22 Airworthiness Directives: 18 airplane, 1 rotorcraft, 2 engine, 1 propeller.
AD 96-13-12 · published Aug 2, 1996, effective Aug 2, 1996
328 Support Services GmbH Airplanes
AD 96-16-05 · published Aug 5, 1996, effective Sep 9, 1996
Fokker Model F28 Mark 1000, 2000, 3000, and 4000 Series Airplanes, and Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes, and Model F28 Mark 0100 series airplanes, that requires repetitive pre-load adjustments of the main landing gear (MLG) downlock-actuator. This AD also provides optional terminating action for the repetitive adjustments. This amendment is prompted by a report that, upon landing, the MLG of an airplane collapsed as a result of the lock toggle-links being pulled out of the over-center position by the downlock-actuator, which was due to the relative movement of the upper and lower side-stay members. The actions specified by this AD are intended to prevent collapse of the MLG, which could adversely affect the controllability of the airplane during landing.
AD 96-13-07 · published Aug 6, 1996, effective Aug 6, 1996
Fokker Services Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracks, and repair or replacement, as necessary, to ensure the continued airworthiness of these airplanes. This amendment adds and revises certain significant structural items for which inspection and repair or replacement is necessary. This amendment is prompted by a structural re-evaluation conducted by the manufacturer, which identified additional structural elements where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes.
AD 96-13-02 · published Aug 7, 1996, effective Aug 7, 1996
British Aerospace Regional Aircraft Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Model 3201 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks and corrosion at the wing/fuselage forward attachment sliding joint, replacing any cracked or corroded part, and eventually replacing the spigots and spigot housing plate with new parts of improved design. A crack in the spigot housing plate assembly found during fatigue testing of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent structural failure of the wing/fuselage area caused by a cracked or corroded spigot housing assembly.
AD 96-16-08 · published Aug 12, 1996, effective Aug 27, 1996
Boeing Model 727-100 and -200 Series Airplanes With a Main Deck Cargo Door Installed in Accordance With Supplemental Type Certificate (STC) SA1797SO
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727-100 and -200 series airplanes. This action requires an inspection to detect discrepancies of internal wires and electrical components of the control box of the main deck cargo door; modification of the wiring and components of the control box of the main deck cargo door; and a revision of the Airplane Flight Manual to impose an operational limitation of the motor pump power relay and pump motor. This amendment is prompted by results of an engineering review of the wiring diagram of the main deck cargo door installations, which revealed potential failures of the control box and hydraulic pump assembly installed in accordance with the STC. The actions specified in this AD are intended to prevent such failures, which could result in an inadvertent opening of the main deck cargo door during flight, with resultant major structural damage and possible reduced controllability of the airplane.
AD 96-17-04 · published Aug 13, 1996, effective Sep 17, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires inspections to detect cracking of the support fittings of the Krueger flap actuator and, if necessary, replacement of existing fittings with new steel fittings and modification of the aft attachment of the actuator. This amendment is prompted by reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. The actions specified by this AD are intended to prevent such cracking, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, and resultant loss of hydraulic fluids. These conditions, if not corrected, could result in possible failure of one or more hydraulic systems, and subsequent reduced controllability of the airplane.
AD 96-17-05 · published Aug 19, 1996, effective Sep 3, 1996
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This action requires the installation of a mechanical flight idle stop on the control quadrant of the flight compartment. This action also requires a revision of the Airplane Flight Manual to ensure the use of certain operating procedures after the mechanical flight idle stop is installed. Additionally, this action provides an optional terminating action for the requirements of this AD. This amendment is prompted by a report indicating that the means of protection against the selection of the ``beta'' range of propeller operation during flight has been reduced on certain modified control quadrants. Additionally, there have been reports indicating that power levers on the control quadrant have been moved aft of the flight idle position during flight due to improper usage of the mechanical beta stop. The actions specified in this AD are intended to prevent such movement of the power lever(s) during flight, which could result in propeller overspeed, engine damage, and loss of power to one or both engines.
AD 96-17-07 · published Aug 19, 1996, effective Sep 23, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection to detect cracking of the swivel bogie beam lugs, and repair, if necessary. For airplanes on which no cracking is found, this amendment also requires an inspection to detect corrosion of the swivel pin lug surfaces and bores, and modification of the forward bogie beams. This amendment is prompted by reports indicating that swivel pin lugs of the main landing gear (MLG) have failed due to cracks resulting from stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in failure of the swivel-type bogie beam of the MLG; this condition could result in collapse of the MLG during landing.
