Results
96-17-12: This amendment supersedes Airworthiness Directive (AD) 87-07-01, which currently requires the following on Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes: repetitively inspecting the nose landing gear (NLG) top cap assembly securing bolts for looseness or cracks, retorquing any loose security bolt, and replacing any cracked security bolt. AD 87-07-01 also provides the option of incorporating a NLG modification as terminating action for the repetitive inspections. A report of cracked and loose bolts found on an airplane with the above-referenced NLG modification prompted this action. This action: retains the repetitive inspections required by AD 87-07-01; increases the AD applicability to include Jetstream Model 3201 airplanes and airplanes that have the NLG top cap assembly modified in accordance with AD 87-07-01; requires replacing two of the NLG top cap assembly securing bolts; and incorporates a new NLG top cap assembly that would eliminate the repetitive inspection requirement of the AD. The actions specified in this AD are intended to prevent failure of the NLG caused by cracked or loose securing bolts, which, if not detected and corrected, could lead to NLG collapse and damage to the airplane.
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.