Results
2006-25-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777 airplanes. This AD requires repetitive inspections for corrosion or missing corrosion inhibiting compound of the fuselage skin under the forward and aft wing-to-body fairings for certain airplanes, or the fuselage skin under the forward wing-to-body fairings only for other airplanes; and corrective action if necessary. The AD also provides an optional preventive modification of the fairing areas, which terminates the repetitive inspections. This AD results from several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wing-to-body fairings. We are issuing this AD to detect and correct corrosion, and prevent subsequent fatigue cracks, on the fuselage skin under the forward and aft wing-to-body fairings, which could result in rapid decompression of the airplane.
2006-25-01: The FAA is superseding an existing airworthiness directive (AD) for certain IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M- A5, V2530-A5, and V2533-A5 turbofan engines. That AD currently requires initial and repetitive inspections of the master magnetic chip detector (MCD) or the No. 1, 2, 3 bearing chamber MCD. This AD requires the same MCD inspections. This AD also requires removing certain No. 3 bearings and removing certain high pressure compressure (HPC) stubshaft assemblies as mandatory terminating actions to the repetitive MCD inspections. This AD results from IAE developing a terminating action to the repetitive inspections of the chip detectors, and from expanding the applicability to include additional serial-numbered engines with certain No. 3 bearings installed. We are issuing this AD to prevent failure of the No. 3 bearing, which could result in an in-flight shutdown (IFSD) and smoke in the cockpit and cabin.
2019-11-07: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-524G2-19, RB211-524G2-T-19, RB211-524G3-19, RB211-524G3-T-19, RB211-524H2-19, RB211-524H2-T-19, RB211-524H-36 and RB211-524H-T-36 engines. This AD requires removal of affected low- pressure compressor (LPC) shafts. This AD was prompted by unauthorized repairs to the affected LPC shafts that reduced their expected life. The FAA is issuing this AD to address the unsafe condition on these products.
2019-11-01: We are superseding Airworthiness Directive (AD) 2018-25-12, which applied to certain Airbus SAS Model A350-941 airplanes. AD 2018- 25-12 required modifying the vertical tail plane (VTP) tension bolts connection by adding sealant and protective treatment to the head of the connection, at the barrel nut cavities, and in the surrounding area. Since we issued AD 2018-25-12, it was determined that the instructions for certain airplanes are unclear for proper accomplishment of the required modification. This AD, for certain airplanes, requires accomplishing a revised modification and, for certain other airplanes, retains the modification required by AD 2018- 25-12, as specified in an European Aviation Safety Agency (EASA) AD, which will be incorporated by reference. We are issuing this AD to address the unsafe condition on these products.
83-15-03: 83-15-03 PICCARD: Amendment 39-4694. Applies to Model AX-6 balloons certificated in any category. Compliance: Within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To reduce the time for pilot light extinguishment after shutoff and prevent damage to main fuel systems modified per General Balloon Corporation Service Letter No. 8 or AD 82-13- 02, accomplish the following: a) Modify P/Ns 5041-X10, 8201-23 or GBC 156 propane jet by drilling out the orifice with a #65 drill (.035 inch diameter) in accordance with Don Piccard Balloons, Inc., Service Letter No. 9 dated May 10, 1983. NOTE: The X in P/N 5041-X10 is a shaded square and is part of the part number. b) If blast valve handle P/N 5041-7 is installed, modify or replace with a P/N PSP 608 handle per Don Piccard Balloon Corporation Service Letter No. 10 dated May 10, 1983. c) If a main fuel quick-shutoff valve is installed, either remove in its entirety or modify the installation in accordance with Don Piccard Balloons, Inc., Service Letter No. 10 dated May 10, 1983. d) An equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office, ACE-115C, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018; telephone (312) 694-7357. This AD supersedes AD 82-13-02, Amendment 39-4406. This amendment becomes effective on August 4, 1983.
