82-22-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4478. Applies to Model AS332C/AS332L series helicopters certificated in all categories that are equipped with main rotor spindles P/N 330A31.1122.09 and .10.
Compliance is required as indicated.
To detect fretting corrosion and to prevent possible cracking of the main rotor head spindle yoke lugs, accomplish the following:
(a) Prior to the first flight of each day following the effective date of the AD, accomplish a visual inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(a) or equivalent approved by the Manager, FAA, Europe, Africa and Middle East office.
(b) Within the next 25 hours' time in service following the effective date of this AD, unless already accomplished, check the torque of the flap hinge pin nut in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(a) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office. Thereafter, at intervals not to exceed 25 hours' time in service since the last inspection, accomplish the inspection in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(1)(c) or an equivalent approved by the Manager, FAA, Europe, Africa and Middle East office.
(c) Within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' total time in service, inspect the spindle yoke lug in accordance with Aerospatiale AS332 Service Bulletin No. 05.02, paragraph 1C(2)(b) or an equivalent inspection approved by the Manager, FAA, Europe, Africa and Middle East office.
NOTE: (1) For spindles having 90 hours' or more time in service, accomplish the inspection of paragraph (c) of this AD within 10 hours' additional time in service following the effective date of this AD.
(2) For spindles having less than 90 hours' time in service, accomplish the inspection of paragraph (c) of this AD prior to attaining 100 hours' total time in service.
(d) In addition to the inspection instructions noted in paragraphs (a), (b) and (c) of this AD, the service life limit of the main rotor hub spindles, PN 330A31.1112.09 and .10 is effectively reduced from 1500 hours' to 300 hours' total time in service. For spindles with more than 300 hours' time in service on the effective date of this AD, remove from service prior to attaining an additional 25 hours' time in service.
(e) The collective pitch limit in level flight specified in the Rotorcraft Flight Manual, Section 2-1, paragraph 15, is reduced from 16.5 degrees to 16 degrees or less and the airspeed is limited to IAS = 131 KT (243 KM/HR).
The following placard must be installed adjacent to the pilot and copilot airspeed indicators. The placard must be within sight of and readable by the pilot and copilot.
EXCEPT IN CASE OF EMERGENCY, COLLECTIVE
PITCH IN LEVEL FLIGHT IS LIMITED TO 16 DEGREES
AND THE AIRSPEED IS NOT TO EXCEED
THE FOLLOWING LIMITS:
HP
A/S KTS IAS
SL
131
1000
128
2000
126
3000
124
4000
120
5000
116
7000
108
9000
96
11000
85
13000
71
This amendment becomes effective November 11, 1982.