Results
47-21-18: 47-21-18 REPUBLIC: (Was Mandatory Note 8 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 Through 303, 305 Through 367, 369 Through 398, 400 Through 445, 448 and 449, 451 Through 454, 456 Through 459, 461 Through 466, 469 and 470, 472, 474, 479 and 482. Compliance required prior to next flight. Prior to each flight until reinforced support bracket is installed, inspect mixture control support at carburetor air filter housing for evidence of cracking. Support bracket must be installed not later than the next 25 hours of operation after July 1, 1947, and in no case later than August 1, 1947. (Republic Seabee Service Bulletin No. 11 dated March 10, 1947, covers this same subject.)
2005-14-11: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller, Inc., McCauley Propeller Systems, and Sensenich Propeller Manufacturing Company, Inc. propellers. This AD requires maintenance actions amounting to an overhaul of the affected propellers. This AD results from the investigation of a failed propeller blade and subsequent inspections of various propeller models returned to service by Southern California Propeller Service, of Inglewood, CA. We are issuing this AD to prevent blade failure that could result in separation of a propeller blade and loss of control of the airplane.
47-35-01: 47-35-01\tSIKORSKY: (Was Mandatory Note 1 of AD-7L-1.) Applies to Model R4-B Helicopter Serial Numbers 43-46500 to 43-46502 and 43-46504 to 43-46539 Inclusive. \n\nCompliance required before November 15, 1947. \n\nTo reduce the possibility of loss of flight control due to failure of the main rotor links from lack of lubrication, the links should be reworked in accordance with the following instructions. This change involves the removal and inspection of main rotor link, P/N VS 36181 and machining of oil grooves. \n\n1.\tStrip paint from the subject links with a paint remover or lacquer thinner, Specification No. AN-TT-T-256 or equivalent. Do not use scraper or wire brush on links, because small cracks may be filled in and covered. \n\n2.\tVisually inspect main rotor links, P/N VS 36181 by one of the following methods for cracks around link pin hole and longitudinally along what was the flash line in original forging. (See Figure 1.) If cracks are present, links should be scrapped.AD 47-35-01 \n\n(a)\tVisual inspection after re-anodizing; or \n\n(b)\tBy caustic etching; or \n\n(c)\tBy an approved fluorescent-black light method. \n\n3.\tMachine oil grooves. (See Figure 1.) \n\n4.\tRemove burrs and clean after machining. \n\n5.\tInspect the two bearings removed from each of the three subject links. \n\n(a)\tIf bearings removed are P/N AT-16, replace with P/N AT-16-OH bearings on assembly. (Bearing AT-16-OH is an AT-16 bearing with an oil hole added to its outer race.) \n\n(b)\tIf bearings removed are P/N AT-16-OH and retainer washers are damaged or show evidence of foreign matter, they are to be replaced. \n\n(Sikorsky Service Bulletin R-4B No. 10 and Army T. O. 01-230HA-15 also cover this same subject.)
2005-14-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires applying an anti-static conductive coating to the fuel access and thermal anti-icing blowout doors at the location of the bonding fasteners on the leading edge of the wings, and performing a resistance test on the new coating to ensure correct ground path resistance. This AD is prompted by a report that an anti-static coating was not applied correctly on doors located within a flammable fluid leakage zone. We are issuing this AD to prevent an uncontrollable fire in the leading edge of the wing, which could damage critical wing structures and cause a fuel tank explosion.
47-43-04: 47-43-04 CESSNA: (Was Service Note 2 of AD-768-5.) Applies to 120 and 140 Aircraft Serial Numbers 8001 to 12349, Inclusive. Inspection required upon each 100 hours of operation until horns are reinforced. Remove the forward part of the tunnel fairing on the cockpit floor and inspect the control cable horns on the rudder bar for signs of bending which probably is caused by excessive foot pressure during application or release of the parking brakes and results in a reduction of the rudder travel. Bent parts which can be straightened without cracking should be reinforced by the installation of Cessna P/N 0411303 or its equivalent. Cracked parts should be replaced with Cessna P/N 0310168 made of 0.080-inch steel. (Cessna Service Letter No. 43 dated July 7, 1947, covers this same subject.)
94-18-09: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 205A, 205A-1, 205B, 212, and 412 series helicopters, that requires removal and replacement of a certain design main transmission lower planetary spider (spider), and establishes a 2,500 hours time-in-service retirement life for the spider. This amendment is prompted by five failures of the spider that occurred during the manufacturer's fatigue tests. The actions specified by this AD are intended to prevent fatigue failure of the spider, failure of the main transmission, and subsequent loss of control of the helicopter.
2005-12-05: The FAA is superseding an existing airworthiness directive (AD), which applies to certain transport category airplanes. That AD currently requires modification of the reinforced flight deck door. This new AD expands the applicability of the existing AD and requires other actions related to the reinforced flight deck door. These other actions include modifying the door, inspecting and modifying wiring in the area, and revising the maintenance program to require more frequent testing of the decompression panels of the flight deck door. This AD is prompted by reports of discrepancies with the reinforced flight deck door. We are issuing this AD to prevent inadvertent release of the decompression latch and consequent opening of the decompression panel in the flight deck door, or penetration of the flight deck door by smoke or shrapnel, any of which could result in injury to the airplane flightcrew. This AD also requires finding and fixing wire chafing, which could result in arcing,fire, and/or reduced controllability of the airplane.
47-51-04: 47-51-04 CURTISS-WRIGHT Applies to All C-46 Series Airplanes Incorporating Hamilton Standard Propellers. \n\n\tCompliance required by March 1, 1948. \n\n\tTo eliminate failure of the propeller flexible feathering line, an antiheat shield shall be installed in accordance with the following instructions: \n\n\t(a)\tRemove the engine cowling adjacent to the propeller feathering line and inspect the flexible propeller feathering hose and lagging material (if installed) for disintegration and deterioration. Replace hose if deterioration is evident. \n\n\t(b)\tFabricate the antiheat shield and attaching clamps as shown in Figure 1. \n\n\t(c)\tPlace antiheat shield over the flexible hose and mount the shield on the engine mount by use of the clamps shown in Figure 1. The shield should be centered over the flexible hose. It may be necessary to rebend the metal feathering line slightly to achieve proper centering. \n\n\t(d)\tUpon completion of installation, check operation of propeller feathering system. \n\n\t(The above information is also contained in Army Air Forces Technical Order 01-25L- 105 dated April 2, 1947. Copies of this Technical Order are not available for distribution by the FAA.)
2005-13-30: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, and -200C series airplanes, that requires repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. The actions specified by this AD are intended to detect and correct fatigue cracking of the skin panels, which could cause rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
2005-13-18: The FAA is superseding an existing airworthiness directive (AD), which applies to certain SAFT America Inc. part number (P/N) 021929-000 (McDonnell Douglas P/N 43B034LB02) and P/N 021904-000 (McDonnell Douglas P/N 43B034LB03) nickel cadmium batteries. That AD currently requires replacing all battery terminal screws, verifying that the battery contains design specification cells, and replacing the cells if the battery contains non-design specification cells. This new AD requires an inspection for certain nickel cadmium batteries and, if necessary, replacing battery terminal screws with new hex head bolts and adding shims. This AD is prompted by a report of battery screws shearing off while under normal torque loads. We are issuing this AD to prevent internal shorting, arcing, and loss of emergency battery power due to failed battery screws, which could result in loss of emergency power to electrical flight components or other emergency power systems required in the event of loss of the aircraft primary power source.