Results
97-03-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300 series airplanes, that requires an inspection to detect fatigue cracking, base trim, and upper flange over-trim of the pulley brackets of the aileron control cables. This amendment also requires, if necessary, replacement of the pulley brackets with new pulley brackets, and replacement of the two button-head rivets with flush-head rivets. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent fatigue cracking or fracturing of the pulley brackets, which could result in slack in the cables and consequent reduced ability of the flightcrew to control the aileron.
62-03-01: 62-03-01 HILLER: Amdt. 395 Part 507 Federal Register January 30, 1962. Applies to All UH-12A and UH-12B Helicopters. Compliance required within the next 150 hours' time in service after the effective date of this AD. To preclude additional failures of the tail rotor drive slip joints which can result in loss of power to the tail rotor, replace CR-10 or CR-10T type rollers of both fore and aft slip joints UH-12A Assembly Nos. 24500-9 and -10 and UH-12B Assembly Nos. 24565 and 24544, with the improved Torrington CR-10U type rollers. (Hiller Service Bulletin No. 44, Revision A covers this same subject.) This supersedes AD 55-08-03. This directive effective January 30, 1962.
83-14-01: 83-14-01 SHORT BROTHERS LTD.: Amendment 39-4681. Applies to SC7 Skyvan Series 3 airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the flaps, accomplish the following: (a) For all affected aircraft, except SNs SH1845 and SH1883, within the next 50 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later, and thereafter at each subsequent 7,000 flights: (1) Inspect the inboard flap outer hinge arm and operating arm attachment ribs and replace the outer hinge arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (b) Within the next 250 flights after the effective date of this AD or upon accumulating 7,000 flights, whichever occurs later: (1) Modify the outboard flap attachment ribs at the inboard hinge arm and operating arm in accordance with Part 1 of the Accomplishment Instructions Section of Short Brothers Service Bulletin No. 57-62, Rev. 1, dated September 9, 1980, or an FAA approved equivalent. (c) For S/Ns SH1845 and SH1883 only: (1) Accomplish the initial inspection and outer hinge arm replacement described in paragraph (a) (1) of this AD within the next 250 flights after the effective date of this AD. (2) Accomplish the modification described in paragraph (b)(1) of this AD within the next 250 flights after the effective date of this AD. (d) For all affected aircraft, including S/Ns SH1845 and SH1883, replace the outboard flap inner hinge arm, P/N SC7-25-39, operating arm, P/N SC7-25-107/8, inboard flap inner hinge arm, P/N SC7-25-39, operating arm P/N SC7-25-109/110, and their associated attachment ribs at 20,000 flights or 18,000 flights, as defined by Short Brothers Life Extension Service Bulletin No. 51-51, Rev. 1, dated October 19, 1978, in accordance with Short Brothers ServiceBulletin No. 57-A61, Rev. 5, dated October 28, 1980, or an FAA approved equivalent. (e) For purposes of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of flights may be determined by multiplying each airplane's hours time-in-service by 2. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on August 19, 1983.
2005-01-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100 and -200B series airplanes. This AD requires installing bonding clips and bonding jumpers from the housing of each fuel pump to airplane structure outside the fuel tanks. This AD is prompted by the results of fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure adequate electrical bonding between the housing of each fuel pump and airplane structure outside the fuel tanks. Inadequate electrical bonding, in the event of a lightning strike or pump electrical fault, could cause electrical arcing and ignition of fuel vapor in the wing fuel tank, which could result in a fuel tank explosion.
2000-11-22: This amendment adopts a new airworthiness directive (AD), applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This AD requires revisions to the Airworthiness Limitations Section of the Allison Engine Company AE 3007A and AE 3007C Engine Manuals to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. Air carriers with an approved continuous airworthiness maintenance program will be allowed to either maintain the records showing the current status of the inspections using the record keeping system specified in the air carrier's maintenance manual or establish an acceptable alternate method of record keeping. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that, if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2023-12-04: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a report that an incorrect wiring arrangement was detected around the weather radar system. This AD requires modifying the weather radar redundant wiring, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-02: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
97-02-13: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JFTD12A series and T73 series turboshaft engines, that requires initial and repetitive fluorescent penetrant inspections (FPI) of compressor hubs, disks, spacers, and bolted on (rotating) airseals for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of extensive compressor rotor part cracking. The actions specified by this AD are intended to prevent disk rupture, an uncontained engine failure, and possible damage to the aircraft.
