Results
2021-14-13: The FAA is adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW2037, PW2037M, PW2040, and F117-PW-100 model turbofan engines. This AD was prompted by a report of an uncontained engine failure resulting from cracks in the knife edge of the high- pressure turbine (HPT) 2nd-stage air seal assembly. This AD requires fluorescent penetrant inspections (FPIs) and visual inspections of the HPT 2nd-stage air seal assembly and, depending on the results of the inspections, replacement of the HPT 2nd-stage air seal assembly with a part eligible for installation. This AD also requires replacement of the affected HPT 2nd-stage air seal assembly, depending on the engine model, at either the next engine shop visit or the next piece-part opportunity. The FAA is issuing this AD to address the unsafe condition on these products.
89-10-02: 89-10-02 AEROSPATIALE: Amendment 39-6201. Applicability: Model ATR42-300 series airplanes up to and including serial number 120, which have not been modified in accordance with Service Bulletin ATR42-28-0013, Revision 2, dated January 6, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a fuel fire in the nacelle, accomplish the following: A. Within 300 flight hours after the effective date of this AD and thereafter at intervals not to exceed 300 flight hours, and at each engine removal/installation, inspect the engine fuel supply hoses for fuel leakage in accordance with Aerospatiale Service Bulletin ATR42-28-0012, dated September 9, 1988. If leakage is found, before further flight, repair or replace the leaking fuel line, in accordance with the service bulletin. B. Replacement of the engine fuel supply hoses in accordance with Aerospatiale Service Bulletin ATR42-28-0013, Revision 2, datedJanuary 6, 1989, constitutes terminating action for the repetitive inspections required by paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined atthe FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6201, AD 89-10-02) becomes effective on May 29, 1989.
86-17-09: 86-17-09 BELL HELICOPTER TEXTRON, INC.: Letter issued August 21, 1986. Applies to all Bell Helicopter Model 212 helicopters, S/N 30501 through 30999, 31101 through 31273, and 31275; 32101 through 32142 and 32201 through 32262 that have T/R hub and blade assembly, P/N 212-011-701-001 installed, certified in any category. Compliance required as indicated unless already accomplished. To prevent failure of the tail rotor control, accomplish the following: (a) Within 25 hours' time in service after receipt of this AD, visually inspect the T/R hub assembly P/N 212-011-701-3, in accordance with Part 1 of Bell Helicopter Textron, Inc. (BHTI), Alert Service Bulletin (ASB) 212-86-39, Revision "A," dated July 23, 1986. (1) If the (P/N) 212-011-716-1 T/R trunnion housing is cracked or there is axial play in the T/R trunnion, or if there are excess balance washers, comply with Part II of the Alert Service Bulletin before further flight. (2) Repeat this inspection every 25 hours' time in service until paragraph (b) of this AD is accomplished. (b) Remove the 212-011-701-1 T/R hub and blade assembly and inspect the trunnion bearing housing, P/N 212-011-716-1, as detailed in Part II of BHTI ASB 212-86-39, Revision "A", dated July 23, 1986, within 150 hours' time in service or within 60 days after the issue date of this AD, whichever occurs first. Replace any housing having an end web thickness of .059 inch or less with a serviceable part. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2006-25-10: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ airplanes. This AD requires calculating the current life of each lift spoiler jack, and eventually replacing each lift spoiler jack. This AD results from a review of all system components as part of the life- extension program for the affected airplanes that indicated the fatigue life limit of certain lift spoiler jacks cannot be extended from the current life limit. We are issuing this AD to prevent failure of the lift spoiler jack, and consequent increased drag and uncommanded roll inputs, which could reduce the flightcrew's ability to control the airplane.
2006-25-11: The FAA is adopting a new airworthiness directive (AD) for certain Lockheed Model L-1011 series airplanes. This AD requires a one- time detailed inspection of the C112 harness clamp assembly for proper installation, a one-time detailed inspection of the C112 and C162 harness assemblies for damage, and corrective actions if necessary. This AD results from a report of electrical arcing of the essential bus feeder cables behind hinged circuit breaker panel CB3 P-K. We are issuing this AD to prevent arcing of essential bus feeder cables due to improper installation of the harness C112 clamp assembly, which could result in loss of electrical systems and smoke and/or fire behind the CB3 P-K hinged circuit breaker panel in the flight compartment.
