manual control sheet (mcs) - ac aviation · maintenance program section 0 page a manual control...

MAINTENANCE PROGRAM SECTION : 0

PAGE : A

MANUAL CONTROL SHEET

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DATE : 27/02/2018

------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ This document is property of AC Aviation Co., Ltd. Do not Copied or distributed without company allowed.

SECTION-0 GENERAL INFORMATION

MANUAL CONTROL SHEET (MCS)

Authority Position Signature Date (dd/mm/yy)

Prepared by Head of Engineer

27/02/2018

Reviewed by Head of Quality

Approved by Accountable Manager

Controlled

Copy No.


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TABLE OF CONTENTS

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DATE : 27/02/2018


TABLE OF CONTENTS (TOC)

Contents SECTION-0 GENERAL INFORMATION ................................................................................................................... A

MANUAL CONTROL SHEET (MCS) .................................................................................................................... A

TABLE OF CONTENTS (TOC) ............................................................................................................................. B

LIST OF EFFECTIVE PAGE-1 (LEP) ......................................................................................................................H

LIST OF EFFECTIVE PAGE-2 (LEP) ....................................................................................................................... I

RECORD of REVISION (ROR) .............................................................................................................................. J

REVISION TRANSMITTAL(RT) ........................................................................................................................... K

CONTROL DISTRIBUTION LIST (CDL)................................................................................................................. L

SECTION 1 – GENERAL REQUIREMENTS .............................................................................................................. 1

1.1 Company Statements ................................................................................................................................. 1

1.2 Aircraft Application .................................................................................................................................... 2

1.3 MP Owner and Maintenance Oragnization Address .................................................................................. 2

1.4 DOCUMENT REFERENCE ............................................................................................................................ 2

1.5 AIRCRAFT UTILIZATION .............................................................................................................................. 3

1.6 Specific structural maintenance programs ................................................................................................ 3

1.7 Reliability program ..................................................................................................................................... 4

1.8 ADs/SBs Assessment ................................................................................................................................... 4

1.9 Repairs and Modifications ......................................................................................................................... 4

1.10 RVSM and PBN Maintenance Procedures................................................................................................ 4

1.10.1 RVSM Maintenance Procedures .......................................................................................................... 4

1.10.2 PBN Maintenance Procedures ............................................................................................................. 5

1.11 Ageing Aircraft System ............................................................................................................................. 5

1.12 Critical Design Configuration Control Limitation )CDCCL( ........................................................................ 5

1.13 Aircraft Electrical Wiring Interconnect System )EWIS( ............................................................................. 5

1.14 Limit Of Validity ) LOV( ............................................................................................................................... 5

1.15 Certification Maintenance Requirements )CMR’s( ................................................................................... 5

1.16 MP Amendments and Review ................................................................................................................. 5

1.17 Permitted Variation to Maintenance Periods –Procedure ...................................................................... 5


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1.18 Airworthiness Limitation Items ................................................................................................................ 7

1.19 Maintenance Certificate release to service )CRS( .................................................................................... 7

1.20 CAAT Maintenance requirements............................................................................................................ 7

1.21 CVR/FDR Download Procedures .............................................................................................................. 9

1.22 Calibration of the FDR system ................................................................................................................. 9

SECTION 2 – MP INTRODUCTION...................................................................................................................... 10

1.0 Information .............................................................................................................................................. 10

A. General............................................................................................................................................... 10

B. Warnings, Cautions and Notes .......................................................................................................... 10

C. Special Conditions Cautionary Notice................................................................................................ 10

D. .Schedule Layout ................................................................................................................................ 11

E. How To Use The Schedule ................................................................................................................. 11

2.0 Periods and Tolerances ............................................................................................................................ 13

A. General Instructions .......................................................................................................................... 13

B. Tolerances .......................................................................................................................................... 15

3.0 Composition of Schedule and Task Numbering....................................................................................... 15

A. Composition of Schedule ................................................................................................................... 15

B .Task Numbering ..................................................................................................................................... 16

4.0 Inspection Periods .................................................................................................................................... 16

A. General............................................................................................................................................... 17

B. There is no Inspection group A, instead, there is a 400 Hour Detailed Walk-Around inspection. .... 18

C. The breakdown of Inspection groups "B", "C", "D", "E "and "F "and the areas dealt with in the

inspections are listed below. ..................................................................................................................... 18

D. Flexible Maintenance Charts (Figure 1. and Figure 2.) ....................................................................... 18

E. The inspections contained in the Schedule are to be completed in accordance with the following

instructions ................................................................................................................................................ 19

F. Sign Off Requirements ....................................................................................................................... 20

5.0 Continued Airworthiness Requirements .................................................................................................. 20

A. At each periodic inspection the depth of inspection must:............................................................... 21

B. A series of standard terms are used throughout the schedule to indicate the inspection

requirements ............................................................................................................................................. 22

C. The inspection criteria ........................................................................................................................... 23


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D. Maintenance Practices and Procedures ............................................................................................ 25

E. All Vital Points and Control Systems .................................................................................................. 26

F. Wear Limits on All Flying Control and Engine Control Cables ........................................................... 26

G. Fuel System Contamination Checks................................................................................................... 27

H. Portable Valise Type Life rafts ........................................................................................................... 27

6.0 Schedule Format....................................................................................................................................... 27

A. Minor and Routine Inspections ......................................................................................................... 27

B. Structural Inspections ........................................................................................................................ 28

C. Out of Phase Inspections ................................................................................................................... 28

D. Special Incident Inspections .............................................................................................................. 28

E. Panel Location Charts ........................................................................................................................ 28

F. Lubrication ......................................................................................................................................... 28

G. Component Requirements ................................................................................................................ 29

7.0 Abbreviations, Terms and Definitions ...................................................................................................... 29

8.0 Additional Requirements Introduced by Revision Action ....................................................................... 30

SECTION 3 - ATA TASK CODES ............................................................................................................................ 37

Chapter 05 - Time Limits/Maintenance Checks .............................................................................................. 37

Chapter 12 - Servicing .................................................................................................................................... 38

Chapter 20 - Standard Practices - Airframe .................................................................................................... 39

Chapter 21 - Air Conditioning ......................................................................................................................... 39

Chapter 22 - Autopilot .................................................................................................................................... 42

Chapter 23 - Communications........................................................................................................................ 42

Chapter 24 - Electrical Power ......................................................................................................................... 43

Chapter 25 - Equipment & Furnishings .......................................................................................................... 45

Chapter 26 - Fire Protection ........................................................................................................................... 46

Chapter 27 - Flight Controls ........................................................................................................................... 47

Chapter 28 - Fuel ............................................................................................................................................ 53

Chapter 29 - Hydraulic Power ........................................................................................................................ 53

Chapter 30 - Ice and Rain Protection ............................................................................................................. 54

Chapter 31 - Instruments ............................................................................................................................... 54

Chapter 32 - Landing Gear.............................................................................................................................. 55


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Chapter 33 - Lights ......................................................................................................................................... 57

Chapter 34 - Navigation ................................................................................................................................. 58

Chapter 35 - Oxygen ....................................................................................................................................... 59

Chapter 38 - Water/Waste .............................................................................................................................. 61

Chapter 49 - Airborne Auxiliary Power .......................................................................................................... 61

Chapter 51 - Structures .................................................................................................................................. 63

Chapter 52 - Doors ......................................................................................................................................... 65

Chapter 53 - Fuselage ..................................................................................................................................... 66

Chapter 55 - Stabilizers................................................................................................................................... 72

Chapter 56 - Windows .................................................................................................................................... 75

Chapter 57 - Wings ......................................................................................................................................... 75

Chapter 70 - Standard Practices Engine ......................................................................................................... 81

Chapter 71 - Power Plant - General ................................................................................................................ 81

Chapter 72 - Engine ........................................................................................................................................ 81

Chapter 73 - Engine - Fuel & Control .............................................................................................................. 81

Chapter 74 - Engine Ignition ........................................................................................................................... 81

Chapter 75 - Engine Air................................................................................................................................... 81

Chapter 76 - Engine Controls ......................................................................................................................... 81

Chapter 77 - Engine Indicating ....................................................................................................................... 82

Chapter 78 - Engine Exhaust .......................................................................................................................... 82

Chapter 79 - Engine Oil ................................................................................................................................... 84

Chapter 80 - Engine Starting .......................................................................................................................... 84

SECTION 4 – PART OF INSPECTION .................................................................................................................... 85

PART-1 MINOR INSPECTIONS ........................................................................................................................ 85

1. Pre-Flight Inspection .............................................................................................................................. 86

2. Post-Flight Inspection .......................................................................................................................... 101

3. TFE731 Engine Inspections .................................................................................................................. 113

4. APU Inspection ..................................................................................................................................... 115

5. 200 hour lubrication ............................................................................................................................ 117

6. 400 Hour Lubrication ........................................................................................................................... 118


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7. 400 Hour Detailed Walk-Around Inspection ........................................................................................ 119

PART-2 ROUTINE INSPECTIONS .................................................................................................................... 132

1. Inspection B ......................................................................................................................................... 133

2. Inspection C ......................................................................................................................................... 157

3. Inspection D ......................................................................................................................................... 178

4. Inspection E .......................................................................................................................................... 194

5. Inspection F .......................................................................................................................................... 207

6. Inspection G ......................................................................................................................................... 220

PART-3 STRUCTURAL INSPECTIONS ................................................................................................................. 226

PART-4 OUT OF PHASE INSPECTION ............................................................................................................ 251

PART-5 SPECIAL INCIDENT INSPECTION ...................................................................................................... 260

1. INSPECTIONS AFTER AN OVERWEIGHT ............................................................................................... 261

OR HEAVY LANDING ................................................................................................................................. 261

2. INSPECTIONS AFTER FLIGHT IN HEAVY TURBULENCE ......................................................................... 266

3. INSPECTIONS AFTER A LIGHTNING STRIKE .......................................................................................... 268

4. INSPECTIONS AFTER MISUSE OF REVERSE THRUST ............................................................................. 270

5. INSPECTION AFTER LANDING GEAR VIBRATION.................................................................................. 271

6. INSPECTION AFTER COLD SOAK BELOW -40 deg .C .............................................................................. 277

7. INSPECTIONS AFTER LANDING OR ABORTED TAKE-OFF IN DEEP WATER PUDDLES, SLUSH OR SNOW

................................................................................................................................................................. 278

8. INSPECTIONS AFTER EMERGENCY STOP ............................................................................................. 279

9. INSPECTIONS AFTER ABNORMAL APU CONDITIONS ........................................................................... 280

10. INSPECTIONS AFTER FLAP OVERSPEED .............................................................................................. 281

PART-6 PANEL LOCATION CHARTS .............................................................................................................. 282

PART-7 LUBRICATION .................................................................................................................................. 292

PART-8 COMPONENT REQUIREMENTS........................................................................................................ 316

H. Air Conditioning ............................................................................................................................... 317

I. Communications .............................................................................................................................. 317

J. Electrical Power ............................................................................................................................... 318

K. Equipment/Furnishings .................................................................................................................... 319

L. Fire Protection ................................................................................................................................. 319

M. Flight Controls .............................................................................................................................. 320


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N. Fuel................................................................................................................................................... 320

O. Hydraulic Power ............................................................................................................................... 320

P. Instruments ...................................................................................................................................... 320

Q. Landing Gear .................................................................................................................................... 321

R. Lights ................................................................................................................................................ 322

S. Navigation ........................................................................................................................................ 323

T. Oxygen ............................................................................................................................................. 323

U. Auxiliary Power Unit ........................................................................................................................ 323

PART-9 SUPPLEMENTAL TYPE CERTIFICATE ................................................................................................ 324

PART-10 MANDATORY LIFE LIMITATION ..................................................................................................... 328

Fire Protection ......................................................................................................................................... 334

Flight Controls .......................................................................................................................................... 335

Fuel........................................................................................................................................................... 336

Hydraulic Power ....................................................................................................................................... 337

Landing Gear ............................................................................................................................................ 338

Oxygen ..................................................................................................................................................... 342

Airborne Auxiliary Power ......................................................................................................................... 343

Fuselage ................................................................................................................................................... 344

Windows .................................................................................................................................................. 345

Wings ....................................................................................................................................................... 346

Power Plant – General ............................................................................................................................. 347

Engines ..................................................................................................................................................... 348

Appendix .................................................................................................................................................. 349


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RECORD OF REVISION

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RECORD of REVISION (ROR)

In order to keep the program update, any change required by the manufacturer, FAA, CAAT

and/or he company pertaining to this program will be revised as applicable. The revision may be

made on the effected page, partial of section or section depends on particular circumstances .

Besides, one or more section may be deleted and/or supplemented upon changing of the company

aircraft fleet.

To revise or supplement this program, the List of Effective Pages issued with each revision

and/or supplement will be changed and each page to be revised and/or supplemented will be

changed, inserted, deleted and/or supplemented as specified in the list. The Record of Revision

should then be entered by the person performing the revision and/or supplement.

Upon receiving of revision and/or supplement, change, insert, delete and/or supplement the

revision pages in the program and enter the revision number, revision date, insertion date and initial

of person incorporating the revision and/or supplement in the appropriate block.

Revision

Number

Date of

Revision Explanation of Amended or Revised

Revised By

Name Signature

0 27/02/2018 AOC Recertification Pitchayakrit


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REVISION TRANSMITTAL(RT)

Section

Remove Insert

Reason of revised Page No. Issue/Rev

No.

Page No. Issue/Rev

No.


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CONTROL DISTRIBUTION LIST

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CONTROL DISTRIBUTION LIST (CDL)

Copy No. Name Position/Location

001 Master copy for Company Document Control Center/QA office

002 Master copy for CAAT AIR,CAAT

003 Stephen Christopher Levesque Accountable Manager / General Manger

004 Palang Khamlek Head of Flight Operation

005 Teerapong Prajittanon Head of Engineer

006 Smith Pongstaporn Head of SMS and AVSEC

007 Phrompratan Sorassa Head of Training

008 Supakij Chanthasenanont Head of Quality


THIS PAGE HAS BEEN INTENTIONALLY LEFT BLANK


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GENARAL REQUIREMENTS

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SECTION 1 – GENERAL REQUIREMENTS

1.1 Company Statements

In the preparation of this Maintenance Programme to meet the requirements of AOCR and

CAAT announcement, the recommendations made by the aircraft, engine and equipment

manufacturers have been evaluated and, where appropriate, have been incorporated.

This Maintenance Schedule lists the tasks and identifies the practices and procedures, which

form the basis for the maintenance programme of the aircraft. The operator undertakes to ensure

that these aircraft will continue to be maintained in accordance with this Programme.

The data contained in this Programme will be reviewed for continued validity at least annually in

the light of operating experience.

It is accepted that this Programme does not prevent the necessity for complying with any new

or amended regulations or requirements published by CAAT from time to time where these new

or amended regulations may override elements of this Programme.

It is understood that compliance with this Programme alone does not discharge the operator

from ensuring that the Programme reflects the maintenance needs of the aircraft, such that

continuing safe operation can be assured. It is further understood that CAAT reserves the right to

suspend, vary or cancel approval of the Maintenance Programme if the CAAT has evidence that

the requirements of the Maintenance Programme are not being followed or that the required

standards of airworthiness are not being maintained.

Name: Teerapong Prajittanon Position: Head of Engineering

Signed: ........................................................ On behalf of AC Aviation Company Limited

Date: 27 - 02 - 2018


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1.2 Aircraft Application

The Hawker Beechcraft 850XP is a company aircraft manufactured by Hawker Beechcraft

Corporation (BHC), Wichita, Kansas, USA. It is under Type Certificate (TC) No. A3EU. The general

information of this aircraft is as follow.

A ) Aircraft model HAWKER 850XP

B ) Manufacture date March 2007

C ) Serial No. 258830

D ) Registration No. HS-PEK

E ) Engine Manufacture and Model Honeywell TFE731-5BR Turbofan Engine

F ) APU Manufacture and Model Honeywell GTCP36-150(W) Gas Turbine Engine

1.3 MP Owner and Maintenance Oragnization Address

Detail Owner’s address

Maintenance Organization address

NAME AC AVIATION CO., LTD. Hawker Pacific Pty.,Ltd. MRO CAAT approval No.99/2533

OFFICE ADDRESS

222 DON MUANG INTERNATIONAL AIRPORT HANGAR No.4426

VIPHAVADEE - RANGSIT Rd. SANAMBIN, DONMUANG, BANGKOK 10210

Hawker Pacific Asia Pte Ltd | 720 West Camp Road Seletar Aerospace Park, Singapore, 797520 SINGAPORE

TELEPHONE +66(0)2-504-3598 +66(0)2-504-3599 +66(0)2-504-3600 F +66(0)2-504-3597

T +65 6681 7897

F +65 6681 7874

POST ADDRESS P.O.BOX

55 DON MUANG, BANGKOK 10211

Same Office Address

E-mail [email protected] [email protected]

Website www.bangkokjets.com www.hawkerpacific.com

1.4 DOCUMENT REFERENCE 1.4.1The document reference shall include these, Name, reference, the revision number and the date

of current revision of the CAAT approved maintenance. The reference number shall print on the cover page.

1.4.2. The document reference list which revelant with Maintenance Program.

Document Name Revision Number Date (dd-mm-yy) Aircraft Flexible Maintenance Schedule Rev. 32 01/09/2016

Airworthiness Limitations Document Rev. 10 01/03/2012

Engine Maintenance Manual Rev. 4 01/01/2008


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1.5 AIRCRAFT UTILIZATION

In the preparation of this Maintenance Schedule (ACA-ENG-MP) to meet the requirements of

the AOCR and CAAT announcement, the recommendations made by the manufacturers have been

evaluated and, where appropriate, have been incorporated. It is agreed that it is a duty of the ACA

or his contracted Maintenance Organization or Fleet Technical Management Organization that

subsequent maintenance recommendations, including airworthiness information promulgated in

Maintenance Review Board Report, Maintenance Planning Document, Service Bulletins, and

Service Letters, etc., issued by the TCH, should be evaluated and, where appropriate, should be

incorporated in this Schedule by approved amendment procedures.

The periods/frequencies of the maintenance tasks in this Schedule are generally based on

an anticipated annual utilization of 225 flying hours and large variations in the annual utilization of

individual aircraft could invalidate the effectiveness of certain tasks . If the annual utilization varies by

more than 25% from that anticipated, the ACA accepts that it, or its contracted maintenance

organization, must review the maintenance tasks and periods with a view to making any necessary

adjustments.

In addition to variations in utilization, the data contained in this Schedule will be reviewed at

least annually by the ACA’s Maintenance Engineering, or its contracted Maintenance Organization,

to ensure that the detailed requirements continue to be valid in the light of operating experience .

1.6 Specific structural maintenance programs

The structural maintenance program is designed to provide timely detection and repair of

structural damage which may occur. Detection of corrosion, stress corrosion, minor accidental

damage and fatigue cracking by visual and/or NDT procedures considered. The Specific structural

are these;

a) Door

b) Fuselage

c) Nacelles/Pylons

d) Stabilizers

e) Windows

f) Wings

The Structural repair shall refer to SRM manual and SSID shall refer to Corrosion control

manual which issued by TCH.

Noted: No repeat inspection for repair assessment in SRM.


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1.7 Reliability program

Refer to ACA-ENG-GMM , Part-1, Section 1.10

1.8 ADs/SBs Assessment

AD shall refer to ACA-ENG-GMM, Part-1, Section .1.5.1.

SB shall refer to ACA-ENG-GMM, Part-1, Section .1.7.2

Noted: SBs applicable reviewed, there are not Repeat inspection item .

1.9 Repairs and Modifications

Repairs or modifications which have been carried out to the aircraft, engine, components or

radio after original manufacturer must be recorded in the appropriate maintenance log book .

Any repair, modification or STC that contains Instructions for Continued Airworthiness

(ICA’s) shall have the ICA included in this program. Scheduled Inspection Checklists and

Worksheets shall be amended to include the additional ICA instructions.

Refer to ACA-ENG-GMM, Part-1, Section .1.7.

1.10 RVSM and PBN Maintenance Procedures

1.10.1 RVSM Maintenance Procedures

Refer to Operation Manual (OM) Part-A Chapter-18 “Specifications for the Operational Flight Plan”

Topic 18.8.2 “RVSM MAINTENANCE PROCEDURES”

Topic 18.8.2.1 “Maintenance Program “

Topic 18.8.2.5 “Maintenance Training “

Topic 18.8.2.11 “Hawker 850XP RVSM MEL”


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1.10.2 PBN Maintenance Procedures

It’s defined in separate document. Refer to ACA-OPS-PBN Manual

1.11 Ageing Aircraft System

Not applicable by refer from manufacturer.

1.12 Critical Design Configuration Control Limitation (CDCCL) Not applicable by refer from manufacturer.

1.13 Aircraft Electrical Wiring Interconnect System (EWIS) Not applicable by refer from manufacturer.

1.14 Limit Of Validity (LOV) Not applicable by refer from manufacturer.

1.15 Certification Maintenance Requirements (CMR’s)

Not applicable by refer from manufacturer.

1.16 MP Amendments and Review

This Maintenance Programme must be reviewed as least annually to ensure that it stills

reflect the latest TCH maintenance publications and procedures. In case of those data were

amended during that period or modifications, STC’s or repairs having an impact on continuing

airworthiness have been incorporated, this Maintenance Programme must be revised in the

shortest delay.

1.17 Permitted Variation to Maintenance Periods –Procedure

The periods prescribed by this Schedule may be varied subject to the conditions and limits

contained in Permitted Variations to Maintenance Periods


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1.17.1 Where the manufacturer has not prescribed tolerances or permitted variations in its

maintenance schedule recommendations then the permitted variations to maintenance periods

described in sub-paragraphs 4 (a) to (e) shall apply. ACA’s Maintenance Engineering department may

vary the periods prescribed by this Schedule provided that such variations are within the limits of

the subparagraphs.

1.17.2. When the manufacturer/TCH has prescribed tolerances or permitted variations then these

will apply. The details must be specified in this Schedule. The Operator may vary the periods

prescribed by this Schedule provided that such variations are within the manufacturer's permitted

tolerances or permitted variations. Sub-paragraphs 4 (a) to (e) shall not apply to this type of variations.

1.17.3 Variations shall be permitted only when the periods prescribed by this Schedule (or

documents in support of this Schedule) cannot be complied with due to circumstances which could

not reasonably have been foreseen by the ACA.

Note-1 Permitted variations to maintenance intervals do not apply to inspections mandated by

Airworthiness Directives, Life Limited Components, Certification Maintenance Requirements, and

Airworthiness Limitations.

Note-2 Any other exceedance of defined interval is subject to CAAT approval and must be

requested in advance by use of appropriate form in order to ensure that inspections intervals will

not be overrun.

1.17.4 The decision to vary any of the prescribed periods shall be made only by the ACA or its

contracted Maintenance organization for the management of Maintenance Schedule. Particulars of

every variation so made shall be entered in the appropriate Log Book(s).

(a) Items Controlled by Flying Hours

Period Involved Maximum Variation of the Prescribed Period

(i) 5000 flying hours or less 10%

(ii) More than 5000 flying hours 500 flying hours

(b) Items Controlled by Calendar Time


(i) 1 year or less 10% or 1 month, whichever is the lesser

(ii) More than 1 year but not exceeding 3 years 10% or 2 months, whichever is the lesser

(iii) More than 3 years 3 months

(c) Items Controlled by Landing/Cycles


(i) 500 landings/cycles or less 10% or 25 landings/cycles, whichever is the lesser

(ii) More than 500 landings/cycles 10% or 500 landings/cycles, whichever is the lesser


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(d) Items Controlled by More Than One Limit.

For items controlled by more than one limit, e.g. items controlled by flying hours and calendar time

or flying hours and landings/cycles, the more restrictive limit shall be applied.

NOTES:

(1) The variations permitted above do not apply to:-

(a) Those components for which an ultimate (scrap) or retirement life has been prescribed

(e.g. primary structure of components with limited fatigue lives and high energy rotating

parts or which containment is not provided). Details concerning all items of this nature are

included in the Type Certificate Holder's documents or manuals.

(b) Those tasks included in the Maintenance Schedule, which have been classified as

mandatory by the Type Certificate Holder or the CAAT.

(c) Certification Maintenance Requirements (CMR) unless specifically approved by the

CAAT.

(2) Air Navigation ACT, CAAT Airworthiness Directive and CAAT Requirements may override

these conditions.

(3) All task variations and tolerances that be extended beyond the specified frequency will

require approval from the CAAT.

1.18 Airworthiness Limitation Items

This Airworthiness Limitations items has been compiled to collate the component lives for

HAWKER 850XP, airplanes. The component lives specified in the Aircraft Maintenance Schedules,

Aircraft Flight Manuals and US Type Certification Data Sheet have been revised and have now

been superseded by this document. In the case of engine components, reference must be made to

the appropriate engine manufacturers' documentation.

The ALI shall refer to ACA-ENG-MP Part-10.

1.19 Maintenance Certificate release to service (CRS)

Refer to ACA-ENG-GMM, Part-1 Continuing Airworthiness Procedure, Section 1.3.1.5

“Maintenance Certification.

1.20 CAAT Maintenance requirements

ACA ‘s Maintenance Engineer department shall strictly control and maintenance these items which

they are required by CAAT following these below table;


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Items Period Remark

Main battery 6 months interval Ref. CMM P/N: F2602-0057

Emergency pack Refer to task no. 250005 ,Part-2 Inspection E6 Ref. Docs : ACA-ENG-MP

Emergency escape provision

Emergency Exits/Hatches

Refer to task no. 520009 Escape Hatches, Part-3

Structural Inspection

Ref. Docs : ACA-ENG-MP

Flexible hoses Refer to Section 3, Part 1 400 Hours Detailed

Walk Around Inspection Ref. Docs : ACA-ENG-MP

Oxygen cylinder Refer to task no.350008, Section 3, Part-2

Inspection C7


Seatbelts and Harness Refer to Section 3, Part-1 400 Hours Detailed

Walk Around Inspection


Weight and Balance

Swing Compass

ATC Transponder function test

Every 60 months interval



Ref.Thai AD 133/2538

Special operation

AWO N/A

RVSM

Refer to Task no. 340013, Section 2 ,Chapter 34 Ref. Doc : ACA-ENG-MP

Refer to OM Part-A, Chapter-18, Section 18.8.2.1 Ref. Doc:ACA-OPS-OMA

ETOPS N/A

MNPS N/A

PBN N/A

Engine EHM 30 days interval

Refer to Section 3 Part of Inspection, Part-1

TFE731 Engine Inspections

Ref. Doc : ACA-ENG-MP

AD repeat inspection

FAA-2000-15-09

FAA-2016-07-02

FAA-74-08-09 R3

HPC Impeller inspection every 1,000 Hrs

Turbine transition duct every 2,600 Hrs.

Air Transport Association (ATA) of America Code

25: Equipment/furnishings repeat every 1,000 Hrs.

Ref: Doc: AD 2000-15-09

Ref: Doc: AD 2016-07-02

Ref: Doc: AD 74-08-09 R3

CVR/FDR -Check CVR/FDR prior to the first flight of the day.

-Calibration of the FDR system refer to Section1.8

-Clean/Test CVR/FDR every 24 months interval

-Replace battery of CVR/FDR every 72 months

interval.

Ref. Docs: ADCA(Issue 2)

Ref. Doc : ACA-ENG-MP

Ref. Docs: Technical Manual

Underwater Acoustic

Beacon Models DK120

Mode-S Transponder Refer to TCH MM-34-43-64 AMMA rev.20

In-Flight Entertainment system Refer to Section 3, Part-9, ST09986SC Ref. Docs: ACA-ENG-MP

Note: APUs controlled by a fixed Hot Section Inspection and Overhaul Life, no entry is required.


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1.21 CVR/FDR Download Procedures

AC Aviation determined the CVR/FDR data download by carry out to Contracted

Maintenance. The interval time of data download is 12 months Downloaded data shall keep in

electronic device such as DVD/Server computer at Operation office.

A flight recorder system shall be considered unserviceable if there is a significant period of

poor quality data, unintelligible signals, or if one or more of the mandatory parameters is not

recorded correctly. The criteria to judgement the equipment inoperative is 95% of parameters that

necessary to be recorded in flight recorder

system are listed (refer to ADCA for the Air Navigation by Aeroplane of AOC holders)

1.22 Calibration of the FDR system

Calibration of the FDR system shall be:

8.1 For those parameters which have sensors dedicated only to the FDR and are not

checked by other means, recalibration shall be carried out at least every 5 years .

8.2 When the parameters of altitude and airspeed are provided by sensors that are

dedicated to the FDR system, there shall be a recalibration performed as at least every 2 years.

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MP INTRODUCTION

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SECTION 2 – MP INTRODUCTION

1.0 Information

Note: Throughout this Aircraft Flexible Maintenance Schedule where Hawker 800XP is referenced,

the designation of Hawker 850XP equally applies.

Note: The airplane illustrations throughout this Aircraft Flexible Maintenance Schedule may

appear without winglets. These illustrations also apply to airplanes equipped with winglets,

even though the winglets are not shown.

A. General

It shall be the responsibility of AC AVIATION company to ensure that the latest revision of the

publications referenced in this schedule are utilized during operation, servicing and maintenance of

the airplane.

B. Warnings, Cautions and Notes

WARNING - Brings attention to an operating procedure, inspection or maintenance practice, which

if not correctly followed, could result in personal injury or loss of life.

CAUTION - Brings attention to an operating procedure, inspection, repair or maintenance condition,

which if not strictly observed, could result in damage or destruction of equipment .

NOTE - Brings attention to an operating procedure, inspection, repair or maintenance condition,

which is essential to highlight.

C. Special Conditions Cautionary Notice

Airplanes operated for Air Taxi, or other than normal operation, and airplanes operated in humid

tropics, cold and damp climates, etc., may need more frequent inspections for wear, corrosion

and/or lack of lubrication. Under these adverse conditions, perform periodic inspections in

compliance with this guide at more frequent intervals until the owner or operator can set his own

inspection periods based on the contingencies of field experience.

Caution: The recommended periods do not constitute a guarantee the item will reach the period

without malfunction as the aforementioned factors cannot be controlled by the

manufacturer.


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D. .Schedule Layout

Title page

A Title page is located at the beginning of the schedule and provides the part number of the

schedule, and instruction data. Information throughout this schedule is applicable to all models listed

on the title page except where specifically stated.

The printed schedule will have a Record of Revisions page. The Record of Revisions is provided

following the Current LOEP List. When a revision is inserted, the revision number, the date the

revision is inserted into the schedule, and the initials of the person(s) inserting the revision should be

recorded on this page and in the Section 0 (Record Of Revision )

ATA Task Codes

This section lists the individual tasks contained in the schedule in ATA order .

E. How To Use The Schedule

The intent of this Maintenance Program is to provide AC AVIATION Company with the option of

selecting the maintenance plan best suited to their own flying schedule. The charts shown in Figure

1 and Figure 2 are used in selecting the inspection method chosen.

Note: For composition of schedules and breakdown refer to paragraphs 3 and 4.

It is the responsibility of AC AVIATION Company, those subsequent maintenance

recommendations, including airworthiness information promulgated in Service Bulletins, Service

Letters, etc., issued by the constructors and vendors should be evaluated and, where appropriate,

should be incorporated in this Schedule by the approved amendment procedures .

The requirements of this Schedule shall normally be implemented at or before the periods specified.

Extensions to prescribed periods are subject to agreement with the CAAT and should be made only

when the periods cannot be complied with due to circumstances which could not have been

reasonably foreseen by AC AVIATION Company or by AC AVIATION Company’ contracted

Maintenance Organization.


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Maintenance Start Data

All the tasks in the Out of Phase, Component Requirements and Airworthiness Limitations

Document (ALD) are calculated as starting from the date of original certification (issuance of original

standard airworthiness certificate) or from component installation during completion. CAAT or

applicable regulatory required inspections and maintenance must be done in accordance with

specific regulatory requirements. All Hawker Beechcraft Corporation recommended inspections,

maintenance and servicing shall be based on the date of release for service following aircraft

completion. These statements are not applicable to the airplane engines or the APU, which must be

maintained in accordance with their own manufacturers, recommended or required maintenance

instructions.

The airplane must be maintained in accordance with the Maintenance Schedule based on original

certification during completion. Both a 400 hour Detailed Walk-Around Inspection and 12 month (E

Inspection) are required at the time of completion if the difference between the date of original

certification and completion is more than six months or if the airplane has more than 50 hours total

flight time.

Any variation to the inspection must be approved by CAAT

Note: The requirements referred to in this Maintenance Schedule are applicable to equipment

installed to Hawker Beechcraft Corporation and Hawker Beechcraft Corporation Completion

Center approved modifications. For airplanes with equipment installed to any other FAA

approved modifications refer, to that particular Design Authority responsible for the

installation. Refer to the relevant Vendor Publication for any Servicing/Maintenance

instructions which are not specifically defined in this schedule.

Factory Aircraft Comprehensive Tracking System (FACTS) program is the factory authorized

computerized maintenance tracking and forecasting system that adheres to the guideline

established in this maintenance schedule.


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2.0 Periods and Tolerances

A. General Instructions

(1) Flying Times

All periods quoted in the Schedule in 'flying hours' are based on flight (take-off to touch-down) times.

Where, due to airport congestion, block (chock-to-chock) times exceed flight times by an average of

more than 20 per cent, corresponding adjustments should be made to the overhaul periods of

selected components such as starter/generators, hydraulic pumps and cut-out valves.

(2) Fatigue Lives and Mandatory Limitations

ALL registered airplanes must comply with the requirements of CAAT.All other life limitations

classified as mandatory by the constructor/manufacturer must also be observed unless varied by

CAAT.

The Structural Inspection frequencies quoted in this Schedule are based on a set of assumed

typical operating conditions. These assumptions take into account the experience obtained in

service with the earlier variants of airplanes together with the enhanced capabilities of the Hawker

800XP Aircraft.

The projected utilization has been described in the form of Flight Plans or Mission Profiles; whilst

these have been invested with a degree of conservatism it is not possible for AC AVIATION

Company to make sure that they will cover every airplane in service.

Should the actual utilization differ significantly from the assumed mission profiles then due

allowance must be made for the effects on the structural damage tolerance and fatigue

characteristics and, hence, the inspection and replacement schedules.

For the purposes of compiling the Structural Inspection frequencies the typical mission profiles

allow for:

One cabin pressurization to full differential (8.55 psi).

One full cycle of flap operation (take-off and landing).

One full undercarriage cycle including braked, full stop landing per flight where a flight is defined as

a single completed take-off and landing sequence. Touch and go landings, or rollers, are considered

to be equivalent to full stop landings for maintenance purposes.


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It is also assumed that the majority of flights are at altitudes of 25,000 feet and above using

normal climb and descent procedures, with an allowance for flights at lower altitudes.

The rate of fatigue damage to the structure could be greater than predicted for the assumed

typical utilization if more than 30% of the flights involve cruises at altitudes below 15,000 feet

or if less than 70% of the flights involve cruises at or above 25,000 feet.

The assumed typical block time for average flights is 1.5 hours. Fatigue damage per flight

could be increased if on average, more than 70% of flights are of a longer duration.

If AC AVIATION Company finds that the utilization of their aircraft differ from the average

conditions outlined above should contact Hawker Beechcraft Corporation for guidance.

In order to fully describe AC AVIATION Company particular usage of our airplane the

following information is required:

(a) Stage length and block time

(b) Climb time and speed

(c) Cruise time, altitude and speed

(d) Descent time and speed

(e) Stand-off time, altitude and speed

(f) Number of pressurizations and differential

(g) Number of flap operation cycles

(h) Number of undercarriage operation cycles

(i) Number of missed approaches

(j) Number of touch-and-go landings (rollers)

(k) Taxi time (pre- and post-flight)

(l) Typical zero fuel weight

(m) Typical landing weight

(n) Percentage of total flights flown to this mission profile.

Note: If the airplane carries out widely differing types of operation these should be divided into

groups of similar profiles each of which require the above data.

Other general information to be advised as follows:

(o) Airplane registration

(p) Airplane serial number

(q) Airplane series

(r) Total flying hours and landings (including touch-and-go landings)


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(s) Hours and landings flown in the described flight profile(s)

(t) Geographical disposition of operations .

(3) Overhaul Periods - Radio and Radar Equipment

Subject to negotiation with the CAAT, radio and radar equipment listed in the servicing of this

Maintenance Schedule may be maintained on an "On Condition" basis.

(4) Date Marking of Equipment

Equipment which is required to be date marked after inspection or re-test to comply with this

Schedule, should be re-marked with the date at which the next inspection or test is due.

B. Tolerances Each inspection has a period for accomplishment, that period is the tolerance window. A tolerance

window is defined as the period that an inspection may be accomplished, and does not change the

next due time. The tolerance window for each inspection is specified in paragraph 4.A.

However AC AVIATION Company will never use these Tolerances unless otherwise approved by

CAAT in the time-by-time of inspections.

3.0 Composition of Schedule and Task Numbering

A. Composition of Schedule The Schedule is composed of nine parts, namely:

Part 1...Minor inspections (Pre-Flight, Post Flight, 200 and 400 Hour Lubrication and 400 Hour

Detailed Walk-Around Inspection).

Note: Pre-Flight and Post Flight inspections are covered in the Hawker 800XP Ground Handling

Checklist P/N 140-590032-0025.

Note: Reference is also made in Part 1 to Engine, APU, Thrust Reverser and Airbrake Selector

Lever Baulk Inspections.

Part 2...Routine Inspections (Inspection "B", Inspection "C", Inspection "D", Inspection "E", Inspection

"F" and Inspection "G").

Part 3...Structural Inspections.

Part 4...Out of Phase Inspections.

Part 5...Special Incident Inspections.

Part 6...Panel Location Charts.

Part 7...Lubrication.


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Part 8...Component Requirements.

Part 9...Mandatory Life Limitations.

B. Task Numbering

Each individual task within parts 1, 2, 3 and 4 has its own unique task number, consisting of six

digits. The first two digits relate directly to the ATA chapter number and the last four digits relate to

the task, e.g. 270025 is the 25th task in Chapter 27, Flight Controls.

For recording requirements each minor and routine inspection period has a unique ATA Chapter 05

code number

Area inspections within the routine inspections are also given a unique code number . These are

05**** numbers and will follow the unique number allocated to the inspection, e.g. the inspection

number for Inspection B3 is 050140, therefore the area inspection number will be 050141 .

The first page of each group of routine inspections consists of the following:

The relevant inspection title (e.g. Inspection "B3")

The unique code number mentioned above (e.g. 050140)

List of Effective Pages

Instructional Data Block

Completion of Inspection Block

4.0 Inspection Periods Note: If an inspection is done within the tolerance window, the time when the inspection is next

due is not changed.

Note: Minor Inspections that are divided into individual task codes so they can be used for

scheduling and tracking, can be phased similar to Part 2. Routine Inspections, providing

each task does not exceed the inspection period or tolerance window, (Example: If Item J.

Rear Equipment Bay inspection in the 400 Hour Detailed Walk-Around has a task code

assigned then the entire "Item J" could be scheduled and completed at the same time as

"Inspection B7 - Rear Equipment Bay and Rear Fuselage inspection").


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A. General Firstly AC AVIATION Company Limited have chosen to complied with the un-phased

inspection method and may be change to the Phased formatting in the future for fit with the

Aircraft fleet mission.

200 Hour lubrication - 200 flying hour interval with 50 flying hour tolerance window (191 to 240).

400 Hour lubrication - 400 flying hour interval with 50 flying hour tolerance window (391 to 440).

400 Hour Detailed Walk-Around inspection has a 400 flying hour interval with a 50 flying hour

tolerance window (391 to 440).

Airbrake Selector Lever Baulk inspection has a 400 flying hour interval with a 50 flying hour

tolerance window (391 to 440).

When an inspection group is not phased:

Inspection group "B" has a 800 flying hour interval with a 50 flying hour tolerance window (791 to

840).

Inspection group "C" has a 1600 flying hour interval with a 100 flying hour tolerance window (1551

to 1650).

Inspection group "D" has a 3200 flying hour interval with a 200 flying hour tolerance window (3151

to 3350).

Inspection group "E" has a 12 month interval with a 1 calendar month tolerance window (11 month

to 13 month).

Inspection group "F" has a 24 month interval with a 2 calendar month tolerance window (22 month

to 26 month).

Inspection "G" has a 48 month interval with a 2 calendar month tolerance window (46 month to 50

month).

When a task or inspection item in an inspection is started, the airplane MUST NOT be flown until

the task or inspection item is completed and the aircraft has been approved for return to service in

accordance with the requirements of the CAAT.

Note: Assure that the task or inspection item performed is signed off in such a manner that

clearly indicates when the inspection tasks are completed.


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▪ Multiple inspections (e.g. B1 through B12) may be accomplished within the same tolerance

window, however each inspection is individually tracked.

▪ Each inspection remains current, when completed, until, at a maximum, the last day or flying

hour of the next allocated period for the identical inspection.

▪ Never exceed the allowed inspection window for a task when changing formats from phased

to un-phased; or from un-phased to phased.

B. There is no Inspection group A, instead, there is a 400 Hour Detailed Walk-

Around inspection.

C. The breakdown of Inspection groups "B", "C", "D", "E" and "F" and the

areas dealt with in the inspections are listed below .

Associated area/function on airplane

B1 C1 D1 E1 F1 Functional tests 1

B2 C2 D2 E2 F2 Functional tests 2

B3 C3 D3 E3 F3 Area F1 & Lubrication


B5 C5 D5 E5 F5 Area F3 (under floor) & Lubrication

B6 C6 D6 E6 F6 Area F3 (above floor) & Lubrication


B8 C8 D8 E8 F8 Area T1 & Lubrication

B9 C9 D9 E9 F9 Area W1 & Lubrication

B10 C10 D10 E10 F10 Area W2 & Lubrication

B11 C11 D11 E11 F11 Area M1/M2 & Lubrication

B12 C12 D12 E12 F12 Area G & Lubrication

Inspection title

D. Flexible Maintenance Charts (Figure 1. and Figure 2).

The charts layout the inspections in hours (Figure 1) and months (Figure 2) with 12 columns for

Inspection groups "B", "C", "D", "E" and "F". Inspection "G" only has one column. For the conventional

inspection method an X would be placed in each column at the interval for that inspection, refer to


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Introduction - Appendix Chart 1 (Sheets 1 and 2) for example. This would be done for each of the six

inspections, B through G.

The flexible or progressive inspection method uses the same charts with X's placed in each column

at the time selected. The X represents that time when each inspection would be done. Appendix

Chart 2 (Sheets 1 to 4) show one example of this method.

Note: The charts are designed to provide maximum flexibility such as doing any individual B

through F inspection in a packaged method, while doing other inspections at one time.

An example of this would be to do Inspection groups B and C in packages and all other

inspections at one time.

Note: The appendix charts are provided as examples of the most commonly used inspection

methods.

E. The inspections contained in the Schedule are to be completed in

accordance with the following instructions

TFE-731-5BR or TFE731-50R

Inspections

To be completed at periods not exceeding the appropriate engine running hour times

as detailed in the engine manufacturers maintenance instructions.

A.P.U.To be completed at periods not exceeding the appropriate APU running hour times

as detailed in the APU manufacturers maintenance instructions.

200 Hour lubrication To be completed every 200 Hours in accordance with Paragraph 4.A.

400 Hour lubrication To be completed every 400 Hours in accordance with Paragraph 4.A.

400 Hour Detailed Walk-Around

Inspection.To be completed every 400 Hours in accordance with Paragraph 4.A.

Inspection groups B, C, D, E and F To be completed in accordance with Paragraph 4.A.

Inspection G (48 months) To be completed at the time period specified.

Structural Inspections To be completed at the periods specified.

Out of Phase Inspections To be completed at the periods specified.

Special Incident Inspections To be completed as and when necessary.


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F. Sign Off Requirements Note: The sign off requirements are based upon the method of scheduled maintenance

accomplishment.

When an inspection group is NOT phased.

Each inspection must be accomplished, but only the top level form requires completion.

No inspection sign off is required.

When an inspection group is phased.

Each inspection must be signed off as a top-level inspection. Each inspection is then tracked

with the appropriate interval.

No overall top level sign off is required.

5.0 Continued Airworthiness Requirements

AC AVIATION Company should institute a system for the assessment of continuing airworthiness

information. This information will originate from the Responsible Authority of the State of

Manufacture in the form of Airworthiness Directives (or documents of comparable intent) and from

the constructor/manufacturer in the form of Service Bulletins, Letters, Safety Communiques,

Information Leaflets etc. resulting from In-Service experience.

AC AVIATION Company should add items to this Schedule to cover their special installations or

equipment, and to make provision for any regulation, national or local, in force at the time.

Nothing in this Schedule is to be construed as absolving persons employed in the implementation

of the requirements of this Schedule from making sure that the airplane is, at all times, maintained

in an airworthy condition. Any damage or defect affecting the safety of the airplane must be rectified

before the airplane flies again.


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Compliance with the mandatory requirements of the Responsible Authority of the country of origin

must be achieved. When referring to all parts within the Schedule the Operator should use only

those items relevant to his own airplane and disregard all other items .

