condition. (QAD Kit)(24-02)

CVR Overhaul Fairchild 93-A100(23-02)

Starter/Generator Brush check.

(24-05)

Visually check Aux. Gen. QAD Kit for general condition

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120-350 NA 1600 FH 32796.1 34396.1

9009W0370 NA 1 YR NA NA

9009W0370 NA 6 MO 8/26/2016 2/24/2017

5931 NA 1600 AHR 28226.0 29826.0

5931 NA 1600 AHR 28226.0 29826.0

5931 NA 800 AHR 28226.0 29026.0

5931 NA 1600 AHR 28226.0 29826.0

120-350 NA 400 FH 32796.1 33196.1

120-350 NA 8000 FH 28458.4 36458.4

85816 NA 1 YR 8/26/2016 8/26/2017

120-350 NA 1 YR 11/30/15 11/29/16

120-350 NA 1 YR 11/30/15 11/2016

120-350 NA 7 YR 05/2014 05/2021PN AC/2-AA-( ) & handlePN AC/10-KK-( )

Perform back-up battery discharge test.(24-19)

Check ELT for condition(25-15)

Discard Beta light Placards

(25-21)

Check DC Distribution Bus diodes.(24-16)

Visually check APU starter generator brushes for general condition(24-12)

Visually check APU starter-generator GCU for operation(24-13)

Verify the complete emergency transfer function operation(24-15)

Check main battery

Restore main battery

(24-11)

Visually check APU QAD Kit for General condition

ELT Battery FAR 91.207(Recertify)

Chapter 25 Equipment

(general control unit) for (24-06)

Verify auxiliary generator GCU for operation(24-07)

(24-08)

(24-09)

Restore APU starter-generator(24-10)


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120-350 NA 5 YR NA by config NA by config




NSN NA 2 YR 11/2015 10/2017

120-350 NA 1 YR* 8/26/2016 8/26/17

120-350 NA 1 YR* 8/26/2016 08/2017

120-350 NA 4000 FH 31911.2 35911.2

(26-01)

120-350 NA 5 YR 07/2014 7/15/2019

(26-02)

5333EL LH FW 10 YR 7/1/12 06/2022

Verify engine fire extinguishing system for circuit integrity.

Verify TWO-WAY CHECK TEE operation

Engine & APU fire extinguisher

Chapter 26 Fire Protection

(25-22)

Visually check the movable partition sealing for security & condition (A/C combi version only)

Replace ELT battery (Interval counted from component DOM)(25-28)

Visually inspect lifejacket for condition & verify the CO2 cylinder for proper weight(25-80E)

Perform lifejacket pressure test & water-activated locator light test.

(25-24)

Visually check the smoke curtain sealing for security & condition. A/C full cargo version only.(25-25)

(25-81E)

Inspect protective canvas (cargo floor protection) for general condition. (A/C combi & full cargo versions only. Zones 231/232 applicable to full cargo version only.(25-23)

Inspect cargo arresting net & cargo stripes for general condition (A/C combi & full cargo. Zones 231/232 applicable to full cargo only)

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LH AFT 10 YR 7/1/12 06/20225218EL RH FW 10 YR 2/1/10 01/2020

RH AFT 10 YR 2/1/10 01/202075027EK APU 10 YR 05/2014 05/2024

5333EL LH FW 5 YR 7/1/12 06/2017LH AFT 5 YR 7/1/12 06/2017

5218EL RH FW 5 YR 8/26/16 08/2021RH AFT 5 YR 8/26/16 08/2021

75027EK APU 5 YR 05/2014 05/2019

120-350 APU 4000 FH 31911.2 35911.2

5333EL LH 5 YR 01/2014 01/20195218EL RH 5 YR 8/26/16 08/2021

75027EK APU 5 YR 08/2014 07/2019

X629989 Cockpit 12 YR 10/2013 10/2025U940094 Cabin 12 YR 08/2014 08/2026V517031 Cabin 12 YR 08/2014 08/2026

X-629989 Cockpit 1 YR 8/26/16 08/2017U940094 Cabin 1 YR 8/26/16 08/2017V517031 STC 1 YR 8/26/16 08/2017

5333EL LH 1 YR 8/26/16 08/20175218EL RH 1 YR 8/26/16 08/2017

75027EK APU 1 YR 8/26/16 08/2017.

5333EL LH 1 YR 8/26/16 08/20175218EL RH 1 YR 8/26/16 08/2017

75027EK APU 1 YR 8/26/16 08/2017


34187D1 NA 1 YR 8/26/16 8/26/1718506F1 5 YR 8/28/12 8/28/17

(26-19)

(26-16)

Portable fire bottles (Hydrostatic Test) NA to disposable bottle(26-10)

Portable fire bottles (Weight Check)(26-11)

(26-15) At time of bottle weight check

Inspect Baggage fire ext bottles (high rate & metering) for weight, Hydro ever 5 years

cartridges (life limit)(26-03)

Verify Engine/Wheelwell & APU fire extinguisher bottle pressure switch operation(26-04)

At time of bottle hydrostatic test

Verify APU fire extinguishing system for circuit integrity.

Inspect combi portable fire extinguisher. Weight check (A/C combi version only)

(26-05)

Engine/Wheelwell & APU fire extinguisher bottles (Hydrostatic Test)(26-09)

Engine/Wheelwell & APU fire extinguisher bottles (Weight Test)(26-12)

Check engine/APU extinguishing relief valve protection cap for proper installation & unobstructed vent holes

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7565 NA 10 YR 03/2012 03/20247566

120-350 NA 5 YR 07/2014 07/2019

120-350 NA 5 YR 7/16/14 7/15/19

120-350 NA 2000 FH NA by config NA by config

120-350 NA 5000 FH 32873.0 37873.0

120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 2000 FH 31911.2 33911.2

120-350 NA 1600 FH 31911.2 33511.2

120-350 NA 2000 FH 31911.2 33911.2

120-350 NA 1600 FH 32213.0 33813.0

120-350 NA 2000 FH 31911.2 33911.2

(27-07)

(27-10)

Check tension of aileron cables(27-08)

Check rudder cables & trim cables tension.(27-17)

(26-22)

Visually check smoke detector maint. Light (red led)(26-25)

Visually check aileron tab dual rods between tab actuator & tab (RH side) & between support & tab. (LH Side)

Chapter+296:336 27 Flight Controls

Baggage comp. Class "C"

Verify aileron control disconnect & alarm systems operations(27-01)

Visually check aileron control disconnect system for condition

(27-06)

Visually check aileron control path from wing root to aileron

Visually check aileron control path from FWD quadrants to wing root.

(27-02)

Discard baggage fire ext bottles (High rate & metering) cartridges.

(26-21)

(26-20)

15 years from DOM or 10 years from installation

Functionally check two-way tee valve at same time as hydro, baggage

comp. Class "C"

Perform baggage fire extinguisher bottles (high rate & metering) hydrostatic test

Baggage comp. Class "C"

Operational check of lavatory smoke detector, if installed(26-26)

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120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 2000 FH 31911.2 33911.2

120-350 NA 2000 FH 31911.2 33911.2

120-350 NA 1600 FH 32213.0 33813.0

120-350 NA 2000 FH 32213.0 34213.0

120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 800 FH 32796.1 33596.1

120-350 NA 400 FH 32796.1 33196.1

120-350 NA 800 FH 32492.0 33292.0

120-350 NA 4000 FH 32492.0 36492.0

120-350 NA 4000 FH 32492.0 36492.0

Check stall warning system angle of attach sensor operation(27-41)

Check stall warning system G-

Verify rudder overboost protection & indication systems operation(27-37)

Verify stall warning system sideslip sensor operation(27-38)

Check stall warning system FLAP INTERFACE SIGNAL(27-39)

Visually check elevator tab dual rods between tab actuator and tab.(27-28)

Visually check rudder II connecting rods for integrity & condition.(27-35)

Functional test of rudder hydraulic system differential pressure(27-36)

Check elevator cables & trim tab cables tension.(27-26)

Visually check elevator control disconnect system for condition.(27-22)

Visually check elevator control path from FWD quadrant to elevator(27-25)

Verify elevator control disconnect & alarm systems operation(27-21)

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120-350 NA 3000 FH 32492.0 35492.0

120-350 NA 4000 FH 32492.0 36492.0

120-350 NA 4000 FH 32492.0 36492.0

120-350 NA 4000 FH 32492.0 36492.0

120-350 NA 4000 FH NA by PN NA by PN

120-350 NA 3000 FH 31407.0 34407.0

120-350 NA 4000 FH 31911.2 35911.2

120-350 NA 1600 FH 32213.0 33813.0

120-350 NA 1600 FH 32213.0 33813.0

120-350 NA 1600 FH 32213.0 33813

120-350 NA 1600 FH NA by SB NA by SB

120-350 NA 400 FH NA by SB NA by SBVisually check aileron control cable for wear, broken strands,

Check aileron trim tab for backlash(27-53)

Check rudder II for backlash

Check elevator trim tab for backlash(27-54)

(27-55)

(27-65)

Inspect fairleads support holes of the aileron control path in the nacelle region

A/C under SB 120-27-0068 REV 1 400 FH

Check flap control unit. A/C with FCU PN 307500-1007, per 1017 only. See IB 120-027-0013(27-49)

Check elevator trim longitudinal proximity switches(27-51)

Check rudder control path from PCU summing lever to rudder for condition& integrity. (27-52)

Verify stall warning system cut-out switch operation(27-44)

Verify stall warning system warning diode operation(27-46)

Verify stall warning system landing gear on-air inhibiting system operation(27-47)

switches operation.(27-42)

Verify stall warning system quick-disconnect function operation (fi installed)(27-43)

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230 NA 4000 FH 32080.3 36080.399 32080.3 32080.3

120-350 NA 30000 FH 28458.4 58458.4

120-350 NA 20000 FH 18124.8 38124.8

120-350 NA 20000 FH 18124.8 38124.8

120-350 NA 20000 FH 18124.8 38124.8

120.350 NA 8000 FH 11/1977 36458.4

120.350 NA 1600 FH 32796.1 34396.1

Check primary return filter clogged filter indicator & secondary return filter by-pass valve(29-06)

Chapter 30 Anti-Ice

Check angle-of-attack & sideslip sensor heating indication relay

REF: AD2008-04-18, MRB SEC6 Part E

(28-16)

Visually inspect Pilot Valve harness inside the conduit

Check elevator trim tab actuators. Applicable to PN: 5299, 5299-1 & CA14501-002(27-67)

corrosion, kinks, & bird caging at nacelle region. A/C pre mod SB 120-27-0068 REV 2 ONLY(27-66)

(28-17)

Visually inspect Vent Valve harness inside the conduitREF: AD2008-04-18, MRB SEC6 Part E(28-18)

Chapter 29 Hydraulic Power

Functionally check critical bonding integrity of selected conduits inside the wing tank, fuel pump and FQIS connectors at tank will, by conductivity

(28-15)

Chapter 28 Fuel System

REF: AD2008-04-18, MRB SEC6 Part E

Visually inspect FQIS harness for clamp & harness isolation integrity.REF: AD2008-04-18, MRB SEC6 Part E

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120.350 NA 1600 FH 32796.1 34396.1

120.350 NA 1 YR 08/26/16 8/26/2017

120.350 NA 1 YR 08/26/16 8/26/2017

120.350 NA 1 YR 8/26/16 8/26/2017

NA 1 YR 8/26/16 8/26/2017P/N Fairchild (31-06)

1625 NA 8000 FH OC OCP/N Fairchild (31-07)

DM3127 NA 6 YR 5/19/14 5/17/202024 MO 8/26/16 8/26/2018

(31-08)

99 NA 6 YR 04/2014 3/30/2020

(31-09)

120.350 NA 3 MO* 08/2016 11/25/2016

(31-10E)

B47 L/H 2500.00 FH 32873.0 35373.012 MO 8/26/2016 8/26/2017

Verify aural warning system operation with the connection of one power source at a time (self test)(31-04)

Flight Data Recorder (Restore)

Flight Data Recorder Underwater Locator Beacon Batter Replacement Ops check PN DK-100

(32-01)Service MLG Shock absorber

Chapter 32 Landing Gear

ULB Switch end cleaned PN DK-100

Replace FLIGHT DATA ACQUISITION UNIT BATTERY. NOTE(1): 6 YR from battery manufacturing date. NOTE(2): Applicable only to FDAU TELEDYNE.

(30-09)

Clean pressure regulator valve drain tube & bowl: water separator bowl & drain(30-13)

Clean ejector control valves(30-14)

Chapter 31 Recording

operation(30-02)

Check deicing system monitor (DMS)

Flight Data Recorder (Verify)

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204 R/H 2500.00 FH 32873.0 35373.012 MO 8/26/2016 8/26/2017

595 LH 400 FH 32796.1 33196.1599 RH 400 FH 32796.1 33196.1

258 NLG 2500.00 FH 32873.0 35373.012 MO 8/26/2016 8/26/2017

258 NLG 400 FH 32796.1 33196.1

258 NLG 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

258 NA 8000.00 FH NA NA48 MO NA NA

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 2000.00 FH 32873.0 34873.012 MO 8/26/2016 8/26/2017

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 2500.00 FH 32796.1 35296.124 MO 4/1/2015 3/31/2017

120.350 NA 800.00 FH 32796.1 33596.1

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 4000.00 FH 31911.2 35911.2

120.350 NA 800.00 FH 32796.1 33596.1

Service NLG Shock Absorber

(32-05)

"A" CHECK OR 12 Months

(32-09)

Lubricate NLG Spring Cartridge

Lubricate MLG Spring Cartridge

(32-13)

"C" CHECK OR 24 Months

"A" CHECK OR 12 Months

Check NLG steering rack & sector gear.

Check emergency & parking brake accumulator nitrogen charge

"2C" CHECK OR 48 Months

Lubricate free-fall uplock release device(32-25) Depends on Lubricant

Check free-fall mechanical control cable adjustment

Check brake metering valve

(32-30)


(32-40)

Check that brake shuttle valves are operating correctly(32-43)

(32-18)

Lubricate emergency & parking brake actuation lever(32-33)

(32-34)

Verify in-flight brake system(32-36)

Lubricate free-fall actuation device. A/C premod 32-0019(32-23)

"5A" CHECK OR 12 Months

Verify landing gear on-ground retraction protection system operation

(32-24) "C" CHECK OR 24 Months

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120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 4000.00 FH 31911.2 35911.2

120.350 NA 8000.00 FH 32873.0 40873.048 MO 8/26/2016 8/25/2020

120.350 LH 11000.00 FC 43001 54001RH 11000.00 FC 43001 54001

120.350 LH 3000.00 FC 43001 46001RH 3000.00 FC 43001 46001

1437 NLG 11000.00 FC 43001 54001

223 NLG 3000.00 FC 43001 46001

1437 NLG 11/27/2014223 NLG 2/24/2015

1437 NLG 11/27/2014223 NLG 2/24/2015

1619 1 4/22/2015471 2 4/14/2015

1616 3 4/24/20151451 4 3/7/2015

1619 1 4/22/2015471 2 4/14/2015

1616 3 4/24/20151451 4 3/7/2015

1619 1 4/22/2015

According to Manufacture's recommendation

(32-53)

Check B.F Goodrich main wheel

halves for cracks & corrosion

Check B.F Goodrich main wheel

"2C" CHECK OR 48 Months

Inspect MLG shock absorber, drag strut, spring cartridge & aux. drag strut

Check anti-skid system, including electronic control unit(32-47)

(32-44)

Check hydraulic fuses are operating correctly

Check landing gear system & warning system (32-45)

A)9000-11000 FC since NEW or last OH

B) 3000,6000,12000 FC since NEW or last OH

SB 120-32-517

SB 120-32-517

(32-48)

Check B.F Goodrich nose wheel

halves for cracks & corrosion

Check B.F Goodrich nose wheel bolt for fatigue evidences & cracks

(32-55)

Inspect NLG shock absorber, drag strut, spring cartridge & aux. drag strut

A)9000-11000 FC since NEW or last OH

(32-49)B) 3000,6000,12000 FC since NEW or last OH

(32-52)According to Manufacture's recommendation

According to Manufacture's recommendation(32-54)

Check B.F Goodrich main wheel bolts for fatigue evidences & cracks


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471 2 4/14/20151616 3 4/24/20151451 4 3/7/2015

120.350 NA 400.00 FH 32873.0 33273.0

120.350 NA 4000.00 FH 31911.2 35911.2

1619 1 8/26/2016471 2 8/26/2016

1616 3 8/26/20161451 4 8/26/2016

120.350 NA 500.00 FH 32796.1 33296.1

120.350 NA 4000.00 FH* 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 2500.00 FH* 32873.0 35373.024 MO 8/26/2016 8/26/2018

120.350 NA 4000.00 FH* 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 2500.00 FH* 32873.0 35373.024 MO 8/26/2016 8/26/2018

120.350 NA 3000 FH 32873.0 35873.024.00 MO 8/26/2016 8/26/2018

120.350 NA 1600 FH 32869.3 34469.3

Lube NLG piston & scraper(32-65)

PN 3-1446 & 3-1446-1

(32-65E)

Check NLG assy. for excessive play(32-67E)

(34-06)

Altimeters & airspeed indicators & complete pitot-static system (Calibration)(34-01)

Chapter 34 Navigation


Verify ADI ATT comparator warning computer operation by operating the AHRS test switch

(32-66E)

Inspect the brake assembly of condition. PN 2-1479-1, 2-1585 & 2-1661(32-64)

(32-56)

Check NLG spring cartridge for general condition(32-68E)

Check nose wheel steering feedback 9-° position proximity switch



Check MLG spring cartridge for general condition

(32-61)

Inspect hub cap clip for controlled gap, general condition, fit & attachment



Check MLG assy. for excessive play.

(32-63)

20 of 115




120.350 #1 24.00 MO 8/26/2016 8/26/2018120.350 #2 24.00 MO 8/26/2016 8/26/2018

120.350 NA 24.00 MO 8/26/2016 8/26/2018

120.350 NA 800 FH 32796.1 33596.1

120.350 NA 1200 FH 32213.0 33413.0

120.350 #1 24.00 MO 8/26/2016 8/26/2018120.350 #2 24.00 MO 8/26/2016 8/26/2018

120.350 #1 24.00 MO 8/26/2016 8/26/2018120.350 24.00 MO 8/26/2016 8/26/2018120.350 #2 24.00 MO 8/26/2016 8/26/2018120.350 24.00 MO 8/26/2016 8/26/2018

507826 NA 5.00 YR 1/1/2013 12/31/2017

ALT282-24028 NA 3.00 YR 4/1/2014 3/31/2017

ALT282-24028 NA 15.00 YR 11/1/2010 10/28/2025

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 12.00 YR NA NA

NA FWD 5 YR NA NA507862 AFT 5 YR 1/1/2013 1/1/2018

Altitude Preselect system (Altitude Alert System) Verify operation

(34-11)

Check Cylinder Shutoff Regulator Valve Note: time of hydrostatic test(35-03)

Oxygen Cylinder Hydrostatic Test (Composite)(35-04)

(35-12)

FAR 91.411 & 91.413 Altimeter certification, Transponder certification

Check transponder system (Inspection(34-08)

(34-12)

Check overspeed warning by using anemometric bench test

AHRS & Standby compass (34-09)

(34-10)

Check overspeed warning through test switches or circuit breakers.

