34 Airworthiness Directives: 26 airplane, 3 rotorcraft, 4 engine, 1 glider.
AD 2003-17-09 · published Sep 2, 2003, effective Oct 7, 2003
Aerospatiale Model ATR42-500 and ATR72 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 and ATR72 series airplanes, that requires inspecting the wire bundle in the area of electrical rack 90VU to detect damage, verifying that the conduit around the wire bundle is in the proper position, and installing a clamp between the wire bundles and the carbon shelves structure. This action is necessary to prevent chafing of a wire bundle, which could result in an electrical short and potential loss of several functions essential for safe flight. This action is intended to address the identified unsafe condition.
AD 2003-17-12 · published Sep 2, 2003, effective Oct 7, 2003
McDonnell Douglas Model MD-11 and MD-11F Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires a one-time visual inspection of the circuit breakers to determine if discrepant circuit breakers are installed, and corrective action if necessary. This action is necessary to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
AD 2003-17-13 · published Sep 2, 2003, effective Oct 7, 2003
Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This AD requires replacement of the elevator stop bumpers of the horizontal stabilizer with new bumpers. The actions specified by this AD are intended to prevent damage to the elevator trailing edge due to a broken or missing elevator stop bumper, which could result in jamming of the spring tab and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-17-14 · published Sep 2, 2003, effective Oct 7, 2003
Airbus Model A300 B2 and B4; A300 B4-600, A300 B4-600R, and A300 F4-600R (Collectively Called A300-600); A310; A319; A320; A321; A330; and A340 Series Airplanes; Equipped With PPG Aerospace Windshields
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4; A300 B4-600, A300 B4-600R, and A300 F4-600R (collectively called A300-600); A310; A319; A320; A321; A330; and A340 series airplanes; equipped with certain PPG Aerospace windshields. This AD requires replacement of certain windshields manufactured by PPG Aerospace with new windshields. This action is necessary to prevent failure of both structural plies of the windshield caused by overheating of the power lead wire, which could cause reduced structural integrity of the windshield assembly, and consequent loss of the windshield during flight. This action is intended to address the identified unsafe condition.
AD 2003-17-16 · published Sep 2, 2003, effective Oct 10, 2003
Robert E. Rust Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Robert E. Rust (R.E. Rust) Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes. This AD requires you to repetitively inspect the tailplane attachment brackets and replace each bracket at a specified time. This AD also requires you to repetitively inspect each joint of the port and starboard engine mount frame and the rear upper mount frame tubes for cracks and/or damage and repair any cracks and/or damage found. This AD is the result of reports of stress corrosion cracking found on the tailplane attachment brackets and fatigue cracking and chaffing of the engine mount frame. The actions specified by this AD are intended to prevent failure of the tailplane attachment brackets caused by stress corrosion cracking and failure of the engine mount, which could result in loss of the tail section and separation of the engine from the airplane respectively. Such failures could lead to loss of control of the airplane.
AD 2003-18-01 · published Sep 3, 2003, effective Sep 18, 2003
General Dynamics (Convair) Model P4Y-2 Airplanes, General Dynamics (Consolidated-Vultee) (Army) Model LB-30 Airplanes, and General Dynamics (Consolidated) (Army) Model C-87A Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to various surplus military airplanes manufactured by Consolidated, Consolidated Vultee, and Convair, that currently requires repetitive inspections to find fatigue cracks in the lower rear cap of the wing front spar, front spar web, and lower skin of the wings; repair or replacement of any cracked part with a new part; and follow- on inspections at new intervals. This amendment continues to require those actions and revises and clarifies the applicability of the existing AD. The actions specified in this AD are intended to find and fix fatigue cracking, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-18-02 · published Sep 5, 2003, effective Oct 10, 2003
Airbus Model A330 and A340 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires, among other actions, a detailed inspection of the rudder travel limitation unit for proper adjustment, measurement of the desynchronization of rudder servo-controls, installation of rigging placards for rudder servo-controls, and follow-on and corrective actions if necessary. This action is necessary to prevent desynchronization of the rudder servo-controls, which could result in high load factors on the rudder servo-controls, and consequent reduced structural integrity of the attachment fittings for the rudder servo- controls. This action is intended to address the identified unsafe condition.
