Results
2015-26-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a report that, during a production flight test, the ram air turbine (RAT) did not pressurize the green hydraulic system. For certain airplanes, this AD requires identification of the part number, serial number, and standard of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacement of the balance weight screw, modification of the actuator coil spring, modification of the actuator, an inspection of the anti- stall valve for correct installation in the RAT pump housing; and corrective actions if necessary. For certain other airplanes, this AD requires re-identification or replacement of the RAT module. We are issuing this AD to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame- out, could result in the loss of control of the airplane.
88-19-06: 88-19-06 CESSNA: Amendment 39-6014. Applies to Model 208B (Serial Numbers 208B0001 through 208B0106) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after effective date of this AD, unless already accomplished. To prevent possible elevator flutter, accomplish the following: (a) Check both elevators for correct balance in accordance with the procedures given in Cessna Service Bulletin CAB 88-27, dated August 19, 1988. If any elevator is out of balance, prior to further flight rebalance the elevator in accordance with the instructions and the criteria contained in the above Service Bulletin. NOTE: The elevator balance limits currently shown in the Maintenance Manual for the 208 series airplane are not applicable to the 208B. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67208; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Co., Customer Services, P.O. Box 7704, Wichita, Kansas 67277; telephone number (316) 946-7550; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6014, becomes effective on September 30, 1988.
2024-25-11: The FAA is superseding Airworthiness Directive (AD) 2022-19- 02, which applied to certain Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes; and Model A330-841 and A330-941 airplanes. AD 2022-19-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD-2022-19-02, and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
87-11-01 R1: 87-11-01 R1 BELLANCA: Amendment 39-5624 as amended by Amendment 39-5684. Applies to Models 17- 30, 17-30A, 17-31, 17-31A, 17-31TC, and 17-31ATC (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude engine power loss due to either the accumulation of water or other contaminants in the fuel system or due to mismanagement of available fuel resources caused by lack of pilot familiarity with the airplane fuel system design and operating procedures, accomplish the following: (a) For all airplanes, within the next 30 days after the effective date of this AD or at the next annual inspection, whichever occurs later, and thereafter at each annual inspection, inspect the fuel filler caps and fuel filler well (scupper) drains in accordance with the instructions contained in Section II of Bellanca Service Letter No. B-105, dated February 2, 1987. (b) For Bellanca Models and Serials identifiedin Table 1., within the next 30 days after the effective date of this AD, accomplish the following: (1) Install the appropriate AFM revision, as specified in Table 1. (2) Install permanent placards which state the following at the specified airplane locations: (i) For Models 17-30 and 17-30A, on the instrument panel adjacent to the auxiliary fuel pump switch: "USE TO RESTORE FUEL PRESSURE AND RELEASE TO PREVENT ENGINE FLOODING." (ii) On the instrument panel adjacent to the fuel quantity gauges: "FUEL GAUGES READ QUANTITY IN TANK SELECTED, MAIN FUEL TANK GAUGE INOPERATIVE WHEN AUXILIARY TANK SELECTED. FUEL REMAINING IN SELECTED TANK CANNOT BE USED SAFELY IN FLIGHT WHEN GAUGE READS ZERO." (iii) On the console adjacent to the fuel selector valve (on airplanes with a 58 gallon capacity fuel system): "LEFT TANK: 15.5 GALLONS RIGHT TANK: 15.5 GALLONS AUXILIARY TANK: 20 GALLONS USE AUX. TANK IN LEVEL FLIGHT ONLY." (3) Placards specified in (b)(2)(i), (b)(2)(ii), and (b)(2)(iii) may be fabricated and installed using letters with minimum 1/10 inch