Index Manuals WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017)

WT9 Dynamic LSA. AIRCRAFT MAINTENANCE MANUAL (AS-AMM-01-000, 22. 05. 2017) - page 6

JACKING

LIFTING

AND SHORING

07-10 JACKING

1. DESCRIPTION

The aircraft has three jacking points (see Fig. 07-1). They are located under the
fuselage and wing central section. The front jack is installed under the jacking point
located on the right front lower side of the fuselage (under firewall). The two rear
jacks are installed under jacking points, located symmetrically in wing central
section (under auxiliary spar). Jacking points are identified on the fuselage by the
placards

“

LIFT HERE”

2. MAINTENANCE PRACTICES

Jacking

Type of maintenance:

Line

Personnel qualification:

Pilot/Owner qualified in accordance with M.A.803
or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Lift jack

3 pcs

Stand

1 pc

Persons

Tab. 07-1 Recommended tools, materials, persons and documentation

(1) Aircraft jacking:

(a) Place the aircraft on paved, level surface.

(b) Put 3 pcs lift jacks to appropriate jacking points.

jacks together to keep the aircraft levelled as much as possible.

(d) Put stand under the tail and secure tail.

Effectivity:

ALL

04. 07. 2019

LIFTING
AND SHORING

Fig. 07-1 Aircraft Jacking

(2) Aircraft lowering:

CAUTION

MAKE SURE THAT THE AREA UNDER THE AIRCRAFT IS CLEAR
BEFORE YOU LOWER THE AIRCRAFT OFF JACKS.

(a) Remove stand under the tail.

(b) Retract the jacks until the wheels are on the ground. Operate the

jacks together to keep the aircraft leveled as much as possible.

SHORING

LIFTING

AND SHORING

07-10 SHORING

1. DESCRIPTION

Before carrying out any maintenance in the rear section of aircraft, shore the aircraft
to avoid upset (see Fig. 07-2).

The aircraft is shored by the front jack installed under the jacking point located on
the right front lower side of the fuselage and the stand under the tail. Jacking point is
identified on the fuselage by the placards

“

LIFT HERE”

2. MAINTENANCE PRACTICES

Shoring

Type of maintenance:

Line

Personnel qualification:

Pilot/Owner qualified in accordance with M.A.803
or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Lift jack

1 pc

Stand

1 pc

Persons

Tab. 07-2 Recommended tools, materials, persons and documentation

(1) Aircraft shoring:

(a) Place the aircraft on paved, level surface.

(b) Put lift jack to front jacking point.

Effectivity:

ALL

04. 07. 2019

LIFTING
AND SHORING

Fig. 07-2 Aircraft Shoring

CONTENTS

LEVELING

AND WEIGHING

08 LEVELING AND

WEIGHING

CONTENTS

GENERAL ......................................................................... 3

INTRODUCTION ....................................................................... 3

08-10

LEVELING ........................................................................ 5

DESCRIPTION .......................................................................... 5

MAINTENANCE PRACTICES ................................................... 5

Aircraft on jacks ................................................................. 5

Aircraft on wheels .............................................................. 6

08-20

WEIGHING ........................................................................ 9

DESCRIPTION .......................................................................... 9

MAINTENANCE PRACTICES ................................................. 10

Aircraft weighing .............................................................. 10

Calculation method .......................................................... 13

GENERAL

LEVELING

AND WEIGHING

08-00 GENERAL

1. INTRODUCTION

This chapter describes how to level and weigh the aircraft.

Use the procedures in Chapter 08-10 to level the aircraft. Use the procedures
in Chapter 08-20 to weigh the aircraft and to calculate the aircraft CG position.

LEVELING

AND WEIGHING

08-10 LEVELING

1. DESCRIPTION

Some operations related to maintenance or repairs require the aircraft to be leveled.

The  aircraft  may  be  leveled  with  jacks  or  by  changing  the  tire  inflation.  To  level
the aircraft,  the cabin sills above main spar and canopy  frame are used (Fig. 08-1).
Lateral and longitudinal leveling is checked using a spirit level. The aircraft should
be placed on a level surface, and should be protected from a wind  (preferably inside
a hangar).

2. MAINTENANCE PRACTICES

Aircraft on jacks

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Lift jack

3 pcs

Stand

1 pc

Spirit level

1 pc

Persons

Tab. 08-1 Recommended tools, materials, persons and documentation

(1) Leveling:

(a) Lift the aircraft on jacks (Chapter 07-10).

(b) Open the canopy.

of appropriate jacks. Check the lateral leveling by a spirit level placed
across the cabin sills above the main spar with the canopy opened
(Fig. 08-1). If the spirit level is not long enough, a suitable extension
(e.g. even wooden plank) may be used with the spirit level placed
on top. Be careful not to damage the cabin sills when leveling.

