Results
75-27-05: 75-27-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2477. Applies to Alouette helicopter Models SE-3130, SE-313B, SA-3180, SA-318C, SA-315B, SE-3160, SA-316B, SA-319B, and SA-316C incorporating 3130 series main rotor blade(s) with serial number 9554 and lower, and 3160 series main rotor blade(s) with serial number 6999 and lower. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Lama Service Bulletin No. 01.04 for the Model SA- 315B, or Alouette Service Bulletin No. 01.30 for the other designated models. To prevent failure of the main rotor blades due to corrosion, inspect the blade spar in the section between the attachment fitting and root end rib for corrosion, repair as necessary, and return to service, in accordance with paragraphs 2 B(2), 2 B(3), 2 B(4) and 2 C of SGAC- approved Alouette Service Bulletin No. 01.30, as amended August 30, 1972, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. This amendment becomes effective on January 19, 1976.
71-06-01: 71-06-01 BEECH: Amdt. 39-1170 as amended by Amendment 39-1222 is further amended by Amendment 39-1321. Applies to all 99 series airplanes (Serial Numbers as applicable). Compliance: Required as indicated, unless already accomplished. To preclude the occurrence of faults, failures and improper operation, accomplish the following: A) On all 99 series airplanes (Serial Numbers U-1 through U-95, U-97 through U- 127, U-130 through U-133, U-135 and U-136) within the next 100 hours' time-in-service after the effective date of this AD, modify the flap position selector in accordance with Beechcraft Service Instruction 0328-158 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. B) On all 99 series airplanes (Serial Numbers U-1 through U-133, U-135 and U- 136) within the next 100 hours' time-in-service after the effective date of this AD, modify the landing gear indicator and warning device in accordance with Beechcraft Service Instruction 0313-158 and 0318-350, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. C) On all 99 series airplanes (Serial Numbers U-2 through U-103, U-105 through U- 133, U-135 and U-136) within the next 75 hours' time-in-service after the effective date of this AD, modify the gear selector panel in accordance with Beechcraft Service Instructions 0299-395 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. D) On all 99 series airplanes (Serial Numbers U-1 through U-103 and U-106 through U-135) within the next 75 hours' time-in-service after the effective date of this AD, modify the instrument static air system in accordance with Beechcraft Service Instruction 0291- 394, Rev. 1, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. E) On Models 99 and 99A (Serial Numbers U-1 through U-136) airplanes within the next 100 hours' time-in-service after the effective date of this AD (March 16, 1971), inspect and test the electrical power distribution system in accordance with Beechcraft Service Instructions 0348-351 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. Amendment 39-1170 became effective March 16, 1971. Amendment 39-1222 became effective June 3, 1971. This Amendment 39-1321 becomes effective October 19, 1971.
87-14-02: 87-14-02 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5732. Applies to IO-520, IO-550, and TSIO-520 series engines with starter adapter shaftgear P/N 649343, a freon compressor, and 25 hours or less time in service installed on the following engines: New Engines Serial Numbers IO-520BB S/N 578239 thru 578250, 578255 thru 578261, 578271, 578272 IO-550B S/N 675329, 675330, 675334 thru 675336 TSIO-520UB S/N 527091, 527093 TSIO-520BE S/N 528383, 528389 IO-520BA S/N 249568 thru 249570, 249588 thru 249593 IO-520BB S/N 248585, 248586, 274505 thru 274520, 274522 thru 274526, 274529, 274532, 274536, 274537, 274540, 274544, 274545, 274549, 274550, 274552, 274554 IO-550B S/N 249124 thru 249130, 249132 Rebuilt Engines Serial Numbers TSIO-520UB S/N 248867, 248869 TSIO-520LB S/N 237242, 237244, 237247, 241909, 241910 TSIO-520WB S/N 274004 thru 274008, 274012 thru 274018 TSIO-520BE S/N 273505 thru 273510 Compliance is required before further flight unless already accomplished. To prevent possible starter adapter shaftgear failure, which could result in loss of lubricating oil and subsequent complete loss of engine power, accomplish the following: (a) Determine if the installed engine(s) has a freon compressor installed. (1) If no freon compressor is installed, no further action is required, proceed to paragraph (f). (b) Engines in compliance with priority letter AD 87-12-12, but