MAINTENANCE MANUAL
SAVANNAH S
Doc. No.:
MM-SVNH-EN
Revision:
07
Rev. Date:
07/11/2022
Proj. Ref.:
SVNH S
A/C:
Savannah S
Applies to Generic Serial Number:
yy-mm-54-xxxx
Page:
27/132
DOC
FMM00
1.17. Airworthiness Limitations
The airworthiness limitations
Chapter 1.17
is issued by the ICP Manufacturer and approved by the
Aviation Authority (i.e. EASA or FAA) in case of Certified Aircraft only, in accordance to the criterion
given in the
Part-21
, requirement
21A.31(a)3.
and
FAR 33.4.
.
There are no particular airworthiness limitations of the aircraft described within the present
Maintenance Manual, except the ones reported in the dedicated section of the approved Aircraft
Flight Manual (POH-SVNH). If the present Maintenance Manual (MM-SVNH) is not respected,
followed and applied in any descriptions, timing (included tolerances) and practices, the continuous
airworthiness of the aircraft is considered not ensured. The consequence is the not operability of the
aircraft. Exception can be made in case of ferry flight to the maintenance workshop, with the
application of certain operational limitations and operator authorization that can be defined case by
case in agreement with the ICP Manufacturer and the Aviation Authority in case of Certified Aircraft.
1.18. Maintenance interval tolerances
The maintenance work can be executed with a tolerance of +/-5 Operating Hours or +/-1 month
(where applicable), which one is shorter, in respect of the schedule. Regarding items subject of time
limits, the tolerance is 5% of the time or 6 month, which one is minor.
1.19. Aircraft lifting
There are many possibility to lift up the aircraft; the only important concept is to distribute the
pressure around the touching point and to press only in structurally rigid areas. Follows some
examples:
-
First point: fuselage rear cone lower skin, with a minimum distribution between two
consecutive bulkhead in the total fuselage width; second point: fuselage cabin area lower
skin, with a minimum distribution between the two lower longitudinal stringers and entire width
of nose; third point: if required below the wing skin to balance the rotation.
-
First point: left wing lower skin, minimum distribution between the two last ribs plus front and
rear spar; second point: the symmetrical on right wing; third point: the tail skid or eventually
the nose, distributing the pressure, to balance the rotation.
-
First point: attachments of the main landing gear; second point: nose of the fuselage, with a
minimum distribution between the two lower longitudinal stringers in the firewall area (paying
attention to fuel pipe).
-
First point: main landing gear wheels; second point: nose landing gear wheel.
-
In case of wing disassembled: four attachments of the wing, in the cabin frame and eventually
balance the rotation with a tail skid point.
-
If aircraft equipped with hooks on the cabin frame: first points from the hooks; second point
from the rear fuselage, with a large belt/strip (preventing damages) passed around the
fuselage tail cone, in front of the stabilizer area.