80-02-05: 80-02-05 ROLLS ROYCE LIMITED: Amendment 39-3655. Applies to Viper MK 601-22 model engine as installed in, but not limited to, Hawker Siddeley HS 125 series 600A and Beechcraft Hawker Siddeley BH 125 series 600A aircraft. Compliance is required as indicated unless already accomplished. To prevent possible failure of the flexible fuel hose, accomplish the following: (a) Within 250 hours engine time in service after the effective date of this AD, remove the flexible fuel hose assembly, Rolls Royce P/N DX 33-180-300 and install a new flexible fuel hose assembly, Rolls Royce P/N V 103813, in accordance with paragraph 2.A., "Accomplishment Instructions," of Rolls Royce Service Bulletin No. 73-A17, dated June 1978, or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Region, Brussels, Belgium. (b) Upon request of an operator, an FAA Maintenance Inspector may adjust the compliance time specified in paragraph (a) of this ADto be compatible with that operator's maintenance schedule. This amendment becomes effective January 24, 1980.
2005-01-11: The FAA adopts a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to check the airplane logbook to determine whether any main landing gear (MLG) actuator (part number (P/N) 960.30.01.103) with serial numbers (SNs) 830E through 881E is installed. If any MLG actuator with one of these SNs is installed, you are required to replace the MLG actuator with a P/N 960.30.01.103 actuator that has a SN other than 830E through 881E. The pilot is allowed to do the logbook check. If the pilot can positively determine that no MLG actuator with one of these SNs is installed, then no further action is required. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to prevent failure of the MLG actuator caused by an incorrect heat treating process, which could result in loss of hydraulic extension/retraction of the MLG. This failure could lead to loss of control during ground operations.
2023-12-01: The FAA is superseding Airworthiness Directive (AD) 2006-10- 13, which applied to all Airbus SAS Model A330-223, -321, -322, and - 323 airplanes. AD 2006-10-13 required repetitive inspections of the firewall of the lower aft pylon fairing (LAPF), and corrective actions if necessary. AD 2006-10-13 also provided an optional terminating action for the repetitive inspections. This AD was prompted by the design of an updated LAPF, the installation of which constitutes terminating action for the repetitive inspection required by AD 2006- 10-13. This AD continues to require the actions specified in AD 2006- 10-13, provides new optional terminating actions, and changes the applicability to exclude certain airplanes; 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.
84-13-06 R2: 84-13-06 R2 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A.: Priority letter AD 84-13-06 as amended by Amendment 39-5043 is further amended by Amendment 39- 5682. Applies to Model A109A and A109A II series helicopters certificated in any category and equipped with P/N 109-0132-02-11 or -15 tail rotor blades. Compliance is required as indicated unless already accomplished. To prevent possible hazards in flight associated with cracking of the tail rotor blade grip, accomplish the following: (a) Within the next 10 hours time in service, inspect the tail rotor blade grip in accordance with Part I of Agusta Service Bulletin (SB) 109-51, Revision A, or an FAA-approved equivalent, and at each additional 25 hours time in service, accomplish the inspection of Part III of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. (b) Prior to the first flight of each day, comply with Part II of the accomplishment instructions of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. This accomplishment may be conducted by the pilot. (c) Remove from service any tail rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office. Priority letter AD 84-13-06 was effective June 29, 1984. Amendment 39-5043 was effective May 13, 1985. This amendment, 39-5682, becomes effective August 30, 1987.
2004-26-10: The FAA is superseding an existing airworthiness directive (AD) for certain RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10, and Tay 651-54 turbofan engines with ice-impact panels installed in the low pressure (LP) compressor case. That AD currently requires visually inspecting all ice-impact panels and fillers in the LP compressor case for certain conditions, and if necessary, replacing any ice-impact panels and fillers that have those conditions. This AD requires initial and repetitive visual inspections of all ice-impact panels and fillers in the LP compressor case for certain conditions and replacing as necessary, any or all panels. This AD also introduces a new compliance date of no later than March 1, 2005, to have all but one engine on each airplane in compliance with the polysulfide bonding of panels. This AD results from RRD issuing two service bulletins since AD 2004-05-22 was published, that required repetitive visual inspections of panels, and defines a minimum configuration and repair standard. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines.
