Results
2002-15-01 R1: This amendment clarifies information contained in Airworthiness Directive (AD) 2002-15-01, which currently requires you to inspect the long aileron push rods in both wings for damage and modify the push rods on all Diamond Aircraft Industries GmbH (Diamond) Models H-36 "Dimona", HK 36 R "Super Dimona", HK 36 TC, HK 36 TS, HK 36 TTC, HK 36 TTC-ECO, HK 36 TTC-ECO (Restricted Category), and HK 36 TTS sailplanes. The Model H-36 "Dimona" sailplane has a different flight control system than the rest of the affected sailplanes. This particular flight control system makes it impossible for the Model H-36 "Dimona" sailplanes to be in compliance with AD 2002-15-01. This document deletes these sailplanes from the AD applicability. The actions specified by this AD are intended to detect and correct damage in the long aileron push control rods, which could result in failure of the aileron push rods and decreased control. Such failure could lead to aeroelastic flutter.
2002-08-54: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (EAD) 2002-08-54, which was sent previously to all known U.S. owners and operators of the specified Bell Helicopter Textron Canada (BHTC) model helicopters by individual letters. This AD requires a visual check of each main rotor grip assembly (grip) and pitch horn at specified intervals and a visual inspection using a 10-power or higher magnifying glass of each affected grip and pitch horn for a crack at specified intervals. If a crack is found, this AD requires replacing each unairworthy grip or pitch horn with an airworthy part before further flight. This AD is prompted by three reports each of a fatigue crack in the grip and pitch horn found during routine inspection of the rotor head. This condition, if not detected, could result in failure of the grip or pitch horn and subsequent loss of control of the helicopter.
2002-16-25: This amendment adopts a new airworthiness directive (AD), that is applicable to Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C turboshaft engines. This amendment requires initial and repetitive visual inspections for fuel leaks, and replacement of fuel pumps that are found leaking fuel. In addition, this amendment requires that fuel pumps found with pump wall thickness below minimum be removed from service. This amendment is prompted by a manufacturing investigation of pump bodies found to have below minimum material thickness, which could cause fuel leakage through thin, porous walls, reducing fuel pump fire resistance. The actions specified by this AD are intended to prevent fuel leakage, which may cause engine fires that could lead to an in- flight engine shutdown, damage to the helicopter, and forced landing.
2002-16-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777 series airplanes, that requires inspection of certain aft axle pivot pins of the main landing gear (MLG) for heat damage and either reworking of damaged pins or replacement of damaged pins with new or serviceable pins. This action is necessary to prevent breakage of the aft axle pivot pin of the MLG, which could overload the center axle, causing the tires to blow out upon landing, and could disengage the aft axle so that it jams the gear in the wheel well, preventing proper extension of the MLG. This action is intended to address the identified unsafe condition.
2002-16-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection for missing bolts on the inboard and outboard support of the inboard main flap, and follow-on inspections and corrective actions, if necessary. This action is necessary to detect missing, loose, or cracked bolts on the supports of the inboard main flap and prevent loss of the inboard main flap, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2002-16-04: This amendment supersedes two different airworthiness directives that require you to inspect the fuel line nipple for damage, replace any suspect part, and replace the elbow fitting on certain Univair Aircraft Corporation (Univair) Models (ERCO) 415-C, (ERCO) 415-CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A airplanes. This AD requires you to accomplish the following on airplanes with the gascolator connected to the side of the carburetor: Replace any aluminum fuel line nipple or elbow fitting with a brass or steel fuel line nipple or elbow fitting, inspect for double support tubes on the gascolator, install these tubes if they do not exist, and inspect the fuel line fittings between the carburetor and gascolator for cracks or misalignment and replace as necessary. This AD will not affect those airplanes with the gascolator mounted on the firewall. This AD is a result of cracks in the subject area on airplanes in compliance with the current ADs.The actions specified by this AD are intended to prevent failure of the fuel line fittings or the gascolator because of the current airplane design configuration (aluminum fuel line nipples, aluminum fuel line elbows, and/or no double support tubes on the gascolator). Such failure could result in a lack of fuel to the engine with consequent loss of control of the airplane.
2002-16-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all Bombardier Model CL-600-2B19 series airplanes. This action requires revising the Airworthiness Limitations section of the maintenance requirements manual to incorporate life limits for certain horizontal stabilizer trim actuators (HSTAs), and replacing the HSTAs with new or serviceable HSTAs. This action is necessary to prevent failure of key components of the HSTAs, which could result in loss of horizontal trim control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2002-13-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-13-51, sent previously to all known U.S. owners and operators of the specified helicopters by individual letters. This AD requires cleaning and inspecting a certain tail rotor (T/R) grip with a magnet to determine if it is made of steel. If it is not made of steel, this AD requires replacing each affected T/R grip with an airworthy, steel T/R grip. This AD is prompted by reports of timed-out T/R grips being improperly remarked and reinstalled on certain helicopters. This unsafe condition, if not detected, could result in failure of the T/R grip and subsequent loss of control of the helicopter.
2002-14-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that currently requires repetitive inspections (tests) of the actuator clutches of the primary and backup pitch trim systems of the horizontal stabilizer for proper pitch trim indications, and replacement of the actuator, if necessary. This amendment expands the applicability in the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a civil airworthiness authority. The actions specified in this AD are intended to prevent loss of pitch trim command during the takeoff and climb phase of flight due to improper set point of the actuator clutches, which could result in high pitch control forces and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2002-14-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 and 11F airplanes. This action requires a one-time inspection to detect loose preload-indicating (PLI) washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, and replacement with new parts if necessary. This action is necessary to detect and correct loose PLI washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, which could result in separation of the inboard flap outboard hinge from the wing structure and consequent reduced controllability of the airplane.