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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.
2004-09-29: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona) (Honeywell) TPE331-10 and -11 series turboprop engines with certain part numbers (P/Ns) and serial numbers (SNs) of first stage turbine disks. This AD requires initial and repetitive fluorescent penetrant inspections (FPIs) and eddy current inspections (ECIs) of the affected first stage turbine disks. This AD results from a report of a first stage turbine disk found cracked at the disk bore. The crack originated from a localized; melt related, low-alloy area of the disk. We are issuing this AD to prevent cracked first stage turbine disks from causing uncontained disk separation, resulting in engine damage and shutdown and damage to the airplane.
98-18-08: This amendment adopts a new airworthiness directive (AD) that applies to certain Bombardier Inc. (formerly deHavilland Inc) Model DHC-3 (Otter) airplanes that have been modified in accordance with A.M. Luton Supplemental Type Certificate (STC) No. SA3777NM. This AD requires modifying the airplane s electrical system. The actions specified by this AD are intended to prevent electrical system failure caused by inadequate electrical system design, which could result in the loss of the engine instruments or a possible electrical fire in the airplane s cockpit.
2021-21-10: The FAA is adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as chafing damage in the port wing skin caused by the fuel system finger filters. This AD requires inspecting the wing internal skin for chafing and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
53-18-01: 53-18-01 CESSNA: Applies to All Model T-50 Aircraft. Compliance required by November 1, 1953. As a result of reported failures of the outer bearing in the Goodrich Model 751A/M, G-3- 49A, 7.50-10 main gear assembly, each resulting in loss of a wheel, the following should be accomplished if the outer bearing has not been replaced since the airplane was converted from military to civil operation. If the outer bearing has been replaced subsequent to that time, compliance only with item 1 is required. 1. Not later than the date specified above, replace the 1 7/16-inch washer located between the axle nut and the inner bearing cone with a washer 1 7/8 inch outside diameter, 0.953 + 0.005 inch inside diameter and 0.093 + 0.005 inch thick manufactured from SAE 1010 or equivalent. This precautionary measure will not prevent bearing failure but may prevent the wheel from coming off the axle during landing in the event of a bearing failure. 2. At the time of item 1 and at every 100 hours of operation thereafter until the bearing is replaced, check wheel side movement, inspect bearing and replace bearing as necessary. Replacement should be accomplished with Timken Cone No. 07100 and Cup No. 07196 or an equivalent bearing. (B.F. Goodrich Co. Service Bulletin No. 36, revised April 20, 1953, covers this same subject and supplies information for the fabrication of the new washer and for ordering proper replacement bearings.)
2004-09-35: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires removing the two direct current (DC) over- voltage/feeder-fault test switches from the Test 2 Panel of the generator control unit, and follow-on actions. This action is necessary to prevent loss of the DC generators, which could result in the loss of normal electrical power to the airplane and increased pilot workload. This action is intended to address the identified unsafe condition.
59-10-09: 59-10-09 PRATT & WHITNEY: Applies to Following Turbo Wasp JT3C-6 Engines: JT3C-6 Engines Prior to Serial Numbers P630735B, Except P630406B Through P630413B, P630607B Through P630609B, P630614B Through P630618B, P630623B Through P630635B, and P630637B. JT3C-6 Engines Prior to Serial Numbers P630742D, Except P629708D, P630612D, P630315D, P630317D, P630319D Through P630325D, P630610D Through P630613D, P630619D Through P630622D, and P630636D. Compliance required as indicated. As a result of two third-stage turbine blade failures, it will be necessary to replace by 300 hours' of blade operating time, the P/N 271303 blade prior to change J-3 and P/N 371603 blade prior to change C-3. Third stage turbine blades P/N 271303, change J-3 and P/N 371603, change C-3, or later, do not require this replacement. (P&W Service Bulletin, Chapter 72-8 dated April 3, 1959, of the Heavy Maintenance Manual, P/N 367069 covers this same subject.)
98-16-02: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-16-02 which was sent previously to all known U.S. owners and operators of Eurocopter France Model SA 3180, SA 318B, SA 318C, SE 3130, SE 313B, SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by individual letters. This AD requires an initial and recurring visual inspections of the upper and lower surfaces of the tail rotor blade (blade) skin for cracks. If a crack is found, replacing the blade with an airworthy blade is required. This amendment is prompted by a report of a crack on the blade skin near an attachment bolt on the blade cuff stem. This condition, if not corrected, could result in fatigue failure of a blade and subsequent loss of control of the helicopter.
2021-21-01: The FAA is superseding Airworthiness Directive (AD) 2019-05- 06, which applied to certain Airbus Helicopters Deutschland GmbH Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, and EC135T3 helicopters. AD 2019-05-06 required replacing the retaining ring, inspecting the hoist cable hook assembly, and, if necessary, replacing the elastomeric energy absorber. This AD continues to require the actions specified in AD 2019-05-06, and also requires a modification or replacement of the hoist cable hook assembly that would terminate the repetitive inspections and retaining ring replacements, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report that a hook detached from the hoist cable. The FAA is issuing this AD to address the unsafe condition on these products.