TECHNICAL INSPECTION AIRCRFAFT APPRAISAL …€¦ · AIRCRFAFT APPRAISAL AND TECHNICAL INSPECTION :...
Transcript of 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 400 FH Ref Insp Ref Insp
120-350 NA 1000 FH Ref Insp Ref Insp
120-350 NA 1500 FH Ref Insp Ref Insp
120-350 NA 1500 FH Ref Insp Ref Insp
120-350 NA 2500 FH Ref Insp Ref Insp
120-350 NA 4000 FH Ref Insp Ref Insp
120-350 NA 8000 FH Ref Insp Ref Insp
120-350 NA 12000 FH Ref Insp Ref Insp
120-350 NA 16000 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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
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)
Must be done at time of S/G restoration Task (24-01)
(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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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)
Must be done at time of S/G restoration Task (24-01)
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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
120-350 NA 5 YR NA by config NA by config
120-350 NA 1 YR NA by config NA by config
120-350 NA 1 YR NA by config NA by config
120-350 NA 1 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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
120-350 NA 1 YR NA by config NA by config
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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)
"C" CHECK OR 24 Months
(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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Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
According to Manufacture's recommendation
19 of 115
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
"5A" CHECK OR 12 Months
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
"C" CHECK OR 24 Months
"C" CHECK OR 24 Months
Check MLG spring cartridge for general condition
(32-61)
Inspect hub cap clip for controlled gap, general condition, fit & attachment
According to Manufacture's recommendation
"5A" CHECK OR 12 Months
Check MLG assy. for excessive play.
(32-63)
20 of 115
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
"C" CHECK OR 24 Months
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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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)
"C" CHECK OR 24 Months
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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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 300.00 AH NA NA
P381 APU 300.00 AH NA NA
P381 APU 1500.00 AH NA NA
P381 APU 1500.00 AH NA NA
P381 APU 1500.00 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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
P381 APU 4500.00 AH 26256.7 30756.7
P381 APU 75.00 AH NA NA
P381 APU 75.00 AH NA NA
P381 APU 75.00 AH NA NA
P381 APU 75.00 AH NA NA
P381 APU 1500.00 AH NA NA
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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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)
LH Prop section LH 9000.00 FHRH Prop section RH 9000.00 FH
(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
LH Prop section LH 10000.00 FHRH Prop section RH 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 Propeller section of this report for details
Reference LH Prop section of this report
Reference Propeller section of this report for details
Reference RH Prop section of this report
Reference RH Prop section of this report
Reference LH Prop section of this report
Chapter 61 Propellers
Verify overspeed governor operation
Reference LH Prop section of this report
Reference RH Prop section of this report
Reference RH Prop section of this report
Reference Propeller section of this report for details
26 of 115
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
(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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
Aircraft Type: Embraer Brasilia N582SW Serial #: 120-350TAT: 32873.0 8/25/2016TAC: 45163
Airframe Airworthiness Limitations
Registration:Effective Date:
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
Registration: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.
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
Registration: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.
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
N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration No.:Effective Date:
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
N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration No.:Effective Date:
Limits
Turbine Wheel PN 167222-1
35 of 115
N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration No.:Effective Date:
Limits
36 of 115
N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration No.:Effective Date:
Limits
A/C Time at install: A/C Cycles at install:
N582SW Serial #: 120-350TAT: 32873 8/29/2016TAC: 45163
Mods, STC's and Repairs
ircraft Registration NoEffective Date:
Limits
Modifications/STC ListingsDocumentDate/EA #
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
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).
NA BY SB 120-055-0008 COMPLIANCE
NA BY SB 120-057-0025 COMPLIANCE
NA BY SB 120-055-0007 COMPLIANCE
43 of 115
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
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).
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
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.
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
21-07
32796.0 34296.0
A1, A3, A5, A Bridge
21-03
32796.0 35296.0
A1, A3, A5, A Bridge
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
Aircraft Registration No.:Date:
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
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
Aircraft Registration No.:Date:
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.
Seat tracks for condition.(*): Applicable to aircraft EMB-120 COMBI,FULL CARGO (EMB-120FC) and QUICKCHANGE.
Seat tracks for condition.(*): Applicable to aircraft EMB-120 COMBI,FULL CARGO (EMB-120FC) and QUICKCHANGE.
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
A2, A4, A6, A Bridge
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.
Wing box beam lower skin andaccess openings.
Wing box beam lower skin andaccess openings.
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
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
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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.
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.
Inspect (General Visual) EWISComponents of POWER FEEDERS ANDWIRING BUNDLES for signs ofdamage, proper installation,chafing and general condition.NOTE: EWISRequires floor panel removal.
67 of 115
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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.
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N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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
N582SW Serial #: 120-350TAT: 32873 8/25/2016TAC: 45163
EMBRAER 2C CHECK
Aircraft Registration No.:Date:
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.
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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
Reinsp Last Due NextDone
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
Reinsp Last Due NextDone
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
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163
Reinsp Last Due NextDone
Corrosion Prevention & Control Program
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
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163
Reinsp Last Due NextDone
Corrosion Prevention & Control Program
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:
Complied with at factory build
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.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
95 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
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).
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
96 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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.
Complied with at factory build
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;
Complied with at factory build
Complied with at factory build
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
97 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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.
NA by aircraft serial number
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.
NA per aircraft serial number
NA per aircraft serial number
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,
Complied with at factory build
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
98 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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,
NA by aircraft serial number
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
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
99 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
100 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
101 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
TAT:TAC:
Non-Recurring Airframe Airworthiness DirectivesAircraft Serial #:
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
NA per aircraft serial number
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
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
103 of 115
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163 Last Done Due Next
Recurring Airframe Directives
Interval
Aircraft Serial #:Effective Date:
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.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
104 of 115
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163 Last Done Due Next
Recurring Airframe Directives
Interval
Aircraft Serial #:Effective Date:
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
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration: N582SW 120-350TAT: 32873 8/29/2016TAC: 45163
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
Aircraft Registration: N582SW 120-35032873 8/29/201645163
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 shaft SN 1/24/13
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
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
108 of 115
Aircraft Registration: N582SW 120-35032873 8/29/201645163
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
NA by shaft SN 1/24/2013
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
NA by shaft SN 1/24/2013
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
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
NA by PN/SNNA 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:
The image part with relationship ID rId1 was not found in the file.
The image part with relationship ID rId1 was not found in the file.
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
NA by PN/SNNA by PN/SN
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
Aircraft Registration: N582SW 120-350TAT: 32873 Effective Date: 8/29/2016TAC: 45163
Addendum #1Aircraft Serial #:
114 of 115
Aircraft Registration: N582SW 120-350TAT: 32873 Effective Date: 8/29/2016TAC: 45163
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