Results
83-10-03: 83-10-03 CESSNA: Amendment 39-4655. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Numbers \n172M\n17266940 thru 17267584\n172N\n17267585 thru 17274009\n172P\n17274010 thru 17275762, 17275764, 17275765, 17275769, 17275770, 17275788, 17275792, 17275793, 17275796, 17275798, 17275800 thru 17275803, 17275806, and 17275818\nR172K\nR1722000 thru R1723454\nF172\nF17201445 thru F17202194\nFR172\nFR17200591 thru FR17200675\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent possible jamming of the elevator control, accomplish the following: \n\n\ta)\tWithin the next 100 hours time-in-service, modify the right-hand control wheel yoke guide in accordance with the instructions in Cessna Single-Engine Customer Care Service Information Letter SE82-38, dated August 13, 1982, and SE82-38 Revision # 1 dated October 29, 1982. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished.c)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendment becomes effective on June 30, 1983.
2005-24-01: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders. This AD requires you to make pen and ink changes to the Limitations Section of the glider maintenance manual to eliminate contradictory information concerning the structural life limit. This AD results from a review by FAA of the Limitations Section of the CENTRAIR Model 101AP glider maintenance manual that revealed conflicting information concerning the structural life limit. We are issuing this AD to assure that the published life limit is adhered to and to prevent structural failure of the glider once this life limit is reached.
2018-23-12: We are adopting a new airworthiness directive (AD) for Zodiac Aero Evacuation Systems (also known as Air Cruisers Company) fusible plugs installed on emergency evacuation equipment for various transport category airplanes. This AD was prompted by reports indicating that affected fusible plugs activated (vented gas) below the rated temperature. This AD requires an inspection of the fusible plugs to determine the part number and lot number, and replacement of all affected fusible plugs. We are issuing this AD to address the unsafe condition on these products.
98-20-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires repetitive inspections to detect cracking of the outer chord of the Body Station (BS) 1480 upper and lower bulkhead and longeron splice fitting, and repair, if necessary. Alternatively, this action requires other repetitive inspections to detect cracking of the BS 1480 upper and lower bulkhead, bulkhead outer chord, web, skin, splice components, and lower bulkhead/stringer interface; and modification of the skin splice plate, the outer chord splice fitting, and the stringer interface of the lower bulkhead, if necessary. This amendment is prompted by a report indicating that fatigue cracking was found in the outer chord of the BS 1480 bulkhead at the overwing longeron splice, and that the longeron splice fitting was completely severed. The actions specified in this AD are intended to detect and correct fatigue cracking of theBS 1480 bulkhead outer chord and longeron splice fitting, which could result in reduced structural integrity of the fuselage and the inability to carry limit load.
89-03-13: 89-03-13 SAAB-SCANIA: Amendment 39-6136. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent erroneous airspeed readings due to ice in the pitot system, accomplish the following: A. Install water traps and insulation pads in the main and standby pitot systems, in accordance with SAAB-Scania Service Bulletin SF340-34-056, dated August 1, 1988. 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 flightpermits 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S-58188, Linkoping, Sweden. 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 (39-6136, AD 89-03-13) becomes effective March 15, 1989.
85-09-04: 85-09-04 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5055. Applies to Model 206L, 206L-1, and 206L-3 helicopters that have main rotor blades, Part Number (P/N) 206-015-001-001 or 206-015-001-103, with inboard trim tabs, P/N 206-015-516-101, installed. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of the main rotor blade, accomplish the following: (a) Remove all main rotor inboard trim tabs, P/N 206-015-516-101, in accordance with Part II, paragraph A of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (b) Accomplish the inspection and repair procedures as necessary in accordance with Part II, paragraphs B & C of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (c) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.0. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspection and repair procedures required by this AD may be accomplished. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. This amendment becomes effective May 20, 1985.
2005-23-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires modification of certain wire bundles located above the center fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent chafed wire bundles near the center fuel tank, which could cause electrical arcing through the tank wall and ignition of fuel vapor in the fuel tank, and result in a fuel tank explosion.
