76-06-10 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2561. Applies to Model DH-104 "Dove" airplanes certificated in all categories which have not been modified in accordance with Dove Modification 1728.
Compliance is required as indicated.
To detect cracks in the nose landing gear inner casting, which could result in failure of the casing and collapse of the nose gear, accomplish the following:
(a) For inner casings (P/N's 4UN.443ND and 4UN.555A) which have not been modified in accordance with either Dove Modification 847 or Modification 1008, comply with the following:
(1) Locate and identify the inner casings in accordance with the instructions contained in paragraph 3.1 of Hawker Siddeley Aviation Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973.
(2) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter atintervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973, or an FAA approved equivalent.
(3) If any cracks are found during an inspection required by paragraph (a)(2) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (a)(2) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet Series CT(104), No 232, Issue 1, dated September 17, 1973, or an FAA-approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection.
(b) For inner casings (P/N's 14UN.467A/ND and 14UN.469A/ND) which have been modified in accordance with either Modification 847 or Modification 1008, comply with the following:
(1) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casings for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent.
(2) If any cracks are found during an inspection required by paragraph (b)(1) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (b)(1) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection.
This amendment becomes effective on April 8, 1976.