TRACE Mini-Pack

MidAmerican Aerospace, Ltd.

2727 16th Ave SW

Cedar Rapids, Iowa 52404

(319) 395-7767

8130 Mini-Pack

MidAmerican Aerospace, Ltd.

2727 16th Ave SW

Cedar Rapids, Iowa 52404

(319) 395-7767

FAA/United States

AUTHORIZED RELEASE CERTIFICATEFAA Form 8130-3, AIRWORTHINESS APPROVAL TAG

4. Organization Name and Address:

TurbineAero Repair50 South 56'^ Street, Chandler, Arizona 85226 (VIJR367K)

6. Item: 7. Description: 8. Part Number: 9. Quantity: 10. Serial Number:

3. Form Tracking Number:

S000019382

5. Work Ordcr/Contract/Invoice

Number:

R35817

ll.StatusAVork:

APU GTCP131-9B 3800702-1 P-5197 Repaired

12. Remarks:

The subject APU has been repaired and functionally tested lAW CMM 49-26-95 rev. 10 dated 14 Jul 2016. No ADs, SBs, DER repairs or PMA parts were incorporated. Refer to the ShopVisit Report, the Log Book Sheet and LLP Summary Sheet for all pertinent information.Engine shipped short the following parts: 28B545-9 starter/generator, 3888448-2 starter/generator wiring harness, 6430589-1 seal plate, MS21043-6 nut (4 ea.), 1549240-1 terminal cover,3885004-1 bleed duct, AS1895-7-350 seal, 234-591-9350 clainp (2 ea.).

TSN = 38715.30 TSO = 6374.79 TSR = 0.0 CSN = 35169 CSO=5780 CSR = 0

Certifies that the work specified in block 11/12 was carried out in accordance with EASA Part-145 and in respect to that work the component is considered ready for release to service underEASA Part-145 Approval Number: EASA 145.4948

3ai'Gertifics t!ie Items idcntllled above were nianiilactui ed. in:coiilbrini^':to;

Q VpproM'd design data .uid arc in a condition lor sate opcnilibivi;, '

Non-approved design data specified 111 Ulotk T2i

14a. El 14 CFR 43.9 Return to Service Other regulation specified in Block 12

Certifies that unless otherwise specified in Block 12, the work identified in Block 11and described in Block 12 was accomplislicd in accordance with Title 14, Code ofFederal Regulations, part 43 and in respect to that worlc, the items arc approved forreturn to service.

3b.- Authorized Sigiiatiiro:.

3d.;Nanie:(Typed!or Printed):

J3c- Approval/Aufhorrzation-No.: I| 14h. Authorized Signature:

14d.^^me (Typed or Printed):Bryan L. Davis

I3e. Date (dd/mmm/yvy.vj

14c. Approval/Certificate No.:

VIJR367K

14e. Date (dd/mmm/yyyy):

Hryan L. uavis | 31 Aug 2017User/Installer Responsibilities

It is important to understand that the existence of this document alone does not automatically constitute authority to install the aircraft engine/propeller/articlc.

Where the user/installer performs work in accordance with the national regulations of an ainvorthiness authority different than the airworthiness authority of the countryspecified in Block 1, it is essential that the user/installer ensures that his/lier airworthiness authority accepts aircraft cnginc(s)/propcllcr(s)/article(s) from the airworthinessauthority of the country specified in Block 1.

Statements in Bloclcs 13a and 14a do not constitute installation certification. In all cases, aircraft maintenance records must contain an installation certification Issued inaccordance with the national regulations by the user/installer before the aircraft may be llown.

FAA Form 8130-3 (02-14) ~~ NSN: 0052-00-012-9005

TurbineAero RepairFAA Repair Station VIJR367K

AP.U. Part No: 3800702-1

T.A.R. Job Number: S000019382

A.P.U. Serial No: P-5197

Airworthiness Directive ReportThe Airworthiness Directive (AD) Report Describes AD's complied with at this shop visit and identifies AD's previouslycomplied with as noted in the logbook.