2018-25-15: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the inboard lower flange and adjacent web near the forward attachment of the outboard flap track at a certain position on a Model 737-300 airplane. The flap tracks of Model 737-300 airplanes are similar to the flap tracks of Model 727 airplanes. This AD requires repetitive detailed inspections and surface high frequency eddy current (HFEC) inspections of each outboard flap track at certain positions for any crack and discrepancy, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
98-19-20: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-7B and -7B/2 series turbofan engines. This action requires initial and repetitive inspections of certain hydromechanical unit (HMU) overspeed governor (OSG) spool valves for out-of-specification conditions or the presence of heavy contact or galling on the spool valve, and optional installation of an improved HMU as a terminating action to the inspections. This amendment is prompted by a report of a flameout that occurred on a flight test engine due to a failed HMU OSG spool valve shaft. The actions specified in this AD are intended to prevent failure of the HMU OSG spool valve shaft, and subsequent engine flameout.
80-24-04: 80-24-04 HUGHES HELICOPTERS: Amendment 39-3979. Applies to Model 369 Series Helicopters, certified in all categories, equipped with Automatic Engine Reignition System. Compliance is required as indicated unless already accomplished. To prevent the possibility of the middle front seat occupant accidentally deactivating the Automatic Engine Reignition System and also from blocking the crew's view of the automatic reignition "ARMED" and "RE-IGN" advisory lights, accomplish the following: (a) Within thirty (30) consecutive calendar days or prior to flight in falling and/or blowing snow, whichever comes first, after the effective date of this AD, install a placard in close proximity to the Automatic Engine Reignition Arming switch and in plain view of the pilot which states "Middle front seat is not to be occupied during flight in falling and/or blowing snow" or equivalent words. (b) Special flight permits may be issued in accordance with FAR 21.197 and .199 to operate aircraft to a base for the accomplishment of modification required this AD. (c) 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.
2005-23-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD requires an accelerated schedule of repetitive testing of the elevator servo control loops, and corrective actions if necessary. This AD results from reports of failed elevator servo controls due to broken guides. We are issuing this AD to ensure proper functioning of the elevator servo controls. Failure of the elevator servo controls during certain phases of takeoff could result in an unannounced loss of elevator control and consequent reduced controllability of the airplane.
2018-25-13: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 airplanes. This AD was prompted by a report of chafing of a wire bundle located at the bottom of the right hand (RH) electrical cabinet. This AD requires a one-time general visual inspection of the wiring bundle for damage, measurement of the clearance between the metallic plate and the wiring bundle, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-25-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of inadequate clearance between the thermal protection system (TPS) insulation blankets and the electronic engine control (EEC) wiring, which resulted in damaged wires. This AD requires repetitive inspections of the EEC wire bundles and clips, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
83-19-06: 83-19-06 BOEING: Amendment 39-4736. Applies to Boeing Model 767 series airplanes equipped with Pratt and Whitney JT9D-7R4D engines certificated in all categories. In order to minimize the possibility of engine stall conditions during low power (idle) descent accomplish the following, unless already accomplished: \n\n\tA.\tWithin 30 days after the effective date of this AD, perform the airplane circuit modifications detailed in Boeing Alert Service Bulletin 767-73A7, dated September 2, 1983, or later FAA approved revisions. \n\n\tB.\tWithin 120 days after the effective date of this AD install Package B type hydromechanical fuel controls in accordance with Pratt & Whitney Aircraft Service Bulletin JT9D-7R4-73-4, dated May 3, 1983, or later FAA approved revisions. \n\n\tNOTE: Engine idle speeds associated with these modifications are not intended to replace or eliminate the requirement for proper observance of existing engine anti-ice limitations when operating in icing conditions, including selection of engine anti-ice "ON" and establishment of correct fan speeds prior to entering icing conditions. \n\n\tC.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tAirplanes may be flown in accordance with FAR 21.197 to a maintenance base to accomplish the above. \n\n\tThis amendment becomes effective October 11, 1983.
2005-23-08: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B4-600 and A300 B4-600R series airplanes, and all Model A300 F4-605R airplanes. That AD currently requires repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of fuselage frame FR47. This new AD revises certain inspection thresholds and intervals. This new AD also adds inspections to detect cracks of additional attachment holes. This AD results from reports of cracks found before the inspection thresholds in the existing AD and cracks found in nearby areas not inspected by the existing AD. We are issuing this AD to prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame. DATES: This AD becomes effective December 19, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 19, 2005. On July 8, 2002 (67 FR 38193, June 3, 2002), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-57-6086, dated June 6, 2000.
