Results
2022-07-05: The FAA is superseding Airworthiness Directive (AD) 2022-05- 09, which applied to certain MARS A.S. emergency parachutes. AD 2022- 05-09 required removing emergency parachutes with certain manufacture dates or serial numbers from service. Since the FAA issued AD 2022-05- 09, the European Union Aviation Safety Agency (EASA) superseded its mandatory continuing airworthiness information (MCAI) to correct an unsafe condition on this aviation product. The MCAI identifies the unsafe condition as the length of the ripcord between the pins being too long, which could cause a malfunction of the emergency parachute. This AD retains the actions required by AD 2022-05-09 and expands the applicability.
68-06-02: 68-06-02 GENERAL DYNAMICS (CONVAIR): Amendment 39-564. Applies to General Dynamics (Convair) Type 30A incorporating Supplemental Type Certificate SA414EA- D. Compliance required as indicated: (a) Upon arrival at the next stop, install a placard on each of the three right hand row seats at fuselage station 1344 (row 28 on American Airlines' Drawing No. FCA-2047 Rev. D) stating, "Do Not Occupy". (b) The placard required by part (a) may be removed by incorporating an approved modification strengthening the seat support structure approved by the Chief, Engineering & Manufacturing Branch, Eastern Region. This amendment is effective March 22, 1968.
2004-15-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections for fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors of the bottom skin panel of the wings, and related corrective action. This amendment also provides for an optional terminating action, which ends the repetitive inspections. This action is necessary to prevent fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
47-47-06: 47-47-06 MARTIN: (Was Service Note 2 of AD-795-1.) Applies to All Model 202 Airplanes With HSP 23260 Propellers With YB2H17F3-48R Blades and Westinghouse D-30 Generators. Compliance required at first major (long period) inspection and thereafter as specified below. Carefully inspect the engine accessory section rear cover for signs of fatigue cracks particularly near the generator mounting pad at the first long period inspection and at every short period inspection thereafter until engine overhaul. After the engine overhaul, the same inspection sequence shall be observed.
2012-25-11: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. That AD currently requires initial and repetitive inspections of the fuselage skin and bear strap at the forward, upper corner of the L1 entry door cutout for cracking, and repair if necessary. That action also provides an optional terminating action for the repetitive inspections. That AD also requires additional inspections for airplanes having repairs or preventative modifications installed and inspections for certain other airplanes. This AD requires the previous actions with additional airplane group configurations added to paragraph (n) of this AD. This AD was prompted by a determination that certain airplane group configurations in paragraph (n) of the existing AD were inadvertently removed in the final rule. We are issuing this AD to detect and correct cracking of the fuselage skin and bear strap at the forward upper corner of theL1 entry door cutout, which could result in reduced structural integrity of the L1 entry door, and consequent rapid decompression of the airplane.
2022-06-16: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that during takeoff, approach, landings, and go-arounds, as a result of this interference, certain airplane systems may not properly function, resulting in increased flightcrew workload while on approach with the flight director, autothrottle, or autopilot engaged, which could result in reduced ability of the flightcrew to maintain safe flight and landing of the airplane. This AD requires revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for takeoff, instrument landing system (ILS) approaches, non-precision approaches, and go-around and missed approaches, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
68-10-06: 68-10-06 PILATUS: Amendment 39-599. Applies to Model PC-6 Series airplanes. Compliance required within the next 200 hours' time in service after the effective date of this AD, unless already accomplished. To prevent horizontal stabilizer stall, install fixed wing spoilers on the trailing edges of the wings in accordance with Pilatus Service Bulletin No. 76, dated November 1967, or later Swiss Federal Air Office approved revision or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment becomes effective June 10, 1968.