not included in the engine serial numbers listed in this AD, may reinstall the air conditioner drive belt. Proceed to paragraph (f). (c) Determine the time in service of the starter adapter shaftgear P/N 649343 for each installed engine. If the time in service is greater than 25 hours with the freon compressor drive belt installed, no further action is required. Proceed to paragraph (f). If the time in service is less than 25 hours, accomplish paragraphs (d) or (e) as applicable. (d) If the engine was new when installed, remove the starter adapter assembly P/N 642087, and return to the manufacturer for replacement. Install the replacement assembly, and proceed to paragraph (f). (e) If the installed engine is a rebuilt engine, gain access to the drive sheave mounted on the rear of the starter adapter shaftgear. Determine, using a light and mirror, if the drive sheave attaching nut is castellated. (1) If the nut is castellated with a cotter key installed, no further action is required, proceed to paragraph (f). (2) If a steel lock nut is installed, inspect the center of the shaft to determine if the shaft has drilled cotter key holes (See TCM Service Bulletin M87-13, dated 29 June 1987, Figure 1). (i) If the shaft has drilled holes, no further action is required, proceed to paragraph (f). (ii) If the shaft is undrilled, remove the starter adapter assembly P/N 642087 and return to the manufacturer for replacement. Install the replacement assembly. (f) Make appropriate logbook entry showing compliance with this AD. NOTES: 1. Contact TCM for shipping instructions. 2. When replacing the starter adapter assembly, retain the drive sheave for reinstallation on new assembly. 3. TCM Service Bulletin M87-13, dated 29 June 1987, refers to this subject. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, Central Region, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349. Priority letter AD 87-14-02 superseded priority letter AD 87-12-12. This amendment 39-5732 becomes effective October 5, 1987, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 87-14-02, issued July 8, 1987, which contained this amendment.
2021-07-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200 series airplanes. This AD was prompted by reports indicating that the pitot heat switch is not always set to ON, which could result in misleading air data. This AD requires replacement of pitot anti-icing system components, installation of a junction box and wiring provisions, repetitive testing of the anti- icing system, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
96-12-23: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 150 and A150 series and Models 152 and A152 airplanes that have a Bush Conversions, Inc., Short Takeoff and Landing (STOL) kit incorporated in accordance with Supplemental Type Certificate (STC) SA1371SW. This action requires measuring the wing stall fence for maximum height, and installing a smaller fence if the fence exceeds the maximum height of 1.28 inches. An accident of a Cessna Model 152 airplane where the STOL kit adversely affected the airplane's stall characteristics prompted this action. The actions specified by this AD are intended to prevent the airplane from entering a stall condition because of improper wing stall fence height, which could result in loss of control of the airplane.
96-06-02: This amendment supersedes an existing airworthiness directive (AD), applicable to The Enstrom Helicopter Corporation Model (Enstrom) F-28A, F-28C, 280, and 280C helicopters, that currently requires an initial and repetitive visual inspections of the upper swashplate bearings for corrosion, and replacement of defective upper swashplate bearings with airworthy bearings. This amendment requires that the visual inspections apply to both the upper and lower swashplate bearings (bearings); expands the applicability to include the Model F-28C-2 helicopter; limits the applicability to those affected helicopters manufactured prior to January 1, 1981; establishes a retirement life of 1,200 hours time-in-service for certain bearings; and provides a corrected upper swashplate bearing part number. This amendment is prompted by the necessity to require visual inspections of the lower swashplate bearings; to expand the applicability to include the Model F-28C-2 helicopter; to establish a retirement life for certain bearings; and to correct the upper swashplate bearing part number from the existing AD. The actions specified by this AD are intended to prevent failure of the bearings and subsequent loss of control of the helicopter.