Continuing Airworthiness and other Service Information must be continuously evaluated AC

AVIATION Company or his contracted maintenance organization and, where necessary,

appropriate action must be taken to amend the Maintenance Schedule .

A. At each periodic inspection the depth of inspection must:

(1) Be of a degree sufficient to make sure that the items to be inspected will remain serviceable until

the next higher period for inspection becomes due.

(2) Make sure that at the time of the inspection items are free from any defects likely to affect

airworthiness. The inspections made to assure this must comply with the minimum standards set

out hereunder, having regard to the material from which the item is made and applying the

appropriate standards wherever possible.

Note: In general, when dismantling and access is known to be required by this Schedule, this is

stated against the item concerned.

Note: Due to different equipment fits between airplanes and in order to achieve a satisfactory

exposure of the area/item to be inspected, it may be necessary to displace/remove other

items, (e.g. electrical cables, piping, fittings etc.) which are not stated in the Schedule.

Note: Access requirements quoted are minimum requirements and further dismantling of an item,

group or assembly may be considered essential by the Chief Inspector or a Licensed

Aircraft Maintenance Engineer in order to assure airworthiness.

Note: Structure is to be sufficiently clean to enable an effective inspection to be done.


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B. A series of standard terms are used throughout the schedule to

indicate the inspection requirements.

Their interpretations are as follows:

(1) Area Inspection... A visual inspection of the area using the inspection criteria as detailed in

paragraph 6.C. for all items of equipment in the area relating to the trade disciplines listed and

access quoted. The depth of the area inspection is determined by the degree of access specified for

the particular inspection period and the structure rendered visible at that time.

(2) Satisfactory Condition... A general visual inspection for signs of damage, cleanliness, security of

attachment and visible connections, locking and bonding .

(3) Detail Inspect... An intensive visual examination of a specific structural area, system, installation or

assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a

direct source of good lighting at intensity deemed appropriate by the inspector . Inspection aids such

as a mirror, magnifying lenses, etc. or an approved NDT technique may be used. A 10X Lighted

Magnifier should be used to inspect all instances of suspected wire damage. All wire related

conditions should be reported using the ATA spec 100, code 97-xx-xx format. Surface cleaning and

elaborate access procedures may be required.

(4) Check... Make a comparison of a measurement of time, pressure, temperature, resistance,

dimension or quantity with a known figure for that measurement.

(5) Test... The component to be tested may be removed from the airplane or checked in situ. All the work

is to be done in accordance with the data contained in the relevant Vendor Maintenance Manual .

(6) Functional Test... Make sure, by use of test equipment if necessary, that a complete system

functions correctly.

(7) Operational Test... Make sure, by use of test equipment if necessary, that a component within a

system OR part of a system operates correctly.

(8) Detailed Walk-Around Inspection... This inspection is to be a thorough visual inspection of the

airplane which does not require removal of access panels, use of specialized tools or equipment.

Lighting and cleanliness is to be adequate to detect damage, failure or irregularity . Suspect

conditions requiring additional investigation is to be treated as defined in "Detail Inspect"

(Ref. Paragraph (4)).


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C. The inspection criteria

(1) Metal parts: e.g. applicable to all metal parts, bodies or casings of units in systems and in electrical,

instrument and radio installations, metal pipes, ducting, tubes, rods, levers.

(a) Inspect for:

Cleanliness, external signs of damage, leaks, overheating or discharge. Fluid ingress. Obstruction

of drainage or vent holes or overflow pipe orifices. Correct seating and sealing of fairings and

serviceability of fasteners. Security of attachment, fasteners, connections, locking and bonding.

(b) Freedom from:

Distortion, dents, scores, chafing, pulled or missing fasteners, rivets, bolts, screws . Signs of

cracks and wear. Separation of bond. Failure of welds and spot welds. Deterioration of protective

treatment, and signs of corrosion.

(2) Rubber, Fabric, Fibre Glass and Plastic Parts e.g. coverings, ducting, flexible pipes, flexible

mountings, seals, heater muffs, windows etc.:

(a) Inspect for:

Cleanliness, cracks, cuts, chafing, kinking, twisting, crushing, contraction - sufficient free length.

Deterioration. Crazing. Loss of flexibility (other than fabric covered component), overheating. Fluid

soakage.

Security of attachment (supports, packing and electrical bonding correctly positioned, serviceable

and secure) connections and locking.

(3) Control system components:

(a) Inspect for:

Correct alignment - no fouling. Free movement. Distortion. Signs of bowing. Scores. Chafing.

Fraying. Kinking. Signs of wear. Flattening. Cracks. Loose rivets. Deterioration of protective

treatment and signs of corrosion. Electrical bonding correctly positioned, undamaged and secure.

Attachments, end connections and locking secure.

Note: Free movement should be established at extreme ranges of travel with full trim applied.

Note: Full travel of the rudder circuit should be confirmed with the pedals at the full forward and

full aft adjustment positions.


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(4) Electrical Motors, Alternators, Generators and Actuators:

(a) Inspect for:

Cleanliness, obvious damage, signs of overheating, signs of corrosion and security of

attachments and connections. If protective covers are required to be removed: cleanliness,

scoring, pitting, brushes free in holders, not excessively worn and correct bedding. Adequate

spring tension. Overheating. Fluid ingress.

(5) Relays, Solenoids and Contactors:

Inspect for:

Cleanliness, obvious damage, signs of overheating, signs of corrosion and security of attachments

and connections. If protective covers are required to be removed: cleanliness, pitting or burning of

contacts, signs of overheating and security of contacts exposed.

(6) Markings, notices, frequency charts, compass corrector cards, warning and caution labels,

placards:

(a) Inspect for:

Legibility and security of attachment.

Note: Any other inspection or work requirement not covered by the above standards is specifically

written into the Schedule.

(7) Electrical Wiring, Cables and Looms:

(a) Detail Inspect for:

Criteria contained in AMM 125/H-20 Chapter 20 - Standard Practices - Airframe, 20-10-50, Wiring

Procedures and Repair.


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(8) Structural Inspection

(a) Detail inspect lap joints, butt straps, stringers, frames, bulkheads, ribs, longerons and

skins for:

Lack of adhesion of the paint or sealant. This could indicate the presence of surface corrosion

under the paint film or sealant.

Bubbles or eruption of the paint film or sealant. This condition could indicate local pockets of

corrosion and it is important to ascertain, beyond reasonable doubt, that any bubble or eruption

found is a build up of paint or sealant and not a build up of corrosion product . If any doubt exists

the bubble or eruption should be broken, the area cleaned up and, if satisfactory, the treatment

restored.

Signs of corrosion on the edge of any member where it joins the skin . If corrosion is found the

suspect area of the joint must be cleaned of all paint. Where corrosion is confirmed and it

penetrates between the faying surfaces of the joint, the affected area must be visually examined

by removing bolts or rivets to check the extent of corrosion and to assist in repair .

Any signs of possible cracking or corrosion is to be stripped of paint and inspected further using

dye penetrant.

(b) Non Destructive Testing (NDT).

Where it is considered that a visual inspection is not possible due to the nature of the structure, or

an excessive amount of dismantling would be necessary, examination by X-ray or other methods of

non-destructive testing in accordance with the approved techniques is used as the inspection

medium. The techniques are contained within the Non-destructive Testing Manual.

D. Maintenance Practices and Procedures Practices and procedures necessary to complete the requirements of this Maintenance Schedule or

work resulting from its application should be, as a minimum, to the standard recommended in:

(1) The relevant Maintenance, TCH Overhaul and TCH Repair Manuals.

(2) The requirements of the Airworthiness Authority.


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E. All Vital Points and Control Systems Whenever inspections are made or work is undertaken on vital points, flying or engine control

systems, a detailed investigation must be made on completion of the task to make sure that all

tools, rags or any other loose articles which could impede the free movement and safe operation of

the system(s) have been removed, and that the systems and installation in the work area are clean

and unobstructed.

If, as a result of the application of this Schedule, any part of either the main or any associated

system is dismantled, adjusted, repaired or renewed, that part of the system (s) which has been

disturbed shall be subjected to a duplicate inspection, with free movement, range, direction and

tension checks and shall be certified in accordance with the requirements of CAAT.

F. Wear Limits on All Flying Control and Engine Control Cables Whenever flying control or engine control cables are required to be inspected in accordance with

this Maintenance Schedule, the following wear limits apply:

(1) Significant wear on outer wires but obviously less than 50% of individual wire cross section and with

individual wires clearly separated can be considered as acceptable.

(2) Wear on outer wires at 50% or more, usually indicated by difficulty in distinguishing individual wires,

and wear area embracing 6 consecutive wires, raise and carry forward for repeat inspection at not

more than 300 flying hour periods.

(3) Wear on outer wires at 50% or more and not more than 3 broken wires at any wear position - change

within 30 flying hours.

(4) Wear or damage in excess of para. (3) - change cable.

(5) Where the possibility of failed wires bunching around pulleys etc . can occur, the cable must be

changed, irrespective of the extent of any other damage.

(6) On sleeved cables, up to 50% wear of the sleeve thickness is acceptable. To clarify a difference in

terminology, "Swaged tubes" and "Sleeved cables" are physically the same thing.


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G. Fuel System Contamination Checks If, as a result of the application of this Maintenance Schedule any part of the system is dismantled,

adjusted, modified, repaired or renewed, the systems shall, after completion of the work, be tested

to establish the correct operation of the system .

The following checks must be made to establish that the fuel systems are free from contamination .

(1) Fuel system water drain checks are to be performed at periods not exceeding 24 hours elapsed

time.

(2) AC AVIATION Company must be satisfied with the quality of all fuel taken on board his airplane,

especially in respect of contamination with water, and monitor the suppliers quality performance.

H. Portable Valise Type Life rafts At the appropriate Overhaul period ten percent of all life rafts installed in fleets using a system

bottle and release mechanism are to be inflated and tested. Make sure that deployment and inflation

is satisfactory.

6.0 Schedule Format

A. Minor and Routine Inspections The requirements of the Minor and Routine Inspections are divided into airplane areas, system and

component requirements:

(1) Area Inspections

The area inspections require a visual inspection of the area using the inspection criteria as detailed

in paragraph 6.C. for all items of equipment in the area relating to the trade disciplines listed and

access quoted. The depth of the area inspection is determined by the degree of access specified for

the particular inspection period and the structure rendered visible at that time.

(2) System and Components Requirements.

These sub-sections give the inspection and servicing requirements of specific systems and

components at the inspection period under consideration . The requirements are laid out in ATA 100-

chapter order.


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System functional tests are given at the beginning of each Inspection and are presented in ATA

100-chapter order. When a requirement in this Schedule refers to an AMM sub-paragraph or specific

step(s) then all relevant warnings, cautions and preparatory procedures must be observed.

Overhaul periods, servicing and bench tests for non-RAC manufactured components are governed

by the maintenance manuals of the respective manufacturers. Where possible, to aid Operators with

their inspection of these components, the Aircraft Maintenance Manual is used as a reference for

removal and installation.

B. Structural Inspections The Structural Inspections are also divided into airplane areas, with each area containing the

inspection requirements and "Not exceed" periods for specific structural parts. The degree of access

required is stipulated for each inspection requirement.

C. Out of Phase Inspections

The Out of Phase Inspections are presented in ATA 100 chapter order . The "Not exceed" period for

the inspection(s) are stated in the individual tasks.

D. Special Incident Inspections

This Part contains the special inspections considered necessary if the airplane has been subjected

to abnormal stresses or climatic conditions in flight, or during landing .

E. Panel Location Charts

The charts contained within this Part illustrate the location of panels which may be required to be

removed or opened during airplane servicing.

F. Lubrication

Details of routine lubrication and types of lubricants used are detailed in the text and illustrations

contained within this Part. The AMM references of the lubricants used for general lubrication,

together with a system of codes denoting lubrication periods, are tabulated in the Introduction at the

beginning of the Part. The AMM references of special purpose lubricants used for specific

applications are included in the relevant text and illustrations .


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G. Component Requirements

Listed within this part are components or assemblies which are subject to hard-time overhaul

periods, bench tests or replacement out of phase with the airplane servicing periods. The

consolidated list is given under system headings in ATA 100-chapter order, and includes Part Nos.

and the names of the manufacturers.

Where the part number of a component is followed by an asterisk(s) (e.g. 42022-**) this indicates that

the requirement is applicable to all variants.

7.0 Abbreviations, Terms and Definitions

All significant terms and abbreviations used within the Schedule are defined below or, in the

absence of formal definitions; those quoted in the World Airlines Technical Operations Glossary are

used.

AMM Aircraft Maintenance Manual.

B/Chk Bench check.

CMM Component Maintenance Manual.

DTD Directorate of Technical Development (UK) specification.

ICAO International Civil Aviation Organization.

ISB Inspection Service Bulletin.

LMM Light Maintenance Manual.

MM Maintenance Manual.

MIL Military (ICAO, US) specification.

NDT Non-destructive Test.

O/H Overhaul.

Repl. Replace.

SB Service Bulletin.

AD Airworthiness Directive

CAAT Civil Aviation Authority Of Thailand

DCA Department Of Civil Aviation


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8.0 Additional Requirements Introduced by Revision Action

Unless otherwise directed by the relevant Letter of Transmittal, or Service Bulletin action, additional

requirements introduced into the Schedule need not be added into an airplanes existing cycle of

maintenance until the next period at which the requirement becomes due.

A. Chart 1 (Figure 1, Sheets 1 and 2)

This chart shows conventional servicing when ALL of the Inspection requirements are done at one

time, e.g.

▪ Inspection B (B1 to B12 inclusive) done at 800 Hour, 1600 Hour, 2400 Hour Etc.

▪ Inspection C (C1 to C12 inclusive) done at 1600 Hour, 3200 Hour, 4800 Hour Etc.

▪ Inspection D (D1 to D12 inclusive) done at 3200 Hour, 6400 Hour, 9600 Hour Etc.

▪ Inspection E (E1 to E12 inclusive) done at 12 Months, 24 Months, 36 months, 48 Months Etc.

▪ Inspection F (F1 to F12 inclusive) done at 24 Months, 48 Months Etc.

B. Chart 2 (Figure 2, Sheets 1, 2, 3, and 4)

This chart shows one suggested flexible method of staggering the sub-inspections.


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Flexible Maintenance Chart – Conventional Servicing (Hours)

Figure 1, Sheet 1


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Flexible Maintenance Chart – Conventional Servicing (Months)

Figure 1, Sheet 2


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Flexible Maintenance Chart – Flexible Servicing (Hours)

Figure 2, Sheet 1


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Flexible Maintenance Chart – Flexible Servicing (Hours)

Figure 2, Sheet 2


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Flexible Maintenance Chart – Flexible Servicing (Months)

Figure 2, Sheet 3


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Flexible Maintenance Chart – Flexible Servicing (Months)

Figure 2, Sheet 4


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SECTION 3 - ATA TASK CODES ATA

Task

Code

Description

Inspection

Chapter 05 - Time Limits/Maintenance Checks

NOTE The majority of Chapter 05 numbers are allocated for Inspection numbers and Area Inspections. As these

are not specific to any airplane system the numbers have not been listed. Chapter 05 numbers allocated to specific tasks/inspections are listed.

050772

B. Left Nose and Fuselage.

400 Hour Walk-Around

Inspection

050773

C. Nose Landing Gear Bay. 400 Hour Walk-Around

Inspection

050774

D. Right Nose and Fuselage.


Inspection

050775

E. Right Wing.


Inspection

050776

F. Right Main Landing Gear.


Inspection

050777

G. Right Engine and Nacelle.


Inspection

050778

H. Aft Fuselage - Right Side.


Inspection

050779

I. Empennage (Tail Section).


Inspection

050780

J. External Baggage Unit (750 Airplanes) - Task transferred to 050779.


Inspection

050781

K. Aft Fuselage - Left Side.


Inspection

050782

L. Rear Equipment Bay.


Inspection

050783

M. Left Engine and Nacelle.


Inspection

050784

N. Left Main Landing Gear and Center Keel.


Inspection

050785

O. Left Wing.



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Inspection

050786

P. Flight Compartment.


Inspection

050787

Q. Vestibule, Passenger Cabin and Toilet Compartment.


Inspection

050788

R. Final Items.


Inspection

Chapter 12 - Servicing

120001 Do any 200 hour lubrication requirements for ALL Area's, refer to Part 7 - Lubrication. 200 Hour

Lubrication

120003 Do any 400 hour lubrication requirements for Area F1, refer to Part 7 - Lubrication. 400 Hour

Lubrication

120004 Do any 400 hour lubrication requirements for Area T1, refer to Part 7 - Lubrication. 400 Hour

Lubrication

120007 Do any 400 hour lubrication requirements for Area W1/W2, refer to Part 7 -

LUBRICATION.

400 Hour

Lubrication

120012 Do any 800 hour lubrication requirements for Area F3, refer to Part 7 - LUBRICATION. B6

120013 Do any 800 hour lubrication requirements for Area F4, refer to Part 7 - LUBRICATION. B7

120015 Do any 800 hour lubrication requirements for Area W1, refer to Part 7 - LUBRICATION. B9

120016 Do any 800 hour lubrication requirements for Area W2, refer to Part 7 - LUBRICATION. B10

120018 Do any 800 hour lubrication requirements for Area G, refer to Part 7 - LUBRICATION. B12

120019 Do any 1600 hour lubrication requirements for Area F1, refer to Part 7 - LUBRICATION. C3





120024 Do any 1600 hour lubrication requirements for Area T1, refer to Part 7 - LUBRICATION. C8

120025 Do any 1600 hour lubrication requirements for Area W1, refer to Part 7 - LUBRICATION. C9

120026 Do any 1600 hour lubrication requirements for Area W2, refer to Part 7 - LUBRICATION. C10


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120027 Transferred to Out of Phase Inspections Task # 760004, refer to Part 7 - LUBRICATION. C11

120030 Do any 3200 hour lubrication requirements for Area F2, refer to Part 7 - LUBRICATION. D4

120049 Do any 24 month lubrication requirements for Area F1, refer to Part 7 - LUBRICATION. F3

120050 Do any 24 month lubrication requirements for Area F2, refer to Part 7 - LUBRICATION. F4

Chapter 20 - Standard Practices - Airframe

200001 Control surfaces. • Do a bonding check (Ref. 125/H-20, 20-10-5016).

B1

200002 Refuel point earthing studs (3 off).

• Do a function test for bonding resistance to the local structure (Ref. 125/H-20, 20-10-

5016).

B1

200003 Radio racking, electrical-bonding.

• Do a bonding check with all the equipment fitted (Ref. 125/H-20, 20-10-5016).

G

Chapter 21 - Air Conditioning

210002

Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Ram air valve and dump valve. • Do a check/test (Ref. AMM 21-10-155, 201, select 750, 800XP, 800XP/850XP Pro Line

21 or 900XP). Airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Ram air valve and vent valve. • Do a check/test (Ref. AMM 21-10-155, 201, select 750 or 900XP).

B1

210003

Environmental control system. • Do a function test of the Pressure regulator and shut off valve (PRSOV) (Ref. AMM 21-10-76, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). • Do a bench check of the PRSOV Overpressure switch (Ref. AMM 21-10-78, 201,

select 750, 800XP, 800XP/850XP ProLine 21 or 900XP).

B1

210004

Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Manual cabin altitude control valve. • Make sure of full and free movement.

B4

210005 Cooling turbine exhaust duct drain. Make sure the drain is free from blockages. B7

210006 Every 400 hours. Water separator. • Inspect for satisfactory condition (Ref. AMM 21-10-95, 601, select 750, 800XP/850XP

Pro Line 21 or 900XP). NOTE Operators may adjust this time based on servicing experience.

Out of Phase


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210007 Every 400 hours. Water separator. Inspect the following items are free from blockages and obstructions (Ref. AMM 21-10-95, 601, select 750, 800XP/850XP Pro

Line 21 or 900XP): • Water separator water drain. • Water separator water drain pipeline. • HP line to water injector nozzle. • Water injector nozzle. NOTE Operators may adjust this time based on servicing experience.

Out of Phase

210008 Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Cabin pressure outflow/safety valve controller. • Visually inspect and make sure that the cabin air sense port screen is clear.

C4

210009 Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Pressurization control venturi screen. • Make sure screen is clean.

C6

210010 Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Pressure regulators. • Clean the filter screens (Ref. AMM 21-30-55, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

G

210011 Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Outflow/safety valves. • Clean the outflow valve poppet valve and seat (Ref. AMM 21-30-25, 701, select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP). • If required, clean exterior of the outflow valve using a cloth or sponge soaked in

cleaning fluid (Ref. AMM 21-30-25,

701, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). • Check that the orifice in the cabin air filter connection is free of obstruction. • Check that the cabin air sense ports are free and clear of any obstruction. • Functionally test operation of valves (Ref. AMM 21-30-25, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP).

G

210012 Air conditioning ducts. Inspect for satisfactory condition (Ref. AMM 21-10-15). C7

210013 Ram air duct. Inspect, as far as is possible, for cracks in the vicinity of the take-off duct

to the shut-off valve, and around the cut-out for the inward relief door. C7

210014 Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Cabin air filters (pressurization system). • Inspect.

G


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210015 Silencer duct and soundproofing (Ref. AMM 21-10-15). • Inspect the silencer duct internally for deterioration of the soundproofing material and

of the perforated inner retaining duct. • Inspect for internal and external corrosion.

D7

210016 System overheat temperature switch. Do a bench check (Ref. AMM 21-60-85). D7

210017 Baggage pannier heating system inlet and outlet valve (if fitted) OR External

baggage unit (EBU) inlet valve (750 airplanes ONLY). • Make sure of the correct operation under normal and 'smoke detected' conditions

(Ref. AMM 21-10-205). NOTE This test is only applicable to airplanes with a baggage pannier in place of the ventral fuel tank OR 750 airplanes with external baggage unit.

D7

210018 Altitude switch, cabin depressurization warning. • Do a functional test (Ref. AMM 21-30-70, 201, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP). NOTE Mod. 259747C (SB 21-3136) introduces a second Altitude Warning Switch (set to

14,000 ft.) to permit operation at high altitude airfields.

G

210019 Cabin supply non-return valve. Inspect, paying particular attention to the security of

the carrier arm/butterfly flap rivets (Ref. AMM 21-10-107).

D7

210020 Electrically actuated auxiliary heat valve.

• Do a functional test (Ref. AMM 21-60-105).

NOTE

This test may be done without engine bleed air.

C1

210021 APU supply, auxiliary supply, ram air supply and main engine supply. Check/non-

return valves.

• Remove and inspect.

• Make sure that the axial and radial play in the flappers is not excessive (0.025 in.

maximum for AiResearch valves).

D7

210022 After 50 flying hours but not more than 300 flying hours from airplane build OR after disturbance of ducts or rubber sleeves. Air conditioning ducts. • Check the duct joint clamp bolts for the correct torque loading: Ref. AMM 21-10-15, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP. Ref. AMM 21-10-87, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP. Ref. AMM 21-10-95, 401, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP.

Out of Phase

210024 Low Limit Temperature Control Valve Filter (if installed). • Clean or replace (Ref. AMM 21-60-61, 201). NOTE This task is only applicable to airplanes with a Honeywell GTCP36-150W APU,

installed to STC ST00459NY.

B7


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210025 PATS APU GTCP36-150W. APU bleed air system. • Inspect for air leaks at clamped joints and pipes. • Inspect load control valve for cracks, dents, deformation or other damage that may

affect the performance of the valve. • Remove and inspect the check valve. Repair as required.

C7

210026 Airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Digital pressurization cabin air filters. • Replace both of the filter element (Ref. AMM 21-31-20, 301, select 750 or 900XP).

C6

210027 Airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Electropneumatic outflow valve (EOV). • Clean each EOV poppet valve seat (Ref. AMM 21-31-10, 701, select 750 or 900XP).

C6

210028 Airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Electropneumatic outflow valve (EOV) pressure limiter. • Do each EOV pressure limiter test (Ref. AMM 21-31-00, 501, select 750 or 900XP).

D6

210029 Every 15,000 Hours, Airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Electropneumatic Outflow Valves. • Do an inspection/check for the smooth operation of the manual electropneumatic

outflow valve (Ref. AMM 21-31-00, 601, select 750 or 900XP).

Out of Phase

Chapter 22 - Autopilot

NOTE No Chapter 22 tasks at this time.

Chapter 23 - Communications

NOTE No Chapter 22 tasks at this time.


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Chapter 24 - Electrical Power

240001 Between 200 and 400 Hours. Starter/generators. • Remove and inspect (Ref. AMM 24-30-21, 401, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP). • Do a brush wear check (Ref. AMM 24-30-21, 601, select 750, 800XP, 800XP/850XP

Pro Line 21 or 900XP). • Inspect cooling fan. • Inspect splines for wear (Ref. AMM 24-30-21, 401, select 750, 800XP, 800XP/850XP

Pro Line 21 or 900XP). • Inspect engine drive for wear. • Install starter/generator (Ref. AMM 24-30-21. 401, select 750, 800XP, 800XP/850XP

Pro Line 21 or 900XP).

Out of Phase

240002 No.1 and No.2 main static inverters. • Operate inverters and make sure, by feel of hand, of a positive airflow output from the

inverter cooling fans.

B1

240003 Frequency wild A.C. system. Do a function test (Ref. AMM 24-22-02). D1

240004 Busbar contactor control. • Set the bustie switch to CLOSE. • Trip the LH generator off-line. • Make sure all d.c. busbars are energized. • Reset the LH generator. • Trip the RH generator off-line. • Make sure all d.c. busbars are energized. • Reset the RH generator.

C1

240005 APU generator overheat indication circuit. Function test (Ref. AMM 24-36-03,

Turbomach APU installation only). D1

240006 D.C. busbar protection/voltage sensing unit. • Check the trip voltage datums (Ref. AMM 24-30-142, 501, select 750, 800XP,


D6

240007 Ground power overvoltage sensor (if fitted). Bench check the trip voltage datum (Ref. AMM 24-30-146).

D7

240009 D.C. generating system. • Do a function test of the emergency contactor control (Ref. AMM 24-30-01, 501, select

750, 800XP, 800XP/850XP ProLine 21 or 900XP).

B1

240010 PE, PS1 and PS2 busbar feeder cables below Panel DA. • Inspect for discoloration due to overheating. • Torque tighten the connections (Ref. AMM 24-01-00, select 750, 800XP, 800XP/850XP


C6


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240011 Busbar PE, PS1 and PS2 feeder fuses. Replace (with new items) the fuses: • F31 an F32 on panel ZL. • F13, F14, F23 and F24 on panel GA. When you do this: • Make sure the fuses are in correct contact with the busbars and the mounting pillars. • Make sure the fuses are clamped in position correctly. • Torque tighten the securing nuts (Ref. AMM 24-01-00).

C7

240012 Busbar PE, PS1 and PS2 feeder system connections. • Inspect for discoloration due to overheating. • Torque tighten the connections (Ref. AMM 24-01-00).

C7

240013 All circuit breakers. Function test for correct mechanical operation. Do two manual

switching cycles for this test. D1

240014 Main generator control unit (GCU). Do a function test of the overvoltage protection

circuit (Ref. AMM 24-30-07). D1

240015 APU Generator control unit (GCU). Do a function test of the overvoltage protection

circuit (Ref. AMM 24-36-03). D1

240016 Electrical cable pressure bungs (in the forward pressure bulkhead). Inspect for

correct location in their housings (Ref. AMM 24-01-00).

D3

240017 Earth stations *16, *17, *18 and *19.

• Inspect. Look for signs of arcing.

• Do an impedance check (Ref. AMM 24-01-00, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

NOTE

It is not necessary to do this task until the second 48 month inspection (96

months). Do the task at every 48 month inspection from that time onwards.

G

240018 Electrical cable pressure bungs (in the rear pressure-bulkhead). Inspect for correct

location in their housings (Ref. AMM 24-01-00).

D7

240024 Every 500 APU running hours. APU starter/generator. • Remove (Ref. AMM 24-30-21, 401, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP). • Check the brush wear (Ref. AMM 24-30-21, 601, select 750, 800XP, 800XP/850XP

Pro Line 21 or 900XP). • Inspect the cooling fan. • Inspect the splines for wear (Ref. AMM 24-30-21, 401, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). • Inspect the engine drive for wear. Install the APU starter/generator (Ref. AMM 24-30-21, 401, select 750, 800XP,


Out of Phase

240025 Electrical cable pressure bungs (in the fuselage keel at the front spar). Inspect for

correct location in their housings (Ref. AMM 24-01-00). D5


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240026 Electrical cable pressure bungs (in the forward pressure bulkhead). Inspect for

correct location in their housings (Ref. AMM 24-01-00). D4

240027 Main batteries. Rebling Plastics "Quick Disconnect" battery connectors, P/N's 7007, 7013, 7016 and

7017 (if fitted): • 750 airplanes, Check (Ref. AMM 24-30-151, 401). • 800XP airplanes, Check (Ref. AMM 24-30-104, 401 or 24-30-151, 401). • 800XP/850XP Pro Line 21 airplanes, Check (Ref. AMM 24-30-151, 401). • 900XP airplanes, Check (Ref. AMM 24-30-151, 401).

D7

240028 Every 400 Hours. Panel GG and Terminal block M. • Do a visual inspection for deformation, displacement, discoloration and heat distress

(Ref. AMM 24-01-00, 201 select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP). NOTE This task is applicable to series 750 airplanes HB-1 thru HB-27, 800XP,

800XP/850XP Pro Line 21 airplanes 258266 thru 258982 and 900XP airplanes HA-0001 thru HA-0092 and HA-0094. 750 airplanes HB-28 and After, do not use terminal block M (Mod. 25G484B). 850XP Pro Line 21 airplanes 258983 and After, do not use terminal block M (Mod. 25G484C). 900XP airplanes HA-0093, HA-0095 and After, do not use terminal block M (Mod. 25G484A).

Out Of Phase

240029 Do a visual inspection for discoloration and signs of distress (Ref. AMM 24-01-00, 201

select, 750, 800XP, 800XP/850XP ProLine 21 or 900XP). Inspect DA-Panel for proper

mounting of components.

E6

240030 Every 200 Hours.

Cabin Inverter (115 VAC) system (if fitted).

• Do a function test of the Cabin Inverter (115 VAC) system (Ref. MMA 24-20-10, 201).

Out Of Phase

240031

Between 200 and 400 Hours. AC Generator Pad (900XP Only): • Remove the AC Generator (Ref. AMM 24-22-21, 401). • Inspect AC Generator QAD pad for deformation, cracks or other damage. • Install the AC Generator (Ref. AMM 24-22-21, 401). Inspection completed at.......................... Hrs. Date.....................

Out Of Phase

Chapter 25 - Equipment & Furnishings

250003 3rd crew members seat (if fitted). • Make sure that the seat stowing action is satisfactory. • Make sure of correct operation and satisfactory condition. NOTE To be done at this inspection or at a period conforming to the requirements of the local regulatory authority.

B6

250005 Emergency packs (if fitted). Inspect contents for condition and make sure expiry dates

are valid. E6

250006 First aid kits. Make sure expiry date is valid and make sure seal is intact. E6


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250007 Crew seats. • Do an operational check (Ref. CMM 25-11-24, 501 (Check 1)) or (CMM 25-11-27, 501

(Check 1)).

B4

250008 Crew seats. • Remove the crew seats (Ref. AMM 25-10-14, 401). • Do a detailed check (Ref. CMM 25-11-24, 501 (Check 2)) or (Ref. CMM 25-11-67,

501(Check 2)). • Install the crew seats (Ref. AMM 25-10-14, 401).

D4

Chapter 26 - Fire Protection

260001 Airplanes with Fire Extinguisher Pressure Gauges ONLY. Fire extinguishers, main engines. • Check the pressure gauge. Make sure the reading is correct, refer to the

pressure/temperature chart. • Do a functional test (Ref. AMM 26-20-00). NOTE For airplanes without Fire Extinguisher Pressure gauges refer to Inspection E7 task 260005.

E1

260002 Rear equipment bay overheat detection system. • Do a functional test (Ref. AMM 26-10-00, 201, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

B1

260003 Portable fire extinguisher. • Check for correct weight or if gauge is fitted, make sure the needle is in the green

sector. • Inspect and look for signs of leaks or discharge.

E4

260004 Portable fire extinguisher (if fitted). • Check for correct weight or if gauge is fitted, make sure the needle is in the green

sector. • Inspect and look for signs of leaks or discharge.

E6

260005 For airplanes without Fire Extinguisher Pressure Gauges ONLY. Fire extinguishers, main engines. • Remove (Ref. AMM 26-20-12). • Inspect. • Check weight (Ref. AMM 26-20-12). • Install (Ref. AMM 26-20-12). • Do a functional test (Ref. AMM 26-20-00). NOTE For airplanes with Fire Extinguisher Pressure Gauges refer to Inspection E1, task260001.

E7

260007 Fire extinguisher, APU (Solar T-40 (Turbomach ONLY)). • Inspect. • Check pressure gauge (Ref. AMM 26-20-54). • Check Hydrostatic and Cartridge due dates. • Do a functional test (Ref. AMM 26-20-00).

E7


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260008 Every 6 months. Smoke Detection System (if fitted). • Do a function test: 750 airplanes (Ref. MMA 26-11-00, 501). 800XP and 800XP Pro Line 21 airplanes (Ref. MMA 26-11-00, 501). 900XP airplanes (Ref. MMA 26-11-00, 501).

Out of Phase

260009 Every 6 months. Baggage Pannier OR External Baggage Unit Smoke Detection System (if fitted). • Do a function test (Ref. AMM 26-10-52, 201, select 750 or 800XP). NOTE This test is only applicable to airplanes with a baggage pannier in place of the ventral fuel tank OR 750 airplanes with an external baggage unit.

Out of Phase

260010 PATS APU GTCP36-150W. APU fire extinguisher. • Inspect. • Check pressure gauge (Meggitt CMM 26-20-02). • Check Hydrostatic and Cartridge due dates. • Do a functional test (Ref. AMM 49-61-20, 501).

E7

260011 External Baggage Unit Fire Extinguisher.

• Inspect.

• Check Pressure gauge.

• Check cartridge expiry date.

• Do a functional test (Ref. AMM 26-20-60, 201).

NOTE

This task is ONLY applicable to 750 airplanes.

E7

Chapter 27 - Flight Controls

270001 Every 400 hours. Airbrake selector lever baulk. • Do an operational test (Ref. AMM 27-61-03, 501). NOTE This task is ONLY applicable to airplanes with Mod. 25F743A or Mod. 25F743C

embodied and is applicable to Canadian registered airplanes only. Mod. 25F743A (SB 27-3150) introduces an airbrake selector lever baulk to 800XP

airplanes. Mod. 25F743C (SB 27-3554) introduces an airbrake selector lever baulk to 800XP

Pro Line 21 airplanes. SB 27-3554, Rev.3, introduces an airbrake selector lever baulk to 850XP airplanes. SB 27-3554, Rev.4, introduces an airbrake selector lever baulk to 900XP airplanes.

Part 1 - Minor

Inspections - Airbrake Selector Lever Baulk Inspection

270002 Flap vane inner. With the flaps lowered, inspect the left outer attachment bracket for

cracking and for security of attachment to the flap leading edge. C9

270003 Flap screwjacks. Inspect the screw threads for satisfactory condition. B9

270004 Stall warning and identification system. • Do a functional test of the stall warning and identification system (Ref. AMM 27-33-00). • Do an angle verification check (Ref. AMM 27-33-00). • Do an electrical zero check (Ref. AMM 27-33-00).

B2


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NOTE The electrical zero check is only applicable to airplanes with Mod. 25G206A or

Mod. 25G206B.

270008 Rudder bias strut heater muffs. • Do a functional test of the rudder bias strut heater muff (Ref. AMM 27-20-00).

B2

270009 Stall detector unit (third channel). Do a function test: • 800XP airplanes (Ref. AMM 27-33-14). • 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-33-14). NOTE This task is only applicable to 800XP and 800XP/850XP Pro Line 21 airplanes Pre-Mod. 25G206A.

OR Pre-Mod. 25G206A and 25G206B.

B2

270011 Gust lock, ailerons and elevators. • Inspect. • Make sure that the bush in the mounting bracket is lightly lubricated and free from

burrs or scores. • With the unit in the operated and locked position but without the engagement of the

claw spigots in the control column bushes, check for positive spring pressure on the claws and for initial resistance to movement when releasing the knurled locking ring.

B4

270012 Rudder trim tab and anti-servo tab. • Check the free movement (backlash) at the trailing edges of the tabs (Ref. AMM 27-20-00, 501). • While the connecting rods are disconnected check the rear rod-end bearings for

smooth operation. • Detail inspect the connecting rod attachment lugs on the tabs for cracks using a X 10

magnifier. NOTE Do not remove the protective coating unless a defect, or suspected defect, is

found.

B8

270013 Elevators and trim tabs. • Check the free movement (backlash) at the trailing edges of the tabs (Ref. AMM 27-30-00, 501). • While the connecting rods are disconnected check the rear rod-end bearings for

smooth operation. • Detail inspect the connecting rod attachment lugs on the trim tabs for cracks, using a

X 10 magnifier. NOTE Do not remove the protective coating unless a defect, or suspected defect, is

found.

B8

270014 Rudder and elevators primary surfaces. Make sure of full and free movement from

stop to stop. B8

270015 Aileron primary surfaces. Make sure of full and free movement from stop to stop and

that all accessible aileron pulleys rotate freely. B9


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270016 Aileron trim and servo tabs. • Check the free movement (backlash) at the trailing edges of the tabs (Ref. AMM 27-10-00, 501). • While the connecting rods are disconnected inspect the rear rod-end bearings for


magnifier. NOTE Do not remove the protective finish unless a defect, or a suspected defect is

found.

B9

270017 Flap Screwjack and reduction gearbox. • Check the gearbox fluid level (Ref. AMM 27-50-141).

B9

270018 Flap synchronization system control cables. • Inspect for fraying, particularly in the vicinity of the pulleys. • Make sure accessible pulleys rotate freely.

B9

270019 Flap control unit. • Check the gearbox fluid level (Ref. AMM 27-50-121).

B9

270020 Flap control unit. • Do a flap control unit neutral selection check (Ref. AMM 27-50-02, 201).

B9

270021 Flap drive shafts. Inspect for signs of corrosion and for movement between the end

fittings and the shafts. B9

270022 Aileron primary surfaces. Make sure of full and free movement from stop to stop and

that all accessible aileron pulleys rotate freely. B10

270023 Aileron servo tabs. • Check the free movement (backlash) at the trailing edges of the tabs (Ref. AMM 27-10-00, 501). • While the connecting rods are disconnected inspect the rear rod-end bearings for


magnifier. NOTE Do not remove the protective finish unless a defect, or a suspected defect is found.

B10

270024 Flap Screwjack and reduction gearbox. • Check the gearbox fluid level (Ref. AMM 27-50-141).

B10

270025 Flap synchronization system control cables. • Inspect for fraying, particularly in the vicinity of the pulleys. • Make sure accessible pulleys rotate freely.

B10

270026 Flap drive shafts. Inspect for signs of corrosion and for movement between the end

fittings and the shafts. B10

270027 Flap control system. Do a function test (Ref. AMM 27-50-02, 501). B12

270028 Airbrake and lift dump system. • Do a functional test (Ref. AMM 27-61-02, 501).

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270030 Elevator trim servo. • Operate the elevator trim switch on the left, or right, control column. • As the elevator trim servo motor operates the elevator trim tabs, hold the manual

elevator trim wheel with sufficient force to stop the trim wheel. • The force needed to stop the trim wheel must not be more than 15 lbs.

C2

270032 Aileron autopilot servo control cables. Check cable tensions are correct: • 750 airplanes (Ref. AMM 27-00-00, 201 and 22-10-10, 401). • 800XP airplanes (Ref. AMM 27-00-00, 201 and 27-10-93, 401). • 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-00-00, 201 and 22-10-10, 401). • 900XP airplanes (Ref. AMM 27-00-00, 201 and 22-10-10, 401).

C4

270033 Elevator control system balance/feel spring. • Inspect.

C4

270034 Elevator primary control cables. Check cable tensions are correct (Ref. AMM 27-30-00).

C5

270035 Flap control cables. Check cable tensions are correct (Ref. AMM 27-50-02). C5

270036 Elevator primary and elevator trim control cables. Check cable tensions are correct

(Ref. AMM 27-30-00). C7

270037 Rudder primary and rudder trim control cables. Check cable tensions are correct

(Ref. AMM 27-20-00). C7

270038 Elevator autopilot servo control cables. Check cable tensions are correct: • 750 airplanes (Ref. AMM 22-10-30, 401). • 800XP airplanes (Ref. AMM 27-30-81, 401). • 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-30, 401). • 900XP airplanes (Ref. AMM 22-10-30, 401).

C7

270039 Rudder autopilot servo control cables. Check cable tensions are correct: • 750 airplanes (Ref. AMM 22-10-20, 401). • 800XP airplanes (Ref. AMM 27-20-121, 401). • 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-20, 401). • 900XP airplanes (Ref. AMM 22-10-20, 401).

C7

270040 Elevator autopilot trim-servo control cables. Check cable tensions are correct (Ref. AMM 27-30-00).

C7

270041 Elevator trim cables. • Inspect the condition of the protective coating (Ref. AMM 20-95-11, Item No. 079) on

the cables over a length of 42 ins (1070 mm) from each trim chain where the cables are

exposed between the horizontal stabilizer and the elevators. • Apply protective coating (Ref. AMM 27-30-00, page block 301), if necessary.

C8

270042 Aileron primary and trim control cables. Check cable tensions are correct (Ref. AMM

27-10-00). C9

270043 Flap drive shaft universal joints. With grease covers removed, inspect joints for wear

and repack with grease (Ref. AMM 27-50-132). C9

270044 Flap Bevel drive assembly. Check that the backlash between the input and output

shafts, measured at the input coupling flange bolts, does not exceed 0.020 in. C9

270045 Flap control unit baulk release cable. Check cable tension is correct (Ref.AMM 27-50-02).

C9


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270046 Flap/airbrake baulk bobbin. Make sure bobbin setting is correct (Ref. AMM 27-50-02). C9

270047 Flap spring drum pulley-lever. • Disconnect rod from pulley lever (Ref. AMM 27-50-02). • Check the pull off force required to move the lever off the spring drum internal stops

is 5.35 lb. to 7 lb., measured at the connecting rod attachment point on the lever. • Check that the lever returns to contact internal stops at or before 5 lb. force at the

connecting rod attachment. • Reconnect control rod to pulley lever.

C9

270048 Flap Screwjack and reduction gearbox. Check that the backlash on the screw

threads does not exceed 0.020 in (Ref. AMM 27-50-141). C9

270049 Flap synchronising system.

• Check the cable tensions are correct (Ref. AMM 27-50-02).

• With the flaps selected up, disconnect the operating link from one transmitter gearbox

only.

• Pressurize the hydraulic system.

• Whilst restraining the disconnected lever arm, select the flaps down.

• Make sure that the flaps start to move and then the system cuts out.

• Depressurize the hydraulic system and connect the transmitter operating link.

• Pressurize the hydraulic system and make sure that the flaps operate correctly.

C9

270050 Airbrake control cables. Check the cable tensions are correct (Ref. AMM 27-61-02). C9

270051 Aileron primary and trim control cables. Check cable tensions are correct (Ref. AMM

27-10-00).

C10

270052 Flap drive shaft universal joints. With grease covers removed, inspect joints for wear

and repack with grease (Ref. AMM 27-50-132).

C10

270053 Flap bevel drive assembly. Check that the backlash between the input and output

shafts, measured at the input coupling flange bolts, does not exceed 0.020 in.

C10

270054 Flap screwjack and reduction gearbox. Check that the backlash on the screw threads

does not exceed 0.020 in (Ref. AMM 27-50-141).

C10

270055 Flap synchronising system.

• Check the cable tensions are correct (Ref. AMM 27-50-02).

• With the flaps selected up, disconnect the operating link from one transmitter gearbox

only.

• Pressurize the hydraulic system.

• Whilst restraining the disconnected lever arm, select the flaps down.

• Make sure that the flaps start to move and then the system cuts out.

• Depressurize the hydraulic system and connect the transmitter operating link.

• Pressurize the hydraulic system and make sure that the flaps operate correctly.

C10

270056 Airbrake control cables. Check the cable tensions are correct (Ref. AMM 27-61-02). C10

270057 Flap control forward spring strut. Check break-out load with one end disconnected

and using a spring balance is 21.5 to 24.5 lb. (Ref. AMM 27-50-02).

D4

270058 Flap control input-circuit. Do a static friction check (Ref. AMM 27-50-02). D4

270059 Control cable pressure seals at rear pressure bulkhead. Inspect for wear. E7


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270060 Filter, auxiliary hydraulic system supply to flap control unit. Replace the filter

element (Ref. AMM 29-20-00, 001).

NOTE

The AMM reference is for component location ONLY.