AD 2003-18-07 · published Sep 10, 2003, effective Oct 15, 2003
Aerospatiale Model ATR42-200, -300, -320, and -500 Series Airplanes; and Model ATR72 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all Aerospatiale Model ATR42-200, -300, -320, and - 500 series airplanes; and all Model ATR72 series airplanes; that currently requires revising the Airplane Flight Manual (AFM) to modify procedures for calculating takeoff performance when Type II or IV de- icing or anti-icing fluids have been used. This amendment requires revising the existing AFM revision to correct the performance values for Model ATR-72 series airplanes and to provide an additional method of compliance for all airplanes. This amendment is prompted by issuance of mandatory continuing airworthiness information by a civil aviation authority. The actions specified by this AD are intended to ensure that the flightcrew is advised of the potential effects of Type II or IV de- icing or anti-icing fluids on the airplane's performance during takeoff, and to ensure that the flightcrew is advised of the revised performance calculations for takeoff to address these effects.
AD 2003-18-05 · published Sep 11, 2003, effective Oct 16, 2003
Boeing Model 757 Series Airplanes Powered by Pratt & Whitney Engines
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires modification of the nacelle strut and wing structure. This amendment reduces a certain compliance time in the existing AD. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut. This action is intended to address the identified unsafe condition.
AD 2003-18-06 · published Sep 11, 2003, effective Oct 16, 2003
Airbus Model A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319-131 and -132; A320-231, -232, and -233; and A321-131 and -231 series airplanes, that requires installing new anti-swivel plates and weights on the engine fan cowl door latches and a new hold-open device. This action is necessary to prevent separation of the engine fan cowl door from the airplane in flight, which could result in damage to the airplane and hazards to persons or property on the ground. This action is intended to address the identified unsafe condition.
AD 2003-18-08 · published Sep 11, 2003, effective Oct 16, 2003
Airbus Model A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires electrical conductivity testing to verify the correct heat treatment of the two half fittings holding the ejection jack for the ram air turbine (RAT). This action is necessary to prevent decreased structural integrity of the two half fittings and loss of the RAT during extension, which could lead to reduced controllability of the airplane in the event of a dual engine failure, or in the event of loss of two or all hydraulic systems. This action is intended to address the identified unsafe condition.
AD 2003-18-10 · published Sep 11, 2003, effective Oct 16, 2003
Boeing Model 767-200, -300, -300F, and -400ER Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires revising the Airworthiness Limitations Section of the Maintenance Planning Data (MPD) Document (767 Airworthiness Limitations Instructions (ALI)). The revision incorporates into the ALI certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSE). This amendment expands the applicability in the existing AD, and requires incorporating a new revision into the Airworthiness Limitations Section of the MPD Document. The actions specified by this AD are intended to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
AD 2003-18-11 · published Sep 11, 2003, effective Sep 26, 2003
Gulfstream Model G-V Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection of the balance weight installation of the left and right ailerons for correctly installed attachment components, and corrective action if necessary. This action is necessary to prevent separation of the balance weights of the aileron, which could result in jamming of the pilot's aileron control system, subsequent loss of aileron control, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-14-02 · published Sep 17, 2003, effective Aug 14, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This document corrects typographical errors that appeared in airworthiness directive (AD) 2003-14-02 that was published as a final rule; correction in the Federal Register on August 15, 2003 (68 FR 48783). The typographical errors resulted in an incorrect AD number and effective date. This AD is applicable to certain Bombardier Model CL- 600-2B19 (Regional Jet series 100 & 440) airplanes. This AD requires a one-time inspection of the aft edge of the left and right main windshields to determine whether a certain placard is installed, and corrective actions if necessary.