2016-23-05: We are superseding Airworthiness Directive (AD) 2007-25-08 for Eurocopter France (now Airbus Helicopters) Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2007-25-08 required checking the tail rotor gearbox (TGB) oil, inspecting the magnetic plug, and either replacing the TGB or performing additional inspections. This AD was prompted by reports of new occurrences of loss of yaw control due to failure of the control rod bearing. This AD requires checking the TGB oil level and replacing the bearing with a new part-numbered bearing. These actions are intended to detect and prevent damage to the bearing resulting in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter.
2016-23-02: We are superseding Airworthiness Directive (AD) 2006-19-12 for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2006-19-12 required inspecting the lower web of the aft fairing of the engine struts for any discoloration, and doing related investigative and corrective actions if necessary; inspecting the heat shield castings for any damage and doing corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This new AD retains those requirements and also requires, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure, and one-time or repetitive conductivity inspections of the aft fairing lower structure, and related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. We are issuing this AD to address the unsafe condition on these products.
87-15-04: 87-15-04 HARTZELL PROPELLER, INC.: Amendment 39-5667. Applies to Hartzell Model HC-B4MN-5( ) propellers installed on CASA Model C-212-CC and -CF airplanes. Compliance required at next propeller overhaul or within 30 days after the effective date of this AD, whichever occurs sooner, unless already accomplished. To prevent pitch change rod failure which could result in loss of propeller control, accomplish the following: Replace the spring assembly, P/N B-831-54, with spring assembly, P/N B-831-64, which includes a strengthened pitch change rod in accordance with Hartzell Service Bulletin No. 153, dated May 1, 1987. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Chicago Aircraft Certification Office, may adjust the compliance time specified in this AD. Hartzell Service Bulletin No. 153, dated May 1, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive which have not already received this document from the manufacturer may obtain copies upon request to Hartzell Propeller, Inc., 1800 Covington Avenue, Piqua, Ohio 45356. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, Attn: Rules Docket No. 87-ANE-20, 12 New England Executive Park, Burlington, Massachusetts 01803 weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment, 39-5667, becomes effective on July 31, 1987.
2004-11-12: The FAA adopts a new airworthiness directive (AD) for all Alexander Schleicher Model ASW 27 sailplanes equipped with integrated (wet inner surface) water ballast tanks in the wings, which could put the center of gravity (CG) of the sailplane out of the acceptable range. This AD requires you to install a warning placard requiring pilots weighing more than 105 kg (231.5 lbs) to use the rearmost backrest hinge position; and requires you to determine the forward empty CG and make any necessary adjustments. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to correct the CG to the acceptable range when integrated ballast water tanks are installed. Failure of the sailplane to be within the acceptable CG range could result in loss of sailplane control.
88-12-51 R1: 88-12-51 R1 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6076. Final copy of, and revision to, Telegraphic AD 88-12-51 issued June 10, 1988. Applies to Model DHC-8-100 series airplanes, Serial Numbers 1 through 113, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent inadvertent unfeathering of the propeller, accomplish the following: A. Within 24 hours after the effective date of this AD, insert the following note into the Emergency Operating Procedures Section of the Airplane Flight Manual (AFM) [PSM-1-81- 1A(FAA)], and alert all flight crews. This may be accomplished by inserting a copy of this airworthiness directive into the front of the Emergency Operating Procedures Section (Section 4) of the AFM: "NOTE: Should an engine failure or fire after V1 occur: Ensure that the emergency procedures of paragraphs 4.1.2., 4.2.1., and 4.2.2 of PSM 1-81-1A(FAA) are followed. The ENGINE SHUTDOWN check, paragraph 4.2.1., is not to be commenced until entering the third segment of the takeoff path. On commencement of the ENGINE SHUTDOWN or ENGINE FIRE (IN FLIGHT) check, paragraph 4.2.1. or 4.2.2, respectively, the check should be completed sequentially and uninterrupted to its conclusion." B. Installation of the modification to the propellers-autofeather latching logic wiring, in accordance with de Havilland Service Bulletin 8-61-12, Revision A, dated October 28, 1988, constitutes terminating action for the requirements of paragraph A., above, and the required "NOTE" may be removed from the AFM. C. An alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment revises Telegraphic AD T88-12-51, issued June 10, 1988. This amendment, 39-6076 (AD 88-12-51 R1), becomes effective December 12, 1988.