D10

270061 After 200 flying hours and not more than 300 flying hours from the airplane build or after Control Cable replacement. Control cables. Check the tensions of the: • Aileron and aileron trim control cables (Ref. AMM 27-10-00, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). • Rudder and rudder trim control cables (Ref. AMM 27-20-00, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). • Elevator and elevator trim control cables (Ref. AMM 27-30-00, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). • Flap control cables (Ref. AMM 27-50-02, 501, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP). • Airbrake control cables (Ref. AMM 27-61-02, 501, select 750, 800XP, 800XP/850XP


Out of Phase

270063 Whenever the SVO-85B servo or its mating servo mount are removed and replaced in

the airplane.

Servomotor assembly SVO-85B (P/N 622-5027-001).

Lubricate and clean as detailed in Collins SVO-85B/C Service Information Letter SIL 1-

01.

Out of Phase

270064 Flap vane inner. With the flaps lowered, inspect the right outer attachment bracket for

cracking and for security of attachment to the flap leading edge.

C10

270065 Flap screwjacks. Inspect the screw threads for satisfactory condition. B10

270066 Aileron Control cable pressure seals. Inspect for wear. B9

270067 Aileron Control cable pressure seals. Inspect for wear. B10

270068 Aileron Servomotor assembly SVO-85B (P/N 622-5027-001).

• Lubricate and clean as detailed in Collins SVO-85B/C Service Information Letter SIL

1-01.

G

270069 Elevator Servomotor assembly SVO-85B (P/N 622-5027-001).


1-01.

G

270070 Rudder Servomotor assembly SVO-85B (P/N 622-5027-001).


1-01.

G

270071 Rudder Trim Jack.

• Do an inspection (Ref. AMM 27-20-111, 301, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

G

270072 Elevator Trim Jack.

• Do an inspection (Ref. AMM 27-30-51, 301, select 750, 800XP, 800XP/850XP Pro Line

21 or 900XP).

G


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Chapter 28 - Fuel

280001 Fuel Transfer System, Wing tanks. Check fuel flow.

• Check for positive flow from the LH and the RH wing tank to the opposite wing tank.

NOTE

For positive flow note a 200lb increase in the fuel gauge indication.

B1

280002 Fuel valve control cables. Check cable tensions are correct (Ref. AMM 28-20-83). C5

280003 LP valves. Do a function test for internal leakage (Ref. AMM 28-20-00). D1

280004 APU fuel inlet filter (if fitted). Inspect, clean or replace the fuel filter element:

• 800XP airplanes (Ref. AMM 28-20-09).

D7

280005 Suction pipe strainers. Visually inspect for satisfactory condition. C9

280006 Water transfer system pipe suction blocks. Visually inspect for satisfactory condition. C9

280007 Suction pipe strainers. Visually inspect for satisfactory condition. C10

280008 Water transfer system pipe suction blocks. Visually inspect for satisfactory condition. C10

280010 After 200 flying hours and not more than 300 flying hours from the airplane build or after Control Cable replacement. Control cables. Check the tensions of the: • LP fuel valve control cables (Ref. AMM 28-20-83, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). • Crossfeed and wing transfer valve control cables (Ref. AMM 28-20-83, 501, select

750, 800XP, 800XP/850XP Pro Line 21 or 900XP). • Auxiliary fuel transfer valve control cables (Ref. AMM 28-20-83, 501, select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP) (if ventral tank installed).

Out of Phase

280014 Applicable to Intertechnique fuel pumps only. Fuel system pumps. • Part No. 2070C01 Check the brush length (14 mm minimum). • Part No. 2070C11 Check the brush length (10 mm minimum).

C9

280015 Applicable to Intertechnique fuel pumps only. Fuel system pumps. • Part No. 2070C01 Check the brush length (14 mm minimum). • Part No. 2070C11 Check the brush length (10 mm minimum).

C10

280016 Low Pressure Fuel Valve Support Strut Part No. 25 PF361, 25 PF361-5A (Mod. 25G310A) and 25 PF363. Do a visual inspection of the Low Pressure Fuel Valve Support Strut, attachment bolt and drain hole for corrosion. NOTE If corrosion is found replace the affected part.

G

Chapter 29 - Hydraulic Power

290003 Suction filter. Replace the element (Ref. AMM 29-10-21). B7

290004 Main hydraulic system.

• At system shutdown check the pressure dissipation time on the main pressure

accumulator (Ref. AMM 29-10-00, 501).

B12

290005 Landing gear and flaps emergency lowering system. Do an operational test (Ref.

AMM 29-20-00).

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290006 Hydraulic tank pressurization system. Drain any accumulation of liquid from the

drain/ground air charge connection.

C7

290007 Flaps, airbrakes, landing gear, nosewheel steering, nose leg self-centring. Do a

test of the main system with a hydraulic test rig (Ref. AMM 29-10-00).

C12

290008 Emergency brake system leak rate. Check the rate that the pressure decreases

(leakage rate) in the accumulator (Ref. AMM 29-10-00).

C12

290009 Auxiliary reservoir low-level warning system. Do a function test (Ref. AMM 29-30-00).

NOTE

Do this task in conjunction with Task # 290005.

B12

290010 Hydraulic reservoir pressurization system. Do a functional test of the non-return

valve (Ref. AMM 29-10-13).

C12

290011 Full-flow relief valve. Clean filter element (Ref. AMM 29-10-71). D7

290012 High temperature warning system. Do a test of the main hydraulic reservoir high

temperature warning system (Ref. AMM 29-30-00).

D7

Chapter 30 - Ice and Rain Protection

300001 Rotary ice detector. Do a function test (Ref. AMM 30-80-00, 501, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP). B1

300002 Windshield electrical de-icing system. Do an operational test of the windscreen

overheat (Ref. AMM 30-41-00).

C1

300003 Airframe de-icing system pressure filter.

• Replace the filter element (Ref. AMM 30-10-52).

B6

300004 Pitot head and static plate heaters. Do a function test (Ref. AMM 30-35-15). C1

300005 Airframe de-icing pump suction-filter.

• Replace the filter element (Ref. AMM 30-10-43, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

C6

300007 Every calendar month.

Applicable if the airframe de-icing system has not been operated during the last calendar

month.

• Airframe Ice protection - purge the airplane ice protection system (Ref. AMM 12-30-00,

301, select 750, 800XP,


Out of Phase

Chapter 31 - Instruments

310001 Flight data recorder (if fitted). Check for correct playback operation (data dump) and for

quality of the recording. NOTE Do the check at this inspection or at a time agreed necessary by the local airworthiness authority. For FDR systems not installed under the original

Airplane Type Certificate, reference the applicable Maintenance Manual Addenda for systems fitted by Supplemental Type Certificate (STC).

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Chapter 32 - Landing Gear

320001 Braking systems. • Do a test of the emergency and parking brake system operation (Ref. AMM 32-40-00,

501).

B12

320002 Maxaret Units.

• Do a function test (Ref. AMM 32-40-101, 501).

B12

320003 Nose gear leg assembly.

• Make sure oil level and gas pressures are correct (Ref. AMM 32-20-12).

• Check the leg extension (Ref. AMM 12-32-00).

B12

320004 Nose gear leg lock and change-over microswitches operating mechanism. Make

sure of freedom of operation.

B12

320005 Nosewheel steering jack.

• Inspect for satisfactory condition.

NOTE

Pay particular attention to scores and the cleanliness of the jack ram.

B12

320006 Nose gear retraction and steering system spring struts. Inspect. B12

320007 Nosewheel steering ON/OFF valve. Inspect. B12

320008 Nose gear drag stay assembly. Check clearances (Ref. AMM 32-20-21). B12

320009 Nosewheel steering jack selector valve.

• Service: Clean and grease the selector valve spring housing and parts (Ref. AMM 32-

50-11, 301), select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

B12

320010 Main gear leg assemblies.

• Make sure oil level and gas pressures are correct (Ref. AMM 32-10-12).

• Check the leg extension (Ref. AMM 12-32-00).

B12

320011 Main landing gear side-stays.

• Inspect the center joint nut for distortion (Ref. AMM 32-10-25).

• Check the side-stay clearances (Ref. AMM 32-10-25).

B12

320012 Main landing gear torque links. Examine the torque link pivots for wear (Ref. AMM 32-

10-12, page block 601).

B12

320013 Main landing gear doors.

• Inspect the hinge bracket assemblies for security and tightness of the nuts.

• Inspect jack attachment brackets and adjacent structure for cracks.

• Inspect for signs of movement of the forward hinge brackets and bolts at their

attachment to the wing structure by attempting to rock the doors in the longitudinal and

transverse directions.

NOTE

If the brackets are found to be loose, inspect the attachment bolt holes and bolts

for wear and corrosion.

B12

320014 Main landing gear door uplock spring struts.

• Inspect.

• Clean the sliding surfaces.

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• Make sure of correct operation:

Check initial breakout/first movement of the spring strut occurs at 19 lb ±2 lb.

Make sure movement of the strut is free over the length of the stroke.

320015 Reversing valves and operating mechanisms.

• Disconnect from the side stay.

• Inspect for satisfactory condition.

• Make sure the mechanisms are free to move correctly.

• Connect to the side stay.

B12

320016 Steering system cables and chains.

• Make sure cable tensions are correct (Ref. AMM 32-50-00, select 750, 800XP,


C4

320017 Nose landing gear retraction spring strut. Check the break-out load (Ref. AMM 32-20-

21).

C12

320018 Nosewheel steering system spring strut break-out load.

• Check the break-out load (Ref. CMM 32-50-00).

• If the load is excessive, dismantle the spring strut, clean, lubricate and reassemble

(Ref. CMM 32-50-00).

C12

320019 Steering system filter element. Remove, inspect and clean filter element (Ref. AMM

32-30-22).

D12

320020 Filters, hydraulic supply (4 off). Clean the filter elements (Ref. AMM 32-30-22). D12

320021 Restrictor valves. Clean the micro filters in the pipe connections (Ref. AMM 32-30-01). D12

320022 Brake master cylinders.

• Check fluid level and replenish, as necessary (Ref. AMM 32-40-00, 301, select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP).

B4

320023 Brake hoses to master cylinders.

• Make sure of an adequate clearance between the hoses and the floor over the full

range of rudder pedal travel.

C4

320024 Axle/Maxaret/Modulator/Plunger Tube.

• Maxaret and modulator unit. Remove and inspect

(Ref. AMM 32-40-91 and AMM 32-40-101).

• While the Maxarets and Modulator units are removed, detail inspect the internal bores

of the axles.

• Inspect the Plunger Tube to Axle Bore for signs of corrosion.

• Reinstall Maxarets and Modulator units

(Ref. AMM 32-40-91 and AMM 32-40-101).

• Do a function test (Ref. AMM 32-40-101, ADJUSTMENT/TEST).

C12

320027 Nose-wheel steering on/off-valve.

• Remove the plunger stop cap.

• Visually inspect the plunger and spring for corrosion, clean and lubricate all surface

areas as required using Grease (Ref. AMM 125/H-20, 20-95-11, Item 034).

• Install the stop cap.

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320028 8 years, then every 4 years.

Main landing gear fairing strut.

• Comply with instructions in NTM 32-10-103.

Structural

320029 Between 25 to 50 landings from build or after nose landing gear drag stay

replacement.

Nose landing gear drag stay. Check clearances (Ref. AMM 32-20-21, 601, select 750,


Out of Phase

320033 Main gear retraction actuator (Ref. AMM 32-30-27).

NOTE

To do this inspection, disconnect the cylinder head end of the actuator. Do not

disconnect the hydraulic lines.

• Detail inspect the actuator attachment lugs.

B12

320034 Plunger Tube/Axle Joint.

• Inspect the flexible seal at the plunger tube to axle joint.

• Make sure the seal is not loose or cracked.

• Rectify as necessary (Ref. AMM Chapter 32, MAIN LEG ASSEMBLY).

B12

320035 Main Leg Assembly Retraction Lever.

• Inspect for excessive movement.

• Inspect for signs of corrosion.

C12

320036 Sidestay Assembly Lock Mechanism Link.

• Inspect for signs of wear.

C12

320037 Nose leg assembly torque links. Examine the torque link pivots for wear (Ref. AMM 32-

20-12, 601).

B12

320038 NOTE

This task is not applicable to airplanes Post Mod. 25G295 or Post SB. 32-3779

Every month if the airplane has been exposed to runway de-icing:

• Lubricate the Main landing gear sidestay shims (Ref. Part 7 - Lubrication, Monthly

lubrication).

Out of Phase

Chapter 33 - Lights

330003 Anti-Collision light system that has a strobe type device in any position.

• Clean the strobe light lenses internal and external.

• Clean the wing-tip lens covers internal and external.

• Check the strobe light flash rate (Flash rate of 60 ± 5 cycles per minute), (Ref. AMM

33-40-12, 201).

NOTE

Refer to the Component Requirements section of this manual for the

manufacturer's recommended period for replacement and strobe light intensity

test procedure.

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Chapter 34 - Navigation

340002 Pitot/static drain traps.

• Pre SB.34-3282 (Mod. 25F889B) or Pre Mod. 25F889A. Drain, do a leak test (Ref. AMM

34-11-19, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

• Post SB.34-3282 (Mod. 25F889B) or Post Mod. 25F889A. Drain (Ref. AMM 34-11-19,

501, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

NOTE

Do this task in conjunction with FAR pitot/static system checks (Task 340006).

Out of Phase

340003 Autopilot aileron servo unit and mount.

• Inspect, particularly for cable and capstan wear, contamination, cable spool-off angle

and security of the servo unit and mount.

• With the autopilot disengaged operate the control system throughout the entire range

and make sure there is no unusual noise, binding, backlash or signs of other mechanical

irregularities from the servo mount.

C4

340004 Autopilot servo units, rudder and elevator.






C7

340005 Autopilot elevator trim servo unit and mount.






C7

340006 Pitot/static and stall warning systems. Do the following tests (Ref. AMM 34-11-19, 501,

select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP): • Pressure Test Complete Pitot System. • Suction Test Complete Static System. • Pressure Test Stall Vent System (This procedure only applies to airplanes Pre-Mod. 25G206A or 25G206B). NOTE

Do this task in accordance with FAR requirements.

Out of Phase

340007 Pitot system isolation valves. Make sure of full and free operation. NOTE This task is not applicable to the Hawker 750 or Hawker 900XP airplanes due to the removal of the third channel stall can. Do this task in conjunction with FAR pitot/static system checks (Task 340006).

Out of Phase


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340008 Mach trim system. Do a test of the Mach trim system: • 750 airplanes (Ref. AMM 22-20-00, 501). • 800XP airplanes (Ref. AMM 34-24-00, 501). • 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-20-00, 501). • 900XP airplanes (Ref. AMM 22-20-00, 501).

D1

340010 Autotrim command isolation relay and autotrim switching relay. NOTE This task is ONLY applicable to airplanes equipped with an FCC-86 Flight Control

Computer. • Do checks as detailed, Ref. AMM 27-30-00, 501, (Autotrim command isolation relay

and autotrim switching relay checks).

D1

340011 This task is NOT applicable to Pro Line 21 Equipped airplanes. Mach trim fail annunciation relays. • Open the MACH TRIM PWR or MACH TRIM MON circuit breaker. • Make sure that the MACH TRIM FAIL annunciator comes on. • Close the MACH TRIM PWR or the MACH TRIM MON circuit breaker. • Make sure that the MACH TRIM FAIL annunciator goes off .

D1

340012 Every 36 months, or at a time period agreed with the local regulatory authority. Compass systems. • Do a check compass swing of the compass systems at four headings 90 degrees

apart. • Compare deviations, if any are found, with the existing deviation card. • If deviations are found then do a compass swing: 750 airplanes (Ref. AMM 34-20-05, 501). 800XP airplanes (Ref. Collins AMM 34-23-61, 501) (Ref. Honeywell AMM 34-20-15, 501). 800XP Pro Line 21 airplanes (Ref. AMM 34-20-05, 501). 900XP airplanes (Ref. AMM 34-20-05, 501).

Out of Phase

340013 After repaint or maintenance in the area affecting the airflow over static ports. Static plates and Airframe (Applicable to airplane serial numbers 258359 and after,

and to airplanes that have complied with Service Bulletin 34-3110, or SB.34-3166 or

SB.34-3381 and are maintaining RVSM capability authorization). Comply with RVSM requirements (Ref. AMM 34-11-29, 601, select 750, 800XP,

800XP/850XP Pro Line 21 or 900XP) for the area disturbed.

Out of Phase

Chapter 35 - Oxygen

350001 Oxygen system master supply valve.

• With the oxygen system fully charged and the supply master valve closed, exhaust

system downstream of the valve until the contents gauge indicates zero.

• After 15 minutes has elapsed, make sure that there is no increase in the contents

gauge indication which would show leakage past the closed valve.

B4

350002 Automatic shut-off valve. Do a functional test (Ref. AMM 35-10-141). D2


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350004 Passenger oxygen system.

• Test automatic operation of baromatic valve (Ref. AMM 35-06-00, 501).

• Test for flow from each mask by reference to operation of the visual indicator (if fitted)

when mask is pulled down to the full hang' position:

750 airplanes (Ref. MMA 35-06-00, 201).

800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 35-06-00, 201).

900XP airplanes (Ref. MMA 35-06-00, 201).

• Inspect drop-out mask units when deployed during system test:




NOTE

If the passenger masks PN. 289-601* do not meet the requirements of the annual

inspection refer to the vendor CMM 35-22-26 for Visual, Overhaul and Repair

procedures.

• Stow drop-out mask units:




E2

350005 Baromatic control valve.

• With passenger supply isolation valve closed, exercise control valve mechanism by

operating the emergency/reset knob several times.

• Leave the knob at the reset position.

E2

350006 Crew masks, smoke set mask (if fitted) and hoses.

• Inspect.

E4

350007 Portable breathing equipment.

• Inspect:

800XP airplanes (Ref. AMM 35-35-10).

OR

750, 800XP, 800XP/850XP Proline 21 and 900XP (Ref. AMM 35-35-15).

• Check the expiry dates.

E4

350008 Oxygen cylinders.

• Inspect cylinder mount clamps for security (Ref. AMM 35-10-14, 401, select 750,


C7


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Chapter 38 - Water/Waste

380001

Water systems:

• Inspect the toilet and galley water systems.

• Make sure the flow of water is correct through the normal and overflow drains and

that there are no leaks.

If you find signs of fluid leakage:

• Inspect the aileron-cable fuselage pressure-seals and the adjacent structure in the

areas to the rear of frame 16. Do this to make sure the fluid leakage has drained

correctly.

• Make sure the drain holes and drain valves are free from blockages and function

correctly. Do this from the inside and the outside of the fuselage.

• Remove all fluid remaining in the area.

• Clean the areas where leakage has occurred.

• Lubricate the aileron cables if necessary (Ref. AMM 12-20-25).

• Replenish the toilet and galley water systems, if required:

800XP airplanes (Ref. AMM 12-38-00 or MMA Chapter 38 as applicable).

800XP/850XP Pro Line 21 airplanes (Ref. AMM 12-38-00 or MMA Chapter 38 as

applicable).

750 airplanes (Ref. MMA Chapter 38).

900XP airplanes (Ref. MMA Chapter 38).

B6

Chapter 49 - Airborne Auxiliary Power

NOTE

Also refer to inspection 050020 for APU servicing information.

490001 Perform in conjunction with Task 490003.

PATS APU GTCP36-150W.

• Visually inspect exhaust for cracks or deformation.

• Visually inspect for loose or frayed wires.

• Inspect for signs of corrosion.

Out of Phase

490002 Every 750 APU running hours.

PATS GTCP36-150W APU.

Igniter plug (Ref. CMM 49-40-33):

• Remove, clean, inspect and install.

Out of Phase

490003 NOTE Choose one of the following options. Do either Oil and Filter change at every 12

months or 1000 flying hours OR do a S.O.A.P. check at 750 APU running hours/12

months. CAUTION

Do not mix options.

Option 1.

Out of Phase


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Every 12 months or 1000 flying hours (whichever comes first). PATS GTCP36-150W APU. Oil and filter change, and magnetic drain plug inspection. Lubricating oil system: • Drain and refill (refer to servicing). NOTE Routine SOAP inspection is not required. Oil and Filter change at every 12 months or 1000 flying Oil Filter Element: • Remove, inspect and replace as necessary (Ref. CMM 49-90-47). Magnetic Drain Plug: • Remove, clean, inspect and install magnetic element of drain plug (Ref. CMM 49-90-46). Option 2. 750 APU running hours or 12 months (whichever comes first). Oil and Filter Element: • Do a S.O.A.P. check (in accordance with Honeywell procedures). Magnetic Drain Plug: • Remove, clean, inspect and install magnetic element of drain plug (Ref. CMM 49-90-46).

490004 Every 1000 APU running hours. PATS GTCP36-150W APU. Fuel filter element: • Remove and replace (Ref. CMM 49-30-52).

Out of Phase

490005 Every 4500 APU running hours. PATS GTCP36-150W APU. Fuel Nozzle Assemblies: Do a fuel flow rate check (Ref. CMM 49-20-00, Page Block 601,

paragraph 5, Fuel Nozzle Assembly Flow Rate Check).

Out of Phase

490006 Every 4500 APU running hours. PATS GTCP36-150W APU. Hot Section Inspection. Do a detailed Hot Section Inspection on the components listed (Ref. CMM 49-20-00, Page Block 601, paragraph (4), Detailed Hot Section Inspection): • Turbine Rotor. • Deswirl Deflector. • Turbine Nozzle. • Airflow Deflector. • Turbine Housing Assembly. • Combustion Chamber. • Labyrinth Seal. • Turbine Wheel Deflector. • Retainer Halves. • Containment Ring.

Out of Phase

490007 Every 4500 APU running hours.

PATS GTCP36-150W APU.

Out of Phase


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Compressor Rotor:

• Visually check compressor rotor for damage by observation through the compressor

screen openings.

NOTE

No damage allowed.

Chapter 51 - Structures

510001 Every 5000 landings or 12 years, whichever occurs first.

Nose landing gear bay sidewalls.

Access: Refer to NTM Technique.


Structural

510002 5000 flights then every 1000 flights.

Front pressure bulkhead.

Access: Sound-proofing blankets removed.

• Detail inspect the upper sidewall beams and the rudder pedal clearance pressings for

cracks (Ref. SRM 53-10-11, Front Pressure Bulkhead Pre Mod. 253090C or Front

Pressure Bulkhead Mod. 253090C).

• Pay special attention to the area in the vicinity of the joint with the canopy center post.

Structural


Flight compartment skin and window structure above windshields.


• Comply with instructions in NTM 53-10-105A.

Structural

510004 Every 20,000 flights.

Upper canopy rail at intersection with the canopy posts.

Access: Trim and insulation removed.

• Detail inspect.

Structural

510005 Between 15 to 18 years, then every 8 years.

Center fuselage structure below the floor, nose landing gear bay to Frame 13 and

Frames 16 to 19.

Access: Refer to relevant NTM Techniques.

• Comply with instructions in

• NTM 53-10-108.

• NTM 53-10-107.

• NTM 53-10-108B.

• NTM 53-10-109.

Structural

510006 Between 15 to 18 years and then every 8 years.

Structure below escape hatch, Frames 13 to 14.

Access: Escape hatch removed, leaded vinyl sleeve peeled back from lower corners of

the escape hatch surround to expose the apertures in the surround.

Structural


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• Detail inspect Frames 13 and 14, as far as is possible, for signs of corrosion using a

borescope probe.


Center fuselage structure below the floor, frames 8 to 17.



Structural


Center fuselage structure below the floor, Frames 13 to 16.



NOTE

In certain instances it may be necessary to lower the wing or separate the wing

from the fuselage to insert the film packs. In order to determine the conditions of

individual airplanes a test may be done by attempting to pass a strip of vinyl

carrier, to the dimensions given in the relevant NTM, between the fuselage lower

skin and the wing top surface.

Structural

510009 8 years and then every 4 years.

Entry door surround.

Access: Panel F66A, F66B, F66C removed.

• Detail inspect the structure at the lower edge of the surround for signs of corrosion

using a borescope probe inserted through the lightening holes in the intercostal.

Structural

510010 Between the 15 th and 18 th year of aircraft operation and then every 8 years.

Center fuselage structure, above the floor.


NOTE

The most economical and practical time to do this inspection is when the quick

trim is removed for refurbishing or other reasons.

NOTE

Airplanes without the digital pressurization control system Mod. 25G726A/C or

Mod. 25G726B/C. When installing local furnishings, make sure a minimum

clearance of 1.0 inch between the motor of the fan operated venturi and local

furnishings is kept.

• Peel back the sound dampening material sufficiently to visually inspect the skin in the

vicinity of the fasteners and other attachments. It is not necessary to remove the sound

dampening material.

• Inspect the skin, as far as is possible, for cracks, signs of corrosion and deterioration

of the protective treatment.

• Comply with instructions in:

• NTM 53-10-101.

• NTM 53-10-102.

Structural


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• NTM 53-10-103A.

• NTM 53-10-104.

• NTM 53-10-106.

Chapter 52 - Doors

520002 Baggage pannier loading door/upper hatch warning system (if fitted) OR External

baggage unit (EBU) (750 airplanes ONLY).

• Test for correct operation (Ref. AMM 52-30-05).

NOTE

This test is only applicable to airplanes with a baggage pannier in place of the

ventral fuel tank OR 750 airplanes with external baggage unit.

C1

520003 Baggage pannier door (if fitted) OR External

baggage unit (EBU) (750 airplanes ONLY).

Inspect (Ref. AMM 52-30-05):

• The door seal for damage, distortion and maintained shape profile.

• Seal for adhesion to the door lip.

• Seal to door surround interface for potential leakage.

• Door surround surface for damage which would prevent good sealing.

NOTE

This test is only applicable to airplanes with a baggage pannier in place of the


C3

520004 Main entry door "not locked" warning microswitches .

• Energize the dc busbars (Ref. AMM 12-24-00, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

• With the main entry door open, operate the "door not closed" microswitch.

• Make sure the "ENT DOOR UNLOCKED" annunciator on the Master warning System

panel remains on.

NOTE

If the annunciator goes off, then investigate the 'door lock 'microswitch for

seizure in the operated position.

• Release the "door not closed" microswitch.

• De-energize the dc busbars.

C6

520005 Escape hatch release mechanism. Check the operating load using the external push

button (Ref. AMM 52-20-00).

B6

520006 Escape hatch seals. Inspect for total seal contact with airframe structure to prevent

ingress of rainwater when the cabin is unpressurized.

B6

520007 Entry door. C6


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• Inspect seal for deterioration and damage.

• Check internal handle operating loads (Ref. AMM 52-11-00, select 750, 800XP,


520008 12 years then every 8 years.

Main entry door.



Structural


Escape hatch.

Access: Trim removed.

• Detail inspect the structure internally and externally for cracks, signs of corrosion and

the deterioration of the protective treatment.

Structural

520010 Main Entry Door - Folding Handrail (if fitted). Inspect:

• 800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 52-15-00, 601).

• 750 airplanes (Ref. MMA 52-15-00, 601).

• 900XP airplanes (Ref. MMA 52-15-00, 601).

C6

520011 External Baggage Unit (EBU) loading Door (750 Airplanes).

• Do a detailed visual inspection of the baggage door latch and pin assemblies.

B7

Chapter 53 - Fuselage


Skin exterior under the dorsal intake, forward of Frame 19.

Access: Dorsal intake removed.

• Detail inspect for cracks, signs of corrosion and deterioration of the protective

treatment.

• Detail inspect for chafing rivets.

Structural


Fuselage skin under wing-to-fuselage fairings.

Access: Panels F124 and F224 removed.

• Inspect visible areas of skin for cracks and signs of corrosion using flashlight, mirror

Structural


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and borescope probes.

530003 This task is NOT APPLICABLE to the Hawker 750 airplane or 750 airplanes with the

Ventral baggage pannier installed in place of the Ventral fuel tank.

Between 15 to 18 years, then every 8 years.

Fuselage skin covered by the ventral fuel tank.

Access: Ventral fuel tank removed.

• Detail inspect especially for signs of corrosion and deterioration of protective

treatments.

• Detail inspect attachment points and links.

Structural

530004 This task is NOT APPLICABLE to the Hawker 750 airplane or 750 airplanes with the

Ventral baggage pannier installed in place

of the Ventral fuel tank.


Ventral fuel tank and attachments.

Access: Ventral fuel tank and tank access panels removed 800XP (Ref. AMM 28-10-15),

800XP/850XP Pro Line 21 (Ref. AMM

28-10-15) and 900XP (Ref. AMM 28-10-15).

• Detail inspect the tank internal structure, skin, access panels, bolts and fasteners,

fuel system components and pipelines.

• Pay particular attention to the security of the nylon vent pipes and the integrity of the

sealant fillets at the pipe joints.

• Inspect the rubber drain non-return valve in the vent system balance pipe for

deterioration and splitting.


• Detail inspect the fuel seal block assembly (P/N: 25-8PT341-1A) at the ventral tank

diaphragm for missing sealer, voids and corrosion.

NOTE

If missing sealer, voids or corrosion are found, remove the fuel seal block

assembly for further detailed inspection.

Structural


Fuselage skin covered by the ventral baggage pannier or EBU (750 airplanes) (if fitted).

Access: Ventral baggage pannier removed or EBU (750 airplanes) (if fitted) removed.

• Detail inspect, specially for signs of corrosion and signs of deterioration of the

protective treatments.


Structural


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NOTE

This task is only applicable to airplanes with a baggage pannier in place of the



Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted) internal structure.

Access: Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted) removed. All

doors open and access panels

removed.

• Detail inspect the pannier internal structure.


NOTE

This task is only applicable to airplanes with a baggage pannier in place of the


Structural

530007 12 years and then every 8 years.

Wing to fuselage attachment links, brackets and bolts.

Access: Panels F124, F224 and W501 removed.

• Detail inspect links, brackets and bolts for cracks, signs of corrosion, fretting and

wear (Ref. AMM 53-40-01, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

Structural

530009 27,000 flights and then every 4500 flights.

Fuselage lap joints.



Structural

530010 Whenever the wings are separated from the fuselage.

Access: Wings separated from the fuselage.

• Detail inspect the skin of the fuselage in the area that is covered by the wing

structure.

• Detail inspect the wing attachment brackets and the frame build-up at frames 13 and

16.

• Detail inspect the drag spigot bearing.

• Inspect the drag spigot housing.

Structural

530011 Every 4 years.

Front face of rear pressure bulkhead (Frame 19).

• Inspect left-hand side of bulkhead with the soundproofing blankets removed.

NOTE


Mod. 25G726B/C. When installing local furnishings, make sure there is a minimum

clearance of 1.0 inch between the motor of the fan operated venturi and the local

Structural


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furnishings.

• Look for signs of corrosion at the boundary angle to Frame 19 joints.

NOTE

If you find any defects, extend the inspection to include the right-hand side of the

bulkhead.


Front face of rear pressure bulkhead (Frame 19).

• Inspect right hand side of bulkhead with soundproofing blanket removed.

NOTE


Mod. 25G726B/C. When installing local furnishings, make sure a minimum

clearance of 1.0 inch between the motor of the fan operated venturi and local

furnishings is kept.

• Look for signs of corrosion at the boundary angle to frame 19 joints.

Structural

530013 Every 10,000 flying hours.

Pylon engine main mounting attachment fittings.



Structural


Rear engine mount fittings.



Structural


Vertical stabilizer root attachment to fuselage.



Structural


Engine beam.

Access: Engines and engine main mounting attachment fittings removed (Ref. AMM 71-

20-00, 401, select, 750 800XP, 800XP/850XP Pro Line 21 or 900XP).

NOTE

The pylon firewall below the engine front mount assembly and the inside of the

engine pick-up mount bracket can be visually inspected from inside the pylon

access panels. The ends of the engine beam with all the doublers and angles can

be inspected from inside the rear equipment bay area.

Structural


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• Detail inspect the multi-layer ends of the beam forming pick-ups for damage, cracks

and signs of corrosion using X 10 magnification.

530017 Whenever the brackets are removed from the engine.

NOTE

This task is only required when the engine has accomplished a Major Periodic

Inspection. Refer to the relevant Honeywell Light Maintenance Manual:

750, 800XP and 800XP Pro Line 21 - TFE731-5BR-1H Series engine. 900XP - TFE731-

50R-1H Series engine.

Forward engine mounting brackets, Part No. 3071071-3.

Access: Engine cowlings M1L, M2R, M3L and M4R removed.

• Remove the mounting brackets.

• Inspect for cracks using a magnetic particle inspection (LMM 72-00-06).

Structural

530018 4800 flying hours, then every 2400 flying hours.

Fuselage skin adjacent to cabin window cutouts.

Detail inspect skin.

Structural

530019 PATS APU GTCP36-150W.

Every 12 months.

NOTE

If any of the following inspections show an abnormal indication or requires the

replacement of structural parts, do Tasks 530022 and 530023.

Detail inspect the following items accessible without removal from the rear equipment

bay, for cracks orfailures:

• All APU support structure external to the fire enclosure.

• Remove the oil filler door and all access covers in the bottom enclosure and inspect

all the APU structure internal to the fire enclosure.

• Inspect the main engine crossbeam and frame 21 in the areas immediately adjacent

to the APU attachment fittings.

• Inspect the five pairs of isolator mounts for deterioration of the silicone rubber.

Visually check on the exterior of the fuselage and make sure that the APU exhaust duct

is centered in the exhaust shroud duct, and that the exhaust shroud duct is centered in

the skin cutout for the APU exhaust.

Structural


Every 3000 APU running hours.

APU Support Structure:

• Detail inspect all mounting parts for cracks or damage.

• Detail inspect all fuselage attachments point for cracks or damage.

NOTE

Repair as required.

Structural



Structural


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NOTE

Do this task in conjunction with the removal of the APU for the Hot Section

inspection (Out of Phase Task # 490006).

• Remove and detail inspect the items listed in Table 1 (Located after Area F4

inspections).

NOTE

Replace all parts with the evidence of any damage.



NOTE



• Detail inspect the fuselage structure for cracks, particularly the support bracket

attachment holes in the upper cap of the main engine cross beam and at the top and left

side of the fuselage at frame 21.

NOTE

The attachment brackets secured to the airframe will have to be removed so that a

detailed inspection of the holes drilled in the airframe for the APU fitting can be

done.

Structural


Every 22,500 APU running hours.

APU support hardware listed in Table 2 (Located after Area F4 inspections)

• Do a fluorescent penetrant inspection (FPI) (Ref. NTM 125, General Techniques, Part

C Liquid Penetrant).

OR

• Replace.

NOTE

FPI using MIL-1-25135C, Group 6A penetrant. Reject all linear indications.



Structural


Every 10,000 flights.

Exhaust and inlet doubler frames and stringers.

• Detail inspect internally and externally for minute cracking conditions or other defects

particularly near the exhaust.

NOTE

Repair as required.

Structural

530026 Between the 15 th and 18 th year of aircraft operation and then every 8 years.

External Baggage Unit (EBU) (750 airplanes ONLY) forward and aft attachment fittings:

• Do a detailed visual inspection.

Structural


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530027 Fuselage Skin.

• Do a visual inspection.

G

Chapter 55 - Stabilizers


Elevators and Tabs:

• Remove elevator (Ref. AMM 27-30-22, 401, select, 750, 800XP, 800XP/850XP Pro

Line, 900XP).

• Detail inspect.

• Inspect the bearings for smooth operation and replace as required.

• Detail inspect the hinge brackets for security and cracks with a X 10 magnifier. Look

for signs of corrosion.

• Install elevator (Ref. AMM 27-30-22, 401, select 750, 800XP, 800XP/850XP Pro Line

21 or 900XP).

Inspection completed at..................... Hrs. Date..........................

Structural


Elevator trim tabs, connecting rods:

• Inspect the rod end bearings for smooth operation and replace as required.

• Apply a coat of silicone lubricant to both exterior surfaces of the bearing at each

connecting rod end (Ref. AMM 27-30-00, 301, select 750, 800XP, 800XP/850XP Pro Line

21 or 900XP).

NOTE

The silicone lubricant is applied to give the rod end bearing protection against

corrosion.

Structural


Elevators.

Access: Refer to relevant NTM Technique.

• Comply with instructions in NTM 55-20-101 and NTM 55-20-102.

• If corrosion is found extend the X-Ray coverage until a complete rib bay is found to be

free from corrosion.

Structural


Rudder and Tab:

• Remove (Ref. AMM 27-20-23, 301, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP).

• Detail inspect.

• Inspect the bearings for smooth operation a replace as required.

Structural


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• Install (Ref. AMM 27-20-23, 301, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP).


Connecting rods, rudder trim tab and anti-servo tab:

• Inspect the rod end bearings for smooth operation and replace as required.

Structural


Rudder.



Structural


Rudder hinge brackets and attachments.

Access: Rudder and rudder hinge bracket cover plates removed.

• Detail inspect the rudder hinge brackets, using a X 10 magnifier.

Structural

550008 Horizontal stabilizer to vertical stabilizer rear attachment fitting.

• Inspect for signs of corrosion, paying special attention to the condition of the outboard

flanges and webs.

NOTE

For corrosion limits refer to Beechcraft Corporation.

Structural


Horizontal stabilizer.

Access: Leading edges removed. Elevators removed. Shroud panels T21R, T22L, T23R,

T24L, T25R, T26L and T45 removed.

Fairing panels T4L, T4R, T5, T6L, T7R, T8L, T9R and T13 removed.

• Detail inspect the front face of the front spar for cracks and signs of corrosion.

• Detail inspect the rear face of the rear spar for cracks and signs of corrosion.

• Detail inspect the vertical stabilizer to horizontal stabilizer attachment fittings.

• Detail inspect the elevator hinge brackets.

• Apply Corrosion Preventive Compound (Ref. AMM 55-13-00, 301, select 800XP or

800XP/850XP Pro Line 21).

NOTE

Application of Corrosion Preventive Compound is ONLY applicable to the series

800XP and 800XP/850XP Pro Line 21 airplanes.

Structural


Vertical stabilizer.

Access: Leading edge panels, upper vertical stabilizer and rudder removed.

• Detail inspect the structure rendered visible.

• Detail inspect the rudder hinge brackets for security, cracks and signs of corrosion.

• Comply with instructions in:

Structural


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• NTM 55-30-101.

• NTM 55-30-102.

• NTM 55-30-103.

• With the leading edge removed detail inspect the internal structure of the vertical

stabilizer for cracks and signs of corrosion using a borescope probe through the access

holes in the front spar and through the root rib.

550011 16 years, then every 8 years (see NOTE).

Horizontal stabilizer to vertical stabilizer attachments. Access: Horizontal stabilizer

removed.

NOTE

Airplanes which have had the horizontal stabilizer removed at or subsequent to

the 12 year inspection can be considered to have satisfied the initial inspection

requirement.

• DETAIL INSPECT THE ATTACHMENT LUGS FOR CRACKS, SIGNS OF

CORROSION AND ELONGATION OF THE ATTACHMENT BOLT HOLES.

• INSPECT THE BOLTS FOR SIGNS OF WEAR OR CORROSION.

• REPLACE ANY WORN BOLTS. IF HOLES ARE ELONGATED REPLACE BOLTS,

SEE SRM 55-10-41.

550012 24 years and then every 8 years. Horizontal stabilizer. Access: Refer to relevant NTM Techniques. NOTE For convenience and improved access it is recommended that this inspection is done when the horizontal stabilizer is removed for the inspection of the attachment lugs (Task No. 550011). • Comply with instructions given in one of the methods below: • Fokker Bond Test, NTM 55-10-104A. • Schlumberger Sonatest NTM 55-10-104B. • Staveley Sonic Bondmaster NTM 55-10-104C.

Structural

550013 Between 15 to 18 years, then every 8 years. Horizontal stabilizer. Access: Refer to relevant NTM Techniques. • Comply with instructions in: • NTM 55-10-101. • NTM 55-10-102. • NTM 55-10-103. • NTM 55-10-105.

Structural

550014 15,000 flights and then at every X-Ray inspection of the horizontal stabilizer

internal structure (Task No.550013). Horizontal stabilizer top skin "T" fitting and joint strap at the center line of the stabilizer. Access: Upper vertical stabilizer removed. • Detail inspect for cracks and signs of corrosion.

Structural

550015 Every 2 years. Elevators:

Structural


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• Remove and inspect mass balance weight side plates, look for signs of corrosion (Ref. AMM 27-30-91, 601, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). • Remove and inspect mass balance weights, spigots and installation, look for signs of

corrosion (Ref. AMM 27-30-91, 601, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP). NOTE Remove all corrosion found from the spigots to a maximum depth of 0.03 in. and

paint with epoxy primer (Ref. AMM 125/H-20, 20-95-401, Item No. 474). NOTE If excessive corrosion is found contact: Repair Design Office Beechcraft Corporation 9709 East Central P.O. Box 85

Wichita, KS 67201-0085, U.S.A

• Assemble the spigots and mass balance weights (Ref. AMM 27-30-91, 601, select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP). • Apply corrosion preventive compound LPS 3 (Ref. AMM 125/H-20, 20-95-11, Item No. 089) or ACF 50 (AMM 125/H-20, 20-95-11, Item No. 090) (Ref. AMM 27-30-91, 601, select

750, 800XP, 800XP/850XP Pro Line 21 or 900XP). • Install the side plate assembly (Ref. AMM 27-30-91, 601, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). NOTE The balance of the elevator must be checked and if necessary adjusted only when a repair has been done or a paint finish changed. CAUTION Make sure that the mass balance weights are installed on the same side that they were removed from.

Chapter 56 - Windows

560004 Windows dry-air system filter (if fitted). • Inspect the filter element (Ref. AMM 56-00-00, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

C6

560005 Passenger cabin windows. • Satisfactory condition of seals and no signs of moisture ingress. • If you find moisture, renew Silica Gel crystals and verify seal integrity (AMM 56-00-00). NOTE Pre Mod. 25G360A ONLY.

B4

560006 Windshield panel 'C' Silica Gel container. • Inspect Silica Gel crystals for discoloration. • Renew as necessary.

560007 Screen heat circuit breakers. • Do a visual inspection for heat distress, discoloration and deformation (Ref. AMM 30-41-00, 501 select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP)

Chapter 57 - Wings

570001 Flap hinge fittings. Inspect. NOTE

B9


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Inspect the bolt head on the bottom skin of the flap (in the area of the inboard

hinge) adjacent to flap screw jack carriage grease fitting for damage caused by

chafing. If damage is found, replace the bolt. NOTE For details of the repair kit refer to Beechcraft Corporation Technical Support (1.800.429.5372 OR 316.676.3140).

570002 Flap hinge fittings. Inspect. NOTE Inspect the bolt head on the bottom skin of the flap (in the area of the inboard

hinge) adjacent to flap screw jack carriage grease fitting for damage caused by

chafing. If damage is found, replace the bolt. For details of the repair kit refer to Beechcraft Corporation Technical Support (1.800.429.5372 OR 316.676.3140).

B10

570003 The internal structure of the wing in the area of Ribs 0 to 4. • Detail inspect. • Look for signs microbiological contamination and corrosion. NOTE If corrosion or microbiological contamination is found: • PROGRESSIVELY EXTEND THE DETAIL INSPECTION, BY VISUAL MEANS OR X-RAY TECHNIQUE, FORWARD OF THE CENTRE SPAR AND OUTBOARD OF RIB 4 UNTIL A CLEAN BAY RIB IS FOUND. • REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND DETAIL INSPECT

INTERNALLY. • DO THE SHOCK PREVENTATIVE PROCEDURE (REF. AMM 28-10-00, PAGE

BLOCK 701).

F9

570004 Applicable to Mod. 259071A airplanes only. Flap skin protection panels (if fitted). Remove panels and inspect the flap skin for

corrosion and deterioration of the protective treatment. NOTE Mod. 259071A introduces protective skins on the flap inboard underside for rough

runway protection.

F9

570005 The internal structure of the wing in the area of Ribs 0 to 4.

• Detail inspect.

• Look for signs microbiological contamination and corrosion.

NOTE

If corrosion or microbiological contamination is found:

• PROGRESSIVELY EXTEND THE DETAIL INSPECTION, BY VISUAL MEANS OR X-

RAY TECHNIQUE, FORWARD OF THE CENTRE SPAR AND OUTBOARD OF RIB 4

UNTIL A CLEAN BAY RIB IS FOUND.

• REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND DETAIL INSPECT

INTERNALLY.

• DO THE SHOCK PREVENTATIVE PROCEDURE (REF. AMM 28-10-00, PAGE

BLOCK 701).

F10

570006 Applicable to Mod. 259071A airplanes only.

Flap skin protection panels (if fitted). Remove panels and inspect the flap skin for

F10


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corrosion and deterioration of the protective treatment.

NOTE

Mod. 259071A introduces protective skins on the flap inboard underside for rough

runway protection.


Wing bottom skins and stringers between the front and rear spars, Rib 0 to Rib 1 and

between the center spar and rear spar from Rib 1 to Rib 4.



• Detail inspect the bottom stringers in the vicinity of the wing skin restraint ties with the

aid of a

flashlight and mirrors.