84-09-01: 84-09-01 BEECH: Amendment 39-4847. Applies to Models and Serial Numbers of 33, 35, 36, 50, 55, 56, 58 (except 58P), 58TC, and 95 series airplanes listed below with seating capacity for more than five occupants. MODELS SERIAL NUMBERS E33, F33, G33 CD-1119 through CD-1304 E33A, F33A CE-180 through CE-918, CE-920 through CE-922, CE-924, CE-926 and CE-928 E33C, F33C CJ-1 through CJ-155 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC, V35B and V35B-TC D-1 through D-10347, D-10349 through D-10352, D-15001 and D-15002 36, A36 E-1 through E-1421, E-1423 through E-1550, E-1552 through E-1568, E-1570 through E-1580, E-1582 through E-1593 A36TC EA-1 through EA-20, EA-22 through EA-27, EA-29 through EA-32 50 H-1 through H-11 B50, C50 CH-12 through CH-360 D50, D50A, D50B, D50C, D50E DH-1 through DH-347 E50 EH-1 through EH-70 F50 FH-71 through FH-93, FH-95 and FH-96 G50 GH-94, GH-97 throughGH-119 H50 HH-120 through HH-149 J50 JH-150 through JH-176 95-55, 95-A55, 95-B55, 95-B55A TC-1 through TC-349, TC-351 through TC-2339, TC-2341 through TC-2354 95-C55, 95-C55A, D55, D55A, E55, E55A TC-350, TE-1 through TE-1151, TE-1153 throughTE-1180 95-B55B (T42A) TF-1 through TF-70 56TC, A56TC TG-2 through TG-94 58, 58A TH-1 through TH-1026, TH-1028 through TH-1061, TH-1063 through TH-1066, TH-1068 through TH-1079 58TC, 58TCA TK-1 through TK-106, TK-109 95, B95, B95A, D95A, E95 TD-2 through TD-721 Compliance: Required as indicated, unless already accomplished. To assure adequate emergency egress provisions, within the next 100 hours time-in- service after the effective date of this AD, accomplish the following: (a) Visually inspect the openable window installation located on the side opposite the entry door to determine: (1) That Beech P/N 96-534051-61 or equivalent release pin has a red handle. (2) That any curtain bars and/or curtains installed are attached to the openable window and not on the window frame so that they will not restrict egress in the event of an emergency. (3) That the tab on the handle assembly does not catch on the back of the hooks on the window. (b) If, as the result of the inspection required by Paragraph a), any deficiencies in the above mentioned requirements are noted, prior to further flight: (1) Paint the handle of the existing release pin red. (2) Either remove the curtains and curtain bars or modify the curtain installation by attaching the bars to the openable window. (3) Trim tab on the back of the handle assembly as required so it doesn't catch on the back of the hooks on the window. (c) Replace existing placard with either Beech placard P/N 58-530258-1 (screwed- on type) or 58-530258-3 (adhesive back) as required which reads as follows: "EMERGENCY EXIT LIFT LATCH-PULL PIN PUSH WINDOW OUT." Locate placard below openable window on the molding. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. This AD supersedes AD 76-04-07, Amendment 39-2525. This amendment becomes effective on May 25, 1984.
2002-16-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 and A310 series airplanes, that requires replacement of certain symbol generator units (SGUs) in the electronic flight instrument system with new, improved SGUs, and modification of associated equipment and wiring. This action is necessary to ensure that the flightcrew has adequate flight information by preventing temporary loss of data from the primary flight and navigation displays. Inadequate flight information could result in reduced situational awareness for the flightcrew, which could contribute to loss of control or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
2018-25-06: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-223F and Model A330-243F airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both left- hand (LH) and right-hand (RH) sides, and applicable related investigative and corrective actions. We are issuing this AD to address the unsafe condition on these products.