2021-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters. This AD was prompted by a report that damage (scorch marks) was found on an internal life raft installation that contained a half rescue kit. This AD requires identifying the part number and serial number of each half rescue kit located in the internal life raft installation and, depending on the findings, inspecting the life raft for damage, inspecting the condition of the flashlight battery, testing the flashlight battery, and replacing the life raft or flashlight battery (including the leak test) as applicable, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that certain airplanes have navigation units with outdated magnetic variation (MagVar) tables. This AD requires revising the existing airplane flight manual (AFM) and applicable corresponding operational procedures to update the flight management system (FMS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2006-25-07: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135ER and -135KE airplanes and Model EMB-145, -145ER, -145MR, -145MP, and -145EP airplanes. This AD requires inspecting the fuel quantity indication system (FQIS) wire harness and the direct current (DC) fuel pump wire harness to determine if the harnesses are properly attached at their respective attachment points and properly separated from one another, and performing corrective actions if necessary. This AD results from a report that the FQIS wire harness may not be properly attached at its attachment points or properly separated from the DC fuel pump wire harness. We are issuing this AD to prevent chafing between those harnesses or chafing of the harnesses against adjacent airplane structure or components, which could present a potential ignition source that could result in a fire or explosion.
2021-10-09: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) CFM56-5B and CFM56-7B model turbofan engines with a certain high-pressure turbine (HPT) inner stationary seal installed. This AD was prompted by cracks found in the rotating air HPT front seal. This AD requires removal, inspection, and replacement of the affected HPT inner stationary seal and, depending on the findings, replacement of the rotating air HPT front seal, HPT rotor blades, and No. 3 ball bearing. The FAA is issuing this AD to address the unsafe condition on these products.
2000-13-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GmbH (ECD) Model EC 135 helicopters. That AD requires conducting a tail rotor drive shaft vibration survey (survey), installing a Fenestron Shaft Retrofit Kit, inspecting each tail rotor drive shaft bearing (bearing) attaching lock plate for bent-open tabs and broken or missing slippage marks, and visually inspecting each bearing support for cracks. This AD requires conducting the survey and installing the Fenestron Shaft Retrofit Kit. This AD also requires installing double bearing supports and struts, revising the required compliance time for the repetitive inspections of the bearing attach hardware and supports, and removing the requirement to contact the FAA if a lock plate tab is bent open or if slippage marks are broken or missing. This amendment is prompted by continued reports of misaligned or cracked bearing supports and loose bearing attachment bolts. The actions specified by this AD are intended to prevent loss of drive to the tail rotor and subsequent loss of control of the helicopter.
87-26-05: 87-26-05 FOKKER B.V.: Amendment 39-5805. Applies to Model F-28 series airplanes, as listed in Fokker B.V. Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987, certificated in any category. Compliance required within 120 flight hours after the effective date of this AD, unless previously accomplished. To prevent sudden decompression of the airplane as a result of failure of a cargo hinge lugs, accomplish the following: A. Visually or dye penetrant inspect the cargo door hinge lugs for cracks, in accordance with Fokker Service Bulletin F28/52-a/100, Revision 1, dated June 19, 1987. Any lugs found to be cracked must be replaced with a serviceable part prior to further flight, in accordance with the limitations set forth in the service bulletin. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approvedby the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Fokker Aircraft, 1199 North Fairfax Street, Alexandria, Virginia 22314. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East marginal Way South, Seattle, Washington. This amendment becomes effective February 1, 1988.
2006-25-04: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 airplanes. That AD currently requires repetitive inspections for cracking and corrosion in the lower rim area of the rear pressure bulkhead and adjacent areas, repetitive inspections for cracking or corrosion in the service apertures and the upper rim area of the rear pressure bulkhead, and corrective actions if necessary. This new AD removes certain repetitive inspections and reduces the repetitive interval of one inspection. This new AD also requires an inspection for missing or damaged sealant in the area between the outer attachment angle and circumferential joint doubler, and corrective action if necessary. This new AD also requires additional inspections for corrosion of certain areas and repetitive inspections for airplanes on which repairs have been done. This AD results from reports of corrosion and cracking in the various components associated with the rear pressure bulkhead. We are issuing this AD to prevent reduced structural capability of the fuselage and consequent decompression of the airplane.
2018-16-51: We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters as Emergency AD 2018-16-51, dated July 26, 2018, which superseded Emergency AD 2018-15-51, dated July 20, 2018. This AD requires inspecting the tail rotor (T/R) gearbox installation, inspecting the T/R gearbox retaining hardware and support attachment point areas, and replacing each nut. This AD is prompted by two reports of T/R gearbox assemblies loosely attached to the gearbox support. The actions of this AD are intended to address an unsafe condition on these products.