height. NOTE: The AFM revisions specified above (and associated placards) are available at a nominal cost from Bellanca, Inc., P.O. Box 964, Alexandria, Minnesota 56308; Telephone (612) 762-1501. The placards are revised versions of existing placards. The existing placards may either be removed and discarded or overlaid by the corresponding revised placard. The placard specified in paragraph (2)(iii) deletes information which was contained in the placard being replaced. This information, however, is presented more clearly in the placard of paragraph (2)(ii) which is a new placard for the airplanes to which paragraph (2)(iii) applies. (c) The requirements of paragraph (b) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him, provided the airplanes are not used in air taxi operations. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Ave., Des Plaines, Illinois 60018; Telephone (312) 694-7357. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Bellanca, Inc., P.O. Box 964, Alexandria, Minnesota 56308; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5624 became effective June 22, 1987. This amendment, 39-5684, becomes effective on August 28, 1987. Table 1. Serial Numbers (may be AFMRevision Model prefixed with year of manufacture) to be installed. 17-30 30001 - 30262 Rev. 15, dtd. 2/2/87 -30A 30263 - 30514 (except 30498) Rev. 6, dtd. 2/2/87 -31 32-1 - 32-14 Rev. 2, dtd. 2/2/87 -31A 32-15 - 32-102 Rev. 8, dtd. 2/2/87 -31TC 31001 - 31003 Rev. 2, dtd. 2/2/87 -31ATC 31004 - 31046 Rev. 8, dtd. 2/2/87
87-04-16: 87-04-16 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5539. Applies to Lockheed Model L-1011 series airplanes equipped with carbon fibre cowls, certificated in any category. Compliance is required within 12 months after the effective date of this AD, unless already accomplished. To prevent loss of throttle control caused by an unstowed left rear fan cowl door support on carbon fibre cowls, accomplish the following: A. Modify the fan cowl support strut stowage mechanism in accordance with Rolls- Royce Service Bulletin RB211-71-8220, dated May 23, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes toa base for the accomplishment of the modification 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 Rolls-Royce PLC, P.O. Box 31, Derby DE 2 8BJ, England, Attention: Technical Publications Department. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective March 9, 1987.
75-17-23 R2: 75-17-23 R2 SIAI-MARCHETTI: Amendment 39-2328 as amended by Amendment 39-4612 is further amended by Amendment 39-5139. Applies to Models S205-18F, S205-18R, S205-20F, S205-20R, S205-22R, S208, and S208A airplanes certificated in any category. Compliance is required as indicated. To detect cracks which could result in the possible failure of the landing gear operating mechanism, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect the internal wing rib brackets, P/N's 205-3-033-18 and 205-3-034-18 for cracks in accordance with Instructions Paragraph (a) of SIAI Marchetti Service Bulletin No. 205B37D, dated March 15, 1985, or an FAA-approved equivalent. (b) If cracks are found during an inspection required by Paragraph (a) of this AD that are in excess of 10 mm (0.394 inch) in length, before further flight comply with the following: (1) Replace the affected brackets with new brackets of the same part number. (2) Unless already accomplished replace the associated washers, P/N AN960-516L, with new design countersunk washers, P/N 205-3-053-16, in accordance with Instructions Paragraph (b) of SIAI Marchetti Service Bulletin No. 205B37D, dated March 15, 1985, or an FAA-approved equivalent. (c) Following accomplishment of Paragraph (b) of this AD continue to inspect in accordance with Paragraph (a) of this AD until brackets P/N 205-3-033-18 and 205-3-034-18 are replaced by new brackets P/N 205-3-313-11 and P/N 205-3-313-12 in accordance with Instructions Paragraph (b) of SIAI-Marchetti Service Bulletin S/B No. 205B37D, dated March 15, 1985. Amendment 39-2328 became effective August 20, 1975. Amendment 39-4612 became effective April 14, 1983. This Amendment 39-5139 becomes effective September 27, 1985.
