Results
67-22-07: 67-22-07 MOONEY: Amdt. No. 39-444, Part 39, Federal Register July 21, 1967. Applies to Model M20F, Serial Numbers 660003, 660004, and 670001 through 670303. Compliance required within the next 15 hours' time in service after the effective date of this AD unless already accomplished. To prevent water retention in the rudder assembly, accomplish the following: Drill .375 (3/8) inch diameter holes in the rudder as shown by Figure 1 of Mooney Service Bulletin M20-149 or FAA-approved equivalent. This may be accomplished without removal of the rudder or any part replacements. This amendment effective August 21, 1967.
2009-20-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727 airplanes. This AD requires performing an operational test of the engine fuel suction feed of the fuel system, and other related testing and corrective actions if necessary. This AD results from a report of in-service occurrences of loss of fuel system suction feed capability, followed by total loss of pressure of the fuel feed system. We are issuing this AD to detect and correct failure of the engine fuel suction feed capability of the fuel system, which could result in multi-engine flameout, inability to restart the engines, and consequent forced landing of the airplane.
2008-07-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A case of loose bond (ungluing) of one mounting wooden block of the control stick base cover, found during the cover reinstallation, was reported to the Type Certificate Holder (TCH) and led to the issuance of the "recommended'' Service Bulletin (SB) No. 031004 in February 2004. Since that date, other similar occurrences have been reported. This SB in its revision 1, has therefore been reclassified "mandatory'' by the TCH. We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-11-10: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311 and -315 airplanes. This AD requires installation of check valves in Numbers 1 and 2 hydraulic systems, removal of the filters from the brake shuttle valves, and removal of the internal garter spring from the brake shuttle valves. This AD results from two instances of brake failure due to the loss of hydraulic fluid from both Numbers 1 and 2 hydraulic systems and one incident of brake failure due to filter blockage in the shuttle valve. We are issuing this AD to prevent the loss of hydraulic power from both hydraulic systems, which could lead to reduced controllability of the airplane, and to prevent brake failure, which could result in the loss of directional control on the ground and consequent departure from the runway during landing.
57-05-01: 57-05-01 CURTISS-WRIGHT: Applies to all C-46 Series aircraft. Compliance required by August 1, 1957. During emergency extension of the landing gear, hydraulic dump valves are actuated in the landing gear hydraulic system to vent fluid directly overboard in order to prevent trapped fluid from preventing the lowering of the landing gear. On early model aircraft this fluid was vented overboard on the inboard side of the nacelles directly aft of the exhaust stack. This has resulted in fires in areas where no fire detection or protection is provided. In order to prevent this occurrence, item (1), (2), or (3) should be accomplished. (1) The vent line should be rerouted to vent from nacelle tail cone in accordance with Curtiss-Wright Service Bulletin C-46 1226 or Curtiss-Wright Drawing No. 20-575-3206. (2) The vent line should be rerouted to return to the main system as outlined in change A of T.O. 01-25LA-209. (3) The vent line should be rerouted to anapproved equivalent of item (1) or (2). Either item (1) or (2) may have been accomplished on later model aircraft at the factory or by the military; however, the aircraft may have been further modified and should be inspected for compliance.
67-17-01: 67-17-01 AERO PRODUCTS: Amdt. 39-417 Part 39 Federal Register May 11, 1967. Applies to Models A6441FN-606 and A6441FN-606A Propellers. Compliance required as indicated. (a) On or before July 1, 1967, unless already accomplished, on each propeller in which is installed a fixed spline P/N 6522974, Serial No. 1367 and up, or P/N's 6523110 and 6509978, accomplish the following: (1) Remove from service all fixed splines P/N's 6523110 and 6509978. (2) Remove from service any P/N 6522974, Serial No. 1367 and up, fixed spline which does not meet the specification requirements for core hardness. (Reference: Allison Commercial Service Letter 189, Page 7, titled "Fixed Spline," Paragraph B.4.c.) (b) Within the next 10 hours' time in service, unless already accomplished, each propeller in which is installed a fixed spline P/N 6523110, or 6509978, or P/N 6522974, with Serial No. 1367 and up, must be inspected and marked as required by Allison telegram THO- 641W-LOD, dated April 7, 1967, as modified by Allison telegram THO-662W-LOD, dated April 10, 1967. Thereafter, repetitive daily inspections are required as specified in those telegrams. (c) If, during the daily inspection, it is determined that a propeller blade is beyond tolerance as set forth in those telegrams, the propeller shall be removed from service and be - (1) Retained by the operator, with immediate notification to the Chief, Engineering and Manufacturing Branch, FAA Central Region, pending further instructions by him; or (2) Returned to an approved overhaul base and the Chief, Engineering and Manufacturing Branch, FAA Central Region, notified immediately. (d) The daily inspection required by this AD may be discontinued when the fixed splines identified in (a)(1) have been removed from service and replaced by airworthy fixed splines, or when the fixed splines identified in (a)(2) have been inspected for core hardness and determined to meet specifications or have been replaced by airworthy fixed splines. (e) Within the next 10 hours' time in service from the effective date of this amendment, unless already accomplished, each propeller which has not been modified to comply with the restrictor installation of paragraph (a) of AD 67-20-01 and in which is installed a fixed spline Part Number 6508538, accomplish the markings and inspections outlined in paragraphs (b) and (c). This amendment effective September 20, 1967, for all persons except those to whom it was made effective by telegram dated September 8, 1967. This supersedes AD 67-12-01. This directive effective May 11, 1967. Revised September 20, 1967.