AD Number Amendment Description Status

None apply to the 131-9B at this time.

Service Bulletin ReportThe following service builetins were incorporated in this A.P.U. during this shop visit:

SB Number Rev. No. Date Description

No service bulletins were incorporated during this shop visit.

Change No

DER RepairsThe following DER repairs were incorporated in this A.P.U. during this shop visit:

Repair Number Repair Description

No DER repairs were incorporated during this shop visit.

PMA Parts

The following PMA parts were incorporated in this A.P.U. during this shop visit:

No PMA parts were incorporated during this shop visit.

Inspector: Date: 31 Aug 2017

LIFE LIMITED PARTS SUMMARY

CUSTOMER: MidAmerican

APU MODEL: GTCP131-9B

APUT.S.N: 38715.30

JOB NUMBER: S000019382

APU SERIAL NUMBER: P-5197

C.S,N: 35169

COMPONENT PART

NUMBER

SERIAL NUMBER TOTAL TIME TOTAL

CYCLES

REMAINING LIFE

HOURS

REMAINING LIFE

CYCLES

U* Stage Turbine Wheel 3840310-3 13-156101-10860 6374.79 5780 N/A 24220

2"^^ Stage Turbine Wheel 3840165-4 020134502760 UNK 27338 N/A 2662

Tie Shaft 3822504-3 01P19070 UNK 27338 N/A 2662

Compressor Impeller 3822391-6 14-162053-00848 6374.79 5780 N/A 24220

NOTE: THE LIFE LIMITED PARTS SUMMARY IS A RESULT OF DATA SUPPLIED BY THE CUSTOMER AND

WHERE APPLICABLE, DATA FROM RECORDS SYSTEM.

THE TIMES AND CYCLES NOTED ARE AS RECEIVED AND DO NOT REFLECT THE TIMES AND CYCLES

INCURRED AT FINAL TEST.

APPROVED BY: DATE: 31 Aug 2017

TURBINEAfiiRO^TurbineAero Repair

FAA Repair Station VIJR367K

Test Type: Light/Medium RepairTest Date: 8/31/2017

Test Sheet#: T-011.038

Rev. Letter: Rev. G

Rev. Date: March 1, 2008 y ̂ATA Manual: 49-26-95, Rev. lU

Fuel Type; Jet A ASTM {D-1655-68)

Test Data Sheet

GTCP131-9[B]P/N 3800702-1

Test Operator: Bud Lohl

Engine Model: GTCP131-98Serial Number: P-5197

Customer: Mid American AeropspaceWork Order: S000019382

Oil Type: MobllJetll (MIL-PRF-23699)

Test Step Description1 Oil Quantity Sensor Check2 Run-In Checks

3 RTL Mode Performance CheckOil Pump Discharge Pressure

Oil Sump Pressure• Gearbox Vibration

Turbine Vibration- , Shaft Speed

EGT Spread, APU EGT 1 to 2EGT Spread. APU to Lab Ave

4 IGV Offset CheckAPU Inlet Temp (T2)

Bleed Pressure Corrected5 Comb. Load Perf. Check

Barometric Pressure

_________ Lab Average Inlet Temperature- EGT Spread. APU EGT 1 to 2

; EGT Spread, APU to Lab AveBleed Pressure Corrected

Bleed Temperature CorrectedBleed Airflow Corrected

• Lab EGT Average Corrected

6 MES Performance CheckBarometric Pressure

Lab Average Inlet TemperatureEGT Spread. APU EGT 1 to 2EGT Spread. APU to Lab Ave

Bleed Pressure Corrected. Bleed Temperature Corrected

Lab EGT Average Corrected

7 Flow Sensor Check7. 1 SCV Opening Check7.1 1 SCV Closing Check7.1 2 WC Error8 Surge System Check8. 2 Surge Check8.4 Surge Stability. 55 Ib/min8.6 Surge Stability, 0 Ib/min9 Surge Margin Check10 Automatic Start Checks1 1 Load Cycle Checks11.4 • 96 kW Shaft Load Stabilitv