71-25-07: 71-25-07 PRATT & WHITNEY AIRCRAFT: Amdt. 39-1354. Applies to all JT8D-1, JT8D-1A, JT8D-7, JT8D-7A, JT8D-9, JT8D-11 turbofan engines which incorporate the following part numbers: 480735, 493332, 501725 and 523476 fuel nozzle support assemblies. To prevent failure of the fuel nozzle support assemblies from fatigue cracking in the base fillet accomplish the following: Within the next 6000 hours' time in service after the effective date of this AD unless already accomplished alter all fuel nozzle support assembly part numbers 480735, 493332, 501725 or 523476 in accordance with P&WA Service Bulletin No. 3536 or equivalent method approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region, or replace with superseding part number fuel nozzle support assembly. Upon submission of substantiating data through an FAA Maintenance Inspector by an owner or operator, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the compliance time. This amendment is effective December 14, 1971.
2012-22-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD was prompted by reports of cracking of air intake cowls on Rolls-Royce Trent engines, worn and detached attachment [[Page 67264]] links, and fractured thermal anti-ice (TAI) piccolo tubes. This AD requires inspecting piccolo tubes, piccolo tube mount links, the aft side of the forward bulkhead, and outer boundary angles (OBA) for cracks, fractures, and broken links, and corrective actions if necessary. We are issuing this AD to prevent degraded structural integrity of the engine nose cowl in case of forward bulkhead damage in conjunction with a broken piccolo tube, and damage to the engine due to operation in icing conditions with reduced TAI performance.
99-10-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that currently requires repetitive inspections to detect cracking, plating degradation, and corrosion of the main landing gear (MLG) actuator beam arms and actuator beam attach bolts; and rework or replacement, if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This amendment removes the requirement to inspect the actuator beam attach bolts, expands the applicability of the existing AD to include additional airplanes, and removes the optional terminating action. This amendment is prompted by reports of cracked MLG actuator beam arms. The actions specified in this AD are intended to detect and correct corrosion and cracking of the MLG actuator beam arm, which could result in damage to the control cables for the aileron and spoiler and consequent reduced controllability of the airplane.
2012-23-02: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E and Model A109S helicopters with certain lower semichannel assemblies installed. This AD requires a one-time inspection of the lower semichannel assemblies to determine if metallic spacers are installed. If the metallic spacers are installed, this AD requires an inspection for the correct installation of the metallic spacers on the semichannels and for the correct seating of the gaskets. If the metallic spacers are not installed with rivets, the lower semichannel assemblies must be modified, and the main drive shaft must be inspected for damage. This AD was prompted by reports of damage to the main drive shaft caused by improperly secured metallic spacers on some A109 model helicopters. The actions of this AD are intended to detect missing spacer rivets, which could allow the metallic spacers to rotate and lead to damage and failure of the main drive shaft, and subsequent loss of helicopter control.
47-10-26: 47-10-26 LOCKHEED: (Was Mandatory Note 29 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2075. Compliance required prior to June 1, 1947. Reroute flap and fan motor drain lines to return direct to main hydraulic system instead of through aspirator, and install check valves at points where drain lines connect to the main system. (LAC Service Bulletin 49/SB-169 covers this same subject.)
99-10-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737 series airplanes. This action requires repetitive inspections and functional tests of a trailing edge flap limit switch to verify proper operation, and replacement of the existing limit switch with a new limit switch, if necessary. This AD also requires modification of the stabilizer control system, which constitutes terminating action for the repetitive inspections and tests. This amendment is prompted by reports of uncommanded stabilizer trim motion due to failure of the trailing edge flap limit switch. The actions specified in this AD are intended to prevent such failure, which could result in uncommanded (nose down) stabilizer trim motion and consequent reduced controllability of the airplane.
2012-24-05: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-Trent 900 series turbofan engines. This AD requires inspection of the low pressure turbine (LPT) bearing housing end cover assembly in certain engines and, if necessary, its replacement. This AD was prompted by a Trent 900 engine experiencing a high intermediate pressure vibration fault, along with other fluctuating engine parameters, while in flight. We are issuing this AD to prevent fracture of the oil transfer tube, which could result in uncontained failure of the engine and damage to the airplane.