NOTE

If corrosion is found while doing NTM 57-30-101, extend the X-Ray coverage (NTM

57-30-102) until a complete rib bay is found to be free from corrosion.

NOTE

If the quality of the radiographs is impaired by the presence of pockets of fuel it

would indicate that the internal fuel drain paths are blocked. Operators are advised

to remedy this condition at the first convenient opportunity.

Structural

570008 8 years, then every 4 years. Main Landing Gear and sidestay attachment fittings. Access: Panels W324, W424 removed. • Detail inspect the landing gear pick-up fittings, specially the sidestay pick-up, for cracks,

signs of corrosion and signs of movement. • Make sure the drain holes are unobstructed. • Check the tightness of all securing bolts.

Structural

570009 4800 flying hours, then every 1200 flying hours. Wing bottom skin (LH and RH) adjacent to flap outboard hinge at Rib 8. Access: Hinge fairings, panels W314 and W414, removed. • Detail inspect for cracks and signs of corrosion.

Structural

570010 Every 4800 flying hours or 8 years, whichever is the sooner. Wing front spar, forward face. Access: Wing leading edges removed. • Detail inspect for cracks, signs of corrosion and distortion, specially between Ribs 1

and 3. • Inspect leading edges for cracks, signs of corrosion, damage and integrity of the bolt

holes. NOTE When replacing the leading edges the profiles must be maintained (see SRM 57-41-00).

Structural

570011 4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying hours or 4 years. Wing rear spar, rear face. Access: Ailerons, aileron shrouds, flaps and airbrakes removed. • Inspect for cracks, signs of corrosion, distortion and damage. • Inspect control surface hinge brackets on the rear spar for wear, cracks, signs of

corrosion and

Structural


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security. 570012 4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying

hours or 4 years. Airbrakes. Access: Airbrakes removed. • Detail inspect. • Inspect the hinges for security.

Structural

570013 Every 2400 flying hours or 4 years, whichever is the sooner. Ailerons: • Remove (Ref. AMM 27-10-31, 401, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP). • Detail inspect. • Inspect the bearings for satisfactory condition and make sure there is adequate

lubrication (Ref. AMM 125/H-20, 20-09-22, 201). • Install (Ref. AMM 27-10-31, 401, select 750, 800XP, 800XP/850XP Pro Line 21 or

900XP).

Structural

570014 Every 2400 flying hours or 4 years, whichever is the sooner. Connecting rods, aileron trim and servo tabs. • Lubricate or replace the front and rear rod end bearings, as required (Ref. AMM 125/H-20, 20-09-22, 201). • Apply a coat of silicone lubricant to both exterior surfaces of the bearing at each trim

tab connecting rod end (Ref. AMM 27-10-00, 501, select, 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP). NOTE

The silicone lubricant is applied to give the rod end bearing protection against corrosion.

Structural

570015 4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying hours or 4 years. Ailerons. Access: Refer to NTM Technique. • Detail inspect the hinge brackets with a X 10 magnifier. • Comply with instructions in NTM 57-50-107.

Structural

570016 4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying hours or 4 years. Flaps and flap vanes. Access: Refer to relevant NTM Technique. • Inspect hinge brackets for security, freedom from cracks and signs of corrosion. • Inspect bearings for satisfactory condition and adequate lubrication. • Comply with instructions in NTM 57-50-105 and NTM 57-50-106.

NOTE If corrosion is found during the X-Ray inspection, extend the X-Ray inspection

coverage until a complete rib bay is found free of corrosion.

Structural

570017 24,000 flying hours and then every 4800 flying hours. Wing bottom skin at attachment to front spar, between Ribs 1 and 7. Access: As visible. • Detail inspect for cracks and signs of corrosion.

Structural

570018 24,000 flying hours and then every 9600 flying hours. Wing bottom skin centerline joint strap. Access: Keel skid removed.

Structural


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• Detail inspect for cracks and signs of corrosion. 570019 24,000 flying hours and then every 9600 flying hours.

Upper surface of the wing bottom skin at the attachment to the centerline joint adjacent to Rib 0. Access: Refer to NTM Technique. • Comply with instructions in NTM 57-30-104. OR 24,000 flying hours and then every 7200 flying hours. • With the sealant removed to expose the skin surface, detail inspect for cracks at the

bolt line.

Structural

570020 24,000 flying hours and then every 12,000 flying hours. Wing bottom skin centerline butt strap and center section beams (24 positions). Access: Refer to NTM Technique. • Comply with instructions in NTM 57-00-102.

Structural

570021 Whenever the wings are separated from the fuselage. Wing top skin in the area that is covered by the fuselage structure and main attachment brackets. Access: Wings separated from the fuselage. • Detail inspect the skin, stiffeners and main attachment brackets for cracks, signs of

corrosion, security of rivets and damage. • Inspect the drag spigot for wear. • Inspect the spigot location plate for security of attachment.

Structural

570022 Every 4800 flying hours. Rear spar, rear face between Rib 1 LH and Rib 1 RH. Access: Main landing gear doors and panels W325, W425, W507 and W508 removed. • Detail inspect the rear face of the rear spar.

Structural

570023 Every 4 years. NOTE

Applicable to airplanes without BC Winglets. Aileron horn balance weight. Access: Aileron horn balance weight cover removed. • Detail inspect the horn balance weight for signs of corrosion. • If signs of corrosion are found, then do an X-Ray inspection


Structural

570024 12,000 flying hours, then every 7200 flying hours. Wing bottom skin at attachment to Rib 1 LH and RH. Access: As visible. • Detail inspect the skin where it is bolted to Rib 1 LH and RH.

Structural

570025 Every 4800 flying hours. Wing bottom skin at attachment to the rear spar, between Rib 1 LH and Rib 1 RH. Access: Main landing gear doors open and keel skid fairing in the area of the main

landing gear doors removed. • Detail inspect the skin where it is bolted to the rear spar, between Rib 1 LH and Rib 1

RH.

Structural

570026 Every 4 years. Wing leading edges. Access: TKS panels removed (also any material that might interfere with visual

inspection). Inspect, specifically rebate area for cracks and signs of corrosion (Ref. SRM 57-41-12,

Structural


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201). 570027 Every 4800 flying hours or 8 years, whichever is the sooner.

Wing internal structure forward of the center spar including the front and center spars from Ribs 0 to 4, and between and including the front and rear spars from Rib 4 to the wing tip. Access: Wing leading edges W102, W120, W130, W202, W220,W230 removed. Front spar access panels W301, W302, W303, W304, W305, W401, W402, W403, W404, W405 removed. Rear spar access panels W115, W116, W117, W215, W216, W217 removed.

NOTE Rear spar access panels W114 and W214 need not be removed for this inspection unless required for other work in the area. Top skin panels W106, W108, W112, W119, W206, W208, W212, W219 removed. Bottom skin panels W306, W308, W309, W310, W312, W313, W329, W330, W406, W408, W409, W410, W412, W413, W429, W430 removed. • Detail inspect the internal structure, as visible. • Inspect for signs of corrosion and microbiological contamination. • Detail inspect the bottom stringers in the vicinity of the wing skin restraint ties with the

aid of a flashlight and mirrors. NOTE

If corrosion or contamination is found, clean and repair in accordance with the Structural Repair Manual. Do the shock preventative treatment (Ref. AMM 28-10-00,

701, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). Fuel system non-return valves in inner and outer wings. • Remove and inspect (Ref. AMM 28-20-32, 401, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP). • Pay particular attention to the condition of the valve and valve seat.

Structural

570028 4800 flying hours or 8 years, whichever is the sooner, then every 4 years. NOTE

Applicable to airplanes without BC Winglets. Aileron at outboard hinge casting. • Do the "Aileron Horn" Inspection/Check: 750 (Ref. AMM 27-10-31, 601), 800XP (Ref. AMM 27-10-31, 601) and

800XP Pro Line 21 (Ref. AMM 27-10-31, 601).

Structural

570029 Applicable to Airplanes with BC Winglets. Every 300 hours. Wing Outer, Upper and Lower Skins. • Visually inspect between Ribs 14 and 16 around the fasteners for cracking in the skins.

NOTE Pay particular attention to those fasteners installed between the front and rear spars.

Out of Phase

570030 Applicable to Airplanes with BC Winglets. Rib 16 and spar fitting where the winglet is attached to the wing. Access: Remove winglet (Ref. SRM 57-30-12, 201)

NOTE It is recommended to re-apply the corrosion preventive treatment every 2 years. Refer to SRM 57-10-19, 201 and inspect for signs of corrosion. If corrosion is found, and

beyond limits, contact Repair Design Office or replace the rib.

F9


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570031 Applicable to Airplanes with BC Winglets. Rib 16 and spar fitting where the winglet is attached to the wing. Access: Remove winglet (Ref. SRM 57-30-12, 201)

NOTE It is recommended to re-apply the corrosion preventive treatment every 2 years. Refer to SRM 57-10-19, 201 and inspect for signs of corrosion. If corrosion is found, and

beyond limits, contact Repair Design Office or replace the rib.

F10

Chapter 70 - Standard Practices Engine

NOTE

No Chapter 70 tasks at this time.

Chapter 71 - Power Plant - General

NOTE


Chapter 72 - Engine

720002 Whenever an engine is removed for a Major Periodic Inspection.

Aft cowling, inner fan duct and exhaust duct. Inspect with the aft cowling removed.

Out of Phase

720003 Whenever an engine is removed for a Major Periodic Inspection.

Exhaust nozzle/exhaust pipe V clamp. Detail inspect, particularly for cracks in the weld

lines of the trunnion nut support tubes, using a X 10 magnifier.

Out of Phase

Chapter 73 - Engine - Fuel & Control

730001 PT2 pipelines to fuel computers. Drain any accumulations of water from the drain

points.

B7

Chapter 74 - Engine Ignition

NOTE


Chapter 75 - Engine Air

750001 NOTE This task is only applicable to Hawker 900XP airplanes. Engine Bleed System. • Inspect the bleed air port low pressure (LP) venturi gasket for signs of deterioration,

deep discoloration, cracks or missing pieces of gasket and replace as necessary.

B11

Chapter 76 - Engine Controls

760001 Throttle lever controls. • Correct operation of the gust lock operated thrust lever baulk. (Ref. AMM 27-72-00, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

B4

760002 Engine power control cables. Check cable tensions are correct (Ref. AMM 76-10-00). C5


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760003 After 200 flying hours and not more than 300 flying hours from the airplane build or after Control Cable replacement. Control cables. Check the tensions of the: Power control cables (Ref. AMM 76-10-00, 501, select 750, 800XP, 800XP/850XP Pro

Line 21 or 900XP).

Out of Phase

760004 Do any lubrication requirement for Area M1/M2, refer to Part 7 - LUBRICATION. Out of Phase

Chapter 77 - Engine Indicating

NOTE


Chapter 78 - Engine Exhaust

780001 Link arm assemblies (8 off). • Remove the link arms (Ref. AMM 78-31-10). • Inspect the attachment bolts (16 off), particularly for signs of corrosion and/or seizing. • Replace any bolts that show signs of corrosion and/or seizing. • Lubricate the bolt shafts and threads before installation, using a dry film lubricant to

specification MILPRF- 907, C5-A (non-aerosol) Item 084 (Ref. AMM 20-95-11). • Install the link arms (Ref. AMM 78-31-10).

B11

780002 Reverser door seals. • Inspect for correct seating (Ref. AMM 78-31-20). • Inspect for cracks and wear. • Make sure the material is pliable.

B11

780003 Thrust reverser stow/deploy microswitches . • Test microswitches coded CWA or CXA (Ref. AMM 78-34-20, 201, select 750, 800XP,

800XP/850XP


C4

780004 Pylon skin panels. • Remove the panels, inspect the fasteners and attachments.

C11

780005 Door link rods and pivot brackets. • Detail inspect (Ref. AMM 78-31-10, 601).

C11

780006 Thrust reverser lever baulk mechanism. • Deploy each thrust reverser in turn. • Make sure that the baulk release lever of the reverser system which is not deployed

stays down and does not show any tendency to lift when the solenoid of the deployed system is energized. • Return both thrust reverser to the stowed position.

D4

780009 Thrust Reversers. • Inspect the afterbody and make sure it is correctly attached. • Inspect the doors for corrosion and wear. • Detail inspect the doors for cracks. • Inspect the fan flaps for signs of fatigue and make sure they are correctly attached and

stow completely. • Detail inspect the fan flaps for cracks.

B11

780010 Thrust Reversers. • Inspect the hydraulic lines for signs of leakage. • Inspect the wire harness for any chaffing in the area of the hydraulic control valve.

B7


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780011 Exhaust nozzle. • Detail inspect for cracks.

B11

780012 Hydraulic Lines. • Make sure the hydraulic lines are correctly attached. • Inspect for leaks. • Inspect the sleeving material for signs of chafing.

B11

780013 Wire harness. • Make sure the wire harness in the thrust reverser and afterbody is correctly attached. • Inspect for signs of chafing.

B11

780014 Fan duct. • Inspect for signs of corrosion and fatigue. • Detail inspect for cracks. • Inspect the contour and general condition of the fan duct fairings.

B11

780015 Latch box springs. • Inspect for signs fatigue. • Detail inspect for cracks.

B11

780016 Latch monitoring switches. • Do an operational test (Ref. AMM 78-33-50, ADJUSTMENT/TEST).

B11

780017 Latches and latch receptacles. • Inspect for wear (78-31-35, INSPECTION/CHECK).

B11

780018 Primary (Ref. AMM 78-32-40) and Latch (Ref. AMM 78-32-50) hydraulic actuators. • Inspect for leaks, corrosion or wear. • Detail inspect for cracks.

B11

780019 Throttle Retard hydraulic actuators (Ref. AMM 78-32-30). • Inspect for leaks, corrosion or wear. • Detail inspect for cracks. • Detail inspect the actuator housing at the bearing on the Throttle Retard.

B11

780020 Fan Flap hydraulic actuators (Ref. AMM 78-32-60). • Inspect for leaks, corrosion or wear. • Detail inspect for cracks. • Detail inspect the actuator housing at the bearing on the Fan Flap.

B11

780021 Pylon Plug. • Make sure the pylon plug fairings M17L and M18R are correctly installed and make a

continuous surface with the pylon.

B11

780022 NOTE This task is NOT APPLICABLE to Series 750 and 900XP Airplanes. Door link rods (Part No. 5453003-7 link rods only) . • Do a thickness check, Link rod - corrosion removal limits). 800XP airplanes (Ref. AMM 78-31-10, 601). 800XP/850XP Pro Line 21 airplanes (Ref. AMM 78-31-10, 601).

C11

780023 Bonding Straps - 900XP Airplanes. NOTE

The Bonding Straps run from the after-body bolt circle to an attachment point

inside the pylon. • Check for corrosion, arcing, wear or fretting. • Make sure the end connections are tight to the mounting attachment points.

C11


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Chapter 79 - Engine Oil

NOTE


Chapter 80 - Engine Starting

NOTE


------------ END of Section 3 -----------


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SECTION 4 – PART OF INSPECTION

PART-1 MINOR INSPECTIONS

1. Pre-Flight Inspection

2. Post-Flight Inspection

3. TFE731 Inspections

4. APU Inspections

5. 200 Hour Lubrication


7. 400 Hour Detailed - Walk-Around Inspection


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PART-1

1. Pre-Flight Inspection

050001

Instructional Data

NOTE

Before you proceed with this inspection make sure that you have read and

understood the Introduction section at the front of this schedule.

Completion of Inspection

Aircraft registration: HS - PEK Aircraft Serial No: 258830

Aircraft total airframe hours: Engine total running hours:

Date of completion of inspection: / / Time: /

Checked by: License #:

All Areas. Access: As visible.

For the Pre-Flight Inspection procedures refer to the Hawker 800XP

Ground Handling Checklist, P/N 140-590032-0025

Revision D2: Apr, 2009

Mechanic Inspector

PART-1


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Pre-Flight Checks

Table of Contents

Preamble

A. General

B. Left Nose and Fuselage

C. Nose Landing Gear and Bay

D. Right Nose and Fuselage

E. Right Wing

F. Right Main Landing Gear

G. Right Engine and Nacelle

H. Aft Fuselage — Right Side

I. Empennage (Tail Section) J. Aft Fuselage — Left Side

K. Rear Equipment Bay

L. Left Engine and Nacelle

M. Left Main Landing Gear and Center Keel

N. Left Wing

O. Flight Compartment

P. Vestibule, Passenger Cabin and Toilet Compartment

Q. Final Items

List of Illustrations

General

Figure 1 - Recommended Walk-Around Sequence Airplanes Without Winglets

Figure 2 - Recommended Walk-Around Sequence Airplanes With Winglets


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Figure 1 Recommended Walk-Around Sequence

Airplanes Without Winglets


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Airplanes With Winglets


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Part 1

PRE-FLIGHT CHECKS

Preamble The PRE-FLIGHT CHECKS supersede and replace the PRE-FLIGHT INSPECTION which was

previously listed in the Hawker 800XP AIRCRAFT FLEXIBLE MAINTENANCE SCHEDULE. It is the responsibility of the Flight Crew and Pilot-in-Command to ensure the items contained within

are accomplished before flight. The Flight Crew or appropriately rated maintenance personnel may

accomplish all items. It is recommended that these pages be photocopied and used as a check-off sheet prior to

each flight.

NOTE: Requirements marked with (preceding the check) need only be completed once

daily, before the first flight.

NOTE: These checks should be done prior to and in conjunction with the External Checks

and Internal

Checks listed in the Normal Procedures section of Approved Airplane Flight Manual.

NOTE: Refer to Figure 1 or Figure 2 (as applicable) — Recommended Walk-Around Sequence.

Marked A. General

Check Box

when Complete

(1) Make sure that any defects reported in the technical log or Pilot’s Report have been

cleared or cleared for flight in accordance with the Minimum Equipment List.

(2) Assure that Post Flight Checks have been accomplished. NOTE: Do not remove gear pins.

(3) Remove external covers, plugs, guards, internal control locks (if installed) and stow

correctly


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Marked B. Left Nose and Fuselage

Check Box

when Complete

(1) Make sure the stall detector vane moves freely through the full range of travel. Vane

movement must be smooth and damped.

* (2) Check pitot tube condition, cover removed and hole clear.

(3) Check static plate and static ports for condition; free from dents, corrosion,

contaminants and obstructions.

(4) Check OAT sensor probe for condition.

(5) Check ice detector for condition and rotor movement.

(6) Check external fuselage and flight compartment windows for damage.

(7) Check nose skin, forward of static plate, free from dents, paint bubbles and sealant bulges.

(8) Make sure avionics access door (if installed) is correctly seated and secure.

(9) Check radome for condition and security.

(10) Check condition of nose taxi light lens and bulbs (L and R).

Marked C. Nose Landing Gear and Bay

Check Box

when Complete

(1) Make sure the nose landing gear ground lock is installed in the nose landing gear and

is secure.

(2) Make sure there is no visible damage to doors, nose gear assembly or wheels.

(3) Check the nose gear bay to make sure there is no fluid leakage.

(4) Check condition of wiring and hoses.

* (5) Make sure that the auxiliary hydraulic system reservoir has been checked.

(6) Check nose landing gear doors are closed and manual release is secure.

* (7) Visually check the strut for normal condition.

* (8) Check tires for condition.


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Marked D. Right Nose and Fuselage

Check Box

when Complete

(1) Check radome for condition and security.

(2) Make sure avionics access door is correctly seated and secure.

(3) Check nose skin, forward of static plate, free from dents, paint bubbles and sealant

bulges.

(4) Check static plate and static ports for condition; free from dents, corrosion,

contaminants and obstructions.

(5) Check external fuselage and flight compartment windows for damage.

* (6) Check pitot tube condition, cover removed and hole clear.

(7) Make sure the stall detector vane moves freely through the full range of travel. Vane

movement must be smooth and damped.

(8) Make sure venturi outlet is clear.

(9) Check SAT sensor for condition.

(10) Check external fuselage and windows for damage; overwing emergency exit closed

and flush with fuselage and dorsal air intake cover removed and intake clear.

Marked E. Right Wing

Check Box

when Complete

(1) Make sure that all water has been drained from the center section fuel tank

sumps

(2) Check condition of the wing ice light lens and bulb.

(3) Check condition of overwing fillet fairing.

(4) Check the condition of the external structure of the wing to make sure it is

clean and undamaged; upper and lower surface (no fuel leaks), leading edge, stall strip,

landing and taxi lights (condition of lens and bulbs) and vortilon.

(5) Make sure the vortex generators are secure and not deformed.

(6) Check the overwing fuel cap for security.

(7) Make sure the stall warning system vent (if installed) is clear.

(8) Make sure the NACA vent is clear.


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(9) Check drain vent surge tank drain.

(10) Check condition of strobe and navigation light lens and bulbs/LEDs

(11) Check condition of wing tip.

(12) Check condition of aileron and aileron trim tab.

(13) Make sure there are no foreign objects or debris in the aileron shrouds.

(14) Make sure the aileron moves freely through the full range of travel .

(15) Check condition of flap and air brakes.

(16) Check for damaged or missing static wicks.

Marked F. Right Main Landing Gear

Check Box

when Complete

(1) Make sure main landing gear ground lock is installed in the main landing gear

and is secure.

(2) Visually inspect the side stay components and attach points for security and

make sure there is no visible damage.

* (3) Visually check the strut for normal condition.

* (4) Check tires for condition.

Marked F. Right Main Landing Gear (cont)

Check Box

when Complete

(5) Make sure there is no visible damage to the fairing and main landing gear

doors.

(6) Check the main gear and inside the main gear bay to make sure there is no

fluid leakage.

(7) Check condition of wiring and hoses.


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Marked G. Right Engine and Nacelle

Check Box

when Complete

(1) Check right engine, remove engine cover and make sure there are no visible

oil leaks in the engine intake and cowling and free from foreign objects. WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE

BLADES IF THE FAN IS WINDMILLING. THE BLADES ARE SHARP. STOP THE FAN BY PUSHING

ON THE SPINNER.

(2) Make sure there is no damage to the fan blades when viewed through the

engine intake.

(3) Check P2T2 sensor clean, undamaged and secure.

(4) Make sure the starter generator cooling intake and outlet are unobstructed.

(5) Check general condition of cowling and latches for damage, vents and drain

holes should be clear.

(6) Check engine oil tank quantity and engine oil filter bypass pin .

(7) Make sure there is no damage to the turbine blades when viewed through the

exhaust.

(8) Make sure there are no visible oil leaks in the engine cowling and engine

exhaust areas.

(9) Check engine exhaust drain mast clear, no leaks.

* (10) Make sure the pin is removed from the thrust reverser and the TR is stowed

and is secure.

Marked H. Aft Fuselage — Right Side

Check Box

when Complete

* (1) Check the APU (if installed) exhaust is unobstructed/undamaged.

(2) Check condition of pressure refuelling cap and make sure it is secure . Make

sure the pressure refuelling door is closed and secured.

(3) Make sure the ground power unit access door is secure.

(4) Make sure the oxygen charging port access panel is secure .


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Marked I. Empennage (Tail Section)

Check Box

when Complete

(1) Check condition of tailcone and make sure it is secured and locked and the

vents are unobstructed.

(2) Check condition of tailcone strobe and navigation light lenses and bulbs .

(3) Make sure there is no visible damage to the vertical stabilizer and rudder .

(4) Make sure there is no visible damage to the horizontal stabilizer and elevator .

(5) Check condition of the upper anti-collision light.

(6) Check condition of static wicks, present and undamaged.

Marked J. Aft Fuselage — Left Side

Check Box

when Complete

(1) Check ventral tank (if installed) filler cap for security and make sure the ventral

tank access door is closed and secure.

(2) Check ventral tank (if installed) fairing installed and secure.

(3) Make sure the fire extinguisher pressure relief indication disc for each engine

is intact and the APU fire extinguisher pressure relief indication disc is intact.

(4) Make sure the APU (if installed) inlet is clear and unobstructed.

Marked K. Rear Equipment Bay

Check Box

when Complete

(1) Open hatch to rear equipment bay and check condition of hatch

(2) Check general condition of rear equipment bay

(3) Check the maintenance panel , located next to the hydraulic accumulators

(4) Assure that hydraulic accumulator pressures have been checked. Check for

minimum pressure

(5) Assure that the main hydraulic reservoir contents (dependant on accumulator

pressure)


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have been checked and there are no leaks

(6) Check battery connectors for security

(7) Check computers, connected and secure

(8) Check APU general condition, no leaks

Marked K. Rear Equipment Bay (cont)

Check Box

when Complete

(9) Make sure the fire extinguisher pressure relief indication disc, located in the

rear bay adjacent to the APU is intact

(10) Check stick pusher assembly, general condition/no leaks

(11) Make sure equipment bay light is off and the hatch is closed and latched

securely

Marked L. Left Engine and Nacelle

Check Box

when Complete

(1) Remove engine cover and check exhaust and make sure it is free from

foreign objects

(2) Make sure there is no damage to the turbine blades when viewed through the

exhaust

(3) Make sure there are no visible oil leaks in the engine cowling and engine

exhaust areas

* (4) Make sure the pin is removed from the thrust reverser and the TR is stowed

and secure

(5) Check general condition of cowling and latches for damage, vents and drain

holes should be clear

(6) Check engine oil tank quantity and engine oil filter bypass pin

(7) Check engine exhaust drain mast clear, no leaks

(8) Make sure there are no visible oil leaks in the engine intake and cowling WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE

BLADES IF THE FAN IS WINDMILLING. THE BLADES ARE SHARP. STOP THE FAN BY PUSHING

ON THE SPINNER

(9) Make sure there is no damage to the fan blades when viewed through the

engine intake


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(10) Check P2T2 sensor clean, undamaged and secure

(11) Make sure the starter generator cooling intake and outlet are unobstructed

Marked M. Left Main Landing Gear and Center Keel

Check Box

when Complete

(1) Make sure the main landing gear ground lock is installed in the main landing

gear and is secure


make sure there is no visible damage

* (3) Visually check the strut for normal condition

* (4) Check tires for condition

Marked M. Left Main Landing Gear and Center Keel (cont)

Check Box

when Complete

(5) Make sure there is no visible damage to the main landing gear doors and

fairing


fluid leakage

(7) Check condition of wiring and hoses

(8) Check condition of anticollision light lens and bulb, located on the center keel

(9) Check all antennas attached to keel are secure and undamaged

(10) Make sure that all water has been drained from ventral fuel tank

Marked N. Left Wing

Check Box

when Complete


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(1) Check condition of flap and air brakes

(2) Check for damaged or missing static wicks

(3) Check condition of aileron and aileron trim tab

(4) Make sure there are no foreign objects or debris in the aileron shrouds

(5) Make sure the aileron moves freely through the full range of travel


(7) Check condition of strobe and navigation light lens and bulbs/LEDs

(8) Check drain vent surge tank drain

(9) Make sure the NACA vent is clear

(10) Make sure the vortex generators are secure and not deformed

(11) Check the overwing fuel cap for security

(12) Make sure the stall warning system vent (if installed) is clear

Marked N. Left Wing (cont)

Check Box

when Complete


clean and undamaged; upper and lower surface (no fuel leaks), leading edge, stall strip,

landing and taxi lights (condition of lens and bulbs) and vortilon

(14) Check condition of wing ice light lens and bulb

(15) Check condition of overwing fillet fairing seal

(16) Check condition of the boarding light lens and bulb

(17) Check condition of the main entry door seal/frame, external fuselage and

windows

(18) Make sure that all water has been drained from the center section fuel tank

sumps

Marked O. Flight Compartment

Check Box

when Complete


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(1) Make sure all flashlights function correctly

(2) Make sure the auxiliary hydraulic system handpump handle/rudder gust lock

is properly stowed

(3) Make sure the dump valve lever is set to SHUT

(4) Make sure there is full and free movement of the aileron, elevator and rudder

primary controls

(5) Make sure the oxygen system contents are adequate and the valves are ON

*

(6) With the landing gear ground locks installed, make sure that the emergency

dump valve is properly exercised by operating the auxiliary hydraulic system selector handle several times. Investigate any undue stiffness in operation. On

completion of the check, make sure the selector handle is reset to the fully-in

position

(7) Check protective breathing equipment and portable breathing equipment

(8) Check the airframe anti-icing system tank contents

(9) Check the fuel tanks for required fuel quantities. NOTE: If the airplane will be operated in an area where microbiological

contamination of fuel is likely to exist, it is strongly recommended that regular use is made of fuel

treated with an approved biocidal additive. Refer to Section 2 (Limitations) in the Approved Airplane Flight Manual

Marked P. Vestibule, Passenger Cabin and Toilet Compartment

Check Box

when Complete

(1) Make sure all emergency equipment is on board and properly stowed

(2) Make sure the emergency exit door is secure

(3) Remove the emergency exit internal locking pin (if installed) and stow securely

Marked Q. Final Items

Check Box

when Complete


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(1) Make sure that all access doors and servicing panels are secure

(2) Make sure that any frost, snow or ice is removed, refer to AFM Section 2 for

limitations. Make sure that any accumulation of snow or ice is removed from the

air conditioning system cooling turbine exhaust duct before starting the APU or the main engines

(3) Make sure steering disconnect pin, located between the nose gear torque

link sleeve and the steering sleeve, is secured in place with the quick-release

pin locked. Quick release pin is locked when indicator groove is exposed and

level with the head

(4) Remove the gear pins and stow

------------- END ------------


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PART-1

2. Post-Flight Inspection

050001

Instructional Data

NOTE




Aircraft registration: HS - PEK Aircraft Serial No: 258830


Date of completion of inspection: / / Time: /



For the Post-Flight Inspection procedures refer to the Hawker

800XP Ground Handling Checklist, P/N 140-590032-0025

Revision D2: Apr, 2009

Mechanic Inspector

.


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PART-1

Post-Flight Checks

Table of Contents

Preamble

A. General




E. Right Wing



H. Aft Fuselage — Right Side

I. Empennage (Tail Section) J. Aft Fuselage — Left Side




N. Left Wing



Q. Final Items (Recommended)

List of Illustrations

General

Figure 1 - Recommended Walk-Around Sequence Airplanes Without Winglets

Figure 2 - Recommended Walk-Around Sequence Airplanes with Winglets


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Airplanes Without Winglets


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Airplanes With Winglets


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Part I

Post-FLIGHT CHECKS

Preamble The POST FLIGHT CHECKS supersede and replace the POST FLIGHT INSPECTION which was previously listed in the Hawker 800XP AIRCRAFT FLEXIBLE MAINTENANCE SCHEDULE. It is the responsibility of the Pilot-in-Command and Flight Crew to make sure the items contained

within are accomplished after the last flight of the day. The Flight Crew or appropriately rated maintenance

personnel may accomplish all items. It is recommended these pages be photocopied and used as a check-off sheet

after the last flight of the day.

NOTE: Requirements marked with preceding the check indicate items which have the

potential to

cause delays if not corrected promptly. These items should be rectified immediately after the

last flight of the day in order to avoid any operational delays which could occur before the next

flight.

NOTE: These checks should be accomplished after the completion of the Leaving Airplane

(Terminating

Flight) Checks listed in the Normal Procedures section of the Approved Airplane Flight

Manual.

NOTE: Refer to Figure 1 or Figure 2 (as applicable) — Recommended Walk-Around Sequence

Marked A. General

Check

Box

when

Complete

(1) Install the landing gear ground locking pins

(2) Install the thrust reverser locking pins, if applicable


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Marked B. Left Nose and Fuselage

Check

Box

when

Complete

** (1) Check external fuselage and flight compartment windows for damage

** (2) Check nose skin, forward of static plate, free from dents, paint bubbles and

sealant bulges.

** (3) Check radome for condition and security

Marked C. Nose Landing Gear and Bay

Check

Box

when

Complete

(1) Make sure the landing gear ground locking pin is installed and secure

** (2) Make sure there is no visible damage to the doors, nose gear assembly,

wheels or tires

** (3) Check the nose gear and inside the nose gear bay to make sure there is no

fluid leakage

Marked D. Right Nose and Fuselage

Check

Box

when

Complete

** (1) Check radome for condition and security

** (2) Check nose skin, forward of static plate, free from dents, paint bubbles and

sealant bulges.

** (3) Check external fuselage, flight compartment windows and passenger

windows for damage


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Marked E. Right Wing

Check

Box

when

Complete

**


clean and undamaged; upper and lower surface (no fuel leaks), leading edge,

stall strip, and vortilon


** (3) Make sure the NACA fuel vent is clear



(6) Make sure there is no damage to the top or bottom surfaces of the flap, and

with the flap lowered, that there is no slush, snow or ice trapped between the flap and wing structure

NOTE: Step E. (6) is only applicable following a landing on a runway

covered with deep water puddles, slush, snow or ice

** (7) Check for missing or damaged static wicks

Marked F. Right Main Landing Gear

Check

Box

when

Complete

(1) Make sure the main landing gear ground locking pin is installed and secure



(3) Make sure the main wheel tires are not damaged or excessively worn


doors

** (5) Check the main gear and inside the main gear bay to make sure there is no

fluid leakage

(6) Check the main wheel tie bolt nuts for evidence of loosening

(7) Make sure the extension of the brake wear indicators have been checked


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Marked G. Right Engine and Nacelle

Check

Box

when

Complete

**

(1) Make sure there are no visible oil leaks in the engine intake and engine

cowling. WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE

BLADES IF THE FAN IS WINDMILLING. THE BLADES ARE SHARP. STOP

THE FAN BY PUSHING ON THE SPINNER

** (2) Make sure there is no damage to the fan blades when viewed through the

engine intake


(4) Check general condition of cowling and latches for damage

(5) Make sure the oil bypass indicator (if installed) has not actuated

(6) Check oil tank quantity

(7) Make sure there are no signs of hydraulic fluid leakage from the engine drain

mast

** (8) Make sure there is no damage to the turbine blades when viewed through the

exhaust

** (9) Make sure there are no visible oil leaks in the engine cowling and engine

exhaust areas

Marked H. Aft Fuselage — Right Side

Check

Box

when

Complete

(1) Check the APU exhaust is unobstructed/undamaged

** (2) Check external fuselage for damage

Marked I. Empennage (Tail Section)

Check

Box

when

Complete

(1) Check condition of tailcone

** (2) Make sure there is no visible damage to the vertical stabilizer and rudder

** (3) Make sure there is no visible damage to the horizontal stabilizer and elevator

** (4) Check condition of static wicks, present and undamaged


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Marked J. Aft Fuselage — Left Side

Check

Box

when

Complete

(1) Check the APU intake is unobstructed/undamaged

** (2) Check external fuselage for damage

(3) Make sure the fire extinguisher pressure relief indication disc for each engine

is intact and the APU fire extinguisher pressure relief indication disc is intact

(4) Check drain lines for signs of leakage

Marked K. Rear Equipment Bay

Check

Box

when

Complete

(1) Check general condition of rear equipment bay

(2) Check the maintenance panel (if installed), located next to the hydraulic

accumulators

(3) Make sure the hydraulic system pressure filter differential pressure indicator

button is not protruding

(4) Make sure there are no signs of fluid leakage

(5) Make sure the fire extinguisher pressure relief indication disc, located in the

rear bay adjacent to the APU is intact

(6) Make sure equipment bay light is off and the hatch is closed and latched

securely

Marked L. Left Engine and Nacelle

Check

Box

when

Complete

** (1) Make sure there is no damage to the turbine blades when viewed through the

exhaust

** (2) Make sure there are no visible oil leaks in the engine cowling and engine

exhaust areas

(3) Check general condition of cowling and latches for damage

(4) Make sure the oil bypass indicator has not actuated


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(5) Check oil tank quantity

(6) Make sure there are no signs of hydraulic fluid leakage from the engine drain

mast

Marked L. Left Engine and Nacelle (cont)

Check

Box

when

Complete

**

(7) Make sure there are no visible oil leaks in the engine intake and engine

cowling. WARNING: DO NOT ATTEMPT TO STOP THE FAN BY HOLDING THE

BLADES IF THE FAN IS WINDMILLING. THE BLADES ARE SHARP. STOP

THE FAN BY PUSHING ON THE SPINNER

** (8) Make sure there is no damage to the fan blades when viewed through the

engine intake


Marked M. Left Main Landing Gear and Center Keel

Check

Box

when

Complete

(1) Make sure the main landing gear ground locking pin is installed and secure



(3) Make sure the main wheel tires are not damaged or excessively worn.


doors


fluid leakage

(6) Check the main wheel tie bolt nuts for evidence of loosening

(7) Make sure the extension of the brake wear indicators have been checked

(8) Check all antennas attached to keel are secure and undamaged


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Marked N. Left Wing

Check

Box

when

Complete

(1) Make sure there is no damage to the top or bottom surfaces of the flap, and

with the flap lowered, that there is no slush, snow or ice trapped between the flap and wing structure. NOTE: Step N. (1) is only applicable following a landing on a runway

covered with deep

water puddles, slush, snow or ice.

** (2) Check for missing or damaged static wicks


(4) Check condition of wing tip

Marked N. Left Wing (cont)

Check

Box

when

Complete

** (5) Make sure that NACA fuel vent is clear


**


clean and undamaged; upper and lower surface (no fuel leaks), leading edge,

stall strip, and vortilon.

** (8) Check condition of main entry door seal/frame, fuselage and passenger

windows

Marked O. Flight Compartment

Check

Box

when

Complete

(1) Check condition of lens and bulbs of all external lights. NOTE: APU or external power required


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Marked P. Vestibule, Passenger Cabin and Toilet Compartment

Check

Box

when

Complete

CAUTION: DRAIN ALL OF THE WATER FROM THE WATER SYSTEMS

WHEN THE AIRPLANE IS TO REMAIN ON THE GROUND AND THE AMBIENT TEMPERATURE IS, OR WILL BE, LESS THAN 0 DEGREES C. (1) Make sure all passenger seat safety belts operate correctly and are secure. Check latch, security and wear

Marked Q. Final Items

Check

Box

when

Complete

(1) Make sure the external covers, plugs and guards are installed

(2) Make sure the emergency exit internal locking pin

(3) Make sure all internal gust locks are installed

------------- END ------------


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PART-1

3. TFE731 Engine Inspections

050010

Instructional Data

NOTE




Aircraft registration: Engine Serial No:


Date of completion of inspection:



Aircraft Registration: Total Airframe Hours: Mechanic Inspector

Engine General

Refer to the Honeywell Light Maintenance Manual for ALL routine and

Out of Phase inspection requirements for the TFE731-5BR-1H or the

TFE731-50R-1H engines, as applicable.


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PART-1

TFE731 ENGINE INSPECTIONS

Engine

Items Limitation Mechanic Inspector

Oil and Filter Analysis (SOAP). 200 hours

Chip Detector – Inspector for contamination. 200 hours

DEEC BITE Check 400 hours

Electrical Wiring and Connections – Check for security and

damage. 400 hours

Fan Rotor Assembly Blades – Inspect for foreign object

damage. 400 hours

Fuel Filter Element – Remove and replace. Note: Remove and replace fuel filter element after initial 25

hours of engine operation. 400 hours

Fuel Heater Oil Tubes (Fluid Transfer Tube) Installation – Check for security, broken, clamps, leaks, cracks, cuts, chafing, or rubbing.

400 hours

Plumbing Lines and Connections – Check for security, loose

or broken clamps and brackets, leaks, cracks, cuts, or rubbing. 400 hours

Igniter Plugs and Leads – Remove and inspect plugs. Inspect

leads in place. 1400 hours

Ignition System – Perform Ignition System Operation Check. 1000 hours

Periodic Inspection Intervals

Items Limitation Mechanic Inspector

Major Periodic Inspection (MPI). 2500 hours

Combustion Chamber Plenum Case Periodic Inspection 2500 hours

Accessory Gearbox 5000 hours

Compressor Zone Inspection (CZI). 5000 hours

Fan Support Assembly Periodic Inspection 5000 hours


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PART-1

4. APU Inspection

050020

Instructional Data

NOTE



Area F4: Rear equipment bay and rear fuselage. Access: Rear equipment bay door

open.

Aircraft Registration: Total Airframe Hours: Mechanic Inspector

Auxiliary Power Unit

050181

For ALL Routine and Out of Phase servicing requirements for

the Sundstrand APU, refer to SB-T-62T-49-77 and the

Turbomach APU Maintenance Manual.For Routine and Out of

Phase servicing requirements for the PATS APU Installation

(STC # ST00459NY), refer to this AFMS.


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PART-1

APU INSPECTIONS

Area F4: Rear equipment bay and rear fuselage. Access: Rear equipment bay door open.

Auxiliary Power Unit Mechanic Inspector

490001

Every 1000 flying hours

Visual inspection exhaust for cracks or deformation.

Visual inspection for loose or frayed wires.

Inspect for sign of corrosion.

490002

Every 750 APU running hours

Igniter plug(CMM 49-40-33):

- Remove, clean, inspect and install.

490003

Every 750 APU running hours (SIL No.APU-49)

-SOAP check Oil and Filter element

-Remove, clean, inspect and install magnetic element of

drain

plug(CMM 49-90-46)

490004 Every 1000 APU running hours

Remove and replace Fuel filter element(CMM49-30-52)

490005

Every 4500 APU running hours :

-Fuel flow rate check of Fuel nozzle assembly(CMM49-20-

00,page

block601paragraph5)

490006


-Hot Section Inspection.

-Detailed The inspection on the components listed:

-Turbine Rotor - Deswirl Deflector

- Turbine Nozzle - Airflow Deflector

- Turbine Housing Assembly- Combustion Chamber

- Labyrinth Seal - turbine Wheel Deflector

- Retainer Halves - Containment Ring

490007


- Visual check Compressor Rotor for damage by observation

through the compressor screen openings.


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PART-1

5. 200 hour lubrication

050030

Instructional Data

NOTE Before you proceed with this inspection make sure that you have read and understood the introduction section at the front of this schedule.


Aircraft registration:

Aircraft total airframe hours:


Checked by: License #

General Lubrication

Aircraft Registration: Total Airframe Hours. Mechanic Inspector

Lubrication - ALL Area's

120001 Do any 200-hour lubrication requirements for ALL Area's, refer

to Part 7 - LUBRICATION.


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PART-1


050770

Instructional Data

NOTE


understood the introduction section at the front of this schedule.






General Lubrication

Aircraft Registration: Total Airframe Hours. Mechanic Inspector

Lubrication - ALL Area's

120003 Do any 400 hour lubrication requirements for Area F1, refer to Part 7 - LUBRICATION.

120004 Do any 400 hour lubrication requirements for Area T1, refer to Part 7 - LUBRICATION.

120007 Do any 400 hour lubrication requirements for Area W1/W2,

refer to Part 7 - LUBRICATION.


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PART-1

7. 400 Hour Detailed Walk-Around Inspection

050771

Instructional Data

NOTE

Refer to the Hawker 750/800XP/850XP/900XP Ground Handling Checklist for

information concerning area locations.

NOTE









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PART-1

400 HOUR DETAILED WALK-AROUND INSPECTION

A. Preparation

Check Comments

1. Flaps and airbrakes in "Lift Dump" (Area E and N).

2. Release Accumulator Hydraulic Pressure (Area K) (AMM 12-29-00,

301)

3. Electrical power "OFF" (ALL areas except P) (AMM 24-01-00, 201)

4. Nose landing gear doors open (Area C) (AMM 32-20-42, 301).

5. Main landing gear doors open (Area F and M) (AMM 32-10-01, 201).

6. Control locks removed (Area O).

7. Nose and main landing gear pins installed (Areas C, F and M) (AMM

10-00-00, 201)


050772 Check Comments

1. Make sure the stall detector vane moves freely through the full

range of travel. Vane movement must be smooth and damped.

Check vane condition.

2. Check pitot tube condition, and sense port and drain holes are clear .

3. Check static plate and static ports for condition; free from dents,

corrosion, contaminants and obstructions.

4. Check O.A.T. sensor probe for condition.

5. Check ice detector for condition and rotor movement.

6. Check external fuselage and flight compartment windows for

damage. Check windscreen weather seal for condition.

7. Check nose skin forward of static plate, free from dents, paint

bubbles and sealant bulges.

8. Make sure the avionics access panel (if fitted) is correctly seated and

secure (AMM 34-11-29, 601).

9. Check radome for condition and security.

10. Check condition of nose taxi light lens and bulbs (Left and Right).


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1. Check overall condition of NLG bay.

2. Make sure there is no visible damage to doors, nose gear assembly

or wheels.

3. Check the nose gear bay to make sure there is no fluid leakage

greater than the AMM tolerance.

4. Check condition of nose gear door bond straps.

5. Check condition of wiring and hoses.

6. Check the auxiliary hydraulic system reservoir for correct fluid level

(AMM 12-29-00, 301).

7.

Close nose landing gear doors and check that manual release is

secure

(AMM 32-20-42, 301)..

8. Visually check the strut for normal condition and leakage

(AMM 12-32-00, 301)..

9. Check tires for condition and pressure (AMM 12-32-00, 301).

10. Check the left and right door operating strut bearings for freedom of

movement by twisting the strut using finger pressure only. If the

bearings cannot be rotated replace as required.



