Results
48-12-02: 48-12-02 DOUGLAS: Applies to All C54-DC Serial and the Following DC-4 Airplanes: 42904 Through 42943, 42948 Through 42952, 42982 Through 42996, 43065 Through 43068, 43071, 43072, 43093, 43094, and 43102. \n\n\tTo be accomplished not later than the date established in accordance with the provisions of Special Civil Air Regulation Serial Number SR-329, or any subsequent regulation affecting this compliance date. \n\n\tAs a result of investigation of heater fires, the following changes are to be accomplished in the nose and cabin heater installation: \n\n\t1.\tInstall steel firewall at Station 260 (cabin forward bulkhead) from ceiling level to top of bulkhead to provide isolation between heater compartment and the space between cabin ceiling and top of fuselage. Also, replace present wood panels under heaters with metal panels. \n\n\t(Douglas Service Bulletin DC-4 No. 47 covers this same subject.) \n\n\t2.\t(a)\tInstall all heater control components in airtight steel containers. \n\t\t(b)\tReplace present heater fuel supply pumps with a single electric driven pump attached to No. 2 main fuel tank. \n\n\t\t(c)\tProvide shrouds around all heater fuel line fittings in fuselage. \t \n\n\t\t(d)\tInstall a fire detector and extinguisher system for the nose heater and cabin heaters. \n\n\t(Douglas Service Bulletins DC-4 Nos. 64 and 64 addendum cover this same subject.) \n\n\tIn some cases, operators have obtained approval from FAA Regional Offices for systems which differ in arrangement and detail from the above provisions. Designs which have been separately approved in this manner are considered to meet the intent of this Note. \n\n\tThis supersedes AD 46-39-02.
2005-19-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800 and - 900 series airplanes. This AD requires installing an updated version of the operational program software (OPS) and certain other software in the flight management computers (FMCs); and doing configuration checks to ensure that certain software is properly installed and doing other specified actions. This AD also requires reinstalling software, if necessary. This AD results from one operator reporting FMC map shifts on several Model 737-400 series airplanes with dual FMCs, using OPS version U10.4A. We are issuing this AD to prevent the FMC from displaying the incorrect actual navigation performance value to the flightcrew, which could prevent adequate alerting of a potential navigation error. This condition could result in a near miss with other airplanes or terrain, or collision if other warning systems also fail.
65-04-01: 65-04-01 BELL: Amdt. 39-36 Part 39 Federal Register February 17, 1965. Applies to Model 47 Series Helicopters Equipped With Transmissions Serial Numbers B12-885 through B12-969. Compliance required within 25 hours' time in service after the effective date of this AD, unless previously accomplished in accordance with Bell Helicopter Company Service Bulletin No. 141SB. Some of the P/N 47-620-535-1 outer races installed in the freewheeling clutch of transmissions listed herein may not have been tempered properly. To eliminate the possibility of excessive wear of these races and subsequent malfunction of the freewheeling clutch, conduct a hardness test on these races as described by Bell Service Bulletin No. 141SB. If the hardness does not fall within the limits prescribed by the bulletin, replace the outer race with one which is within the limits before further flight. This directive effective February 17, 1965.
2018-12-03: We are superseding Airworthiness Directive (AD) 2013-11-09 for all Safran Helicopter Engines, S.A., Arrius 2B1 and 2F turboshaft engines. AD 2013-11-09 required the repetitive replacement of the fuel injector manifolds and privilege injector, or only the privilege injector. This AD retains the repetitive hardware replacement requirements of AD 2013-11-09, but only allows replacement pipe injector preferred assembly, part number (P/N) 0 319 73 044 0, on the Arrius 2F engines. This AD was prompted by reports of engine flameouts as a result of reduced fuel flow due to the presence of coking. We are issuing this AD to address the unsafe condition on these products.
65-03-01: 65-03-01 BEECH: Amdt. 39-26 Part 39 Federal Register January 28, 1965 is amended by Amendment 39-1263. Applies to Models AT-11, C18S, D18S, E18S and C-45 series airplanes which have been modified in accordance with one or more of Airline Training, Inc. Supplemental Type Certificates Nos. SA4-113, SA-119, SA4-128, SA2-280, SA2-383, SA2-523, SA2-820, SA2-1016 and SA2-1246. Compliance required as indicated. Freezing of moisture in the continuous (piano) hinges which attach the stabilizer-to- elevator gap seal strips causes the spring loaded strips to stick in a deflected position. The deflected strips act as aerodynamic spoilers which cause serious longitudinal control difficulties. In order to preclude this condition, accomplish the following: Within 25 hours' time in service after the effective date of this AD, and thereafter at intervals not exceeding 50 hours' time in service, or 60 days, whichever occurs first, accomplish the following or equivalent approved by Engineering and Manufacturing Branch, FAA Southern Region. (a) Apply a good coverage of Federal Specification VV-L-800 oil to the top and bottom sides of both upper and lower stabilizer-to-elevator gap seal strip piano-type hinges. An acceptable alternate lubricant is a mixture of MIL-G-81322 (MIL-G-25760) or MIL-G-23827 (MIL-G-7118) grease and methyl ethyl ketone or aliphatic naphtha (Varsol), to a consistency suitable for application with a squirt-type oil can or an equivalent material approved by Engineering and Manufacturing Branch, FAA Southern Region. (b) While the mixture is being applied, deflect the seal strips several times to assure maximum penetration of the fluid into the hinge pin and hinge mating areas. Amendment 39-26 was effective February 8, 1965. Amendment 39-1263 becomes effective upon publication in the Federal Register.