(34-12)

Chapter 35 Oxygen


PAX Oxygen Chemical Generator (Discard)(35-11)

Portable Oxygen Cylinder (Hydrostatic test) (Steel)

Oxygen Cylinder (Discard) (Composite)(35-05)

Check Altitude sensing switch operation(35-10)

21 of 115




NA FWD507862 AFT

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 4000.00 FH 32873.0 36873.024 MO 8/26/2016 8/26/2018

120.350 NA 10.00 YR NA NA

120.350 NA 5.00 YR NA NA

120.350 NA 5.00 YR NA NA

120.350 NA 4000.00 FH 31911.2 35911.2

P381 APU 500.00 AH 28139.8 28639.8

P381 APU 4500.00 AH 26256.7 30756.7

PN

P381 APU 750.00 AH 32873.0 33623.0PN 12.00 8/26/2016 8/26/2017

P381 APU 1000.00 AH 28139.8 29139.8

P381 APU 4500.00 AH 26256.7 30756.7

Chapter 49 Auxiliary Power

Functionally check pressure regulator of F/A O2 cylinder. (At time of Hydro test)(35-22)


Portable Oxygen Cylinder (Discard) (Steel)

"C" CHECK OR 24 Months(35-20) Check crew masks

(35-12)

UnlimitedUnlimited

Check altitude compensation

pressure regulators-bench check(35-19)

Check APU drain lines for blockage

(35-25)

Check Bleed Air leakage detection system(36-02)

Chapter 36 Pneumatic

Discard/Replace Protective Breathing Equipment (A/C Combi Only)(35-21)

Garrett APU Combustion Chamber Drain Orifice Fitting(49-01)

Functionally check F/A O2 cylinder. (At time of Hydro test)

GTCP-150(A)/(AA)

Garrett APU fuel filter element (Discard)(49-04)

Clean, perform fuel flow rate check & inspect Garrett Fuel

(49-02)

(49-03)

Check APU Chip detector GTCP-150(A)/(AA)

22 of 115




P381 APU 750.00 AH 32873.0 33623.012.00 8/26/2016 8/26/2017

P381 APU 300.00 AH NA NA






P381 APU 750.00 AH 32873.0 33623.012.00 8/26/2016 8/26/2017

P381 APU 750.00 AH 28139.8 28889.8PN

P381 APU 4500.00 AH 26256.7 30756.7

(49-07)

Check Sundstrand APU items for condition and Security (49-08)

Check Sundstrand APU model T-62T40C7E combustor housing assembly.

(49-05)

Garrett APU Oil Filter Element (Discard)(49-06)

Clean & flow-check Sundstrand APU Start Fuel Nozzle holder Assy. & flow Restrictor (Bench Check)

Nozzle Assemblies

Garrett APU Oil Change(49-13)

(49-15)

Garrett APU Hot Section Inspection

(49-09)

Inspect igniter plugGTCP-150(A)/(AA)

(49-14)

Check Sundstrand APU combustor housing drain elbow for cleanliness & obstructions (HIS) (Bench Check)(49-10)

Check Sundstrand APU Lubricating Oil & Discard the oil filter, Fuel Manifold Performed Packings & Fuel inlet filter (HIS) Bench Check)(49-11)

Check Sundstrand APU Fuel Pump Internal filter for contamination & damage & clean filter by Ultrasonic Method (HIS) Bench Check)(49-12)

23 of 115




P381 APU 4500.00 AH 26256.7 30756.7






P381 APU 4500.00 AH* 26256.7 30756.7

120.350 NA 2500.0 FH* 32796.1 35296.124 MO 4/1/2015 3/31/2017

120.350 NA 400.00 FH 32873.0 33273.02 MO 8/26/2016 10/25/2016

120.350 NA 4000.00 FH 32213.0 36213.0

120.350 NA 4000.00 FH 31911.2 35911.2

Check Sundstrand APU Oil levels & for leaks(49-22)

Check Sundstrand APU model T-62T-40C7E air inlet and compressor wheel.(49-23)

Sundstrand APU check for leaks & obstruction(49-20)

Check Sundstrand APU Combustor Housing Drain Discharge Line for Evidence of Fuel Leakage during start & early running(49-21)

Check Garrett APU Compressor Rotor for Damage, using a Fiberscope, by observing through compressor screen openings(49-16)

Sundstrand APU Harness Assy. (Visually check for condition & security)(49-19)

Visually check passenger/crew entry door locking mechanism,

Perform Garrett fuel flow rate check (49-23E)

Chapter 52 Doors

Lubricate escape hatch mechanism bearings.(52-06)

Verify operation of escape hatch locking mechanism(52-07)

Visually check cargo door locking mechanism, cables & spring for condition(52-13)

24 of 115




120.350 NA 400.00 FH 32796.1 33196.1

120.350 NA 400.00 FH 32796.1 33196.1

120.350 NA 2000.00 FH 32796.1 34796.124 MO 4/1/2015 3/31/2017

120.350 NLG 90000 FC 0 90000PN

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 LH 131054 FC 0 131054PN RH 131054 FC 0 131054

120.350 NA 16000 FC 0 16000PNSB 120-53-0071

120.350 NA 16000 FC NA NAPNSB 120-53-0071

120.350 NA 90000 FC 0 90000

folding flap mechanism & springs for condition(52-14)

Check minimum gap between passenger/crew entry door folding flap & door frame, with door closed & locked(52-15)

MLG to Fuselage Attach Rib120-17082

Bridge Interconnection Frame 4 to Fuselage

Windshield Upper Lug120-28503-001

Windshield Lower Lug120-28505-001

120-04145

MLG Wheelwell Rib 13 Fitting120-05618

MLG Wheelwell IB 11 fitting

MLG Wheel well Fwd. Fitting

Visually check escape hatches locking mechanisms(52-19)

Chapter 53 Fuselage Life Limits

Visually check passenger/crew entry door locking mechanism cams & springs for condition(52-16)

NLG Attach fitting120-19667-1, -2

120-05621

120-05619

MLG Wheelwell Door Aft Fitting120-05620

MLG Root Aft Fitting

MLG Root Fwd. Fitting120-05622

25 of 115




120.350 NA 600.00 FH 32796.1 33396.1

(61-11)

120.350 NA 400.00 FH 32796.1 33196.1

(61-13)

980913 LH 5000.00 FH 32869.0 37869.0950440 RH 5000.00 FH 32872.4 37872.4

(61-15)

LH Prop section LH 9000.00 FHRH Prop section RH 9000.00 FH

(61-18)


(61-19)

LH 10000.00 FH10000.00 FH10000.00 FH10000.00 FH

RH 10000.00 FH10000.00 FH10000.00 FH

(61-20) 10000.00 FH

LH 10000.00 FH10000.00 FH10000.00 FH10000.00 FH

RH 10000.00 FH10000.00 FH10000.00 FH

(61-21) 10000.00 FH


Check secondary low-pitch stop (beta) operation.

Inspect propeller control unit. Carry out a torque check of the primary quill on all PCU's that include a secondary drive quill.

Propeller hub major inspection. NOTE: According to Hamilton Sundstrand Maintenance Manual P5186, airworthiness

Outer Bearing race major inspection. NOTE: According to Hamilton Sundstrand Maintenance Manual P5186, airworthiness Limitation Section latest revision.

Blade and pin assembly major inspection. NOTE: According to Hamilton Sundstrand Maintenance Manual P5186, airworthiness Limitation Section latest revision.

Inner Bearing race (two piece) major inspection. NOTE: According to Hamilton Sundstrand Maintenance Manual P5186, airworthiness Limitation Section latest revision.

Actuator assembly major inspection. NOTE: According to

Reference Propeller section of this report for details


Reference LH Prop section of this report


Reference RH Prop section of this report



Chapter 61 Propellers

Verify overspeed governor operation





26 of 115




(61-22)

120.350 LH 800.00 FH 32809.2 33609.2

(71-12)

115630 LH 32809.2(71-13) 115663 RH 32872.4

115630 LH 3500.00 FH 30011.3 33511.3(72-03) 115663 RH 3500.00 FH 32872.4 36372.4

115630 LH-initial 3000.00 FH OC OCLH repeat 600.00 FH OC OC

115663 RH-initial 3000.00 FH OC OCRH repeat 600.00 FH OC OC

115630 LH-initial 3000.00 FH OC OCLH repeat 600.00 FH OC OC

115663 RH-initial 3000.00 FH OC OCRH repeat 600.00 FH OC OC

115630 LH 4000.00 FH NA by SN NA by SN115663 RH 4000.00 FH NA by SN NA by SN

120.350 LH 300.00 FH NA by SN NA by SN120.350 RH 300.00 FH NA by SN NA by SN

120.350 LH OC OC120.350 RH OC OC

115630 LH 600.00 FH 32558.9 33158.9115663 RH 600.00 FH 32872.4 33472.4

115630 LH 1200.00 FH 32558.9 33758.9115663 RH 1200.00 FH 32872.4 34072.4

After engine HMU or EEC replacement or

throttle rigging

Fuel Pump drive gear visual inspection(72-09)

Replace propeller overspeed governor hydraulic pump relief valve.

Chapter 72 Engines

Engine hot section inspection

Reduction gearbox input borescope inspection(72-08)

Hamilton Sundstrand Maintenance Manual P5186, airworthiness Limitation section latest revision.

Chapter 71 Power Plant

Check EEC NH overspeed protective function operation.

(72-10)

Check engine trim.

Visually inspect/clean/bubble point test engine fuel heater low pressure fuel filter

Visually inspect/clean/bubble point test engine HP fuel pump

Intercompressor case P2.5 cavity visual inspection for oil(72-11)

Chapter 73 Fuel Control(72-12)

Perform engine model PW118/118A/118B compressor wash

Manufacture Recommended

(73-01)

27 of 115




115630 LH 1500.00 FH 31990.8 33490.8115663 RH 1500.00 FH 32872.4 34372.4

115630 LH 800.00 FH 32809.2 33609.2115663 RH 800.00 FH 32872.4 33672.4

120.350 NA 24.00 MO 8/26/2016 8/26/2018

115630 LH 500.00 FH 32869.3 33369.3115663 RH 500.00 FH 32873.0 33373.0

115630 LH 4000.00 FH NA NA115663 RH 4000.00 FH NA NA

115630 LH 300.00 FH 32809.2 33109.2115663 RH 300.00 FH 32872.4 33172.4

115630 LH 2000.00 FH 31911.2 33911.2115663 RH 2000.00 FH 31911.2 33911.2

115630 LH 2000.00 FH 31911.2 33911.2115663 RH 2000.00 FH 31911.2 33911.2

120.350 NA 4000.00 FH 31911.2 35911.2

115630 LH 20.0 FH 32873.0 32893.0115663 RH 20.0 FH 32873.0 32893.0

115630 LH 1200.0 FH NA NAClean/check/bubble-point test

Chapter 79 Engine Oil

(79-01)

After cable replacement check MRB for inspection intervals

(76-01)

Verify engine isolation by observing actual closing of the shutoff valves by actuation emergency shutdown handle.

Check engine oil level

(76-02)

Chapter 74 Engine Ignition

(76-01) After cable replacement check MRB for inspection intervals

(74-01)

Visually inspect engine igniter plugs

Chapter 76 Engine Controls

Check engine condition control cable tension

Check engine power control cable tension

(73-08)

Visually inspect engine HMU, Fuel oil lines(73-08)

(73-13)Detailed inspection of fuel pump

(73-04)

Check HMU solenoid valve warning system & if valve is seized at de-energized position.(73-07)

Check HMU solenoid valve

control system Altitude switches.

filter element.(73-02)

Restore engine fuel nozzle. Bench test

28 of 115




115663 RH 1200.0 FH NA NA

115630 LH 1200.0 FH 32558.9 33758.9115663 RH 1200.0 FH 32655.4 33855.4

115630 LH 65.0 FH 32873.0 32938.0115663 RH 65.0 FH 32873.0 32938.0

115630 LH 65.0 FH 32873.0 32938.0115663 RH 65.0 FH 32873.0 32938.0

115630 LH 1200.0 FH 32518.5 33718.5115663 RH 1200.0 FH 32872.4 34072.4

NOTE: * RECOMMENDED TASK (79-10)

or oil change

engine scavenge & main oil filters(79-02)

Discard engine main oil filter

Monitor engine chip detector

(79-04)

(79-08)

Inspect main & scavenge oil filters bypass indicators

(79-09)

Check engine chip detector

29 of 115

Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163

Items S/N Position Life Last Done Next Due Remain

258 NLG 15000 FC 34447 49447 4284

56 NLG 15000 FC 44297 59297 14134

SWA001 NLG 15000 FC 44297 59297 14134

108 NLG 15000 FC 44297 59297 14134

H8346SUC8 NLG 90000 FC 34447 124447 79284PN

ER3012/292 NLG 90000 FC 34447 124447 79284PN

E5 6 SUC1 NLG 90000 FC 34447 124447 79284PN E5 9 SUC1 90000 FC 34447 124447 79284

100520SLC2 NLG 90000 FC 34447 124447 79284PN 100520SLC1 90000 FC 34447 124447 79284

AB 02 NLG 90000 FC 34447 124447 79284PN B042 90000 FC 34447 124447 79284

557084 NLG 90000 FC 34447 65267 79284PN

C2 NLG 90000 FC 34447 65267 79284PN

6A NLG 90000 FC 44297 64735 79284PN 90000

B14 NLG 90000 FC 44297 64735 19572PN

201 NLG 90000 FC 44297 64735 19572PN

R3-5-SUC20 NLG 90000 FC 44297 64735 19572PN

13US60537205 NLG 15000 FC 44297 59297 14134PN

09CGR02106 NLG 15000 FC 4/11/2021 59297 14134PN

Nose Landing Gear


All “due” times are referenced to aircraft total time and total cycles. Last Done column reflects time of last compliance with maintenance item or, in case of components which are moved with continued time, a calculation of

aircraft times which reflect, time since overhaul or last maintenance performed.

Restore NLG Shock Absorber, Steering Actuators, Rack & Selector Gear(32-10)

Restore NLG Main Drag Strut(32-11)

Box, Leg Strut19409-000-03

Restore NLG Spring Cartridge(32-14)

Restore NLG Aux. Drag Strut(32-15)

20117

Piston Tube19414-000-00

Pin, Leg Hinge19919

Pin, Torque Link20168

Torque Link, Half19417

Pin, Torque Link Central20169

Pin, Drag Strut Lower

20702

Drag Strut, Lower Half19424

Pin, Drag Strut Central20003

Drag Strut, Upper Half20597-000-01

Pin, Drag Strut Hinge20009

Inner Spring20701

Outer Spring

30 of 115

Aircraft Type: Embraer Brasilia N582SW 120-350TAT: 32873 Effective Date 8/25/2016TAC: 45163

Items S/N Position Last Done Next Due Remain

204 RH 15000 FC 45162 52545 7382

T98033 RH 15000 FC 33148 48148 2985

B70 RH 15000 FC 40688 55688 10525

419 RH 15000 FC 33144 48144 2984

2041 RH 104054 FC 37545 141599 96436PN 19671-000- 2042 104054 FC 37545 141599 96436

D3248 RH 90000 FC 3723 93723 48560PN

B05-34 RH 104054 FC 3723 107777 62614PN 19432 BA13250-8 104054 FC 3723 107777 62614

B411 RH 104054 FC 3723 107777 62614PN 20241

SUC01 RH 104054 FC 3723 107777 62614PN 19699-001

L14-228-D2 RH 90000 FC 3723 93723 48560PN

D621SUC20A RH 90000 FC 3723 93723 48560PN D611SUC20 90000 FC 3723 93723 48560

F5/204 RH 90000 FC 0 61750 16587PN 090420SLC2 90000 FC 0 61750 16587

15H5SUC8 1911 RH 90000 FC 0 71118 25955PN

B4-2 RH 90000 FC 0 89673 44510PN

B06-930 RH 104054 FC 0 103727 58564PN

B22 RH 104054 FC 0 103727 58564PN

SR1093 RH 30000 FC 24469 54469 9306PN

13US58191X17 RH 15000 FC 44297 59297 14134PN

13US60537112 RH 15000 FC 44297 59297 14134PN

All “due” times are referenced to aircraft total time and total cycles. Last Done column reflects time of last compliance with maintenance item or, in case of components which are moved with continued time, a

calculation of aircraft times which reflect, time since overhaul or last maintenance performed.

Registration:

RH Landing Gear

19783-000-01

Bell (MLG Oleo Strut)19676

Inner Spring20497

Outer Spring

20029-000-01

Drag Strut, Upper Half19437

Pin, Drag Strut Hinge20031-001

Pin, Drag Strut Central

Torque Link, Half

Torque Link, Center Pin

Drag Strut Lower Pin

Piston Tube19429-001

Pin, Leg Hinge19946-001

Pin, Torque Link20030-001

Drag Strut, Lower Half19439-001-01

(32-06)

Restore MLG Aux. Drag Strut

Bushing

Box, Leg Strut19427-001-01

Restore MLG Spring Cartridge

Life

Restore MLG Shock Absorber(32-02)

Restore MLG Drag Strut(32-03)

31 of 115

Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163

Items S/N Position Last Done Next Due Remain

B47 LH 15000 FC 37291 52291 7872

620 LH 15000 FC 44297 59297 14134

244 LH 15000 FC 44297 59297 14134

108 LH 15000 FC 44297 59297 14134

110321SLC2 LH 104054 FC 0 86568 41408PN 19671 110321SLC1 104054 FC 0 86568 41408

B01694 LH 90000 FC 0 83959 38796PN

B0117 LH 104054 FC 0 98013 52850PN 19432 B0212 104054 FC 0 98013 52850

H1 LH 104054 FC 0 86571 41408PN 20241

G5SUC20 LH 104054 FC 0 89108 43945PN 19699-001

770-7-B07B LH 90000 FC 0 83460 38297PN

B3/5 LH 90000 FC 0 83959 38796PN B3/15 90000 FC 0 83959 38796

1A LH 90000 FC 0 83959 38796PN 1B 90000 FC 0 83959 38796

JL-1429-10 LH 90000 FC 0 76468 31305PN

B57 LH 90000 FC 0 89590 44427PN

5H10SUC8 LH 104054 FC 0 89108 43945PN

LH 104054 FC 0 89108 43945PN

SR1018 LH 30000 FC 23387 53387 8224PN

13US58191X2 LH 15000 FC 44297 59297 14134PN

13US60537113 LH 15000 FC 44297 59297 14134PN

Torque Link, Half

19427-001-01

LH Landing Gear


All “due” times are referenced to aircraft total time and total cycles. Last Done column reflects time of last compliance with maintenance item or, in case of components which are moved with continued time, a calculation

of aircraft times which reflect, time since overhaul or last maintenance performed.

