76-08-03 SCOTTISH AVIATION LTD. (Beagle Aircraft Ltd.): Amendment 39-2580. Applies to Model B-121 "PUP," Series 1, 2, and 3 airplanes, certificated in all categories.
Compliance is required as indicated.
To prevent a failure of the flap actuating lever and the consequent loss of airplane control, accomplish the following:
(a) For airplanes with less than 400 hours total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD or before the accumulation of 400 hours total time in service, whichever occurs later, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service and, thereafter, at intervals not to exceed 100 hours time in service from the last inspection.
(b) For airplanes with 400 or more hours total time in service but less than 800 hours total time in serviceon the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service, unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection.
(c) For airplanes with 800 or more total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service, after the effective date of this AD unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection.
(d) Comply with the following:
(1) Remove wing root fillets to gain access to the flap actuating lever assemblies.
(2) Remove split pins,nuts, washers and bolts that attach the flap actuating rods to the port and starboard flap actuating lever assemblies.
(3) Inspect the flap actuating lever assemblies. P/N's BE.45.10181/9 (port) and BE.45.10181/15 (starboard) for cracks, using a dye-penetrant method, or an FAA-approved equivalent means.
(NOTE: During the inspections conducted in accordance with paragraph (d)(3) of this AD particular attention should be directed to the actuating rod attachment boss).
(4) If a cracks is found in any part of the flap actuating lever assembly as a result of any inspection required by this AD, before further flight, replace the cracked part with a new part of the same part number, or an FAA-approved equivalent, and continue to inspect the flap actuating lever assemblies in accordance with paragraph (d) of this AD at the intervals established in paragraph (a), (b) or (c) of this AD, as applicable.
(5) Re-attach the flap actuating rods to the flap actuating lever assemblies using new split pins.
(6) Re-rig flaps.
(7) Re-install wing root fillets.
(8) Perform a functional check of the flap operation.
(Scottish Aviation Ltd. Mandatory Service Bulletin No. B-121/61, Issue 2 dated April 17, 1975, and Beagle "PUP" Series Service Manual No. 121/02/3.68 pertain to this subject).
This amendment becomes effective April 29, 1976.