63-27-05 VICKERS: Amdt. 39-864. Amendment 658 (28 F.R. 13931) as amended by Amendment 39-126 (30 F.R. 11029) is further amended by Amendment 39-864. Applies to Viscount Models 744, 745D and 810 Series Airplanes.
Compliance required as indicated.
Fatigue failures have occurred in the fuselage leading edge frame and associated structure. To preclude further failures accomplish the following:
(a) Fuselage frame:
(1) Within 200 landings after the effective date of this AD on aircraft which have attained 8,000 landings, unless already accomplished within the preceding 500 landings, conduct initial visual inspection for cracks in accordance with the applicable Vickers Preliminary Technical Leaflet referenced herein. Accomplish repair in (2) or (3) as applicable, before further flight if the inspection reveals any of the following:
(i) Cracks in the frame joint pressing or in the floor beam or in the floor beam joint plates - either in the flanges or running towards the flanges or in the heel line of the flanges.
(ii) Any single crack not defined in (a)(1)(i), greater in length than 1.5 inches.
(iii) Two or more cracks not defined in (a)(1)(i).
(2) Model 744 and Model 745D cracked frame joint pressings must be repaired/reinforced per Modification D.3059, or any alternative scheme which has been approved by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area.
(3) Model 810 Series aircraft. Figure 2, PTL 106 Issue 3 of later ARB- approved issue illustrates a temporary repair scheme, applicable only where unacceptable cracks, confined to the areas indicated in Figure 1 of the reference PTL are present. Unacceptable cracks, outside those areas must be repaired/reinforced in accordance with Mod. FG.1928 part (b). Any alternative scheme which has been approved by the Chief Aircraft Certification Division, Europe, Africa and Middle East Area may be used.
(4) Subsequent to the initial inspection, per (1), aircraft are considered serviceable if the following repetitive inspections of the frame structure are accomplished at the periods indicated.
(i) Within every 700 landings:
(a) When no cracks are present.
(b) Where any acceptable single crack not greater in length than 1.5 inches is present.
(c) When VTO/700/169 or any other temporary repair scheme approved by the aircraft manufacturer or by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area, has been incorporated.
(ii) At routine overhaul periods not later than every 12,000 flying hours: After reinforcement of the frame structure by incorporation of Mod. D3059 (for 744 and 745D) or Mod. FG.1928 part (b) (for 810), or any alternative reinforcement approved by the aircraft manufacturer, or by the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area. (Continental Air Lines Repair/Reinforcing Scheme 753-43079 has been approvedby the aircraft manufacturer for aircraft repaired/reinforced prior to the effective date of this AD.)
(b) Inspection of top spigot and socket fittings and attachment bolts:
(1) From effective date of this AD within 1,000 landings on aircraft which have already attained 12,000 landings or within 2,000 landings on aircraft which have accumulated between 8,000 and 12,000 landings, unless already accomplished, conduct initial visual in situ inspection of the spigot and socket fittings for cracks and the associated attachment bolts for damage, in accordance with the applicable PTL referenced herein. Cracked fittings or damaged bolts must be replaced before further flight. Initial inspection of replacement fittings with new original type fittings need not be conducted until these fittings have accumulated 8,000 landings.
(2) Subsequent to the initial inspection in (b)(1) conduct repetitive inspections within every 2,000 landings until Mod. D3072 Part (a) or part (d) (for744 and 745D) Mod. FG 1928 Part (a) or Part (d) (for 810) is embodied. Inspect modified fittings at routine overhaul periods not later than every 12,000 hours' time in service.
(3) Modified fittings shall be used in pairs. Single modified fittings shall not be used to replace unserviceable unmodified items.
(4) Modification D.3129 (for 744 and 745D) Modification FG. 2011 (for 810) introduce oversize top fitting attachment bolts. Strict compliance with paragraph B(2)(i), (ii), or (iii) of the applicable referenced PTL is required should operators incorporate these oversize bolts on a voluntary basis.
(c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Europe, Africa and Middle East Area, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for that type of airplane.
(British Aircraft Corporation (Operating) Ltd. PTL 242 Issue 3 or later ARB-approved issue (700 Series) and Modifications D.3059, D.3072 and D.3129 (for 744 and 745D airplanes) PTL 106 Issue 3 or later ARB-approved issue (800/810 Series) and Modifications FG. 1928 and FG. 2011 (for 810 Series airplanes) cover this subject.)
This directive effective January 21, 1964.
Revised August 26, 1965.
Revised October 30, 1969.