Results
72-14-04: 72-14-04 NORTH AMERICAN ROCKWELL: Amdt. 39-1481. Applies to Models NA-265, NA-265-20, NA-265-30, NA-265-40 (Serial Nos. 282-1 thru 282-105), and NA-265-60 (Serial Nos. 306-1 thru 306-63). Compliance required as indicated: To prevent failure of the main landing gear wheel door torque tube assembly, P/N 265- 333338-1, -2, 285-333338-1, -2, -31, -32, as applicable, accomplish the following: (a) Within 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, and at intervals not to exceed 100 hours' time in service thereafter, perform a dye penetrant inspection of the main landing gear wheel door torque tube in the area 3 inches adjacent to the fore and aft weldments for evidence of cracking, until (c), below, is accomplished. (b) If evidence of cracking is discovered as a result of any of the inspections of (a), above, replace the torque tube assembly with a new or serviceable assembly prior to further flight. Mark the rejected part to prevent inadvertent return to service (Note: The manufacturer has recommended that operators return parts for rework by them. If returned, and after rework, the mark may be removed, the part re-identified, and returned to service). (c) Replace main landing gear wheel door torque tube assemblies P/N 265-333338- 1, -2, 285-333338-1, -2, -31, -32 with torque tube assemblies P/N 285-333338-51, -52, 276- 933338-1, -2, -31, -32, -41, -42, -51, -52 as applicable. This amendment becomes effective July 7, 1972.
2022-13-07: The FAA is adopting a new airworthiness directive (AD) for all AutoGyro Certification Limited (type certificate previously held by RotorSport UK Ltd) Model Calidus, Cavalon, and MTOsport 2017 gyroplanes. This AD was prompted by reports of rotor blade longitudinal cracking and rotor blade attachment bolt hole fretting corrosion and cracking. This AD requires reducing the life limits for the rotor systems, repetitively inspecting each rotor blade, and depending on the outcome, removing parts from service. The FAA is issuing this AD to address the unsafe condition on these products.
69-04-01: 69-04-01\tBOEING: Amdt. 39-723. Applies to Model 727 Series airplanes in which the battery switch is located within ten inches of the galley switch. \n\n\tCompliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tAs a result of FAA evaluations of the 727 electrical system sufficient cause has been found to prevent inadvertent operation of the battery switch located on the flight engineer's panel. Inadvertent operation of the battery switch during some operating conditions could result in loss of the standby electrical system. \n\n\tTo prevent inadvertent operation of the battery switch on the flight engineer's panel on those 727 Series airplanes in which the battery switch is located within ten inches of the galley switch, accomplish one of the following: \n\n\t(1)\tInstall a guard (Grimes P/N 11170-1 or equivalent MS type painted black) on the battery switch. The guard must be installed to force the switch to the "on" position and the guard should be mounted with the hinge down. \n\n\t(2)\tReplace the battery switch with a detent lock type switch, P/N MS 25125-E3 or an equivalent MS type, provided the galley switch is a toggle type switch. \n\n\t(3)\tPerform an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tIn each of the above installations, install decals as necessary to retain "bat" and "on-off" switch function and switch position identification. \n\n\tBoeing Service Bulletin No. 24-44 is forthcoming to cover same subject. \n\n\tThis amendment becomes effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated January 31, 1969.
99-20-03: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic inspection method performed at an approved facility when the disk is exposed during a shop visit, and if a crack indicating a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation, which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed during a forging process. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the aircraft.
2004-17-04: The FAA supersedes Airworthiness Directive (AD) 2001-26-25, which applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III sailplanes. AD 2001-26-25 currently requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD requires you to install additional mass balance in the elevator and ailerons and determine resultant empty weight and empty weight center of gravity; incorporate a revision in the sailplane maintenance manual; and remove the red mark and the red placard on the airspeed indicator (both required by AD 2001-26-25). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
2022-12-12: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4062 model turbofan engines. This AD was prompted by a report of a manufacturing quality escape due to insufficient cooling of the low-pressure turbine (LPT) stage 5 air seal resulting in a reduction of the low-cycle fatigue (LCF) life limit. This AD requires removal and replacement of the LPT stage 5 air seal with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-11: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines, that requires replacement of 3rd, 4th, and 5th stage low pressure turbine (LPT) vane retention bolts and nuts, the removal of the 5th stage vane configuration which includes an electro-discharge machined (EDM) slot and replacement with a cast slot configuration, and prohibits the use of uncured anti-gallant compound on vane retention hardware. This amendment is prompted by reports of LPT failures that resulted in uncontained engine failures. The actions specified by this AD are intended to prevent LPT vane failures, which can result in uncontained engine failure, fire, and possible damage to the aircraft.
99-19-39: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires removal of the insulation blankets surrounding the emergency overwing exit hatches. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the freezing of moisture entrapped in the fiberglass/foam insulation installed on the fuselage structure between the overwing exit door and the fuselage door frame and intercostal, which could interfere with the opening of the overwing emergency exit hatches during an emergency evacuation of the airplane.
99-20-01: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires modification of the electrical wiring of the flight warning computer (FWC), and installation of upgraded computer software into the FWC. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent certain nuisance alerts generated by the FWC and to ensure annunciation of certain flight alerts by the FWC during initial climb. Such nuisance alerts or failures to annunciate certain alerts could result in an improper response by the flight crew and consequent reduced controllability of the airplane.
99-17-17: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-17-17 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R44 helicopters by individual letters. This AD requires, prior to further flight, replacing certain yoke assemblies with airworthy yoke assemblies. This amendment is prompted by an incident in which, during cruise flight, the pilot heard a loud bang and no tail rotor effectiveness due to a cracked yoke assembly. RHC has identified the manufacturing lots associated with the failed yoke assembly. The actions specified by this AD are intended to prevent failure of the yoke assembly, which could result in loss of main and tail rotor drive and subsequent loss of control of the helicopter.