47-21-05: 47-21-05 NAVION: (Was Mandatory Note 4 of AD-782-3.) Applies to Serial Numbers NAV-4-11 Through 21 and 44 Through 47. To be accomplished not later than August 1, 1947. Replace the original propeller control with one that incorporates a positive friction lock in accordance with NAA Kit Drawing 145-89011. (NAA Field Service Bulletin No. 5 covers this change.)
47-32-05: 47-32-05 BELL: (Was Mandatory Note 5 of AD-1H-1.) Applies to Model 47B. Compliance required before next flight. Remove the main rotor mast spinner assembly from all Model 47B helicopters, in order that the possibility of its jamming the mast control tubes, in the event it becomes loose during flight, is eliminated. (Bell Service Bulletin 47C38 dated May 15, 1947, also covers this same subject.)
49-26-01: 49-26-01 BEECH: Applies to All Models 35 and A35 Airplanes Equipped With an Automatic Reel Trailing Antenna. Compliance required by January 1, 1950. Because of reported cases of jamming of the controls due to the rear antenna guide rail being knocked loose by the movable pulley assembly (P/N 1X007) when the antenna wire was broken or came loose in flight, the following should be accomplished: (1) Tack a plywood block to the wood antenna strip in the aft section of the fuselage, with 3/4 inch No. 18 flathead nails. The rear end of the block should be at least 1 1/4 inches forward of the centerline of the aft pulley. (2) Stretch a rubber bumper ring over the block. (Beech Service Bulletin Model 35 No. 13 and Model A-35 No. 4 dated March 15, 1949, covers this same subject.)
2018-13-05: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 turboshaft engines. This AD was prompted by recent reports of failures of the direct drive fuel control gears and bearings in the hydraulic torque sensor gear assembly, part number (P/N) 3101726-3. This AD requires initial and repetitive engine oil filter sampling and analysis of the affected engines and inspections of certain hydraulic torque sensor gear assemblies. We are issuing this AD to address the unsafe condition on these products.
2018-12-07: We are superseding Airworthiness Directive (AD) 2015-24-06 for certain Gulfstream Aerospace Corporation Model GVI airplanes. AD 2015- 24-06 required repetitive breakaway torque checks and torqueing of the main landing gear (MLG) brake inlet self-sealing couplings and inserting a dispatch and takeoff limitation to the limitations section of the airplane flight manual. This AD requires modifying the MLG and brake assembly. This AD was prompted by reports of the self-sealing couplings on the MLG brake inlet fitting backing out of the fully seated position. We are issuing this AD to address the unsafe condition on these products.
89-02-02: 89-02-02 BOEING: Amendment 39-6100. Applicability: Model 757 series airplanes, Group 1 and Group 2, as listed in Boeing Alert Service Bulletin 757-32A0081, dated June 24, 1988, certificated in any category. \n\n\tCompliance: Required within the next 120 days after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the loss of airplane braking due to a single hydraulic failure, accomplish the following: \n\n\tA.\tInspect Group 1 and 2 airplanes left and right alternate antiskid valve module return ports for proper check valve configuration, and correct, if necessary, in accordance with Boeing Alert Service Bulletin 757-32A0081, dated June 24, 1988. \n\n\tB.\tOn Group 1 airplanes, remove the reducer unions installed in the left and right alternate brake metering valve module return ports and install check valves, in accordance with Boeing Alert Service Bulletin 757-32A0081, dated June 24, 1988. \n\n\tC.\tAn alternate means of compliance or adjustment ofthe compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial 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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6100, AD 89-02-02) becomes effective February 8, 1989.
2005-19-01: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model ERJ 170 airplanes. This AD requires inspecting the hydraulic pressure tubes at the outlet of the engine-driven hydraulic pumps to determine the part and serial numbers; and replacing hydraulic pressure tubes having certain serial numbers with new hydraulic pressure tubes. This AD results from failure of a hydraulic system due to leakage of hydraulic fluid from a crack in the pipe coming from the pressure side of the engine-driven pump. We are issuing this AD to prevent cracking of the hydraulic pressure pipes, which could result in failure of hydraulic system 1 or 2 or both, and consequent reduced controllability of the airplane.
