Results
80-25-01: 80-25-01 HUGHES HELICOPTERS: Amendment 39-3980. Applies to Model 369 Series Helicopters certified in all categories. Compliance is required as indicated unless already accomplished. To prevent possible fatigue failure of the Hughes couplings in the tail rotor drive shaft and loss of tail rotor power, accomplish the following: (a) Within 25 hours' time in service from the effective date of this AD, inspect the fore and aft tail rotor drive shaft couplings to determine the serial numbers of the installed couplings. The serial number is on the Bendix part number decal. (b) For those helicopters with the following couplings installed, prior to further flight, remove couplings from service and label couplings "Unairworthy." Hughes Part No. 369H92564, serial numbers 0883U, 0932U, 0933U, 0935U, 0940U, 0950U, 0957U, 0961U, 0971U; and for Hughes Part No. 369A5501, serial numbers 10670U and 10672U. Replace removed coupling with like serviceable part. (c) Installation of any coupling listed in paragraph (b) will render the helicopter unairworthy. (d) Report the serial number of each suspect coupling listed in paragraph (b) found as a result of the inspection of paragraph (a) to the Chief, Engineering and Manufacturing Branch, FAA, Western Region, P.O. Box 92007, World Way Postal Center, Los Angeles, California 90009. Negative reports are not necessary. Reporting approved by Office of Management and Budget, OMB No. 04/R0174. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective December 4, 1980.
2005-25-22: The FAA adopts a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa "PZL-Bielsko" Model SZD-50-3 "Puchacz" gliders. This AD requires you to perform a visual inspection of the turnbuckle link for cracks or wear and replace if cracks or wear is found. This action only applies to those gliders where the turnbuckle is directly connected to the pedal. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and correct cracks in the turnbuckle link, which could result in failure of the rudder cable. This failure could lead to loss of control of the glider.
2019-12-15: We are adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Leonardo) Model AB139 and AW139 helicopters. This AD requires replacing screws installed on the left and right main landing gear (MLG) shock absorber assembly. This AD was prompted by a report that some screws may have been manufactured without meeting specifications. We are issuing this AD to address the unsafe condition on these products.
2011-18-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been reported during operational checks that some failures of the Escape Slide * * * installed on the forward passenger and service door have occurred which prevented the door from opening. * * * [T]his condition * * * could delay an emergency evacuation and increase the chance of injury to passengers and flight crew * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-25-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-52 that was sent previously to all known U. S. owners and operators of all Boeing Model 747 series airplanes by individual telegrams. This AD requires revising the Airplane Flight Manual to include procedures to prevent dry operation of the center wing fuel tank override/jettison pumps and, for certain airplanes, to prohibit operation of the horizontal stabilizer tank transfer pumps in flight. This action is prompted by a report indicating that several override/jettison fuel pumps from the center wing tanks and main tanks had been removed because circuit breakers for the override/jettison fuel pumps were tripped, or low pump output pressure was indicated. The actions specified by this AD are intended to prevent contact between the rotating paddle wheel and the stationary end plates within the center wing tank override/jettison fuel pumps or horizontal stabilizer tanktransfer pumps due to excessive wear of the pump shaft carbon thrust bearing, which could cause sparks and/or a hot surface condition and consequent ignition of fuel vapor in the center wing tank or horizontal stabilizer tank during dry pump operation (no fuel flowing).
98-09-16: This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to add specific flightcrew instructions to be followed in the event of failure of one or both of the direct current (DC) generators. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the second of two DC generators after the failure of the first generator, which could lead to the loss of main battery power and result in the loss of all electrical power, except the emergency battery supply, during flight.
2009-18-07: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and related investigative/corrective actions if necessary. This new AD requires additional repetitive inspections for cracking of certain fuselage structure, and related investigative/corrective actions if necessary. This AD results from fatigue tests and analysis by Boeing that identified areas of the fuselage where fatigue cracks can occur. We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
98-26-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the doorjamb of the forward service door have been previously modified. The action also requires various repetitive inspections to detect cracks of the fuselage skin and doubler at all corners of the doorjamb of the forward service door, and to detect cracks on the skin adjacent to the modification; and various follow-on actions. This amendment is prompted by reports of fatigue cracks found in the fuselage skin and doubler at the corners of the doorjamb of the forward service door. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
56-19-01: 56-19-01 de HAVILLAND: Applies to All Model 104 "Dove" Aircraft. Compliance required as indicated below. A case has occurred in which the mild steel rivet locking the stud, P/N 4CF.607 to the spindle, P/N 4CF.603ND in the aileron differential pulley assembly has sheared, allowing the spindle to unscrew from the stud to such an extent that it, together with the pulley, was on the point of becoming disengaged from the pulley bracket. To prevent a recurrence of this defect, compliance with Dove Modification No. 765 (installation of a H.T.S. pin for locking stud on aileron differential pulley spindle) is considered mandatory by the British Air Registration Board in which the FAA concurs. Accordingly, unless already accomplished, Modification No. 765 should be embodied on all Dove aircraft as soon as possible, but not later than October 15, 1956. (Dove Modification 765 is covered in de Havilland Service Technical News Sheet CT (104) No. 114 dated November 1, 1954.)This supersedes AD 55-02-01.