AD 96-17-08 · published Aug 19, 1996, effective Sep 23, 1996
The Boeing Company Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -40, and KC-10A (military) series airplanes, that requires modification of the AC generator control units. This amendment is prompted by reports of loss of electrical power from two generators and an engine that flamed out due to an overfrequency condition of a generator. The actions specified by this AD are intended to prevent an overfrequency condition of a generator, which could lead to the loss of all electrical power of the airplane.
AD 96-15-01 · published Aug 20, 1996, effective Sep 19, 1996
Textron Aviation Inc. Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-15-01, which was sent previously to all known U.S. owners and operators of Raytheon Aircraft Corporation (formerly Beech) Model 1900D airplanes. This AD requires immediately pulling and banding the circuit breakers leading to the windshield heat control on both the pilot and co-pilot sides, inserting a copy of the priority letter AD into the Limitations section of the Airplane Flight Manual (AFM), and fabricating and installing a placard instructing the pilot to avoid flight into known icing conditions. Reports of smoke and fire in the cockpit on two Beech Model 1900D airplanes caused by a high resistance short circuit condition in the heated windshield wiring prompted the action. The actions specified by this AD are intended to prevent smoke and fire around the forward edge of the glare shield in the cockpit, which could result in loss of control of the airplane. Comments for inclusion in the Rules Docket must be received on or before October 21, 1996.
AD 96-17-09 · published Aug 20, 1996, effective Sep 24, 1996
Beech (Raytheon) Model Hawker 1000 and BAe 125-1000A Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Beech (Raytheon) Model Hawker 1000 and BAe 125-1000A series airplanes, that currently requires inspections to detect various discrepancies of the fuel hose assemblies on the auxiliary power unit (APU), and correction of any discrepancy found. That AD was prompted by several reports of heat damage to the fuel hose assembly on the APU. This amendment adds a requirement to replace the existing conduit of the fuel feed hose with new improved conduit, which will terminate the repetitive inspections. The actions specified by this AD are intended to prevent failure of a fuel hose due to heat damage caused by incorrect routing or bleed air leakage; such failure could result in a malfunction of the APU, a fuel fire in the fuselage rear equipment bay, and reduced structural integrity of the surrounding structure.
AD 96-17-12 · published Aug 22, 1996, effective Oct 21, 1996
Jetstream Aircraft Limited HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 Airplanes
This amendment supersedes Airworthiness Directive (AD) 87-07- 01, which currently requires the following on Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes: repetitively inspecting the nose landing gear (NLG) top cap assembly securing bolts for looseness or cracks, retorquing any loose security bolt, and replacing any cracked security bolt. AD 87-07-01 also provides the option of incorporating an NLG modification as terminating action for the repetitive inspections. A report of cracked and loose bolts found on an airplane with the above-referenced NLG modification prompted this action. This action: retains the repetitive inspections required by AD 87-07-01; increases the AD applicability to include Jetstream Model 3201 airplanes and airplanes that have the NLG top cap assembly modified in accordance with AD 87-07-01; requires replacing two of the NLG top cap assembly securing bolts; and incorporates a new NLG top cap assembly that would eliminate the repetitive inspection requirement of the AD. The actions specified in this AD are intended to prevent failure of the NLG caused by cracked or loose securing bolts, which, if not detected and corrected, could lead to NLG collapse and damage to the airplane.
AD 96-17-13 · published Aug 26, 1996, effective Sep 30, 1996
Textron Aviation Inc. Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 1000A and Model Hawker 1000 airplanes, that requires a one-time inspection for correct sleeve lengths, an inspection to detect discrepancies of the elevator pulley assembly, and correction of any discrepancy. This amendment is prompted by reports indicating that some aircraft have been fitted with an elevator pulley that was assembled incorrectly during manufacture. The actions specified by this AD are intended to prevent reduced structural integrity of the elevator control circuit due to failure of one or more outer lugs or malfunction of the elevator pulley assembly as a result of incorrect assembly of the pulley.
AD 96-17-02 · published Aug 28, 1996, effective Aug 28, 1996
The Boeing Company Airplanes
AD 96-17-03 · published Aug 28, 1996, effective Aug 28, 1996
BAE Systems (Operations) Limited Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires an inspection to determine the serial number of the leg assemblies of the main landing gear (MLG), and replacement of defective pins with serviceable pins. This amendment is prompted by a report indicating that pins installed on certain leg assemblies of the MLG s were heat treated incorrectly during manufacture. The actions specified in this AD are intended to prevent failure of the pins due to incorrect heat treatment, and subsequent structural failure of the MLG.