2012-22-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of an in-service incident where the propeller de- icing system became unavailable due to burnt/chafed wires within the alternating current contactor box (ACCB). This AD requires inspection for chafing, damage, and loose wiring within an ACCB and repair if necessary; and requires rework and re-identification of the wiring installation within each ACCB. We are issuing this AD to detect and correct damaged, chafed, or loose wiring within an ACCB, which could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pilot probe heater, engine intake heater, or propeller de-icing system, and subsequently adversely affect the airplane's flight characteristics in icing conditions.
2022-06-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 D-3 helicopters. This AD was prompted by reports of a main rotor (M/R) blade lead-lag damper in a tilted position. This AD requires inspecting the Flex Control Unit (FCU), and corrective actions if necessary, as well as rework and re-identification of the bearing pin, 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.
48-09-03: 48-09-03 LUSCOMBE: Applies to Model 8 Series Airplanes Below Serial Number 5682 Equipped With Kollsman Airspeed Instruments. Compliance required by April 1, 1948. To obtain more accurate airspeed readings remove small baffle LAC P/N 181112, which is attached to the fuselage at the airspeed static tube opening. Installation of this baffle provides inaccurate airspeed readings ranging from approximately +6 m.p.h. at stall to approximately +15 m.p.h. at minimum trim speed.
96-17-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Beech (Raytheon) Model Hawker 1000 and BAe 125-1000A series airplanes, that currently requires inspections to detect various discrepancies of the fuel hose assemblies on the auxiliary power unit (APU), and correction of any discrepancy found. That AD was prompted by several reports of heat damage to the fuel hose assembly on the APU. This amendment adds a requirement to replace the existing conduit of the fuel feed hose with new improved conduit, which will terminate the repetitive inspections. The actions specified by this AD are intended to prevent failure of a fuel hose due to heat damage caused by incorrect routing or bleed air leakage; such failure could result in a malfunction of the APU, a fuel fire in the fuselage rear equipment bay, and reduced structural integrity of the surrounding structure. The incorporation by reference of Raytheon Service Bulletin SB 49-44, dated January 20, 1995, listed in the regulations was approved previously by the Director of the Federal Register as of May 23, 1995 (60 FR 22501, May 8, 1995)
2004-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing airplane models, that currently requires either inspections for discrepancies of the fueling float switch wiring in the center fuel tank and follow-on actions, or deactivation of the float switch. This amendment requires replacing the float switches in the center and wing fuel tanks with new, improved parts; installing a conduit liner system in the center fuel tank; and replacing conduit assemblies in the wing fuel tanks with new parts, which terminates the existing requirements. For certain airplanes, this amendment also requires replacing certain existing sections of the electrical conduit in the center fuel tank with new conduit. This amendment also adds one additional airplane model to the applicability and removes another. The actions specified by this AD are intended to prevent contamination of the fueling float switch by moisture or fuel, and chafing of the float switch wiring against the fuel tank conduit, which could present an ignition source inside the fuel tank that could cause a fire or explosion. This action is intended to address the identified unsafe condition.
72-11-04: 72-11-04 ENSTROM: Amdt. 39-1452. Applies to Model F-28A (Serial Numbers 1 through 83) helicopters. Compliance: Required as indicated, unless already accomplished. To prevent failure of tail rotor drive taper pins with subsequent loss of directional control, accomplish the following: A) Unless Paragraph B has been accomplished, within 10 hours' time in service after the effective date of this AD visually inspect the 2 forward and 3 aft AN386 taper pins installed in the tail rotor drive shaft assembly for looseness. Prior to further flight replace all loose taper pins with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. NOTE: Loose pins can be detected by: 1. Wiggling the pin with the fingers. 2. Grasping the tail rotor drive shaft with the hand and rotating the shaft back and forth while observing the movement of the pin in the mating hole. 3. Examining for loss of paint on the pin at the edge of the mating hole. 4. Examining for formation of a burr at the edge of the hole. B) Within 25 hours' time in service after the effective date of this AD, replace all AN386 taper pins installed in the tail rotor drive shaft assembly with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. This amendment becomes effective June 1, 1972.