2018-25-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that, for multimaterial (hybrid) joints of the passenger door frame fittings, the interfay sealant was not applied between all surfaces of the joint parts. This AD requires modification of the hybrid joints of the passenger doors by applying additional corrosion protection to the hybrid joints of the passenger door frame fittings. We are issuing this AD to address the unsafe condition on these products.
78-25-07: 78-25-07 CESSNA: Amendment 39-3371. Applies to Models A150M (Serial Numbers A1500654 through A1500734) and A152 (Serial Numbers A1520735 through A1520833) airplanes. COMPLIANCE: Required as indicated, unless already accomplished. To assure necessary structural integrity of the vertical fin attachment to the airplane, in accordance with the instructions contained in Cessna Single Engine Service Letter SE78-62, dated October 13, 1978, or later revisions, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) Replace the two existing Part Number 0431009-3 vertical fin attach brackets with two new Part Number 0431009-3 attach brackets obtained from Cessna. B) Return the two brackets removed from each airplane to the Cessna factory for metallurgical examination. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective December 22, 1978.
2018-25-03: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that debris from the parking brake shut off valve (PBSOV) could create a partial blockage of the restrictor check valve in the hydraulic return line of the PBSOV. This AD requires replacing the restrictor check valve with an improved valve that has a filter screen. We are issuing this AD to address the unsafe condition on these products.
83-09-01: 83-09-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4644. Applies to Model N24A Nomad airplanes (all serial numbers) certificated in any category. Compliance: Required within the next 50-hours time-in-service, unless already accomplished. To ensure Aircraft Flight Manual (AFM) one engine inoperative climb performance is achieved, accomplish the following: (a) Fabricate and install a placard on the instrument panel in plain view which reads as follows: "REDUCE WEIGHT OBTAINED FROM WEIGHT/ALTITUDE/TEMPERATURE CHARTS BY 200 LBS and operate the airplane in accordance with this placard. (b) The placard required by paragraph (a) may be installed by the pilot. NOTE: A maintenance record entry as prescribed by FAR 91.173 is required when complying with this AD. (c) The placard required by paragraph (a) may be removed when DOA AFM General Amendment G8 dated March 17, 1983, has been incorporated in the AFM. (d) An equivalent means of compliance with thisAD may be used if approved by the Manager, Honolulu Aircraft Certification Field Office, Room 7108, Prince Kuhio Federal Building, 300 Ala Moana Boulevard, Honolulu, Hawaii 96850. This amendment becomes effective on May 16, 1983.
98-20-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This amendment requires a one-time inspection for different data on the label of certain hose assemblies, and replacement of all hose assemblies from any discrepant batch with certain new hose assemblies. This action also adds airplanes to the applicability of the existing AD. This amendment is prompted by a report of the failure of a hose assembly in the fire extinguisher system of the engine nacelle due to cracks, caused during manufacture of the hose assemblies, in the swaged ferrule that attaches the hose to the end fitting. The actions specified by this AD are intended to prevent failure of hose assemblies, which could prevent theproper distribution of fire extinguishing agent within the engine nacelle in the event of a fire.
98-19-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that requires modifying the sliding surface of the door 1 left and door 1 right evacuation slide/rafts. This amendment is prompted by a report of injuries to evacuees using the slide/raft to exit the airplane; the evacuees were unable to achieve adequate initial sliding speed and adequate momentum to carry them expeditiously down the slide/raft. The actions specified by this AD are intended to prevent evacuee overload of the slide/rafts, and consequent impeded evacuation and injury to the evacuees.
2002-16-17: This amendment adopts a new airworthiness directive (AD) that applies to certain Barry Aviation, LLC Model PZL-Krosno KR-03A "Peregrine" (Puchatek) sailplanes. This AD requires you to inspect to ensure that the correct horizontal stabilizer attachment fittings are installed, install the correct fittings if necessary, and incorporate a "NO LIFT" placard to the vertical stabilizer. This AD is the result of reports of cracks in the horizontal stabilizer attachment fittings on the affected sailplanes. Analysis of these incidents reveals that incorrect fittings were installed. The actions specified by this AD are intended to prevent such cracks in the horizontal stabilizer attachment fittings, which could result in the horizontal stabilizer separating from the sailplane with consequent loss of control of the sailplane.