2020-24-06: The FAA is superseding Airworthiness Directive (AD) AD 2019- 08-13 for Textron Aviation, Inc., (type certificate previously held by Cessna Aircraft Company) Models 525, 525A, and 525B airplanes with Tamarack Aerospace Group (Tamarack) active load alleviation system (ATLAS) winglets installed in accordance with Supplemental Type Certificate (STC) SA03842NY. AD 2019-08-13 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 describes the unsafe condition as malfunction of the ATLAS. This AD results from the identification of corrective actions that, if implemented, allow operators to reactivate the ATLAS and restore operations to normal procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2003-23-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that currently requires modification of the number 3 left and right emergency exit doors. This amendment requires a new, improved modification of the number 3 left and right emergency exit doors, which terminates the requirements in the existing AD. The actions specified by this AD are intended to prevent the number 3 emergency exit doors from jamming, which could impede the safe evacuation of passengers and crew during an emergency. This action is intended to address the identified unsafe condition.
2009-20-06: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: DGAC [Direction Generale de l'Aviation Civile] France AD 86-102-74(B) [which corresponds to FAA AD 88-06-03, amendment 39-5871] was issued to prevent development of damage, which was discovered during [a] fatigue test in the attachment angles of the rear pressure bulkhead (fuselage frame 80/82). Following the life extension activities linked to the A310 program, the interval of inspection for A310-200 aircraft series was reduced from 12000 flight cycles (FC) to 9000 FC * * *. Some stress analysis conducted in the frame of the life extension activities of the A300-600 program leads the manufacturer to reduce as well the interval of inspection applicable to A300B4- 620 and A300C4-620 aircraft models. * * * * * The unsafe condition is cracking in the attachment angles of the rear pressure bulkhead, which could result in failure of the rear pressure bulkhead. We are issuing this AD to require actions to correct the unsafe condition on these products.
67-03-05: 67-03-05 LOCKHEED: Amdt. 39-326 Part 39 Federal Register December 22, 1966. Applies to Models 649, 749, and 1049 Airplanes Powered by Wright 749C18BD-1 and 975C18CB-1 Engines Equipped With Hamilton Standard 43E60/6869-0, 43E60/6901-0, and 43E60/6903-0 Propellers. Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To minimize propeller vibratory stresses, amend the FAA-approved Airplane Flight Manual to include the following operating limitations: Continuous ground running between 2,300 and 2,650 r.p.m. with the propeller governing is prohibited. Continuous static ground running in a crosswind above 2,650 r.p.m. is prohibited. This directive effective January 23, 1967.
2020-24-05: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA- 28-160, PA-28-180, PA-28-235, PA-32-260, and PA-32-300 airplanes. This AD was prompted by reports of corrosion found in an area of the main wing spar not easily accessible for inspection. This AD requires inspecting the left and right main wing spars for corrosion, and, if corrosion is found, taking all necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-03-15 R1: This amendment revises an existing airworthiness directive (AD), applicable to various Boeing and McDonnell Douglas transport category airplanes, that currently requires revising the Airplane Flight Manual (AFM) to advise the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. The actions specified by that AD are intended to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This amendment removes certain requirements for certain airplanes and revises the direction to the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning occurs, rather than "when the cabin altitude warning horn sounds." This action is intended to address the identified unsafe condition.
