25 Airworthiness Directives: 15 airplane, 2 rotorcraft, 4 engine, 1 propeller, 2 appliance, 1 glider.
AD 97-16-03 · published Aug 1, 1997, effective Sep 5, 1997
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a one-time inspection of the main landing gear (MLG) retaining bolt to ensure that it is installed correctly, and adjustments or repairs, if necessary. This amendment is prompted by a report indicating that a disconnected retaining bolt was found in the MLG forward trunnion joint of a Model 767 series airplane. The actions specified by this AD are intended to prevent aft-acting trunnion loads from being transferred to the MLG beam, and consequent fracture and collapse of the MLG; this condition could result in the loss of control of the airplane on the ground.
AD 97-16-04 · published Aug 1, 1997, effective Sep 5, 1997
Saab Model SAAB SF340A and SAAB 340B Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires inspections to detect improper connections of the wire harness installation to the cartridges of the fire extinguishers in the engine nacelles, correction of any discrepancy, and modification of the wiring. This amendment adds a revised modification of that wiring, which, if accomplished, would terminate the inspections currently required by the existing AD. This amendment is prompted by reports indicating that, due to the removal of a certain clamp during maintenance, these fire extinguisher cartridges still could be connected incorrectly after the modification required by the existing AD has been accomplished. The actions specified by this AD are intended to prevent incorrect wiring of the cartridges, which would result in inability of the fire extinguishers to jointly discharge extinguishing agent into a nacelle in the event of an engine fire.
AD 97-16-05 · published Aug 1, 1997, effective Sep 5, 1997
Gulfstream Aerospace Corporation Model G-159 (G-I) Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Gulfstream Model G-159 (G-I) airplanes, that currently requires repetitive inspections to detect corrosion in the wing planks under the bottom wing center fairings, and repair, if necessary. This amendment requires the installation of a protective paint system which, when accomplished, will allow the inspections to be conducted at longer intervals. This amendment is prompted by the development of a modification that will improve the corrosion resistance of the subject area. The actions specified by this AD are intended to detect and prevent corrosion in the lower skins of the wing center section. If corrosion in this area remains unchecked, it could reduce the integrity of the wing-to-fuselage fitting, and consequently could lead to separation of the wing from the airplane.
AD 97-16-06 · published Aug 1, 1997, effective Sep 5, 1997
Airbus Model A300-600 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300-600 series airplanes, that requires an inspection to detect cracks of certain attachment holes; and installation of a new fastener and follow-on inspections or repair, if necessary. This amendment is prompted by reports of fatigue cracking found on the forward fitting of frame 47 at the level of the last fastener of the external angle fitting. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the airframe.
AD 97-16-08 · published Aug 4, 1997, effective Aug 19, 1997
Fokker Model F28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires a one-time inspection to detect fatigue cracking of the hinges of the cargo doors, and repair, if necessary. This amendment is prompted by reports indicating that, during inspections of the cargo door area, fatigue cracking of hinges of the cargo doors was detected. The actions specified by the proposed AD are intended to detect and correct such cracking, which could result in structural failure of the cargo doors, and consequent rapid decompression of the airplane and possible separation of the cargo doors from the airplane during flight.
AD 97-17-01 · published Aug 12, 1997, effective Sep 16, 1997
Boeing Model 737-100 and -200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100 and -200 series airplanes, that requires replacement of certain outboard and inboard wheel halves with improved wheel halves. This amendment also requires cleaning and inspecting certain outboard and inboard wheel halves for corrosion, missing paint in large areas, and cracks; and repair or replacement of the wheel halves with serviceable wheel halves, if necessary. 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 failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures; and consequent reduced controllability of the airplane.
AD 97-16-09 · published Aug 18, 1997, effective Sep 22, 1997
British Aerospace BAe Model ATP Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires modification of the hydraulic system, and a revision to the Airplane Flight Manual (AFM) to include revised procedures for lowering the landing gear. This amendment is prompted by a report of uncommanded application of the brakes when the direct current (DC) hydraulic pump was selected ON with the main hydraulic system operative; this situation was caused by build-up of back pressure in the brake supply and hydraulic return systems. The actions specified by this AD are intended to prevent uncommanded application of the brakes during landing, as a result of the build-up of back pressure.
