Results
2004-09-28: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011 series airplanes, that currently requires the implementation of a corrosion prevention and control program either by accomplishing specific tasks or by revising the maintenance inspection program to include such a program. This action requires accomplishment of new specific tasks and visual inspections for corrosion of certain structural areas and repair if necessary, or revision of the maintenance inspection program. This amendment relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model L-1011 series airplanes, which indicate that, to ensure long-term continued operational safety, various structural inspections should be accomplished. The actions specified by this AD are intended to prevent structural failure of the airplane due to corrosion.
51-26-02: 51-26-02 LEAR: Applies to All L-2 Series Automatic Pilots. Compliance required at next 100-hour airplane inspection, but not later than January 1, 1952. Inspect all L-2 Series autopilot servos to determine whether servo clutches have green dot on the shaft at the output end of servo capstan shaft, or a green dot on or below the servo nameplate, or a yellow dot on the clutch housing. All clutches not so marked must be replaced. Replacement clutches will be supplied by Lear upon request. (Lear Service Bulletin No. L-2-16 dated October 26, 1951, covers this same subject.) This applies only to Servo Models 121C, 121D, 121F, 121G, 121H, 121J, manufactured prior to March 1, 1952. Reference Lear Service Bulletin No. L-2-44, dated May 24, 1954.
2021-21-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, A320, A321, A330-200, A330-200 Freighter, A330-300, A330-800, A330-900, A340-200, A340-300, A340-500, A340-600, and A380-800 series airplanes. This AD was prompted by a determination that repetitive disconnection and reconnection of certain parts manufacturer approval (PMA) nickel-cadmium (Ni-Cd) batteries during airplane parking or storage could lead to a reduction in capacity of those batteries. This AD requires replacing certain PMA Ni- Cd batteries with serviceable Ni-Cd batteries, or maintaining the electrical storage capacity of those PMA Ni-Cd batteries during airplane storage or parking. This AD corresponds to a previously proposed AD on type design Ni-Cd batteries with the same unsafe condition on the same model airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
52-05-03: 52-05-03 BELL: Applies to All Model 47 Helicopters Incorporating Engine Mount Assembly, P/N 47-612-11-1 or -5. Compliance recommended upon receipt of parts, but required not later than the next 25- hour inspection following receipt of parts or April 1, 1952, whichever occurs first. As a precautionary measure against the serious consequences resulting from the failure of this particular engine mount, Safety Strap Kit, P/N 47-612-132, must be installed. This kit can be obtained free of charge from the Bell Aircraft Corp., and must be installed in accordance with Bell Service Bulletin No. 87. AD 51-27-01 remains in effect and is used in conjunction with this directive. (Bell Service Bulletin No. 87 dated February 12, 1952, covers this same subject.)
2004-09-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that requires a one-time inspection for improper installation of the electrical wiring for the optional lighting in the cabin, and corrective actions if necessary. This action is necessary to find and fix improper installation of the electrical wiring of the basic/optional cabin lighting, which could result in overheating of the wiring and possible smoke/fire in the cabin during an emergency situation. This action is intended to address the identified unsafe condition.
53-13-01: 53-13-01 De HAVILLAND GYPSY QUEEN: Applies to All Model 70-4 Engines and to Those 70, 70-2, and 70-3 Engines Incorporating Modification G.1493. Compliance required not later than September 1, 1953. In order to prevent the loss of propeller control because of failure of the oil transfer mechanism, Modification G.1920, as described in de Havilland Engine Service Modification News Sheet GQ. 70 dated May 8, 1953, must be accomplished. Should Modification G.1728 not be incorporated, it is strongly recommended that it be embodied concurrently with Modification G.1920. The FAA concurs in this mandatory action. (de Havilland Modification News Sheet GQ. 70 dated May 8, 1953, available from de Havilland Aircraft Co., representative at Linden Airport, Linden, N.J., covers the same subject and describes method of repair.)
