Document ID: chunk:federal_register_of_legislation:F2006B08801:body:0:p4
Version: federal_register_of_legislation:F2006B08801
Segment Type: other
Provision Reference: 
Character Range: 8076–10903

areas to be inspected and thoroughly clean the bare surfaces.

(b)     With the aid of a lens of not less than a x8 magnification, inspect the outer wing and centre section upper surface attachment angle doublers for cracking along the radius of the bent up flange. Restore the protective finish when the inspection has been completed.

(c)     Replace cracked doublers with new items before further flight.

             7.    Rivet Inspection:

(a)     Inspect for looseness of the rivets securing lower wing skin of the centre section to the stringers located between the front and rear spars inboard of the attachment angles at Station 142 and over the area covered by the internal skin doubler. The inspection shall be carried out both visually and by lightly tapping the rivet heads with a wooden block.

(b)     If any rivets are found loose or broken they shall be replaced and a careful internal and external inspection for corrosion shall be carried out in the area before further flight.

           Compliance: For Paragraph 1: Before 16,000 hours time in service since installation of the light gauge doublers and attach angles.

           For Paragraph 2(a): At the next removal of the outer wing panel. For Paragraph 2(b):
(a)     For aircraft already reworked in accordance with para. 2(b) or having original centre section lower surface skins NOT fitted with steel doubler plates at the centre and/or front spar positions - before 36,000 hours time in service since new or since last rework and thereafter at intervals not exceeding 36,000 hours time in service.

(b)     For aircraft having centre section lower surface skins fitted with steel doubler plates at the centre spar and/or front spar positions - Forthwith.

(c)     As specified in paragraphs 5(d) and 5(e). For Paragraph 3(a): At intervals not exceeding 500 hours time in service or six months whichever occurs first.

           For Paragraph 3(b): At intervals not exceeding 2000 hours time in service or two years whichever occurs first.

           For Paragraph 4(a) and 4(b): Initially within 8000 hours time in service since new or since rework in accordance with para. 1 of this Order and thereafter at intervals not exceeding 2500 hours time in service except that if the wing has not exceeded 16000 hours time in service since rework in accordance with para. 1 every second inspection may be made "in situ" by an X-ray technique approved by the Secretary.

           For Paragraphs 5(a) and 5(b):

(a)     For aircraft having centre section lower surface skins fitted with steel doubler plates at the front and/or centre spar positions - within 1500 hours time in service since the last visual or X-ray inspection, for cracking at the inspection holes forward or aft of the front and centre spars.

                   (b)     Aircraft