Results
2024-22-04: The FAA is superseding Airworthiness Directive (AD) 2021-09- 03, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2021-09-03 required repetitive replacements of the emergency locator transmitter (ELT) antenna and repetitive inspections of the exterior fuselage skin around the ELT antenna attachment area. This AD was prompted by a report that there was an in-service failure of an ELT antenna that occurred before the repetitive replacement interval required by AD 2021-09-03, and that a terminating action was developed. This AD continues to require the actions in AD 2021-09-03 and requires replacement of the ELT antenna with a new ELT antenna, inspection of the exterior fuselage skin around the ELT antenna attachment holes, and repair if necessary; as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
66-06-01: 66-06-01\tBOEING: Amdt. 39-197 Part 39 Federal Register February 22, 1966. Applies to Model 707-200 and -300 Series Airplanes Equipped with Pratt & Whitney JT4 Engines.\n \n\tCompliance required as indicated, unless already accomplished. \n\n\tTo prevent loose B-nut on the thrust reverser P(s4) lines, accomplish one of the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n\n\t(a)\tWithin the next 1,200 hours' time in service after the effective date of this AD, replace P(s4) tube assemblies (located between the P(s4) engine bleed port and the thrust reverser directional control valve) that incorporate stainless steel 17-4 PH CRES sleeves with tube assemblies that incorporate case-hardened 316 CRES sleeves in accordance with Boeing Service Bulletin 2228, dated August 9, 1965, or later FAA-approved revision; or \n\n\t(b)\tWithin the next 1,200 hours' time in service after the effective date of this AD, replace P(s4) tube assemblies (locatedbetween the P(s4) engine bleed port and the thrust reverse directional control valve) that incorporate stainless steel 17-4 PH CRES sleeves with tube assemblies that incorporate nickel plated carbon steel sleeves or silver plated carbon steel sleeves in accordance with Boeing Service Letter 6-7161-4-8966, dated May 11, 1965, and within the next 3,000 hours' time in service after the effective date of this AD, replace the assemblies that incorporate nickel or silver plated carbon steel sleeves with tube assemblies that incorporate case- hardened 316 CRES sleeves in accordance with Boeing Service Bulletin 2228, dated August 9, 1965, or later FAA-approved revision.\n \n\tThis supersedes AD 65-25-01. \n\n\tThis directive effective February 22, 1966.
67-29-07: 67-29-07 SIKORSKY: Amdt. 39-504 Part 39 Federal Register November 3, 1967. Applies to Type S-55 Helicopters equipped with Wright R-1300 engines (Restricted and Normal Category). Compliance required as indicated. To prevent fatigue failure of the azimuth control rod assembly, P/N S1440-2105-1, accomplish the following: (a) Remove from service all control rod assemblies, P/N S1440-2105-1, with 725 or more hours' time in service on the effective date of this AD within the next 25 hours' time in service. (b) Remove from service all other control rod assemblies P/N S1440-2105-1, before the accumulation of 750 hours' time in service. (c) Within the next 15 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, inspect the control rod assembly in accordance with paragraph B of Sikorsky Service Bulletin No. 55B40-5, dated October 18, 1967, or later revisions approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Equivalent inspections may be approved by an FAA maintenance inspector. This amendment effective November 3, 1967.
2024-14-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports that the baggage bay discharge push-button annunciator (PBA) switch was making contact but was not fully engaged, and the tabs were not fully locked. This AD requires a verification of the baggage bay discharge PBA functionality and tab installation. The FAA is issuing this AD to address the unsafe condition on these products.
2003-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for the servo-controls located on the ailerons and replacement of the servo-controls with new servo-controls when they have reached their operational life limits. This action is necessary to prevent hydraulic leakage and failure of the servo-controls due to cracks in the end caps and along the barrel, which could result in loss of the ailerons and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2016-08-16: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 2E turboshaft engines. This AD requires removing the pre-TU 193 adjusted high-pressure/low-pressure pump and metering valve assembly and replacing it with a part that is eligible for installation. This AD also requires replacing the constant delta- pressure (delta-P) diaphragm of the fuel metering valve. This AD was prompted by reports of fuel flow non-conformities found during acceptance tests of Arriel 2E hydro-mechanical metering units (HMUs). We are issuing this AD to prevent failure of the delta-P diaphragm, which could result in an uncommanded in-flight shutdown and damage to the helicopter.