Restore MLG Shock Absorber(32-02)

Restore MLG Aux. Drag Strut

Restore MLG Drag Strut(32-03)

Restore MLG Spring Cartridge(32-06)

Bushing

20030-001

19783-000-01

20031-001

Bell (MLG Oleo Strut)19676

Inner Spring20497

Outer Spring

Pin, Drag Strut Central

Drag Strut, Lower Half19439-001-01

Life

H4SUC10

Drag Strut, Upper Half19437

Pin, Drag Strut Hinge

Box, Leg Strut

20029-000-01

Torque Link,Center Pin

Drag Strut Lower Pin

Piston Tube19429-001

Pin,Leg Hinge19946-001

Pin,Torque Link

32 of 115

N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163

Serial #: 115630Utilization: High

32873.0 4516342956.8 59762

Oprtrs MfrsTurbomachine: TSN: 42956.8 TCSN: 59762

TSO: 2861.7 TCSO: 3661 NA O/C FHTTSHSI: 2861.7 TCSHSI: 3661

TSN: 42956.8 TCSN: 59762TSO: 2861.7 TCSO: 3661 NA O/C FH

PN SN CSN/TSN Remaining Limit3040689 EAAC000R028 3661 14455 18116 CYC3043294 A00351LP 3661 14411 18072 CYC3039640 A00360ED 3661 7417 11078 CYC3041511 A0035TD8 3661 11339 15000 CYC

3111901-01 VARIOUS 3661 11339 15000 CYCHP Turbine Rear Cover 3039639 A0035T83 3661 11339 15000 CYCAir Interstage Seal 3039172 UAAB4801 3661 11339 15000 CYCLP Disk 3036412 A0035LM2 3661 11336 14997 CYC1st Stage PT Disk 3038613 A0023R94 12260 17740 30000 CYC2nd Stage PT Disk 3033914 A002AH4T 12260 17740 30000 CYC

NOTE:

This engine was overhauled by Standard Aero Sept, 2012 at TET of 40095.1 and TEC 56101, no hot section has been accomplished since the overhaul.

LH Engine

Aircraft Registration No.:Effective Date:

Limits

Left Hand Engine: PW118AECTM Status:

HP Disk

Unknown

A/C Time at install: A/C Cycles at install:

Reduction Gearbox:

ENGINE TT at install: ENGINE TC at install:

HP Turbine Blades

LP ImpellerHP ImpellerHP Turbine Front Cover

Please note the cycle remaining for the HP impeller, LP impeller are figures provided by SkyWest Airline using there formula provided in the Operators program, limits in this report are based on the P&W factoring program based on the engine being operated at the 118B rating.

33 of 115


Serial #: 115663Utilization: High

32873.0 4516338255.9 52085

Oprtrs MfrsTurbomachine: TSN: 38255.9 TCSN: 52085

TSO: 11635.1 TCSO: 15544 NA O/C FHTTSHSI: 7855.1 TCSHSI: 10976

TSN: 38255.9 TCSN: 52085TSO: 11635.1 TCSO: 15544 NA O/C FH

PN SN CSN/TSNRemaining Limit3040689 A0020DB4 15544 6800 18116 CYC3043294 A0021CMM 15544 6783 18072 CYC3039640 A002WMCB 4568 6510 11078 CYC3041511 A002WDBH 4568 10432 15000 CYC3111901-0VARIOUS 4568 10432 15000 CYC

HP Turbine Rear Cover 3039639 A002WF21 4568 10432 15000 CYCAir Interstage Seal 3039172 UAAA0845 4568 10432 15000 CYCLP Disk 3036412 A002WAFD 4568 10429 14997 CYC1st Stage PT Disk 3038613 A002YR00 4568 25432 30000 CYC2nd Stage PT Disk 3033914 A00203C3 4568 25432 30000 CYC

This engine had a repair to the HP vanes prior to departure from the Skywest program, no life limited items were replaced at this time.

RH Engine


Limits

Right Hand Engine: PW118A

A hot section inspection was accomplished March of 2012 where numerous life limited parts were replaced, refer to the life limited sheet provided by Skywest for a quick reference to cycles remaining.The last overhaul was accomplished by Standar Aero May of 2007 at a TET of 26620.8 and TEC of 36541.

ENGINE TC at install:

Reduction Gearbox:

ECTM Status: Unknown

A/C Time at install:

HP Turbine Front Cover

HP Turbine Blades

A/C Cycles at install:

HP Disk

LP ImpellerHP Impeller

ENGINE TT at install:

Please note the cycles remaining for the HP impeller and LP impeller are figures provided by SkyWest Airlines using there formula provided in the Operators program , limits in this report are based on the P&W factoring program based on the engine being operated at the 118B rating.

34 of 115


Manufacturer: SN: P-381

Model:

TTSN: 28226 TCSN: UNK

TTSHSI: 1969 TCSHSI: UNK 4500 FH

Remaining LimiterNA 25000 CYCNA 15000 CYCComp. Wheel PN 167200-1

Auxiliary Power Unit (APU)Garrett/Alliedsignal

GTCP-150 (A)/(AA)

Internal Components-Sundstrand APU ONLY

APU


Limits

Turbine Wheel PN 167222-1

35 of 115


Model: Hamilton Standard 14RF-9

Left Serial #: 98111432873 45163

UNK UNK

TSN: UNK TSMI: 7891.37/2/2011 - NOTE: Major Inspection time/date info based upon highest time component!

9000 HRS7 YRS

Actuator: 10000 HRS10000 HRS

7 YRS10000 HRS

7 YRS10000 HRS

7 YRS10000 HRS

7 YRSBlade #4 6726.2 3273.811/18/2013 11/18/2020887606

Blade #3 1953.0 8047.09/22/2013 9/22/20209810058

Blade #2 5792.7 4207.32/2/2012 2/2/2019888984

Hub:

960412 1109.1 8890.9

Blade #1 936.7 9063.36/21/2014 6/21/2021885404

6442.2 2557.87/2/2011 7/2/20182010090388

Date of Major Inspection:Serial No. Time Since Major Inspection Remaining Limiter

A/C Time at install: A/C Cycles at install:Prop time at install: TSMI at time of install:

LH PROPELLER


Limits

36 of 115


Model: Hamilton Standard 14RF-9

Right Serial #: 98111532481.4 44573

UNK UNK

TSN: UNK TSMI: 9497.611/1/2010 - NOTE: Major inspection time/date info based upon highest time components!

Hub: 9000 HRS7 YRS

Actuator: 10000 HRS10000 HRS

7 YRS10000 HRS

7 YRS10000 HRS

7 YRS10000 HRS

7 YRSBlade #4 8046.6 1953.411/1/2010 11/1/2017856348

Blade #3 3558.4 6441.63/10/2013 3/10/2020863167

Blade #2 291.3 9708.712/30/2014 12/30/20212014090247

981014 3181.6 6818.4

Blade #1 5937.4 4062.61/23/2012 1/23/2019867223

Limiter291.3 8708.7

12/30/2014 12/30/20212013040013

Prop time at install: TSMI at time of install:

Date of Major Inspection:Serial No. Time Since Major Inspection Remaining

RIGHT PROPELLER


Limits

A/C Time at install: A/C Cycles at install:


Mods, STC's and Repairs

ircraft Registration NoEffective Date:

Limits

Modifications/STC ListingsDocumentDate/EA #


21-2032869.3 33269.3

22-0532869.3 33269.3

25-0732796.0 33196.0

25-29

NA NA

25-30

NA NA

27-3032796.0 33196.0

28-2532796.0 33196.0

29-0432796.0 33196.0

Verify FLAP operation usingoverride switches(MSI 27-51-02).

Operational Check Fuel Quantity Indicating System (Measuring Sticks).

EMBRAER A CHECK

Aircraft Registration No.:Date:

Check that ELECTRONIC BAY NACA inlet valve is closed below 20°C (68°F) and that recirculation fans are operating.

Check autopilot APS-65 servos operation with autopilot engaged(aileron, elevator, rudder, and elevator trim).

Visually check toilet WASTE CONTAINER DOOR for condition, operation, and proper sealing (MSI 25-41-01).

Inspect (General Visual) VerticalCargo Nets and strap attachingfittings for integrity and generalcondition.NOTE: Applicable to aircraftFULL CARGO (EMB-120FC)only.

Inspect (General Visual) Horizontal Cargo Arresting Net and attaching fittings for integrity and general condition.NOTE: Applicable to aircraftL CARGO (EMB-120FC)only.

Visually check PRIMARY RETURN FILTER elements (green and blue systems) for contamination (MSI 29-11-03).

32-65

32796.0 33196.0

35-23

32796.0 33196.0

61-03

32796.0 33196.0

61-04

32796.0 33196.0

61-0732796.0 33196.0

61-0832796.0 33196.0

Visually check PROPELLER model 14RF-9 SPINNER BULKHEAD for cracks,nicks, gouges, and security.Check SLIP RINGS for cleanliness,security, pitting and grooving,signs of electrical arcing, anddeteriorated insulation.(MSI 61-20-05).

Visually check PROPELLER model 14RF-9 BLADE SHANK for damage andsecurity.

Remove PROPELLER model 14 RF-9RELIEF VALVE and adapter andvisually inspect for contamination,cracks or other sort of

Lubricate Nose Landing Gear PistonTube and Scraper.NOTE – Applicable to AircraftPost-Mod SB 120-32-0538Equipped with Nose LandingGear leg P/Ns:-P/N 19730-000-00 to P/N19730-000-17-P/N 19730-100-00 to P/N19730-100-17 (Post-Mod SB120-32-0534)-P/N 24080-000-00

Visually check flight attendantoxygen cylinder pressure gaugeindication.NOTE: Or according to LocalRegulatory AuthorityRequirements.

Visually check PROPELLER model 14RF-9 bonded and detachable HEATERLEADS for cleanliness, security,cracks, and deterioratedinsulation on wiring.(MSI 61-20-05).

61-09

32796.0 33196.0

61-1032796.0 33196.0

61-1632796.0 33196.0

61-1732796.0 33196.0

76-07 32869.3 33269.3

71-0132796.0 33196.0

71-0232796.0 33196.0

71-0332796.0 33196.0

71-0432796.0 33196.0

71-05

32796.0 33196.0

Visually check engine cowling HINGES for condition.(MSI 71-11-01).

Visually check engine cowling fixed elements for condition. (MSI 71-11-04).

Visually check engine cowling rear doors HOOK LATCHES for condition(MSI 71-11-07).

Visually check engine cowling cooling air FLEXIBLE HOSES for condition.(MSI 71-11-09/10/11/12).

Check oil level in propellermodel 14 RF-9 HUB.

Check of propeller blade leadingedge (nickel sheath).

Check on propeller blade retaining ring for cracks, corrosionand security.

Check flight idle stop system

Visually check PROPELLER model14 RF-9 HUB for cracks, dents,nicks, and corrosion. Do a torquecheck of the hub retaining nuts.

Visually check engine FORWARD AND AFT MOUNTS and ATTACHMENTS forcondition, and perform drift inspection.NOTE - With engine installed.- Threshold inspection: 2000 FH

71-06

32796.0 33196.0

71-07

32796.0 33196.0

71-08

32796.0 33196.0

71-0932796.0 33196.0

5310-132-02E 32796.0 33196.0

5330-161-02E261

32796.0 33196.0

5330-263-02E264267268

32796.0 33196.0

321-02Z Perform external general visual inspectionof the zone, including visual examinationof the vortex generators (PRE-MOD.SB 120-055-0008).

Visually check engine air intakeduct FLEXIBLE SEALS for condition(MSI 71-61-03).

Toilet drain valve support.

Fuselage aft section I (cargocompartment).- Skin at cargo door cutout.- Cargo door frame and stops.Requires fully-open door.

Fuselage aft section I (cargocompartment) skin and fastenersat frame 46

Visually check engine TORQUE TUBES AND ATTACHMENTS forconditionNOTE - With engine installed.- Threshold inspection: 2000 FH(MSI 71-21-04).

Visually check engine CATCHER MOUNTS AND ATTACHMENTS forcondition.NOTE - With engine installed.- Threshold inspection: 2000 FH(MSI 71-21-03).

Visually check engine air intakeduct attaching CLAMP forcondition(MSI 71-61-05).

NA BY SB 120-055-0008 COMPLIANCE

323-01Z

326-01Z

500-01Z600-01Z

711-01Z

32796.0 33196.0

721-01Z731-01Z

32796.0 33196.0

ZONE 711 - NOSE LANDING GEAR.– Perform external general visual inspectionof the zone.NOTE:EWISRequires doors opening

ZONES 721/731 - MAIN LANDING GEAR.– Perform external general visual inspectionof the zones.NOTE:EWISRequires that doors be opened.

ZONE 323 - VERTICAL STABILIZER LEADINGEDGE.– Perform external general visual inspectionof the zone, including visual examinationof the vortex generators (Pre-Mod.SB 120-055-0008).

ZONE 326 - RUDDER I– Perform external general visual inspectionof the zone, including visual examinationof the vortex generators (Pre-Mod.SB 120-055-0007).

ZONES 500/600 - WINGS, FLAPS, AND AILERONS.– Perform external general visual inspectionof the VORTEX GENERATORS (PRE-MOD.SB 120-057-0025).




43 of 115


TASK #(21-05) 32796.0 33796.0 A1, A3, A5, A Bridge

(21-07) 32796.0 33796.0 A1, A3, A5, A Bridge

(27-56) NA NA

(30-11) 32796.0 33796.0 A1, A2, A3, A4, A5, A6, A Bridge

(35-08) 32492.0 A2, A4, A6, A Bridge

(52-20) 32492.0 33492.0 A2, A4, A6, A Bridge

(76-08) 32796.0 33796.0 A1, A3, A5, A Bridge

(79-08) 32869.3 Service

412-01Z 32796.0 33796.0 A1, A3, A5, A Bridge422-01Z

5710-143-01E 32796.0 33796.0 A1, A2, A3, A4, A5, A6, A Bridge

DISCRIPTION

Check PASSENGER/CREW ENTRY DOOR/LANDING GEAR accumulator nitrogencharge.

Visually inspect flight idle stopsystem components.

EMBRAER 2A CHECK

Aircraft Registration No.: Date:

Wing center section: Lower skin panel and access panels from CL to wing rib 3.Requires fairing removal.

ZONES 412/422 - ENGINE (LH/RH).- Perform internal general visual inspectionof the zones.NOTE:EWIS

Visually inspect flight idle stopsystem components.

Clean ELECTROPNEUMATIC OUTFLOWVALVE seat.

Clean PNEUMATIC OUTFLOW VALVEseat. NOTE – In flights where smoking is allowed, carry out cleaning every 2A.

Visually inspect the washers in the inboard and outboard flaps for general condition, integrity and delamination of aluminum washers (feeler blades).NOTE F i l d SB 120 057Check carbon brushes of propellerbrush block for wear and damage

Check COCKPIT PRESSURE GAUGEindication by comparing withcharging pressure gauge(MSI 35-20-02).


27-57

31407.0 32907.0

5310-221-05E 32796.0 34296.0

5310-231-04E232 32796.0 34296.0

5320-245-01E246 32796.0 34296.0

5320-251-02E252253254

32796.0 34296.0

5330-263-03E264267268

32796.0 34296.0

5750-572-01E672 32213.0 33713.0

5750-582-01E682

32213.0 33713.0

EMBRAER 3A CHECK

Fuselage forward section IIIcrown skin panel.

Fuselage center section I crownskin panel.

Aircraft Registration No.: Date:

Inspect the rollers and the washers in inboard and outboard flaps, paying special attention to the washer wear limits.NOTE - For airplanes post-mod.SB 120-057-0011.

Fuselage center section II (passengercabin) dome skin panel.

Fuselage aft section I dome skinpanel.

Inboard flap skin panels, tracks,vane, and vane support ribs.

Outboard flap skin panel, trackssupport ribs, inboard andoutboard vane, and vane supportribs.

Fuselage forward section II dome skin panel.


21-07

32796.0 34296.0

A1, A3, A5, A Bridge

21-03

32796.0 35296.0


Clean PNEUMATIC OUTFLOW VALVEseat.NOTE – In flights where smoking is allowed, carry out cleaning every 2A.

Replace AIR FILTER element (MSI 21-31-05). NOTE: In flights where smoking is not allowed, replace every 8A.Check POSITIVE PRESSURE RELIEFVALVE in both the electropneumatic and pneumatic outflow valves (MSI 21-32-01).Clean ELECTROPNEUMATIC OUTFLOWVALVE seat.NOTE – In flights where smoking is allowed, carry out cleaning every 2A.Clean PNEUMATIC OUTFLOW VALVEseat.NOTE – In flights where smoking is allowed, carry out cleaning every 2A.Check NEGATIVE PRESSURE RELIEFVALVE in the electropneumatic outflow valve (MSI 21-32-02).Check CABIN ALTITUDE LIMITINGVALVE in the electropneumatic outflow valve.

EMBRAER 4A CHECK



21-05

32796.0 35296.0

21-1131407.0 33907.0

24-14 32492.034992.0

24-20 32492.034992.0

25-03

31911.0 34411.0

25-0531407.0 33907.0

25-2632492.0 34992.0

27-09

31911.2 34411.2

27-18

32213.0 34713.0


Verify isolation between back upbuses and main/emergency buses.

Check external power OVERVOLTAGEPROTECTION circuit.

Perform quick depressurization by actuation of the dump switch and by operation in manual mode.

Clean ELECTROPNEUMATIC OUTFLOWVALVE seat.NOTE – In flights where smoking is allowed, carry out cleaning every 2A.

Visually inspect cockpit seats HARNESS/INERTIAL REEL in detail for wear, deterioration, and damage(MSI 25-11-03).

Visually check attendant SEAT HARNESS and passenger SEAT BELTS

Visually check cockpit and passenger cabin areas for condition.

Check tension of AILERON TRIMCABLESNOTE - Check cables tension at first A before escalating to 5A(MSI 27-10-01).

Check RUDDER PCU LINKS ANDBEARINGS for integrity, interferenceand abnormal friction.(MSI 27-22-01).

EMBRAER 5A CHECK

27-32

31407.0 33907.0

27-3331407.0 33907.0

29-01 32492.0

34992.0

30-03

32796.1 35296.1

30-0432796.1 35296.1

30-0532796.1 35296.1

30-1632213.0 34713.0

32-0131407.0 33907.0

32-0931407.0 33907.0

32-3332796.1 35296.1

35-2432796.1 35296.1

Verify pressurization STATIC PORTHEATING ELEMENT operation.

Functionally check low speed aural/visual alarm system.

Visually check FLAP ACTUATOR RODfor conditionNOTE - Requires access panelremoval and flaps in downposition.(MSI 27-53-02/03).

Visually check flap actuatorELECTRICAL CONNECTOR for security(MSI 27-53-02/03).

Check HYDRAULIC RESERVOIR PRESSURIZATION SYSTEM including low pressure indication (MSI 26-11-03).

Check total-air-temperature (TAT) sensor heating INDICATION RELAY operation.NOTE - If TAT sensor is installed.(MSI 30-33-02/03).

Verify WINDSHIELD WIPERoperation(MSI 30-42-01/02/03/04).

Service MAIN L/G SHOCK ABSORBER (MSI 32-12-05).

Service NOSE L/G SHOCK ABSORBER (MSI 32-22-05).

Lubricate emergency and parkingbrake ACTUATION LEVER(MSI 32-43-04).

Visually check flight attendantcontinuous flow mask.

52-0132796.1 35296.1

52-0331911.2 34411.2

52-0431620.0 34120.0

52-0531620.0 34120.0

52-06

32796.1 35296.1

52-1031620.0 34120.0

52-1832796.1 35296.1

56-0132492.0 34992.0

5310-121-02E/122122 32796.1 35296.1

5310-221-03E/222 32796.1 35296.1

Check DIRECT-VISION WINDOW/EMERGENCY EXIT operation.

Visually check windshield sealant for condition.

Lubricate PASSENGER/CREW ENTRYDOOR BEARING AND LIFTING CAM(MSI 51-12-01).

Verify PASSENGER/CREW ENTRY DOOREMERGENCY VALVE operation(MSI 52-13-03).

Fuselage forward section II external skin panels and fasteners at forward pressure bulkhead.

