14 Airworthiness Directives: 12 airplane, 1 engine, 1 various.
AD 97-01-01 · published Jan 2, 1997
The New Piper Aircraft, Inc. PA24, PA28R, PA30, PA32R, PA34, and PA39 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that supersedes AD 95-20-07, which currently requires repetitively inspecting the main gear sidebrace studs for cracks on certain The New Piper Aircraft, Inc. (Piper) PA24, PA28R, PA30, PA32R, PA34, and PA39 series airplanes, and replacing any cracked main gear sidebrace stud. This AD retains the repetitive inspection and possible replacement requirements of AD 95-20-07; specifies in the ``Applicability'' section of the AD that certain Model PA34-200T airplanes could contain a certain main gear sidebrace assembly configuration that is not affected; and incorporates additional modification and replacement options. This AD results from additional information received by the Federal Aviation Administration (FAA) after the issuance of AD 95-20-07 on the design and service history of the affected airplanes concerning this subject. The actions specified by this AD are intended to prevent a main landing gear collapse caused by main gear sidebrace stud cracks, which could result in loss of control of the airplane during landing operations.
AD 96-26-52 · published Jan 3, 1997, effective Jan 8, 1997
Boeing Model 747 Series Airplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-26-52 that was sent previously to all known U.S. owners and operators of Boeing Model 747 series airplanes by individual telegrams. This AD requires repetitive inspections of the access doors to the midspar/spring beam fuse pins on all engine pylons to detect cracks on the external surface; repetitive inspections of each midspar/spring beam fuse pin to detect if it protrudes beyond its mating nut by a specified distance; and repair of any discrepancy found. This action is prompted by a report indicating that a fuse pin had migrated on an inboard spring beam fitting on the Number 1 engine pylon of a Boeing Model 747-400 airplane. The actions specified by this AD are intended to prevent migration of this fuse pin, which, if not detected and corrected in a timely manner, could result in failure of the engine pylon and consequent separation of the engine from the wing.
AD 96-26-51 · published Jan 8, 1997, effective Dec 13, 1996
Boeing Model 747 Series Airplanes Powered By Rolls Royce Model RB211 Series Engines
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T96-26-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 747 series airplanes powered by Rolls Royce Model RB211 series engines by individual telegrams. This AD requires a one-time inspection to detect cracks and corrosion of various areas at all four engine pylons, and repair of any cracked or corroded engine pylon. This action is prompted by reports of cracking of the aft torque bulkhead at the number 1 and number 2 engine pylons. The actions specified by this AD are intended to detect and correct such cracking, which could result in failure of the pylon and consequent separation of the engine from the wing.
AD 97-01-07 · published Jan 9, 1997, effective Feb 13, 1997
British Aerospace Model BAe 146 and Avro 146-RJ Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires modification of the left and right elevators, and replacement of the elevator spring with a stiffer spring. This amendment is prompted by reports indicating that water and ice have accumulated at the trailing edge of the left and right elevators; this accumulation can cause the elevators to become unbalanced, and oscillate or flutter. The actions specified by this AD are intended to prevent this oscillation or flutter. Elevator oscillation, if not corrected, could result in reduced controllability of the airplane. Elevator flutter, if not corrected, could couple with the natural vibrations of the airplane, and result in loss of the airplane's structural integrity.
AD 97-01-08 · published Jan 9, 1997, effective Feb 13, 1997
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time visual inspection to detect missing rivet heads or loose rivets of the applicable stringer-to-rib connections in the upper and lower wing skin, and repair, if necessary. In lieu of the one-time visual inspection or in addition to that inspection, the AD also requires replacement of certain rivets with certain new rivets in all applicable rib-to-stringer connections of the upper and lower wings. This amendment is prompted by reports of missing rivet heads at the rib-to- stringer connections of the upper and lower wing skin at stringers 5 and 6. The actions specified by this AD are intended to prevent reduced structural integrity of the wings that is caused by problems associated with missing and/or loose rivets.
AD 97-01-11 · published Jan 10, 1997, effective Feb 10, 1997
Airbus Model A300 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that is applicable to certain Airbus Model A320 series. The AD requires detailed visual inspections to detect cracking of a certain fuselage frame, and repair, if necessary; and provides for an optional terminating action for the repetitive inspections. The AD was prompted by reports of a fatigue crack found initiating at hole ``I'' of frame 47 on two of these airplanes. The actions specified by the AD are intended to detect and correct such fatigue cracking, which could result in reduced structural integrity of the airplane. This action corrects the applicability of the currently existing AD to cite an airplane model that was inadvertently omitted.
AD 97-01-10 · published Jan 15, 1997, effective Feb 19, 1997
Boeing Model 737-100 and -200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires replacing the aileron (lateral) control transfer mechanism with a new modified mechanism, or reworking the existing mechanism. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent unexpected, significant control wheel forces and reduced travel of a control wheel due to mechanical interference within the lateral control system transfer mechanism during a jam override condition.
