WORK PACKAGE INSTRUCTIONS - Avtrac · 2019. 9. 11. · INSTRUCTIONS FOR LAMES Avtrac Maintenance...

PERTH MAINTENANCE CONTROL OFFICE

Broome Aviation Pty Ltd Phone: (08) 9477 5205 Perth Maintenance Control Office Fax: (08) 9477 1170 P.O.Box 568, Belmont WA 6984 Mobile: 0418 959 892

WORK PACKAGE INSTRUCTIONS

AIRCRAFT TYPE: …CESSNA 210…… VH – KDM DATE: …17-Oct-18…...

INSPECTION: …..Engine Overhaul/SIDs….. MC NUMBER: …MC2018-1118.….

ORGANISATION: …Broome Air Maintenance Pty Ltd………..

AVTRAC Blue Maintenance Tracking

No Instruction

1 Transfer any open endorsements from current Maintenance Release to Worksheets.

2 Complete the Inspections and events listed in Work Package – certify.

3 Strike thru completed items on Form 090 MC2018-0898.

4 Make Log Book entries as required.

4

Post Work Package immediately to: Mail ONLY:

Aero Group Pty Ltd P.O.Box 568, Belmont, WA 6984

Consigned Freight ONLY (No mail):

Aero Group Pty Ltd Unit 2, 61 Belmont Ave, Belmont, WA 6104

Paul Carey

Mobile: 0418 959 892

INSTRUCTIONS FOR LAMES

Avtrac Maintenance Tracking FORM 05-005 Initial Issue 14/10/13 Page 1

Avtrac Gold Aircraft Maintenance Control System The Avtrac Gold Maintenance Control System is a remote maintenance control system, where the aircraft logbooks are held off site from maintenance. It is the responsibility of each LAME to ensure the requirements of CAR 1998 42ZE and the System of Certification are complied with, and in particular ensuring:

1. DETAILS: All header details are completed on Work and Survey Worksheets – TTIS, Date, and Job Number etc – on each page.

2. SIGNATURE: Each Certification includes a Signature, License Number, and Date. Ensure each Work

and Survey Worksheets has a Category Certification completed at the bottom. Refer to examples for certifications.

3. FINAL CERTIFICATION: Must be completed on Form 125 provided, on your own Loose Log Entries,

or on the M/R for unscheduled items.

4. DUPLICATE: If an Independent Inspection of Flight Control Systems is required IAW CAR 42G (2), include the original certification sheet in the Work Package – we will insert into the logbooks to meet the regulatory requirement. (Make a photocopy if required for your records.)

5. COMPONENTS: If an unscheduled component is replaced on an aircraft, the following must be

recorded:

a) Part Number OFF b) Serial Number OFF c) Part Number ON d) Serial Number ON e) Release Note Number. Provide the original Release Note in the Work Package (Make a

photocopy if required for your records.) or f) Serviceable Tag details. Provide the original Release Note in the Work Package (Make a

photocopy if required for your records.)

6. S/N CHECK: If a scheduled component is due for replacement as called up in a Work Package Work and Survey Worksheet, complete a Serial Number check of the component first. If the Serial Number does not match the component to be removed – call the Maintenance Controller immediately. An audit of the records will be carried out to find out why the serial number does not match. The component may not have to be removed.

7. LIFED COMPONENTS: If a scheduled component is due for replacement as called up in a Work

Package Work and Survey Worksheet, the following must be recorded:

a) Part Number OFF b) Serial Number OFF c) Part Number ON d) Serial Number ON e) Release Note Number. The Release Note MUST detail the life since last overhaul of

the component. Provide the original Release Note in the Work Package (Make a photocopy if required for your records.)

f) Serviceable Tag details. The Serviceable Tag MUST detail the life since last overhaul of the component. Provide the original Release Note in the Work Package (Make a photocopy if required for your records.)

NOTE: If a Work Package is returned with a component change with no life details, the Maintenance

Controller will require details immediately, or will instruct for the component to be removed.

8. MODS: If a modification is carried out on the aircraft, include the original copies of Engineering Orders, STC’s, Modification Drawings, Kit Instructions etc. We will insert into the aircraft logbooks for easy reference.