2023-13-01: The FAA is superseding Airworthiness Directive (AD) 2008-23- 01, which applies to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2008-23-01 required inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the operator's airplane flight manual (AFM) and FAA-approved maintenance program. AD 2008-23-01 also required modifying or replacing certain fuel tank boost pumps, which terminated the AFM limitations and the maintenance program revisions. Since the FAA issued AD 2008-23-01, it has been determined that airplanes fitted with a different fuel pump can be subject to cavitation erosion on the wiring conduit. This AD requires inspecting affected fuel pumps for discrepancies and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA). This AD also requires replacing certain other fuel pumps. This AD also limits the installation of affected fuel pumps under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-10-20: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires repetitive inspections to detect cracking of the fuselage skin in the areas of the left- and right-hand stringerless sidewall window belts, and repair, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin where the skin thickness steps from 0.40 to 0.23 inch. The actions specified by this AD are intended to detect and correct cracking of the fuselage skin, which could result in reduced structural integrity of the airplane.
2016-15-01R1: The FAA is removing Airworthiness Directive (AD) 2016-15-01, which applied to all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2016-15-01 required an inspection to determine trimmable horizontal stabilizer actuator (THSA) part numbers, serial numbers, and flight cycles on certain THSAs; and repetitive replacement of certain THSAs. The FAA issued AD 2016-15-01 to prevent loss of THSA no-back brake (NBB) efficiency. Since the FAA issued AD 2016-15-01, the FAA has issued AD 2022-25-12 to terminate AD 2016-15-01 for Model A310 series airplanes and AD 2023-11-02 to terminate AD 2016-15-01 for Model A300-600 series airplanes. The FAA has also determined that the inclusion of the Model A300 series airplanes in the applicability of AD 2016-15-01 was an inadvertent error. Accordingly, AD 2016-15-01 is removed.
83-02-06: 83-02-06 CASA: Amendment 39-4547. Applies to all CASA 212 series airplanes certificated in all categories. Compliance required within the next 300 hours time in service or 60 days after the effective date of this AD, whichever occurs first. To prevent fuel line blockage accomplish the following unless already accomplished: 1. Modify the ejector fuel filter system in accordance with CASA Service Bulletin 212-28-19 dated December 14, 1982. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 7, 1983.
2023-12-13: The FAA is superseding Airworthiness Directive (AD) 2022-05- 04, which applied to all The Boeing Company Model 737-100, -200, -200C, -300, -400, -500, -600, -700, -700C, -800, -900, and -900ER series airplanes, except for Model 737-200 and -200C series airplanes equipped with a certain flight control system. AD 2022-05-04 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for instrument landing system (ILS) approaches, speedbrake deployment, go-arounds, and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-05-04, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band base stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7- 3.98 GHz. This AD requires revising the limitations and operating procedures sections of the existing AFM to incorporate specific operating procedures for ILS approaches, speedbrake deployment, go- arounds, and missed approaches, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-25-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective action if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This new AD reduces the compliance threshold and repetitive intervals for the inspections required by the existing AD. This AD is prompted by a full-scale fatigue survey on the Model A320 fleet. We are issuing this AD to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. \n\nDATES: This AD becomes effective February 10, 2005. \n\n\tThe incorporation by reference of Airbus Service Bulletin A320-53- 1032, Revision 02, dated December 5, 2001, as listed in the AD, is approved by the Director of the Federal Register as of February 10, 2005. \n\n\tOn February 12, 1999 (64 FR 1114, January 8, 1999), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998.