65-02-03: 65-02-03 RAJAY: Amdt. 39-21 Part 39 Federal Register January 16, 1965. Applies to the Following Aircraft Equipped With Rajay Model 315A10 Turbochargers Installed by Supplemental type Certificate Approvals: Aero Commander 500B STC SA529WE; Aero Commander 500A STC SA583WE; Piper PA-23-250 STC SA539WE; Piper PA-24-250 STC SA811WE; Piper PA-23 and PA-23-160 STC SA3-1637; Cessna 310 Riley Rocket STC SA385WE; Cessna 310 and 310B through 310H STC SA97SO; Cessna 320 STC SA285SO; and Helio 500 STC SA305SO. Compliance required as indicated. A number of cracks in the turbocharger turbine scroll have occurred. To prevent possible turbine scroll failures, accomplish the following: (a) Within 25 hours' time in service after the effective date of this directive, unless previously accomplished within the last 75 hours' time in service, and at intervals thereafter not to exceed 100 hours' time in service from the last inspection, visually inspect the turbocharger turbine scroll for cracks unless the turbocharger has been made inoperative by disconnecting the control or a placard has been placed in the cockpit prohibiting turbocharger operation. (b) If cracks are found, make the turbocharger inoperative by disconnecting the controls or install a placard in the cockpit in full view of the pilot that reads "Do not operate turbochargers", until the turbocharger scroll is replaced. (c) The repetitive inspections required by (a) may be discontinued only when a turbocharger turbine scroll P/N TC-6-11A has been installed. (d) Operators who have not kept records of hours' time in service of turbocharger operation shall substitute airplane hours' time in service in lieu thereof. (Rajay Service Letter No. 2 dated October 26, 1964, covers this subject.) This directive effective January 10, 1965. Revised March 10, 1967.
64-28-03: 64-28-03 PIPER: Amdt. 39-15 Part 39 Federal Register December 24, 1964. Applies to Model PA-30 Aircraft, Serial Numbers 30-1 through 30-565. Compliance required within 30 hours' time in service after the effective date of this AD, unless already accomplished: As a result of instances of progressively stronger stabilator vibration, accomplish the following: Install a new design stabilator torque tube, Piper P/N 22655-07, in accordance with the instructions attached to Piper Service Bulletin No. 222A, dated August 10, 1964, or an equivalent modification approved by the Engineering and Manufacturing Branch, FAA Eastern Region and then remove the "Do not exceed 205 m.p.h. IAS" placard. NOTE: The original stabilator torque tube removed during compliance with this AD should be destroyed to avoid inadvertent reinstallation. (Piper Service Letter No. 428, dated June 30, 1964, and Piper Service Bulletin No. 222A dated August 10, 1964, pertains to this subject.)This supersedes AD 64-16-07. This directive effective December 24, 1964.
2018-12-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-300ER series airplanes. This AD requires replacing the water filter assembly in certain steam ovens. This AD was prompted by a report that water can enter the steam oven cavity and become heated and then released when the oven door is opened. We are issuing this AD to address the unsafe condition on these products.
47-32-18: 47-32-18 BELLANCA: (Was Service Note 1 of AD-773-5.) Applies to Models 14-13, 14-13-2 Serial Numbers 1075, and Up. Compliance required prior to October 15, 1947, and after each 25 hours of operation. Remove the washer and cotter pin from the clevis bolt which holds on the aileron idler sprocket located at the top center of the control yoke and back off the sprocket. Lubricate the entire bearing surface of the clevis pin with oil. Reinstall sprocket and washer, and safety with new cotter pin of same type (AN 380-3-3). (Bellanca Service Bulletin No. 9 covers the same subject, and the installation of a grease fitting to avoid removing the sprocket.)
2005-18-22: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Premier 1 390 airplanes. This AD requires you to verify minimum clearances to correct chafing conditions in the powerplant left-hand and right-hand engine installations. This AD results from reports of inadequate left-hand and right-hand engine assembly cable, wire, and hose routing clearance. We are issuing this AD to detect and correct chafing conditions in the engine installation, which could result in leaking flammable fluids near an ignition source. This failure could lead to fire damage or loss of airplane control.
