Pilatus PC-12/47E MSN-1001-UP, Руководство по обслуживанию

Страница: 104 / 715

− Spare parts
− Assessment as defined in Para 5.3.
5.3 Deviation from Type Design
Deviations from the Type Design in critical locations could make the aircraft ineligible for this life extension.
Therefore:
(a) all concessions,
(b) all repairs, alterations and modifications,
(c) all STC installations
must be assessed to find out if the aircraft will be eligible for this life extension. The owner/operator is responsible
to organize these assessments well in advance of the first SSID inspection. There must be a clear statement for the
specific aircraft MSN available which states that the aircraft with (a), (b) and (c) is eligible for this life extension.
The assessments can be done as follows for:
(a) Concessions - Only Pilatus can do this assessment. Pilatus shall be approached at least 5 months in
advance.
(b) Repairs, alterations and modifications - Any Authority approved Design Organization or equivalent can do
this assessment.
(c) For the aircraft modifications of the STC any Authority approved Design Organization or equivalent can do
this assessment. For the part of the STC itself the STC holder(s) only must do this assessment.
On request, Pilatus can do the assessments for items (b) and the first part of (c) in addition to (a) above, provided
sufficient information is given.
5.4 Supplemental Corrosion Prevention and Control Program (CPCP)
The maximum corrosion level to be maintained is Corrosion Level 1. Refer to AMM 12-B-20-40-00-00A-901A-A for
Corrosion Control Maintenance Practices.
The supplemental CPCP inspection tasks are identified in the column where a calendar time interval is given. The
following additional threshold inspection requirement is applicable for all those CPCP inspection tasks:
− the CPCP inspection task must be accomplished 6 years after Service Bulletin 04-009 has been accomplished
− the CPCP inspection task must not be accomplished before the aircraft reaches 25,000 flying hours or 30,000
landings.
5.5 Damage Tolerance Evaluation
The entire aircraft structure is subject to Damage Tolerance Evaluation when modified or repaired, except for life
limited components as listed in Table 3, which remain as safe-life.
6 Inspection Program
Note
The repeated intervals specified in Table 5 apply AFTER the threshold limitation for the inspection has been
reached.
PC-12/47E AMM Doc No 02300, ISSUE 01 REVISION 26 MSN 545, 1001-1719,
1721-1999
12-B-AM-00-00-00-I
UNCLASSIFIED
Effectivity: All 12-B-04-00-00-00A-000A-A
UNCLASSIFIED 2021-12-04 Page 11