2023-12-15: The FAA is superseding Airworthiness Directive (AD) 2022-09- 18, which applied to all The Boeing Company Model 707, 717, and 727 airplanes; Model DC-8, DC-9, and DC-10 airplanes; Model MD-10 and MD-11 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC- 9-87 (MD-87), and MD-88 airplanes; and Model MD 90-30 airplanes. AD 2022-09-18 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for, depending on the airplane model, instrument landing system (ILS) approaches, non-precision approaches, ground spoiler deployment, and go-around and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-09-18, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations and operating procedures sections of the AFM to incorporate specific operating procedures for, depending on the airplane model, ILS approaches, non-precision approaches, ground spoiler deployment, and go-around and missed approaches, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
86-18-07: 86-18-07 SAAB-FAIRCHILD: Amendment 39-5387. Applies to Model SF-340A airplanes listed in SAAB-Fairchild Service Bulletin SF-340-76-007, Revision 3, dated August 14, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent engine control cable freezing, accomplish the following: A. Modify the engine control cable system in accordance with SAAB-Fairchild Service Bulletin SF340-76-007, Revision 3, dated August 14, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to SAAB-Fairchild, Product Support, S-58188, Linkoping, Sweden. This document 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. This amendment becomes effective September 11, 1986.
2023-12-14: The FAA is superseding Airworthiness Directive (AD) 2022-06- 16, which applied to 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. AD 2022-06-16 required 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 interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) interference as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-06-16, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations section of the existing AFM to incorporate limitations requiring specific operating procedures, and retains the operating procedures for takeoff, ILS approaches, non-precision approaches, and go-around and missed approaches from AD 2022-06-16, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
81-14-09: 81-14-09 ROCKWELL INTERNATIONAL: Amendment 39-4157. Applies to Models NA-265-40, Serial Numbers 282-1 through 282-97, and NA-265-60, Serial Numbers 306-1 through 306-63, airplanes certificated in any category not modified in accordance with life extension modifications per North American Rockwell Drawing No. 306-053010. COMPLIANCE: Required as indicated unless already accomplished. To prevent inadvertent cabin depressurization, accomplish the following: A) On aircraft with 2,000 or more hours total time-in-service as of the effective date of this AD, within the next 600 hours additional time-in-service or within the next 12 months, whichever occurs first: 1. Conduct a dye penetrant inspection of the door stop (beam) in accordance with the Inspection Instructions of Sabreliner Service Bulletin No. 55 dated March 31, 1980, as revised June 16, 1980. 2. If no cracks are detected, repeat the inspection at intervals not to exceed 600 hours time-in-service or 1year, whichever occurs first. 3. If cracks are detected, replace the cracked part with a new part and after an additional 2,000 hours aircraft time-in-service, resume inspections at 600 hour time-in-service intervals, or modify the aircraft in accordance with Sabreliner Service Bulletin No. 3, dated December 19, 1975, as revised August 4, 1978. Installation of the applicable kit in accordance with Sabreliner Service Bulletin No. 3 eliminates the inspection requirement of this AD. B) On aircraft with less than 2,000 hours total time-in-service as of the effective date of this AD, prior to accumulating 2,600 hours time-in-service or within the next 12 months from the time the aircraft has accumulated 2,000 hours time-in-service, whichever occurs first, accomplish the inspection and corrective action specified in Paragraph A) as applicable. C) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. D) Any equivalent methodof compliance with this AD must be approved by the Chief, Aircraft Certification Program, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 942-4285. E) Record compliance with this AD by an appropriate entry in the airplane maintenance records. This should include those airplanes where the provisions of this AD have already been accomplished. This Amendment becomes effective July 13, 1981.
2004-26-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes equipped with certain forward and aft passenger door emergency escape slides. This AD requires modifying the forward and aft door slides. This AD is prompted by manufacturer testing that has shown contact between the inflation hose and fabric roll, within a short period of time after inflation of the emergency escape slides, can rupture the inflation hose at its end fittings. We are issuing this AD to prevent interference between the inflation hose and slide fabric and rupture of the inflation hose, which could result in incomplete inflation of the emergency escape slides and consequent unavailability of those slides during an emergency evacuation.
2023-11-12: The FAA is adopting a new airworthiness directive (AD) for certain DAHER AEROSPACE (type certificate previously held by SOCATA) Model TBM 700 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as interference between the emergency exit trim panel and the upholstery panel, which could result in additional effort required to open the emergency exit door. This AD requires modification of the gripping strap, which maintains the upholstery panel on the emergency exit trim panel. The FAA is issuing this AD to address the unsafe condition on these products.