1. Check pitot tube condition, and sense port and drain holes are clear .

2. Make sure the stall detector vane moves freely through the full

range of travel. Vane movement must be smooth and damped.


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Check condition of vane.

3. Make sure the avionics access panel is correctly seated and secure

(AMM 34-11-29. 601).

4. Check nose skin, forward of static plate, free from dents, paint

bubbles and sealant bulges.

5. Check static plate and static ports for condition; free from dents,

corrosion, contaminants and obstructions.

6. Check external fuselage and flight compartment windows for

damage. Check windscreen weather seal for condition.

7. Check antennas are secure and undamaged.

8. Airplanes without the digital pressurization control system Mod.

25G726A/C or Mod. 25G726B/C:

Make sure Cabin venturi outlet is clear.

9. Check external fuselage and windows for damage.

10. Check overwing emergency exit closed and flush with fuselage.

11. Check condition of overwing fillet fairing seal.

12. Check S.A.T. sensor for condition.

E. Right Wing


1. Check condition of wing ice light and lens.

2. Make sure all water has been drained from the center fuel tank and

lock sump (AMM 12-28-00, 301).

3. Check the condition of the external upper surface structure of the

wing to make sure it is clean and undamaged (no fuel leaks).

4. Check the condition of the external lower surface structure of the

wing to make sure it is clean and undamaged (no fuel leaks).


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E. Right Wing


5. Check stall strip and vortilon, for damage and condition.

6. Check landing and taxi lights for condition of lens and bulbs.

7. Check wing leading edge and TKS panel for damage and sealant

for condition.

8. Check vortex generators for dents and straightness and overwing

fuel cap for security.

9. Make sure the stall warning system vent (if fitted) is clear, free of

foreign objects and fuel leaks.

10. Make sure the NACA vent is clear.

11. Check vent surge tank is drained and locked.

12. Check condition of strobe and navigation lights and lens.

13. Check condition of wing tip.

14. Check condition of wing tip static wick.

15. Check condition of aileron and aileron trim tab.

16. Check condition of aileron and trim tab bond straps.

17. Check condition of aileron and trim tab static wicks.

18. Make sure there are no foreign objects in the aileron shrouds.

19. Make sure the aileron and trim tab move freely through the full

range of travel.

20. Check condition of flap and air brakes. Make sure that there is no

damage to upper and lower surfaces.

21. Check flap for damaged or missing static wick.

22. Check condition of flap and air brake bond straps.

23. Check Flap bay overall condition and for hydraulic leaks.



1. Visually check the strut for normal condition and leakage (AMM 12-

32-00, 301).


3. Check the main wheel tie bolt nuts for evidence of loosening .


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4. Check the extension of the brake wear indicators (AMM 32-40-114,

601).

5. Make sure there is no visible damage to the main landing gear

fairing and doors.

6. Check condition of gear door bond straps.

7. Check the main gear and inside the main gear bay to make sure there is no fluid leakage or damage.




1. Make sure the starter generator cooling intake and outlet is

unobstructed.

2. Check the engine intake for damage and foreign objects.

3. Make sure there is no damage to the fan blades when viewed through the engine intake.

4. Check P2T2 sensor clean, undamaged and secure.

5. Check general condition of cowling and latches for damage. Vents

and drain holes should be clear.

6. Check engine oil tank quantity and engine oil filter bypass pin (Ref. Honeywell Light Maintenance Manual).

7. Check that the engine drain mast is clear and there are no signs of

fluid leaks.

8. Make sure there are no visible fluid leaks or foreign objects in the engine exhaust (including T/R's and afterbody).

9. Make sure there is no damage to the turbine blades when viewed through the exhaust.

10. Check exhaust duct blister sealant coating for condition.

H. Aft Fuselage - Right Side



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H. Aft Fuselage - Right Side


1. Check upper external fuselage (above engine pylon) for condition

and damage.

2. Check the APU exhaust is unobstructed/undamaged.

3. Check dorsal air intake is clear.

4. Check lower external fuselage (below engine pylon) for condition and

damage.

5. Check condition of pressure refueling cap and make sure it is secure. Make sure the pressure refueling door is closed and

secured.

6. Make sure the ground power unit access door is secure.

7. Make sure the oxygen charging port access panel is secure.

8. Make sure that ventral tank fairing is installed and secure.

I. Empennage (Tail Section)


1. Check condition of tailcone and make sure it is secured and locked and the vents are unobstructed.

2. Check condition of tailcone strobe and navigation light lenses and bulbs.

3. Check condition of the bullet fairing.

4. Check overall condition and for no visible damage to the vertical stabilizer, rudder and trim tab.

5. Check overall condition and for no visible damage to the horizontal stabilizer, elevator and trim tab.

6. Check condition of the upper anti-collision light.

7. Check condition of rudder, rudder trim tab, elevator and elevator trim tab bond straps.

8. Check control surfaces for freedom of movement.

9. Check condition of static wicks; present and undamaged.

10. External Baggage Unit (750 airplanes only): Do a detailed visual inspection of the exposed internal and


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I. Empennage (Tail Section)


external structure.

J. Aft Fuselage - Left Side


1. Check ventral tank (if fitted) fairing installed and secure.

2. Check ventral tank (if fitted) filler cap for security and make sure the

ventral tank access door is closed and secure.

3. Check lower external fuselage (below engine pylon) for condition and

damage.

4.

Make sure the fire extinguisher pressure relief indication disc for each engine is intact and the APU fire extinguisher pressure relief indication disc is intact. NOTE : Applicable to Sundstrand APU.

5. Check drain lines for signs of leakage.

6. Check upper external fuselage (above engine pylon) for condition

and damage.

7. Check the APU intake is unobstructed/undamaged.



1. Open door and check condition of door.

2. Check general condition of rear equipment bay.

3. Check all (T/R, MAIN and EMERG.) hydraulic accumulator pre-charge pressures with hydraulic system pressure depleted.

4. Check the main hydraulic reservoir contents (dependant on

accumulator pressure) and make sure there are no leaks (Ref. AMM

12-29-00, 301).

5. Make sure the hydraulic system pressure filter differential pressure indicator button is not protruding (Ref. AMM 29-10-61, 001).

6. Make sure there are no sign of fluid leakage.

7. Check computer connections are secure.


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8. Check APU general condition, no leaks and APU fire extinguisher pressure. NOTE : Applicable to PATS APU.

9. Check stick pusher assembly, general condition/no leaks.

10. Check elevator elliptical unit for free movement and condition.

11. Make sure that the rear equipment bay light is off and door is closed

and latched securely.



1. Make sure there are no visible fluid leaks or foreign objects in the engine exhaust (including T/R's and afterbody).

2. Make sure there is no damage to the turbine blades when viewed through the exhaust.

3. Check exhaust duct blister sealant coating for condition.

4. Check that the engine drain mast is clear and there are no signs of fluid leaks.

5. Check general condition of cowling and latches for damage. Vents

and drain holes should be clear.

6. Check engine oil tank quantity and engine oil filter bypass pin (Ref. Honeywell Light Maintenance Manual).

7. Make sure the starter generator cooling intake and outlet is unobstructed.

8. Check the engine intake for damage and foreign objects.

9. Make sure there is no damage to the fan blades when viewed through the engine intake.

10. Check P2T2 sensor is clean, undamaged and secure.



1. Visually check the strut for normal condition and leakage (AMM 12-

32-00, 301).



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3. Check the main wheel tie bolt nuts for evidence of loosening .

4. Check the extension of the brake wear indicators (AMM 32-40-114,

601).

5. Make sure there is no visible damage to the main landing gear

fairing and doors.

6. Check condition of gear door bond straps.

7. Check the main gear and inside the main gear bay to make sure there is no fluid leakage or damage.


9. Check condition of the anti-collision light lens and bulb, located on

the center keel.

10. Check all antennas attached to the keel are secure and undamaged.

11. Make sure that all water has been drained from the ventral fuel tank

sump and it is locked (AMM 12-28-00, 301).

N. Left Wing


1. Check condition of flap and air brake bond straps.

2. Check flap for damaged or missing static wick.

3. Check Flap bay overall condition and for hydraulic leaks.

4. Check condition of flap and air brakes. Make sure that there is no

damage to upper and lower surfaces.

5. Make sure the aileron and trim tab move freely through the full

range of travel.

6. Make sure there are no foreign objects in the aileron shrouds.

7. Check condition of aileron and trim tab static wicks.

8. Check condition of aileron and trim tab bond straps.

9. Check condition of aileron and aileron trim tab .

10. Check condition of wing tip static wick.

11. Check condition of wing tip.

12. Check condition of strobe and navigation lights and lens.

13. Check vent surge tank is drained and locked.

14. Make sure the NACA vent is clear.


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N. Left Wing


15. Make sure the stall warning system vent is clear, free of foreign objects and fuel leaks.

16. Check vortex generators for dents and straightness and overwing fuel cap for security.

17. Check wing leading edge and TKS panel for damage and sealant for condition.

18. Check the condition of the external upper surface structure of the wing to make sure it is clean and undamaged (no fuel leaks).

19. Check the condition of the external lower surface structure of the wing to make sure it is clean and undamaged (no fuel leaks).

20. Check stall strip and vortilon, for damage and condition.

21. Check landing and taxi lights for condition of lens and bulbs.

22. Check condition of wing ice light and lens.

23. Check condition of over-wing fillet fairing and seal.

24. Make sure all water has been drained from the center section fuel tank sump and it is locked (AMM 12-28-00, 301).

25. Check condition of main entry door seal/frame, fuselage and

passenger windows.



1. Check condition of seat, seat belts and shoulder harnesses .

2. Check seat adjustment for proper operation.

3. Check flight compartment windows for condition.

4. Make sure all flashlights function correctly.

5. Make sure the auxiliary hydraulic system handpump handle/rudder

gust lock is properly stowed.

6. Check operation of the Dump Valve. Make sure the dump valve

lever is set to SHUT (AMM 21-10-155, 201).

7. Make sure there is full and free movement of the aileron, elevator and rudder primary controls and all three trim controls.

8.

With the landing gear ground locks installed, make sure that the emergency dump valve is properly exercised by operating the auxiliary hydraulic handle several times. Investigate any undue

stiffness in operation. WARNING : On completion of the check, make sure the selector

handle is reset to the fully in position.


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9. Check overall status of the flight compartment.

10. Check the airframe anti-icing system tank contents (AMM 12-30-00,

301).



1. Make sure all emergency equipment is on board and properly stowed.

2. Check the portable breathing equipment for condition and date (AMM 35-35-15).

3. Make sure the emergency exit door is secure.

4.

Make sure all passenger seat safety belts (and settee safety

harnesses ) operate correctly and are secure. Check latch security

and wear. Check seat belt attachment hook and safety clip for

distortion and security.

5. Check cabin windows for condition.

6. Check for signs of water leakage from the lavatory and toilet areas .

7. Check lavatory seat and seat belt (if installed) for condition.

8. Check aft avionics equipment for condition and security.

9. Check the condition of the Galley waste container (MMA 25-30-20,

601).

10.

Check the condition of the lavatory waste container, with particular attention to the correct fit, sealing and latching of the container access door (MMA 25-30-20, 601). NOTE : The lavatory waste container inspection satisfies FAA

AD 74-08-09 R3 repetitive requirements.

R. Final Items


1. Energize the airplane 28 vdc busbars (AMM 24-01-00, 201).

2. Check operation of all external lights and beacons (AMM/MMA

Chapter 33, as applicable).

3. Check the operation of the auxiliary heating valve. (AMM 21-60-105,

201). Functional test steps (2) and (4).


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R. Final Items


4. Make sure the oxygen system contents are adequate (AMM 12-35-

00, 301).

5. Check operation of all emergency lights (AMM/MMA Chapter 33, as

applicable).

6. Check operation of cockpit lighting (Ref. AMM/MMA Chapter 33, as

applicable).

7. Check operation of cabin interior lights (AMM/MMA Chapter 33, as

applicable).

8. Make sure that all access doors and servicing panels are secure.

9. De-energize the airplane 28 vdc busbars.

10. Make sure ALL areas are clean and clear of tools and

miscellaneous items of equipment.

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SECTION-4

PART-2 ROUTINE INSPECTIONS

1. INSPECTION B – 050110

2. INSPECTION C – 050240

3. INSPECTION D – 050370

4. INSPECTION E – 050500

5. INSPECTION F – 050630

6. INSPECTION G – 050760


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PART-2

1. Inspection B

050110

Instructional Data

NOTE Inspection B is the top level inspection which covers the accomplishment of Inspections B1 to B12 inclusive.This must be completed by every 800 hours. Inspection B must only be signed when Inspections B1 to B12 inclusive have been completed. ALL within a single tolerance window.






INSPECTION B (Consists of Inspection B1 to B12 inclusive)

Aircraft Registration:

NOTE This inspection may only be signed off when ALL of the above inspections have been

completed.


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PART-2

INSPECTION B1 050120

Functional Tests

Aircraft Registration: Mechanic Inspector

Bonding Checks

200001 Control surfaces. Do a bonding check (125/H-20, 20-10-

5016).

200002

Refuel point earthing studs (3 off). Do a function test for

bonding resistance to the local structure ( 125/H-20, 20-10-5016).

Air Conditioning

210002 Ram air valve and dump valve.

Do a check/test (AMM 21-10-155, 201).

210003

Environmental control system. Do a function test of the Pressure regulator and shut off

valve (PRSOV) (AMM 21-10-76, 501). PRSOV

Overpressure switch (AMM 21-10-78, 201).

Electrical Power

240002

No.1 and No.2 main static inverters. Operate inverters

and make sure, by feel of hand, of a positive airflow output from the inverter cooling fans.

240009

D.C. generating system. Do a function test of the emergency contactor control

(AMM 24-30-01, 501).

Fire Protection

260002 Rear equipment bay overheat detection system.

Do a functional test (AMM 26-10-00, 201)

Fuel

280001

Fuel Transfer System, Wing tanks. Check fuel flow. Check for positive flow from the LH and the RH wing

tank to the opposite wing tank. NOTE : For positive flow note a 200lb increase in the

fuel gauge indication.

Ice and Rain Protection

300001 Rotary ice detector. Do a function test (AMM 30-80-00,

501).

Lights


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Functional Tests


330003

Anti-Collision light system that has a strobe type

device in any position. Clean the strobe light lenses internal and external. Clean the wing-tip lens covers internal and external. Check the strobe light flash rate ( Flash rate of 60 ± 5

cycles per minute), (AMM 33-40-12, 201). NOTE : Refer to the Component Requirements section

of this manual for the manufacturer's recommended period for replacement and strobe light intensity test procedure.

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PART-2


Functional Tests


Flight Controls

270004 Stall warning and identification system.

Do a functional test of the stall warning and identification

system (AMM 27-33-00).

Do an angle verification check (AMM 27-33-00).

Do an electrical zero check (AMM 27-33-00).

NOTE

The electrical zero check is only applicable to airplanes

with Mod. 25G206A or Mod. 25G206A and Mod. 25G206B.

270008

Rudder bias strut heater muffs.

Do a functional test of the rudder bias strut heater muff

(AMM 27-20-00).

270009 Stall detector unit (third channel).

Do a function test: (AMM 27-33-14).

Oxygen

350004 Transferred to Inspection E2.

350005 Transferred to Inspection E2 .

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PART-2


Area F1: External fuselage, nose cone, tail cone and wing-to-fuselage fairing.

Access: Panel F3 removed. Nose cone F1 open. Tail cone F2 removed.


Area Inspection

050141

(a) Airframe.

(b) Electrical.

(c) Avionics.

NOTE

Make sure ALL area inspections are done in accordance with the Inspection

Requirements.

Windows

560005

Passenger cabin windows:

Satisfactory condition of seals and no signs of moisture

ingress.

If you find moisture, renew Silica Gel crystals and verify

seal integrity ( AMM 56-00-00). Note Pre Mod. 25G360A

ONLY.

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PART-2


Area F2: Flight compartment. Access: As visible.


Air Conditioning

210004

Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C: Manual cabin altitude control valve.

Make sure of full and free movement.

Equipment/Furnishings

250007

Crew Seats.

Do an operational check (CMM 25-11-24, 501 (Check 1)) or

(CMM 25-11-67, 501 (Check 1)).

Flight Controls

270011

Gust lock, ailerons and elevators.

Inspect. Make sure that the bush in the mounting bracket is lightly

lubricated and free from burrs or scores. With the unit in the operated and locked position but without

the engagement of the claw spigots in the control column bushes, check for positive spring pressure on the claws and for initial resistance to movement when releasing the knurled locking ring.

Landing Gear

320022

Brake master cylinders.

Check fluid level and replenish, as necessary (AMM 32-40-

00, 301).

Oxygen

350001

Oxygen system master supply valve: With the oxygen system fully charged and the supply

master valve closed, exhaust system downstream of the valve until the contents gauge indicates zero. After 15 minutes has elapsed, make sure that there is no

increase in the contents gauge indication which would show leakage past the closed valve.

Windows

560006 Windshield panel 'C' Silica Gel container:

Inspect Silica Gel crystals for discoloration.


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Area F2: Flight compartment. Access: As visible.


Renew as necessary.

Engine Controls

760001

Throttle lever controls. Correct operation of the gust lock operated thrust lever

baulk (AMM 27-72-00, 501).

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PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (underfloor). Access: As

necessary.


NOTE No underfloor inspections required at this time.

General Lubrication


120011 Task deleted.

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PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (above floor). Access: Radio compartment access panels removed.


Area Inspection

050171

(a) Airframe.

(b) Electrical.

(c) Avionics.

NOTE

Make sure ALL area inspections are done in accordance

with the Inspection Requirements.


250003

3rd crew members seat (if fitted):

Make sure that the seat stowing action is satisfactory.

Make sure of correct operation and satisfactory condition.

NOTE : To be done at this inspection or at a period

conforming to the requirements of the local regulatory

authority.


300003

Airframe de-icing system pressure filter.

Replace the filter element ( AMM 30-10-52).




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Area Inspection

Water/Waste

380001

Water systems:

Inspect the toilet and galley water systems.

Make sure the flow of water is correct through the normal

and overflow drains and that there are no leaks.

If you find signs of fluid leakage:

Inspect the aileron-cable fuselage pressure-seals and the

adjacent structure in the areas to the rear of frame 16. Do

this to make sure the fluid leakage has drained correctly.

Make sure the drain holes and drain valves are free from

blockages and function correctly. Do this from the inside and

the outside of the fuselage.

Remove all fluid remaining in the area.

Clean the areas where leakage has occurred.

Lubricate the aileron cables if necessary ( AMM 12-20-25).

Replenish the toilet and galley water systems, if required:

(AMM 12-38-00 or MMA Chapter 38 as applicable).

Doors and Hatches

520005 Escape hatch release mechanism. Check the operating load

using the external push button (AMM 52-20-00).

520006

Escape hatch seals. Inspect for total seal contact with

airframe structure to prevent ingress of rainwater when the

cabin is unpressurized.

120012 Do any 800 hour lubrication requirements for Area F3, refer to

Part 7 - LUBRICATION.

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PART-2


Area F4: Rear equipment bay and rear fuselage. Access: As visible with bay door open. panels F169 and F170 removed.


Area Inspection

050181

(a) Airframe.

(b) Engines.

(c) Electrical.

(d) Avionics.

NOTE : Make sure ALL area inspections are done in accordance with the

Inspection Requirements.

Air Conditioning

210005 Cooling turbine exhaust duct drain. Make sure the drain is

free from blockages.

210024

Low limit temperature Control Valve Filter (If installed) . Clean or replace ( AMM 21-60-61, 201). Note This task is

only applicable to airplanes with a Honeywell GTCP36-150W APU, installed to STC ST00459NY.

Hydraulic Power

290003 Suction filter . Replace the element (AMM 29-10-21, 401).

Doors

520011

External Baggage Unit (EBU) loading Door (750 Airplanes)

Do a detailed visual inspection of the baggage door latch

and pin assemblies.

Engine - Fuel and Control

730001 PT2 pipelines to fuel computers. Drain any accumulations of

water from the drain points.


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Area F4: Rear equipment bay and rear fuselage. Access: As visible with bay door open. panels F169 and F170 removed.


Engine - Exhaust

NOTE : Before doing Thrust Reverser inspections make sure ALL related Service

Bulletins have been examined and obey any related Airworthiness Directive. NOTE : Any part showing signs of wear or defect should be replaced or overhauled at

the time of the inspection.

780010

Thrust Reversers.

Inspect the hydraulic lines for signs of leakage.

Inspect the wire harness for any chafing in the area of the

hydraulic control valve.

General Lubrication


120012 Do any 800 hour lubrication requirements for Area F4, refer to


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PART-2


Area T1: Horizontal and vertical stabilizers, to include elevators and rudder. Access: Panels T18, T43L and T44R are removed.


Area Inspection

050191

(a) Airframe.

(b) Electrical.

(c) Avionics.


Inspection Requirements detailed in Para.(6) of the Introduction at the front of

this schedule.

Flight Controls

270012

Rudder trim tab and anti-servo tab. Check the free movement (backlash) at the trailing edges

of the tabs ( AMM 27-20-00, 501). While the connecting rods are disconnected check the

rear rod-end bearings for smooth operation. Detail inspect the connecting rod attachment lugs on the

tabs for cracks using a X 10 magnifier. NOTE : Do not remove the protective coating unless a

defect, or suspected defect, is found.

270013

Elevators and trim tabs. Check the free movement (backlash) at the trailing edges

of the tabs ( AMM 27-30-00, 501). While the connecting rods are disconnected check the


trim tabs for cracks, using a X 10 magnifier. NOTE : Do not remove the protective coating unless a

defect, or suspected defect, is found.

270014 Rudder and elevators primary surfaces. Make sure of full and free movement from stop to stop.

------------- END ---------------

PART-2


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Area W1: Wing LH. Access: Flaps lowered and airbrakes open. Main landing gear doors open. Panels W139, W140, W141, W324, W325, W414, W415, W419, W422, W424, W425, W432, W436, W437, W509, W509A, W510, W510A, W511 and W512 removed.


Area Inspection

050201

(a) Airframe.

(b) Electrical.

(c) Avionics.


Inspection Requirements detailed in Para.(6) of the Introduction at the front of

this schedule.

Flight Controls

270015

Aileron primary surfaces. Make sure of full and free

movement from stop to stop and that all accessible aileron pulleys rotate freely.

270016

Aileron trim and servo tabs. Check the free movement (backlash) at the trailing edges

of the tabs (AMM 27-10-00, 501). While the connecting rods are disconnected inspect the


tabs for cracks using a X 10 magnifier. NOTE : Do not remove the protective finish unless a

defect, or a suspected defect is found.

270066 Aileron Control cable pressure seals. Inspect for wear.

270003 Flap screwjacks . Inspect the screw threads for satisfactory

condition.

270017 Flap Screwjack and reduction gearbox.

Check the gearbox fluid level (AMM 27-50-141, 301).

270018

Flap synchronization system control cables. Inspect for fraying, particularly in the vicinity of the pulleys. Make sure accessible pulleys rotate freely.


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Flight Controls (Continued)

270019 Flap control unit .

Check the gearbox fluid level (AMM 27-50-121, 301).

270020

Flap control unit. Do a flap control unit neutral selection check (AMM 27-50-02, 501).

270021

Flap drive shafts. Inspect for signs of corrosion and for movement between

the end fittings and the shafts.

Wings

570001

Flap hinge fittings. Inspect.

NOTE Inspect the bolt head on the bottom skin of the flap (in the

area of the inboard hinge) adjacent to flap screw jack

carriage grease fitting for damage caused by chafing. If damage is found, replace the bolt. For details of the repair kit refer to Beechcraft Corporation Technical Support (1.800.429.5372 OR 316.676.3140).

General Lubrication


120015 Do any 800 hour lubrication requirements for Area W1, refer to Part 7 - LUBRICATION.

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PART-2


Area W2: Wing RH.

Access: Flaps lowered and airbrakes open. Panels W239, W240, W241, W314, W315,

W319, W322, W332, W336, W337, W509, W509A, W510, W510A, W511 and W512

removed.


Area Inspection

050211

(a) Airframe.

(b) Electrical.

(c) Avionics.

NOTE


Requirements.

Flight Controls

270022

Aileron primary surfaces.

Make sure of full and free movement from stop to stop

and that all accessible aileron pulleys rotate freely.

270023

Aileron servo tabs.

Check the free movement (backlash) at the trailing

edges of the tabs (AMM 27-10-00, 501).

While the connecting rods are disconnected inspect the

rear rod-end bearings for smooth operation.

Detail inspect the connecting rod attachment lugs on the

tabs for cracks using a X 10 magnifier.

NOTE : Do not remove the protective finish unless a

defect, or a suspected defect is found.

270067 Aileron Control cable pressure seals.

Inspect for wear.

270024 Flap Screwjack and reduction gearbox.

Check the gearbox fluid level (AMM 27-50-141).

270025

Flap synchronization system control cables.

Inspect for fraying, particularly in the vicinity of the

pulleys.


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area W2: Wing RH.

Access: Flaps lowered and airbrakes open. Panels W239, W240, W241, W314, W315,

W319, W322, W332, W336, W337, W509, W509A, W510, W510A, W511 and W512

removed.


Make sure accessible pulleys rotate freely.

Area W2: Wing RH. Access: Flaps lowered and airbrakes open. Panels W239, W240, W241, W314, W315,

W319, W322, W332, W336, W337, W509, W509A, W510, W510A, W511 and W512 removed.


270026

Flap drive shafts. Inspect for signs of corrosion and for movement between

the end fittings and the shafts.

Flight Controls Cont.

270065 Flap screwjacks.

Inspect the screw threads for satisfactory condition.

Wings

570002

Flap hinge fittings. Inspect.

NOTE Inspect the bolt head on the bottom skin of the flap (in the

area of the inboard hinge) adjacent to flap screw jack

carriage grease fitting for damage caused by chafing. If damage is found, replace the bolt. For details of the repair kit refer to Beechcraft Corporation Technical Support (1.800.429.5372 OR 316.676.3140).


------------- END ---------------


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DATE : 27/02/2018


PART-2


Area M1, M2: Engine installation and pylon, LH and RH.

Access: Engine cowlings M1L, M2R, M3L and M4R removed. Pylon access panels M9L,

M10R, M11L, M12R, M13L, M14R, M19L and M20R removed.


Area Inspection

050221

(a) Engines.

(b) Airframe.

(c) Electrical.

NOTE

Make sure ALL area inspections are done in accordance with the Inspection.

Engine - Exhaust

NOTE

Before doing Thrust Reverser inspections make sure ALL related Service Bulletins

have been examined and obey any related Airworthiness Directive .

NOTE

Any part showing signs of wear or defect should be replaced or overhauled at the

time of the inspection.

Engine - Exhaust Cont.

780001

Link arm assemblies (8 off).

Remove the link arms (AMM 78-31-10).

Inspect the attachment bolts (16 off), particularly for signs of

corrosion and/or seizing.

Replace any bolts that show signs of corrosion and/or

seizing.

Lubricate the bolt shafts and threads before installation,

using a dry film lubricant to specification MIL-PRF-907, C5-A

(non-aerosol) Item 084 (AMM 20-95-11).

Install the link arms (AMM 78-31-10).





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780002

Reverser door seals. Inspect for correct seating (AMM 78-31-20). Inspect for cracks and wear. Make sure the material is pliable.

780009

Thrust Reversers. Inspect the afterbody and make sure it is correctly

attached. Inspect the doors for corrosion and wear. Detail inspect the doors for cracks. Inspect the fan flaps for signs of fatigue and make sure

they are correctly attached and stow completely. Detail inspect the fan flaps for cracks.

780011 Exhaust nozzle.

Detail inspect for cracks.

780012

Hydraulic Lines. Make sure the hydraulic lines are correctly attached. Inspect for leaks. Inspect the sleeving material for signs of chafing.

780013

Wire harness. Make sure the wire harness in the thrust reverser and

afterbody is correctly attached. Inspect for signs of chafing.

780014

Fan duct. Inspect for signs of corrosion and fatigue. Detail inspect for cracks. Inspect the contour and general condition of the fan duct

fairings.

780015

Latch box springs. Inspect for signs fatigue. Detail inspect for cracks.


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780016

Latch monitoring switches.

Do an operational test (AMM 78-33-50,

ADJUSTMENT/TEST).

780017 Latches and latch receptacles.

Inspect for wear ( 78-31-35, INSPECTION/CHECK).

780018

Primary (AMM 78-32-40) and Latch (AMM 78-32-50) hydraulic

actuators.

Inspect for leaks, corrosion or wear.


780019

Throttle Retard hydraulic actuators (AMM 78-32-30).



Detail inspect the actuator housing at the bearing on the

Throttle Retard.

780020

Fan Flap hydraulic actuators ( AMM 78-32-60).



Detail inspect the actuator housing at the bearing on the

Fan Flap.

780021

Pylon Plug.

Make sure the pylon plug fairings M17L and M18R are

correctly installed and make a continuous surface with the

pylon.

------------- END ---------------


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PART-2


Functional Tests


Flight Controls

270027 Flap control system. Do a function test (AMM 27-50-02, 501).

270028 Airbrake and lift dump system.

Do a functional test (AMM 27-61-02, 501).

Hydraulic Power

290004

Main hydraulic system.

At system shutdown check the pressure dissipation time on

the main pressure accumulator (AMM 29-10-00, 501).

290005 Landing gear and flaps emergency lowering system.

Do an operational test (Ref. AMM 29-20-00).

290009

Auxiliary reservoir low-level warning system.

Do a function test (AMM 29-30-00).

NOTE : Do this task in conjunction with Task # 290005.

Landing Gear

320001

Braking systems.

Do a test of the emergency and parking brake system

operation

(AMM 32-40-00, 501).

320002 Maxaret Units.

Do a function test (AMM 32-40-101, 501).


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Area G : Nose gear, main landing gear, nose gear bay and main landing gear

bays. Access: Nose and main landing gear bay doors open.


Area Inspection

050231

(a) Airframe

(b) Electrical

NOTE


with the Inspection Requirements

.

Landing Gear

320003

Nose gear leg assembly:

Make sure oil level and gas pressures are correct (AMM

32-20-12).

Check the leg extension (AMM 12-32-00).

320004

Nose gear leg lock and change-over microswitches

operating mechanism.

Make sure of freedom of operation.

320005

Nosewheel steering jack:

Inspect for satisfactory condition.

NOTE : Pay particular attention to scores and the

cleanliness of the jack ram.

320006 Nose gear retraction and steering system spring struts.

Inspect.

320007 Nosewheel steering ON/OFF valve.

Inspect.

320008 Nose gear drag stay assembly.

Check clearances ( AMM 32-20-21).

320009

Nosewheel steering jack selector valve:

Service: Clean and grease the selector valve spring

housing and parts (AMM 32-50-11, 301).

320037

Nose leg assembly torque links.

Examine the torque link pivots for wear (AMM 32-20-12,

601).


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Landing Gear Cont.

320010

Main gear leg assemblies

Make sure oil level and gas pressures are correct (AMM 32-

10-12).

Check the leg extension (AMM 12-32-00).

320011

Main landing gear side-stays.

Inspect the center joint nut for distortion (AMM 32-10-25).

Check the side-stay clearances (AMM 32-10-25).

320012

Main landing gear torque links.

Examine the torque link pivots for wear (AMM 32-10-12,

601).

320033

Main gear retraction actuator (AMM 32-30-27).

NOTE : To do this inspection, disconnect the cylinder head

end of the actuator. Do not disconnect the hydraulic lines.

Detail inspect the actuator attachment lugs.

320013

Main landing gear doors.

Inspect the hinge bracket assemblies for security and

tightness of the nuts.

Inspect jack attachment brackets and adjacent structure for

cracks.

Inspect for signs of movement of the forward hinge

brackets and bolts at their attachment to the wing structure

by attempting to rock the doors in the longitudinal and

transverse directions.

NOTE : If the brackets are found to be loose, inspect the

attachment bolt holes and bolts for wear and corrosion.

320014

Main landing gear door uplock spring struts.

Inspect.

Clean the sliding surfaces.

Make sure of correct operation: Check initial breakout/first

movement of the spring strut occurs at 19 lb 2 lb.Make

sure movement of the strut is free over the length of the

stroke.

320015 Reversing valves and operating mechanisms:


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Disconnect from the side stay.


Make sure the mechanisms are free to move correctly.

Connect to the side stay.

320034

Plunger Tube/Axle Joint

Inspect the flexible seal at the plunger tube to axle joint .

Make sure the seal is not loose or cracked.

Rectify as necessary (Ref. AMM Chapter 32, MAIN LEG

ASSEMBLY).

General Lubrication


120018 Do any 800 hour lubrication requirements for Area G, refer to


------------- END ---------------


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PART-2

2. Inspection C

050240

Instructional Data

NOTE Inspection C is the top level inspection which covers the accomplishment of Inspections C1 to C12 inclusive. This must be completed by every 1600 hours.

NOTE Inspection C must only be signed when Inspections C1 to C12 inclusive have been completed. ALL within a single tolerance window.






INSPECTION C (Consists of Inspection C1 to C12 inclusive)



completed.


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PART-2

INSPECTION C1 050250

Functional Tests


Air Conditioning

210020

Electrically actuated auxiliary heat valve.

Do a functional test (AMM 21-60-105).

NOTE

This test may be done without engine bleed air.

Electrical Power

240004

Busbar contactor control.

Set the bustie switch to CLOSE.

Trip the LH generator off-line.

Make sure all d.c. busbars are energized.

Reset the LH generator.

Trip the RH generator off-line.

Make sure all d.c. busbars are energized.

Reset the RH generator.


300002 Windshield electrical de-icing system. Do an operational test

of the windscreen overheat (AMM 30-41-00).

300004 Pitot head and static plate heaters.

Do a function test (AMM 30-35-15).

------------- END ---------------


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PART-2


Functional Tests


Flight Controls

270030

Elevator trim servo. Operate the elevator trim switch on the left, or right, control

column. As the elevator trim servo motor operates the elevator trim

tabs, hold the manual elevator trim wheel with sufficient force to stop the trim wheel. The force needed to stop the trim wheel must not be more

than 15 lbs.

------------- END ---------------


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PART OF INSPECTION

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REVISION : 0

DATE : 27/02/2018


PART-2


Area F1: External fuselage, nose cone, tail cone, ventral fuel tank/EBU and wing-to-

fuselage fairings

Access: Panels F4, F122, F123, F222, F223, W502, W503, W511 and W512 removed.


Area Inspection

050271

(a) Airframe.

(b) Electrical.

(c) Avionic.

NOTE


with the Inspection Requirements .

General Lubrication


120019 Do any 1600 hour lubrication requirements for Area F1, refer


------------- END ---------------


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REVISION : 0

DATE : 27/02/2018


PART-2


Area F2: Flight compartment.

Access: Under seat sidewall panels F16 and F17 removed. Center pedestal panels F11

and F12 removed. Step panel F55 removed. Panels F14, F41, F42, F43, F44, F45, F46

and F47 removed.


Area Inspection

050281

(a) Airframe.

(b) Electrical.

(c) Avionic.

(d) Engine.


Inspection.

Air Conditioning

210008

Cabin pressure outflow/safety valve controller .

Visually inspect and make sure that the cabin air sense

port screen is clear.

Flight Controls

270032

Aileron autopilot servo control cables .

Check cable tensions are correct: (AMM 27-00-00, 201

and 27-10-93, 401).

270033 Elevator control system balance/feel spring .

Inspect.

Landing Gear

320016 Steering system cables and chains .

Make sure cable tensions are correct (AMM 32-50-00).

320023

Brake hoses to master cylinders.

Make sure of an adequate clearance between the

hoses and the floor over the full range of rudder pedal

travel.


PAGE : 162

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area F2: Flight compartment.

Access: Under seat sidewall panels F16 and F17 removed. Center pedestal panels F11

and F12 removed. Step panel F55 removed. Panels F14, F41, F42, F43, F44, F45, F46

and F47 removed.


Navigation

340003

Autopilot aileron servo unit and mount .

Inspect, particularly for cable and capstan wear,

contamination, cable spool-off angle and security of the

servo unit and mount.

With the autopilot disengaged operate the control system

throughout the entire range and make sure there is no

unusual noise, binding, backlash or signs of other

mechanical irregularities from the servo mount.

Engine - Exhaust

780003

Thrust reverser stow/deploy microswitches .

Test microswitches coded CWA or CXA (AMM 78-34-20,

201).

General Lubrication




------------- END ---------------


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (underfloor). Access: Floor panels F60, F65, F66A, F66B, F66C, F67, F70, F73, F75, F77, F78C, F84

and F84A removed.


Area Inspection

050291

(a) Airframe.

(b) Engine.

(c) Electrical.

(d) Avionic.

NOTE Make sure ALL area inspections are done in accordance with the Inspection Requirements.

Flight Controls

270034 Elevator primary control cables.

Check cable tensions are correct (AMM 27-30-00).

270035 Flap control cables. Check cable tensions are correct (AMM 27-50-02).

Fuel

280002 Fuel valve control cables.


Engine Controls

760002 Engine power control cables.


General Lubrication




------------- END ---------------


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (above floor).

Access: DA panel F25, removed.


Area Inspection

050301

(a) Airframe.

(b) Engine.

(c) Electrical.

(d) Avionic.

NOTE


Requirements.

Air Conditioning

210009 Pressurization control venturi screen.

Make sure screen is clean.

Electrical Power

240010

PE, PS1 and PS2 busbar feeder cables below Panel DA .

Inspect for discoloration due to overheating.

Torque tighten the connections (AMM 24-01-00).

Ice and Rain Protection.

300005 Airframe de-icing pump suction-filter.

Replace the filter element (Ref. AMM 30-10-43).

Doors

520004

Main entry door "not locked" warning microswitches.

Energize the dc busbars (AMM 12-24-00).

With the main entry door open, operate the "door not

closed" microswitch.

Make sure the "ENT DOOR UNLOCKED" annunciator on

the Master Warning System panel remains on.

NOTE : If the annunciator goes off, then investigate the

'door lock' microswitch for seizure in the operated

position.


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area F3: Vestibule, passenger cabin and toilet compartment (above floor).

Access: DA panel F25, removed.


Release the "door not closed" microswitch.

De-energize the dc busbars.

520007

Entry door:

Inspect seal for deterioration and damage.

Check internal handle operating loads (AMM 52-11-00).

520010 Main Entry Door - Folding Handrail

Inspect: (MMA 52-15-00, 601).

Windows

560004 Windows dry-air system filter

Inspect the filter element (AMM 56-00-00).



------------- END ---------------


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F4: Rear equipment bay, rear fuselage and APU enclosure.

Access: Tail cone F2 and hydraulic box cover F92 removed.


Area Inspection

050311

(a) Airframe.

(b) Engine.

(c) Electrical.

(d) Avionic.

NOTE


Requirements.

Air Conditioning

210012 Air conditioning ducts (AMM 21-10-15):


210013

Ram air duct. Inspect, as far as is possible, for cracks in the vicinity of the

take-off duct to the shut-off valve, and around the cut-out for

the inward relief door.

210025

PATS APU GTCP36-150W. APU bleed air system.

Inspect for air leaks at clamped joints and pipes. Inspect load control valve for cracks, dents, deformation or

other damage that may affect the performance of the valve. Remove and inspect the check valve. Repair as required.

Electrical Power

240011

Busbar PE, PS1 and PS2 feeder fuses . Replace (with new

items) the fuses: F31 an F32 on panel ZL. F13, F14, F23 and F24 on panel GA

When you do this: Make sure the fuses are in correct contact with the busbars

and the mounting pillars. Make sure the fuses are clamped in position correctly. Torque tighten the securing nuts ( AMM 24-01-00).


PAGE : 167

PART OF INSPECTION

ISSUE : 1

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DATE : 27/02/2018





Electrical Power (cont.)

240012

Busbar PE, PS1 and PS2 feeder system connections :

Inspect for discoloration due to overheating.

Torque tighten the connections (AMM 24-01-00).

Flight Controls

270036 Elevator primary and elevator trim control cables.


270037 Rudder primary and rudder trim control cables.


270038 Elevator autopilot servo control cables.

Check cable tensions are correct: (AMM 22-10-30, 401).

270039 Rudder autopilot servo control cables.

Check cable tensions are correct: (AMM 22-10-20, 401).

270040 Elevator autopilot trim-servo control cables.


Hydraulic Power

290006

Hydraulic tank pressurization system .

Drain any accumulation of liquid from the drain/ground air

charge connection.

Navigation

340004

Autopilot servo units, rudder and elevator.












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PART OF INSPECTION

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Navigation

340005

Autopilot elevator trim servo unit and mount .








Oxygen

350008

Oxygen cylinders.

Inspect cylinder mount clamps for security (AMM 35-10-14,

401).



------------- END ---------------


PAGE : 169

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder. Access: Panels T6L, T7R, T14L, T15R, T16L, T17R, T23R, T24L, T25R and T26L

removed.


Area Inspection

050321

(a) Airframe.

(b) Electrical.

(c) Avionics.

Flight Controls

270041

Elevator trim cables :

Inspect the condition of the protective coating ( AMM 20-95-11, Item No. 079) on the cables over a length of 42 ins (1070

mm) from each trim chain where the cables are exposed

between the horizontal stabilizer and the elevators.

Apply protective coating ( AMM 27-30-00, page block 301), if necessary.

General Lubrication


120024 Do any 1600 hour lubrication requirements for Area T1, refer


------------- END ---------------


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W1 Wing LH.

Access: Panels W107, W139, W141, W406, W413, W417, W422, W425, W437, W503,

W508, and W510 removed. Flaps lowered.


Area Inspection

050331

(a) Airframe.

(b) Electrical.

(c) Avionic.


Requirements.

Flight Controls

270002

Flap vane inner . With the flaps lowered, inspect the left outer

attachment bracket for cracking and for security of attachment

to the flap leading edge.

270042 Aileron primary and trim control cables.


270043

Flap drive shaft universal joints . With grease covers

removed, inspect joints for wear and repack with grease (AMM

27-50-132).

270044

Flap Bevel drive assembly .

Check that the backlash between the input and output

shafts, measured at the input coupling flange bolts, does not

exceed 0.020 in.

270045 Flap control unit baulk release cable .

Check cable tension is correct (AMM 27-50-02).

270046 Flap/Airbrake baulk bobbin.

Make sure bobbin setting is correct (AMM 27-50-02).

270047

Flap spring drum pulley-lever .

Disconnect rod from pulley lever (AMM 27-50-02). Check the pull off force required to move the lever off the

spring drum internal stops is 5.35 lb. to 7 lb., measured at the

connecting rod attachment point on the lever. Check that the lever returns to contact internal stops at or


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PART OF INSPECTION

ISSUE : 1

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DATE : 27/02/2018


Area W1 Wing LH.




before 5 lb. force at the connecting rod attachment. Reconnect rod to pulley lever.

Area W1 Wing LH.




Flight Controls (cont.)

270048

Flap Screwjack and reduction gearbox . Check that the

backlash on the screw threads does not exceed 0.020 in (AMM

27-50-141).

270049

Flap synchronising system : Check the cable tensions are correct (AMM 27-50-02). With the flaps selected up, disconnect the operating link

from one transmitter gearbox only. Pressurize the hydraulic system. Whilst restraining the disconnected lever arm, select the

flaps down. Make sure that the flaps start to move and then the system

cuts out. Depressurize the hydraulic system and connect the

transmitter operating link. Pressurize the hydraulic system and make sure that the

flaps operate correctly.

270050 Airbrake control cables .

Check the cable tensions are correct (AMM 27-61-02).

Fuel

280005 Suction pipe strainers . Visually inspect for satisfactory

condition.

280006 Water transfer system pipe suction blocks . Visually inspect

for satisfactory condition.

280014

Applicable to Intertechnique fuel pumps only. Fuel system pumps:

Part No. 2070C01 Check the brush length (14 mm

minimum). Part No. 2070C11 Check the brush length (10 mm


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area W1 Wing LH.




minimum).

General Lubrication



------------- END ---------------


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PART OF INSPECTION

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DATE : 27/02/2018


PART-2


Area W2: Wing RH.

Access: Panels W207, W239, W306, W313, W317, W322, W325, W337, W502, W507 and

W509A removed. Flaps lowered.


Area Inspection

050341

(a) Airframe.

(b) Electrical.

(c) Avionic.



Flight Controls

270064

Flap vane inner. With the flaps lowered, inspect the right outer

attachment bracket for cracking and for security of attachment to the flap leading edge.

270051 Aileron primary and trim control cables.


270052

Flap drive shaft universal joints . With grease covers

removed, inspect joints for wear and repack with grease (AMM

27-50-132).

270053

Flap bevel drive assembly. Check that the backlash between the input and output

shafts, measured at the input coupling flange bolts, does not exceed 0.020 in.

270054

Flap screwjack and reduction gearbox. Check that the backlash on the screw threads does not

exceed 0.020 in. (AMM 27-50-141).

270055

Flap synchronising system: Check the cable tensions are correct (AMM 27-50-02). With the flaps selected up, disconnect the operating link from one

transmitter gearbox only. Pressurize the hydraulic system. Whilst restraining the disconnected lever arm, select the flaps

down. Make sure that the flaps start to move and then the system cuts

out. Depressurize the hydraulic system and connect the transmitter


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PART OF INSPECTION

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Area W2: Wing RH.

