16 Airworthiness Directives: 8 airplane, 3 rotorcraft, 2 engine, 1 propeller, 1 appliance, 1 glider.
AD 94-17-05 · published Sep 6, 1994, effective Sep 6, 1994
Airbus Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A340-211 and -311 series airplanes. This action requires replacement of certain circuit breakers for the toilet system vacuum generator. This amendment is prompted by reports of excessive vacuum generator overloads or blocked rotor conditions, in which the thermal protection device and/or related aircraft circuit breakers do not interrupt the power supply. The actions specified in this AD are intended to prevent a fire in the event of excessive current in the electrical circuit due to overheating of the vacuum generator.
AD 94-18-01 · published Sep 9, 1994, effective Oct 11, 1994
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 and 767 series airplanes, that requires modification of the latch hook installation for the number two cockpit window frame. This amendment is prompted by reports of the flight crew executing rejected takeoffs (RTO) and air turnbacks (ATB) due to false "closed" indications for the number two cockpit window. The actions specified by this AD are intended to prevent unlatched (not completely closed) number two cockpit windows and the resultant execution of RTO's and ATB's by the flight crew.
AD 94-18-05 · published Sep 9, 1994, effective Oct 11, 1994
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SF340A and SAAB 340B series airplanes. This amendment requires inspections to detect discrepancies of certain main landing gear (MLG) retract actuator bracket retaining bolts; replacement of discrepant parts; installation of washers, if necessary; and eventual replacement of certain MLG retract actuator bracket retaining bolts and certain nose landing gear (NLG) trunnion pin cross bolts. This amendment is prompted by reports of extension and retraction problems on the MLG, due to loose retract actuator brackets on the MLG shock struts. The actions specified by this AD are intended to prevent a loose retract actuator bracket from interfering with the MLG shock strut trunnion support, which could result in the inability of the MLG to extend or retract.
AD 91-20-14 R1 · published Sep 12, 1994, effective Sep 12, 1994
Textron Aviation Inc. Airplanes
AD 94-18-07 · published Sep 15, 1994, effective Sep 15, 1994
McDonnell Douglas Corporation Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes and certain Model MD-11 series airplanes, that currently require inspections to determine the serial numbers and to detect defects in the upper and lower lock links on the nose landing gear (NLG), and rework or replacement of any defective link with a serviceable link. This amendment requires additional inspections and provides optional terminating action for those inspections. This amendment is prompted by additional reports of defects found on links that are required to be inspected by the existing AD's. The actions specified in this AD are intended to prevent collapse of the NLG.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 15, 1994.\t\n\tComments for inclusion in the Rules Docket must be received on or before October 31, 1994.
AD 94-16-02 · published Sep 19, 1994, effective Sep 19, 1994
Don Luscombe Aviation History Foundation, Inc. Airplanes
This amendment supersedes AD 79-25-05, which currently requires repetitively inspecting the existing aluminum vertical stabilizer forward attach fitting for cracks on Luscombe Model 8 series airplanes, and replacing any cracked parts. Steel fittings are now available that, when installed, will eliminate the need for repeated removal and inspection of the aluminum fitting, which could result in damage to the fastener holes. This action requires replacing the existing aluminum fitting with a steel vertical stabilizer forward attach fitting on Luscombe Model 8 series airplanes that have round-tipped vertical stabilizer installations. The actions specified by this AD are intended to prevent failure of the vertical stabilizer as a result of a cracked fitting, which could result in loss of control of the airplane.
AD 94-19-04 · published Sep 21, 1994, effective Oct 21, 1994
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-1000A series airplanes, that requires modification of the control circuit wiring for the engine thrust reversers and of the wiring for annunciation of rudder bias status. This amendment is prompted by a report that a single dormant electrical fault in the control circuit of the thrust reversers could cause a thrust reverser to deploy if the pilot selects reverse thrust during the approach phase of flight; and by reports that if an asymmetric thrust reverser condition occurs, the correct rudder bias may not be annunciated before the flight crew applies high reverse thrust. The actions specified by this AD are intended to prevent adversely affected controllability of the airplane.
AD 94-20-05 · published Sep 30, 1994, effective Oct 14, 1994
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech) 1900 series airplanes. This action requires inspecting the hot battery bus fuse assembly for proper wiring, correcting the wiring if incorrect, and modifying the wiring to add a redundant power source for the hot battery bus. This action results from a report of the hot battery bus bar wrongly installed on the lower (load) side of the hot battery bus fuse assembly on one of the affected airplanes. Correct installation is the upper (power) side of the circuit. The actions specified by this AD are intended to protect from overloads to either circuit connected to the hot battery bus from overloads, which, if not protected, could result in loss of certain emergency equipment.