(d) Adjust the aircraft longitudinally leveled position by extending

or retracting of appropriate jacks. Check the longitudinal leveling
by a spirit level on the canopy frame (Fig. 08-1).

(e) Remove the spirit level and close the canopy.

Effectivity:

ALL

12. 06. 2020

LEVELING
AND WEIGHING

Aircraft on wheels

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Pads (various thickness)

Spirit level

1 pc

Persons

Tab. 08-2 Recommended tools, materials, persons and documentation

(1) Leveling:

(a) Open the canopy.

(b) Adjust the aircraft laterally leveled position by deflating the appropriate

main wheels’ tire or install under main wheels suitable pads. Check
the lateral leveling by a spirit level placed across the cabin sills above
the main spar with the canopy opened (Fig. 08-1).

If the spirit level is not long enough, a suitable extension (e.g. even
wooden plank) may be used with the spirit level placed on top.
Be careful not to damage the cabin sills when leveling.

wheel’s tire or install under nose wheel suitable pad. Check
the longitudinal leveling by a spirit level on the canopy frame
(Fig. 08-1).

(d) Remove the spirit level and close the canopy.

CAUTION

AFTER THE OPERATION ON THE LEVELED AIRCRAFT IS
FINISHED,

INFLATE

THE

LANDING

GEAR

TIRES

WITH PRESCRIBED PRESSURE (Chapter 12-10).

NOTE

Deflate  the  tires  slowly  and  in  small  steps  -  note  with  inertia
of  the  system.  When  deflating  the  tire,  take  care  to  avoid
excessive  deformation  of  the  tire.  If  the  deflation  of  the  nose
wheel’s  tire  is  not  sufficient,  install  under  the  main  wheel
the suitable pads.

LEVELING

AND WEIGHING

Fig. 08-1 Aircraft Leveling

WEIGHING

LEVELING

AND WEIGHING

08-20 WEIGHING

1. DESCRIPTION

The aircraft must be operated within the permitted limits of load and center of gravity
to obtain the expected flight performance, flight characteristics and flight safety.

After more complex modification, more extended repair, repainting, etc., of the aircraft,
etc., the weight and center of gravity may be influenced, the new basic empty weight /
moment and CG position must be determined by weighing.

When a compact piece of equipment is installed on (or removed from) the aircraft and
an accurate weight and center of gravity arm (distance from the aircraft’s reference datum
to the installed equipment’s center of gravity) can be accurately specified, the new basic
empty weight / moment and CG position

can be calculated using the aircraft’s weight

and balance record.

Reference  datum  is  an  imaginary  vertical  plane  from  which  all  horizontal  distances
for  the  center  of  gravity  calculations  are  measured.  The  reference  datum  is  located
1.975  mm  forward  direction  from  inner  surface  of  the  firewall,  perpendicular
to the longitudinal axis of the aircraft.

Permitted limits of empty aircraft weight and CG are given in the POH (Chapter 6).

Effectivity:

ALL

12. 06. 2020

LEVELING
AND WEIGHING

2. MAINTENANCE PRACTICES

Aircraft weighing

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Scales

1 pc

Spirit level

1 pc

Plumb line (or optical level)

1 pc

Persons

Tab. 08-3 Recommended tools, materials, persons

and documentation

(1) Preparation for weighing:

(a) Defuel the aircraft

’s fuel system (Chapter 12-10).

(b) Weigh the aircraft in a closed building to prevent errors due to wind

gusts.

’s surfaces.

(d) Remove all snow, ice and dirt from the wheel fairings.

(e) Remove all objects not included in the aircraft

’s Equipment List.

(f)

Remove all objects not included in the aircraft

’s Weight and Balance

Record.

(g) Verify all items in the Equipment List are installed in their correct

location.

(h) Inflate the aircraft

’s tires to their recommended operating pressures

(Chapter 12-10).

(i)

Verify oil, brake fluid and coolant are at their prescribed maximum
levels (Chapter 12-10).

(j)

Close covers and other lids.

(k) Place scales under each wheel (minimum scale capacity 300 kg /

660 lbs).

(l)

Brake lever to PARK position.

(m) Remove the external control locks and place all controls to their neutral

position. Retract the wing flaps

WEIGHING

LEVELING

AND WEIGHING

(2) Aircraft leveling:

(a) Level the aircraft on wheels (Chapter 08-10).

(3) Weighing:

(a) With the aircraft leveled and canopy closed, obtain and record

the aircraft data into a photocopy of the Aircraft Weighing Form
(Fig. 08-2).

(b)

Obtain and record the value “X” by measuring horizontally and parallel
to the aircraft center line, from a line stretched between main wheel
centers to a plumb line dropped from the Reference Point (RP).

record the value “Y” by measuring horizontally and parallel

to the aircraft center line, from a line stretched between main wheel
centers to a plumb line dropped from the center of nose wheel axle.

(d) Obtain and record the weights shown on each scale, deduct the tare

(if any) and calculate the net weights.