Fuselage forward section II external skin panels and fasteners at forward pressure bulkhead.

Verify PASSENGER/CREW ENTRY DOORCOMPENSATING ACCUMULATOR operation (MSI 52-13-04).

Verify PASSENGER/CREW ENTRY DOORRELIEF VALVE operation(MSI 52-13-06).

Lubricate escape hatch mechanismBEARINGS.NOTE - Requires removal of escapehatches and their lining(MSI 52-22-01/52-22-02).

Check PASSENGER/CREW ENTRY DOORPRESSURE SWITCH (MSI 52-71-01).

5410-413-01E423414424415425416426417427418428431441432442433443434444435445436446

32492.0 34992.0

5410-432-02E442 32492.0 34992.0

5410-432-05I442

NA by SN NA AC SN

5510-333-02E334 32492.0 34992.0

5510-333-04E334 32492.0 34992.0

5510-333-05E334 32492.0 34992.0

Nacelle skin panel and fastenersbetween frames 5 and 8.

Nacelle skin panel.

Horizontal stabilizer lower skinfasteners at front spar and rearspar.

Horizontal stabilizer upper skinpanel.

Special detailed inspection forframe 1, using dye penetrantinspection.NOTE - Applicable to aircraftwhich logged more than12,000 FC and Pre-ModSB 120-54-0036.

Horizontal stabilizer upper skinfasteners at front spar and rearspar.

5510-333-06E334 32492.0 34992.0

5750-582-03E682

31911.2 34411.2

231-02Z232-02Z

31911.2 34411.2

241-02Z242-02Z

31911.2 34411.2

251-02Z252-02Z

31911.2 34411.2

Seat tracks for condition.(*): Applicable to aircraft EMB-120 COMBI,FULL CARGO (EMB-120FC) and QUICKCHANGE.

Horizontal stabilizer lower skinpanel.

Externally inspect the compositeoutboard flap actuator supportrib region.NOTE: Threshold inspection at16000 FC and subsequentinspections every 5A.



N582SW Serial #:TAT: 32873 Date: 8/25/2016TAC: 45163

20-21

31911.2 35911.2 1C

21-01

31911.2 35911.2 1C

21-02

31911.2 35911.2

1C

21-13NA NA POST MOD

21-14

31911.2 35911.2 1C

Check triple indicator ALTITUDE WARNING switch NOTE - For aircraft Pre-Mod. S.B.120-021-0022, only. (MSI 21-33-01).

Clean and visually check HEAT EXCHANGER for condition of core (MSI 21-51-04).Check PACK OVERHEAT switch NOTE - Requires access dooropening (MSI 21-51-08).

Aircraft Registration No.:

Inspect (General Visual) EWIScomponents of HYDRAULIC PUMPPOWER SUPPLY for signs of damage,proper installation, chafing andgeneral condition.NOTE: EWISRequires access panel removal.

Verify ventilation system CHECK VALVE operation (MSI 21-26-02).Verify ventilation system VENTILATION VALVE operation. Replace AIR FILTER element (MSI 21-31-05). NOTE: In flights where smoking is not allowed, replace every 8A. Check POSITIVE PRESSURE RELIEFVALVE in both the electropneumatic and pneumatic outflow valves (MSI 21-32-01).Clean ELECTROPNEUMATIC OUTFLOWVALVE seat. NOTE – In flights where smoking is allowed, carry out cleaning every 2A. Clean PNEUMATIC OUTFLOW VALVE seat. NOTE – In flights where smoking is allowed, carry out cleaning every 2A. Check NEGATIVE PRESSURE RELIEF VALVE in the electropneumatic outflow valve (MSI 21-32-02). Check CABIN ALTITUDE LIMITING VALVE in the electropneumatic outflow valve.

Verify ventilation system VENTILATION VALVE operation. Replace AIR FILTER element (MSI 21-31-05).NOTE: In flights where smoking is not allowed, replace every 8A. Check POSITIVE PRESSURE RELIEFVALVE in both the electropneumatic and pneumatic outflow valves (MSI 21-32-01).Clean ELECTROPNEUMATIC OUTFLOWVALVE seat. NOTE – In flights where smoking is allowed, carry out cleaning every 2A. Clean PNEUMATIC OUTFLOW VALVE seat. NOTE – In flights where smoking is allowed, carry out cleaning every 2A. Check NEGATIVE PRESSURE RELIEF VALVE in the electropneumatic outflow valve (MSI 21-32-02).Check CABIN ALTITUDE LIMITINGVALVE in the electropneumatic outflow valve.

EMBRAER C CHECK

120-350

21-1531911.2 35911.2 1C

21-2332481.0 36481.0 Pt_Stc

21-24

NA NA

21-2531911.2 35911.2 1C

21-2631911.2 35911.2 1C

21-27

NA by SN NA by SN

23-03

31911.2 35911.2 1C

24-18 31911.2 35911.2 1C

25-0131911.2 35911.2 1C

25-1128458.4 32458.4 2C

25-1831911.2 35911.2 1C

25-2732492.0 36492.0


26-06

31911.2 35911.2 1C

Operationally check air conditioningdistribution System.NOTE - Applicable to aircraftFULL CARGO (EMB-120FC),QUICK CHANGE and EMB-120COMBI.

Inspect(Detailed Inspection)Exhaust Hose of the ElectronicCompartment ventilation system

Operationally check the Electronic Compartment ventilation system check valve

Clean the Temperature Control Valve feeding line filter By Ultrasonic Method.NOTE - Applicable only to A/C post-mod S.B. 120-21-0052.

Check PACK OVERHEAT switch NOTE - Requires access door opening(MSI 21-51-08).

Check altitude warning switch. NOTE - For airplanes Post-Mod. S.B. 120-021-0022 only.

Visually check crew seats structureand attachment, includingharness attachment, for condition

Visually check passenger seats structure and attachment, including safety belts attachment for condition.

Visually check ENGINE/WHEELWELL AND APU FIRE EXTINGUISHER BOTTLEGAUGES for proper pressure NOTE - If APU is installed (MSI 26-22-03).

Check STATIC DISCHARGERS ohmic resistance and electrical continuity from base to aircraft structure(MSI 23-61-01)

Check APU generator OVERVOLTAGE

Lubricate cockpit seat BEARING,HAND LEVER HINGE, LOCK PIN, ANDCABLES (MSI 25-11-01).

Visually check cargo AFT PARTITION ATTACHMENT PINS for condition.NOTE - Requires rear partition

26-13

31911.2 35911.2 1C

26-14

31911.2 35911.2 1C

26-18

31911.2 35911.2 1C

26-23

31911.2 35911.2 1C

27-0331911.2 35911.2 A2, A

Bridge

27-04

NA NA

27-05

31911.2 35911.2 CABLE

27-13

31911.2 35911.2 1C

27-14

NA by PN NA by PN

27-15

31911.2 35911.2 1C

Check lavatory fire extinguisher temperature indicator and bottle for weight, corrosion, scratches dents, dings, bent tubes or otherevidence of physical damage. (if installed)

Perform functional check of baggage compartment fire extinguishing system (covering the pressure switch, cartridge, baggage fire extinguishing switch, and electrical hardware)NOTE: only for baggagecompartment class “C”.

Visually check the fire extinguishingsystem nozzles fordamage.NOTE: (1)Applicable only to baggagecompartment class “C”.

Lubricate AL DISCON-NECT SYSTEM(MSI 27-10-01).

Discard “HALONITE MODELportable fire extinguisher NOTE -Or after its utilization, or according to LocalAuthorities Regulations

Verify RUDDER PEDAL ADJUSTMENToperation(MSI 27-21-03).

Lubricate AILERON TRIM TABACTUATORNOTE - Applicable only to P/Ns 120-19676-004 and-006. (MSI 27-10-02).

Visually check AILERON CONTROLPATH from control wheel to forward quadrants. Check control wheels, pulleys, and quadrants for wear, corrosion, cracks and security. Check chain for corrosion and cables for corrosion and bird caging.(MSI 27-10-01).

Lubricate RUD G SYSTEMCONTROL KNOB.(MSI 27-21-02).

Lubricate RUDDER TRIMMINGACTUATOR.(MSI 27-21-02).NOTE - Applicable only to P/Ns 120-17211-001, 120-17211-002,003, and 120-17211-007.

27-1631911.2 35911.2 1C

27-23

31911.2 35911.2 A2, A Bridge

27-24

31911.2 35911.2 CABLE

27-25

31911.2 35911.2 CABLE

27-27

NA NA

27-3431911.2 35911.2 1C

27-40 32492.036492.0 A4, A

Bridge

27-45 32492.036492.0 A4, A

Bridge

27-59

31407.0 35407.0 A6, A Bridge

27-60

31911.2 35911.2 1C

27-61 31911.2 35911.2 1C

Visually check ELEVATOR CONTROLPATH from control column to FWDquadrants. Check control columns,rods and quadrants for wear,corrosion, cracks, and security.(MSI 27 31 01)

Lubricate ELEVATOR TAB ACTUATORS(MSI 27-31-01).NOTE - Applicable only to P/Ns120-19685-001 and120-19685-003.

Visually check GUST LOCKING MECHANISM for condition.

Verify stall warning system FAST/SLOW INDICATOR operation.

Lubricate RUDDER PEDAL ADJUSTMENTMECHANISM(MSI 27-21-03).

Lubricate ELEVATOR CONTROLDISCONNECT SYSTEMNOTE - Requires access dooropening.(MSI 27-31-01).

Operationally check air conditioning distribution System. NOTE - Applicable to aircraft FULL CARGO (EMB-120FC), K CHANGE and EMB-120 COMBI.

Verify stall warning system FAST/SLOW INDICATOR operation.

Check bonding ohmic resistance between the flap track and fuselage as well as the contact pressure of the track bonding spring- loaded shoe.Lubricate the aileron trim actuator chain.

Lubricate the aileron trim actuator chain.Lubricate the elevator trim actuator chain.Visually check rudder control path from pedals to PCU summing lever. Check pulleys, quadrants, fairleads, turnbuckles, and control rods for wear, corrosion, cracks and security. Check cables for wear, broken strands, corrosion, kinks, and bird caging.Lubricate flap actuator end-fitting bearing.NOTE: Applicable to aircraft S/N 292/999.Check pusher servo clutches for limiting torque

Lubricate the elevator trim actuator chain.

27-62

31911.2 35911.2 CABLE

27-6431911.2 35911.2 1C

27-68

31911.2 35911.2 1C

27-69

NA by SB NA by SB NA by SB

28-0131911.2 35911.2 1C

28-0431911.2 35911.2 1C

28-0831911.2 35911.2 1C

28-10

31911.2 35911.2 1C

28-11

31911.2 35911.2 1C

29-0331911.2 35911.2 1C

29-0531911.2 35911.2 1C

29-08 31911.2 35911.2 1C

29-1328458.4 32458.4

2C

32-1831911.2 35911.2

Visually check rudder controlpath from pedals to PCU summinglever. Check pulleys, quadrants,fairleads, turnbuckles, andcontrol rods for wear, corrosion,

k d it Ch k bl

Check pusher servo clutchesfor limiting torque

FUNCTIONALLY CHECK STALL WARNING SYSTEM ICE MODE. NOTE: Applicable Only to Aircraft POST-MOD SB 120-27-0092

Visually check VENT FLOAT VALVE for condition (MSI 28-12-01).

Check ELEVATOR TRIM TAB ACTUATORSDAMPERNOTE: Applicable only to aircraftPOST-MOD. SB 120-27-0095.

Check nose L/G steering RACK and SECTOR GEAR adjustment. (MSI 32-22-06).

Check HYDRAULIC SYSTEM for internal leakage (MSI 29-11-03).

Visually check HIGH-PRESSURE FILTER ELEMENTS (green and blue systems) for contamination (MSI 29-11-03).

Check HIGH-PRESSURE RELIEF VALVE.

Visually check hydraulic pump electrical motor BRUSHES.

Check APU FUEL SHUTOFF VALVENOTE - If APU is installed. (MSI 28-24-01).

Check FUEL QUANTITY INDICATION SYSTEM (MSI 28-41-00).

Check engine fuel feed RELIEF VALVE operation.NOTE - Requires access door opening.

Visually check ENGINE FUEL FEEDLINE for leakages.NOTE - Requires access panel andmain landing gear door opening.(MSI 28-22-01).

32-2431911.2 35911.2

32-26

31911.2 35911.2

32-30 31911.2 35911.2

32-3931911.2 35911.2

32-4631911.2 35911.2

32-6031911.2 35911.2

32-6231911.2 35911.2

32-6631911.2 35911.2

34-07

31911.2 35911.2

35-01

31911.2 35911.2

35-0631911.2 35911.2

35-07

31911.2 35911.2

35-09

31911.2 35911.2

Check FREE-FALL MECHANICALCONTROL CABLE adjustment(MSI 32-34-03).

Check STEERING SYSTEM includingELECTRONIC CONTROL MODULECONTINUOUS MONITORING FUNCTIONoperation(MSI 32-50-05).

Check BRAKE METERING VALVE

Functionally Check Thermal Relief Valve of the Emergency / Parking Brake System.

Test high and low oxygen pressurelines for leaks.NOTE - The leak-test of paxoxygen system is notrequired for chemical

ti t

Check OXYGEN LOW PRESSURE SWITCH.(MSI 35-10-05).

Check OXYGEN SYSTEM PRESSURESWITCH .NOTE - Except for oxygen paxsystem with chemicalgenerators.

Verify EFIS remote units (DPU1,DPU2, MPU) and MFD and EFDS fanoperation.NOTE – If EFIS is installed(MSI 34-22B-09).

Verify landing gear OVERRIDESWITCH SYSTEM.

Check nose wheel steeringfeedback 9-degree positionproximity switch.

Check emergency and parkingbrake circuit.

Inspect for corrosion andlubricate main/nose landing gearspring box guide rod.

Verify PAX OXYGEN DOOR latchmechanism operation by positioningselector switch to MAN(MSI 35-20-02).NOTE - For airplanes equipped

ith h i l

35-10

31911.2 35911.2

35-1431911.2 35911.2

35-17

31911.2 35911.2

35-19

31911.2 35911.2

35-20 31911.2 35911.2

36-0331911.2 35911.2

49-1831911.2 35911.2

52-0831911.2 35911.2

52-0931911.2 35911.2

52-11

31911.2 35911.2

52-12

31911.2 35911.2

52-1731911.2 35911.2

52-2131911.2 35911.2

Check PASSENGER/CREW ENTRY doorMICROSWITCHES (MSI 52-72-01).

Check cargo door MICROSWITCHES.(MSI 52-72-02).

Lubricate CARGO DOOR BEARING ANDGEAR of lifting path.NOTE - Requires headlinerremoval(MSI 52-32-02).

Lubricate CARGO DOOR LOCKINGMECHANISMNOTE - Requires cargo doorlining and access panelremoval(MSI 52 32 01)

Check ALTITUDE COMPENSATINGPRESSURE REGULATORS.NOTE - (1) Except for oxygen paxsystem with chemicalgenerators.(2) F i l i d

Check crew masks.

Check bleed overheat switch.NOTE - Requires leading edgeremoval.

Check APU mounts for elastomercondition and elastomer - metalbond.

Check ALTITUDE SENSING SWITCHoperation(MSI 35-30-02).NOTE - For airplanes equippedwith toilet.

Visually check PASSENGER MASKS(MSI 35-20-03).

Check three-position valve.NOTE - Except for oxygen paxsystem with chemicalgenerators.

Visually check DIRECT-VISIONWINDOW LOCKING MECHANISM forcondition.

Check doors, direct-vision andescape hatches rigging.

61-01

31911.2 35911.2

71-10

31911.2 35911.2

73-0931911.2 35911.2

76-0431911.2 35911.2

76-0531911.2 35911.2

76-09

31911.2 35911.2

79-0531911.2 35911.2

5310-121-01E31911.2 35911.2

5310-231-02E232 31911.2 35911.2

5310-231-05E232

NA NA

5320-152-02E31911.2 35911.2

5320-241-01E242 31911.2 35911.2

5320-241-03E242 31911.2 35911.2

Check engine magnetic chipdetection warning system.

Fuselage forward section II externalskin panels, includingcontrols rigging door.

Fuselage forward section III(passenger cabin) window frames

Fuselage forward section IIIdummy pax window.NOTE: (If Installed)

Check FUEL LOW-PRESSURE WARNINGSWICTH.(MSI 28-42-01).

Check POWER LEVER MICROSWITCHSETTING.

Check CONDITION LEVER MICROSWITCHSETTING

Visually inspect (DetailedInspection) the power leversrollers for wear.NOTE – For aircraft PRE-MOD. SB120-76-0023 inspect atevery “C” check.– For aircraft POS-MOD. SB120-76-0023 inspect atevery “2C” check.

Visually check auxiliary pump andmotor for condition.NOTE - Requires thermalprotection removal(MSI 61-20-04).

Verify DRAIN COLLECTOR TANKRETURN LINE check valvesoperation.(MSI 28-23-03).

Toilet drain valve support.NOTE - Applicable to aft lavatoryinstallation only.

Fuselage center section I (passengercabin) external skinpanels.

Fuselage center section I (passengerwindow frames) external.

5320-251-03E252 31911.2 35911.2

5330-161-01E162

31911.2 35911.2

5330-163-01E164

31911.2 35911.2

5330-261-01E262265266

31911.2 35911.2

5330-263-01E264267268

31911.2 35911.2

5330-263-02I264267268

NA NA

5330-311-01I312

31911.2 35911.2

5720-521-01E621 31911.2 35911.2

5720-521-02E621 31911.2 35911.2

5720-522-01E622 31911.2 35911.2

5720-522-02E622 31911.2 35911.2

5720-541-01E641 31911.2 35911.2

Fuselage aft section I(cargocompartment) internal elementsabove floor:– Skin panel and splices.– Upper frame 46 and fin-to fuselagefitti f t

Fuselage aft section II (tailcone) internal elements:– Skin panel splices and doorcutouts.– Access door frame. B lkh d 48 49 50 d 51

Wing box beam lower skin accessopening and nacelle chord wiseangle attachment.

Wing box beam upper skin and nacellechord wise angle attachment.

Fuselage aft section I (cargocompartment) skin panel.Requires bumper plate removal (ifinstalled).

Fuselage aft section I (cargocompartment) skin, includingfasteners at rear pressurebulkhead below floor.

Fuselage aft section I (cargocompartment) skin panels.Requires dorsal fin fairingremoval.

Fuselage aft section I (cargocompartment) skin panels, includingfasteners at rearpressure bulkhead.Splice attachments at frame 47.

Fuselage center section II (passengerwindow frames) external.

Wing box beam upper skin andnacelle chord wise attachment.

Wing box beam lower skin, accessopenings, drain valve and nacellechord wise angle attachment.

Wing box beam lower skin, accessopening, and nacelle chord wiseangle attachment.

5330-263-C01I, 5330-264-C01I

5720-541-02E641 31911.2 35911.2

5720-542-01E642 31911.2 35911.2

5720-542-02E642 31911.2 35911.2

5720-551-01E651 31911.2 35911.2

5720-551-02E651 31911.2 35911.2

5720-552-01E652

31911.2 35911.2

5720-561-01E661

31911.2 35911.2

5720-561-02E661 31911.2 35911.2

211-01Z212-01Z

31911.2 35911.2

300-01Z

31911.2 35911.2

313-01Z

31911.2 35911.2

400-01Z

31911.2 35911.2

Wing box beam upper skin and fuelfiller cap.