AD 96-18-02 · published Aug 28, 1996, effective Feb 26, 1991
American Champion Aircraft Corp. Airplanes
This amendment supersedes Airworthiness Directive (AD) 96-03-11, which currently requires the following on American Champion Aircraft Corporation (American Champion) Models 8KCAB, 8GCBC, 7GCBC, and 7ECA airplanes that are equipped with metal spar wings: inspecting (one-time) the wing front strut attach fittings for cracks, scratches, or surface deformities; replacing any wing front strut attach fitting with cracks, scratches, or surface deformities; and reporting the inspection results to the Federal Aviation Administration (FAA). This action results from reports submitted as a requirement of the existing AD that reference 24 fittings with cracks, scratches, or surface deformities on 7 different airplanes, and the FAA's determination that improved wing front strut attach fittings (developed by American Champion) are not susceptible to cracks, scratches, or surface deformities. This action requires installing removable inspection hole covers for the wing front strut attachfittings, and replacing the wing front strut attach fittings with fittings of improved design. The action also provides the provision of repetitively inspecting the wing front strut attach fittings (provided no cracks, scratches, or surface deformities are found) if parts have been ordered but are not available. The actions specified by this AD are intended to prevent structural failure of a wing caused by cracked wing front strut attach fittings, which, if not detected and corrected, could result in loss of control of the airplane.
AD 96-18-03 · published Aug 30, 1996, effective Oct 4, 1996
Saab AB, Saab Aerosystems Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires installation of an automatic flight idle stop on the control quadrant in the flight compartment. This amendment is prompted by several reports of one or both power levers being moved aft of the flight idle stop on approach. The actions specified by this AD are intended to prevent such movement of the power lever(s) during flight, which could result in the loss of power to one or both engines, as well as severe engine damage.
AD 96-18-04 · published Aug 30, 1996, effective Oct 4, 1996
The Boeing Company Airplanes
This amendment supersedes two existing airworthiness directives (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently require modification of the packing and slide containers of the escape slide, and repetitive inspections of the velcro girt retaining straps of the escape slides at the forward door. The existing AD's were prompted by reports of slide girt material interfering with the girt bar stowage brackets during door opening. This new amendment requires the installation of a new modification, which constitutes terminating action for the repetitive inspection requirements. The actions specified by this amendment are intended to prevent failure or interference of opening of the forward doors, which could delay or impede the evacuation of passengers during an emergency.
AD 96-18-05 · published Aug 30, 1996, effective Sep 16, 1996
Bell Helicopter Textron, A Division of Textron Canada Ltd. Model 206L, 206L-1, and 206L-3 Helicopters
This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 206L, 206L-1, and 206L-3 helicopters, that currently requires a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass. This amendment requires the same actions as the existing AD, but corrects a part number that was incorrectly stated in that AD. This amendment is prompted by a recent accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. The actions specified by this AD are intended to prevent failure of the tailboom and subsequent loss of control of the helicopter.
AD 96-16-07 · published Aug 13, 1996, effective Aug 28, 1996
General Electric Company Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80C2 series turbofan engines. This action supersedes priority letter AD 96-09-01 that currently requires borescope inspections of the rear right hand mount link to determine if the serial number matches those listed in applicable service bulletins as improperly manufactured, and replacement, if necessary, with a serviceable part. This action references a newly revised service bulletin and bases the compliance time on the effective date of this superseding AD for engines installed on McDonnell Douglas MD-11 series aircraft. This amendment is prompted by the availability of the newly revised service bulletin. The actions specified by this AD are intended to prevent rear right hand mount link failure, which could result in engine separation from the aircraft.
AD 96-17-01 · published Aug 19, 1996, effective Sep 9, 1996
Honeywell International Inc. Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to AlliedSignal Inc. (formerly Textron Lycoming) Model T5313B turboshaft engines. This action supersedes priority letter AD 96-15-07 that currently requires, prior to further flight, removal from service of all suspect second stage power turbine disks, identified by serial number, and replacement with serviceable parts. This action corrects an incorrect second stage power turbine disk serial number. This amendment is prompted by report of a typographical error in the serial number listing. The actions specified by this AD are intended to prevent possible failure of a second stage power turbine disk, uncontained engine failure, and damage to aircraft.
AD 96-08-01 R1 · published Aug 2, 1996, effective Aug 2, 1996
Hamilton Sundstrand Propellers
This amendment revises airworthiness directive (AD) 96-08-01, that is applicable to Hamilton Standard Model 14RF-9 propellers. The current AD superseded priority letter AD 95-24- 09, and requires an ultrasonic shear wave inspection, adds a one-time visual and fluorescent penetrant inspection, and repair of the propeller blade shank. This revision will add a new shank eddy current inspection and will allow repair of certain blade shanks removed from service under the current AD. The actions specified by this AD are intended to prevent propeller blade separation due to propeller blade shank cracking that can result in loss of control of the aircraft.