2015-26-03: We are superseding Airworthiness Directive (AD) 2011-07-10 for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. AD 2011-07-10 required revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness; doing detailed visual inspections; removing discrepant material; cleaning the surfaces of the valves, the plug of the sensing port, and the cabin pressure-sensing port plug; securing the insulation; installing a new safety valve, and replacing certain cabin pressure-sensing port plugs. This new AD retains all requirements of AD 2011-07-10, and requires a detailed visual inspection of both safety valves and the surrounding area for foreign material, room temperature vulcanizing (RTV) silicone, contamination, foam on the bulkhead structure, tape or insulation, and loose material; and corrective actions if necessary. This AD was prompted by reports of in-flight loss of cabin pressurization that was attributed to partial blockage ofa safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. We are issuing this AD to detect and correct blockage of a safety valve cabin pressure-sensing port, which could result in loss of cabin pressure.
88-25-03: 88-25-03 BOEING: Amendment 39-6072. Applies to all Model 707-300, -300B, -300C, and -400 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.\n\n\tNOTE: The inspections required by AD 85-12-01 are not changed by this action.\n\n\tTo prevent the separation of the horizontal stabilizer, accomplish the following:\n\n\tA.\tFor airplanes on which the modification required by AD 79-01-06 has not been accomplished: Prior to the accumulation of 8,000 total landings, install structural improvement kits on the horizontal stabilizer outer panels and center section in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988, and Boeing Service Bulletin 3331, Revision 3, dated June 15, 1979.\n\n\tB.\tFor airplanes which have been modified in accordance with Boeing Service Bulletin A3313, Revision 8, or earlier revisions, or Boeing ServiceBulletin 3253, Revision 2, or earlier revisions, in compliance with AD 79-01-06: Within one year after the effective date of this AD, rework the clevis fittings in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, and Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988.\n\n\tC.\tAccomplishment of the modification requirements of this AD, constitutes terminating action for this AD and AD's 77-16-11 and 78-01-04.\n\n\tD.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office.\n\n\tE.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.\n\n\tThis amendment supersedes AD 79-01-06, Amendment 39-3388, effective February 10, 1979.\n\tThis amendment, 39-6072, becomes effective December 30, 1988.
59-25-03: 59-25-03 HILLER: Applies to Hiller UH Series Helicopters As Follows: (a) UH-12 and UH-12A - incorporating both P/N 34126 wobble plate shield and P/N 34158 forged lower cyclic scissors. (b) UH-12B and UH-12C - incorporating the P/N 34158 forged lower cyclic scissors. (c) UH-12D - all Serial Numbers. (d) UH-12E - Serials 942, 954, and 2001 through 2018. Compliance required as indicated. To prevent contact between the lower cyclic scissors and the filister head screws attaching the wobble plate shield, which can result in damage to the lower scissors and subsequent loss of cyclic control, the following inspection and rework are required. (1) Daily inspect the lower cyclic scissors P/N 34158 on all models, or P/N 34141 on Models UH-12D and UH-12E for damage due to striking the wobble plate shield attachment screws. Damaged scissors must be replaced prior to next flight. (2) Not later than January 1, 1960, replace the filister head screws attaching thewobble plate shield with AN 509-8R4 flush head screws in accordance with the procedures in Hiller Service Bulletins No. 87 or No. 2004. (3) Upon accomplished of item (2) the inspections of item (1) may be discontinued.
2024-25-10: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent XWB-97 engines. This AD was prompted by a report of damage to the main fuel hose assembly of the fuel manifold, which resulted an in-flight shut down. This AD requires a one-time set of visual and dimensional inspections of the main fuel hose assembly of the fuel manifold to confirm softness, compliance, and lack of resistance, and for shrinkage, cracks, chafing, dents, kinks, necking, and degradation of the hose braid wire; and, if necessary, replacement of the main fuel hose assembly of the fuel manifold, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2025-03-02: The FAA is adopting a new airworthiness directive (AD) certain Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP, AS-365N2, AS 365 N3, EC 155B, EC155B1, EC225LP, SA-365N, and SA-365N1 helicopters. This AD was prompted by a report of an unintentional activation of the hoist shear-button (shear-button) on the collective pitch handle during a night flight. This AD requires checking the operation of the shear- button safety-cap on each applicable collective pitch handle and prohibits installing certain part-numbered collective pitch handles or collective sticks with those part-numbered collective pitch handles installed unless certain requirements are met. The FAA is issuing this AD to address the unsafe condition on these products.