94-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8, DC-9, and DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) airplanes; that requires inspection of the center and side windshields, and replacement of discrepant windshields. This amendment is prompted by reports that the core ply of certain windshields was incorrectly tempered during the manufacturing process. The actions specified by this AD are intended to prevent failure of the windshield.
2020-23-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. This AD was prompted by a report of a manufacturing and control issue regarding the ceramic balls in the bearing installed in the swashplate assembly of the main rotor mast assembly. This AD requires repetitive inspections of the bearing in the swashplate assembly of the main rotor mast assembly for discrepancies (ceramic balls that have a hard point or sensitive axial play or both) and, depending on the findings, replacement of an affected main rotor mast assembly with a serviceable main rotor mast assembly, 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.
78-09-04: 78-09-04 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-3200. Applies to Model DH-104 "Dove" airplanes, all series, certificated in all categories, except those airplanes incorporating Hawker Siddeley Model DH-104 Modification 779. Compliance is required as indicated. To detect cracking and prevent possible failure of the lugs of the lower center section main spar wing to fuselage attachment, accomplish the following: (a) Within one month after the effective date of this AD, unless already accomplished within the last month, and thereafter at intervals not to exceed two months from the last inspection, remove the lower wing to fuselage fairings and inspect the center section main spar bottom boom lugs for cracks using an ultrasonic inspection method in accordance with appendix 1 of Hawker Siddeley Aviation, Limited Technical News Sheet (TNS) 238, issue 2, dated January 24, 1977, or an FAA-approved equivalent. (b) The repetitive inspections required by paragraph(a) of this AD may be terminated upon incorporation of a steel lower boom in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent. (c) Within two months after accomplishing six repetitive inspections under paragraph (a) of this AD, a steel lower boom must be incorporated in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent. (d) If any crack is found during an inspection required by paragraph (a) of this AD, before further flight, replace the boom with a steel boom in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent. This amendment becomes effective May 24, 1978.
2003-22-13: The FAA adopts a new airworthiness directive (AD) for all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. This AD requires you to visually inspect the ailerons for damage and replace if necessary; adjust the engine power levers aural warning microswitches; set flap extension and flap down operation limitations; and fabricate and install cockpit flap extension and flap down operation restriction placards. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to prevent damage to the aileron due to airplane operation and pre-existing and undetected damage, which could result in failure of the aileron. Such failure could lead to reduced or loss of control of the airplane.
2009-18-14: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: * * * A number of * * * rudder spring tab lever assemblies [of the rudder] were found cracked. This condition, if not corrected, could lead to failure of the rudder flight control system and consequent loss of control of the aircraft. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective October 14, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 14, 2009. On June 9, 2004 (69 FR 24953, May 5, 2004), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.
2020-23-07: The FAA is adopting a new airworthiness directive for all Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD requires removing certain emergency life raft (raft) reservoirs (reservoirs) from service, inspecting the reservoirs and raft actuator cables (actuator cables), and depending on the inspection results, replacing the reservoir or adjusting the actuator cable. This AD was prompted by the inadvertent activation and deployment of a raft while the helicopter was in flight. The actions of this AD are intended to address an unsafe condition on these products.
95-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Rolls- Royce, plc RB211-524 series turbofan engines, that requires a one-time modification of the nozzle guide vane (NGV) assembly to incorporate vane core reinforcement inserts which would prevent release of the stage 2 NGV seal ring, rotor contact, and severance of the rotor drive arm. This amendment is prompted by a report of an uncontained stage 1 low pressure turbine failure. The actions specified by this AD are intended to prevent release of the stage 2 NGV seal ring, which could result in an uncontained engine failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 8, 1995.
2020-23-05: The FAA is superseding Airworthiness Directive (AD) 2018-08-01 for Airbus Helicopters Model EC225LP helicopters. AD 2018-08-01 required inspecting the control rod attachment yokes (yoke) of certain main rotor rotating swashplates (swashplate). This new AD retains the inspection requirements of AD 2018-08-01, expands the applicability, establishes a life limit, and adds a one-time inspection of stripped yokes. This AD was prompted by the identification of additional swashplate serial numbers affected by the unsafe condition and the establishment of a life limit for the swashplates. The FAA is issuing this AD to address the unsafe condition on these products.