(e)

Determine and record the arms “A” and “B”.

(f)

Determine and record the moment for each weighting point using
following formula:

𝑀𝑜𝑚𝑒𝑛𝑡 = 𝑁𝑒𝑡 𝑤𝑒𝑖𝑔ℎ𝑡 𝑥 𝐴𝑟𝑚

(g) Calculate and record the Empty Weight / Moment by totaling

the appropriate columns. Calculate and record the Empty Weight CG
using formula given in the form.

(h) Calculate the correction for unusable fuel and record the Basic Empty

Weight / Moment. Calculate and record the Basic Empty Weight CG
using formula given in the form.

(i)

Compare the calculated values with the permitted limits given
in the POH (Chapter 6).

(j)

Record the new Basic Empty Weight / Moment into the Weight and
Balance Record of POH (Chapter 6).

CAUTION

WHEN PERMITTED TOLERANCE OF AIRCRAFT EMPTY
WEIGHT AND CG POSITION IS EXCEEDED, CONTACT
THE AIRCRAFT MANUFACTURER.

(4) After weighing:

(a) Ensure all air is removed from the fuel system.

(b) Inflate the nose and main landing gear tires to their prescribed

operating pressures (Chapter 12-10).

Effectivity:

ALL

22. 05. 2017

LEVELING
AND WEIGHING

Type:

Model:

Serial Number:

Reg. Number:

Date:

WT9 Dynamic LSA

Club

Measured:

X =………………… m (in)

Y =………………… m (in)

Calculated:

A = X + 1.975 m (77.76 in)

B = A

– Y

AIRCRAFT EMPTY WEIGHT / MOMENT AND CG AS WEIGHED

(Including operating fluids without unusable fuel)

Weigh

ing

point

Scale reading

(kg / lb)

- Tare

(kg / lb)

= Net weight

(kg / lb)

x Arm

(m / in)

= Moment

(kg.m / lb.in/100)

Main LH

A =

Main RH

A =

Nose

B =

Empty Weight / Moment

CG =

𝑪𝑮 =

𝑻𝒐𝒕𝒂𝒍 𝑴𝒐𝒎𝒆𝒏𝒕

𝑻𝒐𝒕𝒂𝒍 𝑾𝒆𝒊𝒈𝒉𝒕

BASIC EMPTY WEIGHT / MOMENT AND CG

(Including operating fluids with unusable fuel)

Unusable fuel

(Add to empty aircraft weight and moment)

5.0 kg /

11 lb

2.580 m /
101.57 in

12.90 kg.m /

11.17 lb.in/100

Basic Empty Weight / Moment

CG =

Fig. 08-2 Aircraft Weighing Form

WEIGHING

LEVELING

AND WEIGHING

Calculation method

Type of maintenance:

Line

Personnel qualification:

Independent certifying staff qualified in accordance

with Part-66 or higher.

Recommended tools, materials, persons and documentation:

ITEM

QUANTITY

Calculator

1 pc

Persons

Tab. 08-3 Recommended tools, materials, persons

and documentation

(1) Calculation:

(a) Record the date the item was installed on (or removed from)

the aircraft in the “Date“ column into the Weight and Balance Record
of POH (Chapter 6) (see Fig. 08-3).

(b)

Mark an “X“ into the “Item No. In” column if the equipment was
installed.

(c)

Mark an “X“ into the “Item No. Out ” column if the equipment was
removed.

(d) Record a brief description of the item or modification into

the “Description of Article or Modification“ column.

(e)

Record the item’s weight into the “Weight Change“ column’s “Weight“
column. “Added (+)“ column for installed items, “Removed (–)“ column
for removed items.

(f)

Record the item’s CG arm into the “Weight Change“ column’s “Arm“
column. “Added (+)“ column for installed items, “Removed (–)“ column
for removed items.

(g) Calculate the moment by multipl

ying the item’s weight and arm

together and enter the resulting value into the “Weight Change“
column’s “Moment“ column. “Added (+)“ column for installed items,
“Removed (–)“ column for removed items.

(h)

Calculate the aircraft’s new Basic Empty Weight and enter the value
into th

e “Basic Empty – Weight“ column. For added items, calculate

the aircraft’s new Basic Empty Weight by adding the item’s weight to
the aircraft’s previous Basic Empty Weight. For removed items,
calculate the aircraft’s new Basic Empty Weight by subtracting
the item’s weight from the aircraft’s previous Basic Empty Weight.

(i)

Calculate the aircraft’s new Basic Empty Moment and enter the value
into th

e “Basic Empty – Moment“ column. For added items, calculate

the aircraft’s new Basic Empty Moment by adding the item’s moment
to the aircraft’s previous Basic Empty Moment. For removed items,
calculate the aircraft’s new Basic Empty Moment by subtracting
the item’s moment from the aircraft’s previous Basic Empty Moment.