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2004-10-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-215-6B11 series airplanes, that currently requires inspections to detect cracking in the rear engine mount struts, and replacement of struts with new struts, if necessary; and the eventual replacement of all struts with new struts. This amendment requires adding repetitive detailed inspections to detect cracking in the rear engine mount struts and replacement of struts with new struts, if necessary. This amendment also expands the applicability of the existing AD and makes the replacement of all struts with new, machined struts an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent failure of the rear engine mount struts, which could subsequently result in reduced structural integrity of the nacelle and engine support structure. This action is intended to address the identified unsafe condition. DATES: Effective June 21, 2004. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 21, 2004. The incorporation by reference of Canadair Alert Service Bulletin 215-A3040, dated September 2, 1992, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 4, 1994 (59 FR 10272, March 4, 1994).
67-23-03: 67-23-03 BRITISH AIRCRAFT: Amdt. 39-461, Part 39, Federal Register August 4, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated. To prevent failure of the reverse thrust plunger unit rods P/N AC 39-117, accomplish the following: (a) Within the next 155 hours' time in service after the effective date of this AD and thereafter at an interval not to exceed 600 hours' time in service from the initial inspection, remove and dismantle reverse thrust plunger units P/N AC 39A 111 and visually inspect plunger rods P/N AC 39-117 for cracks, distortion, or other defects in accordance with British Aircraft Corporation Alert Service Bulletin No. 76-A-PM 2837 or later ARB-approved issue, or FAA- approved equivalent. (b) Replace cracked, distorted, or defective plunger rods, P/N AC 39-117, with serviceable plunger rods of the same part number before further flight. (c) Within the next 1,000 hours time in service after the effective date of this AD, replace reverse thrust plunger units P/N AB 39 A 111 with plunger units P/N AB 39 A 3477 in accordance with British Aircraft Corporation Service Bulletin No. 76-PM 2837 or later ARB- approved issue or FAA-approved equivalent. (d) The inspections required by paragraph (a) may be discontinued after reverse thrust plunger units P/N AB 39 A 111 have been replaced with plunger units P/N AB 39 A 3477 in accordance with paragraph (c). This amendment effective August 4, 1967.
2012-04-11: We are superseding two existing airworthiness directives (AD). One existing AD is for Airbus Model A319, A320, and A321 series airplanes without Airbus modification 26017. That AD currently requires replacing the flight warning computers (FWCs). The other existing AD is for Airbus Model A320 and A321 series airplanes on which Airbus modification 24612 or Airbus Service Bulletin A320-31-1080 has not been accomplished. That existing AD currently requires revising the limitations section of the airplane flight manual. This new AD requires replacing both FWC units with certain FWC units. This AD was prompted by in-service events of thrust lever mismanagement and a manufacturer analysis on the failure to follow procedure or heed existing cockpit cues. The analysis of the thrust lever management issue showed two categories of scenarios that could lead to thrust asymmetry during landing, with controllability and deceleration consequences. We are issuing this AD to prevent thrust asymmetry conditions which could result in loss of control of the airplane during landing.
2021-24-10: The FAA is superseding Airworthiness Directive (AD) 2021-09-04 for all Austro Engine GmbH E4 and E4P model diesel piston engines. AD 2021-09-04 required replacing a certain oil pump as well as the oil filter and engine oil. This AD was prompted by reports of an oil pump blockage on E4 model diesel piston engines. This AD requires replacing a certain oil pump as well as the oil filter and engine oil. The FAA is issuing this AD to address the unsafe condition on these products.
2012-06-14: We are adopting a new airworthiness directive (AD) for PW JT9D-7R4G2 and -7R4H1 turbofan engines. This AD was prompted by the determination that a new lower life limit for high-pressure turbine (HPT) 1st stage air seals, part number (P/N) 735907, is necessary. This AD establishes a new lower life limit for HPT 1st stage air seals, P/N 735907, and requires removing them from service using a drawdown schedule. We are issuing this AD to prevent critical life-limited rotating engine part failure and damage to the airplane.
96-10-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, and -30 series airplanes and KC-10A (military) airplanes, that requires inspections to detect cracks of the upper aft mating bolt hole of the wing pylon truss fittings, and various follow-on actions. This amendment is prompted by reports of cracks found in the upper aft mating bolt hole of the wing pylon truss fitting located near the engine forward mount on Model DC-10-30 series airplanes, which were caused by fatigue-related stress. The actions specified by this AD are intended to prevent fatigue-related cracking, which could lead to failure of the fitting, separation of a portion of the engine forward mount truss from the pylon, and consequent separation of the engine from the airplane.
