Results
2023-03-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by the FAA's analysis of the Model 747 airplane fuel system reviews conducted by the manufacturer, and by the determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
86-10-08: 86-10-08 FAIRCHILD: Amendment 39-5315. Applies to Models SA226 and SA227 airplanes (Serial Numbers (S/N) SA226-T, S/N T201 through T275, T277 through T291; SA226-T(B), S/N T(B)276, T(B)292 through T(B)417; SA226-AT, S/N AT001 through AT074; SA226-TC, S/N TC201 through TC419; SA227-TT, S/N TT421 through TT555; SA227-AT, S/N AT423 through AT631B; SA227-AC, S/N AC406, AC415, AC416, and AC420 through AC632) airplanes certificated in any category. Compliance: Required within the next 200 hours time-in-service or the next 30 calendar days, whichever comes first, after the effective date of this AD, unless already accomplished. To prevent the elevator gust lock from engaging in flight, accomplish the following: (a) Remove the elevator gust lock system components and install the alternate elevator gust lock and associated hardware in accordance with the instructions in Fairchild Aircraft Corporation Service Bulletin (S/B) 226-27-041 revised February 18, 1986, for the SA226 airplane models, or S/B 227-27-016 revised February 18, 1986, for the SA227 airplane models. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance may be used if approved by the Manager of the Airplane Certification Branch, ASW-150, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 877-2070. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Fairchild Aircraft Corporation, Post Office Box 32486, San Antonio, Texas 78284, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on May 28, 1986.
2000-05-14: This amendment supersedes two existing airworthiness directives (AD's), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that require rework or replacement of No. 4 and 5 bearing oil system hardware, initial and repetitive inspections of the oil system, optional installation of an improved oil filter bypass valve, and repetitive inspection of No. 4 and 5 bearing oil inlet tube, to ensure the integrity of the reduction gear system and overspeed protection system. This action would require replacement of the existing power turbine bearing housing assembly with a new, improved power turbine bearing housing assembly, and installation of a reworked or modified fourth turbine rotor disk assembly as a part of a design change to the new No. 4 bearing configuration that eliminates the requirement for repetitive inspections of oil system and No. 4 and 5 bearing oil inlet tube assembly. This amendment is prompted by one report of a contained power turbine rotor shaft separation forward of the Stage 4 low pressure turbine (LPT) rotor on an AlliedSignal Inc. ALF502R-5 engine. The LPT failure was caused by improper inspection of the engine oil system required by AD 97-05-11 R1. The actions specified by this AD are intended to prevent a No. 4 and 5 duplex bearing failure, which can result in a Stage 4 LPT rotor failure, an uncontained engine failure, and damage to the airplane.
2004-25-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-300 and -400ER series airplanes, that requires replacing the tie rods for the waste tank cradle, related investigative actions, corrective actions, and special retrofit action if necessary. This action is necessary to prevent possible failure of the main deck floor stanchions and consequent collapse of the main floor during an emergency landing, which could result in passenger injury and impede passenger evacuation from the airplane. This action is intended to address the identified unsafe condition.