AD 97-17-03 · published Aug 18, 1997, effective Sep 5, 1997
Ayres Corporation S2R Series Airplanes
This amendment supersedes Airworthiness Directive (AD) 97-13- 11, which currently requires inspecting the \1/4\-inch and \5/16\-inch bolt hole areas on the lower spar caps for fatigue cracking on Ayres S2R series airplanes, and replacing any lower spar cap if fatigue cracking is found. That AD resulted from an accident on an Ayres S2R series airplane where the wing separated from the airplane in flight. AD 97-13-11 incorrectly references the Ayres Model S2R-R1340 airplanes as Model S2R-1340R. This AD requires the same actions as AD 97-13-11, but corrects the designation of the Model S2R-R1340 airplanes. The actions specified by this AD are intended to detect fatigue cracking of the lower spar caps, which, if not corrected, could result in the wing separating from the airplane with consequent loss of control of the airplane.
AD 96-23-07 R1 · published Aug 20, 1997, effective Sep 4, 1997
McDonnell Douglas Model DC-9-80 Series Airplanes and Model MD-88 Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires visual/dye penetrant and ultrasonic inspections to detect cracks in the vertical leg of the rear spar lower cap of the wings, and various follow-on actions. This amendment is prompted by the necessity to provide the current address of the FAA office that receives the results of reporting requirements of this AD. The actions specified in this AD are intended to prevent fatigue cracking in the vertical leg of the rear spar lower cap of the wing, which, if not detected and corrected in a timely manner, could result in loss of the spar cap, and consequent damage to the spar cap web and adjacent wing skin structure; this condition could lead to reduced structural integrity of the wing.
AD 97-16-07 · published Aug 20, 1997, effective Sep 24, 1997
Saab Model SAAB 2000 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the existing fire, tailpipe, and bleed-air overheat detector control units with new, improved units. This amendment is prompted by reports indicating that false engine and auxiliary power unit (APU) fire warnings were issued from the fire detector control units due to moisture or induced voltages of the detector control unit. The actions specified by this AD are intended to prevent such false fire warnings, which could result in unnecessary diversion of the airplane, and resultant increased risks to the airplane, passengers, and crew, and the potential for an overweight landing.
AD 97-17-02 · published Aug 20, 1997, effective Sep 4, 1997
Boeing Model 777-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive torquing of the bushing retainer nuts of the pivot pins in the horizontal stabilizer hinge assembly to tighten loose nuts to the new torque value; and repetitive visual inspections, if necessary, to detect bushing migration or damage to adjacent structures, and repair of any damage. This proposal also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by a report of a loose bushing retainer nut, which may be attributed to low nut torque. The actions specified in this AD are intended to detect and correct loose bushing retainer nuts of the pivot pins in the horizontal stabilizer hinge assembly, which could result in bushing migration and consequent damage to the adjacent structure, and reduced controllability of the airplane.
AD 97-17-08 · published Aug 21, 1997, effective Sep 24, 1997
Raytheon Aircraft Company Model 1900D Airplanes (Formerly Known as Beech Aircraft Corporation Model 1900D Airplanes)
This amendment adopts a new airworthiness directive (AD) that is applicable to Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes) that have not had the propeller removed and re-installed since factory installation. This action requires inspecting the propeller mounting bolts for the proper torque and replacing or re- torquing any propeller bolt with the wrong torque level. The manufacturer discovered some under-torqued propeller mounting bolts during factory installation of the propeller. The actions specified by this AD are intended to prevent fatigue cracking and failure of the propeller mounting bolts, which if not detected and corrected, could result in loss of the propeller.
AD 97-17-07 · published Aug 22, 1997, effective Oct 3, 1997
Aviat Aircraft, Inc. Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes (Formerly Known as Pitts Models S- 1S, S-1T, S-2, S-2A, S-2S, and S-2B Airplanes)
This amendment revises AD 96-12-03, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating either part number (P/N) 76090, 2-2107-1, or 1-210-102. That AD currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12-03. Aviat recently started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes. This AD retains the requirements of AD 96-12- 03, but exempts airplanes that had the modified aft lower fuselage wing attach fittings incorporated at manufacture. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.
AD 97-18-07 · published Aug 29, 1997, effective Oct 3, 1997
Raytheon Model BAe 125-800A Series Airplanes, and Model Hawker 800 and Hawker 800XP Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A series airplanes, and Model Hawker 800 and 800XP series airplanes, that requires modification of the rudder. This amendment is prompted by a report indicating that, due to the existing design of the rudder, overbias or overbalance of the rudder occurs during single engine handling. The actions specified by this AD are intended to prevent overbias or overbalance of the rudder, which could result in reduced controllability of the airplane.