11.6 MES Bleed Load Stabilitv11.8 Combined Load Stabilitv11.8.1 Combined Load Stabilitv EGT11.11 RTL Mode Stabilitv12 Oil Consumption Check

Total Starts During TestTotal Hours During Test

Reguired Pass/Fall

PASS

PASS

psig 60 to 75 62.1 PASS

inH20G -20 to 20 7.8 PASS

in/sec 0.65 max 0.370 PASS

in/sec 0.65 max 0.114 PASS

RPM 48678 to 48922 48804 PASS

Deq F 80 max 5 PASS

Deg F 40 max 4 PASS

Deg F 77

psia 51.2 to 52.2 51.5 PASS

psia 14.02

Deg F 77

Deg F 80 max 6 PASS

Deq F 40 max 1 PASS

psia 51.2 to 52.2 51.3 PASS

Deg F 445 max 420 PASS

Ib/min 155 min 155.7 PASS

Deg F 1115 max 1111.2 PASS

seconds 60 max

1160 max 1138.5

4 min I 5

2 min 3.23

Overall Test Results:

psia - 14.00

Deg F 78

Deg F 80 max 11 PASS

Deg F 40 max 3 PASS

psia 53.7 min 54.0 PASS

Deg F 445 max 430 PASS

1105 max 1104.9 PASS

Ib/min 47.7 to 52.4 49.8 PASS

Ib/min 47.7 to 52.4 51.7 PASS

% -5 to 5 1.56 PASS

Remarks:

Operator Signature: Stamp:

12 08311709144S.):is

* *

TURBINEAERO

Shop Visit Report

Prepared for

MIDAMERICAN AEROSPACE

Customer P.O.#;

A.P.U. Model #:

A.P.U. Serial#:

A.P.U. Part#:

Received Date:

Completion Date:

R35817

GTCP131-9B

P-5197

3800702-1

TurbineAero Repair Job #: 8000019382

08-10-2017

08-31-2017

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56'" StreetChandier, AZ 85226

Phone 480-824-2700

Fax 480-824-2699

Customer Reason for Removal:

-Please bench check unit and advise

Customer Requested Workscope:

-Test

Incoming APU Times and Cycles:

TSN: 38,715.30

TSO: 6,374.69 CSO: 5,780

Incoming LLP Times:

1®'stage Turbine Rotor: CSN: 5,780 Cycles Remaining: 24,220

2"^^ Stage Turbine Rotor: CSN: 27,338 Cycles Remaining: 2,662

Turbine Shaft: CSN: 27,338 Cycles Remaining: 2,662

Engine Compressor Rotor: CSN: 5,780 Cycles Remaining: 24,220

UNK

CSN

GSR

CSO

35,169

UNK

5,780

Data Plate Information:

Gearbox Assembly Data Plate: P/N: 3805051-1 S/N:-None Listed

Receiving Inspection Findings:Shipping container is a wooden shipping container with a metal engine stand resting on high density foam-NOTE—This is a brand new TAR leaner 131-9B shipping that was loaned out to MIDAMERICAN on job # 819008that was received in on 05-03-2017 and shipped out to Goodyear Airport to bring in this engine in.

Serial number: N/A

Shipping container damage: ^NO DYES -No Damage

A.P.U. external damage: DNG ^YES -The oil cooler is plugged up with dirt and debris—Numerous rivets onthe inlet plenums are corroded—The inlet plenum T-Boits are very rusty—Load Compressor Static Pressure Tube B-Nutferal is very rusty P/N 3884980-3—Plenum drain tube B-Nut feral Is very rusted P/N 3617068-1—Numerous wire harnessquick release Stand-Off brackets are very rusty—The bonding strap located on the R/H side of the Load Compressorgoing to the inlet sensors is damaged and corroded P/N l\/183413/8-G014BC—The oil cooler tube gang clamp is very rustyP/N 3616869-2—The wire harness brackets that are installed on bracket P/N 3616761-1 are very rusty—The MufflerDrain Tube Aeroquip sheathing Is torn P/N 3883897-1—The main wire harness P1 connector is missing its RFi groundingspring—A.P.U. missing parts: DNO ^YES -Starter Generator P/N 28B545-9—Starter Generator SealPlate P/N 6430589-1—Starter Generator Wire Harness P/N 3888448-2—4ea Starter Generator Terminal Nuts P/N