Access: Panels W207, W239, W306, W313, W317, W322, W325, W337, W502, W507 and

W509A removed. Flaps lowered.


operating link. Pressurize the hydraulic system and make sure that the flaps

operate correctly.

Area W2: Wing RH.

Access: Panels W207, W239, W306, W313, W317, W322, W325, W337, W502, W507 and W509A

removed. Flaps lowered.


Flight Controls Cont.

270056 Airbrake control cables.

Check the cable tensions are correct (AMM 27-61-02).

Fuel

280015

Applicable to Intertechnique fuel pumps only.

Fuel system pumps:

Part No. 2070C01 Check the brush length (14 mm minimum).

Part No. 2070C11 Check the brush length (10 mm minimum).

280007 Suction pipe strainers .

Visually inspect for satisfactory condition.

280008 Water transfer system pipe suction blocks .

Visually inspect for satisfactory condition.

General Lubrication


120026 Do any 1600 hour lubrication requirements for Area W2, refer to Part 7 -

LUBRICATION.

------------- END ---------------


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PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area M1, M2: Engine installation and pylon, LH and RH

Access: Panels M1L, M2R, M3L, M4R, M9L, M10R, M11L, M12R, M13L, M14R, M15L,

M16R removed.


Area Inspection

050351

(a) Engines.

(b) Airframe.

(c) Electrical.



Engine - Exhaust

NOTE : Before doing Thrust Reverser inspections make sure ALL related Service

Bulletins have been examined and obey any related Airworthiness Directive. NOTE : Any part showing signs of wear or defect should be replaced or overhauled at

the time of the inspection.

780004

Pylon skin panels. Remove the panels, inspect the fasteners and

attachments.

780005 Door link rods and pivot brackets.

Detail inspect (AMM 78-31-10, 601).

780022

NOTE : This task is Applicable to Link Rod

Assemblies P/N 5453003-7 Only. Door link rods Do a thickness check, Link rod - corrosion removal limits. (AMM 78-31-10, 601).

120027 Transferred to Out of Phase Inspections Task # 760004, refer to Part 7 - LUBRICATION.

------------- END ---------------


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PART-2


Functional Tests


Hydraulic Power

290007

Flaps, airbrakes, landing gear, nosewheel steering, nose leg self-centering. Do a test of the main system with a

hydraulic test rig (AMM 29-10-00).

290008

Emergency brake system leak rate. Check the rate that the

pressure decreases (leakage rate) in the accumulator (AMM

29-10-00).

290010 Hydraulic reservoir pressurization system. Do a functional

test of the non-return valve (AMM 29-10-13).

Area G: Nose landing gear and bay, left and right main landing gear and bays. Access: Nose and Main landing gear bay doors open.


050361

(a) Airframe:

(b) Electrical:



Nose Landing Gear

320017

Nose landing gear retraction spring strut. Check the break-out load (AMM 32-20-21).

320018

Nosewheel steering system spring strut break-out load. Check the break-out load (CMM 32-50-00). If the load is excessive, dismantle the spring strut, clean,

lubricate and reassemble (CMM 32-50-00).

Main Landing Gear

320024 Axle/Maxaret/Modulator/Plunger Tube .


PAGE : 177

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ISSUE : 1

REVISION : 0

DATE : 27/02/2018




Maxaret and modulator unit. Remove and inspect (AMM 32-40-91 and AMM 32-40-101). While the Maxarets and Modulator units are removed, detail

inspect the internal bores of the axles. Inspect the Plunger Tube to Axle Bore for signs of

corrosion. Reinstall Maxarets and Modulator units (AMM 32-40-91 and

AMM 32-40-101). Do a function test (AMM 32-40-101, ADJUSTMENT/TEST).



Main Landing Gear (cont.)

320035

Main Leg Assembly Retraction Lever . Inspect for excessive movement.

Inspect for signs of corrosion.

320036 Sidestay Assembly Lock Mechanism Link .

Inspect for signs of wear.

General Lubrication


120028 Task deleted.

------------- END ---------------


PAGE : 178

PART OF INSPECTION

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DATE : 27/02/2018


PART-2

3. Inspection D

050370

Instructional Data

NOTE Inspection D is the top level inspection which covers the accomplishment of Inspections D1 to D12 inclusive. This must be completed by every 3200 hours.

NOTE Inspection D must only be signed when Inspections D1 to D12 inclusive have been completed. ALL within a single tolerance window.






INSPECTION D (Consists of Inspection D1 to D12 inclusive)



completed.


PAGE : 179

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

INSPECTION D1 050380

Functional Tests


Electrical Power

240003 Frequency wild A.C. system. Do a function test (AMM 24-22-

02).

240013 All circuit breakers. Function test for correct mechanical

operation. Do two manual switching cycles for this test.

240014 Main generator control unit (GCU). Do a function test of the

overvoltage protection circuit (AMM 24-30-07).

240015 APU Generator control unit (GCU). Do a function test of the

overvoltage protection circuit (AMM 24-36-03).

Fuel

280003 LP valves . Do a function test for internal leakage (AMM 28-20-

00).

Navigation

340008 Mach trim system. Do a test of the Mach trim system: ( AMM

22-20-00, 501)

340010

Autotrim command isolation relay and autotrim switching

relay:

NOTE

This task is ONLY applicable to airplanes equipped with

an FCC-86 Flight Control Computer.

Do checks as detailed, AMM 27-30-00, 501, (Autotrim

command isolation relay and autotrim switching relay

checks).

Navigation Cont.

340011

This task is NOT applicable to Pro Line 21 Equipped airplanes.

Mach trim fail annunciation relays.

Open the MACH TRIM PWR or MACH TRIM MON circuit breaker.

Make sure that the MACH TRIM FAIL annunciator comes on.

Close the MACH TRIM PWR or the MACH TRIM MON circuit

breaker.

Make sure that the MACH TRIM FAIL annunciator goes off.


PAGE : 180

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


------------- END ---------------


PAGE : 181

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Functional Tests


Oxygen

350002 Automatic shut-off valve. Do a functional test (AMM 35-10-141).

------------- END ---------------


PAGE : 182

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to- fuselage fairings Access: As necessary.


Electrical Power

240016

Electrical cable pressure bungs (in the forward pressure

bulkhead). Inspect for correct location in their housings (AMM 24-

01-00).

------------- END ---------------


PAGE : 183

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F2: Flight compartment. Access: Side console panels F52 and F53 removed. Side

trim panels F9 and F10 removed.


Area Inspection

050411

(a) Airframe.

(b) Electrical.

(c) Avionic.

(d) Engine.



Electrical Power

240026

Electrical cable pressure bungs (in the forward pressure

bulkhead).

Inspect for correct location in their housings (AMM 24-01-

00).


250008

Crew Seats. Remove the crew seats ( AMM 25-10-14, 401) Do a detailed check (CMM 25-11-24, 501 (Check 2)) or

(CMM 25-11-67, 501 (Check 2)). Install the crew seats (AMM 25-10-14, 401).

Flight Controls

270057

Flap control forward spring strut. Check break-out load with

one end disconnected and using a spring balance is 21.5 to

24.5 lb. (AMM 27-50-02).

270058 Flap control input-circuit. Do a static friction check (AMM 27-

50-02).

Engine Exhaust

780006

Thrust reverser lever baulk mechanism .

Deploy each thrust reverser in turn.

Make sure that the baulk release lever of the reverser

system which is not deployed stays down and does not


PAGE : 184

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area F2: Flight compartment. Access: Side console panels F52 and F53 removed. Side

trim panels F9 and F10 removed.


show any tendency to lift when the solenoid of the deployed

system is energized.

Return both thrust reverser to the stowed position.

General Lubrication




------------- END ---------------


PAGE : 185

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (underfloor).


Electrical Power

240025

Electrical cable pressure bungs (in the fuselage keel at the

front spar). Inspect for correct location in their housings (AMM

24-01-00).

------------- END ---------------


PAGE : 186

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (above floor).Access: As

visible.


Area Inspection

050431

(a) Airframe

(b) Electrical

(c) Avionic

NOTE


Requirements.

Electrical Power

240006 D.C. busbar protection/voltage sensing unit.

Check the trip voltage datums (AMM 24-30-142).

------------- END ---------------


PAGE : 187

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F4: Rear equipment bay and rear fuselage. Access: Hydraulic box cover and pipe

covers F88, F89, F90 and F91 removed.


050441

(a) Airframe.

(b) Electrical.

(c) Avionic.


Air Conditioning

210015

Silencer duct and soundproofing (AMM 21-10-15). Inspect the silencer duct internally for deterioration of the

soundproofing material and of the perforated inner retaining duct. Inspect for internal and external corrosion.

210016 System overheat temperature switch.

Do a bench check (AMM 21-60-85).

210019

Cabin supply non-return valve. Inspect, paying particular attention to the security of the

carrier arm/butterfly flap rivets (AMM 21-10-107).

210021

APU supply, auxiliary supply, ram air supply and main engine supply. Check/non-return valves:

Remove and inspect. Make sure that the axial and radial play in the flappers is

not excessive (0.025 in. maximum for AiResearch valves).

Electrical Power

240007 Ground power overvoltage sensor (if fitted).

Bench check the trip voltage datum (AMM 24-30-146).

240018

Electrical cable pressure bungs (in the rear pressure-bulkhead).

Inspect for correct location in their housings (AMM 24-01-00).

240027

Main batteries Rebling Plastics "Quick Disconnect" battery connectors,

P/N's 7007, 7013, 7016 and 7017 (if fitted): Check (AMM 24-30-151, 401).


PAGE : 188

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area F4: Rear equipment bay and rear fuselage. Access: Hydraulic box cover and pipe

covers F88, F89, F90 and F91 removed.


Fuel

280004

APU fuel inlet filter Inspect, clean or replace the fuel filter element: (AMM 28-

20-09).

Hydraulic Power

290011 Full-flow relief valve.

Clean filter element (AMM 29-10-71).

290012

High temperature warning system. Do a test of the main hydraulic reservoir high

temperature warning system (AMM 29-30-00).

------------- END ---------------


PAGE : 189

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area T1 : Horizontal and vertical stabilizers, to include elevators and rudder .Access: As

necessary.


NOTE No inspections in this area at this time.

------------- END ---------------


PAGE : 190

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W1 : Wing LH.Access: As necessary.



------------- END ---------------


PAGE : 191

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W2 : Wing RH.Access: As necessary.


Flight Controls

270060

Filter, auxiliary hydraulic system supply to flap control

unit.

Replace the filter element (AMM 29-20-00, 001).

NOTE

The AMM reference is for component location ONLY.

------------- END ---------------


PAGE : 192

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area M1, M2: Engine installation and pylon, LH and RH. Access: As necessary.


NOTE No Airframe/electrical inspections in these areas required at this time.

NOTE For details of Honeywell engine inspections refer to the latest revision of the

Honeywell Light Maintenance Manual (LMM).

------------- END ---------------


PAGE : 193

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area G: Nose landing gear and bay, left and right main landing gear and bays. Access:

Nose and Main landing gear bay doors open. Wing-to-fuselage fairing F124 and F224

removed.


Area Inspection

050491

(a) Airframe

(b) Electrical

NOTE


Requirements.

Nose Landing Gear bay

320019

Steering system filter element.

Remove, inspect and clean filter element (AMM

32-30-22).

Main Landing Gear bays

320020 Filters, hydraulic supply (4 off).

Clean the filter elements ( AMM 32-30-22).

320021

Restrictor valves.

Clean the micro filters in the pipe connections

(AMM 32-30-01).

------------- END ---------------


PAGE : 194

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

4. Inspection E

050500

Instructional Data

NOTE Inspection E is the top level inspection which covers the accomplishment of Inspections E1 to E12 inclusive. This must be completed by every 12 months.

NOTE Inspection E must only be signed when Inspections E1 to E12 inclusive have been completed. ALL within a single tolerance window.






INSPECTION E (Consists of Inspection E1 to E12 inclusive)



completed.


PAGE : 195

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

INSPECTION E1 050510

Functional Tests


Fire Protection

260001

Airplanes with Fire Extinguisher Pressure Gauges ONLY.

Fire extinguishers, main engines.

Check the pressure gauge. Make sure the reading is

correct, refer to the pressure/temperature chart.

Do a functional test (AMM 26-20-00).

NOTE

For airplanes without Fire Extinguisher Pressure gauges

refer to Inspection E7 task 260005.

Instruments

310001

Flight data recorder .

Check for correct playback operation (data dump) and for

quality of the recording.

NOTE

Do the check at this inspection or at a time agreed

necessary by the local airworthiness authority.

------------- END ---------------


PAGE : 196

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Functional Tests


Oxygen

3500041

Passenger oxygen system.

Test automatic operation of baromatic valve (AMM 35-06-

00, 501).

Test for flow from each mask by reference to operation of

the visual indicator (if fitted) when mask is pulled down to

the 'full hang' position: (MMA 35-06-00, 201).

Inspect drop-out mask units when deployed during system

test:

(MMA 35-20-05, 301).

NOTE

If the passenger masks PN. 289-601* do not meet the

requirements of the annual inspection refer to the vendor

CMM 35-22-26 for Visual, Overhaul and Repair

procedures.

Stow drop-out mask units: (MMA 35-20-05, 301).

3500052

Baromatic control valve.

With passenger supply isolation valve closed, exercise

control valve mechanism by operating the emergency/reset

knob several times.

Leave the knob at the reset position.

------------- END ---------------

1 Task move from B2 to E2 2 Task move from B2 to E2


PAGE : 197

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F1: External fuselage, nose cone, tail cone, wing-to-fuselage fairings and nose

landing gear bay. Access: As visible.



------------- END ---------------


PAGE : 198

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F 2: Flight compartment.Access: As visible.


Fire Protection

260003

Portable fire extinguisher:

Check for correct weight or if gauge is fitted, make sure the

needle is in the green sector.

Inspect and look for signs of leaks or discharge.

Oxygen

350006 Crew masks and hoses.

Inspect.

350007

Portable breathing equipment:

Inspect: (AMM 35-35-15).

Check the expiry dates.

------------- END ---------------


PAGE : 199

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F 3: Vestibule, passenger cabin and toilet compartment (under floor). Access: As necessary.


NOTE No underfloor inspections required at this time.

------------- END ---------------


PAGE : 200

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F 3: Vestibule, passenger cabin and toilet compartment (above floor).Access: As

visible.


Electrical Power

240029

Do a visual inspection for discoloration and signs of heat

distress (AMM 24-01-00, 201 select, 800XP Pro Line 21).

Inspect DA - Panel for correct mounting of components.

Equipment and Furnishings

250005

Emergency packs

Inspect contents for condition and make sure expiry dates

are valid.

250006 First aid kits. Make sure expiry date is valid and make sure

seal is intact.

Fire Protection

260004

Portable fire extinguisher

Check for correct weight or if gauge is fitted, make sure the

needle is in the green sector.

Inspect and look for signs of leaks or discharge.

------------- END ---------------


PAGE : 201

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F4: Rear equipment bay, rear fuselage and APU enclosure. Access: As visible.


Area Inspection

050571

(a) Engines.

(b) Airframe.

(c) Electrical.


Electrical Power

240028 Panel GG and Terminal block M (transferred to Out Of Phase

Inspections)

Fire Protection

260005

For airplanes without Fire Extinguisher Pressure Gauges ONLY. Fire extinguishers, main engines:

Remove (AMM 26-20-12). Inspect. Check weight (AMM 26-20-12). Install ( AMM 26-20-12). Do a functional test (AMM 26-20-00).

NOTE For airplanes with Fire Extinguisher Pressure Gauges refer to Inspection E1, task 260001.

260010

PATS APU GTCP36-150W. APU fire extinguisher.

Inspect. Check pressure gauge (Meggitt CMM 26-20-02). Check Hydrostatic and Cartridge due dates. Do a functional test (AMM 49-61-20, 501).

Flight Controls

270059 Control cable pressure seals at rear pressure bulkhead.

Inspect for wear.

------------- END ---------------


PAGE : 202

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder. Access: As necessary.


NOTE No inspections in Area T1 required at this time.

------------- END ---------------


PAGE : 203

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W1 : Wing LH.Access: As necessary.


NOTE No inspections in Area W1 required at this time.

------------- END ---------------


PAGE : 204

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W2 : Wing RH. Access: As necessary.


NOTE No inspections in Area W2 required at this time.

------------- END ---------------


PAGE : 205

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2



Aircraft Registration: Mechanic : Inspector :

NOTE No Airframe/electrical inspections in these areas required at this time.

NOTE For details of Honeywell engine inspections refer to the latest revision of the Honeywell Light Maintenance Manual (LMM).

------------- END ---------------


PAGE : 206

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area G: Nose landing gear and bay, left and right main landing gear and bays. Access: As necessary.


NOTE No inspections in Area G required at this time.

------------- END ---------------


PAGE : 207

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

5. Inspection F

050630

Instructional Data

NOTE Inspection F is the top level inspection which covers the accomplishment of Inspections F1 to F12 inclusive. This must be completed by every 24 months.

NOTE Inspection F must only be signed when Inspections F1 to F12 inclusive have been completed. ALL within a single tolerance window.






INSPECTION F (Consists of Inspection F1 to F12 inclusive)



completed.


PAGE : 208

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

INSPECTION F1 050640

Functional Tests


NOTE No inspections in Area required at this time.

------------- END ---------------


PAGE : 209

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Functional Tests


NOTE No inspections in Area required at this time.

------------- END ---------------


PAGE : 210

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to-

fuselage fairings.

Access: F121, F221, F122, F222, F123, F223 and as visible.


Area Inspection

050661

(a) Airframe.

(b) Electrical.

(c) Avionic.

NOTE

Make sure ALL area inspections are done in accordance with the


General Lubrication


120049 Do any 24 month lubrication requirements for Area F1, refer to


------------- END ---------------


PAGE : 211

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F2: Flight compartment

Access: Instrument panels F6 and F8 and roof panel F5 lowered. Floor panels F41, F42,

F43, F44, F45 and F47 removed.


Area Inspection

050671

(a) Airframe.

(b) Electrical.

(c) Avionic.

NOTE


Inspection Requirements detailed in Para.(6) of the Introduction at the

front of this schedule.

General Lubrication


120050 Do any 24 month lubrication requirements for Area F2, refer to


------------- END ---------------


PAGE : 212

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment (under floor).


NOTE No inspections required in this area at this time.

------------- END ---------------


PAGE : 213

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F3: Vestibule, passenger cabin and toilet compartment.

Access: DA panels F22, F23, F24 and F25 removed. Front and rear radio compartments

access panels removed. Radio junction cover removed. Duct panel F29 removed.


Area Inspection

050691

(a) Airframe.

(b) Electrical.

(c) Avionic.

NOTE


Inspection Requirements detailed in Para.(6) of the Introduction at the

front of this schedule.

------------- END ---------------


PAGE : 214

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area F4: Rear equipment bay and rear fuselage.

Access: As visible with rear equipment bay door open.


Area Inspection

050701

(a) Airframe.

(b ) Electrical.

(c) Avionic.

(d) Engine.

NOTE


Requirements detailed in Para.(6) of the Introduction at the front of this schedule.

------------- END ---------------


PAGE : 215

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder. Access: T13, T25R, T26L and T45 removed.


550008

Horizontal stabilizer to vertical stabilizer rear attachment fitting.

Inspect for signs of corrosion, paying special attention to

the condition of the outboard flanges and webs. NOTE

For corrosion limits refer to Beechcraft Corporation.

------------- END ---------------


PAGE : 216

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W1: Wing LH. Access: Panels W406, W411 and W413 removed.


Area Inspection

050721

(a) Airframe

(b) Electrical

(c) Avionic


Wings

570003

The internal structure of the wing in the area of Ribs 0 to 4 .

Detail inspect. Look for signs microbiological contamination and corrosion.

NOTE If corrosion or microbiological contamination is found:

PROGRESSIVELY EXTEND THE DETAIL INSPECTION,

BY VISUAL MEANS OR X-RAY TECHNIQUE, FORWARD

OF THE CENTRE SPAR AND OUTBOARD OF RIB 4 UNTIL A CLEAN BAY RIB IS FOUND. REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND

DETAIL INSPECT INTERNALLY. DO THE SHOCK PREVENTATIVE PROCEDURE (AMM

28-10-00, PAGE BLOCK 701).

570004

Applicable to Mod. 259071A airplanes only. Flap skin protection panels . Remove panels and inspect the

flap skin for corrosion and deterioration of the protective treatment.

NOTE Mod. 259071A introduces protective skins on the flap

inboard underside for rough runway protection.

------------- END ---------------


PAGE : 217

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area W2: Wing RH. Access : Panels W306, W311 and W313 removed.


Area Inspection

050731

(a) Airframe.

(b) Electrical.

(c) Avionic.


Wings

570005

The internal structure of the wing in the area of Ribs 0 to 4 .

Detail inspect. Look for signs microbiological contamination and corrosion.

NOTE If corrosion or microbiological contamination is found:

PROGRESSIVELY EXTEND THE DETAIL INSPECTION,

BY VISUAL MEANS OR X-RAY TECHNIQUE, FORWARD

OF THE CENTER SPAR AND OUTBOARD OF RIB 4 UNTIL A CLEAN BAY RIB IS FOUND. REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND

DETAIL INSPECT INTERNALLY. DO THE SHOCK PREVENTATIVE PROCEDURE (AMM

28-10-00, PAGE BLOCK 701).

570006

Applicable to Mod. 259071A airplanes only. Flap skin protection panels (if fitted) . Remove panels and

inspect the flap skin for corrosion and deterioration of the protective treatment.

NOTE Mod. 259071A introduces protective skins on the flap

inboard underside for rough runway protection.

------------- END ---------------


PAGE : 218

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2




NOTE No Airframe/electrical inspections in these areas required at this time. For details of Honeywell engine inspections refer to the latest revision of the Honeywell Light Maintenance Manual (LMM).

------------- END ---------------


PAGE : 219

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2


Area G: Nose landing gear and bay, left and right main landing gear and bays.

Access: Nose and main landing gear doors open.


Area Inspection

050751

(a) Airframe:

(b) Electrical:

(c) Avionic:

NOTE


Requirements detailed in Para.(6) of the Introduction at the front of this

schedule.

------------- END ---------------


PAGE : 220

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


PART-2

6. Inspection G

050760

Instructional Data

NOTE



NOTE

Inspection G must be completed every 48 months.






Functional Tests



PAGE : 221

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Functional Tests


Bonding Checks

200003 Radio racking, electrical-bonding. Do a bonding check with

all the equipment fitted (AMM 125/H-20, 20-10-5016).

General Lubrication


120059 Task deleted (Transferred to Lubrication, 1600 Hour).

Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to-

fuselage fairings

Access: Panels F3, F125, F155, F162, F163, F160L, F161R, and F225 removed.

NOTE

It is not necessary to remove panels F160L, F161R, until the second 48 month

inspection (96 months). Remove them at every 48 month inspection from that time

onwards.


Area Inspection

050761

(a) Airframe.

(b) Electrical.

(c) Avionics.



Landing Gear

320027

Nose-wheel steering on/off-valve : Remove the plunger stop cap. Visually inspect the plunger and spring for corrosion, clean

and lubricate all surface areas as required using Grease (AMM 125/H-20, 20-95-11, Item 034). Install the stop cap.

Fuselage

530027 Fuselage Skin :

Do a visual inspection.


PAGE : 222

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018


Area F2: Flight compartment.Access: Soundproofing bags on the forward pressure

bulkhead removed.

NOTE

It is not necessary to remove the soundproofing on the forward pressure bulkhead

until the second 48 month inspection (96 months). Remove the soundproofing at every

48 month inspection from that time onwards.


Area Inspection

050762

(a) Airframe.

(b) Electrical.

(c) Avionics.

(d) Engine.



Flight Controls

270068

Aileron Servomotor assembly SVO-85B (P/N 622-

5027-001).

Lubricate and clean as detailed in Collins SVO-85B/C

Service Information Letter SIL 1-01.


Access: Passenger service units lowered. Toilet trim removed. Cable duct floor panels

F29 to F39 inclusive removed.

Floor panels F61A, F61B, F64A, F64B, F68A, F68B, F71A, F71B, F72, F74A, F74B,

F74C, F76, F78, F82A, F82B, F83 and F87 removed.


Area Inspection

050763

(a) Airframe.

(b) Electrical.

(c) Avionics.

NOTE : Make sure ALL area inspections are done in accordance with the Inspection

Requirements.


PAGE : 223

PART OF INSPECTION

ISSUE : 1

REVISION : 0

DATE : 27/02/2018



Access: Passenger service units lowered. Toilet trim removed. Cable duct floor panels

F29 to F39 inclusive removed.

Floor panels F61A, F61B, F64A, F64B, F68A, F68B, F71A, F71B, F72, F74A, F74B,

F74C, F76, F78, F82A, F82B, F83 and F87 removed.


Area Inspection

Air Conditioning

210010 Pressure regulators .

Clean the filter screens (Ref. AMM 21-30-55).

210011

Outflow/safety valves .

Clean the outflow valve poppet valve and seat (AMM 21-30-

25).

If required, clean exterior of the outflow valve using a cloth

or sponge soaked in cleaning fluid ( AMM 21-30-25).

Check that the orifice in the cabin air filter connection is free

of obstruction.

Check that the cabin air sense ports are free and clear of

any obstruction.

Functionally test operation of valves (AMM 21-30-25, 501).

210014 Cabin air filters (pressurization system):

Inspect.

210018

Altitude switch, cabin depressurization warning.

Do a functional test (AMM 21-30-70, 201).

NOTE

Mod. 259747C (SB 21-3136) introduces a second Altitude

Warning Switch (set to 14,000 ft.) to permit operation at

high altitude airfields.


Access: Hydraulic box cover removed.


Area Inspection

050764

(a) Airframe.

(b) Electrical.

(c) Avionics.


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Access: Hydraulic box cover removed.


NOTE Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para.(6) of the Introduction at the front of this

schedule.

Electrical Power

240017

Earth stations *16, *17, *18 and *19: Inspect. Look for signs of arcing. Do an impedance check (AMM 24-01-00).

NOTE It is not necessary to do this task until the second 48 month inspection (96 months). Do the task at every 48

month inspection from that time onwards.

Flight Controls

270069

Elevator Servomotor assembly SVO-85B (P/N 622-5027-001). Lubricate and clean as detailed in Collins SVO-85B/C Service

Information Letter SIL 1-01.

Area T1: Horizontal and vertical stabilizers, to include elevators and rudder.

Access: Panel T12 removed.


Area Inspection

050765

(a) Airframe.

(b) Electrical.

(c) Avionics.



Flight Controls

270070

Rudder Servomotor assembly SVO-85B (P/N 622-5027-001).

Lubricate and clean as detailed in Collins SVO-85B/C Service

Information Letter SIL 1-01.

270071 Rudder Trim Jack

Do an inspection (AMM 27-20-111, 301).

270072 Elevator Trim Jack


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Access: Panel T12 removed.


Do an inspection (AMM 27-30-51, 301).

Area W1, W2: Wings, LH and RH.

Access: Panels W329, W429, W507 and W508 removed.


Area Inspection

050766

(a) Airframe.

(b) Electrical.

(c) Avionics.

NOTE


Requirements .

Fuel

280016

Low pressure fuel valve support strut. Part No. 25 PF361,

25 PF361-5A (Mod. 25G310A) and 25 PF363.

Do a visual inspection of the low pressure fuel valve support

strut, attachment bolt and drain hole for corrosion.

NOTE

If corrosion is found replace the affected part.

------------- END ---------------


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PART-3 STRUCTURAL INSPECTIONS

PART-3

STRUCTURAL INSPECTIONS

1. STRUCTUAL INSPECTIONS


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PART-3

1. STRUCTUAL INSPECTIONS

Instructional Data

NOTE




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PART-3

STRUCTUAL INSPECTIONS

Area F1: External fuselage, nose cone, tail cone, wing-to-fuselage fairings.


530001

8 years, then every 4 years. Skin exterior under the dorsal intake, forward of Frame 19. Access: Dorsal intake removed.

Detail inspect for cracks, signs of corrosion and

deterioration of the protective treatment. Detail inspect for chafing rivets.


530002

8 years, then every 4 years. Fuselage skin under wing-to-fuselage fairings. Access: Panels F124 and F224 removed.

Inspect visible areas of skin for cracks and signs of

corrosion using flashlight, mirror and borescope probes. Inspection completed at.......................... Hrs. Date......................

NOTE :It is recommended that the following two tasks are done at the same time.

530003

Between 15 to 18 years, then every 8 years. Fuselage skin covered by the ventral fuel tank. Access: Ventral fuel tank removed.

Detail inspect especially for signs of corrosion and

deterioration of the protective treatments. Detail inspect attachment points and links.


530004

Between 15 to 18 years, then every 8 years. Ventral fuel tank and attachments. Access: Ventral fuel tank and tank access panels removed ( AMM 28-10-15)

Detail inspect the tank internal structure, skin, access

panels, bolts and fasteners, fuel system components and pipelines. Pay particular attention to the security of the nylon vent

pipes and the integrity of the sealant fillets at the pipe joints . Inspect the rubber drain non-return valve in the vent system

balance pipe for deterioration and splitting. Detail inspect attachment points and links. Detail inspect the fuel seal block assembly (P/N: 25-8PT341-1A) at the ventral tank diaphragm for missing sealer, voids


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and corrosion.



530004

NOTE

If missing sealer, voids or corrosion are found, remove

the fuel seal block assembly for further detailed

inspection.

Inspection completed at......................... Hrs. Date......................

NOTE : It is recommended that the following three tasks are done at the same time.

520008

12 years then every 8 years.

Main entry door.


Comply with instructions in NTM 52-80-102.

Inspection completed at.......................... Hrs. Date.....................

530007

12 years and then every 8 years.


Access: Panels F124, F224, W501 removed.

Detail inspect links, brackets and bolts for cracks, signs of

corrosion, fretting and wear ( AMM 53-40-01 )

Inspection completed at.........................Hrs. Date........................

530009

27,000 flights and then every 4500 flights.

Fuselage lap joints.



Inspection completed at.................... Flts. Date.......................

530010

Whenever the wings are separated from the fuselage.


Detail inspect the skin of the fuselage in the area that is

covered by the wing structure.

Detail inspect the wing attachment brackets and the frame

build-up at frames 13 and 16.

Detail inspect the drag spigot bearing.

Inspect the drag spigot housing.

Inspection completed at...................... Hrs. Date.........................


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530018

4800 flying hours, then every 2400 flying hours.

Fuselage skin adjacent to cabin window cutouts .

Detail inspect skin.

Inspection completed at...................... Hrs. Date.........................

Area F2: Flight compartment


510001

Every 5000 landings or 12 years, whichever occurs first. Nose landing gear bay sidewalls. Access: Refer to NTM Technique.

Comply with instructions in NTM 53-10-111. Inspection completed at........................ Landings. Date......................

510002

5000 flights then every 1000 flights. Front pressure bulkhead. Access: Sound-proofing blankets removed.

Detail inspect the upper sidewall beams and the rudder

pedal clearance pressings for cracks (RSRM 53-10-11, Front

Pressure Bulkhead Pre-Mod. 253090C and Front Pressure

Bulkhead Mod. 253090C). Pay special attention to the area in the vicinity of the joint

with the canopy center post. Inspection completed at......................... Flts. Date......................

510003

12 years, then every 4 years. Flight compartment skin and window structure above windshields. Access: Refer to NTM Technique.

Comply with instructions in NTM 53-10-105A. Inspection completed at.................... Flts/Hrs. Date....................

510004

Every 20,000 flights. Upper canopy rail at intersection with the canopy posts. Access: Trim and insulation removed.

Detail inspect. Inspection completed at........................ Flts. Date.......................




Center fuselage structure below the floor, nose landing gear


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bay to Frame 13 and Frames 16 to 19.


Comply with instructions in:

NTM 53-10-108

NTM 53-10-107

NTM 53-10-108B

NTM 53-10-109.

Inspection completed at....................... Hrs. Date........................

510006

Between 15 to 18 years and then every 8 years.

Structure below escape hatch, Frames 13 to 14.

Access: Escape hatch removed, leaded vinyl sleeve peeled

back from lower corners of the escape hatch surround to

expose the apertures in the surround.

Detail inspect Frames 13 and 14, as far as is possible, for

signs of corrosion using a borescope probe.

Inspection completed at........................ Hrs. Date.......................

520009


Escape hatch.

Access: Trim removed.

Detail inspect the structure internally and externally for

cracks, signs of corrosion and the deterioration of the

protective treatment.

Inspection completed at...................... Flts./Hrs. Date.................

510007

Between 15 to 18 years and then every 8 years.

Center fuselage structure below the floor, frames 8 to 17.


Comply with instructions in NTM 53-10-106A.





Center fuselage structure below the floor, Frames 13 to 16.


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Comply with instructions in NTM 53-10-108A.

NOTE : In certain instances it may be necessary to lower

the wing or separate the wing from the fuselage to insert

the film packs. In order to determine the conditions of

individual airplanes a test may be done by attempting to

pass a strip of vinyl carrier, to the dimensions given in the

relevant NTM, between the fuselage lower skin and the

wing top surface.


510009

8 years and then every 4 years.

Entry door surround.

Access: Panel F66A, F66B, F66C removed.

Detail inspect the structure at the lower edge of the

surround for signs of corrosion using a borescope probe

inserted through the lightening holes in the intercostal.


510010

Between the 15th and 18th year of aircraft operation and

then every 8 years.

Center fuselage structure, above the floor.


NOTE : The most economical and practical time to do this

inspection is when the quick trim is removed for refurbishing or other reasons. NOTE :Airplanes without the digital pressurization control

system Mod. 25G726A/C or Mod. 25G726B/C. When installing local furnishings, make sure a minimum clearance of 1.0 inch between the motor of the fan

operated venturi and local furnishings is kept. Peel back the sound dampening material sufficiently to

visually inspect the skin in the vicinity of the fasteners and other attachments. It is not necessary to remove the sound

dampening material. Inspect the skin, as far as is possible, for cracks, signs of

corrosion and deterioration of the protective treatment. Comply with instructions in: NTM 53-10-101. NTM 53-10-102. NTM 53-10-103A.


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NTM 53-10-104. NTM 53-10-106.

Inspection completed at......................... Hrs. Date.....................



530011

Every 4 years. Front face of rear pressure bulkhead (Frame 19). Inspect left-hand side of bulkhead with the soundproofing

blankets removed. NOTE

Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C. When installing local furnishings, make sure there is a minimum clearance of 1.0 inch between the motor of the

fan operated venturi and the local furnishings. Look for signs of corrosion at the boundary angle to Frame 19

joints. NOTE

If you find any defects, extend the inspection to include the right-hand side of the bulkhead. Inspection completed at......................... Hrs. Date......................

530012

Every 8 years. Front face of rear pressure bulkhead (Frame 19). Inspect right hand side of bulkhead with soundproofing

blanket removed. NOTE

Airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C. When installing local furnishings, make sure a minimum clearance of 1.0 inch between the motor of the fan

operated venturi and local furnishings is kept. Look for signs of corrosion at the boundary angle to frame 19

joints.

Inspection completed at.......................... Hrs. Date......................

Area F4: Rear fuselage.


530013 Every 10,000 flying hours. Pylon engine main mounting attachment fittings.


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Access: Refer to NTM Technique. Comply with instructions in NTM 53-10-110. Inspection completed at...................... Flts. Date.........................



530014

Every 20,000 flying hours. Rear engine mount fittings. Access: Refer to NTM Technique.

Comply with instructions in NTM 53-10-110A. Inspection completed at...................... Flts. Date.........................

530015

Every 30,000 flying hours. Vertical stabilizer root attachment to fuselage. Access: Refer to NTM Technique.

Comply with instructions in NTM 55-30-104. Inspection completed at........................ Flts. Date......................

530016

Every 10,000 flying hours. Engine beam. Access: Engines and engine main mounting attachment fittings

removed (AMM 71-20-00, 401). NOTE : The pylon firewall below the engine front mount

assembly and the inside of the engine pick-up mount

bracket can be visually inspected from inside the pylon access panels. The ends of the engine beam with all the

doublers and angles can be inspected from inside the rear equipment bay area.

Detail inspect the multi-layer ends of the beam forming pick-ups for damage, cracks and signs of corrosion using X 10 magnification.

Inspection completed at...................... Flts. Date.........................

530019

PATS APU GTCP36-150W. Every 12 months. NOTE : If any of the following inspections show an

abnormal indication or requires the replacement of structural parts, do Tasks 530022 and 530023. Detail inspect the following items accessible without removal from the rear equipment bay, for cracks or failures:

All APU support structure external to the fire enclosure. Remove the oil filler door and all access covers in the

bottom enclosure and inspect all the APU structure internal to the fire enclosure.


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Inspect the main engine crossbeam and frame 21 in the

areas immediately adjacent to the APU attachment fittings. Inspect the five pairs of isolator mounts for deterioration of

the silicone rubber. Visually check on the exterior of the fuselage and make sure that the APU exhaust duct is centered in the exhaust shroud duct, and that the exhaust shroud duct is centered in the skin cutout for the APU exhaust. Inspection completed at..................... Hrs. Date..........................



530021

PATS APU GTCP36-150W. Every 3000 APU running hours. APU Support Structure:

Detail inspect all mounting parts for cracks or damage. Detail inspect all fuselage attachments point for cracks or

damage. NOTE :Repair as required. Inspection completed at..................... Hrs. Date..........................

530022

PATS APU GTCP36-150W. Every 4500 APU running hours. NOTE : Do this task in conjunction with the removal of the

APU for the Hot Section inspection (Out of Phase Task #

490006). Remove and detail inspect the items listed in Table 1 (Located after Area F4 inspections).

NOTE : Replace all parts with the evidence of any damage. Inspection completed at..................... Hrs. Date..........................

530023

PATS APU GTCP36-150W. Every 4500 APU running hours. NOTE : Do this task in conjunction with the removal of the


490006). Detail inspect the fuselage structure for cracks, particularly

the support bracket attachment holes in the upper cap of the main engine cross beam and at the top and left side of the fuselage at frame 21.

NOTE : The attachment brackets secured to the airframe

will have to be removed so that a detailed inspection of the holes drilled in the airframe for the APU fitting can be


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done. Inspection completed at..................... Hrs. Date..........................



530024

PATS APU GTCP36-150W. Every 22,500 APU running hours. APU support hardware listed in Table 2 (Located after Area F4

inspections) Do a fluorescent penetrant inspection (FPI) (NTM 125, General

Techniques, Part C Liquid Penetrant) OR Replace. NOTE : FPI using MIL-1-25135C, Group 6A penetrant. Reject

all linear indications. NOTE : Do this task in conjunction with the removal of the


490006). Inspection completed at..................... Hrs. Date..........................

530025

PATS APU GTCP36-150W. Every 10,000 flights. Exhaust and inlet doubler frames and stringers. Detail inspect internally and externally for minute cracking

conditions or other defects particularly near the exhaust. NOTE : Repair as required.


Table 1 : (PATS APU GTCP36-150W - Items to be inspected in task # 530022)

Part Number Item Quantity

2380054-5 Mount Bracket 2

2380054-7 Mount Bracket 2

2380138-1 Side Brace Bracket 1


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238043-401 or 238043-411 Cradle Mount Assembly 1

2380062-19 Mount Adapter Assembly 2

2380055-403 or 2380055-413 Attach Bracket 3

2380137-401 or 2380137-411 Engine Mount Assembly 1

2350066-1 Special Bolt 5

2380058-5 or 2380058-15 Engine Beam Anchor Bracket 2

2380056-403 or 2380056-413 Mount Tube Assembly 1



2380136-1 or 2380136-11 Eye Bolt 3

2380148-1 Bracket 4

MS27039-1-17 Screw 8

NAS1351-4H12P Cap Screw 16

NAS6203-10 Bolt 8

NAS6203-26 Bolt 2

NAS6203-27 Bolt 1

NAS6203-31 Bolt 1

NAS6206-19 Bolt 2

NAS6206-31 Bolt 1

AN5-13 Bolt 2



2380143-401 or 2380143-411 Cradle Mount Assembly 1

2380062-19 Mount Adapter Assembly 2



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550001

Every 4 years.

Elevators and Tabs:

Remove elevator (AMM 27-30-22, 401).

Detail inspect.

Inspect the bearings for smooth operation and replace as

required.

Detail inspect the hinge brackets for security and cracks

with a X 10 magnifier. Look for signs of corrosion.

Install elevator (AMM 27-30-22, 401).


550002

Every 4 years.

Elevator trim tabs, connecting rods:

Inspect the rod end bearings for smooth operation and

replace as required.

Apply a coat of silicone lubricant to both exterior surfaces of

the bearing at each connecting rod end (AMM 27-30-00,

301).

NOTE : The silicone lubricant is applied to give the rod end

bearing protection against corrosion.


550003

8 years, then every 4 years.

Elevators.

Access: Refer to relevant NTM Technique.

Comply with instructions in NTM 55-20-101 and NTM 55-20-

102.

If corrosion is found extend the X-Ray coverage until a

complete rib bay is found to be free from corrosion.

Inspection completed at....................... Hrs. Date..................


Rudder and Tab:


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Remove (AMM 27-20-23, 401).

Detail inspect.

Inspect the bearings for smooth operation and replace as

required.

Install (AMM 27-20-23, 401).


550005

Every 4 years.

Connecting rods, rudder trim tab and anti-servo tab:

Inspect the rod end bearings for smooth operation and

replace as required.




550006


Rudder.



Inspection completed at...................... Hrs. Date..................

550007

Every 8 years.

Rudder hinge brackets and attachments.

Access: Rudder and rudder hinge bracket cover plates

removed.

Detail inspect the rudder hinge brackets, using a X 10

magnifier.

Inspection completed at ......................... Hrs. Date ......................

550009

Every 8 years. Horizontal stabilizer. Access: Leading edges removed. Elevators removed. Shroud

panels T21R, T22L, T23R, T24L, T25R, T26L and T45 removed. Fairing panels T4L, T4R, T5, T6L, T7R, T8L, T9R

and T13 removed.


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Detail inspect the front face of the front spar for cracks and

signs of corrosion. Detail inspect the rear face of the rear spar for cracks and

signs of corrosion. Detail inspect the vertical stabilizer to horizontal stabilizer

attachment fittings. Detail inspect the elevator hinge brackets. Apply Corrosion Preventive Compound (AMM 55-13-00,

301). NOTE : Application of Corrosion Preventive Compound is

ONLY applicable to the series 800XP and 800XP/850XP

Pro Line 21 airplanes. Inspection completed at........................ Hrs. Date.......................

550010


Vertical stabilizer.

Access: Leading edge panels, upper vertical stabilizer and

rudder removed.

Detail inspect the structure rendered visible.

Detail inspect the rudder hinge brackets for security, cracks

and signs of corrosion.

Comply with instructions in:

NTM 55-30-101

NTM 55-30-102

NTM 55-30-103.

With the leading edge removed detail inspect the internal

structure of the vertical stabilizer for cracks and signs of

corrosion using a borescope probe through the access holes

in the front spar and through the root rib.

Inspection completed at........................ Hrs. Date................



550011

16 years, then every 8 years (see NOTE). Horizontal stabilizer to vertical stabilizer attachments . Access: Horizontal stabilizer removed.

NOTE


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Airplanes which have had the horizontal stabilizer removed at or subsequent to the 12 year inspection can be considered to have satisfied the initial inspection requirement.

Detail inspect the attachment lugs for cracks, signs of

corrosion and elongation of the attachment bolt holes. Inspect the bolts for signs of wear or corrosion. Replace any worn bolts. If holes are elongated replace

bolts, see SRM 55-10-41. Inspection completed at......................... Hrs. Date....................

550012

24 years and then every 8 years. Horizontal stabilizer. Access: Refer to relevant NTM Techniques.

NOTE For convenience and improved access it is recommended that this inspection is done when the horizontal stabilizer is removed for the inspection of the attachment lugs (Task

No. 550011). Comply with instructions given in one of the methods below : Fokker Bond Test NTM 55-10-104A Schlumberger Sonatest NTM 55-10-104B Staveley Sonic Bondmaster NTM 55-10-104C.


550013

Between 15 to 18 years, then every 8 years. Horizontal stabilizer. Access: Refer to relevant NTM Techniques.

Comply with instructions in: NTM 55-10-101 NTM 55-10-102 NTM 55-10-103 NTM 55-10-105.

Inspection completed at........................ Hrs. Date...............



550014

15,000 flights and then at every X-Ray inspection of the

horizontal stabilizer internal structure (Task No.550013). Horizontal stabilizer top skin 'T' fitting and joint strap at the center line of the stabilizer.


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Access: Upper vertical stabilizer removed. Detail inspect for cracks and signs of corrosion.

Inspection completed at........................ Flts. Date......................

