Results
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.
75-25-03: 75-25-03 PIPER AIRCRAFT CORPORATION: Amendment 39-2448. Applies to PA- 34-200T airplanes, serial numbers 34-7570001 through 34-7670077 certificated in all categories. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent loss of engine oil, accomplish the following: Replace the existing engine oil pressure hose assemblies with a tube assembly and a new hose assembly in accordance with Piper Service Bulletin Number 483 or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective December 10, 1975.
2016-22-04: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GV and GV-SP airplanes. This AD was prompted by a new revision to the Airworthiness Limitations Section (ALS) of the Aircraft Maintenance Manual (AMM) based on fatigue and damage tolerance testing, and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of PSEs is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components.
92-10-01: 92-10-01 BOEING: Amendment 39-8234. Docket No. 91-NM-240-AD. Supersedes AD 91-15-13, Amendment 39-7077.\n\n\tApplicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-27-0104, Revision 2, dated September 12, 1991; certificated in any category.\n\n\tCompliance: Required as indicated, unless previously accomplished.\n\n\tTo prevent the overwing escape slide from being damaged by sharp edges of the rub strip on the inboard spoilers, accomplish the following:\n\n\t(a)\tExcept as provided by paragraph (b) of this AD, within the next 9 months after August 29, 1991 (the effective date of amendment 39-7077), modify the inboard edges of the rub strip on the inboard spoilers in accordance with Boeing Service Bulletin 767-27-0104, dated November 15, 1990, or Revision 1, dated May 30, 1991.\n\n\t(b)\tFor airplanes equipped with inboard spoiler assemblies, part numbers 113T4100-37, -38, -41, -42, -45, and -46: Within the next 9 months after the effective date of this AD, modify the inboard edges of the rub strip on the inboard spoilers in accordance with Boeing Service Bulletin 767-27-0104, Revision 2, dated September 12, 1991.\n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO.\n\n\t(d)\tSpecial 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.\n\n\t(e)\tThe modification shall be done in accordance with Boeing Service Bulletin 767-27-0104, dated November 15, 1990; or Revision 1, dated May 30, 1991; or Revision 2, dated September 12, 1991; as applicable. This incorporation by reference was approved by theDirector of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. (The incorporation by reference of Boeing Service Bulletin 767-27-0104, dated November 15, 1990, and Revision 1, dated May 30, 1991, was previously approved by the Director of the Federal Register as of August 29, 1991 (56 FR 34019, July 25, 1991).) Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.\n\n\t(f)\tThis amendment becomes effective on June 11, 1992.
2022-13-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report of inadvertent auto flight system (AFS) altitude changes on the flight control unit (FCU). This AD requires revising the existing airplane flight manual (AFM) to include a procedure on the use of the AFS control panel ALT knob and replacing any affected FCU with a serviceable FCU, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-15: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with certain configurations of Garmin G3X Touch Electronic Flight Instrument System installed per Supplemental Type Certificate (STC) No. SA01899WI or Garmin GI 275 Multi-Function Display (MFD) installed per STC No. SA02658SE. This AD was prompted by a report of a fuel quantity disparity between the amount of fuel indicated and the actual amount of fuel. This AD requires modifying the resistive fuel probe interface. The FAA is issuing this AD to address the unsafe condition on these products.
75-01-02: 75-01-02 PIPER: Amendment 39-2058. Applies to Piper PA-36-285 airplanes serial numbers 36-7360001 through 36-7460026 and 36-7460034 certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible undesirable elevator control forces accomplish the following: Install Piper Flap Travel Modification Kit No. 760-903V in accordance with Piper Service Bulletin No. 439 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective January 6, 1975.
2004-10-13: This amendment adopts a new airworthiness directive (AD), that applies to CFM International, S.A., CFM56-2-C, -3 series, and -5 series turbofan engines. This amendment requires removing from service main fuel pumps with bronze gear-stage bearings and installing main fuel pumps with bi-metal, aluminum/bronze bearings. This amendment results from several reports of main fuel pump bronze bearing failures. We are issuing this AD to prevent main fuel pump bearing failures resulting in fuel nozzle clogging, low pressure turbine (LPT) case burn-through, and damage to the airplane.