2015-25-05: We are adopting a new airworthiness directive (AD) for certain [[Page 80237]] Bombardier, Inc. Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by a report of an aft equipment bay fire due to chafing and subsequent arcing of the integrated drive generator (IDG) power cables. Additionally, we have received several reports of broken support brackets of the hydraulic line. This AD requires a one-time inspection of the IDG power cables for chafing, and for any cracked or broken support bracket of the hydraulic line; and corrective actions if necessary. We are issuing this AD to detect and correct broken support brackets of the hydraulic lines, which could result in inadequate clearance between the IDG power cables and hydraulic lines and chafing of the IDG power cables, and consequent high energy arcing and an uncontrolled fire in the aft equipment bay.
2023-09-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, - 253N, -271N, -272N, and -273N airplanes; and Model A321 series airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements installed at certain positions might not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires a one-time detailed inspection of each affected part installed at an affected position and replacement if necessary, and prohibits the installation of affected parts at affected positions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
87-24-09: 87-24-09 BOEING: Amendment 39-5777. Applies to Model 747 and Model 767 series airplanes, specified in Boeing Service Bulletins 747-34A2286 dated April 30, 1987, and 767- 34A0055, Revision 1, dated September 17, 1987, certificated in any category. Compliance required within 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the possibility of misleading localizer deviation indication to the flight crew caused by electromagnetic interference, accomplish the following: \n\n\tA.\tReplace the existing weather radar receiver-transmitters with modified receiver- transmitters in accordance with the appropriate Boeing Service Bulletin 747-34A2286, or 767- 34A0055, both dated April 30, 1987, or later FAA-approved revision. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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 modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective December 29, 1987.
2022-19-02: The FAA is superseding Airworthiness Directive (AD) 2016-10- 08, AD 2017-05-10, and AD 2019-01-05, which applied to certain Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes; and AD 2019-20-13, which applied to certain Airbus SAS Model A330-200, A330- 200 Freighter, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2016-10-08 required determining the flight cycles accumulated on certain trimmable horizontal stabilizer actuators (THSAs), and replacing the THSA if necessary. AD 2017-05-10, AD 2019- 01-05, and AD 2019-20-13 required revising the existing maintenance or inspection program, as applicable. 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 additional new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-25-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of cracks at certain frames of the forward cargo door. This AD requires a detailed inspection for cracking of certain forward cargo doors, and repair if necessary. We are issuing this AD to detect and correct cracking at certain frames, which could result in the loss of structural integrity of the forward cargo door.
85-07-06: 85-07-06 WESTLAND HELICOPTERS LIMITED: Amendment 39-5019. Applies to Westland 30 helicopters certificated in all categories that are equipped with main rotor tie-bar pin Part Number (P/N) WK 3069-0020-101 or WK 3069-0016-101. Compliance is required as indicted, unless already accomplished. To prevent cracking of the main rotor blade sleeve tie-bar pin and possible loss of a main rotor blade, accomplish the following: (a) Within 50 hours time in service after the effective date of this AD or prior to attaining 500 hours total time in service, whichever occurs later, remove tie-bar pins before further flight. (b) An equivalent method of compliance with this AD may be used when approved by the Manager of the Brussels Aircraft Certification Office, Brussels, Belgium. (c) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. Alert Service Bulletin W30-05-A38, Rev. 1 dated February 26, 1985, pertains to this subject. This amendment becomes effective April 9, 1985.
2015-25-07: We are superseding Airworthiness Directive (AD) 2008-09-01 for certain Alpha Aviation Concept Limited Model R2160 airplanes. 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 need to revise the maintenance program to include the revised airworthiness limitations for the internal wing structure and wing attachment inspections. We are issuing this AD to require actions to address the unsafe condition on these products.