MS21043-6—Starter Generator Terminal Cover P/N 1549240-1—Bleed Duct P/N 3885004-1—1ea bleed duct seal P/N

AS1895-7-350—2ea bleed duct clamps P/N 234-591-9350—

Log Book Received:

Customer Supplied:

IEIno

□no

□yes

□yes

Starter Brush Wear Indicator: □Full □% 0^2 □Va □Flush □N/A

Engine rotation:

Oil condition:

□Smooth □Rough □Seized□Normal □Burnt □Contaminated □No Oil

TARF 4,1,4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56"" StreetChandler, AZ 85226

Phone 480-824-2700Fax 480-824-2699

IGVPull Test (5 lb. max):

Delta "P" Indicators

Oil Pump Delta "P" extended:

Filters

Lube Pump Contamination:

Fuel Control Contamination:

Gen. Scavenge Contamination:

Magnetic Chip Detector

Gearbox Chip Detector;

A.P.U. Borescoped

Borescope Findings:

Load Compressor Rotor:

Engine Compressor Rotor:

1®' Stage Stator:

1^* Stage Turbine Blades:

2"^ Stage Turbine Blades:

Combustion Chamber:

4.0 pounds

[ElNG Dyes

□ None [ELight GModerate GHeavy□None GLight GModerate GHeavy□ None GLight GModerate GHeavy

GNone GLight GModerate GHeavy

□no lYES

□Acceptable GDarnaged

G Acceptable G Damaged

G Acceptable GDamaged -Minor environmental build up

Acceptable GDamaged -Minor tip erosion

Acceptable GDamaged

Acceptable GDamaged -Moderate loss of TBC

Incoming Functional Test ResultsComplete detailed functional test results are available upon request

GA.P.U. was not pre-tested. See remarks below.GA.P.U. was not pre-tested due to major internal damage.GA.P.U. was not pre-tested due to major external damage.GA.P.U. was not pre-tested due to metal contamination in oil.GA.P.U. was pre-tested. Results are within acceptable manual specifications.GA.P.U. was pre-tested. The following results exceed allowable specifications:

-High corrected EGT during Combination Load Performance Check-High corrected EGT and fails EGT split during MES Performance Check

TARF 4,1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56"^ StreetChandler, AZ 85226

Phone 480-824-2700Fax 480-824-2699

Recommended Workscope:Gearbox Workscope:

Load Compressor Workscope:

Power Section Workscope:

Line Replacement Units:

Visually inspect and accept, disassembly not required at this point.

Visually inspect and accept, disassembly not required at this point.

Visually inspect and accept, disassembly not required at this point.

Overhaul Fuel Manifolds. Repair Main Wire Harness (missing RF Spring). Allother LRU's functioned normally during APU testing, visually inspect and use as is.

Misc. Workscope: Repair external damage identified during receiving inspection, in particularthe corrosion identified. Visually inspect remaining components, repair as necessary.