9. NTD: If an inspection is required using a non destructive testing method, the following must be recorded

a) The non-destructive testing method used b) The procedure used to carry out the inspection c) What was found as a result of the inspection d) Provide the original Test Report in the Work Package (Make a photocopy if required for

your records.) If the NDT contractor supplies reports after returning to their business premises, direct the contractor to post the reports to the Maintenance Controller.

10. RETURN: Work Packages must be returned in three working days after the aircraft maintenance has

been completed. If you cannot meet this requirement, consider revising your certification procedures. “Signing as you go” is better practice than “signing up after”. If postage may be delayed, please fax the complete Work Package back immediately.

11. CONTENTS: Work packages must be returned complete, and must include:

a) All pages created by the Maintenance Controller in the original issue b) The expired Maintenance Release (on M/R inspections) c) A copy of the issued Maintenance Release (on M/R inspections) d) All details required above. e) Goods tracking forms, for parts used during maintenance. f) Category and Final Certification forms used during maintenance.

12. PREVENTATIVE MAINTENANCE ITEMS: During the course of maintenance, if the LAME discovers:

a) A part that has worn, but is still within manufacturer limits; or b) A maintenance action that would enhance the serviceability of the aircraft; or c) An acceptable maintenance action the operator or owner requests, that is in addition to

the requirements in the Control System for that aircraft; or d) A maintenance action that may be brought forward before the scheduled due time or date

The LAME may enter the Preventative Maintenance Item on the Work And Survey Sheet to the attention of the Maintenance Controller for entry into the Control System for future scheduling. The LAME may give an expire TTIS/Cyc/Ldg or Date for which the Preventative Maintenance Item must be scheduled to be performed, based on an assessment of the manufacturer limits and data. If the expire TTIS/Cyc/Ldg or Date of the Preventative Maintenance Item occurs in the periodicity of the current Maintenance Release, the Item must be entered on the M/R Part 1 as due maintenance, and the TTIS/Cyc/Ldg or Date entered. We will enter Preventative Maintenance Items into the Control System, and call them up at the next scheduled inspection – or at a time you nominate. Examples: 1 Main Landing Gear torque links approaching

maximum wear limit. Considered satisfactory for 110 flight hours or 12 months. Order new bushes for next Phase Inspection.

P/N 0011223344 Signature W1234 20th Feb 2000

AIRCRAFT RECORDS NOTE: Each Work Package is filed in sequence in the records file for each aircraft. The files are readily accessible to be referenced, faxed or pages copied and sent upon request. Some Maintenance Organisations do not keep copies of Work Packages, and CASA is OK with that as long as access is maintained.



Manufacturer supplied worksheets must be certified correctly – see below.

CATEGORY CO-ORDINATION CERTIFICATION SHEET

AIRCRAFT TYPE ....................................... VH - ..................

INSPECTION ..............................................

AIRCRAFT TTIS ..........................................

AIRCRAFT CYCLES ..................................

HEATER HOURS ........................................

CATEGORY *SIGNATURE LICENSE No DATE

AIRFRAME

ENGINE

ELECTRICAL

INSTRUMENT

RADIO

* A signature in this column constitutes a certification pursuant to Reg 42 ZE, that the category of the inspection to which it relates has been properly carried out.

JOB CO - ORDINATORI certify, pursuant to Reg 42 ZE that I have co - ordinated the whole inspection referred to above and I am satisfied that all maintenance required to be performed, has been completed and properly certified.

SIGNED: ..................................... JOB NUMBER .........................

LICENCE NO: .............................

DATE: ..........................................

MAINTENANCE RELEASE NO: .....................................

