Results
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.
2023-02-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A321-251NX, A321-252NX, A321-253NX, A321-271NX and A321-272NX airplanes. This AD was prompted by an emergency exit slide deployment test on an Airbus Cabin Flex (ACF) overwing emergency exit, the emergency exit slide did not deploy due to disconnected slide release cable junction. This AD requires a one-time detailed inspection of the installation of the ACF overwing emergency exit slide release mechanism for discrepancies, and applicable corrective actions, 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.
2000-23-17: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, that currently requires opening the circuit breaker of the pneumatic sense line heater tape, installing an inoperative ring, and coiling and stowing the electrical wire to the circuit breaker of the pneumatic sense line heater tape. That AD also provides for an optional inspection, which, if accomplished, constitutes terminating action for deactivation of the pneumatic sense line heater tape. This amendment requires repetitive inspections of the subject area and corrective actions, if necessary, and provides for an optional terminating modification(s) for the repetitive inspection requirements. This amendment is prompted by the FAA's determination that the one-time optional terminating inspection in the existing AD does not adequately detect chafing, electrical arcing, or inadequate clearance of the subject area. The actionsspecified by this AD are intended to detect and correct such inadequate clearance, which could result in a hole in the fuel feed pipe caused by electrical arcing, and consequent fuel leakage and possible ignition of the fuel vapors.\n\n\tThe incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of December 27, 2000.\n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-36A030, dated April 2, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 28, 1998 (63 FR 20066, April 23, 1998).
88-13-02: 88-13-02 BRITISH AEROSPACE (BAe) PLC: Amendment 39-5955. Applies to Jetstream Model 3101 (includes Model 3100) (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated unless already accomplished. To reduce the possibility of engine torque oscillations resulting from improperly set propeller RPM levers and to provide remedial procedures if such a situation does occur from any cause, accomplish the following: (a) For airplanes with in-service engines, within the next 50 hours time-in-service after the effective date of this AD, or prior to further flight for airplanes when any overhauled or replacement engine or propeller governor is installed, check the propeller governor low RPM setting as described in Section 2, Accomplishment Instructions, of Garrett Engine Division (GED) Service Bulletin (SB) TPE331-76-0023, Revision 1, dated May 6, 1988. (1) If the low RPM setting is in between 95.5 percent to 96 percent, inclusive, nofurther action is required per this paragraph of the AD unless a replacement engine or propeller governor is subsequently installed. (2) If the low RPM setting is not in between 95.5 percent or 96 percent inclusive, prior to further flight adjust the low RPM setting to the range of 95.5 percent to 96 percent as described in the above SB. (b) Within 7 calendar days from the effective date of the AD, insert Advance Amendment Bulletin No. 1, dated April 13, 1988, into the Airplane Flight Manual, BAe Document No. HP.4.10, facing Page 4, Section 3, and operate the airplane accordingly. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium; Telephone (322) 513.3830 ext. 2710/2711. All persons affected by this directive may obtain copies of the appropriate document(s) referred to herein upon request to Garrett Engine Division, Post Office Box 5217, Phoenix, Arizona 85010; Telephone (602) 225-2548, or British Aerospace, Technical Librarian, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041; Telephone (703) 435- 9100; or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5955, becomes effective on June 16, 1988.
2023-04-19: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and GE90-115B model turbofan engines. This AD was prompted by a manufacturer investigation which discovered that florescent penetrant inspections (FPI) were not performed on the dovetail pressure face of certain high-pressure compressor (HPC) rotor spools at overhaul. This AD requires FPI of the affected HPC rotor stage 7-9 spool and, depending on the results of the inspection, replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2004-24-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires replacement of the retract actuator bracket attachment bolt (RABAB) of the main landing gear (MLG) with a new RABAB; reidentification of the MLG shock strut; an inspection for corrosion, fretting, or other damage of certain RABABs; and applicable corrective actions. The actions specified by this AD are intended to prevent failure of the RABAB, which could result in loosening of the actuator bracket and consequent failure of the MLG to retract, with considerable damage to other landing gear parts, including the MLG trunnion fitting. This action is intended to address the identified unsafe condition.
2022-19-14: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by a report that there is a possibility of the shoulder belt getting stuck during flight due to a step between the divan shroud chamfer and the sideledge panel. This AD requires installing, on the right- and left-hand side divan, a protective fairing covering on the divan shroud and the sideledge panel, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
83-12-03: 83-12-03 CESSNA: Amendment 39-4669. Applies to Model 441, S/N 441-0173 through 441- 0311 and 441-0001 through 441-0172 incorporating Service Kit SK441-37, airplanes certificated in any category. (Airplanes incorporating SK441-37 Revision A or later revisions are not affected.) Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To detect and correct a possible error in battery switch wiring which may contribute to thermal runaway of the nickel-cadmium batteries, accomplish the following: (a) Inspect and, if necessary, prior to further flight modify the dual battery switch installation as specified in Cessna Service Information Letter PJ83-9, dated April 22, 1983, or Revision 1 dated June 3, 1983. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by theManager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209, Telephone (316) 269-7000. This amendment becomes effective on June 28, 1983.
84-06-04: 84-06-04 MESSERSCHMITT-BOLKOW-BLOHM GmbH: Amendment 39-4834. Applies to HFB-320 airplanes as listed in HFB-320 Service Bulletin 55-8 dated September 14, 1983, certificated in all categories. Compliance is required as indicated unless previously accomplished. To prevent failure of the stabilizer/elevator outboard bearing housing fittings accomplish the following: A. Within the next 25 hours time in service or 45 days after the effective date of this AD, whichever occurs first, perform a one-time inspection of the stabilizer/elevator outboard bearing housing fittings in accordance with HFB-320 Service Bulletin 55-8 dated September 14, 1983. Fittings with cracks greater than 0.79 inches must be replaced prior to further flight. Fittings cracked 0.79 inches or less must be stop drilled per the service bulletin, but also must be replaced within six months. B. 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. 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 inspections and/or modifications required by this AD. This amendment becomes effective April 9, 1984.