87-02-05 R1: 87-02-05 R1 BOEING: Amendment 39-5501 as amended by Amendment 39-5675. Applies to Boeing Models 727, 737-100, and 737-200 series airplanes, equipped with hydraulic system "B" Abex P/N 57186 pump motor, certificated in any category. Compliance required as indicated, unless previously accomplished.\n\n\tTo prevent a hydraulic system "B" Abex P/N 57186 pump motor internal wiring fault from burning a hole in the case and igniting the escaping hydraulic fluid, which could ignite fuel leakage, accomplish the following:\n\n\tA.\tWithin the next 300 hours time in service after the effective date of this AD, unless already accomplished within the last 700 hours time in service, and thereafter at intervals not to exceed 1,000 hours time in service, accomplish 1. or 2., below, as applicable:\n\n\t\t1.\tPerform a visual inspection of the cavity drain system components in the left wing-body fairing area for fuel leakage in all Model 727 series airplanes in accordance with Boeing Service Bulletin 727-29-A52, dated October 22, 1976, or later FAA-approved revision. Any evidence of leakage or conditions that could lead to leakage, must be corrected prior to further flight in accordance with approved maintenance procedures.\n\n\t\t2.\tPerform a visual inspection of all fuel system components and associated plumbing installed in the main wheel wells of all Model 737 series airplanes in accordance with Boeing Service Bulletin 737-29-A1033, dated October 22, 1976, or later FAA-approved revisions. Inspect for evidence of leakage, damage, and security of installations. Any evidence of leakage or conditions that could lead to leakage, must be corrected prior to further flight in accordance with approved maintenance procedures.\n\n\tB.\tWithin the next 1,000 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 1,000 hours time in service, accomplish a pressure leakage check of cavity drain system components in the left wing-body fairing area inall Model 727 series airplanes in accordance with Boeing Service Bulletin 727-29-A52, dated October 22, 1976, or later FAA-approved revisions.\n\n\tC.\tPrior to February 2, 1988, either:\n\n\t\t1.\tInstall the ground fault protection systems in the hydraulic system "B" Abex pump motor electric power circuits in accordance with Boeing Service Bulletin 727-29-47, Revision 2, dated October 8, 1976, or Boeing Service Bulletin 737-29-1029, Revision 2, dated October 8, 1976, as applicable, or later FAA-approved revisions; or\n\n\t\t2.\tInstall the hydraulic "B" system motor driven pumps, either new or upgraded, in accordance with Boeing Service Bulletin 727-29-55 dated April 30, 1980, or Boeing Service Bulletin 737-29-1036, dated April 30, 1980, as applicable, or later FAA-approved revisions.\n\n\tThis action constitutes terminating action for the repetitive inspection requirements of paragraphs A. and B., above.\t\n\n\tD.\tAn alternate means of compliance or adjustment of compliance time, which providean acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tE.\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 requirements of 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 the Boeing Commercial Airplane Company, 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 the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n\n\tAmendment 39-5501 became effective February 2, 1987, and superseded AD 76-22-08.\n\n\tThis amendment, 39-5675, becomes effective August 21, 1987.
68-10-01: 68-10-01 AVION MARCEL DASSAULT: Amendment 39-594. Applies to Fan Jet Falcon Airplanes. Compliance required as indicated unless already accomplished. To detect fuel leakage resulting from a rupture of the internal cores of the Janitrol Fuel Heater, P/N B 19D84, located in the engine pylons accomplish the following: (a) Before the next flight and thereafter before each flight where the outside ambient temperature at ground level is forty degrees Fahrenheit or less, remove the access plate on the underside of each engine pylon, remove the plugs labeled "condensate drain", and check to insure that the temperature of the fuel heater is above forty degrees Fahrenheit. If the temperature of the fuel heater is forty degrees or less, raise the temperature above 40 degrees for sufficient time to melt any ice which may be in the internal cores of the Janitrol Fuel Heater. If any water discharges from the condensate drain, the fuel heater drain should be wiped dry with a cleancloth. With the fuel shut-off valves open and throttles in off position, operate the aircraft fuel booster pumps for fifteen minutes and inspect the drain outlets for indications of fuel leakage. If fuel leakage is evidenced, the fuel heater must be replaced before further flight with a fuel heater of the same part number. The replacement fuel heater must have been inspected and marked with a capital letter "I" and the date of inspection on the left side of the fuel heater nameplate above the words "Janitrol Aero Division" as directed in Avions Marcel Dassault Service Bulletin 358. (b) Within the next 100 hours' time in service unless already accomplished, remove the Janitrol Fuel Heater P/N B 19D84 and inspect in accordance with Avions Marcel Dassault Service Bulletin 358, or later SGAC-approved issue, or an FAA-approved equivalent. Defective fuel heater must be replaced before further flight with a fuel heater of the same part number, inspected and marked in accordance withService Bulletin 358. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued as to a particular engine pylon after paragraph (b) has been complied with, or after installation of a fuel heater, inspected and marked in accordance with Service Bulletin 358. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated March 22, 1968.
66-30-05: 66-30-05 FAIRCHILD-HILLER: Amdt. 39-327 Part 39 Federal Register December 20, 1966. Applies to Model FH-1100 Helicopters. Compliance required before further flight. As a result of three failures of the Bendix main engine drive shaft, each of which occurred with less than 15 hours total time on the shaft, remove the Bendix main engine drive shaft P/N 19E49-4 and install Bendix shaft P/N 19E49X3 or 19E49-3 or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, Los Angeles, California. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated December 14, 1966.
98-19-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires modification of certain passenger doors. This amendment is prompted by reports that certain passenger doors could not be opened due to the escape slide shelf assembly and escape slide falling onto the girt bar lifting mechanism of the door. The actions specified by this AD are intended to prevent the escape slide shelf assembly and escape slide from falling on the girt bar of a passenger door due to failed rivets of the escape slide shelf assembly, and consequent inability to open the passenger door and to use the escape slide at that door during an emergency evacuation of the airplane.
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.)