98-26-07: This amendment adopts a new airworthiness directive (AD), applicable to Rolls-Royce Limited, Bristol Engines Division,(R-R) Viper Models Mk.521 and Mk.522 turbojet engines, that requires replacement of certain high pressure (HP) fuel pumps with an improved design which is more tolerant of reduced lubricity fuel caused by water contamination. This amendment is prompted by reports of HP fuel pump drive shaft failures resulting in in-flight engine shutdowns. These failures have been attributed to the reduced lubricity properties of fuel which is contaminated by water. The actions specified by this AD are intended to prevent HP fuel pump failures, which can result in an in-flight engine shutdown. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 16, 1999.
2019-11-02: The FAA is superseding Airworthiness Directive (AD) 2017-16- 10, which applied to all The Boeing Company Model 777 airplanes. AD 2017-16-10 required repetitive inspections of the left and right side underwing longerons for any crack, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-16-10, reduces certain compliance times for certain airplanes, and removes airplanes from the applicability. This AD was prompted by reports of cracks on the underwing longerons. The FAA is issuing this AD to address the unsafe condition on these products.
2007-17-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A nose landing gear leg failed in area of the nose gear leg pivot axle. This airplane was mostly operated on grass runways and training operations. This failure was based on a fatigue crack developed in the pivot axle. Material inspections figured out that this cracks may also develop on other serial No. pending the type of operation. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-12-01: The FAA is adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) LEAP-1B21, -1B23, -1B25, -1B27, - 1B28, -1B28B1, -1B28B2, -1B28B3, -1B28B2C, -1B28BBJ1, and -1B28BBJ2 model turbofan engines. This AD requires initial and repetitive inspections of the transfer gearbox (TGB) scavenge screens and, depending on the results of the inspection, possible removal of the engine from service. This AD was prompted by multiple reports of in- flight shutdowns (IFSDs) due to radial drive shaft (RDS) bearing failure. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-31: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires performing a one-time inspection for chafing of certain electrical wire bundles behind the flight engineer's panel in the cockpit; repairing any chafed wire bundles, if necessary; and installing Teflon sleeving over the inspected wire bundles and rerouting them. This action is necessary to prevent burning of electrical wires, which could result in smoke in the cockpit and loss of function of several airplane systems. This action is intended to address the identified unsafe condition.
79-22-05: 79-22-05 LOCKHEED CALIFORNIA: Amendment 39-3602. Applies to Model L- 1011-385 series airplanes certificated in all categories. Compliance required as indicated unless already accomplished. To prevent rapid loss of cabin pressurization in flight, accomplish the following: (a) Within 800 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 800 hours' time in service until modified in accordance with paragraph (b) of this AD, inspect forward and aft outflow valve gates for delamination in accordance with the instructions contained in Lockheed Service Bulletin No. 093-21-157 dated May 1, 1979, Section 2B ("Full inspection of outflow valves"). Gates found defective must be removed and replaced with a part free from bond joint separation prior to further flight. (b) Within 2400 hours' time in service after the effective date of this AD, modify the outflow valve assemblies in accordance with Hamilton Standard Service Bulletin 21-1141 dated March 28, 1979. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes in pressurized flight to a base for the accomplishment of inspections or modifications required by this AD. No special flight permit is required to operate the airplane unpressurized to a base for the accomplishment of inspections or modifications required by this AD. (d) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective December 6, 1979.