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South se'" StreetChandler, AZ 85226

Phone 480-824-2700

Fax 480-824-2699

EVALUATION AFTER WORKSCOPE

Gearbox Condition CommentsQMetal ContaminationQBearing FailureQGear FailureDOil LeakQLiners Worn/ScoredQHIgh Hours/Cycles□ Requires Modification□Customer Request□other

Gearbox recommended workscope□Repair □Overhaul □Visually Accept □Not

Load Compressor Condition Comments□strike Damage□Bearing Failure□Rub Damage□IGV Wear/Failure□low Performance□Surge Margin□oil Leak□other

Load Compressor recommended workscope□Repair □Overhaul □ Visually Accept □Not

iNot

□Not

Disassembled

Disassembled

Power Section Condition□strike Damage□ Bearing Failure□ Blade Shift□Blade Failure□Rub Damage□High Hours/Cycles□Hot Section Deterioration□ High EOT□oil Leak□other

Power Section recommended workscope□Repair □Overhaul □hSI

Line Replaceable Units□Route for Test and Repair as Necessary□Metal In Oil Check List

Auxiliary Power Unit□ Repair □Overhaul □HSI□Return As Is □ F/T Only

Comments

Visually Accept iNot Disassembled

Comments

□No Fault Found □Beyond Economical Repair/Part Out

TARF 4.1.4-22 (Rev, M, 05/17) TurbineAero Repair50 South 56"" StreetChandler, AZ 85226

Phone 480-824-2700Fax 480-824-2699

Analysis and ConclusionConfirmation of Cause for RemovalConfirmation of Cause for Removal ONo ClYes I^N/AMidamerican Aerospace GTCP131-9B S/N P-5197 (S19382) was received at TurbineAero Repair on 08-10-2017 with arequested workscope to EVALUATE FOR SV CONDITION BENCH TEST. The Customer-provided Time Since New was38,715.30 hours, and Customer-provided Time Since Overhaul was 6,374.79 hours. Time Since Repair was not provided.

The 2"" Stage Turbine Disk and Turbine Shaft each reflect only 2,662 cycles remaining from their original 30,000 cycle lifelimit.

Receiving inspection findings include the following:

External damage identified includes:-The oil cooler is plugged up with dirt and debris.-Numerous rivets on the inlet plenums are corroded.-The inlet plenum T-Bolts are corroded.-P/N 3884980-3 Load Compressor Static Pressure Tube B-Nut ferrule is very corroded.-P/N 3617068-1 Plenum Drain Tube B-Nut ferrule is very corroded.-Numerous wire harness quick release Stand-Off brackets are corroded.-P/N M83413/8-G014BC Bonding Strap on R/H side of Load Compressor going to Inlet Sensors damaged and corroded.-P/N 3616869-2 Oil Cooler Tube gang clamp is corroded.-Wire Harness Brackets that are installed on bracket P/N 3616761-1 are corroded.

-P/N 3883897-1 Muffler Drain Tube Aeroquip sheathing is torn.-The Main Wire Harness PI connector is missing its RFI grounding spring.

Missing parts identified include;-P/N 28B545-9 Starter Generator.

-P/N 6430589-1 Starter Generator Seal Plate.

-P/N 3888448-2 Starter Generator Wire Harness.

-P/N MS21043-6 Starter Generator Terminal Nuts (4ea).-P/N 1549240-1 Starter Generator Terminal Cover.

-P/N 3885004-1 Bleed Duct.

-P/N AS1895-7-350 Bleed Duct Seal

-P/N 234-591-9350 Bleed Duct Clamps (2ea).

Engine rotation was smooth. The Inlet Guide Vane pull test was within limits. The Oil Pump Differential Pressure Indicatorwas not extended. The Lube Pump and Generator Scavenge Filters had light contamination. The Fuel Control Filter wasnot contaminated. The Magnetic Chip Detector was not contaminated.

The Borescope Inspection revealed the following discrepancies:-Minor environmental build-up on the 1®^ Stage Stator:-Minor tip erosion on the 1 Stage Turbine Blades.-Moderate loss of Thermal Barrier Coating on the Combustion Chamber.

The APU was tested and was rejected for the following reasons;-High Corrected Lab EGT Average during Combo Load Performance Check

-Maximum limit = 1115 degrees F; actual EGT recorded = 1138.6 degrees F-APU EGT 1 to APU EGT 2 spread out of limits during MES Performance Check

-Maximum limit = 80 degrees F spread between two readings; actual EGT spread recorded = 82 degrees F-High Corrected Lab EGT Average during MES Performance Check

-Maximum limit = 1105 degrees F; actual EGT recorded = 1129 degrees F

The high EGT mav be attributed to clogged and coking Fuel Nozzles.