550015

Every 2 years. Elevators:

Remove and inspect mass balance weight side plates, look

for signs of corrosion (AMM 27-30-91, 601). Remove and inspect mass balance weights, spigots and

installation, look for signs of corrosion (AMM 27-30-91, 601). NOTE : Remove all corrosion found from the spigots to a

maximum depth of 0.03 in. and paint with epoxy primer

(AMM 125/H-20, 20-95-401, Item No. 474). NOTE : If excessive corrosion is found contact: Repair Design Office Beechcraft Corporation 9709 East Central P.O. Box 85

Wichita, KS 67201-0085, U.S.A

Assemble the spigots and mass balance weights (AMM 27-30-91, 601). Apply corrosion preventive compound LPS 3 ( AMM 125/H-20, 20-95-11, Item No. 089) or ACF 50 (AMM 125/H-20, 20-95-11, Item No. 090) (AMM 27-30-91, 601). Install the side plate assembly (AMM 27-30-91, 601).

NOTE The balance of the elevator must be checked and if necessary adjusted only when a repair has been done or a paint finish changed.

CAUTION Make sure that the mass balance weights are installed on

the same side that they were removed from. Inspection completed at..................... Hrs. Date..........................



320028

8 years, then every 4 years. Main landing gear fairing strut.



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570007


Wing bottom skins and stringers between the front and rear

spars, Rib 0 to Rib 1 and between the center spar and rear

spar from Rib 1 to Rib 4.



Detail inspect the bottom stringers in the vicinity of the wing

skin restraint ties with the aid of a flashlight and mirrors.

NOTE

If corrosion is found while doing NTM 57-30-101, extend

the X-Ray coverage (NTM 57-30-102) until a complete rib

bay is found to be free from corrosion.

NOTE

If the quality of the radiographs is impaired by the

presence of pockets of fuel it would indicate that the

internal fuel drain paths are blocked. Operators are

advised to remedy this condition at the first convenient

opportunity.

Inspection completed at..................... Hrs. Date.........................

570008


Main Landing Gear and sidestay attachment fittings.

Access: Panels W324, W424 removed.

Detail inspect the landing gear pick-up fittings, specially the

sidestay pick-up, for cracks, signs of corrosion and signs of

movement.

Make sure the drain holes are unobstructed.

Check the tightness of all securing bolts.

Inspection completed at.................... Hrs. Date............................


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570009

4800 flying hours, then every 1200 flying hours.

Wing bottom skin (LH and RH) adjacent to flap outboard hinge

at Rib 8.

Access: Hinge fairings, panels W314 and W414, removed.

Detail inspect for cracks and signs of corrosion.




570010

Every 4800 flying hours or 8 years, whichever is the

sooner.

Wing front spar, forward face.

Access: Wing leading edges removed.

Detail inspect for cracks, signs of corrosion and distortion,

specially between Ribs 1 and 3.

Inspect leading edges for cracks, signs of corrosion,

damage and integrity of the bolt holes.

NOTE

When replacing the leading edges the profiles must be

maintained (see SRM 57-41-00).

Inspection completed at.................... Hrs. Date...........................

570011

4800 flying hours or 8 years, whichever is the sooner,

then every 2400 flying hours or 4 years.

Wing rear spar, rear face.

Access: Ailerons, aileron shrouds, flaps and airbrakes

removed.

Inspect for cracks, signs of corrosion, distortion and

damage.

Inspect control surface hinge brackets on the rear spar for

wear, cracks, signs of corrosion and security.

Inspection completed at....................... Hrs. Date.......................

570012 4800 flying hours or 8 years, whichever is the sooner,

then every 2400 flying hours or 4 years.


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Airbrakes.

Access: Airbrakes removed.

Detail inspect.

Inspect the hinges for security.

Inspection completed at......................... Hrs. Date.....................

570013

Every 2400 flying hours or 4 years, whichever is the

sooner.

Ailerons:

Remove (AMM 27-10-31, 401).

Detail inspect.

Inspect the bearings for satisfactory condition and make

sure there is adequate lubrication ( AMM 125/H-20, 20-09-22,

201).

Install (AMM 27-10-31, 401).




570014

Every 2400 flying hours or 4 years, whichever is the sooner. Connecting rods, aileron trim and servo tabs:

Lubricate or replace the front and rear rod end bearings, as

required (AMM 125/H-20, 20-09-22, 201). Apply a coat of silicone lubricant to both exterior surfaces of

the bearing at each trim tab connecting rod end (AMM 27-10-00, 501).

NOTE The silicone lubricant is applied to give the rod end bearing protection against corrosion. Inspection completed at......................... Hrs. Date......................

570015

4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying hours or 4 years. Ailerons. Access: Refer to NTM Technique.

Detail inspect the hinge brackets with a X 10 magnifier. Comply with instructions in NTM 57-50-107.



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570016

4800 flying hours or 8 years, whichever is the sooner, then every 2400 flying hours or 4 years. Flaps and flap vanes. Access: Refer to relevant NTM Technique.

Inspect hinge brackets for security, freedom from cracks

and signs of corrosion. Inspect bearings for satisfactory condition and adequate

lubrication. Comply with instructions in NTM 57-50-105 and NTM 57-50-106.

NOTE If corrosion is found during the X-Ray inspection, extend

the X-Ray inspection coverage until a complete rib bay is

found free of corrosion. Inspection completed at....................... Hrs. Date.......................

570017

24,000 flying hours and then every 4800 flying hours. Wing bottom skin at attachment to front spar, between Ribs 1 and 7. Access: As visible.

Detail inspect for cracks and signs of corrosion. Inspection completed at....................... Hrs. Date.................



570018

24,000 flying hours and then every 9600 flying hours. Wing bottom skin centerline joint strap. Access: Keel skid removed.

Detail inspect for cracks and signs of corrosion. Inspection completed at...................... Hrs. Date.........................


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570019

24,000 flying hours and then every 9600 flying hours. Upper surface of the wing bottom skin at the attachment to the centerline joint adjacent to Rib 0. Access: Refer to NTM Technique.

Comply with instructions in NTM 57-30-104. OR 24,000 flying hours and then every 7200 flying hours.

With the sealant removed to expose the skin surface, detail

inspect for cracks at the bolt line. Inspection completed at....................... Hrs./Flts. Date........................

570020

24,000 flying hours and then every 12,000 flying hours. Wing bottom skin centerline butt strap and center section beams (24 positions). Access: Refer to NTM Technique.

Comply with instructions in NTM 57-00-102. Inspection completed at........................ Hrs. Date.......................

570021

Whenever the wings are separated from the fuselage.

Wing top skin in the area that is covered by the fuselage

structure and main attachment brackets.


Detail inspect the skin, stiffeners and main attachment

brackets for cracks, signs of corrosion, security of rivets and

damage.

Inspect the drag spigot for wear.

Inspect the spigot location plate for security of attachment.


570022

Every 4800 flying hours. Rear spar, rear face between Rib 1 LH and Rib 1 RH. Access: Main landing gear doors and panels W325, W425,

W507 and W508 removed. Detail inspect the rear face of the rear spar.




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570023

Every 4 years. NOTE

Applicable to airplanes without BC Winglets. Aileron horn balance weight. Access: Aileron horn balance weight cover removed.

Detail inspect the horn balance weight for signs of

corrosion. If signs of corrosion are found, then do an X-Ray inspection

of the area Comply with instructions in NTM 57-50-107.


570028

4800 flying hours or 8 years, whichever is the sooner, then every 4 years.

NOTE Applicable to airplanes without BC Winglets.

Aileron at outboard hinge casting. Do the "Aileron Horn" Inspection/Check: ( AMM 27-10-31,

601). Inspection completed at....................... Hrs. Date........................

570024

12,000 flying hours, then every 7200 flying hours. Wing bottom skin at attachment to Rib 1 LH and RH. Access: As visible.

Detail inspect the skin where it is bolted to Rib 1 LH and

RH. Inspection completed at....................... Hrs. Date........................

570025

Every 4800 flying hours. Wing bottom skin at attachment to the rear spar, between Rib 1 LH and Rib 1 RH. Access: Main landing gear doors open and keel skid fairing in

the area of the main landing gear doors removed. Detail inspect the skin where it is bolted to the rear spar,

between Rib 1 LH and Rib 1 RH. Inspection completed at....................... Hrs. Date........................

570026

Every 4 years. Wing leading edges. Access: TKS panels removed (also any material that might

interfere with visual inspection). Inspect, specifically rebate area for cracks and signs of corrosion (SRM 57-41-12, 201). Inspection completed at........................ Hrs. Date........................



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570027

Every 4800 flying hours or 8 years, whichever is the sooner. Wing internal structure forward of the center spar including the front and center spars from Ribs 0 to 4, and between and including the front and rear spars from Rib 4 to the wing tip . Access: Wing leading edges W102, W120, W130, W202, W220,W230 removed. Front spar access panels W301, W302, W303, W304, W305, W401, W402, W403, W404, W405 removed. Rear spar access panels W115, W116, W117, W215, W216, W217 removed.

NOTE Rear spar access panels W114 and W214 need not be removed for this inspection unless required for other work in the area. Top skin panels W106, W108, W112, W119, W206, W208, W212, W219 removed. Bottom skin panels W306, W308, W309, W310, W312, W313, W329, W330, W406, W408, W409, W410, W412, W413, W429, W430 removed.

Detail inspect the internal structure, as visible. Inspect for signs of corrosion and microbiological

contamination. Detail inspect the bottom stringers in the vicinity of the wing

skin restraint ties with the aid of a flashlight and mirrors. NOTE

If corrosion or contamination is found, clean and repair in accordance with the Structural Repair Manual. Do the

shock preventative treatment in (AMM 28-10-00, 701). Fuel system non-return valves in inner and outer wings:

Remove and inspect (AMM 28-20-32, 401). Pay particular attention to the condition of the valve and

valve seat. Inspection completed at........................ Hrs. Date........................



530017 Whenever the brackets are removed from the engine.

NOTE


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This task is only required when the engine has accomplished a Major Periodic Inspection. Refer to the

relevant Honeywell Light Maintenance Manual: 750, 800XP and 800XP Pro Line 21 - TFE731-5BR-1H Series

engine. 900XP - TFE731-50R-1H Series engine. Forward engine mounting brackets, Part No. 3071071-3. Access: Engine cowlings M1L, M2R, M3L and M4R removed. Remove the mounting brackets. Inspect for cracks using a magnetic particle inspection (LMM

72-00-06). Inspection completed at....................... Hrs. Date........................

------------- END ---------------


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PART-4 OUT OF PHASE INSPECTION

PART-4

OUT OF PHASE INSPECTIONS

1. OUT OF PHASE INSPECTIONS


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PART-4

1. OUT OF PHASE INSPECTIONS

Instructional Data

NOTE




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PART-4



Air Conditioning

210006

Every 400 Hours. Water separator.

Inspect for satisfactory condition (AMM 21-10-95, 601). Note Operators may adjust this time based on servicing

experience.

210007

Every 400 Hours. Water separator . Inspect the following items are free from blockages and obstructions (AMM 21-10-95, 601):

Water separator water drain. Water separator water drain pipeline. HP line to water injector nozzle. Water injector nozzle.

NOTE Operators may adjust this time based on servicing experience.

210022

After 50 flying hours but not more than 300 flying hours from airplane build OR after disturbance of ducts or rubber sleeves. Air conditioning ducts:

Check the duct joint clamp bolts for the correct torque

loading: AMM 21-10-15, 201

AMM 21-10-87, 201

AMM 21-10-95, 401


Electrical Power

240001

Between 200 and 400 Hours. Starter/generators:

Remove and inspect (AMM 24-30-21, 401). Do a brush wear check (AMM 24-30-21, 601). Inspect cooling fan. Inspect splines for wear (AMM 24-30-21, 401). Inspect engine drive for wear. Install starter/generator (AMM 24-30-21, 401).



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PART-4



Electrical Power (Cont)

240024

Every 500 APU running hours. APU starter/generator:

Remove (AMM 24-30-21). Check the brush wear (AMM 24-30-21, 601). Inspect the cooling fan. Inspect the splines for wear (AMM 24-30-21, 401). Inspect the engine drive for wear. Install the APU starter/generator (AMM 24-30-21, 401).


Fire Protection

260008

Every 6 months. Smoke Detection System

Do a function test: MMA 26-11-00


Flight Control

270001 Transferred to Part 1, Minor Inspections.

270061

After 200 flying hours and not more than 300 flying hours from the airplane build or after control cable replacement. Control cables. Check the tensions of the:

Aileron and aileron trim control cables AMM 27-10-00, 501). Rudder and rudder trim control cables (AMM 27-20-00, 501). Elevator and elevator trim control cables (AMM 27-30-00,

501). Flap control cables (AMM 27-50-02, 501). Airbrake control cables (AMM 27-61-02, 501).


270063

Whenever the SVO-85B servo or its mating servo mount are

removed and replaced in the airplane. Servomotor assembly SVO-85B (P/N 622-5027-001). Lubricate and clean as detailed in Collins SVO-85B/C Service

Information Letter SIL 1-01. Inspection completed at.......................... Hrs. Date......................


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PART-4



Fuel

280010

After 200 flying hours and not more than 300 flying hours from

the airplane build or after control cable replacement.

Control cables. Check the tensions of the:

LP fuel valve control cables (AMM 28-20-83).

Crossfeed and wing transfer valve control cables (AMM 28-

20-83).

Auxiliary fuel transfer valve control cables (AMM 28-20-

83) (if ventral tank installed).



300007

Every calendar month.

Applicable if the airframe de-icing system has not been

operated during the last calendar month.

Airframe Ice protection - purge the airplane ice protection

system (AMM 12-30-00, 301).


Landing Gear

320029

Between 25 to 50 landings from build or after nose landing

gear drag stay replacement.

Nose landing gear drag stay. Check clearances (AMM 32-20-

21, 601).


320038

NOTE

This task is not applicable to airplanes Post Mod. 25G295

or Post SB. 32-3779.

Every month if the airplane has been exposed to runway de-

icing:

Lubricate the Main landing gear sidestay shims (Part 7 -

Lubrication, Monthly lubrication).



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PART-4



Navigation

340002

Pitot/static drain traps. Pre-SB.34-3282 (Mod. 25F889B) or Pre-Mod. 25F889A. Drain, do a

leak test ( AMM 34-11-19, 501). Post SB.34-3282 (Mod. 25F889B) or Post Mod. 25F889A. Drain

(AMM 34-11-19, 501). Note Do this task in conjunction with FAR

pitot/static system checks (Task 340006). Inspection completed at.......................... Hrs. Date......................

340006

Pitot/static and stall warning systems. Do the following tests (AMM

34-11-19, 501): Pressure Test Complete Pitot System. Suction Test Complete Static System. Pressure Test Stall Vent System (This procedure only applies to

airplanes Pre-Mod. 25G206A or 25G206B). NOTE

Do this task in accordance with FAR requirements. Inspection completed at.......................... Hrs. Date......................

340007

Pitot system isolation valves. Make sure of full and free operation. NOTE

Do this task in conjunction with CAAT pitot/static system checks

(Task 340006). Inspection completed at.......................... Hrs. Date......................

340012

Every 36 months, or at a time period agreed with the local regulatory authority. Compass systems:

Do a check compass swing of the compass systems at four

headings 90 degrees apart. Compare deviations, if any are found, with the existing deviation

card. If deviations are found then do a compass swing: AMM 34-20-05,

501 Inspection completed at.......................... Hrs. Date......................

340013

After repaint or maintenance in the area affecting the airflow over static ports. Static plates and Airframe Comply with RVSM requirements ( AMM 34-11-29, 601) for the area

disturbed. Inspection completed at.......................... Hrs. Date......................


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PART-4



Auxiliary Power Unit

490001

Perform in conjunction with Task 490003. PATS APU GTCP36-150W.

Visually inspect exhaust for cracks or deformation. Visually inspect for loose or frayed wires. Inspect for signs of corrosion.


490002

Every 750 APU running hours. PATS GTCP36-150W APU. Igniter plug (CMM 49-40-33):

Remove, clean, inspect and install. Inspection completed at.......................... Hrs. Date......................

490003

NOTE Choose one of the following options. Do either Oil and Filter

change at every 12 months or 1000 flying hours OR do a S.O.A.P.

check at 750 APU running hours/12 months. CAUTION : Do not mix

options.

Option 1. Every 12 months or 1000 flying hours (whichever comes first). PATS GTCP36-150W APU. Oil and filter change, and magnetic drain plug inspection. Lubricating oil system:

Drain and refill (refer to servicing). NOTE

Routine SOAP inspection is not required. Oil Filter Element:

Remove, inspect and replace as necessary (CMM 49-90-47). Magnetic Drain Plug:

Remove, clean, inspect and install magnetic element of drain plug

(CMM 49-90-46). Option 2. 750 APU running hours or 12 months (whichever comes first). Oil and Filter Element:

Do a S.O.A.P. check (in accordance with Honeywell procedures). Magnetic Drain Plug:

Remove, clean, inspect and install magnetic element of drain plug

(CMM 49-90-46). Inspection completed at.......................... Hrs. Date......................


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PART-4



Auxiliary Power Unit (Cont)

490004

Every 1000 APU running hours. PATS GTCP36-150W APU . Fuel filter element:

Remove and replace (CMM 49-30-52). Inspection completed at.......................... Hrs. Date......................

490005

Every 4500 APU running hours. PATS GTCP36-150W APU. Fuel Nozzle Assemblies: Do a fuel flow rate check (CMM 49-20-00, Page Block 601,

paragraph 5, Fuel Nozzle Assembly Flow Rate Check). Inspection completed at.......................... Hrs. Date......................

490006

Every 4500 APU running hours. PATS GTCP36-150W APU. Hot Section Inspection. Do a detailed Hot Section Inspection on the components listed (CMM

49-20-00, Page Block 601, paragraph (4), Detailed Hot Section

Inspection): Turbine Rotor

Deswirl Deflector

Turbine Nozzle

Airflow Deflector Turbine Housing Assembly

Combustion Chamber

Labyrinth Seal

Turbine Wheel Deflector

Retainer Halves

Containment Ring


490007

Every 4500 APU running hours. PATS GTCP36-150W APU. Compressor Rotor:

Visually check compressor rotor for damage by observation

through the compressor screen openings. NOTE : No damage allowed.



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PART-4



Chapter 57 - Wings

570029

Applicable to airplanes with BC Winglets. Every 300 hours. Wing Outer, Upper and Lower Skins: Visually inspect between Ribs 14 and 16 around the fasteners

for cracking in the skins. NOTE

Pay particular attention to those fasteners installed between the front and rear spars. Inspection completed at.......................... Hrs. Date......................

Engine - General

720002

Whenever an engine is removed for a Major Periodic Inspection. Aft cowling, inner fan duct and exhaust duct. Inspect with

the aft cowling removed. Inspection completed at.......................... Hrs. Date......................

720003

Whenever an engine is removed for a Major Periodic Inspection. Exhaust nozzle/exhaust pipe V clamp. Detail inspect,

particularly for cracks in the weld lines of the trunnion nut support tubes, using a X 10 magnifier. Inspection completed at.......................... Hrs. Date......................

Engine - Controls

760003

After 200 flying hours and not more than 300 flying hours from the airplane build or after control cable replacement. Control cables. Check the tensions of the: Power control cables (Ref. AMM 76-10-00, 501, select 750,

800XP, 800XP/850XP Pro Line 21 or 900XP). Inspection completed at.......................... Hrs. Date......................

760004 Do any lubrication requirement for Area M1/M2, refer to Part 7

- LUBRICATION.

------------- END ---------------


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PART-5 SPECIAL INCIDENT INSPECTION

PART-5

Special Incident Inspections

1. OVERWEIGHT OR HEAVY LANDING

2. FLIGHT IN HEAVY TURBULENCE

3. LIGHTNING STRIKE

4. MISUSE OF REVERSE THRUST

5. LANDING GEAR VIBRATION

6. COLD SOAK BELOW-40˚C

7. LANDING OR ABORTED TAKE-OFF IN DEEP WATER

8. AFTER EMERGENCY STOP

9. AFTER ABNORMAL APU CONDITIONS

10. AFTER FLAP OVERSPEED


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PART-5

1. INSPECTIONS AFTER AN OVERWEIGHT

OR HEAVY LANDING

1. INTRODUCTION

Note: If there is more than 5% residual fuel in the ventral tank on landing it is classed as a heavy

landing.

The airplane has been designed to withstand a vertical descent velocity of 6 ft ./second at the

maximum take-off weight and 10 ft./second at the maximum landing weight. Providing the above values are not exceeded then no inspection should be required, but as it is difficult to accurately determine vertical descent velocity the following inspections, checks and tests must be done whenever an unusually heavy or overweight landing has been reported or is suspected. It is not possible to lay down precise details of the inspection procedure to be adopted after every incident due to the wide variations in weight, speed, nature and direction of loads that can be encountered. It is therefore recommended that before starting the inspection the pilot is consulted

for information regarding the landing conditions. Ascertain, for example:

1. Whether the landing was straight, drifting, wing low, nose or tail heavy. 2. If any noise indicative of a structural failure was heard. 3. The weight of the airplane and the fuel distribution.

2. MAIN LANDING GEAR BAYS

A. Inspect: (1) Wheels and brakes for signs of damage. (2) Tires for bulges, cuts, impact damage. (3) Shock absorbers for signs of fluid leakage and damage. (4) Main leg front and rear attachments for cracks and signs of movement. (5) Sidestay assemblies for distortion and other damage. (6) Retraction jack top attachments for cracks, distortion and other damage. (7) Bay structure, particularly in the vicinity of the landing gear attachments, for distortion and signs of

bolt and rivet failures. (8) Main gear doors and fairing attachments for damage and distortion. (9) For signs of hydraulic fluid leakage.

B. Check: (1) Shock absorbers for correct inflation pressures.


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3. NOSE LANDING GEAR BAY

A. Inspect:

(1) Wheels for signs of damage. (2) Tires for bulges, cuts, impact damage. (3) Nose gear attachment fittings for cracks and signs of movement. (4) Drag stay and attachments for distortion, cracks and signs of movement. (5) Shock absorber for signs of fluid leakage and damage. (6) Steering jack and attachments for damage. (7) Retraction jack attachments for cracks, distortion and other damage. (8) Nose gear bay structure, particularly in the areas of the landing gear attachments, for distortion and

signs of bolt and rivet failures. (9) Nose gear doors for distortion, cracks and security.

(10) For signs of hydraulic fluid leakage. B. Check:

(1) Nose gear shock absorber for correct inflation pressure.

1. WINGS

A. Inspect:

(1) Skins generally for distortion, wrinkling or other damage. (2) Ribs 4 aft of the rear spar for cracks and signs of movement. (3) Rear spar webs for buckling in the vicinity of Ribs 4 and 5. (4) Flap screwjacks and attachments, and flap hinges for cracks and signs of movement. (5) Airbrake hinge attachments, airbrake jacks and attachments for cracks and distortion. (6) Aileron hinges for cracks. (7) Ailerons for damage in the vicinity of the hinges and distortion in the vicinity of the balance weights . (8) For signs of fuel or hydraulic fluid leakage.


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5. FUSELAGE

A. Inspect:

(1) Skinning for distortion, wrinkling or other damage. Pay particular attention to the skin joint areas and

the areas around the entry door, escape hatch, wing fillets and wing-to-fuselage attachments. (2) For signs of fuel leakage including ventral tank fuel line connections and tank skin joints. (3) For signs of hydraulic fluid leakage. (4) Ballast weights (if fitted) for security of attachment. (5) To be done after a landing with fuel in the ventral tank.

Note: If there is more than 5% residual fuel in the ventral tank on landing it is classed as a heavy

landing and is considered to be 'Not Empty'.

Examine the following areas for wrinkling, buckling, distortion, elongated rivet holes or any other damage. Stringers: Lower half of the fuselage, from frame 13 (wing forward spar) to frame 23 (ventral tank aft

attachment). Frames: Frame 16 (wing rear spar attachment) and frame 19 (aft pressure bulkhead). Skins: From frame 16 to frame 23 (full fuselage circumference). Ventral tank, attachment fittings and associated structure.

6. REAR EQUIPMENT BAY

A. Inspect:

(1) Electrical panels for security and signs of movement. (2) Cold air unit and heat exchanger mountings for damage and security. (3) APU and mountings for damage and security. (4) Ducting for signs of movement. (5) Fire extinguisher bottles for security. (6) Batteries for security, with no signs of spilt electrolyte . (7) Inverters for security. (8) For signs of fluid leakage, particularly from the hydraulic box.

B. Test:

(1) The inverters for correct functioning.


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7. STABILIZERS

A. Inspect:

(1) Horizontal stabilizer attachments for damage and signs of movement. (2) Elevators for cracks and distortion in the vicinity of the balance weights . (3) Elevator and rudder hinges for cracks. (4) Superstructure for damage and distortion.

8. ENGINES AND MOUNTINGS

A. Inspect:

(1) Cowlings and pod fillet fairings for wrinkling and distortion. (2) Engine mountings and attachments for damage and signs of movement. (3) For signs of fuel or hydraulic fluid leakage.

9. SYSTEMS AND EQUIPMENT/FURNISHINGS

A. Inspect:

(1) Radar scanner for damage and security. (2) Radio racks and components for damage and security. (3) Equipment for correct stowage and security. (4) Water tanks for security and signs of leakage. (5) Instruments and panels for damage and security. (6) Elevator 'G' weight assembly for signs of movement between the torque tube and shear bushes . (7) The emergency lighting inertia switch (if fitted) and make sure it has not operated. (8) All flying control cables and check the tensions.

B. Test:

(1) Function test the 3rd channel stall detector unit (applicable to Pre-Mod 25G206A or B only). (2) The correct functioning of the gyroscopic units. (3) The correct functioning of the radar scanner and radio equipment. (4) The correct operation of the navigation and essential lighting services . (5) The correct functioning of the avionics flight system .


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10. FINAL ITEMS

A. If structural damage is found:

(1) Do the rigging and symmetry checks. (2) Do a cabin leak rate test. (3) Do the landing gear retraction tests.

B. Function test:

(1) All the flying control systems. (2) The engine control system. (3) The engines by doing engine runs.


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PART-5

2. INSPECTIONS AFTER FLIGHT IN HEAVY TURBULENCE

1. INTRODUCTION

In the event of a reported flight in heavy turbulence the following inspections and checks must be done before the airplane is released for further flight.

Note: Damage may be experienced whenever the values of negative and positive "g" approach -0.5g and 2.5g respectively. A fatigue meter count of either level will give a reasonable

indication of severe turbulence.

2. GENERAL

A. Inspect: (1) All external skinning of the wings, fuselage and stabilizers for wrinkling and distortion.

3. WINGS

A. Inspect: (1) Flap hinges for cracks and evidence of movement, and flaps for damage in the vicinity of the hinges . (2) Aileron hinges for cracks, and ailerons for damage in the vicinity of the hinges. (3) Aileron balance arms for distortion and pulled rivets. (4) For no evidence of fuel leakage.

B. Check: (1) The clearance between the aileron balance arms and the wing cut-outs.

4. FUSELAGE

A. Inspect: (1) Skinning in the vicinity of the skin joints, around the entry door and escape hatch, the wing fillet and

the wing-to-fuselage attachments for distortion, wrinkling and evidence of loose rivets . (2) The fuselage for damage at the forward left-hand wing to fuselage side load link attachment point.

5. STABILIZERS

A. Inspect: (1) Horizontal stabilizer for damage and evidence of movement. (2) Elevators and hinges for cracks, and elevator skinning for distortion in the vicinity of the balance

weight. (3) The rudder hinges for cracks, and rudder skinning for distortion .


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6. REAR EQUIPMENT BAY

A. Inspect: (1) Electrical panels for security and evidence of movement. (2) The cold air unit and heat exchanger mountings for damage and security. (3) The APU and mountings for damage and security. (4) The fire extinguisher bottles for security. (5) For no evidence of fluid leakage.


A. Inspect: (1) Engine cowlings and pod fillets for wrinkling and distortion. (2) Engine mountings and attachments for damage and evidence of movement. (3) For no evidence of fuel or hydraulic fluid leakage.

8. ELECTRICAL

A. Inspect: (1) The batteries for security and evidence of leakage. (2) The inverters for security. (3) The emergency lighting inertia switch (if fitted) and make sure it has not operated.

B. Test: (1) The inverters for correct functioning.

9. FURNISHINGS/EQUIPMENT

A. Inspect: (1) The emergency equipment for security and correct stowage.

10. FLIGHT CONTROLS

A. Make sure: (1) All the control cable tensions are correct.

B. Test: (1) The flight control systems for correct operation.

11. FINAL ITEMS

A. If damage is found: (1) Do the symmetry and rigging checks. (2) Do a cabin leak rate test.


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PART-5

3. INSPECTIONS AFTER A LIGHTNING STRIKE

1. GENERAL

In the event of a lightning strike the following inspections, checks and tests must be done before the airplane is released for further flight. Lightning strikes usually produce two types of damage, that caused by the actual strike and that caused by the discharge of static electricity which follows the strike. A lightning strike usually causes the burning of small circular holes, which may be clustered in one locality or scattered over a large area. A strike may also be indicated by burnt or discoloured skin,

the blistering of Neoprene coverings or the cracking of glassfibre components . Strike damage

usually appears at the fuselage nose, along the top surface of the fuselage and on the wing and stabilizer leading edges. Damage due to the static discharge usually appears on the tips of the wings and stabilizers, trailing edges and antennae, and may be in the form of localized pitting or burning, or damaged or destroyed static dischargers.

2. FUSELAGE

A. Inspect: (1) Radome for damage, particularly to the lightning diverter strips and the radome fasteners . (2) Fuselage skinning for pitting and burning, particularly in the area of the windshields, along the

fuselage top and in the area of the ram air intake. (3) Pitot heads and structure in the area for signs of damage. (4) Aerials, masts and dielectric panels for damage. (5) The nose landing gear doors for distortion and damage. (6) If the landing gear was extended at the time of the strike, then inspect the lower portion of the

landing gear for signs of static discharge.

3. WINGS

A. Inspect: (1) Wing leading edges and spoilers for pitting and burning . (2) Wing tips, trailing edges of ailerons and flaps for pitting, burning and signs of static discharge. (3) Static dischargers for damage or disintegration. (4) The main landing gear doors for distortion and damage. (5) If the landing gear was extended at the time of the strike, then inspect the lower portion of the

landing gear for signs of static discharge.


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4. STABILIZERS

A. Inspect: (1) Vertical stabilizer for burning, pitting and signs of static discharge. (2) Horizontal stabilizer for burning, pitting and signs of static discharge. (3) Rudder for burning, pitting and signs of static discharge. (4) Elevators for burning, pitting and signs of static discharge. (5) Bullet and overfin fairings for burning, pitting and signs of static discharge. (6) If there is any signs of a strike on the overfin fairing, then remove the fairing and inspect the

structure revealed for damage. (7) Static dischargers on vertical and horizontal stabilizers for damage or disintegration .


A. Inspect: (1) Engine pods and structure for signs of burning or pitting. (2) The power plant in accordance with the Garrett Light Maintenance Manual .

6. FINAL ITEMS

A. Test: (1) All radio and radar equipment. (2) All navigation and essential lighting systems. (3) All flying control systems. (4) Compass systems.


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PART-5

4. INSPECTIONS AFTER MISUSE OF REVERSE THRUST

1. GENERAL

If reverse thrust in excess of idle power has been used at speeds below 50 knots, before any

subsequent engine ground running or further flight do the following inspections.

A. Inspect:

(1) Fan blades for foreign object damage, erosion, nicks, cracks or distortion which may affect balance

or blade security. Rotate the fan rotor assembly to inspect all fan blades.

(2) If the inspection requirements of (1) are not met, repair or replace the damaged fan rotor blades in

accordance with the Honeywell Light Maintenance Manual 72-70-03, 4, Approved Repairs.

(3) If foreign object damage is found on any fan blade, then a borescope inspection of the low pressure

compressor first stage rotor blades must be done in accordance with the Honeywell Light

Maintenance Manual 72-30-04, Maintenance Practices.


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PART-5

5. INSPECTION AFTER LANDING GEAR VIBRATION

Note: Do ALL items marked with an asterisk (*). If damage, distortion or a failure of any part or

component inspected on an asterisk (*) inspection is found, the full inspection must be done.

Note: It is recommended that any major disassembly of the landing gear for crack testing is done

at a repair center with the necessary equipment for overhaul and testing of the assembly.

Note: It is necessary that all items are thoroughly cleaned before any inspections for excessive

wear, cracks, damage, distortion or dimensional checks are done.

1. PREPARATION

A. General

(1) (*) Remove airplane electrical power (AMM Chapter 24, ELECTRICAL POWER).

(2) (*) Display signs in the flight compartment to tell personnel "DO NOT USE ELECTRICAL POWER".

(3) (*) Display signs in the flight compartment to tell personnel "DO NOT USE THE LANDING GEAR"

(4) (*) Open, safety and tag the landing gear circuit breakers (AMM Chapter 24, ELECTRICAL POWER).

(5) (*) Make sure that the landing gear locking pins are installed (AMM Chapter 10, PARKING AND

MOORING).

(6) (*) Raise the airplane on jacks (AMM Chapter 07, JACKING AND TRESTLING).


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2. INSPECTION

A. Nose Landing Gear, Drag Stay Assembly and NLG bay

Note: Before doing any crack testing using the liquid dye penetrant method, make sure that all the

surface finish and protective coatings are removed from the areas to be tested. After the

crack testing is complete the protective coating and surface finish must be restored (OM

Chapter 32).

Check/Inspect:

(1) (*) Inspect nosewheels and tires for damage. (2) (*) Inspect torque link joints for excessive wear. (3) (*) Inspect strut for signs of fluid leakage and damage. (4) (*) Check strut for correct nitrogen and fluid servicing (AMM Chapter 12, LANDING GEAR). (5) (*) Inspect steering jack and attachments for damage and excessive wear . (6) (*) Inspect nose gear doors for distortion, cracks and security. (7) (*) Check the balance of the Nosewheel assemblies (Refer to the relevant Vendor CMM). (8) Check axle assembly and bearings for excessive wear and damage (Disassembly required, refer to

AMM Chapter 32, NOSE AXLE ASSEMBLY). (9) Inspect nose gear attachment fittings for cracks and signs of movement.

(10) Inspect drag stay and attachments for distortion, cracks and signs of movement. (11) Inspect nose gear bay structure, particularly in the vicinity of the landing gear attachments, for

distortion and signs of bolt and rivet failure. (12) Check the tightness of all bolts securing the leg and drag stay attachment fittings to the landing gear

bay sidewalls. (13) Check nosewheel steering upper and lower pivot link assemblies for cracks using an approved

crack detection method. (14) Check nosewheel steering levers for cracks using an approved crack detection method . (15) Check nose landing gear casing for cracks (NTM, Chapter 32, LEG CASING). (16) Check nose landing bay sidewalls for cracks (NTM, Chapter 53, NOSE LANDING GEAR BAY

SIDEWALL).


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B. Main Landing Gear and MLG Bays

Note: This inspection is applicable to both LH and RH Main Landing Gear Assemblies.

Check/Inspect:

(1) (*) Inspect tires for cuts, bulges and other damage.

(2) (*) Inspect wheels and brakes for signs of damage.

(3) (*) Inspect brake hoses for damage, security of attachment and signs of fluid leakage.

(4) (*) Check torque link pivots (AMM Chapter 32, MAIN LEG ASSEMBLY - INSPECTION/CHECK).

(5) (*) Inspect struts for signs of fluid leakage and damage.

(6) (*) Check struts for correct nitrogen and fluid servicing (AMM Chapter 12, LANDING GEAR).

(7) (*) Inspect main leg front and rear attachments for cracks and signs of movement.

(8) (*) Inspect the bay structure, particularly near the landing gear attachments, for distortion and signs

of bolt and rivet failure.

(9) (*) Inspect retraction jack top attachments for cracks and signs of movement.

(10) (*) Inspect main gear doors, fairings and associated attachments and fittings for damage and

distortion.

(11) (*) Inspect weight-on-wheels and gear indication microswitches for security of attachment and

damage.


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C. Main Landing Gear - Side Stay Assembly.

Caution: When doing any dismantling of side stays make sure that all right hand side stay

components are kept apart from all left hand side stay components. It is important that

components are reassembled to their original side stay.

Note: This inspection is applicable to both LH and RH Main Landing Gear Side Stay Assemblies.

Note: Before doing any crack testing using the liquid dye penetrant method, make sure that all the

surface finish and protective coatings are removed from the areas to be tested. After the

crack testing is complete the protective coating and surface finish must be restored (OM

Chapter 32, SIDE STAY ASSEMBLY).

Inspection:

(1) (*) Examine the side stay center pivot nut for damage and distortion (AMM Chapter 32, SIDE STAY

ASSEMBLY - INSPECTION/CHECK).

(2) (*) Do a visual inspection of the side stay and attachments in situ.

(3) Remove the side stay (AMM chapter 32, SIDE STAY ASSEMBLY - REMOVAL/INSTALLATION).

(4) Refer to Figure 1. Do a crack test of the side stay to wing attachment lug as given:

(a) Remove the bush, the surface finish and the protective coating . Degrease the areas to be crack

tested.

(b) Do a crack test of the areas given, use a Type 1, Level 1, Method A liquid penetrant in accordance

with the Non-Destructive Testing Manual (NTM) General Techniques - Part C. If you find cracks,

report in full and request instructions from : Hawker Beechcraft Corporation. The instructions must be

obeyed before the airplane flies.

(c) Restore the protective treatment and surface finish to the area tested (AMM 125/H-20, Chapter 20 -

**-**).

(d) Install the bush in accordance with (AMM 125/H-20, SHRINK FITTING OF BOLTS, BUSHES, PINS,

ETC.).

(e) Check the flanged distance tube (OM Chapter 32-10-05, Fig. 2, Index No. 5) for distortion of the

flange. If any distortion is found then replace with a new item of the correct part number .

(5) Install the side stay (AMM Chapter 32, SIDE STAY ASSEMBLY - REMOVAL/INSTALLATION).


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D. Rear Equipment Bay

(1) (*) Inspect the bleed air and air conditioning ducting for security and signs of movement .

(2) (*) Inspect for signs of fluid leakage, particularly from the hydraulic box .

E. Flap Hinges and Attachments

(1) (*) Inspect the flaps for signs of contact with the wing trailing edge.

F. Systems and Equipment/Furnishings

(1) (*) Inspect the radar antenna for damage and security.

(2) (*) Inspect the avionics racks and components for damage and security.

(3) (*) Inspect cabin equipment/furnishings for the correct stowage and security.

(4) (*) Inspect the water tanks for security and signs of leakage.

(5) (*) Inspect the instruments and panels for damage and security.

(6) (*) Check that the emergency lighting inertia switch (if installed) has not operated.

3. CLOSE UP AND TEST

(1) (*) Remove warning notices displayed at paragraph 1.A. (2) and (3).

(2) (*) Remove the safety tags and close the landing gear circuit breakers (AMM Chapter 24,

ELECTRICAL POWER) opened at paragraph 1.A.(4).

(3) (*) Energize the airplane electrical bus-bars (AMM Chapter 24, ELECTRICAL POWER).

(4) (*) Do the landing gear retraction test (AMM Chapter 29, MAIN SYSTEM).

(5) (*) Lower the airplane off the jacks (AMM Chapter 07, JACKING AND TRESTLING).

(6) Do a function test of the gyroscopic units, if installed.

(7) Do a function test of the radar (AMM Chapter 34, WEATHER RADAR).

(8) (*) Remove airplane electrical power (AMM Chapter 24, ELECTRICAL POWER).

(9) (*) Make sure all areas are clean and free of tools and miscellaneous items of equipment .


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PART-5

INSPECTION AFTER LANDING GEAR VIBRATION

WING - SIDE STAY ATTACHMENT FITTING-AREA TO BE CRACK TESTED


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PART-5

6. INSPECTION AFTER COLD SOAK BELOW -40 deg. C

1. GENERAL

In the event of the aircraft experiencing a cold soak below -40 C for a period in excess of four

hours on the ground, the following inspection/checks must be done within 3 days.

A. Test:

(1) Do the functional test of the stall detection system (AMM 27-33-00, Adjustment/Test).


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PART-5

7. INSPECTIONS AFTER LANDING OR ABORTED TAKE-OFF IN DEEP

WATER PUDDLES, SLUSH OR SNOW

1. INTRODUCTION

Note: This inspection is only applicable if a landing or aborted take-off on a runway covered in

deep water puddles, slush or snow has been reported since the last 300 Hour Inspection.

2. FLAP INNER HINGE BOLTS.

1. Adequately support flaps

2. Remove inner hinge bolts.

3. Inspect for signs of overloading.

4. Install inner hinge bolts.


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PART-5

8. INSPECTIONS AFTER EMERGENCY STOP

1. GENERAL

Warning: Take care when you approach the wheels after an emergency stop. Let an adequate cooling

period elapse before you attempt to remove the wheels or brake units.

Warning: THE ground locking pins must be installed whenever the main and nose landing gears are in

the down and locked position (Chapter 10, Parking and Mooring).

Warning: Before you disassemble any part of the landing gear hydraulic system, make sure all the

hydraulic pressure is released (AMM Chapter 29, Main System).

Caution: Hydraulic fluid drained or bled from the landing gear system is to be discarded. Use only

new hydraulic fluid to replenish the hydraulic system or ground servicing rigs.

2. PROCEDURE

Do "Action after an emergency stop", AMM Chapter 32, BRAKE UNIT, Inspection/Check.


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PART-5

9. INSPECTIONS AFTER ABNORMAL APU CONDITIONS

1. DO OIL AND OIL FILTER SAMPLES WHENEVER ONE OF THE

FOLLOWING CONDITIONS OCCUR (PATS APU GTCP36-150W CMM,

Chapter 49-20-00):

Note: Operate the APU for 10 minutes before taking an oil sample.

(1) Request by the SOAP Laboratory/Customer Service Engineering to check out suspected

deficiencies from a previous sample.

(2) Malfunctions occur in the lubrication system, i.e.

(a) High oil temperature.

(b) Low oil pressure shutdowns.

(c) Fluctuating or zero oil pressure.

(d) Excessive oil loss.

(3) Excessive ferrous metal is detected on the magnetic plug.

(4) Excessive vibration is experienced.

(5) Starter motor fails as a result of a rough or malfunctioning sprag clutch.

NOTE: Applicable only to APU's with a DC starter motor.

(6) Abnormal engine or higher than normal acceleration time accompanied by higher than normal peak

exhaust gas temperatures.


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PART-5

10. INSPECTIONS AFTER FLAP OVERSPEED

1. INTRODUCTION

In the event of a reported flap extension at airspeeds exceeding the recommended Vfe and Vfo by

10% or more, the following checks must be done before the airplane is released for further flight .

2. GENERAL

A. Inspect

(1) Flap surfaces for cracks, wrinkling, distortion and loose or missing fasteners.

(2) Flap system drive components for damage and security of attachment (Ref. AMM 27-50-02, 1, Figure

1).

3. FLAPS

A. Inspect

(1) Flap Hinge brackets, Screwjack and Synchronizer linkage for distortion, loose or missing

fasteners/rivets and any other structural damage.

B. Check

(1) Flap Hinge brackets, Screwjack and Synchronizer linkage for excessive play.

4. FINAL ITEMS

A. Check

(1) Do the Rigging, Range of Movement, Friction and Spring Strut function tests (Ref. AMM 27-50-02,

501).

(2) Do a Flap control system functional test (Ref. AMM 27-50-02, 501).

5. CLOSE UP

(1) Make sure the working area is clean and free of tools and miscellaneous items of equipment .

Note: If this inspection turns up any findings like damaged hinge points, skin crinkling, popped

rivets, etc., contact Hawker Beechcraft Corporation, Technical Support for further advice.


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PART-6 PANEL LOCATION CHARTS

PART-6

PANEL LOCATION CHARTS

1. PANEL LOCATION CHART


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PART-6

1. PANEL LOCATION CHARTS

To facilitate maintenance, access panels are numbered and a series of prefix letters together with

blocks of numbers are used to indicate the locations of the panels on the aircraft . Where necessary,

a suffix letter L or R is also used to indicate left or right

The area location letters and number blocks are:

F1 to F300 ... Fuselage internal and external panels.

W101 to W200 ... Panels on the left wing top surface.

W201 to W300 ... Panels on the right wing top surface.

W301 to W400 ... Panels on the right wing bottom surface.

W401 to W500 ... Panels on the left wing bottom surface.

W501 to W550 ... Panels in the front and rear center section fairings.

T1 to T50 ... Tail unit panels.

M1 to M40 ... Engine cowlings and panels in the pod fillets.

In addition, symbols following the panel numbers indicate the types and numbers of fasteners

securing the panels. An "H" adjacent to a symbol indicates that the panel is hinged .