AD 97-18-09 · published Aug 29, 1997, effective Oct 3, 1997
Airbus Model A310 and A300-600 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A310 and A300-600 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) that warns the flight crew of certain consequences associated with overriding the autopilot when it is in the pitch control axis. That AD also requires modification of certain flight control computers (FCC). That AD was prompted by the results of an FAA review of the requirements of an earlier AD. This amendment requires a modification to the autopilot that would enable the flight crew to disconnect the autopilot when direct force is applied to the control column, regardless of its mode and the altitude of the airplane; accomplishment of that modification terminates the current requirement to revise the AFM. This amendment also requires repetitive operational testing of the modified autopilot to determine if the disconnect function operates properly, and repair, if necessary. The actions specified by this AD are intended to prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which could severely reduce controllability of the airplane.
AD 97-16-02 · published Aug 1, 1997, effective Aug 18, 1997
Robinson Helicopter Company Model R44 Helicopters
This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires inspections of the belt tension actuator switches (up-limit switches) for proper operation, and replacement if necessary; and replacement of a certain part-numbered clutch assembly. This amendment is prompted by six occurrences of prematurely worn sprag clutches. The actions specified in this AD are intended to prevent failure of the sprag clutch to lock in the driving direction, which would result in loss of power to the main rotor system and a subsequent forced landing; or failure of the sprag clutch to unlock in the overrunning direction, which, if combined with engine failure, would result in an inability to autorotate and a subsequent loss of control of the helicopter.
AD 97-17-06 · published Aug 20, 1997, effective Sep 24, 1997
Bell Helicopter Textron, Inc. Model 214ST Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST helicopters, that requires replacement of each emergency float inflation solenoid valve (valve). This amendment is prompted by two inadvertent inflations of emergency float systems that resulted from self- activations of the valves. The actions specified by this AD are intended to prevent self-activation of the valves, and subsequent inadvertent inflation of the emergency float system, which could lead to loss of control of the helicopter.
AD 97-05-11 R1 · published Aug 1, 1997, effective Aug 18, 1997
AlliedSignal Inc. ALF502 and LF507 Series Turbofan Engines
This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that currently requires initial and repetitive inspections of the oil system chip detectors and oil filter bypass valve, and optional installation of an improved oil filter bypass valve, to ensure the integrity of the reduction gear system and overspeed protection system. This amendment adds an initial inspection threshold for the oil maintenance requirements that was inadvertently omitted from AD 97-05- 11, and makes editorial corrections. Paragraphs (b) through (f) of AD 97-05-11 have been rearranged in this AD to make these corrections. This amendment is prompted by the inadvertent omission of the initial inspection threshold. The actions specified by this AD are intended to prevent No. 4 and 5 duplex bearing failure, which can result in a Stage 4 low pressure turbine (LPT) rotor failure, an uncontained engine failure, and damage to the aircraft.
AD 97-11-51 R1 · published Aug 7, 1997, effective Aug 7, 1997
Pratt & Whitney PW2000 Series Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney PW2000 series turbofan engines. This action revises telegraphic AD T97-11-51 that currently supersedes AD 97-09-01 by correcting errors in the Serial Number (S/N) tables, and removing the McDonnell Douglas C-17 aircraft from the applicability section, as a different model engine is installed on McDonnell Douglas C-17 aircraft. In addition, that telegraphic AD clarifies that inspections must be performed prior to rework, and clarifies that new parts do not need to be reworked prior to installation, but must be reworked at the next shop visit. Finally, that telegraphic AD makes minor editorial changes for clarity without changing meaning or intent. This action relaxes the compliance intervals for rework and provides relieving requirements. This amendment is prompted by industry input and resulting changes by the manufacturer to the inspection program that would provide relief to operators while maintaining an equivalent level of safety. The actions specified by this AD are intended to prevent fracture of the first stage high pressure turbine (HPT) disk, resulting in a possible uncontained engine failure and damage to the aircraft.
AD 97-17-05 · published Aug 25, 1997, effective Sep 9, 1997
Pratt & Whitney Canada PW100 Series Turboprop Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada PW100 series turboprop engines. This action requires a visual inspection of the two gas generator case drain ports to ensure that they are connected to drain lines or capped in accordance with the applicable aircraft installation configuration. This amendment is prompted by a report of a nacelle fire. The actions specified in this AD are intended to prevent a nacelle fire caused by fluid leaking from the gas generator case drain ports.