AD 97-02-02 · published Jan 17, 1997, effective Feb 6, 1997
Fairchild Aircraft, Inc. SA26, SA226, and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Fairchild Aircraft, Inc. (Fairchild) SA26, SA226, and SA227 series airplanes. This action requires applying torque to the control column pitch bearing attaching nuts, inspecting for any looseness or movement of the bearing assembly, and inspecting the elevator control rod end bearing retainer/dust seals for creasing. If either of these problems are evident, this action requires replacing these parts, as well as installing a new bolt and washer to the elevator control rod end bearing assembly at the walking beam connection. Reports of Fairchild SA227 series airplanes losing pitch control in-flight prompted this action. The actions specified by this AD are intended to prevent loss of pitch control, which if not corrected, could result in loss of the airplane.
AD 97-01-13 · published Jan 22, 1997, effective Feb 3, 1997
Cessna Aircraft Company 100, 200, 300, and 400 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 100, 200, 300, and 400 series airplanes. This action requires checking the airplane maintenance records for any fuel, oil, or hydraulic hose, Cessna part number (P/N) S51-10, replaced between March 1995 and February 3, 1997 (the effective date of this AD); immediately checking any of these hoses for a diagonal or spiral external reinforcement wrap; and immediately replacing any of these hoses that have a diagonal or spiral external reinforcement wrap with one that has a criss-cross external reinforcement wrap. This action was prompted by reports of operators experiencing a loss of engine power because of low fuel feed, in addition to Cessna discovering that the rubber hose installed at the factory on certain Cessna Models 208 and 208B airplanes was defective. The Cessna P/N S51-10 rubber hose is utilized on fuel, oil, and hydraulic hoses on the affected airplanes. The actions specified by this AD are intended to prevent fuel, oil, or hydraulic systems failure caused by a collapsed hose.
AD 97-02-03 · published Jan 23, 1997, effective Feb 27, 1997
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F28 Mark 0100 series airplanes. It requires a one-time inspection to verify the correct routing and tension of the flight control lock cables and the elevator control cables, and rerouting or adjustment of the tension of these cables, if necessary. This amendment is prompted by a report indicating that an inspection for correct routing and tension of those cables may not have been accomplished during modification of the airplanes at the factory. The actions specified by this AD are intended to prevent incorrect routing and tension of the flight control lock cables and the elevator control cables, which could result in inadvertent disconnection of those cables, and consequent reduced controllability of the airplane.
AD 97-02-10 · published Jan 27, 1997, effective Feb 11, 1997
McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) Series Airplanes, Model MD-88 Airplanes, and Model MD-90 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, Model MD-88 airplanes, and Model MD-90 airplanes. This action requires a visual check to determine the part and serial numbers of the upper lock link assembly of the nose landing gear (NLG); repetitive inspections of certain upper lock link assemblies to detect fatigue cracking; and modification of the NLG. This action also provides for terminating action for the repetitive inspections. This amendment is prompted by a report indicating that, due to fatigue cracking, the upper lock link assembly on an airplane fractured, and consequently prevented the NLG from extending fully. The actions specified in this AD are intended to prevent this assembly from fracturing due to fatigue cracking, and the NLG consequently failing to extend fully; this condition could result in injury to passengers and flight crew, and damage to the airplane.
AD 97-02-08 · published Jan 28, 1997, effective Mar 4, 1997
McDonnell Douglas Model DC-9, DC-9-80 and C-9 (Military) Series Airplanes, and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-9, DC-9-80 and C-9 (military) series airplanes, and Model MD-88 airplanes It requires either the installation of external protective doublers between the outboard flight spoiler actuators and the aft spar webs of the wings, or replacement of the pistons of the outboard flight spoiler actuators with improved pistons. This amendment is prompted by reports of failure of the piston of the outboard flight spoiler actuator due to fatigue at the clevis end of the upper lug mounting hole of the piston. The actions specified by this AD are intended to prevent such failure of the piston and the consequent puncturing of the aft spar web, which could result in fuel leakage and reduced structural integrity of the wings.
AD 97-01-05 · published Jan 6, 1997, effective Jan 21, 1997
Williams International, L.L.C. Model FJ44-1A Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Williams International, L.L.C. Model FJ44-1A turbofan engines. This action requires initial and repetitive eddy current inspections (ECI) for possible cracks in high pressure turbine (HPT) disk blade retention posts. In addition, this AD requires the installation of advanced design HPT disks as terminating action to the inspection requirements of this AD. This amendment is prompted by two incidents of HPT disk blade retention post separations. The actions specified in this AD are intended to locate possible cracks in HPT disk blade retention posts, thereby preventing the separation of these posts and the liberation of the turbine blades that they retain, and a subsequent loss of engine power. In addition, the actions specified in this AD are intended to prevent the possible high disk speed uncontained liberation of disk posts and turbine blades, which could cause aircraft damage.
AD 97-01-12 · published Jan 21, 1997, effective Feb 25, 1997
Airtell International, Inc., Centaurus Model C3-100 Ground Proximity Warning System (GPWS), as Installed in Various Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airtell International, Inc., Centaurus Model C3-100 GPWS equipment that is installed on any type of airplane, that requires replacement of this equipment with a similar type of equipment that meets specific performance requirements. This amendment is prompted by results of an investigation, which revealed that, under certain circumstances, the Centaurus GPWS equipment does not provide the flight crew with aural warnings to indicate that the airplane is descending. The actions specified by this AD are intended to prevent failure of the GPWS equipment to provide such aural warnings. If the flight crew relies on receiving such warnings and the GPWS equipment fails to provide those warnings, the ability of the flight crew to prevent the airplane from impacting the ground may be inhibited.