2021-22-14: The FAA is superseding Airworthiness Directive (AD) 2021-05-16 for certain Pratt & Whitney Division (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 model turbofan engines. AD 2021-05-16 required initial and repetitive replacements of the low- pressure turbine (LPT) 4th-stage air sealing ring segment assemblies with parts eligible for installation. AD 2021-05-16 also required initial and repetitive dimensional inspections of the LPT case for bulging and, depending on the results of the dimensional inspections, repair or replacement of the LPT case. This AD was prompted by notification to the FAA of an inadvertent omission in the LPT 4th-stage air sealing ring segment assembly part numbers. This AD requires initial and repetitive replacements of the LPT 4th-stage air sealing ring segment assemblies with parts eligible for installation. This AD also requires initial and repetitive dimensional inspections of the LPT case for bulging and, depending on the results of the dimensional inspections, repair or replacement of the LPT case. The FAA is issuing this AD to address the unsafe condition on these products.
2012-05-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes. This AD requires a general visual inspection for chamfer of the upper edge of each leaf spring, and rework if necessary. This AD also requires installing a new friction brake nut. This AD was prompted by reports that it was possible to inadvertently move the power levers through the flight idle gate into the beta range due to an un-chamfered leaf spring in the friction brake that may contact the power lever latch when the friction adjusting knob is fully loosened. We are issuing this AD to detect and correct an unsafe condition where both engines can inadvertently be operated in beta mode during flight and consequently reduce controllability of the airplane.
72-12-03: 72-12-03 HAWKER SIDDELEY AVIATION, LTD.: Amdt. 39-1457 as amended by Amendment 39-1542 is further amended by Amendment 39-1555. Applies to Hawker Siddeley de Havilland Model DH-104 "Dove" airplanes. Compliance is required on or before February 1, 1973. To prevent possible failure of the air bottles, P/N B.2994, used in the two main air reservoir assemblies, P/N C.51450, of the pneumatic system, replace the main air reservoir assemblies, P/N C.51450, located in the fuselage nose with serviceable assemblies, P/N SAS.388- 002, or SAS.388-003, containing air bottles P/N BAT.205-001. (Hawker Siddeley Technical News Sheet, Series: CT(104) No. 223, Issues 1 and 2 dated June 21, 1971, and September 28, 1971, respectively, cover this same subject.) Amendment 39-1457 became effective July 3, 1972. Amendment 39-1542 was effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by telegram datedAugust 31, 1972, which contained this amendment. This Amendment 39-1555 becomes effective November 13, 1972.
2004-10-01: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, and -20J turbofan engines. This AD clarifies a life limit for certain part numbers of 6th stage low pressure turbine (LPT) air seals, and requires their removal from service before accumulating 15,000 cycles-since-new (CSN). This AD results from reports of certain 6th stage LPT air seals possibly not being life tracked due to confusion from updates to the engine manuals. We are issuing this AD to prevent failure of the 6th stage LPT air seal, which could cause LPT damage resulting in an uncontained engine failure.
98-18-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive high frequency eddy current (HFEC) inspections to detect cracking on all surfaces of the upper recesses in certain latch support fittings of the cargo doorway, and replacement of cracked fittings with new fittings. The existing AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by reports indicating that the repetitive inspections required by the existing AD may not detect cracked fittings in a timely manner. The actions specified by this AD are intended to prevent the cargo door from opening while the airplane is in flight, which could result in rapid decompression of the airplane.
2021-21-12: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A2-20 model turbofan engines. This AD was prompted by flight data obtained from airplanes equipped with certain Rockwell Collins avionics and auto- throttle systems that demonstrated significant oscillation of the engine rotor revolution speed during flight. This AD requires initial and repetitive recalculation of the consumed and remaining service life of certain life-limited parts (LLPs). This AD also requires removal of an LLP prior to its approved life limit or within 90 days after the effective date of this AD, whichever occurs later. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-05: The FAA is superseding Airworthiness Directive (AD) 2021-18- 08, which applied to all Airbus SAS Model A319-171N airplanes; Model A320-271N, -272N, and -273N airplanes; and Model A321-271N, -272N, - 271NX, and -272NX airplanes. AD 2021-18-08 required repetitive inspections of the pylon/engine interface rods for damage, and applicable corrective actions, as specified in European Union Aviation Safety Agency (EASA) AD 2021-0177. AD 2021-18-08 also provided for limited installation of affected parts under certain conditions. Since the FAA issued AD 2021-18-08, operators reported that the requirements of EASA AD 2021-0177 were unclear. This AD retains the requirements of AD 2021-18-08, with clarified instructions, as specified in an EASA AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-10-09: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, and 500N helicopters. This action requires initial and repetitive inspections of each main rotor blade (blade) root for either cracks or paint and sealant cracking or separation between the lower surface root end fitting and the doubler. This amendment is prompted by one accident in which a blade separated from the helicopter, as well as eight other reports of cracked blades. The actions specified in this AD are intended to prevent failure of a blade resulting in separation of the blade and subsequent loss of control of the helicopter.