2023-04-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-8 and 737-9 airplanes, and certain Model 737- 600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of damage to the auxiliary power unit (APU) fuel line shroud located aft of the aft cargo area; investigation revealed that the placement of the pressure switch wire clamp assembly and its fastener allowed interference of the fastener against the APU fuel line shroud. This AD requires inspecting the APU fuel line shroud for damage, inspecting the pressure switch wire clamp for correct bolt orientation and horizontal distance from the APU fuel line shroud, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
63-04-02: 63-04-02 HILLER: Amdt. 535 Part 507 Federal Register February 12, 1963. Applies to All UH-12, UH-12A, UH-12B, and UH-12C Helicopters with P/N's 55008 and 55012 Tail Rotor Blades. Compliance required as indicated. To prevent failures of P/N's 55008 and 55012 tail rotor blades the following shall be accomplished: (a) Within the next 50 hours' time in service, unless already accomplished: (1) Replace all P/N's 55008 and 55012 tail rotor blades with P/N 55064 tail rotor blades in accordance with Hiller Service Bulletin No. 80. (2) On all helicopters equipped with the large diameter (1.375 inch) spar stabilizer, P/N 37003, install the stabilizer strut in accordance with Hiller Service Bulletin No. 75B. (3) On all helicopters equipped with the small diameter (1 inch) spar stabilizer, P/N 37001, install the stabilizer strut in accordance with Hiller Service Bulletin No. 83. (b) Until replacement with the P/N 55064 blade is accomplished, visually inspect the P/N's 55008 and 55012 tail rotor blades prior to each flight and refueling. The outer surface of the skin on both sides of the blade shall be inspected for cracks in the area of the outer tension torsion bar retention bolt and the adjacent rivet pattern through the outer end of the root fitting. Paint must be removed from the areas to facilitate inspection. Any blades found to be cracked must be removed and replaced with P/N 55064 blades prior to further flight. (Hiller Service Bulletins Nos. 75B, 80, and 83 pertain to this subject.) This supersedes AD 58-24-02. This directive effective February 12, 1963.
58-26-02: 58-26-02 BELL: Applies to All Model 47 Series Helicopters Equipped With Marvel- Schebler Automatic Altitude Compensating Carburetor Model MA4-5AA. Compliance required within next 25 hours of operation. With a Marvel-Schebler Model MA4-5AA carburetor installed, it is possible to start and run the engine with the carburetor mixture control in the idle cutoff position if the throttle is partially or fully opened. However, as soon as the throttle is fully closed, the idle cutoff will operate and shut off the engine. Therefore, it would be possible to start the engine, takeoff, and fly with the mixture in idle cutoff as long as the throttle is never closed. The first time the throttle is closed, however, as in autorotation, an immediate engine stoppage would occur. To prevent inadvertent engine stoppage in flight due to failure to place the carburetor mixture control in the "auto" position before takeoff, the following must be accomplished: (a) For Models 47D1, 47G, 47G2, 47H1, and 47J, spring load the cockpit mixture control to the rich or "auto" position by installing a tension spring (Bell P/N 47-631-226-1 or equivalent) between the mixture control cable support bracket (P/N 47-631-125-18) adjacent to the control quadrant and the control cable end of the quadrant mixture control lever. On Models 47D1 and 47H1, attach the spring to the mixture control lever using existing cotter pin hole through flexible control attaching clevis pin. On Models 47G, 47G2, and 47J, attach spring to mixture control lever through existing lower hole in lever. On Model 47D1, remove corners of jog in quadrant mixture control slot. Check that mixture control will return to "auto" position when pulled to "idle cut off" position and released. (b) For Model 47D, remove the quadrant mixture control lever and push-pull mixture control. Place the carburetor mixture control arm in the rich or "auto" position and secure with lockwire. This procedure may be used in lieu of that outlined in (a) for Models 47D1, 47G, 47G2, 47H1, and 47J if preferred. (This same subject is covered in Bell Service Bulletins No. 124SB for Models 47D1, 47G, and 47H1, No. 124SB Supplement 1 for Model 47D, and Service Instruction 257SI for Models 47G2 and 47J.)
2000-05-28: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires a one-time inspection to detect cracking or corrosion of the forward attachment bolts of the engine pylon to wing interface, and corrective action, if necessary. It also requires re-installation with re-protected and sealed bolts torqued to a lower level. 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 detect and correct cracking or corrosion of the forward attachment bolts of the engine pylon to wing interface, which could result in reduced structural integrity of the engine pylon attachment.
2014-05-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by results from fuel system reviews conducted by the manufacturer. This AD requires accomplishing modifications to the fuel system. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2023-06-06: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600- 2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that new and more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate two aircraft maintenance manual (AMM) tasks. The FAA is issuing this AD to address the unsafe condition on these products.