ZONE 211/212 - NOSE UPPER AREA (LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel opening.

Wing box beam lower skin andaccess openings.

Wing box beam upper skin.

Wing box beam lower skin, accessopening, and nacelle chord wiseangle attachment.

Wing box beam upper skin and nacellechord wise angle attachment.

Wing box beam upper skin and nacellechord wise angle attachment

ZONES 300 - TAIL CONE AND EMPENNAGE GROUP.– Perform external general visual inspectionof all tail cone and empennageinstallation in major zone 300.

ZONES 313 - TAIL CONE FAIRING (APUINSTALLED).– Perform internal general visual inspectionof the zone.NOTE: EWISR i f i i d l l

ZONE 400 - POWER PLANT AND NACELLE -EXTERNAL.- Perform external general visual inspectionof all nacelle installation inmajor zone 400.



413-01Z414-01Z

31911.2 35911.2

415-01Z425-01Z

31911.2 35911.2

416-01Z426-01Z

31911.2 35911.2

417-01Z418-01Z

31911.2 35911.2

419-01Z429-01Z

31911.2 35911.2

423-01Z424-01Z

31911.2 35911.2

427-01Z428-01Z

31911.2 35911.2

431-01Z441-01Z

31911.2 35911.2

432-01Z442-01Z

31911.2 35911.2

433-01Z443-01Z

31911.2 35911.2

ZONES 423/424 - RH ENGINE FRONT LATERALCOWLING (LH/RH).- Perform internal general visual inspectionof the zones.R i l i

ZONES 427/428 - ENGINE REAR LATERALCOWLING (LH/RH).- Perform internal general visual inspectionof the zones.Requires access panel opening.

ZONES 431/441 - ENGINE FRONT FAIRING(LH/RH).- Perform internal general visual inspectionof the zones.Requires access panel opening

ZONES 432/442 - NACELLE FRONT STRUCTUREFORWARD OF MLG WHEELWELL (LH/RH).- Perform internal general visual inspectionof the zones.NOTE EWIS

ZONES 433/443 - NACELLE FRONT AREA OF MLGWHEELWELL (LH/RH).- Perform internal general visual inspectionof the zones.NOTE EWIS

ZONES 415/425 - ENGINE FRONT AND REARCOWLING (LH/RH).- Perform internal general visual inspectionof the zones.R i l i

ZONES 416/426 - ENGINE CENTER COWLING(LH/RH).- Perform internal general visual inspectionof the zones.R i l i

ZONES 417/418 - ENGINE REAR LATERALCOWLING (LH/RH).- Perform internal general visual inspectionof the zones.Requires access panel opening.

ZONES 419/429 - ENGINE TAIL PIPE ANDEJETOR (LH/RH).- Perform internal general visual inspectionof the zones.NOTE:EWISR i l i

ZONE 413/414 - ENGINE FRONT LATERALCOWLING.- Perform internal general visual inspectionof the zones.Requires access panel opening.

434-01Z444-01Z

31911.2 35911.2

435-01Z445-01Z

31911.2 35911.2

436-01Z446-01Z

31911.2 35911.2

500-02Z600-02Z

31911.2 35911.2

521-01Z621-01Z

31911.2 35911.2

541-01Z641-01Z

31911.2 35911.2

571-01Z671-01Z

31911.2 35911.2

581-01Z681-01Z

31911.2 35911.2

583-01Z683-01Z

31911.2 35911.2

713-01Z714-01Z

31911.2 35911.2

ZONE 434/444 - UNDERWING AREA OF MLGWHEELWELL (LH/RH).- Perform internal general visual inspectionof the zones.NOTE:EWIS

ZONES 435/445 - NACELLE REAR STRUCTURE(LH/RH).- Perform internal general visual inspectionof the zones.NOTE EWIS

ZONES 436/446 - CENTER FLAP.- Perform internal general visual inspectionof the zones.Requires access panel removal.

Perform external general visual inspectionof all wing, flaps, and aileronsinstallations in major zones 500/600

ZONES 521/621 - WING AREA BETWEEN AUXILIARYSPAR AND FRONT SPAR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE EWIS

ZONES 541/641 - WING AREA OUTBOARD OFNACELLE STRUCTURE FROM AUXILIARY SPAR TOFRONT SPAR AND FROM RIB 14 TO RIB 16(LH/RH)

ZONES 571/671 - WING TRAILING EDGE AFT OFREAR SPAR AND INBOARD OF NACELLE (LH/RH).– Perform internal general visual inspectionf th

ZONES 581/681 - WING TRAILING EDGE AFT OFREAR SPAR AND OUTBOARD OF NACELLE (LH/RH)– Perform internal general visual inspectionf th

ZONES 583/683 - AILERONS (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires fairing access panel removal.

ZONES 713/714 - NOSE LANDING GEAR FRONTDOORS (LH/RH).– Perform external general visual inspectionof the zones.R i th t d b d

715-01Z716-01Z

31911.2 35911.2

723-01Z724-01Z

31911.2 35911.2

725-01Z726-01Z

31911.2 35911.2

733-01Z734-01Z

31911.2 35911.2

735-01Z736-01Z

31911.2 35911.2

811-01Z

31911.2 35911.2

812-01Z821-01Z

31911.2 35911.2

812-02Z821-02Z 31911.2 35911.2

813-01Z31911.2 35911.2

822-01Z

31911.2 35911.2

Perform internal general visual inspectionof the zones.Requires door and lining removal

ZONE 813 - CARGO DOOR.- Perform external general visual inspectionof the zone.

ZONE 822 - EMERGENCY EXIT - GROUND LEVEL.- Perform external general visual inspectionof the zone.

ZONES 733/734 - LEFT MAIN LANDING GEARFRONT DOORS.– Perform external general visual inspectionof the zones.R i d d

ZONES 735/736 - LEFT MAIN LANDING GEAR REARDOORS.– Perform external general visual inspectionof the zones.R i l i

ZONE 811 - PASSENGER/CREW ENTRY DOOR.- Perform external general visual inspectionof the zone.

ZONES 812/821 - EMERGENCY EXIT-OVERWING(LH/RH).- Perform external general visual inspectionof the zones.

ZONES 725/726 - RIGHT MAIN LANDING GEARREAR DOORS.– Perform external general visual inspectionof the zones.R i d d

ZONES 715/716 - NOSE LANDING GEAR REARDOORS (LH/RH).– Perform external general visual inspectionof the zones.R i th t d b d

ZONES 723/724 - RIGHT MAIN LANDING GEARFRONT DOORS.– Perform external general visual inspectionof the zones.R i th t d b d

64 of 115


20-01 28458.4 36458.4

20-02 28458.4 36458.4

20-03

28458.4 36458.4

20-04

28458.4 36458.4

20-05

28458.4 36458.4

EMBRAER 2C CHECK


Clean fuselage area under passenger FLOOR; WIRING, SIDEWALL OUT- LETS ADJACENT AREA AND AREA UNDERTHE TOILET/GALLEY, if installed. NOTE - EWIS Requires floor panel removal.

Inspect (Detailed Inspection) EWIS Components of POWER FEEDERS AND WIRING BUNDLES for signs of damage, proper installation, chafing and general condition.NOTE EWISClean SIDEWALLS OUTLETS AND ADJACENT WIRING, if installed. NOTE - EWIS Requires lining and thermoacoustic insulation removal.

Inspect (General Visual) EWISComponents of POWER FEEDERS andWIRING BUNDLES for signs ofdamage, proper installation,chafing and general condition.NOTE: Applicable only to baggagecompartment class "D"– EWISRequires floor panel removal.

Inspect (General Visual) EWISComponents of POWER FEEDERS andWIRING BUNDLES for signs ofdamage, proper installation,chafing and general condition.NOTE: Applicable only to baggagecompartment class "D"– EWISRequires floor panel removal.

65 of 115


EMBRAER 2C CHECK


20-06

28458.4 36458.4

20-07

28458.4 36458.4

20-08

28458.4 36458.4

20-09

28458.4 36458.4

20-1028458.4 36458.4

20-12

28458.4 36458.4

Inspect (General Visual) EWISComponents of POWER FEEDERS ANDWIRING BUNDLES for signs ofdamage, proper installation,chafing and general condition.NOTE: EWISRequires access panel removal.

Inspect (General Visual) EWISComponents of WIRING BUNDLES forsigns of damage, properinstallation, chafing and generalcondition.NOTE: EWISRequires access panel removal

Inspect (General Visual) EWISComponents of WIRING BUNDLES forsigns of damage, properinstallation, chafing and generalcondition.NOTE: EWISRequires fairing removal.

Clean fuselage area under cockpit floor.NOTE - EWISRequires access panel removal.

Clean fuselage area under passenger FLOOR; WIRING, SIDEWALL OUTLETS ADJACENT AREA AND AREA UNDERTHE TOILET/GALLEY, if installed. NOTE - EWISRequires floor panel removal.

Inspect (Detailed Inspection) EWIS Components of POWER FEEDERS for signs of damage, proper installation, chafing and general condition.NOTE - EWISRequires access panel removal.

66 of 115


EMBRAER 2C CHECK


20-13

28458.4 36458.4

20-14

28458.4 36458.4

20-15

28458.4 36458.4

20-16

28458.4 36458.4

20-17

28458.4 36458.4

20-18

28458.4 36458.4

Inspect (Detailed Inspection) EWIS components of POWER FEEDERS AND WIRING BUNDLES for signs of damage, proper installation, chafing and general condition.NOTE - EWISRequires floor panel removal

Clean fuselage area under passenger FLOOR; WIRING, SIDEWALL OUTLETS ADJACENT AREA, if installed. NOTE - EWISRequires floor panel removal.

Inspect (General Visual) EWISComponents of POWER FEEDERS ANDWIRING BUNDLES for signs ofdamage, proper installation,chafing and general condition.NOTE: EWISRequires floor panel removal.


Clean SIDEWALL OUTLETS, if installed. NOTE - EWISRequires lining and thermoacoustic insulation removal.


67 of 115


EMBRAER 2C CHECK


20-19

28458.4 36458.4

20-22

28458.4 36458.4

25-12

28458.4 36458.4

26-24

31911.2 31911.2 39911.2

27-58

28458.4 36458.4

27-63

28458.4 36458.4

28-21

28458.4 36458.4

Inspect (General Visual) EWISComponents of WIRING BUNDLES forsigns of damage, properinstallation, chafing and generalcondition.NOTE: EWISRequires access panel removal.

Visually check cargo compartmentfloor and REAR PARTITION SEALINGfor condition and security.(MSI 25-41-02)

Clean SIDEWALL OUTLETS, ifinstalled. NOTE - EWISRequires lining and thermoacoustic insulation removal.

Visually check the fire extinguishingsystem discharge pipingfor cracks, bending and loosefittings.NOTE: (1) Applicable only to baggagecompartment class“C”.

Clean filter element of flap actuators line filters.NOTE - For airplanes post-mod.SB 120-027-0038.

Lubricate flap actuatorend-fitting bearing.NOTE: Applicable to aircraft S/N292/999.

Inspect (General Visual) the Wing Stub Harnesses.NOTE - This task complieswith Fuel Tank Ignition Source Prevention (SFAR 88) and EWIS.

68 of 115


EMBRAER 2C CHECK


28-22

28458.4 36458.4

28-23

28458.4 36458.4

28-24

28458.4 36458.4

29-11 28458.4 36458.4

30-01

28458.4 36458.4

30-03

32796.1 40796.1

30-0432796.1 40796.1

32-23

NA NA

32-4728458.4 36458.4

Inspect (General Visual) the Trailing Edge Harnesses.NOTE - This task complieswith Fuel Tank Ignition Source Prevention (SFAR 88) and EWIS.

Check suction line FLUID THERMAL SWITCH

Check ANGLE-OF-ATTACK SENSOR VANE/CASE and SIDESLIP SENSOR VANE/CASE HEATING ELEMENTresistance values. (MSI 30-32-02).

Check total-air-temperature (TAT) sensor heating INDICATION RELAY operation.NOTE - If TAT sensor is installed.(MSI 30-33-02/03).

Inspect (General Visual) the Leading Edge Harness.NOTE - This task complies withFuel Tank Ignition Source Prevention (SFAR 88) and EWIS.

Inspect (General Visual) the Bleed Line.NOTE - This task complieswith Fuel Tank Ignition Source Prevention (SFAR 88).

Verify pressurization STATIC PORTHEATING ELEMENT operation.

Lubricate FREE-FALL ACTUATIONDEVICE. NOTE - For airplanes Pre-Mod.S.B. 120-032-0019 only.(MSI 32-34-02).

Check ANTI-SKID system, includingElectronic Control Unit.

69 of 115


EMBRAER 2C CHECK


35-1532796.1 40796.1

35-1632796.1 40796.1

38-0231911.2 39911.2

5310-121-01I122

31911.2 39911.2

5310-211-02I

28458.4 36458.4

5310-221-05I

32796.1 40796.1

Fuselage forward section II (cockpit) internal upper elements.- Skin panels, including splices, frames, and stringers.

Visually check FULL-FACE MASKSand smoke goggles.

Visually check toilet motor electrical connector for condition

Fuselage forward section II(cockpit) internal elements below floor.– Skin panel, including splices,frames, stringers, and controlsrigging door cutout structure.– Forward pressure bulkhead, includingfloor beam fittings.– Floor beams.– Controls rigging doorstructure.Requires floor and seat removal.

Fuselage forward section I internalelements inside electroniccompartment:– Stringers and frames.– Longitudinal and circumferentialskin splices.

Visually check PORTABLE OXYGENCYLINDER MASK(MSI 35-10-01/35-30-01).

70 of 115


EMBRAER 2C CHECK


5320-141-03I142

28458.4 36458.4

5320-147-01E148 28458.4 36458.4

5320-147-02E148

28458.4 36458.4

5320-152-02I28458.4 36458.4

5320-241-01I242243244245246

28458.4 36458.4

5320-243-01E244 31911.2 39911.2

Fuselage center section I (passengercabin) internal elementsbelow floor:- Skin panel, splice, andstringers.- Bulkhead 24 and stringerattachment, between fuselageSTATION 6653.1 and bulkhead 24.- Wing auxiliary spar web.Requires seat and floor panelremoval.

Fuselage center section I (passengercabin) lower skin panel.Requires fairing removal.

Fuselage center section I (passengercabin) skin and fastenersat bulkhead 28.Requires fairing removal

Toilet drain valve support.NOTE - Applicable to aft lavatoryinstallation only.

Fuselage center section I (passengercabin sidewalls) internalelements above floor:- Skin panel, stringers, frames,and splices.- Passenger window frame.- Escape hatch window frame.- Bulkhead 24 and stringerattachment. B lkh d 25 d t i

Fuselage center section I (passengercabin) skin panel.Requires fairing removal.

71 of 115


EMBRAER 2C CHECK


5320-243-02E244

28458.4 36458.4

5330-311-01E312 28458.4 36458.4

5330-311-02E312 28458.4 36458.4

5410-432-03I442

28458.4 36458.4

5410-433-01I443

28458.4 36458.4

5520-335-04E336 28458.4 36458.4

5530-324-02I

31911.2 39911.2

Visual check of tab hinge fittingat elevator.

Vertical stabilizer internal auxiliary spar caps at fin-to– fuselage fitting.Requires access door and fairingremoval

Fuselage aft section II (tailcone) skin panels.

Fuselage aft section II (tailcone) skin panel, between pressurebulkhead 47 and frame 52.

Nacelle internal elements:– Skin and stringers betweenframes 5 to 8.– Frame 8.– Frame 1-(Post-Mod SB 120-54-0036)Requires that access doors beopened.

Nacelle internal elements:– Skin and stringers betweenframes 10 to 14.Requires opening of the mainlanding gear wheelwell doors andremoval of panels.

Fuselage center section I (passengercabin) skin panel andfittings and fasteners atbulkheads 24, 25, and 28.Requires fairing removal.

72 of 115


EMBRAER 2C CHECK


5530-325-01I

31911.2 39911.2

5530-325-02I31911.2 39911.2

5530-325-03I

31911.2 39911.2

5540-326-01I

28458.4 36458.4

Visual check of vertical stabilizerinternal elements betweenfront and rear spars:– Left and right skin panels andstringers.– Ribs.– Front and rear spars and tiprib fittings.– Fitting at front spar.– Front and rear auxiliary sparsand tip rib fittings.– Tip rib doubler.– Fin-to-horizontal stabilizerrear fitting.– Elevator bellcrank supportfitting at rear spar.– Rudder hinge fittings.– Trailing edge ribs.– Rudder actuator supportfittings.– PCU support fitting.Requires access panel removal

Visual check of fin-to-horizontalstabilizer center fitting.

Visual check of vertical stabilizerrear spar elements.– Rear spar web.– Elevator bellcrank supportfittings.– Rudder hinge fittings.

Visual check of rudder I skinpanels, actuator fittings,leading and trailing edge hingefittings.Requires access panel removal.

73 of 115


EMBRAER 2C CHECK


5540-327-01I

28458.4 36458.4

5710-143-01I

31911.2 39911.2

5710-143-03I

31911.2 39911.2

5710-144-05I31911.2 39911.2

5720-511-01I611 28458.4 36458.4

5720-512-01I612 28458.4 36458.4

Wing center section internalelements:– Upper and lower skin panels andstringers.– Access openings.– Auxiliary spar and fasteners.– Auxiliary spar web-to-fuselagebulkhead 24 attachment.– Front spar.– Front spar web-to-center linerib attachment.– CL rib.– Fuselage stringer-to-ribattachments.– Shear clipsRequires access panel removal.

Wing center section skin panel,CL rib splice, and skin openings.Requires floor panel removal.

Wing auxiliary spar and nacellefitting.Requires leading edge removal.

Wing auxiliary spar and nacellefitting.Requires leading edge removal.

Visual check of rudder II skinpanels, actuator fitting, andleading edge hinge fittings.Requires access panel removal.

Wing center section ext. elementsunder fairing 197, 191, and 192:– Upper skin.– Auxiliary spar web.– Wing-to-fuselage fittingauxiliary spar.Requires fairing removal.

74 of 115


EMBRAER 2C CHECK


5720-522-01I622

31911.2 39911.2

5720-541-01I641

31911.2 39911.2

5720-542-01I642

28458.4 36458.4

5720-551-01I651

28458.4 36458.4

Wing box beam internal elements:– Upper and lower skin,stringers, and access openings.– Stringers 8 and 10.– Front and rear spars.– Ribs.– Drain valve installation.– Shear clipsRequires access panel removal

Wing box beam internal elements:- Auxiliary and front spar.- Upper skin and stringers.- Lower skin and access openings(left wing only).- Lower skin and pressurerefueling installation(right wing only).- Ribs.- Outboard side nacelle fittings.- Shear clipsRequires access panel removal.

Wing box beam internal elements:- Auxiliary and front spars.- Upper and lower skins,stringers, and access openings.- Ribs.- Shear clipsRequires access panel removal .

Wing box beam internal elements:- Upper and lower skin,stringers, and access openings.- Front and rear spars.- Ribs.- Shear clipsRequires access panel removal.

75 of 115


EMBRAER 2C CHECK


5720-552-01I652

28458.4 36458.4

5720-561-01I661

28458.4 36458.4

5720-571-01I671

28458.4 36458.4

5720-581-01I681

28458.4 36458.4

5750-572-02E672 31911.2 39911.2

5750-572-04E672 31911.2 39911.2

Inboard flap skin panels, track,vane , and vane support ribs.