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56'" StreetChandler, AZ 85226

Phone 480-824-2700

Fax 480-824-2699

At this point, the minimum recommended workscope necessary to return this APU to service v^/ouid be to;• Gearbox: Visuaily inspect and accept, disassembly not required at this point.• Load Compressor: Visually inspect and accept, disassembly not required at this point.• Power Section: Visuaily inspect and accept, disassembly not required at this point.• Line Replaceable Units: Overhaul Fuel Manifolds. Repair Main Wire Harness (missing RF Spring). Ail other

LRU's functioned normally during APU testing, visually inspect and use as is.• Miscellaneous: Repair external damage identified during receiving inspection and referenced above, in particular

the corrosion identified. Visually inspect remaining components, repair as necessary.

If overhauling the Fuel Manifolds cannot bring the temperatures into acceptable ranges the Power Section will requiredisassembly, if this becomes necessary, the Customer will need to decide whether to replace the 2"" Stage Turbine Diskand Turbine Shaft that are nearing the end of their service life with only 2,662 cycles remaining.

08-21-2017 update: Customer agreed to perform the minimum recommended workscope listed above.

Significant teardown findings: All 10 Fuel Nozzles failed bench check for a variety of reasons to include streaking, highprimary flow, spray angle out of limits, and low flow. All require replacement. Seven of the 10 Fuel Nozzle Shrouds wererejected for excessive dome erosion.

TARF 4.1.4-22 (Rev. M. 05/17) TurbineAero Repair50 South 56'^ StreetChandler, AZ 85226

Phone 480-824-2700

Fax 480-824-2699

Service Bulletin ReportThe service bulletin report describes all service bulletins incorporated this shop visit.

SB. Number Rev.

No.

Description

No service bulletins were incorporated during this shop visit.

ChangeNo.

Airworthiness Directive ReportThe Airworthiness Directive (A.D.) Report describes A.D.s complied with at this shop visit and identifies A.D.s previously

complied with as noted in the logbook.

A.D. Number Amendment Description

N/A N/A None applicable to this APU at this timeStatus

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56'" StreetChandler, AZ 85226

Phone 480-824-2700

Fax 480-824-2699

Accessories Parts Status ReportRemoved Status Installed

Part Number Serial No. Use Rework O/H Replace Part Number Serial No.

Bleed Air Valve 3291214-2 234 □ □ □ 3291214-2 234

Temperature 160550-1 48-308 □ □ □ 160550-1 48-308Control ValveData Memory 3876287-1 GE2228 □ □ n 3876287-1 GE2228Module

Delta Pressure 3876227-2 141121426652 m □ □ □ 3876227-2 141121426652Sensor

E.G.T. 3876271-1 50413-1400762 □ □ □ 3876271-1 50413-1400762ThermocoupleE.G.T. 3876271-1 50413-1000332 □ □ □ 3876271-1 50413-1000332ThermocoupleFuel Control 441921-5 CUC11194 E] □ □ □ 441921-5 CUC11194Unit