AD 2003-09-04 R1 · published Sep 22, 2003, effective Oct 7, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes
This amendment revises an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet series 100 & 440) airplanes, that currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness by incorporating new structural inspection intervals for the pressure floor skin of the center fuselage at fuselage stations 460 and 513; repair if necessary; and submission of inspection findings to the airplane manufacturer. This amendment terminates the reporting requirement and includes a provision to allow removal of the referenced service information when the information specified in it is included in the general revisions of the maintenance manual. The actions specified in this AD are intended to detect and correct in a timely manner fatigue cracks of the pressure floor skin of the center fuselage at fuselage stations 460 and 513, which could result in failure of the pressure floor skin and consequent rapid decompression of the airplane during flight. This action is intended to address the identified unsafe condition.
AD 2003-19-03 · published Sep 22, 2003, effective Oct 27, 2003
Dornier Model 328-100 and -300 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspection of the nose landing gear (NLG) and main landing gear (MLG) to ensure that certain bolts are in place; repetitive inspections of the bolts and bolt areas for evidence of corrosion; and corrective action, if necessary. This action is necessary to prevent failure of the NLG or MLG due to corroded or missing bolts, which could cause loss of connection pins, and consequent collapse of the landing gear during ground maneuvers or upon landing. This action is intended to address the identified unsafe condition.
AD 2003-19-04 · published Sep 22, 2003, effective Oct 27, 2003
Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 440) Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 440) airplanes, that requires, for certain airplanes, a one- time inspection to detect chafing or other damage of the integrated drive generator (IDG) cables and the firewall separators of the pylon, and corrective action if necessary. For other airplanes, this AD requires identification of the part number of the clamps, and replacement with new clamps if necessary. The actions specified by this AD are intended to prevent electrical arcing between the IDG cables and the firewall separators due to chafing, which could result in an in- flight fire and/or loss of electrical power. This action is intended to address the identified unsafe condition.
AD 2003-19-08 · published Sep 22, 2003, effective Oct 27, 2003
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections for discrepancies of certain areas of the forward and aft sides of the body station 2598 bulkhead, and repair if necessary. This action is necessary to find and fix such discrepancies of the bulkhead structure, which could result in failure of the structure to carry flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-19-09 · published Sep 22, 2003, effective Oct 27, 2003
Boeing Model 767 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive inspections and tests for discrepancies of the drainage system of the canted pressure deck located in the wheel wells of the main landing gear (MLG) of the left and right wings, and corrective actions if necessary. This action is necessary to prevent ice accumulation on the lateral flight control cables and/or components due to water entering the wheel well of the MLG and freezing, which could restrict or jam control cable movement, resulting in loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-19-02 · published Sep 23, 2003, effective Oct 8, 2003
Boeing Model 777 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires inspections of the outboard leading edge slats on the wings for installation of seal assemblies with undersized seal inserts and missing or gapped inserts, and follow-on and corrective actions if necessary. This action also provides for an optional replacement of the seal assembly in lieu of the inspections. This action is necessary to find and fix such discrepancies, which could result in cracking of the slats, subsequent separation of the cove skin, structural damage or loss of the trailing edge wedge, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-19-07 · published Sep 23, 2003, effective Nov 3, 2003
Eagle Aircraft (Malaysia) Sdn. Bhd. Model 150B Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Eagle Aircraft (Malaysia) Sdn. Bhd. (Eagle) Model 150B airplanes. This AD requires you to modify the canard rear spar and the rear spar attachment bracket. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. The type design responsibility has been transferred from Australia to Malaysia since the release of the MCAI. The actions specified by this AD are intended to prevent detachment of the rear spar bracket from the canard rear spar, which could result in failure of the canard rear spar. Such failure could lead to loss of control of the airplane.
AD 2003-19-10 · published Sep 23, 2003, effective Nov 7, 2003
Fairchild Aircraft, Inc., SA226 Series and SA227 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Fairchild Aircraft, Inc. (Fairchild Aircraft) SA226 and SA227 series airplanes. This AD requires you to inspect the fuel boost pump wiring for any chafing, cracked insulation material, or evidence of bare wire(s) (referred to herein as damage), and replace any damaged wiring. This AD also requires you to install protective tubing around the fuel boost pump wiring harness. This AD is the result of reports of chafed fuel boost pump wiring to either the inboard or outboard boost pump wiring. The actions specified by this AD are intended to prevent the fuel boost pump wiring from chafing, which could result in electrical arcing. This could serve as an ignition source inside the fuel tank and result in fire or explosion.