AD 94-18-08 · published Sep 7, 1994, effective Jan 13, 1992
MD Helicopters, Inc. Helicopters
This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Company and Hughes Helicopters, Inc. Model 369, 369A (OH-6A), 369D, E, F, FF, H, HE, HS, and HM series helicopters, that requires daily preflight checks and 100 hours time-in-service (TIS) inspections for tail rotor blade abrasion strip (abrasion strip) debonding until abrasion strip rivets (rivets) are installed. This amendment also supersedes a Priority Letter AD that currently requires installation of rivets, corrects tail rotor blade part numbers listed in the previous AD, and retains the daily preflight checks of the previous AD until rivets are installed to secure the abrasion strip. This AD provides a terminating action for the abrasion strip debonding and also seeks to clear up any confusion among operators caused by having a published AD and a Priority Letter that are applicable to the same helicopter part. This AD replaces both of those documents. Thisamendment is prompted by an accident resulting from the separation of an abrasion strip from a tail rotor blade and subsequent tail rotor separation. The actions specified by this AD are intended to prevent loss of the abrasion strip, separation of the tail rotor, and subsequent loss of control of the helicopter.
AD 94-17-15 · published Sep 15, 1994, effective Sep 15, 1994
Enstrom Helicopter Corporation, The Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to The Enstrom Helicopter Corporation (Enstrom) Model F-28A, F-28C, F-28C2, F-28F, 280, 280C, 280F, and 280FX series helicopters. This action requires initial and repetitive inspections for delamination of the main rotor feathering elastomeric Lamiflex bearing (Lamiflex bearing). This amendment is prompted by several reported failures of the Lamiflex bearing. The actions specified in this AD are intended to prevent failure of the Lamiflex bearing, abnormal vibrations in the airframe and flight control system, and subsequent loss of control of the helicopter.
AD 94-19-02 · published Sep 28, 1994, effective Sep 28, 1994
Bell Helicopter Textron Canada Limited Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, and 206L-3 series helicopters. This action requires initial and repetitive inspections of the swashplate for cracks in the swashplate support assembly fillet radius area and replacement, if necessary. This amendment is prompted by reports of cracks found in the swashplate support assembly fillet radius area near the base. The actions specified in this AD are intended to prevent failure of the swashplate support assembly, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
AD 94-18-03 · published Sep 9, 1994, effective Sep 26, 1994
Rolls-Royce plc Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls- Royce plc (R-R) RB211 series turbofan engines. This action requires removing from service intermediate pressure (IP) compressor stage 6-7 rotor shafts that exceed new, reduced cyclic life limits. This amendment is prompted by a report of an uncontained failure of an IP compressor stage 6-7 rotor shaft. The actions specified in this AD are intended to prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 26, 1994. Comments for inclusion in the Rules Docket must be received on or before November 8, 1994.
AD 94-18-06 · published Sep 9, 1994, effective Sep 26, 1994
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Textron Lycoming LTS101 series turboshaft and LTP101 series turboprop engines. This action requires a one-time removal of 321 No. 2 bearings with serial numbers from suspect manufacturing lots, and replacement with serviceable parts. This amendment is prompted by reports of three in- service bearing failures. The actions specified in this AD are intended to prevent engine power loss and inflight engine shutdown due to No. 2 bearing failure, which could result in possible loss of the aircraft.
AD 94-17-13 · published Sep 15, 1994, effective Sep 15, 1994
Hartzell Propeller, Inc. Propellers
AD 94-19-06 · published Sep 21, 1994, effective Oct 6, 1994
328 Support Services GmbH, Cessna Aircraft Company, Dassault Aviation, Dornier Luftfahrt GmbH, Gulfstream Aerospace Corporation, Textron Aviation Inc., Puritan-Bennett Aero Systems Appliances
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Puritan Bennett Sweep-On Model 2000 crew masks installed on various transport and commuter category airplanes. This action requires modification of certain crew oxygen masks. This amendment is prompted by reports of difficulty in exhaling into certain crew oxygen masks due to misalignment of the demand diaphragm. The actions specified in this AD are intended to prevent the flight crew from experiencing difficulty in exhaling into the affected crew oxygen masks in the event oxygen masks are required for the crew, such as during depressurization of the airplane.
AD 94-17-06 · published Sep 30, 1994, effective Sep 30, 1994
Burkhart Grob Luft-Und, GROB-WERKE GMBH & CO KG Gliders
This amendment adopts a new airworthiness directive (AD) that applies to GROB Luft und Raumfahrt (Grob) Models G102, G103, G109, and G109B gliders. This action requires inspecting (one-time) the airbrake stops for cracks in the surrounding gelcoat and to ensure that the outer airbrake swivel levers are in contact with the stops during operation, and repairing any gelcoat cracks or any airbrake stops not in contact with the swivel levers. Excessive wear caused the airbrake fence to jam on the upper shell of the wing on one of the affected gliders, resulting in an accident. The actions specified by this AD are intended to prevent airbrake failure caused by jamming of the airbrake fence, which could result in loss of control of the glider.
