Results
2012-15-01: We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a deviation in the manufacturing process of fuel hoses installed on the pressure side of part number 893114 fuel pumps. The fuel hoses may not be fuel resistant, which could lead to detachment of particles from the fuel hose and cause irregularities in the carburetor function and possibly result in rough engine operation, engine misfire, in-flight engine shutdown, and forced landing. We are issuing this AD to require actions to address the unsafe condition on these products.
76-03-02: 76-03-02 SIKORSKY AIRCRAFT: Amendment 39-2507. Applies to S-61L, S-61N, S- 61NM, and S-61R helicopters certified in all categories including Military CH-3C, HH-3C, CH- 3E, and HH-3E helicopters using NAS 577-10 or NAS 577-10A barrel nuts for attaching the transmission main gearbox to the fuselage structure. Compliance required as indicated. To prevent fractures in the attaching nuts accomplish the following: Remove the NAS 577-10 or NAS 577-10A barrel nuts and replace with RMLH 2577-108 barrel nuts within the next 30 days after the effective date of this AD, unless already accomplished. (NOTE: Sikorsky Service Bulletin No. 61B35-36B covers this subject.) This supersedes Amendment 39-2202 (40 FR 24355), AD 75-12-13. This amendment becomes effective February 17, 1976.
99-07-17: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-07-17 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (RHC) Model R22 helicopters by individual letters. This AD requires, before further flight, inserting a Special Pilot Caution into the Normal Procedures section of the Rotorcraft Flight Manual (RFM). This amendment is prompted by several reports of sprag clutch assemblies with cracked or fractured sprag ends. The sprag clutch failures, determined to be due to a change in the manufacturing process, could result in loss of main rotor revolutions-per-minute (RPM) during autorotations. The intent of this AD is to alert pilots of the potential for the sprag clutch failing to overrun during autorotation, loss of main rotor RPM, and subsequent loss of control of the helicopter.
2003-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time mid-frequency eddy current (MFEC), a low-frequency eddy current (LFEC), and a detailed inspection for damage or cracking of stringer S-4L and S-4R lap joints and stringer clips between body station (BS) 540 and BS 727, and follow-on inspections and repair if necessary. This action is necessary to find and fix cracking of the fuselage lap joints, which could result in sudden decompression of the airplane.
2012-15-06: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Astra SPX, 1125 Westwind Astra, and Gulfstream 100 airplanes. This AD was prompted by a report indicating that sponge rubber padding was found between wheel well fuel lines and electrical harnesses. This AD requires inspecting for the presence of sponge rubber padding and for proper separation of the fuel lines and electrical harnesses in the wheel well area, and corrective actions if necessary. We are issuing this AD to detect and correct corrosion or chafing of the fuel lines, which could result in fuel leakage and possible fire in the wheel well area.
99-08-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-100, -200, and -300 series airplanes, that requires modification of the flight compartment door; repetitive inspections for wear of the flight compartment door hinges following modification; and repair or replacement of the hinges with new hinges, if necessary. This amendment is prompted by a report that the door lock mechanism of the flight compartment door jammed and could not be opened using the alternate release mechanism. The actions specified by this AD are intended to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during an emergency. Such failure also could result in the flightcrew not being able to assist passengers in the event of an emergency.
99-08-06: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SE. 3160, SA. 316B, SA. 316C, and SA. 319B helicopters. This action requires inspecting the spar skin and main rotor blade (blade) root reinforcement strip area for a bonding separation, corrosion, or a crack, and replacing the blade, if necessary. This amendment is prompted by the in-flight failure of a blade. The actions specified in this AD are intended to detect a bonding separation, corrosion, or a crack in the area of the blade root reinforcement strip, which could result in failure of the blade and subsequent loss of control of the helicopter.
2012-15-04: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC155B1 helicopters with a certain automated flight control system installed. This AD requires changing the minimum required crew for instrument flight rules (IFR) operations from one pilot to two. This AD is prompted by a report that an EC155B1 helicopter experienced significant intermittent roll oscillations while coupled to the autopilot. These actions are intended to decrease the pilot's workload while experiencing any oscillations during landing, which could result in possible loss of control of the helicopter.