96-10-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, -212, and -231 series airplanes, that requires removing the existing forward pintle nut and cross bolt on the main landing gear (MLG), and installing a new nylon spacer and cross bolt and nut. This amendment is prompted by results of fatigue testing which revealed that the cross bolt and nut in the forward pintle pin of the MLG were damaged due to fatigue cracking. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in collapse of the MLG.
83-02-03: 83-02-03 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39- 4554. Applies to all models of the AMD-BA Falcon 20 series airplanes certificated in all categories. The affected freon fire extinguishers were manufactured by Martin or ABG-SEMCA and are identified as follows: two extinguishers type 111-1555-324-12 for the aft compartment and nacelles and type 111-011-324-12 for the MICROTURBO APU if the airplane incorporates AMD-BA Service Bulletin 80, Revision 3, dated May 9, 1968; AMD-BA Service Bulletin 350, Revision 2, dated October 4, 1971; or AMD-BA Service Bulletin 556 dated September 15, 1977. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent the potential failure of the fire extinguisher to operate, accomplish the following: 1. Perform a one-time inspection and repair or replace, as necessary, the pyrotechnic cartridge of the fire extinguisher in accordance with paragraph2, Accomplishment Instructions, of Avions Marcel Dassault-Breguet Aviation Service Bulletin No. 657 dated November 8, 1979. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective February 9, 1983.
99-06-12: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires replacing the nose wheel steering jack seals with seals of an improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the nose landing gear steering from locking up due to deterioration of the original design nose landing gear steering jack seals, which could result in reduced or loss of control of the airplane during takeoff, landing, and taxi operations.
2006-24-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks at certain stringer fastener locations; and repair, if necessary. For certain airplanes, that AD requires a modification in certain areas where reports indicate that cracking was prevalent. This modification terminates the repetitive inspections only for those areas, and is also an option for other airplanes affected by the existing AD. This new AD requires an additional inspection of areas that may have Alodine-coated rivets installed, and repair if necessary. This AD results from a report of cracking discovered in a skin lap joint that was previously inspected using the eddy current method. We are issuing this AD to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels.
2006-24-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections for discrepancies of the grease and gear teeth of the radial variable differential transducer of the nose wheel steering gearbox; or repetitive inspections for damage of the chrome on the bearing surface of the nose landing gear (NLG) main fitting barrel; as applicable. And, for airplanes with any discrepancy or damage, this AD requires an additional inspection or corrective actions. This AD also adds a terminating action. The actions specified by this AD are intended to prevent incorrect operation or jamming of the nose wheel steering, which could cause reduced controllability of the airplane on the ground. This action is intended to address the identified unsafe condition.
2019-11-03: The FAA is adopting an airworthiness directive (AD) for certain The Boeing Company Model 737-700C, -800, and -900ER series airplanes. This AD requires a maintenance records check to determine if any main slat track assembly has been removed, an inspection of the main slat track assemblies for a suspect lot number or a lot number that cannot be determined, and applicable on-condition actions. This AD was prompted by a report that certain main slat track assemblies were manufactured incorrectly and are affected by hydrogen embrittlement. The FAA is issuing this AD to address the unsafe condition on these products.
2019-11-05: We are superseding Airworthiness Directive (AD) 2015-22-02 for certain Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. AD 2015-22-02 required inspecting the tail rotor (TR) pitch link assemblies. This AD retains the inspections of AD 2015-22-02 and requires replacing certain pitch link bearings. This AD was prompted by a new design bearing introduced by Bell. We are issuing this AD to address the unsafe condition on these products.
98-18-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect cracking in the inner flange of door frame 66, and corrective actions, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to correct fatigue cracking in the inner flange of door frame 66, which could result in reduced structural integrity of the airplane.
98-19-14: This amendment adopts a new airworthiness directive (AD) that applies to all S.N. Centrair (Centrair) 101 series sailplanes. This AD requires replacing the airbrake control system with one of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent loss of the airbrake control system caused by cracks in the original design airbrake control system, which could result in an inadvertent forced landing with consequent sailplane damage and/or passenger injury.