Externally inspect compositeinboard flap actuator lugs.

Wing box beam internal elements:- Upper and lower skin,stringers, and access openings.- Front and rear spars.- Ribs.- Shear clips- Requires access panel removal.

Wing box beam internal elements:– Lower skin, stringers, andaccess openings.– Front and auxiliary spars.– Ribs.– Upper skin, stringers, and fuelfiller cap– Shear clipsRequires access panel removal.

Wing rear spar inboard flapsupport fitting and actuatorsupport installation.Requires wing trailing edge upperand lower fairing removal andflap in down position.

Wing rear spar outboard flapsupport fitting, as well asactuator support and aileronhinge installations.Requires wing trailing edge upperand lower fairing removal.

76 of 115


EMBRAER 2C CHECK


5750-572-05E672 31911.2 39911.2

5750-582-01I682

31911.2 39911.2

5750-582-02E682 31911.2 39911.2

5750-582-04E682 31911.2 39911.2

5750-582-05E682 31911.2 39911.2

111-01Z

28458.4 36458.4

113-01Z114-01Z

28458.4 36458.4

Outboard flap tracks supportribs, inboard and outboardvane, and vane support ribs.

Externally inspect the compositeoutboard flap actuator lugs.

Special detailed inspection ofcomposite outboard flap skinusing “TAP TEST”.

ZONE 111 - RADOME.– Perform internal general visual inspection of the zone.The following task is VISUAL EXAMINATION and is accomplished during foregoing zonal task:Bulkhead 1.

Special detailed inspection ofcomposite inboard flap skin using“TAP TEST”.

Outboard flap internal elements:– Skin and stringers.– Ribs.– Actuator support rib.

ZONES 113/114 - NOSE LANDING GEARWHEELWELL.– Perform internal general visual inspectionof the zones.NOTE: EWISRequires door opening

77 of 115


EMBRAER 2C CHECK


115-01Z

28458.4 36458.4

116-01Z

28458.4 36458.4

121-01Z122-01Z

28458.4 36458.4

131-01Z132-01Z

28458.4 36458.4

141-01Z142-01Z

28458.4 36458.4

ZONES 131/132 - AREA UNDER PASSENGERCABIN.– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal.

ZONES 141/142 - AREA FORWARD OF WING CENTERSECTION (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal

ZONE 115 - LOWER NOSE AREA OUTBOARD OF NOSELANDING GEAR WHEELWELL (LH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires door and access panel opening.

ZONE 116 - LOWER NOSE AREA OUTBOARD OF NOSELANDING GEAR WHEELWELL (RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires door and access panel opening.

ZONES 121/122 - AREA UNDER COCKPIT FLOOR(LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal.

78 of 115


EMBRAER 2C CHECK


143-01Z

31911.2 39911.2

144-01Z

31911.2 39911.2

145-01Z146-01Z

28458.4 36458.4

147-01Z148-01Z

28458.4 36458.4

151-01Z152-01Z

28458.4 36458.4

ZONES 145/146 - AREA ABOVE WING CENTERSECTION (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal.

ZONES 147/148 - AREA AFT OF WING CENTERSECTION.– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor and access panel removal.

ZONES 151/152 - AREA UNDER PASSENGERCABIN FLOOR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires access panel removal.

ZONE 143 - WING CENTER FROM AUXILIARY SPARTO FRONT SPAR.– Perform internal general visual inspectionof the zone.NOTE: EWISRequires access panel removal.

ZONE 144 - WING CENTER SECTION FROM FRONTSPAR TO REAR SPAR.- Perform internal general visual inspectionof the zone.NOTE: EWISRequires access panel removal.

79 of 115


EMBRAER 2C CHECK


161-01Z162-01Z

28458.4 36458.4

163-01Z164-01Z

28458.4 36458.4

191-01Z192-01Z

28458.4 36458.4

1911-01Z1912-01Z

28458.4 36458.4

1913-01Z1914-01Z

31911.2 39911.2

ZONES 161/162 - AREA UNDER CARGO COMPARTMENTFLOOR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal.

ZONES 163/164 - AREA UNDER CARGO COMPARTMENTFLOOR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires floor panel removal.

ZONES 191/192 - FORWARD FAIRING - WING -TO-FUSELAGE (LH/RH).– Perform internal general visual inspectionof the zones.Requires fairing removal.

ZONES 1911/1912 - CENTER FAIRING UNDER THEFUSELAGE LOWER SURFACE.- Perform internal general visual inspectionof the zones.NOTE:EWISRequires fairing removal

ZONES 1913 / 1914 - WING-TO-FUSELAGE REARFAIRING- Perform internal general visual inspectionof the zones.Requires fairing removal.

80 of 115


EMBRAER 2C CHECK


193-01Z194-01Z

31911.2 39911.2

195-01Z196-01Z

31911.2 39911.2

197-01Z

31911.2 39911.2

198-01Z

28458.4 36458.4

199-01Z

28458.4 36458.4

221-01Z222-01Z

28458.4 36458.4

ZONE 199 - FAIRING UNDER APU TUBING.– Perform internal general visual inspectionof the zone.Requires fairing removal.

ZONES 221/222 - COCKPIT (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires access panel opening.

ZONES 193/194 - CENTER FAIRING - WING-TO-– FUSELAGE (LH/RH).– Perform internal general visual inspectionof the zones.Requires fairing and access panelremoval

ZONES 195/196 - AFT FAIRING - WING - TOFUSELAGE(LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel removal

ZONE 197 - FUSELAGE CENTER SECTION UNDERWING CENTER SECTION.No additional zonal general visual inspectionrequired.

ZONE 198 - CENTER FAIRING UNDER FUSELAGE.– Perform internal general visual inspectionof the zone.Requires fairing removal.

81 of 115


EMBRAER 2C CHECK


231-01Z232-01Z

28458.4 36458.4

241-01Z242-01Z

28458.4 36458.4

243-01Z244-01Z

28458.4 36458.4

245-01Z246-01Z

28458.4 36458.4

251-01Z252-01Z

28458.4 36458.4

ZONES 231/232 - PASSENGER CABIN (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires lining and thermo acoustic insulationremoval.

ZONES 241/242 - UPPER LATERAL AREA OF PASSENGERCABIN (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires lining and thermo acoustic insulation

ZONES 243/244 - LOWER LATERAL AREA OF PASSENBERCABIN.– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval.

ZONES 245/246 - PASSENGER CABIN CEILING(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval.

ZONES 251/252 - PASSENGER CABIN(LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires side lining and thermo acousticinsulation removal.

82 of 115


EMBRAER 2C CHECK


261-01Z262-01Z

28458.4 36458.4

263-01Z264-01Z

28458.4 36458.4

265-01Z266-01Z

28458.4 36458.4

267-01Z268-01Z

28458.4 36458.4

311-01Z312-01Z

28458.4 36458.4

ZONES 263/264 - CARGO COMPARTMENT(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval.

ZONES 265/266 - CARGO COMPARTMENT CEILING(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval.

ZONES 267/268 -CARGO COMPARTMENT CEILING(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval

ZONES 311/312 - STRUCTURAL AREA AFT OF REARPRESSURE BULKHEAD (LH/RH).– Perform internal general visual inspectionof the zones.NOTE: EWISRequires access panel removal

ZONES 261/262 - CARGO COMPARTMENT(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermo acoustic insulationremoval.

83 of 115


EMBRAER 2C CHECK


321-01Z

28458.4 36458.4

322-02Z

28458.4 36458.4

323-02Z28458.4 36458.4

324-01Z

28458.4 36458.4

325-01Z

31911.2 39911.2

326-02Z28458.4 36458.4

327-01Z

28458.4 36458.4

ZONE 321 - VERTICAL STABILIZER - FRONT,UPPER, AND REAR FAIRINGS.– Perform internal general visual inspectionof the zone.Requires fairing removal

ZONE 322 - DORSAL FIN– Perform internal general visual inspectionof the zone.Requires fairing removal

– Perform internal general visual inspectionof the zone.Requires leading edge removal.

ZONE 324 - FIN AREA BETWEEN AUXILIARY SPARAND FRONT SPAR.– Perform internal general visual inspectionof the zone.Requires access panels removal.

ZONE 325 - FIN AREA BETWEEN FRONT SPAR ANDREAR SPAR.– Perform internal general visual inspectionof the zone.NOTE: EWIS

Perform internal general visual inspection of zone Requires access panel removal.B370

ZONE 327 - RUDDER II- Perform internal general visual inspectionof the zone.Requires access panel removal.

84 of 115


EMBRAER 2C CHECK


331-01Z332-01Z

28458.4 36458.4

333-01Z334-01Z

28458.4 36458.4

335-01Z336-01Z

28458.4 36458.4

337-01Z

28458.4 36458.4

511-01Z611-01Z

28458.4 36458.4

512-01Z612-01Z

28458.4 36458.4

ZONES 512/612 - WING LEADING EDGE OUTBOARDOF NACELLE STRUCTURE (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires leading edge removal.

ZONES 333/334 - HORIZONTAL STABILIZER AREABETWEEN FRONT SPAR AND REAR SPAR (LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel removal

ZONES 335/336 - ELEVATOR/TAB (LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel removal.

ZONE 337- HORIZONTAL STABILIZER FIN ATTACHMENTCENTER AREA.– Perform internal general visual inspectionof the zones.Requires access panel removal.

ZONES 511/611 - WING LEADING EDGE INBOARDOF NACELLE STRUCTURE (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires leading edge removal.

ZONES 331/332 - HORIZONTAL STABILIZERLEADING EDGE (LH/RH).– Perform internal general visual inspectionof the zones.

85 of 115


EMBRAER 2C CHECK


522-01Z622-01Z

28458.4 36458.4

531-01Z631-01Z

28458.4 36458.4

542-01Z642-01Z

28458.4 36458.4

551-01Z651-01Z

28458.4 36458.4

552-01Z652-01Z

28458.4 36458.4

ZONES 522/622 - FUEL TANK INBOARD CELL FROMSPAR TO REAR SPAR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires access panel removal.

ZONES 531/631 - WING AREA BETWEEN FRONTSPAR AND REAR SPAR (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires access panel removal

ZONES 542/642 - WING AREA OUTBOARD OFNACELLE STRUCTURE FROM AUXILIARY SPAR TOFRONT SPAR AND FROM RIB 16 TO RIB 22(LH/RH).– Perform internal general visual inspection

ZONES 551/651 - WING AREA OUTBOARD OFNACELLE STRUCTURE FROM FRONT SPAR TO REARSPAR AND FROM RIB 14 TO RIB 17 (LH/RH).– Perform internal general visual inspectionof the zones.

ZONES 552/652 - WING AREA OUTBOARD OFNACELLE STRUCTURE FROM FRONT SPAR TO REARSPAR AND FROM RIB 17 TO RIB 22 (LH/RH).– Perform internal general visual inspectionof the zones.

86 of 115


EMBRAER 2C CHECK


561-01Z661-01Z

28458.4 36458.4

562-01Z662-01Z

28458.4 36458.4

572-01Z672-01Z

28458.4 36458.4

582-01Z682-01Z

31911.2 39911.2

811-02Z31911.2 39911.2

813-02Z31911.2 39911.2

822-02Z32796.1 40796.1

Perform internal general visual inspectionof the zone.Requires door and lining removal

ZONES 572/672 - INBOARD FLAPS (LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel removal.

ZONES 582/682 - OUTBOARD FLAPS (LH/RH).– Perform internal general visual inspectionof the zones.Requires access panel removal.

Perform internal general visual inspectionof the zone.Requires lining removal.

Perform internal general visual inspectionof the zone.Requires lining and access panel removal

ZONES 561/661 - WING AREA OUTBOARD OFNACELLE STRUCTURE BETWEEN AUXILIARY SPARAND REAR SPAR AND FROM RIB 22 TO RIB 27(LH/RH).

ZONES 562/662 - WING TIP (LH/RH).– Perform internal general visual inspectionof the zones.NOTE:EWISRequires tip removal

N582SW Serial #:TAT: 32873 Date: 8/25/2016TAC: 45163

21-1026845.4 38845.40

N582SW Serial #:TAT: 32873.0 Date: TAC: 45163

20-1124029.3 40029.3 3C

20-2024029.3 40029.3 3C

21-08

27477.1 43477.1

21-0927477.1 43477.1

28-19

18124.8 34124.8

28-20

18124.8 34124.8

5320-251-01I252253254 28458.4 44458.4 2C

5510-333-02I334 32492.0 48492.0 A1, A4, A

Bridge

120-350

EMBRAER 4C CHECK

Check NEGATIVE PRESSURE RELIEFVALVE in the electropneumatic outflow valve (MSI 21-32-02).

Inspect (Detailed Inspection) Tank Unit.NOTE - This task complies with Fuel Tank Ignition Source Prevention (SFAR 88).

Inspect (Detailed Inspection) Fuel Pump Electrical harness.NOTE - This task complies with Fuel Tank Ignition Source Prevention (SFAR 88) and EWIS.

Clean fuselage cockpit area. NOTE - EWIS Requires access panel removal.

Fuselage center section II (passengercabin) internal elementsabove floor:– Window frames.Requires lining and thermoacousticinsulation removal.

Horizontal stabilizer front sparweb inboard of rib 1.Requires leading edge removal.

Clean Underwing area of MLG wheelwell. NOTE - EWIS Requires MLG doors opening.

Check CABIN ALTITUDE LIMITINGVALVE in the electropneumatic outflow valve.

EMBRAER 3C CHECK

120.35Aircraft Registration No.:

Aircraft Registration No.:

Check NEGATIVE PRESSURE RELIEFVALVE in the pneumatic outflow valve.

5510-333-04I334 28458.4 44458.4 2C

5710-143-04I31911.2 47911.2 1C

253-01Z254-01Z

28458.4 44458.4 2C

ZONES 253/254 - PASSENGER CABIN CEILING(LH/RH).– Perform internal general visual inspectionof the zones.Requires lining and thermoacoustic insulationremoval.

Wing center section upper skinpanel and CL splice.Requires floor panel removal.

Horizontal stabilizer rear spar.Requires shroud removal.

89of 115

Aircraft Registration N582SW 120-350TAT: 32873 8/29/2016TAC: 45163

Reinsp Last Due NextDone

5210-811-01E 850 FC 43759 44609 A1, A2,

5210-811-01I 24000 FC 43759 67759 1C

5220-812-01E 8000 FC 44185 52185 A1, A3, 821822

5220-812-02E 1230 FC 44185 45415 A1, A3, 821822

5220-812-01I 32000 FC 44185 76185 A1, A3, 821822

5320-813-01E 4000 FC 44185 48185 52-900-1004 Cross ref has this under 5230-813-01E A3, A6, A bridge, 1C

5320-813-02E 550 FC 43759 44309

5320-813-01I 8000 FC 43759 51759

5320-813-02I 8000 FC 38860 46860

2C5310-113-02I 24000 FC 38860 62860 2C

114115116211212

5310-221-01E 550 FC 43759 44309 A1, A2, 222

5310-221-02E 2750 FC 43759 46509 A1, A2, 222

5310-221-01I 8000 FC 43759 51759 1C222

5310-221-04I 24000 FC 43759 67759 1C222

5310-221-06I 8000 FC 43759 51759 1C222

5310-221-07I 5000 FC 43759 48759 1C222

5310-221-08I 8000 FC 43759 51759 1C222

5310-231-03E 4000 FC 43759 47759 A1, A

5320-241-02E 4000 FC 44185 48185 A1, A3, 242

5320-252-04E 2750 FC 44185 46935 A1, A3,

5320-252-02I 32000 FC 38860 70860 2C44185

5330-163-04I 4000 FC 44185 48185 A3, A 164263264267268

5330-311-04I 4000 FC 44185 48185 A3, A 312

5410-432-01I 2000 FC 44591 46591 A1, A4, A 442

5410-432-02I 4000 FC 44591 48591 A4, A 442

5510-333-01E 2750 FC 44591 47341 A1, A4, A 334

Nacelle internal elements - Rodd &fittings. Requires access doors open.

Horizontal stabilizer upper skin panel

Cargo Door internal elements, including stops & fittings

Special detailed magnetic particle NDT check on cargo door upper/lower stops

Fuselage aft section I cargo compartment rear pressure bulk head done & forged ring. Requires lining, floor panels &thermoacoustic insulation removed

Fuselage aft section II tail cone rear pressure bulkhead dome & forged ring. Requires access door be opened.

Nacelle internal elements - Engine mount fittings. Requires access doors open.

Fuselage forward Section II (cockpit) internal detailed inspection in windshield cutout structure

Windshield cutout structure, center & lateral post attachments & lugs (Pre Mod 120-53-0079)

Windshield cutout structure, center & lateral post attachments & lugs (Pre Mod 120-53-0079)

Fuselage fwd. section III passenger/crew entry door cutout visible structure including external skin & fasteners.

Fuselage fwd. section I passenger cabin overwing escape hatch structure cutout, including external skin & fasteners.

Fuselage fwd. section II passenger cabin escape hatch cutout visible structure including external skin & fasteners.

Fuselage fwd. section II passenger cabin escape hatch frame. Requires lining & insulation removal.

STRUCTURES PROGRAM

Task Number

Passenger/Crew entry door visible structure, stops & fittings

Serial #:

Description

Passenger/Crew entry door internal elements, including stops & fittings. Requires door lining removed

Escape Hatch visible structure.

Escape Hatch window frame

Fuselage forward Section II external skin panels below cockpit windshield & lateral windows

Fuselage forward Section II external skin & fasteners around & above cockpit windows & windshield panel

Fuselage forward Section II (cockpit) internal elements above floor.

Fuselage forward Section II fwd. pressure bulkhead. 400 FC A/C pre mod SB 120-053-0008

Fuselage forward Section I forward pressure bulkhead. A/C pre-mod SB 120-053-008 inspect 400 FC

Escape Hatch internal elements including window frame

Cargo Door visible structure

Cargo Door visible stops & fittings

90of 115

Aircraft Registration N582SW 120-350TAT: 32873 8/29/2016TAC: 45163


STRUCTURES PROGRAM

Task Number

Serial #:

Description

5510-333-03E 2750 FC 44591 47341 A1, A4, A 334

5530-325-02E 4000 FC 44185 48185 A3, A 334

5530-325-04I 32000 FC 31981 63981 6S

5530-325-05I 8000 FC 43759 51759 1C

5530-325-06I 8000 FC 43759 51759 1C

5710-143-02I 32000 FC 31981 63981 6S144

5710-144-01E 1100 FC 43759 44859 A1, A2, 144

5710-144-01I 8000 FC 43759 51759 1C

5710-144-03I 8000 FC 43759 51759 1C

5710-144-04I 800 FC 43759 44559 A1, A2,

5720-521-01I 8000 FC 31911.2 39911 1C621

5720-521-01E 20000 FC 31911.2 58743 1C621

5720-522-02I 20000 FC 31911.2 51911 1C622

5720-531-01E 2015 FC 44591 46606 A1, A4, A 631

5720-531-01I 4000 FC 43001 47001 A6, A 631

5720-531-02I 20000 FC 39804 59804 4S631

5720-531-03I 20000 FC 39804 59804 4S631

5720-531-04I 20000 FC 39804 59804 4S631

5720-541-02I 20000 FC 39804 59804 4S641

5720-551-02I 20000 FC 39804 59804 4S651

5750-572-03E 16000 FC NA NA672 2000 FC 43759 45759 1C

5750-572-02I 32000 FC NA NA672

5750-572-03I 8000 FC 43759 51759 1C672

5750-582-02I 32000 FC NA NA682

5750-582-03I 8000 FC 43759 51759 1C682

Wing front spar lower cap, hidden by main landing gear support rib & wing ribs 11 & 13 using ultrasonic/eddy current inspection methods.