AD 2003-19-11 · published Sep 29, 2003, effective Nov 3, 2003
Learjet Model 60 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Learjet Model 60 airplanes, that currently requires inspection to detect bends in or damage to the fuel crossflow tube; inspection to determine clearance between the fuel crossflow tube and the flight control cables; and replacement or repair of the tube, if necessary. This amendment requires a review of airplane maintenance records or an inspection to determine if a fuel crossflow tube having a certain part number is installed; and follow-on/corrective actions, as applicable. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent chafing and consequent failure of the fuel crossflow tube due to inadequate clearance between the tube and the flight control cables, which could result in loss of fuel from one fuel tank during normal operating conditions or loss of fuel from both main fuel tanks during fuel cross-feeding operations. This action is intended to address the identified unsafe condition.
AD 2003-20-01 · published Sep 29, 2003, effective Sep 29, 2003
Airbus Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes, and Airbus Model A310 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600, B4-600R, and F4- 600R (collectively called A300-600) series airplanes, and Airbus Model A310 series airplanes, that currently requires replacement of Honeywell inertial reference units (IRU) with new or modified Honeywell IRUs. For certain airplanes, that existing AD also requires replacement of Litton IRUs, mode selector units (MSU), and an inertial sensor display unit (ISDU) with new Honeywell IRUs, MSUs, and a new ISDU. This amendment removes the requirement to replace the Litton IRUs, MSUs, and ISDU with Honeywell IRUs, MSUs, and ISDU. This amendment also allows the use of certain Honeywell IRUs as spare parts until the final compliance date of this AD. The actions specified in this AD are intended to prevent loss of positioning data and a display of incorrect attitude data, which could compromise the ability of the flightcrew to maintain the safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
AD 2003-19-13 · published Sep 30, 2003, effective Nov 11, 2003
Grob-Werke Model G120AA Airplanes
The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to modify the flight control system operating levers. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent failure of a ball bearing in the flight control system operating levers. Such failure could lead to reduced control or loss of control of the airplane.
AD 2003-20-02 · published Sep 30, 2003, effective Nov 4, 2003
Dornier Model 328-300 Series Airplanes Equipped With Certain Pratt & Whitney PW306B Engine Nacelles
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires a one-time inspection of the anti-ice tubing in the engine nacelle at the joint between the anti-ice tubing adapter and duct, and also between the joint of the anti-ice shutoff valve and the same duct, to detect any air leakage at the joints. This action is necessary to prevent an uncommanded engine shutdown in a critical phase of flight due to leakage of air from a loose clamp on the anti-ice tubing joint. This action is intended to address the identified unsafe condition.
AD 2003-18-03 · published Sep 8, 2003, effective Oct 14, 2003
Eurocopter France Model EC 155B, SA-365N and N1, AS-365N2, and AS 365 N3 Helicopters
This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the hydraulic brake hose (hose) for crazing, pinching, distortion, or leaks at the torque link hinge and replacing the hose, if necessary. This amendment also requires inspecting the hose and the emergency flotation gear pipe to ensure adequate clearance, and adjusting the landing gear leg, if necessary. This amendment is prompted by a report of a hose compression due to interference with a clamp that attaches the emergency flotation gear pipe. The actions specified by this AD are intended to prevent failure of the hose, resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel, and subsequent loss of control of the helicopter during a run-on landing.
AD 2003-19-01 · published Sep 18, 2003, effective Oct 23, 2003
Eurocopter France Model AS 365 N3 and EC 155B Helicopters
This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model AS 365 N3 and EC 155B helicopters, that requires replacing each Fenestron pitch change control rod (control rod) with an improved reinforced steel airworthy control rod. This amendment is prompted by a failure of a control rod on a prototype helicopter and by the manufacturer making available a newly-designed reinforced steel control rod. The actions specified by this AD are intended to prevent failure of the control rod, loss of control of the tail rotor, and subsequent loss of control of the helicopter.