AD 97-17-04 · published Aug 26, 1997, effective Sep 30, 1997
Pratt & Whitney JT8D-200 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that currently requires cleaning of front compressor front hubs (fan hubs); initial and repetitive eddy current (ECI) and fluorescent penetrant inspections (FPI) of tierod and counterweight holes for cracks; removal of bushings; the cleaning and ECI and FPI of bushed holes for cracks; and, if necessary, replacement with serviceable parts. In addition, the current AD requires reporting the findings of cracked fan hubs. This amendment does not change the current AD's inspection procedures, or the effectivity date that starts the cycle count for the initial inspection schedules. This AD does, however, add an additional inspection schedule that requires the initial inspection of certain fan hubs with standard drilled holes and coolant channel drilled (CCD) holes to occur earlier than the existing AD requires. Also, this AD requires reporting the results of the initial fan hub inspections. This amendment is prompted by additional investigation since publication of the current AD that reveals that certain fan hubs with standard drilled holes and CCD holes may be more susceptible to cracking. The actions specified by this AD are intended to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and damage to the aircraft.
AD 97-18-02 · published Aug 27, 1997, effective Sep 11, 1997
Hartzell Propeller Inc. ( )HC-( )(2,3)(X,V)( )-( ) Series and HA-A2V20-1B Series Propellers With Aluminum Blades
This amendment supersedes four existing airworthiness directives (ADs), applicable to Hartzell Propeller Inc. ( )HC-( )(2,3)(X,V)( )-( ) series propellers with aluminum blades, that currently require inspections for cracks in blade shanks and clamps. This amendment requires initial and repetitive dye penetrant and eddy current inspections of the blade and an optical comparator inspection of the blade retention area, and, if necessary, replacement with serviceable parts. In addition, this AD requires initial and repetitive visual and magnetic particle inspection of the blade clamp, dye penetrant inspection of the blade internal bearing bore, and, if necessary, replacement with serviceable parts. Also, for all HC- (1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, this AD requires an additional initial and repetitive visual and magnetic particle inspection of the hub and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracked blades, blade clamps, and hubs and reports of blade separations. The actions specified by this AD are intended to prevent blade separation due to cracked blades, hubs, or blade clamps, which can result in loss of control of the airplane.
AD 97-16-10 · published Aug 21, 1997, effective Sep 18, 1997
RAPCO, Inc. Filter, Part Numbers RA- 1J4-4, RA-1J4-6, and RA-1J4-7 From Lot Numbers 05597, 07797, and 12597
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-16-10, which was sent previously to owners of airplanes known to have RAPCO, Inc. (RAPCO) in- line pressure filters installed. This AD requires removing RAPCO filters with part numbers (P/N) RA-1J4-4, RA-1J4-6, and RA-1J4-7 that are from Lot Numbers 05597, 07797, and 12597. Recent operator reports and the manufacturer's report of several cracked filter housings on these RAPCO, Inc. in-line pressure filters prompted this AD. The actions specified by this AD are intended to prevent failure of the flight instruments during flight because of a failed in-line pressure filter, which could cause loss of control of the airplane.
AD 97-18-03 · published Aug 26, 1997, effective Sep 22, 1997
Puritan-Bennett Aero Systems Co., Cone and Seal Assemblies, Part Numbers 210543 and 210543-01
This amendment adopts a new airworthiness directive (AD) that applies to Puritan-Bennett Aero Systems Co. (Puritan-Bennett) cone and seal assemblies, part numbers 210543 and 210543-01, that were manufactured or repaired from August 1996 through July 1997. This AD applies to cone and seal assemblies regardless of whether or not they are attached to certain Puritan-Bennett sweep-on crew masks. The AD requires replacing any cone and seal assembly manufactured or repaired during the above time frame. This AD results from quality control tests that show that these cone and seal assemblies could have faulty ultrasonic welds. The actions specified by this AD are intended to prevent failure of the ultrasonic weld on the cone and seal assembly of the oxygen mask with consequent reduced oxygen flow through the mask, which could result in the crew not being able to obtain oxygen in an emergency situation.
AD 97-15-07 · published Aug 5, 1997, effective Aug 15, 1997
Aeromot-Industria Mecanico Metalurgica Ltda. Model AMT-200 Powered Sailplanes
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-07, which was sent previously to all known U.S. owners and operators of Aeromot-Industria Mecanico Metalurgica Ltda. (Aeromot) Model AMT-200 powered sailplanes. This AD requires immediately inspecting, using non-destructive testing (NDT) methods, the forward horizontal stabilizer front bolt, P/N 53451, for defects (scratches, damaged threads, or surface cracks, etc.), and replacing the bolt immediately if found defective or at a certain time period if not found defective. This AD was the result of a failure of the forward horizontal stabilizer bolt, part number (P/N) 53451, on one of the affected powered sailplanes. This failure was caused by a low cycle fatigue crack that was induced by overtorquing the bolt. The actions specified by this AD are intended to prevent failure of the forward horizontal stabilizer bolt, which could result in separation of the horizontal stabilizer from the powered sailplane and consequent loss of control.