74-20-10: 74-20-10 LEIGH SYSTEMS: Amendment 39-1976 as amended by Amendment 39-2038, 39-2732, and 39-3000 is further amended by Amendment 39-3104. Emergency Locator Transmitter Leigh Systems Sharc 7 Series. Applies to all Leigh Systems Sharc 7 Emergency Locator Transmitters Serial Numbers all through 163500 equipped with lithium batteries. \n\n\tCompliance required as indicated. \n\n\tAs a result of chemical corrosion resulting in either failure of the Emergency Locator Transmitter (ELT) to operate or inadvertent activation, jamming the emergency frequencies of 121.5 MHz and 243.0 MHz accomplish the following: \n\n\tWithin the next 90 days and thereafter at each additional 60 day interval after the effective date of this Airworthiness Directive, accomplish the following: \n\n\t1.\tDeleted. \n\n\t2.\tConduct a visual inspection for evidence of corrosion in accordance with photo reproduction which is part of Leigh System's Service Bulletin No. 003A, dated May 15, 1974, or equivalent inspections approved by Chief, Engineering and Manufacturing Branch, FAA Eastern Region. \n\n\t3.\tIf no corrosion is found, prior to reinstalling, determine ELT transmits properly. ELT transmissions are authorized in the first five minutes of any hour or at other times if coordinated with the nearest FAA Tower or Flight Service Station for a total of three audio sweeps (Ref. FAA Advisory Circular 00-35A or 20-81). \n\n\t4.\tIf corrosion is found or if the ELT does not transmit properly, replace with an approved serviceable unit which has been inspected in accordance with paragraph 2; or replace with another TSO approved unit, prior to the next flight except that a ferry flight may be conducted in accordance with FAR 91.52(e)(2). \n\n\tNOTE: ELT's equipped with lithium batteries may be identified by inspecting the identification tags. Units marked in the weight range of 1.5 to 2.0 lbs. are lithium batteries. \n\n\tAmendment 39-1976 was effective October 1, 1974. \n\n\tAmendment 39-2038 was effective December 9, 1974. Amendment 39-2732 was effective September 29, 1976. \n\n\tAmendment 39-3000 was effective August 10, 1977. \n\n\tThis Amendment 39-3104 is effective December 30, 1977.
2012-14-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD was prompted by reports of hydraulic accumulator screw cap or end cap failure. This AD requires replacing the affected parking brake accumulator. We are issuing this AD to prevent failure of the parking brake accumulator screw caps or end caps, which could result in loss of the number 2 hydraulic system and damage to airplane structures, and could potentially have an adverse effect on the controllability of the airplane.
2012-13-11: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 (all versions) and BO-105LS A-3 helicopters. This AD requires inspecting the tail rotor pitch link spherical bearing for proper swaging. This AD is prompted by a report of a tail rotor pitch link with a spherical bearing that had migrated out of the bearing bore. The actions specified by this AD are intended to prevent failure of the tail rotor pitch link and subsequent loss of control of the helicopter.
75-24-13: 75-24-13 MCCAULEY PROPELLERS: Amendment 39-2435. Applies to the two- bladed constant speed and full feathering Model D2AF34C52/ 80GF-0 and D2AF34C52A/80GF- 0 series propellers having hub serial numbers 63000 through 659999, installed on but not limited to Cessna 310I type aircraft. Compliance required as indicated, unless already accomplished. To prevent hub failures, accomplish the following: A. Propellers with 1500 or more total hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) within the next 100 hours in service after the effective date of this AD. B. Propellers with less than 1500 hours in service as of the effective date of this Airworthiness Directive must be inspected and modified in accordance with Paragraph (D) prior to the accumulation of 1600 hours in service. C. Propellers whose total hours in service are unknown will be assumed to have 1500 hours minimum and thus fall within the requirements for inspection and modification in accordance with Paragraph (A). D. Remove propeller from the aircraft, disassemble, inspect components and replace the hub in accordance with McCauley Service Manual No. 710930 and Bulletin No. 111 dated August 11, 1975, or later Federal Aviation Administration approved revisions, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. The manufacturer's specifications and procedures identified in this Directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this Directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this Airworthiness Directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Great Lakes Region. This amendment becomes effective November 26, 1975.
2012-14-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports of some fuselage nuts found cracked. This AD requires an inspection to determine if certain fuselage nuts are installed, a detailed inspection for cracking of fuselage nuts having a certain part number, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity of the airplane.
2018-05-03: We are adopting a new airworthiness directive (AD) for certain Safran Helicopter Engines, S.A., Arrius 2F turboshaft engines. This AD requires inspection and replacement of the magnetic heads installed on oil system electrical magnetic plugs. This AD was prompted by reports from the manufacturer of a batch of non-conforming magnetic heads installed on electrical magnetic plugs. We are issuing this AD to address the unsafe condition on these products.
2012-14-15: We are adopting a new airworthiness directive (AD) for certain aircraft equipped with Honeywell International, Inc. Model KGS200 Mercury\2\ wide area augmentation system (WAAS) global navigation satellite sensor units (GNSSU). This AD requires you cease all localizer performance (LP), localizer performance with vertical guidance (LPV), and satellite based augmentation system (SBAS) lateral navigation/vertical navigation (LNAV/VNAV) approaches until a software problem is corrected. This AD was prompted by a report and follow-up investigation of a software problem that occurred during flight test trials of SBAS-capable aircraft using a similar Honeywell global positioning system (GPS) sensor and the same software as the Model KGS200 Mercury\2\ GNSSU. A software problem occurred that could result in misleading information during LP, LPV, or SBAS LNAV/VNAV approaches. We are issuing this AD to correct the unsafe condition on these products.