AD 2003-19-12 · published Sep 26, 2003, effective Oct 14, 2003
Eurocopter France Model EC 155B Helicopters
This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B helicopters. This action requires, before further flight, determining whether the engine "GOV" warning light caution advisory display (display) panel illuminates the "GOV" warning lights when appropriate. If not, this AD requires replacing the front panel of the display panel with an airworthy display panel before further flight. This amendment is prompted by the discovery of some operating anomalies affecting the red "GOV" warning light due to wiring errors that occurred after modifying the electrical power systems. The actions specified in this AD are intended to prevent failure of the display to warn of an engine governor failure, resulting in an engine over speed, loss of an engine, and subsequent loss of control of the helicopter.
AD 2003-18-04 · published Sep 8, 2003, effective Sep 23, 2003
Wytwornia Sprzetu Komunikacyjnego Engines
The FAA is adopting a new airworthiness directive (AD) for Wytwornia Sprzetu Komunikacyjnego (WSK) PZL-10W turboshaft engines. This AD requires a one-time inspection of the four engine-to-gearbox pin retaining joints for loose or improperly crimped retaining nuts and damaged bolts on certain serial number engines. This AD is prompted by reports of loose or improperly crimped engine-to-gearbox pin joint retaining nuts found during overhaul. We are issuing this AD to prevent loss of nut torque and loosening of engine-to-gearbox pin joint retaining nuts, which could result in misalignment of the engine to the gearbox, causing loss of drive to the gearbox, power turbine overspeed, and uncontained power turbine disc failure.
AD 2003-18-09 · published Sep 9, 2003, effective Sep 24, 2003
Rolls-Royce plc Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines
The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan engines. This AD requires removal from service of certain part numbers of high pressure (HP) compressor rotor shafts, based on a newly established reduced life limit. This AD is prompted by reports of HP compressor drums with small cracks in blade loading slots found at overhaul inspection. The HP compressor drums are an integral part of the HP compressor rotor shaft. We are issuing this AD to prevent possible uncontained HP compressor drum failure, which could result in damage to the airplane.
AD 2003-19-06 · published Sep 17, 2003, effective Oct 22, 2003
Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 Turboshaft Engines
The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 turboshaft engines. This AD requires replacement of the gas generator high pressure (HP) turbine disk before further flight after the engine has accumulated 5 minutes of operating time at the 2\1/2\ minute one engine inoperative (OEI) power rating. This amendment is prompted by a failure of an HP turbine blade during accelerated aging simulation tests performed by the manufacturer on an Arrius 2 B1A engine. We are issuing this AD to prevent engine failure of the only operating engine while experiencing an OEI condition.
AD 2003-19-15 · published Sep 30, 2003, effective Oct 30, 2003
Pratt & Whitney PW4000 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) models PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines. That AD currently requires interim actions to address engine takeoff power loss events until the high-pressure-compressor (HPC) case is redesigned and available for incorporation on the PW4000 engines. That amendment also requires terminating actions for engines installed in the Boeing fleet by incorporating a new Ring Case Configuration (RCC) rear HPC. This amendment requires the same interim and terminating action requirements as that AD, and in addition, expands the terminating action requirements to engines installed on Airbus and McDonnell Douglas fleets. This amendment is prompted by the certification of an RCC rear HPC for PW4000 series turbofan engines installed in the Airbus fleet and McDonnell Douglas fleet. The actions specified by this AD are intended to prevent engine takeoff power losses due to HPC surge.
AD 2003-19-14 · published Sep 30, 2003, effective Oct 20, 2003
Burkhart Grob Luft-und Raumfahrt GmbH & CO KG Models G103 Twin Astir, G103 Twin II, G103A Twin II Acro, and G103C Twin III Acro Sailplanes
The FAA is adopting a new airworthiness directive (AD) for all BURKHART GROB LUFT--UND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. This AD requires you to modify the airspeed indicators and install a flight speed reduction placard and an aerobatic maneuver restriction placard (as applicable). This AD also requires you to revise the flight and maintenance manual. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the possibility of damage to the fuselage during limit load flight due to inadequate safety margins designed into the fuselage. Such a condition could result in reduced structural integrity of the fuselage and lead to loss of control of the sailplane.