56-20-05: 56-20-05 DOUGLAS: Applies to All DC3 Series, DC-4 and C54-DC Series Aircraft Powered With Pratt & Whitney Military R-2000 and Twin Wasp D Series Engines. \n\n\tCompliance required not later than December 1, 1956. \n\n\tTo avoid crankshaft bending failures, the following placard must be placed on the instrument panel in a conspicuous place: "Avoid Continuous Operation of the Engines between 2310 and 2510 r.p.m." The tachometers must be marked with a red radial band in the above range. \n\n\tThis supersedes AD 48-03-01, which applied only to DC-4 airplanes.
2002-18-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France (ECF) Model AS332C, L, and L1 and Model SA330F, G, and J helicopters, that currently requires an inspection to determine the angular play of the tail rotor gearbox (gearbox) at specified intervals. This amendment changes the measurement limits and the load to be applied to a tail rotor blade (blade) when determining the angular play. This amendment is prompted by a review of design data and a determination that the amount of play can be increased with an increase in the amount of applied load during the inspection. The actions specified by this AD are intended to detect excessive angular play and to prevent failure of a gearbox, loss of tail rotor drive, and subsequent loss of control of the helicopter.
85-12-08: 85-12-08 BOEING: Amendment 39-5081. Applies to Boeing Model 757-200 series airplanes, certificated in all categories, listed in Boeing Service Bulletins 757-38-008 dated February 1, 1985, and 757-24-0025 dated May 3, 1985. To prevent the electrical shorting of certain wire bundles due to damaged wire and leaking lavatory waste fluids onto the wire, accomplish the following within the next 50 hours time in service after the effective date of this AD, unless already accomplished: \n\n\tA.\tPerform a visual inspection of the forward lavatory waste drain ducts, to determine if there is any leakage from the duct seals. Repeat the inspection at intervals not to exceed 100 hours time in service. \n\n\tB.\tIf leaks are detected, clean and replace forward lavatory waste drain clamps in accordance with Boeing Service Bulletin 757-38-008, dated February 1, 1985, or later FAA approved revision, and continue to inspect in accordance with paragraph A. at intervals not to exceed 250 hours time inservice. \n\n\tC.\tIncorporation of Boeing Service Bulletin 757-38-008 dated February 1, 1985, or later FAA approved revision, to replace specified narrow clamps with wider clamps on the forward lavatory waste ducts, and incorporation of Boeing Service Bulletin 757-24-0025 dated May 3, 1985, or later FAA approved revision, to replace the damaged wire and to reroute the specified wire bundles from beneath the lavatories, terminates the repetitive inspection requirement of paragraph A., above. \n\n\tD.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.\n \n\tAll persons affected by this proposal who have not already received copies of the service bulletins may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 1900 Pacific Highway South, Seattle, Washington, or 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective June 28, 1985.
73-19-01: 73-19-01 de HAVILLAND: Amendment 39-1709 as amended by Amendment 39-1786. Applies to de Havilland Aircraft of Canada, Ltd., Model DHC-6 aircraft Series 100 and 200, Serial Numbers 6 through 230 inclusive, incorporating propeller autofeather system installed in accordance with de Havilland Modification No. 6/1278 or Supplemental Type Certificate No. SA2608WE and Series 300 Serial Numbers 130, 210, 231 through 290 inclusive (less Serial Numbers 265, 270, 277, 281 and 283). Compliance required within 200 hours after the effective date of this AD unless already accomplished. To prevent inadvertent auto-feathering accomplish the following: 1. (a) Deactivate the auto-feather system by disconnecting the circuit breaker marked "PROP AUTO-FEATHER" in the panel behind the co-pilot's position. (b) Install placard stating "Auto-feather System Deactivated" adjacent to auto-feather select switch. (c) Revise Vmc speed on airspeed limitation placard above pilot's position as follows: Series 100 (Long-Nose) "68 kts. CAS" Series 200 "68 kts. CAS" Series 300 "70 kts. CAS" 2. The accomplishment of de Havilland Modifications Nos. 6/1472 and 6/1459 as applicable or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, nullifies the applicability of this airworthiness directive. (MOT approved Flight Manual Supplements Nos. 13, 14, and 19 pertain to and validate aircraft operations under CAR 3 or SFAR 23.) (Note: Canadian Ministry of Transport Airworthiness Directives CF-73-4 and CA-73-9 cover the same subject.) Amendment 39-1709 was effective September 11, 1973. This Amendment 39-1786 is effective February 18, 1974.