2019-21-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS 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). 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 new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
78-14-02: 78-14-02 AVIONS MARCEL DASSAULT-BREGUET AVIATION (AMD-BA): Amendment 39-3256. Applies to Falcon 10 airplanes serial numbers 1 through 108, except serial numbers 93, 101 and 103, certificated in all categories. Compliance is required within the next 150 hours time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of jamming of the oxygen pressure reducing valve due to water condensation freezing in the valve expansion chamber, modify the oxygen pressure reducing valve installation in accordance with AMD-BA Service Bulletin F10-0135 dated February 11, 1977, including Revision 2, dated January 4, 1978, or a modification approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. NOTE: The oxygen pressure reducing valve is located in the righthand side of the nose landing gear wheel well. This amendment becomes effective July 11, 1978.
76-18-06: 76-18-06 PIPER: Amendment 39-2716. Applies to Model PA-31T, Serial Nos. 31T-7400001 through 31T-7620039 certificated in all categories. To prevent possible hazards in flight associated with cracks in the elevator and elevator tab support structure, accomplish the following within the next fifty hours in service after the effective date of this AD unless previously accomplished. (a) Alter the stabilizer/elevator/elevator tab structure in accordance with Piper Elevator Hinge Modification Kit No. 761 056 or approved equivalent alteration. (b) Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Piper Service Bulletin No. 504 refers to this subject.) This amendment is effective September 10, 1976.
2016-23-07: We are superseding Airworthiness Directive (AD) 2013-02-08 for all Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2013-02-08 required inspection of the trunnions and upper and lower pins of the horizontal stabilizer trim actuator (HSTA), and replacement or re-identification if necessary; and revision of the maintenance program to include safe life limits and inspection requirements for the HSTA. This new AD requires certain actions related to the trunnions and pins for the HSTA, revising the maintenance or inspection program, and removing certain airplanes from the applicability. This AD was prompted by a determination that not all affected attachment pins and trunnions were included in the inspections required by AD 2016-02-08, and that incorrect attachment hardware may have been used in replacements on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
2018-19-33: We are adopting a new airworthiness directive (AD) for all Airbus SAS 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). This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2016-23-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-400 series airplanes. This AD was prompted by reports of cracks in the upper chord of the overwing stub beams at body station (STA) 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord. This AD requires repetitive inspections for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to prevent the unsafe condition on these products.
2016-24-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200 and -300 series airplanes. This AD was prompted by a report of heat damage found on a nacelle firewall after an unsuccessful engine ground start and several events of heat damage found on direct current starter/generator terminal block assemblies. This AD requires an inspection to detect damage on the nacelle firewalls and the terminal block assemblies and to make sure the insulating sleeves are installed and have no damage, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
93-22-03: 93-22-03 FOKKER: Amendment 39-8728. Docket 93-NM-78-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11407, inclusive, 11409, and 11410; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced braking authority and reduced directional control of the airplane while it is on the ground, accomplish the following: (a) Within 30 days after the effective date of this AD, conduct an inspection of the rudder (brake) pedal assemblies, to verify installation of retainer rings, part number (P/N) MS16624-1075, in accordance with Fokker Service Bulletin SBF100-27-047, Revision 1, dated February 9, 1993. (1) If all of the retainer rings are installed correctly, no further action is required by this AD. (2) If any retainer ring is not installed, or is not installed correctly, prior to further flight, install retainer ring, P/N MS16624-1075, in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and necessary installation shall be done in accordance with Fokker Service Bulletin SBF100-27-047, Revision 1, dated February 9, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 February 9, 1993 2-4 Original August 28, 1992 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 16, 1993.