2016-08-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) 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 the discovery of a number of incorrectly calibrated angle of attack (AOA) transducers installed in the stall protection system. This AD requires replacement of affected AOA transducers. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
48-22-01: 48-22-01 PRATT & WHITNEY: Applies to Martin 202, Convair 240, and Douglas DC-6 Aircraft Powered With Double Wasp Engines Equipped With Water-Alcohol Injection System. Compliance required prior to next flight. If water injection lines to carbuertor are incorporated, the water system should be blanked off. This should be accomplished by disconnecting water feed line and installing 1/2-inch pipe plug in regulator entrance. Water vent line should be disconnected at regulator and 1/4-inch pipe plug installed. Water tank should be drained and pump disconnected to preclude inadvertent water flow or pump failure from dry running. If impracticable to secure lines with tape to prevent vibration, they should be removed and stored until system reactivated. Operation of aircraft should be restricted to dry takeoff power pending correction. Water-alcohol injection systems may be reactivated provided either of the following two modifications are accomplished: 1. (a) Incorporate general control solenoid valve part 40R1009 (or equivalent approved by P&W No. 139262) in vapor vent line extending from water tank to water regulator and, (b) Incorporate Mansfield and Green Co. check valve 31-B (P&W No. 139263) in water feed line extending from water pump to water regulator. The installation of these parts should be accomplished in accordance with instructions issued by Pratt and Whitney. 2. (a) Incorporate hydraulically operated check valve Airite Products No. 1015 (or equivalent approved by Pratt and Whitney) in vapor vent line extending from water tank to water regulator and, (b) Incorporate Parker check valve No. 527-10D (or equivalent approved by Pratt and Whitney) in water feed line extending from water pump to water regulator. The installations of these parts should be accomplished in accordance with Consolidated Vultee Drawing 6121501-P.
2003-14-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus airplanes, that requires repetitive inspections for foreign objects between the slider and the girt bar attachment fittings of the emergency escape slides; a one-time inspection for correct adjustment of the slide release mechanism and the girt bar attachment fittings, which would terminate the repetitive inspections; a one-time test for correct extension of the girt bar through the sliders; and corrective action, if necessary. The actions specified by this AD are intended to prevent failure of an emergency escape slide, which could result in a delayed evacuation in an emergency and consequent injury to passengers or crew. This action is intended to address the identified unsafe condition.
2023-21-02: The FAA is superseding Airworthiness Directive (AD) 2022-18- 14, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, A330-300 series, A330-800 series, and A330-900 series airplanes. AD 2022-18-14 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 2022-18- 14, and also requires revising the existing maintenance or inspection program, as applicable to incorporate additional new or more restrictive airworthiness limitations; as specified in two European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
47-21-08: 47-21-08 NAVION: (Was Mandatory Note 7 of AD-782-3.) Applies to Serial Numbers NAV-4-2 Through 411. To be accomplished not later than August 1, 1947. Short circuits have been reported caused between the generator lower terminal and the fitting on the hydraulic pump inlet hose. To prevent such short circuits, install a self-threading insulator No. 145-54053 (or equivalent) on the generator lower terminal stud. (NAA Field Service Bulletin No. 18 covers this change.)
2024-23-07: 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 reports of corrosion, damage, and rupture on the down lock spring assemblies of the main landing gear (MLG) and nose landing gear (NLG). This AD requires inspecting for affected MLG and NLG down lock springs and replacing affected down lock springs, and prohibits the installation of affected parts, 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.
2001-10-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes. This action requires repetitive inspections of any chemical oxygen generators and/or passenger, attendant, or lavatory service unit assemblies of the passenger oxygen system that have been replaced, to verify correct installation of the release pin in the generator firing mechanism of the oxygen generator; and corrective action, if necessary. This action is necessary to find and fix incorrect installation of the release pin in the generator firing mechanism, which could result in the unavailability of supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression. This action is intended to address the identified unsafe condition.
2016-08-08: We are superseding airworthiness directive (AD) 92-06-10 for SOCATA Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235E, and Rallye 235C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue failure of the nose landing gear wheel axle. We are issuing this AD to require actions to address the unsafe condition on these products.
2016-07-31: We are superseding Airworthiness Directive (AD) 2013-22-11 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.
2016-08-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes), modified by a particular supplemental type certificate (STC). This AD was prompted by a report of chafing found on the overflow sensor harness of the surge tank, and subsequent contact between the electrical wiring and fuel tank structure. This AD requires a one-time inspection for damage of the outer tank overflow sensor harness, and repair if necessary. This AD also requires modification of the sensor harness. We are issuing this AD to prevent chafing of the harness and subsequent contact between the electrical wiring and fuel tank structure, which could result in electrical arcing and a fuel tank explosion.