76-02-08: 76-02-08 UNITED AIRCRAFT OF CANADA LIMITED: Amendment 39-2503. Applies to all PT6T-3 and PT6T-6 series turboshaft engines. Compliance required as indicated unless previously accomplished. To preclude leakage of the Sundstrand Aviation 025277 series fuel pump without the part number 5002557 injector cap and screen assembly, accomplish the following: (a) Within the next 25 hours in service after the effective date of this A.D., unless previously accomplished, inspect the fuel pump in accordance with paragraph 2 Accomplishment Instructions detailed in Pratt & Whitney Aircraft of Canada Limited Special Instruction No. 5-75 dated August 12, 1975, or approved equivalent inspection. (b) Within the next 250 hours in service after the effective date of this A.D., unless previously accomplished, install part number 5002557, injector cap and screen assembly, in accordance with paragraph 2 Accomplishment Instructions, Pratt & Whitney Aircraft of Canada Limited Engine Service BulletinNo. 5111 dated September 4, 1975 or approved equivalent alteration. The aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the inspection or alteration can be accomplished. Upon submission of substantiating data, through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this A.D. An equivalent alteration or inspection must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. This amendment is effective February 5, 1976.
2018-12-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This AD requires modifying the main beam assembly of the forward engine mount. We are issuing this AD to address the unsafe condition on these products.
88-01-10 R1: 88-01-10 R1 SHORT BROTHERS: Amendment 39-5819 as amended by amendment 39-6011. Applies to Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3667, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude failure of the horizontal stabilizer attach fittings, accomplish the following: A. Within the next 3 months after the effective date of this AD, inspect the interference fit bushings in each of the four horizontal stabilizer attach fittings in accordance with Shorts Service Bulletin Number SD360-55-10, dated November 1985. B. If the bushing is found to be loose in its fitting and the movement exceeds 0.005 inch, replace the fitting before further flight. C. If the bushing is found to be loose in its fitting and the movement does not exceed 0.005 inch, replace the fitting within the next 60 days. D. 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. E. 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 documents from the manufacturer may obtain copies upon request to Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. These documents may be examined at the 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, 39-6011, amends AD 88-01-10, Amendment 39-5819. This Amendment, 39-6011, becomes effective October 10, 1988.
64-27-04: 64-27-04 VERTOL: Amdt. 39-9 Part 39 (New) Federal Register December 5, 1964. Applies to Models H-21 and 42 Series Helicopters. Compliance required as indicated. As a result of a fatigue failure of a wood rotor blade root socket, P/N 22R1364-1, accomplish the following: (a) Conduct a daily visual inspection, using a magnifying glass of at least 8-power, of wood rotor blade root sockets, P/N 22R1364-1, with 750 or more hours' time in service as of the effective date of this AD, for cracks in the slot area between the inboard clamp bolt and the relief hole at the inboard end of the slot while supporting the rotor blade tip so that the blade does not rest on the droop stop. (b) Replace any cracked socket before further flight. (c) Within 25 hours' time in service after the effective date of this AD retire from service all wood rotor blade root sockets, P/N 22R1364-1, having 725 or more hours' time in service on the effective date of this AD. (d) Upon theaccumulation of 750 hours' time in service, retire from service all wood rotor blade root sockets, P/N 22R1364-1, having less than 725 hours' time in service on the effective date of this AD. This directive effective December 10, 1964.
64-24-05: 64-24-05 PIPER: Amdt. 826 Part 507 Federal Register October 24, 1964. Applies to Model PA-25-235 Aircraft, Serial Numbers 25-02, 25-2000 through 25-2931. Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished. Air leaks, which permit entrance of engine fumes into the cockpit, exist in the area of the fuselage right main landing gear fittings. To correct this condition, accomplish the following: Install seals, Piper Kit Number 756824 or FAA approved equivalent, at the front and rear right main landing gear fittings as indicated on the sketch on the reverse side of Piper Service Bulletin No. 221 dated August 27, 1964. (Piper Service Bulletin No. 221 dated August 27, 1964, pertains to this same subject.) This directive effective October 24, 1964.
2018-12-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks found in the rear spar web and lower chord on the left and right wings. This AD requires repetitive detailed inspections for cracking of the rear spar web and lower chord, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
88-18-05: 88-18-05 SHORT BROTHERS, PLC: Amendment 39-5993. Applies to Model SD3-60 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z," in accordance with accomplishment instructions in Service Bulletin SD360-34-09, dated March 1984. B. 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 Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. These documents may be examined at the 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, 39-5993, becomes effective September 7, 1988.
2005-18-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-200 and A340-300 series airplanes. This AD requires a one-time inspection for discrepancies of the spotfacing for the pylon-to-engine attachment bolts on the pyramid forward fitting of the engine pylon, and repair if necessary. This AD results from a report that, during a routine inspection, it was found that the diameter of the spotfacings was too small for two of the pylon-to- engine attachment bolts on the pyramid forward fitting. We are issuing this AD to prevent reduced structural integrity of the pylon-to-engine attachment bolts on the pyramid forward fitting, which could result in separation of an engine from the airplane.