87-10-02: 87-10-02 BOEING: Amendment 39-5620. Applies to Model 767 series airplanes, as listed in Boeing Alert Service Bulletin 767-27A0074, dated March 20, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent lateral control system restriction or jamming resulting from improper installation of a trailing edge flap drive vapor seal, accomplish the following: \n\n\tA.\tWithin the next 100 landings or 30 days after the effective date of this AD, whichever occurs first, inspect the trailing edge flap drive vapor seals for correct installation in accordance with Boeing Alert Service Bulletin 767-27A0074, dated March 20, 1987, or later FAA-approved revision. Vapor seals found to be installed incorrectly must be reworked to correct the installation before further flight in accordance with the instructions contained in the aforementioned alert service bulletin. \n\n\tNOTE: At the time of issuance of this AD, the Boeing 767 IllustratedParts Catalog, the Boeing 767 Maintenance Manual, and the Boeing 767 Maintenance Planning Data document all contained illustrations depicting a trailing edge flap drive vapor seal installed incorrectly, with the vapor seal flanges aligned vertically. The FAA-approved airplane maintenance program should be revised to take account of these errors. \n\n\tB.\tAn alternate means of compliance which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This information may be examinedat FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment 39-5620 becomes effective May 22, 1987.
2019-11-04: We are adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 D-2 helicopters. This AD requires replacing the rescue hoist cable cut pushbutton flip guard (flip guard). This AD was prompted by reports of unintended lifting of several flip guards. [[Page 26557]] We are issuing this AD to address the unsafe condition on these products.
98-16-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Cessna Model 750 Citation X series airplanes. This action requires repetitive in-flight functional tests to verify proper operation of the secondary horizontal stabilizer pitch trim system, and repair, if necessary. This amendment is prompted by reports of simultaneous failures of the primary and secondary horizontal stabilizer pitch trim system during flight, due to internal water contamination and corrosion damage in the system actuator. The actions specified in this AD are intended to detect and correct such contamination and damage, which could result in simultaneous failure of both primary and secondary pitch trim systems, and consequent reduced controllability of the airplane.
2006-23-12: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes equipped with certain hydraulic accumulators. This AD requires inspecting the hydraulic accumulators to identify certain serial numbers, and replacing any affected accumulator with a new or serviceable accumulator. Operators may delay doing the replacement by doing repetitive inspections of the affected hydraulic accumulators for signs of failure (leaking or cracking), and replacing any failed accumulator with a new or serviceable unit. This AD results from a report that one hydraulic accumulator failed in service, which caused the loss of the yellow hydraulic system when the airplane was configured for landing. We are issuing this AD to prevent damage to the pressure skin, failure of certain hydraulic systems, contamination of the cabin with hydraulic mist, increased workload for the flightcrew associated with the loss of one or more hydraulic circuits, and consequent reduced controllability of the airplane.
2006-22-13: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, PW4090-3, and PW4098 turbofan engines, with certain front turbine hub part numbers installed. This AD requires a onetime visual inspection of the anti-rotation slots in the front turbine hub, for a machining nonconformance, and its replacement if the inspection failed. This AD results from a report of a crack found in an anti-rotation slot of a front turbine hub, during overhaul shop inspection. The anti-rotation slot geometry was not machined in conformance with the design drawing during manufacture. We are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2000-24-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Beech Models A36, B36TC, and 58 airplanes. This AD requires you to inspect for misrouted rudder control cables; replace any worn or damaged guard pins; replace any pulley brackets that are damaged or worn; and replace any misrouted rudder control cables. Three reports of misrouted cables prompted this action. The actions specified by this AD are intended to correct the misrouted rudder control cable and consequent guard pin wear or fraying of the cables with loss of rudder control.