73-13-09: 73-13-09 ROCKWELL INTERNATIONAL: Amdt. 39-1667. Applies to Model 690 airplanes, Serial Numbers 11001 through 11063. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent failure of oil supply lines in the event of an engine fire, accomplish the following: Remove existing oil supply hose assembly and install tube assembly (P/N 610488-111), check valve (P/N 816T-6TT (.014)-12), hose assembly (P/N 610488-113), and attaching parts as listed in Rockwell International Service Bulletin 123, dated April 5, 1973, or equivalent parts and methods approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective June 25, 1973.
70-10-05: 70-10-05\tBOEING: Amdt. 39-989. Applies to Model 707 and 720 series airplanes listed in Boeing Service Bulletin 2108 Revision I dated 28 December 1965. \n\n\tWithin 200 hours time in service after the effective date of this AD and after each emergency extension, inspect crank arm 65-7195 and pulley bracket 69-1087 for cracks and measure cable tension in accordance with instructions contained in the 707/720 maintenance manual. Inspections may be discontinued after modification indicated below is accomplished. \n\n\tWithin 2500 hours time in service after effective date of this AD, unless already accomplished, modify all airplanes in accordance with Boeing Service Bulletins 2108 Revision I, dated 28 December 1965 and 2108A, dated 24 May 1965, or later FAA approved revisions to these service bulletins or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tThis amendment becomes effective May 16, 1970.
2024-23-06: The FAA is adopting a new airworthiness directive (AD) for certain MD Helicopters, LLC (MDHI), Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD was prompted by a report of a seized and damaged roller bearing in the pilot interconnecting cyclic torque tube (torque tube) assembly. This AD requires repetitively inspecting the torque tube assembly and roller bearings, and depending on the results, replacing parts, or accomplishing additional inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2016-08-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-223F and -243F airplanes. This AD was prompted by a report of missing fasteners in certain locations of the fuselage during production. This AD would require inspecting for missing, damaged, or incorrectly installed fasteners; and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the fuselage due to missing, damaged, or incorrectly installed fasteners, which could result in reduced structural integrity of the fuselage.
2016-07-28: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD requires repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and corrective actions if necessary. This AD was prompted by reports of cracking at certain stringers, associated end fittings, and skins in the center wing fuel tank where the stringers meet the end fittings. We are issuing this AD to detect and correct cracking in the center wing lower skin. Such cracking could cause structural failure of the wings.
47-50-09: 47-50-09 FAIRCHILD: Applies to 24R and 24W Series Aircraft. Inspection required each 100 hours of operation. Inspect the landing gear fittings near the lower longeron attachment and also the fuselage fittings for cracks. Cracks in the strut not exceeding 1/8 inch in length may be repaired by electric arc welding. Cracks in excess of 1/8 inch in length should be stop drilled and oxyacetylene welded, and the landing gear strut should be re-heat-treated to 180,000 pounds per square inch. (Fairchild Service Bulletin No. 41-8 dated June 23, 1941, covers this subject.)
71-26-03: 71-26-03 SIKORSKY AIRCRAFT: Amdt. 39-1363. Applies to Sikorsky S-62A and S- 55 type Helicopters certified in all categories. Compliance required as follows: To preclude the failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415. 1. Unless already accomplished within the last 95 hours in service, inspect the servo support bracket within the next 25 hours in service after the effective date of this AD, in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later FAA- approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Inspect the bracket within 120 hours in service after the inspection in paragraph 1 of this airworthiness directive and every 120 hours thereafter in accordance with Part I subparagraph B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 3. Conduct fluorescent magnetic particle inspection in accordance with Part II Accomplishment Instructions of SIK S/B 55B40-6 or 62B40-8 as applicable at gear box overhaul or 1250 hours, whichever comes first; or an alternate method approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 30, 1971.
2016-08-07: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-22B and RB211-524 turbofan engines with low- pressure turbine (LPT) support roller bearing, part number (P/N) LK30313 or P/N UL29651, installed. This AD requires removal of certain LPT support roller bearings installed in RR RB211-22B and RB211-524 engines. This AD was prompted by a report of a breach of the turbine casing and release of engine debris through a hole in the engine nacelle. We are issuing this AD to prevent failure of the LPT support roller bearing, loss of radial position following LPT blade failure, uncontained part release, damage to the engine, and damage to the airplane.
2016-07-18: We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN-235-200 and CN-235-300 airplanes. This AD was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. This AD requires modification of the location and routing of the engine fire detection system. We are issuing this AD to prevent unnecessary engine in-flight shutdown, which could result in reduced controllability of the airplane.