2000-13-06: This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Model S-61 helicopters. That AD requires inspecting certain pylon upper and lower hinge web fittings (web fittings) for corrosion or a crack and either repairing certain web fittings or replacing any unairworthy web fittings with airworthy web fittings. That AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment retains the requirements of that AD but corrects an error in paragraph (a)(3) by removing the words "and 3.E." This amendment is prompted by an operator notifying the FAA of that error which requires an unnecessary major inspection within 25 hours time-in-service (TIS). The actions specified in this AD are intended to remove an undue burden on the public by superseding the AD and removing the requirement for the major inspection within 25 hours TIS.
82-27-03: 82-27-03 ROTO-MASTER, INC. (RAJAY INDUSTRIES, INC.): Amendment 39-4515. Applies to Rajay Model 325E10 and 3AT6EE10J2 turbochargers, installed on but not limited to: Continental Engine Models TSIO-360, 0-470, IO-470, IO-520, TIO-520; Lycoming Engine Models O-320, IO-320, LIO-320, 0-360, IO-360, TO-360, 0-540, IO-540, TIO-540. These engines are installed on, but not limited to the following aircraft: Piper PA-28R-201T, PA-28-RT-201T, PA-28-201T series; PA-34-200, PA-34-200T, series; PA-30 and -39 series; Mooney M-20 A thru K series; Lake LA-4, LA-4A, and LA-200 Series. \n\n\tCompliance is required as indicated, unless already accomplished. \n\n\tTo prevent the possibility of a fire in the powerplant nacelle and/or heat damage to the powerplant installation caused by the engine exhaust gases escaping through a cracked turbocharger turbine housing, accomplish the following: \n\n\t(a)\tWithin 50 hours of time in service after the effective date of this AD inspect the engine turbochargerexhaust systems and determine whether or not the turbine housing Rajay P/N TC-60-11 or Rajay P/N 600510, 600510-01, 600510-02 or TCM P/N 643930 or turbocharger model 325E10 or 3AT6EE10J2 is installed. If any of these part numbers are installed, or if the turbine housing part number cannot be determined, before further flight, and thereafter at intervals not to exceed 200 hours time in service from the last inspection, comply with paragraph (b) through (g) of this AD. \n\n\t(b)\tRemove the turbocharger turbine housing exhaust coupling V-Band and tailpipes (see Figure 1). \n\n\n\n\n\n\n\n\n\n\t(c)\tVisually inspect the turbocharger turbine housing for cracks using a dye penetrant inspection method. (NOTE: The suspect area can be viewed through the exhaust port to ascertain possible presence of cracks penetrating through the outer wall as shown in Fig. 2.) \n\n\t(d)\tInspect coupling V-Band clamp for cracks by spreading the band segments and checking for failed spot welds and for indicationof exhaust flanges bottoming in coupling V-Band (see Figure 1) and clamp bolt for bending, overstress, thread damage, and cracks (see Figure 1). \n\n\t(e)\tInspect turbochargers and tailpipe flanges for cracks and distortion (see Figure 1). Remove all carbon deposits from mating flanges before reassembly. \n\n\t(f)\tInspect mating area of turbocharger exhaust flange to exhaust tailpipe connection for proper mating of surfaces. \n\n\t(g)\tInspect engine mount for indication of overheat, warpage, and corrosion, or rust. Repair as required.\n\n\t(h)\tIf during inspection required by paragraph (c), an internal crack is found that either exceeds the limit shown in Figure 2, View 1 or 2, or a crack penetrates the outer wall of a turbine housing as shown in Figure 2, View 3, the existing turbine housing must be removed from service and replaced with a serviceable turbine housing prior to the next flight. \n\n\t(i)\tIf during the inspections required by paragraphs (d) through (g), cracked, distorted,or otherwise damaged parts, components, or assemblies are found, before further flight repair or replace with serviceable parts, components, and assemblies of the same part number. \n\n\t(j)\tThe inspections required by this AD may be discontinued when the turbine housing is replaced with a Roto-Master part number 600510-04 (TCM P/N 643931). \n\n\t(k)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections required by this AD. \n\n\t(l)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. \n\n\tNOTE: Roto-Master, Inc. Service Letter Number 27, Rev. A dated September 24, 1982, refers to the above procedures. \n\n\tThis amendment becomes effective December 30, 1982.