Starter/Generator Not received □ □ □ □ Not installed

Igniter Plug 305766-1 N/A □ □ □ 305766-1 N/A

Igniter Plug 3876132-12 N/A □ □ □ 3876132-12 N/ALead

Ignition Unit 10-617075-6 980218000284 □ □ □ 10-617075-6 980218000284

Inlet Guide Vane 3886188-3 1600 1^ □ □ □ 3886188-3 1600Actuator

Inlet Pressure 3876225-2 1031121402070 m □ □ □ 3876225-2 1031121402070Sensor

Inlet Temp Bulb MS28034-1 N/A 1^ □ □ □ MS28034-1 N/A

Low Oil 3876255-2 12741 □ □ □ 3876255-2 12741Pressure Switch

Lube Module 4131020-3 1327 □ □ □ 4131020-3 1327

Oil Cooler 160564-2 48-332 □ □ □ 160564-2 48-332

Oil Level Sensor 3876298-3 1416222105834 □ □ n 3876298-3 1416222105834

Speed Sensor Not accessed □ □ □ Not accessed

Surge Control 3291238-2 493 □ □ □ 3291238-2 493Valve

Flow Divider 3883830-1 1010 □ □ □ 3883830-1 1010

Solenoid Valve 692546-4 260 !EI □ □ □ 692546-4 260

Total Pressure Not accessed m □ □ □ Not accessedProbe AssemblyTotal Pressure Not accessed n □ □ Not accessed

Sensor

Starter/Generator Not received □ □ n □ Not installedWiring HarnessMain Wiring 3888449-2 017030 □ □ □ 3888449-2 017030Harness

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56'" StreetChandler. AZ 85226

Phone 480-824-2700Fax 480-824-2699

Life Limited Parts ReportThe life limited parts report describes the operating times and cycles of life limited parts installed on this A.P.U.

First StageTurbine Rotor

Second StageTurbine Rotor

Rotor

Part No. Serial No. J TSN CSN

3840160-5 13-156101- '10860 1

6374.79 5780

3840165-4 020134502760 j UNK 27338

3822504-3 01P19070 UNK 27338

3822391-6 14-162053-

00848

6374.79 5780

Remarks

Not removed

Not removed

Not removed

Not removed

Preservation

Note: APU is preserved in accordance with Honeywell SB 49-7997, current revision. Preservation duration is dependenton owner/operator compliance with SB requirements.

□Short Term Storage (3 months or less)

□Long Term Storage (2 years or less)NOTE: Fuel system preserved for long term storage must be de-preserved in accordance with the applicable CMM.

Acceptance Test Report

The APU was assembled and tested in accordance with ATA manual 49-26-95 rev. 10 dated 14 Jul 2016.

Documents shipped with APU:□8130-3 DFAA form 337 Dlog Book □Test Data Sheet □Shop Visit Report□other

TARF 4.1.4-22 (Rev. M, 05/17) TurbineAero Repair50 South 56"^ StreetChandler, AZ 85226

Phone 480-824-2700Fax 480-824-2699

LOG BOOK Mini-Pack

MidAmerican Aerospace, Ltd.

2727 16th Ave SW

Cedar Rapids, Iowa 52404

(319) 395-7767

FERRY

FLIGHTS Mini-Pack

MidAmerican Aerospace, Ltd.

2727 16th Ave SW

Cedar Rapids, Iowa 52404

(319) 395-7767

REFERENCE

Standard Warranty Policy

Reference: TARR 1.3.1-1

Revision: B

Date: 01/27/17

Page 1 of 3 All information contained herein is competition sensitive, proprietary and the exclusive property of TurbineAero Repair. This

information may not be divulged to any third party in whole or part without the express written consent of TurbineAero Repair.

TARR 1.3.1-1 (Rev. B, 01/17)

STANDARD WARRANTY: All APU Models

WORKSCOPE

DURATION

LIMITER

Minor Repair 6 Months after delivery or 500 APU Hours or Cycles

Whichever comes first. See Notes

Major Repair 12 Months after delivery or 1,000 APU Hours or Cycles

Whichever comes first. See Notes.

1. All warranty services shall be performed in accordance with Buyer’s Authorized Build Standard. This means that the APU warranty repair will conform to the repair and overhaul technical specifications agreed between Buyer and TurbineAero Repair Engineering. These specifications contain the approvals (or otherwise) with regard to the use of DER and PMA parts.

2. Seller warrants that the articles delivered hereunder conform to appropriate technical data in

accordance with FAA requirements and are free from defects in workmanship within the area that repairs were performed for the applicable warranty period only to the extent that such defects are reasonably ascertainable.