2003-08-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires a one-time inspection for chafing of the RDB wire bundle against the No. 2 automatic direction finder (ADF) receiver located at the aft end of the forward right radio rack; repair or replacement, if necessary; and modification of the wire bundle. The actions specified by this AD are intended to prevent chafing of the RDB wire bundle against the No. 2 ADF receiver, which could result in electrical arcing and consequent smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
47-34-02: 47-34-02 BEECH: (Was Mandatory Note 3 of AD-770-1 and Mandatory Note 4 of AD- 765-1.) Applies to D18S, D18C and D18C-T Airplanes Which Do Not Have Drain Provisions at Bulkhead No. 15. Compliance required prior to December 1, 1947. To provide additional drainage, to prevent freezing of trapped moisture in the tail cone which could jam the elevator control system, a 3/4-inch diameter hole should be drilled near the front of the tail cone outer section on the centerline of the lower surface. A suitable marine grommet should be installed to provide for negative pressures. Also a 1/2-inch diameter hole should be drilled on each side of the jack pad through the lower part of bulkhead No. 15. (Beech Service Bulletin D18-46 covers this same subject.)
2021-18-15: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report that displaced teeth were detected on the moveable assemblies of a main rotor (MR) blade droop stop. This AD requires removing from service the moveable assemblies from each affected MR blade droop stop and prohibits installation of an affected MR blade droop stop and moveable assemblies of affected MR blade droop stops. The FAA is issuing this AD to address the unsafe condition on these products.
2012-13-10: We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W-3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). This AD is prompted by an incident where cyclic control stick movement was restricted due to rotation of a loose collector, resulting in locking of the longitudinal control system hydraulic actuator fork end. These actions are intended to prevent rotation of the collector, which could lead to restricted cyclic control stick movement, and subsequent loss of control of the helicopter.
99-06-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. This AD requires repetitively inspecting the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5, and immediately repairing any area found cracked. This repair will eliminate the need for the repetitive inspections on that particular wing spar. This AD is the result of reports of cracks in the wing spar center web cutout caused by fatigue due to airplane maneuvering and wind gusts. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
2003-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This action requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. This action also provides for two optional terminating actions for the detailed inspection(s). This action is necessary to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam of the wing flap systems, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded. Loss or warping of the flap vane in flight could decrease the lift on one side of the airplane, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
67-32-01: 67-32-01 BRITISH AIRCRAFT CORP: Amendment 39-573. Applies to BAC 1-11 Airplanes Model/Type 212AR, 401AK, 410AQ, which have a center fuel tank fitted with Thompson Ramo fuel pumps P/N 248800/4, P/N 248800/5 or pumps manufactured under license by Plessey which include additional part number 570/1/21221/004. Amendment 39-522 (32 F.R. 17515), AD 67-32-1, is amended. Compliance required as indicated. To prevent fuel pump movement and consequent fuel leakage, accomplish the following: (a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, inspect the center tank fuel pump installation in accordance with BAC 1-11 Alert Service Bulletin 28-A-PM 2701, Issue 2, or later ARB-approved issue, or FAA- approved equivalent. (b) If leaks are found when conducting the inspection required by paragraph (a), before further flight stop the leaks by repositioning the fuel booster pump and, if necessary, replacing the seals between the pump and canister. (c) Within the next 1,000 hours' time in service after the effective date of this AD, modify the center tank fuel booster pumps in accordance with British Aircraft Corporation Service Bulletin No. 28-PM 2701 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, European Region. This amendment becomes effective May 2, 1968.
2012-13-12: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-IV, GIV-X, GV, and GV-SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
99-06-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, that requires modification of the P212 and P213 panels of the cabin pressure control system. For certain airplanes, this amendment also requires modification of the P5, P6, and P7 panels, and the W4701, W4703, and W4908 wire bundles, as applicable. This amendment is prompted by a report of in-flight loss of cabin pressurization control due to a single failure of the auxiliary power unit (APU) battery. The actions specified by this AD are intended to prevent loss of control of the cabin pressurization system, which could result in rapid depressurization of the airplane. Such rapid depressurization could result in deleterious physiological effects on the passengers and crew; and airplane diversions, which represent an increased risk to the airplane, passengers, and crew.
2012-13-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report indicating that a fire originated near the first officer's area, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen hose internal anti-collapse spring, which can cause the low-pressure oxygen hose to melt or burn, and a consequent oxygen-fed fire in the flight compartment.