Remarks: The compliance of this AD must be recorded in Aircraft Logbook, where applicable the requirements of this AD must be integrated into Aircraft Technical Documentation. Address inquiries concerning this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport, 160 08 Prague 6, Czech Republic, tel: 420 2 33320922, fax: 420 2 20562270.

This Airworthiness Directive (AD) applies to ATR 42 models 200, 300 and 320 aircraft.

AD 92-044-046(B) was issued further to damage discovered during fatigue tests.

On some aircraft, embodiment of modification 3184 led to a bore oversizing which must be corrected by the implementation of ATR Service Bulletin (SB) 42-52-0058 Revision 2.

This AD replaces AD 92-044-046(B), to which requirements are recovered, and, in its section "COMPLIANCE 1" it mandates the embodiment of SB 42-52-0058 Revision 2.

The following measures are made mandatory from the effective date of this AD.

1. Cargo door outer skin

For ATR 42 models 200, 300 and 320 aircraft fitted with a cargo compartment door on which modification 3191 has not been embodied, in order to prevent the initiation and the growth of cracks in the cargo compartment door outer skin at the hinge fitting:

- Before the aircraft has accumulated 27,000 flights, applies SB ATR 42-52-0058 Revision 2.

2. Fuselage - main frames (lower part)

For ATR 42 models 200, 300 and 320 aircraft, serial numbers: 005 to 016, 018 to 030, 032 to 036, 38, 40, 42, 43, 48 to 62, 64 to 90, 92 to 94 and 96 to 228 inclusive, in order to check that the positioning holes of the lower part of the main frames have been property blanked off with rivets, during production:

- Before the aircraft has accumulated 36,000 flights, check that the positioning holes of the lower part of the main frames have been properly blanked off, and, if necessary, blank off the holes according to the instructions in SB ATR 42-53-0070.

3. Fuselage-typical frames and upper part of main frames

Applies to ATR 42 models 200, 300 and 320 aircraft, serial numbers 003 to 208 inclusive, in order to check that the positioning holes of the typical frames and of the upper part of the main frames have been properly blanked off with rivets, during production:

- Before the aircraft has accumulated 36,000 flights, check that the positioning holes of the standard typical frames and of the upper part of the main frames have been properly blanked off, and, if necessary, blank off the holes according to the instructions in SB ATR 42-53-0076.

4. Forward LH passenger door

For ATR 42-300 aircraft serial numbers : 20, 21, 32, 34, 42, 57, 67, 68, and 114 inclusive.

A. In order to prevent fatigue failure of the stops of the forward LH plug-type passenger door:

- Before the aircraft has logged 10,000 flights, inspect wear of the stops of the forward LH passenger door, and if necessary, replace the stops according to the instructions in SB ATR 42-52-0052.

B. In order to prevent the initiation and the growth of cracks in the skin of the upper frame and in the stops of the forward LH passenger door:

- Before the aircraft has accumulated 18,000 flights, replace the stops and modify the frame of the forward LH passenger door according to the instructions in SB ATR 42-52-0059.

SB ATR 42-52-0058 Revision 2
SB ATR 42-53-0070
SB ATR 42-53-0076
SB ATR 42-52-0052
SB ATR 42-52-0059
Any further approved revision of these SB is acceptable.

This AD replaces AD 92-044-046(B) which is cancelled by its Revision 3.

EFFECTIVE DATE: AUGUST 05, 2000