AD 82-16-06

82-16-06 BELL HELICOPTER TEXTRON: Amendment 39-4422. Applies to Model 222 series helicopters certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To detect cracks and to prevent growth of voids and possible loss of main rotor spar doublers, accomplish the following:

a. Within the next 10 hours' time in service after the effective date of this AD,

(1) Inspect the main rotor center spar doubler scarf joint for doubler debond by visual inspection and by using a tapping tool in accordance with Bell Helicopter Textron Alert Service Bulletin No. 222-82-15, dated April 30, 1982, or FAA approved equivalent.

(2) Visually inspect the main rotor spar doublers for cracks between STA 82 and STA 102 (Operations Safety Notice No. OSN-222-82-3 refers to an inspection of this area).

(3) The scarf joint area to be inspected is shown in Figures I and III of Service Bulletin No. 222-82-15.

b. After the initial inspection, if no cracks or voids are detected, inspect the main rotor center spar doubler scarf joint area in accordance with paragraph a. above at intervals not to exceed 25 hours' time in service from the last inspection.

c. If voids or cracks are detected, accomplish the following:

(1) For voids that are within the limits of Part I, paragraph 4.a, of Service Bulletin No. 222-82-15, the doublers must be sealed and protected in accordance with the instructions of Part II of Service Bulletin No. 222-82-15, or FAA approved equivalent, within the next 25 hours' time in service.

(2) For voids that exceed the limits of Part I, paragraph 4.a, of Service Bulletin No. 222-82-15, but are within the limits of Part I, paragraphs 4.(b) and (c), the doublers must be sealed and protected in accordance with the instructions of Part II of Service Bulletin No. 222-82-15, or FAA approved equivalent, before the next flight, except that a special flight permit may be issued in accordance withFAR 21.197 to allow one flight of the helicopter to a location where the repair can be accomplished.

d. For blades that have been sealed and protected in accordance with the instructions of Part II of Service Bulletin No. 222-82-15 or FAA approved equivalent, accomplish the following:

(1) Inspect the tape daily for proper adhesion and condition.

(2) Replace tape having loose ends prior to flight.

(3) Remove the tape at intervals not to exceed 100 hours' time in service and inspect and repair the main rotor center spar doubler scarf joint in accordance with paragraphs a. and c. of this AD. If no voids or debond areas are found, reapply the protective tape as described in Part II, paragraph 2 of Service Bulletin No. 222-82-15, or FAA approved equivalent.

e. Replace main rotor blades that have voids or debond in excess of the limits of paragraph 4.b and paragraph 4.c of Service Bulletin No. 222-82-15 with serviceable blades.

f. Replace main rotor blades that have cracks in the spars or doublers with serviceable blades.

g. Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Division, Southwest Region, Federal Aviation Administration.

h. In accordance with FAR 21.197, flight is permitted to a base where the inspection required by this AD may be accomplished.

This amendment becomes effective July 30, 1982.