99-13-10: This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 206L-4 helicopters, that requires replacing certain hydraulic relief valves (valves) with airworthy valves. This amendment is prompted by a pilot s report of intermittent hydraulic pressure in the flight controls that was caused by a defective hydraulic relief valve. The actions specified by this AD are intended to prevent intermittent hydraulic pressure to the flight controls and subsequent loss of control of the helicopters
2006-25-02: This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream Model G-159 airplanes, that requires repetitive non-destructive testing inspections to detect corrosion of the skin of certain structural assemblies, and corrective action if necessary. This AD also requires x-ray and ultrasonic inspections to detect corrosion and cracking of the splicing of certain structural assemblies, and repair if necessary. The actions specified by this AD are intended to detect and correct corrosion and cracking of the lower wing plank splices and spot-welded skins of certain structural assemblies, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2000-12-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections of the aft pressure bulkhead to detect cracking, and repair, if necessary. This amendment is prompted by a report of fatigue cracking found in the upper half of the aft pressure bulkhead. The actions specified by this AD are intended to detect and correct cracking in the aft pressure bulkhead, which could result in rapid decompression of the fuselage or overpressurization of the tail section.
2018-20-16: We are superseding Airworthiness Directive (AD) 2013-11-12, which applied to certain Bombardier, Inc., Model BD-100-1A10 airplanes. AD 2013-11-12 required inspecting for the correct serial number of a certain hydraulic system accumulator, and replacing affected hydraulic system accumulators with new or serviceable accumulators. This AD expands the applicability and requires modifying or replacing certain hydraulic brake system accumulators. This AD also requires revising the maintenance or inspection program to add life limits for the accumulators. This AD was prompted by a determination that certain other hydraulic system accumulators must be modified or replaced and life limits must be added. We are issuing this AD to address the unsafe condition on these products.
59-11-04: 59-11-04 VICKERS: Applies to All Viscount 745D Aircraft Which Do Not Embody Modification D.2783. Compliance required as indicated. Service experience has shown that a gap of less than 0.25 inch between the end of No. 3 flap and the aileron may, under certain flight conditions, produce a condition where the flap could foul or contact the inboard end of the aileron (port and starboard wings). As soon as possible but not later than June 15, 1959, inspect for adequate clearance between the outboard end of the No. 3 flap at the No. 4 flap beam unit and the inboard end of the aileron on both the right and left sides. Where the gap is found to be less than 0.25 inch, the outboard end of the No. 3 flap must be modified to provide proper clearance. The British Air Registration Board considers this mandatory. (Vickers-Armstrong PTL No. 208 and Modification Bulletin No. D.2783 cover the same subject.)
2006-09-06 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR series airplanes. That AD currently requires repetitive inspections to detect cracking of certain lower lobe fuselage frames, and repair if necessary. This new AD specifies appropriate service information for certain corrective actions. This AD results from reports indicating that fatigue cracks were found in lower lobe frames on the left side of the fuselage. We are issuing this AD to detect and correct fatigue cracking of certain lower lobe fuselage frames, which could lead to fatigue cracks in the fuselage skin, and consequent rapid decompression of the airplane. \n\n\nDATES: The effective date of this AD is June 7, 2006. \n\n\tOn June 7, 2006 (71 FR 25926, May 3, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2408, Revision 1, dated April 4, 2002. \n\n\tOn May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2408, dated April 25, 1996.
2018-20-14: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR42-500 airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new and/or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2018-20-21: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (CL-604 Variants) airplanes. This AD was prompted by reports of floodlight lamps found burned and the corresponding circuit breaker tripped as a result of fluid entering the cockpit floodlight fixtures. This AD requires installation of new gasket seals on floodlight fixtures. We are issuing this AD to address the unsafe condition on these products.
99-26-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the rudder trim switch in the flight compartment with a new switch having a longer shaft; modification of wiring in panel 408VU; and replacement of the rudder trim control knob with an improved new knob. 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 prevent inadvertent and uncommanded rudder trim activation, which could result in yaw and roll excursions and consequent reduced controllability of the airplane.
2006-24-07: The FAA is adopting a new airworthiness directive (AD) for certain Hartzell Propeller Inc. HC, BHC, and PHC series propellers; and McCauley Propeller Systems controllable propellers serviced by Oxford Aviation Services Limited, doing business as CSE Aviation, in the United Kingdom between September 1998 and October 2003. This AD requires inspecting the propeller blades and other critical propeller parts for wear and mechanical damage. This AD results from findings that CSE Aviation failed to perform some specific inspections and repairs. We are issuing this AD to detect unsafe conditions that could result in a propeller blade separating from the hub and loss of control of the airplane.