82-25-08: 82-25-08 GENERAL ELECTRIC COMPANY: Amendment 39-4507. Applies to the CF6-45 series and CF6-50 series model turbofan engines. Compliance required as indicated. To prevent potential separation of the spacer/impeller which could result in uncontained engine failure, accomplish the following: (a) Perform fluorescent penetrant inspection of the HPT Spacer/Impeller, Part Numbers 9045M59P07, P08, P10, P12; 9173M55P01, P02, P03; 9198M92P01, P02, P03, P04, P05, P06, P07, P08, P09, P10; 9190M82P02, P03; 9234M25P01, P02, P03; and 9234M25P04 in accordance with General Electric CF6-50/45 Service Bulletin 72-748, Revision 1, dated June 9, 1982, or later revision approved by the Manager, Engine Certification Branch, FAA, New England Region, Burlington, Massachusetts 01803, per the following schedule: Prior to the accumulation of 5,000 cycles in service, or within 3,000 cycles since the last inspection, or within the next 100 cycles after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 cycles since last inspection. (NOTE: Established life limits for the part shall not be exceeded.) (b) Spacer/impellers with any crack indications shall be removed from service prior to further flight. (c) Spacer/impeller inspections which have been performed prior to the effective date of this AD which are identical to the inspection requirements of Service Bulletin 72-748 are considered to be an acceptable means of compliance with the initial inspection requirements of Paragraph (a). (d) Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be used if approved by the Manager, Engine Certification Branch, FAA, New England Region. (e) Airplanes may be ferried in accordance with the provisions of Federal Aviation Regulation 21.197 to a base where the AD can be accomplished. This amendment becomes effective on December 30, 1982.
2004-25-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 and A340 series airplanes. This AD requires regularly performing a complete electrical shutdown of the airplane to reset the integrated standby instrument system (ISIS). This AD also provides an optional terminating action. This AD is prompted by reports indicating that an airplane lost the ISIS, then, during the same flight, lost all electronic instrument system (EIS) display units. We are issuing this AD to prevent loss of the ISIS, which, if combined with loss of all EIS display units, could reduce the flightcrew's situational awareness and contribute to loss of control of the airplane or impact with obstacles or terrain.
2014-05-27: We are adopting a new airworthiness directive (AD) for certain Rockwell Collins TPR-720 and TPR-900 Mode select (S) transponders that are installed on airplanes. This AD was prompted by the identification that the TPR-720 and TPR-900 Mode S transponders respond intermittently to Mode S interrogations from both ground-based and traffic collision avoidance system (TCAS-) equipped airplanes. This AD requires testing and calibration of the alignment of the transponders. We are issuing this AD to correct the unsafe condition on these products.
84-15-04: 84-15-04 SIKORSKY AIRCRAFT DIVISION: Amendment 39-4893. Applies to all Sikorsky Model S-76A helicopters, certificated in all categories. Compliance is required within 30 days after the effective date of this AD unless already accomplished. To prevent loss of control of the helicopter due to tail rotor control cable failure, accomplish the following: Unless already accomplished, install a tail rotor controls centering quadrant in accordance with Sikorsky Customer Service Notice No. 76-133, Revision A, dated November 10, 1983, or FAA-approved equivalent. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the compliance time of this AD may be adjusted and/or an equivalent method of compliance may be approved upon request to the Manager, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. This amendment becomes effective August 3, 1984.
2004-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires regularly performing a complete electrical shutdown of the airplane to reset the integrated standby instrument system (ISIS). This AD is prompted by reports indicating that an airplane lost the ISIS, then, during the same flight, lost all electronic instrument system (EIS) display units. We are issuing this AD to prevent loss of the ISIS, which, if combined with loss of all EIS display units, could reduce the flightcrew's situational awareness and contribute to loss of control of the airplane or impact with obstacles or terrain.
2014-05-25: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211- Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211-Trent 977B-84, and RB211-Trent 980-84 turbofan engines. This AD requires inspections of the low-pressure turbine exhaust case and support assembly or tail bearing housing (TBH) to detect cracks or damage. This AD was prompted by an RR structural re-analysis indicating that the TBH may not retain full limit load capability in all fail-safe conditions. We are issuing this AD to prevent failure of the TBH, resulting in damage to the engine and damage to the airplane.
