Pilatus P3 Wing Bolt AD
Swiss Confederation
Airworthiness Directive (AD) FOCAAD
HB-2016-007
Effective Date 03 October 2016 Pilatus – P3
FOCA TCITCDS No: None
Issue Date: 19 September 2016
ATA Chapter: ATA 57- Wings
Subject: Fuselage — Main Frame 3 — Wing to Fuselage Attachment Bolts — Inspection

Manufacturer(s): Pilatus Flugzeugwerke AG
Applicability: Model P3-03 and P3-05 aircraft all Serial Numbers (SIN).
Reason:
This Airworthiness Directive (AD) is prompted due to a report of corrosion of a wing to fuselage attachment bolt The corrosion was detected during an inspection of the fleet leader aircraft. The corrosion of the wing to fuselage attachment bolt can occur when water is entering into the aircraft structure: for example with an open canopy in raining conditions.
Such a condition, if left uncorrected, could lead to stress corrosion cracking in the affected bolts and will prejudice the structural integrity of the aircraft.
In order to correct and control the situation this AD requires a one-time inspection of the wing to fuselage attachment bolts for corrosion and cracking and if corrosion and/or cracks are found, replace the affected wing to fuselage attachment bolts with new bolts.
Required Action(s) and Compliance Required as indicated below, unless already accomplished:
Time(s): (1) Within the next 50 Flight Hours (FH) or at the next annual inspection,
whichever occurs first after the effective date of this AD, remove the wing to fuselage attachment bolts as described in “Technisches Reglement der Fliegertruppe 56.199d” (the technical description and operating instructions of the Swiss Air Force) and perform a visual inspection for corrosion and a dye penetrant inspection for cracks. No corrosion and/or cracks are permitted.
Note I: For the inspection of the attachment bolts it is not necessary to remove the wings from the fuselage.

2014 was not a good year for the P3.

Three Aircraft came to grief in Landing Accidents in 2014. These accidents could have been avoidable
With proper System Knowledge and Maintenance.

An electrical failure does not have to end in a gear up landing.
One needs to be familiar with the manual gear extension and the manual gear indicator
Close to the pilot’s left Foot.

To properly maintain the Landing Gear system, the Gear Motor and the Actuators MUST
be removed, disassembled, cleaned, inspected and lubricated.
(200hr per Maintenance Manual) I recommend this be done every 5-6 Years.

THERE ARE NO EXTERNAL LUBRICATION POINTS FOR THE ACTUATORS

A-865 landed with the Towbar attached. Collapsed the nose gear, damage to the Engine,
Propeller, Cowling, Nose Gear, Actuator and Airframe.

A-821 Landed Gear up after an Electrical failure. The resulting fire, due to the fuel drains breaking, may have totaled this aircraft.

A-811 found the same fate as A-821

For Help and Information contact me at 704-562-3751
Norbert Steinwedel