Broome Air Maintenance Pty Ltd P.O.Box 386 BroomeWestern Australia 6725

Form BAM002

For and on Behalf of Broome Air Maintenance Pty Ltd

CESSNA 210 ENGINE CHANGE SUMMARY SHEET


VH - ______ TTIS: __________ J/N: _____________ No Engine

If not changed – write “No action” Serial Number OFF Leave NO BLANKS

Serial Number ON Leave NO BLANKS

1 Engine IO-520-___ 2 Propeller

No Component Name

If not changed – write “No action” Serial Number OFF Leave NO BLANKS

TSO Leave BLANK

Serial Number ON Leave NO BLANKS

TSO Leave BLANK

1 Magneto LH 2 Magneto RH 3 Fuel Pump 4 FCU 5 Fuel Manifold 6 Alternator 7 CSU 8 Starter Motor 9 Hydraulic Pump

10 Vac Pump 11 Tacho Gen No Accessories

If not changed – write “No action” Work Carried out New fitted, overhauled, inspected only, transferred, no action etc

1 Fuel and Oil Hoses Teflon 2 Fuel and Oil Hoses Non-teflon 3 Vacuum Hoses 4 Engine Mounts 5 Air Filter 6 Breather Separator 7 Alternator Coupling 8 Baffles 9 Exhaust 10 Exhaust transition 11 Air box Note: This page does not constitute a Certification IAW CAR42ZE. Additional work must be raised on worksheets. This Summary Page is an accurate overview of the extent of replacement (ie – core engine only, or complete engine bay)

Form BAM006

Broome Air Maintenance Pty Ltd P.O.Box 386 Broome Western

Australia 6725

Flight Control System : Dual Maintenance Certification Sheet

AIRCRAFT TYPE ....................................... VH - ..................

AIRCRAFT TTIS ......................... DATE ..............................

JOB NUMBER .............................

I certify that the following control system

.................................................................................................................................. Has been inspected for correct assembly and locking from

.................................................................................................................................. To .................................................................................................................................. And the entire control system has been inspected for correct assembly and sense in accordance with the requirements of CASA Regulation 42G.

1st Inspection ...................................................

Lic No/ARN ........................... Date ..........................

2nd Inspection .................................................

Lic No/ARN ........................... Date ...........................

A Certification above constitutes a certification pursuant to CASA Reg 42ZE.

Version 1.1 – 26th May 2015

MAGNETIC COMPASS SWING GUIDELINES


AC 43.13-1B chapter 12 section 3. COMPASS SWING must be performed whenever any ferrous component of the system (i.e. flux valve compensator, or Standby Compass) is installed, removed, repaired, or a new compass is installed. The magnetic compass can be checked for accuracy by using a compass rose located on an airport. The compass swing is normally effected by placing the aircraft on various magnetic headings and comparing the deviations with those on the deviation cards. Refer to CFR14, 23.1327, 14 CFR 23.1547, and the equipment or aircraft manufacturer's manual. A compass swing must be performed on the following occasions: (1) When the accuracy of the compass is suspected. (2) After any cockpit modification or major replacement involving ferrous metal.(Engine change) (3) Whenever a compass has been subjected to a shock; for example, after a hard landing or turbulence. (4) After aircraft has passed through a severe electrical storm. (5) After lighting strike. (6) Whenever a change is made to the electrical system. (7) Whenever a change of cargo is likely to affect the compass. (8) When an aircraft operation is changed to a different geographic location with a major change in

magnetic deviation. (e.g., from Miami, Florida to Fairbanks, Alaska.) (9) After aircraft has been parked on one heading for over a year. (10) When flux valves are replaced. Precautions. (1) The magnetic compass must be checked for accuracy in a location free of steel structures, underground

pipes or cables, or equipment that produces magnetic fields. (2) Personnel engaged in the compensation of the compass shall remove all magnetic or ferrous material

from their possession. (3) Use only nonmagnetic tools when adjusting the compass. (4) Position the aircraft at least 100 yards from any metal object. (5) All equipment in the aircraft having any magnetic effect on the compass must be secured in the position