2016-21-08: We are superseding Airworthiness Directive (AD) 2013-25-08 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2013-25-08 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installation of new lock wire, and corrective actions if needed. This new AD removes airplanes from the applicability, and requires modifying the green, blue, and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which terminates the repetitive inspections required by this AD. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to address the unsafe condition on these products.
2016-22-17: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that the grounding jumpers between the environmental control system (ECS) bracket and the current return network (CRN) straps near certain passenger entry doors were not bonded correctly during manufacturing. This AD requires changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
89-19-05: 89-19-05 CASA: Amendment 39-6320. (Docket No. 89-NM-29-AD) Applicability: All Model C-212 series airplanes, certificated in any category. Compliance: Required within the next 180 days after the effective date of this AD, unless previously accomplished. To prevent hindered egress of passengers in the event of an emergency evacuation, accomplish the following: A. Remove the right rear passenger seats adjacent to the emergency exit or modify the seat installation so that the projected opening of the exit is not obstructed by any part of the seat, including the seat back or armrests, in any position, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. B. Ensure that the left forward seat is installed in a position that provides clearance from the intersection of the plane of the seat cushion and the front of the seat back to hard structure, such as the bulkhead, of 35 inches or greater. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. 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 the requirements of this AD. This amendment (39-6320, AD 89-19-05) becomes effective on October 14, 1989.
87-20-04: 87-20-04 CESSNA: Amendment 39-5733. Applies to Model 185, 185A, 185B, 185C, 185D, 185E, A185E and A185F (Serial Numbers 185-0001 thru 18503153) airplanes certificated in any category. Compliance: Within the next 50 hours of operation or before completion of the next annual inspection, whichever comes first, after the effective date of this AD, unless already accomplished per AD 84-10-01. To prevent power loss or engine stoppage due to water contamination of the fuel system, accomplish the following: (a) Modify the aircraft fuel system using one of the options on the following subparagraphs (a)(1), (a)(2), or (a)(3). (1) Install fuel reservoir (accumulator) quick drains in accordance with STC SA2272CE. This STC is owned by Mike Kelley Aircraft Inc., P.O. Box 541, Wellington, Kansas 67152, telephone (316) 326-8581. This STC is applicable to Cessna 185 and 185A thru 185E, A185E and A185F Serial Numbers 185-0001 thru 18503153. (2) Install fuel reservoir (accumulator) quick drains in accordance with STC SA2245CE. This STC is owned by Safe Air Repair, Inc., 3325 Bridge Avenue, Albert Lea, Minnesota 56007, telephone (507) 373-5408. This STC is applicable to Cessna 185A thru 185E, A185E and A185F, Serial Numbers 185-0414 thru 18503153. (3) Install quick drains in the fuel reservoir (accumulator) outlet line by using equivalent aircraft standard hardware. NOTE: A one-time inspection of the Cessna fuel line Part Number 0500106-329 which is used on Serial Number 185-0001 thru 185-0413 should be performed during installation of the fuel reservoir quick drains. This fuel line requires careful attention to routing in order to insure adequate clearance from moving control components located immediately adjacent to this fuel line. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished if it is determined that no water is present in the fuel reservoir (accumulator) or any other part of the fuel system from which fuel will be used. (c) An equivalent means of compliance with this AD may be used, if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this AD may obtain copies of the document(s) referred to herein upon request to FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 30, 1987.
89-19-02: 89-19-02 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6314. Applicability: Model DHC-8-100 series airplanes, and Model DHC-8-300 series airplanes, serial numbers 001 through 149, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure that the engine fire extinguishing system bottle squibs are connected to the proper actuating switch, accomplish the following: A. Within the next 70 hours time-in-service after the effective date of this AD, perform an inspection to verify proper installation of the fire bottle squib wiring in the engine fire extinguishing system, in accordance with the Accomplishment Instructions of de Havilland Alert Service Bulletin A8-26-8, dated March 20, 1989. If the connector identification sleeves are difficult to read or are damaged, or if it has not been confirmed that the installation is correct, prior to further flight, correct the wiring installation and verify properwiring in accordance with the service bulletin. NOTE: Airplanes on which this inspection and/or repair has previously been performed, as required by paragraphs A. and B. of Telegraphic AD T89-05-51, in accordance with Items 1 through 26 of de Havilland Alert Service Bulletin A8-26-7, dated February 24, 1989, are considered to have complied with the requirements of this paragraph. B. Within the next 120 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, install de Havilland Modification Number 8/1336, "Fire Protection - Fire Extinguisher Squib Electrical Connector Positioning," in accordance with the Accomplishment Instructions of de Havilland Service Bulletin 8-26-9, dated March 23, 1989. C. 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, New York Aircraft Certification Office, FAA, Engine and Propeller Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office. D. 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 information from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garatt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the New York Aircraft Certification Office, Engine and Propeller Directorate, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6314) supersedes Telegraphic AD T89-05-51, issued February 28, 1989. This amendment (39-6314, AD 89-19-02) becomes effective on September 19, 1989.