59-25-04: 59-25-04 LOCKHEED: Applies to All Model 188 Series Aircraft - Serial Numbers 1002 Through 1072. Compliance required as indicated. Insufficient clearance between the generator feeder wires and the leading edge rib at wing Station 221 together with deflection of the leading edge has resulted in abrasion of the insulation on the generator feeder wires and grounding of the generator feeder. (a) Inspect for evidence of abrasion not later than the next 8 hours' time in service with a light and mirror through fillet access doors N125 and N126 left and right without lowering the leading edge section. If the inspection shows evidence of abrasion, additional spacers must be installed prior to the next flight to obtain a minimum 0.38-inch clearance with the flange of the leading edge rib. If no evidence of abrasion is present, the inspection must be repeated at intervals of 60 hours' time in service but not to exceed 250 hours' time in service when additional spacers must be installed to provide at least 0.38-inch clearance. Functionally test the generator differential protection system in accordance with Lockheed Maintenance Manual, Section 24-1-0, page 201. (b) Within the next 250 hours' time in service inspect all wiring in the leading edge and power plant sections for actual or incipient abrasion of wires. If abrasion of wires or insufficient clearance is found, the conditions are to be corrected prior to the next flight. (Lockheed Electra Alert Service Bulletin 376 covers this same subject.)
2004-09-39: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 340B series airplanes equipped with Hamilton Sundstrand propellers. This amendment requires a one-time inspection of two remote controlled circuit breakers (RCCB), located in specific electrical compartments, to identify the part number, and replacement of the RCCBs with new RCCBs having a different part number if necessary. This action is necessary to ensure removal of 35-ampere (amp) RCCBs on a 50-amp electrical circuit. Incorrect RCCBs on an electrical circuit could result in erroneous tripping of the RCCBs (even though an overload condition does not exist), premature failure of the RCCBs, loss of power to the feather pump system, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
68-19-06: 68-19-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-656. Applies to Model BAC 1-11 200 and 400 Series airplanes. Compliance required as indicated, unless already accomplished. To prevent failure of the fuel line, P/N AB15-835, which connects the low pressure fuel filter to the auxiliary power unit, accomplish the following: (a) Within 75 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 75 hours' time in service from the last inspection, inspect fuel line, P/N AB15-835, which connects the low pressure filter to the auxiliary power unit, for signs of fuel leakage, in accordance with BAC 1-11 Alert Service Bulletin 49-A-PM 3579, Issue 1 or later ARB-approved issue or FAA-approved equivalent. (b) If the fuel line, P/N AB15-835, is found to be leaking fuel during the inspection required by paragraph (a), before the next flight, replace the defective fuel line with a serviceable part of the same part of the same part number or with a modified fuel line, P/N AB15-967, or improved P/N AB15-835 manufactured by the Dunlop Company. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the modified fuel line, P/N AB15-967, or improved P/N AB15-835 manufactured by the Dunlop Company, is installed. When the latter fuel line is installed, it should be renumbered as P/N AB15-967. This amendment becomes effective September 19, 1968.
2004-09-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-300 series airplanes, that requires modification of a certain ground cooling fan. This action is necessary to prevent overheating of the connecting terminals of the ground cooling fan, which could result in smoke or fire in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
2012-04-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by reports of the air-driven generator (ADG) failing to provide power during operational/function checks due to wires in the ADG power feeder cables being damaged. The damage was due to galvanic corrosion and inadequate silver-plating. This AD requires replacing ADG power feeder cables. We are issuing this AD to prevent galvanic corrosion on ADG power feeder cables, which could result in damage to the cable and consequently the cable may not be able to provide emergency electrical power to the airplane.
