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63-07-02: 63-07-02 MACCHI: Amdt. 548 Part 507 Federal Register April 2, 1963. Applies to All Models AL-60 (formerly LASA 60) and AL-60B Aircraft. Compliance required as indicated. As a result of several cases of engine exhaust manifold failures, accomplish the following within the next 25 hours' time in service after the effective date of this AD, and thereafter within every 25 hours time in service from the last inspection. (a) Inspect the turbo inlet assembly manifold P/N 629-250 for cracks in the weld area between the two exhaust pipes. (b) If cracks are found, replace or repair the part before further flight. Repair by arc welding a stainless steel plate reinforcement over the area in accordance with Aeronautical Macchi Service Bulletin No. 1, or FAA approved equivalent repair. This directive effective May 2, 1963.
63-06-02: 63-06-02 BELLANCA: Amdt. 543 Part 507 Federal Register March 19, 1963. Applies to Bellanca 14-13 Series and Downer 14-19 and 14-19-2 Aircraft. Compliance required as indicated. As a result of instances of elongation of the control cable attachment bolt hole in the rudder bellcrank, P/N 9817, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, unless accomplished within the last 75 hours' time in service, and thereafter within 100 hours' time in service from the last inspection, remove the left and right rudder bellcranks, P/N 9817, located at the left and right ends of the rudder torque tube. (This may be accomplished by working from inside the cabin and through the inspection hole in the bottom cabin cowl.) Inspect the control cable attachment bolt hole in the rudder bellcrank. (b) If the bolt hole is elongated beyond maximum diameter of 0.210 inch, replace the rudder bellcrank with a new rudder bellcrank of the same part number (P/N 9817), or P/N 9817 modified in accordance with Downer EAI No. 93021, or FAA approved equivalent prior to further flight. NOTE: Modified replacement parts for the Models 14-13, 14-19 and 14-19-2, Serial Numbers 4001 through 4088, are stamped "9817-DEAI-93021". Modified replacement parts for the Model 14-19-2, Serial Numbers 4089 through 4105, are stamped "9817-E EAI 93021". Parts numbered 9817-E are made of steel and may be modified in accordance with Downer EAI-93021 or an FAA approved equivalent. (c) The 100 hour repetitive inspections of the bellcrank hole which are required by (a) may be discontinued when rudder bellcrank P/N 9817 modified in accordance with Downer EAI No. 93021 or FAA approved equivalent is installed. This supersedes AD 62-19-01. This directive effective March 19, 1963.
65-21-02: 65-21-02\tBOEING: Amdt. 39-130 Part 39 Federal Register September 2, 1965. Applies to Models 707B, 707C, and 720B Series Airplanes.\n \n\tCompliance required within the next 1,200 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tThe forward thrust reverser indicating light switch striker bracket may be distorted by reverser actuation impact loads resulting in false indications of reverser operation. To correct this condition, accomplish the following:\n\n\t(a)\tReplace existing sheet metal striker brackets, P/N 66-14396-1, with cast striker bracket, P/N 69-31381-1 or equivalent in accordance with Boeing Service Bulletin 2039 dated December 21, 1964 or later FAA-approved revision. \n\n\t(b)\tApproval of any equivalent means shall be processed through the Aircraft Engineering Division, FAA Western Region, Los Angeles, California. \n\n\tNOTE. - Western Airlines EA 720-20165, dated September 6, 1964, is an equivalent that has been approved by the Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective October 2, 1965.
2018-08-02: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 turbofan engines. This AD requires initial and repetitive inspections of the intermediate-pressure compressor (IPC) stage 1 rotor blades, IPC stage 2 rotor blades, and IPC shaft stage 2 dovetail posts, and removing any cracked parts from service. This AD was prompted by IPC blade separations resulting in engine failures. We are issuing this AD to address the unsafe condition on these products.
63-05-03: 63-05-03 SNOW: Amdt. 541 Part 507 Federal Register March 2, 1963. Applies to Model S-2 Aircraft Serial Numbers 1003 Through 1162. Compliance required as indicated. (a) Within 10 hours' time in service after the effective date of this AD, inspect the wing main spar upper and lower spar web flange for cracks in the vicinity of the wing-fuselage attach points (approximately wing Station 19), using at least a 10-power glass. (b) If cracks are found, repair prior to further flight in accordance with Snow Service Letter No. 23 or FAA Engineering and Manufacturing Branch approved equivalent. (c) If no cracks are found, repeat the inspection specified in (a) at intervals not to exceed 25 hours' time in service from the previous inspection. (d) The repetitive inspection required by (c) may be discontinued when the modification set forth in Snow Service Letter No. 23 or an FAA Engineering and Manufacturing Branch approved equivalent is incorporated. This directive effective March 8, 1963.