2009-18-09: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: A recent design review has been carried out on the F28 Mark 0070/0100 fuel system in accordance with the guidelines related to FAA SFAR 88 [Special Federal Aviation Regulation No. 88] (Fuel Tank Safety Program) and JAA [Joint Aviation Authorities] INT/POL/25/12. The review revealed that under certain failure conditions, prolonged dry running of the fuel transfer pumps may result in an ignition source in the centre wing fuel tank. This condition, if not corrected, could lead to ignition of flammable fuel vapors, resulting in fuel tank explosion and consequent loss of the aircraft. * * * * * We are issuing this AD to require actions tocorrect the unsafe condition on these products.
2020-22-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-10-10 and DC-10-10F airplanes, Model DC-10- 15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, Model MD-10-10F and MD-10-30F airplanes, and Model MD-11 and MD-11F airplanes. This AD was prompted by reports of cracked floor beams and floor beam supports in the area of the overwing exit doors located at certain stations (STA). This AD requires an inspection of the overwing floor beams for any repair, repetitive inspections of the overwing floor beams and floor beam supports at certain STA on the left and right sides for any crack, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-23-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Cessna Model 560 airplanes. This action requires disengaging and tie-strapping the pitch trim and autopilot servo (servo 1) circuit breakers. This action also provides an optional inspection and follow-on actions that, if accomplished, terminates the requirement to disengage and tie-strap those circuit breakers. This action is necessary to prevent a single-point failure in the trim system from causing a runaway trim condition that the pilot may be unable to stop by using the autopilot-disconnect switch. This condition could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2003-22-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600- 2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This amendment requires revising the airplane flight manual to provide the flightcrew with procedures and limitations for operating the airplane with out-of-tolerance angle of attack (AOA) transducers. This amendment also requires, among other actions, measuring the vane angles and voltage of the AOA transducers; reworking the AOA transducer assemblies; repetitive measurements of the resistance of both AOA transducers; and follow-on and corrective actions, as applicable. This action is necessary to prevent flat spots on the potentiometers of the AOA transducers due to wear, which may cause a delay in the commands for stall warning, stick shaker, and stick pusher operation. This action is intended to address the identified unsafe condition.
68-20-07: 68-20-07 DOWTY ROTOL: Amendment 39-664. Applies to Dowty Rotol Propellers (c) R.193/4-30-4/50 installed on Fairchild F. 27A-F-G-J, FH.227 and Fokker F.27 Mk 400, (c) R.257/4-30-4/60 installed on Fairchild FH.227B, FH.227C, FH.227D and FH.227E, and (c) R.184/4-30-4/50 installed on Grumman G-159. Compliance required as indicated unless already accomplished. To prevent failure of the propeller hub driving center, P/N RA 57500, accomplish the following: (a) For all propellers except the (c) R.184/4-30-4/50 propeller, incorporate Dowty Rotol Modification (c) VP.2486, in accordance with Dowty Rotol Service Bulletin No. 61.573B dated June, 1968, or later ARB approved issue, or FAA approved equivalent at the next scheduled overhaul or within the next 4500 hours time in service after the effective date of this AD, whichever occurs first. (b) For (c) R.184/4-30-4/50 propellers accomplish the following: (1) For propeller hubs having 2500 or more hours time in service on the effective date of this AD and that have not been modified in accordance with paragraph (5), inspect the hub in accordance with paragraph (3) within the next 50 hours time in service and incorporate the modification specified in paragraph (5) at the next scheduled overhaul or prior to the accumulation of 400 hours time in service after the effective date of this AD, whichever occurs first. (2) For propeller hubs having less than 2500 hours time in service on the effective date of this AD and that have not been modified in accordance with paragraph (5), inspect the hub in accordance with paragraph (3) prior to the accumulation of 2550 hours time in service and incorporate the modification specified in paragraph (5) within the next 400 hours time in service or prior to the accumulation of 2500 hours time in service, whichever occurs later. (3) Inspect the rear face of the hub driving center flange with a magnifying glass and by the magnetic particle fluid method in accordance with Dowty Rotol Service Bulletin 61-633 dated June 1968, or later approved ARB issue, or an FAA approved equivalent. (4) If cracked hub driving centers are detected during any inspection, before further flight replace the propeller hub driving center with a serviceable part of the same part number having no cracks. (5) Incorporate Dowty Rotol Modification No. (c) VP.2486 in accordance with Dowty Rotol Service Bulletin No. 61-573A dated June 1968, or later ARB approved issue, or an FAA approved equivalent. The inspection specified in paragraph (3) is not required in hubs modified in accordance with this paragraph. This supersedes Amendment 39-587 (33 F.R. 5866), AD 68-08-05. This amendment becomes effective October 8, 1968.