Special detailed inspection for skin hidden

details using ultrasonic inspection methods.

Special detailed inspection for skin hidden

details using ultrasonic inspection methods.

Wing box beam external elements through LG bay.

Wing box beam internal elements (dry bay)

Special detailed inspection for skin hidden details, using ultrasonic inspection method.

Wing front spar lower cap, hidden by main landing gear support rib & wing ribs 11 & 13 using ultrasonic/eddy current inspection methods.

Special detailed inspection for skin hidden details, using ultrasonic inspection method.

Wing center section lower skin panel & access openings from CL Rib 3. Requires lower CL 197 fairing removed.

Wing center section skin panel under fairings 197, 193 & 194. Requires fairing removed & access door opened.

Wing center section internal elements. Upper & lower skin panels & stringers, Center line rib, Center line rib, Center line rib-to-front spar web attachment, upper skin holes, Fuselage bulkhead 28 to rear spar attachment, Fuselage stringers-to-ribs attachment at rear spar, Fuselage stringer 18 attachment, Ribs 2 & 3. Requires access panel removed.

Special detailed inspection for skin hidden details, using ultrasonic inspection method

Front & rear Fin-to-fuselage fitting. Requires access door opened

Visually check fin-to-stabilizer fittings & bolts (with bolts installed)

Detailed inspection with magnifying glass at wing-to-fuselage fitting

Wing center section internal elements: Access opening frame, Front & rear spars. Requires fairing removed.

Wing box beam internal elements

Horizontal stabilizer lower skin panel

Front & rear fin-to-fuselage fittings

Fin-to-horizontal stabilizer attachment bolts, using nondestructive inspection method. Requires access door open & fairing removed

Outboard flap internal elements: Spar Caps

External inspect the composite inboard flap actuator support rib region. Initial 16000, Repeat 2000

Special detailed for upper flap spar cap between ribs 5A & 7A using Eddy Current

Inboard flap internal elements

Special detailed for upper flapspar cap between ribs 16A/17A,using “Eddy Current”.

91of 115

Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163


5210-811-C01I 8 YR 9/22/2012 9/20/2020 2C

5310-113-C01I 4 YR 8/26/2016 8/25/2020 2C114

5310-113-02I 8 YR 9/22/2012 9/20/2020 2C114115116211212

5310-121-C01E 4 YR 8/26/2016 8/25/2020 1C122

5310-121-C01I 4 YR 8/26/2016 8/25/2020 2C122

5310-131-C01E 2 YR 8/26/2016 8/26/2018 1C132

5310-131-C01I 2 YR NA NA 1C132

5310-211-C01E 2 YR 8/26/2016 8/26/2018 1C212

5310-231-C01E 2 YR 8/26/2016 8/26/2018 1C232

5310-231-C01E 4 YR 7/16/2014 7/15/2018 1C232

5320-141-C01E 4 YR 7/16/2014 7/15/2018 1C142

5320-147-C03I 4 YR 7/16/2014 7/15/2018 1C142

5320-151-C01E 2 YR 8/26/2016 8/26/2018 1C152

5320-151-C01I 4 YR 7/16/2014 7/15/2018 1C152

5320-251-C01I 4 YR 8/26/2016 8/25/2020 2C

Fuselage forward section I internal elements below electronic compartment

Fuselage forward section I forward pressure bulkhead. Requires access through NLG wheel well & lateral lid removed.

Corrosion Prevention & Control Program

Task Number

Passenger/Crew entry door internal elements including stops & fittings

Serial #:

Description

Fuselage center section II (passenger cabin) skin panel

Fuselage external elements, in the antennas region. Lower skin panel at stringers & bulkhead

Fuselage forward section II internal elements below floor

Fuselage center section II (passenger cabin)

Fuselage center section I (passenger cabin) internal elements below floor

Fuselage center section II (passenger cabin) internal elements below floor. 2YR aft lavatory installed

Fuselage forward section III (passenger cabin) external skin panels

Fuselage forward section III (passenger cabin) internal elements NOTE: 4 YR for aft lavatory installed

Fuselage forward section I external skin panels & fasteners at bulkhead 1, frames 4 & 6

Front fuselage III ( passenger cabin) skin panel

Front fuselage III ( passenger cabin) internal elements

Fuselage center section I (passenger cabin) lower external skin panel between fuselage station 6653.1 & leading edge of fairings 191& 192

92of 115




Task Number

Serial #:

Description

252253254

5330-161-C01I 4 YR 8/26/2016 8/25/2020 2C162

5330-163-C01I 8 YR 9/22/2012 9/20/2020 2C164

5330-311-C01I 8 YR 9/22/2012 9/20/2020 2C312

5510-337-C01I 8 YR 9/22/2012 9/20/2020 2C338

5520-335-C01E 4 YR 8/26/2016 8/25/2020 2C336

5520-335-C02E 4 YR 8/26/2016 8/25/2020 2C336

5520-335-C01I 8 YR 9/22/2012 9/20/2020 2C336

5520-335-C02I 8 YR 9/22/2012 9/20/2020 2C336

5530-324-C01E 4 YR 8/26/2016 8/25/2020 2C

5530-324-C01I 4 YR 8/26/2016 8/25/2020 2C

5530-325-C01E 4 YR 8/26/2016 8/25/2020 2C

5540-326-C01E 4 YR 8/26/2016 8/25/2020 2C

5540-327-C01E 4 YR 8/26/2016 8/25/2020 2C

5720-552-C02E 2 YR 8/26/2016 8/26/2018 1C652

5750-572-C01I 4 YR 9/22/2012 9/21/2016672

5760-583-C01I 4 YR 9/22/2012 9/21/2016683

Visual check of elevator internal elements

Detailed inspection of torque tube (inside & outside) & it's fittings. NOTE: 2 YR for A/C pre mod SB 120-55-0015

Fuselage aft section II (tail cone) internal elements

Visual check of horizontal stabilizer-to-fin center section internal elements

internal elements above floor.

Fuselage aft section I (cargo compartment) internal elements below floor

Visual check of elevator & tab upper skin panels

Visual check of elevator & tab lower skin panels

Wing box beam upper skin

Vertical stabilizer internal elements between auxiliary spar & front spar,

Vertical stabilizer skin panels between front & rear spars

Vertical stabilizer skin panels between auxiliary spar & front spar

Aileron internal elements.

Visual check of rudder I skin panels & leading & trailing edge hinge fittings

Visual check of rudder II skin panels & leading & trailing edge hinge fittings

Inboard flap internal elements

Fuselage aft section I (cargo compartment) internal elements below floor

93of 115




Task Number

Serial #:

Description

94 of 115

Aircraft Registration: N582SW 120-35032873 8/29/201645163

86-21-112/17/198786-10-01R1

88-16-51R111/7/1988

88-19-0710/7/198887-05-01R2

89-03-082/15/198988-11-04

89-14-097/18/198990-09-02R1

89-23-0311/27/198989-08-01

89-23-0912/1/1989

TAT:TAC:

accomplish the following: A. Insert the following into the FAA-approved Airplane Flight Manual (AFM) and alert all flight crews. This may be accomplished by inserting a copy of this airworthiness directive (AD) into the appropriate section of the AFM.

To reduce the potential for flap asymmetry that could lead to loss of control of the airplane in a critical phase of flight, accomplish the following: replace flap actuator solenoid valves IAW SB 120-027-0050; replace the inlet filter fitting of flap actuators IAW SB 120-027-0042; and install in-line filters to the flap control hydraulic plumbing IAW SB 120-027-0038.

To prevent the loss of essential navigation systems, accomplish the following: Install self-locking nuts, P/N LN9161-05, to secure the No. 1 and No. 2 auxiliary generator control voltage sensor wires to the connecting bars at relays K0035 and K0036 and Install placard 120-47147-001 on the left-hand relay box cover.

Complied with per current AFM revision

Complied with at factory build

NA by serial number

Non-Recurring Airframe Airworthiness Directives

To prevent oil loss in-flight engine shut down, accomplish the following: Oil coolers, PN 160282-1 or 160282-2

NA by serial number

Aircraft Serial #:

Accomplished

NA by S/N

Effective Date:


To prevent an uncontrolled APU overspeed, accomplish the following: Inspect the APU electrical control unit (ECU), Part No. 2118052-1/2118596-2, for water contamination per instructions in AD

To prevent erratic glide slope information during IFR approaches, accomplish the following: Replace the Chelton glide slope antenna, P/N 17-21F6P3, with a Collins glide slope antenna type 37P5, P/N 522-0700-023. Install a pedestal-type support P/N 120-47294-001, in accordance with EMBRAER Service Bulletin 120-034-0072

NA by serial number

To prevent a gear-up landing due to malfunction of the landing gear aural warning system, accomplish the following; Modify the landing gear aural warning system and calibrate new switches, in accordance with either EMBRAER Service Bulletin No. 120-

The image part with relationship ID rId1 was not found in the file.





95 of 115


TAT:TAC:

Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:

Accomplished

Effective Date:

90-17-129/17/199090-07-04R4

95-25-1112/27/1995

96-09-246/11/1996

97-05-024/2/199795-01-01R2

98-03-193/18/199894-03-01R1

To minimize the potential hazards associated with operating the airplane in severe icing conditions, accomplish the following: Revise the FAA-approved Airplane Flight Manual (AFM) by inserting a copy of this AD in the AFM.

032-0055 dated March 16, 1989, or EMBRAER Service Bulletin No. 120-032-0052,

To prevent engine failure due to propeller overspeed, accomplish the following; Install a flight idle position electromechanical lockout device in accordance with EMBRAER Service Bulletin Number 120-076-0009,

NA by serial number

To prevent failure of the propeller and subsequent reduced controllability of the airplane due to high stresses on the propeller at certain nominal propeller revolutions per minute (RPM), accomplish the following: Revise the “limitations” and “normal procedures” sections of the AFM by inserting a copy of the AD.

To prevent binding of the aileron and subsequent reduced controllability of the airplane, accomplish the following: Modify aileron sealing canvas in accordance with SB 120-57-0021, Change 1, dated September 10, 1993; or Change 2, dated March 8,1996.

Complied with at factory build and per current AFM revision

Complied with per current AFM revision

NA by aircraft serial number

NA by serial numberTo prevent power interruption to the attitude heading reference system (AHRS).




96 of 115


TAT:TAC:


Accomplished

Effective Date:

98-13-297/29/1998

98-15-228/27/199897-09-07

99-02-18R13/3/199997-11-03R2

2000-19-0710/31/2000

To prevent a short circuit in the LH DC relay box, Within 75 hrs. , remove the bolt and

To prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight; revise the AFM by inserting a copy of AD.


To prevent delamination of the wing and empennage leading edge due to improper installation of the wing de-ice boot; within 75 hrs. or 120 days, perform a one-time visual inspection of the wing and empennage leading edge area behind the de-ice boots, IAW SB 120-51-A004

To prevent fretting of the titanium thermal insulating blankets, which could result in an increased risk of fire in the engine exhaust duct of the tail pipe;





97 of 115


TAT:TAC:


Accomplished

Effective Date:

2000-19-1010/13/200097-09-08R1

2000-22-1212/12/200097-11-01

2000-23-0912/20/200096-12-01

2000-23-301/2/200195-11-01

2001-06-184/16/200197-06-03R1

washer on the LH DC relay box IAW SB 120-24-A057. If no fastener is installed, seal fastener hole only.


To ensure that the flightcrew is able to recognize the formation of significant ice accretion,

To prevent mechanical blockage of the elevator control cable due to the freezing of water collected inside the fuselage between the rear pressure bulkhead and the firewall of the auxiliary power unit,

NA per aircraft serial number

Para (a) complied with by SWA on 05/06/2001 @ TAT: 4826.0 per AFM revision.



To prevent overheating of the wire between certain circuit breakers,

To prevent rupture of the hydraulic line and loss of hydraulic pressure due to chafing;

To prevent a sudden change in pitch attitude caused by autopilot disconnect,







98 of 115


TAT:TAC:


Accomplished

Effective Date:

2001-20-1710/22/20012001-05-02R2

2003-12-127/28/20032001-11-03R1

2004-01-042/13/200497-05-03R3

2004-06-074/29/20072001-06-02

2004-12-187/27/200142001-02-02R1

2004-13-128/6/2004

To prevent a possible loss of airplane control and subsequent injury to the flight crew and

To prevent significant movement of cargo during operations, which could result in loss of control of the airplane or injury to the flightcrew.

To prevent the landing gear doors from becoming blocked from opening during application of emergency procedures in the event of a loss of hydraulics.

To prevent overheating of cockpit wiring, which could result in loss of operation of the affected systems, or smoke or fire in the cockpit. A/C S/N 120004, 120006-120352

Para (a)(b) & (c ) complied with IAW AD 2001-13-14 by SWA on 07/03/2001 @ TAT: 5237.0. Para

(d)(e ) & (f)-(k) complied with by SWA on 11/21/2001 @ TAT: 6142.8 per SB 120-30-0033

& SkyWest EA# BR207-30.

NA by aircraft configuration

To ensure that the flightcrew is provided with accurate indications of the severity of ice accretion, clear indication of unintentional airplane speed reductions in icing conditions, and appropriate procedures to prevent reduced controllability:

To prevent the unavailability of supplemental oxygen to the flight attendant in the event of cabin decompression, which could result in loss of consciousness of the flight attendant,


Para (d) complied with by SWA on 07/18/2002 @ TAT: 7455.0 per SB 120-30-0030.

NA by aircraft configuration

Para (a)(1) & (a)(2) complied with by SWA on 08/19/2004 @ TAT: 11419.6 per AFM revision






99 of 115


TAT:TAC:


Accomplished

Effective Date:

2003-02-01

2004-13-138/3/20042002-12-02

2004-14-248/23/20042001-07-01R1

2004-14-258/23/20042004-01-06

2005-25-011/9/20062005-06-01

2006-02-022/24/20062005-08-03

2006-07-185/12/20062005-10-03

2006-10-096/20/20092005-12-04

2006-11-106/30/20062005-12-02

2006-12-147/18/20062005-12-03

2007-26-212/28/20082007-03-03

In order to preserve the original certification stick-shaker-to-stick-pusher marginswhen operating under the newly defined intercycle icing conditions, an upgraded Stall Warning Computer with new settings for shaker firing angle-of-attack (AOA) is required to be installed. The unsafe condition is reduced ability of the flightcrew to maintain

To prevent a potential source of ignition near a fuel tank, which, in combination with flammable fuel vapors could result in a fuel tank explosion

To prevent a potential source of ignition near a fuel tank, which in combination with fuel vapors, could result in a fuel tank explosion

To prevent a potential source of ignition near a fuel tank, which in combination with fuel vapors, could result in a fuel tank explosion

To prevent chafed electrical harnesses, which could result in a potential source of ignition for fuel vapors near a fuel tank and consequent fire or fuel tank explosion

To ensure the APU compartment is isolated from the rest of the airplane in the event of an APU Fire.

Perform visual inspection inside the torque tube of the elevator for corrosion, and to apply protective treatment to prevent corrosion in this region

To prevent possible multiple avionics failures caused by a lightning strike, which could reduce the ability of the flightcrew to control the airplane

To prevent inadvertent fuel transfer in flight due to fuel service personnel not repositioning the defuel valve switch control to the closed position after utilization on the ground, which could cause in-flight fuel starvation, A/C S/N 120003, 1200004 & 120006 - 120358.

To prevent restricted movement of the aileron or elevator, which could result in reduced controllability of the airplane.

passengers

Para (a) complied with by SWA on 09/15/2004 @ TAT: 11552.6 per visual inspection IAW SB 120-

57-0038.

Para (a) complied with by SWA on 08/10/2001 @ TAT: 5490.6 per AD 2001-17-01.

Verifed SB 120-36-0016R3 CW, verification CW 5-5-2008 TAT 21988.3

CW para (f) 6-5-2009 TAT 21187.5 TAC 28563

Para (a) complied with by SWA on 09/18/2004 @ TAT: 11552.6 per SB 120-33-037.

CW 9-3-2006 TAT 18266.7 TAC 26622

Para (f) complied with by SWA on 11/21/2005 @ TAT: 13842.7 per SB 120-53-0080.

Para (f) complied with by SWA on 03/17/2006 @ TAT: 14460.1 per EA# BR297A-55. Reference

AMOC letter dated 4/26/2006.

CW 9-4-2006 TAT 18266.7 TAC 26622

Para (f) complied with by SWA on 03/13/2006 @ TAT: 14460.1 per SB 120-30-0034.












100 of 115


TAT:TAC:


Accomplished

Effective Date:

2008-15-018/21/20082001-06-01R4

2009-15-189/2/2009

2010-19-0410/27/20102008-08-01

2011-01-0910/27/2010

2011-04-0910/27/2010

To prevent pitch trim upsets if the pitch trim actuators jam or freeze, which could result inreduced controllability of the airplane.

This AD was prompted by the determination that the current design of chemical oxygengenerators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate this hazard and ensure that all lavatories have a supplemental oxygen supply.

The corrective actions include revising the Limitations section of the airplane flight manual (AFM) to include a minimum fuel quantity, adding a minimum fuel quantity limitation for operation of the fuel booster pump, inspecting the fuel booster pump electrical harness of the left- and right-hand fuel tanks for damage, replacing any fuel booster pump assembly having a damaged electrical harness, installing clamps on the tank structure, and installing tie down straps for the fuel booster pump electrical harness

It has been found the occurrence of corrosion on the Auxiliary Power Unit (APU) mounting rods that could cause the APU rod to break, affecting the APU support structure integrity.

Prevent PBE units from igniting, which could result in a fire and possible injury to the flightcrew or other persons.(g) Within 120 days after the effective date of this AD, determine the serial number of the PBE units installed in the aircraft, (1) For any PBE that has a serial number from 003-50730M to 003-51329M inclusive: Before further flight, replace the PBE with a serviceable PBE, except as provided by paragraph (g)(2) of this AD. (2) For any PBE that has a label showing that it has been restored in accordance with B/E Aerospace Service Bulletin 119003-35-6: The replacement has been done, and no further action is required by paragraph (g) of this AD. (3) For any PBE not having a serial number from 003-50730M to 003-51329M inclusive: No further action is required by paragraph (g) of this AD.

the safe flight and landing of the airplane. The corrective action includes modification of certain electrical wiring and installation of anew Stall Warning Computer.

Verifed SB 120-36-0016R3 CW, verification CW 5-5-2008 TAT 21988.3 by incorporatioin of SB

120-27-0095 and -0096

Verified SB 120-28-0016 CW by Skywest 8-31-2008 TAT 19753.5

Verified SB 120-49-0023 CW by Skywest 5-27-2009 TAT 21187.5

NA by PN or SN installed

Superseded by AD 2012-11-09



101 of 115


TAT:TAC:


Accomplished

Effective Date:

2012-11-0910/27/2010

This AD was prompted by the determination that the current design of chemical oxygengenerators presents a hazard that could jeopardize flight safety. We are issuing this AD to eliminate this hazard and ensure that all lavatories have a supplemental oxygen supply.

