COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
DHC-2 (Beaver) Series Aeroplanes
AD/DHC-2/10
Amdt 8
Lift Strut and Lift Strut Attachment Fittings 3/88
Applicability: All models.
Requirement: 1. Carry out a fluorescent penetrant inspection for cracking of the upper attachment fitting of each lift strut at the times specified in compliance table, item (1).
2. Replace the complete lift struts with new struts at the lives specified in compliance table, Item (1).
Note: The attention of operators is also drawn to de Havilland Aircraft Company of Canada SB No 2/43.
3. Replace the wing/strut attachment fittings and the fuselage/strut attachment fittings with new fittings at the lives specified in compliance table, Items (2) and (3).
4. Check for looseness of the lift strut attachment bolts in their holes, and for any evidence of misalignment of the strut or of the wing and fuselage strut attachment fittings at the times specified in compliance table, Item (4). Any misalignment or looseness of fit shall be corrected before further flight.
5. Replace strut upper and lower attachment bolts with new bolts, at the times specified in compliance table, Item (5).
Compliance: Retirement Lives and Inspections:
Columns headed “A” apply to components which have at any time been fitted to an aircraft while engaged in agricultural operations.
Columns headed “B” apply to components which have never been fitted to an aircraft while engaged in agricultural operations.
Inspection intervals and Retirement Lives are in hours time in service and for modified struts are in hours time in service of the oldest component of the strut.
Item Component | Part Number | Component Inspection Times | Component Retirement Life | ||
|
| A | B | A | B |
1. Lift Strut | C2W1103A | Initial 2100 | Not required | 2480 hours | 20000 hours |
| C2W1104A | hours | by this AD |
|
|
Lift Struts | RU C2W1103A | Repeat after |
|
|
|
modified by | RL C2W1103A | 200 hours | |||
Mod. S.O.O. | RLU C2W1103A |
| |||
2040 and Kit | RU C2W1104A |
| |||
C2W1113 | RL C2W1104A |
| |||
| RLU C2W1104A |
| |||
Lift Strut | C2W1115-1 | Not required | Not required | 25000 hours | Not required |
| C2W1115-2 | by this AD | by this AD |
| by this AD |
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
| All other numbers | NOT PERMITTED IN OPERATION | |||
2. Wing/Strut attachment fitting | C2W781 C2W782 | Not required by this AD | Not required by this AD | 30000 hours | Not required by this AD |
3. Fuselage/Strut attachment fitting | C2FS419A C2FS5475A C2FS5487A | Not required by this AD | Not required by this AD | 30000 hours | Not required by this AD |
4. See para 4. |
| Each time a new lift strut or attachment fitting is fitted and subsequently at intervals not exceeding 2500 hours | Not applicable | ||
5. See para 5. | AN180-26 C2W497 | Not applicable | Each time a new lift strut or attachment fitting is fitted | ||
| AN180-26 C2W497 used with C2W1115-1/-2 fittings | Not applicable | 5000 hours or 60000 flights which ever occurs first | Each time a new lift strut or attachment is fitted. | |
Background: This directive promulgates retirement lives and inspections to prevent/detect fatigue cracking in the lift strut and its attachments. These requirements are based on fatigue testing and analysis carried out by the manufacturer following a number of in-flight failures.
Amendment 8 draws the attention of operators to DHC SB 2/43, which warns against using the lift strut for mooring the aircraft, attachment of external loads, etc. Such usage may significantly reduce the fatigue life of the lift strut assembly.