2023-05-16: The FAA is superseding Airworthiness Directive (AD) 2023-04-08 which applied to certain Continental Aerospace Technologies, Inc. (Continental) GTSIO-520-C, -D, -H, -K, -L, -M, -N, and -S; IO-360-A, - AB, -AF, -C, -CB, -D, -DB, -E, -ES, -G, -GB, -H, -HB, -J, -JB, -K, and -KB; IO-470-D, -E, -G, -H, -J, -K, -L, -M, -N, -P, -R, -S, -T, -U, -V, and -VO; IO-520-A, -B, -BA, -BB, -C, -CB, -D, -E, -F, -J, -K, -L, -M, and -MB; IO-550-A, -B, -C, -D, -E, -F, -G, -L, -N, -P, and -R; LTSIO- 360-E, -EB, -KB, and -RB; LTSIO-520-AE; O-470-A, -B, -E, -G, -H, -J, - K, -L, -M, -N, -R, -S, -T, and -U; TSIO-360-A, -AB, -B, -BB, -C, -CB, - D, -DB, -E, -EB, -G, -GB, -H, -HB, -JB, -KB, -LB, -MB, -RB, and -SB; TSIO-520-A, -AE, -AF, -B, -BB, -BE, -C, -CE, -D, -DB, -E, -EB, -G, -H, -J, -JB, -K, -KB, -L, -LB, -M, -NB, -P, -R, -T, -UB, -VB, and -WB; TSIO-550-A, -B, -C, -E, -G, -K, and -N; TSIOF-550-K; and TSIOL-550-A, - B, and -C model reciprocating engines. AD 2023-04-08 required inspection of the crankshaft assembly for proper installation of the counterweight retaining rings in the counterweight groove and, depending on the results of the inspection, corrective actions if improper installation was found. This AD continues to require inspection of the crankshaft assembly for proper installation of the counterweight retaining rings in the counterweight groove, and corrective actions if improper installation is found. Since the FAA issued AD 2023-04-08, operators notified the FAA, and Continental confirmed, that certain affected model reciprocating engines not included in the applicability of AD 2023-04-08 are also affected by the unsafe condition. Additionally, the FAA determined the special flight permit paragraph required revision. This AD was prompted by a report of a quality escape involving improper installation of counterweight retaining rings in the engine crankshaft counterweight groove during manufacture. The FAA is issuing this AD to address the unsafe condition on these products.
2004-24-10: The FAA adopts a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-3 airplanes modified with A.M. Luton's Supplemental Type Certificate (STC) number SA3777NM. This AD requires you to inspect the wiring for the heating blankets on P3 and PY pneumatic lines and the push-to-test function lights to ensure that they are wired to the correct schematic; replace the circuit breaker switch as applicable; and replace the flight manual supplement currently in use with Revision G, dated March 28, 2001 (incorporates Revision I of Sheet 1 of Drawing 20075, "Electrical System Schematic," dated October 10, 2000). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Canada. We are issuing this AD to detect and correct wiring installed in accordance with an incorrect drawing, which shows the pneumatic heating blankets to the P3 and PY pneumatic lines wired in series with the indicator lights, rather than parallel. This can result in reduced current for the heating blankets and loss of pneumatic line heating, which can lead to loss of engine power or reverse propeller overspeed governing protection and ultimately loss of control of the airplane.
96-26-02: This amendment adopts a new airworthiness directive (AD) that applies to certain FLS Aerospace (Lovaux) Ltd. OA7 Optica series 300 airplanes equipped with a Hoffman fan, part number HO-E315/122EZ, and fan shaft extension. This AD requires replacing the fan shaft extension with one that incorporates Modification No. B2/MOD/047. The AD results from a quality control review that shows that the four counterbores on the fan shaft extension to engine attachment flange have excessive depths. The actions specified in this AD are intended to prevent cracks from forming in the fan shaft extension flange and subsequent structural failure of this area because of counterbores with excessive depth.