2021-21-09: The FAA is superseding Airworthiness Directive (AD) 2005-05- 18, which applied to certain The Boeing Company Model 737-600, -700, - 700C, -800, and -900 series airplanes. AD 2005-05-18 required repetitive inspections for cracking of the webs of the aft pressure bulkhead at a certain body station, and corrective action if necessary. This AD was prompted by cracking found in that inspection area on airplanes not identified in the applicability of AD 2005-05-18. This AD retains the requirements of AD 2005-05-18, revises the applicability to include additional airplanes, and adds an inspection for existing repairs on the newly added airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
97-08-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires a functional flow test and leak test to verify if the pressure reducing valve in the cargo fire extinguishing system is in a serviceable condition, and replacement of any faulty valve with a new valve prior to extended range twin-engine operations of the airplane. This amendment is prompted by a report that, during a scheduled maintenance check, an inoperative pressure reducing valve was found in the cargo fire extinguishing system. The actions specified by this AD are intended to ensure that a faulty pressure reducing valve is not installed, which could result in reduced fire protection of the cargo compartment of the airplane.
98-18-17: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-9-80 series airplanes and Model MD-90-30 and MD-88 airplanes, that requires a one-time inspection of the harness assembly of the tailcone emergency evacuation slide to determine the diameter of the swaged balls; reidentification of the harness assembly; and reinstallation or replacement of the assembly with a new assembly, if necessary. This amendment is prompted by a failed deployment of the tailcone emergency evacuation slide during a system test conducted by the manufacturer. The actions specified by this AD are intended to prevent failure of the tailcone emergency evacuation slide to deploy automatically due to incorrect diameter of the swaged balls on the wire rope of the harness assembly.
59-05-02: 59-05-02 de HAVILLAND: Applies to All Model 104 "Dove" Aircraft With Modification PP.173 Embodied. Compliance required as soon as possible but not later than March 30, 1959. (1) A case has been reported where faulty readings were obtained from the dipstick used in an oil tank P/N 4LT.475A/1, in which Modification PP.173 was embodied. This would result in low oil content which, on prolonged flights, might give rise to oil starvation with consequent engine seizure. (2) Within the period stated above, dipsticks must be removed from oil tanks with Modification PP.173 embodied and reworked as follows: (a) Measure along the dipstick a distance of 4.15 inches from the base and file a notch or deep score mark at this point. (This position also falls 0.65-inch above existing one-half mark.) (b) Obliterate the existing one- quarter and one-half marks. (c) Add a stamped arrow pointing to the notch or score mark followed by this marking "6 US gallons minimum accurate reading". (3) The above rework must be accomplished on spar oil tanks prior to fitment to aircraft. The British Air Registration Board considers this mandatory. The FAA concurs with this action and considers compliance therewith mandatory. (de Havilland TNS CT (104) No. 158 Issue 2 covers the same subject.)
2021-21-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of damage (burns) on the tail rotor blades (TRBs). This AD requires an inspection of each TRB for the general condition and any evidence of burns and replacement if necessary, 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.
69-11-03: 69-11-03\tBOEING: Amdt. 39-766 applies to Model 707-300B and 707-300C series airplanes listed as follows. AA Serial No. 20170, PA Serial Nos. 20030, 20031, 20033, and 20034, LU Serial No. 20123, OA Serial No. 20035, TP Serial No. 19969, LY Serial No. 20097, PK Serial No. 19866, NW, RD, PK and EJ airplane serial numbers on which rudder power control units purchased as spares from Bertea have been installed. \n\tCompliance required as indicated unless already accomplished. \n\tTo prevent cracking of the control rod end of the rudder power control unit, accomplish the following: \n\tPrior to next flight, remove any rudder power unit, Boeing Part Number 10-60815, having Bertea Serial Number 760 through 818 and replace with a power unit of the same part number but of a different serial number than noted above. Power units Numbers 760 through 818 may be returned to service when the rod end, Bertea Part Number 60043-9 (Schafer Part Number YTD 112A), has been replaced in accordance with FAA approved instructions from the manufacturer (Bertea). The airplane may not be ferried under the provisions of FAR 21.197(b) and (c). Airplanes may be ferried after issuance of individual special flight permits under the provisions of FAR 21.197(a)(1) and FAR 21.199 after a pre-takeoff determination that the rudder operates normally in the "Boost On" mode. Pursuant to FAR 21.199(a)(6), the limitations in the special flight permit will prohibit flights over congested areas or which may otherwise endanger persons or property on the ground. \n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated April 14, 1969.