85-24-03: 85-24-03 MOONEY AIRCRAFT CORPORATION: Amendment 39-5173. Applies to Models M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, and M22 (all Serial Numbers (S/N)) airplanes certificated in any category. Compliance: Within 100 hours time-in-service after the effective date of this AD or at the next annual inspection, whichever occurs first, unless already accomplished. To preclude fuel contamination and water entrapment in the fuel tanks accomplish the following: (a) For Models M20B, M20C, M20D, M20E, M20F, M20G (all S/N), M20J (S/N 24-0001 through 24-1498), M20K (S/N 25-0001 through 25-0854) and M22 (all S/N) airplanes, visually inspect all fuel tank bays and rib stations in accordance with the instructions contained in Mooney S/B M20-230, dated April 10, 1985. Repair all discrepancies found prior to further flight. (b) For Models M20C (S/N 2623 through 20-1258), M20D (S/N 201 through 260), M20E, M20F, M20G, M20J, M20K and M22 (all S/N) airplanes, visually inspect the fueltank filler cap assemblies in accordance with the instructions contained in Mooney S/B M20-229, dated April 10, 1985. Repair all discrepancies found prior to further flight. (c) For Models M20J (S/N 24-1499 and on) and 20K (S/N 20-0855 and on) airplanes that have had any fuel tank resealed after initial installation at the factory, visually inspect all fuel tank bays and rib stations in accordance with the instructions contained in Mooney S/B M20-230 dated April 10, 1985. Repair all discrepancies found prior to further flight. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration, Southwest Region, Post Office Box 1689, Fort Worth, Texas 76101. All persons affected by this directive may obtain copies of the documents referred to herein upon request toMooney Aircraft Corporation, Post Office Box 72, Kerrville, Texas 78028-0072 or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 6, 1986.
2011-17-16: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a Back-up Control Module (BCM) retrofit campaign * * *, some BCMs have been found with loose gyrometer screws. * * * When the aeroplane is in control back up configuration (considered to be an extremely remote case), an oscillation of the BCM output order may cause degradation of the BCM piloting laws, potentially leading to erratic motion of the rudder and possible subsequent impact on the Dutch Roll, which constitutes an unsafe condition. * * * * * * * * [S]everal Pedal Feel Trim Units (PFTU) have been found with loose or broken screws during the accomplishment of maintenance tasks on A330 fitted with electrical rudder and A340-600. The loose or failed screws could lead to the loss of the coupling between the Rotary Variable Differential Transducer (RVDT) shaft and the PFTU shaft, and consequently to a potential rudder runaway when the BCM is activated. * * * * * The unsafe condition is loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-25-24: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires repetitive detailed inspections of the forward lugs of the power control unit (PCU), yoke assembly, and forward attachment hardware of the left inboard, left outboard, right inboard, and right outboard flaperon PCUs; and other specified/corrective actions if necessary. For certain airplanes, this AD also requires other related concurrent actions. This AD results from reports indicating that operators have found worn, fretted, and fractured bolts that attach the yoke assembly to the flaperon PCU. We are issuing this AD to prevent damage and eventual fracture of the yoke assembly, pin assembly, and attachment bolts that connect the inboard and outboard PCUs to a flaperon, which could lead to the flaperon becoming unrestrained and consequently departing from the airplane. Loss of a flaperon could result in asymmetric lift and reduced roll control ofan airplane. A departing flaperon could also cause damage to the horizontal and vertical stabilizers, which could result in loss of control of the airplane if damage is significant.
98-26-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the end-pieces of the expansion chamber attenuator (ECA) for the standby pump of the Number 2 hydraulic system with new, improved end-pieces. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent leakage of hydraulic fluid from the Number 2 hydraulic system due to failure of the end-pieces of the ECA, which could result in loss of nose wheel steering, flap operation, normal landing gear operation, and reduced redundancy in the brake and flight controls systems.