3. The customer shall inspect each APU or Accessory promptly after delivery, but in no case, later than 14 days after actual receipt. Unless rejected within such time period, the APU or Accessory shall be deemed by the parties to be accepted. 4. The responsibility of Seller hereunder, and the sole and exclusive remedy of Buyer under this

warranty, is limited to correction or replacement by Seller, at its facility, without charge. Further, any article or part that has been returned to Seller, in accordance with this warranty, shall require that Seller has been notified in writing, of the defect or nonconformity, within the warranty period and that the affected article or part has been returned to Seller within fifteen (15) days after discovery of such defect or nonconformity.

5. The seller shall not be responsible for any costs associated with removal and reinstallation of

the APU or Accessory nor any routine adjustments made at the time of installation. 6. Seller shall have the sole right to determine whether returned articles or parts shall be repaired

or replaced. 7. Seller agrees to assume round-trip transportation costs for defective or non-conforming articles

or parts in an amount not to exceed normal surface shipping charges within the United States, provided the article has been accepted as a valid warranty claim.

REFERENCE

Standard Warranty Policy

Reference: TARR 1.3.1-1

Revision: B

Date: 01/27/17

Page 2 of 3 All information contained herein is competition sensitive, proprietary and the exclusive property of TurbineAero Repair. This

information may not be divulged to any third party in whole or part without the express written consent of TurbineAero Repair.

TARR 1.3.1-1 (Rev. B, 01/17)

STANDARD WARRANTY: All APU Models

8. These warranties will not apply if the articles or any parts thereof have been:

a. subjected to any maintenance, overhaul, installation, storage, operation, use, handling or environment which was not in keeping with industry standards or performed without Seller’s written approval;

b. subjected to any alteration modification, or repair, after the APU or any of its components have been delivered to Buyer, by anyone other than Seller or Seller’s subcontractor;

c. subjected to any accident, misuse, neglect, or negligence after delivery by Seller; d. visually or functionally tested by the Seller or Seller’s representative, as part of a warranty

claim, and no fault was found; e. removed from service due to scheduled retirement or scheduled inspection; f. subject to the removal or modification of the article as a requirement of Federal or State

regulation; or g. subject to erosion or environmental hazard resulting in deterioration of the article’s

performance or efficiency. 9. The warranty shall not apply to any article to the extent that the defect or nonconformity is

attributable to any part not supplied by or repaired by Seller or Seller’s subcontractor. Where OEM new parts were found defective, this warranty is limited to the OEM new part warranty policy. In the event LLP parts are damaged beyond repair, Seller shall only be obligated for the remaining life for those parts.

8. Seller’s obligations under these warranties are conditioned upon Buyer’s obligation to maintain

records that accurately reflect operating time and maintenance performed on affected equipment and establish the nature of any unsatisfactory condition. Seller, at its request, shall be given access to such records for the purpose of substantiating warranty claims.

9. All other warranties, whether express, implied or statutory, such as warranties of merchantability

of fitness for a particular purpose are hereby excluded and disclaimed to the extent they exceed the warranties granted herein. In no event shall Seller be liable for consequential or incidental damages.

REFERENCE

Standard Warranty Policy

Reference: TARR 1.3.1-1

Revision: B

Date: 01/27/17

Page 3 of 3 All information contained herein is competition sensitive, proprietary and the exclusive property of TurbineAero Repair. This

information may not be divulged to any third party in whole or part without the express written consent of TurbineAero Repair.

TARR 1.3.1-1 (Rev. B, 01/17)

STANDARD WARRANTY: All APU Models 10. Warranty repair or replacement of any part shall not extend the warranty beyond the original

warranty period.

11. The first one hundred eighty (180) days of the warranty period will be covered at 100% and the remaining one hundred eighty five (185) days will be covered on a 50% prorate basis.

Covered warranty repairs after the initial 180 days will be calculated using the following formula:

Days in Service - 180 x .50 = Pro Rated Percentage of warranty not covered

13. Warranty is non-transferable without prior written approval by the seller.