2024-26-06: The FAA is superseding Airworthiness Directive (AD) 2022-16- 06, which applied to certain Airbus SAS Model A330-200, A330-200 Freighter, A330-300, and A330-900 series airplanes; and all Model A340- 200 and A340-300 series airplanes. AD 2022-16-06 required modifying the trimmable horizontal stabilizer actuator (THSA) installation, implementing the electrical load sensing device (ELSD) wiring provisions, and installing and activating the ELSD. This AD was prompted by tests that demonstrated that when the upper secondary load path (SLP) of the THSA is engaged, the THSA might not stall, with consequently no indication of SLP engagement, and by the recent determination that the required actions of AD 2022-16-06 cannot be accomplished on certain airplanes. This AD continues to require the actions in AD 2022-16-06 with revised procedures, and also requires additional actions for certain airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-24-05: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-23-250, PA-24-250, PA-24-260, PA-24-400, PA-30, PA-31, PA-31-300, PA-31P, PA-39, and PA-E23-250 airplanes. This AD was prompted by an accident caused by fuel starvation where the shape of the wing fuel tanks and fuel below a certain level in that tank may have allowed the fuel to move away from the tank outlet during certain maneuvers. This AD requires installing a fuel system management placard on the airplane instrument panel and adding text to the Limitations Section of the pilot's operating handbook (POH)/airplane flight manual (AFM). We are issuing this AD to correct the unsafe condition on these products.
85-11-02 R1: 85-11-02 R1 MCDONNELL DOUGLAS: Amendment 39-5068 as amended by 39-5361. Applies to McDonnell Douglas DC-9-10, -20, -30, -40, -50, -80, and C-9 (Military) series airplanes (Fuselage Numbers 1 through 1242), certificated in any category. \n\n\tTo prevent elevator jamming which could result in loss of adequate aircraft control, accomplish the following within 300 flight hours after the effective date of this AD, unless already accomplished within the last 2500 flight hours. \n\n\tA.\tOpen access doors 3507 and 3608 to gain access to inspection area on lower elevator surface. (See Maintenance Manual, Chapter 6-11-3 for DC-9/C-9 or 6-23-00 for MD-80.) \n\n\tB.\tBack off nut, P/N H20-8 or P/N LH7461T-080D, on rod end assembly, P/N 4918153-1 from its torqued position until three or more threads are exposed. \n\n\tC.\tUsing a properly calibrated torque wrench, check the initial running torque on each nut. The initial running torque must be a minimum of 18 inch-pounds: \n\n\t\t1.\tIf the minimum 18inch-pound initial running torque is met, proceed to paragraph D., below. \n\n\t\t2.\tIf the initial running torque does not meet the 18 inch-pound minimum requirement, the nut must be replaced with a new H-20-8 or P/N LH7461T-080D nut which does meet the minimum 18 inch-pound initial running torque requirement. \n\n\tD.\tAfter satisfying the initial minimum 18 inch-pound running torque requirement, retorque the nut on the rod end assembly to a final torque value of 400, plus or minus 50, inch-pounds. \n\n\tE.\tRepeat the inspection requirements of paragraphs A. through D. of this AD at intervals not exceeding 2500 flight hours or 12 months, whichever occurs first, since last such inspection. \n\n\tF.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tG.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplanes to a base to comply with the requirements of this AD. \n\n\tH.\tModification of elevator hydraulic boost cylinder attach rod ends in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 27-262, dated November 27, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, constitutes terminating action for the repetitive inspection requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-5068 became effective June 10, 1985. \n\n\tThis amendment 39-5361 becomes effective August 21, 1986.