90-25-15: 90-25-15 FOKKER: Amendment 39-6826. Docket No. 90-NM-247-AD. Applicability: All Model F-28 Mark 0100 series airplanes, equipped with main wheel assemblies Part Nos. 5008131-2 and 5008131-3, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent wheel failure, reduced steering capability, loss of braking performance, structural damage and possible injury to people, accomplish the following: A. Within 6 days after the effective date of this AD, and thereafter prior to each flight, perform a visual inspection of the main landing gear (MLG) wheel assemblies for missing or cracked tie bolts. If any bolt is broken or missing, prior to further flight, replace the wheel with a serviceable wheel. B. Upon removal of any wheel in accordance with paragraph A. of this AD or for a tire change, accomplish the following: 1. After thorough cleaning, perform a magnetic particle inspection of all main wheel tie bolts for cracks. a. If a bolt is cracked, prior to further flight replace the cracked bolt. b. If a bolt is broken or missing, prior to further flight, replace the bolt and the two adjacent bolts (one on each side). c. If more than one bolt is broken or missing, prior to further flight, replace all bolts. 2. Inspect all bolts and nuts for crossed threads, and the self-locking feature for a minimum torque of 18 inch-pounds (2.0 Nm). If defective parts are found, prior to further flight, replace all defective parts. C. Within 60 days after the effective date of this AD, replace the MLG wheel assemblies, having Part Nos. 5008131-2 or 5008131-3, with modified wheel assemblies, Part Number 5008131-4, in accordance with Fokker Service Bulletin F100-32-044, dated October 24, 1990. Installation of the modified wheel assemblies constitutes terminating action for the repetitive inspections required by paragraphs A. and B. of this AD. NOTE: The Fokker servicebulletin references Aircraft Braking System Corporation Service Bulletin Fo-100-32-24, dated June 30, 1990, for additional instructions. D. 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. E. 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 information from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314 or Aircraft Braking Systems Corporation, 1204 Massillon Road, Akron, Ohio 44306-4186. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6826, AD 90-25-15) becomes effective on December 24, 1990.
2016-23-04: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires replacement of any affected carburetor float with a float that is eligible for installation. This AD was prompted by a report of a quality escape in the manufacturing of the affected floats. We are issuing this AD to prevent failure of the carburetor float, failure of the engine, in-flight shutdown, and loss of the airplane.
88-15-07: 88-15-07 BRITISH AEROSPACE: Amendment 39-5981. Applies to all British Aerospace (BAe) Model 146 series airplanes as listed in BAe 146 Service Bulletin 32-73, dated March 13, 1987, certificated in all categories. Compliance required as indicated, unless previously accomplished. To prevent collapse of the main landing gear (MLG) due to defective main fittings, accomplish the following: A. Prior to the accumulation of 12,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect the main fitting and barrel section of the main fitting in accordance with British Aerospace BAe 146 Service Bulletin 32-73, dated March 13, 1987. If defective parts are identified during the inspection, repair, prior to further flight, in accordance with Dowty Rotol Service Bulletin number 146-32-23. NOTE: British Aerospace BAe Service Bulletin 32-73 references Dowty Rotol Service Bulletin 146-32-23 for specific procedures for identification, inspection, and repair of the affected MLG parts. The modification of MLG fittings in accordance with Dowty Rotol Service Bulletin 146-32-56 (as recommended in Dowty Rotol Service Bulletin 146-32-23) is not made mandatory by this airworthiness directive. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it 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 for the accomplishment of the modifications required by 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 British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5981, becomes effective August 22, 1988.