2022-06-03: The FAA is superseding Airworthiness Directive (AD) 2022-02-02 which applied to certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 204B, 205A, 205A-1, 205B, 210, and 212 helicopters with a certain main rotor hub strap pin (pin) installed. AD 2022-02-02 required removing certain outboard pins from service and prohibited installing them on any helicopter. This AD expands the applicability to all affected pins, regardless if they are outboard or inboard. This AD also requires inspecting the removed pin for any deformation and if it is deformed, removing the mating strap fitting (fitting) from service. This AD was prompted by the discovery that AD 2022-02-02 inadvertently limited its applicability to only outboard pins when, in fact, all pins are subject to the unsafe condition and the determination that a deformed pin may have damaged the fitting. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection to detect cracking of the swivel bogie beam lugs, and repair, if necessary. For airplanes on which no cracking is found, this amendment also requires an inspection to detect corrosion of the swivel pin lug surfaces and bores, and modification of the forward bogie beams. This amendment is prompted by reports indicating that swivel pin lugs of the main landing gear (MLG) have failed due to cracks resulting from stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in failure of the swivel-type bogie beam of the MLG; this condition could result in collapse of the MLG during landing.
73-22-01: 73-22-01 CESSNA: Amendment 39-1735 as amended by Amendment 39-3215. Applies to Model 340 (S/Ns 340-0001 thru 340-0234); Model 401 (S/Ns 401-0001 thru 401-0322); Model 401A (S/Ns 401A0001 thru 401A0132); Model 401B (S/Ns 401B0001 thru 401B0300); Model 402 (S/Ns 402-0001 thru 402-0322); Model 402A (S/Ns 402A0001 thru 402A0129); Model 402B (S/Ns 402B0001 thru 402B0392); Model 411 (S/Ns 411-0001 thru 411-0250); Model 411A (S/Ns 411-0251 thru 411A0300); Model 414 (S/Ns 414-0001 thru 414-0407); Model 421 (S/Ns 421-0001 thru 421-0200); Model 421A (S/Ns 421A0001 thru 421A0158); and Model 421B (S/Ns 421B0001 thru 421B0147 and S/Ns 421B0201 thru 421B0422) airplanes. Model 421 (S/N 421-0151) airplane is excepted from the requirement for the installation of Cessna Service Kit SK421-56 so long as it complies with STC SA599CE. Compliance: Required as indicated, unless already accomplished. To prevent the collection of fuel in the wing leading edge area and to provide additional instructions on preflight inspections and ground or inflight fire procedures, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: Modify the wing leading edge by installing Cessna Service Kit SK 421-56 and install applicable checklist and Flight Manual revisions as specified in Cessna Service Letter ME73-5 (Supplement 1) dated September 7, 1973, or later FAA-approved revisions, or any other modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-1735 became effective October 18, 1973. This amendment 39-3215 becomes effective on May 29, 1978.
2004-15-06: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires various inspections of the fuselage nose structure between stations 4 and 11, and corrective actions if necessary. This action is necessary to detect and correct fatigue cracking in the primary structure of the nose of the airplane at the forward avionics bay (fuselage stations 4 to 11), which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
46-42-01: 46-42-01 GLOBE: (Was Mandatory Note 4 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 228 Inclusive. Compliance required prior to December 1, 1946. Replace the aluminum alloy cabin heater valve assembly with one constructed completely of firewall material equivalent to Globe Valve Assembly, P/N 11-440-3623. This will provide a complete firewall of firewall material. (Globe Customer Service Maintenance Bulletin No. 4 covers this same subject.)