AD Number: AD/PR/35 Amdt 3
Subject: Propeller Hub Wall Cracking 12/2005 TX
Applicability: R334/4-82-F/13, R333/4-82-F/12,
R324/4-82-F/9, and R321/4-82-F/8 propellers with hub part number
(P/N) 660709201.

Note 1: These propeller hubs may be installed
on, but not limited to, CASA 212, Metro III, Merlin IVC, Metro
IIIC, Jetstream Series 3100 and 3200 aircraft.
Requirement: For CASA 212 aircraft:
1. Inspect for cracks in the rear wall of the propeller hub
assemblies in accordance with Dowty Service Bulletin (SB) 61-1119
Revision 4, and report all findings of cracking to Dowty
Propellers.
2. For hub assemblies P/N 660709201, other than zero time
assemblies, assembled in propellers held in storage, inspect in
accordance with paragraph 3 (accomplishment instructions) of Dowty
SB 61-1119 rev 4 or any later EASA approved revision.
4. For hub assemblies P/N 660709201, other than zero time
assemblies, held in storage, inspect in accordance with paragraph 3
(accomplishment instructions) of Dowty SB 61-1119 rev 4 or any
later EASA approved revision.
6. Remove from service any propeller or hub that does not satisfy
the acceptance criteria for further operation.
For Jetstream 3100 and 3200, Merlin IVC/Metro III, and aircraft,
Merlin IIIC
aircraft:
7. Inspect for cracks in the rear wall of the propeller hub
assemblies in accordance with Dowty SB 61-1124 Revision 1, SB 61-
1125 Revision 1 or SB 61-1126 Revision 1 as is applicable, and
report all findings of cracking to Dowty Propellers.
8. Remove from service any propeller or hub that does not satisfy
the acceptance criteria for further operation.
Note 2: CAA UK AD's G-2005-0027, 009-05-2002,
010-05-2002, and 011-05-2002.
and EASA Approval No 2005-6230 refers.
Note 3: CAA UK AD G-2005-0027 supersedes
003-11-2001. This Directive applies
to the R334/4-82-F13 propeller installed on CASA 212
aircraft.
Compliance: 1. Within 10 flight hours or 20 calender days from the
effective date of this Directive; or Within 300 flight hours or 300
flight cycles from the previous inspection whichever occurs
earlier, where the inspection has been previously accomplished
within the last 300 flight hours and 300 flight cycles prior to the
effective date of this Directive. Thereafter repeat the inspection
at intervals not to exceed 300 flight hours or 300 flight cycles
whichever occurs earlier.
2. Prior to installation on an aircraft.
3. Prior to installation on an aircraft.
4. Before further flight.
5. Remains unchanged as detailed in the amendment 2 of this
Directive as: For propellers with 950 hours time in service since
the effective date of the applicable referenced service bulletin;
prior to reaching 1000 hours propeller time in service. Thereafter,
at intervals not to exceed 1000 hours propeller time in service.
For propellers in excess of 950 hours time in service since the
effective date of the applicable reference service bulletin, within
50 hours from the hours accumulated at 26 March 2003 (the effective
date of amendment 2 of this directive). Thereafter, at intervals
not to exceed 1000 hours propeller time in service.
6. Before further flight.
This Amendment becomes effective on 26 September 2005.
Background: There has been a report of cracks
originating from around the threaded insert holes of the rear half
hub. In one instance this resulted in a complete separation from
the engine flange. This Directive requires the inspection of the
rear wall of the propeller for cracks.
Amendment 3 decreases the inspection interval for the propeller
installed on the CASA 212 aeroplane. This change has been prompted
by a hub separation on a CASA 212 aeroplane. Amendment 2 included
additional propeller models and a change to compliance
requirements. Amendment 1 of this Directive included the addition
of extra propeller models using the same hub part number. The
original issue of this Airworthiness Directive became effective on
28 November 2002.
Amendment 1 of this Airworthiness Directive became effective 20
March 2003.
Amendment 2 of this Airworthiness Directive became effective 26
March 2003.