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PART-6


AREA LOCATION

FIGURE 1


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PART-6


SERVICE POINTS

FIGURE 2


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PART-6


FUSELAGE, ENGINES AND VERTICAL STABILIZER

FIGURE 3


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PART-6


FLOOR PANELS, CABLE DUCTS AND PIPE COVERS

FIGURE 4


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PART-6


WINGS AND HORIZONTAL STABILIZER

FIGURE 5


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PART-6


WINGS AND HORIZONTAL STABILIZER (INVERTED PLAN VIEW)

FIGURE 6


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PART-6


FLIGHT COMPARTMENT

FIGURE 7


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PART-6


MAIN DISTRIBUTION PANEL DA

FIGURE 8


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PART-7 LUBRICATION

PART-7

LUBRICATION

1. LUBRICATION


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PART-7

1. LUBRICATION

Instructional Data

The illustrations in this part of the schedule indicate the points that require periodic

lubrication and the method of lubrication. Grease application is by grease gun except where

indicated by a hand symbol. Oil application is indicated by an oil can symbol.

Unless otherwise indicated on the illustrations the lubricants are:-

Grease (Chapter 20 STANDARD PRACTICES - AIRFRAME, Ref. 125/H-20, 20-95-11, Item

No. 078)

Oil (Chapter 20 STANDARD PRACTICES - AIRFRAME, Ref. 125/H-20, 20-95-101, Item No.

126)

The number within the balloon at each lubrication point on the illustration indicates the

recommended interval between applications of the lubricant, as detailed in Table 1 .

The requirements identified in Figure 1 through Figure 4 should be done as well as and in

conjunction with the items listed in the "Lubrication Requirements" table.

Table 1

Lubrication Periods

1. Every 200 flying hours.

2. Every 400 flying hours.

3. Every 800 flying hours/Inspection B.

4. Every 1600 flying hours/Inspection C.

5. Every 3200 flying hours/Inspection D.

6. Every 12 months elapsed time/Inspection E.

7. Every 24 months elapsed time/Inspection F.

8. Every 48 months elapsed time/Inspection G.


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PART-7

LUBRICATION

Monthly

Item Lubricant

Area G (Main Landing Gear and bay, Nose Landing Gear and bay).

NOTE If the airplane has been exposed to runway de-icing do this lubrication at monthly

intervals.

Main landing gear sidestay shims (Ref. Figure 2

(Sheets 1 and 2, detail A)) Post Mod. 253549A or Pre

SB. 32-3779 (Mod. 25G295A).

Corrosion Preventative Lubricant, AMM 20-95-11, Item

092.

200 Hour

Item Lubricant


Nose landing gear steering and retraction mechanism (Ref. Figure 1, Sheet 1).

Oil, AMM 20-95-101, Item No. 126. Grease, AMM 20-95-11, Item

078.

Nose landing gear selector and dump valve (Ref. Figure 1, Sheet 2).

Grease, AMM 20-95-11, Item

034.

Nose landing gear steering selector valve (Ref. Figure 1, Sheet 2).


034.

Main landing gear, inboard doors, reversing and sequence valves (Ref. Figure 2, Sheet 1).


034. Grease, AMM 20-95-11, Item

078.

Main landing gear sidestay shims (Ref. Figure 2

(Sheets 1 and 2, detail A)).


092.

Emergency dump valve linkage and plunger (Ref. Figure 4, Sheet 5, Item E).

Oil, AMM 20-95-101, Item No. 126. Grease, AMM 20-95-11, Item No. 034.


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PART-7

LUBRICATION

400 Hour

Item Lubricant

Area F1

Ventral fuel tank filler cap O-seals (if fitted). Refuelling coupling O-seals, (Ref. Figure 4, Sheet 1).

Grease, AMM 20-95-11, Item No. 078.

Security locks (if fitted) lubricate sparingly. Oil, AMM 20-95-101, Item No. 126.

Main entry door stay center and bottom joints, including lock rollers and mechanisms (Ref. Figure 4,

Sheet 5, Item F).


Rudder bias strut (Ref. Figure 4, Sheet 6, Item J). Oil, AMM 20-95-101, Item No. 126.

Area T1

Elevator and elevator tab hinges (Ref. Figure 3,

Sheet 1). Oil, AMM 20-95-101, Item No. 126.

Elevator trim jack (Ref. Figure 3, Sheet 1). CAUTION

When lubricating the Elevator Trim Jack do not

mix grease Item 078 with grease Item 094. NOTE: Mod.25G138B or SB 27-3840 introduces a

replacement grease for the Elevator Trim Jack. NOTE : Mod.25G138F introduces a replacement

Elevator Trim Jack.

Pre Mod.25G138B or Pre Mod. 25G138F, or Pre SB 27-3840: Grease, AMM 20-95-11, Item No. 078. Mod.25G138B or Mod. 25G138F,

or SB 27-3840: Grease, AMM 20-95-11, Item No. 094.

Rudder and rudder tab hinges (Ref. Figure 4, Sheet

1). Oil, AMM 20-95-101, Item No. 126.

Rudder trim jack, (Ref. Figure 4, Sheet 1). CAUTION

When lubricating the Rudder Trim Jack do not

mix grease Item 078 with grease Item 094. NOTE : Mod.25G138C or SB 27- 3840 introduces a

grease change from Item 078 to Item 094. NOTE : Mod. 25G138E introduces a replacement

Rudder Trim Jack.

Pre.Mod. 25G138C or Pre.Mod. 25G138E, or Pre. SB 27-3840: Grease, AMM 20-95-11, Item No. 078. Mod. 25G138C or Mod. 25G138E, or SB 27-3840: Grease, AMM 20-95-11, Item No. 094.


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PART-7

LUBRICATION

400 Hour

Item Lubricant

Area W1/W2

Aileron and aileron tab hinges (Ref. Figure 3, Sheet

1). Oil, AMM 20-95-101, Item No. 126.

Aileron trim jack (Ref. Figure 3, Sheet 1). CAUTION

When lubricating the Aileron Trim Jack do not

mix grease Item 078 with grease Item 094. NOTE

Mod.25G138A or SB 27-3840 introduces a

replacement grease for the Aileron Trim Jack. NOTE

Mod.25G138F introduces a replacement Aileron

Trim Jack.

Pre Mod.25G138A or Pre Mod. 25G138F, or Pre SB 27-3840: Grease, AMM 20-95-11, Item No. 078. Mod.25G138A or Mod. 25G138F,

or SB 27-3840: Grease, AMM 20-95-11, Item No. 094.

Airbrake hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No. 126.

Fuel tank filler cap seals (Ref. Figure 3, Sheet 1). Grease, AMM 20-95-11, Item No. 078.

Fuel tank filler cap locking handle recesses (AMM 28-10-44) GABB filler caps only, pack with grease (Ref. Figure 3, Sheet 1).


Flap screwjack threads (Ref. Figure 3, Sheet 4, Item

G). Clean and lightly lubricate. Flap screwjack (mount) trunnions (Ref. Figure 3,

Sheet 4, Item G). Flap synch linkage (Ref. Figure 3, Sheet 4, Item G). Flap transmitter linkage (Ref. Figure 3, Sheet 4, Item

G).

Oil, AMM 20-95-101, Item No. 126.

Flap screwjack yoke nut (Ref. Figure 3, Sheet 4, Item

G). Grease, AMM 20-95-11, Item No. 040.

Airbrake trim jack and hinges (Ref. Figure 3, Sheet 4,

Item H).



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PART-7

LUBRICATION

Inspection B (800 Hour)

Item Lubricant

Area F1

Nose cone hinges and stays (Transferred to 1600 Hour lubrication).

Area F3

Escape hatch (Ref. Figure 4, Sheet 6, Item G). Grease, AMM 20-95-11, Item No. 078.

Area F4

Control cables and pressure seals (Ref. Figure 3,

Sheet 1). Grease, AMM 20-95-11, Item No. 034.

Equipment bay door hinges (Transferred to 1600 Hour lubrication).

External baggage unit (EBU) loading door and hatch,

hinges and latch mechanisms. Oil, AMM 20-95-101, Item No. 126.

Area W1/W2

Wing transfer valve control (Ref. Figure 3, Sheet 4,

Item E). Oil, AMM 20-95-101, Item No. 126.

LP and Crossfeed fuel valves controls (Ref. Figure 3,

Sheet 4, Item F). Oil, AMM 20-95-101, Item No. 126.

Flap drive system (Ref. Figure 3, Sheet 4, Item G). Oil, AMM 20-95-101, Item No. 126.

Aileron control cables and pressure seals (Ref. Figure

3, Sheet 1). Grease, AMM 20-95-11, Item No. 034.

Aileron operating mechanism (Ref. Figure 3, Sheet 4,

Item J).

Oil, AMM 20-95-101, Item No. 126.


Nose gear leg lock and change-over microswitch

operating mechanism (Ref. Figure 1, Sheet 1). Oil, AMM 20-95-101, Item No. 126.

Nose gear door quick release strut (Ref. Figure 1,

Sheet 1, Item A). Lubricate splines. Grease, AMM 20-95-11, Item No. 078.

Main gear door uplock spring strut (Ref. Figure 2,

Sheet 1). Lightly lubricate sliding surface. Grease, AMM 20-95-11, Item No. 078.


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PART-7

LUBRICATION

Inspection C (1600 Hour)

Item Lubricant

Area F1

Nose cone hinges and stays (Ref.Figure 3, Sheet 1

and Figure 4, Sheet 1). Oil, AMM 20-95-101, Item No. 126.

Area F2

Center pedestal (Ref. Figure 3, Sheet 2, Item A, Item

L and Sheet 3, Item B).


Parking brake controls (Ref. Figure 4, Sheet 2, Item

A). Oil, AMM 20-95-101, Item No. 126.

Auxiliary hydraulic system (Ref. Figure 4, Sheet 5,

Item E). Oil, AMM 20-95-101, Item No. 126.

Nose landing gear mechanical indicator cable (Ref. Figure 1, Sheet 1) and AMM 32-66-00, 201): Bearing plate and rod end. Mechanical indicator

shaft. Sliding portion of the rod end.

Grease, AMM 20-95-11, Item No. 078. Grease, AMM 20-95-11, Item No. 034.

Area F3

Drag spigot housing (Ref. Figure 3, Sheet 1). Repack

with grease. CAUTION : If grease Item 078 was installed on the

Drag Spigot Housing; ALL traces of grease

MUST BE REMOVED before using Item 093. DO

NOT MIX GREASES.

Pre.Mod.25G317B,

Grease, AMM 20-95-11, Item No. 078. Mod.25G317B,

Grease, AMM 20-95-11, Item No. 093

LP and Crossfeed fuel valves controls chain and sprockets (Ref. Figure 3, Sheet 4, Item F).


Wing transfer valve control cables and pressure seals (Ref. Figure 3, Sheet 4, Item E).


Ventral tank valve control (Ref. Figure 3, Sheet 4,

Item M) (N/A 750 airplane).


Main entry door shaft (Ref. Figure 4, Sheet 5, Item F). Grease, AMM 20-95-11, Item No. 078.


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PART-7

LUBRICATION

Inspection C (1600 Hour)

Item Lubricant

Area F4

Equipment bay door hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No.

126.

Engine control assembly (Ref. Figure 4, Sheet 6, Item

H)

Oil, AMM 20-95-101, Item No.

126.

Area T1

Rudder trim jack chain and sprocket (Ref. Figure 4,

Sheet 1).

Grease, AMM 20-95-11, Item No.

078.

Elevator trim jack chain and sprocket (Ref. Figure 3,

Sheet 1).


078.

Area W1/W2

Aileron trim jack chain and sprocket (Ref. Figure 3,

Sheet 1).


078.

Flap drive system (Ref. Figure 3, Sheet 4). Remove

gaiters, repack with grease, install gaiters.


040.

Inspection D (3200 Hour)

Item Lubricant

Area F2

Steering handwheel and chain (Ref. Figure 3, Sheet

4, Item D).


078.


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PART-7

LUBRICATION

Inspection E (12 Month)

Item Lubricant

Area F3

Escape hatch (Transferred to 800 Hour lubrication).

Area F4

Control cables and pressure seals (Transferred to 800 Hour lubrication).

Area W1/W2

Aileron control cables and pressure seals (Transferred to 800 Hour lubrication).

Inspection F (24 Month)

Item Lubricant

Area F1



092.

Area F2

Flight controls below floor (Ref. Figure 3, Sheet 3,

Item C).


078.

Landing gear selector controls (Ref. Figure 4, Sheet

2, Item B). Oil, AMM 20-95-101, Item No. 126.

Control columns (Ref. Figure 4, Sheet 3, Item C).


Rudder pedal assemblies (Ref. Figure 4, Sheet 4,

Item D).



Nose landing gear mechanical indicator system (Transferred to 1600 Hour lubrication).


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PART-7

LUBRICATION

Inspection G (48 Month)

Item Lubricant

Nose landing gear mechanical indicator system (Transferred to Lubrication, 1600 Hour).

Between 1200 Hours and 2400 Hours

Area M1/M2

Thrust control teleflex cable and disconnect

coupling.

Lubricate (Ref. AMM 76-10-01, page block 601).


046.

NOTE

This task may be done during the removal of an Engine (AMM 71-00-01, 401) or a Power

Plant (AMM 71-00-03, 401); but not to exceed 1200 to 2400 Hours.

------------- END ---------------


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PART-7

LUBRICATION

Nose Landing gear

(Figure 1 sheet 1 of 2)


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LUBRICATION

Nose Landing gear



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LUBRICATION

Main Landing gear



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LUBRICATION

Main Landing gear



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PART-7

LUBRICATION

Fuselage/Wings/Horizontal Stabilizer



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LUBRICATION




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LUBRICATION




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LUBRICATION




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LUBRICATION

Fuselage/Vertical Stabilizer/Rudder



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LUBRICATION




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LUBRICATION




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LUBRICATION




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LUBRICATION




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PART-8 COMPONENT REQUIREMENTS

PART-8

COMPONENT REQUIREMENTS

1. COMPONENT REQUIREMENTS

Instructional Data

NOTE




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PART-8

1. COMPONENT REQUIREMENTS

Component Part No. Manufacturer Period Test Repl O/H

H. Air Conditioning

Non-return valve main air

supply to cabin

AWE124-51

AWE124-51A

AWE124-51-2

Hymatic Engineering Redditch, UK

12,000 hrs *

Switches, bleed air over temperature

156D** 53183* Kidde Graviner

5 years 5 years

* *

I. Communications

NOTE : Overhaul periods for communications equipment are subject to negotiation between

individual operators and their Regulatory Authority, unless listed below. For the manufacturers

recommended overhaul periods for communication equipment, refer to the relevant CMM.

Cockpit voice recorder, model A100A

93-A100-30 Fairchild Industrial Products

8000 hours *

Underwater locator beacon 266-E0305-00 Fairchild Industrial Products

2 years *

Underwater locator beacon 266-E0305-00 Fairchild Industrial Products

6 years *

Underwater locator beacon DK100 DK120

Dukane Corporation 2 years *

Underwater locator beacon DK100 DK120

Dukane Corporation 6 years *

NOTE : Underwater Locator Beacons can be installed on Cockpit Voice Recorders and Flight

Data Recorders.

Underwater locator beacon - battery

ULB Part No. 15957

Fairchild Industrial Products

2 years *

NOTE : For the ULB Part No. 266-E0305-00 the ULB has to be returned to the manufacturers for

the battery to be replaced. For the earlier type ULB Part No.15957 the replacement batteries can

be obtained from the manufacturers.

Battery kit, fitted to Underwater Locator Beacon ELP-362D.

B362-06192

RJE International Inc. (Datasonics Inc.)

6 years *

Emergency locator transmitter

As installed NOTE

Service/Replace in

accordance with the manufacturer's servicing instructions.

Emergency locator transmitter battery pack

As installed


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PART-8



J. Electrical Power

Contactor, inverter supply

LDA200-B18C

Lucas Aerospace Ltd., Electrical Division

5000 hrs *

Contactor, bustie LDA150A-8C

Lucas Aerospace Ltd., Electrical Division

5000 hrs *

Contactor, ground supply

LDG150Y4 Lucas Aerospace Ltd., Electrical Division

6000 hrs *

Starter/generator,

main engines 23080-005

Lucas Aerospace Power Equipment Corporation, 777 Lena Drive, Ohio, USA

1000 hrs *

Starter/generator,

main engines 23080-064


1000 hrs *

Starter/generator,

main engines

140-380026-1


1000 hrs *

Starter/generator,

auxiliary power unit

23080-005

23080-064


1000 APU running hrs

*

Frequency wild A.C. generator

BA02801-1 Lucas Aerospace Ltd., Electrical Division

3000 hrs or 8 years *

Main aircraft batteries As installed NOTE : Service/Replace in accordance

with the manufacturer's instructions.

Aircraft emergency batteries

As installed NOTE : Service/Replace in accordance

with the manufacturer's instructions.

Internal Avionics batteries

As installed

NOTE : Service/Replace in accordance

with the Avionics manufacturer's instructions.


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PART-8



K. Equipment/Furnishings

Lifejackets (manufactured before

March 1980) 102MK2BA RFD Inflatables Ltd.

2 years 4 years 1 year

*

* *

NOTE The overhaul period of 4 years is subject to a satisfactory examination of one pack after 2 years. From 9 years onwards ALL packs must be overhauled every year.

Lifejackets (manufactured after

March 1980) 102MK2BA RFD Inflatables Ltd.

2 years 5 years 1 year

*

* *

NOTE The overhaul period of 5 years is valid from the date of manufacture up to 20 years subject to a satisfactory examination of one pack every 2 years. After 20 years the overhaul period

changes to every year.

L. Fire Protection

Fire extinguisher, main engine

33200002 33200002-3

33200009 33200009-3

HTL Industries Inc. 10 years from date of filling

*

Fire extinguisher, APU 30402104 HTL Industries Inc. 5 years from date of filling

*

Fire extinguisher, APU 4190-* Meggitt/Whittaker/Systron

Donner

5 years from date of filling

*

Fire extinguisher, External baggage unit (EBU)

30300106-1 HTL Industries Inc. 5 years from date of filling

*

APU fire warning switches

17343* Fenwell 5 years *

APU fire warning switch 160275-1 Sundstrand 5 years *

APU generator overheat switch

67100* Fenwall 5 years *

Overheat detection switches

150D01* Graviner (Colnbrook) Ltd. 5 years *

Overheat detection switches

53182* 17343* Fenwall 5 years *


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PART-8



M. Flight Controls

Flap control unit, Type 614 Mk 2

CHA614-001/2

Lucas Aerospace Ltd., Actuation

Division

6000 landings *

Receiver unit, flap synchronizing system, Type 617 Mk. 4

CHA617-104

Lucas Aerospace Ltd., Actuation

Division

4500 landings *

Flight Controls (Cont.)

Flap screwjacks and reduction gearboxes

25-8CW159* 25-8CW161*

Beechcraft Corporation

4000 landings *

Airbrake jacks AIR46520* AIR46521*

AP Precision Hydraulics

3000 hrs *

N. Fuel

Fuel pump, Type 20700-01

2070C01 2070C11

Intertechnique S.A. 4000 hrs *

O. Hydraulic Power

Full flow relief valve AIR45394 AP Precision Hydraulics

4500 flts *

Pressure maintaining valve

AIR45474 AP Precision Hydraulics

5000 flts *

Pressure switch emergency brakes LP warning.

TP42001 Thermal Control Company Ltd. 5000 hrs *

P. Instruments

Fatigue meter (if fitted) M1946 Negretti and Zambra 30,000 counts or 2 years from installation

*


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PART-8



Q. Landing Gear

NOTE : The calendar start time for the BC manufactured Landing Gear components may be

based on the date of release for service following aircraft completion, up to a maximum of three months from the date of original aircraft certification.

Main leg assembly

25-8UM1-* 259W02333-* 25-8UM523-*

Beechcraft Corporation

5000 landings OR 12 years, whichever comes first.

*

Main leg assembly 140-810044-* Beechcraft Corporation


*

Side stay assembly

25-8UM3-* Beechcraft Corporation


*

Side stay assembly 140-810043-* Beechcraft Corporation


*

Nose leg assembly 25-9UN1-* Beechcraft Corporation


*

Nose landing gear drag stay assembly. 25-8UN3-* Beechcraft

Corporation


*

Reversing valve AIR48542 AIR48543



*

Sequence valve AIR48540* AP Precision Hydraulics


*

Main gear jack AIR48502* AIR48503*


5000 landings *

Nose gear jack AIR45404* AP Precision Hydraulics

5000 landings *

Main gear door jacks AIR48484 AIR48485


5000 landings *

Maxaret unit AC65216 AC65218

Dunlop Limited, Aviation Division

3000 landings *

Pressure switch emergency brakes system

TP42000 Thermal Control Company Ltd. 5000 hrs *


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PART-8



R. Lights

NOTE : Accomplish replacement/hardtime restoration as required by this section using any one

of the following methods: Operators may replace the strobe flash tube or strobe light flash tube assembly in accordance with Honeywell Grimes Component Instructions. OR send the strobe light assembly to Honeywell Grimes for hardtime restoration or overhaul. NOTE : If the strobe light replacement/hardtime restoration is not accomplished, the strobe

light must be intensity tested once the initial replacement/hardtime hours are met and then

every 400 ± 50 hours thereafter, or until the strobe light no longer meets the requirements of intensity or flash rate, in which case comply with the previous NOTE. Use Devore Flash Gun Model 4400D or equivalent American Aerospace Model ST-4000 for

testing strobe light flash intensity.

Strobe light assembly - Wings

30-0538-7/-8

Pre Mod. 253262A 31-2059-11

(100 effective candle

power)

Honeywell Grimes

1500 hrs. * * *

Strobe light assembly - Wings

30-1617-1/-2

Mod. 253262A

31-3078-19


power)

Honeywell Grimes

2000 hrs. * * *

Strobe light - Wings

01-0770935-01 01-0770935-02 (Alternate) (100 effective candle

power)

Whelen 2000 hrs. * * *

Strobe light assembly - Tail 30-0531-1

Pre Mod. 253262A 31-1840-1


power)

Honeywell Grimes

1500 hrs. * * *


Mod. 253262A

31-3172-43 (100 effective

candle power)

Honeywell Grimes

1500 hrs. * * *


31-1748-1


power)

Honeywell Grimes

1500 hrs. * * *


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PART-8



Escape Hatch Betalight "Exit" sign

2821003

SRB Technologies (Canada) Inc.

6 years from date of manufacture.

*

NOTE : Escape hatch Betalights that have exceeded the replacement period have 24 months to

comply with the vendor recommendations.

S. Navigation

NOTE Overhaul periods for navigation systems transmitters and receivers are to be subject to

negotiation between individual operators and their regulatory authority.

Elevator trim servo motor

622-3260-001

Rockwell International, Collins General Aviation Division.

3500 hrs. *

T. Oxygen

Oxygen cylinder WKA37447 The Walter Kidde Co. 5 years *

Oxygen cylinder, portable

ZP650 Puritan-Zep Aero

systems. 5 years *

Crew masks MC10-** EROS, France. 6 years *

Crew masks MF10-** EROS, France. 6 years *

Passenger Masks C351-2000* B/E Aerospace/ Puritan Bennet. 6 years *

Passenger Masks 289-601* Scott Refer to the vendor CMM 35-22-26

for the installed unit.

Passenger Masks As applicable to the installed unit.

As applicable to the installed unit.

Refer to the vendor MM for the installed unit.

Crew masks As applicable to the installed unit.


Refer to the vendor MM for the installed unit.

U. Auxiliary Power Unit

APU As applicable to the installed unit.


Refer to the vendor MM, for the installed unit.

------------- END ---------------


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PART-9 SUPPLEMENTAL TYPE CERTIFICATE

PART-9

SUPPLEMENTAL TYPE CERTIFICATE


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PART-9

SUPPLEMENTAL TYPE CERTIFICATE LIST

STC NO. DESCRIPTION INTERVAL

SA2710SW OBSERVER’ JUMP SEAT. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 25-10-15)

N/A

SA7944SW CABIN OXYGEN SYSTEM. FOR CONTINUED AIRWORTHINESS INSPECTION AND SERVICING REQUIREMENTS USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 35-20-05).

EVERY 1 YEAR

SA8062SW THERAPEUTIC OXYGEN SYSTEM. NO MAINTENANCE TASK FOR THIS STC

N/A

SA8063SW CABIN HEADLINER/WINDOW PANEL BRACKET. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 25-20-01).

N/A

ST09262SC TWO SUPPLEMENTAL 750 LITER OXYGEN BOTTLES. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP

MAINTENANCE MANUEL ADDENDA (CHAPTER 35-06-01). FOR HYDROSTATIC TEST EVERY 5 YEARS REFER TO AIRCRAFT FLEXIBLE MAINTANANCE SCHEDULE PART COMPONENT REQUIREMENTS.

HYDROSTATIC TEST EVERY 5 YEARS

ST09651SC CABIN INTERIOR AND AVIONICS SYSTEM. NO MAINTENANCE TASK FOR THIS STC.

N/A

ST09772SC CABIN SMOKE DETECTOR SYSTEM. FOR REMOVE/INSTALL AND ADJUSTMENT/TEST

REQUIREMENTS TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 26-11-00 AND 26-11-00, 501). FOR FUNCTION TEST EVERY 6 MONTHS REFER TO AIRCRAFT FLEXIBLE MAINTANANCE SCHEDULE PART OUT OF PHASE INSPECTIONS.

FUNCTION TEST EVERY 6 MONTHS

ST09986SC AIRSHOW 400 SYSTEM. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP

MAINTENANCE MANUEL ADDENDA (CHAPTER 23-33-40).

N/A

ST10108SC COCKPIT SPEAKER VOLUME RECALIBRATION. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP


N/A


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ST10109SC COCKPIT SPEAKER INHIBIT SWITCH. FOR REMOVE/INSTALL REQUIREMENTS TO USE HAWKER 800XP


N/A

ST10128SC PRECISE FLIGHT PULSELIGHT SYSTEM ACTIVATED BY (EXISTING) TCAS. FOR REMOVE/INSTALL AND ADJUSTMENT/TEST

REQUIREMENTS TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 34-45-06).

N/A

ST10187SC AIRCELL 3100 SATELLITE COMMUNICATION SYSTEM. FOR REMOVE/INSTALL AND SYSTEM TROUBLESHOOTING AND

FUNCTIONAL TEST REQUIREMENTS TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 23-16-20).

N/A

ST10369SC EMERGENCY LIGHTING SYSTEM. FOR REMOVE/INSTALL AND FUNCTIONAL TEST REQUIREMENTS

TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 33-50-05).

N/A

ST103585SC CMS-1 CABIN MANAGEMENT SYSTEM1

NO MAINTENANCE TASK FOR THIS STC. N/A

ST01342WI-D INSTALLATION OF IFIS-5000 AND PRO LINE 21 RADIOS. NO MAINTENANCE TASK FOR THIS STC.

N/A

ST09250AC DEVORE LOGO LIGHT. FOR REPLACEMENT AND ADJUSTMENT/TEST REQUIREMENTS

TO USE HAWKER 800XP MAINTENANCE MANUEL ADDENDA (CHAPTER 33-40-55).

N/A

ST00459NY ALLIED SIGNAL (GARRETT) GTCP 36-150W GAS TURBINE AUXILIARY POWER UNIT. FOR SERVICING REMOVAL/INSTALLATION AND

ADJUSTMENT/TEST REQUIREMENTS TO USE HAWKER 800XP


N/A

SA4147NM COCKPIT SUN VISOR. NO MAINTENANCE TASK FOR THIS ST

N/A

ST02893AT BOOM BEAM TAXI/LANDING LIGHT SYSTEM. FOR CONTINUED AIRWORTHINESS REQUIREMENTS TO USE LOPRESTI DOCUMENT MANUAL NUMBER LSM-500-042 AND

LSM-500-047.

INSPECTION EVERY 24 MONTHS OR 1,800 HRS

ST01431WI-D MODIFICATION OF A COLLINS DBU-4000 OR DBU-4100 DATA

BASE UNIT INSTALLATION TO A COLLINS DBU-5000 DATABASE

UNIT SYSTEM. NO MAINTENANCE TASK FOR THIS STC.

N/A


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ST10001SC-D HONEYWELL SOLID STATE FLIGHT DATA RECORDER WITH INTERFACE TCOLLINS PROLINE 21 FOR REMOVE/INSTALL AND ADJUSTMENT/TEST AND

INSPECTION/CHECK REQUIREMENTS TO USE HAWKER 800XP


N/A

ST01342WI INSTALLATION OF IFIS-5000 AND PRO LINE 21 RADIOS. NO MAINTENANCE TASK FOR THIS STC.

N/A

ST10596SC-D INSTALLATION OF AN AIRCELL VOICE/DATA

COMMUNICATION SYSTEM. NO MAINTENANCE TASK FOR THIS STC.

N/A

ST01809LA INSTALLATION OF SEALED LEAD ACID BATTERY PN 9750W0640. FOR REMOVAL/INSTALLATION AND INSPECTION/CHECK

REQUIREMENTS TO USE AIRCRAFT MAINTENANCE MANUAL (CHAPTER 24-30-151). FOR CONTINUED AIRWORTHINESS CAPACITY CHECK INTERVALS REQUIREMENTS TO USE COMPONENT MAINTENANCE MANUAL PART NO. 9750W0640.

See below:

CAPACITY CHECK INTERVALS Initial Capacity Check: The initial capacity check occurs at, or before, 550 +- 55 days, or 2500 +-250 flight hours,

or 3000 +- 300 APU start events (whichever occurs first), after the installation of a new or reblocked battery. Any capacity check showing greater than or equal to 90% remains: Perform the next capacity check at or before the next 550 +- 55 days, or 2000 +- 200

flight hours, or 2000 +- 200 APU start events have accumulated (whichever occurs first). Any apacity check showing less than 90% but greater than or equal to 85% remains: Perform the next capacity check at or before the next 365 +- 30 days, or 1000 +- 100

flight hours, or 800 +- 80 APU start events have accumulated (whichever occurs first). Any Capacity check showing less than 85% but greater than 80% remains: Perform the next capacity check at or before the next 90 +- 10 days, or 300 +- 30 flight hours, or 250 +- 25 APU start events have accumulated (whichever occurs first). Any Capacity check showing less than or equal to 80% remains: Reject battery, and either submit battery for re-blocking, or scrap.

------------- END ---------------


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PART-10 MANDATOLIMITATION

PART-10

MANDATORY LIFE LIMITATIONS

1. MANDATORY LIFE LIMITATION (AIRWORTINESS LIMITATION)


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PART-10

1. MANDATORY LIFE LIMITATIONS

Instructional Data

NOTE








For the Mandatory Life Limitations for this aircraft refer to the Airworthiness Limitations

Document, Reference CJE-HPA-C-GEN-AW1667.


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PART-10

MANDATORY LIFE LIMITATIONS

INTRODUCTION 1. GENERAL

This Airworthiness Limitations Document has been compiled to collate the component lives for

HAWKER 850XP, airplanes. The component lives specified in the Aircraft Maintenance Schedules,

Aircraft Flight Manuals and US Type Certification Data Sheet have been revised and have now

been superseded by this document. In the case of engine components, reference must be made to

the appropriate engine manufacturers' documentation.

2. PUBLICATIONS CHANGE REQUEST (PCR) If an irregularity or missing information is noted, the user of this manual may access a PCR form at

http://pubs.hawkerbeechcraft.com. Instructions on how to submit a PCR are included on the web

page.

3. PART NUMBERS

Where the part number of a component or assembly is followed by an asterisk (for example

25UM807A/*), this is to indicate that all variants of the component or assembly are subject to the

same life limitation. If the part number suffix letter is given (for example 25CF1445A/B), the life

limitation quoted is unique to that particular variant of the component or assembly.

Where component part numbers are not listed in this document the component is an "On Condition"

item or in the case of landing gear components, lifed in excess of 35,000 landings which is the life

of the airplane.

4. EFFECTIVITY

Each component listed in this document has a "series" column (effectivity). Due to the various

modification build standards of airplanes the information contained in the series column should only

be used as a general guide. Operators must determine the part number of the components installed

in their airplane when complying with the requirements in this document .


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5. COMPONENT LIVES AND MANDATORY LIMITATIONS

The component lives published in this document are mandatory limitations and it is the duty of the

operator or his contracted maintenance organization, where appropriate, to implement these

requirements at or before the periods specified. For the cases in which more than one life limitation

is stated, use the one that elapses first.

The lives quoted by this document are based on a set of assumed typical operating conditions .

These assumptions take into account the experience obtained from in-service airplanes and the

relative performance characteristics of the different variants.

The projected operation has been described in the form of Flight Plans or Mission Profiles; whilst

these have been invested with a degree of conservatism it is not possible for Hawker Beechcraft

Corporation to make sure that they will cover every airplane in service.

Should actual airplane operation differ significantly from the assumed profiles then due allowance

must be made for the effects on the structural fatigue characteristics and hence the prescribed lives

in this document.

Any operator who finds that the operation of their airplane differs from the following typical mission

profiles, which have been used for the purpose of compiling component lives, should contact:

Customer Support Department, Hawker Beechcraft Corporation.

A. For 850XP Airplanes

A typical mission profile allows for:

One cabin pressurization to full differential (8.55 psi),

One full cycle of flap operation, and

One full landing gear cycle including braked, full stop landing,

per flight.

A flight is defined as a single completed take-off and landing sequence.

Touch and go landings, or rollers, are considered to be equivalent to full stop landings for

maintenance purposes.

It is also assumed that the majority of flights are carried out at cruise altitudes of 25000 feet and

above using normal climb and descent procedures, with an allowance for flights at lower cruise

altitudes. The rate of fatigue damage to the structure could be greater than predicted if more than

30% of the flights involve cruises at altitudes below 25000 feet .

The airplane is assumed to operate in a manner typical to normal business operations . The

assumed block time for average flights is 1.5 Hours. Fatigue damage per flight could be increased if

a significant number of flights are shorter in duration, thereby resulting in reduced airworthiness

limitations. Example of flights not typical of normal business operations include frequent landings

due to flight training, low altitude cruise, search and rescue etc.


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B. Control Of Life Limited Parts

All persons who remove life-limited parts from airplanes, safely control these parts. Most life-limited

parts can be controlled using a record keeping system based on the serial numbers of those parts .

Life-limited parts which have been determined to be impractical to mark with a serial number are

identified by a ‡ symbol following their part number in this document. If removal of such a part from

the airplane is required before the end of its published replacement life limitation, it should be

bagged and identified with accumulated hours/cycles; and records should be maintained to ensure

compliance with the life limitation.

Where a serial number was not established for a life-limited part, one of the other acceptable

methods such as a tag or permanent marking can be used . Hawker Beechcraft Corporation

provides the following guidance for adhering to this rule:

(1) The following guidelines may be used to assess the life status of an airplane part .

(a) If the part is original to the airplane:

1 For determining compliance with calendar time life limitations, the beginning of the part life

shall be the date of issuance of the original airplane airworthiness certificate.

2 For determining compliance with usage related life limitations, the total airplane hours,

landings or cycles shall be considered as appropriate.

(b) If the part is a replacement:

1 For determining compliance with calendar time life limitations, consider the calendar time since

the logbook verified installation date plus any prior usage of the replacement part .

2 For determining compliance with usage related life limitations, consider the airplane hours,

landings or cycles, as appropriate, accrued since the logbook verified part installation, plus

any prior usage of the replacement part.

Warning: If the life status of a part cannot be determined, the part shall be considered to be beyond

its safe life and must be disposed of in accordance with CAAT

Note: This is not an exhaustive list.

(a) The part may be marked with permanent ink.

(b) A tag may be attached to the part.

(c) A record keeping procedure may be established for the part.

(3) The following data may be used to track the life status of a part.

Note: This is not an exhaustive list.

(a) Airplane Serial Number.

(b) Part Number.

(c) Part Name.

(d) Part Serial Number.

(e) Date Part Installed/Removed.

(f) Part Flight Hours/Landings/Cycles.

(4) Parts whose life limit have been reached must be disposed of in accordance with CAAT


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C. Recommended Part Serial marking:

Upon doing required scheduled inspection for any component listed herein, if a component serial

number or date code cannot be found marked on it that uniquely identifies the component, then,

except for those items that are noted by a ‡ symbol as being impractical to mark, a serial number

should be assigned to the component.

That serial number should be permanently marked on the component in an accessible location

using an appropriate permanent method and henceforth life tracking of the component should

reflect that serial number.

A recommended serial numbering format for parts installed on in service airplanes is the installed

on airplane serial number followed by a two digit sequence number, i .e. a life limited part installed on

airplane serial number 258658 would be assigned 25865801.

------------- END ---------------


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PART-10

MANDATORY LIFE LIMITATION

Fire Protection

Assembly Component

Life Limitation

Remarks Series Description

Part No. Description Part No.

Fire extinguishers

Extinguisher bottle, engine

33200009-3 10 yrs from installation or 15 yrs from manufacture.

850XP

Cartridge, engine

30900000M 10 yrs from installation or 15 yrs from manufacture. 850XP

Cartridge, PATS APU extinguisher

30900000M 10 yrs from installation or 15 yrs from manufacture. 850XP

Cartridge, PATS APU extinguisher

60-60019 10 yrs from installation or 15 yrs from manufacture. 850XP

Extinguisher bottle, APU

4190-1 10 yrs maximum from date of manufacture

850XP

Portable

extinguisher

container,

part of

BA51015

BA40015

10 years from manufacture.

Start date for life limitation

is the date of manufacture

labelled on the side of

container.

Mod

252739

and Mod

258901

850XP


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PART-10


Flight Controls

Assembly Component

Life Limitation


Part No. Description

Part No.

Flap synchro cables

LH inner

850XP

25CF3455-17A

25CF3455-19A

5,000 flights

Post Mod 25F640A. Direct replacement for cable Part Nos. 25

CF3225/17 & /19

LH outer

850XP 25 CF3455-3A

25 CF3455- 7A

5,000 flights


CF3225/3 & /7

Flap synchro cables

RH inner

850XP 25 CF3455-9A

25 CF3455-11A

5,000 flights


CF3225/9 & /11

RH outer

850XP

25 CF3455-13A

25 CF3455-15A

5,000 flights


CF3225/13 & /15

Airbrake jacks

AIR46520-1

Body AIR111462 25,000

landings 850XP

AIR46521-1

Body AIR111463 25,000

landings 850XP


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PART-10


Fuel

Assembly Component Life

Limitation Remarks Series

Description Part No. Description Part No.

THERE ARE NO EQUIPMENT FOR LIFE LIMITATION.


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PART-10


Hydraulic Power






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PART-10


Landing Gear

Assembly Component

Life

Limitation


Part

No. Description Part No.

NOTE

Refer to SB 32-3615 and SB 32-3696 for information on life limitations for Sidestay

Components. SB 32-3615 and SB 32-3696 are issued because Sidestay components

common to the Series 1 through 1000 (including 750, 800XP, 850XP and 900XP)

airplanes have different life limits but have the same Part Number.

Side Stay

Assembly

Side stay

upper arm

25-8UM71-

1A,2A

12,000

landings

Post Mod

252884U

850XP

Side stay lower

arm

25-8UM31-1A,

-2A

27,000

landings

Pre-Mod

253129A 850XP

Jack distance

pin 25UM423

24,000

landings 850XP

Jack pivot bolt 25UM153A 30,000

landings 850XP

Jack pivot 25UM1229A 4,000

landings

Post Mod

252267.

See

Appendix.

850XP

Upper casing 25-8UM169-

31A 24,000

landings

Post Mod

253549A 850XP

Torque links 25-9UM9-1A

25-9UM11-1A

20,000

landings 850XP

Torque link pin 25-8UM15-1A 20,000

landings

Pre-Mod

253511A 850XP


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NOTE

Refer to SB 32-3697 and SB 32-3614 for information on life limitations of the Main

Landing Gear Plunger Tube. SB 32-3697 and SB 32-3614 are issued because the Plunger

Tube common to the Series 600, 700, 750 800, 800XP, 850XP and 900XP airplanes have

different life limitations but have the same Part Number.

Plunger

tube 25-8UM5 17,000 landings Pre-Mod. 25F952 850XP

Retraction

arm

25-8UM63-

1A 12,000 landings

Post Mod 253129A

NOTE : Retraction

arms in excess of

12,000 landings

are to be

replaced at next

overhaul unless

they exceed

16,600 landings

which would

require

replacement

within 6 months

after May 2007

850XP

Main

Landing

Gear Jack

AIR48502,

AIR48502/2,

/3, /4, /5, /6,

/7

AIR48503,

AIR48503/2,

/3, /4, /5, /6,

/7

Jack eye

end

AIR158922

‡ 10,000 landings

Post Mod

251720A.

SB 32-62

850XP

AIR48502/4,

AIR48503/4

Jack

cylinder

head

AIR127866

12,000 landings

total, or 14

years from the

date of

incorporation of

SB 32-3391,

whichever

occurs first.

Post SB 32-3391

850XP


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Assembly Component

Life

Limitation


Part

No. Description Part No.

Nose Landing

Gear Pivot pin 25UN645A

16,000

landings 850XP

Jack lower pivot pin 25UN597 22,000

landings

Post Mod

251909 850XP

Main casing bolt 25UN603 33,000

landings

Post Mod

251909 850XP

Plunger tube 25UN649 20,000

landings

Post Mod

252094B 850XP

Axle barrel 25-8UN257-

1A

30,000

landings

Post Mod

253129A 850XP

Torque links 25UN491

25UN489

32,000

landings

Pre-Mod

253129A

850

XP

Torque links pick-up

sleeve

25-8UN455-

1

20,000

landings

Post Mod

253129A 850XP

Connecting rod 25-8UN433-

1A

20,000

landings

Post Mod

253129A 850XP

Drag Stay

Assembly

Drag stay bridge

casting

25-8UN487-

1A

33,000

landings

Post Mod

253129A 850XP

Drag strut pick-up 25-8UN265 13,900

landings

Post Mod

253129A 850XP

Bolts, nose gear radius

rod pick-up attachment A102-21J ‡ 10,000

landings

Replace with

DHS1432-

21J

850XP

Bolts, nose gear main

pick-up trunnion

attachment

A102-28J ‡ 10,000

landings

Replace with

DHS1432-

28J

850XP


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Assembly Component

Life

Limitation

Remarks Series


Wheel brake

control valves

AC61520,

AC67352,

AC67732,

AC67740

Knife edge

ACO34629,

ACO34630,

ACO34633

4,500

landings

Post Mod

257211 850XP

Emergency

brake reducing

valves

AC61516,

AC69006,

AC67738,

AC67742

AC69784

Knife edge ACO34629,

ACO34630

4,500

landings

Post Mod

257211

Post Mod

253522A

850XP

Steering Steering pin 25UN605 25,000

landings

Post Mod

251909 850XP

Steering

main

member

25-8UN431-

1A, -2A

35,000

landings

Post Mod

253129A 850XP

Steering

sleeve 25-8UN439-1A

20,000

landings

Post Mod

253129A 850XP

Steering jack AIR45396 Jack eye end AIR110646 ‡ 14,400

flights 850XP

Jack pick-up 25-8UN263-1A 18,000

landings

Post Mod

253129A 850XP


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PART-10


Oxygen




Portable breathing equipment

802300-14 Protective breathing equipment unit

10 years Scott SB 35-3495

850XP


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PART-10


Airborne Auxiliary Power

Assembly Component

Life Limitation

Remarks Series Description Part No. Description

Part No.

APU Honeywell

GTCP36-150

(W) Rotor Turbine See remarks

Honeywell MM 49-23-93

850XP

APU Honeywell

GTCP36-150

(W) Rotor Compressor

See remarks

Honeywell MM 49-23-93

850XP


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PART-10


Fuselage






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PART-10


Windows






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PART-10


Wings

Assembly Component

Life Limitation


Part No. Description Part No.

Wing structure

Bolts, flap hinge attachment angles to main landing gear mounting fittings

DHS1432-7

DHS1555-7 14,600 landings

Pre-Mod.25F947A

850XP


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PART-10


Power Plant – General






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PART-10


Engines




Engines TFE731-

5BR FAN DISC. 3074621-4 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPC STG.1

DISC 3072395-2 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPC STG.2

DISC 3072396-3 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPC STG.3

DISC 3072397-3 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPC STG.4

DISC 3075326-3 20,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR IMPELLER 3075765-2 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR HPT DISC. 3075227-2 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPT STG.1

DISC 3075446-2 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPT STG.2

DISC 3075425-1 10,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

LPT STG.3

DISC 3075573-1 12,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR HPT SHAFT 3072545-1 12,000 Cycles

SB731-72-

3001 850XP

Engines TFE731-

5BR

HPT SEAL

PLATE 3075579-1 30,000 Cycles

SB731-72-

3001 850XP


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PART-10


Appendix

Hawker Beechcraft Corporation has identified that the following items may cause difficulties to some operators when complying with this document. For this reason these items have been

assessed individually and alleviation has been provided . Main landing gear jack pivots - 25UM1199A, 25UM1229A and 25-8UM87-1A

Subject to the accomplishment of the specified inspections, Service Bulletin No. 32-233 allows for

utilization of the main landing gear retraction jack pivots beyond the 4,000 landings limitation specified in this document. Modification Service Bulletin No. 32-233-3597A introduces a modified

jack pivot which has no life limitation and can be used as a direct replacement for the above mentioned items.

------------- END ---------------


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