80-07-13: 80-07-13 PACIFIC INFLATABLES COMPANY: Amendment 39-3731. P/N 4000 and P/N 4000E Series floatation devices. Compliance is required as indicated. To prevent the possible failure of the floatation device due to excessive age, accomplish the following: a. Within 10 days' time in service from the effective date of this AD, remove from service all Pacific Inflatables Company P/N 4000 and 4000E flotation devices. b. As of the effective date of this AD, Pacific Inflatables Company P/N 4000 or 4000E floatation devices are not eligible for installation in aircraft. This amendment becomes effective April 7, 1980.
2023-04-18: The FAA is superseding Airworthiness Directive (AD) 2021-03- 11, which applied to all Dassault Aviation Model FALCON 2000 airplanes. AD 2021-03-11 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2021-03-11, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a 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.
68-14-01: 68-14-01 BEECH: Amendment 39-618. Applies to Model D55, 56TC and E95 airplanes equipped with Beechcraft pneumatic deicer system and Beechcraft Model B5 Autopilot (manufactured as Brittain Model B-5P). Compliance required as indicated. An unsafe condition exists wherein the simultaneous operation of the Model B5 Autopilot and the pneumatic de-icer system might cause the airplane to exceed the structural limits. Since a potential unsafe condition exists, the following operating limitations are prescribed for all affected aircraft: A. Aircraft must not be operated with Beechcraft Model B5 Autopilot and Beechcraft pneumatic de-icer system operating simultaneously. B. Within the next ten hours time in service after receipt of the telegram a placard must be installed in clear view of the pilot near the autopilot controller stating as follows: "Autopilot must be turned OFF whenever the de-icer system is ON." C. Placard is to remain installed in aircraft until such time as Brittain Industries, Inc., Service Bulletin No. 68-1, Revision A, or a satisfactory equivalent modification approved by the Chief, Aircraft Engineering Division, FAA, Western Region, has been accomplished and incorporated into the autopilot system. This amendment becomes effective on July 10, 1968, for all persons except those to whom it was made effective immediately by telegram dated May 29, 1968.
85-18-03: 85-18-03 GENERAL ELECTRIC COMPANY: Amendment 39-5130. Applies to General Electric Model CJ610-8A, -9, and CF700-2D, -2D-2 turbine engines. Compliance is required as indicated unless already accomplished. To prevent failure of the stage 1 turbine disk, P/N 5011T75P01, with serial numbers beginning with the letters GATSRM, accomplish the following: Remove the disk from service in accordance with General Electric Alert SBs (CJ610) A72-142 or (CF700) A72-145, dated August 30, 1983, at or prior to accumulating 5,000 total cycles. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an alternative means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The General Electric Alert SBs (CJ610) A72-142 and (CF700) A72-145, dated August 30, 1983, described in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the SBs from the manufacturer may obtain copies upon request to Project Manager, CJ610/CF700, General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, Rules Docket No. 83-ANE-24, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 15, 1985.
2004-24-09: The FAA is adopting a new airworthiness directive (AD) for certain RRC 250-B and 250-C series turboshaft and turboprop engines. This AD requires a onetime inspection of the fuel nozzle screen for contamination, and if contamination is found, inspection and cleaning of the entire aircraft fuel system before further flight. This AD also requires replacing the fuel nozzle with a new design fuel nozzle, at the next fuel nozzle overhaul or by June 30, 2006, whichever occurs first. This AD results from 10 reports of engine power loss with accompanying collapse of the fuel nozzle screen, due to fuel contamination. We are issuing this AD to minimize the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel contamination and collapse of the screen in the fuel nozzle.
2000-05-16: This amendment adopts a new airworthiness directive (AD) applicable to Sikorsky Model S-61 helicopters. This action 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. The AD also requires creating a log card or equivalent record and implementing a recurring inspection of the web fittings. This amendment is prompted by the discovery of extensive cracking in the area of the web fittings. The actions specified in this AD are intended to prevent structural failure of the tail boom due to a crack or corrosion of certain web fittings and subsequent loss of control of the helicopter.