47-21-23: 47-21-23 REPUBLIC: (Was Service Note 3 of AD-769-2.) Applies to Model RC-3 Aircraft with Engine Serial Numbers 23001 to 24083, Inclusive. Compliance required before the next flight and after 5 hours of operation following each installation of fan. Inspect the engine cooling fan capscrews for tightness. If tab locks are installed ascertain whether the locks are still in place. If the capscrews or the locks have loosened remove the capscrews, fan and pulley sheave. Clean and inspect parts for wear. Reassemble carefully using P/N 17778 drilled head capscrews with plain washers. Torque to 20 foot-pounds, operate engine up to 1,500 r.p.m. for 5 minutes, retorque and safety with 0.041-inch stainless steel wire. Visually inspect locking wire and capscrews after 5 hours of operation. Reassemble in this manner every time the fan is removed. Obtain the new capscrews, washers, and wire from your Seabee distributor or the engine manufacturer. (Franklin Service Bulletin No. 57 dated June 9, 1947, which supersedes Bulletin No. 50 covers this same subject.)
2005-13-26: The FAA is adopting a new airworthiness directive (AD) for certain Airbus models, as specified above. This AD requires installing safety signs on all passenger/crew doors, emergency exit doors, and cargo compartment doors. This AD is prompted by a report of injuries occurring on in-service airplanes when crewmembers forcibly initiated opening of passenger/crew doors against residual pressure causing the doors to rapidly open. We are issuing this AD to ensure that crewmembers are informed of the risks associated with forcibly opening passenger/crew, emergency exit, and cargo doors before an airplane is fully depressurized, which will prevent injury to crewmembers, and subsequent damage to the airplane caused by the rapid opening of the door.
2018-08-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC225LP helicopters. This AD requires inspecting each main rotor rotating swashplate (swashplate) control rod attachment yoke (yoke). This AD is prompted by a finding that the yoke is susceptible to cracking. The actions of this AD are intended to address an unsafe condition on these products.
2018-07-18: We are superseding Airworthiness Directive (AD) 2015-19-12, which applied to certain The Boeing Company Model 767 airplanes. AD 2015-19-12 required a general visual inspection of certain lap splices for missing fasteners, and all applicable related investigative and corrective actions. This AD retains the actions required by AD 2015-19- 12 and revises the applicability by adding airplanes. This AD was prompted by reports indicating that certain fasteners were not installed in a certain stringer lap splice on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
62-26-01: 62-26-01 DOUGLAS: Amdt. 517 Part 507 Federal Register December 8, 1962. Applies to All C54-DC Series and DC-4 Aircraft Equipped With Pratt & Whitney Aircraft Twin Wasp Series and R-2000 Series Engines and Hamilton Standard 23E50/6507-0 Propellers. \n\n\tCompliance required within the next 200 hours' time in service after the effective date of this AD. \n\n\tRecent resurveys of 23E50/6507-0 propeller blade vibration stresses have shown that vibration stresses in excess of allowable limits for continuous safe operation occur over a wider range of engine operating speeds than was determined by previous surveys. To prevent possible blade failures due to exceeding allowable stress limits within this speed range, the following is required: \n\n\t(a)\tRemove the existing placard covering the 1,600 to 1,700 r.p.m. range and install a new placard in full view of the pilot to read: \n\n\t\t"During flight, avoid operation between 1,550 and 1,750 r.p.m. During ground running, avoid operation between 1,550 and 1,800 r.p.m. when the blades are off the low pitch stops." \n\n\t(b)\tMark the tachometers with a red arc over the 1,550 and 1,750 r.p.m. range. \n\n\t(c)\tRevise the operating limitations section of the FAA approved Airplane Flight Manual to incorporate the limitations in (a) and (b). \n\n\tNOTE: The other restricted operating speed range between 2,310 and 2,510 r.p.m. required by AD 56-20-05 still remains in effect. For the purpose of this directive, a single placard reading: "During flight, avoid operation between 1,550 and 1,750 r.p.m. and between 2,310 and 2,510 r.p.m.", in the first sentence, may be installed if desired. Similar wording may be used for the FAA approved Airplane Flight Manual. \n\n\tThis directive effective January 8, 1963.