2024-19-11: The FAA is adopting a new airworthiness directive (AD) for all Robinson Helicopter Company Model R44 and R44 II helicopters. This AD was prompted by reports of a fractured clutch shaft forward yoke (yoke) on the main rotor (M/R) drive due to fatigue cracking. This AD requires visually inspecting a certain part-numbered flex plate assembly (flex plate) and certain part-numbered yokes, including each flex plate bolt, and depending on the inspection results, removing an affected part from service and replacing an affected part with an airworthy part. This AD also requires removing a certain part-numbered yoke from service after accumulating a certain number of hours time-in-service (TIS) or a certain number of years, or as an alternative to removing the part from service, performing a 10x or higher power magnification visual inspection and, if needed, a magnetic particle inspection. The FAA is issuing this AD to address the unsafe condition on these products.
2004-11-04: The FAA is adopting a new airworthiness directive (AD) for all Eagle Aircraft (Malaysia) Sdn. Bhd (Eagle Aircraft) Model Eagle 150B airplanes. This AD requires you to inspect certain canard inboard flap hinge support brackets (initially prior to further flight and repetitively before the first flight of each day) and perform any necessary follow-up action. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authorities for Australia and Malaysia. We are issuing this AD to prevent failure of the canard inboard flap hinge support brackets caused by undetected cracks. This failure could result in asymmetric flap deployment and the inability to lower or raise the flaps with consequent loss of control of the airplane.
70-08-02: 70-08-02 BELL: Amendment 39-968 as amended by Amendment 39-1137 Applies to all Bell Model 47 Series Helicopters and all other helicopters incorporating any of the following tail rotor drive shaft assemblies: 47-644-172-3 47-644-180-1 47-644-186-1 47-644-180-5 47-644-187-5 47-644-214-1 47-644-187-11 Compliance required no later than March 1, 1971; however, replacement is recommended at the next 1200-hour overhaul. To prevent failure from internal corrosion, remove and replace all tail rotor drive shaft assemblies installed on applicable helicopters as indicated below in accordance with the applicable maintenance and overhaul manual: Remove Replace With 47-644-172-3 47-644-172-9 47-644-180-1 47-644-180-9 47-644-180-5 47-644-180-11 47-644-214-1 47-644-214-9 47-644-186-1 47-644-186-5 47-644-187-5 47-644-187-17 47-644-187-11 47-644-187-19 (Bell Service Bulletin No. 47-145, Rev. B, dated March 26, 1970, pertains to this matter) Amendment 39-968 effective May 9, 1970. This amendment, 39-1137, becomes effective January 1, 1971.
90-21-20: 90-21-20 AIRBUS INDUSTRIE: Amendment 39-6770. Docket No. 90-NM-91-AD. Applicability: All Model A320-111, A320-211, and A320-231 series airplanes, certificated in any category. Compliance: Required within the next 350 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent the simultaneous activation in flight of two angle of attack sensors and subsequent incorrect pitch-down command to the elevator, accomplish the following: A. Perform one of the following: 1. Disconnect and modify the wiring in the relay box 103VU, in Zone 127, and in Zone 232, in accordance with Airbus Industrie Service Bulletin A320-34-1012, Revision 1, dated April 10, 1990; or Revision 2, dated June 8, 1990; or 2. Accomplish Modification No. 21824P1953, which consists of moving the test control wires of the angle of attack sensors, in accordance with Airbus Industrie Service Bulletin A320-34-1013, dated June 1, 1990. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6770, AD 90-21-20) becomes effective November 19, 1990.
2016-24-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases. This AD requires removing aluminum transmission aft bearing plate assemblies from the flap track and installing titanium transmission aft bearing plate assemblies to the flap track. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 85119))
2024-19-17: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. Model 204B, 205A, 205A-1, 205B, 210, and 212 helicopters and various restricted category helicopters with certain part-numbered tension torsion (TT) straps installed by supplemental type certificate (STC) No. SR03408CH. This AD was prompted by an accident involving failure of a TT strap. This AD requires removing the specified part-numbered TT straps from service and prohibits installing those TT straps. The FAA is issuing this AD to address the unsafe condition on these products.