occupied in normal flight. Compass Swing Procedures. (1) Have the aircraft taxied to the NORTH (0°) radial on the Compass Rose. Use a hairline sight compass (a reverse reading compass with a gun sight arrangement mounted on top of it) to place the aircraft in the general vicinity. With the aircraft facing North and the person in the cockpit running the engine(s) at 1000 rpm, a mechanic, standing approximately 30 feet in front of the aircraft and facing South, “shoots” or aligns the master compass with the aircraft center line. Using hand signals, the mechanic signals the person in the cockpit to make additional adjustments to align the aircraft with the master compass. Once aligned on the heading, the person in the cockpit runs the engine(s) to approximately 1,700 rpm to duplicate the aircraft’s magnetic field and then the person reads the compass. NOTE: (1) For conventional gear aircraft, the mechanic will have to position the magnetic compass in the straight and level position or mount the tail of the aircraft on a moveable dolly to simulate a straight and level cruise configuration. (2) Remember the hairline sight compass is only intended to be used as a general piece of test equipment. (2) If the aircraft compass is not in alignment with the magnetic North of the master compass, correct the error by making small adjustments to the North-South brass adjustment screw with a nonmetallic screw driver (made out of brass stock or stainless steel welding rod). Adjust the N-S compensator screw until the compass reads North (0°). Turn the aircraft until it is aligned with the East-West, pointing East. Adjust the E-W compensator screw until it reads 90°. Continue by turning the aircraft South 180° and adjust the N-S screw to remove one-half of the South’s heading error. This will throw the North off, but the total North-South should be divided equally between the two headings. Turn the aircraft until it is heading West 270°, and adjust the E-W screw on the compensator to remove one-half of the West error. This should divide equally the total E-W error. The engine(s) should be running. (3) With the aircraft heading West, start your calibration card here and record the magnetic heading of 270° and the compass reading with the avionics/electrical systems on then off. Turn the aircraft to align with each of the lines on the compass rose and record the com pass reading every 30°. There should be not more than a plus or minus 10° difference between any of the compass’ heading and the magnetic heading of the aircraft. (4) If the compass cannot be adjusted to meet the requirements, install another one.

No Part Number Serial Number Description Quantity GRN / Batch No

Broome Air Maintenance Pty LtdWork Package Goods and Services Record

Form BAM004Page No ................VH - ............J/N .....................

BROOME AIR MAINTENANCE Pty Ltd Return to Service work sheet

This sheet does not require certification I.A.W CAR 42ZE, it is a company check sheet to ensure all work sheets and tasks have been completed and certified correctly

Job No. …………..… Aircraft Rego. ………………… Type ……………..……

CHECK THAT ACTION TAKEN AME/LAME DATE

1 Check all flight trim controls are centred/ neutral

2 Oil replenished, cap and Dipstick secure

3 Fuel caps secured

4 All panels are refitted

5 Certifications complete on work sheets

6 Maintenance release issued with all AD’s and maintenance due during validity of M/R recorded on part 1

KDMVH -210N

Engine Overhaul/SIDs

AIRCRAFT TYPE

INSPECTION

JOB CO - ORDINATOR Lic No

REGISTRATION

SERIAL No

TTIS

DATE

JOB No

SURVEY AND WORK SHEET

21063041

ITEM DEFECT RECTIFICATION COMPONENT CHANGES LAMESIGNATURE No

Form BA/100MC No 2018-1118

Broome Air MaintenancePO Box 386 Broome Western Australia 6725

Engine Continental

IO-520-L46B1007842

PART No

S/No OFF

S/No ON

R/N No

Overhaul

1Eng

AME SIGAction:

HOURS

1

Engine Mounts

C210 MMChapter 2

PART No

S/No OFF

S/No ON

R/N No

Replace

1Eng

AME SIGAction:

HOURS

2

Engine Mixture Control

C210 MMChapter 2

PART No

S/No OFF

S/No ON

R/N No

Replace

Eng

AME SIGAction:

HOURS

3

Magnetic Compass Compensation

C210 MMAWB 34-008 Issue 1

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIG

Carry out after engine overhaul/replacement

Action:

HOURS

4

I HEREBY CERTIFY THAT ALL WORK DETAILED HAS BEEN COMPLETED AND CERTIFIED FOR INACCORDANCE WITH THE REQUIREMENTS OF APPLICABLE MANUALS AND SCHEDULES. THISSIGNATURE CONSTITUTES A CERTIFICATION PURSUANT TO CAR 42ZE. LAME DateLICForm revision status: 17 Oct 2018