NA OXYGEN GENERATORS NOT INSTALLED

102 of 115

Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163 Last Done Due Next

87-24-0112/27/1987

97-02-21 (d)3/3/199795-05-01R1

99-17-04 (b) 400 FH NA9/1/1999

99-19-28 400 FH 40010/20/1999

2000-22-08 Inspect 1000 FH12/11/200098-01-02


Terminating action complied with at factory build

NA by serial number

NA by brake part number installed

Terminating Action

To prevent reduced wing structural integrity and fuel leakage of the wing due to cracking of wing rib-to-skin support brackets Inspect wing skin for fuel leaks. Terminating acting Part D of SB 120-57-0031 must be accomplished by 3/3/1999

Prevent chafing between the aileron control cables and nylon grommets, which could result in failure of the aileron cables, and consequent reduced controllability of the airplane. Repetitive inspection 400 FH

Model EMB-120RT and -120ER series airplanes, equipped with BFGoodrich brake assemblies having part number (P/N) 2-1585 or 2-1479-1; certificated in any category

Terminating Action

To prevent deterioration and deformation of the mass-balance weights of the aileron, (a) For a/c s/ns 120-0291, 120-0294, and 120-0296 thru 120-0333, within 150 hrs., measure the clearance between the aileron mass

Terminating Action

Recurring Airframe Directives

Interval

To prevent failure of the main landing gear outboard wheel half, accomplish the following: Within the next 200 landings after the effective date of this AD, inspect the main landing gear outboard wheel halves, part number 300-603, for cracking

Aircraft Serial #:Effective Date:

NA by Part Installed



103 of 115



Interval


2003-15-059/4/200390-07-04R492-08-04R1

2004-12-122003-01-01

2008-04-18 R1 MRB Task 28-15 (SWA task ST28-500-10038/21/2008 Last Done: 28458.4 Next Due: 58458.42007-05-02

MRB Task 28-16, 28-17, & 28-18

Ref. Task 28-15, 28-16, Last Done: 18124.8 Next Due: 38124.828-17, 28-18

2011-08-098/1/2011 CW AD 2011-08-09 by WASI para (g) (h)

SWA tasks ST28-500-1005, ST28-600-1005, ST28-600-1004, & ST28-500-1006

Initial compliance per para (a) completed by SWA on 07/21/2004 and para (b) on 08/05/04 per SB 120-32-0088. Reinspection due each wheel or

speed transducer change.

Para (d)(1) & (2) NA by aircraft serial number. Para (d)(3) complied with by SWA on 04/18/2004 @ TAT: 10756.9 per SB 120-76-0022.

Terminating Action

(g) Within 600 flight hours or 180 days after the effective date of this AD, whichever

To prevent excessive gaps in the anti-skid drive coupling clips for the hubcaps of the main landing gear, which could result in momentary loss of the normal braking system at low speeds, and reduced controllability of the airplane, accomplish the following.

To prevent the potential of ignition sources, in combination with flammable fuel vapors, which could result in fuel tank explosions and consequent loss of the airplane. (f)(3): For the functional checks and detailed visual inspections, Tasks 15 to 18 of Section 6-Part E-Fuel System Limitations," EMBRAER Temporary Revision No. 22-1, dated November 18, 2005,of the EMBRAER EMB-120 Brasilia MRBR, MRB-HI-200: The initial compliance time is within4,000 flight hours or 48 months after the effective date of this AD, whichever occurs first. Thereafter those tasks must be accomplished at the repetitive interval specified in Section 6-PartE-Fuel System Limitations," EMBRAER Temporary Revision No. 22-1, dated November 18, 2005,of the EMBRAER EMB-120 Brasilia MRBR, MRB-HI-200.

Prevent inadvertent or intentional operation with the power levers below the flight idle stop during flight for airplanes that are not certificated for in- flight operation, which could result in engine overspeed and consequent loss of controllability of the airplane. Terminating action must be performed by 3/4/2005

balance weights and attach fittings IAW SB 120-27-0077, Change No. 1. 1. If within limits, reinspect 1000 hrs. until (b) c/w. 2. If outside limits, c/w terminating action IAW Part III of the SB. (b) For all a/c, within 2000 hrs., perform a one-time detailed visual inspection IAW Part II of SB 120-27-0077 change 01.





104 of 115



Interval


TAT:32873.0 Date 8/26/2016 next due TAT:33473.0 Date 2/26/2017

occurs first, with at least 400kg of fuel in each tank, determine the real fuel quantity in each tank using the dripless measuring stick, IAW subjects 28-41-00, fuel quantity indicating and 28-42-00, fuel quantity measuring. Before further flight compare the results of the fuel quantity measurement with the master fuel indicator (1) If the difference of the two measurements is greater than 60 kg on both tanks, before further flight do all corrective actions. (2) If the difference of the two measurements is greater than 60 kg on only one tank do the corrective actions. (I) Before further flight after each refueling, the actions required in (g) of this AD are done. (h) Repeat the actions required in (g) of this AD there after at intervals not to exceed 600 flight hours or 180 days whichever occurs

105 of 115


Limit Last Done Due Next100 FH 32976.1 33076.1

74-08-09R33/28/2012

75-12-10 NA

81-04-06 NA

86-05-02 NA

90-07-08R1 NA7/2/1990

95-22-0112/04/1995

95-26-15R112/26/1996

97-01-12 NA

99-08-21

99-23-22 NA

2001-22-1412/1/2001

2001-15-17

Equipment Airworthiness Directives

Puritan Bennett C351-2000 Passenger Oxygen masks

Transport Category, Lavatory trash bin fire hazard inspection

To prevent failure in multiple servos, modify the 161H-1 programmer (P/N 622-1036-001) in accordance with Collins Service Bulletin No. 6.

To prevent the possibility of destruction of the recording tape in an aircraft accident involving fire, inspect the CVR in accordance with Fairchild Products Alert Service Bulletin No. CVR A140

Effective Date:

S.E.L.A. Cabin fluorescent lighting

To prevent possible erroneous altitude information from being displayed to the pilot, inspect altimeter in accordance with procedures in AD text.

Aircraft Serial #:

Overland Aviation Services Fire Extinguishing System Bottle Cartridges

Aerospace Lighting Corp. Cabin Lighting

TCAS II system, with Mode "C" transponder & Gillham wiring connections

Collins CTL-92 Transponder Control Panels

NA - Bruce lighting installed

NA by cartridges installed

Centaurus Model C3-100 GPWS Equipment

CAS-81 TCAS NA

106 of 115


Equipment Airworthiness Directives

Effective Date:Aircraft Serial #:

8/20/2001

2006-16-18R17/18/2008

NA

Installing a warning placard on the TAWS/RMI

NA

107 of 115


PW118B Last Done Due Next

88-26-51 LH9/22/198989-06-02 RHCF-88-26R1

91-01-03 LH1/7/1991

RH

91-06-02 LH3/29/1991CF-90-21 RH

92-01-08 LH7/27/1992CF-89-14R1 RH

94-03-02 LH2/16/1994CF-94-01 RH

94-11-11 LH7/25/1994CF-91-26R1 RH

97-17-05 LH9/9/199797-06-01R1 RH

98-14-02 LH8/31/199897-10-06 RHCF-96-22

2003-16-04 LH9/10/2003CF-2000-34 RH

2003-21-03 LH11/20/2003CF-2002-10 RH

2006-19-06 LH9/29/2006CF-2005-29 RH

2012-11-14 LH7/20/2012CF-2012-12 RH

NA by engine modelTo prevent a fire in the ICC replace the low pressure rotor speed (NL) sensor port sealing tube IAW PWC SB 20914R4. Remove the switching valve to rear inlet case sealing air tube IAW PWC SB 20914R4

NA by SB21714R2 TABLES 1-5 SN LISTING

To detect prop shafts cracks, on engine SN listed in (ASB) PW100-72-A21813, If cracks are found remove from service before next flight. IF doing visual inspections repeat intervals, every 10 HRS. If doing UI inspections, repeat every 1000 HRS.

NA by shaft SN 7/30/2012

Remove from service high-pressure turbine (HPT) disks, PN 3035711 & 3038411.

To prevent the separation of the fuel filter bowl from the fuel heater, replace Stewart Warner fuel heater PN series 10718 with PN series 10839 or other acceptable part.

NA by PN installed 6/1/98

To prevent seizure of the high-pressure rotor; rework or replace the HP turbine front cover IAW SB 20417, 20412, 20604 OR 20979.


NA by SB21714R2 TABLES 1-5 SN LISTING

NA by PN installed

NA by PN installed

PCW by SKW para. a,b,c,d on 5/27/94

PCW by SKW para a)(1 IAW SB 21112 & 20914

ON 5/27/94

PCW bu SKW para a) IAW SIL PW 100-003 ON 9/6/97

PCW by SKW para a) IAW SB21077R8,21364R1, 12/4/98

PCW by SKW para a)(1 IAW SB 21112 , 6/14/93

Physical verification by SKW 1/27/99

CW 08/02/98 per SWA FCD 98-10-73

Engine Airworthiness Directives

To prevent fire in the engine intercompressor case (ICC) & nacelle cavities, replace the low pressure rotor speed (NL) sensor port sealing tube & external air tube IAW SB 21112

To prevent a nacelle fire caused by fluid leaking from the gas generator case drain ports, visually inspect the two gas generator cases drain ports IAW SIL PW100-003

To detect through-cracks in the propeller shaft & prevent uncontained engine failure & damage to the airplane, remove from service any prop shaft listed in SB PW100-72-21714. Terminating action must be C/W by 12/21/2007

To prevent engine fuel leaks, remove the existing fuel manifold transfer tubes, transfer tube lock plates & fuel manifold drain tubes IAW PWC SB 21077

To prevent a fire hazard in the engine nacelle, perform an HMU leak check & remove from service leaking HMU's

To prevent fuel leakage from fuel filter cover assy. install a new fuel pump filter cover IAW either PWC SB 20897 or 20907. Due 1200 hrs. TIS after 3/29/1991

To prevent an uncontained engine failure resulting from low cycle fatigue failure of certain high-pressure turbine (HPT) components, upon receipt retire HPT front cover, HPT rear cover, and HPT disk prior to 15000 cycles IAW PWC SB 20002.

Aircraft Serial #:Effective Date:TAT:

TAC:

NA by PN installed 1/7/04

NA by engine model

Engine Model:

NA BY SN

C/W @ Factory verified 6/14/93 by SKW

PCW by SKW para. a,b,c,d on 6/14/93

NA BY SN

PCW by SKW para (a) ICW SB20897 7/27/94

NA by PN installed

NA by PN installed














108 of 115


PW118B Last Done Due Next

Engine Airworthiness DirectivesAircraft Serial #:

Effective Date:TAT:TAC:Engine Model:

2012-26-08 LH2/15/2013CF-2012-12 RH

2013-15-08 LH9/17/2013CF-2013-02 RH


Prevent fracture of the first-stage PT blade, possible engine fire, and damage to the airplane. Unless already done, within 60 months after the effective date of this AD or when the affected PT blades are at module level exposure, whichever occurs first, do one of the following: (1) Replace the affected first-stage PT blade with a blade eligible for installation; or (2) Perform a one-time X-ray inspection of the affected first-stage PT blades, using paragraph 3.F.(2) of the Accomplishment Instructions of P&WC Service Bulletin No. PW100-72-21823,Revision 3, dated March 8, 2013

To detect and remove from service prop shafts listed in ASB PW100-72-A21802. Mandatory Terminating Action (1) For propeller shafts with an S/N listed in Table 1 of P&WC ASB No. PW100-72-A21802,Revision 4, dated March 16, 2012, remove the propeller shafts from service before further flight. (2) For affected S/N propeller shafts listed in Table 1 of P&WC ASB No. PW100-72-A21798, Revision 5, dated March 20, 2012, remove the propeller shafts from service within 6 months after theeffective date of this AD. (3) For affected S/N propeller shafts listed in Table 2 of P&WC ASB No. PW100-72-A21798,Revision 5, dated March 20, 2012, remove the propeller shafts from service within 12 months after the effective date of this AD.

NA by part SN, 9/25/13

NA by part SN, 9/25/13




109 of 115

Aircraft Registration: 120-35032873 8/29/201645163

Last Done Due Remaining93-06-067/6/1993 LH NA by PN

94-05-01R3 RH NA by PN

94-06-053/29/1994 LH 32869.0 33369.0 496.0

94-05-02 R1 RH 32869.0 33369.0 496.0

95-22-125/6/1996

TSI: 32869.0 37869.0 4996.0

TSI: 32872.4 37872.4 4999.4

96-08-01R1 LH #13/29/1994 #2

#3#4

RH #1#2#3#4

96-08-02 LH #15/9/1996 #2

#3#4

RH #1#2#3#4

96-25-20 LH PCU 910363 due rem2/7/1997 TSI: 30011.3 40511.3 7638.3

Act. SN 960412TSI: 31763.9 42263.9 9390.9

Xfer tube 99-11-012TSI: 1323.3 42049.8 9176.8

RH PCU 950440TSI: 32872.4 43372.4 10499.4

Act. SN 900637TSI: 26665.3 37165.3 4292.3

Xfer tube 756TSI: 2748.5 40624.5 7751.5

2006-10-07 LH #15/22/2006 #2

NA by PN/SNNA by PN/SNNA by PN/SNNA by PN/SN

NA by PN/SNNA by PN/SN

NA by PN/SN

NA by PN/SN


Ultrasonic shear wave inspection for cracks or surface indications IAW H.S. SB 14RF-9-61-86 or 14RF-9-61-A90 unless PCW by AD95-24-09 or 96-08-01. Perform one-time visual & fluorescent penetrant inspection of prop blade shank IAW SB 14RF-9-1-A92.

To prevent separation of a propeller blade due to cracks initiating in the blade taper bore, perform ultrasonic shear wave inspection for cracks in the blade taper bore IAW H.S. ASB 14RF-9-61-A95.

To prevent loss of propeller control due to failure of critical components, Inspect transfer tube assemblies and PCUs for wear within 6000 hrs. TIS or 3 years, whichever first. Re-inspect each 10,500 hrs. Inspect actuator assemblies for wear within 10,500 hrs. or at the next OH, then each 10,500 hrs. IAW SB 14RF-9-61-64.

To prevent blade failure that could result in separation of a propeller blade and loss of control of the airplane:

950440

PCW by SKW 3-19-98NA by PN/SNNA by PN/SN

NA by PN/SN

NA by PN/SN

NA by PN/SN

PCW by SKW 3/7/07

ASB No. 14RF-9-61-A53. Reinspect 2500 hrs. if ballscrew quill damper installed IAW SB, 500 hrs. otherwise. Terminated by installation of a Secondary Drive Quill IAW SB. With SDQ installed, perform torque check of primary ballscrew quill each 5000 hrs. IAW SB 14RF-9-61-75.

LH PCU SN:

SN's less than 885751

SN's less than 882038

Hamilton Standard Propeller Airworthiness Directives

TAT:TAC:

To prevent propeller hub cracking and loss of engine oil, perform torque check of the prop hub retaining nuts IAW Ham. Stand. Maintenance Manual TR 61-6. Re-torque nuts IAW TR 61-7, Ham. Stand. MM P5186. Perform torque check each 500 hours.

Aircraft Serial #:

PCU ballscrew quill wear. Remove titanium nitride transfer tubes and install A-1 type, replace PCU ballscrew IAW ASB 14RF-9-61-A57

Effective Date:

NA by PN/SN

980913

RH PCU SN:



110 of 115

Aircraft Registration: 120-35032873 8/29/2016

Hamilton Standard Propeller Airworthiness Directives

TAT:Aircraft Serial #:

Effective Date:#3#4

RH #1#2#3#4

2013-16-10 LH #1 6/21/2014 6/21/20219/19/2013 #2 2/2/2012 2/2/2019

#3 9/22/2013 9/22/2020#4 11/18/2013 11/18/2020

RH #1 1/23/2012 1/23/2019#2 12/30/2014 12/30/2021#3 3/10/2013 3/10/2020#4 11/1/2010 11/1/2017

PCW by SKW 11/10/04PCW by SKW 1/27/2006

NA by PN/SN

loss of airplane control. For Hamilton Sundstrand Corporation propeller models 14RF-9, 14RF-21, 14SF-5, 14SF-7,14SF-11E, and 568F-1, that have an approved update to the ALS, within 45 days after the effective date of this AD, perform an MI on the blades and hubs no later than seven years after the date since installation (DSI).

- Perform initial inspection of prop blade per ASB 14RF-9-61-A145 within 10 cycles or 5 days after the effective date of this AD; whichever first.- Perform second inspection of prop blades within 500 cycles or July 1, 2006; whichever first.Blades Model +E with SN's below 885751 (+E2 NA)

PCW by SKW 10/13/06


111 of 115

Aircraft Registration: N582SW 120-350TAT: 32873 Effective Date: 8/29/2016TAC: 45163

Garrett/Alliedsignal APU Airworthiness DirectivesAircraft Serial #:

Embraer Brasilia EMB120ER

N582SW 120-350

12/9/2015 Data Based On: Actual

26433 lbs.

16996 lbs.

9437 lbs.

328.37 ins.

5580939 in/lbs.

Notes: The above figures are with the aircraft configured with 30 passenger seats and an aft lav and galley.

Serial #:

Aircraft Model:Weight and Balance Data

Empty Weight:

Gross Weight:

Effective Date:

Arm ( Center of Gravity):

Moment:

Aircraft Type:

Registration #:

Useful Load:

113 of 115


Addendum #1Aircraft Serial #:

114 of 115


Addendum #2 Aircraft Serial #:

A/C: N560SW TAT: 34167.2SN: 120-334 TAC: 47949

Qty Equipment Manufacturer3 VHF Comm Collins0 HF Comm NA2 Nav Receiver Collins2 Compass System Collins2 Transponder Collins2 DME Receiver Collins2 RMI Indicator Collins2 Artificial Horizon Collins2 Encoding Altimeter Kollsman1 Altitude Alerter Collins1 ADF Receiver Collins2 Audio Control Panels Av-Tech2 Marker Beacon Rcvr Collins1 Weather Radar Collins1 ELT Transmitter Dorn Margolin4 HSI Indicator Collins1 OAT Indicator Ametek2 Directional Gyro Collins2 Autopilot Collins2 Flight Director Collins0 GPS receiver NA2 Data Processing Units Collins1 Standard Altimeter1 Cockpit Voice Rcrdr Fairchild2 Chronometer Astro Tech1 Flight Data Recorder Fairchild2 Vertical Gyro Collins2 Air Data Computer Collins1 Radar Altimeter Collins1 Display Unit FlightMax0 Hour Meter1 GPWS Sundstrand1 TCAS BF Goodrich2 AHRS Collins2 EFIS Collins1 FMS Universal1 MPU Collins

AHC-85 / EFD-86

AVIONICS

Model/Part NumberVHF-22A

NAVIR-32

EHSI-86

TDR-94D and TDR-94DME-42RMI-36AHC-85

24929-951(CP), 28704 45100-E2111

ADF-605091-1-4VIR-32

WXT-250BDMELT14-1-1

ADC-65B

DGL-0C119DAHC-85

APC-65BEFD-86

NADPU-86H24929-951

S200-0012-00LC-2EF1000

AHC-85

EFD-86UNS 1K

MPU-86H

ALT 55800NA

MARK VITCAS 791AHC-85

technical inspection aircrfaft appraisal …€¦ · aircrfaft appraisal and technical inspection :...

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