80-02-17: 80-02-17 CESSNA: Amendment 39-3675. Applies to Model 441 (S/Ns 441-0001 thru 441-0106 and 441-0109 airplanes). COMPLIANCE: Required as indicated unless already accomplished. To preclude accidents resulting from the inability of the airplane to meet flight manual performance data, prior to further flight accomplish either paragraph A) or B) below: A) Install Revision 5 dated March 26, 1979, in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual and operate the airplane in accordance with this revision. (This action was required by AD 79-10-08 on S/Ns 441-0001 through 441-0097 airplanes and incorporated in Airplanes S/Ns 441-0098 through 441-0106 and S/N 441-0109 by the manufacturer.) NOTE: This does not prohibit incorporation of later nonconflicting revisions in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. B) If the engines are equipped with AiResearch P/N 897110-8 fuel control assemblies, modify the airplaneand Pilot's Operating Handbook and FAA Approved Airplane Flight Manual in accordance with the following: 1) Adjust the Engine Fuel Controls and Computers in accordance with Garrett AiResearch Service Bulletin TPE 331-73-0093 and Cessna Customer Care Service Information Letter PJ 80-1. 2) Install a two-sided reversible instrument panel placard in accordance with Cessna Service Kit SK 441-28 and operate the airplane in accordance with this placard. 3) Perform an overspeed governor check in accordance with Cessna Service Kit SK 441-28. 4) Install Revision 8 in the Pilot's Operating Handbook and FAA Approved Flight Manual and operate the airplane in accordance with this revision. C) The airplane may be flown to a location where paragraphs A) or B) can be accomplished, provided it is not operated with aviation gasoline fuel, grades 80/87 or 100LL. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering & ManufacturingDistrict Office No. 43, Federal Aviation Administration, Room 220, Mid-Continent Airport, Wichita, Kansas 67209. Telephone (316) 942-4285. Cessna Propjet Customer Care Service Information Letters PJ 79-8 dated April 2, 1979, and PJ 80-1 dated January 11, 1980, including Garrett AiResearch Service Bulletin TPE 331-73-0093, cover the subject matter of this AD. The AD supersedes AD 79-10-08, Amendment 39-3470 (44 FR 27977). This amendment becomes effective January 29, 1980.
2005-25-26: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400, 747-400D, and 747-400F series airplanes. This AD requires repetitive detailed inspections for damage (degraded finish; missing, lifted, peeling, or blistering paint; or signs of corrosion) of the interior skin in the forward and aft cargo compartments, and corrective actions if necessary. This AD results from reports of skin corrosion on four Boeing Model 747 series airplanes that were delivered between 1995 and 1999. We are issuing this AD to detect and correct corrosion, which can penetrate the thickness of the skin and cause cracking, and result in rapid decompression of the airplane.
2018-26-08: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-214, A320-232, A320-233, A321-211 and A321-231 airplanes. This AD was prompted by an investigation that revealed that the outer cylinder of a certain ram air turbine (RAT) actuator was not properly deburred in accordance with manufacturing specifications. This AD requires a replacement of affected RAT actuators. We are issuing this AD to address the unsafe condition on these products.
98-26-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that currently requires an inspection of the engine fuel shutoff valves (spar valves) to detect leakage of fuel and to ensure that no leakage occurs when the valves are commanded to close. That amendment also requires an alignment procedure of the engine fuel shutoff valves, if necessary. This amendment expands the applicability of the existing AD. This amendment is prompted by additional reports that certain crossfeed valve assemblies and engine shutoff valve assemblies were improperly installed during manufacturing of the airplane. The actions specified in this AD are intended to prevent uncommanded fuel flow from the fuel tanks to the engine nacelle, which could result in reduced airplane fire protection in the event of a leak in the engine fuel line or a fire in the engine nacelle.
86-22-06: 86-22-06 CESSNA: Amendment 39-5453. Applies to Models 208 and 208A (Serial Numbers 20800001 thru 20800105) airplanes certificated in any category. Compliance: Required by December 31, 1986, unless already accomplished. To prevent fuel starvation during takeoff due to improper positioning of the wing fuel tank selectors, accomplish the following: (a) For Models 208 and 208A (Serial Numbers 20800001 through 20800105) airplanes, install the Cessna fuel selector warning system, revise the POH/AFM, and perform all required system checks, as described in Cessna Bulletin CAB86-8 dated October 10, 1986. (b) For Models 208 and 208A (Serial Numbers 20800001 through 20800083) airplanes, modify the low fuel level transmitter supports as described in Cessna Bulletin CAB 86- 26, dated September 5, 1986. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent method of compliance with this AD may be approved by the Manager, Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this AD may obtain copies of the documents referred to herein upon request to Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This action supersedes AD 86-09-08, Amendment 39-5308, published May 12, 1986 (51 FR 17322) and withdraws NPRM Docket Number 86-CE-13-AD published June 5, 1986 (51 FR 20495). This amendment becomes effective on November 7, 1986.
2005-26-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737 airplanes. This AD requires modifying the elevator input torque tube assembly. This AD results from a report of a restriction in the pilot's elevator input control system. A design review performed on the elevator input torque tube assembly in the course of the investigation discovered possible failure modes that could lead to a jam of the elevator control system. We are issuing this AD to prevent loss of elevator control and consequent reduced controllability of the airplane.