Results
2003-12-02: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model ATP airplanes, that requires installing a baulking device for the pintle pin in the nose landing gear (NLG). This action is necessary to prevent failure of the NLG due to an unlocked pintle pin migrating from its support housings, and consequent jamming or collapse of the NLG. This action is intended to address the identified unsafe condition.
2003-11-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes, that currently requires repetitive lubrication of the slide shaft of the input plunger of the brake control valve assembly. This amendment adds requirements for modifying the brake control valve assembly, which terminates the repetitive lubrications required by the existing AD. This amendment also adds subsequent repetitive lubrications of the valve utilizing the grease fittings installed during the modification. This amendment is prompted by reports of temporary loss of braking action upon landing. The actions specified by this AD are intended to prevent temporary loss of braking action due to the freezing of moisture on the input plunger of the brake control valve during steep descent. DATES: Effective July 11, 2003. The incorporation by reference of Bombardier Service Bulletin 601R-32-017, dated November 9,1993, as listed in the regulations, is approved by the Director of the Federal Register as of July 11, 2003. The incorporation by reference of Canadair Regional Jet Alert Service Bulletin S.B.A601R-32-016, dated October 14, 1993, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 4, 1994 (59 FR 2952, January 20, 1994).
2003-11-09: This amendment adopts a new airworthiness directive (AD), that is applicable to Turbomeca Turmo IV A and IV C series turboshaft engines. This amendment requires initial and repetitive borescope and eddy current or ultrasonic inspections of centrifugal compressor intake wheel blades for cracks and evidence of corrosion pitting, and, if found cracked or if there is evidence of corrosion pitting, replacement with serviceable parts. This amendment is prompted by reports of cracked centrifugal compressor intake wheel blades, resulting in the release of one or more blade fragments. The actions specified by this AD are intended to prevent centrifugal compressor intake wheel blade cracks, which can result in in-flight engine power loss or shutdown.
2003-10-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Aerospace LP Model Astra SPX and 1125 Westwind Astra series airplanes, that requires removing the existing oxygen shutoff valve and installing a new oxygen shutoff valve. The actions specified by this AD are intended to prevent rapid adiabatic compression within the oxygen line between the oxygen shutoff valve and the pressure regulator due to a shutoff valve that can be opened quickly, which could result in overheating of the oxygen system and consequent fire in the cockpit. This action is intended to address the identified unsafe condition.
2003-10-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model 717-200 airplanes, that requires modification of certain attachment holes in the rear spar of the left and right wings. This action is necessary to prevent fatigue cracking of the rear spar of the wings, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2003-10-03: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, RB211- 535E4-B-37, and RB211-535E4-B-75 turbofan engines. This amendment requires removal from service of certain high pressure (HP) turbine discs before they reach newly established life limits. This amendment is prompted by the manufacturer's inspections and analysis of HP turbine discs that have accumulated high cycles. The actions specified by this AD are intended to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane.
94-20-04 R2: This amendment revises Airworthiness Directive (AD) 94-20-04 R1, which currently requires ruddervator inspections and modifications on certain Raytheon Aircraft Company (Raytheon) Beech Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B airplanes. This AD maintains the actions of AD 94-20-04 R1, but makes the repetitive visual inspection of the empennage, aft fuselage, and ruddervator control system with any subsequent repair and the setting of the elevator controls, rudder and tab system controls, cable tensions, and rigging a one time action; and adds repetitive inspections of the fuselage bulkheads that were required by AD 94-20- 04. This AD is the result of the need to add a repetitive inspection of the fuselage bulkheads and change other inspections from a repetitive to a one-time action. The actions specified by this AD are intended to prevent structural failure of the V-tail, which could result in loss of control of the airplane.
2003-09-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires you to accomplish a one-time inspection for missing rivets on certain areas of the airplane and, if necessary, install rivets. This AD is the result of Raytheon identifying several instances of missing rivets on these airplanes. The actions specified by this AD are intended to detect and correct an understrength condition in the fuselage, which could result in the failure of the fuselage. Such failure could lead to loss of control of the airplane in flight.
2003-09-09: This amendment supersedes Airworthiness Directive (AD) 2002-09-13, which currently requires a one-time inspection of the fuel boost pump wiring inside and outside the boost pump reservoir and repair or replacement of the wiring as necessary on certain Cessna Aircraft Company (Cessna) Model 441 airplanes. AD 2002-09-13 resulted from several reports of chafing and/or arcing of the fuel boost pump wiring inside and outside the fuel pump reservoir. This AD retains the actions required in AD 2002-09-13, makes the one-time inspection repetitive, requires the inspection and possible replacement of the wire harness, lead wires and fuel boost pump on Model F406 airplanes, and requires eventual installation of an improved design wire harness and fuel boost pump as terminating action for the repetitive inspections. The actions specified by this AD are intended to detect, correct, and prevent chafing and/or arcing fuel boost pump wiring, which could result in arcing within the wing fuel storage system. Such a condition could lead to ignition of explosive vapor within the fuel storage system.
2002-13-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires revisions to the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine Manual to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD adds additional critical life-limited parts for enhanced inspection. This AD is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent the failure of critical, life-limited, rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.