2019-08-11: We are superseding Airworthiness Directive (AD) 2008-24-14, which applied to all Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2008-24-14 required revising the instructions for continued airworthiness to incorporate certain airworthiness limitations for the main landing gear (MLG) trunnion fitting assembly. This AD requires revising the maintenance or inspection program, as applicable, to incorporate certain airworthiness limitations (AWLs). This AD also requires reworking the trunnion fitting in order to meet new structural safe-life limits. This AD was prompted by reports of cracks on the MLG trunnion fitting during fatigue testing; the introduction of new AWL tasks with revised inspection, modification, and safe-life requirements; and a determination that the trunnion fitting lower flange and both forward and aft bore holes are also subject to fatigue cracking. We are issuing this AD to address the unsafe condition on these products.
78-09-07 R3: 78-09-07 R3 BENDIX: Amendment 39-3205 as amended by Amendments 39-3252 and 39-3963 is further amended by Amendment 39-4538. Applies to Bendix S-20 series, S-1200 series, D-2000 series, and D-3000 series magnetos incorporating impulse couplings. Compliance required as indicated unless previously accomplished. To preclude magneto or engine failure resulting from magneto impulse coupling failure, accomplish the following: a. On magnetos having less than 475 hours time in service since new or overhaul, accomplish the provisions of paragraphs "c" and "d" of this AD prior to 500 hours time in service and thereafter at intervals not to exceed 500 hours time in service from the last inspection. b. On magnetos having 475 or more hours in service since new or overhaul, accomplish the provisions of paragraphs "c" and "d" of this AD within the next 25 hours time in service and thereafter at intervals not to exceed 500 hours time in service from the last inspection. c. Inspect and replace, if necessary, impulse coupling components in accordance with the paragraph titled "Detailed Instructions" contained in Bendix Engine Products Division Service Bulletin Number 599B or an FAA approved equivalent. d. After accomplishing paragraph "c" of this AD, make a logbook entry showing the compliance time. Include the magneto make, model, and serial number. (Note: Except for new or zero time overhauled magnetos, any magneto not accompanied by a record of operating time must be in compliance with paragraph "c" upon installation on an approved engine.) e. Equivalent inspections and procedures must be approved by the Manager, New York Aircraft Certification Office, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. f. As permitted by Federal Aviation Regulations (FARs) 21.197 and 21.199, aircraft may be flown to a base where maintenance required by this AD can be accomplished. Amendment 39-3205 was effective May 9, 1978. Amendment 39-3252 amended Amendment 39-3205 effective July 3, 1978. Amendment 39-3963 amended Amendments 39-3205 and 39-3252 effective November 3, 1980. This Amendment 39-4538 is effective on January 17, 1983.
97-24-08: This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob, Luft-und Raumfahrt, GmbH. (Grob) Model G102 Astir CS sailplanes. This action requires replacing the elevator control lever with an improved elevator control lever. The discovery of cracks in the elevator control lever during a routine inspection of a Grob Model G102 Astir CS sailplane prompted this action. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the elevator control lever, which could result in loss of control of the sailplane.
94-03-08: This amendment supersedes an existing airworthiness directive (AD), applicable to McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes, that currently requires certain structural modifications and inspections. This amendment requires additional structural modifications and inspections. This amendment is prompted by an evaluation by the Model DC-10 Task Group, which identified additional modifications for mandatory action. The actions specified by this AD are intended to prevent degradation in the structural capabilities of the affected airplanes. This action also reflects the FAA's decision that long-term continued operational safety should be assured by actual modification of the airframe, where feasible, rather than only repetitive inspections for known service problems.
2019-10-04: We are adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) 912 and 914 model engines. This AD was prompted by power loss and engine revolutions per minute (RPM) drop on certain Rotax 912 and 914 model engines due to a quality control deficiency in the manufacturing process of certain valve push-rod assemblies resulting in partial wear on the rocker arm ball socket and possible malfunction of the valve. This AD requires one-time inspection and, depending on the findings, replacement of the affected parts with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products.