KDMVH -210N


AIRCRAFT TYPE

INSPECTION


REGISTRATION

SERIAL No

TTIS

DATE

JOB No


21063041


Form BA/100MC No 2018-1118


Teflon Engine Hoses

C210 MMChapter 2

PART No

S/No OFF

S/No ON

R/N No

Replace

1Eng

AME SIGAction:

HOURS

5

Engine Throttle Control

C210 MMChapter 2

PART No

S/No OFF

S/No ON

R/N No

Replace

Eng

AME SIGAction:

HOURS

6

Landing Gear Spring CorrosionInspectionSID 32-13-01Visual Inspection

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-147

Nose Gear Torque Link and ForkInspectionSID 32-20-01Visual Inspection

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-148


KDMVH -210N


AIRCRAFT TYPE

INSPECTION


REGISTRATION

SERIAL No

TTIS

DATE

JOB No


21063041


Form BA/100MC No 2018-1118


Seat Rails and Seat Rail StructureCorrosion InspectionSID 53-47-01Visual Inspection

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-149

Horizontal Stabilizer, Elevator, andAttachments InspectionSID 55-10-01Visual and eddy current

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1410

Vertical Stabilizer, Rudder andAttachments InspectionSID 55-30-01Visual and eddy current

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1411

Wing Structure Corrosion Inpsection

SID 57-11-02Visual, borescope

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1412


KDMVH -210N


AIRCRAFT TYPE

INSPECTION


REGISTRATION

SERIAL No

TTIS

DATE

JOB No


21063041


Form BA/100MC No 2018-1118


Aileron Support Structure Inspection

SID 57-51-01Visual, Eddy Current

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1413

Flap Tracks Corrosion Inspection

SID 57-53-01Visual Inspection

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1414

Engine Mount Inspection

SID 71-20-01Visual Inspection

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1415

Wing Front Spar Inspection 2

SID 57-30-01Visual and eddy current

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1416


KDMVH -210N


AIRCRAFT TYPE

INSPECTION


REGISTRATION

SERIAL No

TTIS

DATE

JOB No


21063041


Form BA/100MC No 2018-1118


Rudder Pedal Torque TubeExtensionSID 27-20-01

PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIGAction:

HOURS

2A-1417

Engine Throttle Control Lever

SEB95-15PART No

S/No OFF

S/No ON

R/N No

Inspect

Eng

AME SIG

Inspect the Throttle Control Lever to cable attacharea.

Action:

HOURS

18


AIRCRAFT TYPE

INSPECTION


VH -SERIAL No

LDGS

DATE

ITEM DEFECT RECTIFICATION COMPONENT CHANGESLAME

JOB No

LAME LIC DATE

SIGNATURE No

PART No

S/No ON

S/No OFF

B/N R/N No

CO-ORDINATION CERTIFICATION: I HEREBY CERTIFY THAT ALL WORK DETAILED HAS BEEN COMPLETED AND CERTIFIED FOR IN ACCORDANCE WITH THEREQUIREMENTS OF APPLICABLE MANUALS AND SCHEDULES. THIS SIGNATURE CONSTITUTES A CERTIFICATION PURSUANT TO CAR 42ZE.


PART No

PART No

PART No

S/No OFF

S/No OFF

S/No OFF

S/No ON

S/No ON

S/No ON

B/N R/N No

B/N R/N No

B/N R/N No

AME SIG

AME SIG

AME SIG

AME SIG

Broome Air Maintenance Pty LtdP.O.BOX 386 BROOME

WESTERN AUSTRALIA 6725Form BAM001 MC No

FINAL CERTIFICATION: M/R Part 2 Log Book

TTIS

Version 1.0Jul 2010

WORK PACKAGE INSTRUCTIONS - Avtrac · 2019. 9. 11. · INSTRUCTIONS FOR LAMES Avtrac Maintenance...

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Transcript of WORK PACKAGE INSTRUCTIONS - Avtrac · 2019. 9. 11. · INSTRUCTIONS FOR LAMES Avtrac Maintenance...